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MAINTENANCE MANUAL

§HAEIER_5I
LISI.QE-EEEEQII!E-IEMBflBABI-RE!ISIONS

FOLLOWING IS A COMPLETE LISTING OF ALL ACTIVE TEMPORARY

REVISIONS (TR'S)¢ TR'S NOT LISTED SHOULD BE REMOVED» THE
ATA NUMBER; CONFIG CODE AND PAGE NUMBER IDENTIFIES THE
PAGE PRECEDING THE TR¢

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57-TR LIST
Page 1
050B Jun 15/96
I1 _ _ I“L_______ __
 -0
l.0(IKliEEED (@%§D

MAINTENANCE MANUAL

CHAPTER 57
WING

LIST OF EFFECTIVE PAGES

CHAPTER! CONFIG CHAPTERI CONFIG

SECTION PAGE DATE CODE SECTION PAGE DATE CODE

List of 1 Dec 15/94 57-30-00 2 Dec 1/71

Effective 2 Dec 15/94 57-30-00 3/4 Dec 1/71
Pages 57-31-00 Nov 15/84
57-31-00 Nov 15/81
Table of Nov 15/86 57-31-00 ,JuL 15/84
Contents Nov 15/86 57-32-00 Dec 1/71
Nov 15/86 57-32-00 Dec 1/71
Nov 15/86 57-32-00 Mar 15/83
Nov 15/86 57-33-00 Feb 15/76
7-33-00 Dec 15/94
57-00-00 Jun 15/93 -33-00 Dec 15/94
57—00—00 Aug 15/82 -33-00 Dec 15/94
57~10-00 Nov 15/81 \l‘\l\l-33-00 Dec 15/94
57-10-00 Jun 15/80 JUZ JIUT-U U1U‘lUIU'IUI 7-33-00 Dec 15/94
57-10-00 Nov 15/85 J57-33-01 Nov 15/83
57~10-00 Nov 15/81 57-33-01 Nay 15/88
57-10-00 Jun 15/80 57-33-01 May 15/88
57-11-00 Dec 1/71 57-33-01 May 15/88
57-12-00 Dec 1/71 57-33-02 May 15/82
57-12-00 Dec 1/71 57-33-02 May 15/82
57-12~00 Dec 1/71 57-33-02 May 15/82
57-13-00 Dec 1/71 57-33-02 Jul 15/84
57~13~00 Dec 1/71 57-33-02 Jul 15/84
57-13-00 Dec 1/71 57-33-02 May 15/82
57-13-00 Dec 1/71 57-33-03 Nov 15/84
57-13-00 Dec 1/71 57-33-03 Nov 15/84
57-14-00 Nov 15/85 57-33-03 Nov 15/85
57-14-00 Jul 15/73 57-33-03 Nov 15/85
57-20-00 Jun 15/93 57-33-03 Nov 15/85
57-20-00 Jun 15/93 57-33-03 bbbb oco\o o o§@ ANQ@ § N@§ Xi@ P N4$@£§ Q Nov 15/85
b bmb b b 0000
57-21-00 Jul 15/84 57-33-03 405/406 Nov 15/85
57-21-00 Dec 1/71 57-34-00 1/2 De C 1/71
57-21-00 Apr 15/73 57-34-00 3/4 Dec 1/71
57-22-00 Dec 1/71 57-35-00 1 Dec 15/93
57—22-00 Dec 1/71 57-35-00 2 Dec 1/71
57-22-00 Feb 15/73 57-35-51 401 May 15/82
57-23~00 Nov 15/74 57-35-51 402 Nov 15/74
57-23-00 Nov 15/74 57-40-00 1/2 Dec 1/71
57-23-00 Nov 15/81 57-41-00 1/2 Dec 1/71
57-23-00 \. NAQbdbN AbNwdOb NmaA dN0bwmd a
:an-1»nuLNua~1»->4av:$@‘\\
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57-23-00 403/404 Nov 15/81 57-43-00 1/2 Dec 1/71
57-30-00 Dec 1/71 57-43-01 201 Nov 15/86
List of Effective Pages
Page 1
0508 Dec 15/94
 bu 1
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MAINTENANCE MANUAL

CHAPTERI CONFIG CHAPTER! ¢o~r1@

SECTION PAGE P.L\.I§. .£.QP.§._ EQQL __P/WE. P-‘\,TE CODE
57-43-01 202 Nov 15/86
57-43-01 203 Nov 15/86
57-43-01 204 Nov 15/86
57-43-01 205 Nov 15/86
57-43-01 206 Nov 15/86
57-50-00 1 May 15/73
57-50-00 2 Dec 1/71
57-51-00 1 Jun 15/79
57-51-00 2 Dec 1/71
57-51-O0 3/4 Dec 1/71
57-52-O0 Dec 1/71
57-52-00 Dec 1/71
S7-53-00 Dec 1/71
57-53-00 Dec 1/71
57-54-00 Dec 1/71
57-54-00 Dec 1/71
57-55-00 Nov 15/83
57-55-00 Dec 1/71
57-55-00 May 15/82
57-55-00 May 15/82
57-55-52 401/402 May 15/73

List of Effective Pages

Page 2
0505 Dec 15/94
 LOCKHEED
MAINTENANCE MANUAL

CHAPTER 57 ‘
RING
I

TABLE OF CONTENTS
Chapter
Section Eff ec-
Subject Subject Page tiv ity

NORKSHEET 57-HKSH
Maintenance Horksheet Reference 1 ALL
HINGS _ 57-00-00
R Description and Operation 1 ALL
MAIN FRAHE_ ' _ 57-10-00
R Description and Operation 1 ALL
NING SPARS _ S7-11-00
R Description and Operation 1 ALL
WING BOX RIBS _ 57-12-00
R Description and Operation 1 ALL
WING BOX STRINGERS _ 57-13-00
R Description and Operation 1 ALL
LANDING GEAR SUPPORT STRUCTURE 57-14-00
R Description and Operation 1 ALL

57-CONTENTS
Page 1
0508 Nov 15/as
II.__________.________________________. __
 @ _ —

LOCKHEED
HAINTENANCE MANUAL

Chapter
Section Effec-
Subject Subject Page tivity

AUXILIARY STRUCTURE 57-20-00

R Description ana Operation 1_ ALL
FIXED LEADING EDGE STRUCTURE 57-21-00
R Description and Operation 1 ALL
FIXED TRAILING EDGE STRUCTURE ' 57-22-00
R Description and Operation 1 ALL ‘
UIN6TIP_ _ 57-23-00
R Description and Operation 1 ALL
Removal/Installation 401 ALL
C

57-CONTENTS
Page 2
0508 Nov 15/86

—-—t 1-: 7 7 7 ——
 LOCKHEED
MAINTENANCE MANUAL

----1-If-11-1----11"-I---II11111111-1111"-11IIIIIIII-I1--1--------I}-1

Chapter
Section Effec-
Subject Subject Page tivity

PLATES AND SKINS 57-30-00

R Description and Operation ALL
FIXED LEADING EDGE SKIN _ 57-31-00
R Description and Operation ALL
HING BOX SKIN _ 57-32-00
R Description and Operation ALL
I

ACCESS COVER PLATES AND DOORS 57-33-00

R Description and Operation ALL
DOORS - LOWER ACCESS, OUTER
WING BOX 57-33-01
Removal/Installation ALL
DOORS - UPPER ACCESS, OUTER
NING BOX 57-33-02
Removal/Installation ALL
DOORS - ACCESS, CENTER SECTION FUEL
TANK 57-33-03
Description and Operation 025,
026,
028-036
Removal/Installation 025, 026
028-036
FIXED TRAILING EDGE SKIN_ 57-34-00
R Description and Operation ALL
NINGTIP SKIN 57-35-00
R Description and Operation ALL
CAP - HINGTIP 57-35-51
Removal/Installation ALL

57-CONTENTS
Page 3
050B Nov 15/86

i LL
 LOCKHEED
\

MAINTENANCE MANUAL

Chapter
Section Effec-
Subject Subject Page tivity

ATTACH FITTINGS 57-40-00

R Description and Operation 1 ALL
RING-T0-FUSELAGE ATTACH FITTINGS 57-41-00
R Description and Operation 1 ALL
LANDING GEAR-TO-WING ATTACH FITTINGS 57-42-00
R Description and Operation 1 ALL
PYLON-TO-WING ATTACH FITTINGS 57-43-00
Description and Operation 1 ALL
'PYLON DRAG STRUT AFT SUPPORT
FITTING BEARING 57-43-01
$323 Maintenance Practices 201 ALL

57-CONTENTS
Page 4
0508 Nov 15/86

L____ _
 LOCKHEED
MAINTENANCE MANUAL

Chapter
Section Effec-
Subject Subject Page tivity

FLIGHT SURFACES 57-50-00

R Description and Operation 1 ALL
SLATS _ 57-51-00
R Description and Operation 1 ALL
SPOILERS _ 57-52-00
R Description and Operation 1 ALL
FLAP VANES 57-53-00
R Description and Operation 1 ALL
FLAPS _ _ 57-54-00
R Description and Operation 1 ALL
AILERON 57-55-00
R Description and Operation 1 ALL
ANODIC PLATE - SACRIFICIAL 57-55-52
Removal/Installation 401 ALL

57-CONTENTS
Page 5/6
050B Nov 15/86
'I I -i'

l.0lIKfiElED (Egg)
MAINTENANCE MANUAL

WINGS - DESCRIPTION AND OPERATION

1. General
Each wing provides lift for aircraft, stores fuel, provides
support for main landing gear and wing engine.
wing structure consists of primary and secondary or auxiliary
structures. Primary structure includes the main frame of wing,
consisting of the center wing box and outer uing box. Flap
panels are primary structure. Secondary structure consists of
$33213 fixed leading edge, trailing edge, and flight control surfaces.
Center wing section is an integral part of the fuselage. Each
wing is permanently attached to the center wing section.
Outer wing box structure is a two-spar configuration with
chorduise ribs perpendicular to rear spar. Center wing box has
a five-spar configuration (front spar, rear spar and three
intermediate spars), external rib beams on lower surface, and
fuselage floor beam supports as upper external ribs.

