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S-TEC 9524 Breakout Box Service Manual - For Sale or

1. SHIELD ROLL SERVO T PIERSON REV PER FECO 922 3 15 87 M NEWSON ADD NOTE 8 PER EO 4466 3 31 94 T PIERSON REMOVE NOTE 8 PER FECO 1728 4 4 95 R TUCKER J FROST M KEIRNAN REV PER EO 7572 2 24 99 REV PER 8026 6 15 99 PIERSON RATE GYRO SIGNAL BLACK RATE GYRO REFERENCE WHITE GYRO TACH CREEN GROUND 9 9 SHIELD 18 TURN COORDINATOR 4 D m m 2 tla EXISTING CIRCUIT BREAKER OPTIONAL GPS GAIN SELECT BATTERY BUS HEADING SIGNAL DC AIRFRAME HEADING SIGNAL DC GROUND HEADING SIGNAL DG ORANGE OPTIONAL SIGNAL REFERENCE GREEN DIRECTIONAL GYRO EXCITATION REFERENCE WHITE SEE NOTE 4 GROUND SHIELD SWITCH PICTORIAL CIRCUIT GROUND SHIELD BREAKER 4 RIGHT WH ITE TO VOR LOC CONVERTER BATTERY BUS LEFT w WHITE SEE NOTES 2 amp 5 14 28 VOLTS RED TEST SWITCH
2. GUIDANCE AIRFRAME GND _ COMPUTER ROLL LOGIC RESET BRN FAIL BLK REG 10 WHT LOC SWITCH SOFT LIGHT LOGIC RED MODE ORN ROLL CENTER YEL APPROACH LOGIC GRN ROLL SOL LOGIC BLUE HOG MODE CAP LIGHT LOGIC GRAY REV MODE wur 50 RAD WINDOW WHT BLK GYRO TACH wHT BRN ROLL BAR 1O WHT GRN ROLL BAR HI WHT YEL JUMPER To FO FLAG LO WHT ORN DISABLE NAV FAL LIGHT SEE NOTE 9 SEE NOTE 5 2 SOLENOID ORN LOC SWITCH BLK RADIO RIGHT WHT L RADIO LEFT BLUE RECENER NAV FLAG CONVERT R NAV FLAG YEL GYRO TACH GRN GYRO SIGNAL WHT GYRO SIGNAL BLK BATT BUSS EXCITATION En AIRFRAME GNO DC CRS F DC HDG DC RETURN AC CRS SIGNAL RED EXCITATION REF WHT SIGNAL ORN SIGNAL REF GRN SOLENOID RED SOLENOID GND AK MOTOR 1 GRN MOTOR 2 WHT NOTES
3. ORANGE AIRCRAFT GROUND BLACK AIRFRAME TR T Ts YELLOW INST OR RADIO INSTRUMENT LIGH LIGHT DIMMER OPTIONAL AUTOPILOT DISCONNECT SWITCH DISCONNECT SWITCH 9 CREEN N C SPST MOMENTARY CONTACT 14 28 V DISC SW ALT SW WHITE E CM SEE NOTE 6 ALTITUDE SWITCH BLUE l NA M OPTIONAL ALTITUDE ENGAGE DISENGAGE SWITCH SEE NOTE 7 N O SPST MOMENTARY CONTACT SEE NOTE 8 SEE NOTE 6 ALTITUDE SIGNAL GREEN ALTITUDE GROUND BLACK TRANSDUCER 10 VOLTS RED GROUND SHIELD PITCH MOTOR 1 YELLOW PITCH MOTOR 2 PITCH SOLENOID m RED PITCH SOLENOID GROUND BLACK GROUND SHIELD UP TRIM SWITCH BLUE DOWN TRIM SWITCH ORANGE GROUND TRIM SWITCH WHITE PITCH SERVO 7 ADDITIONAL WIRING REQUIRED TO PITCH SECTION SYSTEM 50 24 NOTES 1 FIELD FABRICATED WIRING TO BE 22 GA MINIMUM UNLESS OTHERWISE NOTED AND 9 PIN 26 SWITCHED TO GROUND ENABLES GPS TRACK GAIN SETTING ON LATER MOD
4. rao 42 Ho IN BATT BUS AIRFRAME GROUND DIRECTIONAL AC CRS SIGNAL GYRO EXCITATION REF AC HDG SIGNAL SIGNAL REF NOTE 5 ROLL SERVO SOLENOID SOLENOID GND MOTOR 1 MOTOR 2 NOTES FIELD FABRICATED WIRING TO BE 22 GA MIN UNLESS NOTED AND MUST MEET OR EXCEED THE REQUIREMENTS OF MIL W 22759 16 OE BLACK AMD A VIOLET WIRE IN PLACE OF WHITE IN THIS 7 PRI REFER TO RADIO MANUFACTURERS SERVICE AND OR INSTALLATION MANUAL CONDUCTOR CABLE FOR SPECIFIC INTERCONNECT INFORMATION REMOVE JUMPER ACROSS PINS 18 amp 34 OF THE RFGC CONNECTOR WHEN AN HSI IS INSTALLED JUMPER IS FOR D G ONLY PIN CONNECTIONS SHOWN ARE FOR D G ONLY WHEN AN HSI IS INSTALLED STEC Corporation REFER TO HEADING SYSTEM INTERCONNECT DETAILS DWG NO 1003 AND HSI MANUFACTURERS SERVICE INSTALLATION MANUAL FOR INTERCONNECT INFORMATION DRAWN R WADE 11 6 79 a One S TEC Way CHECKED p GOETTEL 1 18 80 Municipal Airport Mineral Wells Tx 76067 9236 SOME NAV CONVERTER INDICATORS DO NOT PROVIDE NAV FLAG OUTPUTS FOR 1 mc AUTOPILOT USE WHEN USED WITH THESE TYPE CONVERTER INDICATORS THE 1 18 80 NAV FAILURE WARNING FUNCTION OF THE AUTOPILOT MUST BE DISABLED THIS MAY APPROVE SCHEMATIC WIRING BE CCS IN THE pus FLIGHT GUIDANCE CONNECTOR ADD A JUMPER EE INTERCONNECT SYSTEM 60 1 BETWEEN PIN
5. 34 Verify that the A C control wheel turns to the left 35 Engage the A P HDG mode to stop the A C control wheel 36 Adjust the OBS for a 100 leftward deflection of the Left Right needle from center 37 Engage the A P REV mode 38 Verify that the A C control wheel turns to the right 39 Engage the A P HDG mode to stop the A C control wheel 40 Adjustthe OBS for a centered Left Right needle Altitude Channel Test 41 Move the A C control wheel until the elevator is in the neutral position 42 Engage the A P ALT mode 43 Press and hold the A P UP Switch 44 Verify that the A C control wheel moves in the aft direction 45 Release the A P UP Switch 46 Press and hold the A P DN Switch 47 Verify that the A C control wheel moves in the fore direction Note There will be a slight delay in this movement as the A C control wheel decelerates aft to the null 48 Release the A P DN Switch 49 Engage the A P VS mode to stop the A C control wheel Vertical Speed Channel Test 50 Press and hold the A P UP Switch 51 Verify that the A C control wheel moves in the aft direction 52 Release the A P UP Switch 53 Press and hold the A P DN Switch 54 Verify that the A C control wheel moves in the fore direction Note There will be a slight delay in this movement as the A C control wheel decelerates aft to the null 55 Release the A P DN Switch 56 Engage the A P ALT mode to stop the A C control wheel Ist
6. 57 58 59 Set the A P Trim Master Switch to the ON position Apply maximum aft pressure to the A C control wheel Verifv that a After 3 seconds the A C trim wheel begins to run nose down with increasing speed and TRIM v becomes annunciated on the A P b After 7 seconds TRIM v flashes Apply maximum fore pressure to the A C control wheel Verify that a After 3 seconds the A C trim wheel begins to run nose up with increasing speed and TRIM becomes annunciated on the A P b After 7 seconds TRIM flashes Apply aft pressure to the A C control wheel until the A C trim wheel stops Press either fore or aft on both segments of the A P Manual Electric Trim Switch and then release Verify that the A P disconnects as follows RDY flashes on the A P and the audible alert sounds for 5 seconds after which RDY alone remains annunciated Ist Ed May 11 2001 MEGGITT AVIONICS S TEC FLIGHT LINE SERVICE MANUAL FOR RATE BASED AUTOPILOTS 61 Press aft and maintain pressure on both segments of the A P Manual Electric Trim Switch 62 Verify that the A C trim wheel runs nose up at full speed and TRIM flashes 63 Press and hold the A P Disconnect Trim Interrupt Switch 64 Verify that the A C trim wheel stops 65 Release the A P Disconnect Trim Interrupt Switch 66 Verify that the A C trim wheel resumes running nose up at full speed 67 Release the A P Manual Electric Trim Switch 68 Verify that the A
7. ALTITUDE VERTICAL Al SPEED SELECTOR 20 GA MIN NOTE t1 V C e z e NOTES 1 FIELD WIRING T MINIMUM INI THER NOTI MUST MEI Y 9 Mi wo 3 18 oteo 2 GA OR EXCE REQUIREMENTS MiL W 2275 REFER TO RADIO MANUFACTURERS SERVICE AND OR INSTALLATION MANUAL FOR SPECIFIC INTERCONNECT INFORMATION REFER TO WIRING SECTION OF SPECIFIC AIRCRAFT INSTALLATION BULLETIN FOR FLAP COMPENSATION WIRING CONNECT A P A TO PIN 1 OF THE ANNUNCIATOR CONNECTOR IF A P A IS 14VDC AND TO PIN 2 IF A P A IS 28VDC INSERT JUMPER BETWEEN PINS 1 AND 2 OF THE OPTIONAL FLAP COMPENSATION CONNECTOR IF AN ALTITUDE VERTIAL SPEED SELECTOR ALERTER IS INSTALLED JUMPER BETWEEN PIN 7 AND 6 FOR 14 VOLT OPERATION OR BETWEEN PIN 7 AND PIN 14 FOR 28 VOLT OPERATION USE P N 3536 2 POLE 3 POSITION TOGGLE SWITCH WHEN INSTALLING A FLIGHT DIRECTOR A PICTORIAL IS DRAWN OF A 3536 BECAUSE OF ITS COMPLEXITY IF A FLIGHT DIRECTOR IS NOT INSTALLED P N 3520 SPOT SWITCH MAY BE USED IF TRIM OPTION IS NOT INSTALLED PIN 50 OF P2 MUST BE CONNECTED TO THE AIRCRAFT A VIA ANOTHER CIRCUIT BREAKER 5 AMP MAX OTHER THAN THE AUTOPILOT CIRCUIT BREAKER PIN CONNECTIONS SHOWN AND JUMPER BETWEEN PINS 9 amp 10 OF PI ARE FOR S TEC D G 6401 6406 WHEN HSi IS INSTALLED REMOVE THE JUMPER BETWEEN PINS 9 amp 10 OF REFER TO HEADING SYSTEM INTERCONNECT DETAILS DWG NO 1094 AND HSI M
8. Ist Ed May 11 2001 BENDIX IN 831A P N 400172 8504 8505 T C R C IN 851A 6 AC HOG SIG 18 CT ROTOR H 4 EXC 51 BOOTSTRAP ROTOR H L3 SIG REF 5 19 HOG CT ROTOR C 35 33 BOOTSTRAP ROTOR C STATOR Z BENDIX HSD 880 T C R C 881 d HOG CRS RETURN J 1 1 COLLINS HSI 331A 6P 6R 1 HDG ERROR CT X AZIMUTH XMTR X 4 ERROR CT AZIMUTH XMTR C HOG ERROR CT H 40 AZIMUTH XMTR H T C R C COLLINS 101 T C R C 331A 3G 4 EXC A HOG SYNCHRO ROTOR H HDG SIG HOG SYNCHRO STATOR X Es 9 SIG REF 7 18 SYNCHRO STATOR Y 35 E SYNCHRO ROTOR 5 HSI 6445 INDICATOR T C R C 6443 INDICATOR 1 4 EXC BOOTSTRAP 1 ROTOR H 6 HDG SIG 3 w SIG REF 55 10 CT STATOR X 118 BOOTSTRAP 1 STATOR 2 HDG CT STATOR 7 AERONETICS MODEL 8000 T C R C MODEL 8130 HS 4 EXC 4 BOOTSTRAP ROTOR H 5 SIG HDG CT ROTOR H 3 9 SIG REF BOOTSTRAP ROTOR C 35 44 HOG CT ROTOR riu BOOTSTRAP STATOR X a HOG CT STATOR X BOOTSTRAP STATOR Y 3 CT STATOR Y BOOTSTRAP STATOR Z 16 STATOR Z NARCO 5 100 1005 T C R C HSi 100 100S P201 4 3 L5 SANDEL SN3308 T C R C P2 fal D C HDG SIG Hi DC HDG DATUM 7 1 5 D C HDG SIG LO ss i PI SIGNAL GND NOTE SANDEL INDICATOR MUST BE CONFIGUREO
9. 1 FIELD FABRICATED WIRING TO 22 GA UNLESS OTHERWISE NOTED AND MUST MEET OR EXCEED THE REQUIREMENTS OF MIL W 22759 16 REFER TO RADIO MANUFACTURERS SERVICE AND OR INSTALLATION MANUAL FOR SPECIFIC INTERCONNECT INFORMATION REMOVE JUMPER ACROSS PINS 18 amp 34 OF THE RFGC CONNECTOR WHEN HSi 15 INSTALLED JUMPER 15 FOR D G ONLY PIN CONNECTIONS SHOWN ARE FOR 5 D G ONLY WHEN AN HSI OR ALTERNATE D G IS INSTALLED REFER TO HEADING SYSTEM INTERCONNECT DETAILS DWG NO 1003 ANO HS MANUFACTURER S SERVICE INSTALLATION MANUAL FOR INTERCONNECT INFORMATION SOME NAY CONVERTER INOICATORS DO NOT PROVIDE NAV FLAG OUTPUTS FOR AUTOPILOT USE WHEN USEO WITH THESE TYPE CONVERTER INDICATORS THE NAV FAILURE WARNING FUNCTION OF THE AUTOPILOT MUST BE DISABLED THIS MAY ACCOMPLISHED IN THE ROLL FLIGHT GUIDANCE COMPUTER CONNECTOR ADD A JUMPER BETWEEN PIN 24 NAV FLAG AND PIN 5 REG 10 V AND A JUMPER BETWEEN PIN 6 NAV FLAG AND PIN 26 SIGNAL REFERENCE WIRE TO PIN 54 OF THE PITCH FLIGHT GUIDANCE COMPUTER IS PROVIDED FOR INSTALLATION OF ALTITUDE VERTICAL SPEED SELECTOR OPTION REFER TO WIRING SECTION OF SPECIFIC AIRCRAFT INSTALLATION BULLETIN FOR FLAP POSITION INDICATOR WIRING THIS CONNECTOR CONTAINS PROVISIONS FOR FLIGHT DIRECTOR STEERING HORIZON AND OR ALTITUDE VERTICAL SPEED SELECTOR OPTION REFER TO SPECIFIC OPTION INSTALLATION BULLETIN FOR WIRING INFORMATION SOME INSTALLATIONS MAY ALTERNATELY HAVE A B
10. 2 1c System 55 55 550 Ist Ed May 11 2001 2 7 MEGGITT AVIONICS S TEC FLIGHT LINE SERVICE MANUAL FOR RATE BASED AUTOPILOTS Fig 2 1d System 65 2 8 Ist Ed May 11 2001 MEGGITT AVIONICS S TEC FLIGHT LINE SERVICE MANUAL FOR RATE BASED AUTOPILOTS SECTION 3 FUNCTIONAL GROUND TESTS Ist Ed May 11 2001 3 1 MEGGITT AVIONICS S TEC FLIGHT LINE SERVICE MANUAL FOR RATE BASED AUTOPILOTS 3 1 3 2 3 3 3 4 35 3 0 3 7 3 8 39 3 10 3 11 3 12 3 2 Table of Contents Functional Ground Test for System 20 sess 3 3 Functional Ground Test for System 30 ceteri de o OE ERE EU PR Eco HEP Ere ier 3 5 Functional Ground Test for System 30 3 7 Functional Ground Test for System 40 sis uiis etes n ed rie Am p 3 8 Functional Ground Test for System 50 sse enne inneren 3 10 Functional Ground Test for System 55 3 14 Functional Ground Test for System 55 3 17 Functional Ground Test for System 550 3 21 Functional Ground Test for System 60 1 325 Functional Ground Test for System 60 2 3 27 Functional Ground Test for System 65 3 31 Functional Ground Test for System 60 PSS 222 0 0 1 0 00001 3 35 Ist Ed May 11 2001 MEGGITT AVIONICS S TEC FLIGHT LINE SERVICE MANUAL FOR RATE BASED AU
11. BLK eS vs XDCR 10v RED i 1 HDG SYS OPTIONS SHIELD JPR FOR NO DG SIG REF GRN EXC REF WHT PITCH SERVO AC HDG ORN SOL RED SHIELO SOL GND BLK MOTOR 1 YEL SOL RED b MOTOR 2 GRN SOL GND BLK MOTOR 1 MOTOR 2 WHT DN SW ORN SHIELO SHIELD AIRFRAME 9 i 27775 GND BLK uP Sw BLU SW GND WHT RBS ADDITIONAL WIRING TO ADO PITCH SECTION NOTES 1 FIELD FABRICATED WIRING TO BE 22 GA MINIMUM UNLESS OTHERWISE NOTED AND MUST MEET OR EXCEED THE REQUIREMENTS OF MIL W 22759 16 ALL WIRING TO BE ROUTED amp SECURED IN ACCORDANCE WITH AC43 13 1A CHAPTER 11 SECTION 7 2 REFER TO RADIO MANUFACTURER S SERVICE AND OR INSTALLATION INFORMATION FOR SPECIFIC INTERCONNECT INFORMATION 3 REMOVE JUMPER ACROSS PINS 20 amp 21 OF THE TURN COORDINATOR ROLL COMPUTER CONNECTOR WHEN OPTIONAL DIRECTIONAL GYRO OR A HEADING SYSTEM iS BEING INSTALLED 4 WHEN A HEADING SYSTEM IS INSTALLED REFER TO HEADING SYSTEM INTERCONNECT DETAILS DWG NO 10114 amp HEADING SYSTEM MANUFACTURERS SERVICE AND OR INSTALLATION INTERCONNECT INFORMATION REFER TO DWG NO 0570 FOR MODIFICATION REQUIRED TO ROLL BOARD OF TURN COORDINATOR ROLL COMPUTER 5 THE A P DISCONNECT 1S AN OPTIONAL COMPONENT IF THE A P DISCONNECT IS N
12. BLU UP Sw WHT BRN 10 VOC RED SW GRN YO Sw GNO ROLL CNTR POT BLK ROLL CENTER WHT RED ALT SW vs Sw YEL FD SW GRAY AC EL LIGHT VIO AC EL LIGHT BLU Gc s 2 m IE 28 29 39 E 32 35 25 Le E 39 49 so 4 21 23 24 a m a 27 21181812 Ist Ed May 11 2001 P O ANNUNCIATOR 50 PIN 8 SEE 9 20 GA MIN p 20 GA MIN 47 AIRFRAME GNO AIRFRAME GNO WHT ROLL LOCIC RESET BRN FAIL OLK REG 10 VOC WHT LOC SW WHT RED SOFT UGHT LOGIC RED MAY MODE ORN ROLL CENTER YEL APP LOGIC GRN ROLL SOL LOGIC BLU HOG CAP LIGHT LOGIC GRAY REV 00 WHT 50 RAD WINDOW WHT BLK GYRO TACH WHT BRN ROLL BAR LO WHT GRN ROLL BAR HI WHT YEL FD FLAG LO WHT ORN SOL A ORN A RED Loc sw BK 4 RADIO WHT 1 1 RADIO LT BLU IC PSOE FLAG GRM J L FLAG GYRO TACH GRN GYRO SIG REF WHT GYRO SIG BLK ee Ke AIRFRAME GND DIRECTIONAL GYRO OPTION CONNECTOR P O one nore AVP CABLE ASST NOTES P O ANNUNCIATOR 50 PIN dte MEGGITT
13. Current Requirements System 55 14 VDC 28 VDC Average Operating Current 1 0 Amp 0 5 Amp Maximum Current 5 0 Amp 3 0 Amp Current Requirements System 55X 14 VDC 28 VDC Average Operating Current 1 0 Amp 0 5 Amp Maximum Current 5 0 Amp 3 0 Amp Current Requirements System 550 14 VDC 28 VDC Average Operating Current N A 0 5 Amp Maximum Current N A 3 0 Amp Current Requirements System 60 1 14 VDC 28 VDC Average Operating Current 1 0 Amp 0 5 Amp Maximum Current 3 0 Amp 2 0 Amp Current Requirements System 60 2 14 VDC 28 VDC Average Operating Current 1 0 Amp 0 5 Amp Maximum Current 5 0 Amp 3 0 Amp Current Requirements System 65 14 VDC 28 VDC Average Operating Current 1 0 Amp 0 5 Amp Maximum Current 5 0 Amp 3 0 Amp Current Requirements PSS 14 VDC 28 VDC Average Operating Current 1 0 Amp 0 5 Amp Maximum Current 3 0 Amp 2 0 Amp Ist Ed May 11 2001 8 5 MEGGITT AVIONICS S TEC FLIGHT LINE SERVICE MANUAL FOR RATE BASED AUTOPILOTS PAGE INTENTIONALLY BLANK 8 6 Ist Ed May 11 2001 MEGGITT AVIONICS S TEC FLIGHT LINE SERVICE MANUAL FOR RATE BASED AUTOPILOTS SECTION 9 GLOSSARY Ist Ed 11 2001 9 1 MEGGITT AVIONICS S TEC FLIGHT LINE SERVICE MANUAL FOR RATE BASED AUTOPILOTS PAGE INTENTIONALLY BLANK 9 2 Ist Ed May 11 2001 Term AC ACCEL AFMS ALR ALT APR ARINC ATC C CAP CB CCW CDI CMD CON T CRS CS CTRK DEV CW CWS DC DG DISC DN DSBL DT
14. NAV NDU OBS P N POH POHS POH S POT PSI PSS RDY REF REV RPM RT S S A SB SFM SOL ST STB TACH TIC TC TSO VAC VMC VOR Vpp GLOSSARY CON T Meaning Not Applicable No Connection Navigation Navigational Display Unit Omnibearing Selector Part Number Pilot s Operating Handbook Pilot s Operating Handbook Supplement Potentiometer Pounds Per Square Inch Pitch Stabilization System Ready Reference Reverse Revolutions Per Minute Right Soft Gain Condition Tracking Course Selector Alerter Service Bulletins Supplemental Flight Manual Solenoid Stabilizer Tachometer Turn Coordinator Technical Standard Order Unit Under Test Volts Alternating Current Volts Direct Current Visual Flight Rules Very High Frequency Visual Meteorological Conditions Very High Frequency Omnidirectional Radio Range Volts Peak to Peak Vertical Speed Transducer Yaw Damper Ist Ed May 11 2001
15. Navigation Channel Test with No Heading System Installed 37 38 39 40 41 42 43 Tune the Navigation Receiver to the local VOR frequency Adjust the OBS for a 100 leftward deflection of the Left Right needle from center Engage the A P LO TRK or HI TRK mode Verify that the A C control wheel turns to the left Adjust the OBS for a 100 rightward deflection of the Left Right needle from center Verify that the A C control wheel turns to the right Adjust the OBS for a centered Left Right needle to stop the A C control wheel Altitude Channel Test 44 45 Apply fore and aft pressure to the A C control wheel to sense its freedom of movement Engage the A P ALT mode Ist Ed 11 2001 46 MEGGITT AVIONICS S TEC FLIGHT LINE SERVICE MANUAL FOR RATE BASED AUTOPILOTS Apply fore and aft pressure to the A C control wheel to verify its reduced freedom of movement Trim Channel Test 4T 48 49 50 Apply maximum aft pressure to the A C control wheel Verify that a After 3 seconds TRIM DN becomes annunciated on the A P and the audible alert sounds a steady tone b After 7 seconds TRIM DN flashes and the audible alert becomes periodic Apply maximum fore pressure to the A C control wheel Verify that a After 3 seconds TRIM UP becomes annunciated on the A P and the audible alert sounds a steady tone b After 7 seconds TRIM UP flashes and the audible alert becomes p
16. Power Required Weight Dimensions TSO Programmer System 65 Power Required Weight Dimensions TSO Programmer PSS Power Required Weight Dimensions TSO Ist Ed May 11 2001 14 28 VDC 2 2 Ib 3 250 x 3 250 x 7 100 in C9c C3d 14 28 VDC 2 1 Ib 3 340 x 3 340 x 8 200 in C9c 14 28 VDC 2 8 Ib 3 340 x 3 340 x 8 200 in 14 28 VDC 2 7 1 6 350 x 1 500 x 9 460 in C9c C52a 14 28 VDC 2 7 Ib 6 350 x 1 500 x 9 460 in C9c C52a 28 VDC 2 7 1 6 350 x 1 500 x 9 460 in C9c C52a 14 28 VDC 1 8 Ib 3 343 x 3 343 x 5 200 in C9c C52a 14 28 VDC 1 8 Ib 3 343 x 3 343 x 5 200 in C9c C52a 14 28 VDC 0 60 Ib 2 00 x 2 00 x 5 124 in C9c C52a 14 28 VDC 1 1 Ib 4 500 x 1 312 x 6 000 in C9c C52a 8 3 MEGGITT AVIONICS S TEC FLIGHT LINE SERVICE MANUAL FOR RATE BASED AUTOPILOTS Roll Computer System 60 1 60 2 65 Power Required Weight Dimensions TSO Pitch Computer System 30 30 ALT Power Required Weight Dimensions TSO Pitch Computer System 60 2 65 PSS Power Required Weight Dimensions TSO RemoteAnnunciator System 65 Power Required Weight Dimensions TSO Turn Coordinator Power Required Flag Voltage Detector Operating Limits Flag RPM Detector Operating Limits Weight Dimensions TSO Absolute Pressure Transducer Power Required Pressure Range Overpressure Weight Dimensions Roll
17. Tune the Navigation Receiver to a non receiving VOR frequency so that the Left Right needle is centered Note If no heading system DG or HSI is installed proceed to step 6 Center the Heading Bug DG or Course Pointer HSI under the lubber line Engage the A P NAV mode LO TRK mode for System 20 30 Insert the Roll Centering Adjustment Tool P N 95101 1 into the A P bezel hole as shown in Fig 2 1 until it makes contact with the Roll Centering Potentiometer Adjust the Roll Centering Potentiometer in small increments to null A C control wheel movement allow time between adjustments for the A P system to stabilize 22 In Flight Roll Centering Adjustment optional 2 2 1 A P is a Radio Coupler 1 2 Fly the A C to smooth air and trim for level flight Set the A P Master Switch to the ON position Wait until RDY alone becomes annunciated on the A P display upon completion of the power up self test Tune the Navigation Receiver to a VOR frequency Select the course using the OBS DG or Course Pointer HSI Note If the heading system is an HSI proceed to step 7 Set the Heading Bug to match the selected course Engage the NAV mode and wait until the A P has intercepted the course Insert the Roll Centering Adjustment Tool P N 95101 1 into the A P bezel hole as shown in Fig 2 1 until it makes contact with the Roll Centering Potentiometer Adjust the Roll Centering Potentiometer in small increments to obtain a ce
