L 3 Communications Avionics Systems TRC899 User Manual Install Manual
L-3 Communications, Avionics Systems Install Manual
Contents
- 1. User Manual 1 of 2
- 2. User Manual 2 of 2
- 3. Install Manual
Install Manual
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| Document ID | 149253 |
| Application ID | /OG8MYVI76oBGUZzUkPJtQ== |
| Document Description | Install Manual |
| Short Term Confidential | No |
| Permanent Confidential | No |
| Supercede | No |
| Document Type | User Manual |
| Display Format | Adobe Acrobat PDF - pdf |
| Filesize | 163.79kB (2047380 bits) |
| Date Submitted | 2001-05-11 00:00:00 |
| Date Available | 2001-11-26 00:00:00 |
| Creation Date | 2001-03-14 12:06:38 |
| Producing Software | Acrobat Distiller 4.05 for Windows |
| Document Lastmod | 2001-04-04 07:38:54 |
| Document Title | Install Manual |
Traffic Alert/Advisory System im in ar SKY899 Installation Manual Pr el This manual contains installation instructions and recommended flightline maintenance information for the SKY899 Traffic Alert/Advisory System. This information is supplemented and kept current by Change Notices, Service Bulletins, and Service Memos published by BFGoodrich Avionics Systems. 009-11900-001 (Rev. A) BFGoodrich Avionics Systems, Inc. nd 5353 52 Street, S.E. Grand Rapids, MI USA 49512 30 April 2001 ABOUT THIS MANUAL Chapter 1 – General Information This chapter includes equipment specifications and a functional description. It describes the various hardware configurations and includes a list of items furnished and items required but not supplied with the equipment. Chapter 2 - Installation This chapter contains instructions for unpacking the equipment and inspection for in-shipment damage. It also includes information required to locate, assemble and install the equipment. Chapter 3 – Installation Checkout This chapter contains instructions for doing post-installation and return to service checkout of the SKY899 using the BFGoodrich Avionics Systems TT391 Flightline Tester. ar Chapter 4 – Maintenance This chapter contains general flightline maintenance procedures. It includes periodic maintenance and troubleshooting; instructions for calibrating the directional antenna and instructions for the return of defective components. Appendix A – Signal and Cable Characteristics This appendix defines the electrical characteristics of all input and output signals. in Appendix B – Environmental Qualification Form This appendix has the environmental qualification forms for the TRC899, NY156 & NY164 antennas, and WX-1000/SKY497 display. im Appendix C – Installation Checkout Using The TCAS-201 Ramp Test Set This appendix contains instructions for doing post-installation and return to service checkout of the SKY899 using the IFR Systems TCAS-201 Ramp Test Set (with TCAS I firmware). Pr el Appendix D – Installation Checkout Using The TIC T-49C Flightline Tester This appendix contains instructions for doing post-installation and return to service checkout of the SKY899 using the TIC T-49C Flightline Tester. Appendix E – Using The Terminal Device This appendix contains instructions for using the Terminal Device for installation, testing or troubleshooting of the SKY899. Appendix F – Installation Checkout Using an Alternate Display This appendix contains instructions for doing post-installation and return to service checkout of the SKY899 using an Alternate Display. © Copyright 2001 BFGoodrich Avionics Systems, Inc. ____________________________ Trademarks Alodine® is a registered trademark of Amchem Products, Inc. Flamemaster® is a registered trademark of Flamemaster. HyperTerminal® is a registered trademark of Hilgraeve, Inc. Mylar® and Teflon® are registered trademarks of DuPont. Procomm® is a registered trademark of Datastorm Technologies, Inc. SKYWATCH® HP and Stormscope® are registered trademarks of BFGoodrich Avionics Systems, Inc. Rev. A SKY899 Installation Manual LIST OF EFFECTIVE PAGES Dates of original and changed pages are: Original (Rev. A) .......................... 30 April 2001 NOTE in Page No. ar Total number of pages in this publication consists of the following: The portion of the text affected by the change is indicated by a vertical line in the outer margins of the page. Changes to illustrations (other than diagrams and schematics) are identified with a miniature pointing hand. Shading is used to highlight the area of diagrams and schematics containing a change. Change No. Pr el im Title Page ................................................................. 0 A Page ..................................................................... 0 i thru viii .................................................................... 0 1-1 thru 1-24 ............................................................. 0 2-1 thru 2-36 ............................................................. 0 3-1 thru 3-8 ............................................................... 0 4-1 thru 4-24 ............................................................. 0 A-1 thru A-14 ............................................................ 0 B-1 thru B-4 .............................................................. 0 C-1 thru C-6 .............................................................. 0 D-1 thru D-4 .............................................................. 0 E-1 thru E-6 .............................................................. 0 F-1 thru F-6............................................................... 0 INSERT LATEST CHANGED PAGES, DESTROY SUPERSEDED PAGES. Those responsible for maintaining this publication should ensure that all previous changes have been received and incorporated. Rev. A SKY899 Installation Manual FOREWORD This manual provides information intended for use by persons who, pursuant to current regulatory requirements, are qualified to install this equipment. Because installations vary depending on a particular aircraft, this manual is intended as a guideline. Standard installation practices prescribed in FAA Advisory Circular No. 43.13 must be followed. If further information is required, contact: ar BFGoodrich Avionics Systems Attn: Field Service Engineering 5353 52nd Street, S.E. Grand Rapids, MI USA 49512 Tel. (800) 453-0288 or (616) 949-6600 in We welcome your comments concerning this manual. Although every effort has been made to keep it free of errors, some may occur. When reporting a specific problem, please describe it briefly and include the manual part number, the paragraph/figure/table number, and the page number. Send your comments to: Pr el im BFGoodrich Avionics Systems Attn: Technical Publications 5353 52nd Street, S.E. Grand Rapids, MI USA 49512 ii Rev. A SKY899 Installation Manual TABLE OF CONTENTS Paragraph Page 2.1 2.2 2.3 2.4 2.5 2.6 2.6.1 2.6.2 2.6.3 2.6.4 2.6.5 2.6.6 2.6.7 2.6.8 2.7 2.7.1 2.7.2 2.7.3 2.7.4 2.7.5 2.8 2.9 2.9.1 2.9.2 2.9.3 2.9.4 Chapter 2 INSTALLATION INTRODUCTION .................................................................................................................................. 2-1 UNPACKING, INSPECTION AND STORAGE .................................................................................. 2-1 ANTENNA LOCATION ........................................................................................................................ 2-2 TRC LOCATION.................................................................................................................................... 2-2 DISPLAY LOCATION ......................................................................................................................... 2-15 CABLE REQUIREMENTS AND FABRICATION ............................................................................ 2-16 Antenna Cables.................................................................................................................................... 2-18 Audio Output Cable............................................................................................................................. 2-18 Data Cables .......................................................................................................................................... 2-18 Heading Input Cable ........................................................................................................................... 2-19 Power Cable ......................................................................................................................................... 2-19 Suppression Bus Cable........................................................................................................................ 2-20 WX-1000/SKY497 Display and WX-1000 Processor Cable................................................................ 2-20 Converting Existing Aircraft Wiring from SKY497 to SKY899........................................................ 2-21 AIRCRAFT DISCRETE INPUTS ....................................................................................................... 2-22 Audio Inhibit (Terrain Warning System - GPWS)............................................................................. 2-22 Landing Gear ....................................................................................................................................... 2-22 SKYWATCH/Stormscope Mode Switch .............................................................................................. 2-22 Squat Switch (Weight-On-Wheels) ..................................................................................................... 2-22 ON/OFF Power Switch ........................................................................................................................ 2-23 ALTERNATE DISPLAY...................................................................................................................... 2-24 ARINC-429 ........................................................................................................................................... 2-24 General Sensor Inputs......................................................................................................................... 2-24 Mode S Transponder I/O (future option)............................................................................................ 2-24 Alternate Display Output.................................................................................................................... 2-25 Future Option ...................................................................................................................................... 2-25 Pr el im in ar 1.1 1.2 1.3 1.3.1 1.3.2 1.3.3 1.3.4 1.4 1.4.1 1.4.2 1.4.3 1.5 1.6 1.7 1.8 1.9 1.9.1 1.9.2 Chapter 1 GENERAL INFORMATION INTRODUCTION .................................................................................................................................. 1-1 FUNCTIONAL DESCRIPTION ........................................................................................................... 1-2 PHYSICAL DESCRIPTION.................................................................................................................. 1-2 TRC899 Transmitter Receiver Computer P/N 805-11900-xxx............................................................ 1-6 Configuration Module P/N 814-18005-001......................................................................................... 1-10 Display (Alternate or WX-1000/SKY497 Display P/N 78-8060-5900-x) ........................................... 1-11 Directional Antenna (NY156 P/N 805-10003-001 or NY164 P/N 805-10890-001)........................... 1-13 SPECIFICATIONS .............................................................................................................................. 1-15 Transmitter Receiver Computer (TRC).............................................................................................. 1-15 WX-1000/SKY497 Display................................................................................................................... 1-16 Directional Antenna ............................................................................................................................ 1-16 MODIFICATIONS & SOFTWARE REVISIONS............................................................................... 1-16 INTERFACE ........................................................................................................................................ 1-17 EQUIPMENT REQUIRED NOT SUPPLIED.................................................................................... 1-17 INSTALLATION APPROVAL ............................................................................................................ 1-22 WARRANTY INFORMATION............................................................................................................ 1-22 Warranty Statement............................................................................................................................ 1-22 Related Policies and Procedures......................................................................................................... 1-23 iii Rev. A SKY899 Installation Manual TABLE OF CONTENTS (Continued) 2.10 2.11 2.11.1 2.11.2 2.12 2.13 2.13.1 2.13.2 2.14 2.15 2.16 2.17 2.17.1 2.17.2 2.18 2.19 2.20 2.21 2.22 2.23 2.24 2.25 2.26 2.27 2.27.1 2.27.2 Page Chapter 2 INSTALLATION AUDIO (ALERT) OUTPUT ................................................................................................................ 2-25 BAROMETRIC (UNCORRECTED) ALTITUDE INPUTS ............................................................... 2-25 Gilham Code (Encoding Altimeter) .................................................................................................... 2-26 ADC (ARINC-429) ............................................................................................................................... 2-26 GPS (ARINC-429)................................................................................................................................ 2-26 HEADING INPUT............................................................................................................................... 2-26 Compass Synchro (XYZ)...................................................................................................................... 2-26 AHRS (Attitude Heading and Reference System)............................................................................. 2-27 LAMP OUTPUTS (ABV and BLW) .................................................................................................... 2-27 OPERATIONAL MODE OUTPUT (optional).................................................................................... 2-27 POWER INPUT ................................................................................................................................... 2-27 RADIO ALTIMETER (optional) ......................................................................................................... 2-27 Analog .................................................................................................................................................. 2-28 ARINC-429........................................................................................................................................... 2-28 SERIAL DATA..................................................................................................................................... 2-28 SOFT-KEYS......................................................................................................................................... 2-28 SUPPRESSION BUS I/O .................................................................................................................... 2-28 SYSTEM CONFIGURATION MODULE........................................................................................... 2-28 WX-1000/SKY497 DISPLAY (OPTIONAL) ....................................................................................... 2-30 WX-1000 PROCESSOR (OPTIONAL)................................................................................................ 2-30 ANTENNA INSTALLATION ............................................................................................................. 2-31 TRC MOUNTING TRAY INSTALLATION....................................................................................... 2-32 TRC INSTALLATION......................................................................................................................... 2-34 MOUNTING the WX-1000/SKY497 DISPLAY.................................................................................. 2-36 Panel Cutout........................................................................................................................................ 2-36 Display Installation............................................................................................................................. 2-37 3.1 3.2 3.3 3.3.1 3.3.2 3.4 Chapter 3 INSTALLATION CHECKOUT INTRODUCTION.................................................................................................................................. 3-1 CONTROLS ........................................................................................................................................... 3-1 CHECKOUT PROCEDURE ................................................................................................................. 3-2 System Setup ......................................................................................................................................... 3-3 System Setup Verification and Operation ........................................................................................... 3-5 SELF TEST............................................................................................................................................ 3-7 Pr el im in ar Paragraph Chapter 4 MAINTENANCE 4.1 INTRODUCTION.................................................................................................................................. 4-1 4.2 CONTINUED AIRWORTHINESS....................................................................................................... 4-1 4.3 PERIODIC MAINTENANCE ............................................................................................................... 4-1 4.3.1 WX-1000/SKY497 Display .................................................................................................................... 4-1 4.3.2 TRC ........................................................................................................................................................ 4-1 4.3.3 Antenna.................................................................................................................................................. 4-1 4.4 SERVICE MENU .................................................................................................................................. 4-2 4.4.1 Setup ...................................................................................................................................................... 4-3 4.4.1.1 Aircraft Type.......................................................................................................................................... 4-3 iv Rev. A SKY899 Installation Manual TABLE OF CONTENTS (Continued) 4.4.1.2 4.4.1.3 4.4.1.4 4.4.1.5 4.4.2 4.4.2.1 4.4.2.2 4.4.2.3 4.4.3 4.4.4 4.5 4.6 4.7 4.8 Page Chapter 4 MAINTENANCE Antenna System..................................................................................................................................... 4-4 Audio Level ............................................................................................................................................ 4-4 Communication Ports ............................................................................................................................ 4-4 Avionics Equipment............................................................................................................................... 4-6 Information ............................................................................................................................................ 4-8 Software Version.................................................................................................................................... 4-9 System Log ............................................................................................................................................. 4-9 Data Monitor........................................................................................................................................ 4-10 Calibration ........................................................................................................................................... 4-12 Ground Test ......................................................................................................................................... 4-12 TROUBLESHOOTING ....................................................................................................................... 4-17 ERROR MESSAGES ........................................................................................................................... 4-18 TRC899/WX-1000 ADAPTER PLUG .................................................................................................. 4-20 DISPOSITION OF FAILED ITEMS................................................................................................... 4-21 A.1 A.2 A.3 Appendix A SKY899 INTERFACE SIGNAL & CABLE CHARACTERISTICS INTRODUCTION ................................................................................................................................. A-1 ELECTRICAL CHARACTERISTICS .................................................................................................. A-1 ARINC-429 LABELS .......................................................................................................................... A-11 im in ar Paragraph Appendix B ENVIRONMENTAL QUALIFICATION FORM TRC899 ENVIRONMENTAL QUALIFICATION FORM .................................................................. B-1 NY156 & NY164 ENVIRONMENTAL QUALIFICATION FORM .................................................... B-2 WX-1000/SKY497 DISPLAY ENVIRONMENTAL QUALIFICATION FORM ................................ B-3 Pr el B.1 B.2 B.3 Appendix C INSTALLATION CHECKOUT USING THE TCAS-201 RAMP TEST SET C.1 C.2 C.3 INTRODUCTION ................................................................................................................................. C-1 CONTROLS........................................................................................................................................... C-1 CHECKOUT PROCEDURE................................................................................................................. C-2 Appendix D INSTALLATION CHECKOUT USING THE TIC T-49C FLIGHTLINE TESTER D.1 D.2 D.3 INTRODUCTION ................................................................................................................................. D-1 CONTROLS........................................................................................................................................... D-1 CHECKOUT PROCEDURE................................................................................................................. D-2 Appendix E USING THE TERMINAL DEVICE USING THE TERMINAL DEVICE ................................................................................................................. E-1 Rev. A SKY899 Installation Manual TABLE OF CONTENTS (Continued) Appendix F INSTALLATION CHECKOUT USING AN ALTERNATE DISPLAY F.1 F.2 F.3 F.4 INTRODUCTION.................................................................................................................................. F-1 CONTROLS ........................................................................................................................................... F-1 CHECKOUT PROCEDURE ................................................................................................................. F-1 SELF TEST............................................................................................................................................ F-5 LIST OF ILLUSTRATIONS Figure Page Vertical Display Modes ......................................................................................................................... 1-4 SKY899 System Block Diagram ........................................................................................................... 1-5 Standard TRC Mounting Tray (P/N 805-10870-001) .......................................................................... 1-8 Ruggedized TRC Mounting Tray (P/N 805-10870-003)....................................................................... 1-9 P1 Connector Dimensions (Reference Only)........................................................................................ 1-9 TRC899 Transmitter Receiver Computer (TRC)............................................................................... 1-10 System Configuration Module ............................................................................................................ 1-10 WX-1000/SKY497 Display Equipment Tag ....................................................................................... 1-11 WX-1000/SKY497 Display .................................................................................................................. 1-12 NY156/NY164 Directional Antenna ................................................................................................... 1-14 2-1 2-2 2-3 2-4 2-5 2-6 2-7 2-8 2-9 2-10 2-11 2-12 2-13 2-14 2-15 2-16 Directional Antenna Mounting Location ............................................................................................. 2-2 Interconnect Wiring Without WX-1000 ............................................................................................... 2-3 Interconnect Wiring With WX-1000..................................................................................................... 2-7 Interconnect Wiring With Alternate Display .................................................................................... 2-11 Heading Input Cable ........................................................................................................................... 2-18 Display Cable....................................................................................................................................... 2-20 Above and Below External Lamps ..................................................................................................... 2-26 System Configuration Module ............................................................................................................ 2-28 Typical Location of Configuration Module (Inside Backshell) ......................................................... 2-29 Antenna Mounting Holes.................................................................................................................... 2-31 Directional Antenna Installation ....................................................................................................... 2-31 Mounting Holes for Standard Mount Tray, P/N 805-10870-001 ...................................................... 2-32 Mounting Holes for Ruggedized Mount Tray, P/N 805-10870-003 .................................................. 2-33 TRC899 Installation ............................................................................................................................ 2-34 Instrument Panel Cutout and Mounting Holes................................................................................. 2-35 Display Installation............................................................................................................................. 2-36 3-1 3-2 3-3 3-4 3-5 Controls.................................................................................................................................................. 3-1 Start-up Screen...................................................................................................................................... 3-2 Standby Screen...................................................................................................................................... 3-3 Typical Patch Antenna Tripod Mount.................................................................................................. 3-6 Self Test Screen ..................................................................................................................................... 3-8 4-1 4-2 4-3 4-4 4-4 4-4 Service Menu (Terminal Emulation Program).................................................................................... 4-2 Service Menu (WX-1000/SKY497 Display) .......................................................................................... 4-2 Compact Flash Insertion Instructions ............................................................................................... 4-16 Service Menu Tree (Sheet 1 of 3)........................................................................................................ 4-17 Service Menu Tree (Sheet 2 of 3)........................................................................................................ 4-18 Service Menu Tree (Sheet 3 of 3)........................................................................................................ 4-19 vi Rev. A Pr el im in ar 1-1 1-2 1-3 1-4 1-5 1-6 1-7 1-8 1-9 1-10 SKY899 Installation Manual TABLE OF CONTENTS (Continued) LIST OF ILLUSTRATIONS Figure Page Adapter Plug Assembly ....................................................................................................................... 4-24 A-1 P1 Connector Pin Identifiers.............................................................................................................. A-11 C-1 C-2 C-3 Controls ................................................................................................................................................. C-1 Start-Up Screen .................................................................................................................................... C-3 Standby Screen ..................................................................................................................................... C-3 D-1 D-2 D-3 Controls ................................................................................................................................................. D-1 Start-Up Screen .................................................................................................................................... D-2 Standby Screen ..................................................................................................................................... D-3 F-1 F-2 F-3 SKYWATCH Startup Screen on Terminal Device...............................................................................F-2 External Annunciator Operation..........................................................................................................F-3 Typical Patch Antenna Tripod Mount..................................................................................................F-4 in ar 4-5 LIST OF TABLES Table Page SKY899 System...................................................................................................................................... 