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767 MAINTENANCE MANUAL

AWAS
~¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼ ¦ PAGE DATE CODE ¦ PAGE DATE CODE ¦ PAGE DATE CODE ¦ ¦ ¦ ¦ ¦ ¦ ¦57-05-05 ¦57-31-01 ¦ ¦CHAPTER 57 TAB ¦ 201 DEC 22/09 01 ¦ 401 APR 22/01 01 ¦ ¦ ¦ 202 AUG 22/09 01 ¦ 402 APR 22/02 01 ¦ ¦WINGS ¦ 203 AUG 22/09 01 ¦ 403 APR 22/02 01 ¦ ¦ ¦ 204 AUG 22/09 01 ¦ 404 BLANK ¦ ¦EFFECTIVE PAGES ¦ 205 AUG 22/09 01 ¦ ¦ ¦SEE LAST PAGE OF LIST FOR ¦ 206 AUG 22/09 01 ¦57-41-56 ¦ ¦NUMBER OF PAGES ¦ 207 AUG 22/09 01 ¦ 401 APR 22/05 09 ¦ ¦ ¦ 208 AUG 22/09 01 ¦ 402 AUG 22/01 01 ¦ ¦ ¦ 209 AUG 22/09 01 ¦ 403 APR 22/09 03 ¦ ¦57-CONTENTS ¦ 210 AUG 22/09 03 ¦ 404 APR 22/09 03 ¦ ¦ 1 DEC 22/09 AWW ¦ 211 AUG 22/09 03 ¦ 405 DEC 22/08 02 ¦ ¦ 2 APR 22/09 AWW ¦ 212 AUG 22/09 03 ¦ 406 DEC 22/08 09 ¦ ¦ ¦ ¦ ¦ ¦57-00-00 ¦57-05-06 ¦57-41-57 ¦ ¦ 1 DEC 22/06 01 ¦ 201 DEC 22/09 01 ¦ 401 APR 22/03 01 ¦ ¦ 2 DEC 22/01 01 ¦ 202 AUG 22/09 01 ¦ 402 AUG 22/08 02 ¦ ¦ 3 FEB 10/94 01 ¦ 203 AUG 22/09 01 ¦ 403 APR 22/03 01 ¦ ¦ 4 AUG 22/99 01 ¦ 204 AUG 22/09 01 ¦ 404 AUG 22/08 02 ¦ ¦ 5 AUG 22/99 02 ¦ 205 AUG 22/09 01 ¦ 405 AUG 22/08 02 ¦ ¦ 6 BLANK ¦ 206 AUG 22/09 01 ¦ 406 AUG 22/08 02 ¦ ¦ ¦ 207 AUG 22/09 01 ¦ 407 AUG 22/08 01 ¦ ¦57-05-03 ¦ 208 AUG 22/09 01 ¦ 408 BLANK ¦ ¦ 201 DEC 22/09 03 ¦ 209 AUG 22/09 01 ¦ ¦ ¦ 202 AUG 22/09 06 ¦ 210 AUG 22/09 01 ¦57-41-58 ¦ ¦ 203 AUG 22/09 06 ¦ 211 AUG 22/09 01 ¦ 401 AUG 22/08 03 ¦ ¦ 204 AUG 22/09 06 ¦ 212 AUG 22/09 01 ¦ 402 AUG 22/08 03 ¦ ¦ 205 AUG 22/09 05 ¦ 213 AUG 22/09 01 ¦ 403 DEC 22/09 02 ¦ ¦ 206 AUG 22/09 05 ¦ 214 DEC 22/09 03 ¦ 404 DEC 22/09 04 ¦ ¦ 207 AUG 22/09 06 ¦ 215 DEC 22/09 04 ¦ 405 DEC 22/09 04 ¦ ¦ 208 AUG 22/09 05 ¦ 216 BLANK ¦ 406 AUG 22/08 04 ¦ ¦ 209 AUG 22/09 06 ¦ ¦ 407 DEC 22/09 03 ¦ ¦ 210 AUG 22/09 06 ¦57-05-07 ¦ 408 DEC 22/09 02 ¦ ¦ 211 AUG 22/09 07 ¦ 201 AUG 22/09 02 ¦ 409 AUG 22/07 02 ¦ ¦ 212 AUG 22/09 08 ¦ 202 AUG 22/09 02 ¦ 410 DEC 22/07 02 ¦ ¦ 213 AUG 22/09 08 ¦ 203 AUG 22/09 02 ¦ 411 APR 22/08 02 ¦ ¦ 214 AUG 22/09 08 ¦ 204 BLANK ¦ 412 APR 22/08 02 ¦ ¦ 215 AUG 22/09 08 ¦ ¦ 413 APR 22/08 03 ¦ ¦ 216 BLANK ¦57-10-01 ¦ 414 AUG 22/07 03 ¦ ¦ ¦ 201 APR 22/05 01 ¦ ¦ ¦57-05-04 ¦ 202 APR 22/05 01 ¦57-41-59 ¦ ¦ 201 DEC 22/09 01 ¦ ¦ 401 APR 22/99 05 ¦ ¦ 202 AUG 22/09 01 ¦57-20-01 ¦ 402 AUG 10/90 01 ¦ ¦ 203 AUG 22/09 01 ¦ 201 APR 22/05 01 ¦ 403 APR 22/09 02 ¦ ¦ 204 AUG 22/09 02 ¦ 202 APR 22/05 01 ¦ 404 DEC 22/08 01 ¦ ¦ 205 AUG 22/09 02 ¦ 203 APR 22/05 01 ¦ 405 DEC 22/08 04 ¦ ¦ 206 AUG 22/09 03 ¦ 204 APR 22/05 01 ¦ 406 BLANK ¦ ¦ 207 AUG 22/09 01 ¦ 205 APR 22/05 01 ¦ ¦ ¦ 208 AUG 22/09 01 ¦ 206 APR 22/05 01 ¦57-41-65 ¦ ¦ 209 AUG 22/09 01 ¦ 207 APR 22/05 01 ¦ 401 AUG 10/91 01 ¦ ¦ 210 AUG 22/09 01 ¦ 208 BLANK ¦ 402 APR 22/99 01 ¦ ¦ 211 AUG 22/09 01 ¦ ¦ 403 AUG 10/91 01 ¦ ¦ 212 AUG 22/09 08 ¦57-25-01 ¦ 404 AUG 22/08 01 ¦ ¦ 213 AUG 22/09 06 ¦ 801 DEC 22/06 02 ¦ 405 AUG 22/08 01 ¦ ¦ 214 BLANK ¦ 802 DEC 22/06 02 ¦ 406 BLANK ¦ ¦ ¦ ¦ ¦ ¦ ¦ ¦ ¦ ¦ ¦ ¦ ¦ ¦ ¦ ¦ ¦ ²¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼…¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼…¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¹

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CHAPTER 57 EFFECTIVE PAGES PAGE 1 CONTINUED

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767 MAINTENANCE MANUAL

AWAS
~¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼ ¦ PAGE DATE CODE ¦ PAGE DATE CODE ¦ PAGE DATE CODE ¦ ¦ ¦ ¦ ¦ ¦57-50-01 ¦57-54-04 ¦ ¦ ¦ 201 APR 22/05 01 ¦ 401 APR 22/02 01 ¦ ¦ ¦ 202 APR 22/05 01 ¦ 402 APR 22/99 01 ¦ ¦ ¦ 203 APR 22/05 01 ¦ 403 DEC 22/99 01 ¦ ¦ ¦ 204 APR 22/05 01 ¦ 404 APR 22/00 01 ¦ ¦ ¦ ¦ 405 DEC 10/98 01 ¦ ¦ ¦57-51-03 ¦ 406 DEC 10/98 01 ¦ ¦ ¦ 801 APR 22/01 01 ¦ 407 DEC 22/99 01 ¦ ¦ ¦ 802 AUG 22/01 01 ¦ 408 DEC 22/99 01 ¦ ¦ ¦ 803 AUG 22/09 02 ¦ 409 APR 22/00 02 ¦ ¦ ¦ 804 AUG 22/01 01 ¦ 410 APR 22/00 01 ¦ ¦ ¦ 805 DEC 22/99 01 ¦ 411 APR 22/00 01 ¦ ¦ ¦ 806 APR 22/00 01 ¦ 412 DEC 22/99 01 ¦ ¦ ¦ 807 APR 22/00 01 ¦ ¦ ¦ ¦ 808 BLANK ¦57-54-05 ¦ ¦ ¦ ¦ 401 DEC 22/05 01 ¦ ¦ ¦57-51-10 ¦ 402 DEC 22/05 02 ¦ ¦ ¦ 401 AUG 22/99 01 ¦ 403 APR 22/06 04 ¦ ¦ ¦ 402 FEB 10/92 01 ¦ 404 DEC 22/05 04 ¦ ¦ ¦ 403 AUG 22/99 01 ¦ 405 AUG 22/01 01 ¦ ¦ ¦ 404 AUG 10/90 01 ¦ 406 APR 22/03 01 ¦ ¦ ¦ ¦ 407 AUG 22/01 01 ¦ ¦ ¦57-51-10 ¦ 408 APR 22/06 04 ¦ ¦ ¦ 501 APR 22/08 01 ¦ 409 APR 22/06 05 ¦ ¦ ¦ 502 APR 22/08 02 ¦ 410 DEC 22/05 02 ¦ ¦ ¦ 503 APR 22/08 02 ¦ 411 DEC 22/05 03 ¦ ¦ ¦ 504 APR 22/08 02 ¦ 412 APR 22/06 04 ¦ ¦ ¦ 505 APR 22/08 01 ¦ 413 APR 22/06 02 ¦ ¦ ¦ 506 APR 22/08 01 ¦ 414 BLANK ¦ ¦ ¦ ¦ ¦ ¦ ¦57-51-11 ¦57-54-06 ¦ ¦ ¦ 401 AUG 10/90 01 ¦ 401 AUG 22/06 02 ¦ ¦ ¦ 402 AUG 10/90 01 ¦ 402 AUG 22/03 01 ¦ ¦ ¦ 403 NOV 10/90 01 ¦ 403 AUG 22/03 01 ¦ ¦ ¦ 404 AUG 10/90 01 ¦ 404 AUG 22/03 01 ¦ ¦ ¦ ¦ 405 AUG 22/07 01 ¦ ¦ ¦57-53-01 ¦ 406 AUG 22/03 01 ¦ ¦ ¦ 401 FEB 10/91 01 ¦ 407 AUG 22/06 01 ¦ ¦ ¦ 402 FEB 10/91 01 ¦ 408 AUG 22/03 02 ¦ ¦ ¦ 403 DEC 22/04 01 ¦ 409 AUG 22/06 02 ¦ ¦ ¦ 404 DEC 22/04 01 ¦ 410 AUG 22/07 02 ¦ ¦ ¦ 405 DEC 22/04 01 ¦ 411 AUG 22/06 03 ¦ ¦ ¦ 406 BLANK ¦ 412 AUG 22/03 01 ¦ ¦ ¦ ¦ ¦ ¦ ¦57-54-01 ¦ ¦ ¦ ¦ 401 AUG 10/92 01 ¦ ¦ ¦ ¦ 402 FEB 10/93 01 ¦ ¦ ¦ ¦ 403 APR 22/99 01 ¦ ¦ ¦ ¦ 404 AUG 10/92 01 ¦ ¦ ¦ ¦ 405 APR 22/99 01 ¦ ¦ ¦ ¦ 406 DEC 22/01 01 ¦ ¦ ¦ ¦ 407 APR 22/99 01 ¦ ¦ ¦ ¦ 408 APR 22/99 01 ¦ ¦ ¦ ¦ 409 AUG 22/07 01 ¦ ¦ ¦ ¦ 410 DEC 22/99 01 ¦ ¦ ¦ ¦ 411 DEC 22/99 01 ¦ ¦ ¦ ¦ 412 BLANK ¦ ¦ ¦ ¦ ¦ ¦ ¦ ¦ ¦ ¦ ¦ ²¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼…¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼…¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¹

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CHAPTER 57 - WINGS _________________ TABLE OF CONTENTS Chapter Section _______ Subject

767 MAINTENANCE MANUAL

_______ Subject

____ Page

___________ Effectivity

_____ WINGS Description and Operation General Outer Wing Flight Control Surfaces Structure Wing Attachment Wing Center Section WING INSPECTION Maintenance Practices ___________ CENTER WING CORROSION PREVENTION IN CENTER WING SECTION Maintenance Practices __________ OUTER WING CORROSION PREVENTION IN OUTER WING Maintenance Practices VORTEX GENERATOR GENERATORS - VORTEX Approved Repairs ________ WING TIP WING TIP WINGTIP Removal/Installation _____________________________________ LEADING EDGE AND LEADING EDGE DEVICES LEADING EDGE DOOR - OUTBOARD WING LEADING EDGE SLAT ACTUATOR ROD SEAL Removal/Installation DOOR - THERMAL ANTI-ICE (TAI) Removal/Installation DOORS - INBOARD LEADING EDGE SUPPORT LINK Removal/Installation PANEL - WING LEADING EDGE PRESSURE RELIEF Removal/Installation

57-00-00 1 1 1 2 1 3 2 57-05-03 201 57-10-00 57-10-01 201 57-20-00 57-20-01 201 57-25-00 57-25-01 801 57-30-00 57-31-00 57-31-01 401 57-40-00 57-41-00 57-41-56 401 57-41-58 401 57-41-59 401 57-41-57 401 ALL ALL ALL ALL ALL ALL ALL ALL ALL ALL

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CHAPTER 57 - WINGS _________________ TABLE OF CONTENTS Chapter Section _______ Subject 57-41-65

767 MAINTENANCE MANUAL

_______ Subject PLATE - LEADING EDGE MAIN TRACK BEARING Removal/Installation _______________________________ TRAILING EDGE AND TRAILING EDGE _______ DEVICES CORROSION PREVENTION IN WING TRAILING EDGE Maintenance Practices TRAILING EDGE CONDUCTING FRAME - AILERON Approved Repairs PANELS - TRAILING EDGE Removal/Installation Adjustment/Test SEAL - TRAILING EDGE (FORWARD OF OUTBOARD AILERON) Removal/Installation VORTEX GENERATOR GENERATOR - OUTBOARD FLAP VORTEX Removal/Installation [*] AIRPLANES WITH VORTEX GENERATORS LANDING GEAR SUPPORT LINK - MAIN LANDING GEAR SUPPORT Removal/Installation MAIN LANDING GEAR STRUT SWIVEL FITTING Removal/Installation MAIN LANDING GEAR SUPPORT BEAMREMOVAL/INSTALLATION Removal/Installation MLG SUPPORT BEAM LOAD PLATES REMOVAL/INSTALLATION Removal/Installation

____ Page

___________ Effectivity

401 57-50-00 57-50-01 201 57-51-00 57-51-03 801 57-51-10 401 501 57-51-11 401 57-53-00 57-53-01 401 ON OUTBOARD FLAPS 57-54-00 57-54-01 401 57-54-06 401 57-54-04 401 57-54-05 401

ALL

ALL

ALL ALL ALL

ALL

[*]

ALL

ALL

ALL

ALL

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767 MAINTENANCE MANUAL

1.

_________________________________ WINGS - DESCRIPTION AND OPERATION _______ General A. The wing surfaces develop aerodynamic forces which support the airplane in flight. The wing stores fuel, houses the fuel system equipment, supports the engines, and contains the flaps, spoilers, and ailerons. __________ Outer Wing (Fig. 1) A. Structure (1) Location references on the wing are indicated by a distance, in inches, from a base point along a specific reference line. Wing stations (WS) are measured perpendicular along the rear spar. Wing buttock lines (WBL) are measured parallel from the fuselage centerline. (2) The primary structures of the wing are aluminum. They are front and rear spars, upper and lower spar chords, webs, skin panels and stiffeners, and ribs. The upper and lower spar chord extrusions attach to the front and rear spar webs. Chords, stiffeners, and webs make up the ribs. Conventional ribs are spaced through the entire wing. Shear tie ribs distribute specific loads to the wing frame. Fuel baffle ribs minimize fuel slosh in the fuel tanks. Vapor seal ribs are sealed to keep fuel vapor from leaking into electrical or mechanical equipment areas. Tank end ribs are sealed and form the ends of the fuel tanks. Side-of-body ribs join the outboard wing sections to the center wing section. Upper and lower aluminum skin splice plates join the skin panels. Upper and lower aluminum stringers strengthen the skin panels. The landing gear is supported by the landing gear support beam and rear spar. (3) The wing secondary structure does not carry primary loads. The secondary structure supports aerodynamic fairings or skins, flight control surfaces, and control mechanisms. The secondary structures of the wing are the leading edge, trailing edge, and wingtip. The leading edge is cantilevered forward from the front spar. The leading edge is made of ribs covered by skin panels. The leading edge slats attach to the leading edge. The trailing edge is cantilevered aft from the rear spar. The trailing edge supports the flaps, ailerons, and spoilers. The wingtip is an aerodynamic fairing covering the outboard ends of the wing. Navigation equipment attaches to each wingtip. Non-structural aluminum access doors are in the wing exterior structure. The access doors allow inspection, maintenance, and repair of internal wing structure, fuel tanks, and system components.

2.

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(4) B.

767 MAINTENANCE MANUAL

Six safety harness attach points are located on the upper surface of the wing to assist maintenance personnel. Flight Control Surfaces (1) Trailing edge flight control surfaces have skin panels made of advanced composites. Structural ribs are made of aluminum. (2) The outboard ailerons are the only balance critical flight control surfaces. All other flight control surfaces, however, do have operational balance limits. These limits are listed in SRM 51-60-11. ____ NOTE: A record should be kept of all painting and repairs done to flight control surfaces to ensure that the operational balance moment is not exceeded. Flight control surfaces which exceed the operational balance limits may flutter during flight. Refer to SRM 51-60-00 for operational balance moment determination.

3.

___________________ Wing Center Section (Fig. 2) A. The center wing section is enclosed within the fuselage. The center wing section consists of upper and lower skin panels and front and rear spars. Other structural members are upper and lower spar chord extrusions, stiffeners, webs, and floor beams. Throughout the center wing section, the skin panels are reinforced by spanwise stringers and the spars are reinforced by vertical stiffeners. Spanwise beams are made of stiffeners and webs. Floor beams are made of chords, stiffeners, and webs. B. The keel beam distributes load due to fuselage bending to the lower wing surface. Primary load members are two aluminum extruded chords attached vertically to the lower wing surface by chem milled and stiffened aluminum webs. In addition, there is a series of lattice forged members between the two chords, and small stabilizing bulkheads to the wing lower surface at the front spar, the rear spar and spanwise beam No. 2. The webs are attached to the wing surface with aluminum members. A chem milled and stiffened horizontal web also ties the base of the two chords together. This web has two access holes for inspection of the keel beam box interior.

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767 MAINTENANCE MANUAL

4.

C. Refer to AMM 28-11-00/001 for the fuel tank configuration. _______________ Wing Attachment (Fig. 2) A. The wing center section attaches to the fuselage with the primary splice fittings, lower side-of-body splice, and upper side-of-body splice. The primary splice fittings are at the front and rear wing spars. The splice fittings are vertically mounted modified tee sections machined from forged aluminum alloy. The lower side-of-body splice is a double shear skin splice. The splice is an aluminum chord and external aluminum splice plate which drains to a low point. The upper side of body splice is an aluminum chord.

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767 MAINTENANCE MANUAL

SLAT (6 LOCATIONS)

WS 226 C L NAC

SWB 3 SWB 2 SWB 1

FRONT SPAR WS 0 UPPER SKIN SPLICE WS 213 LOWER SKIN SPLICE TANK END RIB (EXAMPLE) WS 990 WS 1075 WBL 355 REAR SPAR INBOARD AILERON OUTBOARD FLAP WBL 710 OUTBOARD AILERON WBL 929 SPOILER (6 LOCATIONS) WBL 289 WBL 98 INBOARD FLAP BBL 0 WBL 0 LANDING GEAR TRUNNION

Wing Structure Figure 1
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767 MAINTENANCE MANUAL
WING CENTER SECTION SEE A

SAFETY LINE ATTACH POINT (6 LOCATIONS)

FWD

WING SAFETY LINE ATTACH POINTS (LEFT WING IS SHOWN, RIGHT WING IS OPPOSITE)

FLOOR BEAM

BS 1000

BS 790 UPPER SIDE-OF-BODY SPLICE WL 189 REAR SPAR SPLICE FITTINGS BS 950 FRAME LOWER SIDE-OF-BODY SPLICE CHORD SPANWISE BEAM (3 LOCATIONS) BULKHEAD SEGMENT ACCESS FWD WBL 98 FRONT SPAR SPLICE FITTING

WING CENTER SECTION VERTICAL KEEL WEBS KEEL CHORDS

FRONT SPAR

WING CENTER SECTION A Wing Center Section and Safety Line Attach Points Figure 2
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767 MAINTENANCE MANUAL

_______________________________________ WING INSPECTION - MAINTENANCE PRACTICES

1.

TASK 57-05-03-212-809 _____________________________________ Wing Center Section Fuel Tank Wet Bay A. General (1) This procedure is a scheduled maintenance task. B. Inspection S 212-009 Do the inspection.

(1)

2.

TASK 57-05-03-212-810 _____________________________________ Wing Center Section Fuel Tank Wet Bay A. General (1) This procedure is a scheduled maintenance task. B. Inspection S 212-010 Do the inspection.

(1)

3.

TASK 57-05-03-212-811 _____________________________________ Wing Center Section Fuel Tank Wet Bay A. General (1) This procedure is a scheduled maintenance task. B. Inspection S 212-011 Do the inspection.

(1)

4.

TASK 57-05-03-212-812 _____________________________________ Wing Center Section Fuel Tank Wet Bay A. General (1) This procedure is a scheduled maintenance task. B. Inspection S 212-012 Do the inspection.

(1)

5.

TASK 57-05-03-212-813 _____________________________________ Wing Center Section Fuel Tank Wet Bay A. General (1) This procedure is a scheduled maintenance task.

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B. Inspection S 212-013 Do the inspection.

767 MAINTENANCE MANUAL

(1)

6.

TASK 57-05-03-212-814 _______________________________________ Wing Center Section Lower Surface BL 70 A. General (1) This procedure is a scheduled maintenance task. B. Inspection S 212-014 Do the inspection.

(1)

7.

TASK 57-05-03-212-816 _________________________ Wing Center Section Lower A. General (1) This procedure is a scheduled maintenance task. B. Inspection S 212-016 Do the inspection.

(1)

8.

TASK 57-05-03-212-818 __________________ Wing Exterior Left A. General (1) This procedure is a scheduled maintenance task. B. Inspection S 212-018 Do the inspection.

(1)

9.

TASK 57-05-03-212-819 Wing Exterior Left __________________ A. General (1) This procedure is a scheduled maintenance task. B. Inspection S 212-019 Do the inspection.

(1)

TASK 57-05-03-212-820 10. Nacelle Strut No. 1 Aft Upper Spar __________________________________ A. General (1) This procedure is a scheduled maintenance task.

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B. Inspection S 212-020 Do the inspection.

767 MAINTENANCE MANUAL

(1)

TASK 57-05-03-212-821 11. Nacelle Strut No. 1 Upper Link ______________________________ A. General (1) This procedure is a scheduled maintenance task. B. Inspection S 212-021 Do the inspection.

(1)

TASK 57-05-03-212-822 12. Slat 6 Link Brace and Actuator Support ______________________________________ A. General (1) This procedure is a scheduled maintenance task. B. Inspection S 212-022 Do the inspection.

(1)

TASK 57-05-03-212-823 13. Left Wing Fixed Leading Edge Structures _______________________________________ A. General (1) This procedure is a scheduled maintenance task. B. Inspection S 212-023 Do the inspection.

(1)

TASK 57-05-03-212-824 14. Left Wing Fixed Leading Edge Structures _______________________________________ A. General (1) This procedure is a scheduled maintenance task. B. Inspection S 212-024 Do the inspection.

(1)

TASK 57-05-03-212-825 15. Nacelle Strut No. 1 Upper Link ______________________________ A. General (1) This procedure is a scheduled maintenance task.

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B. Inspection S 212-025 Do the inspection.

767 MAINTENANCE MANUAL

(1)

TASK 57-05-03-212-826 16. Leading Edge Slats Interior Structure _____________________________________ A. General (1) This procedure is a scheduled maintenance task. B. Inspection S 212-026 Do the inspection.

(1)

TASK 57-05-03-212-827 17. Left Slat/Nacelle Seal Kreuger Flap ___________________________________ A. General (1) This procedure is a scheduled maintenance task. B. Inspection S 212-027 Do the inspection.

(1)

TASK 57-05-03-212-828 18. Left Leading Edge Exterior __________________________ A. General (1) This procedure is a scheduled maintenance task. B. Inspection S 212-028 Do the inspection.

(1)

TASK 57-05-03-212-829 19. No. 4 Slat Main and Auxiliary Tracks ____________________________________ A. General (1) This procedure is a scheduled maintenance task. B. Inspection S 212-029 Do the inspection.

(1)

TASK 57-05-03-212-830 20. Left Wing Inspar Lower Surface Exterior _______________________________________ A. General (1) This procedure is a scheduled maintenance task.

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B. Inspection S 212-030 Do the inspection.

767 MAINTENANCE MANUAL

(1)

TASK 57-05-03-212-831 21. Left Wing Inspar Lower Surface ______________________________ A. General (1) This procedure is a scheduled maintenance task. B. Inspection S 212-031 Do the inspection.

(1)

TASK 57-05-03-212-832 22. Left Wing Inspar Upper Surface ______________________________ A. General (1) This procedure is a scheduled maintenance task. B. Inspection S 212-032 Do the inspection.

(1)

TASK 57-05-03-212-833 23. Left Wing Inspar Upper Surface ______________________________ A. General (1) This procedure is a scheduled maintenance task. B. Inspection S 212-033 Do the inspection.

(1)

TASK 57-05-03-212-834 24. Left Wing Inspar Lower Surface ______________________________ A. General (1) This procedure is a scheduled maintenance task. B. Inspection S 212-034 Do the inspection.

(1)

TASK 57-05-03-212-835 25. Left Wing Inspar Upper Surface ______________________________ A. General (1) This procedure is a scheduled maintenance task.

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B. Inspection S 212-035 Do the inspection.

767 MAINTENANCE MANUAL

(1)

TASK 57-05-03-212-836 26. Left Wing Lower Surface Spanwise Splice _______________________________________ A. General (1) This procedure is a scheduled maintenance task. B. Inspection S 212-036 Do the inspection.

(1)

TASK 57-05-03-212-837 27. Left Wing Lower Surface Access Hole Cutouts ___________________________________________ A. General (1) This procedure is a scheduled maintenance task. B. Inspection S 212-037 Do the inspection.

(1)

TASK 57-05-03-212-838 28. Left Wing Lower Surface/Side of Box Rib _______________________________________ A. General (1) This procedure is a scheduled maintenance task. B. Inspection S 212-038 Do the inspection.

(1)

TASK 57-05-03-212-839 29. Left Wing Rear Spar Web and Lower Chord _______________________________________ A. General (1) This procedure is a scheduled maintenance task. B. Inspection S 212-039 Do the inspection.

(1)

TASK 57-05-03-212-840 30. Left Wing Rear Spar Lower Chord and Ribs 1, 3 _____________________________________________ A. General (1) This procedure is a scheduled maintenance task.

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05 Page 206 Aug 22/09

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A
B. Inspection S 212-040 Do the inspection.

767 MAINTENANCE MANUAL

(1)

TASK 57-05-03-212-841 31. Left Wing Side of Body Rib Web ______________________________ A. General (1) This procedure is a scheduled maintenance task. B. Inspection S 212-041 Do the inspection.

(1)

TASK 57-05-03-212-842 32. Side of Body Rib Lower Chord Cutouts ____________________________________ A. General (1) This procedure is a scheduled maintenance task. B. Inspection S 212-042 Do the inspection.

(1)

TASK 57-05-03-212-843 33. Left Wing Main Tank ___________________ A. General (1) This procedure is a scheduled maintenance task. B. Inspection S 212-043 Do the inspection.

(1)

TASK 57-05-03-212-844 34. Left MLG Trunnion Backup Structure __________________________________ A. General (1) This procedure is a scheduled maintenance task. B. Inspection S 212-044 Do the inspection.

(1)

TASK 57-05-03-212-845 35. Left MLG Beam Backup Structure ______________________________ A. General (1) This procedure is a scheduled maintenance task.

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57-05-03
06 Page 207 Aug 22/09

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A
B. Inspection S 212-045 Do the inspection.

767 MAINTENANCE MANUAL

(1)

TASK 57-05-03-212-846 36. Left Wing Nacelle Strut Support Backup ______________________________________ A. General (1) This procedure is a scheduled maintenance task. B. Inspection S 212-046 Do the inspection.

(1)

TASK 57-05-03-212-847 37. Left Wing Lower Spar Chords ___________________________ A. General (1) This procedure is a scheduled maintenance task. B. Inspection S 212-047 Do the inspection.

(1)

TASK 57-05-03-212-848 38. Left Wing Lower Spanwise Splice Stringers _________________________________________ A. General (1) This procedure is a scheduled maintenance task. B. Inspection S 212-048 Do the inspection.

(1)

TASK 57-05-03-212-849 39. Left Wing Lower Surface Access Hole Cutouts ___________________________________________ A. General (1) This procedure is a scheduled maintenance task. B. Inspection S 212-049 Do the inspection.

