• 热门标签

当前位置: 主页 > 航空资料 > 机务资料 >

时间:2011-03-27 12:43来源:蓝天飞行翻译 作者:航空
曝光台 注意防骗 网曝天猫店富美金盛家居专营店坑蒙拐骗欺诈消费者

R  A. Removal of the Flap Track Beam 
R  WARNING : SUPPORT THE UNIT/ASSEMBLY OR IT WILL FALL AND BECOME DAMAGED OR_______ 
R  INJURE PERSONNEL. THE UNIT/ASSEMBLY IS HEAVY. 
R  NOTE : The weight of the flap track beam (1) is 57 kg (125.6634 lb).____ 
R  (1) Hold the flap track beam (1). 
R  (2) At the forward mounting: 
R  (a) Remove the nut (25), the bolt (31) and disconnect the bonding 
R  strap (30). 
R  (b) From one side of the beam only, remove and discard the cotter pin 
R  (23). Remove the collar (22), the pin (18) and the anti-chafe 
R  collar (21). 
R  (c) Remove the failsafe pin (26) from the bracket (32) and the flap 
R  track beam (1). 
R  (d) Remove and discard the cotter pin (27). 
R  (e) Remove the nut (28), the washer (29) and the bolt (20). 
R  (f) Install the EXTRACTOR FLAP SPIGOT (98D57004096000) into the 
R  forward spigot pin (24). 
R  (g) Use the EXTRACTOR FLAP SPIGOT to remove the forward spigot pin 
R  (24) through the spherical bearing (19). 
R  (3) At the rear mounting: 
R  (a) Remove and discard the cotter pins (2) and (5). 
R  (b) Remove and discard the lockwire from the nuts (6) and the flanged 
R  nuts (7).

 

R (c) Remove the nuts (6) and the flanged nuts (7) from the studs (8).

R R  (d) Remove the nut (3) and the spherical washer (4) from the aft spigot pin (17). 
R  (4) Lower the rear end of the flap track beam (1). 
R  (5) Remove the flap track beam (1). 
R  **ON A/C ALL
 Subtask 57-51-33-020-056
 B. If you are to install a replacement flap track beam (1).
 (1) Remove and discard the cotter pins (16).
 (2) Remove the nuts (15), the washers (14) and the studs (8).
 (3) From one side at a time, remove the nuts (13), the bolts (9), the bearing pads (11) and the shims (12).
 NOTE : Keep the bearing pads (11) and the shims (12) together in____ different sets so that you can install them in the same position from which they were removed.

 

 TASK 57-51-33-400-003
 Installation of the No.3 Flap Track Beam
 WARNING : MAKE SURE THAT THE FLIGHT CONTROL SAFETY-LOCKS AND THE WARNING
_______
 NOTICES ARE IN POSITION.

 WARNING : MAKE SURE THAT THE GROUND SAFETY-LOCKS ARE IN POSITION ON THE LANDING
_______
 GEAR.

 CAUTION : BE CAREFUL WHEN YOU DO MAINTENANCE TASKS ON THE WING TRAILING EDGE:
_______
 -
DO NOT CAUSE DAMAGE TO THE ELECTRICAL CABLE RACEWAYS.

 -
DO NOT CAUSE DAMAGE TO THE ELECTRICAL CABLE INSTALLATIONS.


 -MAKE SURE THAT THE ELECTRICAL CABLES ARE INSTALLED CORRECTLY. INCORRECT INSTALLATION CAN CAUSE DAMAGE.
 1. Reason for the Job
__________________
 Self Explanatory
 2. Job Set-up Information
______________________
 A. Fixtures, Tools, Test and Support Equipment
 -------------------------------------------------------------------------------REFERENCE QTY DESIGNATION -------------------------------------------------------------------------------
No specific safety barriers
 No specific warning notices
 No specific access platform 4 m (13 ft. 1 in.)

R No specific Torque Wrench : range 0.00 to 1.20 m.daN R (0.00 to 9.00 lbf.ft) No specific Torque Wrench : range 0.20 to 3.60 m.daN
 (2.00 to 26.00 lbf.ft) No specific Torque Wrench : range 1.00 to 10.00 m.daN
 (8.00 to 75.00 lbf.ft) No specific Torque Wrench : range 2.00 to 20.00 m.daN
 (15.00 to 150.00 lbf.ft) 98D27803000000 1 LOCKING TOOL - FLAP/SLAT CONTROL LEVER 98D57004037000 1 EXTRACTOR FLAP SPIGOT B. Consumable Materials


 -------------------------------------------------------------------------------REFERENCE DESIGNATION -------------------------------------------------------------------------------
Material No. 05-002 Material No. 09-001 Material No. 09-018
Material No. 11-026 Material No. 19-003 Material No. 19-010
C. Expendable Parts
USA MIL-P-8116 PUTTY, ZINC CHROMATE GENERAL PURPOSE (Ref. 20-31-00)USA MIL-S-8802 TYPE I CLASS A FUEL TANK SEALANTPOLYSULFIDE (Ref. 20-31-00)USA AMS 3267/3 CORROSION INHIBITING LOW ADHESION SEALANT (Ref. 20-31-00)GB DEF-STAN 68-148/1 SOLVENT GENERAL PURPOSE (Ref. 20-31-00)USA AMS 3819 LINT-FREE COTTON CLOTH (Ref. 20-31-00)USA AMS 5687 LOCKWIRE STAINLESS STEEL ANNEALED 0.8MM DIA (Ref. 20-31-00)
 -------------------------------------------------------------------------------FIG.ITEM |DESIGNATION |IPC-CSN -------------------------------------------------------------------------------
 
中国航空网 www.aero.cn
航空翻译 www.aviation.cn
本文链接地址:A320飞机维护手册 AMM WINGS 机翼3(150)