# Boeing Service Bulletin DC10-53-182: No revision named

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- Title as filed: Boeing Commercial Airplanes - Service Bulletin
- Pages: 26
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### Page 1

Commercial 
Airplanes
DC10
Service Bulletin
Number: DC10-53-182
Original Issue: June 28, 2013
ATA System: 5300
SUBJECT: FUSELAGE - Fuselage - Inspect/Change Left and Right Forward Cargo Compartment
Frame to Cargo Liner Attachment Holes
Export of this technology is controlled under the United States Export Administration Regulations (EAR) (15
CFR 300-774). 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 © 2013 Boeing.
Unpublished Work. All Rights Reserved.
Treatment of this document and its content is governed by contract with Boeing. Rights to use this document
are licensed on a per aircraft basis and such rights may not be transferable. For more information, contact The
Boeing Company.
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, KC-46, KDC-10, MD-10, MD-11, MD-80, MD-88, MD-90, P-8, Poseidon and
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connection with this document unless provided in writing by Boeing.
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2.0

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Table of Contents
Summary ...................................................... 5
1. PLANNING INFORMATION ........................................ 7
A. Effectivity ................................................ 7
1. Airplanes ............................................. 7
2. Spares Affected ........................................ 1 0
B. Concurrent Requirements ...................................... 1 0
C. Reason ................................................ 1 1
D. Description .............................................. 1 1
E. Compliance .............................................. 1 2
F. Approval ............................................... 1 2
G. Manpower .............................................. 1 3
H. Weight and Balance Changes .................................... 1 3
I. Electrical Load Data ......................................... 1 4
J. References .............................................. 1 4
1. Existing Data: ......................................... 1 4
2. Data Supplied with this Service Bulletin: ........................... 1 4
3. Installation Drawings Used in the Preparation of this Service Bulletin: ........... 1 4
K. Publications Affected ........................................ 1 4
L. Interchangeability and Intermixability of Parts ........................... 1 4
M. Software Accomplishment Summary ................................ 1 4
2. MATERIAL INFORMATION ........................................ 1 5
A. Material - Price and Availability ................................... 1 5
B. Industry Support Information .................................... 1 5
C. Parts Necessary for Each Airplane ................................. 1 5
1. Kits/Parts ............................................ 1 5
2. Parts and Materials Supplied by the Operator ........................ 1 6
3. Parts Modified and Reidentified ................................ 1 7
4. Parts Removed and Not Replaced .............................. 1 7
D. Parts Necessary to Change Spares ................................. 1 7
E. Special Tooling - Price and Availability ............................... 1 7
F. Special Tooling Necessary to do this Service Bulletin ....................... 1 7
3. ACCOMPLISHMENT INSTRUCTIONS .................................. 1 9
A. GENERAL INFORMATION ..................................... 1 9
B. WORK INSTRUCTIONS ....................................... 2 0
FIGURE 1: REMOVE CARGO COMPARTMENT FRAME TO CARGO LINER ATTACHMENT FASTENERS
.................................................. 2 1
FIGURE 2: INSPECT CARGO COMPARTMENT FRAME TO CARGO LINER ATTACHMENT HOLES . 23
FIGURE 3: CHANGE CARGO COMPARTMENT FRAME TO CARGO LINER ATTACHMENT HOLES . 25
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Commercial 
Airplanes
DC10
Service Bulletin
SummaryNumber: DC10-53-182Original Issue: June 28, 2013
ATA System: 5300
SUBJECT: FUSELAGE - Fuselage - Inspect/Change Left and Right Forward Cargo Compartment
Frame to Cargo Liner Attachment Holes
CONCURRENT REQUIREMENTS
None.
BACKGROUND
Federal Aviation Administration (FAA) requirement 14 Code of Federal Regulations (CFR) Part 26.21, Amendment
26-6 with effective date May 24/2012, requires the establishment of a binding schedule for the release of new
service actions (Service Bulletins) to support Widespread Fatigue Damage (WFD) rules Limit of Validity (LOV)
from current regulatory limits, refer to 14 CFR Part 121.1115. To extend the LOV for airplanes in Paragraph
1.A.1, Effectivity, beyond the FAA published dates in Table 1 of 14 CFR Part 121.1115, new service actions
