# Boeing Service Bulletin DC10-53-109: Boeing - Service Bulletin

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- Title as filed: Boeing - Service Bulletin
- Pages: 89
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## Text

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### Page 1

McDonnell DouglasCommercial 
Airplanes
DC10
Service Bulletin
Number: DC10-53-109
Original Issue: December 24, 1979
Revision 7: March 03, 2009
ATA System: 5350
SUBJECT: FUSELAGE - Aerodynamic Fairings - Install Electrical Bonding Straps on Extended
Wing-to-Fuselage Fillets
Export of this technology is controlled under the United States Export Administration Regulations (EAR) (15
CFR 730-774). An export license may be required before it is used for development, production or use by foreign
persons from specific countries. The controller of this data has the individual responsibility to abide by all export
laws.
9E991ECCN:
BOEING PROPRIETARY, CONFIDENTIAL, AND/OR TRADE SECRET
Copyright © 1989 The Boeing Company
Unpublished Work - All Rights Reserved
Boeing claims copyright in each page of this document only to the extent that the page contains copyrightable
subject matter. Boeing also claims copyright in this document as a compilation and/or collective work.
This document includes proprietary information owned by The Boeing Company and/or one or more third parties.
Treatment of the document and the information it contains is governed by contract with Boeing. For more
information, contact The Boeing Company, P .O. Box 3707, Seattle, Washington 98124.
Boeing, the Boeing signature, the Boeing symbol, 707, 717, 727, 737, 747, 757, 767, 777, 787, Dreamliner,
BBJ, DC-8, DC-9, DC-10, MD-10, MD-11, MD-80, MD-88, MD-90, P-8A, Poseidon and the Boeing livery are all
trademarks owned by The Boeing Company; and no trademark license is granted in connection with this document
unless provided in writing by Boeing.
BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
Original Issue: December 24, 1979
DC10-53-109Revision 7: March 03, 2009
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4.0

