# Boeing Service Bulletin DC10-53-109: U.S. DOT/FAA - Service Bulletin

- Rights: © The Boeing Company. Filed by the FAA in regulations.gov docket FAA-2012-0327; AD 2012-19-03 incorporates this document by reference. Not covered by OpenAirDocs’ CC0 dedication.
- Document: [Boeing Service Bulletin DC10-53-109](https://openairdocs.org/service-documents/boeing/dc10-53-109.md)
- Title as filed: U.S. DOT/FAA - Service Bulletin
- Pages: 122
- PDF: https://openairdocs.org/files/sha256/48/0f/480fda7202f0165203889ce69ebee845598fdb327b5bd2ec54febd9589f746ee
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## Text

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### Page 1

Commercial 
Airplanes
DC10
Service Bulletin
Number: DC10-53-109
Original Issue: December 24, 1979
Revision 8: March 10, 2011
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Unpublished Work - All Rights Reserved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, KC-10, KDC-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.
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8.0

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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 4
B. Concurrent Requirements ...................................... 1 5
C. Reason ................................................ 1 5
D. Description .............................................. 1 5
E. Compliance .............................................. 1 7
F. Approval ............................................... 1 7
G. Manpower .............................................. 1 8
H. Weight and Balance Changes .................................... 2 0
I. Electrical Load Data ......................................... 2 0
J. References .............................................. 2 0
1. Existing Data: ......................................... 2 0
2. Data supplied with this Service Bulletin: ........................... 2 0
3. Installation Drawings Used in the Preparation of this Service Bulletin: ........... 2 0
4. Process Data: ......................................... 2 1
K. Publications Affected ........................................ 2 1
L. Interchangeability and Intermixability of Parts ........................... 2 1
2. MATERIAL INFORMATION ........................................ 2 3
A. Material - Price and Availability ................................... 2 3
B. Industry Support Information .................................... 2 3
C. Parts Necessary For Each Airplane ................................. 2 3
1. Kits/Parts: ........................................... 2 3
2. Parts and Materials Supplied by the Operator: ........................ 3 0
3. Parts Modified and Reidentified: ............................... 3 1
4. Parts Removed and Not Replaced: .............................. 3 1
D. Parts Necessary to Change Spares ................................. 3 1
E. Special Tooling - Price and Availability ............................... 3 1
F. Special Tooling Necessary to do this Service Bulletin ....................... 3 1
3. ACCOMPLISHMENT INSTRUCTIONS .................................. 3 3
A. GENERAL INFORMATION ..................................... 3 3
B. WORK INSTRUCTIONS ....................................... 3 4
FIGURE 1: EXTENDED WING TO FUSELAGE FILLETS - INSTALLATION OF BONDING STRAPS [Group
1-4, Configuration 1] ...................................... 3 8
FIGURE 2: EXTENDED WING TO FUSELAGE FILLETS - REPLACEMENT OF BONDING STRAPS [Group
3-4, Configuration 2] ...................................... 5 7
FIGURE 3: EXTENDED WING TO FUSELAGE FILLETS - REPLACEMENT OF BONDING STRAPS [Group
1-2, Configuration 2] ...................................... 8 3
FIGURE 4: EXTENDED WING TO FUSELAGE FILLETS - REPLACEMENT OF ONE BONDING STRAP
[Group 1-4, Configuration 3] ................................. 1 0 7
FIGURE 5: EXTENDED WING TO FUSELAGE FILLETS - EXISTING STRAP INSTALLATION INSPECTION
................................................. 1 1 0
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FIGURE 6: EXTENDED WING TO FUSELAGE FILLETS - INSTALLATION OF ONE BONDING STRAP
................................................. 1 1 3
FIGURE 7: EXTENDED WING TO FUSELAGE FILLETS - INSTALLATION OF ONE BONDING STRAP
................................................. 1 1 7
Appendix A: BONDING STRAP INSTALLATION PROCEDURE ..................... 1 2 2
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Commercial 
Airplanes
DC10
Service Bulletin
Revision Transmittal SheetNumber: DC10-53-109Original Issue: December 24, 1979
Revision 8: March 10, 2011
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
Federal Aviation Administration (FAA) Airworthiness Directive AD 2009-26-17 is related to this service bulletin.
More work is necessary on all airplanes changed in accordance with all previous revisions of this service bulletin.
The more work required installs a new braided bonding strap omitted from previous revisions of this service
bulletin. An additional 8.8 task hours are required to do the work.
REASON FOR REVISION
This revision is sent to include the requirement for a new braided bonding strap omitted from previous releases
of this service bulletin and to reinstate airplanes inadvertently dropped from the effectivity.
These sections were changed:
1. In Paragraph 1.A., Effectivity, re-instated airplanes inadvertently dropped from effectivity, and added new
Configurations for Groups 1 through 4.
2. In Paragraph 1.D., Description, added new Group/Configuration data, and description of additional work.
3. In Paragraph 1.E., Compliance, added new Federal Aviation Administration (FAA) Airworthiness Directive
(AD).
4. In Paragraph 1.F., Approval, changed statement to reflect new revision, and added new Airworthiness
Directive.
5. In Paragraph 1.G., Manpower, Changed Table for Configuration 3, added tables for new Group/Configuration
data.
6. In Paragraph 1.J.1., Existing Data, added new AD.
7. In Paragraph 1.J.2., Data supplied with this Service Bulletin, changed drawing revision letter.
8. In Paragraph 1.J.3., Installation Drawings Used In the Preparation of This Service Bulletin, changed drawing
revision letter.
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9. In Paragraph 2.C., Parts Necessary for Each Airplane, added new tables for Group/Configuration
identification, added new part number and changed supplier address.
10. In Paragraph 2.C.2., Parts and Materials Supplied by Operator, revised one part number quantity and
changed supplier address.
11. In Paragraph 3.A., General Information, added new note.
12. In Paragraph 3.B., Work Instructions, added new work instructions for existing Group/Configurations and
new Group/Configuration.
13. In Figure 1, changed illustrations and added new work steps to show additional work.
14. In Figure 2, changed illustrations and added new work steps to show additional work.
15. In Figure 3, changed illustrations and added new work steps to show additional work.
16. In Figure 4, added parts inadvertently omitted from previous revisions to work step table.
17. Added new Figures 5, 6 and 7 to show additional work.
18. In Appendix, clarified work requirements.
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:
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:
March 10, 2011Revision 8:
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Commercial 
Airplanes
DC10
Service Bulletin
SummaryNumber: DC10-53-109Original Issue: December 24, 1979
Revision 8: March 10, 2011
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 was 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 work as follows on the left and right wings:
1. Group 1-4, Configuration 1:
(Airplanes that have not previously done Service Bulletin DC10-53-109)
Installs seven new 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)
Removes and replaces seven solid metal bonding straps with seven 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 solid
metal bonding straps were installed in production)
Removes and replaces seven solid metal bonding straps with seven new braided bonding straps between
the metallic frame of the fillet and the wing leading edge ribs installed in production.
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4. Group 1-4, Configuration 3:
(Airplanes that have previously done Service Bulletin DC10-53-109 Revision 4)
Replaces one existing braided bonding strap with a longer braided bonding strap and installs a new braided
bonding strap on each side 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.
5. Group 1-4, Configuration 4:
(Airplanes that have previously done Service Bulletin DC10-53-109 Revisions 5 and/or 6)
Installs a new braided bonding strap on each side between the metallic frame of the fillet and the wing
leading edge ribs, and 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. .
6. Group 1-4, Configuration 5:
(Airplanes that have previously done Service Bulletin DC10-57-109 Revision 7)
Installs a new braided bonding strap on each side between the metallic frame of the fillet and the wing
leading edge ribs.
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
Federal Aviation Administration (FAA) Airworthiness Directive AD 2009-26-17 is related to this service bulletin.
Boeing recommends that operators do this service bulletin at the earliest scheduled maintenance period.
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
7.514.9DC-10 and MD-10
Group 1-4, Configuration 2
Elapsed HoursTotal Task HoursAirplanes
9.919.8DC-10 and MD-10
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Group 1-4, Configuration 3
Elapsed HoursTotal Task HoursAirplanes
6.3 - 10.312.1 - 20.1DC-10 and MD-10
Group 1-4, Configuration 4
Elapsed HoursTotal Task HoursAirplanes
5.9 - 9.510.5 - 18.5DC-10 and MD-10
Group 1-4, Configuration 5
Elapsed HoursTotal Task HoursAirplanes
6.28.8DC-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
000000  |000000a
1000000 as
GROUPS 1-4, CONFIG 1
AIRPLANES THAT HAVE NOT DONE SERVICE BULLETIN
DC10-53-109
GROUPS 1-4, CONFIG 2
AIRPLANES THAT HAVE PREVIOUSLY DONE SERVICE
BULLETIN DC10-53-109 REVISION 3 OR A PRIOR REVISION
GROUPS 1-4, CONFIG 3
AIRPLANES THAT HAVE PREVIOUSLY DONE SERVICE
BULLETIN DC10-53-109 REVISION 4
GROUPS 1-4, CONFIG 4
AIRPLANES THAT HAVE PREVIOUSLY DONE SERVICE
BULLETIN DC10-53-109 REVISION 5 AND/OR 6
GROUPS 1-4, CONFIG 5
AIRPLANES THAT HAVE PREVIOUSLY DONE SERVICE
BULLETIN DC10-53-109 REVISION 7
LEFT SIDE SHOWN
RIGHT SIDE OPPOSITE
Original Issue: December 24, 1979
Revision 8: March 10, 2011  BOEING PROPRIETARY -  DC10-53-109
Copyright © Unpublished Work - See page 1 for details.  10 of 122