have been identified. Inspecting and changing the frame fastener holes in the forward cargo compartment will
extend the LOV. If the inspection and modification is not completed, there may be undetected cracks in the
fastener holes which could result in the loss of fail safe structural integrity.
The left and right forward cargo compartment frames have been determined to be structure that is susceptible
to Widespread Fatigue Damage (WFD).
ACTION
This service bulletin provides instructions to do as follows:
1. Remove fasteners in the left and right hand sides of the forward cargo compartment.
2. Do an Eddy Current High Frequency (ETHF) inspection of the open fastener holes for cracks. Based
on inspection findings do what follows:
Condition 1 - No Crack Detected
a. Install Hi-Loks.
Condition 2 - Crack Detected in Any Hole
a. Contact Boeing to get instructions for the repair for this service bulletin, and do the work instructed
by Boeing.
EFFECTIVITY
DC-10-10, DC-10-10F, DC-10-30, DC-10-30F, DC-10-40, MD-10-10F, and MD-10-30F Airplane(s). Refer to
Paragraph 1.A.1., Airplanes, for the list of affected airplane(s).
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COMPLIANCE
The Federal Aviation Administration (FAA) will possibly release an Airworthiness Directive related to this service
bulletin. The Airworthiness Directive will make the compliance tasks and times given in this service bulletin
mandatory.
Refer to Paragraph 1.E., Compliance.
INDUSTRY SUPPORT INFORMATION
Boeing warranty remedies are not available for the inspection and/or repair procedures given in this service
bulletin.
MANPOWER
Refer to Paragraph 1.G., Manpower.
MATERIAL INFORMATION
Boeing Supplied Kits/Parts.
Refer to Paragraph 2.A., Material - Price and Availability.
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Commercial 
Airplanes
DC10
Service Bulletin
Number: DC10-53-182
Original Issue: June 28, 2013
ATA System: 5300
SUBJECT: FUSELAGE - Fuselage - Inspect/Change Left and Right Forward Cargo Compartment
Frame to Cargo Liner Attachment Holes
1.    PLANNING INFORMATION
A. Effectivity
1. Airplanes
DESCRIPTIONCONFIGURATIONGROUP
Airplanes with regular size forward cargo door.-1
Airplanes with oversize forward cargo door.-2
Airplane Models:
DC-10-10, DC-10-10F, DC-10-30, DC-10-30F, DC-10-40, MD-10-10F, MD-10-30F
GroupFuselage Num-
ber
11
12
13
14
15
16
17
18
19
110
111
112
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GroupFuselage Num-
ber
113
114
115
116
117
118
119
120
121
122
123
124
125
126
127
228
129
130
131
132
133
234
135
236
137
138
139
240
241
142
243
244
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GroupFuselage Num-
ber
145
246
147
148
149
150
151
152
253
154
155
156
257
158
159
260
161
162
263
164
165
266
167
168
269
170
271
172
273
174
275
176
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GroupFuselage Num-
ber
277
178
279
180
181
282
183
284
285
186
287
288
189
290
291
292
293
294
195
196
297
298
299
2100 - 102
1103
2. Spares Affected
None.
B. Concurrent Requirements
None.
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C. Reason
Federal Aviation Administration (FAA) requirement 14 Code of Federal Regulations (CFR) Part 26.21,
Amendment 26-6 with effective date May 24/2012, requires the establishment of a binding schedule
for the release of new service actions (Service Bulletins) to support Widespread Fatigue Damage (WFD)
rules Limit of Validity (LOV) from current regulatory limits, refer to 14 CFR Part 121.1115. To extend
the LOV for airplanes in Paragraph 1.A.1, Effectivity, beyond the FAA published dates in Table 1 of 14
CFR Part 121.1115, new service actions have been identified. Inspecting and changing the frame
fastener holes in the forward cargo compartment will extend the LOV. If the inspection and modification
is not completed, there may be undetected cracks in the fastener holes which could result in the loss
of fail safe structural integrity.
The left and right forward cargo compartment frames have been determined to be structure that is
susceptible to Widespread Fatigue Damage (WFD).
D. Description
This service bulletin provides instructions to do as follows:
1. Remove fasteners in the left and right hand sides of the forward cargo compartment.
2. Do an Eddy Current High Frequency (ETHF) inspection of the open fastener holes for cracks.
Based on inspection findings do what follows:
Condition 1 - No Crack Detected
a. Install Hi-Loks.
Condition 2 - Crack Detected in Any Hole
a. Contact Boeing to get instructions for the repair for this service bulletin, and do the work
instructed by Boeing.
The work in this service bulletin is done in the maintenance zone(s) given below.
Group 1:
Affected Maintenance Zones
ZoneModel
125, 126DC-10-10, DC-10-10F, DC-10-
30F, MD-10-10F, MD-10-30F
Group 2:
Affected Maintenance Zones
ZoneModel
125, 126DC-10-10, DC-10-10F, DC-10-
30, DC-10-40
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E. Compliance
