(5)
Continue to rotate control wheel from neutral through 75 degrees of travel. Force required at this point shall not exceed 676 pound-inches torque or 104 pounds.
500
Feb 15/81 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 27-11-61 Page 409
T52456
Aileron Deflection Diagram 523
27-11-61 Figure 405 Aug 01/95
Page 410
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
(6)
Repeat steps (2) through (5) for movement of captain's aileron control wheel in
counterclockwise direction from neutral.
NOTE: Captain's aileron control wheel shall return to neutral within + 1 degree when released from either direction.
(7)
Depressurize hydraulic systems A and B. Refer to 27-11-0, Aileron and Aileron Trim Control System - Maintenance Practices.
U. Measure corresponding movement of captain's and first officer's aileron control wheels.
(1)
Rotate captain's aileron control wheel clockwise through ful1 travel.
(2)
Check that first officer's and captain's aileron control wheels have rotated a minimum of 105 degrees clockwise.
(3)
Repeat procedure in counterclockwise direction from neutral.
V. Measure relationship of aileron control wheel movement as compared with aileron surface deflection.
(1)
Rotate captain's aileron control wheel 87 degrees minimum counterclockwise from neutral.
(2)
Check that left aileron moves up and right aileron moves down within limits specified in figure 405.
(3)
Rotate captain's aileron control wheel 87 degrees minimum clockwise from neutral.
(4)
Check that left aileron moves down and right aileron moves up within limits specified in figure 405.
W. Remove control wheel protractor mount and protractor from aileron control wheel.
X. Remove torque wrench adapter tool from aileron control wheel and reinstall medallion.
501
May 15/70 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 27-11-61 Page 411
AILERON POWER CONTROL UNIT - REMOVAL/INSTALLATION
1. General
A. The ailerons are hydraulically powered by two identical aileron power control units. The lower unit is connected to hydraulic system A, and the upper unit is connected to hydraulic system B. Either power control unit may be replaced without affecting the aileron control system mechanical adjustments. However, the aileron power unit valve control rod may require adjustment to ensure synchronization with the other aileron power control unit. This synchronization of power control units is accomplished with the aileron controls in the neutral position.
B. After removal of power control unit, for removal of control linkage and bus drums, refer to 27-11-101.
2. Equipment and Materials
A. Fire Resistant Hydraulic Fluid - BMS 3-11
3. Remove Aileron Power Control Unit
A. Depressurize hydraulic systems A and B (Ref 27-11-0, Maintenance Practices).
B. Disconnect hydraulic hoses at power control unit inlet and outlet ports. Install plugs in hydraulic hoses.
C. If installed, disconnect electrical connector.
D. Remove the protective boot (Fig. 401).
(1)
Remove two straps from inboard end of boot and one strap from outboard end of boot.
(2)
Remove protective boot.
E. Disconnect valve control rod from valve lever (Fig. 401).
(1)
Remove cotter pin, then remove nut.
(2)
Remove bolt and disengage rod from lever.
F. Disconnect power unit and reaction link.
(1)
Remove cotter pin and remove two nuts.
(2)
Remove power control unit attach bolt at outboard end of reaction link.
(3)
Remove bolt securing safety link to reaction link.
(4)
Swing reaction link aft to provide access to unit.
501
May 01/98 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 27-11-71 Page 401
G10326 G10943
Aileron Power Control Unit Installation 500
27-11-71 Page 402 Figure 401 (Sheet 1) BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. May 01/98
500 Aileron Power Control Unit Installation
May 01/99 Figure 401 (Sheet 2) BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 27-11-71 Page 403
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