Commercial 

Airplanes 737

Service Bulletin

ALERT

Number: 737-53A1352

Original Issue: October 02, 2015

ATA System: 5331

SUBJECT: FUSELAGE - Skin - S-14 Lap Splice Lower Fastener Row Inspection

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 © 2015 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Unpublished Work.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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BLANK PAGE
Table of Contents

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

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

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

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

2. Spares Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 27

B. Concurrent Requirements . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 27

C. Reason . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 28

D. Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 28

E. Compliance . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 29

F. Approval . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 30

G. Manpower . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 31

H. Weight and Balance Changes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 32

I. Electrical Load Data . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 32

J. References . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 32

1. Existing Data: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 32

2. Data Supplied with this Service Bulletin: . . . . . . . . . . . . . . . . . . . . . . . . . . . 32

3. Installation Drawings Used in the Preparation of this Service Bulletin: . . . . . . . . . . . 32

K. Publications Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 33

L. Interchangeability and Intermixability of Parts . . . . . . . . . . . . . . . . . . . . . . . . . . . 33

M. Software Accomplishment Summary . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 33

2. MATERIAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 35

A. Material - Price and Availability . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 35

B. Industry Support Information . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 35

C. Parts Necessary for Each Airplane . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 35

1. Kits/Parts . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 35

2. Parts and Materials Supplied by the Operator . . . . . . . . . . . . . . . . . . . . . . . . 35

3. Parts Modified and Reidentified . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 35

4. Parts Removed and Not Replaced . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 35

D. Parts Necessary to Change Spares . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 35

E. Special Tooling - Price and Availability . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 35

F. Special Tooling Necessary to do this Service Bulletin . . . . . . . . . . . . . . . . . . . . . . . 35

3. ACCOMPLISHMENT INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 37

A. GENERAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 37

B. WORK INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 38

FIGURE 1: LFEC INSPECTION OF S-14 LAP SPLICE LOWER FASTENER ROW [Group 1] . . . . . 40

FIGURE 2: LFEC INSPECTION OF S-14 LAP SPLICE LOWER FASTENER ROW [Group 2] . . . . . 43

APPENDIX A: LOGIC DIAGRAM FOR PARAGRAPH 1.E. COMPLIANCE: TABLE 1: INSPECTION FOR ANY

CRACK AT S-14 LAP SPLICE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 46

APPENDIX B: LOGIC DIAGRAM FOR PARAGRAPH 1.E. COMPLIANCE: TABLE 2: INSPECTION FOR ANY

CRACK AT S-14 LAP SPLICE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 48

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BLANK PAGE
Commercial 

Airplanes 737

Service Bulletin

ALERT

Summary Number: 737-53A1352

Original Issue: October 02, 2015

ATA System: 5331

SUBJECT: FUSELAGE - Skin - S-14 Lap Splice Lower Fastener Row Inspection

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

Widespread Fatigue Damage (WFD) analysis of the 737NG, as required by 14 CFR 26.21(b), has resulted in

the conclusion that the existing 737-600/700/800/900 MPD Section 9, Airworthiness Limitation Instruction (ALI)

inspection program is not sufficient to preclude the occurrence of WFD in the S-14L and S-14R lap splice, lower

fastener rows between STA 360-540 and STA 727-887 as the airplane ages. These lap splices have multiple

adjacent identical details which have the potential for Multi-Site Damage (MSD) and the potential for WFD. 14

CFR 26.21 requires evaluation of such designs for the potential for WFD and implementation of the appropriate

service actions to ensure that WFD is precluded out to the Limit of Validity (LOV). Boeing has not received any

in-service fleet reports of cracks in these lap splices. Accomplishment of the inspections described in this service

bulletin will enable detection and repair of cracks if they should occur, at these lap splices. If widespread fatigue

cracking is not found and repaired, the cracks can rapidly link up and can result in possible rapid decompression

and loss of structural integrity.

This Service Bulletin provides more frequent external inspection of the S-14 lap splices in order to prevent WFD

out to the LOV.

The fuselage skin S-14L and S-14R lap splice lower fastener row between STA 360 to STA 540 and STA 727

to STA 887 has been determined to be structure that is susceptible to WFD.

Boeing Fleet Team Digest 737NG FTD 53-14001 is related to this service bulletin.

Boeing Service Related Problem (SRP) 737NG-SRP-53-00471 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

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Planning Data Affected Reference

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

Group 1:

1. Do PART 1: Low Frequency Eddy Current (LFEC) Inspection for any crack on the S-14L and S-14R

lap splice, lower fastener row, between STA 360 to STA 540 and STA 727 to STA 887. If no crack is

found, repeat PART 1: LFEC INSPECTION at the repeat interval in Paragraph 1.E., Compliance. If

any crack is found, contact The Boeing Company to get instructions for S-14 lap splice crack repair

and do the repair.

Group 2:

1. Do PART 1: Low Frequency Eddy Current (LFEC) Inspection for any crack on S-14L lap splice, lower

fastener row, between STA 500 to STA 540 and STA 727 to STA 887 and S-14R lap splice, lower

fastener row, between STA 360 to STA 540 and STA 727 to STA 887. If no crack is found, repeat

PART 1: LFEC INSPECTION at the repeat interval in Paragraph 1.E., Compliance. If any crack is

found, contact The Boeing Company for repair instructions and do the repair.