18. 1 Set the Battery Master Switch to the ON position 2 Set the Avionics Master Switch to the ON position 3 Set the A P Master Switch to the ON position 4 Verify that the following all annunciate on the A P for 10 seconds and then extinguish HDG RDY NAV CWS APR FAIL GPSS REV TRIM ALT GS VS 430 5 Verify that within 3 minutes RDY alone becomes annunciated on the A P 6 Verify that the Low Voltage Flag on the Turn Coordinator is out of view Ist Ed May 11 2001 3 21 MEGGITT AVIONICS S TEC FLIGHT LINE SERVICE MANUAL FOR RATE BASED AUTOPILOTS Heading Channel Test 7 10 11 12 13 14 15 16 Center the bug under the lubber line Engage the A P HDG mode Turn the HDG bug to the left Verify that the A C control wheel turns to the left Center the HDG bug under the lubber line Verify that the A C control wheel stops Turn the HDG bug to the right Verify that the A C control wheel turns to the right Center the HDG bug under the lubber line Verify that the A C control wheel stops Navigation Channel Test Note If the heading system is an HSI this test cannot be performed In that case proceed to step 33 17 18 19 20 21 22 23 24 25 26 2T 28 29 30 31 Tune the Navigation Receiver to the local VOR frequency Adjust the OBS for a 100 leftward deflection of the Left Right needle from center Engage the A P NAV mode Veri
19. 10 11 12 MEGGITT AVIONICS S TEC FLIGHT LINE SERVICE MANUAL FOR RATE BASED AUTOPILOTS Set the A P Master Switch to the TEST position Verify that the TRIM UP and TRIM DN lamps are illuminated on the A P Verify that the TRIM UP lamp extinguishes after 2 seconds and the re appears after 4 seconds Verify that the TRIM DN lamp extinguishes after 7 seconds Verify that the following are all annunciated on the A P STB HDG NAV APR REV Verify that the RDY lamp is illuminated on the A P Set the A P Master Switch to the ON position Verify that all of the annunciations and lamps are extinguished Verify that within 3 minutes the RDY lamp becomes illuminated on the A P Verify that the Low Voltage Flag on the Turn Coordinator is out of view Stabilizer Channel Test 13 14 15 16 17 18 19 20 21 22 Center A P TURN CMD knob under its index Engage the A P STB mode Turn the A P TURN CMD knob to the left Verify that the A C control wheel turns to the left Center the A P TURN CMD knob under its index Verify that the A C control wheel stops Turn the A P TURN CMD knob to the right Verify that the A C control wheel turns to the right Center the A P TURN CMD knob under its index Verify that the A C control wheel stops Note If the A P is not equipped with a Heading System proceed to step 44 Heading Channel Test 23 24 25 Center the HDG bug under the lub
20. 12 13 14 15 16 17 18 19 20 21 22 23 MEGGITT AVIONICS S TEC FLIGHT LINE SERVICE MANUAL FOR RATE BASED AUTOPILOTS Set the Battery Master Switch to the OFF position Disconnect the A P cable harness from the Altitude Transducer Plug the proper end of Extender Cable P N 39310 into the A P cable harness in place of the actual Altitude Transducer Plug the other end of the Extender Cable into the Altitude Transducer Simulator connector Set the Pitch Command Selector Switch on the Altitude Transducer Simulator to the ENG A P ALT MODE position Set the Battery Master Switch to the ON position Set the Avionics Master Switch to the ON position Set the A P Master Switch to the ON position Wait until RDY alone becomes annunciated on the A P display upon completion of the power up self test Engage the A P HDG mode Center the HDG bug under the lubber line to null lateral movement of the A C control wheel Engage the A P ALT mode Move the A C control wheel until the elevator is in the neutral position Set the Pitch Command Selector Switch on the Altitude Transducer Simulator to the PITCH DN position Verify that the A C control wheel moves in the FORE direction Set the Pitch Command Selector Switch on the Altitude Transducer back to the ENG A P ALT MODE position Verify that the A C control wheel stops Set the Pitch Command Selector Switch on the Altitude Transducer Simulator to the PITCH
21. 16 Verify that the A C control wheel turns to the right 17 Center the HDG bug under the lubber line 18 Verify that the A C control wheel stops Navigation Channel Test Note If the heading system is an HSI this test cannot be performed In that case proceed to step 35 19 Tune the Navigation Receiver to the local VOR frequency 20 Adjust the OBS for a 100 leftward deflection of the Left Right needle from center 21 Engage the A P NAV mode 22 Verify that the A C control wheel turns to the left 23 Engage the A P HDG mode to stop the A C control wheel 24 Adjust the OBS for a 100 rightward deflection of the Left Right needle from center 25 Engage the A P NAV mode 26 Verify that the A C control wheel turns to the right 27 Engage the A P REV mode 28 Verify that the A C control wheel turns to the left 29 Engage the A P mode to stop the A C control wheel 30 Adjust the OBS for a 100 leftward deflection of the Left Right needle from center 3 Engage the A P REV mode 32 Verify that the A C control wheel turns to the right 33 Engage the A P HDG mode to stop the A C control wheel 3 26 Ist Ed 11 2001 34 MEGGITT AVIONICS S TEC FLIGHT LINE SERVICE MANUAL FOR RATE BASED AUTOPILOTS Adjust the OBS for a centered Left Right needle A P Disconnect Test 35 Press the A P Disconnect Switch 36 Verify that the A P disconnects as follows RDY flashes on the A P for 5 seconds an
22. AVIONICS S TEC FLIGHT LINE SERVICE MANUAL FOR RATE BASED AUTOPILOTS FLAP TX EXC e FLAP EXC TRIM AIRFRAME ROLL LOGIC RESIST WHT ORN TRIM UGHT CONTROL WHT BRM 50 RAD WINDOW WHT YEL PITCH SOL LOGIC WHT RED 13815 518 Te STR TS S ETE TT 2 8 FLASHER WHT BLK BRM PITCH LOGIC RESET BLK G S FLASHER WHT GRAY UP MODIFIER WHT OLU ON MODIFIER WHT GRM ALT MODE GRAY VS FLASHER BLUE TIME DELAY BY PASS WHT BLK VS MODE ORN VS MOD SELECT RED GS ENGAGE GRN GS ARM ORN j i TO G S RECEIVER GS ENABLE WHT VIO PITCH FAIL YEL ON UGHT LOGIC wHT UP UGHT LOGIC VIO REG 10 VOC WHT 22 GA PITCH REF WHT BLK RED GND WHT BLK ORN PITCH STEERING CENT WHT BLK YEL VS CMD WHT BLK GRN PITCH STEERING BAR WHT BLK BLU VS SEL Sw BLK TEST GRN SOL A WHT A RED SOL4 RED SOL GND MOTOR UP GRM MOTOR DN WHT N l PITCH SOL A RED PITCH SOL GND BLK MOTOR 1 GRN MOTOR 2 YEL TRIM SW A ORN SW 8 Sw COM WHT li lI 31515181516 1515 Te e e 8 Jo Tie 1 Je 8 T6 2e TES ST 8 5 T5 T T T T8 ST S TS TS S T8 T8 e alesis ISISISIBINI TRIM INTRPT BLK WAN TRIM ON WHT MAN TRIM UP GRN TRIM At RED GNO BLK REG 10 VOC RED GS FLAG WHT 95 DN GS UP
23. Ed May 11 2001 3 33 MEGGITT AVIONICS S TEC FLIGHT LINE SERVICE MANUAL FOR RATE BASED AUTOPILOTS Trim Channel Test Note If the A P is equipped with autotrim proceed to step 61 97 58 59 60 Apply maximum aft pressure to the A C control wheel Verifv that a After 3 seconds both TRIM and DN annunciate on the A P Control Head and the audible alert sounds a steadv tone b After 7 seconds both TRIM and DN flash and the audible alert becomes periodic Applv maximum fore pressure to the A C control wheel Verifv that a After 3 seconds both TRIM and UP annunciate on the A P Control Head and the audible alert sounds a steadv tone b After 7 seconds both TRIM and UP flash and the audible alert becomes periodic Note Proceed to step 85 61 62 63 64 65 66 67 68 69 70 71 72 73 74 Set the A P Trim Master Switch to the ON position Apply maximum aft pressure to the A C control wheel Verify that after 3 seconds the A C trim wheel begins to run nose down with increasing speed Apply maximum fore pressure to the A C control wheel Verify that after 3 seconds the A C trim wheel begins to run nose up with increasing speed Apply aft pressure to the A C control wheel until the A C trim wheel stops Press either fore or aft on both segments of the A P Manual Electric Trim Switch and then release Verify that the A P disconnects as follows a RDY flashes on th
24. Extension for 95101 5 39311 Service Manual Flight Line 87104 Ist Ed May 11 2001 1 3 MEGGITT AVIONICS S TEC FLIGHT LINE SERVICE MANUAL FOR RATE BASED AUTOPILOTS 1 5 1 4 Simulates only the following Heading Systems Manufacturer Type P N S TEC DG 6406 S TEC HSI 6443 EDO AIRE DG 52D54 The Breakout Box P N 9524 Adapter Cables P N 39198 amp 39199 and Extender Assembly P N 01264 are used to measure autopilot system power signals and continuity They are connected as shown in Fig 1 2 The third objective is to determine if the system is functioning properly in flight This is accomplished by performing the flight procedures contained in the respective Pilot s Operating Handbook POH However for return of aircraft to service refer to the Aircraft Flight Manual Supplement AFMS Technical Support PH 800 872 7832 FAX 940 325 8808 Ist Ed May 11 2001 Ist Ed May 11 2001 MEGGITT AVIONICS S TEC FLIGHT LINE SERVICE MANUAL FOR RATE BASED AUTOPILOTS Em sees i 95101 5 TURN COORDINATOR SIMULATOR Fig 1 1 Flight Line Autopilot Tester MEGGITT AVIONICS S TEC FLIGHT LINE SERVICE MANUAL FOR RATE BASED AUTOPILOTS 50 PIN MALE TO ROLL HARNESS TO PITCH HARNESS Ri 78 PIN MALE TO ROLL PITCH HARNESS 44 PIN 50 PIN MALE FEMALE 41 39199 ADAPTER CABLE TO ROLL PITCH HARNESS 50 PIN MALE TO HARNESS l 01264 EXTENDER ASSEMBLV TO HARNESS ji 50 PIN MALE 50 PIN
25. OFF position Disconnect the A P cable harness from the Turn Coordinator Connect the proper end of Extender Cable P N 39311 into the A P cable harness in place of the actual Turn Coordinator Connect the other end of the Extender Cable into the Turn Coordinator Simulator connector Set the Gyro Tach Selector Switch on the Turn Coordinator Simulator to the NOT RDY position Set the Std Rate Turn Selector Switch on the Turn Coordinator Simulator to the 0 position Turn the A C control wheel until the ailerons are in the neutral position Center the A P TURN CMD knob under its index Set the Battery Master Switch to the ON position Set the Avionics Master Switch to the ON position Set the A P Master Switch to the ON position Wait 30 seconds for the A P to complete its power up self test Set the Gyro Tach Selector Switch on the Turn Coordinator Simulator to the RDY position Verify that RDY becomes annunciated on the A P display Set the Gyro Tach Selector Switch on the Turn Coordinator Simulator to the NOT RDY position Verify that RDY becomes extinguished on the A P display Set the Gyro Tach Selector Switch on the Turn Coordinator Simulator to the RDY position Engagethe A P STB mode Adjust the A P TURN CMD knob slightly as required to null any A C control wheel creep Turn the A C control wheel until the ailerons are in the neutral position Set the Std Rate Turn Selector Switch on the Turn Coordinator Simulator to the 5
26. Pointer HSI for a 100 leftward deflection of the Left Right needle from center 30 Verify that the A C control wheel turns to the right 40 Adjust the OBS DG or Course Pointer HSI for a centered Left Right needle to stop the A C control wheel Note Proceed to step 52 Navigation Channel Test with No Heading System Installed 41 Tune the Navigation Receiver to the local VOR frequency 42 Adjust the OBS for a 100 leftward deflection of the Left Right needle from center 43 Engage the A P NAV mode 44 Verify that the A C control wheel turns to the left 45 Adjust the OBS for a 100 rightward deflection of the Left Right needle from center 46 Verify that the A C control wheel turns to the right 47 Engage the A P REV mode 48 Verify that the A C control wheel turns to the left 49 Adjust the OBS for a 100 leftward deflection of the Left Right needle from center 50 Verify that the A C control wheel turns to the right 51 Adjust the OBS for a centered Left Right needle to stop the A C control wheel A P Disconnect Test 52 Press the A P ON OFF Mode Switch or the optional Remote Disconnect Switch 53 Verify that a of annunciations are extinguished b The RDY lamp is illuminated END OF TEST 3 5 Functional Ground Test for System 50 Power Up Test 1 Set the Battery Master Switch to the ON position 2 Setthe Avionics Master Switch to the ON position 3 10 Ist Ed 11 2001 9
27. SCALE N A DO NOT SCALE DRAWING SHEET 2 of 2 6 7 STEC One S TEC Way Municipol Airport Mineral Wells Tx 76067 9236 DECIMAL XXX 005 DECIMAL XX 010 FRACTIONS 1 64 ANGLES 30 REMOVE BURRS BREAK SHARP EDGES 010 MEGGITT AVIONICS S TEC FLIGHT LINE SERVICE MANUAL FOR RATE BASED AUTOPILOTS PAGE INTENTIONALLY BLANK 6 8 Ist Ed May 11 2001 MEGGITT AVIONICS S TEC FLIGHT LINE SERVICE MANUAL FOR RATE BASED AUTOPILOTS REVISIONS NOTES UNLESS OTHERWISE SPECIFIED REV DESCRIPTION DATE 1 EXISTING AUTOPILOT CABLE ASSY MAY BE USED TO INTERCONNECT RELEASED PER E O 4257 9 21 63 SYSTEM 55 COMPUTER DESIRED HEADING SYSTEM BY REMOVING A REV PER EO 5212 9 23 94 D C CONNECTOR AND CONNECTING EXISTING WIRES HOG INSTRUMENT B a00 NOTE 2 PER FO 55 8221295 RE PIN PROGRAMMER COMPUTER CONNECTOR AS REQUIRED C I REV PER EO d 59 30 16 95 2 SIGMA 1U262 033 5 OR 10262 034 6 USE STANDARD AUTOPILOT D REV PER EO 8788 2212296 CABLE ASSY SAME AS FOR S TEC 6401 AND 6406 D G OPER EO 5834 RII ae 3 07 96 3 NOT APPLICABLE TO 331A 3F INDICATOR ELIGIBLE ONLY 5514 56 F 3 PER EO 5958 6 20 96 INDICATOR PIN 331A 3G 001 002 003 005 006 007 ONLY CE 10 08 97 L3 K KING 5 55 55 INTERCONNECT BENDIX HSD 880 SIGMA iU445 004 9 COLLINS HS 331 P P PROG COM
28. TRIM FLAP POT YELLOW ORANGE VIOLET BLUE he NOTE 3 i cws CWS GND SHIELD GROUND 39123 LIGHTS A P A GRAY AP MASTER OFF SWITCH 3536 OR 3520 FO SEE NOTE 7 TO AIRCRAFT INSTRUMENT LIGHT BUS A P DISCONNECT ceo oj GROUND SEE NOTE 9 AIRFRAME GROUND 20 GA MIN EXCITATION EXC 10VDC EXC GROUND HEADING LO OC HEADING Hi DC COURSE LO OC COURSE HI SHIELO GROUND TRANSDUCER GROUND 10 TRANSDUCER SIGNAL SHIELD GROUND NAV FLAG NAV FLAG L R RT L R LOC SWITCH SHIELD GROUND AS time efe pee AC COURSE EXCITATION REF S REFERENCE SHIELO GROUND RATE GYRO TACH RATE GYRO REF RATE GYRO 56 SHIELD GROUND BATTERY BUSS WHITE GREEN ALTERNATE HEADING SYSTEM SEE NOTE 9 FOR REF ONLY TRANSDUCER TO NAV RECEIVER CONVERTER SEE NOTE 2 DIRECTIONAL CH GYRO SEE NOTE 9 GREEN WHITE BLACK AIRFRAME GROUND T amp B A BLK PITCH SOL GND PITCH MOTOR TRIM SWITCH DN YELLOW ORANGE PITCH SOLENOID H PITCH MOTOR TRIM SWITCH UP RED GREEN TRIM SWITCH COM BLUE WHT ROLL MOTOR SHIELO GROUND ROLL SOLENOID ROLL MOTOR ROLL SOL GND SHIELD GROUND WHITE REO GREEN BLACK TO FLAP POSITION POTS TO A C BUSS VOLTAGE SELECT JUMPER 2B VOC ALT ENGAGE MANUAL VS SELECT VS COMMAND MASTER 15 SWITCH AUDIO OUTPUT
29. Transducer Simulator to the PITCH UP position Verify that the voltage at the Servo Simulator MOTOR 1 jack relative to the MOTOR 2 jack is positive Set the Pitch Command Selector Switch on the Altitude Transducer Simulator to the PITCH DN position Ist Ed 11 2001 24 25 26 27 28 29 30 31 32 33 MEGGITT AVIONICS S TEC FLIGHT LINE SERVICE MANUAL FOR RATE BASED AUTOPILOTS Verify that the voltage at the Servo Simulator MOTOR 1 jack relative to the MOTOR 2 jack is negative Set the Pitch Command Selector Switch on the Altitude Transducer Simulator to the ENG A P ALT MODE position Set the Trim Command Selector Switch on the Servo Simulator to the TRIM UP position Verify that after a 3 second delay the A P annunciates TRIM UP Set the Trim Command Selector Switch on the Servo Simulator to the NEUTRAL position Verify that the TRIM UP annunciation is extinguished Set the Trim Command Selector Switch on the Servo Simulator to the TRIM DN position Verify that after a 3 second delay the A P annunciates TRIM DN Set the Trim Command Selector Switch on the Servo Simulator to the NEUTRAL position Verify that the TRIM DN annunciation is extinguished 4 2 2 2 No Heading System Installed and A P with STB Mode 1 2 10 11 12 13 14 15 Set the A P Master Switch to the OFF position Set the Avionics Master Switch to the OFF position Set the Battery Master Switch to the
30. UP position Verify that the A C control wheel moves in the AFT direction Set the Pitch Command Selector Switch on the Altitude Transducer Simulator to the ENG A P ALT MODE position Verify that the A C control wheel stops 4 3 2 No Heading System Installed and A P with STB Mode 1 2 3 Set the A P Master Switch to the OFF position Set the Avionics Master Switch to the OFF position Set the Battery Master Switch to the OFF position Disconnect the A P cable harness from the Altitude Transducer Ist Ed May 11 2001 4 11 MEGGITT AVIONICS S TEC FLIGHT LINE SERVICE MANUAL FOR RATE BASED AUTOPILOTS 4 12 10 11 12 13 14 15 16 17 18 19 20 21 22 23 Plug the proper end of Extender Cable P N 39310 into the A P cable harness in place of the actual Altitude Transducer Plug the other end of the Extender Cable into the Altitude Transducer Simulator connector Set the Pitch Command Selector Switch on the Altitude Transducer Simulator to the ENG A P ALT MODE position Set the Battery Master Switch to the ON position Set the Avionics Master Switch to the ON position Set the A P Master Switch to the ON position Wait until RDY alone becomes annunciated on the A P display upon completion of the power up self test Engage the A P STB mode Center the A P TURN CMD knob under its index to null lateral movement of the A C control wheel Engage the A P ALT mode Move the A C
31. control wheel until the elevator is in the neutral position Set the Pitch Command Selector Switch on the Altitude Transducer Simulator to the PITCH DN position Verify that the A C control wheel moves in the FORE direction Set the Pitch Command Selector Switch on the Altitude Transducer to the ENG A P ALT MODE position Verify that the A C control wheel stops Set the Pitch Command Selector Switch on the Altitude Transducer Simulator to the PITCH UP position Verify that the A C control wheel moves in the AFT direction Set the Pitch Command Selector Switch on the Altitude Transducer Simulator to the ENG A P ALT MODE position Verify that the A C control wheel stops Pitch Only A P 1 2 Set the A P Master Switch to the OFF position Set the Avionics Master Switch to the OFF position Set the Battery Master Switch to the OFF position Disconnect the A P cable harness from the Altitude Transducer Plug the proper end of Extender Cable P N 39310 into the A P cable harness in place of the actual Altitude Transducer Plug the other end of the Extender Cable into the Altitude Transducer Simulator connector Ist Ed 11 2001 10 11 12 13 14 15 16 17 18 19 20 21 MEGGITT AVIONICS S TEC FLIGHT LINE SERVICE MANUAL FOR RATE BASED AUTOPILOTS Set the Pitch Command Selector Switch on the Altitude Transducer Simulator to the ENG A P ALT MODE position Set the Battery Master Swi
