**ON A/C ALL
Subtask 27-21-46-865-051
B. Make sure that this(these) circuit breaker(s) is(are) open, safetied and tagged
-------------------------------------------------------------------------------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
_________
R **ON A/C 001-049, 051-099, 101-149, 151-199, 201-299, 401-499,
(Ref. Fig. 401/TASK 27-21-46-991-001)
**ON A/C 301-399,
(Ref. Fig. 401A/TASK 27-21-46-991-001-A)
**ON A/C ALL
Subtask 27-21-46-210-050
A. Preparation for Installation
(1)
Clean the interface of the aircraft structure at the cable quadrant position with CLEANING AGENTS (Material No. 11-002) and let it dry.
(2)
Examine the work area.
(a) Make sure that:
-
the structure,
-
the paint work,
-
the control rod (2),
-
the cables (10),
are clean and show no damage.
(3)
Examine the attachment components.
(a) Make sure that:
-
the screws (8),(9),(19),
-
the nuts (6),(16),
-
the bush (18),
-
the eye-end bearing of the control rod (2) are clean and show no damage.
(4)
Apply COMMON GREASE (Material No. 04-004) to the threads of the screws (8),(9),(19).
(5)
Apply COMMON GREASE (Material No. 04-004) to the bush (18).
(6)
Apply a thin layer of SPECIAL MATERIALS (Material No. 05-005) (Ref. TASK 51-75-13-916-002) to the interface of the structure at the cable quadrant position.
(7)
Apply a thin layer of SPECIAL MATERIALS (Material No. 05-005) (Ref. TASK 51-75-13-916-002) to the interface of the replacement cable quadrant (1).
(8)
Make sure that the rigging pin (21) is installed in the replacement cable quadrant (1).
Subtask 27-21-46-420-050
B. Installation of the Cable Quadrant
(1)
Connect the cable quadrant (1) to the aircraft structure.
(a)
Put the cable quadrant (1) in position at the aircraft structure.
(b)
Hold the cable quadrant (1) in position.
(c)
Install the screws (8) at the top connection positions.
(d)
Install the screws (9) at the bottom connection positions.
(e)
Install the washers (7) and the nuts (6) on the screws (8),(9).
(f)
Tighten the nuts (6).
(g)
Safety the nuts (6) with the cotter pins (5).
(2)
Connect the control rod (2) to the cable quadrant (1).
(a)
Install the bush (18) in the lever arm (4).
(b)
Put the control rod (2) in position in the lever arm (4).
(c)
Align the hole in the eye-end bearing of the control rod (2) with the hole in the lever arm (4).
(d)
Install the screw (19).
(e)
Install the washer (17) and the nut (16) to the screw (19).
(f)
TORQUE the nut (16) to 0.7 m.daN (61.94 lbf.in) and then loosen it, if necessary, to the next cotter pin hole.
(g)
Safety the nut (16) with the cotter pin (15).
(3)
Connect the cables (10) to the cable quadrant (1).
(a)
Release the cables (10).
(b)
Put the cables (10) in position on the cable quadrant (1).
(c)
Put the ends of the cables (10) in position in the levers (3).
(d)
Make sure that the adjustment of the screws (11) is correct (Ref. TASK 27-21-00-820-002).
(e)
Turn the turnbuckles (31) to apply some tension to the cables (10).
Subtask 27-21-46-865-052
C. Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s): 5CC1, 5CC2, 14CC1, 14CC2, 15CC
Subtask 27-21-46-080-050
D. Preparation for the Test
(1)
Remove the PIN - RIGGING (98D27207547000) (21) from the cable quadrant.
(2)
Remove the PIN - RIGGING (98D27207548000) (20) from the bellcrank of the rudder control unit.
(3) 中国航空网 www.aero.cn 航空翻译 www.aviation.cn 本文链接地址：A320飞机维护手册 AMM FLIGHT CONTROLS 飞行操纵2(42)
