L 3 Communications Avionics Systems TRC497 SkyWatch Traffic Advisory System User Manual COVER

L-3 Communications, Avionics Systems SkyWatch Traffic Advisory System COVER

Install Manual part 3 of 3

SKY497Installation Manual4-1Rev. CCHAPTER 4MAINTENANCE4.1 INTRODUCTIONThis chapter contains general flight-line maintenance and troubleshooting procedures for installationsinterfaced to WX-1000/SKY497 display or an alternate display. Removal of components is on condition offailure. 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 becalibrated to the directional antenna (refer to paragraph 4.4.1).4.2 CONTINUED AIRWORTHINESSNo scheduled maintenance is required to ensure continued airworthiness.4.3 PERIODIC MAINTENANCEAt regular inspection intervals, do the periodic maintenance procedures of paragraph 4.3.1 thru 4.3.3.4.3.1 WX-1000/SKY497 Display1. Check that indicator cable is properly mated and secured.2. Check to ensure unit is properly placed and secured to the instrument panel.CAUTIONDo 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. Ifnecessary, clean with a soft cloth moistened with a mild solution of soap and water. Take care toprevent cleaning solution from running down inside the case.4.3.2 TRC1. 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 Antenna1. Check for dents, cracks, and punctures.CAUTIONDo 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 andwater.3. Visually inspect sealant around the antenna base. Reapply sealant if required.
SKY497Installation Manual4-2Rev. C4.4 SERVICE MENUThe Service Menu is intended as an aid in installing, testing and troubleshooting the SKY497. ServiceMenu items are to be used only for testing and troubleshooting an installation. The Service Menu is notintended to be used by the pilot during normal system operation. When interfaced to an alternate displaythe service menu functions must be performed by using an RS-232 terminal device, see appendix D foroperating instructions.The Service Menu is accessed by holding soft-keys (1) and (2) (the left two buttons) depressed as thesystem is turned on. Hold the buttons until the Service Menu is displayed. The Service Menu is shown infigure 4-1.Figure 4-1. Service MenuThe buttons perform the following operations:• EXIT - causes the system to exit the Service Menu and run the power on self-test.• SELECT - selects the highlighted item.• PREV - steps to the previous item.• NEXT - steps to the next item.The Service Menu provides the following choices:• Calibration• System Log• System Data• Ground Test (Available only if squat switch input indicates aircraft is on the ground.)The individual menu items are explained in the following paragraphs.NOTEService Menu screens are shown for documentation purposes only. Each systemmay be configured differently and live data will correspond to the sensorsinstalled in a particular aircraft..
SKY497Installation Manual4-3Rev. C4.4.1 CalibrationNOTEEnsure 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 by selecting that optionfrom the Service Menu (i.e., press SELECT with Calibration high-lighted). The initial calibration screen(see figure 4-2) shows the current calibration value in degrees. Calibration can be performed with theterminal device by using the Cal command.NOTEIf the TRC has never been calibrated, the current calibration value will be displayed as 999. Figure 4-2. Calibration ScreenPress YES to calibrate; press NO to return to the Service Menu. Soft-keys (3) and (4) are not used. Duringthe calibration procedure, the message “Re-Calibrating . . . ” will be displayed.After a successful calibration, both old and new calibration values will be displayed (as shown infigure 4-3). Press EXIT to return to the Service menu. Soft-keys (2), (3), and (4) are not used.Figure 4-3. Successful Re-Calibration
SKY497Installation Manual4-4Rev. CThe calibration value (000-359) is derived from a variety of measurements. Specific values are meaninglesshowever, in a failed TRC, a varying spread may indicate problems with the directional antenna system(antenna, cables, or connectors) or the TRC.If the calibration failed, the message “Re-calibration Failed!” will be display (see figure 4-4).Figure 4-4. Failed CalibrationPress YES to calibrate; press NO to return to the Service Menu. Soft-keys (3) and (4) are not used.4.4.2 System LogThe 20 most recent errors detected by the system self-test are saved in the System Log. For each error, thecorresponding error code and run-time of occurrence are saved. The system log, as shown in figure 4-5, isdisplayed by selecting that option from the Service Menu (i.e., press SELECT with System Log high-lighted). System Log can be accessed with a terminal device by using the Dump command.NOTETables 4-2 and 4-3 provide a list and description of each error code (see paragraph 4.6).Figure 4-5. System Log
SKY497Installation Manual4-5Rev. CThe System Log displays the results in the following format:### HHHHH:MMwhere:### = Error code.HHHHH:MM = Run-time (in hours and minutes) at which error occurred.The total elapsed run-time is displayed in the upper middle portion of the screen (System TimeHHHHH:MM).A textual description of the highlighted error entry is displayed in the bottom portion of the screen.If the System Log is empty, the following message is displayed:NO FAULTS DETECTEDIf, due to a failure of non-volatile memory, the System Log cannot be displayed, the following message isdisplayed:DATA NOT AVAILABLEThe buttons perform the following operations:• EXIT - causes the system to return the Service Menu.• NEXT - steps to the next entry.• PREV - steps to the previous entry.• Soft-key (4) is not used.4.4.3 System DataSystem Data screens (see figures 4-6 through 4-16) contain a record of setup information (softwareidentification and jumper configuration) and real-time sensor data. If you have problems with the SKY497,verify the configuration screens match the wiring diagrams (see figures 2-2 and 2-3) and have thisinformation available when contacting BFGoodrich Avionics Systems Field Service Engineering. The fieldservice engineer must have adequate information to diagnose a problem. System Data screens are accessedby selecting that option from the Service Menu (i.e., press SELECT with System Data high-lighted).The System Data screen provides the following choices:• Software Version• Configuration• Data MonitorFigure 4-6. System Data
SKY497Installation Manual4-6Rev. CThe buttons perform the following operations:• EXIT - returns to the Service Menu (figure 4-1).• SELECT - selects the highlighted item.• PREV - steps to the previous item.• NEXT - steps to the next item.4.4.3.1 Software Version. The software version screen (see figure 4-7) identifies:• IOP Code Version• IOP Boot Version• STP Code Version• STP Boot VersionSoftware version can be accessed with a terminal device by using the Version command.Figure 4-7. Software VersionNOTEThe software version identified on the TRC equipment tag represents the system softwareconfiguration (i.e., a collective designator for all software/firmware installed within theunit).Press EXIT to return to the System Data screen. Soft-keys (2), (3) and (4) are not used.4.4.3.2 Configuration. The configuration display consists of 4 pages. Configuration data on pages 1, 3 and 4must be verified and saved on all new installations or if changes in configuration jumper(s) occur. Thebuttons perform the following operations:• EXIT - returns to the System Data Menu (figure 4-6).• NEXT - steps to the next page.• PREV - steps to the previous page.• SAVE - saves configuration data for that page (not present if configuration jumpers match configuration memory).Configuration information can also be accessed with a terminal device by using the Config command.
SKY497Installation Manual4-7Rev. CNOTES1. Saved configuration data is read at power-up and compared withconfiguration jumpers. If the saved configuration data has never beensaved (e.g., new installations) an ERROR 30 Check Configuration willoccur when the box comes out of standby. If the saved configuration datadoes not match the current jumper(s) an error 30 will occur at power-up.The conflicting jumper(s) will be highlighted on configuration screen(s).(See figure 4-8.)2. Configuration pages 1, 3 and 4 contain configuration jumper data. Oneach page verify jumpers are correct and press SAVE to write the newconfiguration into system memory. When done the SAVE buttondisappears. Repeat this step for each page. Save command can be used ifusing a terminal device.Figure 4-8. Configuration - Page 1Page 1 of 4 (see figure 4-8) displays:• Heading Input Source (Hdg.: XYZ, STEP, 429, or NONE)Configuration Jumpers P1-69 & P1-70 (OPEN or GND)P1-69 P1-70None OPEN OPENSynchro XYZ OPEN GND Stepper GND OPENARINC 429 Bus GND GND• Heading Flag Sense (HIGH or LOW)Configuration Jumper P1-68 (OPEN or GND)P1-68OPEN If LOW level input on HDG_FLG+ (P1-53) indicatesvalid heading or no valid heading input is available.GND If HIGH level input on HDG_FLG+ (P1-53) indicatesvalid heading.• RS422 Interface (DR/Alt. 422: DR or 422)Configuration Jumper P1-67 (OPEN or GND)P1-67Data Recorder OPENAlternate* GND*Future Option
SKY497Installation Manual4-8Rev. CNOTEThe RS422 Interface is used for factory testing and evaluation.Figure 4-9. Configuration - Page 2Page 2 of 4 (see figure 4-9) displays:• Barometric Encoded Altitude (in Gray Code and Feet)• Connector P1 Pin Assignments for Data InputsFigure 4-10. Configuration - Page 3WARNINGVerify displayed antenna position matches antenna location on the aircraft(top or bottom). Failure to do so could give incorrect traffic bearing.
