D. Referenced Information
-------------------------------------------------------------------------------REFERENCE DESIGNATION -------------------------------------------------------------------------------
24-41-00-861-002 Energize the Aircraft Electrical Circuits from the External Power 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 27-92-15-991-001 Fig. 401
3. Job Set-up
__________ Subtask 27-92-15-860-051
A. Aircraft Maintenance Configuration
(1)
Make sure that the warning notice to tell persons not to operate the pedals is in position.
(2)
On the panel 110VU, make sure that the warning notice is in position to tell persons not to use the rudder trim.
(3)
Make sure that the access platform is in position at the access door
811.
(4)
Make sure that the access door 811 is open.
(5)
Make sure that the access platform is in position at the access door
822.
(6)
Make sure that the access door 822 is open.
(7)
On the battery power center 105VU:
-make sure that the protective cover is removed.
(8)
Make sure that the PIN, RIGGING - RUDDER CONTROL (98A27901002000)
(19) is in position on the yaw and braking bellcranks.
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Subtask 27-92-15-865-051
B. Make sure that this(these) circuit breaker(s) is(are) open, safetied and tagged
-------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION -------------------------------------------------------------------------------
49VU FLIGHT CONTROLS/ELAC1/NORM/SPLY 15CE1 B11 R 105VU FLIGHT CONTROLS/ELAC2/STBY SPLY 16CE2 A02 R 105VU FLT CTL/ELAC1/STBY SPLY 16CE1 A01 R
121VU FLIGHT CONTROLS/ELAC2/NORM/SPLY 15CE2 R20
4. Procedure
_________
(Ref. Fig. 401/TASK 27-92-15-991-001)
Subtask 27-92-15-420-050
A. Installation of the Transducer Unit
(1)
Install the transducer unit (12) on its support (18) and install the bolts (1).
(2)
Install the washers (17), install and tighten the nuts (15) and safety with the new cotter pin (16).
(3)
Install the rod (5), install the bolt (2), the washer (6), the nut
(7) and tighten safety with the new cotter pin (8).
(4)
Push in and hold the pin (11) to lock the input lever of the transducer unit (12) in the zero position.
NOTE : The pin (11) is a part of the transducer unit (12).
____
(5)
If you cannot engage the pin (11) freely, adjust the length of the body (3) as follows:
(a)
Cut and remove the lockwires.
(b)
Loosen the nuts (3) and (10) and disengage the lockwashers (4) and (9).
(c)
Adjust the length of the rod (5) until you can engage the bolt (2).
(d)
Engage the lockwashers (4) and (9). Tighten the nuts (3) and (10) and safety them with Lockwire corrosion resistant steel dia 0.8 mm (0.03 in.).
(e)
Make sure that you can remove and install freely the PIN, RIGGING
-RUDDER CONTROL (98A27901002000) (19) on the yaw/brake bellcranks. If you cannot, adjust the length of the rod (5) again. Install the PIN, RIGGING - RUDDER CONTROL (98A27901002000)
(19) on the yaw/brake bellcranks.
(6)
Release the pin (11) and make sure that it disengages freely.
(7)
Remove the blanking caps from the electrical connectors (13) and (14).
(8)
Make sure that the electrical connectors are clean and in the correct condition.
(9)
Connect the electrical connectors (13) and (14) to the transducer unit (12).
Subtask 27-92-15-820-050
B. Preparation for the Test
(1)
Remove the PIN, RIGGING - RUDDER CONTROL (98A27901002000) (19).
(2)
Make sure that the pin (11) is disengaged from the input lever of the transducer unit (12)
Subtask 27-92-15-861-050
C. Energize the aircraft electrical circuits (Ref. TASK 24-41-00-861-002). Subtask 27-92-15-865-052
D. Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s): 15CE1, 16CE1, 15CE2, 16CE2
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Subtask 27-92-15-865-053
E. Make sure that this(these) circuit breaker(s) is(are) closed:
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本文链接地址：A320飞机维护手册 AMM FLIGHT CONTROLS 飞行操纵9(23)
