Commercial 

Airplanes 737

Service Bulletin

ALERT

Number: 737-53A1319

Original Issue: April 04, 2011

Revision 2: April 04, 2014

ATA System: 5331

SUBJECT: FUSELAGE - Skin - Crown Skin Lap Joint - Inspection for Lower Row Cracks at Stringer

S-4, Between Body Station 360 and Body Station 1016

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 © 2011 Boeing.

Unpublished Work. All Rights Reserved.

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

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BOEING SERVICE BULLETIN 737-53A1319

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 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 16

B. Concurrent Requirements . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 16

C. Reason . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 16

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

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

F. Approval . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25

G. Manpower . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 26

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 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 28

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 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 33

FIGURE 1: EXTERNAL INSPECTION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 42

FIGURE 2: INTERNAL INSPECTION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 44

FIGURE 3: CONFIRMING A CRACK INDICATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . 48

FIGURE 4: FIGURE DELETED AT REVISION 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 52

FIGURE 5: INSPECTION ZONES [Group 1-2, 4-7] . . . . . . . . . . . . . . . . . . . . . . . . . . . . 53

FIGURE 6: INSPECTION ZONES [Group 3] . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 56

FIGURE 7: INSPECTION ZONES . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 57

FIGURE 8: INTERNAL GENERAL VISUAL INSPECTION - LOWER SKIN PANEL AT S-4R, BS 908 TO BS

1016 [Group 1, 4, 6] . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 60

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ALERT ALERT
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BOEING SERVICE BULLETIN 737-53A1319

ALERT ALERT

BLANK PAGE
Commercial 

Airplanes 737

Service Bulletin

ALERT

Revision Transmittal Sheet Number: 737-53A1319

Original Issue: April 04, 2011

Revision 2: April 04, 2014

ATA System: 5331

SUBJECT: FUSELAGE - Skin - Crown Skin Lap Joint - Inspection for Lower Row Cracks at Stringer

S-4, Between Body Station 360 and Body Station 1016

This revision includes all pages of the service bulletin.

COMPLIANCE INFORMATION RELATED TO THIS REVISION

Federal Aviation Administration (FAA) Airworthiness Directive AD 2011-08-51 is related to this service bulletin.

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

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

bulletin mandatory.

More work is necessary on the airplanes inspected in accordance with the Original Issue or Revision 1 of this

service bulletin.

Additional work requirements are in Paragraph 1.E., Compliance, Tables 3, 4, 5, and 6.

Optional repeat inspection intervals are in Paragraph 1.E., Compliance, Table 2.

REASON FOR REVISION

This revision is sent to define new groups, provide new compliance tables, and add more inspections. In addition,

the second external inspection in Figure 4 is deleted.

The data given in Information Notice 737-53A1319 IN-01 is included in this revision.

These sections were changed:

1. In Summary, changed Background, Action, Compliance, Industry Support Information, and Summary

Figure.

2. In Paragraph 1.A.1., Airplanes, added Service Bulletin Index and defined new Groups.

3. In Paragraph 1.C., Reason, added fleet findings, Widespread Fatigue Damage (WFD) statement,

Service Related Problem (SRP) number, and Fleet Team Digest (FTD) number.

4. In Paragraph 1.D., Description, changed to agree with Compliance and Work Instructions sections and

added Maintenance Zone tables.

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5. In Paragraph 1.E., Compliance - added Airworthiness Directive (AD) effective date, inspection exceptions,

new compliance requirements, and compliance tables.

6. In Paragraph 1.F., Approval, changed alternative method of compliance (AMOC) approval statement.

7. In Paragraph 1.G., Manpower, changed Manpower tables.

8. In Paragraph 1.J., References, changed Existing Data.

9. In Paragraph 1.M., Software Accomplishment Summary, added software accomplishment section.

10. In Paragraph 2.B., Industry Support Information, added warranty statement.

11. In Paragraph 3.A., General Information, changed Notes.

12. In Paragraph 3.B., Work Instructions, changed to agree with Description and Compliance sections.

13. Figure 1, added locator and changed Non-Destructive Testing (NDT) from Figure to Procedure to agree

with the 737 NDT Manual.

14. Figure 2, added locator, changed illustration, and added inspection note for locations obstructed by

the internal structures.

15. Figure 3, added locator, changed illustration, added inspection note for locations obstructed by the

internal structures and removed the optional open hole rotary probe inspection.

16. Figure 4, deleted figure because Boeing has determined that the second external inspection is no

longer required.

17. Figure 5, added Group heading.

18. Figures 6-7, added new figures for inspection zones.

19. Figure 8, added new figure for internal general visual inspection.

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 important changes.

REVISION HISTORY

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Revision 1: April 08, 2011

Revision 2: April 04, 2014

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BOEING SERVICE BULLETIN 737-53A1319

ALERT ALERT
Commercial 

Airplanes 737

Service Bulletin

ALERT

Summary Number: 737-53A1319

Original Issue: April 04, 2011

Revision 2: April 04, 2014

ATA System: 5331

SUBJECT: FUSELAGE - Skin - Crown Skin Lap Joint - Inspection for Lower Row Cracks at Stringer

S-4, Between Body Station 360 and Body Station 1016

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

A 737-300 airplane, outside of the effectivity of Service Bulletin (SB) 737-53A1255, experienced a rapid

decompression when the lap joint at stringer S-4L between BS 664 - BS 727 cracked and opened up. Investigation

shows that the cracks were caused by fatigue cracks in the lower skin at the lower row of fasteners in the lap

joint. The airplane had 39,781 total flight cycles and 48,740 total flight hours. This service bulletin gives instructions

to inspect the lower row of fasteners at stringer S-4R and S-4L, from BS 360 to BS 908 for cracks in the lower

skin of the lap joint. If cracks at this location go undetected, the cracks could link up, resulting in an uncontrolled

decompression.

After the original issue of this service bulletin, Non-Destructive Testing (NDT) inspections have resulted in

additional fleet findings in the skin at the lap joint lower fastener row. Fourteen (14) aircraft were reported with

crack indications between 38,222 - 44,784 total flight cycles and 46,822 - 54,434 total hours.

Further investigation into these reports of cracks in the lower skin at the lap joint lower row fastener hole have

identified small cracks and cracks from scratches. There were nine (9) findings with scratch cracks. Scratch

cracks form in the lower skin at the lap joint lower fastener row, local to the hole, but may not intersect the hole.

Internal crack confirmation common to doublers and tear straps using hole probe inspections have been removed

from this service bulletin because scratch cracks may not intersect the fastener hole.

Airplanes prior to Line Number 2553 are covered by Service Bulletin (SB) 737-53A1255. This SB covers airplanes

from Line Number 2553 to 3132.

The lap splice - fuselage lower fastener hole in the lower skin has been determined to be structure that is

susceptible to Widespread Fatigue Damage (WFD).

Boeing Service Related Problem (SRP) 737-SRP-53-0330 is related to this service bulletin.

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Boeing Fleet Team Digest (FTD) 737 FTD 53-09004 is related to this service bulletin.

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

information.

Planning Data Affected Reference

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

Paragraph 1.E., Compliance and Paragraph

1.F., Approval

AD Related Yes

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

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

Publications Affected No Paragraph 1.K., Publications Affected

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

Operations Manual and/or FAA Approved Airplane Flight Manual)

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

This service bulletin gives instructions to do as follows:

1. Part 1: (Option 1) External eddy current inspection at S-4L and S-4R, BS 360 to BS 908 for cracks,

excluding BS 540 to BS 727E for Group 3 airplanes.

Or

Part 1: (Option 2) Internal detailed and eddy current inspections at S-4L and S-4R, BS 360 to BS 908

for cracks, excluding BS 540 to BS 727E for Group 3 airplanes.

2. Part 2: One-time internal detailed and eddy current inspections at S-4L and S-4R, BS 360 to BS 908

for cracks, excluding BS 540 to BS 727E for Group 3 airplanes.

3. Group 2-3, 5, 7:

Part 3: One-time internal detailed and eddy current inspections at S-4R, BS 908 to BS 1016 for cracks.

4. Group 2-3, 5, 7:

Part 4: (Option 1) External eddy current inspection at S-4R, BS 908 to BS 1016 for cracks.

