# Boeing Alert Service Bulletin 767-53A0251: Revision 1

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- Document: [Boeing Alert Service Bulletin 767-53A0251](https://openairdocs.org/service-documents/boeing/767-53a0251.md)
- Title as filed: SB-767-53A0251-01--
- Pages: 53
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## Text

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### Page 1

Commercial 
Airplanes
767
Service Bulletin
ALERT
Number: 767-53A0251
Original Issue: August 07, 2013
Revision 1: March 07, 2017
ATA System: 5300
SUBJECT: FUSELAGE - Section 41 - Skins - Stringer 37 (S-37L and S-37R) Lap Splice Inspection
From Body Station 425 to Body Station 431
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Unpublished Work.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
Boeing liveries 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.
Original Issue: August 07, 2013
767-53A0251Revision 1: March 07, 2017
1 of 53
3.0

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Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: August 07, 2013
767-53A0251Revision 1: March 07, 2017
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BOEING SERVICE BULLETIN 767-53A0251
ALERTALERT
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Table of Contents
Revision Transmittal Sheet . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5
Summary . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7
1. PLANNING INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11
A. Effectivity . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11
1. Airplanes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11
2. Spares Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17
B. Concurrent Requirements . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17
C. Reason . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17
D. Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 18
E. Compliance . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 18
F. Approval . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21
G. Manpower . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21
H. Weight and Balance Changes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 22
I. Electrical Load Data . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 22
J. References . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 23
1. Existing Data: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 23
2. Data Supplied with this Service Bulletin: . . . . . . . . . . . . . . . . . . . . . . . . . . . 23
3. Installation Drawings Used in the Preparation of this Service Bulletin: . . . . . . . . . . . 23
K. Publications Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 23
L. Interchangeability and Intermixability of Parts . . . . . . . . . . . . . . . . . . . . . . . . . . . 23
M. Software Accomplishment Summary . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 24
2. MATERIAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25
A. Material - Price and Availability . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25
B. Industry Support Information . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25
C. Parts Necessary for Each Airplane . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25
1. Kits/Parts . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25
2. Parts and Materials Supplied by the Operator . . . . . . . . . . . . . . . . . . . . . . . . 25
3. Parts Modified and Reidentified . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25
4. Parts Removed and Not Replaced . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25
D. Parts Necessary to Change Spares . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 26
E. Special Tooling - Price and Availability . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 26
F. Special Tooling Necessary to do this Service Bulletin . . . . . . . . . . . . . . . . . . . . . . . 26
3. ACCOMPLISHMENT INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 27
A. GENERAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 27
B. WORK INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 29
FIGURE 1: SKIN INSPECTION FOR MISSING FASTENERS  [Group 1] . . . . . . . . . . . . . . . . 32
FIGURE 2: SKIN DETAILED AND OPEN-HOLE INSPECTION [Group 1] . . . . . . . . . . . . . . . . 35
FIGURE 3: FASTENER INSTALLATION [Group 1] . . . . . . . . . . . . . . . . . . . . . . . . . . . . 39
FIGURE 4: SKIN INSPECTION FOR MISSING FASTENERS  [Group 2] . . . . . . . . . . . . . . . . 43
FIGURE 5: SKIN DETAILED AND OPEN-HOLE INSPECTION [Group 2] . . . . . . . . . . . . . . . . 46
FIGURE 6: FASTENER INSTALLATION [Group 2] . . . . . . . . . . . . . . . . . . . . . . . . . . . . 50
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: August 07, 2013
767-53A0251Revision 1: March 07, 2017
3 of 53
BOEING SERVICE BULLETIN 767-53A0251
ALERTALERT

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Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: August 07, 2013
767-53A0251Revision 1: March 07, 2017
4 of 53
BOEING SERVICE BULLETIN 767-53A0251
ALERTALERT
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Commercial 
Airplanes
767
Service Bulletin
ALERT
Revision Transmittal SheetNumber: 767-53A0251Original Issue: August 07, 2013
Revision 1: March 07, 2017
ATA System: 5300
SUBJECT: FUSELAGE - Section 41 - Skins - Stringer 37 (S-37L and S-37R) Lap Splice Inspection
From Body Station 425 to Body Station 431
This revision includes all pages of the service bulletin.
COMPLIANCE INFORMATION RELATED TO THIS REVISION
Federal Aviation Administration (FAA) Airworthiness Directive AD 2015-19-12 is related to this service bulletin.
Effects of this Revision on airplanes on which Original Issue was previously done:
ActionConditionGroup
No more work is required.-Group 1
Do external inspection of Stringer 37 (S-37L and S-37R)
for missing fasteners. If fasteners are missing, install
missing fasteners. If no fasteners are found to be
missing, no more work is required.
-Group 2
Airplane line numbers 1 through 928 were added to Group 2 of this service bulletin effectivity.
REASON FOR REVISION
This revision is sent to do external inspection of Stringer 37 (S-37L and S-37R) for missing fasteners. If fasteners
are missing, install missing fasteners. Airplane line numbers 1 through 928 were added to Group 2 of this service
bulletin effectivity.
These sections were changed:
1. Summary, BACKGROUND - Updated information.
2. Summary, COMPLIANCE - Updated data.
3. Paragraph 1.A.1., Airplanes - Add airplane line numbers 1 through 928 to Group 2.
4. Paragraph 1.C., Reason - Updated information.
5. Paragraph 1.D., Description - Updated information.
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: August 07, 2013
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### Page 6

6. Paragraph 1.G., Manpower - Added tables.
7. Paragraph 1.E., Compliance - Updated data and Added table.
8. Paragraph 1.F., Approval - Added AMOC statement.
9. Paragraph 1.J.1., References - Existing Data - Updated information.
10. Paragraph 2.C.2., Parts and Materials Supplied by the Operator - Updated quantity.
11. Paragraph 3.A., General Information - Updated the notes.
12. Paragraph 3.B., Work Instructions - Updated work instructions.
13. Figure 1, Figure 2 and Figure 3 - Updated illustrations.
14. Added Figure 4, Figure 5 and Figure 6.
Vertical lines are put on the left edge of each page, except in Paragraph 1.A., Effectivity and format changes,
to show the location of all content changes.
Pages with no vertical lines have no changes.
REVISION HISTORY
August 07, 2013Original Issue:
March 07, 2017Revision 1:
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: August 07, 2013
767-53A0251Revision 1: March 07, 2017
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BOEING SERVICE BULLETIN 767-53A0251
ALERTALERT

