MK XXII Enhanced Ground Proximity Warning System (TSO C194 HTAWS) for Rotorwing Aircraft

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1 Airlines & Avionics Products Honeywell International, Inc N.E. 36th Street Redmond, WA PRODUCTION - Release - 01 Mar :20:14 MST - Printed on 19 Apr 2012 MK XXII Enhanced Ground Proximity Warning System (TSO C194 HTAWS) for Rotorwing Aircraft Installation Manual Rev E Part Numbers: CAGE CODE: SCALE: NONE SIZE: A DWG NO: REV: E SHEET 1 OF 324

2 This document is an unpublished work. Copyright , 2009, 2010, 2012 Honeywell, International, Inc. All rights reserved. This document and all information and expression contained herein are the property of Honeywell International Inc., and is provided to the recipient in confidence on a need to know basis. Your use of this document is strictly limited to a legitimate business purpose requiring the information contained therein. Your use of this document constitutes acceptance of these terms. CAGE CODE: SCALE: NONE SIZE: A DWG NO: REV: E SHEET 2

3 Typed names constitute approval signatures. Actual signatures are on file at Honeywell in Redmond, WA. DRAWN Larry Matter 12/01/2003 CHECK Larry Matter 12/01/2003 ENGR Jim Mulkins 12/01/2003 MFG QA APVD Noel Paterson 12/01/2003 APVD REVISION STATUS OF SHEETS INDEX ADDED SHEETS ADDED SHEETS SHEET REV SHEET REV SHEET REV SHEET REV SHEET REV SHEET REV NUMBER LTR NUMBER LTR NUMBER LTR NUMBER LTR NUMBER LTR NUMBER LTR ALL E REVISIONS SH REV DESCRIPTION DATE APPROVED ALL A Updated for 021 and 022 software. Reason: 01 Severity: 10 ALL B Updated for -024 and -026 software. Reason: 01 Severity: 10 12/05/2004 Larry Matter Jim Mulkins 06/30/2008 Larry Matter N. Paterson ALL C UPDATE PER ECO Updated to add TSO-C194 effectivity. 07/20/2009 Larry Matter G. Ostrom Reason: 01 Severity: 10 ALL D UPDATE PER ECO Updated to add new aircraft and display type. Also revised table in 08/13/2010 Larry Matter G. Ostrom CAT 17 and CAT 18, and updated miscellaneous information. L. Ngo EFF PT: 14A ALL E UPDATE PER ECO Updated to add new aircraft, Navigation type and CAT 19, updated miscellaneous information. EFF PT: 14A 2/29/2012 Larry Matter G. Ostrom B. Friedrich CAGE CODE: SCALE: NONE SIZE: A DWG NO: REV: E SHEET 3

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5 TABLE OF CONTENTS SECTION I GENERAL INFORMATION INTRODUCTION APPLICABILITY HOW TO USE THIS DOCUMENT REFERENCE DOCUMENTS DESCRIPTION OF EQUIPMENT MK XXII EGPWS Computer MK XXII EGPWS Configuration Module GPS Antenna OAT Sensor Smart Cable (PCMCIA Interface) TECHNICAL CHARACTERISTICS UNITS SUPPLIED MK XXII EGPWS Configuration Module Smart Cable (PCMCIA Interface) INSTALLATION AND ACCESSORIES KITS MK XXII EGPWS Installation Kits RS-232 Cable Smart Cable Terrain base Cards Flight History Card ACCESSORIES REQUIRED BUT NOT SUPPLIED ARINC 453 Terrain Display wiring GPS Antenna & cable Circuit Breaker Annunciators & Switch/Annunciators GPWS Warning (red) P/TEST; switch/annunciator assembly GPWS Caution (amber) G/S CANCLD switch/annunciator assembly LOW ALT / ON switch/annunciator assembly TERR INHIB / ON switch/annunciator assembly AUDIO INHIBIT / ON switch/annunciator assembly GPWS INOP / TERR INOP annunciator assemblies TERR DISPLAY / ON switch/annunciator assemblies COCKPIT SPEAKER (OPTIONAL) TEMPERATURE PROBES TOOLS REQUIRED Crimping Tool - P1, P2, P Contact Positioner - P1, P2, P CAGE CODE: SCALE: NONE SIZE: A DWG NO: REV: E SHEET 5

6 Insertion/Removal Tool - P1, P2, P Spare Contacts - P1, P2, P LICENSE REQUIREMENTS TSO-C194 DEVIATIONS Environmental Qualification Deviation Electronic Hardware Qualification Deviation LIMITATIONS a. Operating instructions and equipment limitations b. Installation procedures and limitations c. Schematic drawings of the installation procedures d. Wiring diagrams of the installation procedures e. List of components f. Component Maintenance Manual (CMM) g. Material and process specifications list h. Quality control system (QCS) description i. Manufacturer s TSO Qualification test report j. Nameplate drawing k. List of all drawings and processes l. Environmental qualifications form m. Plan for software aspects of certification (PSAC), software configuration index, and software accomplishment summary (SAS) n. Plan for hardware aspects of certification (PHAC), hardware verification plan, top-level drawing, and hardware accomplishment summary NON TSO FUNCTIONS Helicopter Mode Helicopter Mode Helicopter Mode Helicopter Mode Helicopter Mode 4C Helicopter Altitude Callouts Bank Angle Callout Tail Strike Callout Externally Triggered Annunciation Radio Altimeter Test SECTION II - INSTALLATION INTRODUCTION UNPACKING AND INSPECTING THE EQUIPMENT EQUIPMENT INSTALLATION General MK XXII Computer Location MK XXII Computer Installation Configuration Module Location CAGE CODE: SCALE: NONE SIZE: A DWG NO: REV: E SHEET 6

7 2.3.5 Configuration Module Installation GPS Antenna location GPS Antenna Installation OAT Sensor Location OAT Sensor Installation Cockpit Annunciators / Switches Description Location Inhibit Switch Functions and Selection SECTION III SYSTEM PLANNING INTRODUCTION SYSTEM WIRING/ ELECTRICAL INTERFACES Primary Power Input Chassis Ground GPS Antenna Analog and Digital Inputs Discrete Inputs Serial Outputs Audio Output Discrete Outputs Configuration Module CONFIGURABLE INTERFACES Category 1 - Aircraft / Mode Type Select Aircraft / Mode Type Instructions Category 2 Air Input Select Instructions Analog altitude and 500 ohm OAT Digital ARINC 429 (Cat. 2 ID 5, 1, 6) Digital ARINC 575 (Cat. 2 ID 2) Shadin 2000 (Cat. 2 ID 10) Digital ARINC 429 Dual IOC Buses (Cat. 2. ID 253 and 254) Category 3 Position Input Select Instructions ARINC 743 Format GPS Altitude (Label 076) Reference North-South East-West Velocity labels HT- GPS Compatibility ARINC 429 BUS (Cat. 3 ID 0,1,4,5,10-13) RS-232 Transmit-Receive, 9600 baud (Cat. 3 ID 3) Dual ARINC 429 BUS (Cat. 3 ID 253 and 255) Category 4 Altitude Callouts CAGE CODE: SCALE: NONE SIZE: A DWG NO: REV: E SHEET 7

8 Instructions Category 5 Audio Menu Select Instructions Category 6 Terrain Display Select Instructions TAD Selection Terrain Display Configuration Group Display Input Control Group Output 429 Bus Group Sample Display Schematics Category 7 Options Select Group # Instructions Steep Approach (Not Available in the Mk XXII) TA&D Alternate Pop-up Peaks Mode Obstacle Awareness Bank Angle Callout Enabling WOW Reversal GPS Altitude Reference Category 8 Radio Altitude Input Select Instructions Digital Radio Altitude Interface (Cat. 8 ID 2) Analog Radio Altitude Interface (Cat. 8 ID 0,1,3,4,5) Digital ARINC 429 Dual IOC Buses (Cat. 8 ID ) Category 9 Navigation Inputs Select Instructions Analog Glideslope Interface (Cat. 9 ID 0,1,5) Digital Glideslope/Localizer Interface (Cat. 9 ID 2,3,4) Digital ARINC 429 Dual IOC buses (Cat. 9 ID ) Category 10 Attitude Input Select Attitude Signals Instructions Analog Roll Angle (Synchro) (Cat. 10 ID 0,2,4,7) Digital ARINC 429 High Speed (Cat. 10 ID 6) Digital ARINC 429 Dual IOC buses (Cat. 10 ID 128, 253, 254) Category 11 Heading Input Select Instructions Magnetic Heading Analog Heading (Synchro) (CAT. 11 ID 0) Digital ARINC 429 High Speed Digital ARINC 429 Dual IOC buses (Cat. 10 ID 254 & 255) Category 12 Windshear Input Select Instruction CAGE CODE: SCALE: NONE SIZE: A DWG NO: REV: E SHEET 8

9 Category 13 Input / Output Discrete Type Select Instruction Input/Output Discretes Audio Inhibit Discrete Landing Gear Discrete Weight ON Wheels (WOW) Discrete Glideslope Cancel Discrete Mode 6 Low Volume Discrete Minimums/Check Height Silence Discrete Terrain Awareness Inhibit Self Test Discrete Glideslope Inhibit Discrete Timed Audio Inhibit Discrete Low Altitude Mode Select Discrete ICS Audio On Discrete Output Discretes Lamp Format GPWS INOP Discrete TAD INOP Discrete GPWS Warning Discrete GPWS Alert Discrete Glideslope Cancel Discrete TCAS Inhibit Discrete Terrain Display Select #1 & #2 Discrete Timed Audio Inhibit Discrete Low Altitude Mode Discrete Category 14 Audio Output Level Instructions Category 15, Autorotation Threshold Instruction Category 16, Torque Input Select Instructions Category 17 Options Select Group # Instructions Helo Normal Pop-Up Helo Low Altitude Pop-Up Autorotation Callout Option Select Mode 6B Always ON Enable Normal Terrain Airspeed Select Low Altitude Airspeed Select Low Altitude No VFOM Select Category 18 Options Select Group # Instructions CAGE CODE: SCALE: NONE SIZE: A DWG NO: REV: E SHEET 9

10 Audio Inhibit Time Inhibit All Except Minimum Type Callout and 100 Ft Callout Select Inhibit All Except Minimum Type Callout Select Inhibit Includes Too Low Gear Select Inhibit Altitude Callouts 50 ft and Below Over Runway Select Lower MDA/DH Value Select Category 19 Options Select Group # Instructions Low Altitude Mode Mode 2 Terrain Inhibit SECTION IV CONFIGURATION MODULE PROGRAMMING AND TERRAIN DATABASE LOADING INTRODUCTION HARNESS CHECKOUT AND POWER CHECK UNIT INSTALLATION EGPWC INITIALIZATION AND CONFIGURATION RS-232 Communication with the MK XXII EGPWS EGPWC Front Panel Test Connector WinVIEWS WinVIEWS Operation CONFIGURATION MODULE PROGRAMMING CUW and CMR Commands Configuration Module Reprogramming Configuration Module RTC Update REGIONAL TERRAIN DATABASE LOADING Effectivity Description Approval Material Cost and Availability Accomplishment Instructions Verification of the Terrain base Version SECTION V CERTIFICATION INTRODUCTION CERTIFICATION PROCEDURE Equipment Compatibility Equipment Location FAA Requirements Ground Test Flight Manual Revision Flight Test Pilots Guide Failure Modes, Effects, and Safety Analysis Existing STC s CAGE CODE: SCALE: NONE SIZE: A DWG NO: REV: E SHEET 10

11 APPENDIX A - CUSTOMER WORKSHEET APPENDIX B - SAMPLE WIRING DIAGRAMS APPENDIX C WINVIEWS OPERATION INSTRUCTIONS APPENDIX D VENDOR DRAWINGS D 1.0 VENDOR CONTACT INFORMATION D 1.1 EDMO D 1.2 EMTEQ D 1.3 AEROSPACE OPTICS D 1.4 STACOSWITCH APPENDIX E - INTERFACE DESCRIPTION DOCUMENT PART NUMBER PURPOSE SYSTEM OVERVIEW ELECTRICAL INTERFACE INTRODUCTION SIGNAL INTERFACES Grounds Primary Power Input DC Analog Inputs Radio Altitude Low Level Glideslope Localizer Deviation or Low Level Glideslope Validity Barometric Altitude Outside Air Temperature TORQUE INPUTS - DC AC Analog Inputs Synchro Roll Attitude Synchro Magnetic Heading Synchro PITCH ATTITUDE Synchro TORQUE Signal Timing Reference Inputs ARINC 429/575 Digital Serial Bus Inputs RS-232 / RS-422 Digital Serial Bus Inputs GPS RS-232 Digital Serial Bus (serial port 3) GPS RS-422 Digital Serial Bus (serial port 3) Air RS-232 Digital Serial Bus (serial port 2) Air RS-422 Digital Serial Bus (serial port 2) SCI RS-422 Digital Serial Bus (serial port 1) TORQUE INPUTS RS-422 Digital Serial Bus (serial port 1) Discrete Inputs CAGE CODE: SCALE: NONE SIZE: A DWG NO: REV: E SHEET 11

12 4.2.9 Configuration Module Interface GPS Antenna Input OAT Voltage Reference Output Lamp Driver Outputs Monitor Output Characteristics Discrete Output Characteristics Audio Outputs High Level (Speaker) Audio Output Low Level (Interphone) Audio Output ARINC Digital Serial Output Buses ARINC 429 Output Bus ARINC 453 Output Bus Front Panel Test Interface RS-232 Maintenance Port (serial port 4) PCMCIA / SmartCable Port GSE Present Discrete Input Front Panel Status Indicators AIRCRAFT APPLICATION DATA CONFIGURATION TYPES CONFIGURATION SELECTION CONFIGURATION SELECTION TABLES Category 1, Aircraft / Mode Type Select Category 2, Air Input Select Category 3, Position Input Select Category 4, Altitude Callouts Category 5, Audio Menu Select Category 6, Terrain Display Select Category 7, Options 1 Select Category 8, Radio Altitude Input Select Category 9, Navigation Input Select Category 10, Attitude Input Select Category 11, Heading Input Select Category 12, Windshear Input Select Category 13, Input / Output Discrete Type Select Category 14, Audio Output Level Category 15, Autorotation Threshold Category 16, Torque Input Select Category 17, Options 2 Select Category 18, Options 3 Select Category 19, Options 4 Select OUTPUT DATA DEFINITION ARINC 429 OUTPUT DATA Discrete Output Words CAGE CODE: SCALE: NONE SIZE: A DWG NO: REV: E SHEET 12

13 EGPWS Alert Discrete #1 (270) EGPWC Logic Discretes (271) Mode 6 Callouts Discrete #1 (272) Mode 6 Callouts Discrete #2 (273) EGPWS Alert Discrete #2 (274) EGPWC Alert Discrete #3 (300) Internal Outputs Geometric Altitude VFOM (135) Terrain Clearance (164) Geometric Altitude (261) Computed Terrain Clearance (067) Latitude Selected EGPWS (310) Longitude Selected EGPWS (311) Terrain Display Outputs Displayed (050) Terrain Display Status Word (051) Message Word #1 (052) Message Word #2 (053) Message Word #3 (054) Message Word #4 (055) Equipment IDENTIFICATION Equipment IDENTIFICATION WORD FAULT SUMMARY WORDS (for Proline 4/21) FAULT DIAGNOSTIC Word #1 (350) FAULT DIAGNOSTIC Word #2 (351) FAULT DIAGNOSTIC Word #3 (355) PEAK BINARY LABELS Peaks Upper Elevation (011) Peaks Lower Elevation (012) ARINC 708A OUTPUT AUDIO OUTPUT DISCRETE OUTPUTS Ground Proximity Alerts Discrete (Lamp) Outputs Audio On Discrete Monitor Discretes (GPWS, Terrain INOP & Terrain Not Available) Terrain Display Switching Discretes (Wxr/EGPWS Display Select) Glideslope Cancel Discrete Terrain / Obstacle Awareness Alert Discretes Terrain / Obstacle Caution Terrain / Obstacle Warning Terrain Pop Up (Helicopter) Low Altitude Mode Discrete (Tactical) TCAS Inhibit Discrete CAGE CODE: SCALE: NONE SIZE: A DWG NO: REV: E SHEET 13

14 6.4.9 Timed Audio Inhibit Discrete SYSTEM CONFIGURATION STATUS System Status Messages CONNECTOR INTERFACE PINOUT FOR FRONT CONNECTORS SORTED BY PIN NUMBER DEFINITIONS CAGE CODE: SCALE: NONE SIZE: A DWG NO: REV: E SHEET 14

15 SECTION I GENERAL INFORMATION CAGE CODE: SCALE: NONE SIZE: A DWG NO: REV: E SHEET 15

16 SECTION I GENERAL INFORMATION 1.1 Introduction The Honeywell MK XXII Enhanced Ground Proximity Warning System (MK XXII EGPWS) provides alerts and warnings to prevent controlled flight into terrain (CFIT). This Installation Manual must be used in conjunction with the Interface Description Document (Appendix E) for the MK XXII Enhanced Ground Proximity Warning System (MK XXII EGPWS) to select features and design the installation for this system. It is assumed that the user of this document is familiar with avionics installation practices and helicopter systems associated with the installation and operation of the MK XXII EGPWS. It also assumes access to pertinent aircraft wiring diagrams, modification records and manuals. The information contained herein, together with general procedures outlined in FAA AC must be followed carefully to assure a safe, electrically sound, certifiable and operational installation. The contents of this document are for information and reference only and must not be construed as formal FAA approved work authorization. 1.2 Applicability This manual is applicable only to MK XXII EGPWS computers with the following part number: MK XXII How To Use This Document Section 1 provides a system overview. Section 2 provides mechanical installation and location information. Section 3 provides information and instructions for selecting required features of the EGPWS. Section 4 provides Configuration Module programming instructions. Section 5 provides certification requirements. Appendix A Customer Worksheet. Appendix B Sample Wiring Diagrams. Appendix C provides WinViews operation instructions. Appendix D Vendor Information. Appendix E Interface Description Document CAGE CODE: SCALE: NONE SIZE: A DWG NO: REV: E SHEET 16

17 1.4 Reference Documents Following is a list of Honeywell reference documents: Honeywell Product Specification for the MK XXII Enhanced Ground Proximity Warning System (EGPWS) Outline, MK XXII EGPWC Failures Modes, Effects, and Safety Analysis Generic RWFM Supplement For EGPWS (-020 thru -024) Generic RWFM Supplement For EGPWS (-026) Line Maintenance Manual MK XXII Helicopter-Enhanced GPWS Pilot s Guide Installation Ground Test Procedure for the Mk XXII EGPWS for Rotary Wing Aircraft General Flight Test Procedure 1.5 Description of Equipment The MK XXII EGPWS is a rack mount ground proximity warning (GPWS) and terrain display (Class A TAWS) computer. Some of the system features include: Helicopter Ground Proximity Warning Modes 1-5 Mode 6 Altitude, Bank Angle, and Tail Strike Callouts Terrain and Obstacle Awareness alert and display for helicopters Terrain map with runways Internal GPS card Front loading updateable database (requires Smart Cable) External Configuration Module (with Real Time Clock for use with Internal GPS) Internal heater blanket for operation outside of the heated area of the aircraft CAGE CODE: SCALE: NONE SIZE: A DWG NO: REV: E SHEET 17

18 Fig 1.0 MK XXII EGPWC MK XXII EGPWS Computer The MK XXII EGPWS computer is available under P/N XX with internal GPS. The MK XXII EGPWS computer is intended for Helicopters and provides a mixture of analog and digital interfaces. The type of supported displays is limited and includes some EFIS displays. The terrain database included with the MK XXII EGPWS computer are North America, Canada, South America, Europe, Eastern Europe, Africa, South Africa, Asia, Pacific, South Pacific, and Middle East regions and are comprised of terrain data (6 arc second where available), major airports, and man-made obstacles (for North America and limited other regions only) MK XXII EGPWS Configuration Module The MK XXII EGPWS Configuration Module is available under P/N (Included in Installation Kit, see section 1.8). The MK XXII EGPWS uses a Configuration Module installed in the aircraft wiring to store aircraft/egpws interface configuration and includes a Real Time Clock for EGPWS installations using internal GPS. The Configuration module comes prewired and replaces part of the backshell of the (P2) connector that plugs into the front of the MK XXII computer. The Configuration Module is read by the CAGE CODE: SCALE: NONE SIZE: A DWG NO: REV: E SHEET 18

19 EGPWS only during power up. The configuration is copied into Non Volatile Memory (NVM) of the EGPWS. The Configuration Module is programmable via an RS-232 interface with the EGPWS. The contents of the Configuration Module can also be read back via the same RS-232 interface. An optional Configuration Module is available under P/N for non-internal GPS operation only. The Configuration Module includes a GPS Real Time Clock (RTC) counter and position memory to aid in GPS initialization. A capacitor will keep the position memory retained and clock current for approximately 35 days. GPS initialization time should be less than 3 minutes with active RTC data. If the capacitor has discharged then GPS initialization time may be as long as 10 minutes GPS Antenna EGPWS installations using the internal GPS require an active GPS antenna and cabling. The GPS antenna should meet the following qualifications: Frequency: Impedance: Gain: Power: Qualification: MHz 50 ohms 33dB max, 26.5 db preferred 5 VDC (current draw less than 50mA) TSO C129 or C129a or C144 Antenna gain is limited to 33dB gain, maximum. Antennas with 26dB gain are preferred. There are Active GPS antennas with higher gain. However, as the active antenna amplifiers amplify noise as well as the signal, this can overdrive the GPS input AGC circuitry and actually reduce performance. The following GPS antennas are found to be compatible with the EGPWS internal GPS card. Other GPS antennas may be found compatible, contact EGPWS engineering for assistance. It is the responsibility of the OEM or owner/operator (and ultimately the regulatory authorities) to assess the antenna acceptance criteria relative to ARINC, MIL, or other specifications. Boeing has certified the Sensor Systems antenna S (an ARINC 743A antenna with a 33dB gain) for use on all A/C. This antenna is certified for HIRF/EMI, Class 1 flight critical operation. As a result, it is very expensive (about 3X other versions). Honeywell KA 96 P/N TSO-C190 Obsolete King KA 91 P/N TSO-C129 Obsolete King KA 92 P/N TSO-C129 Sensor Systems P/N S TSO-C129, ARINC 743A Sensor Systems P/N S TSO-C129a, ARINC 743A The EGPWS requires an input signal of no less than -106 db (at the EGPWS-GPS coax connector). Installers need to calculate signal strength, plus antenna gain, minus cable line loss to ensure that the input signal does not exceed the -106 db limit. To calculate signal strength at the EGPWS coax connector, assume a received signal strength of -118 db at the antenna (this is average signal strength from a GPS satellite at zenith over the antenna). Add the gain of the antenna, then subtract the line loss of the coax cable, and insertion loss at each connector, except at the EGPWS. Assume 0.6dB insertion loss per connector. CAGE CODE: SCALE: NONE SIZE: A DWG NO: REV: E SHEET 19

20 EXAMPLE: Active GPS Antenna with 26dB gain. A 40 foot coax cable run with 1 coax connector (at the rack disconnect). The cable has a specified line loss of 0.25dB/foot. -118dB (received signal) + 26dB (antenna gain) -92dB -10dB (line loss) (0.25dB/foot x 40 foot run) - 0.6dB (rack coax connector insertion loss) = dB at EGPWS coax connector, better than required -106dB. This is an acceptable installation OAT Sensor The EGPWS uses a separate OAT sensor (Outside Air Temperature) to measure outside air temperature on aircraft that do not have another compatible source of outside air temperature. Outside Air Temperature is used by the EGPWS along with pressure altitude in the Geometric Altitude computation. If Outside Air Temperature is not available, Geometric Altitude is computed using pressure altitude and GPS Altitude with a corresponding reduction in accuracy. Honeywell engineers have determined that the reduction in accuracy is small because the GPS Altitude is the strongest element in the computation. Geometric Altitude is computed by the EGPWS to reduce or eliminate errors potentially induced in corrected barometric altitude by temperature extremes, non-standard altitude conditions, and altimeter miss-sets. Geometric Altitude also allows continuous EGPWS operation in QFE environments without crew intervention Smart Cable (PCMCIA Interface) The EGPWS Smart Cable (part number ) is a removable PCMCIA card interface. The Smart Cable is compatible with any Honeywell supplied ATA style EGPWS PCMCIA cards. The purpose of the Smart Cable in the EGPWS system is for upload of software and databases and also for download of EGPWS Flight History. The Smart Cable loading operation will closely emulate that of an ARINC 615 Loader. (Reference Figure 1-1 MK XXII EGPWS SMART CABLE) CAGE CODE: SCALE: NONE SIZE: A DWG NO: REV: E SHEET 20

21 P3 POWER ON IN PROG CARD CHNG XFER COMP XFER FAIL SMART CABLE PART NO XX USED WITH ENHANCED GROUND PROXIMITY WARNING SYSTEM SERNO: MFG DATE: MOD STATUS FIGURE 1-1 MK XXII EGPWS SMART CABLE 1.6 Technical Characteristics MK XXII EGPWS TSO Compliance: TSO-C194, TSO-C151b, Class A Physical size (HxWxD): 6.20 x 3.04 x Weight: 3.9 pounds maximum Mounting: Standard 3 inch King Radio rack Temperature (operational): -55 C to +70 C (F2) Altitude range: 55,000 feet (F2) Cooling: No cooling necessary Shock: No shock mounting required Power Consumption (28 VDC): 3 Amps 9 watts no warning +7 watts with warning over 8 ohm speaker +3 watts with GPS card +49 watts with heater blanket on CAGE CODE: SCALE: NONE SIZE: A DWG NO: REV: E SHEET 21

22 Configuration Module TSO Compliance: Physical size: Weight: Mounting: Temperature (operational): Altitude range: Cooling: Shock: Power Consumption (5 VDC): TSO-C194, TSO-C151b 2.68 x 1.51 x 0.32 (fits Positronic connector backshell) <1 pound with connector and backshell Mounts to Positronic connector backshell same as MK XXII EGPWS same as MK XXII EGPWS No cooling necessary No shock mounting required from MK XXII EGPWS GPS Antenna Sensor See Section 1.5.3, ARINC 743A,TSO-C129A and Manufacturer s specifications. OAT Sensor Nominal 500 ohm Temperature probe, resistance at 0 C 500-ohm ± 0.6 ohm, -70 C to +60 C (reference ARINC 575 Section 3.8 or ARINC 706 Section 4.8). See Manufacturer s specifications. 1.7 Units Supplied MK XXII EGPWS The part number for the MK XXII EGPWS units is as follows: XX with Internal GPS card Note 1: -0XX defines the Application software version Configuration Module The MK XXII EGPWS Configuration Module is available in two versions. When ordering the Configuration Module, order part number: with Real Time Clock (recommended for all installations) without Real Time Clock (use only with non internal GPS applications) Smart Cable (PCMCIA Interface) The Smart Cable is used for Line Maintenance, only one Smart Cable is required for an installation house or operator. When ordering the Smart Cable, order part number Installation and Accessories Kits Honeywell recommends the Internal GPS kit for all installations and the External GPS kit as an alternate part. NOTE: Not all installation kits are immediately available, contact Honeywell Order Administration ( ) for availability. CAGE CODE: SCALE: NONE SIZE: A DWG NO: REV: E SHEET 22

