Traffic Alert/Advisory System SKY899 Installation Manual

Traffic Alert/Advisory System SKY899 Installation Manual
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 letters and service bulletins.
009-11900-001 (Revision D)
L-3 Communications Avionics Systems
nd
5353 52 Street, S.E.
Grand Rapids, MI USA 49512-9704
www.as.l-3com.com
September 20, 2007
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 Communications Avionics Systems
Attn: Field Service Engineering
5353 52nd Street, S.E.
Grand Rapids, MI USA 49512-9704
Telephone: (800) 453-0288 or (616) 949-6600
Fax: (616) 977-6898
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 Communications Avionics Systems
Attn: Technical Publications
5353 52nd Street, S.E.
Grand Rapids, MI USA 49512-9704
Telephone: (800) 453-0288 or (616) 949-6600
Fax: (616) 977-6898
WARNING
INFORMATION SUBJECT TO EXPORT CONTROL LAWS
This technical data is controlled under the Export Administration
Regulations ECCN #7A994 and may not be exported to a foreign person,
either in the United States or abroad without the proper authorization of
the U.S. Department of Commerce. This document must be marked in
compliance with L-3 Avionics Systems Policy WI 0321S17 prior to
distribution to foreign persons.
© Copyright 2001-2007
L-3 Communications Avionics Systems, Inc.
____________________________
Trademarks
SKYWATCH® HP
Page A
September 20, 2007
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.
and Stormscope® are registered trademarks of L-3 Communications Avionics Systems, Inc.
009-11900-001
Revision D
SKY899
Installation Manual
ABOUT THIS MANUAL
SECTION 1 – GENERAL INFORMATION
This section 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.
SECTION 2 - INSTALLATION
This section contains instructions for unpacking the equipment and inspection for in-shipment damage. It
also includes information required to locate, assemble and install the equipment.
SECTION 3 – INSTALLATION CHECKOUT
This section contains instructions for doing post-installation and return to service checkout of the
SKY899 using the TT391 Flightline Tester.
SECTION 4 – MAINTENANCE
This section 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.
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List of Effective Pages
Dates of original and changed pages are:
Original (Rev. A)............... 4 September 2001
Revision B .............................28 August 2003
Revision C .......................... January 22, 2007
Revision D ..................... September 20, 2007
Total number of pages in this publication consists of the following:
Title page
A Page
i thru x
1-1 thru 1-24
2-1 thru 2-40
3-1 thru 3-10
4-1 thru 4-28
A-1 thru A-18
B-1 thru B-6
C-1 thru C-6
D-1 thru D-6
E-1 thru E-2
F-1 thru F-6
G-1 thru G-2
Revision D Highlights
Revision “D” 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:
•
Adds Appendix G, Permission to Use STC SA01552CH-D for Raytheon C90.
Discard previous editions of the publication.
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Table of Contents
Paragraph
Page
Section 1
General Information
1.1
INTRODUCTION....................................................................................................................................... 1-1
1.2
1.3
1.3.1
1.3.2
1.3.3
1.3.4
1.4
1.4.1
1.4.2
1.4.3
1.5
1.6
1.7
1.8
FUNCTIONAL DESCRIPTION ..................................................................................................1-2
PHYSICAL DESCRIPTION ........................................................................................................1-3
TRC899 Transmitter Receiver Computer P/N 805-11900-001 ....................................................1-5
System Configuration Module P/N 814-18005-001 .....................................................................1-9
Display (Alternate or WX-1000/SKY497 Display P/N 78-8060-5900-x)..................................1-10
Directional Antenna (NY156 P/N 805-10003-001 or NY164 P/N 805-10890-001)..................1-12
SPECIFICATIONS.....................................................................................................................1-14
Transmitter Receiver Computer (TRC) ......................................................................................1-14
WX-1000/SKY497 Display ........................................................................................................1-15
Directional Antenna ....................................................................................................................1-15
MODIFICATIONS & SOFTWARE REVISIONS.....................................................................1-15
INTERFACE ..............................................................................................................................1-17
EQUIPMENT REQUIRED BUT NOT SUPPLIED...................................................................1-17
INSTALLATION APPROVAL .................................................................................................1-23
Section 2
Installation
2.1
2.2
2.3
2.4
2.5
2.6
2.6.1
2.6.2
2.6.3
2.6.4
2.6.5
2.6.6
2.6.7
2.6.8
2.7
2.7.1
2.7.2
2.7.3
2.7.4
2.8
2.9
2.9.1
2.9.2
2.9.3
2.9.4
2.10
2.11
INTRODUCTION ........................................................................................................................2-1
UNPACKING, INSPECTION AND STORAGE.........................................................................2-2
ANTENNA LOCATION..............................................................................................................2-2
TRC LOCATION .........................................................................................................................2-3
DISPLAY LOCATION ................................................................................................................2-4
CABLE REQUIREMENTS AND FABRICATION ..................................................................2-17
Antenna Cables ...........................................................................................................................2-18
Audio Output Cable ....................................................................................................................2-18
Data Cable...................................................................................................................................2-19
Heading Input Cable ...................................................................................................................2-19
Power Cable ................................................................................................................................2-20
Suppression Bus Cable ...............................................................................................................2-20
WX-1000/SKY497 Display and WX-1000 Processor Cable .....................................................2-20
Converting Existing Aircraft Wiring from SKY497 to SKY899 ...............................................2-21
AIRCRAFT DISCRETE INPUTS..............................................................................................2-22
Extended Audio Callout..............................................................................................................2-22
GPWS (Audio inhibit) ................................................................................................................2-22
Landing Gear ..............................................................................................................................2-22
Squat Switch (Weight-On-Wheels) ............................................................................................2-23
ALTERNATE DISPLAY ...........................................................................................................2-23
ARINC-429.................................................................................................................................2-23
General Sensor Inputs .................................................................................................................2-24
Mode S Transponder I/O (future option) ....................................................................................2-24
Alternate Display Output ............................................................................................................2-25
Future Option..............................................................................................................................2-25
AUDIO (ALERT) OUTPUT ......................................................................................................2-25
BAROMETRIC (UNCORRECTED) ALTITUDE INPUTS......................................................2-25
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Table of Contents
(Continued)
Paragraph
Page
Section 2
Installation (continued)
2.11.1
2.11.2
2.12
2.13
2.13.1
2.13.2
2.14
2.15
2.16
2.17
2.18
2.18.1
2.18.2
2.19
2.20
2.21
2.22
2.23
2.24
2.24.1
2.24.2
2.25
2.26
2.27
2.28
2.28.1
2.28.2
Gilham Code (Encoding Altimeter)............................................................................................2-26
ARINC-429 (ADC).....................................................................................................................2-26
(ARINC-429) ..............................................................................................................................2-26
HEADING INPUT......................................................................................................................2-26
Compass Synchro (XYZ)............................................................................................................2-26
ARINC 429 (AHRS - Attitude Heading and Reference System) ...............................................2-27
LAMP OUTPUTS (ABV and BLW)..........................................................................................2-27
ON/OFF SWITCH ......................................................................................................................2-27
OPERATIONAL MODE OUTPUT (OPTIONAL)....................................................................2-28
POWER INPUT..........................................................................................................................2-28
RADIO ALTIMETER (OPTIONAL).........................................................................................2-28
Analog.........................................................................................................................................2-28
ARINC-429.................................................................................................................................2-29
SERIAL DATA ..........................................................................................................................2-29
SOFT-KEYS ...............................................................................................................................2-29
SUPPRESSION BUS I/O ...........................................................................................................2-30
SYSTEM CONFIGURATION MODULE .................................................................................2-31
WX-1000/SKY497 DISPLAY (OPTIONAL) ............................................................................2-32
WX-1000 PROCESSOR (OPTIONAL) .....................................................................................2-32
SKYWATCH/Stormscope Mode Switch....................................................................................2-33
External Overide Switch .............................................................................................................2-33
ANTENNA INSTALLATION ...................................................................................................2-33
TRC MOUNTING TRAY INSTALLATION ............................................................................2-35
TRC INSTALLATION...............................................................................................................2-36
MOUNTING THE WX-1000/SKY497 DISPLAY ....................................................................2-38
Panel Cutout................................................................................................................................2-38
Display Installation .....................................................................................................................2-39
Section 3
Installation Checkout
3.1
3.2
3.3
3.3.1
3.3.1.1
3.3.1.2
3.3.2
3.4
INTRODUCTION ........................................................................................................................3-1
CONTROLS .................................................................................................................................3-1
CHECKOUT PROCEDURE ........................................................................................................3-2
System Setup.................................................................................................................................3-3
System Configuration (via Service Menu)....................................................................................3-3
Download System Configuration (via Compact Flash Card) .......................................................3-5
System Setup Verification and Operation.....................................................................................3-5
SELF TEST...................................................................................................................................3-8
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Table of Contents
(Continued)
Paragraph
Page
Section 4
Maintenance
4.1
4.2
4.3
4.3.1
4.3.2
4.3.3
4.4
4.4.1
4.4.1.1
4.4.1.2
4.4.1.3
4.4.1.4
4.4.1.5
4.4.2
4.4.2.1
4.4.2.2
4.4.2.3
4.4.3
4.4.4
4.4.5
4.5
4.6
4.7
4.8
INTRODUCTION ........................................................................................................................4-1
CONTINUED AIRWORTHINESS..............................................................................................4-1
PERIODIC MAINTENANCE......................................................................................................4-1
WX-1000/SKY497 Display ..........................................................................................................4-1
TRC...............................................................................................................................................4-1
Antenna.........................................................................................................................................4-1
SERVICE MENU .........................................................................................................................4-2
Setup .............................................................................................................................................4-3
Aircraft Type.................................................................................................................................4-4
Antenna System ............................................................................................................................4-4
Audio Level ..................................................................................................................................4-5
ARINC 429 Ports..........................................................................................................................4-5
Avionics Equipment......................................................................................................................4-7
Information .................................................................................................................................4-12
Software Version ........................................................................................................................4-12
System Log .................................................................................................................................4-13
Data Monitor...............................................................................................................................4-14
Calibration ..................................................................................................................................4-17
Ground Test ................................................................................................................................4-18
Configuration Management ........................................................................................................4-19
TROUBLESHOOTING..............................................................................................................4-24
ERROR MESSAGES .................................................................................................................4-25
TRC899/WX-1000 ADAPTER PLUG.......................................................................................4-27
DISPOSITION OF FAILED ITEMS..........................................................................................4-28
Appendix A
SKY899 Interface Signal & Cable Characteristics
A.1
A.2
A.3
INTRODUCTION ....................................................................................................................... A-1
ELECTRICAL CHARACTERISTICS........................................................................................ A-1
ARINC-429 LABELS................................................................................................................ A-17
Appendix B
Environmental Qualification
B.1
B.2
B.3
SKY899 ENVIRONMENTAL QUALIFICATION FORM (FIXED WING: DO-160D) .......... B-1
NY156 & NY164 ANTENNA ENVIRONMENTAL QUALIFICATION FORM..................... B-2
WX-1000/SKY497 DISPLAY ENVIRONMENTAL QUALIFICATION FORM..................... B-4
Appendix C
Installation Checkout Using the TCAS-201 Ramp Test Set
C.1
C.2
C.3
INTRODUCTION ....................................................................................................................... C-1
CONTROLS ................................................................................................................................ C-1
CHECKOUT PROCEDURE ....................................................................................................... C-2
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Table of Contents
(Continued)
Paragraph
Page
Appendix D
Installation Checkout Using the TIC T-49C Flightline Tester
D.1
D.2
D.3
INTRODUCTION ....................................................................................................................... D-1
CONTROLS ................................................................................................................................ D-1
CHECKOUT PROCEDURE ....................................................................................................... D-2
Appendix E
Using the Terminal Device
Using the Terminal Device ....................................................................................................................... E-1
Appendix F
Installation Checkout Using an Alternate Display
F.1
F.2
F.3
F.4
INTRODUCTION ........................................................................................................................F-1
CONTROLS .................................................................................................................................F-1
CHECKOUT PROCEDURE ........................................................................................................F-1
SELF TEST...................................................................................................................................F-6
Appendix G
SKYWATCH® HP SKY899
Permission to use STC SA01552CH-D for Raytheon C90
Permission to use STC SA01552CH-D for Raytheon C90....................................................................... G-1
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List of Illustrations
Figure
Page
Figure 1-1: Typical Vertical Display Modes and Traffic Zones................................................................1-3
Figure 1-2: SKY899 System Block Diagram ............................................................................................1-4
Figure 1-3: Standard TRC Mounting Tray (P/N 805-10870-001).............................................................1-7
Figure 1-4: Ruggedized TRC Mounting Tray (P/N 805-10870-003) ........................................................1-8