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Table of Contents
Revision Transmittal Sheet ............................................ 5
Summary ..................................................... 7
1. PLANNING INFORMATION ........................................ 1 1
A. Effectivity ............................................... 1 1
1. Airplanes ............................................ 1 1
2. Spares Affected ........................................ 1 3
B. Concurrent Requirements ...................................... 1 3
C. Reason ................................................ 1 4
D. Description .............................................. 1 4
E. Compliance .............................................. 1 6
F . Approval ............................................... 1 6
G. Manpower .............................................. 1 6
H. Weight and Balance Changes .................................... 1 7
I. Electrical Load Data ......................................... 1 7
J. References .............................................. 1 7
1. Existing Data: .......................................... 1 7
2. Data supplied with this Service Bulletin: ........................... 1 7
3. Installation Drawings Used in the Preparation of this Service Bulletin: ........... 1 8
4. Process Data: ......................................... 1 8
K. Publications Affected ......................................... 1 8
L. Interchangeability and Intermixability of Parts ........................... 1 8
2. MATERIAL INFORMATION ........................................ 1 9
A. Material - Price and Availability ................................... 1 9
B. Industry Support Information .................................... 1 9
C. Parts Necessary For Each Airplane ................................. 1 9
1. Kits/Parts: ............................................ 1 9
2. Parts and Materials Supplied by the Operator: ........................ 2 1
3. Parts Modified and Reidentified: ................................ 2 2
4. Parts Removed and Not Replaced: .............................. 2 2
D. Parts Necessary to Change Spares ................................. 2 2
E. Special Tooling - Price and Availability ............................... 2 2
F . Special Tooling Necessary to do this Service Bulletin ....................... 2 2
3. ACCOMPLISHMENT INSTRUCTIONS .................................. 2 3
A. GENERAL INFORMATION ..................................... 2 3
B. WORK INSTRUCTIONS ....................................... 2 4
FIGURE 1: EXTENDED WING TO FUSELAGE FILLETS - INSTALLATION OF BONDING STRAPS [Group
1-4, Configuration 1] ...................................... 2 7
FIGURE 2: EXTENDED WING TO FUSELAGE FILLETS - REPLACEMENT OF BONDING STRAPS [Group
3-4, Configuration 2] ...................................... 4 4
FIGURE 3: EXTENDED WING TO FUSELAGE FILLETS - REPLACEMENT OF BONDING STRAPS [Group
1-2, Configuration 2] ...................................... 6 6
FIGURE 4: EXTENDED WING TO FUSELAGE FILLETS - REPLACEMENT OF ONE BONDING STRAP
[Group 1-4, Configuration 3] .................................. 8 6
Appendix A: BONDING STRAP INSTALLATION PROCEDURE ...................... 8 9
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BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
Original Issue: December 24, 1979
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McDonnell DouglasCommercial 
Airplanes
DC10
Service Bulletin
Revision Transmittal SheetNumber: DC10-53-109Original Issue: December 24, 1979
Revision 7: March 03, 2009
ATA System: 5350
SUBJECT: FUSELAGE - Aerodynamic Fairings - Install Electrical Bonding Straps on Extended
Wing-to-Fuselage Fillets
This revision includes all pages of the service bulletin.
COMPLIANCE INFORMATION RELATED TO THIS REVISION
No more work is necessary on airplanes changed as shown on revision 5 and 6 of this service bulletin.
More work is necessary on airplanes changed as shown in original release through revision 4 of this service
bulletin. Measure electrical resistance of previously installed braided bonding straps. An additional 0.5 hours
required.
REASON FOR REVISION
This revision is sent to incorporate an electrical resistance check of previously installed braided bonding straps
and instructions to correct locations that fail the resistance check. An additional 0.5 hours required.
These sections were changed:
1. In Paragraph 1.D., Description, added instructions to measure electrical resistance of previously installed
braided bonding straps and correct any failed resistance checks.
2. In Paragraph 1.F ., Approval, added approval for Revision 7.
3. In Paragraph 1.G., Manpower, added hours for electrical resistance check of previously installed braided
bonding straps and correction of electrical bonds that failed.
4. In Paragraph 2.C.1., Kits/Parts, added angles to table previously omitted in error.
5. In Paragraph 3.B.2., Work Instructions, added electrical resistance test and correction of electrical bonds
that failed.
Vertical lines are put on the left edge of each page, except in Paragraph 1.A., Effectivity, to show the location
of important changes.
Pages with no vertical lines have no important changes.
REVISION HISTORY
December 24, 1979Original Issue:
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Original Issue: December 24, 1979
DC10-53-109Revision 7: March 03, 2009
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August 14, 1981Revision 1:
October 28, 1983Revision 2:
November 14, 1986Revision 3:
October 07, 1992Revision 4:
March 19, 2008Revision 5:
July 10, 2008Revision 6:
March 03, 2009Revision 7:
BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
Original Issue: December 24, 1979
DC10-53-109Revision 7: March 03, 2009
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McDonnell DouglasCommercial 
Airplanes
DC10
Service Bulletin
SummaryNumber: DC10-53-109Original Issue: December 24, 1979
Revision 7: March 03, 2009
ATA System: 5350
SUBJECT: FUSELAGE - Aerodynamic Fairings - Install Electrical Bonding Straps on Extended
Wing-to-Fuselage Fillets
CONCURRENT REQUIREMENTS
This service bulletin may be accomplished in conjunction with Service Bulletin DC10-53-103 or Service Bulletin
DC10-53-119 for convenience of maintenance.
BACKGROUND
An engineering review of the extended wing to fuselage fillet by Boeing revealed an increase in the non metallic
area of the fillet. In the event of a severe lightning strike, induced transients could be imposed on wiring in the
root area. Installation of the new bonding straps to electrically connect the metallic frame of the fillet to the metal
ribs of the wing leading edge will substantially reduce the induced electrical transients.
Service bulletin revision 5 is the result of the safety assessments conducted by Boeing under a Special Federal
Aviation Regulation (SFAR) 88, Fuel Tank System Fault Tolerance Evaluation Requirements.
ACTION
This service bulletin provides instructions to accomplish the following on the left and right wings:
1. Group 1-4, Configuration 1:
(Airplanes that have not Previously done Service Bulletin DC10-53-109)
Install six braided bonding straps between the metallic frame of the fillet and the wing leading edge ribs.
2. Group 1-2, Configuration 2:
(Airplanes that have Previously done Service Bulletin DC10-53-109 Revision 3 or a Prior Revision)
Remove and replace six metal bonding straps with six new braided bonding straps between the metallic
frame of the fillet and the wing leading edge ribs.
3. Group 3-4, Configuration 2:
(Airplanes that have Previously done Service Bulletin DC10-53-109 Revision 3 or a Prior Revision or metal
bonding straps were installed in production)
Remove and replace six metal bonding straps with six new braided bonding straps between the metallic
frame of the fillet and the wing leading edge ribs installed in production.
4. Group 1-4, Configuration 3:
(Airplanes that have Previously done Service Bulletin DC10-53-109 Revision 4)
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Original Issue: December 24, 1979
DC10-53-109Revision 7: March 03, 2009
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Replaces one existing braided bonding strap with one new longer braided bonding strap between the metallic
frame of the fillet and the wing leading edge ribs. Measures electrical resistance of previously installed
braided bonding straps and if resistance check fails, removes braided bonding strap assembly, cleans
mating surfaces, installs bonding strap assembly and measures resistance.
EFFECTIVITY
DC-10 and MD-10 airplanes with extended wing to fuselage fillets. Refer to Paragraph 1.A.1., Airplanes for the
list of affected airplanes.
COMPLIANCE
Boeing recommends that operators do this service bulletin at the earliest scheduled maintenance period.
Federal Aviation Administration (FAA) Airworthiness Directive (AD) 2006-16-03 is related to this service bulletin.
INDUSTRY SUPPORT INFORMATION
Boeing warranty remedies are not available for the configuration changes given in this service bulletin.
MANPOWER
Group 1-4, Configuration 1
Elapsed HoursTotal Task HoursAirplanes
6.613.3DC-10 and MD-10
Group 1-4, Configuration 2
Elapsed HoursTotal Task HoursAirplanes
9.118.2DC-10 and MD-10
Group 1-4, Configuration 3
Elapsed HoursTotal Task HoursAirplanes
5.5 - 9.510.5 - 18.5DC-10 and MD-10
MATERIAL INFORMATION
Boeing Supplied Kits/Parts.
Refer to Paragraph 2.A., Material - Price and Availability.
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BOEING SERVICE BULLETIN DC10-53-109
GROUPS 1-4, CONFIG 1
INSTALL SIX NEW BRAIDED BONDING STRAPS
GROUPS 1-4, CONFIG 2
REPLACE SIX METAL BONDING STRAPS WITH SIX
BRAIDED BONDING STRAPS
GROUPS 1-4, CONFIG 3
REPLACE ONE EXISTING BRAIDED BONDING STRAP
WITH ONE NEW LONGER BRAIDED BONDING STRAP
LEFT SIDE SHOWN
RIGHT SIDE OPPOSITE
Original Issue: December 24, 1979
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BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
Original Issue: December 24, 1979
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McDonnell DouglasCommercial 
Airplanes
DC10
Service Bulletin
Number: DC10-53-109
Original Issue: December 24, 1979
Revision 7: March 03, 2009
ATA System: 5350
SUBJECT: FUSELAGE - Aerodynamic Fairings - Install Electrical Bonding Straps on Extended
Wing-to-Fuselage Fillets
1.    PLANNING INFORMATION
A. Effectivity
1. Airplanes
This service bulletin is for the airplanes shown below.
NOTE: This service bulletin is applicable only to airplanes with extended wing-to-fuselage fillets.
DESCRIPTIONCONFIGURATIONGROUP
Airplane fuselage numbers 268, 277, 280 through 282, 289, 295
through 298, 423 through 446.
-1
Airplanes that have not previously accomplished Service Bulletin
DC10-53-109. Install six new braided bonding straps.
1
Airplanes that have previously accomplished Service Bulletin
DC10-53-109 at Revision 3 or a prior revision. Replace six metal
bonding straps with six braided bonding straps.
2
Airplanes that have previously accomplished Service Bulletin
DC10-53-109 Revision 4. Replace one existing braided bonding strap
with one new longer braided bonding strap.
3
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DESCRIPTIONCONFIGURATIONGROUP
Airplane fuselage number 300 only.-2
Airplanes that have not previously accomplished Service Bulletin
DC10-53-109. Install six new braided bonding straps.
1
Airplanes that have previously accomplished Service Bulletin
DC10-53-109 at Revision 3 or a prior revision. Replace six metal
bonding straps with six braided bonding straps.
2
Airplanes that have previously accomplished Service Bulletin
DC10-53-109 Revision 4. Replace one existing braided bonding strap
with one new longer braided bonding strap.
3
Airplane fuselage numbers 260 through 299 excluding 268, 277, 280
through 282, 289 and 295 through 298.
-3
Airplanes that have not previously accomplished Service Bulletin
DC10-53-109. Install six new braided bonding straps.
1
Airplanes that have previously accomplished Service Bulletin
DC10-53-109 at Revision 3 or a prior revision or metal bonding straps
were installed in production. Replace six metal bonding straps with
six braided bonding straps.
2
Airplanes that have previously accomplished Service Bulletin
DC10-53-109 Revision 4. Replace one existing braided bonding strap
with one new longer braided bonding strap.
3
Airplane fuselage numbers 301 through 422.-4
Airplanes that have not previously accomplished Service Bulletin
DC10-53-109. Install six new braided bonding straps.
1
Airplanes that have previously accomplished Service Bulletin
DC10-53-109 at Revision 3 or a prior revision or metal bonding straps
were installed in production. Replace six metal bonding straps with
six braided bonding straps.
2
Airplanes that have previously accomplished Service Bulletin
DC10-53-109 Revision 4. Replace one existing braided bonding strap
with one new longer braided bonding strap.
3
Airplane Models:
DC-10-10, DC-10-15, DC-10-30, DC-10-30F , DC-10-30F (KC-10A), DC-10-40, DC-10-40F ,
MD-10-10F , MD-10-30F
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GroupFuselage Num-
ber
3260 - 261
3263
1268
3275
1277
1280 - 282
3284
3286
1289
3291 - 293
1295 - 298
3299
2300
4301 - 315
4317 - 319
4321 - 326
4328 - 336
4338 - 353
4355 - 422
1423 - 446
2. Spares Affected
Examine your spares supply for the parts or components identified in Paragraph 2.C., Parts
Necessary for Each Airplane. If any parts or components are found, refer to Paragraph 2.C for the
recommended use.
B. Concurrent Requirements
This service bulletin may be accomplished in conjunction with Service Bulletin DC10-53-103 or Service
Bulletin DC10-53-119 for convenience of maintenance.
BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
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C. Reason
An engineering review of the extended wing to fuselage fillet by Boeing revealed an increase in the
non metallic area of the fillet. In the event of a severe lightning strike, induced transients could be
imposed on wiring in the root area. Installation of the new bonding straps to electrically connect the
metallic frame of the fillet to the metal ribs of the wing leading edge will substantially reduce the induced
electrical transients.
Revision 4 was issued to introduce the replacement of bonding straps with new improved bonding
straps that are less susceptible to cracking and the addition of 24 airplanes to the existing effectivity.
Revision 5 was sent to incorporate engineering released subsequent to Revision 4 of this service
bulletin, which replaces an existing braided bonding strap with a new longer braided bonding strap that
is less susceptible to chafing structure.
Revision 6 was sent to incorporate an optional method of installing the strap assembly in Figure 4 and
correct part number errors in Figure 1 table. The data given in Information Notice DC10-53-109 IN 02
dated April 23, 2008 is included in this revision.
Revision 7 is sent to incorporate an electrical resistance check of previously installed braided bonding
straps and instructions to correct locations that fail the resistance check. An additional 0.5 hours
required.
Service bulletin revision 5 is the result of the safety assessments conducted by Boeing under a Special
Federal Aviation Regulation (SFAR) 88, Fuel Tank System Fault Tolerance Evaluation Requirements.
D. Description
This service bulletin provides instructions to accomplish the following on the left and right wings:
1. Group 1-4, Configuration 1:
(Airplanes that have not Previously done Service Bulletin DC10-53-109)
Installs six braided bonding straps between the metallic frame of the fillet and the wing leading
edge ribs.
2. Group 1-2, Configuration 2:
(Airplanes that have Previously done Service Bulletin DC10-53-109 Revision 3 or a Prior Revision)
Replaces six metal bonding straps with six new braided bonding straps between the metallic frame
of the fillet and the wing leading edge ribs.
3. Group 3-4, Configuration 2:
(Airplanes that have Previously done Service Bulletin DC10-53-109 Revision 3 or a Prior Revision
or metal bonding straps were installed in production)
Replaces six metal bonding straps with six new braided bonding straps between the metallic frame
of the fillet and the wing leading edge ribs installed in production.
4. Group 1-4, Configuration 3:
(Airplanes that have Previously done Service Bulletin DC10-53-109 Revision 4)
BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
Original Issue: December 24, 1979
DC10-53-109Revision 7: March 03, 2009
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Replaces one existing braided bonding strap with one new longer braided bonding strap between
the metallic frame of the fillet and the wing leading edge ribs. Measures electrical resistance of
previously installed braided bonding straps and if resistance check fails, removes braided bonding
strap assembly, cleans mating surfaces, installs bonding strap assembly and measures resistance.
Revision 7 - No more work is necessary on airplanes changed as shown on revision 5 and 6 of this
service bulletin.
More work is necessary on airplanes changed as shown in original release through revision 4 of this
service bulletin. Measure electrical resistance of previously installed braided bonding straps. An
additional 0.5 hours required.
The work in this service bulletin is done in the maintenance zone(s) given below.
Group 1:
Affected Maintenance Zones
ZoneModel
131, 132, 161, 162DC-10-10, DC-10-30, DC-10-
30F , DC-10-30F (KC-10A), MD-
10-10F , MD-10-30F
Group 2:
Affected Maintenance Zones
ZoneModel
131, 132, 161, 162DC-10-30
Group 3:
Affected Maintenance Zones
ZoneModel
131, 132, 161, 162DC-10-30, DC-10-30F
Group 4:
Affected Maintenance Zones
ZoneModel
131, 132, 161, 162DC-10-10, DC-10-15, DC-10-30,
DC-10-30F , DC-10-30F (KC-
10A), DC-10-40, DC-10-40F ,
MD-10-10F , MD-10-30F
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E. Compliance
Boeing recommends that operators do this service bulletin at the earliest scheduled maintenance
period.
Federal Aviation Administration (FAA) Airworthiness Directive (AD) 2006-16-03 and AD Notice of
Proposed Rulemaking (NPRM) 2007-NM-226-AD is related to this service bulletin.
F. Approval
The resultant modification described in Paragraph 1.D has been shown to comply with the applicable
Federal Aviation Regulations, and Revision 7 is approved by the Manager, Los Angeles Aircraft
Certification Office, FAA Northwest Mountain Region, and is approved as an alternative method of
compliance with Paragraphs (f) and (h) of Airworthiness Directive No. 2006-16-03.
G. Manpower
The table below shows an estimate of the task hours necessary to do this change for each airplane.
This estimate is for direct labor only, done by an experienced crew. Adjust the estimate with operator
task hour data if necessary. The estimate does not include lost time. These are some examples of lost
time:
— Time to adjust to the workplace
— Time to schedule the work
— Time to examine the work
— Time to cure the materials
— Time to make the parts
— Time to find the tools.
Group 1-4, Configuration 1:
Elapsed
Hours
Task HoursNumber of PersonsTask
1.83.62Open Access
2.44.92Install Six Braided Bonding Straps
2.44.82Close Access
6.613.3TOTAL FOR EACH AIRPLANE
Group 1-4, Configuration 2:
Elapsed
Hours
Task HoursNumber of PersonsTask
1.83.62Open Access
4.99.82Remove/Install Six Bonding Straps
2.44.82Close Access
9.118.2TOTAL FOR EACH AIRPLANE
BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
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Group 1-4, Configuration 3:
Elapsed
Hours
Task HoursNumber of PersonsTask
1.83.62Open Access
0.81.62Replace One Bonding Strap
0.50.51Do Electrical Resistance Check to Five Previous-
ly Installed Braided Bonding Straps
4.08.02Remove/Clean/Install Braided Bonding Straps
that Failed Resistance Check
(a)
2.44.82Close Access
5.5 - 9.510.5 - 18.5TOTAL FOR EACH AIRPLANE
(a) Hours are a maximum.
H. Weight and Balance Changes
Weight and balances changes affected by incorporation of this service bulletin are contingent upon the
modification of each particular airplane. Weight data to be computed by the operator by weighing parts
removed and parts installed during modification. Necessary revisions should be made to the appropriate
airplane weight and balance report.
I. Electrical Load Data
Not changed.
J. References
1. Existing Data:
a. Standard Wiring Practices Manual (SWPM) 20-50-01.
b. DC-10 Aircraft Maintenance Manual (AMM) 06-35-00and 06-36-00.
c. DC10 Structural Repair Manual (SRM) 51-31-01, 51-32-01, 51-33-01and 51-35-01.
2. Data supplied with this Service Bulletin:
No data is supplied with this service bulletin. To obtain the data necessary to support this service
bulletin submit a data request to:
Data and Services Management
MS D800-0019
3855 Lakewood Boulevard
Long Beach, California 90846
Phone: (562) 593-6996
Fax: (562) 593-2001
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E-mail: dse.boecom@boeing.com
a. Drawings:
ADCNDCN/REVSheetTitleDrawing No
-CDWGWing Root Bonding InstallationSR10530059
3. Installation Drawings Used in the Preparation of this Service Bulletin:
ChangeTitleDocument Number
HStrap Installation - Electrical BondingANB7547
ALRib InstallationARB7127
DBonding Strap InstallationWZZ7573
These drawings were used to prepare this service bulletin. These drawings are not necessary to
make the specified changes, and are not supplied with this service bulletin. These drawings may
not be applicable to all airplane configurations or operators.
4. Process Data:
Douglas Process Specifications referred to on the drawings are not given in this service bulletin
since these procedures are frequently used as standard shop practices.
K. Publications Affected
Chapter-SectionPublication
53-53Illustrated Parts Catalog
L. Interchangeability and Intermixability of Parts
Accomplishment of this service bulletin does not affect interchangeability or intermixability of parts.
BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
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2.    MATERIAL INFORMATION
A. Material - Price and Availability
The operator can supply the parts and materials shown in Paragraph 2.C., Parts Necessary For Each
Airplane. As an alternative, operators can purchase the parts from Boeing Spares.This service bulletin
does not show the Boeing price and supply data.
Reference this service bulletin and submit your purchase order by one of the methods that
follow:
1. Order on-line via ATA Spec 2000 or Boeing Part Page.
2. Fax to (206) 662-7145.
3. Spares Customer Support - MC 36-65
Boeing Spares Department
P .O. Box 3707
Seattle, Washington 98124-2207 USA
B. Industry Support Information
Boeing warranty remedies are not available for the configuration changes given in this service bulletin.
C. Parts Necessary For Each Airplane
1. Kits/Parts:
NOTE: Part numbers in parentheses are prior identification numbers and are equivalent to
SB10530109 part numbers.
NotesExisting Part NumberNameQTYNew Part Number
--PIN56HL328-5-3
--NUT56MS21042L08
--WASHER56NAS1149FN816P
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NotesExisting Part NumberNameQTYNew Part Number
(a) (b) (c) (d)SB10530109-29/-30STRAP ASSEM-
BL Y
4SR10530059-13
or
(ANB7547-41/-42)
SB10530109-8/-9
(ANB7547-27N/-28N)
or
ANB7547-17/-18
or
ANB7547-27/-28
or
WZZ7573-7/-8
or
WZZ7573-13/-14
(a) (b) (c) (d)SB10530109-31/-32/-33/-34STRAP ASSEM-
BL Y
4SR10530059-15
or
(ANB7549-43/-44/-45/-46)
SB10530109-11/-12/-13/-14
(ANB7547-29N/-30N/-31N/-32N)
or
ANB7547-9/-10/-11/-12
or
ANB7547-29/-30/-31/-32
or
WZZ7573-5/-6/-7/-8
(a) (b) (c) (d)SR10530059-21STRAP ASSEM-
BL Y
2SR10530059-27
or
SB10530109-43/-44
or
SB10530109-23/-24 (WZZ7573-
15N/-16N)
or
ANB7547-25/-26
or
WZZ7573-9/-10
or
WZZ7573-15/-16
(a) (b) (c) (d)SB10530109-25/-26/-27/-28STRAP ASSEM-
BL Y
4SR10530059-3
or
(ANB7547-33/-34/-35/-36)
SB10530109-5/-6/-7/-8 (ANB7547-
19N/-20N/-21N/-22N
or
ANB7547-19/-20/-21/-22
or
ANB7547-3/-4/-5/-6
--Angle2SB10530109-35
--Angle2SB10530109-37
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BOEING SERVICE BULLETIN DC10-53-109