The Federal Aviation Administration (FAA) will possibly release an Airworthiness Directive related to
this service bulletin. The Airworthiness Directive will make the compliance tasks and times given in this
service bulletin mandatory.
Do the required actions in accordance with Paragraph 3. Accomplishment Instructions.
Table 1: High Frequency Eddy Current Inspection for Cracks in Fuselage Frame Holes
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever
Occurs Later)
ActionCondition
-Within 72
months after the
original issue
date of this ser-
vice bulletin.
Before 30,000
total flight cy-
cles.
Do an Eddy Current High
Frequency (ETHF) inspec-
tion of left and right for-
ward cargo compartment
frame to cargo liner at-
tachment holes for cracks
and do the work of the
applicable condition that
follows.
All Airplanes
--Before further
flight.
Install Hi-Loks.Condition 1 - No Crack De-
tected.
--Before further
flight.
Contact Boeing to get in-
structions for the repair
for this service bulletin
and do the work instruct-
ed by Boeing.
Condition 2 - Crack Detect-
ed in Any Hole.
F. Approval
For DC-10 Series 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.
For MD-10 Series 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. 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.
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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.
G. Manpower
The table below shows an estimate of the task hours necessary to do this inspection/modification 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 inspect the work
 Time to cure the materials
 Time to make the parts
 Time to find the tools.
Group 1:
Elapsed HoursTask HoursNumber of PersonsTask
2.02.01FIGURE 1
16.016.01FIGURE 2
5.05.01FIGURE 3
23.023.0TOTAL FOR EACH AIRPLANE
NOTE: Task hours for the repair of crack damage, if any, are not listed.
Group 2:
Elapsed HoursTask HoursNumber of PersonsTask
2.52.51FIGURE 1
16.516.51FIGURE 2
5.55.51FIGURE 3
24.524.5TOTAL FOR EACH AIRPLANE
NOTE: Task hours for the repair of crack damage, if any, are not listed.
H. Weight and Balance Changes
Moment Change
(MEW) IN.-LBS
Mfr's Empty
Weight (MEW)
LBS
Approximate Sta-
tion (Inches)Kit SB10530182
+255.0+0.3+1010.6-3
+299.1+0.3+997.0-5
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I. Electrical Load Data
Not changed.
J. References
1. Existing Data:
a. Nondestructive Testing Standard Practice Manual (NDTSPM) (Publication MDC 93K0393),
Part 06 Eddy Current
b. DC-10, MD-10 Structural Repair Manual (SRM) Chapter 51
c. DC-10 Widespread Fatigue Damage / Limit of Validity (WFD/LOV) Document MDC 12K1003
2. Data Supplied with this Service Bulletin:
None.
3. Installation Drawings Used in the Preparation of this Service Bulletin:
ChangeTitleDocument Number
NEWFWD CARGO FRAME - INSPEC-
TION AND MOD
SR10530096
The table above lists the applicable drawing used to prepare this service bulletin. The drawing is
not necessary to make the specified changes, and is not supplied with this service bulletin. The
drawing may not be applicable to all airplane configurations or operators.
K. Publications Affected
1. Publications:
None.
2. Damage Tolerance Based Structural Inspections:
Boeing has evaluated the repairs and/or changes in this service bulletin for effects on Fatigue
Critical Structure (FCS) and for changes to Damage Tolerance Inspections (DTI) required in the
Maintenance Program. This service bulletin affects FCS but no new DTIs are necessary.
L. Interchangeability and Intermixability of Parts
Accomplishment of this service bulletin does not affect interchangeability or intermixability of parts.
M. Software Accomplishment Summary
Not affected.
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2.    MATERIAL INFORMATION
A. Material - Price and Availability
Boeing can supply the kits shown in Paragraph 2.C., Parts Necessary for Each Airplane. Operators
are encouraged to share schedule requirements with Boeing for incorporation of the service bulletin.
The kits are subject to the terms and conditions of the Boeing standard purchase order acknowledgment.
Prices are in United States Dollars. Terms: Net 30 days.
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
REFER TO THE BOEING PART PAGE ON MYBOEINGFLEET.COM OR CONTACT FIRST RESPONDER
AT FR@BOEING.COM FOR THE LATEST REORDER LEAD TIME (ROLT) AND PRICE INFORMATION
Unit Price as of
the original issue
date of this Ser-
vice Bulletin (US
Dollars)
ROLT as of the
original issue
date of this Ser-
vice Bulletin (Cal-
endar Days)
NameKit Number
$762.0060 daysFWD CARGO FRAME - INSPECTION AND
MOD
SB10530182-3
$801.0060 daysFWD CARGO FRAME - INSPECTION AND
MOD
SB10530182-5
B. Industry Support Information
Boeing warranty remedies are not available for the inspection and/or repair procedures 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.
Group 1:
Kit SB10530182
