Traffic Alert/Advisory System

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 revisions, Service
Bulletins, and Service Memos.

009-11900-001 (Rev. B)

L-3 Avionics Systems 01 April 2003

nd
5353 52 Street, S.E.
Grand Rapids, MI USA 49512
 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 TT391 Flightline Tester.

Chapter 4 – Maintenance
This chapter contains general flightline maintenance procedures. It includes periodic maintenance,
troubleshooting, 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.

© Copyright 2001-2002
L-3 Avionics Systems
____________________________
Trademarks

Alodine® is a registered trademark of Amchem Products, Inc.

Flamemaster® is a registered trademark of Flamemaster.
HyperTerminal® is a registered trademark of Hilgraeve, Inc.
Mylar® and Teflon® are registered trademarks of DuPont.
Procomm® is a registered trademark of Datastorm Technologies, Inc.
SKYWATCH® HP and Stormscope® are registered trademarks of L-3 Avionics Systems

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Rev. B
 SKY899
Installation Manual

LIST OF EFFECTIVE PAGES

Dates of original and changed pages are: Original (Rev. A) ..................4 September 2001
Revision B.................................... 01 April 2003

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

Title Page A-1 thru A-16

A Page B-1 thru B-4
i thru viii C-1 thru C-6
1-1 thru 1-22 D-1 thru D-6
2-1 thru 2-38 E-1 thru E-2
3-1 thru 3-10 F-1 thru F-6
4-1 thru 4-28

REVISION B HIGHLIGHTS

Revision “B” is a republication. This republication completely replaces the existing book. It incorporates the
basic manual and all previous changes. New and revised material has been added, including:
• Updated the environmental qualification form.
• Clarification of the antenna calibration data monitor screen.
• Steps to verify that data were saved to the configuration module.
• Additional information relating to the ARINC 429 data monitor displays.
• An updated interconnect wiring diagram to clarify connection to the configuration module.

This revision will be kept current by change notices. As you receive change notices, replace changed pages
with the corresponding numbered page. A new list of effective pages will be issued with each change. The
list shall reflect the current changes in addition to the tabulation of all previous changes, thus providing a
complete history of the manual.

Discard previous editions of the publication.

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 SKY899
Installation Manual

FOREWORD

This manual provides information intended for use by persons who, pursuant to current regulatory
requirements, are qualified to install this equipment. Because installations vary depending on a particular
aircraft, this manual is intended as a guideline. This manual assumes familiarity with the setup and
operation of the aircraft systems that interface with the SKY899. Standard installation practices
prescribed in FAA Advisory Circular No. 43.13 must be followed. If further information is required, contact:

L-3 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:

L-3 Avionics Systems

Attn: Technical Publications
5353 52nd Street, S.E.
Grand Rapids, MI USA 49512

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TABLE OF CONTENTS

Paragraph Page
Chapter 1
GENERAL INFORMATION
1.1 INTRODUCTION .................................................................................................................................. 1-1
1.2 FUNCTIONAL DESCRIPTION ........................................................................................................... 1-2
1.3 PHYSICAL DESCRIPTION.................................................................................................................. 1-3
1.3.1 TRC899 Transmitter Receiver Computer P/N 805-11900-xxx............................................................ 1-5
1.3.2 System Configuration Module P/N 814-18005-001.............................................................................. 1-9
1.3.3 Display (Alternate or WX-1000/SKY497 Display P/N 78-8060-5900-x) ........................................... 1-10
1.3.4 Directional Antenna (NY156 P/N 805-10003-001 or NY164 P/N 805-10890-001) ........................... 1-12
1.4 SPECIFICATIONS .............................................................................................................................. 1-14
1.4.1 Transmitter Receiver Computer (TRC) .............................................................................................. 1-14
1.4.2 WX-1000/SKY497 Display................................................................................................................... 1-15
1.4.3 Directional Antenna ............................................................................................................................ 1-15
1.5 MODIFICATIONS & SOFTWARE REVISIONS............................................................................... 1-15
1.6 INTERFACE ........................................................................................................................................ 1-16
1.7 EQUIPMENT REQUIRED BUT NOT SUPPLIED ........................................................................... 1-16
1.8 INSTALLATION APPROVAL ............................................................................................................ 1-21

Chapter 2
INSTALLATION
2.1 INTRODUCTION .................................................................................................................................. 2-1
2.2 UNPACKING, INSPECTION AND STORAGE .................................................................................. 2-2
2.3 ANTENNA LOCATION ........................................................................................................................ 2-2
2.4 TRC LOCATION.................................................................................................................................... 2-3
2.5 DISPLAY LOCATION ........................................................................................................................... 2-4
2.6 CABLE REQUIREMENTS AND FABRICATION ............................................................................ 2-17
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 GPWS (Audio Inhibit).......................................................................................................................... 2-22
2.7.2 Landing Gear ....................................................................................................................................... 2-22
2.7.3 Squat Switch (Weight-On-Wheels) ..................................................................................................... 2-22
2.8 ALTERNATE DISPLAY...................................................................................................................... 2-23
2.9 ARINC-429 ........................................................................................................................................... 2-23
2.9.1 General Sensor Inputs......................................................................................................................... 2-23
2.9.2 Mode S Transponder I/O (future option) ............................................................................................ 2-24
2.9.3 Alternate Display Output.................................................................................................................... 2-24
2.9.4 Future Option ...................................................................................................................................... 2-24
2.10 AUDIO (ALERT) OUTPUT................................................................................................................. 2-24
2.11 BAROMETRIC (UNCORRECTED) ALTITUDE INPUTS................................................................ 2-24
2.11.1 Gilham Code (Encoding Altimeter)..................................................................................................... 2-25
2.11.2 ARINC-429 (ADC) ............................................................................................................................... 2-25

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TABLE OF CONTENTS
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Paragraph Page
Chapter 2
INSTALLATION
2.12 GPS (ARINC-429)................................................................................................................................ 2-25
2.13 HEADING INPUT............................................................................................................................... 2-25
2.13.1 Compass Synchro (XYZ)...................................................................................................................... 2-25
2.13.2 ARINC-429 (AHRS - Attitude Heading and Reference System) ...................................................... 2-26
2.14 LAMP OUTPUTS (ABV and BLW) .................................................................................................... 2-26
2.15 OPERATIONAL MODE OUTPUT (optional) .................................................................................... 2-26
2.16 ON/OFF Power Switch........................................................................................................................ 2-26
2.17 POWER INPUT ................................................................................................................................... 2-27
2.18 RADIO ALTIMETER (optional) ......................................................................................................... 2-27
2.18.1 Analog .................................................................................................................................................. 2-27
2.18.2 ARINC-429........................................................................................................................................... 2-27
2.19 SERIAL DATA..................................................................................................................................... 2-28
2.20 SOFT-KEYS......................................................................................................................................... 2-28
2.21 SUPPRESSION BUS I/O .................................................................................................................... 2-29
2.22 SYSTEM CONFIGURATION MODULE........................................................................................... 2-29
2.23 WX-1000/SKY497 DISPLAY (OPTIONAL) ....................................................................................... 2-30
2.24 WX-1000 PROCESSOR (OPTIONAL)................................................................................................ 2-30
2.24.1 SKYWATCH/Stormscope Mode Switch .............................................................................................. 2-31
2.24.2 External Override Switch ................................................................................................................... 2-31
2.25 ANTENNA INSTALLATION ............................................................................................................. 2-31
2.26 TRC MOUNTING TRAY INSTALLATION....................................................................................... 2-32
2.27 TRC INSTALLATION......................................................................................................................... 2-34
2.28 MOUNTING THE WX-1000/SKY497 DISPLAY ............................................................................... 2-36
2.28.1 Panel Cutout ........................................................................................................................................ 2-36
2.28.2 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
3.3.1.1 System Configuration (via Service Menu) ........................................................................................... 3-3
3.3.1.2 Download System Configuration (via Compact Flash Card) .............................................................. 3-5
3.3.2 System Setup Verification and Operation ........................................................................................... 3-5
3.4 SELF TEST............................................................................................................................................ 3-8

Chapter 4
MAINTENANCE
4.1 INTRODUCTION.................................................................................................................................. 4-1
4.2 CONTINUED AIRWORTHINESS....................................................................................................... 4-1
4.3 PERIODIC MAINTENANCE ............................................................................................................... 4-1
4.3.1 WX-1000/SKY497 Display .................................................................................................................... 4-1
4.3.2 TRC ........................................................................................................................................................ 4-1
4.3.3 Antenna.................................................................................................................................................. 4-1
4.4 SERVICE MENU .................................................................................................................................. 4-2

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TABLE OF CONTENTS
(Continued)
Paragraph Page
Chapter 4
MAINTENANCE
4.4.1 Setup....................................................................................................................................................... 4-3
4.4.1.1 Aircraft Type .......................................................................................................................................... 4-4
4.4.1.2 Antenna System..................................................................................................................................... 4-4
4.4.1.3 Audio Level............................................................................................................................................. 4-5
4.4.1.4 ARINC 429 Ports ................................................................................................................................... 4-5
4.4.1.5 Avionics Equipment............................................................................................................................... 4-7
4.4.2 Information .......................................................................................................................................... 4-12
4.4.2.1 Software Version.................................................................................................................................. 4-12
4.4.2.2 System Log ........................................................................................................................................... 4-12
4.4.2.3 Data Monitor ........................................................................................................................................ 4-13
4.4.3 Calibration ........................................................................................................................................... 4-16
4.4.4 Ground Test ......................................................................................................................................... 4-17
4.4.5 Configuration Management ................................................................................................................ 4-18
4.5 TROUBLESHOOTING ....................................................................................................................... 4-23
4.6 ERROR MESSAGES ........................................................................................................................... 4-24
4.7 TRC899/WX-1000 ADAPTER PLUG .................................................................................................. 4-26
4.8 DISPOSITION OF FAILED ITEMS................................................................................................... 4-27

Appendix A
SKY899 INTERFACE SIGNAL & CABLE CHARACTERISTICS
A.1 INTRODUCTION ................................................................................................................................. A-1
A.2 ELECTRICAL CHARACTERISTICS .................................................................................................. A-1
A.3 ARINC-429 LABELS .......................................................................................................................... A-15

Appendix B
ENVIRONMENTAL QUALIFICATION FORM
B.1 TRC899 ENVIRONMENTAL QUALIFICATION FORM .................................................................. B-1
B.2 NY156 & NY164 ANTENNA 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

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

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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 Typical Vertical Display Modes and Traffic Zones .............................................................................. 1-3
1-2 SKY899 System Block Diagram ........................................................................................................... 1-4
1-3 Standard TRC Mounting Tray (P/N 805-10870-001) .......................................................................... 1-7
1-4 Ruggedized TRC Mounting Tray (P/N 805-10870-003)....................................................................... 1-8
1-5 P1 Connector Dimensions (Reference Only) ........................................................................................ 1-8
1-6 TRC899 Transmitter Receiver Computer (TRC) ................................................................................. 1-9
1-7 System Configuration Module .............................................................................................................. 1-9
1-8 WX-1000/SKY497 Display Equipment Tag ....................................................................................... 1-10
1-9 WX-1000/SKY497 Display .................................................................................................................. 1-11
1-10 NY156/NY164 Directional Antenna ................................................................................................... 1-13
2-1 Directional Antenna Mounting Location ............................................................................................. 2-3
2-2 Interconnect Wiring Without WX-1000................................................................................................ 2-5
2-3 Interconnect Wiring With WX-1000 ..................................................................................................... 2-9
2-4 Interconnect Wiring With Alternate Display .................................................................................... 2-13
2-5 Heading Input Cable ........................................................................................................................... 2-19
2-6 Display Cable....................................................................................................................................... 2-21
2-7 Above and Below External Lamps ..................................................................................................... 2-26
2-8 System Configuration Module ............................................................................................................ 2-29
2-9 Typical Location of Configuration Module (Inside Backshell).......................................................... 2-29
2-10 Antenna Mounting Holes .................................................................................................................... 2-32
2-11 Directional Antenna Installation........................................................................................................ 2-32
2-12 Mounting Holes for Standard Mount Tray, P/N 805-10870-001 ...................................................... 2-33
2-13 Mounting Holes for Ruggedized Mount Tray, P/N 805-10870-003................................................... 2-34
2-14 TRC899 Installation ............................................................................................................................ 2-35
2-15 Instrument Panel Cutout and Mounting Holes................................................................................. 2-36
2-16 Display Installation............................................................................................................................. 2-37
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.................................................................................................. 3-7
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 Setup Menu............................................................................................................................................ 4-3
4-4 Save Menu ............................................................................................................................................. 4-3
4-5 Aircraft Type Menu ............................................................................................................................... 4-4
4-6 Antenna System Menu.......................................................................................................................... 4-4

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TABLE OF CONTENTS
(Continued)

LIST OF ILLUSTRATIONS
Figure Page
4-7 Top Antenna Menu ................................................................................................................................ 4-5
4-8 Audio Level Menu .................................................................................................................................. 4-5
4-9 ARINC 429 Receivers Menu.................................................................................................................. 4-6
4-10 ARINC 429 Receiver Channel Menu .................................................................................................... 4-6
4-11 Equipment Type Menu .......................................................................................................................... 4-6
4-12 ARINC-429 Receiver Speed Menu ........................................................................................................ 4-7
4-13 Avionics Equipment Menu .................................................................................................................... 4-7
4-14 No Channel Assigned Menu.................................................................................................................. 4-7
4-15 GPS Nav Menu ...................................................................................................................................... 4-8
4-16 Heading Menu........................................................................................................................................ 4-8
4-17 Heading Valid Line Menu ..................................................................................................................... 4-8
4-18 Barometric Altitude Menu .................................................................................................................... 4-9
4-19 Radio Altimeter Menu ........................................................................................................................... 4-9
4-20 Radio Altimeter Valid Line Menu......................................................................................................... 4-9
4-21 Landing Gear Menu............................................................................................................................. 4-10
4-22 Weight-On-Wheels............................................................................................................................... 4-10
4-23 Audio Suppression Menu..................................................................................................................... 4-10
4-24 External Display Menu ....................................................................................................................... 4-11
4-25 Information Menu................................................................................................................................ 4-12
4-26 Software Version Menu ....................................................................................................................... 4-12
4-27 System Log Menu ................................................................................................................................ 4-13
4-28 Data Monitor Menu ............................................................................................................................. 4-13
4-29 ARINC 429 Receivers Data Monitor................................................................................................... 4-14
4-30 Antenna Calibration Data Monitor .................................................................................................... 4-14
4-31 Barometric Altitude Data Monitor ..................................................................................................... 4-15
4-32 Discrete Values Data Monitor............................................................................................................. 4-15
4-33 GPS Nav Data Monitor........................................................................................................................ 4-15
4-34 Mag Heading Data Monitor ................................................................................................................ 4-16
4-35 Radio Altitude Data Monitor............................................................................................................... 4-16
4-36 Antenna Calibration Menu ................................................................................................................. 4-17
4-37 Ground Test Menu............................................................................................................................... 4-17
4-38 Ground Test in Progress...................................................................................................................... 4-18
4-39 Configuration Management Menu...................................................................................................... 4-19
4-40 Compact Flash Insertion Instructions................................................................................................ 4-19
4-41 Service Menu Tree (Sheet 1 of 3) ........................................................................................................ 4-20
4-41 Service Menu Tree (Sheet 2 of 3) ........................................................................................................ 4-21
4-41 Service Menu Tree (Sheet 3 of 3) ........................................................................................................ 4-22
4-42 Adapter Plug Assembly ....................................................................................................................... 4-26

A-1 P1 Connector Pin Identifiers.............................................................................................................. A-13

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

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

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TABLE OF CONTENTS
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LIST OF ILLUSTRATIONS
Figure Page
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 ..................................................................................................................................... 1-5

1-2 TRC Installation Kit P/N 817-11900-xxx ............................................................................................. 1-6
1-3 WX-1000/SKY497 Display Installation Kit P/N 817-10802-001....................................................... 1-10
1-4 Airframe Installation Kits .................................................................................................................. 1-12
1-5 Directional Antenna Installation Kit 817-10009-xxx ........................................................................ 1-13
1-6 TRC899 Hardware Modifications ....................................................................................................... 1-15
1-7 TRC899 Software Revisions................................................................................................................ 1-16
1-8 Minimum Interface Equipment Required.......................................................................................... 1-16
1-9 Directional Antenna SIGMA and DELTA Port Cable Vendors ........................................................ 1-17
1-10 Cable to Connector Reference ............................................................................................................. 1-18
1-11 Heading Input Cable Vendors ............................................................................................................ 1-19
1-12 Display Cable Vendors ........................................................................................................................ 1-22

2-1 Soft-Key Connection Options.............................................................................................................. 2-28

2-2 WX-1000/SKY497 Display Connection............................................................................................... 2-30
2-3 WX-1000 Processor Connection .......................................................................................................... 2-30

4-1 Alternate Display Drivers................................................................................................................... 4-11

4-2 Fault Isolation ..................................................................................................................................... 4-23
4-3 Installation Related Error Messages.................................................................................................. 4-24
4-4 Informational Error Messages............................................................................................................ 4-25

A-1 Compatible Analog Radio Altimeter Specifications.............................................................................A-8

A-2 ARINC-429 Input Labels (Rx) ............................................................................................................A-15
A-3 ARINC-429 Output Labels (Tx)..........................................................................................................A-16

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 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 for the SKY899 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 a 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. If the SKY899 is connected to a WX-1000 processor and a WX-1000/SKY497
display, an alternate display can not be connected to the soft-key inputs. Having
both displays connected to the soft-key inputs could result in conflicting input
commands to the SKY899 and the WX-1000 processor.
3. For a list of compatible alernate displays refer to Service Memo 114. For
additional assistance contact Field Service Engineering at 1-800-453-0288 or 1-
616-949-6600.
4. The SKY899 does not track intruder aircraft approaching at a closure rate greater
than 1200 knots.
5. When interfacing to a weather radar indicator via the Radar Graphics Computer
Model RGC250 with Enhanced Interface or RGC350. The RGC must be installed
in accordance with the installation manual supplied with each unit.
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 F).
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. If you plan on using SKY899’s ADS-B feature in the future, when the aviation
community and the FAA have standardized ADS-B, a GPS input that is GAMA or
ARINC-743A compliant is required. At that time a software upgrade will be
required to the SKY899 in order to activate the ADS-B features.

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1.2 FUNCTIONAL DESCRIPTION
The SKYWATCH® HP SKY899 is a new generation airborne traffic alert/advisory system that
increases the active-mode surveillance range over the SKY497 system from 11 nmi to 35 nmi.
The SKYWATCH HP also has built-in hardware and software that makes it Automatic
Dependent Surveillance-Broadcast (ADS-B) ready for the future when the technology becomes
standardized. The SKY899 will be able to continuously monitor 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. In the future the SKY899 will use 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 will enhance the
traffic alert/advisory abilities by increasing the accuracy of the active-mode surveillance (when
ADS-B becomes standardized). The SKY899 will not require a mode S transponder, ADS-B
capable or otherwise to perform ADS-B surveillance.

The SKY899 advises the flight crew where to look for transponder equipped 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. The system display shows the relative position of traffic
using text, shapes (i.e., Traffic Advisory = solid circle; Other Traffic = open diamond) and colors
(if display is TCAS I compatible). Major differences between SKYWATCH and SKYWATCH HP
are listed below:

Category SKY497 SKY899

• Active ATCRBS Surveillance Range 11 nmi surveillance range 35 nmi surveillance range
• Active ATCRBS Interrogation Power Low-power interrogations High-power interrogations
• Active ATCRBS Interference Limiting No interference limiting TCAS I interference limiting
• ADS-B Surveillance None ADS-B surveillance range 50 nmi
(future option)
• Closure Rate 900 kn closure rate 1200 kn closure rate
• Antenna Configurations Single directional antenna Multiple antenna configurations via
external ASU (future option)
• Aircraft Power Input 11 V dc to 34 V dc 18 V dc to 32 V dc
• Stepper Compass Input Accepts stepper compass input Will not accept stepper compass input
• Radio Altitude Input Accepts only ARINC 429 radio Accepts both analog and ARINC 429
altitude radio altitude
• Display Ranges (WX-1000 CDU) 2 nmi and 6 nmi 'ULYHUVHOHFWDEOHUDQJHVEHWZHHQ
DQGQPLDUHDYDLODEOH
• Installation Configuration Data Connector configuration pins System configuration module
• Vertical Display Modes Normal, Above, & Below ±9,000 ft. Normal, Above, Below & Unrestricted
±9,900 ft.

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1.3 PHYSICAL DESCRIPTION
The SKY899 System consists of the following main components:
• Transmitter Receiver Computer
• System Configuration Module
• WX-1000/SKY497 Display (or alternate 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 radar. 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 35 nmi. The SKY899 does not transmit
ADS-B information, in order to transmit your aircraft position you must have a mode S
transponder capable of ADS-B interrogations.
Figure 1-1 shows the typical vertical display modes and traffic zones used to display intruding
aircraft. The SKY899 listens for traffic in a vertical zone of ±10,000 ft and a horizontal range of
up to 35 nmi. A simplified block diagram of the system and their relationships is shown in figure
1-2.

Figure 1-1. Typical Vertical Display Modes and Traffic Zones

1-3
Rev. B
 SKY899
Installation Manual

Figure 1-2. SKY899 System Block Diagram

1-4
Rev. B
 SKY899
Installation Manual
The following table identifies the components which make-up the SKY899 system.