EFFECTIVITY: ALL
Page 1
0018 Jun 15/93
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EFFECTIVITY: ALL 57""OO"O0
Page 2
0018 Aug 15/82
inuII------------'-"-"-“'""'"'""

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MAINTENANCE MANUAL

UBIN-EBBME_:_Q§§§8lEIIQN_BNQ_QEEBBIIQN

1- Oeescal
R Main frame_of wing consists_of eenter wing_bnx and outer wing
R boxes. Main frame of the_wing is nearly similar to primary
R structure of wing (Ref. Fig. 1).
Outer wing boxes are attached to genter wing_bex which is a part
of the fuselage. A set of_spar fittings positions and bolts
wing in place. A taperjshimmed, continuous V-Joint for each_of
332$ the upper and lower stringers forms a permanent wing connection. A
A. Outer Ning Box Structure
Outer wing box structure (Ref._Fig. 2) consists of front and I
rear spars, upper and lower ekin panels, upper and lower
stringers and ribs. Outer wing bog structures extend from
grggabuttock line (NBL) 116.4 to wingtip bulkhead at NBL

Outer wing box structure is an integral fuel tank that is

compartmentalized by bulkhead ribs into separate fuel tanks.
Inbeard tank extends from inner tank bulkhead at NBL 116.4
to inner wing station (INS) 477.7: Outboard tank structure
extends from INS 477.? to euter wing statron (ONS) 440.5.
Outboard tank has a fuel-tight bulkhead rib at OMS 126.8 for ,
fuel control purposes. Structural surge boxes are located 1
in aft inboard corner of each fuel tank area. A vent/surge
box area is located between outer tank bulkhead at OHS 44 .5
and tip bulkhead at NBL 910.4.
To_prevent_intergranular corrosion, all aluminum_wing bnx
skins, stringers, caps, and webe are sulfuric acid anodized
and sealed, and are assembled with faying surface sealer. 1
Fasteners are installed wete and parts are coated with a
two-parr polyurethane material. To further assure metel
protection, all Joints are frllet-seeled, and all critical
Z30IJT1ZU3.I"ZIZ-UIS3FU2DISU fasteners are brush-coated with sealing compound.
R Lower six inches of tank assembly is coeted with a second
R coat of the two-part polyurethane material.
B. Center wing Box Structure
Center wing box strecture (Ref. Fig. 3) includes 5 spars,
upper and lower_stringer—reinforced_wing skins, 12 lower ‘
external beam ribs, and 12 loneitudinal floor support beams.
Lower external beam ribs and f_oor support beams serve as
3033330 structural components of the wing. Floor beams also support
EFFECTIVITY: 111.1.
Page 1
0018 Nov 1 /81 I
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EFFECTIVITY: ALL 5'/"I9"w
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EFFECTIVITY: ALL
Page 3
gg-15 Nov 15/85
 l.O1ZKl!EiED (Egg)
MAINTENANCE MANUAL

R cabin floor boards and passenger seat tracks. Center wing

R box is part of the mid-section fuselage (Ref. 53-O0-O0
R Figure 1, and 53-11-00 Figure 1).

s|=|=:cr1v11v= ALL 57“‘10“'00

Page 4
0018 NOV

ii
 M A I NT E N A N C E MA N U A L

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WING SPARS - DESCRIPTION AND OPERATION

l. General '
The wing spars are primary structural components of the wing
main frame. The spars extend from one wingtip through the
center wing box structure to the opposite wingtip. The spars
are shear-resistant beam structures. Fatigue resistance and
corrosion protection is provided through saturation
shot-peening. Powerplant pylon fittings (Ref. 57-43-00),
control hinge supports, actuators, and accessory mounts
associated with the flight controls are attached to the spars.
A. Outer Wing Box Spars '
The outer wing spars are constructed of vertically stiffened
webs with one—piece upper and lower spar caps. The spar
webs are machine-tapered from sheet and plate stock. The
vertical web stiffeners are machined from aluminum alloy
extrusions consisting of angles, channels, Z and T sections.
The upper and lower spar caps are machine-tapered and
shot-peened to angular contour. The spars are saturation
shot~peened after machining. One-piece machined forgings
with channel ribs and a centrally located hole are provided
to stiffen the front spars at the slat track penetration
points. Structural slat track cover elements are attached
and sealed on the inside surface of the slat track stiffener
fittings. Fourteen slat track covers are installed on the
inner face of each front spar to prevent fuel leakage from
the wing fuel tanks at the points Jhere slat tracks
penetrate the wing spar. Each cover is constructed of
aluminum and is sealed internally to prevent fuel leakage.
All spar components are faying surface sealed during
assem ly, and the fasteners are installed wet.
B. Center Wing Box Spars ,
Five aluminum alloy spars are used in the design of the
center wing box structure. The front spar with extruded
I—section stiffeners on its front face is positioned at FS
983. The rear spar with extruded T-section stiffeners on
its aft face is located at FS l2ll.93. Three intermediate
spars are located at FS I043, I103, and I163. All of the
spars are approximately I9 feet long, and vary in depth to
accommodate the airfoil contour.

EFFECTIVITY: ALL I -00

Page I/2
Dec I/7|
¢@—w-1 1--L .1-1 _.__ __ _

- 1
l..0CIll-IE so H93’
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WING BOX RIBS — DESCRIPTION AND OPERATION

l. General I
All wing box ribs (Ref. Fig. ll are positioned perpendicular
with respect to the wing rear spar. Wing ribs from WBL ll6.5
outboard to WBL 476.0 are positioned at an angle of
approximately 25 degrees with respect to the fuselage
centerline. From.WBL 476 outboard to the wingtip the ribs are
positioned at an angle of approximately 30 degrees with respect
to the fuselage centerline. All wing ribs are of the web type
with deep drawn lightening holes or truss reinforced access
openings, and stiffeners made from extrusions or from sheet
metal shapes. Some of the outer wing box ribs serve as fuel
tank end ribs or tank divider ribs, and other ribs transmit and
distribute loads from the landing gear and the flight surfaces
into the wing box.
A. intermediate Ribs '
The intermediate rib is the basic rib configuration, which
is used in size variations throughout the wing box.
Intermediate ribs are of minimum weight construction, using
deep-drawn lightening holes and elliptical access holes.
Extruded rib caps are attached to the upper and lower edges
of the rib web. Extruded angles are joined at the forward
and aft ends of each rib for attachment to the forward and
aft spars. The ribs are attached to surface stringers with
extruded cruciform clips.
B. Fuel Tank Bulkhead Ribs
All fuel tank bulkhead ribs and fuel tank divider bulkhead
ribs are of stiffened web construction. Structural clips
sealing cups, and fuel resistant sealant are used to seal’
around the periphery and around the stringers.

EFFECTIVITY: ALI. 57-I 2-00

Page I
Dec I/7|

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Page 3/4
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 I

LOCKHEE
MAINTENANCE MANUAL

‘WING BOX STRINGERS — DESCRIPTION AND OPERATION

General - '
The win -box stringers reinforce the rise-and—fall,
machines-skin panels of the wing boxes. Stringer flanges are
also used as splices for the skin panels of the upper and the
lower skins of the wing boxes.
The wing box stringers are made from a few basic shapes. Each
stringer is machined to different cross sections and
thicknesses. All changes in stringer configurations are made
gradually with taper in various length and with two—directional
taper at the wing—box joints.
Stringer configurations and surface panel thickness are arranged
to meet the design loads, the fail safe requirements and the
fatigue requirements. The stringer-skin combination provides a
uniform stress distribution to ensure a long operation life for
the primary structure wing boxes.
Thirty-seven stringers on the outer wing box upper panels (Ref.
Fig. ll are spaced approximately S inches apart. All stringers
have a Z-shaped cross section, with the exception of two splice
stringers, which have a T-J cross section. Stringers serve also
as integral vent manifolds for the fuel tanks. All surface
stringers are machined from aluminum extrusions. Stringers are
forme to contour by shot-peening or hot-forming methods, and by
saturation shot peening.
Twenty—six stringers (Ref. Fig. 2) spaced approximately 7.5‘
inches apart, are used to reinforce the lower wing box skin
panels. All stringers have a T—J cross sectional shape and are
machined from aluminum alloy extrusions.

EFFECTIVITY: All.
Page I
Dec /7|
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MAINTENANCE MANUAL

LANDING GEAR SUPPORT STRUCTURE - DESCRIPTION AND OPERATION

General
The main landing gear support structure (Ref. Fig. 1) is located
at HBL 222.6, and is connected to the heavy outer wing box ribs
at INS 346.1 and 372.6. The structure is designed as a torque
box cantilevered from the rear spar. A large steel fitting,
Located on the inboard face of the torque box provides the
primary load path from the landing gear to the outer wing box.
The main Landing gear support structure is attached to the rear
spar and the outer wing box ribs by tension bolts. These
tension bolts are torqued to a specified preload. The nuts are
located on the rear side of the rear wing spar and the main
landing gear torque-box fittings.
The preload can be checked by a torque check on the tension bolt
muts. Access is gained through the wheel well for the inboard
set of three nuts and through an access hole in the outboard rib
of the main landing gear torque box for the outboard set of the
three nuts. U

The wing box upper and lower surfaces are extended approximately
15 inches aft of the spars to provide a d1rect shear attachment
of the'main landing gear torque~box structure to the outer uing
box panels.

EFFECTIVITY: ALL
Page 1
001B Nov 15/85

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MAINTENANCE MANUAL

AUXILIARY STRUCTURE - DESCRIPTION AND OPERATION

1. General
Auxiliary structures (Ref. Fig. 1) are those structural wing
components not included as primary structures. Primary
structure includes the wing main frame, the main landing gear
support structure and flap Panels. Auxiliary structures include
the fixed leading edge, the fixed trailing edge, the wingtip
structures and the flight control surfaces excluding flap
321353 3 pane s.

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 LOCK!-IEED
1-, MAINTENANCE MANUAL

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MAINTENANCE MANUAL

FIXED LEADING EDGE STRUCTURE - DESCRIPTION AND OPERATION

1. General‘
The fixed leading edge of the wing (Ref. Fig. 1) extends
approximately 88 feet from the fuselage to the wing tip. The
leading edge structure consists of forged-track rib assemblies,
intermediate A—frame supports, leading edge skin and access
panel support members, truss-type_r1bs for the pylon fairing and
additional snubber ribs for the fixed leading edge structure
outboard of the pylon.
The forged—track rib assemblies and the snubber rib assemblies
R are part of the slat operating mechanism. They serve also as
the supporting structure for the panel support members and the
skin panels of the fixed leading edge.

