Commercial 

Airplanes 747

Service Bulletin

ALERT

Number: 747-53A2861

Original Issue: April 01, 2014

ATA System: 5331

SUBJECT: FUSELAGE - Skin - Lower Lobe Skin Inspection for Corrosion at Circumferential Splice

Locations

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.

ECCN: 9E991

BOEING PROPRIETARY, CONFIDENTIAL AND/OR TRADE SECRET

Copyright © 2014 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Unpublished Work.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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ALERT ALERT

BLANK PAGE
Table of Contents

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

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

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

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

2. Spares Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17

B. Concurrent Requirements . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17

C. Reason . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17

D. Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17

E. Compliance . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 18

F. Approval . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 42

G. Manpower . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 42

H. Weight and Balance Changes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 43

I. Electrical Load Data . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 43

J. References . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 43

1. Existing Data: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 43

2. Data Supplied with this Service Bulletin: . . . . . . . . . . . . . . . . . . . . . . . . . . . 43

3. Installation Drawings Used in the Preparation of this Service Bulletin: . . . . . . . . . . . 43

K. Publications Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 44

L. Interchangeability and Intermixability of Parts . . . . . . . . . . . . . . . . . . . . . . . . . . . 44

M. Software Accomplishment Summary . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 44

2. MATERIAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 45

A. Material - Price and Availability . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 45

B. Industry Support Information . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 45

C. Parts Necessary for Each Airplane . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 45

1. Kits/Parts . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 45

2. Parts and Materials Supplied by the Operator . . . . . . . . . . . . . . . . . . . . . . . . 45

3. Parts Modified and Reidentified . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 45

4. Parts Removed and Not Replaced . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 45

D. Parts Necessary to Change Spares . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 45

E. Special Tooling - Price and Availability . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 45

F. Special Tooling Necessary to do this Service Bulletin . . . . . . . . . . . . . . . . . . . . . . . 45

3. ACCOMPLISHMENT INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 47

A. GENERAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 47

B. WORK INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 49

FIGURE 1: INSPECTION AREA 1 (STA 741) [Group 1] . . . . . . . . . . . . . . . . . . . . . . . . . 54

FIGURE 2: INSPECTION AREA 2 (STA 1741) [Group 1] . . . . . . . . . . . . . . . . . . . . . . . . . 56

FIGURE 3: INSPECTION AREA 3 (STA 1961) [Group 1] . . . . . . . . . . . . . . . . . . . . . . . . . 58

FIGURE 4: INSPECTION AREA 4 (STA 2181) [Group 1] . . . . . . . . . . . . . . . . . . . . . . . . . 60

FIGURE 5: INSPECTION AREA 2 (STA 1741) [Group 2] . . . . . . . . . . . . . . . . . . . . . . . . . 62

FIGURE 6: INSPECTION AREA 3 (STA 1961) [Group 2] . . . . . . . . . . . . . . . . . . . . . . . . . 64

FIGURE 7: WING TO BODY FAIRING PANEL REMOVAL [Group 2] . . . . . . . . . . . . . . . . . . 66

FIGURE 8: WING TO BODY FAIRING PANEL INSTALLATION [Group 2] . . . . . . . . . . . . . . . 68

APPENDIX A: LOGIC DIAGRAM - GROUP 1 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 70

APPENDIX B: LOGIC DIAGRAM - GROUP 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 72

APPENDIX C: GROUP 1 SKIN PANEL DATA [Group 1] . . . . . . . . . . . . . . . . . . . . . . . . . . . 75

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APPENDIX D: GROUP 2 (747SP) SKIN PANEL DATA [Group 2] . . . . . . . . . . . . . . . . . . . . . . 77

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ALERT ALERT
Commercial 

Airplanes 747

Service Bulletin

ALERT

Summary Number: 747-53A2861

Original Issue: April 01, 2014

ATA System: 5331

SUBJECT: FUSELAGE - Skin - Lower Lobe Skin Inspection for Corrosion at Circumferential Splice

Locations

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 external inspections of the skin in the lower lobe at certain

circumferential splice locations for corrosion and cracks. Skin corrosion that is not found and repaired can result

in cracks, which can become large and adversely affect the structural integrity of the airplane.

Several operators have reported that corrosion was found on the mating surfaces between the skin and stringers

in Section 42 and Section 46 at the circumferential skin splices. There were no visual indications of corrosion

apparent during both internal and external inspections of the affected areas. Review of the applicable drawings

shows that the stringers in these circumferential splice locations were not installed with faying surface sealant.

Fillet seals were applied on both the upper and lower sides of the stringer, so if a fillet seal is compromised,

moisture can enter the area and result in corrosion in the area between the skin and the stringer.

Accomplishment of the inspections in this service bulletin will help ensure the structural integrity of the fuselage

skin at the affected circumferential splice locations.

Boeing Service Related Problem (SRP) 747-SRP-53-0392 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

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Planning Data Affected Reference

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 Parts/Material No

Paragraph 2.F., Special Tooling Necessary to

do this Service Bulletin

Special Tooling Required No

ACTION

Do external General Visual Inspections (GVI) of the fuselage skin at the lower circumferential splices at STA

741 (Group 1 only), STA 1741, STA 1961 and STA 2181 (Group 1 only) for the presence of existing external

skin repair doublers or production doublers. If existing repair doublers or production doublers that cover the skin

common to the stringers are found, do surface Low Frequency Eddy Current (LFEC) inspections of the doublers

for cracks in the skin in the areas common to the stringers that are covered by the repair doublers or production

doublers. If cracks are found, repair in accordance with this service bulletin.

If no existing external repair doublers or production doublers are found, and in affected areas not covered by

existing repair doublers or production doublers, do external surface LFEC inspections of the fuselage skin in

the affected areas for corrosion that may exist between the skin inner surface and the stringers.

If corrosion is found, repair in accordance with this service bulletin. In areas where no corrosion was found, do

external surface High Frequency Eddy Current (HFEC) inspections of the skin at the fastener locations common

to the skin and stringers for cracks. Repair any crack found in accordance with this service bulletin.

If no corrosion is found, do external surface HFEC inspections of the skin at the fastener locations common to

the skin and stringers for cracks. Repair any crack found in accordance with this service bulletin.

Repeat the inspections in this service bulletin at the times given in Paragraph 1.E., Compliance.

EFFECTIVITY

747-100B, 747-100B SUD, 747-200B, 747-200C, 747-200F, 747-300, 747-400, 747-400D, 747-400F, 747SR

and 747SP Airplanes. Refer to Paragraph 1.A.1., Airplanes, for the list of affected airplanes.

COMPLIANCE

The Federal Aviation Administration (FAA) will possibly release an Airworthiness Directive related to this service

bulletin. The Airworthiness Directive will make the compliance tasks and times given in this service bulletin

mandatory.

Refer to Paragraph 1.E., Compliance.

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ALERT ALERT
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 1 121.25 32.75

Group 2 85.50 22.50

Refer to Paragraph 1.G., Manpower.

MATERIAL INFORMATION

None.

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ALERT ALERT
Commercial 

Airplanes 747

Service Bulletin

ALERT

Number: 747-53A2861

Original Issue: April 01, 2014

ATA System: 5331

SUBJECT: FUSELAGE - Skin - Lower Lobe Skin Inspection for Corrosion at Circumferential Splice

Locations

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 applicable to 747-100B, 747-100B SUD, 747-200B, 747-200C, 747-200F,

747-300, 747-400, 747-400D, 747-400F, 747SR and 747SP airplanes line number 310 through

1419, except 747 Large Cargo Freighter (LCF) airplanes, in two Groups. The Variable Numbers

and Group Information for the applicable airplanes is given below.

GROUP CONFIGURATION DESCRIPTION

747 airplanes line number 310 through 1419, except 747 Large Cargo

Freighter (LCF) airplanes and 747SP airplanes.

1 -

2 - 747SP airplanes line number 310 through 1419.

Airplane Models:

747-100B, 747-100B SUD, 747-200B, 747-200C, 747-200F, 747-300, 747-400, 747-400D,

747-400F, 747SP, 747SR

Variable Number Group

RA544 - RA548 1

RA726 - RA731 1

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Variable Number Group

RA750 1

RA784 1

RB411 - RB413 1

RB421 1

RB681 - RB697 1

RB711 1

RB721 - RB723 1

RB741 - RB748 1

RD047 - RD059 1

RD081 - RD083 1

RD091 - RD092 1

RD122 - RD127 1

RD134 - RD144 1

RD166 - RD167 1

RD171 - RD172 1

RD181 - RD183 1

RD201 - RD204 1

RD221 - RD227 1

RD231 - RD235 1

RD241 - RD243 1

RD251 - RD262 1

RD271 - RD272 1

RD291 - RD292 1

RD301 - RD302 1

RD311 1

RD351 - RD358 1

RD361 - RD366 1

RD381 - RD383 1

RD411 - RD414 1

RD421 - RD426 1

RD431 - RD435 1

RD441 - RD442 1

RD451 - RD456 1

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Variable Number Group

RD461 1

RD471 - RD475 1

RD513 - RD519 1

RD531 - RD533 1

RD551 1

RD561 1

RD571 1

RD581 - RD583 1

RD591 - RD593 1

RD603 - RD607 1

RD643 - RD649 1

RD652 - RD659 1

RD661 1

RD671 1

RD701 - RD702 1

RD721 - RD722 1

RD741 - RD742 1

RD751 - RD755 1

RD761 1

RD771 - RD775 1

RD781 - RD783 1

RD791 - RD792 1

RE001 1

RF001 - RF006 1

RG006 - RG009 2

RG095 2

RG104 2

RG161 - RG164 2

RG172 - RG174 2

RG191 - RG193 2

RG211 - RG213 2

RG221 - RG222 2

RH101 - RH102 2

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Variable Number Group

RH111 - RH112 2

RH121 - RH122 2

RJ152 1

RJ303 1

RJ321 - RJ322 1

RJ331 - RJ333 1

RL401 - RL403 1

RL411 - RL436 1

RL451 - RL456 1

RL461 - RL462 1

RL471 - RL481 1

RL491 - RL492 1

RL501 - RL502 1

RL511 - RL516 1

RL521 - RL522 1

RL531 - RL534 1

RL551 1

RL561 - RL568 1

RL571 - RL572 1

RL576 - RL577 1

RL579 1

RL581 - RL586 1

RL651 - RL655 1

RL671 - RL675 1

RL681 - RL684 1

RL751 - RL752 1

RM001 - RM007 1

RM010 - RM013 1

RM021 - RM024 1

RM026 - RM030 1

RM036 - RM045 1

RM051 - RM053 1

RM071 1

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ALERT ALERT
Variable Number Group

