4. Procedure
_________
(Ref. Fig. 402/TASK 27-84-44-991-002) Subtask 27-84-44-020-053
A. Removal of the Steady Bearing FIN 6023CM (6073CM)
(1) Remove the bolts (27), then remove the steady bearing (30) from the torque shaft (29) and the steady bearing bracket (28).
TASK 27-84-44-400-004
Installation of the Steady Bearing FIN 6023CM(6073CM)
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
B. Consumable Materials
-------------------------------------------------------------------------------REFERENCE DESIGNATION -------------------------------------------------------------------------------
Material No. 09-018 USA AMS 3267/3 CORROSION INHIBITING LOW ADHESION SEALANT (Ref. 20-31-00)
Material No. 09-019 USA AMS 3267/3 LOW ADHESION CORROSION INHIBITING SEALANT (Ref. 20-31-00)
Material No. 11-004 USA MIL-T-81533 1.1.1TRICHLOROETHANE (METHYL CHLOROFORM) (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 -------------------------------------------------------------------------------
27-50-00-400-003 Installation of the Lock-Torque Shaft - Flaps and
Slats (98D27504030001) 27-84-00-710-001 Operational Test of the Slat System 27-84-45-400-010 Installation of the Torque Shafts 6022CM(6072CM)
3. Job Set-up
__________ Subtask 27-84-44-941-065
A. Safety Precautions
(1)
Make sure that the safety barriers are in position.
(2)
Make sure that the warning notice is in the cockpit to tell persons not to operate the slat controls.
(3)
Make sure that the TOOL-ZERO LOCKING, FLAP SLAT CTL LEVER is on the flap/slat control lever.
Subtask 27-84-44-860-053
B. Aircraft Maintenance Configuration
(1)
Make sure that the access platform is in position below the applicable zone 521 (621).
(2)
Make sure that the applicable access panel 521AT (621AT) is removed.
(3)
Make sure that a LOCK-TORQUE SHAFT (FLAPS AND SLATS) WITH CLAMP-PIVOT is installed (Ref. TASK 27-50-00-400-003) as follows: - on the torque shaft, inboard of the applicable component - on the torque shaft, outboard of the applicable component.
Subtask 27-84-44-865-053
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
_________
Subtask 27-84-44-420-063
A. Preparation for Installation
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)
Use a MISCELLANEOUS (Material No. 19-003) made moist with CLEANING AGENTS (Material No. 11-004) to clean the component interface and/or the adjacent area.
(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.
(4)
Apply a layer of SEALANTS (Material No. 09-018) or SEALANTS (Material No. 09-019) to:
-
the mating faces of the steady bearing (30) and the steady bearing bracket (28)
-
the shanks of the bolts (27).
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本文鏈接地址：A320飛機(jī)維護(hù)手冊 AMM FLIGHT CONTROLS 飛行操縱7(121)