23 1.8.1 MK XXII EGPWS Installation Kits Honeywell (A) EGPWS installation with Internal GPS This kit must be used when using the internal GPS and may be used when using an external GPS source. The MK XXII EGPWS Installation Kit, P/N , contains the following parts: Vendor Name Vendor P/N Description QTY UM Honeywell P/N Positronic Ind. DD78F1OJVLC-15 P1 connector 1 EA Positronic Ind. RD50F1OJVLC-15 P2 connector 1 EA Honeywell Configuration Module 1 EA Bendix/King Computer Mounting Tray 1 EA Note: For all parts in the installation kit the weight of each individual part is less than 0.25 pounds RS-232 Cable The MK XXII EGPWS RS-232 Cable can be ordered using the following part numbers: NOTE: The RS-232 Cable can be built by the Installer/Operator per the description in Section Vendor Name Vendor P/N Description QTY UM Honeywell P/N Honeywell RS-232 Cable 1 EA Smart Cable The MK XXII EGPWS Smart Cable can be ordered using the following part numbers: Vendor Name Vendor P/N Description QTY UM Honeywell P/N Honeywell Smart Cable 1 EA Terrain base Cards The MK XII EGPWS Terrain base Cards can be ordered using the following part numbers: Vendor Name Vendor P/N Description QTY UM Honeywell P/N Honeywell XXXNAM North America 1 EA xxx Honeywell XXXSAM South America 1 EA xxx Honeywell XXXEUR Europe 1 EA xxx Honeywell XXXEEU Eastern Europe 1 EA xxx Honeywell XXXAFR Africa 1 EA xxx Honeywell XXXPAC Pacific 1 EA xxx Honeywell XXXASI Asia 1 EA xxx Honeywell XXXSPA South Pacific 1 EA xxx Honeywell XXXMES Middle East 1 EA xxx Honeywell XXXCAN * Canada 1 EA xxx Honeywell XXXSAF * South Africa 1 EA xxx Honeywell xxx Label, TDB 1 EA xxx Honeywell SM9FLAPC256M1 PCMCIA Card, Blank 256Mb 1 EA ** XXX is the base version number. * New distribution of regions for helicopter databases: In TDB 438 and later, new regions were created for Canada (CAN) which was part of North America (NAM) region and South Africa (SAF) region which was part of Africa (AFR) region due to higher resolution data being available for those areas. ** The PCMCIA card can also be ordered through Smart Modular Technologies with CUxxxxx part number. See SIL EGPWS- MKV/MKVI/MKVII/MKVIII/XXII CAGE CODE: SCALE: NONE SIZE: A DWG NO: REV: E SHEET 23

24 1.8.5 Flight History Card The Flight History Card is a PCMCIA card that has been loaded with a down load instruction file to allow the down loading of flight history data from an EGPWS. Flight History files contain status information, fault history and flight data from 20 seconds prior to 10 seconds after a EGPWS caution or warning event. The card is used to aid in troubleshooting systems faults and or nuisance warnings. The MK XXII EGPWS Flight History Card can be ordered using the following part numbers: Vendor Name Vendor P/N Description QTY UM Honeywell P/N Honeywell Honeywell Flight History Download Flight History Download 1 1 EA EA Note 1: Unprogrammed (blank) 32 Mb ATA PCMCIA card. Note 2: Programmed 32 Mb ATA PCMCIA card. 1.9 Accessories Required but not Supplied ARINC 453 Terrain Display wiring The Terrain display wiring (ARINC 453) must meet the display manufacturer s specifications including termination method. ARINC 453 bus wiring must meet the following requirements: Cable length must be less than 300 feet (91.4 meters). Wire to wire capacitance must not exceed 50 pf/foot. Shielded twisted pair with not less than one twist per inch. Impedance of 78 ohms ±10% at 1 MHz. Vendor Name Vendor P/N Description QTY UM Pic Wire&Cable D ARINC 453 cable A/R EA Pic Wire&Cable D5102QX Hi Temp Quadraxial A/R EA Pic Wire&Cable D MIL-STD 1553 Bus A/R EA ECS ECS ARINC 453 cable (2 shields) ARINC 453 cable (3 shields) A/R A/R EA EA Emteq D T-01 ARINC 453 cable A/R EA M17/ M83536/6-022M M12883/44-01 Military Specification Relay, 4PDT (Note 1) Relay, Socket (Note 1) A/R A/R A/R EA EA EA Note 1: Recommended in EFS 40/50 Installation Manual GPS Antenna & cable The GPS Antenna & cable can be ordered from their manufacturers using the following part numbers: Vendor Name Vendor P/N Description QTY UM Honeywell P/N Honeywell KA 96 GPS Antenna (29dB) 1 EA Honeywell KA 96 Antenna Installation Kit 1 EA Bendix/King KA 92 GPS Antenna (26dB) OPT EA Obsolete * Bendix/King KA 92 Antenna Installation Kit OPT EA Obsolete * Sensor Systems S S67 GPS Antenna (29dB) OPT EA Sensor Systems S S67 GPS Antenna (26dB) OPT EA Sensor Systems S S67 GPS Antenna (33dB) OPT EA CAGE CODE: SCALE: NONE SIZE: A DWG NO: REV: E SHEET 24

25 Thermax M17/128-RG400 Coax Cable, RG400/U A/R EA Coax Cable, RG-142B/U A/R EA PIC S14293 Coax Cable A/R EA PIC S44191 Coax Cable A/R EA ECS Coax Cable A/R EA ECS Coax Cable A/R EA ECS Coax Cable A/R EA Amp TNC Angle Plug, Male OPT EA Amphenol TNC Angle Plug, Male OPT EA NOTE: If a satellite communication system is installed in the aircraft, or the GPS cable run is in the vicinity of a VHF transceiver and/or cable, DO NOT USE R/G 142 or R/G 400 cable. * The KA 92 GPS antenna has been made obsolete by the manufacturer and replaced by the KA 96 GPS antenna. See Honeywell Service Bulletin KA Circuit Breaker The Circuit Breaker needs to be a 3 Amp delayed action circuit breaker. Vendor Name Vendor P/N Description QTY UM Honeywell P/N Klixon (T.I.) Amp Circuit Breaker, 1 EA EGPWS power +28 Klixon (T.I.) Amp Circuit Breaker, lamp power EA Annunciators & Switch/Annunciators The devices shown below are switch/annunciators and are representative of those used in some installations. However, there are other comparable devices on the market that may be substituted at the installer/customers choice. The installer/customer is cautioned to verify regulatory approval of the annunciation devices installed. See Appendix D for Vendors GPWS Warning (red) P/TEST; switch/annunciator assembly The GPWS annunciator provides visual indication of an EGPWS warning. The GPWS warning (red) annunciator also has a switch that is used to manually initiate EGPWS Self Test GPWS Caution (amber) G/S CANCLD switch/annunciator assembly. The GPWS caution annunciator provides visual indication of an EGPWS alert. The EGPWS caution (amber) annunciator also has a switch that is used to manually inhibit EGPWS Mode 5 glideslope alerts. The bottom half of the annunciator provides visual indication that the Mode 5 glideslope alerts have been canceled LOW ALT / ON switch/annunciator assembly The LOW ALT / ON switch/annunciator provides for manual selection of low altitude mode and visual indication that the Mk XXII EGPWS is in low altitude mode TERR INHIB / ON switch/annunciator assembly The TERR INHIBIT switch/annunciator provides for manual selection of terrain inhibit mode and visual indication that the EGPWS Terrain functions have been inhibited. CAGE CODE: SCALE: NONE SIZE: A DWG NO: REV: E SHEET 25

26 AUDIO INHIBIT / ON switch/annunciator assembly The AUDIO INHIBIT switch/annunciator provides for manual selection of audio inhibit mode and visual indication that the EGPWS mode functions have been inhibited GPWS INOP / TERR INOP annunciator assemblies The GPWS INOP annunciator provides visual indication that the EGPWS GPWS modes have a disabled function. The TERR INOP annunciator provides visual indication that the EGPWS Terrain modes have a disabled function TERR DISPLAY / ON switch/annunciator assemblies The TERR DISPLAY switch/annunciator provides for manual selection of the terrain display and visual indication that the EGPWS Terrain Display has been selected for the associated display Cockpit Speaker (Optional) The MK XXII EGPWS can interface to an 8 ohm audio speaker for cockpit annunciation of aural alerts. Vendor Name Vendor P/N Description QTY UM Honeywell P/N Quam 30A05Z8 Audio Speaker 1 EA Utah SP-3A Audio Speaker 1 EA CTS 4AC3 Audio Speaker 1 EA Temperature Probes The MK XXII EGPWS may be optionally interfaced to a dedicated 500-ohm temperature probe meeting the specifications of ARINC 575 Section 3.8. The installer may want to discuss availability of a dual-element probe compatible with the EGPWS and with other systems on the aircraft with the manufacturers. Vendor Name Vendor P/N Description QTY UM Kollsman CIC Norwich Norwich 05257* Single element, unheated Single element, unheated Dual element, unheated EA EA EA Rosemount 102CT2CB 500-ohm 1 EA Rosemount 102AU1AF Single element, heated 1 EA Rosemount 102AU1AG Dual element, heated 1 EA Rosemount 102EH2BH Dual element, heated 1 EA Rosemount 102EH2EB Dual element, heated 1 EA Rosemount 102JE2FG Triple element, heated 1 EA Rosemount 129H-500 Single element, unheated 1 EA Rosemount 129G-500 Dual element, unheated 1 EA *Also available from Donel Systems (formerly CIC) 1.12 Tools Required Crimping Tool - P1, P2, P3 Description UM QTY Vendor Name & Part Number Hand Crimping Tool EA 1 Positronic Ind CAGE CODE: SCALE: NONE SIZE: A DWG NO: REV: E SHEET 26

27 Hand Crimping Tool EA 1 Daniels AFM8 Hand Crimping Tool EA 1 Military M22520/ Contact Positioner - P1, P2, P3 Description UM QTY Vendor Name & Part Number Contact Positioner, Socket P1 EA 1 Positronic Ind Contact Positioner, Socket P1 EA 1 Daniels K41 (for 22 to 28 AWG) Contact Positioner, Socket P1 EA 1 Military M22520/2-06 Contact Positioner, Socket P2 EA 1 Positronic Ind Contact Positioner, Socket P2 EA 1 Daniels K13-1 (20-24 AWG) Contact Positioner, Socket P2 EA 1 Military M22520/2-08 Contact Positioner, Pin P3 EA 1 Positronics Contact Positioner, Pin P3 EA 1 Daniels K42 (22-28 AWG) Contact Positioner, Pin P3 EA 1 Military M22520/ Insertion/Removal Tool - P1, P2, P3 Description UM QTY Vendor Name & Part Number Removal Tool P1, P3 EA 1 Daniels DRK 95-22M Removal Tool P1, P3 EA 1 Military M81969/8-02 Removal Tool P2 EA 1 Daniels DRK145 Insertion Tool P1, P3 EA 1 Daniels DAK 95-22M Insertion Tool P1, P3 EA 1 Military M81969/8-01 Insertion Tool P2 EA 1 Daniels DAK145 Insertion/Removal Tool P1, P3 EA 1 Military M81969/1-04 Insertion/Removal Tool P2 EA 1 Military M81969/ Spare Contacts - P1, P2, P3 P/N Description UM QTY Vendor Name & Part Number pin male with hood EA 1 Positronic Ind. DD15M10YOC pin female EA 1 Positronic Ind. DD15F10OOC pin male EA 1 Positronic Ind. DD15M10OOC pin clamp kit EA 1 AMP male contacts for 15 pin AWG EA 1 Positronic Ind. MC8022D male contacts for 15 pin AWG EA 1 M39029/ female contacts for 50 pin AWG EA 1 Positronic Ind. FC6020D female contacts for 50 pin AWG EA 1 M39029/ female contacts for 78 pin AWG EA 1 Positronic Ind. FC8022D female contacts for 78 pin AWG EA 1 M39029/ These parts are available in EGPWS kit PN License Requirements There are no Radio license requirements for the MK XXII EGPWS. CAGE CODE: SCALE: NONE SIZE: A DWG NO: REV: E SHEET 27

28 1.14 TSO-C194 Deviations Honeywell The MK XXII EGPWS and its Configuration Module have two (2) deviations to TSO-C194. Honeywell has shown that the system maintains an equivalent level of safety and the FAA has evaluated and approved the deviations Environmental Qualification Deviation TSO-C194 states in Section 3 (Requirements), paragraph d (Environmental Qualification) Test the equipment according to RTCA/DO-160F, Environmental Conditions and Test Procedures for Airborne Equipment, dated December 6, Deviation: The original qualification testing for the MK XXII EGPWS, part number [ ], and Configuration Module, part number , was performed in 2003 at which time RTCA/DO-160D was the current version. The appropriate categories were tested for helicopter applications. Honeywell has compared DO- 160D to DO-160F, while DO-160F contains several test procedures updates DO-160D remains a valid series of minimum standard environmental test conditions. The appropriateness and FAA acceptance of this qualification basis has been shown by TSO-C151a/b authorization as well as the numerous MK XXII STC and TC approvals in helicopter applications. Approval Status: Honeywell has demonstrated an equivalent level of safety as required by TSO-C194 in Section 3 (Requirements), paragraph g (Deviation). The FAA has approved this deviation. See Environmental Qualification Form, Table I Electronic Hardware Qualification Deviation TSO-C194 states in Section 3 (Requirements), paragraph f (Electronic Hardware Qualification). If the article includes a complex custom micro-coded component, develop the component to the guidance in FAA Advisory Circular (AC) , RTCA, Inc. Document RTCA/DO-254, Design Assurance Guidance for Airborne Electronic Hardware" The hardware design assurance level should be consistent with the failure condition classification in paragraph 3b of this TSO. Deviation: The MK XXII EGPWS hardware was developed in 2002 which predates FAA Advisory Circular (AC) issue date of 6/30/05. The MK XXII EGPWS contains one programmable logic device (PLD) and two ARINC 429 Receiver chips that are considered complex electronic hardware. The Configuration Module includes two PLDs. Honeywell followed an FAA agreed upon complex electronic hardware approval method for TSO submittals. The design assurance method included DER review and approval, with FAA form , of the programmable logic device lifecycle data. This approval process occurred each time minor changes were made to the EPLD to support board updates. CAGE CODE: SCALE: NONE SIZE: A DWG NO: REV: E SHEET 28

29 Approval Status: Honeywell has demonstrated an equivalent level of safety as required by TSO-C194 in Section 3 (Requirements), paragraph g (Deviation). The FAA has approved this deviation Limitations TSO-C194 paragraph 5. Application Requirements a. Operating instructions and equipment limitations The Honeywell MK XXII Helicopter EGPWS Pilot Guide HPN including section MK XXII System Limitations / Constraints is available upon request from Honeywell Technical Publications to Honeywell authorized installers and dealers. Installers will provide a Flight Manual Supplement as part of their STC submittal b. Installation procedures and limitations The installer will provide detailed installation drawings as part their STC submittal noting any limitations in their submittal package. The conditions and tests for TSO approval of this article are minimum performance standards. Those installing this article, on or in a specific type or class of aircraft, must determine that the aircraft installation conditions are within the TSO standards. TSO articles must have separate approval for installation in an aircraft. The article may be installed only according to 14 CFR part 43 or the applicable airworthiness requirements c. Schematic drawings of the installation procedures Section 2 of this document provides specific installation guidance for computer mounting, configuration module installation, optional GPS antenna mounting, and required cockpit annunciators d. Wiring diagrams of the installation procedures Section 3 of this document provides specific installation guidance for known aircraft interfaces e. List of components Section 1 of this document details required and optional items used for installation f. Component Maintenance Manual (CMM) ATA No (HPN ) available to Honeywell authorized installers and dealers from Honeywell Technical Publications g. Material and process specifications list provided to the FAA h. Quality control system (QCS) description Honeywell is an authorized Production Approval Holder (PAH). CAGE CODE: SCALE: NONE SIZE: A DWG NO: REV: E SHEET 29

30 i. Manufacturer s TSO Qualification test report This item is included in the Plan for Software Aspects of Certification (PSAC) and is available upon request from Honeywell Technical Publications to Honeywell authorized installers and dealers j. Nameplate drawing Honeywell drawing number is available upon request from Honeywell Technical Publications to Honeywell authorized installers and dealers k. List of all drawings and processes provided to the FAA l. Environmental qualifications form Honeywell drawing number Qualification by Test and Similarity Report is available upon request to Honeywell authorized installers and dealers from Honeywell Technical Publications m. Plan for software aspects of certification (PSAC), software configuration index, and software accomplishment summary (SAS) The Plan for Software Aspects of Certification (PSAC), Software Configuration Index, and Software Accomplishment Summary (SAS) are available upon request from Honeywell Technical Publications to Honeywell authorized installers and dealers n. Plan for hardware aspects of certification (PHAC), hardware verification plan, top-level drawing, and hardware accomplishment summary All hardware related data is covered in the Plan for Software Aspects of Certification (PSAC), and is available upon request from Honeywell Technical Publications to Honeywell authorized installers and dealers. CAGE CODE: SCALE: NONE SIZE: A DWG NO: REV: E SHEET 30

31 NOMENCLATURE: EGPWS MK XXII Honeywell Environmental Qualification Form TYPE/MODEL/PART NO: [ ] TSO NUMBER C194, C151b MANUFACTURER S SPECIFICATION AND/OR OTHER APPLICABLE SPECIFICATION: Product Specification for the Helicopter Enhanced Ground Proximity Warning System (EGPWS) Rev D MANUFACTURER: HONEYWELL INTERNATIONAL INC. ADDRESS: N. 19 th Ave., Phoenix, AZ REVISION & CHANGE NUMBER OF DO-160: NEW DATE TESTED: March April 2003 CONDITIONS SECTION DESCRIPTION OF TESTS CONDUCTED Temperature and Altitude 4.0 Equipment tested to Categories F2, Low Temperature -55C Operation High Temperature +70C Operation In-Flight Loss of Cooling NA & Category F2 for Temperature and Altitude No cooling necessary Altitude: 55,000 Ft Decompression: 8,000 ft to -55,000 ft Overpressure: -15,000 ft Category A2 for Decompression and Overpressure Temperature Variation 5.0 Equipment tested to Category B Humidity 6.0 Equipment tested to Category A Operational Shock and Crash safety 7.0 Equipment tested to Category B Vibration 8.0 Equipment tested to Category U: Helicopter unknown frequencies. Curves F and F1. Explosive Atmosphere 9.0 Equipment tested to Category E Waterproofness 10.0 X, (no test required) Fluids Susceptibility 11.0 X, (no test required) Sand and Dust 12.0 X, (no test required) Fungus 13.0 F, (no test, non-nutrient material certification) Salt Fog Test 14.0 X, (no test required) Magnetic Effect 15.0 Equipment tested to Category Z CAGE CODE: SCALE: NONE SIZE: A DWG NO: REV: E SHEET 31

32 CONDITIONS SECTION DESCRIPTION OF TESTS CONDUCTED Power Input 16.0 Equipment tested to Category A Voltage Spike 17.0 Equipment tested to Category A Audio Frequency Susceptibility 18.0 Equipment tested to Category Z Induced Signal Susceptibility 19.0 Equipment tested to Category C Radio Frequency Susceptibility 20.0 Equipment tested for conducted susceptibility to Category R and for radiated susceptibility to Category RR Radio Frequency Emission 21.0 Equipment tested to Category M Lightning Induced Transient Susceptibility 22.0 Equipment tested to Category A3E3 Lightning Direct Effects 23.0 X, (no test required) Icing 24.0 X, (no test required) Electrostatic Discharge 25.0 Equipment tested to Category A Fire, Flammability 26.0 Not Applicable Other Tests REMARKS Table I Environmental Qualification Form CAGE CODE: SCALE: NONE SIZE: A DWG NO: REV: E SHEET 32

33 1.16 Non TSO functions A non-tso function is one that is not covered by a TSO-approved minimum performance standard (MPS), does not support or affect the hosting article s TSO function(s), and could technically be implemented outside of the TSO article. Honeywell s MK XXII EGPWS includes optional features that meet the non-tso definition. The following tables briefly describe existing non-tso functions included in the MK XXII EGPWS. The Mode envelopes are similar to the fixed wing TSO C92c Mode envelopes but adjusted for helicopters Helicopter Mode 1 Helicopter Mode 1 provides alerts when the aircraft has excessive descent rate close to the terrain. This envelope is not part of TSO C Helicopter Mode 2 Helicopter Mode 2 provides alerts when the aircraft is closing with the terrain at an excessive rate. This envelope is not part of TSO C Helicopter Mode 3 Helicopter Mode 3 provides alerts when the aircraft loses a significant amount of altitude immediately after takeoff or during a missed approach. This envelope is not part of TSO C Helicopter Mode 4 Helicopter Mode 4 provides alerts for insufficient terrain clearance with respect to phase of flight and speed. This envelope is not part of TSO C Helicopter Mode 4C Helicopter Mode 4C provides a Mode 4 Too Low Terrain warning if the aircraft exhibits insufficient climb performance during take-off. This envelope is not part of TSO C Helicopter Altitude Callouts The Altitude Callouts option, enabled via a configuration module selection, aurally annunciates various altitude callouts and descent below minimum selected decision height during final approach. Other sets of callouts are also provided during autorotation and cruise to provide altitude awareness to the rotor wing pilot. Pre-defined callout menus are selected with configuration module option. This function is not part of TSO C Bank Angle Callout The Bank Angle option, enabled via a configuration module selection, provides an aural advisory for excessive bank angles. This function is not part of TSO C Tail Strike Callout Tail Strike provides an aural advisory for excessive pitch angles when the aircraft is low to the ground and there is danger of tail rotor strike. CAGE CODE: SCALE: NONE SIZE: A DWG NO: REV: E SHEET 33

34 Externally Triggered Annunciation Honeywell The EGPWC responds to the external commands by generating aural annunciations prioritized with respect to other ground proximity alerts. This function is not part of TSO C194. Low Rotor Fire Engine 1/2" Engine 1/2 Failure Fire APU Airspeed Radio Altimeter Self Test Smoke In Baggage Hover Altitude Swash Plate Temperature Level Off Decouple Hover Altitude Gearbox Pressure Check Power Smoke In Cabin Gear Box Oil Out A maintenance DH voice advisory call is provided from the EGPWC during an on ground Radio Altimeter test. This function is not part of TSO C194. CAGE CODE: SCALE: NONE SIZE: A DWG NO: REV: E SHEET 34

35 MK XXII EGPW Installation Manual SECTION II INSTALLATION CAGE CODE: SCALE: NONE SIZE: A DWG NO: REV: E SHEET 35

36 MK XXII EGPW Installation Manual SECTION II - INSTALLATION 2.1 Introduction This section contains suggestions and factors to consider before installing the Enhanced Ground Proximity Warning System. Close adherence to these suggestions will assure satisfactory performance from the equipment. NOTE The conditions and tests performed on this article are minimum performance standards. It is the responsibility of those desiring to install this article either on or within a specific type or class of aircraft to determine that the aircraft installation conditions are within these performance standards. The article may be installed only if further evaluation by the applicant, documents an acceptable installation and is approved by the Administrator. 2.2 Unpacking and Inspecting the Equipment Exercise extreme caution when unpacking equipment. Perform a visual inspection of the unit for evidence of damage incurred during shipment. If a damage claim must be filed then save the shipping container and all packing materials to substantiate your claim. The claim should be filed as soon as possible. The shipping container and all packing materials should be retained in the event that storage or reshipment of the equipment is necessary. 2.3 Equipment Installation General The following paragraphs contain information pertaining to the installation of the MK XXII EGPWS, including instructions concerning the location and mounting of the equipment. The equipment should be installed in the aircraft in a manner consistent with acceptable workmanship and engineering practices, and in accordance with the instructions set forth in this publication. To ensure the system has been properly and safely installed in the aircraft, the installer should make a thorough visual inspection and conduct an overall operational check of the system, on the ground, prior to flight. CAUTION AFTER INSTALLATION OF THE CABLING AND BEFORE INSTALLATION OF THE EQUIPMENT, A CHECK SHOULD BE MADE WITH THE AIRCRAFT PRIMARY POWER SUPPLIED TO THE MOUNTING CONNECTOR, TO ENSURE THAT POWER IS APPLIED ONLY TO THE PINS SPECIFIED IN THE INTERWIRING DIAGRAMS IN SECTION III. CAGE CODE: SCALE: NONE SIZE: A DWG NO: REV: E SHEET 36

37 2.3.2 MK XXII Computer Location Honeywell MK XXII EGPW Installation Manual Care should be exercised to avoid mounting components near equipment operating with high pulse current or high power outputs such as radar and satellite communications equipment. In general, the equipment should be installed in a location convenient for operation, inspection, and maintenance, and in an area free from excessive vibration, heat, and noise generating sources. The MK XXII EGPWS computer has an internal heater blanket allowing the computer to be mounted outside the heated area of the aircraft. The computer has been qualified for operation up to 50,000 feet and -55 C using the heater blanket. The computer has been vibration tested to 3-axis allowing mounting orientation in any direction. All mechanical installation drawings referenced in this section are located at the end of Section II, of the manual. Determine the mounting location for the system components following the guidelines below. The length of cables from the EGPWS connectors to other system units is not generally critical because unit interfaces are designed with high impedance inputs, low impedance outputs, and low noise susceptibility characteristics. The exception is the wires from the EGPWS Configuration Module, which was designed to be a part of the EGPWS connector backshell because of the requirement for short lead length. Follow aircraft manufacturer s, sub-system manufacturer s or ARINC specifications for shield grounding. To allow for inspection or repair of the wiring of the connector assembly itself, sufficient lead length should be left so that EGPWS may be moved several inches. A bend should be made in the harness to allow water droplets that might form on the harness due to condensation, to drip off at the bend and not collect in the connector. Prior to installing any equipment, make a continuity check of all wires and cables associated with the system. Then apply power and check for proper voltages at system connectors, and then remove power before completing the installation MK XXII Computer Installation The MK XXII EGPWS installation will conform to standards designated by the customer, installing agency, and existing conditions as to the unit location and type of installation. However, the following suggestions will assure a more satisfactory performance from the equipment. A. Plan a location on the aircraft so that the EGPWS is accessible for front panel maintenance controls. Check to be sure that there is adequate space in the front of the computer for connectors and cabling. B. Refer to Figure 2-2 and 2-3 for outline dimensions of the computer and mounting tray. C. Mount the EGPWS mounting tray in the aircraft radio rack or other location using the four screw mounting holes. Match drill the mounting holes using the Mounting Tray as a template. D. Ensure that the mounting tray is electrically bonded (less than 10 milli-ohm to aircraft ground). CAGE CODE: SCALE: NONE SIZE: A DWG NO: REV: E SHEET 37

