Commercial 

Airplanes 747

Service Bulletin

ALERT

Number: 747-53A2854

Original Issue: September 17, 2012

ATA System: 5331

SUBJECT: FUSELAGE - Skin - Skin Panel Chem-Milled Pocket Inspection and Repair at Locations

Adjacent to Lap Splices

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ECCN: 9E991

BOEING PROPRIETARY, CONFIDENTIAL AND/OR TRADE SECRET

Copyright © 2012 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Unpublished Work.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

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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 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11

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

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

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

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

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

J. References . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13

1. Existing Data: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13

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 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15

E. Special Tooling - Price and Availability . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15

F. Special Tooling Necessary to do this Service Bulletin . . . . . . . . . . . . . . . . . . . . . . . 15

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

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

B. WORK INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17

FIGURE 1: SKIN INSPECTION IN SECTION 42, 44 AND 46 [Group 1] . . . . . . . . . . . . . . . . . 19

FIGURE 2: SKIN INSPECTION IN SECTION 42 [Group 2] . . . . . . . . . . . . . . . . . . . . . . . . 30

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BLANK PAGE
Commercial 

Airplanes 747

Service Bulletin

ALERT

Summary Number: 747-53A2854

Original Issue: September 17, 2012

ATA System: 5331

SUBJECT: FUSELAGE - Skin - Skin Panel Chem-Milled Pocket Inspection and Repair at Locations

Adjacent to Lap Splices

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 fuselage skin for cracks just above certain lap

splice locations. Skin cracks that are not found and repaired can become large and cause sudden loss of cabin

pressure and loss of structural integrity..

Two operators of Boeing 757 airplanes have reported cracking, on two airplanes, that initiated at multiple locations

on the inboard surface of the skin, along the edge of the chem-milled step just above the skin lap splice. No

cracking of this kind has been reported on 747 airplanes, but analysis by Boeing indicates that the 747 fuselage

skin in the areas shown in this service bulletin may be susceptible to similar cracking.

The related Boeing 757 service bulletin is 757-53-0097, "FUSELAGE - Skin - Crown Skin Panel - Station 297

to Station 439, Chem-Milled Step Above Stringer 4 Left and Stringer 4 Right Lap Joint - Inspection".

Accomplishment of the inspections in this service bulletin and installation of a repair will help prevent in-flight

depressurization of the airplane and ensure the structural integrity of the fuselage skin at certain chem-milled

skin locations.

The skin at the edge of chem-milled steps above certain skin lap splices has been determined to be structure

that is susceptible to Widespread Fatigue Damage (WFD). For more information about WFD, refer to

747-SL-53-088A.

Boeing Service Related Problem (SRP) 747-SRP-53-0396 is related to this service bulletin.

This table is provided to operators for planning purposes only. Refer to the applicable sections for more

information.

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Planning Data Affected Reference

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

AD Related No Paragraph 1.E., Compliance

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)

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

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

by the Operator

Operator Supplied Material No

Paragraph 2.F., Special Tooling Necessary to

do this Service Bulletin

Special Tooling Required No

ACTION

Get external access to the fuselage skin just above certain lap splice locations. Do external sliding probe eddy

current inspections at the affected locations for cracks. If no crack indications are found, put the airplane back

to a serviceable condition, and do the inspection again at the times given in this service bulletin. If crack indications

are found, contact Boeing for repair data and do the repair. After repair, put the airplane back to a serviceable

condition, and do the inspection again at the times given in this service bulletin.

EFFECTIVITY

747-100B SUD, 747-300 and 747SP Airplanes. Refer to Paragraph 1.A.1., Airplanes, for the list of affected

airplanes.

COMPLIANCE

Refer to Paragraph 1.E., Compliance.

INDUSTRY SUPPORT INFORMATION

Boeing warranty remedies are not available for the inspection and repair procedures given in this service bulletin.

MANPOWER

Airplanes Total Task Hours Elapsed Hours

Group 1 56.50 28.50

Group 2 10.00 5.25

Refer to Paragraph 1.G., Manpower.

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MATERIAL INFORMATION

None.

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BLANK PAGE
Commercial 

Airplanes 747

Service Bulletin

ALERT

Number: 747-53A2854

Original Issue: September 17, 2012

ATA System: 5331

SUBJECT: FUSELAGE - Skin - Skin Panel Chem-Milled Pocket Inspection and Repair at Locations

Adjacent to Lap Splices

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 D6-30300 Part 3 for Airplane Variable Number, Line Number, and

Serial Number data.

