(f)
If the chafing damage goes through the outer bonded skin, do a repair per 747-400 SRM 57-60-01 Structural Repair Manual.
S 224-009
(2)
Make sure the worn areas of the structural attach points are not out of tolerance (AMM 27-11-01/601).
S 224-010
(3)
If you install used bolts or bushings, make sure the worn areas are not out of tolerance (AMM 27-11-01/601).
S 644-011
(4)
Apply corrosion preventive compound to all the aileron hinge bolts and bearings.
S 494-012
(5)
Attach the hoist adapter, load positioner, and applicable hoist to the aileron.
S 864-044
(6)
Balance the weight of the aileron and the adapter.
G.
Install the Inboard Aileron (Fig. 401)
S 424-013
(1)
Install the inboard aileron.
(a)
Move the aileron into its position.
(b)
Install the nuts (3, 7, 14 and 23), hinge bolts (5, 11, 17 and 26), bushing (12) and washers (2, 4, 6, 10, 13, 16, 22 and 25).
(c)
Tighten the nut (3) to 10-15 pound-inches (View "C")
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747-400 MAINTENANCE MANUAL
(d)
Tighten the nut (7) to 900-1100 pound-inches (View "B").
(e)
Tighten the nut (14) to 1000-1300 pound-inches (View "D").
(f)
Tighten the nut (23) to 10-15 pound-inches (View E).
(g)
Install the hinge bolts and washers correctly (Fig. 401).
1) Use the subsequent parts for the inboard hinge (Detail D): a) One 3.173-inch long bolt b) Two 0.625-inch long bushings c) One 0.032-inch thick washer below the bolthead d) One 0.090-inch thick washer below the nut.
2) As an alternative, you can also use these parts for the inboard hinge: a) One 3.048-inch long bolt b) Two 0.490-inch long bushings c) One 0.032-inch thick washer below the bolthead d) One 0.032-inch thick washer and two 0.090-inch thick
washers below the nut.
(h)
Install the antirotation plate (21) at the inboard primary hinge.
(i)
Install the cotter pins in all the hinge bolts.
(j)
Remove the hoist equipment.
S 644-037
(2)
Lubricate the inboard aileron (AMM 12-21-16/301).
S 214-048
(3)
Make sure the top surface of the inboard aileron aligns with the top surface of the trailing edge panel.
NOTE: A maximum tolerance of 0.5 inch is permitted.
____
S 214-049
(4) Make sure the bottom surface of the inboard aileron aligns with the bottom surface of the trailing edge (TE) panel.
NOTE: A maximum of 25% of the TE span can have a tolerance of 0.12
____ inch if the average for the full span is 0.06 inch or less.
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(5) S 714-038Do a check of the inboard aileron operation: (a) Manually move the aileron through a minimum of two full cycles. (b) Make sure the aileron moves easily and moves through full travel.
(6) S 284-039Examine the adjustment and worn areas of the aileron seals: (a) Make sure the seal attach angle does not touch the aileron. (b) Make sure the seals compress 10% maximum.
(7) S 434-040Install the antirotation plates (30 and 34) if it is necessary (Fig. 401, Section A-A).
(8) S 434-041Install the reaction truss link (39). (a) Connect the reaction truss link (39) to the aileron with the dual load path bolt (40), washer (36 and 42) and nut (41). (b) Make sure the retaining ring (38) is on the bolthead. (c) Use a spanner wrench to measure the friction torque of the nut. (d) Tighten the nut (41) to 2850-3050 pound-inches more than the friction torque.
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