EFFECTIVITY

All 737-600/-700/-700C/-800/-900/-900ER Airplanes. Refer to Paragraph 1.A.1., Airplanes, for the list of affected

airplanes.

COMPLIANCE

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

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

mandatory.

Federal Aviation Administration (FAA) Airworthiness Directive AD 2013-19-23 is related to this service bulletin.

The effective date of AD 2013-19-23 is November 7, 2013.

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BOEING SERVICE BULLETIN 737-53A1352

ALERT ALERT
This service bulletin affects Principle Structural Element (PSE) 53-30-04-6, 53-30-04-6a, 53-60-04-6 and

53-60-04-6a of Subsection B, Airworthiness Limitations-Structural Inspections of 737-600/700/800/900 MPD

Section 9, which is mandated by AD 2013-19-23.

Refer to Paragraph 1.E., Compliance.

INDUSTRY SUPPORT INFORMATION

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

MANPOWER

Refer to Paragraph 1.G., Manpower.

MATERIAL INFORMATION

None.

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Commercial 

Airplanes 737

Service Bulletin

ALERT

Number: 737-53A1352

Original Issue: October 02, 2015

ATA System: 5331

SUBJECT: FUSELAGE - Skin - S-14 Lap Splice Lower Fastener Row Inspection

THIS BULLETIN IS SENT TO THE OPERATORS OF RECORD OF THE AIRPLANES SHOWN IN PARAGRAPH

1.A., EFFECTIVITY. IF AN AIRPLANE HAS BEEN LEASED OR SOLD, SEND THIS SERVICE BULLETIN TO

THE NEW OPERATOR. IF APPLICABLE SPARES HAVE BEEN SOLD, SEND THIS SERVICE BULLETIN TO

THE NEW OWNER.

1. PLANNING INFORMATION

A. Effectivity

1. Airplanes

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

Serial Number data.

This service bulletin is applicable to all 737-600/-700/-700C/-800/-900/-900ER Airplanes, line

numbers 1-99999 in 2 Groups. The Variable Numbers and Group Information for the applicable

airplanes is given below.

NOTE: The Variable Number table below includes all affected airplanes up to Line Number 6060.

Affected airplanes after Line Number 6060 will be added to the service bulletin's

MyBoeingFleet.com (MBF) "get effectivity" result when they are added to the MBF Fleet

Profile Page.

GROUP CONFIGURATION DESCRIPTION

1 - 737-600/-700/-800/-900/-900ER Passenger airplane.

2 - 737-700C Convertible airplane.

Airplane Models:

737-600, 737-700, 737-700C, 737-800, 737-900, 737-900ER

Variable Number Group

YA001 - YA099 1

YA101 - YA199 1

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Variable Number Group

YA201 - YA211 1

YA221 1

YA231 - YA242 1

YA251 - YA256 1

YA271 - YA272 1

YA291 1

YA301 - YA302 1

YA311 - YA314 1

YA321 - YA323 1

YA336 - YA345 1

YA351 1

YA356 - YA357 1

YA366 - YA367 1

YA371 - YA377 1

YA501 - YA536 1

YA541 - YA552 1

YA571 - YA578 1

YA601 - YA615 1

YA621 - YA622 1

YA626 - YA631 1

YA635 - YA636 1

YA641 - YA642 1

YA645 - YA650 1

YA656 - YA659 1

YA666 - YA667 1

YA671 - YA672 1

YA681 - YA691 1

YA701 - YA710 1

YA721 - YA722 1

YA731 - YA734 1

YA751 - YA756 1

YA801 - YA803 1

YA809 1

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Variable Number Group

YA811 - YA814 1

YA831 - YA835 1

YA841 - YA862 1

YA881 - YA882 1

YA891 - YA892 1

YA961 - YA978 1

YB001 - YB006 1

YB101 - YB132 1

YB151 - YB153 1

YB156 - YB158 1

YB161 - YB164 1

YB171 - YB172 1

YB181 - YB184 1

YB201 - YB208 1

YB271 1

YB276 1

YB301 - YB310 1

YB371 - YB392 1

YB501 - YB502 1

YB521 - YB526 1

YB541 - YB544 1

YB551 1

YB561 - YB598 1

YB601 - YB636 1

YB651 1

YB656 1

YB671 - YB672 1

YB851 - YB863 1

YB871 - YB874 1

YB881 - YB893 1

YB901 - YB903 1

YB911 1

YB961 - YB975 1

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Variable Number Group

YB981 1

YB986 - YB998 1

YC001 - YC030 1

YC051 - YC084 1

YC091 - YC095 1

YC101 - YC104 1

YC111 - YC113 1

YC121 1

YC126 - YC127 1

YC136 - YC141 1

YC146 - YC147 1

YC151 - YC156 1

YC166 - YC171 1

YC176 - YC179 1

YC186 - YC190 1

YC201 - YC203 1

YC206 - YC207 1

YC301 - YC305 1

YC321 - YC387 1

YC391 - YC394 1

YC396 1

YC401 - YC417 1

YC421 - YC422 1

YC426 - YC428 1

YC436 - YC439 1

YC441 - YC448 1

YC451 - YC455 1

YC459 1

YC461 - YC467 1

YC471 - YC499 1

YC501 - YC526 1

YC571 - YC583 1

YC587 - YC589 1

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Variable Number Group

YC591 - YC593 1

YC601 - YC655 1

YC681 - YC696 1

YC701 - YC715 1

YC720 - YC725 1

YC727 - YC752 1

YC761 - YC770 1

YC781 - YC793 1

YC801 - YC892 1

YC901 - YC907 1

YC921 - YC922 1

YC931 - YC932 1

YC941 - YC951 1

YC971 - YC978 1

YC981 - YC983 1

YD001 - YD007 1

YD021 - YD025 1

YD041 - YD057 1

YD081 - YD084 1

YD101 - YD117 1

YD121 - YD126 1

YD151 - YD159 1

YD171 - YD172 1

YD201 - YD203 1

YD206 - YD209 1

YD216 - YD219 1

YD251 - YD254 1

YD256 - YD257 1

YD261 1

YD301 - YD334 1

YD391 1

YD401 - YD410 1

YD412 - YD422 1

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Variable Number Group

YD481 - YD485 1

YD491 - YD499 1

YD501 - YD512 1

YD531 - YD535 1

YD541 - YD547 1

YD561 - YD564 1

YD571 - YD572 1

YD591 - YD595 1

YD601 - YD612 1

YD651 - YD655 1

YE001 - YE020 1

YE051 1

YE101 - YE109 1

YE151 - YE157 1

YE171 - YE172 1

YE201 - YE206 1

YE301 - YE305 1

YE321 - YE326 1

YE371 - YE383 1

YF001 - YF011 1

YF021 - YF049 1

YF051 - YF080 1

YF086 - YF087 1

YF106 - YF107 1

YF111 - YF114 1

YF116 - YF119 1

YF121 - YF132 1

YF176 - YF178 1

YF191 - YF192 1

YF201 - YF276 1

YF401 - YF402 1

YF431 - YF432 1

YF436 - YF437 1

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Variable Number Group

YF441 - YF442 1

YF451 - YF460 1

YF501 - YF599 1

YF601 - YF682 1

YF701 - YF707 1

YF801 - YF805 1

YF831 - YF832 1

YF836 - YF838 1

YF871 - YF872 1

YF901 - YF905 1

YF921 - YF928 1

YF951 - YF954 1

YG001 - YG044 1

YG061 - YG064 1

YG066 - YG089 1

YG091 - YG099 1

YG101 - YG104 1

YG111 - YG114 1

YG116 - YG143 1

YG146 1

YG201 - YG205 1

YG211 - YG214 1

YG221 - YG224 1

YG251 - YG252 1

YG501 - YG513 2

YG515 2

YG601 - YG602 2

YG701 2

YG711 2

YG721 - YG722 2

YH001 - YH012 1

YH031 - YH055 1

YH071 - YH080 1

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Variable Number Group

YH101 - YH132 1

YH201 - YH202 1

YH206 - YH207 1

YH301 - YH306 1

YH321 - YH322 1

YH501 - YH542 1

YH551 - YH594 1

YH601 - YH606 1

YH611 - YH620 1

YH631 - YH632 1

YH636 - YH637 1

YH641 1

YH681 - YH683 1

YH701 - YH732 1

YH735 - YH742 1

YH751 - YH754 1

YH801 - YH843 1

YH851 - YH858 1

YH901 - YH908 1

YH911 - YH915 1

YH951 - YH952 1

YJ001 - YJ013 1

YJ021 1

YJ471 - YJ480 1

YJ501 - YJ517 1

YJ531 - YJ579 1

YJ591 - YJ599 1

YJ631 - YJ632 1

YJ671 - YJ694 1

YJ801 - YJ867 1

YJ871 - YJ880 1

YJ901 - YJ904 1

YJ908 - YJ929 1

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Variable Number Group

YJ931 - YJ937 1

YJ941 - YJ956 1

YJ961 1

YJ976 - YJ977 1

YK001 - YK007 1

YK101 - YK104 1

YK111 - YK112 1

YK121 - YK122 1

YK131 - YK133 1

YK136 - YK139 1

YK141 - YK142 1

YK146 - YK148 1

YK151 - YK154 1

YK161 - YK167 1

YK171 1

YK176 - YK177 1

YK186 1

YK191 1

YK196 1

YK201 - YK202 1

YK301 - YK314 1

YK321 - YK340 1

YK361 - YK378 1

YK401 - YK406 1

YK426 - YK427 1

YK431 - YK450 1

YK456 - YK467 1

YK471 - YK473 1

YK476 1

YK480 - YK487 1

YK491 - YK493 1

YK495 - YK499 1

YK511 - YK516 1

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Variable Number Group

YK521 - YK530 1

YK551 - YK571 1

YK576 - YK577 1

YK580 - YK585 1

YK601 - YK602 1

YK606 - YK607 1

YK611 - YK616 1

YK621 - YK634 1

YK641 - YK644 1

YK651 - YK665 1

YK671 - YK672 1

YK676 - YK677 1

YK681 - YK686 1

YK691 1

YK695 - YK699 1

YK701 - YK713 1

YK716 - YK719 1

YK721 - YK741 1

YK751 - YK770 1

YK776 - YK778 1

YK781 - YK785 1

YK791 - YK792 1

YK796 - YK797 1

YK801 - YK899 1

YK901 - YK912 1

YK918 - YK919 1

YK921 - YK929 1

YK941 - YK999 1

YL001 - YL005 1

YL011 - YL016 1

YL021 - YL024 1

YL051 - YL052 1

YL056 - YL057 1

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ALERT ALERT
Variable Number Group