Figure 1-5: P1 Connector Dimensions (Reference Only) ..........................................................................1-8
Figure 1-6: TRC899 Transmitter Receiver Computer (TRC)....................................................................1-9
Figure 1-7: System Configuration Module ................................................................................................1-9
Figure 1-8: WX-1000/SKY497 Display Equipment Tag ........................................................................1-10
Figure 1-9: WX-1000/SKY497 Display ..................................................................................................1-11
Figure 1-10: NY156/NY164 Directional Antenna...................................................................................1-13
Figure 2-1: Directional Antenna Mounting Location ................................................................................2-3
Figure 2-2: Interconnect Wiring Without WX-1000 .................................................................................2-5
Figure 2-3: Interconnect Wiring with WX-1000 .......................................................................................2-9
Figure 2-4: Interconnect Wiring with Alternate Display .........................................................................2-13
Figure 2-5: Heading Input Cable .............................................................................................................2-19
Figure 2-6: Display Cable........................................................................................................................2-21
Figure 2-7: Above and Below External Lamps .......................................................................................2-27
Figure 2-8: System Configuration Module ..............................................................................................2-31
Figure 2-9: Typical Location of System Configuration Module (Inside Backshell) ...............................2-31
Figure 2-10: Antenna Mounting Holes ....................................................................................................2-34
Figure 2-11: Directional Antenna Installation ........................................................................................2-34
Figure 2-12: Mounting Holes for Standard Mounting Tray, P/N 805-10870-001..................................2-35
Figure 2-13: Mounting Holes for Ruggedized Mounting Tray, P/N 805-10870-003..............................2-36
Figure 2-14: TRC899 Installation ............................................................................................................2-37
Figure 2-15: Instrument Panel Cutout and Mounting Holes....................................................................2-38
Figure 2-16: Display Installation .............................................................................................................2-39
Figure 3-1: Controls...................................................................................................................................3-1
Figure 3-2: Start-up Screen ........................................................................................................................3-2
Figure 3-3: Standby Screen........................................................................................................................3-3
Figure 3-4: Typical Patch Antenna Tripod Mount.....................................................................................3-7
Figure 3-5: Self Test Screen ......................................................................................................................3-8
Figure 4-1: Service Menu (Terminal Emulation Program)........................................................................4-2
Figure 4-2: Service Menu (WX-1000/SKY497 Display) ..........................................................................4-2
Figure 4-3: Setup Menu .............................................................................................................................4-3
Figure 4-4: Save Menu...............................................................................................................................4-3
Figure 4-5: Aircraft Type Menu ................................................................................................................4-4
Figure 4-6: Antenna System Menu ............................................................................................................4-4
Figure 4-7: Top Antenna Menu .................................................................................................................4-5
Figure 4-8: Audio Level Menu ..................................................................................................................4-5
Figure 4-9: ARINC 429 Receivers Menu ..................................................................................................4-6
Figure 4-10: ARINC 429 Receiver Channel Menu ...................................................................................4-6
Figure 4-11: Equipment Type Menu..........................................................................................................4-6
Figure 4-12: ARINC-429 Receiver Speed Menu.......................................................................................4-7
Figure 4-13: Avionics Equipment Menu ...................................................................................................4-7
Figure 4-14: No Channel Assigned Menu .................................................................................................4-7
Figure 4-15: GPS Nav Menu .....................................................................................................................4-8
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List of Illustrations
(continued)
Figure
Page
Figure 4-16: Heading Menu.......................................................................................................................4-8
Figure 4-17: Heading Valid Line Menu.....................................................................................................4-8
Figure 4-18: Barometric Altitude Menu ....................................................................................................4-9
Figure 4-19: Radio Altimeter Menu...........................................................................................................4-9
Figure 4-20: Radio Altimeter Valid Line Menu ........................................................................................4-9
Figure 4-21: Landing Gear Menu ............................................................................................................4-10
Figure 4-22: Weight-On-Wheels Menu ...................................................................................................4-10
Figure 4-23: Audio Suppression Menu....................................................................................................4-10
Figure 4-24: External Display Menu .......................................................................................................4-11
Figure 4-25: Information Menu ...............................................................................................................4-12
Figure 4-26: Software Version Menu ......................................................................................................4-13
Figure 4-27: System Log Menu ...............................................................................................................4-13
Figure 4-28: Data Monitor Menu.............................................................................................................4-14
Figure 4-29: ARINC 429 Receivers Data Monitor ..................................................................................4-14
Figure 4-30: Antenna Calibration Data Monitor......................................................................................4-15
Figure 4-31: Barometric Altitude Data Monitor ......................................................................................4-15
Figure 4-32: Discrete Values Data Monitor.............................................................................................4-15
Figure 4-33: GPS Nav Data Monitor .......................................................................................................4-16
Figure 4-34: Mag Heading Data Monitor ................................................................................................4-16
Figure 4-35: Radio Altitude Data Monitor ..............................................................................................4-16
Figure 4-36: Antenna Calibration Menu..................................................................................................4-17
Figure 4-37: Ground Test Menu ..............................................................................................................4-18
Figure 4-38: Ground Test in Progress......................................................................................................4-18
Figure 4-39: Configuration Management Menu ......................................................................................4-19
Figure 4-40: Compact Flash Insertion Instructions..................................................................................4-20
Figure 4-41: Service Menu Tree (Sheet 1 of 3) .......................................................................................4-21
Figure 4-42: Adapter Plug Assembly.......................................................................................................4-27
Figure A-1: I/O Connector P1 Pin Assignments.....................................................................................A-15
Figure C-1: Controls ................................................................................................................................. C-1
Figure C-2: Start-up Screen ...................................................................................................................... C-3
Figure C-3: Standby Screen ...................................................................................................................... C-3
Figure D-1: Controls .................................................................................................................................D-1
Figure D-2: Start-up Screen ......................................................................................................................D-2
Figure D-3: Standby Screen......................................................................................................................D-3
Figure F-1: SKYWATCH Startup Screen on Terminal Device................................................................ F-2
Figure F-2: External Annunciator Operation. .......................................................................................... F-3
Figure F-3: Typical Patch Antenna Tripod Mount ................................................................................... F-5
Figure G-1: STC SA01552CH-D Cover Sheet ......................................................................................... G-2
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Installation Manual
List of Tables
Table
Page
Table 1-1: SKY899 System .......................................................................................................................1-5
Table 1-2: TRC Installation Kit P/N 817-11900-xxx ................................................................................1-6
Table 1-3: WX-1000/SKY497 Display Installation Kit P/N 817-10802-001..........................................1-10
Table 1-4: Airframe Installation Kits.......................................................................................................1-12
Table 1-5: Directional Antenna Installation Kit 817-10009-xxx.............................................................1-13
Table 1-6: TRC899 Hardware Modifications ..........................................................................................1-16
Table 1-7: TRC899 Software Revisions ..................................................................................................1-16
Table 1-8: Minimum Interface Equipment Required...............................................................................1-17
Table 1-9: Directional Antenna SIGMA and DELTA Port Cable Vendors ............................................1-18
Table 1-10: Cable to Connector Reference..............................................................................................1-19
Table 1-11: Heading Input Cable Vendors ..............................................................................................1-21
Table 1-12: Display Cable Vendors.........................................................................................................1-23
Table 2-1: Soft-Key Connection Options ................................................................................................2-30
Table 2-2: WX-1000/SKY497 Display Connection ................................................................................2-32
Table 2-3: WX -1000 Processor Connection ...........................................................................................2-32
Table 4-1: Alternate Display Drivers.......................................................................................................4-12
Table 4-2: Fault Isolation.........................................................................................................................4-24
Table 4-3: Installation Related Error Messages .......................................................................................4-25
Table 4-4: Informational Error Messages ................................................................................................4-26
Table A-1: Compatible Analog Radio Altimeter Specifications ..............................................................A-9
Table A-2: ARINC-429 Input Labels (Rx) .............................................................................................A-17
Table A-3: ARINC-429 Output Labels (Tx)...........................................................................................A-18
Table C-1: IFR Systems TCAS-201 Ramp Test Set Setup Data .............................................................. C-2
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Section 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 alternate 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.
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Installation Manual
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.
9. Software version 1.8 (or higher) and Mod D adds Verbal Intruder Positioning (ViP™),
SKYWATCH HP’s new extended audio callout feature. The ViP™ extended audio adds range,
relative altitude and relative bearing callout to the aural TA’s.
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 altitude
Accepts both analog and ARINC 429 radio
altitude
• Display Ranges (WX-1000 CDU)
2 nmi and 6 nmi
Driver selectable ranges between 2 and 24
nmi are available.
• 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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Installation Manual
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
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Figure 1-2: SKY899 System Block Diagram
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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
805-10890-00x**
* 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 and 1.4.3).
1.3.1 TRC899 Transmitter Receiver Computer P/N 805-11900-001
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 rightangle backshell (see Figure 1-5).
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Table 1-2: TRC Installation Kit P/N 817-11900-xxx
KIT P/N
817-11900-001
817-11900-002
817-11900-003
817-11900-004
817-11900-005
DESCRIPTION
Installation on Fixed-Wing Aircraft with Straight 1.5 inch
(3.8 cm) Backshell Consists of:
Standard Mounting Tray Assembly
1.5" (3.8 cm) Straight Backshell
I/O Connector, 100-Position, Female, (Mil-C-38999 Series III)
(Includes #22D Crimp Terminals)
Spare Terminals for I/O Connector
Power Connector, 3-Position, Straight Plug
(Includes #16 Crimp Terminals)
Spare Terminals for Power Connector (M39029/32-247)
System Configuration Module Assembly
Installation on Fixed-Wing Aircraft with Straight 2.5 inch
(6.4 cm) Backshell Consists of:
Standard Mounting Tray Assembly
2.5" (6.4 cm)Straight Backshell
I/O Connector, 100-Position, Female, (Mil-C-38999 Series III)
(Includes #22D Crimp Terminals)
Spare Terminals for I/O Connector
Power Connector, 3-Position, Straight Plug
(Includes #16 Crimp Terminals)
Spare Terminals for Power Connector (M39029/32-247)
System Configuration Module Assembly
Installation on Fixed-Wing Right-Angle (90°) Backshell
Consists of:
Standard Mounting Tray Assembly
Right-Angle (90°) Backshell
I/O Connector, 100-Position, Female, (Mil-C-38999 Series III)
(Includes #22D Crimp Terminals)
Spare Terminals for I/O Connector
Power Connector, 3-Position, Straight Plug
(Includes #16 Crimp Terminals)
Spare Terminals for Power Connector (M39029/32-247)
System Configuration Module Assembly
Installation with ruggedized tray, 2.5 inch (6.4 cm) Backshell.
Consists of:
Ruggedized Mounting Tray Assembly
2.5" (6.4 cm)Straight Backshell
I/O Connector, 100-Position, Female, (Mil-C-38999 Series III)
(Includes #22D Crimp Terminals)
Spare Terminals for I/O Connector
Power Connector, 3-Position, Straight Plug
(Includes #16 Crimp Terminals)
Spare Terminals for Power Connector (M39029/32-247)
System Configuration Module Assembly
Installation with ruggedized tray, Right-Angle (90°) Backshell.
Consists of:
Ruggedized Mounting Tray Assembly
Right-Angle (90°) Backshell
I/O Connector, 100-Position, Female, (Mil-C-38999 Series III)
(Includes #22D Crimp Terminals)
Spare Terminals for I/O Connector
Power Connector, 3-Position, Straight Plug
(Includes #16 Crimp Terminals)
Spare Terminals for Power Connector (M39029/32-247)
System Configuration Module Assembly
Page 1-6 - General Information
September 20, 2007
QUANTITY
PART NUMBER
1
1
1
805-10870-001
613-10039-001
605-10251-001
10
1
M39029/56-348
MS3126F12-3S
4
1
607-10018-001
814-18005-001
1
1
1
805-10870-001
613-10042-001
605-10251-001
10
1
M39029/56-348
MS3126F12-3S
4
1
607-10018-001
814-18005-001
1
1
1
805-10870-001
613-10043-001
605-10251-001
10
1
M39029/56-348
MS3126F12-3S
4
1
607-10018-001
814-18005-001
1
1
1
805-10870-003
613-10042-001
605-10251-001
10
1
M39029/56-348
MS3126F12-3S
4
1
607-10018-001
814-18005-001
1
1
1
805-10870-003
613-10043-001
605-10251-001
10
1
M39029/56-348
MS3126F12-3S
4
1
607-10018-001
814-18005-001
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Revision D
SKY899
Installation Manual
NOTE
DIMENSIONS ARE IN INCHES (MILLIMETERS)
3.
(97 84
MA .5)
X.
4.15
(105.4)
MAX.
3.37
(85.6)
MAX.
REAR HOLD-DOWN PINS
(2-PLACES)
G
CO
5
1.1 .2)
(29
50
0.7 .1)
(19
G
CO
CL
RETAINER CUPS
HOLD-DOWN KNOBS
(2-PLACES)
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)
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NOTE
DIMENSIONS ARE IN INCHES (MILLIMETERS)
S
E
O
D
IN
E
34 ) CR
4. 0.2 E S
1 D
(1 CLU
T
O
N
W
S
D
A
E
H
3.66
(93.0)
MAX.
03
1.2.6)
(30
5
0.71)
.
(19
CL
G
O
C
G
CO
9
5.6.5)
4
(14
.36
13 .3)
9
3
3
( X.
MA
0
1.72)
.
(43 X.
MA
Figure 1-4: Ruggedized TRC Mounting Tray (P/N 805-10870-003)
1.5" BACKSHELL
3.75 (95.3)
or
2.5" BACKSHELL
4.75 (120.7)
REF.
NOTE
DIMENSIONS ARE IN INCHES (MILLIMETERS)
4.25
(108.0)
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)
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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:
System Configuration Module).
6.00
(152.4)
REF.
0.75
(19.1)
CONFIG MODULE
P/N 814-18005-001
0.25
(6.4)
0.42
(10.7)
Figure 1-7: System Configuration Module
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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 postinstallation 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
1
1
2
25
26-1001-6374-5
26-1003-5633
26-1006-2426-6
26-1006-1089-3
26-1003-4274-9
Screw, Machine, 6-32 x 3/4 in. Phillips Pan Head, Black Oxide
Connector, 25 Position Recpt. Shell
Connector Backshell, DB25
Connector Lock Post Assembly
Connector Socket, Screw Machine (M39029/63-368)
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SKY899
Installation Manual
3
(9 .89
8.
8)
NOTE
DIMENSIONS ARE IN INCHES (MILLIMETERS)
CL
C.G.
3.18
(80.8)
3.37
(85.6)
J101
CL
3.18
(80.8)
3.37
(85.6)
0.55
(14.0)
CL
CL
C.G.