This service bulletin is for the airplanes shown below.

GROUP CONFIGURATION DESCRIPTION

1 - All 747SP airplanes.

747-100B SUD airplanes line number 636 and 655, and 747-300

airplanes line number 692 through 695.

2 -

Airplane Models:

747-100B SUD, 747-300, 747SP

Variable Number Group

RG001 - RG009 1

RG091 1

RG095 1

RG101 - RG104 1

RG121 - RG126 1

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Variable Number Group

RG141 - RG142 1

RG161 - RG164 1

RG171 - RG174 1

RG191 - RG193 1

RG211 - RG213 1

RG221 - RG222 1

RH101 - RH102 1

RH111 - RH112 1

RH121 - RH122 1

RS001 - RS002 2

RS265 - RS268 2

2. Spares Affected

None.

B. Concurrent Requirements

None.

C. Reason

This service bulletin gives instructions to do inspections of the fuselage skin for cracks just above

certain lap splice locations. Skin cracks that are not found and repaired can become large and cause

sudden loss of cabin pressure and loss of structural integrity..

Two operators of Boeing 757 airplanes have reported cracking, on two airplanes, that initiated at multiple

locations on the inboard surface of the skin, along the edge of the chem-milled step just above the skin

lap splice. No cracking of this kind has been reported on 747 airplanes, but analysis by Boeing indicates

that the 747 fuselage skin in the areas shown in this service bulletin may be susceptible to similar

cracking.

The related Boeing 757 service bulletin is 757-53-0097, "FUSELAGE - Skin - Crown Skin Panel - Station

297 to Station 439, Chem-Milled Step Above Stringer 4 Left and Stringer 4 Right Lap Joint - Inspection".

Accomplishment of the inspections in this service bulletin and installation of a repair will help prevent

in-flight depressurization of the airplane and ensure the structural integrity of the fuselage skin at certain

chem-milled skin locations.

The skin at the edge of chem-milled steps above certain skin lap splices has been determined to be

structure that is susceptible to Widespread Fatigue Damage (WFD). For more information about WFD,

refer to 747-SL-53-088A.

Boeing Service Related Problem (SRP) 747-SRP-53-0396 is related to this service bulletin.

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D. Description

Get external access to the fuselage skin just above certain lap splice locations. Do external sliding

probe eddy current inspections at the affected locations for cracks. If no crack indications are found,

put the airplane back to a serviceable condition, and do the inspection again at the times given in this

service bulletin. If crack indications are found, contact Boeing for repair data and do the repair. After

repair, put the airplane back to a serviceable condition, and do the inspection again at the times given

in this service bulletin.

The work in this service bulletin is done in the maintenance zone(s) given below.

Group 1:

Affected Maintenance Zones

Model Zone

747SP 122, 147, 148, 241, 242

Group 2:

Affected Maintenance Zones

Model Zone

747-100B SUD, 747-300 225, 226

E. Compliance

Accomplish the required actions, based on the applicable conditions in Table 1, in accordance with

Paragraph 3. Accomplishment Instructions.

Group 1:

Table 1: Skin Inspection

Repeat Interval

(Not to Exceed)

Compliance Time (Whichever

Occurs Later)

Condition Action

Within 500 -

flight-cycles or

one year after

the original issue date of this

service bulletin,

whichever occurs later.

Before 18,500

total flight-cycles

Do an external sliding

probe eddy current inspections for cracking in

accordance with Paragraph 3.B., Work Instructions.

All airplanes

Contact Boeing for repair Before further flight -

data and do the repair.

Any cracking found

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Group 1:

Table 1: Skin Inspection

Repeat Interval

(Not to Exceed)

Compliance Time (Whichever

Occurs Later)

Condition Action

Within 500 flight-cycles after the 500 flight-cycles

previous inspection.

Do external sliding probe

eddy current inspections

for cracking in unrepaired

areas in accordance with

Paragraph 3.B., Work Instructions.

No cracking found

Group 2:

Table 2: Skin Inspection

Repeat Interval

(Not to Exceed)

Compliance Time (Whichever

Occurs Later)

Condition Action

Within 800 -

flight-cycles or

one year after

the original issue date of this

service bulletin,

whichever occurs later.

Before 18,500

total flight-cycles

Do an external sliding

probe eddy current inspections for cracking in

accordance with Paragraph 3.B., Work Instructions.