YL061 1

YL066 - YL069 1

YL076 - YL077 1

YL101 - YL137 1

YL201 - YL237 1

YL241 - YL242 1

YL271 - YL272 1

YL281 - YL284 1

YL301 - YL303 1

YL311 - YL314 1

YL316 - YL321 1

YL351 - YL353 1

YL371 - YL374 1

YL401 1

YL421 - YL429 1

YL431 - YL444 1

YL461 - YL478 1

YL501 - YL509 1

YL531 - YL534 1

YL541 - YL551 1

YL561 - YL579 1

YL591 - YL598 1

YL601 - YL606 1

YL611 - YL612 1

YL616 - YL617 1

YL621 1

YL626 1

YL631 - YL634 1

YL636 - YL637 1

YL661 - YL664 1

YL676 - YL691 1

YL696 - YL697 1

YL701 - YL707 1

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ALERT ALERT
Variable Number Group

YL731 1

YL751 - YL752 1

YL756 - YL757 1

YL761 - YL780 1

YL796 - YL797 1

YL801 - YL815 1

YL901 - YL910 1

YL921 - YL940 1

YL951 - YL968 1

YM101 - YM103 1

YM201 - YM244 1

YM251 - YM299 1

YM301 - YM399 1

YM401 - YM415 1

YM471 1

YM481 - YM484 1

YM501 - YM515 1

YM521 - YM522 1

YM541 1

YM551 - YM553 1

YM571 - YM572 1

YM581 - YM582 1

YM591 - YM599 1

YM631 - YM634 1

YM641 - YM652 1

YM671 - YM674 1

YM691 - YM699 1

YM701 - YM710 1

YM761 - YM765 1

YM771 - YM779 1

YN001 - YN016 1

YN021 - YN024 1

YN061 1

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ALERT ALERT
Variable Number Group

YN071 - YN082 1

YN091 - YN092 1

YN101 - YN112 1

YN121 1

YN126 1

YN201 - YN202 1

YN211 - YN219 1

YN231 - YN236 1

YN261 1

YN501 1

YN531 - YN534 1

YN551 - YN564 1

YN581 - YN585 1

YN591 - YN592 1

YN601 - YN606 1

YN651 - YN653 1

YN701 - YN702 1

YN741 - YN746 1

YN756 1

YQ001 - YQ003 1

YQ011 - YQ021 1

YQ026 - YQ029 1

YQ036 - YQ045 1

YQ201 - YQ207 1

YQ231 1

YQ241 - YQ251 1

YQ281 - YQ284 1

YQ291 - YQ296 1

YQ301 - YQ302 1

YQ321 - YQ324 1

YQ331 - YQ334 1

YQ346 - YQ347 1

YQ351 1

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ALERT ALERT
Variable Number Group