38 MK XXII EGPW Installation Manual E. Slide the EGPWS unit in the mounting tray, and secure it using the Hold Down latch. F. (After Continuity and Power check) Attach the cable harness to the front panel connectors and lock connectors using the slide lock of the P1 & P2 connectors. The EGPWS should be wired according to the interconnect diagrams in Section III, of this manual Configuration Module Location The aircraft configuration is programmed into the EGPWS Configuration Module installed in the aircraft wiring. The Configuration Module is identified as Honeywell part number (optional part number ). The Configuration Module is installed as one side of the P2 (50 pin) mating connector backshell and contains electrically reprogrammable memory for configuration storage. The Configuration Module when installed is wired directly to the appropriate pins in the P2 connector Configuration Module Installation The purpose of this procedure is to give an assembly sequence for assembly of the Configuration Module with the P2 connector and backshell. A. The P2 connector, Honeywell part number , vendor part number RD50F1OJVLC-15, when ordered comes with 50 contacts and a plastic backshell (hood). B. The Configuration Module will replace the Backshell Plate. The Backshell Plate can be discarded. C. Wire the Configuration Module to the P2 connector using contacts provided with the connector. Wire per the following wire list: Wire Color P2 pin # Violet P2-17 Blue P2-16 Orange P2-33 Wire Color P2 pin # Black P2-50 White P2-49 Red P2-32 D. Position Slide Lock and Spring Clip onto connector. E. Install Backshell Housing onto connector. The Ground wire (used for ESD discharge) is terminated with shielded pigtails inside the backshell to the P2 connector. (Note: Ground wire is not applicable to Configuration Modules.) F. Organize and dress wire exiting from the backshell, route Configuration Module wires in a coil. Install Cable Clamp, do not tighten Cable Clamp screws. G. Secure the Configuration Module to the connector using screws provided. Tighten Cable Clamp screws as required. CAGE CODE: SCALE: NONE SIZE: A DWG NO: REV: E SHEET 38

39 REQUIRED: Two items as follows: Honeywell MK XXII EGPW Installation Manual CONFIGURATION MODULE ASSEMBLY ITEM 1.0 Connector (P2) Positronic Ind. RD50F10JVLC-15 * ITEM 2.0 Configuration Module Honeywell * This item may be available from Honeywell under Part No. ( ) ITEM 1 DESCRIPTION: Connector P2 (Positronic Ind. PN RD50F10JVLC-15) is a packaged kit consisting of the following parts: 1.1 Connector, 50 socket D-Sub Qty Contacts, size 20 crimp Qty Backshell housing Qty Backshell plate Qty Screws, Phillips CSK Qty Spring Clip Qty Slide Lock Qty Screws, Slotted Qty Cable Clamp Qty - 1 INSTALLATION ASSEMBLY SEQUENCE STEP 1 Install all MK XXII system aircraft wiring to this connector using items 1.2 (Crimp Contacts) and item 1.1 (Connector). See figure below. FIGURE MK XXII EGPWS CONFIGURATION MODULE CAGE CODE: SCALE: NONE SIZE: A DWG NO: REV: E SHEET 39

40 MK XXII EGPW Installation Manual STEP 2 Wire item 2.0 (Configuration Module). This part will replace item 1.4 (Backshell plate). Install the pre-crimped colored wires into item 1.1 (Connector) as shown in figure below. FIGURE MK XXII EGPWS CONFIGURATION MODULE Note: The Ground wire (used for ESD discharge) is Not Applicable to Configuration Module PN CAGE CODE: SCALE: NONE SIZE: A DWG NO: REV: E SHEET 40

41 MK XXII EGPW Installation Manual STEP 3 Position item 1.7 (Slide lock) onto wired connector as shown in figure below: FIGURE MK XXII EGPWS CONFIGURATION MODULE CAGE CODE: SCALE: NONE SIZE: A DWG NO: REV: E SHEET 41

42 MK XXII EGPW Installation Manual STEP 4 Install item 1.3 (Backshell Housing) onto connector using item 1.8 (Screws) as shown in figure below: Ground Wire (used for electrostatic discharge {ESD} protection) is terminated with shielded pigtails of wires at this connector. (See Note par E) FIGURE MK XXII EGPWS CONFIGURATION MODULE Note: The Ground wire (used for ESD discharge) is Not Applicable to Configuration Module PN CAGE CODE: SCALE: NONE SIZE: A DWG NO: REV: E SHEET 42

43 MK XXII EGPW Installation Manual STEP 5 Install item 1.6 (Spring Clip) as shown figure below: FIGURE MK XXII EGPWS CONFIGURATION MODULE CAGE CODE: SCALE: NONE SIZE: A DWG NO: REV: E SHEET 43

44 MK XXII EGPW Installation Manual STEP 6 Organize and dress wiring exiting from backshell. Route Configuration Module wires exiting from connector, then coil as shown in figure below. Install item 1.9 (Cable Clamp) as shown. Do not tighten screws yet. FIGURE MK XXII EGPWS CONFIGURATION MODULE CAGE CODE: SCALE: NONE SIZE: A DWG NO: REV: E SHEET 44

45 MK XXII EGPW Installation Manual STEP 7 Secure Configuration Module to connector assembly using item 1.5 (Screws) as shown in figure below. Tighten Cable Clamp screws as required. FIGURE MK XXII EGPWS CONFIGURATION MODULE CAGE CODE: SCALE: NONE SIZE: A DWG NO: REV: E SHEET 45

46 MK XXII EGPW Installation Manual GPS Antenna location The antenna must be mounted on top of the fuselage in the centerline of the aircraft. Avoid mounting the antenna near any projections such as the rotor mast, or engine exhaust, where shadows could occur or high heat could damage the antenna. It is recommended that there be a separation of at least 3 feet between the GPS antenna and any VHF Comm antenna on the aircraft. The GPS antenna baseplate must be level within ± 5 in both axis when the aircraft is level (level is defined as the aircraft attitude required when weighing the aircraft for weight and balance). If the GPS antenna is tilted more than 5 or is mounted close to other objects that shadow it, loss of some of the satellites will occur and system performance may be degraded. See manufacturer for specifications of GPS antenna, antenna cables, and connector information. Some GPS Antenna cable and connector information, including vendor information, is listed below. Cable Length Cable Part EGPWS TNC Antenna TNC Max Loss* Number (VPN) Connector (VPN) Connector (VPN) 0 to 40 ft RG142B/U TED Mfg TED Mfg RG400/U 0 to 80 ft ECS TED Mfg TED Mfg to 100 ft ECS TED Mfg TED Mfg to 165 ft Contact TED, ECS or PIC for complete cable/connector assembly * Maximum Allowable Loss 1575 MHz for cable and connector using nominal 26.5 db gain. TED Manufacturing Corp Johnson Drive Shawnee, Kansas Tel: (913) Electronic Cable Specialists (ECS) 5300 W. Franklin drive Franklin, Wisconsin Tel: (800) PIC Wire & Cable N63 W Main Street Sussex, Wisconsin Tel: (800) GPS Antenna Installation Refer to manufacturer s procedures or applicable STC documentation OAT Sensor Location The OAT sensor should be mounted on the underside (belly) of the aircraft or other convenient location meeting the following conditions. Avoid mounting the sensor where it can be affected by direct sunlight, or exhaust gases from engines or heaters. The probe tip should extend beyond the aircraft boundary layer into the turbulent airflow. See manufacturer for specifications OAT Sensor Installation Refer to manufacturer s procedures or applicable STC documentation. CAGE CODE: SCALE: NONE SIZE: A DWG NO: REV: E SHEET 46

47 MK XXII EGPW Installation Manual Cockpit Annunciators / Switches This section provides information for selecting, locating and mounting of the MK XXII EGPWS Lighted annunciators / switches. NOTE: The nomenclature given for each lamp is an example only. Other manufacturers use nomenclature that is also acceptable. Refer to Honeywell Product Specification for additional information and for electrical loads specification. NOTE: When using the Bendix/King Multifunction Display (MFD) KMD 550/850 most of the annunciation and switch functions described below are available on screen text and as softkeys Description EGPWS warning GPWS P/TEST This assembly is illuminated with Red background and black or white letters, for dark cockpits black background and Red letters. The EGPWS warning annunciator is not normally dimmable. For Lamp Format 1 (I/O Discrete Type 128) the lamp is activated during any Mode 1 through Mode 4, and Terrain /Obstacle Awareness alerts and warnings. For Lamp Format 2 (I/O Discrete Type 129) the lamp is activated during Mode 1 and Mode 2 Pull Up, and Terrain /Obstacle Awareness warnings. This assembly also includes a momentary switch that will activate EGPWS Self Test. EGPWS caution GPWS G/S CANCLD This assembly is illuminated with Amber background and black or white letters, for dark cockpits black background and Amber letters. The EGPWS alert annunciator is not normally dimmable. For Lamp Format 1 (I/O Discrete Type 128) the lamp is activated during any Mode 5 alert. For Lamp Format 2 (I/O Discrete Type 129) the lamp is activated during any Mode 1 through Mode 4, and Terrain /Obstacle Awareness alerts. This assembly also includes a momentary switch that will activate glideslope cancel. LOW ALTITUDE LOW ALT ON This assembly is illuminated with black background and white, blue, or green letters. This assembly also includes a momentary switch that will activate / de-activate (cancel) EGPWS low altitude mode. TERRAIN INHIBIT TERR INHIB ON This assembly is illuminated with black background and white, blue, or green letters. This assembly also includes a alternate action switch that will activate / de-activate (cancel) Terrain inhibit mode. (Optional see section ) AUDIO INHIBIT AUDIO INHIB ON This assembly is illuminated with black background and white, blue, or green letters. This assembly also includes a momentary switch that will activate / de-activate (cancel) Audio inhibit mode. (Optional see section ) GPWS system validity GPWS INOP TERR INOP This assembly is illuminated with black background and amber letters activated during any detected partial or total failure of the GPWS modes 1-5 and TA&D. CAGE CODE: SCALE: NONE SIZE: A DWG NO: REV: E SHEET 47

48 MK XXII EGPW Installation Manual TERRAIN select TERR DISPLAY ON This assembly is illuminated with white background and activated after the flight crew has initiated the manual selection of the EGPWS terrain display for the associated cockpit display. This assembly also includes a momentary switch that will activate EGPWS Terrain display feature Location Cockpit layout, size and operator s preference will determine if only one set of lights is used (i.e., mounted in the center), or if dual sets of lights are used (one set on each side), or a combination thereof is desired. For a typical example of cockpit light locations refer to Figure 2-8. For panel cutouts and assembly options see the manufacturer s specifications. The following are recommended locations: GPWS warning (red) & GPWS alert (amber) These lights should be located together and in the flight crew s primary field of view. This would include either the instrument panel or the edge of the glareshield. LOW ALTITUDE This light should be located in the flight crew s field of view and within reach of both crewmembers. This light/switch may be located in an assembly with the GPWS red and GPWS amber lights and/or other EGPWS annunciators. TERR INHIBIT ON (Optional see section ) This light should be located in the flight crew s field of view and within reach of both crewmembers. This light/switch may be located in an assembly with the TERR DISPLAY light(s) and/or other EGPWS annunciators. AUDIO INHIBIT ON (Optional see section ) This light should be located in the flight crew s field of view and within reach of both crewmembers. This light/switch may be located in an assembly with the TERR DISPLAY light(s) and/or other EGPWS annunciators. TERR DISPLAY ON This light should be located near the associated cockpit display, in the flight crew s field of view and within reach of one or both crewmembers. This light/switch may be located in an assembly with the TERR INHIBIT light(s) and/or other EGPWS annunciators. GPWS INOP This light should be located within at least one crewmember s field of view or with other system INOP lights of similar importance. It is recommended that this light not be located in the flight crew s primary field of view. The reason being that in the event of a GPWS system failure at the beginning of a flight, this light will remain ON until the problem is fixed. TERR INOP This light should be located within at least one crewmember s field of view or with other system INOP lights of similar importance. Note: Annunciators are available with split legend GPWS INOP / TERR INOP in one assembly. It is recommended that this light not be located in the flight crew s primary field of view. The reason being that in the event of a GPWS system failure at the beginning of a flight, this light will remain ON until the problem is fixed. CAGE CODE: SCALE: NONE SIZE: A DWG NO: REV: E SHEET 48

49 MK XXII EGPW Installation Manual FIGURE 2-8 MK XXII EGPWS Annunciators/Switches Location CAGE CODE: SCALE: NONE SIZE: A DWG NO: REV: E SHEET 49

50 MK XXII EGPW Installation Manual Inhibit Switch Functions and Selection The Terrain Inhibit and Audio Inhibit functions are optional but it is recommended that one be used to inhibit the system during certain operations. The operator should evaluate the two options together with the Low Altitude Mode function and select the one that best fits his operational requirements. The Low Altitude Mode is also described below for reference Terrain Inhibit The Terrain Inhibit will inhibit Terrain and Obstacle audio alerts and warnings. It will not deselect the Terrain Display. The switch is a toggle action, which must be pressed to turn ON and re-pressed to turn OFF. The switch lighting must be activated thru the switch contacts. This Inhibit is recommended for corporate transport operations. Note that Modes 1, 2, 3, and 4 are still enabled Audio Inhibit (Timed) The Timed Audio Inhibit will inhibit most audio output for a configurable period. The default inhibit time is 5 minutes. It will not affect visual alert and warning outputs and will not deselect the terrain display. The switch is momentary and the lamp is illuminated by an output from the EGPWS. This inhibit is recommended for EMS and SAR operations. Configuration options in the Options 3 (Category 18) menu provide a variety of inhibit selections Audio Inhibit (Not Described Above) The Audio Inhibit will inhibit all audio output as long as it is active. It will not affect visual alert and warning outputs and will not deselect the terrain display. The switch is a toggle action, which must be pressed to turn ON and re-pressed to turn OFF. The switch lighting must be activated thru the switch contacts. This Inhibit is NOT RECOMMENDED Low Altitude Mode To allow for helicopter operations that require low altitude flight, a Low Altitude function is enabled with a switch. This function is designed for flight at low altitude in VFR conditions. When this function is engaged Mode 1 is inhibited and, Mode 2 and Mode 4 warning boundaries are significantly reduced and Terrain Advisory look ahead distances are reduced. Low Altitude operation is defined as operation below 500 feet AGL. There are other circumstances where the use of the Low Altitude Mode is appropriate. Those include operation in a high-density metropolitan environment with high rise buildings, operation below 1250 feet AGL when the GPS is not operational or is providing poor accuracy ICS Audio On This discrete input or Command Word bit is to be used with Central Aural Warning Systems to provide handshaking for priority management. When the ICS Audio On is set true, all audio messages that are prioritized below the Warning Terrain and Warning Obstacle messages will be inhibited allowing priority messages to be broadcast. See Category 13 ID s Minimums/Check Height Silence This discrete input will inhibit a Mode 6 "Minimums Minimums" or "Check Height Check Height" callout for 3 minutes. The momentary action switch is normally mounted in the Cyclic lever and is usually found on Eurocopter aircraft. See Category 13 ID s CAGE CODE: SCALE: NONE SIZE: A DWG NO: REV: E SHEET 50

51 MK XXII EGPW Installation Manual FIGURE 2-2 MK XXII EGPWS OUTLINE CAGE CODE: SCALE: NONE SIZE: A DWG NO: REV: E SHEET 51

52 MK XXII EGPW Installation Manual FIGURE 2-3 MK XXII EGPWS MOUNTING TRAY Honeywell P/N CAGE CODE: SCALE: NONE SIZE: A DWG NO: REV: E SHEET 52

53 SECTION III SYSTEM PLANNING CAGE CODE: SCALE: NONE SIZE: A DWG NO: REV: E SHEET 53

54 SECTION III SYSTEM PLANNING 3.1 Introduction This section provides information for selecting features and wiring the electrical interfaces of the MK XXII EGPWS. Sample wiring diagrams for the most commonly used MK XXII EGPWS configurations are provided in Appendix B. Appendix E Section 5.3 groups features (functions) into sets called Categories. This document follows the Category structure of the Appendix E. It provides descriptions of the features and instructions for selecting features and for determining the correct wiring. 1. Make a copy of Appendix E Table 3. Use this table along with Appendix B Fig A1.1, A1.2, and A1.3 to record feature selection and determine the wiring interface. 3.2 System Wiring/ Electrical Interfaces System wiring is broken down into the following main components: - Electrical Interfaces (power and ground) - GPS Antenna - Analog and Digital Inputs - Discrete Inputs - Serial Outputs - Audio Outputs - Discrete Outputs - Configuration Module Many of these inputs and outputs will be defined as the Categories are selected for Configuration Module programming. Appendix E Table 7.1 shows the typical usage for each pin, on the Left (J1), Right (J2) and Upper (J3) connectors Primary Power Input The MK XXII EGPWC requires a primary power input (28 VDC input power) and ground. The Primary power should be connected as follows. Pin Signal *Pin pairs J1-40/J1-60 and J1-40, J1-60 * +28 VDC Input J1-41/J1-61 are internally J1-41, J1-61 * +28 VDC Return shorted to each other. Recommended EGPWC Power Control Device: 3 Amp Delayed Action Circuit Breaker Chassis Ground Chassis ground provides a redundant metal connection and should not be used as a normal current carrying conductor. Chassis ground should be connected as follows: Pin J1-42, J1-53 Signal GND CAGE CODE: SCALE: NONE SIZE: A DWG NO: REV: E SHEET 54

55 Pins J1-42 and J1-53 are both connected to chassis ground internally. It is not necessary to tie them both to ground in the aircraft wiring. Pin J1-53 was made available to provide a convenient way to supply a ground to external equipment. If the OAT probe is not present, nothing needs to be tied to J GPS Antenna A GPS antenna connector is available on the front of the MK XXII EGPWS XX Analog and Digital Inputs The analog and digital inputs to the MK XXII EGPWS are defined as the Categories are selected. Instructions for documenting these interfaces are provided with the Category selection instructions. Section 3.3 contains detailed category configuration information Discrete Inputs Additional information for some discretes is provided within the Category in which they are used. See section Serial Outputs The EGPWC provides for ARINC 453 and ARINC 429 serial outputs. Terrain display data is output on two ARINC 453 channels when the Terrain Awareness display function is enabled. Two ARINC 429 low speed output buses are provided by the EGPWC. The ARINC 429 output data includes: 1. Internal data (data output for test purposes only such as internal logic booleans, Geometric Altitude, and Terrain Clearance information). 2. Alert/Warning status (Voice and Lamp activity can be provided to display systems and flight recorders). 3. Internal mode status. 4. Terrain display messages for TAD cockpit integration. Note: During EGPWS Self Test, the SSM of each output label is set to the Functional Test status code. For category configuration information see section CAGE CODE: SCALE: NONE SIZE: A DWG NO: REV: E SHEET 55

56 3.2.7 Audio Output The audio outputs consist of both an 8-ohm amplifier and a transformer isolated 600-ohm output. Audio output messages are provided as specified in the selected Audio Menu (Category 5) when inputs are valid and the audio inhibit discretes are not active. When audio inhibit is enabled, the output discrete(s) associated with suppressed message(s) are active Discrete Outputs The MK XXII EGPWS provides for up to twelve 0.5 amp (1 amp maximum) Ground/Open discrete outputs. The discrete outputs are defined in Appendix E Category 13. The discrete outputs are optional if the ARINC 429 output data is used for driving the alert/warning annunciators via a EFIS display. Except for fully integrated cockpits, most Aircraft Types do not use the ARINC 429 output data for lamp control. (This data is typically sent to the Flight Recorder.) All outputs to lamps are driven by solid state switches to ground. These outputs can also be used as discrete drivers for other devices (e.g. terrain display switching). See section Output discretes are intended to operate with +28 VDC lamp sources and will not operate with +5 VDC lamp sources Configuration Module The EGPWS aircraft configuration is programmed into a configuration module installed in the aircraft wiring. This Configuration Module is identified as Honeywell part number The configuration module is installed as part of the P2 mating connector backshell and contains electrically reprogrammable memory for configuration storage. By this method the aircraft configuration is stored in the configuration module on the aircraft and each newly installed EGPWS computer does not require operator assisted programming before or during installation. The aircraft configuration in the Configuration Module can be changed at any time by use of the WinViews software, as explained in Section IV. 3.3 Configurable Interfaces The following subsections define configurable interfaces for the EGPWS. Typical interface connection information and diagrams are provided. Use this in conjunction with Appendix E which has detailed interface configuration information. CAGE CODE: SCALE: NONE SIZE: A DWG NO: REV: E SHEET 56

57 3.3.1 Category 1 - Aircraft / Mode Type Select Category 1 specifies the general aircraft type, fixed or retractable gear, tail strike warning selection and terrain approach speed regime. Note: Category 16 will set the engine torque value used for autorotation mode Aircraft / Mode Type The Aircraft Type identifies the aircraft as Manufacture and Model. The aircraft category defines configurable data that control performance. The configurable values are not user defined or controlled. Appendix E Table lists the combinations of Aircraft/Mode Types and identifies the first MK XXII EGPWS version in which the option was available (see the Effectivity entry), and describes the options available with each Aircraft/Model type (see Description column). Note that with the part number , all of the Aircraft Types have been renumbered from earlier versions Instructions 1. Using Appendix E Table 5.3, under Step/category 1 select Aircraft type. Using Table and the instructions below to select ID number for your aircraft type and record that number on Table 5.3 under Ident No. This number will be used for programming the configuration module. 2. Select the aircraft first by gear type, retractable or fixed. Then select the tail strike warning profile from Table below. Tail strike options are Type 0 (No Tail Strike Warning), Type 1 (higher tail profile), Type 2 (lower tail profile), Type 3 (S-92 tail profile) and Type 4 (AW 139 tail profile). Tail Strike Type Description Aircraft Models 0 No Warning MD 900, MD High Tail Profile S-76, AS-332, Bell 407, Bell 212/412,, EH-101, US-101, Agusta Low Tail Profile EC-135, EC-155B,, AS-350, AS-355, AS-365, HH-65, Bell 427, Bell High Tail Profile S-92 4 High Tail Profile AW 139 Table Helo Tail Strike Warning Selection 3. Finally select the operational speed profile for your aircraft and it's normal mission. This sets two approach speed profile values. The first (approach) is the higher end speed an approach will start at. The second (hover), is the lower approach speed of an approach. The Terrain function will inhibit all warnings below this speed. Two speed options are available, fast and slow. The fast profile, which fits most applications and is Honeywell's recommended selection, sets Approach to 100 knots and Hover to 70 knots. The slow profile sets Approach to 90 knots and Hover to 60 knots. The slower range should only be used by aircraft flying slower and who prefer a more conservative warning protection. Speed Profile Cruise Approach Hover Fast >100 Kts Kts <70 Kts Slow >90 Kts Kts <60 Kts Table Helo Operational Speed Profile CAGE CODE: SCALE: NONE SIZE: A DWG NO: REV: E SHEET 57

58 3.3.2 Category 2 Air Input Select Category 2 defines the Air interface. The Air input currently defines 5 analog and 7 digital air data types Instructions 1. Using Appendix E Table 5.3, under Step/category 2 select Air Source. Using Table and x select the ID number for your air data source and record that number on Table 5.3 under Ident No. for step 2. This number will be used during programming of the configuration module. 2. Using Appendix E Tables x, where x is the Air Type number, define the electrical interfaces required to support your Air Type. Using Table x, determine the wiring interconnects and record it on Appendix A Fig A1-2. CAGE CODE: SCALE: NONE SIZE: A DWG NO: REV: E SHEET 58

59 Analog altitude and 500 ohm OAT EGPWS MK XXII J1 Analog Air Computer Uncorrected Barometric Altitude (+) (-) Altitude Out Signal Common Baro Altitude Valid +28V 9 BIT Out +5V Excitation 25 Temp. Input (+) (-) ohm Temperature Probe Chassis Ground 53 Analog-ADC.vsd Cat 2 Uncorrected Baro Altitude Vendor Model ID Altitude Out Common BIT Out Kollsman CIC J1-F J1-G J1-E Collins ADS-65 3 J1-12 J1-13 J1-5 Kollsman CIC J1-A J1-B J1-E Honeywell AZ /12 J1-63 J1-11 J1-12 Honeywell AZ-242/244 11/12 J1A-40 J1A-11 J1A-12 Honeywell AZ /12 J1-J J1-G J1-U Honeywell AZ /12 J1A-78 J1A-10 J1A-34 Honeywell AZ /12 J1A-78 J1A-10 J1A-34 Honeywell AZ /12 J1A-17 J1B-11 J1B-13 NOTE: NOTE: NOTE: NOTE: The connector pin numbers given in the Table above are to the best knowledge of Honeywell EGPWS engineering. Please contact the manufacturer s customer service to confirm your installation. Honeywell AZ-810 should only be used as an analog source if it does not have a digital interface. ID 12 does not require an OAT input, instead a constant temperature of 25 deg C is assumed. Honeywell AZ-242 with part numbers , -709, -710, -712, -713 and 742 have DC Altitude out at pin J1B-17. Part numbers and -711 have DC Altitude out at pin J1A-40. CAGE CODE: SCALE: NONE SIZE: A DWG NO: REV: E SHEET 59

60 Digital ARINC 429 (Cat. 2 ID 5, 1, 6) Air Type 1 (AZ-800 or equivalent) is a low speed, digital ARINC 429 signal having the air data labels 203, 206, 212, and 213. Air Type 5 (AZ-800 or equivalent) is a low speed, digital ARINC 429 signal having the air data labels 203, 204, 206, 212, and 213. Air Type 6 (AZ-800 or equivalent) is a low speed, digital ARINC 429 signal having the air data labels 203, 206, and 213. Air Type 13 is a low speed, digital ARINC 429 signal having the air data label 203 only. Air Type 14 is a high speed, digital ARINC 429 signal having air data labels 203, 206, 212, and 213. If the hardware is capable of transmitting all label sets, the preferred Air Type is 5. If only label 204 is missing, use Air Type 1, and if both labels 204 and 212 are missing use Air Type 6. EGPWS MK XXII J2 ARINC 429 Air ARINC 429 Low Speed Air Bus A B A B ARINC 429 Bus - Hi ARINC 429 Bus - Lo Digital-ADC.vsd Cat 2 Bus 1 Bus 2 Vendor Model ID A B A B Sperry AZ-6XX,-8XX 5* J1B-26 J1B-27 J1B-70 J1B-71 Kollsman CIC * J1-12 J1-13 Kollsman CIC mod 6 1* J2-J J2-K KDC 281 1* P P KDC 481 5* P4811-U P4811- i B&D * J1-27 J1-9 B&D ** 6 8 B&D ** B&D * P P Collins ADC 85/86/850 5* P2-9 P2-10 P2-29 P2-30 Shadin ADC-2000 (s/w mod ) 5* J1-40 J1-22 Thommen AC/AD32*** 5* B C q r NOTE: The connector pin numbers given in the Table above are to the best knowledge of Honeywell EGPWS engineering. Please contact the manufacturer s customer service to confirm your installation. * Category 2, ID 5, 1 or 6 depending on availability of labels 204 and 212. ID 5 is the preferred selection, 1 is next, and 6 is last. CIC air data computers installed without Baro Set pots should be configured as Cat 2 ID 1. ** EGPWS installations with the B&D 2600 ADC should be configured for Cat 2 ID 6 because the B&D 2600 Altitude Rate ARINC 429 label 212 has a poor response to altitude changes and causes nuisance alerts. *** Configure for Low speed ARINC 429 transmitting labels 203, 204, 206, 212, and 213. CAGE CODE: SCALE: NONE SIZE: A DWG NO: REV: E SHEET 60