SKY497Installation Manual4-9Rev. CPage 3 of 4 (see figure 4-10) displays:• Antenna Position (Ant. Pos.: TOP or BOT)Configuration Jumper P1-100 (OPEN or GND)P1-100Top OPENBottom* GND*See paragraph 2.3 (ANTENNA LOCATION)• Antenna Type (NY164 or NY156)Configuration Jumper P1-99 (OPEN or GND)P1-99NY164 OPENNY156 GND• Airframe (Ant. Pos.: FIX or ROT)Configuration Jumper P1-98 (OPEN or GND)P1-98Fixed Wing OPENRotorcraft GNDFigure 4-11. Configuration - Page 4Page 4 of 4 (see figure 4-11) displays:• Alternate Display Type (None Selected, ARINC 735 Type 1, or Illegal Display)Configuration Jumpers P1-77, P1-78, P1-79 & P1-80 (OPEN or GND)P1-77 P1-78 P1-79 P1-80None OPEN OPEN OPEN OPEN 735 Type 1 OPEN OPEN OPEN GND4.4.3.3 Data Monitor. The data monitor display consists of 5 pages. The buttons perform the followingoperations:• EXIT - returns to the System Data Menu (figure 4-6).• NEXT - steps to the next page.• PREV - steps to the previous page.• Soft-key (4) is not used.The data monitor information can be accessed with a terminal device by using the Bar, Head, Rad andConfig commands.
SKY497Installation Manual4-10Rev. CFigure 4-12. Data Monitor - Page 1NOTEValues displayed on the Data Monitor are continuously updated. The sensorsource (e.g., ARINC 429, Synchro XYZ, etc.) is latched at power-up. If it isnecessary to change a configuration, cycle power to ensure the correctinformation is read into memory.Page 1 of 5 (see figure 4-12) displays:• Barometric AltitudeSource (Encoded Inputs, ARINC 429, or Simulated)Altitude (in Feet)• Heading DataSource (Synchro XYZ, ARINC 429, None, or Simulated)Heading (in Degrees)Flag Line (Valid or Invalid)NOTES1. When the system is set to GROUND TEST, the barometric altimeter issimulated to 50,000 ft and the heading simulated to 0 degrees.2. If an INVALID “Flag Line” is detected, the “Heading” will be flaggedINVALID.Figure 4-13. Data Monitor - Page 2
SKY497Installation Manual4-11Rev. CPage 2 of 5 (see figure 4-13) displays:• Radio AltitudeSource (ARINC 429, None, or Simulated)Altitude (in Feet)NOTEWhen the system is set to GROUND TEST, the radio altimeter simulated to 2,500 ft.Figure 4-14. Data Monitor - Page 3Page 3 of 5 (see figure 4-14) displays ARINC 429 Data:• Transmit Data (Tx: None Selected or ARINC 735 Type 1*, Illegal)*Alternate Display Device• Received Data (Rx):Status (Locked or Seeking)Speed (High or Low)Number of Parity Errors• Label DataLabel Number & Function164 RadAlt (Radar Altimeter)203 BarAlt (Barometric Altimeter)320 MagHead (Magnetic Heading)Channel (1 or 2)Value (Altitude in Feet; Heading in Degrees)A “Failed” message will appear if the system fails an internal ARINC 429 communications test.
SKY497Installation Manual4-12Rev. CFigure 4-15. Data Monitor - Page 4Page 4 of 5 (see figure 4-15) displays switch status:• Squat Switch (ON GND/FLYING)Connector P1-88 (SQUAT) Input (OPEN or GND)P1-88Flying OPENOn Ground GND• Landing Gear (UP/DOWN)Connector P1-87 (GEAR) Input (OPEN or GND)P1-87Gear Up OPENGear Down GND• GPWS (ACTIVE/INACTIVE)Connector P1-33 (GPWS) Input (OPEN or GND)P1-32Inactive OPENActive GNDFigure 4-16. Data Monitor - Page 5Page 5 of 5 (see figure 4-16) displays measurements of the following internal values:• Voltage (+5 VDC, + 15 VDC, & -15 VDC)• Processor Temperature (Degrees C)
SKY497Installation Manual4-13Rev. C4.4.4. Ground TestGround Test initializes the system for on-the-ground testing. In this configuration, the barometricaltimeter is simulated to 50,000 ft, heading simulated to 0 degrees, and the radar altimeter simulated to2,500 ft.NOTEGround test is available only if the squat switch input indicates aircraft is on the ground.Ground test (see figure 4-17) is accessed by selecting that option from the Service Menu (i.e., pressSELECT with Ground Test highlighted). To access ground test with a terminal device use the GroundTest command.Figure 4-17. Ground TestIf the system detects a heading fault, HDG will be displayed in the bottom center portion of the screen.The buttons perform the following operations in this mode:• EXIT - causes the system to return the System Data Menu (figure 4-6).• Soft-key (2) toggles the system through the above (ABV), normal (NRM), and below (BLW)altitude display modes. It is labeled to indicate current mode (i.e., ABV, NRM, or BLW).• Soft-key (3) toggles the display range between 2 and 6 nm. It is labeled to indicate currentrange (i.e., 2nm or 6nm).• Soft-key (4) is not used.
SKY497Installation Manual4-14Rev. C4.5 TROUBLESHOOTINGTable 4-1 is intended to assist trained electronic technicians to determine which assembly is inoperative.Do the corrective action steps in the order described. Use the Service Menu (refer to paragraph 4.4) as anaid in fault isolation. Information available from the service menu can help identify conditions that need tobe resolved. If interfaced to an alternate display service menu must be accessed via an RS-232 terminaldevice, see Appendix D for operating instructions.Table 4-1. Fault IsolationSYMPTOM CORRECTIVE ACTIONDisplay remains dark after SKYWATCH is powered ON. a. Check position of the WX-1000 maintenance switch(NORMAL/OVERRIDE).b. Reset circuit breaker if it is tripped.c. Check aircraft power source.d. Check connection to WX-1000 processor, if installed.e. Check power input at TRC mating connector.P8-A +28V (10.5-34V PWR)P8-B +28V_RET (AIRCRAFT PWR RETURN)f. Check cables connected to display.g. Replace Display.Display is distorted. Check for interference from aircraft systems.Incorrect response to buttons (soft-keys). Check soft-key wiring inside display cable and WX-1000processor cable (if installed).SKYWATCH will not enter service menu. a. Check soft-key wiring.b. Verify alternate display pins (P1-77, P1-78, P1-79, orP1-80) are not configured to ground. Service menu isnot accessible via softkeys when an alternate display isconfigured.c. If using an alternate display service menu must beaccessed via an RS-232 terminal device.The self-test successfully completes without audioannunciation.a. Check headphones/speaker and aircraft audio panelswitch settings.b. Check cables connected to TRC.Audio Alert Output:P1-92 (AUDIO_H - 600-Ohm)P1-91 (AUDIO_L - 150-Ohm)P1-90 (AUDIO_C - Common)SKYWATCH Failed. a. Check system log (para 4.4.2) for errors. Errormessages 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 connection between the TRC and the squat switch sensor.Squat Switch Input: P1-88The display cannot be switched between SKYWATCH andthe 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 displaymode switch (para 2.6.11/figure 2-2).WX-1000 processor has been removed for service;SKYWATCH fails to operate.Check position of the WX-1000 maintenance switch(NORMAL/OVERRIDE). When the WX-1000 has beenremoved for service, it should be set to the OVERRIDEposition. This switch may be located in the avionics bay.
SKY497Installation Manual4-15Rev. CTable 4-1. Fault Isolation (Continued)SYMPTOM CORRECTIVE ACTIONSKYWATCH paints itself as a target (e.g., TA). a. Verify suppression bus shielded cable is groundedcorrectly at both ends.b. Connect an oscilloscope to the suppression bus andverify that the SKY497 suppression pulse (100 µs ±5 µs)exceeds +15 V dc.c. If less than +15 V dc, the suppression bus isoverloaded.d. Check all equipment connected to the bus.e. Repair/replace the offending device.SKYWATCH TRC497 has been removed for service; theWX-1000 Stormscope fails to operate.Check the adapter plug (see para 4.7). If the TRC497 isremoved for service, an adapter plug is required to permitcontinued operation of the WX-1000.4.6 ERROR MESSAGESSKYWATCH firmware is designed to generate error messages associated with a particular condition orstep in the program. The 20 most recent errors detected by the system are saved in the System Log (seepara 4.4.2). System Log can be accessed with a terminal device by using the Dump command. For yourconvenience, in table 4-2, we have listed the error messages that have been associated with SKYWATCHinstallations. Where appropriate, procedures that may assist in resolving installation problems areprovided. When a severe error occurs SKYWATCH will fail.Table 4-2. Installation Related Error MessagesERROR NO. MESSAGE RemarksERROR 016 RF BITE a. Check directional antenna and associated cables.b. Turn system power ON.c. Calibrate directional antenna (para 4.4.1).NOTEEnsure transponder is in standby and DME is OFF while doing calibration.d. Cycle power.e. Run pilot initiated self-test.ERROR 017 RF Amplitude a. Check directional antenna and associated cables.b. Turn system power ON.c. Calibrate directional antenna (para 4.4.1).NOTEEnsure transponder is in standby and DME is OFF while doing calibration.d. Cycle power.e. Run pilot initiated self-test.ERROR 18 RF Angle a. Check directional antenna and associated cables.b. Turn system power ON.c. Calibrate directional antenna (para 4.4.1).NOTEEnsure transponder is in standby and DME is OFF while doing calibration.d. Cycle power.e. Run pilot initiated self-test.