YQ354 - YQ355 1

YQ362 1

YQ371 1

YQ401 - YQ403 1

YQ451 - YQ454 1

YQ456 1

YQ461 1

YQ471 1

YQ501 - YQ520 1

YR001 - YR043 1

YR045 1

YR051 - YR087 1

YR090 - YR098 1

YR101 - YR105 1

YR111 - YR124 1

YR126 - YR144 1

YR166 - YR182 1

YR186 - YR198 1

YR201 - YR205 1

YR231 - YR294 1

YR296 - YR297 1

YR301 - YR334 1

YR338 - YR341 1

YR361 - YR366 1

YR371 - YR373 1

YR376 1

YR381 - YR382 1

YR386 - YR388 1

YR391 1

YR396 - YR398 1

YR401 - YR405 1

YR411 - YR413 1

YR416 - YR418 1

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Variable Number Group

YR421 - YR424 1

YR426 - YR455 1

YR457 - YR499 1

YR501 - YR506 1

YR511 - YR520 1

YR526 - YR544 1

YR546 - YR551 1

YR556 - YR562 1

YR571 - YR582 1

YR591 - YR592 1

YR601 - YR605 1

YR616 - YR658 1

YR661 - YR663 1

YR671 - YR672 1

YR676 - YR678 1

YR681 - YR682 1

YR701 - YR769 1

YR771 - YR799 1

YR801 - YR816 1

YR831 - YR838 1

YR841 - YR898 1

YR901 - YR903 1

YR931 - YR934 1

YR938 - YR944 1

YR951 - YR979 1

YR981 - YR996 1

YS001 - YS002 1

YS006 - YS009 1

YS031 - YS032 1

YS051 - YS073 1

YS101 - YS120 1

YS126 - YS138 1

YS149 - YS160 1

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Variable Number Group

YS166 - YS194 1

YS196 - YS197 1

YS201 - YS209 1

YS221 - YS225 1

YS231 - YS236 1

YS271 - YS287 1

YS301 - YS334 1

YS343 - YS347 1

YS351 - YS365 1

YS369 1

YS371 - YS374 1

YS377 1

YS381 - YS383 1

YS401 1

YS451 1

YS456 - YS457 1

YS462 1

YS467 1

YS501 - YS502 1

YS506 1

YS511 - YS513 1

YS515 - YS516 1

YS531 1

YS538 1

YS541 1

YS551 - YS553 1

YS556 1

YS561 - YS578 1

YS581 - YS595 1

YS601 - YS690 1

YS701 - YS708 1

YS721 - YS759 1

YS761 - YS762 1

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Variable Number Group

YS771 - YS780 1

YS806 - YS810 1

YS816 - YS818 1

YS823 - YS825 1

YS851 - YS860 1

YS876 1

YS881 - YS883 1

YS901 - YS909 1

YS911 - YS928 1

YS938 - YS939 1

YS951 1

YS956 - YS957 1

YS961 - YS965 1

YS981 - YS983 1

YS991 - YS998 1

YT001 - YT004 1

YT006 1

YT026 - YT027 1

YT031 - YT032 1

YT036 - YT038 1

YT061 - YT068 1

YT101 - YT112 1

YT115 - YT117 1

YT126 - YT130 1

YT136 - YT138 1

YT176 - YT181 1

YT191 1

YT196 - YT199 1

YT201 1

YT206 - YT207 1

YT211 - YT213 1

YT251 - YT271 1

YT278 - YT287 1

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Variable Number Group

YT301 - YT304 1

YT306 - YT307 1

YT311 - YT312 1

YT321 - YT328 1

YT340 - YT342 1

YT381 1

YT391 1

YT395 1

YT401 - YT403 1

YT411 - YT415 1

YT427 1

YT461 - YT471 1

YT475 1

YT491 - YT492 1

YT501 - YT504 1

YT516 - YT521 1

YT551 1

YT556 1

YT558 - YT561 1

YT563 1

YT571 - YT572 1

YT601 - YT606 1

YT701 - YT702 1

YT705 - YT706 1

YT761 - YT780 1

YT791 1

YT796 1

YT801 - YT804 1

YT811 - YT813 1

YT831 1

YT852 1

YT856 - YT862 1

YT891 - YT894 1

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ALERT ALERT
Variable Number Group

YT901 - YT908 1

YT915 - YT925 1

YU001 - YU046 1

YU053 - YU054 1

YU201 - YU212 1

YV001 1

YV045 1

YV081 1

YV083 1

YV101 - YV106 1

YV115 - YV121 1

YV351 - YV353 1

YV356 - YV358 1

YV381 1

YV383 1

YV501 1

YV521 1

YV571 1

YV575 1

YV651 - YV654 1

YV695 1

YV741 - YV743 1

YV781 1

YV801 - YV802 1

YW011 - YW040 1

YW261 1

2. Spares Affected

None.

B. Concurrent Requirements

None.

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C. Reason

Widespread Fatigue Damage (WFD) analysis of the 737NG, as required by 14 CFR 26.21(b), has

resulted in the conclusion that the existing 737-600/700/800/900 MPD Section 9, Airworthiness Limitation

Instruction (ALI) inspection program is not sufficient to preclude the occurrence of WFD in the S-14L

and S-14R lap splice, lower fastener rows between STA 360-540 and STA 727-887 as the airplane

ages. These lap splices have multiple adjacent identical details which have the potential for Multi-Site

Damage (MSD) and the potential for WFD. 14 CFR 26.21 requires evaluation of such designs for the

potential for WFD and implementation of the appropriate service actions to ensure that WFD is precluded

out to the Limit of Validity (LOV). Boeing has not received any in-service fleet reports of cracks in these

lap splices. Accomplishment of the inspections described in this service bulletin will enable detection

and repair of cracks if they should occur, at these lap splices. If widespread fatigue cracking is not

found and repaired, the cracks can rapidly link up and can result in possible rapid decompression and

loss of structural integrity.

This Service Bulletin gives a more frequent inspection for the S-14 lap splices to prevent WFD out to

the LOV.

The fuselage skin S-14L and S-14R lap splice lower fastener row between STA 360 to STA 540 and

STA 727 to STA 887 has been determined to be structure that is susceptible to WFD.

Boeing Fleet Team Digest 737NG FTD 53-14001 is related to this service bulletin.

Boeing Service Related Problem 737NG-SRP-53-00471 is related to this service bulletin.

D. Description

Group 1:

1. Do PART 1: Low Frequency Eddy Current (LFEC) Inspection for any crack on the S-14L and

S-14R lap splice, lower fastener row, between STA 360 to STA 540 and STA 727 to STA 887. If

no crack is found, repeat PART 1: LFEC INSPECTION at the repeat interval in Paragraph 1.E.,

Compliance. If any crack is found, contact The Boeing Company for repair instructions and do the

repair.

Group 2:

1. Do PART 1: Low Frequency Eddy Current (LFEC) Inspection for any crack on the S-14L lap splice,

lower fastener row, between STA 500 to STA 540 and STA 727 to STA 887 and S-14R lap splice,

lower fastener row, between STA 360 to STA 540 and STA 727 to STA 887. If no crack is found,

repeat PART 1: LFEC INSPECTION at the repeat interval in Paragraph 1.E., Compliance. If any

crack is found, contact The Boeing Company for repair instructions and do the repair.

