Commercial 

Airplanes 747

Service Bulletin

ALERT

Number: 747-53A2494

Original Issue: September 18, 2003

Revision 1: January 09, 2015

ATA System: 5312

SUBJECT: FUSELAGE - Section 46 - Body Station 2231 Frame Inner Chord Crack Inspection and

Repair

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 © 2003 Boeing.

Unpublished Work. All Rights Reserved.

Treatment of this document and its content is governed by contract with Boeing. Rights to use this document

are licensed on a per aircraft basis and such rights may not be transferable. For more information, contact The

Boeing Company.

Boeing, the Boeing signature, the Boeing symbol, 707, 717, 727, 737, 747, 757, 767, 777, 787, Dreamliner,

BBJ, DC-8, DC-9, DC-10, KC-10, KC-46, KDC-10, MD-10, MD-11, MD-80, MD-88, MD-90, P-8, Poseidon and

Boeing liveries are all trademarks owned by The Boeing Company; and no trademark license is granted in

connection with this document unless provided in writing by Boeing.

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BOEING SERVICE BULLETIN 747-53A2494

ALERT ALERT

BLANK PAGE
Table of Contents

Revision Transmittal Sheet ............................................ 5

Summary ...................................................... 7

1. PLANNING INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11

A. Effectivity . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11

1. Airplanes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11

2. Spares Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20

B. Concurrent Requirements . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20

C. Reason . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20

D. Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21

E. Compliance . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 22

F. Approval . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 24

G. Manpower . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25

H. Weight and Balance Changes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 27

I. Electrical Load Data . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 27

J. References . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 27

1. Existing Data: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 27

2. Data Supplied with this Service Bulletin: . . . . . . . . . . . . . . . . . . . . . . . . . . . 27

3. Installation Drawings Used in the Preparation of this Service Bulletin: . . . . . . . . . . . 27

K. Publications Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 27

L. Interchangeability and Intermixability of Parts . . . . . . . . . . . . . . . . . . . . . . . . . . . 28

M. Software Accomplishment Summary . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 28

2. MATERIAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 29

A. Material - Price and Availability . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 29

B. Industry Support Information . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 29

C. Parts Necessary for Each Airplane . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 29

1. Kits/Parts: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 29

2. Parts and Materials Supplied by the Operator: . . . . . . . . . . . . . . . . . . . . . . . . 29

3. Parts Modified and Reidentified: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 29

4. Parts Removed and Not Replaced: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 29

D. Parts Necessary to Change Spares . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 29

E. Special Tooling - Price and Availability . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 29

F. Special Tooling Necessary to do this Service Bulletin . . . . . . . . . . . . . . . . . . . . . . . 29

3. ACCOMPLISHMENT INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 31

A. GENERAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 31

B. WORK INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 32

FIGURE 1: THIS FIGURE IS DELETED . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 35

FIGURE 2: ACCESS / RESTORATION FOR CONFIGURATION WITH PASSENGERS IN THE AFT BODY

[Group 1, 3] . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 36

FIGURE 3: ACCESS / RESTORATION FOR CONFIGURATION WITH CARGO IN THE AFT BODY [Group

2, 4] . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 38

FIGURE 4: INSPECTION [Group 1-4, Configuration 1] . . . . . . . . . . . . . . . . . . . . . . . . . . 40

FIGURE 5: HFEC INSPECTION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 43

APPENDIX A: LOGIC DIAGRAM [Group 1-4, Configuration 1] . . . . . . . . . . . . . . . . . . . . . . . . 46

APPENDIX B: LOGIC DIAGRAM [Group 1-4, Configuration 2] . . . . . . . . . . . . . . . . . . . . . . . . 48

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BLANK PAGE
Commercial 

Airplanes 747

Service Bulletin

ALERT

Revision Transmittal Sheet Number: 747-53A2494

Original Issue: September 18, 2003

Revision 1: January 09, 2015

ATA System: 5312

SUBJECT: FUSELAGE - Section 46 - Body Station 2231 Frame Inner Chord Crack Inspection and

Repair

This revision includes all pages of the service bulletin.

COMPLIANCE INFORMATION RELATED TO THIS REVISION

More work is necessary on the airplane(s) changed or inspected in accordance with the original issue of this

service bulletin. Do HFEC initial inspection and repeat inspections in accordance with this revision.

Airplanes RT631-RT632, RT743 and RT876, which have been modified to the 747 Large Cargo Freighter (LCF)

configuration, have been removed from the effectivity of this service bulletin.

Federal Aviation Administration (FAA) Airworthiness Directive AD 2005-01-09 is related to this service bulletin.

REASON FOR REVISION

This revision is sent to include HFEC initial inspection and repeat inspections for the Body Station (STA) 2231

Frame Inner Chord. This revision is also sent to include new SRM repairs. The inspections in this service bulletin

are similar to the inspections in Boeing Service Bulletin 747-53A2450 R07, which begin before 16,000 total flight

cycles.

These sections were changed:

1. In the Background paragraph in the Summary section, changed to include new work, SRP references

and planning data table.