Or

Part 4: (Option 2) Internal detailed and eddy current inspections at S-4R, BS 908 to BS 1016 for cracks.

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BOEING SERVICE BULLETIN 737-53A1319

ALERT ALERT
5. Group 1, 4, 6:

Part 5: Internal general visual inspection of lower skin panel at S-4R, BS 908 to BS 1016 for open or

closed pockets.

EFFECTIVITY

737-300, 737-400, and 737-500 Airplanes. Refer to Paragraph 1.A.1., Airplanes, for the list of affected airplanes.

COMPLIANCE

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

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

bulletin mandatory.

Federal Aviation Administration (FAA) Airworthiness Directive AD 2011-08-51 is related to this service bulletin.

The effective date of AD 2011-08-51 is June 2, 2011.

Refer to Paragraph 1.E., Compliance.

INDUSTRY SUPPORT INFORMATION

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

bulletin.

MANPOWER

Refer to Paragraph 1.G., Manpower.

MATERIAL INFORMATION

None.

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BOEING SERVICE BULLETIN 737-53A1319

ALERT ALERT
Commercial 

Airplanes 737

Service Bulletin

ALERT

Number: 737-53A1319

Original Issue: April 04, 2011

Revision 2: April 04, 2014

ATA System: 5331

SUBJECT: FUSELAGE - Skin - Crown Skin Lap Joint - Inspection for Lower Row Cracks at Stringer

S-4, Between Body Station 360 and Body Station 1016

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 for the airplane(s) shown below.

Refer to Service Bulletin Index D6-19567 Part 3 for Airplane Variable Number, Line Number, and

Serial Number data.

GROUP CONFIGURATION DESCRIPTION

737-300 airplanes with specific inspection zones S-4R and S-4L, BS

360 to BS 908 and internal general visual inspection for open or

closed pockets at S-4R, BS 908 to BS 1016.

1 -

737-300 airplanes with specific inspection zones S-4R and S-4L, BS

360 to BS 908 and S-4R, BS 908 to BS 1016.

2 -

737-300 airplanes with specific inspection zones S-4R and S-4L, BS

360 to BS 540 and BS 727E to BS 908 and S-4R, BS 908 to BS

1016.

3 -

737-400 airplanes with specific inspection zones S-4R and S-4L, BS

360 to BS 908 and internal general visual inspection for open or

closed pockets at S-4R, BS 908 to BS1016.

4 -

737-400 airplanes with specific inspection zones S-4R and S-4L, BS

360 to BS 908 and S-4R, BS 908 to BS 1016.

5 -

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GROUP CONFIGURATION DESCRIPTION

737-500 airplanes with specific inspection zones S-4R and S-4L, BS

360 to BS 908 and internal general visual inspection for open or

closed pockets at S-4R, BS 908 to BS 1016.

6 -

737-500 airplanes with specific inspection zones S-4R and S-4L, BS

360 to BS 908 and S-4R, BS 908 to BS 1016.

7 -

Airplane Models:

737-300, 737-400, 737-500

Variable Number Group

PJ552 - PJ559 5

PJ560 - PJ561 4

PJ601 - PJ615 4

PJ811 4

PJ816 - PJ817 4

PM543 - PM550 2

PP518 - PP520 2

PP876 - PP877 1

PQ297 - PQ299 2

PQ345 - PQ348 2

PQ370 - PQ373 2

PQ391 - PQ393 2

PQ394 - PQ395 1

PQ408 - PQ410 2

PQ414 2

PQ415 - PQ418 1

PQ431 - PQ438 2

PQ447 2

PQ448 1

PQ451 1

PQ454 1

PQ473 - PQ475 2

PQ772 2

PQ933 - PQ935 2

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BOEING SERVICE BULLETIN 737-53A1319

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Variable Number Group

PQ951 2

PQ971 2

PQ972 - PQ997 1

PR001 - PR017 1

PR021 - PR034 1

PR041 - PR045 1

PR061 - PR072 1

PR077 - PR082 1

PR091 - PR092 1

PR096 1

PR101 1

PR121 - PR122 1

PR131 - PR132 1

PR141 - PR143 1

PR161 - PR172 1

PR181 1

PS617 - PS629 2

PS630 1

PS704 - PS706 2

PS763 - PS799 3

PS811 2

PS836 - PS837 2

PS841 - PS846 2

PS851 - PS852 2

PS856 2

PS861 - PS863 2

PS866 - PS868 2

PS871 - PS874 1

PS896 - PS897 2

PS901 - PS906 3

PS907 - PS924 2

PS925 - PS941 1

PS956 - PS957 2

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BOEING SERVICE BULLETIN 737-53A1319

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Variable Number Group

PS961 - PS963 1

PS971 - PS978 1

PT012 - PT014 7

PT015 6

PT029 - PT031 7

PT064 7

PT126 - PT131 7

PT132 - PT138 6

PT188 7

PT307 - PT309 7

PT513 - PT517 7

PT585 7

PT586 6

PT643 - PT644 7

PT656 7

PT681 - PT685 6

PT716 - PT717 7

PT721 7

PT722 - PT725 6

PT801 - PT834 7

PT851 - PT853 7

PT854 6

PT871 - PT876 7

PT877 - PT886 6

PT901 - PT930 6

PT971 - PT973 7

PT981 - PT985 6

PT996 6

PU301 6

PU311 - PU313 6

PV204 - PV205 5

PV206 - PV209 4

PV226 5

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BOEING SERVICE BULLETIN 737-53A1319

ALERT ALERT
Variable Number Group

PV227 - PV229 4

PV284 - PV285 5

PV286 - PV287 4

PV296 5

PV301 5

PV302 4

PV351 4

PV356 - PV357 4

PW086 - PW088 5

PW168 - PW171 4

PW245 - PW251 5

PW252 4

PW262 5

PW263 - PW264 4

PW271 - PW275 5

PW276 4

PW282 - PW292 5

PW401 - PW403 5

PW404 - PW408 4

PW411 - PW413 5

PW414 - PW418 4

PW421 - PW424 4

PW431 - PW435 4

PW441 - PW450 4

PW521 - PW522 5

PW524 - PW525 5

PW527 - PW530 5

PW547 - PW550 5

PW621 - PW622 5

PW635 - PW637 5

PW831 4

PW851 - PW856 4

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BOEING SERVICE BULLETIN 737-53A1319

ALERT ALERT
2. Spares Affected

None.

B. Concurrent Requirements

None.

C. Reason

A 737-300 airplane, outside of the effectivity of Service Bulletin (SB) 737-53A1255, experienced a rapid

decompression when the lap joint at stringer S-4L between BS 664 - BS 727 cracked and opened up.

Investigation shows that the cracks were caused by fatigue cracks in the lower skin at the lower row

of fasteners in the lap joint. The airplane had 39,781 total flight cycles and 48,740 total flight hours.

This service bulletin gives instructions to inspect the lower row of fasteners at stringer S-4R and S-4L,

from BS 360 to BS 908 for cracks in the lower skin of the lap joint. If cracks at this location go undetected,

the cracks could link up, resulting in an uncontrolled decompression.

After the original issue of this service bulletin, Non-Destructive Testing (NDT) inspections have resulted

in additional fleet findings in the skin at the lap joint lower fastener row. Fourteen (14) aircraft were

reported with crack indications between 38,222 - 44,784 total flight cycles and 46,822 - 54,434 total

hours.

Further investigation into these reports of cracks in the lower skin at the lap joint lower row fastener

hole have identified small cracks and cracks from scratches. There were nine (9) findings with scratch

cracks. Scratch cracks form in the lower skin at the lap joint lower fastener row, local to the hole, but

may not intersect the hole. Internal crack confirmation common to doublers and tear straps using hole

probe inspections have been removed from this service bulletin because scratch cracks may not

intersect the fastener hole.

Airplanes prior to Line Number 2553 are covered by Service Bulletin (SB) 737-53A1255. This SB covers

airplanes from Line Number 2553 to 3132.

The lap splice - fuselage lower fastener hole in the lower skin has been determined to be structure that

is susceptible to Widespread Fatigue Damage (WFD).

Boeing Service Related Problem (SRP) 737-SRP-53-0330 is related to this service bulletin.

