(3)  
Set aileron trim control knob in zero trim position.

(4)  
The outboard trailing edge flaps must be properly adjusted, or must be extended 1 to 5 degrees to eliminate possible deflection of point A (Fig. 506) on the wing structure (Ref 27-51-0, Trailing Edge Flap System).

(5)  
Ensure hydraulic system A and B are depressurized (Ref 27-11-0, Maintenance
Practices).

D.  Test Aileron and Aileron Trim Control System
(1)  Check for control wheel and control column binding.
(a)  
Move column repeatedly fore and aft between stops and simultaneously move control wheel repeatedly left and right between stops.

(b)  
Hold control wheel left against stop and move control column fore and aft between stops.

(c)  
Hold control wheel right against stop and move control column fore and aft between stops.

(d)  
Hold control column full forward and move control wheel left and right between stops.

(e)  
Hold control column full aft and move control wheel left and right between stops.

(1A) Using torque wrench and control wheel torque and force test adapter tool, measure force required to manually rotate captain's aileron control wheel clockwise and counterclockwise from neutral. If tool is not available, apply force tangentially to captain's control wheel at 6.5-inch radius.
(a)  
The force required to begin clockwise rotation shall not exceed 192 pound-inches torque or 29.5 pounds.

(b)  
Rotate control wheel clockwise to 20 degrees. Measured force shall not exceed 220 pound-inches torque or 33.8 pounds.

(c)  
Continue clockwise rotation to 40 degrees. Measured force shall not exceed 256 pound-inches torque or 39.4 pounds. 

(d)  
Continue clockwise rotation to 75 degrees. Measured force shall not exceed 310 pound-inches torque or 47.7 pounds.

(e)  
Repeat steps (a) thru (d) in a counterclockwise direction.

506 
27-11-0 Page 524  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  Nov 15/80 

(2)  Measure first officer's aileron control wheel for lost motion in clockwise and counterclockwise direction from neutral.
(a)  
Install rigging pin A/S-3 (Fig. 504).

(b)  
Rotate first officer's control wheel and check right AA and AB cables for initial movement. As initial movement occurs, the control wheel shall have rotated 12 士1 degrees from neutral.

NOTE:  The aileron control drum on the first officer's control column may be used to determine when the lost motion device has reached its stop (Fig. 503).
At approximately 6 degrees of control wheel travel from neutral position, the aileron power control unit slide valve bottoms out and considerably more force is required to turn the control wheel. This is normal and test is to be performed with hydraulic system depressurized.
(c)  Remove rigging pin A/S-3.
(3)  
Measure corresponding movement of captain's and first officer's aileron control wheels.

(a)  
Rotate captain's aileron control wheel clockwise through full travel.

(b)  
Check that first officer's and captain's aileron control wheels have rotated a minimum of 105 degrees clockwise.

(c)  
Repeat procedure in counterclockwise direction from neutral.

(4)  
Measure relationship of aileron control wheel movement as compared with aileron surface deflection (for static conditions).

NOTE:  All measurements are made with the wing trailing edge flaps extended one to five units. No airload condition is necessary for you to get the specified surface deflection.
(a)  
Pressurize hydraulic systems A and B (AMM 27-11-0/201).

(b)  
Rotate captain's aileron control wheel 87 degrees minimum counterclockwise from neutral.

(c)  
Check that left aileron moves up and right aileron moves down within limits specified in Fig. 506. 

(d)  
Rotate captain's aileron control wheel 87 degrees minimum clockwise from neutral.

(e)  
Check that left aileron moves down and right aileron moves up within limits specified in Fig. 506.

(f)  
Release pressure from hydraulic systems A and B (AMM 27-11-0/201).

501 
Aug 01/96  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  27-11-0 Page 525 

(5)  
With index mark on aileron aligned with index mark on wing within 0.03 inch, check mismatch between aileron trailing edge and aileron tab trailing edge. Using straightedge or aileron tab alignment protractor, measure mismatch from trailing edge of tab to theoretical extension of aileron bottom surface at three locations. Record all measurements for later addition. If trailing edge of tab is above theoretical extension of aileron bottom surface, measurement is recorded as a plus (+) dimension. If trailing edge of tab is below theoretical extension of aileron bottom surface, measurement is recorded as a minus (-) dimension.
　
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