Commercial 

Airplanes 777

Service Bulletin

ALERT

Number: 777-55A0018

Original Issue: July 27, 2011

Revision 1: March 06, 2012

ATA System: 5510

SUBJECT: STABILIZERS - Horizontal Stabilizer - Pivot Pin - Inspection, Rework, and Replacement

Export of this technology is controlled under the United States Export Administration Regulations (EAR) (15

CFR 730-774). An export license may be required before it is used for development, production or use by foreign

persons from specific countries. The controller of this data has the individual responsibility to abide by all export

laws.

ECCN: 9E991

BOEING PROPRIETARY, CONFIDENTIAL, AND/OR TRADE SECRET

Copyright © 2011 The Boeing Company

Unpublished Work - All Rights Reserved

Boeing claims copyright in each page of this document only to the extent that the page contains copyrightable

subject matter. Boeing also claims copyright in this document as a compilation and/or collective work.

This document includes proprietary information owned by The Boeing Company and/or one or more third parties.

Treatment of the document and the information it contains is governed by contract with Boeing. For more

information, contact The Boeing Company, P.O. Box 3707, Seattle, Washington 98124.

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

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

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connection with this document unless provided in writing by Boeing.

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4.0
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BOEING SERVICE BULLETIN 777-55A0018

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BLANK PAGE
Table of Contents

Revision Transmittal Sheet ............................................ 5

Summary ...................................................... 9

1. PLANNING INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13

A. Effectivity . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13

1. Airplanes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13

2. Spares Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 18

B. Concurrent Requirements . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 18

C. Reason . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 18

D. Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19

E. Compliance . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19

F. Approval . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21

G. Manpower . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21

H. Weight and Balance Changes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 22

I. Electrical Load Data . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 22

J. References . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 22

1. Existing Data . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 22

2. Data supplied with this Service Bulletin . . . . . . . . . . . . . . . . . . . . . . . . . . . . 22

3. Installation Drawings Used in the Preparation of this Service Bulletin . . . . . . . . . . . . 22

K. Publications Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 23

L. Interchangeability and Intermixability of Parts . . . . . . . . . . . . . . . . . . . . . . . . . . . 23

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

3. Parts Modified and Reidentified . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 27

4. Parts Removed and Not Replaced . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 28

D. Parts Necessary to Change Spares . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 28

E. Special Tooling - Price and Availability . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 28

F. Special Tooling Necessary to do this Service Bulletin . . . . . . . . . . . . . . . . . . . . . . . 28

3. ACCOMPLISHMENT INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 29

A. GENERAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 29

B. WORK INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 30

FIGURE 1: 182W6401-1 OUTER PIVOT PIN REWORK . . . . . . . . . . . . . . . . . . . . . . . . . 38

FIGURE 2: 182W6401-2 OR 182W6401-301 INNER PIVOT PIN REWORK . . . . . . . . . . . . . . 42

FIGURE 3: 182W6403-1 ANTI-ROTATION PLATE REWORK [Group 1] . . . . . . . . . . . . . . . . 44

APPENDIX A: HORIZONTAL STABILIZER TEMPORARY PIVOT PIN FABRICATION/INSTALLATION . 46

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BOEING SERVICE BULLETIN 777-55A0018

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BLANK PAGE
Commercial 

Airplanes 777

Service Bulletin

ALERT

Revision Transmittal Sheet Number: 777-55A0018

Original Issue: July 27, 2011

Revision 1: March 06, 2012

ATA System: 5510

SUBJECT: STABILIZERS - Horizontal Stabilizer - Pivot Pin - Inspection, Rework, and Replacement

This revision includes all pages of the service bulletin.

COMPLIANCE INFORMATION RELATED TO THIS REVISION

Federal Aviation Administration (FAA) Notice of Proposed Rule Making (NPRM) 2011-NM-181-AD is related to

this service bulletin.

No more work is necessary on airplanes changed in accordance with the original issue of this service bulletin.

No airplanes were added to the service bulletin effectivity. However, Group 1 from the original issue of this

service bulletin has been divided into two groups. 777-200 and 777-300 airplanes, line numbers 423 through

868, which were included in Group 1 in the original issue of this service bulletin, have been moved to new Group

3. Group 1 now includes 777-200 and 777-300 airplanes line numbers 1 through 422. Airplane Group 2 has not

been changed.

REASON FOR REVISION

This revision is sent to include a new top kit for 777-200 and 777-300 airplanes, line numbers 1 through 422.

For these airplanes, new Top Kit 005W3480-2 includes new anti-rotation plates for use when accomplishing the

Paragraph 3.B., PART 1 and PART 2 replacement. An alternative to rework existing anti-rotation plates has

also been added as new Figure 3.

These sections were changed:

1. In the BACKGROUND section of the Summary, the Summary Evaluation Table was added.

2. In the COMPLIANCE section of the Summary, reference to FAA NPRM 2011-NM-181-AD was added.

3. In Paragraph 1.A.1., Airplanes, the description of Group 1 was changed. A description of new Group 3 was

added.

4. In Paragraph 1.C., Reason, a description of the changes in Revision 1 was added.

5. In Paragraph 1.D., Description, a "no more work" statement was added for Revision 1. Maintenance Zones

were added for Group 3.

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6. In Paragraph 1.E., Compliance, reference to FAA NPRM 2011-NM-181-AD was added. Tables 1, 2 and 3

were changed in several places to specify the work in Paragraph 3.B., Work Instructions, PART 1 and PART

2, not PART 1 or PART 2. The Compliance Time grace period in Table 1 was changed to "within 750 days

after the Revision 1 date of this service bulletin." Table 2 was marked as being applicable to Group 3. The

data in the "Repeat Interval" column in Tables 2 and 3 was changed to add "after the most recent inspection".

7. In Paragraph 1.G., Manpower, the Task descriptions in the table have been changed due to changes in

Paragraph 3.B., Work Instructions.

8. In Paragraph 1.J.1., Existing Data, reference to FAA NPRM 2011-NM-181-AD was added.

9. In Paragraph 2.A., Material - Price and Availability, new Top Kit 005W3480-2 was added.

10. In Paragraph 2.C.1., Kits/Parts, new Top Kit 005W3480-2 was added for Group 1 airplanes. Existing Top

Kit 005W3480-1 was changed to be applicable to Group 2 and Group 3 airplanes.

11. In Paragraph 2.C.2., Parts and Materials Supplied by the Operator, Retention Pin 182W6401-5, Anti-Rotation

Plate 182W6403-1, Anti-Rotation Plate 182W6403-301 and Nut 182W6404-5 were added. Conditions under

which these parts may be needed were also added.

12. In Paragraph 2.C.3., Parts Modified and Reidentified, the anti-rotation plate was added for Group 1 airplanes.

13. In Paragraph 2.F., Special Tooling Necessary to do this Service Bulletin, information for jacking and support

of the horizontal stabilizer was added.

14. In Paragraph 3.A., General Information, a note that did not allow intermixing of new and reworked pivot

pins on an airplane was deleted. A new note was added to specify that the pivot pins should only be removed

from one side of the airplane at a time.

15. In Paragraph 3.B., Work Instructions, Step 1 was changed to specify removal of the load from the horizontal

stabilizer pivot joint.