SKY497Installation Manual4-16Rev. CTable 4-2. Installation Related Error Messages (Continued)ERROR NO. MESSAGE RemarksERROR 020 Barometric Altitude Input a. Check altimeter source. Is the unit turned on and been given enough time to warm up.NOTEWhen interfacing via an ARINC 429 serial data bus, at power-upthe TRC must adjust (auto-baud) to the speed of the incomingdata. Normally the TRC will lock-on after approximately 15seconds.b. Cycle power.c. Ensure that barometric altitude is input from only one source (Gray Code or ARINC 429, not both).d. Encoded inputs can be checked from the system configuration screen (para 4.4.3.2, Configuration - Page 2).e. Using the Data Monitor, verify barometric source and altitude (para 4.4.3.3).f. Check wiring associated with altimeter source.ERROR 021 Power Supply a. Using the Data Monitor, observe internal voltage measurements (para 4.4.3.3, Data Monitor - Page 5).b. Check aircraft power source.c. Check power input at mating connector.P8-A +28V (10.5-34V PWR)P8-B +28V_RET (AIRCRAFT PWR RETURN)ERROR 30 Check Configuration Configuration jumpers not saved or changed and need validated.a. Using the Configuration menu, verify pages 1, 3 and 4 are correctthen save (para 4.4.3.2, Configuration).b. Check wiring associated with configuration jumpers.ERROR 152 HDG Invalid synchro XYZ input.a. Check heading source.b. Verify status of heading configuration jumpers (input source and flag sense - para 4.4.3.2).c. Using the Data Monitor, verify heading data (source, heading & flag - para 4.4.3.3).d. If the heading signals become valid, the system will recover automatically.e. Check wiring associated with compass heading.ERROR 153 HDG Invalid heading reference (400 Hz).a. Check heading source.b. Verify status of heading configuration jumpers (input source and flag sense - para 4.4.3.2).c. Using the Data Monitor, verify heading data (source, heading & flag - para 4.4.3.3).d. If the reference signal becomes valid, the system will recover automatically.e. Check wiring associated with compass heading.
SKY497Installation Manual4-17Rev. CThe error messages in table 4-3 are used by factory technicians in determining what actions may havepreceded a system failure. These messages do not necessarily indicate a current system failure and areprovided for information only. Should the installer observe these messages in the error log without aSKY497 Failed message during normal operation, no service action is required.Table 4-3. Informational Error MessagesERROR NO. MESSAGE ERROR NO. MESSAGEERROR 001 Boot ERROR 146 ProcessorERROR 019 RF Transmitter ERROR 147 Processor VGA MemoryERROR 022 Processor RAM ERROR 148 Processor RAM (Low Byte)ERROR 023 Processor ROM ERROR 149 Processor RAM (High Byte)ERROR 024 Processor Reset ERROR 150 Flash Memory ChecksumERROR 025 RF Self Test Timeout ERROR 151 HDGERROR 026 Processor Not Detected ERROR 154 Processor TimeoutERROR 027 Self Test Comm ERROR 155 Operating SystemERROR 028 Pulse Detection HW ERROR 156 HDGERROR 029 Processor Comm ERROR 157 Processor FaultERROR 129 Boot ERROR 158 ARINC 429ERROR 144-145 Processor Comm
SKY497Installation Manual4-18Rev. C4.7 TRC497/WX-1000 ADAPTER PLUGAn adapter plug can be used to by-pass SKYWATCH if a WX-1000 Stormscope system is installed. Theadapter will permit continued operation of the WX-1000 if the TRC497 is removed for service. It can alsobe used as a troubleshooting tool when attempting to isolate a problem to either or both systems.The adapter plug mates with P1. It can be purchased from BFGoodrich Avionics Systems (P/N 805-10810-001) or fabricated locally from the details provided in table 4-4 and figures 4-18 and 4-19.Table 4-4. Adapter Plug JumpersJUMPER PINSFUNCTION56DPWR-15724DPWR+1514 15 DSPLY_GND35 37 VIDEO_LO36 38 VIDEO_HI46 48 HSYNC_LO47 49 HSYNC_HI60 62 VSYNC_LO61 63 VSYNC_HI73 82 SFTKEY474 83 SFTKEY375 84 SFTKEY276 85 SFTKEY1Figure 4-18. Adapter Plug Jumper InstallationCONNECTORMIL # D38999/20FH35PNCRIMP PINJUMPER#22 AWG WIRE SHORTING CAPBACKSHELLGLENAIR #340HS002M23-2H12A0.10+0.07-0.00NOTEAPPLY LOCTITE TO THE INTERNAL THREADSOF THE BACKSHELL PRIOR TO ASSEMBLY.®Figure 4-19. Adapter Plug Assembly
SKY497Installation Manual4-19Rev. C4.8 DISPOSITION OF FAILED ITEMSReturn defective components to your authorized BFG Avionics Systems dealer or to::BFG Avionics SystemsAttn: Customer Service5353 52nd Street, S.E. Grand Rapids, MI USA 49588-0873If available, pack components in their original shipping container. If the original container is not available,pack them as follows:CAUTIONDo not use desiccant crystals when packaging electronic assemblies. Since theassembly must be packed tightly, crystals in bag form cannot be used. The use ofloose 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 onthe display, TRC, and antenna.2. The display and TRC contain electrostatic discharge sensitive (ESDS) parts and must be wrapped instatic 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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SKY497Installation ManualA-1Rev. CAPPENDIX ASKY497 INTERFACESIGNAL & CABLE CHARACTERISTICSA.1 INTRODUCTIONThis appendix defines the electrical characteristics of all input and output signals to the SKY497 System.Sufficient data is included to perform an electrical load analysis for the aircraft. The interfacecharacteristics contained in this appendix are fully compatible with ARINC specifications where noted.Connection information identifies the connector-pin and signal names as they appear on the interconnectwiring diagram(figures 2-2 and 2-3) or, in the case of antenna cables, the connector type (e.g., BNC orTNC).NOTEExternal isolation diodes are not required and SHOULD NOT be installed.SIGNAL CHARACTERISTICSAltitude Digitizer / These signals are Gilham Code (or Gray Code) inputs coming from anEncoding Altimeter Input airdata computer or altitude digitizer (see para 2.6.6). These 10 lines maybe connected in parallel with the aircraft transponder. If the aircraft isequipped with selectable altitude encoders, connect the altitude inputs sothat SKY497 is always connected to the selected encoder. (ReferenceARINC 572-1.)NOTEOnly one altimeter input source (Gray Code or ARINC 429, not both)should be connected. The altimeter input should be from the same sourcethat is interfaced with the transponder or at least as accurate as thatsource, i.e., ± 125 ft.CONNECTION TRC P1-40 (ALT_A1)TRC P1-41 (ALT_A2)TRC P1-50 (ALT_A4)TRC P1-51 (ALT_B1)TRC P1-56 (ALT_B2)TRC P1-57 (ALT_B4)TRC P1-58 (ALT_C1)TRC P1-59 (ALT_C2)TRC P1-71(ALT_C4)TRC P1-72 (ALT_D4)TRC P1-81 (ALT_COMN)CABLE Minimum 22 AWG wire for each connectionfor lengths up to 30 ft.VOLTAGE +30 V input max.CURRENT <1 mA sourced per line.FREQUENCY <100 HzSOURCE Z >10 kΩ per line.MAX CAPACITANCE <20 pF per line.NOTEIf the aircraft has switched encoders that use 28V RETURN or AIRCRAFTGROUND as reference for encoder selection, then ALT_COMMON (TRCP1-81) should be left unconnected.
SKY497Installation ManualA-2Rev. CSIGNAL CHARACTERISTICSAntenna Top Directional SUM (SIGMA) Port (Blue)CONNECTION TRC J9, TNC connector.CABLE Cable attenuation must not exceed 2.5 dB, VSWR1.5:1. Refer to para 2.6.1.Impedance: 50 ΩAntenna Top Directional BIT PROBE Port (Black)CONNECTION TRC J10, BNC connector.CABLE Cable attenuation must not exceed 6 dB, VSWR1.5:1. Refer to para 2.6.1.Impedance: 50 ΩAntenna Top Directional DIFFERENCE (DELTA) Port (Red)CONNECTION TRC J11, TNC connector.CABLE Cable attenuation must not exceed 2.5 dB, VSWR1.5:1. Refer to para 2.6.1.Impedance: 50 ΩARINC 429 External Interface The SKY497 has two ARINC 429 receivers and one transmitter (see para2.6.5). The receivers operate at either low speed (12.5 kHz) or high speed(100 kHz). The transmitter operates only at high speed (100 kHz).The ARINC 429 transmitter is intended to provide the capability tointerface with alternate display devices other than the WX-1000/SKY497display.The two ARINC 429 receivers can be used to input data from otheravionics systems. The following labels are supported:LABEL FUNCTION164 Radio Altimeter (See note 1 & 3.)203 Barometric Altitude (Uncorrected - see note 3.)320 Magnetic Heading (See note 2 & 3.)NOTES1. The radio altimeter must provide full range output between 0and 2500 feet. Not all altimeters provide this full range output.The full range output can sometimes be obtained as a mod tothe radio altimeter . Check with the specific altimetermanufacturer for compatibility and availability of modification,if necessary.2. When using 429 input for heading, the HEADING FLAGSENSE (P1-68 - see para 2.6.2) should remain open (i.e., notjumpered to configuration ground).3. The TRC can only accept Radio Altimeter input from ARINC 429source. The Barometric Altitude (uncorrected) can be ARINC 429 orGilham Code. The Magnetic Heading can be ARINC 429, Synchro(XYZ) or Stepper depending on the configuration pins andinterconnect wiring. (See figure 2-2 or 2-3.)
