# Boeing Service Bulletin DC10-53-111: Boeing - Service Bulletin

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## Text

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### Page 1

McDonnell DouglasCommercial 
Airplanes
DC10
Service Bulletin
Number: DC10-53-111
Original Issue: December 05, 1980
Revision 6: March 03, 2009
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Unpublished Work - All Rights Reserved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, 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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DC10-53-111Revision 6: March 03, 2009
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5.0

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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 7
B. Concurrent Requirements ...................................... 1 7
C. Reason ................................................ 1 7
D. Description .............................................. 1 7
E. Compliance .............................................. 1 9
F . Approval ............................................... 1 9
G. Manpower .............................................. 1 9
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
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: ........................ 2 4
3. Parts Modified and Reidentified: ................................ 2 5
4. Parts Removed and Not Replaced: .............................. 2 5
D. Parts Necessary to Change Spares ................................. 2 5
E. Special Tooling - Price and Availability ............................... 2 5
F . Special Tooling Necessary to do this Service Bulletin ....................... 2 5
3. ACCOMPLISHMENT INSTRUCTIONS .................................. 2 7
A. GENERAL INFORMATION ..................................... 2 7
B. WORK INSTRUCTIONS ....................................... 2 8
FIGURE 1: CONVENTIONAL WING TO FUSELAGE FILLETS - INSTALLATION OF BONDING STRAPS
[Group 1, Configuration 1] ................................... 3 0
FIGURE 2: CONVENTIONAL WING TO FUSELAGE FILLETS - REPLACEMENT OF BONDING STRAPS
[Group 2, Configuration 1] ................................... 3 9
FIGURE 3: CONVENTIONAL WING TO FUSELAGE FILLETS - REPOSITION ONE BONDING STRAP
AND REPLACEMENT OF FASTENERS [Group 1-2, Configuration 2] ........... 5 8
Appendix A: BONDING STRAP INSTALLATION PROCEDURE ...................... 6 7
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McDonnell DouglasCommercial 
Airplanes
DC10
Service Bulletin
Revision Transmittal SheetNumber: DC10-53-111Original Issue: December 05, 1980
Revision 6: March 03, 2009
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
No more work is necessary on airplanes changed as shown on revision 5 of this service bulletin.
More work is necessary on airplanes changed as shown in original release through revision 4 of this service
bulletin. Measure electrical resistance of previously installed braided bonding straps. An additional 0.5 hours
required.
REASON FOR REVISION
This revision is sent to incorporate 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.
These sections were changed:
1. In Paragraph 1.D., Description, clarified group configuration description.
2. In Paragraph 1.F ., Approval, added Revision 6 and Alternative Method Of Compliance (AMOC) information.
3. In Paragraph 1.G., Manpower, added hours for electrical resistance check of previously installed braided
bonding straps and correction of electrical bonds that failed.
4. In Paragraph 1.H., Weight and Balance Changes, reinstated weight and balance table removed from revision
4.
5. In Paragraph 3.B.1., Work Instructions, added resistance check for braided bonding straps previously
installed.
6. In Figure 1, Sheet 2, Corrected fastener pattern.
7. In Figure 3, Added "as required" statement prior to step table.
Paragraph 1.A., Effectivity, shows changes of airplane operators. Each operator should examine the Effectivity
paragraph for changes.
Vertical lines are put on the left edge of each page, except in Paragraph 1.A., Effectivity, to show the location
of important changes.
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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:
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McDonnell DouglasCommercial 
Airplanes
DC10
Service Bulletin
SummaryNumber: DC10-53-111Original Issue: December 05, 1980
Revision 6: March 03, 2009
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 is 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/as required. Measures
electrical resistance of previously installed braided bonding straps.
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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
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.
Federal Aviation Administration (FAA) Airworthiness Directive 2006-16-03 is related to this service bulletin.
INDUSTRY SUPPORT INFORMATION
Boeing warranty remedies are not available for the configuration changes given in this service bulletin.
MANPOWER
Group 1, 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
Boeing Supplied Kits/Parts.
Refer to Paragraph 2.A., Material - Price and Availability.
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BOEING SERVICE BULLETIN DC10-53-111
00000/00  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
U51648
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Revision 6: March 03, 2009  DC10-53-111
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McDonnell DouglasCommercial 
Airplanes
DC10
Service Bulletin
Number: DC10-53-111
Original Issue: December 05, 1980
Revision 6: March 03, 2009
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.
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
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GroupFuselage Num-
ber
11
110
2100
1101 - 103
2104
1105 - 106
1108
111
1110 - 113
2114
1115 - 116
2117
1118 - 119
112
1120
2121 - 123
1124
2125
1126
2127
1128 - 129
113
1130 - 133
2134 - 135
1136
2137
1138 - 139
114
1140
2141
1142 - 145
2146
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GroupFuselage Num-
ber
1147 - 148
2149
115
2150
1151 - 157
2158
1159
116
2160
1161 - 169
117
2170
1171
1173 - 177
2178 - 179
118
1180 - 181
1183 - 185
2186
1187
2188
1189
119
1190 - 191
2192 - 193
1194
2195
1196
2197
1198
2199
22
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GroupFuselage Num-
ber
120
2200
1201 - 202
2203 - 204
1205
2206
1207 - 209
121
1210 - 211
2212 - 214
1215
2216
1217
2218
2220 - 226
1227
2228 - 229
123
2230 - 231
1232 - 233
2234 - 236
1237
2239
124
2240
1241 - 242
2243 - 244
1245
2246
1247 - 249
125
1250
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GroupFuselage Num-
ber
2251 - 252
1253
2254
1255
2256
1257
2258 - 259
126
2262
2264 - 266
1267
2269
127
1270 - 271
2272
1273
2274
2276
2278 - 279
128
2283
2285
2287 - 288
2290
1294
13
130 - 31
2316
132
2327
233
2337
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GroupFuselage Num-
ber
134 - 35
2354
136 - 39
14
140 - 43
145 - 49
15
150 - 56
257
158 - 59
16
160 - 62
263
164 - 69
17
170 - 72
273
174
275
176
277 - 78
179
18
180
182 - 83
185 - 86
288
189
19
290 - 91
192
293 - 95
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GroupFuselage Num-
ber
196 - 98
299
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.
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 is 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 adds Figures 3 and 4 to show Configuration 2 for airplanes that have not
done this service bulletin. In addition Figures 3 and 4 changes one bonding strap position to remove
a riding condition and corrects 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 is 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.
This service bulletin revision 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:
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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/as required. Measures electrical resistance of previously installed braided bonding straps.
Revision 6 - No more work is necessary on airplanes changed as shown on revision 5 of this service
bulletin.
More work is necessary on airplanes changed as shown in original release through revision 4 of this
service bulletin. Measure electrical resistance of previously installed braided bonding straps. An
additional 0.5 hours required.