### Page 7

Commercial 
Airplanes
767
Service Bulletin
ALERT
SummaryNumber: 767-53A0251Original Issue: August 07, 2013
Revision 1: March 07, 2017
ATA System: 5300
SUBJECT: FUSELAGE - Section 41 - Skins - Stringer 37 (S-37L and S-37R) Lap Splice Inspection
From Body Station 425 to Body Station 431
THIS DOCUMENT IS SENT TO THE OPERATORS OF RECORD OF THE AIRPLANES SHOWN IN
PARAGRAPH 1.A., EFFECTIVITY. IF AN AIRPLANE HAS BEEN LEASED OR SOLD, SEND THIS DOCUMENT
TO THE NEW OPERATOR. IF APPLICABLE SPARES HAVE BEEN SOLD, SEND THIS DOCUMENT TO THE
NEW OWNER.
CONCURRENT REQUIREMENTS
None.
BACKGROUND
This service bulletin gives instructions to do inspections of Stringer 37 (S-37L and S-37R) lap splice just forward
of the Body Station (STA) 434 circumferential splice for missing fasteners. Missing fasteners can result in cracks
in the fuselage skin, which could adversely affect the structural integrity of the airplane.
Boeing has discovered that up to ten fasteners may not have been installed in Stringer 37 (S-37L and S-37R)
lap splices on some airplanes during production. Accomplishment of the inspections and fastener installations,
if necessary, in this service bulletin will help ensure the structural integrity of the S-37 lap splices.
Boeing Service Related Problem (SRP) 767-53-0424 and 767-53-0534 are related to this service bulletin.
This table is provided to operators for planning purposes only. Refer to the applicable sections for more
information.
ReferenceAffectedPlanning Data
Paragraph 1.A.2., Spares AffectedNoSpares Affected
Paragraph 1.E., Compliance and Paragraph
1.F., Approval
YesAD Related
Paragraph 1.H., Weight and Balance ChangesNoWeight and Balance Change
Paragraph 1.I., Electrical Load DataNoElectrical Load Changed
Paragraph 1.K., Publications AffectedNoPublications Affected
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
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ReferenceAffectedPlanning Data
Paragraph 1.K., Publications AffectedNoAirplane Flight Operations Affected (Flight Crew
Operations Manual and/or FAA Approved Air-
plane Flight Manual)
Paragraph 2.C.1., Kits/PartsNoKits/Parts Required
Paragraph 2.C.2., Parts and Materials Supplied
by the Operator
YesOperator Supplied Parts/Material
Paragraph 2.F., Special Tooling Necessary to
do this Service Bulletin
NoSpecial Tooling Required
ACTION
Do external general visual inspections of Stringer 37 (S-37L and S-37R) lap splices for missing fasteners. If no
fasteners are found to be missing, no more work is required.
If fasteners are found to be missing, get internal access and remove fasteners adjacent to the missing fastener
locations. Do internal and external detailed inspections in the area for any crack or corrosion, or any other
discrepancy, such as broken sealant. Also do open-hole High Frequency Eddy Current (HFEC) inspections of
the skin at the open fastener holes for cracks. If no crack or corrosion is found, install fasteners in accordance
with this service bulletin.
If any crack or corrosion is found, determine if the damage is within the repair limits in the SRM. If all cracking
and corrosion is within the repair limits in the SRM, do repairs in accordance with the SRM. If any crack or
corrosion is found that is beyond the repair limits in the SRM, contact Boeing for repair instructions and do the
repair.
EFFECTIVITY
767-200, 767-300, 767-300F and 767-400ER Airplanes. Refer to Paragraph 1.A.1., Airplanes, for the list of
affected airplane(s).
COMPLIANCE
Federal Aviation Administration (FAA) Airworthiness Directive AD 2015-19-12 is related to this service bulletin.
The effective date of AD 2015-19-12 is November 3, 2015.
This service bulletin affects SSI 53-10-I07C and 53-10-I07D of MPD D622T001 Section 9.
Refer to Paragraph 1.E., Compliance.
INDUSTRY SUPPORT INFORMATION
Boeing warranty remedies are available for airplanes in warranty as of September 11, 2012. Please refer to
Paragraph 2.B., Industry Support Information. The warranty remedies will expire eight years from the original
issue date of this service bulletin.
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
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MANPOWER
Elapsed HoursTotal Task HoursAirplanes
0.100.10Inspection for missing fasteners
7.2512.75Additional inspections and fastener instal-
lation if fasteners are found to be miss-
ing
Refer to Paragraph 1.G., Manpower.
MATERIAL INFORMATION
Operator Supplied Parts/Materials.
Refer to Paragraph 2.A., Material - Price and Availability.
Export Controlled ECCN: 9E991 - BOEING
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### Page 10 (OCR)

BOEING SERVICE BULLETIN 767-53A0251
ALERT  ALERT
STA
434
STA
246
STA
434
S-171
→ S-26L
*S-37L
S-37R
DO EXTERNAL GENERAL VISUAL INSPECTIONS
OF STRINGER (S37-LAND S37-R) LAP SPLICES,
JUST FORWARD OF THE STA 434
CIRCUMFERENTIAL SPLICE, FOR MISSING
FASTENERS. IF NO FASTENERS ARE MISSING,
NO MORE WORK IS NECESSARY. IF
FASTENERS ARE MISSING, DO ADDITIONAL
INSPECTIONS, REPAIR IF NECESSARY, AND
INSTALL FASTENERS.
Original Issue: August 07, 2013
Revision 1: March 07, 2017  Export Controlled ECCN: 9E991 - BOEING  PROPRIETARY - Copyright © Unpublished  767-53A0251
Work - See page 1 for details.  10 of 53