32. second by sensing the increased freedom of A C control wheel movement in the fore and aft directions 15 Release the A P DN Switch 16 Verify that the pitch servo immediately re engages by sensing the reduced freedom of A C control wheel movement in the fore and aft directions Power Up Test 17 Set the A P Master Switch to the ON position 18 Verify that all of the annunciations and illuminations are extinguished Altitude Channel Test 19 Move the A C control wheel until the elevator is in the neutral position 20 Engage the A P ALT mode 2 Press and hold the A P UP Switch 22 Verify that the A C control wheel moves in the aft direction 23 Release the A P UP Switch 24 Press and hold the A P DN Switch 25 Verify that the A C control wheel moves in the fore direction Note There will be a slight delay in this movement as the A C control wheel decelerates aft to the null 26 Release the A P DN Switch 27 Engage the A P VS mode to stop the A C control wheel Vertical Speed Channel Test 28 Press and hold the A P UP Switch 29 Verify that the A C control wheel moves in the aft direction 30 Release the A P UP Switch Ist Ed May 11 2001 MEGGITT AVIONICS S TEC FLIGHT LINE SERVICE MANUAL FOR RATE BASED AUTOPILOTS 3 Press and hold the A P DN Switch 32 Verify that the A C control wheel moves in the fore direction Note There will be a slight delay in this movement as the A C control wheel dece
33. 0 RT position Verify that the A C control wheel turns to the left Set the Std Rate Turn Selector Switch on the Turn Coordinator Simulator to the 0 position Verify that the A C control wheel stops Ist Ed May 11 2001 4 15 MEGGITT AVIONICS S TEC FLIGHT LINE SERVICE MANUAL FOR RATE BASED AUTOPILOTS 4 16 27 28 29 30 Set the Std Rate Turn Selector Switch on the Turn Coordinator Simulator to the 50 LT position Verify that the A C control wheel turns to the right Set the Std Rate Turn Selector Switch on the Turn Coordinator Simulator to the 0 position Verify that the A C control wheel stops Notes 1 7590 90 may be selected instead of 50 in steps 23 and 27 2 Turning the HDG bug sufficiently to the right will cause the A C control wheel to stop in step 24 3 Turning the HDG bug sufficiently to the left will cause the A C control wheel to stop in step 28 4 Setting the Std Rate Turn Selector Switch to the VARY position enables custom turn rate selection using the Vary Adjust Pot The scale is 1 VDC for a std rate turn 3 sec as measured at the TURN RATE jack relative to the TURN RATE REF jack The voltage Polarity is negative for a right turn and positive for a left turn Ist Ed 11 2001 MEGGITT AVIONICS S TEC FLIGHT LINE SERVICE MANUAL FOR RATE BASED AUTOPILOTS SECTION 6 HEADING INTERCONNECT DRAWINGS Ist Ed May 11 2001 6 1 MEGGITT AVIONICS S TEC FLIGHT LINE SERVICE M
34. 2 12 23 97 J FROST REV EO 7572 2 24 99 T PIERSON BATT a d P o O BACK OF O3905 ALTITUDE HOLD SW BUSS HOLD SA ALT HOLD PWR SW lt 4 Se S TEC P N 4906 S TEC P N 3520 01261 PITCH COMPUTER 39195 CABLE ASSY ALT LED WHT ALT SW GRN BLU PITCH A RED DN LED ORN MM UP LED YEL SHIELD SEE NOTE 3 ROLL SOL RED WHT 3 1 PIEZO ALARM 4 HORN WHT 1 PIEZO ALARM fee HORN LO BLU WHT SHIELD X ki d A C INST DIMMER RHEOSTAT BLK ALT XDCR SEE NOTE 4 XDCR SIG GRN l XDCR GND BLK ALT ENG DISENGAGE SW l XDCR RED S TEC P N 3532 SE NOTE 2 SHIELD SOLENOID RED SOL GND BLK MOTOR 1 YEL MOTOR 2 GRN UP Sw BLU SW GND WHT DN SW ORN SHIELD AIRFRAME GND NOTES FIELD FABRICATED WIRING TO BE 22 GA MINIMUM Jiu OTHERWISE NOTED amp MUST MEET OR EXCEED THE REQUIREMENTS OF MIL W 22759 16 ALL WIRING TO BE ROUTED amp SECURED I A W A C 45 13 1A CHAPTER 11 SECTION 7 THE ALTITUDE ENGAGE DISENGAGE SWITCH IS AN OPTIONAL COMPONENT CONNECT TWO 22 GA WIRES TO PINS 4 amp 10 OF THE ALTITUDE HOLD SWITCH amp ROUTE TO CONTROL WHEEL CONNECT WIRES TO 3532 SWITCH WIRES 1 amp 3 ARE JUMPERED AS SHOWN IF AN EXISTING ROLL AUTOPILOT 15 INSTALLED IN THE AIR CRAFT ROLL SOLENOID MAY BE USED AS A PIT
35. 24 NAV FLAG AND PIN 5 REG 10V AND ADD A JUMPER BETWEEN RANCE PIN 6 NAV FLAG AND PIN 26 SIGNAL REFERENCE ee dud 6 THESE WIRES ARE PROVIDED FOR USE WITH 2 AXIS FLIGHT DIRECTOR Pecan xx 7 SYSTEM REFER TO OPTIONAL FLIGHT DIRECTOR STEERING HORIZON ST 60 1 FRACTIONS 1 64 DRAWING NO 1001 INSTALLATION BULLETIN NO 120 FOR WIRING INFORMATION NOT USED NEXT ASSY USED ON E 24210 30 WITH SINGLE AXIS SYSTEMS APPLICATIONS BREAK SHARP EDGES 01 DO NOT SCALE DRAWING Ist Ed May 11 2001 7 13 MEGGITT AVIONICS S TEC FLIGHT LINE SERVICE MANUAL FOR RATE BASED AUTOPILOTS PAGE INTENTIONALLY BLANK 7 14 Ist Ed 11 2001 MEGGITT AVIONICS S TEC FLIGHT LINE SERVICE MANUAL FOR RATE BASED AUTOPILOTS c NNNM Rev DESCRIPTION aE APPROVED FRENIS _ H REDRAWN PER EO 1646 amp JIl IS SSITPIERSON NOTE 8 NOTE 8 1 REV PER 922 BGN A ded J REV PER FECO 988 Pic eran ier pccis rre 1019 14112 6 5 3 2 1 REV PER 5086 6 29 94 T PIERSON PROGRAMMER ANNUNCIATOR s 1 0 1 2 12 v4T34T of 41 81121177 61 7 5 24 11571 3118 27129125145 161251 19122130126128145144 477 1512115331 581 31141 FO A WHT FO LIGHT ORN ROLL FLIGHT 2 i ii 8055 fa
36. 60 CES IG 832 895 ose D C HDG SIGNAL P EXC 10 VDC HOG CRS RETURN DC CRS SIGNAL AERONETICS MODEL 8000 2 NARCO HSl 100 1005 MODEL 8130 HSI 51 100 1005 EXCITATION BOOTSTRAP ROTOR H RESC HDG SIGNAL HDG C T ROTOR H EXCITATION CRS SIGNAL CRS DATUM CT ROTOR H EXCITATION REF SIGNAL REF BOOTSTRAP ROTOR C CRS SIGNAL HDG CT ROTOR C HDG SIGNAL CRS DATUM CT ROTOR C EDO 52054 520154 SIGNAL REF BOOTSTRAP STATOR X e CRS DATUM CT STATOR X HDG CT STATOR X BOOTSTRAP STATOR Y 52D54 154 CRS DATUM CT STATOR Y AC CRS SIG AUTOPILOT HDG OUTPUT HDG CT STATOR Y r4 AC HDG SIG 18 OUTPUT COMMON BOOTSTRAP STATOR Z EXCIT REF CRS DATUM CT STATOR Z SIGNAL REF E iNPUT COMMON COLLINS PN 101 HDG CT STATOR Z 331A 3G NOTE 2 KING KPI 550 550A BENDIX IN 831A DATUM SYNCHRO ROTOR H KPI550 550A PN 400172 8504 8505 EXCITATION SYNCHRO ROTOR H 5 SIGNAL SYNCHRO STATOR x Ex DATUM SYNCHRO ROTOR H INB31A CRS SIGNAL DATUM SYNCHRO STATOR X EXCITATION SYNCHRO ROTOR H SIGNAL REF SYNCHRO STATOR Y HDG SIGNAL SYNCHRO STATOR X EXCITATION BOOTSTRAP ROTOR H SYNCHRO ROTOR C DATUM SYNCHRO STATOR X proc AC HDG SIG 18 HDG CT ROTOR H DATUM SYNCHRO ROTOR C SIGNAL REF SYNCHRO STATOR Y IG CRS CT ROTOR H DATUM SYNCHRO STATOR Y SYNCHRO ROTOR C SIGNAL REF CRS CT ROTOR C DATUM SYNCHRO ROTOR X HDG CT ROTOR C DATUM SYNCHRO STATOR Y BOOTSTRAP ROTOR C STATOR Z EDO 52D254 BENDIX HSD 880 DG M
37. 7 GS FLAG RED NOTES CONT EASED PER 1520 06 86 O SAN PER FECO 841 PER FECO 380 30 86 aR PER FECO 922 PER FECO 988 ind PER FECO 2115 11 21 97 KEIRNAN REV PER ECO 9603 9 WIRES TO PINS 15 AND 35 OF 37 PIN ANNUNCIATOR PLUG ARE NOT CONNECTED AS SHOWN THEY ARE PROVIDED FOR CONVENIENCE IF FLIGHT DIRECTOR OR YAW DAMPER OPTIONS ARE INSTALLED IN CONJUNCTION WiTH THE SYSTEM 65 AUTOPILOT REMOVE COVER FROM 37 PIN CONMECTOR TO ACCESS THESE WIRES REMOVE INSULATION ANO INSERT IN LOCATION REQUIRED FOR YAW DAMPER OPTION IN SERT ORANGE WIRE IN PIN 35 LOCATION AND INSTALL JUMPER BETWEEN PINS 40 AND 42 OF 50 PIN ANNUNCIATOR CONNECTOR FOR FLIGHT DIRECTOR OPTION INSERT GRAY WIRE IN PIN 15 LOCATION THESE WIRES ARE NOT TO BE INSTALLED UNLESS THE RESPECTIVE OPTIONS ARE INSTALLED SOME INSTALLATIONS MAY ALTERNATELY HAVE A BROWN WIRE IN PLACE OF BLACK AND A VIOLET WIRE PLACE OF WHITE 1 FIELD FABRICATED WIRING TO 22 GA MIN UNLESS OTHERWISE NOTED AND MUST MEET OR EXCEED THE REQUIREMENTS OF MIL W 22759 18 2 ore TO RADIO MANUFACTURERS SERVICE AND OR INSTALLATION MANUAL FOR SPECIFIC INTERCONNECT INFOR 3 PIN CONNECTIONS ARE SHOWN FOR D G ONLY WHEN AN 5 IS INSTALLED REFER TO HEADING SYSTEM INTERCONNECT DETAILS MO 1003 AND H S I MANUFACTURERS SERVICE INSTALLATION MANUAL FOR INTERCONNECT INFOR SOME CONVERTER IN
38. A DVM ED ENG EXC FAA FAF FD FPM GND GPS GPSS GS HDG HD Hg HI TRK HSI IFR ILS IMC IN JPR LR LBS LOC LORAN LO TRK IT MAN MOD MOT Ist Ed Mav 11 2001 MEGGITT AVIONICS S TEC FLIGHT LINE SERVICE MANUAL FOR RATE BASED AUTOPILOTS GLOSSARY Meaning Aircraft Autopilot Aircraft Power 14 VDC or 28 VDC Alternating Current Acceleration Airplane Flight Manual Airplane Flight Manual Supplement Alert Altitude Approach Aeronautical Radio Incorporated Air Traffic Control Capture Gain Condition Course Captured Circuit Breaker Counterclockwise Course Deviation Indicator Command Continued Course Capture Soft Gain Condition Tracking Course or Localizer Cross Track Deviation Clockwise Control Wheel Steering Direct Current Directional Gyro Disconnect Down Disable Data Digital Volt Meter Edition Engage Excitation Federal Aviation Administration Final Approach Fix Hlight Director Feet Per Minute Ground Global Positioning System Global Positioning System Steering Glideslope Heading Mercury High Gain Tracking Horizontal Situation Indicator Instrument Flight Rules Instrument Landing System Instrument Meteorological Conditions Inches Jumper Left Right Pounds Localizer Long Range Navigation Low Gain Tracking Left Manual Modify Motor 9 3 MEGGITT AVIONICS S TEC FLIGHT LINE SERVICE MANUAL FOR RATE BASED AUTOPILOTS 9 4 Term N A N C
39. ANUAL FOR RATE BASED AUTOPILOTS Table of Contents System 20 30 c ectetuer ete tee ei Syste m40 50 aede aer e e ire e System 53 55 X edo n a oe Et System 60 1 60 2 65 csse ses tee tee te le acts cer Pe e eet Pee euge 6 2 Ist Ed May 11 2001 KING 5 55 55 INTERCONNECT KCS 55 5SA P101 8 f3 b c sic AHP 1 45 HOG CRS RETURN 5 55 KING KPI 550 550A T C R C 550 550 A Exc P D HOG SYNCHRO ROTOR H 6 SIG HDG SYNCHRO STATOR X 3 1 5 SIG REF 3 8 SYNCHRO STATOR Y 55 _ rotor 520254 DG MODEL 4000 5 OR 6 1U262 014 4 10262 015 5 16 EXC 10V0C 12 36 EXC GND 20 G DC HDG SIG 17 m EDO 52D54 OR 52D154 T C R C 52054 154 6 AC HDG SIG 4 5 EXC REF oj 3 SIG REF 18 35 E EDO NSD 360 360A DG 360 CENTURY NSD 1000 CESSNA ARC 832A 16 832C 1G 895A T C R C NSD 360 IG 832 895 15 EXC 10 0 A 20 EXC GND E DC HDG SIG ss 3 SIGMA IU445 004 9 T C R C t6 EXC 10V0C 20 36 EXC GND 19 8 1 3 DC HDG SIG 21 35 SIGMA TEK DG 1U262 014 13 OR 11 OR SEE NOTE 2 T C R C 262 015 12 OR 13 161 6 EXC 410VDC 12 36 EXC GND 20 SIG 12 Bs
40. ANUFACTURERS SERVICE INSTALLATION MANUAL FOR INT RCONNECT INFORMATION SOME NAV CONVERTER INDICATORS 00 NOT PROVIDE NAV FLAG OUTPUTS FOR AUTO PILOT USE WHEN USED WITH THIS TYPE CONVERTER INDICATOR THE NAV FAILURE WARNING FUNCTION OF THE AUTO PILOT MUST BE DISABLED TO DISABLE THIS FUNCTION ADD A JUMPER BETWEEN PIN 13 NAV FLAG AND PIN 33 REG 159 AND ADD A JUMPER BETWEEN PIN 14 FLAG AND PIN 27 SIGNAL REFERENCE A2 ALERTER COMPUTER OPTIONAL ALTITUDE VERTICAL SPEED SELECTOR NOTES CONT D 11 CONNECT PIN 27 THROUGH LEAD MARKED AUDIO AMP TO ANY AVAILABLE NON MUTED INPUT OF THE AUDIO AMPLIFIER FOR PIN DESIGNATIONS NEAR THE AUDIO AMP CONNECTOR REFER TO AMPLIFIER MANUFACTURER S SERVICE INFORMATION CONNECT PIN 43 SHIELO TO ANY CONVENIENT AIRFRAME GROUND AUDIO INPUTS MAY BE JOINED INTO A COMMON AUDIO AMP INPUT BY USING 300 ohm 1 4 WATT RESISTORS 1 ii 1 a 5 5 55 55 USED APPLICATIONS oTY TEM PART NUMBER DESCRIPTION UST Of MATERIALS APPROVAL DATE STEC Corporation One GL 9 21 95 casino DORIA TLE ac TOLERANCES UNLESS Ones SPCOFED DECMAL XXX 005 CECH XX 010 fRACTOMS 1 64 SCHEMATIC WIRING INTERCONNECT SYSTEM 55 MEGGITT AVIONICS S TEC FLIGHT LINE SERVICE MANUAL F
41. ASED AUTOPILOTS Table of Contents 4 1 Operating Procedure for Heading System Simulator P N 95101 2 4 2 Operating Procedure for Servo Simulator P N 951013 4 22 RoellServVozu ia a a L a Mia eta E 4 2 1 1 Heading System Installed 4 2 1 2 No Heading System Installed and A P with STB Mode 4 22 BHGBISGEVO eee tec ie te t e IHE ue bete tet 4 2 2 1 Heading System Installed 4 2 2 2 No Heading System Installed and A P with STB Mode 42 23 Pitch Only AJP eee eae ia UR eie dde 423 Trim Servo ioo REPRE IRURE BON ERR RR eR NER 4 3 Operating Procedure for Altitude Transducer Simulator P N 95101 4 431 Heading System Installed 4 3 2 Heading System Installed and A P with STB 433 Only AYP eee eee bre eod tete te eterne 4 4 Operating Procedure for Turn Coordinator Simulator P N 95101 5 4 4 1 Heading System Installed 442 Heading System Installed and A P with STB 4 2 Ist Ed May 11 2001 MEGGITT AVIONICS S TEC FLIGHT LINE SERVICE MANUAL FOR RATE BASED AUTOPILOTS 4 1 Operating Procedure for Heading System Simulator P N 95101 2 This procedure applies to the following Heading Systems MFG TYPE P N S TEC DG 6406 S TEC HSI 6443 EDO AIRE DG 52D54 1 Se
42. C trim wheel stops and the TRIM annunciation is extinguished 69 Press fore and maintain pressure on both segments of the A P Manual Electric Trim Switch 70 Verify that the A C trim wheel runs nose down at full speed and TRIM flashes 71 Press and hold the A P Disconnect Trim Interrupt Switch 72 Verify that the A C trim wheel stops 73 Release the A P Disconnect Trim Interrupt Switch 74 Verify that the A C trim wheel resumes running nose down at full speed 75 Release the A P Manual Electric Trim Switch 76 Verify that the A C trim wheel stops and TRIM annunciation is extinguished END OF TEST A P Disconnect Test TT 78 Press the A P Disconnect Trim Interrupt Switch Verify that RDY flashes on the A P and an audible alert sounds for 5 seconds after which RDY alone remains annunciated and the audible alert ceases END OF TEST 3 7 Functional Ground Test for System 55X Power Up Test 1 2 3 Set the Battery Master Switch to the ON position Set the Avionics Master Switch to the ON position Set the A P Master Switch to the ON position Ist Ed May 11 2001 3 17 MEGGITT AVIONICS S TEC FLIGHT LINE SERVICE MANUAL FOR RATE BASED AUTOPILOTS 4 Verify that the following all annunciate on the A P for 10 seconds and then extinguish HDG NAV CWS APR FAIL GPSS REV TRIM GS VS 16 5 Verify that within 3 minutes RDY alone becomes annunciated A P 6 Verify that the
43. CH MODE ENABLE BY PROVIDING A SWITCHED LIST OF MATERIALS TO PIN 3 OF THE PITCH COMPUTER THIS WILL ENABLE THE ALTITUDE HOLD SYSTEM ONLY WHEN A ROLL MODE 15 ENGAGED ON THE EXISTING AUTOPILOT EXTRACT THE PIN OUT OF PIN 3 amp COVER WITH WITH HEAT SHRINK INSERT THE ROLL SOLENOID WIRE INTO PIN 3 IF THIS OPTION IS TO BE UTILIZED One 5 Woy CHECKED KEIRNAN Municipal Airport Minerol Wells Tx 76067 9236 RECEPTIS A REMOTELY MOUNTED AUDIBLE ALARM PIEZO ALARM S TEC P N 6547 IS REQUIRED TO PROVIDE AN AURAL ELEVATOR OUT OF TRIM INDICATION WHEN THE PITCH COMPUTER IS LOCATED OUTSIDE THE CABIN Ex x y y 22 AREA DU TEE SCHEMATIC 30 ALT WIRING INTERCONNECT ALL SOLDER CONNECTIONS OR SPLICES TO BE COVERED WITH HEAT SHRINK DECIMAL XXX 005 FRA AER DRAWING NO 10115 3 ede SE Um D APPLICATIONS BREAK SHARP EDGES 010 SCALE N A DO NOT SCALE DRAWING Ist Ed May 11 2001 7 5 MEGGITT AVIONICS S TEC FLIGHT LINE SERVICE MANUAL FOR RATE BASED AUTOPILOTS PAGE INTENTIONALLY BLANK 7 6 Ist Ed 11 2001 MEGGITT AVIONICS S TEC FLIGHT LINE SERVICE MANUAL FOR RATE BASED AUTOPILOTS fo 1 REMISIONS APPROVED T PIERSON T PIERSON T PIERSON PROGRAMMER COMPUTER ROLL MOTOR i 9 GREEN ROLL MOTOR 2 WHITE ROLL SOLENOID RED SOLENOID GROUND BLACK SHIELD
44. D 7 A C BUSS NOTES 5 5 FLAG WHT ALL FIELD FABRICATED WIRING 22 GA UNLESS OTHERWISE NOTED amp MUST MEET OR EXCEED REQUIREMENTS OF MIL W 22759 16 ot Hoe oe o UCM WIRING TO BE ROUTED amp SECURED I A W A 43 13 1A CHAPTER 11 SECTION 7 PARAGRAPH 514 G S FLAG RED USE NAVIGATIONAL EQUIPMENT MANUFACTURERS INFORMATION TO DETERMINE TERMINATIONS FOR RADIO INTERFACE LOC SWITCH PIN 9 OF MOLEX CONNECTOR MUST BE GROUNDED WHEN RADIO IS TUNED TO AN ILS LOCALIZER FREQUENCY WIRE TO PIN 54 BLK OF THE COMPUTER 15 PROVIDEO REOR INSTALLATION OF ALTITUDE VERTICLE SPEED SELECTOR OPTION REFER TO INSTALLATION BULLETIN NO 119 FOR WIRING INFORMATIOI REFER TO FLAP COMPENSATOR INST L DWG OF SPECIFIC AIRCRAFT INSTALLATION BULLETIN FOR CONNECTION INFORMATION NOT USED ON SOME AIRCRAFT MODELS THIS CONNECTOR IS PARTIAL PROVISION FOR AUTOMATIC PITCH TRIM SYSTEM OPTIONAL REFER TO AUTOTRIM SECTION OF SPECIFIC A C INSTALLATION BULLETIN FOR CONNECTION INFORMATION IM ADDITION AIRCRAFT INTERFACE INFORMATION THIS CONNECTOR CONTAINS PROVISIONS FOR ALTITUDE VERTICLE SPEED SELECTOR OPTION REFER TO INSTALLATION NO 119 4 BULLETIN NO 360 FOR WIRING INFORMATION STEC IF THE AIRCRAFT HAS AN EXISTING SINGLE AXIS ROLL AUTOPILOT INSTALLED THE COMMON OF SECTION 5 OF THE PITCH STAB MASTER RAM PIERSON One 5 Woy SMICH SHOULD BE CONNECTED TO THE ROLL SOL ENABLE LEAD OF THE EXISTING AUTOPILOT THIS
45. D GROUND AIRFRAME GROUND DIRECTIONAL GYRO SEE NOTE 9 RATE GYRO PITCH MOTOR TRIM SWITCH UP TRIM SWITCH COM SHIELO GROUND ROLL MOTOR ROLL SOLENOID ROLL MOTOR ROLL SOL GNO SHIELD GROUND Ist Ed May 11 2001 TT NO CONTROL SEE NOTE 6 E WHEEL STEERING J SWITCH TO A C BUSS 20 GA MIN 8 NOTE t1 NOTES 1 FIELD FABRICATED WIRING TO BE 22 GA MINIMUM UNLESS OTHER WISE NOTED AND MUST MEET OR EXCEED THE REQUIREMENTS OF MIL W 22759 16 REFER TO RADIO MANUFACTURERS SERVICE AND OR INSTALLATION MANUAL FOR SPECIFIC INTERCONNECT INFORMATION REFER TO WIRING SECTION OF SPECIFIC AIRCRAFT INSTALLATION BULLETIN FOR FLAP COMPENSATION WIRING CONNECT A P A TO PIN 1 OF THE ANNUNCIATOR CONNECTOR IF A P A IS 14VDC AND TO PIN 2 IF A P A IS 28V0C INSERT JUMPER BETWEEN PINS 1 AND 2 OF THE OPTIONAL FLAP COMPENSATION CONNECTOR IF AN ALTITUDE VERTIAL SPEED SELECTOR ALERTER IS INSTALLED JUMPER BETWEEN PIN 7 AND PIN 6 FOR 14 VOLT OPERATION OR BETWEEN PIN 7 AND PIN 14 FOR 28 VOLT OPERATION USE P N 3536 2 POLE 3 POSITION TOGGLE SWITCH WHEN INSTALLING A FLIGHT DIRECTOR PICTORIAL IS DRAWN OF 3556 BECAUSE OF ITS COMPLEXITY IF A FLIGHT OIRECTOR IS NOT INSTALLED P N 3520 SPDT SWITCH MAY BE USED IF TRIM OPTION IS NOT INSTALLED PIN 50 OF P2 MUST BE CONNECTED TO THE AIRCRAFT A ANOTHER CIRCUIT BREAKER 5 AMP MAX OTHER THAN THE AUTOPILOT CIRCUIT BREAKER PIN CONNECT
46. DICATORS DO NOT PROVIDE NAV FLAG OUTPUTS FOR AUTOPILOT USE WHEN USED WITH THESE TYPE CONVERTER INDICATORS THE NAY FAILURE WARNING FUNCTION OF THE AUTOPILOT MUST BE DISABLED THIS MAY BE ACCOMPLISHEO THE ROLL FLIGHT GUIDANCE COMPUTER CONNECTOR ADD A JUMPER BETWEEN PIN 24 FLAG AND PIN 5 REG 10V AND A JUMPER BETWEEN PIN 6 NAV FLAG AND PIN 26 SIGNAL REFERENCE WIRE TO PIN 54 OF THE PITCH FLIGHT GUIDANCE COMPUTER IS PROVIDED FOR INSTALLATION OF ALTITUDE VERTICAL SPEED SELECTOR OPTION REFER TO WIRING SECTION OF SPECIFIC AIRCRAFT INSTALLATIOM BULLETIN FOR FLAP COMPENSATION WIRING THIS CONNECTOR CONTAINS PROVISIONS FOR FLIGHT DIRECTOR STEERING HORIZON ANO OR ALTITUDE VERTICAL SPEED SELECTOR OPTAINAL REFER TO SPECIFIC OPTION INSTALLATION BULLETIN FOR WIRING INFORMATION IN THIS 7 CONDUCTOR CABLE et PART NUMBER DESCRIPTION UST OF MATERIALS CABLE IS WIRED FOR USE WITH 28 VDC IF USED WITH 14 VDC THE FOLLOWING CHANGES MUST BE COMPLETED PRIOR N A TO USE INSTALL JUMPER AFFIXED TO PROGRAMMER CONNECTOR COVER BETWEEN PINS 5 AND 7 OF PROGRAMMER CONNECTOR MOVE WIRE IN PIN 1 TO PIN 6 MOVE WIRE IN PIN 14 TO PIN 18 NEXT ASSY BULLETIN 400 USED ON SCHEMATIC WIRING INTERCONNECT SYS 65 DRAWING NO REV INGLES 07 XY ki 1016 F pacu SHARP COGES 010 SCALE wot SCALE DRAWING SHEET DECMA XX 010 MEGGITT AVIONICS S TEC FLI
47. E a WIRING SYSTEM 40 50 7 SOME INSTALLATIONS MAY ALTERNATELY HAVE A BROWN WIRE IN PLACE OF BLACK AND Ile A VIOLET WIRE IN PLACE OF WHITE IN THIS 7 CONDUCTOR CABLE BULLETIN 300 PRACPONS 1 64 SIZE DRAWING NO REV 8 FOR SATLOC NAVIGATION INSTALLATIONS THE OPTIONAL ALTITUDE ENGAGE DISENGAGE SWITCH ASST USED ON ANGLES 0 10135 L MUST BE POWERED FROM PIN 4 10 VOLTS INSTEAD OF PIN 20 14 28 VOLTS NEXT assy USED ON Remove cures SCALE SHEET APPLICATIONS BREAK SHARP EDGES 010 N A DO NOT SCALE DRAWING 1 of 2 Ist Ed May 11 2001 7 7 MEGGITT AVIONICS S TEC FLIGHT LINE SERVICE MANUAL FOR RATE BASED AUTOPILOTS PAGE INTENTIONALLY BLANK 7 8 Ist Ed 11 2001 P2 39122 BEES 9399888856 886 0 9 SHIELD GROUND SIGNAL REF ROLL STR SIG PICH STR S6 LE BLACK RED ORANGE WHITE ANNUNCIATOR LOAD f GREEN ANNUNCIATOR CLOCK BLACK ANNUNCIATOR DATA SHIELD GROUND M MOOR up e TRIM MOTOR UP TRIM SOLENOID GROUND SOLENOID SHIELO GROUND MANUAL DOWN SW 1 MANUAL DOWN SW MANUAL UP SW 14 28 voc Ll SHEILD GROUND eras GNS FLAG GNS UP SHIELD GROUND 10 PARALLAX POT PITCH STR CENTERING WHITE WHITE GREEN RED BLACK BLACK WHITE GREEN RED RED WHITE GREEN BLACK REO OPTIONAL ELEVATOR T