All airplanes

Contact Boeing for repair Before further flight -

data and do the repair.

Any cracking found

Within 800 flight-cycles after the 800 flight-cycles

previous inspection.

Do external sliding probe

eddy current inspections

for cracking in unrepaired

areas in accordance with

Paragraph 3.B., Work Instructions.

No cracking found

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.

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ALERT ALERT
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 - Skin Inspection in Section 42, 44 and 46

Task Number of Persons Task Hours Elapsed Hours

Prepare 1 0.50 0.50

Inspect (Figure 1) 2 56.00 28.00

TOTAL FOR EACH AIRPLANE 56.50 28.50

Group 2:

Table 2 - Skin Inspection in Section 42

Task Number of Persons Task Hours Elapsed Hours

Prepare 1 0.50 0.50

Inspect (Figure 2) 2 9.50 4.75

TOTAL FOR EACH AIRPLANE 10.00 5.25

NOTE: More time will be required for repairs if cracks are found.

H. Weight and Balance Changes

None.

I. Electrical Load Data

Not applicable.

J. References

1. Existing Data:

a. Boeing Service Bulletin 757-53-0097

b. Boeing Service Letter 747-SL-51-048, 747-SL-53-088A

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c. Boeing Service Related Problem (SRP) 747-SRP-53-0396

d. Service Bulletin Index D6-30300

e. 747 Non-Destructive Testing (NDT) Manual Part 6, 53-30-25

2. Data Supplied with this Service Bulletin:

None.

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

Drawing Number Title

65B04112 Skin Panel Instl - STA 741.1 to STA 1000.0 Stgr 6 to Stgr 12

65B18625 Skin Panel Instl - STA 520 to STA 1000 S-23R to S-34R

65B18631 Skin Panel Instl - STA 1000 to STA 1200.0, Stgr 6 to Stgr 12

The table above lists applicable drawings used to prepare this service bulletin. The drawings are

not necessary to make the specified changes, and are not supplied with this service bulletin. The

drawings may not be applicable to all airplane configurations or operators.

K. Publications Affected

1. Publications:

None.

2. Damage Tolerance Based Structural Inspections:

Boeing has evaluated the repairs and/or changes in this service bulletin for effects on Fatigue

Critical Structure (FCS) and for changes to Damage Tolerance Inspections (DTI) required in the

Maintenance Program. This service bulletin affects FCS but no new DTIs are necessary.

L. Interchangeability and Intermixability of Parts

Accomplishment of this service bulletin does not affect interchangeability or intermixability of parts.

M. Software Accomplishment Summary

Not affected.

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2. MATERIAL INFORMATION

A. Material - Price and Availability

None.

B. Industry Support Information

Boeing warranty remedies are not available for the inspection and repair procedures given in this

service bulletin.

C. Parts Necessary for Each Airplane

1. Kits/Parts

None.

2. Parts and Materials Supplied by the Operator

None.

3. Parts Modified and Reidentified

None.

4. Parts Removed and Not Replaced

None.

D. Parts Necessary to Change Spares

None.

E. Special Tooling - Price and Availability

None.

F. Special Tooling Necessary to do this Service Bulletin

No special tools or equipment are necessary to do the change in this service bulletin. But, maintenance

and overhaul tools in the manuals given in Paragraph 1.J., References, can be necessary. Examine

operator tool supply to make sure all necessary tools are available.

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BLANK PAGE
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

4. 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.

5. Boeing Service Letter 747-SL-51-048, 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.

6. 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.

7. 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.

B. WORK INSTRUCTIONS

Group 1:

SKIN INSPECTION

1. Get external access and do external sliding probe eddy current inspections for cracking in

accordance with FIGURE 1.

NOTE: If any part of the inspection area is covered by an external doubler, contact Boeing for

inspection instructions.

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ALERT ALERT
2. If any cracking is found, contact Boeing for repair data and do the repair.

3. Put the airplane back in a serviceable condition. Do the external sliding probe eddy current

inspections again in all affected unrepaired areas at the time given in Paragraph 1.E., Compliance,

Table 1.

Group 2:

SKIN INSPECTION

1. Get external access and do external sliding probe eddy current inspections for cracking in

accordance with FIGURE 2.

NOTE: If any part of the inspection area is covered by an external doubler, contact Boeing for

inspection instructions.

