R 4. Procedure_________
R (Ref. Fig. 408/TASK 57-51-37-991-007)
R Subtask 57-51-37-420-058
R A. Preparation for Installation
R (1) Clean the component interfaces and/or the adjacent area with a
R MISCELLANEOUS (Material No. 19-003) made moist with CLEANING AGENTS
R (Material No. 11-026).
R (2) Do an inspection of the component interface and/or the adjacent area.
R (3) Make sure that the parts retained from the removed component are
R clean and in the correct condition.
R Subtask 57-51-37-420-059
R B. Installation of the Access Panel 575AT(675AT)
R (1) Put the access panel (1) in position.
R (2) Install the bolts (2) but do not tighten. Make sure that you can move
R the access panel (1) sufficient to adjust its position.
R (3) Set the access panel (1) so that:
R - the dimension W is 2.0 mm (0.0787 in.) + 2.3 mm (0.0905 in.)/- 1.5
R mm (0.0590 in.) along the full length of the panel
R - the dimension X is 2.0 mm (0.0787 in.) +/- 0.5 mm (0.0196 in.)
R along the full width of the panel inboard end
R - the dimension Y is 4.0 mm (0.1574 in.) + 2.0 mm (0.0787 in.)/- 1.0
R mm (0.0393 in.) along the full width of the panel outboard end
R - the dimension Z is 0.0 mm (0.0000 in.) + 0.5 mm (0.0196 in.) along
R the full length of the panel seal.
R (4) TORQUE tighten the bolts (2) to between 0.4 and 0.45 m.daN (35.39 and
R 39.82 lbf.in).
R (5) Fill the clearance between the access panel (1) edges and the wing
R skin with SEALANTS (Material No. 09-016).
R 5. Close-up________
R Subtask 57-51-37-942-057
R A. Removal of Equipment
R (1) Remove the TOOL-ZERO LOCKING, FLAP SLAT CTL LEVER from the flap/slat
R control lever.
R (2) Make sure that the work area is clean and clear of tool(s) and other
R items.
R (3) Remove the access platform(s).
R (4) Remove the ground support and maintenance equipment, the special and
R standard tools and all other items.
R (5) Remove the warning notice(s).
R (6) Remove the safety barriers.
INBOARD FLAP - DESCRIPTION AND OPERATION
________________________________________
1. General
_______
R **ON A/C 001-049, 051-099, 101-149, 151-199, 201-299, 401-499,
(Ref. Fig. 001)
**ON A/C 301-399,
(Ref. Fig. 001A, 002)
R **ON A/C 001-049, 051-099, 101-149, 151-199, 201-299, 401-499,
The inboard flap is a fowler flap assembly. In its retracted position the
inboard flap assembly is the wing trailing edge between the fuselage side
and the outboard flap.
The spars, the ribs and the skin of the inboard flap are made of Carbon
Fiber Reinforced Plastics (CFRP). The leading edge is made of honeycomb core
with a skin made of CFRP. The trailing edge is made of honeycomb core with a
skin made of aluminum sheet metal.
The drive strut assembly-track 1 attaches the inboard flap assembly to the
carriage assembly-track 1. Two bolt connections attach the drive strut
assembly-track 1 to the drive trunnion. A forked bolt assembly attaches the
drive strut assembly-track 1 to the rotary actuator-track 1.
A spherical bearing attaches the drive trunnion to the carriage
assembly-track The drive trunnion is a fail-safe part. The drive strut
assembly is not a fail- safe part.
Between RIB9 and RIB10 there is a bracket. The bracket is to attach the
drive strut assembly-track 2. Bolts connect the drive strut assembly-track 2
to the bracket. Drive strut assembly-track 2 is a fail-safe-part.
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