The work in this service bulletin is done in the maintenance zone(s) given below.
Group 1:
Affected Maintenance Zones
ZoneModel
131, 132, 161, 162DC-10-10, DC-10-10F , DC-10-
30, DC-10-30F , DC-10-30F
(KDC-10), 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
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E. Compliance
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.
Federal Aviation Administration (FAA) Airworthiness Directive 2006-16-03 is related to this service
bulletin.
F. Approval
The resultant modification described in Paragraph 1.D has been shown to comply with the applicable
Federal Aviation Regulations, and Revision 6 is approved by the Manager, Los Angeles Aircraft
Certification Office, FAA Northwest Mountain Region, and is approved as an alternative method of
compliance with Paragraphs (f) and (h) of Airworthiness Directive No. 2006-16-03.
G. Manpower
The table below shows an estimate of the task hours necessary to do this change for each airplane.
This estimate is for direct labor only, done by an experienced crew. Adjust the estimate with operator
task hour data if necessary. The estimate does not include lost time. These are some examples of lost
time:
— Time to adjust to the workplace
— Time to schedule the work
— Time to examine the work
— Time to cure the materials
— Time to make the parts
— Time to find the tools.
Group 1, 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
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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/as 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. DC-10 Aircraft Maintenance Manual (AMM) 06-35-00, 06-36-00.
b. Federal Aviation Administration (FAA) Airworthiness Directive 2006-16-03.
c. Standard Wiring Practices Manual (SWPM) 20-50-01.
2. Data supplied with this Service Bulletin:
None.
3. Installation Drawings Used in the Preparation of this Service Bulletin:
ChangeTitleDocument Number
CService Rework DrawingSR10530059
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K. Publications Affected
Chapter-SectionPublication
53-53Illustrated Parts Catalog
Weight and Balance Documents
L. Interchangeability and Intermixability of Parts
Accomplishment of this service bulletin does not affect interchangeability or intermixability of parts.
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2.    MATERIAL INFORMATION
A. Material - Price and Availability
The operator can supply the parts and materials shown in Paragraph 2.C., Parts Necessary For Each
Airplane. As an alternative, operators can purchase the parts from Boeing Spares.This service bulletin
does not show the Boeing price and supply data.
Reference this service bulletin and submit your purchase order by one of the methods that
follow:
1. Order on-line via ATA Spec 2000 or Boeing Part Page.
2. Fax to (206) 662-7145.
3. Spares Customer Support - MC 36-65 Boeing Spares Department P .O. Box 3707 Seattle,
Washington 98124-2207 USA
B. Industry Support Information
Boeing warranty remedies are not available for the configuration changes given in this service bulletin.
C. Parts Necessary For Each Airplane
1. Kits/Parts:
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 ASSEMBL Y2SR10530059-13
or
ANB7553-27/-28
or
ANB7553-7/-8
or
ANB7553-17N/-18N
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NotesExisting Part NumberNameQTYNew Part Number
(a) (b) (c) (d)SB10530111-3/-4STRAP ASSEMBL Y2SR10530059-15
or
ANB7553-3/-4
or
ANB7553-23/-24
or
ANB7553-13N/-14N
(a) (b) (c) (d)SB10530111-11/-12STRAP ASSEMBL Y2SR10530059-19
or
ANB7553-31/-32
or
ANB7553-11/-12
or
ANB7553-21N/-22N
(a) (b) (c) (d)SB10530111-5/-6 or -9/-10STRAP ASSEMBL Y4SR10530059-21
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)
Y ou 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 as given in Service
Rework Drawing SR10530059.
(c)
CAGECooner Manufacturer CompanyNEQL48830 overbraid maybe obtained from:(d)
637949186 Independence Avenue
Chatsworth, California 91311-5902
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
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Original Issue: December 05, 1980
DC10-53-111Revision 6: March 03, 2009
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BOEING SERVICE BULLETIN DC10-53-111

