Commercial 

Airplanes 737

Service Bulletin

ALERT

Number: 737-53A1351

Original Issue: July 08, 2015

ATA System: 5330

SUBJECT: FUSELAGE - Skin - Window Corner 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Unpublished Work.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

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Boeing Company.

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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 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 27

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

E. Compliance . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 28

F. Approval . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 32

G. Manpower . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 32

H. Weight and Balance Changes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 33

I. Electrical Load Data . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 33

J. References . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 33

1. Existing Data: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 33

2. Data Supplied with this Service Bulletin: . . . . . . . . . . . . . . . . . . . . . . . . . . . 33

3. Installation Drawings Used in the Preparation of this Service Bulletin: . . . . . . . . . . . 33

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

L. Interchangeability and Intermixability of Parts . . . . . . . . . . . . . . . . . . . . . . . . . . . 34

M. Software Accomplishment Summary . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 34

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: EXTERNAL INSPECTION OF THE UPPER FORWARD AND LOWER AFT WINDOW CORNER,

STA 360 TO STA 540 LEFT SIDE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 40

FIGURE 2: EXTERNAL INSPECTION OF THE UPPER FORWARD AND LOWER AFT WINDOW CORNER,

STA 360 TO STA 540 RIGHT SIDE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 42

FIGURE 3: EXTERNAL INSPECTION OF THE LOWER FORWARD AND UPPER AFT WINDOW CORNER,

STA 727 TO STA 887 LEFT SIDE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 44

FIGURE 4: EXTERNAL INSPECTION OF THE LOWER FORWARD AND UPPER AFT WINDOW CORNER,

STA 727 TO STA 887 RIGHT SIDE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 46

APPENDIX A: LOGIC DIAGRAM FOR PARAGRAPH 1.E., COMPLIANCE: TABLE 1: WINDOW CORNER

EXTERNAL INSPECTION FROM STA 360 TO STA 540 AND FROM STA 727 TO STA 887

[Group 1] . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 48

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ALERT ALERT
APPENDIX B: LOGIC DIAGRAM FOR PARAGRAPH 1.E., COMPLIANCE: TABLE 2: WINDOW CORNER

EXTERNAL INSPECTION FROM STA 360 TO STA 540 AND FROM STA 727 TO STA 887

[Group 2] . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 50

APPENDIX C: LOGIC DIAGRAM FOR PARAGRAPH 1.E., COMPLIANCE: TABLE 3: WINDOW CORNER

EXTERNAL INSPECTION FROM STA 360 TO STA 540 AND FROM STA 727 TO STA 887

[Group 3] . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 52

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ALERT ALERT
Commercial 

Airplanes 737

Service Bulletin

ALERT

Summary Number: 737-53A1351

Original Issue: July 08, 2015

ATA System: 5330

SUBJECT: FUSELAGE - Skin - Window Corner 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

This service bulletin gives instructions to inspect for any crack in the skin around fasteners in window corners

from STA 360 to STA 540 and from STA 727 to STA 887, left and right side between stringers S-10 and S-14.

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

the conclusion that the existing MPD Section 9, Airworthiness Limitation Instruction (ALI) inspection program is

not sufficient to preclude the occurrence of WFD in the window corner surround structure from STA 360 to STA

540 and from STA 727 to STA 887, left and right sides between S-10 and S-14, as the airplane ages. The window

corner surround structure has multiple adjacent identical details which have the potential for Multi-Element

Damage (MED) 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). Accomplishment of the inspections described in this service bulletin will enable detection and

repair of cracks if they should occur, at the window corner surround structure. Boeing has not received any

in-service fleet reports of cracks in the window corner surround structure. 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.

The window corner surround structure from STA 360 to STA 540 and from STA 727 to STA 887, left and right

sides between S-10 and S-14, 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-53-0474 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

Do an external High Frequency Eddy Current (HFEC) inspection of the skin around fasteners in window corners

from STA 360 to STA 540 and from STA 727 to STA 887. If no crack is found, do repeat inspections. If any

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

EFFECTIVITY

All 737-600, -700, -700C, -800, -900, and -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.

This service bulletin affects Principle Structural Element (PSE) 53-30-05-1, 53-30-05-2, 53-30-05-3, 53-60-05-1,

53-60-05-2, and 53-60-05-3 of Subsection B, Airworthiness Limitations-Structural Inspections of Section 9 of

the 737-600/700/800/900 MPD 626A001-CMR, 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 given in this service bulletin.

MANPOWER

Refer to Paragraph 1.G., Manpower.

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MATERIAL INFORMATION

None.