61 Digital ARINC 575 (Cat. 2 ID 2) Air Type 2 (ADC-80 or equivalent) is a low speed, digital ARINC 575 signal having the air data labels 203, 206, 212, and 213. EGPWS MK XXII J2 ARINC 575 Air ARINC 575 Air Bus A B A B ARINC 575 Bus - Hi ARINC 575 Bus - Lo ARINC575-ADC.vsd Cat 2 Bus 1 Bus 2 Vendor Model ID A B A B Collins ADC-80( ) 2 P3-35 P3-36 Collins ADC-82A B&D J1-27 J1-9 NOTE: The connector pin numbers given in the Table above are to the best knowledge of Honeywell EGPWS engineering. Please contact the manufacturer s customer service to confirm your installation. CAGE CODE: SCALE: NONE SIZE: A DWG NO: REV: E SHEET 61

62 Shadin 2000 (Cat. 2 ID 10) Air Type 10 (Shadin 2000 or equivalent) is a low speed, digital ARINC 429 signal having the air data labels 203, 204, 206, and 212. Total Air Temperature is from a dedicated (EGPWS) 500-ohm probe using +5 volt excitation from the MK XXII EGPWC. EGPWS MK XXII J2 ARINC 429 Air ARINC 429 Low Speed Air Bus A B A B ARINC 429 Bus - Hi ARINC 429 Bus - Lo J1 +5V Excitation 25 Temp. Input (+) (-) ohm Temperature Probe Chassis Ground 53 Shadin2000.vsd Cat 2 Bus 1 Bus 2 Vendor PN ID A B A B ,2,3 10 J2-7 J A-1,2, A-X-S A-X-S A-1-S-7(B212/412) 10 J1-40 J1-22 NOTE: The connector pin numbers given in the Table above are to the best knowledge of Honeywell EGPWS engineering. Please contact the manufacturer s customer service to confirm your installation. CAGE CODE: SCALE: NONE SIZE: A DWG NO: REV: E SHEET 62

63 Digital ARINC 429 Dual IOC Buses (Cat. 2. ID 253 and 254) Air Type 253 (IOC bus or equivalent) is a dual, high speed, digital ARINC 429 signal having the air data labels 203, 206, 212, and 213. Air Type 254 (IOC bus or equivalent) is a dual, high speed, digital ARINC 429 signal having the air data labels 203, 204, 206, 212, and 213. EGPWS MK XXII J2 IOC Buses ARINC 429 High Speed A B 37* 36* A B IOC Bus 1 ARINC 429 High Speed A B 41* 40* A B IOC Bus 2 ARINC429-IOC-1.vsd Cat 2 IOC Bus 1 IOC Bus 2 Vendor Model ID A B A B 253* 254 NOTE: The connector pin numbers given in the Table above are to the best knowledge of Honeywell EGPWS engineering. Please contact the manufacturer s customer service to confirm your installation. * For ID 253 the MK XXII connections at connector J2 are J2-39/38 and J2-21/04. CAGE CODE: SCALE: NONE SIZE: A DWG NO: REV: E SHEET 63

64 3.3.3 Category 3 Position Input Select Category 3 defines the Global Position System bus type and interface. GPS Input selection is available in the following formats: ARINC 429 low speed and ARINC 429 high speed in either ARINC 743 or 743A format, RS-232 Pxpress format, and Internal GPS card Instructions 1. Using Appendix E Table 5.3, Under Step/category 3 select Position Input Source. Using Table and x select ID number for your position input source and record that number on Table 5.3 under Ident No. for step 3. This number will be used during programming of the configuration module. 2. Appendix E Tables x, where x is the position input type number, define the electrical interfaces required to support the position input type. Using Tables x determine the wiring interconnects and record it on Appendix A Fig A1-3. Note: See Category 7 to select GPS Altitude Reference (mean sea level or WGS-84) for ARINC 429 label ARINC 743 Format This option provides the ability to specify the GPS input data format as ARINC 743 instead of the ARINC 743A data format. For ARINC 743A the VFOM is in feet and the HFOM is in nautical miles (nm). For ARINC 743 both VFOM and HFOM are derived from VDOP and HDOP signals and are in meters. Note: Universal UNS-1 C/D/K/M GPS only, output is in ARINC 743 format. NOTE: in -030 software update HDOP (101) and VDOP (102) were added as required labels for Category 3 ID s 0, 1, 4, 5, 10, 11, 12, 13, 252, 253 and GPS Altitude (Label 076) Reference The GPS Altitude (label 076) may be referenced to mean sea level or WGS-84. Determine which reference your GPS position uses and program the GPS Altitude Reference accordingly in Category 7. Note: Universal UNS-1 C/D/K/M GPS only, output the Altitude Label 076 referenced to WGS North-South East-West Velocity labels ID s and 253 are provided to support GPS interfaces that do not provide North-South East-West Velocity labels 166 & 174. ID s 0,1,4,5, and 255 are preferred HT- GPS Compatibility ID 14 is provided to support HT- GPS interfaces that do not provide HDOP, VDOP and Sensor Status labels. CAGE CODE: SCALE: NONE SIZE: A DWG NO: REV: E SHEET 64

65 ARINC 429 BUS (Cat. 3 ID 0,1,4,5,10-13) EGPWS MK XXII J2 ARINC 429 GPS ARINC 429 GPS Bus A B 25 8 A B ARINC 429 Bus - Hi ARINC 429 Bus - Lo ARINC429-GPS.vsd Cat GPS Alt ARINC Bus 1 Bus 2 Vendor Model ID Speed Ref. 743/743A A B A B Collins GNLU-910A Note 4 High MSL 743A LMP-2J LMP-2K Collins GPS /4 2 H/L 2 MSL 743A MP-11A MP-11B UNS UNS GPS- (1075-( )) 1 Low WGS TP-12A TP-12B TP-11A TP-11B UNS GPS-A (1078-( )) UNS GPS-1200 (1080-( )) 0 Low MSL 743A TP-12A TP-12B TP-11A TP-11B UNS-1C (1017-3X-( )) or (1017-4X-( )) UNS-1CSP (1019-3X-( )) (1019-4X-( )) UNS-1D ( ( )) or ( ( )) UNS-1F(w), -1E ( ( )) UNS-1ESP (2019-4X-( )) 1 Low WGS P1-a P1-b 1 Low WGS MP-10J MP-10K 0 Low MSL 743A MP-10J MP-10K MP-4J MP-4K UNS-1K, -1L 1 Low WGS MP-4C MP-4D (1116-3X-( )) or (1116-4X-( )) UNS-1M (1013-4X-( )) 1 Low WGS P2-K P2-L UNS-1MSP (1114-4X-( )) (1114-5X-( )) GNS-XLS ( ) SM04 ( ) SM07 0 Low MSL 743A J101-N5 1 J101-N6 1 GNS-XL (18355-) SM07 0 Low MSL 743A J101-N5 J101-N6 GNS-X / CDU-XLS (NMU) ( ) SM04 0 Low MSL 743A JA-A01 JA-A02 HG2021GBXX/ABXX 1/5 2 H/L 2 MSL 743 J1-38 J1-39 J1-24 J1-25 HG2021GC/GDXX 0/4 2 H/L 2 MSL 743A J1-38 J1-39 J1-24 J1-25 HT/HT /12 H/L MSL 743A MP-C02 MP-C01 FreeFlight (Trimble) 2101 I/O Approach Plus 1 Low MSL 743A 5 J2-16 J2-23 J2-58 J2-57 (81440-XX software ver. 241G) FreeFlight Systems 1203 GPS/WAAS ( X-XXXX) 0/4 2 H/L 2 MSL 743A J1-14 J1-13 J1-18 J1-17 NOTE: The connector pin numbers and software versions given in the Table above are to the best knowledge of Honeywell EGPWS engineering. Please contact the manufacturer s customer service to confirm your installation. 1 The Enhanced GNS-XLS ARINC 429 bus also contains label 2 HG2021G: Pin 21 open = high speed; Pin 21 GND = Low speed; GPS-4000: MP-4C = HiSpd/LoSpd select; FFS 1203: Pin 11 = HiSpd/LoSpd select 3 NOT COMPATIBLE with MK XXII EGPWS a. Honeywell HT-9000 / KLN-89 / KLN-90 / KLN-670 / GNS-XES b. IIMorrow Apollo 2101 CAGE CODE: SCALE: NONE SIZE: A DWG NO: REV: E SHEET 65

66 c. Trimble 2100 / 2101 / TNL8100 d. Universal GPS-950, UNS-1A (1161-X-X), UNS-1B (1190-X-X), UNS Check manufacturer for compatibility with North-South, East-West Velocities. 5 If ARINC 743 is selected (ID 1) the EGPWS computes HFOM/VFOM from HDOP/VDOP. This is done to improve the value of HFOM/VFOM that the EGPWS uses for GPS (743 or 743A) that still assume selective availability is on RS-232 Transmit-Receive, 9600 baud (Cat. 3 ID 3) EGPWS MK XXII J2 RS-232 GPS TX 45 NC RX Receive In RS 232 GPS Bus RX 29 TX Transmit Out CM 28 GND RS232-GPS.vsd GPS Alt ARINC NS RS-232 Vendor Model Ref. 743/743A EW RX TX GND GARMIN GNS430 Software Version 2.21 KLN XXX MSL Note P Chassis MSL OK P Chassis KLN 94 MSL OK P941-6 Chassis NOTE: The connector pin numbers and software versions given in the Table above are to the best knowledge of Honeywell EGPWS engineering. Please contact the manufacturer s customer service to confirm your installation. The KLN 90B is not compatible with EGPWS. The GNS 430 software mod is also applicable to the GPS 400 and GNC 420 units. Check manufacturer for compatibility with North-South, East-West Velocities. CAGE CODE: SCALE: NONE SIZE: A DWG NO: REV: E SHEET 66

67 Dual ARINC 429 BUS (Cat. 3 ID 253 and 255) NOTE: If GPS #2 is not installed in the aircraft, then GPS bus #1 must be connected in parallel to both EGPWS GPS input ports. Non-IOC aircraft can use ID 255 to activate dual GPS inputs for redundancy and improved system availability, but the interface must have dual, High Speed, ARINC 743A GPS, and this cannot be used if using Category 10 ID 5 or Category 11 ID 2. EGPWS MK XXII J2 ARINC 429 GPS ARINC 429 GPS Bus A B 25* 8* A B Hi ARINC 429 Bus 1 Lo ARINC 429 GPS Bus A B 23* 6* A B Hi ARINC 429 Bus 2 Lo ARINC429-DualGPS-1.vsd Cat. 3 GPS Alt ARINC Bus 1 Bus 2 Aircraft Model ID Ref. 743/743A A B A B 253* 743A A NOTE: The connector pin numbers given in the Table above are to the best knowledge of Honeywell EGPWS engineering. Please contact the manufacturer s customer service to confirm your installation. * For ID 253 the MK XXII connections at connector J2 are J2-37/36 and J2-41/40. CAGE CODE: SCALE: NONE SIZE: A DWG NO: REV: E SHEET 67

68 3.3.4 Category 4 Altitude Callouts Category 4 defines the Altitude Callout menu choices and Smart 500 Callout selection. Appendix E Table defines the Altitude Callout Menu options and identifies the first MK XXII EGPWS version in which the option was available (see the Effectivity entry). The Altitude callout menus have selected combinations of Minimums-Minimums or "Check Height", Smart 500, 200, 100, 50, 40, 30, 20, and 10. No altitude callouts may also be selected. Recommended selections are ID 5, 14 or 15. NOTE: For applications that use Category 16 Torque Type ID 0 (No Torque Input), where autorotation will not be detected, it is strongly recommended that a callout menu be selected that provides, as a minimum, 200 and 100 feet such as ID 5 or 15. NOTE: Auto-rotation selection has moved to Category 17. The Altitude Callout menu provides altitude annunciation for descent below predefined altitudes (example: One Hundred is annunciated when descending through 100 feet radio altitude). A Smart 500 foot callout is available that will issue a 500 callout when the aircraft is 500 AGL. This callout is active only during non-precision approaches or when the Glideslope or Localizer deviation is greater than 2 dots. Since normal helicopter operation may include flight at or below 500 feet, a Smart 500 callout is not recommended. Minimums-Minimums or "Check Height" callout can be selected or deselected from these combinations by connecting or not connecting the Decision Height (DH) discrete (J1-33) of Category 8. The AVAD compliant callout menu selections are available for altitudes of 100 feet thru 160 feet although only 100 is normally used. AVAD compliant callouts are required for North Sea Offshore operation and are unique in that they do not latch and so can be retriggered with succeeding transitions thru the callout altitude Instructions 1. Using Appendix E Table 5.3.4, select the preferred Altitude Callout Menu Type (ID) that matches the feature preferences and version (part number) being installed. Using Table select ID number for your Altitude callouts and record that number on Table 5.3 under Ident No. for step 4. This number will be used during programming of the configuration module. 2. If the Minimums-Minimums or "Check Height" callout will be used, use the electrical interfaces (pin-outs) for Radio Altitude Input Select Type (Category 8) shown in Appendix E Table x to generate the installation wiring diagrams. CAGE CODE: SCALE: NONE SIZE: A DWG NO: REV: E SHEET 68

69 3.3.5 Category 5 Audio Menu Select Category 5 defines a basic Audio Menu (ID 128 or ID 129) for most Helicopters and a special Audio Menus (ID 251 or ID 254) for S-76 factory installations and (ID 252, ID 253 and ID 255) designed to support S-92 Helicopters Instructions 1. Using Appendix E Table 5.3, Under Step/category 5 select Audio Menu. Using Table 5.3.5, select ID number for your audio menu and record that number on Table 5.3 under Ident No. This number will be used for programming the configuration module. 2. Audio Menu has no bearing on Aircraft wiring interface. CAGE CODE: SCALE: NONE SIZE: A DWG NO: REV: E SHEET 69

70 3.3.6 Category 6 Terrain Display Select Category 6 defines the Terrain Display options available. Appendix E Table defines the Terrain Display Select options (Display Configuration Group Tables, Display Input Control Group Tables and Output 429 Bus Group Tables) and identifies the first MK XXII EGPWS version in which the option was available (see the Effectivity entry). Note: TA&D mode enabling/disabling is controlled by Category 6. Chose ID 2 for aircraft without TA&D Instructions 1. Using Appendix E Table and x select the Terrain Display Select Type (ID) that matches the aircraft configuration, feature preferences and version (part number) being installed. Record the ID number for the Terrain Display Select Type from Appendix E Table 5.3 under the Ident No. heading for Step (Category) Using the ID number Table as x, go to the Table x. The electrical interfaces (pin-outs) for the Display are shown in the Display Configuration Group, Display Input Control Group, and Output 429 Bus Group, Table x are used to generate the installation wiring diagrams. Determine the wiring interconnects and record it on Appendix A Fig A1-1. Figure is an example of single tube Wx/Terrain display wiring connections TAD Selection The Terrain Awareness & Display feature consists of a Terrain Awareness Alerting feature and a Terrain Awareness Display feature. The Terrain Awareness Alerting feature continuously computes terrain clearance envelopes ahead of the aircraft and issues alerts if the boundaries of these envelopes conflict with terrain elevation data in the terrain database. The Terrain Awareness Display feature displays the terrain data relative to aircraft altitude. A False entry in Appendix E Table for TAD Disable indicates that TA&D is ENABLED (the Disable is disabled). CAGE CODE: SCALE: NONE SIZE: A DWG NO: REV: E SHEET 70

71 Terrain Display Configuration Group This option provides the ability to specify the type of Terrain Display compatible with the aircraft configuration. A definition of each of the entries in the Display Configuration Group tables is provided in the table below. Function Value Reference section Display Type Display manufacturer, model, etc. Sweep Type The type of sweep used for terrain data (fan, standard, etc.) Auto Pop Up Category 7, Options Select Group #1 TA&D Alternate Pop Up: False TA&D Alternate Pop Up: True The TA&D Alternate Pop Up is set to The TA&D Alternate Pop Up is set to False or True in Category 7. If False, False or True in Category 7. If True, Pop Up behavior for the terrain Pop Up behavior for the terrain display is described here. display is described here. Peaks Mode Category 7, Options Select Group #1 Manual select See Note 1 Peaks Enable: False Peaks Enable: True Peaks Enable is set to False or True in Category 7. The effect of setting it to False is described here. Peaks Enable is set to False or True in Category 7. The effect of setting it to True is described here. Describes if/when terrain display(s) can be manually selected Manual deselect Describes if/when terrain display(s) can be manually deselected Auto Defines if the display data is automatically scaled and, if so, the scale used (such as 10 nautical miles) Moving Marker Indicates whether or not a moving marker is provided Overlay Page Describes where TERR and Peaks Elevations overlays will be located on the display screen. Display Priority Indicates the priority for displaying terrain data. For example: Standard (PWS Warn, Terrain Warn, PWS Caution, Terrain Caution) Searchlights Display bus type Defines the display bus type KC Picture Bus (ASPB), Honeywell Picture Bus or ARINC 453. TX453-1 CONNECT TO: A = J1-58 B = J1-59 Indicates the correct connection for these pins TX453-2 CONNECT TO: A = J1-56 B = J1-57 Indicates the correct connection for these pins Notes: 1 Peaks Mode (Not Available) or (Elevations via overlay) shown here. Peaks mode Not Available means that this display type cannot display Peaks Mode. Table Definition of Display Configuration Group Tables (Appendix E Section 5.3.6) CAGE CODE: SCALE: NONE SIZE: A DWG NO: REV: E SHEET 71

72 #1 A B #2 A B 453 #1 A B 453 #2 A B Gnd DSD #1 Gnd DSD #2 Gnd Gnd J2-37 J2-36 J2-41 J2-40 J1-58 J1-59 J1-56 J1-57 J1-51 J1-32 J1-31 J1-54 WX System R/T 429 IN 453 OUT ARINC 429 RANGE BUS ARINC 453 TERRAIN BUS #1 Terrain Pop-Up Discrete Output Display Select Discrete #1 Input TERR ON BRT/ DIM/ TEST DISPLAY RELAY Momentary Terrain Display Select #1 Discrete Output FIGURE Single Tube Wx/Terrain Display Wx/TERR Display System A B 429 Output Bus A B 453 WX / TERR BUS TERRAIN POP-UP TERRAIN SELECTED 28 VDC * Display relay specifications: - 4PDT - Continuous Duty Cycle - Pickup Voltage: 13.5 Vdc Max. - Dropout Voltage: Vdc - Coil Resistance: nominal 500 Ohms 28 Vdc) - Coil Rating: 26.0 Vdc (nominal) 34 Vdc (max.) - Contact V drop: < rated load - Contact current rating: 2 Amps 28 Vdc CAGE CODE: SCALE: NONE SIZE: A DWG NO: REV: E SHEET 72

73 Display Input Control Group This input bus is connected to the display (or display controller) and transmits settings, Display Mode, and Display status to the MK XXII EGPWC Output 429 Bus Group This output bus is commonly connected to EFIS and/or EICAS displays and Flight Recorders and transmits MK XXII EGPWC alert, fault, and mode status to other systems Sample Display Schematics Honeywell GNS-XLS Honeywell KMD 540 / 550 / 850 Honeywell Grimes TRA-45A Honeywell Grimes MFRD Universal MFD-640 Honeywell Primus UDI with Avtech DSU Collins IND-300 UDI with Avtech DSU Honeywell Bendix PPI-4B Garmin MX-20 Collins Pro-Line II Honeywell Bendix EFS-40/50 Collins WXI-701/711 Honeywell Primus 440/660/880 Integrated Honeywell Bendix RDR 2000 / IN182A Collins Pro-Line IV Honeywell Bendix EFS-10 Honeywell SPZ 7600 / SG-705 Honeywell SPZ 8000 / SG-811 CAGE CODE: SCALE: NONE SIZE: A DWG NO: REV: E SHEET 73

74 HONEYWELL MK XXII H-EGPWS XX P1 MK XXII CATEGORY 6 ID 0, 18-20, 230, 242 (KCPB) All Aircraft NOTE 5 Bendix KMD-540 Honeywell GNS-XLS Honeywell TRA-45A NOTE 7 Honeywell MFRD Universal MFD-640 J3001 J1 J101 J2 ARINC 453 OUTPUT (A) ARINC 453 OUTPUT (B) P2 P NOTE 3 P Q Q6 09 * * * See Note 8 (A) KCPB BUS (B) Shield (*= Chassis) 02 Q5 39 Un-terminated (A) RANGE INPUT (B) (A) RANGE INPUT (B) P P P J3 28 N N6 34 * * * See Note 8 (A) ARINC 429 TX (B) Shield (*= Chassis) (A) ARINC 429 OUTPUT (B) P P See Note 8 (A) ARINC 429 RX (B) Shield NOTES: 1. All stranded wire shall conform to MIL-W-22759/16 or equivalent. All shielded wire shall conform to MIL-C spec. or equivalent. All wires are 22 gauge unless otherwise noted. 2. Connect the shield to aircraft chassis or unit pin with as short a conductor as practical. 3. Use M17/00002 wire per MIL-C-17/176D spec. or equivalent for KCPB interface. 4. Refer to the appropriate Installation Manual for configuration setup instructions. 5. The KMD 540 must have the KAC 502 EGPWS card installed for the Terrain Display function. 6. The Avidyne FlightMax is not compatible with MK XXII computers. 7. GNS-XLs Enhanced PN XXXX SM04 or later. 8. The Universal MFD 640 has configurable inputs & outputs. See Universal Installation Manual for details. CAGE CODE: SCALE: NONE SIZE: A DWG NO: REV: E SHEET 74

75 HONEYWELL MK XXII H-EGPWS XX TERR ON MK XXII CATEGORY 6 ID 0, 18, 230, 242 (KCPB) Primus radar BRT/DIM ANN. POWER Momentary Action Annunciator Press To Test ARINC 453 OUTPUT (A) ARINC 453 OUTPUT (B) P P NOTE 3 P J J2 AVTECH DSU (H) ARINC 453 (C) 2 Terrain Select RANGE INPUT (A) RANGE INPUT (B) RANGE INPUT (A) RANGE INPUT (B) P P P P Terrain Status (A) ARINC 429 (B) STBY UDI SHLD RED+ RED - GRN - GRN+ BLUE+ BLUE - SEL+ SEL - SVR+ SVR - SHR+ SHR - RANGE0 - IN RANGE1 - IN RANGE2 - IN RANGE3 - IN UDI GND J P P P P P P P P 90, 100, 200, 300, 300SL, 400, 500, AVQ30 450, 650 w/o Lightening, , 650 w/ Lightening, 660, 700, 870, NC 7 N J E S U T D H R F M K L A C P B V G HONEYWELL PRIMUS SERIES WXR INDICATOR (UDI PORT) NOTES: 1. All stranded wire shall conform to MIL-W-22759/16 or equivalent. All shielded wire shall conform to MIL-C spec. or equivalent. All wires are 22 gauge unless otherwise noted. 2. Connect the shield to aircraft chassis or unit pin with as short a conductor as practical. 3. Use M17/00002 wire per MIL-C-17/176D spec. or equivalent for KCPB interface. 4. Refer to the appropriate Installation Manual for configuration setup instructions. CAGE CODE: SCALE: NONE SIZE: A DWG NO: REV: E SHEET 75

76 HONEYWELL MK XXII H-EGPWS XX P1 TERR ON MK XXII CATEGORY 6 ID 0, 18, 230, 242 (KCPB) Collins Radar BRT/DIM ANN. POWER Momentary Action ARINC 453 OUTPUT (A) ARINC 453 OUTPUT (B) P NOTE 3 P J J2 (H) ARINC 453 (C) AVTECH DSU Terrain Select RANGE INPUT (A) RANGE INPUT (B) P P Terrain Status (A) ARINC 429 (B) RANGE INPUT (A) RANGE INPUT (B) P SSBY 2.58 MHz H 2.58 MHz L SHLD RED + RED - GRN - GRN+ BLUE+ BLUE - RADAR BLK ALPHA_BLNK TGT ENABLE SHLD 2 SVR+ SVR - SHR+ SHR - RANGE0 - IN RANGE1 - IN RANGE2 - IN RANGE3 - IN UDI GND J J P P P P 37-Pin DSUB 50-Pin DSUB P NC 4 COLLINS IND-220, IND-270, IND-270A, IND-300 NOTES: 1. All stranded wire shall conform to MIL-W-22759/16 or equivalent. All shielded wire shall conform to MIL-C spec. or equivalent. All wires are 22 gauge unless otherwise noted. 2. Connect the shield to aircraft chassis or unit pin with as short a conductor as practical. 3. Use M17/00002 wire per MIL-C-17/176D spec. or equivalent for KCPB interface. 4. Refer to the appropriate Installation Manual for configuration setup instructions. 5. GPS Ground Speed required before Collins radar display will show EGPWS terrain picture. P P P P CAGE CODE: SCALE: NONE SIZE: A DWG NO: REV: E SHEET 76

77 CAGE CODE: SCALE: NONE SIZE: A DWG NO: REV: E SHEET 77

78 CAGE CODE: SCALE: NONE SIZE: A DWG NO: REV: E SHEET 78

79 EGPWS Terrain Display Select (out) ARINC 453 Video #1 A B Terrain Display Select (in) ARINC 429 #1 A B ARINC 429 #2 A B Terrain Display Select (in) ARINC 453 Video #2 A B Terrain Display Select (out) MK XXII or later. MK XXII or later. J J J V EGPWS PWR Bus To WX R/T TERR momentary ON Lamp Test 28V Lamp Dimming Bus TERR ON momentary To WX R/T 28V EGPWS PWR Bus Note: For interface and operation of the Collins Proline II displays see Collins SIL Collins Wx Pnl WXP-840/850 A B ARINC 453 Picture 11 Remote ON A ARINC 429 B A B Collins Wx Pnl WXP-840/850 ARINC Remote ON A ARINC 453 Picture B CollinsP2.vsd Collins ProLine II with WXP-840/850 Cat. 6 - ID's 3,5,& 6 CAGE CODE: SCALE: NONE SIZE: A DWG NO: REV: E SHEET 79