SKY497Installation ManualA-3Rev. CSIGNAL CHARACTERISTICSARINC 429 External Interface (Continued).Both transmitters (data sources) must be set to the same speed. The TRCwill automatically adjust both receivers to the speed of the first detectedincoming data.NOTEIf 429 barometric altitude is used, it should be from the samesource that is interfaced with the transponder or it must be atleast as accurate as that source, i.e., ± 125 ft.Once the TRC detects valid ARINC 429 input from a Barometric Altitudesensor (Label 203), it will accept only 429 data from that sensor.CONNECTION TRC P1-45 (ARINC-429 RX 1A)TRC P1-44 (ARINC-429 RX 1B)TRC P1-43 (ARINC-429 RX 2A)TRC P1-42 (ARINC-429 RX 2B)TRC P1-34 (ARINC-429 TX 1A)TRC P1-33 (ARINC-429 TX 1B)Audio Alert Output This output is directly compatible with industry standard audio panels(see para 2.6.7).NOTEAudio output from the TRC is transformer isolated.This output is disabled when a GPWS alarm is detected (see para 2.6.9) .CONNECTION TRC P1-92 (AUDIO_H) - For 600 Ω audio systems.TRC P1-91 (AUDIO_L) - For 150-Ω audio systems.TRC P1-90 (AUDIO_C) Audio CommonCABLE Minimum 22 AWG twisted shielded pair cable forlengths up to 30 ft.POWER 400 mW into a 600 Ω load.FREQUENCY 0 - 3.0 kHzLOAD Z Selectable 150 or 600 ΩDiagnostic Port NO CONNECTION TO EXISTING AIRCRAFT WIRING. The Diagnostic Port(RS-232) is available to support factory testing and analysis and SHOULDBE LEFT UNCONNECTED. The port defaults to the following settings:Baud Rate 19,200Parity: NoneData Bits 8Stop Bits` 1CONNECTION TRC J7-2 (DIAG_RX)TRC J7-3 (DIAG_TX)TRC J7-5 (DIAG_GND)
SKY497Installation ManualA-4Rev. CSIGNAL CHARACTERISTICSDisplay Power Power supply to WX-1000/SKY497 display. +15/-15 V dc from theWX-1000 Processor (if installed) and output to the display.CONNECTION P1-24 (DPWR+15_IN) From ProcessorP1-5 (DPWR-15_IN) From ProcessorP1-15 (DSPLY_GND) From ProcessorP1-7 (DPWR+15_OUT) To DisplayP1-6 (DPWR-15_OUT) To DisplayP1-14 (DSPLY_GND) To DisplayCABLE See paragraph 2.6.3.VOLTAGE +15/-15 V dcCURRENT 0.7 A input max.Ground Proximity Warning This input senses a GPWS alarm and temporarily disables theSystem (GPWS) Flag Input SKY497 audible alert messages until the warning clears (see para 2.6.9).The input can be either a constant flag signal or an alternating flagoutput. The flag must be cleared for five (5) seconds before the TRCaccepts a "NO ALARM" condition and restores audible alerts. IF THEAIRCRAFT IS NOT EQUIPPED WITH GPWS, LEAVE THIS INPUT UNCONNECTED.NOTEIf the aircraft is equipped with GPWS, it must be connected to theTRC.CONNECTION TRC P1-32 (GPWS)CABLE Minimum 22 AWG wire for lengths up to 30 ft.VOLTAGE GPWS ALARM, Aircraft Ground.NO GPS ALARM, open or 5-35 V dc.CURRENT <5 mA sourced.Heading Valid Indicates that the heading source is providing valid heading information.If the heading source does not have a FLAG LO (-), the heading sourceFLAG HI(+) input is connected to P1-53 (HDG_FLG+) and P1-52(HDG_FLG-) is connected to ground.NOTEThe active polarity (i.e., HEADING FLAG (+) or HEADING FLAG (-)is selected via the Heading Flag Sense jumper P1-68 (see Table A onthe Interconnect Wiring Diagram, figures 2-2 and 2-3, sheet 2)located in the connector back-shell.If the heading system has a low level flag between 1.5 V dc and 2.7 V dc (whenvalid), P1-68 (HEADING FLAG SENSE) should not be jumpered to groundand P1-53 (HDG_FLG+) must remain unconnected.CONNECTION P1-53 (HDG FLAG+)P1-52 (HDG FLAG-)CABLE See paragraph 2.6.4.VOLTAGE High Sense (FLAGHI - FLAGLO):Min: 5.0 V dcMax: 30.0 V dcLow Sense (FLAGHI - FLAGLO):Min: -30.0 V dcMax: 1.0 V dcINPUT IMPEDANCE >2 kΩINPUT CURRENT Active: Min: 1 mAMax: 15 mA
SKY497Installation ManualA-5Rev. CSIGNAL CHARACTERISTICSHorizontal Sync Balanced horizontal sync from the WX-1000 Processor (if installed) andoutput to the WX-1000/SKY497 display. Signal levels as specified inRS-422.CONNECTION TRC P1-47 (HSYNC_IN_HI) From ProcessorTRC P1-46 (HSYNC_IN_LO) From ProcessorTRC P1-49 (HSYNC_OUT_HI) To DisplayTRC P1-48 (HSYNC_OUT_LO) To DisplayCABLE See paragraph 2.6.3.VOLTAGE 0-5 V dcCURRENT <100 mAFREQUENCY 16.4 kHzLOAD Z 1 kΩLanding Gear Switch Input This signal line is to be connected to the landing gear switch to sense theposition of the landing gear (see para 2.6.13).IF THE AIRCRAFT DOES NOT HAVE A LANDING GEAR SWITCH, THIS INPUT MUSTREMAIN UNCONNECTED. With this configuration, if no ARINC 429 compatibleradio altimeter is installed, the system will default to the highest TAsensitivity level (level B) and audio TA announcements (i.e., “traffic, traffic”)will not be inhibited during takeoff and landing.CONNECTION TRC P1-87 (GEAR)CABLE Minimum 22 AWG wire for lengths up to 30 ft.VOLTAGE GEAR UP Indication 4.5 - 32 V dc or OPENGEAR DOWN Indication, Aircraft GroundCURRENT <5 mA sourced.SOURCE Z >40 kΩMAX CAPACITANCE <20 pFNormal/ Over-ride This is a WX-1000 Maintenance over-ride switch (see para 2.6.11). Over-ride control (SW2 on the Interconnect Wiring Diagram, figure 2-3) isnecessary only if a WX-1000 processor is also installed. It enables theSKY497 to be powered-up if the WX-1000 processor has been removed forservice. During normal operation, with a WX-1000 processor installed,SW2 should remain in the WX-1000 position. Any general purpose DPDTtoggle switch can be used.CONNECTION TRC P1-11 (PWR_SW_HI)TRC P1-3 (PWR_SW_LO)CABLE Minimun 22 AWG.VOLTAGE Less than 0.7 V = ON; open = OFF.CURRENT <100 mAPower Input (TRC) 11-34 V dc. 7.5 A circuit breaker required for 14 V aircraft systems and a 5A circuit breaker for 28V systems (see para 2.6.14).CONNECTIONTRC J8-A (+28V)TRC J8-B (+28V_RET)CABLE Use twisted shielded pair cable (Beldon 83322,Alpha 2826/2, or equivalent). Terminate shield toairframe at sensor or power source.VOLTAGE 11 to 34 V dc, 70 Watts (Maximum)
SKY497Installation ManualA-6Rev. CSIGNAL CHARACTERISTICSRS422 Interface NO CONNECTION TO EXISTING AIRCRAFT WIRING. The RS422 Interface isavailable to support factory testing and analysis and SHOULD BE LEFTUNCONNECTED.NOTERS422 interface is configured via jumper P1-67 (see Table A onthe Interconnect Wiring Diagram, figures 2-2 and 2-3, sheet 2)located in the connector back-shell.CONNECTION TRC P1-9 (DR_RX+)TRC P1-8 (DR_RX-)TRC P1-2 (DR_TX+)TRC P1-1 (DR_TX-)Serial Interface NO CONNECTION TO EXISTING AIRCRAFT WIRING. This interface (RS-232) isavailable to support factory testing and analysis and SHOULD BE LEFTUNCONNECTED. This serial interface defaults to the following settings:Baud Rate 19,200Parity: NoneData Bits 8Stop Bits` 1CONNECTION TRC P1-21 (IOP_SERIAL_TX)TRC P1-22 (IOP_SERIAL_RX)TRC P1-23 (IOP_SERIAL_GND)SKYWATCH/STORMSCOPE If a WX-1000 processor is installed, this signal (SW1 on the InterconnectWiring Diagram, figure 2-3) switches the display between the WX-1000and SKY497 (see para 2.6.10). Any general purpose SPST toggle switchcan be used.CONNECTION TRC P1-31 (CWS_SS)TRC P1-4 (SW_RET)CABLE Minimum 22 AWG.VOLTAGE CLOSED (Less than 0.7 V) = Stormscope DisplayModeOPEN = SKYWATCH Display Mode.CURRENT <100 mASoft-keys Soft-key inputs from the WX-1000/SKY497 display and output to theWX-1000 processor (if installed). The pushbuttons on the front of thedisplay are referred to as Soft-keys (1), (2), (3), and (4). In every operatingmode a label identifying the button function is displayed next to thebutton (see paragraph 3.2).CONNECTION TRC P1-85 (SFTKEY1_IN) From DisplayTRC P1-84 (SFTKEY2_IN) From DisplayTRC P1-83 (SFTKEY3_IN) From DisplayTRC P1-82 (SFTKEY4_IN) From DisplayTRC P1-76 (SFTKEY1_OUT) To ProcessorTRC P1-75 (SFTKEY2_OUT) To ProcessorTRC P1-74 (SFTKEY3_OUT) To ProcessorTRC P1-73 (SFTKEY4_OUT) To ProcessorCABLE See paragraph 2.6.3.