EFFECTIVITY: ALL “'00

Page 1
0015 Jul 15/84 =
 LOCKHEED ®
MAINTENANCE MANUAL

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Page 2
D508 Dec /71
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Page 3/4

U‘ t I Apr IS/73
 LOCKHEEDQQQ}
MAINTENANCE MANUAL

FIXED TRAILING EDGE STRUCTURE — DESCRIPTION AND OPERATION

I. General
The fixed trailing edge structure (Ref. Fig. ll consists of all
wing structure aft of the rear spar (from'wBL I17 outboard to
the wingtip), except for the landing gear support structure
which is part of the wing box. The fixed trailing edge
structure supports the inboard and outboard flaps, vanes,
spoilers, ailerons, and the fixed and removable panels on the
upper and lower surfaces. A cavity in the trailing edge
structure accommodates the landing gear strut.
Support for the four double-slotted fowler flaps is provided by
torque boxes, which are part of the fixed trailing edge
structure. Each flap segment is supported at each en by -
carriage tracks, which are mounted on the side of torque box
ribs, and by a swing link, which is fixed to the aft end of the
torque box.
Torque boxes number two and five have tracks and swing—links on
both sides. Torque boxes number three, four and six.have a
track and a swing link on one side only and an aileron on the
opposite side. The rib for the inboard track and swing—link for
flap number one is attached to the fuselage.
A. Inboard Trailing Edge
This portion of the fixed trailing edge is triangular in
shape and extends from the fuselage to the inboard aileron.
It is also referred to as the bat wing because of its
characteristic shape and location.
Four beams and their associated rib structure provide
support for the fixed trailing edge surface panels and the
spoiler assemblies.
The forward intermediate beam forms the forward side wall of
the landing gear well. The aft intermediate beam and the
inboard auxiliary beam, with their adjoining rib structure
and surface panels, form a box beam which provides support
for the inboard spoiler. This box beam is sup orted at the
inboard ends of the beam by fittings mated witg
corresponding fuselage attachment fittings.
The outboard auxiliary beam provides support for the fixed
trailing edge surface panels and for the flap and spoiler
support structure.

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 - ll r
I. o c ii ll E r n
MAINTENANCE MANUAL
The four trailing edge beams are simple truss and web
members. The ribs are of the built-up truss type. The rib
and spar assemblies are fabricated from extrusions, sheet,
and machined fittings of aluminum alloy. ’
B. Outboard Trailing Edge
The outboard fixed trailing edge structure consists of
built—up ribs, hinge fittings, and actuator support fittings ;
which are attached to the wing box rear spar. hese
fittings are machined from aluminum alloy forgings.

EFFECTIVITY: ALI. 57-2 2-00

Page 2
050 Dec /7|
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1- sensual '
R The wing tip structure (Ref. Fig. 1) consists of the front-spar
extension bean, the rear-spar extension bean and the
longitudinal beam. All beams are oi a truss-type construction.
R They are enclosed and connected to the uing tip skins and panels

R Hing tip position lights are located forward and aft on the
assembly.
The wing tip assembly is removed and installed as a unit. The
wing tip is attached with bolts to the leading edge closeout -
rib, the outer uing box closeout rib and the front and rear spar
Z333 extensions of the outer wing box.

EFFECTIVITY: ALL PDQO 1

I 9015 Nov 15/75
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MAINTENANCE MANUAL

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R Figure 1
EFFECTIVITY: ALL
Page 2
i 0016 Nov 15174
 ,i, __i - _ i... , _-_., 1

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MAINTENANCE MANUAL

HlN§_IlE_:-B§flQ!flL_fiNQ_lN§I£LL£IlQN

1. Esuieesot_aod_Materials
General Purpose Universal Sling, B-715, or equivalent
Crane or lifting device for approximately 100-pound capacity
Sealant - PR8501K (Products Research Corp), or equivalent
Spatula, wood or plastic

2- Beiereesed_Eressdurs
R 20-51-04 Environmental Sealing

3- Bseoselllesrelletioe
A. Removal
(1) Remove lower main panel from wing tip (Ref. Fig. 401).
(2) Disconnect connectors for strobe and position lights.
(3) Remove three hoist point screws (Ref. Fig. 401), attach
sling with removed screws, and take up s ack.
(4) Remove screws along the outer wing box closeout rib.
(5) Scrape eff aerodynamic sealing compound along wing tip
separation line, using wooden or plastic spatula.
(6) Remove attachment bolts from forward and rear spars.
(7) Remove wing_tip with horizontal outboard motion until
flux valve 15 cleared.
(8) Stow wing tip in protected area (as required).
B. Installation
NQIE: ;f a wing tip other than the one removed is to be
installed, it may_be necessary to increase the _
dgameter of certain holes 1n_the upper and lower wing
tip skin panels. Refer to Figere 401 delta notes 1
and 2 for the location of SD8C1f1C holes (6 on uppeq
panel and 4 on lower panel) which may be increased in

EFFECTIVITY: ALL
Page 401
0018 Nov 15/81
——7—- ————' 7 7T7 it i '7 7 fit’ ' g
 LOCKHEED @
MAINTENANCE MANUAL

ZONES 535 AND O35

HOIST POINT r ,
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R Figure 401
EFFECTIVITY: nu. 57"ga§e"%
0018 Nov 15/74
 LOCKHEED
MAINTENANCE MANUAL

size from 0.193/0.199 (No. 10), to 0.218/0.224 (7/32)

inch diameter
Remove sealing compqund along wing tip_separation line
on wing structure with wooden or plastic spatula and
clean as required.
Remove lower main panel from replacement wing tip.
Check condition of antichafe material on wing structure
mating surfaces with the wing tip.
QAUILQN: D0 NOT ALLOW WING TIP TO CONTACT FLUX VALVE.
Attech sling to hoist points, and lift wing tip into
position.
Install bolts to attaeh forward and rear spar
extensions to outer wing box spars (Ref. Fig. 401).
Install scgews to coneect wing tip to outer wing box
closeout rib, to leading edge panel, and to trailing
edge panel.
Remove sling and install hoist point screws.
Cqnnect electrigal connectors for strobe and position
lights, and verify operation.
Install lower main panel.
N915: Captive (reduced shank) type screws will be
torqued to same value as noncaptive screws of
same size (Ref. 20-51-02, Table X).
Fill external gap between wing skin and wing tip skin
with aerodynamic sealing compound (Ref. 20- 1-04).

R EFFECTIVITY ALL
Page 403(404
0019‘ l Nov 1:/81
 "__""' ' _ " ' “W ”' " _ W ""i " **

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Locum 2 an *"'9'1"
MAINTENANCE mum.

PLATES AND SKINS — DESCRIPTION AND OPERATION

1. General 0

Plates and skins (Ref. Fig. 1) which cover all of the ex t exiox
'
surfaces of the wing, including the fli g ht cont: o 1 suxfaces axe
made of aluminum alclad sheet, aluminum alclad plate, laminated
bonded sheet Dmetal , an d aluminum honeycomb core sandwich plates
oz pane 1 s. 1e—cast
' aluminum
' access doors are also included
' as
wing suxface plates.
The skins and plates located on the oute: wing box and center
wing box stxuctuxe are highly stxessed and are paxt of the
pximaty structuxe. lhe su:£ace—skins of the fixed leadin ed B e ,
txailing edge, wingtip, and ilight contxols axe classifies as
paxt of the secondaxy structure.

EFFECTIVITY: ALI. 57-'3 0 -00

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MAINTENANCE MANUAL

HING FIXED LEADING EDGE SKIN - DESCRIPTION AND OPERATION

1. General
Skin panels (Ref. Fig. 1) of wing fixed leading edge are
generally made of aluminum honeycomb sandwich with fiber glass
reinforced closeout edging. Skin panels with hinged blowout
panels and refueling access panels are of conventional aluminum
panel construction.
'All panels are attached with screws. Lower panels can easily be
opened for inspection and maintenance of system components
inside wing fixed leading edge. All lower panels have
single-length captive screws and nonstructural suspension hinges
for retention of panels to structure in the open position.
Five lower panels between fuselage and engine support pylon have
provisions for relief of overpressure from inside wing fixed
leading edge (Ref. Fig. 2).
Hinged blowout panels are located between panel stiffeners.
They have latches with a controlled holding force. Excessive
internal pressure in fixed leading edge, like pressure caused by
ruptured engine bleed air duct, would overcome latch holding
force and open hinged blowout panels for pressure relief.
Ningfid blowout panels can be closed by manual re-engagement of
atc .
Blowout panel latches can be_disengaged on the ground, and
panels can also be used for inspection and access.
Panel latch is opened by inserting a screw driver into slot of
thumb pad and pushing towards wing trailing edge to overpower
the latch holding force.
R Latch holding force is used in four steps, ranging between 40
R and 100 pounds.
R Closing of blowout/access panel is done manually by closing
hinged blowout/access panel with slotted thumb pad extended and
then pushing slotted thumb pad to the flush position for latch
engagement.

EFFECTIVITY: ALL '00

Page 1
001B Nov 15/84

___i
 .i_._____ _

L0CKHEED
MAINTENANCE FIANUAL

SIEII. Illll SIIIIPS IIYPI

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EFFECTIVITY: ALL Nov Page
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 LODKHEED $9
MAINTENANCE MANUAL

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MAINTENANCE MANUAL
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WING BOX SKIN - DESCRIPTION AND OPERATION

I. General
Three outer wing box panels (Ref. Fig. I and 21 are joined to
form the upper and lower skins of the outer wing box. The
individual surface fianels are machined from
five-eighths-inch-t ick hard clad plates on the inner surface,
leaving the clad material on the external surface only. Rise
and fall machining provides integral reinforced areas on the
internal or wet side. The panels are tapered to provide gradual
changes in cross section.
The wing box skins are fabricated from 7075-T7651 clad plate,
shot-peened to contour, and saturation shot-peened to improve
corrosion and fatigue resistance.
I
Two skin panels on each surface comprise the cover of the upper
and lower surfaces of the center wing box structure. Each skin
anel is machine-sculptured from 7075-T765! aluminum alloy.
ggins are also tapered, shot-peened, and finished as described
3 Ove.