80 CAGE CODE: SCALE: NONE SIZE: A DWG NO: REV: E SHEET 80

81 RS-181A/811A RS-841A/861A ART 2000/2100 RTA-4A/B CAGE CODE: SCALE: NONE SIZE: A DWG NO: REV: E SHEET 81

82 MFD SYMBOL GENERATOR P465 BENDIX/KING SG 465 2B 68 R/T T RANSMITT ER 429 A OUT 81 R/T TRANSM IT TER 429 B OUT DA TA B US A IN DAT A BUS B IN P 465 1B 37 T ERRAIN PO P-UP DISCRETE IN P 465 1A 22 T ERRA IN S ELECTE D DISCRE TE IN NOT ES : 1. US E M 17/ S HIELDE D WIRE OR QUA DRA X CA BLE FOR THE 453 DA TA BUS A ND T HE KCP B. 2. REF ER TO THE WEATHER RADAR SECTION O F T HIS M ANUAL (3.13) FO R THE COMPLETE INTERFACE TO THE BENDIX /KING WEATHER RADARS. 3. THE CA TE GORY 6 DISPLA Y TY PE ID 10 (INT EGRA TE D E FIS 40/50) IS THE REQUIRED CONFIGURATION. THE CATEGORY 13 I/O DISCRETE T YPE ID 1 (LAMP F ORMAT 2) IS THE PREF ERRED CONF IGURATION. 4. THIS CONF IGURATION IS NO T SUPPORT ED PRIOR T O EGPWS CO MPUTE R P ART NUM BE RS: MARK VI EGPW S MARK VI EG PWS W/INTERNAL G PS MARK VIII EGPWS MA RK VIII E GPW S W/INTERNA L G PS SE E NOT E 1. A NNUNCIATOR PRESS -TO-TE S T ANNUNCIATOR DIMMER BUS TE RRAIN O N (MOM E NTA RY) SE E NOT E 1. TERRAIN INHIBIT EGPWS F AIL (ALT ERNATE ACTION) SEE NOTE 1. S EE NOTE V DC A V IONICS PO WER SE E NOT E 1. S E E NOTE 1. E GP WS ANNUNCIATOR DIMM ER B US A NNUNCIAT OR P RESS -T O-TE ST BE NDIX/K ING WEAT HER RADAR R/T SE E NO TE CO NTROL BUS 1A IN 429 CONTRO L BUS 1B IN 453 DAT A B US A OUT 453 DATA BUS B O UT MARK VI/VIII ENHANCED GRO UND PROXIMITY W ARNING COM PUTER J2 NO. 2 DIS PL AY RANGE 429 A IN 41 NO. 1 DISPLAY RANG E 429 A IN 37 NO. 1 DIS P LAY RANGE 429 B IN 36 NO. 2 DISPLAY RANGE 429 B IN 40 J1 KCPB A OUT 58 S E NOTE 3. KCP B B OUT 59 TERRAIN POP -UP OUT VDC POWER IN VDC POWER IN 4 0 T ERRAIN SELECT RELAY OUT 54 TERRAIN INOP 55 TE RRAIN INHIBIT S WIT CH IN 12 TE RRA IN SELE CT SW ITCH IN 32 CAGE CODE: SCALE: NONE SIZE: A DWG NO: REV: E SHEET 82

83 HONEYWELL MK XXII H-EGPWS XX P1 RADAR IND RDR TERR MK XXII CATEGORY 6 ID 12 Collins WXI BRT/DIM ANN. POWER TERRAIN SELECT (IN) Momentary Action Annunciator Press To Test Collins WXI-701 RADAR IND CPN XXXX TERRAIN RELAY (OUT) 54 ARINC 453 OUTPUT (A) 58 ARINC 453 OUTPUT (B) 59 P SEE NOTE 3,5 D3 D1 C3 C1 B3 B1 A3 A1 NC NO D2 C2 B2 A2 X1 P J1 WXI (H) T/R Bus (L) 70-Ohm termination P2 RELAY X2 15 RT On/Off 1 RANGE INPUT (A) RANGE INPUT (B) P P (A) Control Bus A (B) P RANGE INPUT (A) RANGE INPUT (B) VDC RELAY POWER WRT-XXX WX RT SYSTEM P 59J1 8 9 (P) T/R Bus (N) 6B RT On/Off 1? NOTES: 1. All stranded wire shall conform to MIL-W-22759/16 or equivalent. All shielded wire shall conform to MIL-C spec. or equivalent. All wires are 22 gauge unless otherwise noted. 2. Connect the shield to aircraft chassis or unit pin with as short a conductor as practical. 3. Use M17/00002 wire per MIL-C-17/176D spec. or equivalent for ARINC 453 interface. 4. Refer to the appropriate Installation Manual for configuration setup instructions. 5. Some installations may require a 75-ohm resistor for termination of the ARINC 453 video bus. P? (A) Control Bus A (B) CAGE CODE: SCALE: NONE SIZE: A DWG NO: REV: E SHEET 83

84 HONEYWELL MK XXII H-EGPWS XX P1 RADAR IND RDR TERR MK XXII CATEGORY 6 ID 13 and 15 WI-440/660/ BRT/DIM ANN. POWER TERRAIN SELECT (IN) Momentary Action HONEYWELL PRIMUS RADAR IND HPN X1X TERRAIN RELAY (OUT) 54 ARINC 453 OUTPUT (A) 58 ARINC 453 OUTPUT (B) 59 P SEE NOTE 3, D3 D1 C3 C1 B3 B1 A3 A1 NC NO D2 C2 B2 A2 X1 Annunciator Press To Test P 63J1 M L W WI-880/660/650/440 (P) WXPD BUS (N) Shield P2 RELAY X2 X EGPWS SELECT RANGE INPUT (A) RANGE INPUT (B) P P F G (P) SCI BUS (N) T Shield RANGE INPUT (A) RANGE INPUT (B) VDC RELAY POWER WU-880/660/440 WX RT SYSTEM P 59J1 3 4 (P) CENTER WXPD BUS (N) 72 NOTES: 1. All stranded wire shall conform to MIL-W-22759/16 or equivalent. All shielded wire shall conform to MIL-C spec. or equivalent. All wires are 22 gauge unless otherwise noted. 2. Connect the shield to aircraft chassis or unit pin with as short a conductor as practical. 3. Use M17/00002 wire per MIL-C-17/176D spec. or equivalent for ARINC 453 interface. 4. Refer to the appropriate Installation Manual for configuration setup instructions. 5. Some installations may require a 75-ohm resistor for termination of the ARINC 453 video bus. 6. Radar Indicators must be modified from part number x0x to -x1x for EGPWS Terrain display. 7. Not Compatible with Category 2 RS-422 Air interface. P 71 (P) LEFT SCI BUS (N) CAGE CODE: SCALE: NONE SIZE: A DWG NO: REV: E SHEET 84

85 HONEYWELL MK XXII EGPWS XX RANGE INPUT (A) RANGE INPUT (B) J P non-integrated PROLINE 4 INTERFACE MK XXII EGPWS Category 6, ID 235 P P1 3* 4* #1 - IOC (ICC-4000) * ICC-851A pins 13 & 14 LA-GP-5 bus (Label 155) RANGE INPUT (A) RANGE INPUT (B) P P P1 3* 4* #2 - IOC (ICC-4000) * ICC-851A pins 13 & 14 RA-GP-5 bus (Label 155) J1 MOM TERR SELECT #1 32 ARINC 453 OUTPUT (A) 58 ARINC 453 OUTPUT (B) 59 P +28 VDC TERR 70Ω* * In the OEM installations a single weather radar 453 bus enters the left MFD, passes through, and is terminated (70 ohm) at the right MFD. For EGPWS installations break the 453 radar bus between the MFDs, install switching relays, and wire one relay to each MFD. The right MFD connection is moved to remove the 70 ohm termination at that MFD. To allow proper radar termination when EGPWS is passing through the relays, the radar picture bus has a 70 ohm resistor (added externally). P P1 8D #1 - MFD H - ARINC D L - (unterminated) 10D L - (70 ohm terminated) TERR RLY SELECT # VDC P1 #1 - WXR +28 VDC TERR P 4 29 H ARINC 453 OUT L MOM TERR SELECT #2 31 ARINC 453 OUTPUT (A) ARINC 453 OUTPUT (B) P P P1 8D #2 - MFD H - ARINC D L - (unterminated) 10D L - (70 ohm terminated) TERR RLY SELECT # VDC CAGE CODE: SCALE: NONE SIZE: A DWG NO: REV: E SHEET 85

86 HONEYWELL MK XXII H-EGPWS XX P1 RADAR IND RDR TERR MK XXII CATEGORY 6 ID 246 EFIS BRT/DIM ANN. POWER TERRAIN SELECT (IN) Momentary Action Annunciator Press To Test EFIS 10 B/K SG 101A/B SYM GEN (A) PICTURE OUTPUT (B) P NOTE 3, 5 D3 D1 C3 C1 B3 B1 A3 A1 NC NO D2 C2 B2 A2 X1 P SG-101A SG-101B P P1A-48 P P1A-49 (H) ARINC 453 (C) TERRAIN RELAY (OUT) 54 RELAY X2 (A) RANGE INPUT (B) P P P P P1B-52 P P1B-04 (A) ARINC 429 (B) (A) RANGE INPUT (B) P +28 VDC RELAY POWER WX RT SYSTEM RS-181A/811A RS-841A/861A ART 2000/2100 RTA-4A/B P P1001 P X 9 A P BP 2D 3D (H) ARINC 453 (C) P ZA G 2 3 3B 4B (A) ARINC 429 (B) NOTES: 1. All stranded wire shall conform to MIL-W-22759/16 or equivalent. All shielded wire shall conform to MIL-C spec. or equivalent. All wires are 22 gauge unless otherwise noted. 2. Connect the shield to aircraft chassis or unit pin with as short a conductor as practical. 3. Use M17/00002 wire per MIL-C-17/176D spec. or equivalent for ARINC 453 interface. 4. Refer to the appropriate Installation Manual for configuration setup instructions. 5. Some installations may require a 75-ohm resistor for termination of the ARINC 453 video bus. 6. NO TRAFFIC AVAILABLE WITH EFIS 10. CAGE CODE: SCALE: NONE SIZE: A DWG NO: REV: E SHEET 86

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90 DC-811 LEFT DISPLAY CONTROLLER Controller Serial J H L HONEYWELL SPZ 8000 Cat. 6 - ID 255 H L J DC-811 RIGHT DISPLAY CONTROLLER Controller Serial TERRAIN POP UP 31 'WX / TERR' pushbutton GND 23 1 H L J MK XXII EGPWS DISPLAY BUS #1 TERRAIN POP UP (HPN XX) DISPLAY BUS #2 J H L TERRAIN POP UP 'WX / TERR' pushbutton GND SG-811 LEFT SYMBOL GENERATOR Controller Serial * EFIS ARINC 429 INPUT FROM EGPWS CAN BE PROGRAMMED FOR CH 1 (J2A-64/65) OR CH 7 (J1B-4/5). EGPWS ARINC 429 * CHAN. 7 WX/TERR PICTURE BUS IN J1A J1B 4 5 * PROG PIN * OPEN = CH 7 GND = CH 1 NOTE: Service Bulletin modifies to -314 and adds EGPWS interface. 1 2 H L H L H L H L H L J2 H L H L H L H L h J ARINC 429 OUTPUT BUS SERIAL BUS RANGE INPUT Left Picture Bus Radar R/T WR-800 (HPN MI ) Right Picture Bus Picture Bus Shield J_ L M g H L J1A J1B SG-811 RIGHT SYMBOL GENERATOR Controller Serial * EFIS ARINC 429 INPUT FROM EGPWS CAN BE PROGRAMMED FOR CH 1 (J2A-64/65) OR CH 7 (J1B-4/5). EGPWS ARINC 429 CHAN. 7 * PROG PIN 111 * * OPEN = CH 7 GND = CH 1 WX/TERR PICTURE BUS IN NOTE: Service Bulletin modifies to -314 and adds EGPWS interface. DOUT #0 9 L-EFIS +28 VDC R-EFIS +28 VDC 9 DOUT #0 Radar Serial PGM PIN GND H L H L A T Left EFIS Control Bus Right EFIS Control Bus V B H L H L Radar Serial PGM PIN GND PROG PIN 110 EGPWS INSTALLED +28V GND J2A L-EFIS +28 VDC H L J_ Radar Controller * * * WI-870 Indicator pins J1-F/G (HPN XXX ) * WC-870 Controller pins J4-A/B (HPN XXX ) * WC-874 Controller pins J4-A/B (HPN XXX ) R-EFIS +28 VDC J2A PROG PIN 110 EGPWS INSTALLED +28V GND PN PN i j CAGE CODE: SCALE: NONE SIZE: A DWG NO: REV: E SHEET 90

91 3.3.7 Category 7 Options Select Group #1 Category 7 enables/disables the following Options: Steep Approach (not available in MK XXII), TA&D Alternate Pop Up, Peaks Mode, Obstacle Awareness, Bank Angle, WOW Reversal, and GPS Altitude Reference. Appendix E Table E defines the Options Select group and identifies the first MK XXII EGPWS version in which the option was available (see the Effectivity entry). Note: Disabling peaks mode is not an option in the Mk XXII and for Helicopters Steep Approach and TA&D Alternate Pop Up should always be set to False Instructions 1. Review the sections below for information on Steep Approach, TA&D Pop Up, Peaks Mode, Obstacle Awareness, Bank Angle, WOW Reversal, and GPS Altitude Reference 2. Using Appendix E Table 5.3.7, select the preferred Category 7 (Options Select Group #1) ID that matches the aircraft configuration, features preferences and version (part number) being installed. Record the ID number for the Options Select Group #1 from Appendix E Table 5.3 under the Ident No. heading for Step (Category) 7. This number will be used for programming the configuration module Steep Approach (Not Available in the Mk XXII) This feature is not applicable to MK XXII TA&D Alternate Pop-up The Display Configuration Group Type (Category 6) defines default and alternate definitions for EGPWS alert Pop-up behavior, when no terrain displays are active or when a combination of terrain and non-terrain displays are active. (Some Display Configuration Group Types do not support an Alternate Pop-up definition.) Category 7 enables/disables TA&D Alternate Pop Up. For Helicopters TA&D Alternate Pop Up should always be set to False. Pop-Up and Alternate Pop-Up Defines whether EGPWC visual alerts will pop-up on displays not currently displaying terrain data. The entries are: False True Selected terrain-compatible displays will switch to display surrounding terrain data. (Some displays will only Pop Up when display is in the proper mode.) EGPWS alerts will not pop-up in terrain-compatible displays Peaks Mode Peaks mode is an alternate means of displaying terrain data. The standard terrain display mode displays terrain relative to the aircraft altitude that is within the aircraft envelope (the terrain is above or not more than 2000 feet below the aircraft). The terrain display is typically blank during the cruise portion of a flight. Peaks CAGE CODE: SCALE: NONE SIZE: A DWG NO: REV: E SHEET 91

92 mode provides increased situational awareness by providing the same information as the standard display mode as well as displaying terrain outside of the aircraft envelope and the highest and lowest elevations of terrain displayed. Peaks mode displays terrain based on the absolute terrain elevations. Disabling peaks mode is not an option in the Mk XXII. Peaks Mode is always selected Obstacle Awareness The Obstacle Awareness feature adds a database of (man-made) obstacles that are at least 100 feet taller than the surrounding terrain and continuously computes obstacle clearance envelopes ahead of the aircraft, issuing alerts if the boundaries of these envelopes conflict with obstacle elevation data in the obstacle database (similar to the Terrain Awareness function). Obstacle data is currently available for North America and parts of Europe and the Caribbean. Not all obstacles will be contained in the database. Category 7 enables Obstacle Awareness if TA&D is not disabled in Category 6. Note: TAD must be enabled if Obstacle Awareness is enabled. Honeywell strongly recommends the selection of Obstacle Awareness for helicopters Bank Angle Callout Enabling The Bank Angle feature provides protection for over banking during maneuvering on approach or climb-out and while at altitude. The Bank Angle callout can be enabled or disabled as appropriate for each installation WOW Reversal (Weight-On-Wheels) The WOW discrete input is defined in Category 13. The Category 7 control is used to reverse the defined logic to match aircraft wiring, if necessary. +28 VDC WOW discrete (J1-37) active position: WOW Reversal WOW Discrete (Category 13) False True WOW Discrete = +28V WOW Not WOW WOW Discrete = Open (or GND) Not WOW WOW Ground seeking WOW discrete (J1-18) active position: WOW Reversal WOW Discrete (Category 13) False True WOW Discrete = GND WOW Not WOW WOW Discrete = Open (or +28V) Not WOW WOW GPS Altitude Reference The GPS Altitude (ARINC 429 label 076, Category 3) may be referenced to mean sea level (MSL) or WGS- 84. Determine which reference the GPS position uses and set the GPS Altitude Reference accordingly in this Category. If using the internal GPS card select MSL. CAGE CODE: SCALE: NONE SIZE: A DWG NO: REV: E SHEET 92

93 3.3.8 Category 8 Radio Altitude Input Select Category 8 defines the Radio Altitude and Decision Height interface Instructions 1. Using Appendix E Tables 5.3, under Step/category 8 select Radio Altitude Type. Using Table and x select ID number for your Radio Altimeter and record that number on Table 5.3 under Ident No. for step 8. This number will be used during programming of the configuration module. 2. Appendix E Tables x, where x is the Radio Altimeter Type number, define the electrical interfaces required to support each Radio Altimeter. Using Table x determine the wiring interconnects and record it on Appendix A Fig A The Decision Height discrete (J1-33, Category 8) indicates to the MK XXII EGPWC whether the aircraft is above or below the selected Decision Height. This discrete is typically connected to the Decision Height output on the Radio Altimeter indicator. If the Minimums-Minimums callout is not wanted the Decision Height discrete should be left open. Using Table x determine the wiring interconnects for Decision Height and record it on Appendix A Fig A Digital Radio Altitude Interface (Cat. 8 ID 2) EGPWS MK XXII J2 ARINC 429 Radio Altitude A B 21 4 J1 DH Discrete (Gnd) 33 Radio Altimeter R/T A ARINC 429 B Radio Altimeter Indicator DH Vendor Model Indicator R/T R/T Indicator SCALE DH A B Collins RAC-870 ALI-55 ARINC 429 P1-V P1-2 P1-3 Honeywell ALA-52A ARINC 429 MP-B2 MP-B3 Honeywell KRA 405B KNI-415/416 ARINC 429 M B C CAGE CODE: SCALE: NONE SIZE: A DWG NO: REV: E SHEET 93

94 Analog Radio Altitude Interface (Cat. 8 ID 0,1,3,4,5) EGPWS MK XXII J1 Radio Altimeter R/T Analog Radio Altitude (+) (-) ARINC 552, ALT 55, RT-200/300 Radio Altitude Valid +28V 29 Valid Radio Altimeter Indicator DH Discrete (Gnd) 33 DH Vendor Model Cat. Indicator R/T R/T Indicator ID DH + - Valid Collins ALT 55 (3) ALI-55 1 P1-V P1-57 P1-59 P1-49 Collins ALT 50 5 P1-57 P1-59 P1-49 Honeywell HG7502 JG1072( ) 0 P1-e P4-47 P4-46 P4-27 Honeywell RT-221/300 (1) RA P1-F P1-X P1-N P1-Y Honeywell RT-220/300 (2) RA P1-F P1-N P1-W P1-Y Honeywell KRA-405 KNI-415/416 4 M P1-B P1-g S Honeywell KRA 405B KNI-415/416 4 M E X j KRA 405B (2) 3 G Z j KRA 405B 0 Z G j Honeywell ALA-51A INA-51( ) 0 P2-e P1B-47 P1B-46 P1B-12 Collins 860F-1/4 339H-1/-2 0 P1-e P1B-47 P1B-46 P1B-12 TRT AHV P1B-47 P1B-46 P1B-12 Honeywell APN-209 RT-1115/ID-1917 NOTE 1: The following RT-300 part numbers meet ARINC 552 for the Auxiliary Output: , -906, -912, -916, -917, -918, - 922, -926, -928, -932, -936, -937, and Some RT-221 s are also compatible, consult your Honeywell representative. NOTE 2: This is the precision output from the R/T. Note the + and signals are swapped to convert the 4mV to +4mV. RT-300 (-9X1, - 9X3,-904, -9X5) should also use the Precision Output, same as the RT-220. NOTE 3: The ALT-55 provides compromised EGPWS performance due to the average altitude tracking algorithm employed Digital ARINC 429 Dual IOC Buses (Cat. 8 ID ) Radio Altitude Type 251 (IOC bus or equivalent) is a dual high speed, digital ARINC 429 signal having labels 164 and 170. Radio Altitude Type 253 (IOC bus or equivalent) is a dual high speed, digital ARINC 429 signal having label 164 and a analog discrete DH input. Radio Altitude Type 254 (IOC bus or equivalent) is a dual high speed, digital ARINC 429 signal having labels 164, 170 and 370. Radio Altitude Types 252 & 255 (IOC bus or equivalent) are a dual high speed, digital ARINC 429 signal having labels 164 and 370. For interface description see paragraph Air Type. CAGE CODE: SCALE: NONE SIZE: A DWG NO: REV: E SHEET 94

95 3.3.9 Category 9 Navigation Inputs Select Category 9 selects the Glideslope and Localizer Deviation interfaces and Glideslope Validity and ILS Tuned discretes. Appendix E Table defines the Category 9 Navigation Inputs Select options (called Navigation Inputs Select Types) and identifies the first MK XXII EGPWS version in which the option was available (see the Effectivity entry) Instructions 1. Using Appendix E Tables 5.3, and x as described above, select the Navigation Input Select Type that matches the aircraft configuration, feature preferences, and version (part number) being installed. 2. Record the ID number for the Navigation Inputs Select Type from Appendix E Table 5.3 under the Ident No. heading for Step (Category) 9. This number will be used during programming of the configuration module. 3. Using the Navigation Inputs Select number from Appendix E Table as x, go to Appendix E Table x..The electrical interfaces (pin-outs) for the Navigation Inputs Select Type are shown in Appendix E Table x and are used to determine the wiring interconnects and record it on Appendix A Fig A1-1. Navigation Inputs Select (Glideslope & Localizer Inputs) Glideslope Deviation is basic (required) and is available in analog and digital formats. Localizer Deviation is an enhancement (not required) and is available in analog and digital formats. Glideslope Validity Glideslope Validity (+28V Super Flag) is required for Navigation Inputs Select 0 or 5 at pin J1-11. Glideslope Validity (Low Level) is required for Navigation Inputs Select 1 at pins J1-30 (+) and J1-10 (-). Digital ARINC 429 Glideslope interfaces (Navigation Inputs 2 & 3) do not require Glideslope Validity input. Localizer Validity Localizer Validity (+28V Super Flag) is required for Navigation Inputs Select 5 at pin J1-48. Digital ARINC 429 Localizer interfaces do not require Localizer Validity input. ILS Tuned Discrete Input #1 (+28V) and #2 (GND) The ILS Tuned Discrete indicates that an Instrument Landing System frequency has been selected on the Captain s (or selected) ILS. The ILS Tuned Discretes #1 (+28V) and #2 (GND) are optional to each other. These discretes are used with the analog Glideslope inputs. When an ILS is tuned, the MK XXII EGPWS checks the Glideslope Validity discretes and monitors the Glideslope inputs. CAGE CODE: SCALE: NONE SIZE: A DWG NO: REV: E SHEET 95

96 Analog Glideslope Interface (Cat. 9 ID 0,1,5) EGPWS MK XXII GS Deviation J1 GS Valid Low Level GS Valid ILS Receiver +Up GS Deviation +Dn Super Flag +28V + - GS Flag (Low Level) ILS Tuned +28 GND Delayed ILS Mode ILS Energize + 30 LOC Deviation +R LOC Deviation L LOC Valid LOC Val +28V GS Inhibit (BC) Backcourse GS Inhibit (BC) GND 19 Backcourse Analog-ILS-2.vsd GS Valid LOC Valid ILS Tuned Deviation Vendor Model Cat. 9 SuperFlag Low Level SuperFlag GS +up LOC +R ID +28V Flag +28V GND +dn +L Honeywell J J J KNR J J J J J J Honeywell P1-e P1-T KNR P1-q P1-k P1-V Honeywell KNR P P P P P P P P P Honeywell P692-S P692-B KGM P692-W P692-T P692-a P692-C Honeywell P601-e P601-r P601-m KNR 600A 1 P601-q P601-A P601-k P601-s P601-n Collins 51RV-1, 51RV-4( ) 5 TP-27 2 TP-21 TP-8 BP-39 TP-22 BP-50 BP-18 TP-9 BP-40 Collins P1-9 P1-5 P2-10 VIR-30, -31, P1-17 P1-13 P2-18 P2-40 P1-1 P2-13 Honeywell J J VNS 41A 5 P P J J J Honeywell TP-8 BP-39 RNA-34A 5 TP-27 TP-21 BP-50 BP-18 TP-9 BP-40 Honeywell P2-13 P2-P KN 53 1 P2-R P2-12 P2-14 Honeywell KN 72 P1-2 P1-10 Honeywell P1-B60 P1-B79 P1-B78 RNZ P1-A74 P1-B106 P1-B91 P1-B64 P1-B75 P1-B75 Honeywell P901-U P901-S P901-s (KX-165) KX-155/165 1 P901-R P P401-8 P901-T P901-k (only NOTE: The connector pin numbers given in the Table above are to the best knowledge of Honeywell EGPWS engineering. eplease contact the manufacturer s customer service to confirm your installation , -01, -04, -05, -10, -11, -14 and 15 only. 2 51RV-4( ) only. CAGE CODE: SCALE: NONE SIZE: A DWG NO: REV: E SHEET 96

97 Digital Glideslope/Localizer Interface (Cat. 9 ID 2,3,4) EGPWS MK VI / MK VIII A ARINC 429 ILS B J ILS Bus A B ARINC 429 Low Speed Vendor Model Cat 9 ARINC 429 Bus 1 ARINC 429 Bus 2 ID A B A B Chelton VNS 411A 2,3 P1-C P1-D Chelton VNS 411B 2,3 P P Honeywell RNA-34A 2,3 P P P P Honeywell KNR 634A 4 P P P P Honeywell KN 40A(B) 4 P401(403)-41 P401(403)-42 P401(403)-44 P401(403)-45 Collins VIR-432 2,3 P1-35 P1-36 P1-22 P1-23 Garmin GNS-430 2,3 P P NOTE: The connector pin numbers given in the Table above are to the best knowledge of Honeywell EGPWS engineering. Please contact the manufacturer s customer service to confirm your installation Digital ARINC 429 ILS bus (Cat. 9 ID 6) Navigation Input Select Type 6 (ILS bus or equivalent) is a single low speed, digital ARINC 429 bus including Vertical Deviation (117), Lateral Deviation (116) and Mode 5 Control (163) labels for Precision Approach landings. See Primus APEX for interface description Digital ARINC 429 Dual IOC buses (Cat. 9 ID ) Navigation Input Select Type (IOC bus or equivalent) are dual high speed, digital ARINC 429 signal having labels 173, and 174 along with combinations of Selected Course and PFD Mode Select Word. Navigation Input Select Type 249 & 252 are designed to use ARINC 429 receive channels 2 & 5. Navigation Input Select Type 248 (IOC bus or equivalent) is a dual high speed, digital ARINC 429 bus including Vertical Deviation (117), Lateral Deviation (116) and Mode 5 Control (163) labels for Precision Approach landings. For interface description see paragraph Air Type. CAGE CODE: SCALE: NONE SIZE: A DWG NO: REV: E SHEET 97

