(5)
At the Nos. 5 and 6 slat tracks:
(a)
Remove and discard the cotter pins (23) from the nuts (32), (47),
(55)
and (56).
(b)
Loosen the nuts (32), (47), (55) and (56), but do not remove them.
(c)
Remove and discard the cotter pins (23) from the nuts (22), (24),
(49)
and (51).
(d)
Remove the items that follow:
-
the nuts (22), (24), (49) and (51)
-
the washers (21), (25), (48) and (50)
-
the bolts (27), (30), (41) and (42)
-
the bush (26).
NOTE : The bush (26) is a part of the slat track and the slat
____
track linkage assembly.
(6) Lift the slat (30 kg (66.1386 lb)) from the slat tracks.
(7) Move the slat with the hoist and lower it onto the support structure. **ON A/C ALL
Subtask 27-84-64-942-050
B. Removal of Equipment
(1) If you are to install a new slat, remove the SLING-SLATS (Ref. TASK 27-80-00-000-001).
R 1EFF : ALL 1 27-84-64Page 411 1 1 May 01/04 1 1 1CES 1
INTENTIONALLY BLANK
R 1 1
27-84-64Page 412
1 1 May 01/04 1 1 1CES 1 TASK 27-84-64-400-002
Installation of the No. 2 Slat
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.
1. Reason for the Job__________________
Self Explanatory
2. Job Set-up Information______________________
A. Fixtures, Tools, Test and Support Equipment
-------------------------------------------------------------------------------
REFERENCE QTY DESIGNATION
-------------------------------------------------------------------------------
No specific adjustable access platform No specific pneumatic wrench No specific safety barriers No specific warning notice No specific Torque Wrench : range 0.20 to 3.60 m.daN
(2.00 to 26.00 lbf.ft) 98D27804001000 1 ADAPTOR-DRIVE, SLAT (AND FLAP) 98D27804009001 1 SLING-SLATS 98D27804011000 1 BAR-TURNING 98D27804020000 1 BLOCK-SLAT GAPPING
1EFF : ALL 1 27-84-64Page 413 1 1 Nov 01/03R 1 1 1CES 1
B. Consumable Materials
-------------------------------------------------------------------------------
REFERENCE DESIGNATION
-------------------------------------------------------------------------------
No specific lockwire, corrosion resistant steel 0.8 mm (0.032 in) dia Material No. 09-001 USA MIL-S-8802 TYPE I CLASS A FUEL TANK SEALANTPOLYSULFIDE (Ref. 20-31-00)
Material No. 09-016 USA MIL-PRF-81733D TYPE II CLASS B
CORROSION INHIBITING FILLET CONSISTENCY
(Ref. 20-31-00)
Material No. 11-026 GB DEF-STAN 68-148/1
SOLVENT GENERAL PURPOSE (Ref. 20-31-00)
Material No. 19-003 USA AMS 3819
LINT-FREE COTTON CLOTH (Ref. 20-31-00)
Material No. 19-010 USA AMS 5687
LOCKWIRE STAINLESS STEEL ANNEALED 0.8MM DIA
(Ref. 20-31-00)
C. Expendable Parts
-------------------------------------------------------------------------------
FIG.ITEM |DESIGNATION |IPC-CSN
-------------------------------------------------------------------------------
23 cotter pins 27-84-05 42A-077
23 cotter pins 27-84-05 42T-077
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)-
R 24-42-00-861-001 Energize the Ground Service Network from the External
R Power
R 24-42-00-862-001 De-energize the Ground Service Network Supplied from
R the External Power 27-50-00-000-003 Removal of the Lock-Torque Shaft - Flaps and Slats (98D27504030001) 27-50-00-400-003 Installation of the Lock-Torque Shaft - Flaps and Slats (98D27504030001)
-------------------------------------------------------------------------------
REFERENCE DESIGNATION
-------------------------------------------------------------------------------
27-80-00-000-001 Removal of the Hoisting Sling 27-80-00-200-002 Check of the Permitted Aerodynamic Tolerances between
the Slats 1 thru 5 27-80-00-400-001 Installation of the Hoisting Sling 27-80-00-866-004 Extending the Slats on the Ground 27-84-00-710-001 Operational Test of the Slat System 27-84-45-000-004 Removal of the Torque Shaft 6010CM(6060CM) 27-84-45-400-005 Installation of the Torque Shaft 6010CM(6060CM) 27-84-69-000-001 Removal of the Closing Plates for the Slat Tracks 1
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 FLIGHT CONTROLS 飞行操纵8(127)