48. EC FLIGHT LINE SERVICE MANUAL FOR RATE BASED AUTOPILOTS 50 51 52 Verify that a After 3 seconds TRIM becomes annunciated on the A P and the audible alert sounds b After 7 seconds TRIM flashes and the audible alert ceases Apply maximum fore pressure to the A C control wheel Verify that a After 3 seconds TRIM becomes annunciated on the A P and the audible alert sounds b After 7 seconds TRIM 4 flashes and the audible alert ceases Note Proceed to step 77 53 54 93 56 57 58 59 60 61 62 63 Set the A P Trim Master Switch to the ON position Apply maximum aft pressure to the A C control wheel Verify that a After 3 seconds the A C trim wheel begins to run nose down with increasing speed and TRIM becomes annunciated A P b After 7 seconds TRIM v flashes Apply maximum fore pressure to the A C control wheel Verify that a After 3 seconds the A C trim wheel begins to run nose up with increasing speed and TRIM becomes annunciated on the A P b After 7 seconds TRIM flashes Apply aft pressure to the A C control wheel until the A C trim wheel stops Press either fore or aft on both segments of the A P Manual Electric Trim Switch and then release Verify that the A P disconnects as follows RDY flashes on the A P and the audible alert sounds for 5 seconds after which RDY alone remains annunciated Press aft and maintai
49. EL UNITS MUST MEET OR EXCEED THE REQUIRMENTS OF MIL W 22759 16 ALL WIRING TO SYS 40 LES amp 91520 EFFECTIVE CODE AND ABOVE ROUTED AND SECURED IN ACCORDANCE WITH AC43 13 1A CHAPTER 11 SECTION 7 SYS 50 0131 amp 0132 EFFECTIVE CODE E AND ABOVE USE ONE SET OF CONTACTS ON THE EXTERNAL NAV GPS SELECT 1 2 2 REFER TO RADIO MANUFACTURERS SERVICE AND OR INSTALLATION INFORMATION FOR SWITCH THIS CONNECTION iS BECORMENDED WHEN INTERFACING E yp SPECIFIC INTERCONNECT INFORMATION RECEIVER 3 REMOVE JUMPER ACROSS PINS 23 amp 39 OF THE PROGRAMMER COMPUTER CONNECTOR 1 4 WHEN A HEADING SYSTEM IS INSTALLED REFER TO HEADING SYSTEM INTERCONNECT 0 APPROVAL S TEC Corporation DETAILS DWG 1014 AND HEADING SYSTEM MANUFACTURERS SERVICE AND OR s 17 s5 One Wa INSTALLATION INFORMATION FOR INTERCONNECT INFORMATION REFER TO DRAWING NO a sc Minera Wels et Cabe SAGRA 0508 FOR MODIFICATION REQUIRED TO ROLL BOARD OF PROGRAMMER COMPUTER CHECKED 5 20 85 DENIE N TE HARING VOR LOS aiT ANE AET eemo 6 IF DISCONNECT SWITCH IS NOT USED CONNECT WHITE AND GREEN WIRES AND COVER PROVED pean 5 30 83 SCHEMATIC EXTERNAL CONNECTION WITH HEAT SHRINK TUBING OR EQUIVALENT IF ALTITUDE ENGAGE DISENGAGE CNET m SWITCH IS NOT USED COVER BLUE LEAD AND TIE BACK INTO BUNDL
50. FLASHER WHT BLK BRN G S FLASHER WHT GRY ALT VS SEL OPTION UP MODIFIER WHT BLU SEE NOTE 6 DN MODIFIER WHT GRN ALT MODE GRAY VS SEL LIGHT G S_ARM WHT BLK SEE NOTE 8 VS MODE ORN AIRFRAME CNO ji VS MOD SELECT RED ROLL SOL LOGIC G S ENGAGE GRN G S ARMED BRN A C BUSS LOC SW SEE NOTE 2 C S ENABLE WHT VIO REG 10VDC YEL 22 GA TEST ON LIGHT LOGIC WHT AP A UP LIGHT LOGIC VIO VS COMMAND WHT BLK GRN 3L MASTER GND WHT 8LK ORN FIN 2 SWITCH P N 3505 SIG REF WHT ELK RED SEE NOTE 5 2 REG 10VDC WHT 22 GA NC SEE NOTES 3 amp 9 VS SEL SWITCH BLK PITCH SERVO P N 0107 OR 0108 q AP lt IO ROLL SOL ENABLE OF SAL EXISTING ROLL A P OR TO TRIM A RED PITCH STAB C B IF NO TRIM INTRPT BLK ROLL A P IS INSTALLED MAN TRIM UP GRN SEE NOTE 7 MAN TRIM DN WHT IPITCH STAB C SEE NOTES 2 amp 10 AT VA P N 4906 20 GA MIN 20 CA MIN TO GATT BUSS S PITCH STAB PITCH SOL A RED he b C B 5 AMP PITCH SOL GNO BLK SEE NOTE 12 MOTOR 1 GRN G S FLAG WHT Q MOTOR 2 YEL SEE NOTE 7 6 5 FLAG REO INTERFACE 2 TRIM SW A ORN G S UP CRN 6 5 INTERFACE TRIM SW B BLU 6 5 0 BLK TRIM SW CMO WHT SEE NOTE 12 PM TO ROLL SOL ENABLE OF EXISTING ROLL A P TRANSDUCER SIG GRN ND BLK REG IOVDC RE
51. FOR KING KCS 55 5A HEADING SYSTEM MEGGITT AVIONICS S TEC FLIGHT LINE SERVICE MANUAL FOR RATE BASED AUTOPILOTS REVISIONS RELEASED PER 6099 1 1 6 97 IWDAVIS A REV PER 6556 10 8 97 KEIRNAN ADDED SN3308 INFO PER E 0 7582 2 25 99 T PIERSON NOTES 1 2 EXISTING A P CABLE ASSY MAY BE USED FO INTERCONNECT SYSTEM 50 ROLL COMPUTER TO DESIRED HEADING SYSTEM BY REMOVING D G CONNECTOR amp CONNECTING EXISTING WIRES TO HDG INSTRUMENT RE PIN PROGRAMMER COMPUTER CONNECTOR AS REQUIRED SIGMA TEK 1U262 033 5 OR 1U262 034 6 USE STANDARD AUTOPILOT CABLE ASSY SAME FOR 5 6406 0 2 1 ITEM PART NUMBER DESCRIPTION LIST OF MATERIALS STEC One S TEC Woy Municip Airport Mineral Wells 76067 9236 SCHEMATIC HEADING SYSTEM INTER CONNECT DETAIL SYS 20 30 amp gt NEXT ASSY USED ON ope 10114 1 REMOVE BURRS i 27 wa eo orent oem TE 6 3 MEGGITT AVIONICS S TEC FLIGHT LINE SERVICE MANUAL FOR RATE BASED AUTOPILOTS PAGE INTENTIONALLY BLANK 6 4 Ist Ed May 11 2001 KING KCS 55 55A INTERCONNECT KCS 55 55A PROG COMP P101 D C SIGNAL HDG CRS RETURN HSI 100 100S HSI 100 100S PROG COMP P201 EXCITATION EXCITATION REF HDG SIGNAL SIGNAL REF COLLINS PN 101 PROG COMP 351A 3G EXCITATION HDG SIGNAL SIGNAL REF HDG SYNCHRO ROTOR H HDG SYNCHRO STA
52. GHT LINE SERVICE MANUAL FOR RATE BASED AUTOPILOTS PAGE INTENTIONALLY BLANK 7 18 Ist Ed 11 2001 MEGGITT AVIONICS S TEC FLIGHT LINE SERVICE MANUAL FOR RATE BASED AUTOPILOTS REVISIONS bare APPROVE RELEASED PER EO 953 10 21 82 ERSON EO 1565 7 1 85 PIERSOI PITCH PROGRAMMER ANNUNCIATOR DETAIL 1514 9 24 85 P N 0117 OR 0116 PFGC 22 FLAP TX EXC StE NOTES 3g A 11 FECO 922 3 13 87 MARK l l PFGC 39 FLAP TX TRIM Tul OPTION P TRIM INTRPT 1 FECO 1237 5 13 91 PFGC 73 FLAP TX EXC TRIM A C BUSS REF DC RTI OR Sort 4 1337 RT TO ROLL SOL ENBL OF EXST COMMON OF SECTION 3 OF PITCH STAB EO 6055 10 28 96 T PIERSON 12 POSITION ROLL AP OR TO PITCH STAB MASTER SWITCH CONV 70 NEW FORMAT NO REV PER EO 7773 m T Penson OPTION CONN G B E ROLL AP IS IN PITCH DISC TRIM INTRPT SWITCH 2912115 UT 7 34 15 TO FLAP POSITION POT SEE NOTES 4 amp 9 PITGH FLIGHT GUIDANCE COMPUTER nL AIRFRAME GND LAP TX EXC TRIM LAP TX TRIM FLAP TX EXC LAP TX 1 30 AIRCRAFT GND PFGC 24 GND 1715131271 LOGIC RESET TRIM LOGIC TRIM LIGHT CONTROL WHT BRN 171515121 SOX RAD WINDOW WET YEL PITCH SOL LOGIC WHT RED NTROL WHEEL PITCH DISC INTRPT SW P N 3519 PRESSURE TRANSDUCER P N 0111
53. IONS SHOWN AND JUMPER BETWEEN PINS 9 amp 10 OF PI ARE FOR S TEC D G 6401 OR 6406 WHEN AN HSI IS INSTALLED REMOVE THE JUMPER BETWEEN PINS 9 amp 10 OF AND REFER TO HEADING SYSTEM INTERCONNECT DETAILS DWG NO 1094 AND HSI MANUFACTURERS SERVICE INSTALLATION MANUAL FOR INTERCONNECT INFORMATION SOME NAV CONVERTER INDICATORS DO NOT PROVIDE NAV FLAG OUTPUTS FOR AUTO PILOT USE WHEN USED WITH THIS TYPE CONVERTER INDICATOR THE NAV FAILURE WARNING FUNCTION OF THE AUTO PILOT MUST BE DISABLED TO DISABLE THIS FUNCTION ADD A JUMPER BETWEEN PIN 13 NAV FLAG AND PIN 33 REG 10 AND ADD JUMPER BETWEEN PIN 14 NAV FLAG AND PIN 27 SIGNAL REFERENCE MEGGITT AVIONICS S TEC FLIGHT LINE SERVICE MANUAL FOR RATE BASED AUTOPILOTS 6413 SINGLE CUE 14 VOLTAGE SELECT JUMPER 28 ALT MANUAL VS SELECT VS COMMAND MASTER DISC SWITCH AUDIO OUTPUT ALTITUDE VERTICAL 1 SPEED SELECTOR ALERTER COMPUTER OPTIONAL ALTITUDE VERTICAL SPEED SELECTOR NOTES CONT D REVISIONS DESCRIPTION RELEASED PER E O 4257 3 T PiERSON REV FOD amp NOTE 11 EO 4482 4 14 94 PIERSON REV FOD amp NOTE 11 EO 4496 5 2 94 T PIERSON REV PER 500 7 e 22 94 RT 0 REV FOO PER O 5137 84 984 T PIERSON E REV NOTE 9 PER EO 5390 3 3 85 TPIERSON F REV PER EO 7572 REV PER FECO 2670 7 9 14 60 11 CONNECT PIN 27 THRO
54. ITCH WHT SOLENOID LI ESSEN RED AP GRN TEST RED TRIM TRIM INTR GRN MAN TRIM UP WHT TRIM DN TO G S RECEIVER SEE NOTE 2 SEE NOTE 9 PITCH SOL A4 PITCH SOL GND 6 MOTOR 1 4 MOTOR 2 5 TRIM SW A Lal TRIM Sw 27 TRIM SW COM 125 e 11 TRANSDUCER SIG m REO REG 10 43 12 WHT GS FLAG 58 BLK 05 DN 45 GRN GS UP 46 RED GS FLAG 2 r me ae DESCRIPTION One S TEC Woy Municipal Airport Mineral Wells Tx 76067 9236 SCHEMATIC WIRING INTERCONNECT SYSTEM 60 2 11055 Emm m IS E Eom 010 NEXT ASSY APPLICATIONS MEGGITT AVIONICS S TEC FLIGHT LINE SERVICE MANUAL FOR RATE BASED AUTOPILOTS PAGE INTENTIONALLY BLANK 7 16 Ist Ed 11 2001 ANNUNCIATOR 37 PIN 215 eT S STET S T8 14 eT S JUMPER PIN 14 UGHTS SEE Futuna a amp PIN 7 FOR NOTE 8 LIGHT BUSS 28V UGHT BUSS 14 28v 147 14 28 14 28 VDC INPUT WHT ALT BRN vs YEL FD ON GRAY PWR OM BLU WHT BLU REV REO UP wet REV SW GRN SW ORN HOG SW WHT RED PWR SW BRN YO TRIM GRAY vio AC COM FOR LCD
55. Low Voltage Flag on the Turn Coordinator is out of view Heading Channel Test 7 Center the HDG bug under the lubber line 8 Engage the A P HDG mode 9 Turn the HDG bug to the left 10 Verify that the A C control wheel turns to the left 11 Center the HDG bug under the lubber line 12 Verify that the A C control wheel stops 13 Turn the HDG bug to the right 14 Verify that the A C control wheel turns to the right 15 Center the HDG bug under the lubber line 16 Verify that the A C control wheel stops Navigation Channel Test Note If the heading system is an HSI this test cannot be performed In that case proceed to step 33 17 Tune the Navigation Receiver to the local VOR frequency 18 Adjust the OBS for a 100 leftward deflection of the Left Right needle from center 19 Engage the A P NAV mode 20 Verify that the A C control wheel turns to the left 21 Engage the A P mode to stop the A C control wheel 22 Adjust the OBS for a 100 rightward deflection of the Left Right needle from center 23 Engage the A P NAV mode 24 Verify that the A C control wheel turns to the right 25 Engage the A P REV mode 26 Verify that the A C control wheel turns to the left 3 18 Ist Ed 11 2001 27 28 29 30 31 32 MEGGITT AVIONICS S TEC FLIGHT LINE SERVICE MANUAL FOR RATE BASED AUTOPILOTS Engage the A P HDG mode to stop the A C control wheel Adjust the OBS for a 100 left
56. M UP lamp becomes illuminated on the A P b After 7 seconds the TRIM UP lamp flashes A P Disconnect Test 62 Press the A P ON OFF Mode Switch or the optional Remote Disconnect Switch 63 Verify that a Allof the annunciations are extinguished b The TRIM UP and TRIM DN lamps are extinguished c The RDY lamp is illuminated END OF TEST Ist Ed May 11 2001 3 13 MEGGITT AVIONICS S TEC FLIGHT LINE SERVICE MANUAL FOR RATE BASED AUTOPILOTS 3 6 Functional Ground Test for System 55 Power Up Test 1 Set the Battery Master Switch to the ON position 2 Setthe Avionics Master Switch to the ON position 3 Setthe A P Master Switch to the ON position 4 Verify that the following all annunciate on the A P for 10 seconds and then extinguish HDG RDY NAV CWS APR FAIL REV TRIM ALT GS VS 18 5 Verify that within 3 minutes RDY alone becomes annunciated on the A P 6 Verify that the Low Voltage Flag on the Turn Coordinator is out of view Heading Channel Test 7 Center the HDG bug under the lubber line 8 Engage the A P HDG mode 9 Turn the HDG bug to the left 10 Verify that the A C control wheel turns to the left 11 Center the HDG bug under the lubber line 12 Verify that the A C control wheel stops 13 Turn the HDG bug to the right 14 Verify that the A C control wheel turns to the right 15 Center the HDG bug under the lubber line 16 Verify that the A C control wheel stops Navigation Chann
57. MALE 50 PIN 50 PIN FEMALE MALE 9524 BREAKOUT BOX NEVER CONNECT SIMULTANEOUSLY 78 PIN 78 PIN FEMALE MALE SYS 60 1 60 2 65 PSS 50 PIN 9524 BREAKOUT BOX SYS 40 50 50 PIN MALE 50 PIN FEMALE 9524 BREAKOUT BOX SYS 20 30 30 ALT 50 PIN FEMALE 50 PIN MALE 9524 BREAKOUT BOX SYS 55 55X 550 Fig 1 2 Breakout Connections 0109 RFGC 0110 PFGC 50 PIN FEMALE MALE 0101 0102 0103 0104 0116 0117 0141 0142 PROG ANNUN 0129 0130 ROLL ONLY 0131 0132 ROLL amp PITCH PROG COMP 50PIN 44 PIN 44 PIN MALE FEMALE MALE 01260 TC ROLL COMP 01261 39198 PITCH COMP ADAPTER CABLE 50 PIN 50 PIN FEMALE MALE 01192 ROLL amp PITCH PROG COMP 50 PIN MALE Ist Ed May 11 2001 MEGGITT AVIONICS S TEC FLIGHT LINE SERVICE MANUAL FOR RATE BASED AUTOPILOTS SECTION 2 ROLL CENTERING Ist Ed May 11 2001 2 1 MEGGITT AVIONICS S TEC FLIGHT LINE SERVICE MANUAL FOR RATE BASED AUTOPILOTS PAGE INTENTIONALLY BLANK 2 2 Ist Ed May 11 2001 MEGGITT AVIONICS S TEC FLIGHT LINE SERVICE MANUAL FOR RATE BASED AUTOPILOTS 2 0 Roll Centering The Roll Centering Adjustment should be performed routinely to ensure optimal A P system performance 21 Ground Roll Centering Adjustment 1 2 Level the A C Set the A P Master Switch to the ON position Wait until RDY alone becomes annunciated on the A P display upon completion of the power up self test
58. ODEL 4000C 5 OR 6 10445 004 9 014 4 1U262 015 5 D C HDG SIGNAL IU445 004 9 EXC 10 VDC HDG CRS RETURN EXC GND D C CRS SIGNAL EXC 10 3 DC HDG CRS SIG EXC GND DC HDG SIG DC CRS SIG LIST OF MATERIALS 1 APPROVAL STEC Corporation person 8 29 3 One S TEC Woy 2 Municipal Airport Minerol Wells Tx 76067 9236 SCHEMATIC HEADING SYSTEM Dan CAES SPE FED INTERCONNECT DETAIL SYS 60 65 aaa DECIMAL XXX 005 BULLETIN 400 DECIMAL XX 010 N A BULLETIN 100 FRACTIONS 1 64 DRAWING NO 1003 NEXT ASSY USED ON C APPLICATIONS BREAK SHARP EDGES 010 SCALE N A DO NOT SCALE DRAWING SHEET 1 of 2 Ist Ed May 11 2001 6 11 SIGMA TEK DG NOTES MM 07 W262 014 13 OR 11 OR 1 EXISTING AUTOPILOT CABLE ASSY MAY BE USED TO INTERCONNECT 10262 015 12 OR 13 SYSTEM 60 ROLL COMPUTER TO DESIRED HEADING SYSTEM BY REMOVING D G CONNECTOR AND CONNECTING EXISTING WIRES TO HDG INSTRUMENT EXC 10 VDC RE PIN RFGC CONNECTOR AS REQUIRED EXC GND 2 NOT APPLICABLE TO 331A 3F INDICATOR ELIGIBLE ONLY ON 331A 3G DC SIG INDICATOR P N S 331A 3G 001 002 003 005 006 AND 007 ONLY DC CRS SIG 3 SIGMA 11262 035 5 OR 1U262 034 6 USE STAMDARD AUTOPILOT CABLE ASSY SAME AS FOR S TEC 6401 AND 6406 Pp 1 MEGGITT AVIONICS S TEC FLIGHT LINE SERVICE MANUAL FOR RATE BASED AUTOPILOT
59. OFF position Disconnect the A P cable harness from the Altitude Transducer Plug the proper end of Extender Cable P N 39310 into the A P cable harness in place of the actual Altitude Transducer Plug the other end of the Extender Cable into the Altitude Transducer Simulator connector Set the Pitch Command Selector Switch on the Altitude Transducer Simulator to the ENG A P ALT MODE position Disconnect the A P cable harness from the Pitch Servo Plug the proper end of Extender Cable P N 39309 into the A P cable harness in place of the actual Pitch Servo Plug the other end of the Extender Cable into the Servo Simulator connector Set the Trim Command Selector Switch on the Servo Simulator to the NEUTRAL position Set the Battery Master Switch to the ON position Set the Avionics Master Switch to the ON position Set the A P Master Switch to the ON position Wait until RDY alone becomes annunciated on the A P display upon completion of the power up self test Ist Ed May 11 2001 4 7 MEGGITT AVIONICS S TEC FLIGHT LINE SERVICE MANUAL FOR RATE BASED AUTOPILOTS 4 2 2 3 4 8 16 17 18 19 20 21 22 23 24 25 26 24 28 29 30 31 32 Engage the A P STB mode Center the A P TURN CMD knob under its index to null lateral movement of the A C control wheel Engage the A P ALT mode Verify that the voltage at the Servo Simulator SOL jack relative to the SOL GND jack is appro
60. OLERANCES MESS P EDS DECIMAL XXX 005 DECIMAL 010 FRACTIONS 1 64 ULLETIN 400 BULLETIN 100 NEXT ASSY USED ON APPLICATIONS BREAK SHARP EDGES 010 STEC One S TEC Woy Municipal Airport Mineral Wells Tx 76067 9236 SCHEMATIC HEADING SYSTEM INTERCONNECT DETAIL SYS 60 65 SCALE N A DO NOT SCALE DRAWING SHEET 2 of 2 6 13 MEGGITT AVIONICS S TEC FLIGHT LINE SERVICE MANUAL FOR RATE BASED AUTOPILOTS PAGE INTENTIONALLY BLANK 6 14 Ist Ed May 11 2001 MEGGITT AVIONICS S TEC FLIGHT LINE SERVICE MANUAL FOR RATE BASED AUTOPILOTS SECTION 7 SYSTEM INTERCONNECT DRAWINGS Ist Ed May 11 2001 7 1 MEGGITT AVIONICS S TEC FLIGHT LINE SERVICE MANUAL FOR RATE BASED AUTOPILOTS 7 2 Table of Contents System 20 30 e A ERU e emet e 7 3 System 30A TT s oct deti e e E ete e pere ert tu ets 7 5 System 40 50 ei Aie Rete dt ta Ages am A Ot I e e Rh a RES 7 1 SYSE DD s esce ctiain terni totu ed e e RUE e p eite RUM te o utente eerie sieben utt 7 9 System 55 55X effective 9 14 00 sistit SA de ea RO ba 7 11 System 60 1 Sx i Meu etm mde b A 7 13 System 60 2 EO dE DU ORE ER REPRE IRE RUE a 7 15 9 7 17 PSS E oh A ed o A A 7 19 Ist Ed May 11 2001 MEGGITT AVIONICS S TEC FLIGHT LINE SERVICE MANUAL FOR RATE BASED AUTOPILO
61. OOTSTRAP STATOR 2 HDG C T STATOR Z CRS DATUM STATOR 7 EDO 52D54 OR 52D154 52054 520154 AC HDG SIG AC CRS SIG EXC REF SIGNAL REF BENDIX IN 831A S TEC HSI 6443 INDICATOR PROG COMP PI 6443 INDICATOR CN 1 EXCITATION HOG SIGNAL CRS SIGNAL SIGNAL REF BOOTSTRAP 1 ROTOR H HDG C T ROTOR H CRS DATUM C T ROTOR H BOOTSTRAP 1 ROTOR C HDG ROTOR CRS DATUM C T ROTOR C BOOTSTRAP 1 STATOR X CRS DATUM C T STATOR SIGNAL REF SYNCHRO STATOR Y PROG COMP KPIS50 550A CUISINE STAIR Y HI Fi w CRS DUM SYNCRO CRS DATUM SYNCHRO ROTOR H PN 140017278504 85059 CRS DATUM C T STATOR Y CRS DATUM SYNCHRO STATOR Y 25A EXCITATION SYNCHRO ROTOR H PROG COMP STATOR X HDG SIGNAL A HDG SYNCHRO STATOR X INB31A BOOTSTRAP STATOR 2 8 CRS SIGNAL CRS DATUM SYNCHRO STATOR X 56 18 CT ROTOR CRS DATUM C T STATOR Z 27 SIGNAL E SYNCHRO STATOR Y EXCITATION 31 ROTOR H HOG C T STATOR Z aa E HOG SYNCHRO ROTOR C AC CRS SIG B CRS CT ROTOR H F CRS DATUM SYNCHRO ROTOR C SIGNAL REF r 19_ CRS ROTOR ROTOR 33 BOOTSTRAP ROTOR C STATOR 2 LFS CRS DATUM SYNCHRO STATOR Y EDO NSD 360 360A DG 360 CESSNA IG 832A IG 832C IG 895A EDO 520254 RC ALLEN DG 105 0010 01 MODEL RCA110 3 DG MODEL 4000C 5
62. OR 6 SANDEL SN3308 PROG COMP NSO 360 19262 014 4 PROG COMP RANG IG 832 895A RNC PROG COMP SANDEL SN3308 EXC 10 voc 3 20 re AC 4 EXC is EXC 10 voc hz o c EXC REF DC CRS SIG me EXC END Ho m DC CRS HI SIG REF 12 22 DC HDG CRS LO 22 yyy 26 Lo 12 D C CRS LO i NOTE SANDEL INDICATOR MUST CONFIGURED FOR KCS 55 5A HEADING SYSTEM LIST OF MATERIALS SCHEMATIC WIRING INTERCONNECT SYSTEM 55 55X BULLETIN 600 _ USED ON NEXT ASSY ied B DATE APPLICATION DO NOT SCALE DRAWING SHEET 4 or 1 Ist Ed May 11 2001 MEGGITT AVIONICS S TEC FLIGHT LINE SERVICE MANUAL FOR RATE BASED AUTOPILOTS PAGE INTENTIONALLY BLANK 6 10 Ist Ed May 11 2001 MEGGITT AVIONICS S TEC FLIGHT LINE SERVICE MANUAL FOR RATE BASED AUTOPILOTS REVISIONS DESCRIPTION PROVED RELEASED PER EO 263 REDRAWN WITH CHANGES FECO411 REV PER FECO 1532 REV PER EO 1598 REV PER EO 2063 11 6 87 REV PER 2107 REV PER 2322 4 11 89 REV PER EO 2385 7 31 89 REV PER 2424 2874 REV PER 2955 REV PER 5584 REDRAWN PER EO 4266 10 4 93 REDRAWN PER 4484 REV PER EO 5087 ADD NOTE 3 PER EO 5560 21 95 PIERSON REV PER EO 7588 2 19 99 J FROST EDO NSD 360 360A DG 360 KING 5 55 55 INTERCONNECT CESSNA ARC IG 832A IG 832C IG 895A 2 KCS A NSD 3
