-------------------------------------------------------------------------------REFERENCE DESIGNATION -------------------------------------------------------------------------------
Material No. 11-004 USA MIL-T-81533
 1.1.1TRICHLOROETHANE (METHYL CHLOROFORM)
 (Ref. 20-31-00) Material No. 19-003 USA AMS 3819
 LINT-FREE COTTON CLOTH (Ref. 20-31-00)
 C. Expendable Parts
 -------------------------------------------------------------------------------FIG.ITEM |DESIGNATION |IPC-CSN -------------------------------------------------------------------------------
6 cotter pin 57-55-05 04 -020 6 cotter pin 57-55-05 06 -020
 D. Referenced Information
 -------------------------------------------------------------------------------REFERENCE DESIGNATION -------------------------------------------------------------------------------
20-28-00-912-004 Electrical Bonding of Components With Conductive
 Bolts and Screws and Bonding Straps in the Fuselage
 and in the Wings (this does not include the tanks)-27-50-00-866-009 Retraction of the Flaps on the Ground 27-54-00-710-001 Operational Test of the Flap System 57-55-11-400-001 Installation of the Flap Track Fairings Nos. 2, 3 and
 4 57-55-11-991-005 Fig. 407
 3. Job Set-up
__________
 (Ref. Fig. 407/TASK 57-55-11-991-005)
 Subtask 57-55-11-941-063
 A. Safety Precautions
 (1)
 Make sure that the warning notices are in position in the cockpit to tell persons not to operate the flaps or slats.

 (2)
 Make sure that the safety barriers are in position.

 1EFF : ALL 1 57-55-11Page 443 1 1 May 01/04R 1 1 1CES 1

 Subtask 57-55-11-860-066

 B. Aircraft Maintenance Configuration
 (1)
 Make sure that the flaps are fully retracted (Ref. TASK 27-50-00-866-009).

 (2)
 Make sure that the TOOL-ZERO LOCKING, FLAP SLAT CTL LEVER is installed on the slat/flap control-lever.

 (3)
 Make sure that the access platform is in position below the applicable flap track 3 or 4, zone 532 (632) or 533 (633).

 Subtask 57-55-11-865-072
 C. Make sure that this(these) circuit breaker(s) is(are) open, safetied and tagged
 -------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION -------------------------------------------------------------------------------49VU FLIGHT CONTROLS/FLP/CTL AND MONG/SYS1 6CV B07 121VU FLIGHT CONTROLS/FLP/CTL AND/MONG/SYS2 8CV Q21
 4. Procedure
_________
 (Ref. Fig. 407/TASK 57-55-11-991-005)
 Subtask 57-55-11-410-054
 A. Lifting the Movable Fairing
 WARNING : USE SOLVENTS/CLEANING AGENTS, SEALANTS AND OTHER SPECIAL
_______ MATERIALS ONLY WITH A GOOD SUPPLY OF AIR. OBEY THE MANUFACTURERS INSTRUCTIONS. PUT ON PROTECTIVE CLOTHING. DO NOT GET THEM IN YOUR MOUTH. DO NOT SMOKE. DO NOT BREATHE THE GAS. THESE MATERIALS ARE POISONOUS, FLAMMABLE AND SKIN IRRITANT. GET MEDICAL HELP IF YOUR SKIN OR EYES BECOME IRRITATED.
 (1)
 Make sure that the parts retained from the removed component are clean and in the correct condition.

 (2)
 Lift the flap fairing:

 WARNING : SUPPORT THE UNIT/ASSEMBLY OR IT WILL FALL AND BECOME
_______ DAMAGED OR INJURE PERSONNEL. THE UNIT/ASSEMBLY IS HEAVY.
 NOTE : The weight of the flap fairings is approximately 18kg (40lb).
____
 (a)
 Move the movable fairing to align the control rod (7) with the flap drive lever.

 (b)
 Temporarily install the control rod (7) with the bolt (11), the sliding bush (5), the washer (4) and the nut (3).

 (3)
 Temporarily install the top cover (1) with some of the screws (2).

 (4)
 Make sure that:

 -
the flap track No. 3 movable fairing is correctly adjusted (Ref. TASK 57-55-11-400-001)

 -
the flap track No. 4 movable fairing is correctly adjusted (Ref. TASK 57-55-11-400-001).

 (5)
 Remove the screws (2) and the top cover (1).

 (6)
 Hold the movable fairing and remove the nut (3), the washer (4), the sliding bush (5) and the bolt (11).

 (7)
 Use a MISCELLANEOUS (Material No. 19-003), made moist with CLEANING AGENTS (Material No. 11-004) to clean the interfaces of:

 -
the bolt (11) and the sliding bush (5)

 -
the flap drive lever and the control rod (7).

 (8)
 Apply a thin layer of SEALANTS (Material No. 09-018) or SEALANTS (Material No. 09-019) to the interfaces of the sliding bush (5) and the bolt (11), but not to the threads.
　
中國航空網(wǎng) www.k6050.com
航空翻譯 www.aviation.cn
本文鏈接地址：A320飛機(jī)維護(hù)手冊 AMM WINGS 機(jī)翼5(63)