16. In Paragraph 3.B., Work Instructions, PART 1 and PART 2 were changed. PART 1, which previously showed

only pivot pin replacement, now shows Left Side pivot pin replacement or rework. PART 2, which previously

showed only pivot pin rework, now shows Right Side pivot pin replacement or rework. This reorganization

of PART 1 and PART 2 results from adding the allowance to intermix new and reworked pivot pins during

the initial replacement or rework, which was not allowed in the original issue of this service bulletin.

17. In Paragraph 3.B., Work Instructions, steps were added to PART 1 and PART 2 to remove and replace or

rework the anti-rotation plates on Group 1 airplanes. The After-Replacement / Rework inspection instructions

in PART 3 were changed to add applicability to new Group 3 and to add anti-rotation plate replacement or

rework.

18. In FIGURE 1 and FIGURE 2, footnote (a) was changed. Dry film lubricant may have been previously removed

when chrome plate was removed.

19. New FIGURE 3 was added for anti-rotation plate rework.

The data given in Information Notice 777-55A0018 IN 01 is included in this revision. IN 01 was sent to advise

operators that new or reworked anti-rotation plates would be necessary on line number 1 - 422 airplanes if new

pivot pins are installed. IN 01 also advised operators of upcoming changes to horizontal stabilizer jacking

equipment SPL-2037 (Part Number J55004-1), which is referred to in 777 AMM 55-17-01 for pivot joint

disassembly.

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BOEING SERVICE BULLETIN 777-55A0018

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Vertical lines are put on the left edge of each page, except in Paragraph 1.A., Effectivity, to show the location

of important changes.

Pages with no vertical lines have no important changes.

REVISION HISTORY

Original Issue: July 27, 2011

Revision 1: March 06, 2012

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BOEING SERVICE BULLETIN 777-55A0018

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BLANK PAGE
Commercial 

Airplanes 777

Service Bulletin

ALERT

Summary Number: 777-55A0018

Original Issue: July 27, 2011

Revision 1: March 06, 2012

ATA System: 5510

SUBJECT: STABILIZERS - Horizontal Stabilizer - Pivot Pin - Inspection, Rework, and Replacement

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 replace the existing horizontal stabilizer pivot pins with new or reworked

pivot pins that have improved resistance to corrosion. If the work given in this service bulletin is not done,

horizontal stabilizer pivot pins with corrosion could eventually crack and fracture. A fractured horizontal stabilizer

pivot pin may cause excessive horizontal stabilizer freeplay and structural damage significant enough to result

in loss of control of the airplane.

The left and right horizontal stabilizer pivot joints each contain inner and outer pivot pins, along with spacers,

washers, and retaining hardware. These parts join the horizontal stabilizer to the section 48 stabilizer support

bulkhead at body station 2370.

Boeing has received several reports of horizontal stabilizer pivot pin corrosion damage on the outer diameter

chrome surface. One operator sent a corroded pivot pin to Boeing for analysis. Upon close examination, Boeing

found micro cracks in the chrome plating of the pivot pin. Some of the micro cracks extended into the base

metal.

Accomplishment of this service bulletin will remove the micro-cracking process condition found in existing

horizontal stabilizer pivot pins and ensure that the pins are free of corrosion damage that could result in pivot

pin fracture.

Boeing Fleet Team Digest (FTD) article 777 FTD 55-10001 is related to this service bulletin.

Boeing Service Related Problem (SRP) 777-SRP-55-0049 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 No 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

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 (PRR 62777-78S)

Remove the horizontal stabilizer inner and outer pivot pins. Install new pivot pins that have improved resistance

to corrosion. Alternatively, rework and re-install the existing pivot pins or install spare pivot pins that have already

been reworked in accordance with this service bulletin. After replacement, do detailed and ultrasonic inspections

of the horizontal stabilizer pivot pins. Accomplish all actions in accordance with paragraph 1.E., Compliance.

EFFECTIVITY

777-200, 777-200LR, 777-300, 777-300ER, and 777F airplanes. Refer to Paragraph 1.A.1., Airplanes, for the

list of affected airplanes.

COMPLIANCE

Federal Aviation Administration (FAA) Notice of Proposed Rule Making NPRM 2011-NM-181-AD, is related to

this service bulletin.

Refer to Paragraph 1.E., Compliance.

INDUSTRY SUPPORT INFORMATION

Boeing warranty remedies are not available for the inspection and replacement procedures given in this service

bulletin.

MANPOWER

Airplanes Total Task Hours Elapsed Hours

All airplanes. 38.00 9.50

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BOEING SERVICE BULLETIN 777-55A0018

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MATERIAL INFORMATION

Boeing Supplied Kits/Parts.

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

Operator Supplied Materials.

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BLANK PAGE
Commercial 

Airplanes 777

Service Bulletin

ALERT

Number: 777-55A0018

Original Issue: July 27, 2011

Revision 1: March 06, 2012

ATA System: 5510

SUBJECT: STABILIZERS - Horizontal Stabilizer - Pivot Pin - Inspection, Rework, and Replacement

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

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

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

THE NEW OWNER.

1. PLANNING INFORMATION

A. Effectivity

1. Airplanes

Refer to Service Bulletin Index Document D624W001 Part 3 for Airplane Variable Number, Line

Number, and Serial Number data.

This service bulletin is for the airplane(s) shown below. An equivalent change is on subsequent

production airplanes. Refer to PRR 62777-78S for data about this change.

GROUP CONFIGURATION DESCRIPTION

1 - 777-200 and 777-300 airplanes, line numbers 1 through 422.

777-200LR, 777-300ER, and 777F airplanes, line numbers 423

through 919.

2 -

3 - 777-200 and 777-300 airplanes, line numbers 424 through 868.

Airplane Models:

777-200, 777-200LR, 777-300, 777-300ER, 777F

Variable Number Group

WA001 - WA017 1

WA076 - WA080 1

WA086 - WA093 1

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Variable Number Group

WA101 - WA104 1

WA116 - WA119 1

WA131 - WA137 1

WA171 - WA175 1

WA196 - WA198 1

WA206 - WA212 1

WA221 - WA223 1

WA231 - WA232 1

WA241 - WA250 1

WA261 - WA266 1

WA281 - WA283 3

WA301 - WA304 3

WB001 - WB021 1

WB031 - WB046 1

WB051 - WB088 1

WB101 - WB106 1

WB121 - WB125 1

WB131 - WB138 1

WB139 - WB148 3

WB151 - WB155 1

WB161 - WB175 1

WB176 - WB177 3

WB181 - WB190 1

WB191 - WB194 3

WB201 - WB212 1

WB213 - WB215 3

WB231 - WB242 1

WB243 - WB247 3

WB271 - WB273 1

WB276 - WB286 1

WB291 - WB302 1

WB306 - WB307 1

WB311 - WB337 1

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BOEING SERVICE BULLETIN 777-55A0018

