G27515
Flap 40 Unit Switches Adjustment 530
27-51-331 Figure 501 May 15/70
Page 502
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
2. Flap 40-Unit Switches Test
A. Prepare to test flap 40-unit switches.
(1)
Close FLAP LOAD LIMITER circuit breaker on circuit breaker panel\P6.
(2)
Pressurize hydraulic system A.
(3)
Position flap control lever to 40-unit detent.
NOTE: If airplane is on jacks, compress right-hand main gear strut approximately 5 inches to the ground position.
B. Test flap 40-unit switches.
(1)
Actuate flap load limiter test switch on the equipment bay light panel in the electronics compartment to the SYSTEM TEST position. Observe that flaps retract to 30-unit position.
(2)
Release test switch and check that flaps extend to 40-unit position.
(3)
Place flap control lever in 30-unit position and check that flaps retract to 30-unit position.
(4)
Actuate flap load limiter test switch to SWITCH TEST position and observe that test lamp lights; and that light extinguishes upon release of switch.
C. Return airplane to normal.
(1)
Raise flaps by positioning flap control lever to FLAPS UP detent.
(2)
Turn off hydraulic system A power.
(3)
Open FLAP LOAD LIMITER circuit breaker on circuit breaker panel\P6.
530
Jun 20/90 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 27-51-331 Page 503
INBOARD MIDFLAP SEAL PLATE - REMOVAL/INSTALLATION
1. General
A. The following procedure applies to both the left and right inboard midflap seal plates. Equipment and Materials
A. Primer - BMS 10-11, Type I (Ref 20-30-41)
B. Sealant - BMS 5-79, Class C (Ref 20-30-11)
3. Remove Seal Plate (Fig. 401)
A. Provide system A hydraulic power (Ref 27-51-0, Maintenance Practices).
B. Extend flaps to full down position.
C. Remove system A hydraulic power (Ref 27-51-0).
D. Remove seal plate mounting bolts and screw, and remove plate from midflap.
NOTE: Retain all filler plates and shims for reinstallation of seal plate.
4. Install Seal Plate (Fig 401)
A. Position seal plate on midflap and install all bolts and screws. Install fillers and shims removed with old seal plate. Apply primer to bare shims and install shims and fillers with faying surface sealant.
B. Position seal plate at approximate center of slotted holes and tighten bolts and screws.
C. Provide system A hydraulic power (Ref 27-51-0).
500
May 15/78 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 27-51-341 Page 401
D. Raise flaps to the full up position.
E. Adjust gap between seal plate and wing to body fairing.
(1)
Check that gap at leading edge is 0.06 + 0.19/-0.06 inch. Average of readings taken at 6-8-inch intervals including maximum gap must not exceed 0.09 inch.
(2)
Check that gap at trailing edge is 0.06 + 0.19/-0.06 inch. Average of readings taken at 6-8-inch intervals including maximum gap must not exceed 0.15 inch.
(3)
If adjustment is required, adjust by increasing or decreasing thickness of shims or repositioning in slots as shown in Fig. 401.
(4)
If average readings cannot be obtained or seal plate deformation occurs during retraction due to contact at lower edge, adjust seal plate vertically to obtain gap less than stated in above steps.
F. With flaps in full up position, check that lower curved end fits to give maximum contact with minimum pressure to fairing. If adjustment is required, adjust by increasing or decreasing thickness of shim as shown in Fig. 401.
G. Extend flaps and check that at least 0.03 -inch clearance between seal plate and body fairing is maintained during flap transit. Check that seal plate does not bind against flap track fairing. Readjust if necessary.
H. Check that forward segment of seal plate fairs with main seal plate within 0.00 to 0.03 inches and that forward segment clears body fairing 0.03 inch throughout full cycle of flaps. If not, readjust as necessary. Apply primer to bare shims and install with faying surface sealant.
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