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 2 of 3

4. WHEN INTERFACING TO AN ALTERNATE DISPLAY THE SERVICE MENU CANNOT BE ACCESSED,THEREFORE A TERMINAL DEVICE (I.e., LAPTOP) MUST BE USED FOR SETUP AND CHECKOUTOF TRC497.15. WHEN INTERFACING TO AN ALTERNATE DISPLAY THE SOFTKEY INPUTS MUST BE CONNECTED PERDISPLAY MANUFACTURER INSTRUCTIONS.SKY497Installation ManualFigure 2-2. Interconnect Wiring Without WX-1000(Sheet 1 of 2)2-3 (page 2-4 blank)Rev. CHSYNCHIHSYNCLOVSYNCHIVSYNCLOVIDEOHIVIDEOLOPWRSWHIPWRSWLODSPGND-15+15SHIELDNOTES:1. ALL WIRES TO BE 22 AWG EXCEPT WHERE NOTED.2. TP - USE TWISTED SHIELDED PAIR CABLE. TERMINATE SHIELD TO AIRFRAME5. A RADIO ALTIMETER, AIRDATA COMPUTER, OR OTHER ARINC 429 OUTPUTDEVICE MAY REPLACE ANALOG SENSORS FOR MAGNETIC HEADING, RADIOALTITUDE, OR BAROMETRIC ALTITUDE.SQUAT SWITCHLANDING GEAR POSITIONALTITUDEA1A2A4B1B2B4C1C2C4D4220161517112425191314121823227810956P101 J101SEE NOTE #6SEE NOTE #15SEE NOTE #6LOWHIGHZYX}}26 VAC REFERENCEHEADINGDIRECTIONAL GYRO COMPASSTRANSMITTERRECEIVERCOMPUTERUNITHDG_FLG+HDG_FLG-SYNC_XSYNC_YSYNC_ZSYNC_HISYNC_LO52536665645554J1 P1100DPWR+15_OUTDPWR-15_OUT7DSPLY_GND6HSYNC_OUT_HI14HSYNC_OUT_LO49VSYNC_OUT_HI48VSYNC_OUT_LO63VIDEO_OUT_HI62VIDEO_OUT_LO38PWR_SW_HI37PWR_SW_LO11TOP_BOT3NY164_NY156 99FIX_ROTOR 98DR_RX+ 9DR_RX- 8DR_TX+ 2DR_TX- 1ALT_A1 40ALT_A2 41ALT_A4 50ALT_B1 51ALT_B2 56ALT_B4 57ALT_C1 58ALT_C2 59ALT_C4 71ALT_D4 72SQUAT 88GEAR 87103993SEE TABLE "A"TPTPTPTPTPTPTPALT_COMMONTRC497WX-10003. THE SUM CABLE WILL HAVE A BLUE BAND AT EACH END. THE DIFFERENCE CABLEWILL HAVE A RED BAND AT EACH END.6. TIE THE OUTER SHIELD TO THE CONNECTOR BACKSHELL. CONNECTOR BACKSHELL IS CHASSIS GROUND.7. FOR FUTURE EXPANSION. LEAVE UNCONNECTED.HEADING INPUT CABLEDISPLAY CABLESEE NOTE #68. DELETEDWHTORNBLUWHTBLUWHTBLUBLUWHTBLUWHTBLUWHTBLUWHTBLUORNWHTBLUORNREDGRNWHTBLUWHTBLUWHTBLUWHTBLUBLUORNWHTBLUWHTBLUORNWHTBLUORNREDGRNWHTBLUWHT WHTSEE NOTE #12BLUWHT ORNORNTP BLUWHTSEE NOTE #6SFTKEY1SFTKEY2SFTKEY4SFTKEY3N/C+15V-15VSPARE_1SPARE_2SPARE_3GROUND AT SENSOR (OR POWER SOURCE).9. USE AUDIO_H FOR 600 OHM AUDIO SYSTEMS. USE AUDIO_L FOR 150 OHM AUDIO10. DO NOT INSTALL EXTERNAL ISOLATION DIODES.SEE NOTE 10SEE NOTE 10SEE NOTE 10DISPLAYSTP_CONFIG4STP_CONFIG5STP_CONFIG6 959697STP_CONFIG8STP_CONFIG7 8694ALT_COMN 81SFTKEY4_IN 82SFTKEY3_IN 83SFTKEY2_IN 84SFTKEY1_IN 856867HEADING_FLGDR_ALT422777069STEPPER_INSYNCHRO_INALT_DISP4SEE NOTE #778ALT_DISP379ALT_DISP2ALT_DISP1 80BLKYELBLUWHTBLUWHTWHTBLUWHTBLUYELBLKTPTP4321 CHASSISGND1SYSTEMS.11. SPARE PINS 16, 17, 18, 19, 20, 25, 26, 27, 28, 29, AND 30ARE NOT SHOWN AND NOT USED.HEADING VALID12. HEADING FLAG CONNECTIONS NEED TO BE CONFIGURED PROPERLY FOR YOURAIRCRAFT.DIGITIZERP/O P/OWHTBLUTP ORN ORNWHTBLUBLUWHTWHTORNBLUWHTBLUBLUWHTBLUWHTBLUORNWHTGROUNDAIRFRAMETP54556465665352SYNC_LOSYNC_HISYNC_ZSYNC_YSYNC_XHDG_FLG-HDG_FLG+KI-525 INDICATORJVSEE NOTE #6HAFLAG-FLAG+NCNCP1P2TOPBOTSTEPPERHEADINGALTERNATEINPUTSEE NOTE #13HDG FLAG +UNREG +15DRIVE MOTOR 1DRIVE MOTOR 3HDG FLAG -13. STEPPER HEADING INPUT MAY BE USED IN PLACE OF SYNCHRO HEADING.14. DELETED1312CONFIG_GNDCONFIG_GNDSEE NOTE #6VIDEO_IN_LO 35SW_RETCWS_SSSFTKEY4_OUTSFTKEY3_OUTSFTKEY2_OUTSFTKEY1_OUT43173747576DPWR+15_INDPWR-15_INDSPLY_GNDHSYNC_IN_HIHSYNC_IN_LOVSYNC_IN_HIVSYNC_IN_LOVIDEO_IN_HI466036611547245N/CN/CN/CN/CN/CN/CN/CN/CN/CGNDGNDGNDGNDSEE NOTE #12
SKY497Installation ManualFigure 2-2. Interconnect Wiring Without WX-1000(Sheet 2 of 2)2-5 (page 2-6 blank)Rev. CF3J11J7TYPE TNCDIAG_GNDDIAG_RXDIAG_TX523}TRANSMITTERRECEIVERCOMPUTERUNITJ8 P8+28VSPARE+28V_RETAIRCRAFT POWERABC16 AWGCONNECTORTRC497J10DIFFERENCEJ9SUMCONNECTORTYPE TNCCONNECTORTYPE BNCTEST ONLYSUMDIFFERENCEBLUE BANDRED BANDDIRECTIONALANTENNASEE NOTE # 3TNCBNCTNCP9P10P11 P1P2P3AIRCRAFT POWER RETURNSEE NOTE #2BIT_PROBE BIT_PROBESEE NOTE #316 AWG(11 - 34VDC)NY164/NY156TEST ONLY}232221IOP_SERIAL_TXIOP_SERIAL_GNDIOP_SERIAL_RXNOTE: FOR 14V USE 7.5 AFOR 28V USE 5.0 ASUPPRESSION I/OAUDIO COMMONSEE NOTE #6AUDIO HIGHSEE NOTE #2SEE NOTE #6TPTPTP3233344243444589GPWSARINC-429 TX 1BARINC-429 TX 1AARINC-429 RX 2BARINC-429 RX 2AARINC-429 RX 1BARINC-429 RX 1ASUP_BUSSEE NOTE #2ARINC 429DEVICE(SEE NOTE #5)(SEE NOTE #5)DEVICEARINC 429GPWSFLAGTP90AUDIO_C91AUDIO_L92AUDIO_HJ1 P1P/O P/OFUNCTIONAIRFRAMEFIXED WINGROTOR CRAFTCONFIGURATION JUMPERP1-98(OPEN)(JUMPER TO CONFIG GROUND)10ANTENNANY-164NY-156P1-9910(OPEN)(JUMPER TO CONFIG GROUND)ANTENNA POSITIONTOPBOTTOMARINC-429 ALTERNATE DISPLAYNONEARINC735 TYPE1P1-10010(OPEN)(JUMPER TO CONFIG GROUND)P1-7711(1 = OPEN)(O = JUMPER TO CONFIG GROUND)P1-7811P1-7911P1-8010HEADING INPUT SOURCENONESYNCHROP1-69 P1-701011 (1 = OPEN)(O = JUMPER TO CONFIG GROUND)STEPPER 0 1ARINC429 BUS 0 0(JUMPER TO CONFIG GROUND)(OPEN)01P1-67ALTERNATEDATA RECORDERRS422 INTERFACE*(CONFIG GROUND IS AVAILABLE AT P1-12 AND P1-13)TABLE "A"*FUTURE OPTIONHDG_FLG+ (P1-53) INDICATES VALID HEADING.)(1 = OPEN - IF LOW LEVEL INPUT ON HDG_FLG+ (P1-53)HEADING FLAG SENSELOWP1-681INDICATES VALID HEADING OR NO VALID HEADING INPUT ISAVAILABLE OR WHEN ARINC-429 INPUT IS HEADING SOURCE.)HIGH 0 (O = JUMPER TO CONFIG GROUND - IF HIGH LEVEL INPUT ON(RED)(BLUE)CAUTION: THE AIRCRAFT TRANSPONDER MUSTHAVE SHIELDED SUPPRESSION CIRCUITRYTO ENSURE THAT SKYWATCH DOES NOTDISPLAY ITSELF AS A TARGET (TA).INSTALLATION CONFIGURATION(OPTIONAL)ALTERNATEDISPLAY(SEE NOTE #4)SEE NOTE #2SEE NOTE #6SEE NOTE #9
