L 3 Communications Avionics Systems TRC899 User Manual

Page 1

Traffic Alert/Advisory System

Preliminary

SKY899 Installation Manual

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. 30 April 2001 5353 52 Grand Rapids, MI USA 49512

Street, S.E.

Page 2

Preliminary

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.

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.

Appendix B – Environmental Qualification Form

This appendix has the environmental qualification forms for the TRC899, NY156 & NY164 antennas, and WX-1000/SKY497 display.

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).

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.

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

and Stormscope® are registered trademarks of BFGoodrich Avionics Systems, Inc.

A Rev. A

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LIST OF EFFECTIVE PAGES

Dates of original and changed pages are: Original (Rev. A) ..........................30 April 2001

NOTE

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.

Total number of pages in this publication consists of the following:

Page Change No. No.

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.

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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:

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

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:

BFGoodrich Avionics Systems

Attn: Technical Publications

5353 52nd Street, S.E.

Grand Rapids, MI USA 49512

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Paragraph Page

Chapter 1

GENERAL INFORMATION

1.1 INTRODUCTION .................................................................................................................................. 1-1

1.2 FUNCTIONAL DESCRIPTION ........................................................................................................... 1-2

1.3 PHYSICAL DESCRIPTION.................................................................................................................. 1-2

1.3.1 TRC899 Transmitter Receiver Computer P/N 805-11900-xxx............................................................ 1-6

1.3.2 Configuration Module P/N 814-18005-001......................................................................................... 1-10

1.3.3 Display (Alternate or WX-1000/SKY497 Display P/N 78-8060-5900-x)........................................... 1-11

1.3.4 Directional Antenna (NY156 P/N 805-10003-001 or NY164 P/N 805-10890-001) ........................... 1-13

1.4 SPECIFICATIONS .............................................................................................................................. 1-15

1.4.1 Transmitter Receiver Computer (TRC) .............................................................................................. 1-15

1.4.2 WX-1000/SKY497 Display................................................................................................................... 1-16

1.4.3 Directional Antenna ............................................................................................................................1-16

1.5 MODIFICATIONS & SOFTWARE REVISIONS............................................................................... 1-16

1.6 INTERFACE ........................................................................................................................................ 1-17

1.7 EQUIPMENT REQUIRED NOT SUPPLIED.................................................................................... 1-17

1.8 INSTALLATION APPROVAL ............................................................................................................1-22

1.9 WARRANTY INFORMATION............................................................................................................ 1-22

1.9.1 Warranty Statement............................................................................................................................ 1-22

1.9.2 Related Policies and Procedures ......................................................................................................... 1-23

Chapter 2

INSTALLATION

2.1 INTRODUCTION .................................................................................................................................. 2-1

2.2 UNPACKING, INSPECTION AND STORAGE ..................................................................................2-1

2.3 ANTENNA LOCATION ........................................................................................................................2-2

2.4 TRC LOCATION.................................................................................................................................... 2-2

2.5 DISPLAY LOCATION ......................................................................................................................... 2-15

2.6 CABLE REQUIREMENTS AND FABRICATION ............................................................................ 2-16

2.6.1 Antenna Cables.................................................................................................................................... 2-18

2.6.2 Audio Output Cable ............................................................................................................................. 2-18

2.6.3 Data Cables .......................................................................................................................................... 2-18

2.6.4 Heading Input Cable ...........................................................................................................................2-19

2.6.5 Power Cable ......................................................................................................................................... 2-19

2.6.6 Suppression Bus Cable........................................................................................................................ 2-20

2.6.7 WX-1000/SKY497 Display and WX-1000 Processor Cable................................................................ 2-20

2.6.8 Converting Existing Aircraft Wiring from SKY497 to SKY899........................................................ 2-21

2.7 AIRCRAFT DISCRETE INPUTS .......................................................................................................2-22

2.7.1 Audio Inhibit (Terrain Warning System - GPWS)............................................................................. 2-22

2.7.2 Landing Gear ....................................................................................................................................... 2-22

2.7.3 SKYWATCH/Stormscope Mode Switch .............................................................................................. 2-22

2.7.4 Squat Switch (Weight-On-Wheels) ..................................................................................................... 2-22

2.7.5 ON/OFF Power Switch ........................................................................................................................ 2-23

2.8 ALTERNATE DISPLAY...................................................................................................................... 2-24

2.9 ARINC-429 ........................................................................................................................................... 2-24

2.9.1 General Sensor Inputs......................................................................................................................... 2-24

2.9.2 Mode S Transponder I/O (future option)............................................................................................ 2-24

2.9.3 Alternate Display Output.................................................................................................................... 2-25

2.9.4 Future Option ......................................................................................................................................2-25

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TABLE OF CONTENTS

(Continued)

Paragraph Page

Chapter 2

INSTALLATION

2.10 AUDIO (ALERT) OUTPUT ................................................................................................................ 2-25

2.11 BAROMETRIC (UNCORRECTED) ALTITUDE INPUTS ............................................................... 2-25

2.11.1 Gilham Code (Encoding Altimeter) .................................................................................................... 2-26

2.11.2 ADC (ARINC-429) ............................................................................................................................... 2-26

2.12 GPS (ARINC-429)................................................................................................................................ 2-26

2.13 HEADING INPUT............................................................................................................................... 2-26

2.13.1 Compass Synchro (XYZ)...................................................................................................................... 2-26

2.13.2 AHRS (Attitude Heading and Reference System)............................................................................. 2-27

2.14 LAMP OUTPUTS (ABV and BLW) .................................................................................................... 2-27

2.15 OPERATIONAL MODE OUTPUT (optional) .................................................................................... 2-27

2.16 POWER INPUT ................................................................................................................................... 2-27

2.17 RADIO ALTIMETER (optional) ......................................................................................................... 2-27

2.17.1 Analog .................................................................................................................................................. 2-28

2.17.2 ARINC-429........................................................................................................................................... 2-28

2.18 SERIAL DATA..................................................................................................................................... 2-28

2.19 SOFT-KEYS......................................................................................................................................... 2-28

2.20 SUPPRESSION BUS I/O .................................................................................................................... 2-28

2.21 SYSTEM CONFIGURATION MODULE........................................................................................... 2-28

2.22 WX-1000/SKY497 DISPLAY (OPTIONAL) ....................................................................................... 2-30

2.23 WX-1000 PROCESSOR (OPTIONAL)................................................................................................2-30

2.24 ANTENNA INSTALLATION ............................................................................................................. 2-31

2.25 TRC MOUNTING TRAY INSTALLATION....................................................................................... 2-32

2.26 TRC INSTALLATION......................................................................................................................... 2-34

2.27 MOUNTING the WX-1000/SKY497 DISPLAY.................................................................................. 2-36

2.27.1 Panel Cutout........................................................................................................................................ 2-36

2.27.2 Display Installation............................................................................................................................. 2-37

Chapter 3

INSTALLATION CHECKOUT

3.1 INTRODUCTION.................................................................................................................................. 3-1

3.2 CONTROLS ........................................................................................................................................... 3-1

3.3 CHECKOUT PROCEDURE ................................................................................................................. 3-2

3.3.1 System Setup ......................................................................................................................................... 3-3

3.3.2 System Setup Verification and Operation ........................................................................................... 3-5

3.4 SELF TEST............................................................................................................................................ 3-7

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

Chapter 4

MAINTENANCE

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(Continued)

Paragraph Page

Chapter 4

MAINTENANCE

4.4.1.2 Antenna System..................................................................................................................................... 4-4

4.4.1.3 Audio Level ............................................................................................................................................ 4-4

4.4.1.4 Communication Ports ............................................................................................................................ 4-4

4.4.1.5 Avionics Equipment............................................................................................................................... 4-6

4.4.2 Information ............................................................................................................................................4-8

4.4.2.1 Software Version.................................................................................................................................... 4-9

4.4.2.2 System Log ............................................................................................................................................. 4-9

4.4.2.3 Data Monitor........................................................................................................................................ 4-10

4.4.3 Calibration ........................................................................................................................................... 4-12

4.4.4 Ground Test ......................................................................................................................................... 4-12

4.5 TROUBLESHOOTING ....................................................................................................................... 4-17

4.6 ERROR MESSAGES ...........................................................................................................................4-18

4.7 TRC899/WX-1000 ADAPTER PLUG ..................................................................................................4-20

4.8 DISPOSITION OF FAILED ITEMS................................................................................................... 4-21

Appendix A

SKY899 INTERFACE SIGNAL & CABLE CHARACTERISTICS

A.1 INTRODUCTION ................................................................................................................................. A-1

A.2 ELECTRICAL CHARACTERISTICS .................................................................................................. A-1

A.3 ARINC-429 LABELS .......................................................................................................................... A-11

Appendix B

ENVIRONMENTAL QUALIFICATION FORM

B.1 TRC899 ENVIRONMENTAL QUALIFICATION FORM .................................................................. B-1

B.2 NY156 & NY164 ENVIRONMENTAL QUALIFICATION FORM.................................................... B-2

B.3 WX-1000/SKY497 DISPLAY ENVIRONMENTAL QUALIFICATION FORM ................................ B-3

Appendix C

INSTALLATION CHECKOUT USING THE TCAS-201 RAMP TEST SET

C.1 INTRODUCTION ................................................................................................................................. C-1

C.2 CONTROLS........................................................................................................................................... C-1

C.3 CHECKOUT PROCEDURE................................................................................................................. C-2

Appendix D

INSTALLATION CHECKOUT USING THE TIC T-49C FLIGHTLINE TESTER

D.1 INTRODUCTION ................................................................................................................................. D-1

D.2 CONTROLS........................................................................................................................................... D-1

D.3 CHECKOUT PROCEDURE................................................................................................................. D-2

USING THE TERMINAL DEVICE ................................................................................................................. E-1

Appendix E

USING THE TERMINAL DEVICE

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(Continued)

Appendix F

INSTALLATION CHECKOUT USING AN ALTERNATE DISPLAY

F.1 INTRODUCTION.................................................................................................................................. F-1

F.2 CONTROLS ........................................................................................................................................... F-1

F.3 CHECKOUT PROCEDURE .................................................................................................................F-1

F.4 SELF TEST ............................................................................................................................................ F-5

LIST OF ILLUSTRATIONS

Figure Page

1-1 Vertical Display Modes ......................................................................................................................... 1-4

1-2 SKY899 System Block Diagram ........................................................................................................... 1-5

1-3 Standard TRC Mounting Tray (P/N 805-10870-001) .......................................................................... 1-8

1-4 Ruggedized TRC Mounting Tray (P/N 805-10870-003)....................................................................... 1-9

1-5 P1 Connector Dimensions (Reference Only)........................................................................................ 1-9