P101
0.17 ±0.02
(4.3 ±0.5)
3.40
(86.4)
8.07
(205.0)
0.08
(2.0)
1.30
(33.0)
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
BAE/RAYTHEON
BEECH
HAWKER 400, 600, 700, 800, and 1000
BEECHJET, KING AIR 90, 100, 200, 300, and 350
BARON 33, 35, 36, 55, 58, BE-99, 1300, & 1900C/D
817-10009-004
817-10009-001
817-10009-002
CANADAIR
CHALLENGER 600 and 601
817-10009-005
CESSNA
CITATION III, VI, VII
CITATIONJET, CITATION I, II, V
182, 210, 337, 401, 414, 425, 441
817-10009-001
817-10009-004
817-10009-006
COMMANDER
114
817-10009-006
DASSAULT
FALCON 10, 20, 50
FALCON 900
817-10009-001
817-10009-005
DEHAVILLAND
Dash 7/8
817-10009-001
EMBREAR
EMB 110, 120
817-10009-001
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
817-10009-004
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
SOCATA
TBM-700
817-10009-001
TB20
817-10009-006
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Revision D
SKY899
Installation Manual
Table 1-5: Directional Antenna Installation Kit 817-10009-xxx
SUPPLIED PARTS *
KIT PART NUMBER
PART NUMBER
DESCRIPTION
QUANTITY
817-10009-001
817-10009-002
817-10009-003
817-10009-004
817-10009-005
800-10066-001
800-10066-002
800-10066-004
800-10066-003
800-10066-005
Special Adapter Plate, 40 Inch (101.6 cm) Radius
Special Adapter Plate, 63 Inch (160.0 cm) Radius
Special Adapter Plate, 80 Inch (203.2 cm) Radius
Special Adapter Plate, 32 Inch (81.3 cm) Radius
Special Adapter Plate, 47 Inch (119.4 cm) Radius
1
1
1
1
1
817-10009-006
(No Adapter Plate)
100-10022-001*
101-10027-001*
Screw, 10-32 x 1 PPH SS (MS51958-67)
Stop Nut, 10-32 (MS21044C3)
4
4
* Hardware supplied with all kits.
Figure 1-10: NY156/NY164 Directional Antenna
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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, 2.5 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 1-800-4530288 or 1-616-949-6600 for latest certification information.
Page 1-14 - General Information
September 20, 2007
009-11900-001
Revision D
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:
2.5 lb ± 0.2 lb (1.1 kg ± 0.1 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 - White Paint)
805-10890-001 (NY164 - White Paint)
805-10890-002 (NY164 - Black Paint)
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 or black 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 Table 1-6 and Table 1-7.
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Installation Manual
Table 1-6: TRC899 Hardware Modifications
MOD
DESCRIPTION
A
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 SB #107.
B
A production change that adds circuitry to the Input/Output PCB assembly to increase the
clock voltage level on U8 and U11 from 3 V dc TTL to 5 V dc CMOS level. Mod not required
for field units. Refer to SB #113.
C
A production change that replaces Q1 on the IF Demodulator PCB with a higher gain part.
Not required for field units. Refer to SB #125.
D
Adds the audio phrases, to U2, necessary for the ViP™ Extended Audio Callouts located in
Software Version 1.8. This changes the Input/Output PCB Assembly to P/N 812-11903-002.
Refer to SB805-11900-002.
Table 1-7: TRC899 Software Revisions
SYSTEM
REVISION
SKY HP
VERSION
1.4
1.05
Original production release.
1.5
1.06
Refer to Service Bulletin 102.
DESCRIPTION
•
•
•
1.6
1.07
Refer to Service Bulletin 116.
•
•
1.7
1.08
•
•
1.09
Page 1-16 - General Information
September 20, 2007
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.
Refer to Service Bulletin 121.
•
1.8
For Collins ProLine 4 transponder interface, corrects label 350 used by the
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 System ARINC-429
heading interface.
Corrects tracking of non-altitude reporting intruders when own aircraft is
greater than approximately 6,200 feet.
Corrects the displayed status of the radio altimeter (valid/invalid) when an
offscale condition occurs (i.e., MSG annunciator will not appear on the CDU
when radio altimeter is offscale, unless the discrete flag line changes to
invalid).
Changes the displayed company logo and name to reflect new ownership by
L-3 communications.
Refer to Service Bulletin SB805-11900-1.
•
Adds ViP™ Extended Audio Callout feature.
•
Eliminates false failures during the transmitter power self-test by adjusting
the pass/fail parameters to the correct range.
009-11900-001
Revision D
SKY899
Installation Manual
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
X
¬
−
®
Ã
1.7
X
ON - OFF SWITCH
¬
AUDIO SYSTEMS
X
PILOT CONTROLS
(PUSHBUTTONS)
X
EXTERNAL LAMPS
ATCRBS & ADS-B
(future option)
GPWS/EGPWS/TAWS
(AUDIO INHIBIT)
¬
SUPPRESSION BUS
X
SQUAT SWITCH (WOW)
RADIO ALTITUDE
¬
LANDING GEAR SWITCH
BAROMETRIC ALTITUDE
ATCRBS
(Active Only)
GPS NAV
SURVEILLANCE
MODE
MAGNETIC HEADING
AVIONICS EQUIPMENT
¬
X
X
−
®
®
X
Ã
¬
X
X
−
®
®
X
Ã
Required.
Optional but will enhance performance. (See individual paragraphs in chapter two for
details.)
Required if Terrain Warning System (GPWS, EGPWS, or TAWS) is installed.
Only if Alternate Display requires it, see display manufacturer's instructions.
Required and may be provided by the display (e.g., WX-1000/SKY497 display OFF/BRT
switch).
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 crossreference.
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.
009-11900-001
Revision D
General Information - Page 1-17
September 20, 2007
SKY899
Installation Manual
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
Part Number
Attenuation
(dB/100 ft 1.0 gHz)
Weight (lb)
(per 100 ft)
10.93
8.79
7.9
5.25
4.0
3.31
2.6
3.8
4.5
7.4
6.8
11.8
Polyethylene
PFLX195-500
PFLX240-500
PFLX240-501
PFLX340-500
PFLX400-500
PFLX500-500
Maximum Length
(ft)
Minimum Bend
Radius (in)
21
27
30
40
59
71
0.50
0.75
0.85
1.00
1.00
1.25
14
17
24
30
40
68
0.50
0.85
0.75
2.0
1.5
4.5
Teflon
TFLX130-100
16.7
1.4
TFLX165-100
13.8
2.2
TFLX205-100
9.9
3.2
TFLX225-100
7.9
4.1
TFLX295-100
5.95
7.2
TFLX480-100
3.5
19
Frequency: 1030 MHz
Loss: <2.5 dB at 1030 MHz (includes all cables and connectors)
VSWR: <1.5:1 at 1030 MHz
Electronic Cable Specialists
1-800-327-9473
414-421-5300
FAX 414-421-5301
Part Number
Attenuation
(dB/100 ft 1.0 gHz)
Weight (lb)
(per 100 ft)
12.2
8.7
5.56
3.63
2.7
5.5
8.5
16.1
352001
311601
311201
310801
Maximum Length
(ft)
15
26
41
63
Minimum Bend
Radius (in)
0.81
1.15
1.59
2.26
PIC Wire and Cable
1-800-742-3191
262-246-0500
FAX 262-246-0450
Part Number
Attenuation
(dB/100 ft 1.0 gHz)
Weight (lb)
(per 100 ft)
Maximum Length
(ft)
7.2
5.7
3.8
6.5
8.2
18
32
40
61
S33141
S55122
S22089
Minimum Bend
Radius (in)
1.5
1.6
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.
Page 1-18 - General Information
September 20, 2007
009-11900-001
Revision D
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
Polyethylene
PFLX195-500
PFLX240-500
PFLX240-501
PFLX340-500
PFLX400-500
PFLX500-500
Teflon
TFLX130-100
TFLX165-100
TFLX205-100
TFLX225-100
TFLX295-100
TFLX480-100
TNC Straight
TNC Right Angle
BNC Straight
BNC Right Angle
TMS195-1
TMS240-1
TMS240-1
TMS340-1
TMS400-1
TMS500-1
TMR195-1
TMR240-1
TMR240-1
TMR340-1
TMR400-1
TMR500-1
BMS195-1
BMS240-1
BMS240-1
BMS340-1
BMS400-1
BMS500-1
BMR195-1
BMR240-1
BMR240-1
BMR340-1
BMR400-1
BMR500-1
TMS130-1
TMS165-1
TMS205-1
TMS225-1
TMS295-1
TMS488-1
TMR130-1
TMR165-1
TMR205-1
TMR225-1
TMR295-1
TMR488-1
BMS130-1
BMS165-1
BMS205-1
BMS225-1
BMS295-1
BMS488-1
BMR130-1
BMR165-1
BMR205-1
BMR225-1
BMR295-1
BMR488-1
Electronic Cable Specialists
1-800-327-9473
414-421-5300
FAX 414-421-5301
Cable Part Number
311601
311201
310801
352001
TNC Straight
CTS922
CTS122
CTS022
CTS3522
TNC Right Angle
CTR922
CTR122
CTR022
CTR3522
BNC Straight
CBS922
CBS122
CBS022
CBS3522
BNC Right Angle
CBR922
CBR122
CBR022
CBR3522
PIC Wire and Cable
1-800-742-3191
262-246-0500
FAX 262-246-0450
Cable Part Number
S33141
S55122
S22089
TNC Straight
190308
190608
190408
TNC Right Angle
190309
190609
190409
BNC Straight
190312
190612
190412
BNC Right Angle
190313
190613
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
(Optional)
Compact flash card can be used for configuration management, data 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
009-11900-001
Revision D
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SKY899
Installation Manual
Connector Installation
Data Cables
Flightline Tester
Page 1-20 - General Information
September 20, 2007
J9, J10, & J11
Antenna
P1
Interconnect
P8
Power
P101
Display
See Table 1-8.
Tool M22520/5-01
Die M22520/5-19 (EMTEQ Cable PFLX195-500)
Die M22520/5-43 (EMTEQ Cable PFLX240-500)
Die M22520/5-43 (EMTEQ Cable PFLX240-501)
Die M22520/5-35 (EMTEQ Cable PFLX340-500)
Die M22520/5-61 (EMTEQ Cable PFLX400-500)
Die M22520/5-21 (EMTEQ Cable PFLX500-500)
Die M22520/5-19 (EMTEQ Cable TFLX130-100)
Die M22520/5-19 (EMTEQ Cable PFLX165-100)
Die M22520/5-43 (EMTEQ Cable PFLX205-100)
Die M22520/5-43 (EMTEQ Cable PFLX225-100)
Die M22520/5-35 (EMTEQ Cable PFLX295-100)
Die M22520/5-27 (EMTEQ Cable PFLX480-100)
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)
Crimping Tool M22520/2-01
Positioner M22520/2-07
Insertion MS27495 A22M
Removal MS27495 R22M
Crimping Tool M22520/1-01
Positioner M22520/1-02
Insertion MS24256A16
Removal MS24356R16
Crimping Tool M22520/2-01
Positioner M22520/2-08
Insertion/Removal M81969/1-02
RS-232, RS-422, and ARINC-429 data cables are #22 AWG (minimum)
twisted, shielded cables.
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.
009-11900-001
Revision D
SKY899
Installation Manual
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
COMPANY
Dallas Avionics
1-800-527-2581
214-320-9776
FAX 214-320-1057
WX-5
(6.84 lb/
100 ft)
Electronic Cable
Specialists
1-800-327-9473
414-421-5300
FAX 414-521-5301
3N6607
(7.5 lb/
100 ft)
A.E. Petsche
817-461-9473
FAX 817-277-2887
TZGYR
(6.84 lb/
100 ft)
EDMO Distributors
1-800-235-3300
805-295-6689
FAX 1-800-828-0623
FAX 805-295-6703
WX-1000
SYNCHRO
PIC Wire and Cable
1-800-742-3191
262-246-0500
FAX 262-246-0450
WM25807
(7.2 lb/
100 ft)
Electrical & Mechanical Technologies
(EMTEQ)
1-888-679-6170
262-679-6170
FAX 262-679-6175
Lamps
(external annunciators)
CABLE
P/N
CFLX-C07243T-01
External annunciators are required when using an alternate display that is 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 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.
009-11900-001
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Installation Manual
Miscellaneous Hardware
The installer must provide suitable hardware to attach the TRC Mounting Tray.
The following stainless steel fasteners are recommended:
Channel Mount:
Four 8-32 UNC-2A pan head machine screws per ANSI
B18.6.3. (Six are required for the ruggedized tray.)
Or
Four 8-32 UNC-2A hex socket cap machine screws per
ANSI/ASME B18.3. (Six are required for the ruggedized
tray.)
Four No. 8 helical spring lockwasher per ANSI/ASME
B18.21.1. (Six are required for the ruggedized tray.)
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
(e.g., Laptop Computer)
Required if using an alternate display, (see Appendix E for instructions).
Terminal device is used for system setup, post installation checkout and
troubleshooting. Any computer, with RS-232 terminal emulation software
(e.g., Procomm®, HyperTerminal, etc.) may be used as the terminal device. A
standard 9-pin serial cable is required.
Surface Preparation
Alodine® No. 1001 required for installation of the antenna.
Switches
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).
Extended Audio Switch
(Required)
An extended audio callout switch is required when interfacing to the extended
audio switch input P1-32 of the TRC899. Units with Mod D and software 1.8
or higher are ViP™ Extended Audio Callout capable. This switch allows the
pilot to turn on and off (mute) the range, relative altitude and relative bearing
callout from the aural TA’s. When the switch is in the “Normal” position the
standard phrase “Traffic, Traffic” is still annunciated.
Any SPST toggle switch (1/2 A @ 28 V dc) may be used.
