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Leading Edge Flap and Slat Control Valve Adjustment 500
27-81-0 Figure 501 (Sheet 1) May 15/67
Page 502
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
500 Leading Edge Flap and Slat Control Valve Adjustment
May 15/67 Figure 501 (Sheet 2) 27-81-0
Page 503
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
Leading Edge Flap Nose Linkage Adjustment 531
27-81-0 Figure 502 (Sheet 1) Feb 15/73
Page 504
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
531 Leading Edge Flap Linkage Adjustment
Jan 20/83 Figure 502 (Sheet 2) 27-81-0
Page 505
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
Leading Edge Flap Linkage Adjustments 531
27-81-0 Figure 502 (Sheet 3) Oct 20/86
Page 506
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
(2) Leading flaps and slats will be properly adjusted when the following conditions are met.
(a)
Leading Edge Flap Control Valve
1) With flaps hydraulically retracted, valve slide shall align with indexing surface within + 0.010 inch (Fig. 501). If not, this condition may be met by adjusting leading edge link in right wheel well per par. 2.(c)(2).
(b)
Leading Edge Flaps (If conditions listed are not met see par. 2.(c)(3) for adjustment). 1) With leading edge flaps extended, flap nose shall seat firmly on pads as shown in Fig. 502.
2) With leading edge flaps retracted hydraulically, the trailing edge of each flap shall fair with fixed wing structure within + 0.02 inch for 75% of flap span and within + 0.04 inch for remaining 25% of span.
3) With leading edge flaps retracted hydraulically, gaps between edge of flaps and
wing structure shall be 0.06 to 0.12 inch. 4) Gaps between adjacent flaps shall be 0.06 to 0.15 inch at all flap positions. 5) Retractable flap nose shall clear structure and equipment on retraction and
when retracted.
(c) Leading Edge Slats (If conditions listed are not met see par. 2.C.(4) for adjustment.)
1) With slat retracted, check that the following gaps and mismatches are as shown in section B-B, Fig. 504: a) Slat trailing edge upper and lower gap b) Slat trailing edge upper and lower surface mismatches
2) With leading edge slats retracted, actuator door and thermal anti-icing tube door shall firmly contact structure on all edges. 3) With slats in intermediate position, check that slat trailing edge gap is as shown in section C-C, Fig. 504. 4) With leading edge slats fully extended, check that slat trailing edge gap is shown in Fig. 506.
B. Equipment and Materials
(1)
Rigging Pin No. F-1 - 0.311 +0.000/-0.002-inch diameter x 2.35 +0.06-inch length (MS20392-4)
NOTE: Rigging pin is part of kit F70207-61 or -84.
(2)
Kit Leading Edge Flap and Slat Locks - F80048-78
C. Adjust Leading Edge Flaps and Slats
(1)
Prepare System for Adjustment
(a)
Remove fixed leading edge access panels and slat track access panels.
(b)
Connect electrical power to airplane.
(c)
Provide system A hydraulic power (Ref 27-81-0, MP).
(2)
Adjust Leading Edge Flap Control Valve
(a)
Position flap control lever to FLAP UP detent position.
(b)
After 5 minutes, depressurize hydraulic system A (Ref 27-81-0 MP).
(c)
Remove lower pan from flap control unit.
(d)
Check that rigging pin F-1 fits freely in the flap control unit. If rigging pin F-1 does not fit, the trailing edge flap system is not properly adjusted (Ref 27-51-01 A/T for adjustment procedure).
(e)
Check that valve slide and indexing surface of leading edge flap control valve align within + 0.010 inch (Fig. 501). If not, adjust leading edge link as follows: 1) Remove lockwire and loosen checknut. 2) Remove rod end bolt at cam follower arm. 3) Turn rod end in 1/2-turn increments to obtain adjustment. 4) Install rod end bolt and check that valve slide and indexing surface align within +
0.010 inch.
5) Secure rod end bolt with washer and locknut.
6) Tighten checknut and install lockwire.
7) Ensure that thread engagement of rod end is within limits.
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