(a)
Remove and discard the cotter pin (4).
(b)
Remove the nut (5), the washer (6) and the bolt (10).
(2)
Disconnect the centering rod (1) from the bellcrank assembly (2).
(a)
Remove and discard the cotter pin (11).
(b)
Hold the centering rod (1) in position.
(c)
Remove the nut (12), the washer (13) and the bolt (17).
(3)
Remove the centering rod (1).
(a)
Move the fork-end of the centering rod (1) clear of the attachment bracket.
(b)
Move the eye-end of the centering rod (1) clear of the lever arm at the bellcrank assembly (2).
(4)
Temporarily safety the sliding bush (7) in the flanged bush (8) at the fork-end of the centering rod (1) with lockwire corrosion-resistant steel 0.8 mm (0.032 in.).
(5)
Temporarily safety the sliding bush (14) in the flanged bush (15) at the lever arm of the bellcrank assembly (2) with lockwire corrosion-resistant steel 0.8 mm (0.032 in.).
NOTE : The flanged bushes (8),(9),(15),(16) are safetied in the lever
____
arm and the fork-end with loctite.
TASK 27-21-48-400-001
Installation of the Centering Rod of the Rudder Control
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 warning notices
No specific access platform 11.0 m (36 ft. 1 in.) R No specific Torque Wrench : range 0.00 to 1.20 m.daN R (0.00 to 9.00 lbf.ft)
98D27207545000 1 PIN - RIGGING B. Consumable Materials
-------------------------------------------------------------------------------
REFERENCE DESIGNATION
-------------------------------------------------------------------------------
No specific lockwire corrosion-resistant steel 0.8 mm (0.032 in.)
R Material No. 04-004 USA MIL-PRF-23827 TYPE I SYNTH.ESTER BASED GREASE HIGH PRESSURE (Ref. 20-31-00) Material No. 05-002 USA MIL-P-8116 PUTTY, ZINC CHROMATE GENERAL PURPOSE (Ref. 20-31-00) Material No. 08-029 USA MIL-R-46082 TYPE I ADHESIVE (Ref. 20-31-00)
C. Expendable Parts
-------------------------------------------------------------------------------
FIG.ITEM |DESIGNATION |IPC-CSN
-------------------------------------------------------------------------------
4 cotter pin 27-21-04 11 -050 11 cotter pin 27-21-04 11 -050
D. Referenced Information
-------------------------------------------------------------------------------
REFERENCE DESIGNATION
-------------------------------------------------------------------------------
24-41-00-862-002 De-energize the Aircraft Electrical Circuits Supplied
from the External Power 27-24-00-710-001 Operational Test of the Rudder Hydraulic Actuation 29-00-00-864-001 Put the Related Hydraulic System in the Depressurized
Configuration before Maintenance Action
55-33-13-010-002 Opening/Removal of the Trailing Edge Access-Panels 325EL, 325ER, 325DL, 325DR, 325CL, 325CR, 325BL and 325BR
55-33-13-410-002 Closing/Installation of the Trailing Edge Access-Panels 325EL, 325ER, 325DL, 325DR, 325CL, 325CR, 325BL and 325BR
27-21-48-991-001 Fig. 401
3. Job Set-up__________
(Ref. Fig. 401/TASK 27-21-48-991-001)
R Subtask 27-21-48-860-052-A
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本文鏈接地址：A320飛機維護手冊 AMM FLIGHT CONTROLS 飛行操縱2(51)