### Page 21

NotesExisting Part NumberNameQTYNew Part Number
--Angle2SB10530109-39
--Angle2SB10530109-41
(a) Discard the existing part.
(b) This part is used in production.
(c) Y ou cannot use the existing part to replace the new or changed part
(d) At operator's option - Bonding straps may be fabricated from NEQL48830 overbraid per Service
Rework Drawing SR10530059.
CAGECooner Manufacturer CompanyNEQL48830 overbraid may be pur-
chased from: 637949186 Independence Avenue
Chatsworth, California 91311-5902
2. Parts and Materials Supplied by the Operator:
NotesNameGroup 1, 2, 3, 4Part Number / Specification
QTY
(a)Rivet136NAS1738B4-2
(a)Rivet100NAS1738E4-2
(a)Rivet100NAS1739E4-2
(b)Sealant, Polysulfide, Aluminized8 Oz.AC-632, B-2
(DMS 1819 B-1/2)
or
Equivalent
(c)Chemical Conversion Coating1 Oz.Alodine 1200S
(c)Primer, Fluid Resistant1 Oz.Koropon 515-700 with Catalyst
910-704 (DMS 1786)
or
Equivalent
(c)Sealant8 Oz.PR-1422 B-2 (DMS 2082)
or
Equivalent
CAGEHi-Shear Corporation(a) May be obtained from:
731972600 Skypark Drive
Torrance, California 90505
1DWR5Advanced Chemistry and Technology, Incorporated(b) May be obtained from:
7341 Anaconda Avenue
Garden Grove, California 92841-2921
92108PRC-DeSoto International, Incorporated(c) May be obtained from:
5454 Fernando Road
Glendale, California 91203
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### Page 22

3. Parts Modified and Reidentified:
None.
4. Parts Removed and Not Replaced:
NotesQTYNameExisting Part
Number
(a)2FillerANB7547-15
(a) Keep the part if there are other uses for it.
D. Parts Necessary to Change Spares
None.
E. Special Tooling - Price and Availability
None.
F. Special Tooling Necessary to do this Service Bulletin
No special tools or equipment are necessary to do the change in this service bulletin. But, maintenance
and overhaul tools in the manuals given in Paragraph 1.J., References, can be necessary. Examine
operator tool supply to make sure all necessary tools are available.
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### Page 23