Table 1-1. SKY899 System

COMPONENT PART NUMBER
TRC899 Transmitter Receiver Computer 805-11900-001
System Configuration Module 814-18005-001*
WX-1000/SKY497 Display (Optional) 78-8060-5900-x**
Directional Antenna
NY156 805-10003-001
NY164 805-10890-001
* System Configuration Module is included in the installation kit P/N 817-11900-xxx (see table
1-2).
** Dash numbers identify different versions (refer to para 1.4.2).

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

The TRC is mounted in a mounting tray supplied with the installation kit (see table 1-2). The
standard tray (figure 1-3) will meet the requirements for fixed wing aircraft. A ruggedized
version of the tray (figure 1-4) is required for installations in a high vibration environment.

To meet different space requirements, the I/O signal connector (P1) will accommodate either a
straight or right-angle backshell. TRC installation kits (see table 1-2) include either a straight
backshell or right-angle backshell (see figure 1-5).

1-5
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 SKY899
Installation Manual
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) 4 607-10018-001
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) 4 607-10018-001
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) 4 607-10018-001
System Configuration Module Assembly 1 814-18005-001
817-11900-004 For Installation with ruggedized tray, 2.5 inch (6.4 cm) Backshell
Consists of:
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) 4 607-10018-001
System Configuration Module Assembly 1 814-18005-001
817-11900-005 For Installation with ruggedized tray, 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) 4 607-10018-001
System Configuration Module Assembly 1 814-18005-001

1-6
Rev. B
 SKY899
Installation Manual

NOTE
DIMENSIONS ARE IN INCHES (MILLIMETERS)

3.
(97 84
MA .5)
X. 4.15
(105.4)
MAX.
3.37
(85.6) G
REAR HOLD-DOWN PINS MAX. CO
(2-PLACES)
5
1.1 .2)
(29
50
0.7 .1)
(19

RETAINER CUPS G
HOLD-DOWN KNOBS CO
(2-PLACES)
CL

0
6.7 .2)
0
(17

G
CO

.44
13 1.4)
(34 AX.
M

5
1.8 .0)
(47 X.
MA

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

1-7
Rev. B
 SKY899
Installation Manual
NOTE
DIMENSIONS ARE IN INCHES (MILLIMETERS)

D
O
E
S

4. 0.2 E S
N
O

(1 CLU

34 ) CR
T

1 D
IN

E
W
H
3.66

E
A
D
S
(93.0)
MAX.

03
1.2.6)
(30
5
0.71)
.
(19

CL
O
G G
CO

9
5.6.5)
4
(14

.36
13 .3)
9
(33 X.
MA

0
1.72)
.
(43 X.
MA

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

1.5" BACKSHELL NOTE

DIMENSIONS ARE IN INCHES (MILLIMETERS)
3.75 (95.3)
or 4.25
2.5" BACKSHELL (108.0)
4.75 (120.7) REF.
REF.

3.25
(82.6)
REF.

STRAIGHT
BACKSHELL
1.5" P/N 613-10039-001
2.5" P/N 613-10042-001 SPLIT ELBOW
90° BACKSHELL
P/N 613-10043-001

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

1-8
Rev. B
 SKY899
Installation Manual

NOTE
3.
DIMENSIONS ARE IN INCHES (MILLIMETERS) (90 56 ±0
.4 ± .03
.8) 1

2
7.6 0)
3.
(19 X.
MA
G
CO

5
4.1 4)
05.
(1

CO
G
J9

INT J1
ER
CO
NN
EC
T
J1
0

4.1
5-
(10 REF
5.4 J1
1
)

0
1.0 EF ) J
PO 8
R 5.4 WE
(2 R
04
±0.
J7
TE
52 .0)
ST
ME J
MO 12 12. .0 ±1
RY G 8
CA
RD
CO (31

5
5.6 5)
3.
(14

1.7
(43 1
.4)

CO
G

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 (see figure 1-7).
6.00 0.75
(152.4) (19.1) 0.25
REF. (6.4)

CONFIG MODULE 0.42

P/N 814-18005-001
(10.7)

Figure 1-7. System Configuration Module

1-9
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 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 may be linked together or separate depending on the capabilities of the alternate
display. When installed with only an alternate display device, a terminal device (i.e., laptop) is
required for system setup and post-installation checkout (see appendix F).
The SKY899 is designed to transmit traffic information to an 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 1-8) 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 Customer Service (1-800-453-0288 or 1-616-949-6600) for details.

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

NOTE
The original Stormscope® WX-1000 display (P/N 78-8051-9170-3) has not been
approved for use with the SKY899. Contact Customer Service (1-800-453-0288 or 1-
616-949-6600) for replacement options.
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 1-9
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)

1-10
Rev. B
 SKY899
Installation Manual

NOTE
DIMENSIONS ARE IN INCHES (MILLIMETERS)

(9 .89
8)
3
8.
3.37 3.18
CL
(85.6) (80.8)
C.G.

J101

CL
3.18
3.37 (80.8)
(85.6)

0.55
(14.0)

CL CL
C.G.

P101

0.17 ±0.02 3.40

(4.3 ±0.5) (86.4)
8.07 1.30
(205.0) (33.0)
0.08
(2.0)

Figure 1-9. WX-1000/SKY497 Display

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 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 O-ring) 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 1-10 depicts the antenna dimensions.

Table 1-4. Airframe Installation Kits

INSTALLATION KIT
MANUFACTURER AIRFRAME PART NUMBER
AEROSPATIALE ATR-42 817-10009-001
AGUSTA A109 817-10009-006
BAE/RAYTHEON HAWKER 400, 600, 700, 800, and 1000 817-10009-004
BEECH BEECHJET, KING AIR 90, 100, 200, 300, and 350 817-10009-001
BARON 33, 35, 36, 55, 58, BE-99, 1300, & 1900C/D 817-10009-002
BELL 206, 407, 427 817-10009-006
CANADAIR CHALLENGER 600 and 601 817-10009-005
CESSNA CITATION III, VI, VII 817-10009-001
CITATIONJET, CITATION I, II, V 817-10009-004
182, 210, 337, 401, 414, 425, 441 817-10009-006
COMMANDER 114 817-10009-006
DASSAULT FALCON 10, 20, 50 817-10009-001
FALCON 900 817-10009-005
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 817-10009-001
NAVAJO 817-10009-002
MIRAGE, MALIBU 817-10009-005
SARATOGA, SENECA 817-10009-006
SAAB SF-340 817-10009-001
SABRELINER SABRE 65 817-10009-001
SHORTS 360 817-10009-001
SIKORSKY S-76 817-10009-006
SOCATA TBM-700 817-10009-001
TB20 817-10009-006

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 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

817-10009-006 100-10022-001* Screw, 10-32 x 1 PPH SS (MS51958-67) 4

(No Adapter Plate) 101-10027-001* Stop Nut, 10-32 (MS21044C3) 4
* Hardware supplied with all kits.

NOTE
DIMENSIONS ARE IN INCHES (MILLIMETERS)
DO NOT PAINT

6.23 ±0.08
FWD (158.2 ±2.0)

1.30
FORWARD
(33.0)

0.725
(18.4)
0.45
SUM PORT DIFFERENCE PORT (11.4)
(Blue Band) (Red Band)
PROBE PORT
(Black Band)

5.06 5.71
(128.5) (145.0)
11.12
(282.4)

Figure 1-10. NY156/NY164 Directional Antenna

1-13
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 SKY899
Installation Manual
1.4 SPECIFICATIONS

1.4.1 Transmitter Receiver Computer (TRC)

PART NUMBER: 805-11900-001 - TRC899

SIZE: 12.52 inches (31.90 cm) Deep

3.56 inches (9.04 cm) Wide
7.62 inches (19.36 cm) High

WEIGHT: 9.00 lb (4.08 kg) Not Including Mounting Tray

9.88 lb (4.48 kg) With Standard Mounting Tray
11.01 lb (4.99 kg) With Ruggedized Mounting Tray

OPERATING TEMPERATURE: -55 to +70 degrees Celsius (-67 to +158 degrees Fahrenheit)
STORAGE TEMPERATURE: -55 to +85 degrees Celsius (-67 to +185 degrees Fahrenheit)

OPERATING ALTITUDE: 55,000 feet (Maximum)

COOLING: Conduction and Forced Air (Internal Fan) Convection

POWER REQUIREMENTS: 18 to 32 V dc, 2 Amps maximum at + 28 V dc

TRACKING CAPABILITY: Up to 35 intruder aircraft (The 8 highest priority aircraft are displayed on the WX-1000/SKY497
display. Some alternate displays, depending on the manufacturer, may show up to 30 intruder
aircraft.)
SURVEILLANCE RANGE: Horizontal tracking radius:
35 nmi Maximum ATCRBS Surveillance
50 nmi Maximum ADS-B Surveillance (ADS-B surveillance will not be active in the
SKY899 until ADS-B is standardized by the aviation community and the FAA, at which
time you will be able to get a software upgrade to activate all of SKY899’s ADS-B
features.)
Relative altitude tracking range:
±10,000 ft maximum
DISPLAY RANGES: Horizontal display ranges:
Display Dependent
WX-1000/SKY497 Display defaults at 2, 6 & 15 nmi .
Additional driver selectable ranges between 2 and 24 nmi are available.
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: ± 0.05 nmi (Typical)

BEARING ACCURACY: With NY156 Antenna - 5° RMS (Typical) 30° Peak Error
With NY164 Antenna - 7° RMS (Typical) 30° Peak Error
ALTITUDE ACCURACY: ±200 ft

CERTIFICATION: * USA (FAA) TSO C118 (TCAS I) & C147, Class A (TAS) Refer to FSAW 98-04B (or later
approved version) for Flight Standards Service policy concerning follow-on
field approvals.
RTCA COMPLIANCE: Software DO178-B Level D
DO-160D Category (For further details refer to Appendix B - Environmental Qualification Form.)

FCC COMPLIANCE: PART 87 ID# PMYTRC899

* 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.

1-14
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 SKY899
Installation Manual
1.4.2 WX-1000/SKY497 Display

PART NUMBER DEFINITION:

78-8060-5900-8 (Black Bezel)
78-8060-5900-9 (Gray Bezel)

SIZE:
Height: 3.37 inches (8.56 cm)
Width: 3.37 inches (8.56 cm)
Depth: 8.24 inches (20.92 cm)
WEIGHT:
2.3 lb (1.0 kg)

OPERATING TEMPERATURE:
-20 to +55 degrees Celsius (-4 to +131 degrees Fahrenheit)

STORAGE TEMPERATURE:
-55 to +70 degrees Celsius (-67 to +158 degrees Fahrenheit)
OPERATING ALTITUDE:
55,000 feet (Maximum)

TSO COMPLIANCE:
FAA C110a & C113
JTSO C113
RTCA COMPLIANCE:
DO-160C (For further details refer to Appendix B - Environmental Qualification Form.)

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 (For further details refer to Appendix B - Environmental Qualification Form.)
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. SKYWATCH HP software version can be verified via the service
menu. Hardware modifications and software versions are listed in tables 1-6 and 1-7.
Table 1-6. TRC899 Hardware Modifications
MOD COMPLIANCE DESCRIPTION

A Optional Adds additional transient protection for the ±15 V dc display power lines. The only
equipment that connects to these lines is the WX-1000/SKY497 display. Refer to Service
Bulletin Nr. 1xx.

1-15
Rev. B
 SKY899
Installation Manual
Table 1-7. TRC899 Software Revisions
SYSTEM SKY HP
REVISION VERSION DESCRIPTION

1.4 1.05 Original production release.

1.5 1.06 Refer to Service Bulletin 102.

• For Collins ProLine 4 transponder interface, corrects label 350 used bythe
maintenance computer.
• Corrects valid altitude limits for Collins ALT-50 and ALT-55 and King
KRA405 and KRA10/10A altimeter interface.
• Corrects intruder heading for Meggit Magic Display Sysem ARINC-429
heading interface.

1.6 1.07 Refer to Service Bulletin xxx.

• Corrects the use of the antenna calibration factor when using a bottom
mounted antenna.
• Adds the detection of off-scale condition for the KRA-405 Radio Altimeter.

1.6 INTERFACE
The electrical characteristics of all input and output signals are detailed in Appendix A. Listed
below in table 1-8 is the minimum equipment required to interface with the SKY899. See
chapter 2 for details.
Table 1-8. Minimum Interface Equipment Required
AVIONICS EQUIPMENT
BAROMETRIC ALTITUDE

LANDING GEAR SWITCH

SQUAT SWITCH (WOW)

GPWS/EGPWS/TAWS
MAGNETIC HEADING

SUPPRESSION BUS

EXTERNAL LAMPS

ON - OFF SWITCH
PILOT CONTROLS
RADIO ALTITUDE

AUDIO SYSTEMS
(PUSHBUTTONS)
(AUDIO INHIBIT)
GPS NAV

SURVEILLANCE
MODE

ATCRBS
(Active Only)
① X ① ① X X ② ③ ③ X ➃

ATCRBS & ADS-B X X ① X ① X X ② ③ ③ X ➃

(future option)

X Required.
① Optional but will enhance performance. (See individual paragraphs in chapter two for
details.)
② Required if Terrain Warning System (GPWS, EGPWS, or TAWS) is installed.
③ Only if Alternate Display requires it, see display manufacturer’s instructions.
➃ Required and may be provided by the display (e.g., WX-1000/SKY497 display
OFF/BRT switch).

1-16
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 SKY899
Installation Manual
1.7 EQUIPMENT REQUIRED BUT NOT SUPPLIED
Antenna Cables The installer will supply all antenna cables and connectors. The directional
antenna requires three cable assemblies; sum (Sigma Port), bit probe
(Probe Port) and difference (Delta Port). Cable attenuation for the sum and
difference ports must not exceed 2.5 dB. Table 1-9 identifies U. S. vendors
who sell approved cables by the foot. Table 1-10 provides a cable to
connector cross-reference.
RG142B or equivalent may be used for the bit probe cable. Attenuation for
the bit probe cable must not exceed 6 dB.
NOTE
Use of any cable not meeting specifications voids all
system warranties.

Table 1-9. Directional Antenna SIGMA and DELTA Port Cable Vendors
Electrical & Mechanical Technologies (EMTEQ)
1-888-679-6170
262-679-6170
FAX 262-679-6175

Attenuation Weight (lb) Maximum Length Minimum Bend

Part Number (dB/100 ft 1.0 gHz) (per 100 ft) (ft) Radius (in)
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
Electronic Cable Specialists
1-800-327-9473
414-421-5300
FAX 414-421-5301

Attenuation Weight (lb) Maximum Length Minimum Bend

Part Number (dB/100 ft 1.0 gHz) (per 100 ft) (ft) Radius (in)
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
PIC Wire and Cable
1-800-742-3191
262-246-0500
FAX 262-246-0450

Attenuation Weight (lb) Maximum Length Minimum Bend

Part Number (dB/100 ft 1.0 gHz) (per 100 ft) (ft) Radius (in)
S33141 7.2 6.5 32 1.5
S55122 5.7 8.2 40 1.6
S22089 3.8 18 61 2.5

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.

1-17
Rev. B
 SKY899
Installation Manual
Table 1-10. 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
Compact Flash Card Compact flash card can be used for configuration management, data
(Optional) storage (engineering only) or software upgrades (factory issued only). Refer
to chapter 4 for instructions. To purchase compact flash cards reference the
following part numbers when ordering:
Compact Flash Card 8M 3.3V P/N 825-10050-001
Compact Flash Card 80.2M 3.3V P/N 825-10051-001
Compact Flash Card 96.2M 3.3V P/N 825-10052-001
Connector Installation J9, J10, & J11 See table 1-8.
Antenna Tool M22520/5-01
Die M22520/5-19 (EMTEQ Cable PFLX195-100)
Die M22520/5-43 (EMTEQ Cable PFLX240-100)
Die M22520/5-35 (EMTEQ Cable PFLX340-100)
Die M22520/5-19 (ECS Cable 311601)
Die M22520/5-61 (ECS Cable 311201)
Die M22520/5-21 (ECS Cable 310801)
Die 190318 (PIC Cable S33141)
Die 190418 (PIC Cable S22089)
Die 190618 (PIC Cable S55122)

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Connector Installation P1 Interconnect Crimping Tool M22520/2-01

(Continued) Positioner M22520/2-07
Insertion MS27495 A22M
Removal MS27495 R22M
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 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 1-11.
Table 1-11. Heading Input Cable Vendors
US CABLE
COMPANY P/N

Dallas Avionics WX-5

1-800-527-2581 (6.84 lb/
214-320-9776 100 ft)
FAX 214-320-1057

Electronic Cable 3N6607

Specialists (7.5 lb/
1-800-327-9473 100 ft)
414-421-5300
FAX 414-521-5301

A.E. Petsche TZGYR

817-461-9473 (6.84 lb/
FAX 817-277-2887 100 ft)

EDMO Distributors WX-1000

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

PIC Wire and Cable WM25807

1-800-742-3191 (7.2 lb/
262-246-0500 100 ft)
FAX 262-246-0450

Lamps External annunciators are required when using an alternate display that is
(external annunciators) not capable of displaying above, below and unrestricted vertical modes.
Lamp outputs are switched to ground when active (LP1OUT & LP2OUT).
Lamps should be labeled ABV and BLW. An optional operation mode lamp
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Installation Manual
can be installed to show system has been switched from standby into
operation mode and should be labeled OPR.
Lamps can be 12 or 28V dc with maximum current 300 mA. An isolation
relay is required for ac operation. Refer to paragraph 2.14, 2.16 and A.2 for
details.
Miscellaneous Hardware The installer must provide suitable hardware to attach the TRC Mounting
Tray. The following stainless steel fasteners are recommended:
Channel Mount: Four 8-32 UNC-2A pan head machine screws per
ANSI B18.6.3. (Six are required for the ruggedized
tray.)
Or
Four 8-32 UNC-2A hex socket cap machine screws
per ANSI/ASME B18.3. (Six are required for the
ruggedized tray.)
Four No. 8 helical spring lockwasher per
ANSI/ASME B18.21.1. (Six are required for the
ruggedized tray.)

Flat Mount Eight 6-32 UNC-2A 100 degree flat head machine
screws per B18.6.3.
Oscilloscope Required to verify SKY899 suppression pulse (100 µs ±5µs, +28 V dc).
Power Cable For the power cable, use #16 AWG (minimum) twisted shielded pair cable
(Beldon 83322, Alpha 2826/2, or equivalent).

RS-232 Terminal Device Required if using an alternate display, (see Appendix E for instructions).
(e.g., Laptop Computer) 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
Alternate Display ON/OFF - A separate ON/OFF switch may be required. Any general
purpose SPDT toggle switch (1/2 A @ 28 V dc) may be used.
OPR/STB - Depending upon display capabilities a separate momentary
switch may be required to toggle between operate and standby
modes.
RANGE - Depending upon display capabilities a separate momentary
switch may be required to change display ranges.
TEST/ALT - Depending upon display capabilities a separate momentary
switch may be required to perform pilot initiated self-test
and/or change between altitude modes (NRM, ABV, BLW &
UNR). Label switch accordingly (i.e., TEST, TEST/ALT or
ALT).
WX-1000 If the final configuration includes a WX-1000 Stormscope Weather Mapping
System, two external switches are required. Any general purpose toggle

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switch (1/2 A @ 28 V dc) may be used for SW1 & SW2 switches.
SW1 - A SPST switch is required for the SKYWATCH/Stormscope display
mode switch.
SW2 - A DPDT switch is required for the WX-1000 maintenance switch.
WX-1000/SKY497 Display & This cable is used to connect the WX-1000/SKY497 display and/or WX-1000
WX-1000 Processor Cable 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 1-12.
NOTE
Use of any cable not meeting specifications voids all
system warranties.

Table 1-12. Display Cable Vendors

U.S. DISPLAY CABLE WEIGHT
COMPANY P/N (LB PER 100 FT)

Dallas Avionics WX-3 10.5

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

Electronic Cable Specialists 3N6715 16

1-800-327-9473
414-421-5300
FAX 414-421-5301

A.E. Petsche TZDIS 13.1

817-461-9473
FAX 817 277 2887

PIC Wire and Cable WM25815 14.5

1-800-742-3191
262-246-0500
FAX 262-246-0450

EDMO Distributors WX-1000 Display ---

1-800-235-3300
509-535-8280
FAX 1-800-828-0623
FAX 509-535-8266

1.8 INSTALLATION APPROVAL

The SKY899 must be treated as a major alteration on F.A.A. form 337 referencing STC Number
ST01552CH-D, if not installed under a type certificate or supplemental type certificate. Refer to
FSAW 98-04B bulletin for follow-on field approvals of Traffic Alert/Advisory Systems and Traffic
Alert and Collision Avoidance Systems (TCAS I)

Aircraft mandated for TCAS I under the provisions of 14 CFR part 135, must be installed under
a type certificate or supplemental type certificate.

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CHAPTER 2
INSTALLATION
2.1 INTRODUCTION
The information and instructions provided in this manual are directed toward fixed-wing aircraft.
Installation must be made by qualified personnel, in conformance with applicable government regulations.
The 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.
3. Tolerances (unless otherwise indicated):
ANGLES ARE ± .5°
.00 TWO PLACE DECIMALS ARE ± .01
.000 THREE PLACE DECIMALS ARE ± .005

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2.2 UNPACKING, INSPECTION AND STORAGE

CAUTION
The display and TRC are sensitive to electrostatic discharge (ESD) and may
be damaged if not handled correctly. Do not remove protective covers from
electrical connectors during unpacking. Touching an exposed connector may
cause electrostatic damage to equipment.