63. OR RATE BASED AUTOPILOTS 3 4 23 Turn the HDG bug to the right 24 Verify that the A C control wheel turns to the right 25 Center the HDG bug under the lubber line 26 Verify that the A C control wheel stops Navigation Channel Test with Heading System DG or HSI Installed 27 Tune the Navigation Receiver to the local VOR frequency 28 Adjust the OBS DG or Course Pointer HSI for a 100 leftward deflection of the Left Right needle from center 29 Engage the A P LO TRK or HI TRK mode 30 Verify that the A C control wheel turns to the left 31 Adjust the OBS DG or Course Pointer HSI for a 100 rightward deflection of the Left Right needle from center 32 Verify that the A C control wheel turns to the right 33 Adjust the OBS DG or Course Pointer HSI for a centered Left Right needle to stop the A C control wheel Note Proceed to step 41 Navigation Channel Test with No Heading System Installed 34 Tune the Navigation Receiver to the local VOR frequency 35 Adjust the OBS for a 100 leftward deflection of the Left Right needle from center 36 Engage the A P LO TRK or HI TRK mode 37 Verify that the A C control wheel turns to the left 38 Adjust the OBS for a 10046 rightward deflection of the Left Right needle from center 39 Verify that the A C control wheel turns to the right 40 Adjust the OBS for a centered Left Right needle to stop the A C control wheel A P Disconnect Test 4
64. OR RATE BASED AUTOPILOTS PAGE INTENTIONALLY BLANK 7 10 Ist Ed 11 2001 P2 39122 SHIELD GROUND FD Locke SIGNAL REF RED ROLL STR SIG ORANGE PITCH STR SIG WHITE ANNUNCIATOR LOAD 1 73 GREEN K O0 ANNUNCIATOR CLOCI BLACK ANNUNCIATOR DATA JE SHIELD GROUND TRIM MOTOR 0N WHITE TRIM MOTOR UP GREEN TRIM SOLENOID RED GROUND SOLENOID BLACK SHIELD GROUND ANNUNCIATOR OPTIONAL ELEVATOR TRIM SYSTEM COMMAND SWITCH 7 Sn 1 TRIM INTERRUPT BLACK MANUAL DOWN SW WHITE MANUAL UP SW GREEN 14 28 VOC TRIM RED een 17 G S FLAG WHITE RECEIVER TRIM MASTER SWITCH B G S B Down BLACK SEE NOTE 2 SHIELD GROUND 10 VOC PARALLAX POT RED PITCH STR CENTERING WHITE FD POT GROUND BLACK SIG REF H j wHT BRN FLAG GREEN ENGAGE SIG f chiy ALT SEL CONTROL BLUE VS SIGNAL WHT RED Fo wee Wit SHIELD GROUND AUDIO WHITE GROUND BLACK ALT SEL JUMPER WHITE ROLL SOL LOGIC YD PITCH FLAP SIGNAL REFERENCE ORANGE TRIM FLAP POT OPTION F D A S i M 5 8055 C AS DISC NOTE 44 TTT TRIM INTR i RT QUT PITCH FB ROLL FB MOTOR REF UP O
65. OT USED CAP OFF I APPROVA DATE THE ENDS OF THE WIRES MARKED A P DISCONNECT amp TIE BACK INTO WIRING BUNDLE CS PRAWN TUCKER 9 19 96 One 5 Woy 6 A REMOTELY MOUNTED AUDIBLE ALARM PIEZO ALARM 5 P N 6547 IS REQUIRED TO PROVIDE 9 19 96 Municipal Airport Mineral Wells Tx 76067 9236 AN AUDIBLE ELEVATOR OUT OF TRIM INDICATION WHEN THE PITCH COMPUTER IS LOCATED OUTSIDE M Jess ERMAN 178 97 TITLE 3 ff caso SCHEMATIC EXTERNAL WIRING 7 ATTACH 5279 SOCKETS TO WIRE WHERE APPLICABLE USING 22520 2 01 CRIMPING TOOL amp DMC 22520 2 06 INSERT ee o INTERCONNECT SYS 20 30 B PIN 42 TO GND ENABLES GPS TRACK GAIN SETTING USE ONE SET OF CONTACTS ON THE EXTERNAL 147 DECIMAL XXX 005 AP SELECT SWITCH FOR NAV GPS THIS CONNECTION IS REQUIRED WHEN INTERFACING TO GPS RECEIVER 858 DECIMAL 010 1 1 1 BULLETIN 700 FRACTIONS 1 64 SCALE N A DO NOT SCALE DRAWING 7 3 NEXT ASSY USED ON APPLICATIONS Ist Ed May 11 2001 MEGGITT AVIONICS S TEC FLIGHT LINE SERVICE MANUAL FOR RATE BASED AUTOPILOTS PAGE INTENTIONALLY BLANK 7 4 1st Ed May 11 2001 MEGGITT AVIONICS S TEC FLIGHT LINE SERVICE MANUAL FOR RATE BASED AUTOPILOTS REVISIONS DESCRIPTION APPROVED RELEA 0 5 2 97 M KEIRNAN EASED PER E O 6397 A REV PER FECO 2052 7 8 97 M KEIRNAN B REV PER EO 6550 10 1 97 M KEIRNAN REV PER EO 669
66. OWN zm efe d DRA REV 12 SOME INSTALLATIONS MAY ALTERNATELY HAVE A BROWN WIRE IN PLACE OF BLACK AND A Pepe 9913 1 ANY WIRES NOT USED SHALL TERMINATED WITH SUITABLE INSULATEO MATERIAL VIOLET WIRE IN PLACE OF WHITE IN THIS 7 CONDUCTOR CABLE NEXT ASSY USED N APPUCATONS se SRE WA sene omne SET Ist Ed May 11 2001 MEGGITT AVIONICS S TEC FLIGHT LINE SERVICE MANUAL FOR RATE BASED AUTOPILOTS PAGE INTENTIONALLY BLANK 7 20 Ist Ed 11 2001 MEGGITT AVIONICS S TEC FLIGHT LINE SERVICE MANUAL FOR RATE BASED AUTOPILOTS SECTION 8 SYSTEM SPECIFICATIONS Ist Ed May 11 2001 8 1 MEGGITT AVIONICS S TEC FLIGHT LINE SERVICE MANUAL FOR RATE BASED AUTOPILOTS PAGE INTENTIONALLY BLANK 8 2 Ist Ed May 11 2001 MEGGITT AVIONICS S TEC FLIGHT LINE SERVICE MANUAL FOR RATE BASED AUTOPILOTS Programmer Computer System 20 30 Power Required Weight Dimensions TSO Programmer Computer System 40 Power Required Weight Dimensions TSO Programmer Computer System 50 Power Required Weight Dimensions TSO Programmer Computer System 55 Power Required Weight Dimensions TSO Programmer Computer System 55X Power Required Weight Dimensions TSO Programmer Computer System 550 Power Required Weight Dimensions TSO Programmer System 60 1 Power Required Weight Dimensions TSO Programmer System 60 2
67. P PROG COMP KCS 55 55A ROC COM MESA 22 10445 004 9 Pt P101 PI fa um CRS DATUM H FE AF EA 4 x CRS DATUM C 28 71 o c SIGNAL 28 D C SIGNAL EC EM E CRS DATUM X HOG CRS RETURN LS 22 HH HOG CRS RETURN SIG CRS DATUM Y m Le m 11 CRS SIG 22 CRS DATUM 2 D C CRS SIGNAL Le 11 D C CRS SIGNAL m m ERROR C T Z AERONETICS MODEL 8000 SIGMA TEK DG AZIMUTH XMTR Z HDG ERROR C T Y PROG COMP PROG COMP 262 014214 OR 11 PROG COMP AZIMUTH XMTR Y NARCO HSI 100 1008S 2 015 12 OR 15 UDG ERROR C EXCITATION BOOTSTRAP ROTOR H a A exc 10 voc NOTE 2 CRS SIGNAL ERROR C PROG COMP HSI 100 1005 HOG SIGNAL HDG C T ROTOR H 45 EXC GND 20 SIGNAL REF AZIMUTH XMTR C P201 CRS SIGNAL CRS DATUM C T ROTOR H 28 DC HOG SIG HDG SIGNAL HDG ERROR CT H EXCITATION SIGNALERER BOOTSTRAP ROTOR C 11 CRS SIG EXCITATION AZIMUTH XMTR H EXCITATION REF HDG C T ROTOR C ei CRS SIGNAL HOG SIGNAL SIGNAL REF COLLINS 101 PROG COMP 331A 3G NOTE 3 EXCITATION HDG SIGNAL CRS SIGNAL Z CRS DATUM SYNCHRO ROTOR H SYNCHRO ROTOR SYNCHRO STATOR x CRS DATUM SYNCHRO STATOR X KING 550 550A CRS DATUM C T ROTOR C BOOTSTRAP STATOR X HDG C T STATOR X CRS DATUM C T STATOR X BOOTSTRAP STATOR Y HOG C T STATOR Y CRS DATUM C T STATOR Y B
68. PER EO 1527 ADD 52D54 154 PER FECO 916 REV PER EO 2063 REV PER EO 2107 REV PER EO 2385 REV PER EO 2424 REV PER EO 2875 REV PER EO 2953 REV PER EO 3384 REV PER 4126 REDRAWN PER 4266 APPROVED o 1 o gt a gt tix olnimjojo a lt ni ind t ER eje eom Co ADD NOTE 2 PER EO 5561 8 21 95 PIERSON REV PER EO 6555 10 9 97 REV PER 7585 2 19 99 SIGMA lU445 004 9 IU445 004 9 EXC 10 EXC GND DC HDG SIG N N BEE SIGMA TEK DG 1U262 014 15 OR 11 OR NOTE 2 19262 015 12 OR 13 EXC 10 VDC SIG EDO 52054 OR 520154 52054 154 AC HDG SIG EXC REF SIGNAL REF BENDIX IN B31A PN 400172 8504 8505 PROG COMP p rem e BULLETIN 300 NEXT ASSY USED ON APPLICATIONS AC HDG SIG EXCITATION SIGNAL REF HDG CT ROTOR H BOOTSTRAP ROTOR H HDG CT ROTOR C BOOTSTRAP ROTOR C STATOR Z DRAWN PIERSON 8 29 85 CHECKED B 30 83 ENGINEER 8 30 83 One S TEC Way Municipal Airport Mineral Wells Tx 76067 9236 TITLE SCHEMATIC HEADING SYSTEM INTERCONNECT DETAIL SYS 40 50 DRAWING NO 1 01 A SCALE N A DO NOT SCALE DRAWING SHEET 1062 DECIMAL XXX 005 DECIMAL XX FRACTIONS 1 64 BREAK SHARP EDGES 010 MEGGITT AVIONICS S TEC FLIGHT LINE SERVICE MANUAL FOR RATE BASED AUTOPILOTS PAGE INTENTIONALLY BLANK 6 6 Is
69. Press and hold the A P Push Mode Switch for 3 seconds or press the optional Remote Disconnect Switch 42 Verify that RDY flashes on the A P and the audible alert sounds for 5 seconds after which RDY alone remains annunciated and the audible alert ceases END OFTEST Ist Ed May 11 2001 MEGGITT AVIONICS S TEC FLIGHT LINE SERVICE MANUAL FOR RATE BASED AUTOPILOTS 3 2 Functional Ground Test for System 30 Power Up Test 1 Set the Battery Master Switch to the ON position 2 Setthe Avionics Master Switch to the ON position 3 Setthe A P Master Switch to the ON position 4 Verify that RDY ALT ST HD LO TRK HI TRK TRIM UP and TRIM DN all annunciate on the A P 5 Verify that the TRIM UP annunciation extinguishes after 2 seconds 6 Verify that RDY ST HD LO TRK HI TRK and TRIM DN annunciations all extinguish after 7 seconds 7 Verify that the ALT annunciation extinguishes after 10 seconds 8 Verify that within 3 minutes RDY alone becomes annunciated on the A P 9 Verify that the Low Voltage Flag on the A P is out of view Stabilizer Channel Test 10 Center the A P TURN CMD knob under its index 11 Engage the A P ST mode 12 Tum the A P TURN CMD knob to the left 13 Verify that the A C control wheel turns to the left 14 Center the A P TURN CMD knob under its index 15 Verify that the A C control wheel stops 16 Turn the A P TURN CMD knob to the right 17 Verify that the A C control wheel turns to the right 18 C
70. Proceed to step 55 Navigation Channel Test with No Heading System Installed 44 45 46 4T 48 Tune the Navigation Receiver to the local VOR frequency Adjust the OBS for a 100 leftward deflection of the Left Right needle from center Engage the A P NAV mode Verify that the A C control wheel turns to the left Adjust the OBS for a 100 rightward deflection of the Left Right needle from center Ist Ed May 11 2001 MEGGITT AVIONICS S TEC FLIGHT LINE SERVICE MANUAL FOR RATE BASED AUTOPILOTS 49 Verify that the A C control wheel turns to the right 50 Engage the A P REV mode 51 Verify that the A C control wheel turns to the left 52 Adjust the OBS for a 100 leftward deflection of the Left Right needle from center 53 Verify that the A C control wheel turns to the right 54 Adjust the OBS for a centered Left Right needle to stop the A C control wheel Altitude Channel Test 55 Apply maximum fore and aft pressure to the A C control wheel to sense its freedom of movement 56 Engage the A P ALT mode 57 Apply for and aft pressure to the A C control wheel to verify its reduced freedom of movement Trim Channel Test 58 Apply maximum aft pressure to the A C control wheel 59 Verify that a After 3 seconds the TRIM DN lamp becomes illuminated on the A P b After 7 seconds the TRIM DN lamp flashes 60 Apply fore pressure to the A C control wheel 61 Verify that a After 3 seconds the TRI
71. RFRAME GROUND LOC Sw PROGRAMMER RADIO HR GND ANNUNCIATOR RADIO t TEST NAV FLAG A P DISCONNECT NAV FLAG YELLOW A P At LOGIC RESET BRN C3 NAV FAIL BLK REG 10 WHT LOC SWITCH WHT RED SOFT LIGHT LOGIC RED NAV MODE ORN ROLL CENTER YELLOW APPR LOGIC GREEN ROLL SOL LOGIC BLUE HDG MODE CAPT LITE GRAY REV MODE WHT 50 RADIO WINDOW WHT BLK GYRO TACH WHT BRN FO FLAG LO WHT ORN ROLL BAR HI WHT YEL ROLL BAR LO WHT GRN SEE NOTE 6 JUMPER TO DISABLE WEE IL m m fof fs kabel sls RATE GYRO GYRO TACH GREEN GYRO SIGNAL WHT GYRO SIGNAL 16 6 Hat 25
72. RIM SYSTEM ANNUNCIATOR SEE NOTE 8 188 4 TRIM INTR SWITCH RT OUT PITCH FB ROLL FB TO A C BUSS G S RECEIVER SEE NOTE 2 OPTION F O A S WH WHITE BLACK FD POT GROUND SIG F D FLAG ALT ENGAGE tt ALT SEL CONTROL VS SIGNAL rb erase SHIELD GROUND WHT BRN GREEN GRAY BLUE WHT RED VIOLET 1282200 TRIM MASTER SWITCH UP OUT FD ENGAGE 15 VOC 15 10V ONLY GROUND AP FO FLAG TRIM C 8 MOTOR REF MEGGITT AVIONICS S TEC FLIGHT LINE SERVICE MANUAL FOR RATE BASED AUTOPILOTS 6413 SINGLE CUE REVISIONS REV DESCRIPTION RELEASED PER 4257 8 21 95 REV FOD amp NOTE 11 EO 4482 DATE APPROVED 2 14 94 T PIERSON REV amp NOTE 11 EO 4496 5 2 94 REV PER EO 5080 6 22 94 R T T PIERSON D FOD PER EO 5137 8 4 84 IT PERSON E REV NOTE 9 PER EO 5390 3 3 95 T PIERSON REV PER EO 7572 2 24 99 PIERSON 5 3 AUDIO G WHITE SHIELD GROUND GROUND A gt BLACK ALT SEL JUMPER WHITE see NOTE 5 FOR USE WITH YAW DAMPHR OPTION BPLEBELEBERI S Y S T E M 5 5 C U T E R SEE NOTE 10 Ist Ed May 11 2001 ROLL SOL LOGIC YD wHT RED PITCH FLAP POT SIGNAL REFERENCE l
73. ROWN WIRE IN PLACE OF BLACK AND A VIOLET WIRE IN PLACE OF WHITE IN THIS 7 CONDUCTOR CABLE Ist Ed May 11 2001 SEE NOTE 2 RATE GYRO DIRECTIONAL GYRO ROLL SERVO ALT SEL ENG GRN C D NOTE 6 N C AP OISCONNECT REV PER EO 5157 8 19 94 T PIERSON REV PER EO 7572 2 24 99 T PIERSON TO FLAP POSITION POT NOTE 7 PITCH FLIGHT GUIDANCE COMPUTER AIRFRAME GND E TX EXC TRM FLAP TX TRIM FLAP TX EXC FLAP TX WHT ORN ROLL LOGIC RESET TRIM LOGIC WHT BRN TRIM LIGHT CONTROL WHT YEL 50 RAD WINDOW WHT RED PITCH SOL LOGIC TRIM INTERCONNECT PITCH SERVO TRANSDUCER WHT BLK BRN FLASHER BLACK PITCH LOGIC RESET WHT GRAY G S FLASH WHT BLUE UP MODIFIER WHT GRN MODIFIER GRAY ALT MODE BLUE VS FLASHER WHT BLK TIME OELAY BY PASS ORN vs MODE RED VS MOD SELECT GRN 0 9 ENGAGE BRN G S ARMED G S ENABLE YELLOW PITCH FAIL DON LIGHT LOGIC UP LIGHT LOGIC WHT 22 GA REG 10 VDC WHT BLK RED SIGNAL REF WHT BLK ORN GROUND WHT B8LK YEL P STEERING CENT WHT BLK GRN VS COMMAND WHT BLK BLUE P STEERING BAR BLK VS SEL SW
74. S PAGE INTENTIONALLY BLANK 6 12 Ist Ed May 11 2001 SANDEL INDICATOR MUST BE CONFIGURED FOR KING KCS 55 55A HEADING SYSTEM COLLINS HSI 331A 6P 6R CRS SIG SIG REF HOG SIG HDG ERROR CT Z AZIMUTH XMTR Z HDG ERROR CT Y AZIMUTH XMTR Y HDG ERROR CT X AZIMUTH XMTR X HDG ERROR CT C AZIMUTH XMTR C HDG ERROR CT H EXCITATION AZIMUTH XMTR H S TEC HSI 6443 INDICATOR 6443 INDICATOR 1 EXCITATION HDG SIG CRS SIG SIG REF BOOTSTRAP 1 ROTOR H HDG C T ROTOR H CRS DATUM C T ROTOR H BOOTSTRAP 1 ROTOR C HDG C T ROTOR C CRS DATUM C T ROTOR C BOOTSTRAP 1 STATOR X CRS DATUM C T STATOR X HDG C T STATOR Y BOOTSTRAP 1 STATOR Y CRS DATUM C T STATOR Y HDG C T STATOR X BOOTSTRAP 1 STATOR Z CRS DATUM C T STATOR Z HDG C T STATOR 2 SANDEL SN 3308 SN3308 P2 DC SIG DC HDG DATUM DC CRS SIG DC CRS DATUM HDG CRS RETURN SIGNAL GND P1 Ist Ed May 11 2001 RC ALLEN DG 105 0016 01 MEGGITT AVIONICS S TEC FLIGHT LINE SERVICE MANUAL FOR RATE BASED AUTOPILOTS REVISIONS DESCRIPTION RELEASED PER EO 2955 REV PER EO 4125 REDRAWN PER EO 4266 REV PER EO 4484 REV PER EO 5958 REV PER EO 6554 APPROVED T 10 4 95 PIERSON PIERSON ROGERS lt 4 lt MODEL RCA110 3 CRS REF SIG REF RCA110 3 4 4 TIE REV PER EO 7588 10 8 97 2 19 99 J FROST LIST OF MATERIALS APPROVAL pee rs T
75. TOPILOTS 3 1 Functional Ground Test for System 20 Power Up Test 1 2 6 Set the Battery Master Switch to the ON position Set the Avionics Master Switch to the ON position Set the A P Master Switch to the ON position Verify that RDY ST HD LO TRK and HI TRK all annunciate on the A P for 7 seconds and then extinguish Verify that within 3 minutes RDY alone becomes annunciated on A P Verify that the Low Voltage Flag on the A P is out of view Stabilizer Channel Test 7 10 11 12 13 14 15 16 Center the A P TURN CMD knob under its index Engage the A P ST mode Turn the A P TURN CMD knob to the left Verify that the A C control wheel turns to the left Center the A P TURN CMD knob under its index Verify that the A C control wheel stops Turn the A P TURN CMD knob to the right Verify that the A C control wheel turns to the right Center the A P TURN CMD knob under its index Verify that the A C control wheel stops Note If the A P is not equipped with a Heading System proceed to step 34 Heading Channel Test 17 18 19 20 21 22 Center the HDG bug under lubber line Engage the A P HDG mode Turn the HDG bug to the left Verify that the A C control wheel turns to the left Center the HDG bug under the lubber line Verify that the A C control wheel stops Ist Ed May 11 2001 3 3 MEGGITT AVIONICS S TEC FLIGHT LINE SERVICE MANUAL F
76. TOR X HDG SYNCHRO STATOR Y HDG SYNCHRO ROTOR C EDO 50 560 560 DG 360 CESSNA ARC IG 852A IG 852C IG 895A NSD 360 PROG COMP IG 832 895A EXC 10 EXC GND DC HDG SIG NOTES 1 EXISTING AUTOPILOT CABLE ASSY MAY BE USED TO INTERCONNECT SYSTEM 40 50 COMPUTER TO DESIRED HEADING SYSTEM BY REMOVING D G CONNECTOR AND CONNECTING EXISTING WIRES TO HDG INSTRUMENT RE PIN PROGRAMMER COMPUTER CONNECTOR AS REQUIRED 2 SIGMA 1U262 0335 5 OR 10262 054 6 USE STANDARD AUTOPILOT CABLE 55 SAME AS FOR S TEC 6401 AND 6406 D G Ist Ed May 11 2001 BENDIX HSD 880 PROG COMP IN881A D C HDG SIGNAL HDG CRS RETURN AERONETICS MODEL 8000 PROG COMP EXCITATION HDG SIGNAL SIGNAL REF KING KPI 550 550A PROG COMP EXCITATION HDG SIGNAL SIGNAL REF EDO 52D254 DG MODEL 4000C 5 OR 6 MODEL 8130 HSI BOOTSTRAP ROTOR H HDG C T ROTOR H BOOTSTRAP ROTOR C HDG C T ROTOR C BOOTSTRAP STATOR X HDG C T STATOR X BOOTSTRAP STATOR Y HDG C T STATOR Y BOOTSTRAP STATOR Z C T STATOR 2 PROG COMP KPI550 550A SYNCHRO ROTOR H SYNCHRO STATOR X SYNCHRO STATOR Y SYNCHRO ROTOR C IU262 014 4 OR PROG COMP EXC 10 VDC EXC GND DC SIG 1U262 015 5 PROG COMP PROG COMP MEGGITT AVIONICS S TEC FLIGHT LINE SERVICE MANUAL FOR RATE BASED AUTOPILOTS REVISIONS DESCRIPTION RELEASED PER 1035 REDRAWN WITH CHANGES FECO417 REV PER FECO 521 REV
77. TS REVISIONS RELEASED PER EO 6098 O wavs REV PER EO 6384 5 6 97 MKEIRNAN amp REV FER EO taqa MEKEIRNAN D REV PER EO 66932 l12 23 87 FROST A P CB 5 AMP A P MASTER Sw Ga eS 2 20 98 S TEC P N 4908 ESN 3520 01260 TURN COORDINATOR 20 cA 01261 ROLL COMPUTER BATT BUSS PITCH COMPUTER 39188 CABLE ASSY 39189 CABLE ASSY ROLL SOL LOGIC BLU PITCH FAIL GRN ALT LED WHT UP LED YEL ON LED ORN ROLL LOGIC BLU PITCH FAJL GRN ALT LED WHT UP LED YEL DN LED ORN A P RED A RED d TO INSTRUMENT PANEL DIMMER 555 AP A4 RED DISC 11 I A P DISCONNECT 1 init M S TEC P N 3532 OPTIONAL REMOTE MODE SWITCH S TEC P N 3532 10 0 MODE SW SW WHT Nook 1OvDC BLU WHT ALT ENG DISENG S TEC P N 3532 N SEE NOTE paige Sema ma iEn SEE NOTE 6 OPTIONAL SEE NOTE 5 pupa e a piezo A __ HORN Hi WHT RHEOSTAT WHT TO INSTR PANEL DIMMER 8547 Eg HORN LO BLU WHT L R ART A4 RCVR SHIELD L R WHT 5 NOTE 2 ieda OPTIONAL DC HDG Hi XDCR SIG GRN HOG o T1 1 XDCR GND
78. To buy sell rent or trade in this product please click on the link below http www avionteg com STEC 9524 Breakout Box aspx AvionTEq est with full trust Flight Line Service Manual For Rate Based Autopilots MEGGITT AVIONICS S TEC P N 87102 MEGGITT AVIONICS S TEC FLIGHT LINE SERVICE MANUAL FOR RATE BASED AUTOPILOTS List of Effective Pages Theasterisk indicates pages changed added or deleted by the current change Section 5 deleted in its entirety RE RETAIN THIS RECORD IN THE FRONT OF THE MANUAL ON Record of Revisions RECEIPT OF REVISIONS INSERT REVISED PAGES THEN ENTER DATE INSERTED AND INITIAL REVISION INSERTION SBNUMBER INSERTION SBNUMBER DATE DATE BY INCLUDED DATE BY INCLUDED MEGGITT AVIONICS S TEC FLIGHT LINE SERVICE MANUAL FOR RATE BASED AUTOPILOTS PAGE INTENTIONALLY BLANK ii MEGGITT AVIONICS S TEC FLIGHT LINE SERVICE MANUAL FOR RATE BASED AUTOPILOTS SECTION 1 OVERVIEW Ist Ed May 11 2001 1 1 MEGGITT AVIONICS S TEC FLIGHT LINE SERVICE MANUAL FOR RATE BASED AUTOPILOTS PAGE INTENTIONALLY BLANK 1 2 Ist Ed May 11 2001 MEGGITT AVIONICS S TEC FLIGHT LINE SERVICE MANUAL FOR RATE BASED AUTOPILOTS 11 Service Manual Organization Overview Section 1 Roll Centering Section 2 Functional Ground Tests Section 3 Simulator Operation Section 4 Pilot s Operating Handbooks Section 5 Heading Interconnect Drawings Section 6 System Interconnect Drawings Section 7 System Specificati
79. Trim Servo Power Required Weight Dimensions TSO Pitch Servo Power Required Weight Dimensions TSO Current Requirements System 20 Average Operating Current Maximum Current Current Requirements System 30 Average Operating Current Maximum Current 8 4 14 28 VDC 2 3 Ib 5 250 x 2 100 x 13 33 in C9c C52a 14 28 VDC 1 1 Ib 3 250 x 1 812 x 5 800 in C9c 14 28 VDC 3 0 Ib 5 250 x 2 100 x 13 33 in C9c 52 14 28 VDC 0 90 Ib 3 420 x 1 600 x 6 500 in C9c C52a 14 28 VDC 9 VDC Nominal RPM less 2090 1 8 Ibs 3 250 x 3 250 x 6 550 in C3b 10 VDC Supplied by Programmer Computer 0 15 PSI Absolute 150 of Operating Maximum 0 20 Ibs 3 000 x 2 430 x 1 880 in 14 28 VDC 2 9 Ibs 3 880 x 3 750 x 7 250 in 9 14 28 VDC 2 9 165 3 880 x 3 750 x 7 250 in 9 14 VDC 28 VDC 1 0 Amp 0 5 Amp 3 0 Amp 2 0 Amp 14 VDC 28 VDC 1 0 Amp 0 5 Amp 5 0 Amp 3 0 Amp Ist Ed May 11 2001 MEGGITT AVIONICS S TEC FLIGHT LINE SERVICE MANUAL FOR RATE BASED AUTOPILOTS Current Requirements System 30 ALT 14 VDC 28 VDC Average Operating Current 1 0 Amp 0 5 Amp Maximum Current 3 0 Amp 2 0 Amp Current Requirements System 40 14 VDC 28 VDC Average Operating Current 1 0 Amp 0 5 Amp Maximum Current 3 0 Amp 2 0 Amp Current Requirements System 50 14 VDC 28 VDC Average Operating Current 1 0 Amp 0 5 Amp Maximum Current 5 0 Amp 3 0 Amp
