Material No. 09-019  USA AMS 3267/3 LOW ADHESION CORROSION INHIBITING SEALANT
 Material No. 11-026 Material No. 19-003  (Ref. 20-31-00)GB DEF-STAN 68-148/1 SOLVENT GENERAL PURPOSE (Ref. 20-31-00)USA AMS 3819
 Material No. 19-010  LINT-FREE COTTON CLOTH (Ref. 20-31-00)USA AMS 5687
 LOCKWIRE STAINLESS STEEL ANNEALED 0.8MM DIA
 (Ref. 20-31-00)
 C. Expendable Parts

 -------------------------------------------------------------------------------
FIG.ITEM --------- |DESIGNATION ------------------------------------ |IPC-CSN----------------------------------
14  cotter pin  57-55-05 01 -060
 14  cotter pin  57-55-05 01H-060
 28  cotter pin  57-55-05 02 -020
 50  cotter pin  57-55-05 04 -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
 57-55-11-200-001  Check of the Flap Track Fairing Lateral Movement
 57-55-11-991-023  Fig. 401
 57-55-11-991-001  Fig. 402
 57-55-11-991-002  Fig. 403
 57-55-11-991-003  Fig. 404
 57-55-11-991-004  Fig. 405 

R 1EFF : 001-049, 051-099, 101-149, 151-199, 1 57-55-11Page 411 1201-299, 401-499, 1Aug 01/05 1 1 1CES 1

 3. Job Set-up
__________ Subtask 57-55-11-941-056
 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. Subtask 57-55-11-860-054
 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 on the flap/slat control-lever.

 (3)
 Make sure that the adjustable access platform is in position below the applicable fairing at flap track 2, 3 or 4, zone 531(631), 532(632) or 533(633).

 Subtask 57-55-11-865-053
 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
R 1EFF : 001-049, 051-099, 101-149, 151-199, 1 57-55-11Page 412 1201-299, 401-499, 1Aug 01/05 1 1 1CES 1

 4. Procedure
_________
 (Ref. Fig. 401/TASK 57-55-11-991-023, 402/TASK 57-55-11-991-001, 403/TASK
 57-55-11-991-002, 404/TASK 57-55-11-991-003, 405/TASK 57-55-11-991-004) Subtask 57-55-11-420-072
 A. Preparation for Installation
 (1)
 Clean the component interface and/or the adjacent area with a MISCELLANEOUS (Material No. 19-003), made moist with CLEANING AGENTS (Material No. 11-026).

 (2)
 Do an inspection of the component interface and/or the adjacent area.

 (3)
 Make sure that the parts retained from the removed component are clean and in the correct condition.

 Subtask 57-55-11-420-050-A
 B. Installation of the Flap Track Fairings
 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) Install the applicable movable fairing as follows: 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 fairing is approximately 18 kg (39.6831 lb).
____
 (a)
 Install the adjusters (42) and make sure that they are adjusted fully into their mountings.

 (b)
 Align the movable fairing at the forward pivot, then install the splined fittings (43).

R 1EFF : 001-049, 051-099, 101-149, 151-199, 1 57-55-11Page 413 1201-299, 401-499, 1Aug 01/05 1 1 1CES 1
　
中國航空網 www.k6050.com
航空翻譯 www.aviation.cn
本文鏈接地址：A320飛機維護手冊 AMM WINGS 機翼5(54)