SKY497Installation ManualFigure 2-3. Interconnect Wiring With WX-1000(Sheet 1 of 2)2-7 (page 2-8 blank)Rev. CHSYNCHIHSYNCLOVSYNCHIVSYNCLOVIDEOHIVIDEOLOPWRSWHIPWRSWLODSPGND-15+15SHIELDNOTES:1. ALL WIRES TO BE 22 AWG EXCEPT WHERE NOTED.2. TP - USE TWISTED SHIELDED PAIR CABLE. TERMINATE SHIELD TO AIRFRAME4. FUTURE OPTION.5. A RADIO ALTIMETER, AIRDATA COMPUTER, OR OTHER ARINC 429 OUTPUTDEVICE MAY REPLACE ANALOG SENSORS FOR MAGNETIC HEADING, RADIOALTITUDE, OR BAROMETRIC ALTITUDE.SQUAT SWITCHLANDING GEAR POSITIONALTITUDEA1A2A4B1B2B4C1C2C4D4220161517112425191314121823227810956P101 J101SEE NOTE #6SEE NOTE #6LOWHIGHZYX}}26 VAC REFERENCEHEADINGDIRECTIONAL GYRO COMPASSTRANSMITTERRECEIVERCOMPUTERUNITHDG_FLG+HDG_FLG-SYNC_XSYNC_YSYNC_ZSYNC_HISYNC_LO52536665645554P1100DPWR+15_OUTDPWR-15_OUT7DSPLY_GND61449486362383711TOP_BOT3NY164_NY156 99FIX_ROTOR 98DR_RX+ 9DR_RX- 8DR_TX+ 2DR_TX- 1ALT_A1 40ALT_A2 41ALT_A4 50ALT_B1 51ALT_B2 56ALT_B4 57ALT_C1 58ALT_C2 59ALT_C4 71ALT_D4 72SQUAT 88GEAR 87103993SEE TABLE "A"TPTPTPTPTPTPTPALT_COMMONTRC497WX-10003. THE SUM CABLE WILL HAVE A BLUE BAND AT EACH END. THE DIFFERENCE CABLEWILL HAVE A RED BAND AT EACH END.6. TIE THE OUTER SHIELD TO THE CONNECTOR BACKSHELL. CONNECTOR BACKSHELL7. FOR FUTURE EXPANSION. LEAVE UNCONNECTED.HEADING INPUT CABLEDISPLAY CABLESEE NOTE #6WHTORNBLUWHTBLUWHTBLUBLUWHTBLUWHTBLUWHTBLUWHTBLUORNWHTBLUORNREDGRNWHTBLUWHTBLUWHTBLUWHTBLUBLUORNWHTBLUWHTBLUORNWHTBLUORNREDGRNWHTBLUWHT WHTSEE NOTE #12BLUWHT ORNORNTP BLUWHTSEE NOTE #6SFTKEY1SFTKEY2SFTKEY4SFTKEY3SPARE_1SPARE_2SPARE_3GROUND AT SENSOR (OR POWER SOURCE).SEE NOTE 10SEE NOTE 10SEE NOTE 10DISPLAYSTP_CONFIG4STP_CONFIG5STP_CONFIG6 959697STP_CONFIG8STP_CONFIG7 8694ALT_COMN 81828384856867HEADING_FLGDR_ALT422777069STEPPER_INSYNCHRO_INALT_DISP4SEE NOTE #778ALT_DISP379ALT_DISP2ALT_DISP1 80BLKYELBLUWHTBLUWHTWHTBLUWHTBLUYELBLKTPTP4321 CHASSIS1WX-1000PROCESSORTPTP BLKYEL76SFTKEY1_OUT 75SFTKEY2_OUT 74SFTKEY3_OUT 73SFTKEY4_OUTWHTREDORNBLUTPTPTP3536VIDEO_IN_LO60VIDEO_IN_HI61VSYNC_IN_LO46VSYNC_IN_HI47HSYNC_IN_LO15HSYNC_IN_HI5DSPLY_GND24DPWR-15_INDPWR+15_INBLUWHTBLUWHTWHTORNBLUWHTBLUWHTBLUWHTBLUWHTBLUWHTBLUWHTORNBLUBLUWHTBLUWHTBLUWHTBLUWHTYELBLKSFTKEY3SFTKEY4SFTKEY2SFTKEY1WHTGRNREDORNBLU62340739222120382636934344+15-15DSPGNDPWRSWLOPWRSWHIVIDEOLOVIDEOHIVSYNCLOVSYNCHIHSYNCLOHSYNCHI5SHIELD31CWS_SS SW1P301 J301HEADING VALIDDIGITIZER4SW_RETSW2P/OWHTBLUTP ORN ORNWHTBLUBLUWHTWHTORNBLUWHTBLUBLUWHTBLUWHTBLUORNWHTGROUNDAIRFRAMETP54556465665352SYNC_LOSYNC_HISYNC_ZSYNC_YSYNC_XHDG_FLG-HDG_FLG+KI-525 INDICATORJVSEE NOTE #6HAFLAG-FLAG+NCNCP1P2TOPBOTSTEPPERHEADINGALTERNATEINPUTSEE NOTE #13HDG FLAG +UNREG +15DRIVE MOTOR 1DRIVE MOTOR 3HDG FLAG -1312CONFIG_GNDCONFIG_GNDOVER-RIDE NORMALSTORMSCOPESKYWATCHSEE NOTE #6PWR_SW_LOPWR_SW_HIVIDEO_OUT_LOVIDEO_OUT_HIVSYNC_OUT_LOVSYNC_OUT_HIHSYNC_OUT_LOHSYNC_OUT_HISFTKEY4_INSFTKEY3_INSFTKEY2_INSFTKEY1_INJ1P/OAND NOTE #8SEE NOTE #6AND NOTE #8GNDGND+15VGND-15VGNDN/CGNDN/CN/CN/CN/CN/CN/CN/CN/CSEE NOTE 148. IF THE SKYWATCH IS BEING INSTALLED TO AN EXISTING WX-1000 SYSTEM, THECABLE GROUND AT THE WX-1000 DISPLAY AND THE WX-1000 PROCESSOR MUSTBE CHANGED FROM AS SHOWN IN THE WX-1000 MANUAL TO BE AS SHOWN HERE.9. USE AUDIO_H FOR 600 OHM AUDIO SYSTEMS. USE AUDIO_L FOR 150 OHM AUDIOSYSTEMS.10. DO NOT INSTALL EXTERNAL ISOLATION DIODES.11. SPARE PINS 16, 17, 18, 19, 20, 25, 26, 27, 28, 29, AND 30ARE NOT SHOWN AND NOT USED.12. HEADING FLAG CONNECTIONS NEED TO BE CONFIGURED PROPERLY FOR YOURAIRCRAFT.13. STEPPER HEADING INPUT MAY BE USED IN PLACE OF SYNCHRO HEADING.14. INSTALLATION INSTRUCTIONS FOR THE WX-1000 ARE DETAILED IN THEWX-1000 INSTALLATION MANUAL.SEE NOTE #12IS CHASSIS GROUND.