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Commercial 
Airplanes
DC10
Service Bulletin
Number: DC10-53-109
Original Issue: December 24, 1979
Revision 8: March 10, 2011
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 done Service Bulletin DC10-53-109.1
Airplanes that have previously done Service Bulletin DC10-53-109
Revision 3 or a prior revision.
2
Airplanes that have previously done Service Bulletin DC10-53-109
Revision 4.
3
Airplanes that have previously done Service Bulletin DC10-53-109
Revision 5 and/or 6.
4
Airplanes that have previously done Service Bulletin DC10-53-109
Revision 7.
5
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DESCRIPTIONCONFIGURATIONGROUP
Airplane fuselage number 300 only.-2
Airplanes that have not done Service Bulletin DC10-53-109.1
Airplanes that have previously done Service Bulletin DC10-53-109
Revision 3 or a prior revision.
2
Airplanes that have previously done Service Bulletin DC10-53-109
Revision 4.
3
Airplanes that have previously done Service Bulletin DC10-53-109
Revision 5 and/or 6.
4
Airplanes that have previously done Service Bulletin DC10-53-109
Revision 7.
5
Airplane fuselage numbers 260 through 299 excluding 268, 277, 280
through 282, 289 and 295 through 298, and the effectivities of Service
Bulletins DC10-53-103 and DC10-53-119.
-3
Airplanes that have not done Service Bulletin DC10-53-109.1
Airplanes that have previously done Service Bulletin DC10-53-109
Revision 3 or a prior revision.
2
Airplanes that have previously done Service Bulletin DC10-53-109
Revision 4.
3
Airplanes that have previously done Service Bulletin DC10-53-109
Revision 5 and/or 6.
4
Airplanes that have previously done Service Bulletin DC10-53-109
Revision 7.
5
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DESCRIPTIONCONFIGURATIONGROUP
Airplane fuselage numbers 301 through 422 as listed in this service
bulletin.
-4
Airplanes that have not done Service Bulletin DC10-53-109.1
Airplanes that have previously done Service Bulletin DC10-53-109
Revision 3 or a prior revision.
2
Airplanes that have previously done Service Bulletin DC10-53-109
Revision 4.
3
Airplanes that have previously done Service Bulletin DC10-53-109
Revision 5 and/or 6.
4
Airplanes that have previously done Service Bulletin DC10-53-109
Revision 7.
5
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
GroupFuselage Num-
ber
346
360
371
382
384
3114
3131 - 133
3156
3159
3171
3174
3176
3183 - 185
3187
3195
3201 - 202
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GroupFuselage Num-
ber
3217
3219
3232 - 234
3236
3241
3260 - 261
3263
3267
1268
3275
1277
1280 - 282
3284
3286
1289
3291 - 293
1295 - 298
3299
2300
4301 - 315
4317 - 319
4321 - 326
4328 - 336
4338 - 347
4349 - 353
4355 - 371
4373 - 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.
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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.
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.
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.
Revision 4 was issued to introduce the replacement of solid metal bonding straps with new improved
braided metal 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 replaced 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 was sent to incorporate an electrical resistance check of previously installed braided bonding
straps and instructions to correct locations that fail the resistance check.
Revision 8 is sent to include the requirement for a new braided bonding strap omitted from all previous
releases of this service bulletin and to reinstate airplanes inadvertently dropped from the effectivity.
D. Description
This service bulletin provides instructions to accomplish the work as follows on the left and right wings:
1. Group 1-4, Configuration 1:
(Airplanes that have not previously done Service Bulletin DC10-53-109)
Installs seven new 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)
Removes and replaces seven solid metal bonding straps with seven 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 solid metal bonding straps were installed in production)
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Removes and replaces seven solid metal bonding straps with seven 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)
Replaces one existing braided bonding strap with a longer braided bonding strap and installs a
new braided bonding strap on each side 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.
5. Group 1-4, Configuration 4:
(Airplanes that have previously done Service Bulletin DC10-53-109 Revisions 5 and/or 6)
Installs a new braided bonding strap on each side between the metallic frame of the fillet and the
wing leading edge ribs, and 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. .
6. Group 1-4, Configuration 5:
(Airplanes that have previously done Service Bulletin DC10-57-109 Revision 7)
Installs a new braided bonding strap on each side between the metallic frame of the fillet and the
wing leading edge ribs.
Revision 8 - More work is necessary on all airplanes changed in accordance with all previous revisions
of this service bulletin. The more work installs a braided bonding strap omitted from previous revisions
of this service bulletin..
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
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Group 3:
Affected Maintenance Zones
ZoneModel
131, 132, 161, 162DC-10-30, DC-10-30F, MD-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
E. Compliance
Federal Aviation Administration Airworthiness Directive AD 2009-26-17 is related to this service bulletin.
Boeing recommends that operators do this service bulletin at the earliest scheduled maintenance
period.
F. Approval
DC-10 Airplanes
This service bulletin was examined by the Federal Aviation Administration (FAA). The changes specified
in this service bulletin comply with the applicable regulations and are FAA approved, as well as European
Aviation Safety Agency (EASA)/Joint Aviation Authorities (JAA) approved for all EASA/JAA approved
airplanes listed in the service bulletin effectivity. This service bulletin and its approval were based on
the airplane in its original Boeing delivery configuration or as modified by other approved Boeing
changes.
If an airplane has a non-Boeing modification or repair that affects a component or system also affected
by this service bulletin, the operator is responsible for obtaining appropriate regulatory agency approval
before incorporating this service bulletin.
In addition, the Manager of the FAA Los Angles Aircraft Certification Office approves the action (i.e.
inspection or modification) defined in this service bulletin as an alternative method of compliance to
the requirements of paragraphs (g), (h), (i), (k) and (m) of Airworthiness Directive No. 2009-26-17. All
provisions of AD 2009-26-17 that are not specifically referenced in the above statement remain fully
applicable and must be complied with.
For MD-10 Airplanes
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This service bulletin was examined by the Federal Aviation Administration (FAA). The changes specified
in this service bulletin comply with the applicable regulations and are FAA approved. This service
bulletin and its approval were based on the airplane in its original Boeing delivery configuration or as
modified by other approved Boeing changes.
If an airplane has a non-Boeing modification or repair that affects a component or system also affected
by this service bulletin, the operator is responsible for obtaining appropriate regulatory agency approval
before incorporating this service bulletin.
In addition, the Manager of the FAA Los Angles Aircraft Certification Office approves the action (i.e.
inspection or modification) defined in this service bulletin as an alternative method of compliance to
the requirements of paragraphs (g), (h), (i), (k) and (m) of Airworthiness Directive No. 2009-26-17. All
provisions of AD 2009-26-17 that are not specifically referenced in the above statement remain fully
applicable and must be complied with.
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
3.36.52Install Seven Braided Bonding Straps
2.44.82Close Access
7.514.9TOTAL FOR EACH AIRPLANE
Group 1-4, Configuration 2:
Elapsed
Hours
Task HoursNumber of PersonsTask
1.83.62Open Access
5.711.42Remove Seven Solid Metal Bonding Straps and
Install Seven Braided Bonding Straps
2.44.82Close Access
9.919.8TOTAL FOR EACH AIRPLANE
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### Page 19

