Commercial 

Airplanes 737

Service Bulletin

ALERT

Number: 737-55A1097

Original Issue: July 01, 2015

ATA System: 5510

SUBJECT: STABILIZERS - Horizontal Stabilizer - Rear Spar Upper Chord 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Unpublished Work.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.

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BLANK PAGE
Table of Contents

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

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

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

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

2. Spares Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 31

B. Concurrent Requirements . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 31

C. Reason . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 31

D. Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 32

E. Compliance . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 32

F. Approval . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 39

G. Manpower . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 40

H. Weight and Balance Changes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 41

I. Electrical Load Data . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 41

J. References . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 41

1. Existing Data: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 41

2. Data Supplied with this Service Bulletin: . . . . . . . . . . . . . . . . . . . . . . . . . . . 42

3. Installation Drawings Used in the Preparation of this Service Bulletin: . . . . . . . . . . . 42

K. Publications Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 42

L. Interchangeability and Intermixability of Parts . . . . . . . . . . . . . . . . . . . . . . . . . . . 42

M. Software Accomplishment Summary . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 42

2. MATERIAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 43

A. Material - Price and Availability . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 43

B. Industry Support Information . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 43

C. Parts Necessary for Each Airplane . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 43

1. Kits/Parts . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 43

2. Parts and Materials Supplied by the Operator . . . . . . . . . . . . . . . . . . . . . . . . 43

3. Parts Modified and Reidentified . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 43

4. Parts Removed and Not Replaced . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 43

D. Parts Necessary to Change Spares . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 43

E. Special Tooling - Price and Availability . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 43

F. Special Tooling Necessary to do this Service Bulletin . . . . . . . . . . . . . . . . . . . . . . . 43

3. ACCOMPLISHMENT INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 45

A. GENERAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 45

B. WORK INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 46

FIGURE 1: LEFT SIDE HORIZONTAL STABILIZER IDENTIFICATION PLATE INSPECTION . . . . . 52

FIGURE 2: RIGHT SIDE HORIZONTAL STABILIZER IDENTIFICATION PLATE INSPECTION . . . . 54

FIGURE 3: LEFT SIDE HORIZONTAL STABILIZER REAR SPAR UPPER CHORD - HFEC INSPECTION

TO DETECT ANY CRACK 0.100 INCH OR GREATER USING A 0.050 INCH SCAN INCREMENT

. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 56

FIGURE 4: RIGHT SIDE HORIZONTAL STABILIZER REAR SPAR UPPER CHORD - HFEC INSPECTION

TO DETECT ANY CRACK 0.100 INCH OR GREATER USING A 0.050 INCH SCAN INCREMENT

. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 58

FIGURE 5: LEFT SIDE HORIZONTAL STABILIZER REAR SPAR UPPER CHORD - HFEC INSPECTION

TO DETECT ANY CRACK 0.200 INCH OR GREATER USING A 0.100 INCH SCAN INCREMENT

. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 60

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BOEING SERVICE BULLETIN 737-55A1097

ALERT ALERT
FIGURE 6: RIGHT SIDE HORIZONTAL STABILIZER REAR SPAR UPPER CHORD - HFEC INSPECTION

TO DETECT ANY CRACK 0.200 INCH OR GREATER USING A 0.100 INCH SCAN INCREMENT

. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 62

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

STABILIZER IDENTIFICATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 64

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

STABILIZER IDENTIFICATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 68

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ALERT ALERT
Commercial 

Airplanes 737

Service Bulletin

ALERT

Summary Number: 737-55A1097

Original Issue: July 01, 2015

ATA System: 5510

SUBJECT: STABILIZERS - Horizontal Stabilizer - Rear Spar Upper Chord 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 cracking in the horizontal stabilizer rear spar upper chord

on horizontal stabilizers with serial numbers SAIC0001-SAIC0143, SAIC0145-SAIC0625, SAIC0627-SAIC1144,

SAIC1146-SAIC1601, and SAMC1602-SAMC2639. If the work in this service bulletin is not done, corrosion

damage may lead to cracking in the horizontal stabilizer rear spar upper chord. Fracture of the upper chord of

the horizontal stabilizer will compromise the structural integrity which could lead to departure of the horizontal

stabilizer from the airplane. This will lead to loss of continued safe flight and landing.

Due to a manufacturing oversight, supplier SAMC (Shanghai Aviation Manufacturing Corporation, formally SAIC,

Shanghai Aviation Industrial Corporation) omitted the required protective finish (zinc-nickel alloy plate or cadmium

plate) on the 182A1508-4/-5/-6 bushings (in line with the terminal fitting holes) installed in the rear spar upper

chord on horizontal stabilizers with serial numbers SAIC0001-SAIC0143, SAIC0145-SAIC0625,

SAIC0627-SAIC1144, SAIC1146-SAIC1601, and SAMC1602-SAMC2639. This issue was discovered after

production of the affected stabilizers.

The 182A1508-4/-5/-6 bushings are made from aluminum-nickel-bronze. When these bushings are installed

into the 2024-T3511 aluminum horizontal stabilizer rear spar upper chord, this can lead to galvanic corrosion

between the dissimilar metals. This corrosion can lead to cracking of the rear spar upper chord, which can result

in the failure of the upper chord.

Boeing Fleet Team Digest (FTD) 737NG FTD 55-14001 is related to this service bulletin.

Boeing Service Related Problem (SRP) 737NG-SRP-55-0056 is related to this service bulletin.

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

information.

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Planning Data Affected Reference

Spares Affected Yes Paragraph 1.A.2., Spares Affected

Paragraph 1.E., Compliance and Paragraph

1.F., Approval

AD Related Yes

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

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

Publications Affected Yes 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

To determine if the left and right horizontal stabilizers are affected, do one of the following:

- OPTION 1: Do a check of delivery and maintenance records to find the serial number of the horizontal stabilizer

installed on the airplane during production and to determine if the horizontal stabilizer has been exchanged.

- OPTION 2: Gain access to the horizontal stabilizer identification plate and do an inspection of the identification

plate to find the serial numbers of the horizontal stabilizers.

If any affected horizontal stabilizer is installed on the airplane, do one of the following:

- OPTION 1 (TO DETECT ANY CRACK 0.100 INCH OR GREATER): Do a High Frequency Eddy Current (HFEC)

inspection of the horizontal stabilizer rear spar upper chord for any crack using a 0.050 inch scan increment.

- OPTION 2 (TO DETECT ANY CRACK 0.200 INCH OR GREATER): Do an HFEC inspection of the horizontal

stabilizer rear spar upper chord for any crack using a 0.100 inch scan increment.

If no crack is found, repeat the OPTION 1 or OPTION 2 HFEC inspection at the repeat interval given in Paragraph

1.E., Compliance.

If any crack is found, contact Boeing to get instructions for the repair for this service bulletin, and do the work

instructed by Boeing. Repeat the inspection for any crack at the unrepaired areas.

EFFECTIVITY

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

airplanes.

Refer to Paragraph 1.A.2., Spares Affected for the list of affected components.

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BOEING SERVICE BULLETIN 737-55A1097

ALERT ALERT
COMPLIANCE

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

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

mandatory.

Refer to Paragraph 1.E., Compliance.

INDUSTRY SUPPORT INFORMATION

Boeing warranty remedies are available for 737 airplanes in warranty as of December 20, 2012. Refer to

Paragraph 2.B., Industry Support Information. The warranty remedies will expire eight years from the original

issue date of this service bulletin.

MANPOWER

Refer to Paragraph 1.G., Manpower.

MATERIAL INFORMATION

None.