RM081 - RM084 1

RM091 1

RM096 - RM097 1

RM116 - RM117 1

RM126 - RM132 1

RM136 - RM147 1

RM156 - RM158 1

RM166 - RM177 1

RM191 - RM192 1

RM231 - RM233 1

RM241 - RM246 1

RM261 - RM264 1

RM316 - RM318 1

RM331 - RM333 1

RM341 1

RM351 - RM355 1

RM366 - RM367 1

RM401 - RM403 1

RM426 1

RM431 1

RM441 - RM443 1

RM445 1

RM801 - RM803 1

RM811 - RM813 1

RM851 - RM859 1

RM861 - RM863 1

RM871 - RM899 1

RM901 - RM906 1

RM911 1

RR001 - RR005 1

RR021 - RR025 1

RR031 1

RR202 - RR206 1

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BOEING SERVICE BULLETIN 747-53A2861

ALERT ALERT
Variable Number Group

RR223 - RR226 1

RR262 - RR267 1

RR303 - RR310 1

RR331 - RR332 1

RR336 1

RR345 1

RR361 - RR362 1

RR421 - RR422 1

RR431 - RR432 1

RR441 - RR442 1

RR451 1

RR501 - RR504 1

RR521 - RR522 1

RR526 1

RR531 1

RR551 - RR556 1

RR561 1

RR566 1

RR701 1

RR721 - RR724 1

RR746 - RR748 1

RR851 - RR856 1

RR861 - RR862 1

RR951 - RR952 1

RS001 - RS002 1

RS201 1

RS211 - RS212 1

RS221 - RS222 1

RS231 - RS241 1

RS251 - RS259 1

RS263 1

RS265 - RS268 1

RS271 - RS276 1

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ALERT ALERT
Variable Number Group

RS291 - RS292 1

RS301 - RS306 1

RS311 - RS320 1

RS331 - RS333 1

RS341 - RS342 1

RS699 1

RS701 - RS703 1

RS711 - RS713 1

RS721 - RS722 1

RS731 - RS732 1

RS741 - RS743 1

RS751 - RS752 1

RS761 - RS762 1

RS771 1

RS781 - RS782 1

RS786 1

RT001 - RT014 1

RT021 - RT022 1

RT031 - RT035 1

RT041 - RT047 1

RT061 1

RT071 - RT075 1

RT101 - RT103 1

RT121 1

RT131 - RT137 1

RT151 - RT152 1

RT161 - RT168 1

RT401 - RT412 1

RT431 - RT447 1

RT451 - RT469 1

RT471 - RT499 1

RT501 - RT535 1

RT551 - RT568 1

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ALERT ALERT
Variable Number Group

RT571 - RT591 1

RT601 - RT630 1

RT633 - RT657 1

RT671 - RT673 1

RT681 - RT682 1

RT691 - RT699 1

RT701 - RT704 1

RT711 - RT717 1

RT741 - RT742 1

RT744 - RT757 1

RT776 - RT777 1

RT781 - RT784 1

RT801 - RT803 1

RT811 - RT814 1

RT831 - RT837 1

RT861 - RT864 1

RT877 - RT880 1

RT931 - RT932 1

RT945 - RT949 1

RT951 - RT955 1

RT966 - RT967 1

RU001 - RU006 1

RU016 - RU017 1

RU031 - RU032 1

RU051 - RU052 1

RU059 - RU062 1

RU081 - RU083 1

RU101 - RU102 1

RU121 - RU132 1

RU801 - RU809 1

RU831 - RU841 1

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BOEING SERVICE BULLETIN 747-53A2861

ALERT ALERT
2. Spares Affected

None.

B. Concurrent Requirements

None.

C. Reason

This service bulletin gives instructions to do external inspections of the skin in the lower lobe at certain

circumferential splice locations for corrosion and cracks. Skin corrosion that is not found and repaired

can result in cracks, which can become large and adversely affect the structural integrity of the airplane.

Several operators have reported that corrosion was found on the mating surfaces between the skin

and stringers in Section 42 and Section 46 at the circumferential skin splices. There were no visual

indications of corrosion apparent during both internal and external inspections of the affected areas.

Review of the applicable drawings shows that the stringers in these circumferential splice locations

were not installed with faying surface sealant. Fillet seals were applied on both the upper and lower

sides of the stringer, so if a fillet seal is compromised, moisture can enter the area and result in corrosion

in the area between the skin and the stringer.

Accomplishment of the inspections in this service bulletin will help ensure the structural integrity of the

fuselage skin at the affected circumferential splice locations.

Boeing Service Related Problem (SRP) 747-SRP-53-0392 is related to this service bulletin.

D. Description

Do external General Visual Inspections (GVI) of the fuselage skin at the lower circumferential splices

at STA 741 (Group 1 only), STA 1741, STA 1961 and STA 2181 (Group 1 only) for the presence of

existing external skin repair doublers or production doublers. If existing repair doublers or production

doublers that cover the skin common to the stringers are found, do surface Low Frequency Eddy Current

(LFEC) inspections of the doublers for cracks in the skin in the areas common to the stringers that are

covered by the repair doublers or production doublers. If cracks are found, repair in accordance with

this service bulletin.

If no existing external repair doublers or production doublers are found, and in affected areas not

covered by existing repair doublers or production doublers, do external surface LFEC inspections of

the fuselage skin in the affected areas for corrosion that may exist between the skin inner surface and

the stringers.

If corrosion is found, repair in accordance with this service bulletin. In areas where no corrosion was

found, do external surface High Frequency Eddy Current (HFEC) inspections of the skin at the fastener

locations common to the skin and stringers for cracks. Repair any crack found in accordance with this

service bulletin.

If no corrosion is found, do external surface HFEC inspections of the skin at the fastener locations

common to the skin and stringers for cracks. Repair any crack found in accordance with this service

bulletin.

Repeat the inspections in this service bulletin at the times given in Paragraph 1.E., Compliance.

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BOEING SERVICE BULLETIN 747-53A2861

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

Group 1:

Affected Maintenance Zones

Model Zone

747-100B, 747-100B SUD, 747- 125, 126, 143, 144, 147, 148

200B, 747-200C, 747-200F,

747-300, 747-400, 747-400D,

747-400F, 747SR

Group 2:

Affected Maintenance Zones

Model Zone

747SP 143, 144

E. Compliance

The Federal Aviation Administration (FAA) will possibly release an Airworthiness Directive related to

this service bulletin. The Airworthiness Directive will make the compliance tasks and times given in this

service bulletin mandatory.

Do the required actions in accordance with Paragraph 3. Accomplishment Instructions.

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.

Group 1:

Table 1: Inspection and Repair of the Skin at the Lower Lobe Circumferential Splice at STA 741 (Area 1)

Repeat Interval

(Not to Exceed)

Compliance Time (Whichever

Occurs Later)

Condition Action

Within 3,000 -

flight cycles or

24 months after

the original issue date of this

service bulletin,

whichever occurs first.

Before 10,000

total flight cycles, or within

10 years from

the date of issuance of the

original certificate of airworthiness or the original export certificate of airworthiness, whichever

occurs first.

Do external GVI of the fuselage

skin in Area 1 as shown in PART

1: INSPECTION AREAS for the

presence of external doublers.

All airplanes

Export Controlled ECCN: 9E991 - BOEING

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BOEING SERVICE BULLETIN 747-53A2861

ALERT ALERT
Group 1:

Table 1: Inspection and Repair of the Skin at the Lower Lobe Circumferential Splice at STA 741 (Area 1)

Repeat Interval

(Not to Exceed)

Compliance Time (Whichever

Occurs Later)

Condition Action

Do PART 2: EXTERNAL LOW- Before further flight. -

ER LOBE EXTERNAL DOUBLER SURFACE LFEC INSPECTION FOR SKIN CRACKS in the

area of any doubler. Determine

if the doubler ends on a row of

fasteners common to a stringer.

CONDITION 1: ANY

EXISTING EXTERNAL

DOUBLER FOUND IN

THE AFFECTED AREAS

Do PART 3: EXTERNAL LOW- Before further flight. -

ER LOBE SKIN SURFACE

LFEC INSPECTION FOR CORROSION in affected areas.

CONDITION 2: AFFECTED AREAS WITH

NO EXISTING EXTERNAL DOUBLER

FOUND

800 flight cycles

or 24 months,

whichever occurs earlier.

If the doubler ends on a stringer

fastener row: Repeat PART 2:

EXTERNAL LOWER LOBE

DOUBLER SURFACE LFEC

INSPECTION FOR SKIN

CRACKS in the area of the doubler.

CONDITION 3: NO

SKIN CRACK FOUND

UNDER EXTERNAL

DOUBLER

3,000 flight cycles or 24

months,

whichever occurs earlier.

If the doubler ends one or two -

fastener rows beyond a stringer

fastener row: Repeat PART 2:

EXTERNAL LOWER LOBE

DOUBLER SURFACE LFEC

INSPECTION FOR SKIN

CRACKS in the area of the doubler.

If the doubler ends three or more - -

fastener rows beyond a stringer

fastener row: No more work is

necessary in the area of the

doubler.

Export Controlled ECCN: 9E991 - BOEING

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BOEING SERVICE BULLETIN 747-53A2861

ALERT ALERT
Group 1:

Table 1: Inspection and Repair of the Skin at the Lower Lobe Circumferential Splice at STA 741 (Area 1)

Repeat Interval

(Not to Exceed)

Compliance Time (Whichever

Occurs Later)

Condition Action

(ACTION 1) Do PART 5: RE- Before further flight. -

PAIR.

CONDITION 4: ANY

SKIN CRACK FOUND

UNDER EXTERNAL

DOUBLER 800 flight cycles

or 24 months,

whichever occurs earlier.

(ACTION 2) If the repair doubler -

installed in accordance with

PART 5: REPAIR ends on a

stringer fastener row: Repeat

PART 2: EXTERNAL LOWER

LOBE DOUBLER SURFACE

LFEC INSPECTION FOR SKIN

CRACKS in the area of the doubler.