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Variable Number Group

WB341 - WB342 1

WB366 - WB367 1

WB368 3

WB371 - WB388 1

WB406 1

WB411 - WB413 1

WB416 - WB435 1

WB436 - WB439 3

WB446 - WB453 1

WB476 1

WB481 - WB484 1

WB501 - WB507 1

WB508 - WB512 3

WB531 - WB535 1

WB536 - WB537 3

WB551 - WB554 1

WB591 - WB595 1

WB596 - WB597 3

WB601 - WB606 1

WB611 - WB618 1

WB619 - WB622 3

WB631 - WB638 1

WB646 1

WB647 - WB649 3

WC051 - WC073 1

WC101 - WC104 1

WC111 - WC114 1

WC115 - WC120 3

WC221 - WC224 3

WC241 - WC242 1

WC243 3

WC281 - WC282 1

WC283 - WC290 3

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Variable Number Group

WC301 - WC308 3

WC361 - WC364 3

WC371 - WC374 3

WC381 - WC395 3

WC441 3

WC446 - WC449 3

WC456 - WC459 3

WC486 - WC493 3

WC506 - WC508 3

WC521 - WC522 3

WC531 - WC536 3

WC546 - WC548 3

WC556 3

WC566 - WC567 3

WC571 - WC574 3

WC581 3

WD001 - WD002 2

WD011 - WD018 2

WD031 - WD036 2

WD046 - WD055 2

WD066 - WD075 2

WD081 - WD088 2

WD091 2

WD096 2

WD101 - WD103 2

WD501 - WD513 2

WD521 - WD541 2

WD546 - WD554 2

WD561 - WD573 2

WD581 - WD599 2

WD606 - WD609 2

WD621 - WD632 2

WD651 - WD665 2

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BOEING SERVICE BULLETIN 777-55A0018

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Variable Number Group

WD671 - WD676 2

WD691 - WD709 2

WD741 - WD752 2

WD761 - WD771 2

WD786 - WD788 2

WD796 - WD813 2

WD826 - WD837 2

WD846 - WD861 2

WD871 - WD883 2

WD911 - WD915 2

WD921 - WD922 2

WD936 - WD939 2

WD946 - WD951 2

WD966 - WD970 2

WD981 - WD982 2

WD986 - WD987 2

WD996 2

WE001 - WE004 2

WE011 - WE012 2

WE021 - WE025 2

WE031 2

WE051 - WE052 2

WE071 2

WE081 - WE082 2

WE126 - WE133 2

WF001 - WF004 2

WF016 - WF020 2

WF031 - WF032 2

WF046 - WF054 2

WF076 - WF077 2

WF081 - WF088 2

WF096 - WF099 2

WF106 - WF107 2

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BOEING SERVICE BULLETIN 777-55A0018

ALERT ALERT
Variable Number Group

WF111 - WF112 2

WF121 2

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

This service bulletin gives instructions to replace the existing horizontal stabilizer pivot pins with new

or reworked pivot pins that have improved resistance to corrosion. If the work given in this service

bulletin is not done, horizontal stabilizer pivot pins with corrosion could eventually crack and fracture.

A fractured horizontal stabilizer pivot pin may cause excessive horizontal stabilizer freeplay and structural

damage significant enough to result in loss of control of the airplane.

The left and right horizontal stabilizer pivot joints each contain inner and outer pivot pins, along with

spacers, washers, and retaining hardware. These parts join the horizontal stabilizer to the section 48

stabilizer support bulkhead at body station 2370.

Boeing has received several reports of horizontal stabilizer pivot pin corrosion damage on the outer

diameter chrome surface. One operator sent a corroded pivot pin to Boeing for analysis. Upon close

examination, Boeing found micro cracks in the chrome plating of the pivot pin. Some of the micro cracks

extended into the base metal.

Accomplishment of this service bulletin will remove the micro-cracking process condition found in

existing horizontal stabilizer pivot pins and ensure that the pins are free of corrosion damage that could

result in pivot pin fracture.

Boeing Fleet Team Digest (FTD) article 777 FTD 55-10001 is related to this service bulletin.

Boeing Service Related Problem (SRP) 777-SRP-55-0049 is related to this service bulletin.

Revision 1 is sent to include a new top kit for 777-200 and 777-300 airplanes, line numbers 1 through

422. For these airplanes, new Top Kit 005W3480-2 includes new anti-rotation plates for use when

accomplishing the Paragraph 3.B., PART 1 and PART 2 replacement. An alternative to rework existing

anti-rotation plates has also been added as new Figure 3. The data given in Information Notice

777-55A0018 IN 01 is included in Revision 1. IN 01 was sent to advise operators that new or reworked

anti-rotation plates would be necessary on line number 1 - 422 airplanes if new pivot pins are installed.

IN 01 also advised operators of upcoming changes to the SPL-2037 horizontal stabilizer jacking tool,

which is referred to in 777 AMM 55-17-01 for pivot joint disassembly.

Other changes have also been made as part of Revision 1. A detailed list of these changes is given

under "Reason for Revision" in the Revision Transmittal Sheet Section of Revision 1 of this service

bulletin.

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BOEING SERVICE BULLETIN 777-55A0018

ALERT ALERT
D. Description

Remove the horizontal stabilizer inner and outer pivot pins. Install new pivot pins that have improved

resistance to corrosion. Alternatively, rework and re-install the existing pivot pins or install spare pivot

pins that have already been reworked in accordance with this service bulletin. After replacement, do

detailed and ultrasonic inspections of the horizontal stabilizer pivot pins. Accomplish all actions in

accordance with Paragraph 1.E., Compliance.

Revision 1 - No more work is necessary on airplanes changed in accordance with the original issue of

this service bulletin.

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

Group 1, 3:

Affected Maintenance Zones

Model Zone

777-200, 777-300 313, 314, 331, 341

Group 2:

Affected Maintenance Zones

Model Zone

777-200LR, 777-300ER, 777F 313, 314, 331, 341

E. Compliance

Federal Aviation Administration (FAA) Notice of Proposed Rule Making NPRM 2011-NM-181-AD, is

related to this service bulletin.

Table 1: Horizontal Stabilizer Pivot Pin Replacement or Rework

Repeat Interval

(Not to Exceed)

Compliance Time (Whichever

Occurs Later)

Condition Action

Within 750 days -

after the Revision 1 date of

this service bulletin.

Before 16,000

total flight cycles

or within 3,000

days after the

date of issuance

of the original

certificate of airworthiness or

the original export certificate,

whichever occurs first.

Do the pivot pin replacement or rework in accordance with paragraph

3.B., Work Instructions,

PART 1 and PART 2

All airplanes.

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Group 1, 3:

Table 2: After Replacement / Rework Inspections - 777-200 and 777-300 Airplanes.

Repeat Interval

(Not to Exceed)

Compliance Time (Whichever

Occurs First)

Condition Action

Within 6,000 -

days after accomplishment of

the pivot pin replacement or rework in accordance with

paragraph 3.B.,

Work Instructions, PART 1

and PART 2.

Within 32,000

flight cycles after accomplishment of the pivot pin replacement or rework

in accordance

with paragraph

3.B., Work Instructions,

PART 1 and

PART 2.

Do the after replacement

/ rework detailed and ultrasonic inspections in accordance with paragraph

3.B., Work Instructions,

PART 3.

All airplanes on which pivot

pins have been replaced or

reworked in accordance

with paragraph 3.B., Work

Instructions, PART 1 and

PART 2.

Replace the pivot pin in Before further flight. -

accordance with paragraph 3.B., Work Instructions, PART 3.

Any crack, corrosion damage, or other irregularity

found on a pivot pin during

PART 3 inspections.

