G05490 G05497
500 Aileron System Cable Tension Requirements
Jun 20/85 Figure 402 27-11-61
Page 405
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
Aileron Control Wheel Adjustment 500
27-11-61 Figure 403 Aug 15/67
Page 406
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
K. Remove straightedge from control wheels and rotate control wheel through several cycles.
L. Check rigging by placing a straightedge across upper ends of both control wheels. One end of first officer's control wheel may be out of contact with straightedge by 0.20 inch maximum.
M. Check that cable tension is within values in figure 402.
N. Install cable shields and clamps.
O. Adjust right cables AA and AB.
NOTE: Aileron trim system must be adjusted prior to proceeding with this step.
(1)
Place control wheels in neutral by clamping straightedge on upper ends of both control wheels.
(2)
Place aileron trim control knob in zero trim position.
(3)
Check that trim roller is firmly detented against cam.
(4)
Adjust cable tension within required value range on figure 402.
(5)
Rotate aileron control wheel through several complete cycles.
(6)
Insert rigging pins A/S-1, A/S-A and A/S-3.
(7)
Check that cable tension is within required value range on figure 402.
(8)
Install turnbuckle locking clips.
(9)
Remove all rigging pins.
P. Install protractor and protractor mount on first officer's aileron control wheel.
Q. Remove medallion and install torque wrench adapter tool on captain's control wheel. (See figure 404.)
506
Aug 15/69 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 27-11-61 Page 407
G10235
Control Wheel Torque and Force Test Adapter Tool 500
27-11-61 Figure 404 Nov 15/72
Page 408
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
R. Using torque wrench and torque wrench adapter, measure force required to manually rotate captain's aileron control wheel clockwise and counterclockwise from neutral. If torque wrench adapter tool is not available, apply force tangentially to captain's control wheel at a 6.5-inch radius.
(1)
Measure force required to rotate control wheel clockwise until aileron begins to move. Force required shall not exceed 192 pound-inches torque or 29.5 pounds.
(2)
Continue rotating control wheel to 20 degrees from neutral. Force required shal1 not exceed 220 pound-inches torque or 33.8 pounds.
(3)
Continue rotating to 40 degrees. Force required shal1 not exceed 256 pound-inches torque or 39.4 pounds.
(4)
Continue rotating to 75 degrees. Force required shal1 not exceed 310 pound-inches torque or 47.7 pounds.
(5)
Repeat steps (1) through (4) in a counterclockwise direction.
S. Measure first officer's aileron control wheel for lost motion in clockwise and counterclockwise direction from neutral.
(1) Rotate first officer's control wheel and check right AA and AB cables for initial movement. As initial movement occurs, the control wheel should have rotated 12 (+ 1) degrees from neutral.
T. Measure force required to operate transfer mechanism.
(1)
Pressurize hydraulic systems A and B. Refer to 27-11-0, Aileron and Aileron Trim Control System - Maintenance Practices.
(2)
Hold first officer's aileron control wheel rigid in neutral position.
(3)
Rotate captain's aileron control wheel in clockwise direction from neutral.
(4)
Force required to initially rotate captain's control wheel from neutral position shall not exceed 436 pound-inches torque or 67 pounds.
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