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

Group 1:

Affected Maintenance Zones

Model Zone

737-600, 737-700, 737-800, 231, 232, 241, 242

737-900, 737-900ER

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Group 2:

Affected Maintenance Zones

Model Zone

737-700C 231, 232, 241, 242

E. Compliance

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

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

service bulletin mandatory.

Federal Aviation Administration (FAA) Airworthiness Directive AD 2013-19-23 is related to this service

bulletin. The effective date of AD 2013-19-23 is November 7, 2013.

For airplanes which have not incorporated Boeing Business Jet Lower Cabin Altitude (LCA) Supplemental

Type Certificate ST01697SE (6,500 feet maximum cabin altitude in lieu of 8,000 feet) as referenced

in Boeing Service Bulletin 737-21-1149. This service bulletin affects Principle Structural Element (PSE)

53-30-04-6, 53-30-04-6a, 53-60-04-6, and 53-60-04-6a of Subsection B, Airworthiness

Limitations-Structural Inspections of 737-600/700/800/900 MPD Section 9 C626A001-CMR Table 9-2,

which is mandated by AD 2013-19-23.

For airplanes which have incorporated Boeing Business Jet Lower Cabin Altitude (LCA) Supplemental

Type Certificate ST01697SE (6,500 feet maximum cabin altitude in lieu of 8,000 feet) as referenced

in Boeing Service Bulletin 737-21-1149. This service bulletin affects Principle Structural Element (PSE)

53-30-04-6 and 53-60-04-6 of Subsection B, Airworthiness Limitations-Structural Inspections of

737-600/700/800/900 MPD Section 9 626A001-CMR Table 9-3, which is mandated by AD 2013-19-23.

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

A logic diagram showing compliance tasks and compliance times is included as an aid in APPENDIX

A and APPENDIX B.

Table 1: Inspection For Any Crack at S-14 Lap Splice

Repeat Interval

(Not to Exceed)

Condition Action Compliance Time

Before 54,000 To- -

tal Flight Cycles.

Do PART 1: LFEC INSPECTION for any crack.Airplanes that have not accomplished Boeing Service

Bulletin 737-21-1149.

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Table 1: Inspection For Any Crack at S-14 Lap Splice

Repeat Interval

(Not to Exceed)

Condition Action Compliance Time

Before further -

flight.

ACTION 1:

Contact The Boeing

Company for repair instructions and do the repair.

CONDITION 1:

ANY CRACK FOUND

12,000 Flight Cycles.ACTION 2: -

Repeat PART 1: LFEC

INSPECTION for any

crack at the unrepaired

areas.

12,000 Flight Cycles.Repeat PART 1: LFEC -

INSPECTION for any

crack.

CONDITION 2:

NO CRACK FOUND

Table 2: Inspection For Any Crack at S-14 Lap Splice

Repeat Interval

(Not to Exceed)

Condition Action Compliance Time

Before 41,000 To- -

tal Flight Cycles.

Do PART 1: LFEC INSPECTION for any crack.Airplanes that have accomplished Boeing Service

Bulletin 737-21-1149.

Before further -

flight.

ACTION 1:

Contact The Boeing

Company for repair instructions and do the repair.

CONDITION 1:

ANY CRACK FOUND

8,800 Flight Cycles.ACTION 2: -

Repeat PART 1: LFEC

INSPECTION for any

crack at the unrepaired

areas.

8,800 Flight Cycles.Repeat PART 1: LFEC -

INSPECTION for any

crack.

CONDITION 3:

NO CRACK FOUND

F. Approval

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

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

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

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

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

changes.

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This service bulletin is also approved for airplanes having FAA Aviation Partners Boeing (APB)

Supplemental Type Certificate (STC) number ST00830SE installed (not including any areas affected

by the split scimitar winglet configuration).

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, for airplanes which have incorporated Boeing Business Jet Lower Cabin Altitude (LCA)

Supplemental Type Certificate ST01697SE (6,500 feet maximum cabin altitude in lieu of 8,000 feet)

as referenced in Boeing Service Bulletin 737-21-1149, The Manager of the FAA Seattle Aircraft

Certification Office (SACO) approves the accomplishment of the inspections defined in this Service

Bulletin (SB) along with the corresponding compliance times specified in Paragraph 1.E., Compliance,

of this SB, Original Issue as an Alternative Method of Compliance (AMOC) to the inspections, defined

in D626A001-DTR for PSEs 53-30-04-6 and 53-60-04-6, and 737-600/700/800/900 MPD Section 9,

D626A001-CMR Table 9-3, required by paragraph (g) and (h) of Airworthiness Directive (AD) AD

2013-19-23. This AMOC is only applicable after accomplishment of the initial inspections specified in

Paragraph 1.E., Compliance of this service bulletin. All provisions of AD 2013-19-23 that are not

specifically referenced in this paragraph remain fully applicable and must be complied with accordingly.

