AF N4504W ND CF-NAB TS N73715 and N73717 NZ ZK-NAC thru ZK-NAE and ZK-NAM,  less NZ airplanes incorporating SB 27-1021, and 60 士3 degrees clockwise from original neutral position on all other airplanes.
NOTE:  Control wheel neutral position for maintenance purposes is determined by rotating the control wheel left and right in decreasing amounts until the neutral position can be determined by feel.
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Feb 20/85  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  27-11-0 Page 528A 

(c)  
Check that left aileron moves down and right aileron moves up 2.95 + 0.15 inches on airplanes ZK-NAC, ZK-NAD, ZK-NAE and ZK-NAM, and 3.00 +0.14 inches on all other airplanes.

(d)  
Measure force required to rotate aileron control wheel 75 degrees counterclockwise. Force should not exceed 137 pound-inches torque or 21 pounds.

(e)  
Release aileron control wheel from 75-degree counterclockwise position. Check that control wheel returns to 58 +3 or 60 +3 degree clockwise position, as applicable.

(f)  
Operate aileron trim knob counterclockwise to the 10-unit position.

(g)  
Measure movement of captain's and first officer's aileron control wheels from neutral position. Control wheels should have rotated 62 +3 degrees counterclockwise on ZK-NAC, ZK-NAD, ZK-NAE and ZK-NAM, less NZ airplanes incorporating SB 27-1021, and 60 +3 degrees counterclockwise on ZK-NAK and on plus NZ airplanes incorporating SB 27-1021.

(h)  
Check that left aileron moves up 2.95 +0.15 and right aileron moves down 3.15 +0.15 inches on airplanes ZK-NAC, ZK-NAD, ZK-NAE and ZK-NAM, 3.05 +0.15 inches on ZK-NAK, and 3.00 +0.14 inches on all other airplanes.

(i)  
Measure force required to rotate aileron control wheel 75 degrees clockwise. Force should not exceed 137 pound-inches torque or 21 pounds.

(j)  
Release aileron control wheel from 75-degree clockwise position. Check that control wheel returns to 62 +3 or 60 +3 degree counterclockwise position, as applicable.

(k)  
Place aileron trim control knob between 1/3 and 1/2 unit of trim right of zero trim position, or in zero trim position as applicable, and install rudder trim knob torque adapter on knob.

(l)  
Measure force required to rotate knob clockwise until stop is contacted, then counterclockwise until opposite stop is contacted, and then back to between 1/3 and 1/2 unit of trim right of zero trim position, or in zero trim position, as applicable. Force to rotate knob through full travel should not exceed 15 pound-inches torque.

(m)  
Remove rudder trim knob torque adapter.

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(11) Measure force required to operate transfer mechanism.
(a)  
Hold first officer's aileron control wheel rigid in neutral position.

(b)  
Rotate captain's aileron control wheel in clockwise direction from neutral.

(c)  
Force required to initially rotate captain's control wheel from neutral position shall not exceed 436 pound-inches torque or 67 pounds.

(d)  
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.

(e)  
Observe, during rotation of control wheel, that the spring cartridge is compressing and is free from binding.

(f)  
Repeat steps (a) through (e) for movement of captain's aileron control wheel in counterclockwise direction from neutral.

NOTE:  Captain's aileron control wheel shall return to neutral within士1 degree when released from either direction.
(12) Check operation of transfer mechanism. 
(a)  
On airplanes with 65-54200-4 or 65-54200-5 transfer mechanism assembly: 1) With aileron trim knob in rigged position, hold first officer's aileron control wheel in neutral position. 2) Rotate captain's control wheel 100 to 110 degrees in clockwise direction from neutral and return to neutral. 3) Observe, during rotation of control wheel, that there is no binding or other evidence of roughness in the transfer mechanism.

4)  Repeat steps 1), 2), and 3) for movement of captain's aileron control wheel in counterclockwise direction from neutral. 

(b)
On airplanes with all transfer mechanism assemblies EXCEPT 65-54200-4 and -5:

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May 15/70  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  27-11-0 Page 529 

1)  With first officer's control wheel held at 80 degrees in clockwise direction from neutral, rotate captain's control wheel in counterclockwise direction until the transfer mechanism stops are contacted.
　
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