# Boeing Service Bulletin DC10-53-111: Boeing - 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 DC10-53-111](https://openairdocs.org/service-documents/boeing/dc10-53-111.md)
- Title as filed: Boeing - Service Bulletin
- Pages: 66
- PDF: https://openairdocs.org/files/sha256/d6/2a/d62ac7c2b0baf155cad73d3543f7539fab8cac1a83d61785f515a9fab0d46af2
- Page: https://openairdocs.org/service-documents/boeing/dc10-53-111/file/d62ac7c2b0ba

## Text

Some pages are OCR from a scan. OCR can misread letters and numbers. Each page's text from the PDF; open the PDF at a page with #page=N.

### Page 1

Commercial 
Airplanes
DC10
Service Bulletin
Number: DC10-53-111
Original Issue: December 05, 1980
Revision 7: March 16, 2011
ATA System: 5350
SUBJECT: FUSELAGE - Aerodynamic Fairings - Install Electrical Bonding Straps on Conventional
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Unpublished Work - All Rights Reserved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.
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: December 05, 1980
DC10-53-111Revision 7: March 16, 2011
1 of 66
4.0

### Page 2

BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: December 05, 1980
DC10-53-111Revision 7: March 16, 2011
2 of 66
BOEING SERVICE BULLETIN DC10-53-111
BLANK PAGE

### Page 3

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 5
B. Concurrent Requirements ...................................... 1 5
C. Reason ................................................ 1 5
D. Description .............................................. 1 6
E. Compliance .............................................. 1 7
F. Approval ............................................... 1 7
G. Manpower .............................................. 1 8
H. Weight and Balance Changes .................................... 1 9
I. Electrical Load Data ......................................... 1 9
J. References .............................................. 1 9
1. Existing Data: ......................................... 1 9
2. Data supplied with this Service Bulletin: ........................... 1 9
3. Installation Drawings Used in the Preparation of this Service Bulletin: ........... 1 9
K. Publications Affected ........................................ 2 0
L. Interchangeability and Intermixability of Parts ........................... 2 0
2. MATERIAL INFORMATION ........................................ 2 1
A. Material - Price and Availability ................................... 2 1
B. Industry Support Information .................................... 2 1
C. Parts Necessary For Each Airplane ................................. 2 1
1. Kits/Parts: ........................................... 2 1
2. Parts and Materials Supplied by the Operator: ........................ 2 2
3. Parts Modified and Reidentified: ............................... 2 3
4. Parts Removed and Not Replaced: .............................. 2 3
D. Parts Necessary to Change Spares ................................. 2 3
E. Special Tooling - Price and Availability ............................... 2 3
F. Special Tooling Necessary to do this Service Bulletin ....................... 2 3
3. ACCOMPLISHMENT INSTRUCTIONS .................................. 2 5
A. GENERAL INFORMATION ..................................... 2 5
B. WORK INSTRUCTIONS ....................................... 2 6
FIGURE 1: CONVENTIONAL WING TO FUSELAGE FILLETS - INSTALLATION OF BONDING STRAPS
[Group 1, Configuration 1] ................................... 2 8
FIGURE 2: CONVENTIONAL WING TO FUSELAGE FILLETS - REPLACEMENT OF BONDING STRAPS
[Group 2, Configuration 1] ................................... 3 7
FIGURE 3: CONVENTIONAL WING TO FUSELAGE FILLETS - REPOSITION ONE BONDING STRAP
AND REPLACEMENT OF FASTENERS [Group 1-2, Configuration 2] ........... 5 6
Appendix A: BONDING STRAP INSTALLATION PROCEDURE ..................... 6 6
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: December 05, 1980
DC10-53-111Revision 7: March 16, 2011
3 of 66
BOEING SERVICE BULLETIN DC10-53-111

### Page 4

BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: December 05, 1980
DC10-53-111Revision 7: March 16, 2011
4 of 66
BOEING SERVICE BULLETIN DC10-53-111
BLANK PAGE

### Page 5

Commercial 
Airplanes
DC10
Service Bulletin
Revision Transmittal SheetNumber: DC10-53-111Original Issue: December 05, 1980
Revision 7: March 16, 2011
ATA System: 5350
SUBJECT: FUSELAGE - Aerodynamic Fairings - Install Electrical Bonding Straps on Conventional
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.
No more work is necessary on the airplane(s) changed in accordance with Revision 6 of this service bulletin.
REASON FOR REVISION
This revision is sent to re-instate one airplane inadvertently dropped from the effectivity of this service bulletin.
These sections were changed:
1. In Paragraph 1.A., Effectivity, reinstated fuselage number 317 into effectivity.
2. In Paragraph 1.E., Compliance, added new Federal Aviation Administration (FAA) Airworthiness Directive
(AD).
3. In Paragraph 1.F. Approval, changed approval statement for newly referenced AD.
4. In Paragraph 1.J.1., Existing Data, added new AD.
5. In Paragraph 1.K., Publications, added Damage Tolerance Based Structural Inspections information.
6. In Paragraph 2.C., Parts Necessary for Each Airplane, changed supplier address.
7. In Paragraph 2.C.2., Parts and Materials Supplied by Operator, changed supplier address.
8. In Paragraph 3.A., General information, added new note.
9. In Figure 1, added information about part number substitution.
10. In Figure 2, added information about part number substitution.
11. In Figure 3, added information about part number substitution.
12. In Appendix, clarified work requirements.
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: December 05, 1980
DC10-53-111Revision 7: March 16, 2011
5 of 66

### Page 6

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 05, 1980Original Issue:
October 07, 1983Revision 1:
November 17, 1986Revision 2:
August 24, 1992Revision 3:
September 21, 2006Revision 4:
March 19, 2008Revision 5:
March 03, 2009Revision 6:
March 16, 2011Revision 7:
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: December 05, 1980
DC10-53-111Revision 7: March 16, 2011
6 of 66
BOEING SERVICE BULLETIN DC10-53-111

### Page 7

Commercial 
Airplanes
DC10
Service Bulletin
SummaryNumber: DC10-53-111Original Issue: December 05, 1980
Revision 7: March 16, 2011
ATA System: 5350
SUBJECT: FUSELAGE - Aerodynamic Fairings - Install Electrical Bonding Straps on Conventional
Wing-to-Fuselage Fillets
CONCURRENT REQUIREMENTS
None.
BACKGROUND
An engineering review of the conventional wing to fuselage fillet by Boeing revealed the requirement for bonding
the fuselage mounted fillet support ribs to the fixed leading edge ribs. In the event of a severe lightning strike,
the integrity of the electrical/electronic components interfaced with the wiring routed through the wing leading
edge could be impaired. This condition is attributed to induced transients being imposed on wiring in the wing
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 4 was the result of the safety assessments conducted by Boeing under a Special
Federal Aviation Ruling (SFAR) 88, Fuel Tank System Fault Tolerance Evaluation Requirements.
ACTION
Group 1, Configuration 1:
Airplanes that have not Previously Accomplished Service Bulletin DC10-53-111
1. Installs ten new braided bonding straps between the metallic frame of the left and right wing to fuselage
fillets and the wing leading edge ribs.
Group 2, Configuration 1:
Airplanes that have not Previously Accomplished Service Bulletin DC10-53-111
1. Replaces ten existing metal bonding straps with ten new braided bonding straps between the metallic frame
of the left and right wing to fuselage fillets and the wing leading edge ribs.
Group 1-2, Configuration 2:
Airplanes that have Previously Accomplished Service Bulletin DC10-53-111
1. Verifies one existing braided bonding strap between the metallic frame of the left and right wing to fuselage
fillets and the wing leading edge ribs is installed correctly and corrects the installation if required. Measures
electrical resistance of previously installed braided bonding straps.
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: December 05, 1980
DC10-53-111Revision 7: March 16, 2011
7 of 66