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ALERT ALERT
Commercial 

Airplanes 737

Service Bulletin

ALERT

Number: 737-55A1097

Original Issue: July 01, 2015

ATA System: 5510

SUBJECT: STABILIZERS - Horizontal Stabilizer - Rear Spar Upper Chord 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

This service bulletin is applicable to 737-600, -700, -700C, -800, -900, -900ER airplanes in 2

Groups. The Variable Numbers and Group Information for the applicable airplanes is given below.

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

Serial Number data.

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

737-600, -700, -700C, -800, -900, -900ER airplanes, line numbers

379-1117, 1119-1782, 1784-2504, 2506-4484. These airplanes were

possibly delivered with affected stabilizers installed.

1 -

737-600, -700, -700C, -800, -900, -900ER airplanes, line numbers

1-378, 1118, 1783, 2505, 4485 and on. These airplanes were not

delivered with any affected stabilizer installed.

2 -

Airplane Models:

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

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Variable Number Group

YA001 - YA049 2

YA050 - YA099 1

YA101 - YA199 1

YA201 - YA206 2

YA207 - YA211 1

YA221 1

YA231 - YA242 2

YA251 - YA254 2

YA255 - YA256 1

YA271 - YA272 2

YA291 2

YA301 - YA302 2

YA311 - YA314 2

YA321 - YA322 2

YA323 1

YA336 - YA345 1

YA351 1

YA356 - YA357 1

YA366 - YA367 1

YA371 - YA377 1

YA501 - YA535 2

YA536 1

YA541 - YA546 2

YA547 - YA552 1

YA571 - YA577 2

YA578 1

YA601 - YA608 2

YA609 - YA615 1

YA621 - YA622 1

YA626 - YA631 1

YA635 - YA636 1

YA641 - YA642 1

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Variable Number Group

YA645 - YA650 1

YA656 - YA659 1

YA666 - YA667 1

YA671 - YA672 1

YA681 - YA691 1

YA701 - YA704 2

YA705 - YA710 1

YA721 - YA722 2

YA731 2

YA732 - YA734 1

YA751 - YA756 2

YA801 - YA803 1

YA809 1

YA811 - YA814 2

YA831 - YA832 2

YA833 - YA835 1

YA841 - YA842 2

YA843 - YA862 1

YA881 2

YA882 1

YA891 - YA892 1

YA961 - YA978 1

YB001 - YB006 1

YB101 - YB112 1

YB113 2

YB114 - YB132 1

YB151 - YB153 1

YB156 - YB158 1

YB161 - YB164 1

YB171 - YB172 1

YB181 - YB184 1

YB201 - YB208 1

YB271 1

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Variable Number Group

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

YB981 1

YB986 - YB998 1

YC001 - YC011 2

YC012 - YC030 1

YC051 - YC058 2

YC059 - YC070 1

YC071 - YC076 2

YC077 - YC084 1

YC091 - YC095 1

YC101 - YC103 2

YC104 1

YC111 - YC112 2

YC113 1

YC121 2

YC126 - YC127 2

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Variable Number Group

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 - YC302 2

YC303 - YC305 1

YC321 - YC348 2

YC349 - YC380 1

YC381 - YC382 2

YC383 - YC387 1

YC391 2

YC392 - YC394 1

YC396 1

YC401 - YC408 2

YC409 - YC417 1

YC421 - YC422 1

YC426 - YC428 1

YC436 - YC439 1

YC441 - YC448 1

YC451 - YC455 1

YC459 1

YC461 - YC467 1

YC471 - YC475 2

YC476 - YC499 1

YC501 - YC515 2

YC516 - YC526 1

YC571 - YC580 2

YC581 - YC583 1

YC587 - YC589 1

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Variable Number Group

YC591 - YC593 2

YC601 - YC611 2

YC612 - YC655 1

YC681 - YC696 1

YC701 - YC706 2

YC707 - YC715 1

YC720 - YC725 1

YC727 - YC730 1

YC731 - YC734 2

YC735 - YC750 1

YC751 - YC752 2

YC761 - YC763 2

YC764 - YC770 1

YC781 - YC784 2

YC785 - YC793 1

YC801 - YC819 2

YC820 - YC892 1

YC901 - YC907 1

YC921 - YC922 1

YC931 - YC932 2

YC941 - YC942 2

YC943 - YC951 1

YC971 2

YC972 - 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

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Variable Number Group

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 - YD419 1

YD420 - YD422 2

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 - YE017 2

YE018 - YE020 1

YE051 1

YE101 - YE109 2

YE151 - YE153 2

YE154 - YE157 1

YE171 - YE172 1

YE201 - YE206 1

YE301 - YE305 1

YE321 - YE326 1

YE371 - YE383 1

YF001 - YF011 1

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Variable Number Group

YF021 - YF049 1

YF051 - YF072 1

YF073 - YF080 2

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

YF441 - YF442 1

YF451 - YF460 1

YF501 - YF599 1

YF601 - YF661 1

YF662 - YF685 2

YF691 - YF695 2

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 - YG018 2

YG019 1

YG020 - YG023 2

YG024 - YG026 1

YG027 - YG032 2

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Variable Number Group

YG033 - YG044 1

YG061 - YG064 1

YG066 - YG089 1

YG091 - YG099 1

YG101 - YG104 1

YG111 - YG114 1

YG116 - YG138 1

YG139 - YG146 2

YG201 - YG205 1

YG211 - YG214 1

YG221 - YG224 1

YG251 - YG252 1

YG501 - YG512 1

YG513 - YG515 2

YG601 - YG602 1

YG701 1

YG711 1

YG721 - YG722 2

YH001 - YH012 1

YH031 - YH055 1

YH071 - YH080 1

YH101 - YH132 1

YH201 - YH202 1

YH206 - YH207 1

YH301 - YH306 1

YH307 2

YH321 - YH322 1

YH501 - YH525 1

YH526 - YH530 2

YH531 - YH537 1

YH538 - YH542 2

YH551 - YH581 1

YH582 - YH594 2

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BOEING SERVICE BULLETIN 737-55A1097

ALERT ALERT
Variable Number Group

YH601 - YH606 1

YH611 - YH620 1

YH631 - YH632 1

YH636 - YH637 2

YH641 1

YH681 - YH683 2

YH701 - YH708 1

YH709 - YH740 2

YH751 - YH755 2

YH801 - YH856 2

YH901 - YH908 2

YH911 - YH915 2

YH951 - YH952 2

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

YJ931 - YJ937 1

YJ941 - YJ956 1

YJ961 1

YJ976 - YJ977 1

YK001 - YK007 1

YK101 - YK104 1

YK111 - YK112 1

YK121 - YK122 1

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BOEING SERVICE BULLETIN 737-55A1097

ALERT ALERT
Variable Number Group

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

YK478 2

YK480 - YK487 1

YK491 - YK493 1

YK495 - YK499 1

YK511 - YK516 1

YK521 - YK530 1

YK551 - YK571 1

YK576 - YK577 1

YK580 - YK585 1

YK601 - YK602 1

YK606 - YK607 1

YK611 - YK616 1

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BOEING SERVICE BULLETIN 737-55A1097

ALERT ALERT
Variable Number Group

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

YL061 1

YL066 - YL069 1

YL076 - YL077 1

YL101 - YL137 1

YL201 - YL237 1

YL241 - YL242 1

YL271 - YL272 1

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BOEING SERVICE BULLETIN 737-55A1097