SKY497Installation ManualA-7Rev. CSIGNAL CHARACTERISTICSSoft-keys (Continued) VOLTAGE Active: Min: 0.0 VMax: 1.5 VInactive: Min: 3.5 V or Open(Internal 4.7 kΩ pull-up)Max: 5.0 VSquat Switch Input This signal line is to be connected to the squat switch to sense when theaircraft is on the ground (see para 2.6.12).CONNECTION TRC P1-88 (SQUAT)CABLE Minimum 22 AWG wire for lengths up to 30 ft.VOLTAGE IN FLIGHT Indication4.5 - 32 V dc or OPENON THE GROUND IndicationAircraft GroundCURRENT <5 mA sourced.Stepper Heading Input These connections will accept heading information from a King KCS55 (King KCS55) stepper drive unit (see para 2.6.4).NOTEStepper heading input is selected via the Heading Input Sourcejumpers P1-69 & P1-70 (see Table A on the Interconnect WiringDiagram, figures 2-2 and 2-3, sheet 2) located in the connectorback-shell.Stepper Drive Motor 1 & 3FREQUENCY Min: 0 HzMax: Turn Rate Dependent (.25 degreeincrements per edge transition)VOLTAGE Low Level: Min: 0 VMax: 2 VHigh Level: Min: 13 VMax: 17 VMax: 35 VrmsINPUT IMPEDANCE >50 kΩCONNECTION P1-65 (DRIVE MOTOR 1) to KI-525 P2-AP1-54 (DRIVE MOTOR 3) to KI-525 P2-HCABLE See paragraph 2.6.4.Stepper Drive Motor Unregulated +15 VVOLTAGE Min: 13 VMax: 17 VINPUT IMPEDANCE >50 kΩCONNECTION P1-55 (UNREG +15) to KI-525 P1-VCASE GND (AIRFRAME GROUND) toKI-525 P1-J)CABLE See paragraph 2.6.4.
SKY497Installation ManualA-8Rev. CSIGNAL CHARACTERISTICSSuppression Bus I/O The SKY497 outputs a 100 µs (± 5 µs) suppression pulse on the aircraftsuppression bus (see para 2.6.8). In addition, the SKY497 receivessuppression signals from all other devices on the suppression bus (e.g.,transponder, DME). (Reference ARINC 735-2 and DO-197A.)CAUTIONThe aircraft transponder must have suppression circuitry to ensurethat SKYWATCH does not paint itself as a target (e.g., TA).CONNECTION TRC P1-89 (SUP_BUS)CABLE Any size low capacitance shielded cable may beused.VOLTAGE 18 - 70 V dc input, greater than 20 V dc output.CURRENT 0.3 A output max.FREQUENCY 100 µs positive pulse output, DC-1 mHz input.SOURCE Z 2 kΩLOAD Z 10.5 kΩMAX CAPACITANCE <50 pFVertical Sync Balanced vertical sync from the WX-1000 Processor (if installed) andoutput to the display. Signal levels as specified in RS-422.CONNECTION TRC P1-61 (VSYNC_IN_HI) From ProcessorTRC P1-60 (VSYNC_IN_LO) From ProcessorTRC P1-63 (VSYNC_OUT_HI) To DisplayTRC P1-62 (VSYNC_OUT_LO) To DisplayCABLE See paragraph 2.6.3.VOLTAGE 0-5 V dcFREQUENCY 60 HzSOURCE Z 1 kΩVideo Output Balanced video from the WX-1000 Processor (if installed) and output tothe display. Signal levels as specified in RS-422.CONNECTION TRC P1-36 (VIDEO_IN_HI) From ProcessorTRC P1-35 (VIDEO_IN_LO) From ProcessorTRC P1-38 (VIDEO_OUT_HI) To DisplayTRC P1-37 (VIDEO_OUT_LO) To DisplayCABLE See paragraph 2.6.3.VOLTAGE 0-5 VCURRENT <100 mAFREQUENCY <15 mHzLOAD Z 1 kΩ
SKY497Installation ManualA-9Rev. CSIGNAL CHARACTERISTICSXYZ Synchro Input These connections from the aircraft heading source (ARINC Synchro SignalPractices) allow the unit to rotate the displayed data as the aircraft turns.NOTESynchro heading input is selected via the Heading Input Sourcejumpers P1-69 & P1-70 (see Table A on the Interconnect WiringDiagram, figures 2-2 and 2-3, sheet 2) located in the connectorback-shell.X(S1), Y(S3), Z(S2)FREQUENCY Min: 50 HzMax: 1500 HzVOLTAGEMin: 5.0 Vrms (w/reduced angular resolution.)Max: 14.0 Vrms (external padding required forhigher levels.)INPUT IMPEDANCE >50 kΩCONNECTION P1-66 (SYNC_X)P1-65 (SYNC_Y)P1-64 (SYNC_Z)CABLE See paragraph 2.6.4.H and C (high and low reference)FREQUENCY Min: 50 HzMax: 1500 HzVOLTAGEMin: 3.5Max: 35 VrmsINPUT IMPEDANCE >50 kΩCONNECTION P1-55 (SYNC_HI)P1-54 (SYNC_LO)CABLE See paragraph 2.6.4.
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SKY497Installation ManualB-1Rev. CAPPENDIX BINSTALLATION CHECKOUTUSING THE TCAS-201 RAMP TEST SETB.1 INTRODUCTIONThis appendix contains the self test and post installation checkout procedures. Refer to the SKY497 Pilot'sGuide for complete operating instructions. The post installation checkout section contains instructions fordoing the checkout procedure with an IFR Systems TCAS-201 Ramp Test Set (with TCAS I firmware).NOTES1. This procedure assumes familiarity with the set up and operation of the TCASramp test set.2. All test equipment used in completing these tests shall be calibrated inaccordance with the manufacturer's recommendations.3. When the SKY497 is interfaced to an alternate display, reference Appendix Ewhile performing this checkout procedure.This procedure will validate the installation and return to service of the BFGoodrich Avionics SystemsSKY497.B.2 CONTROLSAll operating controls are located on the front of the WX-1000/SKY497 display. Figure B-1 shows thelocations of the controls. Complete operating instructions for the SKY497 are provided in the SKY497Pilot's Guide supplied with each system.Figure B-1. ControlsOFF/BRTSwitchPower is applied by rotating the knob clockwise past the detent. Continuedclockwise rotation increases display brightness.1, 2, 3, & 4PushbuttonsAlso referred to as soft-keys (1), (2), (3), and (4). In every operating mode a labelidentifying the button function will be displayed next to the button.
SKY497Installation ManualB-2Rev. CB.3 CHECKOUT PROCEDUREIf the indications given in the following steps, except for the ramp test set, are not obtained, refer to thetroubleshooting procedures in Chapter 4. If indications given for the ramp test set are not obtained, referto the manual supplied with that equipment.1. Enter and store the setup information identified in table B-1 (see next page) into the TCAS-201 RampTest Set.2.Table B-1. IFR Systems TCAS-201 Ramp Test Set Setup DataSCREEN STORAGE NUMBER 1SETUP #1 INTRUDER TYPE: ATCRBSUUT DIST: HORIZ = Distance (ft.) from aircraftUUT DIST; VERT = Vertical height (ft.) difference between testantenna and SKY497 antennaALT REPORTING: ONSTORE 0RECALL 0GAIN_1030 9.4 dBLOSS 1.3 dBSETUP #2 RANGE MAX: 20 NMRANGE MIN: 0 NMALT MAX: 60,000 ftALT MIN: 0 ftSCENARIO TEST RANGE: 5.0 NMRANGE RATE: +200 ktALT: 51,000 ftALT: RATE: 0 FPMREPLY TEST RANGE: 5.0 NMALTITUDE 50,500 ft%REPLY: 100 %3. Make sure the aircraft's transponder is in the STBY mode and the DME is turned OFF. At theaircraft's instruments, verify all compass/HSI flags are valid.NOTEAfter power up, it may take a couple of minutes for the altitude encoder toreturn a valid altitude to the transponder and SKY497.4. Turn SKY497 ON. The display will show a start-up screen similar to one shown in figure B-2. Afterstart-up screen appears, rotate the OFF/BRT switch. Verify that clockwise rotation increases displaybrightness.
SKY497Installation ManualB-3Rev. CFigure B-2. Start-up ScreenAfter approximately thirty seconds the display will show the STANDBY screen (see figure B-3).NOTEIf the TRC has not been calibrated to the directional antenna (see step 6below), the display may show a “SKY497 FAILED” message.Figure B-3. Standby Screen5. Turn SKY497 OFF and then enter the Service Menu (see paragraph 4.4) by holding the left twobuttons (soft-keys 1 and 2) depressed as the system is turned ON.6. From the Service Menu, calibrate the TRC to the directional antenna (see paragraph 4.4.1).7. Return to the Service Menu and select System Data (see paragraph 4.4.3).a. Verify status and save the configuration jumpers (see paragraph 4.4.3.2, Configuration).b. Verify that the system has recognized and is responding to installed sensors (see paragraph4.4.3.3, Data Monitor).1) Sequence through each Data Monitor display page.2) Verify that the sensor information displayed is correct.3) If the information is not correct, the sensor has failed to communicate with the TRC.Check operation of the sensor and cables between the TRC and sensor.