1-6 TRC Installation Kit P/N 817-11900-xxx ............................................................................................. 1-7 WX-1000/SKY497 Display Installation Kit P/N 817-10802-001 ....................................................... 1-11 Airframe Installation Kits................................................................................................................... 1-13 Directional Antenna Installation Kit 817-10009-xxx ........................................................................ 1-14 TRC899 Software Revisions................................................................................................................ 1-17 Minimum Interface Equipment Required.......................................................................................... 1-17 Directional Antenna SIGMA and DELTA Port Cable Vendors ........................................................ 1-18 Cable to Connector Reference ............................................................................................................. 1-19 Heading Input Cable Vendors ............................................................................................................ 1-20 Display Cable Vendors ........................................................................................................................ 1-22 2-1 2-2 2-3 Alternate Display Drivers ................................................................................................................... 2-25 WX-1000/SKY497 Display Connection ............................................................................................... 2-30 WX-1000 Processor Connection .......................................................................................................... 2-30 4-1 4-2 4-3 Fault Isolation...................................................................................................................................... 4-20 Installation Related Error Messages.................................................................................................. 4-21 Informational Error Messages ............................................................................................................ 4-22 A-1 A-2 ARINC-429 Input Labels (Rx)............................................................................................................ A-13 ARINC-429 Output Labels (Tx) ......................................................................................................... A-14 C-1 IFR Systems TCAS-201 Ramp Test Set Setup Data .......................................................................... C-2 Pr el im 1-1 1-2 1-3 1-4 1-5 1-6 1-7 1-8 1-9 1-10 1-11 vii Rev. A in ar SKY899 Installation Manual Pr el im This page intentionally left blank. viii Rev. A SKY899 Installation Manual CHAPTER 1 GENERAL INFORMATION 1.1 INTRODUCTION This section contains a functional description of the BFGoodrich Avionics Systems SKY899 traffic alert/advisory system sensor, describes the various hardware and software configurations, outlines the main features of the system, and provides a system block diagram. The SKY899 is a new generation traffic alert/advisory system that has different inputs and outputs and it requires different wiring than the SKY497. Connector P1 is keyed differently to prevent connection to the wrong TRC. NOTES 1. The SKY899 is designed to be installed as a TCAS I traffic alert system or as a TAS traffic advisory system. The system installation differences are as follows: TCAS I installations requires an alternate display device (i.e., EFIS, MFD, IVSI, weather radar indicator) FAA approved for displaying TCAS I information and the antenna must be an NY156 directional antenna. • TAS installations can have an alternate display device, the WX-1000/SKY497 display, or both as the primary means displaying traffic information. Either the NY156 or NY164 directional antenna can be used. in ar • im 2. Contact Field Service Engineering at 1-800-453-0288 or 1-616-949-6600 for approved displays and software version requirements of the TRC899. 3. The SKY899 does not track intruder aircraft approaching at a closure rate greater than 1200 knots. Pr el 4. This section provides installation information for the SKY899 using the WX1000/SKY497 Display. If using an alternate display device refer to manufacturer instructions for installation details. 5. When interfacing to a weather radar indicator via the BFGoodrich Avionics Systems RGC250 (Radar Graphics Computer) refer to the RGC250 Installation Manual for installation instructions. RGC250 must have software version 1.5 or later. 6. When an alternate display device is installed the service menu can not be accessed via the display, therefore a terminal device (i.e., laptop) is required for system setup and post-installation checkout (refer to appendix E). 7. When planning ARINC-429 receiver interfaces note that: • The equipment connected to receive channels 1 and 2 must be the same speed (12.5 or 100 kHz). • The equipment connected to receive channels 3 and 4 must be the same speed (12.5 or 100 kHz). • Channel 5 receiver is independent of the other receivers and can be set to 12.5 or 100 kHz. 8. In order to use ADS-B SKYWATCH HP requires a GPS input that is GAMA or ARINC-743A compliant. 1-1 Rev. A SKY899 Installation Manual 1.2 FUNCTIONAL DESCRIPTION The BFG Avionics Systems SKYWATCH® HP SKY899 is a new generation airborne traffic alert/advisory system that increases the active-mode surveillance range over the SKY497 system from 20 nmi to 35 nmi and adds Automatic Dependent Surveillance-Broadcast (ADS-B) surveillance mode. The SKY899 continuously monitors the dedicated data link frequency (1090 MHz) for ADS-B mode S extended squitter messages within 50 nmi. The ADS-B message contains navigational information about the intruder aircraft including GPS position, ident, ground speed, and intent. The SKY899 uses this navigational information along with its own aircraft GPS navigation data to calculate the relative position of the intruder to augment its active ATCRBS surveillance of the intruder. ADS-B surveillance enhances the traffic alert/advisory abilities by increasing the accuracy of the active-mode surveillance. The SKY899 does not require a mode S transponder, ADS-B capable or otherwise to perform its ADS-B surveillance. ar The SKY899 advises the flight crew where to look for aircraft that may pose a collision threat. It is intended for use by corporate and general aviation aircraft. SKY899 alerts the flight crew to nearby transponder equipped aircraft and assists the pilot in the visual acquisition of aircraft that may represent a danger. Traffic information out to a selected range is graphically displayed on the display. Using shapes (i.e., Traffic Advisory = solid circle; Other Traffic = open diamond) and text, the display shows the relative position of threat aircraft. im in 1.3 PHYSICAL DESCRIPTION The SKY899 System consists of the following main components: • Transmitter Receiver Computer • System Configuration Module • Alternate Display (or optional monochrome WX-1000/SKY497 display) • Directional Antenna, NY156 or NY164 (depending on TCAS I or TAS installation) Pr el SKY899 is an active system that operates as an aircraft-to-aircraft interrogation device. The SKY899 equipment interrogates transponders in the surrounding airspace similar to ground based radars. When replies to these active interrogations are received, the responding aircraft’s range, altitude, and closure rates are computed to plot traffic location and predict collision threats. The effective active range is approximately 20 nmi. The SKY899 does not transmit ADS-B interrogations, in order to transmit your aircraft position you must have a mode S transponder capable of ADS-B interrogations. Figure 1-1 shows the SKY899 vertical display modes used to display intruding aircraft. The unrestricted altitude of the surveillance zone is ±10,000 ft, but the display is only capable of showing to ±9,900 ft. A simplified block diagram of the system and their relationships is shown in figure 1-2. 1-2 Rev. A SKY899 Installation Manual Major differences between SKYWATCH and SKYWATCH HP are listed below: Category SKY899 • Active ATCRBS Display Range 6 nmi display range 15 nmi display range • Active ATCRBS Surveillance Range 11 nmi surveillance range 35 nmi surveillance range • Active ATCRBS Interrogation Power Low-power interrogations High-power interrogations • Number of Whisper-Shout Steps 4 Whisper-Shout steps 7 Whisper-Shout steps • Active ATCRBS Interference Limiting No interference limiting TCAS I for TAS interference limiting • ADS-B Surveillance None ADS-B surveillance range 50 nmi • Performance Single-sensor target tracking Multisensor target tracking • Closure Rate 900 kn closure rate 1200 kn closure rate • Antenna Configurations Single directional antenna Multiple antenna configurations via external ASU (future option) • Aircraft Power Input 11 V dc to 34 V dc • Stepper Compass Input Accepts stepper compass input Will not accept stepper compass input • Radio Altitude Input Accepts only ARINC 429 radio altitude Accepts both analog and ARINC 429 radio altitude • Display Ranges (WX-1000 CDU) 2 nmi and 6 nmi 2 nmi, 6 nmi, and 15 nmi • Installation Configuration Data Connector configuration pins System configuration module • Vertical Display Modes Normal, Above, & Below ±9,000 ft Normal, Above, Below & Unrestricted ±9,900 ft SKY497 Pr el im in ar 18 V dc to 32 V dc 1-3 Rev. A SKY899 Installation Manual Max. Display Range +9900 ft Max. Display Range +9000 ft Intruder Aircraft +2700 ft in 0.2 nmi +800 ft +600 ft 0 ft This area or 20 seconds * –600 ft Sensitivity Level B im This area or 30 seconds ** *15 seconds for non-altitude reporting intruder aircraft **20 seconds for non-altitude reporting intruder aircraft Traffic Advisory Symbol Other Traffic Symbol Figure 1-1. Vertical Display Modes 1-4 Rev. A +1200 ft Sensitivity Level A Pr el Normal (NRM) 0.55 nmi ar 4 nmi Look Down (BLW) Unrestricted (UNR) Look Up (ABV) Max. Display Range –800 ft –1200 ft –2700 ft Not To Scale –9000 ft –9900 ft SKY899 Installation Manual Intruder Aircraft +28 VDC +28 VDC Return Transponder Interrogations Transponder Replies Transponder Interrogations Transponder Replies ADS-B Squitter Broadcasts ADS-B Squitter Broadcasts Barometric Altitude (Gilham Code) System Mode Switch Encoding Altimeter State Magnetic Heading Valid System Mode Switch Magnetic Heading (Synchro XYZ) 3 Suppression Bus Synchro XYZ Compass State Audio Inhibit State GPWS/TAWS ar WX-1000 Video WX-1000 Controls WX-1000 Processor CDU Video in Power On/Off Pilot Controls WX-1000 CDU Alternate 429 Display Radio Altitude Valid Indicator Lamp Outputs (3) Squat Switch Discrete I/O Indicator Lamps Aircraft Audio System (RS-232) Laptop Computer Barometric Altitude (ARINC-429) ADC Bidirectional Discrete I/O (1) Landing Gear Diagnostic Data Pr el Radio Altimeter Radio Altitude (Analog) Radio Altitude (ARINC-429) im Alternate 429 Display Data (ARINC-429) Weight-On-Wheels State Audio Output ® SKYWATCH HP Transmitter/Receiver/Computer (TRC899) Control Panel Landing Gear State Aircraft Suppression Bus Auxiliary Serial Data (RS-232) Auxiliary RS-232 Port Auxiliary Serial Data (RS-422) Auxiliary RS-422 Port Magnetic Heading (ARINC-429) AHRS Flash Card Data Configuration Settings Flash Card ARINC-429 RX Data GPS Navigation System TX Coord (ARINC-429) XT Coord (ARINC-429) Comm-B (ARINC-429) Comm-A (ARINC-429) GPS Nav Data (ARINC-429) 429 RX Port Mode S Transponder (Future Option) System Configuration Module Notes: 1 Power On/Off and Pilot Controls are wired discretely when using an external display 2 Barometric altitude can be obtained from any of these sources 3 Magnetic heading can be obtained from any of these sources 4 Radio altitude can be obtained from analog or ARINC 429 sources Figure 1-2. SKY899 System Block Diagram 1-5 Rev. A SKY899 Installation Manual The following table identifies the components which make-up the SKY899 system. Table 1-1. SKY899 System COMPONENT PART NUMBER TRC899 Transmitter Receiver Computer 805-11900-001 System Configuration Module 814-18005-001* WX-1000/SKY497 Display (Optional) 78-8060-5900-x** Directional Antenna NY156 805-10003-001 NY164 805-10890-001 System Configuration Module is included in the installation kit P/N 817-11900-xxx (see table 1-2). ** Dash numbers identify different versions (refer to para 1.4.2). 1.3.1 TRC899 Transmitter Receiver Computer P/N 805-11900-xxx The TRC is mounted in a mounting tray supplied with the installation kit (see table 1-2). The standard tray (figure 1-3) will meet the requirements for fixed wing aircraft. A ruggedized version of the tray (figure 1-4) is required for rotorcraft installations. Pr el im in ar To meet different space requirements, the I/O signal connector (P1) will accommodate either a straight or right-angle backshell. TRC installation kits (see table 1-2) include either a straight backshell or right-angle backshell (see figure 1-5). 1-6 Rev. A SKY899 Installation Manual Table 1-2. TRC Installation Kit P/N 817-11900-xxx KIT P/N DESCRIPTION 817-11900-001 For Installation on Fixed-Wing Aircraft with Straight 1.5 inch (3.8 cm) Backshell Consists of: Standard Mounting Tray Assembly 1.5" (3.8 cm) Straight Backshell I/O Connector, 100-Position, Female, (Mil-C-38999 Series III) (Includes #22D Crimp Terminals) Spare Terminals for I/O Connector Power Connector, 3-Position, Straight Plug (Includes #16 Crimp Terminals) Spare Terminals for Power Connector (M39029/32-247) System Configuration Module Assembly For Installation on Fixed-Wing Aircraft with Straight 2.5 inch (6.4 cm) Backshell Consists of: Standard Mounting Tray Assembly 2.5" (6.4 cm)Straight Backshell I/O Connector, 100-Position, Female, (Mil-C-38999 Series III) (Includes #22D Crimp Terminals) Spare Terminals for I/O Connector Power Connector, 3-Position, Straight Plug (Includes #16 Crimp Terminals) Spare Terminals for Power Connector (M39029/32-247) System Configuration Module Assembly ar in For Installation on Fixed-Wing Right-Angle (90°) Backshell Consists of: Standard Mounting Tray Assembly Right-Angle (90°) Backshell I/O Connector, 100-Position, Female, (Mil-C-38999 Series III) (Includes #22D Crimp Terminals) Spare Terminals for I/O Connector Power Connector, 3-Position, Straight Plug (Includes #16 Crimp Terminals) Spare Terminals for Power Connector (M39029/32-247) System Configuration Module Assembly Pr el im 817-11900-003 817-11900-004 817-11900-005 For Installation on Rotorcraft with 2.5 inch (6.4 cm) Backshell Ruggedized Mounting Tray Assembly 2.5" (6.4 cm)Straight Backshell I/O Connector, 100-Position, Female, (Mil-C-38999 Series III) (Includes #22D Crimp Terminals) Spare Terminals for I/O Connector Power Connector, 3-Position, Straight Plug (Includes #16 Crimp Terminals) Spare Terminals for Power Connector (M39029/32-247) System Configuration Module Assembly For Installation on Rotorcraft with Right-Angle (90°) Backshell Consists of: Ruggedized Mounting Tray Assembly Right-Angle (90°) Backshell I/O Connector, 100-Position, Female, (Mil-C-38999 Series III) (Includes #22D Crimp Terminals) Spare Terminals for I/O Connector Power Connector, 3-Position, Straight Plug (Includes #16 Crimp Terminals) Spare Terminals for Power Connector (M39029/32-247) System Configuration Module Assembly PART NUMBER 805-10870-001 613-10039-001 605-10251-001 10 M39029/56-348 MS3126F12-3S 607-10018-001 814-18005-001 805-10870-001 613-10042-001 605-10251-001 10 M39029/56-348 MS3126F12-3S 607-10018-001 814-18005-001 805-10870-001 613-10043-001 605-10251-001 10 M39029/56-348 MS3126F12-3S 607-10018-001 814-18005-001 805-10870-003 613-10042-001 605-10251-001 10 M39029/56-348 MS3126F12-3S 607-10018-001 814-18005-001 805-10870-003 613-10043-001 605-10251-001 10 M39029/56-348 MS3126F12-3S 607-10018-001 814-18005-001 817-11900-002 QUANTITY 1-7 Rev. A SKY899 Installation Manual NOTE DIMENSIONS ARE IN INCHES (MILLIMETERS) ar 3. (97 84 MA .5) X. im in REAR HOLD-DOWN PINS (2-PLACES) RETAINER CUPS HOLD-DOWN KNOBS (2-PLACES) CO CL Pr el 6.7 .2) (17 CO .44 13 1.4) (34 AX. 1.8 .0) (47 X. MA Figure 1-3. Standard TRC Mounting Tray (P/N 805-10870-001) 1-8 Rev. A 4.15 (105.4) MAX. 3.37 (85.6) MAX. CO 1.1 .2) (29 50 0.7 .1) (19 SKY899 Installation Manual NOTE DIMENSIONS ARE IN INCHES (MILLIMETERS) IN 34 ) CR 4. 0.2 E S 1 D (1 LU 3.66 (93.0) MAX. 03 1.2.6) (30 ar CL 0.71) (19 CO in 5.6.5) (14 im .36 13 .3) (33 X. MA Pr el 1.72) (43 X. MA Figure 1-4. Ruggedized TRC Mounting Tray (P/N 805-10870-003) NOTE DIMENSIONS ARE IN INCHES (MILLIMETERS) 4.75 (120.7) REF. 4.25 (108.0) REF. 3.25 (82.6) REF. STRAIGHT BACKSHELL P/N 613-10042-001 SPLIT ELBOW 90° BACKSHELL P/N 613-10043-001 Figure 1-5. P1 Connector Dimensions (Reference Only) 1-9 Rev. A SKY899 Installation Manual NOTE DIMENSIONS ARE IN INCHES (MILLIMETERS) 3.5 (90 ±0. .4 031 ±.8 7.62 (193.0) MAX. CO CO J9 INT J1 ER CO NN EC 1.0 EF R .4) (25 PO 8 WE J7 TE ST ME J MO 12 RY CA RD im J1 in J1 4.15 - REF (105.4) 4.15 (105.4) ar Ae ros pa ce CO .04 ±0 .0) ± 12 8.0 (31 Pr el 5.6.5) (14 1.7 (43 1 .4) CO Figure 1-6. TRC899 Transmitter Receiver Computer (TRC) 1.3.2 System Configuration Module P/N 814-18005-001 The system configuration module is used to store aircraft installation dependent information via the service menu. The system configuration is read from the module during turn-on. The module is included in the installation kit and is designed to be installed inside the backshell of connector P1. 1-10 Rev. A SKY899 Installation Manual 1.3.3 Display (Alternate or WX-1000/SKY497 Display P/N 78-8060-5900-x) The display used is installation dependent. If installing to meet the requirements for a TCAS I installation an alternate display device (i.e., EFIS, MFD, IVSI, weather radar indicator) approved for displaying TCAS I information is required. If installing to meet requirements for a TAS installation an alternate display device, the WX-1000/SKY497 display, or both can be used as primary means for displaying traffic information. When interfaced to both displays (alternate display and WX-1000/SKY497 display), display functions can be linked together or separate depending on the capabilities of the alternate display. When installed with an alternate display device only, the service menu cannot be accessed via the display, therefore a terminal device (i.e., laptop) is required for system setup and post-installation checkout (see appendix F). If both displays are connected the service menu can be accessed by the WX-1000/SKY497 display only. The SKY899 is designed to transmit traffic information to the alternate display device via our ARINC-429 bus interface (100 kHz fixed speed). Refer to display manufacturer instructions for installation details. Series II Weather Mapping Systems in Stormscope TRAFFIC ADVISORY SYSTEM WX-1000 / SKY497 DISPLAY 78-8060-5900-9 TSO C110a, C113 Pat. USA 4,023,408; U.K. 1,529,624; Germany 26-00-658; Others Pend. 2.3lb. 1.0kg. TAG MUST IDENTIFY SKYWATCH AND TSO-C113. im SERIAL NO. ar WX-1000/SKY497 Display P/N 78-8060-5900-x. To operate with SKYWATCH HP, existing WX-1000 displays must conform to TSO-C113. If the equipment tag on the back of the unit (see figure 1-7) does not identify SKYWATCH and TSO-C113, return the display to the factory for modification. To schedule workload and ensure a quick turn around, a return authorization will be required. Call BFG Avionics Systems Customer Service (1-800-453-0288 or 1-616-949-6600) for details. Aerospace BFGoodrich Avionics Systems, Inc. Grand Rapids, MI USA Figure 1-7. WX-1000/SKY497 Display Equipment Tag Pr el The display unit mounts in a standard 3ATI panel cutout. All connections to the display are made through a single 25-position male D-subminiature connector on the back panel. Figure 1-8 depicts the indicator dimensions. The last digit of the part number identifies the different versions (refer to para 1.4.2). Table 1-3 lists the contents of an installation kit supplied with each unit. Table 1-3. WX-1000/SKY497 Display Installation Kit P/N 817-10802-001 QUANTITY PART NUMBER DESCRIPTION 25 26-1001-6374-5 26-1003-5633 26-1006-2426-6 26-1006-1089-3 26-1003-4274-9 Screw, Machine, 6-32 x 3/4 in. Phillips Pan Head, Black Oxide Connector, 25 Position Recpt. Shell Connector Backshell, DB25 Connector Lock Post Assembly Connector Socket, Screw Machine (M39029/63-368) 1-11 Rev. A SKY899 Installation Manual (9 .89 8. 8) NOTE DIMENSIONS ARE IN INCHES (MILLIMETERS) ar C.G. 3.37 (85.6) CL J101 in CL 3.37 (85.6) Pr el CL im 0.55 (14.0) 3.18 (80.8) CL C.G. 0.17 ±0.02 (4.3 ±0.5) 3.40 (86.4) 8.07 (205.0) 0.08 (2.0) Figure 1-8. WX-1000/SKY497 Display 1-12 Rev. A P101 1.30 (33.0) 3.18 (80.8) SKY899 Installation Manual 1.3.4 Directional Antenna (NY156 P/N 805-10003-001 or NY164 P/N 805-10890-001) The directional antenna is a teardrop-shaped antenna. Connections are made through two TNC and one BNC connector. The antenna is sealed against environmental extremes and is non-repairable. To ensure a tight seal between the airframe and antenna, an O-ring seal (i.e., an O-ring groove for an MS28775-044 Oring) has been incorporated into the design. An O-ring is supplied with each antenna and must be installed when mounting the antenna. To fit specific airframes, a special adapter plate is also required. The adapter plate is included in the installation kit shipped with each system. Refer to table 1-4 for a list of installation kits associated with various airframes. For aircraft not listed, contact the aircraft manufacturer for information relative to the radius of the area where the antenna is to be mounted. Table 1-5 lists the contents of each installation kit. The installation kits differ only in the size of the special airframe adapter plate. Figure 1-9 depicts the antenna dimensions. Table 1-4. Airframe Installation Kits INSTALLATION KIT AIRFRAME PART NUMBER AEROSPATIALE ATR-42 AGUSTA A109 BAE/RAYTHEON BEECH HAWKER 400, 600, 700, 800, and 1000 BEECHJET, KING AIR 90, 100, 200, 300, and 350 BARON 33, 35, 36, 55, 58, BE-99, 1300, & 1900C/D BELL 206, 407, 427 CANADAIR CHALLENGER 600 and 601 817-10009-005 CESSNA CITATION III, VI, VII CITATIONJET, CITATION I, II, V 182, 210, 337, 401, 414, 425, 441 817-10009-001 817-10009-004 817-10009-006 im in ar MANUFACTURER COMMANDER 114 DASSAULT FALCON 10, 20, 50 FALCON 900 817-10009-001 817-10009-006 817-10009-004 817-10009-001 817-10009-002 817-10009-006 817-10009-006 817-10009-001 817-10009-005 Dash 7/8 817-10009-001 EMBREAR EMB 110, 120 817-10009-001 EUROCOPTER EC135 817-10009-006 FAIRCHILD METROLINER, METROLINER III, MERLIN 817-10009-001 FOKKER F28 817-10009-003 GULFSTREAM G-I, G-II, and G-III 817-10009-001 IAI WESTWIND 1125 817-10009-001 LEARJET 31, 35, 36, 55, and 60 817-10009-004 Pr el DEHAVILLAND LEARJET MITSUBISHI MU-2 817-10009-002 MOONEY M20 817-10009-006 PILATIS PC-12 817-10009-001 PIPER CHEYENNE 400LS NAVAJO MIRAGE, MALIBU SARATOGA, SENECA 817-10009-001 817-10009-002 817-10009-005 817-10009-006 SAAB SF-340 817-10009-001 SABRELINER SABRE 65 817-10009-001 SHORTS 360 817-10009-001 SIKORSKY S-76 817-10009-006 SOCATA TBM-700 TB20 817-10009-001 817-10009-006 1-13 Rev. A SKY899 Installation Manual Table 1-5. Directional Antenna Installation Kit 817-10009-xxx SUPPLIED PARTS * KIT PART NUMBER PART NUMBER DESCRIPTION QUANTITY 817-10009-001 817-10009-002 817-10009-003 817-10009-004 817-10009-005 800-10066-001 800-10066-002 800-10066-004 800-10066-003 800-10066-005 Special Adapter Plate, 40 Inch (101.6 cm) Radius Special Adapter Plate, 63 Inch (160.0 cm) Radius Special Adapter Plate, 80 Inch (203.2 cm) Radius Special Adapter Plate, 32 Inch (81.3 cm) Radius Special Adapter Plate, 47 Inch (119.4 cm) Radius 817-10009-006 (No Adapter Plate) 100-10022-001* 101-10027-001* Screw, 10-32 x 1 PPH SS (MS51958-67) Stop Nut, 10-32 (MS21044C3) * Hardware supplied with all kits. in im 6.23 ±0.08 (158.2 ±2.0) Pr el FWD DO NOT PAINT ar NOTE DIMENSIONS ARE IN INCHES (MILLIMETERS) 1.30 (33.0) FORWARD 0.725 (18.4) DIFFERENCE PORT (Red Band) SUM PORT (Blue Band) PROBE PORT (Black Band) 5.71 (145.0) 5.06 (128.5) 11.12 (282.4) Figure 1-9. NY156/NY164 Directional Antenna 1-14 Rev. A 0.45 (11.4) SKY899 Installation Manual 1.4 SPECIFICATIONS 1.4.1 Transmitter Receiver Computer (TRC) 805-11900-001 - TRC899 SIZE: Approximately 12.52 inches (31.90 cm) Deep Approximately 3.56 inches (9.04 cm) Wide Approximately 7.62 inches (19.36 cm) High WEIGHT: Approximately 8.88 lb (4.03 kg) Not Including Mounting Tray Approximately 9.76 lb (4.43 kg) With Standard Mounting Tray Approximately 10.89 lb (4.94 kg) With Ruggedized Mounting Tray OPERATING TEMPERATURE: -55 to +70 degrees Celsius (-67 to +158 degrees Fahrenheit) STORAGE TEMPERATURE: -55 to +85 degrees Celsius (-67 to +185 degrees Fahrenheit) OPERATING ALTITUDE: 55,000 feet (Maximum) COOLING: Conduction and Forced Air (Internal Fan) Convection POWER REQUIREMENTS: 18 to 32 V dc, 2 Amps @ + 28 V dc(Maximum) TRACKING CAPABILITY: Up to 35 intruder aircraft (displays only the 8 highest priority aircraft) SURVEILLANCE RANGE: Horizontal tracking radius: 35 nmi Maximum ATCRBS Surveillance 50 nmi Maximum ADS-B Surveillance in ar PART NUMBER: Relative altitude tracking range: ±10,000 ft maximum DISPLAY RANGES: im Horizontal display ranges: 2, 6 & 15 nmi (WX-1000/SKY497 Display) Relative altitude display ranges: ±2,700 ft (normal mode) +9,000 ft to -2,700 ft (above mode/look up) +2,700 ft to -9,000 ft (below mode/look down) +9,900 ft to -9,900 ft (unrestricted) ± 0.05 nmi (Typical) BEARING ACCURACY: With NY156 Antenna - 5° RMS (Typical) 30° Peak Error With NY164 Antenna - 7° RMS (Typical) 30° Peak Error ALTITUDE ACCURACY: ±200 ft CERTIFICATION: * USA Pr el RANGE ACCURACY: RTCA COMPLIANCE: (FAA) TSO C118 (TCAS I) & C147 (TAS) Refer to FSAW 98-04B for Flight Standards Service policy concerning follow-on field approvals. Software DO178-B Level D DO-160D Category F2XBAB[(SBM)(UG)]XXXXXXZBABARRLXXXXXXA * Listed are current certifications at time of publication, contact Field Service Engineering at 1-800-4530288 or 1-616-949-6600 for latest certification information. 1-15 Rev. A SKY899 Installation Manual 1.4.2 WX-1000/SKY497 Display PART NUMBER DEFINITION: 78-8060-5900-8 (Black Bezel) 78-8060-5900-9 (Gray Bezel) SIZE: Height: 3.37 inches (8.56 cm) Width: 3.37 inches (8.56 cm) Depth: 8.24 inches (20.92 cm) WEIGHT: 2.3 lb (1.0 kg) OPERATING TEMPERATURE: -20 to +55 degrees Celsius (-4 to +131 degrees Fahrenheit) ar STORAGE TEMPERATURE: -55 to +70 degrees Celsius (-67 to +158 degrees Fahrenheit) TSO COMPLIANCE: C110a & C113 POWER REQUIREMENTS: +15/-15 V dc, 0.7 A (Maximum) 1.4.3 Directional Antenna SIZE: WEIGHT: SPEED: FREQUENCY: TSO CATEGORY: ENVIRONMENTAL CATEGORY: FINISH: 805-10003-001 (NY156) 805-10890-001 (NY164) Pr el PART NUMBER: im RTCA COMPLIANCE: DO-160C F1-CA(NBM)XXXXXXZXXXZUAXXXXXX in OPERATING ALTITUDE: 55,000 feet (Maximum) 1.3 inches (3.25 cm) high 6.23 in (15.82 cm) wide 11.12 in (27.94 cm) deep 2.3 lb (1.04 kg) Rated to 600 knots (0.9 Mach) @ 25,000 feet. 1030-1090 MHz C118 DO-160C F2-AC(CLM)XSFDFSXXXXXXXL(2A)X Gloss white Skydrol resistant polyurethane paint 1.5 MODIFICATIONS & SOFTWARE REVISIONS Modifications (MODS) and software revisions for the TRC899 are identified by an entry on the S/N & I.D. tag. The system software revision is a collective designator for all software/firmware installed within the TRC899. SKY HP software version can be verified via the service menu. Hardware modifications and software versions are listed below. Hardware Modifications - None at the time of publication. 1-16 Rev. A SKY899 Installation Manual Table 1-6. TRC899 Software Revisions SYSTEM REVISION SKY HP VERSION 1.00 1.00 DESCRIPTION Original production release. 1.6 INTERFACE The electrical characteristics of all input and output signals are detailed in Appendix A. Listed below in table 1-7 is the minimum equipment required to interface with the SKY899. See chapter 2 for details. Table 1-7. Minimum Interface Equipment Required EXTERNAL LAMPS PILOT CONTROLS (PUSHBUTTONS) AUDIO SYSTEMS ② ③ ③ ① ② ③ ③ ① AUDIO INHIBIT (GPWS) SUPPRESSION BUS ① ar ATCRBS & ADS-B SQUAT SWITCH (WOW) ① LANDING GEAR SWITCH in RADIO ALTITUDE ① GPS NAV BAROMETRIC ALTITUDE ATCRBS (Active Only) im SURVEILLANCE MODE MAGNETIC HEADING AVIONICS EQUIPMENT Pr el Required. ① Optional but will enhance performance. (See paragraphs 2.7 thru 2.23 for details.) ② Required if Terrain Warning System (GPWS) is installed. ③ Only if Alternate Display requires it, see display manufacturer's instructions. 1.7 EQUIPMENT REQUIRED BUT NOT SUPPLIED Antenna Cables The installer will supply all antenna cables and connectors. The directional antenna requires three cable assemblies; sum (Sigma Port), bit probe (Probe Port) and difference (Delta Port). Cable attenuation for the sum and difference ports must not exceed 2.5 dB. Table 1-8 identifies U. S. vendors who sell approved cables by the foot. Table 1-9 provides a cable to connector cross-reference. RG142B or equivalent may be used for the bit probe cable. Attenuation for the bit probe cable must not exceed 6 dB. NOTE Use of any cable not meeting BFGoodrich Avionics Systems specifications voids all system warranties. 1-17 Rev. A SKY899 Installation Manual Table 1-8. Directional Antenna SIGMA and DELTA Port Cable Vendors Electrical & Mechanical Technologies (EMTEQ) 1-888-679-6170 262-679-6170 FAX 262-679-6175 Part Number PFLX195-100 PFLX240-100 PFLX340-100 Attenuation (dB/100 ft 1.0 gHz) 10.81 9.76 6.3 Weight (lb) (per 100 ft) Maximum Length (ft) 2.7 4.5 7.2 Minimum Bend Radius (in) 21.8 25.0 38.2 0.50 0.75 0.88 Electronic Cable Specialists 1-800-327-9473 414-421-5300 FAX 414-421-5301 12.2 8.7 5.56 3.63 Weight (lb) (per 100 ft) 2.7 5.5 8.5 16.1 S33141 S55122 S22089 Attenuation (dB/100 ft 1.0 gHz) 7.2 5.7 3.8 Weight (lb) (per 100 ft) 6.5 8.2 18 im Part Number 15 26 41 63 in PIC Wire and Cable 1-800-742-3191 262-246-0500 FAX 262-246-0450 Maximum Length (ft) Minimum Bend Radius (in) 352001 311601 311201 310801 Attenuation (dB/100 ft 1.0 gHz) ar Part Number Maximum Length (ft) 32 40 61 0.81 1.15 1.59 2.26 Minimum Bend Radius (in) 1.5 1.6 2.5 Pr el If cable weight is not a consideration, select lowest loss cable. Contact cable vendors before installation. New low-loss light-weight cables may be available. 