ALERT ALERT
Variable Number Group

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

YL731 1

YL751 - YL752 1

YL756 - YL757 1

YL761 - YL780 1

YL796 - YL797 1

YL801 - YL815 1

YL901 - YL910 1

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BOEING SERVICE BULLETIN 737-55A1097

ALERT ALERT
Variable Number Group

YL921 - YL940 1

YL951 - YL968 1

YM101 - YM103 1

YM201 - YM230 1

YM231 2

YM232 - YM244 1

YM251 - YM299 1

YM301 - YM399 1

YM401 - YM415 1

YM471 1

YM481 - YM484 1

YM501 - YM502 1

YM503 2

YM504 - 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

YN071 - YN082 1

YN091 - YN092 1

YN101 - YN112 1

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BOEING SERVICE BULLETIN 737-55A1097

ALERT ALERT
Variable Number Group

YN121 1

YN126 1

YN201 - YN202 1

YN211 - YN219 1

YN231 - YN236 1

YN261 1

YN501 1

YN531 - YN534 1

YN551 - YN555 1

YN556 - YN566 2

YN581 - YN585 2

YN591 - YN592 2

YN601 - YN606 1

YN651 - YN652 1

YN653 2

YN701 - YN702 1

YN741 - YN743 1

YN744 - YN746 2

YN756 2

YQ001 - YQ003 1

YQ011 - YQ021 1

YQ026 - YQ029 1

YQ036 - YQ045 1

YQ201 - YQ203 1

YQ204 - YQ207 2

YQ231 1

YQ241 - YQ251 1

YQ281 - YQ284 1

YQ291 - YQ296 1

YQ301 - YQ302 1

YQ321 - YQ323 1

YQ324 2

YQ331 - YQ332 1

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BOEING SERVICE BULLETIN 737-55A1097

ALERT ALERT
Variable Number Group

YQ333 - YQ334 2

YQ346 1

YQ347 2

YQ351 - YQ362 2

YQ371 2

YQ401 - YQ403 1

YQ451 - YQ454 1

YQ456 1

YQ461 1

YQ471 1

YQ501 - YQ505 1

YQ506 - YQ520 2

YR001 - YR023 1

YR024 - YR044 2

YR051 - YR069 1

YR070 - YR090 2

YR091 - YR096 1

YR097 - YR098 2

YR101 - YR104 1

YR105 2

YR111 - YR118 1

YR119 - YR124 2

YR126 - YR143 1

YR144 2

YR166 - YR182 1

YR186 - YR188 1

YR189 - YR198 2

YR201 - YR204 1

YR231 - YR266 1

YR267 - YR270 2

YR271 - YR289 1

YR290 2

YR291 - YR294 1

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BOEING SERVICE BULLETIN 737-55A1097

ALERT ALERT
Variable Number Group

YR296 - YR297 1

YR301 - YR327 1

YR328 - YR334 2

YR338 - YR341 2

YR361 - YR366 1

YR371 - YR372 1

YR373 2

YR376 - YR377 2

YR381 - YR382 1

YR386 1

YR387 - YR388 2

YR391 2

YR396 - YR397 1

YR398 2

YR401 - YR405 1

YR411 - YR413 1

YR416 - YR417 1

YR418 2

YR421 - YR422 1

YR423 - YR424 2

YR426 1

YR427 - YR430 2

YR431 - YR436 1

YR437 - YR440 2

YR441 - YR446 1

YR447 - YR450 2

YR451 - YR455 1

YR457 - YR481 1

YR482 - YR499 2

YR501 - YR506 1

YR511 - YR520 1

YR526 - YR534 1

YR535 2

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BOEING SERVICE BULLETIN 737-55A1097

ALERT ALERT
Variable Number Group

YR536 - YR541 1

YR542 - YR544 2

YR546 1

YR547 - YR551 2

YR556 - YR562 2

YR571 - YR582 2

YR591 - YR592 2

YR601 - YR605 1

YR616 - YR630 1

YR631 - YR650 2

YR651 - YR658 1

YR661 - YR663 1

YR671 - YR672 2

YR676 - YR678 2

YR681 - YR682 2

YR701 - YR759 1

YR760 - YR769 2

YR771 - YR799 2

YR801 - YR814 1

YR815 - YR820 2

YR831 - YR838 1

YR841 - YR845 1

YR846 - YR850 2

YR851 - YR866 1

YR867 - YR899 2

YR901 - YR903 1

YR931 - YR933 1

YR934 2

YR938 - YR940 2

YR941 - YR944 1

YR951 - YR960 1

YR961 - YR976 2

YR981 - YR991 1

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BOEING SERVICE BULLETIN 737-55A1097

ALERT ALERT
Variable Number Group

YR992 - YR996 2

YS001 - YS002 1

YS006 - YS009 2

YS031 - YS032 1

YS051 - YS064 1

YS065 - YS073 2

YS101 - YS112 1

YS113 - YS120 2

YS126 - YS142 2

YS146 - YS148 2

YS151 - YS160 1

YS166 - YS173 1

YS174 - YS194 2

YS196 1

YS197 2

YS201 - YS207 1

YS208 - YS209 2

YS221 - YS225 1

YS231 - YS236 2

YS271 - YS273 1

YS274 - YS288 2

YS301 - YS316 1

YS317 - YS346 2

YS351 - YS352 1

YS353 - YS368 2

YS371 - YS374 1

YS375 - YS377 2

YS381 - YS383 2

YS401 2

YS451 1

YS456 - YS457 2

YS462 2

YS467 2

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BOEING SERVICE BULLETIN 737-55A1097

ALERT ALERT
Variable Number Group

YS501 - YS502 1

YS506 2

YS511 - YS516 2

YS531 2

YS536 - YS538 2

YS541 2

YS551 - YS553 1

YS554 - YS556 2

YS561 - YS562 1

YS563 - YS578 2

YS581 - YS590 2

YS591 1

YS592 - YS595 2

YS601 - YS638 1

YS639 - YS685 2

YS686 - YS690 1

YS701 - YS705 1

YS706 - YS708 2

YS721 - YS727 1

YS728 - YS762 2

YS771 - YS775 1

YS776 - YS780 2

YS806 - YS810 2

YS816 - YS818 2

YS823 - YS825 2

YS851 - YS861 2

YS876 2

YS881 - YS883 2

YS901 - YS909 2

YS911 - YS939 2

YS951 2

YS956 - YS957 2

YS961 - YS965 2

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BOEING SERVICE BULLETIN 737-55A1097

ALERT ALERT
Variable Number Group

YS981 - YS987 2

YS991 - YS998 2

YT001 1

YT002 - YT004 2

YT006 2

YT026 - YT027 2

YT031 - YT032 2

YT036 - YT038 2

YT061 - YT068 2

YT101 - YT117 2

YT126 - YT131 2

YT136 - YT138 2

YT176 - YT181 2

YT191 2

YT196 - YT199 2

YT201 2

YT206 - YT207 2

YT211 - YT213 2

YT251 - YT283 2

YT301 - YT307 2

YT311 - YT312 2

YT321 - YT341 2

YT381 2

YT391 - YT395 2

YT401 - YT403 2

YT411 - YT417 2

YT427 2

YT461 - YT474 2

YT491 - YT492 2

YT501 - YT520 2

YT551 - YT552 2

YT556 - YT559 2

YT561 - YT563 2

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BOEING SERVICE BULLETIN 737-55A1097

ALERT ALERT
Variable Number Group

YT571 2

YT601 - YT606 2

YT701 - YT706 2

YT761 - YT780 2

YT791 - YT793 2

YT796 - YT797 2

YT801 - YT804 2

YT811 - YT813 2

YT826 - YT827 2

YT831 - YT832 2

YT851 - YT852 2

YT856 - YT859 2

YT891 - YT895 2

YT901 - YT925 2

YU001 - YU054 2

YU201 - YU212 2

YV001 - YV002 2

YV006 - YV008 2

YV041 - YV042 2

YV045 - YV047 2

YV081 2

YV083 2

YV097 2

YV101 - YV119 2

YV301 - YV305 2

YV351 - YV356 2

YV381 - YV382 2

YV431 - YV433 2

YV501 2

YV521 2

YV571 - YV574 2

YV601 - YV605 2

YV651 - YV654 2

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BOEING SERVICE BULLETIN 737-55A1097

ALERT ALERT
Variable Number Group

YV711 2

YV741 2

YV781 2

YV801 2

YV881 - YV883 2

YW001 2

YW011 - YW032 2

2. Spares Affected

Examine your spares supply for the parts or components identified below . If any parts or

components are found, refer to Paragraph 3.B., Work Instructions for the recommended action.