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BLANK PAGE
Commercial 

Airplanes 737

Service Bulletin

ALERT

Number: 737-53A1351

Original Issue: July 08, 2015

ATA System: 5330

SUBJECT: FUSELAGE - Skin - Window Corner 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 737-600/-700/-700C/-800/-900/-900ER Airplanes, line numbers

1-99999 in 3 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 airplanes.

2 - 737-700C/900 airplanes.

3 - 737-800/900ER airplanes.

Airplane Models:

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

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Variable Number Group

YA001 - YA099 1

YA101 - YA199 1

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

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Variable Number Group

YA751 - YA756 1

YA801 - YA803 1

YA809 1

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

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Variable Number Group

YB901 - YB903 1

YB911 1

YB961 - YB975 1

YB981 1

YB986 - YB998 1

YC001 - YC030 3

YC051 - YC084 3

YC091 - YC095 3

YC101 - YC104 3

YC111 - YC113 3

YC121 3

YC126 - YC127 3

YC136 - YC141 3

YC146 - YC147 3

YC151 - YC156 3

YC166 - YC171 3

YC176 - YC179 3

YC186 - YC190 3

YC201 - YC203 3

YC206 - YC207 3

YC301 - YC305 3

YC321 - YC387 3

YC391 - YC394 3

YC396 3

YC401 - YC417 3

YC421 - YC422 3

YC426 - YC428 3

YC436 - YC439 3

YC441 - YC448 3

YC451 - YC455 3

YC459 3

YC461 - YC467 3

YC471 - YC499 3

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Variable Number Group

YC501 - YC526 3

YC571 - YC583 3

YC587 - YC589 3

YC591 - YC593 3

YC601 - YC655 3

YC681 - YC696 3

YC701 - YC715 3

YC720 - YC725 3

YC727 - YC752 3

YC761 - YC770 3

YC781 - YC793 3

YC801 - YC892 3

YC901 - YC907 3

YC921 - YC922 3

YC931 - YC932 3

YC941 - YC951 3

YC971 - YC978 3

YC981 - YC983 3

YD001 - YD007 3

YD021 - YD025 3

YD041 - YD057 3

YD081 - YD084 3

YD101 - YD117 3

YD121 - YD126 3

YD151 - YD159 3

YD171 - YD172 3

YD201 - YD203 3

YD206 - YD209 3

YD216 - YD219 3

YD251 - YD254 3

YD256 - YD257 3

YD261 3

YD301 - YD334 3

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Variable Number Group

YD391 3

YD401 - YD410 3

YD412 - YD422 3

YD481 - YD485 3

YD491 - YD499 3

YD501 - YD512 2

YD531 - YD535 2

YD541 - YD547 2

YD561 - YD564 2

YD571 - YD572 2

YD591 - YD595 2

YD601 - YD612 2

YD651 - YD655 2

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 3

YF021 - YF049 3

YF051 - YF080 3

YF086 - YF087 3

YF106 - YF107 3

YF111 - YF114 3

YF116 - YF119 3

YF121 - YF132 3

YF176 - YF178 3

YF191 - YF192 3

YF201 - YF276 3

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Variable Number Group

YF401 - YF402 3

YF431 - YF432 3

YF436 - YF437 3

YF441 - YF442 3

YF451 - YF460 3

YF501 - YF599 3

YF601 - YF685 3

YF691 - YF695 3

YF701 - YF707 3

YF801 - YF805 3

YF831 - YF832 3

YF836 - YF838 3

YF871 - YF872 3

YF901 - YF905 3

YF921 - YF928 3

YF951 - YF954 3

YG001 - YG044 1

YG061 - YG064 1

YG066 - YG089 1

YG091 - YG099 1

YG101 - YG104 1

YG111 - YG114 1

YG116 - YG146 1

YG201 - YG205 1

YG211 - YG214 1

YG221 - YG224 1

YG251 - YG252 1

YG501 - YG515 2

YG601 - YG602 2

YG701 2

YG711 2

YG721 - YG722 2

YH001 - YH012 3

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Variable Number Group