1-18 Rev. A SKY899 Installation Manual Table 1-9. Cable to Connector Reference Electrical & Mechanical Technologies (EMTEQ) 1-888-679-6170 262-679-6170 FAX 262-679-6175 Cable Part Number PFLX195-100 PFLX240-100 PFLX340-100 TNC Straight TNC Right Angle TMS195-1 TMS240-1 TMS340-1 TMR195-1 TMR240-1 TMR340-1 BNC Straight BMS195-1 BMS240-1 BMS340-1 BNC Right Angle BMR195-1 BMR240-1 BMR340-1 Electronic Cable Specialists 1-800-327-9473 414-421-5300 FAX 414-421-5301 TNC Straight TNC Right Angle CTS922 CTS122 CTS022 CTS3522 CTR922 CTR122 CTR022 CTR3522 BNC Straight 311601 311201 310801 352001 CBS922 CBS122 CBS022 CBS3522 ar Cable Part Number BNC Right Angle CBR922 CBR122 CBR022 CBR3522 S33141 S55122 S22089 Circuit Breaker 190308 190608 190408 TNC Right Angle Connector Installation 190309 190609 190409 BNC Straight 190312 190612 190412 BNC Right Angle 190313 190613 190413 For pressurized aircraft, use a sealant that meets the requirements of SAE AMS-S-8802 such as Flamemaster® CS3204 class B. For non-pressurized aircraft, use a non-corrosive sealant that meets the physical requirements of MIL-A-46146 such as General Electric RTV162. Pr el Antenna Sealant TNC Straight im Cable Part Number in PIC Wire and Cable 1-800-742-3191 262-246-0500 FAX 262-246-0450 5 Amp Antenna Cables See table 1-8. Tool M22520/5-01 Die M22520/5-19 (EMTEQ Cable PFLX195-100) Die M22520/5-43 (EMTEQ Cable PFLX240-100) Die M22520/5-35 (EMTEQ Cable PFLX340-100) Die M22520/5-19 (ECS Cable 311601) Die M22520/5-61 (ECS Cable 311201) Die M22520/5-21 (ECS Cable 310801) Die 190318 (PIC Cable S33141) Die 190418 (PIC Cable S22089) Die 190618 (PIC Cable S55122) P1 Crimping Tool M22520/2-01 Positioner M22520/2-07 Insertion MS27495 A22M Removal MS27495 R22M Interconnect 1-19 Rev. A SKY899 Installation Manual P8 Connector Installation (Continued) Power Crimping Tool M22520/1-01 Positioner M22520/1-02 Insertion MS24256A16 Removal MS24356R16 P101 Display Crimping Tool M22520/2-01 Positioner M22520/2-08 Insertion/Removal M81969/1-02 RS-232, RS-422, and ARINC-429 data cables are #22 AWG (minimum) twisted, shielded cables. Flightline Tester Either the BFG TT391 Flightline Tester, IFR Systems TCAS-201 (with TCAS I firmware) Ramp Test Set (Appendix C), or TIC T-49C Flightline Tester (Appendix D). The test set is required to do the post installation checkout. Heading Input Cable This cable provides aircraft heading information to the SKY899. Cable that meets the specification for SKY899 installation is available from suppliers listed in table 1-10. ar Data Cables Table 1-10. Heading Input Cable Vendors im Dallas Avionics 1-800-527-2581 214-320-9776 FAX 214-320-1057 1-20 Rev. A WX-5 (6.84 lb/ 100 ft) Electronic Cable Specialists 1-800-327-9473 414-421-5300 FAX 414-521-5301 3N6607 (7.5 lb/ 100 ft) A.E. Petsche 817-461-9473 FAX 817-277-2887 TZGYR (6.84 lb/ 100 ft) EDMO Distributors 1-800-235-3300 805-295-6689 FAX 1-800-828-0623 FAX 805-295-6703 WX-1000 SYNCHRO PIC Wire and Cable 1-800-742-3191 262-246-0500 FAX 262-246-0450 WM25807 (7.2 lb/ 100 ft) Pr el Lamps (external annunciators) CABLE P/N in US COMPANY External annunciators are required when using an alternate display that is not capable of displaying above and below vertical modes. Lamp outputs are switched to ground when active (LP1OUT & LP2OUT). Lamps should be labeled ABV and BLW. An optional operation mode lamp can be installed to show system has been switched from standby into operation mode. Refer to paragraph 2.14, 2.15 and A.2. Lamps can be 12V or 28V with maximum current 300 mA SKY899 Installation Manual Miscellaneous Hardware The installer must provide suitable hardware to attach the TRC Mounting Tray. The following stainless steel fasteners are recommended: Channel Mount: Four 8-32 UNC-2A pan head machine screws per ANSI B18.6.3. (Six are required for the ruggedized tray.) or Four 8-32 UNC-2A hex socket cap machine screws per ANSI/ASME B18.3. (Six are required for the ruggedized tray.) Four No. 8 helical spring lockwasher per ANSI/ASME B18.21.1. (Six are required for the ruggedized tray.) Eight 6-32 UNC-2A 100 degree flat head machine screws per B18.6.3. ar Flat Mount Required to verify SKY899 suppression pulse (100 µs ±5µs, +28 V dc). Power Cable For the power cable, use #16 AWG (minimum) twisted shielded pair cable (Beldon 83322, Alpha 2826/2, or equivalent). RS-232 Terminal Device (e.g., Laptop Computer) Required if using an alternate display, (see Appendix E for instructions). Terminal device is used for system setup, post installation checkout and troubleshooting. Any computer, with RS-232 terminal emulation software (e.g., Procomm®, HyperTerminal, etc.) may be used as the terminal device. A standard 9-pin serial cable is required. Surface Preparation Alodine® No. 1001 required for installation of the antenna. Switches If an alternate display is used a separate ON/OFF switch is required. Any general purpose SPDT toggle switch (3 A @ 28 V dc) may be used. im in Oscilloscope Pr el If the final configuration includes a WX-1000 Stormscope Weather Mapping System, two external switches will be required. A SPST switch will be required for the SKYWATCH/Stormscope display mode switch (SW1). A DPDT switch will be required for the WX-1000 maintenance switch (SW2). Any general purpose toggle switch (3 A @ 28 V dc) may be used. WX-1000/SKY497 Display & WX-1000 Processor Cable This cable is used to connect the WX-1000/SKY497 display and/or WX-1000 processor to the TRC. Required connectors and contact pins are supplied in the installation kit. Cable specifications and U.S. vendors are listed below in table 1-11. NOTE Use of any cable not meeting BFG Avionics Systems specifications voids all system warranties. 1-21 Rev. A SKY899 Installation Manual Table 1-11. Display Cable Vendors DISPLAY CABLE P/N WEIGHT (LB PER 100 FT) Dallas Avionics 1-800-527-2581 214-320-9776 FAX 214-320-1057 WX-3 10.5 Electronic Cable Specialists 1-800-327-9473 414-421-5300 FAX 414-421-5301 3N6715 16 A.E. Petsche 817-461-9473 FAX 817 277 2887 TZDIS 13.1 PIC Wire and Cable 1-800-742-3191 262-246-0500 FAX 262-246-0450 WM25815 EDMO Distributors 1-800-235-3300 509-535-8280 FAX 1-800-828-0623 FAX 509-535-8266 WX-1000 Display U.S. COMPANY ar 14.5 in --- Pr el im 1.8 INSTALLATION APPROVAL The SKY899 must be treated as a major alteration on F.A.A. form 337, if not installed under a type certificate or supplemental type certificate. Aircraft mandated for TCAS I (i.e., part 91 & 135), must be installed under a type certificate or supplemental type certificate, refer to FSAW 98-04B. Application for approval may be made at any F.A.A. Flight Standards District Office. 1.9 WARRANTY INFORMATION The SKY899 Traffic Alert/Advisory System is warranted for two years from the date of installation (not to exceed 30 months from the date of shipment from BFGoodrich Avionics Systems) subject to the following limitations. 1.9.1 Warranty Statement BFGoodrich Avionics Systems, (hereinafter called BFGAS), warrants each item of new equipment manufactured or sold by BFGAS to be free from defects in material and workmanship, under normal use as intended, for a period of 30 months from date of shipment by BFGAS to an authorized facility, or 24 months from date of installation by an authorized facility, whichever occurs first. No claim for breach of warranties will be allowed unless BFGAS is notified thereof, in writing, within thirty (30) days after the material or workmanship defect is found. The obligation of BFGAS shall be limited to replacing or repairing at its factory the equipment found defective under terms of this warranty certificate; providing that such equipment is returned in an approved shipping container, transportation charges prepaid, to BFGAS, Grand Rapids, Michigan, or such other location as BFGAS may authorize. BFGAS reserves the right to have necessary repairs performed by an authorized agency. 1-22 Rev. A SKY899 Installation Manual This warranty shall not apply to any unit or part thereof which has not been installed or maintained in accordance with BFGAS instructions, or has been repaired or altered in any way so as to adversely affect its performance or reliability, or which has been subjected to misuse, negligence or accident. This warranty is exclusive and is accepted by buyer in lieu of all other guaranties or warranties express or implied, including without limitation the implied warranties of merchantability and fitness for a particular purpose. Buyer agrees that in no event will BFGAS liability for all losses from any cause, whether based in contract, negligence, strict liability, other tort or otherwise, exceed buyer’s net purchase price, nor will BFGAS be liable for any special, incidental, consequential, or exemplary damages. BFGAS reserves the right to make changes in design or additions to or improvements in its equipment without the obligation to install such additions or improvement in equipment theretofore manufactured. 1.9.2 Related Policies and Procedures If the original registered owner of a SKY899 system sells the aircraft in which the system is installed during the warranty period, the remaining warranty may be transferred. Written notification of the transaction must be submitted by the initial recipient of the warranty to: 1. in ar ATTENTION: WARRANTY ADMINISTRATOR BFGoodrich Avionics Systems 5353 52nd Street, S.E. Grand Rapids, MI USA 49512 Equipment must be installed by a BFG Avionics Systems authorized dealer or installer. Installation of equipment by facilities not specifically authorized will void the equipment warranty. 3. Notice of a claimed product defect must be given to BFG Avionics Systems or a designated BFG Avionics Systems Service Agency within the specified warranty period. 4. A product which is defective in workmanship and/or material shall be returned to BFG Avionics Systems via any Authorized Dealer with transportation charges prepaid. After correction of such defects, the equipment will be returned to the Dealer, transportation prepaid by BFG Avionics Systems via surface transportation. Any other means of transportation must be paid by the customer. im 2. Pr el The risk of loss or damage to all products in transit shall be assumed by the party initiating the transportation of such products. All items repaired or replaced hereunder shall be warranted for the unexpired portion of the original warranty. 5. BFG Avionics Systems is in no way obligated or responsible for supporting or participating in the costs of the installation warranty. The entire responsibility lies with the BFG Avionics Systems Authorized Dealer making the installation. BFG Avionics Systems is only responsible for the product warranties outlined in paragraph 1.9.1. 6. BFG Avionics Systems cannot authorize warranty credit for troubleshooting of other systems in the aircraft in order to reduce noise interference with the SKY899 system. 1-23 Rev. A in ar SKY899 Installation Manual Pr el im This page intentionally left blank. 1-24 Rev. A SKY899 Installation Manual CHAPTER 2 INSTALLATION 2.1 INTRODUCTION The information and instructions provided in this section are directed toward fixed-wing aircraft. The complex nature of rotorcraft installations (e.g., antenna placement; composite versus metal blades, available ground plane, rotor mast interference, strike kits, etc.) requires that each installation be evaluated on a case-by-case basis. Before starting a rotorcraft installation, contact Field Service Engineering at 1-800-453-0288 or 1-616-949-6600. NOTE Tolerances (unless otherwise indicated): ar ANGLES ARE .00 TWO PLACE DECIMALS ARE .000 THREE PLACE DECIMALS ARE ± 1° ± .02 ± .010 in Installation must be made by qualified personnel, in conformance with applicable government regulations. This information furnished is for convenience only. im NOTES 1. The conditions and test required for TSO approval of this article are minimum performance standards. It is the responsibility of those installing this article either on or within a specific type or class of aircraft to determine that the aircraft installation conditions are within the TSO standards. The article may be installed only if the installation is performed in accordance with Part 43 or the applicable airworthiness requirements. Pr el 2. Installation instructions for the WX-1000 processor are detailed in the WX-1000 Installation Manual. 2.2 UNPACKING, INSPECTION AND STORAGE CAUTION The display and TRC are sensitive to electrostatic discharge (ESD) and may be damaged if not handled correctly. Do not remove protective covers from electrical connectors during unpacking. Touching an exposed connector may cause electrostatic damage to equipment. Carefully unpack the system and note any damage to shipping containers or equipment. Visually inspect each component for evidence of damage. Compare the equipment received with that noted on the packing list. Immediately report any missing items or evidence of damage to the carrier making the delivery. To justify a claim, retain the original shipping container and all packing materials. Every effort should be made to retain the original shipping containers for storage. If the original containers are not available, a separate cardboard container should be prepared that is large enough to accommodate sufficient packing material to prevent movement. The ambient temperature of the storage area should not fall below -55 °C (-67 °F) or rise above 85 °C (185 °F). 2-1 Rev. A SKY899 Installation Manual 2.3 ANTENNA LOCATION Location is an important factor for maximum antenna performance. Optimum location for a particular aircraft type is usually available from the aircraft manufacturer. In selecting a location, consider the following: The mounting site should be on the top forward fuselage, as close to the centerline as possible, and within -10° of the in-flight horizon (see figure 2-1). The optimum mounting point for maximum coverage is as far forward as possible without exceeding the -10° forward pitch. If necessary, consideration should be given to relocating other antennas to obtain the furthest forward location for the directional antenna. The antenna should be mounted on the aircraft with at least 20 dB isolation (about 30 inches (76.2 cm)) from other Lband frequency antennas and 24 inches (61.0 cm) from other antennas or obstructions. The ground-plane should be as large as possible, a 30-inch (76.2 cm) ground-plane diameter is recommended. Directional Antenna Pr el im in ar The directional antenna can be bottom mounted only if a suitable top mount location is not available. Each bottom mount installation must be evaluated on a case-by-case basis. Before starting a bottom mount installation, contact Field Service Engineering at 1-800-453-0288 or 1-616-949-6600. Figure 2-1. Directional Antenna Mounting Location 2.4 TRC LOCATION Typically the TRC is installed in the electronics bay. In selecting a location, consider the following: Cable Length Cable runs should be as short as practicable in order to minimize potential electrical interference. Cable length to antennas must not exceed the values listed in table 1-6. Cooling While the TRC has no special cooling requirements, it should be mounted to permit adequate ventilation. Caution should be observed to not inhibit airflow from the rear mounted fan. Allow at least three inches (8 cm) of rear clearance. Pressurized Aircraft The TRC may mount inside or outside the pressure vessel. The TRC contains no batteries or potentially explosive components and will operate up to 55,000 ft. 2-2 Rev. A SKY899 Installation Manual P/O P1 DIRECTIONAL GYRO COMPASS SEE NOTE 6 HEADING_FLG HEADING_C HEADING_H HEADING_Z HEADING_Y HEADING_X N/C 51 50 49 48 47 46 TP ORN TP BLU WHT DISCRETE TRC899 OPER_MODE LP1OUT LP2OUT 32 WHT TP BLU TP ORN TP RED TP GRN TP BLK TP YEL WHT ORN BLU WHT BLU WHT BLU WHT BLU WHT BLU WHT BLU WHT BLU ar 56 57 58 59 60 61 67 68 69 70 71 72 24 33 14 DISPLAY CABLE SEE NOTE 6 in ALT_A1 ALT_A2 ALT_A4 ALT_B1 ALT_B2 ALT_B4 ALT_C1 ALT_C2 ALT_C4 ALT_D2 ALT_D4 ALT_COMN SQUAT GEAR RAD_ALT_IN_HI RAD_ALT_IN_LO RADIO_ALT_FLG 10 11 12 13 22 16 17 18 19 20 21 SEE NOTE 13 TP HIGH DC ANALOG ALT LOW VALID FLAG N/C DISCRETE I/O SEE NOTE 4 31 66 85 92 99 100 RADIO ALT SEE NOTE 9 LAMP, SEE NOTE 14 LAMP ABV LAMP BLW SEE NOTE 12 PERSONALITY PLUG 3.3V PLUG_GND SDA SCL ORN HEADING VALID LOW 26 VAC REFERENCE HIGH HEADING BLU WHT HEADING INPUT CABLE SEE NOTE 6 SEE NOTE 6 DPWR+15_OUT DPWR-15_OUT DSPLY_GND_OUT HSYNC_OUT+ HSYNC_OUTVSYNC_OUT+ VSYNC_OUTVIDEO_OUT+ VIDEO_OUTON/OFF ON/OFF_RET SFTKEY1_IN SFTKEY2_IN SFTKEY3_IN SFTKEY4_IN SEE NOTE 9 N/C BLU WHT BLU WHT BLU ORN WHT BLU WHT BLU WHT BLU ORN WHT im P/O J1 3.3V PLUG_GND SDA SCL INSIDE CONNECTOR BACKSHELL Pr el TRANSMITTER RECEIVER COMPUTER UNIT P101 SEE NOTE 6 WHT ORN BLU WHT BLU WHT BLU WHT BLU WHT BLU WHT BLU WHT BLU WHT BLU ORN RED GRN BLK YEL N/C N/C N/C N/C N/C N/C N/C N/C 19 14 18 10 22 23 13 12 25 24 11 17 15 16 20 21 J101 +15 -15 DSPGND HSYNCHI HSYNCLO VSYNCHI VSYNCLO VIDEOHI VIDEOLO PWRSWHI PWRSWLO SFTKEY1 SFTKEY2 SFTKEY3 SFTKEY4 SHIELD GND N/C GND -15V GND +15V GND GND CHASSIS WX-1000 DISPLAY A1 A2 ALTITUDE A4 DIGITIZER B1 B2 B4 C1 SEE NOTE 9 C2 C4 D2 D4 ALT_COMMON SQUAT SWITCH LANDING GEAR POSITION NOTES: 1.) ALL WIRES TO BE 22 AWG EXCEPT WHERE NOTED. 2.) TP - USE TWISTED SHIELDED PAIR CABLE. TERMINATE SHIELD TO AIRFRAME GROUND AT SENSOR (OR POWER SOURCE). 3.) THE SUM CABLE WILL HAVE A BLUE BAND AT EACH END. THE DIFFERENCE CABLE WILL HAVE A RED BAND AT EACH END. 4.) FUTURE OPTION. 5.) A RADIO ALTIMETER, AIRDATA COMPUTER, OR OTHER ARINC 429 OUTPUT DEVICE MAY REPLACE ANALOG SENSORS FOR MAGNETIC HEADING, RADIO ALTITUDE, OR BAROMETRIC ALTITUDE. 6.) TIE THE OUTER SHIELD TO THE CONNECTOR BACKSHELL. CONNECTOR BACKSHELL IS CHASSIS GROUND. 7.) REFER TO INSTALLATION INSTRUCTIONS FOR CABLE SELECTION ON ANTENNA CABLES. 8.) USE AUDIO_H FOR 600 OHM AUDIO SYSTEMS. USE AUDIO_L FOR 150 OHM AUDIO SYSTEMS. 9.) DO NOT INSTALL EXTERNAL ISOLATION DIODES. 10.) THESE TWO DEVICES MUST BOTH BE HIGH SPEED OR BOTH BE LOW SPEED. 11.) THESE TWO DEVICES MUST BOTH BE HIGH SPEED OR BOTH BE LOW SPEED. 12.) ONLY USED WITH EXTERNAL DISPLAYS THAT DO NOT ANNUNCIATE ABOVE AND BELOW. 13.) IF D2 IS NOT USED THEN IT IS A "NO CONNECT" (N/C). 14.) OPTIONAL, MAY BE USED TO DRIVE INDICATOR DEPICTING OPERATIONAL MODE. Figure 2-2. Interconnect Wiring Without WX-1000 (Sheet 1 of 2) 2-3 (page 2-4 blank) Rev. A SKY899 Installation Manual P/O P1 81 82 83 84 75 76 73 74 64 65 62 63 SEE NOTE 4 TP TP TP TP SEE NOTE 2 TP SEE NOTE 2 A429RX1_A A429RX1_B A429TX3_A A429TX3_B A429TX2_A A429TX2_B 54 55 TP 52 53 44 45 TP OPTIONAL ARINC 429 XMIT (SEE NOTES 5 AND 10) OPTIONAL ARINC 429 XMIT (SEE NOTES 5 AND 10) A429TX1_A A429TX1_B 42 43 SEE NOTE 2 OPTIONAL XPDR ARINC 429 TX BUS (SEE NOTE 4) OPTIONAL EXTERNAL ARINC 429 DISPLAY TP SEE NOTE 6 34 89 90 91 RS422_TXA RS422_TXB RS422_RXA RS422_RXB TRC899 RS232_TX2 RS232_RX2 RS232_GND2 +5V -15V ASU_SEL ASU_MODE ASU_SEL_ACK ASU_MOD_ACK ASU_GND in AUDIO_H AUDIO_L AUDIO_C 93 TP 77 78 79 80 86 87 88 94 95 96 97 98 SEE NOTE 4 SEE NOTE 4 SEE NOTE 4 F3 16 AWG J8 P8 5A +28V +28V_RET SPARE J7 SEE NOTE 2 OPTIONAL XPDR ARINC 429 XT BUS (SEE NOTE 4) OPTIONAL ARINC 429 XMIT (SEE NOTE 5) CAUTION: THE AIRCRAFT TRANSPONDER MUST HAVE SHIELDED SUPPRESSION CIRCUITRY TO ENSURE THAT SKYWATCH DOES NOT DISPLAY ITSELF AS A TARGET (TA). SEE NOTE 6 SUPPRESSION I/O GPWSFLAG SEE NOTE 8 SEE NOTE 6 AUDIO HIGH AUDIO COMMON im GPWS OPTIONAL ARINC 429 XMIT (SEE NOTES 5 AND 11) SEE NOTE 2 16 AWG AIRCRAFT POWER (18 - 32VDC) Pr el SUPBUS SEE NOTE 2 OPTIONAL ARINC 429 XMIT (SEE NOTES 5 AND 11) SEE NOTE 4 SEE NOTE 2 TRANSMITTER RECEIVER COMPUTER UNIT SEE NOTE 2 A429RX8_A A429RX8_B A429RX7_A A42RRX7_B A429RX5_A A429RX5_B A429RX4_A A42RRX4_B A429RX3_A A429RX3_B A429RX2_A A429RX2_B ar P/O J1 AIRCRAFT POWER RETURN SEE NOTE 2 DEBUG PORT DIAG_GND DIAG_RX DIAG_TX CTS RTS TEST ONLY SEE NOTE 7 SEE NOTE 3 NY164/NY156 DIRECTIONAL ANTENNA SEE NOTE 3 J9 SUM (BLUE) P3 P9 TYPE TNC J10 BIT_PROBE P10 CONNECTOR J11 DIFFERENCE (RED) P11 CONNECTOR TYPE BNC TYPE TNC CONNECTOR SUM TNC BLUE BAND P2 BIT_PROBE BNC P1 TNC DIFFERENCE RED BAND Figure 2-2. Interconnect Wiring Without WX-1000 (Sheet 2 of 2) 2-5 (page 2-6 blank) Rev. A SKY899 Installation Manual P/O J1 P/O P1 DIRECTIONAL GYRO COMPASS SEE NOTE 6 HEADING_FLG HEADING_C HEADING_H HEADING_Z HEADING_Y HEADING_X 51 50 49 48 47 46 TP ORN TP BLU BLU WHT BLU WHT BLU ORN WHT BLU WHT BLU WHT BLU ORN WHT WHT HEADING INPUT CABLE SEE NOTE 6 SEE NOTE 6 25 26 27 28 29 30 41 35 36 37 38 39 40 WHT TP BLU TP ORN TP RED TP GRN TP BLK TP YEL WHT ORN BLU WHT BLU WHT BLU WHT BLU WHT BLU WHT BLU WHT TP BLU TP ORN TP RED TP BLK TP YEL DISPLAY CABLE WHT ORN BLU WHT BLU WHT BLU WHT BLU WHT BLU WHT BLU WHT BLU STORMSCOPE SKYWATCH ALT_A1 ALT_A2 ALT_A4 ALT_B1 ALT_B2 ALT_B4 ALT_C1 ALT_C2 ALT_C4 ALT_D2 ALT_D4 ALT_COMN SQUAT GEAR RAD_ALT_IN_HI RAD_ALT_IN_LO RADIO_ALT_FLG DISCRETE OPER_MODE LP1OUT LP2OUT SW1 23 56 57 58 59 60 61 67 68 69 70 71 72 24 33 14 32 SEE NOTE 13 LAMP, SEE NOTE 16 LAMP ABV LAMP BLW 3.3V PLUG_GND SDA SCL RADIO ALT SEE NOTE 9 SEE NOTE 12 INSIDE CONNECTOR BACKSHELL NOTES: 1.) ALL WIRES TO BE 22 AWG EXCEPT WHERE NOTED. 2.) TP - USE TWISTED SHIELDED PAIR CABLE. TERMINATE SHIELD TO AIRFRAME GROUND AT SENSOR (OR POWER SOURCE). 3.) THE SUM CABLE WILL HAVE A BLUE BAND AT EACH END. THE DIFFERENCE CABLE WILL HAVE A RED BAND AT EACH END. 4.) FUTURE OPTION. 5.) A RADIO ALTIMETER, AIRDATA COMPUTER, OR OTHER ARINC 429 OUTPUT DEVICE MAY REPLACE ANALOG SENSORS FOR MAGNETIC HEADING, RADIO ALTITUDE, OR BAROMETRIC ALTITUDE. 6.) TIE THE OUTER SHIELD TO THE CONNECTOR BACKSHELL. CONNECTOR BACKSHELL IS CHASSIS GROUND. 7.) REFER TO INSTALLATION INSTRUCTIONS FOR CABLE SELECTION ON ANTENNA CABLES. 8.) USE AUDIO_H FOR 600 OHM AUDIO SYSTEMS. USE AUDIO_L FOR 150 OHM AUDIO SYSTEMS. WHT SEE NOTE 6 AND NOTE 14 P101 WHT BLU ORN RED GRN BLK YEL 19 14 18 10 22 23 13 12 25 24 11 17 15 16 20 21 SEE NOTE 6 AND NOTE 14 WHT ORN BLU WHT BLU WHT BLU WHT BLU WHT BLU WHT BLU WHT BLU WHT BLU ORN RED GRN BLK YEL 36 38 23 40 39 22 21 20 26 43 44 J101 +15 -15 DSPGND HSYNCHI HSYNCLO VSYNCHI VSYNCLO VIDEOHI VIDEOLO PWRSWHI PWRSWLO SFTKEY1 SFTKEY2 SFTKEY3 SFTKEY4 SHIELD GND N/C GND -15V GND +15V GND GND CHASSIS WX-1000 DISPLAY J301 +15 -15 DSPGND HSYNCHI HSYNCLO VSYNCHI VSYNCLO VIDEOHI VIDEOLO PWRSWHI PWRSWLO SFTKEY1 SFTKEY2 SFTKEY3 SFTKEY4 SHIELD WX-1000 PROCESSOR SEE NOTE 15 A1 A2 ALTITUDE A4 DIGITIZER B1 B2 B4 C1 SEE NOTE 9 C2 C4 D2 D4 ALT_COMMON PERSONALITY PLUG 3.3V PLUG_GND SDA SCL NORMAL HIGH DC ANALOG ALT LOW VALID FLAG DISCRETE I/O SEE NOTE 4 31 66 85 92 99 100 OVER-RIDE SW2 TP N/C HEADING VALID LOW 26 VAC REFERENCE HIGH HEADING P301 im SMS_RET 15 N/C BLU N/C N/C N/C N/C N/C N/C N/C N/C Pr el SMS ORN WHT ORN BLU WHT BLU WHT BLU WHT BLU WHT BLU WHT BLU WHT BLU DPWR+15_IN DPWR-15_IN DSPLY_GND_IN HSYNC_IN+ HSYNC_INVSYNC_IN+ VSYNC_INVIDEO_IN+ VIDEO_INSFTKEY1_OUT SFTKEY2_OUT SFTKEY3_OUT SFTKEY4_OUT 10 11 12 13 22 16 17 18 19 20 21 ar DPWR+15_OUT DPWR-15_OUT DSPLY_GND_OUT HSYNC_OUT+ HSYNC_OUTVSYNC_OUT+ VSYNC_OUTVIDEO_OUT+ VIDEO_OUTON/OFF ON/OFF_RET SFTKEY1_IN SFTKEY2_IN SFTKEY3_IN SFTKEY4_IN TRC899 SEE NOTE 9 N/C in TRANSMITTER RECEIVER COMPUTER UNIT SQUAT SWITCH LANDING GEAR POSITION 9.) DO NOT INSTALL EXTERNAL ISOLATION DIODES. 10.) THESE TWO DEVICES MUST BOTH BE HIGH SPEED OR BOTH BE LOW SPEED. 11.) THESE TWO DEVICES MUST BOTH BE HIGH SPEED OR BOTH BE LOW SPEED. 12.) ONLY USED WITH EXTERNAL DISPLAYS THAT DO NOT ANNUNCIATE ABOVE AND BELOW. 13.) IF D2 IS NOT USED THEN IT IS A "NO CONNECT" (N/C). 14.) IF THE SKYWATCH IS BEING INSTALLED TO AN EXISTING WX-1000 SYSTEM, THE CABLE GROUND AT THE WX-1000 DISPLAY AND THE WX-1000 PROCESSOR MUST BE CHANGED FROM AS SHOWN IN THE WX-1000 MANUAL TO BE AS SHOWN HERE. 15.) INSTALLATION INSTRUCTIONS FOR THE WX-1000 ARE DETAILED IN THE 16.) OPTIONAL, MAY BE USED TO DRIVE INDICATOR DEPICTING OPERATIONAL MODE. Figure 2-3. Interconnect Wiring With WX-1000 (Sheet 1 of 2) 2-7 (page 2-8 blank) Rev. A SKY899 Installation Manual P/O P1 81 82 83 84 75 76 73 74 64 65 62 63 SEE NOTE 4 TP TP TP TP SEE NOTE 2 TP SEE NOTE 2 A429RX1_A A429RX1_B A429TX3_A A429TX3_B A429TX2_A A429TX2_B 54 55 TP 52 53 44 45 TP OPTIONAL ARINC 429 XMIT (SEE NOTES 5 AND 10) OPTIONAL ARINC 429 XMIT (SEE NOTES 5 AND 10) A429TX1_A A429TX1_B 42 43 SEE NOTE 2 OPTIONAL XPDR ARINC 429 TX BUS (SEE NOTE 4) OPTIONAL EXTERNAL ARINC 429 DISPLAY TP SEE NOTE 6 34 89 90 91 TP 77 78 79 80 RS422_TXA RS422_TXB RS422_RXA RS422_RXB TRC899 86 87 88 RS232_TX2 RS232_RX2 RS232_GND2 94 95 96 97 98 +5V -15V ASU_SEL ASU_MODE ASU_SEL_ACK ASU_MOD_ACK ASU_GND in AUDIO_H AUDIO_L AUDIO_C 93 SEE NOTE 4 SEE NOTE 4 SEE NOTE 4 F3 16 AWG J8 P8 5A +28V +28V_RET SPARE J7 SEE NOTE 2 OPTIONAL XPDR ARINC 429 XT BUS (SEE NOTE 4) OPTIONAL ARINC 429 XMIT (SEE NOTE 5) CAUTION: THE AIRCRAFT TRANSPONDER MUST HAVE SHIELDED SUPPRESSION CIRCUITRY TO ENSURE THAT SKYWATCH DOES NOT DISPLAY ITSELF AS A TARGET (TA). SEE NOTE 6 SUPPRESSION I/O GPWSFLAG SEE NOTE 8 SEE NOTE 6 AUDIO HIGH AUDIO COMMON im GPWS OPTIONAL ARINC 429 XMIT (SEE NOTES 5 AND 11) SEE NOTE 2 16 AWG AIRCRAFT POWER (18 - 32VDC) Pr el SUPBUS SEE NOTE 2 OPTIONAL ARINC 429 XMIT (SEE NOTES 5 AND 11) SEE NOTE 4 SEE NOTE 2 TRANSMITTER RECEIVER COMPUTER UNIT SEE NOTE 2 A429RX8_A A429RX8_B A429RX7_A A42RRX7_B A429RX5_A A429RX5_B A429RX4_A A42RRX4_B A429RX3_A A429RX3_B A429RX2_A A429RX2_B ar P/O J1 AIRCRAFT POWER RETURN SEE NOTE 2 DEBUG PORT DIAG_GND DIAG_RX DIAG_TX CTS RTS TEST ONLY SEE NOTE 7 SEE NOTE 3 NY164/NY156 DIRECTIONAL ANTENNA SEE NOTE 3 J9 SUM (BLUE) P3 P9 TYPE TNC J10 BIT_PROBE P10 CONNECTOR J11 DIFFERENCE (RED) P11 CONNECTOR TYPE BNC TYPE TNC CONNECTOR SUM TNC BLUE BAND P2 BIT_PROBE BNC P1 TNC DIFFERENCE RED BAND Figure 2-3. Interconnect Wiring With WX-1000 (Sheet 2 of 2) 2-9 (page 2-10 blank) Rev. A SKY899 Installation Manual P/O P1 DIRECTIONAL GYRO COMPASS SEE NOTE 6 HEADING_FLG HEADING_C HEADING_H HEADING_Z HEADING_Y HEADING_X N/C 51 50 49 48 47 46 TP ORN TP BLU BLU WHT BLU WHT BLU ORN WHT BLU WHT BLU WHT BLU ORN WHT WHT SEE NOTE 6 DISCRETE TRC899 OPER_MODE LP1OUT LP2OUT 32 BLK TP YEL BLU N/C BLU WHT BLU SEE NOTE 13 TP HIGH DC ANALOG ALT LOW VALID FLAG N/C DISCRETE I/O SEE NOTE 4 31 66 85 92 99 100 RADIO ALT SEE NOTE 9 LAMP, SEE NOTE 14 LAMP ABV SEE NOTE 12 LAMP BLW PERSONALITY PLUG 3.3V PLUG_GND SDA SCL ORN BLU WHT HEADING VALID LOW 26 VAC REFERENCE HIGH HEADING DISPLAY_GND_OUT 56 57 58 59 60 61 67 68 69 70 71 72 24 33 14 TP ar ON/OFF ON/OFF_RET ALT_A1 ALT_A2 ALT_A4 ALT_B1 ALT_B2 ALT_B4 ALT_C1 ALT_C2 ALT_C4 ALT_D2 ALT_D4 ALT_COMN SQUAT GEAR RAD_ALT_IN_HI RAD_ALT_IN_LO RADIO_ALT_FLG 10 18 19 20 21 in DSPLY_GND_OUT SFTKEY1_IN SFTKEY2_IN SFTKEY3_IN SFTKEY4_IN SEE NOTE 9 N/C HEADING INPUT CABLE SEE NOTE 6 im P/O J1 3.3V PLUG_GND SDA SCL INSIDE CONNECTOR BACKSHELL NOTES: Pr el TRANSMITTER RECEIVER COMPUTER UNIT TEST/ALT RANGE STBY/OPER "OFF" "ON" 3A @ 28VDC A1 A2 ALTITUDE A4 DIGITIZER B1 B2 B4 C1 SEE NOTE 9 C2 C4 D2 D4 ALT_COMMON SQUAT SWITCH LANDING GEAR POSITION 1.) ALL WIRES TO BE 22 AWG EXCEPT WHERE NOTED. 2.) TP - USE TWISTED SHIELDED PAIR CABLE. TERMINATE SHIELD TO AIRFRAME GROUND AT SENSOR (OR POWER SOURCE). 3.) THE SUM CABLE WILL HAVE A BLUE BAND AT EACH END. THE DIFFERENCE CABLE WILL HAVE A RED BAND AT EACH END. 4.) FUTURE OPTION. 5.) A RADIO ALTIMETER, AIRDATA COMPUTER, OR OTHER ARINC 429 OUTPUT DEVICE MAY REPLACE ANALOG SENSORS FOR MAGNETIC HEADING, RADIO ALTITUDE, OR BAROMETRIC ALTITUDE. 6.) TIE THE OUTER SHIELD TO THE CONNECTOR BACKSHELL. CONNECTOR BACKSHELL IS CHASSIS GROUND. 7.) REFER TO INSTALLATION INSTRUCTIONS FOR CABLE SELECTION ON ANTENNA CABLES. 8.) USE AUDIO_H FOR 600 OHM AUDIO SYSTEMS. USE AUDIO_L FOR 150 OHM AUDIO SYSTEMS. 9.) DO NOT INSTALL EXTERNAL ISOLATION DIODES. 10.) THESE TWO DEVICES MUST BOTH BE HIGH SPEED OR BOTH BE LOW SPEED. 11.) THESE TWO DEVICES MUST BOTH BE HIGH SPEED OR BOTH BE LOW SPEED. 12.) ONLY USED WITH EXTERNAL DISPLAYS THAT DO NOT ANNUNCIATE ABOVE AND BELOW. 13.) IF D2 IS NOT USED THEN IT IS A "NO CONNECT" (N/C). 14.) OPTIONAL, MAY BE USED TO DRIVE INDICATOR DEPICTING OPERATIONAL MODE. Figure 2-4. Interconnect Wiring with Alternate Display (Sheet 1 of 2) 2-11 (page 2-12 blank) Rev. A SKY899 Installation Manual P/O P1 81 82 83 84 75 76 73 74 64 65 62 63 SEE NOTE 4 TP TP TP TP SEE NOTE 2 TP SEE NOTE 2 A429RX1_A A429RX1_B A429TX3_A A429TX3_B A429TX2_A A429TX2_B 54 55 TP 52 53 44 45 TP OPTIONAL ARINC 429 XMIT (SEE NOTES 5 AND 10) OPTIONAL ARINC 429 XMIT (SEE NOTES 5 AND 10) A429TX1_A A429TX1_B 42 43 SEE NOTE 2 OPTIONAL XPDR ARINC 429 TX BUS (SEE NOTE 4) EXTERNAL ARINC 429 DISPLAY TP SEE NOTE 6 34 89 90 91 TP 77 78 79 80 RS422_TXA RS422_TXB RS422_RXA RS422_RXB TRC899 86 87 88 RS232_TX2 RS232_RX2 RS232_GND2 94 95 96 97 98 +5V -15V ASU_SEL ASU_MODE ASU_SEL_ACK ASU_MOD_ACK ASU_GND in AUDIO_H AUDIO_L AUDIO_C 93 SEE NOTE 4 SEE NOTE 4 SEE NOTE 4 F3 16 AWG J8 P8 5A +28V +28V_RET SPARE J7 SEE NOTE 2 OPTIONAL XPDR ARINC 429 XT BUS (SEE NOTE 4) OPTIONAL ARINC 429 XMIT (SEE NOTE 5) CAUTION: THE AIRCRAFT TRANSPONDER MUST HAVE SHIELDED SUPPRESSION CIRCUITRY TO ENSURE THAT SKYWATCH DOES NOT DISPLAY ITSELF AS A TARGET (TA). SEE NOTE 6 SUPPRESSION I/O GPWSFLAG SEE NOTE 8 SEE NOTE 6 AUDIO HIGH AUDIO COMMON im GPWS OPTIONAL ARINC 429 XMIT (SEE NOTES 5 AND 11) SEE NOTE 2 16 AWG AIRCRAFT POWER (18 - 32VDC) Pr el SUPBUS SEE NOTE 2 OPTIONAL ARINC 429 XMIT (SEE NOTES 5 AND 11) SEE NOTE 4 SEE NOTE 2 TRANSMITTER RECEIVER COMPUTER UNIT SEE NOTE 2 A429RX8_A A429RX8_B A429RX7_A A42RRX7_B A429RX5_A A429RX5_B A429RX4_A A42RRX4_B A429RX3_A A429RX3_B A429RX2_A A429RX2_B ar P/O J1 AIRCRAFT POWER RETURN SEE NOTE 2 DEBUG PORT DIAG_GND DIAG_RX DIAG_TX CTS RTS TEST ONLY SEE NOTE 7 SEE NOTE 3 NY164/NY156 DIRECTIONAL ANTENNA SEE NOTE 3 J9 SUM (BLUE) P3 P9 TYPE TNC J10 BIT_PROBE P10 CONNECTOR J11 DIFFERENCE (RED) P11 CONNECTOR TYPE BNC TYPE TNC CONNECTOR SUM TNC BLUE BAND P2 BIT_PROBE BNC P1 TNC DIFFERENCE RED BAND Figure 2-4. Interconnect Wiring with Alternate Display (Sheet 2 of 2) 2-13 (page 2-14 blank) Rev. A SKY899 Installation Manual 2.5 DISPLAY LOCATION The display should be mounted in a location easily accessible and clearly visible to the pilot. If using an alternate display device refer to manufacturer instructions for location. In selecting a location for WX1000/SKY497 display, consider the following: Magnetic Effect Where possible to avoid it, the display should not be mounted within 3 inches (8 cm) of an electric turn and bank indicator, as the magnetic effect of the turn and bank motor may affect the display presentation. (A common symptom of magnetic interference is a wobbling or vibrating display raster.) NOTE If it is necessary to mount the display unit next to a device that may affect the CRT display, magnetic shielding material can be placed around the display unit. Shielding material is available from BFG Avionics Systems. Specify P/N 78-8060-5882-8 when ordering. Adequate depth must be available behind the instrument panel to allow for the display, the display connector, and excess display cable. Remember that a service loop is necessary to allow access to the display connector when removing the display or inserting it into the instrument panel. Cooling While the display has no special cooling requirements, it should be mounted to permit adequate ventilation. Viewing Angle The viewing angle for the CRT display is not a critical factor. The most favorable mounting position would be near eye level and no more than arms length from the principle user of the instrument. Pr el im in ar Panel Depth 2-15 Rev. A SKY899 Installation Manual 2.6 CABLE REQUIREMENTS AND FABRICATION The installer will supply and fabricate all system cables. Cable specifications and approved vendors are provided in paragraph 1.7, equipment required but not supplied. Appendix A defines the electrical characteristics of all input and output signals and identifies the cable requirements for each signal. Required connectors and contact pins are supplied in the installation kits. NOTES 1. Use of any cable not meeting BFG Avionics Systems specifications voids all system warranties. 