Part Name Serial Number

SAIC0001-SAIC0143, SAIC0145-SAIC0625, SAIC0627-SAIC1144, SAIC1146-SAIC1601, SAMC1602-

SAMC2639

Horizontal Stabilizer

B. Concurrent Requirements

None.

C. Reason

This service bulletin gives instructions to inspect for cracking in the horizontal stabilizer rear spar upper

chord on horizontal stabilizers with serial numbers SAIC0001-SAIC0143, SAIC0145-SAIC0625,

SAIC0627-SAIC1144, SAIC1146-SAIC1601, and SAMC1602-SAMC2639. If the work in this service

bulletin is not done, corrosion damage may lead to cracking in the horizontal stabilizer rear spar upper

chord. Fracture of the upper chord of the horizontal stabilizer will compromise the structural integrity

which could lead to departure of the horizontal stabilizer from the airplane. This will lead to loss of

continued safe flight and landing.

Due to a manufacturing oversight, supplier SAMC (Shanghai Aviation Manufacturing Corporation,

formally SAIC, Shanghai Aviation Industrial Corporation) omitted the required protective finish (zinc-nickel

alloy plate or cadmium plate) on the 182A1508-4/-5/-6 bushings (in line with the terminal fitting holes)

installed in the rear spar upper chord on horizontal stabilizers with serial numbers SAIC0001-SAIC0143,

SAIC0145-SAIC0625, SAIC0627-SAIC1144, SAIC1146-SAIC1601, and SAMC1602-SAMC2639. This

issue was discovered after production of the affected stabilizers.

The 182A1508-4/-5/-6 bushings are made from aluminum-nickel-bronze. When these bushings are

installed into the 2024-T3511 aluminum horizontal stabilizer rear spar upper chord, this can lead to

galvanic corrosion between the dissimilar metals. This corrosion can lead to cracking of the rear spar

upper chord, which can result in the failure of the upper chord.

Boeing Fleet Team Digest (FTD) 737NG FTD 55-14001 is related to this service bulletin.

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BOEING SERVICE BULLETIN 737-55A1097

ALERT ALERT
Boeing Service Related Problem (SRP) 737NG-SRP-55-0056 is related to this service bulletin.

D. Description

To determine if the left and right horizontal stabilizers are affected, do one of the following:

- OPTION 1: Do a check of delivery and maintenance records to find the serial number of the horizontal

stabilizer installed on the airplane during production and to determine if the horizontal stabilizer has

been exchanged.

- OPTION 2: Gain access to the horizontal stabilizer identification plate and do an inspection of the

identification plate to find the serial numbers of the horizontal stabilizers.

If any affected horizontal stabilizer is installed on the airplane, do one of the following:

- OPTION 1 (TO DETECT ANY CRACK 0.100 INCH OR GREATER): Do a High Frequency Eddy

Current (HFEC) inspection of the horizontal stabilizer rear spar upper chord for any crack using a 0.050

inch scan increment.

- OPTION 2 (TO DETECT ANY CRACK 0.200 INCH OR GREATER): Do an HFEC inspection of the

horizontal stabilizer rear spar upper chord for any crack using a 0.100 inch scan increment.

If no crack is found, repeat the OPTION 1 or OPTION 2 HFEC inspection at the repeat interval given

in Paragraph 1.E., Compliance.

If any crack is found, contact Boeing to get instructions for the repair for this service bulletin, and do

the work instructed by Boeing. Repeat the inspection for any crack at the unrepaired areas.

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

Affected Maintenance Zones

Model Zone

737-600, 737-700, 737-700C, 332, 342

737-800, 737-900, 737-900ER

E. Compliance

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

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

service bulletin mandatory.

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

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

more than one ACTION is given for a CONDITION number or an OPTION number, do all of the ACTION

numbers for that CONDITION number or OPTION number.

Logic diagrams showing compliance tasks and compliance times are included as aids in APPENDIX

A and APPENDIX B.

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BOEING SERVICE BULLETIN 737-55A1097

ALERT ALERT
Group 1:

Table 1: Horizontal Stabilizer Identification

Repeat Interval

(Not to Exceed)

Compliance Time (Whichever

Occurs Later)

Condition Action

Within 12 -

months after the

original issue

date of this service bulletin

Before 20,000

total horizontal

stabilizer flight

cycles or within

10 years from

the date of issuance of the

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

occurs first

OPTION 1: Do PART 1:

RECORDS CHECK.

All airplanes

OPTION 2: Do PART 2:

HORIZONTAL STABILIZER IDENTIFICATION

PLATE INSPECTION. (b)

CONDITION 1: CURRENT- No more work is required. - - -

LY INSTALLED HORIZONTAL STABILIZER NOT

AFFECTED (a)

Within 12 -

months after the

original issue

date of this service bulletin

Before 20,000

total horizontal

stabilizer flight

cycles or within

10 years from

the date of issuance of the

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

occurs first

OPTION 1 (TO DETECT

ANY CRACK 0.100 INCH

OR GREATER): Do an

HFEC inspection of the

horizontal stabilizer rear

spar upper chord for any

crack. (c)

CONDITION 2: CURRENTLY INSTALLED HORIZONTAL STABILIZER AFFECTED (a)

OPTION 2 (TO DETECT

ANY CRACK 0.200 INCH

OR GREATER): Do an

HFEC inspection of the

horizontal stabilizer rear

spar upper chord for any

crack. (c)

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BOEING SERVICE BULLETIN 737-55A1097

ALERT ALERT
Group 1:

Table 1: Horizontal Stabilizer Identification

Repeat Interval

(Not to Exceed)

Compliance Time (Whichever

Occurs Later)

Condition Action

Within 12 -

months after the

original issue

date of this service bulletin

Before 20,000

total horizontal

stabilizer flight

cycles or within

10 years from

the date of issuance of the

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

occurs first

Do PART 2: HORIZONTAL STABILIZER IDENTIFICATION PLATE INSPECTION. (b)CONDITION 3: PRODUCTION HORIZONTAL STABILIZER NOT EXCHANGED AND SERIAL

NUMBER UNKNOWN

Within 12 -

months after the

original issue

date of this service bulletin

Before 20,000

total horizontal

stabilizer flight

cycles or within

10 years from

the date of issuance of the

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

occurs first

OPTION 1: Check maintenance records to find the

original delivered airplane

for the horizontal stabilizer.