(1)

TASK 57-05-03-212-850 40. Nacelle Strut No. 1 Backup Structure ____________________________________ A. General (1) This procedure is a scheduled maintenance task.

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57-05-03
05 Page 208 Aug 22/09

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A
B. Inspection S 212-050 Do the inspection.

767 MAINTENANCE MANUAL

(1)

TASK 57-05-03-212-851 41. Left Wing Spanwise Splice Stringer L-15 _______________________________________ A. General (1) This procedure is a scheduled maintenance task. B. Inspection S 212-051 Do the inspection.

(1)

TASK 57-05-03-212-852 42. Left Wing Front Spar Lower Chord Ribs 7, 9 __________________________________________ A. General (1) This procedure is a scheduled maintenance task. B. Inspection S 212-052 Do the inspection.

(1)

TASK 57-05-03-212-854 43. Left Trailing Edge Flap Support Backup Structure ________________________________________________ A. General (1) This procedure is a scheduled maintenance task. B. Inspection S 212-054 Do the inspection.

(1)

TASK 57-05-03-212-855 44. Left Wing Outboard Dry Bay __________________________ A. General (1) This procedure is a scheduled maintenance task. B. Inspection S 212-055 Do the inspection.

(1)

TASK 57-05-03-212-857 45. Wingtip and Outboard Side of WBL 929 Rib ________________________________________ A. General (1) This procedure is a scheduled maintenance task.

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57-05-03
06 Page 209 Aug 22/09

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A
B. Inspection S 212-057 Do the inspection.

767 MAINTENANCE MANUAL

(1)

TASK 57-05-03-212-859 46. Left Wing Trailing Edge Support Structure and Rear Spar _______________________________________________________ A. General (1) This procedure is a scheduled maintenance task. B. Inspection S 212-059 Do the inspection.

(1)

TASK 57-05-03-212-860 47. Upper Wing/Side of Body Splice ______________________________ A. General (1) This procedure is a scheduled maintenance task. B. Inspection S 212-060 Do the inspection.

(1)

TASK 57-05-03-212-861 48. Left Wing Trailing Edge _______________________ A. General (1) This procedure is a scheduled maintenance task. B. Inspection S 212-061 Do the inspection.

(1)

TASK 57-05-03-212-862 49. Left Main Gear Drag Brace and MLG Beam ______________________________________ A. General (1) This procedure is a scheduled maintenance task. B. Inspection S 212-062 Do the inspection.

(1)

TASK 57-05-03-212-863 50. Left Wing Trailing Edge _______________________ A. General (1) This procedure is a scheduled maintenance task.

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06 Page 210 Aug 22/09

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A
B. Inspection S 212-063 Do the inspection.

767 MAINTENANCE MANUAL

(1)

TASK 57-05-03-212-864 51. Left Wing Spoilers __________________ A. General (1) This procedure is a scheduled maintenance task. B. Inspection S 212-064 Do the inspection.

(1)

TASK 57-05-03-212-865 52. Left Wing Inboard Trailing Edge Flap Box ________________________________________ A. General (1) This procedure is a scheduled maintenance task. B. Inspection S 212-065 Do the inspection.

(1)

TASK 57-05-03-212-866 53. Left Wing Inboard Trailing Edge Flap Box ________________________________________ A. General (1) This procedure is a scheduled maintenance task. B. Inspection S 212-066 Do the inspection.

(1)

TASK 57-05-03-212-867 54. Left Inboard Trailing Edge Flap Torque Tube ___________________________________________ A. General (1) This procedure is a scheduled maintenance task. B. Inspection S 212-067 Do the inspection.

(1)

TASK 57-05-03-212-869 55. Left Wing Inboard Trailing Edge Flap ____________________________________ A. General (1) This procedure is a scheduled maintenance task.

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07 Page 211 Aug 22/09

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A
B. Inspection S 212-069 Do the inspection.

767 MAINTENANCE MANUAL

(1)

TASK 57-05-03-212-870 56. Left Inboard Aileron Interior _____________________________ A. General (1) This procedure is a scheduled maintenance task. B. Inspection S 212-070 Do the inspection.

(1)

TASK 57-05-03-212-871 57. Left Inboard Aileron ____________________ A. General (1) This procedure is a scheduled maintenance task. B. Inspection S 212-071 Do the inspection.

(1)

TASK 57-05-03-212-872 58. Left Inboard Aileron ____________________ A. General (1) This procedure is a scheduled maintenance task. B. Inspection S 212-072 Do the inspection.

(1)

TASK 57-05-03-212-873 59. Left Inboard Aileron ____________________ A. General (1) This procedure is a scheduled maintenance task. B. Inspection S 212-073 Do the inspection.

(1)

TASK 57-05-03-212-874 60. Wing Trailing Edge Support Structure/Rear Spar ______________________________________________ A. General (1) This procedure is a scheduled maintenance task.

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08 Page 212 Aug 22/09

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A
B. Inspection S 212-074 Do the inspection.

767 MAINTENANCE MANUAL

(1)

TASK 57-05-03-212-875 61. Left Wing Outboard Trailing Edge Flap Box _________________________________________ A. General (1) This procedure is a scheduled maintenance task. B. Inspection S 212-075 Do the inspection.

(1)

TASK 57-05-03-212-876 62. Left Wing Outboard Trailing Edge Flap Box _________________________________________ A. General (1) This procedure is a scheduled maintenance task. B. Inspection S 212-076 Do the inspection.

(1)

TASK 57-05-03-212-877 63. Left Wing Outboard Trailing Edge Flap Box _________________________________________ A. General (1) This procedure is a scheduled maintenance task. B. Inspection S 212-077 Do the inspection.

(1)

TASK 57-05-03-212-878 64. Left Wing Outboard Trailing Edge Flap _____________________________________ A. General (1) This procedure is a scheduled maintenance task. B. Inspection S 212-078 Do the inspection.

(1)

TASK 57-05-03-212-879 65. Left Wing Outboard Trailing Edge Flap _____________________________________ A. General (1) This procedure is a scheduled maintenance task.

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57-05-03
08 Page 213 Aug 22/09

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A
B. Inspection S 212-079 Do the inspection.

767 MAINTENANCE MANUAL

(1)

TASK 57-05-03-212-881 66. Left Outboard Aileron _____________________ A. General (1) This procedure is a scheduled maintenance task. B. Inspection S 212-081 Do the inspection.

(1)

TASK 57-05-03-212-882 67. Left Outboard Aileron _____________________ A. General (1) This procedure is a scheduled maintenance task. B. Inspection S 212-082 Do the inspection.

(1)

TASK 57-05-03-212-883 68. Outboard Aileron Spar, Hinges, Actuator _______________________________________ A. General (1) This procedure is a scheduled maintenance task. B. Inspection S 212-083 Do the inspection.

(1)

TASK 57-05-03-212-886 69. Right Wing Exterior ___________________ A. General (1) This procedure is a scheduled maintenance task. B. Inspection S 212-086 Do the inspection.

(1)

TASK 57-05-03-212-887 70. Right Wing Exterior ___________________ A. General (1) This procedure is a scheduled maintenance task.

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08 Page 214 Aug 22/09

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A
B. Inspection S 212-087 Do the inspection.

767 MAINTENANCE MANUAL

(1)

TASK 57-05-03-212-888 71. Nacelle Strut No. 2 Aft Upper Spar __________________________________ A. General (1) This procedure is a scheduled maintenance task. B. Inspection S 212-088 Do the inspection.

(1)

TASK 57-05-03-212-889 72. Nacelle Strut No. 2 Upper Link ______________________________ A. General (1) This procedure is a scheduled maintenance task. B. Inspection S 212-089 Do the inspection.

(1)

TASK 57-05-03-212-890 73. Slat 7 Link Brace and Actuator Support ______________________________________ A. General (1) This procedure is a scheduled maintenance task. B. Inspection S 212-090 Do the inspection.

(1)

TASK 57-05-03-212-891 74. Nacelle Strut No. 2 Upper Link ______________________________ A. General (1) This procedure is a scheduled maintenance task. B. Inspection S 212-091 Do the inspection.

(1)

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08 Page 215 Aug 22/09

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767 MAINTENANCE MANUAL

_______________________________________ WING INSPECTION - MAINTENANCE PRACTICES

1.

TASK 57-05-04-212-001 ______________________________________ Right Wing Leading Edge Slats Interior A. General (1) This procedure is a scheduled maintenance task. B. Inspection S 212-003 Do the inspection.

(1)

2.

TASK 57-05-04-212-004 ____________________________________ Right Slat/Nacelle Seal Kreuger Flap A. General (1) This procedure is a scheduled maintenance task. B. Inspection S 212-006 Do the inspection.

(1)

3.

TASK 57-05-04-212-007 ___________________________ Right Leading Edge Exterior A. General (1) This procedure is a scheduled maintenance task. B. Inspection S 212-009 Do the inspection.

(1)

4.

TASK 57-05-04-212-010 ____________________________________ No. 9 Slat Main and Auxiliary Tracks A. General (1) This procedure is a scheduled maintenance task. B. Inspection S 212-012 Do the inspection.

(1)

5.

TASK 57-05-04-212-013 _______________________________________ Right Wing Fixed Leading Edge Structure A. General (1) This procedure is a scheduled maintenance task.

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57-05-04
01 Page 201 Dec 22/09

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A
B. Inspection S 212-015 Do the inspection.

767 MAINTENANCE MANUAL

(1)

6.

TASK 57-05-04-212-016 _______________________________________ Right Wing Fixed Leading Edge Structure A. General (1) This procedure is a scheduled maintenance task. B. Inspection S 212-018 Do the inspection.

(1)

7.

TASK 57-05-04-212-019 ________________________________________ Exterior Right Wing Inspar Lower Surface A. General (1) This procedure is a scheduled maintenance task. B. Inspection S 212-021 Do the inspection.

(1)

8.

TASK 57-05-04-212-022 _______________________________ Right Wing Inspar Lower Surface A. General (1) This procedure is a scheduled maintenance task. B. Inspection S 212-024 Do the inspection.

(1)

9.

TASK 57-05-04-212-025 Right Wing Inspar Upper Surface _______________________________ A. General (1) This procedure is a scheduled maintenance task. B. Inspection S 212-027 Do the inspection.

(1)

TASK 57-05-04-212-028 10. Right Wing Inspar Upper Surface _______________________________ A. General (1) This procedure is a scheduled maintenance task.

EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùùû ú ALL ú ú ú

57-05-04
01 Page 202 Aug 22/09

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A
B. Inspection S 212-030 Do the inspection.

767 MAINTENANCE MANUAL

(1)

TASK 57-05-04-212-031 11. Right Wing Inspar Lower Surface _______________________________ A. General (1) This procedure is a scheduled maintenance task. B. Inspection S 212-033 Do the inspection.

(1)

TASK 57-05-04-212-034 12. Right Wing Inspar Upper Surface _______________________________ A. General (1) This procedure is a scheduled maintenance task. B. Inspection S 212-036 Do the inspection.

(1)

TASK 57-05-04-212-037 13. Right Wing Lower Surface Spanwise Splice ________________________________________ A. General (1) This procedure is a scheduled maintenance task. B. Inspection S 212-039 Do the inspection.

(1)

TASK 57-05-04-212-040 14. Right Wing Lower Surface Access Hole Cutouts ____________________________________________ A. General (1) This procedure is a scheduled maintenance task. B. Inspection S 212-042 Do the inspection.

(1)

TASK 57-05-04-212-043 15. Right Wing Lower Surface/Side of Body Rib _____________________________________________ A. General (1) This procedure is a scheduled maintenance task.

EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùùû ú ALL ú ú ú

57-05-04
01 Page 203 Aug 22/09

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A
B. Inspection S 212-045 Do the inspection.

767 MAINTENANCE MANUAL

(1)

TASK 57-05-04-212-046 16. Right Wing Rear Spar Web and Lower Chord ________________________________________ A. General (1) This procedure is a scheduled maintenance task. B. Inspection S 212-048 Do the inspection.

(1)

TASK 57-05-04-212-049 17. Right Wing Rear Spar Lower Chord Rib 183 ________________________________________ A. General (1) This procedure is a scheduled maintenance task. B. Inspection S 212-051 Do the inspection.

(1)

TASK 57-05-04-212-052 18. Right Wing Side of Body Rib Web _______________________________ A. General (1) This procedure is a scheduled maintenance task. B. Inspection S 212-054 Do the inspection.

(1)

TASK 57-05-04-212-055 19. Side of Body Rib Lower Chord Cutouts ____________________________________ A. General (1) This procedure is a scheduled maintenance task. B. Inspection S 212-057 Do the inspection.

(1)

TASK 57-05-04-212-058 20. Right Wing Main Tank ____________________ A. General (1) This procedure is a scheduled maintenance task.

EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùùû ú ALL ú ú ú

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02 Page 204 Aug 22/09

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A
B. Inspection S 212-060 Do the inspection.

767 MAINTENANCE MANUAL

(1)

TASK 57-05-04-212-061 21. Right MLG Trunnion Backup Structure ___________________________________ A. General (1) This procedure is a scheduled maintenance task. B. Inspection S 212-063 Do the inspection.

(1)

TASK 57-05-04-212-064 22. Right MLG Beam Backup Structure _______________________________ A. General (1) This procedure is a scheduled maintenance task. B. Inspection S 212-066 Do the inspection.

(1)

TASK 57-05-04-212-067 23. Right Wing Nacelle Strut Support Backup _______________________________________ A. General (1) This procedure is a scheduled maintenance task. B. Inspection S 212-069 Do the inspection.

(1)

TASK 57-05-04-212-070 24. Right Wing Upper Spar Chords ____________________________ A. General (1) This procedure is a scheduled maintenance task. B. Inspection S 212-072 Do the inspection.

(1)

TASK 57-05-04-212-073 25. Right Wing Lower Spanwise Splice Stringers __________________________________________ A. General (1) This procedure is a scheduled maintenance task.

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57-05-04
02 Page 205 Aug 22/09

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A
B. Inspection S 212-075 Do the inspection.

767 MAINTENANCE MANUAL

(1)

TASK 57-05-04-212-076 26. Right Wing Lower Surface Access Hole Cutouts ____________________________________________ A. General (1) This procedure is a scheduled maintenance task. B. Inspection S 212-078 Do the inspection.

(1)

TASK 57-05-04-212-079 27. Nacelle Strut No. 2 Backup Structure ____________________________________ A. General (1) This procedure is a scheduled maintenance task. B. Inspection S 212-081 Do the inspection.

(1)

TASK 57-05-04-212-082 28. Right Wing Spanwise Splice Stringer L-15 ________________________________________ A. General (1) This procedure is a scheduled maintenance task. B. Inspection S 212-084 Do the inspection.

(1)

TASK 57-05-04-212-085 29. Right Wing Front Spar Lower Chord Rib 7, 9 __________________________________________ A. General (1) This procedure is a scheduled maintenance task. B. Inspection S 212-087 Do the inspection.

(1)

TASK 57-05-04-212-091 30. Right Trailing Edge Flap Support Backup Structure _________________________________________________ A. General (1) This procedure is a scheduled maintenance task.

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57-05-04
03 Page 206 Aug 22/09

BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.

A
B. Inspection S 212-093 Do the inspection.

767 MAINTENANCE MANUAL

(1)

TASK 57-05-04-212-094 31. Right Wing Outboard Dry Bay ___________________________ A. General (1) This procedure is a scheduled maintenance task. B. Inspection S 212-096 Do the inspection.

(1)

TASK 57-05-04-212-100 32. Wingtip and Outboard Side of WBL 929 Rib ________________________________________ A. General (1) This procedure is a scheduled maintenance task. B. Inspection S 212-102 Do the inspection.

(1)

TASK 57-05-04-212-106 33. Right Wing Trailing Edge Support Structure and Rear Spar ________________________________________________________ A. General (1) This procedure is a scheduled maintenance task. B. Inspection S 212-108 Do the inspection.

(1)

TASK 57-05-04-212-109 34. Upper Wing/Side of Body Splice ______________________________ A. General (1) This procedure is a scheduled maintenance task. B. Inspection S 212-111 Do the inspection.

(1)

TASK 57-05-04-212-112 35. Right Wing Trailing Edge ________________________ A. General (1) This procedure is a scheduled maintenance task.

EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùùû ú ALL ú ú ú

57-05-04
01 Page 207 Aug 22/09

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A
B. Inspection S 212-114 Do the inspection.

767 MAINTENANCE MANUAL

(1)

TASK 57-05-04-212-115 36. Right Main Gear Drag Brace MLG Beam ___________________________________ A. General (1) This procedure is a scheduled maintenance task. B. Inspection S 212-117 Do the inspection.

(1)

TASK 57-05-04-212-118 37. Right Wing Trailing Edge ________________________ A. General (1) This procedure is a scheduled maintenance task. B. Inspection S 212-120 Do the inspection.

(1)

TASK 57-05-04-212-121 38. Right Wing Spoilers ___________________ A. General (1) This procedure is a scheduled maintenance task. B. Inspection S 212-123 Do the inspection.

(1)

TASK 57-05-04-212-124 39. Right Wing Inboard Trailing Edge Flap Box _________________________________________ A. General (1) This procedure is a scheduled maintenance task. B. Inspection S 212-126 Do the inspection.

(1)

TASK 57-05-04-212-127 40. Right Wing Inboard Trailing Edge Flap Box _________________________________________ A. General (1) This procedure is a scheduled maintenance task.

EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùùû ú ALL ú ú ú

57-05-04
01 Page 208 Aug 22/09

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A
B. Inspection S 212-129 Do the inspection.

767 MAINTENANCE MANUAL

(1)

TASK 57-05-04-212-130 41. Right Inboard Trailing Edge Flap Torque Tube ____________________________________________ A. General (1) This procedure is a scheduled maintenance task. B. Inspection S 212-132 Do the inspection.

(1)

TASK 57-05-04-212-136 42. Right Wing Inboard Trailing Edge Flaps ______________________________________ A. General (1) This procedure is a scheduled maintenance task. B. Inspection S 212-138 Do the inspection.

(1)

TASK 57-05-04-212-139 43. Right Inboard Aileron Interior ______________________________ A. General (1) This procedure is a scheduled maintenance task. B. Inspection S 212-141 Do the inspection.

(1)

TASK 57-05-04-212-142 44. Right Inboard Aileron _____________________ A. General (1) This procedure is a scheduled maintenance task. B. Inspection S 212-144 Do the inspection.

(1)

TASK 57-05-04-212-145 45. Right Inboard Aileron _____________________ A. General (1) This procedure is a scheduled maintenance task.

EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùùû ú ALL ú ú ú

57-05-04
01 Page 209 Aug 22/09

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A
B. Inspection S 212-147 Do the inspection.

767 MAINTENANCE MANUAL

(1)

TASK 57-05-04-212-148 46. Right Inboard Aileron _____________________ A. General (1) This procedure is a scheduled maintenance task. B. Inspection S 212-150 Do the inspection.

(1)

TASK 57-05-04-212-151 47. Right Wing Trailing Edge Support Structure and Rear Spar ________________________________________________________ A. General (1) This procedure is a scheduled maintenance task. B. Inspection S 212-153 Do the inspection.

(1)

TASK 57-05-04-212-154 48. Right Wing Outboard Trailing Edge Flap Box __________________________________________ A. General (1) This procedure is a scheduled maintenance task. B. Inspection S 212-156 Do the inspection.

(1)

TASK 57-05-04-212-157 49. Right Wing Outboard Trailing Edge Flap Box __________________________________________ A. General (1) This procedure is a scheduled maintenance task. B. Inspection S 212-159 Do the inspection.

(1)

TASK 57-05-04-212-160 50. Right Wing Outboard Trailing Edge Flap Box __________________________________________ A. General (1) This procedure is a scheduled maintenance task.

EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùùû ú ALL ú ú ú

57-05-04
01 Page 210 Aug 22/09

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A
B. Inspection S 212-162 Do the inspection.

767 MAINTENANCE MANUAL

(1)

TASK 57-05-04-212-163 51. Right Wing Outboard Trailing Edge Flap __________________________________________ A. General (1) This procedure is a scheduled maintenance task. B. Inspection S 212-165 Do the inspection.

(1)

TASK 57-05-04-212-166 52. Right Wing Outboard Trailing Edge Flap __________________________________________ A. General (1) This procedure is a scheduled maintenance task. B. Inspection S 212-168 Do the inspection.

(1)

TASK 57-05-04-212-172 53. Right Outboard Aileron ______________________ A. General (1) This procedure is a scheduled maintenance task. B. Inspection S 212-174 Do the inspection.

(1)

TASK 57-05-04-212-175 54. Right Outboard Aileron ______________________ A. General (1) This procedure is a scheduled maintenance task. B. Inspection S 212-177 Do the inspection.

(1)

TASK 57-05-04-212-178 55. Outboard Aileron Spar, Hinges, Actuator _______________________________________ A. General (1) This procedure is a scheduled maintenance task.

EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùùû ú ALL ú ú ú

57-05-04
01 Page 211 Aug 22/09

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A
B. Inspection S 212-180 Do the inspection.

767 MAINTENANCE MANUAL

(1)

TASK 57-05-04-212-193 56. Right Wing Trailing Edge Outboard Flap ______________________________________ A. General (1) This procedure is a scheduled maintenance task. B. Inspection S 212-195 Do the inspection.

(1)

TASK 57-05-04-212-220 57. Right Wing Trailing Edge Inboard Flap _____________________________________ A. General (1) This procedure is a scheduled maintenance task. B. Inspection S 212-222 Do the inspection.

(1)

TASK 57-05-04-212-232 58. Right Wing Trailing Edge Inboard Flap _____________________________________ A. General (1) This procedure is a scheduled maintenance task. B. Inspection S 212-234 Do the inspection.

(1)

TASK 57-05-04-212-235 59. Right Wing Trailing Edge Inboard Flap _____________________________________ A. General (1) This procedure is a scheduled maintenance task. B. Inspection S 212-237 Do the inspection.

(1)

TASK 57-05-04-212-262 60. Right Wing Trailing Edge Inboard Flap _____________________________________ A. General (1) This procedure is a scheduled maintenance task.

EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùùû ú ALL ú ú ú

57-05-04
08 Page 212 Aug 22/09

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A
B. Inspection S 212-264 Do the inspection.

767 MAINTENANCE MANUAL

(1)

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767 MAINTENANCE MANUAL

_______________________________________ WING INSPECTION - MAINTENANCE PRACTICES

1.

TASK 57-05-05-212-016 __________________________________________ Right Wing Front Spar Lower Chord and Skin A. General (1) This procedure is a scheduled maintenance task. B. Inspection S 212-018 Do the inspection.

(1)

2.

TASK 57-05-05-212-019 ___________________________________ Right Wing Outboard Lower Stringers A. General (1) This procedure is a scheduled maintenance task. B. Inspection S 212-021 Do the inspection.

(1)

3.

TASK 57-05-05-212-022 __________________________________________ Right Wing Front Spar Lower Chord and Skin A. General (1) This procedure is a scheduled maintenance task. B. Inspection S 212-024 Do the inspection.

(1)

4.

TASK 57-05-05-212-025 ___________________________________ Right Wing Outboard Lower Stringers A. General (1) This procedure is a scheduled maintenance task. B. Inspection S 212-027 Do the inspection.

(1)

5.

TASK 57-05-05-212-031 _____________________________________ Right Wing Trailing Edge Inboard Flap A. General (1) This procedure is a scheduled maintenance task.

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01 Page 201 Dec 22/09

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B. Inspection S 212-033 Do the inspection.

767 MAINTENANCE MANUAL

(1)

6.

TASK 57-05-05-212-034 _______________________________ Wing Trailing Edge Inboard Flap A. General (1) This procedure is a scheduled maintenance task. B. Inspection S 212-036 Do the inspection.

(1)

7.

TASK 57-05-05-212-037 ____________________________________ Left Wing Trailing Edge Inboard Flap A. General (1) This procedure is a scheduled maintenance task. B. Inspection S 212-039 Do the inspection.

(1)

8.

TASK 57-05-05-212-040 _______________________________ Wing Trailing Edge Inboard Flap A. General (1) This procedure is a scheduled maintenance task. B. Inspection S 212-042 Do the inspection.

(1)

9.

TASK 57-05-05-212-046 Right Wing Inspar Lower Surface _______________________________ A. General (1) This procedure is a scheduled maintenance task. B. Inspection S 212-048 Do the inspection.

(1)

TASK 57-05-05-212-058 10. Right Wing Inspar Lower Surface _______________________________ A. General (1) This procedure is a scheduled maintenance task.

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01 Page 202 Aug 22/09

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A
B. Inspection S 212-060 Do the inspection.

767 MAINTENANCE MANUAL

(1)

TASK 57-05-05-212-061 11. Right Wing Rear Spar Lower Chord/Skin _____________________________________ A. General (1) This procedure is a scheduled maintenance task. B. Inspection S 212-063 Do the inspection.

(1)

TASK 57-05-05-212-064 12. Right Wing Rear Spar Lower Chord/Skin _____________________________________ A. General (1) This procedure is a scheduled maintenance task. B. Inspection S 212-066 Do the inspection.

(1)

TASK 57-05-05-212-067 13. Right Wing Outboard Lower Stringers ___________________________________ A. General (1) This procedure is a scheduled maintenance task. B. Inspection S 212-069 Do the inspection.

(1)

TASK 57-05-05-212-070 14. Right Wing Rear Spar Lower Chord and Skin _________________________________________ A. General (1) This procedure is a scheduled maintenance task. B. Inspection S 212-072 Do the inspection.

(1)

TASK 57-05-05-212-076 15. Right Wing Trailing Edge Outboard Flap ______________________________________ A. General (1) This procedure is a scheduled maintenance task.

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57-05-05
01 Page 203 Aug 22/09

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A
B. Inspection S 212-078 Do the inspection.

767 MAINTENANCE MANUAL

(1)

TASK 57-05-05-212-079 16. Left Wing Trailing Edge Outboard Flap _____________________________________ A. General (1) This procedure is a scheduled maintenance task. B. Inspection S 212-081 Do the inspection.

(1)

TASK 57-05-05-212-082 17. Wing Trailing Edge Inboard Flap _______________________________ A. General (1) This procedure is a scheduled maintenance task. B. Inspection S 212-084 Do the inspection.

(1)

TASK 57-05-05-212-085 18. Wing Trailing Edge Inboard Flap _______________________________ A. General (1) This procedure is a scheduled maintenance task. B. Inspection S 212-087 Do the inspection.

(1)

TASK 57-05-05-212-088 19. Right Wing Trailing Edge Inboard Flap _____________________________________ A. General (1) This procedure is a scheduled maintenance task. B. Inspection S 212-090 Do the inspection.

(1)

TASK 57-05-05-212-091 20. Left Wing Trailing Edge Inboard Flap ____________________________________ A. General (1) This procedure is a scheduled maintenance task.

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01 Page 204 Aug 22/09

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A
B. Inspection S 212-093 Do the inspection.

767 MAINTENANCE MANUAL

(1)

TASK 57-05-05-212-094 21. Right Wing Trailing Edge Inboard Flap _____________________________________ A. General (1) This procedure is a scheduled maintenance task. B. Inspection S 212-096 Do the inspection.

(1)

TASK 57-05-05-212-097 22. Left Wing Trailing Edge Inboard Flap ____________________________________ A. General (1) This procedure is a scheduled maintenance task. B. Inspection S 212-099 Do the inspection.

(1)

TASK 57-05-05-212-109 23. Right Wing Front Spar Lower Chord and Skin __________________________________________ A. General (1) This procedure is a scheduled maintenance task. B. Inspection S 212-111 Do the inspection.

(1)

TASK 57-05-05-212-112 24. Right Wing Outboard Lower Stringers ___________________________________ A. General (1) This procedure is a scheduled maintenance task. B. Inspection S 212-114 Do the inspection.

(1)

TASK 57-05-05-212-115 25. Right Wing Outboard Lower Stringers ___________________________________ A. General (1) This procedure is a scheduled maintenance task.

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57-05-05
01 Page 205 Aug 22/09

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A
B. Inspection S 212-117 Do the inspection.

767 MAINTENANCE MANUAL

(1)

TASK 57-05-05-212-118 26. Right Wing Spar Lower Chord/Skin ________________________________ A. General (1) This procedure is a scheduled maintenance task. B. Inspection S 212-120 Do the inspection.

(1)

TASK 57-05-05-212-121 27. Right Wing Inspar Lower Surface _______________________________ A. General (1) This procedure is a scheduled maintenance task. B. Inspection S 212-123 Do the inspection.

(1)

TASK 57-05-05-212-130 28. Left Wing Trailing Edge Outboard Flap _____________________________________ A. General (1) This procedure is a scheduled maintenance task. B. Inspection S 212-132 Do the inspection.

(1)

TASK 57-05-05-212-133 29. Right Wing Trailing Edge Inboard Flap _____________________________________ A. General (1) This procedure is a scheduled maintenance task. B. Inspection S 212-135 Do the inspection.

(1)

TASK 57-05-05-212-136 30. Left Wing Trailing Edge Inboard Flap ____________________________________ A. General (1) This procedure is a scheduled maintenance task.

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57-05-05
01 Page 206 Aug 22/09

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B. Inspection S 212-138 Do the inspection.

767 MAINTENANCE MANUAL

(1)

TASK 57-05-05-212-139 31. Right Wing Trailing Edge Inboard Flap _____________________________________ A. General (1) This procedure is a scheduled maintenance task. B. Inspection S 212-141 Do the inspection.

