(2)
Clean the component interface and/or the adjacent area.
(3)
Do an inspection of the component interface and/or the adjacent area.
(4)
Apply SEALANTS (Material No. 09-016) to the mating surface of the gear box (123) and the structural bearing at longeron 4.
(5)
Apply SEALANTS (Material No. 09-016) to the mating surface of the flange bearing (122) and the support bracket (117).
(6)
Apply SEALANTS (Material No. 09-013) to the shaft and the heads of the screws (119) and the bolts (112).
R 1EFF : ALL 1 52-32-21Page 448 1 1 Aug 01/05 1 1 1CES 1
(7) Apply COMMON GREASE (Material No. 04-004) to the mating surfaces of the drive shaft lever (102), the safety cam (130), the lever (124) and the shaft lever (110).
**ON A/C 051-052,
Subtask 52-32-21-910-051-B
A. Preparation for Installation (Ref. Fig. 404A/TASK 52-32-21-991-003-C, 405A/TASK 52-32-21-991-004-C)
(1)
Make sure that the parts retained from the removed component are clean and in the correct condition.
(2)
Clean the component interface and/or the adjacent area.
(3)
Do an inspection of the component interface and/or the adjacent area.
(4)
Apply SEALANTS (Material No. 09-016) to the mating surface of the gear box (123) and the structural bearing at longeron (116).
(5)
Apply SEALANTS (Material No. 09-016) to the mating surface of the flange bearing (122) and the support bracket (117).
(6)
Apply SEALANTS (Material No. 09-013) to the shaft and the heads of the screws (119) and the bolts (112).
(7)
Apply COMMON GREASE (Material No. 04-004) to the mating surfaces of the drive shaft lever (102), the safety cam (130), the lever (124) and the shaft lever (76).
R **ON A/C 106-149, 221-299, 301-399, 401-499,
Subtask 52-32-21-910-051-A
A. Preparation for Installation R **ON A/C 106-149, 221-299, 301-399,
R (Ref. Fig. 404B/TASK 52-32-21-991-003-B)
R 1EFF : ALL 1 52-32-21Page 449 1 1 Aug 01/05 1 1 1CES 1
R **ON A/C 401-499,
R R (Ref. Fig. 404D/TASK 52-32-21-991-003-D) **ON A/C 106-149, 221-299, 301-399,
R R (Ref. Fig. 405B/TASK 52-32-21-991-004-B) **ON A/C 401-499,
R R (Ref. Fig. 405D/TASK 52-32-21-991-004-D) **ON A/C 106-149, 221-299, 301-399, 401-499,
(1) Make sure that the parts retained from the removed component are clean and in the correct condition.
(2) Clean the component interface and/or the adjacent area. (3) Do an inspection of the component interface and/or the adjacent area. (4) Apply SEALANTS (Material No. 09-016) to the mating surface of the cover assembly (17) and the structural bearing at beam 4. (5) Apply SEALANTS (Material No. 09-013) to the shaft and the heads of the bolts (14), (19), (18), (15) and (6) and (2). **ON A/C 001-049, 053-099, 101-105, 151-199, 201-220,
Subtask 52-32-21-560-052
B. Preparation for the Replacement Components **ON A/C 001-049, 053-099, 101-105, 201-220,
(Ref. Fig. 405/TASK 52-32-21-991-004) **ON A/C 151-199,
(Ref. Fig. 405C/TASK 52-32-21-991-004-A)
R 1EFF : 001-049, 053-099, 101-149, 151-199, 1 52-32-21Page 450 1201-299, 301-399, 401-499, 1Aug 01/05 1 1 1CES 1 **ON A/C 001-049, 053-099, 101-105, 151-199, 201-220,
(1)
Install the gear box (123) temporarily at longeron (116) with screws (119).
(2)
Measure the gap between the surface of the gear box (123) and the longeron (116) find the correct thickness of the laminated shim (115).
(3)
Remove the screws (119) and the temporarily installed gear box (116) from the longeron (116).
(4)
Remove as many layers of the laminated shim (115) as necessary to get the correct thickness.
NOTE : Make sure that the thickness of the laminated shim (115) is
____ one layer thicker than the measured gap. This is necessary because the thickness of the laminated shim (115) becomes smaller when it is compressed during the installation.
**ON A/C 051-052,
Subtask 52-32-21-560-052-A
B. Preparation for the Replacement Components
(Ref. Fig. 405A/TASK 52-32-21-991-004-C)
(1)
Install the gear box (27) temporarily at longeron 4 with screws (24).
(2)
Measure the gap between the surface of the gear box (27) and the longeron 4 to find the correct thickness of the laminated shim (26).
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5(85)