Carefully unpack the system and note any damage to shipping containers or equipment. Visually inspect
each component for evidence of damage. Compare the equipment received with that noted on the packing
list. Immediately report any missing items or evidence of damage to the carrier making the delivery. To
justify a claim, retain the original shipping container and all packing materials.

Every effort should be made to retain the original shipping containers for storage. If the original
containers are not available, a separate cardboard container should be prepared that is large enough to
accommodate sufficient packing material to prevent movement. The ambient temperature of the storage
area should not fall below -55 °C (-67 °F) or rise above 85 °C (185 °F).

2.3 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 L-
band 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.

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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 1-9.
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.
Memory Card Access The TRC is equipped with a front access memory card connector port intended for
use with compact flash cards. This connector port may be used for system
configuration, future software upgrades and data recording. In order to insert and
extract the memory card (without removing the TRC from its mounting tray),
clearance must be maintained for the access door to open and permit space for the
installer’s hand.

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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 WX-
1000/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 L-3 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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Figure 2-2. Interconnect Wiring Without WX-1000

(Sheet 1 of 2)
2-5 (page 2-6 blank)
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Installation Manual

Figure 2-2. Interconnect Wiring Without WX-1000

(Sheet 2 of 2)

2-7 (page 2-8 blank)

Rev. B
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Installation Manual

Figure 2-3. Interconnect Wiring With WX-1000

(Sheet 1 of 2)
2-9 (page 2-10 blank)
Rev. B
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Installation Manual

Figure 2-3. Interconnect Wiring With WX-1000

(Sheet 2 of 2)
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Rev. B
 SKY899
Installation Manual

Figure 2-4. Interconnect Wiring with

Alternate Display (Sheet 1 of 2)
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Installation Manual

Figure 2-4. Interconnect Wiring with

Alternate Display (Sheet 2 of 2)
2-15 (page 2-16 blank)
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Installation Manual

2.6 CABLE REQUIREMENTS AND FABRICATION

The installer will supply and fabricate all system cables. Cable specifications and approved vendors are
provided in paragraph 1.7, equipment required but not supplied. Appendix A defines the electrical
characteristics of all input and output signals and identifies the cable requirements for each signal.
Required connectors and contact pins are supplied in the installation kits.

NOTES
1. Use of any cable not meeting 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. If you fabricate your own cables, you must verify that the attenuation and
VSWR does not exceed the specified values.
2. To add strain relief and alleviate stress caused by aircraft vibration, place 4-
6 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
1-9) and direct as possible.
• Avoid sharp bends (do not exceed maximum bend radius detailed in table 1-9).
• 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 Cable

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 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.

1
6

5
2

3
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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 SKY899
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7 2

6 11

10 3

9 1

5 4

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. Figure A-1 shows the TRC497 P1 connections corresponding to the TRC899 connector
P1. In order to relocate pin positions use the insertion and extraction tools listed in paragraph 1.7, under
sub title "Connector Installation."

Some of the differences:

TRC899 TRC497
• 7 ARINC-429 RX channels 2 ARINC-429 RX channels
• 3 ARINC-429 TX channels 1 ARINC-429 TX channel
• System Configuration Module Individual configuration pins
• Heading valid, 1 input pin (active low or high) Heading valid, 2 input pins (active low or high)
• Analog radio altimeter and flag Not available
• GPS Position (for ADS-B) Not available
• Altimeter Gilham Code "D2" added Altimeter Gilham Code "D2" not available
• Lamp Outputs - above, below and oper_mode Not available
(used with alternate display)
• Stepper (heading) not available Stepper (heading) available
• Landing Gear Switch (active low or high) Active low only
• Squat Switch (active low or high) Active low only
• Audio inhibit (GPWS/EGPWS/TAWS) Active low only
(active low or high)
• 18 - 32 V dc power input 11 - 34 V dc power input

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2.7 AIRCRAFT DISCRETE INPUTS

The aircraft discrete inputs are used for audio suppression and to assist in determining the aircraft’s
phase of flight or flight condition (e.g., on ground or in flight). The discrete inputs are configured in the
service menu and saved to the System Configuration Module. There are three service menu options, none,
active low (electrically ground, 0 V dc to 2.0 V dc) and active high (electrically high, +9 V dc to +28 V dc)
for each input. The inputs are diode isolated inside the TRC, do not install isolation diodes externally.
Refer to appendix A for signal characteristics.

2.7.1 GPWS (Audio inhibit)

The audio inhibit input will sense a terrain warning alarm (i.e., GPWS, EGPWS, TAWS) and temporarily
delay the audio alert output until the terrain warning clears. The input can be either a constant flag signal
or an alternating flag signal. The flag must be cleared for 5 seconds before the TRC accepts a “NO
ALARM” condition and restores audible alerts.

NOTE
If the aircraft is equipped with terrain warning system the GPWS, EGPWS, or TAWS
flag must be connected to the TRC.
GPWS 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). 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.
Landing gear connection:
GEAR P1-33

2.7.3 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.

NOTE
If the aircraft is not equipped with a squat switch, it is recommended that a
squat switch or an alternate 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.
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.

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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 in-
flight.

2.8 ALTERNATE DISPLAY

Alternate display(s) are connected to the ARINC-429 TX1 output channel. Each alternate display will
show the information consistent with the capabilities of that particular display. Display functions can be
controlled through the discrete soft-key inputs or the alternate display depending on the display’s
capabilities. Refer to paragraph 2.9.3 for alternate display connection information and paragraph 2.20 for
soft-key connections. Alternate display driver configurations are covered in Chapter 4.

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-2 and A-3.

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

2-23
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 SKY899
Installation Manual

2.9.2 Mode S Transponder I/O (future option)

The TRC has one receive and one transmit channel designated for the mode S transponder XT & TX bus
interface. The receiver and transmit speed is fixed at 100 kHz. This is a future option, do not connect at
this time.

Mode S Transponder XT bus connections:

A429RX7_A P1-83
A429RX7_B P1-84

Mode S Transponder TX bus connections:

A429TX2_A P1-44
A429TX2_B P1-45

2.9.3 Alternate Display Output

The TRC has one transmit channel designated for alternate displays (i.e., EFIS, MFD and weather radar
via a Radar Graphics Computer). The transmitter speed is fixed at 100 kHz. A maximum (typical) of ten
loads (displays) can be connected to the output channel. See Appendix A for signal characteristics.
Alternate Display connections:
A429TX1_A P1-42
A429TX1_B P1-43

2.9.4 Future Option

The TRC has one spare receiver A429RX8_A & A429RX8_B and one spare transmitter A429TX3_A &
A429TX3_B 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/EGPWS/TAWS) is active. The audio output is delayed when a terrain warning system (flag) alarm
is detected and remains delayed until the warning clears.

Two outputs, 150 ohm and 600 ohm, can supply up to 40 mW to the audio distribution system. Volume
level is set via the Service Menu.
Audio output connections:
AUDIO_H P1-89 (600 Ohm)
AUDIO_L P1-90 (150 Ohm)
AUDIO_C P1-91 (Audio Common)

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 or
ARINC-429 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.

2-24
Rev. B
 SKY899
Installation Manual

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 ARINC-429 (ADC)

ARINC-429 (ADC) speed can be 12.5 or 100 kHz. Refer to paragraph 2.9.1 for ARINC-429 general sensor
input information.

2.12 GPS (ARINC-429)

The GPS (ARINC-429) speed can be 12.5 or 100 kHz. Refer to paragraph 2.9.1 for ARINC-429 general
sensor input information. In order to use ADS-B, in the future when it is standardized, SKYWATCH HP
requires a GPS input that is GAMA or ARINC-743A compliant.

2.13 HEADING INPUT

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. Only one heading source, either compass Synchro or ARINC-429 should be connected.

NOTE
The SKY899 will work without heading input, but it will experience degraded
performance during high-rate-of-turn maneuvers. Therefore, it is
recommended that heading input be connected to the TRC. Heading input
will prevent intruders from dropping and reappearing on the display while
the aircraft is turning.

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.
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)
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 SKY899
Installation Manual
2.13.2 ARINC 429 (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. Refer to paragraph 2.9.1 for ARINC-429 general sensor input 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), below (BLW) and unrestricted (UNR). 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. Refer to Appendix A for electrical characteristics.

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 ABV BLW ABV BLW ABV BLW

(Normal) (Above) (Below) (Unrestricted)

Figure 2-7. Above and Below External Lamps

2.15 ON/OFF SWITCH

This input connection turns the system 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.
WX-1000/SKY497 Display (without WX-1000). Connect per figure 2-2.
Alternate Display. A separate ON/OFF switch is required (any SPDT toggle switch rated at 1/2 A @ 28 V
dc can be used). Reference the display manufactures instructions and figure 2-4 for further details.
WX-1000 Override Switch (SW2). See paragraph 2.24.2 and figure 2-3.

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

2.16 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 lamp requires a
separate dc source (constant or dimming circuit). If lamp voltage is an ac source then an isolation relay
must be used. Refer to Appendix A for electrical characteristics.

Operational mode connection:

OPER_MODE P1-31

2-26
Rev. B
 SKY899
Installation Manual

2.17 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.
Power connection:
+28V P8-A
+28V_RET P8-B
SPARE P8-C

2.18 RADIO ALTIMETER (optional)

If available, connect the SKY899 to a radio altimeter. The TRC can accept radio altimeter input from
analog or ARINC-429 (label 164 required) source. Interface to a radio altimeter will add ground intruder
filtering. It will also improve the SKY899s ability to determine when to display a TA (i.e., adjust
sensitivity levels) and when to mute aural announcements to minimize pilot distraction (i.e., suppress
SKY899 audio). Without the benefit of radio altitude, ground speed or the landing gear position are used to
determine sensitivity level and audio suppression.
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.

2.18.1 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
RADIO_ALT_FLG (P1-14) unconnected and select None in the Service Menu (Rad Alt Flag sub-menu).

The SKY899 can accept altitude that is compatible with ARINC characteristic 552 and 552A. In addition,
special drivers are available to support the following altimeters:
Bonzer Mark 10X
Collins ALT-50
Collins ALT-55
King KRA 405 (Aux. Output #1)
King KRA10/10A
Sperry AA-100
Terra TRA 3000

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)

See appendix A for signal characteristics. Some analog radio altimeters have multiple outputs (e.g., King
model KRA405), verify the output to be interfaced to matches the signal characteristics listed table A-1.

2.18.2 ARINC-429
Radio altimeter ARINC-429 speed can be 12.5 or 100 kHz. Refer to paragraph 2.9.1 for ARINC-429 general
sensor input information.
2-27
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 SKY899
Installation Manual

2.19 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

2.20 SOFT-KEYS
Soft-key inputs are active low (see Appendix A for signal levels). If using a WX-1000/SKY497 display
connect the soft-keys 1 thru 4 per figures 2-2 or 2-3. Do not connect an external display to soft-key inputs
when sharing the WX-1000/SKY497 display with a WX-1000 processor.

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 (e.g., some displays control operation mode internally and ranges externally, while others
handle ranges internally and operation modes externally).

When installing multiple alternate displays, soft-keys inputs may require several displays being connected
to the same input (e.g., WX-1000/SKY497 connected to all soft-key inputs; RGC250/350 to soft-keys 2, 3, &
4; GNS430 to soft-keys 2 & 4 and Collins EFIS to soft-keys 2, 3, & 4). Refer to table 2-1 for soft-key
connections.
NOTE
Pilot must be able to perform the functions listed in table 2-1, with the either display
switches or external momentary switches. Check with display manufacturer for
display’s capabilities, before wiring soft-key inputs.

Table 2-1. Soft-Key Connection Options

Signal Name Function WX-1000/SKY497 Alternate Display(s)
Display
SFTKEY1_IN (P1-18) MSG Connect Do not Connect
SFTKEY2_IN (P1-19) TEST/ALT Connect Connect (Momentary Switch - external switch or alternate
(NRM/ABV/BLW/ display open-collector output). Label external switch TEST/ALT,
UNR) TEST or ALT depending on alternate display capabilities.
SFTKEY3_IN (P1-20) RANGE Connect Optional - Display specific. Label external switch RANGE.
SFTKEY4_IN (P1-21) OPR/STB Connect Connect (Momentary Switch - external switch or alternate
display open-collector output). Label external switch OPR/STB.

2-28
Rev. B
 SKY899
Installation Manual
2.21 SUPPRESSION BUS I/O
The TRC outputs a 100 µs (± 5 µs) suppression pulse on the aircraft suppression bus. 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).
Suppression Bus connection:
SUPBUS P1-93

2.22 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).
NOTE
The system configuration module must be located inside the backshell of
connector P1 and wire-tied to the bundle of wires. Reference figure 2-9.
System Configuration Module connections:
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) RED

TO P1-92 (PLUG_GND) BLACK CONFIG MODULE
TO P1-100 (SCL) GREEN P/N 814-18005-001
TO P1-99 (SDA) YELLOW

TERMINAL
P/N M39029/56-348

Figure 2-8. System Configuration Module

CONFIGURATION MODULE
SPLIT ELBOW P/N 814-18005-001
90° BACKSHELL (located inside backshell)
P/N 613-10043-001

.
s, INC
tem
Sys
nics
Avio
rich
ood ule
BFG
n Mod 1
ratio 005-00
figu
Con 814-18
P/N

NOT TO SCALE 100 PIN CONNECTOR

P/N 605-10251-001

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

2-29
Rev. B
 SKY899
Installation Manual
2.23 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).

2.24 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 BLUE 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).

2-30
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 SKY899
Installation Manual

2.24.1 SKYWATCH/Stormscope Mode Switch

The SKYWATCH/Stormscope mode switch (SW1) is required only if a WX-1000 Stormscope Weather
Mapping System is installed. This switch permits the flight crew to switch the display between the
SKY899 and WX-1000. If a TA (Traffic Advisory) is detected while in the Stormscope mode, the display will
switch to the SKYWATCH mode. Refer to figure 2-3 for interconnect wiring information.
Any general purpose SPST toggle switch (1/2 Amp @ 28 V dc) may be used. Display mode switch cable
routing and length are not critical to system operation. Mount the switch at a location easily accessible to
the pilot.
SKYWATCH/Stormscope mode switch connections:
SMS P1-15
SMS_RET P1-23

2.24.2 External Overide Switch

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 (1/2 Amp @ 28 V dc) may be used to switch the WX-1000/SKY497
display PWSWHI and PWSWLO signals from the WX-1000 processor to the TRC ON/OFF control lines.
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.
TRC ON/OFF power control switch connection:
ON/OFF P1-4
ON/OFF_RET P1-5

2.25 ANTENNA INSTALLATION

The following paragraphs provide installation details for directional antenna. Standard installation
practices prescribed in FAA Advisory Circular No. 43.13 must be followed. The installer must ensure the
immediate antenna installation area is clean and prepared so that the antenna is electrically bonded
(metal-to-metal contact) to the aircraft. To provide optimum bonding through the mounting holes, prepare
the surfaces with Alodine No. 1001.
To facilitate mounting to the airframe, the dimensions shown in Figure 2-10 can be used to locate and drill
mounting and connector access holes. Connection to the antenna should be made in accordance with the
system interconnect diagram (figure 2-2, 2-3 or 2-4).
NOTE
A doubler plate (not supplied) is required to reinforce the aircraft skin.
1. Connect each of the three antenna cables. Check to ensure that each cable is connected to the correct
antenna connector. Each connector/cable has a matching color band (see note par.2.6.1).
2. Attach the antenna to the aircraft, with the special adapter plate and o-ring, using 10-32 hardware
provided. See Figure 2-11.
NOTES
1. When mounting the antenna remove the O-ring from the bag and install it
in the O-ring groove on the bottom of the antenna.
2. For pressurized aircraft, use a sealant that meets the requirements of SAE
AMS-S-8802 such as Flamemaster CS3204 class B. For non-pressurized
aircraft, use a non-corrosive sealant that meets the physical requirements
of MIL-A-46146 such as General Electric RTV162.
2-31
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 SKY899
Installation Manual

Figure 2-10. Antenna Mounting Holes

Figure 2-11. Directional Antenna Installation

2.26 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
installations in a high vibration environment, must be channel mounted.

2-32
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 SKY899
Installation Manual

1. Position tray at the installation location.

2. Determine centers for mounting holes, and drill for required fasteners. See figure 2-12 (standard tray)
or 2-13 (ruggedized tray).
3. Secure tray in place using suitable 8-32 (channel mount) or 6-32 (flat mount) hardware.

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

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 SKY899
Installation Manual

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

2.27 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.

2-34
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 SKY899
Installation Manual

)
UE
(BL K)
M AC
- SU BL
J9 E( )
R OB ED
- P E (R
0 NC
J1
J9
ERE
J1 INT J1
ER IFF
-D
CO
INTERCONNECT NN
EC
T
11
J1 J
(I/O SIGNAL) ST
0

Y TE
R
TO
AC
J1
1

- F
J7

J8 J
PO 8
WE
POWER R
J7
TE
ST

J1
ME
MO
2
MOUNTING TRAY
RY
CA
RD

J12
MEMORY CARD RETAINER CUPS
ACCESS DOOR (2 PLACES)

HOLD-DOWN KNOBS
(2 PLACES)

Figure 2-14. TRC899 Installation

2-35
Rev. B
 SKY899
Installation Manual

2.28 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.

2.28.1 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.

NOTE
DIMENSIONS ARE IN INCHES (MILLIMETERS)

0.15 (3.8)
00 2

4 HOLES
(1 3.9
)
.0

#25 Drill Bit

3.06 3.21
(78.0) (82.0)

3.06
(78.0)
3.21
(82.0)

NOT TO SCALE

Figure 2-15. Instrument Panel Cutout and Mounting Holes

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 SKY899
Installation Manual

2.28.2 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 AIRCRAFT PANEL
(QTY 4)

MOORING PLATE (NOT SUPPLIED)

DISPLAY

REAR MOUNT

6-32 X 3/4 PHMS AIRCRAFT PANEL

(QTY 4)

MOORING PLATE (NOT SUPPLIED)

DISPLAY

FRONT MOUNT

Figure 2-16. Display Installation

®
Use Rivnuts or a mooring clamp to secure the display to the instrument panel.
NOTE
1. The mooring clamp is not furnished with the display.
2. A mooring clamp (P/N 78-8060-5856-2) can be ordered when the order for the
display is placed.
3. A 3ATI mooring clamp is also available from:
MSP, Incorporated
R.R. 4, Box 383A
Nashville, Indiana 47448
Tel. (812) 988-6623 or FAX (812) 988-6181

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CHAPTER 3
INSTALLATION CHECKOUT
3.1 INTRODUCTION
This section contains instructions for using the 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

1 4

2 3

Figure 3-1. Controls

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

1, 2, 3, & 4 Also referred to as soft-keys (1), (2), (3), and (4). In every operating mode a label
Pushbuttons 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. Verify all
avionics equipment interfaced with the SKY899 (i.e., GPS, ADC, AHRS, synchro compass, encoding
altimeter) is turned ON and signal condition is valid.

NOTE

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

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

AVIONICS SYSTEMS

SkyHP Vx.xx

Figure 3-2. Start-up Screen

After approximately thirty seconds the display will show the STANDBY screen (see figure 3-3).

NOTE
If the TRC has not been calibrated to the directional antenna the display
may show a “SKY899 FAILED” message. Calibration will be done during
system setup verification and operation.

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BRT
OFF

SKY899
Standby

MSG OPR
TEST RNG

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.
3.3.1.1 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 fixed wing aircraft type (rotorcraft is provided for future option, do not select at this
time). 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.

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5. From the Setup menu, select ARINC 429 ports and manually configure each receiver channel (Refer to
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.
2. The data rate for receive channels 1 and 2 must be set to the same speed
(12.5 or 100 kHz). The data rate for receive 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.
3. Autodetect will configure the equipment type and speed of each receiver
channel. To identify the equipment Autodetect checks for ARINC-429
label 377 (equipment ID), if that’s not present then it checks for label 371
(general aviation equipment ID). If the equipment can not be identified
then the receiver channel will be set to the default of NoType and
NoSpeed. Autodetect will not work for multiple data inputs (i.e., ARINC-
429 superbus).

a. The ARINC 429 Receivers menu will appear. With all (source) avionics equipment turned on
highlight and select the RX channel to be configured.
b. Select Type from the menu. The Equipment type menu will appear, select source equipment
from list (i.e., GPS, BarAlt, etc.). If connected to an ARINC-429 super bus, select all the other
equipment(s) that are located on that bus. When finished selecting equipment press exit.
c. Rx channel menu will appear, select speed from the menu. The ARINC 429 receiver speed
menu will appear, select correct speed.
d. The ARINC 429 Rcvrs menu will appear, verify receiver channels match desired wiring
interface.
e. Repeat above steps a thru d for each receiver channel input that is connected.
f. Select exit to return to Setup Menu.
6. From the Setup menu, select Avionics Equipment:
a. The Equipment menu will appear, select Browse All Avionics. (See paragraph 4.4.1.5.)
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 sub-menus,
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.
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. To verify changes made to the configurations module, turn the SKY899 OFF and then enter the
Service Menu (see paragraph 4.4) and repeat Step 6.
8. Perform system setup verification and operation procedure in paragraph 3.3.2.

