# Boeing Alert Service Bulletin 767-53A0251: U.S. DOT/FAA - Service Bulletin 767-53A0251 Revision 00

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- Document: [Boeing Alert Service Bulletin 767-53A0251](https://openairdocs.org/service-documents/boeing/767-53a0251.md)
- Title as filed: U.S. DOT/FAA - Service Bulletin 767-53A0251 Revision 00
- Pages: 31
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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
ATA System: 5300
SUBJECT: FUSELAGE - Section 41 - Skins - Stringer 37 Lap Splice Inspection Between Body
Stations 428 and 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Unpublished Work.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
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6.0

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Table of Contents
Summary ...................................................... 5
1. PLANNING INFORMATION ........................................ 9
A. Effectivity ................................................ 9
1. Airplanes ............................................. 9
2. Spares Affected ........................................ 1 0
B. Concurrent Requirements ...................................... 1 0
C. Reason ................................................ 1 0
D. Description .............................................. 1 0
E. Compliance .............................................. 1 1
F. Approval ............................................... 1 2
G. Manpower .............................................. 1 3
H. Weight and Balance Changes .................................... 1 3
I. Electrical Load Data ......................................... 1 3
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 5
3. Parts Modified and Reidentified ................................ 1 5
4. Parts Removed and Not Replaced .............................. 1 5
D. Parts Necessary to Change Spares ................................. 1 6
E. Special Tooling - Price and Availability ............................... 1 6
F. Special Tooling Necessary to do this Service Bulletin ....................... 1 6
3. ACCOMPLISHMENT INSTRUCTIONS .................................. 1 7
A. GENERAL INFORMATION ..................................... 1 7
B. WORK INSTRUCTIONS ....................................... 1 8
FIGURE 1: SKIN INSPECTION FOR MISSING FASTENERS ...................... 2 1
FIGURE 2: SKIN DETAILED AND OPEN-HOLE INSPECTION ..................... 2 4
FIGURE 3: FASTENER INSTALLATION .................................. 2 8
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Commercial 
Airplanes
767
Service Bulletin
ALERT
SummaryNumber: 767-53A0251Original Issue: August 07, 2013
ATA System: 5300
SUBJECT: FUSELAGE - Section 41 - Skins - Stringer 37 Lap Splice Inspection Between Body
Stations 428 and 431
THIS BULLETIN 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 SERVICE BULLETIN TO
THE NEW OPERATOR. IF APPLICABLE SPARES HAVE BEEN SOLD, SEND THIS SERVICE BULLETIN TO
THE NEW OWNER.
CONCURRENT REQUIREMENTS
None.
BACKGROUND
This service bulletin gives instructions to do inspections of the stringer 37 (S-37) left and right 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 six fasteners may not have been installed in the left and right S-37 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 is 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
Paragraph 1.K., Publications AffectedNoAirplane Flight Operations Affected (Flight Crew
Operations Manual and/or FAA Approved Air-
plane Flight Manual)
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ReferenceAffectedPlanning Data
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 the left and right S-37 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
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.
This service bulletin affects SSI 53-10-I07C and 53-10-I07D of MPD 622T009 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.
MANPOWER
Elapsed HoursTotal Task HoursAirplanes
0.100.10Inspection for missing fasteners
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Elapsed HoursTotal Task HoursAirplanes
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.
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BOEING SERVICE BULLETIN 767-53A0251
ALERT  ALERT
STA
434
STA
246
STA
434
S-17L
- S-26L
*S-37L
S-37R
DO EXTERNAL GENERAL VISUAL INSPECTIONS
OF THE LEFT AND RIGHT STRINGER 37 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.
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Commercial 
Airplanes
767