### Page 8

EFFECTIVITY
DC-10 and MD-10 Airplanes with conventional wing to fuselage fillets. Refer to Paragraph 1.A.1., Airplanes, for
the list of affected airplanes.
Airplane factory serial number 47840 (Number 337) assigned to operator has had the original modification
incorporated at manufacturers facility as an installation verification.
COMPLIANCE
Federal Aviation Administration (FAA) Airworthiness Directive AD 2009-26-17 is related to this service bulletin.
Boeing recommends that this service bulletin be accomplished at the first convenient maintenance period after
receipt of parts, but not to exceed 7500 flight-hours from the issue date of Revision 3 of this service bulletin.
INDUSTRY SUPPORT INFORMATION
Boeing warranty remedies are not available for the configuration changes given in this service bulletin.
MANPOWER
Group 1, Configuration 1:
Elapsed HoursTotal Task HoursAirplanes
8.316.6DC-10 and MD-10
Group 2, Configuration 1:
Elapsed HoursTotal Task HoursAirplanes
12.424.8DC-10 and MD-10
Group 1-2, Configuration 2:
Elapsed HoursTotal Task HoursAirplanes
2.4 - 7.33.8 - 13.4DC-10 and MD-10
MATERIAL INFORMATION
Operator Supplied Parts/Materials.
Refer to Paragraph 2.A., Material - Price and Availability
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: December 05, 1980
DC10-53-111Revision 7: March 16, 2011
8 of 66
BOEING SERVICE BULLETIN DC10-53-111

### Page 9 (OCR)

BOEING SERVICE BULLETIN DC10-53-111
GROUP 1 CONFIG 1:
INSTALLS TEN NEW BRAIDED
BONDING STRAPS ON CONVENTIONAL
WING TO FUSELAGE FILLETS
GROUP 2 CONFIG 1:
REMOVE TEN METAL BONDING STRAPS
AND INSTALLS TEN NEW BRAIDED
BONDING STRAPS ON CONVENTIONAL
WING TO FUSELAGE FILLETS
GROUPS 1-2, CONFIG 2:
REPOSITION ONE BRAIDED BONDING
STRAP ON CONVENTIONAL WING TO
FUSELAGE FILLETS
LEFT SIDE SHOWN
RIGHT SIDE OPPOSITE
Original Issue: December 05, 1980
Revision 7: March 16, 2011  BOEING PROPRIETARY -  DC10-53-111
Copyright © Unpublished Work - See page 1 for details.  9 of 66

### Page 10

BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: December 05, 1980
DC10-53-111Revision 7: March 16, 2011
10 of 66
BOEING SERVICE BULLETIN DC10-53-111
BLANK PAGE

### Page 11

Commercial 
Airplanes
DC10
Service Bulletin
Number: DC10-53-111
Original Issue: December 05, 1980
Revision 7: March 16, 2011
ATA System: 5350
SUBJECT: FUSELAGE - Aerodynamic Fairings - Install Electrical Bonding Straps on Conventional
Wing-to-Fuselage Fillets
1.    PLANNING INFORMATION
A. Effectivity
1. Airplanes
NOTE: This service bulletin is applicable only to airplanes with conventional wing to fuselage
fillets. Airplanes that have installed the Cruise Performance Improvement Package (CPIP)
fillets using Boeing Service Bulletin DC10-53-103 or DC10-53-119 should accomplish
Boeing Service Bulletin DC10-53-109.
This service bulletin is for the airplanes shown below.
DESCRIPTIONCONFIGURATIONGROUP
Airplanes that did not receive metal bonding straps during production.-1
Airplanes that have not previously accomplished Service Bulletin
DC10-53-111.
1
Airplanes that have previously accomplished Service Bulletin
DC10-53-111.
2
Airplanes that received metal bonding straps during production.-2
Airplanes that have not previously accomplished Service Bulletin
DC10-53-111.
1
Airplanes that have previously accomplished Service Bulletin
DC10-53-111.
2
Airplane Models:
DC-10-10, DC-10-10F, DC-10-30, DC-10-30F, DC-10-30F (KDC-10), DC-10-40, DC-10-40F,
MD-10-10F, MD-10-30F
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: December 05, 1980
DC10-53-111Revision 7: March 16, 2011
11 of 66

### Page 12

GroupFuselage Num-
ber
11
22
13 - 21
123 - 28
130 - 32
233
134 - 43
145
147 - 56
257
158 - 59
161 - 62
263
164 - 70
172
273
174
275
176
277 - 78
179 - 80
183
185 - 86
288
189
290 - 91
192
293 - 95
196 - 98
299 - 100
1101 - 103
2104
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: December 05, 1980
DC10-53-111Revision 7: March 16, 2011
12 of 66
BOEING SERVICE BULLETIN DC10-53-111

### Page 13

GroupFuselage Num-
ber
1105 - 106
1108
1110 - 113
1115 - 116
2117
1118 - 120
2121 - 123
1124
2125
1126
2127
1128 - 130
2134 - 135
1136
2137
1138 - 140
2141
1142 - 145
2146
1147 - 148
2149 - 150
1151 - 155
1157
2158
2160
1161 - 169
2170
1173
1175
1177
2178 - 179
1180 - 181
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: December 05, 1980
DC10-53-111Revision 7: March 16, 2011
13 of 66
BOEING SERVICE BULLETIN DC10-53-111

### Page 14

GroupFuselage Num-
ber
2186
2188
1189 - 191
2192 - 193
1194
1196
2197
1198
2199 - 200
2203 - 204
1205
2206
1207 - 211
2212 - 214
1215
2216
2218
2220 - 226
1227
2228 - 231
2235
1237
2239 - 240
1242
2243 - 244
1245
2246
1247 - 250
2251 - 252
1253
2254
1255
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: December 05, 1980
DC10-53-111Revision 7: March 16, 2011
14 of 66
BOEING SERVICE BULLETIN DC10-53-111

### Page 15

GroupFuselage Num-
ber
2256
1257
2258 - 259
2262
2264 - 266
2269
1270 - 271
2272
1273
2274
2276
2278 - 279
2283
2285
2287 - 288
2290
1294
2316
2327
2337
2354
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
None.
C. Reason
An engineering review of the conventional wing to fuselage fillet by Boeing revealed the requirement
for bonding the fuselage mounted fillet support ribs to the fixed leading edge ribs. In the event of a
severe lightning strike, the integrity of the electrical/electronic components interfaced with the wiring
routed through the wing leading edge could be impaired. This condition is attributed to induced transients
being imposed on wiring in the wing root area.
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: December 05, 1980
DC10-53-111Revision 7: March 16, 2011
15 of 66
BOEING SERVICE BULLETIN DC10-53-111

### Page 16

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 4 was the result of the safety assessments conducted by Boeing under a
Special Federal Aviation Ruling (SFAR) 88, Fuel Tank System Fault Tolerance Evaluation Requirements.
Revision 3 was issued to introduce the replacement of the bonding straps installed on Group 2 airplanes.
Revision 4 was sent to incorporate engineering released subsequent to the Revision 3 release of this
service bulletin. This revision added Figures 3 and 4 to show Configuration 2 for airplanes that have
not done this service bulletin. In addition, Figures 3 and 4 changed one bonding strap position to remove
a riding condition and corrected the part numbers of fasteners used to install the bonding straps.
Revision 5 was sent to incorporate changes to define Groups/Configurations subsequent to Revision
4 of this bulletin. This revision changed Figures 1 and 2 and added a new Figure 3 to reposition one
bonding strap. Configurations 1 and 2 added to Groups 1 and 2.
Revision 6 was sent to incorporate comments reported by operators which will clarify service bulletin
instructions. The data given in Information Notice DC10-53-111, IN 01 is included in this revision.
Revision 7 is sent to re-instate one airplane inadvertently dropped from the effectivity of this service
bulletin.
Service Bulletin Revision 4 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 modification accomplishes the following:
Group 1, Configuration 1:
Airplanes that have not Previously Accomplished Service Bulletin DC10-53-111
1. Installs ten new braided bonding straps between the metallic frame of the left and right wing to
fuselage fillets and the wing leading edge ribs.
Group 2, Configuration 1:
Airplanes that have not Previously Accomplished Service Bulletin DC10-53-111
1. Replaces ten existing metal bonding straps with ten new braided bonding straps between the
metallic frame of the left and right wing to fuselage fillets and the wing leading edge ribs.
Group 1-2, Configuration 2:
Airplanes that have Previously Accomplished Service Bulletin DC10-53-111
1. Verifies one existing braided bonding strap between the metallic frame of the left and right wing
to fuselage fillets and the wing leading edge ribs is installed correctly and corrects the installation
if required. Measures electrical resistance of previously installed braided bonding straps.
Revision 7 - No more work is necessary on airplanes changed as shown on Revision 6 of this service
bulletin.
The work in this service bulletin is done in the maintenance zone(s) given below.
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: December 05, 1980
DC10-53-111Revision 7: March 16, 2011
16 of 66
BOEING SERVICE BULLETIN DC10-53-111

