Commercial 

Airplanes 737

Service Bulletin

SPECIAL ATTENTION

Number: 737-55-1093

Original Issue: April 09, 2012

ATA System: 5510

SUBJECT: STABILIZERS - Horizontal Stabilizer - Replacement of Rear Spar Attach Pins With

Unapproved Surface Coating

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 © 2012 Boeing.

Unpublished Work. All Rights Reserved.

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

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

Boeing Company.

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

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

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

with this document unless provided in writing by Boeing. BOEING is a trademark of Boeing Management

Company.

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BOEING SERVICE BULLETIN 737-55-1093

BLANK PAGE
Table of Contents

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

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

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

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

2. Spares Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21

B. Concurrent Requirements . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21

C. Reason . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21

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

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

F. Approval . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 22

G. Manpower . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 22

H. Weight and Balance Changes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 23

I. Electrical Load Data . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 23

J. References . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 23

1. Existing Data: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 23

2. Data Supplied with this Service Bulletin: . . . . . . . . . . . . . . . . . . . . . . . . . . . 23

3. Installation Drawings Used in the Preparation of this Service Bulletin: . . . . . . . . . . . 23

K. Publications Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 24

L. Interchangeability and Intermixability of Parts . . . . . . . . . . . . . . . . . . . . . . . . . . . 24

M. Software Accomplishment Summary . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 24

2. MATERIAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25

A. Material - Price and Availability . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25

B. Industry Support Information . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25

C. Parts Necessary for Each Airplane . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25

1. Kits/Parts . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25

2. Parts and Materials Supplied by the Operator . . . . . . . . . . . . . . . . . . . . . . . . 26

3. Parts Modified and Reidentified . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 26

4. Parts Removed and Not Replaced . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 26

D. Parts Necessary to Change Spares . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 26

E. Special Tooling - Price and Availability . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 26

F. Special Tooling Necessary to do this Service Bulletin . . . . . . . . . . . . . . . . . . . . . . . 26

3. ACCOMPLISHMENT INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 27

A. GENERAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 27

B. WORK INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 27

FIGURE 1: LEFT HORIZONTAL STABILIZER - REAR SPAR ATTACH LOCATION - PIN REPLACEMENT

. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 34

FIGURE 2: LEFT HORIZONTAL STABILIZER - REAR SPAR ATTACH LOCATION - GUSSET AND

BRACKET ASSEMBLY INSTALLATION . . . . . . . . . . . . . . . . . . . . . . . . . . . 38

FIGURE 3: RIGHT HORIZONTAL STABILIZER - REAR SPAR ATTACH LOCATION - PIN REPLACEMENT

. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 41

FIGURE 4: RIGHT HORIZONTAL STABILIZER - REAR SPAR ATTACH LOCATION - BRACKET AND

GUSSET ASSEMBLY INSTALLATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . 45

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BOEING SERVICE BULLETIN 737-55-1093

BLANK PAGE
Commercial 

Airplanes 737

Service Bulletin

SPECIAL ATTENTION

Summary Number: 737-55-1093

Original Issue: April 09, 2012

ATA System: 5510

SUBJECT: STABILIZERS - Horizontal Stabilizer - Replacement of Rear Spar Attach Pins With

Unapproved Surface Coating

BOEING RECOMMENDS THAT EACH OPERATOR EXAMINE THIS SERVICE BULLETIN IMMEDIATELY.

CONCURRENT REQUIREMENTS

None.

BACKGROUND

Boeing has found that pins with an unapproved surface coating may be installed at the horizontal stabilizer rear

spar attach locations. An incorrect procedure to apply the surface coating was used by a supplier. The pins were

installed on new airplanes and were also distributed by Boeing Spares. If pins with unapproved surface coating

are not replaced they could fail prematurely in-service, causing reduced structural integrity of the horizontal

stabilizer to fuselage intersection which could possibly result in loss of control of the airplane.

A large number of 180A1612-3 and 180A1612-4 pins that were supplied to Boeing between June 30, 2006 and

January 31, 2008 have an unapproved surface coating. These pins were distributed by Boeing Spares between

June 30, 2006 and June 17, 2008 and were installed on most new airplanes delivered between August 2006

and July 2008. These pins could also have been installed as terminating action for Boeing Service Bulletin

737-55-1086 or during maintenance in accordance with 737-600/700/800/900 MPD Section 9. No practical

non-destructive inspection procedures exist to determine whether the pins have an approved or unapproved

surface coating.

This service bulletin gives instructions to replace all 180A1612-3 and 180A1612-4 pins.

Boeing Service Related Problem (SRP) 737NG-SRP-55-0046 and Boeing Fleet Team Digest (FTD)

737NG-FTD-55-08002 are 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 Yes Paragraph 1.A.2., Spares Affected

AD Related Yes Paragraph 1.E., Compliance

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

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

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Planning Data Affected Reference

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 Yes Paragraph 2.C.1., Kits/Parts

Paragraph 2.C.2., Parts and Materials Supplied

by the Operator

Operator Supplied Material Yes

Paragraph 2.F., Special Tooling Necessary to

do this Service Bulletin

Special Tooling Required No

ACTION

Support the horizontal stabilizer(s) and disconnect, lock and configure horizontal stabilizer systems. Open

tailcone access door and remove access panels to get access to the pins. Replace the pins. Install all removed

parts and access panels and close the tailcone access door. Restore horizontal stabilizer systems and remove

horizontal stabilizer support. Put the airplane back to a serviceable condition.

EFFECTIVITY

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

airplanes.

COMPLIANCE

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

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

mandatory.