Group 1-4, Configuration 3:
Elapsed
Hours
Task HoursNumber of PersonsTask
1.83.62Open Access
0.81.62Replace One Braided Bonding Strap on Each
Side
0.81.62Install One Braided 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
6.3 - 10.312.1 - 20.1TOTAL FOR EACH AIRPLANE
(a) Hours are a maximum.
Group 1-4, Configuration 4:
Elapsed
Hours
Task HoursNumber of PersonsTask
1.83.62Open Access
0.81.62Install One Braided 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.
Group 1-4, Configuration 5:
Elapsed
Hours
Task HoursNumber of PersonsTask
1.83.62Open Access
0.81.62Install One Braided Bonding Strap
3.63.62Close Access
6.28.8TOTAL FOR EACH AIRPLANE
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### Page 20

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. Federal Aviation Administration (FAA) Airworthiness Directive (AD) 2009-26-17 .
b. Standard Wiring Practices Manual (SWPM) 20-50-01.
c. DC-10 Aircraft Maintenance Manual (AMM) 06-35-00 , 06-36-00.
d. DC10 Structural Repair Manual (SRM) 51-31-01, 51-32-01, 51-33-01, 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
E-mail: dse.boecom@boeing.com
a. Drawings:
ADCNDCN/REVSheetTitleDrawing No
-EDWGWing 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
EWing Root Bonding InstallationSR10530059
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### Page 21

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
1. Publications:
None.
2. Damage Tolerance Based Structural Inspections:
Boeing has evaluated the repairs and/or changes in this service bulletin for effects on Fatigue
Critical Structure (FCS) and for changes to Damage Tolerance Inspections (DTI) required in the
Maintenance Program. This service bulletin does not affect FCS, therefore DTIs are not necessary.
L. Interchangeability and Intermixability of Parts
Accomplishment of this service bulletin does not affect interchangeability or intermixability of parts.
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### Page 22

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BLANK PAGE

### Page 23

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.
Group 1-4, Configuration 1:
NotesExisting Part NumberNameQTYNew Part Number
--PIN56HL328-5-3
--NUT56MS21042L08
--WASHER56NAS1149FN816P
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### Page 24

Group 1-4, Configuration 1:
NotesExisting Part NumberNameQTYNew Part Number
(a) (b) (c) (d)SB10530109-29/-30STRAP ASSEM-
BLY
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-
BLY
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-
BLY
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-
BLY
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
(e)-ANGLE2SB10530109-35
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### Page 25

Group 1-4, Configuration 1:
NotesExisting Part NumberNameQTYNew Part Number
(e)-ANGLE2SB10530109-37
(e)-ANGLE2SB10530109-39
(e)-ANGLE2SB10530109-41
(e)-ANGLE2SR10530059-29
(a) Discard the existing part.
(b) This part is used in production.
(c) You 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.
(e) Part may required on some airplanes and should be determined by examination.
CAGECooner Wire CompanyNEQL48830 overbraid can be pur-
chased from: 637949265 Owensmouth Avenue
Chatsworth, California 91311
Group 1-2, Configuration 2:
NotesExisting Part NumberNameQTYNew Part Number
--PIN56HL328-5-3
--NUT56MS21042L08
--WASHER56NAS1149FN816P
(a) (b) (c) (d)SB10530109-29/-30STRAP ASSEM-
BLY
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
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### Page 26

Group 1-2, Configuration 2:
NotesExisting Part NumberNameQTYNew Part Number
(a) (b) (c) (d)SB10530109-31/-32/-33/-34STRAP ASSEM-
BLY
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-
BLY
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-
BLY
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
(e)2ANGLE2SR10530059-29
(a) Discard the existing part.
(b) This part is used in production.
(c) You 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.
(e) Part may required on some airplanes and should be determined by examination.
CAGECooner Wire CompanyNEQL48830 overbraid can be pur-
chased from: 637949265 Owensmouth Avenue
Chatsworth, California 91311
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### Page 27

Group 3-4, Configuration 2:
NotesExisting Part NumberNameQTYNew Part Number
--PIN56HL328-5-3
--NUT56MS21042L08
--WASHER56NAS1149FN816P
(a) (b) (c) (d)SB10530109-29/-30STRAP ASSEM-
BLY
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-
BLY
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-
BLY
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
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### Page 28

Group 3-4, Configuration 2:
NotesExisting Part NumberNameQTYNew Part Number
(a) (b) (c) (d)SB10530109-25/-26/-27/-28STRAP ASSEM-
BLY
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
(e)-ANGLE2SB10530109-37
(e)-ANGLE2SB10530109-39
(e)-ANGLE2SB10530109-41
(e)2ANGLE2SR10530059-29
(a) Discard the existing part.
(b) This part is used in production.
(c) You 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.
(e) Part may required on some airplanes and should be determined by examination.
CAGECooner Wire CompanyNEQL48830 overbraid can be pur-
chased from: 637949265 Owensmouth Avenue
Chatsworth, California 91311
Group 1-4, Configuration 3:
NotesExisting Part NumberNameQTYNew Part Number
--PIN8HL328-5-3
--NUT8MS21042L08
--WASHER8NAS1149FN816P
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### Page 29

Group 1-4, Configuration 3:
NotesExisting Part NumberNameQTYNew Part Number
(a) (b) (c) (d)SB10530109-29/-30STRAP ASSEM-
BLY
2SR10530059-13
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)SR10530059-21STRAP ASSEM-
BLY
2SR10530059-27
(e)2ANGLE2SR10530059-29
(a) Discard the existing part.
(b) This part is used in production.
(c) You 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.
(e) Part may required on some airplanes and should be determined by examination.
CAGECooner Wire CompanyNEQL48830 overbraid can be pur-
chased from: 637949265 Owensmouth Avenue
Chatsworth, California 91311
Group 1, Configuration 4-5; Group 2, Configuration 4-5; Group 3, Configuration 4-5; Group 4, Con-
figuration 4-5:
NotesExisting Part NumberNameQTYNew Part Number
--PIN8HL328-5-3
--NUT8MS21042L08
--WASHER8NAS1149FN816P
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### Page 30

Group 1, Configuration 4-5; Group 2, Configuration 4-5; Group 3, Configuration 4-5; Group 4, Con-
figuration 4-5:
NotesExisting Part NumberNameQTYNew Part Number
(a) (b) (c) (d)SB10530109-29/-30STRAP ASSEM-
BLY
2SR10530059-13
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
(e)2ANGLE2SR10530059-29
(a) Discard the existing part.
(b) This part is used in production.
(c) You 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.
(e) Part may required on some airplanes and should be determined by examination.
CAGECooner Wire CompanyNEQL48830 overbraid can be pur-
chased from: 637949265 Owensmouth Avenue
Chatsworth, California 91311
2. Parts and Materials Supplied by the Operator:
NOTE: Parts quantities listed are maximum number required to accomplish this service bulletin.
The actual number required is to be determined by operator based on airplane
configuration.
NotesNameGroup 1, 2, 3, 4Part Number / Specification
QTY
(a)Rivet136NAS1738B4-2
(a)Rivet108NAS1738E4-2
(a)Rivet100NAS1739E4-2
(b)Sealant, Polysulfide, Aluminized8 Oz.AC-632, B-2
(DMS 1819 B-1/2)
or
Equivalent
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### Page 31