### Page 25

Group 1 - 2
NotesNameQTYPart Number / Specification
(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
CAGE
73197
Hi-Shear Corporation
2600 Skypark Drive
(a) May be obtained from:
Torrance, California 90505-5373
84971Kirkhill-TA Corporation Division TA Aerospace(b) May be obtained from:
28065 Franklin Parkway
Valencia, California 91355-4117
83574PRC-DeSoto International, Incorporated(c) May be obtained from:
Sealant Adhesives and Coatings Division
5430 San Fernando Road
Glendale, California 91203-1521
3. Parts Modified and Reidentified:
None.
4. Parts Removed and Not Replaced:
NotesQTYNameExisting Part Number
Discard2BracketTA10B18D-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.
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### Page 26

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BOEING SERVICE BULLETIN DC10-53-111
BLANK PAGE

### Page 27

3.    ACCOMPLISHMENT INSTRUCTIONS
A. GENERAL INFORMATION
WARNING: IF ELECTRICAL POWER IS APPLIED TO THE AIRPLANE, MAKE SURE YOU OBEY
ALL PRECAUTIONS WHILE YOU DO WORK. IF YOU DO NOT OBEY THE
PRECAUTIONS, DEATH OR INJURY TO PERSONS, AND DAMAGE TO THE AIRPLANE
CAN OCCUR.
CAUTION: KEEP THE WORK AREA, WIRES, AND ELECTRICAL BUNDLES CLEAN OF METAL
PARTICLES OR CONTAMINATION WHEN YOU USE TOOLS. UNWANTED MATERIAL,
METAL PARTICLES OR CONTAMINATION CAUGHT IN WIRE BUNDLES CAN CAUSE
DAMAGE TO THE BUNDLES. DAMAGED WIRE BUNDLES CAN CAUSE SPARKS OR
OTHER ELECTRICAL DAMAGE.
CAUTION: ELECTRICALL Y GROUND THE AIRPLANE. THIS WILL HELP TO PREVENT DAMAGE
TO THE AIRPLANE OR EQUIPMENT.
NOTE: 1. Manual titles are referred to by acronyms. Refer to Paragraph 1.J., References, for
definition of the acronyms.
2. For approved fastener and process material substitutions, refer to DC-10 Structural
Repair Manual, Chapter 51.
3. If the length of fasteners specified in this service bulletin do not meet the installation
standards, fasteners of the same specification, or an approved substitute, one grip
length longer or shorter may be used.
4. 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 "as
given in" 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.
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BOEING SERVICE BULLETIN DC10-53-111

### Page 28

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 as given in DC-10 AMM 06-35-00 and DC-10 AMM 06-36-00
as an accepted procedure.
Group 1, Configuration 1:
(Airplanes that have not previously done Service Bulletin DC10-53-111)
a. Install ten new braided bonding straps as given in Figure 1.
NOTE: All strap locations are approximate. No attempt to exactly verify the location per the
figures should be made. For these installations, the location of the strap is acceptable
under the following conditions:-
1. Each end of the strap is located on the correct part or assembly and is
installed picking up on any existing holes as identified in Figure 1.
2. All strap fastener hole edge distances are at least 2D from any edge, joggle
or detail such as a lightening hole of the structure to which it is attached.
3. There is enough slack in the strap that when installed there is no chance
that the strap will be pulled tight in flight.
Group 2, Configuration 1:
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 as given in
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 as given in 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 as given in 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 in accordance with 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:
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BOEING SERVICE BULLETIN DC10-53-111

### Page 29

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 as given
in DC-10 AMM 06-35-00 and DC-10 AMM 06-36-00.
3. Put the airplane back to a serviceable condition.
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BOEING SERVICE BULLETIN DC10-53-111

### Page 30 (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 -
STA
Z=-70.000
FWD<
ANB7257-1 (LS)
ANB7257-2 (RS)
DOOR ASSY (REF)
A-A
FIGURE 1: CONVENTIONAL WING TO FUSELAGE FILLETS - INSTALLATION OF BONDING STRAPS
(SHEET 1 OF 9)
Original Issue: December 05, 1980
Revision 6 March 03, 2009
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### Page 31 (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  I 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)
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Revision 6 March 03, 2009  DC10-53-111
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### Page 32 (OCR)

BOEING SERVICE BULLETIN DC10-53-111
ARB1297-3 (LS)  ARB1297-4 (RS)  36  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
240
OUTBD
STA
Y=1139.000
B—B
AFTER MODIFICATION
(LOOKING AFT)  U69179
FIGURE 1: CONVENTIONAL WING TO FUSELAGE FILLETS - INSTALLATION OF BONDING STRAPS
(SHEET 3 OF 9)
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Revision 6 March 03, 2009  DC10-53-111
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### Page 33 (OCR)

BOEING SERVICE BULLETIN DC10-53-111
STA
Y=1123.530
D
12) 14
2.720 IN.
113
10 11 13
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
10 13
OUTBD ,  FWD
_C-C  1352737
LOOKING FORWARD
FIGURE 1: CONVENTIONAL WING TO FUSELAGE FILLETS - INSTALLATION OF BONDING STRAPS
(SHEET 4 OF 9)
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### Page 34 (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.
(17) 19)  LONGN 29
STA
Y=1139.000
0.40 IN.
(15  18
ARB1297-3 (LS)
ARB1297-4 (RS)
FORMER (REF)
0.38 IN.
OUTBD FND
E-E
LOOKING UP AND FORWARD
U69181
FIGURE 1: CONVENTIONAL WING TO FUSELAGE FILLETS - INSTALLATION OF BONDING STRAPS
(SHEET 5 OF 9)
Original Issue: December 05, 1980
Revision 6 March 03, 2009  DC10-53-111
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### Page 35 (OCR)