### Page 11

Commercial 
Airplanes
767
Service Bulletin
ALERT
Number: 767-53A0251
Original Issue: August 07, 2013
Revision 1: March 07, 2017
ATA System: 5300
SUBJECT: FUSELAGE - Section 41 - Skins - Stringer 37 (S-37L and S-37R) Lap Splice Inspection
From Body Station 425 to Body Station 431
THIS DOCUMENT IS SENT TO THE OPERATORS OF RECORD OF THE AIRPLANES SHOWN IN
PARAGRAPH 1.A., EFFECTIVITY. IF AN AIRPLANE HAS BEEN LEASED OR SOLD, SEND THIS DOCUMENT
TO THE NEW OPERATOR. IF APPLICABLE SPARES HAVE BEEN SOLD, SEND THIS DOCUMENT TO THE
NEW OWNER.
1.    PLANNING INFORMATION
A. Effectivity
1. Airplanes
This service bulletin is applicable to 767-200, 767-300, 767-300F and 767-400ER Airplanes, line
numbers 1-1028 in 2 Group. The Variable Numbers and Group Information for the applicable
airplanes is given below.
Refer to Service Bulletin Index D624T001 Part 3 for Airplane Variable Number, Line Number, and
Serial Number data.
DESCRIPTIONCONFIGURATIONGROUP
767-200, 767-300, 767-300F and 767-400ER airplanes line numbers
929 through 1028.
-1
767-200, 767-300, 767-300F and 767-400ER airplanes line numbers
1 through 928.
-2
Airplane Models:
767-200, 767-300, 767-300F, 767-400ER
GroupVariable Number
2VA001 - VA020
2VA301 - VA315
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GroupVariable Number
2VA501 - VA530
2VA701 - VA719
2VA801 - VA810
2VB001 - VB002
2VB051 - VB055
2VB101 - VB125
2VB201 - VB202
2VB251 - VB253
2VB281 - VB284
2VB301 - VB302
2VB321 - VB332
2VB371 - VB373
2VB401
2VB441 - VB444
2VE001 - VE003
2VE021 - VE023
2VE041 - VE043
2VE061 - VE069
2VE083 - VE086
2VE101 - VE104
2VE116 - VE118
2VE121 - VE126
2VE141 - VE152
2VE171 - VE172
2VF001 - VF002
2VF041 - VF042
2VF051
2VF061 - VF062
2VF071 - VF072
2VF091 - VF093
2VF101 - VF102
2VF161 - VF162
2VF171 - VF172
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GroupVariable Number
2VF180 - VF184
2VF251
2VK001 - VK016
2VK021 - VK022
2VK031 - VK056
2VK081 - VK113
2VK131 - VK133
2VK141 - VK148
2VK161 - VK164
2VK171
2VK181
2VK186
2VL001 - VL006
2VL011
2VL701 - VL703
2VL751 - VL755
2VL806 - VL807
2VL871 - VL873
2VL891 - VL900
2VL911 - VL914
2VL931 - VL932
2VL941
2VN001 - VN041
2VN051 - VN064
2VN081 - VN099
2VN111 - VN127
2VN130 - VN137
2VN151 - VN158
2VN163 - VN168
2VN171 - VN174
2VN191 - VN198
2VN211 - VN212
2VN221 - VN225
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GroupVariable Number
2VN231 - VN234
2VN241 - VN243
2VN251 - VN276
2VN291 - VN293
2VN301 - VN314
2VN371 - VN372
2VN376
2VN381 - VN388
2VN421 - VN427
2VN436
2VN471 - VN472
2VN491 - VN513
2VN531 - VN532
2VN536 - VN537
2VN541 - VN542
2VN546 - VN547
2VN551
2VN556 - VN557
2VN561 - VN562
2VN631 - VN638
2VN651 - VN658
2VN671 - VN672
2VN676
2VN681 - VN691
2VN731 - VN732
2VN751 - VN753
2VN791 - VN792
2VN811 - VN813
2VN921 - VN922
2VN931 - VN936
2VN951 - VN953
2VN966 - VN972
2VQ001 - VQ021
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GroupVariable Number
2VQ071 - VQ086
1VQ111
2VR051 - VR060
2VR081
2VR084
2VR086
1VR087 - VR089
1VR106 - VR109
2VR201 - VR211
2VR251
2VR256 - VR260
1VR266 - VR283
2VR401
2VR421 - VR423
2VR426
2VR441
2VR461
2VR471 - VR472
2VS051 - VS056
2VS061
2VS066 - VS070
2VS073 - VS078
2VS091 - VS104
2VS111 - VS113
2VS131 - VS133
2VS136 - VS137
2VS176 - VS177
2VS186 - VS187
2VS196 - VS203
2VS206 - VS208
2VS211
2VS216 - VS217
2VS231
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GroupVariable Number
2VS246 - VS248
2VS261 - VS263
2VS266 - VS274
2VS291 - VS293
2VS301 - VS303
2VS306 - VS311
2VS316
2VS321 - VS324
2VS331 - VS333
2VS336 - VS337
2VS366 - VS367
2VS381 - VS382
2VS391 - VS392
2VS401
2VS426 - VS428
2VS466 - VS472
2VS486
2VS496 - VS497
2VS506 - VS507
2VS526
2VS546 - VS549
2VS701 - VS711
1VS712 - VS720
2VS721 - VS731
1VS732 - VS736
2VS751 - VS759
2VS821 - VS825
2VS841 - VS844
2VS861
2VS881 - VS882
1VS883
2VS891
2VS896
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GroupVariable Number
1VS901 - VS912
1VS916
1VS921 - VS928
1VS931 - VS933
1VS941
1VS951 - VS954
1VS961 - VS969
1VS971 - VS976
1VS981 - VS982
2VT501
1VT511 - VT513
1VT521 - VT523
1VT531 - VT533
1VT541 - VT543
1VT551
2VV001
2VW701 - VW721
2VW851
2. Spares Affected
None.
B. Concurrent Requirements
None.
C. Reason
This service bulletin gives instructions to do inspections of Stringer 37 (S-37L and S-37R) lap splice
just forward of the Body Station (STA) 434 circumferential splice for missing fasteners. Missing fasteners
can result in cracks in the fuselage skin, which could adversely affect the structural integrity of the
airplane.
Boeing has discovered that up to ten fasteners may not have been installed in Stringer 37 (S-37L and
S-37R) lap splices on some airplanes during production. Accomplishment of the inspections and fastener
installations, if necessary, in this service bulletin will help ensure the structural integrity of the S-37 lap
splices.
Boeing Service Related Problem (SRP) 767-53-0424 and 767-53-0534 are related to this service
bulletin.
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Revision 1 is sent to do external inspection of Stringer 37 (S-37L and S-37R) for missing fasteners. If
fasteners are missing, install missing fasteners. Airplane line numbers 1 through 928 were added to
Group 2 of this service bulletin effectivity.
D. Description
Do external general visual inspections of Stringer 37 (S-37L and S-37R) lap splices for missing fasteners.
If no fasteners are found to be missing, no more work is required.
If fasteners are found to be missing, get internal access and remove fasteners adjacent to the missing
fastener locations. Do internal and external detailed inspections in the area for any crack or corrosion,
or any other discrepancy, such as broken sealant. Also do open-hole High Frequency Eddy Current
(HFEC) inspections of the skin at the open fastener holes for cracks. If no crack or corrosion is found,
install fasteners in accordance with this service bulletin.
If any crack or corrosion is found, determine if the damage is within the repair limits in the SRM. If all