Boeing Fleet Team Digest (FTD) 737 FTD 53-09004 is related to this service bulletin.

Revision 1 was sent to correct a figure label and to clarify figure details. Manpower estimates are also

included.

Revision 2 is sent to define new groups, provide new compliance tables, and add more inspections.

In addition, the second external inspection in Figure 4 is deleted.

The data given in Information Notice 737-53A1319 IN-01 is included in Revision 2.

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BOEING SERVICE BULLETIN 737-53A1319

ALERT ALERT
D. Description

This service bulletin gives instructions to do as follows:

1. Part 1: (Option 1) External eddy current inspection at S-4L and S-4R, BS 360 to BS 908 for cracks,

excluding BS 540 to BS 727E for Group 3 airplanes.

Or

Part 1: (Option 2) Internal detailed and eddy current inspections at S-4L and S-4R, BS 360 to BS

908 for cracks, excluding BS 540 to BS 727E for Group 3 airplanes.

2. Part 2: One-time internal detailed and eddy current inspections at S-4L and S-4R, BS 360 to BS

908 for cracks, excluding BS 540 to BS 727E for Group 3 airplanes.

3. Group 2-3, 5, 7:

Part 3: One-time internal detailed and eddy current inspections at S-4R, BS 908 to BS 1016 for

cracks.

4. Group 2-3, 5, 7:

Part 4: (Option 1) External eddy current inspection at S-4R, BS 908 to BS 1016 for cracks.

Or

Part 4: (Option 2) Internal detailed and eddy current inspections at S-4R, BS 908 to BS 1016 for

cracks.

5. Group 1, 4, 6:

Part 5: Internal general visual inspection of lower skin panel at S-4R, BS 908 to BS 1016 for open

or closed pockets.

Revision 2 - More work is necessary on airplanes inspected in accordance with the Original Issue or

Revision 1 of this service bulletin.

Additional work requirements are in Paragraph 1.E., Compliance, Tables 3, 4, 5, and 6.

Optional repeat inspection intervals are in Paragraph 1.E., Compliance, Table 2.

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

Group 1-3:

Affected Maintenance Zones

Model Zone

737-300 107, 108

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ALERT ALERT
Group 4-5:

Affected Maintenance Zones

Model Zone

737-400 107, 108

Group 6-7:

Affected Maintenance Zones

Model Zone

737-500 107, 108

E. Compliance

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

related to this service bulletin. The Airworthiness Directive will make the compliance tasks and times

given in this service bulletin mandatory.

Federal Aviation Administration (FAA) Airworthiness Directive AD 2011-08-51 is related to this service

bulletin. The effective date of AD 2011-08-51 is June 2, 2011.

If the airplane has had a skin panel replaced common to the subject lap joint areas, the compliance

times for inspection of the lower skin may be affected. Contact Boeing for alternate lap joint lower row

inspections for the lap joint areas affected by skin panel replacements.

Inspection Exceptions:

1. If an existing external repair doubler is common to the inspection area of the lap joint lower fastener

row and meets the criteria shown below, then it is not required to inspect the lower skin at the lap

joint lower fastener row under the existing repair doubler.

a. The installed repair was approved by the FAA or by a Boeing Authorized Representative who

was authorized by the FAA to make such findings.

b. The installed repair extends a minimum of three rows of fasteners above the chem-mill step

and three rows of fasteners below the lap joint lower row.

2. If the repair does not meet the above conditions, then inspect the lower skin lap joint lower row

internally in the area covered by the doubler in accordance with FIGURE 2.

If any inspection has not been accomplished in accordance with the Original Issue or Revision 1 of this

service bulletin, then Table 1 requirements must be accomplished before starting Table 2 requirements.

Follow-on repetitive inspections may be accomplished using Table 2.

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.

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BOEING SERVICE BULLETIN 737-53A1319

ALERT ALERT
Table 1: Eddy Current Inspections for Cracks at S-4L and S-4R, BS 360 to BS 908

Repeat Interval (Not

to Exceed)

Compliance Time (Whichever Occurs

Later)

Condition Action

Within 20 days after -

the effective date of

AD 2011-08-51

Before 30,000 total

flight cycles

Do PART 1: (OPTION 1) EXTERNAL

EDDY CURRENT

INSPECTION AT S4L AND S-4R, BS

360 TO BS 908 for

cracks.

Airplanes with less

than 30,000 total

flight cycles as of the

effective date of AD

2011-08-51

OR

Do PART 1: (OPTION 2) INTERNAL

DETAILED AND EDDY CURRENT INSPECTIONS AT S4L AND S-4R, BS

360 TO BS 908 for

cracks.

Within 20 days after -

the effective date of

AD 2011-08-51

Do PART 1: (OP- -

TION 1) EXTERNAL

EDDY CURRENT

INSPECTION AT S4L AND S-4R, BS

360 TO BS 908 for

cracks.

Airplanes with

30,000 or more total

flight cycles and less

than 35,000 total

flight cycles as of the

effective date of AD

2011-08-51

OR

Do PART 1: (OPTION 2) INTERNAL

DETAILED AND EDDY CURRENT INSPECTIONS AT S4L AND S-4R, BS

360 TO BS 908 for

cracks.

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ALERT ALERT
Table 1: Eddy Current Inspections for Cracks at S-4L and S-4R, BS 360 to BS 908

Repeat Interval (Not

to Exceed)

Compliance Time (Whichever Occurs

Later)

Condition Action

Within 5 days after -

the effective date of

AD 2011-08-51

Do PART 1: (OP- -

TION 1) EXTERNAL

EDDY CURRENT

INSPECTION AT S4L AND S-4R, BS

360 TO BS 908 for

cracks.

Airplanes with

35,000 or more total

flight cycles as of the

effective date of AD

2011-08-51

OR

Do PART 1: (OPTION 2) INTERNAL

DETAILED AND EDDY CURRENT INSPECTIONS AT S4L AND S-4R, BS

360 TO BS 908 for

cracks.

Repeat inspection in - - 500 flight cycles

PART 1: (OPTION 1)

EXTERNAL EDDY

CURRENT INSPECTION AT S-4L AND

S-4R, BS 360 TO BS

908 for cracks.

CONDITION 1:

NO CRACK FOUND

OR - - -

Repeat inspections - - 500 flight cycles

in PART 1: (OPTION

2) INTERNAL DETAILED AND EDDY

CURRENT INSPECTIONS AT S-4L AND

S-4R, BS 360 TO BS

908 for cracks.

Contact Boeing for Before further flight -

repair instructions

and do the repair.

CONDITION 2:

ANY CRACK

FOUND

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BOEING SERVICE BULLETIN 737-53A1319

ALERT ALERT
Table 2: Airplanes on which any inspection specified in Table 1 or Table 2 of this service bulletin has

been accomplished - Optional Repeat Inspection Intervals

Repeat Interval (Not

to Exceed)

Compliance Time (Whichever Occurs

Later)

Condition Action

2,000 flight cycles

until the accumulation of 38,001 total

flight cycles

Repeat inspection in - -

PART 1: (OPTION 1)

EXTERNAL EDDY

CURRENT INSPECTION AT S-4L AND

S-4R, BS 360 TO BS

908 for cracks.

Airplanes with

38,000 total flight cycles or less as of the

most recent inspection

CONDITION 1:

NO CRACK FOUND

OR

Repeat inspections

in PART 1: (OPTION

2) INTERNAL DETAILED AND EDDY

CURRENT INSPECTIONS AT S-4L AND

S-4R, BS 360 TO BS

908 for cracks.

1,500 flight cycles

until the accumulation of 42,501 total

flight cycles

Repeat inspection in - -

PART 1: (OPTION 1)

EXTERNAL EDDY

CURRENT INSPECTION AT S-4L AND

S-4R, BS 360 TO BS

908 for cracks.

Airplanes with more

than 38,000 total

flight cycles but less

than or equal to

42,500 total flight cycles as of the most

recent inspection

CONDITION 1:

NO CRACK FOUND OR

Repeat inspections

in PART 1: (OPTION

2) INTERNAL DETAILED AND EDDY

CURRENT INSPECTIONS AT S-4L AND

S-4R, BS 360 TO BS

908 for cracks.