In addition, for airplanes which have not incorporated Boeing Business Jet Lower Cabin Altitude (LCA)

Supplemental Type Certificate ST01697SE (6,500 feet maximum cabin altitude in lieu of 8,000 feet)

as referenced in Boeing Service Bulletin 737-21-1149, The Manager of the FAA Seattle Aircraft

Certification Office (SACO) approves the accomplishment of the inspections defined in this Service

Bulletin (SB) along with the corresponding compliance times specified in Paragraph 1.E., Compliance,

of this SB, Original Issue as an Alternative Method of Compliance (AMOC) to the inspections, defined

in D626A001-DTR for PSEs 53-30-04-6, 53-30-04-6a, 53-60-04-6, and 53-60-04-6a, and

737-600/700/800/900 MPD Section 9 D626A001-CMR Table 9-2, required by paragraph (g) and (h)

of Airworthiness Directive (AD) AD 2013-19-23. This AMOC is only applicable after accomplishment

of the initial inspections specified in Paragraph 1.E., Compliance of this service bulletin. All provisions

of AD 2013-19-23 that are not specifically referenced in this paragraph 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 inspection for each airplane.

This estimate is for direct labor only, done by an experienced crew. Adjust the estimate with operator

task hour data if necessary. The estimate does not include lost time. These are some examples of lost

time:

• Time to adjust to the workplace

• Time to schedule the work

• Time to inspect the work

• Time to cure the materials

• Time to make the parts

• Time to find the tools.

Group 1:

Task Number of Persons Task Hours Elapsed Hours

Figure 1 2 84.00 42.00

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Group 1:

Task Number of Persons Task Hours Elapsed Hours

TOTAL FOR EACH AIRPLANE 84.00 42.00

Group 2:

Task Number of Persons Task Hours Elapsed Hours

Figure 2 2 65.00 32.50

TOTAL FOR EACH AIRPLANE 65.00 32.50

H. Weight and Balance Changes

None.

I. Electrical Load Data

Not applicable.

J. References

1. Existing Data:

a. Boeing Service Bulletin 737-21-1149

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

c. Boeing Service Related Problem (SRP) 737NG-SRP-53-00471

d. Federal Aviation Administration (FAA) Airworthiness Directive (AD) 2013-19-23

e. Service Bulletin Index D6-19567

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

g. 737 Non-Destructive Testing (NDT) Manual Part 6, 53-30-50

h. 737-600/700/800/900 Maintenance Planning Data (MPD) Section 9

i. 737NG Fleet Team Digest (FTD) 53-14001

2. Data Supplied with this Service Bulletin:

None.

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

Drawing Number Title

142A3000 Skin Installation - STA 259.5 to STA 540, S-24L to S-4R

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Drawing Number Title

143A3150 Skin Installation - S-10 to S-14, STA 360 to 540

143A3210 Skin Installation - STA 360 to 540, S-14L to S-24L

143A3250 Skin Installation - STA 360 to 540, S-14R to S-24R

146A3150 Skin Installation, S-10 to S-14, Station 727-888

146A3200 Skin Installation, S-14L to S-23L, Station 727-888

146A3250 Skin Installation, S-14R to S-23R, Station 727-888

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

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

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

K. Publications Affected

1. Publications:

None.

2. Damage Tolerance Based Structural Inspections:

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

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

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

L. Interchangeability and Intermixability of Parts

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

M. Software Accomplishment Summary

Not affected.

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BLANK PAGE
2. MATERIAL INFORMATION

A. Material - Price and Availability

None.

B. Industry Support Information

Boeing warranty remedies are not available for the inspection 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 the change in this service bulletin. But maintenance

and overhaul tools in the manuals given in Paragraph 1.J., References, can also 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

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

Aircraft 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. 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.

8. 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.

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9. Refer to APPENDIX A and APPENDIX B for logic diagram. 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.

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. Use of colors in Figures is based on guidance from the ATA e-Business Program

(ATA) iSpec 2200.

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

are in Paragraph 1.E., Compliance.

14. The CONDITIONS, ACTIONS and OPTIONS shown apply to each S-14 Lap Splice

independently.

15. Some steps in the Work Instructions are labeled as Required for Compliance (RC).

If this service bulletin is mandated by an Airworthiness Directive (AD), then the steps

labeled as RC, including sub-steps under an RC step and any figures identified in

an RC step, must be done to comply with the AD. An Alternative Method of

Compliance (AMOC) is required for any deviations to RC steps, including sub-steps

and identified figures. Steps not labeled as RC may be deviated from using accepted

methods in accordance with the operator's maintenance or inspection program without

obtaining approval of an AMOC. This is provided that the RC steps, including

sub-steps and identified figures, can still be done as specified, and the airplane can

be put back in an airworthy condition.

B. WORK INSTRUCTIONS

1. Airplanes that have not accomplished Boeing Service Bulletin 737-21-1149, Boeing Business Jet

Lower Cabin Altitude (LCA) Supplemental Type Certificate ST01697SE (6,500 feet maximum

cabin altitude in lieu of 8,000 feet).

a. Do PART 1: LFEC INSPECTION for any crack.

(1) CONDITION 1: ANY CRACK FOUND.

(a) ACTION 1: Contact The Boeing Company for repair instructions and do the repair.

(b) ACTION 2: Repeat PART 1: LFEC INSPECTION for any crack at the unrepaired

areas at the repeat interval in Paragraph 1.E., Compliance.

(2) CONDITION 2: NO CRACK FOUND.

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(a) Repeat PART 1: LFEC INSPECTION for any crack at the repeat interval in Paragraph

1.E., Compliance.

