(2)  
Retract flaps by providing system A hydraulic power (Ref 27-51-0), retracting flaps to FLAPS UP position and removing system A hydraulic power (Ref 27-51-0).

(3)  
Check that aftflap leading edge to midflap trailing edge gap is per Section A-A. If necessary, adjust aftflap pushrods at both flap track fairings to obtain correct gap.

(4)  
Extend flaps to 40 units and ensure that mid-to-aftflap gaps and dimension B remain unchanged.

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L.  Retract flaps
M.  Adjust aftflap trailing edge as follows (Fig. 402):
(1)  
Retract flaps.

(2)  
Remove plug screws and attach outboard flap rigging tool at location marked by black arrows at WBL 228.5 or hand position outboard flap rigging beam to black stripes located at WBL 228.5 on front and rear spar.

NOTE:  If black stripes are not on airplane, stencil 0.25 inch wide stripes per tool drawing F80209.

(3)  
Check that gap between aftflap trailing edge and fairing sidewall, on both sides of fairing is

0.10 inch. If not, adjust fairing supports.
NOTE:  Excessive pressure from fairing will lift trailing edge of fairing.
(4)  Apply 30 pound upward force against a minimum 4.0 by 6.0 inch aluminum plate at aft edge of aftflap near aftflap track rollers to hold aftflap in retracted position and measure flap position at flap rigging tool and fixed rib at outboard end of flap. Check that flap trailing edge is 0.00 to 0.25 inch below wing chord plane with aftflap airload rollers contacting flap track. Check that flap is symmetrical within 0.10 inch of opposite flap wing chord plane alignment.
NOTE:  If this dimension cannot be achieved without exceeding the 0.23-inch maximum allowable shim thickness, use a 0.23-inch shim regardless of the flap position relative to the wing chord. If you have made trim corrections with the outboard TE flaps, the dimension can be more than the 0.00 to 0.25-inch limit.
The aftflap is in the retracted position when the clearance between the lower trailing edge of the midflap and the leading edge of the aftflap is 0.00 to 0.13-inch for the full length of the aftflap.
(5)  
If flap trailing edge is not within limits, refer to chart and determine shim thickness required to position flap trailing edge 0.00 to 0.25 inch below wing chord plane. Inboard and outboard carriage shims should be equal within 0.12 inch.

NOTE:  Inboard and outboard carriage shims may be changed to within 0.120 inch after first flight to achieve straight and level flight, however, thickness of shim cannot exceed 0.23 inch.

(6)  
Remove access panels from upper surface of midflap to gain access to each carriage bearing support.

(7)  
Remove bolts attaching carriage bearing support to midflap forging.

(8)  
Position carriage bearing support over end of flap carriage with correct shim thickness installed between carriage support and midflap forging, install bolt with washer and nut. Tighten 3/8-inch nut 160 to 190 pound-inches and tighten 5/16-inch nut 100 to 140 pound-inches.

(9)  
Remove outboard flap rigging tool and install plug screws if required.

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Jun 20/91  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  27-51-91 Page 407 

N.  Apply sealant to access panel and midflap faying surface and install access panels at midflap upper trailing edge.
O.  Check for correct aftflap leading edge seal compression as follows (Detail C, Fig. 401):
(1)  
With flap extended, mark a line on lower surface of aftflap 2.00 inches aft of leading edge.

(2)  
Retract flap, then mark a line on lower surface of midflap 2.15 inches forward of line marked on aftflap.

(3)  
Extend flap and check that aft face of seal retainer aligns with line marked on midflap.

(4)  
If seal retainer does not align, loosen screws and position seal retainer to obtain correct position. Tighten screws.

P.  Adjust flap jackscrew preload pad (Fig. 403)
(1)  
If installed, remove aft fairing.

(2)  
Remove flap jackscrew preload pad from aftflap.

(3)  
With flaps retracted, measure dimension B. If dimension B is not within limits adjust shims in gimbal as follows:

(a)  
Position flap control lever to FLAP DOWN detent.

(b)  
Support flap so that weight of flap is off trunnions. Loosen gimbal bushing clamp-up bolts, remove gimbal bushing retaining bolts and slightly withdraw horizontal bushings to free shims. Adjust shim laminations to attain dimension B (Section A-A, Fig. 403).
　
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