Within 16,000 flight

cycles or within

3,000 days,

whichever occurs

first, after the most

recent inspection.

Repeat the after replace- - -

ment / rework detailed

and ultrasonic inspections

in accordance with paragraph 3.B., Work Instructions, PART 3.

No crack, corrosion damage, or other irregularity

found during PART 3 inspections, or pivot pins that

have been replaced.

Group 2:

Table 3: After Replacement / Rework Inspections - 777-200LR, 777-300ER, and 777F Airplanes.

Repeat Interval

(Not to Exceed)

Compliance Time (Whichever

Occurs First)

Condition Action

Within 6,000 -

days after accomplishment of

the pivot pin replacement or rework in accordance with

paragraph 3.B.,

Work Instructions, PART 1

and PART 2.

Within 32,000

flight cycles after accomplishment of the pivot pin replacement or rework

in accordance

with paragraph

3.B., Work Instructions,

PART 1 and

PART 2.

Do the after replacement

/ rework detailed and ultrasonic inspections in accordance with paragraph

3.B., Work Instructions,

PART 3.

All airplanes on which pivot

pins have been replaced or

reworked in accordance

with paragraph 3.B., Work

Instructions, PART 1 and

PART 2.

Replace the pivot pin in Before further flight. -

accordance with paragraph 3.B., Work Instructions, PART 3.

Any crack, corrosion damage, or other irregularity

found in a pivot pin during

PART 3 inspections.

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BOEING SERVICE BULLETIN 777-55A0018

ALERT ALERT
Group 2:

Table 3: After Replacement / Rework Inspections - 777-200LR, 777-300ER, and 777F Airplanes.

Repeat Interval

(Not to Exceed)

Compliance Time (Whichever

Occurs First)

Condition Action

Within 12,000 flight

cycles or within

3,000 days,

whichever occurs

first, after the most

recent inspection.

Repeat the after replace- - -

ment / rework detailed

and ultrasonic inspections

in accordance with paragraph 3.B., Work Instructions, PART 3.

No crack, corrosion damage, or other irregularity

found during PART 3 inspections, or pivot pins that

have been replaced.

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.

G. Manpower

The table below shows an estimate of the task hours necessary to do the horizontal stabilizer pivot pin

replacement 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.

Task Number of Persons Task Hours Elapsed Hours

Pivot Pin Replace- 4 16.00 4.00

ment (PART 1 and

PART 2) (a)

PART 3 - After Re- 4 22.00 5.50

placement / Rework

Detailed and Ultrasonic Inspections (a)

TOTAL FOR EACH AIRPLANE 38.00 (b) 9.50 (b)

(a) This task includes Removal and Installation steps.

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Task Number of Persons Task Hours Elapsed Hours

(b) Estimate assumes existing pivot pins are replaced with new pivot pins that

have improved resistance to corrosion. If pivot pins are reworked in accordance

with FIGURE 1 and FIGURE 2, more time will be required.

H. Weight and Balance Changes

None.

I. Electrical Load Data

Not changed.

J. References

1. Existing Data

a. Engineering Change Memo PRR 62777-78S

b. Boeing Service Related Problem (SRP) 777-SRP-55-0049

c. Standard Overhaul Practices Manual (SOPM) 20-10-02, 20-10-03, 20-10-04, 20-20-01,

20-30-02, 20-30-03, 20-42-03, 20-50-08, 20-50-10

d. 777 Aircraft Maintenance Manual (AMM) 55-17-01

e. 777 Fleet Team Digest (FTD) 55-10001

f. 777 Illustrated Parts Catalog (IPC) 55-10-00

g. 777 Non-Destructive Testing (NDT) Manual Part 4, 55-17-01

h. Boeing Process Specifications BAC5736 and BAC5882

i. Federal Aviation Administration (FAA) Notice of Proposed Rule Making (NPRM)

2011-NM-181-AD

2. Data supplied with this Service Bulletin

None.

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

This drawing was used to prepare this service bulletin. This drawing is not necessary to make the

specified changes, and is not supplied with this service bulletin. This drawing may not be applicable

to all airplane configurations.

Drawing Number Title

180W0000 Horizontal Stabilizer Top Instl

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BOEING SERVICE BULLETIN 777-55A0018

ALERT ALERT
K. Publications Affected

1. Publications:

Publication Chapter-Section

777 Illustrated Parts Catalog 55-10

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

Refer to Paragraph 2.C., Parts Necessary for Each Airplane, for interchangeability and intermixability

information.

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ALERT ALERT

BLANK PAGE
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 - 777 HORI- Available 49 265 $12,731.00

ZONTAL STABILIZER

- PIVOT PIN - REPLACEMENT

005W3480-1

October 11, 17 300 $13,751.00

2012

TOP KIT - 777 HORIZONTAL STABILIZER

- PIVOT PIN - REPLACEMENT

005W3480-2

November 8, 17

2012

December 10, 16

2012

B. Industry Support Information

Boeing warranty remedies are not available for the inspection and replacement procedures given in

this service bulletin.

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.

1.

2. For Group 1 airplanes, original Top Kit 005W3480-1 plus two 182W6403-301

Anti-rotation plates, is equivalent to new Top Kit 005W3480-2.

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BOEING SERVICE BULLETIN 777-55A0018

ALERT ALERT
Kit 005W3480

Existing Part Notes

Number

New Part Number QTY Name

-1 -2

Group 2

and

Group 3

TOP KIT - 777 -

HORIZONTAL

STABILIZER - PIVOT PIN - REPLACEMENT

005W3480-1 - .

TOP KIT - 777 - Group 1

HORIZONTAL

STABILIZER - PIVOT PIN - REPLACEMENT

005W3480-2 . -

OUTER PIN - PIV- 182W6401-1 (a) (c)

OT, HORIZONTAL

STABILIZER

182W6401-303 2 2

INNER PIN - PIV- 182W6401-2, -301 (a) (c)

OT, HORIZONTAL

STABILIZER

182W6401-304 2 2

SPACER - PIVOT, 182W6402-1 (b)

HORIZONTAL

STABILIZER

182W6402-4 1 1

SPACER - PIVOT, 182W6402-2 (b)

HORIZONTAL

STABILIZER

182W6402-5 2 2

SPACER - PIVOT, 182W6402-3 (b)

HORIZONTAL

STABILIZER

182W6402-6 1 1

ANTI-ROTATION 182W6403-1 (a) (c)

PLATE - PIVOT,

HORIZONTAL

STABILIZER

182W6403-301 . 2

(a) Discard the existing part or rework the existing part in accordance with this

service bulletin.

(b) Discard the existing part or the existing part can be re-used if it is inspected

(using detailed inspection methods) and found to be free of cracks, corrosion

damage, or other irregularity.

(c) You cannot use the existing part to replace the new part unless the existing part

has been reworked in accordance with this service bulletin. If you use the existing

part (without rework) to replace the new part, you cancel the effect of the change

given in this service bulletin.

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ALERT ALERT
2. Parts and Materials Supplied by the Operator

Part Number / QTY Name Notes

Specification

BMS 10-79, Type 2 Oz. Primer (a)

III (BMS10-11,

Type I optional)

BMS 3-33 2 Oz. Grease (a)

BMS 3-8 2 Oz. Solid (Dry) Film Lubricant (a)

182W6401-5 2 Retention Pin (b)

182W6403-1 2 Anti-Rotation Plate (d)

182W6403-301 2 Anti-Rotation Plate (c)

182W6404-5 2 Nut (b)

(a) Refer to the Qualified Products List at the end of the Boeing Material Specification (BMS)

for supplier data.