2. If any cracking is found, contact Boeing for repair data and do the repair.

3. Put the airplane back in a serviceable condition. Do the external sliding probe eddy current

inspections again in all affected unrepaired areas at the time given in Paragraph 1.E., Compliance,

Table 2.

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This Figure applies only to: Group 1.

FIGURE 1: SKIN INSPECTION IN SECTION 42, 44 AND 46

(SHEET 1 OF 11)

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FIGURE 1: SKIN INSPECTION IN SECTION 42, 44 AND 46

(SHEET 2 OF 11)

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BOEING SERVICE BULLETIN 747-53A2854

ALERT ALERT
FIGURE 1: SKIN INSPECTION IN SECTION 42, 44 AND 46

(SHEET 3 OF 11)

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BOEING SERVICE BULLETIN 747-53A2854

ALERT ALERT
FIGURE 1: SKIN INSPECTION IN SECTION 42, 44 AND 46

(SHEET 4 OF 11)

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BOEING SERVICE BULLETIN 747-53A2854

ALERT ALERT
FIGURE 1: SKIN INSPECTION IN SECTION 42, 44 AND 46

(SHEET 5 OF 11)

Export Controlled ECCN: 9E991 - BOEING

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BOEING SERVICE BULLETIN 747-53A2854

ALERT ALERT
FIGURE 1: SKIN INSPECTION IN SECTION 42, 44 AND 46

(SHEET 6 OF 11)

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BOEING SERVICE BULLETIN 747-53A2854

ALERT ALERT
FIGURE 1: SKIN INSPECTION IN SECTION 42, 44 AND 46

(SHEET 7 OF 11)

Export Controlled ECCN: 9E991 - BOEING

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Original Issue: September 17, 2012

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BOEING SERVICE BULLETIN 747-53A2854

ALERT ALERT
FIGURE 1: SKIN INSPECTION IN SECTION 42, 44 AND 46

(SHEET 8 OF 11)

Export Controlled ECCN: 9E991 - BOEING

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Original Issue: September 17, 2012

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BOEING SERVICE BULLETIN 747-53A2854

ALERT ALERT
FIGURE 1: SKIN INSPECTION IN SECTION 42, 44 AND 46

(SHEET 9 OF 11)

Export Controlled ECCN: 9E991 - BOEING

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Original Issue: September 17, 2012

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BOEING SERVICE BULLETIN 747-53A2854

ALERT ALERT
FIGURE 1: SKIN INSPECTION IN SECTION 42, 44 AND 46

(SHEET 10 OF 11)

Export Controlled ECCN: 9E991 - BOEING

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BOEING SERVICE BULLETIN 747-53A2854

ALERT ALERT
The step number shown below agrees with the number shown in the circle symbols in the figure.

Step Task Name Identification Qty More Data

Do external sliding

probe eddy current

inspections of the

skin for cracks just

above the upper row

of fasteners in the

affected lap joint in

accordance with 747

NDT Part 6, 53-30-

25.

1 Inspect Skin - -

FIGURE 1: SKIN INSPECTION IN SECTION 42, 44 AND 46

(SHEET 11 OF 11)

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This Figure applies only to: Group 2.

FIGURE 2: SKIN INSPECTION IN SECTION 42

(SHEET 1 OF 4)

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BOEING SERVICE BULLETIN 747-53A2854

ALERT ALERT
FIGURE 2: SKIN INSPECTION IN SECTION 42

(SHEET 2 OF 4)

Export Controlled ECCN: 9E991 - BOEING

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Original Issue: September 17, 2012

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BOEING SERVICE BULLETIN 747-53A2854

ALERT ALERT
FIGURE 2: SKIN INSPECTION IN SECTION 42

(SHEET 3 OF 4)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: September 17, 2012

747-53A2854

32 of 33

BOEING SERVICE BULLETIN 747-53A2854

ALERT ALERT
The step number shown below agrees with the number shown in the circle symbols in the figure.

Step Task Name Identification Qty More Data

Do external sliding

probe eddy current

inspections of the

skin for cracks just

above the upper row

of fasteners in the

affected lap joint in

accordance with 747

NDT Part 6, 53-30-

25.

1 Inspect Skin - -

FIGURE 2: SKIN INSPECTION IN SECTION 42

(SHEET 4 OF 4)

Export Controlled ECCN: 9E991 - BOEING

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BOEING SERVICE BULLETIN 747-53A2854

ALERT ALERT