NotesNameGroup 1, 2, 3, 4Part Number / Specification
QTY
(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) Can be purchased from:
731972600 Skypark Drive
Torrance, California 90505
1DWR5Advanced Chemistry and Technology, Incorporated(b) Can be purchased from:
7341 Anaconda Avenue
Garden Grove, California 92841-2921
92108PRC-DeSoto International, Incorporated(c) Can be purchased from:
P.O. Box 1800
Sylmar, California 91342
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 32

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BLANK PAGE

### Page 33

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: ELECTRICALLY 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 34

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 "in
accordance with" 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.
11. Operators may install a different part number grounding strap assembly than called
for in the work steps to insure there is no wire strain on installation.
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 done Service Bulletin DC10-53-109)
a. Install seven new braided bonding straps between the metallic frame of the fillet and the wing
leading edge ribs in accordance with 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.
Group 1-2, Configuration 2:
(Airplanes that have previously done Service Bulletin DC10-53-109 Revision 3 or a Prior
Revision)
a. Replace seven solid bonding straps between the metallic frame of the fillet and the wing
leading edge ribs with braided bonding straps in accordance with Figure 3.
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### Page 35

Group 3-4, Configuration 2:
(Airplanes that have previously done Service Bulletin DC10-53-109 Revision 3 or a Prior
Revision or Solid Metal Bonding Straps were Installed in Production)
a. Replace seven solid bonding straps between the metallic frame of the fillet and the wing
leading edge ribs with braided bonding straps in accordance with Figure 2.
Group 1-4, Configuration 3:
(Airplanes that have previously done Service Bulletin DC10-53-109 Revision 4)
a. Remove and keep fillet assembly ANB7483-1 (left side) and fillet assembly ANB7483-2 (right
side) and attaching parts.
NOTE: Remove cured sealant from fillet assemblies and fuselage surfaces using a
non-metallic tool.
b. Open door assembly ANB7489-1 (left side) and door assembly ANB7489-2 (right side).
c. Replace the braided bonding strap between the metallic frame of the fillet and the wing leading
edge ribs in accordance with Figure 4.
d. Examine the area identified in Figure 5 for the existence of an installed solid metal bonding
strap.
Bonding strap installed
(1) Replace the solid metal bonding strap with a braided bonding strap between the metallic
frame of the fillet and the wing leading edge ribs in accordance with Figure 6.
Bonding strap not installed
(1) Install one new braided bonding strap between the metallic frame of the fillet and the
wing leading edge ribs in accordance with Figure 7.
e. Measure electrical resistance across each bonding joint of the six previously installed braided
strap assemblies in accordance with SWPM 20-50-01, Paragraph 3.A. Verify brackets have
an acceptable fillet seal in accordance with Appendix A. 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.
Electrical Resistance Test Passes and Brackets have Acceptable Fillet Seal
(1) No further work required.
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BOEING SERVICE BULLETIN DC10-53-109

### Page 36

f. Close door assembly ANB7489-1 (left side) and door assembly ANB7489-2 (right side).
g. Apply a 0.25 inch bead of DMS 1819 sealant to the fillet assembly seals and install the kept
fillet assembly ANB7483-1 (left side) and fillet assembly ANB7483-2 (right side) using kept
attaching parts.
h. Apply a fillet seal, overlapping the fillet assembly's seal and the fuselage/wing rubstrip
approximately 0.125 inch wide using DMS 1819 sealant.
Group 1-4, Configuration 4:
(Airplanes that have previously done Service Bulletin DC10-53-109 Revision 5 and/or 6)
a. Open door assembly ANB7489-1 (left side) and door assembly ANB7489-2 (right side).
b. Examine the area identified in Figure 5 for the existence of an installed solid metal bonding
strap.
Bonding strap installed
(1) Replace the solid metal bonding strap with a braided bonding strap between the metallic
frame of the fillet and the wing leading edge ribs in accordance with Figure 6.
Bonding strap not installed
(1) Install one new braided bonding strap between the metallic frame of the fillet and the
wing leading edge ribs in accordance with Figure 7.
c. At operators option, for ease of access to bonding strap installations located near the upper
surfaces of the fillet assembly remove and retain fillet assembly ANB7483-1 (left side) and
fillet assembly ANB7483-2 (right side) and attaching parts.
NOTE: Remove cured sealant from fillet assemblies and fuselage surfaces using a
non-metallic tool.
d. Measure electrical resistance across each bonding joint of the six previously installed braided
strap assemblies in accordance with SWPM 20-50-01, Paragraph 3.A. Verify brackets have
an acceptable fillet seal in accordance with Appendix A. 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.
Electrical Resistance Test Passes and Brackets have Acceptable Fillet Seal
(1) No further work required.
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: December 24, 1979
DC10-53-109Revision 8: March 10, 2011
36 of 122
BOEING SERVICE BULLETIN DC10-53-109

