(3)
Remove the universal joint (8).
1EFF : ALL 1 27-84-45Page 414 1 1 May 01/98R 1 1 1CES 1
TASK 27-84-45-400-003
Installation of the Torque Shaft 6006CM(6056CM)
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 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) 98D27504030001 2 LOCK-TORQUE SHAFT (FLAPS AND SLATS) WITH CLAMP-PIVOT
B. Consumable Materials
-------------------------------------------------------------------------------REFERENCE DESIGNATION -------------------------------------------------------------------------------
Material No. 04-018
GENERAL PURPOSE ASSEMBLY PASTE (Ref. 20-31-00)
Material No. 04-022 USA MIL-PRF-81322 GRADE 2
SYNTHE.HYDROCARBON GREASE HIGH PRESSURE
(Ref. 20-31-00)
Material No. 11-026 GB DEF-STAN 68-148/1 R SOLVENT GENERAL PURPOSE (Ref. 20-31-00)
Material No. 15-007 AIB TN 10138 TYPE II GRADE 1 CORROSION PREVENTIVE TEMPORARY PROTECTIVE COMPOUND (Ref. 20-31-00)
Material No. 19-003 USA AMS 3819
LINT-FREE COTTON CLOTH (Ref. 20-31-00)
C. Referenced Information
-------------------------------------------------------------------------------REFERENCE DESIGNATION -------------------------------------------------------------------------------
R 27-50-00-000-003 27-50-00-400-003 27-80-00-866-005 27-84-00-710-001 32-12-00-010-001 32-12-00-410-001 53-35-13-000-002 53-35-13-400-002 27-84-45-991-001 27-84-45-991-002 Removal of the Lock-Torque Shaft - Flaps and Slats (98D27504030001)Installation of the Lock-Torque Shaft - Flaps and Slats (98D27504030001)Retracting the Slats on the GroundOperational Test of the Slat SystemOpen the Main Gear Doors for AccessClose the Main Gear Doors after AccessRemoval of the Quick-Release Access Panels from the Belly Fairing StructureInstallation of the Quick-Release Access Panels on the Belly Fairing StructureFig. 401 Fig. 402
3. Job Set-up__________
(Ref. Fig. 401/TASK 27-84-45-991-001)
Subtask 27-84-45-941-059
A. Safety Precautions
(1) Make sure that the safety barriers are in position.
(2) Make sure that the warning notice is in position to tell persons not to operate the slat controls.
(3) Make sure that the warning notice is in position to tell persons not to operate the landing gear doors.
Subtask 27-84-45-860-052
B. Aircraft Maintenance Configuration
R (1) Make sure that the MLG doors are open (Ref. TASK 32-12-00-010-001).
R R (2) Make sure that the GROUND LOCK SLEEVE is on the applicable MLG door actuator.
(3) Make sure that the applicable access panel 191BB, 192FB is removed (Ref. TASK 53-35-13-000-002).
(4) Make sure that the slats are fully retracted (Ref. TASK 27-80-00-866-005).
(5) Make sure that the TOOL-ZERO LOCKING, FLAP SLAT CTL LEVER is installed on the flap/slat control lever on panel 114VU.
(6) Make sure that a LOCK-TORQUE SHAFT (FLAPS AND SLATS) WITH CLAMP-PIVOT is installed (Ref. TASK 27-50-00-400-003): - on the torque shaft, inboard of the removed component - on the torque shaft, outboard of the removed component.
Subtask 27-84-45-865-060
C. Make sure that this(these) circuit breaker(s) is(are) open, safetied and tagged
-------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION -------------------------------------------------------------------------------49VU FLIGHT CONTROLS/SLT/CTL AND MONG/SYS1 5CV B06 121VU FLIGHT CONTROLS/SLT/CTL/SYS2 7CV R21
4. Procedure_________
R R (Ref. Fig. 402/TASK 27-84-45-991-002)
Subtask 27-84-45-420-066
R A. Preparation for Installation
R R CAUTION : DO NOT APPLY MORE THAN ONE TYPE OF LUBRICANT._______ GREASE AND ASSEMBLY PASTE DO NOT MIX.
R R (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).
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7(130)