(b) If necessary, for use during pivot pin installation.

(c) Group 1 only, if 182W6401-301SP or 182W6401-304 inner pivot pins are installed and

the existing 182W6403-1 anti-rotation plate is not reworked in accordance with FIGURE

3 of this service bulletin.

(d) Group 3 only, if reworked 182W6401-2SP inner pivot pins are installed.

3. Parts Modified and Reidentified

The parts shown in the following table are modified and reidentified only if the rework given in this

service bulletin is accomplished. The QTY is the number of parts necessary for each airplane.

Existing Part QTY Name New Part Number Notes

Number

182W6401-1 2 Outer Pivot Pin 182W6401-1SP (a) (b)

182W6401-2 2 Inner Pivot Pin 182W6401-2SP (a) (b)

OR ------ ------------------------ ------------------------ ------------------------

182W6401-301 2 Inner Pivot Pin 182W6401-301SP (a) (b)

182W6403-1 2 Anti-Rotation Plate 005W3480-4 (b) (c)

(a) Make the change in accordance with this service bulletin.

(b) The "New Part Number" is the part number after the change is done in accordance with

this service bulletin. Refer to SOPM 20-50-10 as an accepted procedure to apply Code M

part mark.

(c) Group 1 only, reworked in accordance with FIGURE 3 as an alternative to new Anti-Rotation

Plate 182W6403-301.

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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 have been developed specifically for this service bulletin. However,

operators may choose to install temporary pins in the horizontal stabilizer pivot joints while existing

pivot pins are being reworked. Refer to Appendix A for fabrication and installation of temporary pins.

Accomplishment of the modification in this service bulletin requires that the horizontal stabilizer be

supported to remove the load from the pivot joint. The J55004-1 Horizontal Stabilizer Jack described

in 777 AMM 55-17-01 is an example of an appropriate tool for this purpose. However, J55004-1 is only

appropriate for airplanes line number 1 - 40. A horizontal stabilizer jacking tool for airplanes after line

number 40 is currently being designed.

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
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 limits to tighten nuts and bolts are in SRM Chapter 51

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

SRM Chapter 51.

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

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

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

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

necessary. Surface cleaning and elaborate procedures may be required.

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. 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.

8. 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.

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9. 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.

10. Deleted.

11. The Work Instructions given in this service bulletin assume that 182W6401-1 outer

pivot pins reworked in accordance with this service bulletin are reidentified as

182W6401-1SP.

12. The Work Instructions given in this service bulletin assume that 182W6401-2 inner

pivot pins reworked in accordance with this service bulletin are reidentified as

182W6401-2SP.

13. The Work Instructions given in this service bulletin assume that 182W6401-301 inner

pivot pins reworked in accordance with this service bulletin are reidentified as

182W6401-301SP.

14. The pivot pins should only be removed from one side of the airplane at a time.

B. WORK INSTRUCTIONS

Removal

CAUTION: THIS PROCEDURE ALLOWS INSTALLATION OF TEMPORARY PIVOT PINS WHILE

REWORK IS BEING DONE ON EXISTING PIVOT PINS. TEMPORARY PIVOT PINS

ARE NOT APPROVED FOR FLIGHT AND MUST BE MARKED AS TEMPORARY WHILE

IN USE. IF TEMPORARY PIVOT PINS ARE INSTALLED, MAKE SURE THEY ARE

REMOVED, AND NEW OR REWORKED PIVOT PINS INSTALLED, BEFORE FLIGHT.

1. For the initial pivot pin and spacer removal, get access, remove the load from the horizontal

stabilizer pivot joint, and remove the following parts from the airplane. Refer to 777 AMM 55-17-01

as an accepted procedure.

NOTE: If the existing pivot pins will be reworked, it is acceptable to install temporary pins while

the rework is being done. Refer to Appendix A for fabrication and installation of temporary

pins.

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ALERT ALERT
Quantity per More Data

Airplane

Part Number Part Name

182W6401-1 Outer Pivot Pin 2 Refer to 777 IPC 55-10-00.

182W6401-2 or Inner Pivot Pin 2

182W6401-301

182W6402-1 Spacer 1

182W6402-2 Spacer 2

182W6402-3 Spacer 1

182W6403-1 (Group 1 on- Anti-Rotation Plate 2

ly) or 182W6403-301

(Group 2 and Group 3)

PART 1 - Left Side Pivot Pin Replacement or Rework

1. Remove the existing horizontal stabilizer inner and outer pivot pins and spacers. Refer to the

Removal steps as an accepted procedure.

2. For the existing Left Side horizontal stabilizer pivot joint outer pin, do one of the following:

a. Replace the existing 182W6401-1 outer pivot pin with a new 182W6401-303 outer pivot pin.

or

b. Rework the existing 182W6401-1 outer pivot pin in accordance with PART 4 - Pivot Pin Rework

or replace the outer pivot pin with a 182W6401-1SP outer pivot pin that has been reworked

in accordance with PART 4 - Pivot Pin Rework.

3. Group 1:

For the existing Left Side horizontal stabilizer pivot joint inner pin, do one of the following pin

replacement steps (and the anti-rotation plate replacement step, as necessary):

a. Replace the existing 182W6401-2 inner pivot pin with a new 182W6401-304 inner pivot pin.

Also replace the existing 182W6403-1 anti-rotation plate with a 182W6403-301 anti-rotation

plate.

NOTE: As an alternative to the replacement of the 182W6403-1 anti-rotation plate, rework

the existing 182W6403-1 anti-rotation plate in accordance with FIGURE 3 or replace

the anti-rotation plate with a 005W3480-4 anti-rotation plate that has been reworked

in accordance with FIGURE 3.

or

b. Rework the existing 182W6401-2 inner pivot pin in accordance with PART 4 - Pivot Pin Rework

or replace the inner pivot pin with a 182W6401-2SP inner pivot pin that has been reworked

in accordance with PART 4 - Pivot Pin Rework.

or

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c. Rework the existing 182W6401-2 inner pivot pin in accordance with PART 4 - Pivot Pin Rework

or replace the inner pivot pin with a 182W6401-301SP inner pivot pin that has been reworked

in accordance with PART 4 - Pivot Pin Rework. Also replace the existing 182W6403-1

anti-rotation plate with a 182W6403-301 anti-rotation plate.

NOTE: As an alternative to the replacement of the 182W6403-1 anti-rotation plate, rework

the existing 182W6403-1 anti-rotation plate in accordance with FIGURE 3 or replace

the anti-rotation plate with a 005W3480-4 anti-rotation plate that has been reworked

in accordance with FIGURE 3.

4. Group 2:

For the existing Left Side horizontal stabilizer pivot joint inner pin, do one of the following pin

replacement steps (and the anti-rotation plate replacement step, as necessary):

a. Replace the existing 182W6401-301 inner pivot pin with a new 182W6401-304 inner pivot

pin.

or

b. Rework the existing 182W6401-301 inner pivot pin in accordance with PART 4 - Pivot Pin

Rework or replace the inner pivot pin with a 182W6401-301SP inner pivot pin that has been

reworked in accordance with PART 4 - Pivot Pin Rework.