2. All wiring must be in accordance with industry accepted methods, techniques and practices. 3. All wires are 22 AWG. except where noted, refer to figures 2-2, 2-3 and 2-4 for interconnect wiring information. The length and routing of the external cables must be carefully studied and planned before attempting installation of the equipment. Observe the following precautions: ar • ARINC-429 inputs (receive channels) must be paired with other ARINC-429 inputs of the same speed (12.5 or 100 kHz). Details are outlined in paragraph 2.9. • All cable routing should be kept as short and direct as possible. in • Avoid routing the cables too close to aircraft control cables. • Avoid routing cable near the ADF, comm radio, or transponder antenna cables (allow at least a 12 inch (30.5 cm) separation). im • Avoid routing cable near power sources (e.g., 400 Hz generators, trim motors, etc.) and near power for fluorescent lighting. • Use pressurized bulkhead connectors certified for your specific aircraft pressurization. • To limit the possibility of wire chafing, it is recommended that heat shrink sleeving be installed over the wire bundle between the shield termination’s (inside the connector backshell) and the connector cable clamp. Pr el • Observe all wiring notes on interconnect wiring diagram (figures 2-2, 2-3 and 2-4). After fabricating the cables and before installing the equipment, use the interconnect diagram to verify continuity between each pin and its opposite end termination. Check resistance to ground between each connector pin. When a path to ground is detected, verify its validity. Figure A-1 P1 connector pin identifiers has been added to assist in fabrication and continuity verification of the interconnect cable. 2-16 Rev. A SKY899 Installation Manual 2.6.1 Antenna Cables NOTES 1. Use of any cable not meeting BFGoodrich Avionics Systems specifications voids all system warranties. 2. If you fabricate your own cables, you must verify that the attenuation and VSWR does not exceed the specified values. 3. To add strain relief and alleviate stress caused by aircraft vibration, place 46 inches (10.2 to 15.2 cm) of heat shrink tubing over each antenna connector and cable. The directional antenna requires three cable assemblies; sum (Sigma Port), bit probe (Probe Port) and difference (Delta Port). Cable attenuation for the sum and difference ports must not exceed 2.5 dB. Attenuation for the bit probe cable must not exceed 6 dB. VSWR, on cables attached to the sum, bit probe, and difference ports, must not exceed 1.5:1. (See paragraph 1.7 for antenna cable vendors and specifications.) ar At the antenna, each connector has an identifying color band. To ensure the cables are connected to the correct port, affix the following marking at the termination points of each cable: The Sum (Sigma) port is the forward antenna connector. It is marked with a blue band. Fabricate the sum antenna cable with a TNC connector at each end. Affix a blue marking band on each connector. At the TRC, the sum port (J9) is identified with blue marking. Bit Probe Port The Bit Probe port is the center antenna connector. Fabricate the probe cable with a BNC connector at each end. Difference (Delta) Port The Difference (Delta) port is the rear antenna connector. It is marked with a red band. Fabricate the difference antenna cable with a TNC connector at each end. Affix red marking band on each connector. At the TRC, the difference port (J11) is identified with red marking. Pr el im in Sum (Sigma) Port When routing antenna cables, observe the following precautions: • All cable routing should be kept as short (do not exceed maximum cable length detailed in table 16) and direct as possible. • Avoid sharp bends (do not exceed maximum bend radius detailed in table 1-6). • Avoid routing cable near power sources (e.g., 400 Hz generators, trim motors, etc.) and near power for fluorescent lighting. • Avoid routing cable near ADF antenna cable (allow at least a 12-inch (30.5) separation). 2.6.2 Audio Output Cable For audio output cable use #22 AWG (minimum) twisted shielded pairs with the shield grounded at both ends. Cable runs can be up to 30 ft., but should be as short as practicable. 2.6.3 Data Cables RS-232, RS-422, and ARINC-429 data cables are #22 AWG (minimum) twisted, shielded cables. The shield shall be grounded at both ends and at all breaks. Cable runs should be as short as practicable. 2-17 Rev. A SKY899 Installation Manual 2.6.4 Heading Input Cable The heading input cable connects the TRC899 to the aircraft synchro heading system (refer to the Interconnect Wiring Diagram, figure 2-2, 2-3 or 2-4). Cable specifications are listed below (see paragraph 1.7 for cable vendors). NOTE Use of any cable not meeting BFG Avionics Systems specifications voids all system warranties. 3. 4. 5. 6. 7. ar 2. Twisted, Shielded, Jacketed Triad #24 AWG Colors: White, Blue, Orange Shield: Tin Plated Copper Braid, 90% min. Jacket: FEP .007 in. min., White Twisted, Shielded, Jacketed Pair #24 AWG Colors: White, Blue Shield: Tin Plated Copper Braid, 90% min. Jacket: FEP .007 in. min., Blue Same as Item 2, except Orange jacket. Aluminized Mylar® Wrap. #34 AWG braided shield. FEP Teflon® jacket .013 in. - .023 in., clear (translucent). Marker tape with vendor P/N. in 1. The synchro cable consists of the following (refer to figure 2-5): Pr el im The sub-cable color-coded jackets and shields should be left on the sub-cables as close to the connector as practical to provide the required shielding and to identify the sub-cables. Figure 2-5. Heading Input Cable 2.6.5 Power Cable For the power cable, use #16 AWG (minimum) twisted shielded pair cable (Beldon 83322, Alpha 2826/2, or equivalent). The power cable runs from the aircraft circuit breaker panel to the TRC. The power cable is connected to the TRC using the MS3126F12-3S connector included in the TRC installation kit. Terminate the shield to airframe ground at the power source. Power cable routing and length are not critical to system operation. The SKY899 is a 28 V dc system (18 to 32 V dc). NOTE 5 A circuit breaker is required. 2-18 Rev. A SKY899 Installation Manual 2.6.6 Suppression Bus Cable For the suppression bus use any size low capacitance shielded cable. Cable runs should be as short as practicable and the shields should be grounded at both ends. 2.6.7 WX-1000/SKY497 Display and WX-1000 Processor Cable The display cable connects the TRC to the WX-1000/SKY497 Display. Cable specifications are listed below (see paragraph 1.7 for cable vendors). If a WX-1000 Stormscope® Weather Mapping System is installed, the same cable is used to connect the TRC to a WX-1000 processor. Refer to figure 2-2 (without WX-1000 processor) or 2-3 (with WX-1000 processor) for interconnect wiring information. Pin-out information relating to the WX-1000 display and processor is also provided in tables 2-2 and 2-3. ar The display cable consists of the following (refer to figure 2-6). For alternate display device cable see ARINC-429 data cable (par. 2.6.3) and refer to figure 2-4 for connections. Twisted, shielded, jacketed triad #22 AWG Colors: White, Blue, Orange Shield: Tin plated copper braid, 90% min. Jacket: FEP .007 in. min., White jacket 2. Twisted, shielded, jacketed pair #24 AWG Colors: White, Blue Shield: Tin plated copper braid, 90% min. Jacket: FEP .007 in. min., Blue jacket 3. Same as 2 except Orange jacket. 4. Same as 2 except Green jacket. 5. Same as 2 except Red jacket. 6. Same as 2 except Black jacket. 7. Same as 2 except Yellow jacket. 8. Aluminized Mylar® wrap. 9. #34 AWG braided shield. 10. FEP Teflon® jacket .013 in. - .023 in., Red tint. 11. Marker tape with Vendor P/N. Pr el im in 1. 2-19 Rev. A SKY899 Installation Manual 11 10 Figure 2-6. Display Cable ar The sub-cable color-coded jackets and shields should be left on the sub-cables as close to the connectors as practical to provide the required shielding and to identify the sub-cables. im in 2.6.8 Converting Existing Aircraft Wiring from SKY497 to SKY899 In some instances, it may be desirable to convert an existing SKY497 installation to a SKY899 installation. The SKY899 is a new system with the addition of a system configuration module and a new TRC899. Even though the TRC899 resembles a TRC497, uses the same antenna and mounting hardware, the external connector P1 has different pinouts and is keyed differently to prevent the possibility of damaging a TRC. In order to relocate pin positions use the insertion and extraction tools listed in paragraph 1.7, under sub title "Connector Installation." NOTE Pr el All P1 connections will need to be moved from an existing pin location to a new pin location, as well as the addition of the system configuration module. Only the power and antenna connections remain the same. Some of the differences: TRC899 TRC497 • 7 ARINC-429 RX channels 2 ARINC-429 RX channels • 3 ARINC-429 TX channels 1 ARINC-429 TX channel • System Configuration Module (configure system in service menu) Individual configuration pins • Heading valid, 1 input pin (low/high level selected in service menu) Heading valid, 2 input pins (low or high level) • Analog radio altimeter Not available • 18 - 32 V dc power input 11 - 34 V dc power input • ADS-B (requires mode S transponder address) Not available • Altimeter Gilham Code "D2" added (do not connect if not available) Altimeter Gilham Code "D2" not available • Lamp Outputs - above, below and oper_mode (used with alternate display) Not available • Transponder input/output Not available • Stepper (heading) not available Stepper (heading) available 2-20 Rev. A SKY899 Installation Manual 2.7 AIRCRAFT DISCRETE INPUTS The aircraft discrete inputs are used to assist in determining the aircraft's phase of flight or flight condition (e.g., on ground or in flight). Inputs are diode isolated inside the TRC, do not install isolation diodes externally. The active or inactive state of the inputs can be high or low, they will be saved in the System Configuration Module during system setup using the service menu. 2.7.1 Audio Inhibit (Terrain Warning System - GPWS) The audio inhibit input will sense a terrain warning alarm (i.e., GPWS, EGPWS, TAWS) and temporarily disable the audio alert output until the terrain warning clears. The input can be either a constant flag signal or an alternating flag output. The flag must be cleared for 5 seconds before the TRC accepts a “NO ALARM” condition and restores audible alerts. NOTES 1. If the aircraft is equipped with terrain warning system, it must be connected to the TRC. ar 2. If the aircraft is not equipped with terrain warning system, leave this input unconnected. Audio inhibit connection: GPWS P1-34 Landing gear connection: GEAR P1-33 im in 2.7.2 Landing Gear This input is to be connected to the landing gear switch to sense the position of the landing gear (fixed, up or down). The switch status of this input is selected during system setup via the service menu. This input has three service menu options, none (fixed gear), active low (electrically ground with aircraft on the ground) and active high (electrically high (+9 V to +28 V) with aircraft on the ground). Pr el If the aircraft does not have a landing gear switch (e.g., fixed-gear aircraft), leave this input unconnected. With this configuration, if a radio altimeter (analog or ARINC-429) is not installed, the system will default to the highest TA sensitivity level (level B) and audio TA announcements (i.e., “traffic, traffic”) will not be inhibited during takeoff and landing. 2.7.3 SKYWATCH/Stormscope Mode Switch The SKYWATCH/Stormscope mode switch (SW1) is required only if a WX-1000 Stormscope Weather Mapping System is installed. This switch permits the flight crew to switch the display between the SKY899 and WX-1000. If a TA (Traffic Advisory) is detected while in the Stormscope mode, the display will switch to the SKYWATCH mode. Refer to figure 2-3 for interconnect wiring information. Any general purpose SPST toggle switch (3 Amp @ 28 V dc) may be used. Display mode switch cable routing and length are not critical to system operation. Mount the switch at a location easily accessible to the pilot. SKYWATCH/Stormscope mode switch connections: SMS SMS_RET P1-15 P1-23 2.7.4 Squat Switch (Weight-On-Wheels) This input is to be connected to the squat switch (weight-on-wheels) to sense when the aircraft is on the ground. The switch status of this input is selected during system setup via the service menu. This input has three service menu options, none (no squat switch installed), active low (electrically ground with aircraft on the ground) and active high (electrically high (+9 V to +28 V) with aircraft on the ground). 2-21 Rev. A SKY899 Installation Manual NOTE If the aircraft is not equipped with a squat switch, it is recommended that a squat switch be installed. Squat switch connection: SQUAT P1-24 If a squat switch is not available, this input could be tied to an airspeed switch inline with the pitot system as an alternate input for the squat switch. In this configuration care should be taken to ensure the switch is set to trigger at a speed consistent with take-off and landing. On helicopter installations with skids, and a squat switch is not available, this input can be tied to the collective switch. In this configuration care should be taken to ensure the switch is connected to provide a ground when the aircraft is on the ground and open when the aircraft is airborne. ar If it is not possible to install a squat switch, airspeed switch, or collective switch, select none in service menu. With this configuration the pilot must toggle the system in and out of standby manually. Traffic will only be displayed when the pilot switches out of the standby position. in With a squat switch installed, SKYWATCH HP will automatically switch out of standby 8 to 10 seconds after takeoff and switch back to standby 24 seconds after landing. A squat switch would also prevent the pilot from placing SKYWATCH HP in standby (i.e., pressing the →STB button) while the aircraft is inflight. im 2.7.5 ON/OFF Power Switch This input connection turns the TRC ON and OFF. Wiring of this input will vary depending upon your specific installation. With pin P1-4 connected to P1-5 the system will turn on. There are three possible configurations discussed below: Alternate Display. A separate ON/OFF switch is required (any SPDT toggle switch rated at 3A @ 28 V dc can be used). Refer to display manufactures instructions and figure 2-4 concerning this connection. Pr el WX-1000/SKY497 Display (without WX-1000). Connect per figure 2-2. Stormscope WX-1000 Installation. This external over-ride switch (SW2) is required if a WX-1000 Stormscope Weather Mapping System is installed. The override switch enables the SKYWATCH HP to be powered-up if the WX-1000 processor has been removed for maintenance. During normal operation the switch should remain in the NORMAL position and moved to OVERRIDE only if the WX-1000 processor has been removed for service or if it is necessary to access the WX-1000 service menu. Connect per figure 2-3 Any general purpose DPDT toggle switch (3 Amp @ 28 V dc) may be used. The maintenance switch cable routing and length are not critical to system operation. The switch can be located in the avionics bay near the WX-1000 processor. ON/OFF power switch connection: ON/OFF ON/OFF_RET P1-4 P1-5 2.8 ALTERNATE DISPLAY Alternate display (ARINC-735 compatible is required for TCAS I installation) is connected to ARINC-429 output channel. Refer to paragraph 2.9 for ARINC-429 output channel information. 2-22 Rev. A SKY899 Installation Manual 2.9 ARINC-429 The ARINC-429 interface can be divided into four sections: general sensor inputs, mode S transponder input/output, alternate display output and future input/output options. The TRC has seven receive channels and three transmit channels that are used to accomplish the various interfaces. However, two receiver and two transmitter channels are not used at this time (future option). ARINC-429 labels accepted and transmitted are listed in tables A-3 and A-4. ar NOTES 2.9.1 General Sensor Inputs The TRC can use four general sensor inputs: barometric altimeter, radio altimeter, magnetic heading, and GPS navigation data. Five receive channels have been designated for these inputs and will allow various combinations of speed and equipment types. It is also possible for multiple data inputs (barometric altimeter, radio altimeter, magnetic heading and GPS navigation) from one source to be received on one channel (e.g., ARINC-429 superbus). Receiver speed and equipment type must be set via the service menu. When planning the ARINC-429 interface note the following: Pr el A429RX3_A (P1-64) A429RX3_B (P1-65) A429RX4_A (P1-73) A429RX4_B (P1-74) im ARINC-429 General Sensor Input connections: A429RX1_A (P1-54) A429RX1_B (P1-55) A429RX2_A (P1-62) A429RX2_B (P1-63) in 1. The data rate for RX channels 1 and 2 must be set to the same speed (12.5 or 100 kHz). 2. The data rate for RX channels 3 and 4 must be set to the same speed (12.5 or 100 kHz). 3. The data rate for channel 5 is independent of the other receivers. Channel 5 can be set to 12.5 or 100 kHz. A429RX5_A (P1-75) A429RX5_B (P1-76) 2.9.2 Mode S Transponder I/O (future option) The TRC has one receive and one transmit channel designated for the mode S transponder XT & TX bus interface. The receiver and transmit speed is fixed at 100 kHz. This is a future option, do not connect at this time. Mode S Transponder XT bus connections: A429RX7_A (P1-83) A429RX7_B (P1-84) Mode S Transponder TX bus connections: A429TX2_A (P1-44) A429TX2_B (P1-45) 2-23 Rev. A SKY899 Installation Manual 2.9.3 Alternate Display Output The TRC has one transmit channel designated for alternate displays (i.e., EFIS, MFD and weather radar via RGC250). The transmitter speed is fixed at 100 kHz. The display driver must be selected via the service menu. The display drivers control the ranges and information that will be presented on the alternate display. The drivers are listed in table 2-1 along with their specifications. NOTE When an alternate display is selected via the service menu the alternate display is the master display and the WX-1000/SKY497 display is the slave (i.e., display range settings are controlled by the alternate display driver). Alternate Display connections: A429TX1_A (P1-42) A429TX1_B (P1-43) Table 2-1. Alternate Display Drivers DISPLAY RANGES STANDBY RANGE SELF-TEST RANGE Standard Type 1 2, 6, 15 nmi 15 nmi 6 nmi Standard Type 2 6, 12, 20 nmi 12 nmi Standard Type 3 5, 10, 20 nmi 10 nmi Sextant Type 1 6, 12, 24 nmi 12 nmi Sextant Type 2 6, 12, 24 nmi 12 nmi 6 nmi Does not display unrestricted mode Sextant CG 6, 12, 24 nmi 6 nmi 6 nmi Does not display unrestricted mode 2, 5, 10, 20 nmi 10 nmi 5 nmi 5, 10, 25 nmi 10 nmi 5 nmi Forestry Serv ar No alternate display connected must use WX1000/SKY497 display. 6 nmi 5 nmi 6 nmi Pr el Collins EFIS Type 1 REMARKS in None im DISPLAY DRIVER NAME Displays unrestricted mode, must use external lamps to annunciate UNR mode. Sends only 8 most threatening intruders to display. EFIS changes ranges internally. 2.9.4 Future Option The TRC has one spare receiver A429RX8_A (P1-81) & A429RX8_B (P1-82) and one spare transmitter A429TX3_A (P1-52) & A429TX3_B (P1-53) reserved for a future option. Do not connect these I/O channels. 2.10 AUDIO (ALERT) OUTPUT Voice messages are output to the aircraft audio system, unless the audio inhibit input (from GPWS) is active. The audio output is disabled when a terrain warning system (GPWS) alarm is detected and remains disabled until the warning clears. Two outputs, 150 ohm and 600 ohm, can supply up to 40 mW to the audio distribution system. Volume level is set via the Service Menu. Audio output connections: AUDIO_H AUDIO_L AUDIO_C 2-24 Rev. A P1-89 (600 Ohm) P1-90 (150 Ohm) P1-91 (Audio Common) SKY899 Installation Manual 2.11 BAROMETRIC (UNCORRECTED) ALTITUDE INPUTS The TRC requires an uncorrected barometric altimeter input. The barometric altitude can be gilham code or ARINC-429 (air data computer (ADC)). NOTES 1. Only one uncorrected barometric altimeter input source, either gilham code, ARINC-429 (ADC) should be connected. 2. The uncorrected barometric altimeter input (gilham code or ARINC-429) should be from the same source that is interfaced with the transponder or it must be at least as accurate as that source, i.e., ± 125 ft. ar 2.11.1 Gilham Code (Encoding Altimeter) These signals are gilham code inputs coming from an airdata computer or altitude digitizer (encoding altimeter). These 11 lines may be connected in parallel with the aircraft transponder. If the aircraft is equipped with selectable altitude encoders, connect the altitude inputs so that SKY899 is always connected to the selected encoder. (Reference ARINC 572-1.) Altitude encoder connections: in NOTE If the aircraft has switched encoders that use 28V RETURN or AIRCRAFT GROUND as reference for encoder selection, then ALTITUDE COMMON should be left unconnected. D2* -to- P1-70 D4 -to- P1-71 im A1 -to- P1-56 B1 -to- P1-59 C1 -to- P1-67 A2 -to- P1-57 B2 -to- P1-60 C2 -to- P1-68 A4 -to- P1-58 B4 -to- P1-61 C4 -to- P1-69 ALTITUDE COMMON - to P1-72 * If D2 is not used P1-70 should remain unconnected Pr el 2.11.2 ADC (ARINC-429) ADC (ARINC-429) speed can be 12.5 or 100 kHz and must be paired with another input device set to the same speed. Refer to paragraph 2.9 for ARINC-429 receiver channel information. 2.12 GPS (ARINC-429) The GPS (ARINC-429) speed can be 12.5 or 100 kHz and must be paired with another input device set to the same speed. Refer to paragraph 2.9 for ARINC-429 receiver channel information. In order to use ADS-B, SKYWATCH HP requires a GPS input that is GAMA or ARINC-743A compliant. 2.13 HEADING INPUT The magnetic heading can be provided by synchro (XYZ) or ARINC-429 (attitude heading and reference system), depending on the configuration settings. Heading source will be selected during system setup via the service menu. Select only one heading source for the input. 2.13.1 Compass Synchro (XYZ) Synchro (XYZ) heading input accepts ARINC 407, 407-1 signals. The FLAG line input provides the TRC with flag status (or heading valid) information. The status of the heading valid signal can be none, active high, or active low (see appendix A for signal characteristics) and must be selected during system setup via the service menu. 2-25 Rev. A SKY899 Installation Manual Synchro (XYZ) heading connections: HEADING_X HEADING_Y HEADING_Z HEADING_H HEADING_C HEADING_FLG P1-46 (Synchro X) P1-47 (Synchro Y) P1-48 (Synchro Z) P1-49 (26 V ac High) P1-50 (26 V ac Low) P1-51 (Heading Valid) 2.13.2 AHRS (Attitude Heading and Reference System) AHRS provides aircraft attitude and heading values via the ARINC-429 bus. ARINC-429 receiver channel speed can be 12.5 or 100 kHz and must be paired with another input device set to the same speed. Refer to paragraph 2.9 for ARINC-429 receiver channel information. ar 2.14 LAMP OUTPUTS (ABV and BLW) The lamp outputs are used only with an alternate display that is not capable of annunciating the vertical display modes for above (ABV) and below (BLW). Outputs are switched to ground when active. The lamps require a separate dc source (constant or dimming circuit). If lamp voltage is an ac source then an isolation relay must be used. LP1OUT LP2OUT P1-66 (ABV) P1-85 (BLW) in Lamp connections: ABV BLW (Above) Pr el ABV BLW (Normal) im Depending on the vertical display mode selected the appropriate annunciator(s) will light. If in normal mode neither lamp will light, if in above mode the ABV lamp will light, if in below mode the BLW lamp will light, and when unrestricted vertical mode is selected both lamps will light. See figure 2-7. ABV BLW (Below) ABV BLW (Unrestricted) Figure 2-7. Above and Below External Lamps 2.15 OPERATIONAL MODE OUTPUT (optional) Operational mode output can drive a lamp annunciating when the system is in operational mode (i.e., not in standby mode). Output is switched to ground when system is in operation mode. The maximum current draw is 300 mA. The lamp requires a separate dc source (constant or dimming circuit). If lamp voltage is an ac source then an isolation relay must be used. Operational mode connection: OPER_MODE P1-31 2.16 POWER INPUT The SKY899 is a 28 V dc system (18 to 32 V dc) and requires a 5A circuit breaker. See paragraph 2.6.5 for cable and shield connection information. 2-26 Rev. A SKY899 Installation Manual Power connection: +28V +28V_RET SPARE P8-A P8-B P8-C 2.17 RADIO ALTIMETER (optional) It is recommended an radio altimeter be connected to the TRC, which will be used in selecting the appropriate sensitivity level based on your distance above ground. The TRC can accept radio altimeter input from analog or ARINC-429 source. NOTE The radio altimeter must provide full range output between 0 and 2500 feet. Not all altimeters provide this full range output. The full range output can sometimes be obtained as a mod to the radio altimeter. Check with the specific altimeter manufacturer for compatibility and availability of modification, if necessary. in ar 2.17.1 Analog This interface allows a DC analog radio altimeter to be used to monitor own aircraft height above ground and includes input for radio altitude valid signal. Some analog radio altimeters utilize a discrete valid/invalid signal line to indicate radio altitude validity, while others set the analog data input line to a high out-of-range value for invalid altitude conditions. If a discrete flag signal is not available leave RAD_ALT_FLG (P1-14) unconnected and select None in the Service Menu (Rad Alt Flag sub-menu). RAD_ALT_IN_HI RAD_ALT_IN_LO RAD_ALT_FLG im Analog radio altitude connections: P1-6 (High) P1-7 (Low) P1-14 (Valid Flag) Pr el 2.17.2 ARINC-429 Radio altimeter ARINC-429 speed must be paired with another input device set to the same speed, either low (12.5 kHz) or high (100 kHz). Refer to paragraph 2.9 for ARINC-429 receiver channel information. 2.18 SERIAL DATA The TRC has one RS-232 debug port (J7, terminal device) for service menu access. The TRC has an auxiliary RS-232 and RS-422 data bus designated for future use (do not connect at this time). Debug port connection: DIAG_GND DIAG_RX DIAG_TX CTS RTS P7-5 P7-2 P7-3 P7-7 P7-8 Auxiliary RS-232 connection (future use): RS232_TX2 P1-86 RS232_RX2 P1-87 RS232_GND2 P1-88 Auxiliary RS-422 connection (future use): RS422_TXA P1-77 RS422_TXB P1-78 RS422_RXA P1-79 RS422_RXB P1-80 2-27 Rev. A SKY899 Installation Manual 2.19 SOFT-KEYS If using a WX-1000/SKY497 display connect the soft-keys 1 thru 4 per figures 2-2 or 2-3. When using an alternate display device reference figure 2-4 as well as manufacturer instructions concerning these connections. Required soft-key connections will depend upon the alternate display capabilities. 2.20 SUPPRESSION BUS I/O The TRC outputs a 100 µs (± 5 µs) suppression pulse on the aircraft suppression bus (P1-93). In addition, the TRC899 receives suppression signals from all other devices on the suppression bus (e.g., transponder, DME). (Reference ARINC 735-2 and DO-197.) CAUTION The aircraft transponder must have suppression circuitry to ensure that SKY899 does not paint itself as a target (e.g., TA). in ar 2.21 SYSTEM CONFIGURATION MODULE The system configuration module (figure 2-8) is used to store aircraft installation dependent information (e.g., aircraft type, discrete inputs, heading source, speed of data bus, etc.). Aircraft specific information is selected via the service menu, typically during system setup. Once the setup settings have been saved the system configuration will stay with the aircraft wiring allowing the TRC to be replaced or exchanged without having to re-configure the TRC. When powered up the configuration information is sent to the TRC via the bi-directional serial data bus (SDA). im NOTE The system configuration module must be located inside the backshell of connector P1 and wire-tied to the bundle of wires. Reference figure 2-9. System Configuration Module connections: Pr el System Configuration Module Red (VCC) -toBlack (Ground) -toGreen (Serial Clock) -toYellow (Serial Data) -to- TRC899 P1-2 (+3.3V) P1-92 (PLUG_GND) P1-100 (SCL) P1-99 (SDA) RED BLACK GREEN YELLOW TO P1-2 (+3.3V) TO P1-92 (PLUG_GND) TO P1-100 (SCL) TO P1-99 (SDA) TERMINAL P/N M39029/56-348 Figure 2-8. System Configuration Module 2-28 Rev. A CONFIG MODULE P/N 814-18005-001 SKY899 Installation Manual CONFIGURATION MODULE P/N 814-18005-001 (located inside backshell) SPLIT ELBOW 90° BACKSHELL P/N 613-10043-001 s, INC tem cs Sys oni Avi rich ood dul BFG Mo 1 on rati 005-00 figu Con 814-18 P/N NOT TO SCALE 100 PIN CONNECTOR P/N 605-10251-001 Figure 2-9. Typical Location of System Configuration Module (Inside Backshell) ar 2.22 WX-1000/SKY497 DISPLAY (OPTIONAL) The WX-1000/SKY497 display can be used to display traffic alert/advisory information as well as Stormscope information. Connections are listed in table 2-2. Display 19 14 18 10 22 (SW2*) 23 (SW2*) 13 12 25 24 Pr el (Inner Jackets) DPWR+15_OUT DPWR-15_OUT DSPLY_GND HSYNC_OUT_HI HSYNC_OUT_LO VSYNC_OUT_HI VSYNC_OUT_LO VIDEO_OUT_HI VIDEOOUT_LO PWR_SW_HI PWR_SW-LO SFTKEY1_IN SFTKEY2_IN SFTKEY3_IN SFTKEY4_IN P101 im FUNCTION in Table 2-2. WX-1000/SKY497 Display Connection WIRE COLOR TRC SUB-CABLE WIRE P1 WHITE WHITE WHITE BLUE BLUE ORANGE ORANGE RED RED GREEN GREEN BLACK BLACK YELLOW YELLOW WHITE ORANGE BLUE BLUE WHITE WHITE BLUE WHITE BLUE WHITE BLUE WHITE BLUE WHITE BLUE P1-8 P1-9 P1-10 P1-11 P1-12 P1-13 P1-22 P1-16 P1-17 P1-4 P1- 5 P1-18 P1-19 P1-20 P1-21 *SW2 required if WX-1000 Processor installed (see figure 2-2). 2-29 Rev. A SKY899 Installation Manual 2.23 WX-1000 PROCESSOR (OPTIONAL) The SKYWATCH HP can be interfaced to the Stormscope weather mapping system. The connections are listed in table 2-3. Table 2-3. WX -1000 Processor Connection WIRE COLOR WIRE TRC899 P301-5 P301-21 P301-20 P301-3 P301-36 P301-38 P301-6 P301-23 P301-40 P301-7 P301-22 P301-39 P301-9 P301-26 P301-43 P301-44 GREEN GREEN WHITE WHITE WHITE WHITE BLUE ORANGE ORANGE RED RED BLACK BLACK YELLOW YELLOW WHITE BLUE WHITE ORANGE BLUE BLUE WHITE WHITE BLUE BLUE WHITE WHITE BLUE WHITE BLUE SW2* SW2* P1-25 P1-26 P1-27 P1-28 P1-29 P1-30 P1-41 P1-35 P1-36 P1-37 P1-38 P1-39 P1-40 SUB-CABLE ar SHIELD PWRSWHI PWRSWLO +15 -15 DSPGND HSYNCHI HSYNCLO VSYNCHI VSYNCLO VIDEOHI VIDEOLO SFTKEY1 SFTKEY2 SFTKEY3 SFTKEY4 WX-1000 Processor in FUNCTION *SW2 required if WX-1000 Processor installed (see figure 2-2). Pr el im 2.24 ANTENNA INSTALLATION The following paragraphs provide installation details for directional antenna. Standard installation practices prescribed in FAA Advisory Circular No. 43.13 must be followed. The installer must ensure the immediate antenna installation area is clean and prepared so that the antenna is electrically bonded (metal-to-metal contact) to the aircraft. To provide optimum bonding through the mounting holes, prepare the surfaces with Alodine No. 1001. To facilitate mounting to the airframe, the dimensions shown in Figure 2-10 can be used to locate and drill mounting and connector access holes. Connection to the antenna should be made in accordance with the system interconnect diagram (figure 2-2, 2-3 or 2-4). NOTE A doubler plate (not supplied) is required to reinforce the aircraft skin. 1. Connect each of the three antenna cables. Check to ensure that each cable is connected to the correct antenna connector. Each connector/cable has a matching color band (see note par.2.6.1). 