### Page 17

Group 1:
Affected Maintenance Zones
ZoneModel
131, 132, 161, 162DC-10-10, DC-10-10F, DC-10-
30, DC-10-30F, DC-10-40, MD-
10-10F, MD-10-30F
Group 2:
Affected Maintenance Zones
ZoneModel
131, 132, 161, 162DC-10-10, DC-10-10F, DC-10-
30, DC-10-30F, DC-10-30F
(KDC-10), DC-10-40, DC-10-
40F, MD-10-10F
E. Compliance
Federal Aviation Administration (FAA) Airworthiness Directive AD 2009-26-17 is related to this service
bulletin.
Boeing recommends that this service bulletin be accomplished at the first convenient maintenance
period after receipt of parts, but not to exceed 7500 flight-hours from the issue date of Revision 3 of
this service bulletin.
F. Approval
For 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), (j), (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
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: December 05, 1980
DC10-53-111Revision 7: March 16, 2011
17 of 66
BOEING SERVICE BULLETIN DC10-53-111

### Page 18

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), (j), (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, Configuration 1:
Elapsed HoursTask HoursNumber of PersonsTask
1.83.62Open Access
4.18.22Install Ten Bonding Straps
2.44.82Close Access
8.316.6TOTAL FOR EACH AIRPLANE
Group 2, Configuration 1:
Elapsed HoursTask HoursNumber of PersonsTask
1.83.62Open Access
8.216.42Remove/Install Ten Bonding Straps
2.44.82Close Access
12.424.8TOTAL FOR EACH AIRPLANE
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: December 05, 1980
DC10-53-111Revision 7: March 16, 2011
18 of 66
BOEING SERVICE BULLETIN DC10-53-111

### Page 19

Group 1-2, Configuration 2:
Elapsed HoursTask HoursNumber of PersonsTask
0.61.22Open Access
0.20.21Verify One Bonding Strap Installed Cor-
rectly
0.81.62Reposition One Bonding Strap if Re-
quired
1.01.01Do Electrical Resistance Check to Previ-
ously Installed Braided Bonding Straps
4.18.22Remove/Clean/Install Braided Bonding
Straps that Failed Resistance Check
(a)
0.61.22Close Access
2.4 - 7.33.8 - 13.4TOTAL FOR EACH AIRPLANE
(a) Hours are a maximum.
H. Weight and Balance Changes
Moment Change
(MEW) IN.-LBS
Mfr's Empty Weight
(MEW) LBS
Approximate Station
(Inches)Airplane
+1467.7+1.31129.0DC10 and MD10
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.
2. Data supplied with this Service Bulletin:
None.
3. Installation Drawings Used in the Preparation of this Service Bulletin:
ChangeTitleDocument Number
DService Rework DrawingSR10530059
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: December 05, 1980
DC10-53-111Revision 7: March 16, 2011
19 of 66
BOEING SERVICE BULLETIN DC10-53-111

### Page 20

K. Publications Affected
1. Publications:
Chapter-SectionPublication
53-15Illustrated Parts Catalog
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.
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.
Original Issue: December 05, 1980
DC10-53-111Revision 7: March 16, 2011
20 of 66
BOEING SERVICE BULLETIN DC10-53-111

### Page 21

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 these methods:
1. Order on-line via ATA Spec 2000 or The Boeing Part Page
2. Fax to (206) 662-7145
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:
To get the kits/parts shown below, refer to Paragraph 2.A., Material - Price and Availability.
NOTE: One top kit and the items shown in Paragraph 2.C.2., Parts and Materials Supplied by
the Operator, are necessary for each airplane.
NotesExisting Part NumberNameQTYNew Part Number
--PIN38HL328-5-3
--PIN2HL328-8-3
--NUT38MS21042L08
--NUT2MS21042L4
--WASHER2NAS1149F0432P
--WASHER38NAS1149FN816P
(a) (b) (c) (d)SB10530111-7/-8STRAP ASSEMBLY2SR10530059-13
or
ANB7553-27/-28
or
ANB7553-7/-8
or
ANB7553-17N/-18N
(a) (b) (c) (d)SB10530111-3/-4STRAP ASSEMBLY2SR10530059-15
or
ANB7553-3/-4
or
ANB7553-23/-24
or
ANB7553-13N/-14N
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: December 05, 1980
DC10-53-111Revision 7: March 16, 2011
21 of 66
BOEING SERVICE BULLETIN DC10-53-111

### Page 22

NotesExisting Part NumberNameQTYNew Part Number
(a) (b) (c) (d)SB10530111-11/-12STRAP ASSEMBLY2SR10530059-19
or
ANB7553-31/-32
or
ANB7553-11/-12
or
ANB7553-21N/-22N
(a) (b) (c) (d)SB10530111-5/-6 or -9/-10STRAP ASSEMBLY4SR10530059-21
or
ANB7553-5/-6 or -29/-30
or
ANB7553-25/-26 or -9/-10
or
ANB7553-15N/-16N or 19N/-20N
Discard the existing part.(a)
You cannot use the existing part to replace the new or changed part.(b)
At operator's option - Bonding straps may be fabricated from NEQL48830 overbraid in accordance with
Service Rework Drawing SR10530059.
(c)
CAGECooner Manufacturer CompanyNEQL48830 overbraid can be obtained from:(d)
637949265 Owensmouth Avenue
Chatsworth, California 91311
2. Parts and Materials Supplied by the Operator:
Group 1 - 2
NotesNameQTYPart Number / Specification
(a)Rivet68NAS1738E4-2
(a)Rivet68NAS1739E4-2
(a)Rivet4MS20470AD3-4
(b)Bracket2TA4074D0616
(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
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: December 05, 1980
DC10-53-111Revision 7: March 16, 2011
22 of 66
BOEING SERVICE BULLETIN DC10-53-111

### Page 23

CAGE
73197
Hi-Shear Corporation
2600 Skypark Drive
(a) Can be obtained from:
Torrance, California 90505-5373
84971Kirkhill-TA Corporation Division TA Aerospace(b) Can be obtained from:
28065 Franklin Parkway
Valencia, California 91355-4117
92108PRC-DeSoto International, Incorporated(c) Can be obtained from:
P.O. Box 1800
Sylmar, California 91342
3. Parts Modified and Reidentified:
None.
4. Parts Removed and Not Replaced:
NotesQTYNameExisting Part Number
2BracketTA10B18D-8-28
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.
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: December 05, 1980
DC10-53-111Revision 7: March 16, 2011
23 of 66
BOEING SERVICE BULLETIN DC10-53-111

### Page 24

BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: December 05, 1980
DC10-53-111Revision 7: March 16, 2011
24 of 66
BOEING SERVICE BULLETIN DC10-53-111
BLANK PAGE

### Page 25

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. 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.
5. Obey all of the warnings and cautions given in the specified manual sections.
6. 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.
7. At operator's option fabricate bonding straps as shown on Service Rework Drawing
SR10530059.
8. 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.
9. 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.
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: December 05, 1980
DC10-53-111Revision 7: March 16, 2011
25 of 66
BOEING SERVICE BULLETIN DC10-53-111

### Page 26

B. WORK INSTRUCTIONS
1. Remove and keep 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.
Group 1, Configuration 1:
(Airplanes that have not previously done Service Bulletin DC10-53-111)
a. Install ten new braided bonding straps 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 2, Configuration 1:
(Airplanes that have not previously done Service Bulletin DC10-53-111)
a. Remove ten metal bonding straps and install ten new braided bonding straps in accordance
with Figure 2.
Group 1-2, Configuration 2:
(Airplanes that have previously done Service Bulletin DC10-53-111)
a. Do a general visual inspection and verify braided bonding strap is installed in accordance with
Figure 3, sheet 7 of 9. Based on inspection results do as follows:
Braided Bonding Strap is Installed Correctly
(1) Go to next step.
Braided Bonding Strap is not Installed Correctly
(1) Reposition braided bonding strap and replace fasteners in accordance with Figure 3,
steps 6 through 13.
b. Measure electrical resistance across each bonding joint of braided strap assemblies previously
installed in original release through revision 4 of this service bulletin. Refer to SWPM 20-50-01,
Paragraph 3.A. Verify brackets have an acceptable fillet seal. Locations of braided strap
assemblies are shown in Figure 3. Based on results do as follows:
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: December 05, 1980
DC10-53-111Revision 7: March 16, 2011
26 of 66
BOEING SERVICE BULLETIN DC10-53-111