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3.3.1.2 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. Carefully align the arrow from the flash card with the arrow on the
front of the TRC899 while inserting (see figure 4-40).
2. Enter the Service Menu (see paragraph 4.4), select Configuration Management.
3. At the Configuration Management menu, select Retrieve from CF. Verify the "download was
successful" message is displayed. If an error occurs during download, the configuration setup must be
done manually (see above "System Configuration" procedure).
4. Turn off the SKY899 and remove the compact flash card from J12 memory card connector.
5. Perform the system setup verification and operation procedure below (see paragraph 3.3.2) to verify
configuration data was downloaded correctly.

3.3.2 System Setup Verification and Operation

1. With SKY899 turned OFF, 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. 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.
2. From the Service menu select Information. From the Information menu, select Data Monitor. The
Data Monitors menu will appear.
3. 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 sensor.
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.
4. From the Service Menu, select Ground Test (see paragraph 4.4.4).
5. From the Ground Test menu, select Perform Ground Test.
6. 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.
7. Select the 6 nautical mile range.
8. 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).
9. Select the NRM (normal) mode.
10. 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, approximately 100 ft. (or less), from the aircraft.

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11. 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.
12. Setup and verify operation of the TT391 Flightline Tester:
a. Open the chassis lid and remove the lid from the chassis by sliding the lid off of the hinge pins
(sliding it to the right). The lid "stay" must be removed from the lid before mounting. The stay
will pop off of the lid. (The stay is the hinged part that props the lid open on the chassis).
NOTE
The Patch Antenna may be used without a tripod. The Patch Antenna can be
held, or secured, and pointed towards the SKYWATCH HP aircraft under test
WITH THE MOUNTING STUD POINT TOWARD THE GROUND. This orientation is
critical.
b. Mount the chassis lid, with the Patch Antenna facing the aircraft, onto a tripod (not included).
The tripod must be capable of holding the antenna (approximately 2.5 lb) and must provide a
standard base mounting stud threaded 1/4"-20. A typical tripod mount is shown in figure 3-4.
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).

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PATCH
ANTENNA
ASSEMBLY

TRIPOD ASSEMBLY
(OPTIONAL -
NOT INCLUDED)
RF
LINK

COAX
CABLE

Figure 3-4. Typical Patch Antenna Tripod Mount

13. 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.
14. Return the TT391 assemblies to their position in the aluminum carrying case.
15. Restart SKY899 by cycling power OFF and then ON.
16. 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.
17. Cycle power to the SKY899 and verify the standby screen appears after approximately 30 seconds.
Press OPR soft-key (4) and verify the MSG label does not appear on the display after 10 seconds.

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NOTE
If MSG label is present press MSG soft-key (1) for degraded operation
message and refer to Chapter 4 troubleshooting to isolate the problem.
18. This completes the post installation checkout procedure.

3.4 SELF TEST

1. Turn SKY899 OFF and then:
a. Make sure the aircraft’s transponder is in the STANDBY, ON, or ALT mode.

NOTE
After power up, it may take a couple of minutes for the altitude encoder to
return a valid altitude to the transponder and SKY899.
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.
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. Select test from the audio level
menu to hear a "traffic traffic" aural message.)
c. Check audio connection to the TRC:
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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. Removal of components is on
condition of failure.

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.

CAUTION

Do not paint the antennas.

Do not use cleaning solvents on the antennas.
2. Remove all dirt and grease from surface areas. Clean with a soft cloth moistened with mild soap and
water.
3. Visually inspect sealant around the antenna base. Reapply sealant if required.

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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 section (figure 4-41). When interfaced to an alternate display the service
menu functions are accessed via an RS-232 terminal device (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

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

NOTE
To prevent conflict between the display and RS-232 interfaces, do not connect
a terminal device to the TRC while accessing the Service Menu via a
WX-1000/SKY497 display.

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 SEL
NEXT PREV

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

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

The buttons perform the following operations:

EXIT - backs up one screen (if in service menu screen it will exit and enter normal/standby mode).
NEXT - scrolls to the next item.
SEL - selects the highlighted item.
PREV - scrolls to the previous item.

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The individual menu items are explained in the following paragraphs.

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, ARINC 429 ports, and avionics equipment. In the setup menu, the current
choice is displayed in asterisks (i.e., Aircraft Type *Fixed Wing*). Select setup from the service menu
screen.

The Setup menu provides the following choices:

BRT
OFF
Setup

Aircraft Type
Antenna Sytem
Audio Level
Arinc 429 Ports
Avionics Equipment

EXIT SEL
NEXT PREV

Figure 4-3. Setup Menu

The following menu will appear when you exit the setup menu if changes were made in the system
configuration. Save changes will store configuration settings in system configuration module. Revert to old
settings will restore the system configuration back to the last saved configuration.

BRT
OFF
Save or Revert
Changes have been made!
Screen appears
Save Changes when exiting Setup
Revert to Old Settings menu and changes
have been made

SEL
NEXT PREV

Figure 4-4. Save Menu

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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. Rotorcraft is
provided for future option, do not select it at this time.

The Aircraft Type menu provides the following choices:

BRT
OFF

Aircraft Type
*Fixed Wing*
Rotor Craft

EXIT SEL
NEXT PREV

Figure 4-5. Aircraft Type Menu

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."

WARNING

Verify displayed antenna position matches antenna location on the aircraft

(top or bottom). Failure to do so could give incorrect traffic bearing.

The Antenna System menu provides the following choices:

BRT
OFF
Antenna System
Top Antenna
[NY156 Directional]
Bottom Antenna
[None]

EXIT SEL
NEXT PREV

Figure 4-6. Antenna System Menu

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

BRT
OFF

Top Antenna
None
NY164 Directional
*NY156 Directional*

EXIT SEL
NEXT PREV

(Bottom Antenna menu is same as Top Antenna menu)

Figure 4-7. Top Antenna Menu

4.4.1.3 Audio Level

The audio level menu allows you to set and test the audio level output. Audio level range is 0 to 40 mW into
600 Ohm load, indicated by percentage (0-100%). Audio level can be adjusted up or down in 5% increments.
Selecting test will cause the "traffic traffic" aural message to be annunciated over the aircraft audio
system.

The Audio Level menu provides the following choices:

BRT
OFF
Audio Level
Volume
[50%]
Up
Down
Test

EXIT SEL
NEXT PREV

Figure 4-8. Audio Level Menu

4.4.1.4 ARINC 429 Ports

Configuring the ARINC 429 ports should be done before configuring the avionics equipment. Select ARINC
429 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. Manually configuring each individual receiver channel is recommended,
however you can select Autodetect.

Autodetect will configure the equipment type and speed of each receiver channel. To identify the
equipment Autodetect checks for ARINC-429 label 377 (equipment ID), if that’s not present then it checks
for label 371 (general aviation equipment ID). If the equipment can not be identified then the receiver
channel will be set to the default of NoType and NoSpeed. Autodetect will not work for multiple data
inputs (i.e., ARINC-429 superbus).

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Selecting ARINC 429 ports from the Setup menu will cause the ARINC 429 Receivers menu to appear:

BRT
OFF
Arinc 429 Rcvrs
Autodetect Please wait... will
Ch. 1: Multi 100 kHz be displayed while
Ch. 2: NoType 100 kHz autodetect is being
Receiver menu shows
the 5 RX channels, the
Ch. 3: GPS 12.5 kHz performed
Ch. 4: NoType NoSpeed
429 source and the
speed. To change Ch. 5: NoType NoSpeed
individual channel, EXIT SEL
highlight desired channel NEXT PREV
and press SEL.

Figure 4-9. ARINC 429 Receivers Menu

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.

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

BRT
OFF

Arinc 429 Rx Ch 1
Type:
BarAlt
GPS
Speed: 100 kHz

EXIT SEL
NEXT PREV

Figure 4-10. ARINC 429 Receiver Channel Menu

Selecting Type will cause the Equipment Type menu to appear:

BRT
OFF
Equipment Type
More than one source can be
NoType selected for each 429 RX
*BarAlt* channel. Each selected source
MagHdg will have an asterisk's before
*GPS*
RadAlt and after it. If more than one
source is selected the word
"Multi" will appear in the ARINC
EXIT SEL 429 Receivers menu.
NEXT PREV

Figure 4-11. Equipment Type Menu

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Selecting Speed will cause the Speed menu to appear:

BRT
OFF
Speed
* 12.5 kHz *
100 kHz

SEL
NEXT PREV

Figure 4-12. ARINC-429 Receiver Speed Menu

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. Browse function will sequentially step 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:

Using Next button to scroll
BRT
Equipment OFF down will cause these
additional menu choices to
Browse All Avionics appear one at a time.
GPS Nav
[Gama] Radio Altitude
Magnetic Heading [None]
[Synchro Compass] Landing Gear
Barometric Altitude [None]
[Encoding Altimeter] Weight-On-Wheels
[Active Low]
EXIT SEL Audio Suppression
NEXT PREV [None]
External Display
[None]

Figure 4-13. Avionics Equipment Menu

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:

BRT
OFF
No Chan Assigned
Choose a channel
Ch.1: NoType 100 kHz This Menu appears when
Ch.2: Multi 100 kHz ARINC 429 equipment has
Ch.3: NoType NoSpeed been selected, but was not
Ch.4: NoType NoSpeed assigned to a channel via
Ch.5: NoType NoSpeed
the Communication Ports Menu
EXIT SEL
NEXT PREV

Figure 4-14. No Channel Assigned Menu

4-7
Rev. B
 SKY899
Installation Manual
The Avionics Equipment sub-menus are as follows.

The GPS Nav menu provides the following choices:

BRT
OFF
GPS Nav
*None*
GAMA
ARINC 743A

EXIT SEL
NEXT PREV

Figure 4-15. GPS Nav Menu

The Heading menu provides the following choices:

BRT
OFF
Heading
*Synchro Compass*
Arinc 429

EXIT SEL
NEXT PREV

Figure 4-16. Heading Menu

Selecting Synchro Compass causes Heading Valid Line menu to appear:

BRT
OFF

Heading Valid Line

*None*
Active Low
Active High

EXIT SEL
NEXT PREV

Figure 4-17. Heading Valid Line Menu

4-8
Rev. B
 SKY899
Installation Manual
The Barometric Altitude menu provides the following choices:

BRT
OFF

Barometric Altitude
*Arinc 429*
Encoding Altimeter

EXIT SEL
NEXT PREV

Figure 4-18. Barometric Altitude Menu

The Radio Altimeter menu provides the following choices:

BRT
OFF Using Next button to scroll
Radio Altimeter down will cause these
additional menu choices to
*None*
Arinc429 appear one at a time.
Arinc 552
Arinc 552A King KRA10/10A
Bonzer Mark 10X King KRA 405
Collins ALT-50 Sperry AA-100
Collins ALT-55 Terra TRA 3000
EXIT SEL
NEXT PREV

Figure 4-19. Radio Altimeter Menu

The Radio Altimeter menu lists the known altimeter manufacturers and models that are compatible with
SKY899 (see appendix A for signal characteristics). For digital interfaces select ARINC-429 (label 164
required). Select Arinc 552 or Arinc 552A for units that comply with these characteristics. All other choices
are DC analog interfaces, highlight your manufacturer/model and press SEL.

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

BRT
OFF
Rad Alt Valid Line

*None*
Active Low
Active High

EXIT SEL
NEXT PREV

Figure 4-20. Radio Altimeter Valid Line Menu

4-9
Rev. B
 SKY899
Installation Manual
The Landing Gear menu provides the following choices:

BRT
OFF
Landing Gear
*None*
Active Low
Active High

EXIT SEL
NEXT PREV

Figure 4-21. Landing Gear Menu

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

BRT
OFF
Weight-On-Wheels
*Active Low*
Active High

EXIT SEL
NEXT PREV

Figure 4-22. Weight-On-Wheels Menu

The Audio Suppression (audio inhibit) menu provides the following choices:

BRT
OFF
Audio Suppression
*None*
Active Low
Active High

EXIT SEL
NEXT PREV

Figure 4-23. Audio Suppression Menu

4-10
Rev. B
 SKY899
Installation Manual
The External Display menu is used to select display drivers and provides the following choices:

BRT
OFF
External Display
Using Next button to scroll
*None* down will cause these
Standard Type1
Standard Type2 additional menu choices to
Standard Type3 appear one at a time.
Sextant Type1
Sextant Type2 Forestry Serv
Sextant CG Standard Type4
Standard Type5
EXIT SEL
NEXT PREV

Figure 4-24. External Display Menu

Each alternate display will show the information consistent with the capabilities of that particular display.
Refer to table 4-1 when selecting display drivers, it list display drivers and ranges. Consider the following
when selecting the display driver:
• If "None" is selected the ARINC 429 alternate display output (see paragraph 2.9.3) is turned off and the
WX-1000/SKY497 display defaults to Standard Type 1.
• When selecting a display driver determine the range and function capabilities of your alternate display.
Select the driver that matches your alternate display. Refer to table 4-1 for display drivers.
• Standard Type 1 thru 5 are the typical display drivers to be used with the WX-1000/SKY497 display
and available for use with alternate displays. Sextant (1501/1502 displays) and Forestry Service
drivers should be selected only for those specific installations.
• If the system has more than one display the current range, altitude mode and the number of intruders
displayed may be different between displays.
• The display drivers determine which range the system will be in when it comes out of standby and self-
test, as well as the number of intruders displayed. Some alternate displays control their functions
internally and ignore portions or all of our display driver functions.
• When connecting a WX-1000/SKY497 display with other alternate displays select a display driver that
matches the ranges of the alternate displays. This will allow the WX-1000/SKY497 display to mirror
the ranges of the other displays (e.g., The Garmin GNS430 ranges are 2, 6, 12, & 24. Selecting
standard type 5 for a display driver will allow the WX-1000/SKY497 display to have the same ranges as
the GNS430).
Table 4-1. Alternate Display Drivers
DISPLAY STANDBY SELF-TEST
DISPLAY DRIVER NAME REMARKS
RANGES RANGE RANGE

None - - - No alternate display connected.

Standard Type 1 2, 6, 15 nmi 6 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
Standard Type 4 6, 12, 24 nmi 12 nmi 6 nmi
Standard Type 5 2, 6, 12, 24 nmi 12 nmi 6 nmi
Sextant Type 1 6, 12, 24 nmi 12 nmi 6 nmi Displays unrestricted mode, must use external lamps to
annunciate UNR mode.
Sextant Type 2 6, 12, 24 nmi 12 nmi 6 nmi Does not support unrestricted mode.
Sextant CG 6, 12, 24 nmi 6 nmi 6 nmi Does not support unrestricted mode.
Forestry Serv 2, 5, 10, 20 nmi 10 nmi 5 nmi Designed for U.S. Forestry Service application.

4-11
Rev. B
 SKY899
Installation Manual
4.4.2 Information
The information screens contain a record of software version, system (error) log and real-time sensor data
(data monitor). If you have problems with the SKY899 record the software version and the error messages,
then verify the Data Monitor screens match the aircraft wiring. 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:

BRT
OFF
Information
Software Version
System Log
Data Monitor

EXIT SEL
NEXT PREV

Figure 4-25. Information Menu

4.4.2.1.Software Version
Select Software Version menu to display the overall system software version.
NOTE
The software version identified on the TRC serial number tag represents the
system software revision and is a combination of the software/firmware
installed within the TRC. The software version displayed in this menu may
not match the software version (system revision) identified on the serial
number tag.
The Software Version menu displays the following:

BRT
OFF

Software Version
SkyHP Vx.x

EXIT

Figure 4-26. Software Version Menu

4.4.2.2 System Log

The 20 most recent errors detected by the system are saved in the System Log. For each error, the
corresponding error code and run-time of occurrence are saved. The system log, as shown in figure 4-27, is
displayed by selecting that option from the Information Menu.

4-12
Rev. B
 SKY899
Installation Manual
NOTE
Tables 4-3 and 4-4 provide a list and description of each error code (see paragraph 4.6 error
messages).

BRT
OFF
Sys Log 000032:28
LATEST 20 000030:24 TIME OF ERROR
ERROR CODE BarAlt Input Error (hhhhhh:mm, Run-Time in hours and minutes.)
## hhhhhh:mm
## hhhhhh:mm
## hhhhhh:mm
## hhhhhh:mm DESCRIPTION
OF ERROR
Using NEXT button to scroll EXIT SEL
down will cause additional NEXT PREV
errors (up to 20) to appear.

Figure 4-27. System Log Menu

The System Log displays the results in the following format:

## hhhhhh:mm
where:
## = Error code.
hhhhhh:mm = Run-time (in hours and minutes) when error occurred.
The total elapsed run-time is displayed beside the title in the upper middle portion of the screen (Sys Log
hhhhhh:mm).
With an error highlighted pressing SEL will cause the textual description to appear underneath the error.
If the System Log is empty, the following message is displayed:
NO FAULTS DETECTED
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
OFF
Data Monitors
Arinc 429
Antenna Calibration
Barometric Altitude
Discrete Values
GPS Nav
Mag Heading
Rad Altitude
EXIT SEL
NEXT PREV

Figure 4-28. Data Monitor Menu

4-13
Rev. B
 SKY899
Installation Manual
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 shows the configuration of the ARINC 429 receivers. If any
parity errors were detected the error cout per channel will be shown. A large increasing number of parity
erros may indicate the 429 wiring for that channel is reversed.

BRT
OFF
ARINC 429 Rcvrs
Ch 1: Multi high
parity: xxxxx
Ch 2: NoType high
parity: 0
Ch 3: NoType NoSpeed
parity: 0
Ch 4: NoType NoSpeed
parity: 0
Ch 5: NoType NoSpeed
parity: 0
EXIT

Figure 4-29. ARINC 429 Receivers Data Monitor

The Antenna Calibration Data Monitor screen shows the phase and calibration values for the selected
antenna (top or bottom). If the averaged current phase (Cur. Phase) differs from the calibration phase
(Cal. Phase) by morethan 30 degrees there may be problem with the antenna system or the antenna may
require recalibration.
The current amplitude (Cur. Amp) reflects the amplitude of the latest test signal. This could be used as a
means for evaluating interference. For example, if an active transponder lowers the value by more than 5
dBm system performance has been degraded by 5 dBm.

BRT
Data Monitor OFF
Antenna Calibration
Top Antenna
Cal. Phase: 129.76 deg
Cur. Phase: 130.10 deg
Cur. Amp: -80.00 dBm
Bottom Antenna
invalid
EXIT

Figure 4-30. Antenna Calibration Data Monitor

The Barometric Altitude Data Monitor screen shows the barometric encoded altitude (in gray code and feet)
and connector P1 pin assignments for the data inputs.

4-14
Rev. B
 SKY899
Installation Manual
BRT
Data Monitor OFF If Arinc 429 was selected
Baro Alt for Barometric Altitude
(Encoding Altimeter) source in equipment
Valid Altitude: 9000 ft menu the following data
A4=1 (P58) C4=0 (P69) monitor will appear:
A2=1 (P57) C2=1 (P68)
A1=0 (P56) C1=0 (P67)
B4=0 (P61) D4=0 (P71) (Arinc 429)
B2=1 (P60) D2=1 (P70)
B1=1 (P59))
EXIT
Valid Altitude: 9000 ft

Figure 4-31. Barometric Altitude Data Monitor

The Discrete Values Data Monitor screen shows the configuration and status of the aircraft discretes.

BRT
OFF
Data Monitor
Discretes
WOW sense: Active Low
WOW state: on grnd
Gear sense: Active Low
Gear state: down
Audio sense: Active Low
Audio state: Normal
EXIT

Figure 4-32. Discrete Values Data Monitor

The GPS Nav Data Monitor screen shows data read from the GPS/Navigation system.

BRT
OFF
Data Monitor
GPS Nav
(GAMA)
Lat 42.308 deg
Lon -82.020 deg
Trk invalid
Spd invalid

EXIT

Figure 4-33. GPS Nav Data Monitor

The Mag Heading Data Monitor screen shows data read from the heading source (i.e., heading, flag, & flag
configuration).

4-15
Rev. B
 SKY899
Installation Manual
BRT
OFF
Data Monitor If Arinc 429 was selected
Mag Heading for heading source in
(Synchro Compass) equipment menu the
following data monitor
Sense: Active Low will appear:
Validity: Valid
Heading: 29.8 degs (Arinc 429)
Mag Heading: 29.9 degs
EXIT True Heading: 35.0 degs
Status: Valid

Figure 4-34. Mag Heading Data Monitor

The Rad Alt Data Monitor screen shows data read from the radio altimeter (e.g,, source, altitude (in feet),
warning flag and flag configuration).

BRT
OFF
If DC Analog Radio
Data Monitor Altimeter was selected in
Rad Alt equipment menu the
(Arinc 429) following data monitor
will appear:
Validity: Valid
Altitude: 4005 ft (Bonzer Mark 10X)
Sense: Active Low
Validity: Valid
EXIT Altitude: 39 ft

Figure 4-35. Radio Altitude Data Monitor

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 Invalid.