3.    ACCOMPLISHMENT INSTRUCTIONS
A. GENERAL INFORMATION
WARNING: IF ELECTRICAL POWER IS APPLIED TO THE AIRPLANE, MAKE SURE YOU OBEY
ALL PRECAUTIONS WHILE YOU DO WORK. IF YOU DO NOT OBEY THE
PRECAUTIONS, DEATH OR INJURY TO PERSONS, AND DAMAGE TO THE AIRPLANE
CAN OCCUR.
CAUTION: KEEP THE WORK AREA, WIRES AND ELECTRICAL BUNDLES CLEAN OF METAL
PARTICLES OR CONTAMINATION WHEN YOU USE TOOLS. UNWANTED MATERIAL,
METAL PARTICLES OR CONTAMINATION CAUGHT IN WIRE BUNDLES CAN CAUSE
DAMAGE TO THE BUNDLES. DAMAGED WIRE BUNDLES CAN CAUSE SPARKS OR
OTHER ELECTRICAL DAMAGE.
CAUTION: ELECTRICALL Y GROUND THE AIRPLANE. THIS WILL HELP TO PREVENT DAMAGE
TO THE AIRPLANE OR EQUIPMENT.
NOTE: 1. Manual titles are referred to by acronyms. Refer to Paragraph 1.J., References, for
definition of the acronyms.
2. For approved fastener and process material substitutions, refer to DC-10 Structural
Repair Manual, Chapter 51.
3. If the length of fasteners specified in this service bulletin do not meet the installation
standards, fasteners of the same specification, or an approved substitute, one grip
length longer or shorter may be used.
4. Refer to the DC-10 SRM chapters for applicable operations as follows:
SubjectChapter
Installation of Screws, Bolts, and WashersDC10 SRM 51-31-01
Installation of LockboltsDC10 SRM 51-32-01
Installation of Hi-LoksDC10 SRM 51-33-01
Installation of RivetsDC10 SRM 51-35-01
5. A 1/8-inch thick stack of the same type washers called for in this service bulletin is
the maximum thickness which may be used under fastener head or nut to counteract
accumulation of tolerances.
EXCEPTION: When the available fastener length increments are greater than
1/16-inch, a 3/16-inch thick stack of the same type washers may be used.
6. Obey all of the warnings and cautions given in the specified manual sections.
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### Page 24

7. These work instructions refer to procedures included on other Boeing documents.
When the words "refer to" are used and the operator has an accepted alternative
procedure, the accepted alternative procedure can be used. When the words "as
given in" are included in the instruction, the procedure in the Boeing document must
be used.
8. At operator's option fabricate bonding straps as shown on Service Rework Drawing
SR10530059.
9. Install bonding strap brackets in the location as shown. Locations of brackets to be
determined on the airplane by the operator. Pick up on existing fastener locations
as applicable. Note: Grounding strap cannot be tight, no wire strain is permitted.
10. Fill open holes as required using NAS1738B4-(x) type blind rivets.
B. WORK INSTRUCTIONS
1. Remove and retain inboard wing leading edge access panels 515AB and 515BB left side and
panels 615AB and 615BB right side. Refer to DC-10 AMM 06-35-00 and DC-10 AMM 06-36-00.
2. Install electrical braided bonding straps on the left and right wings as follows:
Group 1-4, Configuration 1:
(Airplanes that have not previously done Service Bulletin DC10-53-109)
a. Open the left side door assembly ANB7489-1 and right side door assembly ANB7489-2 as
given in Figure 1.
b. Install six new braided bonding straps between the metallic frame of the fillet and the wing
leading edge ribs as given in Figure 1.
NOTE: All strap locations are approximate. No attempt to exactly verify the location per the
figures should be made. For these installations, the location of the strap is acceptable
under the following conditions:
1. Each end of the strap is located on the correct part or assembly and is
installed picking up on any existing holes as identified in Figure 1.
2. All strap fastener hole edge distances are at least 2D from any edge, joggle
or detail such as a lightening hole of the structure to which it is attached.
3. There is enough slack in the strap that when installed there is no chance
that the strap will be pulled tight in flight.
c. Close left side door assembly ANB7489-1 and right side door assembly ANB7489-2 as given
in Figure 1.
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### Page 25

Group 1-2, Configuration 2:
(Airplanes that have Previously done Service Bulletin DC10-53-109 Revision 3 or a Prior
Revision)
a. Open the left side door assembly ANB7489-1 and right side door assembly ANB7489-2 as
given in Figure 3.
b. Replace the six bonding straps between the metallic frame of the fillet and the wing leading
edge ribs as given in Figure 3.
c. Close left side door assembly ANB7489-1 and right side door assembly ANB7489-2 as given
in Figure 3.
Group 3-4, Configuration 2:
(Airplanes that have Previously done Service Bulletin DC10-53-109 Revision 3 or a Prior
Revision or Metal Bonding Straps were Installed in Production)
a. Open the left side door assembly ANB7489-1 and right side door assembly ANB7489-2 as
given in Figure 2.
b. Replace six bonding straps between the metallic frame of the fillet and the wing leading edge
ribs as given in Figure 2.
c. Close left side door assembly ANB7489-1 and right side door assembly ANB7489-2 as given
in Figure 2.
Group 1-4, Configuration 3:
(Airplanes that have Previously done Service Bulletin DC10-53-109 Revision 4)
a. Open the left side door assembly ANB7489-1 and right side door assembly ANB7489-2 as
given in Figure 4.
b. Replace bonding strap between the metallic frame of the fillet and the wing leading edge ribs
as given in Figure 4.
c. Measure electrical resistance across each bonding joint of the five previously installed braided
strap assemblies in accordance with SWPM 20-50-01, Paragraph 3.A. Verify brackets have
an acceptable fillet seal. Based on results do as follows:
Electrical Resistance Test fails or Brackets having Damaged or Missing Fillet Seal
(1) Remove braided bonding strap assembly.
(2) Clean and install braided bonding strap assembly in accordance with Appendix A.
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BOEING SERVICE BULLETIN DC10-53-109

### Page 26

Electrical Resistance Test Passes and Brackets have Acceptable Fillet Seal
(1) No further work required.
d. Close left side door assembly ANB7489-1 and right side door assembly ANB7489-2 as given
in Figure 4.
3. Install left side access panels 515AB, 515 BB left side and right side access panels 615AB, 615BB.
Refer to DC-10 AMM 06-35-00and DC-10 AMM 06-36-00.
4. Put the airplane back to a serviceable condition.
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### Page 27 (OCR)

BOEING SERVICE BULLETIN DC10-53-109
This Figure applies only to: Group 1-4, Configuration 1.
LEFT SIDE SHOWN
200  RIGHT SIDE OPPOSITE
STA  STA  STA  STA
Y=1079.000  Y=1099.000  Y=1119.000  Y=1139.000  161 62 63
ANB7483-1 (LS)
STA  ANB7483-2 (RS)
Z=-20.000  FILLET ASSY (REF)
(SHEET  5)E-→  L (SHEET 11)
J(SHEET 9)
STA
Z=-40.000
STA  → GISHEET.  7)
Z=-45.000
D
(SHEET 4
164)  ANB7489-1  (LS)
STA  ANB7489-2 (RS)
Z=-60.000  DOOR ASSY (REF)
B
STA
Z=-80.000
(SHEET 3) CH  -B (SHEET 2)
FWD <  VIEW A-A  U54443
FIGURE 1: EXTENDED WING TO FUSELAGE FILLETS - INSTALLATION OF BONDING STRAPS
(SHEET 1 OF 17)
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### Page 28 (OCR)

BOEING SERVICE BULLETIN DC10-53-109
•ARB7127-3 (LS)
ARB7127-4 (RS)
FORMER (REF)
STA
Y=1139.000  0.80 IN.
0.50 IN.
40
(6)
2.32 IN.
STA
Z=-70.000
-0.44 IN.
ANB7488-3 (LS)
ANB7488-4 (RS)
RIB (REF)
0.50 IN.
OUTBD‹  ›FWD
VIEW B-B
STA
LOOKING FORWARD  Y=1139.00
FIGURE 1: EXTENDED WING TO FUSELAGE FILLETS - INSTALLATION OF BONDING STRAPS
(SHEET 2 OF 17)
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### Page 29 (OCR)

BOEING SERVICE BULLETIN DC10-53-109
- ARB7127-3 (LS)
STA
ARB7127-4 (RS)
Y=1119.000  FORMER (REF)
- 0.50 IN.
- 0.80 IN.
(2 PLACES)
(10)12
STA
Z=-60.000
STA
X=120.000
2.82 IN.
(10
811
0.44 IN.
ANB7487-3 (LS)
ANB7487-4 (RS)
RIB (REF)
STA
(2 PLACES)  Z=-70.000
OUTBO FWD  -0.50 IN.
VIEW C-C
LOOKING FORWARD  STA
Y=1119.000
FIGURE 1: EXTENDED WING TO FUSELAGE FILLETS - INSTALLATION OF BONDING STRAPS
(SHEET 3 OF 17)
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### Page 30 (OCR)