### Page 27

Electrical Resistance Test fails or Brackets have Damaged or Missing Fillet Seal
(1) Remove braided bonding strap assembly.
(2) Clean and install braided bonding strap assembly in accordance with applicable step in
Figure 3 and Appendix A.
Electrical Resistance Test Passes and Brackets have Acceptable Fillet Seal
(1) No further work required.
2. Install left side access panels 515AB, 515BB and right side access panels 615AB, 615BB. Refer
to DC-10 AMM 06-35-00 and DC-10 AMM 06-36-00.
3. Put the airplane back to a serviceable condition.
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: December 05, 1980
DC10-53-111Revision 7: March 16, 2011
27 of 66
BOEING SERVICE BULLETIN DC10-53-111

### Page 28 (OCR)

BOEING SERVICE BULLETIN DC10-53-111
This Figure applies only to: Group 1, Configuration 1.
LEFT SIDE SHOWN
RIGHT SIDE OPPOSITE
STA
Y=1139.000
STA  STA  STA  STA
Y=1099.000  Y=1109.000 Y=1119.000  Y=1129.000
STA
Z=-30.000
(SHEET 6);
(SHEET 5)
STA
Z=-40.000
(SHEET 7
STA
Z=-50.000
ARB1297-3 (LS)
ARB1297-4 (RS)
(SHEET 4)  FORMER (REF)
STA
Z=-60.000
(SHEETS 2-3)
B F
STA
Z=-70.000
FWD <
ANB7257-1 (LS)
ANB7257-2 (RS)
DOOR ASSY (REF)  U69178
A-A
FIGURE 1: CONVENTIONAL WING TO FUSELAGE FILLETS - INSTALLATION OF BONDING STRAPS
(SHEET 1 OF 9)
Original Issue: December 05, 1980
Revision 7 March 16, 2011  BOEING PROPRIETARY -  DC10-53-111
Copyright © Unpublished Work - See page 1 for details.  28 of 66

### Page 29 (OCR)

BOEING SERVICE BULLETIN DC10-53-111
ARB1297-3 (LS)
ARB1297-4 (RS)
FORMER (REF)
ANB7068-17 (LS)
ANB7068-18 (RS)
STIFFENER (REF)
STA
X=119.900
STA
STA  X=118.200
Z=-70.000
OUTBD
STA  • FWD
Y=1139.000
B-B
BEFORE MODIFICATION
(LOOKING AFT)
1355963
FIGURE 1: CONVENTIONAL WING TO FUSELAGE FILLETS - INSTALLATION OF BONDING STRAPS
(SHEET 2 OF 9)
Original Issue: December 05, 1980
Revision 7 March 16, 2011  DC10-53-111
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.  29 of 66

### Page 30 (OCR)

BOEING SERVICE BULLETIN DC10-53-111
ARB1297-3 (LS)  ARB1297-4 (RS)  30  460
FORMER (REF)
ANB7068-17 (LS)  £ 0.90 IN.
ANB7068-18 (RS)
STIFFENER (REF)
-0.50 IN.
0.40 IN.
STA
x=119.900
5X7
STA
STA  x=118.200
Z=-70.000
246
STA
Y=1139.000
B-B
AFTER MODIFICATION
(LOOKING AFT)
FIGURE 1: CONVENTIONAL WING TO FUSELAGE FILLETS - INSTALLATION OF BONDING STRAPS
(SHEET 3 OF 9)
Original Issue: December 05, 1980
Revision 7 March 16, 2011  BOEING PROPRIETARY -  DC10-53-111
Copyright © Unpublished Work - See page 1 for details.  30 0f 66

### Page 31 (OCR)

BOEING SERVICE BULLETIN DC10-53-111
STA
Y=1123.530
2.720 IN.
113
10)
0.44 IN.
OUTBD
D-D  ANB7069-5  (LS)
ANB7069-6  (RS)
STIFFENER  (REF)
STA
Y=1119.000
ARB1297-3 (LS)  STA
ARB1297-4 (RS)  Z=-60.000
FORMER (REF)
• STA
Z=-61.650
STA  0.44 IN.
X=119.900  (12) 14)
STA
X=118.200
D13
OUTBD  FWD
c-c  1352737
LOOKING FORWARD
FIGURE 1: CONVENTIONAL WING TO FUSELAGE FILLETS - INSTALLATION OF BONDING STRAPS
(SHEET 4 OF 9)
Original Issue: December 05, 1980
Revision 7 March 16, 2011  BOEING PROPRIETARY -  DC10-53-111
Copyright © Unpublished Work - See page 1 for details.  31 of 66

### Page 32 (OCR)

BOEING SERVICE BULLETIN DC10-53-111
ANB7067-3 (LS)
ANB7067-4 (RS)
RIB (REF)
16) 18
STA
X=118.200
0.38 IN.
STA
STA
Z=-30.000  x=119.000
0.35 IN.
LONGN 29
STA
Y=1139.000
0.40 IN.
15 18
ARB1297-3 (LS)
ARB1297-4 (RS)  17/19
FORMER (REF)
16 18)  0.38 IN.
OUTBD O FWD
E-E
LOOKING UP AND FORWARD
FIGURE 1: CONVENTIONAL WING TO FUSELAGE FILLETS - INSTALLATION OF BONDING STRAPS
(SHEET 5 OF 9)
Original Issue: December 05, 1980
Revision 7 March 16, 2011  DC10-53-111
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.  32 of 66

### Page 33 (OCR)

BOEING SERVICE BULLETIN DC10-53-111
(20 21) 22)
(24 25)  28 30
STA
Y=1118.200
- 0.30 IN.
0.44 IN..
0.44 IN.
ANB7135-3 (LS)
ANB7135-4  (RS)
RIB (REF)
STA
Z=-40.000
0.50 IN.
0.44 IN.
ANB1297-3 (LS)  STA
ANB1297-4 (RS)  X=118.200
FORMER (REF)
STA
X=119.000
AFT OUTBD  LOOKING UP AND AFT  F-F  U69182
FIGURE 1: CONVENTIONAL WING TO FUSELAGE FILLETS - INSTALLATION OF BONDING STRAPS
(SHEET 6 OF 9)
Original Issue: December 05, 1980
Revision 7 March 16, 2011  DC10-53-111
Copyright © Unpublished Work - See page 1 for details.  BOEING PROPRIETARY -  33 of 66

### Page 34

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
Refer to DC-10 AMM 06-35-00 and DC-
10 AMM 06-36-00.
1
1
ANB7257-1
ANB7257-2
Door AssemblyOpen1
Remove 2 rivets from each stiffener.2ANB7068-17StiffenerDrill2
2ANB7068-18
Mark hole positions for fasteners. (a) (c)2SR10530059-15Strap AssemblyLocate3
0.1605/0.1625-inch diameter.8-HolesDrill/Deburr4
(c)-Alodine 1200SChemical Con-
version Coating
Apply5
(a) (c)2SR10530059-15Strap AssemblyInstall6
8HL328-5-3Pin
8NAS1149FN816PWasher
80MS21042L08Nut
(c)- -FR PR-1422 B-2Primer SealantApply7
Remove 2 rivets from each stiffener.2ANB7069-5StiffenerDrill8
2ANB7069-6
Mark hole positions for fasteners. (a) (c)2SR10530059-13Strap AssemblyLocate9
0.1605/0.1625-inch diameter.6-HolesDrill/Deburr10
Pick up on existing holes and open holes
to 0.2450/0.2470-inch diameter.
2-HolesDrill/Deburr11
(c)-Alodine 1200SChemical Con-
version Coating
Apply12
Install Pin HL328-8-3, Washer
NAS1149F0432P and Nut MS21042L4
(1 off of each) in the corner hole of bond-
ing strap attached to each former. (a) (c)
2
6
2
6
SR10530059-13
HL328-5-3
HL328-8-3
NAS1149FN816P
Strap Assembly
Pin
Pin
Washer
Install13
2NAS1149F0432PWasher
6MS21042L08Nut
2MS21042L4Nut
(c)- -FR PR-1422 B-2Primer SealantApply14
Mark hole positions for fasteners. (a) (c)2SR10530059-21Strap AssemblyLocate15
0.1605/0.162-inch diameter.8-HolesDrill/Deburr16
FIGURE 1: CONVENTIONAL WING TO FUSELAGE FILLETS - INSTALLATION OF BONDING STRAPS
(SHEET 7 OF 9)
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: December 05, 1980
DC10-53-111Revision 7 March 16, 2011
34 of 66
BOEING SERVICE BULLETIN DC10-53-111