3,000 flight cycles or 24

months,

whichever occurs earlier.

(ACTION 2) If the repair doubler -

installed in accordance with

PART 5: REPAIR ends one or

two fastener rows beyond a

stringer fastener row: Repeat

PART 2: EXTERNAL LOWER

LOBE DOUBLER SURFACE

LFEC INSPECTION FOR SKIN

CRACKS in the area of the doubler.

(ACTION 2) If the repair doubler - -

installed in accordance with

PART 5: REPAIR ends three or

more fastener rows beyond a

stringer fastener row: No more

work is necessary in the area of

the repair.

Do PART 4: EXTERNAL LOW- Before further flight. -

ER LOBE SKIN SURFACE

HFEC INSPECTION FOR

CRACKS in affected areas.

CONDITION 5: NO

CORROSION FOUND

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BOEING SERVICE BULLETIN 747-53A2861

ALERT ALERT
Group 1:

Table 1: Inspection and Repair of the Skin at the Lower Lobe Circumferential Splice at STA 741 (Area 1)

Repeat Interval

(Not to Exceed)

Compliance Time (Whichever

Occurs Later)

Condition Action

(ACTION 1) Do PART 5: RE- Before further flight. -

PAIR in areas where corrosion

was found.

CONDITION 6: ANY

CORROSION FOUND

(ACTION 2) Do PART 4: EXTER- Before further flight. -

NAL LOWER LOBE SKIN SURFACE HFEC INSPECTION FOR

CRACKS in affected areas

where no corrosion was found

or where corrosion was removed

by blending.

800 flight cycles

or 24 months,

whichever occurs earlier.

(ACTION 3) If a repair doubler -

installed in accordance with

PART 5: REPAIR ends on a

stringer fastener row: Repeat

PART 2: EXTERNAL LOWER

LOBE DOUBLER SURFACE

LFEC INSPECTION FOR SKIN

CRACKS in the area of the doubler.

3,000 flight cycles or 24

months,

whichever occurs earlier.

(ACTION 3) If a repair doubler -

installed in accordance with

PART 5: REPAIR ends one or

two fastener rows beyond a

stringer fastener row: Repeat

PART 2: EXTERNAL LOWER

LOBE DOUBLER SURFACE

LFEC INSPECTION FOR SKIN

CRACKS in the area of the doubler.

(ACTION 3) If a repair doubler - -

installed in accordance with

PART 5: REPAIR ends three or

more fastener rows beyond a

stringer fastener row: No more

work is necessary in the area of

the repair.

3,000 flight cycles or 24

months,

whichever occurs earlier.

Repeat PART 3: EXTERNAL -

LOWER LOBE SKIN SURFACE

LFEC INSPECTION FOR CORROSION and PART 4: EXTERNAL LOWER LOBE SKIN SURFACE HFEC INSPECTION FOR

CRACKS at all affected unrepaired areas. (a)

CONDITION 7: NO

CRACK FOUND

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BOEING SERVICE BULLETIN 747-53A2861

ALERT ALERT
Group 1:

Table 1: Inspection and Repair of the Skin at the Lower Lobe Circumferential Splice at STA 741 (Area 1)

Repeat Interval

(Not to Exceed)

Compliance Time (Whichever

Occurs Later)

Condition Action

(ACTION 1) Do PART 5: RE- Before further flight. -

PAIR.

CONDITION 8: ANY

CRACK FOUND

800 flight cycles

or 24 months,

whichever occurs earlier.

(ACTION 2) If a repair doubler -

installed in accordance with

PART 5: REPAIR ends on a

stringer fastener row: Repeat

PART 2: EXTERNAL LOWER

LOBE DOUBLER SURFACE

LFEC INSPECTION FOR SKIN

CRACKS in the area of the doubler.

3,000 flight cycles or 24

months,

whichever occurs earlier.

(ACTION 2) If a repair doubler -

installed in accordance with

PART 5: REPAIR ends one or

two fastener rows beyond a

stringer fastener row: Repeat

PART 2: EXTERNAL LOWER

LOBE DOUBLER SURFACE

LFEC INSPECTION FOR SKIN

CRACKS in the area of the doubler.

(ACTION 2) If a repair doubler - -

installed in accordance with

PART 5: REPAIR ends three or

more fastener rows beyond a

stringer fastener row: No more

work is necessary in the area of

the repair.

3,000 flight cycles or 24

months,

whichever occurs earlier.

(ACTION 3) Repeat PART 3: -

EXTERNAL LOWER LOBE

SKIN SURFACE LFEC INSPECTION FOR CORROSION and

PART 4: EXTERNAL LOWER

LOBE SKIN SURFACE HFEC

INSPECTION FOR CRACKS at

all affected unrepaired areas. (a)

(a) For the purposes of these inspections, "unrepaired areas" are defined as affected areas where the skin

is not covered with a doubler. Areas repaired with only blends or oversized fasteners should be treated

as unrepaired.

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BOEING SERVICE BULLETIN 747-53A2861

ALERT ALERT
Group 1:

Table 2: Inspection and Repair of the Skin at the Lower Lobe Circumferential Splice at STA 1741 (Area

2)

Repeat Interval

(Not to Exceed)

Compliance Time (Whichever

Occurs Later)

Condition Action

Within 3,000 -

flight cycles or

24 months after

the original issue date of this

service bulletin,

whichever occurs first.

Before 10,000

total flight cycles, or within

10 years from

the date of issuance of the

original certificate of airworthiness or the original export certificate of airworthiness, whichever

occurs first.

Do external GVI of the fuselage

skin in Area 2 as shown in PART

1: INSPECTION AREAS for the

presence of external doublers.

All airplanes

Do PART 2: EXTERNAL LOW- Before further flight. -

ER LOBE DOUBLER SURFACE

LFEC INSPECTION FOR SKIN

CRACKS in the area of the doubler. Determine if the doubler

ends on a row of fasteners

common to a stringer.

CONDITION 1: ANY

EXISTING EXTERNAL

DOUBLER FOUND IN

THE AFFECTED AREAS

Do PART 3: EXTERNAL LOW- Before further flight. -

ER LOBE SKIN SURFACE

LFEC INSPECTION FOR CORROSION in affected areas.

CONDITION 2: AFFECTED AREAS WITH

NO EXISTING EXTERNAL DOUBLER

FOUND

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BOEING SERVICE BULLETIN 747-53A2861

ALERT ALERT
Group 1:

Table 2: Inspection and Repair of the Skin at the Lower Lobe Circumferential Splice at STA 1741 (Area

2)

Repeat Interval

(Not to Exceed)

Compliance Time (Whichever

Occurs Later)

Condition Action

1,500 flight cycles or 48

months,

whichever occurs earlier.

If the doubler ends on a stringer

fastener row: Repeat PART 2:

EXTERNAL LOWER LOBE

DOUBLER SURFACE LFEC

INSPECTION FOR SKIN

CRACKS in the area of the doubler.

CONDITION 3: NO

SKIN CRACK FOUND

UNDER EXTERNAL

DOUBLER

6,000 flight cycles or 48

months,

whichever occurs earlier.

If the doubler ends one or two -

fastener rows beyond a stringer

fastener row: Repeat PART 2:

EXTERNAL LOWER LOBE

DOUBLER SURFACE LFEC

INSPECTION FOR SKIN

CRACKS in the area of the doubler.

If the doubler ends three or more - -

fastener rows beyond a stringer

fastener row: No more work is

necessary in the area of the

doubler.

(ACTION 1) Do PART 5: RE- Before further flight. -

PAIR.

CONDITION 4: ANY

SKIN CRACK FOUND

UNDER EXTERNAL

DOUBLER 1,500 flight cycles or 48

months,

whichever occurs earlier.

(ACTION 2) If the doubler ends -

on a stringer fastener row: Repeat PART 2: EXTERNAL

LOWER LOBE DOUBLER

SURFACE LFEC INSPECTION

FOR SKIN CRACKS in the area

of the doubler.

6,000 flight cycles or 48

months,

whichever occurs earlier.

(ACTION 2) If the doubler ends -

one or two fastener rows beyond

a stringer fastener row: Repeat

PART 2: EXTERNAL LOWER

LOBE DOUBLER SURFACE

LFEC INSPECTION FOR SKIN

CRACKS in the area of the doubler.

(ACTION 2) If the doubler ends - -

three or more fastener rows beyond a stringer fastener row: No

more work is necessary in the

area of the doubler.

Export Controlled ECCN: 9E991 - BOEING

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Original Issue: April 01, 2014

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BOEING SERVICE BULLETIN 747-53A2861

ALERT ALERT
Group 1:

Table 2: Inspection and Repair of the Skin at the Lower Lobe Circumferential Splice at STA 1741 (Area

2)

Repeat Interval

(Not to Exceed)

Compliance Time (Whichever

Occurs Later)

Condition Action

Do PART 4: EXTERNAL LOW- Before further flight. -

ER LOBE SKIN SURFACE

HFEC INSPECTION FOR

CRACKS in affected areas.

CONDITION 5: NO

CORROSION FOUND

(ACTION 1) Do PART 5: RE- Before further flight. -

PAIR in areas where corrosion

was found.

CONDITION 6: ANY

CORROSION FOUND

(ACTION 2) Do PART 4: EXTER- Before further flight. -

NAL LOWER LOBE SKIN SURFACE HFEC INSPECTION FOR

CRACKS in affected areas

where no corrosion was found

or where corrosion was removed

by blending.

1,500 flight cycles or 48

months,

whichever occurs earlier.

(ACTION 3) If a repair doubler -

installed in accordance with

PART 5: REPAIR ends on a

stringer fastener row: Repeat

PART 2: EXTERNAL LOWER

LOBE DOUBLER SURFACE

LFEC INSPECTION FOR SKIN

CRACKS in the area of the doubler.

6,000 flight cycles or 48

months,

whichever occurs earlier.

(ACTION 3) If a repair doubler -

installed in accordance with

PART 5: REPAIR ends one or

two fastener rows beyond a

stringer fastener row: Repeat

PART 2: EXTERNAL LOWER

LOBE DOUBLER SURFACE

LFEC INSPECTION FOR SKIN

CRACKS in the area of the doubler.

(ACTION 3) If a repair doubler - -

installed in accordance with

PART 5: REPAIR ends three or

more fastener rows beyond a

stringer fastener row: No more

work is necessary in the area of

the repair.