SKY497Installation ManualFigure 2-3. Interconnect Wiring With WX-1000(Sheet 2 of 2)2-9 (page 2-10 blank)Rev. CF3J11J7TYPE TNCDIAG_GNDDIAG_RXDIAG_TX523}TRANSMITTERRECEIVERCOMPUTERUNITP8+28VSPARE+28V_RETAIRCRAFT POWERABC16 AWGCONNECTORTRC497J10DIFFERENCEJ9SUMCONNECTORTYPE TNCCONNECTORTYPE BNCTEST ONLYSUMDIFFERENCEBLUE BANDRED BANDDIRECTIONALANTENNASEE NOTE # 3TNCBNCTNCP9P10P11 P1P2P3AIRCRAFT POWER RETURNSEE NOTE #2BIT_PROBE BIT_PROBESEE NOTE #316 AWG(11 - 34VDC)NY164/NY156TEST ONLY}232221IOP_SERIAL_TXIOP_SERIAL_GNDIOP_SERIAL_RXNOTE: FOR 14V USE 7.5 AFOR 28V USE 5.0 ASEE NOTE #4SUPPRESSION I/OAUDIO COMMONSEE NOTE #6AUDIO HIGHSEE NOTE #2SEE NOTE #6TPTPTP3233344243444589GPWSSUP_BUSSEE NOTE #2ARINC 429DEVICE(SEE NOTE #5)(SEE NOTE #5)DEVICEARINC 429GPWSFLAGTP90AUDIO_C91AUDIO_L92AUDIO_HP1P/OFUNCTIONAIRFRAMEFIXED WINGROTOR CRAFTCONFIGURATION JUMPERP1-98(OPEN)(JUMPER TO CONFIG GROUND)10ANTENNANY-164NY-156P1-9910(OPEN)(JUMPER TO CONFIG GROUND)ANTENNA POSITIONTOPBOTTOMARINC-429 ALTERNATE DISPLAYNONEP1-10010(OPEN)(JUMPER TO CONFIG GROUND)P1-771 (1 = OPEN)(O = JUMPER TO CONFIG GROUND)P1-781P1-791P1-801HEADING INPUT SOURCENONESYNCHROP1-69 P1-701011(1 = OPEN)(O = JUMPER TO CONFIG GROUND)STEPPER 0 1ARINC429 BUS 0 0(JUMPER TO CONFIG GROUND)(OPEN)01P1-67ALTERNATEDATA RECORDERRS422 INTERFACE*TABLE "A"FUTURE OPTION*HDG_FLG+ (P1-53) INDICATES VALID HEADING.)(1 = OPEN - IF LOW LEVEL INPUT ON HDG_FLG+ (P1-53)HEADING FLAG SENSELOWP1-681INDICATES VALID HEADING OR NO VALID HEADING INPUT ISAVAILABLE OR WHEN ARINC-429 INPUT IS HEADING SOURCE.)HIGH 0 (O = JUMPER TO CONFIG GROUND - IF HIGH LEVEL INPUT ON(RED)(BLUE)(CONFIG GROUND IS AVAILABLE AT P1-12 AND P1-13)INSTALLATION CONFIGURATIONSHIELDED SUPPRESSION CIRCUITRY TO ENSURETHAT SKYWATCH DOES NOT DISPLAY ITSELF ASATARGET (TA).THE AIRCRAFT TRANSPONDER MUST HAVECAUTION:J8J1P/OARINC-429 RX 1AARINC-429 RX 1BARINC-429 RX 2AARINC-429 RX 2BARINC-429 TX 1AARINC-429 TX 1BSEE NOTE #6SEE NOTE #9
SKY497Installation Manual2-11Rev. C2.5 DISPLAY LOCATIONThe display should be mounted in a location easily accessible and clearly visible to the pilot. In selecting alocation, consider the following:Magnetic Effect Where possible to avoid it, the display should not be mounted within3 inches (8 cm) of an electric turn and bank indicator, as the magneticeffect of the turn and bank motor may affect the display presentation. (acommon symptom of magnetic interference is a wobbling or vibratingdisplay raster.)NOTEIf it is necessary to mount the display unit next to a device that may affectthe CRT display, magnetic shielding material can be placed around thedisplay unit. Shielding material is available from BFG Avionics Systems.Specify P/N 78-8060-5882-8 when ordering.Panel Depth Adequate depth must be available behind the instrument panel to allow forthe display, the display connector, and excess display cable. Remember, aservice loop is necessary to allow access to the display connector whenremoving the display or inserting it into the instrument panel.Cooling While the display has no special cooling requirements, it should bemounted to permit adequate ventilation.Viewing Angle The viewing angle for the CRT display is not a critical factor. The mostfavorable mounting position would be near eye level and no more thanarms length from the principle user of the instrument.2.6 CABLE REQUIREMENTS AND FABRICATIONNOTEAll wiring must be in accordance with industry accepted methods,techniques and practices.The installer will supply and fabricate all system cables. Appendix A defines the electrical characteristicsof all input and output signals and identifies the cable requirements for each signal. Refer to figure 2-2(without WX-1000) or 2-3 (with WX-1000) for interconnect wiring information. Required connectors andcontact pins are supplied in the installation kits.The length and routing of the external cables must be carefully studied and planned before attemptinginstallation of the equipment. Observe the following precautions:• Note the signal characteristics of flag lines and discrete signal inputs; an external relay may berequired to provide proper polarity or "sense" of the signals.• All cable routing should be kept as short and direct as possible.• Avoid sharp bends (do not exceed the minimum bend radius detailed in table 2-1).• 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 12inch separation).• Avoid routing cable near power sources (e.g., 400 Hertz generators, trim motors, etc.) and nearpower for fluorescent lighting.• To limit the possibility of wire chafing, it is recommended that heat shrink sleeving be installedover the wire bundle between the shield termination’s (inside the connector backshell) and theconnector cable clamp.• Observe all wiring notes on interconnect wiring diagram.