Replace all 180A1612-3 pins and 180A1612-4 pins with 180A1612-7 pins and 180A1612-8 pins in accordance

with Paragraph 3.B., Work Instructions, PART 2, before 56,000 total flight cycles or within 3,000 flight cycles

after the original issue date of this service bulletin, whichever occurs later.

NOTE: No work is necessary at any location where a 180A1612-7 or a 180A1612-8 pin is installed.

INDUSTRY SUPPORT INFORMATION

Boeing warranty remedies are available for airplanes in warranty as of July 24, 2008. Please refer to Paragraph

2.B., Industry Support Information.

MANPOWER

Airplanes Total Task Hours Elapsed Hours

All 38.70 19.30

Refer to Paragraph 1.G., Manpower.

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BOEING SERVICE BULLETIN 737-55-1093
MATERIAL INFORMATION

Boeing Supplied Kits/Parts.

Refer to Paragraph 2.A., Material - Price and Availability.

Export Controlled ECCN: 9E991 - BOEING

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BOEING SERVICE BULLETIN 737-55-1093

BLANK PAGE
Commercial 

Airplanes 737

Service Bulletin

SPECIAL ATTENTION

Number: 737-55-1093

Original Issue: April 09, 2012

ATA System: 5510

SUBJECT: STABILIZERS - Horizontal Stabilizer - Replacement of Rear Spar Attach Pins With

Unapproved Surface Coating

BOEING RECOMMENDS THAT EACH OPERATOR EXAMINE THIS SERVICE BULLETIN IMMEDIATELY.

1. PLANNING INFORMATION

A. Effectivity

1. Airplanes

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

Number, and Serial Number data.

This service bulletin is for the airplanes shown below.

GROUP CONFIGURATION DESCRIPTION

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

airplanes line number 1-3534, excluding P-8A airplanes.

1 -

Airplane Models:

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

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

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Variable Number Group

YA301 - YA302 1

YA311 - YA314 1

YA321 - YA323 1

YA336 - YA345 1

YA351 1

YA356 - YA357 1

YA366 - YA367 1

YA371 - YA377 1

YA501 - YA536 1

YA541 - YA552 1

YA571 - YA578 1

YA601 - YA615 1

YA621 - YA622 1

YA626 - YA631 1

YA635 - YA636 1

YA641 - YA642 1

YA645 - YA650 1

YA656 - YA659 1

YA666 - YA667 1

YA671 - YA672 1

YA681 - YA691 1

YA701 - YA710 1

YA721 - YA722 1

YA731 - YA734 1

YA751 - YA756 1

YA801 - YA803 1

YA809 1

YA811 - YA814 1

YA831 - YA835 1

YA841 - YA862 1

YA881 - YA882 1

YA891 - YA892 1

YA961 - YA978 1

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BOEING SERVICE BULLETIN 737-55-1093
Variable Number Group

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 - YB635 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 - YB996 1

YC001 - YC030 1

YC051 - YC084 1

YC091 - YC095 1

YC101 - YC104 1

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Variable Number Group

YC111 - YC113 1

YC121 1

YC126 - YC127 1

YC136 - YC141 1

YC146 - YC147 1

YC151 - YC156 1

YC166 - YC171 1

YC176 - YC179 1

YC186 - YC190 1

YC201 - YC203 1

YC206 - YC207 1

YC301 - YC305 1

YC321 - YC387 1

YC391 - YC394 1

YC396 1

YC401 - YC417 1

YC421 - YC422 1

YC426 - YC428 1

YC436 - YC439 1

YC441 - YC448 1

YC451 - YC455 1

YC459 1

YC461 - YC467 1

YC471 - YC499 1

YC501 - YC526 1

YC571 - YC583 1

YC587 - YC589 1

YC591 - YC593 1

YC601 - YC655 1

YC681 - YC696 1

YC701 - YC715 1

YC720 - YC725 1

YC727 - YC752 1

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BOEING SERVICE BULLETIN 737-55-1093
Variable Number Group

YC761 - YC770 1

YC781 - YC793 1

YC801 - YC892 1

YC901 - YC907 1

YC921 - YC922 1

YC931 - YC932 1

YC941 - YC951 1

YC971 - YC978 1

YC981 - YC983 1

YD001 - YD007 1

YD021 - YD025 1

YD041 - YD057 1

YD081 - YD084 1

YD101 - YD113 1

YD121 - YD126 1

YD151 - YD159 1

YD171 - YD172 1

YD201 - YD203 1

YD206 - YD209 1

YD216 - YD219 1

YD251 - YD254 1

YD256 - YD257 1

YD261 1

YD301 - YD334 1

YD391 1

YD401 - YD410 1

YD412 - YD417 1

YD481 - YD485 1

YD491 - YD499 1

YD501 - YD512 1

YD531 - YD535 1

YD541 - YD547 1

YD561 - YD564 1

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BOEING SERVICE BULLETIN 737-55-1093
Variable Number Group

YD571 - YD572 1

YD591 - YD595 1

YD601 - YD612 1

YD651 - YD655 1

YE001 - YE020 1

YE051 1

YE101 - YE109 1

YE151 - YE157 1

YE171 - YE172 1

YE201 - YE206 1

YE301 - YE305 1

YE321 - YE326 1

YE371 - YE383 1

YF001 - YF011 1

YF021 - YF049 1

YF051 - YF065 1

YF086 - YF087 1

YF106 - YF107 1

YF111 - YF114 1

YF116 - YF119 1

YF121 - YF128 1

YF176 - YF178 1

YF191 - YF192 1

YF201 - YF276 1

YF401 - YF402 1

YF431 - YF432 1

YF441 - YF442 1

YF451 - YF460 1

YF501 - YF599 1

YF601 - YF604 1

YF701 - YF707 1

YF801 - YF803 1

YF831 - YF832 1

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BOEING SERVICE BULLETIN 737-55-1093
Variable Number Group