### Page 37

e. If fillets were removed, apply a 0.25 inch bead of DMS 1819 sealant to the fillet assembly
seals and install the kept fillet assembly ANB7483-1 (left side) and fillet assembly ANB7483-2
(right side) using kept attaching parts.
f. If fillets were removed, apply a fillet seal, overlapping the fillet assembly's seal and the
fuselage/wing rubstrip approximately 0.125 inch wide using DMS 1819 sealant.
g. Close door assembly ANB7489-1 (left side) and door assembly ANB7489-2 (right side).
Group 1-4, Configuration 5:
(Airplanes that have previously done Service Bulletin DC10-53-109 Revision 7)
a. Open door assembly ANB7489-1 (left side) and door assembly ANB7489-2 (right side).
b. Examine the area identified in Figure 5 for the existence of an installed solid metal bonding
strap.
Bonding strap installed
(1) Replace the solid metal bonding strap with a braided bonding strap between the metallic
frame of the fillet and the wing leading edge ribs in accordance with Figure 6.
Bonding strap not installed
(1) Install one new braided bonding strap between the metallic frame of the fillet and the
wing leading edge ribs in accordance with Figure 7.
c. Close door assembly ANB7489-1 (left side) and door assembly ANB7489-2 (right side).
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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Copyright © Unpublished Work - See page 1 for details.
Original Issue: December 24, 1979
DC10-53-109Revision 8: March 10, 2011
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BOEING SERVICE BULLETIN DC10-53-109

### Page 38 (OCR)

BOEING SERVICE BULLETIN DC10-53-109
This Figure applies only to: Group 1-4, Configuration 1.
LEFT SIDE SHOWN
RIGHT SIDE OPPOSITE
STA  STA  STA  STA
Y=1079.000  Y=1099.000  Y=1119.000  Y=1139.000  100
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  G (SHEET 7)
Z=-45.000
(SHEET  4)
72  ANB7489-1 (LS)
STA  ANB7489-2 (RS)
Z=-60.000  DOOR ASSY (REF)
N
(SHEET 13)  n
STA
Z=-80.000
(SHEET 3) C  B (SHEET 2)
FWD C  VIEW A-A  U54443
FIGURE 1: EXTENDED WING TO FUSELAGE FILLETS - INSTALLATION OF BONDING STRAPS
(SHEET 1 OF 19)
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### Page 39 (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.
46
2.32 IN.
STA
Z=-70.000
-0.44 IN.
-ANB7488-3 (LS)
ANB7488-4  (RS)
RIB (REF)
0.50 IN.
OUTBO FWD  VIEW B-B  STA  U54994
LOOKING FORWARD
Y=1139.00
FIGURE 1: EXTENDED WING TO FUSELAGE FILLETS - INSTALLATION OF BONDING STRAPS
(SHEET 2 OF 19)
Original Issue: December 24, 1979
Revision 8 March 10, 2011  BOEING PROPRIETARY -  DC10-53-109
Copyright © Unpublished Work - See page 1 for details.  39 of 122

### Page 40 (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)12
11
0.44 IN.
ANB7487-3  (LS)
ANB7487-4  (RS)
RIB (REF)
11  STA
(2 PLACES)  Z=-70.000
OUTBD  > FWD  0.50 IN.
LOOKING FORWARD  VIEW C-C  STA  U55017
Y=1119.000
FIGURE 1: EXTENDED WING TO FUSELAGE FILLETS - INSTALLATION OF BONDING STRAPS
(SHEET 3 OF 19)
Original Issue: December 24, 1979
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### Page 41 (OCR)

BOEING SERVICE BULLETIN DC10-53-109
EDGE OF
ANB7485-3 WEB
STA -
Z=-45.720
ARB7127-45 (LS)
ARB7127-46 (RS)  (14) 16)17
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) 22  0.40 IN.
(19) 21)  SEE
STA
ANB7485-9 (LS)  Y=1089.000
ANB7485-10 (RS)
STIFFENER (REF)
ANB7485-3  0.50 IN.
WEB (REF)
STA  20 22)  OUTBD<  > FWD
X=120.000  13) 19 21  VIEW D-D
STA  • STA  LOOKING FORWARD  U55453
Z=-45.720  Y=1099.000
FIGURE 1: EXTENDED WING TO FUSELAGE FILLETS - INSTALLATION OF BONDING STRAPS
(SHEET 4 OF 19)
Original Issue: December 24, 1979
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Copyright © Unpublished Work - See page 1 for details.  41 of 122

### Page 42 (OCR)

BOEING SERVICE BULLETIN DC10-53-109
ANB7484-7  (LS)
ANB7484-8  (RS)
STIFFENER (REF)
(2 PLACES)
STA  (29 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
FIGURE 1: EXTENDED WING TO FUSELAGE FILLETS - INSTALLATION OF BONDING STRAPS
(SHEET 5 OF 19)
Original Issue: December 24, 1979
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Copyright © Unpublished Work - See page 1 for details.  42 of 122

### Page 43 (OCR)

BOEING SERVICE BULLETIN DC10-53-109
STA
Y=1099.000
24 26 21
2.08 IN.  /(4 PLACES)
CONSTANT
25 2J
(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 19)
Original Issue: December 24, 1979
Revision 8 March 10, 2011  DC10-53-109
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### Page 44 (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.  H^  0.50 IN.
(SHEET 8)  0.40 IN.
STA
Z=-36.995
STA
Z=-40.000
ARB7127-45 (LS)
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 19)
Original Issue: December 24, 1979
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### Page 45 (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 19)
Original Issue: December 24, 1979
Revision 8 March 10, 2011  DC10-53-109
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Copyright © Unpublished Work - See page 1 for details.  45 of 122

### Page 46 (OCR)

BOEING SERVICE BULLETIN DC10-53-109
STA
Z=-20.000
48 50
•0.50 IN.
RADIUS
48,50
STA
0.40 IN.  2.55 IN.  Y=1119.000
ANB7482-3 (LS)
ANB7482-4 (RS)
RIB (REF)
47 50
(SHEET  10)
- ARB7127-45 (LS)
ARB7127-46 (RS)
0.50 IN.
FORMER (REF)
• STA
Z=-30.000
STA
Y=1119.000
VIEW J-J  OUTBD FWD
LOOKING UP AND FORWARD
FIGURE 1: EXTENDED WING TO FUSELAGE FILLETS - INSTALLATION OF BONDING STRAPS
(SHEET 9 OF 19)
Original Issue: December 24, 1979
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Copyright © Unpublished Work - See page 1 for details.  46 of 122

