500 Horizontal Stabilizer to Body Center Section
Jan 20/82 Rear Spar Attach Fittings Bushing Replacement 27-41-131
Figure 802 (Sheet 2) Page 809
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
Horizontal Stabilizer to Body Center Section 500
27-41-131 Rear Spar Attach Fittings Bushing Replacement Jan 20/82
Page 810 Figure 802 (Sheet 3)
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
500 Horizontal Stabilizer to Body Center Section
Jan 20/82 Rear Spar Attach Fittings Bushing Replacement 27-41-131
Figure 802 Page 811
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
Replacement Bushing Fabrication 500
27-41-131 Figure 803 May 20/82
Page 812
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
(3)
Mask or shield structure to prevent contamination with abrasive materials during abrasive blast cleaning or with shot during shot peening.
CAUTION: FOREIGN PARTICLES MAY CAUSE CORROSION TO STRUCTURE.
(4)
Clean and deburr holes and adjacent surfaces thoroughly.
(5)
Oversize hole with Quickset reamer to 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.
(6)
Spotface forward and aft faces of lug fittings to provide seat for bushing flange to maximum depth of 0.015 inch. Spotface inner faces of clevis to provide seat for bushing flange to maximum depth of 0.015 inch. Spotface outer faces of clevis flanges to provide seat for bolt head or washer to maximum depth of 0.015 inch. Contact Boeing if corrosion still exists in lug holes or on spotfaced surfaces. Remove corrosion products from other areas of lug per Structural Repair Manual, Chapter 51. Do not use chemical removal if solution can penetrate fay surfaces. Use chemical or dry abrasive surface.
(7)
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.
(8)
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.
(9)
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 flanged bushing.
(1)
Fabricate oversize bushing per Fig. 803 for interference fit with lug or clevis inside diameter.
(2)
Shrink fit bushing in lug with wet primer. Use -230 bushing installation tool.
(3)
Secure -601 tool frame assembly to rear spar as shown with -619 potting pin installed per View 1 or View 2 at the two unaltered holes and C-clamp as shown.
(4)
Proceed to ream new bushings with -112 arbor (-111 dowel press fit into -112 arbor) and -110 shell reamer. Continue to ream bushing using -124 reamer and -128 standard reamer provided.
(5)
Hone internal diameter of bushing to diameter of 1.2530 to 1.2540 inches with machine finish 63 microinches AA. Use - 610 hone for this location.
500
Jan 20/82 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 27-41-131 Page 813
E. Machine new bushing flanges.
(1)
Remove -610 tool frame assembly from rear spar.
(2)
After completion of bushing replacement per par. D, measure and record the distance between the new bushing flange face and clevis or lug in the same marked location. Subtract the previous measurement from this new measurement to obtain the amount of material to remove from the flange.
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