2. In the Action paragraph in the Summary section, changed to include new work.

3. In the Effectivity paragraph in the Summary section, changed to better describe affected airplanes.

4. In the Compliance paragraph in the Summary section, updated to direct to Paragraph 1.E..

5. Summary illustration updated to include new work.

6. In Paragraph 1.A., Effectivity, airplanes RT631, RT632, RT743, and RT876 have been removed from

the effectivity, and Group configurations added to the table.

7. In Paragraph 1.C., Reason, changed to include new work and added new paragraphs describing the

reason for revision.

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8. In Paragraph 1.D., Description, updated work summary, added reason for revision and maintenance

zone data.

9. In Paragraph 1.E., Compliance, added Airworthiness Directive statement and new compliance information

in tabular format.

10. In Paragraph 1.F., Approval, updated approval statement and added new Airworthiness Directive

statement.

11. In Paragraph 1.G., Manpower, added new manpower tables for repeat inspections.

12. In Paragraph 1.J., References, added new SRP and AD references.

13. In Paragraph 1.K., Publications Affected, a Damage Tolerance statement was added.

14. In Paragraph 2.B., Industry Support Information, revised the statement.

15. In Paragraph 3.B., Work Instructions, updated to include new general information and new inspections.

16. FIGURE 1 was deleted and Logic Diagram moved to Appendix A and Appendix B.

17. In FIGURE 2, added group information.

18. In FIGURE 3, added group information.

19. In FIGURE 4, added group information, changed sheet 2 and step table.

20. FIGURE 5 was added for HFEC Inspection.

21. APPENDIX A and APPENDIX B were added to include new Logic Diagrams.

Vertical lines are put on the left edge of each page, except in Paragraph 1.A., Effectivity and format changes,

to show the location of all content changes.

Pages with no vertical lines have no changes.

REVISION HISTORY

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BOEING SERVICE BULLETIN 747-53A2494

ALERT ALERT
Commercial 

Airplanes 747

Service Bulletin

ALERT

Summary Number: 747-53A2494

Original Issue: September 18, 2003

Revision 1: January 09, 2015

ATA System: 5312

SUBJECT: FUSELAGE - Section 46 - Body Station 2231 Frame Inner Chord Crack Inspection and

Repair

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

Accomplishment of this service bulletin will make sure that the body frame at station 2231 at stringer 26 does

not have any nicks, scratches, and / or gouges, and has no cracks. Cracks can initiate at nicks, scratches, and

/ or gouges. If not repaired, cracks could result in damage to the adjacent structure which could result in rapid

depressurization of the airplane.

The body frame at station 2231 is forward of the number 5 main entry door opening. The door 5 lower main sill

goes through a cutout in the station 2231 frame at stringer 26. Boeing investigation indicates that during production,

the door lower main sill chord can rub the station 2231 frame. If the sill rubs the frame, nicks, scratches, and /

or gouges in the frame inner chord can occur which can cause frame cracks. Cracks in the inner chords and

web at this location could extend with continued operation and fully cut the frame. If the frame becomes fully

cut, skin cracks could occur which could cause a rapid depressurization of the airplane.

One operator has reported cracked inner chords (forward and aft) and a cracked web at station 2231 and stringer

26L. Refer to Paragraph 1.C., Reason, for a detailed service history.

Airplane line numbers 1334 and on were delivered with additional checks to ensure no nicks, scratches, and/or

gouges were added during the production process.

Inspections accomplished in accordance with Service Bulletin 747-53A2450 R07 are an acceptable substitute

for the inspections specified in this service bulletin. Airplane line numbers 1-1419, except 747SP and 747-400

LCF, are affected by Service bulletin 747-53A2450 R07 .

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

Paragraph 1.E., Compliance and Paragraph

1.F., Approval

AD Related Yes

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

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

Publications Affected No Paragraph 1.K., Publications Affected

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

Operations Manual and/or FAA Approved Airplane Flight Manual)

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

Boeing Service Related Problems (SRP) 747-SRP-53-0202 and 747-SRP-53-0452 are related to this service

bulletin.

ACTION

Do a detailed inspection for nicks, scratches, and / or gouges of the station 2231 frame inner chords (forward

and aft), and web, at stringer 26 at the edge and side of the inner chords and do a surface High Frequency Eddy

Current (HFEC) inspection of the Station 2231 frame inner chords (forward and aft), for cracks. If any nicks,

scratches, and / or gouges are found, repair in accordance with the Structural Repair Manual (SRM) before next

flight. If cracks are found do a repair in accordance with the SRM, or contact Boeing for repair instructions,

before further flight. Repeat the HFEC inspection for cracks in accordance with Paragraph 1.E., Compliance.

EFFECTIVITY

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

and 747SR Airplane(s). Refer to Paragraph 1.A.1., Airplanes, for the list of affected airplane(s).

COMPLIANCE

Refer to Paragraph 1.E., Compliance.

INDUSTRY SUPPORT INFORMATION

Boeing warranty remedies are available for airplanes in warranty as of November 22, 2002. Please refer to

Paragraph 2.B., Industry Support Information.

