(c)
Remove the connection rod (11) and the bushes (6),(7) from the fuselage fitting (4).
(3)
Close the Bulk door (Ref. TASK 52-30-00-860-008).
(4)
Cut and remove the lockwire and loosen the clamping screw (34) until the torsion spring (53) is fully released.
(5)
Disengage the connection rod (11) from the forward lever (15) as follows:
(a)
Remove and discard the cotter pin (12) from the nut (13).
(b)
Remove the nut (13), the washers (14) and the bolt (16).
(c)
Remove the connection rod (11) and the bushes (17),(18) from the forward lever (15).
(6)
Lift the forward lever (15) and remove the adjustment gage.
(7)
Lower the forward lever (15) against the stop fitting of the adjacent beam.
R **ON A/C 106-149, 221-221, 224-224, 228-228,
Subtask 52-33-41-020-050-A
A. Removal of the Connection Road
(1) Release the tension of the balance mechanism as follows:
(a) Install the adjustment gage between the forward lever (15) and the stop fitting of the beam 2.
NOTE : The permitted tolerance of the adjustment gage thickness
____ is between 17.7 mm (0.6968 in.) and 18.3 mm (0.7204 in.).
(b) Fully open the Bulk door (Ref. TASK 52-30-00-860-010).
R 1EFF : 001-049, 051-099, 101-149, 221-221, 1 52-33-41Page 406 1224-224, 228-228, 1May 01/05 1 1 1CES 1
(2)
Disconnect the connection rod (11) from the fuselage fitting (4) as follows:
(a)
Remove and discard the cotter pin (1) from the castle nut (2).
(b)
Remove the castle nut (2), the washers (3), and the bolt (5).
(c)
Remove the connection rod (11) and the bushes (6),(7) from the fuselage fitting (4).
(3)
Close the Bulk door (Ref. TASK 52-30-00-860-008).
(4)
Cut and remove the lockwire and loosen the clamping screw (34) until the torsion spring (53) is fully released.
(5)
Disengage the connection rod (11) from the forward lever (15) as follows:
(a)
Remove and discard the cotter pin (12) from the nut (13).
(b)
Remove the nut (13), the washers (14) and the bolt (16).
(c)
Remove the connection rod (11) and the bushes (17),(18) from the forward lever (15).
(6)
Lift the forward lever (15) and remove the adjustment gage.
(7)
Lower the forward lever (15) against the stop fitting of the adjacent beam.
R **ON A/C 001-049, 051-099, 101-149, 221-221, 224-224, 228-228,
Subtask 52-33-41-020-052
B. Removal of the Pre-Load Unit (20)
(1)
Remove the connection rod (11) (Ref. Para. 4.A) to release the torsion spring (53).
(2)
Remove the clamping screw (34) together with the washer (35) from the clamping sleeve (25).
(3)
Remove the nuts (28), the washers (29) and the bolts (31) from the flange bearing (30).
(4)
Disconnect the flange bearing (30) carefully from the Bulk door.
R 1EFF : 001-049, 051-099, 101-149, 221-221, 1 52-33-41Page 407 1224-224, 228-228, 1May 01/05 1 1 1CES 1
(5)
If necessary, remove the screw (33) and the washer (32) from the flange bearing (30).
(6)
Disconnect the clamping sleeve (25) from the aft lever (21) as follows:
(a)
Remove and discard the cotter pin (27) from the nut (26).
(b)
Remove the nut (26), the washers (24) and the bolt (23).
(c)
Disengage the clamping sleeve (25) from the special shaft (22).
(d)
If necessary, remove the special nut (38) from the clamping sleeve (25).
(7) If necessary, remove the special shaft (22) from the aft lever (21). Subtask 52-33-41-020-051
C. Removal of the Torsion Spring (53)
(1)
Remove the connection rod (11) (Ref. Para. 4.A) to release the torsion spring (53).
(2)
Carefully open the Bulk door sufficiently to remove the torsion spring (53) through the serrated sleeve (61).
(3)
Safety the opened Bulk door with an applicable support device .
(4)
Remove the retaining rings (51) and the covers (52) from the opening of the serrated sleeves (54),(61).
(5)
Move the torsion spring (53) in the aft direction until it comes free from the serrated sleeve (61).
(6)
Remove the support device and put the Bulk door carefully into the closed position.
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 DOORS 艙門6(78)