NotesExisting Part
Number
NameQTYNew Part Number
-3
----SB10530182-3
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Group 1:
Kit SB10530182
NotesExisting Part
Number
NameQTYNew Part Number
-3
(a) (b)MS20470AD5PIN-OVERSIZE76HLT426-6-2
--NUT76MS21042L3
--WASHER76NAS1252-10L
(a) Discard the existing part.
(b) May be purchased from: Hi-Shear Corporation, 2600 Skypark Drive
Torrance, California 90505; CAGE 73197
Group 2:
Kit SB10530182
NotesExisting Part
Number
NameQTYNew Part Number
-5
----SB10530182-5
(a) (b)MS20470AD5PIN-OVERSIZE80HLT426-6-2
--NUT80MS21042L3
--WASHER80NAS1252-10L
(a) Discard the existing part.
(b) May be purchased from: Hi-Shear Corporation, 2600 Skypark Drive
Torrance, California 90505; CAGE 73197
2. Parts and Materials Supplied by the Operator
The following parts or materials are necessary to do the change in this service bulletin. Parts and
materials in the manuals given in Paragraph 1.J., References, can also be necessary. Examine
operator part and material supply to make sure all necessary parts and materials are available.
NotesNameQTYPart Number /
Specification
(a)Sealant, Low Viscosity3 Pt.P/S 870 C-12/20
(DMS 2013 Type 1
Class A) or Equiva-
lent)
(a) Can be purchased from: PRC-DeSoto International 12780 San Fernando Road, Sylmar,
CA. 91342; CAGE 92108.
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3. Parts Modified and Reidentified
None.
4. Parts Removed and Not Replaced
None.
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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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: ELECTRICALLY GROUND THE AIRPLANE. THIS WILL HELP TO PREVENT DAMAGE
TO THE AIRPLANE OR EQUIPMENT.
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.
NOTE: 1. Manual titles are referred to by acronyms. Refer to Paragraph 1.J., References, for
definition of the acronyms.
2. Equivalent parts are listed in the AEPL, Drawing 7595071.
3. Use the approved fastener, process material substitutions, and installation in
accordance with DC-10, MD-10 SRM Chapter 51.
4. If the length of any fastener specified in this service bulletin does not meet installation
standards given in Structural Repair Manual (SRM) Chapter 51, then a fastener of
the same specification, or an approved substitute, with a length which meets the
installation standards given in SRM Chapter 51 may be used. In addition, washers
may be installed for fastener grip length in accordance with SRM Chapter 51.
5. A 1/8-inch thick stack of the same type washers called for in this service bulletin is
the maximum thickness which may be used under fastener head or nut to counteract
accumulation of tolerances.
EXCEPTION: When the available fastener length increments are greater than
1/16-inch, a 3/16-inch thick stack of the same type washers may be used.
6. Unless shown differently, these dimensions and tolerances are used:
– Linear dimensions are in inches
– Tolerance on linear dimensions, other than rivet and bolt edge margins, is plus
or minus 0.03 inch.
– Tolerance on rivet and bolt edge margin is plus or minus 0.05 inch
– Angular tolerance is plus or minus 2 degrees
– Hole dimensions for standard solid rivets are in DC-10, MD-10 SRM Chapter
51.
– Torque limits to tighten nuts and bolts are in DC-10, MD-10 SRM Chapter 51.
7. Obey all of the warnings and cautions given in the specified manual sections.
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8. These work instructions refer to procedures included in 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.
9. If it is necessary to remove more parts for access, you can remove those parts. If
you can get access without removing identified parts, it is not necessary to remove
all of the identified parts. Jacking and shoring limitations must be observed.
10. Shaded areas in Figures are reference only. Shaded areas in Figures may look
different than your airplane.
11. When more than one OPTION is given for a CONDITION, do only one of the OPTION
numbers. When more than one ACTION is given for a CONDITION number or an
OPTION number, do all of the ACTION numbers for that CONDITION number or
OPTION number.
12. The compliance times for the actions in Paragraph 3.B., WORK INSTRUCTIONS
are in Paragraph 1.E., Compliance.
B. WORK INSTRUCTIONS
1. Remove fasteners in accordance with FIGURE 1.
2. Do an Eddy Current High Frequency (ETHF) inspection of the frame open fastener holes in
accordance with FIGURE 2, based on inspection findings do as follows:
Condition 1 - No Crack Detected
a. Install Hi-Loks in accordance with FIGURE 3.
b. Return airplane to serviceable condition.
Condition 2 - Crack Detected in Any Hole
a. Contact Boeing to get instructions for the repair for this service bulletin, and do the work
instructed by Boeing.
b. Return airplane to serviceable condition.
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BOEING SERVICE BULLETIN DC10-53-182