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BOEING SERVICE BULLETIN 737-53A1319

ALERT ALERT
Table 2: Airplanes on which any inspection specified in Table 1 or Table 2 of this service bulletin has

been accomplished - Optional Repeat Inspection Intervals

Repeat Interval (Not

to Exceed)

Compliance Time (Whichever Occurs

Later)

Condition Action

Repeat inspections - - 500 flight cycles

in PART 1: (OPTION

1) EXTERNAL EDDY

CURRENT INSPECTION AT S-4L AND

S-4R, BS 360 TO BS

908 for cracks.

Airplanes with more

than 42,500 total

flight cycles as of the

most recent inspection

CONDITION 1:

NO CRACK FOUND

OR

Repeat inspections

in PART 1: (OPTION

2) INTERNAL DETAILED AND EDDY

CURRENT INSPECTIONS AT S-4L AND

S-4R, BS 360 TO BS

908 for cracks.

Contact Boeing for Before further flight -

repair instructions

and do the repair.

CONDITION 2:

ANY CRACK

FOUND

Table 3: One-Time Internal Detailed and Eddy Current Inspections for Cracks at S-4L and S-4R, BS 360

to BS 908

Repeat Interval (Not

to Exceed)

Compliance Time (Whichever Occurs

Later)

Condition Action

Within 1,000 flight -

cycles after the Revision 2 date of this

service bulletin

Before 45,000 total

flight cycles, but not

earlier than 40,000

total flight cycles

Do PART 2: ONETIME INTERNAL

DETAILED AND EDDY CURRENT INSPECTIONS AT S4L AND S-4R, BS

360 TO BS 908 for

cracks. (a)

All Airplanes

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BOEING SERVICE BULLETIN 737-53A1319

ALERT ALERT
Table 3: One-Time Internal Detailed and Eddy Current Inspections for Cracks at S-4L and S-4R, BS 360

to BS 908

Repeat Interval (Not

to Exceed)

Compliance Time (Whichever Occurs

Later)

Condition Action

In accordance with

Table 1 or Table 2

Continue repeat in- - -

spection in PART 1:

(OPTION 1) EXTERNAL EDDY CURRENT INSPECTION

AT S-4L AND S-4R,

BS 360 TO BS 908

for cracks.

CONDITION 3:

NO CRACK FOUND

OR

Continue repeat inspections in PART 1:

(OPTION 2) INTERNAL DETAILED AND

EDDY CURRENT

INSPECTIONS AT

S-4L AND S-4R, BS

360 TO BS 908 for

cracks.

Contact Boeing for Before further flight -

repair instructions

and do the repair.

CONDITION 4:

ANY CRACK

FOUND

(a) Accomplishment of the one-time internal inspection is an acceptable method of compliance for the accomplishment of one Option 1 or one Option 2 inspection specified in Table 1 or Table 2.

Group 2-3, 5, 7:

Table 4: One-Time Internal Detailed and Eddy Current Inspections for Cracks at S-4R, BS 908 TO BS

1016

Repeat Interval (Not

to Exceed)

Compliance Time (Whichever Occurs

Later)

Condition Action

Within 1,000 flight -

cycles after the Revision 2 date of this

service bulletin

Before 76,000 total

flight cycles, but not

earlier than 75,000

total flight cycles

Do PART 3: ONETIME INTERNAL

DETAILED AND EDDY CURRENT INSPECTIONS AT S4R, BS 908 TO BS

1016 for cracks.

All Airplanes

No further Table 4 - -

work required.

CONDITION 5:

NO CRACK FOUND

Do the work in Table

5.

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BOEING SERVICE BULLETIN 737-53A1319

ALERT ALERT
Group 2-3, 5, 7:

Table 4: One-Time Internal Detailed and Eddy Current Inspections for Cracks at S-4R, BS 908 TO BS

1016

Repeat Interval (Not

to Exceed)

Compliance Time (Whichever Occurs

Later)

Condition Action

Contact Boeing for Before further flight -

repair instructions

and do the repair.

CONDITION 6:

ANY CRACK

FOUND

Group 2-3, 5, 7:

Table 5: Eddy Current Inspections for Cracks at S-4R, BS 908 TO BS 1016

Repeat Interval (Not

to Exceed)

Compliance Time (Whichever Occurs

Later)

Condition Action

Within 1,500 flight -

cycles after the Revision 2 date of this

service bulletin

Before 76,500 total

flight cycles

Do PART 4: (OPTION 1) EXTERNAL

EDDY CURRENT

INSPECTION AT S4R, BS 908 TO BS

1016 for cracks.

All Airplanes

OR

Do PART 4: (OPTION 2) INTERNAL

DETAILED AND EDDY CURRENT INSPECTIONS AT S4R, BS 908 TO BS

1016 for cracks.

1,500 flight cycles

until the accumulation of 80,000 total

flight cycles

Repeat inspection in - -

PART 4: (OPTION 1)

EXTERNAL EDDY

CURRENT INSPECTION AT S-4R, BS

908 TO BS 1016 for

cracks.

CONDITION 7:

NO CRACK FOUND

THEN

500 flight cycles after

the accumulation of

80,000 total flight cycles OR

Repeat inspections

in PART 4: (OPTION

2) INTERNAL DETAILED AND EDDY

CURRENT INSPECTIONS AT S-4R, BS

908 TO BS 1016 for

cracks.

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BOEING SERVICE BULLETIN 737-53A1319

ALERT ALERT
Group 2-3, 5, 7:

Table 5: Eddy Current Inspections for Cracks at S-4R, BS 908 TO BS 1016

Repeat Interval (Not

to Exceed)

Compliance Time (Whichever Occurs

Later)

Condition Action

Contact Boeing for Before further flight -

repair instructions

and do the repair.

CONDITION 8:

ANY CRACK

FOUND

Group 1, 4, 6:

Table 6: Internal General Visual Inspection of Lower Skin Panel at S-4R, BS 908 to BS 1016

Repeat Interval (Not

to Exceed)

Compliance Time (Whichever Occurs

Later)

Condition Action

Within 1,500 flight -

cycles after the Revision 2 date of this

service bulletin.

Before 75,000 total

flight cycles

Do PART 5: INTERNAL GENERAL VISUAL INSPECTION

OF LOWER SKIN

PANEL AT S-4R, BS

908 TO BS 1016 for

open or closed pockets. (a)

All Airplanes

No further work re- - - -

quired at S-4R, BS

908 TO BS 1016.

CONDITION 9: ANY

CLOSED POCKETS

FOUND ADJACENT

TO THE S-4R LAP

JOINT, BS 908 TO

BS 1016

Contact Boeing for Before further flight (b)

inspections or repair

instructions and do

the work instructed

by Boeing.

CONDITION 10:

ANY OPEN POCKETS FOUND ADJACENT TO THE S-4R

LAP JOINT, BS 908

TO BS 1016

(a) Refer to FIGURE 8 for illustrations of open or closed pockets.

(b) Depending on configuration information, the repair instructions may result in repetitive inspection instructions

similar to Part 3 and Part 4 for Group 2-3, 5, and 7 airplanes.

F. Approval

This service bulletin was examined by the Federal Aviation Administration (FAA). The changes specified

in this service bulletin comply with the applicable regulations and are FAA approved, as well as European

Aviation Safety Agency (EASA)/Joint Aviation Authorities (JAA) approved for all EASA/JAA approved

airplanes listed in the service bulletin effectivity. This service bulletin and its approval were based on

the airplane in its original Boeing delivery configuration or as modified by other approved Boeing

changes.

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BOEING SERVICE BULLETIN 737-53A1319

ALERT ALERT
If an airplane has a non-Boeing modification or repair that affects a component or system also affected

by this service bulletin, the operator is responsible for obtaining appropriate regulatory agency approval

before incorporating this service bulletin.

In addition, the Manager of the FAA Seattle Aircraft Certification Office approves accomplishment of

the Stringer S-4L and S-4R, BS 360 to BS 908 inspections and compliance times in accordance with

Boeing Alert Service Bulletin 737-53A1319 Revision 2 as an alternative method of compliance to the

inspections required by paragraphs (g), (i) and (k) of AD 2011-08-51. All provisions of AD 2011-08-51

that are not specifically referenced in the above statement remain fully applicable and must be complied

with accordingly.