80. UGH LEAD MARKED AUDIO ANY AVAILABLE NON MUTED INPUT OF THE AUDIO AMPLIFIER FOR PIN DESIGNATIONS NEAR THE AUDIO AMP CONNECTOR AMP INPUT BY USING 300 ohm 1 4 WATT RESISTORS GPS RECEIVER 429 OUTPUT MUST HAVE 121 AND 3512 LABELS REFER TO AMPLIFIER MANUFACTURER S SERVICE INFORMATION CONNECT PIN 43 SHIELD TO ANY CONVENIENT AIRFRAME GROUND AUDIO INPUTS MAY BE JOINED INTO A COMMON AUDIO REFER TO GPS MANUFACTURER S SERVICE AND OR INSTALLATION MANUAL FOR SPECIFIC INTERCONNECT INFORMATION REMOVE GPSS JUMPER BETWEEN PINS 38 AND 43 IF GPSS IS NOT USEQ 2 PART NUMBER DESCRIPTION APPLICATIONS LIST OF MATERIALS One S TEC Airport Mineral Wells Tx 76067 9236 SCHEMATIC WIRING INTERCONNECT SYSTEM 55 55X 1093 SORE nor sou 8 SIZE DRAWING NO MEGGITT AVIONICS S TEC FLIGHT LINE SERVICE MANUAL FOR RATE BASED AUTOPILOTS PAGE INTENTIONALLY BLANK 7 12 Ist Ed 11 2001 MEGGITT AVIONICS S TEC FLIGHT LINE SERVICE MANUAL FOR RATE BASED AUTOPILOTS AP MASTER SWITCH REVISIONS BATTERY BUS DESCRIPTION RELEASED PER E O 121 1 21 86 R WADE REDRAWN PER FO 1593 REV PER 922 REV PER FECO 988 AIRFRAME GND SSS Se A P REDRAWN PER EO 4266 10 4 TEST DISCONNECT REV PER EO 7572 2 24 99 ROLL FLIGHT GUIDANCE COMPUTER TO NAV SOL 20 RECEIVER CONVERTER AP A 20 GA NOTE 2 AI
81. UT FD ENGAGE 15 VOC 15 vDC 10v ONLY GROUND f PaRALLAX Por csee NOTE 5 FOR USE WITH YAW DAMPER OPTION ke FLAP POSITION POTS 3 SEE NOTE 3 SHIELD GROUND GPSS ARINC 429 A GPSS ARINC 429 B BEB if N M LIGHTS A P A oe SIECRING Ne e SHIELD GNO SEE NOTE 13 GPS STEERING USED ON 55X ONLY SEE NOTES 2 AND 12 AP MASTER OFF SWITCH 3536 OR 3520 FO SEE NOTE 7 ON TO AIRCRAFT INSTRUMENT LIGHT BUS A P DISCONNECT EXCITATION GROUND FOR D G GROUND SEE NOTE 9 AIRFRAME GROUND 3 20 GA MIN EXC 1 GROUND ALTERNATE DC HEADING LO DC HEADING i DC COURSE LO DC COURSE HI SHIELD GROUND HEADING SYSTEM SEE NOTE S FOR REF ONLY TRANSDUCER S Y 5 T E M 5 5 c B G B M P U T E R SHIELD GROUND NAV FLAG NAV FLAG L R RT GREEN ORANGE WHITE SEE NOTE 10 beka TRANSDUCER GROUND BLACK 10 VDC RED TRANSOUCER SIGNAL GREEN TO NAV RECEIVER CONVERTER SEE NOTE 2 AC HEADING ORANGE AC COURSE RED EXCITATION REF WHITE SIGNAL REFERENCE GREEN SHIELD GROUND EB RN BATTERY BUSS 4 gt PITCH SOL GND PITCH MOTOR TRIM SWITCH DN PITCH SOLENOIO L R RED LOC SWITCH BLACK SHIELD GROUND RATE GYRO TACH GREEN RATE GYRO REF WHITE RATE GYRO SIG BLACK SHIEL
82. WILL ENABLE THE PITCH STABILIZATION Moricpd Arport Minerol Wels Tx 76067 9236 SYSTEM ONLY WHEN A ROLL MODE IS ENGAGED ON THE EXISTING AUTOPILOT IF THE AIRCRAFT DOES NOT HAVE AN EXISTING ROLL AXIS A 10 IF USED WITH KING Kl 211 SERIES INTEGRATED GLIDESLOPE RECEIVER INDICATOR OR OTHER THE COMMON OF SECTION 3 OL THE PITCH STAG MASTER SWITCH SHOULD CONNECTED TO THE PITCH STAB IF AUTOPILOT OPTION SIMILAR INTEGRATED UNIT NOT PROVIDING zA FLAG OUTPUTS FOR AP USE CONNECT PFGC 77 IS INSTALLED IN CONJUNCTION WITH THE PITCH STAB SYSTEM WIRE PER DETAIL A DASH DENOTES WIRING REQUIRED WHEN OPTIONAL RED WIRE TO PIN 1 OF OPTION CONNECTOR RES 1006 AND CONNECT PIN 58 WHT WIRE TRIM SYSTEM IS INSTALLED PIN 2 OF OPTION CONNECTOR SIGNAL REF IF ALT PRESELECT OPTION IS INSTALLED PIN 10 OF THE 12 POSITION OPTION CONNECTOR MAY IF DESIRED BE CONNECTED TO A PANEL 11 ON SOME AIRCRAFT THE EXISTING FLAP TRANSMITTER 16 USED TO PRODUCE INFORMATION MOUNTED VS SELECTS ANNUNCIATOR LIGHT NOT SUPPLIED THE VS SELECT ANNUNCIATOR OUTPUT PROVIDES A LIGHT SENSOR CONTROLLED QUIRED TO CAUSE PITCH MOTOR TO WITH FLAP ACTUATION MAKE CONNECTIONS AS CALLED LOW WHEN IN VS SELECT MODE 100 MILLIAMP MAX Li SELECT A LAMP 327 FOR 2BV AIRCRAFT OR 8550 FOR 14V AIRCRAFT RECOM OUT iN THE WIRING INSTALLATION SECTION OF THE INSTALLATION BULLETIN 00 OF RATED VOLTAGE ANO CURRENT AND CONNECT AS SH
83. aft direction 44 Engage the A P ALT mode to stop the A C control wheel 45 Engage the A P VS mode 46 Command a pitch down using the A P ALT VS modifier knob 47 Verify that the A C control wheel moves in the fore direction 48 Engage the A P ALT mode to stop the A C control wheel Trim Channel Test Note If the A P is equipped with autotrim proceed to step 53 49 Apply maximum aft pressure to the A C control wheel 50 Verify that a After 3 seconds TRIM becomes annunciated on the A P and the audible alert sounds b After 7 seconds TRIM flashes and the audible alert ceases 51 Apply maximum fore pressure to the A C control wheel Ist Ed May 11 2001 3 23 MEGGITT AVIONICS S TEC FLIGHT LINE SERVICE MANUAL FOR RATE BASED AUTOPILOTS 52 Verify that a After 3 seconds TRIM becomes annunciated on the A P and the audible alert sounds b After 7 seconds TRIM 4 flashes and the audible alert ceases Note Proceed to step 77 53 54 99 56 57 58 59 61 62 63 64 65 66 67 Set the A P Trim Master Switch to the ON position Apply maximum aft pressure to the A C control wheel Verify that a After 3 seconds the A C trim wheel begins to run nose down with increasing speed and TRIM becomes annunciated A P b After 7 seconds TRIM flashes Apply maximum fore pressure to the A C control wheel Verify that a After 3 seconds t
84. ber line Engage the A P HDG mode Turn the HDG bug to the left Ist Ed May 11 2001 3 11 MEGGITT AVIONICS S TEC FLIGHT LINE SERVICE MANUAL FOR RATE BASED AUTOPILOTS 26 27 28 29 30 31 32 Verify that the A C control wheel turns to the left Center the HDG bug under the lubber line Verify that the A C control wheel stops Turn the HDG bug to the right Verify that the A C control wheel turns to the right Center the HDG bug under the lubber line Verify that the A C control wheel stops Navigation Channel Test with Heading System DG or HSI Installed 33 34 35 36 37 38 39 40 41 42 43 Tune the Navigation Receiver to the local VOR frequency Adjust the OBS DG or Course Pointer HSI for a 100 leftward deflection of the Left Right needle from center Engage the A P NAV mode Verify that the A C control wheel turns to the left Adjust the OBS DG or Course Pointer HSI for a 100 rightward deflection of the Left Right needle from center Verify that the A C control wheel turns to the right Engage the A P REV mode Verify that the A C control wheel turns to the left Adjust the OBS DG or Course Pointer HSI for a 100 leftward deflection of the Left Right needle from center Verify that the A C control wheel turns to the right Adjust the OBS DG or Course Pointer HSI for a centered Left Right needle to stop the A C control wheel Note
85. ction of the Left Right needle from center 38 Engage the A P NAV mode 3 28 Ist Ed May 11 2001 39 40 41 42 43 44 45 46 4T MEGGITT AVIONICS S TEC FLIGHT LINE SERVICE MANUAL FOR RATE BASED AUTOPILOTS Verify that the A C control wheel turns to the right Engage the A P REV mode Verify that the A C control wheel turns to the left Engage the A P HDG mode to stop the A C control wheel Adjust the OBS for a 100 leftward deflection of the Left Right needle from center Engage the A P REV mode Verify that the A C control wheel turns to the right Engage the A P HDG mode to stop the A C control wheel Adjust the OBS for a centered Left Right needle Altitude Channel Test 48 49 50 51 52 53 54 Move the A C control wheel until the elevator is in the neutral position Engage the A P ALT mode Press and hold the A P UP Switch Verify that the A C control wheel moves in the aft direction Release the A P UP Switch Press and hold the A P DN Switch Verify that the A C control wheel moves in the fore direction Note There will be a slight delay in this movement as the A C control wheel decelerates aft to the null 55 56 Release the A P DN Switch Engage the A P VS mode to stop the A C control wheel Vertical Speed Channel Test 51 58 59 60 61 Press and hold the A P UP Switch Verify that the A C control wheel moves in the aft
86. d on the ALT HOLD ON OFF Switch and the audible alert sounds a steady tone b After 7 seconds TRIM UP flashes and the audible alert becomes periodic A P Power Down Test 12 Push the ALT HOLD ON OFF Switch to the OFF state 13 Verify that all annunciations on the ALT HOLD ON OFF Switch are extinguished END OF TEST 3 4 Functional Ground Test for System 40 Power Up Test 1 Set the Battery Master Switch to the ON position 2 Setthe Avionics Master Switch to the ON position 3 Setthe A P Master Switch to the TEST position 4 Verify that the following are all annunciated on the A P STB HDG NAV APR REV 5 Verify that the RDY lamp is illuminated on the A P 6 Set the A P Master Switch to the ON position 7 Verify that all of the annunciations and the RDY lamp are extinguished 8 Verify that within 3 minutes the RDY lamp becomes illuminated on the A P 9 Verify that the Low Voltage Flag on the Turn Coordinator is out of view Stabilizer Channel Test 10 Center the A P TURN CMD knob under its index 11 Engage the A P STB mode 12 Turn the A P TURN CMD knob to the left 3 8 Ist Ed 11 2001 13 14 15 16 17 18 19 Note If the A P is not equipped with a Heading System proceed to step 41 MEGGITT AVIONICS S TEC FLIGHT LINE SERVICE MANUAL FOR RATE BASED AUTOPILOTS Verify that the A C control wheel turns to the left Center the A P TURN CMD knob under its index Verify that the A C control wheel stop
87. d then it alone remains annunciated 3 10 Functional Ground Test for System 60 2 Manual Excessive G Force Test 10 11 12 13 14 15 Set the Battery Master Switch to the ON position Set the Avionics Master Switch to the ON position Set the A P Master Switch to the TEST position Verify that the following are all annunciated on the A P RDY FD REV HDG APR VS ALT GS SEL CAP DSABL FAIL SOFT TRIM Verify that the UP and DN Switches on the A P are both illuminated Center the HDG bug under the lubber line Engage the A P HDG mode Apply fore and aft pressure to the A C control wheel to sense its freedom of movement Engage the A P ALT mode Apply fore and aft pressure to the A C control wheel to verify its reduced freedom of movement Press and hold the A P UP Switch while maintaining a grasp on the A C control wheel Verify that the pitch servo disengages after 1 2 second by sensing the increased freedom of A C control wheel movement in the fore and aft directions Release the A P UP Switch Verify that the pitch servo immediately re engages by sensing the reduced freedom of A C control wheel movement in the fore and aft directions Press and hold the A P DN Switch while maintaining a grasp on the A C control wheel Ist Ed May 11 2001 3 27 MEGGITT AVIONICS S TEC FLIGHT LINE SERVICE MANUAL FOR RATE BASED AUTOPILOTS 16 Verify that the pitch servo disengages after 1 2 second by sensing
88. direction Release the A P UP Switch Press and hold the A P DN Switch Verify that the A C control wheel moves in the fore direction Note There will be a slight delay in this movement as the A C control wheel decelerates aft to the null 62 Release the A P DN Switch Ist Ed May 11 2001 3 29 MEGGITT AVIONICS S TEC FLIGHT LINE SERVICE MANUAL FOR RATE BASED AUTOPILOTS 63 Engage the A P ALT mode to stop the A C control wheel Trim Channel Test Note If the A P is equipped with autotrim proceed to step 68 64 Apply maximum aft pressure to the A C control wheel 65 Verify that a After 3 seconds the A P DN Switch illuminates TRIM annunciates and the audible alert sounds a steady tone b After 7 seconds the A P DN Switch flashes TRIM flashes and the audible alert becomes periodic 66 Apply maximum fore pressure to the A C control wheel 67 Verify that a After 3 seconds the A P UP Switch illuminates TRIM annunciates and the audible alert sounds a steady tone b After 7 seconds the A P UP Switch flashes TRIM flashes and the audible alert becomes periodic Note Proceed to Step 92 68 Set the A P Trim Master Switch to the ON position 69 Apply maximum aft pressure to the A C control wheel 70 Verify that after 3 seconds the A C trim wheel begins to run nose down with increasing speed 71 Apply maximum fore pressure to the A C control wheel 72 Verify that after 3 seconds the A C trim wheel begins to r
89. e A P Remote Annunciator for 5 seconds and then it alone remains annunciated b ON alone remains annunciated on the A P Control Head Press aft and maintain pressure on both segments of the A P Manual Electric Trim Switch Verify that the A C trim wheel runs nose up at full speed and TRIM flashes on the A P Control Head Press and hold the A P Disconnect Trim Interrupt Switch Verify that the A C trim wheel stops Release the A P Disconnect Trim Interrupt Switch Verify that the A C trim wheel resumes running nose up at full speed Ist Ed May 11 2001 MEGGITT AVIONICS S TEC FLIGHT LINE SERVICE MANUAL FOR RATE BASED AUTOPILOTS 75 Release the A P Manual Electric Trim Switch 76 Verify that the A C trim wheel stops and the TRIM annunciation is extinguished 77 Press fore and maintain pressure on both segments of the A P Manual Electric Trim Switch 78 Verify that the A C trim wheel runs nose down at full speed and TRIM flashes on the A P Control Head 79 Press and hold the A P Disconnect Trim Interrupt Switch 80 Verify that the A C trim wheel stops 81 Release the A P Disconnect Trim Interrupt Switch 82 Verify that the A C trim wheel resumes running nose down at full speed 83 Release the A P Manual Electric Trim Switch 84 Verify that the A C trim wheel stops and the TRIM annunciation is extinguished END OF TEST A P Disconnect Test 85 Press the A P Disconnect Trim Interrupt Switch 86 Verify that the A P discon
90. e P N 39309 into the A P cable harness in place of the actual Roll Servo Plug the other end of the Extender Cable into the Servo Simulator connector Center the A P TURN CMD knob under its index Set the Battery Master Switch to the ON position Set the Avionics Master Switch to the ON position Set the A P Master Switch to the ON position Wait until RDY alone becomes annunciated on the A P display upon completion of the power up self test Engage the A P STB mode Verify that the voltage at the Servo Simulator SOL jack relative to the SOL GND jack is approximately 12 VDC A 14VDC 24 VDC A 28 VDC Verify that the voltage at the Servo Simulator MOTOR 1 jack relative to the MOTOR 2 jack is approxi mately 0 VDC Turn the A P TURN CMD knob to the right Verify that the voltage at the Servo Simulator MOTOR 1 jack relative to the MOTOR 2 jack is positive Center the A P TURN CMD knob under its index Turn the A P TURN CMD knob to the left Verify that the voltage at the Servo Simulator MOTOR 1 jack relative to the MOTOR 2 jack is negative 11 2001 4 5 MEGGITT AVIONICS S TEC FLIGHT LINE SERVICE MANUAL FOR RATE BASED AUTOPILOTS 4 2 2 4 2 2 1 4 6 Pitch Servo Heading System Installed l 2 10 11 12 13 14 15 16 17 18 19 20 21 22 23 Set A P Master Switch to the OFF position Set the Avionics Master Switch to the OFF position Set the Battery Mas
91. e Pitch Command Selector Switch on the Altitude Transducer Simulator to the PITCH UP position Verify that the voltage at the Servo Simulator MOTOR 1 jack relative to the MOTOR 2 jack is positive Set the Pitch Command Selector Switch on the Altitude Transducer Simulator to the PITCH DN position Verify that the voltage at the Servo Simulator MOTOR 1 jack relative to the MOTOR 2 jack is negative Set the Pitch Command Selector Switch on the Altitude Transducer Simulator to the ENG A P ALT MODE position Set the Trim Command Selector Switch on the Servo Simulator to the TRIM UP position Verify that after a 3 second delay the A P annunciates TRIM UP Set the Trim Command Selector Switch on the Servo Simulator to the NEUTRAL position Verify that the TRIM UP annunciation is extinguished Set the Trim Command Selector Switch on the Servo Simulator to the TRIM DN position Verify that after a 3 second delay the A P annunciates TRIM DN Set the Trim Command Selector Switch on the Servo Simulator to the NEUTRAL position Verify that the TRIM DN annunciation is extinguished 11 2001 4 9 MEGGITT AVIONICS S TEC FLIGHT LINE SERVICE MANUAL FOR RATE BASED AUTOPILOTS 4 2 3 4 3 4 10 Trim Servo 10 11 12 13 14 15 16 17 Set the A P Master Switch to the OFF position Set the Avionics Master Switch to the OFF position Set the Battery Master Switch to the OFF position Disconnect the A P cable harness from the Tr
92. e harness from the Altitude Transducer 5 Plug the proper end of Extender Cable P N 39310 into the A P cable harness in place of the actual Altitude Transducer 6 Plug the other end of the Extender Cable into the Altitude Transducer Simulator connector Ist Ed May 11 2001 10 11 12 13 14 15 16 17 18 19 20 21 22 23 24 25 26 27 28 29 30 31 Ist Ed May MEGGITT AVIONICS S TEC FLIGHT LINE SERVICE MANUAL FOR RATE BASED AUTOPILOTS Set the Pitch Command Selector Switch on the Altitude Transducer Simulator to the ENG A P ALT MODE position Disconnect the A P cable harness from the Pitch Servo Plug the proper end of Extender Cable P N 39309 into the A P cable harness in place of the actual Pitch Servo Plug the other end of the Extender Cable into the Servo Simulator connector Set the Trim Command Selector Switch on the Servo Simulator to the NEUTRAL position Set the Battery Master Switch to the ON position Set the Avionics Master Switch to the ON position Set the A P Master Switch to the ON position Wait until the A P has completed its power up self test Engage the A P ALT mode Verify that the voltage at the Servo Simulator SOL jack relative to the SOL GND jack is approximately 12 VDC A 14VDC 24 VDC A 28 VDC Verify that the voltage at the Servo Simulator MOTOR 1 jack relative to the MOTOR 2 jack is approxi mately 0 VDC Set th
93. el Test Note If the heading system is an HSI this test cannot be performed In that case proceed to step 33 17 18 19 20 21 Tune Navigation Receiver to local VOR frequency Adjust the OBS for a 100 leftward deflection of the Left Right needle from center Engage the A P NAV mode Verify that the A C control wheel turns to the left Engage the A P HDG mode to stop the A C control wheel Ist Ed May 11 2001 22 23 24 25 26 27 28 29 30 31 32 MEGGITT AVIONICS S TEC FLIGHT LINE SERVICE MANUAL FOR RATE BASED AUTOPILOTS Adjust the OBS for a 100 rightward deflection of the Left Right needle from center Engage the A P NAV mode Verify that the A C control wheel turns to the right Engage the A P REV mode Verify that the A C control wheel turns to the left Engage the A P HDG mode to stop the A C control wheel Adjust the OBS for a 100 leftward deflection of the Left Right needle from center Engage the A P REV mode Verify that the A C control wheel turns to the right Engage the A P HDG mode to stop the A C control wheel Adjust the OBS for a centered Left Right needle Altitude Channel Test 33 34 35 36 37 38 39 40 41 Move the A C control wheel until the elevator is in the neutral position Engage the A P ALT mode Command a pitch up using the A P ALT VS modifier knob Verify that the A C control wheel moves i