2. Attach the antenna to the aircraft, with the special adapter plate and o-ring, using 10-32 hardware provided. See Figure 2-11. NOTES 1. When mounting the antenna remove the O-ring from the bag and install it in the O-ring groove on the bottom of the antenna. 2. For pressurized aircraft, use a sealant that meets the requirements of SAE AMS-S-8802 such as Flamemaster CS3204 class B. For non-pressurized aircraft, use a non-corrosive sealant that meets the physical requirements of MIL-A-46146 such as General Electric RTV162. 2-30 Rev. A in ar SKY899 Installation Manual Pr el im Figure 2-10. Antenna Mounting Holes Figure 2-11. Directional Antenna Installation 2.25 TRC MOUNTING TRAY INSTALLATION To accommodate different space limitations, the standard TRC mounting tray (P/N 805-10870-001) can be channel or flat mounted. To flat mount the tray, simply remove the eight 6-32 (Phillips) screws that secure the channel to the tray. The ruggedized TRC mounting tray (P/N 805-10870-003), required for rotorcraft installations, must be channel mounted. 1. Position tray at the installation location. 2-31 Rev. A SKY899 Installation Manual Determine centers for mounting holes, and drill for required fasteners. See figure 2-12 (standard tray) or 2-14 (ruggedized tray). 3. Secure tray in place using suitable 8-32 (channel mount) or 6-32 (flat mount) hardware. Pr el im in ar 2. Figure 2-12. Mounting Holes for Standard Mounting Tray, P/N 805-10870-001 2-32 Rev. A in ar SKY899 Installation Manual Figure 2-13. Mounting Holes for Ruggedized Mounting Tray, P/N 805-10870-003 im 2.26 TRC INSTALLATION CAUTION Pr el Before placing the TRC into its mounting tray, de-energize or disconnect all power and signal sources and loads used with the SKY899 system. 1. Slide the TRC into the mounting tray (see figure 2-14). Ensure that the rear hold-down pins on the mounting tray are properly inserted into receptacles on the TRC. 2. Place the retainer cups over the TRC J-hooks. Secure the TRC to the mounting tray by tightening the self-locking hold-down knobs. 3. Connect the three antenna inputs to the connectors on the front panel. a. Connect the Sum port antenna connector (P9 - a TNC connector identified with a blue band) to connector J9 (identified with blue marking). b. Connect the Probe (Bit) port antenna connector (P10 - a BNC connector identified with a black band) to connector J10. c. Connect the Difference (Delta) port antenna connector (P11 - a TNC connector identified with a red band) to connector J11 (identified with red marking). 4. Connect I/O Signal Cable (P1 - a 100-pin connector) to connector J1. 5. Connect the power cable (P8 - a three-pin connector) to connector J8. 2-33 Rev. A ar SKY899 Installation Manual J9 INT J1 ER CO NN EC J1 im J1 INTERCONNECT (I/O SIGNAL) J1 PO 8 WE J7 TE ST Pr el J8 POWER UE (BL K) AC SU J9 E( OB ED (R NC J1 RE IFF -D ST TE TO AC J7 in Ae ros pa ce J1 ME MO RY CA RD RETAINER CUPS (2 PLACES) HOLD-DOWN KNOBS (2 PLACES) Figure 2-14. TRC899 Installation 2-34 Rev. A MOUNTING TRAY SKY899 Installation Manual 2.27 MOUNTING THE WX-1000/SKY497 DISPLAY The display mounts in a standard 3ATI panel cutout (figure 2-15). The unit may be mounted from the front or rear. The following paragraphs describe the installation procedure. Pr el im in ar 2.27.1 Panel Cutout Refer to figure 2-15 for the panel cutout and mounting hole dimensions. Drill and punch the required holes. The instrument panel cutout is a standard 3ATI. Figure 2-15. Instrument Panel Cutout and Mounting Holes 2-35 Rev. A SKY899 Installation Manual 2.27.2 Display Installation Figure 2-16 shows a typical display installation. The display can be mounted to the instrument panel from the front or from the rear. An optional mooring clamp is available for increased stability in high-vibration environments. 6-32 X 3/4 PHM (QTY 4) AIRCRAFT PANEL ar MOORING PLATE (NOT SUPPLIED) DISPLAY 6-32 X 3/4 PHMS (QTY 4) in REAR MOUNT AIRCRAFT PANEL Pr el im MOORING PLATE (NOT SUPPLIED) DISPLAY FRONT MOUNT Figure 2-16. Display Installation Use rivnuts® or a mooring clamp to secure the display to the instrument panel. NOTE 1. The mooring clamp is not furnished with the display. 2. A mooring clamp (P/N 78-8060-5856-2) can be ordered when the order for the display is placed. 3. A 3ATI mooring clamp is also available from: MSP, Incorporated R.R. 4, Box 383A Nashville, Indiana 47448 Tel. (812) 988-6623 or FAX (812) 988-6181 2-36 Rev. A SKY899 Installation Manual CHAPTER 3 INSTALLATION CHECKOUT 3.1 INTRODUCTION This section contains instructions for using the BFGoodrich Avionics Systems TT391 Flightline Tester to do post-installation checkout of the SKY899. Detailed setup, operation and maintenance information for the TT391 Flightline Tester is provided in the TT391 Instruction Manual. NOTES 1. This procedure assumes familiarity with the set up and operation of the TT391 Flightline Tester. 2. All test equipment used in completing these tests shall be calibrated in accordance with the manufacturer's recommendations. ar 3. This section provides checkout information for the SKY899 using the WX-1000 Display. If using an alternate display use Appendix F for installation checkout. 4. Checkout of the WX-1000 processor should be done in accordance with the procedures detailed in the WX-1000 Installation Manual. in This procedure will validate the installation and return to service of the SKY899. BRT OFF Pr el im 3.2 CONTROLS All operating controls are located on the front of the display. Figure 3-1 shows the locations of the controls. Complete operating instructions are provided in the SKY899 Pilot's Guide supplied with each system. Figure 3-1. Controls OFF/BRT Switch 1, 2, 3, & 4 Pushbuttons Power is applied by rotating the knob clockwise past the detent. Continued clockwise rotation increases display brightness. Also referred to as soft-keys (1), (2), (3), and (4). In every operating mode a label identifying the button function will be displayed next to the button. 3-1 Rev. A SKY899 Installation Manual 3.3. CHECKOUT PROCEDURE The TT391 Flightline Tester simulates both a ground based secondary surveillance radar (SSR) and an airborne transponder. With the SKY899 set to GROUND TEST (i.e., the barometric altimeter is simulated to 50,000 ft, heading simulated to 0 degrees, and the radar altimeter simulated to 2,500 ft) the TT391 will simulate two targets; a Traffic Advisory (i.e., a solid circle) at ¼ nm and Other Traffic (i.e., open diamond) at 4.5 nm. Both targets will be displayed in level flight at own aircraft altitude (i.e., "00" displayed above the traffic symbol). If the indications given in the following procedure, except for the Flightline Tester, are not obtained, refer to the troubleshooting procedures in Chapter 4. If indications given for the Flightline Tester are not obtained, refer to the maintenance section of the TT391 Instruction Manual. 1. Make sure the aircraft's transponder is in the STBY mode and the DME is turned OFF. At the aircraft's instruments, verify all compass/HSI flags are valid. Verify all avionics equipment that is interfaced with the SKY899 (i.e., GPS, ADC, AHRS, encoding altimeter) are turned ON. NOTE Turn SKY899 ON. The display will show a start-up screen similar to one shown in figure 3-2. After start-up screen appears, rotate the OFF/BRT switch. Verify that clockwise rotation increases display brightness. in 2. ar After power up, it may take a couple of minutes for the altitude encoder to return a valid altitude to the transponder and SKY899. Pr el im BRT OFF BFGoodrich Avionics Systems,Inc. Figure 3-2. Start-up Screen After approximately thirty seconds the display will show the STANDBY screen (see figure 3-3). NOTE If the TRC has not been calibrated to the directional antenna the display may show a “SKY899 FAILED” message. Calibration will be done during system setup. 3-2 Rev. A SKY899 Installation Manual BRT OFF SKY899 Standby MSG OPR TEST ar Figure 3-3. Standby Screen System Configuration (via Service Menu) in 3.3.1 System Setup The system configuration can be done using the service menu or it can be downloaded with a previously saved configuration using the Compact Flash Card. Both setup procedures are described below and assume familiarity with service menu operation, see chapter 4 for operation information. Turn SKY899 OFF and then enter the Service Menu (see paragraph 4.4) by holding the left two buttons (soft-keys 1 and 2) depressed as the system is turned ON. 2. From the Service Menu, select Setup and then select Aircraft Type. The Aircraft Type menu will appear, select correct aircraft type (fixed wing or rotorcraft). Select exit to return to setup menu. 3. From the Setup menu, select Antenna System: im 1. The Antenna System menu will appear, select correct antenna location (top or bottom). b. The antenna model menu will appear, select correct antenna model (NY164 or NY156). c. Verify Antenna location and model, then Select exit until you return to setup menu. Pr el a. WARNING Verify displayed antenna position matches antenna location on the aircraft (top or bottom). Failure to do so could give incorrect traffic bearing. 4. 5. From the Setup menu, select Audio Level: a. The Audio Level menu will appear, set the desired audio level using the up and down selections (level is adjusted in 5% increments). b. Test the audio level by selecting Test. Verify the aural Traffic Traffic message is heard at a comfortable level, then Select exit to return to setup menu. From the Setup menu, select Communication Ports: a. The Arinc 429 Receivers menu will appear, with all source avionics equipment turned on select autodetect. The Please wait... message will appear for approximately 20 seconds as the system configures the receiver channel, equipment type, and speed. 3-3 Rev. A SKY899 Installation Manual b. Verify receiver channels match desired wiring interface. If an interconnect error is discovered, correct wiring and then re-select autodetect. (To manually change individual receiver channels, highlight and select that channel. See see paragraph 4.4.1.4) NOTES 1. It is possible for multiple data inputs (barometric altimeter, radio altimeter, magnetic heading and GPS navigation) from one source to be received on one channel (e.g., ARINC-429 superbus). Multiple data inputs will be indicated by the word Multi in the Arinc 429 Receiver Menu. (See see paragraph 4.4.1.4) 2. The data rate for RX channels 1 and 2 must be set to the same speed (12.5 or 100 kHz). The data rate for RX channels 3 and 4 must be set to the same speed (12.5 or 100 kHz). The data rate for channel 5 is independent of the other receivers. Channel 5 can be set to 12.5 or 100 kHz. From the Setup menu, select Avionics Equipment: a. ar 6. Select exit until you return to Setup Menu. c. The Equipment menu will appear, select Browse All Avionics. 8. Verify the equipment shown in parentheses under each equipment title matches the wiring interface. To change equipment source, highlight and select it from the menu. (See see paragraph 4.4.1.5.) c. Select exit until you return to Service Menu. d. The Save or Revert menu will appear upon exiting setup menu. Select Save Changes to keep current configuration. (Selecting Revert to Old Settings will cause system to exit the service menu without saving changes.) im b. From the Service Menu, select Calibration: Pr el 7. in The system will step you through each equipment sub-menu. As you select the equipment the next equipment menu in the loop will appear. Once you have stepped through all 8 submenus, the equipment menu will reappear. a. Select correct antenna location (top or bottom). The "SKY899 Antenna Calibration in Process..." message will appear. The Built In Test (BIT) signal phase will be calibrated for the TRC, cable connections, and antenna (see paragraph 4.4.3). b. Verify calibration passed: A new bit phase value is displayed and no error messages appeared. c. Press exit to return to Service Menu screen. Perform system setup verification and operation procedure in paragraph 3.3.2. Download System Configuration (via Compact Flash Card) 1. With the SKY899 OFF, lift the memory card door on the front of the TRC899 and insert the compact flash card into J12 connector. 2. Enter the Service Menu (see paragraph 4.4), select Configuration Management. 3. At the Configuration Management menu select Retrieve from CF. Verify the "download was successful" message is displayed. If an error occurs during download, the configuration setup must be done manually (see above "System Configuration" procedure). 4. Turn off the SKY899 and remove the compact flash card from J12 memory card connector. 5. Perform the system setup verification and operation procedure below (see paragraph 3.3.2) to verify configuration data was downloaded correctly. 3-4 Rev. A SKY899 Installation Manual 3.3.2 System Setup Verification and Operation 1. Turn ON all avionics equipment interfaced to the SKY899. 2. From the Service Menu (see paragraph 4.4), select Information. 3. From the Information menu, select Data Monitor. The Data Monitors menu will appear. 4. Select each of the data monitors and verify the sensor information is correct (see paragraph 4.4.2.3): a. Change the status of the landing gear, squat switch, altitude, and heading sensors. Verify data monitors show the correct input changes (i.e., sensing of these signals). b. If the information is not correct, the sensor has failed to communicate with the TRC. Check operation of the sensor and connections between the TRC and sensor. c. Select exit until you return to the Service Menu. From the Service Menu, select Ground Test (see paragraph 4.4.4). 6. From the Ground Test menu, select Perform Ground Test. 7. Verify operation of range function. Soft-key (3) is labeled to indicate the current range. Press soft-key (3) to toggle the display range between 2, 6 and 15 nm. 8. Select the 6 nautical mile range. 9. Verify that the system toggles through the altitude display modes. Soft-key (2) is labeled to indicate the current mode. Press Soft-key (2) to select normal (NRM), below (BLW), above (ABV), and unrestricted (UNR). ar in 10. Select the NRM (normal) mode. 5. im 11. Position the aircraft with the nose aligned on any 90 degree heading. Avoid areas within 250 ft of obstructions (e.g., hangers, large aircraft, control towers, etc.) where there is a potential for multipath problems. Locate and mark test points at 30 degree intervals (i.e., 000, 030, 060, 090, 120, 150, 180, 210, 240, 270, 300, and 330 degrees) with respect to the directional antenna. Mark these points at the same distance, between 100 and 150 ft, from the aircraft. Pr el 12. Position the TT391 Flightline Tester on one of the test points identified in previous step. CAUTION The Flightline Tester is not weatherproof when the lid is open. Do not setup or operate the Flightline Tester in conditions of rain, sleet, etc. 13. Setup and verify operation of the TT391 Flightline Tester: a. Open the chassis lid and remove the lid from the chassis by sliding the lid off of the hinge pins (sliding it to the right). The lid "stay" must be removed from the lid before mounting. The stay will pop off of the lid. (The stay is the hinged part that props the lid open on the chassis). NOTE The Patch Antenna may be used without a tripod. The Patch Antenna can be held, or secured, and pointed towards the SKYWATCH HP aircraft under test WITH THE MOUNTING STUD POINT TOWARD THE GROUND . This orientation is critical. b. Mount the chassis lid, with the Patch Antenna facing the aircraft, onto a tripod (not included). The tripod must be capable of holding the antenna (approximately 2.5 lb) and must provide a standard base mounting stud threaded 1/4"-20. A typical tripod mount is shown in figure 3-4. 3-5 Rev. A SKY899 Installation Manual If the internal batteries are being utilized, proceed to sub-step f. If the Flightline Tester AC Converter Power Supply is to be utilized, proceed to sub-step d. d. Connect the AC Converter Power Supply cable connector to the chassis external connector. e. Connect the AC Converter Power Supply input power cable connector to one of the following AC sources:. • 115 Vac, 60 Hz • 115 Vac, 400 Hz f. Set the Flightline Tester POWER switches to the ON position. g. Verify that the LOW indicator is not steady on (it may flash). If the LOW indicator remains on (i.e., lit), perform one of the following three options. • Use the AC Converter Power Supply to power the unit. • Recharge the internal batteries. • Replace the internal batteries. h. Set the SELF-TEST switch to the 1030 position and verify that the 1030 indicator blinks on for 1/2 second every 5 seconds. i. Set the SELF-TEST switch to the 1090 position and verify that the 1090 indicator blinks on for 1/2 second every 5 seconds. j. Set SELF-TEST switch to center position (off). Set the POWER switch to the OFF position. NOTE ar c. Connect the Flightline Tester coax cable to J3 on the Patch Antenna and to connector J1 in the chassis. (J2 should remain capped by the dust cover). im k. in Care should be taken to ensure that the Patch Antenna is connected to TT391 connector J1 and NOT J2. IF THE PATCH ANTENNA IS CONNECTED TO J2 THE TT391 WILL NOT FUNCTION CORRECTLY. TRIPOD ASSEMBLY (OPTIONAL NOT INCLUDED) Pr el PATCH ANTENNA ASSEMBLY RF LINK COAX CABLE Figure 3-4. Typical Patch Antenna Tripod Mount 3-6 Rev. A SKY899 Installation Manual 14. From each test point (see step 12): a. Position the TT391 Patch Antenna facing the SKYWATCH HP aircraft under test. b. Set the TT391 POWER switch to the ON position. c. Verify that the display shows, in the direction (± 30 degrees) of the TT391, two targets; a Traffic Advisory (i.e., a solid circle) at ¼ nm and Other Traffic (i.e., open diamond) at 4.5 nm. Both targets will be displayed in level flight at own aircraft altitude (i.e., "00" displayed above the traffic symbol). NOTES 1. If the display reflects a gross error in target bearing, check the directional antenna cables at TRC connectors J9 (sum port) and J11 (difference port). They may be reversed. A further indication of this condition would be a target that moved in a counter-clockwise direction when the TT391 is moved in a clockwise direction. ar 2. Multiple targets or a faulty bearing may result from multipath distortion (see step 1). 3. During these tests, the SKY899 may detect and display other active targets. d. in 4. To obtain a better line of sight, it may be necessary to elevate the patch antenna. Set the TT391 POWER switch to the OFF. Repeat procedure from each test point. Step 15 can be done from the last test point. im NOTE To prevent SKYWATCH HP from tracking the movement of the test-set, it is necessary to set the TT391 POWER switch to OFF after completing each bearing measurement. Pr el 15. Return the TT391 assemblies to their position in the aluminum carrying case. 16. Restart SKY899 by cycling power OFF and then ON. 17. Connect an oscilloscope to the suppression bus and verify that the SKY899 suppression pulse (100 µs ±5 µs) exceeds +15 V dc. If less than +15 V dc the suppression bus is overloaded. Check all equipment connected to the bus. Repair/replace the offending device. 18. This completes the post installation checkout procedure. 3.4 SELF TEST 1. Turn SKY899 OFF and then: a. Make sure the aircraft's transponder is in the STANDBY, ON, or ALT mode. NOTE After power up, it may take a couple of minutes for the altitude encoder to return a valid altitude to the transponder and SKY899. 2. b. If installed, power up the radio altimeter. c. Make sure all compass/HSI flags are cleared from the aircraft's instruments. Turn SKY899 ON. The display should show a start-up screen similar to one shown in figure 3-2. 3-7 Rev. A SKY899 Installation Manual 3. After approximately thirty seconds, observe the STANDBY screen and then press the TEST button (soft-key (2)). 4. The display should present a screen similar to that shown in figure 3-5. ar BRT OFF Figure 3-5. Self Test Screen If the SKY899 passes the self-test, the system will return to the STANDBY screen (see figure 3-3) and the voice message, "SKYWATCH SYSTEM TEST PASSED," will be enunciated over the cockpit audio system. 6. If you do not hear the voice message or if the voice message is of insufficient volume: Check headphones/speaker and aircraft audio panel switch settings. im a. in 5. NOTE Audio levels can be adjusted via the service menu and at the aircraft audio panel. There is no internal audio adjustment. Reset the audio level via the service menu (see paragraph 4.4.1.3). c. Check audio connection to the TRC: Pr el b. 1) 600-ohm audio systems should be connected to P1-89 (AUDIO_H). 2) 150-ohm audio systems should be connected to P1-90 (AUDIO_L). 3) Audio common is connected to P1-91 (AUDIO_C). NOTE Audio output from the TRC is transformer isolated. 7. If SKY899 fails the self-test: a. The "SKY899 Failed" screen with an error message indicating the type of failure will be displayed. b. The voice message, "SKYWATCH SYSTEM TEST FAILED", will be enunciated over the cockpit audio system. c. To re-test, press TEST button soft-key (2). d. Refer to the fault isolation procedures in Chapter 4. 3-8 Rev. A SKY899 Installation Manual CHAPTER 4 MAINTENANCE 4.1 INTRODUCTION This chapter contains general flight-line maintenance and troubleshooting procedures for installations interfaced to WX-1000/SKY497 display or an alternate display. Removal of components is on condition of failure. Troubleshooting is intended to aid in isolating failures to a defective assembly. Each time the TRC, directional antenna, or directional antenna cables (including connectors) are replaced, the TRC must be calibrated to the directional antenna (refer to paragraph 4.4.3). 4.2 CONTINUED AIRWORTHINESS No scheduled maintenance is required to ensure continued airworthiness. ar 4.3 PERIODIC MAINTENANCE At regular inspection intervals, do the periodic maintenance procedures of paragraph 4.3.1 thru 4.3.3. 4.3.1 WX-1000/SKY497 Display Check that indicator cable is properly mated and secured. 2. Check to ensure unit is properly placed and secured to the instrument panel. in 1. im CAUTION Do not use cleaning solvents on the viewing face. Check face-plate for cleanliness. Wipe the viewing face with a damp lint-free, static-free cloth. If necessary, clean with a soft cloth moistened with a mild solution of soap and water. Take care to prevent cleaning solution from running down inside the case. 4.3.2 TRC Pr el 3. 1. Check that connectors are properly mated and secure. 2. Check to ensure that the hold-down knobs on the mounting tray are secured to the TRC. 4.3.3 Antenna 1. Check for dents, cracks, and punctures. CAUTION Do not paint the antennas. Do not use cleaning solvents on the antennas. 2. Remove all dirt and grease from surface areas. Clean with a soft cloth moistened with mild soap and water. 3. Visually inspect sealant around the antenna base. Reapply sealant if required. 4-1 Rev. A SKY899 Installation Manual 4.4 SERVICE MENU The Service Menu is intended as an aid in installing, testing and troubleshooting the SKY899 (figure 4-2). The Service Menu is not intended to be used by the pilot during normal system operation. A service menu tree is provided at the end of this paragraph (figure 4-3). When interfaced to an alternate display the service menu functions are accessed via a computer (figure 4-1) using a terminal emulation program, see appendix E for operating instructions. To access the service menu from the terminal emulation program, type the menu command and then type the corresponding prefix for each selection (e.g., 1, 2, x, etc.). 1 Setup 2 Information 3 Calibration 4 Ground Test 5 Configuration Management ar x Exit Service Menu Figure 4-1. Service Menu (Terminal Emulation Program) in Access the Service Menu on a WX-1000/SKY497 display by holding soft-keys (1) and (2) (the left two buttons) depressed as the system is turned on. Hold the buttons until the Service Menu is displayed. The Service Menu is shown in figure 4-2. im BRT OFF SERVICE MENU Pr el Setup Information Calibration Ground Test Configuration Management EXIT NEXT SEL PREV Figure 4-2. Service Menu (WX-1000/SKY497 Display) Ground Test is available only if squat switch input indicates aircraft is on the ground. The buttons perform the following operations: EXIT - backs up one screen (if in service menu screen it will exit and enter normal/standby mode). NEXT - scrolls to the next item. SEL - selects the highlighted item. PREV - scrolls to the previous item. The individual menu items are explained in the following paragraphs. 4-2 Rev. A SKY899 Installation Manual NOTE Service Menu screens are shown for documentation purposes only. Each system may be configured differently and live data will correspond to the sensors installed in a particular aircraft. 4.4.1 Setup The setup menu configures the SKY899 system to your specific installation. Setup covers the aircraft type, antenna system, audio level, communication ports, and avionics equipment. Setup can be accessed by selecting it in the service menu screen. The Setup menu provides the following choices: BRT OFF Setup EXIT SEL PREV in NEXT ar Aircraft Type Antenna Sytem Audio Level Communications Ports Avionics Equipment Pr el im The following menu will appear when you exit the setup menu if changes were made in the system configuration. Save changes will store configuration settings in system configuration module. Revert to old settings will restore the system configuration back to the last saved configuration. BRT OFF Save or Revert Changes have been made! Save Changes Revert to Old Settings Screen appears when exiting Setup menu and changes have been made SEL NEXT PREV Each setup item is covered in the following paragraphs. 4.4.1.1 Aircraft Type The aircraft type menu allows you to choose between fixed wing or rotorcraft aircraft. 4-3 Rev. A SKY899 Installation Manual The Aircraft Type menu provides the following choices: BRT OFF Aircraft Type *None* Fixed Wing Rotorcraft SEL EXIT PREV NEXT The Antenna System menu provides the following choices: ar 4.4.1.2 Antenna System The SKY899 allows you to install the antenna on top or bottom of aircraft and can use the NY156 (TCAS I installation) or NY164 antenna. Only one antenna location can be selected, when choosing an antenna location the other location will automatically be set to "None." BRT OFF in Antenna System im Top Antenna *NY156 Directional* Bottom Antenna [None] EXIT Pr el NEXT SEL PREV Selecting Top Antenna (or Bottom Antenna) provides the following choices: BRT OFF Top Antenna None NY164 Directional *NY156 Directional* EXIT NEXT SEL PREV (Bottom Antenna menu is same as Top Antenna menu) 4-4 Rev. A SKY899 Installation Manual 4.4.1.3 Audio Level The audio level menu allows you to set and test the audio level output. Audio level range is 0 to 40 mW into 600 Ohm load, indicated by percentage (0-100%). Audio level can be adjusted up or down in 5% increments. Selecting test will cause the "traffic traffic" aural message to be annunciated over the aircraft audio system. The Audio Level menu provides the following choices: BRT OFF Audio Level Volume [50%] Up Down Test PREV ar NEXT SEL EXIT im in 4.4.1.4 Communication Ports Configuring the communication ports should be done before configuring the avionics equipment. Select Communication Ports from the Setup menu, the ARINC 429 receiver menu will be displayed. With all avionics equipment turned on, you can set the speed and the equipment type for each channel automatically (Autodetect) or individually. Autodetect is recommended to configure the ARINC 429 receiver's, however you can manually select the equipment type and speed for each individual channel. Selecting Communication Ports from the Setup menu will cause the ARINC 429 Receivers menu to appear: BRT OFF Arinc 429 Receivers Pr el Autodetect Ch. 1: Multi 100 kHz Ch. 2: None 100 kHz Ch. 3: None Auto Ch. 4: None Auto Ch. 5: None Auto SEL EXIT PREV NEXT Receiver menu shows the 5 RX channels, the 429 source and the speed. To change individual channel, highlight desired channel and press SEL. Please wait... will be displayed while autodetect is being performed NOTES 1. The data rate for RX channels 1 and 2 must be set to the same speed (12.5 or 100 kHz). 2. The data rate for RX channels 3 and 4 must be set to the same speed (12.5 or 100 kHz). 