G. Manpower

The table below shows an estimate of the task hours necessary to do this inspections 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, 4, 6:

Task Number of Persons Task Hours Elapsed Hours

Part 1 (Option 1) 2 6.00 3.00

Part 1 (Option 2) 20 4270.00 213.50

Part 2 20 4270.00 213.50

Part 5 10 550.00 55.00

TOTAL FOR EACH AIRPLANE (a) (b) (b)

(a) Additional hours will be required for repair if any crack is found.

(b) Total hours dependent upon Parts and Options accomplished.

Group 2-3, 5, 7:

Task Number of Persons Task Hours Elapsed Hours

Part 1 (Option 1) 2 6.00 3.00

Part 1 (Option 2) 20 4270.00 213.50

Part 2 20 4270.00 213.50

Part 3 10 550.00 55.00

Part 4 (Option 1) 2 4.00 2.00

Part 4 (Option 2) 10 550.00 55.00

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BOEING SERVICE BULLETIN 737-53A1319

ALERT ALERT
Group 2-3, 5, 7:

Task Number of Persons Task Hours Elapsed Hours

TOTAL FOR EACH AIRPLANE (a) (b) (b)

(a) Additional hours will be required for repair if any crack is found.

(b) Total hours dependent upon Parts and Options accomplished.

H. Weight and Balance Changes

None.

I. Electrical Load Data

None.

J. References

1. Existing Data:

a. Boeing Service Bulletin 737-53A1255

b. Boeing Service Letter 737-SL-51-042

c. Boeing Service Related Problem (SRP) 737-SRP-53-0330

d. Federal Aviation Administration (FAA) Airworthiness Directive (AD) 2011-08-51

e. Service Bulletin Index D6-19567

f. Standard Overhaul Practices Manual (SOPM) 20-50-01

g. 737 Fleet Team Digest (FTD) 53-09004

h. 737 Non-Destructive Testing (NDT) Manual Part 6, 53-30-00 Procedure 9, Part 6, 53-30-12,

Part 6, 53-30-16

i. 737-300/400/500 Aircraft Maintenance Manual (AMM) 21-23-25, 25-21-39, 25-21-45, 25-21-71,

25-23-61, 25-24-31, 25-31-21, 25-31-31, 25-31-61, 25-40-01

2. Data Supplied with this Service Bulletin:

None.

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

None.

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BOEING SERVICE BULLETIN 737-53A1319

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 does not affect FCS, therefore DTIs are not necessary.

L. Interchangeability and Intermixability of Parts

None.

M. Software Accomplishment Summary

Not affected.

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BOEING SERVICE BULLETIN 737-53A1319

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/or 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
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BOEING SERVICE BULLETIN 737-53A1319

ALERT ALERT

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 737 Structural Repair Manual,

Chapter 51.

— Values for airframe maintenance tasks are included in Chapter 20 of 737

Airplane Maintenance Manual (AMM).

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

SRM Chapter 51.

5. If the length of any fastener specified in this service bulletin does not meet installation

standards given in SRM Chapter 51, then a fastener of the same specification, or

an approved substitute, with a length which meets the installation standards given

in SRM Chapter 51 may be used. In addition, washers may be installed for fastener

grip length in accordance with SRM Chapter 51. Refer to SOPM 20-50-01 for alternate

full threaded fasteners (screws) needed for installation in this service bulletin.

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

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

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

appropriate.

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

cleaning and elaborate procedures may be required.

7. A General Visual Inspection is defined as: A visual examination of an interior or

exterior area, installation or assembly to detect obvious damage, failure or irregularity.

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BOEING SERVICE BULLETIN 737-53A1319

ALERT ALERT
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.

8. These work instructions refer to procedures included in other Boeing documents.

When the words "refer to" are used and the operator has an accepted alternative

procedure, the accepted alternative procedure can be used. When the words "in

accordance with" are included in the instruction, the procedure in the Boeing document

must be used.

9. Boeing Service Letter 737-SL-51-042, Damage Reporting and Repair Plan/Design

Guidelines, is an acceptable procedure to request information from Boeing for

additional structural repair instructions. The Service Letter describes what information

must be provided to Boeing before a structural repair can be provided.

10. The instructions in Paragraph 3.B., Work Instructions and the figures can include

operation of tools or test equipment. Boeing Engineering Tool Drawings, the Illustrated

Tool and Equipment Manual, and the Special Tool and Ground Handling Drawing

Index contain data on versions of the tools or test equipment that you can use. It is

permitted to use replaced tools. It is not permitted to use superseded tools.

11. If it is necessary to remove more parts for access, you can remove those parts. If

you can get access without removing identified parts, it is not necessary to remove

all of the identified parts. Jacking and shoring limitations must be observed.

12. Where the work instructions include installation of a kept part, a new or serviceable

part with the same part number can be installed as an alternative to the kept part.

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

non-authoritative information from the critical and authoritative information.

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

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

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

OPTION number.

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

are in Paragraph 1.E., Compliance.

16. Inspection Exceptions:

— If an existing external repair doubler is common to the inspection area of the lap

joint lower fastener row and meets the criteria shown below, then it is not required

to inspect the lower skin at the lap joint lower fastener row under the existing

repair doubler.

— The installed repair was approved by the FAA or by a Boeing Authorized

Representative who was authorized by the FAA to make such findings.

Export Controlled ECCN: 9E991 - BOEING

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BOEING SERVICE BULLETIN 737-53A1319

ALERT ALERT
— The installed repair extends a minimum of three rows of fasteners above

the chem-mill step and three rows of fasteners below the lap joint lower

row.

— If the repair does not meet the above conditions, then inspect the lower skin lap

joint lower row internally in the area covered by the doubler in accordance with

FIGURE 2.

B. WORK INSTRUCTIONS

1. Do PART 1: (OPTION 1) EXTERNAL EDDY CURRENT INSPECTION AT S-4L AND S-4R, BS

360 TO BS 908 for cracks.

Or

Do PART 1: (OPTION 2) INTERNAL DETAILED AND EDDY CURRENT INSPECTIONS AT S-4L

AND S-4R, BS 360 TO BS 908 for cracks.

CONDITION 1: NO CRACK FOUND

a. Repeat inspection in PART 1: (OPTION 1) EXTERNAL EDDY CURRENT INSPECTION AT

S-4L AND S-4R, BS 360 TO BS 908 for cracks.

Or

Repeat inspections in PART 1: (OPTION 2) INTERNAL DETAILED AND EDDY CURRENT

INSPECTIONS AT S-4L AND S-4R, BS 360 TO BS 908 for cracks.

CONDITION 2: ANY CRACK FOUND

a. Contact Boeing for repair instructions and do the repair.

2. Do PART 2: ONE-TIME INTERNAL DETAILED AND EDDY CURRENT INSPECTIONS AT S-4L

AND S-4R, BS 360 TO BS 908 for cracks.

CONDITION 3: NO CRACK FOUND

a. Continue repeat inspection in PART 1: (OPTION 1) EXTERNAL EDDY CURRENT

INSPECTION AT S-4L AND S-4R, BS 360 TO BS 908 for cracks.

Or

Continue repeat inspections in PART 1: (OPTION 2) INTERNAL DETAILED AND EDDY

CURRENT INSPECTIONS AT S-4L AND S-4R, BS 360 TO BS 908 for cracks.

CONDITION 4: ANY CRACK FOUND

a. Contact Boeing for repair instructions and do the repair.

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BOEING SERVICE BULLETIN 737-53A1319

ALERT ALERT
3. Group 2-3, 5, 7:

Do PART 3: ONE-TIME INTERNAL DETAILED AND EDDY CURRENT INSPECTIONS AT S-4R,

BS 908 TO BS 1016 for cracks.

CONDITION 5: NO CRACK FOUND

a. Do PART 4: (OPTION 1) EXTERNAL EDDY CURRENT INSPECTION AT S-4R, BS 908 TO

BS 1016 for cracks.

Or

Do PART 4: (OPTION 2) INTERNAL DETAILED AND EDDY CURRENT INSPECTIONS AT

S-4R, BS 908 TO BS 1016 for cracks.