94. enter the A P TURN CMD knob under its index 19 Verify that the A C control wheel stops Note If the A P is not equipped with a Heading System proceed to step 37 Heading Channel Test 20 Center the HDG bug under the lubber line 21 Engage the A P mode 22 Turn the HDG bug to the left 23 Verify that the A C control wheel turns to the left Ist Ed May 11 2001 3 5 MEGGITT AVIONICS S TEC FLIGHT LINE SERVICE MANUAL FOR RATE BASED AUTOPILOTS 3 6 24 Center the HDG bug under the lubber line 25 Verify that the A C control wheel stops 26 Turn the HDG bug to the right 21 28 29 Verifv that the A C control wheel turns to the right Center the HDG bug under the lubber line Verifv that the A C control wheel stops Navigation Channel Test with Heading Svstem DG or HSI Installed 30 31 32 33 34 35 36 Tune the Navigation Receiver to the local VOR frequency Adjust the OBS DG or Course Pointer HSI for a 10096 leftward deflection of the Left Right needle from center Engage the A P LO TRK or HI TRK mode Verify that the A C control wheel turns to the left Adjust the OBS DG or Course Pointer HSI for a 100 rightward deflection of the Left Right needle from center Verify that the A C control wheel turns to the right Adjust the OBS DG or Course Pointer HSI for a centered Left Right needle to stop the A C control wheel Note Proceed to step 44
95. eriodic A P Disconnect Test 51 52 Press and hold the A P PUSH MODE Switch for 3 seconds or press the optional Remote Disconnect Switch Verify that RDY flashes on the A P and the audible alert sounds for 5 seconds after which RDY alone remains annunciated and the audible alert ceases END OF TEST 3 3 Functional Ground Test for System 30 ALT Power Up Altitude Channel Tests l 2 Apply fore and aft pressure to the A C control wheel to sense its freedom of movement Push the ALT HOLD ON OFF Switch to the ON state Verify that ON ALT TRIM UP and TRIM DN all annunciate on the ALT HOLD ON OFF Switch Verify that the TRIM UP annunciation extinguishes after 2 seconds Verify that the TRIM DN annunciation extinguishes after 7 seconds Verify that the ALT annunciation extinguishes after 10 seconds Apply fore and aft pressure to the A C control wheel to sense its reduced freedom of movement Trim Channel Test 8 9 Apply maximum aft pressure to the A C control wheel Verify that Ist Ed May 11 2001 3 7 MEGGITT AVIONICS S TEC FLIGHT LINE SERVICE MANUAL FOR RATE BASED AUTOPILOTS a After3 seconds TRIM DN becomes annunciated on the ALT HOLD ON OFF Switch and the audible alert sounds a steady tone b After 7 seconds TRIM DN flashes and the audible alert becomes periodic 10 Apply maximum fore pressure to the A C control wheel 11 Verify that a After 3 seconds TRIM UP becomes annunciate
96. ft Set Std Rate Turn Selector Switch on the Turn Coordinator Simulator to the 0 position Verify that the A C control wheel stops Set Std Rate Turn Selector Switch on the Turn Coordinator Simulator to the 50 LT position Verify that the A C control wheel turns to the right Set Std Rate Turn Selector Switch on the Turn Coordinator Simulator to the 0 position Verify that the A C control wheel stops Notes 1 7590 90 may be selected instead of 50 in steps 23 and 27 2 Turning the HDG bug sufficiently to the right will cause the A C control wheel to stop in step 24 3 Turning the HDG bug sufficiently to the left will cause the A C control wheel to stop in step 28 4 Setting the 9o Std Rate Turn Selector Switch to the VARY position enables custom turn rate selection using the Vary Adjust Pot The scale is 1 VDC for a std rate turn 3 sec as measured at the TURN RATE jack relative to the TURN RATE REF jack The voltage polarity is negative for a right turn and positive for a left turn Ist Ed 11 2001 MEGGITT AVIONICS S TEC FLIGHT LINE SERVICE MANUAL FOR RATE BASED AUTOPILOTS 4 4 2 No Heading System Installed and A P with STB Mode 1 2 10 11 12 13 14 15 16 17 18 19 21 22 23 24 25 26 Set the A P Master Switch to the OFF position Set the Avionics Master Switch to the OFF position Set the Battery Master Switch to the
97. fy that the A C control wheel turns to the left Engage the A P HDG mode to stop the A C control wheel Adjust the OBS for a 100 rightward deflection of the Left Right needle from center Engage the A P NAV mode Verify that the A C control wheel turns to the right Engage the A P REV mode Verify that the A C control wheel turns to the left Engage the A P HDG mode to stop the A C control wheel Adjust the OBS for a 100 leftward deflection of the Left Right needle from center Engage the A P REV mode Verify that the A C control wheel turns to the right Engage the A P HDG mode to stop the A C control wheel Ist Ed 11 2001 MEGGITT AVIONICS S TEC FLIGHT LINE SERVICE MANUAL FOR RATE BASED AUTOPILOTS 32 Adjustthe OBS for a centered Left Right needle Altitude Channel Test 33 Move the A C control wheel until the elevator is in the neutral position 34 Engage the A P ALT mode 35 Command a pitch up using the A P ALT VS modifier knob 36 Verify that the A C control wheel moves in the aft direction 37 Engage the A P VS mode to stop the A C control wheel 38 Engage the A P ALT mode 39 Command a pitch down using the A P ALT VS modifier knob 40 Verify that the A C control wheel moves in the fore direction 41 Engage the A P VS mode to stop the A C control wheel Vertical Speed Channel Test 42 Command a pitch up using the A P ALT VS modifier knob 43 Verify that the A C control wheel moves in the
98. fy that the A C trim wheel resumes running nose down at full speed Release the A P Manual Electric Trim Switch Verify that the A C trim wheel stops and the TRIM annunciation is extinguished END OF TEST A P Disconnect Test TI 78 Press the A P Disconnect Trim Interrupt Switch Verify that RDY flashes on the A P and an audible alert sounds for 5 seconds after which RDY alone remains annunciated and the audible alert ceases END OF TEST 3 9 Functional Ground Test for System 60 1 Power Up Test l 2 Set the Battery Master Switch to the ON position Set the Avionics Master Switch to the ON position Set the A P Master Switch to the TEST position Verify that the following are all annunciated on the A P RDY REV HDG APR CAP FAIL SOFT Set the A P Master Switch to the ON position Verify that all of the annunciations are extinguished Verify that within 3 minutes RDY alone becomes annunciated on the A P Verify that the Low Voltage Flag on the Turn Coordinator is out of view Ist Ed May 11 2001 3 25 MEGGITT AVIONICS S TEC FLIGHT LINE SERVICE MANUAL FOR RATE BASED AUTOPILOTS Heading Channel Test 9 Center the HDG bug under the lubber line 10 Engage the A P HDG mode 11 Turn the HDG bug to the left 12 Verify that the A C control wheel turns to the left 13 Center the HDG bug under the lubber line 14 Verify that the A C control wheel stops 15 Turn the HDG bug to the right
99. he A C trim wheel begins to run nose up with increasing speed and TRIM becomes annunciated on the A P b After 7 seconds TRIM flashes Apply aft pressure to the A C control wheel until the A C trim wheel stops Press either fore or aft on both segments of the A P Manual Electric Trim Switch and then release Verify that the A P disconnects as follows RDY flashes on the A P and the audible alert sounds for 5 seconds after which RDY alone remains annunciated Press aft and maintain pressure on both segments of the A P Manual Electric Trim Switch Verify that the A C trim wheel runs nose up at full speed and TRIM flashes Press and hold the A P Disconnect Trim Interrupt Switch Verify that the A C trim wheel stops Release the A P Disconnect Trim Interrupt Switch Verify that the A C trim wheel resumes running nose up at full speed Release the A P Manual Electric Trim Switch Verify that the A C trim wheel stops and the TRIM annunciation is extinguished Ist Ed May 11 2001 69 70 71 72 73 74 75 76 MEGGITT AVIONICS S TEC FLIGHT LINE SERVICE MANUAL FOR RATE BASED AUTOPILOTS Press fore and maintain pressure on both segments on the A P Manual Electric Trim Switch Verify that the A C trim wheel runs nose down at full speed and TRIM flashes Press and hold the A P Disconnect Trim Interrupt Switch Verify that the A C trim wheel stops Release the A P Disconnect Trim Interrupt Switch Veri
100. im Servo Plug the proper end of Extender Cable P N 39309 into the A P cable harness in place of the actual Trim Servo Plug the other end of the Extender Cable into the Servo Simulator connector Set the Battery Master Switch to the ON position Set the Avionics Master Switch to the ON position Set the A P Master Switch to the ON position Wait until RDY alone becomes annunciated on the A P display upon completion of the power up self test Verify that the voltage at the Servo Simulator MOTOR 1 jack relative to the MOTOR 2 jack is approx imately 0 VDC Press AFT and hold the Manual Electric Trim Switch to command TRIM UP Verify that the voltage at the Servo Simulator SOL jack relative to the SOL GND jack is approximately 12 VDC A 14VDC 24 VDC A 28 VDC Verify that the voltage at the Servo Simulator MOTOR 1 jack relative to the MOTOR 2 jack is approx imately 12 VDC A 14VDC 24 VDC A 28 VDC Release the Manual Electric Trim Switch Press FORE and hold the Manual Electric Trim Switch to command TRIM DN Verify that the voltage at the Servo Simulator MOTOR 1 jack relative to the MOTOR 2 jack is approx imately 12 VDC A 14VDC 24 VDC A 28 VDC Operating Procedure for Altitude Transducer Simulator P N 95101 4 Heading System Installed 1 2 Set the A P Master Switch to the OFF position Set the Avionics Master Switch to the OFF position Ist Ed 11 2001 10 11
101. into the Servo Simulator connector Center the HDG bug under the lubber line Set the Battery Master Switch to the ON position Set the Avionics Master Switch to the ON position Set the A P Master Switch to the ON position Wait until RDY alone becomes annunciated on the A P display upon completion of the power up self test Engage the A P HDG mode Verify that the voltage at the Servo Simulator SOL jack relative to the SOL GND jack is approximately 12 VDC 14VDC 24 VDC A 28 VDC Verify that the voltage at the Servo Simulator MOTOR 1 jack relative to the MOTOR 2 jack is approx imately 0 VDC Turn the HDG bug to the right Ist Ed May 11 2001 16 17 8 19 MEGGITT AVIONICS S TEC FLIGHT LINE SERVICE MANUAL FOR RATE BASED AUTOPILOTS Verifv that the voltage at the Servo Simulator MOTOR 1 jack relative to the MOTOR 2 jack is positive Center the HDG bug under the lubber line Turn the HDG bug to the left Verifv that the voltage at the Servo Simulator MOTOR 1 jack relative to the MOTOR 2 jack is negative 4 2 1 2 No Heading System Installed and A P with STB Mode 1 2 10 11 12 13 14 15 16 17 18 19 Ist Ed May Set the A P Master Switch to the OFF position Set the Avionics Master Switch to the OFF position Set the Battery Master Switch to the OFF position Disconnect the A P cable harness from the Roll Servo Plug the proper end of Extender Cabl
102. lerates aft to the null 33 Releasethe A P DN Switch 34 Engage the A P ALT mode to stop the A C control wheel Trim Channel Test Note If the A P is equipped with autotrim proceed to step 39 35 Apply maximum aft pressure to the A C control wheel 36 Verify that a After 3 seconds the A P DN Switch illuminates TRIM annunciates and the audible alert sounds a steady tone b After 7 seconds the A P DN Switch flashes TRIM flashes and the audible alert becomes periodic 37 Apply maximum fore pressure to the A C control wheel 38 Verify that a After 3 seconds the A P UP Switch illuminates TRIM annunciates and the audible alert sounds a steady tone b After 7 seconds the A P UP Switch flashes TRIM flashes and the audible alert becomes periodic Note Proceed to Step 63 30 Setthe A P Trim Master Switch to the ON position 40 Apply maximum aft pressure to the A C control wheel 41 Verify that after 3 seconds the A C trim wheel begins to run nose down with increasing speed 42 Apply maximum fore pressure to the A C control wheel 43 Verify that after 3 seconds the A C trim wheel begins to run nose up with increasing speed 44 Apply aft pressure to the A C control wheel until the A C trim wheel stops 45 Press either fore or aft on both segments of the A P Manual Electric Trim Switch and then release 46 Verify that the A P disconnects as follows annunciations are extinguished 47 Press aft and maintain press
103. n pressure on both segments of the A P Manual Electric Trim Switch Verify that the A C trim wheel runs nose up at full speed and TRIM flashes Press and hold the A P Disconnect Trim Interrupt Switch Verify that the A C trim wheel stops Ist Ed May 11 2001 MEGGITT AVIONICS S TEC FLIGHT LINE SERVICE MANUAL FOR RATE BASED AUTOPILOTS 65 Release the A P Disconnect Trim Interrupt Switch 66 Verify that the A C trim wheel resumes running nose up at full speed 67 Release A P Manual Electric Trim Switch 68 Verify that the A C trim wheel stops and the TRIM annunciation is extinguished 69 Press fore and maintain pressure on both segments of the A P Manual Electric Trim Switch 70 Verify that the A C trim wheel runs nose down at full speed and TRIM flashes 71 Press and hold the A P Disconnect Trim Interrupt Switch 72 Verify that the A C trim wheel stops 73 Release the A P Disconnect Trim Interrupt Switch 74 Verify that the A C trim wheel resumes running nose down at full speed 75 Release the A P Manual Electric Trim Switch 76 Verify that the A C trim wheel stops and TRIM annunciation is extinguished END OF TEST A P Disconnect Test T Press the A P Disconnect Trim Interrupt Switch 78 Verify that RDY flashes on the A P and an audible alert sounds for 5 seconds after which RDY alone remains annunciated and the audible alert ceases END OF TEST 3 8 Functional Ground Test for System 550 Power Up Test
104. n the aft direction Engage the A P VS mode to stop the A C control wheel Engage the A P ALT mode Command a pitch down using the A P ALT VS modifier knob Verify that the A C control wheel moves in the fore direction Engage the A P VS mode to stop the A C control wheel Vertical Speed Channel Test 42 43 44 45 46 4T Command a pitch up using the A P ALT VS modifier knob Verify that the A C control wheel moves in the aft direction Engage the A P ALT mode to stop the A C control wheel Engage the A P VS mode Command a pitch down using the A P ALT VS modifier knob Verify that the A C control wheel moves in the fore direction Ist Ed May 11 2001 3 15 MEGGITT AVIONICS S TEC FLIGHT LINE SERVICE MANUAL FOR RATE BASED AUTOPILOTS 48 Engage the A P ALT mode to stop the A C control wheel Trim Channel Test Note If the A P is equipped with autotrim proceed to step 53 49 50 51 52 Apply maximum aft pressure to the A C control wheel Verify that a After 3 seconds TRIM becomes annunciated on A P and audible alert sounds b After 7 seconds TRIM flashes and the audible alert ceases Apply maximum fore pressure to the A C control wheel Verify that a After 3 seconds TRIM becomes annunciated on the A P and the audible alert sounds b After 7 seconds TRIM 4 flashes and the audible alert ceases Note Proceed to step 77 53 54 29 56
105. nects as follows a RDY flashes on the A P Remote Annunciator for 5 seconds and then it alone remains annunciated b ON alone remains annunciated on the A P Control Head END OF TEST 3 12 Functional Ground Test for System 60 PSS Manual Excessive G Force Test 1 Set the Battery Master Switch to the ON position 2 Set the Avionics Master Switch to the ON position 3 Set the A P Master Switch to the TEST position 4 Verify that the following are all annunciated on the A P VS AIT 65 TRIM 5 Verify that the UP and DN Switches on the A P are both illuminated 6 Apply fore and aft pressure to the A C control wheel to sense its freedom of movement 7 Engage the A P ALT mode 8 Apply fore and aft pressure to the A C control wheel to verify its reduced freedom of movement Ist Ed May 11 2001 3 35 MEGGITT AVIONICS S TEC FLIGHT LINE SERVICE MANUAL FOR RATE BASED AUTOPILOTS 9 Press and hold the A P UP Switch while maintaining a grasp on the A C control wheel 10 Verify that the pitch servo disengages after 1 2 second by sensing the increased freedom of A C control wheel movement in the fore and aft directions 11 Release the A P UP Switch 12 Verify that the pitch servo immediately re engages by sensing the reduced freedom of A C control wheel movement in the fore and aft directions 13 Press and hold the A P DN Switch while maintaining a grasp on the A C control wheel 14 Verify that the pitch servo disengages after 1 2
106. ntered Left Right needle allow time between adjustments for the A P system to stabilize Ist Ed May 11 2001 2 3 MEGGITT AVIONICS S TEC FLIGHT LINE SERVICE MANUAL FOR RATE BASED AUTOPILOTS 2 2 2 A P is a Radio Tracker 2 4 Fly the aircraft to smooth air and trim for level flight Set the A P Master Switch to the ON position Wait until RDY alone becomes annunciated on the A P display upon completion of the power up self test Tune the Navigation Receiver to a VOR frequency Select the course using the OBS Fly the A C onto the selected course such that the Left Right needle is centered Engage the A P NAV mode LO TRK mode for System 20 30 Insert the Roll Centering Adjustment Tool P N 95101 1 into the A P bezel hole as shown in Fig 1 1 until it makes contact with the Roll Centering Potentiometer Adjust the Roll Centering Potentiometer in small increments to obtain a centered Left Right needle allow time between adjustments for the A P system to stabilize Ist Ed May 11 2001 MEGGITT AVIONICS S TEC FLIGHT LINE SERVICE MANUAL FOR RATE BASED AUTOPILOTS STEP 1 REMOVE SCREW Fig 2 la System 20 30 Ist Ed May 11 2001 2 5 MEGGITT AVIONICS S TEC FLIGHT LINE SERVICE MANUAL FOR RATE BASED AUTOPILOTS STEP 1 REMOVE SCREW W Fig 2 Ib System 40 50 60 1 60 2 2 6 Ist Ed May 11 2001 MEGGITT AVIONICS S TEC FLIGHT LINE SERVICE MANUAL FOR RATE BASED AUTOPILOTS Fig
107. ons Section 8 Glossary Section 9 12 Purpose This manual provides flight line service information for the following S TEC MEGGITT rate based autopilots System 20 30 30 ALT System 40 50 System 55 55X 550 System 60 1 60 2 System 65 System 60 PSS 13 Required Test Equipment Nomenclature P N Flight Line Autopilot Tester 95101 Breakout Box 9524 Adapter Cable 39198 Adapter Cable 39199 Extender Assembly 01264 1 4 Service Philosophy The first objective is to determine if the installed autopilot system is functioning properly on the ground This is accomplished by performing the functional ground test for that particular system No external test equipment is required The second objective is to isolate a failure to a system component The equipment listed in section 1 3 is designed to aid in this effort The Flight Line Autopilot Tester P N 95101 is used to simulate some of the major system components It is shown in Fig 1 1 and contains the following each removable from a suitcase for remote use about the aircraft Nomenclature P N Tool Roll Centering Adjustment 95101 1 Simulator Heading System 95101 2 Simulator Servo Roll Pitch Trim 95101 3 Simulator Altitude Transducer 95101 4 Simulator Turn Coordinator 95101 5 Cable Assembly Extension for 95101 2 6406 52D54 39307 Cable Assembly Extension for 95101 2 6443 39308 Cable Assembly Extension for 95101 3 39309 Cable Assembly Extension for 95101 4 39310 Cable Assembly