YH031 - YH055 3

YH071 - YH080 3

YH101 - YH132 3

YH201 - YH202 3

YH206 - YH207 3

YH301 - YH307 3

YH321 - YH322 3

YH501 - YH542 3

YH551 - YH594 3

YH601 - YH606 3

YH611 - YH620 3

YH631 - YH632 3

YH636 - YH637 3

YH641 3

YH681 - YH683 3

YH701 - YH740 3

YH751 - YH755 3

YH801 - YH856 3

YH901 - YH908 3

YH911 - YH915 3

YH951 - YH952 3

YJ001 - YJ013 3

YJ021 3

YJ471 - YJ480 3

YJ501 - YJ517 3

YJ531 - YJ579 3

YJ591 - YJ599 3

YJ631 - YJ632 3

YJ671 - YJ694 3

YJ801 - YJ867 3

YJ871 - YJ880 3

YJ901 - YJ904 3

YJ908 - YJ929 3

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Variable Number Group

YJ931 - YJ937 3

YJ941 - YJ956 3

YJ961 3

YJ976 - YJ977 3

YK001 - YK007 3

YK101 - YK104 3

YK111 - YK112 3

YK121 - YK122 3

YK131 - YK133 3

YK136 - YK139 3

YK141 - YK142 3

YK146 - YK148 3

YK151 - YK154 3

YK161 - YK167 3

YK171 3

YK176 - YK177 3

YK186 3

YK191 3

YK196 3

YK201 - YK202 3

YK301 - YK314 3

YK321 - YK340 3

YK361 - YK378 3

YK401 - YK406 3

YK426 - YK427 3

YK431 - YK450 3

YK456 - YK467 3

YK471 - YK473 3

YK476 3

YK478 3

YK480 - YK487 3

YK491 - YK493 3

YK495 - YK499 3

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ALERT ALERT
Variable Number Group

YK511 - YK516 3

YK521 - YK530 3

YK551 - YK571 3

YK576 - YK577 3

YK580 - YK585 3

YK601 - YK602 3

YK606 - YK607 3

YK611 - YK616 3

YK621 - YK634 3

YK641 - YK644 3

YK651 - YK665 3

YK671 - YK672 3

YK676 - YK677 3

YK681 - YK686 3

YK691 3

YK695 - YK699 3

YK701 - YK713 3

YK716 - YK719 3

YK721 - YK741 3

YK751 - YK770 3

YK776 - YK778 3

YK781 - YK785 3

YK791 - YK792 3

YK796 - YK797 3

YK801 - YK899 3

YK901 - YK912 3

YK918 - YK919 3

YK921 - YK929 3

YK941 - YK999 3

YL001 - YL005 3

YL011 - YL016 3

YL021 - YL024 3

YL051 - YL052 3

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ALERT ALERT
Variable Number Group

YL056 - YL057 3

YL061 3

YL066 - YL069 3

YL076 - YL077 3

YL101 - YL137 3

YL201 - YL237 3

YL241 - YL242 3

YL271 - YL272 3

YL281 - YL284 3

YL301 - YL303 3

YL311 - YL314 3

YL316 - YL321 3

YL351 - YL353 3

YL371 - YL374 3

YL401 3

YL421 - YL429 3

YL431 - YL444 3

YL461 - YL478 3

YL501 - YL509 3

YL531 - YL534 3

YL541 - YL551 3

YL561 - YL579 3

YL591 - YL598 3

YL601 - YL606 3

YL611 - YL612 3

YL616 - YL617 3

YL621 3

YL626 3

YL631 - YL634 3

YL636 - YL637 3

YL661 - YL664 3

YL676 - YL691 3

YL696 - YL697 3

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ALERT ALERT
Variable Number Group

YL701 - YL707 3

YL731 3

YL751 - YL752 3

YL756 - YL757 3

YL761 - YL780 3

YL796 - YL797 3

YL801 - YL815 3

YL901 - YL910 3

YL921 - YL940 3

YL951 - YL968 3

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

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ALERT ALERT
Variable Number Group

YN061 1

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 - YN566 1

YN581 - YN585 1

YN591 - YN592 1

YN601 - YN606 1

YN651 - YN653 1

YN701 - YN702 1

YN741 - YN746 1

YN756 1

YQ001 - YQ003 3

YQ011 - YQ021 3

YQ026 - YQ029 3

YQ036 - YQ045 3

YQ201 - YQ207 3

YQ231 3

YQ241 - YQ251 3

YQ281 - YQ284 3

YQ291 - YQ296 3

YQ301 - YQ302 3

YQ321 - YQ324 3

YQ331 - YQ334 3

YQ346 - YQ347 3

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ALERT ALERT
Variable Number Group

