(7) If you will install the same rudder trim actuator (3), do the subsequent steps:
(a)
Make sure that the mobile red index is in the zero position on the position indicator of the rudder trim actuator. (Ref. Fig. 405/TASK 27-22-51-991-007)
(b)
Cut, remove and discard the lockwire from the plug in the rigging hole of the rudder trim actuator (3).
(c)
Remove the plug from the rigging hole of the rudder trim actuator (3).
(d)
Install the PIN - LOCKING (6137-060) (19) in the rigging hole of the rudder trim actuator (3).
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R Position Indicator of the Rudder Trim Actuator - PN 6137-4/6137-5 Figure 405/TASK 27-22-51-991-007
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Installation of the Rudder Trim Actuator (10CC)
WARNING : PUT THE SAFETY DEVICES AND THE WARNING NOTICES IN POSITION BEFORE YOU
_______
START A TASK ON OR NEAR:
-
THE FLIGHT CONTROLS
-
THE FLIGHT CONTROL SURFACES
-
THE LANDING GEAR AND THE RELATED DOORS
-COMPONENTS THAT MOVE.
WARNING : MAKE SURE THAT THE TRAVEL RANGES OF THE FLIGHT CONTROL SURFACES ARE
_______
CLEAR BEFORE YOU PRESSURIZE/DEPRESSURIZE A HYDRAULIC SYSTEM.
WARNING : PRESSURIZE ONLY THE HYDRAULIC SYSTEM(S) THAT IS (ARE) NECESSARY FOR
_______ THE TASK. ISOLATE THE OTHER HYDRAULIC SYSTEM(S) BEFORE YOU SUPPLY HYDRAULIC POWER TO THE AIRCRAFT.
1. Reason for the Job
__________________
Self Explanatory
2. Job Set-up Information
______________________
A. Fixtures, Tools, Test and Support Equipment
-------------------------------------------------------------------------------REFERENCE QTY DESIGNATION -------------------------------------------------------------------------------
No specific 2 ACCESS PLATFORM 6M (20 FT) - ADJUSTABLE
No specific 2 WARNING NOTICE R No specific Torque Wrench : range 0.00 to 1.20 m.daN R (0.00 to 9.00 lbf.ft)
No specific Torque Wrench : range 0.20 to 3.60 m.daN
(2.00 to 26.00 lbf.ft) 6137-013 1 PIN - LOCKING 6137-060 1 PIN - LOCKING 98D27207546000 1 PIN - RIGGING 98D27207547000 1 PIN - RIGGING 98D27207548000 1 PIN - RIGGING B. Consumable Materials
-------------------------------------------------------------------------------REFERENCE DESIGNATION -------------------------------------------------------------------------------
Material No. 04-004 USA MIL-PRF-23827 TYPE I
SYNTH.ESTER BASED GREASE HIGH PRESSURE
Material No. 05-002 (Ref. 20-31-00)USA MIL-P-8116
Material No. 19-010 PUTTY, ZINC CHROMATE GENERAL PURPOSE (Ref. 20-31-00)USA AMS 5687
LOCKWIRE STAINLESS STEEL ANNEALED 0.8MM DIA
(Ref. 20-31-00)
C. Referenced Information
-------------------------------------------------------------------------------REFERENCE DESIGNATION -------------------------------------------------------------------------------
20-28-00-912-004 22-96-00-710-001 22-97-00-710-001 24-41-00-862-002 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)-Operational Test of the AFSOperational Test of the LAND CAT III CapabilityDe-energize the Aircraft Electrical Circuits Supplied from the External Power
27-21-00-840-001 Removal/Installation of the control rod on the rudder mechanical control
27-22-00-710-002 27-24-00-710-001 29-00-00-864-001 55-33-13-000-001 Operational Test of the Rudder Trim ActuationOperational Test of the Rudder Hydraulic ActuationPut the Related Hydraulic System in the Depressurized Configuration before Maintenance ActionRemoval of the Trailing Edge Access-Panels 325EL, 325ER, 325DL, 325DR, 325CL, 325CR, 325BL and 325BR
55-33-13-010-002 Opening/Removal of the Trailing Edge Access-Panels 325EL, 325ER, 325DL, 325DR, 325CL, 325CR, 325BL and
325BR
55-33-13-400-001 Installation of the Trailing Edge Access-Panels 325EL, 325ER, 325DL, 325DR, 325CL, 325CR, 325BL and
325BR
55-33-13-410-002 Closing/Installation of the Trailing Edge Access-Panels 325EL, 325ER, 325DL, 325DR, 325CL,
325CR, 325BL and 325BR
27-22-51-991-001 27-22-51-991-004 Fig. 401Fig. 402
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-------------------------------------------------------------------------------REFERENCE DESIGNATION -------------------------------------------------------------------------------
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