(3)
Check that aileron trim control rigging is within allowable tolerances. Correct rigging as necessary (Ref 27-11-0, A/T).
(4)
Check that outboard trailing edge flap mismatch is within allowable tolerances. Correct rigging as necessary (Ref 27-51-72 A/T).
(5)
Check that spoiler to flap clearance and spoiler pickup points are within allowable tolerances. Correct rigging as necessary (Ref 27-61-0 A/T and 27-62-0 A/T).
(6)
Check that rudder rigging and rudder centering mechanism are within allowable
tolerances. Correct rigging as necessary (Ref 27-21-0 AT).
(7)
If any noted discrepancy is corrected, determine the effect on the excessive aileron trim requirement. See Fig. 501 to determine amount of shim required for FLAP UP trim correction.
503
27-09-400 Page 502 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. Jun 20/84
C. Prepare for Shimming
(1)
Provide system A hydraulic power (Ref 27-51-0 MP).
(2)
Position flap control lever to FLAP DOWN (40-unit) detent.
(3)
Remove system A hydraulic power (Ref 27-51-0).
(4)
Remove access panels from upper surface of midflap to gain access to each carriage bearing support.
D. Shim Outboard Flaps
(1) If reported discrepancy is right wing heavy condition requiring excessive left trim, proceed as follows:
(a)
Remove bolts attaching left wing carriage bearing support to midflap forging (Fig. 502).
(b)
Remove shims from left outboard flap or add shims to right outboard flap or a combination of both to obtain required shim thickness change, determined from Fig.
501. Shims must be added or removed equally from both carriages of a flap.
NOTE: The recommended total shim thickness is 0.20 inch and the allowable total shim thickness shall not exceed 0.23 inch. Total shim thickness includes shims installed during assembly and installation plus shims added for trim correction. Marking and dating total shim thickness on upper access panel will provide a record to aid further adjustments.
Following any shimming for the purpose of trim correction, the allowable tolerance of 0.00 to -0.25 inch for outboard flap trailing edge mismatch with the wing trailing edge may be exceeded.
Shim thickness between leaf spring and midflap must be changed an equal amount when shim thickness between carriage bearing support and midflap is changed (i.e. add same thickness shim under leaf spring as removed from under carriage bearing support). Tapered filler between leaf spring and midflap may be used individually or at both track locations and may be positioned with thick end forward or aft or reversed relative to each other.
501
Feb 20/89 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 27-09-400 Page 503
(2) If reported discrepancy is left wing heavy condition requiring excessive right trim, proceed as follows:
(a)
Remove bolts attaching right wing carriage bearing support to midflap forging.
(b)
Remove shims from right outboard flap or add shims to left outboard flap or a combination of both to obtain required shim thickness change, determined from Fig.
501. Shims must be added or removed equally from both carriages of a flap.
NOTE: The recommended total shim thickness is 0.20 inch and the allowable total shim thickness shall not exceed 0.23 inch. Total shim thickness includes shims installed during assembly and installation plus shims added for trim correction. Marking and dating total shim thickness on upper access panel will provide a record to aid further adjustments.
Following any shimming for the purpose of trim correction, the allowable tolerance of 0.00 to -0.25 inch for outboard flap trailing edge mismatch with the wing trailing edge may be exceeded.
Shim thickness between leaf spring and midflap must be changed an equal amount when shim thickness between carriage bearing support and midflap is changed (i.e. add same thickness shim under leaf spring as removed from under carriage bearing support). Tapered filler between leaf spring and midflap may be used individually or at both track locations and may be positioned with thick end forward or aft or reversed relative to each other.
G42319
Trailing Edge Flap Adjustment 500
27-09-400 Figure 501 (Sheet 1) Jun 20/89
Page 504
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
G42320
500 Trailing Edge Flap Adjustment
Jun 20/89 Figure 501 (Sheet 2) 27-09-400
Page 505
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