(b)
tighten the bolts (62).
(3)
To install the removed slat-track can 11, do these steps:
(a)
Put the bracket assembly (111) in position on the slat-track can (114).
(b)
Install the bolts (117) and the nuts (110).
(c)
Install the bolts (116) and the nuts (112).
(d)
Tighten the nuts (110) and (112).
(4)
Connect and tighten the drain pipe (61) to the slat-track can (60).
(5)
For the slat-track can 12, apply a layer of SEALANTS (Material No. 09-005) to the seal faces of the slat-track can (70) and the bolts (72).
(6)
If you replace the slat-track can 12, do these steps: NOTE : It is not necessary to install the bracket assembly on the new
____
slat-track can.
(a) Install the slat-track can (70) with the bolts (72). Make sure that you install the bolts (72) in the same positions from which you removed them.
1EFF : ALL 1 57-24-11Page 421 1 1 May 01/04R 1 1 1CES 1
(b) Tighten the bolts (72).
(7) To install the removed slat-track can 12, do these steps:
(a)
Put the bracket assembly (122) in position on the slat-track can (124).
(b)
Install the bolts (120) and the nuts (121).
(c)
Install the bolts (127) and the nuts (123).
(d)
Tighten the nuts (121) and (123).
(8) Connect and tighten the drain pipe (71) to the slat-track can (70). Subtask 57-24-11-410-052
G. Preparation for Test
(1)
Install the removed access panels (Ref. TASK 57-27-11-400-001), (Ref. TASK 57-27-11-400-002), (Ref. TASK 28-12-46-400-001) and (Ref. TASK 28-10-00-910-002).
(2)
Energize the electrical circuits (Ref. TASK 24-41-00-861-002).
(3)
Refuel the wing tanks to the low level cut-off condition (Ref. TASK 12-11-28-650-003).
R **ON A/C 001-049, 051-099, 101-149, 151-199, 201-299, 401-499,
Subtask 57-24-11-790-051
H. Leak Test
(1)
Remove the applicable leading edge access panels.
(2)
Examine the slat-track cans and the front spar for leaks (Ref. TASK 28-11-00-790-002).
(3)
Remove the access platform(s).
(4)
Remove the ground support and maintenance equipment, the special and standard tools and all other items.
R **ON A/C 301-399,
R Subtask 57-24-11-790-051-A
R H. Leak Test
R (1) Remove tha applicable leading edge access panels.
R R (2) Examine the slat-track cans and the front spar for leaks (Ref. TASK 28-11-00-790-008)
R **ON A/C ALL
5. Close-up________
Subtask 57-24-11-650-052
A. Fuel Configuration
(1) Refuel, defuel or transfer fuel as necessary (Ref. TASK 12-11-28-650-003) ,(Ref. TASK 28-25-00-650-001) or (Ref. TASK 28-25-00-869-001)
Subtask 57-24-11-860-053
B. Aircraft Configuration
(1) Install the applicable leading edge access panels.
(2) Remove the TOOL-ZERO LOCKING, FLAP SLAT CTL LEVER (98D27803500001) from the slat/flap control lever.
(3) Fully retract the slats (Ref. TASK 27-80-00-866-005).
(4) De-energize the aircraft electrical circuits (Ref. TASK 24-41-00-862-002).
Subtask 57-24-11-942-051
C. Removal of Equipment
(1) Make sure that the work area is clean and clear of tool(s) and other items.
(2) Remove the warning notice(s).
FITTINGS - DESCRIPTION AND OPERATION
____________________________________
1. Component Description
_____________________
A. Wing-Tip Attachment Fitting
There are butt straps attached to the top skin and bottom skin panels, outboard of RIB27. The wingtip is bolted to the buttstraps. Two spigots machined from aluminum alloy are attached to RIB27 at the front and rear spar datum positions. The spigots locate and support the attachment of the wingtip to the outer wing.
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)
**ON A/C ALL
B. Pylon Attachment Fittings
There are forward and rear attachment fittings on the wing box for the
engine pylon.
The two forward attachment fittings are at the front spar at ribs RIB7
and RIB8.
The forward attachment for the pylon has:
-
a bracket assembly that absorbs the vertical loads
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