3. The data rate for channel 5 is independent of the other receivers. Channel 5 can be set to 12.5 or 100 kHz. 4-5 Rev. A SKY899 Installation Manual Selecting any channel (ch.1 thru ch.5) will cause that individual Rx channel menu to appear: BRT OFF Arinc 429 Rx Ch 1 Type: ADC GPS Speed: 100 kHz EXIT NEXT SEL PREV Equipment Type BRT OFF EXIT NEXT in SEL PREV im Selecting Speed will cause the Speed menu to appear: Speed BRT OFF Pr el 12.5 kHz 100 kHz NEXT 4-6 Rev. A More than one source can be selected for each 429 RX channel. Each selected source will have an asterisk's before and after it. If more than one source is selected the word "Multi" will appear in the ARINC 429 Receivers menu. ar None *ADC* AHRS *GPS* Rad Alt Selecting Type will cause the Equipment Type menu to appear: SEL PREV SKY899 Installation Manual 4.4.1.5 Avionics Equipment Avionics equipment menu allows you to set the source equipment interfaced to SKY899 and sets discrete inputs. With all of the avionics turned on in the aircraft select Browse All Avionics from the avionics equipment menu. This will sequentially step you through the setup of all avionics equipment interfaces. After completing Browse All Avionics selections, corrections can be made by selecting the individual items from the Equipment menu. The Avionics Equipment menu provides the following choices: BRT OFF Browse All Avionics GPS Nav [Gama] Magnetic Heading [None] Barometric Altitude [None] SEL EXIT PREV ar NEXT Using Next button to scroll down will cause these additional menu choices to appear one at a time. Radio Altitude [None] Landing Gear [None] Weight-On-Wheels [None] Audio Suppression [None] External Display [None] Equipment in If ARINC-429 equipment is selected in the avionics equipment menu, but was not configured in the communications port menu the following menu will appear: No Chan Assigned Choose a channel im Ch.1: None Ch.2: Multi Ch.3: None Ch.4: None Ch.5: None Pr el EXIT NEXT BRT OFF 100 kHz 100 kHz 100 kHz 100 kHz 100 kHz This Menu appears when ARINC 429 equipment has been selected, but was not assigned to a channel via the Communication Ports Menu SEL PREV The Avionics Equipment sub-menus are as follows. The GPS Nav menu provides the following choices: GPS Nav BRT OFF *None* GAMA ARINC 743A EXIT NEXT SEL PREV 4-7 Rev. A SKY899 Installation Manual The Magnetic Heading menu provides the following choices: Magnetic Heading BRT OFF *None* Synchro Compass AHRS SEL PREV EXIT NEXT BRT OFF *None* Valid Low Valid High SEL PREV in EXIT NEXT ar Heading Valid Line im The Barometric Altitude menu provides the following choices: BRT OFF Barometric Altitude Pr el *None* ADC Encoding Altimeter EXIT NEXT SEL PREV Selecting ADC will cause the ADC menu to appear: BRT OFF ADC *None* ARINC 429 EXIT NEXT 4-8 Rev. A SEL PREV Selecting Synchro Compass causes Heading Valid Line menu to appear: SKY899 Installation Manual The Radio Altimeter menu provides the following choices: Radio Altimeter BRT OFF *None* Arinc429 Arinc 552 Arinc 552A Bonzer Mark 10X Collins ALT-50 Collins ALT-55 EXIT NEXT Using Next button to scroll down will cause these additional menu choices to appear one at a time. King KRA10/10A King KRA 405 Sperry AA-100 Terra TRA 3000 SEL PREV *None* Valid Low Valid High SEL PREV in EXIT NEXT BRT OFF ar Rad Alt Valid Line Selecting a DC analog radio altimeter will cause Rad Alt Valid Line menu to appear: im The Landing Gear menu provides the following choices: Landing Gear BRT OFF Pr el *None* Valid Low Valid High EXIT NEXT SEL PREV The Weight-On-Wheels (squat switch) menu provides the following choices: Weight-On-Wheels BRT OFF *None* Valid Low Valid High EXIT NEXT SEL PREV 4-9 Rev. A SKY899 Installation Manual The Audio Suppression menu provides the following choices: Audio Suppression BRT OFF *None* Valid Low Valid High EXIT NEXT SEL PREV External Display Using Next button to scroll down will cause these additional menu choices to appear one at a time. EXIT NEXT ar *None* Standard Type1 Standard Type2 Standard Type3 Sextant Type1 Sextant Type2 Sextant CG Forestry Serv Collins EFIS Type1 in If a WX-1000/SKY497 display is installed and an external display driver is selected the WX-1000/SKY497 display ranges are slaved to the external display driver (i.e., display range settings are controlled by the alternate display driver). Refer to table 2-2 for display drivers and ranges. BRT OFF The External Display menu provides the following choices: SEL PREV Pr el im 4.4.2 Information The information screens contain a record of software versions, system (error) log and real-time sensor data (data monitor). If you have problems with the SKY899 record the software versions, the error messages, and then verify the Data Monitor screens match Service Menu selections and the wiring diagrams (figures 2-2 thru 2-4). Have this information available when contacting Field Service Engineering. The field service engineer must have adequate information to diagnose a problem. Select Information from the Service Menu to access the following menus. The Information menu provides the following choices: Information BRT OFF Software Version System Log Data Monitor EXIT NEXT 4-10 Rev. A SEL PREV SKY899 Installation Manual 4.4.2.1.Software Version Select Software Version menu to display the overall system software version. NOTE The software version identified on the TRC serial number tag represents the system software revision and is a combination of the software/firmware installed within the TRC. The software version displayed in this menu may not match the software version (system revision) identified on the serial number tag. The Software Version menu displays the following: BRT OFF Software Version SKYHP Vx.x ar EXIT im in 4.4.2.2 System Log The 20 most recent errors detected by the system self-test are saved in the System Log. For each error, the corresponding error code, date and run-time of occurrence are saved. The system log is displayed by selecting that option from the Information Menu. NOTE Tables 4-2 and 4-3 provide a list and description of each error code (see paragraph 4.6 error messages). Pr el The System Log displays the results in the following format: Using Next button to scroll down will cause additional erros (up to 20) to appear. System Log BRT OFF 24 12/22/00 12:24:35 Software Error ## MM/dd/yy hh:mm:ss ## MM/dd/yy hh:mm:ss ## MM/dd/yy hh:mm:ss EXIT NEXT With an Error highlighted pressing SEL will cause error description to appear SEL PREV where: ## MM:dd:yy hh:mm:ss Error code. Date (month, day and year) Run-time (in hours, minutes and seconds) when error occurred. If the System Log is empty, the following message is displayed: NO FAULTS DETECTED 4-11 Rev. A SKY899 Installation Manual If, due to a failure of non-volatile memory, the System Log cannot be displayed, the following message is displayed: DATA NOT AVAILABLE 4.4.2.3 Data Monitor The data monitor menu consists of 7 data monitors. All data is real-time and is updated to the screen once per second. The Data Monitor menu provides the following choices: Data Monitors BRT OFF in ar SEL PREV EXIT NEXT ARINC 429 Antenna Calibration Barometric Altitude Discrete Values GPS Nav Mag Heading Rad Altitude NOTE im Values displayed on the Data Monitor are continuously updated. The sensor source is read at power-up or whenever a configuration change has been saved. You can change the sensor source, save it and have the data monitor reflect the change without cycling power to the system. This will help in troubleshooting installation problems. Pr el The ARINC 429 Receivers Data Monitor screen displays the following: BRT OFF ARINC 429 Receivers Ch 1: Multi high parity: xxxxx Ch 2: None high parity: 0 Ch 3: None Auto parity: 0 Ch 4: None Auto parity: 0 Ch 5: None Auto parity: 0 EXIT 4-12 Rev. A Parity display is the count of bad parities received. If the number is continuing to increase that is typically a sign of bad data being received. If you have a parity of 0 then valid data is being received. SKY899 Installation Manual The Antenna Calibration Data Monitor screen displays the following: BRT Data Monitor OFF Antenna Calibration Top Antenna Cal. Phase: 129.76 deg Cur. Phase: 130.10 deg Cur. Amp: -80.00 deg Bottom Antenna invalid EXIT BRT OFF If ADC (ARINC-429) was selected for Barometric Altitude source in equipment menu the following data monitor will appear: ar Data Monitor Baro Alt (Encoding Altimeter) Validity: Valid Altitude: 1000 ft The Barometric Altitude Data Monitor screen displays the following: in A4=0 B4=0 C4=0 D4=0 A2=0 B2=1 C2=1 D2=0 A1=0 B1=1 C1=0 D1=0 im EXIT (ADC) Validity: Valid Altitude: 1000 ft The Discrete Values Data Monitor screen displays the following: BRT OFF Pr el Data Monitor Discretes WOW sense: Active Low WOW state: on grnd Gear sense: Active Low Gear state: down Audio sense: Active Low Audio state: suppress EXIT The GPS Nav Data Monitor screen displays the following: Data Monitor GPS Nav (GAMA) Lat 42.308 deg Lon -82.020 deg Trk invalid Spd invalid BRT OFF EXIT 4-13 Rev. A SKY899 Installation Manual The Mag Heading Data Monitor screen displays the following: Magnetic Heading BRT OFF *None* Synchro Compass AHRS SEL PREV EXIT NEXT BRT OFF Validity: Valid Altitude: 4005 ft in (Bonzer Mark 10X) Sense: Active Low Validity: Valid Altitude: 39 ft im EXIT If DC Analog Radio Altimeter was selected in equipment menu the following data monitor will appear: ar Data Monitor Rad Alt (Arinc 429) The Rad Alt Data Monitor screen displays the following: 4.4.3 Calibration NOTE Ensure transponder is in standby while doing calibration. Pr el Each time the TRC, directional antenna, or any of the directional antenna cables (including connectors) have been repaired or replaced the TRC must be calibrated. Calibration is accessed from the Service Menu (i.e., press SEL with Calibration highlighted). The calibration screen shows the current calibration value of each antenna. Since only one antenna location (top or bottom) can be used the antenna location not configured will have an invalid bit phase message. NOTE If the TRC has never been calibrated, the current calibration value will be displayed as 999. The Calibration menu provides the following choices: Calibration The message SKY899 Antenna Calibration in Process... will be displayed while calibration is being performed. Top Antenna Bit Phase: 131.10 degs Bottom Antenna Bit Phase: Invalid EXIT NEXT 4-14 Rev. A BRT OFF SEL PREV After a successful calibration, the new Bit Phase value will be displayed. SKY899 Installation Manual The calibration value (000-359) is derived from a variety of measurements. Specific values are meaningless however, in a failed TRC, a varying spread may indicate problems with the directional antenna system (antenna, cables, or connectors) or the TRC. If the calibration failed, the message “Calibration Failed!” will be displayed. 4.4.4. Ground Test Ground Test initializes the system for on-the-ground testing. In this configuration, the barometric altimeter is simulated to 50,000 ft, heading simulated to 0 degrees, and the radar altimeter simulated to 2,500 ft. Ground test menu is accessed by selecting that option from the Service Menu (i.e., press SEL with Ground Test highlighted). Ground Test BRT OFF SEL im in EXIT ar Perform Ground Test The Ground Test screen displays the following: Selecting Perform Ground Test initializes the ground test software and displays the following: Pr el BRT OFF NOTES 1. When the system is set to GROUND TEST, the barometric altimeter is simulated to 50,000 ft and the heading simulated to 0 degrees. 2. Ground test is available only if the squat switch input indicates aircraft is on the ground. 3. When the system is set to GROUND TEST, the radio altimeter simulated to 2,500 ft. 4-15 Rev. A SKY899 Installation Manual The buttons perform the following operations in this mode: EXIT causes the system to return to the Information Menu. Soft-key (2) - toggles the system through the above (ABV), normal (NRM), below (BLW), and unrestricted (UNR) altitude display modes. It is labeled to indicate current mode (i.e., ABV, NRM, or BLW). Soft-key (3) - toggles the display range between 2, 6 and 15nm. It is labeled to indicate current range (i.e., 2nm, 6nm or 15nm). Soft-key (4) - is not used. 4.4.5 Configuration Management Configuration Management menu allows you to save system configuration to a compact flash, retrieve system configuration from a compact flash, or restore system configuration to factory defaults. To access configuration management, select it from the Service Menu. ar The Configuration Management screen displays the following: Config Management BRT OFF in Archive to CF Retrieve from CF Restore Factory Defaults Pr el im EXIT NEXT 4-16 Rev. A SEL PREV SKY899 Installation Manual SERVICE MENU Setup Information Calibration Ground Test Config Management Setup Aircraft Type Antenna System Audio Level Communication Ports Avionics Equipment EXIT NEXT EXIT NEXT SEL PREV Top Antenna *None* NY164 Directional NY156 Directional EXIT NEXT EXIT NEXT SEL PREV Save or Revert Changes have been made! Save Changes Revert to Old Settings SEL PREV Equipment Arinc 429 Receivers Browse All Avionics GPS Nav [Gama] Magnetic Heading [None] Barometric Altitude [None] Radio Altitude [None] Landing Gear [None] Weight-On-Wheels [None] Audio Suppression [None] External Display [None] Autodetect Ch. 1: Multi 100 kHz Ch. 2: None 100 kHz Ch. 3: None Auto Ch. 4: None Auto Ch. 5: None Auto ar SEL PREV Volume [50%] Up Down Test Please wait... will be displayed while autodetect is being performed SEL PREV in EXIT NEXT Audio Level Top Antenna *NY156 Directional* Bottom Antenna [None] SEL PREV SEL PREV im *None* Fixed Wing Rotor Craft Antenna System Pr el Aircraft Type EXIT NEXT Information Menu Sheet 3 of 3 Calibration Menu Sheet 3 of 3 Ground Test Menu Sheet 3 of 3 Configuration Management Menu Sheet 3 of 3 NEXT Screen appears when exiting Setup menu and changes have been made EXIT NEXT SEL PREV EXIT NEXT SEL PREV Arinc 429 Rx Ch 1 Type: ADC GPS Speed: 100 kHz EXIT NEXT SEL PREV Avionics Equipment submenu on sheet 2 of 3 Bottom Antenna Equipment Type *None* NY164 Directional NY156 Directional None *ADC* AHRS *GPS* Rad Alt EXIT NEXT EXIT NEXT SEL PREV SEL PREV Speed 12.5 kHz 100 kHz NEXT SEL PREV Figure 4-3. Service Menu Tree (Sheet 1 of 3) 4-17 Rev. A SKY899 Installation Manual No Chan Assigned Choose a channel Ch.1: None 100 kHz Ch.2: Multi 100 kHz Ch.3: None 100 kHz Ch.4: None 100 kHz Ch.5: None 100 kHz Browse All Avionics GPS Nav [Gama] Magnetic Heading [None] Barometric Altitude [None] Radio Altitude [None] Landing Gear [None] Weight-On-Wheels [None] Audio Suppression [None] External Display [None] *None* GAMA ARINC 743A EXIT NEXT SEL PREV EXIT NEXT Magnetic Heading SEL PREV Heading Valid Line *None* Valid Low Valid High EXIT NEXT Barometric Altitude *None* ADC Encoding Altimeter EXIT NEXT SEL PREV SEL PREV ADC *None* ARINC 429 EXIT NEXT SEL PREV *None* Arinc429 Arinc 552 Arinc 552A Bonzer Mark 10X Collins ALT-50 Collins ALT-55 King KRA10/10A King KRA 405 Sperry AA-100 Terra TRA 3000 EXIT SEL NEXT PREV Rad Alt Valid Line *None* Valid Low Valid High EXIT NEXT SEL PREV SEL PREV Weight-On-Wheels *None* Valid Low Valid High EXIT NEXT SEL PREV Audio Suppression *None* Valid Low Valid High EXIT NEXT SEL PREV External Display *None* Standard Type1 Sextant Type2 Sextant CG Forestry Serv Collins EFIS Type1 Figure 4-3. Service Menu Tree (Sheet 2 of 3) 4-18 Rev. A EXIT NEXT Radio Altimeter Pr el EXIT NEXT *None* Valid Low Valid High im *None* Synchro Compass AHRS SEL PREV Landing Gear in GPS Nav SEL PREV Equipment EXIT NEXT Menu appears when ARINC 429 equipment has been selected, but not assigned to a channel via the Communication Ports Menu ar Avionics Equipment Submenu from Sheet 1 of 3 EXIT NEXT SEL PREV SKY899 Installation Manual From Service Menu Sheet 1 of 3 SKY899 Antenna Calibration in Process... will be displayed while calibration is being performed Information Software Version System Log Data Monitor SEL PREV Config Management 24 12/22/00 12:24:35 Software Error ## MM/dd/yy hh:mm:ss ## MM/dd/yy hh:mm:ss ## MM/dd/yy hh:mm:ss With an Error highlighted pressing SEL will cause error description to appear SEL EXIT NEXT SEL PREV in SEL PREV EXIT SEL PREV EXIT NEXT Archive to CF Retrieve from CF Restore Factory Defaults Bottom Antenna Bit Phase: Invalid System Log EXIT NEXT Ground Test Perform Ground Test ar EXIT NEXT Calibration Top Antenna Bit Phase: 131.10 degs Software Version im SKYHP Vx.x Pr el EXIT Data Monitors Data Monitor Baro Alt (Encoding Altimeter) Validity: Valid Altitude: 1000 ft A4=0 B4=0 C4=0 D4=0 A2=0 B2=1 C2=1 D2=0 A1=0 B1=1 C1=0 D1=0 EXIT (ADC) Validity: Valid Altitude: 1000 ft ARINC 429 Antenna Calibration Barometric Altitude Discrete Values GPS Nav Mag Heading Rad Altitude EXIT SEL NEXT PREV ARINC 429 Receivers Ch 1: Multi high parity: xxxxx Ch 2: None high parity: 0 Ch 3: None Auto parity: 0 Ch 4: None Auto parity: 0 Ch 5: None Auto parity: 0 EXIT Data Monitor Antenna Calibration Top Antenna Cal. Phase: 129.76 deg Cur. Phase: 130.10 deg Cur. Amp: -80.00 deg Bottom Antenna invalid EXIT Data Monitor Rad Alt (Arinc 429) Data Monitor Mag Heading (Synchro Compass) Validity: Valid Altitude: 4005 ft Sense: Active Low Validity: Valid Heading: 29.877 degs Data Monitor GPS Nav (GAMA) Lat 42.308 deg Lon -82.020 deg Trk invalid Spd invalid EXIT EXIT EXIT (Bonzer Mark 10X) (AHRS) Sense: Active Low Validity: Valid Altitude: 39 ft Mag Heading: 29.998 degs True Heading: 35.002 degs Status: Valid Data Monitor Discretes WOW sense: Active Low WOW state: on grnd Gear sense: Active Low Gear state: down Audio sense: Active Low Audio state: suppress EXIT Figure 4-3. Service Menu Tree (Sheet 3 of 3) 4-19 Rev. A SKY899 Installation Manual 4.5 TROUBLESHOOTING Table 4-1 is intended to assist trained electronic technicians to determine which assembly is inoperative. Do the corrective action steps in the order described. Use the Service Menu (refer to paragraph 4.4) as an aid in fault isolation. Information available from the service menu can help identify conditions that need to be resolved. If interfaced to an alternate display service menu must be accessed via an RS-232 terminal device, see Appendix E for operating instructions. Table 4-1. Fault Isolation SYMPTOM CORRECTIVE ACTION a. Check position of the WX-1000 maintenance switch (NORMAL/OVERRIDE). b. Reset circuit breaker if it is tripped. c. Check aircraft power source. d. Check connection to WX-1000 processor, if installed. e. Check power input at TRC mating connector. P8-A +28V (18 - 32 V dc PWR) P8-B +28V_RET (AIRCRAFT PWR RETURN) f. Check cables connected to display. g. Replace Display. Display is distorted. Check for interference from aircraft systems. Incorrect response to buttons (soft-keys). Check soft-key wiring inside display cable and WX-1000 processor cable (if installed). SKY899 will not enter service menu. a. Check soft-key wiring. in ar Display remains dark after SKY899 is powered ON. b. If using an alternate display device the soft-key's needed for accessing service menu from the WX1000/SKY497 display are not connected. im c. If using an alternate display service menu must be accessed with an RS-232 terminal device by typing the menu command. (Appendix E) SKY899 Failed. 4-20 Rev. A Pr el The self-test successfully completes without audio annunciation. a. Check headphones/speaker and aircraft audio panel switch settings. b. Check volume level and run audio test in service menu. c. Check cables connected to TRC. Audio Alert Output: P1-89 (AUDIO_H - 600-Ohm) P1-90 (AUDIO_L - 150-Ohm) P1-91 (AUDIO_C - Common) a. Check system log (para 4.4.2) for errors. Error messages are detailed in para 4.6. b. Replace TRC. Self-test does not execute. Aircraft is on the ground. a. If standby screen is displayed, check soft-key wiring inside display cable and WX-1000 processor cable (if installed). b. Check squat switch connection to the TRC and the weight-on-wheels configuration in service menu. Squat Switch Input: P1-24 The display cannot be switched between SKY899 and the WX-1000. Both systems are installed. a. Check circuit breakers. Reset if tripped. b. Check position of the WX-1000 maintenance switch (SW2). It should be set to the NORMAL position. c. Check wiring of the SKYWATCH/Stormscope display mode switch (para 2.7.3 and figure 2-2). WX-1000 processor has been removed for service; SKY899 fails to operate. Check position of the WX-1000 maintenance switch (NORMAL/OVERRIDE). When the WX-1000 has been removed for service, it should be set to the OVERRIDE position. This switch may be located in the avionics bay. SKY899 Installation Manual Table 4-1. Fault Isolation (Continued) SYMPTOM CORRECTIVE ACTION a. Verify suppression bus shielded cable is grounded correctly at both ends. b. Connect an oscilloscope to the suppression bus and verify that the SKY899 suppression pulse (100 µs ±5 µs) exceeds +15 V dc. c. If less than +15 V dc, the suppression bus is overloaded. d. Check all equipment connected to the bus. e. Repair/replace the offending device. SKY899 TRC899 has been removed for service; the WX1000 Stormscope fails to operate. Check the adapter plug (see para 4.7). If the TRC899 is removed for service, an adapter plug is required to permit continued operation of the WX-1000. SKY899 paints itself as a target (e.g., TA). in ar 4.6 ERROR MESSAGES SKY899 firmware is designed to generate error messages associated with a particular condition or step in the program. The 20 most recent errors detected by the system are saved in the System Log (see para 4.4.2.2). For your convenience, in table 4-2, we have listed the error messages that have been associated with SKY899 installations. Where appropriate, procedures that may assist in resolving installation problems are provided. When a severe error occurs SKY899 will fail. Table 4-2. Installation Related Error Messages MESSAGE REMARKS ERROR 06 I2C Bus Error a. Configuration module is present, however the BUS communication (SDA or SCL) is incorrect check associated wiring. im ERROR NO. b. Replace TRC. c. Replace configuration module. ERROR 07 Config Module Error a. Configuration module is not found check associated wiring. Pr el b. Replace TRC. c. Replace configuration module. ERROR 10 Compact Flash Error a. Unable to read the compact flash information correctly, verify compact flash is inserted into J12 correctly. b. Try a different compact flash. c. Replace TRC. ERROR 14 RF Amplitude Error a. Check directional antenna and associated cables. b. Calibrate directional antenna (para 4.4.3) NOTE Ensure transponder is in standby and DME is OFF while doing calibration c. Cycle power and run pilot initiated self-test. ERROR 15 RF Angle Error a. Check directional antenna and associated cables. b. Calibrate directional antenna (para 4.4.3) NOTE Ensure transponder is in standby and DME is OFF while doing calibration c. Cycle power and run pilot initiated self-test. ERROR 17 Mag Var Table Error a. Unable to read the compact flash information correctly, verify compact flash is inserted into J12 correctly. b. Try a different compact flash. c. Replace TRC. 4-21 Rev. A SKY899 Installation Manual Table 4-2. Installation Related Error Messages (Continued) ERROR NO. MESSAGE REMARKS ERROR 20 Barometric Input Error a. Check altimeter source. Is the unit turned on and been given enough time to warm up. b. Cycle power. c. Ensure that barometric altitude input is from only one source (gilham code or ARINC429). d. Encoded inputs can be checked from the barometric altimeter data monitor screen (para 4.4.2.3). e. Using the service menu, verify barometric source configuration and altitude information (para 4.4.2.3). f. ERROR 21 GPS Input Error Check wiring associated with altimeter source. a. Check GPS source is it turned on and locked onto satellites. b. Using the service menu, verify configuration (speed and equipment type) is set correctly. ERROR 22 Heading Input Error c. Check ARINC-429 wiring associated with GPS. No heading input being received (ARINC-429 or synchro compass). ar a. Check heading source. b. Using the service menu, verify heading setup in Mag Heading data monitor (para 4.4.2.3). c. If the heading signals become valid, the system will recover automatically. ERROR 23 Synchro Input Error in d. Check wiring associated with heading input. Invalid synchro compass input (XYZ signals or 400 Hz reference). a. Check heading source. b. Using the service menu, verify heading setup in mag heading data monitor (para 4.4.2.3). im c. If the heading signals become valid, the system will recover automatically. d. Check wiring associated with synchro compass input. ERROR 29 System Config Error a. SKY899 requires a barometric altitude input in order to operate. Verify a source has been selected in service menu. Pr el b. Check wiring associated with configuration module if error reoccurs replace configuration module. The error messages in table 4-3 are used by factory technicians in determining what actions may have preceded a system failure. These messages do not necessarily indicate a current system failure and are provided for information only. Should the installer observe these messages in the error log without a SKY899 Failed message during normal operation, no service action is required. Table 4-3. Informational Error Messages 4-22 Rev. A ERROR NO. MESSAGE ERROR NO. MESSAGE ERROR 01 Boot Error ERROR 16 Antenna Sel. Unit Error ERROR 02 ROM Memory Error ERROR 18 ARINC 429 Comm Error ERROR 03 RAM Memory Error ERROR 19 Serial Comm Error ERROR 04 Watchdog Error ERROR 24 Software Error ERROR 05 Bus Fault Error ERROR 25 Operating Sys Error ERROR 08 Unused Interrupt Error ERROR 26 Video Controller Error ERROR 09 I/O Board Error ERROR 27 Video Memory Error ERROR 11 Power Supply Error ERROR 28 NVRAM Error ERROR 12 RF Failure Error ERROR 30 System Test Error ERROR 13 RF Transmitter Error SKY899 Installation Manual 4.7 TRC899/WX-1000 ADAPTER PLUG An adapter plug can be used to by-pass SKY899 only if a WX-1000 Stormscope system is installed. The adapter will permit continued operation of the WX-1000 if the TRC899 is removed for service. It can also be used as a troubleshooting tool when attempting to isolate a problem to either or both systems. The adapter plug mates with P1. It can be purchased from BFGoodrich Avionics Systems (P/N 805-11910001) or fabricated locally from the details provided in figure 4-4. ADAPTER PLUG CONNECTIONS JUMPER PINS PIN INSERT VIEW FUNCTION 25 26 DPWR-15 10 27 DSPLY_GND 11 28 HSYNC_+ 12 29 HSYNC_- 13 30 VSYNC_+ 22 41 VSYNC_- 16 35 VIDEO_+ 17 36 VIDEO_- 18 37 SFTKEY1 19 38 SFTKEY2 20 39 SFTKEY3 21 40 SFTKEY4 35 16 46 56 67 77 86 94 DPWR+15 ar 25 in 100 15 93 24 55 34 45 76 85 66 im ADAPTER PLUG JUMPER INSTALLATION Pr el NOTE ® APPLY LOCTITE TO THE INTERNAL THREADS OF THE BACKSHELL PRIOR TO ASSEMBLY. 0.10 +0.07 -0.00 CRIMP PIN JUMPER #22 AWG WIRE SHORTING CAP BACKSHELL GLENAIR #340HS002M23-2H12A CONNECTOR MIL # D38999/20FH35PB Figure 4-4. Adapter Plug Assembly 4-23 Rev. A SKY899 Installation Manual 4.8 DISPOSITION OF FAILED ITEMS Return defective components to your authorized BFG Avionics Systems dealer or to:: BFG Avionics Systems Attn: Customer Service 5353 52nd Street, S.E. Grand Rapids, MI USA 49512 If available, pack components in their original shipping container. If the original container is not available, pack them as follows: CAUTION Do not use desiccant crystals when packaging electronic assemblies. Since the assembly must be packed tightly, crystals in bag form cannot be used. The use of loose crystals may cause unnecessary damage resulting in a cleaning problem. Ensure that nonconductive covers/caps are installed on the exposed terminals of cable connectors on the display, TRC, and antenna. 2. The display and TRC contain electrostatic discharge sensitive (ESDS) parts and must be wrapped in static protective materials. 3. Wrap with bubble pack. Secure bubble pack with reinforced tape. 4. Place assembly in a cardboard box. 5. Wrap any accessories in tissue and place in the box. Fill spaces with bubble pack. 6. Put a letter on top of bubble pack. The letter must contain: im in ar 1. Your name, address, and telephone number. • Purchase order number. • Description of component including, when applicable, model and serial number. • Date of purchase. • A brief description of the difficulty. • Type of display and radar altimeter. • Copy of error log, if available. Pr el • 7. Shut box and seal with reinforced tape. 8. Attach packing list to outside of box. 4-24 Rev. A SKY899 Installation Manual APPENDIX A SKY899 INTERFACE SIGNAL & CABLE CHARACTERISTICS A.1 INTRODUCTION This appendix defines the electrical characteristics of all input/output signals to the TRC899 and the labels for the ARINC-429 data bus. Sufficient data is included to perform an electrical load analysis for the aircraft. The interface characteristics contained in this appendix are fully compatible with ARINC specifications where noted. Connection information identifies connector-pin and signal names as they appear on interconnect wiring diagram, figure A-1 shows P1 connector pin locations and signal names. NOTE External isolation diodes are not required and SHOULD NOT be installed. A.2 ELECTRICAL CHARACTERISTICS CHARACTERISTICS Altitude (Gilham Code) / Encoding Altimeter Input These uncorrected barometric signals are Gilham code (or gray code) inputs coming from an airdata computer or encoding altimeter (see paragraph 2.11). These 11 lines may be connected in parallel with the aircraft transponder. If the aircraft is equipped with selectable altitude encoders, connect the altitude inputs so that SKY899 is always connected to the selected encoder. (Reference ARINC 572-1.) NOTES 1. Only one altimeter input source (gray code or ARINC-429, not both) should be connected. The altimeter input should be from the same source that is interfaced with the transponder or at least as accurate as that source, i.e., ± 125 ft. 2. If the aircraft has switched encoders that use 28V RETURN or AIRCRAFT GROUND as reference for encoder selection, then ALT_COMMON (P1-72) should be left unconnected. 3. If altitude D2 is not used P1-70 should remain unconnected. Pr el im in ar SIGNAL Signal Name Connector-Pin P1-56 ALT_A1 P1-57 ALT_A2 P1-58 ALT_A4 P1-59 ALT_B1 P1-60 ALT_B2 P1-61 ALT_B4 P1-67 ALT_C1 P1-68 ALT_C2 P1-69 ALT_C4 P1-70 ALT_D2 P1-71 ALT_D4 P1-72 ALT_COMN CABLE Minimum 22 AWG wire for lengths up to 30 ft. VOLTAGE +30 V input max. CURRENT <1 mA sourced per line. FREQUENCY <100 Hz SOURCE Z >10 kΩ per line. MAX CAPACITANCE <20 pF per line. CONNECTION A-1 Rev. A SKY899 Installation Manual SIGNAL CHARACTERISTICS Antenna Top Directional SUM (SIGMA) Port (Blue) Signal Name Connector J9 - TNC SUM Cable attenuation must not exceed 2.5 dB, VSWR 1.5:1. Refer to paragraph 2.6.1. Impedance: 50 Ω CONNECTION CABLE Top Directional BIT PROBE Port (Black) Signal Name CONNECTION Connector J10 - BNC BIT CABLE Cable attenuation must not exceed 6 dB, VSWR 1.5:1. Refer to paragraph 2.6.1. Impedance: 50 Ω Antenna Top Directional DIFFERENCE (DELTA) Port (Red) Signal Name CONNECTION Connector J11 - TNC DIFFERENCE CABLE Cable attenuation must not exceed 2.5 dB, VSWR 1.5:1. Refer to paragraph 2.6.1. Impedance: 50 Ω ar Antenna im in ARINC-429 External Interface The SKY899 has seven ARINC-429 receivers and three transmitter (paragraph 2.9). Four of the channels are paired internally and can operate at either low speed (12.5 kHz) or high speed (100 kHz). However, the paired channels must be set to the same speed (see tables A-1 and A2). The transmitters operate only at high speed (100 kHz). The first ARINC-429 transmitter (A429TX1) is intended to provide the capability to interface with alternate display device. The second and third ARINC-429 transmitters (A429TX2 & TX3) are a future option. Pr el Five of the ARINC-429 receivers can be used to input data from other avionics systems. The sixth and seventh receivers are not used at this time (future option). NOTES 1. The radio altimeter must provide full range output between 0 and 2500 feet. Not all altimeters provide this full range output. The full range output can sometimes be obtained as a mod to the radio altimeter . Check with the specific altimeter manufacturer for compatibility and availability of modification, if necessary. 2. The TRC can accept Radio Altimeter input from ARINC-429 or DC analog source. The Barometric Altitude can be ARINC-429 or Gilham Code. The Magnetic Heading can be ARINC-429 or Synchro (XYZ). Select only one source for each aircraft input. 