C. Test Autopilot Stabilizer Trim Servo (SP-177)
(1)
Engage autopilot A in CWS and pull control column aft approximately 2 inches and release.
CAUTION: TO PREVENT STABILIZER TRIM MOTOR FROM BURNING OUT, DO NOT OPERATE MORE THAN ONE MINUTE IN EVERY 10 MINUTES.
(2)
Observe that the stabilizer begins to drive. Observe stabilizer leading edge moves down and trims at a rate of 3 units in 30 to 40 seconds.
(3)
Disengage autopilot (this terminates trimming action) and return stabilizer to 5 units of trim.
(4)
Extend flaps to 5 degrees. Engage autopilot B in CWS and push the control column forward approximately 2 inches and release.
(5)
Observe that the stabilizer begins to drive. Observe stabilizer leading edge moves up and trims at a rate of 1 unit in 4 to 7 seconds.
(6)
Disengage autopilot.
D. Restore Airplane to Normal Configuration
(1)
Raise the flaps.
(2)
Remove electrical and hydraulic power if no longer required.
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PITCH CONTROL WHEEL STEERING FORCE TRANSDUCER -REMOVAL/INSTALLATION
EFFECTIVITY
SA ZS-SBL thru ZS-SBR WA N4502W-N4571M GJ ALL EXCEPT B-2509 and B-2510
1. General
A. Each control column has a pitch force transducer installed on the elevator control quadrant assembly. The two force transducers are installed opposite to each other; however, removal/installation of the transducers is similar.
2. Equipment and Materials
A. Rigging Pins E1 and E5 - 0.309 +0.003/-0.000-inch diameter, 6-inch minimum length (MS20392-4)
3. Remove Pitch Force Transducer
A. Open pitch channel circuit breakers on load control center P6.
B. Open lower nose access door 1103 (Ref Chapter 12 Access Doors and Panels).
C. Disconnect force transducer connector from airplane wiring (Fig. 401).
D. Remove force transducer cable from clamps.
E. Remove two bolts, washers, and nuts and remove force transducer from quadrant assembly.
4. Prepare to Install Pitch Force Transducer
A. Open lower nose access door 1103 (Ref Chapter 12 Access Doors and Panels).
B. Remove tail cone access panel 3802 (Ref Chapter 12 Access Doors and Panels).
C. Insert rigging pin E5 in elevator right aft quadrant.
NOTE: Rigging pins should fit freely.
D. Insert rigging pin E1 in elevator left forward quadrant.
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H19221
Pitch Force Transducer Installation 500
22-11-91Page 402 Figure 401 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. Feb 20/86
500 Pitch Transducer Rigging Pin Location
Feb 20/86 Figure 402 22-11-91
Page 403
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
5. Install Pitch Force Transducer
A. Loosen the adjustable rod end and locknuts to allow fine adjustment nut and rod end to be rotated with fingers.
B. Hold pitch force transducer in position and connect to quadrant assembly.
NOTE: Adjustable end should face forward on right quadrant. Adjustable end should face aft on left quadrant.
C. Adjust force transducer. Refer to Pitch Control Wheel Steering Force Transducer -Adjustment/Test.
D. Install lockwire through locknuts, fine adjustment nut, and washer tab on adjustable rod end.
E. Clamp force transducer cable to structure.
F. Connect force transducer to airplane wiring.
G. Remove rigging pins.
H. Close access doors.
500
22-11-91 Page 404 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. Feb 20/86
PITCH CONTROL WHEEL STEERING FORCE TRANSDUCER - ADJUSTMENT/TEST
EFFECTIVITY
SA ZS-SBL thru ZS-SBR GJ ALL EXCEPT B-2509 and B-2510
1. General
A. Each control column has a pitch force transducer installed on the elevator control quadrant assembly. The two force transducers are installed opposite to each other and are electrically 180 degrees out of phase to reduce null error voltage to the autopilot system. The following procedures are intended to verify the force transducers are adjusted and operating properly. The adjustment of the force transducers is fairly critical and if not adjusted properly, the pitch channel may not engage.
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