### Page 35

MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
(c)-Alodine 1200SChemical Con-
version Coating
Apply17
(a) (c) (d)2SR10530059-21Strap AssemblyInstall18
8HL328-5-3Pin
8NAS1149FN816PWasher
8MS21042L08Nut
(c)- -FR PR-1422 B-2Primer SealantApply19
Drill out 2 rivets in bracket TA10B18D-8-
28 attached to each rib.
2ANB7135-3/-4RibDrill20
-2TA10B18D-8-28BracketRemove21
(b)4-HolesFill22
Mark hole positions for fasteners.2TA4074D0616BracketLocate23
No. 40 diameter.4-HolesDrill/Deburr24
To the edge of the holes.-Alodine 1200SChemical Con-
version Coating
Apply25
-2TA4074D0616BracketInstall26
4MS20470AD3-4Rivet
Mark hole positions for fasteners. (a) (c)2SR10530059-21Strap AssemblyLocate27
0.1605/0.1625-inch diameter.8-HolesDrill/Deburr28
(c)-Alodine 1200SChemical Con-
version Coating
Apply29
(a) (c) (d)2SR10530059-21Strap AssemblyInstall30
8HL328-5-3Pin
8NAS1149FN816PWasher
8MS21042L08Nut
(c)- -FR PR-1422 B-2Primer SealantApply31
Mark hole positions for fasteners. (a)2SR10530059-19Strap AssemblyLocate32
0.1605/0.1625-inch diameter.8-HolesDrill/Deburr33
(c)-Alodine 1200SChemical Con-
version Coating
Apply34
(a) (c)2SR10530059-19Strap AssemblyInstall35
8HL328-5-3Pin
8NAS1149FN816PWasher
8MS21042L08Nut
(c)- -FR PR-1422 B-2Primer SealantApply36
Refer to DC-10 AMM 06-35-00 and DC-
10 AMM 06-36-00.
1
1
ANB7257-1
ANB7257-2
Door AssemblyClose37
FIGURE 1: CONVENTIONAL WING TO FUSELAGE FILLETS - INSTALLATION OF BONDING STRAPS
(SHEET 8 OF 9)
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: December 05, 1980
DC10-53-111Revision 7 March 16, 2011
35 of 66
BOEING SERVICE BULLETIN DC10-53-111

### Page 36

MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
(a) 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.
(b) Apply alodine 1200S around the edge of each hole. Determine whether the installation of a protruding
head fastener (NAS1738E4-2) adjacent to the strap installation will interfere with the strap installation. If it
does interfere install a countersink rivet NAS1739E4-2. If there is no interference install NAS1738E4-2.
(c) Refer to Appendix A for bonding installation procedure.
(d) Operators may substitute SR10530059-27 strap assembly, if/as required, to prevent wire strain.
Note: Changing P/N SR10530058-17 strap with P/N SR10530059-23 strap is equivalent to substituting strap
assembly part numbers. If changing strap only part numbers, verify electrical bonding between strap and
brackets in accordance with SWPM 20-50-01 .
FIGURE 1: CONVENTIONAL WING TO FUSELAGE FILLETS - INSTALLATION OF BONDING STRAPS
(SHEET 9 OF 9)
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: December 05, 1980
DC10-53-111Revision 7 March 16, 2011
36 of 66
BOEING SERVICE BULLETIN DC10-53-111

### Page 37 (OCR)

BOEING SERVICE BULLETIN DC10-53-111
This Figure applies only to: Group 2, Configuration 1.
LEFT SIDE SHOWN
RIGHT SIDE OPPOSITE
STA
Y=1139.000
STA  Y=1109.000  STA  Y=1119.000  STA  Y=1129.000  STA  → G (BEFORE)
Y=1099.000  (SHEET 8)
OR
STA  (BEFORE) I  F (BEFORE)
Z=-30.000  (SHEET 11)  (SHEET 7)
OR
(BEFORE)H  F (AFTER)
(SHEET 10)  (SHEET 9)
OR
STA  G (AFTER)
Z=-40.000  (BEFORE)K  (SHEET 9)
(SHEET 14)
OR /  H (AFTER)  ARB1297-3 (LS)
(BEFORE) J  (SHEET 12)  ARB1297-4 (RS)
STA  (SHEET 13)  OR  FORMER (REF)
Z=-50.000  I (AFTER)
(SHEET 12)
STA  D (BEFORE)  C (BEFORE)
Z=-60.000  (SHEET 5)  (SHEET 3)
(AFTER) J  OR
(SHEET 15) |  • B (BEFORE)
(BEFORE)K  OR  + D (AFTER)  ==  (SHEET 2)
STA  (SHEET 15)  (SHEET 6)
Z=-70.000
B (AFTER)
ANB7257-1 (LS) 1  (SHEET 4)
ANB7257-2 (RS)  OR
DOOR ASSY (REF)  FWD<  A-A  C (AFTER)
(SHEET 4)
FIGURE 2: CONVENTIONAL WING TO FUSELAGE FILLETS - REPLACEMENT OF BONDING STRAPS
(SHEET 1 OF 19)
Original Issue: December 05, 1980
Revision 7 March 16, 2011  BOEING PROPRIETARY .  DC10-53-111
Copyright © Unpublished Work - See page 1 for details.  37 of 66

### Page 38 (OCR)

BOEING SERVICE BULLETIN DC10-53-111
ARB1297-3 (LS)
ARB1297-4 (RS)
FORMER (REF)
(2) (4 PLACES)
(2) (5 PLACES)
STA
Y=1139.000
ANB7068-17 (LS)
ANB7068-18 (RS)  000  STA
STIFFENER (REF)  X=119.900
STA
STA  X=118.200
Z=-70.000
1 OUTBD
FWD
B—B
BEFORE MODIFICATION
LOOKING AFT
INSTALLATION MAY VARY SLIGHTLY PER AIRPLANE
FIGURE 2: CONVENTIONAL WING TO FUSELAGE FILLETS - REPLACEMENT OF BONDING STRAPS
(SHEET 2 OF 19)
Original Issue: December 05, 1980
Revision 7 March 16, 2011  BOEING PROPRIETARY -  DC10-53-111
Copyright © Unpublished Work - See page 1 for details.  38 of 66

### Page 39 (OCR)

BOEING SERVICE BULLETIN DC10-53-111
• ARB1297-3 (LS)
ARB1297-4 (RS)
FORMER (REF)
2) (4 PLACES)
2) (5 PLACES)
STA
Y=1139.000
ANB7068-17 (LS)
ANB7068-18 (RS)  STA
STIFFENER (REF)  X=119.900
STA
STA  X=118.200
Z=-70.000
OUTBD
> FWD
C-C
BEFORE MODIFICATION
LOOKING AFT
INSTALLATION MAY VARY SLIGHTLY PER AIRPLANE  U73524
FIGURE 2: CONVENTIONAL WING TO FUSELAGE FILLETS - REPLACEMENT OF BONDING STRAPS
(SHEET 3 OF 19)
Original Issue: December 05, 1980
Revision 7 March 16, 2011  DC10-53-111
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.  39 of 66

### Page 40 (OCR)

BOEING SERVICE BULLETIN DC10-53-111
•ARB1297-3 (LS)
ARB1297-4 (RS)
FORMER (REF)
ANB7068-17 (LS)
ANB7068-18 (RS)
STIFFENER (REF)
0.40 IN.
STA  -0.90 IN.
Y=1139.000
STA
X=119.900
STA
STA  x=118.200
Z=-70.000
(6x8)
B—B
C-C
AFTER MODIFICATION
LOOKING AFT
INSTALLATION MAY VARY SLIGHTLY PER AIRPLANE
FIGURE 2: CONVENTIONAL WING TO FUSELAGE FILLETS - REPLACEMENT OF BONDING STRAPS
(SHEET 4 OF 19)
Original Issue: December 05, 1980
Revision 7 March 16, 2011  DC10-53-111
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.  40 of 66

### Page 41 (OCR)

BOEING SERVICE BULLETIN DC10-53-111
ARB1297-17 (LS)
ARB1297-18 (RS)
FORMER (REF)
ARB1297-3 (LS)
ARB1297-4 (RS)
FORMER (REF)
STA
Y=1123.530
(4 PLACES)
10 12
STA
Y=1119.000
ANB7069-5 (LS)
ANB7069-6 (RS)
STIFFENER (REF)
006"6 LL=X
(10 (5 PLACES)
002*8LL=X
OUTBO SENO
D-D
BEFORE MODIFICATION
INSTALLATION MAY VARY SLIGHTLY PER AIRPLANE  LOOKING FORWARD  U73526
FIGURE 2: CONVENTIONAL WING TO FUSELAGE FILLETS - REPLACEMENT OF BONDING STRAPS
(SHEET 5 OF 19)
Original Issue: December 05, 1980
Revision 7 March 16, 2011  BOEING PROPRIETARY -  DC10-53-111
Copyright © Unpublished Work - See page 1 for details.  41 of 66