5. Group 3:

For the existing Left Side horizontal stabilizer pivot joint inner pin, do one of the following pin

replacement steps (and the anti-rotation plate replacement step, as necessary):

a. Replace the existing 182W6401-301 inner pivot pin with a new 182W6401-304 inner pivot

pin.

or

b. Rework the existing 182W6401-301 inner pivot pin in accordance with PART 4 - Pivot Pin

Rework or replace the inner pivot pin with a 182W6401-301SP inner pivot pin that has been

reworked in accordance with PART 4 - Pivot Pin Rework.

or

c. Replace the existing 182W6401-301 inner pivot pin with a 182W6401-2SP inner pivot pin that

has been reworked in accordance with PART 4 - Pivot Pin Rework. Also replace the existing

182W6403-301 anti-rotation plate with a 182W6403-1 anti-rotation plate.

6. Replace the existing 182W6402-1 spacer with a 182W6402-4 spacer. As an alternative to

replacement, do a detailed inspection of the existing 182W6402-1 spacer for corrosion damage

or other irregularity.

a. If any corrosion damage or other irregularity is found, replace the existing 182W6402-1 spacer

with a 182W6402-4 spacer or another serviceable 182W6402-1 spacer. Before installing

another serviceable 182W6402-1 spacer, apply primer in accordance with PART 5 - Spacer

Refinish.

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b. If no corrosion damage or other irregularity is found, the existing spacer can be re-installed.

Before re-installing the existing spacer, apply primer in accordance with PART 5 - Spacer

Refinish.

7. Replace the existing 182W6402-2 spacer with a 182W6402-5 spacer. As an alternative to

replacement, do a detailed inspection of the existing 182W6402-2 spacer for corrosion damage

or other irregularity.

a. If any corrosion damage or other irregularity is found, replace the existing 182W6402-2 spacer

with a 182W6402-5 spacer or another serviceable 182W6402-2 spacer. Before installing

another serviceable 182W6402-2 spacer, apply primer in accordance with PART 5 - Spacer

Refinish.

b. If no corrosion damage or other irregularity is found, the existing spacer can be re-installed.

Before re-installing the existing spacer, apply primer in accordance with PART 5 - Spacer

Refinish.

8. Install the horizontal stabilizer inner and outer pivot pins and spacers. Refer to the Installation

steps as an accepted procedure. Apply grease BMS 3-33 to the inner and outer diameters of the

anti-rotation plate before installation.

PART 2 - Right Side Pivot Pin Replacement or Rework

1. Remove the existing horizontal stabilizer inner and outer pivot pins and spacers. Refer to the

Removal steps as an accepted procedure.

2. For the existing Right Side horizontal stabilizer pivot joint outer pin, do one of the following:

a. Replace the existing 182W6401-1 outer pivot pin with a new 182W6401-303 outer pivot pin.

or

b. Rework the existing 182W6401-1 outer pivot pin in accordance with PART 4 - Pivot Pin Rework

or replace the outer pivot pin with a 182W6401-1SP outer pivot pin that has been reworked

in accordance with PART 4 - Pivot Pin Rework.

3. Group 1:

For the existing Right Side horizontal stabilizer pivot joint inner pin, do one of the following pin

replacement steps (and the anti-rotation plate replacement step, as necessary):

a. Replace the existing 182W6401-2 inner pivot pin with a new 182W6401-304 inner pivot pin.

Also replace the existing 182W6403-1 anti-rotation plate with a 182W6403-301 anti-rotation

plate.

NOTE: As an alternative to the replacement of the 182W6403-1 anti-rotation plate, rework

the existing 182W6403-1 anti-rotation plate in accordance with FIGURE 3 or replace

the anti-rotation plate with a 005W3480-4 anti-rotation plate that has been reworked

in accordance with FIGURE 3.

or

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b. Rework the existing 182W6401-2 inner pivot pin in accordance with PART 4 - Pivot Pin Rework

or replace the inner pivot pin with a 182W6401-2SP inner pivot pin that has been reworked

in accordance with PART 4 - Pivot Pin Rework.

or

c. Rework the existing 182W6401-2 inner pivot pin in accordance with PART 4 - Pivot Pin Rework

or replace the inner pivot pin with a 182W6401-301SP inner pivot pin that has been reworked

in accordance with PART 4 - Pivot Pin Rework. Also replace the existing 182W6403-1

anti-rotation plate with a 182W6403-301 anti-rotation plate.

NOTE: As an alternative to the replacement of the 182W6403-1 anti-rotation plate, rework

the existing 182W6403-1 anti-rotation plate in accordance with FIGURE 3 or replace

the anti-rotation plate with a 005W3480-4 anti-rotation plate that has been reworked

in accordance with FIGURE 3.

4. Group 2:

For the existing Right Side horizontal stabilizer pivot joint inner pin, do one of the following pin

replacement steps (and the anti-rotation plate replacement step, as necessary):

a. Replace the existing 182W6401-301 inner pivot pin with a new 182W6401-304 inner pivot

pin.

or

b. Rework the existing 182W6401-301 inner pivot pin in accordance with PART 4 - Pivot Pin

Rework or replace the inner pivot pin with a 182W6401-301SP inner pivot pin that has been

reworked in accordance with PART 4 - Pivot Pin Rework.

5. Group 3:

For the existing Right Side horizontal stabilizer pivot joint inner pin, do one of the following pin

replacement steps (and the anti-rotation plate replacement step, as necessary):

a. Replace the existing 182W6401-301 inner pivot pin with a new 182W6401-304 inner pivot

pin.

or

b. Rework the existing 182W6401-301 inner pivot pin in accordance with PART 4 - Pivot Pin

Rework or replace the inner pivot pin with a 182W6401-301SP inner pivot pin that has been

reworked in accordance with PART 4 - Pivot Pin Rework.

or

c. Replace the existing 182W6401-301 inner pivot pin with a 182W6401-2SP inner pivot pin that

has been reworked in accordance with PART 4 - Pivot Pin Rework. Also replace the existing

182W6403-301 anti-rotation plate with a 182W6403-1 anti-rotation plate.

6. Replace the existing 182W6402-3 spacer with a 182W6402-6 spacer. As an alternative to

replacement, do a detailed inspection of the existing 182W6402-3 spacer for corrosion damage

or other irregularity.

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a. If any corrosion damage or other irregularity is found, replace the existing 182W6402-3 spacer

with a 182W6402-6 spacer or another serviceable 182W6402-3 spacer. Before installing

another serviceable 182W6402-3 spacer, apply primer in accordance with PART 5 - Spacer

Refinish.

b. If no corrosion damage or other irregularity is found, the existing spacer can be re-installed.

Before re-installing the existing spacer, apply primer in accordance with PART 5 - Spacer

Refinish.

7. Replace the existing 182W6402-2 spacer with a 182W6402-5 spacer. As an alternative to

replacement, do a detailed inspection of the existing 182W6402-2 spacer for corrosion damage

or other irregularity.

a. If any corrosion damage or other irregularity is found, replace the existing 182W6402-2 spacer

with a 182W6402-5 spacer or another serviceable 182W6402-2 spacer. Before installing

another serviceable 182W6402-2 spacer, apply primer in accordance with PART 5 - Spacer

Refinish.

b. If no corrosion damage or other irregularity is found, the existing spacer can be re-installed.

