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535 Sep 20/82 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 27-51-01 Page 509
G12073 Flap Power Unit Adjustment 535 27-51-01 Figure 504 May 15/72 Page 510 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
(c) Check that valve slide and indexing surface of trailing edge flap control valve align within + 0.010 inch. (See detail A.) If not, adjust trailing edge cam link as follows: 1) Remove lockwire and loosen two checknuts. (See detail B.) 2) Adjust sleeve to align valve slide and indexing surface within + 0.010 inch. 3) Tighten checknuts and install lockwire, two places. 4) Ensure that thread engagement of rod end and vernier sleeve is within limits. 5) If thread engagement is not within limits: a) Remove rod end bolt. b) Loosen checknut and turn rod end at one-half turn increments to obtain approximate adjustment. c) Install rod end bolt and secure with washer and locknut. d) Repeat steps 1) through 4). (d) With rigging pin F-1 still installed, check that valve slide and indexing surface of leading edge flap control valve align within + 0.010 inch. 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 at one-half 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 as shown in view 1.
(e) Remove rigging pin F-1.
CAUTION: IF NOT REMOVED, RIGGING PIN F-1 MAY DAMAGE FLAP CONTROL UNIT WHEN HYDRAULIC POWER IS APPLIED.
(f) Provide hydraulic system A power. Refer to 27-51-0.
(g) Position flap control lever in 5-unit detent to extend flaps, then set lever in FLAP UP detent.
535 May 15/72 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 27-51-01 Page 511
CAUTION: MONITOR FLAP RETRACTION CLOSELY TO PREVENT DAMAGE DUE TO IMPROPERLY ADJUSTED OR DISCONNECTED COMPONENTS. NOTE: If asymmetry shutoff mechanism is not properly adjusted, the flaps may not operate. Manually positioning asymmetry shutoff valve will allow flap operation. (h) If flap drive system creeps, wait 2 minutes before removing hydraulic system A power. Refer to 27-51-0.
(i) Check that rigging pin F-1 fits freely in flap control unit. If rigging pin does not fit freely, adjust trailing edge cam link as follows: 1) Remove lockwire and loosen two checknuts. 2) Remove rigging pin F-1. 3) Provide hydraulic system A power. Refer to 27-51-0. 4) Adjust sleeve to align rigging pin holes for rigging pin F-1.
CAUTION: DO NOT INSTALL RIGGING PIN F-1 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. 5) Position flap control lever in 5-unit detent to extend flaps, then set lever in FLAP UP detent. 6) After 2-minute wait, remove hydraulic system A power. Refer to 27-51-0. 535 27-51-01 Page 512 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. Nov 15/79
7) Check that rigging pin F-1 fits freely. If not, repeat steps 2) thru 6). 8) Tighten checknuts and install lockwire, two places. 9) Ensure that thread engagement of rod end and sleeve is within limits.
(j) Remove rigging pin F-1.
(k) Provide hydraulic system A power (Ref 27-51-0).
(l) Operate flap control system by moving flap control lever from FLAP UP to FLAP DOWN (40-unit) position and back to UP. Pause at UP and DOWN positions to allow flap drive unit to respond. Repeat for at least two cycles.
(m) Position flap control lever in FLAP UP detent.
(n) After waiting 2 minutes, remove hydraulic system A power (Ref 27-51-0).
(o) Check that rigging pin F-1 fits freely in flap control unit. If rigging pin does not fit freely, repeat steps (i) thru (n).
(p) Install lower pan on flap control unit.
(5) Adjust flap transmissions. (a) With trailing edge flaps retracted to FLAP UP position per step 1.C.(1), check that each transmission is positioned so that angular clearance between stop on ball screw nut and upstop on screw yoke is 170 to 190 degrees (1/2 turn + 10 degrees) turn (Fig. 505).
NOTE: When you turn the flap drive torque tubes to get 1 turn of the inboard flap jackscrews, you will get a 1/2 turn of the outboard flap jackscrews. www.aero.cn 航空翻译 www.aviation.cn 本文链接地址：737 AMM 飞机维护手册 飞行操纵 FLIGHT CONTROLS 3