### Page 47 (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 19)
Original Issue: December 24, 1979
Revision 8 March 10, 2011  DC10-53-109
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Copyright © Unpublished Work - See page 1 for details.  47 of 122

### Page 48 (OCR)

BOEING SERVICE BULLETIN DC10-53-109
STA
Y=120.000
57)
- 0.50 IN
RADIUS
58 60 61
0.40 IN.
STA
Y=1139.000
ANB7482-5 (LS)
ANB7482-6 (RS)
M  (56 59  RIB (REF)
(SHEET,  12)
ARB7127-45 (LS)
ARB7127-46 (RS)
0.50 IN.-  FORMER (REF)
58 60 61
STA
Z=-30.000
STA  OUTBD FWD
Y=1139.000
VIEW L-L
LOOKING UP AND FORWARD
U57489
FIGURE 1: EXTENDED WING TO FUSELAGE FILLETS - INSTALLATION OF BONDING STRAPS
(SHEET 11 OF 19)
Original Issue: December 24, 1979
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### Page 49 (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
-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 19)
Original Issue: December 24, 1979
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### Page 50 (OCR)

BOEING SERVICE BULLETIN DC10-53-109
STA
Y=1099.000
(67 68) 69)
Z=-50.000
0.50 IN.
0.40 IN.
(68)
0.40 IN.
- 0.50 IN.
OUTBD T  →FWD
LOOKING FORWARD  VIEW N-N  2020676
FIGURE 1: EXTENDED WING TO FUSELAGE FILLETS - INSTALLATION OF BONDING STRAPS
(SHEET 13 OF 19)
Original Issue: December 24, 1979
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Copyright © Unpublished Work - See page 1 for details.  50 of 122

### Page 51 (OCR)

BOEING SERVICE BULLETIN DC10-53-109
3 EQUAL
SPACES
- 0.31  - 0.31
0.38
Z=-50.000
2.10 + .25
62 63 64 65
40 + .25
FWD
0-0
VIEW LOOKING OUTBOARD  2041761
FIGURE 1: EXTENDED WING TO FUSELAGE FILLETS - INSTALLATION OF BONDING STRAPS
(SHEET 14 OF 19)
Original Issue: December 24, 1979
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### Page 52

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.
2SR10530059-3Strap AssemblyLocate3
(b) (f)
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.
2SR10530059-3Strap AssemblyLocate8
(b) (f)
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
FIGURE 1: EXTENDED WING TO FUSELAGE FILLETS - INSTALLATION OF BONDING STRAPS
(SHEET 15 OF 19)
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DC10-53-109Revision 8 March 10, 2011
52 of 122
BOEING SERVICE BULLETIN DC10-53-109

### Page 53

MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
Mark hole positions for fas-
teners.
2SB10530109-41AngleLocate14
0.144/0.147 inch diameter
in former.
4-HolesDrill/Deburr15
(f)-Alodine 1200SChemical Conversion
Coating
Apply16
Between former and web.2SB10530109-41AngleInstall17
4NAS1738B4-2Rivet
Mark hole positions for fas-
teners.
2SR10530059-27Strap AssemblyLocate18
(b) (f)
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
(g)
Mark hole positions for fas-
teners.
2SB10530109-39AngleLocate24
(g)
0.144/0.147 inch diameter
in former.
8-HolesDrill/Deburr25
(g)
(f) (g)-Alodine 1200SChemical Conversion
Coating
Apply26
Between stiffener and for-
mer.
2
8
SB10530109-39
NAS1738B4-2
Angle
Rivet
Install27
(g)
Mark hole positions for fas-
teners.
2SR10530059-13Strap AssemblyLocate28
(b) (f) (g)
FIGURE 1: EXTENDED WING TO FUSELAGE FILLETS - INSTALLATION OF BONDING STRAPS
(SHEET 16 OF 19)
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Original Issue: December 24, 1979
DC10-53-109Revision 8 March 10, 2011
53 of 122
BOEING SERVICE BULLETIN DC10-53-109

### Page 54

MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
0.1605/0.1625 inch diame-
ter.
8-HolesDrill/Deburr29
(g)
(f) (g)-Alodine 1200SChemical Conversion
Coating
Apply30
(b) (e) (f) (g)2SR10530059-13Strap AssemblyInstall31
8HL328-5-3Pin
8NAS1149FN816PWasher
8MS21042L08Nut
(f) (g)-FRPrimerApply32
-PR-1422 B-2Sealant
Drill out 2 rivets in each rib.1ANB7484-25RibDrill/Deburr33
(h)1ANB7484-26
Mark hole positions for fas-
teners.
2SB10530109-39AngleLocate34
(h)
0.144/0.147 inch diameter
in former.
8-HolesDrill/Deburr35
(h)
(f) (h)-Alodine 1200SChemical Conversion
Coating
Apply36
Between rib and former.2SB10530109-39AngleInstall37
(h)8NAS1738B4-2Rivet
Mark hole positions for fas-
teners.
2SR10530059-13Strap AssemblyLocate38
(b) (f) (h)
0.1605/0.1625 inch diame-
ter.
8-HolesDrill/Deburr39
(h)
(f) (h)-Alodine 1200SChemical Conversion
Coating
Apply40
(b) (e) (f) (h)2SR10530059-13Strap AssemblyInstall41
8HL328-5-3Pin
8NAS1149FN816PWasher
8MS21042L08Nut
(f) (h)-FRPrimerApply42
-PR-1422 B-2Sealant
Mark hole positions for fas-
teners.
2SB10530109-37AngleLocate43
FIGURE 1: EXTENDED WING TO FUSELAGE FILLETS - INSTALLATION OF BONDING STRAPS
(SHEET 17 OF 19)
BOEING PROPRIETARY -
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Original Issue: December 24, 1979
DC10-53-109Revision 8 March 10, 2011
54 of 122
BOEING SERVICE BULLETIN DC10-53-109

