32-12-00
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A
747-400
MAINTENANCE MANUAL
WARNING: MAKE SURE THAT ALL PERSONS AND EQUIPMENT ARE CLEAR OF
_______ THE DOOR OPERATION PATHS. DO NOT MOVE THE DOORS TOO QUICKLY. IT CAN CAUSE INJURY TO PERSONS OR DAMAGE TO EQUIPMENT.
2) Operate the release handles to the close position for the wheel well doors of the wing and body landing gears. 3) Remove the pressure from hydraulic systems No. 1 and 4 (AMM 29-11-00/201). 4) Make sure the inboard and outboard doors of the wheel well for the wing landing gears are closed and locked. 5) If the door falls open, remove the packing and adjust the door again. 6) After you install the packing again, do a last check with the airplane hydraulic power. 7) Remove the packing from the face of the door stop.
S 865-070
(9)
Make sure that you do not pressurize hydraulic systems No. 1 and 4 (AMM 29-11-00/201).
S 225-071
(10)
Make sure that switch clearance for the wing landing gear is in the limits (AMM 32-61-32/201).
NOTE: Do not stand on the door or apply force to the door
____
while you get this dimension.
L. Adjust The Outboard Door For The Shock Strut (Fig. 506).
NOTE: You must adjust the outboard door before you install the
____
inboard door of the shock strut if it was removed.
S 825-202
(1) Table 503 (for Fig. 506) shows expanded tolerances which were permitted at delivery. Use these tolerances only if you cannot get the usual tolerances.
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747-400
MAINTENANCE MANUAL
DOOR OUTBOARD WING GEAR SHOCK STRUT SEE A
SEE B
LINKAGE ROD OUTBOARD DOOR OUTBOARD DOOR SHOCK STRUT WING GEAR SHOCK STRUT WING GEAR SEE C DOOR FAIRING SHOCK STRUT WING GEAR INBOARD DOOR SHOCK STRUT
INBD FWD FWD
A
DRAG STRUT WING GEAR
ROD LINKAGE DOOR INBOARD DOOR SHOCK STRUT WING GEAR NUT LINKAGE ROD
SEE C
FWD
INBOARD DOOR SHOCK STRUT WING GEAR B INBD C
Wing Gear Shock Strut Door Adjustment
Figure 506 (Sheet 1)
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747-400
MAINTENANCE MANUAL
Wing Gear Shock Strut Door Adjustment
Figure 506 (Sheet 2)
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747-400 MAINTENANCE MANUAL
WING GEAR SHOCK STRUT OUTBOARD DOOR
D-D
LOCATION CLEARANCE
POINT A 0.63 +0.10/-0.33 INCH (16.00 +2.54/-8.38 mm)
POINT B 0.63 +0.10/-0.28 INCH (16.00 +2.54/-7.11 mm)
POINT C 0.75 +0.10/-0.45 INCH (16.00 +2.54/-11.43 mm)
POINT D 0.75 +0.10/-0.35 INCH (16.00 +2.54/-8.89 mm)
GAPS LESS THAN 0.50 INCH
(12.7 mm) MAY RESULT IN DAMAGE TO THE BODY STRUCTURE.
TABLE
Wing Gear Shock Strut Door Adjustment
Figure 506 (Sheet 3)
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú 中國航空網 www.k6050.com 航空翻譯 www.aviation.cn 本文鏈接地址：747-400 AMM 飛機維護手冊 起落架 LANDING GEAR 2(84)