SKY497Installation ManualB-4Rev. C4) Change the status of the landing gear, squat switch, altitude, and heading sensors. Verifythat the display shows the correct input (i.e., sensing of these signals).8. Exit the service menu and do the SKYWATCH self-test (see para 3.4).9. Do the SKYWATCH self-test (see para 3.4).10. Turn SKY497 OFF, return to the Service Menu and select Ground Test (see paragraph 4.4.4).11. Verify operation of range function. Soft-key (3) is labeled to indicate the current range. Press soft-key(3) to toggle the display range between 2 and 6 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 indicatethe current mode. Press Soft-key (2) to select normal (NRM), below (BLW), and above (ABV).14. Select the NRM (normal) mode.15. Position the aircraft with the nose aligned on any 90 degree heading. Avoid areas within 250 ft ofobstructions (e.g., hangers, large aircraft, control towers, etc.) where there is a potential for multipathproblems. 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 SKY497 directional antenna). Mark these points atthe same distance, approximately 100 ft, from the aircraft.16. 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/STOPkey.NOTEThe TCAS-201 display will indicate “NO WHISPER-SHOUT SEQUENCE”.d. Verify that the SKY497 display shows an other traffic symbol (open diamond) at the 12 O'clockposition (±30 degrees), approximately 5.0 nm, in level flight, and at an altitude of 500 ft aboveown aircraft (i.e., "+05").NOTESIf the display reflects a gross error in target bearing, check the directionalantenna cables at TRC connectors J9 (sum port) and J11 (difference port).They may be reversed. A further indication of this condition would be a targetthat moved in a counter-clockwise direction when the test set is moved in aclockwise direction.Multiple targets or a faulty bearing may result from multipath distortion(see step 2).During these tests, the SKY497 may detect and display other active targets.e. Repeat a, b, c, and d from each of the test points (see step 2).16. Do the following dynamic test.a. Position the ramp test set on the test point directly in front of the test aircraft (i.e.,approximately 100 ft in front of the aircraft, see step 2).b. Connect the TCAS-201 Flat Antenna (facing towards the test aircraft) to the antenna connector.c. At the TCAS-201 test set, press the SCEN key.d. Initiate the SCENARIO TEST by pressing the ANTENNA push button switch or theRUN/STOP key.
SKY497Installation ManualB-5Rev. Ce. 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 analtitude 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 thesymbol changes from an other traffic symbol (open diamond) to a traffic advisory (solid circle).NOTEThe voice message, “TRAFFIC, TRAFFIC,” will be enunciated over thecockpit audio system.g. The target, when it reaches 0.0 nm, will reverse direction and move outbound on the sameheading.NOTEThe target may momentarily drop from the display and then reappear as another traffic symbol (open diamond).17. Restart SKYWATCH by cycling power OFF and then ON.18. This completes the post installation checkout procedure.
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SKY497Installation ManualC-1Rev. CAPPENDIX CINSTALLATION CHECKOUTUSING THE TIC T-49C FLIGHTLINE TESTERC.1 INTRODUCTIONThis section contains instructions for using the TIC T-49C Flightline Tester to do post-installationcheckout of the BFG Avionics Systems SKY497. Detailed setup, operation and maintenance informationfor the T-49C Flightline Tester is provided in the T-49C Operating and Maintenance Instruction Manual.NOTES1. This procedure assumes familiarity with the set up and operation of the T-49CFlightline Tester.2. All test equipment used in completing these tests shall be calibrated inaccordance with the manufacturer's recommendations.3. When the SKY497 is interfaced to an alternate display, reference Appendix Ewhile performing this checkout procedure.This procedure will validate the installation and return to service of the BFGoodrich Avionics SystemsSKY497.C.2 CONTROLSAll operating controls are located on the front of the WX-1000/SKY-497 display. Figure C-1 shows thelocations of the controls. Complete operating instructions for the SKY497 are provided in the SKY497Pilot's Guide supplied with each system.Figure C-1. ControlsOFF/BRTSwitchPower is applied by rotating the knob clockwise past the detent. Continuedclockwise rotation increases display brightness.1, 2, 3, & 4PushbuttonsAlso referred to as soft-keys (1), (2), (3), and (4). In every operating mode a labelidentifying the button function will be displayed next to the button.
SKY497Installation ManualC-2Rev. CC.3 CHECKOUT PROCEDUREThe T-49C Flightline Tester simulates a ground based secondary surveillance radar (SSR) when the TCASINTRUDER selector switch is in the ATCRBS/Mode-S XPDR TEST position. When the T-49C intrudertype 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 SKY497 from as far as 14 nauticalmiles and as close as a few hundred feet. The apparent distance from the simulated intruder to theSKY497 system under test decreases as if the intruder was converging on the aircraft under test. The testset determines the altitude of the aircraft under test by interrogating the transponder using an ATCRBSinterrogation. By adding or subtracting the desired differential altitude, as selected by the front-panelscenario switch, the initial altitude of the scenario is controlled by the microprocessor. This altitude, likethe distance, is varied so that the simulated intruder converges on the aircraft’s position.1. Make sure the aircraft's transponder is in the STBY mode and the DME is turned OFF. At theaircraft's instruments, verify all compass/HSI flags are valid.NOTEAfter power up, it may take a couple of minutes for the altitude encoder toreturn a valid altitude to the transponder and SKY497.2. Turn SKY497 ON. The display will show a start-up screen similar to one shown in figure C-2. Afterstart-up screen appears, rotate the OFF/BRT switch. Verify that clockwise rotation increases displaybrightness.Figure C-2. Start-up ScreenAfter approximately thirty seconds the display will show the STANDBY screen (see figure C-3).NOTEIf the TRC has not been calibrated to the directional antenna (see step 4below), the display may show a “SKY497 FAILED” message.
SKY497Installation ManualC-3Rev. CFigure C-3. Standby Screen3. Turn SKY497 OFF and then enter the Service Menu (see paragraph 4.4) by holding the left twobuttons (soft-keys 1 and 2) depressed as the system is turned ON.4. From the Service Menu, calibrate the TRC to the directional antenna (see paragraph 4.4.1).5. Return to the Service Menu and select System Data (see paragraph 4.4.3).a. Verify status and save the configuration jumpers (see paragraph 4.4.3.2, Configuration).b. Verify that the system has recognized and is responding to installed sensors (see paragraph4.4.3.3, Data Monitor).1) Sequence through each Data Monitor display page.2) Verify that the sensor information displayed is correct.3) If the information is not correct, the sensor has failed to communicate with the TRC.Check operation of the sensor and cables between the TRC and sensor.4) Change the status of the landing gear, squat switch, altitude, and heading sensors. Verifythat the display shows the correct input (i.e., sensing of these signals).6. Exit the Service Menu. Verify that the display shows the standby screen (figure C-3) and then pressSoft-key (4), labeled OPR.7. Verify operation of range function. Soft-key (3) is labeled to indicate the current range. Press Soft-key(3) to toggle the display range between 2 and 6 nm.8. Select the 6 nautical mile range.9. Verify that the system toggles through the altitude display modes. Soft-key (2) is labeled to indicatethe current mode. Press Soft-key (2) to select normal (NRM), below (BLW), and above (ABV).10. Select the NRM (normal) mode.11. If installed, turn the radio altimeter OFF.12. Do the SKYWATCH self-test (see para 3.4).13. Position the aircraft with the nose aligned on any 90 degree heading. Avoid areas within 250 ft ofobstructions (e.g., hangers, large aircraft, control towers, etc.) where there is a potential for multipathproblems. 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 SKY497 directional antenna. Mark thesepoints at the same distance, between 100 and 150 ft, from the aircraft.
SKY497Installation ManualC-4Rev. C13a. Change the aircraft's transponder from STBY mode to the ON position.14. Position the T-49C Flightline Tester on one of the test points identified in previous step.CAUTIONThe Flightline Tester is not weatherproof when the lid is open. Do not setupor operate the Flightline Tester in conditions of rain, sleet, etc.15. Setup and verify operation of the T-49C Flightline Tester with the HI/LOW power switch in the HIposition and then:a. Set the TCAS INTRUDER selector switch of the T-49C to the ATCRBS/Mode-S XPDR TESTposition and press TEST and the INTERROGATE. This will store the aircraft’s barometricaltitude in the T-49C.NOTEThe T49-C will display the pressure altitude of the aircraft under test.b. Verify that the SKY497 display shows the standby screen (figure C-3) and then press soft-key(4), labeled OPR. Select NRM mode and 6 nm range by pressing appropriate soft-key's.c. Set the TCAS INTRUDER selector switch to the ATCRBS position and the SCENARIO selectorswitch to the 0 altitude offset position. Press INTERROGATE, and when the range on thedisplay decreases to 5 NM, press TEST. This will freeze the scenario and represent a stationaryintruder aircraft 5 NM away at the same altitude as the UUT aircraft. Verify that the SKY497displays, in the direction (±30 degrees) of the T-49C, a symbol for other traffic (i.e., opendiamond) at 5 NM. Target will be displayed in level flight at own aircraft altitude (i.e., “00”displayed above the traffic symbol).NOTES1) If the display reflects a gross error in target bearing, check the SKY497directional antenna cables at TRC connectors J9 (sum port) and J11(difference port). They may be reversed. A further indication of thiscondition would be a target that moved in a counter-clockwise directionwhen 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 SKY497 may detect and display other activetargets.4) To obtain a better line of sight, it may be necessary to elevate theantenna.d. Move the T-49C to each test point and verify that the display shows the corresponding bearingdisplacement.NOTEIt is necessary to wait a few seconds after moving to let the test target stabilizein position.16. This completes testing with the T-49C, reattach top lid of the T-49C.17. If installed, TURN ON the radio altimeter.18. This completes the post installation checkout procedure.
