(b)
AIRPLANES WITH SB 57-1203; tighten nut 220 to 280 pound-inches.
E. Ensure that three bushings are installed in track support fitting. If not, install bushings with wet primer.
F. Raise track to align with holes in aft support fitting on rear spar. If installed, position shim between track and support fitting.
NOTE: Thickness of shim shall equal that removed during disassembly.
G. On airplanes with phenolic rub strips, clean sealant from bolt holes, coat bolts with corrosion preventive compound and install bolts with countersunk washer under head.
H. On airplanes with aluminum rub strips, clean sealant from bolt holes, coat bolts with corrosion preventive compound and install inboard bolt with torque indicating washer under bolt head and install outboard bolt with countersunk washer under bolt head.
I. Ensure that lower bushing on outboard bolt does not protrude above skin into track support fitting.
J. On airplanes with phenolic rub strips, tighten bolts as follows:
(1)
Install nuts and washers. Tighten inboard bolt 480 to 600 pound-inches. If end of bolt bottoms out on barrel nut retainer, add washer under bolt head.
(2)
Install nut and washer on outboard bolt. Tighten nut 220 to 360 pound-inches and lockwire bolt heads on inboard and outboard bolts. Check that minimum of one thread extends through nut.
K. On airplanes with aluminum rub strips, tighten bolts as follows:
(1) Install nuts and washers. Tighten inboard bolt until outer ring of torque indicating washer is no longer free to turn, (do not apply more than 1300 pound-inches). If end bolt bottoms out on barrel nut retainer, add washer under bolt head.
NOTE: Do not reuse torque indicating washer. Use new torque indicating washer before tightening bolt. If outer ring of torque indicating washer is still free to turn at 1300 pound-inches, the holes are not properly aligned.
5C8
27-51-151 Page 406 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. May 01/99
NOTE: Do not reuse torque indicating washer. Use new torque indicating washer before tightening bolt. If outer ring of torque indicating washer is still free to turn at 1300 pound-inches, the holes are not properly aligned.
(2) Install nut and washer on outboard bolt. Tighten outboard bolt 360 to 420 pound-inches and lockwire bolt heads on inboard and outboard bolts. Check that minimum of one thread extends through nut.
L. Clean area around bolt heads.
M. Apply fillet of sealant around bolt heads.
6. Restore Airplane to Normal Configuration
A. Install outboard foreflap sequencing carriage (Ref 27-51-111 R/I).
B. Install flap transmission (Ref 27-51-281 R/I).
C. Install trailing edge flaps (Ref 27-51-72 R/I).
505
May 01/99 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 27-51-151 Page 407
OUTBOARD MIDFLAP TRACKS - INSPECTION/CHECK
1. General
A. This data consists of illustrations and a wear limit chart. There is no procedure given for gaining access to the component for removal or replacement after inspection for wear. Refer to Outboard Midflap Carriage - Removal/Installation for this information.
2. Outboard Midflap Carriage Wear Limits (Fig. 601)
G18267 G21626
500 Outboard Flap Track Wear Limits
Aug 01/95 Figure 601 (Sheet 1) 27-51-151
Page 601
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
INDEX DESIGN LIMITS WEAR LIMTS REPLACE WORN REPAIR WORN REPAIR
DIAMETER MAX WEAR MAX DIAM CLEAR-
NO. PART NAME DIM MIN MAX DIM. ANCE PART PART INSTR.
1 FITTING ID 0.5613 0.5621 0.0100 X
2 BUSHING OD X
2 BUSHING ID 0.4370 0.4420 0.4470 0.0100 X
BOLT OD 0.4365 0.4370 0.4270 X
Outboard Flap Track Wear Limits 500
27-51-151 Figure 601 (Sheet 2) Apr 01/97
Page 602
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INDEX NO. PART NAME DIM. DESIGN LIMITS WEAR LIMITS REPLACE WORN PART REPAIR WORN PART REPAIR INSTR.
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