(1)

TASK 57-05-05-212-142 32. Left Wing Trailing Edge Inboard Flap ____________________________________ A. General (1) This procedure is a scheduled maintenance task. B. Inspection S 212-144 Do the inspection.

(1)

TASK 57-05-05-212-145 33. Right Wing Trailing Edge Inboard Flap _____________________________________ A. General (1) This procedure is a scheduled maintenance task. B. Inspection S 212-147 Do the inspection.

(1)

TASK 57-05-05-212-148 34. Left Wing Trailing Edge Inboard Flap ____________________________________ A. General (1) This procedure is a scheduled maintenance task. B. Inspection S 212-150 Do the inspection.

(1)

TASK 57-05-05-212-151 35. Right Wing Trailing Edge Inboard Flap _____________________________________ A. General (1) This procedure is a scheduled maintenance task.

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57-05-05
01 Page 207 Aug 22/09

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A
B. Inspection S 212-153 Do the inspection.

767 MAINTENANCE MANUAL

(1)

TASK 57-05-05-212-154 36. Left Wing Trailing Edge Inboard Flap ____________________________________ A. General (1) This procedure is a scheduled maintenance task. B. Inspection S 212-156 Do the inspection.

(1)

TASK 57-05-05-212-157 37. Right Wing Trailing Edge Inboard Flap _____________________________________ A. General (1) This procedure is a scheduled maintenance task. B. Inspection S 212-159 Do the inspection.

(1)

TASK 57-05-05-212-160 38. Left Wing Trailing Edge Inboard Flap ____________________________________ A. General (1) This procedure is a scheduled maintenance task. B. Inspection S 212-162 Do the inspection.

(1)

TASK 57-05-05-212-187 39. Left Wing Trailing Edge Inboard Flap ____________________________________ A. General (1) This procedure is a scheduled maintenance task. B. Inspection S 212-189 Do the inspection.

(1)

TASK 57-05-05-212-196 40. Right Wing Trailing Edge Inboard Flap _____________________________________ A. General (1) This procedure is a scheduled maintenance task.

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01 Page 208 Aug 22/09

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A
B. Inspection S 212-198 Do the inspection.

767 MAINTENANCE MANUAL

(1)

TASK 57-05-05-212-199 41. Left Wing Trailing Edge Inboard Flap ____________________________________ A. General (1) This procedure is a scheduled maintenance task. B. Inspection S 212-201 Do the inspection.

(1)

TASK 57-05-05-212-202 42. Right Wing Trailing Edge Inboard Flap _____________________________________ A. General (1) This procedure is a scheduled maintenance task. B. Inspection S 212-204 Do the inspection.

(1)

TASK 57-05-05-212-205 43. Left Wing Trailing Edge Inboard Flap ____________________________________ A. General (1) This procedure is a scheduled maintenance task. B. Inspection S 212-207 Do the inspection.

(1)

TASK 57-05-05-212-208 44. Right Wing Trailing Edge Inboard Flap _____________________________________ A. General (1) This procedure is a scheduled maintenance task. B. Inspection S 212-210 Do the inspection.

(1)

TASK 57-05-05-212-211 45. Left Wing Trailing Edge Inboard Flap ____________________________________ A. General (1) This procedure is a scheduled maintenance task.

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57-05-05
01 Page 209 Aug 22/09

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A
B. Inspection S 212-213 Do the inspection.

767 MAINTENANCE MANUAL

(1)

TASK 57-05-05-212-214 46. Right Wing Trailing Edge Inboard Flap _____________________________________ A. General (1) This procedure is a scheduled maintenance task. B. Inspection S 212-216 Do the inspection.

(1)

TASK 57-05-05-212-217 47. Left Wing Trailing Edge Inboard Flap ____________________________________ A. General (1) This procedure is a scheduled maintenance task. B. Inspection S 212-219 Do the inspection.

(1)

TASK 57-05-05-212-220 48. Right Wing Trailing Edge Inboard Flap _____________________________________ A. General (1) This procedure is a scheduled maintenance task. B. Inspection S 212-222 Do the inspection.

(1)

TASK 57-05-05-212-223 49. Left Wing Trailing Edge Inboard Flap ____________________________________ A. General (1) This procedure is a scheduled maintenance task. B. Inspection S 212-225 Do the inspection.

(1)

TASK 57-05-05-212-229 50. Left Wing Trailing Edge Inboard Flap ____________________________________ A. General (1) This procedure is a scheduled maintenance task.

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03 Page 210 Aug 22/09

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A
B. Inspection S 212-231 Do the inspection.

767 MAINTENANCE MANUAL

(1)

TASK 57-05-05-212-232 51. Left Wing Trailing Edge Inboard Flap ____________________________________ A. General (1) This procedure is a scheduled maintenance task. B. Inspection S 212-234 Do the inspection.

(1)

TASK 57-05-05-212-259 52. Right Wing Trailing Edge Inboard Flap _____________________________________ A. General (1) This procedure is a scheduled maintenance task. B. Inspection S 212-261 Do the inspection.

(1)

TASK 57-05-05-212-262 53. Left Wing Trailing Edge Inboard Flap ____________________________________ A. General (1) This procedure is a scheduled maintenance task. B. Inspection S 212-264 Do the inspection.

(1)

TASK 57-05-05-212-265 54. Right Wing Trailing Edge Inboard Flap _____________________________________ A. General (1) This procedure is a scheduled maintenance task. B. Inspection S 212-267 Do the inspection.

(1)

TASK 57-05-05-212-268 55. Left Wing Trailing Edge Inboard Flap ____________________________________ A. General (1) This procedure is a scheduled maintenance task.

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03 Page 211 Aug 22/09

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A
B. Inspection S 212-270 Do the inspection.

767 MAINTENANCE MANUAL

(1)

TASK 57-05-05-212-271 56. Right Wing Trailing Edge Inboard Flap _____________________________________ A. General (1) This procedure is a scheduled maintenance task. B. Inspection S 212-273 Do the inspection.

(1)

TASK 57-05-05-212-274 57. Left Wing Trailing Edge Inboard Flap ____________________________________ A. General (1) This procedure is a scheduled maintenance task. B. Inspection S 212-276 Do the inspection.

(1)

TASK 57-05-05-212-277 58. Right Wing Trailing Edge Inboard Flap _____________________________________ A. General (1) This procedure is a scheduled maintenance task. B. Inspection S 212-279 Do the inspection.

(1)

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03 Page 212 Aug 22/09

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767 MAINTENANCE MANUAL

_______________________________________ WING INSPECTION - MAINTENANCE PRACTICES

1.

TASK 57-05-06-212-001 ____________________________________ Left Wing Trailing Edge Inboard Flap A. General (1) This procedure is a scheduled maintenance task. B. Inspection S 212-003 Do the inspection.

(1)

2.

TASK 57-05-06-212-004 _____________________________________ Right Wing Trailing Edge Inboard Flap A. General (1) This procedure is a scheduled maintenance task. B. Inspection S 212-006 Do the inspection.

(1)

3.

TASK 57-05-06-212-007 ____________________________________ Left Wing Trailing Edge Inboard Flap A. General (1) This procedure is a scheduled maintenance task. B. Inspection S 212-009 Do the inspection.

(1)

4.

TASK 57-05-06-212-010 ____________________________________ Left Wing Trailing Edge Inboard Flap A. General (1) This procedure is a scheduled maintenance task. B. Inspection S 212-012 Do the inspection.

(1)

5.

TASK 57-05-06-212-037 _________________________________________ Left Wing Front Spar Lower Chord and Skin A. General (1) This procedure is a scheduled maintenance task.

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01 Page 201 Dec 22/09

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A
B. Inspection S 212-039 Do the inspection.

767 MAINTENANCE MANUAL

(1)

6.

TASK 57-05-06-212-040 __________________________________ Left Wing Outboard Lower Stringers A. General (1) This procedure is a scheduled maintenance task. B. Inspection S 212-042 Do the inspection.

(1)

7.

TASK 57-05-06-212-043 _____________________________________ Right Wing Trailing Edge Inboard Flap A. General (1) This procedure is a scheduled maintenance task. B. Inspection S 212-045 Do the inspection.

(1)

8.

TASK 57-05-06-212-046 ____________________________________ Left Wing Trailing Edge Inboard Flap A. General (1) This procedure is a scheduled maintenance task. B. Inspection S 212-048 Do the inspection.

(1)

9.

TASK 57-05-06-212-049 Right Wing Trailing Edge Inboard Flap _____________________________________ A. General (1) This procedure is a scheduled maintenance task. B. Inspection S 212-051 Do the inspection.

(1)

TASK 57-05-06-212-052 10. Left Wing Trailing Edge Inboard Flap ____________________________________ A. General (1) This procedure is a scheduled maintenance task.

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57-05-06
01 Page 202 Aug 22/09

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A
B. Inspection S 212-054 Do the inspection.

767 MAINTENANCE MANUAL

(1)

TASK 57-05-06-212-055 11. Right Wing Trailing Edge Inboard Flap _____________________________________ A. General (1) This procedure is a scheduled maintenance task. B. Inspection S 212-057 Do the inspection.

(1)

TASK 57-05-06-212-058 12. Left Wing Trailing Edge Inboard Flap ____________________________________ A. General (1) This procedure is a scheduled maintenance task. B. Inspection S 212-060 Do the inspection.

(1)

TASK 57-05-06-212-061 13. Right Wing Trailing Edge Inboard Flap _____________________________________ A. General (1) This procedure is a scheduled maintenance task. B. Inspection S 212-063 Do the inspection.

(1)

TASK 57-05-06-212-064 14. Left Wing Trailing Edge Inboard Flap ____________________________________ A. General (1) This procedure is a scheduled maintenance task. B. Inspection S 212-066 Do the inspection.

(1)

TASK 57-05-06-212-067 15. Right Wing Trailing Edge Inboard Flap _____________________________________ A. General (1) This procedure is a scheduled maintenance task.

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57-05-06
01 Page 203 Aug 22/09

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A
B. Inspection S 212-069 Do the inspection.

767 MAINTENANCE MANUAL

(1)

TASK 57-05-06-212-070 16. Left Wing Trailing Edge Inboard Flap ____________________________________ A. General (1) This procedure is a scheduled maintenance task. B. Inspection S 212-072 Do the inspection.

(1)

TASK 57-05-06-212-073 17. Left Wing Front Spar Lower Chord and Skin _________________________________________ A. General (1) This procedure is a scheduled maintenance task. B. Inspection S 212-075 Do the inspection.

(1)

TASK 57-05-06-212-076 18. Left Wing Outboard Lower Stringers __________________________________ A. General (1) This procedure is a scheduled maintenance task. B. Inspection S 212-078 Do the inspection.

(1)

TASK 57-05-06-212-085 19. Left Wing Inspar Lower Surface ______________________________ A. General (1) This procedure is a scheduled maintenance task. B. Inspection S 212-087 Do the inspection.

(1)

TASK 57-05-06-212-097 20. Left Wing Inspar Lower Surface ______________________________ A. General (1) This procedure is a scheduled maintenance task.

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01 Page 204 Aug 22/09

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A
B. Inspection S 212-099 Do the inspection.

767 MAINTENANCE MANUAL

(1)

TASK 57-05-06-212-100 21. Left Wing Rear Spar Lower Chord/Skin ____________________________________ A. General (1) This procedure is a scheduled maintenance task. B. Inspection S 212-102 Do the inspection.

(1)

TASK 57-05-06-212-103 22. Left Wing Rear Spar Lower Chord/Skin ____________________________________ A. General (1) This procedure is a scheduled maintenance task. B. Inspection S 212-105 Do the inspection.

(1)

TASK 57-05-06-212-106 23. Right Wing Trailing Edge Inboard Flap _____________________________________ A. General (1) This procedure is a scheduled maintenance task. B. Inspection S 212-108 Do the inspection.

(1)

TASK 57-05-06-212-109 24. Left Wing Trailing Edge Inboard Flap ____________________________________ A. General (1) This procedure is a scheduled maintenance task. B. Inspection S 212-111 Do the inspection.

(1)

TASK 57-05-06-212-112 25. Right Wing Trailing Edge Outboard Flap ______________________________________ A. General (1) This procedure is a scheduled maintenance task.

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57-05-06
01 Page 205 Aug 22/09

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A
B. Inspection S 212-114 Do the inspection.

767 MAINTENANCE MANUAL

(1)

TASK 57-05-06-212-115 26. Left Wing Trailing Edge Outboard Flap _____________________________________ A. General (1) This procedure is a scheduled maintenance task. B. Inspection S 212-117 Do the inspection.

(1)

TASK 57-05-06-212-118 27. Right Wing Trailing Edge Outboard Flap ______________________________________ A. General (1) This procedure is a scheduled maintenance task. B. Inspection S 212-120 Do the inspection.

(1)

TASK 57-05-06-212-121 28. Left Wing Trailing Edge Outboard Flap _____________________________________ A. General (1) This procedure is a scheduled maintenance task. B. Inspection S 212-123 Do the inspection.

(1)

TASK 57-05-06-212-124 29. Right Wing Trailing Edge Outboard Flap ______________________________________ A. General (1) This procedure is a scheduled maintenance task. B. Inspection S 212-126 Do the inspection.

(1)

TASK 57-05-06-212-127 30. Left Wing Trailing Edge Outboard Flap _____________________________________ A. General (1) This procedure is a scheduled maintenance task.

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01 Page 206 Aug 22/09

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A
B. Inspection S 212-129 Do the inspection.

767 MAINTENANCE MANUAL

(1)

TASK 57-05-06-212-130 31. Right Wing Trailing Edge Outboard Flap ______________________________________ A. General (1) This procedure is a scheduled maintenance task. B. Inspection S 212-132 Do the inspection.

(1)

TASK 57-05-06-212-133 32. Left Wing Trailing Edge Outboard Flap _____________________________________ A. General (1) This procedure is a scheduled maintenance task. B. Inspection S 212-135 Do the inspection.

(1)

TASK 57-05-06-212-136 33. Left Wing Outboard Lower Stringers __________________________________ A. General (1) This procedure is a scheduled maintenance task. B. Inspection S 212-138 Do the inspection.

(1)

TASK 57-05-06-212-139 34. Left Wing Rear Spar Lower Chord and Skin ________________________________________ A. General (1) This procedure is a scheduled maintenance task. B. Inspection S 212-141 Do the inspection.

(1)

TASK 57-05-06-212-154 35. Left Wing Front Spar Lower Chord and Skin _________________________________________ A. General (1) This procedure is a scheduled maintenance task.

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57-05-06
01 Page 207 Aug 22/09

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A
B. Inspection S 212-156 Do the inspection.

767 MAINTENANCE MANUAL

(1)

TASK 57-05-06-212-157 36. Left Wing Outboard Lower Stringers __________________________________ A. General (1) This procedure is a scheduled maintenance task. B. Inspection S 212-159 Do the inspection.

(1)

TASK 57-05-06-212-160 37. Left Wing Outboard Lower Stringers __________________________________ A. General (1) This procedure is a scheduled maintenance task. B. Inspection S 212-162 Do the inspection.

(1)

TASK 57-05-06-212-163 38. Left Wing Spar Lower Chord/Skin _______________________________ A. General (1) This procedure is a scheduled maintenance task. B. Inspection S 212-165 Do the inspection.

(1)

TASK 57-05-06-212-166 39. Left Wing Inspar Lower Surface ______________________________ A. General (1) This procedure is a scheduled maintenance task. B. Inspection S 212-168 Do the inspection.

(1)

TASK 57-05-06-212-169 40. Right Wing Trailing Edge Outboard Flap ______________________________________ A. General (1) This procedure is a scheduled maintenance task.

EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùùû ú ALL ú ú ú

57-05-06
01 Page 208 Aug 22/09

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A
B. Inspection S 212-171 Do the inspection.

767 MAINTENANCE MANUAL

(1)

TASK 57-05-06-212-172 41. Left Wing Trailing Edge Outboard Flap _____________________________________ A. General (1) This procedure is a scheduled maintenance task. B. Inspection S 212-174 Do the inspection.

(1)

TASK 57-05-06-212-175 42. Right Wing Trailing Edge Outboard Flap ______________________________________ A. General (1) This procedure is a scheduled maintenance task. B. Inspection S 212-177 Do the inspection.

(1)

TASK 57-05-06-212-178 43. Left Wing Trailing Edge Outboard Flap _____________________________________ A. General (1) This procedure is a scheduled maintenance task. B. Inspection S 212-180 Do the inspection.

(1)

TASK 57-05-06-212-181 44. Right Wing Trailing Edge Outboard Flap ______________________________________ A. General (1) This procedure is a scheduled maintenance task. B. Inspection S 212-183 Do the inspection.

(1)

TASK 57-05-06-212-184 45. Left Wing Trailing Edge Outboard Flap _____________________________________ A. General (1) This procedure is a scheduled maintenance task.

EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùùû ú ALL ú ú ú

57-05-06
01 Page 209 Aug 22/09

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A
B. Inspection S 212-186 Do the inspection.

767 MAINTENANCE MANUAL

(1)

TASK 57-05-06-212-187 46. Right Wing Trailing Edge Outboard Flap ______________________________________ A. General (1) This procedure is a scheduled maintenance task. B. Inspection S 212-189 Do the inspection.

(1)

TASK 57-05-06-212-190 47. Left Wing Trailing Edge Outboard Flap _____________________________________ A. General (1) This procedure is a scheduled maintenance task. B. Inspection S 212-192 Do the inspection.

(1)

TASK 57-05-06-212-193 48. Right Wing Trailing Edge Outboard Flap ______________________________________ A. General (1) This procedure is a scheduled maintenance task. B. Inspection S 212-195 Do the inspection.

(1)

TASK 57-05-06-212-196 49. Left Wing Trailing Edge Outboard Flap _____________________________________ A. General (1) This procedure is a scheduled maintenance task. B. Inspection S 212-198 Do the inspection.

(1)

TASK 57-05-06-212-202 50. Inboard Flap Support Structure ______________________________ A. General (1) This procedure is a scheduled maintenance task.

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B. Inspection S 212-204 Do the inspection.

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(1)

TASK 57-05-06-212-211 51. Inboard Flap Support Structure ______________________________ A. General (1) This procedure is a scheduled maintenance task. B. Inspection S 212-213 Do the inspection.

(1)

TASK 57-05-06-212-214 52. Inboard Flap Support Structure ______________________________ A. General (1) This procedure is a scheduled maintenance task. B. Inspection S 212-216 Do the inspection.

(1)

TASK 57-05-06-212-223 53. Inboard Flap Support Structure ______________________________ A. General (1) This procedure is a scheduled maintenance task. B. Inspection S 212-225 Do the inspection.

(1)

TASK 57-05-06-212-226 54. Wing Center Section Lower Surface _________________________________ A. General (1) This procedure is a scheduled maintenance task. B. Inspection S 212-228 Do the inspection.

(1)

TASK 57-05-06-212-229 55. Wing Center Section Rear Spar Lower Chord _________________________________________ A. General (1) This procedure is a scheduled maintenance task.

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B. Inspection S 212-231 Do the inspection.

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(1)

TASK 57-05-06-212-232 56. Right Wing Trailing Edge Outboard Flap ______________________________________ A. General (1) This procedure is a scheduled maintenance task. B. Inspection S 212-234 Do the inspection.

(1)

TASK 57-05-06-212-235 57. Left Wing Trailing Edge Outboard Flap _____________________________________ A. General (1) This procedure is a scheduled maintenance task. B. Inspection S 212-237 Do the inspection.

(1)

TASK 57-05-06-212-238 58. Right Wing Trailing Edge Outboard Flap ______________________________________ A. General (1) This procedure is a scheduled maintenance task. B. Inspection S 212-240 Do the inspection.

(1)

TASK 57-05-06-212-241 59. Left Wing Trailing Edge Outboard Flap _____________________________________ A. General (1) This procedure is a scheduled maintenance task. B. Inspection S 212-243 Do the inspection.

(1)

TASK 57-05-06-212-244 60. Right Wing Trailing Edge Outboard Flap ______________________________________ A. General (1) This procedure is a scheduled maintenance task.

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B. Inspection S 212-246 Do the inspection.

767 MAINTENANCE MANUAL

(1)

TASK 57-05-06-212-247 61. Left Wing Trailing Edge Outboard Flap _____________________________________ A. General (1) This procedure is a scheduled maintenance task. B. Inspection S 212-249 Do the inspection.

(1)

TASK 57-05-06-212-250 62. Right Wing Trailing Edge Outboard Flap ______________________________________ A. General (1) This procedure is a scheduled maintenance task. B. Inspection S 212-252 Do the inspection.

(1)

TASK 57-05-06-212-253 63. Left Wing Trailing Edge Outboard Flap _____________________________________ A. General (1) This procedure is a scheduled maintenance task. B. Inspection S 212-255 Do the inspection.

(1)

TASK 57-05-06-212-256 64. Right Wing Trailing Edge Outboard Flap ______________________________________ A. General (1) This procedure is a scheduled maintenance task. B. Inspection S 212-258 Do the inspection.

(1)

TASK 57-05-06-212-259 65. Left Wing Trailing Edge Outboard Flap _____________________________________ A. General (1) This procedure is a scheduled maintenance task.

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B. Inspection S 212-261 Do the inspection.

767 MAINTENANCE MANUAL

(1)

TASK 57-05-06-212-271 66. Wing Center Section Lower Surface _________________________________ A. General (1) This procedure is a scheduled maintenance task. B. Inspection S 212-273 Do the inspection.

(1)

TASK 57-05-06-212-277 67. Wing Center Section Fuel Tank _____________________________ A. General (1) This procedure is a scheduled maintenance task. B. Inspection S 212-279 Do the inspection.

(1)

TASK 57-05-06-202-280 68. Visually Inspect the Wing Vortex Generators ___________________________________________ A. General (1) This procedure is a scheduled maintenance task. B. Inspection S 212-281 Visually inspect the wing vortex generators (7 per wing, upper surface) for condition and security.

(1)

TASK 57-05-06-202-283 69. Visually Inspect the Outboard Flap Vortex Generators ____________________________________________________ A. General (1) This procedure is a scheduled maintenance task.

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B. Inspection

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(1)

S 212-282 Visually inspect the outboard flap vortex generators (25 per flap, upper surface).

TASK 57-05-06-962-286 70. Replace the Main Landing Gear Support Structure _______________________________________________ A. General (1) This procedure is a scheduled maintenance task. B. Inspection S 962-285 Replace the main landing gear support structure.

(1)

TASK 57-05-06-962-288 71. Replace the Main Landing Gear Support Structure _______________________________________________ A. General (1) This procedure is a scheduled maintenance task. B. Procedure S 962-287 Replace the main landing gear support structure.

(1)

TASK 57-05-06-962-289 72. Replace the Main Landing Gear Retract Actuator Fitting and Pin ______________________________________________________________ A. General (1) This procedure is a scheduled maintenance task. B. Procedure S 962-290 Replace the main landing gear retract actuator fitting and pin.

(1)

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___________________________________________ WING CENTER SECTION - MAINTENANCE PRACTICES

1.

TASK 57-05-07-212-004 _____________________________ Wing Center Section Fuel Tank A. General (1) This procedure is a scheduled maintenance task. B. Inspection S 212-006 Do the inspection.

(1)

2.

TASK 57-05-07-212-010 _____________________________________ Wing Center Section Fuel Tank Wet Bay A. General (1) This procedure is a scheduled maintenance task. B. Inspection S 212-012 Do the inspection.

(1)

3.

TASK 57-05-07-212-016 ______________________________________ Right Wing Trailing Edge Outboard Flap A. General (1) This procedure is a scheduled maintenance task. B. Inspection S 212-018 Do the inspection.

(1)

4.

TASK 57-05-07-212-019 _____________________________________ Left Wing Trailing Edge Outboard Flap A. General (1) This procedure is a scheduled maintenance task. B. Inspection S 212-021 Do the inspection.

(1)

5.

TASK 57-05-07-212-022 ______________________________________ Right Wing Trailing Edge Outboard Flap A. General (1) This procedure is a scheduled maintenance task.

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B. Inspection S 212-024 Do the inspection.

767 MAINTENANCE MANUAL

(1)

6.

TASK 57-05-07-212-025 _____________________________________ Left Wing Trailing Edge Outboard Flap A. General (1) This procedure is a scheduled maintenance task. B. Inspection S 212-027 Do the inspection.

(1)

7.

TASK 57-05-07-212-028 ______________________________________ Right Wing Trailing Edge Outboard Flap A. General (1) This procedure is a scheduled maintenance task. B. Inspection S 212-030 Do the inspection.

(1)

8.

TASK 57-05-07-212-031 _____________________________________ Left Wing Trailing Edge Outboard Flap A. General (1) This procedure is a scheduled maintenance task. B. Inspection S 212-033 Do the inspection.

(1)

9.

TASK 57-05-07-212-034 Right Wing Trailing Edge Outboard Flap ______________________________________ A. General (1) This procedure is a scheduled maintenance task. B. Inspection S 212-036 Do the inspection.

(1)

TASK 57-05-07-212-037 10. Left Wing Trailing Edge Outboard Flap _____________________________________ A. General (1) This procedure is a scheduled maintenance task.

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B. Inspection S 212-039 Do the inspection.

767 MAINTENANCE MANUAL

(1)

TASK 57-05-07-212-040 11. Right Wing Trailing Edge Outboard Flap ______________________________________ A. General (1) This procedure is a scheduled maintenance task. B. Inspection S 212-042 Do the inspection.

(1)

TASK 57-05-07-212-043 12. Left Wing Trailing Edge Outboard Flap _____________________________________ A. General (1) This procedure is a scheduled maintenance task. B. Inspection S 212-045 Do the inspection.

(1)

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___________________________________________ CORROSION PREVENTION IN CENTER WING SECTION 1. _______ General A. Corrosion can occur on the upper skin, under the base plate of the drain screen at BBL 71. This is the area where the wing upper skin touches the slope of the pressure deck. TASK 57-10-01-602-001 _______________________________ Corrosion Prevention Treatment A. References (1) AMM 51-21-03/701, Corrosion Removal and Control-Cleaning/Painting (2) AMM 51-24-09/701, Corrosion Inhibiting Compound-Cleaning/Painting B. Consumable Materials (1) G0009 Compound, Organic Corrosion Preventive - BMS 3-23 C. Access (1) Location Zones 133/134 Left Wing Center Section/Right Wing Center Section D. Corrosion Protection S 602-002 Following cleaning of suspected areas (Ref AMM 51-21-03/701), a full inspection is effective to ensure that the protective finishes provided during manufacture remain intact. S 602-006 For minor corrosion, to minimize the downtime of the airplane, the corrosion products should be cleaned off, followed by the application of a corrosion inhibiting compound into the affected area to decrease the corrosion process (Ref AMM 51-24-09/701). The finish system should be repaired at the first opportunity consistent with the maintenance schedule.

2.

(1)

(2)

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SEE

A

FLOOR BEAM (TYPICAL 8 PLACES) 2

RBBL 97.95

REAR SPAR 1 U-1C STA 955.10 SPANWISE BEAM NO. 1 L-5C U-24C SPANWISE BEAM NO. 2 L-11C 1 1

U-7C

U-16C LBBL 97.95

UPPER SKIN PANEL ON TOP SURFACE 2 FWD FRONT SPAR 1

L-17C STA 785.90

SPANWISE BEAM NO. 3 1

LOWER SKIN PANEL 1

A

1 2

APPLY BMS 3-23, TYPE II CORROSION INHIBITING COMPOUND APPLY BMS 3-23, TYPE II CORROSION INHIBITING COMPOUND, FOLLOWED BY BMS 3-26 TYPE II CORROSION INHIBITING COMPOUND

Center Wing Section Corrosion Protection Figure 201
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__________________________________ CORROSION PREVENTION IN OUTER WING 1.

767 MAINTENANCE MANUAL

_______ General A. Corrosion can occur on the front and rear spars. The deployment of flight control surfaces exposes the spars to ground contaminants, thrust reverser soot, runway dirt and debris, and inclement weathr elements, all of which contribute to corrosion. B. Corrosion has been found on the wing skin around fastener head at RH WS 107, stringer S-1, and between fasteners along the span at RH WS614 to 620, stringers S-4, S-5, and S-6. C. Corrosion can occur on the upper skin under the wing-to-body fairing. Corrosion can also start at rivet heads under the fairing. The fairing seal can cause wear on these surfaces. D. Corrosion can occur on the fuel-tank access doors. The knitted-wire gaskets were dry, without serviceable anti-corrosion grease. E. The spar chords can get corrosion at fasteners between the chord and web. F. Corrosion can occur on the splice plates at the lower surface of the fixed leading edge. The corrosion starts on the upper aft surface and can go completelythrough the splice plates. G. Corrosion can occur on the upper chord of the inboard spoiler beam. Corrosion was found in three locations between WBL 165 and WBL 215. TASK 57-20-01-602-001 _______________________________ Corrosion Prevention Treatment A. General (1) Following cleaning of suspected areas (Ref AMM 51-21-03/701), a full inspection is effective to ensure that protective finishes provided during manufacture remain intact. (2) Make periodic inspections of the drain holes. Use a pipe cleaner or thin wooden dowel to remove debris and contaminants from drain holes. (3) Where corrosion exists (noticeable bulges of the skin or white deposits of corrosion products at fastener heads or joint edges), refer to the Structural Repair Manual for details of corrosion removal. (4) For minor corrosion, to minimize the downtime of the airplane, the corrosion products should be cleaned off, followed by the application of a corrosion inhibiting compound into the affected area to retard the corrosion process (Ref AMM 51-24-09/701). The finish system should be repaired at the first opportunity consistent with the maintenance schedule.