CONDITION 4: ANY HORIZONTAL STABILIZER

EXCHANGED AND INSTALLED HORIZONTAL

STABILIZER SERIAL

NUMBER UNKNOWN OPTION 2: Do PART 2:

HORIZONTAL STABILIZER IDENTIFICATION

PLATE INSPECTION. (b)

CONDITION 8: HORIZON- No more work is required. - - -

TAL STABILIZER IS

FROM AIRPLANE LINE

NUMBER 1-378, 1118,

1783, 2505, OR 4485-5388

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BOEING SERVICE BULLETIN 737-55A1097

ALERT ALERT
Group 1:

Table 1: Horizontal Stabilizer Identification

Repeat Interval

(Not to Exceed)

Compliance Time (Whichever

Occurs Later)

Condition Action

Within 12 -

months after the

original issue

date of this service bulletin

Before 20,000

total horizontal

stabilizer flight

cycles or within

10 years from

the date of issuance of the

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

occurs first

Do PART 2: HORIZONTAL STABILIZER IDENTIFICATION PLATE INSPECTION. (b)CONDITION 9: HORIZONTAL STABILIZER IS

FROM AIRPLANE LINE

NUMBER 379-1117, 1119-

1782, 1784-2504, OR

2506-4484 OR IS FROM

UNKNOWN AIRPLANE

(a) Affected horizontal stabilizer serial numbers are SAIC0001-SAIC0143, SAIC0145-SAIC0625, SAIC0627-

SAIC1144, SAIC1146-SAIC1601, and SAMC1602-SAMC2639.

(b) Refer to Table 3 for resulting conditions and corrective actions.

(c) Refer to Table 4 for resulting conditions and corrective actions.

Group 2:

Table 2: Horizontal Stabilizer Identification

Repeat Interval

(Not to Exceed)

Compliance Time (Whichever

Occurs Later)

Condition Action

Within 12 -

months after the

original issue

date of this service bulletin

Before 20,000

total horizontal

stabilizer flight

cycles or within

10 years from

the date of issuance of the

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

occurs first

OPTION 1: Do PART 1:

RECORDS CHECK.

All airplanes

OPTION 2: Do PART 2:

HORIZONTAL STABILIZER IDENTIFICATION

PLATE INSPECTION. (b)

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ALERT ALERT
Group 2:

Table 2: Horizontal Stabilizer Identification

Repeat Interval

(Not to Exceed)

Compliance Time (Whichever

Occurs Later)

Condition Action

CONDITION 5: NO HORI- No more work is required. - - -

ZONTAL STABILIZER EXCHANGED OR ANY HORIZONTAL STABILIZER

EXCHANGED WITH AN

UNAFFECTED HORIZONTAL STABILIZER (a)

Within 12 -

months after the

original issue

date of this service bulletin

Before 20,000

total horizontal

stabilizer flight

cycles or within

10 years from

the date of issuance of the

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

occurs first

OPTION 1 (TO DETECT

ANY CRACK 0.100 INCH

OR GREATER): Do an

HFEC inspection of the

horizontal stabilizer rear

spar upper chord for any

crack. (c)

CONDITION 6: ANY HORIZONTAL STABILIZER

EXCHANGED AND AFFECTED HORIZONTAL

STABILIZER INSTALLED

(a)

OPTION 2 (TO DETECT

ANY CRACK 0.200 INCH

OR GREATER): Do an

HFEC inspection of the

horizontal stabilizer rear

spar upper chord for any

crack. (c)

Within 12 -

months after the

original issue

date of this service bulletin

Before 20,000

total horizontal

stabilizer flight

cycles or within

10 years from

the date of issuance of the

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

occurs first

OPTION 1: Check maintenance records to find the

original delivered airplane

for the horizontal stabilizer.

CONDITION 7: ANY HORIZONTAL STABILIZER

EXCHANGED AND INSTALLED HORIZONTAL

STABILIZER SERIAL

NUMBER UNKNOWN OPTION 2: Do PART 2:

HORIZONTAL STABILIZER IDENTIFICATION

PLATE INSPECTION. (b)

CONDITION 8: HORIZON- No more work is required. - - -

TAL STABILIZER IS

FROM AIRPLANE LINE

NUMBER 1-378, 1118,

1783, 2505, OR 4485-5388

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ALERT ALERT
Group 2:

Table 2: Horizontal Stabilizer Identification

Repeat Interval

(Not to Exceed)

Compliance Time (Whichever

Occurs Later)

Condition Action

Within 12 -

months after the

original issue

date of this service bulletin

Before 20,000

total horizontal

stabilizer flight

cycles or within

10 years from

the date of issuance of the

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

occurs first

Do PART 2: HORIZONTAL STABILIZER IDENTIFICATION PLATE INSPECTION. (b)CONDITION 9: HORIZONTAL STABILIZER IS

FROM AIRPLANE LINE

NUMBER 379-1117, 1119-

1782, 1784-2504, OR

2506-4484 OR IS FROM

UNKNOWN AIRPLANE

(a) Affected horizontal stabilizer serial numbers are SAIC0001-SAIC0143, SAIC0145-SAIC0625, SAIC0627-

SAIC1144, SAIC1146-SAIC1601, and SAMC1602-SAMC2639.

(b) Refer to Table 3 for resulting conditions and corrective actions.

(c) Refer to Table 4 for resulting conditions and corrective actions.

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ALERT ALERT
Table 3: PART 2: HORIZONTAL STABILIZER IDENTIFICATION PLATE INSPECTION - Corrective Actions

Repeat Interval

(Not to Exceed)

Compliance Time (Whichever

Occurs Later)

Condition Action

CONDITION 10: NO AF- No more work is required. - - -

FECTED SERIAL NUMBER FOUND (a)

Within 12 -

months after the

original issue

date of this service bulletin

Before 20,000

total horizontal

stabilizer flight

cycles or within

10 years from

the date of issuance of the

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

occurs first

OPTION 1 (TO DETECT

ANY CRACK 0.100 INCH

OR GREATER): Do an

HFEC inspection of the

horizontal stabilizer rear

spar upper chord for any

crack. (b)

CONDITION 11: ANY AFFECTED SERIAL NUMBER FOUND (a)

OPTION 2 (TO DETECT

ANY CRACK 0.200 INCH

OR GREATER): Do an

HFEC inspection of the

horizontal stabilizer rear

spar upper chord for any

crack. (b)

(a) Affected horizontal stabilizer serial numbers are SAIC0001-SAIC0143, SAIC0145-SAIC0625, SAIC0627-

SAIC1144, SAIC1146-SAIC1601, and SAMC1602-SAMC2639.

(b) See Table 4 for resulting conditions and corrective actions.

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Table 4: Horizontal Stabilizer Rear Spar Upper Chord HFEC Inspection - Corrective Actions

Repeat Interval

(Not to Exceed)

Condition Action Compliance Time

CONDITION 12: NO Do one of the following: - -

CRACK FOUND 3,000 horizontal

stabilizer flight cycles

Repeat OPTION 1 (TO -

DETECT ANY CRACK

0.100 INCH OR

GREATER) HFEC inspection of the horizontal stabilizer rear spar upper

chord.

2,000 horizontal

stabilizer flight cycles

Repeat OPTION 2 (TO -

DETECT ANY CRACK

0.200 INCH OR

GREATER) HFEC inspection of the horizontal stabilizer rear spar upper

chord.

ACTION 1: Contact Boe- Before further flight -

ing to get instructions for

the repair for this service

bulletin, and do the work

instructed by Boeing.

CONDITION 13: ANY

CRACK FOUND

ACTION 2: Do one of the - -

following:

3,000 horizontal

stabilizer flight cycles

Repeat OPTION 1 (TO -

DETECT ANY CRACK

0.100 INCH OR

GREATER) HFEC inspection of the horizontal stabilizer rear spar upper

chord, for any crack of

the unrepaired area.

