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

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persons from specific countries. The controller of this data has the individual responsibility to abide by all export

laws.

ECCN: 9E991

BOEING PROPRIETARY, CONFIDENTIAL AND/OR TRADE SECRET

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BLANK PAGE
Table of Contents

Summary ...................................................... 5

1. PLANNING INFORMATION ........................................ 9

A. Effectivity ................................................ 9

1. Airplanes ............................................. 9

2. Spares Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 10

B. Concurrent Requirements . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 10

C. Reason . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 10

D. Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 10

E. Compliance . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11

F. Approval . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 12

G. Manpower . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13

H. Weight and Balance Changes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13

I. Electrical Load Data . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13

J. References . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14

1. Existing Data: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14

2. Data Supplied with this Service Bulletin: . . . . . . . . . . . . . . . . . . . . . . . . . . . 14

3. Installation Drawings Used in the Preparation of this Service Bulletin: . . . . . . . . . . . 14

K. Publications Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14

L. Interchangeability and Intermixability of Parts . . . . . . . . . . . . . . . . . . . . . . . . . . . 14

M. Software Accomplishment Summary . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14

2. MATERIAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15

A. Material - Price and Availability . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15

B. Industry Support Information . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15

C. Parts Necessary for Each Airplane . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15

1. Kits/Parts . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15

2. Parts and Materials Supplied by the Operator . . . . . . . . . . . . . . . . . . . . . . . . 15

3. Parts Modified and Reidentified . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15

4. Parts Removed and Not Replaced . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15

D. Parts Necessary to Change Spares . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 16

E. Special Tooling - Price and Availability . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 16

F. Special Tooling Necessary to do this Service Bulletin . . . . . . . . . . . . . . . . . . . . . . . 16

3. ACCOMPLISHMENT INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17

A. GENERAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17

B. WORK INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 18

FIGURE 1: SKIN INSPECTION FOR MISSING FASTENERS . . . . . . . . . . . . . . . . . . . . . . 21

FIGURE 2: SKIN DETAILED AND OPEN-HOLE INSPECTION . . . . . . . . . . . . . . . . . . . . . 24

FIGURE 3: FASTENER INSTALLATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 28

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BLANK PAGE
Commercial 

Airplanes 767

Service Bulletin

ALERT

Summary 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.

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.

Planning Data Affected Reference

Spares Affected No Paragraph 1.A.2., Spares Affected

Paragraph 1.E., Compliance and Paragraph

1.F., Approval

AD Related Yes

Weight and Balance Change No Paragraph 1.H., Weight and Balance Changes

Electrical Load Changed No Paragraph 1.I., Electrical Load Data

Publications Affected No Paragraph 1.K., Publications Affected

Airplane Flight Operations Affected (Flight Crew No Paragraph 1.K., Publications Affected

Operations Manual and/or FAA Approved Airplane Flight Manual)

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Planning Data Affected Reference

Kits/Parts Required No Paragraph 2.C.1., Kits/Parts

Paragraph 2.C.2., Parts and Materials Supplied

by the Operator

Operator Supplied Parts/Material Yes

Paragraph 2.F., Special Tooling Necessary to

do this Service Bulletin

Special Tooling Required No

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

Airplanes Total Task Hours Elapsed Hours

Inspection for missing fasteners 0.10 0.10

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ALERT ALERT
Airplanes Total Task Hours Elapsed Hours

Additional inspections and fastener instal- 12.75 7.25

lation if fasteners are found to be missing

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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ALERT ALERT
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.

GROUP CONFIGURATION DESCRIPTION

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

Variable Number Group

VQ111 1

VR087 - VR089 1

VR106 - VR109 1

VR266 - VR283 1

VS712 - VS720 1

VS732 - VS736 1

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Variable Number Group

VS883 1

VS901 - VS912 1

VS916 1

VS921 - VS928 1

VS931 - VS933 1

VS941 1

VS951 - VS954 1

VS961 - VS969 1

VS971 - VS976 1

VS981 - VS982 1

VT511 - VT513 1

VT521 - VT523 1

VT531 - VT533 1

VT541 - VT543 1

VT551 1

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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BOEING SERVICE BULLETIN 767-53A0251

ALERT ALERT
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

Model Zone

767-200, 767-300, 767-300F, 123, 124

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)

Condition Action

Within 2 years -

after the original

issue date of

this service bulletin.

Within 3,000

flight-cycles after the original

issue date of

this service bulletin.