2.

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ENGINE STRUT W STA 344.3

W STA 433.1 DRY BAY

D E D

E

FWD

A
LEADING EDGE FRONT SPAR

A

LANDING GEAR BEAM

WBL 929.12

B
TRAILING EDGE REAR SPAR

C

C B

WING TIP

FRONT SPAR REAR SPAR 1 LEADING EDGE SKIN SKIN LAP INSPAR UPPER PANEL VERTICAL STIFFENER

WEB

1

SPLICE PLATE (TYP) FWD INSPAR LOWER PANEL

FWD

WIGGLE PLATE

LEADING EDGE FRONT SPAR A-A

TRAILING EDGE REAR SPAR B-B

Outer Wing Corrosion Protection Figure 201 (Sheet 1)
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1 1

WING TIP C-C

1

DRY BAY BARRIER FRONT SPAR

DRY BAY D-D

1

1

BOOST PUMP CAVITY E-E
1 APPLY BMS 3-23 TYPE 2 CORROSION INHIBITING COMPOUND TO ALL STRUCTURAL SURFACES. OVERSPRAY IS PERMITTED WHERE THE ACCESS IS NOT EASY

Outer Wing Corrosion Protection Figure 201 (Sheet 2)
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SUPPORT LINK MAIN GEAR SUPPORT BEAM 2

DRAG BRACE SUPPORT FITTING 1 TRUNNION BEARING REAR SPAR

WS 213.55

WS 300 SIDE BRACE (REF) TRUNNION BEARING SUPPORT FITTING MAIN GEAR BEAM OUTBOARD SUPPORT FITTING SEE A 1

INBD

FWD

CAUTION: _______

DO NOT LET THE CORROSION INHIBITING COMPOUND GO INTO BEARINGS OR BUSHINGS.

1

APPLY BMS 3-23 CORROSION INHIBITING COMPOUND. BE SURE TO INCLUDE FASTENERS AND FAYING SURFACES. APPLY LIBERALLY TO PERMIT PENETRATION BETWEEN FITTING AND REAR SPAR APPLY BMS 3-23 CORROSION INHIBITING COMPOUND TO ALL SURFACES. BE SURE TO INCLUDE CONNECTION POINTS

2

Main Landing Gear Trunnion Support Structure Corrosion Protection Figure 202 (Sheet 1)
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WS 392 WS 372

767 MAINTENANCE MANUAL

SEE

B SEE C

FWD

A

FWD FWD

B

C

Main Landing Gear Trunnion Support Structure Corrosion Protection Figure 202 (Sheet 2)
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(5)

767 MAINTENANCE MANUAL

B.

C.

D.

Frequency of Application (a) Periodic inspection is required in areas identified as susceptible to corrosion and should be consistent to the schedules specified in the Maintenance Planning Document. Operators must be aware of reported problems and areas of occurrences. (b) Periodic application of BMS 3-23 compound is necessary to areas identified and should be consistent to the schedule specified in the Maintenance Planning Document. References (1) AMM 51-21-03/701, Corrosion Removal and Control-Cleaning/Painting (2) AMM 51-24-09/701, Corrosion Inhibiting Compound-Cleaning/Painting Consumable Materials (1) A00247 Sealant - BMS 5-95 (2) C00033 Enamel - BMS 10-60, Type II (3) G0009 Compound, Organic Corrosion Preventive - BMS 3-23 Access (1) Location Zones 500/600 Left Wing/Right Wing Procedure S 602-007 At first opportunity consistent with scheduled maintenance activity, do corrosion prevention treatment on the primary structure and skin of the outer wing. S 602-003 Apply BMS 10-79 type 3 primer followed by BMS 10-100 (Aeroflex G12E25) coating where repair or replacement is required on existing finish. ____ NOTE: The BMS 10-100 coating is chemically compatible with the Corogard coating, but the two coatings have slight differences in color and finish.

E.

(1)

(2)

S 602-006 _______ CAUTION: DO NOT APPLY CORROSION INHIBITING COMPOUNDS NEAR ENGINES, COWLING, OR OTHER AREAS OF HIGH TEMPERATURE, OR WHERE FIREWALL SEALANT IS USES. THE HIGH TEMPERATURES CAN CAUSE DETERIORATIO DETERIORATION OF THE COMPOUNDS. CORROSION INHIBITING COMPOUNDS CAN CAUSE DAMAGE TO THE SEALANT.

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(3)

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FOR AIRPLANES WITH SB 51-0008; Apply BMS 5-95, class F sprayable sealant, followed by BMS 10-60 enamel, to external surfaces. S 602-005 Apply BMS 3-23 Type 2 corrosion inhibiting compound on the front spar, rear spar and dry bay area. ____ NOTE: Corrosion inhibiting compounds can be used on fiberglass fairings and ducts if the temperature of the duct is not hotter than 220 F. Corrosion inhibiting compounds can be used on fuel vapor barriers.

(4)

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___________________________________ VORTEX GENERATORS - APPROVED REPAIR 1. _______ General A. This procedure contains one task. The task gives instructions to do repairs of the vortex generators. B. The repairs done in this procedure are temporary. It is satisfactory to have these temporary repairs only until the airplane gets to a location that can do permanent repairs. You must obey the instructions in the Structural Repair Manual when you do the permanent repairs. TASK 57-25-01-308-007 ___________________________ Repair the Vortex Generator A. References (1) 51-21-02/701, Prepaint Cleaning and Treatment B. Consumable Materials (1) B00148 Methyl Ethyl Ketone (MEK) - TT-M-261 (2) B00386 Solvent - Toluene (3) C00035 Finish - Corogard (4) Adhesive: ____ NOTE: Use one of the adhesives that follow.

2.

C.

(a) A00779 BMS 5-26 Type II (b) A00247 BMS 5-95 Class B (c) A00708 Sealant - Fast Curing, 2-part - PR-1828 Access (1) Location Zone 500/600 Left Wing/Right Wing Procedure S 038-001 Make sure the vertical flange is smooth with the top surface of the horizontal flange. S 148-002 _______ WARNING: DO NOT GET SOLVENTS IN YOUR MOUTH, OR YOUR EYES, OR ON YOUR SKIN. DO NOT BREATHE THE FUMES FROM SOLVENTS. SOLVENTS ARE HAZARDOUS MATERIALS. SOLVENTS MAY BE FLAMMABLE OR HARMFUL TO THE ENVIRONMENT. REFER TO PRODUCT MATERIAL SAFETY DATA SHEETS (MSDS) AND LOCAL REQUIREMENTS FOR PROPER HANDLING PROCEDURES.

D.

(1)

(2)

Remove the corogard paint from the bond area with solvent, Series 88 (AMM 20-30-88/201).

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(3)

S 348-003 Bond the vortex generator to the top surface of the horizontal flange as follows: (a) Refer to the manufacturer's instructions to mix the base compound with the activator. ____ NOTE: (b) (c) Do not make the adhesive thin.

(d)

Apply a thin, continuous layer of the adhesive mixture to each mating surface. Put the vortex generator in its position immediately and apply sufficient pressure to make sure the mating surfaces fully touch. Let the adhesive cure at room temperature. ____ NOTE: The times to get full adhesive strength are as follows: ________ Adhesive BMS 5-26 Class B 1/2 BMS 5-26 Class B 2 BMS 5-95 Class B 1/2 BMS 5-95 Class B 2 BMS 5-95 Class B 4 PR-1828 Class B-1/4 PR-1828 Class B-1/2 _________ Cure time 16 hours 48 hours 20 hours 48 hours 84 hours 4 hours @ 50F 10 hours @ 35F 4.5 hours @ 50F 10.5hours @ 35F

(e)

If you need to decrease the cure time, increase the temperature to a maximum of 140 degrees F. ____ NOTE: Cure time decreases by a half for each 20 degrees F increase in temperature.

(4)

S 378-006 Apply Corogard paint to the wing surface as necessary.

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_______________________________ WING TIP - REMOVAL/INSTALLATION 1.

767 MAINTENANCE MANUAL

_______ General A. This procedure contains two tasks. (1) The first task gives the instructions to remove the right and left wing tips. (2) The second task gives the instructions to install the right and left wing tips. B. The steps for the right and left wing tips are the same. TASK 57-31-01-004-001 ___________________ Remove the Wing Tip (Fig. 401) A. Equipment (1) Attach Fitting Set - Wing Safety Harness, A20002-4 B. References (1) 20-10-27/201, Flight Control Surfaces Safety Harness Receptacle (2) 33-43-01/201, Wing Forward Position Lights (3) 33-43-02/201, Wing Rear Position Lights (4) 33-44-01/201, Wing Anti-Collision Lights C. Access (1) Location Zones 545/645 Wing Tips D. Procedure S 494-015 _______ WARNING: ATTACH A SAFETY HARNESS WHEN YOU DO WORK ON TOP OF THE WING. FAILURE TO ATTACH A SAFETY HARNESS CAN CAUSE INJURY OR DAMAGE.

2.

(1)

Attach the safety harness (Ref 20-10-27). S 014-002 Remove the forward position light from the wing (Ref 33-43-01). S 014-003 Remove the rear position light from the wing (Ref 33-43-02). S 014-004 Remove the anti-collision light from the wing (Ref 33-44-01). S 014-006 Remove the access panels (Fig. 401). S 024-007 Remove the attach bolts and the wing tip.

(2)

(3)

(4)

(5)

(6)

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SEE

A

FORWARD POSITION LIGHT

BOLT (EXAMPLE) ANTI-COLLISION LIGHT BOLT (EXAMPLE) WING TIP

AUXILLIARY FORWARD POSITION LIGHT ACCESS PANEL AFT POSITION LIGHT BOLT (EXAMPLE)

WINGTIP A

Wing Tip Figure 401
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14898

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767 MAINTENANCE MANUAL

3.

TASK 57-31-01-404-008 ____________________ Install the Wing Tip (Fig. 401) A. Equipment (1) Attach Fitting Set - Wing Safety Harness, A20002-4 B. References (1) 20-10-27/201, Flight Control Surfaces Safety Harness Receptacle (2) 33-43-01/201, Wing Forward Position Lights (3) 33-43-02/201, Wing Rear Position Lights (4) 33-44-01/201, Wing Anti-Collision Lights C. Access (1) Location Zones 545/645 Wing Tips D. Procedure S 424-009 Hold the wing tip in position and install the attach bolts. S 414-010 Install the access panels (Fig. 401). S 414-012 Install the anti-collision light on the wing (Ref 33-44-01). S 414-013 Install the rear position light on the wing (Ref 33-43-02). S 414-014 Install the forward position light on the wing (Ref 33-43-01). S 094-016 Remove the safety harness if it is not necessary (Ref 20-10-27).

(1)

(2)

(3)

(4)

(5)

(6)

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________________________________________________________ OUTBOARD WING LEADING EDGE SLAT ACTUATOR ROD SEAL DOOR ____________________ REMOVAL/INSTALLATION 1. _______ General A. This procedure contains two tasks. (1) The first task is instructions to remove the seal door for the slat actuator rod on the outboard leading edge. (2) The second task is instructions to install the seal door for the slat actuator rod on the outboard leading. B. The seal door for the slat actuator rod is referred to as the seal door in this procedure. C. The removal and installation steps for the right and the left side seal doors are equivalent. D. If fuel is found near one of the drain tubes for the slat track housing, it is possible that there is a leak in the drain tube. Refer to AMM 28-11-00/801 for temporary repair procedure of fuel leakage in the drain tubes. TASK 57-41-56-004-001 ____________________ Remove the Seal Door (Fig. 401) A. References (1) AMM 27-81-00/201, Leading Edge Slat System (2) AMM 27-81-00/501, Leading Edge Slat System (3) AMM 78-31-00/201, Thrust Reverser System B. Access (1) Location Zones 500/600 Left Wing/Right Wing C. Procedure S 044-037 _______ WARNING: DO THE THRUST REVERSER DEACTIVATION PROCEDURE TO PREVENT THE OPERATION OF THE THRUST REVERSER. THE ACCIDENTAL OPERATION OF THE THRUST REVERSER CAN CAUSE INJURY TO PERSONS OR DAMAGE TO EQUIPMENT.

2.

(1)

AIRPLANES WITH PW4000 SERIES ENGINES; Do this procedure: Thrust Reverser Deactivation for Ground Maintenance (AMM 78-31-00/201). S 014-031 Fully retract the slats on the outboard leading edge (AMM 27-81-00/201). S 034-006 Remove the screws from the seal door.

(2)

(3)

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OUTBOARD LEADING EDGE SLAT ACTUATOR SEAL DOOR SEE A

767 MAINTENANCE MANUAL

A

SEAL

SCREWS (6 LOCATIONS) SHIM (EXAMPLE)

A

OUTBOARD LEADING EDGE SLAT ACTUATOR SEAL DOOR A
LEADING EDGE SLAT ROTARY ACTUATOR

FRONT SPAR

ACTUATOR ROD ACTUATOR ROD BRACKETS SEAL DOOR AFT SUPPORT BRACKET

A-A

Outboard Wing Leading Edge Slat Actuator Rod Seal Door Figure 401
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(4)

S 024-007 Remove the seal door. ____ NOTE: Keep the shims, and write a record of their positions to help you install them correctly in the subsequent installation procedure.

S 214-040 _______ WARNING: DO NOT LET OBJECTS GET IN THE HOUSING ASSEMBLY OF THE SLAT TRACK. THIS WILL HELP PREVENT A PUNCTURE OF THE HOUSING ASSEMBLY THAT COULD CAUSE A FUEL LEAK. THE FUEL LEAK COULD CAUSE A FIRE AND POSSIBLE DEATH OR INJURY TO PERSONNEL. Examine the area to make sure objects are not left in the slat track housing assembly. S 494-021 _______ CAUTION: TEMPORARILY ATTACH THE AFT SUPPORT BRACKET TO THE ACTUATOR ROD. THE ACCIDENTAL OPERATION OF THE SLAT CAN CAUSE INJURY TO PERSONS OR DAMAGE TO EQUIPMENT.

(5)

(6)

Temporarily attach the aft support bracket to the actuator rod.

3.

TASK 57-41-56-404-042 ____________________________________ Remove the Seal Door for CDL 57-41-1 (Fig. 40l) A. References (1) AMM 27-81-00/201, Leading Edge Slat System (2) AMM 27-81-00/501, Leading Edge Slat System (3) AMM 78-31-00/201, Thrust Reverser System B. Access (1) Location Zones 500/600 Left Wing/Right Wing

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C. Procedure

767 MAINTENANCE MANUAL

(1)

S 024-049 This procedure is for the temporary removal of the slat actuator seal door due to damage and for allowed continued revenue flight per CDL 57-41-1. S 044-043

_______ WARNING:

DO THE THRUST REVERSER DEACTIVATION PROCEDURE TO PREVENT THE OPERATION OF THE THRUST REVERSER. THE ACCIDENTAL OPERATION OF THE THRUST REVERSER CAN CAUSE INJURY TO PERSONS OR DAMAGE TO EQUIPMENT.

(2)

Do this procedure: Thrust Reverser Deactivation for Ground Maintenance (AMM 78-31-00/201). S 864-050 Fully retract the outboard leading edge slats (Ref 27-81-00/201). S 044-044 Do this procedure: Remove power from the Outboard Leading Edge Slats (AMM 27-81-00-/201). S 014-045 Remove the screws from the seal door. S 024-046 Remove the seal door. NOTE: ____ Keep the shims, and write a record of their positions to help you install them correctly in the subsequent installation procedure.

(3)

(4)

(5)

(6)

S 214-047 _______ WARNING: DO NOT LET OBJECTS GET IN THE HOUSING ASSEMBLY OF THE SLAT TRACK . THIS WILL HELP PREVENT A PUNCTURE OF THE HOUSING ASSEMBLY THAT COULD CAUSE A FUEL LEAK. THE FUEL LEAK COULD CAUSE A FIRE AND POSSIBLE DEATH OR INJURY TO PERSONNEL. Examine the area to make sure objects are not left in the slat track housing assembly.

(7)

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S 024-048 _______ CAUTION: DO NOT OPERATE THE SLATS WITH THE SUPPORT/ATTACHMENT BRACKETS DOWN (LOOSE AT ONE END) WHEN THE CONTROL ROD DOOR (ACTUATOR SEAL DOOR) IS REMOVED. IMPACT DAMAGE TO THE FIXED SPLICE PLATE ON THE LEADING EDGE LOWER SURFACE CAN OCCUR. Remove the outboard leading edge slat linkage fairing panel aft position support bracket as follows: (a) Remove the bolt that attaches the aft support bracket and the actuator rod to the rotary actuator drive arm. (b) Remove the aft support bracket from the actuator rod to the rotary actuator drive arm. (c) Reinstall the bolt for the actuator rod to the actuator drive arm.

(8)

4.

TASK 57-41-56-404-009 _____________________ Install the Seal Door (Fig. 40l) A. References (1) AMM 27-81-00/201, Leading Edge Slat System (2) AMM 27-81-02/501, Outboard Leading Edge Slat (3) AMM 78-31-00/201, Thrust Reverser System B. Access (1) Location Zones 500/600 Left Wing/Right Wing C. Procedure S 214-010 Make sure the slats on the outboard leading edge are fully retracted (AMM 27-81-00/201). S 094-011 Disconnect the temporary support of the actuator rod to the aft support bracket. S 434-012 Put the shims and the seal door in position. S 434-014 Install the screws that hold the seal door to the brackets. S 214-015 Do a check of the seal door clearance and flushness to the adjacent skin panels (AMM 27-81-02/501). S 824-016 Adjust the seal door for the correct clearance if it is necessary (AMM 27-81-02/501).

(1)

(2)

(3)

(4)

(5)

(6)

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S 214-041 _______ WARNING: DO NOT LET OBJECTS GET IN THE HOUSING ASSEMBLY OF THE SLAT TRACK. THIS WILL HELP PREVENT A PUNCTURE OF THE HOUSING ASSEMBLY THAT COULD CAUSE A FUEL LEAK. THE FUEL LEAK COULD CAUSE A FIRE AND POSSIBLE DEATH OR INJURY TO PERSONNEL. Examine the area to make sure objects are not left in the slat track housing assembly. S 444-019 AIRPLANES WITH PW4000 SERIES ENGINES; Do the activation procedure for the thrust reverser (AMM 78-31-00/201).

(7)

(8)

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_______________________________________________________________ WING LEADING EDGE PRESSURE RELIEF PANELS - REMOVAL/INSTALLATION 1. _______ General A. The Wing Leading Edge Pressure Relief Panels blow out if a high pressure leak occurs. These panels are located in the inboard and outboard fixed section on the underside of the leading edge of the wing. This procedure contains tasks to remove the pressure panels and tasks to install the pressure panels. TASK 57-41-57-024-010 _____________________________ Pressure Relief Panel Removal (Fig. 401) A. Access (1) Location Zones 510/610 Leading Edge - Inboard of Nacelle Strut 520/620 Leading Edge - Outboard of Nacelle Strut B. Procedure S 024-004 To remove the Leading Edge Pressure Panels (511KB or 611KB), do the following: (a) Remove the 8 fasteners that attach the aft outer retainer to the pressure panel. (b) Remove the aft outer retainer and the pressure relief panel. S 024-015 To remove the Leading Edge Pressure Panels (521AMB or 621AMB), do the following: (a) Remove the two aft fasteners and washers that attach the outer retainer to the pressure panel. (b) Remove the four forward fasteners that attach the outer retainer to the pressure panel. (c) Remove the seven outboard fasteners that attach the outer retainer to the pressure panel. (d) Carefully remove the outer retainer and the pressure relief panel. S 024-014 To remove the Leading Edge Pressure Panels (521ANB or 621ANB), do the following: (a) Remove the seven aft fasteners that attach the outer retainer to the pressure panel.

2.

(1)

(2)

(3)

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(b) (c) (d)

767 MAINTENANCE MANUAL

Remove the eight forward fasteners that attach the outer retainer to the pressure panel. Remove the eight outboard fasteners that attach the outer retainer to the pressure panel. Carefully remove the outer retainer and the pressure relief panel.

S 214-016 _______ WARNING: DO NOT LET OBJECTS GET IN THE HOUSING ASSEMBLY OF THE SLAT TRACK. THIS WILL HELP PREVENT A PUNCTURE OF THE HOUSING ASSEMBLY THAT COULD CAUSE A FUEL LEAK. THE FUEL LEAK COULD CAUSE A FIRE AND POSSIBLE DEATH OR INJURY TO PERSONNEL. (4) Examine the area to make sure objects are not left in the slat track housing assembly. TASK 57-41-57-414-011 __________________________________ Pressure Relief Panel Installation (Fig. 401) A. Access (1) Location Zones 510/610 Leading Edge - Inboard of Nacelle Strut 520/620 Leading Edge - Outboard of Nacelle Strut B. Procedure S 424-006 To install the pressure relief panel (511KB or 611KB), do the following steps: (a) Put the panel's forward plate edge between the forward outer retainer and the retainer assembly. (b) Push the aft end of the panel against the substructure. (c) Make sure that a gap of 0.05 to 0.14 inch (1.27 to 3.56 mm) exists between the panel and the forward outer retainer. (d) Install the 8 fasteners to attach the aft outer retainer and panel. (e) Make sure that a gap of 0.05 to 0.14 inch (1.27 to 3.56 mm) exists between the panel and the aft outer retainer. (f) Make sure that the gaps at the inboard and outboard panel joints are 0.06 inch +0.06 or -0.00 inch (1.54 mm +1.54 or -0.00 mm). (g) Make sure that all joints of the panel do not have an aerodynamic misfair greater than 0.020 inch (0.508 mm). S 424-013 To install the pressure relief panel (521AMB or 621AMB), do the following steps: (a) Put the panel's inboard plate edge between the outer retainer and the retainer assembly. (b) Push the pressure relief panel against the substructure.

3.

(1)

(2)

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(c) (d)

767 MAINTENANCE MANUAL

(e) (f)

(g) (h) (i) (j)

Put the outer retainer into position against the panel. Make sure that a clearance of 0.06 to 0.12 inch (1.52 to 3.05 mm) exists between the panel and the outer retainer forward edge. Make sure that a clearance of 0.06 to 0.12 inch (1.52 to 3.05 mm) exists between the panel and the outer retainer aft edge. Make sure that the clearances at the inboard and outboard panel joints are 0.06 inch +0.06 or -0.00 inch (1.54 mm +1.54 or -0.00 mm). Install the seven fasteners on the outboard panel edge. Install the four fasteners on the forward panel edge. Install the two fasteners and washers on the aft panel edge. Torque the fasteners to a range between 15 to 25 pound-inches (1.69 to 2.82 nm).

(3)

S 424-012 To install the pressure relief panel (521ANB or 621ANB), do the following steps: (a) Put the panel's inboard plate edge between the outer retainer and the retainer assembly. (b) Push the pressure relief panel against the substructure. (c) Put the outer retainer into position against the panel. (d) Make sure that a clearance of 0.06 to 0.12 inch (1.52 to 3.05 mm) exists between the panel and the outer retainer forward edge. (e) Make sure that a clearance of 0.06 to 0.12 inch (1.52 to 3.05 mm) exisits between the panel and the outer retainer aft edge. (f) Make sure that the clearances at the inboard and outboard panel joints are 0.06 inch +0.06 or -0.00 inch (1.54 mm +1.54 or -0.00 mm). (g) Install the eight fasteners on the outboard panel edge. (h) Install the eight fasteners on the forward panel edge. (i) Install the seven fasteners on the aft panel edge. (j) Torque the fasteners to a range between 15 to 25 pound-inches (1.69 to 2.82 nm).

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S 214-017 _______ WARNING: DO NOT LET OBJECTS GET IN THE HOUSING ASSEMBLY OF THE SLAT TRACK. THIS WILL HELP PREVENT A PUNCTURE OF THE HOUSING ASSEMBLY THAT COULD CAUSE A FUEL LEAK. THE FUEL LEAK COULD CAUSE A FIRE AND POSSIBLE DEATH OR INJURY TO PERSONNEL. (4) Examine the area to make sure objects are not left in the slat track housing assembly.

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A
LEFT (RIGHT) PRESSURE RELIEF PANEL, 521ANB (621ANB) SEE C

767 MAINTENANCE MANUAL
A

LEFT (RIGHT) PRESSURE RELIEF PANEL, 511KB (611KB) SEE A

LEFT (RIGHT) PRESSURE RELIEF PANEL, 521AMB (621AMB) SEE B

PANEL ASSEMBLY TAB AFT OUTER RETAINER

FASTENER (8 LOCATIONS)

A

AFT INNER NUTPLATE RETAINER ASSEMBLY

FWD

PRESSURE RELIEF PANEL, 511KB (PRESSURE RELIEF PANEL, 611KB IS EQUIVALENT) A
NOSE BEAM FORWARD INNER NUTPLATE RETAINER ASSEMBLY PANEL ASSEMBLY TAB

INBD

PRESSURE RELIEF PANEL

PANEL ASSEMBLY TAB

AFT INNER NUTPLATE RETAINER ASSEMBLY

WING FRONT SPAR SPLICE PLATE

WING LEADING EDGE SKIN PANEL

FORWARD OUTER RETAINER FWD

0.05-0.14 INCH (1.27-3.56 mm)

0.05-0.14 INCH (1.27-3.56 mm)

A-A

AFT OUTER RETAINER

Wing Leading Edge Pressure Relief Panel Installation Figure 401 (Sheet 1)
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FORWARD FASTENER (4 LOCATIONS)

767 MAINTENANCE MANUAL
B
FORWARD INNER NUTPLATE RETAINER ASSEMBLY

PANEL ASSEMBLY TAB OUTBOARD INNER NUTPLATE RETAINER ASSEMBLY

FWD

INBD

PANEL ASSEMBLY TAB

OUTBOARD FASTENER (7 LOCATIONS)

AFT INNER NUTPLATE RETAINER ASSEMBLY

AFT FASTENER (2 LOCATIONS)

B

AFT INNER NUTPLATE RETAINER ASSEMBLY

PRESSURE RELIEF PANEL, 521AMB (PRESSURE RELIEF PANEL, 621AMB IS EQUIVALENT)
PANEL ASSEMBLY TAB

B

PRESSURE RELIEF PANEL

FORWARD INNER NUTPLATE RETAINER PANEL ASSEMBLY ASSEMBLY TAB

OUTER RETAINER

0.06 - 0.12 INCH (1.52 - 3.05 mm)

FWD

0.06 - 0.12 INCH (1.52 - 3.05 mm)

OUTER RETAINER

B-B

Wing Leading Edge Pressure Relief Panel Installation Figure 401 (Sheet 2)
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A
FORWARD FASTENER (8 LOCATIONS)

767 MAINTENANCE MANUAL
C
PANEL ASSEMBLY TAB FORWARD INNER NUTPLATE RETAINER ASSEMBLY

OUTBOARD FASTENER (8 LOCATIONS)

PANEL ASSEMBLY TAB

C
AFT INNER NUTPLATE RETAINER ASSEMBLY WING FRONT SPAR SPLICE PLATE FWD

AFT FASTENER (7 LOCATIONS) WING LEADING EDGE SKIN PANEL

PRESSURE RELIEF PANEL, 521ANB (PRESSURE RELIEF PANEL, 621ANB IS EQUIVALENT) C

INBD

FORWARD INNER NUTPLATE RETAINER PANEL ASSEMBLY ASSEMBLY TAB

PRESSURE RELIEF PANEL

PANEL ASSEMBLY TAB

AFT INNER NUTPLATE RETAINER ASSEMBLY

OUTER RETAINER

0.06 - 0.12 INCH (1.52 - 3.05 mm)

FWD

0.06 - 0.12 INCH (1.52 - 3.05 mm)

OUTER RETAINER

C-C

Wing Leading Edge Pressure Relief Panel Installation Figure 401 (Sheet 3)
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_____________________________________________________ THERMAL ANTI-ICE (TAI) DOOR - REMOVAL/INSTALLATION 1. _______ General A. The Thermal Anti-Ice (TAI) door gives you access to the Thermal Anti-Icing telescopic duct in the leading edge of wing. This procedure contains three tasks. The first task gives instructions to remove the TAI Door. The second task gives instructions to install the TAI door. The third task gives instructions to rig the TAI door. TASK 57-41-58-004-001 ________________ TAI Door Removal (Fig 401) A. References (1) 27-81-00/201, Leading Edge Slat System B. Access (1) Location Zones 521/621 Leading Edge to Front Spar C. Procedure S 864-040 _______ CAUTION: MAKE SURE THAT THE STRUT ACCESS DOORS ARE CLOSED BEFORE YOU EXTEND OR RETRACT THE LEADING EDGE SLATS.

2.

(1)

Extend the leading edge slats (AMM 27-81-00/201). S 044-047 Deactivate the leading edge slats and attach DO-NOT-CLOSE TAGS (AMM 27-81-00/201). S 024-041 Remove the TAI door: (a) Remove the 3 aft fasteners through the gap plate. (b) Remove and keep the gap plate. (c) Remove the 2 forward fasteners that go through the duct bracket. (d) Disconnect and discard the ground jumper and the sleeving. (e) Remove the seal TAI door.