BOEING SERVICE BULLETIN DC10-53-111
28 30
24 25)  1
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.
30  0.44 IN.
ANB1297-3 (LS)  STA  29/31)
ANB1297-4 (RS)  FORMER (REF)  28) 30)  X=118.200
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)
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Revision 6 March 03, 2009  DC10-53-111
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### Page 36

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
(c)-Alodine 1200SChemical Con-
version Coating
Apply17
FIGURE 1: CONVENTIONAL WING TO FUSELAGE FILLETS - INSTALLATION OF BONDING STRAPS
(SHEET 7 OF 9)
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BOEING SERVICE BULLETIN DC10-53-111

### Page 37

MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
(a) (c)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)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)
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BOEING SERVICE BULLETIN DC10-53-111

### Page 38

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.
FIGURE 1: CONVENTIONAL WING TO FUSELAGE FILLETS - INSTALLATION OF BONDING STRAPS
(SHEET 9 OF 9)
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### Page 39 (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  STA  STA
STA  Y=1109.000  Y=1119.000  Y=1129.000  1 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)
I (SHEET 12)
STA  D (BEFORE)  C (BEFORE)
Z=-60.000  (SHEET 5)  (SHEET 3)
(AFTER)J  OR
(SHEET 15)  B (BEFORE)
OR  (SHEET 2)
D (AFTER)
(BEFORE)K
STA  (SHEET 15)  (SHEET 6)
Z=-70.000
B (AFTER)
ANB7257-1 (LS) (  (SHEET 4)
ANB7257-2 (RS)  OR
DOOR ASSY (REF)  A-A  C (AFTER)
(SHEET 4)
FIGURE 2: CONVENTIONAL WING TO FUSELAGE FILLETS - REPLACEMENT OF BONDING STRAPS
(SHEET 1 OF 19)
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### Page 40 (OCR)

BOEING SERVICE BULLETIN DC10-53-111
ARB1297-3 (LS)
ARB1297-4 (RS)
FORMER (REF)
2) (4 PLACES)
• O1S 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
B—B
BEFORE MODIFICATION
LOOKING AFT
INSTALLATION MAY VARY SLIGHTLY PER AIRPLANE  U73523
FIGURE 2: CONVENTIONAL WING TO FUSELAGE FILLETS - REPLACEMENT OF BONDING STRAPS
(SHEET 2 OF 19)
Original Issue: December 05, 1980
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### Page 41 (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
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)
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### Page 42 (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
(8)
OUTBD
B—B  FWD
C-C
AFTER MODIFICATION
LOOKING AFT
INSTALLATION MAY VARY SLIGHTLY PER AIRPLANE  U73525
FIGURE 2: CONVENTIONAL WING TO FUSELAGE FILLETS - REPLACEMENT OF BONDING STRAPS
(SHEET 4 OF 19)
Original Issue: December 05, 1980
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### Page 43 (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)
STA
X=119.900
(10 (5 PLACES)
STA
X=118.200
OUTBO BENO
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)
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### Page 44 (OCR)

BOEING SERVICE BULLETIN DC10-53-111
STA
14 17)  Y=1123.530
(16)18
ARB1297-17 (LS)-
ARB1297-18 (RS)  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
\18
STA  0.44 IN.
X=119.900
STA
x=118.200
2.720 IN.
OUTBD  D-D  OUTBD,  FWD
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 6 March 03, 2009  DC10-53-111
BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.  44 of 67

### Page 45 (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 6 March 03, 2009  DC10-53-111
BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.  45 0f 67

### Page 46 (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
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  U73530
FIGURE 2: CONVENTIONAL WING TO FUSELAGE FILLETS - REPLACEMENT OF BONDING STRAPS
(SHEET 8 OF 19)
Original Issue: December 05, 1980
Revision 6 March 03, 2009  DC10-53-111
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### Page 47 (OCR)

BOEING SERVICE BULLETIN DC10-53-111
ANB7067-3 (LS)
ANB7067-4 (RS)
23 25  RIB (REF)
STA
X=118.200
• 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)  125
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 6 March 03, 2009  DC10-53-111
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### Page 48 (OCR)