The Calibration menu provides the following choices:

4-16
Rev. B
 SKY899
Installation Manual
BRT
OFF
Calibration
Top Antenna
The message SKY899 Bit Phase: 131.10 degs After a successful
Antenna Calibration in calibration, the new Bit
process... will be displayed Bottom Antenna
Bit Phase: Invalid Phase value will be
while calibration is being displayed.
performed.
EXIT SEL
NEXT PREV

Figure 4-36. Antenna Calibration Menu

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.

NOTE

If the calibration failed, the BIT phase value will be displayed as Invalid. If
calibration was successful a BIT phase value between 000 - 359 will be
displayed.

4.4.4. Ground Test

Ground Test initializes the system for on-the-ground testing. Select Ground test from the Service Menu
(i.e., press SEL with Ground Test highlighted).

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.

The Ground Test screen displays the following:

BRT
OFF
Ground Test
Perform Ground Test

EXIT SEL

Figure 4-37. Ground Test Menu

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

4-17
Rev. B
 SKY899
Installation Manual
BRT
OFF

Figure 4-38. Ground Test in Progress

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, BLW, or UNR).
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 archive (save) system configuration to a compact flash,
retrieve system configuration from a compact flash, restores system configuration to factory defaults or
update system software. To access configuration management, select it from the Service Menu. (Refer to
figure 4-40 for compact flash insertion instructions. For compact flash card part numbers refer to
paragraph 1.7 Equipment Required But Not Supplied.)

NOTE
A terminal device can be used to verify there is files located on the compact flash.
With the compact flash inserted in the TRC899, turn on power and at the
terminal device type Dir <Enter>. (The Dir command lists all files located in a
directory, if name is left blank it will show all directories and files located on the
compact flash.) See appendix E for terminal device operation information.

Archive to CF. Archive to compact flash can be used to create a backup copy of the system configuration.
This backup copy can be used to later restore system configuration or download system configuration to
other installations (i.e., OEM installation of same equipment model(s) during aircraft production).
Retrieve from CF. Retrieve from compact flash allows you to copy a previously saved system
configuration from a compact flash to your system.
Restore Factory Defaults. Restore factory defaults changes system configuration to factory defaults (i.e.,
ARINC 429 ports to none, Heading source to synchro compass, etc.). Restore to factory defaults will not
restore original system software version it will only restore configuration settings.
Software Update. Software update allows an authorized L-3 Avionics Systems representative to update
the system software in the field. The download software does not reside within the SKY899; it will be
located on the compact flash that contains the new system software version. The representative must
reference the appropriate service bulletin for software update instructions.

The Configuration Management screen displays the following:

4-18
Rev. B
 SKY899
Installation Manual
BRT
OFF
Config Management

Archive to CF
Retrieve from CF
Restore Factory Defaults
Software Update

EXIT SEL
NEXT PREV

Figure 4-39. Configuration Management Menu

J9
To insert the compact flash, perform the following 1

steps:
J10

1. Remove power from the SKY899 system. J1

INTERCONNECT

J11

CAUTION Goodrich Avionics Systems, Inc.

TRC899 Grand Rapids, Michigan USA

Removing or inserting the data card while A

I J
MODS
B C D

F G

K
H

L
P/N 805-11900-

S/N
Wt:
8.75 lbs.
3.97 kg.
SW VERSION
1.0 1.1 1.2 1.3

1.4 1.5 1.6 1.7

1.8 1.9 2.0 2.1

the TRC899 is powered on may result in

damage to the card. J7
TEST

2. At the TRC899 (see figure 4-40), open the J8

POWER

memory card door and insert compact flash into J12

MEMORY CARD

J12 connector. Be sure to align the arrow on the

compact flash card with the arrow above the
memory card door.

Figure 4-40. Compact Flash Insertion Instructions

4-19
Rev. B
 SKY899
Installation Manual
Service Menu

Setup
Information Information Menu Sheet 3 of 3
Calibration Calibration Menu Sheet 3 of 3
Ground Test Ground Test Menu Sheet 3 of 3
Config Management Configuration Management
Menu Sheet 3 of 3
Setup
EXIT SEL
Aircraft Type NEXT PREV
Antenna System
Audio Level
Arinc 429 Ports
Avionics Equipment

EXIT SEL Please wait... will

NEXT PREV be displayed while
autodetect is being
performed

Aircraft Type Antenna System Audio Level Save or Revert Equipment Arinc 429 Rcvrs
*Fixed Wing* Top Antenna Volume Changes have been made! Browse All Avionics Autodetect
Rotor Craft [NY156 Directional] [50%] GPS Nav Ch. 1: Multi 100 kHz
Bottom Antenna Up Save Changes [None] Ch. 2: NoType 100 kHz
[None] Down Revert to Old Settings Magnetic Heading Ch. 3: NoType NoSpeed
Test [Synchro Compass] Ch. 4: NoType NoSpeed
Barometric Altitude
[Encoding Altimeter] Ch. 5: NoType NoSpeed
EXIT SEL EXIT SEL EXIT SEL SEL Radio Altitude EXIT SEL
NEXT PREV NEXT PREV NEXT PREV NEXT PREV [None] NEXT PREV
Landing Gear
[None]
Weight-On-Wheels
Top Antenna [Active Low] Arinc 429 Rx Ch 1
Audio Suppression
*None* Screen appears [None] Type:
NY164 Directional when exiting Setup External Display BarAlt
NY156 Directional menu and changes [None] GPS
have been made Speed: 100 kHz
EXIT SEL
NEXT PREV

EXIT SEL EXIT SEL

NEXT PREV NEXT PREV
Avionics Equipment
submenu on sheet 2 of 3
Bottom Antenna Equipment Type

*None* NoType
NY164 Directional *BarAlt*
NY156 Directional MagHdg
*GPS*
RadAlt

EXIT SEL EXIT SEL

NEXT PREV NEXT PREV

Speed
12.5 kHz
* 100 kHz *

SEL
NEXT PREV

Figure 4-41. Service Menu Tree (Sheet 1 of 3)

4-20
Rev. B
 SKY899
Installation Manual
No Chan Assigned
Choose a channel Menu appears when
Avionics Equipment Submenu Ch.1: NoType 100kHz ARINC 429 equipment has
from Sheet 1 of 3 Ch.2: Multi 100 kHz been selected, but not
Ch.3: NoType NoSpeed assigned to a channel via
Ch.4: NoType NoSpeed the Communication Ports Menu
Ch.5: NoType NoSpeed

EXIT SEL
NEXT PREV
Equipment

Browse All Avionics

GPS Nav
[None]
Magnetic Heading
GPS Nav [Synchro Compass] Landing Gear
Barometric Altitude
*None* [Encoding Altimeter] *None*
GAMA Radio Altitude Active Low
ARINC 743A [None] Active High
Landing Gear
[None]
Weight-On-Wheels
[Active Low]
EXIT SEL Audio Suppression EXIT SEL
NEXT PREV [None] NEXT PREV
External Display
[None]

EXIT SEL
Heading NEXT PREV Weight-On-Wheels
None *Active Low*
*Synchro Compass* Active High
Arinc 429

Barometric Altitude
EXIT SEL EXIT SEL
NEXT PREV Arinc 429 NEXT PREV
Encoding Altimeter
Radio Altimeter

*None*
Heading Valid Line Arinc429 Audio Suppression
Arinc 552
*None* Arinc 552A *None*
Active Low EXIT SEL
NEXT PREV Bonzer Mark 10X Active Low
Active High Collins ALT-50 Active High
Collins ALT-55
King KRA10/10A
King KRA 405
Sperry AA-100
EXIT SEL Terra TRA 3000
NEXT EXIT SEL
PREV NEXT
EXIT SEL PREV
NEXT PREV
External Display

Rad Alt Valid Line *None*

Standard Type1
*None* Standard Type2
Active Low Standard Type3
Active High Sextant Type1
Sextant Type2
Sextant CG
Forestry Serv
Standard Type4
Standard Type5
EXIT SEL
NEXT PREV EXIT SEL
NEXT PREV

Figure 4-41. Service Menu Tree (Sheet 2 of 3)

4-21
Rev. B
 SKY899
Installation Manual
From Service Menu Sheet 1 of 3

SKY899 Antenna Calibration

Information in process... will be displayed
while calibration is being
Software Version performed
System Log
Data Monitor Ground Test
Calibration Config Management
Top Antenna Perform Ground Test
Bit Phase: 131.10 degs Archive to CF
Retrieve from CF
EXIT SEL Bottom Antenna Restore Factory Defaults
NEXT PREV Bit Phase: Invalid Software Update

EXIT SEL EXIT SEL EXIT SEL

Sys Log 000032:28 NEXT PREV NEXT PREV
20 000030:24
BarAlt Input Error
## hhhhhh:mm With an Error highlighted
## hhhhhh:mm pressing SEL will
## hhhhhh:mm cause error description
## hhhhhh:mm to appear
EXIT SEL
NEXT PREV

Software Version

SkyHP Vx.xx

Data Monitor
Baro Alt
(Encoding Altimeter)
EXIT Valid Altitude: 9000 ft
A4=1 (P58) C4=0 (P69)
A2=1 (P57) C2=1 (P68)
A1=0 (P56) C1=0 (P67) (Arinc 429)
B4=0 (P61) D4=0 (P71)
B2=1 (P60) D2=0 (P70)
B1=1 (P59)) Valid Altitude: 9000 ft
Data Monitors EXIT

Arinc 429
Antenna Calibration
Barometric Altitude
Discrete Values
GPS Nav
Mag Heading
Rad Altitude
EXIT SEL
NEXT PREV

ARINC 429 Rcvrs Data Monitor Data Monitor Data Monitor Data Monitor Data Monitor
Antenna Calibration Rad Alt Mag Heading GPS Nav Discretes
Ch 1: Multi high
parity: xxxxx Top Antenna (Arinc 429) (Synchro Compass) (GAMA)
Ch 2: NoType high WOW sense: Active Low
parity: 0 Cal. Phase: 129.76 deg Lat 42.308 deg WOW state: on grnd
Ch 3: NoType NoSpeed Cur. Phase: 130.10 deg Validity: Valid Sense: Active Low Lon -82.020 deg Gear sense: Active Low
parity: 0 Cur. Amp: -80.00 dbm Altitude: 4005 ft Trk invalid Gear state: down
Ch 4: NoType NoSpeed Validity: Valid
Heading: 29.8 degs Spd invalid Audio sense: Active Low
parity: 0 Bottom Antenna
Ch 5: NoType NoSpeed invalid Audio state: Normal
parity: 0
EXIT EXIT EXIT EXIT EXIT EXIT

(Bonzer Mark 10X) (AHRS)

Sense: Active Low Mag Heading: 29.8 degs

Validity: Valid True Heading: 35.0 degs
Altitude: 39 ft Status: Valid

Figure 4-41. Service Menu Tree (Sheet 3 of 3)

4-22
Rev. B
 SKY899
Installation Manual
4.5 TROUBLESHOOTING
Table 4-2 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, the service menu must be accessed via an RS-232
terminal device, see Appendix E for operating instructions.
Table 4-2. Fault Isolation
SYMPTOM CORRECTIVE ACTION

RF Failure (error 12) or antenna calibration screen displays a. Verify antenna location and type was correctly set
an invalid BIT phase during the calibration procedure. during setup.
b. Calibrate antenna by selecting calibration from setup
menu. Verify BIT phase shows a number and not an
invalid message.
c. Check directional antenna and associated cables.

Display remains dark after SKY899 is powered ON. a. Check position of the WX-1000 maintenance switch
(NORMAL/OVERRIDE).
b. Reset circuit breaker if it is tripped.
c. Check aircraft power source.
d. Check connection to WX-1000 processor, if installed.
e. Check power input at TRC mating connector.
P8-A +28V (18 - 32 V dc PWR)
P8-B +28V_RET (AIRCRAFT PWR RETURN)
f. Check cables connected to display.
g. Replace Display.
Display is distorted. Check for interference from aircraft systems.
Incorrect response to buttons (soft-keys). Check soft-key wiring inside display cable and WX-1000
processor cable (if installed).
SKY899 will not enter service menu. a. If using an WX-1000/SKY497 display check soft-key
wiring.
b. If using an alternate display service menu must be
accessed with an RS-232 terminal device. (Appendix E)

The self-test successfully completes without audio a. Check headphones/speaker and aircraft audio panel
annunciation. 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)
SKY899 Failed. a. Check system log (para 4.4.2) for errors. Error
messages are detailed in para 4.6.
b. Replace TRC.

Self-test does not execute. Aircraft is on the ground. a. If standby screen is displayed, check soft-key wiring
inside display cable and WX-1000 processor cable
(if installed).
b. Check squat switch connection to the TRC and the
weight-on-wheels configuration in service menu.
Squat Switch Input: P1-24
The display cannot be switched between SKY899 and the a. Check circuit breakers. Reset if tripped.
WX-1000. Both systems are installed. b. Check position of the WX-1000 maintenance switch
(SW2). It should be set to the NORMAL position.
c. Check wiring of the SKYWATCH/Stormscope display
mode switch (para 2.24.1 and figure 2-2).

4-23
Rev. B
 SKY899
Installation Manual
Table 4-2. Fault Isolation (Continued)
SYMPTOM CORRECTIVE ACTION
WX-1000 processor has been removed for service; Check position of the WX-1000 maintenance switch
SKY899 fails to operate. (NORMAL/OVERRIDE). When the WX-1000 has been
removed for service, it should be set to the OVERRIDE
position. This switch may be located in the avionics bay.
SKY899 paints own aircraft as an intruder (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 WX- Check the adapter plug (see para 4.7). If the TRC899 is
1000 Stormscope fails to operate. removed for service, an adapter plug is required to permit
continued operation of the WX-1000.
Alternate dislay does not show traffic information. a. Access the Service Menu and verify that an alternate
display driver has been selected.
b. Check connection to TRC.
Alternate Display Output:
P1-42 (A429TX1-A)
P1-43 (A429TX1-B)

4.6 ERROR MESSAGES

The 20 most recent errors detected by the system are saved in the System Log (see paragraph 4.4.2.2). For
your convenience, in table 4-3, we have listed the error messages that have been associated with SKY899
installations. Where appropriate, procedures that may assist in resolving installation problems are
provided. When a severe error occurs SKY899 will fail.
Table 4-3. 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 configuration module.
c. Replace TRC.
ERROR 10 Compact Flash Error a. Unable to read the compact flash information correctly, verify compact flash is inserted
into J12 correctly. Refer to figure 4-40.
b. Try a different compact flash.
c. Replace TRC.
ERROR 14 RF Amplitude Error a. Check directional antenna and associated cables.
b. Calibrate directional antenna (para 4.4.3)
NOTE
Ensure transponder is in standby and DME is OFF while doing calibration
c. Cycle power and run pilot initiated self-test.
ERROR 15 RF Angle Error a. Check directional antenna and associated cables.
b. Calibrate directional antenna (para 4.4.3)
NOTE
Ensure transponder is in standby and DME is OFF while doing calibration
c. Cycle power and run pilot initiated self-test.
ERROR 17 Mag Var Table Error a. Unable to read the compact flash information correctly, verify compact flash is inserted
into J12 correctly.
b. Try a different compact flash.
c. Replace TRC.

4-24
Rev. B
 SKY899
Installation Manual
Table 4-3. Installation Related Error Messages (Continued)
ERROR NO. MESSAGE REMARKS

ERROR 20 Barometric Input Error a. Verify altimeter source is turned on, warmed up, and is selected correctly in service
menu.
b. Cycle power.
c. Ensure that barometric altitude input data is from only one source (gilham code or
ARINC-429).
d. Encoded inputs can be checked from the barometric altimeter data monitor screen (para
4.4.2.3).
e. Using the service menu, verify barometric source configuration and altitude information
(para 4.4.2.3).
f. Check wiring associated with altimeter source.

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 recover automatically.
d. Check wiring associated with synchro compass input.

ERROR 29 System Config Error Check wiring associated with configuration module if error reoccurs replace configuration
module.

MSG GPS Input Error Degraded operation, ADS-B feature will not be usable.
Degraded message a. Verify GPS source is it turned on and locked onto satellites.
appears on WX-1000 b. Using the service menu, verify configuration (speed and equipment type) is set correctly.
display c. Check ARINC-429 wiring associated with GPS.

MSG Heading Input Error No heading input being received (ARINC-429 or synchro compass). Degraded operation; will
cause targets to disappear from the screen when your aircraft changes heading.
a. Check heading source.
b. Using the service menu, verify heading setup in Mag Heading data monitor (para
Degraded message
4.4.2.3).
appears on WX-1000
c. If the heading signals become valid, the system will recover automatically.
display
d. Check wiring associated with heading input.

The error messages in table 4-4 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 4-4. 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 Analog/PS Error ERROR 28 NVRAM Error

ERROR 12 RF Failure Error ERROR 30 System Test Error

ERROR 13 RF Transmitter Error

4-25
Rev. B
 SKY899
Installation Manual
4.7 TRC899/WX-1000 ADAPTER PLUG
An adapter plug can be used to by-pass SKY899 only if a WX-1000 Stormscope system is installed. The
adapter will permit continued operation of the WX-1000 if the TRC899 is removed for service. It can also be
used as a troubleshooting tool when attempting to isolate a problem to either or both systems.
The adapter plug mates with P1. It can be purchased from L-3 Avionics Systems (P/N 805-11910-001) or
fabricated locally from the details provided in figure 4-42.

ADAPTER PLUG CONNECTIONS PIN INSERT VIEW

JUMPER PINS FUNCTION

35 56
25 46 67
8 25 DPWR+15 16 77
8 86
9 26 DPWR-15
1 94
10 27 DSPLY_GND
2
11 28 HSYNC_+ 3
12 29 HSYNC_-
13 30 VSYNC_+
22 41 VSYNC_- 7
16 35 VIDEO_+ 100

17 36 VIDEO_- 15 93
24 85
18 37 SFTKEY1 34 55 76
45 66
19 38 SFTKEY2
20 39 SFTKEY3
ADAPTER PLUG JUMPER INSTALLATION
21 40 SFTKEY4

NOTE
®
APPLY LOCTITE TO THE INTERNAL THREADS
OF THE BACKSHELL PRIOR TO ASSEMBLY.

+0.07
0.10 -0.00

CRIMP PIN

JUMPER
#22 AWG WIRE SHORTING CAP
BACKSHELL
GLENAIR #340HS002M23-2H12A
CONNECTOR
MIL # D38999/20FH35PB

Figure 4-42. Adapter Plug Assembly

4-26
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 SKY899
Installation Manual
4.8 DISPOSITION OF FAILED ITEMS
Return defective components to your authorized L-3 Avionics Systems dealer or to:

L-3 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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4-28
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 SKY899
Installation Manual

APPENDIX A
SKY899 INTERFACE
SIGNAL & CABLE CHARACTERISTICS
A.1 INTRODUCTION
This appendix defines the electrical characteristics of all input/output signals to the TRC899 and the labels
for the ARINC-429 data bus. Sufficient data is included to perform an electrical load analysis for the
aircraft. The interface characteristics contained in this appendix are fully compatible with ARINC
specifications where noted. Connection information identifies connector-pin and signal names as they
appear on interconnect wiring diagram, figure A-1 shows P1 connector pin locations and signal names.
NOTE
External isolation diodes are not required and SHOULD NOT be installed.
A.2 ELECTRICAL CHARACTERISTICS
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 Signal Name
P1-56 ALT_A1
P1-57 ALT_A2
P1-58 ALT_A4
P1-59 ALT_B1
P1-60 ALT_B2
P1-61 ALT_B4
P1-67 ALT_C1
P1-68 ALT_C2
P1-69 ALT_C4
P1-70 ALT_D2
P1-71 ALT_D4
P1-72 ALT_COMN
CABLE Minimum 22 AWG wire for lengths up to 30 ft.
VOLTAGE +30 V input max.
CURRENT <1 mA sourced per line.
FREQUENCY <100 Hz
SOURCE Z >10 kΩ per line.
MAX CAPACITANCE <20 pF per line.

A-1
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 SKY899
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SIGNAL CHARACTERISTICS
Antenna Top Directional SUM (SIGMA) Port (Blue)
J9 CONNECTION Connector Signal Name
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)
J10 CONNECTION Connector Signal Name
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)
J11 CONNECTION Connector Signal Name
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 ARINC-429
transmitters (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. The
transmitters operate only at high speed (100 kHz).
The first ARINC-429 transmitter (A429TX1) is intended to provide the
capability to interface with alternate display device. The second and third
ARINC-429 transmitters (A429TX2 & TX3) are future options.
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 Heading can be ARINC-429 or Synchro (XYZ).
Select only one source for each aircraft input.
3. If 429 barometric altitude is used, it should be from the same source
that is interfaced with the transponder or it must be at least as
accurate as that source, i.e., ± 125 ft.
4. Receive channels 1 and 2 must be set to the same speed (12.5 or 100
kHz). Receive channels 3 and 4 must be set to the same speed (12.5
or 100 kHz). Channel 5 is independent of the other receivers and
can be to 12.5 or 100 kHz.