MANPOWER

Airplanes Total Task Hours Elapsed Hours

Groups 1 and 3 4 3

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Airplanes Total Task Hours Elapsed Hours

Groups 2 and 4 (with two MED #5) 4 3

Groups 2 and 4 (with one MED #5) 2 1.5

MATERIAL INFORMATION

None.

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Commercial 

Airplanes 747

Service Bulletin

ALERT

Number: 747-53A2494

Original Issue: September 18, 2003

Revision 1: January 09, 2015

ATA System: 5312

SUBJECT: FUSELAGE - Section 46 - Body Station 2231 Frame Inner Chord Crack Inspection and

Repair

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

This service bulletin is applicable to 747-100, -100B, -100B SUD, -200B, -200C, -200F, -300, -400,

-400D, -400F and 747SR Airplanes, line numbers 1-1333, except 747 Large Cargo Freighter (LCF)

airplanes, in four Groups. The Variable Numbers and Group Information for the applicable airplanes

is given below.

Refer to Service Bulletin Index Document D6-30300 Part 3 for Airplane Variable Number, Line

Number, and Serial Number data.

GROUP CONFIGURATION DESCRIPTION

747-100, 747-100B, 747-100B SUD, 747-200B, 747-300, 747-400,

747-400D and 747SR airplanes, line number 1 through 1304, except

Combi, Special Freighter, Boeing Converted Freighter (BCF) and

747 Large Cargo Freighter (LCF) airplanes.

1 -

1 That have not completed the original issue of this service bulletin.

2 That have completed the original issue of this service bulletin.

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GROUP CONFIGURATION DESCRIPTION

747-200B, 747-200C, 747-200F, 747-300, 747-400 and 747-400F

Freighter, Convertible, Combi, Special Freighter, and BCF airplanes,

line number 1 through 1304.

2 -

1 That have not completed the original issue of this service bulletin.

2 That have completed the original issue of this service bulletin.

3 - 747-400 Passenger airplanes, from line number 1305 through 1333.

1 That have not completed the original issue of this service bulletin.

2 That have completed the original issue of this service bulletin

4 - 747-400F airplanes, from line number 1305 through 1333.

1 That have not completed the original issue of this service bulletin.

2 That have completed the original issue of this service bulletin

Airplane Models:

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

747-400D, 747-400F, 747SR

Variable Number Group

RA001 - RA034 1

RA101 - RA115 1

RA161 - RA164 1

RA201 - RA203 1

RA216 - RA217 1

RA245 - RA246 1

RA251 - RA266 1

RA301 - RA318 1

RA351 - RA360 1

RA369 - RA373 1

RA401 - RA418 1

RA501 - RA502 1

RA521 - RA528 1

RA532 - RA548 1

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Variable Number Group

RA551 - RA552 1

RA559 - RA561 1

RA581 - RA582 1

RA585 1

RA601 - RA602 1

RA631 - RA635 1

RA651 - RA652 1

RA671 - RA677 1

RA701 - RA702 1

RA721 - RA731 1

RA741 - RA745 1

RA749 - RA750 2

RA761 - RA762 1

RA781 - RA784 1

RA901 - RA916 1

RB001 - RB016 1

RB041 - RB044 1

RB071 - RB075 1

RB101 - RB102 1

RB411 - RB413 2

RB421 2

RB601 - RB607 1

RB681 - RB697 1

RB711 1

RB721 - RB723 1

RB741 - RB748 1

RD001 - RD004 1

RD021 - RD022 1

RD041 - RD059 1

RD071 - RD072 1

RD081 - RD083 1

RD091 - RD092 1

RD101 - RD104 1

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Variable Number Group

RD121 - RD127 1

RD131 - RD144 1

RD166 - RD167 1

RD171 - RD172 1

RD181 - RD183 1

RD201 - RD204 2

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

RD461 1

RD471 - RD475 1

RD513 - RD519 1

RD531 - RD533 2

RD551 2

RD561 2

RD571 2

RD581 - RD583 2

RD591 - RD593 2

RD601 - RD607 2

RD621 - RD623 2

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Variable Number Group

RD641 - RD649 2

RD651 - RD659 2

RD661 2

RD671 2

RD681 - RD682 2

RD691 - RD692 2

RD701 - RD702 2

RD721 - RD722 2

RD741 - RD742 2

RD751 - RD755 2

RD761 2

RD771 - RD775 2

RD781 - RD783 2

RD791 - RD792 2

RE001 1

RF001 - RF006 3

RJ131 - RJ133 2

RJ151 - RJ152 2

RJ301 - RJ303 2

RJ321 - RJ322 2

RJ331 - RJ333 2

RL401 - RL402 2

RL403 4

RL411 - RL419 2

RL420 - RL421 4

RL431 - RL432 4

RL651 - RL654 2

RL655 4

RL671 - RL673 4

RL681 - RL682 4

RL751 - RL752 4

RM001 - RM007 1

RM010 - RM013 1

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Variable Number Group

RM021 - RM024 1

RM026 - RM029 1

RM036 - RM045 1

RM051 - RM052 1

RM071 1

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 - RM402 3

RM426 3

RM801 - RM803 2

RM811 - RM813 2

RM851 - RM858 2

RM861 2

RM862 4

RM871 - RM876 2

RM877 - RM879 4

RM881 - RM886 2

RM887 4

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Variable Number Group

RM891 - RM899 2

RM901 - RM904 2

RM905 - RM906 4

RM911 2

RR001 - RR005 2

RR021 - RR025 2

RR031 2

RR201 - RR206 2

RR221 - RR226 2

RR261 - RR267 2

RR301 - RR310 2

RR331 - RR332 2

RR336 2

RR341 - RR345 2

RR361 - RR362 2

RR421 - RR422 2

RR431 - RR432 2

RR441 - RR442 2

RR451 2

RR501 - RR504 2

RR521 - RR522 2

RR526 2

RR531 2

RR551 - RR556 2

RR561 2

RR566 2

RR701 2

RR721 - RR724 2

RR746 - RR748 2

RR851 - RR856 2

RR861 - RR862 2

RR951 - RR952 2

RS001 - RS002 1

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ALERT ALERT
Variable Number Group

RS201 1

RS211 - RS212 1

RS221 - RS222 1

RS231 - RS241 1

RS251 - RS259 1

RS263 1

RS265 - RS268 1

RS271 - RS276 1

RS291 - RS292 1

RS301 - RS306 1

RS311 - RS320 1

RS331 - RS333 1

RS341 - RS342 1

RS699 1

RS701 - RS703 2

RS711 - RS713 2

RS721 - RS722 2

RS731 - RS732 2

RS741 - RS743 2

RS751 - RS752 2

RS761 - RS762 2

RS771 2

RS781 - RS782 2

RS786 2

RT001 - RT014 2

RT021 - RT022 2

RT031 - RT035 2

RT041 - RT047 2

RT061 2

RT071 - RT075 2

RT101 - RT103 2

RT121 2

RT131 - RT137 2

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Variable Number Group

RT151 - RT152 2

RT161 - RT168 2

RT401 - RT412 1

RT431 - RT447 1

RT451 - RT469 1

RT471 - RT499 1

RT501 - RT535 1

RT551 - RT568 1

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

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Variable Number Group

RU059 - RU062 1

RU081 - RU083 1

RU101 - RU102 1

RU121 - RU132 1

RU801 - RU809 1

RU831 - RU841 1

2. Spares Affected

None.

B. Concurrent Requirements

None.

C. Reason

Accomplishment of this service bulletin will make sure that the body frame at station 2231 at stringer

26 does not have any nicks, scratches, and / or gouges, and has no cracks. Cracks can initiate at nicks,

scratches, and / or gouges. If not repaired, cracks could result in damage to the adjacent structure

which could result in rapid depressurization of the airplane.

The body frame at station 2231 is forward of the number 5 main entry door opening. The door 5 lower

main sill goes through a cutout in the station 2231 frame at stringer 26. Boeing investigation indicates

that during production, the door lower main sill chord can rub the station 2231 frame. If the sill rubs the

frame, nicks, scratches, and / or gouges in the frame inner chord can occur which can cause frame

cracks. Cracks in the inner chords and web at this location could extend with continued operation and

fully cut the frame. If the frame becomes fully cut, skin cracks could occur which could cause a rapid

depressurization of the airplane.

One operator has reported cracked inner chords (forward and aft) and a cracked web at station 2231

and stringer 26L. The following table provides service history details.

Service History

Cycles / Hours Report

Both chords and web severed on BS 2231 Frame at

Stringer 26L

14,687 / 87,877

Between the release of the original issue and Revision 1 of this service bulletin, there have been further

reports of cracking in the inner chords at station 2231 and stringer 26 (left and right). The crack at this

location is also inspected in accordance with 747-53A2450 R07, which must begin before 16,000 flight

cycles. The following table provides the service history details of one of the reports provided between

the original issue and Revision 1.

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Service History

Cycles / Hours Report

0.25" crack on BS 2231 Frame inner chord at Stringer

26R

11,023 / 91,788

Airplane line numbers 1334 and on were delivered with additional checks to ensure no nicks, scratches,

and/or gouges were added during the production process.

Inspections accomplished in accordance with Service Bulletin 747-53A2450 Revision 7 are similar to

the inspections specified in this service bulletin. Airplane line numbers 1-1419, except 747SP and

747-400LCF, are affected by Service bulletin 747-53A2450 R07.

Revision 1 is sent to add a repeat surface High Frequency Eddy Current (HFEC) inspection of the

Station 2231 frame inner chord.

Boeing Service Related Problems (SRP) 747-SRP-53-0202 and 747-SRP-53-0452 are related to this

service bulletin.

D. Description

Do a detailed inspection for nicks, scratches, and / or gouges of the station 2231 frame inner chords

(forward and aft) at stringer 26 at the edge and side of the inner chords and do a surface High Frequency

Eddy Current (HFEC) inspection of the frame inner chords (forward and aft) for cracks. If any nicks,

scratches, and / or gouges are found, repair in accordance with the Structural Repair Manual (SRM)

before next flight. If cracks are found do a repair in accordance with the SRM, or contact Boeing for

repair instructions, before further flight. Repeat the HFEC inspection for cracks in accordance with

Paragraph 1.E., Compliance.