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EFFECTIVITY: ALL
Page 3/4
0018 Mar 15/83
7_ j _* _ _ _ — —— —- " ‘ "" "*’ "' '7 ‘-1'
iI

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MAINTENANCE MANUAL

ACCESS COVER PLATES AND DOORS - DESCRIPTION AND OPERATION

1. General
Access into the outer wing box structure is through 20 openings
on the lower surface that are approximately 11.5 by 16 inches
R (Ref. Fig. 1). The inboard tanks have five openings: four into
the fuel tank area proper and one into the surge box area.
Large holes through rib webs provide a crawl path for fuel tank
maintenance operations. The fifteen openings in the outer wing
tank permit maintenance operations in adjacent bays through rib
web holes. The doors are of aluminum alloy, pressure die~cast
construction, with integral stiffeners and bosses which house
the insert nuts.
There are three access openings in the upper surface (Ref. Fig.
2). One opening in each fuel tank provides access to the vent
valve and fuel Level control switch. The third opening; located
near the outboard end of the outboard fuel tank, provides access
to the wing fuel vent box installation
A. Lower Surface Access
The lower surface access doors are flanged to rest and to
seal against the inner side of the structural wing skin.
The access doors are installed with an external clamp ring,
and one—quarter-inch—diameter screws of the same length.
The access door (534AB/634AB) next to each wing tip has
nonmagnetic stainless steel screws because of proximity to
the flux valve. All other doors have alloy steel screws.
The attachment screws have a thread length which limits the
engagement depth into the encapsulated dome nuts for
protection of the dome against damage or penetration. A
groove around the edge of each door accepts a molded
D-section, Buna-N fuel seal. The seal is cemented into the
groove. A phenolic chafing strip, or ring, is bonded
outside the seal groove around the edge of the door to
prevent fretting of the door on the wing skin seat.
The clamp ring is a flat, one—eighth-inch-thick piece of
7075-T6 aluminum alloy with countersunk holes to accept the
retaining screws. Access covers and wing surface panels are
finished to provide good electrical continuity.
An aluminum-mesh gasket is installed with the clamp ring.
This gasket prevents or reduces fretting and
stress-corrosion in clamping ring contact areas with the
structural wing skin. The aluminum mesh gasket is treated
with anticorrosion grease. In addition the aluminum-mesh
EFFECTIVITY: ALL
. Page 1
0018 Feb 15/76

,. .,_ 7 bi‘ i 7 i ~ ”"" "’i’ I—ll' ' '

 . . _-|---_. .-q-1 -—: 7 :____,___ ___
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MAINTENANCE MANUAL

gasket provides electrical conductivity between the door and

wing skin for lightning protection.
NOTE: An expedient airworthy repair, when the aluminum mesh
gasket has been damaged or otherwise unuseable and no
parts are available, is to omit the aluminum mesh
gasket as long as the electrical resistance checks of
the door to wing skin are performed per MM 20-24-O4,
Table 202, Item 18 (or equivalent resistance check
included in the respective removal/installation
instructions) are met. An AMPS item follow up must
be generated to install the aluminum wire mesh gasket
fififififi within the following two calendar days.
Upper Surface Access
The upper wing surface has three access openings in each
wing: one over each tank level control and vent valve, and
one over the vent venturi standpipe in the vent box.‘ The
access door (534AT/634AT) next to each wing tip has
nonmagnetic stainless steel screws because of proximity to
the flux valve. All other doors have alloy steel screws.
The fuel level control and vent valve openings are 9 by 14
inches, and the vent box access opening is 9.5 inches by 16
inches. All doors are held in place with one-quarter-inch
screws.
The upper access doors are mounted on the outside of the
wing skin, and the clamp ring is mounted internally.
Retainers prevent the clamp ring from falling inward when
the door is removed. Two D—section seals and the
encapsulated floating insert nuts are located in the clamp
ring. Each upper door has two removable screws installed in
encapsulated nuts. These screws are used for attachment of
a locally fabricated handle to aid in the removal and
installation of the door.
On aircraft 001-031 without S857-092,
an aluminum gasket (unplated, 0.012 inch thick) is installed
between the wing skin and the door flange at the two
locations for access to the vent valve and fuel level
control switch. The aluminum gasket is treated with
anticorrosion grease. The gasket provides conductivity for
lightning protection and prevents fretting in the area where
the access door contacts the wing skin. The aluminum gasket
is not used for the access door that provide access to the
wing fuel vent box (Ref. Fig. 402).
On aircraft 001-031 with SB57-092 and 032-999
an aluminum gasket (unplated, 0.012 inch thick) is bonded to
the wing skin under the door flange at all three upper wing
322$
323 3703 23 surface locations. The aluminum gasket is treated with
EFFECTIVITY: ALL
Page 2
OO1B Dec 15/94

"\
 -0
|.O(IKliElED (Egg)

MAINTENANCE MANUAL

R anticorrosion grease. The gasket provides conductivity for

R lightning protection and prevents fretting in areas where
R the access door contacts the wing skin (Ref. Fig 402).

EFFECTIVITY: ALL 57"'33"00

Page 3
0018 DEC
-» _| _

I.O(IKliEIED

MAINTENANCE MANUAL

/
I

_ ' DOOR

'7?’ nut
_____ 1/ nmmta
-------" /-. - 5 _r ‘.'7= v rust stat
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. U PHENOLIC
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8.5“, AMESH

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ACCESS DOOR

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A AN EXPEDIENT AIRWORTHY REPAIR, WHEN THE ALUMINUM MESH GASKET HAS BEEN DAMAGED OR
OTHERWISE UNUSEABLE AND NO PARTS ARE AVAILABLE, IS TO OMIT THE ALUMINUM MESH CASKET
AS LONG AS THE ELECTRICAL RESISTANCE CHECKS OF THE DOOR TO WIND SKIN ARE PERFORMED
RER NIIM 20'2d-Dd, TABLE 202, ITEM I8 (OR EQUIVALENT RESISTANCE CHECK INCLUDED IN THE
RESPECTIVE REMOVAUINSTALIATION INSTRUCTIONSIAREII-1EI. AN AMPS ITEM FOLLOW UP MUST
BE CENLRAIED TO INSTALL THE ALUMINUM WIRE MESH GASKET WITHIN THE FOLLOWING TWO
CALENDAR DAYS. Ml-(IID')-'57-DTI

C Lower Surface Access Doors

C Figure 1
2 EFFECTIVITY: ALL
Page 4
001B Dec 15/94
 _.i-_ ____ __. _. . ..i__.i--._...- - _ _ _ _ _ ,__ _ __

I.O(IKIiEIED

MAINTENANCE MANUAL

/
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RETAINER III

zoms sac sac

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REMOVABLE SCREWS
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AERODYNAMIC
PRIMARY ELECTRICAL PATH SEALANT
gmum __ WING SKIN

RETAINER
chrnvs scam FUR SEAL Rm "p PZIIENOLIC STRIP
DOOR I I
IZI
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rtommc mszar aI1‘éI<‘II‘UM
FUEL wmc Sm“ THIS VIEW APPLICABLE
stat amc \ 10 mo maomzo ACCESS nooas
mpg; y\_JK Hm SEAL mm
PHENOLIC stmr AERODYNAMIC
PRIMARY ELECTRICAL PATH SEALANT
nonmc mstm CLAMP Rm“ wmc sxm
i "'

run
sew RING --.;,-.~ rueaouc stmr
IZI IZI
FLOATING mscar
THIS VIEW APPLICABLE TO
OUTBOARD ACCESS DOOR _
INO ALUMINUM GASKETI

Ml'0(II)-SHHI

Upper Surface Access Doors

Figure 2
I; EFFECTIVITY: 001-031 wnwour ses?-092 57-'33-00
Page 5
0018 Dec 15/94

‘I
-

{ll-¢iIf1>.“IIIl)
LOCKHEED
MAINTENANCE MANUAL

\\
/
4/
%§\_ RETAINER MI
\ ix .-
no / cum nmc
Ti)!
zoutsso aao ’ 0:.” /Q 45/.;.
I 1/ i

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I} ° . Q .. 9 REMOVABLE scams
FOR LIFTING HANDLE

ataoovmumc
PRIMARY nccmucw ram / swam
SEALANT __ WING S KIN
AI "
semen. "' I!-H ,-
CAPTIVE SCREW FUEL SEA‘ Rmg / '5" :,;',m0uc Srmp
DOOR IZI
ALUMINUM
" FLOATI NO INSERT QASKET
nu Jr II

rug, ' L: 1:‘ WIND SKIN

sm nmc \ Ag!I PHENOIIC stew
KEEPER rue. sat amc
cum ems
nomwc msam @

III 'OOOO'ST-OT!

R Upper Surface Access Doors

R Figure 2
R Errecnvnv: 001-031 um: sas?-092 mo 032-999 57-33-00
Dec 15/94
 iFiIii'

LOCKHEED
MAINTENANCE MANUAL

OUTER NINE BOX, LOWER ACCESS DOORS - REMOVAL AND INSTALLATION

1. General '
This removal and installation procedure is applicable_to all
lager access doors of the fuel tanks (Ref. 6-40-O0, Fig. 18 and
Q

NOTE: Fuel tanks can be left open and dry for an indefinite
period of time with no adverse effect.

2. Eguigment and Materials

Anticorrosion Grease, Aeroshell 14 (MIL-G-25537), or equivalent

Referenc ed Procedures
6-40-DD Exterior Access Doors and Panels
12-11-00 Fuel Tank Replenishing
20-24-O4 Grounding Connections - LCP 84-10278
28-11-DO Fuel Tanks - Maintenance Practices
R 28-11-00 Tanks — Inspection and Check
28-22-O0 Defueling — Servicing

4. Removal/Installation
WARNING: THE FUEL TANKS CONTAIN EXPLOSIVE VAPOR. THEREFORE,
OBSERVE ALL APPLICABLE SAFETY REQUIREMENTS AS
SPECIFIED IN 28-11-DO.
A. Removal
(1) Defuel tank (Ref. 28-22-OD).
CAUTION: ACCESS DOORS 534AB AND 634AB ARE ATTACHED WITH
NONMAGNETIC STAINLESS STEEL SCRENS. DO NOT MIX
STAINLESS STEEL SCREHS WITH ALLOY STEEL SCREWS OF
OTHER ACCESS DOORS.
(2) Rgmove screws and retain for reinstallation (Ref. Fig.

EFFECTIVITY: ALL
' Page 401
001B Nov 15/83

—— * i — j -i — -.-__.
 ..__. J‘

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MAINTENANCE MANUAL

(3) Remove clamp ring and aluminum-mesh gasket. Retain

gasket for possible reinstallation.
CR NOTE: An expedient airworthy repair, when the aluminum
CR mesh gasket has been damaged or otherwise
CR unuseable and no parts are available, is to omit
CR the aluminum mesh gasket as long as the
CR electrical resistance checks of the door to wing
CR skin are performed per MN 20-24-O4, Table 202,
CR Item 18 (or equivalent resistance check
CR removal/installation instructions) are met. An
CR AMPS item follow up must be generated to install
CR the aluminum wire mesh gasket within the
CR following two calendar days. -
(4) Push access door up, tilt and rotate out of access hole
CAUTION: PROTECT FUEL SEAL CONTACT AREA ouarwc ssnvtce
OPERATIONS. .
(S) Purge fuel tank (Ref. 28-11-O0).
(6) Place suitable protective cover over access opening as
required.
B. Installation
(1) Check door for condition of fasteners, phenolic strips,
and fuel seal ring. Check seal contact area on wing
skin for cleanness and surface condition.
(2) Prepare for electrical bonding and for lightning
protection as follows:
(a) Check and clean faying surfaces of clamp ring,
access door, and wing skin which contacts
aluminum-mesh gasket.
(b) Check aluminum—mesh gasket for mesh resilience and
surface conductivity. Clean as required, and
C apply Aeroshell 14 grease. Work sufficient grease
into the aluminum mesh so that the gasket will be
saturated.
CR NOTE: An expedient airworthy repair, when the
CR aluminum mesh gasket has been damaged or
CR otherwise unuseable and no parts are
CR available, is to omit the aluminum mesh
CR gasket as long as the electrical resistance
CR checks of the door to wing skin are
CR performed per NM 20-24-O4, Table 202, Item
CR 18 (or equivalent resistance check included
EFFECTIVITY: ALL 57-33-01
0018 iI§§’f'is‘;2§
l __k i_,._ ....__..i.i. . --,7 _— _ Iii