Before re-installing the existing spacer, apply primer in accordance with PART 5 - Spacer

Refinish.

8. Install the horizontal stabilizer inner and outer pivot pins and spacers. Refer to the Installation

steps as an accepted procedure. Apply grease BMS 3-33 to the inner and outer diameters of the

anti-rotation plate before installation.

PART 3 - After Replacement / Rework Detailed and Ultrasonic Inspections

1. Remove the horizontal stabilizer inner and outer pivot pins. Get access, remove the load from the

horizontal stabilizer pivot joint, and remove the following parts from the airplane. Refer to 777 AMM

55-17-01 as an accepted procedure for removal.

Quantity per More Data

Airplane

Part Number Part Name

182W6401-303 or Outer Pivot Pin 2 Refer to 777 IPC 55-10-00.

182W6401-1SP

182W6401-304 or Inner Pivot Pin 2

182W6401-2SP or

182W6401-301SP

2. Do a detailed inspection of the outer pivot pins and inner pivot pins for cracks, corrosion damage,

or other irregularity.

3. Do an ultrasonic inspection of the outer pivot pins for cracks in accordance with 777 NDT Part 4,

55-17-01.

NOTE: Ultrasonic inspection of the outer pivot pins in accordance with 777 NDT Part 4, 55-17-01

can be done with the outer pivot pins installed or removed. Because the pivot pins need

to be removed for detailed inspection, Boeing recommends that the ultrasonic inspection

be done with the outer pivot pins removed. If removed, clean the inner and outer diameters

of the outer pivot pins before inspection.

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ALERT ALERT
4. If any crack, corrosion damage, or other irregularity is found on an outer pivot pin, replace it with

a new or serviceable outer pivot pin with part number 182W6401-303 or 182W6401-1SP. Discard

the damaged pin.

5. Group 1, 3:

If any crack, corrosion damage, or other irregularity is found on an inner pivot pin, replace it with

a new or serviceable inner pivot pin with part number 182W6401-304 or 182W6401-2SP or

182W6401-301SP. Discard the damaged pin.

a. If a 182W6401-2SP inner pivot pin is replaced with a 182W6401-301SP or a 182W6401-304

inner pivot pin, also replace the existing 182W6403-1 anti-rotation plate with a 182W6403-301

anti-rotation plate. As an alternative, rework the existing 182W6403-1 anti-rotation plate in

accordance with FIGURE 3 or replace the anti-rotation plate with a 005W3480-4 anti-rotation

plate that has been reworked in accordance with FIGURE 3.

b. If a 182W6401-301SP or a 182W6401-304 inner pivot pin is replaced with a 182W6401-2SP

inner pivot pin, also replace the existing 182W6403-301 anti-rotation plate with a 182W6403-1

anti-rotation plate.

6. Group 2:

If any crack, corrosion damage, or other irregularity is found on an inner pivot pin, replace it with

a new or serviceable inner pivot pin with part number 182W6401-304 or 182W6401-301SP. Discard

the damaged pin.

7. If no crack, corrosion damage, or other irregularity is found or damaged pins have been replaced,

repeat the detailed and ultrasonic inspections in accordance with Paragraph 1.E., Compliance.

8. Install the horizontal stabilizer inner and outer pivot pins. Refer to the Installation steps as an

accepted procedure.

PART 4 - Pivot Pin Rework

1. Rework the 182W6401-1 outer pivot pin in accordance with FIGURE 1. If any crack is found during

inspections required by FIGURE 1, discard the pin.

2. Rework the 182W6401-2 or 182W6401-301 inner pivot pin in accordance with FIGURE 2. If any

crack is found during inspections required by FIGURE 2, discard the pin.

3. Make sure all reworked pivot pins are reidentified with an "SP" part number in accordance with

Paragraph 2.C.3., Parts Modified and Reidentified. The "SP" part mark on a pivot pin will indicate

that the pin has been shot peened.

PART 5 - Spacer Refinish

1. For 182W6402-1 spacers: Manually apply wipe-on BMS10-79, Type III primer (F-19.451) or wipe-on

BMS10-11, Type I primer (F-19.45) to the outer diameter, except no primer on the threads. Refer

to BAC5882 as an accepted procedure for application of wipe-on BMS10-79, Type III or refer to

BAC5736 as an accepted procedure for application of wipe-on BMS 10-11, Type I.

2. For 182W6402-2 spacers: Manually apply wipe-on BMS10-79, Type III primer (F-19.451) or wipe-on

BMS10-11, Type I primer (F-19.45) to the outer diameter. Refer to BAC5882 as an accepted

procedure for application of wipe-on BMS10-79, Type III or refer to BAC5736 as an accepted

procedure for application of wipe-on BMS 10-11, Type I.

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ALERT ALERT
3. For 182W6402-3 spacers: Manually apply wipe-on BMS10-79, Type III primer (F-19.451) or wipe-on

BMS10-11, Type I primer (F-19.45) to the outer diameter. Refer to BAC5882 as an accepted

procedure for application of wipe-on BMS10-79, Type III or refer to BAC5736 as an accepted

procedure for application of wipe-on BMS 10-11, Type I.

Installation

1. Install horizontal stabilizer pivot joint pins and installation hardware. Refer to 777 AMM 55-17-01

as an accepted procedure. Make sure to apply sufficient BMS3-33 grease to provide visible squeeze

out of grease between components in the joints.

2. Return the airplane to a serviceable condition.

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ALERT ALERT
FIGURE 1: 182W6401-1 OUTER PIVOT PIN REWORK

(SHEET 1 OF 4)

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ALERT ALERT
FIGURE 1: 182W6401-1 OUTER PIVOT PIN REWORK

(SHEET 2 OF 4)

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ALERT ALERT
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 each component.

IDENTIFICA- QTY MORE DATA

TION

STEP TASK NAME

Refer to SOPM

20-30-02 as an

accepted procedure.

Existing Chrome - -

Plate

1 Remove

Existing Solid - - (a)

(Dry) Film Lubricant

2 Remove

Do a magnetic

particle inspection of the pin. (b)

3 Inspect Outer Pivot Pin - -

4 Machine Outer Pivot Pin - - (c)

5 Heat Treat Outer Pivot Pin - - (d)

6 Shot Peen Outer Pivot Pin - - (e)

7 Apply Chromium Plate F-15.34 - (f)

8 Grind Outer Pivot Pin - - (g)

Solid Film Lubri- BMS3-8 - (h)

cant

9 Apply

BMS10-79, Type 1 Oz. (i)

III

10 Apply Primer

BMS10-11, Type

I (optional)

11 Apply Marking - - (j)

(a) If not removed during the previous step, remove existing solid film lubricant from the threads and inner

diameter. Refer to SOPM 20-30-02 as an accepted procedure.

(b) Refer to SOPM 20-20-01 as an accepted procedure. If any crack is found during magnetic particle inspection, discard the outer pivot pin.

(c) Machine the outer diameter of the pin to the "before plating" diameter, as shown. Maintain surface finish

of 63 Microinches Ra or better. Maintain 0.050 - 0.070 inch radius under the head as shown.