1-6 TRC899 Transmitter Receiver Computer (TRC)............................................................................... 1-10

1-7 System Configuration Module............................................................................................................ 1-10

1-8 WX-1000/SKY497 Display Equipment Tag ....................................................................................... 1-11

1-9 WX-1000/SKY497 Display .................................................................................................................. 1-12

1-10 NY156/NY164 Directional Antenna................................................................................................... 1-14

2-1 Directional Antenna Mounting Location ............................................................................................. 2-2

2-2 Interconnect Wiring Without WX-1000 ............................................................................................... 2-3

2-3 Interconnect Wiring With WX-1000..................................................................................................... 2-7

2-4 Interconnect Wiring With Alternate Display .................................................................................... 2-11

2-5 Heading Input Cable........................................................................................................................... 2-18

2-6 Display Cable....................................................................................................................................... 2-20

2-7 Above and Below External Lamps ..................................................................................................... 2-26

2-8 System Configuration Module............................................................................................................ 2-28

2-9 Typical Location of Configuration Module (Inside Backshell) ......................................................... 2-29

2-10 Antenna Mounting Holes.................................................................................................................... 2-31

2-11 Directional Antenna Installation ....................................................................................................... 2-31

2-12 Mounting Holes for Standard Mount Tray, P/N 805-10870-001 ...................................................... 2-32

2-13 Mounting Holes for Ruggedized Mount Tray, P/N 805-10870-003 .................................................. 2-33

2-14 TRC899 Installation............................................................................................................................ 2-34

2-15 Instrument Panel Cutout and Mounting Holes................................................................................. 2-35

2-16 Display Installation............................................................................................................................. 2-36

3-1 Controls.................................................................................................................................................. 3-1

3-2 Start-up Screen...................................................................................................................................... 3-2

3-3 Standby Screen...................................................................................................................................... 3-3

3-4 Typical Patch Antenna Tripod Mount.................................................................................................. 3-6

3-5 Self Test Screen..................................................................................................................................... 3-8

4-1 Service Menu (Terminal Emulation Program)....................................................................................4-2

4-2 Service Menu (WX-1000/SKY497 Display) .......................................................................................... 4-2

4-3 Compact Flash Insertion Instructions ............................................................................................... 4-16

4-4 Service Menu Tree (Sheet 1 of 3)........................................................................................................ 4-17

4-4 Service Menu Tree (Sheet 2 of 3)........................................................................................................ 4-18

4-4 Service Menu Tree (Sheet 3 of 3)........................................................................................................ 4-19

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(Continued)

LIST OF ILLUSTRATIONS

Figure Page

4-5 Adapter Plug Assembly ....................................................................................................................... 4-24

A-1 P1 Connector Pin Identifiers.............................................................................................................. A-11

C-1 Controls ................................................................................................................................................. C-1

C-2 Start-Up Screen .................................................................................................................................... C-3

C-3 Standby Screen ..................................................................................................................................... C-3

D-1 Controls ................................................................................................................................................. D-1

D-2 Start-Up Screen .................................................................................................................................... D-2

D-3 Standby Screen ..................................................................................................................................... D-3

F-1 SKYWATCH Startup Screen on Terminal Device...............................................................................F-2

F-2 External Annunciator Operation..........................................................................................................F-3

F-3 Typical Patch Antenna Tripod Mount ..................................................................................................F-4

LIST OF TABLES

Table Page

1-1 SKY899 System...................................................................................................................................... 1-6

1-2 TRC Installation Kit P/N 817-11900-xxx ............................................................................................. 1-7

1-3 WX-1000/SKY497 Display Installation Kit P/N 817-10802-001 ....................................................... 1-11

1-4 Airframe Installation Kits................................................................................................................... 1-13

1-5 Directional Antenna Installation Kit 817-10009-xxx ........................................................................ 1-14

1-6 TRC899 Software Revisions................................................................................................................ 1-17

1-7 Minimum Interface Equipment Required.......................................................................................... 1-17

1-8 Directional Antenna SIGMA and DELTA Port Cable Vendors ........................................................ 1-18

1-9 Cable to Connector Reference............................................................................................................. 1-19

1-10 Heading Input Cable Vendors ............................................................................................................1-20

1-11 Display Cable Vendors ........................................................................................................................ 1-22

2-1 Alternate Display Drivers ................................................................................................................... 2-25

2-2 WX-1000/SKY497 Display Connection............................................................................................... 2-30

2-3 WX-1000 Processor Connection .......................................................................................................... 2-30

4-1 Fault Isolation...................................................................................................................................... 4-20

4-2 Installation Related Error Messages.................................................................................................. 4-21

4-3 Informational Error Messages............................................................................................................ 4-22

A-1 ARINC-429 Input Labels (Rx)............................................................................................................ A-13

A-2 ARINC-429 Output Labels (Tx) ......................................................................................................... A-14

C-1 IFR Systems TCAS-201 Ramp Test Set Setup Data .......................................................................... C-2

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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.

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.

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.

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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.

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.

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)

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.

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Major differences between SKYWATCH and SKYWATCH HP are listed below:

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.

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).

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Table 1-2. TRC Installation Kit P/N 817-11900-xxx

KIT P/N DESCRIPTION QUANTITY PART NUMBER

817-11900-001 For Installation on Fixed-Wing Aircraft with Straight 1.5 inch

(3.8 cm) Backshell Consists of:

Standard Mounting Tray Assembly 1 805-10870-001

1.5" (3.8 cm) Straight Backshell 1 613-10039-001 I/O Connector, 100-Position, Female, (Mil-C-38999 Series III) 1 605-10251-001

(Includes #22D Crimp Terminals) Spare Terminals for I/O Connector 10 M39029/56-348 Power Connector, 3-Position, Straight Plug 1 MS3126F12-3S

(Includes #16 Crimp Terminals) Spare Terminals for Power Connector (M39029/32-247) 2 607-10018-001 System Configuration Module Assembly 1 814-18005-001

817-11900-002 For Installation on Fixed-Wing Aircraft with Straight 2.5 inch

(6.4 cm) Backshell Consists of:

Standard Mounting Tray Assembly 1 805-10870-001

2.5" (6.4 cm)Straight Backshell 1 613-10042-001 I/O Connector, 100-Position, Female, (Mil-C-38999 Series III) 1 605-10251-001

(Includes #22D Crimp Terminals) Spare Terminals for I/O Connector 10 M39029/56-348 Power Connector, 3-Position, Straight Plug 1 MS3126F12-3S

(Includes #16 Crimp Terminals) Spare Terminals for Power Connector (M39029/32-247) 2 607-10018-001 System Configuration Module Assembly 1 814-18005-001

817-11900-003 For Installation on Fixed-Wing Right-Angle (90°) Backshell

Consists of:

Standard Mounting Tray Assembly 1 805-10870-001 Right-Angle (90°) Backshell 1 613-10043-001 I/O Connector, 100-Position, Female, (Mil-C-38999 Series III) 1 605-10251-001

(Includes #22D Crimp Terminals) Spare Terminals for I/O Connector 10 M39029/56-348 Power Connector, 3-Position, Straight Plug 1 MS3126F12-3S

(Includes #16 Crimp Terminals) Spare Terminals for Power Connector (M39029/32-247) 2 607-10018-001 System Configuration Module Assembly 1 814-18005-001

817-11900-004 For Installation on Rotorcraft with 2.5 inch (6.4 cm) Backshell

Ruggedized Mounting Tray Assembly 1 805-10870-003

2.5" (6.4 cm)Straight Backshell 1 613-10042-001 I/O Connector, 100-Position, Female, (Mil-C-38999 Series III) 1 605-10251-001

(Includes #22D Crimp Terminals) Spare Terminals for I/O Connector 10 M39029/56-348 Power Connector, 3-Position, Straight Plug 1 MS3126F12-3S

(Includes #16 Crimp Terminals) Spare Terminals for Power Connector (M39029/32-247) 2 607-10018-001 System Configuration Module Assembly 1 814-18005-001

817-11900-005 For Installation on Rotorcraft with Right-Angle (90°) Backshell

Consists of:

Ruggedized Mounting Tray Assembly 1 805-10870-003 Right-Angle (90°) Backshell 1 613-10043-001 I/O Connector, 100-Position, Female, (Mil-C-38999 Series III) 1 605-10251-001

(Includes #22D Crimp Terminals) Spare Terminals for I/O Connector 10 M39029/56-348 Power Connector, 3-Position, Straight Plug 1 MS3126F12-3S

(Includes #16 Crimp Terminals) Spare Terminals for Power Connector (M39029/32-247) 2 607-10018-001 System Configuration Module Assembly 1 814-18005-001

1-7

Rev. A

Page 18

Preliminary

SKY899

Installation Manual

RETAINER CUPS

HOLD-DOWN KNOBS

(2-PLACES)

DIMENSIONS ARE IN INCHES (MILLIMETERS)

NOTE

REAR HOLD-DOWN PINS

(2-PLACES)

(

)

3.37 (85.6) MAX.

(

)

(

)

(

4.15

(105.4)

MAX.

)

1-8 Rev. A

)

(

)

Figure 1-3. Standard TRC Mounting Tray (P/N 805-10870-001)

Page 19

Preliminary

SKY899

Installation Manual

DIMENSIONS ARE IN INCHES (MILLIMETERS)

NOTE

DOES NOT INCLUDE SCREW

COG

)

(

)

HEADS

)

(

3.66 (93.0) MAX.

)

(

)

(

)

(

Figure 1-4. Ruggedized TRC Mounting Tray (P/N 805-10870-003)

DIMENSIONS ARE IN INCHES (MILLIMETERS)

4.75

(120.7)

REF.

NOTE

4.25

(108.0)

REF.

3.25

(82.6)

REF.

STRAIGHT

BACKSHELL

P/N 613-10042-001

Figure 1-5. P1 Connector Dimensions (Reference Only)

SPLIT ELBOW

90° BACKSHELL

P/N 613-10043-001

1-9

Rev. A

Page 20

Preliminary

SKY899

Installation Manual

4.15 - REF (105.4)

DIMENSIONS ARE IN INCHES (MILLIMETERS)

NOTE

)

7.62

(193.0)

MAX.

4.15

(105.4)

(

)

2 Y

)

(

)

(

)

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

Page 21

Preliminary

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.

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.

Stormscope

Weather Mapping Systems

Series II

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.

SERIAL NO.

ace

erosp

2.3lb. 1.0kg.

BFGoodrich Avionics Systems, Inc. Grand Rapids, MI USA

TAG MUST IDENTIFY

SKYWATCH AND TSO-C113.