SKY497Installation Manual2-12Rev. CAfter fabricating the cables and before installing the equipment, use the interconnect diagram to verifycontinuity between each pin and its opposite end termination. Check resistance to ground between eachconnector pin. When a path to ground is detected, verify its validity.2.6.1 Antenna CablesNOTES1. Use of any cable not meeting BFG Avionics Systems specifications voids allsystem warranties.2. If you fabricate your own cables, you must verify that the attenuation andVSWR does not exceed the specified values.3. To add strain relief and alleviate stress caused by aircraft vibration, place 4-6 inches of heat shrink tubing over each antenna connector and cable.The directional antenna requires three cable assemblies; sum (Sigma Port), bit probe (Probe Port) anddifference (Delta Port). Cable attenuation for the sum and difference ports must not exceed 2.5 dB. Table2-1 identifies U. S. vendors who sell approved cables by the foot. Table 2-2 provides a cable to connectorcross reference. RG142B or equivalent may be used for the bit probe cable. Attenuation for the bit probecable must not exceed 6 dB. VSWR, on cables attached to the sum, bit probe, and difference ports, must notexceed 1.5:1.Table 2-1. Directional Antenna SIGMA and DELTA Port Cable VendorsElectrical & Mechanical Technologies (EMTEQ)1-888-879-6170262-679-6170FAX 262-679-6175Part NumberAttenuation(dB/100 ft 1.0 gHz)Weight (lb)(per 100 ft)Maximum Length(ft)Minimum BendRadius (in)PFLX195-100 10.81 2.7 21.8 0.50PFLX240-100 9.76 4.5 25.0 0.75PFLX340-100 6.3 7.2 38.2 0.88Electronic Cable Specialists1-800-327-9473414-421-5300FAX 414-421-5301Part NumberAttenuation(dB/100 ft 1.0 gHz)Weight (lb)(per 100 ft)Maximum Length(ft)Minimum BendRadius (in)352001 12.2 2.7 15 0.81311601 8.7 5.5 26 1.15311201 5.56 8.5 41 1.59310801 3.63 16.1 63 2.26PIC Wire and Cable1-800-742-3191262-246-0500FAX 262-246-0450Part NumberAttenuation(dB/100 ft 1.0 gHz)Weight (lb)(per 100 ft)Maximum Length(ft)Minimum BendRadius (in)S33141 7.2 6.5 32 1.5S55122 5.7 8.2 40 1.6S22089 3.8 18 61 2.5If cable weight is not a consideration, select lowest loss cable. Contact cable vendors before installation.New low-loss light-weight cables may be available.
SKY497Installation Manual2-13Rev. CAt the antenna, each connector has an identifying color band. To ensure the cables are connected to thecorrect 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 witha blue band. Fabricate the sum antenna cable with a TNC connector ateach end. Affix a blue marking band on each connector. At the TRC, thesum port (J9) is identified with blue marking.Probe (Bit) Port The Probe (Bit) port is the center antenna connector. Fabricate the probecable with a BNC connector at each end.Difference (Delta) Port The Difference (Delta) port is the rear antenna connector. It is marked witha red band. Fabricate the difference antenna cable with a TNC connector ateach end. Affix red marking band on each connector. At the TRC, thedifference 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 table2-1) and direct as possible.• Avoid sharp bends (do not exceed maximum bend radius detailed in table 2-1).• Avoid routing cable near power sources (e.g., 400 Hertz generators, trim motors, etc.) and nearpower for fluorescent lighting.• Avoid routing cable near ADF antenna cable (allow at least a 12-inch separation).• Observe all wiring notes on interconnect wiring diagram (figure 2-2 or 2-3).• Use pressurized bulkhead connectors certified to 30 psi or greater where needed.Table 2-2. Cable to Connector ReferenceElectrical & Mechanical Technologies (EMTEQ)1-888-879-6170262-679-6170FAX 262-679-6175Cable Part Number TNC Straight TNC Right Angle BNC Straight BNC Right AnglePFLX195-100 TMS195-1 TMR195-1 BMS195-1 BMR195-1PFLX240-100 TMS240-1 TMR240-1 BMS240-1 BMR240-1PFLX340-100 TMS340-1 TMR340-1 BMS340-1 BMR340-1Electronic Cable Specialists1-800-327-9473414-421-5300FAX 414-421-5301Cable Part Number TNC Straight TNC Right Angle BNC Straight BNC Right Angle311601 CTS922 CTR922 CBS922 CBR922311201 CTS122 CTR122 CBS122 CBR122310801 CTS022 CTR022 CBS022 CBR022352001 CTS3522 CTR3522 CBS3522 CBR3522PIC Wire and Cable1-800-742-3191262-246-0500FAX 262-246-0450Cable Part Number TNC Straight TNC Right Angle BNC Straight BNC Right AngleS33141 190308 190309 190312 190313S55122 190608 190609 190612 190613S22089 190408 190409 190412 190413