YF836 - YF838 1

YF901 - YF905 1

YF921 - YF927 1

YF951 1

YG001 - YG044 1

YG061 - YG064 1

YG066 - YG089 1

YG091 - YG099 1

YG101 - YG104 1

YG111 - YG114 1

YG116 - YG128 1

YG201 - YG205 1

YG211 - YG214 1

YG221 - YG224 1

YG251 - YG252 1

YG501 - YG511 1

YG601 - YG602 1

YG701 1

YG711 1

YH001 - YH012 1

YH031 - YH055 1

YH071 - YH078 1

YH101 - YH132 1

YH201 - YH202 1

YH206 - YH207 1

YH301 - YH306 1

YH321 - YH322 1

YJ001 - YJ013 1

YJ021 1

YJ471 - YJ480 1

YJ501 - YJ517 1

YJ531 - YJ579 1

YJ591 - YJ599 1

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BOEING SERVICE BULLETIN 737-55-1093
Variable Number Group

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

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

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BOEING SERVICE BULLETIN 737-55-1093
Variable Number Group

YK471 - YK473 1

YK476 1

YK480 - YK487 1

YK491 1

YK495 - YK498 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

YK621 - YK634 1

YK641 - YK644 1

YK651 - YK665 1

YK671 - YK672 1

YK676 - YK677 1

YK681 - YK686 1

YK691 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 - YK928 1

YK941 - YK959 1

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BOEING SERVICE BULLETIN 737-55-1093
Variable Number Group

YK961 - YK996 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 - YL136 1

YL201 - YL226 1

YL271 - YL272 1

YL281 - YL284 1

YL301 - YL303 1

YL311 - YL314 1

YL316 - YL321 1

YL351 - YL353 1

YL371 - YL374 1

YL401 1

YL421 - YL429 1

YL431 - YL444 1

YL461 - YL478 1

YL501 - YL509 1

YL531 - YL534 1

YL541 - YL544 1

YL561 - YL569 1

YL591 - YL598 1

YL601 - YL606 1

YL611 - YL612 1

YL616 - YL617 1

YL621 1

YL626 1

YL631 - YL634 1

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BOEING SERVICE BULLETIN 737-55-1093
Variable Number Group

YL636 - YL637 1

YL661 - YL664 1

YL676 - YL681 1

YL691 1

YL696 - YL697 1

YL701 - YL706 1

YL731 1

YL751 - YL752 1

YL756 - YL757 1

YL761 - YL779 1

YL796 - YL797 1

YL801 - YL815 1

YL901 - YL910 1

YL921 - YL940 1

YL951 - YL968 1

YM101 - YM103 1

YM201 - YM242 1

YM251 - YM299 1

YM301 - YM398 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 - YM698 1

YM701 - YM710 1

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Variable Number Group

YM761 - YM765 1

YN001 - YN016 1

YN021 - YN024 1

YN061 1

YN071 - YN082 1

YN091 - YN092 1

YN101 - YN112 1

YN121 1

YN201 - YN202 1

YN211 - YN219 1

YN231 - YN236 1

YN261 1

YN501 1

YQ001 - YQ003 1

YQ011 - YQ018 1

YQ026 - YQ027 1

YQ036 - YQ042 1

YQ201 1

YQ231 1

YQ241 - YQ242 1

YQ291 - YQ295 1

YQ401 - YQ403 1

YR001 - YR005 1

YR051 - YR053 1

YR101 1

YR111 - YR112 1

YR126 1

YR166 1

YR201 - YR203 1

YR231 - YR233 1

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BOEING SERVICE BULLETIN 737-55-1093
2. Spares Affected

Examine your spares supply for the parts or components identified in Paragraph 2.C., Parts

Necessary for Each Airplane. If any parts or components are found, refer to Paragraph 2.C. for

the recommended use.

B. Concurrent Requirements

None.

C. Reason

Boeing has found that pins with an unapproved surface coating may be installed at the horizontal

stabilizer rear spar attach locations. An incorrect procedure to apply the surface coating was used by

a supplier. The pins were installed on new airplanes and were also distributed by Boeing Spares. If

pins with unapproved surface coating are not replaced they could fail prematurely in-service, causing

reduced structural integrity of the horizontal stabilizer to fuselage intersection which could possibly

result in loss of control of the airplane.

A large number of 180A1612-3 and 180A1612-4 pins that were supplied to Boeing between June 30,

2006 and January 31, 2008 have an unapproved surface coating. These pins were distributed by Boeing

Spares between June 30, 2006 and June 17, 2008 and were installed on most new airplanes delivered

between August 2006 and July 2008. These pins could also have been installed as terminating action

for Boeing Service Bulletin 737-55-1086 or during maintenance in accordance with 737-600/700/800/900

MPD Section 9. No practical non-destructive inspection procedures exist to determine whether the pins

have an approved or unapproved surface coating.

This service bulletin gives instructions to replace all 180A1612-3 and 180A1612-4 pins.

Boeing Service Related Problem (SRP) 737NG-SRP-55-0046 and Boeing Fleet Team Digest (FTD)

737NG-FTD-55-08002 are related to this service bulletin.

D. Description

Support the horizontal stabilizer(s) and disconnect, lock and configure horizontal stabilizer systems.

Open tailcone access door and remove access panels to get access to the pins. Replace the pins.

Install all removed parts and access panels and close the tailcone access door. Restore horizontal

stabilizer systems and remove horizontal stabilizer support. Put the airplane back to a serviceable

condition.