YQ351 - YQ362 3

YQ371 3

YQ401 - YQ403 3

YQ451 - YQ454 3

YQ456 3

YQ461 3

YQ471 3

YQ501 - YQ520 3

YR001 - YR044 3

YR051 - YR098 3

YR101 - YR105 3

YR111 - YR124 3

YR126 - YR144 3

YR166 - YR182 3

YR186 - YR198 3

YR201 - YR204 3

YR231 - YR294 3

YR296 - YR297 3

YR301 - YR334 3

YR338 - YR341 3

YR361 - YR366 3

YR371 - YR373 3

YR376 - YR377 3

YR381 - YR382 3

YR386 - YR388 3

YR391 3

YR396 - YR398 3

YR401 - YR405 3

YR411 - YR413 3

YR416 - YR418 3

YR421 - YR424 3

YR426 - YR455 3

YR457 - YR499 3

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ALERT ALERT
Variable Number Group

YR501 - YR506 3

YR511 - YR520 3

YR526 - YR544 3

YR546 - YR551 3

YR556 - YR562 3

YR571 - YR582 3

YR591 - YR592 3

YR601 - YR605 3

YR616 - YR658 3

YR661 - YR663 3

YR671 - YR672 3

YR676 - YR678 3

YR681 - YR682 3

YR701 - YR769 3

YR771 - YR799 3

YR801 - YR820 3

YR831 - YR838 3

YR841 - YR899 3

YR901 - YR903 3

YR931 - YR934 3

YR938 - YR944 3

YR951 - YR976 3

YR981 - YR996 3

YS001 - YS002 3

YS006 - YS009 3

YS031 - YS032 3

YS051 - YS073 3

YS101 - YS120 3

YS126 - YS142 3

YS146 - YS148 3

YS151 - YS160 3

YS166 - YS194 3

YS196 - YS197 3

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ALERT ALERT
Variable Number Group

YS201 - YS209 3

YS221 - YS225 3

YS231 - YS236 3

YS271 - YS288 3

YS301 - YS346 3

YS351 - YS368 3

YS371 - YS377 3

YS381 - YS383 3

YS401 3

YS451 3

YS456 - YS457 3

YS462 3

YS467 3

YS501 - YS502 3

YS506 3

YS511 - YS516 3

YS531 3

YS536 - YS538 3

YS541 3

YS551 - YS556 3

YS561 - YS578 3

YS581 - YS595 3

YS601 - YS690 3

YS701 - YS708 3

YS721 - YS762 3

YS771 - YS780 3

YS806 - YS810 3

YS816 - YS818 3

YS823 - YS825 3

YS851 - YS861 3

YS876 3

YS881 - YS883 3

YS901 - YS909 3

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ALERT ALERT
Variable Number Group

YS911 - YS939 3

YS951 3

YS956 - YS957 3

YS961 - YS965 3

YS981 - YS987 3

YS991 - YS998 3

YT001 - YT004 3

YT006 3

YT026 - YT027 3

YT031 - YT032 3

YT036 - YT038 3

YT061 - YT068 3

YT101 - YT117 3

YT126 - YT131 3

YT136 - YT138 3

YT176 - YT181 3

YT191 3

YT196 - YT199 3

YT201 3

YT206 - YT207 3

YT211 - YT213 3

YT251 - YT283 3

YT301 - YT307 3

YT311 - YT312 3

YT321 - YT341 3

YT381 3

YT391 - YT395 3

YT401 - YT403 3

YT411 - YT417 3

YT427 3

YT461 - YT474 3

YT491 - YT492 3

YT501 - YT520 3

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ALERT ALERT
Variable Number Group

YT551 - YT552 3

YT556 - YT559 3

YT561 - YT563 3

YT571 3

YT601 - YT606 3

YT701 - YT706 3

YT761 - YT780 3

YT791 - YT793 3

YT796 - YT797 3

YT801 - YT804 3

YT811 - YT813 3

YT826 - YT827 3

YT831 - YT832 3

YT851 - YT852 3

YT856 - YT859 3

YT891 - YT895 3

YT901 - YT925 3

YU001 - YU054 3

YU201 - YU212 3

YV001 - YV002 3

YV006 - YV008 3

YV041 - YV042 3

YV045 - YV047 3

YV081 3

YV083 3

YV097 3

YV101 - YV119 3

YV301 - YV305 3

YV351 - YV356 3

YV381 - YV382 3

YV431 - YV433 3

YV501 3

YV521 3

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ALERT ALERT
Variable Number Group

YV571 - YV574 3

YV601 - YV605 3

YV651 - YV654 3

YV711 3

YV741 3

YV781 3

YV801 3

YV881 - YV883 3

YW001 3

YW011 - YW032 3

2. Spares Affected

None.

B. Concurrent Requirements

None.