2,000 horizontal

stabilizer flight cycles

Repeat OPTION 2 (TO -

DETECT ANY CRACK

0.200 INCH OR

GREATER) HFEC inspection of the horizontal stabilizer rear spar upper

chord, for any crack of

the unrepaired area.

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

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ALERT ALERT
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.

The Manager of the Seattle ACO approves the incorporation of the inspection threshold, interval, and

methods as given in Table 4, under Paragraph 1.E., Compliance in this service bulletin, as an Alternative

Method of Compliance (AMOC) to the incorporation of the corresponding HFEC inspections in the area

of Principal Structural Elements 55-10-04-10A, 55-10-04-10B, and 55-10-04-10C, specified in Subsection

B of Section 9 of Boeing Model 737-600/700/700C/800/900/900ER MPD, Document D626A001-CMR,

Revision July 2011, December 2011, or August 2012, required by paragraphs (g) and (h) of AD

2013-19-23. All provisions of AD 2013-19-23 that are not specifically referenced in the preceding

sentence remain fully applicable and must be complied with accordingly.

G. Manpower

The tables below show an estimate of the task hours necessary to do this inspection for each airplane

or component. 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.

1. Airplane-Level Work

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HORIZONTAL STABILIZER - REAR SPAR UPPER CHORD - INSPECTION

Task Number of Persons Task Hours Elapsed Hours

Preparation and 1 1.50 1.50

Open Access

FIGURE 1 1 0.05 0.05

FIGURE 2 1 0.05 0.05

FIGURE 3 or FIG- 1 1.00 1.00

URE 5

FIGURE 4 or FIG- 1 1.00 1.00

URE 6

Restoration and 1 1.50 1.50

Close Access

TOTAL FOR EACH AIRPLANE 5.10 5.10

2. Component-Level Work

HORIZONTAL STABILIZER - REAR SPAR UPPER CHORD - INSPECTION

Task Number of Persons Task Hours Elapsed Hours

FIGURE 1 1 0.05 0.05

FIGURE 2 1 0.05 0.05

FIGURE 3 or FIG- 1 1.00 1.00

URE 5

FIGURE 4 or FIG- 1 1.00 1.00

URE 6

TOTAL FOR LEFT SIDE OF AIRPLANE 2.10 2.10

H. Weight and Balance Changes

None.

I. Electrical Load Data

Not changed.

J. References

1. Existing Data:

a. Boeing Service Related Problem (SRP) 737NG-SRP-55-0056

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

c. Service Bulletin Index D6-19567

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

e. 737 Non-Destructive Testing (NDT) Manual Part 6, 55-10-27

f. 737-600/700/800/900 Aircraft Maintenance Manual (AMM) 06-42-00, 27-31-00, 27-41-11

g. 737NG Fleet Team Digest (FTD) 55-14001

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:

Publication Chapter-Section

737 NDT Manual Part 6 55-10-27

2. Damage Tolerance Based Structural Inspections:

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

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

Maintenance Program. This service bulletin affects FCS. DTI requirements for the structure affected

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

L. Interchangeability and Intermixability of Parts

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

M. Software Accomplishment Summary

Not affected.

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ALERT ALERT
2. MATERIAL INFORMATION

A. Material - Price and Availability

None.

B. Industry Support Information

Boeing warranty remedies are available for 737 airplanes in warranty as of December 20, 2012. For

inspection labor task hour reimbursement for airplanes in warranty as of that date, send a warranty

claim to Boeing Fleet Support Contracts - Warranty. If the condition described in this service bulletin

is found during the inspection for airplanes in warranty as of that date and additional task hours, parts,

and/or special tools are required, send a warranty claim to Boeing Fleet Support Contracts - Warranty.

Please refer to this service bulletin number and reference the airplane variable number(s) in your

purchase order. The warranty remedies will expire eight years from the original issue date of this service

bulletin.

C. Parts Necessary for Each Airplane

1. Kits/Parts

None.

2. Parts and Materials Supplied by the Operator

None.

3. Parts Modified and Reidentified

None.

4. Parts Removed and Not Replaced

None.

D. Parts Necessary to Change Spares

None.

E. Special Tooling - Price and Availability

None.

F. Special Tooling Necessary to do this Service Bulletin

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

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

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

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ALERT ALERT

BLANK PAGE
3. ACCOMPLISHMENT INSTRUCTIONS

A. GENERAL INFORMATION

CAUTION: KEEP THE WORK AREA, WIRES AND ELECTRICAL BUNDLES CLEAN OF METAL

PARTICLES OR CONTAMINATION WHEN YOU USE TOOLS. UNWANTED MATERIAL,

METAL PARTICLES OR CONTAMINATION CAUGHT IN WIRE BUNDLES CAN CAUSE

DAMAGE TO THE BUNDLES. DAMAGED WIRE BUNDLES CAN CAUSE SPARKS OR

OTHER ELECTRICAL DAMAGE.

NOTE: 1. Manual titles are referred to by acronyms. Refer to Paragraph 1.J., References, for

definition of the acronyms.

2. Obey all of the warnings and cautions given in the specified manual sections.

3. Unless shown differently, these dimensions and tolerances are used:

– Linear dimensions are in inches

– Tolerance on linear dimensions, other than rivet and bolt edge margins, is plus

or minus 0.03 inch

– Tolerance on rivet and bolt edge margin is plus or minus 0.05 inch

– Angular tolerance is plus or minus 2 degrees

– Hole dimensions for standard solid rivets and fasteners are in Structural Repair

Manual (SRM) Chapter 51

– Torque Values:

— Values for structural fasteners are given in 737 Structural Repair Manual,

Chapter 51.

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

Aircraft Maintenance Manual (AMM).

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

Standard Wiring Practices Manual (SWPM).

— Values for engine maintenance tasks are included in Chapter 70 of 737

Aircraft Maintenance Manual (AMM).

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

applicable installation step.

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

SRM Chapter 51.

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

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

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

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

must be used.

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7. Refer to APPENDIX A and APPENDIX B for logic diagram(s). 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.

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

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

11. This service bulletin includes functional test procedures for the systems changed by

this service bulletin. More functional tests can possibly be necessary in accordance

with standard maintenance practices because of interruption to other airplane systems.

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

non-authoritative information from the critical and authoritative information.

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

(ATA) iSpec 2200.

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

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

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

OPTION number.

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

are in Paragraph 1.E., Compliance.

16. 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.

17. A check of the airplane maintenance and delivery records is an acceptable method

to determine if the left and right horizontal stabilizers are affected provided the installed

components can be conclusively determined from that check.

B. WORK INSTRUCTIONS

1. RC - To determine if the left and right horizontal stabilizers are affected, do one of the following

options:

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a. OPTION 1 : Do PART 1: RECORDS CHECK.

b. OPTION 2: Do PART 2: HORIZONTAL STABILIZER IDENTIFICATION PLATE INSPECTION.