CONDITION 6: ANY CRACK FOUND

a. Contact Boeing for repair instructions and do the repair.

4. Group 2-3, 5, 7:

Do PART 4: (OPTION 1) EXTERNAL EDDY CURRENT INSPECTION AT S-4R, BS 908 TO BS

1016 for cracks.

Or

Do PART 4: (OPTION 2) INTERNAL DETAILED AND EDDY CURRENT INSPECTIONS AT S-4R,

BS 908 TO BS 1016 for cracks.

CONDITION 7: NO CRACK FOUND

a. Repeat inspection in PART 4: (OPTION 1) EXTERNAL EDDY CURRENT INSPECTION AT

S-4R, BS 908 TO BS 1016 for cracks.

Or

Repeat inspections in PART 4: (OPTION 2) INTERNAL DETAILED AND EDDY CURRENT

INSPECTIONS AT S-4R, BS 908 TO BS 1016 for cracks.

CONDITION 8: ANY CRACK FOUND

a. Contact Boeing for repair instructions and do the repair.

5. Group 1, 4, 6:

Do PART 5: INTERNAL GENERAL VISUAL INSPECTION OF LOWER SKIN PANEL AT S-4R,

BS 908 TO BS 1016 for open or closed pockets.

CONDITION 9: ANY CLOSED POCKETS FOUND ADJACENT TO THE S-4R LAP JOINT, BS

908 TO BS 1016

a. No further work required at S-4R, BS 908 TO BS 1016.

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BOEING SERVICE BULLETIN 737-53A1319

ALERT ALERT
CONDITION 10: ANY OPEN POCKETS FOUND ADJACENT TO THE S-4R LAP JOINT, BS 908

TO BS 1016

a. Contact Boeing for inspections or repair instructions and do the work instructed by Boeing.

NOTE: Depending on configuration information, the repair instructions may result in repetitive

inspection instructions similar to Part 3 and Part 4 for Group 2-3, 5, and 7 airplanes.

PART 1: (OPTION 1) EXTERNAL EDDY CURRENT INSPECTION AT S-4L AND S-4R, BS 360 TO

BS 908

1. Group 1-2, 4-7:

Do the external eddy current inspection for cracks in the lower skin lap joint lower fastener row at

S-4L and S-4R from BS 360 to BS 908 in accordance with FIGURE 5 inspection zones.

2. Group 3:

Do the external eddy current inspection for cracks in the lower skin lap joint lower fastener row at

S-4L and S-4R from BS 360 to BS 540 and BS 727E to BS 908 in accordance with FIGURE 6

inspection zones.

3. Do the external eddy current inspection for cracks along the centerline of the lap joint lower fastener

row at stringers S-4L and S-4R in accordance with FIGURE 1.

4. Optional. Airplanes with any crack indication when external eddy current inspections are

accomplished, do internal eddy current inspections at crack indication in accordance with FIGURE

3 to confirm crack indications.

5. Put the airplane back to a serviceable condition.

PART 1: (OPTION 2) INTERNAL DETAILED AND EDDY CURRENT INSPECTIONS AT S-4L AND

S-4R, BS 360 TO BS 908

1. Remove and keep interior equipment at the inspection body station locations. Refer to the applicable

AMM reference below as an accepted procedure.

Equipment 737-300/-400/-500 AMM Subject

Galley No. 2 737-300/400/500 AMM 25-31-21

Galley No. 3 737-300/400/500 AMM 25-31-31

Galley No. 6 737-300/400/500 AMM 25-31-61

Lavatory 737-300/400/500 AMM 25-40-01

Sculptured Ceiling Panels 737-300/400/500 AMM 25-21-45

Lowered Ceiling Panels 737-300/400/500 AMM 25-21-71

Sidewall and Ceiling Insulation 737-300/400/500 AMM 25-21-39

Overhead Stowage Bins 737-300/400/500 AMM 25-24-31

Passenger Service Units 737-300/400/500 AMM 25-23-61

Overhead Air Distribution Duct 737-300/400/500 AMM 21-23-25

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BOEING SERVICE BULLETIN 737-53A1319

ALERT ALERT
2. Group 1-2, 4-7:

a. Do internal detailed and eddy current inspections for cracks in the lower skin at the lap joint

lower fastener row at S-4L and S-4R from BS 360 to BS 908 in accordance with FIGURE 5

inspection zones.

3. Group 3:

a. Do internal detailed and eddy current inspections for cracks in the lower skin at the lap joint

lower fastener row at S-4L and S-4R from BS 360 to BS 540 and BS 727E to BS 908 in

accordance with FIGURE 6 inspection zones.

4. Do internal detailed and eddy current inspections for cracks in the lower skin at the lap joint lower

fastener row at S-4L and S-4R in accordance with FIGURE 2.

a. At locations where the stringer channel prevents the inspection probe from scanning 360

degrees around the fastener formed tail, do an internal eddy current inspection for cracks in

the lower skin in accordance with FIGURE 2, View A-A.

NOTE: Inspection procedures 737 NDT Manual Part 6, 53-30-12 and 737 NDT Manual Part 6,

53-30-16 show limited effectivity. The inspections applicable to the lower skin at the lap

joint lower fastener row at stringers S-4L and S-4R in these procedures are applicable

to the full effectivity in this service bulletin.

5. Install kept interior equipment at the inspection body station locations. Refer to the applicable AMM

reference below as an accepted procedure.

Equipment 737-300/-400/-500 AMM Subject

Galley No. 2 737-300/400/500 AMM 25-31-21

Galley No. 3 737-300/400/500 AMM 25-31-31

Galley No. 6 737-300/400/500 AMM 25-31-61

Lavatory 737-300/400/500 AMM 25-40-01

Sculptured Ceiling Panels 737-300/400/500 AMM 25-21-45

Lowered Ceiling Panels 737-300/400/500 AMM 25-21-71

Sidewall and Ceiling Insulation 737-300/400/500 AMM 25-21-39

Overhead Stowage Bins 737-300/400/500 AMM 25-24-31

Passenger Service Units 737-300/400/500 AMM 25-23-61

Overhead Air Distribution Duct 737-300/400/500 AMM 21-23-25

6. Put the airplane back to a serviceable condition.

PART 2: ONE-TIME INTERNAL DETAILED AND EDDY CURRENT INSPECTIONS AT S-4L AND

S-4R, BS 360 TO BS 908

1. Remove and keep interior equipment at the inspection body station locations. Refer to the applicable

AMM reference below as an accepted procedure.

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BOEING SERVICE BULLETIN 737-53A1319

ALERT ALERT
NOTE: Accomplishment of the one-time internal inspection is an acceptable method of compliance

for the accomplishment of one Option 1 or one Option 2 inspection specified in PART 1.

Equipment 737-300/-400/-500 AMM Subject

Galley No. 2 737-300/400/500 AMM 25-31-21

Galley No. 3 737-300/400/500 AMM 25-31-31

Galley No. 6 737-300/400/500 AMM 25-31-61

Lavatory 737-300/400/500 AMM 25-40-01

Sculptured Ceiling Panels 737-300/400/500 AMM 25-21-45

Lowered Ceiling Panels 737-300/400/500 AMM 25-21-71

Sidewall and Ceiling Insulation 737-300/400/500 AMM 25-21-39

Overhead Stowage Bins 737-300/400/500 AMM 25-24-31

Passenger Service Units 737-300/400/500 AMM 25-23-61

Overhead Air Distribution Duct 737-300/400/500 AMM 21-23-25

2. Group 1-2, 4-7:

a. Do internal detailed and eddy current inspections for cracks in the lower skin at the lap joint

lower fastener row at S-4L and S-4R from BS 360 to BS 908 in accordance with FIGURE 5

inspection zones.

3. Group 3:

a. Do internal detailed and eddy current inspections for cracks in the lower skin at the lap joint

lower fastener row at S-4L and S-4R from BS 360 to BS 540 and BS 727E to BS 908 in

accordance with FIGURE 6 inspection zones.

4. Do internal detailed and eddy current inspections for cracks in the lower skin at the lap joint lower

fastener row at S-4L and S-4R in accordance with FIGURE 2.

a. At locations where the stringer channel prevents the inspection probe from scanning 360

degrees around the fastener formed tail, do an internal eddy current inspection for cracks in

the lower skin in accordance with FIGURE 2, View A-A.