The airplane effectivity is divided into four groups because of access requirements.

Revision 1 - More work is necessary on airplanes changed or inspected in accordance with the original

issue of this service bulletin. Do HFEC initial inspection and repeat inspections in accordance with this

revision.

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

Group 1:

Affected Maintenance Zones

Model Zone

747-100, 747-100B, 747-100B 271, 272

SUD, 747-200B, 747-300, 747-

400, 747-400D, 747SR

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BOEING SERVICE BULLETIN 747-53A2494

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Group 2:

Affected Maintenance Zones

Model Zone

747-200B, 747-200C, 747-200F, 271, 272

747-300, 747-400, 747-400F

Group 3:

Affected Maintenance Zones

Model Zone

747-400 271, 272

Group 4:

Affected Maintenance Zones

Model Zone

747-400F 271, 272

E. Compliance

Federal Aviation Administration (FAA) Airworthiness Directive 2005-01-09 is related to this service

bulletin. The effective date of AD 2005-01-09 is February 11, 2005.

Group 1-4, Configuration 1:

Table 1: Station 2231 Frame Inner Chord - Detailed and HFEC Inspections

Repeat Interval

(Not to Exceed)

Compliance Time

(Whichever Occurs Later)

Condition Action

Within 1,500 -

flight cycles

after the effective date

of AD 2005-

01-09.

Before

10,000 total

flight cycles

Do a detailed inspection for nicks, scratches, or gouges of the

frame inner chords and

web in accordance with

Paragraph 3.B., Work

Instructions, Step 3 (a)

All airplanes.

AND

Within 1,500 -

flight cycles

after the release of Revision 1 of this

service bulletin.

Before

10,000 total

flight cycles.

Do a surface HFEC inspection of the frame

inner chords for cracks

in accordance with

Paragraph 3.B., Work

Instructions, Step 4. (a)

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ALERT ALERT
Group 1-4, Configuration 1:

Table 1: Station 2231 Frame Inner Chord - Detailed and HFEC Inspections

Repeat Interval

(Not to Exceed)

Compliance Time

(Whichever Occurs Later)

Condition Action

Before fur- - -

ther flight.

Repair in accordance

with Paragraph 3.B.,

Work Instructions, Step

5

Nicks, scratches or

gouges found and no

cracks found.

AND

3,000 flight cycles.Repeat the surface - -

HFEC inspection of the

frame inner chords for

cracks in accordance

with Paragraph 3.B.,

Work Instructions, Step

11. (a)

Before fur- - -

ther flight.

Repair in accordance

with Paragraph 3.B.,

Work Instructions, Step

7

Any crack found.

AND

3,000 flight cycles.Repeat the surface - -

HFEC inspection of the

frame inner chords for

cracks in accordance

with Paragraph 3.B.,

Work Instructions, Step

11. (b)

3,000 flight cycles.Repeat the surface - -

HFEC inspection of the

frame inner chords for

cracks in accordance

with Paragraph 3.B.,

Work Instructions, Step

11. (a)

No nicks, scratches or

gouges found and no

cracks found.

(a) Inspections accomplished in accordance with Service Bulletin 747-53A2450 Revision 7

are similar to the inspections specified in this service bulletin.

(b) For airplanes with inner chords repaired in accordance with Paragraph 3.B., Work Instructions Step 7, do the inspections in accordance with Paragraph 3.B., Work Instructions Step

11 for the chords that were not repaired.

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ALERT ALERT
Group 1-4, Configuration 2:

Table 2: Station 2231 Frame Inner Chord - HFEC Inspections

Repeat Interval

(Not to Exceed)

Compliance Time (Whichever

Occurs Later)

Condition Action

Within 1,500 -

flight cycles after the release

of Revision 1 of

this service bulletin.

Before 10,000

total flight cycles.

Do the surface HFEC inspection of the frame inner chords for cracks in

accordance with Paragraph 3.B., Work Instructions, Step 6. (a)

All airplanes.

Repair in accordance with Before further flight. -

Paragraph 3.B., Work Instructions, Step 7.

Any crack found.

AND

Repeat the surface HFEC - - 3,000 flight cycles.

inspection of the frame

inner chords for cracks in

accordance with Paragraph 3.B., Work Instructions, Step 11. (b)

Repeat the surface HFEC - - 3,000 flight cycles.

inspection of the frame

inner chords for cracks in

accordance with Paragraph 3.B., Work Instructions, Step 11. (a)

No crack found.

(a) Inspections accomplished in accordance with Service Bulletin 747-53A2450 Revision 7 are similar to the

inspections specified in this service bulletin.

(b) For airplanes with inner chords repaired in accordance with Paragraph 3.B., Work Instructions Step 7,

do the inspections in accordance with Paragraph 3.B., Work Instructions Step 11 for the chords that were

not repaired.