NOTE: The actions of this service bulletin do not impact the compliance of Boeing Service Bulletin

737-55-1086 or the compliance of 737-600/700/800/900 MPD Section 9 requirements related

to it.

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, 313, 314, 317, 318, 333, 343

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

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BOEING SERVICE BULLETIN 737-55-1093
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.

Replace all 180A1612-3 pins and 180A1612-4 pins with 180A1612-7 pins and 180A1612-8 pins in

accordance with Paragraph 3.B., Work Instructions, PART 2, before 56,000 total flight cycles or within

3,000 flight cycles after the original issue date of this service bulletin, whichever occurs later.

NOTE: No work is necessary at any location where a 180A1612-7 or a 180A1612-8 pin is installed.

F. Approval

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

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

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

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

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

changes.

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

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

before incorporating this service bulletin.

The Manager of the FAA Seattle Aircraft Certification Office approves the replacement of the rear spar

pins per the Accomplishment Instructions in SB 737-55-1093, Original Issue, as an alternative method

of compliance to the inspection or replacement of the rear spar pins required by paragraphs (a), (b),

(c), (d) and (e) of AD 2004-05-19. All other provisions of AD 2004-05-19 not specifically referenced in

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

G. Manpower

The table below shows an estimate of the task hours necessary to do this service bulletin 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.

Number of Task-Hours Elapsed Hours

Persons

Task

Open access 4 7.60 1.90

FIGURE 1 (a) 2 8.00 4.00

FIGURE 2 (b) 1 3.75 3.75

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BOEING SERVICE BULLETIN 737-55-1093
Number of Task-Hours Elapsed Hours

Persons

Task

FIGURE 3 (a) 2 8.00 4.00

FIGURE 4 (b) 1 3.75 3.75

Close access 4 7.60 7.60

Total per Airplane 38.70 19.30

(a) Some of the work in this figure is optional for access and may not be necessary.

(b) This figure closes optional access and may not be necessary.

H. Weight and Balance Changes

None.

I. Electrical Load Data

Not changed.

J. References

1. Existing Data:

a. Boeing Service Bulletin 737-55-1086

b. Boeing Service Related Problem (SRP) 737NG-SRP-55-0046

c. Standard Overhaul Practices Manual (SOPM) 20-30-03

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

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

f. 737NG Fleet Team Digest (FTD) 737NG-FTD-55-08002

2. Data Supplied with this Service Bulletin:

None.

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

Drawing Number Title

180A1610 INTEGRATION INSTL - HORIZONTAL STABILIZER

182A5001 RIB ASSY/INSTL - INBD CLOSURE, HORIZ. STAB.

186A3001 PANEL INSTL - GAP COVER, HORIZ STAB

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BOEING SERVICE BULLETIN 737-55-1093
These drawings were used to prepare this service bulletin. These drawings are not necessary to

make the specified changes, and are not supplied with this service bulletin. These drawings may

not be applicable to all airplane configurations or operators.

K. Publications Affected

1. Publications:

Publication Chapter-Section

737 Illustrated Parts Catalog 55-10

Component Maintenance Manual 55-10-07

2. Damage Tolerance Based Structural Inspections:

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

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

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

L. Interchangeability and Intermixability of Parts

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

M. Software Accomplishment Summary

Not affected.

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BOEING SERVICE BULLETIN 737-55-1093
2. MATERIAL INFORMATION

A. Material - Price and Availability

Boeing can supply the kits shown in Paragraph 2.C., Parts Necessary for Each Airplane. Operators

are encouraged to share schedule requirements with Boeing for incorporation of the service bulletin.

The kits are subject to the terms and conditions of the Boeing standard purchase order acknowledgment.

Prices are in United States Dollars. Terms: Net 30 days.

Reference this service bulletin and submit your purchase order by one of these methods:

1. Order on-line via ATA Spec 2000 or The Boeing PART Page

2. Fax to (206) 662-7145

REFER TO THE BOEING PART PAGE ON MYBOEINGFLEET.COM OR CONTACT FIRST RESPONDER

AT FR@BOEING.COM FOR THE LATEST REORDER LEAD TIME (ROLT) AND PRICE INFORMATION

Unit Price as of

the original issue

date of this Service Bulletin

(US Dollars)

ROLT as of the

original issue

date of this Service Bulletin

(Calendar Days)

Kit Number Name Date QTY

TOP KIT - RETROFIT 03/22/12 31 570 6,312.00

- HORIZONTAL STABILIZER ATTACH PINS

002A0001-95

B. Industry Support Information

As a result of the condition described in this service bulletin, upon accumulation of 50,000 total flight

cycles, operators may submit their purchase order for the service bulletin kit/parts at no charge for such

airplane if in-warranty as of July 24, 2008. In the event you plan on replacing pins prior to the normal

maintenance interval of 56,000 total flight cycles, please submit your request for warranty remedies to

your Warranty Regional Manager providing your planned incorporation date as well as reason for

replacing the pins prior to 56,000 total flight cycles. As a result of normal maintenance, operators

normally remove and inspect the horizontal stabilizer pins so no warranty labor remedy is available.

C. Parts Necessary for Each Airplane

1. Kits/Parts

To get the kits/parts shown below, refer to Paragraph 2.A., Material - Price and Availability.

NOTE: One top kit and the items shown in Paragraph 2.C.2., Parts and Materials Supplied by

the Operator, are necessary for each airplane.

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BOEING SERVICE BULLETIN 737-55-1093
Kit 002A0001-95

Notes

Existing Part

QTY Name Number

New Part

Number

TOP KIT - RETROFIT - HORIZONTAL -

STABILIZER ATTACH PINS

002A0001-95 -

180A1612-7 2 PIN- REAR SPAR UPPER 180A1612-3 (a)

180A1612-8 4 PIN- REAR SPAR 180A1612-4 (a)

(a) Discard the existing part. You cannot use the existing part to replace the new or changed

part.