(2)

(3)

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S 214-051 _______ WARNING: DO NOT LET OBJECTS GET IN THE HOUSING ASSEMBLY OF THE SLAT TRACK. THIS WILL HELP PREVENT A PUNCTURE OF THE HOUSING ASSEMBLY THAT COULD CAUSE A FUEL LEAK. THE FUEL LEAK COULD CAUSE A FIRE AND POSSIBLE DEATH OR INJURY TO PERSONNEL. (4) Examine the area to make sure objects are not left in the slat track housing assembly. TASK 57-41-58-434-044 _____________________ TAI Door Installation (Fig 401) A. References (1) SOPM 20-10-06 (2) SOPM 20-41-02 (3) SOPM 20-43-03 (4) SOPM 20-44-04 (5) SWPM 20-20-00 (6) AMM 20-11-00/201, Standard Torque Values (7) AMM 27-81-00/201, Leading Edge Slat System B. Access (1) Location Zones 521/621 Leading Edge to Front Spar C. Consumable Materials (1) C00432 Primer - BMS 10-11, Type I (2) C00130 Primer BMS 10-79, Type II (3) B00624 Compound - Lubricant BMS 3-28 (4) C00308 Corrosion Preventative Compound - MIL-C-11796, Class 3 (5) C00001 Anti-Static Coating - BMS 10-21, Type III Procedure S 864-049 AIRPLANES PRE-SB 57-0104; Do these steps: (a) Apply primer BMS 10-11, Type I to all areas of the fastener holes that go through the gap plate and the TAI duct bracket including the countersink before you install the bolts. 1) Let the primer dry before you apply the Corrosion Preventative Compound (CPC).

3.

D.

(1)

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767 MAINTENANCE MANUAL

SEE

A

FORWARD TEE ASSEMBLY

AFT TEE ASSEMBLY

LEADING EDGE SLATS

FWD

A
TAI SEAL DOOR

A A

TAI Duct Seal Door - Removal/Installation Figure 401 (Sheet 1)
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùùû AIRPLANES PRE-SB 57-0104 ú ú ú ú

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(b)

767 MAINTENANCE MANUAL

Apply CPC MIL-C-11796 Class 3 to all areas of the fastener holes in the gap plate and the TAI duct bracket including the countersink before you install the bolts. MAKE SURE THAT THE TEFLON HEAT RESISTANT SLEEVING IS INSTALLED ON THE GROUND JUMPER. THE GROUND JUMPER AND THE SLEEVING ARE PART OF THE SEAL DOOR, AND THEY CAN EASILY FALL OFF.

_______ CAUTION:

(c) (d) (e) (f) (g) (h) (i)

Examine the sleeving to make sure that it is installed correctly. Temporarily install the seal door to get the necessary clearances. Adjust and align the door in view A-A, Fig. 401. If you install a new door, trim the seal door as necessary to obtain the clearance in view D-D, Fig. 401. If you install the same door, get the clearance in view D-D, Fig. 401. Align the seal door per views A-A and C-C in figure 401. Measure the distance between the hinge bolt and the hinge pin in view D-D, fig. 401. ____ NOTE: This dimension is recommended and not a requirement.

(j)

If necessary adjust the distance between the hinge bolt and the hinge pin in view D-D, fig. 401; loosen the bolts in the slotted holes to allow adjustment. ____ NOTE: Full slot adjustment is allowed to get the distance.

(k)

(l)

(m)

Turn the hinge bolt finger tight view A-A, figure 401 and continue to a maximum of 8 pound-inches or until the cotter key slot aligns. If you installed a new door and after you trimmed the door, apply alodine 600 on the edge of the metal erosion strip of the seal door (view D-D, Fig. 401 ) (SOPM 20-43-03). 1) Apply primer BMS 10-79, Type II on the entire edge of the seal door (view D-D, Fig. 401). Apply BMS 3-28 lubricant to the fasteners prior to installation (AMM 20-11-00/201). ____ NOTE: The BMS 3-28 will prevent corrosion on the threads of the fasteners and make them easier to remove.

(n) (o) (p)

Install the gap plate (view A-A, Fig. 401) and maintain a clearance between 0.03 - 0.09 inch. Connect the ground jumper. Apply the conducting coating BMS 10-21, Type 1 to the 3 fasteners with the flagnote per view A-A, Fig. 401 (SOPM 20-10-06).

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(q)

767 MAINTENANCE MANUAL

Do a check of the resistance value of 0.001 ohms from the hinge to the seal door at the jumper location (SWPM 20-20-00). ____ NOTE: The resistance value should not exceed 0.001 ohms

(2)

S 864-050 AIRPLANES POST-SB 57-0104; Do these steps: (a) Temporarily install the seal door to get the necessary clearances. (b) Adjust and align the door in view A-A Fig. 401A. 1) Get the clearance in views B-B, C-C, and D-D Fig. 401A. 2) Hold the door in position with two fasteners at TAI duct forward hinge attachment location, refer to view A-A fig. 401A. (c) If you trim the new door, to get the clearance in view C-C, apply alodine 600 on the edge of the metal erosion strip of the seal door (SOPM 20-43-03). 1) Apply primer BMS 10-79, Type II on the entire edge of the seal door, view C-C, Fig. 401A.(SOPM 20-44-04) (d) Apply primer BMS 10-11, Type I to all areas of the fastener holes that go through the gap plate and the TAI duct hinge including the countersink before you install the bolts. (SOPM 20-41-02). 1) Let the primer dry before you apply the Corrosion Preventative Compound (CPC). (e) Apply CPC MIL-C-11796 Class 3 to all areas of the fastener holes in the gap plate and the TAI duct hinge including the countersink before you install the bolts. (SOPM 20-41-03) _______ CAUTION: MAKE SURE THAT THE TEFLON HEAT RESISTANT SLEEVING IS INSTALLED ON THE GROUND JUMPER. THE GROUND JUMPER AND THE SLEEVING ARE PART OF THE SEAL DOOR, AND THEY CAN EASILY FALL OFF.

(f) (g)

Examine the sleeving to make sure that it is installed on the ground jumper. Measure the distance between the hinge bolt and the hinge pin in view C-C, Fig. 401A. ____ NOTE: This dimension is recommended and not a requirement. 1) If necessary adjust the distance between the hinge bolt and the hinge pin in view C-C, Fig. 401A; loosen the bolts in the slotted holes to allow adjustment. NOTE: ____ Full slot adjusment is allowed, to get the distances.

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(h)

767 MAINTENANCE MANUAL

Torque the hinge bolt in view C-C, figure 401A and continue to a maximum of 8 pound-inches or until the cotter key slot aligns. (i) Install the gap plate (view A-A, Fig. 401A). 1) Maintain clearance as shown in view A-A, Fig. 401A. (j) Apply sealant BMS5-95 to the nut, washer and terminal fitting on the ground jumper (SOPM 20-11-03). (k) Connect the ground jumper. (l) Clean the hinge and splice place contact surface, refer to cleaning method (CM3) of SOPM 20-11-03. (m) Apply sealant BMS5-95 to the surface between the hinge and the splice plate and allow the sealant to squeeze out (SOPM 20-11-03). (n) Install all the fasteners. 1) Adjust and align the door to get the necessary clearance in views C-C, D-D and E-E. 2) If necessary, loosen the TAI duct seal door and move it aft to get the clearance given in view E-E. (o) Adjust the door to make sure that the gaps are as shown in view B-B; Fig. 401A. 1) The door may twist when the door closes, only adjust the door to fit inside the opening between the fixed leading edge panels. 2) Make sure that there is necessary clearance between the door and structure when the door is fully closed. (p) Measure the electrical resistance of the ground jumper from the aft terminal fitting of ground jumper to a position 0.5 to 1.0 inch away from the edge of the door hinge on the splice plate. 1) The electrical resistance must not be more than 0.001 ohms, refer to SWPM 20-20-00. WARNING: DO NOT LET OBJECTS GET IN THE HOUSING ASSEMBLY OF THE SLAT _______ TRACK. THIS WILL HELP PREVENT A PUNCTURE OF THE HOUSING ASSEMBLY THAT COULD CAUSE A FUEL LEAK. THE FUEL LEAK COULD CAUSE A FIRE AND POSSIBLE DEATH OR INJURY TO PERSONNEL. (q) Examine the area to make sure objects are not left in the slat track housing assembly. TASK 57-41-58-834-045 TAI Seal Door Rigging _____________________ A. Procedure S 714-046 Before you rig the TAI door, make sure that the outboard slats are rigged and in the fully retracted (cruise) position.

4.

(1)

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SEAL DOOR HINGE BOLT

C
GAP PLATE

B D
C L TAI DUCT

D
FASTENER

GROUND JUMPER AND SLEEVING

B

FASTENER 1

C

FWD

TAI DUCT SEAL DOOR A-A

1

THESE FASTENERS ARE USED TO ADJUST THE ALIGNMENT AT THE DOOR. TIGHTEN AFTER INSTALLATION IS COMPLETE.

TAI Duct Seal Door - Removal/Installation Figure 401 (Sheet 2)
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BOLT (TIGHTEN TO 15 POUND-INCHES)

B-B

SEAL DOOR STRUCTURE

STRUCTURE 0.03 INCH (0.76 mm) MINIMUM

C-C

0.03 INCH (0.76 mm) MINIMUM

DUCT BRACKET

TAI DUCT

HINGE BOLT

1.27-1.31 INCHES (32.26-33.27 mm)

CENTER HINGE

STRUCTURE FWD FORWARD HINGE DEFLECTOR PLATE HINGE PIN SLOTTED HOLE 0.10-0.18 INCH (2.54-4.57 MM) GAP

SEAL DOOR

D-D

TAI Duct Seal Door - Removal/Installation Figure 401 (Sheet 3)
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767 MAINTENANCE MANUAL

SEE

A

FWD

THERMAL ANTI-ICE (TAI) DUCT

GROUND JUMPER SPLICE PLATE

A +

TAI DUCT SEAL DOOR

A FWD INBD

SEE

B

A

TAI Duct Seal Door - Removal/Installation Figure 401A (Sheet 1)
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767 MAINTENANCE MANUAL
FASTENER (3 LOCATIONS)
1 2

DEFLECTOR PLATE TAI DUCT

CENTER HINGE

FASTENER (3 LOCATIONS)
1 2

HINGE PIN
C L

D C

TAI DUCT SEAL DOOR

AFT HINGE 0.03-0.09 INCH (0.76-2.29 mm)

C E B B

C L

E

OSS 460.7250 GAP PLATE

FORWARD HINGE

HINGE BOLT FWD INBD

D GROUNDING SLEEVE AND JUMPER

0.03-0.09 INCH (0.76-2.29 mm) SPLICE PLATE

0.12 INCH (3.05 mm)

A-A

0.03-0.09 INCH (0.76-2.29 mm) (EACH SIDE)

TAI DUCT SEAL DOOR

B-B
2 APPLY BMS3-28 TO THE FASTENERS PRIOR TO INSTALLATION (SOPM 20-50-01).

1

THESE FASTENERS ARE USED TO ADJUST THE ALIGNMENT AT THE DOOR. TIGHTEN AFTER INSTALLATION IS COMPLETE.

TAI Duct Seal - Removal/Installation Figure 401A (Sheet 2)
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767 MAINTENANCE MANUAL

DUCT BRACKET

TAI DUCT

HINGE BOLT

1.27-1.31 INCH (32.26-33.27 mm)

CENTER HINGE TAI DUCT SEAL DOOR

FORWARD HINGE STRUCTURE DEFLECTOR PLATE HINGE PIN 0.10-0.18 INCH (2.54-4.57 mm) GAP UP

BOLT/SLOTTED HOLE

C-C
FWD

OSS 460.7250

TAI DUCT SEAL DOOR

STRUCTURE 0.03 INCH (0.76 mm) MINIMUM

STRUCTURE 0.03 INCH (0.76 mm) MINIMUM

UP

D-D

TAI Duct Seal Door - Removal/Installation Figure 401A (Sheet 3)
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C TAI DUCT L

TAI DUCT DOOR (CLOSED)

TAI DUCT TAI DUCT DOOR (OPENED) 0.040 INCH (1.016 mm) MIN CLEARANCE TO TOP SURFACE OF HINGE

E-E

NUT TAI DUCT SEAL DOOR WASHER B GROUND JUMPER

WASHER A SPLICE PLATE

FWD

INBD

B

TAI Duct Seal Door - Removal/Installation Figure 401A (Sheet 4)
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(2)

S 834-043 To rig the TAI door do as follows: _______ CAUTION: DO NOT LOOSEN THE TWO BOLTS COMMON TO THE SERRATED FORWARD HINGE HALVES.

(a)

Loosen the bolts that attach the forward hinge to the forward edge of the door (view B-B, Fig. 401; and view A-A, Fig. 401A).

_______ CAUTION:

IF YOU EXTEND THE SLATS TOO MUCH, IT WILL PRELOAD THE TAI DOOR.

(b) (c)

(d)

(e) (f) (g) (h) (i)

Extend the outboard slats 1.25 +/-0.25 revolution of the outboard slat drive torque tube. Push on the forward end of the seal door with hand pressure into the contour until the seal door lands make contact along the entire length on adjacent panels. While you maintain the hand pressure on the forward end of the door, tighten the 4 bolts that attach the forward hinge assembly. 1) If insufficient adjustment exists, loosen the 2 bolts common to the serrated hinge halves and adjust as necessary. Tighten the bolts after adjustment. Repeat the process to push the door and to tighten and loosen the bolts as it is necessary. Retract the outboard slats to fully retracted (cruise) position (AMM 27-81-00/201). Do a check for fit and fair of the TAI door. Operate the slats for smooth operation of the door. ____ NOTE: Slat lower edge will contact and slide against the deflector plate.

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(j)

767 MAINTENANCE MANUAL

Make a final inspection of the seal door. 1) Do a check for mismatch between the door in the rigged position and the adjacent structure. ____ NOTE: The mismatch should not exceed +/- 0.02 inch for a minimum of 75% of any edge. The mismatch should not exceed +/-0.04 inch for a maximum of 25% of any edge.

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______________________________________________________________ INBOARD LEADING EDGE SUPPORT LINK DOORS - REMOVAL/INSTALLATION 1. _______ General A. This procedure has two tasks: (1) The first task is to remove the support link doors on the inboard leading edge of the wing. (2) The second task is to install the support link doors on the inboard leading edge of the wing. B. The removal and installation of the right and left side inboard leading edge support link doors are equivalent. C. This procedure removes and installs the side brace support link door and the mid support link door. D. The side brace support link door and the mid support link door are referred to as the door in this procedure. TASK 57-41-59-004-002 _______________ Remove the Door (Fig. 401) A. References (1) AMM 27-81-00/201, Leading Edge Slat System (2) AMM 78-31-00/201, Thrust Reverser System B. Access (1) Location Zones 510/610 Wing Leading Edge - Forward of front spar and inboard of nacelle strut C. Procedure S 044-017 _______ WARNING: DO THE THRUST REVERSER DEACTIVATION PROCEDURE TO PREVENT THE OPERATION OF THE THRUST REVERSER. ACCIDENTAL OPERATION OF THE THRUST REVERSER CAN CAUSE INJURY TO PERSONS OR DAMAGE TO EQUIPMENT.

2.

(1)

ALL AIRPLANES EXCEPT AIRPLANES WITH CF6-80C2 ENGINES; Do the deactivation procedure for the thrust reverser (AMM 78-31-00/201). S 034-006 Fully retract the inboard leading edge slats (AMM 27-81-00/201). S 864-007 Remove power from the inboard leading edge slats (AMM 27-81-00/201). S 024-008 Remove the screws from the door and remove the door. ____ NOTE: Keep the shims for the subsequent installation.

(2)

(3)

(4)

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767 MAINTENANCE MANUAL

INBOARD LEADING EDGE SIDE BRACE SUPPORT LINK DOOR SEE A

SCREW (EXAMPLE) INBOARD LEADING EDGE MID SUPPORT LINK DOOR SEE B

DOOR SUPPORT (2 LOCATIONS)

SHIM SCREW (9 LOCATIONS) DOOR SUPPORT (3 LOCATIONS)

SHIM

MID SUPPORT LINK SCREW (17 LOCATIONS) SHIM

INBOARD LEADING EDGE SIDE BRACE SUPPORT LINK DOOR A

SHIM

SHIM

INBOARD LEADING EDGE MID SUPPORT LINK DOOR B Inboard Leading Edge Support Link Doors Figure 401
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S 214-021 _______ WARNING: DO NOT LET OBJECTS GET IN THE HOUSING ASSEMBLY OF THE SLAT TRACK. THIS WILL HELP PREVENT A PUNCTURE OF THE HOUSING ASSEMBLY THAT COULD CAUSE A FUEL LEAK. THE FUEL LEAK COULD CAUSE A FIRE AND POSSIBLE DEATH OR INJURY TO PERSONNEL. (5) Examine the area to make sure objects are not left in the slat track housing assembly. TASK 57-41-59-404-023 _______________ Remove the Seal Door for CDL 57-41-1 (Fig. 40l) A. References (1) AMM 27-81-00/201, Leading Edge Slat System (2) AMM 27-81-00/501, Leading Edge Slat System (3) AMM 78-31-00/201, Thrust Reverser System B. Access (1) Location Zones 510/610 Leading Edge - Forward of front spar and inboard of nacelle strut C. Procedure S 024-024 This procedure is for the temporary removal of the slat actuator seal door due to damage and for allowed continued revenue flight per CDL 57-41-1.

3.

(1)

S 044-025 _______ WARNING: DO THE THRUST REVERSER DEACTIVATION PROCEDURE TO PREVENT THE OPERATION OF THE THRUST REVERSER. THE ACCIDENTAL OPERATION OF THE THRUST REVERSER CAN CAUSE INJURY TO PERSONS OR DAMAGE TO EQUIPMENT EQUIPMENT. (2) Do this procedure: Thrust Reverser Deactivation for Ground Maintenance (AMM 78-31-00/201).

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767 MAINTENANCE MANUAL

(3)

S 864-031 Fully retract the inboard leading edge slats (Ref 27-81-00/201). S 044-026 Do this procedure: Remove power from the Inboard Leading Edge Slats (AMM 27-81-00-/201). S 014-027 Remove the screws from the seal door. S 024-028 Remove the seal door. NOTE: ____ Keep the shims, and write a record of their positions to help you install them correctly in the subsequent installation procedure.

(4)

(5)

(6)

S 214-029 _______ WARNING: DO NOT LET OBJECTS GET IN THE HOUSING ASSEMBLY OF THE SLAT TRACK . THIS WILL HELP PREVENT A PUNCTURE OF THE HOUSING ASSEMBLY THAT COULD CAUSE A FUEL LEAK. THE FUEL LEAK COULD CAUSE A FIRE AND POSSIBLE DEATH OR INJURY TO PERSONNEL. Examine the area to make sure objects are not left in the slat track housing assembly. S 024-030 _______ CAUTION: DO NOT OPERATE THE SLATS WITH THE SUPPORT/ATTACHMENT BRACKETS DOWN (LOOSE AT ONE END) WHEN THE CONTROL ROD DOOR (ACTUATOR SEAL DOOR) IS REMOVED. IMPACT DAMAGE TO THE FIXED SPLICE PLATE ON THE LEADING EDGE LOWER SURFACE CAN OCCUR. Remove the outboard leading edge slat linkage fairing panel aft position support bracket as follows: (a) Remove the bolt that attaches the aft support bracket and the actuator rod to the rotary actuator drive arm. (b) Remove the aft support bracket from the actuator rod to the rotary actuator drive arm. (c) Reinstall the bolt for the actuator rod to the actuator drive arm.

(7)

(8)

4.

TASK 57-41-59-404-009 ________________ Install the Door (Fig. 401) A. References (1) AMM 27-81-00/201, Leading Edge Slat System (2) AMM 78-31-00/201, Thrust Reverser System

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B.

767 MAINTENANCE MANUAL

Access (1) Location Zones 510/610 Wing Leading Edge - Forward of front spar and inboard of nacelle strut Procedure S 434-010 Put the shims in the same positions from which they were removed. S 424-011 Install the door with the screws. S 224-012 Make sure the edges of the door are smooth to within 0.02 inch of the contour of the leading edge slat. S 434-013 If the door is not within tolerance, add or remove the correct amount of shims on the door supports.

C.

(1)

(2)

(3)

(4)

S 214-022 _______ WARNING: DO NOT LET OBJECTS GET IN THE HOUSING ASSEMBLY OF THE SLAT TRACK. THIS WILL HELP PREVENT A PUNCTURE OF THE HOUSING ASSEMBLY THAT COULD CAUSE A FUEL LEAK. THE FUEL LEAK COULD CAUSE A FIRE AND POSSIBLE DEATH OR INJURY TO PERSONNEL. (5) Examine the area to make sure objects are not left in the slat track housing assembly. S 444-018 ALL AIRPLANES EXCEPT AIRPLANES WITH CF6-80C2 ENGINES; Do the activation procedure for the thrust reverser (AMM 78-31-00/201). S 864-001 Return power to the inboard leading edge slats (AMM 27-81-00/201).

(6)

(7)

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_______________________________________________ MAIN TRACK BEARING PLATE - REMOVAL/INSTALLATION 1.

767 MAINTENANCE MANUAL

_______ General A. This procedure contains two tasks. The first task is the removal of the bearing plates for the main track of the outboard leading edge. The second task is the installation of the bearing plates. B. There are two pairs of bearing plates attached to each main track rib on the outboard leading edge. The two pairs are referred to as the aft bearing plates and the forward bearing plates. TASK 57-41-65-004-020 ____________________________________________ Remove the Bearing Plates for the Main Track (Fig. 401) A. Access (1) Location Zones 520/620 Wing Leading Edge - Forward of front spar and outboard of nacelle strut B. Procedure S 034-017 Do the steps that follow to remove the aft bearing plates (View A-A, Fig. 401): (a) Remove the forward bolt. _______ CAUTION: DO NOT REMOVE THE AFT BOLT. IF YOU REMOVE THE AFT BOLT, THE STOP FITTING CAN FALL INTO THE TRACK HOUSING FOR THE INTERNAL TANK.

2.

(1)

(b) (c)

Loosen the aft bolt until the bearing plate is loose. Remove the aft bearing plate.

(2)

S 034-018 Do the steps that follow to remove the forward bearing plates (View B-B, Fig. 401). (a) Remove the aft bolt.

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767 MAINTENANCE MANUAL
OUTBOARD SLAT SEE A

AUXILIARY TRACK

AUXILIARY TRACK

OUTBOARD SLAT

MAIN TRACK RIB SEE B FWD

INBD

OUTBOARD SLAT PLAN VIEW, SLAT NO. 5 SHOWN (EXAMPLE, SLAT NO. 1-4 AND 8-12) A
ROLLER (2 LOCATIONS) FORWARD BEARING PLATE ROLLER (2 LOCATIONS)

GROMMET

AFT BEARING PLATE 1

A

A B B
FWD

BOLT (4 LOCATIONS)

MAIN TRACK RIB B
1 THE AFT BEARING PLATE IS NOT USED ON ALL MAIN TRACK INSTALLATIONS

Main Track Bearing Plate Figure 401 (Sheet 1)
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1.70 INCHES 1.68 MAIN TRACK RIB (2 LOCATIONS) MAIN TRACK RIB (2 LOCATIONS) WASHER BOLT (4 LOCATIONS) SHIM (2 LOCATIONS) SHIM (2 LOCATIONS)

767 MAINTENANCE MANUAL
PIN (2 LOCATIONS) 1.70 INCHES 1.68

WASHER BOLT (2 LOCATIONS)

AFT BEARING PLATE SEE C

FORWARD BEARING PLATE SEE D

STOP FITTING (2 LOCATIONS)

A-A

B-B

SHIM SHIM BEARING PLATE

SHIM NUTPLATE

SHIM BEARING PLATE

BEARING PLATE

BEARING PLATE

AFT BEARING PLATE C

FORWARD BEARING PLATE D

Main Track Bearing Plate Figure 401 (Sheet 2)
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899737

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(b) Remove the bearing plate.

767 MAINTENANCE MANUAL

S 214-025 _______ WARNING: DO NOT LET OBJECTS GET IN THE HOUSING ASSEMBLY OF THE SLAT TRACK. THIS WILL HELP PREVENT A PUNCTURE OF THE HOUSING ASSEMBLY THAT COULD CAUSE A FUEL LEAK. THE FUEL LEAK COULD CAUSE A FIRE AND POSSIBLE DEATH OR INJURY TO PERSONNEL. Examine the area to make sure objects are not left in the slat track housing assembly.

(3)

3.

TASK 57-41-65-404-019 _____________________________________________ Install the Bearing Plates for the Main Track (Fig. 401) A. Consumable Materials (1) C00259 Primer - BMS 10-11, Type I B. Access (1) Location Zones 520/620 Wing Leading Edge - Forward of front spar and outboard of nacelle strut C. Procedure S 434-010 Do the steps that follow to install the aft bearing plates (View A-A, Fig. 401): (a) Put the aft bearing plate in the correct location with the aft bolt in the slot. (b) Install the forward bolt. (c) Tighten the aft bolt. S 434-021 Do the steps that follow to install the forward bearing plates (View B-B, Fig. 401): (a) Put the forward bearing plate in the correct location with the pin in the slot. (b) Install the aft bolt. S 224-022 Make sure the clearance between the bearing plate surfaces is 1.68 to 1.70 inches (Views A-A and B-B, Fig. 401). S 824-023 If you do not get the correct clearance, do the steps that follow: (a) Remove the bearing plates. (b) Adjust the thickness of the shims on the back of the bearing plates. ____ NOTE: (c) (d) The maximum shim thickness is 0.063 inch.

(1)

(2)

(3)

(4)

Apply primer to the bare shim surface. Install the bearing plates.

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(e) Do a clearance check again.

767 MAINTENANCE MANUAL

S 214-026 _______ WARNING: DO NOT LET OBJECTS GET IN THE HOUSING ASSEMBLY OF THE SLAT TRACK. THIS WILL HELP PREVENT A PUNCTURE OF THE HOUSING ASSEMBLY THAT COULD CAUSE A FUEL LEAK. THE FUEL LEAK COULD CAUSE A FIRE AND POSSIBLE DEATH OR INJURY TO PERSONNEL. Examine the area to make sure objects are not left in the slat track housing assembly.

(5)

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__________________________________________ CORROSION PREVENTION IN WING TRAILING EDGE 1. _______ General A. The deployment of flight control surfaces exposes the spars to ground contaminants, thrust reverser soot, runway dirt and debris, and inclement weathr elements, all of which contribute to corrosion. B. Severe corrosion can occur around nutplates and rib chords of inboard aileron support ribs (Figure 201). C. Corrosion can occur under the cove panel of the inboard flaps. D. Minor surface corrsion can occur on the right and left wing inboard trailing edge flap rear spar upper chord (Figure 201). E. Corrosion can occur on the balance arms of the outboard ailerons where the balance weights are attached. F. Surface corrosion can occur on the upper chord of the inboard-trailing-edge flap rear spar. This corrosion causes bulges in the cove panel lap joint at the rear spar. Corrosion can also occur on the lower chord. Corrosion can be caused by moisture which comes in when removable fasteners are not installed with sealant. TASK 57-50-01-602-001 _______________________________ Corrosion Prevention Treatment A. General (1) Following cleaning of suspected areas (Ref AMM 51-21-03/701), a full inspection is effective to ensure that protective finishes provided during manufacture remain intact. (2) For minor corrosion, to minimize the downtime of the airplane, the corrosion products should be cleaned off, followed by the application of a corrosion inhibiting compound into the affected area to retard the corrosion process (Ref AMM 51-24-09/701). The finish system should be repaired at the first opportunity consistent with the maintenance schedule. (3) Frequency of Application (a) Regular inspection is required in areas that can get corrosion. Use the schedules in the Maintenance Planning Document. Operators must know of reported problems and areas. (b) Periodic application of BMS 3-23 compound is necessary to areas identified and should be consistent to the schedule specified in the Maintenance Planning Document. B. References (1) AMM 51-21-03/701, Corrosion Removal and Control-Cleaning/Painting (2) AMM 51-24-09/701, Corrosion Inhibiting Compound-Cleaning/Painting C. Consumable Materials (1) G0009 Compound, Organic Corrosion Preventive - BMS 3-23

2.

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A
INBD TRAILING EDGE FLAP SEE B INBD AILERON RIB STRUCTURE SEE A

767 MAINTENANCE MANUAL
OUTBOARD AILERON SEE D

AILERON HINGE SUPPORT RIB NUTPLATE LOCATIONS 1 (TYPICAL) AILERON HINGE SUPPORT RIB REAR SPAR

WS 468.11

SLING ASSY

AILERON HINGE RIB A

COVE PANEL

2

SEE

C

BRACKET (3 PLACES) 2

REAR SPAR INBD TE MAIN FLAP FRONT SPAR CORROSION COVE PANEL

INBD TRAILING EDGE FLAP B

REAR SPAR UPPER CHORD

1

CORROSION FOUND AROUND NUTPLATES AND RIB CHORD AT THIS LOCATION

C
2 IF FASTENERS ARE REMOVED, INSTALL THEM WITH WET SEALANT

Wing Trailing Edge Corrosion Protection Figure 201 (Sheet 1)
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HINGE FITTINGS

BALANCE ARM NO. 3 SEE HINGE FITTING ACTUATOR FITTINGS HINGE FITTING INBD FWD E

OUTBOARD AILERON D

BALANCE ARM NO. 5 SKIN LEADING EDGE HINGE FITTING SEE BALANCE WEIGHT F BRACKET COVER

FAY SEALANT

FASTENERS INSTALLED WITH WET SEALANT

AERODYNAMIC SEAL (REF)

NO. 3 BALANCE ARM DETAILS E
SEALANT WEIGHT UNTRIMMED EDGE COVER WEIGHT SEALANT TRIMMED EDGE COVER

BRACKET

BRACKET

CONFIGURATION BEFORE THE CHANGE (REF) F

CONFIGURATION AFTER THE CHANGE F

Wing Trailing Edge Corrosion Protection Figure 201 (Sheet 2)
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D.

