R 1EFF : 001-049, 051-099, 101-149, 151-199, 1 27-54-61Page 403 1201-299, 401-499, 1Aug 01/05 1 1 1CES 1 Subtask 27-54-61-860-052
B. Aircraft Maintenance Configuration
(1)
Make sure that the flaps are retracted fully (Ref. TASK 27-50-00-866-009).
(2)
Make sure that the TOOL-ZERO LOCKING, FLAP SLAT CTL LEVER is on the flap/slat control lever.
Subtask 27-54-61-865-050
C. Make sure that this(these) circuit breaker(s) is(are) open, safetied and tagged
-------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION -------------------------------------------------------------------------------49VU FLIGHT CONTROLS/FLP/CTL AND MONG/SYS1 6CV B07 121VU FLIGHT CONTROLS/FLP/CTL AND/MONG/SYS2 8CV Q21
**ON A/C 001-001, 051-052,
Subtask 27-54-61-010-051
D. Get Access
(Ref. Fig. 401/TASK 27-54-61-991-001)
(1)
Put the access platform in position below the applicable inboard flap.
(2)
Lower the flap track No. 2 movable fairing for access (Ref. TASK 57-55-11-010-001).
(3)
Remove the pylon aft movable fairing (Ref. TASK 54-55-00-000-001).
(4)
Manually extend the flaps (Ref. TASK 27-50-00-866-011) to get access to the fasteners of the rubbing strip (2).
(5)
Install the LOCK-TORQUE SHAFT (FLAPS AND SLATS) WITH CLAMP-PIVOT (98D27504030001) on the torque shaft 6220CM (6270CM) (Ref. TASK 27-50-00-400-003).
(6)
Remove the support (1) and the rubbing strip (2).
R 1EFF : 001-049, 051-099, 101-149, 151-199, 1 27-54-61Page 404 1201-299, 401-499, 1Aug 01/05 1 1 1CES 1
Details of the Wing to Fuselage Panels
Figure 401/TASK 27-54-61-991-001
R 1EFF : 001-001, 051-052, 1 27-54-61Page 405 1 1 May 01/05 1 1 1CES 1
(7)
Remove the screw (4) from the sliding panel and disconnect the cable
(3) from the drive trunnion of the inboard flap.
(8)
Remove the fairing panels 193AB(194AB) and 193BB(194BB) as follows: NOTE : The attachment screws of the fairing panels are not all the
____ same length. Record the position of the screws as you remove them. This will make sure that they are installed correctly when the fairing panel is installed.
(a) For the fairing panel 193AB(194AB): 1 Hold the fairing panel and remove the attachment screws and
_
washers.
2 Remove the fairing panel from the aircraft.
_
(b) For the fairing panel 193BB(194BB): 1 Hold the fairing panel and remove the attachment screws.
_
2 Remove the fairing panel from the aircraft.
_
(9) Remove the LOCK-TORQUE SHAFT (FLAPS AND SLATS) WITH CLAMP-PIVOT from the applicable torque shaft.
(10)
Manually extend the flaps to position 1 (Ref. TASK 27-50-00-866-011).
(11)
Install the LOCK-TORQUE SHAFT (FLAPS AND SLATS) WITH CLAMP-PIVOT is on the applicable torque shaft.
(12)
Remove the flap kink seals (Ref. TASK 27-54-61-000-002).
R **ON A/C 001-049, 051-099, 101-149, 151-199, 201-299, 401-499, Post SB 27-1117 For A/C 001-001,051-052, Subtask 27-54-61-010-051-A
D. Get Access
(Ref. Fig. 401A/TASK 27-54-61-991-001-A)
(1)
Put the access platform in position below the applicable inboard flap.
(2)
Lower the flap track No. 2 movable fairing for access (Ref. TASK 57-55-11-010-001).
R 1EFF : 001-049, 051-099, 101-149, 151-199, 1 27-54-61Page 406 1201-299, 401-499, 1Aug 01/05 1 1 1CES 1
R Details of the Wing to Fuselage Panels Figure 401A/TASK 27-54-61-991-001-A
1EFF : 1 1 1CES ALL 1 111 27-54-61 Page 407 Aug 01/02
(3)
Remove the pylon aft movable fairing (Ref. TASK 54-55-00-000-001).
(4)
Manually extend the flaps (Ref. TASK 27-50-00-866-011) to get access to the fasteners of the rubbing strip (2).
(5)
Install the LOCK-TORQUE SHAFT LOCK-TORQUE SHAFT (FLAPS AND SLATS) WITH CLAMP-PIVOT (98D27504030001) on the shaft 6220CM (6270CM) (Ref. TASK 27-50-00-400-003).
(6)
Remove the support (1) and the rubbing strip (2).
(7)
Remove the fairing panels 193AB(194AB) and 193BB(194BB) as follows: NOTE : The attachment screws of the fairing panels are not all the
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