BOEING SERVICE BULLETIN DC10-53-109
EDGE OF
ANB7485-3 WEB
STA -
Z=-45.720
ARB7127-45 (LS)
ARB7127-46 (RS)
FORMER (REF)
UP  1.85 IN.
→FWD
LOOKING OUTBOARD  0.88 IN.
0.38 IN.
(TYP)
0.40 IN.
(18,21
0.50 IN.
(20,  122  0.40 IN.
SEE
STA
ANB7485-9 (LS)  Y=1089.000
ANB7485-10 (RS)
STIFFENER (REF)
ANB7485-3  0.50 IN.
WEB (REF)
STA  20  OUTBD<  > FWD
X=120.000  19  121  VIEW D-D
LOOKING FORWARD
STA  STA
Z=-45.720  Y=1099.000
FIGURE 1: EXTENDED WING TO FUSELAGE FILLETS - INSTALLATION OF BONDING STRAPS
(SHEET 4 OF 17)
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### Page 31 (OCR)

BOEING SERVICE BULLETIN DC10-53-109
ANB7484-7 (LS)
ANB7484-8 (RS)
STIFFENER (REF)
(2 PLACES)
STA  31
Y=1099.000  STA
Z=-36.000
0.50 IN.  30 32
(29 31
(2 PLACES)
0.50 IN.
0.40 IN.
0.40 IN.
(28) 31)  (SHEET 6)
ANB7484-3 (LS)
ANB7484-4 (RS)  (30 32)  ARB7127-45 (LS)
RIB (REF)  ARB7127-46 (RS)
STA  (24) 26 27)  FORMER (REF)
Z=-40.000
VIEW E-E
GROUPS 1, 3  AFT OUTBD
LOOKING AFT
U55984
FIGURE 1: EXTENDED WING TO FUSELAGE FILLETS - INSTALLATION OF BONDING STRAPS
(SHEET 5 OF 17)
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### Page 32 (OCR)

BOEING SERVICE BULLETIN DC10-53-109
STA
Y=1099.000
24 26 27
(4 PLACES)
2.08 IN.
CONSTANT
25) 27
(4 PLACES)
PERPENDICULAR
TO Z-AXIS
-3 EQUAL→  0.31 IN.
0.38 IN.  SPACES  (TYP)
•ARB7127-45 (LS)
ARB7127-46 (RS)
FORMER (REF)
VIEW F-F
GROUPS 1, 3
LOOKING OUTBOARD
U56271
FIGURE 1: EXTENDED WING TO FUSELAGE FILLETS - INSTALLATION OF BONDING STRAPS
(SHEET 6 OF 17)
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### Page 33 (OCR)

BOEING SERVICE BULLETIN DC10-53-109
ANB7484-25 (LS)
ANB7484-26 (RS)  (2 PLACES)
RIB (REF)\  33) 39 41  40 42
- 0.50 IN.
(2 PLACES)
• STA
Z=-30.000
0.40 IN.  0.50 IN.
(SHEET 8)  0.40 IN.
STA  40
Z=-36.995
STA
Z=-40.000
ARB7127-45 (LS)  OUTBD SE  FWD
ARB7127-46 (RS)
FORMER (REF)
VIEW G-G
GROUPS 2, 4
LOOKING FORWARD  U56275
FIGURE 1: EXTENDED WING TO FUSELAGE FILLETS - INSTALLATION OF BONDING STRAPS
(SHEET 7 OF 17)
Original Issue: December 24, 1979
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### Page 34 (OCR)

BOEING SERVICE BULLETIN DC10-53-109
STA
Y=1099.000
54 36 37
2.17 IN.
CONSTANT
35 37
(4 PLACES)
-3 EQUAL→  0.31 IN.
0.38 IN.  SPACES  (TYP)
•ARB7127-45 (LS)
ARB7127-46 (RS)
FORMER (REF)
VIEW H-H
GROUPS 2, 4
LOOKING OUTBOARD
U56276
FIGURE 1: EXTENDED WING TO FUSELAGE FILLETS - INSTALLATION OF BONDING STRAPS
(SHEET 8 OF 17)
Original Issue: December 24, 1979
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### Page 35 (OCR)

BOEING SERVICE BULLETIN DC10-53-109
• STA
Z=-20.000
X50
0.50 IN.
RADIUS
48/50
O
STA
0.40 IN.  2.55 IN.  Y=1119.000
ANB7 482-3  (LS)
ANB7482-4  (RS)
RIB (REF)
47 50
(SHEET  {10>
ARB7127-45 (LS)
0.50 IN.-  ARB7127-46 (RS)  FORMER (REF)
(49 51)
• STA
Z=-30.000
STA
Y=1119.000
VIEW J-J  OUTBD FWD
LOOKING UP AND FORWARD  U56871
FIGURE 1: EXTENDED WING TO FUSELAGE FILLETS - INSTALLATION OF BONDING STRAPS
(SHEET 9 OF 17)
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### Page 36 (OCR)

BOEING SERVICE BULLETIN DC10-53-109
43 45 46
Y=1119.000
2.30 IN.
CONSTANT
0.38 IN.-  - 3 EQUAL
(TYP)  SPACES
(44) 46)
(4 PLACES)
ARB7127-45 (LS)
ARB7127-46 (RS)
FORMER (REF)
VIEW K-K
LOOKING OUTBOARD
U56877
FIGURE 1: EXTENDED WING TO FUSELAGE FILLETS - INSTALLATION OF BONDING STRAPS
(SHEET 10 OF 17)
Original Issue: December 24, 1979
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### Page 37 (OCR)

BOEING SERVICE BULLETIN DC10-53-109
STA
Y=120.000
X59
0.50 IN
RADIUS
58
57) 59
0.40 IN.
STA
Y=1139.000
ANB7485-4 (LS)
ANB7485-6 (RS)
56 59)  RIB (REF)
(SHEET  12)
ARB7127-45 (LS)
0.50 IN.-  ARB7127-46 (RS)
FORMER (REF)
(58 60)
55)
• STA
Z=-30.000
Y=1139.000  STA  OUTBD FWD
VIEW L-L
LOOKING UP AND FORWARD
U57489
FIGURE 1: EXTENDED WING TO FUSELAGE FILLETS - INSTALLATION OF BONDING STRAPS
(SHEET 11 OF 17)
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### Page 38 (OCR)

BOEING SERVICE BULLETIN DC10-53-109
STA
Y=1139.000
0.38 IN.  - 3 EQUAL -
(TYP)  SPACES
(53) 55)  2.30 IN.
(4 PLACES)  CONSTANT
52)54 55
-ARB7127-45 (LS)
ARB7127-46 (RS)
FORMER (REF)
VIEW M-M
LOOKING OUTBOARD
U57491
FIGURE 1: EXTENDED WING TO FUSELAGE FILLETS - INSTALLATION OF BONDING STRAPS
(SHEET 12 OF 17)
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### Page 39

The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY
numbers shown below are the number of parts necessary for each airplane.
MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
(a)1ANB7483-1Fillet AssemblyRemove/Keep1
1ANB7483-2
1ANB7489-1Door AssemblyOpen2
1ANB7489-2
Mark hole positions for fas-
teners. (b) (f)
2SR10530059-3Strap AssemblyLocate3
0.1605/0.1625 inch diame-
ter in rib (4 off) and former
(4 off).
8-HolesDrill/Deburr4
(f)-Alodine 1200SChemical Conversion
Coating
Apply5
(b) (e) (f)2SR10530059-3Strap AssemblyInstall6
8HL328-5-3Pin
8NAS1149FN816PWasher
8MS21042L08Nut
(f)-FRPrimerApply7
-PR-1422 B-2Sealant
Mark hole positions for fas-
teners. (b) (f)
2SR10530059-3Strap AssemblyLocate8
0.1605/0.1625 inch diame-
ter in rib (4 off) and former
(4 off).
8-HolesDrill/Deburr9
(f)-Alodine 1200SChemical Conversion
Coating
Apply10
(b) (e) (f)2SR10530059-3Strap AssemblyInstall11
8HL328-5-3Pin
8NAS1149FN816PWasher
8MS21042L08Nut
(f)-FRPrimerApply12
-PR-1422 B-2Sealant
Drill out 2 rivets attached to
each web.
1
1
ANB7485-3
ANB7485-4
WebDrill/Deburr13
Mark hole positions for fas-
teners.
2SB10530109-41AngleLocate14
0.144/0.147 inch diameter
in former.
4-HolesDrill/Deburr15
FIGURE 1: EXTENDED WING TO FUSELAGE FILLETS - INSTALLATION OF BONDING STRAPS
(SHEET 13 OF 17)
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### Page 40

MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
To the mating surfaces of
angle and former.
-PR-1422 B-2SealantApply16
Between former and web.2SB10530109-41AngleInstall17
4NAS1738B4-2Rivet
Mark hole positions for fas-
teners. (b) (f)
2SR10530059-27Strap AssemblyLocate18
0.1605/0.1625 inch diame-
ter.
8-HolesDrill/Deburr19
(f)-Alodine 1200SChemical Conversion
Coating
Apply20
(b) (e) (f)2SR10530059-27Strap AssemblyInstall21
8HL328-5-3Pin
8NAS1149FN816PWasher
8MS21042L08Nut
(f)-FRPrimerApply22
-PR-1422 B-2Sealant
Drill out 2 rivets in each
stiffener.
1
1
ANB7484-7
ANB7484-8
StiffenerDrill/Deburr23
Mark hole positions for fas-
teners.
2SB10530109-39AngleLocate24
0.144/0.147 inch diameter
in former.
8-HolesDrill/Deburr25
To the mating surfaces of
the angle and former.
-PR-1422 B-2SealantApply26
Between stiffener and for-
mer.
2
8
SB10530109-39
NAS1738B4-2
Angle
Rivet
Install27
Mark hole positions for fas-
teners. (b) (f)
2SR10530059-13Strap AssemblyLocate28
0.1605/0.1625 inch diame-
ter.
8-HolesDrill/Deburr29
(f)-Alodine 1200SChemical Conversion
Coating
Apply30
(b) (e) (f)2SR10530059-13Strap AssemblyInstall31
8HL328-5-3Pin
8NAS1149FN816PWasher
8MS21042L08Nut
(f)-FRPrimerApply32
-PR-1422 B-2Sealant
FIGURE 1: EXTENDED WING TO FUSELAGE FILLETS - INSTALLATION OF BONDING STRAPS
(SHEET 14 OF 17)
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### Page 41

MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
Drill out 2 rivets in each rib.1ANB7484-25RibDrill/Deburr33
1ANB7484-26
Mark hole positions for fas-
teners.
2SB10530109-39AngleLocate34
0.144/0.147 inch diameter
in former.
8-HolesDrill/Deburr35
To the mating surfaces of
the angle and former.
-PR-1422 B-2SealantApply36
Between rib and former.2SB10530109-39AngleInstall37
8NAS1738B4-2Rivet
Mark hole positions for fas-
teners. (b) (f)
2SR10530059-13Strap AssemblyLocate38
0.1605/0.1625 inch diame-
ter.
8-HolesDrill/Deburr39
(f)-Alodine 1200SChemical Conversion
Coating
Apply40
(b) (e) (f)2SR10530059-13Strap AssemblyInstall41
8HL328-5-3Pin
8NAS1149FN816PWasher
8MS21042L08Nut
(f)-FRPrimerApply42
-PR-1422 B-2Sealant
Mark hole positions for fas-
teners.
2SB10530109-37AngleLocate43
0.144/0.147 inch diameter
in former.
8-HolesDrill/Deburr44
To the mating surfaces of
the angle and former.
-PR-1422 B-2SealantApply45
Between rib and former.2SB10530109-37AngleInstall46
8NAS1738B4-2Rivet
Mark hole positions for fas-
teners. (b) (f)
2SR10530059-15Strap AssemblyLocate47
0.1605/0.1625 inch diame-
ter.
8-HolesDrill/Deburr48
(f)-Alodine 1200SChemical Conversion
Coating
Apply49
FIGURE 1: EXTENDED WING TO FUSELAGE FILLETS - INSTALLATION OF BONDING STRAPS
(SHEET 15 OF 17)
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DC10-53-109Revision 7 March 03, 2009
41 of 89
BOEING SERVICE BULLETIN DC10-53-109

### Page 42

MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
(b) (e) (f)2SR10530059-15Strap AssemblyInstall50
8HL328-5-3Pin
8NAS1149FN816PWasher
8MS21042L08Nut
(f)-FRPrimerApply51
-PR-1422 B-2Sealant
Mark hole positions for fas-
teners.
2SB10530109-35AngleLocate52
0.144/0.147 inch diameter
in former.
8-HolesDrill/Deburr53
To the mating surfaces of
the angle and former.
-PR-1422 B-2SealantApply54
Between rib and former.2SB10530109-35AngleInstall55
8NAS1738B4-2Rivet
Mark hole positions for fas-
teners. (b) (f)
2SR10530059-15Strap AssemblyLocate56
0.1605/0.1625 inch diame-
ter.
8-HolesDrill/Deburr57
(f)-Alodine 1200SChemical Conversion
Coating
Apply58
(b) (e) (f)2SR10530059-15Strap AssemblyInstall59
8HL328-5-3Pin
8NAS1149FN816PWasher
8MS21042L08Nut
(f)-FRPrimerApply60
-PR-1422 B-2Sealant
(c)-DMS 1819SealantApply61
-1ANB7483-1Fillet AssemblyInstall62
1ANB7483-2
(d)-DMS 1819SealantApply63
1ANB7489-1Door AssemblyClose64
1ANB7489-2
(a) Remove cured sealant from the fillet assembly and faying surface of fuselage using a non metallic tool.
(b) Install bonding strap brackets in the location as shown. Locations of brackets to be determined on the
airplane by the operator. Pick up on existing fastener locations as applicable. Note: Grounding strap
cannot be tight, no wire strain is permitted. Strap brackets may be trimmed as required to clear rivet if
adverse tolerance build up causes unacceptable edge distance. Twice the diameter of the attachment is
minimum acceptable edge distance.
(c) Apply a 0.25 inch bead of sealant to the center of the fillet seal.
FIGURE 1: EXTENDED WING TO FUSELAGE FILLETS - INSTALLATION OF BONDING STRAPS
(SHEET 16 OF 17)
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Original Issue: December 24, 1979
DC10-53-109Revision 7 March 03, 2009
42 of 89
BOEING SERVICE BULLETIN DC10-53-109

### Page 43

MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
(d) Apply sealant to the edge of the seal overlapping 0.125 inches on to the rub strip.
(e) Adjust the strap installation up and inboard as required to maintain 4D spacing between the nearest strap
installation fastener hole and any existing pilot hole.
(f) Refer to Appendix A for bonding strap installation procedure.
FIGURE 1: EXTENDED WING TO FUSELAGE FILLETS - INSTALLATION OF BONDING STRAPS
(SHEET 17 OF 17)
BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
Original Issue: December 24, 1979
DC10-53-109Revision 7 March 03, 2009
43 of 89
BOEING SERVICE BULLETIN DC10-53-109

### Page 44 (OCR)

BOEING SERVICE BULLETIN DC10-53-109
This Figure applies only to: Group 3-4, Configuration 2.
ANB7483-1 (LS)
ANB7483-2 (RS)
FILLET ASSY (REF)
D980 81
STA  STA  STA  STA
Y=1079.000  Y=1099.000  Y=1119.000  Y=1139.000
STA  H (SHEET 14)
Z=-20.000  7G (SHEET 12)  (BEFORE)
(SHEET 10)  (BEFORE)
(SHEET 8)E  F (BEFORE  H (SHEET 15)
(BEFORE)  -G (SHEET 13)  (AFTER)
(AFTER) E F (AFTER)  (SHEET 9)  (SHEET 11)  (AFTER)
STA
Z=-40.000
(SHEET 6)
STA  (BEFORE)
Z=-45.720
D
(SHEET 7)  (SHEET 4)
STA  (AFTER)  - (BEFORE>
Z=-60.000
¡B (SHEET 2)
(BEFORE)
STA
Z=-80.000
(SHEET 5)
ANB7489-1  ANB7489-2 (RS)  (LS) (2  ' (AFTER)  ¡ (SHEET 3)
DOOR ASSY (REF)  (AFTER)  U55022
VIEW A-A
FIGURE 2: EXTENDED WINGTO FUSELAGE FILLETS - REPLACEMENT OF BONDING STRAPS
(SHEET 1 OF 22)
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### Page 45 (OCR)

BOEING SERVICE BULLETIN DC10-53-109
ANB7547-19 (LS)  ANB7547-20 (RS)  SB10530109-5 (LS)  SB10530109-6 (RS)  STA  7=-70.000  (5 PLACES)
STRAP (REF)
OR  OUTBDEWD
(4 PLACES)
STA  Y=1139.000  ANB7488-3 (LS)  (RS)  ANB7488-4  RIB (REF)  STRAP INSTALLATION MAY VARY SLIGHTLY PER AIRPLANE
ARB7127-3 (LS)  ARB7127-4 (RS)  FORMER (REF)  ANB7547-3 (LS)  ANB7547-4 (RS)  STRAP (REF)  OR  STA  Z=-70.000  (5 PLACES)  VIEW B-B  BEFORE MODIFICATION  LOOKING FORWARD
(4 PLACES)  OUTBO END
ARB7127-3 (LS)  ARB7127-4 (RS)  FORMER (REF)  STA  Y=1139.000  ANB7488-3 (LS)  ANB7488-4 (RS)  RIB (REF)
FIGURE 2: EXTENDED WING TO FUSELAGE FILLETS - REPLACEMENT OF BONDING STRAPS
(SHEET 2 OF 22)
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### Page 46 (OCR)

BOEING SERVICE BULLETIN DC10-53-109
•ARB7127-3 (LS)
ARB7127-4 (RS)
FORMER (REF)
STA
Y=1139.000  0.80 IN.
0.50 IN.
(3 PLACES)
(2 PLACES)
(2 PLACES)
STA
Z=-70.000
0.44 IN.
ANB7488-3 (LS)
ANB7488-4 (RS)
RIB (REF)
(3 PLACES)
0.50 IN.
VIEW B-B
OUTBD  > FWD
AFTER MODIFICATION
LOOKING FORWARD
STRAP INSTALLATION MAY VARY SLIGHTLY PER AIRPLANE
FIGURE 2: EXTENDED WINGTO FUSELAGE FILLETS - REPLACEMENT OF BONDING STRAPS
(SHEET 3 OF 22)
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### Page 47 (OCR)