SKY497Installation Manual2-14Rev. C2.6.2 Configuration JumpersAll installation dependent selections are defined via configuration jumpers. The configuration jumpers, asdetailed in table 2-3, are installed on the TRC mating connector (P1). Figure 2-4 shows the contactarrangement for connector P1. Configuration ground is available at P1-12 and P1-13.Figure 2-4. Connector P1 Contact ArrangementTable 2-3. Configuration JumpersFUNCTION CONFIGURATION JUMPERAirframe P1-98Fixed Wing 1 (Open)Rotor Craft 0 (Jumper to Configuration Ground)Antenna P1-99NY-164 1 (Open)NY-156 0 (Jumper to Configuration Ground)Antenna Position P1-100Top 1 (Open)Bottom* 0 (Jumper to Configuration Ground)ARINC-429 Alternate Display P1-77 P1-78 P1-79 P1-80None 1 1 1 1 (1 = Open)ARINC 735 Type 1 Device** 1 1 1 0 (0 = Jumper to Configuration Ground)Heading Flag Sense P1-68LOW 1 (1 = Open - If LOW level input on HDG_FLG+ (P1-53)indicates valid heading or no valid heading input isavailable or when ARINC 429 input is heading source.)HIGH 0 (0 = Jumper to Configuration Ground - If HIGH level input onHDG_FLG+ (P1-53) indicates valid heading.)Heading Input Source P1-69 P1-70None 1 1 (1 = Open)Synchro 1 0 (0 = Jumper to Configuration Ground)Stepper 0 1ARINC 429 Bus 0 0RS422 Interface P1-67Data Recorder 1 (Open)Alternate*** 0 (Jumper to Configuration Ground)* See paragraph 2.3 Antenna Position** ARINC-735 Type 1 device is a BFGAS designation that identifies the current display driver*** Future Option
SKY497Installation Manual2-15Rev. CHeading flag logic, as detailed in table 2-4, is programmed with a jumper between P1-68 (Heading FlagSense) and configuration ground.NOTEIf the heading system has a low level flag between 1.5 VDC and 2.7 VDC(when valid), P1-68 (HEADING FLAG SENSE) should not be jumpered toground and P1-53 (HDG_FLG+) must remain unconnected.Table 2-4. Heading Flag ActionHeading Flag Logic FLAG SENSE LOW(P1-68 Open)FLAG SENSE HIGH(P1-68 Jumpered to ground.)Heading Status VALID FLAGGED VALID FLAGGEDP1-53 Relative to P1-52(HDG_FLG+ - HDG_FLG-) <1 V >5 V >5V <1V2.6.3 Display CableThe display cable connects the TRC to the WX-1000/SKY497 Display. If a WX-1000 Stormscope® WeatherMapping System is installed, the same type cable is used to connect the TRC to a WX-1000 processor.Refer to figure 2-2 (without WX-1000) or 2-3 (with WX-1000) for interconnect wiring information. Pinoutinformation relating to the WX-1000 processor and display is also provided in tables 2-5 and 2-6.Table 2-5. WX-1000/SKY497 Display ConnectionDisplay WIRE COLOR TRCFUNCTION P101 SUB-CABLE WIRE P1(Inner Jackets) 2DPWR+15_OUT 19 WHITE WHITE P1-7DPWR-15_OUT 14 WHITE ORANGE P1-6DSPLY_GND 18 WHITE BLUE P1-14HSYNC_OUT_HI 6 BLUE BLUE P1-49HSYNC_OUT_LO 5 BLUE WHITE P1-48VSYNC_OUT_HI 9 ORANGE WHITE P1-63VSYNC_OUT_LO 10 ORANGE BLUE P1-62VIDEO_OUT_HI 8 RED WHITE P1-38VIDEOOUT_LO 7 RED BLUE P1-37PWR_SW_HI 22 (SW2*) GREEN WHITE P1-11PWR_SW-LO 23 (SW2*) GREEN BLUE P1-3SFTKEY1_IN 13 BLACK WHITE P1-85SFTKEY2_IN 12 BLACK BLUE P1-84SFTKEY3_IN 25 YELLOW WHITE P1-83SFTKEY4_IN 24 YELLOW BLUE P1-82*SW2 required if WX-1000 Processor installed (see figure 2-2).
SKY497Installation Manual2-16Rev. CTable 2-6. WX -1000 Processor ConnectionWIRE COLORFUNCTION WX-1000 Processor SUB-CABLE WIRE TRC497SHIELD P301-5PWRSWHI P301-21 GREEN WHITE SW2*PWRSWLO P301-20 GREEN BLUE SW2*+15 P301-3 WHITE WHITE P1-24-15 P301-36 WHITE ORANGE P1-5DSPGND P301-38 WHITE BLUE P1-15HSYNCHI P301-6 WHITE BLUE P1-47HSYNCLO P301-23 BLUE WHITE P1-46VSYNCHI P301-40 ORANGE WHITE P1-61VSYNCLO P301-7 ORANGE BLUE P1-60VIDEOHI P301-22 RED BLUE P1-36VIDEOLO P301-39 RED WHITE P1-35SFTKEY1 P301-9 BLACK WHITE P1-76SFTKEY2 P301-26 BLACK BLUE P1-75SFTKEY3 P301-43 YELLOW WHITE P1-74SFTKEY4 P301-44 YELLOW BLUE P1-73*SW2 required if WX-1000 Processor installed (see figure 2-2).Table 2-7 identifies U.S. vendors who sell approved display cables by the foot.NOTEUse of any cable not meeting BFG Avionics Systems specifications voids allsystem warranties.Table 2-7. Display Cable VendorsU.S.COMPANYDISPLAY CABLEP/NWEIGHT(LB PER 100 FT)Dallas Avionics1-800-527-2581214-320-9776FAX 214-320-1057WX-3 10.5Electronic Cable Specialists414-421-5300FAX 414-421-53013N6715 16A.E. Petsche817-461-9473FAX 817 277 2887TZDIS 13.1PIC Wire and Cable1-800-742-3191414-246-0500FAX 414-246-0450WM25815 14.5EDMO Distributors1-800-235-3300509-535-8280FAX 1-800-828-0623FAX 509-535-8266WX-1000 Display ---Required connectors and contact pins are supplied in the installation kit.
SKY497Installation Manual2-17Rev. CThe display cable consists of the following (refer to figure 2-5).1. Twisted, shielded, jacketed triad #22 AWGColors: White, Blue, OrangeShield: Tin plated copper braid, 90% min.Jacket: FEP .007 in. min., White jacket2. Twisted, shielded, jacketed pair #24 AWGColors: White, BlueShield: Tin plated copper braid, 90% min.Jacket: FEP .007 in. min., Blue jacket3. Same as 2 except Orange jacket.4. Same as 2 except Green jacket.5. Same as 2 except Red jacket.6. Same as 2 except Black jacket.7. Same as 2 except Yellow jacket.8. Aluminized Mylar® wrap.9. #34 AWG braided shield.10. FEP Teflon® jacket .013 in. - .023 in., Red tint.11. Marker tape with Vendor P/N.Figure 2-5. Display CableThe sub-cable color-coded jackets and shields should be left on the sub-cables as close to the connectors aspractical to provide the required shielding and to identify the sub-cables.