LOCKHEED
MAINTENANCE MANUAL

I ' DOOR
pt?’ NUT
if __,_ acumen
/"I ~- » ,___r "=;"=“ run SEAL
- ' 1-— -|l H L RING
' I I . PHENOLIC
rJ Z4 I//2 \“ _‘ STRIP
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mm, Rm ® wmc sxm
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ACCESS DIDR

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A ALUMINUM-MESH CASKET O Q ,9
NOTE
A AN EXPEDIENT AIRIVORTHY REPAIR, WHEN TIII. ALUMINUM MESH GASKET HAS BEEN DAMAGED OR
OTHERWISE UNUSEABLE AND NO PARTS ARE AVAILABLE, IS TO OMIT THE ALUMINUM MESH GASKET
AS LONG AS THE ELECTRICAL RESISTANCE CHECKS OT THE DOOR TO WING SKIN ARE PERFORMED
PER MIM 20-24-OII, TABLE Z02, ITEM I8 IOR EOUIVALENT RESISTANCE CHECK INCLUDED IN THE
RESPECTIVE REMOVALIINSTALLATION INSTRUCTIONSI ARE MET. AN AMPS ITEM FOLLOW UP MUST
BE GENERATED TO INSTALL THE ALUMINUM WIRE MESH GASKET WITHIN THE FOLLOWING TWO
CALENDAR DAYS. Ml'W'ST"DTI

CR Access Doors - Removal and Installation

CR Figure 401
EFFECTIVITY: ALL
Page 403
0018 May 15/88
 IiII¢_¢I 1-:-v 1 _ i-_ — i

l.0(iKliEl5D (Egg)
MAINTENANCE MANUAL

ca in the respective removal/installation

ca instructions) are met. An AMPS item follow
CR up must be generated to install the
CR aluminum wire mesh gasket within the
ck following two calendar days.
CAUTION: DO NOT APPLY EXCESSIVE ANTICORROSION GREASE.
ANTICORROSION GREASE MUST NOT BE SQUEEZED INTO THE
TANK AREA WHEN DOOR IS CLAMPED IN POSITION.

C (3) Apply Aeroshell 14 grease to access door directly

inside of the molded rubber seal (Ref Fig. 401, View
A). Grease on rubber seal is permitted.
(4) Position access door in place and install aluminum mesh
gasket and clamp ring. -
O

(5) Torque screws 35 to 45 lb in.

(6) Wipe off excessive grease.
(7) Check electrical resistance of access door to wing skin
(Ref. 20-24-O4).
NOTE: Electrical resistance for installed access door
bfitween door and wingskin must not exceed 0.0025
0 m.
(8) Replenish fuel tank (Ref. 12-11-00) and perform leak
check (Ref. 28-11-00).

EFFECTIVITY: ALL 57"'33"'01

Page 404
0018 May 15/88

1_______._______________________.__.______________i
l,.................______________.- _s- ---m_ - s______________________
1
L()Cl(HlEEl)g£§E9
MAINTENANCE MANUAL

QUI§B_HlB§_EQZ4-UEE§B-&§EE§§_QQQB§_:_8§UQ!&L_BNQ-I8§IfiLL5IlQN

1- General I
This procedure is ap I0— le to all upper access doors for the
fuel tanks (Ref. 6-4 (DU Q-*- On vm U'‘
N915: Fuel tanks can be left open and dry for an indefinite
period of time with no adverse effect

2- §quiement-eed_@eteciels
Handle for access door removal (handle to be locally fabricated)
R Grease, Aeroshell 14 (MIL-G-25537), or equivalent
R Anticorrosion Compound, MIL-C-16173, Grade 4, or equivalent
R Cleaner, MIL-T-81533, 1-1-1, Trichloroethane, or equivalent
R Sealing Compound, PR 8501-K (Products Research Co., Burbank,
R Calif) or equivalent
R Sealing Compound, LCM40-2188 (Essex Chemical Corp., Compton,
R Calif) or equivalent
R Mold Release Agent, RAM mold Release No. 225 (RAM Chemicals Co.,
R Gardena, Calif.), or equivalent
R Adhesive, Fed. Spec. MMM-A-1617 (1) Type III, or equivalent
Spatula, uood or plastic

3- Be!e:eesed-Eceseduce
R 6-40-00 Exterior_Access Doors and Removable Panels -
R Description and Operation
20-24-O4 Grounding Connections - LCP 84-10278
28-11-00 Fuel Tanks - Maintenance Practices

4- Bemevelllestellatien
QABNINQ: THE FUEL TANKS CONTAIN EXPLOSIVE VAPOR. THEREFORE
OBSERVE ALL APPLICABLE SAFETY REQUIREMENTS AS I
SPECIFIED IN Z8-11-O0.

EFFECTIVITY: ALL
Page 401 i
I ooiel . May 15/82
-- -»__ __ - — * 1-in —
V'——_——'____—" I M “O I I
1
L(JC|<HlEEl)‘£%g)
MAINTENANCE MANUAL

A. Removal
(1) Remove sealant from gap around access door. Use wood
or plastic spatula.
ggulggu: ACCESS oocas 534AT AND 634AT ARE ATTACHED WITH
NONMAGNETIC STAINLESS STEEL sceews. 00 NOT MIX
STAINLESS STEEL SCREWS WITH ALLOY STEEL SCREWS OF
OTHER ACCESS DOORS.
(2) Remove two serews in central area of door and install
locally fabricated door handle.
(3) Remove all ecrews from periphery of door and retain for
reinstallation.
(4) Remove access door.
(S) If clamp ring is to be removed, proceed as follows:
(a) Remove sealant from around clamp ring retainers
and screws (4 places)
(b) Loosen captive screws on clamp ring, rotate
retainers, and carefully lower clamp ring. Rotate
clamp ring and remove from access hole. (Ref.
Fig. 401).
(c) On aircraft_001-031 without $85?-O92,
remove aluminum gasket for either of two inboard
access doors 531AT/631AT or 532AT/632AT (Outboard
access doors 534AT and 634AT do not require the
aluminum gasket.)
(c) On aircraft O01-O31 with S857-092 and 032-999,
aluminum gaskets are bonded to wing skin recesses
R of all three doors and should not e removed
R unless damaged. .
(6) Place suitable protective cover over access opening as
required.
B. Installation

(1) On aircraft O01-031 without SB57-O92,

clean and check clamp_ring,_sealed dome nuts fuel seal
rinee, screws, phenolic strips, aluminum gasfiet (at
app icable locations), door decals and door and wing
skin faying surfaces for condition.
(1) On aircraft OO1-O31 with S857-O92 and O32-999,
clean and check clamp ring, sealed dome nuts, fuel seal
EFFECTIVITY AU. 57'33'U2
Page 402
OO1B May 15/82
L
 m—'%— L OCKHEED
MAINTENANCE MANUAL

,1 M
\\
h RETAINER Ill
\ ‘\ ___ ._
iii’ \\" X
Q»
0 o A T CLAMP mm

zouesao aao O ,,e = S D 0 ~

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0 I‘ 0 °
Q O///
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O O9

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Q-

g, ". M /.*>“® ACCESS noon

ITYPICAL 3 PLACES)

A sum“
~=,_,~
O.
REMOVABLE SCREWS
roe unmo I-IANDIE A
RETAINER P
CAPTIVE SCRBIU
DOOR
‘ $1?

:?§.J nu
, ‘

;
I 0- e I n 1 \ ¢ . ll

vu ‘
. Am I I-_=;l=;?'- 1 Wm Sm AERODYIIAIAIC
sun mac PRIMARY ELECTRICAL mu SEALANT
.;;, PHENOLIC STRIP __ wmc sxm
“EMA run SEAL ems A
D G j‘ i
rlomno INSERT @ CUM Rm“ 5' PI-I
A saw. ems mm OI. ' c STRIP
ALIIAINIJM A
on FIOATI NB INSERT ggggg
u I THIS VIEW APPLICABLE
A LOCALLY FABRICATE LIFTING HANDLE To mg mggggp g(;(;|;55 99935
A, UNPIATED AIUMINUM casket. 0.012 m. THICK ,mn,,m,|c
I2 INBOARD ooons omv I. con BOTI-I smss or sum"
cases: -aim AHTICDRROSIOH GREASE. AEROSHEIL PRIMARY HECTRICM Pam
w (MIL-6-25537) on EQUIVALENT ""46 SKI"
A AT use clmr RING RETAINER I4I, APPLY SEAIAIIT -Ii?
T0 ENTIRE urea: sums: IINCUJDINC new Ir SCREW! A FUEL I?”
AND SIUES Q RETAINER IRE. 20-51-04) SEAL RING _$_ Puaqouc SIR")

4 con SCMS, rumour: muss mo All mmc (3; I2)

sumccs WITH ANTICORROSION cams, AERO-
sum I4 IhIIl'-0-255371 on zeumuzm nonmc INSERT
5 ON ACCLSS DOOR. APPLY COATING CF MOLD RELEASE nus vim APPLICABLE to
AGENT TO roun RECTSSED AREAS. THESE AREAS ALIGII ouiguggo Acczss noon
WITH CIMIP RING RTJAINER. mg Au_w||m_p,\ cgsgm
A com run. sm. mm WITH
-W-$7-03

2 Access Doors - Removal and Installation

Figure 401
EFFECTIVITY: OO1-O31 WITHOUT SB57-D92
Page 403
001B May 15/82

L
 Fl— *" _-— -----_ -~- -. - --i-A---N ii -

LOCKHEED
MAINTENANCE MANUAL

-> RETAINER Ill

*=:~@_.____
—-—-
-"=-- , ntcn.
""""-""""" ‘--'-__'—'

‘ zones sn on

scnsw mmcau
ACCESS noon

I
'\
1
~ wmn SKIN

ACCESS DOOR ITYPICAL 3 PLACESI

cum? mm
CREW

Acczss o0oa\ =.
fl
' SCREW ITYPICALI
-.
1

-.
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rm sm amc. :2: Q.)