C. Reason

This service bulletin gives instructions to inspect for any crack in the skin around fasteners in window

corners from STA 360 to STA 540 and from STA 727 to STA 887, left and right side between stringers

S-10 and S-14. Widespread Fatigue Damage (WFD) analysis of the 737NG, as required by 14 CFR

26.21(b), has resulted in the conclusion that the existing MPD Section 9, Airworthiness Limitation

Instruction (ALI) inspection program is not sufficient to preclude the occurrence of WFD in the window

corner surround structure from STA 360 to STA 540 and from STA 727 to STA 887, left and right sides

between S-10 and S-14, as the airplane ages. The window corner surround structure has multiple

adjacent identical details which have the potential for Multi-Element Damage (MED) 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).

Accomplishment of the inspections described in this service bulletin will enable detection and repair of

cracks if they should occur, at the window corner surround structure. Boeing has not received any

in-service fleet reports of cracks in the window corner surround structure. 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.

The window corner surround structure from STA 360 to STA 540 and from STA 727 to STA 887, left

and right sides between S-10 and S-14, 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-53-0474 is related to this service bulletin.

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ALERT ALERT
D. Description

Do an external High Frequency Eddy Current (HFEC) inspection of the skin around fasteners in window

corners from STA 360 to STA 540 and from STA 727 to STA 887. If no crack is found, do repeat

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

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

Group 1:

Affected Maintenance Zones

Model Zone

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

Group 2:

Affected Maintenance Zones

Model Zone

737-700C, 737-900 231, 232, 241, 242

Group 3:

Affected Maintenance Zones

Model Zone

737-800, 737-900ER 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.

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

A, B, and C.

For airplanes which have incorporated Boeing Business Jet Lower Cabin Altitude 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 flight cycle related compliance times are different from those specified

in this service bulletin. The initial compliance time (threshold) for 737-700 airplanes must be reduced

to 46,000 total flight cycles and the repeat interval must be reduced to 3,400 flight cycles. The initial

compliance time (threshold) for 737-800, -900ER airplanes must be reduced to 39,000 total flight cycles

and the repeat interval must be reduced to 3,400 flight cycles.

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ALERT ALERT
For airplanes that have not incorporated Boeing Business Jet Lower Cabin Altitude 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 PSE 53-30-05-2 and 53-60-05-2 of Subsection

B, Airworthiness Limitations-Structural Inspections of Section 9 of the 737-600/700/800/900 MPD

626A001-CMR Table 9-2, which is mandated by AD 2013-19-23. The inspections in this bulletin are

for the skin surrounding the passenger window frame at two of the four corners and must be

accomplished in addition to the 737-600/700/800/900 MPD D626A001-CMR inspections (which apply

only to the window frames), beginning at the threshold identified in section E of this bulletin.

For airplanes which have incorporated Boeing Business Jet Lower Cabin Altitude 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) 53-30-05-1,

53-30-05-2, 53-30-05-3, 53-60-05-1, 53-60-05-2, and 53-60-05-3 of Subsection B, Airworthiness

Limitations-Structural Inspections of Section 9 of the 737-600/700/800/900 MPD 626A001-CMR Table

9-3, which is mandated by AD 2013-19-23. The inspections in this bulletin are for the skin surrounding

the passenger window frames at two of the four corners and must be accomplished in addition to the

737-600/700/800/900 MPD D626A001-CMR inspections beginning at the threshold identified in section

E of this bulletin. 737-600/700/800/900 MPD D626A001-CMR PSE number 53-30-05-3 and 53-60-05-3

inspections apply to the skin completely surrounding the passenger window frames. 737-600/700/800/900

MPD D626A001-CMR PSE number 53-30-05-1, 53-60-05-1, 53-30-05-2 and 53-60-05-2 inspections

apply only to the window frames.

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

Group 1:

Table 1: Window Corner External Inspection From STA 360 to STA 540 and From STA 727 to STA 887

Repeat Interval

(Not to Exceed)

Condition Action Compliance Time

Do PART 1: WINDOW Before 64,000 total flight cycles. -

CORNER EXTERNAL

HFEC INSPECTION

FROM STA 360 TO STA

540 AND FROM STA 727

TO STA 887, LEFT AND

RIGHT SIDE for any

crack.

All Airplanes

Repeat PART 1: WIN- - 4,600 flight cycles.

DOW CORNER EXTERNAL HFEC INSPECTION

FROM STA 360 TO STA

540 AND FROM STA 727

TO STA 887, LEFT AND

RIGHT SIDE for any

crack.

CONDITION 1: NO

CRACK FOUND

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BOEING SERVICE BULLETIN 737-53A1351

ALERT ALERT
Group 1:

Table 1: Window Corner External Inspection From STA 360 to STA 540 and From STA 727 to STA 887

Repeat Interval

(Not to Exceed)

Condition Action Compliance Time

CONDITION 2: ANY ACTION 1: Before Further Flight. -

CRACK FOUND Contact The Boeing

Company for repair instructions and do the repair.

