_
(b) For the fairing panel 193BB(194BB): 1 Put the fairing panel in position on the aircraft.
_
2 Install the attachment screws.
_
(5)
Put the cable (3) in position around the drive trunnion of the inboard flap. Attach it to the sliding panel with the screw (4).
(6)
TORQUE the screw (4) to between 0.4 and 0.5 m.daN (35.39 and 44.24 lbf.in).
(7)
Install the rubbing strip (2) and the support (1).
R 1EFF : 001-049, 051-099, 101-149, 151-199, 1 27-54-61Page 448 1201-299, 401-499, 1Aug 01/05 1 1 1CES 1R **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 27-54-61-410-051-B
R. Close Access
(Ref. Fig. 401A/TASK 27-54-61-991-001-A)
(1)
Make sure that the work area is clean and clear of tool(s) and other items.
(2)
Lift the flap track No. 2 movable fairing (Ref. TASK 57-55-11-410-001).
(3)
Install the pylon aft moveable fairing (Ref. TASK 54-55-00-400-001).
(4)
Install the fairing panels 193AB(194AB) and 193BB(194BB) as follows:
(a) For the fairing panel 193AB(194AB): 1 Put the fairing panel in position on the aircraft.
_
2 Install the attachment screws and washers.
_
(b) For the fairing panel 193BB(194BB): 1 Fully retract the flaps (Ref. TASK 27-50-00-866-009).
_ 2 Put the hook of the sliding panel (3) in position on the flap
_ drive trunnion. Hold the sliding panel (3) in this position.
3 With the sliding panel (3) held in position, align the fairing
_
panel with it.
4 Move the fairing panel onto the sliding panel (3).
_
5 Turn the fairing panel, together with the sliding panel (3),
_ and put it in its installed position on the aircraft. Install the attachment screws.
(5)
Extend the flaps (Ref. TASK 27-50-00-866-008) sufficiently to install the rubbing strip (2).
(6)
Install the rubbing strip (2) and the support (1).
R 1EFF : 001-049, 051-099, 101-149, 151-199, 1 27-54-61Page 449 1201-299, 401-499, 1Aug 01/05 1 1 1CES 1 **ON A/C 001-001, 051-052,
Subtask 27-54-61-220-064
S. Measurement and Adjustment (Ref. Fig. 401/TASK 27-54-61-991-001) **ON A/C 001-001, 051-052, Post SB 27-1117 For A/C 001-001,051-052,
(Ref. Fig. 401A/TASK 27-54-61-991-001-A) **ON A/C 001-001, 051-052,
(1)
Check the dimension A, between the flap drive trunnion and the sliding panel. This must be 6 mm (0.2362 in.) +/- 3 mm (0.1181 in.).
(2)
If the dimension A is more than 9 mm (0.3543 in.), do the steps that follow:
(a)
Do an inspection of the flap drive trunnion (Ref. ISB 27-1066) or (Ref. ISB 27-1108).
(b)
If the flap drive trunnion is not defective, replace the cable
(3)
as follows:
1_ Remove the screws (4) from the sliding panel, and disconnect
the cable (3) from the flap drive trunnion. Discard the cable
(3).
2_ Install a new cable (3) with the screws (4).
3_ TORQUE the screws (4) to between 0.4 and 0.5 m.daN (35.39 and
44.24 lbf.in).
R 1EFF : 001-001, 051-052, 1 27-54-61Page 450 1 1 Aug 01/05 1 1 1CES 1R **ON A/C 001-049, 051-099, 101-149, 151-199, 201-299, 401-499,
Subtask 27-54-61-866-058
T. Retract the Flaps
(1)
Retract the flaps fully (Ref. TASK 27-50-00-866-009).
(2)
Put the TOOL-ZERO LOCKING, FLAP SLAT CTL LEVER (98D27803500001) on the flap/slat control lever on panel 114VU.
**ON A/C 001-001, 051-052,
Subtask 27-54-61-820-055
U. Adjust the Wing to Fuselage Panels
(Ref. Fig. 401/TASK 27-54-61-991-001)
(1)
Measure the dimension X, this must be between 23.5 mm (0.9251 in.) and 22.5 mm (0.8858 in.).
(2)
Measure the dimension U, this must be between 33.5 mm (1.3188 in.) and 32.5 mm (1.2795 in.).
(3)
If the dimension X is not correct loosen the screws (6) and move the aft seal until the dimension X is correct.
(4)
If the dimension U is not correct, loosen the screws (5) and move the forward seal until the dimension U is correct.
(5) TORQUE the applicable screws (5) and/or (6) to between 0.4 and 0.45 m.daN (35.39 and 39.82 lbf.in). 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,
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