98 Category 10 Attitude Input Select Category 10 defines the Roll and Pitch Attitude interface Attitude Signals Roll Angle is used for Bank Angle callout, Pseudo Altitude Algorithm and Terrain Awareness display. Pitch Angle is used for the Tail Strike alert. NOTE: For MD900 series aircraft where no Tail Strike alert is applicable, Pitch is not required, so a roll only configuration may be selected. Appendix E Table defines the Attitude Input Select type and identifies the first MK XXII EGPWS version in which the option was available (see the Effectivity entry) Instructions 1. Using Appendix E Tables 5.3 and ,select the Attitude Input Select type that matches the aircraft configuration, feature preferences, and version (part number) being installed. 2. Record the ID number for the Attitude Input Select from Appendix E Table under the Ident No. heading for Step (Category) 10 on Table 5.3. This number will be used for programming the configuration module 3. Using the Attitude Input Select ID number from Appendix E Table as x, go to Appendix E Table x. The electrical interfaces (pin-outs) for the Attitude Input Select Type are used to determine the wiring interconnects and record it on Appendix A Fig A1-3. CAGE CODE: SCALE: NONE SIZE: A DWG NO: REV: E SHEET 98

99 Analog Roll Angle (Synchro) (Cat. 10 ID 0,2,4,7) EGPWS MK XXII J1 Vertical Gyro Roll Synchro X Y Z X Y Z Roll Angle Pitch Synchro X Y Z X Y Pitch Angle Z Vendor Model Attitude Pitch Synchro (Note 1) Roll Synchro (Note 1) V/G Valid +28 X Y Z X Y Z Aeronetics RVG 801 P1-U P1-A P1-B P1-C P1-D P1-E P1-F Collins AHC-85( ) P1-13 P2-50 P2-51 P2-52 P2-42 P2-43 P2-44 Collins 332D-11 N A B C D E F Honeywell HG1075/95 J1B-G3 J1B-C9 J1B-C10 J1B-C11 J1B-D9 J1B-D10 J1B-D11 Honeywell AH-600 J1B-11 J1B-52 J1B-53 J1B-54 J1B-49 J1B-50 J1B-51 Jet VG-208 P1-U P1-A P1-B P1-C P1-D P1-E P1-F King KVG-350 HH X Y Z P Q R Litef LTR-81 MP-A11 MP-B1 MP-B2 MP-B3 MP-B4 MP-B5 MP-B6 Litef LCR-92& 93 Note 2 J3-11 J3-40 J3-26 J3-16 J3-39 J3-25 Sperry VG-14A Note 3 X Y Z P Q R Sperry VG-311 P1-45 P1-5 P1-4 P1-6 P1-7 P1-8 P1-9 Note 1: The connector pin numbers given in the table above are to the best knowledge of Honeywell EGPWS engineering. Please contact the manufacturer s customer service to confirm your installation. Note 2: See LCR installation manual. Note 3: See airframe drawing. CAGE CODE: SCALE: NONE SIZE: A DWG NO: REV: E SHEET 99

100 Digital ARINC 429 High Speed (Cat. 10 ID 6 and 128) Attitude Input ID 128 (Litef LCR 92S or equivalent) is a high speed, digital ARINC 429 signal having roll pitch angle, and roll pitch rate labels 325, 324, 327, and 326. EGPWS MK XXII J2 AHRS AHRS 429 HS A B 23 6 A B Roll Pitch Angle Vendor Model Cat 10 ARINC 429 Bus 1 ARINC 429 Bus 2 ID A B A B Collins AHC-85(D/E only) 6* P1-16 P1-14 P1-24 P1-22 Litef LTR-81 AHRS 6* MP-G7 MP-G8 MP-E5 MP-E6 Litef LCR-92/LCR-93 AHRS 6* J4-08 J4-29 J4-49 J4-07 Honeywell HG1075/1095 IRU 6* J1B-G7 J1B-G8 J1B-E5 J1B-E6 NOTE: The connector pin numbers given in the Table above are to the best knowledge of Honeywell EGPWS engineering. Please contact the manufacturer s customer service to confirm your installation. * ID 6 is preferred with Category 2 Air with ARINC 429 Barometric Altitude Rate (label 212), otherwise ID 5. ID 6 cannot be used with analog Air interfaces Digital ARINC 429 Dual IOC buses (Cat. 10 ID 253, 254) Attitude Input Select Type 253 and 254 (IOC bus or equivalent) are dual high speed, digital ARINC 429 signal having labels 324, 325, 326 and 327. Attitude Input Select Type 253 also includes Inertial Vertical Speed (365) and Inertial Altitude (361). For interface description see paragraph Air Type Category 11 Heading Input Select Category 11 defines the Magnetic Heading interface. Appendix E Table defines the Heading Input Select types and identifies the first MK XXII EGPWS version in which the option was available (see the Effectivity entry) Instructions 1. Using Appendix E Tables 5.3, and x, select Heading Input type that matches the aircraft configuration, feature preferences, and version (part number) being installed. 2. Record the ID number for the Heading Input Select from Appendix E Table under the Ident No. heading for Step (Category) 11 on Table 5.3. This number will be used for programming the configuration module. CAGE CODE: SCALE: NONE SIZE: A DWG NO: REV: E SHEET 100

101 3. Using the Heading Input Select number from Appendix E Table as x, go to Appendix E Table x. The electrical interfaces (pin-outs) for the Heading Input Select Type are shown in Appendix E Table x are used to determine the wiring interconnects and record it on Appendix A Fig A Magnetic Heading Magnetic Heading is used for Terrain Awareness alert and display and for Envelope Modulation Analog Heading (Synchro) (CAT. 11 ID 0) EGPWS MK XXII J1 Directional Gyro Heading Synchro X Y Z X Y Z Heading 26 VAC Reference H C Mag Hdg Validity H Heading Ref C +28V = Valid Analog-HDG.vsd Vendor Model Heading Heading Reference Heading Synchro (Note 1) D/G Valid H C X Y Z Aeronetics Model 9100 P1-28 P1-6 P1-7 P1-8 P1-9 P1-10 Collins AHC-85( ) P2-57 P2-57 P2-34 P2-35 P2-36 Collins DGS-65 P1-50 P1-6 P1-3 P1-25 P1-40 P1-24 Honeywell HG 1075 J1B-G2 J1B-F13 J1B-G13 J1B-E10 J1B-E11 J1B-E12 Honeywell AH-600 J1B-37 J1B-38 J1B-39 J1B-40 J1B-41 J1B-42 Honeywell KSG 105 P1-V P1-P P1-d P1-Z P1-W P1-T Honeywell KI J2-P J2-R J2-U J2-S J2-V J2-T Jet DN-104 P2-31 P2-9 P2-10 P2-1 P2-2 P2-3 Litef LTR-81 MP-E15 MP-B12 MP-B13 MP-B9 MP-B10 MP-B11 Litef LCR 92/LCR-93 Note 2 J3-05 J3-20 J3-13 J3-42 J3-28 Sperry C-14A P1-e P1-H P1-J P1-L P1-M P1-K Sperry C-14D P1-DD P1-X P1-Y P1-AA P1-BB P1-Z Sperry DG-234 P2-F P1-L P1-K P1-J Note 1: The connector pin numbers given in the table above are to the best knowledge of Honeywell EGPWS engineering. Please contact the manufacturer s customer service to confirm your installation. Note 2: See LCR installation manual. Note 3: The KI-525 must have the proper mod for HEADING TRANSMITTER output. The Heading Valid output at J2-P needs to be converted from ground active to +28V active output using an external relay for use with EGPWS. CAGE CODE: SCALE: NONE SIZE: A DWG NO: REV: E SHEET 101

102 Digital ARINC 429 High Speed (CAT. 11 ID 2 and 3) Heading Input ID (Litef LCR 92S or equivalent) is a high speed, digital ARINC 429 signal having roll angle, pitch angle, roll rate, pitch rate, and heading labels 320, 325, 324, 327, and 326. EGPWS MK XXII J2 AHRS AHRS 429 HS A B 23 6 A B Heading Vendor Model 429 High Speed AHRS A B Litef LCR 92S Digital ARINC 429 Dual IOC buses (Cat. 10 ID 254 & 255) Heading Input Select Type 254 & 255 (IOC bus or equivalent) are dual high speed, digital ARINC 429 signal having labels True Heading (314) or Magnetic Heading (320). For interface description see paragraph Air Type Category 12 Windshear Input Select Category 12 defines the Windshear interface. Windshear is not applicable to MK XXII Instruction Select ID 0 for all helicopter configurations. CAGE CODE: SCALE: NONE SIZE: A DWG NO: REV: E SHEET 102

103 Category 13 Input / Output Discrete Type Select Category 13 defines the input and output discretes not defined as part of any of the other Categories. Appendix E Table defines the Input/Output discretes options and identifies the first MK XXII EGPWS version in which the option was available (see the Effectivity entry) Instruction 1. Using Appendix E Tables 5.3, , and x, select the Input/Output Discrete Type number that matches the aircraft configuration, feature preferences and version (part number) being installed. Note: Normal Helicopter I/O Discrete options are Types 128 or 129. The difference is the Output Lamp format described below in section Record the ID number for the Input/Output Discrete Select number from Appendix E Table under the Ident No. heading for Step (Category) 13 in Appendix E Table 5.3. This number will be used for programming the configuration module. 3. Using the Input/Output Discrete Type number from Appendix E Table as x, the ICD Table x. is used to determine the wiring interconnects, record it on Appendix A Fig A1-1, A1-2, and A1-3. Note: When there are two discrete pin choices for the same pin function in Appendix E Table x, use only the one that matches the aircraft wiring (use only the +28V and 0V or the Ground and Open definitions) Input/Output Discretes Additional information for the discretes is provided below Audio Inhibit Discrete Honeywell does not recommend the use of this input for Helicopters. The Audio Inhibit discrete is an optional input to maintain audio and visual prioritization. When activated, this discrete inhibits all audio (Ground Proximity and Terrain Awareness). Activation of the Audio Inhibit input for more than 60 seconds will result in the All Modes Inhibit The Audio Inhibit discrete input can be connected to any or all of the following (as applicable to the aircraft configuration): a separately labeled guarded cockpit switch For some existing GPWS installations, this discrete may have been tied to the analog Radio Altimeter Receiver-Transmitter Self-Test output. This connection is no longer required but may be left intact for this installation. Discrete Position / Status Connector Pin Audio Inhibit +28 Inhibit = +28V J1-36 Not Inhibit = Gnd/Open Landing Gear Discrete Landing Gear discrete is supplied by the Gear (or Gear handle) switch. The active position (+28V or GND) indicates Gear Down and should be connected to a contact that will indicate Gear Down when the Gear are lowered. CAGE CODE: SCALE: NONE SIZE: A DWG NO: REV: E SHEET 103

104 Discrete Position / Status Connector Pin Landing Gear +28 Down = +28V J1-35 Not Down = Gnd/Open Landing Gear Gnd Down = Gnd Not Down = +28V /Open J1-16 For fixed gear or skid equipped aircraft this input is not required Weight ON Wheels (WOW) Discrete The Weight on Wheels (WOW) discrete is supplied by the WOW system in the aircraft. Connection can be made to the actual OLEO switch or relay logic later in the aircraft wiring. For aircraft without WOW indication such as those with fixed gear or skids, this input discrete is not required. Discrete Position / Status Connector Pin WOW +28 On Ground = +28V J1-37 In Air = Gnd/Open WOW Gnd On Ground = Gnd In Air = +28V /Open J1-18 NOTE: The logic sense of the WOW discrete can be reversed by selecting the WOW eversal option in Category 7, see section Glideslope Cancel Discrete The Glideslope Cancel discrete provides the crew with the capability to manually cancel Mode 5 for an approach. This is automatically reset when the aircraft descends below 30 feet or ascends above 2000 feet or by selecting a non-ils frequency. This discrete is typically supplied by a momentary action cockpit Glideslope mode manual inhibit switch, typically part of the Glideslope Lamp assembly (Below GS). Discrete Position / Status Connector Pin Glideslope Cancel Cancel = Gnd J1-15 Normal = Open Mode 6 Low Volume Discrete The Mode 6 Low Volume discrete permanently or temporarily modifies the volume of the Mode 6 altitude and bank angle callouts. This discrete operates independent of the Category 14 options. The Mode 6 Low Volume discrete is used to reduce the Mode 6 volume by 6dB from the volume level select in Category 14. This discrete is typically connected to ground to lower the volume an additional 6dB. In some installations, it is connected to the windshield wiper control to decrease the Mode 6 Volume level under normal conditions and automatically increase Mode 6 volume 6dB when the cabin noise increases due to the windshield wipers being on. CAGE CODE: SCALE: NONE SIZE: A DWG NO: REV: E SHEET 104

105 Discrete Position / Status Connector Pin Mode 6 Low Volume Low Volume = Gnd Not Low Volume = Open J Minimums/Check Height Silence Discrete The Minimum/Check Height Silence discrete will silence a "Minimum Minimums" or Check Height Check Height" message for 3 minutes. This discrete is normally connected to a momentary action switch mounted on the Cyclic column. This is the same switch that would have previously been used to silence callouts from the AVAD system. Discrete Position / Status Connector Pin Minimums/Check Silence = Gnd J1-13 Height Silence Normal = Open Terrain Awareness Inhibit The Terrain Awareness inhibit discrete, inhibits the Terrain Awareness modes in the MK XXII EGPWS. This discrete is normally connected to an alternate action switch in the cockpit. The recommended label for this switch is Terrain Override although labeling for this switch should be consistent with existing cockpit nomenclature. Terrain Inhibited will be annunciated during cockpit Self-Test if these functions are inhibited. Discrete Position / Status Connector Pin TA Inhibit Inhibit = Gnd Not Inhibit = Open J Self Test Discrete The cockpit Self Test discrete is provided to manually initiate test of the EGPWC, EGPWS aircraft interface, and to annunciate system configuration and status information. This discrete is typically supplied by a momentary action cockpit push to test switch, typically part of the GPWS WARN Lamp assembly. This discrete must be momentarily connected to ground to activate the Self Test. Activation of this discrete continuously for more than 60 seconds will result in the Self Test Invalid fault which will cause a GPWS INOP indication. Discrete Position / Status Connector Pin Self Test Self Test = Gnd J1-34 Normal = Open Glideslope Inhibit Discrete The Glideslope Inhibit Discrete, also known as the Backcourse Inhibit, provides an inhibit to the Glideslope alert when on a backcourse approach. The Glideslope Inhibit is usually connected to the Flight Director or FMS backcourse discrete output. CAGE CODE: SCALE: NONE SIZE: A DWG NO: REV: E SHEET 105

106 Discrete Position / Status Connector Pin Glideslope Inhibit +28 Inhibit = +28V J1-38 Not Inhibit = Gnd/Open Glideslope Inhibit Gnd Inhibit = Gnd Not Inhibit = +28V /Open J Timed Audio Inhibit Discrete The Timed Audio Inhibit will cause the inhibiting of most audio messages for a configurable period. See Options 3 (Category 18). The default inhibit period is 5 minutes or until reset. The discrete input is connected to a momentary lighted switch. When pressed the condition is latched in memory and will be reset after 5 minutes have elapsed or pressing the switch again or when landing. The switch lighting, indicating the Audio is Inhibited is driven by a discrete output described below. Discrete Position / Status Connector Pin Timed Audio Inhibit Momentary Toggle = Gnd Normal = Open J1-17 NOTE: Either the Timed Audio Inhibit or the Terrain Inhibit should be used depending on the aircraft operations. See discussion is section Low Altitude Mode Select Discrete The Low Altitude Mode select is a required input and is used for cruise operation below 500 feet AGL and for operation in high density metropolitan environments such as tall buildings. When selected, the Low Altitude Mode inhibits Excessive Terrain Closure (Mode 2) warnings, retards the Terrain Clearance warnings (Mode 4), and reduces the Terrain look ahead distances and width. When selected, Low Altitude Mode may be deselected by pressing the switch again. The Low Altitude select switch is a lighted momentary switch where the selected condition lighting is driven by an output discrete described below ICS Audio On Discrete The ICS Audio On discrete will inhibit all audio messages prioritized below the Warning Terrain and Warning Obstacle messages. Self Test messages are excluded. This discrete is designed to be used in handshaking with a Central Aural Warning System in conjunction with the Audio On output discrete Output Discretes The MK XXII EGPWS supports two kinds of Ground/Open discrete outputs used to indicate various conditions. Monitor outputs are used to indicate failure conditions for the EGPW system. Monitor outputs default to an active state when there is a failure or if power is removed from the EGPWS (no connection if the EGPWC is removed from the rack). The Discrete Out Lamp driver outputs are used to indicate alert modes (GPWS WARN, BELOW GS, etc.) or mode control status (Terrain Display Select, etc.) of the EGPWS. CAGE CODE: SCALE: NONE SIZE: A DWG NO: REV: E SHEET 106

107 Short-term current limit protection is provided on all drivers for output shorting conditions. Ground going output discretes may be connected together to produce a wired OR function for the active low state of the outputs. If output discretes are wire OR d then diodes must be installed for isolation. All EGPWS Output Discretes have corresponding bit assignments in the EGPWS ARINC 429 output data Lamp Format The Lamp Format Type (configuration) is a function of the discrete output pin functions and defines the operation of the red and amber GPWS cockpit lamps. For Lamp Format Type 1, the amber Below G/S lamp is driven by the GPWS Alert (Glideslope only) discrete and the red GPWS lamp is driven by the remaining alerts and warnings. For Lamp Format Type 2, the red EGPWS lamp is driven by the GPWS Warning (Pull Up, Warning Terrain, and Warning Obstacle only) discrete and the amber EGPWS lamp is driven by the remaining alerts and warnings GPWS INOP Discrete The GPWS INOP discrete (J1-72) indicates GPWS modes are inoperative. This feature activates a GPWS INOP lamp located in the cockpit within sight of the pilots TAD INOP Discrete The TAD INOP discrete (J1-55) indicates, Terrain Awareness (TA), and Terrain Display are Not Available. This feature activates a TERRAIN INOP lamp located in the cockpit within sight of the pilots GPWS Warning Discrete (Lamp Format Type 1 definition) GPWS Warning discrete (J1-78) will activate during any Mode 1 through Mode 4 alert or warning, Terrain Awareness caution/warning, and Obstacle Awareness caution/warning. This feature activates a GPWS lamp located in the cockpit within sight of each pilot. Note that Mode 6 does not activate any lamp outputs, only voices GPWS Alert Discrete (Lamp Format Type 1 definition) GPWS Alert discrete (J1-77) will activate during Mode 5 Glideslope cautions only. This feature activates a BELOW GS red lamp located in the cockpit within sight of each pilot Glideslope Cancel Discrete -Optional- Glideslope Cancel discrete (J1-76) will activate when the Glideslope Cancel discrete (momentary) has been pressed any time below 2000 feet Radio Altitude if the ILS is tuned. This feature activates a G/S CAN amber lamp located in the cockpit within sight of the pilots. CAGE CODE: SCALE: NONE SIZE: A DWG NO: REV: E SHEET 107

108 TCAS Inhibit Discrete -Optional- TCAS Inhibit discrete (J1-69) will activate during any EGPWS voice annunciation. This output is used to inhibit TCAS from talking during EGPWS annunciation. This feature does not have a lamp associated with it Terrain Display Select #1 & #2 Discrete Terrain Display Select #1 & #2 discrete (J1-54 & J1-49) will activate after the related pilot has initiated manual selection of the Terrain Display Select (momentary) discrete #1 or #2 (J1-32 & J1-31, Category 6). This feature activates a TERR white lamp located in the cockpit within sight of each pilot. The lamp serves to remind the flight crew that this function is active. The select switches (J1-32 & J1-31) and the indicator lamps (J1-54 & J1-49) are commonly combined in switch-lamp assemblies mounted near the displays being selected Timed Audio Inhibit Discrete The Timed Audio Inhibit discrete (J1-52) will activate after a Timed Audio Inhibit switch (momentary) is pressed in the cockpit. The discrete will stay active until the Timed Audio Inhibit latch resets after 5 minutes or the switch is pressed again or the aircraft lands. The discrete is used to light the ON status portion of the Timed Audio Inhibit lighted switch assembly Low Altitude Mode Discrete The Low Altitude Mode discrete (J1-73) will activate after a Low Alt switch (momentary) is pressed in the cockpit. The discrete is used to light the ON status portion of the Low Altitude lighted switch assembly. The discrete will stay active as long as the Low Altitude Mode is selected. The Low Altitude Mode may be deselected by pressing the Low Alt switch again. CAGE CODE: SCALE: NONE SIZE: A DWG NO: REV: E SHEET 108

109 Table MK XXII EGPWS Example Cockpit Lights CAGE CODE: SCALE: NONE SIZE: A DWG NO: REV: E SHEET 109

110 Category 14 Audio Output Level Category 14 controls the Audio Output level for alert menu callouts (cautions and warnings). Refer to Category 13 for information on the Mode 6 Low Volume discrete. Appendix E Table defines the Audio Output Level options and identifies the first MK XXII EGPWS version in which the option was available (see the Effectivity entry) Instructions 1. Using Appendix E Tables 5.3 and as described above, select the Audio Output Level ID number that matches the feature preferences and version (part number) being installed. 2. Record the ID number for the Audio Output Level from Appendix E Table under the Ident No. heading for Step (Category) 14 in Appendix E Table 5.3. The Nominal Volume Select is equivalent to MK XXII MAX volume level. The 6dB through 24 db are successively lower volume from Nominal. The Nominal output is 4 watts rms into an 8-ohm load and 100 milli-watts rms into a 600-ohm load. The audio output level for Mode 6 alerts can be reduced an additional 6 db by activating the Mode 6 Low Volume discrete of Category 13. H L J1-70 J1-71 High level audio 8 ohm H L J1-75 J1-74 Low level audio 600 ohm Audio Panel FIGURE Audio Interface Note: Because most helicopters use a full muff headset, cockpit speakers are not applicable. CAGE CODE: SCALE: NONE SIZE: A DWG NO: REV: E SHEET 110

111 Category 15, Autorotation Threshold Category 15 controls the Autorotation Threshold level used for Autorotation detection. Actual thresholds are determined during first of type flight. The thresholds are found in Table below. Appendix E Table defines the Autorotation threshold options Instruction 1. Using Table below and Appendix E Tables 5.3 and as described above, select the Autorotation threshold torque ID number that was determined during flight test. 2. Record the ID number for the Autorotation threshold torque Level from Table or Table below under the Ident No. heading for Step (Category) 15 in Appendix E Table 5.3. Table : AUTOROTATION THRESHOLD Aircraft Model Threshold % Threshold ID Agusta 109E 2 4 AS 365N Bell Bell Bell Bell 427 TBD EC-135P TBD EC-155B HH MD900/ S-76 Series BK-117 TBD Bell 222 TBD EH S AW CAGE CODE: SCALE: NONE SIZE: A DWG NO: REV: E SHEET 111

112 Category 16, Torque Input Select Torque data is primarily used to detect an Autorotation. Category 16 defines the Torque interface. Interface is provided for ARINC 429 and RS 422 digital inputs and 4 DC Torque inputs as shown below. Many DC Torque signals are very high impedance and are not compatible with the MK XXII. In these cases two options are available. A DC to ARINC 429 Torque Converter may be used, as described below and in Appendix D, for aircraft whose torque indications systems use a DC signal and have no DC reference (such as S-76A, A+, A++, and C autopilot output) or those who have a 10.0 VDC reference. Note that some Eurocopter aircraft provide a DC torque signal but use an AC reference (AS350, AS355, AS365N/N1/N2). These may not be compatible with the DC to 429 Torque Converter and may need to chose the second option below. The MK XXII may be configured for no torque input. This type does not detect autorotation and thus do not provide the autorotation altitude callouts or advanced gear warnings. Mode 1 is inhibited in these types Instructions 1. Using Appendix E Table 5.3, under Step/category 16 select Torque Source. Using the guide below and Tables and x select the ID number for your Torque source and record that number on Table 5.3 under Ident No. for step 16. This number will be used during programming of the configuration module. 2. Using Appendix E Tables x, where x is the Torque Type number, define the electrical interfaces required to support your Torque Type. Using Table x determine the wiring interconnects and record it on Appendix A Fig A1-2. Table : Torque Application Guide ID Signal Type Aircraft Application 0 No Torque AS-350, AS-355N, AS-365N/N1/N2, EC ARINC 429 S76B/C+ 4 Synchro Bell 212/412 5 ARINC 429 BNR EC-155B, AS-365N3 6 RS-422 MD900/902, Agusta 109E, EC-135P1 7 DC AS ARINC 429 BCD EC-155B, AS-365N3 10 ARINC 429 BNR Bell 430, DC Bell 212/ DC HH DC BK117A/B-2/C-1(Note 1) 17 ARINC 429 DC to ARINC 429 Torque Converter S76A, A+, A++ and C, BK117A/B-2/C-1 (Note 1) 18 ARINC 429 S-92, AW-139 CAGE CODE: SCALE: NONE SIZE: A DWG NO: REV: E SHEET 112

113 ID Signal Type Aircraft Application 19 ARINC 429 EH RS 422 MD 902 (PW206E) 21 RS 422 EC-135P1 (PW026B V27) 22 RS 422 EC-135P1 (PW026B V28) 23 DC H-60 Blackhawk 24 RS 422 Maintenance Port (8000 Hex Sync) 25 RS 422 Maintenance Port (8FFF Hex Sync) 26 RS 422 A-109E (PW206C V27) 27 RS 422 A-109E (PW206C V28) 28 RS 422 Maintenance Port (8000 Hex Sync) 29 RS 422 Maintenance Port (8FFF Hex Sync) 30 ARINC 429 Late model EC-227, EC 725, EC-135, EC-145, EC-155/A 31 DC EC ARINC 429 EC-120, EC-130, AS-350B2 and B4 33 ARINC 429 AS-355 Note 1: BK-117 series can use the CSAS output or the DC to ARINC 429 Torque Converter interface. If your aircraft is not listed or for help in selecting the correct Torque type, contact the Honeywell Avionics Technical Assistance line (or from outside the USA). DC to ARINC 429 Torque Converter For aircraft with a DC Torque signal system such as S-76A, A+, A++, and C or many Bell Aircraft the DC Torque signal is not compatible with the MK XXII. For these aircraft it is recommended that a DC to ARINC 429 converter be used. At the time of this writing a certifiable source for a DC to ARINC 429 Torque converter has not been identified. Contact Honeywell for recommendations. CAGE CODE: SCALE: NONE SIZE: A DWG NO: REV: E SHEET 113