Figure 1-7. WX-1000/SKY497 Display Equipment Tag

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

4 26-1001-6374-5 Screw, Machine, 6-32 x 3/4 in. Phillips Pan Head, Black Oxide 1 26-1003-5633 Connector, 25 Position Recpt. Shell 1 26-1006-2426-6 Connector Backshell, DB25 2 26-1006-1089-3 Connector Lock Post Assembly

25 26-1003-4274-9 Connector Socket, Screw Machine (M39029/63-368)

1-11

Rev. A

Page 22

Preliminary

SKY899

Installation Manual

3.37

(85.6)

0.55

(14.0)

NOTE

C.G.

3.37

(85.6)

DIMENSIONS ARE IN INCHES (MILLIMETERS)

3.89

(98.8)

3.18

(80.8)

J101

3.18

(80.8)

1-12 Rev. A

0.17 ±0.02

(4.3 ±0.5)

0.08

(2.0)

C.G.

3.40

(86.4)

8.07

(205.0)

P101

1.30

(33.0)

Figure 1-8. WX-1000/SKY497 Display

Page 23

Preliminary

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

MANUFACTURER AIRFRAME

AEROSPATIALE ATR-42 817-10009-001

AGUSTA A109 817-10009-006

BAE/RAYTHEON HAWKER 400, 600, 700, 800, and 1000 817-10009-004

BEECH

BELL 206, 407, 427 817-10009-006

CANADAIR CHALLENGER 600 and 601 817-10009-005

CESSNA CITATION III, VI, VII

COMMANDER 114 817-10009-006

DASSAULT FALCON 10, 20, 50

DEHAVILLAND 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 LEARJET 31, 35, 36, 55, and 60 817-10009-004

MITSUBISHI MU-2 817-10009-002

MOONEY M20 817-10009-006

PILATIS PC-12 817-10009-001

PIPER CHEYENNE 400LS

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

BEECHJET, KING AIR 90, 100, 200, 300, and 350

BARON 33, 35, 36, 55, 58, BE-99, 1300, & 1900C/D

CITATIONJET, CITATION I, II, V 182, 210, 337, 401, 414, 425, 441

FALCON 900

NAVAJO

MIRAGE, MALIBU

SARATOGA, SENECA

TB20

PART NUMBER

817-10009-001 817-10009-002

817-10009-001 817-10009-004 817-10009-006

817-10009-001 817-10009-005

817-10009-001

817-10009-002

817-10009-005

817-10009-006

817-10009-001

817-10009-006

1-13

Rev. A

Page 24

Preliminary

SKY899

Installation Manual

Table 1-5. Directional Antenna Installation Kit 817-10009-xxx

SUPPLIED PARTS *

KIT PART NUMBER PART NUMBER DESCRIPTION QUANTITY

817-10009-001 800-10066-001 Special Adapter Plate, 40 Inch (101.6 cm) Radius 1 817-10009-002 800-10066-002 Special Adapter Plate, 63 Inch (160.0 cm) Radius 1 817-10009-003 800-10066-004 Special Adapter Plate, 80 Inch (203.2 cm) Radius 1 817-10009-004 800-10066-003 Special Adapter Plate, 32 Inch (81.3 cm) Radius 1 817-10009-005 800-10066-005 Special Adapter Plate, 47 Inch (119.4 cm) Radius 1

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.

4 4

DIMENSIONS ARE IN INCHES (MILLIMETERS)

NOTE

FWD

DO NOT PAINT

FORWARD

6.23 ±0.08

(158.2 ±2.0)

1.30

(33.0)

1-14 Rev. A

0.725

(18.4)

SUM PORT (Blue Band)

PROBE PORT

(Black Band)

5.06

(128.5)

11.12

(282.4)

DIFFERENCE PORT

(Red Band)

5.71

(145.0)

0.45

(11.4)

Figure 1-9. NY156/NY164 Directional Antenna

Page 25

Preliminary

Installation Manual

1.4 SPECIFICATIONS

1.4.1 Transmitter Receiver Computer (TRC)

SKY899

PART NUMBER:

SIZE:

WEIGHT:

OPERATING TEMPERATURE:

STORAGE TEMPERATURE:

OPERATING ALTITUDE:

COOLING:

POWER REQUIREMENTS:

TRACKING CAPABILITY:

SURVEILLANCE RANGE:

DISPLAY RANGES:

805-11900-001 - TRC899

Approximately 12.52 inches (31.90 cm) Deep Approximately 3.56 inches (9.04 cm) Wide Approximately 7.62 inches (19.36 cm) High

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

-55 to +70 degrees Celsius (-67 to +158 degrees Fahrenheit)

-55 to +85 degrees Celsius (-67 to +185 degrees Fahrenheit)

55,000 feet (Maximum)

Conduction and Forced Air (Internal Fan) Convection

18 to 32 V dc, 2 Amps @ + 28 V dc(Maximum)

Up to 35 intruder aircraft (displays only the 8 highest priority aircraft)

Horizontal tracking radius:

35 nmi Maximum ATCRBS Surveillance 50 nmi Maximum ADS-B Surveillance

Relative altitude tracking range:

±10,000 ft maximum

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)

RANGE ACCURACY:

BEARING ACCURACY:

ALTITUDE ACCURACY:

CERTIFICATION: *

RTCA COMPLIANCE:

± 0.05 nmi (Typical)

With NY156 Antenna - 5° RMS (Typical) 30° Peak Error With NY164 Antenna - 7° RMS (Typical) 30° Peak Error

±200 ft

USA (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 1-800-453-

0288 or 1-616-949-6600 for latest certification information.

Rev. A

1-15

Page 26

Preliminary

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 Fahren heit)

STORAGE TEMPERATURE:

-55 to +70 degrees Celsius (-67 to +158 degrees Fahrenheit)

OPERATING ALTITUDE:

55,000 feet (Maximum)

TSO COMPLIANCE:

C110a & C113

SKY899

Installation Manual

RTCA COMPLIANCE:

DO-160C F1-CA(NBM)XXXXXXZXXXZUAXXXXXX

POWER REQUIREMENTS:

+15/-15 V dc, 0.7 A (Maximum)

1.4.3 Directional Antenna

PART NUMBER: 805-10003-001 (NY156)

805-10890-001 (NY164)

SIZE: 1.3 inches (3.25 cm) high

6.23 in (15.82 cm) wide

11.12 in (27.94 cm) deep

WEIGHT: 2.3 lb (1.04 kg)

SPEED: Rated to 600 knots (0.9 Mach) @ 25,000 feet.

FREQUENCY: 1030-1090 MHz

TSO CATEGORY: C118

ENVIRONMENTAL CATEGORY: DO-160C F2-AC(CLM)XSFDFSXXXXXXXL(2A)X

FINISH: 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. software versions are listed below.

SKY HP software version can be verified via the service menu. Hardware modifications and

Hardware Modifications - None at the time of publication.

1-16 Rev. A

Page 27

Preliminary

SKY899

Installation Manual

Table 1-6. TRC899 Software Revisions

SYSTEM

REVISION

1.00 1.00 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.

SURVEILLANCE

MODE

SKY HP

VERSION

DESCRIPTION

Table 1-7. Minimum Interface Equipment Required

AVIONICS EQUIPMENT

GPS NAV

MAGNETIC HEADING

RADIO ALTITUDE

SQUAT SWITCH (WOW)

BAROMETRIC ALTITUDE

LANDING GEAR SWITCH

SUPPRESSION BUS

(PUSHBUTTONS)

PILOT CONTROLS

EXTERNAL LAMPS

AUDIO INHIBIT (GPWS)

AUDIO SYSTEMS

ATCRBS

(Active Only)

ATCRBS & ADS-B X X

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

Use of any cable not meeting BFGoodrich Avionics Systems specifications voids all system warranties.

①

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.

①①

①

NOTE

①

②③ ③

1-17

Rev. A

Page 28

Preliminary

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

Attenuation

Part Number

PFLX195-100 10.81 2.7 21.8 0.50 PFLX240-100 9.76 4.5 25.0 0.75 PFLX340-100 6.3 7.2 38.2 0.88

Part Number

352001 12.2 2.7 15 0.81 311601 8.7 5.5 26 1.15 311201 5.56 8.5 41 1.59 310801 3.63 16.1 63 2.26

Part Number

S33141 7.2 6.5 32 1.5 S55122 5.7 8.2 40 1.6 S22089 3.8 18 61 2.5

(dB/100 ft 1.0 gHz)

Attenuation

(dB/100 ft 1.0 gHz)

Attenuation

(dB/100 ft 1.0 gHz)

Weight (lb) (per 100 ft)

Electronic Cable Specialists

1-800-327-9473

414-421-5300

FAX 414-421-5301

Weight (lb) (per 100 ft)

PIC Wire and Cable

1-800-742-3191

262-246-0500

FAX 262-246-0450

Weight (lb) (per 100 ft)

Maximum Length

(ft)

Maximum Length

(ft)

Maximum Length

(ft)

Minimum Bend

Radius (in)

Minimum Bend

Radius (in)

Minimum Bend

Radius (in)

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

Page 29

Preliminary

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 TNC Straight TNC Right Angle BNC Straight BNC Right Angle

PFLX195-100 TMS195-1 TMR195-1 BMS195-1 BMR195-1 PFLX240-100 TMS240-1 TMR240-1 BMS240-1 BMR240-1 PFLX340-100 TMS340-1 TMR340-1 BMS340-1 BMR340-1

Electronic Cable Specialists

1-800-327-9473

414-421-5300

FAX 414-421-5301

Cable Part Number TNC Straight TNC Right Angle BNC Straight BNC Right Angle

311601 CTS922 CTR922 CBS922 CBR922 311201 CTS122 CTR122 CBS122 CBR122 310801 CTS022 CTR022 CBS022 CBR022 352001 CTS3522 CTR3522 CBS3522 CBR3522

PIC Wire and Cable

1-800-742-3191

262-246-0500

FAX 262-246-0450

Cable Part Number TNC Straight TNC Right Angle BNC Straight BNC Right Angle

S33141 190308 190309 190312 190313 S55122 190608 190609 190612 190613 S22089 190408 190409 190412 190413

Antenna Sealant 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.

Circuit Breaker 5 Amp

Connector Installation 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)

P1 Interconnect Crimping Tool M22520/2-01

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)

Positioner M22520/2-07 Insertion MS27495 A22M

Removal MS27495 R22M

1-19

Rev. A

Page 30

Preliminary

SKY899

Installation Manual

Connector Installation (Continued)

P8 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

Data Cables 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.