SKY497Installation Manual2-18Rev. C2.6.4 Heading Input CableThe heading input cable connects the TRC497 to the aircraft heading system (refer to the InterconnectWiring Diagram, figure 2-2 or 2-3). This cable provides XYZ and HC aircraft heading information (or KingKCS55 stepper signals) to the TRC497. FLAG lines are also included in the heading input cable to providethe TRC497 processor with flag status (or heading valid) information.Figure 2-6 shows the TRC497 heading validation circuit of the King KCS55 that provides a heading validsignal to the TRC497.Figure 2-6. KCS55 Heading Flag ConnectionIf the heading source does not have a FLAG LO (-), the heading source FLAG HI(+) input is connected toP1-53 (HDG_FLG+) and P1-52 (HDG_FLG-) is connected to ground.If the heading system has a low level flag between 1.5 VDC and 2.7 VDC (when valid), P1-68 (HEADINGFLAG SENSE) should not be jumpered to ground and P1-53 (HDG_FLG+) must remain unconnected.Table 2-8 lists some U.S. vendors who sell the required cable by the foot.NOTEUse of any cable not meeting BFG Avionics Systems specifications voids all systemwarranties.The synchro cable consists of the following (refer to figure 2-7):1. Twisted, Shielded, Jacketed Triad #24 AWGColors: White, Blue, OrangeShield: Tin Plated Copper Braid, 90% min.Jacket: FEP .007 in. min., White2. Twisted, Shielded, Jacketed Pair #24 AWGColors: White, BlueShield: Tin Plated Copper Braid, 90% min.Jacket: FEP .007 in. min., Blue3. Same as Item 2, except Orange jacket.4. Aluminized Mylar® Wrap.5. #34 AWG braided shield.
SKY497Installation Manual2-19Rev. C6. 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 aspractical to provide the required shielding and to identify the sub-cables.Table 2-8. Heading Input Cable VendorsUSCOMPANYCABLEP/NDallas Avionics1-800-527-2581214-320-9776FAX 214-320-1057Electronic CableSpecialists414-421-5300FAX 414-521-5301A.E. Petsche817-461-9473FAX 817-277-2887EDMO Distributors1-800-235-3300805-295-6689FAX 1-800-828-0623FAX 805-295-6703PIC Wire and Cable1-800-742-3191414-246-0500FAX 414-246-0450WX-5(6.84 lb/100 ft)3N6607(7.5 lb/100 ft)TZGYR(6.84 lb/100 ft)WX-1000SYNCHROWM25807(7.2 lb/100 ft)Figure 2-7. Heading Input Cable
SKY497Installation Manual2-20Rev. C2.6.5 ARINC 429 Data CablesARINC 429 Data Input Cable. The two ARINC 429 receivers can be used to input data from other avionicssystems. The following labels are supported:LABEL FUNCTION164 Radio Altimeter (see note)203 Barometric Altitude (Uncorrected)320 Magnetic HeadingNOTEThe radio altimeter must provide full range output between 0 and 2500 feet. Not allaltimeters provide this full range output. The full range output can sometimes beobtained as a mod to the radio altimeter. Check with the specific altimetermanufacturer for compatibility and availability of modification, if necessary.Data can be input at either low speed (12.5 kHz) or high speed (100 kHz). Both transmitters (data sources)must be set to the same speed. The TRC will automatically adjust both receivers to the speed of the firstdetected incoming data.The TRC can only accept Radio Altimeter input from ARINC 429 source. The Barometric Altitude can beARINC 429 or Gilham Code. The Magnetic Heading can be ARINC 429, Synchro (XYZ) or Stepperdepending on the configuration pins and interconnect wiring. (See figure 2-2 or 2-3.)NOTEIf 429 barometric altitude is used, it should be from the same source that is interfacedwith the transponder or it must be at least as accurate as that source, i.e., ± 125 ft.Once the TRC detects valid ARINC 429 barometric altitude (Label 203) input, it will only use 429 data as asource. ARINC 429 data cables are #22 AWG (minimum) twisted, shielded cables. Cable runs should be asshort as practicable.Receiver “1” connection:ARINC-429 RX 1A -to- P1-45ARINC-429 RX 1B -to- P1-44Receiver “2” connection:ARINC-429 RX 2A -to- P1-43ARINC-429 RX 2B -to- P1-42Refer to figure 2-2 or 2-3 for detailed interconnect wiring information. Ground overall shields to theairframe at the processor end only.ARINC 429 Output Cable. The ARINC 429 transmitter can be used to output data to an external alternatedisplay (e.g., weather radar via BFGoodrich Avionics Systems RGC250). The output speed is 100 kHz.ARINC 429 data cables are #22 AWG (minimum) twisted, shielded cables. Cable runs should be as short aspracticable.Transmitter connection:ARINC-429 TX 1A -to- P1-34ARINC-429 TX 1B -to- P1-33Refer to figure 2-2 for detailed interconnect wiring information.
SKY497Installation Manual2-21Rev. C2.6.6 Altimeter Input CableNOTEOnly one altimeter input source (Gray Code or ARINC 429, not both) should beconnected. The altimeter input should be from the same source that is interfaced withthe transponder or it must be at least as accurate as that source, i.e., ± 125 ft.These signals are Gilham Code inputs coming from an airdata computer or altitude digitizer. These 10lines may be connected in parallel with the aircraft transponder. If the aircraft is equipped with selectablealtitude encoders, connect the altitude inputs so that SKY497 is always connected to the selected encoder.(Reference ARINC 572-1.)Altitude encoder connection:A1 -to- P1-40 B1 -to- P1-51 C1 -to- P1-58 D4 -to- P1-72A2 -to- P1-41 B2 -to- P1-56 C2 -to- P1-59A4 -to- P1-50 B4 -to- P1-57 C4 -to- P1-71ALTITUDE COMMON - to P1-81NOTEIf the aircraft has switched encoders that uses 28V RETURN or AIRCRAFT GROUNDas reference for encoder selection, then ALTITUDE COMMON should be leftunconnected.For each connection use #22 AWG (minimum). Cable runs should be as short as practicable. Refer to figure2-2 or 2-3 for detailed interconnect wiring information.2.6.7 Audio Alert Output CableAudio output from the TRC is directly compatible with industry standard aircraft audio panels. There is nointernal audio adjustment. Audio levels are adjusted at the aircraft audio panel. This output is disabledwhen a GPWS alarm is detected and remains disabled until the warning clears.Use #22 AWG (minimum) twisted shielded pair cable for lengths up to 30 ft. . Cable runs should be asshort as practicable.• Connect 600-ohm audio systems to P1-92 (AUDIO_H).• Connect 150-ohm audio systems to P1-91 (AUIDO_L).• Audio common is connected to P1-90 (AUDIO_C)Refer to figure 2-2 or 2-3 for detailed interconnect wiring information.2.6.8 Suppression Bus I/OThe TRC497 outputs (P1-89) a 100 µs (± 5 µs) suppression pulse on the aircraft suppression bus. Inaddition, the TRC497 receives suppression signals from all other devices on the suppression bus (e.g.,transponder, DME). (Reference ARINC 735-2 and DO-197.)CAUTIONThe aircraft transponder must have suppression circuitry to ensure thatSKYWATCH does not paint itself as a target (e.g., TA).Any size low capacitance shielded cable may be used. Cable runs should be as short as practicable and theshields should be grounded at both ends of the cable. Refer to figure 2-2 or 2-3 for detailed interconnectwiring information.