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: April 01, 2014

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25 of 77

BOEING SERVICE BULLETIN 747-53A2861

ALERT ALERT
Group 1:

Table 2: Inspection and Repair of the Skin at the Lower Lobe Circumferential Splice at STA 1741 (Area

2)

Repeat Interval

(Not to Exceed)

Compliance Time (Whichever

Occurs Later)

Condition Action

6,000 flight cycles or 48

months,

whichever occurs earlier.

Repeat PART 3: EXTERNAL -

LOWER LOBE SKIN SURFACE

LFEC INSPECTION FOR CORROSION and PART 4: EXTERNAL LOWER LOBE SKIN SURFACE HFEC INSPECTION FOR

CRACKS at all affected unrepaired areas. (a)

CONDITION 7: NO

CRACK FOUND

Export Controlled ECCN: 9E991 - BOEING

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Original Issue: April 01, 2014

747-53A2861

26 of 77

BOEING SERVICE BULLETIN 747-53A2861

ALERT ALERT
Group 1:

Table 2: Inspection and Repair of the Skin at the Lower Lobe Circumferential Splice at STA 1741 (Area

2)

Repeat Interval

(Not to Exceed)

Compliance Time (Whichever

Occurs Later)

Condition Action

(ACTION 1) Do PART 5: RE- Before further flight. -

PAIR.

CONDITION 8: ANY

CRACK FOUND

1,500 flight cycles or 48

months,

whichever occurs earlier.

(ACTION 2) If a repair doubler -

installed in accordance with

PART 5: REPAIR ends on a

stringer fastener row: Repeat

PART 2: EXTERNAL LOWER

LOBE DOUBLER SURFACE

LFEC INSPECTION FOR SKIN

CRACKS in the area of the doubler.

6,000 flight cycles or 48

months,

whichever occurs earlier.

(ACTION 2) If a repair doubler -

installed in accordance with

PART 5: REPAIR ends one or

two fastener rows beyond a

stringer fastener row: Repeat

PART 2: EXTERNAL LOWER

LOBE DOUBLER SURFACE

LFEC INSPECTION FOR SKIN

CRACKS in the area of the doubler.

(ACTION 2) If a repair doubler - -

installed in accordance with

PART 5: REPAIR ends three or

more fastener rows beyond a

stringer fastener row: No more

work is necessary in the area of

the repair.

6,000 flight cycles or 48

months,

whichever occurs earlier.

(ACTION 3) Repeat PART 3: -

EXTERNAL LOWER LOBE

SKIN SURFACE LFEC INSPECTION FOR CORROSION and

PART 4: EXTERNAL LOWER

LOBE SKIN SURFACE HFEC

INSPECTION FOR SKIN

CRACKS at all affected unrepaired areas. (a)

(a) For the purposes of these inspections, "unrepaired areas" are defined as affected areas where the skin

is not covered with a doubler. Areas repaired with only blends or oversized fasteners should be treated

as unrepaired.

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: April 01, 2014

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27 of 77

BOEING SERVICE BULLETIN 747-53A2861

ALERT ALERT
Group 1:

Table 3: Inspection and Repair of the Skin at the Lower Lobe Circumferential Splice at STA 1961 (Area

3)

Repeat Interval

(Not to Exceed)

Compliance Time (Whichever

Occurs Later)

Condition Action

Within 3,000 -

flight cycles or

24 months after

the original issue date of this

service bulletin,

whichever occurs first.

Before 10,000

total flight cycles, or within

10 years from

the date of issuance of the

original certificate of airworthiness or the original export certificate of airworthiness, whichever

occurs first.

Do external GVI of the fuselage

skin in Area 3 as shown in PART

1: INSPECTION AREAS for the

presence of external doublers.

All airplanes

Do PART 2: EXTERNAL LOW- Before further flight. -

ER LOBE DOUBLER SURFACE

LFEC INSPECTION FOR SKIN

CRACKS in the area of the doubler. Determine if the doubler

ends on a row of fasteners

common to a stringer.

CONDITION 1: ANY

EXISTING EXTERNAL

DOUBLER FOUND IN

THE AFFECTED AREAS

Do PART 3: EXTERNAL LOW- Before further flight. -

ER LOBE SKIN SURFACE

LFEC INSPECTION FOR CORROSION in affected areas.

CONDITION 2: AFFECTED AREAS WITH

NO EXISTING EXTERNAL DOUBLER

FOUND

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BOEING SERVICE BULLETIN 747-53A2861

ALERT ALERT
Group 1:

Table 3: Inspection and Repair of the Skin at the Lower Lobe Circumferential Splice at STA 1961 (Area

3)

Repeat Interval

(Not to Exceed)

Compliance Time (Whichever

Occurs Later)

Condition Action

800 flight cycles

or 24 months,

whichever occurs earlier.

If the doubler ends on a stringer

fastener row: Repeat PART 2:

EXTERNAL LOWER LOBE

DOUBLER SURFACE LFEC

INSPECTION FOR SKIN

CRACKS in the area of the doubler.

CONDITION 3: NO

SKIN CRACK FOUND

UNDER EXTERNAL

DOUBLER

6,000 flight cycles or 48

months,

whichever occurs earlier.

If the doubler ends one or two -

fastener rows beyond a stringer

fastener row: Repeat PART 2:

EXTERNAL LOWER LOBE

DOUBLER SURFACE LFEC

INSPECTION FOR SKIN

CRACKS in the area of the doubler.

If the doubler ends three or more - -

fastener rows beyond a stringer

fastener row: No more work is

necessary in the area of the

doubler.

(ACTION 1) Do PART 5: RE- Before further flight. -

PAIR.

CONDITION 4: ANY

SKIN CRACK FOUND

UNDER EXTERNAL

DOUBLER 800 flight cycles

or 24 months,

whichever occurs earlier.

(ACTION 2) If the doubler ends -

on a stringer fastener row: Repeat PART 2: EXTERNAL

LOWER LOBE DOUBLER

SURFACE LFEC INSPECTION

FOR SKIN CRACKS in the area

of the doubler.

6,000 flight cycles or 48

months,

whichever occurs earlier.

(ACTION 2) If the doubler ends -

one or two fastener rows beyond

a stringer fastener row: Repeat

PART 2: EXTERNAL LOWER

LOBE DOUBLER SURFACE

LFEC INSPECTION FOR SKIN

CRACKS in the area of the doubler.

(ACTION 2) If the doubler ends - -

three or more fastener rows beyond a stringer fastener row: No

more work is necessary in the

area of the doubler.

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: April 01, 2014

747-53A2861

29 of 77

BOEING SERVICE BULLETIN 747-53A2861

ALERT ALERT
Group 1:

Table 3: Inspection and Repair of the Skin at the Lower Lobe Circumferential Splice at STA 1961 (Area

3)

Repeat Interval

(Not to Exceed)

Compliance Time (Whichever

Occurs Later)

Condition Action

Do PART 4: EXTERNAL LOW- Before further flight. -

ER LOBE SKIN SURFACE

HFEC INSPECTION FOR

CRACKS in affected areas.

CONDITION 5: NO

CORROSION FOUND

(ACTION 1) Do PART 5: RE- Before further flight. -

PAIR in areas where corrosion

was found.

CONDITION 6: ANY

CORROSION FOUND

(ACTION 2) Do PART 4: EXTER- Before further flight. -

NAL LOWER LOBE SKIN SURFACE HFEC INSPECTION FOR

CRACKS in affected areas

where no corrosion was found

or where corrosion was removed

by blending.

800 flight cycles

or 24 months,

whichever occurs earlier.

(ACTION 3) If a repair doubler -

installed in accordance with

PART 5: REPAIR ends on a

stringer fastener row: Repeat

PART 2: EXTERNAL LOWER

LOBE DOUBLER SURFACE

LFEC INSPECTION FOR SKIN

CRACKS in the area of the doubler.

6,000 flight cycles or 48

months,

whichever occurs earlier.

(ACTION 3) If a repair doubler -

installed in accordance with

PART 5: REPAIR ends one or

two fastener rows beyond a

stringer fastener row: Repeat

PART 2: EXTERNAL LOWER

LOBE DOUBLER SURFACE

LFEC INSPECTION FOR SKIN

CRACKS in the area of the doubler.

(ACTION 3) If a repair doubler - -

installed in accordance with

PART 5: REPAIR ends three or

more fastener rows beyond a

stringer fastener row: No more

work is necessary in the area of

the repair.

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: April 01, 2014

747-53A2861

30 of 77

BOEING SERVICE BULLETIN 747-53A2861

ALERT ALERT
Group 1:

Table 3: Inspection and Repair of the Skin at the Lower Lobe Circumferential Splice at STA 1961 (Area

3)

Repeat Interval

(Not to Exceed)

Compliance Time (Whichever

Occurs Later)

Condition Action

6,000 flight cycles or 48

months,

whichever occurs earlier.

Repeat PART 3: EXTERNAL -

LOWER LOBE SKIN SURFACE

LFEC INSPECTION FOR CORROSION and PART 4: EXTERNAL LOWER LOBE SKIN SURFACE HFEC INSPECTION FOR

CRACKS at all affected unrepaired areas. (a)

CONDITION 7: NO

CRACK FOUND

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Original Issue: April 01, 2014

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BOEING SERVICE BULLETIN 747-53A2861

ALERT ALERT
Group 1:

Table 3: Inspection and Repair of the Skin at the Lower Lobe Circumferential Splice at STA 1961 (Area

3)

Repeat Interval

(Not to Exceed)

Compliance Time (Whichever

Occurs Later)

Condition Action

(ACTION 1) Do PART 5: RE- Before further flight. -

PAIR.

CONDITION 8: ANY

CRACK FOUND

800 flight cycles

or 24 months,

whichever occurs earlier.

(ACTION 2) If a repair doubler -

installed in accordance with

PART 5: REPAIR ends on a

stringer fastener row: Repeat

PART 2: EXTERNAL LOWER

LOBE DOUBLER SURFACE

LFEC INSPECTION FOR SKIN

CRACKS in the area of the doubler.

6,000 flight cycles or 48

months,

whichever occurs earlier.

(ACTION 2) If a repair doubler -

installed in accordance with

PART 5: REPAIR ends one or

two fastener rows beyond a

stringer fastener row: Repeat

PART 2: EXTERNAL LOWER

LOBE DOUBLER SURFACE

LFEC INSPECTION FOR SKIN

CRACKS in the area of the doubler.