3. If 429 barometric altitude is used, it should be from the same source that is interfaced with the transponder or it must be at least as accurate as that source, i.e., ± 125 ft. 4. Receive channels 1 and 2 must be set to the same speed (12.5 or 100 kHz). Receive channels 3 and 4 must be set to the same speed (12.5 or 100 kHz). Channel 5 is independent of the other receivers and can be to 12.5 or 100 kHz. A-2 Rev. A SKY899 Installation Manual SIGNAL CHARACTERISTICS CONNECTION Connector-Pin P1-54 P1-55 P1-62 P1-63 P1-64 P1-65 P1-73 P1-74 P1-75 P1-76 P1-83 P1-84 P1-81 P1-82 Signal Name A429RX1_A Ch. 1 line A A429RX1_B Ch. 1 line B A429RX2_A Ch. 2 Line A A429RX2_B Ch. 2 Line B A429RX3_A Ch. 3 Line A A429RX3_B Ch. 3 Line B A429RX4_A Ch. 4 Line A A429RX4_B Ch. 4 Line B A429RX5_A Ch. 5 Line A A429RX5_B Ch. 5 Line B A429RX7_A Ch. 7 Line A A429RX7_B Ch. 7 Line B A429RX8_A Ch. 8 Line A A429RX8_B Ch. 8 Line B ARINC-429 External Interface (Continued) im Audio (Alert) Output (see paragraph 2.10). in ar P1-42 A429TX1_A Ch. 1 Line A P1-43 A429TX1_B Ch. 1 Line B P1-44 A429TX2_A Ch. 2 Line A P1-45 A429TX2_B Ch. 2 Line B P1-52 A429TX3_A Ch. 3 Line A P1-53 A429TX3_B Ch. 3 Line B This output is directly compatible with industry standard audio panels NOTE Audio output from the TRC is transformer isolated. This output is disabled when a terrain warning alarm is detected (see paragraph 2.7.1) Pr el CONNECTION CABLE POWER FREQUENCY LOAD Z Audio Inhibit (Terrain Warning System GPWS) Connector-Pin Signal Name P1-89 (AUDIO_H) - 600 Ω P1-90 (AUDIO_L) - 150 Ω P1-91 (AUDIO_C) Audio Common Minimum 22 AWG twisted shielded pair cable for lengths up to 30 ft. 40 mW into a 600 Ω load. Audio level is adjustable via service menu. 0 - 3.0 kHz Selectable 150 or 600 Ω This input senses a terrain warning alarm and temporarily disables the SKY899 audible alert messages until the warning clears (see paragraph 2.7.1). The input can be either a constant flag signal or an alternating flag output. The flag must be cleared for five (5) seconds before the TRC accepts a "NO ALARM" condition and restores audible alerts. IF THE AIRCRAFT IS NOT EQUIPPED WITH TERRAIN WARNING SYSTEM, LEAVE THIS INPUT UNCONNECTED. NOTE If the aircraft is equipped with terrain warning system (GPWS), it must be connected to the TRC. A-3 Rev. A SKY899 Installation Manual CHARACTERISTICS Signal Name Connector-Pin P1-34 (GPWS) Minimum 22 AWG wire for lengths up to 30 ft. WARNING: 0 V dc to +2.5 V dc (Aircraft Ground). NO WARNING: +9 V dc to +30 V dc or open. <5 mA sourced. CONNECTION CABLE VOLTAGE CURRENT Debug Port NO CONNECTION TO EXISTING AIRCRAFT WIRING. The Debug Port (RS-232) is used for laptop interface to support system setup, post installation checkout and troubleshooting. The port defaults to the following settings: Baud Rate Parity: None Data Bits Stop Bits No handshaking Signal Name DIAG_RX DIAG_TX DIAG_GND CTS RTS in These connections from the aircraft heading source (ARINC 407 & 407-1 Synchro System Manual) allow the unit to rotate the displayed data as the aircraft turns. See Heading Flag in this appendix for flag input specifications. im Heading Input (XYZ Synchro) Connector-Pin J7-2 J7-3 J7-5 J7-7 J7-8 ar CONNECTION 19,200 SIGNAL Min: 50 Hz Pr el X(S1), Y(S3), Z(S2) FREQUENCY Max: 1500 Hz VOLTAGE Min: 5.0 V ac rms (w/reduced angular resolution.) Max: 14.0 V ac rms (external padding required for higher levels.) INPUT IMPEDANCE >50 kΩ Signal Name Connector-Pin P1-46 HEADING_X P1-47 HEADING_Y P1-48 HEADING_Z CABLE See paragraph 2.6.4. H and C (high and low reference) FREQUENCY Min: 50 Hz Max: 1500 Hz Spec says 400 Hz ±20% VOLTAGE Min: 3 V ac rms Max: 35 V ac rms INPUT IMPEDANCE >50 kΩ CONNECTION CONNECTION CABLE A-4 Rev. A Signal Name Connector-Pin P1-49 HEADING_H P1-50 HEADING_C See paragraph 2.6.4. SKY899 Installation Manual SIGNAL CHARACTERISTICS Heading Valid Indicates that the heading source is providing valid heading information. The status of the heading valid signal can be none, active high, or active low and must be selected during system setup via the service menu. Signal Name Connector-Pin P1-51 HEADING_FLG CABLE See paragraph 2.6.4. VOLTAGE None: Open or no connection Active Low: (ref. to aircraft ground) Valid: -5 V dc to +2.5 V dc Invalid: +9 V dc to +32 V dc Active High: (ref. to aircraft ground) Valid: +9 V dc to +32 V dc Invalid: -5 V dc to +2.5 V dc INPUT IMPEDANCE >2 kΩ INPUT CURRENT Active: Min: 1 mA Max: 15 mA ar CONNECTION Balanced horizontal sync from the WX-1000 Processor (if installed) and output to the WX-1000/SKY497 display. Signal levels as specified in RS-422. in Horizontal Sync im CONNECTION Pr el CABLE VOLTAGE CURRENT FREQUENCY LOAD Z Signal Name Connector-Pin P1-28 (HSYNC_IN+) From Processor P1-29 (HSYNC_IN-) From Processor P1-11 (HSYNC_OUT-) To Display See paragraph 2.6.7. 0-5 V dc <100 mA 16.4 kHz 1 kΩ Lamp Outputs (above and below) External annunciators are required when using an alternate display that is not capable of displaying above and below vertical modes. Outputs are switched to ground when active. The lamps require a separate dc source (constant or dimming circuit). If lamp voltage is an ac source then an isolation relay must be used. Depending on the vertical display mode selected the appropriate annunciator will light. If in normal vertical display mode neither lamp will light, if in above mode the ABV lamp will light, if in below mode then the BLW lamp will light, and when unrestricted vertical mode is selected both lamps will light. CONNECTION CABLE VOLTAGE CURRENT Signal Name Connector-Pin P1-66 LP1OUT - (ABV) P1-85 LP2OUT - (BLW) Minimum 22 AWG wire for lengths up to 30 ft. ON: 0 V dc or Ground OFF: Maximum +32 V dc or open Maximum current 300 mA. A-5 Rev. A SKY899 Installation Manual SIGNAL CHARACTERISTICS Operational mode Operational mode output can drive a lamp annunciating when the system is in operational mode. (See lamp outputs above for characteristics.) Signal Name Connector-Pin P1-31 OPER_MODE Minimum 22 AWG wire for lengths up to 30 ft. ON: 0 V dc or Ground OFF: Maximum +32 V dc or open Maximum current 300 mA. CONNECTION CABLE VOLTAGE CURRENT This signal line is to be connected to the landing gear switch to sense the position of the landing gear (fixed, up or down, see paragraph 2.7.2). The state of the switch can be active low or active high in reference to aircraft ground. The switch status can be fixed, active low or active high, this is selected via service menu. Landing Gear Switch Input IF THE AIRCRAFT DOES NOT HAVE A LANDING GEAR SWITCH , THIS INPUT MUST ar REMAIN UNCONNECTED . With this configuration, if no ARINC 429 compatible radio altimeter is installed, the system will default to the highest TA sensitivity level (level B) and audio TA announcements (i.e., “traffic, traffic”) will not be inhibited during takeoff and landing. in Connector-Pin Signal Name P1-33 GEAR CABLE Minimum 22 AWG wire for lengths up to 30 ft. VOLTAGE Fixed: Open or no connection Active Low: (ref. to aircraft ground) Valid: -5 V dc to +2.5 V dc Invalid: +9 V dc to +32 V dc Active High: (ref. to aircraft ground) Valid: +9 V dc to +32 V dc Invalid: -5 V dc to +2.5 V dc CURRENT <5 mA sourced. SOURCE Z >40 kΩ MAX CAPACITANCE <20 pF ON/OFF Power (SW2) Pr el im CONNECTION This input turns the TRC on and off. (See paragraph 2.7.5.) When an alternate display is installed a separate switch is required, any general purpose SPDT toggle switch capable of 3A @ 28 V dc can be used. When a WX-1000 processor is connected to with a SKY899 a maintenance over-ride switch is necessary to enable the SKY899 to be powered-up if the WX-1000 processor has been removed for service. During normal operation, with a WX-1000 processor installed, SW2 should remain in the WX-1000 position. Any general purpose DPDT toggle switch can be used. CONNECTION CABLE VOLTAGE CURRENT A-6 Rev. A Signal Name Connector-Pin P1-4 ON/OFF P1-5 ON/OFF_RET Minimun 22 AWG. Less than 0.7 V = ON; open = OFF. <100 mA SKY899 Installation Manual SIGNAL CHARACTERISTICS Operational Mode Output (optional) Operational mode output can drive a lamp annunciating when the system is in operational mode. Output is switched to ground when system is in operation mode. The lamp requires a separate dc source (constant or dimming circuit). If lamp voltage is an ac source then an isolation relay must be used. CONNECTION CABLE VOLTAGE CURRENT 18-32 V dc. A 5 A circuit breaker is required (see paragraph 2.16). This interface allows a DC analog radio altimeter to be used to monitor own aircraft height above ground and includes input for radio altitude valid signal. Some analog radio altimeters utilize a discrete valid/invalid signal line to indicate radio altitude validity, while others set the analog data input line to a high out-of-range value for invalid altitude conditions. If a discrete flag signal is not available leave RADIOALT_FLG (P1-14) unconnected. im Radio Altimeter (Analog) in CABLE VOLTAGE Pr el CONNECTION SKYWATCH/STORMSCOPE (SW1) Signal Name Connector-Pin P8-A +28V P8-B +28V_RET Use twisted shielded pair cable (Beldon 83322, Alpha 2826/2, or equivalent). Terminate shield to airframe at sensor or power source. 18 to 32 V dc, 70 Watts (Maximum) ar CONNECTION Power Input (TRC) Signal Name Connector-Pin P1-31 OPER_MODE Minimum 22 AWG wire for lengths up to 30 ft. ON: 0 V dc or Ground OFF: Maximum +32 V dc or open Maximum current 300 mA. Connector-Pin P1-6 P1-7 P1-14 Signal Name RAD_ALT_IN_HI RAD_ALT_IN_LO RAD_ALT_FLG If a WX-1000 processor is installed, this signal (SW1 on the Interconnect wiring diagram, figure 2-3) switches the display between the WX-1000 and SKY899. Any general purpose SPST toggle switch can be used. CONNECTION CABLE VOLTAGE CURRENT Signal Name Connector-Pin P1-15 SMS P1-23 SMS_RET Minimum 22 AWG. CLOSED (< 0.7 V dc) = Stormscope display mode OPEN = SKYWATCH display mode. <100 mA A-7 Rev. A SKY899 Installation Manual SIGNAL CHARACTERISTICS Soft-keys Soft-key inputs from the WX-1000/SKY497 display and output to the WX-1000 processor (if installed). The pushbuttons on the front of the display are referred to as soft-keys (1), (2), (3), and (4). In every operating mode a label identifying the button function is displayed next to the button. When using an alternate display device refer to manufacturer instructions concerning these connections. Use of soft-key inputs will depend upon the alternate display capabilities. Connector-Pin P1-18 Signal Name P1-19 SFTKEY2_IN From Display P1-20 SFTKEY3_IN From Display P1-21 P1-38 P1-40 CABLE SFTKEY2_OUT To Processor SFTKEY3_OUT To Processor SFTKEY3_OUT To Processor See paragraph 2.6.7 Active: im VOLTAGE Inactive: Min: 0.0 V Max: 1.5 V Min: 3.5 V or Open (Internal 4.7 kΩ pull-up) Max: 5.0 V This signal line is to be connected to the squat switch to sense when the aircraft is on the ground (see paragraph 2.7.4). The state of the switch can be active low or active high in reference to aircraft ground. The switch status can be none, active low or active high, this is selected via service menu. Pr el Squat Switch Input (Weight-On-Wheels) SFTKEY1_OUT To Processor in P1-39 SFTKEY4_IN From Display ar P1-37 SFTKEY1_IN From Display CONNECTION If a squat switch is not installed on the aircraft, it is recommended to install a switch, which will enhance system operation. CONNECTION CABLE VOLTAGE CURRENT A-8 Rev. A Signal Name Connector-Pin P1-24 SQUAT Minimum 22 AWG wire for lengths up to 30 ft. None: Open or no connection Active Low: (ref. to aircraft ground) Valid: -5 V dc to +2.5 V dc Invalid: +9 V dc to +32 V dc Active High: (ref. to aircraft ground) Valid: +9 V dc to +32 V dc Invalid: -5 V dc to +2.5 V dc <5 mA sourced. SKY899 Installation Manual SIGNAL CHARACTERISTICS Suppression Bus I/O The SKY899 outputs a 100 µs (± 5 µs) suppression pulse on the aircraft suppression bus (see paragraph 2.20). In addition, the SKY899 receives suppression signals from all other devices on the suppression bus (e.g., transponder, DME). (Reference ARINC 735-2 and DO-197A.) CAUTION The aircraft transponder must have suppression circuitry to ensure that SKYWATCH HP does not paint itself as a target (e.g., TA). Signal Name Connector-Pin P1-93 SUPBUS CABLE Any size low capacitance shielded cable may be used. VOLTAGE 18 - 70 V dc input, greater than 20 V dc output. CURRENT 0.3 A output max. FREQUENCY ATCRBS - 100 µs ± 5 µs output Mode S - 70 µs ±1 µs output DC-1 MHz input. SOURCE Z 2 kΩ LOAD Z 10.5 kΩ MAX CAPACITANCE <50 pF ar CONNECTION im in System Configuration Module The configuration module (i.e., personality plug) is used to store aircraft installation dependent information. Aircraft specific information is selected via the service menu, typically during system setup. Once the setup settings have been saved the system configuration will stay with the aircraft wiring allowing the TRC to be replaced or exchanged without having to re-configure the TRC. When powered up the configuration information is sent to the TRC via the bi-directional serial data bus (SDA). The configuration module is located inside backshell of P1 connector. See paragraph 2.21. Pr el CONNECTION CABLE VOLTAGE Vertical Sync Signal Name Connector-Pin P1-2 3.3V P1-92 PLUG_GND P1-99 SDA P1-100 SCL Minimum 22 AWG wire for lengths up to 30 ft. ??????????????? Balanced vertical sync from the WX-1000 Processor (if installed) and output to the display. Signal levels as specified in RS-422. CONNECTION CABLE VOLTAGE FREQUENCY SOURCE Z Signal Name Connector-Pin P1-30 VSYNC_IN+ From Processor P1-41 VSYNC_IN- From Processor P1-13 VSYNC_OUT+ To Display P1-22 VSYNC_OUT- To Display See paragraph 2.6.7 0-5 V dc 60 Hz 1 kΩ A-9 Rev. A SKY899 Installation Manual SIGNAL CHARACTERISTICS Video Output Balanced video from the WX-1000 Processor (if installed) and output to the display. Signal levels as specified in RS-422 specification. Signal Name Connector-Pin P1-35 VIDEO_IN+ From Processor P1-36 VIDEO_IN- From Processor P1-16 VIDEO_OUT+ To Display P1-17 VIDEO_OUT- To Display CABLE See paragraph 2.6.7 VOLTAGE 0-5 V dc CURRENT <100 mA FREQUENCY <15 MHz LOAD Z 1 kΩ Power supply to WX-1000/SKY497 display. +15/-15 V dc from the Display WX-1000 Processor (if installed) and output to the display. ar WX-1000/SKY497 Display Power CONNECTION Future Options im CABLE VOLTAGE CURRENT The following connections are reserved for future use. THESE PINS MUST REMAIN UNCONNECTED. Pr el CONNECTION A-10 Rev. A Signal Name Connector-Pin P1-25 DPWR+15_IN From Proc. P1-26 DPWR-15_IN From Proc. P1-27 DSPLY_GND_IN From Proc. P1-8 DPWR+15_OUT To Display P1-9 DPWR-15_OUT To Display P1-10 DSPLY_GND_OUT To Display See paragraph 2.6.7 +15/-15 V dc 0.7 A input max. in CONNECTION Connector-Pin Signal Name P1-1 +5 V P1-3 -15 V P1-32 DI02 P1-77 RS422_TXA P1-78 RS422_TXB P1-79 RS422_RXA P1-80 RS422_RXB P1-86 RS232_TX2 P1-87 RS232_RX2 P1-88 RX232_GND2 SKY899 Installation Manual PIN INSERT VIEW 56 ALT_A1 ar 25 35 VIDEO_IN+ DPWR+15_IN 16 +5V DPWR-15_OUT 3.3V 86 HEADING_Y ALT_C2 RS232_TX2 37 58 SFTKEY1_OUT 27 ALT_C4 59 SFTKEY2_OUT SFTKEY3_OUT ASU_SEL 95 ASU_MODE RS232_GND2 80 RS422_RXB ALT_B2 50 RS232_RX2 88 ALT_D2 60 29 94 RS422_RXA 70 HEADING_H 39 87 79 ALT_B1 49 HSYNC_IN+ SFTKEY2_IN RS422_TXB 69 HEADING_Z 28 19 78 ALT_A4 48 38 SFTKEY1_IN 11 RS422_TXA DPWR-15_IN DSPLY_GND_IN DSPLY_GND_OUT ALT_A2 68 18 10 77 47 VIDEO_OUT- 57 VIDEO_IN- 17 67 ALT_C1 26 in DPWR+15_OUT 46 HEADING_X 36 VIDEO_OUT+ im P1-51 P1-52 P1-53 P1-54 P1-55 P1-56 P1-57 P1-58 P1-59 P1-60 P1-61 P1-62 P1-63 P1-64 P1-65 P1-66 P1-67 P1-68 P1-69 P1-70 P1-71 P1-72 P1-73 P1-74 P1-75 P1-76 P1-77 P1-78 P1-79 P1-80 P1-81 P1-82 P1-83 P1-84 P1-85 P1-86 P1-87 P1-88 P1-89 P1-90 P1-91 P1-92 P1-93 P1-94 P1-95 P1-96 P1-97 P1-98 P1-99 P1-100 el PINS HEADING_FLG A429TX3_A A429TX3_B A429RX1_A A429RX1_B ALT_A1 ALT_A2 ALT_A4 ALT_B1 ALT_B2 ALT_B4 A429RX2_A A429RX2_B A429RX3_A A429RX3_B LP1OUT ALT_C1 ALT_C2 ALT_C4 ALT_D2 ALT_D4 ALT_COMN A429RX4_A A429RX4_B A429RX5_A A429RX5_B RS422_TXA RS422_TXB RS422_RXA RS422_RXB A429RX8_A A429RX8_B A429RX7_A A429RX7_B LP2OUT RS232_TX2 RS232_RX2 RS232_GND2 AUDIO_H AUDIO_L AUDIO_C PLUG_GND SUPBUS ASU_SEL ASU_MODE ASU_SEL_ACK ASU_MOD_ACK ASU_GND SDA SCL 96 89 71 -15V ASU_SEL_ACK HSYNC_OUT+ Pr SIGNAL NAME ALT_D4 HEADING_C HSYNC_IN- AUDIO_H 20 40 61 81 97 ON/OFF SFTKEY3_IN SFTKEY4_OUT ALT_B4 A429RX8_A ASU_MOD_ACK 12 30 51 72 90 HSYNC_OUT- VSYNC_IN+ HEADING_FLG ALT_COMN AUDIO_L 98 ON/OFF_RET 21 41 SFTKEY4_IN ta PINS P1-01 P1-02 P1-03 P1-04 P1-05 P1-06 P1-07 P1-08 P1-09 P1-10 P1-11 P1-12 P1-13 P1-14 P1-15 P1-16 P1-17 P1-18 P1-19 P1-20 P1-21 P1-22 P1-23 P1-24 P1-25 P1-26 P1-27 P1-28 P1-29 P1-30 P1-31 P1-32 P1-33 P1-34 P1-35 P1-36 P1-37 P1-38 P1-39 P1-40 P1-41 P1-42 P1-43 P1-44 P1-45 P1-46 P1-47 P1-48 P1-49 P1-50 ca +5V 3.3V -15V ON/OFF ON/OFF_RET RAD_ALT_IN_HI RAD_ALT_IN_LO DPWR+15_OUT DPWR-15_OUT DSPLY_GND_OUT HSYNC_OUT+ HSYNC_OUTVSYNC_OUT+ RAD_ALT_FLG SMS VIDEO_OUT+ VIDEO_OUTSFTKEY1_IN SFTKEY2_IN SFTKEY3_IN SFTKEY4_IN VSYNC_OUTSMS_RET SQUAT DPWR+15_IN DPWR-15_IN DSPLY_GND_IN HSYNC_IN+ HSYNC_INVSYNC_IN+ OPER_MODE DI02 GEAR GPWS VIDEO_IN+ VIDEO_INSFTKEY1_OUT SFTKEY2_OUT SFTKEY3_OUT SFTKEY4_OUT VSYNC_INA429TX1_A A429TX1_B A429TX2_A A429TX2_B HEADING_X HEADING_Y HEADING_Z HEADING_H HEADING_C So SIGNAL NAME RAD_ALT_IN_HI RAD_ALT_IN_LO 13 VSYNC_OUT+ 62 A429RX8_B A429RX2_A VSYNC_IN- 31 52 73 91 99 OPER_MODE A429TX3_A A429RX4_A AUDIO_C SDA 92 100 PLUG_GND SCL 22 42 63 83 VSYNC_OUT- A429TX1_A A429RX2_B A429RX7_A 32 14 RAD_ALT_FLG 53 DI02 23 SUPBUS 85 A429RX3_B 55 GPWS 93 A429RX5_A 65 A429TX2_A 34 A429RX7_B 75 A429RX1_A 44 SQUAT 84 A429RX3_A 54 GEAR 24 A429RX4_B 64 A429TX1_B 33 SMS 74 A429TX3_B 43 SMS_RET 15 ASU_GND 82 LP2OUT 76 A429RX1_B A429RX5_B 45 66 A429TX2_B LP1OUT Figure A-1. P1 Connector Pin Identifiers A-11 (page A-12 blank) Rev. A SKY899 Installation Manual A.3 ARINC-429 LABELS The various interface equipment and their ARINC-429 labels (accepted and transmitted) are listed in tables A-3 and A-4. Any input labels not listed in table A-3 are rejected and not used by the SKY899. Table A-3. ARINC-429 Input Labels (Rx) Equipment Data Air Data Computer Altitude GPS (GAMA) 203* Baro Corrected Altitude #1 204 Altitude Rate 212 Altitude Rate 232 General Aviation Equipment ID 371 Equipment ID 377 Greenwich Mean Time (BCD) 150 Date (BCD) 260 ar 311* Ground Speed (BNR) 312* in 310* Present Position Longitude (BNR) Track Angle (BNR) 313* Specific Equipment ID (DSC) 371 Equipment Hex ID Code (DSC) 377 GPS Altitude 076 HDOP 101 im Either Label 314 or 320 is required for input to be used. Radio Altimeter 261* Present Position Latitude (BNR) VDOP 102 GPS Track Angle 103* GPS Latitude 110* Pr el Attitude & Heading Reference System 125 Greenwich Mean Time (BNR) GPS Discrete Word 1 (DSC) GPS (GNSS) Label GPS Longitude 111* GPS Ground Speed 112* GPS Latitude Fine 120 GPS Longitude Fine 121 UTC 125 Horizontal Integrity Limit (HIL) 130* UTC 150 Vertical Velocity 165 Date 260 Equipment ID 377 Magnetic Heading 014 True Heading 314* Magnetic Heading 320* General Aviation Equipment ID 371 Equipment ID 377 Radio Height Equipment ID 164* 377 * Required for ARINC-429 Input to be used. A-13 Rev. A SKY899 Installation Manual Table A-4. ARINC-429 Output Labels (Tx) Equipment Data Label External Display DITS Control 013 ARINC-735 TCAS I Formatted Traffic Data Altitude Select Limits 015 DITS Control 016 Intruder Range 130 Intruder Altitude 131 132 Own A/C Altitude. 203 Vertical RA 270 Transponder Control 274 Own A/C Heading. Fault Summary ar (RTS) Request To Send Intruder Bearing 350 357 357 GA Equipment Ident 371 Equipment Identifier 377 im in (ETX) End of Transmission Pr el A-14 Rev. A 320 SKY899 Installation Manual APPENDIX B ENVIRONMENTAL QUALIFICATION FORM This appendix includes the environmental qualification forms required for the SKY899 system. Forms included are for the TRC899, NY156 & NY164 antennas, and WX-1000/SKY497 display. B.1 TRC899 ENVIRONMENTAL QUALIFICATION FORM ® NOMENCLATURE: SKYWATCH HP MODEL: TRC899 PART NO.: 805-11900-001 TSO NO.: TSO-C118 and TSO-C147 APPLICABLE SPEC. NO.: RTCA/DO-197A Revision & Change Number of DO-160: DO-160D SECTION/ PARAGRAPH in CONDITION Temperature and Altitude 4.0 4.5.1 im Low Temperature Ground Survival High Temp. ar MANUFACTURER: BFGoodrich Avionics Systems, Inc. ADDRESS: 5353 52nd Street SE, Grand Rapids, MI 49512 (616) 949-6600 TEST DESCRIPTION Tested to Category F2 -55° Celsius 4.5.2 +85° Celsius 4.5.3 +70° Celsius 4.5.4 Category X-No test performed 4.6.1 55,000 ft. MSL 4.6.2 4.6.3 Not Applicable Not Applicable Temperature Variation 5.0 Tested to Category B Humidity 6.0 Tested to Category A Operational Shock and Crash Safety 7.0 Vibration 8.0 Tested to Category B Category S, aircraft zone 2 using vibration test curves B and M for fixed wings; Category U, aircraft zone 1 using test curves F and F1 for helicopter without shock mounts Operating High Temp. Loss of Cooling Altitude Pr el Decompression Overpressure Explosion Proofness 9.0 Category X - No test performed Waterproofness 10.0 Category X - No test performed Fluids Susceptibility 11.0 Category X - No test performed Sand and Dust 12.0 Category X - No test performed Fungus Resistance 13.0 Category X - No test performed Salt Spray 14.0 Category X - No test performed B-1 Rev. A SKY899 Installation Manual TRC899 Environmental Qualification Form (Continued) TEST DESCRIPTION Magnetic Effect 15.0 Tested to Class Z Power Input 16.0 Tested to Category B Voltage Spike 17.0 Tested to Category A Audio Frequency Susceptibility 18.0 Tested to Category B Induced Signal Susceptibility 19.0 Tested to Category A Radio Frequency Susceptibility 20.0 Tested to Category U for conducted and category U for radiated. Category X for pulse test - No test performed Radio Frequency Emission 21.0 Tested to Category L Lightning Induced Transient Susceptibility 22.0 Category XXXX- No test performed Lightning Direct Effects 23.0 Icing 24.0 Electrostatic Discharge 25.0 ar SECTION/ PARAGRAPH Category X - No test performed in Category X - No test performed im CONDITION Tested to Category A B.2 NY156 & NY164 ANTENNA ENVIRONMENTAL QUALIFICATION FORM ® MANUFACTURER: ADDRESS: Pr el NOMENCLATURE: SKYWATCH MODEL: NY156 & NY164 PART NO.: 805-10003-001 & 805-10890-001 APPLICABLE SPEC. NO.: RTCA/DO-160C TSO NO.: TSO-C118 Sensor Systems, Inc. 8929 Fullbright Ave., Chatsworth, CA 91311 USA (818) 341-5366 Revision & Change Number of DO-160: DO-160C CONDITIONS SECTION TEST DESCRIPTION 4.0 Equipment tested to Categories F2. 4.5.1 4.5.2 & 4.5.3 4.5.4 -55 Degrees Celsius +70 Degrees Celsius - Not Applicable - 4.6.1 4.6.2 4.6.3 55,000 Feet - Not Applicable - Not Applicable - Temperature Variation 5.0 Equipment tested to Category A. Humidity 6.0 Equipment tested to Category C. Temperature and Altitude Low Temperature High Temperature In-Flight Loss of Cooling Altitude Decompression Overpressure B-2 Rev. A SKY899 Installation Manual NY156 & NY164 Environmental Qualification Form (Continued) SECTION TEST DESCRIPTION Operational Shock and Crash Safety 7.0 Operation and Crash Vibration 8.0 Equipment tested to Category C, L, and M. Explosion 9.0 Category X - No test performed. Waterproofness 10.0 Equipment tested to Category S. Fluids Susceptibility 11.0 Equipment tested to Category F. Sand and Dust 12.0 Equipment tested to Category D. Fungus 13.0 Equipment tested to Category F. Salt Spray 14.0 Equipment tested to Category S. Magnetic Effect 15.0 Category X - No test performed. Power Input 16.0 Category X - No test performed. Voltage Spike 17.0 Audio Frequency Susceptibility 18.0 Induced Signal Susceptibility 19.0 Radio Frequency Susceptibility 20.0 Category X - No test performed. Radio Frequency Emission 21.0 Category X - No test performed. ar Category X - No test performed. Category X - No test performed. in im Lightning Induced Transient Susceptibility Lightning Direct Effects Category X - No test performed. 22.0 Equipment tested to Category L. 23.0 Equipment tested to Category 2A. 24.0 Category X - No test performed. Pr el Icing Other Tests CONDITIONS No test required B.3 WX-1000/SKY497 DISPLAY ENVIRONMENTAL QUALIFICATION FORM NOMENCLATURE: Stormscope MODEL: WX-1000 PART NO.: 78-8060-5900-8 ® TSO NO.: TSO-C113 APPLICABLE SPEC. NO.: RTCA/DO-160C MANUFACTURER: BFGoodrich Avionics Systems, Inc. ADDRESS: 5353 52nd Street SE, Grand Rapids, MI 49512 (616) 949-6600 B-3 Rev. A SKY899 Installation Manual Revision & Change Number of DO-160: DO-160C SECTION/ PARAGRAPH TEST DESCRIPTION Temperature and Altitude Operating Low Temperature Operating High Temperature Short-Time Operating High Temp. Loss of Cooling Ground Survival Low Temp. Ground Survival High Temp. 4.0 4.5.1 4.5.3 4.5.2 4.5.4 4.5.1 4.5.2 Tested to Category F1-20° Celsius +55° Celsius +70° Celsius -Not Applicable-55° Celsius +85° Celsius 4.6.1 55,000 Feet MSL Temperature Variation 5.0 Tested to Category C Humidity 6.0 Tested to Category A Operational Shock and Crash Safety Operational Shock Crash Safety 7.0 7.2 7.3 Vibration 8.0 Explosion Proofness 9.0 Waterproofness 10.0 Fluids Susceptibility 11.0 Sand and Dust Fungus Resistance ar in Tested to Categories [NBM] Instrument Panel Mount Without Vibration Isolators Category X - No test required Category X - No test required Category X - No test required 12.0 Category X - No test required 13.0 Category X - No test required 14.0 Category X - No test required Pr el Salt Spray Magnetic Effect 6 g's Peak 15 g's all axes im Altitude CONDITION 15.0 Tested to Class Z 16.0 Category X - No test required 17.0 Category X - No test required Audio Frequency Susceptibility 18.0 Category X - No test required Induced Signal Susceptibility 19.0 Tested to Category Z Radio Frequency Susceptibility 20.0 Tested to Category U Radio Frequency Emission 21.0 Tested to Category A Lightning Induced Transient Susceptibility 22.0 Category X - No test required Lightning Direct Effects 23.0 Category X - No test required Icing 24.0 Category X - No test required Power Input Voltage Spike Other Tests X-Ray Radiation Other Tests U.V. Radiation Other Tests Thermal Shock B-4 Rev. A SKY899 Installation Manual APPENDIX C INSTALLATION CHECKOUT USING THE TCAS-201 RAMP TEST SET C.1 INTRODUCTION This section contains instructions for using the TCAS-201 Ramp Test Set (with TCAS I firmware) to do ® post-installation checkout of the BFG Avionics Systems SKYWATCH HP SKY899. This procedure provides test setup data for the TCAS-201 ramp test set, refer to manufacturers instructions for detailed setup, operation and maintenance information. NOTES 1. This procedure assumes familiarity with the set up and operation of the TCAS201 ramp test set. ar 2. All test equipment used in completing these tests shall be calibrated in accordance with the manufacturer's recommendations. in 3. When the SKY899 is interfaced to an alternate display, reference Appendix F while performing this checkout procedure. This procedure will validate the installation and return to service of the BFGoodrich Avionics Systems SKY899. Pr el im C.2 CONTROLS All operating controls are located on the front of the WX-1000/SKY497 display. Figure C-1 shows the locations of the controls. Complete operating instructions for the SKY899 are provided in the SKY899 Pilot's Guide supplied with each system. Figure C-1. Controls OFF/BRT Switch 1, 2, 3, & 4 Pushbuttons Power is applied by rotating the knob clockwise past the detent. Continued clockwise rotation increases display brightness. Also referred to as soft-keys (1), (2), (3), and (4). In every operating mode a label identifying the button function will be displayed next to the button. C-1 Rev. A SKY899 Installation Manual C.3 CHECKOUT PROCEDURE If the indications given in the following steps, except for the ramp test set, are not obtained, refer to the troubleshooting procedures in Chapter 4. If indications given for the ramp test set are not obtained, refer to the manual supplied with that equipment. 1. Enter and store the setup information identified in table C-1 into the TCAS-201 Ramp Test Set. Table C-1. IFR Systems TCAS-201 Ramp Test Set Setup Data SCREEN INTRUDER TYPE: SCENARIO TEST RANGE: RANGE RATE: ALT: ALT: RATE: REPLY TEST RANGE: ALTITUDE %REPLY: im RANGE MAX: RANGE MIN: ALT MAX: ALT MIN: 35 NM (was 20 NM for Sky497) 0 NM 60,000 ft 0 ft 5.0 NM +200 kt 51,000 ft 0 FPM 5.0 NM 50,500 ft 100 % Make sure the aircraft's transponder is in the STBY mode and the DME is turned OFF. At the aircraft's instruments, verify all compass/HSI flags are valid. Pr el 2. SETUP #2 in ALT REPORTING: STORE RECALL GAIN_1030 LOSS ATCRBS Distance (ft.) from aircraft Vertical height (ft.) difference between test antenna and SKY899 antenna ON 9.4 dB 1.3 dB UUT DIST: HORIZ = UUT DIST; VERT = ar SETUP #1 STORAGE NUMBER 1 NOTE After power up, it may take a couple of minutes for the altitude encoder to return a valid altitude to the transponder and SKY899. 3. Turn SKY899 ON. The display will show a start-up screen similar to one shown in figure C-2. After start-up screen appears, rotate the OFF/BRT switch. Verify that clockwise rotation increases display brightness. C-2 Rev. A SKY899 Installation Manual Figure C-2. Start-up Screen After approximately thirty seconds the display will show the STANDBY screen (see figure C-3). in ar NOTE If the TRC has not been calibrated to the directional antenna the display may show a “SKY899 FAILED” message. Calibration will be done during system setup. im BRT OFF SKY899 Pr el Standby MSG OPR TEST Figure C-3. Standby Screen 4. Perform System Setup in paragraph 3.3.1. (If System Setup has already been done, proceed to next step.) 5. Turn SKY899 OFF and then enter the Service Menu (see paragraph 4.4) by holding the left two buttons (soft-keys 1 and 2) depressed as the system is turned ON. 6. From the Service Menu, calibrate the TRC to the directional antenna (see paragraph 4.4.3). If calibration was just done during System Setup (see paragraph 3.3.1) proceed to next step. 7. Return to the Service Menu and select Information. 8. From the Information menu, select Data Monitor. The Data Monitors menu will appear. 9. Select each of the data monitors and verify the sensor information is correct (see paragraph 4.4.2.3): a. Change the status of the landing gear, squat switch, altitude, and heading sensors. Verify data monitors show the correct input changes (i.e., sensing of these signals). C-3 Rev. A SKY899 Installation Manual b. If the information is not correct, the sensor has failed to communicate with the TRC. Check operation of the sensor and connections between the TRC and sensor. c. Select exit until you return to the Service Menu. 10. Do SKY899 self test (paragraph 3.4). 11. From the Service Menu, select Ground Test (see paragraph 4.4.4). 12. From Ground Test menu, select Perform Ground Test. 13. Verify operation of range function. Soft-key (3) is labeled to indicate the current range. Press soft-key (3) to toggle the display range between 2, 6 and 15 nm. 14. Select the 6 nautical mile range. 15. Verify that the system toggles through the altitude display modes. Soft-key (2) is labeled to indicate the current mode. Press Soft-key (2) to select normal (NRM), below (BLW), and above (ABV). 16. Select the NRM (normal) mode. ar 17. Position the aircraft with the nose aligned on any 90 degree heading. Avoid areas within 250 ft of obstructions (e.g., hangers, large aircraft, control towers, etc.) where there is a potential for multipath problems. Locate and mark test points, every 30 degrees (i.e., at 000, 030, 060, 090, 120, 150, 180, 210, 240, 270, 300, and 330 degrees with respect to the SKY899 directional antenna). Mark these points at the same distance, approximately 100 ft, from the aircraft. in 18. Do the following static tests: Connect the TCAS-201 Flat Antenna (facing towards the test aircraft) to the antenna connector. b. At the TCAS-201 test set, press the REPLY TEST key. c. Initiate the REPLY TEST by pressing the ANTENNA push button switch or the RUN/STOP key. im a. NOTE The TCAS-201 display will indicate “NO WHISPER-SHOUT SEQUENCE”. Verify that the SKY899 display shows an other traffic symbol (open diamond) at the 12 O'clock position (±30 degrees), approximately 5.0 nm, in level flight, and at an altitude of 500 ft above own aircraft (i.e., "+05"). NOTES Pr el d. 1. If the display reflects a gross error in target bearing, check the directional antenna cables at TRC connectors J9 (sum port) and J11 (difference port). They may be reversed. A further indication of this condition would be a target that moved in a counter-clockwise direction when the test set is moved in a clockwise direction. 