ACTION 2: - 4,600 flight cycles.

Repeat PART 1: WINDOW CORNER EXTERNAL HFEC INSPECTION

FROM STA 360 TO STA

540 AND FROM STA 727

TO STA 887, LEFT AND

RIGHT SIDE for any

crack at the unrepaired

areas.

Group 2:

Table 2: Window Corner External Inspection From STA 360 to STA 540 and From STA 727 to STA 887

Repeat Interval

(Not to Exceed)

Condition Action Compliance Time

Do PART 1: WINDOW Before 58,000 total flight cycles. -

CORNER EXTERNAL

HFEC INSPECTION

FROM STA 360 TO STA

540 AND FROM STA 727

TO STA 887, LEFT AND

RIGHT SIDE for any

crack.

All Airplanes

Repeat PART 1: WIN- - 4,600 flight cycles.

DOW CORNER EXTERNAL HFEC INSPECTION

FROM STA 360 TO STA

540 AND FROM STA 727

TO STA 887, LEFT AND

RIGHT SIDE for any

crack.

CONDITION 1: NO

CRACK FOUND

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ALERT ALERT
Group 2:

Table 2: Window Corner External Inspection From STA 360 to STA 540 and From STA 727 to STA 887

Repeat Interval

(Not to Exceed)

Condition Action Compliance Time

CONDITION 2: ANY ACTION 1: Before Further Flight. -

CRACK FOUND Contact The Boeing

Company for repair instructions and do the repair.

ACTION 2: - 4,600 flight cycles.

Repeat PART 1: WINDOW CORNER EXTERNAL HFEC INSPECTION

FROM STA 360 TO STA

540 AND FROM STA 727

TO STA 887, LEFT AND

RIGHT SIDE for any

crack at the unrepaired

areas.

Group 3:

Table 3: Window Corner External Inspection From STA 360 to STA 540 and From STA 727 to STA 887

Repeat Interval

(Not to Exceed)

Condition Action Compliance Time

Do PART 1: WINDOW Before 53,000 total flight cycles. -

CORNER EXTERNAL

HFEC INSPECTION

FROM STA 360 TO STA

540 AND FROM STA 727

TO STA 887, LEFT AND

RIGHT SIDE for any

crack.

All Airplanes

Repeat PART 1: WIN- - 4,600 flight cycles.

DOW CORNER EXTERNAL HFEC INSPECTION

FROM STA 360 TO STA

540 AND FROM STA 727

TO STA 887, LEFT AND

RIGHT SIDE for any

crack.

CONDITION 1: NO

CRACK FOUND

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ALERT ALERT
Group 3:

Table 3: Window Corner External Inspection From STA 360 to STA 540 and From STA 727 to STA 887

Repeat Interval

(Not to Exceed)

Condition Action Compliance Time

CONDITION 2: ANY ACTION 1: Before Further Flight. -

CRACK FOUND Contact The Boeing

Company for repair instructions and do the repair.

ACTION 2: - 4,600 flight cycles.

Repeat PART 1: WINDOW CORNER EXTERNAL HFEC INSPECTION

FROM STA 360 TO STA

540 AND FROM STA 727

TO STA 887, LEFT AND

RIGHT SIDE for any

crack at the unrepaired

areas.

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.

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.

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.

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ALERT ALERT
Task Number of Persons Task Hours Elapsed Hours

Inspect 1 0.50 0.50

TOTAL FOR EACH WINDOW (a) 0.50 0.50

(a) Estimate for each window, multiply number of windows to be inspected by the

estimate given to arrive at the total for each aircraft.

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 Related Problem (SRP) 737NG-SRP-53-0474

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

d. Service Bulletin Index D6-19567

e. 737 Non-Destructive Testing (NDT) Manual Part 6, 51-00-00

f. 737-600/700/800/900 Maintenance Planning Data (MPD)

2. Data Supplied with this Service Bulletin:

None.

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

None.

K. Publications Affected

1. Publications:

None.

2. Damage Tolerance Based Structural Inspections:

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

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

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

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ALERT ALERT
L. Interchangeability and Intermixability of Parts

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

M. Software Accomplishment Summary

Not affected.

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ALERT ALERT
2. MATERIAL INFORMATION

A. Material - Price and Availability

None.

B. Industry Support Information

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

C. Parts Necessary for Each Airplane

1. Kits/Parts

None.