767 MAINTENANCE MANUAL

Access (1) Location Zones 550/650 Left Wing Trailing Edge/Right Wing Trailing Edge Procedure S 602-002 At first opportunity consistent with scheduled maintenance activity, do the corrosion prevention treatment on the skins, structure and devices of the wing trailing edge. S 402-006 Install removable fasteners used at sling bracket locations with sealant to prevent water intrusion and subsequent entrapment within Inboard Trailing Edge Main Flap. S 602-007 CAUTION: DO NOT APPLY CORROSION INHIBITING COMPOUNDS ON GREASE JOINTS OR SEALED BEARINGS. THESE COMPOUNDS DISSOLVE GREASE AND OTHER LUBRICANTS. THEY ARE PENETRATING COMPOUNDS AND CAN GET AROUND THE SEALS AND INTO THE BEARINGS.

E.

(1)

(2)

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__________________________________ AILERON CONDUCTING STRIP - REPAIRS 1. _______ General A. This section contains one task: (1) The repair of a static discharger conducting frame assembly (referred to as "conducting frame") at the outboard aileron. B. The repair of the conducting frame is as follows: (1) Remove the static dischargers, (2) Remove the damaged conducting frame, (3) Clean the new conducting frame, (4) Bond the new conducting frame to the aileron, (5) Install the static dischargers, (6) Apply a smooth finish to the conducting frame. C. This procedure gives instructions to repair the items as follows: (1) The aluminum conducting frame between the outboard aileron trailing edge and the two static dischargers. (a) You must replace the conducting strip if more than half the width of the strip is damaged. (b) You can apply the approved conductive paint to the surface with BMS 10-21. (c) Do this step if less than half the width of the conducting strip is damaged. (2) The static discharger attaches to the outboard aileron. (a) Static dischargers also attach to the ground strap. The ground strap is bonded with adhesive to the non-conductive aileron surface of the trailing edge. Then the strap is electrically bonded to the aileron outboard rib. (b) If the electrical bond of the ground strap at the outboard rib becomes weak, these conditions will follow: 1) The static dischargers to the aileron can become electrically isolated. 2) The static dischargers will not operate. (c) If you find these conditions, you must repair the electrical bond of the ground strap. TASK 57-51-03-308-001 Repair the Conducting Strip ___________________________ A. Standard Tools and Equipment (1) Meter - Bonding (Ref 20-10-21/601 Electrical Bonding) (2) Scraper - Plastic or Hardwood B. Consumable Materials (1) G00000 Paper - Aluminum Oxide, 240-grit or finer (2) B00000 Cleaner - Alkaline, Ridolene No. 53 (3) A00966 Compound - EC-2216 Part A and Part B (4) B00148 Solvent - Methyl Ethyl Ketone (MEK), TT-M-261 (5) G00033 Cheesecloth

2.

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(6) (7)

767 MAINTENANCE MANUAL

C.

D.

E.

A00247 Sealant - BMS 5-95 C00064 Coating - Surface treatment, MIL-C-5541 (Alodine 1200 or 1200S) (8) G00000 Aluminum Sheet - 1100-0 or 505250, 0.010 inch thick References (1) 23-61-00/201, Static Dischargers (2) SRM 51-40-09 (3) Phosphoric Acid (SRM 51-70-09). Access (1) Location Zone 592 Outboard Aileron, Left 692 Outboard Aileron, Right Remove the conducting strip (Ref Figure 801). S 038-002 Cut the conducting strip near the base of each static discharger found at the ends of the damaged area. S 018-003 Remove the static dischargers if it is necessary (Ref 23-61-01/201). S 358-004 Remove the damaged parts of the conducting strip. (a) Remove the strip from the aileron where it is possible. ____ NOTE: Be careful to prevent damage to the fiberglass.

(1)

(2)

(3)

_______ CAUTION:

DO NOT APPLY PRESSURE TO THE SURFACE OF THE OF AILERON TO WHERE YOU CAUSE DAMAGE TO THE FIBERGLASS. DO NOT APPLY PRESSURE TO CAUSE THE FIBERGLASS FILAMENTS TO COME OUT.

F.

As a last step, remove the remaining strip with aluminum oxide sandpaper. Install the conducting strip (Ref Figure 802). S 358-005 Make the conducting strip. (a) Use the remaining conducting strip found above the static discharger locations as a template. (b) Use this template to cut the new strip to make the correct fit. (c) Drill holes in the new strip to align with the attach holes in the remaining strips. S 118-006 Before installation, clean the new conducting strip. (a) Remove the grease and apply the recommended alkaline cleaner.

(b)

(1)

(2)

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(b)

767 MAINTENANCE MANUAL

Soak the conducting strip in the alkaline cleaner for a minimum of 10 minutes. ____ NOTE: 1) The temperature of the cleaner must be 160bF to 180bF.

(c)

Flush the conducting strip with clean water until the strip has no more water on it. Dry the strip with a lint-free cloth. ____ NOTE: The temperature of the water must be a minimum of 110bF.

(d) (e)

For the side that you bond, rub smooth grit sandpaper on that side. Wash and rub that side clean.

(3)

S 388-014 Use the BOEGEL sol-gel method (preferred) or the Phosphoric Acid Containment System (PACS) method (alternate) to prepare the conductive strip and the repair area for bonding (SRM 51-70-10). S 428-007 Install the conducting strip. (a) Prepare the adhesive. _______ WARNING: THESE CHEMICALS AGENTS ARE POISONOUS. USE IN OPEN AREAS ONLY. WITHOUT PROTECTION, DO NOT TOUCH THE RESIN OR THE CURING AGENT. DO NOT GET THEM IN YOUR EYES. ALWAYS WEAR RUBBER GLOVES ON TOP OF THE COTTON GLOVES FOR PROTECTION OF YOUR HANDS. IF YOUR SKIN TOUCHES THE RESINS OR THE CURING AGENT, CLEAN THOSE AREAS WITH WARM WATER AND SOAP. DO NOT USE SOLVENTS TO CLEAN YOUR SKIN.

(4)

1)

Fully mix 140 parts by weight of EC-2216 Part A with 100 parts by weight of EC-2216 Part B. ____ NOTE: The pot life of the mixture is approximately 2 hours.

_______ WARNING:

DO NOT GET SOLVENTS IN YOUR MOUTH, OR YOUR EYES, OR ON YOUR SKIN. DO NOT BREATHE THE FUMES FROM SOLVENTS. SOLVENTS ARE HAZARDOUS MATERIALS. SOLVENTS MAY BE FLAMMABLE OR HARMFUL TO THE ENVIRONMENT. REFER TO PRODUCT MATERIAL SAFETY DATA SHEETS (MSDS) AND LOCAL REQUIREMENTS FOR PROPER HANDLING PROCEDURES.

(b) (c)

Apply solvent, Series 89 (AMM 20-30-89) to the area where you removed the conducting strip. Also clean the areas of the remaining conducting strip above the static discharger.

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(d)

767 MAINTENANCE MANUAL

Use a clean gauze or cheesecloth to absorb the solvent before it dries. ____ NOTE: To prevent contamination on the surfaces, permit no more than 1 hour span from the time you clean to the time you you bond.

(e) (f)

Apply a thin layer of adhesive to the trailing edge of the aileron and to the conducting strip. Do not apply adhesive to the ends of the strip where it makes an overlap with the remaining strip. ____ NOTE: New and remaining strips must have full electrical contact at areas that make an overlap

(g)

Remove the unwanted adhesive with a clean gauze or cheesecloth lightly moist with solvent, Series 89 (AMM 20-30-89). ____ NOTE: Do not permit the solvent to get in the area that you bond.

(h)

Apply pressure and dry the bond (SRM 51-70-03).

(5)

S 418-008 To complete the static discharger installation, you must obey 23-61-01/201 and the instructions that follow: (a) Apply sealant if it is necessary to fill the space where the new conducting strip makes an overlap with the remaining strip. (b) Use the bonding meter to measure the resistance between the discharger base and the conducting strip (Ref 20-10-21/601). (c) To make sure that there is electrical contact between the strips, measure to the remaining conducting strip and to the new conducting strip. ____ NOTE: The resistance must be no more than 0.010 ohms.

G.

S 228-009 Measure the resistance between the rod and the base of the static dischargers that you installed during this repair (Ref 23-61-01/201). Conducting Strip Finish. (6) S 358-010 Use smooth grit sandpaper to make the open surface of the conducting strip shiny.

(1)

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(2)

S 168-011 Wash and rub the area clean. S 378-012 Use a brush to apply Alodine 1200S or 1200 to the open surface of the strip. ____ NOTE: You will apply this last finish if it is necessary.

(3)

H.

Repair the Aileron Static Discharger Conducting Strip S 358-013 If you only want to repair the electrical bonding of the aileron static discharger conducting strip, do the following: (a) Remove the static dischargers. (b) Remove the damaged portion of the conducting strip. (c) Clean the faying surfaces between the conducting strip and the aileron surface with aluminum oxide paper. (d) Wash and wipe the cleaned surfaces to remove residue. (e) Treat the cleaned surfaces with Alodine. (f) Bond the new conducting strip to the aileron. (g) Install the static dischargers. (h) Check the bonding resistance between the existing conducting strip and the new conducting strip. NOTE: (i) The resistance must be no more than 0.010 ohms.

(1)

Check the bonding resistance between the existing conducting strip and the static dischargers. NOTE: The resistance must be no more than 0.010 ohms.

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767 MAINTENANCE MANUAL

SEE

A

OUTBOARD TRAILING EDGE WEDGE BOX DISCHARGER BASE TRIM LINE, REPLACEMENT STRIP

TRIM LINE, EXISTING STRIP

STRIP OVERLAP

TRIM LINE, EXISTING STRIP

STATIC DISCHARGER

CONDUCTING STRIP TRIM LINE, REPLACEMENT STRIP FWD

TRAILING EDGE CONDUCTING STRIP AND STATIC DISCHARGERS (TYPICAL) A Aileron Conducting Strip Repair Figure 801
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LOWER CHORD

FILLER

EXISTING BOLTS

1 AILERON SKIN PANEL NEW GROUND STRAP. ROUTE APPROX AS SHOWN

1 EXISTING GROUND STRAP

1

CLEAN FAYING SURFACES SHOWN

Aileron Internal Bonding Repair Figure 802
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___________________________________________ TRAILING EDGE PANELS - REMOVAL/INSTALLATION 1. _______ General A. This procedure has two tasks: (1) The first task gives instructions to remove the trailing edge panels from the wing. (2) The second task gives instructions to install the trailing edge panels on the wing. TASK 57-51-10-004-003 _______________________________ Remove the Trailing Edge Panels A. Equipment (1) Attach Fitting Set - Wing Safety Harness, A20002-4 B. References (1) 27-51-00/201, Trailing Edge Flap System C. Access (1) Location Zones 500/600 Left Wing/Right Wing D. Procedure S 424-019 _______ WARNING: USE A MAN LIFT TO ATTACH THE SAFETY HARNESS FITTINGS TO THE RECEPTACLES. MAINTENANCE PERSONS CAN FALL WHICH MAY CAUSE INJURY TO PERSONS OR DAMAGE TO EQUIPMENT. DO NOT WALK ON THE WING WITHOUT A SAFETY HARNESS. MAINTENANCE PERSONS CAN FALL WHICH MAY CAUSE INJURY TO PERSONS OR DAMAGE TO EQUIPMENT.

2.

_______ WARNING:

(1)

Attach the Flight Control Safety Lanyard to the wing (AMM 20-10-27).

(2)

S 014-004 Fully retract the trailing edge flaps (Ref 27-51-00). S 864-005 Do the Deactivation Procedure for the Trailing Edge Flaps procedure (Ref 27-51-00). S 864-001 Put these switches on the pilots' overhead panel, P5, in the OFF position and attach DO-NOT-OPERATE tags: (a) L WING FLT CONTROL SHUTOFF (b) C WING FLT CONTROL SHUTOFF (c) R WING FLT CONTROL SHUTOFF S 214-006 Make sure the amber light-switch is on.

(3)

(4)

(5)

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ADJUSTABLE WING TRAILING EDGE PANELS ADJUSTABLE WING TRAILING EDGE PANELS WING TRAILING EDGE

WING TRAILING EDGE PANELS

SUPPORT ROD (EXAMPLE) ATTACH BOLT PANEL ATTACH BOLT (EXAMPLE) 2 LOCKNUT ATTACH BOLT SEAL

TRAILING EDGE PANEL (EXAMPLE) 1

ATTACH BOLT

LOCKNUT PANEL ATTACH BOLT (EXAMPLE) 2

SUPPORT ROD (EXAMPLE) SEAL

TRAILING EDGE PANEL (EXAMPLE) 1

ATTACH BOLT

SUPPORT ROD (EXAMPLE)
1 THE CLEARANCE BETWEEN THE ADJACENT TRAILING EDGE PANELS, AND BETWEEN THE TRAILING EDGE PANELS AND THE LOWER WING SKIN PANELS IS 0.02 TO 0.12 INCH. DO NOT FILL THE CLEARANCES WITH AERODYNAMIC SMOOTHER. MAKE SURE THE FLUSHNESS BETWEEN THE BOLTS AND THE EXTERIOR SURFACE OF THE WING TRAILING EDGE PANELS IS BETWEEN -0.010 INCH AND +0.005 INCH.

2

Wing Trailing Edge Panels Figure 401
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24958

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(6)

S 864-007 Open these circuit breakers on the overhead circuit breaker panel, P11, and attach DO-NOT-CLOSE tags: (a) 11H14 or 11H15, FLT CONT SHUTOFF WING LEFT (b) 11H15 OR 11H16, FLT CONT SHUTOFF WING CENTER (c) 11H26, FLT CONT SHUTOFF WING RIGHT S 014-008 Open the panels. ____ NOTE: You cannot open some of the panels.

(7)

(8)

S 034-009 Disconnect the bonding jumpers. S 034-010 Remove the bolts from the panels.

(9)

S 024-011 (10) Remove the panels. TASK 57-51-10-404-012 ________________________________ Install the Trailing Edge Panels A. Access (1) Location Zones 500/600 Left Wing/Right Wing B. Procedure S 434-013 Put the panels on the support structure to align the fastener holes. S 434-014 Install the bolts (Fig. 401). S 414-015 On the panels that you can open, connect the bonding jumpers. S 414-016 Close the panels. S 864-017 Remove the DO-NOT-CLOSE tags and close these circuit breakers on the P11 panel: (a) 11H14 OR 11H15, FLT CONT SHUTOFF WING LEFT (b) 11H15 OR 11H16, FLT CONT SHUTOFF WING CENTER

3.

(1)

(2)

(3)

(4)

(5)

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(c) 11H26, FLT CONT SHUTOFF WING RIGHT

767 MAINTENANCE MANUAL

(6)

S 864-002 Remove the DO-NOT-OPERATE tags and put these switches on the P5 panel in the ON position: (a) L WING FLT CONTROL SHUTOFF (b) C WING FLT CONTROL SHUTOFF (c) R WING FLT CONTROL SHUTOFF

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______________________________________ TRAILING EDGE PANELS - ADJUSTMENT/TEST 1. _______ General A. This procedure contains two tasks. (1) The first task is the adjustment of the lower trailing edge panels. (2) The second task is the adjustment of the upper trailing edge panels. TASK 57-51-10-825-001 _______________________________________ Adjustment - Lower Trailing Edge Panels A. Consumable Materials (1) A00247 Sealant - BMS 5-95 B. References (1) 27-51-03/401, Inboard TE Flap (2) 51-31-01/201, Seals and Sealing C. Access (1) Location Zones 550/650 Wing Trailing Edge D. Procedure S 825-002 Adjust the main flaps (Ref 27-51-03) S 225-003 Measure the vertical flushness between the lower trailing edge panels and the main flap (View A-A, Fig. 501). S 825-004 If the vertical flushness is not as shown (Fig. 501), adjust the lower trailing edge panels as follows: (a) Remove the wing access panels, as necessary, to get access to the tie-rods for the lower trailing edge. (b) Adjust one or more tie-rods, as necessary, until the vertical flushness is correct along the full length of the trailing edge panels. S 225-005 Measure the clearance between the bulb seal retainer and the leading edge of the main flap (View A-A, Fig. 501). S 825-006 If the clearance is not as shown (Fig. 501), adjust the bulb seal retainer as follows: (a) Remove the sealant from the area that you will adjust. (b) Adjust the bulb seal retainer, as necessary, until the clearance is correct along the full length of the lower trailing edge panels.

2.

(1)

(2)

(3)

(4)

(5)

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_______ CAUTION:

OBEY THE INSTRUCTIONS IN THE PROCEDURE TO APPLY THE SEALANT. IF YOU DO NOT OBEY THE INSTRUCTIONS, DAMAGE TO THE AIRPLANE SURFACE CAN OCCUR.

(c)

Apply the sealant on the area that you adjusted (AMM 51-31-01/201).

(6)

S 415-007 Install the wing access panels.

3.

TASK 57-51-10-825-009 ________________________________________ Adjustment - Upper Trailing Edge Panels A. Access (1) Location Zones 550/650 Wing Trailing Edge B. Procedure S 225-010 Measure the vertical flushness between the upper trailing edge panels and the adjacent spoiler panels and fixed wing (View B, Fig. 501). S 825-011 If the vertical flushness is not as shown (Fig. 501), adjust the upper trailing edge panels as follows: (a) Remove the wing access panels, as necessary, to get access to the tie-rods for the upper trailing edge. (b) Adjust one or more tie-rods, as necessary, until the vertical flushness is correct along the full length of the trailing edge panels. S 825-012 Measure the gap clearance between the upper trailing edge panel and the fixed wing (View B, Fig. 501). S 825-013 If the gap clearance is not as shown (Fig. 501), adjust the upper trailing edge panels as follows: (a) Remove the wing access panels, as necessary, to get access to the tie-rods for the upper trailing edge panel.

(1)

(2)

(3)

(4)

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(b)

767 MAINTENANCE MANUAL

Adjust one or more tie-rods, as necessary, until the gap clearance between the upper trailing edge panel and the fixed wing is correct along the full length of the trailing edge panels.

(5)

S 415-014 Install the wing access panels.

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TRAILING EDGE PANEL SEE A

UPPER TRAILING EDGE PANEL TIE ROD

TIE ROD TIE ROD

A

A

LOWER TRAILING EDGE PANEL ACCESS PANEL (EXAMPLE)

LOWER TRAILING EDGE PANEL

TRAILING EDGE PANEL (RIGHT SIDE IS SHOWN, LEFT SIDE IS EQUIVALENT) (VIEW IN THE FORWARD DIRECTION) A

Trailing Edge Panels Adjustment Figure 501 (Sheet 1)
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UPPER TRAILING EDGE PANEL TO FIXED WING GAP SEE B

767 MAINTENANCE MANUAL

UPPER TRAILING EDGE PANEL

MAIN FLAP

TIE ROD

BULB SEAL REATINER 2 BULB SEAL SEALANT 3 FWD

1

LOWER TRAILING EDGE PANEL

A-A
1 2 THE VERTICAL FLUSHNESS BETWEEN THE LOWER TRAILING EDGE PANEL AND THE MAIN FLAP IS |0.06 INCH (|1.524 mm). THE CLEARANCE BETWEEN THE BULB SEAL RETAINER AND THE LEADING EDGE OF THE MAIN FLAP IS FROM 0.01-0.06 INCH (0.254-1.524 mm) ON L/N 001 TO L/N 602 AND 0.00-0.06 INCH (0.00-1.524 mm) FOR L/N 603 AND ON. SEALANT IS REQUIRED ONLY ON L/N 001-L/N 602.

3

Trailing Edge Panels Adjustment Figure 501 (Sheet 2)
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5

4

UP

FWD

UPPER TRAILING EDGE PANEL TO FIXED WING GAP B

4 5

|0.03 INCH (|0.762 mm) TO FIXED WING AND ADJACENT SPOILER PANELS. 0.28 -0.16/+0.08 INCH (7.112 -4.064/+2.03 mm) GAP BETWEEN UPPER TRAILING EDGE PANEL AND FIXED WING.

Trailing Edge Panels Adjustment Figure 501 (Sheet 3)
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_______________________________________________________________________ TRAILING EDGE SEAL (FORWARD OF OUTBOARD AILERON) - REMOVAL/INSTALLATION 1. _______ General A. This procedure has two tasks: (1) The first task is instructions to remove the trailing edge seal (forward of the outboard aileron). (2) The second task is instructions to install the trailing edge seal (forward of the outboard aileron). TASK 57-51-11-004-005 _______________ Remove the Seal (Fig. 401) A. References (1) 27-51-00/201, Trailing Edge Flaps

2.

UPPER FIXED WING PANEL

BOLT (EXAMPLE)

SEAL RETAINER

A
NUT

UPPER SURFACE OUTBOARD AILERON SEAL 1

A

1

THE LEFT OUTBOARD AILERON SEAL IS SHOWN. THE RIGHT OUTBOARD AILERON SEAL IS EQUIVALENT.

A-A

Trailing Edge Seal (Forward of Outboard Aileron) Figure 401
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(2) 57-51-10/401, Trailing Edge Panels Access (1) Location Zones 500/600 Left Wing/Right Wing Procedure - Remove the seal

767 MAINTENANCE MANUAL

B.

C.

(1)

S 864-001 Put these switches on the right side panel, P61, in the OFF position: (a) L WING FLT CONTROL SHUTOFF (b) C WING FLT CONTROL SHUTOFF (c) R WING FLT CONTROL SHUTOFF S 214-002 Make sure the legend lights in the switches are on. S 864-006 Open these circuit breakers on the overhead circuit breaker panel, P11, and attach DO-NOT-CLOSE tags: (a) 11H14, FLT CONT SHUTOFF WING LEFT (b) 11H15, FLT CONT SHUTOFF WING CENTER (c) 11H26, FLT CONT SHUTOFF WING RIGHT S 034-007 Do the Deactivation Procedure for the Trailing Edge Flap System procedure (Ref 27-51-00). S 034-008 Remove the panels for the lower trailing edge as it is necessary to get access to the attach bolts (Ref 57-51-10). S 034-009 Remove the bolts from the seal. S 024-010 Remove the seal and the seal retainer.

(2)

(3)

(4)

(5)

(6)

(7)

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3.

TASK 57-51-11-404-011 ________________ Install the Seal (Fig. 401) A. References (1) 57-51-10/401, Trailing Edge Panels (2) 29-11-00/201, Main (Left, Right, and Center) Hydraulic Systems B. Access (1) Location Zones 500/600 Left Wing/Right Wing C. Procedure - Install the Seal S 424-012 Put the new seal and seal retainer in position. S 434-013 Install the bolts. S 434-014 Install the lower trailing edge panels (Ref 57-51-10). S 864-015 Remove the DO-NOT-CLOSE tags and close these circuit breakers on the overhead circuit breaker panel, P11: (a) 11H14, FLT CONT SHUTOFF WING LEFT (b) 11H15, FLT CONT SHUTOFF WING CENTER (c) 11H26, FLT CONT SHUTOFF WING RIGHT S 864-003 Put these switches on the P61 panel in the ON position: (a) L WING FLT CONTROL SHUTOFF (b) C WING FLT CONTROL SHUTOFF (c) R WING FLT CONTROL SHUTOFF S 844-016 Supply hydraulic power (Ref 29-11-00).

(1)

(2)

(3)

(4)

(5)

(6)

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(7)

S 714-017 Operate the outboard ailerons. S 714-004 Make sure the seal permits the aileron to operate correctly. S 034-018 Remove the hydraulic power if it is not necessary (Ref 29-11-00).

(8)

(9)

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_____________________________________________________ OUTBOARD FLAP VORTEX GENERATOR - REMOVAL/INSTALLATION 1. _______ General A. This procedure contains two tasks: (1) The first task is the removal instructions for the outboard flap vortex generator (generator). (2) The second task is the installation instructions for the generator. TASK 57-53-01-004-001 _________________________________________ Remove the Outboard Flap Vortex Generator A. Equipment (1) Attach Fitting Set - Wing Safety Harness, A20002-4 B. References (1) 20-10-27/201, Flight Control Surfaces Safety Harness Receptacle. (2) 27-51-00/201, Trailing Edge Flaps (3) 27-61-00/201, Spoiler/Speedbrake Control System C. Access (1) Location Zone 500/600 Wing D. Prepare for the Removal of the Outboard Flap Vortex Generator S 044-002 _______ WARNING: MOVE ALL PERSONS AND EQUIPMENT AWAY FROM THE SPOILERS WHEN YOU DO THE DEACTIVATION PROCEDURE FOR THE SPOILERS. THE SPOILERS CAN RETRACT QUICKLY AND CAUSE INJURY OR DAMAGE.

2.

(1)

Do the deactivation procedure for the spoilers (Ref 27-61-00). ____ NOTE: Make sure the spoilers are in the up position.

(2)

S 014-003 Extend the trailing edge flaps to the 5-unit detent, or to a position that permits satisfactory access to the generator (Ref 27-51-00). S 044-004 Do the deactivation procedure for the trailing edge flap system (Ref 27-51-00). S 864-005 Put these switches on the right side panel, P61, in the OFF position and attach DO-NOT-OPERATE tags: (a) FLT CONTROL SHUTOFF WING L (b) FLT CONTROL SHUTOFF WING C (c) FLT CONTROL SHUTOFF WING R S 214-006 Make sure the amber switch-position legend lights are ON.

(3)

(4)

(5)

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E.

S 864-007 Open these circuit breakers on the overhead circuit breaker panel, P11, and attach DO-NOT-CLOSE tags: (a) 11H14, FLT CONT SHUTOFF WING LEFT (b) 11H15, FLT CONT SHUTOFF WING CENTER (c) 11H26, FLT CONT SHUTOFF WING RIGHT Procedure - Remove the Outboard Flap Vortex Generator (6) S 494-028 _______ WARNING: ATTACH A SAFETY HARNESS WHEN YOU DO WORK ON TOP OF THE HORIZONTAL STABILIZER. FAILURE TO OBEY CAN CAUSE INJURY OR DAMAGE.

(1)

Attach the safety harness (Ref 20-10-27) S 934-008

_______ WARNING:

MAKE SURE YOU COMPLETED THE DEACTIVATION PROCEDURE FOR THE SPOILERS AND FLAPS. THE ACCIDENTAL MOVEMENT OF THE SPOILERS, FLAPS, AND AILERON CAN CAUSE INJURY OR DAMAGE.

(2)

Make a mark of the location of the old generator to help the subsequent installation of a new generator. ____ NOTE: The tolerance for the installation of a new generator is |0.03 inch and |1.0 degree.

(3)

S 034-009 Remove the screw that holds the generator to the flap. S 024-010 Remove the generator.

(4)

3.

TASK 57-53-01-404-011 __________________________________________ Install the Outboard Flap Vortex Generator A. Equipment (1) Threaded transfer punch to match vortex generator mounting screw - commercially available

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B.

C.

D.

(2) Attach Fitting Set - Wing Safety Harness, A20002-4 Consumable Materials (1) B00325 Cleaner, alkaline - Turco Jet Clean E (2) C00308 Corrosion Preventive Compound MIL-C-11796, Class 3 (3) C00259 Primer - BMS 10-11, Type I (4) A00247 Sealant, Chromate Type - BMS 5-95, Type I, Class B or C References (1) 20-10-27/201, Flight Control Surfaces Safety Harness Receptacle. (2) 27-51-00/201, Trailing Edge Flaps (3) 27-61-00/201, Spoiler/Speedbrake Control System (4) 51-21-01/701, Paint Stripping (5) 51-21-02/701, Prepaint Cleaning and Treatment (6) 51-21-10/701, Decorative Exterior Finishes (7) 51-31-01/201, Seals and Sealing Access (1) Location Zone 500/600 Wing Procedure - Install the Outboard Flap Vortex Generator S 024-031 _______ CAUTION: OBEY THE INSTRUCTIONS IN THE PROCEDURE TO REMOVE THE SEALANT. IF YOU DO NOT OBEY THE INSTRUCTIONS, DAMAGE TO THE AIRPLANE SURFACE CAN OCCUR.

E.

(1)

Remove the sealant from the area on the flap where the old generator was installed (AMM 51-31-01/201). S 934-013 Make a mark for the location of the screw hole for the generator as follows: (a) Put a threaded transfer punch in the nutplate on the flap at a depth that lets you make a mark on the new generator. (b) Put the new generator at the location on the flap where you made a mark. (c) Push the new generator to the transfer punch tip until you make a mark on the generator. (d) Make sure edge distance for the mounting screw is not less than 0.375 inch. (e) Remove the threaded transfer punch. S 324-014 Drill a 0.260-0.280-inch diameter hole in the new generator at the point where you made a mark. S 324-015 Countersink the hole in the generator at 100 degrees, until you get a 0.378-0.388 inch diameter.

(2)

(3)

(4)

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(5)

S 394-016 Prepare the flap and the generator mating surfaces for bonding (Ref 51-31-01). S 394-033

_______ CAUTION:

OBEY THE INSTRUCTIONS IN THE PROCEDURE TO APPLY THE SEALANT. IF YOU DO NOT OBEY THE INSTRUCTIONS, DAMAGE TO THE AIRPLANE SURFACE CAN OCCUR.