Table 1-10. Heading Input Cable Vendors

COMPANY

Dallas Avionics 1-800-527-2581 214-320-9776 FAX 214-320-1057

CABLE

P/N

WX-5 (6.84 lb/ 100 ft)

Lamps (external annunciators)

Electronic Cable Specialists 1-800-327-9473 414-421-5300 FAX 414-521-5301

A.E. Petsche 817-461-9473 FAX 817-277-2887

EDMO Distributors 1-800-235-3300 805-295-6689 FAX 1-800-828-0623 FAX 805-295-6703

3N6607 (7.5 lb/ 100 ft)

TZGYR (6.84 lb/ 100 ft)

WX-1000 SYNCHRO

PIC Wire and Cable 1-800-742-3191 262-246-0500 FAX 262-246-0450

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

WM25807 (7.2 lb/ 100 ft)

1-20 Rev. A

Page 31

Preliminary

SKY899

Installation Manual

Miscellaneous Hardware

Oscilloscope

Power Cable For the power cable, use #16 AWG (minimum) twisted shielded pair cable

RS-232 Terminal Device (e.g., Laptop Computer)

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.)

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.)

Flat Mount Eight 6-32 UNC-2A 100 degree flat head machine

screws per B18.6.3.

Required to verify SKY899 suppression pulse (100 µs ±5µs, +28 V dc).

(Beldon 83322, Alpha 2826/2, or equivalent).

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.

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

Page 32

Preliminary

Installation Manual

Table 1-11. Display Cable Vendors

U.S.

COMPANY

Dallas Avionics

1-800-527-2581

214-320-9776

FAX 214-320-1057

Electronic Cable Specialists

1-800-327-9473

414-421-5300

FAX 414-421-5301

A.E. Petsche

817-461-9473

FAX 817 277 2887

PIC Wire and Cable

1-800-742-3191

262-246-0500

FAX 262-246-0450

EDMO Distributors

1-800-235-3300

509-535-8280

FAX 1-800-828-0623

FAX 509-535-8266

SKY899

DISPLAY CABLE

P/N

WX-3 10.5

3N6715 16

TZDIS 13.1

WM25815 14.5

WX-1000 Display ---

WEIGHT

(LB PER 100 FT)

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

Page 33

Preliminary

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

1. 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:

ATTENTION: WARRANTY ADMINISTRATOR

BFGoodrich Avionics Systems

5353 52nd Street, S.E.

Grand Rapids, MI USA 49512

2. 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.

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

Page 34

Preliminary

SKY899

Installation Manual

This page intentionally left blank.

1-24 Rev. A

Page 35

Preliminary

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):

ANGLES ARE ± 1° .00 TWO PLACE DECIMALS ARE ± .02 .000 THREE PLACE DECIMALS ARE ± .010

Installation must be made by qualified personnel, in conformance with applicable government regulations. This information furnished is for convenience only.

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.

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).

Rev. A

2-1

Page 36

Preliminary

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:

Directional Antenna 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.

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

Page 37

Preliminary

TRANSMITTER

RECEIVER

COMPUTER

UNIT

TRC899

P/O P/O

J1 P1

HEADING_FLG

HEADING_C

HEADING_H

HEADING_Z HEADING_Y HEADING_X

DPWR+15_OUT

DPWR-15_OUT

DSPLY_GND_OUT

HSYNC_OUT+

HSYNC_OUT-

VSYNC_OUT+

VSYNC_OUTVIDEO_OUT+

VIDEO_OUT-

ON/OFF_RET

SFTKEY1_IN SFTKEY2_IN SFTKEY3_IN SFTKEY4_IN

ALT_COMN

RAD_ALT_IN_HI

RAD_ALT_IN_LO

RADIO_ALT_FLG

DISCRETE

OPER_MODE

PLUG_GND

ON/OFF

ALT_A1 ALT_A2 ALT_A4 ALT_B1 ALT_B2

ALT_B4 ALT_C1 ALT_C2 ALT_C4 ALT_D2 ALT_D4

SQUAT

GEAR

LP1OUT

LP2OUT

3.3V

SDA SCL

51 50 49 48 47 46

8 9 10 11 12 13 22 16 17 4 5 18 19 20 21

56 57 58 59 60 61 67 68 69 70 71 72 24 33 6 7 14

31 66 85

2 92 99 100

N/C

WHT

BLU

ORN

RED

GRN

BLKTP

YEL

SEE NOTE 13

BLU

ORN

WHT BLU

BLU

WHT BLU ORN

WHT

SEE NOTE 6

N/C

PERSONALITY PLUG

3.3V PLUG_GND SDA SCL

SEE NOTE 6

WHT ORN

BLU

WHT

BLU

WHT

BLU

WHT

BLU

WHT

BLU

WHT

BLU

WHT

BLU

DISCRETE I/O SEE NOTE 4

LAMP, SEE NOTE 14

LAMP ABV

LAMP BLW

HEADING INPUT CABLE

SEE NOTE 6

SEE NOTE 12

}

INSIDE CONNECTOR BACKSHELL

SKY899

Installation Manual

SEE NOTE 6

BLU WHT

BLU WHT BLU

ORN

WHT

DISPLAY CABLE

HIGH

}

LOW VAL ID F LAG

RADIO ALT

SEE NOTE 9

DC ANALOG ALT

SEE NOTE 6

WHT ORN

BLU

WHT

BLU

WHT

BLU

WHT

BLU

WHT

BLU

WHT

BLU

WHT

BLU

N/C N/C N/C N/C N/C N/C N/C N/C

ORN

BLU

WHT

BLU

ORN

RED

GRN

BLK

YEL

N/C

DIRECTIONAL GYRO COMPASS

HEADING VALID

LOW

26 VAC REFERENCE

}

HIGH Z

HEADING

}

P101 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

CHASSIS

A1 A2

ALTITUDE

DIGITIZER

B1 B2 B4 C1

SEE NOTE 9

C2 C4

ALT_COMMON

SEE NOTE 9

WX-1000 DISPLAY

SQUAT SWITCH LANDING GEAR POSITION

NOTES:

1.) ALL WIRES TO BE 22 AWG EXCEPT WHERE NOTED.

2.) TP - USE TWISTED SHIELDED PAIR CABLE.TERMI NATE SHIELDTO 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 TOTHE 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.) THESETWO 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

Page 38

Preliminary

P/O P/ O

J1 P1

A429RX8_A A429RX8_B A429RX7_A

A42RRX7_B

A429RX5_A A429RX5_B A429RX4_A

A42RRX4_B

A429RX3_A A429RX3_B A429RX2_A A429RX2_B

A429RX1_A A429RX1_B

SKY899

Installation Manual

81 82

83 84 75 76 73 74 64 65 62 63

54 55

SEE NOTE 4

SEE NOTE 2

OPTIONAL ARINC 429

XMIT

(SEE NOTES 5

AND 10)

SEE NOTE 2 SEE NOTE 2 SEE NOTE 2 SEE NOTE 2 SEE NOTE 2

OPTIONAL ARINC 429

XMIT

(SEE NOTES 5

AND 10)

OPTIONAL ARINC 429

XMIT

(SEE NOTES 5

AND 11)

OPTIONAL ARINC 429

XMIT

(SEE NOTES 5

AND 11)

OPTIONAL ARINC 429

XMIT

(SEE NOTE 5)

OPTIONAL

XPDR

ARINC 429

XT BUS

(SEE NOTE 4)

TRANSMITTER

RECEIVER

COMPUTER

UNIT

TRC899

A429TX3_A A429TX3_B A429TX2_A A429TX2_B

A429TX1_A A429TX1_B

RS422_TXA

RS422_TXB RS422_RXA RS422_RXB

RS232_TX2

RS232_RX2

RS232_GND2

ASU_MODE

ASU_SEL_ACK

ASU_MOD_ACK

J8 P8

SUPBUS

GPWS

AUDIO_H

AUDIO_L

AUDIO_C

+5V

-15V

ASU_SEL

ASU_GND

+28V

+28V_RET

SPARE

52 53 44 45

42 43

89 90 91

77 78 79 80

86 87 88

1 3 94 95 96 97 98

A B C

SEE NOTE 4

SEE NOTE 6

16 AWG

SEE NOTE 2

OPTIONAL EXTERNAL ARINC 429

DISPLAY

AIRCRAFT POWER

(18 - 32VDC)

AIRCRAFT POWER RETURN

OPTIONAL

XPDR

ARINC 429

TX BUS

(SEE NOTE 4)

CAUTION:

THE AIRCRAFT TRANSPONDER MUST HAVE SHIELDED SUPPRESSION CIRCUITRY TO ENSURE THAT SKYWATCH DOES NOT DISPLAY ITSELF AS ATARGET (TA).

SEE NOTE 6

SUPPRESSION I/O

GPWSFLAG

SEE NOTE 8

AUDIO HIGH

AUDIO COMMON

DIAG_GND

DIAG_RX

DIAG_TX

CTS RTS

SUM

(BLUE)

J10

BIT_PROBE

J11

DIFFERENCE

(RED)

5 2 3 7 8

P10

P11

DEBUG PORT

TEST ONLY

TYPE TNC

CONNECTOR

TYPE BNC

CONNECTOR

TYPE TNC CONNECTOR

SEE NOTE 3

SEE NOTE 7

TNC

BNC

TNC

SEE NOTE 3

SUM

BIT_PROBE

DIFFERENCE

NY164/NY156

DIRECTIONAL

ANTENNA

BLUE BAND

RED BAND

Figure 2-2. Interconnect Wiring Without WX-1000

(Sheet 2 of 2)

2-5 (page 2-6 blank)

Rev. A

Page 39

Preliminary

TRANSMITTER

RECEIVER

COMPUTER

UNIT

TRC899

P/O

HEADING_FLG

HEADING_C HEADING_H

HEADING_Z HEADING_Y HEADING_X

DPWR+15_OUT

DPWR-15_OUT

DSPLY_GND_OUT

HSYNC_OUT+

HSYNC_OUT-

VSYNC_OUT+

VSYNC_OUTVIDEO_OUT+

VIDEO_OUT-

ON/OFF

ON/OFF_RET

SFTKEY1_IN SFTKEY2_IN SFTKEY3_IN SFTKEY4_IN

DPWR+15_IN

DPWR-15_IN

DSPLY_GND_IN

HSYNC_IN+

HSYNC_IN-

VSYNC_IN+

VSYNC_INVIDEO_IN+

VIDEO_INSFTKEY1_OUT SFTKEY2_OUT SFTKEY3_OUT SFTKEY4_OUT

SMS

SMS_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

DISCRETE

OPER_MODE

LP1OUT LP2OUT

3.3V

PLUG_GND

SDA

SCL

51 50 49 48 47 46

8 9 10 11 12 13 22 16 17 4 5 18 19 20 21

25 26 27 28 29 30 41 35 36 37 38 39 40

56 57 58 59 60 61 67 68 69 70 71 72 24 33 6 7 14

66 85

2 92 99 100

N/C

SEE

NOTE 6

TP BLK

SEE NOTE 13

ORN

BLU

WHT

BLU

ORN

RED

GRN

BLKTP

YEL

WHT

BLUTP

ORN

RED

YEL

N/C

PERSONALITY PLUG

3.3V PLUG_GND SDA SCL

BLU WHT BLU WHT BLU

ORN

WHT

ORN

BLU

WHT

BLU

WHT

BLU

WHT

BLU

WHT

BLU

WHT

BLU

WHT

BLU

WHT

ORN

BLU

WHT

BLU

WHT

BLU

WHT

BLU

WHT

BLU

WHT

BLU

DISCRETE I/O SEE NOTE 4

LAMP, SEE NOTE 16

LAMP ABV

LAMP BLW

HEADING INPUT CABLE

SEE NOTE 6

SW1

HIGH LOW VAL ID F LAG

RADIO ALT

SEE NOTE 9

STORMSCOPE

DC ANALOG ALT

}

SEE NOTE 12

}

INSIDE CONNECTOR BACKSHELL

SKYWATCH

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.

