fitting as shown in view 2.
3) Tighten bolts (9).
(5)
Provide hydraulic system A power (Ref AMM 27-51-0).
(6)
Retract flaps and check that seal on lower trailing edge panel contacts full span of midflap, if not:
(a)
Support outboard flap.
(b)
Disconnect flap drive torque tubes at both sides of inboard flap outboard
transmission.
(c)
Using flap drive adapter, rotate transmission input to position outboard end of flap to contact seal. Do not exceed flap jackscrew stop clearance of 170 to 190 degrees (1/2
+ 10 degrees) turn.
(d)
Connect torque tubes to transmission. Secure screws with lockwire.
(e)
Remove support from outboard flap.
(7)
Extend and retract flaps through full travel and remove hydraulic system A power (Ref AMM 27-51-0). During flap travel, check the following:
(a)
Check that flap drive screws clear all other linkage, structure, and components by
0.25 inch minimum.
(b)
Check that flap outboard drive screw end fitting enters preload pad slightly before full up flap position.
(c)
Ensure that flap inboard and outboard drive screw end fittings seat firmly against preload pads when flap is fully retracted.
(8)
Recheck flap adjustment as in step R. Ensure that all adjustments remain within limits.
(9)
Provide system A hydraulic power (Ref 27-51-0).
(10)
Position flap control lever to FLAP DOWN (40-unit) position to extend flaps.
(11)
Check flap at full down position. Check that down stops clear by at least 1/4 turn of jackscrew.
(12)
Retract flaps and check for binding, interference, or other malfunction.
(13)
Remove system A hydraulic power (Ref 27-51-0).
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Nov 15/79 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 27-51-12 Page 415
U. Check that clearance between inboard ground spoiler panel and top of midflap is per section A-A. Adjust if required (Ref 27-62-0, Speed Brake Control System).
V. With flaps in normal up position, check that bulb seal on lower forward edge of ground spoiler with respect to upper edge of foreflap is compressed 0.10 to 0.20 inch. If seal compression is not within limits adjust seal retainer to obtain compression.
W. Check that clearance between upper wing panel trailing edge and top of midflap is per section B-B. Adjust by adding or removing shims at panel attach points. Adjust panel trailing edge on outboard end by adjusting bracket.
X. Provide system A hydraulic power (Ref 27-51-0), extend flaps to 1 degree setting.
(1) Check that aft bulb seal on spoiler and fixed upper panel is in contact with foreflap. If not, install tapered filler between seat attach surface and seal to provide contact 80 percent of seal with 0.02 inch gap allowed for remainder.
Y. Extend flaps to FLAP DOWN (40-unit) position and check the following:
(1)
Check that opposite aftflaps extend symmetrically within 0.12 inch. Measure between aft edge of midflap lower skin and aftflap nose at both ends of aftflap.
(2)
If aftflap extension is not symmetrical, adjust aftflap pushrods to obtain symmetry. If pushrods are adjusted secure rod ends and recheck aftflap position per Inboard Trailing Edge Flap - Adjustment/Test.
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27-51-12 Page 416 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. Feb 15/81
Z. Check that bumper plate (Detail B, Fig. 401) did not contact skin of clearance door in nacelle fairing (Detail C, Fig. 402) at any point throughout travel in which the two were in contact. Shim nylon rub strip on clearance door per section D-D and/or bend bumper plate per Detail B, Fig. 401 as required to eliminate door skin contact.
AA. Extend and retract flaps. Check all seals and clearances during flap travel and that there is no evidence of binding or interference.
AB. Remove hydraulic system A power (Ref AMM 27-51-0 MP).
AC. Install inboard flap track fairing (Ref AMM 27-51-141 R/I).
AD. Install pan on lower surface of engine-to-wing aft fairing, access panel on rear bulkhead of engine-to-wing aft fairing and access cover on forward overhead engine-to-wing aft fairing (Ref Chapter 54, Engine-to-Wing Fairing).
AE. Adjust inboard midflap seal plate (Ref AMM 27-51-341 R/I).
AF. Install engine (Ref Chapter 71, Power Plant) or install thrust reverser (Ref Chapter 78, Thrust
Reverser). AG. Check gap between wing lower trailing edge and bottom of seal support (Section C-C, Fig. 402). If gap exceeds 0.06 inch, fill gap with aerodynamic smoother.
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