2. Parts and Materials Supplied by the Operator

Part Number / QTY Name Notes

Specification

CORROSION INHIBITING MATERI- (a)

AL, NON-DRYING PASTE

BMS3-38 8oz

(a) See the Qualified Products List at the end of the Boeing Material Specification (BMS) for

supplier data.

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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BOEING SERVICE BULLETIN 737-55-1093
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:

– Torque limits to tighten nuts and bolts are in 737 SRM, Chapter 51

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

737 SRM, Chapter 51. Alternate fasteners are listed in 737 SRM Chapter 51.

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

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

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

SRM Chapter 51 may be used.

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.

7. 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 removal

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

8. 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.

The removed part can be discarded if a new or serviceable part is installed.

B. WORK INSTRUCTIONS

PART 1 - OPEN ACCESS

1. Do the following to get access to the pins at the left horizontal stabilizer rear spar attach locations

as necessary:

NOTE: The open access steps for the left and right horizontal stabilizers can be done concurrently.

a. Support the weight of the left horizontal stabilizer. Refer to 737-600/700/800/900 AMM 27-41-11

as an accepted procedure.

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NOTE: The horizontal stabilizer and elevator assembly weigh approximately 874 pounds.

b. Remove hydraulic pressure from system A and B. Refer to 737-600/700/800/900 AMM 27-31-00

as an accepted procedure.

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

d. Open the following circuit breakers and install safety tags.

F/O Electrical System Panel, P6-2

Row Col Number Name

B 10 C00207 FLIGHT CONTROL STAB TRIM CONT

D 10 C00840 FLIGHT CONTROL STAB TRIM ACTUATOR

CAPT Electrical System Panel, P18-1

Row Col Number Name

C 2 C00849 AFCS STABILIZER TRIM

CAPT Electrical System Panel, P18-2

Row Col Number Name

C 8 C00544 FLIGHT RECORDER POSITION SENSOR

CAPT Electrical System Panel, P18-3

Row Col Number Name

A 15 C00644 EXTERIOR LIGHTING LOGO ILLUM (a)

(a) If installed.

e. Use the stabilizer trim wheel on the control stand to set the horizontal stabilizer at zero degrees

(4 units of trim).

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

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

(1) Turn the trim wheel to put the handle at the top of the wheel.

(2) Adjust the height of the trim lock to put the trim wheel handle correctly on the yoke.

(3) Install the pin through the yoke.

(4) Install the safety pin.

g. Open the Tailcone Access Door, 318BR. Refer to 737-600/700/800/900 AMM 27-41-11 as

an accepted procedure.

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BOEING SERVICE BULLETIN 737-55-1093
h. Remove the following access panels as necessary. Refer to 737-600/700/800/900 AMM

06-42-00.

Number Name

Horizontal Stabilizer, Gap Cover, Horizontal Stabilizer

to Body

332AB

Horizontal Stabilizer, Gap Cover, Horizontal Stabilizer

to Body

332AT

Horizontal Stabilizer, Gap Cover, Horizontal Stabilizer

to Body

333AB

Horizontal Stabilizer, Gap Cover, Horizontal Stabilizer

to Body

333AT

2. Do the following to get access to the pins at the right horizontal stabilizer rear spar attach locations

as necessary:

NOTE: The open access steps for the left and right horizontal stabilizers can be done concurrently.

a. Support the weight of the right horizontal stabilizer. Refer to 737-600/700/800/900 AMM

27-41-11 as an accepted procedure.

NOTE: The horizontal stabilizer and elevator assembly weigh approximately 874 pounds.

b. Remove hydraulic pressure from system A and B. Refer to 737-600/700/800/900 AMM 27-31-00

as an accepted procedure.

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

d. Open the following circuit breakers and install safety tags.

F/O Electrical System Panel, P6-2

Row Col Number Name

B 10 C00207 FLIGHT CONTROL STAB TRIM CONT

D 10 C00840 FLIGHT CONTROL STAB TRIM ACTUATOR

CAPT Electrical System Panel, P18-1

Row Col Number Name

C 2 C00849 AFCS STABILIZER TRIM

CAPT Electrical System Panel, P18-2

Row Col Number Name

C 8 C00544 FLIGHT RECORDER POSITION SENSOR

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BOEING SERVICE BULLETIN 737-55-1093
CAPT Electrical System Panel, P18-3

Row Col Number Name

A 15 C00644 EXTERIOR LIGHTING LOGO ILLUM (a)

(a) If installed.

e. Use the stabilizer trim wheel on the control stand to set the horizontal stabilizer at zero degrees

(4 units of trim).

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

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

(1) Turn the trim wheel to put the handle at the top of the wheel.

(2) Adjust the height of the trim lock to put the trim wheel handle correctly on the yoke.

(3) Install the pin through the yoke.

(4) Install the safety pin.

g. Open the Tailcone Access Door, 318BR. Refer to 737-600/700/800/900 AMM 27-41-11 as

an accepted procedure.

h. Remove the following access panels as necessary. Refer to 737-600/700/800/900 AMM

06-42-00.

Number Name

Horizontal Stabilizer, Gap Cover, Horizontal Stabilizer

to Body

342AB

Horizontal Stabilizer, Gap Cover, Horizontal Stabilizer

to Body

342AT

Horizontal Stabilizer, Gap Cover, Horizontal Stabilizer

to Body

343AB

Horizontal Stabilizer, Gap Cover, Horizontal Stabilizer

to Body

343AT

PART 2 - PIN REPLACEMENT

1. Replace each 180A1612-3 and 180A1612-4 pin installed at the left horizontal stabilizer rear spar

attach location in accordance with FIGURE 1.

a. If the gusset and/or bracket assemblies were removed for access, reinstall them in accordance

with FIGURE 2.