Logic diagrams showing compliance tasks and compliance times are included as an aid in Appendix

A and B.

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
The Manager of the FAA Seattle ACO approves the accomplishment of the inspection as defined by

Boeing SB 747-53A2494 Revision 1 as an AMOC to the accomplishment of the inspection as defined

by Boeing SB 747-53A2494 Original Issue required by paragraph (f) and (h) of AD 2005-01-09. All

provisions of AD 2005-01-09 that are not specifically referenced in the above statement remain fully

applicable and must be complied with accordingly.

G. Manpower

The tables below show estimates 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 examine the work

— Time to cure the materials

— Time to make the parts

— Time to find the tools.

GROUP 1 AND GROUP 3 AIRPLANES:

Number of Per- Task-Hours Elapsed Hours

sons

Task

Open Access 1 1 1

Inspection 2 2 1

Close Access 1 1 1

TOTAL FOR EACH AIRPLANE (a) 4 3

(a) Additional time may be required if repairs are accomplished.

GROUP 2 AND GROUP 4 AIRPLANES WITH ACTIVE OR INACTIVE MAIN

ENTRY DOOR 5 ON BOTH SIDES OF THE AIRPLANE:

Number of Per- Task-Hours Elapsed Hours

sons

Task

Open Access 1 1 1

Inspection 2 2 1

Close Access 1 1 1

TOTAL FOR EACH AIRPLANE (a) 4 3

(a) Additional time may be required if repairs are accomplished.

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GROUP 2 AND GROUP 4 AIRPLANES WITH ACTIVE OR INACTIVE MAIN

ENTRY DOOR 5 ON ONE SIDE OF THE AIRPLANE:

Number of Per- Task-Hours Elapsed Hours

sons

Task

Open Access 1 .5 .5

Inspection 2 1 .5

Close Access 1 .5 .5

TOTAL FOR EACH AIRPLANE (a) 2 1.5

(a) Additional time may be required if repairs are accomplished.

GROUP 1 AND GROUP 3 AIRPLANES:

Number of Per- Task-Hours Elapsed Hours

sons

Task

Open Access 1 1 1

Repeat Inspection 2 2 1

Close Access 1 1 1

TOTAL FOR EACH AIRPLANE (a) 4 3

(a) Additional time may be required if repairs are accomplished.

GROUP 2 AND GROUP 4 AIRPLANES WITH ACTIVE OR INACTIVE MAIN

ENTRY DOOR 5 ON BOTH SIDES OF THE AIRPLANE:

Number of Per- Task-Hours Elapsed Hours

sons

Task

Open Access 1 1 1

Repeat Inspection 2 2 1

Close Access 1 1 1

TOTAL FOR EACH AIRPLANE (a) 4 3

(a) Additional time may be required if repairs are accomplished.

GROUP 2 AND GROUP 4 AIRPLANES WITH ACTIVE OR INACTIVE MAIN

ENTRY DOOR 5 ON ONE SIDE OF THE AIRPLANE:

Number of Per- Task-Hours Elapsed Hours

sons

Task

Open Access 1 .5 .5

Repeat Inspection 2 1 .5

Close Access 1 .5 .5

TOTAL FOR EACH AIRPLANE (a) 2 1.5

(a) Additional time may be required if repairs are accomplished.

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H. Weight and Balance Changes

None.

I. Electrical Load Data

Not changed.

J. References

1. Existing Data:

a. Service Related Problem (SRP) 747-SRP-53-0202

b. Service Related Problem (SRP) 747-SRP-53-0452

c. 747-100/-200/-300 Maintenance Manual (AMM) Subjects 25-21-03, 25-21-04, 25-59-05

d. 747-400 Maintenance Manual (AMM) Subjects 25-21-03, 25-21-04

e. 747-100/-200/-300 Structural Repair Manual (SRM) Subjects 51-10-01, 53-10-04 Figure 147

f. 747-400 Structural Repair Manual (SRM) Subjects 51-10-00, 53-60-07 Repair 7

g. 747-400F Structural Repair Manual (SRM) Subject 53-60-07 Repair 7

h. 747-400SF Structural Repair Manual (SRM) Subject 53-60-07 Repair 7

i. 747 Nondestructive Test (NDT) Manual D6-7170, Part 6, Subject 51-00-00

j. Boeing Service Bulletin 747-53-2450

k. Federal Aviation Administration (FAA) Airworthiness Directive (AD) 2005-01-09, 2013-17-08

2. Data Supplied with this Service Bulletin:

None.

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

None.

K. Publications Affected

1. Publications:

None.

2. Damage Tolerance Based Structural Inspections:

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

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

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

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BOEING SERVICE BULLETIN 747-53A2494

ALERT ALERT
L. Interchangeability and Intermixability of Parts

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

M. Software Accomplishment Summary

Not affected.

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2. MATERIAL INFORMATION

A. Material - Price and Availability

None.