Installation Manual

DISPLAY CABLE

OVER-RIDE

SW2

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 INSTALLEDTO 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 THEWX-1000 ARE DETAILED IN THE

16.) OPTI ONAL, MAY BE USED TO DRIVE INDICATOR DEPICTING OPERATIONAL MODE.

NORMAL

SKY899

SEE NOTE 6

BLU WHT

BLU WHT BLU

ORN

WHT

SEE NOTE 6

AND NOTE 14

WHT ORN

BLU

WHT

BLU

WHT

BLU

WHT

BLU

WHT

BLU

WHT

BLU

WHT

BLU

SEE NOTE 6

AND NOTE 14

WHT ORN

BLU

WHT

BLU

WHT

BLU

WHT

BLU

WHT

BLU

WHT

BLU

WHT

BLU

N/C N/C N/C N/C N/C N/C N/C N/C

ORN

BLU

WHT

BLU

ORN

RED

GRN

BLK

YEL

WHT

BLU

ORN

RED

GRN

BLK

YEL

DIRECTIONAL GYRO COMPASS

N/C

HEADING VALID

LOW

}

HIGH Z

HEADING

}

P101 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

CHASSIS

P301 J301

+15

-15

DSPGND

HSYNCHI

HSYNCLO

VSYNCHI

VSYNCLO

VIDEOHI

VIDEOLO

PWRSWHI

PWRSWLO

SFTKEY1

SFTKEY2

SFTKEY3

SFTKEY4

SHIELD

A1 A2 A4 B1 B2 B4 C1 C2 C4 D2 D4 ALT_COMMON

SEE NOTE 9

26 VAC REFERENCE

ALTITUDE DIGITIZER

WX-1000 DISPLAY

WX-1000

PROCESSOR

SEE NOTE 15

SQUAT SWITCH LANDING GEAR POSITION

Figure 2-3. Interconnect Wiring With WX-1000

(Sheet 1 of 2)

2-7 (page 2-8 blank)

Rev. A

Page 40

Preliminary

P/O P/ O

J1 P1

A429RX8_A A429RX8_B A429RX7_A

A42RRX7_B

A429RX5_A A429RX5_B A429RX4_A

A42RRX4_B

A429RX3_A A429RX3_B A429RX2_A A429RX2_B

A429RX1_A A429RX1_B

SKY899

Installation Manual

81 82 83 84 75 76 73 74 64 65 62 63

54 55

SEE NOTE 4

SEE NOTE 2

OPTIONAL ARINC 429

XMIT

(SEE NOTES 5

AND 10)

SEE NOTE 2 SEE NOTE 2 SEE NOTE 2 SEE NOTE 2 SEE NOTE 2

OPTIONAL ARINC 429

XMIT

(SEE NOTES 5

AND 10)

OPTIONAL ARINC 429

XMIT

(SEE NOTES 5

AND 11)

OPTIONAL ARINC 429

XMIT

(SEE NOTES 5

AND 11)

OPTIONAL ARINC 429

XMIT

(SEE NOTE 5)

OPTIONAL

XPDR

ARINC 429

XT BUS

(SEE NOTE 4)

TRANSMITTER

RECEIVER

COMPUTER

UNIT

TRC899

A429TX3_A A429TX3_B A429TX2_A A429TX2_B

A429TX1_A A429TX1_B

RS422_TXA

RS422_TXB RS422_RXA RS422_RXB

RS232_TX2

RS232_RX2

RS232_GND2

ASU_MODE

ASU_SEL_ACK

ASU_MOD_ACK

J8 P8

SUPBUS

GPWS

AUDIO_H

AUDIO_L

AUDIO_C

+5V

-15V

ASU_SEL

ASU_GND

+28V

+28V_RET

SPARE

52 53 44 45

42 43

89 90 91

77 78 79 80

86 87 88

1 3 94 95 96 97 98

A B C

SEE NOTE 4

SEE NOTE 6

16 AWG

SEE NOTE 2

OPTIONAL EXTERNAL ARINC 429

DISPLAY

AIRCRAFT POWER

(18 - 32VDC)

AIRCRAFT POWER RETURN

OPTIONAL

XPDR

ARINC 429

TX BUS

(SEE NOTE 4)

CAUTION:

THE AIRCRAFT TRANSPONDER MUST HAVE SHIELDED SUPPRESSION CIRCUITRY TO ENSURE THAT SKYWATCH DOES NOT DISPLAY ITSELF AS ATARGET (TA).

SEE NOTE 6

SUPPRESSION I/O

GPWSFLAG

SEE NOTE 8

AUDIO HIGH

AUDIO COMMON

DIAG_GND

DIAG_RX

DIAG_TX

CTS RTS

SUM

(BLUE)

J10

BIT_PROBE

J11

DIFFERENCE

(RED)

5 2 3 7 8

P10

P11

DEBUG PORT

TEST ONLY

TYPE TNC

CONNECTOR

TYPE BNC

CONNECTOR

TYPE TNC CONNECTOR

SEE NOTE 3

SEE NOTE 7

TNC

BNC

TNC

SEE NOTE 3

SUM

BIT_PROBE

DIFFERENCE

NY164/NY156

DIRECTIONAL

ANTENNA

BLUE BAND

RED BAND

Figure 2-3. Interconnect Wiring With WX-1000

(Sheet 2 of 2)

2-9 (page 2-10 blank)

Rev. A

Page 41

Preliminary

TRANSMITTER

RECEIVER

COMPUTER

UNIT

P/O P/O

J1 P1

HEADING_FLG

HEADING_C

HEADING_H

HEADING_Z HEADING_Y HEADING_X

SKY899

Installation Manual

N/C

51 50

49 48 47 46

ORN

BLU

WHT

SEE NOTE 6

BLU

WHT

BLU

WHT

BLU ORN WHT

HEADING INPUT CABLE

SEE NOTE 6

BLU WHT BLU WHT BLU ORN WHT

ORN

BLU

WHT

DIRECTIONAL GYRO COMPASS

N/C

HEADING VALID

LOW

}

HIGH Z Y

}

SEE NOTE 9

26 VAC REFERENCE

HEADING

TRC899

DSPLY_GND_OUT

SFTKEY1_IN SFTKEY2_IN SFTKEY3_IN SFTKEY4_IN

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

DISCRETE

OPER_MODE

LP1OUT

LP2OUT

3.3V

PLUG_GND

SDA SCL

10 18 19 20 21

4 5 56 57 58 59 60 61 67 68 69 70 71 72 24 33 6 7 14

66 85

2 92 99 100

BLKTP

YEL

SEE NOTE 13

BLU N/C BLU

WHT

BLU

DISCRETE I/O SEE NOTE 4

N/C

PERSONALITY PLUG

3.3V PLUG_GND SDA SCL

LAMP, SEE NOTE 14

LAMP ABV

LAMP BLW

SEE NOTE 12

}

INSIDE CONNECTOR BACKSHELL

DISPLAY_GND_OUT

TEST/ALT RANGE

"OFF"

"ON" 3A @ 28VDC

HIGH

}

LOW VAL ID F LAG

RADIO ALT

SEE NOTE 9

DC ANALOG ALT

STBY/OPER

A1 A2

ALTITUDE

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 DI FFERENCE 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 USEDTHEN 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)

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P/O P/ O

J1 P1

SKY899

Installation Manual

TRANSMITTER

RECEIVER

COMPUTER

UNIT

A429RX8_A A429RX8_B A429RX7_A

A42RRX7_B

A429RX5_A A429RX5_B A429RX4_A

A42RRX4_B

A429RX3_A A429RX3_B A429RX2_A A429RX2_B

A429RX1_A A429RX1_B

A429TX3_A A429TX3_B A429TX2_A A429TX2_B

A429TX1_A A429TX1_B

SUPBUS

GPWS

AUDIO_H

AUDIO_L

AUDIO_C

81 82 83 84 75 76 73 74 64 65 62 63

54 55

52 53 44 45

42 43

89 90 91

SEE NOTE 4

SEE NOTE 2

SEE NOTE 6

OPTIONAL ARINC 429

XMIT

(SEE NOTES 5

AND 10)

EXTERNAL ARINC 429

DISPLAY

SEE NOTE 2 SEE NOTE 2 SEE NOTE 2 SEE NOTE 2 SEE NOTE 2

OPTIONAL ARINC 429

XMIT

(SEE NOTES 5

AND 10)

SEE NOTE 2

OPTIONAL

XPDR

ARINC 429

TX BUS

(SEE NOTE 4)

OPTIONAL ARINC 429

XMIT

(SEE NOTES 5

AND 11)

OPTIONAL ARINC 429

XMIT

(SEE NOTES 5

AND 11)

OPTIONAL ARINC 429

XMIT

(SEE NOTE 5)

CAUTION:

OPTIONAL

XPDR

ARINC 429

XT BUS

(SEE NOTE 4)

THE AIRCRAFT TRANSPONDER MUST HAVE SHIELDED SUPPRESSION CIRCUITRY TO ENSURE THAT SKYWATCH DOES NOT DISPLAY ITSELF AS ATARGET (TA).

SEE NOTE 6

SUPPRESSION I/O

GPWSFLAG

SEE NOTE 8

AUDIO HIGH

AUDIO COMMON

TRC899

RS422_TXA

RS422_TXB RS422_RXA RS422_RXB

RS232_TX2

RS232_RX2

RS232_GND2

ASU_MODE

ASU_SEL_ACK

ASU_MOD_ACK

J8 P8

+28V_RET

DIAG_GND

DIAG_RX

DIAG_TX

CTS RTS

SUM

(BLUE)

J10

BIT_PROBE

J11

DIFFERENCE

(RED)

+5V

-15V

ASU_SEL

ASU_GND

+28V

SPARE

5 2 3 7 8

P10

P11

77 78 79 80

86 87 88

1 3 94 95 96 97 98

A B C

DEBUG PORT

TEST ONLY

TYPE TNC

CONNECTOR

TYPE BNC

CONNECTOR

TYPE TNC CONNECTOR

SEE NOTE 4

SEE NOTE 2

SEE NOTE 3

16 AWG

SEE NOTE 7

AIRCRAFT POWER

(18 - 32VDC)

AIRCRAFT POWER RETURN

SEE NOTE 3

SUM

TNC

BIT_PROBE

BNC

DIFFERENCE

TNC

NY164/NY156

DIRECTIONAL

ANTENNA

BLUE BAND

RED BAND

Figure 2-4. Interconnect Wiring with

Alternate Display (Sheet 2 of 2)

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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.