2. Replace each 180A1612-3 and 180A1612-4 pin installed at the right horizontal stabilizer rear spar

attach location in accordance with FIGURE 3.

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a. If the gusset and/or bracket assemblies were removed for access, reinstall them in accordance

with FIGURE 4.

PART 3 - CLOSE ACCESS

1. Do the following to close access to the pins at the left horizontal stabilizer rear spar attach locations

as necessary:

NOTE: The close access steps for the left and right horizontal stabilizers can be done concurrently.

a. Install the following access panels. Refer to 737-600/700/800/900 AMM 06-42-00.

Number Name

Horizontal Stabilizer, Gap Cover, Horizontal Stabilizer

to Body

332AB

332AT Horizontal Stabilizer, Middle Top Gap Cover

Horizontal Stabilizer, Gap Cover, Horizontal Stabilizer

to Body

333AB

333AT Horizontal Stabilizer, Aft Top Gap Cover

b. Close the Tailcone Access Door, 318BR. Refer to 737-600/700/800/900 AMM 27-41-11 as

an accepted procedure.

c. Remove the lock, F71336-501 from the stabilizer trim wheel at the control stand.

d. Set the stabilizer trim cutout switches to the NORMAL position.

e. Remove the safety tags and close the following circuit breakers:

F/O Electrical System Panel, P6-2

Row Col Number Name

B 10 C00207 FLIGHT CONTROL STAB TRIM CONT

D 10 C00840 FLIGHT CONTROL STAB TRIM ACTUATOR

CAPT Electrical System Panel, P18-1

Row Col Number Name

C 2 C00849 AFCS STABILIZER TRIM

CAPT Electrical System Panel, P18-2

Row Col Number Name

C 8 C00544 FLIGHT RECORDER POSITION SENSOR

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BOEING SERVICE BULLETIN 737-55-1093
CAPT Electrical System Panel, P18-3

Row Col Number Name

A 15 C00644 EXTERIOR LIGHTING LOGO ILLUM (a)

(a) If installed.

f. Restore hydraulic pressure to system A and B. Refer to 737-600/700/800/900 AMM 27-31-00

as an accepted procedure.

g. Remove the support from the left horizontal stabilizer.

2. Do the following to close access to the pins at the right horizontal stabilizer rear spar attach locations

as necessary:

NOTE: The close access steps for the left and right horizontal stabilizers can be done concurrently.

a. Install the following access panels. Refer to 737-600/700/800/900 AMM 06-42-00.

Number Name

Horizontal Stabilizer, Gap Cover, Horizontal Stabilizer

to Body

342AB

342AT Horizontal Stabilizer, Middle Top Gap Cover

Horizontal Stabilizer, Gap Cover, Horizontal Stabilizer

to Body

343AB

343AT Horizontal Stabilizer, Aft Top Gap Cover

b. Close the Tailcone Access Door, 318BR. Refer to 737-600/700/800/900 AMM 27-41-11 as

an accepted procedure.

c. Remove the lock, F71336-501 from the stabilizer trim wheel at the control stand.

d. Set the stabilizer trim cutout switches to the NORMAL position.

e. Remove the safety tags and close the following circuit breakers:

F/O Electrical System Panel, P6-2

Row Col Number Name

B 10 C00207 FLIGHT CONTROL STAB TRIM CONT

D 10 C00840 FLIGHT CONTROL STAB TRIM ACTUATOR

CAPT Electrical System Panel, P18-1

Row Col Number Name

C 2 C00849 AFCS STABILIZER TRIM

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CAPT Electrical System Panel, P18-2

Row Col Number Name

C 8 C00544 FLIGHT RECORDER POSITION SENSOR

CAPT Electrical System Panel, P18-3

Row Col Number Name

A 15 C00644 EXTERIOR LIGHTING LOGO ILLUM (a)

(a) If installed.

f. Restore hydraulic pressure to system A and B. Refer to 737-600/700/800/900 AMM 27-31-00

as an accepted procedure.

g. Remove the support from the right horizontal stabilizer.

3. Put the airplane back to a serviceable condition.

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BOEING SERVICE BULLETIN 737-55-1093
FIGURE 1: LEFT HORIZONTAL STABILIZER - REAR SPAR ATTACH LOCATION - PIN REPLACEMENT

(SHEET 1 OF 4)

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FIGURE 1: LEFT HORIZONTAL STABILIZER - REAR SPAR ATTACH LOCATION - PIN REPLACEMENT

(SHEET 2 OF 4)

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BOEING SERVICE BULLETIN 737-55-1093
The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY

numbers shown below are the number of parts necessary for this figure.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

1 Remove / Keep BOLT - 2 (a)

Remove / Keep NUT - 2 (a)

Remove / Keep WASHER - 2 Under the nut (a)

Under the bolt head

(a)

Remove / Keep WASHER - 2

2 Remove / Keep BOLT - 17 (a)

Remove / Keep NUT - 17 (a)

Remove / Keep WASHER - 17 Under the nut (a)

Under the bolt head

(a)

Remove / Keep WASHER - 17

3 Remove / Keep UPPER CLIP - 1 (a)

Remove / Keep GUSSET - 1 (a)

Remove / Keep FORMER - 1 (a)

Remove / Keep SEAL - 1 (a)

Remove / Keep LOWER CLIP - 1 (a)

4 Remove / Keep BOLT - 5 (b)

Remove / Keep NUT - 5 (b)

5 Remove / Keep BRACKET - 1 (b)

Remove / Keep LOWER BRACKET - 1 (b)

CAUTION: ONLY REMOVE ONE PIN AT A TIME FOR EACH STABILIZER. IF YOU REMOVE MORE

THAN ONE PIN AT A TIME FOR EACH STABILIZER, DAMAGE TO THE HORIZONTAL STABILIZER STRUCTURE OR SYSTEMS MAY OCCUR.