BOEING SERVICE BULLETIN DC10-53-109
ARB7127-3 (LS)  ARB7127-4 (RS)  ANB7547-21 (LS)  ANB7547-22 (RS)  SB10530109-7 (LS)  SB10530109-8 (RS)  STRAP (REF)  STA  Z=-70.000
FORMER (REF)  OR
(4 PLACES)  STA  Z=-60.000
STA  Y=1119.000  STA  X=120.000  (5 PLACES)  STRAP INSTALLATION MAY VARY SLIGHTLY PER AIRPLANE
AFWD  ANB7547-5 (LS)  ANB7547-6 (RS)  OR  ANB7487-3 (LS)  (RS)  ANB7487-4  RIB (REF)  VIEW C-C  BEFORE MODIFICATION  LOOKING FORWARD
(REF)
OUTBD  STRAP  'STA  Z=-70.000
ARB7127-3 (LS)  ARB7127-4 (RS)  FORMER (REF)  (4 PLACES)  STA  Z=-60.000  (5 PLACES)
Y=1119.000  STA  X=120.000
STA
ANB7487-3  ANB7487-4  RIB (REE)
FIGURE 2: EXTENDED WING TO FUSELAGE FILLETS - REPLACEMENT OF BONDING STRAPS
(SHEET 4 OF 22)
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### Page 48 (OCR)

BOEING SERVICE BULLETIN DC10-53-109
ARB7127-3 (LS)
STA
ARB7127-4 (RS)
Y=1119.000  FORMER (REF)
0.50 IN.
(15)17
(2 PLACES)
0.80 IN.
(3 PLACES)
STA
Z=-60.000
(16 18)
STA
X=120.000
(3 PLACES)
0.44 IN.
ANB7487-3  (LS)
ANB7487-4  (RS)
RIB (REF)
16,18
STA
(15) 17)  Z=-70.000
(2 PLACES)
OUTBD<  F WD  VIEW C-C  -0.50 IN.
AFTER MODIFICATION
LOOKING FORWARD
STRAP INSTALLATION MAY VARY SLIGHTLY PER AIRPLANE
FIGURE 2: EXTENDED WINGTO FUSELAGE FILLETS - REPLACEMENT OF BONDING STRAPS
(SHEET 5 OF 22)
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### Page 49 (OCR)

BOEING SERVICE BULLETIN DC10-53-109
ARB7127-45 (LS)
OUTBD <  _FWD  ARB7127-46 (RS)
FORMER (REF)
(20)  ) WZZ7573-9 (LS)
WZZ7573-10 (RS)
STRAP (REF)
WZZ7573-11
ANGLE (REF)
ANB7485-9 (LS)
STA
ARB7485-10 (RS)
STIFFENER (REF)  Y=1089.000
ARB7127-45 (LS)  STA
ARB7127-46 (RS)  Y=120.000  ANB7485-3
FORMER (REF)  WEB (REF)
OR  STA
Z=-45.720 Y=1099.000  STA
ANB7547-25 (LS)
ANB7547-26 (RS)
OR
SB10530109-23 (LS)
SB10530109-24 (RS)
OR
ARB7127-75  WZZ7573-15 (LS)
OR  WZZ7573-16 (RS)
WZZ7573-11 20)  (REF)
OR
SB10530109-21
ANGLE  STA
(REF)  Y=1089.000
ANB7485-9 (LS)
ANB7485-10 (RS)  STA  ANB7485-3
STIFFENER (REF)  X=120.000  WEB (REF)
VIEW D-D
STA  BEFORE MODIFICATION
STRAP INSTALLATION MAY VARY SLIGHTLY PER AIRPLANE  Z=-45.720  LOOKING FORWARD  U55005
FIGURE 2: EXTENDED WING TO FUSELAGE FILLETS - REPLACEMENT OF BONDING STRAPS
(SHEET 6 OF 22)
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### Page 50 (OCR)

BOEING SERVICE BULLETIN DC10-53-109
EDGE OF
ANB7485-3 WEB
21)
(2 PLACES)
STA
Z=-45.720
ARB7127-45 (LS)
ARB7127-46 (RS)
FORMER (REF)
1.85 IN.
→ FWD
LOOKING OUTBOARD  0.88 IN.
0.38 IN.
(TYP)
0.40 IN.
(26) 29)
0.50 IN.
28 30  0.40 IN.
SEE
27/29  (22) 24 25)
(2 PLACES)
STA
ANB7485-9 (LS)  Y=1089.000
ANB7485-10 (RS)
STIFFENER (REF)
ANB7485-3  0.50 IN.
WEB (REF)
STA  28) 30  OUTBD  > FWD
X=120.000  129)  VIEW D-D
LOOKING FORWARD
STA  STA
STRAP INSTALLATION MAY VARY SLIGHTLY PER AIRPLANE  Z=-45.720  Y=1099.000  U55900
FIGURE 2: EXTENDED WINGTO FUSELAGE FILLETS - REPLACEMENT OF BONDING STRAPS
(SHEET 7 OF 22)
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### Page 51 (OCR)

BOEING SERVICE BULLETIN DC10-53-109
AFT <  •OUTBD  ANB7484-7 (LS)  ANB7484-8 (RS)
STIFFENER (REF)
STA
Y=1099.000
ANB7547-17 (LS)
32  ANB7547-18 (RS)
OR
STA  WZZ7573-7 (LS)
Z=-30.000  WZZ7573-8 (RS)
STRAP (REF)
ANB7484-3 (LS)
ANB7484-4 (RS)  OR
ARB7127-45 (LS)
RIB (REF)  STA  ARB7127-46 (RS)
Z=-40.000  FORMER (REF)
ANB7484-7 (LS)
ANB7484-8 (RS)
STIFFENER (REF)
STA  ANB7547-27 (LS)
Y=1099.000  32 ANB7547-28 (RS)
AFT <  > OUTBD  OR
SR10530109-9 (LS)
SR10530109-10 (RS)
STA  STRAP (REF)
Z=-30.000
) ARB7127-73
OR
SB10530109-19
ANGLE (REF)
ANB7484-3 (LS)  VIEW E-E
ANB7484-4 (RS)  ARB7127-45 (LS)
RIB (REF)  STA -  BEFORE MODIFICATION  ARB7127-46 (RS)
Z=-40.000  GROUP 3  FORMER (REF)
LOOKING AFT
STRAP INSTALLATION MAY VARY SLIGHTLY PER AIRPLANE
FIGURE 2: EXTENDED WING TO FUSELAGE FILLETS - REPLACEMENT OF BONDING STRAPS
(SHEET 8 OF 22)
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### Page 52 (OCR)

BOEING SERVICE BULLETIN DC10-53-109
ANB(484-7 (LS)
ANB7484-8 (RS)
STIFFENER (REF)
(2 PLACES)
(2 PLACES)  (4 PLACES)
STA  33  39 41) (2 PLACES)
Y=1099.000
0.50 IN.  54 36 37
STA
Z=-30.000
0.50 IN.
0.40 IN.
0.40 IN.
40 42)
ANB7484-3  (LS)
ANB7484-4  RIB (REF)  (RS)  (40)  ARB7127-45 (LS)  ARB7127-46 (RS)
STA  (35 37)  FORMER (REF)
Z=-40.000  (4 PLACES)
VIEW E-E
AFTER MODIFICATION  AFT ROUTED
GROUP 3
STRAP INSTALLATION MAY VARY SLIGHTLY PER AIRPLANE  LOOKING AFT  U56875
FIGURE 2: EXTENDED WINGTO FUSELAGE FILLETS - REPLACEMENT OF BONDING STRAPS
(SHEET 9 OF 22)
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### Page 53 (OCR)

BOEING SERVICE BULLETIN DC10-53-109
MS20470AD5-6  ANB7547-15
RIVET (REF)  FILLER (REF)
(2 OFF)
OUTBD <  FWD
STA
Y=1099.000  ANB7484-25 (LS)
(4 PLACES)  ANB7484-26 (RS)
RIB (REF)
STA
MS20470AD5-8
RIVET (REF)  Z=-30.000
(2 OFF)
WZZ7573-13 (LS)
44
(4 PLACES)  WZZ7573-14 (RS)
STRAP (REF)
STA
Z=-40.000
ANB7127-45 (LS)  ANB7484-25 (LS)
ANB7127-46 (RS)  ANB7484-26 (RS)
FORMER (REF)  OR  RIB (REF)
STA
Y=1099.000
(4 PLACES)
STA
ARB7127-73 44  Z=-30.000
OR
SB10530109-19
ANGLE (REF)
44 ANB7547-27 (LS)
MS20470AD5-6  ANB7547-28 (RS)
RIVET (REF)  OR
ARB7127-45 (LS)  STA  (2 OFF)  SB10530109-9 (LS)
ARB7127-46 (RS)  Z=-40.000  SB10530109-10 (RS)
FORMER (REF)  (4 PLACES)  VIEW F-F  STRAP (REF)
BEFORE MODIFICATION
GROUP 4
LOOKING FORWARD  U55914
STRAP INSTALLATION MAY VARY SLIGHTLY PER AIRPLANE
FIGURE 2: EXTENDED WING TO FUSELAGE FILLETS - REPLACEMENT OF BONDING STRAPS
(SHEET 10 OF 22)
Original Issue: December 24, 1979
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### Page 54 (OCR)