Service Bulletin
ALERT
Number: 767-53A0251
Original Issue: August 07, 2013
ATA System: 5300
SUBJECT: FUSELAGE - Section 41 - Skins - Stringer 37 Lap Splice Inspection Between Body
Stations 428 and 431
THIS BULLETIN 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 SERVICE BULLETIN TO
THE NEW OPERATOR. IF APPLICABLE SPARES HAVE BEEN SOLD, SEND THIS SERVICE BULLETIN TO
THE NEW OWNER.
1.    PLANNING INFORMATION
A. Effectivity
1. Airplanes
Refer to Service Bulletin Index D624T001 Part 3 for Airplane Variable Number, Line Number, and
Serial Number data.
This service bulletin is for the airplane(s) shown below.
DESCRIPTIONCONFIGURATIONGROUP
767-200, 767-300, 767-300F and 767-400ER airplanes line number
929 through 1028.
-1
Airplane Models:
767-200, 767-300, 767-300F, 767-400ER
GroupVariable Number
1VQ111
1VR087 - VR089
1VR106 - VR109
1VR266 - VR283
1VS712 - VS720
1VS732 - VS736
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GroupVariable Number
1VS883
1VS901 - VS912
1VS916
1VS921 - VS928
1VS931 - VS933
1VS941
1VS951 - VS954
1VS961 - VS969
1VS971 - VS976
1VS981 - VS982
1VT511 - VT513
1VT521 - VT523
1VT531 - VT533
1VT541 - VT543
1VT551
2. Spares Affected
None.
B. Concurrent Requirements
None.
C. Reason
This service bulletin gives instructions to do inspections of the stringer 37 (S-37) left and right 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 six fasteners may not have been installed in the left and right S-37 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 is related to this service bulletin.
D. Description
Do external general visual inspections of the left and right S-37 lap splices for missing fasteners. If no
fasteners are found to be missing, no more work is required.
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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.
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
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.
This service bulletin affects SSI 53-10-I07C and 53-10-I07D of MPD 622T009 Section 9.
Do the required actions in accordance with Paragraph 3. Accomplishment Instructions.
Table 1: S-37 Lap Splice Inspection for Missing Fasteners Between STA 428 and 431
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever
Occurs First)
ActionCondition
-Within 2 years
after the original
issue date of
this service bul-
letin.
Within 3,000
flight-cycles af-
ter the original
issue date of
this service bul-
letin.
Do an external General
Visual Inspection of the
Stringer 37 (S-37) lap
splice, just forward of the
circumferential splice at
Body Station (STA) 434,
for missing fasteners.
All affected airplanes.
--No more work is neces-
sary.
CONDITION 1: NO MISS-
ING FASTENERS
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Table 1: S-37 Lap Splice Inspection for Missing Fasteners Between STA 428 and 431
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever
Occurs First)
ActionCondition
-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.
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.
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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 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.
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
Table 2 - 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 2)
0.500.501Fastener installation
(Figure 3)
2.755.502Close Access
7.2512.75TOTAL 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 Related Problem (SRP) 767-53-0424
b. Service Bulletin Index D624T001
c. 767 Aircraft Maintenance Manual (AMM) 25-52-03, 52-33-00, 53-01-05
d. 767 Maintenance Planning Data (MPD) Section 9
e. 767 Non-Destructive Testing (NDT) Manual Part 6, 51-00-04, Part 6, 51-00-11, Part 6, 51-00-16
f. 767-200 Structural Repair Manual (SRM) 53-00-01
g. 767-300 Structural Repair Manual (SRM) 53-00-01
h. 767-300F Structural Repair Manual (SRM) 53-00-01
i. 767-400 Aircraft Maintenance Manual (AMM) 25-52-03, 52-33-00, 53-01-05
j. 767-400 Structural Repair Manual (SRM) 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.
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)
Rivet20BACR15FV6KE6
BACR15FV6KE8 optional.
(a)
Rivet10BACR15FV6KE7
(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.
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 limits to tighten nuts and bolts are in SRM Chapter 51
4. Use the approved fastener and process 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.
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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### Page 18