### Page 42 (OCR)

BOEING SERVICE BULLETIN DC10-53-111
STA
Y=1123.530
18
ARB1297-17 (LS)-
ARB1297-18 (RS)  13 117
FORMER (REF)
ARB1297-3 (LS)  0.44 IN.
ARB1297-4 (RS)
FORMER (REF)  ANB7069-5 (LS)
ANB7069-6 (RS)
STIFFENER (REF)
STA
Y=1119.000
_ STA
Z=-60.000
- STA
Z=-61.650
16 18)
STA  0.44 IN.
X=119.900
STA
X=118.200
2.720 IN.
OUTBD  D-D  OUTBD ,
LOOKING FORWARD
E-E  AFTER MODIFICATION  1352736
INSTALLATION MAY VARY SLIGHTLY PER AIRPLANE
FIGURE 2: CONVENTIONAL WING TO FUSELAGE FILLETS - REPLACEMENT OF BONDING STRAPS
(SHEET 6 OF 19)
Original Issue: December 05, 1980
Revision 7 March 16, 2011  DC10-53-111
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.  42 of 66

### Page 43 (OCR)

BOEING SERVICE BULLETIN DC10-53-111
ANB7067-3 (LS)
ANB7067-4 (RS)
RIB (REF)
STA
X=118.200
(19 (3 PLACES)
STA  STA
Z=-30.000  X=119.900  STA
Y=1139.000
20
(19) (4 PLACES)
ARB1297-3 (LS)
ARB1297-4 (RS)  21) (2 PLACES)
FORMER (REF)
OUTBD FWD
F-F
BEFORE MODIFICATION
LOOKING UP AND FORWARD
INSTALLATION MAY VARY SLIGHTLY PER AIRPLANE
U73529
FIGURE 2: CONVENTIONAL WING TO FUSELAGE FILLETS - REPLACEMENT OF BONDING STRAPS
(SHEET 7 OF 19)
Original Issue: December 05, 1980
Revision 7 March 16, 2011  BOEING PROPRIETARY -  DC10-53-111
Copyright © Unpublished Work - See page 1 for details.  43 of 66

### Page 44 (OCR)

BOEING SERVICE BULLETIN DC10-53-111
ARB7067-3 (LS)
ARB7067-4 (RS)
OR
ANB1297-3 (LS)
ANB1297-4 (RS)
RIB (REF)
STA
X=118.200
19) (3 PLACES)
STA
STA
Z=-30.000  X=119.900  STA
.Y=1139.000
21
20
19) (4 PLACES)
ARB1297-3 (LS)
ARB1297-4 (RS)  21) (2 PLACES)
FORMER (REF)
OUTBD FWD
G-G
BEFORE MODIFICATION
LOOKING UP AND FORWARD
INSTALLATION MAY VARY SLIGHTLY PER AIRPLANE
FIGURE 2: CONVENTIONAL WING TO FUSELAGE FILLETS - REPLACEMENT OF BONDING STRAPS
(SHEET 8 OF 19)
Original Issue: December 05, 1980
Revision 7 March 16, 2011  DC10-53-111
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.  44 0f 66

### Page 45 (OCR)

BOEING SERVICE BULLETIN DC10-53-111
ANB7067-3 (LS)
ANB7067-4 (RS)
13 25  RIB (REF)
STA
X=118.200
L
- 0.38 IN.
STA  STA
Z=-30.000  x=119.900
0.35 IN.
LONGN 29
STA
Y=1139.000
0.40 IN.
(22 25)
ARB1297-3 (LS)
ARB1297-4 (RS)  26  (23) 25)
FORMER (REF)
0.38 IN.
F-F  G-G  OUTBD FWD
AFTER MODIFICATION
LOOKING UP AND FORWARD
INSTALLATION MAY VARY SLIGHTLY PER AIRPLANE  U73531
FIGURE 2: CONVENTIONAL WING TO FUSELAGE FILLETS - REPLACEMENT OF BONDING STRAPS
(SHEET 9 OF 19)
Original Issue: December 05, 1980
Revision 7 March 16, 2011  BOEING PROPRIETARY -  DC10-53-111
Copyright © Unpublished Work - See page 1 for details.  45 of 66

### Page 46 (OCR)

BOEING SERVICE BULLETIN DC10-53-111
ANB7135-3 (LS)
ANB7135-4 (RS)
RIB (REF)
31) (4 PLACES)
29  STA
X=118.200
30
31) (2 PLACES)
28
27) (4 PLACES)
ARB1297-3 (LS)
ARB1297-4 (RS)  STA
FORMER (REF)  X=119.900
H-H
AFT OUTBD  BEFORE MODIFICATION
LOOKING UP AND AFT
INSTALLATION MAY VARY SLIGHTLY PER AIRPLANE
U73532
FIGURE 2: CONVENTIONAL WING TO FUSELAGE FILLETS - REPLACEMENT OF BONDING STRAPS
(SHEET 10 OF 19)
Original Issue: December 05, 1980
Revision 7 March 16, 2011  DC10-53-111
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.  46 of 66

### Page 47 (OCR)

BOEING SERVICE BULLETIN DC10-53-111
- ARB7135-3 (LS)
ARB7135-4 (RS)
RIB (REF)
2731 (4 PLACES)
STA
X=118.200
31) (2 PLACES)
STA
-Z=-40.000
27) (4 PLACES)
ARB1297-3 (LS)
ARB1297-4 (RS)  STA
FORMER (REF)  x=119.000
AFT OUTBD  I-I
BEFORE MODIFICATION
LOOKING UP AND AFT
INSTALLATION MAY VARY SLIGHTLY PER AIRPLANE
U73533
FIGURE 2: CONVENTIONAL WING TO FUSELAGE FILLETS - REPLACEMENT OF BONDING STRAPS
(SHEET 11 OF 19)
Original Issue: December 05, 1980
Revision 7 March 16, 2011  DC10-53-111
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.  47 of 66

### Page 48 (OCR)

BOEING SERVICE BULLETIN DC10-53-111
ANB7135-3 (LS)
ANB7135-4 (RS)
RIB (REF)
0.44 IN.  - 0.30 IN.
-0.44 IN.
STA
Z=-40.000
0.50 IN.
• 0.44 IN.
38
ANB1297-3 (LS)  STA  40) 42
ANB1297-4 (RS)  FORMER (REF)  (39 41  X=118.200
STA
x=119.900
H-H
AFT<  •OUTBD  I-I
AFTER MODIFICATON
LOOKING UP AND AFT
STA Y=1119.000
INSTALLATION MAY VARY SLIGHTLY PER AIRPLANE
FIGURE 2: CONVENTIONAL WING TO FUSELAGE FILLETS - REPLACEMENT OF BONDING STRAPS
(SHEET 12 OF 19)
Original Issue: December 05, 1980
Revision 7 March 16, 2011  BOEING PROPRIETARY -  DC10-53-111
Copyright © Unpublished Work - See page 1 for details.  48 of 66

### Page 49 (OCR)

BOEING SERVICE BULLETIN DC10-53-111
STA
Y=1099.000
ANB7136-7
STIFFENER  STA
(REF)  STA  Z=-50.000
STA  X=118.200
Y=1109.000
STA
(4 PLACES)  Z=-53.750
STA
X=119.900
(4 PLACES)
ARB1297-3 (LS)  ANB7136-3 (LS)
ARB1297-4 (RS)  ANB7136-4 (RS)
FORMER (REF)  WEB (REF)
_ FWD
J-J
BEFORE MODIFICATION
LOOKING FORWARD
INSTALLATION MAY VARY SLIGHTLY PER AIRPLANE  U73535
FIGURE 2: CONVENTIONAL WING TO FUSELAGE FILLETS - REPLACEMENT OF BONDING STRAPS
(SHEET 13 OF 19)
Original Issue: December 05, 1980
Revision 7 March 16, 2011  BOEING PROPRIETARY -  DC10-53-111
Copyright © Unpublished Work - See page 1 for details.  49 of 66

