NOTE: A 0.003-inch shim lamination will change dimension B 0.0167 inch. Transfer shim equally to maintain 0.006- to 0.010-inch clearance between bushings and gimbal. Also clearance between midflap gimbal attach fittings and gimbal shall be 0.01 inch minimum.
(c)
Install gimbal bushing retaining bolts and tighten gimbal bushing clamp-up bolts 60 to 85 pound-inches.
543
27-51-91 Page 408 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. Jun 20/91
G18852 G21337
543 Flap Jackscrew Preload Pad Adjustment
May 15/78 Figure 403 (Sheet 1) 27-51-91
Page 409
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
Flap Jackscrew Preload Cup Adjustment 543
27-51-91 Figure 403 (Sheet 2) Oct 20/84
Page 410
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
(4)
With flaps extended, check that jackscrew end fitting has 0.03 inch minimum vertical clearance with fitting on midflap. If clearance is not adequate, adjust ball nut shims as follows:
(a)
Support flap so that weight of flap is not on trunnions. Remove ball nut bushing retaining bolts and slightly withdraw vertical bushings to free shims. Adjust shims laminations to attain clearance.
NOTE: Transfer shims equally to maintain 0.006 to 0.010 inch between bushings and ball nut.
(b)
Install ball nut bushing retainer bolts in gimbal.
(5)
Position flap control lever to FLAP UP detent to retract flaps.
(6)
During retraction check that flap jackscrew clears all linkage and structure.
(7)
With flaps retracted place up load on aftflap and measure dimension A.
(8)
Position flap control lever to 1-unit position to partially extend flaps.
(9)
Install flap jackscrew preload pad and shim so that dimension C is as specified (Fig. 403).
NOTE: If dimension C is greater than specified when no shims are installed, dimension A may be increased, as required, per step (4).
(10)
Position flap control lever to FLAP UP detent.
(11)
Check that flap jackscrew end fitting enters preload pad slightly before flap full up position and seats firmly against preload pad when flap is retracted.
(12)
Position aft fairing on center fairing and install attaching screws.
Q. Check aftflap operates smoothly with no binding or structural interference.
5. Restore Airplane to Normal Configuration
A. Position flap control lever to FLAP UP detent.
B. Depressurize hydraulic system A (Ref 27-51-0, Maintenance Practices).
543
Aug 01/75 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 27-51-91 Page 411
OUTBOARD TRAILING EDGE AFT FLAP - INSPECTION/CHECK
1. General
A. This data consists of illustrations and a wear limit chart. There will be no procedure given for gaining access to the component for removal or replacement after inspection for wear. Refer to Outboard Trailing Edge Aft Flap, Removal/Installation for this information.
2. Outboard Trailing Edge Aft Flap Wear Limits (Fig. 601)
G19770
500 Outboard Trailing Edge Aft Wear Limits
Aug 15/73 Figure 601 27-51-91
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BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
OUTBOARD FOREFLAP - REMOVAL/INSTALLATION
1. General
A. The upper leading edge of the foreflap is finished with an abrasion resistant teflon coating. If repair of teflon coating is required, refer to Chapter 51, Abrasion Resistant Teflon Finish system.
2. Remove Outboard Foreflap
A. Provide system A hydraulic power. Refer to 27-51-0, Trailing Edge Flaps - Maintenance Practices.
B. Position flap control lever to FLAP DOWN (40-unit) detent, to extend flaps.
C. Remove system A hydraulic power. Refer to 27-51-0.
D. Remove bolts attaching foreflap to foreflap sequencing carriage at each flap track. (See figure 401.)
E. Remove bolts attaching each foreflap link assembly to foreflap track and remove foreflap.
NOTE: Foreflap weighs approximately 64 pounds.
3. Install Outboard Foreflap
A. Align foreflap fitting with lugs on each sequencing carriage and install bolts. (See figure 401.)
Secure bolt with washer and nut. Tighten nut to 60-85 pound-inches and install cotter pin.
B. Install bolts connecting foreflap links to foreflap tracks. 中國航空網 www.k6050.com 航空翻譯 www.aviation.cn 本文鏈接地址：737 AMM 飛機維護手冊 飛行操縱 FLIGHT CONTROLS 3(40)
