(c)  
Make sure the step clearances at the quadrants of the power control unit are not out of tolerance (AMM 27-11-0/501).

(d)  
If flaps up lateral trim exceeds 3/4 unit, manual reversion discrepancy should not be corrected until trim is corrected and manual reversion discrepancy verified by next flight.

WARNING:  CHECK THAT HYDRAULIC SYSTEMS A AND B ARE DEPRESSURIZED BEFORE PROCEEDING FURTHER (REF 27-11-0/201).
(2)  Excessive Forces Left Discrepancy Correction
(a)  
Forces are recorded by pilots at approximately 30 degrees clockwise and 30 degrees counterclockwise control wheel position.

NOTE:  The forces are measured and recorded in the “Flight Test to determine and correct Asymmetrical Flight Control Forces” (AMM 27-11-0/501).

(b)  
Get the force ratio by dividing counterclockwise force by clockwise force or else divide clockwise force by counterclockwise force to get a value greater than 1.0.

(c)  
Forces are corrected by changing tab rod lengths to raise or lower aileron tab relative to aileron.

(d)  
After force ratio is determined, select correct amount of tab rod change from Fig. 503.

(e)  
With aileron indexes aligned, measure the tab trailing edge mismatch with the lower aileron surface by using a straightedge or aileron tab alignment protractor positioned at the rod attach points and record this dimension.

NOTE:  After aileron tab control rod length adjustments are completed, the aileron tab trailing edge must be within -0.01 to +0.15 inch of the aileron lower surface on airplanes with nonadjustable aileron tab control rods, or within +0.05 to +0.09 inch of the aileron lower surface on airplanes with adjustable aileron tab control rods. These dimensions are applicable at the midpoint of the aileron tab. To complete the adjustment within the required dimensions, it may be necessary to divide the total required control rod adjustment between the left and the right wings (Ref 27-11-0 A/T).

(f)  
Either shorten left tab rod set or lengthen right tab rod set or a combination of both to obtain required amount of tab rod change from Fig. 503. 1) Shorten or lengthen nonadjustable aileron tab rods as follows:

NOTE: For either tab, both rods must be changed in sets.
501 
Aug 01/96  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  27-09-400 Page 515 

a)  Note amount and direction of required adjustment of tab trailing edge. Take measurements of trailing edge back of tab rod attachment.

G42321
Aileron Tab Adjustment Chart  500 
27-09-400  Figure 503  Jun 20/90 
Page 516 
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 

b) Remove bolts attaching tab rods to forward fittings.
c) Remove aileron tab hinge bolts and remove tab and rods from aileron.
d) Record rod lengths and drill out two 5/32 inch diameter rivets at forward

rod end fitting of each tab set. e) Reposition rod end fitting to shorten or lengthen rod as required, and clamp securely in a suitable jig. f) Redrill holes and install two 3/16 inch diameter rivets in each forward rod end fitting and tab rod. 2) Shorten or lengthen adjustable aileron tab control rods as follows: a) Note amount and direction of required adjustment of tab trailing edge. Take
measurements of trailing edge back of tab rod attachment. b) Remove bolts attaching tab rods to aileron hinge fitting on rear spar. c) Remove aileron tab hinge bolts and remove tab and rods from aileron. d) Loosen jamnuts on tab rod being careful not to reposition rod end or rod
barrel. e) Turn barrel required number of turns, being careful to restrain rod and rod end angularly.
f)  Check that witness holes in barrel are covered. Tighten jamnuts using a torque of 100 to 140 pound-inches for the smaller jamnut and 80 to 100 pound-inches for larger jamnut. Lockwire jamnuts.
g)  Reinstall tab and rods on aileron. Attach bolts for tab rods must be inserted with fingers only to ensure there is no binding between rod and bolt or deflection of rods. Readjust length of rod if binding or deflecting occurs.
h)  With aileron indexes aligned, measure and record the tab trailing edge mismatch with the lower aileron surface by using a straightedge or aileron tab alignment protractor positioned at the rod attach points.
NOTE:  The trailing edge of the aileron balance tab must move in the direction that is necessary. To correct high left forces, the tab trailing edge must move down on the left aileron or up on the right aileron or a combination of the two. To correct the high right forces, the tab trailing edge must move down on the right aileron or up on the left aileron or a combination of the two.
　
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