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 MISSING 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)

Condition Action

Remove fasteners adja- Before further flight. -

cent to the missing fastener locations. Do detailed

inspections for any crack,

any corrosion, and any

other discrepancy, such

as broken sealant. Do

open-hole HFEC inspections for cracks at the

open fastener holes.

CONDITION 2: ANY

MISSING FASTENERS

CONDITION 3: NO Install fasteners. Before further flight. -

CRACK, CORROSION OR

OTHER DISCREPANCY

FOUND

Determine if the crack, Before further flight. -

corrosion or other discrepancy is within the repair

limits in the SRM.

CONDITION 4: ANY

CRACK, CORROSION OR

OTHER DISCREPANCY

FOUND

Repair in accordance with Before further flight. -

the SRM.

CONDITION 5: ALL

CRACKING, CORROSION

OR OTHER DISCREPANCY FOUND IS WITHIN

SRM LIMITS

Contact Boeing for repair Before further flight. -

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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ALERT ALERT
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

Task Number of Persons Task Hours Elapsed Hours

Inspect for missing 1 0.10 0.10

fasteners (Figure 1)

TOTAL FOR EACH AIRPLANE 0.10 0.10

Table 2 - Additional Inspections and Fastener Installation if Fasteners are Found to be

Missing

Task Number of Persons Task Hours Elapsed Hours

Open internal access 2 5.50 2.75

Detailed and eddy 1 1.25 1.25

current inspections

(Figure 2)

Fastener installation 1 0.50 0.50

(Figure 3)

Close Access 2 5.50 2.75

TOTAL FOR EACH AIRPLANE 12.75 7.25

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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ALERT ALERT
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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ALERT ALERT
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.

Part Number / QTY Name Notes

Specification

BACR15FV6KE7 optional.

(a)

BACR15FV6KE6 20 Rivet

BACR15FV6KE8 optional.

(a)

BACR15FV6KE7 10 Rivet

8 Sealant (b)

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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ALERT ALERT
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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ALERT ALERT
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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ALERT ALERT
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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BOEING SERVICE BULLETIN 767-53A0251

ALERT ALERT
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.

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ALERT ALERT
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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ALERT ALERT
FIGURE 1: SKIN INSPECTION FOR MISSING FASTENERS

(SHEET 1 OF 3)

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ALERT ALERT
FIGURE 1: SKIN INSPECTION FOR MISSING FASTENERS

(SHEET 2 OF 3)

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ALERT ALERT
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.

Step Task Name Identification Qty More Data

Do an external General Visual Inspection of the S-37 lap

splice for missing

fasteners.

1 Inspect Skin - -

FIGURE 1: SKIN INSPECTION FOR MISSING FASTENERS

(SHEET 3 OF 3)

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ALERT ALERT
FIGURE 2: SKIN DETAILED AND OPEN-HOLE INSPECTION

(SHEET 1 OF 4)

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ALERT ALERT
FIGURE 2: SKIN DETAILED AND OPEN-HOLE INSPECTION

(SHEET 2 OF 4)

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ALERT ALERT
FIGURE 2: SKIN DETAILED AND OPEN-HOLE INSPECTION

(SHEET 3 OF 4)

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ALERT ALERT
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.

Step Task Name Identification Qty More Data

Do internal and external detailed inspections for any crack,

any corrosion, and

any other discrepancy, such as broken

sealant, in the area

shown. (a)

1 Inspect Skin - -

Adjacent to the locations where fasteners were found to be

missing.

2 Remove Fasteners - 9

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.

3 Inspect Skin - 9

(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)

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ALERT ALERT
FIGURE 3: FASTENER INSTALLATION

(SHEET 1 OF 4)

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ALERT ALERT
FIGURE 3: FASTENER INSTALLATION

(SHEET 2 OF 4)

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ALERT ALERT
FIGURE 3: FASTENER INSTALLATION

(SHEET 3 OF 4)

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BOEING SERVICE BULLETIN 767-53A0251

ALERT ALERT
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: 1. The driven head of the new rivets should be 1.5 times the rivet shank diameter.

2. Remove and reapply any BMS 5-95 sealant found broken in the affected area.

Step Task Name Identification Qty More Data

BACR15FV7KE7

optional (a)

1 Install (New) Rivet BACR15FV6KE6 4

BACR15FV7KE8

optional (a)

2 Install (New) Rivet BACR15FV6KE7 5

Align the rows of

new fasteners with

the existing rows of

fasteners in the lap

splice.

3 Install (New) Rivet BACR15FV6KE6 6

(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

ALERT ALERT