A-2
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 SKY899
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SIGNAL CHARACTERISTICS

ARINC-429 External Interface CONNECTION Connector-Pin Signal Name

(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)
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 Signal Name
P1-89 (AUDIO_H) - 600 Ω
P1-90 (AUDIO_L) - 150 Ω
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
LOAD Z Selectable 150 or 600 Ω
Debug Port NO CONNECTION TO EXISTING AIRCRAFT WIRING. The Debug Port (RS-232) is
used for laptop interface to support system setup, post installation
checkout and troubleshooting. The port defaults to the following settings:
Baud Rate: 19,200
Data Bits: 8
Parity: None
Stop Bits: 1
Flow Control: Xon/Xoff

A-3
Rev. B
 SKY899
Installation Manual
SIGNAL CHARACTERISTICS

Debug Port (Continued) CONNECTION Connector-Pin Signal Name

J7-2 DIAG_RX
J7-3 DIAG_TX
J7-5 DIAG_GND
J7-7 CTS
J7-8 RTS

GPWS This input senses a terrain warning alarm and temporarily disables the
(Audio Inhibit) SKY899 audible alert messages until the warning clears (see paragraph
2.7.1).
The input can be either a constant flag signal or an alternating flag output.
The flag must be cleared for five (5) seconds before the TRC accepts a "NO
ALARM" condition and restores audible alerts. IF THE AIRCRAFT IS NOT
EQUIPPED WITH TERRAIN WARNING SYSTEM, LEAVE THIS INPUT
UNCONNECTED.
NOTE
If the aircraft is equipped with terrain warning system the
GPWS, EGPWS, or TAWS flag must be connected to the TRC.
CONNECTION Connector-Pin Signal Name
P1-34 (GPWS)
CABLE Minimum 22 AWG wire for lengths up to 30 ft.
VOLTAGE Active Low: (ref. to aircraft electrical ground)
WARNING: -5 V dc to +2.5 V dc
NO WARNING: +9 V dc to +30 V dc or open
Active High: (ref. to aircraft electrical ground)
WARNING: +9 V dc to +30 V dc
NO WARNING: -5 V dc to +2.5 V dc or open
CURRENT <5 mA sourced.

GEAR This signal line is to be connected to the landing gear switch to sense the
(Landing Gear Switch Input) position of the landing gear (fixed, up or down, see paragraph 2.7.2). The
state of the switch can be active low or active high in reference to aircraft
ground. The switch status can be fixed, active low or active high, this is
selected via service menu.
IF THE AIRCRAFT DOES NOT HAVE A LANDING GEAR SWITCH, THIS INPUT MUST
REMAIN UNCONNECTED. With this configuration, if no ARINC 429 compatible
radio altimeter is installed, the system will default to the highest TA
sensitivity level (level B) and audio TA announcements (i.e., “traffic, traffic”)
will not be inhibited during takeoff and landing.
CONNECTION Connector-Pin Signal Name
P1-33 GEAR
CABLE Minimum 22 AWG wire for lengths up to 30 ft.

A-4
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 SKY899
Installation Manual
SIGNAL CHARACTERISTICS

GEAR (Continued) VOLTAGE Fixed Gear: Open or no connection

Active Low: (ref. to aircraft electrical ground)
Gear Down: -5 V dc to +2.5 V dc
Gear Up: +9 V dc to +32 V dc or open
Active High: (ref. to aircraft electrical ground)
Gear Down: +9 V dc to +32 V dc
Gear Up: -5 V dc to +2.5 V dc or open
CURRENT <5 mA sourced.
SOURCE Z >40 kΩ
MAX CAPACITANCE <20 pF

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
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
higher levels.)
INPUT IMPEDANCE >50 kΩ
CONNECTION Connector-Pin Signal Name
P1-46 HEADING_X
P1-47 HEADING_Y
P1-48 HEADING_Z
CABLE See paragraph 2.6.4.
H and C (high and low reference - 400 Hz)
FREQUENCY Min: 320 Hz
Max: 480 Hz
VOLTAGE Min: 3 V ac rms
Max: 35 V ac rms
INPUT IMPEDANCE >50 kΩ
CONNECTION Connector-Pin Signal Name
P1-49 HEADING_H
P1-50 HEADING_C
CABLE See paragraph 2.6.4.
Heading Valid Indicates that the heading source is providing valid heading information.
The status of the heading valid signal can be none, active low, or active
high and must be selected during system setup via the service menu.

CONNECTION Connector-Pin Signal Name

P1-51 HEADING_FLG
CABLE See paragraph 2.6.4.

A-5
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 SKY899
Installation Manual
SIGNAL CHARACTERISTICS
Heading Valid (Continued) VOLTAGE None: Open or no connection
Active Low: (ref. to aircraft electrical ground)
Valid signal: -5 V dc to +2.5 V dc
Invalid signal: +9 V dc to +32 V dc or open
Active High: (ref. to aircraft electrical ground)
Valid signal: +9 V dc to +32 V dc
Invalid signal: -5 V dc to +2.5 V dc or open
INPUT IMPEDANCE >2 kΩ
INPUT CURRENT Active: Min: 1 mA
Max: 15 mA
Horizontal Sync Balanced horizontal sync from the WX-1000 Processor (if installed) and
output to the WX-1000/SKY497 display. Signal levels as specified in
RS-422.
CONNECTION Connector-Pin Signal Name
P1-28 (HSYNC_IN+) From Processor
P1-29 (HSYNC_IN-) From Processor
P1-11 (HSYNC_OUT+) To Display
P1-12 (HSYNC_OUT-) To Display
CABLE See paragraph 2.6.7.
VOLTAGE 0-5 V dc
CURRENT <100 mA
FREQUENCY 16.4 kHz
LOAD Z 1 kΩ
Lamp Outputs External annunciators are required when using an alternate display that
(above and below) is not capable of displaying above, below, and unrestricted vertical modes.
Outputs are switched to ground when active. The lamps require a separate
dc source (constant or dimming circuit). If lamp voltage is an ac source
then an isolation relay must be used.
Depending on the vertical display mode selected the appropriate
annunciator will light. If in normal vertical display mode neither lamp will
light, if in above mode the ABV lamp will light, if in below mode then the
BLW lamp will light, and when unrestricted vertical mode is selected both
lamps will light.
CONNECTION Connector-Pin Signal Name
P1-66 LP1OUT - (ABV)
P1-85 LP2OUT - (BLW)
CABLE Minimum 22 AWG wire for lengths up to 30 ft.
VOLTAGE ON: 0 V dc or Ground
OFF: Maximum +32 V dc or open
CURRENT Maximum current 300 mA.
ON/OFF Power This input turns the TRC on and off. (See paragraph 2.24.2) When an
alternate display is installed a separate switch may be required, any
general purpose SPDT toggle switch capable of 1/2 A @ 28 V dc can be
used.

A-6
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 SKY899
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SIGNAL CHARACTERISTICS
ON/OFF Power (Continued) When a WX-1000 processor is connected to with a SKY899 a maintenance
(SW2) over-ride switch is necessary to enable the SKY899 to be powered-up if the
WX-1000 processor has been removed for service. During normal
operation, with a WX-1000 processor installed, SW2 should remain in the
WX-1000 position. Any general purpose DPDT toggle switch can be used.

CONNECTION Connector-Pin Signal Name

P1-4 ON/OFF
P1-5 ON/OFF_RET
CABLE Minimun 22 AWG.
VOLTAGE Less than 0.7 V = ON; open = OFF.
CURRENT <100 mA
Operational Mode Output Operational mode output can drive a lamp annunciating when the system
(optional) is in operational mode. Output is switched to ground when system is in
operation mode. The lamp requires a separate dc source (constant or
dimming circuit). If lamp voltage is an ac source then an isolation relay
must be used.
CONNECTION Connector-Pin Signal Name
P1-31 OPER_MODE
CABLE Minimum 22 AWG wire for lengths up to 30 ft.
VOLTAGE ON: 0 V dc or Ground
OFF: Maximum +32 V dc or open
CURRENT Maximum current 300 mA.
Power Input (TRC) 18-32 V dc. A 5 A circuit breaker is required.
CONNECTION Connector-Pin Signal Name
P8-A +28V
P8-B +28V_RET
CABLE Use #16 AWG (min.) twisted shielded pair cable
(Beldon 83322, Alpha 2826/2, or equivalent).
Terminate shield to airframe at sensor or power
source.
VOLTAGE 18 to 32 V dc, 70 Watts (Maximum)
Radio Altimeter (Analog) A radio altimeter enables ground intruder filtering, optimizes TA
sensitivity levels, and makes it possible to inhibit audio below 400 AGL.
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 RADIO_ALT_FLG (P1-14) unconnected.
Some analog radio altimeters have multiple outputs (e.g., King model
KRA405), verify the output connected to matches the signal characteristics
listed in table A-1.
CONNECTION Connector-Pin Signal Name
P1-6 RAD_ALT_IN_HI
P1-7 RAD_ALT_IN_LO
P1-14 RADIO_ALT_FLG
CABLE Minimum 22 AWG twisted shielded pair cables for
lengths up to 30 ft for signal input. Minimum 22
AWG wire for lengths up to 30 ft for flag input.

A-7
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 SKY899
Installation Manual
SIGNAL CHARACTERISTICS
Radio Altimeter (Analog) VOLTAGE 0 to +35 V dc
(Continued) LOAD Z >100 k Ohm
MAX CAPACITANCE <20 pF per line.
FLAG VOLTAGE Active Low: (ref. to aircraft electrical ground)
Valid signal: -5 V dc to +2.5 V dc
Invalid signal: +9 V dc to +32 V dc or open
Active High: (ref. to aircraft electrical ground)
Valid signal: +9 V dc to +32 V dc
Invalid signal: -5 V dc to +2.5 V dc or open

NOTE
If connected, 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 modification to the radio altimeter. Check with
the specific altimeter manufacturer for compatibility and availability of
modification, if necessary.

Table A-1. Compatible Analog Radio Altimeter Specifications

OUTPUT DC
ALTIMETER ALTITUDE RANGE OUTPUT DC VOLTAGE
VOLTAGE RANGE

0 to +500 ft 20 mV/ft
ARINC 0 to 2500 ft 0 to +26.0944 V
+500 to +2500 ft 10 Ln 2.178 x ft
Characteristic 552
500

-20 to +480 ft 20 mV/ft + 0.4 V

ARINC 0 to 2500 ft 0 to +26.1741 V
+480 to +2500 ft 10 Ln 2.178 x (ft + 20)
Characteristic 552A
500

Bonzer Mark 10X +40 to 2500 ft +0.4 to +25 V +40 to +2500 ft 10 mV/ft

0 to +16.4 V -20 to +500 ft 20 mV/ft + 0.4 V

Collins ALT-50 0 to 2000 ft
(+18 ±0.5 V Offscale) +500 to +2000 ft 3 mV/ft + 10.4 V

0 to +16.4 V -20 to +500 ft 20 mV/ft + 0.4 V

Collins ALT-55 0 to 2500 ft
(+18 ±0.5 V Offscale) +500 to +2500 ft 3 mV/ft + 10.4 V

+0.8 to +21 V
King KRA10/10A +20 to 2500 ft +20 to +2500 ft 4 mV/ft
(+19 ±2 V Offscale)

King KRA 405 -20 to +500 ft 20 mV/ft + 0.4 V

0 to 2500 ft 0 to +16.4 V
(Aux. Output #1) +500 to +2500 ft 3 mV/ft + 10.4 V

+40 to +500 ft 6.2 mV/(ft - 40) + 0.198 V

Sperry AA-100 0 to 2500 ft +0.198 to +4.066 V
+500 to +2500 ft 508 µV/(ft - 500) + 3.05 V

Terra TRA 3000 +40 to 2500 ft +0.1 to +6.25 V +40 to +2500 ft 2.5 mV/ft

Radio Altimeter (Digital) See ARINC-429 External Interface in paragraph A.2.

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 SKY899
Installation Manual
SIGNAL CHARACTERISTICS

SKYWATCH/STORMSCOPE If a WX-1000 processor is installed, this signal (SW1 on the Interconnect

(SW1) wiring diagram, figure 2-3) switches the display between the WX-1000 and
SKY899. Any general purpose SPST toggle switch can be used.
CONNECTION Connector-Pin Signal Name
P1-15 SMS
P1-23 SMS_RET
CABLE Minimum 22 AWG.
VOLTAGE CLOSED (< 0.7 V dc) = Stormscope display mode
OPEN = SKYWATCH display mode.
CURRENT <100 mA
Soft-keys Soft-key inputs come from the WX-1000/SKY497 display and are sent the
WX-1000 processor (if installed). The pushbuttons on the front of the
display are referred to as soft-keys (1), (2), (3), and (4). In every operating
mode a label identifying the button function is displayed next to the
button.
When using an alternate display device reference figure 2-4 as well as
manufacturer instructions concerning these connections. Required soft-key
connections will depend upon the alternate display capabilities (e.g., some
displays control operation mode internally and ranges externally, while
others handle ranges internally and operation modes externally). When
installing multiple alternate displays, soft-keys inputs may require several
displays being connected to the same input (e.g., WX-1000/SKY497
connected to all soft-key inputs, GNS430 to soft-keys 2 & 4 and Collins
EFIS to soft-keys 2, 3, & 4).

CONNECTION Connector-Pin Signal Name

P1-18 SFTKEY1_IN From Display
P1-19 SFTKEY2_IN From Display
P1-20 SFTKEY3_IN From Display
P1-21 SFTKEY4_IN From Display
P1-37 SFTKEY1_OUT To WX-1000 Processor
P1-38 SFTKEY2_OUT To WX-1000 Processor
P1-39 SFTKEY3_OUT To WX-1000 Processor
P1-40 SFTKEY4_OUT To WX-1000 Processor
CABLE See paragraph 2.6.7
VOLTAGE Active: Min: 0.0 V
Max: 1.5 V
Inactive: Min: 3.5 V or Open
(Internal 4.7 kΩ pull-up)
Max: 5.0 V

A-9
Rev. B
 SKY899
Installation Manual
SIGNAL CHARACTERISTICS

Squat Switch Input This signal line is to be connected to the squat switch to sense when the
(Weight-On-Wheels) aircraft is on the ground (see paragraph 2.7.3). The state of the switch can
be active low or active high in reference to aircraft ground. The switch
status can be none, active low or active high, this is selected via service
menu.
If a squat switch is not installed on the aircraft, it is recommended to
install a switch, which will enhance system operation.
CONNECTION Connector-Pin Signal Name
P1-24 SQUAT

CABLE Minimum 22 AWG wire for lengths up to 30 ft.

VOLTAGE None: Open or no connection
Active Low: (ref. to aircraft electrical ground)
On Ground: -5 V dc to +2.5 V dc
Flying: +9 V dc to +32 V dc or open
Active High: (ref. to aircraft electrical ground)
On Ground: +9 V dc to +32 V dc
Flying: -5 V dc to +2.5 V dc or open
CURRENT <5 mA sourced.
Suppression Bus I/O The SKY899 outputs a 100 µs (± 5 µs) suppression pulse on the aircraft
suppression bus (see paragraph 2.21). In addition, the SKY899 receives
suppression signals from all other devices on the suppression bus (e.g.,
transponder, DME). (Reference ARINC 735-2 and DO-197A.)
CAUTION
The aircraft transponder must have suppression circuitry to ensure
that SKYWATCH HP does not paint itself as a target (e.g., TA).
CONNECTION Connector-Pin Signal Name
P1-93 SUPBUS
CABLE Any size low capacitance shielded cable may be used.
VOLTAGE 18 - 70 V dc input, greater than 20 V dc output.
CURRENT 0.3 A output max.
PERIOD ATCRBS - 100 µs ± 5 µs output
SOURCE Z 2 kΩ
LOAD Z 10.5 kΩ
MAX CAPACITANCE <50 pF
System Configuration Module The system configuration module is used to store aircraft installation
dependent information. Aircraft specific information is selected via the
service menu, typically during system setup. Once the setup settings have
been saved the system configuration will stay with the aircraft wiring
allowing the TRC to be replaced or exchanged without having to re-
configure the TRC. When powered up the configuration information is sent
to the TRC via the bi-directional serial data bus (SDA). The configuration
module is located inside backshell of P1 connector. See paragraph 2.22.

A-10
Rev. B
 SKY899
Installation Manual
SIGNAL CHARACTERISTICS

System Configuration Module CONNECTION Connector-Pin Signal Name

(Continued)
P1-2 3.3V
P1-92 PLUG_GND
P1-99 SDA
P1-100 SCL
CABLE Minimum 22 AWG wire for lengths up to 30 ft.
Vertical Sync Balanced vertical sync from the WX-1000 Processor (if installed) and
output to the display. Signal levels as specified in RS-422.
CONNECTION Connector-Pin Signal Name
P1-30 VSYNC_IN+ From Processor
P1-41 VSYNC_IN- From Processor
P1-13 VSYNC_OUT+ To Display
P1-22 VSYNC_OUT- To Display
CABLE See paragraph 2.6.7
VOLTAGE 0-5 V dc
FREQUENCY 60 Hz
SOURCE Z 1 kΩ
Video Output Balanced video from the WX-1000 Processor (if installed) and output to the
display. Signal levels as specified in RS-422 specification.
CONNECTION Connector-Pin Signal Name
P1-35 VIDEO_IN+ From Processor
P1-36 VIDEO_IN- From Processor
P1-16 VIDEO_OUT+ To Display
P1-17 VIDEO_OUT- To Display
CABLE See paragraph 2.6.7
VOLTAGE 0-5 V dc
CURRENT <100 mA
FREQUENCY <15 MHz
LOAD Z 1 kΩ

WX-1000/SKY497 Display Power supply to WX-1000/SKY497 display. +15/-15 V dc from the Display
Power WX-1000 Processor (if installed) and output to the display.
CONNECTION Connector-Pin Signal Name
P1-25 DPWR+15_IN From Proc.
P1-26 DPWR-15_IN From Proc.
P1-27 DSPLY_GND_IN From Proc.
P1-8 DPWR+15_OUT To Display
P1-9 DPWR-15_OUT To Display
P1-10 DSPLY_GND_OUT To Display
CABLE See paragraph 2.6.7
VOLTAGE +15/-15 V dc
CURRENT 0.7 A input max.

A-11
Rev. B
 SKY899
Installation Manual
SIGNAL CHARACTERISTICS

Future Options The following connections are reserved for future use. THESE PINS MUST
REMAIN UNCONNECTED.
CONNECTION Connector-Pin Signal Name
P1-1 +5 V
P1-3 -15 V
P1-32 DI02
P1-77 RS422_TXA
P1-78 RS422_TXB
P1-79 RS422_RXA
P1-80 RS422_RXB
P1-86 RS232_TX2
P1-87 RS232_RX2
P1-88 RX232_GND2
P1-83 A429RX7_A
P1-84 A429RX7_B
P1-81 A429RX8_A
P1-82 A429RX8_B
P1-44 A429TX2_A
P1-45 A429TX2_B
P1-52 A429TX3_A
P1-53 A429TX3_B

A-12
Rev. B
 TRC899 TRC497 TRC899 TRC497
SKY899
Installation Manual
SIGNAL NAME PIN PIN SIGNAL NAME SIGNAL NAME PIN PIN SIGNAL NAME
+5V P1-01 ----- ----- HEADING_FLG P1-51 P1-53 HDG_FLG+
3.3V P1-02 ----- ----- A429TX3_A P1-52 ----- -----
-15V P1-03 ----- ----- A429TX3_B P1-53 ----- -----
ON/OFF P1-04 P1-11 PW_SW_HI A429RX1_A P1-54 P1-45 ARINC-429 RX 1A
ON/OFF_RET P1-05 P1-03 PW_SW_LO A429RX1_B P1-55 P1-44 ARINC-429 RX 1B
RAD_ALT_IN_HI P1-06 ----- ----- ALT_A1 P1-56 P1-40 ALT_A1
PIN INSERT VIEW
RAD_ALT_IN_LO P1-07 ----- ----- ALT_A2 P1-57 P1-41 ALT_A2
DPWR+15_OUT P1-08 P1-07 DPWR+15_OUT ALT_A4 P1-58 P1-50 ALT_A4
DPWR-15_OUT P1-09 P1-06 DPWR-15_OUT ALT_B1 P1-59 P1-51 ALT_B1
35 56
DSPLY_GND_OUT P1-10 P1-14 DSPLY_GND ALT_B2 P1-60 P1-56 ALT_B2
VIDEO_IN+ ALT_A1
HSYNC_OUT+ P1-11 P1-49 HSYNC_OUT_HI ALT_B4 P1-61 P1-57 ALT_B4 25 46 67
HSYNC_OUT- P1-12 P1-48 HSYNC_OUT_LO A429RX2_A P1-62 P1-43 ARINC-429 RX 2A
DPWR+15_IN HEADING_X ALT_C1
VSYNC_OUT+ P1-13 P1-63 VSYNC_OUT_HI A429RX2_B P1-63 P1-42 ARINC-429 RX 2B 16 36 57 77
RADIO_ALT_FLG P1-14 ----- ----- A429RX3_A P1-64 ----- ----- VIDEO_OUT+ VIDEO_IN- ALT_A2 RS422_TXA
SMS P1-15 P1-31 CWS_SS A429RX3_B P1-65 ----- ----- 8 26 47 68 86

VIDEO_OUT+ P1-16 P1-38 VIDEO_OUT_HI LP1OUT P1-66 ----- ----- DPWR+15_OUT DPWR-15_IN HEADING_Y ALT_C2 RS232_TX2
VIDEO_OUT- P1-17 P1-37 VIDEO_OUT_LO ALT_C1 P1-67 P1-58 ALT_C1 17 37 58 78