Panel Depth 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.

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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:

• 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.

• 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).

• 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.

• 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.

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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.)

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:

Sum (Sigma) Port 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.

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 1-

6) 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.

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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.

The synchro cable consists of the following (refer to figure 2-5):

1. Twisted, Shielded, Jacketed Triad #24 AWG Colors: White, Blue, Orange Shield: Tin Plated Copper Braid, 90% min. Jacket: FEP .007 in. min., White

2. Twisted, Shielded, Jacketed Pair #24 AWG Colors: White, Blue Shield: Tin Plated Copper Braid, 90% min. Jacket: FEP .007 in. min., Blue

3. Same as Item 2, except Orange jacket.

4. Aluminized Mylar® Wrap.

5. #34 AWG braided shield.

6. FEP Teflon® jacket .013 in. - .023 in., clear (translucent).

7. Marker tape with vendor P/N.

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.

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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.

For alternate display device cable see ARINC-429 data cable (par. 2.6.3) and refer to figure 2-4 for connections.

The display cable consists of the following (refer to figure 2-6).

1. 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.

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Figure 2-6. Display Cable

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.

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."

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

• 7 ARINC-429 RX channels

• 3 ARINC-429 TX channels

• System Configuration Module

(configure system in service menu)

• Heading valid, 1 input pin (low/high level selected in service menu)

• Analog radio altimeter

• 18 - 32 V dc power input

• ADS-B (requires mode S transponder address)

• Altimeter Gilham Code "D2" added

(do not connect if not available)

• Lamp Outputs - above, below and oper_mode (used with alternate display)

• Transponder input/output

• Stepper (heading) not available

NOTE

TRC497

2 ARINC-429 RX channels

1 ARINC-429 TX channel

Individual configuration pins

Heading valid, 2 input pins (low or high level)

Not available

11 - 34 V dc power input

Not available

Altimeter Gilham Code "D2" not available

Not available

Stepper (heading) available

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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.

2. If the aircraft is not equipped with terrain warning system, leave this input unconnected.

Audio inhibit connection:

GPWS P1-34

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).

Landing gear connection:

GEAR P1-33

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/

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:

Stormscope

SMS P1-15 SMS_RET P1-23

Mode Switch

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).

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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.

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.

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.

ON/OFF

2.7.5

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.

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:

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.

Power Switch

ON/OFF P1-4 ON/OFF_RET P1-5

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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.

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:

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.

ARINC-429 General Sensor Input connections:

A429RX1_A (P1-54) A429RX1_B (P1-55) A429RX2_A (P1-62) A429RX2_B (P1-63)

A429RX3_A (P1-64) A429RX3_B (P1-65) A429RX4_A (P1-73) A429RX4_B (P1-74)

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)

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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 DRIVER NAME

DISPLAY RANGES

STANDBY

RANGE

SELF-TEST

RANGE

REMARKS

None - - - No alternate display connected must use WX-

Standard Type 1 2, 6, 15 nmi 15 nmi 6 nmi

Standard Type 2 6, 12, 20 nmi 12 nmi 6 nmi

Standard Type 3 5, 10, 20 nmi 10 nmi 5 nmi

Sextant Type 1 6, 12, 24 nmi 12 nmi 6 nmi Displays unrestricted mode, must use external lamps to

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

Forestry Serv 2, 5, 10, 20 nmi 10 nmi 5 nmi

Collins EFIS Type 1 5, 10, 25 nmi 10 nmi 5 nmi Sends only 8 most threatening intruders to display.

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.

1000/SKY497 display.

annunciate UNR mode.

EFIS changes ranges internally.

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 P1-89 (600 Ohm) AUDIO_L P1-90 (150 Ohm) AUDIO_C P1-91 (Audio Common)

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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.

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.)

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.

Altitude encoder connections:

A1 -to- P1-56 B1 -to- P1-59 C1 -to- P1-67 D2* -to- P1-70 A2 -to- P1-57 B2 -to- P1-60 C2 -to- P1-68 D4 -to- P1-71 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

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.

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Synchro (XYZ) heading connections:

HEADING_X P1-46 (Synchro X) HEADING_Y P1-47 (Synchro Y) HEADING_Z P1-48 (Synchro Z) HEADING_H P1-49 (26 V ac High) HEADING_C P1-50 (26 V ac Low) HEADING_FLG 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.

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.

Lamp connections:

LP1OUT P1-66 (ABV) LP2OUT P1-85 (BLW)

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

(Normal)

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

ABV BLW

(Above)

ABV BLW

(Below)

ABV BLW

(Unrestricted)

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.

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Power connection:

+28V P8-A

+28V_RET P8-B SPARE 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.

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).

Analog radio altitude connections:

RAD_ALT_IN_HI P1-6 (High) RAD_ALT_IN_LO P1-7 (Low) RAD_ALT_FLG P1-14 (Valid Flag)

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 P7-5 DIAG_RX P7-2 DIAG_TX P7-3 CTS P7-7 RTS 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

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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).

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).

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:

System Configuration Module TRC899

Red (VCC) -to- P1-2 (+3.3V) Black (Ground) -to- P1-92 (PLUG_GND) Green (Serial Clock) -to- P1-100 (SCL) Yellow (Serial Data) -to- P1-99 (SDA)

TO P1-2 (+3.3V) TO P1-92 (PLUG_GND) TO P1-100 (SCL) TO P1-99 (SDA)

Figure 2-8. System Configuration Module

NOTE

TERMINAL P/N M39029/56-348

RED BLACK GREEN YELLOW

CONFIG MODULE

P/N 814-18005-001

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SPLIT ELBOW

90° BACKSHELL

P/N 814-18005-001

(located inside backshell)

P/N 613-10043-001

CONFIGURATION MODULE

.BFGoodrich Avionics Systems, INC. C N I

, s

m e t

s y

S s c

n o i

v A

h c i r

d o

- a r

0 i f

4 C

Configuration Module

1 8

N /

P/N 814-18005-001

NOT TO SCALE

100 PIN CONNECTOR

P/N 605-10251-001

Figure 2-9. Typical Location of System Configuration Module (Inside Backshell)

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.

Table 2-2. WX-1000/SKY497 Display Connection

Display WIRE COLOR TRC

FUNCTION P101 SUB-CABLE WIRE P1

(Inner Jackets) 2

DPWR+15_OUT 19 WHITE WHITE P1-8

DPWR-15_OUT 14 WHITE ORANGE P1-9

DSPLY_GND 18 WHITE BLUE P1-10

HSYNC_OUT_HI 6 BLUE BLUE P1-11

HSYNC_OUT_LO 5 BLUE WHITE P1-12

VSYNC_OUT_HI 9 ORANGE WHITE P1-13

VSYNC_OUT_LO 10 ORANGE BLUE P1-22

VIDEO_OUT_HI 8 RED WHITE P1-16

VIDEOOUT_LO 7 RED BLUE P1-17

PWR_SW_HI 22 (SW2*) GREEN WHITE P1-4

PWR_SW-LO 23 (SW2*) GREEN BLUE P1- 5

SFTKEY1_IN 13 BLACK WHITE P1-18

SFTKEY2_IN 12 BLACK BLUE P1-19

SFTKEY3_IN 25 YELLOW WHITE P1-20

SFTKEY4_IN 24 YELLOW BLUE P1-21

*SW2 required if WX-1000 Processor installed (see figure 2-2).

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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

FUNCTION WX-1000 Processor SUB-CABLE WIRE TRC899

SHIELD P301-5

PWRSWHI P301-21 GREEN WHITE SW2*

PWRSWLO P301-20 GREEN BLUE SW2*

+15 P301-3 WHITE WHITE P1-25

-15 P301-36 WHITE ORANGE P1-26

DSPGND P301-38 WHITE BLUE P1-27

HSYNCHI P301-6 WHITE BLUE P1-28

HSYNCLO P301-23 BLUE WHITE P1-29

VSYNCHI P301-40 ORANGE WHITE P1-30

VSYNCLO P301-7 ORANGE BLUE P1-41

VIDEOHI P301-22 RED BLUE P1-35

VIDEOLO P301-39 RED WHITE P1-36

SFTKEY1 P301-9 BLACK WHITE P1-37

SFTKEY2 P301-26 BLACK BLUE P1-38

SFTKEY3 P301-43 YELLOW WHITE P1-39

SFTKEY4 P301-44 YELLOW BLUE P1-40

*SW2 required if WX-1000 Processor installed (see figure 2-2).

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.

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.

NOTES

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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.

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2. 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.

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Figure 2-12. Mounting Holes for Standard Mounting Tray, P/N 805-10870-001

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Figure 2-13. Mounting Holes for Ruggedized Mounting Tray, P/N 805-10870-003

2.26 TRC INSTALLATION

CAUTION

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.

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INTERCONNECT

(I/O SIGNAL)

POWER

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)

(

)

(

)

(

MOUNTING TRAY

2-34 Rev. A

RETAINER CUPS

(2 PLACES)

HOLD-DOWN KNOBS

(2 PLACES)

Figure 2-14. TRC899 Installation

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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.

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

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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

MOORING PLATE (NOT SUPPLIED)

DISPLAY

REAR MOUNT

6-32 X 3/4 PHMS

(QTY 4)

FRONT MOUNT

Figure 2-16. Display Installation

Use rivnuts® or a mooring clamp to secure the display to the instrument panel.

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

AIRCRAFT PANEL

MOORING PLATE (NOT SUPPLIED)

DISPLAY

NOTE

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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.

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.

This procedure will validate the installation and return to service of the SKY899.

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.

BRT

OFF

OFF/BRT

Switch

Figure 3-1. Controls

Power is applied by rotating the knob clockwise past the detent. Continued clockwise rotation increases display brightness.

1, 2, 3, & 4

Pushbuttons

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.

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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

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. 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.

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).

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.

NOTE

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BRT

OFF

SKY899

Standby

OPRMSG

TEST

Figure 3-3. Standby Screen

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.

System Configuration (via Service Menu)

1. 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:

a. 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.

WARNING

Verify displayed antenna position matches antenna location on the aircraft (top or bottom). Failure to do so could give incorrect traffic bearing.