114 Category 17 Options Select Group #2 Category 17 enables/disables the following Options: Helo Normal Pop-Up, Helo Low Altitude Pop-Up, Autorotation Callout Option Select, Mode 6B Always ON Enable, Normal Terrain Airspeed Select, Low Altitude Airspeed Select, Low Altitude No VFOM Select. Appendix E Table defines the Options Select group and identifies the first MK XXII EGPWS version in which the option was available (see the Effectivity entry) Instructions 1. Review the sections below for information on Helo Normal Pop-Up, Helo Low Altitude Pop-Up, Autorotation Callout Option Select. 2. Using Appendix E Table , select the preferred Category 17 (Options Select Group #2) ID that matches the aircraft configuration, features preferences and version (part number) being installed. Record the ID number for the Options Select Group #2 from Appendix E Table 5.3 under the Ident No. heading for Step (Category) 17. This number will be used for programming the configuration module Helo Normal Pop-Up If the display type selected via Category 6 supports Auto Pop-Up and Auto-Ranging then the Helo Normal Pop-Up Select chooses the Terrain Display to be forced during a non-low Altitude Mode Pop- Up. The 5 NM range selection is recommended if the selected display type supports a 5 NM range. Otherwise select an option using a 10 NM range Helo Low Altitude Pop-Up If the display type selected via Category 6 supports Auto Pop-Up and Auto-Ranging then the Helo Low Altitude Pop-Up Select chooses the Terrain Display to be forced during a Low Altitude Mode Pop-Up. The 2.5 NM range selection is recommended if the selected display type supports a 2.5 NM range. Otherwise select the lowest range above 2.5 NM that the display will support Autorotation Callout Option Select The Autorotation feature was previously (up to ) activated via Category 4. Now this category selects the Auto-rotation callouts via one of the following options: Autorotation Callout Option Select 0: No Auto-rotation callouts selected (the callout menu selected via category 4 will remain active in auto-rotation). Auto-rotation Callout Option Select 1: Selects 200 and 100 for Auto-rotation. Auto-rotation Callout Option Select 2: Selects 200, 100, 80, 60, 40, 20 and 10 for Autorotation. CAGE CODE: SCALE: NONE SIZE: A DWG NO: REV: E SHEET 114

115 Mode 6B Always ON Enable Selecting this option enables the "Altitude Altitude" or "Check Height Check Height" callout (Mode 6B) at all times. The significant difference in this function is that the call out will be spoken for each transition thru the DH Bug or setting. This option is often selected for Offshore operation Normal Terrain Airspeed Select This option configures the system to use airspeed instead of ground speed to enable/disable the Terrain Look Ahead function during normal (not Low Altitude) operations. A special consideration should be made before selecting this option as it can lead to nuisance alerts when landing or taking off into strong headwind. (See commentary below) Aircraft operating in strong head winds will see a resulting decrease in ground speed. Depending on speed this may reduce ground speeds below look ahead enabling speeds thus turning the terrain look ahead function off. With this option selected, the Terrain Look Ahead function is enabled with airspeed allowing the look ahead alert to be active in some circumstances when it otherwise would not. However, based on customer feedback, this selection can increase the risk of nuisance alerts when landing or taking off into headwinds Low Altitude Airspeed Select This option configures the system to use airspeed instead of ground speed to enable/disable the Terrain Look Ahead function during Low Altitude operations when the Low Altitude Mode is selected. A special consideration should be made before selecting this option as it can lead to nuisance alerts when landing or taking off into strong headwind. (See commentary in section ) Low Altitude No VFOM Select (was SAR select) This option removes the addition of VFOM from the Terrain Floor when Low Altitude is selected. This is necessary to allow SAR operations at 200 feet AGL. This option should only be selected on aircraft whose mission requires operation down to 200 feet AGL. CAGE CODE: SCALE: NONE SIZE: A DWG NO: REV: E SHEET 115

116 Category 18 Options Select Group #3 Category 18 enables/disables the following Options: Audio Inhibit Time, Inhibit All Except Minimums Type Callout and 100 Ft Callout select, Inhibit All Except Minimums Type Callout select, Inhibit Includes Too Low Gear Select, Inhibit Altitude Callouts 50 ft and Below Over Runway select, Lower MDA/DH Value select. Appendix E Table defines the Options Select group and identifies the first MK XXII EGPWS version in which the option was available (see the Effectivity entry) Instructions 1. Review the sections below for information on Audio Inhibit Time, Inhibit All Except Minimums Type Callout and 100 Ft Callout select, Inhibit All Except Minimums Type Callout select, Inhibit Includes Too Low Gear Select, Inhibit Altitude Callouts 50 ft and Below Over Runway select, Lower MDA/DH Value select. 2. Using Appendix E Table , select the preferred Category 18 (Options Select Group #3) ID that matches the aircraft configuration, features preferences and version (part number) being installed. Record the ID number for the Options Select Group #3 from Appendix E Table 5.3 under the Ident No. heading for Step (Category) 18. This number will be used for programming the configuration module Audio Inhibit Time This option allows selection of the Timed Audio Inhibit time. Options provide 2 to 2.5 minute increments from 3 to 20 seconds. An additional state is provided that allows the Audio Inhibit to be toggled ON and OFF. Timed Audio Inhibit will inhibit all audio except the following. Too Low Gear Minimums Minimums Minimums Check Height Check Height Altitude Altitude Altitude Selected Altitude Callouts Glideslope Tail Too Low Bank Angle* Be Alert Terrain INOP For the S-92 the following externally triggered messages are added to the list: Low Rotor Smoke In Baggage Fire Engine 1/2 Hover Altitude Engine 1/2 Failure Airspeed Gear Box Pressure Check Altitude Swash Plate Temperature Check Power Fire APU Decouple Smoke In Cabin Level Off CAGE CODE: SCALE: NONE SIZE: A DWG NO: REV: E SHEET 116

117 Inhibit All Except Minimum Type Callout and 100 Ft Callout Select This option alters the above list to inhibit all audio messages except the following messages and the 100 foot callout. Minimums Minimums Minimums Check Height Check Height Altitude Altitude Altitude This option is most often used on aircraft operating offshore and combined with audio menus and callout options using Check Height Inhibit All Except Minimum Type Callout Select This option alters the inhibit list in to inhibit all audio messages except the following message. Minimums Minimums Minimums Check Height Check Height Altitude Altitude Altitude This option is most often used on aircraft operating onshore and combined with audio menus and callout options using Check Height Inhibit Includes Too Low Gear Select This option adds the Too Low Gear message to those messages inhibited by the Timed Audio inhibit. This option is intended for those aircraft that perform low altitude rescue operations with landing gear up Inhibit Altitude Callouts 50 ft and Below Over Runway Select This option will inhibit selected altitude callouts at 50 feet and below when the aircraft is over an airport with a published instrument approach. This silences altitude callouts during final approach when ATC communications traffic maybe high Lower MDA/DH Value Select This option is effective when Category 8 (Radio Altitude Input) ID 251, ID 252, ID 254 or ID 255 are configured. These allow the input of two sources of MDA or DH. Normally the higher of the two values is selected for use. This option allows the selection of the lower of the two values for use by the Mode 6 functions. CAGE CODE: SCALE: NONE SIZE: A DWG NO: REV: E SHEET 117

118 Category 19 Options Select Group #4 Category 19 selects the Low Altitude Mode of operation (Land, SAR, or Offshore transport). Appendix E Table defines the Options Select group and identifies the first MK XXII EGPWS version in which the option was available (see the Effectivity entry) Instructions 1. Review the sections below for information on Low Altitude Mode options. 2. Using Appendix E Table , select the preferred Category 19 (Options Select Group #4) ID that matches the aircraft operation, system response, and version (part number) being installed. Record the ID number for the Options Select Group #4 from Appendix E Table 5.3 under the Ident No. heading for Step (Category) 19. This number will be used for programming the configuration module Low Altitude Mode Low Altitude Mode is selected with the use of the Low Altitude Mode Select (Tactical) discrete. This discrete is sourced from an analog switch or digital ARINC 429 bits. Prior to the -030 release when Low Altitude Mode was activated GPWS classic modes and the forward looking terrain alert function were modified to allow flight in congested areas, low altitude routes or while performing special operations. In release -030 and on, this option category allows tailoring of the MK XXII system response to the Low Altitude Mode Select (Tactical) discrete. When Low Altitude Mode Select is true the HTAWS provides a Reduced Protection Mode allowing operations below the defined alert envelopes without issuing alerts. Low Altitude Mode Select affects the following modes regardless of the configuration option selected below (see table for further changes in operation): GPWS Mode 2 inhibited. GPWS Mode 3 inactive above 100 feet AGL. Mode 6 provides the message Altitude Altitude or Check Height for each transitioning below the selected decision height 1. Forward Looking Terrain Alerting Threat Detection is biased to allow closer proximity to terrain. 1 For S-92 Altitude Altitude callout is always active. Low Altitude Suggested Operations Option 0 Low level operations over land 1 SAR over water 2 Offshore transport See Appendix E for MK XXII system response Mode 2 Terrain Inhibit Many HTAWS installations provide a Terrain Inhibit switch that allows the pilot to disable (or inhibit) Terrain Awareness Alerts. When this switch is active the Forward Looking Terrain Alerting function is inhibited CAGE CODE: SCALE: NONE SIZE: A DWG NO: REV: E SHEET 118

119 however, the radio altimeter based, classic GPWS Mode 2 alerts are not. This can lead to pilot dissatisfaction. The following is a scenario to illustrate the potential for confusion: Pilot is flying VFR and is intentionally close to terrain; Forward Looking Terrain Alert activates providing Caution! Terrain aural and alert visual; pilot inhibits terrain by selecting the Terrain Inhibit switch; Forward Looking Terrain Alert ceases but due to close proximity to terrain the GPWS Mode 2 alert activates providing the Terrain Terrain aural and alert visual. In this scenario the pilot has made the decision and commanded the system to inhibit terrain alerts but the system continues to provide them albeit from a different mode. In the -030 release the Mode 2 Terrain Inhibit option allows the Terrain Inhibit switch to affect the Mode 2 function. Mode 2 Terrain Inhibit = False; Terrain Inhibit does not affect Mode 2 (pre -030 release behavior). Mode 2 Terrain Inhibit = True; Terrain Inhibit will also inhibit the Mode 2 alert function. CAGE CODE: SCALE: NONE SIZE: A DWG NO: REV: E SHEET 119

120 SECTION IV CONFIGURATION MODULE PROGRAMMING AND TERRAIN DATABASE LOADING CAGE CODE: SCALE: NONE SIZE: A DWG NO: REV: E SHEET 120

121 SECTION IV CONFIGURATION MODULE PROGRAMMING AND TERRAIN DATABASE LOADING 4.1 Introduction The following procedures outline the steps necessary to accomplish a complete configuration of the MK XXII EGPWS. This section must be accomplished in the order presented to minimize errors in configuring and operating the system(s). If problems are encountered in performing these procedures, the installer may refer to aircraft wiring diagrams for harness troubleshooting or the aircraft maintenance manual to isolate faulty equipment. All discrepancies should be resolved before proceeding. This section will also load the Regional Terrain base in MK XXII EGPWS that will be operating outside of the North American region. 4.2 Harness Checkout and Power Check Prior to installing any equipment, it is important to verify that all interfaces have been made and that power and ground at each unit connector is correct, using the wiring diagrams for the installation. Any discrepancies in the wiring must be resolved before proceeding. The wire harness should also be checked for proper clearance near any control cables and other potential areas that may cause binding and/or chafing. 4.3 Unit Installation After the harness check has been completed and any discrepancies have been resolved, the units should be installed into their respective racks, and all connections to the wiring harness should be made (connectors attached). Verify that all of the units are secure in their respective racks, panels, etc., and all harness connections are secure. Refer to aircraft installation drawings for the unit locations and mounting information. 4.4 EGPWC Initialization and Configuration The first time a MK XXII EGPWS is turned on in a new installation, the Configuration Module in the EGPWS harness must be programmed to the specific interface configuration for the aircraft. This programming is done via RS-232 cable connection between the EGPWC and a PC running the Honeywell WinViews software. This interface capability is provided to facilitate diagnostic and configuration functions with the EGPWC during post installation checkout. Refer to Appendix C for instructions related to using the WinViews software RS-232 Communication with the MK XXII EGPWS The MK XXII EGPWS computer contains software that allows monitoring of its internal parameters, for testing purposes, without altering its operation. The monitoring of these parameter values enables the operator to quickly determine if the EGPWC is using the correct signal and scaling. The communication link utilizes the RS-232 communication protocol configured as follows: Baud, No Parity, 8 Bits, and 1 Stop Bit CAGE CODE: SCALE: NONE SIZE: A DWG NO: REV: E SHEET 121

122 4.4.2 EGPWC Front Panel Test Connector The RS-232 interface with the EGPWC is accomplished via a test connector provided on the EGPWC front panel (J3). This provides access for a PC test monitor and portable data loading capabilities. The mating connector for the EGPWC test plug (P3) is a male, 15 pin, double density D-subminiature type (or equivalent). The connection between the PC serial port connector (with standard DB9) and the EGPWC RS-232 interface is defined as follows: RS-232 Receive RS-232 Transmit RS-232 Ground EGPWS Front Connector (J3) Pin 3 Pin 4 Pin 1 Standard (PC)* DB9 Connector Pin 3 Pin 2 Pin 5 *NOTE: Some PC Comm Ports have Pins 2 & 3 reversed from what is described above. Connector, AMP Socket Contact, AMP , QTY 3 M39029/ PCOM Connector, AMP * Pin Contact, , QTY 4* M39029/ Backshell, AMP Jackscrew, AMP Grommet Set, AMP P Length as required (5' to 50') * Alternate part number connector and or 7 pin contact WinVIEWS (Windows Virtual Interface to the Enhanced Warning System) WinVIEWS is a software tool developed by Honeywell to communicate with the EGPWS. WinVIEWS provides a detailed status of the software configuration and input signals, which enables quick identification of system configuration, and is utilized for programming the system Configuration Module. WinVIEWS software can be downloaded from the internet website ( CAGE CODE: SCALE: NONE SIZE: A DWG NO: REV: E SHEET 122

123 4.4.4 WinVIEWS Operation 1. Connect the PC to the EGPWC using the RS-232 cable as described in section On the PC, start Windows 3.1, or higher. 3. Start the WinVIEWS.EXE program. 4. Use F6 to select the Terminal Mode. Various commands are available in this mode. Type HELP or? for a list of the commands available. 4.5 Configuration Module Programming The EGPWC reads the aircraft configuration from the Configuration Module, which is installed in the EGPWC connector. The Configuration Module must have the aircraft specific configuration ID string written to it before the EGPWS is operational. The ID string is defined by 15 separate categories listed in Appendix E Table 3, Category ID Selection Procedure. For programming the Configuration Module, the following procedure is used: 1. Verify EGPWC interface to P2 connector (including Configuration Module) and RS-232 interface to PC. 2. Power EGPWC and PC and start WinVIEWS. 3. With WinVIEWS active in the Terminal Mode, configuration sub-mode commands are available for programming purpose. Type CFG at the Terminal Mode prompt (>). At this point, the CFG> prompt is displayed and the program and EGPWC are ready for entering the program command and data string. Type HELP or? to display a list of the Terminal Mode commands and their description. CUW is the preface command for entering the ID string. 4. Using the Category ID s as chosen from the Appendix E (refer to completed Table 3), create a command string with the following structure: CUW 0/19 # # # # # # # # # # # # # # # # # # #/ - CUW<space>0 is the command and version number. CUW writes the category ID s defined by version 0 definition (0 is the only version currently available) to the Configuration Module via the EGPWC without a CRC (checksum) value attached (this is generated by the EGPWC when the data is transmitted). - /19 indicates the beginning of the data string (/) with 19 being the number of categories to follow. - <space><cat 1 ID#><space><Cat 2 ID #> <Cat 19ID#>/ each Cat ID# is the chosen ID for the category from the Appendix E Table 3. The ending slash (/) indicates the end of the data string. Note: If 19 ID s do not follow /19, the error message Invalid Parameter. Not enough ID s. Configuration update failed, please try again. will be given. The value entered for each category must be an available ID for the associated category or a similar error message will be given. If the number of categories provided is less than 19 (e.g., /8 # #/ with eight ID s defined), then the remaining categories (9 through 19) will be set to 0. CAGE CODE: SCALE: NONE SIZE: A DWG NO: REV: E SHEET 123

124 After completing the data string as defined above, pressing ENTER the cursor will flash waiting for an answer Y or N. Pressing the Y (or y) key confirms the data and sends the data to the EGPWC to write to the Configuration Module. Note: Using Kermit or a similar terminal emulator pressing ENTER results in a question: Confirm this data reflects configuration to be programmed (Y/N). Pressing the Y (or y) key confirms the data and sends the data to the EGPWC to write to the Configuration Module. Following the writing to the Configuration Module the EGPWC is automatically rebooted in order for the new configuration to take affect. Note: If when the ENTER key is pressed the question response is not given (cursor just moves to the next line), pressing any character key should provide the proper response. Pressing the N key results in the message Command aborted No configuration module change has been made. If necessary, revise the data to correct or change as necessary and continue as above. The backspace key can be used to make corrections. 5. Following the successful writing to the Configuration Module (no error messages) and EGPWC reboot, pressing Control Z (Ctrl-Z) restarts the WinVIEWS Terminal Mode communication. 6. There are a couple ways to now confirm the Configuration Module programming with the following being the preferred. As above, type CFG to restart the Configuration sub-mode. At the CFG> prompt, type CMR<Enter>. Each category and its associated ID is read from the Configuration Module and listed on the PC screen. Alternately, when not in the Configuration sub-mode, the command PS<Enter> (Present Status) will display EGPWC and configuration data. 7. Configuration Module programming is complete. If the CFG > prompt is still present type Exit<Enter> to exit the Configuration sub-mode CUW and CMR Commands An example CUW command/data string, its definition, and the corresponding CWR list is provided below. CUW command/data string: CFG > CUW 0/ / Above configuration defined: Category 1 Aircraft/Mode Type: 128 Category 2 Air Type: 3 Category 3 Position Type: 2 Category 4 Altitude Callouts Menu: 2 (All Callouts) Category 5 Audio Menu: 128 ( menu) Category 6 Display Type: 3 Category 7 Options Select Group #1: 29 (Selections shown at end of list) Category 8 Radio Altitude Type: 1 Category 9 Navigation Type: 0 CAGE CODE: SCALE: NONE SIZE: A DWG NO: REV: E SHEET 124

125 Category 10 Attitude Type: 2 Category 11 Heading Type: 0 Category 12 Windshear select Type: 0 Category 13 Discrete I/O Type: 129 Category 14 Audio Output Level Type: 0 Category 15 Autorotation Threshold 15 Category 16 Torque Type 1 Category 17 Options Select Group #2 123 (Selections shown at end of list) Category 18 Options Select Group #3 18 (Selections shown at end of list) Category 19 Options Select Group #4 0 (Selections shown at end of list) Peaks Mode Enable Obstacle Awareness Enabled GPS Altitude Ref. MSL Auto Rotation Callout Option 1 Selected Normal Pop Up 5 Selected Low Altitude Pop Up 2.5 Selected Normal Terrain With Airspeed Selected SAR Low Altitude Selected Audio Inhibit Time 5 CWR list: (based on the above configuration) CFG > CMR<Enter> CONFIGURATION MODULE: Format Version: 0 Category 1 ID: 128 Category 2 ID: 3 Category 3 ID: 2 Category 4 ID: 2 Category 5 ID: 128 Category 6 ID: 3 Category 7 ID: 29 Category 8 ID: 1 Category 9 ID: 0 Category 10 ID: 2 Category 11 ID: 0 Category 12 ID: 0 Category 13 ID: 129 Category 14 ID: 0 Category 15 ID: 15 Category 16 ID: 1 Category 17 ID: 123 Category 18 ID: 18 Category 19 ID: 0 CRC: Configuration Module Reprogramming Reprogramming the EGPWS Configuration Module is accomplished similar to the programming process above. Prior to reprogramming, the desired new configuration should be determined based on the MK XXII Installation Manual (Appendix E), document number For reprogramming the Configuration Module, the following procedure is used: 1. Verify EGPWC interface to P2 connector (including Configuration Module) and RS-232 interface to PC. CAGE CODE: SCALE: NONE SIZE: A DWG NO: REV: E SHEET 125

126 2. Power EGPWC and PC and start WinVIEWS. 3. With WinVIEWS active in the Terminal Mode, start the Configuration sub-mode by typing CFG at the prompt (>). At this point, either all the ID s can be rewritten using the CUW command as before, or individual categories can be changed as follows: 4. At the CFG > prompt use the CAT command with the following structure: - CAT<space><category #><space><id#><space><t or F><Enter> - <category #> is the Appendix E Category to change (example 7) - <ID #> is the new ID to change to (example 29) - <T or F> is True or False for rebooting the EGPWC. Use T if only one category is to be changed and the EGPWC will reboot following <Enter>. Use F if another individual ID is to be changed by another CAT operation. Example: CFG > CAT 7 29 T<Enter> 5. After inputting the desired change information, pressing <Enter> will transmit the data to the EGPWC to write to the Configuration Module. If a reboot is commanded (T), then the EGPWC will reboot at the completion of the write process. If a reboot is not commanded (F), then a message Writing to configuration module Category 7 ID updated successfully. is given and the CFG > prompt is again displayed. At this point the Configuration Module has been changed, but the change will not be effective until the EGPWC is rebooted. Additional changes can be made with the final change set to command the EGPWC to reboot (or cycle EGPWC power to reboot). 6. Verification of the changes made is the same as before. As above, type CFG to restart the Configuration sub-mode. At the CFG > prompt, type CMR<Enter>. Each category and its associated ID is read from the Configuration Module and listed on the PC display. Alternately, when not in the Configuration sub-mode, the command PS<Enter> (Present Status) will display the EGPWC and Configuration Module data. 7. Configuration Module reprogramming is complete Configuration Module RTC Update To improve the EGPWS GPS card Time-to-first-fix performance a new configuration module has been made available which includes a Real Time Clock and battery back up (super cap) RAM. Additional commands are added for this function to initialize the RTC and the position data stored in the RAM during installation. 1. RDT Read Date and Time returns the stored date and time from the configuration module and the GPS card in Zulu time as follows: RTC: hh:mm:ss_yymmdd example: RTC: 20:15:30_ GPS: 20:15:31_ RLL Read Latitude and Longitude returns the stored latitude and longitude from the configuration module and the GPS card in the following format: CFG MOD POS: (<Latitude>, <Longitude>) example: CFG MOD POS: , INT GPS POS: , WDT Write Date and Time enters a date and time to be stored in the configuration module in Zulu time as follows: CAGE CODE: SCALE: NONE SIZE: A DWG NO: REV: E SHEET 126

127 WDT hh:mm:ss_yymmdd example: WDT 20:15:30_ WLL Write Latitude and Longitude enters a latitude and longitude to be stored in the configuration module in the following format: WLL <Latitude>, <Longitude> example: WLL , Regional Terrain base Loading Effectivity The MK XXII EGPWS ( XX) are shipped from the factory with the Regional Terrain base requested by the customer installed. Aircraft operating outside of the installed region will have to load one of the other eight Regional Terrain bases before beginning the ground test. Use (operation) of a MK XXII EGPWS outside of the loaded Regional Terrain base will result in the Terrain Awareness function being unavailable Description This modification consists of loading the PCMCIA card into the EGPWS either In The Aircraft or On The Bench. An optional verification procedure is provided Approval This procedure contains no modification information that revises the approved configuration and therefore does not require FAA or other regulatory agency approval Material Cost and Availability Regional Terrain base PCMCIA cards are available for Operators that will be operating outside of the installed database region. To order a regional terrain database send a purchase order or request to Orders@Honeywell.com or Quotes@Honeywell.com listing the part number and quantity required: Vendor Name Vendor P/N Description QTY UM Honeywell P/N Honeywell XXXNAM North America 1 EA XXX Honeywell XXXSAM South America 1 EA XXX Honeywell XXXEUR Europe 1 EA XXX Honeywell XXXEEU Eastern Europe 1 EA XXX Honeywell XXXAFR Africa 1 EA XXX Honeywell XXPAC Pacific 1 EA XXX Honeywell XXXSPA South Pacific 1 EA XXX Honeywell XXXMES Middle East 1 EA XXX Honeywell XXXCAN Canada 1 EA XXX Honeywell XXXSAF South Africa 1 EA XXX Honeywell XXXASI Asia 1 EA XXX CAGE CODE: SCALE: NONE SIZE: A DWG NO: REV: E SHEET 127

128 4.6.5 Accomplishment Instructions Honeywell Load the PCMCIA card data as described in paragraphs A. or B. below. Loading time will be approximately 70 minutes. A. Loading the PCMCIA Card with the Computer mounted in the Aircraft. (1) Connect the Smart Cable (Honeywell PN ) to the EGPWC J3 connector. (2) Ensure that the 28 VDC circuit breaker to the EGPWC is ON and that the COMPUTER OK LED on the EGPWC front panel is on. (3) Insert the PCMCIA card into the Smart Cable PCMCIA card slot. NOTE: Precautionary notes on the PCMCIA card, regarding insertion and/or removal while power is applied, should be ignored since the EGPWC automatically handles the application and removal of PCMCIA card power. (4) While the loading is in progress, the IN PROG LED on the Smart Card remains ON and the COMPUTER OK LED on the EGPWC is OFF. (5) When loading is complete the XFER COMP LED on the Smart Card turns ON. (6) Remove the PCMCIA card from the Smart Card slot. (7) After approximately 15 seconds the COMPUTER OK LED comes ON to indicate that the contents of the PCMCIA card were successfully transferred. (8) Remove the Smart Card connector from the EGPWC front panel J3 connector. (9) To perform the verification of the Terrain base version, go to paragraph below. B. Loading the PCMCIA Card with the Computer removed from aircraft (1) Locate a 28 VDC Power Supply with a minimum supply current of 2 amps. (2) With the Power Supply turned OFF, connect the Power Supply to the J1 connector of the EGPWC as follows: J1 connector Pin Pin Nomenclature J1-40, J VDC (+) J1-41, J VDC (-) J1-42, J1-53 Chassis GND (3) Connect the Smart Cable (Honeywell PN ) to the EGPWC J3 connector. (4) Turn the Power Supply ON and verify the COMPUTER OK LED on front of the EGPWC panel is on. (5) Insert the PCMCIA card into the Smart Cable PCMCIA card slot. CAGE CODE: SCALE: NONE SIZE: A DWG NO: REV: E SHEET 128