cracking and corrosion is within the repair limits in the SRM, do repairs in accordance with the SRM.
If any crack or corrosion is found that is beyond the repair limits in the SRM, contact Boeing for repair
instructions and do the repair.
Effects of this Revision on airplanes on which Original Issue was previously done:
ActionConditionGroup
No more work is required.-Group 1
Do external inspection of Stringer 37 (S-37L and S-37R)
for missing fasteners. If fasteners are missing, install
missing fasteners. If no fasteners are found to be
missing, no more work is required.
-Group 2
Airplane line numbers 1 through 928 were added to Group 2 of this service bulletin effectivity.
The work in this service bulletin is done in the maintenance zone(s) given below.
Affected Maintenance Zones
ZoneModel
123, 124767-200, 767-300, 767-300F,
767-400ER
E. Compliance
Federal Aviation Administration (FAA) Airworthiness Directive AD 2015-19-12 is related to this service
bulletin. The effective date of AD 2015-19-12 is November 3, 2015.
This service bulletin affects SSI 53-10-I07C and 53-10-I07D of MPD D622T001 Section 9.
Do the required actions in accordance with Paragraph 3. Accomplishment Instructions.
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Group 1:
Table 1: S-37 Lap Splice Inspection for Missing Fasteners Between STA 425 and 431
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever
Occurs First)
ActionCondition
-Within 2 years
after the effec-
tive date of AD
2015-19-12.
Within 3,000
flight cycles af-
ter the effective
date of AD
2015-19-12.
Do an external General
Visual Inspection of
Stringer 37 (S-37L and S-
37R) lap splice, just for-
ward of the circumferen-
tial splice at Body Station
(STA) 434, for missing
fasteners.
All affected airplanes.
--No more work is neces-
sary.
CONDITION 1: NO MISS-
ING FASTENERS
-Before further flight.Remove fasteners adja-
cent to the missing fasten-
er locations. Do detailed
inspections for any crack,
any corrosion, and any
other discrepancy, such
as broken sealant. Do
open-hole HFEC inspec-
tions for cracks at the
open fastener holes.
CONDITION 2: ANY
MISSING FASTENERS
-Before further flight.Install fasteners.CONDITION 3: NO
CRACK, CORROSION OR
OTHER DISCREPANCY
FOUND
-Before further flight.Determine if the crack,
corrosion or other discrep-
ancy is within the repair
limits in the SRM.
CONDITION 4: ANY
CRACK, CORROSION OR
OTHER DISCREPANCY
FOUND
-Before further flight.Repair in accordance with
the SRM.
CONDITION 5: ALL
CRACKING, CORROSION
OR OTHER DISCREPAN-
CY FOUND IS WITHIN
SRM LIMITS
-Before further flight.Contact Boeing for repair
instructions and do the
repair.
CONDITION 6: ANY
CRACK, CORROSION OR
OTHER DISCREPANCY
FOUND THAT IS BEYOND
SRM LIMITS
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Group 2:
Table 2: S-37 Lap Splice Inspection for Missing Fasteners Between STA 425 and 431
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever
Occurs First)
ActionCondition
-Within 2 years
after the Revi-
sion 1 date of
this service bul-
letin.
Within 3,000
flight-cycles af-
ter the Revision
1 date of this
service bulletin.
Do an external General
Visual Inspection of
Stringer 37 (S-37L and S-
37R) lap splice, just for-
ward of the circumferen-
tial splice at Body Station
(STA) 434, for missing
fasteners.
All affected airplanes.
--No more work is neces-
sary.
CONDITION 1: NO MISS-
ING FASTENERS
-Before further flight.Remove fasteners adja-
cent to the missing fasten-
er locations. Do detailed
inspections for any crack,
any corrosion, and any
other discrepancy, such
as broken sealant. Do
open-hole HFEC inspec-
tions for cracks at the
open fastener holes.
CONDITION 2: ANY
MISSING FASTENERS
-Before further flight.Install fasteners.CONDITION 3: NO
CRACK, CORROSION OR
OTHER DISCREPANCY
FOUND
-Before further flight.Determine if the crack,
corrosion or other discrep-
ancy is within the repair
limits in the SRM.
CONDITION 4: ANY
CRACK, CORROSION OR
OTHER DISCREPANCY
FOUND
-Before further flight.Repair in accordance with
the SRM.
CONDITION 5: ALL
CRACKING, CORROSION
OR OTHER DISCREPAN-
CY FOUND IS WITHIN
SRM LIMITS
-Before further flight.Contact Boeing for repair
instructions and do the
repair.
CONDITION 6: ANY
CRACK, CORROSION OR
OTHER DISCREPANCY
FOUND THAT IS BEYOND
SRM LIMITS
NOTE: 1. Lap splice fastener installation and repairs will affect Structural Significant Items
(SSIs) 53-10-I07C and 53-10-I07D as listed in 767 MPD Section 9, Airworthiness
Limitations - Structural Inspections.
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2. After accomplishment of this service bulletin, refer to the 767 MPD Section 9,
Airworthiness Limitation - Structural Inspection, for inspections.
F. Approval
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.
The Manager of the FAA Seattle Aircraft Certification Office approves the inspections, related
investigative and corrective actions defined in this service bulletin as an alternative method of compliance
to the inspections, related investigative and corrective actions required by paragraph (g) of AD
2015-19-12. All provisions of AD 2015-19-12 that are not specifically referenced above remain fully
applicable and must be complied with accordingly.
G. Manpower
The table below shows an estimate of the task hours necessary to do this inspection 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:
Table 1 - Inspection for Missing Fasteners
Elapsed HoursTask HoursNumber of PersonsTask
0.100.101Inspect for missing
fasteners (Figure 1)
0.100.10TOTAL FOR EACH AIRPLANE
Group 1:
Table 2 - Additional Inspections and Fastener Installation if Fasteners are Found to be
Missing
Elapsed HoursTask HoursNumber of PersonsTask
2.755.502Open internal access
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Group 1:
Table 2 - Additional Inspections and Fastener Installation if Fasteners are Found to be
Missing
Elapsed HoursTask HoursNumber of PersonsTask
1.251.251Detailed and eddy
current inspections
(Figure 2)
0.650.651Fastener installation
(Figure 3)
2.755.502Close Access
