(g)
Safety the lock nut (2) with Lockwire-corrosion resistant steel dia 0.8 mm (0.03 in.).
(h)
Make sure that you can engage easily the rigging pin into the elevator position transducer-unit (1) on the two sides. (Ref. Fig. 502/TASK 27-34-00-991-009)
Adjustment of the Elevator Servocontrol Figure 501/TASK 27-34-00-991-001
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NOTE : The rigging pin is part of the transducer unit.
____
If you cannot, adjust the length of the control rod (4) as follows:
1_ Depressurize the aircraft hydraulic systems (Ref. TASK 29-10-
00-864-003) (Ref. TASK 29-23-00-864-001) (Ref. TASK 29-24-00-
864-001).
2_ Cut and discard the lockwire from the nuts (2).
3_ Loosen the nuts (2).
4_ Remove the bonding lead from the lock washer (3).
5_ Disengage the lock washers (3).
6_ Turn the control rod body (4) until you can engage freely the
rigging pin in the transducer unit (1).
7_ Engage the lock washers (3) and tighten the nuts (2) on the
rod (4).
8_ Pressurize the aircraft hydraulic systems (Ref. TASK 29-10-00-
863-003) (Ref. TASK 29-23-00-863-001) (Ref. TASK 29-24-00-863-
001).
9_ Do again these steps (from para.6_) until you can engage
freely the rigging pin in the transducer unit (1).
10__ When you can engage the rigging pin:
- On the upper ECAM display unit, make sure that the ELAC 2
PITCH FAULT warning is not shown.
- Depressurize the aircraft hydraulic systems (Ref. TASK 29-
10-00-864-003) (Ref. TASK 29-23-00-864-001) (Ref. TASK 29-
24-00-864-001).
11__ Tighten the lock nut
12__ Safety the nuts (2) with lockwire-corrosion resistant steel
dia 0.8 mm (0.03 in.).
13__ Install the bonding lead on the washer (3).
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Elevator Position Transducer Unit Figure 502/TASK 27-34-00-991-009
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14__ Safety the lock nut with Lockwire corrosion-resistant steel
dia 0.8 mm (0.03 in.)
15__ Pressurize the aircraft hydraulic systems (Ref. TASK 29-10-00-
863-003) (Ref. TASK 29-23-00-863-001) (Ref. TASK 29-24-00-863-
001).
(2)
On the overhead panel 24VU:
-release the FLT CTL/ELAC 2 pushbutton switch (on this pushbutton switch, the OFF legend comes on).
(3)
Make sure that the elevator trailing edge position has not changed. NOTE : Now, the inboard servocontrols are in the damping mode.
____ The outboard servocontrols are in the active mode.
(4)
If the elevator moves, do this adjustment :
(a)
Cut and remove the lockwire from the lock nut (2).
(b)
Loosen the lock nut (2).
(c)
Move the lock washers (3) apart.
(d)
Turn the rod (4) (in the correct direction) until: 1 The trailing edges of the elevators are aligned with the
_ reference triangle on the two sides of the tail cone.
2 You can easily engage and disengage the rigging pin into the
_ elevator position transducer-unit.
3 On the upper ECAM display unit, make sure that the ELAC 1
_ PITCH FAULT warning is not shown.
(e) TORQUE the lock nut (2) to between 3 and 3.5 m.daN (22.12 and
25.81 lbf.ft).
(f)
Make sure that the adjustment does not change when you TORQUE the lock nut.
(g)
Safety the lock nut (2) with Locwire corrosion-resistant steel dia 0.8 mm (0.03 in.).
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(5) On the overhead panel 24VU: - push the FLT CTL/ELAC 2 pushbutton switch (on this pushbutton switch, the OFF legend goes off and the FAULT legend comes). - when the FAULT legend goes off, release the FLT CTL/ELAC 2 pushbutton switch (on this pushbutton switch, the OFF legend comes on).
(6) Make sure that the elevator trailing edge position has not changed. If you see a position variation, do the adjustment of the servocontrol again.
(7) On the overhead panel 24VU: - push the FLT CTL/ELAC 2 pushbutton switch (on this pushbutton switch, the OFF legend goes off).
R R (8) Remove the pointer of LOAD APPLICATION TOOL - ELEVATOR, AILERON, RUDDER (98D27303000001).
R (9) Remove the rigging pin from the CAPT and F/O sidestick controllers.
R (10) Remove the rigging pin (5) from the screwjack of the THS actuator (6). (Ref. Fig. 501/TASK 27-34-00-991-001)
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本文链接地址：A320飞机维护手册 AMM FLIGHT CONTROLS 飞行操纵3(25)