‘ xi!
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|\‘ ' ncczss noon
O)‘:2,-:\-32: E==»
SE5, cum» umc
acumen m
vnzw snowmc AREAS mzoummc wamcmou |([[p£R (4,
mo casm . I wmc sum
1.7:‘ _=»-—~;\_______, M
ii J WING sum
casm I1!-'1:-‘I A CU‘-"I9 “II”

II TI
9
VIEW OF DOOR INSTALLED ITYPICALI @
VIEW maoucu cum nmmen
mo LUBRICATION AREAS
~
GASKET BONDED TO SKIN RECESSED SURFACE WITH LCM 40-2188
APFLY mIL-G 25537 IAERO SHELL III PREFERREOI GREASE TO FAYING SURFACES OF DOOR, RIM
AND GASKETS AS SHOWN
THE GROOVE AROUND DOOR AND SKIN PERIPI-IERY TO REMAIN FREE OF BOTH MIL-6*-5537 GREASE
AND MIL-C-16173, GRADE 4 CORROSION COMPOUND
RING RETAINER TO BE INSTALLED ON TOP OF GASKET, AND MUST NEST INSIDE RECESS IN
ACCESS DOOR
INSTALL ACCESS DOORS BY USING MIL-C-T6173, GRADE 4 ANTICORROSION GREASE
ON ALL NUTS IN DOOR RING BY FILLING AND ORAINING CAVITIES, AND ON ALL ATTACH HQE
COUNTERSINKS WET INSTALL ATTACHING SCREWS ON INSTALLATION
AFTER DOOR INSTALLATION CLEAN GROOVE AROUND DOOR PERIPHERY AND APPLY AEROOYNAAIIC
COMPOUND PRBSOI K
COAT FUEL SEAL RING WITH MMM A I6ITIII TYPE III ADHESIVE
Ml'IIIlB'57'NZ

Access Doors Removal and Installation

F1gure 401
EFFECTIVITY 001-031 wnu s05?-092, 032 999
Page 404
9313 Jul 15/84
V""'_____—“" I ——?_—fi
LOCKMEED ®
MAINTENANCE MANUAL

rings, screws, phenolic strips, door decal and door and

bonded gasket faying surfaces for condition.
(2) Prepare for electrical bonding and lightning protection
as follows:
(a) Verify that all faying surfaces are clean.
(b) Verify that clamp ring retainers and captive
screws are clean.
(c) On aircraft 001-031 without SB57-092,
for either of two inboard access doors _
(531AT/631AT or 532AT/632AT), verify that aluminum
gasket is clean. Apply coat of anticorrosion
grease to each side of gasket and install in
position in wing skin recess.
(c) On aircraft 001~031 with 5857-092 and 032-999,
for three access doors (531AT/631AT, 532ATl632AT
or 534AT/634AT), verify that bonded gasket upper
surface is clean. Apply coat of anticorrosion
grease to upper surface of gasket.
QAUTION: D0 NOT APPLY AN EXCESSIVE AMOUNT OF ANTICORROSION
COMPOUND.
(3) Ueing anticonrosion compound, lunricate nuts in clamp
ring by filling and drain]ng cavities and coating
attach hole countersinks in door (Ref. Fig. 402).
(4) Install fuel seal ring(s) (Ref. Fig. 401) using
MMM-A—161? (1) Type III Adhesive in the groove making
certain that the seal ringls) do not pop out prior to
installing the clamp ring.‘
4'5 U’! Mn’ Apply grease to clamp rirr r 1! Itlhi
FCOI
Qoplnnnqq
D-"J l-cl
Q05-I
ullu
gananapqn
‘Ill |=|

fuel eeal ring (Ref. Fig. -I-\lC£ ) If--‘I ~10 Irt- Grease on fuel seal
ring is permitted.
(6) Position clamp ring in tank; engage and tighten captive
screws in clamp ring retainers.
(7) At each of four clamp ning retainers, apply sealant to
entire upper surface (including head of captive screw)
and sides of retainer (Ref. 20-51-O4).
gglg: Apply sufficient sealant on top surface of
retainers t6'f1ll matching recessed areas in
doer. Access door is installed while sealant is
we .

R EFFECTIVITY:
R
All 57-33"OZ
Page 405
001B Jul 15/84

LI
 ‘ " '— ass’ i —-'¢_"'i

l.O(IKfIEIED <E§gD
MAINTENANCE MANUAL

(8) On access door, apply coating of mold release agent to

four neceseed areae. These recessed areas align with
clamping ring retainers.
(9) On aircraft 001-O31 without S85?-092,
Install access door, and torque screws 35 to 45 lb in.
(9) On aircraft O01-031 with SB57-O92 and O32-999,
install access door; completely coat screws (except
exterior flat surface of head) with anticorrosion
compound: Torque screws to 20 to 25 lb in. per placard
instructions.
(10) Check electrical resistance of access door to wingskin
(Ref. 20-24-04).
NOTE: Electrical resistance for installed access door
between door and wing must not exceed 0.0025
o m.
(11) Remove excess greese from around door gap and clean as
required for application of sealant
(12) Apply sealing compound to fill gap between access door
and wingskin (Ref. 20-51-O4).

R EFFECTIVITY: ALL
Page 406
001B May 15/82
 LOCKI'iEED |
MAINTENANCE MANUAL

CENTER SECTION FUEL TANK, ACCESS DOORS - DESCRIPTION AND OPERATION I

1. General
Access into the center section fuel structure is through three
openings, on the lower surface there is one located at FS 985
and two located at F5 1212. Large holes through rib webs inside
the center section fuel tank provide a crawl path for fuel tank
maintenance operations in adjacent bays. The doors are of
aluminum alloy, pressure die-cast construction, with integral
stiffeners and bosses which house the insert nuts. The
attachment screws have a thread length which limits the
engagement depth into the encapsulated dome nuts for protection
of the dome against damage or penetration. The doors with seal
is cemented into the grove (Ref. Fig. 1).

. R EFFECTIVITY: 025, 026, 028-036

R Page 1
0013 Nov 15/84

;_ ________
 7

l.O(ZKIiEIED QQEED
MAINTENANCE MANUAL

PS TAM SA
PS IIO3 §3
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FS IIIB AND ES I16) AIl'm'!I"IBT

Center Section Fuel Tank, Access Doors

Figure 1
R EFFECTIV m= 025, 02¢, 02a-03¢ 5?-33-D3
R
001a 2
Nov P°°°
15/84

L —— 7 "fir-——7'" i3 * '~
 ' LOCKHEED @
MAINTENANCE MANUAL

CENTER SECTION FUEL TANK ACCESS DOORS - REMOVAL AND INSTALLATION

1. General
This removal and installation procedure is applicable to all
doors of the center section fuel tank and dry bay (Ref.
6-50-00).
NOTE: Fuel tanks can be left open and dry for an indefinite
period of time with no adverse effect.

2. Eguigment and Materials

Anticorrosion Grease, Aeroshell 14 (MIL-G-25537), or equivalent

3. Referenced Procedures
6-50-00 Interior Access Doors and Panels
12-11-O0 Fuel Tank Replenishing
20-24-04 Grounding Connections
20-51-O1 wrench Torque Values
28-11-00 Fuel Tanks - Maintenance Practices
28-11-00 Tanks - Inspection and Check
28-21-00 Pressure Fueling System - Description and Operation
28-22-00 Defueling System - Description and Operation

4. Removal/Installation
NARNINQ: FUEL TANKS CONTAIN EXPLOSIVE VAPOR. OBSERVE ALL
ggPn%C3SLE SAFETY REQUIREMENTS AS SPECIFIED IN

A. Removal
(1) Defuel appropriate 1A or 3A fuel tank (Ref. 28-22-00).

R (2) On aircraft without SB57-165,

R remove access door fasteners and retain for
R reinstallation (Ref. Fig. 401).
EFFECTIVITY: 025, 026, 028-036
Page 401
001B Nov 15/85

L. _ I ii E j T T
 l.O(IKIiEEED Qgfig)
MAINTENANCE MANUAL

(2) On aircraft with 88577165, _

remove fastener securing bonding strap to access door
(Ref. Fig. 402). Remove remaining access door
Zgeeeners and retain for reinstallation (Ref. Fig.
332$”

(3) Remove access door frame where applicable.

__ (4) Push access door in and remove.
CAUTION: PROTECT ACCESS DOOR SEAL CONTACT AREA DURING
SERVICE OPERATIONS.
(5) Purge fuel tank (Ref. 28-11-00). e_,
(6) Place suitable protective cover over access opening as
required. _
B. Installation
(1) Check access door for condition of fasteners and access
door seal ring. Check access door seal contact area on
center section fuel tank for cleanliness and surface
condition.
CAUTION: DO NOT APPLY EXCESSIVE ANTICORROSION GREASE.
ANTICORROSION GREASE MUST NOT BE SQUEEZED INTO THE
TANK AREA NHEN DOOR IS IN POSITION.
(2) Apply anticorrosion grease to access door directly
inside of the molded rubber seal. Grease on rubber
R seal is permitted.
R (3) On aircraft without SB57-165,
R position access door in place and install fasteners
R (Ref. Fig. 401).
(3) On aircraft with S857-165,
position access door in plece and install bonding strap
$330 and door fasteners (Ref. Fig. 401 and 402).
R NOTE: Bonding strap should be installed on upper
R center door fastener.
R (a) Bond the bonding strap in accordance with
R 20-24-O4.
(4) Torque fasteners (Ref. 20-51-01).
(5) wipe off excessive grease.

EFFECTIVITY: 02s 026 02s-036 57-33-03

I I Page 402
001B . Nov 15/85

--N - — _..__ —— ——— —- ii — 1 1 -1 _ 7 7 — — 41

 I
I.O(IKIIEIED <@%g)
MAINTENANCE MANUAL

(6) Check electrical resistance of access door to center

section fuel tank (Ref. 20-24-O4).
§Q1§: Electrical resistance for installed access door
between door and center section fuel tank must
not exceed 1.0 ohm.
(7) Replenish appropriate center section fuel tank (Ref.
12-11-00) and perform leak check (Ref. 28-11-00).

R EFFECTIVITY: 025, 026, 028-036

R P age 403
001B Nov 15/85

- --- I
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LOCKHEED
MAINTENANCE MANUAL

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Center Section Fuel Tank, Access Doors

Figure 401
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0013 Page 404
Nov 15/85

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MAINTENANCE MANUAL

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R Figure 402
R EFFECTIVITY: AIRCRAFT NITI-I SB57-165
R Page 405/406
001B Nov 15/85
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LOCK!-IE so WI’
wammumcs MANUAL

FIXED TRAILINO EDGE SKIN - DESCRIPTION AND OPERATION

I, General _
The upper and lower fixed trailing edge skins (Ref. Fig. I) are
made of aluminum honeycomb core panels, compressed aluminum
honeycomb core panels, and aluminum sheet panels.
A. Upper Surface Panels
Therupper trailing edge structure inboard of the pylons is
covered with six aluminum honeycomb and three small
compressed aluminum-honeycomb core panels that are
permanently joined to the substructure.
The upper skin panels outboard of the pylons are of two
configurations. The fixed panels forward of the two
outboard flaps are compressed aluminum honeycomb. The fixed
panels forward of both ailerons are aluminum honeycomb with
fiber-glass-reinforced closeout edging. The trailin 8 ed 8 e
of the panels have aerodynamic seals where they interface
with flight control surfaces.
Lower Surface Panels
The lower surface panels inboard of the pylon are of
honeycomb construction. These nonstructural, tethered
access panels have single-length captive screws. One fixed
panel on the lower inboard area forms the forward edge of
the main landing gear cavity. This panel is made of
compressed aluminum honeycomb sandwich and is riveted to the
substructure. Nylon tether straps fastened to the forward
inside edges retain the panels when they are opened.
The lower panels forward of the outboard aileron are of
aluminum
Y honeycomb sandwich construction . These pane l s are
hinged on the forward side and attached with screws. All
panels trailin g ed ges h ave aerodynamic
' seals.

