(c)
LE flaps No. 3 and 4
(d)
LE flaps No. 4 and 5
(e)
LE flaps No. 22 and 23
(f)
LE flaps No. 23 and 24
(g)
LE flaps No. 25 and 26
(h)
Or LE flaps No. 26 and 26E.
S 035-086
(8)
Loosen the mounting bolts on the rotary actuator.
S 035-021
(9)
Move axially until you can disengage the connected drive shaft spline with the actuator output spline remaining engaged (Ref 27-81-07/401).
S 835-022
CAUTION:_______MAKE SURE TO ADJUST THE LINKAGE ACCURATELY. THE LE FLAP POWER DRIVE UNIT WILL NOT OPERATE CORRECTLY IF THE LINKAGE ADJUSTMENT IS NOT ACCURATE.
(10) Manually turn the input shaft of the rotary actuator until the dimension X (Fig. 505) is not larger than the given values.
NOTE: The rigging bar measures the flap linkage extension.
____
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747-400
MAINTENANCE MANUAL
~.......................................................... | | DIMENSION X | DIMENSION Y | | FLAP NO. | (| 0.03 Inch) | (| 0.03 Inch) | ............................................................ | 1E AND 26E | 30.89 | 30.80 | | (OUTBD LINKS) | | | ............................................................ | 1E AND 26E | 30.87 | 30.78 | | (INBOARD LINKS) | | | ............................................................ | 1 AND 26 | 30.87 | 30.78 | ............................................................ | 2, 3, 24, 25 | 30.88 | 30.79 | ............................................................ | 4, 5, 22, 23 | 30.89 | 30.80 | ............................................................ | 6 AND 21 | 35.71 | 35.62 | ............................................................ | 7 AND 20 | 35.71 | 35.62 | | (OUTBD LINKS) | | | ............................................................ | 7 AND 20 | 35.73 | 35.64 | | (INBD LINKS) | | | ............................................................ | 8 AND 19 | 35.73 | 35.64 | ............................................................ | 9 AND 18 | | | | (OUTBD LINKS) | 35.76 | 35.67 | ............................................................ | 9 AND 18 | | | | (INBD LINKS) | 35.79 | 35.70 | ............................................................ | 10 AND 17 | | | | (OUTBD LINKS) | 35.82 | 35.73 | ............................................................ | 10 AND 17 | | | | (INBD LINKS) | 35.88 | 35.79 | 2.................…......................….................1
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú
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ALL ú ú 01 Page 522 ú Oct 18/01
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
747-400 MAINTENANCE MANUAL
S 645-023
(11)
Apply a thin layer of grease on the drive shaft and the rotary actuator splines.
S 435-024
(12)
If it is necessary, move the actuator in and at the same time turn the input shaft to engage the nearest drive shaft spline.
NOTE: The input shaft must not turn more than 10 degrees in each
____
direction.
S 435-079
(13)
Install the actuator with eight bolts.
S 835-025
(14)
Align the drive shafts then install two screws.
S 435-081
(15)
Install the lockwire.
S 035-026
(16)
Remove the stop access screws.
S 435-091
(17)
Turn the flap retract stop in fully.
S 095-027
WARNING: MAKE SURE TO REMOVE THE SAFETY LOCKS AS SPECIFIED IN THE
_______ PROCEDURE BELOW. FAST MOVEMENT OF THE LE FLAPS CAN CAUSE INJURY TO PERSONS OR DAMAGE TO EQUIPMENT IF YOU DO NOT REMOVE THE LOCKS CORRECTLY.
(18) Remove the safety locks on all the flaps (Ref 27-81-00/201).
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本文鏈接地址：747-400 AMM 飛機(jī)維護(hù)手冊(cè) 飛行操縱 FLIGHT CONTROLS 7(65)