NOTE: Inspection procedures 737 NDT Manual Part 6, 53-30-12 and 737 NDT Manual Part 6,

53-30-16 show limited effectivity. The inspections applicable to the lower skin at the lap

joint lower fastener row at stringers S-4L and S-4R in these procedures are applicable

to the full effectivity in this service bulletin.

5. Install kept interior equipment at the inspection body station locations. Refer to the applicable AMM

reference below as an accepted procedure.

Equipment 737-300/-400/-500 AMM Subject

Galley No. 2 737-300/400/500 AMM 25-31-21

Galley No. 3 737-300/400/500 AMM 25-31-31

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BOEING SERVICE BULLETIN 737-53A1319

ALERT ALERT
Equipment 737-300/-400/-500 AMM Subject

Galley No. 6 737-300/400/500 AMM 25-31-61

Lavatory 737-300/400/500 AMM 25-40-01

Sculptured Ceiling Panels 737-300/400/500 AMM 25-21-45

Lowered Ceiling Panels 737-300/400/500 AMM 25-21-71

Sidewall and Ceiling Insulation 737-300/400/500 AMM 25-21-39

Overhead Stowage Bins 737-300/400/500 AMM 25-24-31

Passenger Service Units 737-300/400/500 AMM 25-23-61

Overhead Air Distribution Duct 737-300/400/500 AMM 21-23-25

6. Put the airplane back to a serviceable condition.

Group 2-3, 5, 7:

PART 3: ONE-TIME INTERNAL DETAILED AND EDDY CURRENT INSPECTIONS AT S-4R, BS

908 TO BS 1016

1. Remove and keep interior equipment at S-4R from BS 908 to BS 1016. Refer to the applicable

AMM reference below as an accepted procedure.

Equipment 737-300/-400/-500 AMM Subject

Galley No. 3 737-300/400/500 AMM 25-31-31

Lavatory 737-300/400/500 AMM 25-40-01

Sculptured Ceiling Panels 737-300/400/500 AMM 25-21-45

Lowered Ceiling Panels 737-300/400/500 AMM 25-21-71

Sidewall and Ceiling Insulation 737-300/400/500 AMM 25-21-39

Overhead Stowage Bins 737-300/400/500 AMM 25-24-31

Passenger Service Units 737-300/400/500 AMM 25-23-61

Overhead Air Distribution Duct 737-300/400/500 AMM 21-23-25

2. Do internal detailed and eddy current inspections for cracks in the lower skin at the lap joint lower

fastener row at stringer S-4R from BS 908 to BS 1016 in accordance with FIGURE 7 inspection

zones.

3. Do internal detailed and eddy current inspections for cracks in the lower skin at the lap joint lower

fastener row at S-4R in accordance with FIGURE 2.

a. At locations where the stringer channel prevents the inspection probe from scanning 360

degrees around the fastener formed tail, do an internal eddy current inspection for cracks in

the lower skin in accordance with FIGURE 2, View A-A.

Export Controlled ECCN: 9E991 - BOEING

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BOEING SERVICE BULLETIN 737-53A1319

ALERT ALERT
NOTE: Inspection procedures 737 NDT Manual Part 6, 53-30-12 and 737 NDT Manual Part

6, 53-30-16 show limited effectivity. The inspections applicable to the lower skin at

the lap joint lower fastener row at stringer S-4R in these procedures are applicable

to the full effectivity in this service bulletin.

4. Install kept interior equipment at the inspection body station locations. Refer to the applicable AMM

reference below as an accepted procedure.

Equipment 737-300/-400/-500 AMM Subject

Galley No. 3 737-300/400/500 AMM 25-31-31

Lavatory 737-300/400/500 AMM 25-40-01

Sculptured Ceiling Panels 737-300/400/500 AMM 25-21-45

Lowered Ceiling Panels 737-300/400/500 AMM 25-21-71

Sidewall and Ceiling Insulation 737-300/400/500 AMM 25-21-39

Overhead Stowage Bins 737-300/400/500 AMM 25-24-31

Passenger Service Units 737-300/400/500 AMM 25-23-61

Overhead Air Distribution Duct 737-300/400/500 AMM 21-23-25

5. Put the airplane back to a serviceable condition.

Group 2-3, 5, 7:

PART 4: (OPTION 1) EXTERNAL EDDY CURRENT INSPECTION AT S-4R, BS 908 TO BS 1016

1. Do the external eddy current inspection for cracks in the lower skin lap joint lower fastener row at

stringer S-4R from BS 908 to BS 1016 in accordance with FIGURE 7 inspection zones.

2. Do the external eddy current inspection for cracks along the centerline of the lower skin at the lap

joint lower fastener row at stringer S-4R from BS 908 to BS 1016 in accordance with FIGURE 1.

3. Optional. Airplanes with any crack indication when external eddy current inspections are

accomplished, do internal eddy current inspections at crack indication in accordance with FIGURE

3 to confirm crack indications.

4. Put the airplane back to a serviceable condition.

Group 2-3, 5, 7:

PART 4: (OPTION 2) INTERNAL DETAILED AND EDDY CURRENT INSPECTIONS AT S-4R, BS

908 TO BS 1016

1. Remove and keep interior equipment at S-4R from BS 908 to BS 1016. Refer to the applicable

AMM reference below as an accepted procedure.

Equipment 737-300/-400/-500 AMM Subject

Galley No. 3 737-300/400/500 AMM 25-31-31

Lavatory 737-300/400/500 AMM 25-40-01

Sculptured Ceiling Panels 737-300/400/500 AMM 25-21-45

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BOEING SERVICE BULLETIN 737-53A1319

ALERT ALERT
Equipment 737-300/-400/-500 AMM Subject

Lowered Ceiling Panels 737-300/400/500 AMM 25-21-71

Sidewall and Ceiling Insulation 737-300/400/500 AMM 25-21-39

Overhead Stowage Bins 737-300/400/500 AMM 25-24-31

Passenger Service Units 737-300/400/500 AMM 25-23-61

Overhead Air Distribution Duct 737-300/400/500 AMM 21-23-25

2. Do internal detailed and eddy current inspections for cracks in the lower skin at the lap joint lower

fastener row at stringer S-4R from BS 908 to BS 1016 in accordance with FIGURE 7 inspection

zones.

3. Do internal detailed and eddy current inspections for cracks in the lower skin at the lap joint lower

fastener row at S-4R in accordance with FIGURE 2.

a. At locations where the stringer channel prevents the inspection probe from scanning 360

degrees around the fastener formed tail, do an internal eddy current inspection for cracks in

the lower skin in accordance with FIGURE 2, View A-A.

NOTE: Inspection procedures 737 NDT Manual Part 6, 53-30-12 and 737 NDT Manual Part

6, 53-30-16 show limited effectivity. The inspections applicable to the lower skin at

the lap joint lower fastener row at stringer S-4R in these procedures are applicable

to the full effectivity in this service bulletin.

4. Install kept interior equipment at the inspection body station locations. Refer to the applicable AMM

reference below as an accepted procedure.

Equipment 737-300/-400/-500 AMM Subject

Galley No. 3 737-300/400/500 AMM 25-31-31

Lavatory 737-300/400/500 AMM 25-40-01

Sculptured Ceiling Panels 737-300/400/500 AMM 25-21-45

Lowered Ceiling Panels 737-300/400/500 AMM 25-21-71

Sidewall and Ceiling Insulation 737-300/400/500 AMM 25-21-39

Overhead Stowage Bins 737-300/400/500 AMM 25-24-31

Passenger Service Units 737-300/400/500 AMM 25-23-61

Overhead Air Distribution Duct 737-300/400/500 AMM 21-23-25

5. Put the airplane back to a serviceable condition.

Group 1, 4, 6:

PART 5: INTERNAL GENERAL VISUAL INSPECTION OF LOWER SKIN PANEL AT S-4R, BS 908

TO BS 1016

1. Remove and keep interior equipment at S-4R from BS 908 to BS 1016. Refer to the applicable

AMM reference below as an accepted procedure.