SKY497Installation Manual2-22Rev. C2.6.9 Ground Proximity Warning System (GPWS) InputThis input senses a GPWS alarm and temporarily disables the audio alert output until the warning clears.The input can be either a constant flag signal or an alternating flag output. The flag must be cleared forfive (5) seconds before the TRC accepts a “NO ALARM” condition and restores audible alerts.NOTES1. If the aircraft is equipped with GPWS, it must be connected to the TRC.2. If the aircraft is not equipped with GPWS, leave this input unconnected..For the GPWS input (P1-32) line, use #22 AWG (minimum) unshielded cable. Routing and length are notcritical to system operation.2.6.10 SKYWATCH/Stormscope Mode SwitchThe SKYWATCH/Stormscope mode switch (SW1) is required only if a WX-1000 Stormscope WeatherMapping System is installed. This switch permits the flight crew to switch the display between theSKY497 and WX-1000. If a TA (Traffic Advisory) is detected in the Stormscope mode, the display willswitch to the SKYWATCH mode. Refer to figure 2-3 for interconnect wiring information. Any generalpurpose SPST toggle switch (3 Amp @ 28 VDC) may be used. Display mode switch cable routing and lengthare not critical to system operation. Mount the switch at a location easily accessible to the pilot.2.6.11 WX-1000 Maintenance SwitchON/OFF control and display brightness is controlled through the OFF/BRT switch located on the WX-1000display. An external NORMAL/OVERRIDE control over-ride switch (SW2) is required only if a WX-1000Stormscope Weather Mapping System is installed. The override switch enables the SKYWATCH to bepowered-up if the WX-1000 processor has been removed for maintenance. During normal operation theswitch should remain in the NORMAL position and moved to OVERRIDE only if the WX-1000 processorhas been removed for service or if it is necessary to access the WX-1000 service menu. Refer to figure 2-3for interconnect wiring information. Any general purpose DPDT toggle switch (3 Amp @ 28 VDC) may beused. The maintenance switch cable routing and length are not critical to system operation. The switch canbe located in the avionics bay near the WX-1000 processor.2.6.12 Squat Switch InputThis signal line is to be connected to the squat switch to sense when the aircraft is on the ground. If theaircraft is not equipped with a squat switch, it is recommended that a squat switch be installed.For the SQUAT input (P1-88) line, use #22 AWG (minimum) unshielded cable. Routing and length are notcritical to system operation.If a squat switch is not available, this input could be tied to an airspeed switch inline with the pitot systemas an alternate input for the squat switch. In this configuration care should be taken to ensure the switchis set to trigger at a speed consistent with take-off and landing.On helicopter installations with skids, and a squat switch is not available, this input can be tied to thecollective switch. In this configuration care should be taken to ensure the switch is connected to provide aground when the aircraft is on the ground and open when the aircraft is airborne.If it is not possible to install a squat switch, airspeed switch, or collective switch ground this input. Withthis configuration the pilot must press soft-key (4), labeled →→→→OPR or →→→→STB, to toggle the system in andout of standby. To display traffic, the pilot will have to switch out of standby by pressing the →→→→OPRbutton.With a squat switch installed, SKYWATCH will automatically switch out of standby (i.e, ABV/6nm) 8 to 10seconds after takeoff and switch back to standby 24 seconds after landing. A squat switch would alsoprevent the pilot from placing SKYWATCH in standby (i.e., pressing the →→→→STB button) while the aircraftis in-flight.
SKY497Installation Manual2-23Rev. C2.6.13 Landing Gear Switch InputThis signal line is to be connected to the landing gear switch to sense the position of the landing gear.For the GEAR input (P1-87) line, use #22 AWG (minimum) unshielded cable. Routing and length are notcritical to system operation.If the aircraft does not have a landing gear switch input (e.g., fixed-gear aircraft), leave this inputunconnected. With this configuration, if no ARINC 429 compatible radio altimeter is installed, the systemwill default to the highest TA sensitivity level (level B) and audio TA announcements (i.e., “traffic, traffic”)will not be inhibited during takeoff and landing.2.6.14 Power CableThe power cable (not supplied) runs from the aircraft circuit breaker panel to the TRC. The power cable isconnected to the TRC using the MS3126F12-3S connector included in the TRC installation kit. For thepower cable, use #16 AWG (minimum) twisted shielded pair cable (Beldon 83322, Alpha 2826/2, orequivalent).NOTEFor 14 V aircraft systems a 7.5 A circuit breaker is required and for 28 Vsystems a 5 A circuit breaker is required. The circuit breaker may be selectedto match components of the individual aircraft.The positive wire (P8-A) connects to the circuit breaker. The negative wire (P8-B) connects to the aircraftpower return. Terminate the shield to airframe ground at the power source. Power cable routing andlength are not critical to system operation.2.7 ANTENNA INSTALLATIONThe following paragraphs provide installation details for directional antenna. The installer must ensurethe immediate antenna installation area is clean and prepared so that the antenna is electrically bonded(metal-to-metal contact) to the aircraft. To provide optimum bonding through the mounting holes, preparethe surfaces with Alodine No. 1001.To facilitate mounting to the airframe, the dimensions shown in figure 2-8 can be used to locate and drillmounting and connector access holes. Connection to the antenna should be made in accordance with thesystem interconnect diagram (figure 2-2 or 2-3).NOTEA 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 correctantenna connector. Each connector/cable has a matching color band (see note para 2.6.1).2. Attach the antenna to the aircraft, with the special adapter plate and o-ring, using 10-32 hardwareprovided. See figure 2-9.NOTES1. When mounting the antenna remove the O-ring from the bag and install itin the O-ring groove on the bottom of the antenna.2. The antenna must be sealed to the airframe. For pressurized aircraft, usea sealant that meets the requirements of SAE AMS-S-8802 such asFlamemaster® CS3204 class B. For non-pressurized aircraft, use a non-corrosive sealant that meets the physical requirements of MIL-A-46146such as General Electric RTV162.
