-
FOR 6025CM
remove the torque shaft FIN 6026CM
-
FOR 6075CM
remove the torque shaft FIN 6076CM.
(5)
Make sure that the LOCK-TORQUE SHAFT (FLAPS AND SLATS) WITH CLAMP-PIVOT (98D27504030001) is on the applicable torque shaft (Ref. TASK 27-50-00-400-003).
4. Procedure
_________
(Ref. Fig. 402/TASK 27-84-44-991-002) Subtask 27-84-44-020-054
A. Removal of the Steady Bearing FIN 6025CM (6075CM)
(1) Remove the bolts (33), then remove the anti-flailing cap (32) and the steady bearing (35) from the nose rib (36).
TASK 27-84-44-400-005
Installation of the Steady Bearing FIN 6025CM(6075CM)
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 27-84-45-000-007 Removal of the Torque Shafts
6016CM(6066CM)/6020CM(6070CM)/6026CM(6076CM)/
6030CM(6080CM) 27-84-45-000-010 Removal of the Torque Shafts 6024CM(6074CM) 27-84-45-400-011 Installation of the Torque Shafts 6024CM(6074CM) FOR FIN 6075CM 27-84-45-400-008 Installation of the Torque Shafts
6016CM(6066CM)/6020CM(6070CM)/6026CM (6076CM)/6030CM(6080CM)
3. Job Set-up
__________
Subtask 27-84-44-941-066
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 27-84-44-860-054
B. Aircraft Maintenance Configuration
(1)
Make sure that the adjustable access platform is below the applicable access panel.
(2)
Make sure that the applicable access panel is removed 521EB, 522AB, 522CB (621EB, 622AB, 622CB).
(3)
Make sure that the applicable torque shaft (37) has been removed (Ref. TASK 27-84-45-000-010):
-
FOR 6025CM
remove the torque shaft FIN 6024CM
-
FOR 6075CM
remove the torque shaft 6074CM.
(4)
Make sure that the applicable torque shaft (34) has been removed (Ref. TASK 27-84-45-000-007):
-
FOR 6025CM
remove the torque shaft FIN 6026CM
-
FOR 6075CM
remove the torque shaft 6076CM.
(5)
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 removed component - on the torque shaft outboard of the removed component.
Subtask 27-84-44-865-054
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
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