(ACTION 2) If a repair doubler - -

installed in accordance with

PART 5: REPAIR ends three or

more fastener rows beyond a

stringer fastener row: No more

work is necessary in the area of

the repair.

6,000 flight cycles or 48

months,

whichever occurs earlier.

(ACTION 3) Repeat PART 3: -

EXTERNAL LOWER LOBE

SKIN SURFACE LFEC INSPECTION FOR CORROSION and

PART 4: EXTERNAL LOWER

LOBE SKIN SURFACE HFEC

INSPECTION FOR CRACKS at

all affected unrepaired areas. (a)

(a) For the purposes of these inspections, "unrepaired areas" are defined as affected areas where the skin

is not covered with a doubler. Areas repaired with only blends or oversized fasteners should be treated

as unrepaired.

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: April 01, 2014

747-53A2861

32 of 77

BOEING SERVICE BULLETIN 747-53A2861

ALERT ALERT
Group 1:

Table 4: Inspection and Repair of the Skin at the Lower Lobe Circumferential Splice at STA 2181 (Area

4)

Repeat Interval

(Not to Exceed)

Compliance Time (Whichever

Occurs Later)

Condition Action

Within 3,000 -

flight cycles or

24 months after

the original issue date of this

service bulletin,

whichever occurs first.

Before 10,000

total flight cycles, or within

10 years from

the date of issuance of the

original certificate of airworthiness or the original export certificate of airworthiness, whichever

occurs first.

Do external GVI of the fuselage

skin in Area 4 as shown in PART

1: INSPECTION AREAS for the

presence of external doublers.

All airplanes

Do PART 2: EXTERNAL LOW- Before further flight. -

ER LOBE DOUBLER SURFACE

LFEC INSPECTION FOR SKIN

CRACKS in the area of the doubler. Determine if the doubler

ends on a row of fasteners

common to a stringer.

CONDITION 1: ANY

EXISTING EXTERNAL

DOUBLER FOUND IN

THE AFFECTED AREAS

Do PART 3: EXTERNAL LOW- Before further flight. -

ER LOBE SKIN SURFACE

LFEC INSPECTION FOR CORROSION in affected areas.

CONDITION 2: AFFECTED AREAS WITH

NO EXISTING EXTERNAL DOUBLER

FOUND

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ALERT ALERT
Group 1:

Table 4: Inspection and Repair of the Skin at the Lower Lobe Circumferential Splice at STA 2181 (Area

4)

Repeat Interval

(Not to Exceed)

Compliance Time (Whichever

Occurs Later)

Condition Action

800 flight cycles

or 24 months,

whichever occurs earlier.

If the doubler ends on a stringer

fastener row: Repeat PART 2:

EXTERNAL LOWER LOBE

DOUBLER SURFACE LFEC

INSPECTION FOR SKIN

CRACKS in the area of the doubler.

CONDITION 3: NO

SKIN CRACK FOUND

UNDER EXTERNAL

DOUBLER

6,000 flight cycles or 48

months,

whichever occurs earlier.

If the doubler ends one or two -

fastener rows beyond a stringer

fastener row: Repeat PART 2:

EXTERNAL LOWER LOBE

DOUBLER SURFACE LFEC

INSPECTION FOR SKIN

CRACKS in the area of the doubler.

If the doubler ends three or more - -

fastener rows beyond a stringer

fastener row: No more work is

necessary in the area of the

doubler.

(ACTION 1) Do PART 5: RE- Before further flight. -

PAIR.

CONDITION 4: ANY

SKIN CRACK FOUND

UNDER EXTERNAL

DOUBLER 800 flight cycles

or 24 months,

whichever occurs earlier.

(ACTION 2) If the doubler ends -

on a stringer fastener row: Repeat PART 2: EXTERNAL

LOWER LOBE DOUBLER

SURFACE LFEC INSPECTION

FOR SKIN CRACKS in the area

of the doubler.

6,000 flight cycles or 48

months,

whichever occurs earlier.

(ACTION 2) If the doubler ends -

one or two fastener rows beyond

a stringer fastener row: Repeat

PART 2: EXTERNAL LOWER

LOBE DOUBLER SURFACE

LFEC INSPECTION FOR SKIN

CRACKS in the area of the doubler.

(ACTION 2) If the doubler ends - -

three or more fastener rows beyond a stringer fastener row: No

more work is necessary in the

area of the doubler.

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ALERT ALERT
Group 1:

Table 4: Inspection and Repair of the Skin at the Lower Lobe Circumferential Splice at STA 2181 (Area

4)

Repeat Interval

(Not to Exceed)

Compliance Time (Whichever

Occurs Later)

Condition Action

Do PART 4: EXTERNAL LOW- Before further flight. -

ER LOBE SKIN SURFACE

HFEC INSPECTION FOR

CRACKS in affected areas.

CONDITION 5: NO

CORROSION FOUND

(ACTION 1) Do PART 5: RE- Before further flight. -

PAIR in areas where corrosion

was found.

CONDITION 6: ANY

CORROSION FOUND

(ACTION 2) Do PART 4: EXTER- Before further flight. -

NAL LOWER LOBE SKIN SURFACE HFEC INSPECTION FOR

CRACKS in affected areas

where no corrosion was found

or where corrosion was removed

by blending.

800 flight cycles

or 24 months,

whichever occurs earlier.

(ACTION 3) If a repair doubler -

installed in accordance with

PART 5: REPAIR ends on a

stringer fastener row: Repeat

PART 2: EXTERNAL LOWER

LOBE DOUBLER SURFACE

LFEC INSPECTION FOR SKIN

CRACKS in the area of the doubler.

6,000 flight cycles or 48

months,

whichever occurs earlier.

(ACTION 3) If a repair doubler -

installed in accordance with

PART 5: REPAIR ends one or

two fastener rows beyond a

stringer fastener row: Repeat

PART 2: EXTERNAL LOWER

LOBE DOUBLER SURFACE

LFEC INSPECTION FOR SKIN

CRACKS in the area of the doubler.

(ACTION 3) If a repair doubler - -

installed in accordance with

PART 5: REPAIR ends three or

more fastener rows beyond a

stringer fastener row: No more

work is necessary in the area of

the repair.

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ALERT ALERT
Group 1:

Table 4: Inspection and Repair of the Skin at the Lower Lobe Circumferential Splice at STA 2181 (Area

4)

Repeat Interval

(Not to Exceed)

Compliance Time (Whichever

Occurs Later)

Condition Action

3,000 flight cycles or 24

months,

whichever occurs earlier.

Repeat PART 3: EXTERNAL -

LOWER LOBE SKIN SURFACE

LFEC INSPECTION FOR CORROSION and PART 4: EXTERNAL LOWER LOBE SKIN SURFACE HFEC INSPECTION FOR

CRACKS at all affected unrepaired areas. (a)

CONDITION 7: NO

CRACK FOUND

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ALERT ALERT
Group 1:

Table 4: Inspection and Repair of the Skin at the Lower Lobe Circumferential Splice at STA 2181 (Area

4)

Repeat Interval

(Not to Exceed)

Compliance Time (Whichever

Occurs Later)

Condition Action

(ACTION 1) Do PART 5: RE- Before further flight. -

PAIR.

CONDITION 8: ANY

CRACK FOUND

800 flight cycles

or 24 months,

whichever occurs earlier.

(ACTION 2) If a repair doubler -

installed in accordance with

PART 5: REPAIR ends on a

stringer fastener row: Repeat

PART 2: EXTERNAL LOWER

LOBE DOUBLER SURFACE

LFEC INSPECTION FOR SKIN

CRACKS in the area of the doubler.

6,000 flight cycles or 48

months,

whichever occurs earlier.

(ACTION 2) If a repair doubler -

installed in accordance with

PART 5: REPAIR ends one or

two fastener rows beyond a

stringer fastener row: Repeat

PART 2: EXTERNAL LOWER

LOBE DOUBLER SURFACE

LFEC INSPECTION FOR SKIN

CRACKS in the area of the doubler.

(ACTION 2) If a repair doubler - -

installed in accordance with

PART 5: REPAIR ends three or

more fastener rows beyond a

stringer fastener row: No more

work is necessary in the area of

the repair.

3,000 flight cycles or 24

months,

whichever occurs earlier.

(ACTION 3) Repeat PART 3: -

EXTERNAL LOWER LOBE

SKIN SURFACE LFEC INSPECTION FOR CORROSION and

PART 4: EXTERNAL LOWER

LOBE SKIN SURFACE HFEC

INSPECTION FOR CRACKS at

all affected unrepaired areas. (a)

(a) For the purposes of these inspections, "unrepaired areas" are defined as affected areas where the skin

is not covered with a doubler. Areas repaired with only blends or oversized fasteners should be treated

as unrepaired.

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ALERT ALERT
Group 2:

Table 5: Inspection and Repair of the Skin at the Lower Lobe Circumferential Splice at STA 1741 (Area

2)

Repeat Interval

(Not to Exceed)

Compliance Time (Whichever

Occurs Later)

Condition Action

Within 3,000 -

flight cycles or

24 months after

the original issue date of this

service bulletin,

whichever occurs first.

Before 10,000

total flight cycles, or within

10 years from

the date of issuance of the

original certificate of airworthiness or the original export certificate of airworthiness, whichever

occurs first.

Do external GVI of the fuselage

skin in Area 2 as shown in PART

1: INSPECTION AREAS for the

presence of repair doublers. (a)

All airplanes

Contact Boeing for inspection Before further flight. -

requirements and do the inspections.

CONDITION 9: ANY

EXISTING REPAIR

DOUBLER FOUND IN

THE AFFECTED AREAS

In Area 2A, do PART 3: EXTER- Before further flight. -

NAL LOWER LOBE SKIN SURFACE LFEC INSPECTION FOR

CORROSION.

CONDITION 10: AFFECTED AREAS WITH

NO EXISTING REPAIR

DOUBLER FOUND

In Area 2B, do PART 2: EXTER- Before further flight. -

NAL LOWER LOBE DOUBLER

SURFACE LFEC INSPECTION

FOR SKIN CRACKS (a)

In Area 2C, do PART 6: EXTER- Before further flight. -

NAL LOWER LOBE SKIN DETAILED INSPECTION FOR

CRACKS

3,000 flight cycles or 24

months,

whichever occurs earlier.