PART 1: RECORDS CHECK

1. Group 1:

RC - Do a check of delivery and maintenance records to find the serial numbers of the horizontal

stabilizers installed on the airplane during production and to determine if any horizontal stabilizer

has been exchanged. Affected horizontal stabilizer serial numbers are SAIC0001-SAIC0143,

SAIC0145-SAIC0625, SAIC0627-SAIC1144, SAIC1146-SAIC1601, and SAMC1602-SAMC2639.

a. CONDITION 1: CURRENTLY INSTALLED HORIZONTAL STABILIZER NOT AFFECTED

(1) No more work is required.

b. CONDITION 2: CURRENTLY INSTALLED HORIZONTAL STABILIZER AFFECTED

(1) Do PART 4: HORIZONTAL STABILIZER REAR SPAR UPPER CHORD - HFEC

INSPECTION.

c. CONDITION 3: PRODUCTION HORIZONTAL STABILIZER NOT EXCHANGED AND SERIAL

NUMBER UNKNOWN

(1) Do PART 2: HORIZONTAL STABILIZER IDENTIFICATION PLATE INSPECTION.

d. CONDITION 4: ANY HORIZONTAL STABILIZER EXCHANGED AND INSTALLED

HORIZONTAL STABILIZER SERIAL NUMBER UNKNOWN

(1) OPTION 1: Check maintenance records to find the original delivered airplane for the

horizontal stabilizer.

(a) CONDITION 8: HORIZONTAL STABILIZER IS FROM AIRPLANE LINE NUMBER

1-378, 1118, 1783, 2505, OR 4485-5388

1) No more work is required.

(b) CONDITION 9: HORIZONTAL STABILIZER IS FROM AIRPLANE LINE NUMBER

379-1117, 1119-1782, 1784-2504, OR 2506-4484 OR IS FROM UNKNOWN

AIRPLANE

1) Do PART 2: HORIZONTAL STABILIZER IDENTIFICATION PLATE

INSPECTION.

(2) OPTION 2: Do PART 2: HORIZONTAL STABILIZER IDENTIFICATION PLATE

INSPECTION.

2. Group 2:

RC - Do a check of maintenance records to determine if any horizontal stabilizer has been

exchanged.

a. CONDITION 5: NO HORIZONTAL STABILIZER EXCHANGED OR ANY HORIZONTAL

STABILIZER EXCHANGED WITH AN UNAFFECTED HORIZONTAL STABILIZER

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(1) No more work is required.

b. CONDITION 6: ANY HORIZONTAL STABILIZER EXCHANGED AND AFFECTED

HORIZONTAL STABILIZER INSTALLED

(1) Do PART 4: HORIZONTAL STABILIZER REAR SPAR UPPER CHORD - HFEC

INSPECTION.

c. CONDITION 7: ANY HORIZONTAL STABILIZER EXCHANGED AND INSTALLED

HORIZONTAL STABILIZER SERIAL NUMBER UNKNOWN

(1) OPTION 1: Check maintenance records to find the original delivered airplane for the

installed horizontal stabilizer.

(a) CONDITION 8: HORIZONTAL STABILIZER IS FROM AIRPLANE LINE NUMBER

1-378, 1118, 1783, 2505, OR 4485-5388

1) No more work is required.

(b) CONDITION 9: HORIZONTAL STABILIZER IS FROM AIRPLANE LINE NUMBER

379-1117, 1119-1782, 1784-2504, OR 2506-4484 OR IS FROM UNKNOWN

AIRPLANE

1) Do PART 2: HORIZONTAL STABILIZER IDENTIFICATION PLATE

INSPECTION.

(2) OPTION 2: Do PART 2: HORIZONTAL STABILIZER IDENTIFICATION PLATE

INSPECTION.

PART 2: HORIZONTAL STABILIZER IDENTIFICATION PLATE INSPECTION

1. Do PART 3: PREPARATION AND ACCESS - AIRPLANE-LEVEL WORK ONLY.

2. RC - Inspect the horizontal stabilizer identification plates in accordance with FIGURE 1 and FIGURE

2.

a. CONDITION 10: NO AFFECTED SERIAL NUMBER FOUND

(1) No more work is required.

b. CONDITION 11: ANY AFFECTED SERIAL NUMBER FOUND

(1) Do PART 4: HORIZONTAL STABILIZER REAR SPAR UPPER CHORD - HFEC

INSPECTION.

3. Do PART 5: RESTORATION - AIRPLANE-LEVEL WORK ONLY.

PART 3: PREPARATION AND ACCESS - AIRPLANE-LEVEL WORK ONLY

1. Remove pressure from elevator hydraulic systems A and B. Refer to 737-600/700/800/900 AMM

27-31-00 as an accepted procedure.

2. Set the stabilizer trim cutout switches (located on the control stand) to the cutout position.

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3. Open the following circuit breakers and attach DO-NOT-CLOSE tags:

a. Circuit Breaker Panel P6-2:

(1) 6B10 FLIGHT CONTROL STAB TRIM CONT.

(2) 6D10 FLIGHT CONTROL STAB TRIM ACTUATOR.

b. Circuit Breaker Panel P18-1:

(1) 18C2 AFCS STABILIZER TRIM.

c. Circuit Breaker Panel P18-2:

(1) 18C8 FLIGHT RECORDER POSITION SENSOR.

d. Circuit Breaker Panel P18-3:

(1) 18A15 EXTERIOR LIGHTING LOGO ILLUM (If installed).

4. Use the stabilizer trim wheel on the control stand and set the horizontal stabilizer at zero degrees

(4 units of trim).

5. Install the lock F71336-501 to the stabilizer trim wheel at the control stand. Refer to

737-600/700/800/900 AMM 27-41-11 as an accepted procedure.

6. Remove and keep gap covers 332AB and 342AB or 332AT and 342AT from the horizontal stabilizer.

Refer to 737-600/700/800/900 AMM 06-42-00.

PART 4: HORIZONTAL STABILIZER REAR SPAR UPPER CHORD - HFEC INSPECTION

1. Do one of the following options:

a. RC - OPTION 1 (TO DETECT ANY CRACK 0.100 INCH OR GREATER): Do a High Frequency

Eddy Current (HFEC) inspection of the horizontal stabilizer rear spar upper chord for any

crack in accordance with FIGURE 3 and FIGURE 4.

(1) CONDITION 12: NO CRACK FOUND

(a) Do one of the following:

1) Repeat OPTION 1 (TO DETECT ANY CRACK 0.100 INCH OR GREATER)

HFEC inspection of the horizontal stabilizer rear spar upper chord for any crack

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

2) Repeat OPTION 2 (TO DETECT ANY CRACK 0.200 INCH OR GREATER)

HFEC inspection of the horizontal stabilizer rear spar upper chord for any crack

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

(2) CONDITION 13: ANY CRACK FOUND

(a) Contact Boeing to get instructions for the repair for this service bulletin, and do the

work instructed by Boeing.

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(b) Do one of the following:

1) Repeat OPTION 1 (TO DETECT ANY CRACK 0.100 INCH OR GREATER)

HFEC inspection of the horizontal stabilizer rear spar upper chord for any crack

at the unrepaired area at the repeat interval given in Paragraph 1.E., Compliance.

2) Repeat OPTION 2 (TO DETECT ANY CRACK 0.200 INCH OR GREATER)

HFEC inspection of the horizontal stabilizer rear spar upper chord for any crack

at the unrepaired area at the repeat interval given in Paragraph 1.E., Compliance.

b. RC - OPTION 2 (TO DETECT ANY CRACK 0.200 INCH OR GREATER): Do an HFEC

inspection of the horizontal stabilizer rear spar upper chord for any crack in accordance with

FIGURE 5 and FIGURE 6.

(1) CONDITION 12: NO CRACK FOUND

(a) Do one of the following:

1) Repeat OPTION 1 (TO DETECT ANY CRACK 0.100 INCH OR GREATER)

HFEC inspection of the horizontal stabilizer rear spar upper chord for any crack

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

2) Repeat OPTION 2 (TO DETECT ANY CRACK 0.200 INCH OR GREATER)

HFEC inspection of the horizontal stabilizer rear spar upper chord for any crack

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

(2) CONDITION 13: ANY CRACK FOUND

(a) Contact Boeing to get instructions for the repair for this service bulletin, and do the

work instructed by Boeing.