SFTKEY1_IN P1-18 P1-85 SFTKEY1_IN ALT_C2 P1-68 P1-59 ALT_C2 1

VIDEO_OUT- SFTKEY1_OUT ALT_A4 RS422_TXB
94
9 27 48 69 87

SFTKEY2_IN P1-19 P1-84 SFTKEY2_IN ALT_C4 P1-69 P1-71 ALT_C4 +5V DPWR-15_OUT DSPLY_GND_IN HEADING_Z ALT_C4 RS232_RX2 ASU_SEL
18 38 59 79
SFTKEY3_IN P1-20 P1-83 SFTKEY3_IN ALT_D2 P1-70 ----- -----
SFTKEY1_IN SFTKEY2_OUT ALT_B1 RS422_RXA
2 95
10 28 49 70 88
SFTKEY4_IN P1-21 P1-82 SFTKEY4_IN ALT_D4 P1-71 P1-72 ALT_D4 3.3V ASU_MODE
DSPLY_GND_OUT HSYNC_IN+ HEADING_H ALT_D2 RS232_GND2
VSYNC_OUT- P1-22 P1-62 VSYNC_OUT_LO ALT_COMN P1-72 P1-81 ALT_COMN 19 39 60 80
SMS_RET P1-23 P1-04 SW_RET A429RX4_A P1-73 ----- ----- SFTKEY2_IN SFTKEY3_OUT ALT_B2 RS422_RXB
3 96
SQUAT P1-24 P1-88 SQUAT A429RX4_B P1-74 ----- ----- 11 29 50 71 89
-15V ASU_SEL_ACK
DPWR+15_IN P1-25 P1-24 DPWR+15_IN A429RX5_A P1-75 ----- ----- HSYNC_OUT+ HSYNC_IN- HEADING_C ALT_D4 AUDIO_H
DPWR-15_IN P1-26 P1-05 DPWR-15_IN A429RX5_B P1-76 ----- ----- 4 20 40 61 81 97

DSPLY_GND_IN P1-27 P1-15 DSPLY_GND RS422_TXA P1-77 ----- ----- ON/OFF SFTKEY3_IN SFTKEY4_OUT ALT_B4 A429RX8_A ASU_MOD_ACK
12 30 51 72 90
HSYNC_IN+ P1-28 P1-47 HSYNC_IN_HI RS422_TXB P1-78 ----- ----- 5 98
HSYNC_IN- P1-29 P1-46 HSYNC_IN_LO RS422_RXA P1-79 ----- ----- ON/OFF_RET
HSYNC_OUT- VSYNC_IN+ HEADING_FLG ALT_COMN AUDIO_L
ASU_GND
21 41 62 82
VSYNC_IN+ P1-30 P1-61 VSYNC_IN_HI RS422_RXB P1-80 ----- -----
SFTKEY4_IN VSYNC_IN- A429RX2_A A429RX8_B
OPER_MODE P1-31 ----- ----- A429RX8_A P1-81 ----- ----- 6 13 31 52 73 91 99
DISCRETE P1-32 ----- ----- A429RX8_B P1-82 ----- -----
RAD_ALT_IN_HI VSYNC_OUT+ OPER_MODE A429TX3_A A429RX4_A AUDIO_C SDA
GEAR P1-33 P1-87 GEAR A429RX7_A P1-83 ----- ----- 22 42 63 83
GPWS P1-34 P1-32 GPWS A429RX7_B P1-84 ----- ----- VSYNC_OUT- A429TX1_A A429RX2_B A429RX7_A
VIDEO_IN+ P1-35 P1-36 VIDEO_IN_HI LP2OUT P1-85 ----- ----- 7 14 32 53 74 92 100

VIDEO_IN- P1-36 P1-35 VIDEO_IN_LO RS232_TX2 P1-86 ----- ----- RAD_ALT_IN_LO RADIO_ALT_FLG DISCRETE A429TX3_B A429RX4_B PLUG_GND SCL
23 43 64 84
SFTKEY1_OUT P1-37 P1-76 SFTKEY1_OUT RS232_RX2 P1-87 ----- -----
SMS_RET A429TX1_B A429RX3_A A429RX7_B
SFTKEY2_OUT P1-38 P1-75 SFTKEY2_OUT RS232_GND2 P1-88 ----- ----- 15 33 54 75 93

SMS GEAR A429RX1_A A429RX5_A SUPBUS

SFTKEY3_OUT P1-39 P1-74 SFTKEY3_OUT AUDIO_H P1-89 P1-92 AUDIO_H 24 44 65 85

SFTKEY4_OUT P1-40 P1-73 SFTKEY4_OUT AUDIO_L P1-90 P1-91 AUDIO_L SQUAT A429TX2_A A429RX3_B LP2OUT
34 55 76
VSYNC_IN- P1-41 P1-60 VSYNC_IN_LO AUDIO_C P1-91 P1-90 AUDIO_C
GPWS A429RX1_B A429RX5_B
A429TX1_A P1-42 P1-34 ARINC-429 TX 1A PLUG_GND P1-92 ----- ----- 45 66
A429TX1_B P1-43 P1-33 ARINC-429 TX 1B SUPBUS P1-93 P1-89 SUP_BUS A429TX2_B LP1OUT
A429TX2_A P1-44 ----- ----- ASU_SEL P1-94 ----- -----
A429TX2_B P1-45 ----- ----- ASU_MODE P1-95 ----- -----
HEADING_X P1-46 P1-66 SYNC_X ASU_SEL_ACK P1-96 ----- -----
HEADING_Y P1-47 P1-65 SYNC_Y ASU_MOD_ACK P1-97 ----- -----
HEADING_Z P1-48 P1-64 SYNC_Z ASU_GND P1-98 ----- -----
HEADING_H P1-49 P1-55 SYNC_H SDA P1-99 ----- -----
HEADING_C P1-50 P1-54 SYNC_C SCL P1-100 ----- -----
Figure A-1. P1 Connector Pin Identifiers
CORRESPONDING SKY497 CONNECTIONS ARE PROVIDED TO ASSIST IN UPGRADING AN EXISTING SKY497 INSTALLATION TO THE
NEW GENERATION SKY899. TO PREVENT MISMATING, THE 100-PIN CONNECTORS ON THE TRC497 AND TRC899 HAVE DIFFERENT A-13 (page A-14 blank)
KEYING ARRANGEMENTS. Rev. B
 SKY899
Installation Manual
A.3 ARINC-429 LABELS
The various interface equipment and their ARINC-429 labels (accepted and transmitted) are listed in
tables A-2 and A-3. Not all labels listed are required at this time, but may be required for future options
and are included for reference only. Any input labels not listed in table A-1 are rejected and not used by the
SKY899.
Table A-2. ARINC-429 Input Labels (Rx)
Equipment Data Label

Air Data Computer Altitude 203*

Baro Corrected Altitude #1 204
Altitude Rate 212
Air Temperature 213
Altitude Rate 232
General Aviation Equipment ID 371
Equipment ID 377

GPS (GAMA) Greenwich Mean Time (BCD) 125

Greenwich Mean Time (BNR) 150
Date (BCD) 260
GPS Discrete Word 1 (DSC) 261*
Present Position Latitude (BNR) 310*
Present Position Longitude (BNR) 311*
Ground Speed (BNR) 312*
Track Angle (BNR) 313*
Specific Equipment ID (DSC) 371
Equipment Hex ID Code (DSC) 377

GPS (GNSS - ARINC 743A) GPS Altitude 076

HDOP 101
VDOP 102
GPS Track Angle 103*
GPS Latitude 110*
GPS Longitude 111*
GPS Ground Speed 112*
GPS Latitude Fine 120
GPS Longitude Fine 121
UTC 125
Horizontal Integrity Limit (HIL) 130*
UTC 150
Vertical Velocity 165
Date 260
Equipment ID 377

Attitude & Heading Reference System Magnetic Heading 014

True Heading 314**
Magnetic Heading 320**
General Aviation Equipment ID 371
Equipment ID 377

Radio Altimeter Radio Height 164*

Equipment ID 377
* Label(s) required for ARINC-429 Input data to be used by the SKY899 for computations.
** Only one label 314 or 320 is required for input to be used.
A-15
Rev. B
 SKY899
Installation Manual

Table A-3. ARINC-429 Output Labels (Tx)

Equipment Data Label

External Display DITS Control 013

ARINC-735 TCAS I Formatted Traffic Data Altitude Select Limits 015

DITS Control 016
Intruder Range 130
Intruder Altitude 131
Intruder Bearing 132
Own A/C Altitude. 203
Vertical RA 270
Transponder Control 274
Own A/C Heading 320
Fault Summary 350
(RTS) Request To Send 357
(ETX) End of Transmission 357
GA Equipment Ident 371
Equipment Identifier 377

A-16
Rev. B
 SKY899
Installation Manual

APPENDIX B
ENVIRONMENTAL QUALIFICATION FORM
This appendix includes the environmental qualification forms required for the SKY899 system. Forms
included are for the TRC899, NY156 & NY164 antennas, and WX-1000/SKY497 display.

B.1 TRC899 ENVIRONMENTAL QUALIFICATION FORM

(Reference Document 016-11933-001, Rev. G)

MODEL: TRC899 TSO NO: TSO-C147, Class A. TSO-C118

PART NO: 805-11900-001 APPLICABLE SPEC NO: RTCA/DO-197A
MANUFACTURER: L-3 Avionics Systems
ADDRESS: 5353 52nd St. SE, Grand Rapids, MI 49512-9704
Revision and change number of DO-160: DO-160D (RF Susceptibility to Chg 1) Date Tested: May 21,
2001 – October 10, 2001
SECTION-
CONDITION TEST CATEGORY
PARAGRAPH
Temperature and Altitude 4.0 Equipment tested to Category F2
Low Temperature 4.5.1 -55° Celsius
High Temperature 4.5.2 & 4.5.3 +70° Celsius
Loss of Cooling 4.5.4 Category X-No test performed
Altitude 4.6.1 55,000 ft. MSL
Decompression 4.6.2 Not Applicable
Overpressure 4.6.3 Not Applicable
Temperature Variation 5.0 Equipment tested to Category B
Humidity 6.0 Equipment tested to Category A
Operational Shock and Crash Safety 7.0 Equipment tested to Category B
Vibration 8.0 Equipment tested to Category S, aircraft zone
2 using vibration test curves B and M for fixed
wings
Critical frequencies for sinusoidal test, curve
M:
X axis: 14.83 Hz @ 3.18 g
22.35 Hz @ 4.72 g
Y axis: 47.25 Hz @ 4.23 g
73.45 Hz @16.03 g
Z axis: 44.44 Hz @ 6.25 g
73.45 Hz @ 7.87 g
No changes in critical frequencies were
observed in all three major test axes.
Explosion Proofness 9.0 Equipment identified as Category X - No test
performed
Waterproofness 10.0 Equipment identified as Category X - No test
performed
Fluids Susceptibility 11.0 Equipment identified as Category X - No test
performed
Sand and Dust 12.0 Equipment identified as Category X - No test
performed

B-1
Rev. B
 SKY899
Installation Manual
SECTION-
CONDITION TEST CATEGORY
PARAGRAPH
Fungus Resistance 13.0 Equipment identified as Category X - No test
performed
Salt Spray 14.0 Equipment identified as Category X - No test
performed
Magnetic Effect 15.0 Equipment to meet Class Z
Power Input 16.0 Equipment tested to Category B
Voltage Spike 17.0 Equipment tested to Category A
Audio Frequency Susceptibility 18.0 Equipment tested to Category B
Induced Signal Susceptibility 19.0 Equipment tested to Category A
Radio Frequency Susceptibility 20.0 Equipment tested to Category RR
Radio Frequency Emission 21.0 Equipment tested to Category L
Lightning Induced Transient 22.0 Equipment identified as Category XXXX - No
Susceptibility test performed
Lightning Direct Effects 23.0 Equipment identified as Category X - No test
performed
Icing 24.0 Equipment identified as Category X - No test
performed
Electrostatic Discharge 25.0 Equipment tested to Category A
Other Tests No test required

B.2 NY156 & NY164 ANTENNA ENVIRONMENTAL QUALIFICATION FORM

®
NOMENCLATURE: SKYWATCH
MODEL: NY156 & NY164 TSO NO.: TSO-C118
PART NO.: 805-10003-001 & 805-10890-001
APPLICABLE SPEC. NO.: RTCA/DO-160C

MANUFACTURER: Sensor Systems, Inc.

ADDRESS: 8929 Fullbright Ave., Chatsworth, CA 91311 USA
(818) 341-5366

Revision & Change Number of DO-160: DO-160C

CONDITIONS SECTION TEST DESCRIPTION
Temperature and Altitude 4.0 Equipment tested to Categories F2.
Low Temperature 4.5.1 -55 Degrees Celsius
High Temperature 4.5.2 & 4.5.3 +70 Degrees Celsius
In-Flight Loss of Cooling 4.5.4 - Not Applicable -
Altitude 4.6.1 55,000 Feet

B-2
Rev. B
 SKY899
Installation Manual
NY156 & NY164 Environmental Qualification Form (Continued)

CONDITIONS SECTION TEST DESCRIPTION

Decompression 4.6.2 - Not Applicable -
Overpressure 4.6.3 - Not Applicable -
Temperature Variation 5.0 Equipment tested to Category A.
Humidity 6.0 Equipment tested to Category A.
Operational Shock and Crash Safety 7.0 Operation and Crash
Vibration 8.0 Equipment tested to Category C, L, M, and Y.
Explosion 9.0 Category X - No test performed.
Waterproofness 10.0 Equipment tested to Category S.
Fluids Susceptibility 11.0 Equipment tested to Category F.
Sand and Dust 12.0 Equipment tested to Category D.
Fungus 13.0 Equipment tested to Category F.
Salt Spray 14.0 Equipment tested to Category S.
Magnetic Effect 15.0 Category X - No test performed.
Power Input 16.0 Category X - No test performed.
Voltage Spike 17.0 Category X - No test performed.
Audio Frequency Susceptibility 18.0 Category X - No test performed.
Induced Signal Susceptibility 19.0 Category X - No test performed.
Radio Frequency Susceptibility 20.0 Category X - No test performed.
Radio Frequency Emission 21.0 Category X - No test performed.
Lightning Induced Transient 22.0 Equipment tested to Category L.
Susceptibility
Lightning Direct Effects 23.0 Equipment tested to Category 2A.
Icing 24.0 Category X - No test performed.
Other Tests No test required

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

(Reference Document 016-10831-001, Rev. A)

®
NOMENCLATURE: Stormscope
MODEL: WX-1000 TSO NO.: TSO-C113
PART NO.: 78-8060-5900-8 APPLICABLE SPEC. NO.: RTCA/DO-160C

MANUFACTURER: L-3 Avionics Systems

ADDRESS: 5353 52nd Street SE, Grand Rapids, MI 49512
(616) 949-6600

B-3
Rev. B
 SKY899
Installation Manual
Revision & Change Number of DO-160: DO-160C
SECTION/
CONDITION TEST DESCRIPTION
PARAGRAPH

Temperature and Altitude 4.0 Tested to Category F1-

Operating Low Temperature 4.5.1 -20° Celsius
Operating High Temperature 4.5.3 +55° Celsius
Short-Time Operating High Temp. 4.5.2 +70° Celsius
Loss of Cooling 4.5.4 -Not Applicable-
Ground Survival Low Temp. 4.5.1 -55° Celsius
Ground Survival High Temp. 4.5.2 +85° Celsius
Altitude 4.6.1 55,000 Feet MSL
Temperature Variation 5.0 Tested to Category C
Humidity 6.0 Tested to Category A
Operational Shock and Crash Safety 7.0
Operational Shock 7.2 6 g's Peak
Crash Safety 7.3 15 g's all axes
Vibration 8.0 Tested to Categories [NBM] Instrument
Panel Mount Without Vibration Isolators
Explosion Proofness 9.0 Category X - No test required
Waterproofness 10.0 Category X - No test required
Fluids Susceptibility 11.0 Category X - No test required
Sand and Dust 12.0 Category X - No test required
Fungus Resistance 13.0 Category X - No test required
Salt Spray 14.0 Category X - No test required
Magnetic Effect 15.0 Tested to Class Z
Power Input 16.0 Category X - No test required
Voltage Spike 17.0 Category X - No test required
Audio Frequency Susceptibility 18.0 Category X - No test required
Induced Signal Susceptibility 19.0 Tested to Category Z
Radio Frequency Susceptibility 20.0 Tested to Category U
Radio Frequency Emission 21.0 Tested to Category A
Lightning Induced Transient 22.0 Category X - No test required
Susceptibility
Lightning Direct Effects 23.0 Category X - No test required
Icing 24.0 Category X - No test required
Other Tests X-Ray Radiation
Other Tests U.V. Radiation
Other Tests Thermal Shock

B-4
Rev. B
 SKY899
Installation Manual

APPENDIX C
INSTALLATION CHECKOUT
USING THE TCAS-201 RAMP TEST SET
C.1 INTRODUCTION
This section contains instructions for using the TCAS-201 Ramp Test Set (with TCAS I firmware) to do the
®
post-installation checkout of the SKYWATCH HP SKY899. This procedure provides test setup data for the
TCAS-201 ramp test set, refer to manufacturers instructions for detailed setup, operation and maintenance
information.
NOTES
1. This procedure assumes familiarity with the set up and operation of the TCAS-
201 ramp test set.
2. All test equipment used in completing these tests shall be calibrated in
accordance with the manufacturer’s recommendations.
3. When the SKY899 is interfaced to an alternate display, reference Appendix F
while performing this checkout procedure.
This procedure will validate the installation and return to service of the SKY899.
C.2 CONTROLS
All operating controls are located on the front of the WX-1000/SKY497 display. Figure C-1 shows the
locations of the controls. Complete operating instructions for the SKY899 are provided in the SKY899
Pilot’s Guide supplied with each system.

BRT
OFF

1 4

2 3

Figure C-1. Controls

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

1, 2, 3, & 4 Also referred to as soft-keys (1), (2), (3), and (4). In every operating mode a label
Pushbuttons identifying the button function will be displayed next to the button.

C-1
Rev. B
 SKY899
Installation Manual
C.3 CHECKOUT PROCEDURE

If the indications given in the following steps, except for the ramp test set, are not obtained, refer to the
troubleshooting procedures in Chapter 4. If indications given for the ramp test set are not obtained, refer to
the manual supplied with that equipment.
1. Enter and store the setup information identified in table C-1 into the TCAS-201 Ramp Test Set.
Table C-1. IFR Systems TCAS-201 Ramp Test Set Setup Data

SCREEN STORAGE NUMBER 1

SETUP #1 INTRUDER TYPE: ATCRBS

UUT DIST: HORIZ = Distance (ft.) from aircraft
UUT DIST; VERT = Vertical height (ft.) difference between test
antenna and SKY899 antenna
ALT REPORTING: ON
STORE 0
RECALL 0
GAIN_1030 9.4 dB
LOSS 1.3 dB
SETUP #2 RANGE MAX: 35 NM (was 20 NM for Sky497)
RANGE MIN: 0 NM
ALT MAX: 60,000 ft
ALT MIN: 0 ft
SCENARIO TEST RANGE: 5.0 NM
RANGE RATE: +200 kt
ALT: 51,000 ft
ALT: RATE: 0 FPM
REPLY TEST RANGE: 5.0 NM
ALTITUDE 50,500 ft
%REPLY: 100 %

2. Make sure the aircraft’s transponder is in the STBY mode and the DME is turned OFF. Verify all
avionics equipment interfaced with the SKY899 (i.e., GPS, ADC, AHRS, synchro compass, encoding
altimeter) is turned ON and signal condition is valid.

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

3. Turn SKY899 ON. The display will show a start-up screen similar to one shown in figure C-2. After
start-up screen appears, rotate the OFF/BRT switch. Verify that clockwise rotation increases display
brightness.

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Installation Manual

BRT
OFF

AVIONICS SYSTEMS

SkyHP Vx.xx

Figure C-2. Start-up Screen

After approximately thirty seconds the display will show the STANDBY screen (see figure C-3).
NOTE
If the TRC has not been calibrated to the directional antenna the display
may show a “SKY899 FAILED” message. Calibration will be done during
system setup verification and operation.

BRT
OFF

SKY899
Standby

MSG OPR
TEST RNG

Figure C-3. Standby Screen

4. Perform System Setup in paragraph 3.3.1. (If System Setup has already been done, proceed to next
step.)
5. Turn SKY899 OFF and then enter the Service Menu (see paragraph 4.4) by holding the left two
buttons (soft-keys 1 and 2) depressed as the system is turned ON.
6. From the Service Menu, calibrate the TRC to the directional antenna (see paragraph 3.3.2 and 4.4.3).
7. Cycle power to the SKY899 and verify the standby screen appears after approximately 30 seconds.
Press OPR soft-key (4) and verify the MSG label does not appear on the display after 10 seconds.

NOTE
If MSG label is present press MSG soft-key (1) for degraded operation
message and refer to Chapter 4 troubleshooting to isolate the problem before
proceeding.