7.4012.90TOTAL FOR EACH AIRPLANE
Group 2:
Table 3 - Inspection for Missing Fasteners
Elapsed HoursTask HoursNumber of PersonsTask
0.100.101Inspect for missing
fasteners (Figure 4)
0.100.10TOTAL FOR EACH AIRPLANE
Group 2:
Table 4 - Additional Inspections and Fastener Installation if Fasteners are Found to be
Missing
Elapsed HoursTask HoursNumber of PersonsTask
2.755.502Open internal access
1.251.251Detailed and eddy
current inspections
(Figure 5)
0.750.751Fastener installation
(Figure 6)
2.755.502Close Access
7.5013.00TOTAL FOR EACH AIRPLANE
NOTE: More time is required for repairs if damage is found.
H. Weight and Balance Changes
None.
I. Electrical Load Data
Not changed.
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J. References
1. Existing Data:
a. Boeing Service Letter 767-SL-51-036
b. Boeing Service Related Problem (SRP) 767-53-0424, 767-53-0534
c. Federal Aviation Administration (FAA) Airworthiness Directive (AD) 2015-19-12
d. Service Bulletin Index D624T001
e. Standard Overhaul Practices Manual (SOPM) 20-50-01
f. 767 Aircraft Maintenance Manual (AMM) 25-52-03, 52-33-00, 53-01-05
g. 767 Maintenance Planning Data (MPD) Section 9
h. 767 Non-Destructive Testing (NDT) Manual Part 6, 51-00-04, Part 6, 51-00-11, Part 6, 51-00-16
i. 767-200 Structural Repair Manual (SRM) 51-40-05, 53-00-01
j. 767-300 Structural Repair Manual (SRM) 51-41-05, 53-00-01
k. 767-300F Structural Repair Manual (SRM) 51-41-05, 53-00-01
l. 767-400 Aircraft Maintenance Manual (AMM) 25-52-03, 52-33-00, 53-01-05
m. 767-400 Structural Repair Manual (SRM) 51-40-05, 53-00-01
2. Data Supplied with this Service Bulletin:
None.
3. Installation Drawings Used in the Preparation of this Service Bulletin:
None.
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.
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M. Software Accomplishment Summary
Not affected.
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2.    MATERIAL INFORMATION
A. Material - Price and Availability
None.
B. Industry Support Information
Boeing warranty remedies are available for 767 airplanes in warranty as of September 11, 2012. For
inspection labor task hour reimbursement for airplanes in warranty as of that date, send a warranty
claim to Boeing Warranty & Product Assurance Contracts. If the condition described in this service
bulletin is found during the inspection for airplanes in warranty as of that date and additional task hours
and parts are required, send a warranty claim to Boeing Warranty & Product Assurance Contracts.
Please refer to this service bulletin number and reference the airplane variable numbers in your purchase
order. The warranty remedies will expire eight years from the original issue date of this service bulletin.
C. Parts Necessary for Each Airplane
1. Kits/Parts
None.
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
BACR15FV6KE7 optional.
(a) (c)
Rivet28BACR15FV6KE6
BACR15FV6KE8 optional.
(a) (c)
Rivet14BACR15FV6KE7
(b)Sealant8
ounces
BMS 5-95
(a) Refer to 767 Structural Repair Manual Chapter 51 for alternate fasteners.
(b) Refer to the Qualified Products List at the end of the Boeing Material Specification (BMS)
for supplier data.
(c) Quantity required is per airplane as necessary.
3. Parts Modified and Reidentified
None.
4. Parts Removed and Not Replaced
None.
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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
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. Obey all of the warnings and cautions given in the specified manual sections.
3. 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 and fasteners are in Structural Repair
Manual (SRM) Chapter 51
– Torque Values:
— Values for structural fasteners are given in 767 Structural Repair Manual,
Chapter 51.
4. Use the approved fastener, process and material substitutions in accordance with
SRM Chapter 51.
5. If the length of any fastener specified in this service bulletin does not meet installation
standards given in 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. Refer to SOPM 20-50-01 for alternate
full threaded fasteners (screws) needed for installation in this service bulletin.
6. A Detailed Inspection is defined as: An intensive examination of a specific item,
installation, or assembly to detect damage, failure, or irregularity. Available lighting
is normally supplemented with a direct source of good lighting at an intensity deemed
appropriate. Inspection aids such as mirrors, magnifying lenses, etc. may be
necessary. Surface cleaning and elaborate procedures may be required.
7. A General Visual Inspection is defined as: A visual examination of an interior or
exterior area, installation or assembly to detect obvious damage, failure or irregularity.
This level of inspection is made from within touching distance unless otherwise
specified. A mirror may be necessary to enhance visual access to all exposed surfaces
in the inspection area. This level of inspection is made under normally available
lighting conditions such as daylight, hangar lighting, flashlight or drop-light and may
require removal or opening of access panels or doors. Stands, ladders or platforms
may be required to gain proximity to the area being checked.
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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. Boeing Service Letter 767-SL-51-036, Damage Reporting and Repair Plan/Design
Guidelines, is an acceptable procedure to request information from Boeing for
additional structural repair instructions. The Service Letter describes what information
must be provided to Boeing before a structural repair can be provided.
10. The instructions in Paragraph 3.B., Work Instructions and the figures can include
operation of tools or test equipment. Boeing Engineering Tool Drawings, the Illustrated
Tool and Equipment Manual, and the Special Tool and Ground Handling Drawing
Index contain data on versions of the tools or test equipment that you can use. It is
permitted to use replaced tools. It is not permitted to use superseded tools.