BOEING SERVICE BULLETIN DC10-53-111
ANB7135-3 (LS)
ANB7135-4 (RS)
RIB (REF)
27) 31) (4 PLACES)
STA
X=118.200
(30
31) (2 PLACES)
27) (4 PLACES)
ARB1297-3 (LS)
ARB1297-4 (RS)  STA
FORMER (REF)  X=119.900
AFT OUTBD  BEFORE MODIFICATION  H—H
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 6 March 03, 2009  DC10-53-111
BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.  48 of 67

### Page 49 (OCR)

BOEING SERVICE BULLETIN DC10-53-111
- ARB7135-3 (LS)
ARB7135-4 (RS)
RIB (REF)
27 31 (4 PLACES)
STA
X=118.200
30
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 6 March 03, 2009  DC10-53-111
BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.  49 of 67

### Page 50 (OCR)

BOEING SERVICE BULLETIN DC10-53-111
ANB7135-3 (LS)
ANB7135-4 (RS)
RIB (REF)
34) 35)36
0.44 IN.  - 0.30 IN.
- 0.44 IN.
(33 36
STA
Z=-40.000
0.50 IN.
0.44 IN.
38  X41
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  U73534
FIGURE 2: CONVENTIONAL WING TO FUSELAGE FILLETS - REPLACEMENT OF BONDING STRAPS
(SHEET 12 OF 19)
Original Issue: December 05, 1980
Revision 6 March 03, 2009  DC10-53-111
BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.  50 of 67

### 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
STA
(4 PLACES)  Z=-53.750
STA
x=119.900
43)
(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 6 March 03, 2009  DC10-53-111
BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.  51 of 67

### Page 52 (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)
OUTBOR FNO
K—K
BEFORE MODIFICATION
LOOKING FORWARD
INSTALLATION MAY VARY SLIGHTLY PER AIRPLANE
U73536
FIGURE 2: CONVENTIONAL WING TO FUSELAGE FILLETS - REPLACEMENT OF BONDING STRAPS
(SHEET 14 OF 19)
Original Issue: December 05, 1980
Revision 6 March 03, 2009  DC10-53-111
BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.  52 of 67

### Page 53 (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
47 49)  X=119.900
Q  (48) 50
48/50
0.44 IN.
-0.44 IN.
0.38 IN.
ARB1297-3 (LS)  Y49)  (47 49)  OUTBOR FWO
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 6 March 03, 2009  DC10-53-111
BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.  53 of 67

### Page 54

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
Pick up on existing fastener hole and
open up hole to 0.2450/0.2480-inch
diameter.
2-HolesDrill/Deburr15
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 6 March 03, 2009
54 of 67
BOEING SERVICE BULLETIN DC10-53-111

### Page 55

MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
(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)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
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
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 6 March 03, 2009
55 of 67
BOEING SERVICE BULLETIN DC10-53-111

### Page 56

MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
(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)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
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
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 6 March 03, 2009
56 of 67
BOEING SERVICE BULLETIN DC10-53-111

### Page 57

MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
(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.
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 6 March 03, 2009
57 of 67
BOEING SERVICE BULLETIN DC10-53-111

### Page 58 (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
000
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  C (BEFORE)  (SHEET 3)
Z=-60.000
(SHEET 7)G
→ B(SHEET 2)
C(AFTER)
(SHEET 4)
STA
Z=-70.000
ANB7257-1 (LS) 1  L B(SHEET 2)
ANB7257-2 (RS)
DOOR ASSY (REF)
FWDY A-A
FIGURE 3: CONVENTIONAL WING TO FUSELAGE FILLETS - REPOSITION ONE BONDING STRAP AND
REPLACEMENT OF FASTENERS
(SHEET 1 OF 9)
Original Issue: December 05, 1980
Revision 6 March 03, 2009
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### Page 59 (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.
Y=1139.000
STA
X=119.900
STA
STA  X=118.200
Z=-70.000
2X4
OUTBD
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 9)
Original Issue: December 05, 1980
Revision 6 March 03, 2009  DC10-53-111
BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.  59 of 67

### Page 60 (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 9)
Original Issue: December 05, 1980
Revision 6 March 03, 2009  DC10-53-111
BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.  60 of 67

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