NOTE: Rigging pin is a part of kit F70207-61 or -84.
(2)
Tensiometer - 0 to 100-pound capacity
(3)
Flap Drive Adapter - F70300-1
(4)
Grease - MIL-G-23827 (Ref 20-30-21)
(5)
Wrench Set - F80197-5 (Preferred) or F80197-1 (Optional)
B. Adjust Flap Control Unit
(1) Adjust flap follow-up cables WFFA and WFFB.
(a) Check that index mark on drum and matching mark on flap power unit housing align within + 0.03 inch (Fig. 501). If index marks do not align, proceed as follows: 1) Remove screws, attaching both torque tube coupling sleeves to splines on flap
power unit and slide sleeves off splines to disconnect torque tubes. 2) Use flap drive adapter to rotate flap power unit output shaft so that mark on drum and matching mark on housing align within + 0.03 inch.
NOTE: Positioning flap bypass valve to BYPASS (Position 2) will allow rotation of flap power unit.
3) Connect flap drive torque tube on each side of flap power unit. Install screws through sleeve and coupling. Lockwire heads of screws together.
NOTE: If flap transmission adjustment is to be checked, it is not necessary to connect torque tubes at this time. Torque tubes will be connected during check of transmission adjustment.
(b)
Check that rigging pin F-1 fits freely in flap control unit (Fig. 502).
(c)
Adjust follow-up cables WFFA and WFFB to tension specified in temperature-tension chart in Fig. 501. Balance load on cables so that rig pin F-1 fits freely.
587
May 01/99 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 27-51-201 Page 501
G24314
Flap Power Unit Adjustment 505
27-51-201 Figure 501 Nov 15/77
Page 502
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
(d)
Install turnbuckle locking clips.
(e)
Remove rigging pin F-1.
(2) Adjust flap control valves.
(a)
Ensure that flap control lever is in FLAP UP detent.
(b)
Install rigging pin F-1 in flap control unit.
(c)
Check that valve slide and indexing surface of trailing edge flap control valve align within + 0.010-inch. (See figure 502, 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 in 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) 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 in one-half turn increments to obtain adjustment.
500
Nov 15/67 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 27-51-201 Page 503
G24380G24382
Trailing Edge Flap Control Valve Installation 535
27-51-201 Figure 502 (Sheet 1) Feb 15/73
Page 504
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
500 Flap Control Unit Adjustment
Feb 15/73 Figure 502 (Sheet 2) 27-51-201
Page 505
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
4) Install rod end bolt with washer and locknut.
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)
Pressurize hydraulic system A (Ref 27-51-0, Trailing Edge Flaps - Maintenance Practices).
(g)
Position flap control lever in 5-unit detent to extend flaps, then set lever in FLAP UP detent.
(h)
After 2 minute wait, depressurize hydraulic system A (Ref 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 system A hydraulic power (Ref 27-51-0). 4) Adjust sleeve to align rigging pin holes for rigging pin F-1.
中国航空网 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(58)