Repeat PART 2: EXTERNAL -

LOWER LOBE DOUBLER

SURFACE LFEC INSPECTION

FOR SKIN CRACKS (a)

CONDITION 3: NO

SKIN CRACK FOUND

UNDER EXTERNAL

DOUBLER In Area 2B

(ACTION 1) Do PART 5: RE- Before further flight. -

PAIR.

CONDITION 4: ANY

SKIN CRACK FOUND

UNDER EXTERNAL

DOUBLER In Area 2B 3,000 flight cycles or 24

months,

whichever occurs earlier.

Repeat PART 2: EXTERNAL -

LOWER LOBE DOUBLER

SURFACE LFEC INSPECTION

FOR SKIN CRACKS in unrepaired areas. (b)

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ALERT ALERT
Group 2:

Table 5: Inspection and Repair of the Skin at the Lower Lobe Circumferential Splice at STA 1741 (Area

2)

Repeat Interval

(Not to Exceed)

Compliance Time (Whichever

Occurs Later)

Condition Action

Do PART 4: EXTERNAL LOW- Before further flight. -

ER LOBE SKIN SURFACE

HFEC INSPECTION FOR

CRACKS

CONDITION 5: NO

CORROSION FOUND

In Area 2A

(ACTION 1) Do PART 5: RE- Before further flight. -

PAIR in areas where corrosion

was found.

CONDITION 6: ANY

CORROSION FOUND

In Area 2A

(ACTION 2) Do PART 4: EXTER- Before further flight. -

NAL LOWER LOBE SKIN SURFACE HFEC INSPECTION FOR

CRACKS in affected areas

where no corrosion was found

or where corrosion was removed

by blending.

6,000 flight cycles or 48

months,

whichever occurs earlier.

Repeat PART 3: EXTERNAL -

LOWER LOBE SKIN SURFACE

LFEC INSPECTION FOR CORROSION and PART 4: EXTERNAL LOWER LOBE SKIN SURFACE HFEC INSPECTION FOR

CRACKS in unrepaired areas of

Area 2A. (b)

CONDITION 7: NO

CRACK FOUND In

Area 2A

(ACTION 1) Do PART 5: RE- Before further flight. -

PAIR.

CONDITION 8: ANY

CRACK FOUND In

Area 2A 6,000 flight cycles or 48

months,

whichever occurs earlier.

(ACTION 2) Repeat PART 3: -

EXTERNAL LOWER LOBE

SKIN SURFACE LFEC INSPECTION FOR CORROSION and

PART 4: EXTERNAL LOWER

LOBE SKIN SURFACE HFEC

INSPECTION FOR CRACKS in

unrepaired areas of Area 2A. (b)

1,500 flight cycles or 24

months,

whichever occurs earlier.

Repeat PART 6: EXTERNAL -

LOWER LOBE SKIN DETAILED

INSPECTION FOR CRACKS in

unrepaired areas of Area 2C. (b)

CONDITION 11: NO

CRACK FOUND In

Area 2C

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ALERT ALERT
Group 2:

Table 5: Inspection and Repair of the Skin at the Lower Lobe Circumferential Splice at STA 1741 (Area

2)

Repeat Interval

(Not to Exceed)

Compliance Time (Whichever

Occurs Later)

Condition Action

(ACTION 1) Do PART 5: RE- Before further flight. -

PAIR.

CONDITION 12: ANY

CRACK FOUND In

Area 2C 1,500 flight cycles or 24

months,

whichever occurs earlier.

(ACTION 2) Repeat PART 6: -

EXTERNAL LOWER LOBE

SKIN DETAILED INSPECTION

FOR CRACKS in unrepaired areas of Area 2C. (b)

(a) An existing doubler installed during production covers all of the affected fuselage skin in Area 2B and

should not be considered a repair doubler.

(b) For the purposes of these inspections, "unrepaired areas" are defined as affected areas where the skin

is not covered with a repair doubler. Areas repaired with only blends or oversized fasteners should be

treated as unrepaired.

Group 2:

Table 6: Inspection and Repair of the Skin at the Lower Lobe Circumferential Splice at STA 1961 (Area

3)

Repeat Interval

(Not to Exceed)

Compliance Time (Whichever

Occurs Later)

Condition Action

Within 3,000 -

flight cycles or

24 months after

the original issue date of this

service bulletin,

whichever occurs first.

Before 10,000

total flight cycles, or within

10 years from

the date of issuance of the

original certificate of airworthiness or the original export certificate of airworthiness, whichever

occurs first.

Do external GVI of the fuselage

skin in Area 3 as shown in PART

1: INSPECTION AREAS for the

presence of external doublers.

All airplanes

Contact Boeing for inspection Before further flight. -

requirements and do the inspections.

CONDITION 9: ANY

EXISTING REPAIR

DOUBLER FOUND IN

THE AFFECTED AREAS

Do PART 3: EXTERNAL LOW- Before further flight. -

ER LOBE SKIN SURFACE

LFEC INSPECTION FOR CORROSION in affected areas.

CONDITION 10: AFFECTED AREAS WITH

NO EXISTING REPAIR

DOUBLER FOUND

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ALERT ALERT
Group 2:

Table 6: Inspection and Repair of the Skin at the Lower Lobe Circumferential Splice at STA 1961 (Area

3)

Repeat Interval

(Not to Exceed)

Compliance Time (Whichever

Occurs Later)

Condition Action

Do PART 4: EXTERNAL LOW- Before further flight. -

ER LOBE SKIN SURFACE

HFEC INSPECTION FOR

CRACKS in affected areas.

CONDITION 5: NO

CORROSION FOUND

(ACTION 1) Do PART 5: RE- Before further flight. -

PAIR in areas where corrosion

was found.

CONDITION 6: ANY

CORROSION FOUND

(ACTION 2) Do PART 4: EXTER- Before further flight. -

NAL LOWER LOBE SKIN SURFACE HFEC INSPECTION FOR

CRACKS in affected areas

where no corrosion was found

or where corrosion was removed

by blending.

6,000 flight cycles or 48

months,

whichever occurs earlier.

Repeat PART 3: EXTERNAL -

LOWER LOBE SKIN SURFACE

LFEC INSPECTION FOR CORROSION and PART 4: EXTERNAL LOWER LOBE SKIN SURFACE HFEC INSPECTION FOR

CRACKS at all affected unrepaired areas. (a)

CONDITION 7: NO

CRACK FOUND

(ACTION 1) Do PART 5: RE- Before further flight. -

PAIR.

CONDITION 8: ANY

CRACK FOUND

6,000 flight cycles or 48

months,

whichever occurs earlier.

(ACTION 2) Repeat PART 3: -

EXTERNAL LOWER LOBE

SKIN SURFACE LFEC INSPECTION FOR CORROSION and

PART 4: EXTERNAL LOWER

LOBE SKIN SURFACE HFEC

INSPECTION FOR CRACKS at

all affected unrepaired areas. (a)

(a) For the purposes of these inspections, "unrepaired areas" are defined as affected areas where the skin

is not covered with a doubler. Areas repaired with only blends or oversized fasteners should be treated

as unrepaired.

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ALERT ALERT
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.

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

Task Number of Persons Task Hours Elapsed Hours

External inspection 1 3.25 3.25

for doublers

External inspection 4 59.00 14.75

for corrosion

External inspection 4 59.00 14.75

for cracks

TOTAL FOR EACH AIRPLANE 121.25 32.75

NOTE: More time will be necessary for additional inspections if existing doublers are found. More

time will also be required for repairs if corrosion or cracks are found.

Group 2:

Table 2 - Inspection

Task Number of Persons Task Hours Elapsed Hours

External inspection 1 1.50 1.50

for doublers

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ALERT ALERT
Group 2:

Table 2 - Inspection

Task Number of Persons Task Hours Elapsed Hours

External inspection 4 42.00 10.50

for corrosion

External inspection 4 42.00 10.50

for cracks

TOTAL FOR EACH AIRPLANE 85.50 22.50

NOTE: More time will be necessary for additional inspections if existing doublers are found. More

time will also be required for repairs if corrosion or cracks are found.

H. Weight and Balance Changes

None.

I. Electrical Load Data

Not changed.

J. References

1. Existing Data:

a. Boeing Service Related Problem (SRP) 747-SRP-53-0392

b. Service Bulletin Index D6-30300

c. 747 Non-Destructive Testing (NDT) Manual Part 6, 51-00-00, Part 6, 53-30-03

d. 747-100/200/300 Structural Repair Manual (SRM) 53-30-03

e. 747-400 Structural Repair Manual (SRM) 53-00-01

f. 747-400F Structural Repair Manual (SRM) 53-00-01

g. 747-400SF Structural Repair Manual (SRM) 53-00-01

h. 747-SP Structural Repair Manual (SRM) 53-39-01

2. Data Supplied with this Service Bulletin:

None.

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

None.

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ALERT ALERT
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. DTI requirements for the structure affected

are contained in Paragraph 1.E., Compliance of this service bulletin.

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 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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ALERT ALERT

BLANK PAGE
3. ACCOMPLISHMENT INSTRUCTIONS

A. GENERAL INFORMATION

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 747 Structural Repair Manual,

Chapter 51.

— Values for airframe maintenance tasks are included in Chapter 20 of 747

Airplane Maintenance Manual (AMM).

— Values for electrical maintenance tasks are included in Chapter 20 of

Standard Wiring Practices Manual (SWPM).

— Values for engine maintenance tasks are included in Chapter 70 of 747

Airplane Maintenance Manual (AMM).

— Non-standard torque values for maintenance tasks are included in the

applicable installation step.

4. Use the approved fastener and process material substitutions in accordance with

SRM Chapter 51.

5. 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.

6. 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.

7. 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.

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ALERT ALERT
8. 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.

9. 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.

10. If shading is used, shaded areas in Figures are to separate the non-critical and

non-authoritative information from the critical and authoritative information.

11. When more than one OPTION is given for a CONDITION, do only one of the OPTION

numbers. When more than one ACTION is given for a CONDITION number or an

OPTION number, do all of the ACTION numbers for that CONDITION number or

OPTION number.

12. The compliance times for the actions in Paragraph 3.B., WORK INSTRUCTIONS

are in Paragraph 1.E., Compliance.

