S 864-009
(10)
Supply electrical power (AMM 24-22-00/201).
S 864-010
(11)
Push the ALTN FLAPS ARM switch to put the flaps in alternate control.
S 864-011
CAUTION: REMOVE THE TWO AFT ROLLER SUPPORTS AND ATTACH THE GENEVA CAMS
_______ TO THE FLAP CARRIAGES BEFORE YOU MOVE THE FLAPS. YOU CAN CAUSE DAMAGE TO THE FLAPS.
(12) Turn the ALTN FLAPS switch to EXT position to electrically extend the flaps.
NOTE: The flaps will extend to the 25-unit position.
____
S 864-012
(13) Disconnect electrical power if it is not necessary (AMM 24-22-00/201).
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú
27-51-01
ALL ú ú 01 Page 408 ú Oct 18/00
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
747-400 MAINTENANCE MANUAL
S 014-013
(14)
Remove the movable inboard flap track fairings (AMM 27-51-26/401).
S 034-014
(15)
Remove the fixed and movable links for the flap track fairing from the aft end of the flap track (AMM 27-51-44/401).
S 034-015
(16)
Remove the inboard foreflap (AMM 27-51-02/401).
S 494-016
(17)
Make sure that the three midflap tracks will not move into the midflap.
F.
Remove the inboard flaps.
S 944-017
(1) Measure and write down the distance between the ballscrew nut and the ballscrew downstop on each track (dimension Y, Fig. 401).
NOTE: This will make it easier to adjust the flap when it is
____
installed.
S 494-018
CAUTION: DO NOT PERMIT THE ANGLE BETWEEN THE CENTERLINES OF THE
_______ TRANSMISSION AND THE BALL SCREW TO BE MORE THAN 10 DEGREES. THE TRANSMISSION UNIVERSAL JOINT CAN BE DAMAGED.
(2)
Install the ball and screw support tool on each track.
S 494-019
(3)
Attach the strongback to the midflap (Fig. 402).
G.
Do these steps to attach the spreader bar and the load positioner to the strongbacks (Fig. 402).
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú
27-51-01
ALL ú ú 01 Page 409 ú Feb 18/01
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
747-400 MAINTENANCE MANUAL
OVERHEAD CRANE
LOAD POSITIONER
ADJUSTABLE LENGTH
SLING COUNTERWEIGHT SEE C
SPREADER BAR (10OHME65B00116)
STRONGBACK
(2 LOCATIONS)
(11ME65B00116)
MIDFLAP
SEE B
SEEA SEEA TURNBUCKLE (2 LOCATIONS) (12ME65B00116)
CLIP (2 LOCATIONS)
AFTFLAP
C FLAP TRACK C FLAP TRACK
L L
STRONGBACK
STRONGBACK ATTACH BOLT (2 LOCATIONS)
A
WINGNUT
SLIDE CABLE WITH COLLAR TO OBTAIN
CLIP "A" DIM FOR EACH LIFTING CONDITION
TURNBUCKLE
MIDFLAP BOLT -A-
-A-LIFTING CONDITION
INBOARD
OUTBD UPPER
A 31 3/4 31 3/4 FORE FLAP
SKIN PANEL
21 1/4 20 MID FLAP CAR. & BOG.
MID & AFT FLAP 18
18
CARRIAGE & BOGGIE
16 14
AFT FLAP
TOOL MOUNTING UPPER SKIN ATTACHING SCREW - SIZE 10-32
SCREW - SIZE 1/4-28 C (TYPICAL)
(TYPICAL)
B
Inboard Flap Installation Tools Figure 402
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú
27-51-01
ALL ú ú 02 Page 410 ú Feb 18/00
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
747-400
MAINTENANCE MANUAL
S 484-075
WARNING:_______ MAKE SURE THE SPREADER BAR IS ATTACHED TO THE HOLES MARKED
"INSTL- REMOVAL POSITION" ON THE STRONGBACK. THE FLAP WILL
MOVE QUICKLY WHEN IT IS OFF THE TRACK. YOU CAN CAUSE INJURY TO
PERSONNEL OR DAMAGE TO EQUIPMENT. 中国航空网 www.aero.cn 航空翻译 www.aviation.cn 本文链接地址：747-400 AMM 飞机维护手册 飞行操纵 FLIGHT CONTROLS 4(68)