11. 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.
12. Where the work instructions include installation of a kept part, a new or serviceable
part with the same part number can be installed as an alternative to the kept part.
13. If shading is used, shaded areas in Figures are to separate the non-critical and
non-authoritative information from the critical and authoritative information.
14. 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.
15. The compliance times for the actions in Paragraph 3.B., WORK INSTRUCTIONS
are in Paragraph 1.E., Compliance.
16. The CONDITIONS, ACTIONS and OPTIONS shown apply to each side of the airplane
independently.
17. Some steps in the Work Instructions are labeled as Required for Compliance (RC).
If this service bulletin is mandated by an Airworthiness Directive (AD), then the steps
labeled as RC, including sub-steps under an RC step and any figures identified in
an RC step, must be done to comply with the AD. If a step or sub-step is labeled
"RC Exempt," then the RC requirement is removed from that step or sub-step. An
Alternative Method of Compliance (AMOC) is required for any deviations to RC steps,
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including sub-steps and identified figures. Steps not labeled as RC may be deviated
from using accepted methods in accordance with the operator's maintenance or
inspection program without obtaining approval of an AMOC. This is provided that
the RC steps, including sub-steps and identified figures, can still be done as specified,
and the airplane can be put back in an airworthy condition.
B. WORK INSTRUCTIONS
Group 1:
1. RC - Do an external General Visual Inspection of Stringer 37 (S-37L and S-37R) lap splice, just
forward of the circumferential splice at Body Station (STA) 434, for missing fasteners in accordance
with FIGURE 1.
a. CONDITION 1: NO MISSING FASTENERS
(1) No more work is required.
b. CONDITION 2: ANY MISSING FASTENERS
(1) Get internal access. Refer to PART 1 - ACCESS as an accepted procedure.
(2) Remove fasteners adjacent to the missing fasteners.
(3) Do inspections in accordance with FIGURE 2.
(a) CONDITION 3: NO CRACK, CORROSION OR OTHER DISCREPANCY FOUND
1) Install fasteners in accordance with FIGURE 3.
(b) CONDITION 4: ANY CRACK, CORROSION OR OTHER DISCREPANCY FOUND
1) Determine if the crack, corrosion or other discrepancy is within the repair limits
in 767-200 SRM 53-00-01, 767-300 SRM 53-00-01, 767-300F SRM 53-00-01
or 767-400 SRM 53-00-01.
a) CONDITION 5: ALL CRACKING, CORROSION OR OTHER DISCREPANCY
FOUND IS WITHIN SRM LIMITS
{1} Repair in accordance with 767-200 SRM 53-00-01, 767-300 SRM
53-00-01, 767-300F SRM 53-00-01 or 767-400 SRM 53-00-01.
b) CONDITION 6: ANY CRACK, CORROSION OR OTHER DISCREPANCY
FOUND THAT IS BEYOND SRM LIMITS
{1} Contact Boeing for repair instructions and do the repair.
c. Apply finishes to the affected area to match adjacent structure.
d. Install equipment that was removed for internal access. Refer to PART 2 - RESTORATION
as an accepted procedure.
2. Put the airplane back to a serviceable condition.
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Group 2:
1. RC - Do an external General Visual Inspection of Stringer 37 (S-37L and S-37R) lap splice, just
forward of the circumferential splice at Body Station (STA) 434, for up to 10 missing fasteners in
accordance with FIGURE 4.
a. CONDITION 1: NO MISSING FASTENERS
(1) No more work is required.
b. CONDITION 2: ANY MISSING FASTENERS
(1) Get internal access. Refer to PART 1 - ACCESS as an accepted procedure.
(2) Remove fasteners adjacent to the missing fasteners.
(3) Do inspections in accordance with FIGURE 5.
(a) CONDITION 3: NO CRACK, CORROSION OR OTHER DISCREPANCY FOUND
1) Install fasteners in accordance with FIGURE 6.
(b) CONDITION 4: ANY CRACK, CORROSION OR OTHER DISCREPANCY FOUND
1) Determine if the crack, corrosion or other discrepancy is within the repair limits
in 767-200 SRM 53-00-01, 767-300 SRM 53-00-01, 767-300F SRM 53-00-01
or 767-400 SRM 53-00-01.
a) CONDITION 5: ALL CRACKING, CORROSION OR OTHER DISCREPANCY
FOUND IS WITHIN SRM LIMITS
{1} Repair in accordance with 767-200 SRM 53-00-01, 767-300 SRM
53-00-01, 767-300F SRM 53-00-01 or 767-400 SRM 53-00-01.
b) CONDITION 6: ANY CRACK, CORROSION OR OTHER DISCREPANCY
FOUND THAT IS BEYOND SRM LIMITS
{1} Contact Boeing for repair instructions and do the repair.
c. Apply finishes to the affected area to match adjacent structure.
d. Install equipment that was removed for internal access. Refer to PART 2 - RESTORATION
as an accepted procedure.
2. Put the airplane back to a serviceable condition.
PART 1: ACCESS
1. Open the forward lower lobe cargo door. Refer to 767 AMM 52-33-00 or 767-400 AMM 52-33-00
as accepted procedures.
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2. Remove and keep cargo compartment floor panels as necessary for internal access to the affected
Stringer 37 (S-37L and S-37R) area just forward of STA 434. Refer to 767 AMM 53-01-05 or
767-400 AMM 53-01-05 as accepted procedures.
3. Remove and keep cargo compartment insulation as necessary for internal access to the affected
Stringer 37 (S-37L and S-37R) area just forward of STA 434. Refer to 767 AMM 25-52-03 or
767-400 AMM 25-52-03 as accepted procedures.
PART 2: RESTORATION
1. Install cargo compartment insulation that was removed for access. Refer to 767 AMM 25-52-03
or 767-400 AMM 25-52-03 as accepted procedures.
2. Install cargo compartment floor panels that were removed for access. Refer to 767 AMM 53-01-05
or 767-400 AMM 53-01-05 as accepted procedures.
3. Close the forward lower lobe cargo door. Refer to 767 AMM 52-33-00 or 767-400 AMM 52-33-00
as accepted procedures.
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BOEING SERVICE BULLETIN 767-53A0251
ALERT  ALERT
This Figure applies only to: Group 1.
STA
434
STA  STA
246
STA
434
-5-174
- S-26L
FWD
*S-37L
S-37R
2221659
FIGURE 1: SKIN INSPECTION FOR MISSING FASTENERS
(SHEET 1 OF 3)
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### Page 33