Page 1-22 - General Information
September 20, 2007
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Revision D
SKY899
Installation Manual
Switches (continued)
WX-1000
If the final configuration includes a WX-1000 Stormscope Weather Mapping
System, two external switches are required. Any general purpose toggle 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 &
WX-1000 Processor Cable
This cable is used to connect the WX-1000/SKY497 display and/or WX-1000
processor to the TRC. Required connectors and contact pins are supplied in the
installation kit. Cable specifications and U.S. vendors are listed below in
Table 1-12.
NOTE
Use of any cable not meeting specifications voids all system warranties.
Table 1-12: Display Cable Vendors
1.8
U.S.
COMPANY
DISPLAY CABLE
P/N
WEIGHT
(LB PER 100 FT)
Dallas Avionics
1-800-527-2581
214-320-9776
FAX 214-320-1057
WX-3
10.5
Electronic Cable Specialists
1-800-327-9473
414-421-5300
FAX 414-421-5301
3N6715
16
A.E. Petsche
817-461-9473
FAX 817 277 2887
TZDIS
13.1
PIC Wire and Cable
1-800-742-3191
262-246-0500
FAX 262-246-0450
WM25815
14.5
EDMO Distributors
1-800-235-3300
509-535-8280
FAX 1-800-828-0623
FAX 509-535-8266
WX-1000 Display
---
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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September 20, 2007
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SKY899
Installation Manual
Section 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
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.
Installation instructions for the WX-1000 processor are detailed in the WX-1000 Installation Manual.
Tolerances (unless otherwise indicated):
Angles are
± .5°
.00 Two Place Decimals are
± .01
.000 Three Place Decimals are
± .005
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).
009-11900-001
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Installation Manual
2.3
ANTENNA LOCATION
Location is an important factor for maximum antenna performance. Optimum location for a particular
aircraft type is usually available from the aircraft manufacturer. In selecting a location, consider the
following:
Directional Antenna
The mounting site should be on the top forward fuselage, as close to the
centerline as possible, and within -10° of the in-flight horizon (see Figure 2-1).
The optimum mounting point for maximum coverage is as far forward as
possible without exceeding the -10° forward pitch. If necessary, consideration
should be given to relocating other antennas to obtain the furthest forward
location for the directional antenna. The antenna should be mounted on the
aircraft with at least 20 dB isolation (about 30 inches (76.2 cm)) from other Lband frequency antennas and 24 inches (61.0 cm) from other antennas or
obstructions. The ground-plane should be as large as possible, a 30-inch (76.2
cm) ground-plane diameter is recommended.
The directional antenna can be bottom mounted only if a suitable top mount
location is not available. Each bottom mount installation must be evaluated on a
case-by-case basis. Before starting a bottom mount installation, contact Field
Service Engineering at 1-800-453-0288 or 1-616-949-6600.
Figure 2-1: Directional Antenna Mounting Location
Page 2-2 - Installation
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009-11900-001
Revision D
SKY899
Installation Manual
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.
2.5
DISPLAY LOCATION
The display should be mounted in a location easily accessible and clearly visible to the pilot. If using an
alternate display device refer to manufacturer instructions for location. In selecting a location for WX1000/SKY497 display, consider the following:
Magnetic Effect
Where possible to avoid it, the display should not be mounted within 3 inches (8 cm)
of an electric turn and bank indicator, as the magnetic effect of the turn and bank
motor may affect the display presentation. (A common symptom of magnetic
interference is a wobbling or vibrating display raster.)
NOTE
If it is necessary to mount the display unit next to a device that may
affect the CRT display, magnetic shielding material can be placed around
the display unit. Shielding material is available from 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)
009-11900-001
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Page 2-5 (2-6 blank)
September 20, 2007
SKY899
Installation Manual
Figure 2-2. Interconnect Wiring Without WX-1000
(Sheet 2 of 2)
009-11900-001
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Page 2-7 (2-8 blank)
September 20, 2007
SKY899
Installation Manual
Figure 2-3. Interconnect Wiring With WX-1000
(Sheet 1 of 2)
009-11900-001
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Section 2 - Installation
Page 2-9 (2-10 blank)
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SKY899
Installation Manual
Figure 2-3. Interconnect Wiring With WX-1000
(Sheet 2 of 2)
009-11900-001
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Section 2 - Installation
Page 2-11 (2-12 blank)
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SKY899
Installation Manual
Figure 2-4. Interconnect Wiring with
Alternate Display (Sheet 1 of 2)
009-11900-001
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SKY899
Installation Manual
Figure 2-4. Interconnect Wiring with
Alternate Display (Sheet 2 of 2)
009-11900-001
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SKY899
Installation Manual
2.6
CABLE REQUIREMENTS AND FABRICATION
The installer will supply and fabricate all system cables. Cable specifications and approved vendors are
provided in paragraph 1.7, equipment required but not supplied. Appendix A defines the electrical
characteristics of all input and output signals and identifies the cable requirements for each signal.
Required connectors and contact pins are supplied in the installation kits.
NOTES
1. Use of any cable not meeting 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 Figure 2-2,
Figure 2-3 and Figure 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 ARINC-429.
•
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 (Figure 2-2, Figure 2-3 and Figure 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.
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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.
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, Figure 2-3 or Figure 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.
7
1
6
5
2
4
3
Figure 2-5: Heading Input Cable
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2.6.5
Power Cable
For the power cable, use #16 AWG (minimum) twisted shielded pair cable (Beldon 83322, Alpha 2826/2,
or equivalent). The power cable runs from the aircraft circuit breaker panel to the TRC. The power cable
is connected to the TRC using the MS3126F12-3S connector included in the TRC installation kit.
Terminate the shield to airframe ground at the power source. Power cable routing and length are not
critical to system operation. The SKY899 is a 28 V dc system (18 to 32 V dc).
NOTE
5 A circuit breaker is required.
2.6.6
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 Figure 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 Table
2-2 and Table 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.
4.
5.
6.
7.
Same as 2 except Orange jacket.
Same as 2 except Green jacket.
Same as 2 except Red jacket.
Same as 2 except Black jacket.
Same as 2 except Yellow jacket.
Aluminized Mylar® wrap.
8.
9.
10.
11.
#34 AWG braided shield.
FEP Teflon® jacket .013 in. - .023 in., Red tint.
Marker tape with Vendor P/N.
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7
2
6
11
10
3
9
1
8
4
5
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
7 ARINC-429 RX channels
3 ARINC-429 TX channels
System Configuration Module
Heading valid, 1 input pin (active low or high)
Analog radio altimeter and flag
GPS Position (for ADS-B)
Altimeter Gilham Code "D2" added
Lamp Outputs - above, below and oper_mode
(used with alternate display)
Stepper (heading) not available
Landing Gear Switch (active low or high)
Squat Switch (active low or high)
Audio inhibit (GPWS/EGPWS/TAWS)
(active low or high)
18 - 32 V dc power input
Antenna: NY156 (TCAS) or NY164 (TAS)
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2 ARINC-429 RX channels
1 ARINC-429 TX channel
Individual configuration pins
Heading valid, 2 input pins (active low or high)
Not available
Not available
Altimeter Gilham Code "D2" not available
Not available
Stepper (heading) available
Active low only
Active low only
Active low only
11 - 34 V dc power input
Antenna: NY164 (TAS only)
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2.7
AIRCRAFT DISCRETE INPUTS
The aircraft discrete inputs are used for ViP™ extended audio callout, 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
ViP™ Extended Audio Callout
The SKY899 must have software version 1.8 (or higher) and Mod D installed in order to use this feature.
In order to enable extended audio callouts, connect P1-32 (EXT_AUDIO_SW) to ground via a pilot
operated switch. When the pilot operated switch is in extended mode the TA aural alerts will have “range,
relative altitude (when available) and relative bearing” information announced as well as traffic. When
the switch is in the “Normal” position it mutes the range, relative altitude, and bearing callout from the
aural TA’s, but the standard phrase “Traffic, Traffic” is still annunciated.
CAUTION
Do not connect a switch to the extended audio switch input
(EXT_AUDIO_SW, P1-32), unless the TRC899 has Mod D and
Software Version 1.8 or higher.
Any SPST switch (1/2 A @ 28 V dc) can be connected to P1-32 (see notes on Figure 2-2, 2-3 or 2-4).
Extended Audio Callout Switch connection:
EXT_AUDIO_SW
P1-32
2.7.2 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
2.7.3
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
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2.7.4
Squat Switch (Weight-On-Wheels)
This input is to be connected to the squat switch (weight-on-wheels) to sense when the aircraft is on the
ground.
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 or airspeed switch, ground this input and select "Active Low
when configuring "Weight on Wheels" in the service menu. With this configuration the pilot must toggle
the system in and out of standby manually. Traffic will only be displayed when the pilot switches out of
the standby position.
With a squat switch installed, SKYWATCH HP will automatically switch out of standby 8 to 10 seconds
after takeoff and switch back to standby 24 seconds after landing. A squat switch would also prevent the
STB button) while the aircraft is inpilot from placing SKYWATCH HP in standby (i.e., pressing the
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.
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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
2.9.2
A429RX3_A
A429RX3_B
A429RX4_A
A429RX4_B
P1-64
P1-65
P1-73
P1-74
A429RX5_A
A429RX5_B
P1-75
P1-76
Mode S Transponder I/O (future option)
The TRC has one receive and one transmit channel designated for the mode S transponder XT & TX bus
interface. The receiver and transmit speed is fixed at 100 kHz. This is a future option, do not connect at
this time.
Mode S Transponder XT bus connections:
A429RX7_A
P1-83
A429RX7_B
P1-84
Mode S Transponder TX bus connections:
A429TX2_A
P1-44
A429TX2_B
P1-45
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2.9.3
Alternate Display Output
The TRC has one transmit channel designated for alternate displays (i.e., EFIS, MFD and weather radar
via 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.
Connect this output to an unmuted audio panel input.
Two outputs, 150 ohm and 600 ohm, can supply up to 40 mW to the audio distribution system. Volume
level is set via the Service Menu.
Audio output connections:
AUDIO_H
AUDIO_L
AUDIO_C
P1-89 (600 Ohm)
P1-90 (150 Ohm)
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 ARINC429) 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.
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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 (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.
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Synchro (XYZ) heading connections:
HEADING_X
P1-46 (Synchro X)
HEADING_Y
P1-47 (Synchro Y)
HEADING_Z
P1-48 (Synchro Z)
HEADING_H
P1-49 (26 V ac High)
HEADING_C
P1-50 (26 V ac Low)
HEADING_FLG
P1-51 (Heading Valid)
2.13.2 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 and 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
(Normal)
ABV BLW
(Above)
ABV BLW
(Below)
ABV BLW
(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
ON/OFF_RET
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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
2.17 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
+28V_RET
SPARE
P8-A
P8-B
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).
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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.
2.19 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.
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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 softkey connections.
NOTE
Pilot must be able to perform the functions listed in Table 2-1, with
either the 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
DISPLAY
ALTERNATE DISPLAY(S)
SFTKEY1_IN (P1-18)
MSG
Connect
Do not Connect
SFTKEY2_IN (P1-19)
TEST/ALT
Connect
Connect (Momentary Switch - external switch or alternate
display open-collector output). Label external switch TEST/ALT,
TEST or ALT depending on alternate display capabilities.
(NRM/ABV/BLW/
UNR)
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.
2.21 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
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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
Red (VCC)
-toBlack (Ground)
-toGreen (Serial Clock)
-toYellow (Serial Data)
-to-
TRC899
P1-2 (+3.3V)
P1-92 (PLUG_GND)
P1-100 (SCL)
P1-99 (SDA)
RED
BLACK
GREEN
YELLOW
TO P1-2 (+3.3V)
TO P1-92 (PLUG_GND)
TO P1-100 (SCL)
TO P1-99 (SDA)
CONFIG MODULE
P/N 814-18005-001
TERMINAL
P/N M39029/56-348
Figure 2-8: System Configuration Module
SPLIT ELBOW
90° BACKSHELL
P/N 613-10043-001
CONFIGURATION MODULE
P/N 814-18005-001
(located inside backshell)
.
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)
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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
FUNCTION
P101
WIRE COLOR
SUB-CABLE
(Inner Jackets)
2
DPWR+15_OUT
19
WHITE
DPWR-15_OUT
14
WHITE
DSPLY_GND
18
WHITE
HSYNC_OUT_HI
6
BLUE
HSYNC_OUT_LO
5
BLUE
VSYNC_OUT_HI
9
ORANGE
VSYNC_OUT_LO
10
ORANGE
VIDEO_OUT_HI
8
RED
VIDEOOUT_LO
7
RED
PWR_SW_HI
22 (SW2*)
GREEN
PWR_SW-LO
23 (SW2*)
GREEN
SFTKEY1_IN
13
BLACK
SFTKEY2_IN
12
BLACK
SFTKEY3_IN
25
YELLOW
SFTKEY4_IN
24
YELLOW
*SW2 required if WX-1000 Processor installed (see figure 2-2).
TRC
WIRE
WHITE
ORANGE
BLUE
BLUE
WHITE
WHITE
BLUE
WHITE
BLUE
WHITE
BLUE
WHITE
BLUE
WHITE
BLUE
P1
P1-8
P1-9
P1-10
P1-11
P1-12
P1-13
P1-22
P1-16
P1-17
P1-4
P1- 5
P1-18
P1-19
P1-20
P1-21
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
PWRSWHI
PWRSWLO
+15
-15
DSPGND
HSYNCHI
HSYNCLO
VSYNCHI
VSYNCLO
VIDEOHI
VIDEOLO
SFTKEY1
SFTKEY2
SFTKEY3
SFTKEY4
P301-5
P301-21
P301-20
P301-3
P301-36
P301-38
P301-6
P301-23
P301-40
P301-7
P301-22
P301-39
P301-9
P301-26
P301-43
P301-44
GREEN
GREEN
WHITE
WHITE
WHITE
BLUE
BLUE
ORANGE
ORANGE
RED
RED
BLACK
BLACK
YELLOW
YELLOW
WHITE
BLUE
WHITE
ORANGE
BLUE
BLUE
WHITE
WHITE
BLUE
BLUE
WHITE
WHITE
BLUE
WHITE
BLUE
SW2*
SW2*
P1-25
P1-26
P1-27
P1-28
P1-29
P1-30
P1-41
P1-35
P1-36
P1-37
P1-38
P1-39
P1-40
*SW2 required if WX-1000 Processor installed (see Figure 2-2).