EFFECTIVITY: All. 57*?) 4-""0 0 ,

Page I/2
Dec I/7|
 LOCKHEED
MAINTENANCE MANUAL
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I.O(2KIiEIED <@%g)
MAINTENANCE MANUAL

HINGTIP SKIN - DESCRIPTION AND OPERATION

1. General
The wingtip skin surfaces (Ref. Fig. 1) consist of a
double-contoured, outer cap of aluminum alloy, upper and lower
forward aluminum honeycomb sandwich panels, two aluminum close
out panels in the middle section, and upper and lower fixed
aluminum panels along the aft section inboard of the end cap.
The removable panels consist of the lower forward honeycomb
panel and the outer cap panel. Transparent lens panels enclose
the forward and aft wing position light assemblies.
R A removable aluminum plate is located in the upper forward
R honeycomb panel for access to the flux valve.

EFFECTIVITY: ALL 57-35-00

Page 1
0010 Dec 15/93

A
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LOCKHEED @
MAINTENANCE MANUAL

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wingtip Skins and Panels

Figure 1
errscnvtfv: ALL
Page 2
0508 Dec 1/71
V"__"_'_____——“m'_'_—_“"—'__
I.OlIKIiEIED @
' MAINTENANCE MANUAL

UlD§-IlE-§BE-:-BEUQ!BL-BND-IU§IBLLBIlQU

R 1- §ouiomc0t_e0d_Matccials
R Torque wrench

R 2- Bcicce0scd-EcQscdu:c
R 20-S1-02 Preparation for and Installation of Mechanical
R Fasteners

R 3- Bemeralilcslallaticn
A. Removal
(1) Remove noncaptive screws (Ref. Fig. 401, Details A and
B). Retain and_mark noneaptive screws separetely for
front and rear installation (screws are of different
lengths).
(2) Unfasten captive fasteners and remove wing tip cap.
B. Installation
(1) Position wing tip cap in place and loosely attach some
of the captive fasteners.
R (2) Install noncaptive screws (Ref. Fig. 401).
(3) Install all captive fasteners.
NQIE: Captive (reduced shank) type screws will be
torqued to same value as noncaptive screws of
R same size (Ref. 20-51-02).

srrzcnvrm All
Page 401
I 0018 May 15/82
___ g _ _ _ _ 7 H I I.
 —

R E
LOTCKIIEIED
MAINTENANCE MANUAL

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R Hing Tip Cap - Removal and Installation

R - Figure 401
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ATTACH FITTINGS - DESCRIPTION AND OPERATION

I. Genezal
Fittings used as a connection between main structural garts
include wing terminal fittings, landing gear attach fi tings,
pylon attacn fittings, wingtip attach fi tings, flight con :01
attach fittings, an wing equ1pment attach fittings.

b EFFECTIVITY: ALI.
Page I/2
O50 Dec I/7!
?3——i _”“_

Q - 1)
LOC xn 2 2 0 H9""
mxnramucz mmm.

WING-TO-FUSELAGE ATTACH FITTINGS - DESCRIPTION AND OPERATION

1. General
The win terminal fittings are heavy flanged forgings. Four cf
these fittings are used uring mating of the outer wings to the
wing center section. The fitting flanges mate with fittings at
the four corners of the center wing box assembly.

er-'|=|zcnvmz= Ai.T.*_""""'_'“ “'00

Page I/2
Dec I/7|

L
 _ __ _- _ _ .a___..-
- 1
iocxuri-:0 'r'\9""
MAINTENANCE MANUAL

LANDING GEAR-TO-WING ATTACH FITTINGS - DESCRIPTION AND OPERATION

I. General
The main landing gear strut fittings (Ref. S7-I4-00, Fig. I) are
located inboard in the trailing edge structure at approximately
INS 346. The fittings are forged 4340 steel. The fittings are
components of the main landing gear torque box. Lugs on his
fitting provide all the wing attach points for the main landing
gear shock strut.

EFFECTIVITY: ALI.
Page I/2
QSQ Dec I/7|

1 — r———fi- —| n-n-Q-_Qn
I 1)
iocxue so ."?'9‘l"
nuursmmcr MANUA1.

PYLON-TO4NING ATTACH FITTINGS - DESCRIPTION AND OPERATION

l. General
A three—point support system attaches the engine ylon to the
wing structure. wo forward support fittings macfiined from
6AL-4V titanium forgings, are mounted on the front s ar. The
fittings are approxima ely 18.5 inches center-to—cen¥er and
symmetrical about the centerline of the pylon. The aft support
fitting is attached to the wing box lower surface along the
pylon centerline. Two large 1~section beams s an the forward
and aft fittings. The beams are attached to tfie wing lower
surface, using the wing box skin as the upper close-out member
of the pylon. _

IO

EFFECTIVITY: ALI.
Page I/2
050 Dec I/71
?ii__“” ” "T "T will

LOCKHEED
MAINTENANCE MANUAL

R PYLON DRAG STRUT AFT SUPPORT FITT ING BEARING°

R NAINIENANGE PRAGIIGES

R General
R A pfilon drag strut aft support fitting bearing can be replaced
R wit an engine installed or removed.
R In each case the engine or pylon must be properly supported to
R prevent damage to the aircraft. I

R Eguigment and Materials

R Bearing, KSSBS6-20, or approved equivalent
R Tool Kit Box EL014A1-1, consisting of: Bearing Removal and
R Installation Tools

R Referenced Procedures
R 7-11-DO Hing and Fuselage Jacking - Maintenance Practices
R 12-26-O2 Hing Pylon Attach Fittings Lubrication ~ Servicing
R 54-DO-O3 Pylon/Hing Attach Bolts - Removal and Installation
R with Hing Engine Installed
R 54-O0-O4 Pylon/wing Attachment Bolts - Removal and
R Installation with Engine Removed
R 71-OD-O1 wing Mounted QEC Unit - Removal and Installation
R 71—11-01 Left-Hand Hinged Cowl - Removal and Installation
R 71-11-O2 Right-Hand Hinged Cowl - Removal and Installation

R 4. Aft Bearing Access

R WARNING: BEFORE REMOVING DRAG STRUT AFT ATTACHMENT BOLT,
R PROVIDE ADEQUATE SUPPORT FOR DRAG STRUT. DRAG STRUT
R HEIGHS APPROXIMATELY 380 POUNDS. .
R A. On Aircraft with Engine Installed,
R (1) Prepare for drag strut aft attachment bolt removal
R [Ref. 54-OO-03,401 Steps 4A(1) through (13)]

R EFFECTIVITY: ALL
R Page 201
OO1B Nov 15/86
P".-'""'" LOCKHEED
MAINTENANCE MANUAL

R A. On Aircraft with Engine Removed,

R (1) Prepare for drag strut aft'attachment bolt removal
R. ERBT. 54'UD'U4, U1, SIGDS 4A(1) TNPOUQN (8)3.

~ R 5. Bearing Removal/Installation
R R. Removal
R (1) Verify that drag strut is adequately supported by means
R of nylon strap or equivalent.
R <2) Disconnect clamps or brackets attached to drag strut
R that can interface with drag strut movement.
R' (3) Disconnect hydraulic flex lines that are routed
R parallel to drag,strut at rear connection.
R NOTE: It may be necessary to disconnect these lines at
R forward end to prevent damage when drag strut is
R moved.
(4) Loosen, but do not remove, two nuts at forward end of
drag strut.
(5) On aircraft with engine installed,
remove nut and bolt from drag strut aft attachment
point as described in 54-D0-03,401 Steps 4B(1)(a)
through (h).
(5) 0n aircraft with engine removed,
remove nut and bolt from drag strut aft attachment
pzgnt described in 54-00-04,401 Steps 48(1) through
@3033
ZZZIW

R (6) Move drag strut away from wing fitting a minimum

R distance as required to clear bearing work area.
R (7) Remove bearing from wing skate angle aft fitting as
R follows:
R (a) Insert bushing (EL422H7-108, DET.—2D1) into -
R bearing (Ref. Fig. 201).
R (b) Using C-clamp, clamp the above bearing
R (EL422H7-108, DET.~201) on 1527342 wing fitting.
R (cl Insert hole saw (EL422H7-108 DET.-101) in motor
R spindle of yoke assembly <cré2sx31-1).

R EFFECTIVITY: ALL
R Page 202
OOTB Nov 15/86

Li _
P--'-'—-i-"""""""'" ""'e "‘ "'" "' = “R” '-

LOCKHEED
MAINTENANCE MANUAL

(d) Hith clamp spindle end of yoke hinged back, insert

pilot of tool into pilot hole of bushing on
opposite side of bearing flange.
(el with pilot engaged in bushing, close hinge of
clamp spindle end and lock with pin. Turn clamp
spindle until both pilots are inserted into
bushing and slack is taken up. Move yoke assembly
(Ct€%5X31-1) up tight against bushing to prevent
wo e.
(f) Turn on motor and adjust valve (on opposite end of
motor from spindle) to reach slower and more
cggtrggégble speed, using wrench (CL225X31-1,
$33233
ZQZZ D u- 0

R (g) Carefully cut away bearing flange and remove

R bearing.
R B. Installation
R (1) Verify wing fitting is clean and free of chips or other
R contamination.
R (2) Install new bearing as follows:
R (a) Insert bearing into wing skate angle aft fitting.
R (b) Insert bushing (EL422H?-108, DET.-201) into
R bearing, and using C-clamp, clamp bushing to skate
R angle aft fitting.
R (c) Install staking tool (EL325B15-166) in motor
R spindle of yoke assembly (CLZZSXZ1-1).
R (d) with clamp spindle end of yoke hinged back, insert
R pilot_of tool into pilot hole of bushing on
R opposite side of bearing flange.
(e) with pilot engaged in bushing, close hinge of
clamp spindle end and lock with pin. Turn clamp
spindle until both pilots are inserted into
bushing and slack is taken up. Move yoke assembly
(Cg€%5X31-1) up tight against bushing to prevent
wo e.
(fl Swage bearing until bearing flange has a minimum
diameter of 3.56 inch, or a feeler gage
penetration check passes close inspection (Ref.
$333933
Z323 Fig. 202).

