(a)  
Take measurement 0.5 inch in from inboard end of tab. Check that tab trailing edge aligns with an extension of aileron bottom surface within requirements shown on Fig. 510. Record measurement.

(b) 
 Take measurement 3.75 士.25 inch in from outboard end of tab. Tab trailing edge must align with an extension of aileron bottom surface within requirements shown on Fig. 509. Record measurement.

(c)  
Take measurement at midpoint along tab. Check that tab trailing edge aligns with an extension of aileron bottom surface within requirements shown on Fig. 509. Record measurement.

(6)  
Sum up dimensions taken and recorded in step (5). Add plus sign dimensions and subtract minus sign dimensions when determining sum. Sum must be between +0.30 and +0.12 inch.

(7)  
Using straightedge or aileron tab alignment protractor, measure each aileron tab deflection. Take measurement from any point along trailing edge of tab to theoretical extension of aileron bottom surface.

(a)  
Manually move aileron 3.81 inches down from index mark on wing. Check that tab moves up 1.25士0.07 inches.

(b)  
Manually move aileron 3.81 inches up from index mark on wing. Check that tab moves down 1.25 士0.07 inches.

(8)  
Provide systems A and B hydraulic power (Ref 27-11-0).

(9)  
Measure effect of power control units.

(a)  
With hydraulic systems pressurized, and aileron trim knob in zero position, measure force required to rotate either control wheel clockwise until ailerons begin to move. Force required shall not exceed 29.25 pound-inches torque or 4.5 pounds.

(b)  
Continue rotating control wheel to 5 degrees from neutral position. Force required shall not exceed 35.75 pound-inches torque or 5.5 pounds.

(c)  
Continue rotating control wheel to 20 degrees from neutral position. Force required shall not exceed 55.25 pound-inches torque or 8.5 pounds.

(d)  
Continue rotating control wheel clockwise to 40 degrees from neutral position. Force required shall not exceed 87.75 pound-inches torque or 13.5 pounds.

(e)  
Continue rotating control wheel clockwise to 75 degrees from neutral. Force required shall not exceed 120.25 pound-inches torque or 18.5 pounds.

(f)  
Release control wheel from 75-degree clockwise direction. Control wheel should return to neutral position within士1 degree.

(g)  
Repeat steps (a) thru (f) in counterclockwise direction.

(h)  
Position flight controls switch B off and operate control wheel slowly through full range of aileron travel. Check system for smooth operation. Verify balance tabs operate in opposite direction of aileron movement.

(i)  
Position flight controls switch A off and switch B on and repeat step (h).

(j)  
Position flight controls switches A and B on and repeat step (h).

(10)
Measure effect of aileron trim knob operation.

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Sep 20/82  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  27-11-0 Page 527 

NOTE:  All measurements are to be made with wing trailing edge flap extended one to five units.
(a)  
Operate aileron trim knob clockwise to the 10 unit position.

(b)  
Measure movement of captain's and first officer's aileron control wheels from neutral (zero trim) position. Assist control wheels, as necessary, to new neutral position. Check that control wheel position is 60 士3 degrees clockwise from original neutral position.

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.

(c)  
Check that left aileron moves down 3.00士0.14 inches.

(d)  
Check that right aileron moves up 3.00 士0.14 inches.

(i)  
Position flight controls switch A off and switch B on and repeat step (h).

(j)  
Position flight controls switches A and B on and repeat step (h).

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(10) Measure effect of aileron trim knob operation.
NOTE:  All measurements are to be made with wing trailing edge flap extended one to five units.
(a)  
Operate aileron trim knob clockwise to the 10 unit position.

(b)  
Measure movement of captain's and first officer's aileron control wheels from neutral (zero trim) position. Assist control wheels, as necessary, to new neutral position. Check that control wheel position is 58 士3 degrees clockwise from original neutral position on airplanes:
　
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