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BOEING SERVICE BULLETIN 737-53A1319

ALERT ALERT
Equipment 737-300/-400/-500 AMM Subject

Galley No. 3 737-300/400/500 AMM 25-31-31

Lavatory 737-300/400/500 AMM 25-40-01

Sculptured Ceiling Panels 737-300/400/500 AMM 25-21-45

Lowered Ceiling Panels 737-300/400/500 AMM 25-21-71

Sidewall and Ceiling Insulation 737-300/400/500 AMM 25-21-39

Overhead Stowage Bins 737-300/400/500 AMM 25-24-31

Passenger Service Units 737-300/400/500 AMM 25-23-61

Overhead Air Distribution Duct 737-300/400/500 AMM 21-23-25

2. Do an internal general visual inspection of the lower skin panel at S-4R, from BS 908 to BS 1016

for open or closed pockets adjacent to the S-4R lap joint in accordance with FIGURE 7 inspection

zones.

3. Do an internal general visual inspection of the lower skin panel at S-4R, from BS 908 to BS 1016

for open or closed pockets adjacent to the S-4R lap joint in accordance with FIGURE 8.

4. Install kept interior equipment at the inspection body station locations. Refer to the applicable AMM

reference below as an accepted procedure.

Equipment 737-300/-400/-500 AMM Subject

Galley No. 3 737-300/400/500 AMM 25-31-31

Lavatory 737-300/400/500 AMM 25-40-01

Sculptured Ceiling Panels 737-300/400/500 AMM 25-21-45

Lowered Ceiling Panels 737-300/400/500 AMM 25-21-71

Sidewall and Ceiling Insulation 737-300/400/500 AMM 25-21-39

Overhead Stowage Bins 737-300/400/500 AMM 25-24-31

Passenger Service Units 737-300/400/500 AMM 25-23-61

Overhead Air Distribution Duct 737-300/400/500 AMM 21-23-25

5. Put the airplane back to a serviceable condition.

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BOEING SERVICE BULLETIN 737-53A1319

ALERT ALERT
FIGURE 1: EXTERNAL INSPECTION

(SHEET 1 OF 2)

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BOEING SERVICE BULLETIN 737-53A1319

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

STEP TASK NAME IDENTIFICATION QTY MORE DATA

Crown Lap Joints Lower - - (a)

Skin

1 Inspect

(a) Do an external eddy current inspection for cracks along the centerline of the lap joint lower fastener row

in accordance with 737 NDT Manual Part 6, 53-30-00 Procedure 9.

FIGURE 1: EXTERNAL INSPECTION

(SHEET 2 OF 2)

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ALERT ALERT
FIGURE 2: INTERNAL INSPECTION

(SHEET 1 OF 4)

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BOEING SERVICE BULLETIN 737-53A1319

ALERT ALERT
FIGURE 2: INTERNAL INSPECTION

(SHEET 2 OF 4)

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BOEING SERVICE BULLETIN 737-53A1319

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

STEP TASK NAME IDENTIFICATION QTY MORE DATA

Between tear straps (a) (b)

(e)

Crown Lap Joints Lower - -

Skin

1 Inspect

Crown Lap Joints Lower - - At tear straps (a) (c) (e)

Skin

2 Inspect

Where lower skin doubler is

not chem-milled at the lap

joint (a) (d) (e)

Crown Lap Joints Lower - -

Skin

3 Inspect

(a) Do a Detailed Inspection of the lap joint lower fastener row for cracks.

(b) Do an internal Mid Frequency Eddy Current (MFEC) inspection for cracks in the lap joint lower fastener

row between tear straps in accordance with 737 NDT Manual Part 6, 53-30-16.

(c) Do an internal Low Frequency Eddy Current (LFEC) inspection for cracks in the lap joint lower fastener

row through the tear strap in accordance with 737 NDT Manual Part 6, 53-30-12.

(d) Do an internal Low Frequency Eddy Current (LFEC) inspection for cracks in the lap joint lower fastener

row through the lower doubler in accordance with 737 NDT Manual Part 6, 53-30-12.

FIGURE 2: INTERNAL INSPECTION

(SHEET 3 OF 4)

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BOEING SERVICE BULLETIN 737-53A1319

ALERT ALERT
STEP TASK NAME IDENTIFICATION QTY MORE DATA

(e) View A-A provides an alternative inspection method to note (b), (c), or (d) the full 360-degree probe

scanning around the fastener formed tail that is obstructed by the internal structures. View A-A is illustrated

for between tear straps, but the method can be used at tear straps and where the lower skin is not chemmilled at the lap joint.

FIGURE 2: INTERNAL INSPECTION

(SHEET 4 OF 4)

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BOEING SERVICE BULLETIN 737-53A1319

ALERT ALERT
FIGURE 3: CONFIRMING A CRACK INDICATION

(SHEET 1 OF 4)

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BOEING SERVICE BULLETIN 737-53A1319

ALERT ALERT
FIGURE 3: CONFIRMING A CRACK INDICATION

(SHEET 2 OF 4)

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BOEING SERVICE BULLETIN 737-53A1319

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

STEP TASK NAME IDENTIFICATION QTY MORE DATA

Crown Lap Joints Lower - - Between tear straps (a) (d)

Skin

1 Inspect

Crown Lap Joints Lower - - At tear straps (b) (d)

Skin

2 Inspect

Where lower skin doubler is

not chem-milled at the lap

joint (c) (d)

Crown Lap Joints Lower - -

Skin

3 Inspect

(a) If there was a crack indication at this location as a result of the external eddy current inspection: Do an

internal Mid Frequency Eddy Current (MFEC) inspection for cracks in the lap joint lower fastener row between tear straps in accordance with 737 NDT Manual Part 6, 53-30-16.

(b) If there was a crack indication at this location: Do an internal Low Frequency Eddy Current (LFEC) inspection

for cracks in the lap joint lower fastener row through the tear strap in accordance with 737 NDT Manual

Part 6, 53-30-12.

(c) If there was a crack indication at this location: Do an internal Low Frequency Eddy Current (LFEC) inspection

for cracks in the lap joint lower fastener row through the lower doubler in accordance with 737 NDT Manual Part 6, 53-30-12.

FIGURE 3: CONFIRMING A CRACK INDICATION

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STEP TASK NAME IDENTIFICATION QTY MORE DATA

(d) View A-A provides an alternative inspection method to note (a), (b), or (c) the full 360-degree probe

scanning around the fastener formed tail that is obstructed by the internal structures. View A-A is illustrated

for between tear straps, but the method can be used at tear straps and where the lower skin is not chemmilled at the lap joint.

FIGURE 3: CONFIRMING A CRACK INDICATION

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FIGURE 4: FIGURE DELETED AT REVISION 2

(SHEET 1 OF 1)

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This Figure applies only to: Group 1-2, 4-7.

FIGURE 5: INSPECTION ZONES

(SHEET 1 OF 3)

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FIGURE 5: INSPECTION ZONES

(SHEET 2 OF 3)

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FIGURE 5: INSPECTION ZONES

(SHEET 3 OF 3)

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This Figure applies only to: Group 3.

FIGURE 6: INSPECTION ZONES

(SHEET 1 OF 1)

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FIGURE 7: INSPECTION ZONES

(SHEET 1 OF 3)

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FIGURE 7: INSPECTION ZONES

(SHEET 2 OF 3)

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FIGURE 7: INSPECTION ZONES

(SHEET 3 OF 3)

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This Figure applies only to: Group 1, 4, 6.

FIGURE 8: INTERNAL GENERAL VISUAL INSPECTION - LOWER SKIN PANEL AT S-4R, BS 908 TO BS

1016

(SHEET 1 OF 3)

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FIGURE 8: INTERNAL GENERAL VISUAL INSPECTION - LOWER SKIN PANEL AT S-4R, BS 908 TO BS

1016

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

STEP TASK NAME IDENTIFICATION QTY MORE DATA

1 Inspect Lower Skin Panel - - (a)

(a) Do an Internal General Visual Inspection of the lower skin panel at S-4R, from STA 908 to STA 1016 for

any open or closed pockets adjacent to the S-4R lap joint.

FIGURE 8: INTERNAL GENERAL VISUAL INSPECTION - LOWER SKIN PANEL AT S-4R, BS 908 TO BS

1016

(SHEET 3 OF 3)

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