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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 WX1000/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 (metalto-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, Figure 2-3 or Figure 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.
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NOTES
1. Before installing the antenna on an aircraft remove the tape, which
holds the O-RING gasket in place during shipment (refer to SL-206).
If the O-ring is in a separate bag, remove 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 nonpressurized aircraft, use a non-corrosive sealant that meets the
physical requirements of MIL-A-46146 such as General Electric
RTV162.
Figure 2-10: Antenna Mounting Holes
Figure 2-11: Directional Antenna Installation
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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.
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 Figure 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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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.
4. Connect the Sum port antenna connector (P9 - a TNC connector identified with a blue band) to
connector J9 (identified with blue marking).
5. Connect the Probe (Bit) port antenna connector (P10 - a BNC connector identified with a black band)
to connector J10.
6. Connect the Difference (Delta) port antenna connector (P11 - a TNC connector identified with a red
band) to connector J11 (identified with red marking).
7. Connect I/O Signal Cable (P1 - a 100-pin connector) to connector J1.
8. Connect the power cable (P8 - a three-pin connector) to connector J8.
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J9
INT
J
ER 1
CO
N
NE
CT
J1
0
J1
1
J8
POWER
)
UE
K)
AC
L
B
(
J
)
BE
ED
RO
(R
P
E
0
C
J1
EN
ER
F
IF
-D
J1 1
ST
TE
Y
R
TO
AC
F
J7
S
9-
J1
INTERCONNECT
(I/O SIGNAL)
(B L
UM
POJ8
WE
R
J7
TE
ST
J1
ME
MOUNTING TRAY
2
MO
RY
C
AR
D
J12
MEMORY CARD
ACCESS DOOR
RETAINER CUPS
(2 PLACES)
HOLD-DOWN KNOBS
(2 PLACES)
Figure 2-14: TRC899 Installation
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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.
(1 3.9
00 2
.0
)
NOTE
DIMENSIONS ARE IN INCHES (MILLIMETERS)
0.15 (3.8)
4 HOLES
#25 Drill Bit
3.06
(78.0)
3.21
(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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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
(QTY 4)
AIRCRAFT PANEL
MOORING PLATE (NOT SUPPLIED)
DISPLAY
REAR MOUNT
6-32 X 3/4 PHMS
(QTY 4)
AIRCRAFT PANEL
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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Section 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
Switch
1, 2, 3, & 4
Pushbuttons
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Power is applied by rotating the knob clockwise past the detent. Continued clockwise
rotation increases display brightness.
Also referred to as soft-keys (1), (2), (3), and (4). In every operating mode a label
identifying the button function will be displayed next to the button.
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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.
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.
1. 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.
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).
The ARINC 429 Receivers menu will appear. With all (source) avionics equipment turned on
highlight and select the RX channel to be configured.
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.
Rx channel menu will appear, select speed from the menu. The ARINC 429 receiver speed menu will
appear, select correct speed.
The ARINC 429 Rcvrs menu will appear, verify receiver channels match desired wiring interface.
Repeat above steps a thru d for each receiver channel input that is connected.
Select exit to return to Setup Menu.
6. From the Setup menu, select Avionics Equipment:
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.
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.
Select exit until you return to Service Menu.
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 configuration 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:
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).
Verify calibration passed: A new bit phase value is displayed and no error messages appeared.
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 extended audio switch, 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:.
f.
•
115 Vac, 60 Hz
•
115 Vac, 400 Hz
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.
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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).
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.
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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.
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.
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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:
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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Section 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
NEXT
SEL
PREV
Figure 4-2: Service Menu (WX-1000/SKY497 Display)
Ground Test is available only if squat switch input indicates aircraft is on the ground.
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The buttons perform the following operations:
EXIT - backs up one screen (if in service menu screen it will exit and enter normal/standby mode).
NEXT - scrolls to the next item.
SEL - selects the highlighted item.
PREV - scrolls to the previous item.
The individual menu items are explained in the following paragraphs.
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
NEXT
SEL
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!
Save Changes
Revert to Old Settings
NEXT
Screen appears
when exiting Setup
menu and changes
have been made
SEL
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
NEXT
SEL
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
NEXT
SEL
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
NEXT
SEL
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
NEXT
SEL
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
Ch. 1: Multi
Ch. 2: NoType
Ch. 3: GPS
Ch. 4: NoType
Ch. 5: NoType
EXIT
NEXT
Receiver menu shows
the 5 RX channels, the
429 source and the
speed. To change
individual channel,
highlight desired channel
and press SEL.
100 kHz
100 kHz
12.5 kHz
NoSpeed
NoSpeed
SEL
PREV
Please wait... will
be displayed while
autodetect is being
performed
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
NEXT
SEL
PREV
Figure 4-10: ARINC 429 Receiver Channel Menu
Selecting Type will cause the Equipment Type menu to appear:
BRT
OFF
Equipment Type
NoType
*BarAlt*
MagHdg
*GPS*
RadAlt
EXIT
NEXT
SEL
PREV
More than one source can be
selected for each 429 RX
channel. Each selected source
will have an asterisk's before
and after it. If more than one
source is selected the word
"Multi" will appear in the ARINC
429 Receivers menu.
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
NEXT
SEL
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:
BRT
OFF
Equipment
Browse All Avionics
GPS Nav
[Gama]
Magnetic Heading
[Synchro Compass]
Barometric Altitude
[Encoding Altimeter]
EXIT
NEXT
Using Next button to scroll
down will cause these
additional menu choices to
appear one at a time.
Radio Altitude
[None]
Landing Gear
[None]
Weight-On-Wheels
[Active Low]
Audio Suppression
[None]
External Display
[None]
SEL
PREV
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
Ch.2: Multi
100 kHz
Ch.3: NoType NoSpeed
Ch.4: NoType NoSpeed
Ch.5: NoType NoSpeed
EXIT
NEXT
This Menu appears when
ARINC 429 equipment has
been selected, but was not
assigned to a channel via
the Communication Ports Menu
SEL
PREV
Figure 4-14: No Channel Assigned Menu
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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
NEXT
SEL
PREV
Figure 4-15: GPS Nav Menu
The Heading menu provides the following choices:
BRT
OFF
Heading
*Synchro Compass*
Arinc 429
EXIT
NEXT
SEL
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
NEXT
SEL
PREV
Figure 4-17: Heading Valid Line Menu
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The Barometric Altitude menu provides the following choices:
BRT
OFF
Barometric Altitude
*Arinc 429*
Encoding Altimeter
EXIT
NEXT
SEL
PREV
Figure 4-18: Barometric Altitude Menu
The Radio Altimeter menu provides the following choices:
Radio Altimeter
BRT
OFF
*None*
Arinc429
Arinc 552
Arinc 552A
Bonzer Mark 10X
Collins ALT-50
Collins ALT-55
EXIT
NEXT
Using Next button to scroll
down will cause these
additional menu choices to
appear one at a time.
King KRA10/10A
King KRA 405
Sperry AA-100
Terra TRA 3000
SEL
PREV
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
NEXT
SEL
PREV
Figure 4-20: Radio Altimeter Valid Line Menu
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The Landing Gear menu provides the following choices:
BRT
OFF
Landing Gear
*None*
Active Low
Active High
EXIT
NEXT
SEL
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
NEXT
SEL
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
NEXT
SEL
PREV
Figure 4-23: Audio Suppression Menu
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The External Display menu is used to select display drivers and provides the following choices:
BRT
OFF
External Display
*None*
Standard Type1
Standard Type2
Standard Type3
Sextant Type1
Sextant Type2
Sextant CG
EXIT
NEXT
Using Next button to scroll
down will cause these
additional menu choices to
appear one at a time.
Forestry Serv
Standard Type4
Standard Type5
SEL
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).
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Table 4-1: Alternate Display Drivers
DISPLAY
RANGES
STANDBY
RANGE
SELF-TEST
RANGE
-
-
-
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.
2, 5, 10, 20 nmi
10 nmi
5 nmi
Designed for U.S. Forestry Service application.
DISPLAY DRIVER NAME
None
Forestry Serv
4.4.2
REMARKS
No alternate display connected.
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
NEXT
SEL
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.
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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.
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
ERROR CODE
Using NEXT button to scroll
down will cause additional
errors (up to 20) to appear.
20 000030:24
BarAlt Input Error
## hhhhhh:mm
## hhhhhh:mm
## hhhhhh:mm
## hhhhhh:mm
EXIT
NEXT
TIME OF ERROR
(hhhhhh:mm, Run-Time in hours and minutes.)
DESCRIPTION
OF ERROR
SEL
PREV
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
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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
SEL
EXIT
PREV
NEXT
Figure 4-28: Data Monitor Menu
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 count per channel will be shown. A large increasing number of
parity errors 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
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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 more than 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.
BRT
Data Monitor OFF
Baro Alt
(Encoding Altimeter)
Valid Altitude: 9000 ft
A4=1 (P58) C4=0 (P69)
A2=1 (P57) C2=1 (P68)
A1=0 (P56) C1=0 (P67)
B4=0 (P61) D4=0 (P71)
B2=1 (P60) D2=1 (P70)
B1=1 (P59))
EXIT
If Arinc 429 was selected
for Barometric Altitude
source in equipment
menu the following data
monitor will appear:
(Arinc 429)
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 discrete.
Figure 4-32: Discrete Values Data Monitor
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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).
BRT
OFF
If Arinc 429 was selected
for heading source in
equipment menu the
following data monitor
will appear:
Data Monitor
Mag Heading
(Synchro Compass)
Sense: Active Low
Validity: Valid
Heading: 29.8 degs
(Arinc 429)
Mag Heading: 29.9 degs
True Heading: 35.0 degs
Status: Valid
EXIT
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).
Data Monitor
Rad Alt
(Arinc 429)
If DC Analog Radio
Altimeter was selected in
equipment menu the
following data monitor
will appear:
Validity: Valid
Altitude: 4005 ft
(Bonzer Mark 10X)
EXIT
Sense: Active Low
Validity: Valid
Altitude: 39 ft
BRT
OFF
Figure 4-35: Radio Altitude Data Monitor
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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:
BRT
OFF
Calibration
The message SKY899
Antenna Calibration in
process... will be displayed
while calibration is being
performed.
Top Antenna
Bit Phase: 131.10 degs
Bottom Antenna
Bit Phase: Invalid
EXIT
NEXT
After a successful
calibration, the new Bit
Phase value will be
displayed.
SEL
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.
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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:
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.
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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:
BRT
OFF
Config Management
Archive to CF
Retrieve from CF
Restore Factory Defaults
Software Update
EXIT
NEXT
SEL
PREV
Figure 4-39: Configuration Management Menu
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J9
To insert the compact flash, perform the following
steps:
1. Remove power from the SKY899 system.
1
J10
J1
INTERCONNECT
J11
CAUTION
Removing or inserting the data card while
the TRC899 is powered on may result in
damage to the card.
2. At the TRC899 (see figure 4-40), open the
memory card door and insert compact flash into
J12 connector. Be sure to align the arrow on the
compact flash card with the arrow above the
memory card door.
TRC899
A
MODS
B C D
E
F
G
H
I
J
K
L
L-3 Avionics Systems, Inc.
Grand Rapids, Michigan USA
SW VERSION
1.0 1.1 1.2 1.3
P/N 805-11900-
1.4 1.5 1.6 1.7
Wt:
8.75 lbs.
3.97 kg.
S/N
1.8 1.9 2.0 2.1
J7
TEST
J8
POWER
J12
MEMORY CARD
Figure 4-40: Compact Flash Insertion Instructions
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Figure 4-41: Service Menu Tree (Sheet 1 of 3)
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Figure 4-41: Service Menu Tree (Sheet 2 of 3)
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Figure 4-41: Service Menu Tree (Sheet 3 of 3)
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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
an invalid BIT phase during the calibration procedure.
a. Verify antenna location and type was correctly set 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.
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)
Check cables connected to display.
Replace Display.
Display remains dark after SKY899 is powered ON.
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).
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)
SKY899 will not enter service menu.
The self-test successfully completes without audio
annunciation.
a. Check headphones/speaker and aircraft audio panel switch
settings.
b. Check volume level and run audio test in service menu.
c. Check cables connected to TRC.
Audio Alert Output:
P1-89 (AUDIO_H - 600-Ohm)
P1-90 (AUDIO_L - 150-Ohm)
P1-91 (AUDIO_C - Common)
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
WX-1000. Both systems are installed.
a. Check circuit breakers. Reset if tripped.
b. Check position of the WX-1000 maintenance switch (SW2).
It should be set to the NORMAL position.
c. Check wiring of the SKYWATCH/Stormscope display mode
switch (para 2.24.1 and figure 2-2).
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Table 4-2: Fault Isolation (Continued)
SYMPTOM
CORRECTIVE ACTION
WX-1000 processor has been removed for service;
SKY899 fails to operate.
Check position of the WX-1000 maintenance switch
(NORMAL/OVERRIDE). When the WX-1000 has been
removed for service, it should be set to the OVERRIDE
position. This switch may be located in the avionics bay.
SKY899 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 WX1000 Stormscope fails to operate.
Check the adapter plug (see para 4.7). If the TRC899 is
removed for service, an adapter plug is required to permit
continued operation of the WX-1000.
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
ERROR 10
ERROR 14
Config Module Error
Compact Flash Error
RF Amplitude Error
a.
Configuration module is not found check associated wiring.
b.
Replace configuration module.
c.
Replace TRC.
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.