8. Return to the Service Menu (paragraph 4.4) and select Information.

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9. From the Information menu, select Data Monitor. The Data Monitors menu will appear.
10. 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.
11. Do SKY899 self test (paragraph 3.4).
12. From the Service Menu, select Ground Test (see paragraph 4.4.4).
13. From Ground Test menu, select Perform Ground Test.
14. 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.
15. Select the 6 nautical mile range.
16. 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 toggle between normal (NRM), below (BLW), above (ABV), and
unrestricted (UNR).
17. Select the NRM (normal) mode.
18. Position the aircraft with the nose aligned on any 90 degree heading. Avoid areas within 250 ft of
obstructions (e.g., hangers, large aircraft, control towers, etc.) where there is a potential for multipath
problems. Locate and mark test points, every 30 degrees (i.e., at 000, 030, 060, 090, 120, 150, 180, 210,
240, 270, 300, and 330 degrees with respect to the SKY899 directional antenna). Mark these points at
the same distance, approximately 100 ft (or less), from the aircraft.
19. Do the following static tests:
a. Connect the TCAS-201 Flat Antenna (facing towards the test aircraft) to the antenna connector.
b. At the TCAS-201 test set, press the REPLY TEST key.
c. Initiate the REPLY TEST by pressing the ANTENNA push button switch or the RUN/STOP
key.
NOTE
The TCAS-201 display will indicate “NO WHISPER-SHOUT SEQUENCE”.
d. Verify that the SKY899 display shows an other traffic symbol (open diamond) at the 12 O'clock
position (±30 degrees), approximately 5.0 nm, in level flight, and at an altitude of 500 ft above
own aircraft (i.e., "+05").
NOTES
1. If the display reflects a gross error in target bearing, check the directional antenna cables
at TRC connectors J9 (sum port) and J11 (difference port). They may be reversed. A further
indication of this condition would be a target that moved in a counter-clockwise direction
when the test set is moved in a clockwise direction.
2. Multiple targets or a faulty bearing may result from multipath distortion
(see step 2).
3. During these tests, the SKY899 may detect and display other active targets.
e. Repeat a, b, c, and d from each of the test points (see step 2).

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20. Do the following dynamic test.
a. Position the ramp test set on the test point directly in front of the test aircraft (i.e.,
approximately 100 ft (or less) in front of the aircraft, see step 2).
b. Connect the TCAS-201 Flat Antenna (facing towards the test aircraft) to the antenna connector.
c. At the TCAS-201 test set, press the SCEN key.
d. Initiate the SCENARIO TEST by pressing the ANTENNA push button switch or the RUN/STOP
key.
e. Verify that the display shows an "other traffic" symbol (open diamond) at the 12 o’clock position
(±30 degrees) approximately 5.0 nm and in level flight. The traffic symbol should be at an
altitude of 500 ft above own aircraft (i.e., "+05") and moving towards your aircraft.
f. When the target approaches closer than approximately 1 nm from own aircraft, verify that the
symbol changes from an other traffic symbol (open diamond) to a traffic advisory (solid circle).

NOTE
The voice message, “TRAFFIC, TRAFFIC,” will be enunciated over the cockpit
audio system.

g. The target, when it reaches 0.0 nm, will reverse direction and move outbound on the same
heading.
NOTE
The target may momentarily drop from the display and then reappear as an
other traffic symbol (open diamond).

21. This completes the post installation checkout procedure.

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APPENDIX D
INSTALLATION CHECKOUT
USING THE TIC T-49C FLIGHTLINE TESTER
D.1 INTRODUCTION
This section contains instructions for using the TIC T-49C Flightline Tester to do post-installation checkout
®
of the SKYWATCH HP SKY899. Detailed setup, operation and maintenance information for the T-49C
Flightline Tester is provided in the T-49C Operating and Maintenance Instruction Manual.
NOTES
1. This procedure assumes familiarity with the set up and operation of the T-49C
Flightline Tester.
2. All test equipment used in completing these tests shall be calibrated in
accordance with the manufacturer’s recommendations.
3. When the SKY899 is interfaced to an alternate display, reference Appendix F
while performing this checkout procedure.
This procedure will validate the installation and return to service of the SKY899.

D.2 CONTROLS
All operating controls are located on the front of the WX-1000/SKY497 display. Figure D-1 shows the
locations of the controls. Complete operating instructions for the SKY899 are provided in the SKY899
Pilot’s Guide supplied with each system.
BRT
OFF

1 4

2 3

Figure D-1. Controls

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

1, 2, 3, & 4 Also referred to as soft-keys (1), (2), (3), and (4). In every operating mode a label
Pushbuttons identifying the button function will be displayed next to the button.

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D.3 CHECKOUT PROCEDURE
The T-49C Flightline Tester simulates a ground based secondary surveillance radar (SSR) when the TCAS
INTRUDER selector switch is in the ATCRBS/Mode-S XPDR TEST position. When the T-49C intruder type
switch is set to ATCRBS, the unit responds to ATCRBS Mode C interrogations. A varying delay time,
controlled from the microprocessor, delays the replies returned to the SKY899 from as far as 14 nautical
miles and as close as a few hundred feet. The apparent distance from the simulated intruder to the SKY899
system under test decreases as if the intruder was converging on the aircraft under test. The test set
determines the altitude of the aircraft under test by interrogating the transponder using an ATCRBS
interrogation. By adding or subtracting the desired differential altitude, as selected by the front-panel
scenario switch, the initial altitude of the scenario is controlled by the microprocessor. This altitude, like
the distance, is varied so that the simulated intruder converges on the aircraft’s position.
1. Make sure the aircraft's transponder is in the STBY mode and the DME is turned OFF. Verify all
avionics equipment interfaced with the SKY899 (i.e., GPS, ADC, AHRS, synchro compass, encoding
altimeter) is turned ON and signal condition is valid.

NOTE

After power up, it may take a couple of minutes for the altitude encoder to
return a valid altitude to the transponder and SKY899.
2. Turn SKY899 ON. The display will show a start-up screen similar to one shown in figure D-2. After
start-up screen appears, rotate the OFF/BRT switch. Verify that clockwise rotation increases display
brightness.

BRT
OFF

AVIONICS SYSTEMS

SkyHP Vx.xx

Figure D-2. Start-up Screen

After approximately thirty seconds the display will show the STANDBY screen (see figure D-3).
NOTE
If the TRC has not been calibrated to the directional antenna the display
may show a “SKY899 FAILED” message. Calibration will be done during
system setup verification and operation.

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Installation Manual

BRT
OFF

SKY899
Standby

MSG OPR
TEST RNG

Figure D-3. Standby Screen

3. Perform System Setup in paragraph 3.3.1. (If System Setup has already been done, proceed to next
step.)
4. Turn SKY899 OFF and then enter the Service Menu (see paragraph 4.4) by holding the left two
buttons (soft-keys 1 and 2) depressed as the system is turned ON.
5. From the Service Menu, calibrate the TRC to the directional antenna (see paragraph 3.3.2 and 4.4.3).
6. Cycle power to the SKY899 and verify the standby screen appears after approximately 30 seconds.
Press OPR soft-key (4) and verify the MSG label does not appear on the display after 10 seconds.

NOTE
If MSG label is present press MSG soft-key (1) for degraded operation
message and refer to Chapter 4 troubleshooting to isolate the problem before
proceeding.
7. 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. From the Service Menu, select
Information.
8. From the Information menu, select Data Monitor. The Data Monitors menu will appear.
9. Select each of the data monitors and verify the sensor information is correct (see paragraph 4.4.2.3):
a. Change the status of the landing gear, squat switch, altitude, and heading sensors.
Verify data monitors show the correct input changes (i.e., sensing of these signals).
b. If the information is not correct, the sensor has failed to communicate with the TRC. Check
operation of the sensor and connections between the TRC and sensor.
c. Select exit until you return to the Service Menu.
10. Exit the Service Menu. Verify that the display shows the standby screen (figure D-3) and then press
Soft-key (4), labeled OPR.
11. 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.
12. Select the 6 nautical mile range.
13. 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 toggle between normal (NRM), below (BLW), above (ABV), and
unrestricted (UNR).
14. Select the NRM (normal) mode.

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15. If installed, turn the radio altimeter OFF.
16. Do the SKY899 self test (paragraph 3.4).
17. Position the aircraft with the nose aligned on any 90 degree heading. Avoid areas within 250 ft of
obstructions (e.g., hangers, large aircraft, control towers, etc.) where there is a potential for multipath
problems. Locate and mark test points at 30 degree intervals (i.e., 000, 030, 060, 090, 120, 150, 180,
210, 240, 270, 300, and 330 degrees) with respect to the SKY899 directional antenna. Mark these
points at the same distance, approximately 100 ft. (or less), from the aircraft.
18. Change the aircraft’s transponder from STBY mode to the ON position.
19. Position the T-49C Flightline Tester on one of the test points identified in previous step.

CAUTION

The Flightline Tester is not weatherproof when the lid is open. Do not setup
or operate the Flightline Tester in conditions of rain, sleet, etc.
20. Setup and verify operation of the T-49C Flightline Tester with the HI/LOW power switch in the HI
position and then:
a. Set the TCAS INTRUDER selector switch of the T-49C to the ATCRBS/Mode-S XPDR TEST
position and press TEST and the INTERROGATE. This will store the aircraft’s barometric
altitude in the T-49C.
NOTE
The T49-C will display the pressure altitude of the aircraft under test.

b. Verify that the SKY899 display shows the standby screen (figure D-3) and then press soft-key
(4), labeled OPR. Select NRM mode and 6 nm range by pressing appropriate soft-keys.
c. Set the TCAS INTRUDER selector switch to the ATCRBS position and the SCENARIO selector
switch to the 0 altitude offset position. Press INTERROGATE, and when the range on the
display decreases to 5 NM, press TEST. This will freeze the scenario and represent a stationary
intruder aircraft 5 NM away at the same altitude as the UUT aircraft. Verify that the SKY899
displays, in the direction (±30 degrees) of the T-49C, a symbol for other traffic (i.e., open
diamond) at 5 NM. Target will be displayed in level flight at own aircraft altitude (i.e., “00”
displayed above the traffic symbol).

NOTES
1) If the display reflects a gross error in target bearing, check the SKY899
directional antenna cables at TRC connectors J9 (sum port) and J11
(difference port). They may be reversed. A further indication of this
condition would be a target that moved in a counter-clockwise direction
when the T-49C is moved in a clockwise direction.
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
antenna.
d. Move the T-49C to each test point and verify that the display shows the corresponding bearing
displacement.

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NOTE
It is necessary to wait a few seconds after moving to let the test target stabilize
in position.
21. This completes testing with the T-49C, reattach top lid of the T-49C.
22. If installed, TURN ON the radio altimeter.
23. This completes the post installation checkout procedure.

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APPENDIX E
Using the Terminal Device
(e.g., Laptop Computer)

When interfacing to an alternate display a terminal device must be used to access the service menu for
system configuration, testing and troubleshooting of the SKY899. Connect terminal device to the RS-232
serial data TEST port (J7) located on the front of the TRC899. TRC connector J7 is a female DB9
receptacle. A standard serial cable that has RXD (pin 2), TXD (pin 3), GND (pin 5), CTS (pin 7), and RTS
(pin 8) can be used. Any computer, with RS-232 terminal emulation software (e.g., Procomm,
HyperTerminal, etc.), may be used as the terminal device. To communicate with the TRC, the RS-232
terminal device must be setup as follows, with no hardware or software handshaking (flow control) being
used.

Baud Rate: 19200

Data Bits: 8
Parity: None
Stop Bits: 1
Flow Control: Xon/Xoff

To access the service menu, with RS-232 terminal emulation software running, type menu <Enter>. The
following will appear:

Service Menu

1 Setup
2 Information
3 Calibration
4 Ground Test

x Exit

Choice:

The terminal device Service Menu is similar to the one described in Chapter 4, except for a prefix. Type the
prefix character (1<Enter>, 2<Enter>, x<Enter>, etc.) to select the function. Refer to chapter 4 for service
menu details.

NOTE

1. The information screens contain live data that is constantly updated, however
the terminal device emulation software will not automatically update or
refresh the data to the screen. To refresh data to the terminal device screen
press <Enter>.
2. When using service menu the system will not perform display commands
(e.g., OPR, STB, MSG, or range).

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 SKY899
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Special laptop commands designed for field service engineering are hidden in the system. Typing help or ?
at the prompt will cause the following list to appear. These commands should only be used by factory
personnel and are not supported in this manual.

Commands Descriptions

? or Help The ? or help command displays a list of available commands.

? or Help: Displays the following list
fdrec track mbite mxmit
head rad discretes bar
gps say volume mrep
cal ground adsb dump
// attrib comflash copy
del delay dir echo
hello help menu ren
restart time type ver
For Information on any particular command, enter the command followed by
--help (i.e., ident --help) or -? (abbreviated help screen).

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 SKY899
Installation Manual

APPENDIX F
Installation Checkout Using
an Alternate Display
F.1 INTRODUCTION
®
This section contains installation checkout procedures for the SKYWATCH HP SKY899 that is interfaced
to an alternate display (e.g., EFIS, IVSI, L-3 Avionics Systems RGC250, MFD).

NOTES
1. This section provides checkout information for the SKY899 interfaced to an
Alternate Display.
2. When interfacing to a weather radar indicator via Radar Graphics Computer
Model RGC250 with Enhanced Interface (P/N 805-11400-003 or -004) or
RGC350 (P/N 805-12400-001 or -002).
3. This procedure assumes familiarity with the set up and operation of the TT391
Flightline Tester and RS-232 terminal device (see Appendix E). If using another
approved tester refer to the appropriate appendices for test procedure.
4. All test equipment used in completing these tests shall be calibrated in
accordance with the manufacturer’s recommendations.
This procedure will validate the installation and return to service of the SKY899.

F.2 CONTROLS
Operating instructions for each alternate display are provided with the display manufacturer’s
documentation.
NOTE
When using an alternate display all SKY899 functions are controlled through
the alternate display or external controls. Each alternate display will show
information consistent with the capabilities of that particular display.
Therefore, the text displayed may be different from what is called out in this
procedure. Reference the alternate display documentation for appropriate
screen text.

F.3 CHECKOUT PROCEDURE

The TT391 Flightline Tester simulates both a ground based secondary surveillance radar (SSR) and an
airborne transponder. With the SKY899 set to GROUND TEST (i.e., the barometric altimeter is simulated
to 50,000 ft, heading simulated to 0 degrees, and the radar altimeter simulated to 2,500 ft) the TT391 will
simulate two targets; a Traffic Advisory (i.e., a solid circle) at ¼ nm and Other Traffic (i.e., open diamond)
at 4.5 nm. Both targets will be displayed in level flight at own aircraft altitude (i.e., "00" displayed above
the traffic symbol).
If the indications given in the following procedure, except for the Flightline Tester, are not obtained, refer
to the troubleshooting procedures in Chapter 4. If indications given for the Flightline Tester are not
obtained, refer to the maintenance section of the TT391 Instruction Manual.
1. Connect the RS-232 terminal device to J7 TEST port on the TRC899. Turn ON and setup the terminal
device. (See Appendix E for terminal device commands, setup, and operating instructions.)

F-1
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2. Make sure the aircraft’s transponder is in the STBY mode and the DME is turned OFF. Verify all
avionics equipment interfaced with the SKY899 (i.e., GPS, ADC, AHRS, synchro compass, encoding
altimeter) is turned ON and signal condition is valid.

NOTE
After power up, it may take a couple of minutes for the altitude encoder to
return a valid altitude to the transponder and SKY899.
2. Turn SKY899 ON. Start up screen similar to one shown in figure F-1 will be displayed on the terminal
device. After approximately thirty seconds the alternate display will show the standby screen.

Welcome to the Goodrich Avionics Systems SKYWATCH HP

Copyright (c) 2001 Goodrich Avionics Systems, Inc.

All rights reserved
Figure F-1. SKYWATCH Startup Screen on Terminal Device

NOTE
If the TRC has not been calibrated to the directional antenna, the display may show a
FAIL message. Calibration will be done during system setup verification and
operation.

4. At the terminal device, enter the Service Menu by typing Menu <Enter>. The service menu displayed
on the terminal device is similar to the one seen in Chapter 4, except each command has a prefix. To
select a menu item type the prefix <Enter> (i.e., 1 <Enter>, 2 <Enter>, x <Enter>, etc.).
5. Perform the System Setup in paragraph 3.3.1 (start at step 2).
6. From the Service Menu select Calibration (3 <Enter>). Calibrate antenna to system by selecting the
correct antenna location.

NOTE
Some alternate displays show "TCAS OFF" instead of standby, this does not mean
that SKY899 is turned off.

7. Cycle power to the SKY899 and verify the standby screen appears after approximately 30 seconds. At
the display press OPR button (soft-key 4) and verify system comes out of standby.

NOTE
The displays function button’s (soft-key input) may be an external panel mounted
momentary switch or a momentary switch located on the display.

8. From the Service Menu (see paragraph 4.4), select Information (2 <Enter>).
9. From the Information menu, select Data Monitor (3 <Enter>). The Data Monitors menu will appear.
10. 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 (x <Enter>) until you return to the Service Menu.
11. At the alternate display, perform the SKYWATCH HP self-test (see paragraph F.4).
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12. At the terminal device, enter the Service Menu by typing Menu <Enter>.
13. From the Service Menu, select Ground Test (4 <Enter>).
14. From the Ground Test menu, select Perform Ground Test (1 <Enter>).
15. At the alternate display, verify ground test screen is being displayed. Change the display ranges and
verify display range patterns are correct.
16. Select the 6 nautical mile range.
17. Change the altitude display modes from normal (NRM), below (BLW), above (ABV), and unrestricted
(UNR). Verify that the system toggles through the altitude display modes correctly (some alternate
displays do not support unrestricted display mode). If external annunciators are connected verify
correct operation (see figure F-2).

Figure F-2. External Annunciator Operation.

18. If oper_mode annunciator (optional) is connected, verify annunciator works when system is turned
ON.
19. Select the normal (NRM) mode.
20. 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, approximately 100 ft. (or less), from the aircraft.
21. Position the TT391 Flightline Tester on one of the test points identified above.

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.
22. Setup and verify operation of the TT391 Flightline Tester:
a. Open the chassis lid and remove the lid from the chassis by sliding the lid off of the hinge pins
(sliding it to the right). The lid "stay" must be removed from the lid before mounting. The stay
will pop off of the lid. (The stay is the hinged part that props the lid open on the chassis).
NOTE
The Patch Antenna may be used without a tripod. The Patch Antenna can be
held, or secured, and pointed towards the SKYWATCH HP aircraft under test
WITH THE MOUNTING STUD POINT TOWARD THE GROUND. This orientation is
critical.
b. Mount the chassis lid, with the Patch Antenna facing the aircraft, onto a tripod (not included).
The tripod must be capable of holding the antenna (approximately 2.5 lb.) and must provide a
standard base mounting stud threaded 1/4"-20. A typical tripod mount is shown in figure F-3.
c. If the internal batteries are being utilized, proceed to sub-step f. If the Flightline Tester AC
Converter Power Supply is to be utilized, proceed to sub-step d.
d. Connect the AC Converter Power Supply cable connector to the chassis external connector.

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 SKY899
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e. Connect the AC Converter Power Supply input power cable connector to one of the following AC
sources:
• 115 V ac, 60 Hz
• 115 V ac, 400 Hz
f. Set the Flightline Tester POWER switch to the ON position.
g. Verify that the LOW indicator is not steady on (it may flash). If the LOW indicator remains on
(i.e., lit), perform one of the following three options:
• Use the AC Converter Power Supply to power the unit.
• Recharge the internal batteries.
• Replace the internal batteries.
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).

Figure F-3. Typical Patch Antenna Tripod Mount

23. From each test point (see step 13):
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.
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 SKY899
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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 16 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.
24. Return the TT391 assemblies to their position in the aluminum carrying case.
25. Restart SKYWATCH HP by cycling power OFF and then ON.
26. 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.
27. This completes the post installation checkout procedure.

F.4 SELF TEST

1. Turn SKYWATCH HP OFF and then:
a. Make sure the aircraft’s transponder is in the STANDBY, ON, or ALT mode.

NOTE
After power up, it may take a couple of minutes for the altitude encoder to
return a valid altitude to the transponder and SKY899.
b. If installed, power up the radio altimeter.
c. Make sure all compass/HSI flags are cleared from the aircraft’s instruments.
2. Turn SKYWATCH HP ON.
3. After approximately thirty seconds, observe the standby screen and then perform the SKYWATCH HP
self test (see alternate display operating instructions on how to perform self test).
4. If SKYWATCH HP passes the self-test, the system will return to the standby screen and the voice
message, "SKYWATCH SYSTEM TEST PASSED," will be enunciated over the cockpit audio system.
5. If you do not hear the voice message or if the voice message is of insufficient volume:
a. Check headphones/speaker and aircraft audio panel switch settings.

NOTE
Audio levels are adjusted via the service menu and at the aircraft audio
panel. There is no internal audio adjustment.
b. Reset the audio level via the service menu. (See paragraph 4.4.1.3. Select test from the audio level
menu to hear a "traffic traffic" aural message.)

F-5
Rev. B
 SKY899
Installation Manual
c. Check audio connection to the TRC:
1) 600-ohm audio systems should be connected to P1-89 (AUDIO_H).
2) 150-ohm audio systems should be connected to P1-90 (AUDIO_L).
3) Audio common is connected to P1-91 (AUDIO_C).
NOTE
Audio output from the TRC is transformer isolated.
6. If SKYWATCH HP fails the self-test:
a. The fail screen will be displayed.
b. The voice message, "SKYWATCH SYSTEM TEST FAILED", will be enunciated over the cockpit
audio system.
c. Refer to the fault isolation procedures and error messages in Chapter 4.

F-6
Rev. B