2. Airplanes that have accomplished Boeing Service Bulletin 737-21-1149, Boeing Business Jet

Lower Cabin Altitude (LCA) Supplemental Type Certificate ST01697SE (6,500 feet maximum

cabin altitude in lieu of 8,000 feet).

a. Do PART 1: LFEC INSPECTION for any crack.

(1) CONDITION 1: ANY CRACK FOUND.

(a) ACTION 1:Contact The Boeing Company for repair instructions and do the repair.

(b) ACTION 2: Repeat PART 1: LFEC INSPECTION for any crack at the unrepaired

areas at the repeat interval in Paragraph 1.E., Compliance.

(2) CONDITION 3: NO CRACK FOUND.

(a) Repeat PART 1: LFEC INSPECTION for any crack at the repeat interval in Paragraph

1.E., Compliance.

3. Put the airplane back to a serviceable condition.

PART 1: LFEC INSPECTION

1. RC - Do Low Frequency Eddy Current (LFEC) inspection for any crack at S-14L and S-14R lap

splice for any crack at lower fastener row in accordance with 737 NDT Manual Part 6, 53-30-50

and the table below:

Group Figure

1 FIGURE 1

2 FIGURE 2

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This Figure applies only to: Group 1.

FIGURE 1: LFEC INSPECTION OF S-14 LAP SPLICE LOWER FASTENER ROW

(SHEET 1 OF 3)

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FIGURE 1: LFEC INSPECTION OF S-14 LAP SPLICE LOWER FASTENER ROW

(SHEET 2 OF 3)

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

numbers shown below are by location identification provided.

More

Data

Step Task Name Location

S-14L Lap Between STA 360 to STA 540 (a)

Splice

1 Inspect

S-14R Lap Between STA 360 to STA 540 (a)

Splice

Inspect

S-14L Lap Between STA 727 to STA 887 (a)

Splice

2 Inspect

S-14R Lap Between STA 727 to STA 887 (a)

Splice

Inspect

(a) In accordance with 737 NDT Manual Part 6, 53-30-50.

FIGURE 1: LFEC INSPECTION OF S-14 LAP SPLICE LOWER FASTENER ROW

(SHEET 3 OF 3)

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This Figure applies only to: Group 2.

FIGURE 2: LFEC INSPECTION OF S-14 LAP SPLICE LOWER FASTENER ROW

(SHEET 1 OF 3)

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FIGURE 2: LFEC INSPECTION OF S-14 LAP SPLICE LOWER FASTENER ROW

(SHEET 2 OF 3)

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

numbers shown below are by location identification provided.

More

Data

Step Task Name Location

S-14L Lap Between STA 500 and STA 540 (a)

Splice

1 Inspect

S-14R Lap Between STA 360 and STA 540 (a)

Splice

Inspect

S-14L Lap Between STA 727 and STA 887 (a)

Splice

2 Inspect

S-14R Lap Between STA 727 and STA 887 (a)

Splice

Inspect

(a) In accordance with 737 NDT Manual Part 6, 53-30-50.

FIGURE 2: LFEC INSPECTION OF S-14 LAP SPLICE LOWER FASTENER ROW

(SHEET 3 OF 3)

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ALERT ALERT
Logic diagrams are provided as an aid only. Information contained in Paragraph 1.E., Compliance is the primary

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

for tasks required for compliance.

1. The table below gives the description for the parts and conditions called out in the logic diagrams.

Title Description

PART 1: LFEC INSPECTION for any crack.

CONDITION 1: ANY CRACK FOUND

ACTION 1: Contact The Boeing Company for repair instructions and do the repair.

ACTION 2: Repeat PART 1: LFEC INSPECTION for any crack at the unrepaired areas.

CONDITION 2: NO CRACK FOUND

APPENDIX A: LOGIC DIAGRAM FOR PARAGRAPH 1.E. COMPLIANCE: TABLE 1: INSPECTION FOR ANY

CRACK AT S-14 LAP SPLICE

(SHEET 1 OF 2)

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APPENDIX A: LOGIC DIAGRAM FOR PARAGRAPH 1.E. COMPLIANCE: TABLE 1: INSPECTION FOR ANY

CRACK AT S-14 LAP SPLICE

(SHEET 2 OF 2)

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ALERT ALERT
Logic diagrams are provided as an aid only. Information contained in Paragraph 1.E., Compliance is the primary

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

for tasks required for compliance.

1. The table below gives the description for the parts and conditions called out in the logic diagrams.

Title Description

PART 1: LFEC INSPECTION for any crack.

CONDITION 1: ANY CRACK FOUND

ACTION 1: Contact The Boeing Company for repair instructions and do the repair.

ACTION 2: Repeat PART 1: LFEC INSPECTION for any crack at the unrepaired areas.

CONDITION 3: NO CRACK FOUND

APPENDIX B: LOGIC DIAGRAM FOR PARAGRAPH 1.E. COMPLIANCE: TABLE 2: INSPECTION FOR ANY

CRACK AT S-14 LAP SPLICE

(SHEET 1 OF 2)

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APPENDIX B: LOGIC DIAGRAM FOR PARAGRAPH 1.E. COMPLIANCE: TABLE 2: INSPECTION FOR ANY

CRACK AT S-14 LAP SPLICE

(SHEET 2 OF 2)

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ALERT ALERT