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.
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Cycle power and run pilot initiated self-test.
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Table 4-3: Installation Related Error Messages (Continued)
ERROR NO.
MESSAGE
REMARKS
ERROR 15
RF Angle Error
a.
b.
ERROR 17
Mag Var Table Error
a.
c.
b.
c.
ERROR 20
Barometric Input Error
a.
b.
c.
d.
e.
f.
ERROR 23
Synchro Input Error
Check directional antenna and associated cables.
Calibrate directional antenna (para 4.4.3)
NOTE
Ensure transponder is in standby and DME is OFF while doing calibration
Cycle power and run pilot initiated self-test.
Unable to read the compact flash information correctly, verify compact flash is inserted
into J12 correctly.
Try a different compact flash.
Replace TRC.
Verify altimeter source is turned on, warmed up, and is selected correctly in service
menu.
Cycle power.
Ensure that barometric altitude input data is from only one source (Gilham code or
ARINC-429).
Encoded inputs can be checked from the barometric altimeter data monitor screen (para
4.4.2.3).
Using the service menu, verify barometric source configuration and altitude information
(para 4.4.2.3).
Check wiring associated with altimeter source.
Invalid synchro compass input (XYZ signals or 400 Hz reference).
a.
b.
c.
d.
Check heading source.
Using the service menu, verify heading setup in mag heading data monitor (para 4.4.2.3).
If the heading signals become valid, the system will recover automatically.
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 appears a.
b.
on WX-1000 display
c.
MSG
Heading Input Error
Verify GPS source is it turned on and locked onto satellites.
Using the service menu, verify configuration (speed and equipment type) is set correctly.
Check ARINC-429 wiring associated with GPS.
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.
b.
Degraded message appears
c.
on WX-1000 display
d.
Check heading source.
Using the service menu, verify heading setup in Mag Heading data monitor (para
4.4.2.3).
If the heading signals become valid, the system will recover automatically.
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
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4.7
TRC899/WX-1000 ADAPTER PLUG
An adapter plug can be used to by-pass SKY899 only if a WX-1000 Stormscope system is installed. The
adapter will permit continued operation of the WX-1000 if the TRC899 is removed for service. It can also
be used as a troubleshooting tool when attempting to isolate a problem to either or both systems.
The adapter plug mates with P1. It can be purchased from L-3 Avionics Systems (P/N 805-11910-001) or
fabricated locally from the details provided in figure 4-42.
ADAPTER PLUG CONNECTIONS
JUMPER PINS
PIN INSERT VIEW
FUNCTION
25
8
25
DPWR+15
9
26
DPWR-15
10
27
DSPLY_GND
11
28
HSYNC_+
12
29
HSYNC_-
13
30
VSYNC_+
22
41
VSYNC_-
16
35
VIDEO_+
17
36
VIDEO_-
18
37
SFTKEY1
19
38
SFTKEY2
20
39
SFTKEY3
21
40
SFTKEY4
35
16
46
56
67
77
8
86
1
94
2
3
7
100
15
93
24
55
34
45
76
85
66
ADAPTER PLUG JUMPER INSTALLATION
NOTE
®
APPLY LOCTITE TO THE INTERNAL THREADS
OF THE BACKSHELL PRIOR TO ASSEMBLY.
0.10
+0.07
-0.00
CRIMP PIN
JUMPER
#22 AWG WIRE
SHORTING CAP
BACKSHELL
GLENAIR #340HS002M23-2H12A
CONNECTOR
MIL # D38999/20FH35PB
Figure 4-42: Adapter Plug Assembly
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4.8
DISPOSITION OF FAILED ITEMS
Return defective components to your authorized L-3 Avionics Systems dealer or to:
L-3 Communications Avionics Systems, Inc.
Attn: Customer Service
5353 52nd Street, S.E.
Grand Rapids, MI USA 49512
If available, pack components in their original shipping container. If the original container is not
available, pack them as follows:
CAUTION
Do not use desiccant crystals when packaging electronic assemblies.
Since the assembly must be packed tightly, crystals in bag form cannot
be used. The use of loose crystals may cause unnecessary damage
resulting in a cleaning problem.
1. Ensure that nonconductive covers/caps are installed on the exposed terminals of cable connectors on
the display, TRC, and antenna.
2. The display and TRC contain electrostatic discharge sensitive (ESDS) parts and must be wrapped in
static protective materials.
3. Wrap with bubble pack. Secure bubble pack with reinforced tape.
4. Place assembly in a cardboard box.
5. Wrap any accessories in tissue and place in the box. Fill spaces with bubble pack.
6. Put a letter on top of bubble pack. The letter must contain:
• Your name, address, and telephone number.
• Purchase order number.
• Description of component including, when applicable, model and serial number.
• Date of purchase.
• A brief description of the difficulty.
• Type of display and radar altimeter.
• Copy of error log, if available.
7. Shut box and seal with reinforced tape.
8. Attach packing list to outside of box.
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Appendix A
SKY899 Interface
Signal Name & 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) /
Encoding Altimeter Input
These uncorrected barometric signals are Gilham code (or gray code)
inputs coming from an airdata computer or encoding altimeter (see
paragraph 2.11). These 11 lines may be connected in parallel with the
aircraft transponder. If the aircraft is equipped with selectable altitude
encoders, connect the altitude inputs so that SKY899 is always
connected to the selected encoder. (Reference ARINC 572-1.)
NOTES
1. Only one altimeter input source (gray code or ARINC-429, not both)
should be connected. The altimeter input should be from the same
source that is interfaced with the transponder or at least as accurate
as that source, i.e., ± 125 ft.
2. If the aircraft has switched encoders that use 28V RETURN or
AIRCRAFT GROUND as reference for encoder selection, then
ALT_COMMON (P1-72) should be left unconnected.
3. If altitude D2 is not used P1-70 should remain unconnected.
CONNECTION
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Connector-Pin
P1-56
P1-57
P1-58
P1-59
P1-60
P1-61
P1-67
P1-68
P1-69
P1-70
P1-71
P1-72
Signal Name
ALT_A1
ALT_A2
ALT_A4
ALT_B1
ALT_B2
ALT_B4
ALT_C1
ALT_C2
ALT_C4
ALT_D2
ALT_D4
ALT_COMN
Appendix A - Page A-1
September 20, 2007
SKY899
Installation Manual
SIGNAL
CHARACTERISTICS
Altitude (Gilham Code) /
Encoding Altimeter Input
(Continued)
CABLE
VOLTAGE
CURRENT
FREQUENCY
SOURCE Z
MAX CAPACITANCE
Antenna
J9
Top Directional SUM (SIGMA) Port (Blue)
CONNECTION
Signal Name
Connector
J9 - TNC
SUM
CABLE
Minimum 22 AWG wire for lengths up to 30 ft.
+30 V input max.
<1 mA sourced per line.
<100 Hz
>10 kΩ per line.
<20 pF per line.
Cable and connector attenuation must not
exceed 2.5 dB, VSWR 1.5:1 (without antenna
connected). Refer to paragraph 2.6.1.
Impedance: 50 Ω
Antenna
J10
Top Directional BIT PROBE Port (Black)
CONNECTION
Signal Name
Connector
J10 - BNC
BIT
CABLE
Cable and connector attenuation must not
exceed 6 dB, VSWR 1.5:1 (without antenna
connected). Refer to paragraph 2.6.1.
Impedance: 50 Ω
Antenna
J11
Top Directional DIFFERENCE (DELTA) Port (Red)
CONNECTION
Signal Name
Connector
J11 - TNC
DIFFERENCE
CABLE
Cable and connector attenuation must not
exceed 2.5 dB, VSWR 1.5:1 (without antenna
connected). Refer to paragraph 2.6.1.
Impedance: 50 Ω
Page A-2 - Appendix A
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SIGNAL
CHARACTERISTICS
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.
CONNECTION
009-11900-001
Revision D
Connector-Pin
P1-54
P1-55
P1-62
P1-63
P1-64
P1-65
P1-73
P1-74
P1-75
P1-76
P1-83
P1-84
P1-81
P1-82
P1-42
P1-43
P1-44
P1-45
P1-52
P1-53
Signal Name
A429RX1_A Ch. 1 line A
A429RX1_B Ch. 1 line B
A429RX2_A Ch. 2 Line A
A429RX2_B Ch. 2 Line B
A429RX3_A Ch. 3 Line A
A429RX3_B Ch. 3 Line B
A429RX4_A Ch. 4 Line A
A429RX4_B Ch. 4 Line B
A429RX5_A Ch. 5 Line A
A429RX5_B Ch. 5 Line B
A429RX7_A Ch. 7 Line A
A429RX7_B Ch. 7 Line B
A429RX8_A Ch. 8 Line A
A429RX8_B Ch. 8 Line B
A429TX1_A Ch. 1 Line A
A429TX1_BCh. 1 Line B
A429TX2_A Ch. 2 Line A
A429TX2_BCh. 2 Line B
A429TX3_A Ch. 3 Line A
A429TX3_BCh. 3 Line B
Appendix A - Page A-3
September 20, 2007
SKY899
Installation Manual
SIGNAL
CHARACTERISTICS
Audio (Alert) Output
(see paragraph 2.10)
This output is directly compatible with industry standard audio panels
NOTE
Audio output from the TRC is transformer isolated.
This output is disabled when a terrain warning alarm is detected (see
paragraph 2.7.1)
CONNECTION
CABLE
POWER
FREQUENCY
LOAD Z
Debug Port
Connector-Pin
Signal Name
P1-89
(AUDIO_H) - 600 Ω
P1-90
(AUDIO_L) - 150 Ω
P1-91
(AUDIO_C) Audio Common
Minimum 22 AWG twisted shielded pair cable
for lengths up to 30 ft.
40 mW into a 600 Ω load. Audio level is
adjustable via service menu.
0 - 3.0 kHz
Selectable 150 or 600 Ω
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 (no hardware flow control):
Baud Rate:
Data Bits:
Parity:
Stop Bits:
Flow Control:
CONNECTION
Extended Audio Switch
(Required to enable the
ViP™ Extended Audio
Callout feature)
Connector-Pin
J7-2
J7-3
J7-5
J7-7
J7-8
19,200
8
None
1
Xon/Xoff
Signal Name
DIAG_RX
DIAG_TX
DIAG_GND
CTS
RTS
An extended audio callout switch is required when interfacing to the extended
audio switch input P1-32 of the TRC899. Units with Mod D and software 1.8
or higher are ViP™ Extended Audio Callout capable. This switch allows the
pilot to turn on and off (mute) the range, relative altitude and relative bearing
callout from the aural TA’s. When the switch is in the “Normal” position the
standard phrase “Traffic, Traffic” is still annunciated.
Any SPST toggle switch (1/2 A @ 28 V dc) may be used.
CONNECTION
CABLE
VOLTAGE
Page A-4 - Appendix A
September 20, 2007
Connector-Pin
Signal Name
P1-32
EXT_AUDIO_SW
Minimum 22 AWG unshielded cable
Active:
Min:0.0 V dc
Max: 1.5 V dc
Inactive
Min:3.5 V dc (open)
Max: 5.0 V dc
(internal 10K pull-up resistor)
009-11900-001
Revision D
SKY899
Installation Manual
SIGNAL
CHARACTERISTICS
GPWS
(Audio Inhibit)
This input senses a terrain warning alarm and temporarily disables the
SKY899 audible alert messages until the warning clears (see paragraph
2.7.1).
The input can be either a constant flag signal or an alternating flag
output. The flag must be cleared for five (5) seconds before the TRC
accepts a "NO ALARM" condition and restores audible alerts. IF THE
AIRCRAFT IS NOT EQUIPPED WITH TERRAIN WARNING SYSTEM, LEAVE
THIS INPUT UNCONNECTED.
NOTE
If the aircraft is equipped with terrain warning system the
GPWS, EGPWS, or TAWS flag must be connected to the TRC.
CONNECTION
CABLE
VOLTAGE
CURRENT
GEAR
(Landing Gear Switch Input)
Connector-Pin
Signal Name
P1-34
(GPWS)
Minimum 22 AWG wire for lengths up to 30 ft.
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
<5 mA sourced.
This signal line is to be connected to the landing gear switch to sense the
position of the landing gear (fixed, up or down, see paragraph 2.7.2). The
state of the switch can be active low or active high in reference to aircraft
ground. The switch status can be fixed, active low or active high, this is
selected via service menu.
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
CABLE
Connector-Pin
Signal Name
P1-33
GEAR
Minimum 22 AWG wire for lengths up to 30 ft.
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
009-11900-001
Revision D
Appendix A - Page A-5
September 20, 2007
SKY899
Installation Manual
SIGNAL
CHARACTERISTICS
Heading Input
(XYZ Synchro)
These connections from the aircraft heading source (ARINC 407 & 407-1
Synchro System Manual) allow the unit to rotate the displayed data as
the aircraft turns. See Heading Flag in this appendix for flag input
specifications.
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
Heading Input
(XYZ Synchro)
(Continued)
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
Connector-Pin
Signal Name
CONNECTION
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.
Connector-Pin
Signal Name
CONNECTION
P1-51
HEADING_FLG
CABLE
See paragraph 2.6.4.
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
Page A-6 - Appendix A
September 20, 2007
CONNECTION
009-11900-001
Revision D
SKY899
Installation Manual
SIGNAL
CHARACTERISTICS
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
CABLE
VOLTAGE
CURRENT
FREQUENCY
LOAD Z
Lamp Outputs
(above and below)
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
See paragraph 2.6.7.
0-5 V dc
<100 mA
16.4 kHz
1 kΩ
External annunciators are required when using an alternate display that
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
CABLE
VOLTAGE
CURRENT
ON/OFF Power
(SW2)
Connector-Pin
Signal Name
P1-66
LP1OUT - (ABV)
P1-85
LP2OUT - (BLW)
Minimum 22 AWG wire for lengths up to 30 ft.
