AILERON CENTERING SPRING AND TRIM MECHANISM - ADJUSTMENT/TEST
1. Equipment and Materials
A. Control Column Protractor Assembly-4MIT65B80307-1 (Preferred) or F52485-500
(Optional) which is used with the following adapters:
(1)
Control Wheel Protractor Mount-F72790
(2)
Forward Thrust Lever Protractor Adapter-F72952-2
B. Control Wheel Torque and Force Test Adapter-F72867-1
2. Aileron Centering Spring and Trim Mechanism Adjustment
A. Install protractor mount and protractor on first officer's control wheel.
B. Remove medallion from captain's control wheel and install torque wrench adapter (Fig. 501).
C. Release centering spring tension to eliminate artificial feel input forces.
D. Provide Systems A and B hydraulic power (Ref 27-11-0, MP).
E. Set aileron trim control knob in zero trim position. Using control wheel torque and force test adapter, measure force required to rotate captain's control wheel 2 degrees clockwise and counterclockwise from neutral position. If adapter is not available, forces may be measured by applying force tangentially to captain's control wheel at 6.5-inch radius. The measured force should be less than 2.0 pounds or 13 pound-inches torque.
F. Record force obtained in step E.
G. Tighten centering springs equally at eyebolts to provide artificial feel input forces.
H. Measure force required to rotate captain's control wheel 2 degrees clockwise and counterclockwise from neutral position. Measured force should increase value obtained in step E. by 1.5 to 2.0 pounds or 10 to 13 pound-inches torque. Force shall not exceed 4.5 pounds or 29.25 pound-inches torque.
542
May 01/99 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 27-11-81 Page 501
G10977
Control Wheel Torque and Force Test Adapter 500
27-11-81 Figure 501 Feb 15/73
Page 502
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
I. If forces obtained are not within limits as specified in step H., adjust centering spring eyebolts. Adjustment of both centering springs must be accomplished equally. Nuts on each eyebolt should be equally tightened or loosened in 1/2-turn increments.
NOTE: Centering spring forces are increased by tightening eyebolt and decreased by loosening eyebolts.
J. Repeat steps H. and I. until correct centering spring tension is obtained.
3. Aileron Centering Spring and Trim Mechanism Test
A. With hydraulic systems A and B pressurized, do the steps that follow:
(1)
Measure force required to rotate either control wheel 75 degrees clockwise from neutral position. Force should not exceed 120.25 pound-inches torque or 18.5 pounds.
(2)
Release control wheel from 75 degrees clockwise direction. Control wheel should return to neutral position within + 1 degree.
(3)
Repeat steps (1). and (2). in counterclockwise direction.
(4)
Operate control wheel slowly through full range of aileron travel. Check system for smooth operation.
B. Repeat step D, but only with hydraulic system B pressurized (AMM 27-11-0/201).
C. Repeat step D, but only with hydraulic system A pressurized (AMM 27-11-0/201).
D. With hydraulic systems A and B pressurized, measure force required to manually rotate captain's aileron control wheel clockwise and counterclockwise from neutral.
(1)
Measure force required to rotate control wheel clockwise until ailerons begin to move. Force required shall not exceed 29.25 pound-inches torque or 4.5 pounds.
(2)
Continue rotating control wheel to 5 degrees from neutral. Force required shall not exceed
35.75 pound-inches torque or 5.5 pounds.
(3)
Continue rotating to 20 degrees. Force required should not exceed 55.25 pound-inches torque or 8.5 pounds.
500
May 01/98 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 27-11-81 Page 503
T52460
Aileron Deflection Diagram 523
27-11-81 Figure 502 Aug 01/95
Page 504
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
(4)
Continue rotating to 40 degrees. Force required should not exceed 87.75 pound-inches torque or 13.5 pounds.
(5) 中國航空網 m.k6050.com 航空翻譯 www.aviation.cn 本文鏈接地址：737 AMM 飛機維護手冊 飛行操縱 FLIGHT CONTROLS 1(85)