13. The CONDITIONS, ACTIONS and OPTIONS shown apply to each affected skin joint

independently.

14. Refer to APPENDIX A and APPENDIX B for logic diagrams. Logic diagrams are

provided as an aid only. Information contained in Paragraph 1.E., Compliance is the

primary source for compliance times. Information in Paragraph 3.B., Work Instructions

is the primary source for tasks required for compliance.

15. Refer to APPENDIX C and APPENDIX D for data about the affected skin panels.

This information may be helpful in accomplishing the necessary inspections.

16. 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.

17. Paragraph 3.B., Work Instructions, PART 1, shows the applicable general areas to

be inspected. In any given inspection area, do the described inspections only along

the rows of fasteners common to the skin, doubler (if installed), and stringers.

18. 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
B. WORK INSTRUCTIONS

Group 1:

1. Do external General Visual Inspections of the fuselage skin in the affected areas shown in PART

1: INSPECTION AREAS for the presence of external repair doublers.

a. CONDITION 1: ANY EXISTING EXTERNAL DOUBLER FOUND IN THE AFFECTED AREAS

(1) Do PART 2: EXTERNAL LOWER LOBE DOUBLER SURFACE LFEC INSPECTION FOR

SKIN CRACKS in the area of the doubler. Determine if the doubler ends on a row of

fasteners common to a stringer.

NOTE: Refer to CONDITION 2 for actions in affected areas that are not covered by a

doubler.

(a) CONDITION 3: NO SKIN CRACK FOUND UNDER EXTERNAL DOUBLER

1) Repeat PART 2: EXTERNAL LOWER LOBE DOUBLER SURFACE LFEC

INSPECTION FOR SKIN CRACKS in the area of the doubler.

(b) CONDITION 4: ANY SKIN CRACK FOUND UNDER EXTERNAL DOUBLER

1) (ACTION 1) Do PART 5: REPAIR.

2) (ACTION 2) Repeat PART 2: EXTERNAL LOWER LOBE DOUBLER SURFACE

LFEC INSPECTION FOR SKIN CRACKS in the area of the doubler.

NOTE: If any doubler ends three or more fastener rows beyond a row of

fasteners common to a stringer, no more inspections of that doubler

are necessary.

b. CONDITION 2: AFFECTED AREAS WITH NO EXISTING EXTERNAL DOUBLER FOUND

(1) Do PART 3: EXTERNAL LOWER LOBE SKIN SURFACE LFEC INSPECTION FOR

CORROSION in affected areas.

(a) CONDITION 5: NO CORROSION FOUND

1) Do PART 4: EXTERNAL LOWER LOBE SKIN SURFACE HFEC INSPECTION

FOR CRACKS in affected areas.

a) CONDITION 7: NO CRACK FOUND

{1} Repeat PART 3: EXTERNAL LOWER LOBE SKIN SURFACE LFEC

INSPECTION FOR CORROSION and PART 4: EXTERNAL LOWER

LOBE SKIN SURFACE HFEC INSPECTION FOR CRACKS in affected

unrepaired areas.

b) CONDITION 8: ANY CRACK FOUND

{1} (ACTION 1) Do PART 5: REPAIR.

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ALERT ALERT
{2} (ACTION 2) Repeat PART 3: EXTERNAL LOWER LOBE SKIN

SURFACE LFEC INSPECTION FOR CORROSION and PART 4:

EXTERNAL LOWER LOBE SKIN SURFACE HFEC INSPECTION FOR

CRACKS at all affected unrepaired areas.

(b) CONDITION 6: ANY CORROSION FOUND

1) (ACTION 1) Do PART 5: REPAIR in areas where corrosion was found.

2) (ACTION 2) Do PART 4: EXTERNAL LOWER LOBE SKIN SURFACE HFEC

INSPECTION FOR CRACKS in affected areas where no corrosion was found

or where corrosion was removed by blending.

a) CONDITION 7: NO CRACK FOUND

{1} Repeat PART 3: EXTERNAL LOWER LOBE SKIN SURFACE LFEC

INSPECTION FOR CORROSION and PART 4: EXTERNAL LOWER

LOBE SKIN SURFACE HFEC INSPECTION FOR CRACKS at all

affected unrepaired areas.

b) CONDITION 8: ANY CRACK FOUND

{1} (ACTION 1) Do PART 5: REPAIR.

{2} (ACTION 2) If a repair doubler was installed in accordance with PART

5: REPAIR, repeat PART 2: EXTERNAL LOWER LOBE DOUBLER

SURFACE LFEC INSPECTION FOR SKIN CRACKS in the area of the

doubler.

{3} (ACTION 3) Repeat PART 3: EXTERNAL LOWER LOBE SKIN

SURFACE LFEC INSPECTION FOR CORROSION and PART 4:

EXTERNAL LOWER LOBE SKIN SURFACE HFEC INSPECTION FOR

CRACKS at all affected unrepaired areas.

3) (ACTION 3) If a repair doubler was installed in accordance with PART 5: REPAIR,

repeat PART 2: EXTERNAL LOWER LOBE DOUBLER SURFACE LFEC

INSPECTION FOR SKIN CRACKS in the area of the doubler.

2. Put the airplane back to a serviceable condition.

Group 2:

1. Remove wing-to-body fairing panels for access to the lower body skin near STA 1741. Refer to

FIGURE 7 as an accepted procedure.

2. Do external General Visual Inspections of the fuselage skin in the affected areas shown in PART

1: INSPECTION AREAS for the presence of external repair doublers.

NOTE: An existing doubler installed during production covers all of the affected fuselage skin in

Area 2B.

a. CONDITION 9: ANY EXISTING REPAIR DOUBLER FOUND IN THE AFFECTED AREAS

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ALERT ALERT
(1) Contact Boeing for inspection requirements, and do the inspections.

b. CONDITION 10: AFFECTED AREAS WITH NO EXISTING REPAIR DOUBLER FOUND

(1) Do the inspections that follow:

(a) In Area 2A and Area 3, do PART 3: EXTERNAL LOWER LOBE SKIN SURFACE

LFEC INSPECTION FOR CORROSION.

(b) In Area 2B, do PART 2: EXTERNAL LOWER LOBE DOUBLER SURFACE LFEC

INSPECTION FOR SKIN CRACKS.

(c) In Area 2C, do PART 6: EXTERNAL LOWER LOBE SKIN DETAILED INSPECTION

FOR CRACKS.

c. CONDITION 3: NO SKIN CRACK FOUND UNDER EXTERNAL DOUBLER

(1) In Area 2B, repeat PART 2: EXTERNAL LOWER LOBE DOUBLER SURFACE LFEC

INSPECTION FOR SKIN CRACKS in the area of the doubler.

d. CONDITION 4: ANY SKIN CRACK FOUND UNDER EXTERNAL DOUBLER

(1) (ACTION 1) In Area 2B, do PART 5: REPAIR.

(2) (ACTION 2) In Area 2B, repeat PART 2: EXTERNAL LOWER LOBE DOUBLER SURFACE

LFEC INSPECTION FOR SKIN CRACKS in the area of the doubler.

e. CONDITION 5: NO CORROSION FOUND

(1) In Area 2A and Area 3, do PART 4: EXTERNAL LOWER LOBE SKIN SURFACE HFEC

INSPECTION FOR CRACKS in affected areas.

(a) CONDITION 7: NO CRACK FOUND

1) In Area 2A and Area 3, repeat PART 3: EXTERNAL LOWER LOBE SKIN

SURFACE LFEC INSPECTION FOR CORROSION and PART 4: EXTERNAL

LOWER LOBE SKIN SURFACE HFEC INSPECTION FOR CRACKS in affected

unrepaired areas.

(b) CONDITION 8: ANY CRACK FOUND

1) (ACTION 1) In Area 2A and Area 3, do PART 5: REPAIR.

2) (ACTION 2) In Area 2A and Area 3, repeat PART 3: EXTERNAL LOWER LOBE

SKIN SURFACE LFEC INSPECTION FOR CORROSION and PART 4:

EXTERNAL LOWER LOBE SKIN SURFACE HFEC INSPECTION FOR CRACKS

at all affected unrepaired areas.

f. CONDITION 6: ANY CORROSION FOUND

(1) (ACTION 1) In Area 2A and Area 3, do PART 5: REPAIR in areas where corrosion was

found.

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ALERT ALERT
(2) (ACTION 2) In Area 2A and Area 3, do PART 4: EXTERNAL LOWER LOBE SKIN

SURFACE HFEC INSPECTION FOR CRACKS in affected areas where no corrosion

was found or where corrosion was removed by blending.

(a) CONDITION 7: NO CRACK FOUND

1) In Area 2A and Area 3, repeat PART 3: EXTERNAL LOWER LOBE SKIN

SURFACE LFEC INSPECTION FOR CORROSION and PART 4: EXTERNAL

LOWER LOBE SKIN SURFACE HFEC INSPECTION FOR CRACKS at all

affected unrepaired areas.

(b) CONDITION 8: ANY CRACK FOUND

1) (ACTION 1) In Area 2A and Area 3, do PART 5: REPAIR.

2) (ACTION 2) In Area 2A and Area 3, repeat PART 3: EXTERNAL LOWER LOBE

SKIN SURFACE LFEC INSPECTION FOR CORROSION and PART 4:

EXTERNAL LOWER LOBE SKIN SURFACE HFEC INSPECTION FOR CRACKS

at all affected unrepaired areas.

g. CONDITION 11: NO CRACK FOUND

(1) In Area 2C, repeat PART 6: EXTERNAL LOWER LOBE SKIN DETAILED INSPECTION

FOR CRACKS.

h. CONDITION 12: ANY CRACK FOUND

(1) (ACTION 1) In Area 2C, do PART 5: REPAIR.

(2) (ACTION 2) In Area 2C, repeat PART 6: EXTERNAL LOWER LOBE SKIN DETAILED

INSPECTION FOR CRACKS at all affected unrepaired areas.

