(b) Do the steps written above again and disconnect these hinges at their related rib positions of the vertical stabilizer (1):
 -
the hinge No. 3 at RIB5

 -
the hinge No. 4 at RIB6

 -
the hinge No. 5 at RIB7.

 (8)
 Apply a tension to the SLING - R/I VERTICAL STABILIZER AND RUDDER (98D55307518000) and remove the load from the hinges of the rudder (2).

 (9)
 Remove the bolt (52) from the hinge No. 7 at RIB11 (Ref. Fig. 405/TASK 27-21-41-991-005)

 (a) Remove the bolt (52), the washer (15) and the locking plate (53) from the connection of the bracket (51) and the hinge arm (50).
 (10)
 Remove the bolt (23) from the hinge No. 1 at RIB2 (Ref. Fig. 403/TASK 27-21-41-991-003)

 (a) Remove the bolt (23), the washer (15) and the locking plate (24) from the connection of the bracket (11) and the hinge arm (12).

 (11)
 Remove the rudder (2) from the vertical stabilizer (1).

 (a)
 Move the rudder (2) aft and down in the 90 degree direction from the rudder axis until it touches the rubber mat.

 (b)
 Move the rudder (2) to the left of the aircraft center line.

 (c)
 Move the rudder (2) aft, away from the vertical stabilizer (1) and lower it onto a rudder support.

 (12)
 Disconnect the SLING - R/I VERTICAL STABILIZER AND RUDDER (98D55307518000) from the rudder (2).

R 1EFF : 001-003, 051-054, 1 27-21-41Page 417 1 1 May 01/05 1 1 1CES 1

 (13)
 Remove the bushes from the hinge locations.

 (a)
 Remove the bushes (25),(26) from the bracket (11) of the rudder

 (2)
 at the location of the hinge No. 1. (Ref. Fig. 403/TASK 27-21-41-991-003)

 (b)
 Remove the bushes (94),(95) from the brackets (91) of the rudder

 (2)
 at the locations of the hinges 2,3,4 and 5. (Ref. Fig. 406/TASK 27-21-41-991-006)

 (c)
 Remove the bushes (54),(55) from the brackets (51) of the rudder

 (2)
 at the location of the hinge No. 7. (Ref. Fig. 405/TASK 27-21-41-991-005)

 (d)
 Remove the bushes (73),(74) from the hinge arm (63) at the location of the hinge No. 6 at rib 9 of the vertical stabilizer (1). (Ref. Fig. 405/TASK 27-21-41-991-005)

 (14)
 Remove the bushes (47),(48) from the attachment brackets (36) on the rudder (2). (Ref. Fig. 404/TASK 27-21-41-991-004-B)

R **ON A/C 004-049, 055-099, 101-149, 151-199, 201-299, 301-399, 401-499,
 Subtask 27-21-41-020-050-A
 A. Removal of the Rudder
 (1)
 Make sure you identify all the components you remove during the subsequent procedure with their correct position and location.

 (2)
 Disconnect the push-rod (10) of the transducer 42WV from the bracket

 (11)
 of the rudder (2).
 (Ref. Fig. 403/TASK 27-21-41-991-003)

 (a)
 Remove and discard the cotter pin (22).

 (b)
 Remove the nut (21), the washer (20) and the bolt (16).

 (c)
 Disconnect the eye-end of the push-rod (10) from the attachment bracket (14).

 (d) Safety the push-rod (10) and the transducer 42WV (13)

 (e)
 Remove the sliding bush (17) and the flanged bushes (18),(19) from the attachment bracket (14).

 (3)
 Disconnect the hinge No. 1 at RIB2 from the bracket (11) of the rudder (2) (Ref. Fig. 403/TASK 27-21-41-991-003)

 (a)
 Remove the bolt (30) and disconnect the bonding strap (31) from the attachment bracket (32).

 (b)
 Use the TOOL - EXTRACTION, TAB WASHERS STA-LOK NSA5454 (SL90-314-5625) and remove the tab washer (28) and the spring ring (29) from the slotted nut (27).

 (c)
 Use the WRENCHES - NOTCHED, TIGHTENING OF NUTS NSA5454 (SL90-322-5625) and remove the slotted nut (27) from the bolt (23). Do not remove the bolt (23) at this time.

 (4)
 Disconnect the servo actuators 1025GM/2025GM/3025GM (35) from the brackets (36) of the rudder (2). (Ref. Fig. 404A/TASK 27-21-41-991-004-A)

 1_ Use the tie wraps to temporarily attach the push-rod (10) to
 the hinge arm (12).
 2_ Do this at a position where the push-rod (10) and the
 transducer 42WV (13) are not damaged during the subsequent
 procedures.

 (a) Disconnect the servo actuator 1025GM (35) at RIB3 as follows: 1 Remove and discard the cotter pin (113).
　
中國航空網 m.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(3)