ON: 0 V dc or Ground
OFF: Maximum +32 V dc or open
Maximum current 300 mA.
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.
When a WX-1000 processor is connected to with a SKY899 a
maintenance over-ride switch is necessary to enable the SKY899 to be
powered-up if the WX-1000 processor has been removed for service.
During normal operation, with a WX-1000 processor installed, SW2
should remain in the WX-1000 position. Any general purpose DPDT
toggle switch can be used.
CONNECTION
CABLE
VOLTAGE
CURRENT
009-11900-001
Revision D
Connector-Pin
Signal Name
P1-4
ON/OFF
P1-5
ON/OFF_RET
Minimun 22 AWG.
Less than 0.7 V = ON; open = OFF.
<100 mA
Appendix A - Page A-7
September 20, 2007
SKY899
Installation Manual
SIGNAL
CHARACTERISTICS
Operational Mode Output
(optional)
Operational mode output can drive a lamp annunciating when the system
is in operational mode. Output is switched to ground when system is in
operation mode. The lamp requires a separate dc source (constant or
dimming circuit). If lamp voltage is an ac source then an isolation relay
must be used.
CONNECTION
CABLE
VOLTAGE
OFF:
CURRENT
Power Input (TRC)
18-32 V dc. A 5 A circuit breaker is required.
CONNECTION
CABLE
VOLTAGE
Radio Altimeter (Analog)
Connector-Pin
Signal Name
P1-31
OPER_MODE
Minimum 22 AWG wire for lengths up to 30 ft.
ON: 0 V dc or Ground
Maximum +32 V dc or open
Maximum current 300 mA.
Connector-Pin
Signal Name
P8-A
+28V
P8-B
+28V_RET
Use #16 AWG (min.) twisted shielded pair
cable (Beldon 83322, Alpha 2826/2, or
equivalent). Terminate shield to airframe at
sensor or power source.
18 to 32 V dc, 2.0 Amps (Maximum)
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
CABLE
VOLTAGE
LOAD Z
MAX CAPACITANCE
Page A-8 - Appendix A
September 20, 2007
Connector-Pin Signal Name
P1-6
RAD_ALT_IN_HI
P1-7
RAD_ALT_IN_LO
P1-14
RADIO_ALT_FLG
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.
0 to +35 V dc
>100 k Ohm
<20 pF per line.
009-11900-001
Revision D
SKY899
Installation Manual
SIGNAL
CHARACTERISTICS
Radio Altimeter (Analog)
(continued)
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
ALTITUDE RANGE
OUTPUT DC
VOLTAGE RANGE
ARINC
Characteristic 552
0 to 2500 ft
0 to +26.0944 V
ARINC
Characteristic 552A
0 to 2500 ft
ALTIMETER
Bonzer Mark 10X
Collins ALT-50
Collins ALT-55
+40 to 2500 ft
0 to 2000 ft
0 to 2500 ft
OUTPUT DC VOLTAGE
0 to +500 ft
20 mV/ft
+500 to +2500 ft
10 Ln 2.178 x ft
500
-20 to +480 ft
20 mV/ft + 0.4 V
+480 to +2500 ft
10 Ln 2.178 x (ft + 20)
500
+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
(+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
(+18 ±0.5 V Offscale)
+500 to +2500 ft
3 mV/ft + 10.4 V
+20 to +2500 ft
4 mV/ft
-20 to +500 ft
20 mV/ft + 0.4 V
+500 to +2500 ft
3 mV/ft + 10.4 V
+40 to +500 ft
6.2 mV/(ft - 40) + 0.198 V
+500 to +2500 ft
508 μV/(ft - 500) + 3.05 V
+40 to +2500 ft
2.5 mV/ft
0 to +26.1741 V
+0.8 to +21 V
King KRA10/10A
+20 to 2500 ft
(+19 ±2 V Offscale)
King KRA 405
(Aux. Output #1)
Sperry AA-100
Terra TRA 3000
0 to 2500 ft
0 to 2500 ft
+40 to 2500 ft
Radio Altimeter (Digital)
009-11900-001
Revision D
0 to +16.4 V
+0.198 to +4.066 V
+0.1 to +6.25 V
See ARINC-429 External Interface in paragraph A.2.
Appendix A - Page A-9
September 20, 2007
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
CABLE
VOLTAGE
CURRENT
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 softkey 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., WX1000/SKY497 connected to all soft-key inputs, GNS430 to soft-keys 2 &
4 and Collins EFIS to soft-keys 2, 3, & 4).
CONNECTION
CABLE
VOLTAGE
Page A-10 - Appendix A
September 20, 2007
Connector-Pin
Signal Name
P1-15
SMS
P1-23
SMS_RET
Minimum 22 AWG.
CLOSED (< 0.7 V dc) = Stormscope display mode
OPEN = SKYWATCH display mode.
<100 mA
Connector-Pin
P1-18
Signal Name
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
See paragraph 2.6.7
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
009-11900-001
Revision D
SKY899
Installation Manual
SIGNAL
CHARACTERISTICS
Squat Switch Input
(Weight-On-Wheels)
This signal line is to be connected to the squat switch to sense when the
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
P1-24
CABLE
VOLTAGE
Minimum 22 AWG wire for lengths up to 30 ft.
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
<5 mA sourced.
CURRENT
Suppression Bus I/O
Signal Name
SQUAT
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 reconfigure 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.
009-11900-001
Revision D
Appendix A - Page A-11
September 20, 2007
SKY899
Installation Manual
SIGNAL
CHARACTERISTICS
System Configuration
Module (Continued)
CONNECTION
Connector-Pin
CABLE
P1-2
3.3V
P1-92
PLUG_GND
P1-99
SDA
P1-100
SCL
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
CABLE
VOLTAGE
FREQUENCY
SOURCE Z
Video Output
Signal Name
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
See paragraph 2.6.7
0-5 V dc
60 Hz
1 kΩ
Balanced video from the WX-1000 Processor (if installed) and output to
the display. Signal levels as specified in RS-422 specification.
CONNECTION
CABLE
VOLTAGE
CURRENT
FREQUENCY
LOAD Z
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
See paragraph 2.6.7
0-5 V dc
<100 mA
<15 MHz
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
CABLE
VOLTAGE
CURRENT
Page A-12 - Appendix A
September 20, 2007
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
See paragraph 2.6.7
+15/-15 V dc
0.7 A input max.
009-11900-001
Revision D
SKY899
Installation Manual
SIGNAL
CHARACTERISTICS
Future Options
The following connections are reserved for future use. THESE PINS
MUST REMAIN UNCONNECTED.
CONNECTION
009-11900-001
Revision D
Connector-Pin
P1-1
P1-3
P1-32
P1-77
P1-78
P1-79
P1-80
P1-86
P1-87
P1-88
P1-83
P1-84
P1-81
P1-82
P1-44
P1-45
P1-52
P1-53
Signal Name
+5 V
-15 V
DI02
RS422_TXA
RS422_TXB
RS422_RXA
RS422_RXB
RS232_TX2
RS232_RX2
RX232_GND2
A429RX7_A
A429RX7_B
A429RX8_A
A429RX8_B
A429TX2_A
A429TX2_B
A429TX3_A
A429TX3_B
Appendix A - Page A-13
September 20, 2007
SKY899
Installation Manual
This page intentionally left blank.
Page A-14 - Appendix A
September 20, 2007
009-11900-001
Revision D
SKY899
Installation Manual
TRC899
SIGNAL NAME
TRC497
PIN
PIN
P1-01
P1-02
P1-03
P1-04
P1-05
P1-06
P1-07
P1-08
P1-09
P1-10
P1-11
P1-12
P1-13
P1-14
P1-15
P1-16
P1-17
------------P1-11
P1-03
--------P1-07
P1-06
P1-14
P1-49
P1-48
P1-63
----P1-31
P1-38
P1-37
SFTKEY1_IN
P1-18
P1-85
SFTKEY2_IN
P1-19
SFTKEY3_IN
P1-20
+5V
3.3V
-15V
ON/OFF
ON/OFF_RET
RAD_ALT_IN_HI
RAD_ALT_IN_LO
DPWR+15_OUT
DPWR-15_OUT
DSPLY_GND_OUT
HSYNC_OUT+
HSYNC_OUTVSYNC_OUT+
RADIO_ALT_FLG
SMS
VIDEO_OUT+
VIDEO_OUT-
SFTKEY4_IN
P1-21
TRC899
TRC497
SIGNAL NAME
SIGNAL NAME
PIN
PIN
------------PW_SW_HI
PW_SW_LO
--------DPWR+15_OUT
DPWR-15_OUT
DSPLY_GND
HSYNC_OUT_HI
HSYNC_OUT_LO
VSYNC_OUT_HI
----CWS_SS
VIDEO_OUT_HI
VIDEO_OUT_LO
HEADING_FLG
A429TX3_A
A429TX3_B
A429RX1_A
A429RX1_B
ALT_A1
ALT_A2
ALT_A4
ALT_B1
ALT_B2
ALT_B4
A429RX2_A
A429RX2_B
A429RX3_A
A429RX3_B
LP1OUT
ALT_C1
P1-51
P1-52
P1-53
P1-54
P1-55
P1-56
P1-57
P1-58
P1-59
P1-60
P1-61
P1-62
P1-63
P1-64
P1-65
P1-66
P1-67
P1-53
--------P1-45
P1-44
P1-40
P1-41
P1-50
P1-51
P1-56
P1-57
P1-43
P1-42
------------P1-58
HDG_FLG+
--------ARINC-429 RX 1A
ARINC-429 RX 1B
ALT_A1
ALT_A2
ALT_A4
ALT_B1
ALT_B2
ALT_B4
ARINC-429 RX 2A
ARINC-429 RX 2B
------------ALT_C1
SFTKEY1_IN
ALT_C2
P1-68
P1-59
ALT_C2
P1-84
SFTKEY2_IN
ALT_C4
P1-69
P1-71
ALT_C4
P1-83
SFTKEY3_IN
ALT_D2
P1-70
-----
P1-82
SFTKEY4_IN
ALT_D4
P1-71
P1-72
SIGNAL NAME
PIN INSERT VIEW
25
46
67
HEADING_X
ALT_C1
36
VIDEO_OUT+
P1-22
P1-23
P1-24
P1-25
P1-26
P1-27
P1-28
P1-29
P1-30
P1-31
P1-32
P1-33
P1-34
P1-35
P1-36
P1-62
P1-04
P1-88
P1-24
P1-05
P1-15
P1-47
P1-46
P1-61
----P1-86
P1-87
P1-32
P1-36
P1-35
VSYNC_OUT_LO
SW_RET
SQUAT
DPWR+15_IN
DPWR-15_IN
DSPLY_GND
HSYNC_IN_HI
HSYNC_IN_LO
VSYNC_IN_HI
----EXT_AUDIO_SW
GEAR
GPWS
VIDEO_IN_HI
VIDEO_IN_LO
ALT_COMN
A429RX4_A
A429RX4_B
A429RX5_A
A429RX5_B
RS422_TXA
RS422_TXB
RS422_RXA
RS422_RXB
A429RX8_A
A429RX8_B
A429RX7_A
A429RX7_B
LP2OUT
RS232_TX2
P1-72
P1-73
P1-74
P1-75
P1-76
P1-77
P1-78
P1-79
P1-80
P1-81
P1-82
P1-83
P1-84
P1-85
P1-86
P1-81
---------------------------------------------------------
ALT_COMN
---------------------------------------------------------
SFTKEY1_OUT
P1-37
P1-76
SFTKEY1_OUT
RS232_RX2
P1-87
-----
-----
SFTKEY2_OUT
P1-38
P1-75
SFTKEY2_OUT
RS232_GND2
P1-88
-----
-----
SFTKEY3_OUT
P1-39
P1-74
SFTKEY3_OUT
AUDIO_H
P1-89
P1-92
68
86
DPWR+15_OUT
DPWR-15_IN
HEADING_Y
ALT_C2
RS232_TX2
37
9
+5V
DPWR-15_OUT
VSYNC_INA429TX1_A
A429TX1_B
A429TX2_A
A429TX2_B
HEADING_X
HEADING_Y
HEADING_Z
HEADING_H
HEADING_C
P1-40
P1-73
SFTKEY4_OUT
SFTKEY1_OUT
38
28
DSPLY_GND_OUT
P1-41
P1-42
P1-43
P1-44
P1-45
P1-46
P1-47
P1-48
P1-49
P1-50
P1-60
P1-34
P1-33
--------P1-66
P1-65
P1-64
P1-55
P1-54
VSYNC_IN_LO
ARINC-429 TX 1A
ARINC-429 TX 1B
--------SYNC_X
SYNC_Y
SYNC_Z
SYNC_H
SYNC_C
P1-90
P1-91
AUDIO_L
AUDIO_C
PLUG_GND
SUPBUS
ASU_SEL
ASU_MODE
ASU_SEL_ACK
ASU_MOD_ACK
ASU_GND
SDA
SCL
P1-91
P1-92
P1-93
P1-94
P1-95
P1-96
P1-97
P1-98
P1-99
P1-100
P1-90
----P1-89
-----------------------------
AUDIO_C
----SUP_BUS
-----------------------------
ASU_SEL
95
ASU_MODE
RS232_GND2
80
RS422_RXB
ALT_B2
50
71
96
89
ASU_SEL_ACK
-15V
HSYNC_OUT+
AUDIO_H
ALT_D4
HEADING_C
HSYNC_IN-
4
20
40
61
81
97
ON/OFF
SFTKEY3_IN
SFTKEY4_OUT
ALT_B4
A429RX8_A
ASU_MOD_ACK
12
30
51
72
90
HSYNC_OUT-
VSYNC_IN+
HEADING_FLG
ALT_COMN
AUDIO_L
5
98
ON/OFF_RET
41
21
13
RAD_ALT_IN_HI VSYNC_OUT+
7
A429RX8_B
A429RX2_A
31
52
73
91
99
OPER_MODE
A429TX3_A
A429RX4_A
AUDIO_C
SDA
92
100
PLUG_GND
SCL
22
42
63
83
A429TX1_A
A429RX2_B
A429RX7_A
32
14
53
43
33
SMS
84
75
65
A429TX2_A
SUPBUS
85
A429RX3_B
55
GPWS
93
A429RX5_A
A429RX1_A
44
34
A429RX7_B
A429RX3_A
54
GEAR
SQUAT
A429RX4_B
64
A429TX1_B
SMS_RET
74
A429TX3_B
EXT_AUDIO_SW
23
15
ASU_GND
82
VSYNC_OUT-
RAD_ALT_IN_LO RADIO_ALT_FLG
Appendix A - Signal & Cable Characteristics
62
VSYNC_IN-
SFTKEY4_IN
6
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
KEYING ARRANGEMENTS.