(6)

Apply the sealant to the flap and the generator mating surfaces that are aft of the flap front spar only (AMM 51-31-01/201). ____ NOTE: You must not apply the sealant to the mating surfaces that are forward of the front spar of the flap.

(7)

S 424-018 Put the new generator in position on the flap. S 104-019 Clean the countersink, and the holes in the generator and the flap skin with alkaline cleaner (Ref 51-21-02). S 374-020 Apply the primer to the countersink, and to the holes in the generator and the flap skin (Ref 51-21-10).

(8)

(9)

S 374-021 (10) When the primer is dry, apply the corrosion preventive compound to the countersink, and to the holes in the generator and the flap skin. S 214-022 (11) Make sure the generator is installed at the correct location. S 434-023 (12) Install the screw that holds the generator to the flap. ____ NOTE: You must install the screw in less than two hours after you apply the corrosion preventive compound.

S 094-029 (13) Remove the safety harness if it is not necessary (Ref 20-10-27).

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F. Put the Airplane Back to Its Usual Condition S 864-024 Remove the DO-NOT-CLOSE tags P11 panel: (a) 11H14, FLT CONT SHUTOFF (b) 11H15, FLT CONT SHUTOFF (c) 11H26, FLT CONT SHUTOFF

767 MAINTENANCE MANUAL

(1)

and close these circuit breakers on the WING LEFT WING CENTER WING RIGHT

(2)

S 864-025 Remove the DO-NOT-OPERATE tags and put these switches that are on the P61 panel in the ON position: (a) FLT CONTROL SHUTOFF WING L (b) FLT CONTROL SHUTOFF WING C (c) FLT CONTROL SHUTOFF WING R S 444-026

_______ WARNING:

MOVE ALL PERSONS AND EQUIPMENT AWAY FROM THE SPOILERS WHEN YOU DO THE ACTIVATION PROCEDURE FOR THE SPOILERS. THE SPOILERS CAN RETRACT QUICKLY AND CAUSE INJURY OR DAMAGE.

(3)

Do the activation procedure for the spoilers (Ref 27-61-00). S 444-027 Fully retract the trailing edge flaps (Ref 27-51-00).

(4)

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_____________________________________________________ MAIN LANDING GEAR SUPPORT LINK - REMOVAL/INSTALLATION 1. _______ General A. This procedure contains two tasks. The first task removes the main landing gear (MLG) support link from the strut swivel fitting and the support fitting. The second task installs the MLG support link to the strut swivel fitting and the support fitting. TASK 57-54-01-004-039 ______________________________________ Main Landing Gear Support Link Removal A. References (1) 07-11-01/201, Jacking Airplane (2) 29-11-00/201, Pressurize/Depressurize Main Hydraulic System (3) 32-00-15/201, Landing Gear Door Locks (4) 32-00-20/201, Landing Gear Downlocks B. Access (1) Location Zones 731/741 Main Landing Gear (MLG) 732/742 MLG Body Doors C. Prepare for the Removal of the MLG Support Link (Fig. 401) S 494-040 _______ WARNING: MAKE SURE YOU INSTALL THE DOWNLOCKS ON ALL THE LANDING GEAR (BEFORE YOU MOVE THE CONTROL LEVEL). WITHOUT THE DOWNLOCKS, THE LANDING GEAR CAN RETRACT AND CAUSE INJURY TO PERSONS AND DAMAGE TO EQUIPMENT.

2.

(1)

Install the downlocks for the main landing gear (Ref 32-00-20/201). S 494-041

_______ WARNING:

OBEY THE INSTALLATION PROCEDURE FOR THE DOOR LOCKS. THE DOORS OPEN AND CLOSE QUICKLY. THE MOVEMENT OF THE DOORS CAN CAUSE INJURY AND DAMAGE TO EQUIPMENT.

(2)

Open the MLG doors and install the door locks (Ref 32-00-15/201). S 864-042 Remove the pressure from the center hydraulic system (Ref 29-11-00/201).

(3)

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MAIN WHEEL WELL SEE A HYDRAULIC LINES (REF) MAIN LANDING GEAR BEAM SIDE STRUT SWIVEL FWD INBD SIDE BRACE LOCK SPRING

MAIN LANDING GEAR BEAM SUPPORT LINK SEE B

RIGHT MAIN WHEEL WELL (LEFT OPPOSITE)
SUPPORT FITTING

A

C

C

B

B
MAIN LANDING GEAR SUPPORT LINK

A

A

FWD INBD

STRUT SWIVEL FITTING

MAIN LANDING GEAR BEAM SUPPORT LINK B Main Landing Gear Support Link Installation Figure 401 (Sheet 1)
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(4)

S 584-043 Lift the airplane on jacks of the leading edge of the wing adjacent to the fuselage until the wheels are above the ground (Ref 07-11-01/201).

D.

S 224-044 Measure the clearances "A", "B", "C", "D", "E", "F", "G", "H", and "I" before you remove the MLG support link (Fig. 401). MLG Support Link Removal (5) S 024-045 To remove the MLG support link, remove the three connection points as shown in Fig. 401. (a) Remove the washer (1), the nut (4), the washer (5), the plate-pin retainer (6), the bolt (8), the washer (10), and the nut (11). (b) Remove the bottle pin (3). (c) Remove the inner pin (12), the washer (13), the outer pin (14), the spacer (15), the spacer (17), the washer (19), the nut (20), the washer (21), the nut (22) and the lockwire (23) from the upper aft connection point. (d) Remove the inner pin (31), the outer pin (24), the washer (30), the washer (25), the lockwire (26), the nut (27), the washer (28), and the nut (29) from the upper forward connection point. (e) Remove the washers (7), the washers (9), the washer (16), and the washer (18) from clearances "A" thru "I". S 224-046 Measure and make a record of the washer thickness at each clearance. (a) If you install the same washers, make a permanent mark of the letter location on the washer from where you removed the washer.

(1)

(2)

3.

TASK 57-54-01-404-047 Main Landing Gear Support Bottom Link Installation __________________________________________________ A. References (1) 07-11-01/201, Jacking Airplane (2) 29-11-00/201, Pressurize/Depressurize Main Hydraulic System (3) 32-00-15/201, Landing Gear Door Locks B. Access (1) Location Zones 731/741 Main Landing Gear (MLG) 732/742 MLG Body Doors

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CLEARANCE C CLEARANCE A CLEARANCE B MAIN LANDING GEAR SUPPORT LINK CLEARANCE D

CLEARANCE E CLEARANCE F

2. WASHER 1. WASHER

3. BOTTLE PIN

4. NUT 11. NUT 9. WASHER 10. WASHER BUSHING (EXAMPLE) 8. BOLT FWD STRUT SWIVEL FITTING 7. WASHER 6. PLATE-PIN RETAINER BUSHING (EXAMPLE) 5. WASHER

A-A

Main Landing Gear Support Link Installation Figure 401 (Sheet 2)
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NO CLEARANCE 15. SPACER 14. OUTER PIN 13. WASHER 12. INNER PIN NO CLEARANCE BUSHING (REF) 16. WASHER

767 MAINTENANCE MANUAL
17. SPACER 18. WASHER 19. WASHER 20. NUT 21. WASHER 22. NUT

SEE

C

D

D
23. LOCKWIRE

SPHERICAL BEARING (REF)

B-B

20. NUT

19. WASHER

23. LOCKWIRE BUSHING (REF) 17. SPACER

CLEARANCE H SPHERICAL BEARING

CLEARANCE G

0`-30` 22. NUT

19. WASHER 20. NUT 16. WASHER 21. WASHER 22. NUT 23. LOCKWIRE 21. WASHER

D-D

18. WASHER NO CLEARANCE

C

Main Landing Gear Support Link Installation Figure 401 (Sheet 3)
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BUSHING (REF)

BUSHING (REF) 25. WASHER

24. OUTER PIN

26. LOCKWIRE 27. NUT 28. WASHER 29. NUT

31. INNER PIN

30. WASHER CLEARANCE I

C-C

Main Landing Gear Support Link Installation Figure 401 (Sheet 4)
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C. Procedure (Fig. 401)

767 MAINTENANCE MANUAL

(1)

S 434-048 Prepare the washer(s) (7) of equal thickness at each clearance "D" and "E". (a) Install the washers (7) to get the same value as the clearance at "D" and "E". ____ NOTE: The maximum sum of the clearances between "D" and "E" must measure 0.020 inch after washer installation.

(b)

Before you install the washers, make a permanent record of the part number on each washer and the letter location it is installed.

(2)

S 434-049 Prepare the washer(s) (7) of equal thickness at each clearance "C" and "F". (a) Install the washers (7) to get the same value as the clearance at "C" and "F". ____ NOTE: The maximum clearances at each location "C" and "F" must measure between 0.015-0.025 inch after washer installation.

(b)

Before you install the washers, make a permanent record of the part number on each washer and the letter location it is installed.

(3)

S 224-050 With the clearances at "C" and "F" equal, measure the clearance at "B". S 434-051 Install the washer(s) (9) to get the same value as the clearance at "B". ____ NOTE: After you install the washer(s) (9), the permitted clearance tolerance is from 0.005 to 0.010 inch. Before you install the washer(s), make a permanent record of the part number on the washer(s) and the letter location it is installed.

(4)

(a)

(5)

S 434-052 With the washer(s) (9) installed at "B", put the bottle pin (3) end into the forward end of the support link. S 434-053 At the forward end of the bottle pin (3), install the washer (10) and the washer (2).

(6)

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(7)

S 434-054 Install the washer (1), the washer (5), the plate-pin retainer (6), the bolt (8), the nut (4) and the nut (11). S 434-055 Turn the nut (11) until the washer (2) is tightly against the shoulder of the bottle pin (3). S 824-056 Push the strut swivel fitting forward until the clearance at B closes to 0.0 inch. (a) While you hold the position of the swivel fitting, push the washer (10) tightly against the washer (2).

(8)

(9)

S 224-057 (10) Measure the clearance at "A". S 434-058 (11) Install the washer(s) (9) to get the same value as the clearance at "A". ____ NOTE: After you install the washer(s) (9), the permitted clearance tolerance is from 0.010 to 0.020 inch. Before you install the washer(s) (9), make a permanent record of the part number on each washer and the letter location it is installed.

(a)

S 224-082 (12) Before you tighten the nuts for the bottle pin, measure the clearances again at "A", "B", "C" and "F",and "D" and "E". (a) Make sure that the tolerances have not changed before you continue. S 434-059 (13) Tighten the nut (4). S 434-060 (14) Torque the nut (11) to 3500-4000 pound-inches. S 434-061 (15) Install the spacer (17), the inner pin (12), the outer pin (14), the washer (13) and the spacer (15) at the top aft link. (a) Apply grease between the inner pin (12) and the outer pin (14) before assembly. (b) Make sure that no clearance is between the spacer (15) and the bushing (Fig. 401, view B-B).

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S 434-065 (16) Install the washer(s) (16) between the spherical bearing and the bushings. (a) Make sure that there is no clearance between the washer(s) (16) and the bushings on the forward and aft sides of the spherical bearing (Fig. 401, view B-B and detail C). (b) Make sure that the clearance at "H" is greater than 0.010 inch (Fig. 401, detail C). S 224-084 (17) Make sure that the clearance at "G" is greater than 0.010 inch (Fig. 401, view C). S 434-066 (18) Install the washer (18) and the washer (19). S 224-068 (19) Before you tighten the nut (20), do the following: (a) Make sure that no clearance is between the spacer (15) and the bushing. (b) Make sure that no clearance is between the spacer (17) and the washer (18). (c) Make sure that no clearance is between the spherical bearing and the bushings. (d) Measure the clearances again at "G" and "H". S 434-067 (20) Install the nut (20). (a) Make sure the washer (19) is in the orientation shown in Fig. 401, detail D-D. S 434-068 (21) Torque the nut (20) to 480-790 pound-inches. S 434-069 (22) Install the washer (21) and nut (22). S 434-070 (23) Torque the nut (22) to 1500 to 2500 pound-inches. S 434-071 (24) Install the lockwire (23), (Fig. 401, view D-D). S 644-072 (25) Apply grease to the inner pin (31) and the outer pin (24) before their assembly at the top link at the forward end. S 434-073 (26) Install the washer (30), the inner pin (31) and the outer pin (24).

EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùùû ú ALL ú ú ú

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S 434-074 (27) Install the washer (25) and the nut (27). S 434-075 (28) Torque the nut (27) to 480-790 pound-inches. S 224-067 (29) Measure the clearance "I" between the bushing and the washer (25). ____ NOTE: The minimum permitted clearance at "I" must be 0.005 inch after the washer installation.

S 434-077 (30) Install the washer (28) and the nut (29). S 434-078 (31) Torque the nut (29) to 480-700 pound-inches. S 434-079 (32) Install the lockwire (26). S 584-080 (33) Lower the airplane off the jacks (Ref 07-11-01/201). S 844-085 (34) Put the airplane back into the original condition: _______ WARNING: OBEY THE PROCEDURE FOR THE DOOR LOCKS. THE DOORS OPEN AND CLOSE QUICKLY. THE MOVEMENT OF THE DOORS CAN CAUSE INJURY AND DAMAGE TO EQUIPMENT.

(a) (b)

Remove the door locks from the main landing gear doors (Ref 32-00-15/201). Pressurize the center hydraulic system (Ref 29-11-00/201).

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(c)

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Remove the downlocks for the main landing gear (Ref 32-00-20/201).

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_____________________________________________________ MAIN LANDING GEAR SUPPORT BEAM - REMOVAL/INSTALLATION 1. ________ General A. This procedure has two tasks. The first task is to remove the Main Landing Gear Support Beam. The second task is the installation of the Main Landing Gear Support Beam. TASK 57-54-04-914-001 _________________________________________ Main Landing Gear Support Beam - Removal A. References (1) 06-44-00/201 Wings (Major Zones 500 and 600) Access Doors and Panels (2) 07-11-01/201 Jacking Airplane (3) 27-51-00/201 Trailing Edge Flap System (4) 29-11-00/201 Pressurize/Depressurize Main Hydraulic System (5) 29-15-00/201 Hydraulic Systems A, B, and Standby (6) 32-00-15/201 Landing Gear Down Locks (7) 32-00-20/201 Landing Gear Downlocks (8) 32-11-01/601 Main Gear (9) 32-11-03/401 Main Gear Side Brace (10) 32-11-10/401 Main Gear Drag Brace (11) 32-12-06/401 Shock Strut Door and Linkage (12) 32-12-08/401 Drag Brace Door and Linkage (13) 32-12-11/401 Trunnion Door and Linkage (14) 32-32-02/401 Main Gear Lock Actuators (15) 32-32-05/401 Main Gear Jury Strut Spring (16) 32-32-18/401 Main Gear Truck Positioner (17) 57-54-01/401 MLG Support Link (18) 57-54-05/401 MLG Support Beam Load Plates B. Equipment (1) Winch (2) Support structure (3) Fuse pin puller C. Consumable Materials (1) Cotton swabs D. Access (1) Location Zones 119/120 Main Equipment Center 143/144 Main Landing Gear Wheel Well 211/212 Control Cabin 731/741 Main Landing Gear (MLG) 732/742 Main Landing Gear Doors 733/743 Main Landing Gear Drag Brace Doors 734/744 Main Landing Gear Oleo Doors 735/745 Main Landing Gear Trunnion Doors

2.

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(2)

767 MAINTENANCE MANUAL

E.

Access Panels 551FT/651FT Landing Gear 551GT/651GT Landing Gear Support Beam 551JT/651JT Landing Gear Support Beam 551LT/651LT Landing Gear Support Beam 551MT/651MT Landing Gear Trunnion 551NT/651NT Landing Gear Support Beam 551QB/651QB Lower Wing Structure 551PT/651PT Lower Wing Structure 551SB/651SB Lower Wing Structure 551TB/651TB Lower Wing Structure 551VB/651VB Landing Gear Support Beam 551WB/651WB Landing Gear Support Beam 552AB/652AB Landing Gear Support Beam 552BB/652BB Landing Gear Support Beam 552CB/652CB Landing Gear Support Beam Prepare for the Main Landing Gear Support Beam Removal S 014-003 Remove the left access panels (AMM 06-44-00/201). (a) 551FT (b) 551GT (c) 551JT (d) 551LT (e) 551MT (f) 551NT (g) 551QB (h) 551PT (i) 551SB (j) 551TB (k) 551VB (l) 551WB (m) 552AB (n) 552BB (o) 552CB S 014-030 Remove the right access panels (AMM 06-44-00/201). (a) 651FT (b) 651GT (c) 651JT (d) 651LT (e) 651MT (f) 651NT (g) 651QB (h) 651PT (i) 651SB

(1)

(2)

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(j) (k) (l) (m) (n) (o) 651TB 651VB 651WB 652AB 652BB 652CB

767 MAINTENANCE MANUAL

(3)

S 024-009 Disconnect the attaching linkages between panel support and the main landing gear support beam. S 044-004 Make sure Circuit Breakers are open. S 494-029 Make sure the downlocks are installed on the nose and main landing gear (AMM 32-00-15/201). S 584-005 Jack the airplane (AMM 07-11-01/201). S 044-006 Depressurize hydraulics (AMM 29-11-00/201). S 024-007 Disconnect (a) Put a (b) Put a (c) Put a

(4)

(5)

(6)

(7)

(8)

hydraulic lines from Main Landing Gear Beam. cap on the hydraulic ports. plug on the lines. tag on the lines to make installation easier.

(9)

S 024-008 Remove Offset Gearbox Support Bracket for the Trailing Edge Flap Drive.

S 024-038 (10) 767-200/300; Remove the MLG stabilizer strut (1), (Fig. 402). (a) Put a support under the MLG stabilizer strut (1).

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(b)

767 MAINTENANCE MANUAL

F.

Disconnect the trunnion door from the MLG stabilizer strut (1) (AMM 32-12-11/401). (c) At the aft end of the MLG stabilizer strut (1), remove the cotter pin (5), the nut (6), the washer (4), the washer (3), and the bolt (2). (d) At the forward end of the MLG stabilizer strut (1), remove the cotter pin (10), the nut (11), the washer (9), the washer (8), and the bolt (7). Main Landing Gear Support Beam Removal (Fig. 401) S 034-010 _______ CAUTION: MAKE SURE TO SUPPORT THE MAIN LANDING GEAR SUPPORT BEAM. DAMAGE OR BODILY INJURY WILL OCCUR IF NOT SUPPORTED.

(1)

Hold the MLG Support Beam with support structure. ____ NOTE: The support beam is very heavy. To support it safely and effectively, it is suggested that you use either hydraulic jacks with a cradle, or a crane with a sling. A pad to protect the equipment from the support beam is also suggested.

(2)

S 024-012 To disconnect the inboard end of the support beam from its support, see (AMM 57-54-01/401). S 024-011 Do the procedure to remove the MLG Support Beam Load Distribution Plates (AMM 57-54-05/401). S 024-013 Do the procedure to remove the Main Landing Gear Trunnion. S 484-014 Attach hoists to the Main Landing Gear Beam. S 564-015 Carefully lower the Main Landing Gear Beam. S 584-016 Place beam on a stable platform.

(3)

(4)

(5)

(6)

(7)

3.

TASK 57-54-04-574-002 ______________________________________________ Main Landing Gear Support Beam - Installation A. References (1) 06-44-00/201 Wings (Major Zones 500 and 600) Access Doors and Panels (2) 07-11-01/201 Jacking Airplane (3) 27-51-00/201 Trailing Edge Flap System

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LEFT MAIN WHEEL WELL SEE A

MAIN GEAR DOOR

MAIN LANDING GEAR BEAM SUPPORT LINK HYDRAULIC LINES

MAIN LANDING GEAR SUPPORT BEAM SEE B

FWD

MAIN LANDING GEAR SIDE BRACE SIDE STRUT SWIVEL SIDE BRACE LOCK SPRING

INBD

LEFT MAIN WHEEL WELL (RIGHT MAIN WHEEL WELL IS OPPOSITE) A Main Landing Gear Beam Installation Figure 401 (Sheet 1)
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SUPPORT LINK

MAIN LANDING GEAR SUPPORT BEAM

INBD

FWD

MAIN LANDING GEAR SUPPORT BEAM B

Main Landing Gear Beam Installation Figure 401 (Sheet 2)
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SEE

A LEFT (RIGHT) ACCESS PANEL, 551MT (651MT)

LEFT WING (RIGHT WING IS OPPOSITE)

MLG BEAM STABLIZER STRUT

SEE

B

FWD SEE C

(ACCESS PANEL REMOVED) A

Stabilizer Strut Installation Figure 402 (Sheet 1)
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MLG BEAM END FITTING STABILIZER STRUT

2. BOLT

5. COTTER PIN

3. WASHER

FORWARD TRUNNION BEARING SIDE BRACE

1. MLG BEAM STABILIZER STRUT 6. NUT 4. WASHER FWD HINGE ATTACH TRUNNION DOOR

AFT HINGE ATTACH TRUNNION DOOR 7. BOLT STABILIZER STRUT PLATE

8. WASHER INBD FWD 10. COTTER PIN

MLG BEAM STABLIZER STRUT B

9. WASHER FWD

11. NUT

INBD

MLG BEAM STABLIZER STRUT C

Stabilizer Strut Installation Figure 402 (Sheet 2)
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B.

C. D.

(4) 29-11-00/201 Pressurize/Depressurize Main Hydraulic System (5) 29-15-00/201 Hydraulic Systems A, B, and Standby (6) 32-00-15/201 Landing Gear Down Locks (7) 32-00-20/201 Landing Gear Downlocks (8) 32-11-01/601 Main Gear (9) 32-11-03/401 Main Gear Side Brace (10) 32-11-10/401 Main Gear Drag Brace (11) 32-12-06/401 Shock Strut Door and Linkage (12) 32-12-08/401 Drag Brace Door and Linkage (13) 32-12-11/401 Trunnion Door and Linkage (14) 32-32-02/401 Main Gear Lock Actuators (15) 32-32-05/401 Main Gear Jury Strut Spring (16) 32-32-18/401 Main Gear Truck Positioner (17) 57-54-01/401 MLG Hanger Link (18) 57-54-05/401 MLG Support Beam Load Plates Equipment (1) Winch (2) Support structure (3) Fuse pin puller Consumable Materials (1) Cotton swabs Access (1) Location Zones 119/120 Main Equipment Center 143/144 Main Landing Gear Wheel Well 211/212 Control Cabin 731/741 Main Landing Gear (MLG) 732/742 Main Landing Gear Doors 733/743 Main Landing Gear Drag Brace Doors 734/744 Main Landing Gear Oleo Doors 735/745 Main Landing Gear Trunnion Doors (2) Access Panels 551FT/651FT Landing Gear 551GT/651GT Landing Gear Support Beam 551JT/651JT Landing Gear Support Beam 551LT/651LT Landing Gear Support Beam 551MT/651MT Landing Gear Trunnion 551NT/651NT Landing Gear Support Beam 551QB/651QB Lower Wing Structure 551PT/651PT Lower Wing Structure 551SB/651SB Lower Wing Structure 551TB/651TB Lower Wing Structure 551VB/651VB Landing Gear Support Beam 551WB/651WB Landing Gear Support Beam 552AB/652AB Landing Gear Support Beam 552BB/652BB Landing Gear Support Beam 552CB/652CB Landing Gear Support Beam

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E.

767 MAINTENANCE MANUAL

Prepare for the Main Landing Gear Support Beam Installation (Fig. 401) S 414-032 Hold the MLG Support Beam in place with support structure. ____ NOTE: The support beam is very heavy. To support it safely and effectively, it is suggested that you use either hydraulic jacks with a cradle, or a crane with a sling. A pad to protect the support structure from the support beam is also suggested.

(1)

(2)

S 484-017 Attach hoist securely to beam and position into place. S 424-019 Install the Main Landing Gear Beam Load Distribution Plates (AMM 57-54-05/401). S 414-037 To connect the inboard end of the support beam to its support, see (AMM 57-54-01/401). S 424-020 Install bushing in MLG Beam for MLG Trunnion. S 424-021 Install MLG Trunnion. S 424-022 Attach Offset Gearbox Support Bracket for the T.E.

(3)

(4)

(5)

(6)

(7)

Flap Drive.

(8)

S 404-039 767-200/300; Install the MLG stabilizer strut (1), (Fig. 402). (a) Install the forward end of the MLG stabilizer strut (1) to the forward trunnion bearing side brace: 1) Apply a thin layer of grease, BMS 3-33 to the outer diameter and the threads of the bolt (7).

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2) Install the washer (8), nut (11) and the cotter bolt (7) on the inboard (1). Tighten the nut (11) to newton-meters). ____ NOTE:

767 MAINTENANCE MANUAL the bolt (7), the washer (9), the pin (10) with the head of the side of the MLG stabilizer strut 350 inch-pounds (39.54

3)

If you cannot align the nut slot with the crossbolt hole, another washer can be added under the nut.

4)

(b)

Tighten the nut (11) to align the nut slot with the crossbolt hole, but do not tighten more than 450 inch-pounds (50.8 newton-meters). Install the aft end of the MLG stabilizer strut (1) to the MLG beam stabilizer strut end fitting: 1) Apply a thin layer of grease, BMS 3-33, to the outer diameter and to the threads of the bolt (2). 2) Install the washer (3), the bolt (2), the washer (4), the nut (6), and the cotter pin (5) with the head of the bolt (2) on the inboard side of the MLG stabilizer strut (1). 3) Tighten the nut (6) to 350 inch-pounds (39.54 newton-meters). ____ NOTE: If you cannot align the nut slot with the crossbolt hole, another washer can be added underneath the nut (6).

4)

(c)

Tighten the nut (6) to align the nut slot with the crossbolt hole, but do not tighten more than 450 inch-pounds (50.8 newton-meters). Connect the trunnion door to the MLG stabilizer strut (1) (AMM 32-12-11/401).

F.

S 424-023 (9) Install and attach hydraulic lines to the MLG Beam. Put the Airplane Back to its Usual Condition S 414-024 Install access panels. S 844-025 Pressurize the left, center, and right hydraulic system.

(1)

(2)

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(3)

S 844-026 Lower the airplane (AMM 07-11-01/201). S 844-027 Close circuit breakers. S 844-028 Return airplane to normal operating conditions.

(4)

(5)

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___________________________________________________ MLG SUPPORT BEAM LOAD PLATES - REMOVAL/INSTALLATION 1. _______ General A. This procedure contains two tasks. The first task removes the Main Landing Gear (MLG) Beam Load Distribution Plates from the MLG Beam Outboard Support and the MLG Support Beam. The second task installs the MLG Beam Load Distribution Plates between the MLG Beam Outboard Support and the MLG Support Beam. B. This procedure is to be used to remove/replace the MLG Beam Load Distribution Plates in the right or left wing. TASK 57-54-05-004-001 _________________________________________________ MLG Support Beam Load Distribution Plates Removal A. References (1) AMM 06-44-00/201, Wing (Major Zones 500 and 600) Access Doors and Panels (2) AMM 07-11-01/201, Jacking Airplane (3) AMM 12-12-01/301, Hydraulic Systems (4) AMM 24-22-00/201, Electric Power - Control (5) AMM 29-11-00/201, Pressurizing/Depressurizing Main Hydraulic System (6) AMM 32-00-15/201, Landing Gear Doorlocks (7) AMM 32-00-20/201, Landing Gear Downlocks (8) AMM 32-32-01/401, Main Landing Gear Retract Actuator B. Access (1) Location Zones 551/661 Rear Spar to MLG Support Beam 731/741 Main Landing Gear (MLG) 732/742 MLG Body Doors (2) Access Panels 551TB Wing Access Panel (Bottom, Left) 551UB Wing Access Panel (Bottom, Left) 551PT Wing Access Panel (Top, Left) 551XBX Wing Access Panel (Bottom, Left) 651TB Wing Access Panel (Bottom, Right) 651UB Wing Access Panel (Bottom, Right) 651PT Wing Access Panel (Top, Right) 651XBX Wing Access Panel (Bottom, Right) Prepare for the removal of the MLG Support Beam Load Distribution Plates (Fig. 401)

2.

C.

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S 414-032 _______ WARNING: BEFORE YOU MOVE THE CONTROL LEVER, INSTALL THE DOWNLOCKS ON ALL THE LANDING GEAR. WITHOUT THE DOWNLOCKS, THE LANDING GEAR CAN RETRACT. THIS CAN CAUSE INJURIES TO PERSONNEL, AND DAMAGE TO EQUIPMENT.

(1)

Install the downlocks for the main landing gear (AMM 32-00-20/201). S 424-033

_______ WARNING:

OBEY THE INSTALLATION PROCEDURE FOR THE DOOR LOCKS. THE DOORS OPEN AND CLOSE QUICKLY. THE MOVEMENT OF THE DOORS CAN CAUSE INJURY TO PERSONNEL AND DAMAGE TO EQUIPMENT.

(2)

Open the MLG doors and install the door locks (AMM 32-00-15/201). S 614-004 Remove the pressure from the center hydraulic system (AMM 29-11-00/201). S 014-005 To gain access to the work area, remove the following access panels (AMM 06-44-00/201): (a) 551TB (b) 551UB (c) 551PT (d) 551XBX (e) 651TB (f) 651UB (g) 651PT (h) 651XBX S 614-006 Without lifting the landing gear off the ground, lift the airplane on jacks, using the jack points at the leading edge of the wings adjacent to the fuselage, until the weight of the airplane is off the landing gear (AMM 07-11-01/201). S 424-007 Install auxilliary jacks D, E, and F (AMM 07-11-01/201). ____ NOTE: Auxilliary jacks are for stabilization of the airplane. preload is required on the jacks. No

(3)

(4)

(5)

(6)

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(7)

S 614-008 Support the Main Landing Gear Beam at its outboard end as follows: (a) If the Main Landing Gear is not installed, put the support jack under the beam near the outboard end and adjust it to touch the beam. (b) Deflate the shock struts of the main landing gear (AMM 12-15-01/301). ____ NOTE: Record the pressure of the shock strut for use in restoring the shock to normal.

