Location of the Rigging Pins and the Attached Components
Figure 401/TASK 27-21-47-991-001
Subtask 27-21-47-865-053
B. Make sure that this(these) circuit breaker(s) is(are) closed:
-------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION -------------------------------------------------------------------------------49VU AUTO FLT/FAC1/28VDC 5CC1 B04 49VU AUTO FLT/FAC1/26VAC 14CC1 B03 121VU AUTO FLT/RUDDER/TRIM/IND 15CC M20 121VU AUTO FLT/FAC2/28VDC 5CC2 M19 121VU AUTO FLT/FAC2/26VAC 14CC2 M18
Subtask 27-21-47-860-050
C. Aircraft Maintenance Configuration
WARNING : MAKE SURE THAT THE TRAVEL RANGES OF THE FLIGHT CONTROL SURFACES
_______ ARE CLEAR BEFORE YOU PRESSURIZE/DEPRESSURIZE A HYDRAULIC SYSTEM.
(1)
Energize the aircraft electrical circuits. (Ref. TASK 24-41-00-861-002)
(2)
Pressurize the Blue hydraulic system with the electric pump. (Ref. TASK 29-10-00-863-003)
(3)
Put the rudder pedals in the neutral position.
(4)
On the center pedestal, on the panel 110VU, make sure that the RUD TRIM indicator shows 0.
(5)
Depressurize the Blue hydraulic system and put it in the maintenance configuration (Ref. TASK 29-00-00-864-001).
(6)
Make sure that the Green and Yellow hydraulic systems are depressurized and put them in the maintenance configuration (Ref. TASK 29-00-00-864-001).
(7)
On the overhead panel 23VU, release the FLT CTL/FAC 1 pushbutton switch. The OFF legend comes on.
(8)
On the overhead panel 24VU, release the FLT CTL/FAC 2 pushbutton switch. The OFF legend comes on.
(9)
Put the warning notices in the cockpit to tell persons not to operate the flight controls.
(10)
De-energize the aircraft electrical circuits. (Ref. TASK 24-41-00-862-002)
(11)
Put the warning notices in position to tell persons not to operate the hydraulic systems:
-in the cockpit on the hydraulic section 40VU of the overhead panel,
- on the ground service panels of the Green, Yellow and Blue hydraulic systems.
(12)
Put the PIN - RIGGING (98D27207546000) (71) in the bellcrank of the servo actuator 1025GM.
(13)
Put the PIN - RIGGING (98D27207547000) (70) in the rudder cable quadrant.
Subtask 27-21-47-865-050
D. Open, safety and tag this(these) circuit breaker(s):
-------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION -------------------------------------------------------------------------------49VU AUTO FLT/FAC1/28VDC 5CC1 B04 49VU AUTO FLT/FAC1/26VAC 14CC1 B03 121VU AUTO FLT/RUDDER/TRIM/IND 15CC M20 121VU AUTO FLT/FAC2/28VDC 5CC2 M19 121VU AUTO FLT/FAC2/26VAC 14CC2 M18
4. Procedure
_________
(Ref. Fig. 402/TASK 27-21-47-991-002)
Subtask 27-21-47-020-050
A. Removal of the Rudder Control Frame
(1)
Remove the centering spring rod (6) for the yaw-damper servo actuators 3CC1, 3CC2 (4) (Ref. TASK 27-26-41-000-001).
(2)
Remove the yaw-damper servo actuators 3CC1 and 3CC2 (4) (Ref. TASK 27-26-51-000-001).
(3)
Disconnect the electrical connections to:
-
the artificial feel and trim unit (8) (Ref. TASK 27-23-41-000-001),
-
the rudder trim actuator 10CC (5) (Ref. TASK 27-22-51-000-001).
(4)
Disconnect the support beams (52),(53) for the hydraulic pipelines from the rudder control frame (1).
Rudder Control Frame
Figure 402/TASK 27-21-47-991-002
1EFF : ALL 1 27-21-47 Page 406
1 1 Feb 01/98
1 1
1CES 1
(a) Remove the nuts (56), the washers (55) and the bolts (54) connecting the support beam (52) at each side of the rudder control frame (1).
NOTE : Identify nuts (56), the washers (55) and the bolts (54)
____ removed from the bonding points for installation in the same positions.
(b)
Move the support beam (52) away from the top connection to the rudder control frame (1).
(c)
Remove the nuts (57), the washers (58) and the bolts (59) connecting the support beam (53) at each side of the rudder control frame (1).
(d)
Move the support beam (53) away from the bottom connection to the rudder control frame (1).
中國航空網 www.k6050.com
航空翻譯 www.aviation.cn
本文鏈接地址：A320飛機維護手冊 AMM FLIGHT CONTROLS 飛行操縱2(44)