PIN- REAR SPAR UP- 180A1612-3 1 (c)

PER

6 Remove

CORROSION INHIBIT- BMS3-38 - (d)

ING MATERIAL

7 Apply

PIN- REAR SPAR UP- 180A1612-7 1 (e)

PER

8 Install (New)

FIGURE 1: LEFT HORIZONTAL STABILIZER - REAR SPAR ATTACH LOCATION - PIN REPLACEMENT

(SHEET 3 OF 4)

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BOEING SERVICE BULLETIN 737-55-1093
STEP TASK NAME IDENTIFICATION QTY MORE DATA

CAUTION: ONLY REMOVE ONE PIN AT A TIME FOR EACH STABILIZER. IF YOU REMOVE MORE

THAN ONE PIN AT A TIME FOR EACH STABILIZER, DAMAGE TO THE HORIZONTAL STABILIZER STRUCTURE OR SYSTEMS MAY OCCUR.

9 Remove PIN- REAR SPAR 180A1612-4 1 (c)

CORROSION INHIBIT- BMS3-38 - (d)

ING MATERIAL

10 Apply

11 Install (New) PIN- REAR SPAR 180A1612-8 1 (e)

CAUTION: ONLY REMOVE ONE PIN AT A TIME FOR EACH STABILIZER. IF YOU REMOVE MORE

THAN ONE PIN AT A TIME FOR EACH STABILIZER, DAMAGE TO THE HORIZONTAL STABILIZER STRUCTURE OR SYSTEMS MAY OCCUR.

12 Remove PIN- REAR SPAR 180A1612-4 1 (c)

CORROSION INHIBIT- BMS3-38 - (d)

ING MATERIAL

13 Apply

14 Install (New) PIN- REAR SPAR 180A1612-8 1 (e)

(a) Removal of the Gusset Assembly is optional for access. The upper clip, gusset, former, seal and lower

clip can be removed as an assembly.

(b) Removal of the Aft Bracket Assembly is optional for access. The bracket and lower bracket can be removed

as an assembly.

(c) Remove the existing pin. Refer to 737-600/700/800/900 AMM 27-41-11 as an accepted procedure.

(d) Clean the hole, refer to SOPM 20-30-03 as an accepted procedure. Apply corrosion inhibiting compound

to the bolt and hole liberally, including the inner diameter of the bushing.

(e) Install a new pin. Refer to 737-600/700/800/900 AMM 27-41-11 as an accepted procedure.

FIGURE 1: LEFT HORIZONTAL STABILIZER - REAR SPAR ATTACH LOCATION - PIN REPLACEMENT

(SHEET 4 OF 4)

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BOEING SERVICE BULLETIN 737-55-1093
FIGURE 2: LEFT HORIZONTAL STABILIZER - REAR SPAR ATTACH LOCATION - GUSSET AND BRACKET

ASSEMBLY INSTALLATION

(SHEET 1 OF 3)

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BOEING SERVICE BULLETIN 737-55-1093
FIGURE 2: LEFT HORIZONTAL STABILIZER - REAR SPAR ATTACH LOCATION - GUSSET AND BRACKET

ASSEMBLY INSTALLATION

(SHEET 2 OF 3)

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BOEING SERVICE BULLETIN 737-55-1093
The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY

numbers shown below are the number of parts necessary for this figure.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

1 Install (Kept) UPPER CLIP - 1 (a)

Install (Kept) GUSSET - 1 (a)

Install (Kept) FORMER - 1 (a)

Install (Kept) SEAL - 1 (a)

Install (Kept) LOWER CLIP - 1 (a)

2 Install (Kept) BOLT - 17

Install (Kept) NUT - 17

Install (Kept) WASHER - 17 Under the nut

Install (Kept) WASHER - 17 Under the bolt head

3 Install (Kept) BOLT - 2

Install (Kept) NUT - 2

Install (Kept) WASHER - 2 Under the nut

Install (Kept) WASHER - 2 Under the bolt head

4 Install (Kept) BRACKET - 1 (b)

Install (Kept) LOWER BRACKET - 1 (b)

5 Install (Kept) BOLT - 5

Install (Kept) NUT - 5

(a) Install the upper clip, gusset, former, seal and lower clip as an assembly.

(b) Install the bracket and lower bracket as an assembly.

FIGURE 2: LEFT HORIZONTAL STABILIZER - REAR SPAR ATTACH LOCATION - GUSSET AND BRACKET

ASSEMBLY INSTALLATION

(SHEET 3 OF 3)

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BOEING SERVICE BULLETIN 737-55-1093
FIGURE 3: RIGHT HORIZONTAL STABILIZER - REAR SPAR ATTACH LOCATION - PIN REPLACEMENT

(SHEET 1 OF 4)

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BOEING SERVICE BULLETIN 737-55-1093
FIGURE 3: RIGHT HORIZONTAL STABILIZER - REAR SPAR ATTACH LOCATION - PIN REPLACEMENT

(SHEET 2 OF 4)

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BOEING SERVICE BULLETIN 737-55-1093
The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY

numbers shown below are the number of parts necessary for this figure.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

1 Remove / Keep BOLT - 2 (a)

Remove / Keep NUT - 2 (a)

Remove / Keep WASHER - 2 Under the nut (a)