B. Industry Support Information

Boeing warranty remedies are available for the original issue Service Bulletin work statement for 747

airplanes in warranty as of November 22, 2002. For inspection man-hour reimbursement for airplanes

in warranty as of that date, send a warranty claim to BCA Fleet Support Contracts - Warranty. If the

condition described in this service bulletin is found during inspection for airplanes in warranty as of that

date and additional man hours are required, send a warranty claim to BCA Fleet Support Contracts -

Warranty. Please refer to this service bulletin number and reference the airplane variable numbers in

your purchase order.

Boeing warranty remedies are not available for the additional work statement described in Revision 1

of 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

– 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, process and material substitutions in accordance with

SRM Chapter 51.

5. A Detailed Inspection is defined as: An intensive examination of a specific item,

installation, or assembly to detect damage, failure, or irregularity. Available lighting

is normally supplemented with a direct source of good lighting at an intensity deemed

appropriate. Inspection aids such as mirrors, magnifying lenses, etc. may be

necessary. Surface cleaning and elaborate procedures may be required.

6. 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.

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7. 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.

8. Refer to Appendix A and 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.

9. 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.

10. 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.

11. 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.

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

are in Paragraph 1.E., Compliance.

13. Refinish bare metal areas to match surrounding area.

B. WORK INSTRUCTIONS

1. Airplanes configured to carry passengers in the aft body should use FIGURE 2 for access.

2. Airplanes configured to carry cargo in the aft body should use FIGURE 3 for access.

3. Group 1-4, Configuration 1:

Do a detailed inspection of the Station 2231 Frame Inner Chord (forward and aft) surfaces and

edge and web edge for nicks, scratches, or gouges in accordance with FIGURE 4.

4. Group 1-4, Configuration 1:

Do a surface High Frequency Eddy Current (HFEC) inspection on the Station 2231 Frame Inner

Chord (forward and aft) surfaces for cracks in accordance with Figure 4.

5. Group 1-4, Configuration 1:

If any nicks, scratches, or gouges are found and no cracks were found in accordance with Step

4, repair as follows:

a. Rework in accordance with 747-100/-200/-300 SRM Section 51-10-01 (747-400 SRM 51-10-02,

747-400F SRM 51-10-02, 747-400SF SRM 51-10-02).

b. Get a surface finish of 63 micro-inches or better. Break sharp edges.

c. Maintain a minimum 2D edge margin to adjacent fastener locations.

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d. Maintain a minimum rework radius of 0.30 inch.

e. Group 1-2, Configuration 1:

Measure minimum distance "A" from the outboard edge of the chord flange to the rework

radius as shown in FIGURE 4. Minimum acceptable dimension is:

0.625 inch

If rework results in less than this dimension, contact Boeing for repair instructions and do the

repair.

f. Group 3-4, Configuration 1:

Measure minimum distance "A" from the outboard edge of the chord flange to the rework

radius as shown in FIGURE 4. Minimum acceptable dimension is:

0.510 inch

If rework results in less than this dimension, contact Boeing for repair instructions and do the

repair.

g. Accomplish a surface High Frequency Eddy Current (HFEC) inspection of the reworked edge

to ensure a crack free condition. Inspect in accordance with Nondestructive Test (NDT) Manual

D6-7170, Part 6, Subject 51-00-00, Procedure 4 or 23.

6. Group 1-4, Configuration 2:

Do a surface HFEC inspection on the Station 2231 Frame Inner Chord (forward and aft) surfaces

for cracks in accordance with FIGURE 5.

7. If any crack is found, repair in accordance with 747-100/200/300 SRM 53-10-04 (Figure 147),

747-400 SRM 53-60-07 (Repair 7), 747-400F SRM 53-60-07 (Repair 7), 747-400SF SRM 53-60-07

(Repair 7), or contact Boeing for repair instructions and do the repair.

NOTE: After the repair, it will be necessary to do inspections of the repaired area of the frame

in accordance with 747-100/200/300 SRM 53-10-04 (Figure 147), 747-400 SRM 53-60-07

(Repair 7), 747-400F SRM 53-60-07 (Repair 7), 747-400SF SRM 53-60-07 (Repair 7),

as applicable. If only one of the aft or forward inner chords is repaired, repeat the

inspections in accordance with Step 11 for the chords that are not repaired.

8. Airplanes configured to carry passengers in the aft body should use FIGURE 2 for restoration.

9. Airplanes configured to carry cargo in the aft body should use FIGURE 3 for restoration.

10. Put the airplane back to a serviceable condition.

11. Do a repeat surface High Frequency Eddy Current (HFEC) inspection on the Station 2231 Frame

Inner Chord (forward and aft) surfaces for cracks in accordance with FIGURE 5. If any crack is

found, repair in accordance with 747-100/200/300 SRM 53-10-04 (Figure 147), 747-400 SRM

53-60-07 (Repair 7), 747-400F SRM 53-60-07 (Repair 7), 747-400SF SRM 53-60-07 (Repair 7),

or contact Boeing for repair instructions and do the repair.