3. Install wing-to-body fairing panels that were removed for access to the lower body skin near STA

1741. Refer to FIGURE 8 as an accepted procedure.

4. Put the airplane back to a serviceable condition.

PART 1: INSPECTION AREAS

1. Group 1:

a. STA 741 (Area 1) is shown in FIGURE 1. Area 1 extends from STA 720 to STA 760, along

stringers S-45, S-46 and S-47.

b. STA 1741 (Area 2) is shown in FIGURE 2. Area 2 extends from STA 1720 to STA 1760, along

stringers S-42, S-43, S-44 and S-45.

c. STA 1961 (Area 3) is shown in FIGURE 3. Area 3 extends from STA 1961 to STA 1980, along

stringers S-47, S-48, S-49, S-50 and S-51.

d. STA 2181 (Area 4) is shown in FIGURE 4. Area 4 extends from STA 2160 to STA 2200, along

stringers S-47, S-48, S-49, S-50 and S-51.

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ALERT ALERT
2. Group 2:

a. STA 1741 (Area 2) is shown in FIGURE 5.

– Area 2A extends from STA 1720 to STA 1741, along stringers S-42, S-43, S-44 and S-45.

– Area 2B extends from STA 1741 to STA 1760, along stringers S-42, S-43, S-44 and S-45.

– Area 2C extends from STA 1720 to STA 1741, along stringers S-47, S-48, S-49, S-50

and S-51.

b. STA 1961 (Area 3) is shown in FIGURE 6. Area 3 extends from STA 1961 to STA 1980, along

stringers S-47, S-48, S-49, S-50 and S-51.

PART 2: EXTERNAL LOWER LOBE DOUBLER SURFACE LFEC INSPECTION FOR SKIN CRACKS

1. RC - Do external surface LFEC inspections of the fuselage skin under repairs in affected areas

for cracks, in accordance with 747 NDT Manual Part 6, 51-00-00, Procedure 8.

PART 3: EXTERNAL LOWER LOBE SKIN SURFACE LFEC INSPECTION FOR CORROSION

1. RC - Do external surface LFEC inspections of the skin in affected areas for corrosion that may

exist between the skin inner surface and the stringer, in accordance with 747 NDT Manual Part

6, 51-00-00, Procedure 5 or Procedure 12.

PART 4: EXTERNAL LOWER LOBE SKIN SURFACE HFEC INSPECTION FOR CRACKS

1. RC - Do external surface HFEC inspections of the skin in affected areas (at fastener locations

common to the skin and stringers) for cracks, in accordance with 747 NDT Manual Part 6, 53-30-03

or 747 NDT Manual Part 6, 51-00-00, Procedure 4 or Procedure 23.

PART 5: REPAIR

1. RC - Repair any damage found in accordance with 747-100/200/300 SRM 53-30-03, 747-400

SRM 53-00-01, 747-400F SRM 53-00-01, 747-400SF SRM 53-00-01, or 747-SP SRM 53-39-01.

If the damage exceeds the limits given in the Structural Repair Manual, contact Boeing for repair

data and do the repair.

PART 6: EXTERNAL LOWER LOBE SKIN DETAILED INSPECTION FOR CRACKS

1. RC - Do external detailed inspections of the skin in affected areas (at fastener locations common

to the skin and stringers) for cracks.

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ALERT ALERT
This Figure applies only to: Group 1.

FIGURE 1: INSPECTION AREA 1 (STA 741)

(SHEET 1 OF 2)

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FIGURE 1: INSPECTION AREA 1 (STA 741)

(SHEET 2 OF 2)

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ALERT ALERT
This Figure applies only to: Group 1.

FIGURE 2: INSPECTION AREA 2 (STA 1741)

(SHEET 1 OF 2)

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FIGURE 2: INSPECTION AREA 2 (STA 1741)

(SHEET 2 OF 2)

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ALERT ALERT
This Figure applies only to: Group 1.

FIGURE 3: INSPECTION AREA 3 (STA 1961)

(SHEET 1 OF 2)

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FIGURE 3: INSPECTION AREA 3 (STA 1961)

(SHEET 2 OF 2)

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ALERT ALERT
This Figure applies only to: Group 1.

FIGURE 4: INSPECTION AREA 4 (STA 2181)

(SHEET 1 OF 2)

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FIGURE 4: INSPECTION AREA 4 (STA 2181)

(SHEET 2 OF 2)

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ALERT ALERT
This Figure applies only to: Group 2.

FIGURE 5: INSPECTION AREA 2 (STA 1741)

(SHEET 1 OF 2)

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FIGURE 5: INSPECTION AREA 2 (STA 1741)

(SHEET 2 OF 2)

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ALERT ALERT
This Figure applies only to: Group 2.

FIGURE 6: INSPECTION AREA 3 (STA 1961)

(SHEET 1 OF 2)

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FIGURE 6: INSPECTION AREA 3 (STA 1961)

(SHEET 2 OF 2)

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ALERT ALERT
This Figure applies only to: Group 2.

FIGURE 7: WING TO BODY FAIRING PANEL REMOVAL

(SHEET 1 OF 2)

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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 each airplane.

Step Task Name Identification Qty More Data

Wing-to-Body Fairing - 8 (a) (b)

Panel

1 Remove / Keep

(a) 193C, 193D, 293D and 293E on the left side.

(b) 194C, 194D, 294D and 294E on the right side.

FIGURE 7: WING TO BODY FAIRING PANEL REMOVAL

(SHEET 2 OF 2)

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This Figure applies only to: Group 2.

FIGURE 8: WING TO BODY FAIRING PANEL INSTALLATION

(SHEET 1 OF 2)

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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 each airplane.

Step Task Name Identification Qty More Data

Wing-to-Body Fairing - 8 (a) (b)

Panel

1 Install (Kept)

(a) 193C, 193D, 293D and 293E on the left side.

(b) 194C, 194D, 294D and 294E on the right side.

FIGURE 8: WING TO BODY FAIRING PANEL INSTALLATION

(SHEET 2 OF 2)

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ALERT ALERT
APPENDIX A: LOGIC DIAGRAM - GROUP 1

(SHEET 1 OF 2)

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APPENDIX A: LOGIC DIAGRAM - GROUP 1

(SHEET 2 OF 2)

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APPENDIX B: LOGIC DIAGRAM - GROUP 2

(SHEET 1 OF 3)

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APPENDIX B: LOGIC DIAGRAM - GROUP 2

(SHEET 2 OF 3)

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APPENDIX B: LOGIC DIAGRAM - GROUP 2

(SHEET 3 OF 3)

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ALERT ALERT
This Appendix applies only to: Group 1.

Table 1 - Area 1 Skin Panel Data

Thickness Skin Panel Type Effectivity

(inches)

Location Part Number

R0351-R0381, R1073-R1261, R1262-

R1267, R1513-R1519, R1544-R1620,

R1621-R1629, R4009-R4009, R4103-

R4107, R4108-R4108, R6009-R6016,

R6103-R6143, R6144-R6153, R6154-

R6157

STA 720-741, 65B04107-2 0.062 Solid with no taper

S-45L - S-45R

R2001-R2005, R2006-R2015, R2016-

R2027, R2028-R2055, R2401-R2414,

R2415-R2425, R2426-R2478, R2479-

R2533, R2534-R2721, R2901-R2902,

R2903-R2920

65B04107-26 0.063

R2722-R2726, R6601-R6654, R6655-

R6715, R7001-R7002, R7003-R7006,

R7201-R7206

142U3280-1/-11

142U3013-1 Machined with no taper R6501-R6518

R7101-R7110, R7111-R7134, R7135-

R7199, R7251-R7299

142U3281-1/-11

65B04313-2, All affected airplanes

142U3282-1/-2 /-

11/-12/-13/-14 /-

15

STA 741-760,

S-45L - S-45R

Table 2 - Area 2 Skin Panel Data

Thickness Skin Panel Type Effectivity

(inches)

Location Part Number

Machined with taper All affected airplanes

(refer to drawing)

Taper from

0.071 to

0.17

65B04488-7/-8 /-

9/-10/-21/-22 /-

23/-24/-29/-30 /-

31/-32

STA 1720-

1741, S-42L/R

- S-45L/R

65B04141-2/-5, 0.063 Solid with no taper All affected airplanes

146U3275-1/-2,

146U3271-3

STA 1741-

1760, S-42L -

S-45L

APPENDIX C: GROUP 1 SKIN PANEL DATA

(SHEET 1 OF 2)

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Table 2 - Area 2 Skin Panel Data

Thickness Skin Panel Type Effectivity

(inches)

Location Part Number

Bonded with 0.04 inter- All affected airplanes

nal doubler

65B07002-8, 0.08

65B23792-1/-2 /-

5/-6/-17/-19/-20

STA 1741-

1760, S-42R -

S-43R

STA 1741- Chem Milled

1760, S-44R -

S-45R

Table 3 - Area 3 Skin Panel Data

Thickness Skin Panel Type Effectivity

(inches)

Location Part Number

chem milled with no ta- All affected airplanes

per

146U3292-2/-4/- 0.10

7, 146U3293-2,

65B20264-1/-2

STA 1961-1980,

S-47L - S-47R

Table 4 - Area 4 Skin Panel Data

Thickness Skin Panel Type Effectivity

(inches)

Location Part Number

chem milled with no ta- All affected airplanes

per

65B20264-1/-2, 0.10

146U3292-2/-4/-

7, 146U3293-2

STA 2160-2181,

S-47L - S-47R

65B06801-1/-4, 0.103 Machined with no taper All affected airplanes

146U3282-5/-6/-

7

STA 2181-2200,

S-47L - S-47R

APPENDIX C: GROUP 1 SKIN PANEL DATA

(SHEET 2 OF 2)

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ALERT ALERT
This Appendix applies only to: Group 2.

Thickness Skin Panel Type Effectivity

(inches)

Inspection Area Part Number

2A 65B18643-1/-2 0.09 Solid with no taper All affected airplanes

Solid; no taper; 0.032 All affected airplanes

inch external Doubler

2B (S-42L - S-45L) 65B04141-326 0.062

R3019-R3021, R3301-

R3301

2B (S-42R - S-43R) 65B07002-8 0.08 Solid; no taper

Solid; no taper; 0.04 inch

internal Doubler

2B (S-44R - S-45R) 65B07002-8 0.12

R3022-R3035, R3302-

R3310

2B (S-42R - S-45R) 65B23792-1 0.16 Chem-milled, no taper

Machined with taper (re- All affected airplanes

fer to drawing)

Taper from 0.11

to 0.183

2C 65B19098-1

3 65B19633-1 0.09 Chem-milled All affected airplanes

APPENDIX D: GROUP 2 (747SP) SKIN PANEL DATA

(SHEET 1 OF 1)

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ALERT ALERT