4. 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.

5. 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.

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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.

c. Select exit until you return to Setup Menu.

6. From the Setup menu, select Avionics Equipment:

a. The Equipment menu will appear, select Browse All Avionics.

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.

b. 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.)

7. From the Service Menu, select Calibration:

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.

8. 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.

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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.

5. 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).

10. Select the NRM (normal) mode.

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.

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).

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.

NOTE

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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 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

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.

k. 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).

PAT C H

ANTENNA

ASSEMBLY

TRIPOD ASSEMBLY

(OPTIONAL -

NOT INCLUDED)

COAX

CABLE

Figure 3-4. Typical Patch Antenna Tripod Mount

LINK

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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.

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. Set the TT391 POWER switch to the OFF. Repeat procedure from each test point. Step 15 can

be done from the last test point.

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.

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.

After power up, it may take a couple of minutes for the altitude encoder to return a valid altitude to the transponder and SKY899.

NOTE

b. If installed, power up the radio altimeter.

c. Make sure all compass/HSI flags are cleared from the aircraft's instruments.

2. Turn SKY899 ON. The display should show a start-up screen similar to one shown in figure 3-2.

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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.

BRT

OFF

Figure 3-5. Self Test Screen

5. 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:

a. Check headphones/speaker and aircraft audio panel switch settings.

NOTE

Audio levels can be 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.

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.

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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.

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

1. Check that indicator cable is properly mated and secured.

2. Check to ensure unit is properly placed and secured to the instrument panel.

CAUTION

Do not use cleaning solvents on the viewing face.

3. 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

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.

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.

CAUTION

3. Visually inspect sealant around the antenna base. Reapply sealant if required.

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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.).

Service Menu

1 Setup 2 Information 3 Calibration 4 Ground Test 5 Configuration Management

x Exit

Figure 4-1. Service Menu (Terminal Emulation Program)

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.

BRT

OFF

SERVICE MENU

Setup

Information Calibration Ground Test Configuration Management

EXIT

Figure 4-2. Service Menu (WX-1000/SKY497 Display)

Ground Test is available only if squat switch input indicates aircraft is on the ground.

SEL

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.

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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

Setup

Aircraft Type

Antenna Sytem Audio Level Communications Ports Avionics Equipment

OFF

SEL

OFF

BRT

Screen appears when exiting Setup menu and changes have been made

EXIT

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.

Save or Revert

Changes have been made!

Save Changes

Revert to Old Settings

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.

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The Aircraft Type menu provides the following choices:

Aircraft Type

*None*

Fixed Wing Rotorcraft

OFF

BRT

EXIT

SEL

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."

The Antenna System menu provides the following choices:

BRT

Antenna System

Top Antenna

*NY156 Directional* Bottom Antenna [None]

EXIT

OFF

SEL

Selecting Top Antenna (or Bottom Antenna) provides the following choices:

4-4 Rev. A

BRT

OFF

Top Antenna

None

NY164 Directional *NY156 Directional*

EXIT

SEL

(Bottom Antenna menu is same as Top Antenna menu)

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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

Audio Level

Volume

[50%]

Down Test

OFF

EXIT

SEL

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

Please wait... will be displayed while autodetect is being performed

SEL

Receiver menu shows the 5 RX channels, the 429 source and the speed. To change individual channel, highlight desired channel and press SEL.

Arinc 429 Receivers

Autodetect

Ch. 1: Multi 100 kHz Ch. 2: None 100 kHz

Ch. 3: None Auto Ch. 4: None Auto

Ch. 5: None Auto

EXIT

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.

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Selecting any channel (ch.1 thru ch.5) will cause that individual Rx channel menu to appear:

BRT

Arinc 429 Rx Ch 1

Type:

Speed: 100 kHz

ADC GPS

OFF

EXIT

SEL

Selecting Type will cause the Equipment Type menu to appear:

Equipment Type

None

*ADC* AHRS

*GPS*

Rad Alt

EXIT

OFF

SEL

Selecting Speed will cause the Speed menu to appear:

Speed

12.5 kHz

100 kHz

OFF

BRT

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.

BRT

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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

Equipment

Browse All Avionics

GPS Nav [Gama] Magnetic Heading [None] Barometric Altitude [None]

EXIT

OFF

SEL

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:

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]

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

EXIT

The Avionics Equipment sub-menus are as follows.

The GPS Nav menu provides the following choices:

*None*

GAMA ARINC 743A

EXIT

GPS Nav

SEL

OFF

BRT

This Menu appears when ARINC 429 equipment has been selected, but was not assigned to a channel via the Communication Ports Menu

BRT

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The Magnetic Heading menu provides the following choices:

Magnetic Heading

*None*

Synchro Compass AHRS

OFF

BRT

EXIT

SEL

Selecting Synchro Compass causes Heading Valid Line menu to appear:

BRT

OFF

Heading Valid Line

*None*

Valid Low Valid High

EXIT

SEL

The Barometric Altitude menu provides the following choices:

BRT

Barometric Altitude

*None*

ADC Encoding Altimeter

OFF

EXIT

Selecting ADC will cause the ADC menu to appear:

*None*

ARINC 429

EXIT

4-8 Rev. A

ADC

SEL

OFF

BRT

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The Radio Altimeter menu provides the following choices:

Radio Altimeter

*None*

Arinc429 Arinc 552 Arinc 552A Bonzer Mark 10X Collins ALT-50 Collins ALT-55

EXIT

SEL

OFF

BRT

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

Selecting a DC analog radio altimeter will cause Rad Alt Valid Line menu to appear:

BRT

Rad Alt Valid Line

*None*

Valid Low Valid High

EXIT

OFF

SEL

The Landing Gear menu provides the following choices:

BRT

Landing Gear

*None*

Valid Low Valid High

EXIT

OFF

SEL

The Weight-On-Wheels (squat switch) menu provides the following choices:

Weight-On-Wheels

*None*

Valid Low Valid High

EXIT

SEL

OFF

BRT

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The Audio Suppression menu provides the following choices:

Audio Suppression

*None*

Valid Low Valid High

OFF

BRT

EXIT

SEL

The External Display menu provides the following choices:

BRT

OFF

Using Next button to scroll down will cause these additional menu choices to appear one at a time.

Forestry Serv Collins EFIS Type1

SEL

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.

External Display

*None*

Standard Type1 Standard Type2 Standard Type3 Sextant Type1 Sextant Type2 Sextant CG

EXIT

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

Software Version

System Log Data Monitor

EXIT

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SEL

OFF

BRT

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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

Software Version

SKYHP Vx.x

EXIT

OFF

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).

The System Log displays the results in the following format:

BRT

OFF

With an Error highlighted pressing SEL will cause error description to appear

SEL

Using Next button to scroll down will cause additional erros (up to 20) to appear.

System Log

24 12

/22/00 12:24:35

Software Error

MM/dd/yy hh:mm:ss

EXIT

where:

## = Error code. MM:dd:yy = Date (month, day and year) hh:mm:ss = Run-time (in hours, minutes and seconds) when error occurred.

If the System Log is empty, the following message is displayed:

NO FAULTS DETECTED

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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:

BRT

Data Monitors

ARINC 429

Antenna Calibration Barometric Altitude Discrete Values GPS Nav Mag Heading Rad Altitude

EXIT

OFF

SEL

NOTE

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.

The ARINC 429 Receivers Data Monitor screen displays the following:

BRT

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

OFF

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.

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The Antenna Calibration Data Monitor screen displays the following:

BRT

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

The Barometric Altitude Data Monitor screen displays the following:

OFF

BRT

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

OFF

The Discrete Values Data Monitor screen displays the following:

BRT

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

OFF

If ADC (ARINC-429) was selected for Barometric Altitude source in equipment menu the following data monitor will appear:

(ADC)

Validity: Valid Altitude: 1000 ft

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

EXIT

OFF

BRT

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The Mag Heading Data Monitor screen displays the following:

Magnetic Heading

*None*

Synchro Compass AHRS

OFF

BRT

EXIT

SEL

The Rad Alt Data Monitor screen displays the following:

Data Monitor Rad Alt (Arinc 429)

Validity: Valid Altitude: 4005 ft

EXIT

OFF

BRT

If DC Analog Radio Altimeter was selected in equipment menu the following data monitor will appear:

(Bonzer Mark 10X)

Sense: Active Low Validity: Valid Altitude: 39 ft

4.4.3 Calibration

NOTE

Ensure transponder is in standby while doing calibration.

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.

4-14 Rev. A

Top Antenna

Bit Phase: 131.10 degs

Bottom Antenna

Bit Phase: Invalid

EXIT

SEL

OFF

BRT

After a successful calibration, the new Bit Phase value will be displayed.

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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).

The Ground Test screen displays the following:

BRT

Ground Test

Perform Ground Test

OFF

EXIT

Selecting Perform Ground Test initializes the ground test software and displays the following:

SEL

OFF

BRT

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.

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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.

The Configuration Management screen displays the following:

BRT

Config Management

Archive to CF

Retrieve from CF Restore Factory Defaults

OFF

EXIT

SEL

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Setup

Information Calibration Ground Test Config Management

Setup

Aircraft Type

Antenna System Audio Level Communication Ports Avionics Equipment

EXIT

SERVICE MENU

SEL

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

Aircraft Type

*None*

Fixed Wing Rotor Craft

EXIT

Top Antenna

*NY156 Directional* Bottom Antenna [None]

EXIT

SEL

*None*

NY164 Directional NY156 Directional

EXIT

*None*

NY164 Directional NY156 Directional

Antenna System

Top Antenna

Bottom Antenna

SEL

Volume

[50%]

Down Test

EXIT

Audio Level

Changes have been made!