### Page 21 (OCR)

BOEING SERVICE BULLETIN DC10-53-182
GROUP  LEFT SIDE STA Y=  RIGHT SIDE STA Y=
899, 919, 939, 959,  966, 979, 999, 1019,
979, 999,  1019  1039, 1059, 10/9,
1039,  1059, 1079,  1099
1099
2  879, 899, 919, 939,  879, 888.7, 1009.3,
959,  979, 999  019, 1039, 105
1019, 1039, 1059,  079. 1099
1079, 1099
• STRUT
L-38
X=82.00-
L-39
• STRUT
L-40
• Z = -93.50
INED  L-41
A-A  FRAME
LOOKING FORWARD
LEFT SIDE SHOWN
RIGHT SIDE OPPOSITE
FRAME
• FRAME
FIGURE 1: REMOVE CARGO COMPARTMENT FRAME TO CARGO LINER ATTACHMENT FASTENERS
(SHEET 1 OF 2)
Original Issue: June 28, 2013
PROPRIETARY - Copyright ® Unpublished  Export Controlled ECCN: 9E991 - BOEING  DC10-53-182
Work - See page 1 for details.  21 of 26

### Page 22

The step numbers shown below agree with the numbers shown in the circle symbols in the figure.
More DataQtyIdentificationNameTaskStep
-MS20470AD5RIVETRemove1
FIGURE 1: REMOVE CARGO COMPARTMENT FRAME TO CARGO LINER ATTACHMENT FASTENERS
(SHEET 2 OF 2)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: June 28, 2013
DC10-53-182
22 of 26
BOEING SERVICE BULLETIN DC10-53-182