009-11900-001
Revision D
RS232_RX2
88
ALT_D2
60
SFTKEY3_OUT
94
RS422_RXA
70
HEADING_H
29
87
79
ALT_B1
39
SFTKEY2_IN
ALT_C4
49
HSYNC_IN+
11
RS422_TXB
69
59
SFTKEY2_OUT
SFTKEY1_IN
3
ALT_A4
HEADING_Z
DSPLY_GND_IN
10
78
48
18
AUDIO_H
AUDIO_L
58
27
24
SFTKEY4_OUT
RS422_TXA
47
19
VSYNC_OUTSMS_RET
SQUAT
DPWR+15_IN
DPWR-15_IN
DSPLY_GND_IN
HSYNC_IN+
HSYNC_INVSYNC_IN+
OPER_MODE
EXT_AUDIO_SW
GEAR
GPWS
VIDEO_IN+
VIDEO_IN-
ALT_A2
VIDEO_IN-
VIDEO_OUT-
ALT_D4
77
26
1
3.3V
57
8
17
2
56
ALT_A1
DPWR+15_IN
16
-----
35
VIDEO_IN+
LP2OUT
76
A429RX1_B
A429RX5_B
45
66
A429TX2_B
LP1OUT
Figure A-1. P1 Connector Pin Identifiers
Page A-15 (A-16 blank)
September 20, 2007
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
Air Data Computer
GPS (GAMA)
GPS (GNSS - ARINC 743A)
Attitude & Heading Reference System
Radio Altimeter
Data
Altitude
Label
203*
Baro Corrected Altitude #1
204
Altitude Rate
212
Air Temperature
213
Altitude Rate
232
General Aviation Equipment ID
371
Equipment ID
377
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 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
Magnetic Heading
014
True Heading
314**
Magnetic Heading
320**
General Aviation Equipment ID
371
Equipment ID
377
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.
009-11900-001
Revision D
Appendix A - Page A-17
September 20, 2007
SKY899
Installation Manual
Table A-3: ARINC-429 Output Labels (Tx)
Equipment
Data
External Display
DITS Control
013
ARINC-735 TCAS I Formatted Traffic Data
Altitude Select Limits
015
DITS Control
016
Page A-18 - Appendix A
September 20, 2007
Label
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
009-11900-001
Revision D
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 SKY899 ENVIRONMENTAL QUALIFICATION FORM (FIXED WING: DO-160D)
(Reference Document 016-11933-001, Rev. G)
MODEL: TRC899 TSO NO:
PART NO: 805-11900-001
MANUFACTURER:
ADDRESS:
TSO-C147, Class A. and TSO-C118
APPLICABLE SPEC NO: RTCA/DO-197A
Goodrich Avionics Systems, Inc.
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
CONDITION
Temperature and Altitude
Low Temperature
High Temperature
Loss of Cooling
Altitude
Decompression
Overpressure
Temperature Variation
Humidity
Operational Shock and Crash Safety
Vibration
SECTIONPARAGRAPH
4.0
4.5.1
4.5.2 & 4.5.3
4.5.4
4.6.1
4.6.2
4.6.3
5.0
6.0
7.0
8.0
Explosion Proofness
9.0
Waterproofness
10.0
Fluids Susceptibility
11.0
Sand and Dust
12.0
Fungus Resistance
13.0
009-11900-001
Revision D
TEST CATEGORY
Equipment tested to Category F2
-55° Celsius
+70° Celsius
Category X-No test performed
55,000 ft. MSL
Not Applicable
Not Applicable
Equipment tested to Category B
Equipment tested to Category A
Equipment tested to Category B
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.
Equipment identified as Category X - No test
performed
Equipment identified as Category X - No test
performed
Equipment identified as Category X - No test
performed
Equipment identified as Category X - No test
performed
Equipment identified as Category X - No test
performed
Appendix B - Page B-1
September 20, 2007
SKY899
Installation Manual
CONDITION
Salt Spray
SECTIONPARAGRAPH
14.0
Magnetic Effect
Power Input
Voltage Spike
Audio Frequency Susceptibility
Induced Signal Susceptibility
Radio Frequency Susceptibility
Radio Frequency Emission
Lightning Induced Transient
Susceptibility
Lightning Direct Effects
15.0
16.0
17.0
18.0
19.0
20.0
21.0
22.0
Icing
24.0
Electrostatic Discharge
Other Tests
25.0
23.0
TEST CATEGORY
Equipment identified as Category X - No test
performed
Equipment to meet Class Z
Equipment tested to Category B
Equipment tested to Category A
Equipment tested to Category B
Equipment tested to Category A
Equipment tested to Category RR
Equipment tested to Category L
Equipment identified as Category XXXX - No
test performed
Equipment identified as Category X - No test
performed
Equipment identified as Category X - No test
performed
Equipment tested to Category A
No test required
B.2 NY156 & NY164 ANTENNA ENVIRONMENTAL QUALIFICATION FORM
NOMENCLATURE: SKYWATCH®
MODEL: NY156 & NY164
PART NO.: 805-10003-001 & 805-10890-001
APPLICABLE SPEC. NO.: RTCA/DO-160C
TSO NO.: TSO-C118
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
High Temperature
In-Flight Loss of Cooling
Altitude
Decompression
Overpressure
4.5.1
4.5.2 & 4.5.3
4.5.4
4.6.1
4.6.2
4.6.3
-55 Degrees Celsius
+70 Degrees Celsius
- Not Applicable 55,000 Feet
- Not Applicable - 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.
Page B-2 - Appendix B
September 20, 2007
009-11900-001
Revision D
SKY899
Installation Manual
NY156 & NY164 Antenna Environmental Qualification Form (continued)
CONDITIONS
SECTION
TEST DESCRIPTION
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
Susceptibility
22.0
Equipment tested to Category L.
Lightning Direct Effects
23.0
Equipment tested to Category 2A.
Icing
24.0
Category X - No test performed.
Other Tests
009-11900-001
Revision D
No test required
Appendix B - Page B-3
September 20, 2007
SKY899
Installation Manual
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: BFGoodrich Avionics Systems, Inc.
ADDRESS: 5353 52nd Street SE, Grand Rapids, MI 49512
(616) 949-6600
Revision & Change Number of DO-160: DO-160C
SECTION/
CONDITION
PARAGRAPH
Temperature and Altitude
4.0
Operating Low Temperature
4.5.1
Operating High Temperature
4.5.3
Short-Time Operating High Temp.
4.5.2
Loss of Cooling
4.5.4
Ground Survival Low Temp.
4.5.1
Ground Survival High Temp.
4.5.2
Altitude
Temperature Variation
TEST DESCRIPTION
Tested to Category F1-20° Celsius
+55° Celsius
+70° Celsius
-Not Applicable-55° Celsius
+85° Celsius
4.6.1
5.0
55,000 Feet MSL
Tested to Category C
Humidity
6.0
Tested to Category A
Operational Shock and Crash Safety
Operational Shock
Crash Safety
Vibration
7.0
7.2
7.3
8.0
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
Page B-4 - Appendix B
September 20, 2007
6 g's Peak
15 g's all axes
Tested to Categories [NBM] Instrument Panel
Mount Without Vibration Isolators
009-11900-001
Revision D
SKY899
Installation Manual
WX-1000/SKY497 Display Environmental Qualification Form (continued)
CONDITION
Radio Frequency Emission
SECTION/
PARAGRAPH
21.0
TEST DESCRIPTION
Tested to Category A
Lightning Induced Transient
Susceptibility
22.0
Category X - No test required
Lightning Direct Effects
23.0
Category X - No test required
Icing
24.0
Category X - No test required
Other Tests
X-Ray Radiation
Other Tests
U.V. Radiation
Other Tests
Thermal Shock
009-11900-001
Revision D
Appendix B - Page B-5
September 20, 2007
SKY899
Installation Manual
This page intentionally left blank.
Page B-6 - Appendix B
September 20, 2007
009-11900-001
Revision D
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
Switch
1, 2, 3, & 4
Pushbuttons
009-11900-001
Revision D
Power is applied by rotating the knob clockwise past the detent. Continued clockwise
rotation increases display brightness.
Also referred to as soft-keys (1), (2), (3), and (4). In every operating mode a label
identifying the button function will be displayed next to the button.
Appendix C - Page C-1
September 20, 2007
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
SETUP #1
INTRUDER TYPE:
UUT DIST: HORIZ =
UUT DIST; VERT =
ALT REPORTING:
STORE
RECALL
GAIN_1030
LOSS
STORAGE NUMBER 1
ATCRBS
Distance (ft.) from aircraft
Vertical height (ft.) difference between test
antenna and SKY899 antenna
ON
0
0
9.4 dB
1.3 dB
SETUP #2
RANGE MAX:
RANGE MIN:
ALT MAX:
ALT MIN:
35 NM (was 20 NM for Sky497)
0 NM
60,000 ft
0 ft
SCENARIO TEST
RANGE:
RANGE RATE:
ALT:
ALT: RATE:
5.0 NM
+200 kt
51,000 ft
0 FPM
REPLY TEST
RANGE:
ALTITUDE
%REPLY:
5.0 NM
50,500 ft
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.
Page C-2 - Appendix C
September 20, 2007
009-11900-001
Revision D
SKY899
Installation Manual
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
TEST
OPR
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.
009-11900-001
Revision D
Appendix C - Page C-3
September 20, 2007
SKY899
Installation Manual
8. Return to the Service Menu (paragraph 4.4) and select Information.
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 extended audio switch, 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").
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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).
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
Switch
Power is applied by rotating the knob clockwise past the detent. Continued clockwise
rotation increases display brightness.
1, 2, 3, & 4
Pushbuttons
Also referred to as soft-keys (1), (2), (3), and (4). In every operating mode a label
identifying the button function will be displayed next to the button.
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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 frontpanel 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.
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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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 extended audio switch, 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 Softkey (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.
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d. Move the T-49C to each test point and verify that the display shows the corresponding bearing
displacement.
NOTE
It is necessary to wait a few seconds after moving to let the test target
stabilize in position.
21. This completes testing with the T-49C, reattach top lid of the T-49C.
22. If installed, TURN ON the radio altimeter.
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 9-pin serial cable (pin-to-pin) 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 software flow
control being used (no hardware control).
Baud Rate:
Data Bits:
Parity:
Stop Bits:
Flow Control:
19200
8
None
1
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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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
head
gps
cal
//
del
hello
restart
track
rad
say
ground
attrib
delay
help
time
mbite
discretes
volume
adsb
comflash
dir
menu
type
mxmit
bar
mrep
dump
copy
echo
ren
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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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.
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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.)
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. 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 L-3 Avionics Systems SKYWATCH HP
Copyright (c) 2003 L-3 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):
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a.
Change the status of the extended audio switch, 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).
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).
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NOTE
The Patch Antenna may be used without a tripod. The Patch Antenna can
be held, or secured, and pointed towards the SKYWATCH HP aircraft
under test WITH THE MOUNTING STUD POINT TOWARD THE GROUND. This
orientation is critical.
b.
Mount the chassis lid, with the Patch Antenna facing the aircraft, onto a tripod (not included).
The tripod must be capable of holding the antenna (approximately 2.5 lb.) and must provide a
standard base mounting stud threaded 1/4"-20. A typical tripod mount is shown in figure F-3.
c.
If the internal batteries are being utilized, proceed to sub-step f. If the Flightline Tester AC
Converter Power Supply is to be utilized, proceed to sub-step d.
d.
Connect the AC Converter Power Supply cable connector to the chassis external connector.
e.
Connect the AC Converter Power Supply input power cable connector to one of the following
AC sources:
•
115 V ac, 60 Hz
•
115 V ac, 400 Hz
Set the Flightline Tester POWER switch to the ON position.
f.
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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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.
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.
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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.
c.
If installed, power up the radio altimeter.
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.
c.
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.)
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.
Page F-6 - Appendix F
September 20, 2007
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Revision D
SKY899
Installation Manual
Appendix G
®
SKYWATCH HP SKY899
Permission to use STC SA01552CH-D for
Raytheon C90
Consistent with FAA Order 8110.4C and AC21-40, L-3 Communications Avionics Systems, Inc.
(hereafter L-3 Avionics Systems) grants permission to L-3 Avionics Systems dealers, installers, and
owners of the SKYWATCH® HP SKY899 Traffic Avoidance System and associated equipment to use
this STC and the data associated with it, for the sole purpose of installation and approval of the
SKYWATCH® HP SKY899 System on the aircraft associated with the listed STC. Figure G-1 is a copy
of the STC cover page.
For additional assistance or information call L-3 Avionics Systems, Customer Service (800-453-0288 or
616-949-6600).
009-11900-001
Revision D
Appendix G - Page G-1
September 20, 2007
SKY899
Installation Manual
Figure G-1: STC SA01552CH-D Cover Sheet
Page G-2 - Appendix G
September 20, 2007
009-11900-001
Revision D
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