FIGURE 1: SKIN INSPECTION FOR MISSING FASTENERS
(SHEET 2 OF 3)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
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767-53A0251Revision 1 March 07, 2017
33 of 53
BOEING SERVICE BULLETIN 767-53A0251
ALERTALERT

### 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 one side of the airplane.
More DataQtyIdentificationNameTaskStep
Do an external General Visual Inspec-
tion of Stringer 37 (S-37L and S-37R)
lap splice for missing fasteners.
--SkinInspect1
FIGURE 1: SKIN INSPECTION FOR MISSING FASTENERS
(SHEET 3 OF 3)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: August 07, 2013
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BOEING SERVICE BULLETIN 767-53A0251
ALERTALERT

### Page 35 (OCR)

BOEING SERVICE BULLETIN 767-53A0251
ALERT  ALERT
This Figure applies only to: Group 1.
STA
434
STA  STA
132  246
STA
434
→ S-17L
~ S-26L
PWD
728-S.
S-37R
B
FIGURE 2: SKIN DETAILED AND OPEN-HOLE INSPECTION
(SHEET 1 OF 4)
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Work - See page 1 for details.  35 of 53

### Page 36

FIGURE 2: SKIN DETAILED AND OPEN-HOLE INSPECTION
(SHEET 2 OF 4)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: August 07, 2013
767-53A0251Revision 1 March 07, 2017
36 of 53
BOEING SERVICE BULLETIN 767-53A0251
ALERTALERT

### Page 37

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 one side of the airplane.
More DataQtyIdentificationNameTaskStep
Do internal and external detailed in-
spections for any crack, any corrosion,
and any other discrepancy, such as
broken sealant, in the area shown. (a)
--SkinInspect1
Adjacent to the locations where fasten-
ers were found to be missing.
9-FastenersRemove2
FIGURE 2: SKIN DETAILED AND OPEN-HOLE INSPECTION
(SHEET 3 OF 4)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: August 07, 2013
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BOEING SERVICE BULLETIN 767-53A0251
ALERTALERT

### Page 38

More DataQtyIdentificationNameTaskStep
Do open-hole HFEC inspections for
cracks at the open fastener holes in
accordance with 767 NDT Manual
Part 6, 51-00-04, or 767 NDT Manual
Part 6, 51-00-11 or 767 NDT Manual
Part 6, 51-00-16.
9-SkinInspect3
(a) The area to be inspected extends one inch above the top row of fasteners in the lap splice to one inch
below the bottom row of fasteners in the lap splice. The forward and aft ends of the area to be inspected
are located mid-way between the columns of fasteners shown.
FIGURE 2: SKIN DETAILED AND OPEN-HOLE INSPECTION
(SHEET 4 OF 4)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: August 07, 2013
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BOEING SERVICE BULLETIN 767-53A0251
ALERTALERT

### Page 39 (OCR)

BOEING SERVICE BULLETIN 767-53A0251
ALERT  ALERT
This Figure applies only to: Group 1.
STA
434
STA  STA
132  246
STA
434
→ S-17L
~ S-26L
PWD
S-37L
S-37R
B
FIGURE 3: FASTENER INSTALLATION
(SHEET 1 OF 4)
Original Issue: August 07, 2013
Revision 1 March 07, 2017  Export Controlled ECCN: 9E991 - BOEING  767-53A0251
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.  39 of 53

### Page 40 (OCR)

BOEING SERVICE BULLETIN 767-53A0251
ALERT  ALERT
STA
434
5 LOCATIONS (3
S-37L
3.20
FWD  3.14
FIGURE 3: FASTENER INSTALLATION
(SHEET 2 OF 4)
Original Issue: August 07, 2013
Revision 1 March 07, 2017  Export Controlled ECCN: 9E991 - BOEING  767-53A0251
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.  40 of 53

### Page 41 (OCR)

BOEING SERVICE BULLETIN 767-53A0251
ALERT  ALERT
STA
434
(3) 5 LOCATIONS
S-37R-
3.20
3.14
FWD
2221791
FIGURE 3: FASTENER INSTALLATION
(SHEET 3 OF 4)
Original Issue: August 07, 2013
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Work - See page 1 for details.  41 of 53

### Page 42

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 one side of the airplane.
NOTE: The driven head of the new rivets should be 1.5 times the rivet shank diameter.1.
2. Remove and reapply any BMS 5-95 sealant found broken in the affected area.
More DataQtyIdentificationNameTaskStep
0.190 - 0.196--HOLEDrill1
(a)--HOLEClean/Deburr
BACR15FV7KE7 optional (b)4BACR15FV6KE6RivetInstall (New)2
BACR15FV7KE8 optional (b)5BACR15FV6KE7RivetInstall (New)3
Align the rows of new fasteners
with the existing rows of fasten-
ers in the lap splice.
6BACR15FV6KE6RivetInstall (New)4
(a) Clean hole, refer to SOPM 20-30-03 as an accepted procedure. Deburr hole, refer to 767-200 SRM 51-
40-05 or 767-300 SRM 51-41-05 or 767-300F SRM 51-41-05 or 767-400 SRM 51-40-05 as an accepted
procedure.
(b) Optional, if oversize is necessary due to hole quality requirements.
FIGURE 3: FASTENER INSTALLATION
(SHEET 4 OF 4)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: August 07, 2013
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BOEING SERVICE BULLETIN 767-53A0251
ALERTALERT

