(4)
Lockwire bolt heads.
(5)
Deleted.
(6)
Provide system A hydraulic power (refer to 27-51-0), and check for leakage.
(7)
Test solenoid valve (Ref Flap Load Limiter Solenoid Valve - Adjustment/Test).
F. Return Airplane to Normal
(1) Remove system A hydraulic power (Refer 27-51-0).
522
Feb 15/81 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 27-51-212 Page 407
TRAILING EDGE FLAP CONTROL VALVE -ADJUSTMENT/TEST
1. Trailing Edge Flap Control Valve Adjustment
A. Equipment and Materials
(1) Rigging Pin - F-1, 0.311 (+0.000/-0.002) inch diameter, 2.35 +0.06 inches long (MS20392-4)
NOTE: Rigging pin is a part of kit F70207-61 or -84.
B. Prepare Trailing Edge Flap Control Valve for Adjustment
(1)
Pressurize hydraulic system A (Ref 27-51-0 MP).
(2)
Position flap control lever to FLAP DOWN detent.
(3)
Position flap control lever in FLAP UP detent.
(4)
Wait 2 minutes then depressurize hydraulic system (Ref 27-51-0 MP).
(5)
Remove lower pan from flap control unit (Fig. 501).
C. Adjust Trailing Edge Flap Control Valve
(1) Check that valve slide and indexing surface of trailing edge flap control valve align within
+ 0.010 inch (Fig. 501, Detail A). If not, adjust trailing edge cam link as follows:
(a)
Remove lockwire and loose two checknuts (Detail B).
(b)
Adjust sleeve to align valve slide and indexing surface within + 0.010 inch.
(c)
Tighten checknuts and install lockwire (2 places).
(d)
Ensure that thread engagement of rod end and vernier sleeve is within limits.
587
Feb 20/88 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 27-51-212 Page 501
G25426G25423
Trailing Edge Flap Control Valve Adjustment 522
27-51-212 Figure 501 (Sheet 1) Feb 15/71
Page 502
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
522 Trailing Edge Flap Control Valve Adjustment
Feb 15/71 Figure 501 (Sheet 2) 27-51-212
Page 503
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
(e) If thread engagement is not within limits: 1) Remove rod end bolt. 2) Loosen checknut and turn rod end in one-half turn increments to obtain
approximate adjustment.
3) Install rod end bolt and secure with washer and locknut.
4) Repeat steps (a) through (d).
(2)
Ensure that rigging pin F-1 is not installed.
CAUTION: IF NOT REMOVED, RIGGING PIN F-l MAY DAMAGE FLAP CONTROL UNIT WHEN HYDRAULIC POWER IS APPLIED.
(3)
Provide system A hydraulic power. Refer to 27-51-0.
(4)
Position flap control lever in 5-unit detent to extend flaps, then set lever in FLAP UP detent.
(5)
After 2-minute wait, remove system A hydraulic power. Refer to 27-51-0.
(6)
Check that rigging pin F-1 fits freely in the flap control unit. If rigging pin does not fit freely, adjust trailing edge cam link as follows:
(a)
Remove lockwire and loosen two checknuts.
(b)
Remove rigging pin F-1.
(c)
Provide system A hydraulic power. Refer to 27-51-0.
(d)
Adjust sleeve to align rigging pin holes for rigging pin F-1.
CAUTION: DO NOT INSTALL RIGGING PIN F-l WITH HYDRAULIC POWER ON.
NOTE: If rigging pin slot in follow-up cam must be rotated downward, cam link must be shortened. This is accomplished by rotating sleeve clockwise.
(e)
Position flap control lever in 5-unit detent to extend flaps, then set lever in FLAP UP detent.
(f)
After 2-minute wait, remove system A hydraulic power. Refer to 27-51-0.
(g)
Check that rigging pin F-1 fits freely. If not, repeat steps (b) through (f).
(h)
Tighten checknuts and install lockwire, two places.
(i)
Ensure that thread engagement of rod end and sleeve is within limits.
522
27-51-212 Page 504 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. Nov 15/79
(7)
Remove rigging pin F-1.
(8)
Provide system A hydraulic power (Ref 27-51-0).
(9)
Position flap control lever to FLAP DOWN detent and then to FLAP UP detent. Pause at FLAP DOWN and FLAP UP detent to allow flap drive unit to respond. Repeat for five cycles.
中國航空網(wǎng) www.k6050.com
航空翻譯 www.aviation.cn
本文鏈接地址：737 AMM 飛機(jī)維護(hù)手冊 飛行操縱 FLIGHT CONTROLS 3(62)
