Feb 20/93 22-11-291 Page 501
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(i) POWER switch to ON.
NOTE: Power Lights (on A lights and some B lights) should be ON. B NSS excitation Light should be OFF.
D. Adjust Sensor (A SYSTEM)
(1)
Position hydraulic system A and B switches to ON and close FLT CONT SYS circuit breaker.
WARNING: MAKE SURE ALL PERSONNEL AND OBSTRUCTIONS ARE CLEAR OF AILERON, ELEVATOR AND TAB SURFACES. SURFACES MAY MOVE ABRUPTLY WHEN HYDRAULIC POWER IS APPLIED.
(2)
Operate position control knob on test set until meter is at lowest reading. Check that voltage between Jl0A and J11A is less than 0.08 volt and lock position control in place.
(3)
Disconnect VTVM and connect to NSS FEEDBACK J7A and J8A on test set.
(4)
Loosen screw on sensor clamp only enough to allow sensor to be rotated.
(5)
Rotate sensor housing slowly in both directions until a reading of less than 60 millivolts is obtained and tighten clamp screws 8-12 lb.-in.
(6)
Remove lockwiring and turn thumb nut on microadjustment rod until the smallest possible reading less than 30 millivolts is obtained. Lockwire thumbnut.
(7)
Disconnect VTVM, test set and test cables.
(8)
Connect airplane wiring to A/P actuators and aileron position sensor.
(9)
Test sensor.
(10)
Repeat for B system test jacks and adjust B SYSTEM sensors.
2. A/P Aileron Actuator/Position Sensor Test
A. Prepare to Test
(1)
Provide electrical power and hydraulic power.
(2)
Check that hydraulic system A and B switches on P5 panel are positioned to ON and that FLT CONT SYS circuit breaker on P6 panel is closed.
WARNING: MAKE SURE ALL PERSONNEL AND OBSTRUCTIONS ARE CLEAR OF AILERON, ELEVATOR AND TAB SURFACES. SURFACES MAY MOVE ABRUPTLY WHEN HYDRAULIC POWER IS APPLIED.
(3)
Check that all autopilot, attitude, compass and air data systems circuit breakers on P6 and P18 load control centers are closed.
B. Test Actuator/Sensor
(1)
Place autopilot A (or B as applicable) engage switches to CWS. Observe that CWS ROLL and CWS PITCH is annunciated.
(2)
Rotate control wheel left and check that left aileron goes up.
(3)
Rotate control wheel to right and check that right aileron goes up.
(4)
Return control wheel to center detent and check that ailerons are centered.
(5)
Disengage autopilot.
(6)
Remove electrical and hydraulic power if no longer required.
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Oct 20/87
ELEVATOR POSITION SENSOR - REMOVAL/INSTALLATION
EFFECTIVITY
SA ZS-SIA and on GJ B-2509 and B-2510
1. General (Fig. 401)
A. The elevator position sensor is connected to the elevator torque tube and mounted on the aft bulkhead station 1156 (Ref Chapter 27, Elevator and Tab Control System). The elevator position sensor is connected to the lower (input) torque tube (adjacent to lower RH control cable quadrant).
2. Remove Sensor
A. Remove tail cone access panel 3802 (Ref Chapter 12, Access Doors and Panels).
B. Open autopilot AC circuit breakers on P6 and P18 load control centers.
C. Disconnect sensor electrical connectors.
D. Loosen screw in sensor crank and remove crank from sensor shaft.
E. Loosen screw in sensor clamp and remove sensor.
3. Install Sensor
A. Set horizontal stabilizer at 0 degrees, (3 units trim) equal to B dimension of 41.57 +0.05 inches (Ref Chapter 27, Horizontal Stabilizer Trim Control System).
B. Ensure mach trim actuator is extended (Ref Chapter 27, Elevator and Tab Control Systems).
C. On airplanes with stick nudger installed, ensure stick nudger actuator is fully extended (Ref Chapter 27, Elevator and Tab Control Systems).
D. Align index marks on sensor housing and sensor shaft.
E. Install sensor in clamp and crank with index mark aligned with slot in crank.
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