### Page 23 (OCR)

BOEING SERVICE BULLETIN DC10-53-182
GROUP  LEFT SIDE STA Y=  RIGHT SIDE STA Y=
899, 919, 939, 959,  966, 979, 999, 1019,
979, 999,  1019  1039, 1059, 10/9,
1039,  1059, 1079,  1099
1099
2  879, 899, 919, 939,  879, 888.7, 1009.3,
959,  979, 999  019, 1039, 105
1019, 1039, 1059,  079. 1099
1079, 1099
• STRUT
L-38
X=82.00-
L-39
• STRUT
L-40
• Z = -93.50
INED  L-41
A-A  FRAME
LOOKING FORWARD
LEFT SIDE SHOWN
RIGHT SIDE OPPOSITE
TYPICAL  •TYPICAL
CRACK  CRACK
FRAME
• FRAME
2234888
FIGURE 2: INSPECT CARGO COMPARTMENT FRAME TO CARGO LINER ATTACHMENT HOLES
(SHEET 1 OF 2)
Original Issue: June 28, 2013
Export Controlled ECCN: 9E991 - BOEING  DC10-53-182
PROPRIETARY - Copyright ® Unpublished
Work - See page 1 for details.  23 of 26

### Page 24

The step numbers shown below agree with the numbers shown in the circle symbols in the figure.
More DataQtyIdentificationNameTaskStep
(a)4-HOLEInspect1
(a) Refer to Nondestructive Testing Standard Practice Manual NDTSPM Part 06 Eddy Current, Procedure
3, 06-10-01.003 as an accepted procedure.
FIGURE 2: INSPECT CARGO COMPARTMENT FRAME TO CARGO LINER ATTACHMENT HOLES
(SHEET 2 OF 2)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: June 28, 2013
DC10-53-182
24 of 26
BOEING SERVICE BULLETIN DC10-53-182

### Page 25 (OCR)

BOEING SERVICE BULLETIN DC10-53-182
GROUP  LEFT SIDE STA Y=  RIGHT SIDE STA Y=
899, 919, 939, 959,  966, 979, 999, 1019,
979, 999,  1019  1039, 1059, 10/9,
1039,  1059, 1079,  1099
1099
2  879, 899, 919, 939,  879, 888.7, 1009.3,
959,  979, 999  019, 1039, 105
1019, 1039, 1059,  079. 1099
1079, 1099
• STRUT
L-38
X=82.00-
L-39
• STRUT
L-40
• Z = -93.50
INED  L-41
A-A  FRAME
LOOKING FORWARD
LEFT SIDE SHOWN
RIGHT SIDE OPPOSITE
FRAME
• FRAME
FIGURE 3: CHANGE CARGO COMPARTMENT FRAME TO CARGO LINER ATTACHMENT HOLES
(SHEET 1 OF 2)
Original Issue: June 28, 2013
Export Controlled ECCN: 9E991 - BOEING  DC10-53-182
PROPRIETARY - Copyright ® Unpublished
Work - See page 1 for details.  25 of 26

### Page 26

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 frame.
More DataQtyIdentificationNameTaskStep
(a) (b) (c)4HLT426-6-2PIN-OVERSIZEInstall (New)1
(b)4MS21042L3NUTInstall (New)
(b)4NAS1252-10LWASHERInstall (New)
(a) Hole diameter 0.1981-0.2011
(b) Refer to DC-10, MD-10 SRM Chapter 51 as an accepted procedure.
(c) Install fasteners with DMS 2013 Type 1 Class A or equivalent sealant. Refer to DC-10, MD-10 SRM
Chapter 51 as an accepted procedure.
FIGURE 3: CHANGE CARGO COMPARTMENT FRAME TO CARGO LINER ATTACHMENT HOLES
(SHEET 2 OF 2)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: June 28, 2013
DC10-53-182
26 of 26
BOEING SERVICE BULLETIN DC10-53-182

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