### Page 50 (OCR)

BOEING SERVICE BULLETIN DC10-53-111
STA
Y=1099.000
ANB7136-7
STIFFENER  STA
(REF) -  STA  Z=-50.000
STA  X=118.200
Y=1109.000
STA
(4 PLACES)  2=-53.750
STA
X=119.900
(4 PLACES)
ARB1297-3 (LS)  ANB7136-3 (LS)
ARB1297-4 (RS)  ANB7136-4 (RS)
FORMER (REF)  WEB (REF)
FWD
K-K
BEFORE MODIFICATION
LOOKING FORWARD
INSTALLATION MAY VARY SLIGHTLY PER AIRPLANE
FIGURE 2: CONVENTIONAL WING TO FUSELAGE FILLETS - REPLACEMENT OF BONDING STRAPS
(SHEET 14 OF 19)
Original Issue: December 05, 1980
Revision 7 March 16, 2011  DC10-53-111
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.  50 of 66

### Page 51 (OCR)

BOEING SERVICE BULLETIN DC10-53-111
STA
Y=1099.000
ANB7136-7
STIFFENER  STA
(REF)  STA  Z=-50.000
STA  X=118.200
Y=1109.000
0.40 IN.  STA
Z=-53.750
STA
(49  x=119.900
(48 50
0.44 IN.
-0.44 IN.
0.38 IN.
ARB1297-3 (LS)  149‚
ARB1297-4 (RS)
FORMER (REF)
ANB7136-3 (LS)
ANB7136-4 (RS)
WEB (REF)
J-J
K—K
AFTER MODIFICATION
LOOKING FORWARD
INSTALLATION MAY VARY SLIGHTLY PER AIRPLANE  U73537
FIGURE 2: CONVENTIONAL WING TO FUSELAGE FILLETS - REPLACEMENT OF BONDING STRAPS
(SHEET 15 OF 19)
Original Issue: December 05, 1980
Revision 7 March 16, 2011  DC10-53-111
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.  51 of 66

### 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
Refer to DC-10 AMM 06-35-00 and
DC-10 AMM 06-36-00.
1
1
ANB7257-1
ANB7257-2
Door AssemblyOpen1
Remove 4 rivets from former and 5
rivets from stiffener (if installed).
9
9
ANB7068-17/-18
ARB1297-3/-4
Stiffener
Former
Drill2
-1ANB7553-3/-4 or
ANB7553-13N/-14N or
ANB7553-23/-24
Strap Assembly
(Metal)
Remove3
Plug 3 holes in each former
ARB1297-3/-4 and 3 holes in each
stiffener ANB7068-17/-18. (e)
12-HolesFill4
Pick up on existing fastener hole in
former and mark hole position for
fastener vertically above. (f)
2SR10530059-15Strap AssemblyLocate5
0.1605/0.162-inch diameter.8-HolesDrill/Deburr6
Remove treatment/paint from the for-
mer and stiffener at the locations
where the bonding strap will be at-
tached.
-Alodine 1200SChemical Conver-
sion Coating
Apply7
(a) (f)2SR10530059-15Strap AssemblyInstall8
8HL328-5-3Pin
8NAS1149FN816PWasher
8MS21042L08Nut
(f)- -FR PR-1422 B-2Primer SealantApply9
Remove 4 rivets from each former
and 5 rivets from each stiffener.
9
9
ANB7069-5/-6
ARB1297-3/-4
Stiffener FormerDrill10
-1ANB7553-7/-8 or
ANB7553-17N/-18N or
ANB7553-27/-28
Strap Assembly
(Metal)
Remove11
(d)14-HolesFill12
Mark hole positions for fasteners. (a)
(f)
2SR10530059-13Strap AssemblyLocate13
0.1605/0.1625-inch diameter (as ap-
plicable).
6-HolesDrill/Deburr14
FIGURE 2: CONVENTIONAL WING TO FUSELAGE FILLETS - REPLACEMENT OF BONDING STRAPS
(SHEET 16 OF 19)
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: December 05, 1980
DC10-53-111Revision 7 March 16, 2011
52 of 66
BOEING SERVICE BULLETIN DC10-53-111

### Page 53

MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
Pick up on existing fastener hole and
open up hole to 0.2450/0.2480-inch
diameter.
2-HolesDrill/Deburr15
(f)-Alodine 1200SChemical Conver-
sion Coating
Apply16
Install Pin HL328-8-3, Washer
NAS1149F0432P and Nut
MS21042L4 (1 off of each) in the
corner hole of bonding strap attached
to each former. (a) (f)
2
6
2
6
2
SR10530059-13
HL328-5-3
HL328-8-3
NAS1149FN816P
NAS1149F0432P
Strap Assembly
Pin
Pin
Washer
Washer
Install17
6MS21042L08Nut
2MS21042L4Nut
(f)- -FR PR-1422 B-2Primer SealantApply18
Drill out 4 rivets in former and 3 rivets
in rib each side.
7
7
ARB7067-3/-4
ANB1297-3/-4
Rib FormerDrill19
-1ANB7553-5/-6 or
ANB7553-15N/-16N or
ANB7553-25/-26
Strap Assembly
(Metal)
Remove20
Plug 2 end holes in each former
ARB1297-3/-4 and center hole in
each rib ANB79067-3/-4. (e)
6-HolesFill21
Use existing 2 center holes in each
former ARB1297-3/-4 and the 2 open
holes in each rib ANB7067-3/-4. (a)
(f)
2SR10530059-21Strap AssemblyLocate22
0.1605/0.1625-inch diameter.8-HolesDrill/Deburr23
(f)-Alodine 1200SChemical Conver-
sion Coating
Apply24
(a) (f) (g)2SR10530059-21Strap AssemblyInstall25
8HL328-5-3Pin
8NAS1149FN816PWasher
8MS21042L08Nut
(f)- -FR PR-1422 B-2Primer SealantApply26
Drill out 4 rivets in former and 4 rivets
in rib each side.
8
8
ANB7135-3/-4
ARB1297-3/-4
Rib FormerDrill27
-1ANB7553-9/-10 or
ANB7553-19N/20N or
ANB7553-29/-30
Strap Assembly
(Metal)
Remove28
FIGURE 2: CONVENTIONAL WING TO FUSELAGE FILLETS - REPLACEMENT OF BONDING STRAPS
(SHEET 17 OF 19)
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: December 05, 1980
DC10-53-111Revision 7 March 16, 2011
53 of 66
BOEING SERVICE BULLETIN DC10-53-111

### Page 54

MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
Drill out 2 rivets in strap assembly
where bracket TA4074D0616 is at-
tached.
1ANB7553-9/-10 or
ANB7553-19N/20N or
ANB7553-29/-30
Strap AssemblyDrill29
-2TA4074D0616BracketRe-
move/Keep
30
(b)12-HolesFill31
(f)-Alodine 1200SChemical Conver-
sion Coating
Apply32
Mark hole positions for fasteners.2TA4074D0616BracketLocate33
No.40 diameter. (c)4-HolesDrill/Deburr34
To the edge of the holes.-Alodine 1200SChemical Conver-
sion Coating
Apply35
-2TA4074D0616BracketInstall36
4MS20470AD3-4Rivet
(f)- -FR PR-1422 B-2Primer SealantApply37
Mark hole positions for fasteners. (a)
(f)
2SR10530059-21Strap AssemblyLocate38
0.1605/0.1625-inch diameter.8-HolesDrill/Deburr39
Remove treatment/paint from the for-
mer and stiffener at the locations
where the bonding strap will be at-
tached.
-Alodine 1200SChemical Conver-
sion Coating
Apply40
(a) (f) (g)2SR10530059-21Strap AssemblyInstall41
8HL328-5-3Pin
8NAS1149FN816PWasher
8MS21042L08Nut
(f)- -FR PR-1422 B-2Primer SealantApply42
Drill out 4 attachment rivets in former
and 4 attachment rivets in rib each
side.
8
8
ANB7136-3/-4
ARB1297-3/-4
Web
Former
Drill43
-1ANB7553-11/-12 or
ANB7553-21N/22N or
ANB7553-31/-32
Strap Assembly
(Metal)
Remove44
Plug 2 holes in each former
ARB1297-3/-4 and 2 holes in each
web ANB7136-3/-4. (e)
8-HolesFill45
Use existing holes from strap assem-
bly removed. (a) (f)
2SR10530059-19Strap AssemblyLocate46
FIGURE 2: CONVENTIONAL WING TO FUSELAGE FILLETS - REPLACEMENT OF BONDING STRAPS
(SHEET 18 OF 19)
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: December 05, 1980
DC10-53-111Revision 7 March 16, 2011
54 of 66
BOEING SERVICE BULLETIN DC10-53-111

