500 Vertical Fin to Body Front Spar
Jan 20/82 Attach Fittings Bushing Replacement 55-30-11
Figure 802 (Sheet 2) Page 809
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
Vertical Fin to Body Front Spar 500
55-30-11 Attach Fittings Bushing Replacement Jan 20/82
Page 810 Figure 802 (Sheet 3)
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
500 Replacement Bushing Fabrication
Jun 20/84 Figure 803 55-30-11
Page 811
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
(4)
Oversize hole with Quickset reamer to the minimum oversize in 0.010 inch increments up to maximum allowable to achieve corrosion removal (Ref Fig. 803 for maximum bore oversize). Contact Boeing if corrosion still exists.
(5)
Spotface lug or clevis flange to remove corrosion to maximum depth of 0.015 inch. Contact Boeing if corrosion still exists. Remove corrosion products from other area of lug per Structural Repair Manual, Chapter 51. Do not use chemical removal if solution can penetrate fay surface. Use chemical or dry abrasive surface.
(6)
Shot peen holes and spotfaced surfaces as follows:
(a)
Shot peen (flap peen optional) minimum flat diameter of spot face per Overhaul Manual, Section 20-10-03. On aluminum parts, use shot number 230 to 550, intensity 0.014A, coverage 2.0. On steel parts, use shot number 170 to 460, intensity 0.016A, coverage 2.0.
(b)
Shot peen (flap peen optional) hole in clevis or lug per Overhaul Manual, Section 20-10-03. For aluminum parts, use shot number 230 to 550, intensity 0.014A, coverage 2.0. For steel parts, use shot number 170 to 460, intensity 0.016A, coverage 2.0.
(c)
Hone inside diameter maximum of 0.0004 inch with 63 microinch finish to achieve final hole size.
(7)
Finish hole of steel parts with two coats of primer or chemically treat hole in aluminum parts to meet requirements of MIL-C-5541 (colored film) and apply one coat of primer. Allow to dry one hour minimum.
(8)
Finish spotface and reworked surfaces of lugs (except holes) with manual application of colored chemical coating per BAC5719 and apply two coats of primer.
D. Ream inside diameter of new bushing (Section A-A).
(1)
Fabricate oversize bushing per Fig. 803 for interference fit with lug or clevis.
(2)
Install new bushing, shrink fit, with wet primer. Use -130 bushing installation tool.
(3)
Secure -201 tool frame assembly to front spar with C-clamps and with -204 clamping pin and -215 and -218 spacers as shown in section A-A.
(4)
Ream bushings from aft side of spar with -208 arbor, with -207 dowel press fit into -208, and -206 shell reamer. Continue to ream bushing using -220 reamer and -217 standard reamers provided.
(5)
Hone internal diameter of bushing to 0.8780 to 0.8790 inch with machine finish 63 microinches AA.
E. Seal bushing installation
(1) Fill void at each end of bushing with sealant.
F. Install vertical stabilizer (fin) (55-30-0).
500
55-30-11 Page 812 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. Jan 20/82
DORSAL FIN - REMOVAL/INSTALLATION
1. Remove Dorsal Fin
A. Open front spar access doors 9503 and 9504 (Ref Access Doors and Panels, Chapter 12).
B. Remove attachment bolts at aft end of fin (Fig. 401).
C. Open forward access door in aft lowered ceiling.
D. Remove section of air conditioning distribution duct above access door (Ref Passenger Cabin Conditioned Air Distribution System, Chapter 21).
E. Open entry light lens on aft center portion of aft lowered ceiling.
F. Remove entry light fixture by removing attaching screws.
G. Remove insulation blankets within center portion of aft lowered ceiling to gain access to dorsal fin attachment bolts (Ref Ceiling Insulation, Chapter 25).
H. Remove dorsal fin attachment bolts.
NOTE: To facilitate installation, note type and location of bolts.
I. Lift dorsal fin away from fuselage.
2. Install Dorsal Fin
A. Position dorsal fin on fuselage.
B. Install attachment bolts with pressure fillet sealant. For sealant application refer to Seals and Sealing, Chapter 51.
C. Check gaps and mismatch tolerances as shown in Fig. 401.
D. Replace front spar access door 9503 and 9504.
E. Replace insulation blankets, air conditioning distribution duct section, and entry light fixture.
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