BOEING SERVICE BULLETIN DC10-53-109
ANB7484-25 (LS)
ANB7484-26 (RS)
RIB (REF)  (2 PLACES)
52,54  (51 53)
7
STA
Y=1099.000
(2 PLACES)
51)53
0.50 IN.
(52) 54
0.40 IN.  0.50 IN
0.40 IN.
47 49)
48)  (4 PLACES)  50 53
STA
Z=-40.000
ARB7127-45 (LS)  ARB7127-46 (LS)  OUTBO AFNO
FORMER (REF)
VIEW F-F
AFTER MODIFICATION
GROUP 4
LOOKING FORWARD
STRAP INSTALLATION MAY VARY SLIGHTLY PER AIRPLANE
FIGURE 2: EXTENDED WING TO FUSELAGE FILLETS - REPLACEMENT OF BONDING STRAPS
(SHEET 11 OF 22)
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### Page 55 (OCR)

BOEING SERVICE BULLETIN DC10-53-109
STA  Z=-20.000  Y=1119.000  ANB7482-3 (LS)  ANB7482-4 (RS)
STA  RIB (REF)  ANB7547-29 (LS)  ANB7547-30 (RS)  OR  SB10530109-11 (LS)  SB10530109-12 (RS)  STRAP (REF)  STA  Z=-30.000
STA  Y=1119.000  STRAP INSTALLATION MAY VARY SLIGHTLY PER AIRPLANE
OUTBD & FWD  STA  Z=-20.000  OR  ARB7127-71  OR  SB10530109-17  ANGLE (REF)  STA  Y=1119.000  ANB7482-3 (LS)  ANB7482-4 (RS)  RIB (REF)  ANB7547-9 (LS)  ANB7547-10 (RS)  OR  WZZ7573-5 (LS)  WZZ7573-6 (RS)  (REF)  STRAP  ARB7127-45 (LS)  ARB7127-46 (RS)  FORMER (REF)  VIEW G-G  BEFORE MODIFICATION
STA  Z=-30.000
·=1 19.000
ARB7127-45 (LS)  ARB7127-46 (RS)  FORMER (REE)  U55976
FIGURE 2: EXTENDED WING TO FUSELAGE FILLETS - REPLACEMENT OF BONDING STRAPS
(SHEET 12 OF 22)
Original Issue: December 24, 1979
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### Page 56 (OCR)

BOEING SERVICE BULLETIN DC10-53-109
(2 PLACES)
63) 65
STA
Z=-20.000
166)  X66
0.40 IN.  STA
Y=1119.000
ANB7482-3 (LS)
ANB7482-4 (RS)
RIB (REF)
162  165
S
0.50 IN.  -58 60
ARB7127-45 (LS)
60  ARB7127-46 (RS)
FORMER (REF)
(63 65)  Z=-30.000  STA
(2 PLACES)  STA
Y=1119.000
(59 61)
(4 PLACES)
OUTBD *  • FWD
G-G
AFTER MODIFICATION
LOOKING UP AND FORWARD
STRAP INSTALLATION MAY VARY SLIGHTLY PER AIRPLANE
FIGURE 2: EXTENDED WINGTO FUSELAGE FILLETS - REPLACEMENT OF BONDING STRAPS
(SHEET 13 OF 22)
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### Page 57 (OCR)

BOEING SERVICE BULLETIN DC10-53-109
OUTBD FND  STA  Z=-20.000  STA  Y=1139.000  ANB7482-5 (LS)  (RS)  ANB7482-6  RIB (REF)  ANB7547-31 (LS)  ANB7547-32 (RS)  SB10530109-13 (LS)  SB10530109-14 (RS)  STRAP (REF)
OR
STA  X=120.000
STA  Y=1139.000  STRAP INSTALLATION MAY VARY SLIGHTLY PER AIRPLANE
ARB7127-69  OR  SB10530109-15  ANGLE  ARB7127-45 (LS)  ARB7127-46 (RS)  FORMER (REF)  VIEW H-H  BEFORE MODIFICATION
'STA  Z=-20.000  OR  STA  Y=1139.000  (LS)  ANB7482-5  ANB7482-6  (RS)  RIB (REF)  ANB7547-7 (LS)  ANB7547-8 (RS)  WZZ7573-3 (LS)  WZZ7573-4 (RS)
STRAP (REE)
x=120.000  OR
68
STA
Y=1139.000
ARB7127-45 (LS)  ARB7127-46 (RS)  FORMER (REF)  U56273
FIGURE 2: EXTENDED WING TO FUSELAGE FILLETS - REPLACEMENT OF BONDING STRAPS
(SHEET 14 OF 22)
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### Page 58 (OCR)

BOEING SERVICE BULLETIN DC10-53-109
STA
X=120.000
(76/78
(2 PLACES)
. STA
Z=-20.000
0.50 IN.
RADIUS
0.40 IN.
STA
Y=1139.000
76/78
ANB7482-5 (LS)
0.50 IN.  74/77  ANB7482-6 (RS)  RIB (REF)
75
(2 PLACES)
ANB7127-45 (LS)
ANB7127-46 (RS)  STA
FORMER (REF)  Y=1139.000  (4 PLACES)
OUTBD FUD
H-H
AFTER MODIFICATION
LOOKING UP AND FORWARD
STRAP INSTALLATION MAY VARY SLIGHTLY PER AIRPLANE
FIGURE 2: EXTENDED WINGTO FUSELAGE FILLETS - REPLACEMENT OF BONDING STRAPS
(SHEET 15 OF 22)
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### Page 59

The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY
numbers shown below are the number of parts necessary for each airplane.
MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
(a)1ANB7483-1Fillet AssemblyRemove/Keep1
1ANB7483-2
1ANB7489-1Door AssemblyOpen2
1ANB7489-2
Drill out 4 rivets in each for-
mer and 5 rivets in each rib.
1
1
ARB7127-3
ARB7127-4
Former RibDrill/Deburr3
1ARB7488-3
1ARB7488-4
-1ANB7547-3Strap AssemblyRemove4
1ANB7547-4
or
1ANB7547-19
1ANB7547-20
or
1SB10530109-5
1SB10530109-6
Fill 3 holes in each rib and
each former. (e)
12-HolesFill5
Mark hole positions for fas-
teners. (b) (f)
2SR10530059-3Strap AssemblyLocate6
0.1605/0.1625 inch diame-
ter (2 off) in each rib and
former.
8-HolesDrill/Deburr7
(f)-Alodine 1200SChemical Conversion
Coating
Apply8
(b) (f)2SR10530059-3Strap AssemblyInstall9
8HL328-5-3Pin
8NAS1149FN816PWasher
8MS21042L08Nut
(f)-FRPrimerApply10
-PR-1422 B-2Sealant
Drill out 4 rivets in each for-
mer and 5 rivets in each rib.
1
1
ARB7127-3
ARB7127-4
FormerDrill/Deburr11
1ARB7487-3Rib
1ARB7487-4
FIGURE 2: EXTENDED WING TO FUSELAGE FILLETS - REPLACEMENT OF BONDING STRAPS
(SHEET 16 OF 22)
BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
Original Issue: December 24, 1979
DC10-53-109Revision 7 March 03, 2009
59 of 89
BOEING SERVICE BULLETIN DC10-53-109

### Page 60

MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
-1ANB7547-5StrapRemove12
1ANB7547-6Assembly
1ANB7547-21
1ANB7547-22
1SB10530109-7
1SB10530109-8
Fill 3 holes in each rib and
each former. (e)
12-HolesFill13
Mark hole positions for fas-
teners. (b) (f)
2SR10530059-3Strap AssemblyLocate14
0.1605/0.1625 inch diame-
ter (2 off) in each rib and
former.
8-HolesDrill/Deburr15
(f)-Alodine 1200SChemical Conversion
Coating
Apply16
(b) (f)2SR10530059-3Strap AssemblyInstall17
8HL328-5-3Pin
8NAS1149FN816PWasher
8MS21042L08Nut
(f)-FRPrimerApply18
-PR-1422 B-2Sealant
Drill out 4 rivets in each for-
mer (2 in strap and 2 in an-
gle) and 5 rivets in each
web.
1
1
ARB7127-45
ARB7127-46
FormerDrill/Deburr19
1
1
ARB7485-9
ARB7485-10
Web
-1WZZ7573-9Strap AssemblyRemove20
1WZZ7573-10 or
1ANB7547-25
1ANB7547-26 or
1SB10530109-23
1SB10530109-24 or
1WZZ7573-15
1WZZ7573-16
2WZZ7573-11 orAngle
2ARB7127-75 or
2SB10530109-21
Fill 2 holes in each former
and in each web. (e)
8-HolesFill21
Mark hole positions for fas-
teners.
2SB10530109-41AngleLocate22
FIGURE 2: EXTENDED WING TO FUSELAGE FILLETS - REPLACEMENT OF BONDING STRAPS
(SHEET 17 OF 22)
BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
Original Issue: December 24, 1979
DC10-53-109Revision 7 March 03, 2009
60 of 89
BOEING SERVICE BULLETIN DC10-53-109

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