2. Multiple targets or a faulty bearing may result from multipath distortion (see step 2). 3. During these tests, the SKY899 may detect and display other active targets. e. Repeat a, b, c, and d from each of the test points (see step 2). 19. Do the following dynamic test. a. Position the ramp test set on the test point directly in front of the test aircraft (i.e., approximately 100 ft in front of the aircraft, see step 2). b. Connect the TCAS-201 Flat Antenna (facing towards the test aircraft) to the antenna connector. c. At the TCAS-201 test set, press the SCEN key. d. Initiate the SCENARIO TEST by pressing the ANTENNA push button switch or the RUN/STOP key. C-4 Rev. A SKY899 Installation Manual e. Verify that the display shows an "other traffic" symbol (open diamond) at the 12 o'clock position (±30 degrees) approximately 5.0 nm and in level flight. The traffic symbol should be at an altitude of 500 ft above own aircraft (i.e., "+05") and moving towards your aircraft. f. When the target approaches closer than approximately 1 nm from own aircraft, verify that the symbol changes from an other traffic symbol (open diamond) to a traffic advisory (solid circle). NOTE The voice message, “TRAFFIC, TRAFFIC,” will be enunciated over the cockpit audio system. g. The target, when it reaches 0.0 nm, will reverse direction and move outbound on the same heading. NOTE Pr el im in ar 20. This completes the post installation checkout procedure. The target may momentarily drop from the display and then reappear as an other traffic symbol (open diamond). C-5 Rev. A in ar SKY899 Installation Manual Pr el im This page intentionally left blank. C-6 Rev. A SKY899 Installation Manual APPENDIX D INSTALLATION CHECKOUT USING THE TIC T-49C FLIGHTLINE TESTER D.1 INTRODUCTION This section contains instructions for using the TIC T-49C Flightline Tester to do post-installation ® checkout of the BFG Avionics Systems SKYWATCH HP SKY899. Detailed setup, operation and maintenance information for the T-49C Flightline Tester is provided in the T-49C Operating and Maintenance Instruction Manual. NOTES 1. This procedure assumes familiarity with the set up and operation of the T-49C Flightline Tester. ar 2. All test equipment used in completing these tests shall be calibrated in accordance with the manufacturer's recommendations. 3. When the SKY899 is interfaced to an alternate display, reference Appendix F while performing this checkout procedure. in This procedure will validate the installation and return to service of the BFGoodrich Avionics Systems SKY899. Pr el im D.2 CONTROLS All operating controls are located on the front of the WX-1000/SKY497 display. Figure D-1 shows the locations of the controls. Complete operating instructions for the SKY899 are provided in the SKY899 Pilot's Guide supplied with each system. Figure D-1. Controls OFF/BRT Switch 1, 2, 3, & 4 Pushbuttons Power is applied by rotating the knob clockwise past the detent. Continued clockwise rotation increases display brightness. Also referred to as soft-keys (1), (2), (3), and (4). In every operating mode a label identifying the button function will be displayed next to the button. D-1 Rev. A SKY899 Installation Manual D.3 CHECKOUT PROCEDURE The T-49C Flightline Tester simulates a ground based secondary surveillance radar (SSR) when the TCAS INTRUDER selector switch is in the ATCRBS/Mode-S XPDR TEST position. When the T-49C intruder type switch is set to ATCRBS, the unit responds to ATCRBS Mode C interrogations. A varying delay time, controlled from the microprocessor, delays the replies returned to the SKY899 from as far as 14 nautical miles and as close as a few hundred feet. The apparent distance from the simulated intruder to the SKY899 system under test decreases as if the intruder was converging on the aircraft under test. The test set determines the altitude of the aircraft under test by interrogating the transponder using an ATCRBS interrogation. By adding or subtracting the desired differential altitude, as selected by the front-panel scenario switch, the initial altitude of the scenario is controlled by the microprocessor. This altitude, like the distance, is varied so that the simulated intruder converges on the aircraft’s position. 1. Make sure the aircraft's transponder is in the STBY mode and the DME is turned OFF. At the aircraft's instruments, verify all compass/HSI flags are valid. NOTE Turn SKY899 ON. The display will show a start-up screen similar to one shown in figure D-2. After start-up screen appears, rotate the OFF/BRT switch. Verify that clockwise rotation increases display brightness. Pr el im in 2. ar After power up, it may take a couple of minutes for the altitude encoder to return a valid altitude to the transponder and SKY899. Figure D-2. Start-up Screen After approximately thirty seconds the display will show the STANDBY screen (see figure D-3). NOTE If the TRC has not been calibrated to the directional antenna the display may show a “SKY899 FAILED” message. Calibration will be done during system setup. D-2 Rev. A SKY899 Installation Manual BRT OFF SKY899 Standby MSG OPR TEST Figure D-3. Standby Screen Perform System Setup in paragraph 3.3.1. (If System Setup has already been done, proceed to next step.) 4. Turn SKY899 OFF and then enter the Service Menu (see paragraph 4.4) by holding the left two buttons (soft-keys 1 and 2) depressed as the system is turned ON. 5. From the Service Menu, calibrate the TRC to the directional antenna (see paragraph 4.4.3). If calibration was just done during System Setup (see paragraph 3.3.1) proceed to next step. 6. Return to the Service Menu and select Information. 7. From the Information menu, select Data Monitor. The Data Monitors menu will appear. 8. Select each of the data monitors and verify the sensor information is correct (see paragraph 4.4.2.3): in im a. Change the status of the landing gear, squat switch, altitude, and heading sensors. Verify data monitors show the correct input changes (i.e., sensing of these signals). b. If the information is not correct, the sensor has failed to communicate with the TRC. Check operation of the sensor and connections between the TRC and sensor. c. Select exit until you return to the Service Menu. Pr el 9. ar 3. Exit the Service Menu. Verify that the display shows the standby screen (figure D-3) and then press Soft-key (4), labeled OPR. 10. Verify operation of range function. Soft-key (3) is labeled to indicate the current range. Press Soft-key (3) to toggle the display range between 2, 6 and 15 nm. 11. Select the 6 nautical mile range. 12. Verify that the system toggles through the altitude display modes. Soft-key (2) is labeled to indicate the current mode. Press Soft-key (2) to select normal (NRM), below (BLW), and above (ABV). 13. Select the NRM (normal) mode. 14. If installed, turn the radio altimeter OFF. 15. Do the SKY899 self test (paragraph 3.4). 16. Position the aircraft with the nose aligned on any 90 degree heading. Avoid areas within 250 ft of obstructions (e.g., hangers, large aircraft, control towers, etc.) where there is a potential for multipath problems. Locate and mark test points at 30 degree intervals (i.e., 000, 030, 060, 090, 120, 150, 180, 210, 240, 270, 300, and 330 degrees) with respect to the SKY899 directional antenna. Mark these points at the same distance, between 100 and 150 ft, from the aircraft. D-3 Rev. A SKY899 Installation Manual 17. Change the aircraft's transponder from STBY mode to the ON position. 18. Position the T-49C Flightline Tester on one of the test points identified in previous step. CAUTION The Flightline Tester is not weatherproof when the lid is open. Do not setup or operate the Flightline Tester in conditions of rain, sleet, etc. 19. Setup and verify operation of the T-49C Flightline Tester with the HI/LOW power switch in the HI position and then: Set the TCAS INTRUDER selector switch of the T-49C to the ATCRBS/Mode-S XPDR TEST position and press TEST and the INTERROGATE. This will store the aircraft’s barometric altitude in the T-49C. NOTE a. The T49-C will display the pressure altitude of the aircraft under test. Verify that the SKY899 display shows the standby screen (figure D-3) and then press soft-key (4), labeled OPR. Select NRM mode and 6 nm range by pressing appropriate soft-keys. c. Set the TCAS INTRUDER selector switch to the ATCRBS position and the SCENARIO selector switch to the 0 altitude offset position. Press INTERROGATE, and when the range on the display decreases to 5 NM, press TEST. This will freeze the scenario and represent a stationary intruder aircraft 5 NM away at the same altitude as the UUT aircraft. Verify that the SKY899 displays, in the direction (±30 degrees) of the T-49C, a symbol for other traffic (i.e., open diamond) at 5 NM. Target will be displayed in level flight at own aircraft altitude (i.e., “00” displayed above the traffic symbol). im in ar b. NOTES 2) 3) 4) d. If the display reflects a gross error in target bearing, check the SKY899 directional antenna cables at TRC connectors J9 (sum port) and J11 (difference port). They may be reversed. A further indication of this condition would be a target that moved in a counter-clockwise direction when the T-49C is moved in a clockwise direction. Multiple targets or a faulty bearing may result from multipath distortion (see step 1). During these tests, the SKY899 may detect and display other active targets. To obtain a better line of sight, it may be necessary to elevate the antenna. Pr el 1) Move the T-49C to each test point and verify that the display shows the corresponding bearing displacement. NOTE It is necessary to wait a few seconds after moving to let the test target stabilize in position. 20. This completes testing with the T-49C, reattach top lid of the T-49C. 21. If installed, TURN ON the radio altimeter. 22. This completes the post installation checkout procedure. D-4 Rev. A SKY899 Installation Manual APPENDIX E Using the Terminal Device (e.g., Laptop Computer) 19200 None ar Baud Rate: Parity: Data Bits: Stop Bits: A terminal device can be used as an aid in installing, testing and troubleshooting the SKY899. The terminal device must be connected to the RS-232 serial data TEST port (J7) located on the front of the TRC899. TRC connector J7 is a female DB9 receptacle. A standard serial cable that has RXD (pin 2), TXD (pin 3), GND (pin 5), CTS (pin 7), and RTS (pin 8) can be used. Any computer, with RS-232 terminal emulation software (e.g., Procomm, HyperTerminal, etc.), may be used as the terminal device. To communicate with the TRC, the RS-232 terminal device must be setup as follows, with no hardware or software handshaking (flow control) being used. im in The SKY899 includes the following commands to help with installation, testing, and troubleshooting. These commands are listed in the order they appear when the help menu is accessed and can be typed in upper case or lower case letters. Ctrl+R repeats the last command. Help screens have been created for your convenience, to access the command help screen type help or ? at the prompt. To access the help or about screen for each command, type the command followed by --help, -? or --about. Typing --help will give the command with a brief description, typing -? will give you the commands only. NOTE Commands ? or Help Pr el To access the service menu type menu. Terminal device Service Menu is identical to the one described in Chapter 4, except for a prefix. Type prefix to select a command (i.e., 1 , 2 , x ). When using service menu, system will not perform display commands (e.g., OPR, STB, MSG, or range). Descriptions The ? or help command displays a list of available commands. ? or Help: // del echo ident time Displays the following list attrib delay edit menu type baud dir hello ren ver copy dr help repeat For Information on any particular command, enter the command followed by --help (i.e., ident --help) or -? (abbreviated help screen). // The // (comment) command is used for editing files and is intended for factory use only. E-1 Rev. A SKY899 Installation Manual Commands Descriptions Attrib The attrib command allows you to view or change the attributes of a file. Attrib [filename]: Displays file and associated attributes. (If filename is left blank all files with attributes will be displayed.) Attrib [[filename][+ or - [attrib]]]: Change attributes, + turns it on, - turns it off. Attributes are: A - Archive attribute R - Read Only attribute S - System attribute H - Hidden attribute The baud command allows you to change the communication baud rate between the system and the terminal device. Changes baud rate. Rates are: - displays current baud rate. 115200 57600 38400 19200 9600 1200 in Baud [rate]: im Baud Abbreviated help screen. Help screen with descriptions. About screen information. ar Attrib -?: Attrib --help: Attrib --about: Copy Abbreviated help screen. Help screen with descriptions. About screen information. Pr el Baud -?: Baud --help: Baud --about: The copy command copies files on the compact flash, where filename1 is the source file to be copied into filename2, the destination file. Copy [[filename1] [filename2]]: Copy -?: Copy --help: Copy --about: Del E-2 Rev. A Makes duplicate copy of a file. Abbreviated help screen. Help screen with descriptions. About screen information. The del command allows you to delete a file (filename) located on the compact flash. Del [filename]: Deletes file from compact flash. Del -?: Del --help: Del --about: Abbreviated help screen. Help screen with descriptions. About screen information. SKY899 Installation Manual Commands Descriptions Delay The delay command allows you to create a delay (pause) between commands. Can be useful when creating script files, it is intended for factory use only. Delay [milliseconds]: Delays specified amount of time [milliseconds] before executing the next command. Abbreviated help screen. Help screen with descriptions. About screen information. Delay -?: Delay --help: Delay --about: The dir command will display all of the files located on the compact flash. If a compact flash is not present no information will appear. Dir: Lists all files located in a directory, if name is left blank it will show all directories and files located on the compact flash. Dir -?: Dir --help: Dir --about: Abbreviated help screen. Help screen with descriptions. About screen information. The dr command allows flight data to be recorded to a compact flash and is intended for factory use only. Records flight data. DR on opens new file and starts recording data. DR off stops recording data. If DR is on and DR on command is executed the old file is closed and a new file is opened and starts recording data. im DR [on/off]: in DR ar Dir Echo Edit Abbreviated help screen. Help screen with descriptions. About screen information. Pr el Attrib -?: Attrib --help: Attrib --about: The echo command allows you verify communication between system and terminal device. Sent text will be displayed on the laptop if proper communications has occurred. Echo [{text}]: Sends text through unit back to terminal device. Echo -?: Echo --help: Echo --about: Abbreviated help screen. Help screen with descriptions. About screen information. The edit command allows you to edit a text file on the compact flash. Intended for factory use only. Edit [filename]: Opens file to be edited. Edit -?: Edit --help: Edit --about: Abbreviated help screen. Help screen with descriptions. About screen information. E-3 Rev. A SKY899 Installation Manual Commands Descriptions Hello The hello command allows you to see the start-up screen on the laptop (i.e., company name, software version, etc.). Menu Hello -?: Hello --help: Hello --about: Abbreviated help screen. Help screen with descriptions. About screen information. The help command displays a list of available commands. Displays all available commands. Help [{cmdname}]: Help [all]: Help -?: Help --help: Help --about: Help screen with descriptions for that command. Displays all available commands. Abbreviated help screen. Help screen with descriptions. About screen information. ar Help: The ident command displays the vcs header information of all files. Intended for factory use only. Ident: Shows the vcs header information of all the files. Ident -?: Ident --help: Ident --about: Abbreviated help screen. Help screen with descriptions. About screen information. in Ident Displays start up screen. im Help Hello: The menu command allows the system to enter the service menu. There are no help screens are available, type the prefix character (1, 2, x, etc.) to perform that operation. Pr el Example: Service Menu 1 Setup 2 Information 3 Calibration 4 Ground Test x Exit Ren The ren command allows you to rename a file located on the compact flash. Ren [{oldfilename} {newfilename}]: Changes file name. Ren -?: Ren --help: Ren --about: E-4 Rev. A Abbreviated help screen. Help screen with descriptions. About screen information. SKY899 Installation Manual Commands Descriptions Repeat The repeat command allows you to repeat a command a specific number of times with a specified amount of time delay between the commands execution. Repeat [{number} {delay} {command}]: Repeats command. {number} - number of times to be repeated, zero will cause command to repeat until a key is pressed. {delay} number of milliseconds delay between commands. {command}- command to be repeated. The SKY899 does not have a real-time clock. The time command allows you to see the time received via the GPS nav information, if available. If not available, the time displayed will be the software creation date. ar Time Abbreviated help screen. Help screen with descriptions. About screen information. Repeat -?: Repeat --help: Repeat --about: The year is :2000 The month is :8 The hour is :13 The minute is :51 The second is :38 The millisecond is :3 im in Time: Time -?: Time --help: Time --about: Ver The type command allows you to see the contents of a file. Pr el Type Abbreviated help screen. Help screen with descriptions. About screen information. Type [{filename}]: Displays the contents of a file. Type -?: Type --help: Type --about: Abbreviated help screen. Help screen with descriptions. About screen information. The ver command allows you to see the system software version. It includes the following information: MQX Copyright, MQX Library Creation Date, MQX Version, Build Copyright, Build Version, Build MakeDate, Build MakeTime, CPU Type, and CPU Number. Ver: Displays system software version. Ver -?: Ver --help: Ver --about: Abbreviated help screen. Help screen with descriptions. About screen information. E-5 Rev. A ar SKY899 Installation Manual Pr el im in This page intentionally left blank. E-6 Rev. A SKY899 Installation Manual APPENDIX F Installation Checkout Using an Alternate Display F.1 INTRODUCTION This section contains installation checkout procedures for the BFGoodrich Avionics Systems ® SKYWATCH HP SKY899 that is interfaced to an alternate display (e.g., EFIS, IVSI, BFGoodrich Avionics Systems RGC250, MFD). NOTES 1. This section provides checkout information for the SKY899 interfaced to an Alternate Display. ar 2. When interfacing to BFG Avionics Systems RGC250, software version for RGC250 must be 1.5 or higher. in 3. This procedure assumes familiarity with the set up and operation of the TT391 Flightline Tester and RS-232 terminal device (see Appendix E). If using another approved tester refer to the appropriate appendices for test procedure. 4. All test equipment used in completing these tests shall be calibrated in accordance with the manufacturer's recommendations. im This procedure will validate the installation and return to service of the BFGoodrich Avionics Systems SKY899. Pr el F.2 CONTROLS Operating instructions for each alternate display are provided with the display manufacturer's documentation. NOTE When using an alternate display all SKY899 functions are controlled through the alternate display. Each alternate display will show information consistent with the capabilities of that particular display. Therefore, the text displayed may be different from what is called out in this procedure. Reference the alternate display documentation for appropriate screen text. F.3 CHECKOUT PROCEDURE The TT391 Flightline Tester simulates both a ground based secondary surveillance radar (SSR) and an airborne transponder. With the SKY899 set to GROUND TEST (i.e., the barometric altimeter is simulated to 50,000 ft, heading simulated to 0 degrees, and the radar altimeter simulated to 2,500 ft) the TT391 will simulate two targets; a Traffic Advisory (i.e., a solid circle) at ¼ nm and Other Traffic (i.e., open diamond) at 4.5 nm. Both targets will be displayed in level flight at own aircraft altitude (i.e., "00" displayed above the traffic symbol). If the indications given in the following procedure, except for the Flightline Tester, are not obtained, refer to the troubleshooting procedures in Chapter 4. If indications given for the Flightline Tester are not obtained, refer to the maintenance section of the TT391 Instruction Manual. 1. Connect the RS-232 terminal device to J7 TEST port on the TRC899. Turn ON and setup the terminal device. (See Appendix E for terminal device commands, setup, and operating instructions.) F-1 Rev. A SKY899 Installation Manual 2. Make sure the aircraft's transponder is in the STBY mode and the DME is turned OFF. At the aircraft's instruments, verify all compass/HSI flags are valid. NOTE After power up, it may take a couple of minutes for the altitude encoder to return a valid altitude to the transponder and SKY899. 3. Turn SKY899 ON. Start up screen similar to one shown in figure F-1 will be displayed on the terminal device. After approximately thirty seconds the alternate display will show the standby screen. Welcome to the BFGoodrich Avionics Systems SKYWATCH HP Copyright (c) 2001 BFGoodrich Avionics Systems, Inc. All rights reserved ˝ ar Figure F-1. SKYWATCH Startup Screen on Terminal Device At the terminal device, enter the Service Menu by typing Menu . The service menu displayed on the terminal device is identical to the one seen in Chapter 4, except each command has a prefix. To select a menu item type the prefix (i.e., 1 , 2 , x , etc.). im 4. in NOTE If the TRC has not been calibrated to the directional antenna, the display may show a FAIL message. Calibration will be done during system setup. NOTE While using service menu, system will not perform display commands (e.g., OPR, STB, MSG, or range). Perform the System Setup in paragraph 3.3.1 (start at step 2 of par. 3.3.1). 6. Turn ON all avionics equipment interfaced to the SKY899. 7. From the Service Menu (see paragraph 4.4), select Information. 8. From the Information menu, select Data Monitor. The Data Monitors menu will appear. 9. Select each of the data monitors and verify the sensor information is correct (see paragraph 4.4.2.3): Pr el 5. a. Change the status of the landing gear, squat switch, altitude, and heading sensors. Verify data monitors show the correct input changes (i.e., sensing of these signals). b. If the information is not correct, the sensor has failed to communicate with the TRC. Check operation of the sensor and connections between the TRC and sensor. c. Select exit until you return to the Service Menu. 10. At the alternate display, perform the SKYWATCH HP self-test (see paragraph F.4). 11. At the terminal device, enter the Service Menu by typing Menu . 12. From the Service Menu, select Ground Test (4 ). 13. From the Ground Test menu, select Perform Ground Test (1 ). 14. At the alternate display, verify ground test screen is being displayed. Change the display ranges and verify display range patterns are correct. 15. Select the 6 nautical mile range. F-2 Rev. A SKY899 Installation Manual 16. Change the altitude display modes from normal (NRM), below (BLW), above (ABV), and unrestricted (UNR). Verify that the system toggles through the altitude display modes correctly (some alternate displays do not support unrestricted display mode). If external annunciators are connected verify correct operation (see figure F-2). ABV BLW (Normal) ABV BLW (Above) ABV BLW (Below) ABV BLW (Unrestricted) Figure F-2. External Annunciator Operation. 17. If oper_mode annunciator (optional) is connected, verify annunciator works when system is turned ON. 18. Select the normal (NRM) mode. ar 19. Position the aircraft with the nose aligned on any 90 degree heading. Avoid areas within 250 ft of obstructions (e.g., hangers, large aircraft, control towers, etc.) where there is a potential for multipath problems. Locate and mark test points at 30 degree intervals (i.e., 000, 030, 060, 090, 120, 150, 180, 210, 240, 270, 300, and 330 degrees) with respect to the directional antenna. Mark these points at the same distance, between 100 and 150 ft, from the aircraft. 20. Position the TT391 Flightline Tester on one of the test points identified above. in CAUTION The Flightline Tester is not weatherproof when the lid is open. Do not setup or operate the Flightline Tester in conditions of rain, sleet, etc. a. im 21. Setup and verify operation of the TT391 Flightline Tester: Open the chassis lid and remove the lid from the chassis by sliding the lid off of the hinge pins (sliding it to the right). The lid "stay" must be removed from the lid before mounting. The stay will pop off of the lid. (The stay is the hinged part that props the lid open on the chassis). Pr el NOTE The Patch Antenna may be used without a tripod. The Patch Antenna can be held, or secured, and pointed towards the SKYWATCH HP aircraft under test WITH THE MOUNTING STUD POINT TOWARD THE GROUND . This orientation is critical. b. Mount the chassis lid, with the Patch Antenna facing the aircraft, onto a tripod (not included). The tripod must be capable of holding the antenna (approximately 2.5 lb.) and must provide a standard base mounting stud threaded 1/4"-20. A typical tripod mount is shown in figure F-3. c. If the internal batteries are being utilized, proceed to sub-step f. If the Flightline Tester AC Converter Power Supply is to be utilized, proceed to sub-step d. d. Connect the AC Converter Power Supply cable connector to the chassis external connector. e. Connect the AC Converter Power Supply input power cable connector to one of the following AC sources: • 115 V ac, 60 Hz • 115 V ac, 400 Hz f. Set the Flightline Tester POWER switch to the ON position. g. Verify that the LOW indicator is not steady on (it may flash). If the LOW indicator remains on (i.e., lit), perform one of the following three options: • Use the AC Converter Power Supply to power the unit. • Recharge the internal batteries. • Replace the internal batteries. F-3 Rev. A SKY899 Installation Manual h. Set the SELF-TEST switch to the 1030 position and verify that the 1030 indicator blinks on for 1/2 second every 5 seconds. i. Set the SELF-TEST switch to the 1090 position and verify that the 1090 indicator blinks on for 1/2 second every 5 seconds. j. Set SELF-TEST switch to center position (off). Set the POWER switch to the OFF position. NOTE Care should be taken to ensure that the Patch Antenna is connected to TT391 connector J1 and NOT J2. IF THE PATCH ANTENNA IS CONNECTED TO J2 THE TT391 WILL NOT FUNCTION CORRECTLY. Connect the Flightline Tester coax cable to J3 on the Patch Antenna and to connector J1 in the chassis. (J2 should remain capped by the dust cover). in ar k. Figure F-3. Typical Patch Antenna Tripod Mount im 22. From each test point (see step 13): Position the TT391 Patch Antenna facing the SKYWATCH HP aircraft under test. b. Set the TT391 POWER switch to the ON position. c. Verify that the display shows, in the direction (± 30 degrees) of the TT391, two targets; a Traffic Advisory (i.e., a solid circle) at ¼ nm and Other Traffic (i.e., open diamond) at 4.5 nm. Both targets will be displayed in level flight at own aircraft altitude (i.e., "00" displayed above the traffic symbol). Pr el a. NOTES 1. If the display reflects a gross error in target bearing, check the directional antenna cables at TRC connectors J9 (sum port) and J11 (difference port). They may be reversed. A further indication of this condition would be a target that moved in a counter-clockwise direction when the TT391 is moved in a clockwise direction. 2. Multiple targets or a faulty bearing may result from multipath distortion (see step 1). 3. During these tests, the SKY899 may detect and display other active targets. 4. To obtain a better line of sight, it may be necessary to elevate the patch antenna. d. F-4 Rev. A Set the TT391 POWER switch to the OFF. Repeat procedure from each test point. Step 16 can be done from the last test point. SKY899 Installation Manual NOTE To prevent SKYWATCH HP from tracking the movement of the test-set, it is necessary to set the TT391 POWER switch to OFF after completing each bearing measurement. 23. Return the TT391 assemblies to their position in the aluminum carrying case. 24. Restart SKYWATCH HP by cycling power OFF and then ON. 25. Connect an oscilloscope to the suppression bus and verify that the SKY899 suppression pulse (100 µs ±5 µs) exceeds +15 V dc, if less than +15 V dc the suppression bus is overloaded. Check all equipment connected to the bus. Repair/replace the offending device. 26. This completes the post installation checkout procedure. F.4 SELF TEST a. Turn SKYWATCH HP OFF and then: Make sure the aircraft's transponder is in the STANDBY, ON, or ALT mode. ar 1. NOTE After power up, it may take a couple of minutes for the altitude encoder to return a valid altitude to the transponder and SKY899. If installed, power up the radio altimeter. c. Make sure all compass/HSI flags are cleared from the aircraft's instruments. in b. Turn SKYWATCH HP ON. 3. After approximately thirty seconds, observe the standby screen and then perform the SKYWATCH HP self test (see alternate display operating instructions on how to perform self test). 4. If SKYWATCH HP passes the self-test, the system will return to the standby screen and the voice message, "SKYWATCH SYSTEM TEST PASSED," will be enunciated over the cockpit audio system. 5. If you do not hear the voice message or if the voice message is of insufficient volume: a. Pr el im 2. Check headphones/speaker and aircraft audio panel switch settings. NOTE Audio levels are adjusted via the service menu and at the aircraft audio panel. There is no internal audio adjustment. b. Reset the audio level via the service menu (see paragraph 4.4.1.3). c. Check audio connection to the TRC: 1) 600-ohm audio systems should be connected to P1-89 (AUDIO_H). 2) 150-ohm audio systems should be connected to P1-90 (AUDIO_L). 3) Audio common is connected to P1-91 (AUDIO_C). NOTE Audio output from the TRC is transformer isolated. 6. If SKYWATCH HP fails the self-test: a. The fail screen will be displayed. b. The voice message, "SKYWATCH SYSTEM TEST FAILED", will be enunciated over the cockpit audio system. c. Refer to the fault isolation procedures and error messages in Chapter 4. F-5 Rev. A ar SKY899 Installation Manual Pr el im in This page intentionally left blank. F-6 Rev. A
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