SKY497Installation ManualD-1Rev. CAPPENDIX DUsing the Terminal Device(e.g., Laptop Computer)A terminal device can be used as an aid in installing, testing and troubleshooting the SKY497. Theterminal device must be connected to the RS-232 serial data TEST port (J7) located on the front of theTRC497. TRC connector J7 is a female DB9 receptacle. A standard serial cable that has RXD (pin 2), TXD(pin 3), and GND (pin 5) 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, theRS-232 terminal device must be setup as follows, with no hardware or software handshaking being used.Baud Rate: 19200Parity: NoneData Bits: 8Stop Bits: 1The SKY497 includes the following commands to help with installation, testing, and troubleshooting.These commands are listed in the order they appear when the help menu is accessed and can be typed inupper case or lower case letters. Ctrl+R repeats the last command once; Ctrl+L continually repeats the lastcommand (to stop continuously repeating the command press <Enter>). Help screens have been created foryour convenience, to access the command help screen type help or ? at the prompt. To access the helpscreen for each command, type the command followed by help.Commands Descriptions? or Help The help or ? command displays a list of available commands. Executing theHelp command displays the following list.stp>? ? .................... Command help Arinc429 ............. Arinc 429 cmds Arinc735 ............. Arinc 735 cmds Bar .................. Displays barometric altitude Cal .................. Executes antenna calibration Config ............... SKY497 Config Options Dump ................. Displays the List of Logged Errors Ground ............... Turns ground test mode on or off Head ................. Displays heading Help ................. Command help Rad .................. Displays Radio altitude Save ................. Saves System Configuration Say .................. Says Phrase from Speech Chip Sensors .............. Displays sensor data Version .............. SW Version informationFor Information on any particular command, enter the command followedby help.
SKY497Installation ManualD-2Rev. CCommands DescriptionsArinc429 Displays the ARINC-429 sensor inputs and label status. Data shown is liveand will change as the sensor changes. To view changes re-type thecommand.stp>Arinc429Arinc429 Operating,Rx: Seeking, LowRx Parity Errors: 0Lbl Functn Chn Ssm Value164 RadAlt --- --- ------203 BarAlt --- --- ------320 MagHead --- --- ------Arinc735 Displays the ARINC-735 alternate display type and status. Data shown islatched during turn on, configuration changes will not take affect untilpower is cycled.stp>arinc735Tx Selected: None Selectedstp>arinc735Tx Selected: ARINC735 Type1stp>arinc735Tx Selected: Illegal DisplayBar (help) Displays the barometric altitude source, validity, and value. Data shown islive and will change as the sensor changes. To view changes re-type thecommand.Bar help: Displays the command specific help message.Bar: Displays barometric altitude data.stp>barBarometric Altitude source: Encoded InputsBarometric Altitude: 1000 feetEncoded Altitude Bitsd4 c4c2c1 b4b2b1 a4a2a1 0 0 1 0 0 1 1 0 0 0Encoded Altitude: 1000 feet
SKY497Installation ManualD-3Rev. CCommands DescriptionsCal (help) Calibrates the antenna to the system (includes cables, connectors, andTRC497).Cal: Performs system calibration.stp>calAsking for current calibration value.Starting calibration. Please Wait...Re-Calibration Successful!Old Cal Value: 283 degreesNew Cal Value: 273 degreesCal help: Displays the command specific help message.Config Displays the state of the configuration pins, switches, barometric altitudebits, and internal voltage and temperature readings. Checks theinput/output circuitry. Data shown is live and will change as the sensor orconfiguration changes. To view changes re-type the config command.stp>configSKY497 Configuration Straps:Hdg. (XYZ/STEP/429): XYZ P1-70 : GND P1-69 : OPENHeading Flag Sense : HIGH P1-68 : GNDDR/Alt.422 (DR/422): DR P1-67 : OPENAnt. Pos. (TOP/BOT): TOP P1-100 : OPENAntenna NY(164/156): NY164 P1-99 : OPENAirframe (FIX/ROT): FIX P1-98 : OPENAlternate Display Type: None Selected P1-80 : OPEN P1-79 : OPEN P1-78 : OPEN P1-77 : OPENIOP Soft Switches:Squat (ON GND/FLY): ON GND P1-88 : GNDGear (UP/DOWN): DOWN P1-87 : GNDGPWS (ACT/INACT): INACT P1-32 : OPENBarometric Encoded Altitude:d4 c4c2c1 b4b2b1 a4a2a1 0 0 1 0 0 1 1 0 0 0Altitude: 1000 feeta1=P1-40 b1=P1-51 c1=P1-58a2=P1-41 b2=P1-56 c2=P1-59a4=P1-50 b4=P1-57 c4=P1-71d4=P1-72IOP Internal Status:Internal +5 VDC: +5.1 VInternal +15 VDC: +15.0 VInternal -15 VDC: -15.1 VInternal Temp. : +34 C
SKY497Installation ManualD-4Rev. CCommands DescriptionsDump (help) Displays the error messages stored in the error log. If no errors are stored inthe system log, the message NO FAULTS DETECTED is displayed.Dump help: Displays command specific help message.Dump: Displays system error log.stp>dumpSKY497 SYSTEM LOGSystem Time - 00704:14Err# Time Description019 - 00693:41 - RF Transmitter018 - 00668:47 - RF Angle020 - 00668:03 - Barometric Altitude Input024 - 00647:52 - Processor Reset153 - 00647:38 - HDGGround (help | test | off) SKY497 enters the ground test mode.Ground help: Displays the command specific help message.Ground (or Ground 0ff): Exits ground test mode (if active).Ground Test: Enters ground test mode.stp> ground helpParameter: TEST to enter ground test mode or OFF (or nothing) to exit modestp>groundSystem no longer in Ground Test ModeReturning to aircraft sensors and switch inputsstp> ground testSystem in Ground Test ModeSimulating Barometric Altitude: 50,000 ft.Simulating RADAR Altimeter: 2,500 ft.Simulating Heading: 0 degGear and Squat switch override in effectHead (help) Displays the current heading source, degrees, and heading flag status (validor invalid). Heading source is latched during turn on and will not changeuntil power is cycled, all other data is live.Head help: Displays the command specific help message.Head: Displays heading data.stp>headHeading Source: Synchro XYZHeading: 0 degreesFlag line: Valid
SKY497Installation ManualD-5Rev. CCommands DescriptionsHelp or ? The help or ? command displays a list of available commands. Executing theHelp command displays the following list.stp>? ? .................... Command help Arinc429 ............. Arinc 429 cmds Arinc735 ............. Arinc 735 cmds Bar .................. Displays barometric altitude Cal .................. Executes antenna calibration Config ............... SKY497 Config Options Dump ................. Displays the List of Logged Errors Ground ............... Turns ground test mode on or off Head ................. Displays heading Help ................. Command help Rad .................. Displays Radio altitude Save ................. Saves System Configuration Say .................. Says Phrase from Speech Chip Sensors .............. Displays sensor data Version .............. SW Version informationFor Information on any particular command, enter the command followedby help.Save Saves all configuration jumper settings into system memory. Once the datais written to memory the saved configuration data is displayed on theterminal device. The system configuration is read on power up and comparedto the current jumpers. If the jumpers disagree with the saved memory, anError 30 will occur. Configuration jumpers can also be read by typing theConfig command.stp>saveSaving SKY497 Config Straps:Configuration P1-70, Heading. set to Ground.Configuration P1-69, Heading. set to Open.Configuration P1-68, HeadFlgSen set to High.Configuration P1-67, DR/Alt.422 set to Data Rec.Configuration P1-100, Ant.Pos. set to Top.Configuration P1-99, Ant.Type set to NY-164.Configuration P1-98, Airframe set to Fixed Wing.Configuration P1-80, AltDispType set to Open.Configuration P1-79, AltDispType set to Open.Configuration P1-78, AltDispType set to Open.Configuration P1-77, AltDispType set to Open.Say (help | 1-4) Forces the TRC to announce one of four commands, depending on thenumber (1 thru 4) entered after the command SAY. Can be used to helptroubleshoot audio output problems.say help: Displays command specific help message.say 1: Traffic Avoidance System Testsay 2: Passedsay 3: Failedsay 4: Traffic! Traffic!
