(9)
Measure force transducer null voltage after installation and rotate fine adjustment nut until previous null + 20 mv is obtained.
(10)
Tighten locknut on adjustable sleeve (pressing washer against end cap of transducer), tighten locknut on rod end and install lockwiring.
(11)
Remove shims.
(12)
Pressurize hydraulic systems A and B (Ref 29-11-0 and 29-12-0).
WARNING: MAKE SURE ALL PERSONNEL AND OBSTRUCTIONS ARE CLEAR OF AILERON, ELEVATOR, OUTBOARD SPOILERS AND RUDDER SYSTEMS. SURFACES AND CONTROLS MAY MOVE ABRUPTLY WHEN HYDRAULIC POWER IS APPLIED.
(13)
Cycle control wheel + 30 degrees. Gradually center control wheel.
(14)
Measure null voltage. Check that null voltage is less than 300 mv.
(15)
Turn off test box, remove adapter cable and reconnect force transducer to airplane wiring.
(16)
Close access panel.
(17)
Remove control column tag and test roll control wheel force transducer.
580
Jun 20/86 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 22-11-112 Page 503
3. Roll Force Transducer Test
A. Equipment and Materials
(1) Adapter Assembly, Control Wheel Torque Tool - F80075-1
B. Prepare to Test Roll Force Transducer
(1)
Verify control surfaces are free of obstructions and personnel.
(2)
Provide electrical and hydraulic power.
(3)
Check that hydraulic system A and B switches on P5 panel are positioned to ON and that FLT CONT SYS circuit breaker on P6 load control center 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.
(4)
Ensure ailerons are operable.
(5)
Ensure autopilot circuit breakers are closed.
(6)
Connect adapter and torque wrench to hub of captain's control wheel.
C. Test Roll Force Transducer
(1)
Place autopilot engage switch A to CWS. Observe CWS ROLL and CWS PITCH is annunciated.
NOTE: If the force transducer is not adjusted properly, the roll channel may not engage.
(2)
Slowly rotate control wheel to the right. Check that wheel begins to drive between 8.0 and
16.0 inch-pounds force. Repeat rotating wheel to left.
(3)
Place autopilot engage switch to CMD and select heading select mode.
(4)
Rotate the control wheel to the right. Check that heading select mode goes off when the scale indicates 60 to 100 inch-pounds. Disengage autopilot.
(5)
Repeat steps (1) thru (4) using autopilot engage switch B.
D. Restore Airplane to Normal Configuration
(1)
Remove torque wrench and adapter from control wheel.
(2)
Remove electrical and hydraulic power if no longer required.
580
22-11-112 Page 504 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. May 15/81
ELEVATOR NEUTRAL SHIFT SENSOR - REMOVAL/INSTALLATION
EFFECTIVITY
SA ZS-SBL thru ZS-SBR SD ST-AFK, ST-AFL WA N4502W-N4571M GJ ALL EXCEPT B-2509 and B-2510
1. General
A. The elevator neutral shift sensor, mounted on the feel and centering unit, is located immediately aft of bulkhead station 1156 (Ref Chapter 27, Elevator and Tab Control System).
2. Remove Elevator Neutral Shift Sensor
A. Remove tail cone access panel 3802 (Ref Chapter 12, Access Doors and Panels).
B. Remove electrical connector from sensor (Fig. 401).
C. Loosen screw in sensor crank and remove crank from sensor shaft.
D. Loosen two screws in sensor clamp and remove sensor.
3. Install Elevator Neutral Shift Sensor
A.
Set horizontal stabilizer at 0 degrees, equal to B dimension of 41.57 士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.
Align index marks on sensor housing and sensor shaft.
NOTE: If index marks on sensor are difficult to identify, refer to Fig. 402 or 403 for positioning sensor to electrical zero position.
D. Install sensor with index mark in vertical position pointing upward.
E. Tighten two screws in sensor clamp and tighten nuts within torque range of 8 to 12 pound-inches (Fig. 401).
CAUTION: ENSURE THAT ELEVATOR NEUTRAL SHIFT POSITION TRANSMITTER
CRANK IS CORRECTLY ORIENTED IN THE UP DIRECTION.
F. Without disturbing position of sensor, install sensor crank on sensor shaft. 中国航空网 www.aero.cn 航空翻译 www.aviation.cn 本文链接地址：737 AMM 飞机维护手册 AUTO FLIGHT 自动飞行 2(13)
