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1) Using a push/pull scale 0-25 pound (0-11 kilogram), STD-753. Make sure the force to
turn the control wheel is not more than 29.0 pound-inches (3.2 newton-meters) or 4.5
pounds (20.0 newtons).
SUBTASK 27-11-00-820-021
(4) If the control wheels center properly, and breakout forces are within the limits above, then no
adjustment is necessary.
SUBTASK 27-11-00-820-013
(5) If the control wheels are not in the center or the breakout forces are out of tolerance, adjust the
tension of the springs [63] on the centering unit [61]:
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(a) Hold the eyebolt [66] while you tighten or loosen the nut [65] in 1/2 turn increments.
NOTE: You must tighten the two eyebolts [66] equally. Tighten the eyebolts [66] to
increase the spring forces. Loosen the eyebolts [66] to decrease the spring
forces.
(b) Adjust the nut [65] until the force to turn the control wheel is not more than 29.0 poundinches
(3.3 newton-meters) or 4.5 pounds (20.0 newtons).
(c) Tighten the checknuts [64].
(d) Make sure the shaft [70] can turn freely.
SUBTASK 27-11-00-750-001
(6) After adjustment of breakout forces above, do the following steps to do a check of the breakout
forces and make sure the control wheel is centered properly:
(a) Turn the control wheel clockwise until the aileron starts to move.
1) Make sure the force to turn the control wheel is not more than 29.0 pound-inches (3.3
newton-meters) or 4.5 pounds (20.0 newtons).
(b) Release the control wheel.
1) Make sure the control wheel goes back to the neutral position in 0.0 ±0.4 units of trim
(2.4 degrees).
(c) Turn the control wheel counterclockwise until the aileron starts to move.
1) Make sure the force to turn the control wheel is not more than 29.0 pound-inches (3.3
newton-meters) or 4.5 pounds (20.0 newtons).
(d) Release the control wheel.
1) Make sure the control wheel goes back to the neutral position in 0.0 ±0.4 units of trim
(2.4 degrees).
G. Put the Airplane Back to Its Usual Condition
SUBTASK 27-11-00-080-006
(1) Remove the adapter, SPL-1674 from the captain’s aileron control wheel.
SUBTASK 27-11-00-080-007
(2) Remove the mount, SPL-1670 and the control column assembly protractor, SPL-1680 from the
first officer’s control wheel.
SUBTASK 27-11-00-080-008
(3) Remove power from hydraulic systems A and B, do this task: Hydraulic System A or B Power
Removal, TASK 29-11-00-860-805.
------------------------- END OF TASK ---------------------------
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Aileron Feel and Centering Unit Adjustment
Figure 505 (Sheet 1 of 2)/27-11-00-990-806
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Aileron Feel and Centering Unit Adjustment
Figure 505 (Sheet 2 of 2)/27-11-00-990-806
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TASK 27-11-00-820-805
6. Do A Check of the Aileron System Adjustment
(Figure 506)
A. References
Reference Title
27-51-00-860-803 Extend the Trailing Edge Flaps (P/B 201)
27-51-00-860-804 Retract the Trailing Edge Flaps (P/B 201)
29-11-00-860-801 Hydraulic System A or B Pressurization (P/B 201)
29-11-00-860-805 Hydraulic System A or B Power Removal (P/B 201)
32-00-01-480-801 Landing Gear Downlock Pins Installation (P/B 201)
B. Tools/Equipment
NOTE: When more than one tool part number is listed under the same "Reference" number, the
tools shown are alternates to each other within the same airplane series. Tool part numbers
that are replaced or non-procurable are preceded by "Opt:", which stands for Optional.
Reference Description
SPL-1585 Kit - Rigging Pins, All Systems
(Part #: F70207-109, Supplier: 81205, A/P Effectivity: 737-600, -700,
-700C, -700ER, -700QC, -800, -900, -900ER, -BBJ)
SPL-1671 Straightedge - Control Wheel
(Part #: SE27-0001, Supplier: 81205, A/P Effectivity: 737-100, -200,
-200C, -300, -400, -500, -600, -700, -700C, -700ER, -700QC, -800, -900,
　
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