108. r Up Test 12 Verify that within 3 minutes RDY becomes annunciated on the A P Remote Annunciator 13 Verify that the Low Voltage Flag on the Turn Coordinator is out of view 14 Press the FD AP Switch on the A P Control Head to turn ON the A P Heading Channel Test 15 Center the HDG bug under the lubber line 16 Engage the A P HDG mode 17 Turn the HDG bug to the left 18 Verify that the A C control wheel turns to the left 19 Center the bug under the lubber line 20 Verify that the A C control wheel stops 2 Turn the HDG bug to the right 22 Verify that the A C control wheel turns to the right 23 Center the HDG bug under the lubber line 24 Verify that the A C control wheel stops Navigation Channel Test Note If the heading system is an HSI this test cannot be performed In that case proceed to step 41 25 Tune the Navigation Receiver to the local VOR frequency 26 Adjust the OBS for a 100 leftward deflection of the Left Right needle from center 27 Engage the A P NAV mode 28 Verify that the A C control wheel turns to the left 29 Engage the A P HDG mode to stop the A C control wheel 30 Adjust the OBS for a 100 rightward deflection of the Left Right needle from center 31 Engage the A P NAV mode 32 Verify that the A C control wheel turns to the right Ist Ed 11 2001 MEGGITT AVIONICS S TEC FLIGHT LINE SERVICE MANUAL FOR RATE BASED AUTOPILOTS 33 Engage the A P REV mode
109. s Turn the A P TURN CMD knob to the right Verify that the A C control wheel turns to the right Center the A P TURN CMD knob under its index Verify that the A C control wheel stops Heading Channel Test 20 21 22 23 24 25 26 27 28 29 Center the HDG bug under the lubber line Engage the A P HDG mode Turn the HDG bug to the left Verify that the A C control wheel turns to the left Center the HDG bug under the lubber line Verify that the A C control wheel stops Turn the HDG bug to the right Verify that the A C control wheel turns to the right Center the HDG bug under the lubber line Verify that the A C control wheel stops Navigation Channel Test with Heading System DG or HSI Installed 30 31 32 33 34 35 36 Tune the Navigation Receiver to the local VOR frequency Adjust the OBS DG or Course Pointer HSI for a 100 leftward deflection of the Left Right needle from center Engage the A P NAV mode Verify that the A C control wheel turns to the left Adjust the OBS DG or Course Pointer HSI for a 100 rightward deflection of the Left Right needle from center Verify that the A C control wheel turns to the right Engage the A P REV mode Ist Ed May 11 2001 3 9 MEGGITT AVIONICS S TEC FLIGHT LINE SERVICE MANUAL FOR RATE BASED AUTOPILOTS 37 Verify that the A C control wheel turns to the left 38 Adjust the OBS DG or Course
110. t Ed May 11 2001 NOTES 1 SANDEL INDICATOR MUST BE CONFIGURED FOR KING 5 55 55 HEADING SYSTEM COLLINS HS 331A 6P 6R HDG ERROR 2 AZIMUTH XMTR Z HDG ERROR C T Y AZIMUTH XMTR Y HDG ERROR C T X AZIMUTH XMTR X ERROR C AZIMUTH XMTR C HDG ERROR C T H AZIMUTH XMTR H PROG COMP SIGNAL REF HDG SIGNAL EXCITATION S TEC HSI 6443 INDICATOR PROG COMP 6443 INDICATOR CN 1 EXCITATION HDG SIGNAL SIGNAL REF BOOTSTRAP 1 ROTOR H HDG C T ROTOR H BOOTSTRAP 1 ROTOR C HDG C T ROTOR C BOOTSTRAP 1 STATOR X HDG C T STATOR Y BOOTSTRAP 1 STATOR Y HDG C T STATOR X BOOTSTRAP 1 STATOR Z HDG C T STATOR Z Ist Ed May 11 2001 RC ALLEN DG 1035 0010 01 MODEL 110 3 PROG COMP RCA110 3 HDG SIG EXC REF SIG REF SANDEL SN 5508 PROG COMP P2 1211 69 DC HDG DATUM DC HDG LO EG SIGNAL GND P1 poly BULLETIN 300 NEXT ASSY USED ON APPLICATIONS MEGGITT AVIONICS S TEC FLIGHT LINE SERVICE MANUAL FOR RATE BASED AUTOPILOTS REVISIONS DESCRIPTION DATE RELEASED PER EO 2955 REV PER EO 3161 REV PER EO 4126 REDRAWN PER EO 4266 REV PER EO 5958 REV PER 6555 REV PER EO 7585 APPROVED T LIN NIN 1 N T 4 12 93 6 20 96 10 9 9 1 9 lt LIST OF MATERIALS APPROVAL DATE DRAWN T PIERSON 8 21 91 ENGINEER TITLE SCHEMATIC HEADING SYSTEM INTERCONNECT DETAIL SYS 40 50 DRAWING NO 1 01 4
111. t the A P Master Switch to the OFF position 2 Setthe Avionics Master Switch to the OFF position 3 Setthe Battery Master Switch to the OFF position 4 Disconnect the A P cable harness from the Heading System Note For the 6443 HSI only the topmost DB 25 connector needs to be disconnected 5 Identify which one of the following Extender Cables is to be used P N 39307 for use with 6406 52D54 P N 39308 for use with 6443 6 Plug the proper end of the Extender Cable into the A P cable harness in place of the actual Heading System 7 Plug the other end of the Extender Cable into the proper Heading System Simulator connector 6406 6443 or 52D54 8 Connect the black lead Pin Plug from the Heading System Simulator to Airframe Ground Note This Pin Plug may be inserted into an Airframe Ground Pin Jack on S TEC Breakout Box P N 9524 if used Otherwise rely on the Pin Jack Alligator Clip supplied 9 Set the Heading Error Selector Switch on the Heading System Simulator to 0 10 Turn the A C control wheel until the ailerons are in the neutral position 11 Center the HDG bug under the lubber line 12 Set the Battery Master Switch to the ON position 13 Set the Avionics Master Switch to the ON position 14 Set the A P Master Switch to the ON position 15 Wait until RDY alone becomes annunciated on the A P display upon completion of the power up self test 16 Engage the A P HDG mode 17 Adjust the A P roll centering as required to null an
112. tch Verify that the A C trim wheel stops and the TRIM annunciation is extinguished END OF TEST A P Disconnect Test 92 93 Press the A P Disconnect Trim Interrupt Switch Verify that the A P disconnects as follows RDY flashes on the A P for 5 seconds and then it alone remains annunciated END OF TEST 3 11 Functional Ground Test for System 65 Manual Excessive G Force Test Set the Battery Master Switch to the ON position Set the Avionics Master Switch to the ON position Apply fore and aft pressure to the A C control wheel to sense its freedom of movement Press and hold the A P UP Switch while maintaining a grasp on A C control wheel Verify that the pitch servo engages by sensing the reduced freedom of A C control wheel movement in the fore and aft directions Release the A P UP Switch Verify that the pitch servo disengages by sensing the increased freedom of A C control wheel movement in the fore and aft directions Press and hold the A P DN Switch while maintaining a grasp on A C control wheel Verify that the pitch servo engages by sensing the reduced freedom of A C control wheel movement in the fore and aft directions Ist Ed May 11 2001 3 31 MEGGITT AVIONICS S TEC FLIGHT LINE SERVICE MANUAL FOR RATE BASED AUTOPILOTS 10 Release the A P DN Switch 11 Verify that the pitch servo disengages by sensing the increased freedom of A C control wheel movement in the fore and aft directions Powe
113. tch to the ON position Set the Avionics Master Switch to the ON position Set the A P Master Switch to the ON position Wait until the A P has completed its power up self test Engage the A P ALT mode Move the A C control wheel until the elevator is in the neutral position Set the Pitch Command Selector Switch on the Altitude Transducer Simulator to the PITCH DN position Verify that the A C control wheel moves in the FORE direction Set the Pitch Command Selector Switch on the Altitude Transducer to the ENG A P ALT MODE position Verify that the A C control wheel stops Set the Pitch Command Selector Switch on the Altitude Transducer Simulator to the PITCH UP position Verify that the A C control wheel moves in the AFT direction Set the Pitch Command Selector Switch on the Altitude Transducer Simulator to the ENG A P ALT MODE position Verify that the A C control wheel stops 4 4 Operating Procedure for Turn Coordinator Simulator P N 95101 5 441 Heading System Installed 1 2 Set the A P Master Switch to OFF position Set the Avionics Master Switch to the OFF position Set the Battery Master Switch to the OFF position Disconnect the A P cable harness from the Turn Coordinator Connect the proper end of Extender Cable P N 39311 into the A P cable harness in place of the actual Turn Coordinator Connect the other end of the Extender Cable into the Turn Coordinator Simulator connector Set the Gyro Tach Selec
114. ter Switch to the OFF position Disconnect the A P cable harness from the Altitude Transducer Plug the proper end of Extender Cable P N 39310 into the A P cable harness in place of the actual Altitude Transducer Plug the other end of the Extender Cable into the Altitude Transducer Simulator connector Set the Pitch Command Selector Switch on the Altitude Transducer Simulator to the ENG A P ALT MODE position Disconnect the A P cable harness from the Pitch Servo Plug the proper end of Extender Cable P N 39309 into the A P cable harness in place of the actual Pitch Servo Plug the other end of the Extender Cable into the Servo Simulator connector Set the Trim Command Selector Switch on the Servo Simulator to the NEUTRAL position Set the Battery Master Switch to the ON position Set the Avionics Master Switch to the ON position Set the A P Master Switch to the ON position Wait until RDY alone becomes annunciated on the A P display upon completion of the power up self test Engage the A P HDG mode Center the HDG bug under the lubber line to null lateral movement of the A C control wheel Engage the A P ALT mode Verify that the voltage at the Servo Simulator SOL jack relative to the SOL GND jack is approximately 12 VDC A 14VDC 24 VDC A 28 VDC Verify that the voltage at the Servo Simulator MOTOR 1 jack relative to the MOTOR 2 jack is approxi mately 0 VDC Set the Pitch Command Selector Switch on the Altitude
115. the increased freedom of A C control wheel movement in the fore and aft directions 17 Release the A P DN Switch 18 Verify that the pitch servo immediately re engages by sensing the reduced freedom of A C control wheel movement in the fore and aft directions Power Up Test 19 Setthe A P Master Switch to the ON position 20 Verify that all of the annunciations and illuminations are extinguished 21 Verify that within 3 minutes RDY alone becomes annunciated on the A P 22 Verify that the Low Voltage Flag on the Turn Coordinator is out of view Heading Channel Test 23 Engage the A P HDG mode 24 Turn the HDG bug to the left 25 Verify that the A C control wheel turns to the left 26 Center the HDG bug under the lubber line 27 Verify that the A C control wheel stops 28 Turn the HDG bug to the right 29 Verify that the A C control wheel turns to the right 30 Center the HDG bug under the lubber line 31 Verify that the A C control wheel stops Navigation Channel Test Note If the heading system is an HSI this test cannot be performed In that case proceed to step 48 32 Tune the Navigation Receiver to the local VOR frequency 33 Adjust the OBS for a 100 leftward deflection of the Left Right needle from center 34 Engage the A P NAV mode 35 Verify that the A C control wheel turns to the left 36 Engage the A P HDG mode to stop the A C control wheel 37 Adjust the OBS for a 100 rightward defle
116. tor Switch on the Turn Coordinator Simulator to the NOT RDY position Set the Std Rate Turn Selector Switch on the Turn Coordinator Simulator to the 0 position Turn the A C control wheel until the ailerons are in the neutral position Ist Ed May 11 2001 4 13 MEGGITT AVIONICS S TEC FLIGHT LINE SERVICE MANUAL FOR RATE BASED AUTOPILOTS 4 14 10 11 12 13 14 15 16 17 18 19 20 21 22 23 24 25 26 27 28 29 30 Center the bug under the lubber line Set the Battery Master Switch to the ON position Set the Avionics Master Switch to the ON position Set the A P Master Switch to the ON position Wait 30 seconds for the A P to complete its power up self test Set the Gyro Tach Selector Switch on the Turn Coordinator Simulator to the RDY position Verify that RDY becomes annunciated on the A P display Set the Gyro Tach Selector Switch on the Turn Coordinator Simulator to the NOT RDY position Verify that RDY becomes extinguished on the A P display Set the Gyro Tach Selector Switch on the Turn Coordinator Simulator to the RDY position Engage the A P HDG mode Adjust the HDG bug slightly as required to null any A C control wheel creep Turn the A C control wheel until the ailerons are in the neutral position Set the Std Rate Turn Selector Switch on the Turn Coordinator Simulator to the 50 RT position Verify that the A C control wheel turns to the le
117. un nose up with increasing speed 73 Apply aft pressure to the A C control wheel until the A C trim wheel stops 74 Press either fore or aft on both segments of the A P Manual Electric Trim Switch and then release 75 Verify that the A P disconnects as follows RDY flashes on the A P for 5 seconds and then it alone remains annunciated 76 Press aft and maintain pressure on both segments of the A P Manual Electric Trim Switch 77 Verify that the A C trim wheel runs nose up at full speed and TRIM flashes 78 Press and hold the A P Disconnect Trim Interrupt Switch 79 Verify that the A C trim wheel stops 80 Release the A P Disconnect Trim Interrupt Switch 81 Verify that the A C trim wheel resumes running nose up at full speed Ist Ed May 11 2001 82 83 84 85 86 87 88 89 90 91 MEGGITT AVIONICS S TEC FLIGHT LINE SERVICE MANUAL FOR RATE BASED AUTOPILOTS Release the A P Manual Electric Trim Switch Verify that the A C trim wheel stops and the TRIM annunciation is extinguished Press fore and maintain pressure on both segments of the A P Manual Electric Trim Switch Verify that the A C trim wheel runs nose down at full speed and TRIM flashes Press and hold the A P Disconnect Trim Interrupt Switch Verify that the A C trim wheel stops Release the A P Disconnect Trim Interrupt Switch Verify that the A C trim wheel resumes running nose down at full speed Release the A P Manual Electric Trim Swi
118. ure on both segments of the A P Manual Electric Trim Switch 48 Verify that the A C trim wheel runs nose up at full speed Ist Ed May 11 2001 3 37 MEGGITT AVIONICS S TEC FLIGHT LINE SERVICE MANUAL FOR RATE BASED AUTOPILOTS 49 50 5l 52 53 54 92 56 57 58 59 60 61 62 Press and hold the Pitch Disconnect Trim Interrupt Switch Verify that the A C trim wheel stops Release the Pitch Disconnect Trim Interrupt Switch Verify that the A C trim wheel resumes running nose up at full speed Release the A P Manual Electric Trim Switch Verify that the A C trim wheel stops Press fore and maintain pressure on both segments of the A P Manual Electric Trim Switch Verify that the A C trim wheel runs nose down at full speed Press and hold the Pitch Disconnect Trim Interrupt Switch Verify that the A C trim wheel stops Release the Pitch Disconnect Trim Interrupt Switch Verify that the A C trim wheel resumes running nose down at full speed Release the A P Manual Electric Trim Switch Verify that the A C trim wheel stops END OF TEST A P Disconnect Test 63 64 Press the A P OFF Switch Verify that all annunciations are extinguished END OF TEST Ist Ed 11 2001 MEGGITT AVIONICS S TEC FLIGHT LINE SERVICE MANUAL FOR RATE BASED AUTOPILOTS SECTION 4 SIMULATOR OPERATION Ist Ed May 11 2001 4 1 MEGGITT AVIONICS S TEC FLIGHT LINE SERVICE MANUAL FOR RATE B
119. ward deflection of the Left Right needle from center Engage the A P REV mode Verify that the A C control wheel turns to the right Engage the A P HDG mode to stop the A C control wheel Adjust the OBS for a centered Left Right needle Altitude Channel Test 33 34 35 36 37 38 39 40 41 Move control wheel until elevator is in neutral position Engage the A P ALT mode Command a pitch up using the A P ALT VS modifier knob Verify that the A C control wheel moves in the aft direction Engage the A P VS mode to stop the A C control wheel Engage the A P ALT mode Command a pitch down using the A P ALT VS modifier knob Verify that the A C control wheel moves in the fore direction Engage the A P VS mode to stop the A C control wheel Vertical Speed Channel Test 42 43 44 45 46 4T 48 Command a pitch up using the A P ALT VS modifier knob Verify that the A C control wheel moves in the aft direction Engage the A P ALT mode to stop the A C control wheel Engage the A P VS mode Command a pitch down using the A P ALT VS modifier knob Verify that the A C control wheel moves in the fore direction Engage the A P ALT mode to stop the A C control wheel Trim Channel Test Note If the A P is equipped with autotrim proceed to step 53 49 Apply maximum aft pressure to the A C control wheel Ist Ed May 11 2001 3 19 MEGGITT AVIONICS S T
120. ximately 12 VDC A 14VDC 24 VDC A 28 VDC Verify that the voltage at the Servo Simulator MOTOR 1 jack relative to the MOTOR 2 jack is approxi mately 0 VDC Set the Pitch Command Selector Switch on the Altitude Transducer Simulator to the PITCH UP position Verify that the voltage at the Servo Simulator MOTOR 1 jack relative to the MOTOR 2 jack is positive Set the Pitch Command Selector Switch on the Altitude Transducer Simulator to the PITCH DN position Verify that the voltage at the Servo Simulator MOTOR 1 jack relative to the MOTOR 2 jack is negative Set the Pitch Command Selector Switch on the Altitude Transducer Simulator to the ENG A P ALT MODE position Set the Trim Command Selector Switch on the Servo Simulator to the TRIM UP position Verify that after a 3 second delay the A P annunciates TRIM UP Set the Trim Command Selector Switch on the Servo Simulator to the NEUTRAL position Verify that the TRIM UP annunciation is extinguished Set the Trim Command Selector Switch on the Servo Simulator to the TRIM DN position Verify that after a 3 second delay the A P annunciates TRIM DN Set the Trim Command Selector Switch on the Servo Simulator to the NEUTRAL position 33 Verify that the TRIM DN annunciation is extinguished Pitch Only A P 1 Set the A P Master Switch to the OFF position 2 Setthe Avionics Master Switch to the OFF position 3 Setthe Battery Master Switch to the OFF position 4 Disconnect the A P cabl
121. y lateral A C control wheel movement 18 Turn the A C control wheel until the ailerons are in the neutral position 19 Set the Heading Error Selector Switch on the Heading System Simulator to the 10 RT TO HDG position Ist Ed May 11 2001 4 3 MEGGITT AVIONICS S TEC FLIGHT LINE SERVICE MANUAL FOR RATE BASED AUTOPILOTS 4 2 4 2 1 4 2 1 1 4 4 20 21 22 23 24 25 26 Verify that the A C control wheel turns to the right Set the Heading Error Selector Switch on the Heading System Simulator back to 0 position Verify that the A C control wheel stops Set the Heading Error Selector Switch on the Heading System Simulator to the 10 LT TO HDG position Verify that the A C control wheel turns to the left Set the Heading Error Selector Switch on the Heading System Simulator back to the 0 position Verify that the A C control wheel stops Note 45 may be selected instead of 10 in steps 19 and 23 Operating Procedure for Servo Simulator P N 95101 3 Roll Servo Heading System Installed 1 2 10 11 12 13 14 15 Set the A P Master Switch to the OFF position Set the Avionics Master Switch to the OFF position Set the Battery Master Switch to the OFF position Disconnect the A P cable harness from the Roll Servo Plug the proper end of Extender Cable P N 39309 into the A P cable harness in place of the actual Roll Servo Plug the other end of the Extender Cable

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