(10)
Remove electrical power, if no longer required.

500 
May 01/01  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  27-41-111 Page 501 

HORIZONTAL STABILIZER ATTACH FITTINGS - APPROVED REPAIRS
1. General
A.  Corrosion of vertical and horizontal stabilizer attachment lug bushings has been found on some airplanes. The corrosion is due to moisture collection and retention in the lugs of the attach fittings. Unchecked corrosion could result in cracked lugs or loose bushings requiring extensive unscheduled manhours and downtime to repair. This procedure is released to provide a bushing replacement procedure for individual bushings specified in SB 55-1028 if corrosion is found when inspecting bushings and lugs per the service bulletin. For replacement of vertical stabilizer bushings, refer to 55-30-11, Approved Repairs.
B.  This procedure provides special locating tooling to establish and maintain centerline location of hole in bushing being removed so that special reamers also provided can be used to ream hole in replacement bushing with identical hole centerline location as removed bushing. This is necessary because the bushings may have eccentric outer and inner diameters. Be careful when removing bolts to avoid bushing rotation. If a bushing is loose or rotates, it is necessary to accomplish the alternative bushing replacement procedure per SB 55-1028, unless the bolt hole centerline can be established. If at any time during bushing removal the bushing rotates, or it is suspected that the bushing has rotated, it is necessary to perform the alternative bushing replacement per SB 55-1028.
2.  Equipment and Materials
A.  Horizontal Stabilizer and Fin Bushing Replacement Kit - F80231
B.  Wet Primer - BMS 10-11, Type 1 (Ref 20-30-41)
C.  Sealant - BMS 5-95 (Ref 20-30-11)
3.  Replace Horizontal Stabilizer Front Spar Lug or Clevis Individual Bushing (Fig. 801)
A.  Remove horizontal stabilizer (Ref 27-41-11).
B.  Prepare tooling for reaming operation (potting of reamer bushings).
(1)  
Set up -501 frame assembly on front spar lugs or clevis so that end of frame assembly through which -508 potting pin will be installed is located at clevis or lug at which replacement bushing is to be installed.

(2)  
Align opposite end of -501 frame assembly with other end of lug or clevis and secure with -510 bolt, -218 and -505 spacers.

(3)  
Install -508 potting pin and P80-16-.8780 and P-40-16-3/8 potting bushings at lug or clevis as shown.

(4)  
Apply potting compound through port hole in -501 frame to fill in around potting bushings.

(5)  
Remove tool assembly after potting compound is cured and firmly set.

500 
Jan 20/82  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  27-41-131 Page 801 

C.  Ream oversize holes in clevis or lug.
(1)  
Remove existing defective bushing. Use CJ107 slide hammer and either -126 or -525 slide hammer adapter. If bushing is being removed from clevis, remove bushing using -125 bushing removal drive pin.

(2)  
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.

(3)  
Clean and deburr holes and adjacent surfaces thoroughly.

(4)  
Oversize hole with Quickset reamer to minimum oversize in 0.010 inch increments up to maximum allowable to achieve corrosion removal (Fig. 803). Contact Boeing if corrosion still exists.

(5)  
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.

(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
　
中國航空網 www.k6050.com
航空翻譯 www.aviation.cn
本文鏈接地址：737 AMM 飛機維護手冊 飛行操縱 FLIGHT CONTROLS 2(166)