129 NOTE: Precautionary notes on the PCMCIA card, regarding insertion and/or removal while power is applied, should be ignored since the EGPWC automatically handles the application and removal of PCMCIA card power. (6) While the loading is in progress, the IN PROG LED on the Smart Card remains ON and the COMPUTER OK LED on the EGPWC remains OFF. (7) When loading is complete the XFER COMP LED on the Smart Card turns ON. (8) Remove the PCMCIA card from the Smart Card slot. (9) After approximately 15 seconds the COMPUTER OK LED comes ON to indicate that the contents of the PCMCIA card were successfully transferred. (10) Remove the Smart Card connector from the EGPWC front panel J3 connector. (11) To perform the verification of the Terrain base version, go to paragraph below Verification of the Terrain base Version Since the EGPWC software verifies the PCMCIA card loading process, this verification is to assure the operator/installer that the correct Regional Terrain base version is installed. Terrain base version verification is accomplished with the EGPWS Self Test (ST) function. The ST function may be initiated from the aircraft cockpit with the GPWS Test Switch. NOTE: Initiation of the cockpit ST function may vary from one aircraft to another. For example, the ST function may be initiated by pressing the GPWS (PULL-UP) light assembly, or by activating a separate ST switch. The EGPWS ST function has 6 levels that describe the current condition and configuration of the EGPWS, the fault and warning history, and the condition of the various inputs. To help navigate through the various levels, there are 2 cancel functions: SHORT CANCEL (press and hold the ST button for more than 0.5 seconds, but less than 2 seconds) and LONG CANCEL (press and hold the ST button for more than 2 seconds, but less than 8 seconds). The Short Cancel and Long Cancel functions operate differently, depending upon the ST level. To initiate a ST sequence, or to continue from level-to-level, the ST button must also be pressed and held for more than 0.5 seconds, but less than 2 seconds, which is identical to the Short Cancel function. Therefore, for simplicity, the phrase Press ST Button in the verification procedure means to press and hold the ST button for more than 0.5 seconds, but less than 2 seconds. The procedure guides the operator directly to ST Level 3, System Configuration, skipping most of ST Level 1 and Level 2. To verify the Regional Terrain base that was just loaded into the EGPWC, perform these steps: NOTE: On the Bench, this test requires an audio speaker and a self test button. (1) Ensure the EGPWC power is ON CAGE CODE: SCALE: NONE SIZE: A DWG NO: REV: E SHEET 129

130 (2) Press ST button to initiate ST Level 1. (3) After ST Level 1 message starts, Press ST button to cancel Level 1 and start Level 2. (4) After ST Level 2 message, Current Faults, is heard, Press ST button to cancel Level 2. (5) When the message, Press to Continue, is heard, Press ST button to start ST Level 3. (6) Verify the Terrain base version annunciated in the following sequence: a) SYSTEM CONFIGURATION b) PART NUMBER XXX c) MOD STATUS XX d) SERIAL NUMBER XXXX e) APPLICATION SOFTWARE VERSION XXXXX f) TERRAIN DATABASE VERSION XXXX The following example of Terrain base Version annunciation: 424NAM (for NORTH AMERICA), 424EUR (for EUROPE), or 424PAC (for PACIFIC). Other versions/regions will follow the same pattern. (7) Other messages that follow the Terrain base Version can be ignored. When ST Level 3 finishes, the message Press to Continue is heard. If the ST button is not pressed again the ST sequence terminates. NOTE: If power was connected to the EGPWC per steps B1 through B4, perform shut-down per steps (7) and (8) following. (8) Turn Power Supply OFF. (9) Disconnect Power leads from the EGPWC. END OF TEST CAGE CODE: SCALE: NONE SIZE: A DWG NO: REV: E SHEET 130

131 SECTION V CERTIFICATION CAGE CODE: SCALE: NONE SIZE: A DWG NO: REV: E SHEET 131

132 SECTION V CERTIFICATION 5.1 Introduction This section outlines the procedures required to obtain FAA approval for the MK XXII EGPWS installation. 5.2 Certification Procedure Equipment Compatibility Careful consideration must be paid to the electrical characteristics of existing equipment or possible additions that will be interfaced to the MK XXII EGPWS, in order to ensure system compatibility. Section III of this manual provides system-planning guidelines, and defines the electrical characteristics of the EGPWS. The installing agency should contact Honeywell Complete Customer Care Center ( ), for information regarding the compatibility of equipment not listed in Section III or interface into any airframe not listed in Appendix E Table Equipment Location The EGPWS and associated indicators, annunciators, and switches should be clearly visible and within easy reach of the pilot(s). Refer to Section II of this manual for complete installation information FAA Requirements The installing agency should contact a local FAA Inspector who will determine whether the installation may be approved by Supplemental Type Certificate (STC) or by submitting FAA Form 337 with an applicable STC package Ground Test Honeywell has developed a generic Installation Ground Test Procedure for the MK XXII EGPWS, drawing number Flight Manual Revision Honeywell has developed a generic Rotorwing Flight Manual Supplement for the MK XXII EGPWS, drawing number for part number thru -024 and for part number CAGE CODE: SCALE: NONE SIZE: A DWG NO: REV: E SHEET 132

133 5.2.6 Flight Test Honeywell has developed a generic Flight Test procedure for the MK XXII EGPWS, drawing number The Flight Test procedure was developed for first of type installations, for these installations all sections of the Flight Test procedure shall be performed. For follow on installations of the same aircraft type and interface, the flight test is not required. When updating an STC to the current part number it is only necessary to flight test significant new features. The notice of change is available in Honeywell Service Bulletins Pilots Guide Honeywell has developed a Pilot s Guide for the MK XXII EGPWS, drawing number that provides a description of the modes and the controls of the EGPWS Failure Modes, Effects, and Safety Analysis Honeywell has developed a Failure Modes, Effects, and Safety Analysis document for the MK XXII EGPWS, drawing number that provides an analysis of the failure modes of the EGPWS Existing STC s For more information and a list of existing STC s see the EGPWS web site CAGE CODE: SCALE: NONE SIZE: A DWG NO: REV: E SHEET 133

134 APPENDIX A CUSTOMER WORKSHEET CAGE CODE: SCALE: NONE SIZE: A DWG NO: REV: E SHEET 134

135 MK XXII EGPWS ENHANCED GROUND PROXIMITY WARNING SYSTEM The purpose for this work sheet is to obtain the necessary aircraft data for determining the specific interface configuration for the MK XXII Enhanced Ground Proximity Warning System (EGPWS). For defined MK XXII EGPWS interface data, refer to Honeywell document No , Installation Manual for the MK XXII For product description information, refer to Honeywell document No , Product Specification for the MK XXII Enhanced Ground Proximity Warning System. Contact Honeywell EGPWS Applications Engineering for assistance. Aircraft Operator: Contact: Phone: Aircraft Type (be specific): Model S/N N # Installer: Contact: Phone: Engine Type (model number): AIRCRAFT SYSTEMS INFORMATION: Please provide the manufacturer, model number, part number, software part number, quantity per aircraft, and output data information for: SYSTEM MFGR. MODEL NO. PART NO. S/W PART NO. QTY Air Computers GPS * OUTPUT DATA FORMAT NOTES (ARINC 429, 547, 552, 575, DC, synchro, potentiometer, discrete, etc. Identify available ARINC 429 labels) Radio Altimeters ILS Receivers AHRS / IRU / INU VG DG Engine Torque * GPS Altitude Reference: WGS-84 MSL Use if Not Applicable CAGE CODE: SCALE: NONE SIZE: A DWG NO: REV: E SHEET 135

136 MK XXII EGPWS ENHANCED GROUND PROXIMITY WARNING SYSTEM COCKPIT DISPLAYS: Please provide the following information for intended EGPWS display purposes (include any new displays planned): SYSTEM QTY MANUFACTURER MODEL NO. PART NO. SOFTWARE NO. EFIS Symbol Generator EFIS Display EFIS Display Control Panel Multifunction Display (MFD) Weather Radar Indicator Weather Radar R/T Weather Radar Controller Other (specify) DISCRETE INPUTS: Please check applicable boxes for both up and down positions. PARAMETER GND OPEN +28 VDC DH > > WOW < < Landing Gear Down Landing Gear Up Notes: Listed below are typical parameters from each system, which are required to implement the EGPWS functions. Note that this list is a typical example. Actual source systems may vary depending on aircraft configuration and selected options. CAGE CODE: SCALE: NONE SIZE: A DWG NO: REV: E SHEET 136

137 MK XXII EGPWS ENHANCED GROUND PROXIMITY WARNING SYSTEM SYSTEM PARAMETERS RADIO ALTIMETER ADC IRS / AHRS ILS / NAV receiver FMS / GPS Engine 1 and 2 or FADEC Display radio altitude, decision height barometric altitude, corrected baro altitude, baro rate, computed airspeed, static air temperature or total air temperature magnetic heading, vertical velocity, pitch, roll glideslope deviation / flag, localizer deviation / flag altitude, latitude, longitude, ground speed, true track, true heading, mag variation, Nav mode, horizontal figure of merit, horizontal integrity limit, vertical figure of merit Torque GENERIC MODEL INFORMATION Aircraft Tail Geometry: Manufacturer: Model: (be specific) Engine(s): Height of Tail Tip of Tail to CG CAGE CODE: SCALE: NONE SIZE: A DWG NO: REV: E SHEET 137

138 MK XXII EGPWS ENHANCED GROUND PROXIMITY WARNING SYSTEM Height of Nominal CG above ground Distance from CG to Tail (Lowest point of tail or skid) Distance from CG to center of Tail Rotor Distance from lowest point of tail or tail-skid to ground Distance from tail rotor blade (lowest point) to ground Rotational Frequencies: Main Rotor RPM No. Of Blades (Main Rotor) SYSTEM Number of Engines DATA FORMAT Signal Scale Factor NOTES (ARINC 429, RS 422, RS 232, synchro, DC, AC In % Torque Engine Torque CAGE CODE: SCALE: NONE SIZE: A DWG NO: REV: E SHEET 138

139 APPENDIX B SAMPLE WIRING DIAGRAMS CAGE CODE: SCALE: NONE SIZE: A DWG NO: REV: E SHEET 139

140 AIRCRAFT +28 VDC ESS BUS RADIO ALTITUDE RADIO ALTIMETER R/T UNIT HI CAT. 8 ID # LO VALID RAD ALT INDICATOR RAD ALT DH GLIDESLOPE AND/OR LOCALIZER GLIDESLOPE RCVR NO.2 COPLT G/S DEV (+UP) G/S DEV (+DN) G/S VALID GLIDESLOPE RCVR NO.1 PILOT G/S DEV (+UP) G/S DEV (+DN) CAT. 9 ID # G/S VALID TTL NO.2 ILS SEL (GND) TTL NO.1 ILS SEL (GND) FLT DIR CTRL PNL NO.2 BACKCOURSE FLT DIR CTRL PNL NO.1 BACKCOURSE P1 CKT BKR PNL GPWS MK XXII EGPWS (+) LOW LEVEL (H) PRE-AMP OUTPUT 3 AMP (+) POWER 600 OHMS NOMINAL (C) INPUT: (RETURN) 28 VDC (RETURN) DC 42 CHASSIS GROUND AIRCRAFT 53 GROUND CHASSIS/SIGNAL DC GROUND HIGH LEVEL (H) SPEAKER OUTPUT 8 OHMS NOMINAL (C) DISPLAY (A) 64 (+) RADIO ALTITUDE INPUT RANGE #1 45 (-) ARINC 552 / ALT INPUT (B) 29 RAD ALT VALIDITY: +28 VDC OR P2 21 (A) RADIO ALTITUDE INPUT (B) ARINC 429 LS SH P1 33 DH DISCRETE GND = BELOW DH EGPWS OUTPUT (A) P2 ARINC 429 (B) 22 (A) ILS BUS INPUT (B) ARINC 429 LS AVIONIC SWITCH UNIT SH (CUSTOMER OPTION) OR P1 UP 65 TERRAIN DISPLAY (A) OUTPUT DATA #1 ARINC 453 (B) G/S DEV (+UP) DN 46 G/S DEV (+DN) TERRAIN DISPLAY (A) SH TTL SH 20 DC GND ILS FREQ OUTPUT DATA #2 OR ARINC 453 (B) VAL VDC SELECT SH + - OR SH G/S VALIDITY +28 VDC G/S DEV DC SIGNAL LOW LEVEL SIG RETURN VALIDITY 250mVDC P AU AU WX IN #1 453 (A) WX IN #1 453 (B) WX IN #2 453 (A) WX IN #2 453 (B) AVIONIC SWITCH UNIT (CUSTOMER OPTION) AUDIO UN-SWITCHED AUDIO IN PILOT ICS CHASSIS GND COPLT DSPLY CTL (DC-811) J1 TERRAIN SELECT POP-UP J1 DISPLAY CONFIGURATION EXAMPLE: ID 250 (SPZ7600 / EDZ705) COPLT SYMBOL GENERATOR J1A ( ) DC-811 DATA (+) CAT. 6 TERR SEL OUT ID # J2B (+) ARINC 2 DATA ( ) COPILOT INSTRUMENT PANEL WX VIDEO IN 1A WX VIDEO IN 1B TERR DISPLAY (GRN) ON (GRN) ANNUNCIATOR BOX SEE SHEET 2, ZONE D3 PILOT INSTRUMENT PANEL PLT DSPLY CTL (DC-811) J1 TERR DISPLAY ON (GRN) (GRN) PLT SYMBOL GENERATOR J1A ( ) DC-811 DATA (+) J2B WX VIDEO IN 1A WX VIDEO IN 1B (+) ( ) ARINC 2 DATA Honeywell International Inc. Redmond, Wasington DWG TITLE WIRING DIAGRAM, WORKSHEET Mk XXII ENHANCED GPWS FIGURE B1-1 REV LOCALIZER RCVR NO.1 PILOT LOC DEV (+LT) LOC DEV (+RT) LOC VALID TERR DISPLAY POPUP DISCRETE OUTPUT DISPLAY (A) RANGE #2 422 INPUT (B) OR VDC ILS OR 19 DC GND BACKCOURSE 30 LOC DEV (+LT) 10 LOC DEV (+RT) 48 LOC VALIDITY SH +28 VDC SH P P1 51 P AU SH SH TYP, 2 PLCS SH SH UN-SWITCHED AUDIO IN COPILOT COCKPIT CAT. 14 ICS SPEAKER ID # CHASSIS GND DEDICATED GPWS SPEAKER 8 OHM, 4 WATTS DO NOT CONNECT "SIGNAL RETURN" WIRE TO ANY GROUND MOM POP-UP TERRAIN SELECT J1 C/S MOM. TERR SEL OUT C CAGE CODE: SCALE: NONE SIZE: A DWG NO: REV: E SHEET 140

141 AIR DATA P2 AIR DATA COMPUTER MK XXII EGPWS CAT. 2 ID # CAT. 3 ID # STATIC PITOT POSITION ARINC 429 (A) OUTPUT (B) ARINC 743(A) GPS GPS #1 OUTPUT ARINC 429 ARINC 743(A) GPS GPS #2 OUTPUT ARINC 429 (A) (B) (A) (B) SH OAT PROBE SH OR OR DUAL SH SH SH P1 P (A) AIR DATA INPUT (B) ARINC 429 (+) (-) AIR DATA INPUT ANALOG DC AIR DATA VALIDITY DISCRETE (+28VDC) +5VDC REF AIR TEMP (+) AIR TEMP (-) GROUND (A) (B) GPS INPUT ARINC (A) GPS INPUT 6 (B) ARINC 429 OAT PROBE INPUT GPWS WARN OUTPUT GND = LAMP ON SELF TEST INPUT SELF TEST = GND GPWS CAUT OUTPUT GND = LAMP ON G/S CANCELLED LAMP OUTPUT GND = LAMP ON G/S CANCEL INPUT CANCEL = GND LOW ALT OUTPUT GND = LAMP ON LOW ALT INPUT LOW ALT = GND TERR AWARENESS & TCF INHIBIT INPUT INHIBIT = GND AUDIO INHIBIT INPUT INHIBIT = GND SH SH TIMED AUDIO INHIBIT OR LAMP OUTPUT 52 GND = LAMP ON NC 45 TX 29 RX GPS INPUT 28 COM RS232 OR GPS ANT. GPS ANTENNA TNC ATTITUDE/MAGNETIC HEADING CAT. 10 ID # NO.1 VG or AHRS ROLL ATTITUDE SYNCHRO (X) (Y) (Z) P1 21 (X) (Y) (Z) ROLL ATTITUDE SYNCHRO EGPWS MONITOR RS232C COM 1 (RX) 3 (TX) GND (X) PITCH ATTITUDE (Y) SYNCHRO (Z) 14 (X) PITCH (Y) ATTITUDE SYNCHRO (Z) ATTITUDE VALIDITY ATTITUDE VALID 68 DISCRETE (+28 VDC) CAT. 11 ID # HEADING SYNCHRO (X) (Y) (Z) HEADING VALID 26 VAC REF (H) (L) 22 (X) 23 (Y) (Z) MAGNETIC HEADING SYNCHRO 28 MAG HEADING VALIDITY DISCRETE (+28 VDC) 4 (H) 26 VAC REF 24 (L) GPWS INOP GND = LAMP ON TAD/TCF INOP GND = LAMP ON NO.1 DG or AHRS OR P2 23 (A) AHRS BUS INPUT (B) ARINC 429 HS AUDIO ON / TCAS INHIBIT OUT 69 SH P1 J3 P1 REF ONLY ANNUNCIATOR BOX PRESS-TO-TEST OUTPUT (GROUND = TEST) VISIBLE WHITE LEGEND PWR (0VDC DAY/+16VDC NIGHT) DEADFACE LEGEND PWR (+28VDC DAY/+16VDC NIGHT) A1A 18 CENTER INSTRUMENT PANEL GPWS INOP (AMBER) TERR INOP (AMBER) TCAS TPT-66A AUDIO INHIBIT PILOT/COPILOT INSTR PANEL SHEET 1, ZONE B2 GPWS LIGHTS 1 AMP AIRCRAFT +28VDC NO. 2 AVIONICS BUSS INPUT/OUTPUT DISCRETE FUNCTIONS PILOT INSTRUMENT PANEL GPWS (RED) CAT. 13 P/TEST (GRN) ID # MOM. GPWS (AMBER) G/S CANCLD (GRN) MOM. LOW ALT ON (GRN) (GRN) MOM. AUDIO INHIB ON (GRN) (AMBER) ALT. OPTIONAL TERR INHIBIT SEE BELOW COPILOT INSTRUMENT PANEL GPWS (RED) P/TEST (GRN) MOM. C/S GPWS (AMBER) G/S CANCLD (GRN) MOM. LOW ALT ON (GRN) (GRN) MOM. AUDIO INHIB ON (GRN) (AMBER) ALT. TERR INHIB ON (GRN) (AMBER) ALT. Honeywell International Inc. Redmond, Wasington DWG TITLE WIRING DIAGRAM, WORKSHEET Mk XXII ENHANCED GPWS FIGURE B1-2 REV. C CAGE CODE: SCALE: NONE SIZE: A DWG NO: REV: E SHEET 141

142 CAGE CODE: SCALE: NONE SIZE: A DWG NO: REV: E SHEET 142

143 APPENDIX C WinViews OPERATION INSTRUCTIONS CAGE CODE: SCALE: NONE SIZE: A DWG NO: REV: E SHEET 143

144 MK XXII Installation Manual APPENDIX C WinViews Operation Instructions RS-232 COMMUNICATION WITH THE EGPWS The EGPWS contains software that allows monitoring of its internal parameters, for testing purposes, without altering its operation. The monitoring of these parameter values enables the operator to quickly determine if the correct signal and scaling is being used by the EGPWS computer. The communication link utilizes the RS-232 Communication Protocol configured as follows: Baud, No Parity, 8 bits, and 1 stop bit. The RS-232 interface with the EGPWS is accomplished via the J3 test connector on the front of the EGPWS. The connection between a PC (with a standard DB9 serial port connector) and the EGPWS RS-232 interface is defined as follows: (Please note that the EGPWS will activate its RS-232 port only when it receives the command CONTROL Z after power is applied to the EGPWS. The CONTROL Z command is automatically sent by WinVIEWS) RS-232 Receive RS-232 Transmit RS-232 Ground EGPWS Front Connector Pin 3 Pin 4 Pin 1 Standard DB9 Connector (for a PC)* Pin 3 Pin 2 Pin 5 *NOTE: Some PC Comm Ports have Pins 2 & 3 reversed from what is described above. The mating connector for the EGPWS J3 test connector is a male (pins) 15 pin double density D- subminiature type, Positronics Industries (kit) part number ODD15M1OYOZ or the following individual parts: Nomenclature (AMP) Amp Part Number Military Part Number Connector Shell (HDP-22 Crimp Snap In Contact) reference MIL-C Size 22 DM Crimp Snap In Contacts Pin M39029/ Backshell (Shielded Cable Clamp Assembly) Jackscrews, 2 required (4-40 Male Jackscrew Kit) Grommet Sets The following tools will work with Positronics, Amp, and Mil Spec Connectors: Insertion / Extraction Tool M81969/1-04 Hand Crimp Tool Positioner M22520/2-01 M22520/2-09 CAGE CODE: SCALE: NONE SIZE: A DWG NO: REV: E SHEET 144

145 MK XXII Installation Manual WinVIEWS OPERATION: Windows Virtual Interface to the Enhanced Warning System WinVIEWS software is a tool developed by Honeywell to monitor or view values within the EGPWS. The WinVIEWS software provides a monitor function that does not alter the operation of the EGPWS. The monitoring of values assists in the installation testing of the EGPWS by allowing the operator to quickly determine if the correct signal and scaling is being used by the EGPWS. Additionally, WinVIEWS provides a detailed status of the software configuration and input signals which enables quick identification of system anomalies. WinVIEWS software can be ordered as Honeywell part number A User s Guide to WinVIEWS is available as Honeywell document number The software consists of the WinVIEWS executable file, a help file, and sample command files. Command file updates are available at The command file is a simple text file that should include each CVT Item used in this test procedure. A sample command file for this test procedure is found on the following page. The file must be a Text Only type of file, such as those created in the Microsoft Windows Note Pad program. It should have a filename extension of.cmd. Once this file is loaded, WinVIEWS can automatically display the current value of each parameter listed in the file. Normal Operation for Ground Testing the EGPWS: STEP 1 - Connect the PC to the EGPWS via the RS-232 cable as defined above. STEP 2 - On the PC, start Windows 3.1, or higher. STEP 3 - Start the WinVIEWS program. STEP 4 - Under the File Menu select the Load Command File option and load the appropriate Command File. STEP 5 - Use F6 to select Display Mode. Each CVT Item listed in the Command File will be continuously updated at a rate of greater than once per second. The values shown for the CVT Items listed will be the test values. CAGE CODE: SCALE: NONE SIZE: A DWG NO: REV: E SHEET 145

146 MK XXII Installation Manual Command File: MK XXII_GTP.CMD The format for the WinVIEWS command file is: 1. ASCII Text Only; no spaces 2. A CVT Item as specified in the test procedure 3. Each CVT Item Name is followed by a <return> or <enter> RawRA1 VF ARA1Val V DHDsc V RawBAlt1 VF RawBaroRt1 VF RawCAS1 VF RawSAT1 VF ILSTuned1 V GnILSTuned1 V RawAACGS1 VF AGS1Val V GPSLatude1 VF GPSLngude1 VF RawGLat1 VF RawGLng1 VF RawGAlt1 VF RawVFOM1 VF RawHFOM1 VF RawGGSpd1 VF RawHil1 VF RawGTTk1 VF RawRoll1 VF RawPitch1 VF AnAtt1Val V RawAACMHD VF AACMHDVal V WOWDsc V LandGrDsc V GSCan V AudInhDsc V M6LwVolDsc V GSInh V GSlnhDsc V TAWxRng1 VF TAWxRng2 VF TerrDis V AnaTerrDis V RawTorque1 VF RawTorque2 VF TacticalSel V TAInop C TAInop1 C TAInop2 C EngTorque1 VF EngTorque2 VF DispRngOut1 V DispRngOut2 V CAGE CODE: SCALE: NONE SIZE: A DWG NO: REV: E SHEET 146

147 APPENDIX D VENDOR DRAWINGS CAGE CODE: SCALE: NONE SIZE: A DWG NO: REV: E SHEET 147

148 D 1.0 Vendor Contact Information Honeywell APPENDIX D VENDOR DRAWINGS The vendor contact information provided below is current at the time of publication of this document. AMP Barry Controls Donel Systems EDMO Electronic Cable Specialists and Electrical Conservation Systems, Inc. EMTEQ, Inc Fulling Mill Road MS Middletown, PA Burbank, CA Brighton, MA Don Wilen (516) E. Rutter Ave. Spokane, WA W Franklin Drive Franklin, WI S84 W18693 Enterprise Drive Muskego, WI (888) (262) (262) Fax smatar@emteq.com United Kingdom: Surrey, England 44 (0932) Germany: Raunheim, Germany 49 (6142) 43077/8/9 FreeFlight Systems 3700 Interstate 35 Waco, TX Hollingsead International Sante Fe Springs, CA Todd Ellison, Sales Engineer IDD Aerospace ITT Cannon Redmond, WA Santa Ana, CA Kollsman CIC Cheryl CAGE CODE: SCALE: NONE SIZE: A DWG NO: REV: E SHEET 148

149 Korry Electronics Master Specialties Co. 901 Dexter Avenue North Seattle, WA Attention: Airline Sales For orders and AOG requirements, contact: Sonya Cordova fax: SITA: SEAKEXD For engineering inquiries, contact: Bob Jacques Airline Business Manager fax: Costa Mesa, CA Tom Howard Airline Business Manager fax: Optima Wire PIC Wire & Cable Supply Sensor Systems, Inc. StacoSwitch 1120 Harpeth Industrial Ct. Franklin, TN N63 W22619 Main Street P.O. Box 330 Sussex, WI Fax: Fullbright Avenue Chatsworth, CA Fax: Baker Street Costa Mesa, CA Fax: Cathy Harper Dan Sugg Also contact EDMO Avionics Distributor for StacoSwitch West Coast Specialties P.O. Box 5010 Preston, WA Fax: Contact: Bruce Maxwell, (Rep) Fax: CAGE CODE: SCALE: NONE SIZE: A DWG NO: REV: E SHEET 149

150 D 1.1 EDMO EDMO Distributors (800) One Stop Shopping for the following EGPWS and TAWS support products: * MD41-12XX/13XX TAWS ACU s from Mid-Continent Instruments * PMA d TAWS ACU from West Coast Specialties * Eaton and StacoSwitch EGPWS split switch & annunciator kits * Shadin XYZ compass to RS-232/422 Converters * Shadin low cost Airdata computers * Solid State Altitude Encoders (most models) * GAE-1575 GPS Repeater for hangar testing * Installation Supplies CAGE CODE: SCALE: NONE SIZE: A DWG NO: REV: E SHEET 150