SKY497Installation Manual2-24Rev. CFigure 2-8. Antenna Mounting HolesFigure 2-9. Directional Antenna Installation
SKY497Installation Manual2-25Rev. C2.8 TRC MOUNTING TRAY INSTALLATIONTo accommodate different space limitations, the standard TRC mounting tray (P/N 805-10870-001) can bechannel or flat mounted. To flat mount the tray, simply remove the eight 6-32 (Phillps) screws that securethe channel to the tray. The ruggedized TRC mounting tray (P/N 805-10870-003), required for rotorcraftinstallations, must be channel mounted.Figure 2-10. Mounting Holes for Standard Mounting Tray, P/N 805-10870-001Figure 2-11. Mounting Holes for Ruggedized Mounting Tray, P/N 805-10870-003
SKY497Installation Manual2-26Rev. C1. Position tray at the installation location.2. Determine centers for mounting holes, and drill for required fasteners. See figure 2-10 (standard tray)or 2-11 (ruggedized tray).3. Secure tray in place using suitable 8-32 (channel mount) or 6-32 (flat mount) hardware.2.9 TRC INSTALLATIONCAUTIONBefore placing the TRC into its mounting tray, de-energize or disconnect allpower and signal sources and loads used with the SKY497 system.1. Slide the TRC into the mounting tray (see figure 2-12). Ensure that the rear hold-down pins on themounting 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 theself-locking hold-down knobs.3. Connect the three antenna inputs to the connectors on the front panel.a. Connect the Sum port antenna connector (P9 - a TNC connector identified with a blue band) toconnector J9 (identified with blue marking).b. Connect the Probe (Bit) port antenna connector (P10 - a BNC connector identified with a blackband) to connector J10.c. Connect the Difference (Delta) port antenna connector (P11 - a TNC connector identified with ared band) to connector J11 (identified with red marking).4. Connect I/O Signal Cable (P1 - a 100-pin connector) to connector J1.5. Connect the power cable (P8 - a three pin connector) to connector J8.
SKY497Installation Manual2-27Rev. CFigure 2-12. TRC497 Installation
SKY497Installation Manual2-28Rev. C2.10 MOUNTING THE WX-1000/SKY497 DISPLAYThe display mounts in a standard 3ATI panel cutout (figure 2-13). The unit may be mounted from the frontor rear. The following paragraphs describe the installation procedure.2.10.1 Panel Cutout.Refer to figure 2-13 for the panel cutout and mounting hole dimensions. Drill and punch the requiredholes. The instrument panel cutout is a standard 3ATI.Figure 2-13. Instrument Panel Cutout and Mounting Holes
SKY497Installation Manual2-29Rev. C2.10.2 Display InstallationFigure 2-14 shows a typical display installation. The display can be mounted to the instrument panel fromthe front or from the rear. An optional mooring clamp is available for increased stability in high-vibrationenvironments.Figure 2-14. Display InstallationUse rivnuts® or a mooring clamp to secure the display to the instrument panel.NOTE1. 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 thedisplay is placed.3. A 3ATI mooring clamp is also available from:MSP, IncorporatedR.R. 4, Box 383ANashville, Indiana 47448Tel. (812) 988-6623 or FAX (812) 988-6181
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SKY497Installation Manual3-1Rev. CCHAPTER 3INSTALLATION CHECKOUT3.1 INTRODUCTIONThis section contains instructions for using the BFGoodrich Avionics Systems TT391 Flightline Tester todo post-installation checkout of the BFG Avionics Systems SKY497. Detailed setup, operation andmaintenance information for the TT391 Flightline Tester is provided in the TT391 Instruction Manual.NOTES1. This procedure assumes familiarity with the set up and operation of the TT391Flightline Tester.2. All test equipment used in completing these tests shall be calibrated inaccordance with the manufacturer's recommendations.3. This section provides checkout information for the BFGoodrich AvionicsSystems SKY497 using the WX-1000 Display. If using an alternate display useAppendix E for installation checkout.4. Checkout of the WX-1000 processor should be done in accordance with theprocedures detailed in the WX-1000 Installation Manual.This procedure will validate the installation and return to service of the BFGoodrich Avionics SystemsSKY497.3.2 CONTROLSAll operating controls are located on the front of the indictor. Figure 3-1 shows the locations of the controls.Complete operating instructions for the SKY497 are provided in the SKY497 Pilot's Guide supplied witheach system.Figure 3-1. 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 Manual3-2Rev. C3.3. 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. 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 3-2. Afterstart-up screen appears, rotate the OFF/BRT switch. Verify that clockwise rotation increases displaybrightness.Figure 3-2. Start-up ScreenAfter approximately thirty seconds the display will show the STANDBY screen (see figure 3-3).NOTEIf the TRC has not been calibrated to the directional antenna (see step 3)the display may show a “SKY497 FAILED” message.
SKY497Installation Manual3-3Rev. CFigure 3-3. 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).WARNINGVerify displayed antenna position matches antenna location on the aircraft(top or bottom). Failure to do so could give incorrect traffic bearing.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 and do the SKYWATCH self-test (see para 3.4).7. Turn SKY497 OFF, return to the Service Menu and select Ground Test (see paragraph 4.4.4).8. 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.9. Select the 6 nautical mile range.10. 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).11. Select the NRM (normal) mode.
SKY497Installation Manual3-4Rev. C12. 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.13. Position the TT391 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.14. 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).NOTEThe 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 3-4.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 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 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).
SKY497Installation Manual3-5Rev. CFigure 3-4. Typical Patch Antenna Tripod Mount15. From each test point (see step 12):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 15 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.16. Return the TT391 assemblies to their position in the aluminum carrying case.17. Restart SKYWATCH by cycling power OFF and then ON.18. Connect an oscilloscope to the suppression bus and verify that the SKY497 suppression pulse (100 µs±5 µs) exceeds +15 V dc. If less than +15 V dc the suppression bus is overloaded. Check all equipmentconnected to the bus. Repair/replace the offending device.19. This completes the post installation checkout procedure.
SKY497Installation Manual3-6Rev. C 3.4 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. 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 (1)).4. The display should present a screen similar to that shown in figure 3-5.Figure 3-5. Self Test Screen5. If SKYWATCH passes the self-test, the system will return to the STANDBY screen (see figure 3-3)and the voice message, "TRAFFIC ADVISORY SYSTEM TEST PASSED," will be enunciated over thecockpit 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.NOTEAudio levels are adjusted at the aircraft audio panel. There is no internalaudio adjustment.
SKY497Installation Manual3-7Rev. Cb. 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.7. If SKYWATCH fails the self-test:a. The "SKY497 Failed" screen (see figure 3-6) with an error message indicating the type of failurewill be displayed.b. The voice message, "TRAFFIC ADVISORY SYSTEM TEST FAILED", will be enunciated over thecockpit audio system.c. Soft-key (1) will be labeled TEST. To re-test, press soft-key (1).d. Soft-keys (2), (3), and (4) are not used.Figure 3-6. Self Test Failed Screene. Refer to the fault isolation procedures in Chapter 4.
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