(3)
On the overhead panel 23VU:
(a) Push the FLT CTL/ELAC 1 and FLT CTL/SEC 1 pushbutton switches (on these pushbutton switches, the OFF legends are off).
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(b) Make sure that the F/CTL ELAC 1 PITCH FAULT warning is not shown on the upper ECAM display unit.
Subtask 27-34-00-820-065
G. Adjustment of the Outboard Servocontrol of the Left Elevator NOTE : At this step, the inboard servocontrol (Green) is in the damping
____ mode. The outboard servocontrol (Blue) is in the active mode.
(1)
In order to taking-up the play of the servocontrol attachment, loosen the servocontrol attachment bolts on the two ends (Ref. TASK 27-34-51-000-001).
(2)
Apply a force of 20 +10 -10 daN (44.9617 +22.4808 -22.4808 lbf) with the LOAD APPLICATION TOOL - ELEVATOR, AILERON, RUDDER (98D27303000001) to the down direction.
(3)
Tighten the servocontrol attachment bolts while you keep the force in the down direction (Ref. TASK 27-34-51-400-001), then release the force.
(4)
Remove the LOAD APPLICATION TOOL - ELEVATOR, AILERON, RUDDER (98D27303000001).
NOTE : Use the new elevator neutral position written on the tail cone
____
to do the adjustment.
R (Ref. Fig. 505/TASK 27-34-00-991-010) If not, adjust the outboard servocontrol: (Ref. Fig. 501/TASK 27-34-00-991-001)
(5)
Remove and discard the lockwire from the lock nut (2).
(6)
Loosen the lock nut (2).
(7)
Disengage the lock washer (3).
(8)
Turn the rod (4) (in the correct direction) until:
(a)
The pointer on the trailing edge of the elevator is in line with the mark made before on the adhesive tape.
(b)
You can easily engage/disengage the rigging pin into/from the elevator position transducer-unit (1).
(9)
Engage the lock washer (3).
(10)
TORQUE the lock nut (2) to between 3 and 3.5 m.daN (22.12 and 25.81 lbf.ft)
(11)
Make sure that the adjustment does not change when you TORQUE the lock nut.
(12)
Safety the lock nut (2) with Lockwire-corrosion resistant steel dia
0.8 mm (0.03 in.).
(13)
Remove the adhesive paper tape.
(14)
Install a new reference triangle (8) on the tail cone with its center in line with the pointer on the trailing edge of the elevator (Ref. TASK 11-00-00-960-001).
(15) Depressurize the Blue hydraulic system (Ref. TASK 29-10-00-864-003). Subtask 27-34-00-710-058
H. Test
(1) Preparation for the test
(a)
Removal of the tools
(b)
On the overhead panel 24VU: 1 Push the FLT CTL/ELAC 2 and FLT CTL/SEC2 pushbutton switches
1_ Remove the PIN - RIGGING (0U190360) (5) from the screwjack of
the THS actuator (6).
(Ref. Fig. 501/TASK 27-34-00-991-001)
2_ Remove the pointer of the LOAD APPLICATION TOOL - ELEVATOR,
AILERON, RUDDER (98D27303000001).
3_ Remove the PIN-SIDE STICK LOCKING (98D27903500000) from the
CAPT and F/O side sticks.
_ (on these pushbutton switches, the OFF legends go off).
(2) Do the operational test of the elevators (Ref. TASK 27-34-00-710-001).
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5. Close-up
________
Subtask 27-34-00-860-074
A. Put the Aircraft back to its Initial Configuration.
(1)
Depressurize the aircraft hydraulic systems (Ref. TASK 29-23-00-864-001) (Ref. TASK 29-24-00-864-001) (Ref. TASK 29-10-00-864-003).
(2)
Remove the warning notice(s).
(3)
Make sure that the work area is clean and clear of tool(s) and other items.
(4)
De-energize the aircraft electrical circuits (Ref. TASK 24-41-00-862-002).
Subtask 27-34-00-410-064
B. Close Access.
(1) Close the access door 312AR.
R (2) Close the THS trailing edge access panels (Ref. TASK 55-13-11-400-R 001):
(a)
334DB, 334AT 334BB for the left elevator.
(b)
344DB, 344AT 344BB for the right elevator.
(3)
Install the protective cover on the battery power center 105VU.
(4)
Tighten the two screws.
(5)
Close the access door 822
(6)
Remove the access platform(s).
ELEVATOR AND HYDRAULIC ACTUATION - INSPECTION/CHECK
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