(b)
Check that seal supports on aft lower wing panels have ful1 span contact with nose of each midflap.
(c)
If requirements in steps (a) and (b) are not met, adjust flap transmissions as follows:
1) If all transmissions on one wing require similar adjustment, disconnect torque tube from flap power unit. Rotate torque tube until transmission upstop and midflap seal support requirements are obtained.
535
Aug 01/94 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 27-51-01 Page 513
2) If individual transmissions require adjustment, disconnect torque tubes at both sides of each transmission to be adjusted. Rotate transmission input shaft until upstop and midflap seal support requirements are obtained.
(d) Connect torque tubes at all transmissions and at flap power unit.
NOTE: Ensure that position of transmissions and flap power unit are not disturbed as torque tubes are connected.
1) Secure torque tubes by installing screws through sleeve and coupling. 2) Lockwire heads of screws together.
(e)
Provide hydraulic system A power (Ref 27-51-0).
(f)
Operate trailing edge flaps 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 flaps to respond fully. Repeat for at least two cycles and check the following: 1) The ball screw nut upstop must stop in the range of 170 to 190 degrees (1/2
turn + 10 degrees) turns from contact at FLAP UP position. 2) The ball screw nut downstop must stop at least 1/4 turn from contact at FLAP DOWN (40-unit) position.
(g)
Extend flaps to FLAP DOWN (40-unit) position and check that angles of opposite midflaps are symmetrical within 1 degree. Measure along lower surface of midflap at midspan for inboard flaps, and at outboard flap track for outboard flaps using protractor. Lift outboard flap trailing edge so that main carriage flight load rollers contact flap track.
(h)
If angles of opposite flaps are not within limits, correct by disconnecting appropriate flap drive torque tubes and adjusting flap transmissions to obtain symmetry. Connect torque tubes, secure couplings and lockwire heads of torque tube coupling screws.
(i)
If flap transmissions are adjusted per step (h), check jackscrew and seal clearance per steps (a) and (b).
(j)
Retract trailing edge flaps to FLAP UP position, then remove hydraulic system A power (Ref 27-51-0).
535
27-51-01 Page 514 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. Nov 15/79
G12095
535 Flap Transmission Assembly Adjustment
May 15/72 Figure 505 27-51-01
Page 515
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
(6)
Adjust flap limit switches (Ref 27-51-291, Adjust Flap Limit Switches).
(7)
Adjust flap position transmitters (Ref 27-58-01, Adjust Trailing Edge Flap Position Indicating System).
(8)
Test trailing edge flap system.
2. Trailing Edge Flap System Test
A. Test Trailing Edge Flap System
(1) Test left asymmetry shutoff system.
(a)
Provide electrical power (Ref 24-22-0 MP).
(b)
Provide system A hydraulic power (Ref 27-51-0 MP).
(c)
Position flap control lever in FLAP UP (0-unit) detent.
(d)
After waiting 2 minutes, remove system A hydraulic power (Ref 27-51-0 MP).
(e)
Position flaps as follows (Fig. 505A): 1) At number 4 jackscrew, measure and record X dimension. 2) On AF F-GBYA thru F-GBYL; GJ B-2501 thru B-2503; IDO A17301 and
A17302; PI N761N thru N811N, reposition flaps electrically so that X dimension measured in step 1) is an additional 24.38 to 24.53 inches (15-unit position).
3) On AF ALL EXCEPT F-GBYA thru F-GBYL; GJ ALL EXCEPT B-2501 thru B-2503; IDO ALL EXCEPT A17301 and A17302; PI ALL EXCEPT N761N thru N811N, reposition flaps electrically so that X dimension measured in step 1) is an additional 25.52 to 25.68 inches (25-unit position).
(f)
Remove four transmitter mounting bolts and remove left flap position transmitter.
(g)
Rotate flap position transmitter input shaft clockwise until flap bypass valve red indicator lever point moves to position\2.
(h)
Check that angle of separation between flap position indicator needles is between 8 to 20 degrees (chordal dimension of 0.08 to 0.21 inch Fig. 506).
(i)
Rotate flap position transmitter input shaft counterclockwise until flap bypass valve red indicator lever point moves to position 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(2)