(8)

S 424-055 Install shock torsion retention straps (AMM 32-11-10/401). S 034-056

_______ CAUTION:

THE LANDING GEAR CAN MOVE ABOUT 7.9 INCHES (20 CM) INBOARD WHEN THE JURY STRUT SPRINGS ARE REMOVED.

(9)

Remove the jury strut springs (AMM 32-32-05/401). (a) Push up on the jury strut to release it from the overcenter position.

S 024-058 (10) Remove the Main Landing Gear Retract Actuator (AMM 32-32-01/401). S 024-104 (11) AIRPLANES PRE-SB 57-0073; At Holes No. 1 and No. 2, remove the bolt (7), nut (9), washer (8), plug (3), and fuse pin nut (6). S 024-103 (12) AIRPLANES POST SB 57-0073; At Holes No. 1 and No. 2, remove the cotter pin (19), bolt (7), castellated nut (9), washer (8), plug (3), and fuse pin nut (6).

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S 924-030 _______ CAUTION: DO NOT APPLY A PRESSURE OF MORE THAN 5000 LBS (2268 Kg) ON THE MAIN LANDING GEAR SUPPORT BEAM. TOO MUCH PRESSURE CAN CAUSE DAMAGE TO EQUIPMENT.

(13) Slowly lift the MLG steering beam. (a) Stop lifting the MLG Support Beam when its weight is removed from the Load Distribution Plates Fuse Pins (2), and they can be rotated (Fig. 401). ____ NOTE: If the fuse pins cannot be rotated using a 10 inch wrench, a hit with a plastic hammer may loosen them. Also, penetrating oil may loosen them.

S 014-089 (14) If you are unable to rotate the fuse pins, do the following: (a) Disconnect and remove MLG Beam Outboard Support rod (18). (b) Remove the MLG Side Brace Lock Spring and unlock the brace (AMM 32-32-03/401). (c) Move the landing gear until the fuse pins (2) rotate. ____ NOTE: This should happen when the landing gear Center of Gravity (CG) is under the MLG Support Beam Trunnion bearing. The drag brace actuator rod will be about 5.75 inches (146.05 mm) long at that time.

S 424-034 _______ CAUTION: THE MLG SUPPORT BEAM COULD MOVE OR FALL DOWN AND INJURE PERSONNEL OR EQUIPMENT IF IT IS NOT ATTACHED WITH STRAPS OR SUPPORTED.

(15) If the Main Landing Gear is removed, attach straps or support the MLG Support Beam to keep the beam in place when the fuse pins are removed. S 424-097 (16) If applicable, remove the MLG Beam Outboard Support Rod (18). S 024-010 (17) Remove the two fuse pins (2), washers (1) and (4), shims (5). ____ NOTE: Record the thickness and position of all shims and washers while removing the pins. Retain all hardware (washers, nuts, plug, bolts, and fuse pins) for use when restoring to original condition.

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SUPPORT FITTING FOR THE RETRACT ACTUATOR SEE A

RETRACT ACTUATOR UP LINE RETURN LINE DOWN LINE SHOCK STRUT

LINE TO TRANSFER CYLINDER LOAD DISTRIBUTION PLATES REAR WING SPAR FITTING SEE B

MLG SUPPORT BEAM FWD INBD

SUPPORT FITTING FOR THE RETRACT ACTUATOR (LEFT SUPPORT FITTING IS SHOWN, RIGHT SUPPORT FITTING IS OPPOSITE) A MLG Support Beam Load Distribution Plates Installation Figure 401 (Sheet 1)
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B
FWD HOLE NO. 1 SEE C HOLE NO. 2 SEE C

A

A

HOLE NO. 3

B

LOAD DISTRIBUTION PLATES B
TOTAL GAP NOT TO EXCEED 0.02 INCH (0.508 mm) LOAD DISTRIBUTION PLATES GAP MAXIMUM 0.005 INCH (0.127 mm) 13. SUPPORT LINK WASHER 17. LOCKWIRE 14. RETAINING NUT 20. SHIM 10. PIN GAP 0.003-0.010 INCH (0.0762-0.254 mm) 18. MLG BEAM OUTBOARD SUPPORT ROD

GAP MAXIMUM 0.005 INCH (0.127 mm)

12. BOLT 15. NUT 11. WASHER 16. PLUG

FWD

A-A

MLG Support Beam Load Distribution Plates Installation Figure 401 (Sheet 2)
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REAR SPAR FITTING LOAD PLATE

C

C

B-B

0.005-0.020 INCH (0.127-0.508 mm) GAP

LOAD PLATE

0.005-0.020 INCH (0.127-0.508 mm) GAP

REAR SPAR FITTING

LOAD PLATE

C-C

MLG Support Beam Load Distribution Plates Installation Figure 401 (Sheet 3)
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1. WASHER 2. FUSE PIN

3. PLUG

9. NUT 1 8. WASHER 6. NUT 4. WASHER

7. BOLT 5. SHIMS

19. COTTER PIN 2

HOLE (EXAMPLE) C

CASTLE NUT

1

AIRPLANES PRE-SB 57-0073; SELF-LOCKING NUT AIRPLANES POST-SB 57-0073; CASTLELLATED NUT AND COTTER PIN

2

MLG Support Beam Load Distribution Plates Installation Figure 401 (Sheet 4)
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S 024-041 (18) Remove MLG Support Beam outboard support pin (12), nut (15), washer (11), and plug (16) common to the support beam and the load distribution plates. S 024-040 (19) Remove lockwire (17), and retaining nut (14) followed by support link washer (13). S 024-042 _______ WARNING: LOAD DISTRIBUTION PLATES CAN CAUSE INJURY TO PERSONS OR EQUIPMENT IF NOT PROPERLY SUPPORTED.

(20) Remove fuse pin (10). ____ NOTE: You can use a rubber mallet to remove pin if necessary.

S 024-011 (21) Remove both load distribution plates (Fwd & Aft) from the wing. TASK 57-54-05-404-012 ______________________________________________________ MLG Support Beam Load Distribution Plates Installation A. References (1) AMM 06-44-00/201, Wing (Major Zones 500 and 600) Access Doors and Panels (2) AMM 07-11-01/201, Jacking Airplane (3) AMM 12-12-01/301, Hydraulic Systems (4) AMM 24-22-00/201, Electric Power - Control (5) AMM 29-11-00/201, Pressurizing/Depressurizing Main Hydraulic System (6) AMM 32-00-15/201, Landing Gear Doorlocks (7) AMM 32-00-20/201, Landing Gear Downlocks (8) AMM 32-32-01/401, Main Gear Retract Actuator B. Equipment (1) 0.005 inch undersize temporary fuse pin. (2) Honing tool for final fitting of fuse and attach pins C. Consumable Materials (1) Grease, BMS 3-33 D. Access (1) Location Zones 551/661 Rear Spar to MLG Support Beam 731/741 Main Landing Gear (MLG) 732/742 MLG Body Doors

3.

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(2) Access Panels 551TB Wing 551UB Wing 551PT Wing 551XBX Wing 651TB Wing 651UB Wing 651PT Wing 651XBX Wing Procedure

767 MAINTENANCE MANUAL

Access Access Access Access Access Access Access Access

Panel Panel Panel Panel Panel Panel Panel Panel

(Bottom, Left) (Bottom, Left) (Top, Left) (Bottom, Left) (Bottom, Right) (Bottom, Right) (Top, Right) (Bottom, Right)

E.

(1)

S 424-061 Install the MLG Support Beam Load Distribution Plates (Fig. 401) (a) Obtain the hardware that was retained when the plates were removed. (b) Using the retained hardware, attach the MLG Support Beam Load Distribution PLates to the MLG Support Beam outboard support structure. ____ NOTE: As a temporary attachment, use a 0.005 inch undersize temporary fuse pin to attach the plates to the MLG Beam Outboard Attachment Structure.

(c)

Using the jack installed under the main landing gear support beam, position the beam such that it is between the two load distribution plates.

(2)

S 424-043 Install pin (10), washer (11), bolt (12), support link washer (13), and retaining nut (14), (Fig. 401). (a) Apply grease, BMS3-33, between the bolt (12) and pin (10). S 424-048 Put washer (1) on fuse pin (2) and insert into load distribution plates. S 424-049 Put shims (5) and washer (4) on fuse pin (2). (a) Make sure that the gap between the shims and the forward face of the bushing is 0.005 to 0.020 inch (0.127 to 0.508 mm). S 424-016 Put shims (20) in the area between the bearings in the MLG Beam outboard end and the distribution plates such that there is a maximum 0.005 inch gap. ____ NOTE: Use shims equally on each side of the MLG Beam Outboard end. The total shim dimension on either side cannot be more than 0.020 inches (0.508 mm) thicker than the other.

(3)

(4)

(5)

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(6)

S 424-060 Install nut (6). S 024-018 Remove the temporary fuse pin connecting the load distribution plates to the MLG Beam Outboard end support structure. S 824-035

(7)

_______ CAUTION:

DO NOT REMOVE AND REPLACE MORE THAN ONE PIN AT A TIME OR REALIGNMENT OR RE-SHIMMING MAY BE REQUIRED.

(8)

Check the hole for alignment by looking through it. If it is aligned, attempt to insert an operational fuse pin. If it does not fit or fits too tightly, hone the opening up to 0.005 inches (0.127 mm) until the operational pin can be temporarily inserted. (a) Use a brass (or soft metal) drift punch to aid in the installation of the fuse pin as necessary. S 024-020 Remove the bottom temporary fuse pin connecting the load distribution plates to the MLG Beam Outboard end support structure. S 824-036

(9)

_______ CAUTION:

DO NOT REMOVE AND REPLACE MORE THAN ONE PIN AT A TIME OR REALIGNMENT OR RE-SHIMMING MAY BE REQUIRED.

(10) Repeat the alignment check and honing procedure listed in the previous steps as required until an operational fuse pin can be inserted in the bottom position. S 424-052 (11) Torque retaining nut (14) to 480-790 inch-pounds (54.2-89.3 Nm). S 424-053 (12) Attach lockwire (17) to retaining nut (14) and support link washer (13). S 424-054 (13) Insert plug (16). S 424-059 (14) Attach nut (15) and torque to 2200-4000 inch-pounds (248.6-451.9 Nm).

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S 414-068 (15) Complete the installation of the two smaller fuse pins: (a) Torque nuts (6) to 480 to 600 inch-pounds (54.2-67.8 Nm). S 424-100 (16) AIRPLANES PRE-SB 57-0073; Install bolt (7), washer (8), nut (9), plug (3), and tighten. S 424-101 (17) AIRPLANES POST-SB 57-0073; Install bolt (7), washer (8), castellated nut (9), cotter pin (19), plug (3), and tighten. S 424-064 (18) Install MLG Beam Outboard Support Rod (18). S 424-023 (19) Install Retract Actuator to original condition (AMM 32-32-01/401). S 414-024 (20) Fasten the following access panels (AMM 06-44-00/201): (a) 551TB (b) 551UB (c) 551PT (d) 551XBX (e) 651TB (f) 651UB (g) 651PT (h) 651XBX S 024-051 _______ WARNING: DO THE PROCEDURE TO REMOVE THE DOOR LOCKS (AMM 32-00-15/201). THE DOORS OPEN AND CLOSE QUICKLY AND CAN CAUSE INJURY TO PERSONS OR DAMAGE TO EQUIPMENT.

(21) Remove the door locks from the landing gear doors and close the doors (AMM 32-00-15/201). S 844-026 (22) Lower the airplane and remove the jacks (AMM 07-11-01/201). S 844-027 (23) Pressurize the hydraulic control back to normal operating conditions (AMM 12-12-01/301). S 614-065 (24) Remove the Landing Gear Downlocks (AMM 32-00-20/201).

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S 844-028 (25) Return airplane to normal operating condition.

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_____________________________________________________________ MAIN LANDING GEAR STRUT SWIVEL FITTING - REMOVAL/INSTALLATION 1. ________ General A. This procedure has two tasks. The first task is to remove the Main Landing Gear Strut Swivel Fitting. The second task is the installation of the Main Landing Gear Strut Swivel Fitting. TASK 57-54-06-914-001 ________________________________________________ Main Landing Gear Strut Swivel Fitting - Removal A. References (1) AMM 07-11-01/201, Jacking Airplane (2) AMM 12-12-01/301, Hydraulic Systems - Servicing (3) AMM 12-21-17/301, Aft Wheel Well Bulkhead Spherical Bearing Servicing (Lubrication) (4) AMM 12-25-01/301, Airplane Servicing - Cleaning and Washing (5) AMM 20-10-09/401, Tubing - Flareless - Removal/Installation (6) AMM 27-11-00/501, Operational Test - Aileron and Aileron Trim Control System (7) AMM 27-51-03/401, Inboard Flap - Removal/Installation (8) AMM 27-51-04/201, Inboard Flap Mechanism - Maintenance Practices (9) AMM 27-51-07/401, Inboard Flap Fairing Door - Removal/Installation (10) AMM 29-11-00/201, Main (Left, Right and Center) Hydraulic Systems Maintenance Practices (11) AMM 32-00-15/201, Locks - Landing Gear Doors (12) AMM 32-11-04/401, Main Gear Upper Side Brace - Removal/Installation (13) AMM 32-32-00/501, Main gear Extension and Retraction Adjustment/Test (14) AMM 32-41-00/501, Hydraulic Brake System - Adjustment/Test B. Equipment (1) Hydraulic System Pressurization Valve Locking Pin - A29002-6 (2) A57008 - Spanner Wrench C. Consumable Material (1) G00508 Corrosion Preventive Compound - MIL-C-11796, Class 3 D. Access (1) Location Zones 144 Right MLG Wheel Well (2) Access Panels 437BL/437BR Hydraulic System E. Prepare to remove the Main Landing Gear Strut Swivel Fitting (Fig. 401) S 944-003 Jack the airplane at jack locations A, B, and C and stabilize at locations D, E, and F (AMM 07-11-01/201). S 914-004 Fully extend the trailing edge flaps into the down position (AMM 27-51-04/201).

2.

(1)

(2)

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(3)

S 784-005 Depressurize the left, right and center main hydraulic systems and drain the left, right and center hydraulic reservoirs (AMM 29-11-00/201). S 434-006 Remove the lockwire from the handle on the drain valve at the bottom of the reservoir. S 684-007

(4)

_______ CAUTION:

HYDRAULIC FLUID LEAKAGE MUST BE IMMEDIATELY REMOVED. HYDRAULIC FLUID CAN DAMAGE PAINTED SURFACES AND OTHER AIRPLANE EQUIPMENT.

(5)

Open the drain valve and drain the fluid into a container. S 694-008 Close the drain valve and install the lockwire in the handle of the drain valve. S 024-067

(6)

_______ WARNING:

MAKE SURE EACH TUBE AND THE PORT FITTINGS HAVE TAGS TO IDENTIFY THE CORRECT INSTALLATION LOCATIONS. IF YOU DO NOT PUT TAGS ON THE TUBES AND PORT FITTINGS, CROSS-CONNECTION OF THE TUBES CAN OCCUR DURING INSTALLATION. IF THIS OCCURS, UNINTENDED OPERATION OR MALFUNCTION OF AIRPLANE SYSTEMS CAN RESULT AND CAUSE INJURY TO PERSONS AND DAMAGE TO EQUIPMENT.

(7)

Disconnect the hydraulic tubing (AMM 20-10-09/401). S 024-010 Put a cap on the open ends of the tubing and remove as an assembly. ____ NOTE: Tubes are marked with tape tags which indicate their function, flow direction and system (left, right or center).

(8)

(9)

S 114-011 Clean all surfaces that have hydraulic fluid contamination from tubing removal (AMM 12-25-01/301).

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S 024-012 (10) Remove the inboard trailing edge flap segment, if necessary, to get better access to the STA 1065 fitting (AMM 27-51-03/401). ____ NOTE: If the flap segment is not removed, support the flap while it is in the extended position.

S 024-013 (11) Remove the inboard hinge cutout flipper door and the forward flipper door 195HL and 195FL, respectively (AMM 27-51-07/401). S 024-014 (12) Disassemble and remove the two large lugs of the side (a) Remove the drive arms pin joint of each arm S 024-015 (13) Remove the fairing panels. S 024-016 (14) Remove the upper section of the frame to get access for removal of the bottle pin (3) and access to the trailing edge flap linkages. ____ NOTE: This step will prevent interference between the aft wheel well and fairing frame and the bottle pin when the pin is removed. Do not cut the frame web to gain access. For disassembly and repair instructions, use SRM 53-60-71.

shaft assembly which passes through the strut swivel (AMM 27-51-04/201). connected to the shaft up to the first or link.

(a) (b)

S 784-017 (15) Deflate the Main Landing Gear (MLG) shock strut. instructions on the gear. S 484-018 (16) Install an axle jack under the MLG truck bogey.

Use the

S 484-059 (17) Raise the MLG truck bogey to remove the load on the bolt that goes through the upper side brace and the side strut swivel assembly (AMM 32-11-04/401). ____ NOTE: The load has been removed from the bolt when the bolt rotates freely.

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S 024-019 (18) Remove the side brace lock spring (AMM 32-11-04/401). S 024-020 (19) Remove the MLG upper side strut brace from the upper side brace spindle (AMM 32-11-04/401). S 024-021 (20) Remove the fairing panel that is below the MLG Beam. S 024-022 (21) Remove the bolt between the upper side brace and the lower lock link (AMM 32-11-04/401). ____ NOTE: This step will move the brace out of the way so you can make space for a jack between the work stand and the MLG truck.

S 484-023 _______ CAUTION: DO NOT PUT THE JACK INTO DIRECT CONTACT WITH THE MLG BEAM WITHOUT A PROTECTIVE PAD. THE JACK WILL DAMAGE THE MLG BEAM IF A PROTECTIVE PAD IS NOT USED.

(22) Install a jack under the inboard end of the main landing gear beam. ____ NOTE: Use a jack that distributes the load over a wide area of the beam. A 727 tool is available (F72711-9) which can be used to help distribute the load. It may also help to use a block of wood between the jack and the beam. Make a groove in the block so it fits the bottom of the main landing gear beam.

S 484-024 (23) Jack the main landing gear beam slowly until the bottle pin (3) turns freely. ____ NOTE: The step will (incrementally) raise and unload the MLG beam and the bottle pin which connects the MLG beam, the side strut swivel, and the support link.

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S 024-025 (24) Remove the fail-safe-fitting that is mounted on the aft wall of the wheel well bulkhead. ____ NOTE: Removal of the fitting will permit the removal of the inboard flap drive shaft and the side strut swivel assembly.

S 024-026 (25) Disconnect the four flap drive reaction link supports connected to the side strut swivel at the first joint aft of the shaft. (a) Leave the first segment of each arm or link connected to the inboard flap mechanism shaft. (b) Tie the links out of the way to prevent interference. S 024-027 (26) Remove the trailing edge flap drive shaft to permit bottle pin (3) removal. S 024-028 (27) Remove the trailing edge support rod from the MLG beam. ____ NOTE: The bolt from the trailing edge support rod is located adjacent to the outboard bolt that connects the side strut swivel to the MLG beam.

S 484-029 (28) Install a jack beneath the side strut swivel assembly to support the fitting when it is removed. (a) Place a pad between the jack stand and side strut swivel fitting to prevent damage to part or assembly. (b) Install the Spanner Wrench A57008 on the bottle pin (3) to keep it from spinning freely. (c) After the bottle pin (3) is removed, the side strut swivel assembly will be free to fall.

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767 MAINTENANCE MANUAL

SEE

A

STATION 1065 BULKHEAD MAIN LANDING GEAR BEAM SUPPORT FITTING

TRAILING EDGE FLAP DRIVE SHAFT

6-7 DRIVE ARM

MAIN LANDING GEAR SUPPORT LINK

BOTTLE PIN NUT SEE B UPPER SIDE BRACE SIDE STRUT SWIVEL ASSEMBLY FLAP DRIVE REACTION LINK SUPPORTS

INBD SIDE BRACE LOCK SPRING FWD

FAIL SAFE FITTING

INBOARD FLAP SUPPORT SHAFT

AFT WHEEL WELL FAIRING FRAME

LEFT MAIN LANDING GEAR WHEEL WELL (RIGHT MAIN LANDING GEAR WHEEL WELL IS OPPOSITE) A

Main Landing Gear Strut Swivel Fitting installation Figure 401 (Sheet 1)
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STA 1065

767 MAINTENANCE MANUAL
STA 1043

BOTTLE PIN

A A

MAIN LANDING GEAR SUPPORT LINK

MAIN LANDING GEAR BEAM SIDE STRUT SWIVEL FITTING FWD INBD

LEFT SIDE IS SHOWN, RIGHT SIDE IS OPPOSITE (HYDRAULIC LINES NOT SHOWN FOR CLARITY) B
8. BOLT MAIN LANDING GEAR SUPPORT LINK

3. BOTTLE PIN

2. WASHER 1. WASHER 12. SAFETY NUT 11. NUT 1 10. WASHER

4. NUT 2 5. WASHER

6. PLATE-PIN RETAINER BUSHING (EXAMPLE) 7. LAMINATED WASHERS 1 2 STRUT SWIVEL FITTING

9. LAMINATED WASHERS BUSHING (EXAMPLE)

FWD

A-A

TORQUE NUT TO 3500-4000 INCH-POUNDS (395.4-451.9 Nm) TORQUE NUT TO 480-850 INCH-POUNDS (54.20-95.98 Nm)

Main Landing Gear Strut Swivel Fitting Installation Figure 401 (Sheet 2)
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S 024-030 _______ CAUTION: MAKE SURE TO MAKE A RECORD OF THE POSITION AND THICKNESS OF THE WASHERS INSTALLED AT THE BOTTLE PIN JOINT. EACH WASHER MUST BE ASSEMBLED INTO THE INITIAL LOCATION. INCORRECT WASHER THICKNESSES OR WASHERS INSTALLED IN THE WRONG POSITION CAN CAUSE MISALIGNMENT BETWEEN THE SIDE STRUT SWIVEL AND THE SWIVEL LINK.

(29) Remove the nut (4), the washer (5), the plate-pin retainer (6), the bolt (8), the washer (1), the bottle pin nut (11) and the washers (2) and (10). (a) Make a record of the number and thickness of the washers that are removed. S 024-031 (30) Remove the bottle pin (3). S 424-066 (31) Fill hole in cavity inside bushing with corrosion preventive compound to exclude any moisture. S 024-032 (32) Remove the strut swivel fitting. TASK 57-54-06-914-002 _____________________________________________________ Main Landing Gear Strut Swivel Fitting - Installation A. References (1) AMM 07-11-01/201, Jacking Airplane (2) AMM 12-12-01/301, Hydraulic Systems - Servicing (3) AMM 12-21-17/301, Aft Wheel Well Bulkhead Spherical Bearing Servicing (Lubrication) (4) AMM 12-25-01/301, Airplane Servicing - Cleaning and Washing (5) AMM 20-10-09/401, Tubing - Flareless - Removal/Installation (6) AMM 27-11-00/501, Operational Test - Aileron and Aileron Trim Control System (7) AMM 27-51-03/401, Inboard Flap - Removal/Installation (8) AMM 27-51-04/201, Inboard Flap Mechanism - Maintenance Practices (9) AMM 27-51-07/401, Inboard Flap Fairing Door - Removal/Installation (10) AMM 29-11-00/201, Main (Left, Right and Center) Hydraulic Systems Maintenance Practices (11) AMM 32-00-15/201, Locks - Landing Gear Doors (12) AMM 32-11-04/401, Main Gear Upper Side Brace - Removal/Installation (13) AMM 32-32-00/501, Main gear Extension and Retraction Adjustment/Test (14) AMM 32-41-00/501, Hydraulic Brake System - Adjustment/Test B. Equipment (1) Hydraulic System Pressurization Valve Locking Pin - A29002-6

3.

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C.

D.

E.

(2) A57008 - Spanner Wrench Consumable Material (1) G00508 Corrosion Preventive Compund - MIL-C-11796, Class 3 (2) A00247 Sealant - BMS 5-95, Class B-1/2 or B-2 Access (1) Location Zones 144 Right MLG Wheel Well (2) Access Panels 437BL/437BR Hydraulic System Prepare to install the Main Landing Gear Strut Swivel Fitting (Fig. 401) S 414-033 _______ WARNING: BE CAREFUL WHEN YOU LIFT THE SIDE STRUT SWIVEL FITTING INTO POSITION WITH A JACK. SIDE STRUT SWIVEL FITTING IS EXTREMELY HEAVY AND CAN CAUSE BODILY HARM OR DAMAGE TO EQUIPMENT IF DROPPED.

(1)

Lift the Strut Swivel Fitting to the MLG beam and hold in position. S 394-064 Fillet seal bushing flanges with sealant. S 424-073 Install the spanner wrench on the bottle pin (3), if necessary, to keep it from spinning freely. S 424-072

(2)

(3)

_______ CAUTION:

MAKE SURE TO INSTALL THE WASHERS AT THE BOTTLE PIN JOINT INTO THEIR INITIAL POSITION AND LOCATION. INCORRECT WASHER THICKNESSES OR WASHERS INSTALLED IN THE WRONG POSITION CAN CAUSE MISALIGNMENT BETWEEN THE SIDE STRUT SWIVEL AND THE SWIVEL LINK.

(4)

Slide bottle pin (3) into position to the forward end of the support link. (a) Insert laminated washers (7) and (9) into initial position as bottle pin (3) is inserted. S 424-075 At the forward end of the bottle pin (3), install the washer (10) and the washer (2).

(5)

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(6)

S 424-074 Turn the nut (11) until the washer (2) is tight against the shoulder of the bottle pin (3). S 424-036 Torque nut (11) to 3500-4000 inch-pounds (395.4-451.9 Newton-meters). S 024-070 Remove the spanner wrench A57008 from the bottle pin (3). S 424-061 Install the washer (1), the washer (5), the plate-pin retainer (6), the bolt (8), the nut (4) and the safety nut (12). ____ NOTE: You will have to push bolt through corrosion preventive compound. Do not remove corrosion preventive compound since it excludes any moisture.

(7)

(8)

(9)

S 424-038 (10) Torque nut (4) to 480-850 inch-pounds (54.20-95.98 Newton Meters). S 424-039 (11) Install the trailing edge support rod from the MLG Beam. ____ NOTE: The bolt from the trailing edge support rod is located adjacent to the outboard bolt that connects the side strut swivel to the MLG beam.

S 424-040 (12) Install the trailing edge flap drive shaft. S 424-041 (13) Connect the four flap drive linkages connected to the side strut swivel at the first joint aft of the shaft. S 424-042 (14) Install the fail-safe-fitting at the aft wall of the wheel well bulkhead. S 424-043 (15) Install the MLG upper side brace spindle (AMM 32-11-04/401). S 424-044 (16) Install the upper side brace and the bolt that is installed between the upper side brace and the lower lock link into position.

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S 424-045 (17) Install the side brace lock spring (AMM 32-11-04/401). S 484-046 (18) Lower the MLG truck bogey and apply the load that goes through the upper side brace and the side strut swivel assembly. S 784-047 (19) Inflate the the Main Landing Gear (MLG) shock strut per instructions on the gear. S 424-048 (20) Install the upper section of the frame (Refer to SRM 53-60-71 for assembly and repair instructions). S 424-049 (21) Install the inboard hinge cutout flipper door and the forward flipper door 195HL and 195FL, respectively (AMM 27-51-07/401). S 424-050 (22) Install the inboard trailing edge flap segment, if necessary (AMM 27-51-03/401). ____ NOTE: If flap segment is not removed, remove the support for the flap.

S 014-051 (23) Remove caps from hydraulic tubing. S 424-068 _______ WARNING: MAKE SURE EACH TUBE AND THE PORT FITTINGS HAVE TAGS TO IDENTIFY THE CORRECT INSTALLATION LOCATIONS. IF YOU DO NOT PUT TAGS ON THE THE TUBES AND PORT FITTINGS, CROSS-CONNECTION OF THE TUBES CAN OCCUR DURING INSTALLATION. IF THIS OCCURS, UNINTENDED OPERATION OR MALFUNCTION OF AIRPLANE SYSTEMS CAN RESULT AND CAUSE INJURY TO PERSONS AND DAMAGE TO EQUIPMENT.

(24) Install hydraulic tubing (AMM 20-10-09/401). ____ NOTE: Tubes are marked with tape tags which indicate their function, flow direction and system (left, right or center).

EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùùû ú ALL ú ú ú

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A

767 MAINTENANCE MANUAL

S 914-053 (25) Fill the left, right and center hydraulic reserviors. Pressurize the left, right and center main hydraulic systems as follows (AMM 29-11-00/201). S 414-054 (26) Close all access panels. S 944-055 (27) Lower the main landing gear beam slowly. S 944-056 (28) Fully retract the trailing edge flaps into the up position, zero detent (AMM 27-51-04/201). S 944-057 (29) Lower airplane at jack locations A, B, C, D, E and F (AMM 07-11-01/201). S 844-058 (30) Return airplane to normal operating conditions.

EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùùû ú ALL ú ú ú

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