R EFFECTIVITY: ALL
R Page 203
OO1B Nov 15/86

L
V“_—___
tocxueee ®
MAINTENANCE MANUAL

R NOTE: After installation any crack visible to

R the naked eye shalt be cause for rejection
R of bearing. _
R (3) On aircraft with engine installed,
R install drag strut aft bolt, washers and nut as
R described in 54-D0-03,401, Steps 4B(2)(a) through (h).
R (3) On aircraft with engine removed,
R install drag strut aft bolt, washers and nut as
R described in 54-OD-04,401 Steps 4C(1) through (8).
R (4) Reinstall fluid lines if disconnected.
R (5) Reinstall clamps, brackets etc. disconnected in Steps
R SA(2) and (3). y
R (6) with wrench on bolt heads to prevent turning, torque
R - drag strut inboard and outboard forward nuts to 1400 to
R 1500 pound—inches, and lubricate (Ref. 12-26-O2).
R (7) On aircraft with engine installed,
R CAUTION: VERIFY THAT NORKSTANDS AND EQUIPMENT IS CLEAR
R OF AIRCRAFT BEFORE REMOVING ENGINE SUPPORT.

R (a) Remove overhead crane support or equivalent

R support from engine.
R (b) Install engine cowling (Ref. 71-11—O1 and
R 71-11-O2).
R (c) Install panels 452/462 FR, 452/462 FL, 453/463 GR,
R 453/463 GL, 453 DR and 463 DL, 453/463B and
R 453/463C.
R (d) Remove workstands and platforms.
R (e) Lower aircraft and remove stabilizing jacks, as
R required (Ref. 7-11-O0).
R (f) Close applicable engine 1 or 3 circuit breakers.
R (g) Verify fuel shutoff and hydraulic shutoff valves
R are returned to open position.
R (7) On aircraft with engine removed,
R (a) Perform completion procedure ERef. 54-OD-04,401,
R Steps 4H(1) through (7)1.

R EFFECTIVITY: ALL
R Page 204
OO1B Nov 15/B6

ha- _
 -___.._........._......_.
LOCKHEED ®
MAINTENANCE MANUAL

CLAMP SPINDLE
CL225)(3I-I YOKE ASSEMBLY - IRIWD

HINGE PIN
AIR FMTOR
MOTOR SPINDLE
LOCK PIN

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R Bearing Removal/Installation
R Figure 201
E EFFECTIVITY: ALL §7'=43-01
Page 205
0018 Nov 15/86

ha. ___
‘

LOCl(HEEl) '
MAINTENANCE NANUAL
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FLIGHT SURFACES -- DESCRIPTION AND QPERATIOI!

I. General _
The flight control surraces (Ref. Fig. ll consist or slats,
spoilers, vanes, flaps and ailerons.
Seven slats are provided on the leading edge or each.wing. The
slats,_when retracted, rorm the tront pact le or the wing ahead
or the fixed leading edge structure. e tour outboard slats
only are provided w th an anti-icing system. The slats serve as
airtlow control devices during takeoff and landing.
Six aerodynamic spoilers are provided to assist roll control, to
serve as air brakes, and to spoil lift during and after landing.
The spoilers are located on t e upper surface of the wing above
the trailing edge flaps.
Four vane assemblies are located on each wing. A vane assembly
is mounted just ahead of each trailing edge landing rlap. The
vanes are supported by carriages operating in tracks mounted in
the torque boxes. Each vane s operated y linkages connecting
the tlap and vane. The vane serves to improve the aerodynamic
characteristics or the tlap.
I

Four rlap assemblies are located on each wing. Two rlaps

assemblies are mounted inboard and two are mounted outboard or
the inboard aileron. Each flap with its associated vane
assembly forms a double—slotted Fowler-type flap. Each flap
assembly is supported by rollers, linkages, and tracks on
full-depth ribs (torque boxes). The flaps are extended or
retracted by jackscrew assemblies. _
Two aileron assemblies are located on each wing. The outboard
aileron is mounted near the wingtip, and the inboard aileron is
mounted inboard of the two outboard flaps. The ailerons are
attached by hinge fittings to the wing rear spar. There are two
. hinges on each inboard aileron and four on each outboard
aileron.

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There are seven slotted slats (Ref. Figs 1 and 2) on each wing
leading edge. Three slats are located inboard of the engine
sup ort py on, and four slats_outboard of the pylog. The
outboard slats erg provided with a hot air anti—icing system. A
short length of fixed, unslatted leadinguedge structure is
located between the inner slat and the se age.
R Inboard slats are constructed of aluminum honeycomb sandwich or
R of sheet metal panels supported by machined—fos%ed ribs. The
outboard slats are of sheet metal and forged ri s.
Each inboard slat is approximately nine feet long and thirty
inches wide. The slat consists of oge outer and four inner
honeycomb surface panels. The four innes panels of each inboard
slat are removable. _Each outboard slat is approximately 13 feet
long and 24 isches uide. Each slat consists of three sections:
the nose section, center section,_and trailing edge. A front
and rear spar connects thess sections. Each outboard slat has
two snubbers, sn actuator rib,_two_tragk support ribs,
intermediate ribs, ago a hot air_distribution duct. Each slat
has_a_flexible seal interconnecting the ends of each slat. The
trailiqg edge of each slat consists of a nylon arrowhead
extrusion to pfevent chafing of the fixed eading edge structure
when the slat is stowed.

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SPOILERS - DESCRI in '-I .ll O ll: ‘-:-. 25U (D'5 E TION

I. General
Six spoiler assemblies (Ref. Fig. ll are mounted on the trailing
edge structure of the wing.
All spoiler panels are bonded aluminum honeycomb assemblies.
The bonded panel assemblies consist of aluminum sheet skins; a
full depth, contoured, aluminum honeycomb wedge; a channel front
beam; formed sheet end closure ribs which are flanged outward;
and an extruded metal channel trailing edge closure. The gaps
between spoilers that do not interface with fixed trailing edge
structure have flat strip seals attached to the spoiler side
edges to form a butt joint with the adjacent spoiler.

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FLAP wmes - DESCRIPTION AND orammon

l. General
Vane assemblies (Ref. Fig. I) are made of aluminum sheet metal.
The assemblies consist of:
Machined aluminum carriage support fittings at each end
A beam composed of T—caps
A web with lightening holes and stiffeners
An aluminum alloy extruded arrowhead trailing edge
Sheet metal skins with bonded doublers
Sheet metal former ribs
The upper and lower surface panels are attached with rivets.
The leading edge nose section is removable and is attached with
screws and nut plates. The leading edge is removable and
acgess to the aft section is achieved through holes ih the beam
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MAINTENANCE MANUAL

FLAPS - DESCRIPTION AND OPERATION

l. General
The flap (Ref. Fig. ll is of conventional aluminum alloy sheet
construction. Each flap has a forward and an aft beam
(consisting of T-caps, webs, and stiffeners); web and stiffener
ribs; air load ribs, (consisting of T-caps with extruded truss
members); an extruded panel support member near the nose;
machined aluminum track support fittings with supporting sheet
metal to form the flap end ribs; interchangeable titanium
tracks; sheet metal skins with bonded doublers; and
interchangeable trailing edge segments made from crushed
aluminum honeycomb core panels wrapped around the trailing edge
radius. _
Lower surface panels are attached with screws and nut plates for
access and inspection. The leading edge and upper surface
panels are permanently attached.

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MAINTENANCE MANUAL

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MAINTENANCE MANUAL

AILERON - DESCRIPTION AND OPERATION

1. General
The inboard aileron (Ref. Fig. 1 and 2) consists of a ueb and
cap front beam assembly; an extruded I—section rear beam; ribs
with stiffened sheet metal webs and extruded caps; truss-type
airload ribs; forged aluminum hinge and actuator_fittings;
webbed end closure ribs; molded fiber glass fairing end caps;
aluminum upper and lower skin panels; and a crushed aluminum
honeycomb core trailing edge wedge. The lower skin panels are
interchangeable and attached with flush screws. Aileron leading
edge shroud fairings are riveted to the aileron front beam. The
fairings are made of two layers of metal bonded together and
stabilized by formed sheet metal nose ribs. The outboard
aileron construction and attachment features are the same as
those described for the inboard aileron.
On aircraft 034, 035,
an Advanced Composite Aileron is used. This aileron uses
graphite epoxy tape and graphite epoxy fabric for the aileron
covers, ribs, and front spar. The forged aluminum hinge and
actuator fittings and aluminum sheet leading edge shroud are
basically the same as on the aluminum aileron. The trailing
edge wedge is fabricated from Kevlar material having a Nomex
core.
CR NOTE: The inboard ailerons installed on aircraft 31036 and
CR 31035 are constructed of advanced composite materials,
CR for the purpose of a service evaluation program in which
CR Lockheed (LCC) is participating under NASA sponsorship.
CR In the event of damage to a composite aileron, or
CR detection of any questionable condition, Engineering must
CR be contacted prior to further flight. Lockheed must also
CR ,subsequently be advised through their Resident Service
CR Manager at MCI. If visually detected damage requires NOT
CR verification, an ultrasonic procedure is contained in the
CR L10i1 NDT manual, part 4, chapter/section 57-55-00, pages
CR 1 thru 5.

EFFECTIVITY: ALL 57'-55-OI]

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ZONES 552/B52
IIADING EDII SHROUD
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MAINTENANCE MANUAL

a SACRIFICIAL A N omc PLATE - nrmowu. AND INSTALLATION

I. General '
Ihis procedure describes the removal and installation oi
sacriiicial anodic plates, located at the outboard trailing edge
of left and right outboard aileron trailing edge wedge, at HBL
(Hing butt line) 920.0 L or R (approx), in zones S72 and 672.
The sacrificial anodic plate is installed for the purpose ot
absorbing the damaging eifects associated with lightn ng strike
activity.

2. Referenced Procedure
LCP 77-I028 Chemical Film Protective Treatment, Clear,
Non-Immersion, for Clad Aluminum Alloys

3. Removal /Installa tion

A. Removal
(II Remove three tri-wing screws and remove plate.
B. Installation
NOTE: The sacrificial anodic Slates are made of 7075-T6
clad a1uminum.alloy, 0. 80 in. thick. They should be
bare on the outer surface and finished with a clear
chemical £i1m on the faying surface (Rat.
lCP77-I028). The plates are 4.82 in. long and 3.35
1n. wide. The aft edge corners should be rounded to
a 3.0-inch radius.
(I) install sacrificial anodic plate on outboard aileron
using three triuing screws.

EFFECTIVITY: ALL 57""'5 5""52

Page 40I/402
OOI Why IS/73