Under the bolt head

(a)

Remove / Keep WASHER - 2

2 Remove / Keep BOLT - 17 (a)

Remove / Keep NUT - 17 (a)

Remove / Keep WASHER - 17 Under the nut (a)

Under the bolt head

(a)

Remove / Keep WASHER - 17

3 Remove / Keep UPPER CLIP - 1 (a)

Remove / Keep GUSSET - 1 (a)

Remove / Keep FORMER - 1 (a)

Remove / Keep SEAL - 1 (a)

Remove / Keep LOWER CLIP - 1 (a)

4 Remove / Keep BOLT - 5 (b)

Remove / Keep NUT - 5 (b)

5 Remove / Keep BRACKET - 1 (b)

Remove / Keep LOWER BRACKET - 1 (b)

CAUTION: ONLY REMOVE ONE PIN AT A TIME FOR EACH STABILIZER. IF YOU REMOVE MORE

THAN ONE PIN AT A TIME FOR EACH STABILIZER, DAMAGE TO THE HORIZONTAL STABILIZER STRUCTURE OR SYSTEMS MAY OCCUR.

PIN- REAR SPAR UP- 180A1612-3 1 (c)

PER

6 Remove

CORROSION INHIBIT- BMS3-38 - (d)

ING MATERIAL

7 Apply

PIN- REAR SPAR UP- 180A1612-7 1 (e)

PER

8 Install (New)

FIGURE 3: RIGHT HORIZONTAL STABILIZER - REAR SPAR ATTACH LOCATION - PIN REPLACEMENT

(SHEET 3 OF 4)

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BOEING SERVICE BULLETIN 737-55-1093
STEP TASK NAME IDENTIFICATION QTY MORE DATA

CAUTION: ONLY REMOVE ONE PIN AT A TIME FOR EACH STABILIZER. IF YOU REMOVE MORE

THAN ONE PIN AT A TIME FOR EACH STABILIZER, DAMAGE TO THE HORIZONTAL STABILIZER STRUCTURE OR SYSTEMS MAY OCCUR.

9 Remove PIN- REAR SPAR 180A1612-4 1 (c)

CORROSION INHIBIT- BMS3-38 - (d)

ING MATERIAL

10 Apply

11 Install (New) PIN- REAR SPAR 180A1612-8 1 (e)

CAUTION: ONLY REMOVE ONE PIN AT A TIME FOR EACH STABILIZER. IF YOU REMOVE MORE

THAN ONE PIN AT A TIME FOR EACH STABILIZER, DAMAGE TO THE HORIZONTAL STABILIZER STRUCTURE OR SYSTEMS MAY OCCUR.

12 Remove PIN- REAR SPAR 180A1612-4 1 (c)

CORROSION INHIBIT- BMS3-38 - (d)

ING MATERIAL

13 Apply

14 Install (New) PIN- REAR SPAR 180A1612-8 1 (e)

(a) Removal of the Gusset Assembly is optional for access. The upper clip, gusset, former, seal and lower

clip can be removed as an assembly.

(b) Removal of the Aft Bracket Assembly is optional for access. The bracket and lower bracket can be removed

as an assembly.

(c) Remove the existing pin. Refer to 737-600/700/800/900 AMM 27-41-11 as an accepted procedure.

(d) Clean the hole, refer to SOPM 20-30-03 as an accepted procedure. Apply corrosion inhibiting compound

to the bolt and hole liberally, including the inner diameter of the bushing.

(e) Install a new pin. Refer to 737-600/700/800/900 AMM 27-41-11 as an accepted procedure.

FIGURE 3: RIGHT HORIZONTAL STABILIZER - REAR SPAR ATTACH LOCATION - PIN REPLACEMENT

(SHEET 4 OF 4)

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BOEING SERVICE BULLETIN 737-55-1093
FIGURE 4: RIGHT HORIZONTAL STABILIZER - REAR SPAR ATTACH LOCATION - BRACKET AND GUSSET

ASSEMBLY INSTALLATION

(SHEET 1 OF 3)

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BOEING SERVICE BULLETIN 737-55-1093
FIGURE 4: RIGHT HORIZONTAL STABILIZER - REAR SPAR ATTACH LOCATION - BRACKET AND GUSSET

ASSEMBLY INSTALLATION

(SHEET 2 OF 3)

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BOEING SERVICE BULLETIN 737-55-1093
The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY

numbers shown below are the number of parts necessary for this figure.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

1 Install (Kept) UPPER CLIP - 1 (a)

Install (Kept) GUSSET - 1 (a)

Install (Kept) FORMER - 1 (a)

Install (Kept) SEAL - 1 (a)

Install (Kept) LOWER CLIP - 1 (a)

2 Install (Kept) BOLT - 17

Install (Kept) NUT - 17

Install (Kept) WASHER - 17 Under the nut.

Install (Kept) WASHER - 17 Under the bolt head.

3 Install (Kept) BOLT - 2

Install (Kept) NUT - 2

Install (Kept) WASHER - 2 Under the nut.

Install (Kept) WASHER - 2 Under the bolt head.

4 Install (Kept) BRACKET - 1 (b)

Install (Kept) LOWER BRACKET - 1 (b)

5 Install (Kept) BOLT - 5

Install (Kept) NUT - 5

(a) Install the upper clip, gusset, former, seal and lower clip as an assembly.

(b) Install the bracket and lower bracket as an assembly.

FIGURE 4: RIGHT HORIZONTAL STABILIZER - REAR SPAR ATTACH LOCATION - BRACKET AND GUSSET

ASSEMBLY INSTALLATION

(SHEET 3 OF 3)

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BOEING SERVICE BULLETIN 737-55-1093