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NOTE: After the repair, it will be necessary to do inspections of the repaired area of the frame

in accordance with 747-100/200/300 SRM 53-10-04 (Figure 147), 747-400 SRM 53-60-07

(Repair 7), 747-400F SRM 53-60-07 (Repair 7), 747-400SF SRM 53-60-07 (Repair 7),

as applicable. If only one of the aft or forward inner chords is repaired, repeat the

inspections in accordance with Step 11 for the chords that are not repaired.

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ALERT ALERT
FIGURE 1: THIS FIGURE IS DELETED

(SHEET 1 OF 1)

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ALERT ALERT
This Figure applies only to: Group 1, 3.

FIGURE 2: ACCESS / RESTORATION FOR CONFIGURATION WITH PASSENGERS IN THE AFT BODY

(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 one side of the airplane.

STEP TASK NAME REFERENCES QTY NOTES

747 AMM 25-21-03, 747- 1 -

400 AMM 25-21-03

Lower transition

Panel

1 Remove

747 AMM 25-59-05, 747 - (a)

AMM 25-21-04, 747-400

AMM 25-21-04

2 Pull Back Insulation Blankets

(a) Pull back insulation blankets in area of inspection. Insulation blankets not shown in figure.

STEP TASK NAME REFERENCES QTY NOTES

747 AMM 25-59-05, 747 - -

AMM 25-21-04, 747-400

AMM 25-21-04

3 Install Insulation Blankets

747 AMM 25-21-03, 747- 1 -

400 AMM 25-21-03

Lower transition

Panel

4 Install

FIGURE 2: ACCESS / RESTORATION FOR CONFIGURATION WITH PASSENGERS IN THE AFT BODY

(SHEET 2 OF 2)

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ALERT ALERT
This Figure applies only to: Group 2, 4.

FIGURE 3: ACCESS / RESTORATION FOR CONFIGURATION WITH CARGO IN THE AFT BODY

(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 one side of the airplane.

STEP TASK NAME REFERENCES QTY NOTES

747 AMM 25-59-01, 747- 1 -

400 AMM 25-59-01

Lower transition

Panel

1 Remove

747 AMM 25-59-05, 747- - (a)

400 AMM 25-59-05

2 Pull Back Insulation Blankets

(a) Pull back insulation blankets in area of inspection. Insulation blankets not shown in figure.

STEP TASK NAME REFERENCES QTY NOTES

747 AMM 25-59-05, 747- - -

400 AMM 25-59-05

3 Install Insulation Blankets

747 AMM 25-59-01, 747- 1 -

400 AMM 25-59-01

Lower transition

Panel

4 Install

FIGURE 3: ACCESS / RESTORATION FOR CONFIGURATION WITH CARGO IN THE AFT BODY

(SHEET 2 OF 2)

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ALERT ALERT
This Figure applies only to: Group 1-4, Configuration 1.

FIGURE 4: INSPECTION

(SHEET 1 OF 3)

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ALERT ALERT
FIGURE 4: INSPECTION

(SHEET 2 OF 3)

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ALERT ALERT
The step numbers shown below agree with the numbers shown in the circle symbols in the figure.

STEP TASK NAME PROCEDURE REFERENCES NOTES

Station 2231 Detailed Inspection - (a)

Frame Inner

Chords (surfaces

and edge) and

Web Edge

1 Inspect

747 Nondestructive (b)

Test (NDT) Manual

D6-7170, Part 6,

Subject 51-00-00,

Procedure 4 or 23

Surface High Frequency Eddy Current (HFEC) InspectionStation 2231

Frame Inner

Chords (surfaces)

2 Inspect

(a) Do a detailed inspection of the Station 2231 Frame Inner Chords (forward and aft surfaces

and edge) and Web edge for nicks, scratches, and / or gouges.

(b) Do a surface HFEC inspection on the Station 2231 Frame Inner Chords (forward and aft surfaces) for cracks.

FIGURE 4: INSPECTION

(SHEET 3 OF 3)

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ALERT ALERT
FIGURE 5: HFEC INSPECTION

(SHEET 1 OF 3)

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FIGURE 5: HFEC INSPECTION

(SHEET 2 OF 3)

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ALERT ALERT
The step numbers shown below agree with the numbers shown in the circle symbols in the figure.

STEP TASK NAME PROCEDURE REFERENCES NOTES

747 Nondestructive (a)

Test (NDT) Manual

D6-7170, Part 6,

Subject 51-00-00,

Procedure 4 or 23

Surface High Frequency Eddy Current (HFEC) Inspection

Station 2231

Frame Inner

Chords (surfaces)

1 Inspect

(a) Do a surface HFEC inspection on the Station 2231 Frame Inner Chords (forward and aft surfaces) for cracks.

FIGURE 5: HFEC INSPECTION

(SHEET 3 OF 3)

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ALERT ALERT
This Appendix applies only to: Group 1-4, Configuration 1.

APPENDIX A: LOGIC DIAGRAM

(SHEET 1 OF 2)

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APPENDIX A: LOGIC DIAGRAM

(SHEET 2 OF 2)

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ALERT ALERT
This Appendix applies only to: Group 1-4, Configuration 2.

APPENDIX B: LOGIC DIAGRAM

(SHEET 1 OF 1)

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ALERT ALERT