Save Changes

Revert to Old Settings

SEL

Screen appears when exiting Setup menu and changes have been made

SEL

Save or Revert

Equipment

Browse All Avionics

GPS Nav [Gama] Magnetic Heading [None] Barometric Altitude [None] Radio Altitude

SEL

[None] Landing Gear [None] Weight-On-Wheels [None] Audio Suppression [None] External Display [None]

EXIT

Avionics Equipment

submenu on sheet 2 of 3

Please wait... will be displayed while autodetect is being performed

Arinc 429 Receivers

Autodetect

Ch. 1: Multi 100 kHz Ch. 2: None 100 kHz

Ch. 3: None Auto Ch. 4: None Auto

Ch. 5: None Auto

EXIT

Type:

Speed: 100 kHz

SEL

EXIT

None

*ADC* AHRS

*GPS*

Rad Alt

Arinc 429 Rx Ch 1

Equipment Type

ADC GPS

SEL

EXIT

SEL

EXIT

12.5 kHz

100 kHz

Speed

Figure 4-3. Service Menu Tree (Sheet 1 of 3)

SEL

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from Sheet 1 of 3

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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

Menu appears when ARINC 429 equipment has been selected, but not assigned to a channel via the Communication Ports Menu

GPS Nav

*None*

GAMA ARINC 743A

EXIT

*None*

Synchro Compass AHRS

EXIT

Heading Valid Line

*None*

Valid Low Valid High

EXIT

SEL

Magnetic Heading

SEL

Barometric Altitude

*None*

ADC Encoding Altimeter

EXIT

*None*

ARINC 429

ADC

SEL

Equipment

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]

EXIT

Radio Altimeter

*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

EXIT

SEL

Audio Suppression

*None*

Valid Low Valid High

EXIT

Landing Gear

*None*

Valid Low Valid High

EXIT

Weight-On-Wheels

*None*

Valid Low Valid High

EXIT

SEL

4-18 Rev. A

EXIT

SEL

Rad Alt Valid Line

*None*

Valid Low Valid High

EXIT

SEL

Figure 4-3. Service Menu Tree (Sheet 2 of 3)

External Display

*None*

Standard Type1 Sextant Type2 Sextant CG Forestry Serv Collins EFIS Type1

EXIT

SEL

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From Service Menu Sheet 1 of 3

Information

Software Version

System Log Data Monitor

EXIT

24 12

## ## ##

EXIT

SEL

System Log

/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

SEL

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Installation Manual

SKY899 Antenna Calibration in Process... will be displayed while calibration is being performed

Calibration

Top Antenna

Bit Phase: 131.10 degs

Bottom Antenna

Bit Phase: Invalid

EXIT

With an Error highlighted pressing SEL will cause error description to appear

SEL

Ground Test

Perform Ground Test

EXIT

SEL

Config Management

Archive to CF

Retrieve from CF

Restore Factory Defaults

EXIT

SEL

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

Software Version

SKYHP Vx.x

EXIT

Data Monitors

ARINC 429

Antenna Calibration Barometric Altitude Discrete Values GPS Nav Mag Heading Rad Altitude

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

SEL

Data Monitor Rad Alt (Arinc 429)

Validity: Valid Altitude: 4005 ft

EXIT

(Bonzer Mark 10X)

Sense: Active Low Validity: Valid Altitude: 39 ft

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

Data Monitor Mag Heading (Synchro Compass)

Sense: Active Low Validity: Valid Heading: 29.877 degs

EXIT

(AHRS)

Mag Heading: 29.998 degs True Heading: 35.002 degs Status: Valid

(ADC)

Validity: Valid

Altitude: 1000 ft

Data Monitor GPS Nav (GAMA)

Lat 42.308 deg Lon -82.020 deg Trk invalid Spd invalid

EXIT

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)

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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

Display remains dark after SKY899 is powered ON.

Display is distorted.

Incorrect response to buttons (soft-keys).

SKY899 will not enter service menu.

The self-test successfully completes without audio annunciation.

SKY899 Failed.

Self-test does not execute. Aircraft is on the ground.

The display cannot be switched between SKY899 and the WX-1000. Both systems are installed.

WX-1000 processor has been removed for service; SKY899 fails to operate.

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.

Check for interference from aircraft systems.

Check soft-key wiring inside display cable and WX-1000 processor cable (if installed).

a. Check soft-key wiring.

b. If using an alternate display device the soft-key's

needed for accessing service menu from the WX1000/SKY497 display are not connected.

c. If using an alternate display service menu must be

accessed with an RS-232 terminal device by typing the menu command. (Appendix E)

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.

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

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/

mode switch (para 2.7.3 and figure 2-2).

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.

Stormscope

display

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Table 4-1. Fault Isolation (Continued)

SYMPTOM CORRECTIVE ACTION

SKY899 paints itself as a target (e.g., TA). 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.

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.

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.

Table 4-2. Installation Related Error Messages

ERROR NO. MESSAGE REMARKS

ERROR 06 I2C Bus Error a. Configuration module is present, however the BUS communication (SDA or SCL) is

incorrect check associated wiring.

b. Replace TRC.

c. Replace configuration module.

ERROR 07 Config Module Error a. Configuration module is not found check associated wiring.

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

ERROR 15 RF Angle Error a. Check directional antenna and associated cables.

ERROR 17 Mag Var Table Error a. Unable to read the compact flash information correctly, verify compact flash is inserted

Ensure transponder is in standby and DME is OFF while doing calibration

c. Cycle power and run pilot initiated self-test.

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.

into J12 correctly.

b. Try a different compact flash.

c. Replace TRC.

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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 ARINC-

429).

d. Encoded inputs can be checked from the barometric altimeter data m onitor screen (para

4.4.2.3).

e. Using the service menu, verify barometric source configuration and altitude information

(para 4.4.2.3).

f. Check wiring associated with altimeter source.

ERROR 21 GPS Input Error 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.

c. Check ARINC-429 wiring associated with GPS.

ERROR 22 Heading Input Error No heading input being received (ARINC-429 or synchro compass).

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.

d. Check wiring associated with heading input.

ERROR 23 Synchro Input Error 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).

c. If the heading signals become valid, the system will r ecover 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.

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

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

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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 805-11910-

001) or fabricated locally from the details provided in figure 4-4.

ADAPTER PLUG CONNECTIONS

JUMPER PINS FUNCTION

825DPWR+15

926DPWR-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

NOTE

APPLY LOCTITE TO THE INTERNAL THREADS

OF THE BACKSHELL PRIOR TO ASSEMBLY.

PIN INSERT VIEW

ADAPTER PLUG JUMPER INSTALLATION

100

+0.07

0.10

-0.00

CRIMP PIN

CONNECTOR

MIL # D38999/20FH35PB

JUMPER

#22 AWG WIRE

SHORTING CAP

BACKSHELL

GLENAIR #340HS002M23-2H12A

Figure 4-4. Adapter Plug Assembly

Rev. A

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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.

1. 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:

• 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.

7. Shut box and seal with reinforced tape.

8. Attach packing list to outside of box.

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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

SIGNAL CHARACTERISTICS

Altitude (Gilham Code) / These uncorrected barometric signals are Gilham code (or gray code) Encoding Altimeter Input 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.

CONNECTION Connector-Pin

P1-56 ALT_A1 P1-57 ALT_A2 P1-58 ALT_A4 P1-59 ALT_B1 P1-60 ALT_B2

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.

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

Signal Name

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SIGNAL CHARACTERISTICS

Antenna Top Directional SUM (SIGMA) Port (Blue)

CONNECTION Connector

J9 - TNC SUM

CABLE Cable attenuation must not exceed 2.5 dB, VSWR

1.5:1. Refer to paragraph 2.6.1. Impedance: 50 Ω

Antenna Top Directional BIT PROBE Port (Black)

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)

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

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 A-

2). The transmitters operate only at high speed (100 kHz).

Signal Name

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.

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.

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SIGNAL CHARACTERISTICS

ARINC-429 External Interface CONNECTION Connector-Pin (Continued) P1-54 A429RX1_A Ch. 1 line A

P1-55 A429RX1_B Ch. 1 line B P1-62 A429RX2_A Ch. 2 Line A P1-63 A429RX2_B Ch. 2 Line B P1-64 A429RX3_A Ch. 3 Line A P1-65 A429RX3_B Ch. 3 Line B P1-73 A429RX4_A Ch. 4 Line A P1-74 A429RX4_B Ch. 4 Line B P1-75 A429RX5_A Ch. 5 Line A P1-76 A429RX5_B Ch. 5 Line B P1-83 A429RX7_A Ch. 7 Line A P1-84 A429RX7_B Ch. 7 Line B P1-81 A429RX8_A Ch. 8 Line A P1-82 A429RX8_B Ch. 8 Line B

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 Audio (Alert) Output This output is directly compatible with industry standard audio panels (see paragraph 2.10).

Signal Name

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)

CONNECTION Connector-Pin

P1-89 P1-90 P1-91 (AUDIO_C) Audio Common

CABLE Minimum 22 AWG twisted shielded pair cable for

lengths up to 30 ft.

POWER 40 mW into a 600 Ω load. Audio level is adjustable

via service menu.

FREQUENCY 0 - 3.0 kHz

Audio Inhibit This input senses a terrain warning alarm and temporarily disables the (Terrain Warning System - SKY899 audible alert messages until the warning clears (see paragraph

GPWS) The input can be either a constant flag signal or an alternating flag

LOAD Z Selectable 150 or 600 Ω

2.7.1).

output. The flag must be cleared for five (5) seconds before the TRC accepts a "NO ALARM" condition and restores audible alerts.

AIRCRAFT IS NOT EQUIPPED WITH TERRAIN WARNING SYSTEM

INPUT UNCONNECTED

If the aircraft is equipped with terrain warning system (GPWS), it must be connected to the TRC.

NOTE

Signal Name (AUDIO_H) - 600 Ω (AUDIO_L) - 150 Ω

IF THE

, LEAVE THIS

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SIGNAL CHARACTERISTICS

CONNECTION Connector-Pin

P1-34 (GPWS) CABLE Minimum 22 AWG wire for lengths up to 30 ft. VOLTAGE WARNING: 0 V dc to +2.5 V dc (Aircraft Ground).

NO WARNING: +9 V dc to +30 V dc or open. CURRENT <5 mA sourced.

Debug Port

Heading Input These connections from the aircraft heading source (ARINC 407 & 407-1 (XYZ Synchro) Synchro System Manual) allow the unit to rotate the displayed data as the

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 19,200

Parity: None

Data Bits 8

Stop Bits 1 No handshaking

CONNECTION Connector-Pin

J7-2 DIAG_RX

J7-3 DIAG_TX

J7-5 DIAG_GND

J7-7 CTS

J7-8 RTS

aircraft turns. See Heading Flag in this appendix for flag input specifications.

X(S1), Y(S3), Z(S2)

FREQUENCY Min: 50 Hz Max: 1500 Hz VOLTAGE

Min: 5.0 V ac rms (w/reduced angular resolution.) Max: 14.0 V ac rms (external padding required for

INPUT IMPEDANCE >50 kΩ

Signal Name

higher levels.)

A-4 Rev. A

CONNECTION Connector-Pin

P1-46 HEADING_X

CABLE See paragraph 2.6.4.

H and C (high and low reference)

FREQUENCY Min: 50 Hz

VOLTAGE Min: 3 V ac rms

INPUT IMPEDANCE >50 kΩ

CONNECTION Connector-Pin

CABLE See paragraph 2.6.4.

P1-47 HEADING_Y P1-48 HEADING_Z

Max: 1500 Hz

Max: 35 V ac rms

P1-49 HEADING_H P1-50 HEADING_C

Signal Name

Spec says 400 Hz ±20%

Signal Name