### Page 43 (OCR)

BOEING SERVICE BULLETIN 767-53A0251
ALERT  ALERT
This Figure applies only to: Group 2.
STA
434
STA  STA
132  246
STA
434
-5-171
• S-26L
'S-37L
S-37R
8689992
FIGURE 4: SKIN INSPECTION FOR MISSING FASTENERS
(SHEET 1 OF 3)
Original Issue: August 07, 2013
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Work - See page 1 for details.  43 of 53

### Page 44

FIGURE 4: SKIN INSPECTION FOR MISSING FASTENERS
(SHEET 2 OF 3)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: August 07, 2013
767-53A0251Revision 1 March 07, 2017
44 of 53
BOEING SERVICE BULLETIN 767-53A0251
ALERTALERT

### Page 45

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 one side of the airplane.
More DataQtyIdentificationNameTaskStep
Do an external General Visual Inspec-
tion of Stringer 37 (S-37L and S-37R)
lap splice for up to 10 missing fasten-
ers.
--SkinInspect1
FIGURE 4: SKIN INSPECTION FOR MISSING FASTENERS
(SHEET 3 OF 3)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: August 07, 2013
767-53A0251Revision 1 March 07, 2017
45 of 53
BOEING SERVICE BULLETIN 767-53A0251
ALERTALERT

### Page 46 (OCR)

BOEING SERVICE BULLETIN 767-53A0251
ALERT  ALERT
This Figure applies only to: Group 2.
STA
434
STA  STA
132  246
STA
434
- 5-171
— S-26L
S-37L
S-37R
2555900
FIGURE 5: SKIN DETAILED AND OPEN-HOLE INSPECTION
(SHEET 1 OF 4)
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Revision 1 March 07, 2017  Export Controlled ECCN: 9E991 - BOEING  767-53A0251
PROPRIETARY - Copyright @ Unpublished
Work - See page 1 for details.  46 of 53

### Page 47

FIGURE 5: SKIN DETAILED AND OPEN-HOLE INSPECTION
(SHEET 2 OF 4)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: August 07, 2013
767-53A0251Revision 1 March 07, 2017
47 of 53
BOEING SERVICE BULLETIN 767-53A0251
ALERTALERT

### Page 48

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 one side of the airplane.
More DataQtyIdentificationNameTaskStep
Do internal and external detailed in-
spections for any crack, any corrosion,
and any other discrepancy, such as
broken sealant, in the area shown. (a)
--SkinInspect1
FIGURE 5: SKIN DETAILED AND OPEN-HOLE INSPECTION
(SHEET 3 OF 4)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: August 07, 2013
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BOEING SERVICE BULLETIN 767-53A0251
ALERTALERT

### Page 49

More DataQtyIdentificationNameTaskStep
For every missing fastener, remove
the fasteners adjacent to the missing
location (above, below, left and right).
11-FastenersRemove2
Do open-hole HFEC inspections for
cracks at the open fastener holes in
accordance with 767 NDT Manual
Part 6, 51-00-04, or 767 NDT Manual
Part 6, 51-00-11 or 767 NDT Manual
Part 6, 51-00-16.
11-SkinInspect3
(a) The area to be inspected extends one inch above the top row of fasteners in the lap splice to one inch
below the bottom row of fasteners in the lap splice. The forward and aft ends of the area to be inspected
are located mid-way between the columns of fasteners shown.
FIGURE 5: SKIN DETAILED AND OPEN-HOLE INSPECTION
(SHEET 4 OF 4)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: August 07, 2013
767-53A0251Revision 1 March 07, 2017
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BOEING SERVICE BULLETIN 767-53A0251
ALERTALERT

### Page 50 (OCR)

BOEING SERVICE BULLETIN 767-53A0251
ALERT  ALERT
This Figure applies only to: Group 2.
STA
434
STA  STA
132  246
STA
434
- 5-171
— S-26L
S-37L
S-37R
2555903
FIGURE 6: FASTENER INSTALLATION
(SHEET 1 OF 4)
Original Issue: August 07, 2013
Revision 1 March 07, 2017  Export Controlled ECCN: 9E991 - BOEING  767-53A0251
PROPRIETARY - Copyright @ Unpublished
Work - See page 1 for details.  50 of 53

### Page 51 (OCR)

BOEING SERVICE BULLETIN 767-53A0251
ALERT  ALERT
STA
434
(3) 7 LOCATIONS
S-37L
3.20
3.14
FWD
2555904
FIGURE 6: FASTENER INSTALLATION
(SHEET 2 OF 4)
Original Issue: August 07, 2013
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Work - See page 1 for details.  51 of 53

### Page 52 (OCR)

BOEING SERVICE BULLETIN 767-53A0251
ALERT  ALERT
STA
434
3) 7 LOCATIONS
S-37R
3.20
3.14
FWD
B
2555920
FIGURE 6: FASTENER INSTALLATION
(SHEET 3 OF 4)
Original Issue: August 07, 2013
Revision 1 March 07, 2017  Export Controlled ECCN: 9E991 - BOEING  767-53A0251
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.  52 of 53

### Page 53

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 one side of the airplane.
NOTE: The driven head of the new rivets should be 1.5 times the rivet shank diameter.1.
2. Remove and reapply any BMS 5-95 sealant found broken in the affected area.
More DataQtyIdentificationNameTaskStep
(0.190 - 0.196). Drill up to 5
missing fasteners on each row.
--HOLEDrill1
(a)--HOLEClean/Deburr
BACR15FV7KE7 optional. (b)4BACR15FV6KE6RivetInstall (New)2
BACR15FV7KE8 optional. (b)
(c)
7BACR15FV6KE7RivetInstall (New)3
Align the rows of new fasteners
with the existing rows of fasten-
ers in the lap splice. (b) (c)
10BACR15FV6KE6RivetInstall (New)4
(a) Clean hole, refer to SOPM 20-30-03 as an accepted procedure. Deburr hole, refer to 767-200 SRM 51-
40-05 or 767-300 SRM 51-41-05 or 767-300F SRM 51-41-05 or 767-400 SRM 51-40-05 as an accepted
procedure.
(b) Optional, if oversize is necessary due to hole quality requirements.
(c) Install up to 5 missing fasteners on each row.
FIGURE 6: FASTENER INSTALLATION
(SHEET 4 OF 4)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: August 07, 2013
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53 of 53
BOEING SERVICE BULLETIN 767-53A0251
ALERTALERT

---
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