2. Parts and Materials Supplied by the Operator

None.

3. Parts Modified and Reidentified

None.

4. Parts Removed and Not Replaced

None.

D. Parts Necessary to Change Spares

None.

E. Special Tooling - Price and Availability

None.

F. Special Tooling Necessary to do this Service Bulletin

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

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

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

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ALERT ALERT

BLANK PAGE
3. ACCOMPLISHMENT INSTRUCTIONS

A. GENERAL INFORMATION

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.

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

applicable installation step.

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

SRM Chapter 51.

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

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

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

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

must be used.

6. Boeing Service Letter 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.

7. Refer to Appendix A, B, and C for logic diagrams. Logic diagrams are provided as

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

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

primary source for tasks required for compliance.

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8. 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.

9. 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.

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

non-authoritative information from the critical and authoritative information.

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

(ATA) iSpec 2200.

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

are in Paragraph 1.E., Compliance.

13. The CONDITIONS, ACTIONS and OPTIONS shown apply to each inspection location

independently.

14. 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. RC - Do PART 1: WINDOW CORNER EXTERNAL HFEC INSPECTION FROM STA 360 TO STA

540 AND FROM STA 727 TO STA 887, LEFT AND RIGHT SIDE for any crack.

a. CONDITION 1: NO CRACK FOUND.

(1) RC - Repeat PART 1: WINDOW CORNER EXTERNAL SURFACE HFEC INSPECTION

FROM STA 360 TO STA 540 AND FROM STA 727 TO STA 887 for any crack at the

repeat interval in Paragraph 1.E., Compliance.

b. CONDITION 2: ANY CRACK FOUND.

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

(2) RC - ACTION 2: Repeat PART 1: WINDOW CORNER EXTERNAL HFEC INSPECTION

FROM STA 360 TO STA 540 AND FROM STA 727 TO STA 887, LEFT AND RIGHT

SIDE for any crack at the unrepaired areas.

2. Put the airplane back to a serviceable condition.

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PART 1: WINDOW CORNER EXTERNAL HFEC INSPECTION FROM STA 360 TO STA 540 AND

FROM STA 727 TO STA 887, LEFT AND RIGHT SIDE

1. Do the following inspections:

NOTE: If a Boeing ODA approved repair via FAA Form 8100-9 was installed to eliminate cracking

that was previously found, inspections in the window corner are not required at the repaired

location only.

Group 2:

NOTE: For 737-700C airplanes, inspections are not required at the windows in the main deck

cargo door located between STA 360 and STA 540.

a. Do an external High Frequency Eddy Current (HFEC) inspection for any crack in the skin at

the upper forward and lower aft corners of each left side window from STA 360 to STA 540

in accordance with FIGURE 1.

b. Do an external HFEC inspection for any crack in the skin at the upper forward and lower aft

corners of each right side window from STA 360 to STA 540 in accordance with FIGURE 2.

c. Do an external HFEC inspection for any crack in the skin at the lower forward and upper aft

corners of each left side window from STA 727 to STA 887 in accordance with FIGURE 3.

d. Do an external HFEC inspection for any crack in the skin at the lower forward and upper aft

corners of each right side window from STA 727 to STA 887 in accordance with FIGURE 4.

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FIGURE 1: EXTERNAL INSPECTION OF THE UPPER FORWARD AND LOWER AFT WINDOW CORNER,

STA 360 TO STA 540 LEFT SIDE

(SHEET 1 OF 2)

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STEP TASK NAME IDENTIFICATION QTY MORE DATA

1 Inspect Skin - - (a)

(a) Do an external HFEC inspection for any crack in the skin around the fasteners in window corners in

accordance with 737 NDT Manual Part 6, 51-00-00, Procedure 4 or 23.

FIGURE 1: EXTERNAL INSPECTION OF THE UPPER FORWARD AND LOWER AFT WINDOW CORNER,

STA 360 TO STA 540 LEFT SIDE

(SHEET 2 OF 2)

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FIGURE 2: EXTERNAL INSPECTION OF THE UPPER FORWARD AND LOWER AFT WINDOW CORNER,

STA 360 TO STA 540 RIGHT SIDE

(SHEET 1 OF 2)

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STEP TASK NAME IDENTIFICATION QTY MORE DATA

1 Inspect Skin - - (a)

(a) Do an external HFEC inspection for any crack in the skin around the fasteners in window corners in

accordance with 737 NDT Manual Part 6, 51-00-00, Procedure 4 or 23.