### Page 55

MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
0.1605/0.1625-inch diameter.8-HolesDrill/Deburr47
Remove treatment/paint from the for-
mer and stiffener at the locations
where the bonding strap will be at-
tached.
-Alodine 1200SChemical Conver-
sion Coating
Apply48
(a) (f)2SR10530059-19Strap AssemblyInstall49
8HL328-5-3Pin
8NAS1149FN816PWasher
8MS21042L08Nut
(f)- -FR PR-1422 B-2Primer SealantApply50
Refer to DC-10 AMM 06-35-00 and
DC-10 AMM 06-36-00.
1
1
ANB7257-1
ANB7257-2
Door AssemblyClose51
(a) 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 the minimum acceptable edge
distance.
(b) Apply alodine 1200S around edge of holes. Plug 4 holes in rib ANB7135-3/-4 and 2 holes (one each end)
in each former ARB1297-3/-4. Determine whether the installation of a protruding head fastener (NAS1738E4-
2) adjacent to the strap installation will interfere with the strap installation. If it does install a countersink rivet
NAS1739E4-2. If there is no interference install NAS1738E4-2.
(c) When drilling holes observe 4D spacing to avoid getting the 2 holes for the installation of the bracket too
close to the existing plugged hole in the ANB7135-3/-4 ribs.
(d) Apply alodine 1200S to edge of holes. Plug 4 open holes in each former ARB1297-3/-4 and 3 open holes
in each stiffener ANB7069-5/-6. Determine whether the installation of a protruding head fastener (NAS1738E4-
2) adjacent to the strap installation will interfere with the strap installation. If it does install a countersink rivet
NAS1739E4-2. If there is no interference install NAS1738E4-2.
(e) Apply alodine 1200S around edge of holes. Determine whether the installation of a protruding head fastener
(NAS1738E4-2) adjacent to the strap installation will interfere with the strap installation. If it does install a
countersink rivet NAS1739E4-2. If there is no interference install NAS1738E4-2 rivets.
(f) Refer to Appendix A for bonding installation procedure.
(g) Operators may substitute SR10530059-27 strap assembly, if/as required, to prevent wire strain.
Note: Changing P/N SR10530058-17 strap with P/N SR10530059-23 strap is equivalent to substituting strap
assembly part numbers. If changing strap only part numbers, verify electrical bonding between strap and
brackets in accordance with SWPM 20-50-01 .
FIGURE 2: CONVENTIONAL WING TO FUSELAGE FILLETS - REPLACEMENT OF BONDING STRAPS
(SHEET 19 OF 19)
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: December 05, 1980
DC10-53-111Revision 7 March 16, 2011
55 of 66
BOEING SERVICE BULLETIN DC10-53-111

### Page 56 (OCR)

BOEING SERVICE BULLETIN DC10-53-111
This Figure applies only to: Group 1-2, Configuration 2.
LEFT SIDE SHOWN
RIGHT SIDE OPPOSITE
STA
Y=1139.000
DOU  STA  STA  STA
STA  Y=1109.000 Y=1119.000  Y=1129.000  • E(SHEET 5)
Y=1099.000
STA
Z=-30.000
[F (SHEET 6)_  E(SHEET 5)
STA
Z=-40.000  (SHEET 7)G •
F (SHEET 6)  ARB1297-3 (LS)
ARB1297-4 (RS)
STA  FORMER (REF)
Z=-50.000
STA  7C(BEFORE)  (SHEET 3)
Z=-60.000
(SHEET 7)G
C(AFTER)
(SHEET 4)
STA
Z=-70.000
ANB7257-1 (LS) (1)  120
ANB7257-2 (RS)
DOOR ASSY (REF)  FWD A-A  U52183
FIGURE 3: CONVENTIONAL WING TO FUSELAGE FILLETS - REPOSITION ONE BONDING STRAP AND
REPLACEMENT OF FASTENERS
(SHEET 1 OF 10)
Original Issue: December 05, 1980
Revision 7 March 16, 2011  BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.  99 10 99

### Page 57 (OCR)

BOEING SERVICE BULLETIN DC10-53-111
24  ARB1297-3 (LS)
ARB1297-4 (RS)
FORMER (REF)
(2)4)
ANB7068-17 (LS)
ANB7068-18 (RS)
STIFFENER (REF)
0.40 IN.
STA  -0.90 IN.
000*6LL=x
STA
x=119.900
STA
STA  X=118.200
Z=-70.000
FWD
B—B
LOOKING AFT
INSTALLATION MAY VARY SLIGHTLY PER AIRPLANE  U52930
FIGURE 3: CONVENTIONAL WING TO FUSELAGE FILLETS - REPOSITION ONE BONDING STRAP AND
REPLACEMENT OF FASTENERS
(SHEET 2 OF 10)
Original Issue: December 05, 1980
Revision 7 March 16, 2011  DC10-53-111
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.  57 of 66

### Page 58 (OCR)

BOEING SERVICE BULLETIN DC10-53-111
ARB1297-3 (LS)
ARB1297-4 (RS)
FORMER (REF)
STA
Y=1123.530
ANB7069-5 (LS)
ANB7069-6 (RS)
STIFFENER (REF)
STA
Y=1119.000
. STA
0.44 IN..  Z=-60.000
STA
Z=-61.650
STA  0.44 IN.
X=119.900
STA
X=118.200
OUTBD,  FWD
C-C
BEFORE MODIFICATION
LOOKING FORWARD  U53483
INSTALLATION MAY VARY SLIGHTLY PER AIRPLANE
FIGURE 3: CONVENTIONAL WING TO FUSELAGE FILLETS - REPOSITION ONE BONDING STRAP AND
REPLACEMENT OF FASTENERS
(SHEET 3 OF 10)
Original Issue: December 05, 1980
Revision 7 March 16, 2011  BOEING PROPRIETARY -  DC10-53-111
Copyright © Unpublished Work - See page 1 for details.  58 of 66

### Page 59 (OCR)

BOEING SERVICE BULLETIN DC10-53-111
ANB7067-3 (LS)
ANB7067-4 (RS)
14 16  RIB (REF)
STA
X=118.200
0.38 IN.
STA
STA
Z=-30.000  X=119.900
0.35 IN.
(15) 17)  LONGN 29
STA
Y=1139.000
0.40 IN.
(14 16)
ARB1297-3 (LS)
ARB1297-4 (RS)
FORMER (REF)
0.38 IN.
LOOKING UP AND FORWARD OUTBDEWD
INSTALLATION MAY VARY SLIGHTLY PER AIRPLANE  U53928
FIGURE 3: CONVENTIONAL WING TO FUSELAGE FILLETS - REPOSITION ONE BONDING STRAP AND
REPLACEMENT OF FASTENERS
(SHEET 4 OF 10)
Original Issue: December 05, 1980
Revision 7 March 16, 2011  DC10-53-111
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.  59 of 66

### Page 60 (OCR)

BOEING SERVICE BULLETIN DC10-53-111
ANB7135-3 (LS)
ANB7135-4 (RS)
RIB (REF)
0.44 IN.  - 0.30 IN.
-0.44 IN.
STA
Z=-40.000
0.50 IN.
(18) 20)  • 0.44 IN.
ANB1297-3 (LS)  STA  19 21)
ANB1297-4 (RS)  FORMER (REF)  18) 20  X=118.200
STA
x=119.900
AFT<  •OUTBD
F-F
LOOKING UP AND AFT
STA Y=1119.000
INSTALLATION MAY VARY SLIGHTLY PER AIRPLANE
FIGURE 3: CONVENTIONAL WING TO FUSELAGE FILLETS - REPOSITION ONE BONDING STRAP AND
REPLACEMENT OF FASTENERS
(SHEET 5 OF 10)
Original Issue: December 05, 1980
Revision 7 March 16, 2011  BOEING PROPRIETARY -  DC10-53-111
Copyright © Unpublished Work - See page 1 for details.  60 of 66

The text continues at https://openairdocs.org/service-documents/boeing/dc10-53-111/file/d62ac7c2b0ba.md?from=61

---
OpenAirDocs.org is an independent research project of [Contrail Labs](https://contraillabs.com/). It is not affiliated with the FAA or the NTSB. Source documents are U.S. government works in the public domain, except the copies of manufacturers’ service documents, which belong to their rights holders.