(b) Do one of the following:

1) Repeat OPTION 1 (TO DETECT ANY CRACK 0.100 INCH OR GREATER)

HFEC inspection of the horizontal stabilizer rear spar upper chord for any crack

at the unrepaired area at the repeat interval given in Paragraph 1.E., Compliance.

2) Repeat OPTION 2 (TO DETECT ANY CRACK 0.200 INCH OR GREATER)

HFEC inspection of the horizontal stabilizer rear spar upper chord for any crack

at the unrepaired area at the repeat interval given in Paragraph 1.E., Compliance.

PART 5: RESTORATION - AIRPLANE-LEVEL WORK ONLY

1. Install the kept gap covers 332AB and 342AB or 332AT and 342AT on the horizontal stabilizer.

Refer to 737-600/700/800/900 AMM 06-42-00.

2. Remove the lock F71336-501 from the stabilizer trim wheel at the control stand. Refer to

737-600/700/800/900 AMM 27-41-11 as an accepted procedure.

3. Close the circuit breakers that were opened above and remove the DO-NOT-CLOSE tags.

4. Reset the stabilizer trim cutout switches.

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5. Restore pressure to elevator hydraulic systems A and B. Refer to 737-600/700/800/900 AMM

27-31-00 as an accepted procedure.

6. Put the airplane back to a serviceable condition.

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FIGURE 1: LEFT SIDE HORIZONTAL STABILIZER IDENTIFICATION PLATE INSPECTION

(SHEET 1 OF 2)

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Step Task Name Identification Qty More Data

1 Inspect Identification Plate MS27253-F1 1 (a)

(a) Inspect the left side horizontal stabilizer identification plate for affected serial number SAIC0001-SAIC0143,

SAIC0145-SAIC0625, SAIC0627-SAIC1144, SAIC1146-SAIC1601, or SAMC1602-SAMC2639. The serial

number may have leading zeros in the number. The use of a flashlight and mirror may be necessary.

FIGURE 1: LEFT SIDE HORIZONTAL STABILIZER IDENTIFICATION PLATE INSPECTION

(SHEET 2 OF 2)

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FIGURE 2: RIGHT SIDE HORIZONTAL STABILIZER IDENTIFICATION PLATE INSPECTION

(SHEET 1 OF 2)

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Step Task Name Identification Qty More Data

1 Inspect Identification Plate MS27253-F1 1 (a)

(a) Inspect the left side horizontal stabilizer identification plate for affected serial number SAIC0001-SAIC0143,

SAIC0145-SAIC0625, SAIC0627-SAIC1144, SAIC1146-SAIC1601, or SAMC1602-SAMC2639. The serial

number may have leading zeros in the number. The use of a flashlight and mirror may be necessary.

FIGURE 2: RIGHT SIDE HORIZONTAL STABILIZER IDENTIFICATION PLATE INSPECTION

(SHEET 2 OF 2)

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FIGURE 3: LEFT SIDE HORIZONTAL STABILIZER REAR SPAR UPPER CHORD - HFEC INSPECTION TO

DETECT ANY CRACK 0.100 INCH OR GREATER USING A 0.050 INCH SCAN INCREMENT

(SHEET 1 OF 2)

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Step Task Name Identification Qty More Data

Horizontal Stabilizer - 1 (a)

Rear Spar Upper Chord

1 Inspect

(a) Do a High Frequency Eddy Current (HFEC) inspection to detect any crack 0.100 inch or greater using a

0.050 inch scan increment in accordance with 737 NDT Manual Part 6, 55-10-27.

FIGURE 3: LEFT SIDE HORIZONTAL STABILIZER REAR SPAR UPPER CHORD - HFEC INSPECTION TO

DETECT ANY CRACK 0.100 INCH OR GREATER USING A 0.050 INCH SCAN INCREMENT

(SHEET 2 OF 2)

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FIGURE 4: RIGHT SIDE HORIZONTAL STABILIZER REAR SPAR UPPER CHORD - HFEC INSPECTION

TO DETECT ANY CRACK 0.100 INCH OR GREATER USING A 0.050 INCH SCAN INCREMENT

(SHEET 1 OF 2)

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ALERT ALERT
Step Task Name Identification Qty More Data

Horizontal Stabilizer - 1 (a)

Rear Spar Upper Chord

1 Inspect

(a) Do a High Frequency Eddy Current (HFEC) inspection to detect any crack 0.100 inch or greater using a

0.050 inch scan increment in accordance with 737 NDT Manual Part 6, 55-10-27.

FIGURE 4: RIGHT SIDE HORIZONTAL STABILIZER REAR SPAR UPPER CHORD - HFEC INSPECTION

TO DETECT ANY CRACK 0.100 INCH OR GREATER USING A 0.050 INCH SCAN INCREMENT

(SHEET 2 OF 2)

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FIGURE 5: LEFT SIDE HORIZONTAL STABILIZER REAR SPAR UPPER CHORD - HFEC INSPECTION TO

DETECT ANY CRACK 0.200 INCH OR GREATER USING A 0.100 INCH SCAN INCREMENT

(SHEET 1 OF 2)

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ALERT ALERT
Step Task Name Identification Qty More Data

Horizontal Stabilizer - 1 (a)

Rear Spar Upper Chord

1 Inspect

(a) Do a High Frequency Eddy Current (HFEC) inspection to detect any crack 0.200 inch or greater using a

0.100 inch scan increment in accordance with 737 NDT Manual Part 6, 55-10-27.

FIGURE 5: LEFT SIDE HORIZONTAL STABILIZER REAR SPAR UPPER CHORD - HFEC INSPECTION TO

DETECT ANY CRACK 0.200 INCH OR GREATER USING A 0.100 INCH SCAN INCREMENT

(SHEET 2 OF 2)

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FIGURE 6: RIGHT SIDE HORIZONTAL STABILIZER REAR SPAR UPPER CHORD - HFEC INSPECTION

TO DETECT ANY CRACK 0.200 INCH OR GREATER USING A 0.100 INCH SCAN INCREMENT

(SHEET 1 OF 2)

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ALERT ALERT
Step Task Name Identification Qty More Data

Horizontal Stabilizer - 1 (a)

Rear Spar Upper Chord

1 Inspect

(a) Do a High Frequency Eddy Current (HFEC) inspection to detect any crack 0.200 inch or greater using a

0.100 inch scan increment in accordance with 737 NDT Manual Part 6, 55-10-27.

FIGURE 6: RIGHT SIDE HORIZONTAL STABILIZER REAR SPAR UPPER CHORD - HFEC INSPECTION

TO DETECT ANY CRACK 0.200 INCH OR GREATER USING A 0.100 INCH SCAN INCREMENT

(SHEET 2 OF 2)

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

STABILIZER IDENTIFICATION

(SHEET 1 OF 4)

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

STABILIZER IDENTIFICATION

(SHEET 2 OF 4)

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

STABILIZER IDENTIFICATION

(SHEET 3 OF 4)

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

STABILIZER IDENTIFICATION

(SHEET 4 OF 4)

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

STABILIZER IDENTIFICATION

(SHEET 1 OF 4)

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

STABILIZER IDENTIFICATION

(SHEET 2 OF 4)

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

STABILIZER IDENTIFICATION

(SHEET 3 OF 4)

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

STABILIZER IDENTIFICATION

(SHEET 4 OF 4)

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