FIGURE 2: EXTERNAL INSPECTION OF THE UPPER FORWARD AND LOWER AFT WINDOW CORNER,

STA 360 TO STA 540 RIGHT SIDE

(SHEET 2 OF 2)

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FIGURE 3: EXTERNAL INSPECTION OF THE LOWER FORWARD AND UPPER AFT WINDOW CORNER,

STA 727 TO STA 887 LEFT SIDE

(SHEET 1 OF 2)

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STEP TASK NAME IDENTIFICATION QTY MORE DATA

1 Inspect Skin - - (a)

(a) Do an external HFEC inspection for any crack in the skin around the fasteners in window corners in

accordance with 737 NDT Manual Part 6, 51-00-00, Procedure 4 or 23.

FIGURE 3: EXTERNAL INSPECTION OF THE LOWER FORWARD AND UPPER AFT WINDOW CORNER,

STA 727 TO STA 887 LEFT SIDE

(SHEET 2 OF 2)

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FIGURE 4: EXTERNAL INSPECTION OF THE LOWER FORWARD AND UPPER AFT WINDOW CORNER,

STA 727 TO STA 887 RIGHT SIDE

(SHEET 1 OF 2)

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ALERT ALERT
STEP TASK NAME IDENTIFICATION QTY MORE DATA

1 Inspect Skin - - (a)

(a) Do an external HFEC inspection for any crack in the skin around the fasteners in window corners in

accordance with 737 NDT Manual Part 6, 51-00-00, Procedure 4 or 23.

FIGURE 4: EXTERNAL INSPECTION OF THE LOWER FORWARD AND UPPER AFT WINDOW CORNER,

STA 727 TO STA 887 RIGHT SIDE

(SHEET 2 OF 2)

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This Appendix applies only to: Group 1.

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.

APPENDIX A: LOGIC DIAGRAM FOR PARAGRAPH 1.E., COMPLIANCE: TABLE 1: WINDOW CORNER

EXTERNAL INSPECTION FROM STA 360 TO STA 540 AND FROM STA 727 TO STA 887

(SHEET 1 OF 2)

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

Title Description

WINDOW CORNER EXTERNAL HFEC INSPECTION FROM STA 360 TO

STA 540 AND FROM STA 727 TO STA 887, LEFT AND RIGHT SIDE

PART 1

CONDITION 1 NO CRACK FOUND

CONDITION 2 ANY CRACK FOUND

APPENDIX A: LOGIC DIAGRAM FOR PARAGRAPH 1.E., COMPLIANCE: TABLE 1: WINDOW CORNER

EXTERNAL INSPECTION FROM STA 360 TO STA 540 AND FROM STA 727 TO STA 887

(SHEET 2 OF 2)

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This Appendix applies only to: Group 2.

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.

APPENDIX B: LOGIC DIAGRAM FOR PARAGRAPH 1.E., COMPLIANCE: TABLE 2: WINDOW CORNER

EXTERNAL INSPECTION FROM STA 360 TO STA 540 AND FROM STA 727 TO STA 887

(SHEET 1 OF 2)

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

Title Description

WINDOW CORNER EXTERNAL HFEC INSPECTION FROM STA 360 TO

STA 540 AND FROM STA 727 TO STA 887, LEFT AND RIGHT SIDE

PART 1

CONDITION 1 NO CRACK FOUND

CONDITION 2 ANY CRACK FOUND

APPENDIX B: LOGIC DIAGRAM FOR PARAGRAPH 1.E., COMPLIANCE: TABLE 2: WINDOW CORNER

EXTERNAL INSPECTION FROM STA 360 TO STA 540 AND FROM STA 727 TO STA 887

(SHEET 2 OF 2)

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This Appendix applies only to: Group 3.

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.

APPENDIX C: LOGIC DIAGRAM FOR PARAGRAPH 1.E., COMPLIANCE: TABLE 3: WINDOW CORNER

EXTERNAL INSPECTION FROM STA 360 TO STA 540 AND FROM STA 727 TO STA 887

(SHEET 1 OF 2)

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

Title Description

WINDOW CORNER EXTERNAL HFEC INSPECTION FROM STA 360 TO

STA 540 AND FROM STA 727 TO STA 887, LEFT AND RIGHT SIDE

PART 1

CONDITION 1 NO CRACK FOUND

CONDITION 2 ANY CRACK FOUND

APPENDIX C: LOGIC DIAGRAM FOR PARAGRAPH 1.E., COMPLIANCE: TABLE 3: WINDOW CORNER

EXTERNAL INSPECTION FROM STA 360 TO STA 540 AND FROM STA 727 TO STA 887

(SHEET 2 OF 2)

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ALERT ALERT