SKY497Installation ManualD-6Rev. CCommands DescriptionsSensors (help) Displays the current source and value for the heading, barometric altitude,and radio altitude.Sensors help: Displays command specific help message.Sensors: Displays current sensor status.stp>sensorsHeading source: Synchro XYZHeading is Valid, 0 degreesBarometric Altitude source: Encoded InputsBarometric Altitude is Valid, 1000 feetRadio Altitude source: ARINC 429Radio Altitude is InvalidVersion Displays the versions for the IOP Code, IOP Boot, STP Code, and STP Bootsoftware. Contact customer service department for version information.stp>versionIOP Code X.XXIOP Boot X.XXSTP Code X.XXSTP Boot X.XX
SKY497Installation ManualE-1Rev. CAPPENDIX EInstallation Checkout Usingan Alternate DisplayE.1 INTRODUCTIONThis section contains installation checkout procedures for the SKY497 that is interfaced to an alternatedisplay (e.g., BFGoodrich Avionics Systems RGC250).NOTES1. This section provides checkout information for the BFGoodrich AvionicsSystems SKY497 interfaced to an Alternate Display. When interfacing to analternate display the TRC497 must have software version 1.4 or above.2. This procedure assumes familiarity with the set up and operation of the TT391Flightline Tester and RS-232 terminal device (see Appendix D). If usinganother approved tester refer to the appropriate appendices for test procedure.3. All test equipment used in completing these tests shall be calibrated inaccordance with the manufacturer's recommendations.This procedure will validate the installation and return to service of the BFGoodrich Avionics SystemsSKY497.E.2 CONTROLSOperating instructions for each alternate display are provided with the display manufacturersdocumentation.NOTEWhen using an alternate display all SKY497 functions are controlled throughthe alternate display. Each alternate display will show information consistentwith the capabilities of that particular display. Therefore, the text displayedmay be different from what is called out in this procedure. Reference thealternate display documentation for appropriate screen text.E.3 CHECKOUT PROCEDUREThe TT391 Flightline Tester simulates both a ground based secondary surveillance radar (SSR) and anairborne transponder. With the SKY497 set to GROUND TEST (i.e., the barometric altimeter is simulatedto 50,000 ft, heading simulated to 0 degrees, and the radar altimeter simulated to 2,500 ft) the TT391 willsimulate 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 abovethe traffic symbol).If the indications given in the following procedure, except for the Flightline Tester, are not obtained, referto the troubleshooting procedures in Chapter 4. If indications given for the Flightline Tester are notobtained, refer to the maintenance section of the TT391 Instruction Manual.1. Connect the RS-232 terminal device to J7 TEST port on the TRC497. Setup and turn on the terminaldevice. (See Appendix D 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. At theaircraft's instruments, verify all compass/HSI flags are valid.
SKY497Installation ManualE-2Rev. CNOTEAfter power up, it may take a couple of minutes for the altitude encoder toreturn a valid altitude to the transponder and SKY497.3. Turn SKY497 ON. After approximately thirty seconds the display will show the standby screen.NOTEIf the TRC has not been calibrated to the directional antenna, the display may showa FAIL message. Calibrate the system (see step 4 below).4. At the terminal device, type Cal <Enter>. Verify the Re-Calibration Successful! is displayed.5. Type Config <Enter>. Verify status of the configuration jumpers displayed on the screen. (You mayneed to page up in order to see all of the data. See Appendix D for example.) Once correctconfiguration is verified type Save <Enter>.Change the status of the landing gear, squat switch, and altitude sensors. Type Config <Enter> againand verify that the displayed information changed correctly (i.e., sensing of these signals).6. At the terminal device, type the commands listed below. For each command verify the sensorinformation displayed is correct (see Appendix D for examples). If the information is not correct, theconfiguration setting may be wrong or the sensor communication with the TRC may have failed.Check operation of the sensor and cables between the TRC and sensor.Arinc429 <Enter>Arinc735 <Enter>Bar <Enter>Rad <Enter>Head <Enter> (Change heading of aircraft and verify heading changes.)7. At the alternate display, perform the SKYWATCH self-test (see paragraph E.3.1).8. At the terminal device, type Ground Test <Enter>.9. At the alternate display, change the display ranges (if applicable) and verify display patterns arecorrect.10. Select the 6 nautical mile range.11. Change the altitude display modes from normal (NRM), below (BLW), and above (ABV). Verify thatthe system toggles through the altitude display modes correctly.12. Select the normal (NRM) mode.13. Position the aircraft with the nose aligned on any 90 degree heading. Avoid areas within 250 ft ofobstructions (e.g., hangers, large aircraft, control towers, etc.) where there is a potential for multipathproblems. 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 thesame distance, between 100 and 150 ft, from the aircraft.14. Position the TT391 Flightline Tester on one of the test points identified above.CAUTIONThe Flightline Tester is not weatherproof when the lid is open. Do not setupor operate the Flightline Tester in conditions of rain, sleet, etc.15. 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 staywill pop off of the lid. (The stay is the hinged part that props the lid open on the chassis).
SKY497Installation ManualE-3Rev. CNOTEThe Patch Antenna may be used without a tripod. The Patch Antenna can beheld, or secured, and pointed towards the SKYWATCH aircraft under testWITH THE MOUNTING STUD POINT TOWARD THE GROUND. This orientation iscritical.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 astandard base mounting stud threaded 1/4"-20. A typical tripod mount is shown in figure E-1.c. If the internal batteries are being utilized, proceed to sub-step f. If the Flightline Tester ACConverter 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 ACsources:.•115 Vac, 60 Hz•115 Vac, 400 Hzf. Set the Flightline Tester POWER switch to the ON position.g. Verify that the LOW indicator is not steady on (it may flash). If the LOW indicator remains on(i.e., lit), perform one of the following three options:.•Use the AC Converter Power Supply to power the unit.•Recharge the internal batteries.•Replace the internal batteries.h. Set the SELF-TEST switch to the 1030 position and verify that the 1030 indicator blinks on for1/2 second every 5 seconds.i. Set the SELF-TEST switch to the 1090 position and verify that the 1090 indicator blinks on for1/2 second every 5 seconds.j. Set SELF-TEST switch to center position (off). Set the POWER switch to the OFF position.NOTECare should be taken to ensure that the Patch Antenna is connected to TT391connector J1 and NOT J2. IF THE PATCH ANTENNA IS CONNECTED TOJ2 THE TT391 WILL NOT FUNCTION CORRECTLY.k. Connect the Flightline Tester coax cable to J3 on the Patch Antenna and to connector J1 in thechassis. (J2 should remain capped by the dust cover).Figure E-1. Typical Patch Antenna Tripod Mount
SKY497Installation ManualE-4Rev. C16. From each test point (see step 13):a. Position the TT391 Patch Antenna facing the SKYWATCH 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 TrafficAdvisory (i.e., a solid circle) at ¼ nm and Other Traffic (i.e., open diamond ) at 4.5 nm. Bothtargets will be displayed in level flight at own aircraft altitude (i.e., "00" displayed above thetraffic symbol).NOTES1. If the display reflects a gross error in target bearing, check the directionalantenna cables at TRC connectors J9 (sum port) and J11 (difference port).They may be reversed. A further indication of this condition would be atarget that moved in a counter-clockwise direction when the TT391 ismoved in a clockwise direction.2. Multiple targets or a faulty bearing may result from multipath distortion(see step 1).3. During these tests, the SKY497 may detect and display other activetargets.4. To obtain a better line of sight, it may be necessary to elevate the patchantenna.d. Set the TT391 POWER switch to the OFF. Repeat procedure from each test point. Step 16 canbe done from the last test point.NOTETo prevent SKYWATCH from tracking the movement of the test-set, it isnecessary to set the TT391 POWER switch to OFF after completing eachbearing measurement.17. Return the TT391 assemblies to their position in the aluminum carrying case.18. Restart SKYWATCH by cycling power OFF and then ON.19. Connect an oscilloscope to the suppression bus and verify that the SKY497 suppression pulse (100 µs±5 µs) exceeds +15 Vdc. If less than +15 Vdc, the suppression bus is overloaded. Check all equipmentconnected to the bus. Repair/replace the offending device.20. This completes the post installation checkout procedure.
SKY497Installation ManualE-5Rev. CE.3.1 Self Test1. Turn SKYWATCH OFF and then:a. Make sure the aircraft's transponder is in the STANDBY, ON, or ALT mode.NOTEAfter power up, it may take a couple of minutes for the altitude encoder toreturn a valid altitude to the transponder and SKY497.b. If installed, power up the radio altimeter.c. Make sure all compass/HSI flags are cleared from the aircraft's instruments.2. Turn SKYWATCH ON.3. After approximately thirty seconds, observe the standby screen and then perform the SKYWATCHself test (see alternate display operating instructions on how to perform self test).4. If SKYWATCH passes the self-test, the system will return to the standby screen and the voicemessage, "TRAFFIC ADVISORY SYSTEM TEST PASSED," will be enunciated over the cockpit audiosystem.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.NOTEAudio levels are adjusted at the aircraft audio panel. There is no internalaudio adjustment.b. Check audio connection to the TRC:1) 600-ohm audio systems should be connected to P1-92 (AUDIO_H).2) 150-ohm audio systems should be connected to P1-91 (AUDIO_L).3) Audio common is connected to P1-90 (AUDIO_C).NOTEAudio output from the TRC is transformer isolated.6. If SKYWATCH fails the self-test:a. The fail screen will be displayed.b. The voice message, "TRAFFIC ADVISORY SYSTEM TEST FAILED", will be enunciated over thecockpit audio system.c. Refer to the fault isolation procedures and error messages in Chapter 4.
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