### Page 55

MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
0.144/0.147 inch diameter
in former.
8-HolesDrill/Deburr44
(f)-Alodine1200SChemical Conversion
Coating
Apply45
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
(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
(f)-Alodine 1200SChemical Conversion
Coating
Apply54
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
FIGURE 1: EXTENDED WING TO FUSELAGE FILLETS - INSTALLATION OF BONDING STRAPS
(SHEET 18 OF 19)
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BOEING SERVICE BULLETIN DC10-53-109

### Page 56

MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
(b)2SR10530059-29BracketLocate62
0.1605/0.1625 inch diame-
ter.
8HolesDrill/Deburr63
(f)Alodine 1200SChemical Conversion
Coating
Apply64
(f)2SR10530059-29BracketInstall65
8NAS1738E4-2Rivet
(b)2SR10530059-13Strap AssemblyLocate66
0.1605/0.1625 inch diame-
ter.
8HolesDrill/Deburr67
(f)Alodine 1200SChemical Conversion
Coating
Apply68
(f)2SR10530059-13Strap AssemblyInstall69
8HL328-5-3Pin
8NAS1149FN816PWasher
8MS21042L08Nut
-1ANB7483-1Fillet AssemblyInstall70
1ANB7483-2
(d)-DMS 1819SealantApply71
1ANB7489-1Door AssemblyClose72
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.
(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.
(g) Applicable to Groups 1 and 3 only.
(h) Applicable to Groups 2 and 4 only.
FIGURE 1: EXTENDED WING TO FUSELAGE FILLETS - INSTALLATION OF BONDING STRAPS
(SHEET 19 OF 19)
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: December 24, 1979
DC10-53-109Revision 8 March 10, 2011
56 of 122
BOEING SERVICE BULLETIN DC10-53-109

### Page 57 (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)
1 92 93
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  IF (BEFORE)
(BEFORE)  →G (SHEET 13)  H (SHEET 15)  (AFTER)
STA  (SHEET 9)  (AFTER)  •F (AFTER)  (SHEET 11)  (AFTER)
Z=-40.000
(SHEET 6)
STA  (BEFORE)
Z=-45.720
D<  (SHEET 16)
(SHEET 7)  IJ (BEFORE)  (SHEET 4)
STA  (AFTER)  1C (BEFORE›
Z=-60.000
(SHEET 17)
• (AFTER)
B (SHEET 2)
(BEFORE)
STA
Z=-80.000
(SHEET 5)
ANB7489-1  ANB7489-2 (RS)  (LS) (2  Y94  ¡ (AFTER)  ¡ (SHEET 3)
FWD C  DOOR ASSY (REF)  (AFTER)  U55022
VIEW A-A
FIGURE 2: EXTENDED WING TO FUSELAGE FILLETS - REPLACEMENT OF BONDING STRAPS
(SHEET 1 OF 26)
Original Issue: December 24, 1979
Revision 8 March 10, 2011  BOEING PROPRIETARY -  DC10-53-109
Copyright © Unpublished Work - See page 1 for details.  57 of 122

### Page 58 (OCR)

BOEING SERVICE BULLETIN DC10-53-109
ANB7547-19 (LS)  ANB7547-20 (RS)  SB10530109-5 (LS)  SB10530109-6 (RS)  STA  Z=-70.000  (5 PLACES)
STRAP (REF)
OR  OUTBDEWD
(4 PLACES)
STA  Y=1139.000  ANB7488-3 (LS)  ANB7488-4 (RS)  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)
ARB7127-3 (LS)  ARB7127-4 (RS)  FORMER (REF)  STA  Y=1139.000  ANB7488-3 (LS)  ANB7488-4 (RS)  RIB (REF)
U56281
FIGURE 2: EXTENDED WING TO FUSELAGE FILLETS - REPLACEMENT OF BONDING STRAPS
(SHEET 2 OF 26)
Original Issue: December 24, 1979
Revision 8 March 10, 2011  BOEING PROPRIETARY -  DC10-53-109
Copyright © Unpublished Work - See page 1 for details.  58 of 122

### Page 59 (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)
9
(2 PLACES)
STA
Z=-70.000
8 10
-0.44 IN.
-ANB7488-3 (LS)
ANB7488-4  (RS)
RIB (REF)
(3 PLACES)
0.50 IN.
OUTBD<  →FWD  VIEW B-B
AFTER MODIFICATION
LOOKING FORWARD
STRAP INSTALLATION MAY VARY SLIGHTLY PER AIRPLANE
FIGURE 2: EXTENDED WING TO FUSELAGE FILLETS - REPLACEMENT OF BONDING STRAPS
(SHEET 3 OF 26)
Original Issue: December 24, 1979
Revision 8 March 10, 2011  BOEING PROPRIETARY -  DC10-53-109
Copyright © Unpublished Work - See page 1 for details.  59 of 122

### Page 60 (OCR)

BOEING SERVICE BULLETIN DC10-53-109
ARB7127-3 (LS)  ARB7127-4 (RS)  FORMER (REF)  (LS)  ANB7547-21  ANB7547-22 (RS)  OR  SB10530109-7 (LS)  (RS)  SB10530109-8  STRAP (REF)  STA  Z=-70.000
(4 PLACES)  STA  Z=-60.000
STA  Y=1119.000  STA  X=120.000  (5 PLACES)  STRAP INSTALLATION MAY VARY SLIGHTLY PER AIRPLANE
OUTBO FWD  ANB7547-5 (LS)  ANB7547-6 (RS)  OR  ANB7487-3 (LS)  ANB7487-4 (RS)  RIB (REF)  VIEW C-C  BEFORE MODIFICATION  LOOKING FORWARD
STRAP (REF)  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 (LS)  ANB7487-4  RIB (REF)  U56863
FIGURE 2: EXTENDED WING TO FUSELAGE FILLETS - REPLACEMENT OF BONDING STRAPS
(SHEET 4 OF 26)
Original Issue: December 24, 1979
Revision 8 March 10, 2011  BOEING PROPRIETARY -  DC10-53-109
Copyright © Unpublished Work - See page 1 for details.  60 of 122

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