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. 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 identified as Required for Compliance (RC).
If this service bulletin is mandated by an Airworthiness Directive (AD), then the steps
identified as RC must be done to comply with the AD. Alternative procedures for
steps not identified with RC can be used if the RC steps can still be done as specified,
and the airplane can be put back in a serviceable condition. An Alternative Method
of Compliance (AMOC) is not necessary for deviations to steps that are not identified
as RC.
B. WORK INSTRUCTIONS
1. RC - Do an external General Visual Inspection of the Stringer 37 (S-37) lap splice, just forward of
the circumferential splice at Body Station (STA) 434, for missing fasteners in accordance with
FIGURE 1.
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### Page 19

CONDITION 1: NO MISSING FASTENERS
a. No more work is required.
CONDITION 2: ANY MISSING FASTENERS
a. Get internal access. Refer to PART 1 - ACCESS as an accepted procedure.
b. RC - Remove fasteners adjacent to the missing fastener locations and do inspections in
accordance with FIGURE 2.
CONDITION 3: NO CRACK, CORROSION OR OTHER DISCREPANCY FOUND
(1) RC - Install fasteners in accordance with FIGURE 3.
CONDITION 4: ANY CRACK, CORROSION OR OTHER DISCREPANCY FOUND
(1) RC - 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.
CONDITION 5: ALL CRACKING, CORROSION OR OTHER DISCREPANCY FOUND
IS WITHIN SRM LIMITS
(a) RC - 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.
CONDITION 6: ANY CRACK, CORROSION OR OTHER DISCREPANCY FOUND THAT
IS BEYOND SRM LIMITS
(a) RC - 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.
2. Remove and keep cargo compartment floor panels as necessary for internal access to the affected
S-37 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
S-37 area just forward of STA 434. Refer to 767 AMM 25-52-03 or 767-400 AMM 25-52-03 as
accepted procedures.
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
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### Page 20

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.
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
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### Page 21 (OCR)

BOEING SERVICE BULLETIN 767-53A0251
ALERT  ALERT
STA
107  434
STA
246
STA
434
> S-17L
• S-26L
S-37L
'S-37R
2221659
FIGURE 1: SKIN INSPECTION FOR MISSING FASTENERS
(SHEET 1 OF 3)
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### Page 22

FIGURE 1: SKIN INSPECTION FOR MISSING FASTENERS
(SHEET 2 OF 3)
Export Controlled ECCN: 9E991 - BOEING
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Work - See page 1 for details.
Original Issue: August 07, 2013
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### Page 23

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 Gen-
eral Visual Inspec-
tion of the S-37 lap
splice for missing
fasteners.
--SkinInspect1
FIGURE 1: SKIN INSPECTION FOR MISSING FASTENERS
(SHEET 3 OF 3)
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### Page 24 (OCR)

BOEING SERVICE BULLETIN 767-53A0251
ALERT  ALERT
STA
434
STA
246
STA
434
-S-17L
- S-26L
S-37L
*S-37R
2221775
FIGURE 2: SKIN DETAILED AND OPEN-HOLE INSPECTION
(SHEET 1 OF 4)
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### Page 25

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
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### Page 26

FIGURE 2: SKIN DETAILED AND OPEN-HOLE INSPECTION
(SHEET 3 OF 4)
Export Controlled ECCN: 9E991 - BOEING
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### Page 27

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 exter-
nal detailed inspec-
tions for any crack,
any corrosion, and
any other discrepan-
cy, such as broken
sealant, in the area
shown. (a)
--SkinInspect1
Adjacent to the loca-
tions where fasten-
ers were found to be
missing.
9-FastenersRemove2
Do open-hole HFEC
inspections for
cracks at the open
fastener holes in ac-
cordance 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
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### Page 28 (OCR)

BOEING SERVICE BULLETIN 767-53A0251
ALERT  ALERT
STA
434
STA
246
STA
434
-S-17L
- S-26L
S-37L
*S-37R
2221783
FIGURE 3: FASTENER INSTALLATION
(SHEET 1 OF 4)
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### Page 29 (OCR)

BOEING SERVICE BULLETIN 767-53A0251
ALERT  ALERT
STA
434
1 2 LOCATIONS
5 LOCATIONS 2
- S-37L
3.20
3.14
. 3 EQUAL
SPACES
FWD
2221784
FIGURE 3: FASTENER INSTALLATION
(SHEET 2 OF 4)
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PROPRIETARY - Copyright © Unpublished
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### Page 30 (OCR)

BOEING SERVICE BULLETIN 767-53A0251
ALERT  ALERT
STA
434
→ 2 LOCATIONS (1
2) 5 LOCATIONS
S-37R
3.20
3.14
3 EQUAL
SPACES
FWD
2221791
FIGURE 3: FASTENER INSTALLATION
(SHEET 3 OF 4)
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PROPRIETARY - Copyright © Unpublished
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### Page 31

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
BACR15FV7KE7
optional (a)
4BACR15FV6KE6RivetInstall (New)1
BACR15FV7KE8
optional (a)
5BACR15FV6KE7RivetInstall (New)2
Align the rows of
new fasteners with
the existing rows of
fasteners in the lap
splice.
6BACR15FV6KE6RivetInstall (New)3
(a) Optional, if oversize is necessary due to hole quality requirements.
FIGURE 3: FASTENER INSTALLATION
(SHEET 4 OF 4)
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BOEING SERVICE BULLETIN 767-53A0251
ALERTALERT

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