(d) Stress relieve the outer pivot pin at 875 degrees F for 1-4 hours. Refer to SOPM 20-10-02 as an accepted

procedure.

(e) Shot peen the outer diameter of the pin. Refer to SOPM 20-10-03 as an accepted procedure. Intensity =

0.012A to 0.017A. Coverage = 2.0. Overspray allowed on all areas, except threads and inner diameter.

Make sure to maintain the "before plating" diameter.

(f) Apply Class 3 chrome plate (F-15.34) to the outer diameter of the pin. Refer to SOPM 20-42-03 as an

accepted procedure.

FIGURE 1: 182W6401-1 OUTER PIVOT PIN REWORK

(SHEET 3 OF 4)

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ALERT ALERT
IDENTIFICA- QTY MORE DATA

TION

STEP TASK NAME

(g) Grind the outer diameter of the pivot pin to meet the "after plating" dimension shown. Refer to SOPM 20-

10-04 as an accepted procedure. Make sure the final surface finish is 16 Microinches Ra or better.

(h) Apply BMS3-8 solid film lubricant (F-19.10) to the threads and inner diameter. Refer to SOPM 20-50-08,

Type 8.

(i) Solvent clean the outer diameter of the pin. Refer to SOPM 20-30-03 as an accepted procedure. Manually

apply wipe-on BMS10-79, Type III primer (F-19.451) or wipe-on BMS10-11, Type I primer (F-19.45) to

the outer diameter. Refer to BAC5882 as an accepted procedure for application of wipe-on BMS10-79,

Type III or refer to BAC5736 as an accepted procedure for application of wipe-on BMS 10-11, Type I.

(j) Change the part number of the reworked outer pin to the new part number given in paragraph 2.C.3.,

Parts Modified and Reidentified. Refer to SOPM 20-50-10 as an accepted procedure to apply Code M

part mark.

FIGURE 1: 182W6401-1 OUTER PIVOT PIN REWORK

(SHEET 4 OF 4)

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BOEING SERVICE BULLETIN 777-55A0018

ALERT ALERT
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 each component.

IDENTIFICA- QTY MORE DATA

TION

STEP TASK NAME

Refer to SOPM

20-30-02 as an

accepted procedure.

Existing Chrome - -

Plate

1 Remove

Existing Solid - - (a)

(Dry) Film Lubricant

2 Remove

Do a magnetic

particle inspection of the pin. (b)

3 Inspect Inner Pivot Pin - -

FIGURE 2: 182W6401-2 OR 182W6401-301 INNER PIVOT PIN REWORK

(SHEET 1 OF 2)

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ALERT ALERT
IDENTIFICA- QTY MORE DATA

TION

STEP TASK NAME

4 Machine Inner Pivot Pin - - (c)

5 Heat Treat Inner Pivot Pin - - (d)

6 Shot Peen Inner Pivot Pin - - (e)

7 Apply Chromium Plate F-15.34 - (f)

8 Grind Inner Pivot Pin - - (g)

Solid Film Lubri- BMS3-8 - (h)

cant

9 Apply

BMS10-79, Type 1 Oz. (i)

III

10 Apply Primer

BMS10-11, Type

I (optional)

11 Apply Marking - - (j)

(a) If not removed during the previous step, remove existing solid film lubricant from the threads. Refer to

SOPM 20-30-02 as an accepted procedure.

(b) Refer to SOPM 20-20-01 as an accepted procedure. If any crack is found during magnetic particle inspection, discard the inner pivot pin.

(c) Machine the outer diameter of the pin to the "before plating" diameter, as shown. Maintain surface finish

of 63 Microinches Ra or better. Maintain 0.050 - 0.070 inch radius under the head as shown.

(d) Stress relieve the inner pivot pin at 875 degrees F for 1-4 hours. Refer to SOPM 20-10-02 as an accepted

procedure.

(e) Shot peen the outer diameter of the pin. Refer to SOPM 20-10-03 as an accepted procedure. Intensity =

0.012A to 0.017A. Coverage = 2.0. Overspray allowed on all areas, except threads. Make sure to maintain

the "before plating" diameter.

(f) Apply Class 3 chrome plate (F-15.34) to the outer diameter of the pin. Refer to SOPM 20-42-03 as an

accepted procedure.

(g) Grind the outer diameter of the pivot pin to meet the "after plating" dimension shown. Refer to SOPM 20-

10-04 as an accepted procedure. Make sure the final surface finish is 16 Microinches Ra or better.

(h) Apply BMS3-8 solid film lubricant (F-19.10) to the threads. Refer to SOPM 20-50-08, Type 8.

(i) Solvent clean the outer diameter of the pin. Refer to SOPM 20-30-03 as an accepted procedure. Manually

apply wipe-on BMS10-79, Type III primer (F-19.451) or wipe-on BMS10-11, Type I primer (F-19.45) to

the outer diameter. Refer to BAC5882 as an accepted procedure for application of wipe-on BMS10-79,

Type III or refer to BAC5736 as an accepted procedure for application of wipe-on BMS 10-11, Type I.

(j) Change the part number of the reworked inner pin to the new part number given in paragraph 2.C.3., Parts

Modified and Reidentified. Refer to SOPM 20-50-10 as an accepted procedure to apply Code M part mark.

FIGURE 2: 182W6401-2 OR 182W6401-301 INNER PIVOT PIN REWORK

(SHEET 2 OF 2)

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ALERT ALERT
This Figure applies only to: Group 1.

FIGURE 3: 182W6403-1 ANTI-ROTATION PLATE REWORK

(SHEET 1 OF 2)

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BOEING SERVICE BULLETIN 777-55A0018

ALERT ALERT
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 each component.

IDENTIFICA- QTY MORE DATA

TION

STEP TASK NAME

Anti-rotation - - (a)

Plate

1 Clean

Anti-rotation - - (b)

Plate

2 Machine

Anti-rotation - - as shown.

Plate

3 Chamfer

Do a magnetic

particle inspection of the part.

(c)

Anti-rotation - -

Plate

4 Inspect

5 Apply Finish - - (d)

6 Apply Marking - - (e)

(a) Clean the part as necessary to accomplish the rework. Refer to SOPM 20-30-03 as an accepted procedure.

(b) Machine the outer diameter of the anti-rotation plate to the diameter shown. Blend new diameter into existing relief cut to create new 0.050 - 0.070 inch radius as shown. Break sharp edges 0.010 - 0.020 R after

machining. Maintain surface finish of 125 Microinches Ra or better on all machined surfaces.

(c) Refer to SOPM 20-20-01 as an accepted procedure. If any crack is found during magnetic particle inspection, discard the part.

(d) Passivate the entire part. Refer to SOPM 20-30-03 or BAC5625, Method II as an accepted procedure. As

an option, locally passivate only the newly machined areas of the part.

(e) Change the part number of the reworked anti-rotation plate to the new part number given in Paragraph

2.C.3., Parts Modified and Reidentified. Refer to SOPM 20-50-10 as an accepted procedure to apply Code

RO part mark.

FIGURE 3: 182W6403-1 ANTI-ROTATION PLATE REWORK

(SHEET 2 OF 2)

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ALERT ALERT
Fabricate temporary pins, as necessary, for installation in the horizontal stabilizer pivot joints while the inner

and outer pivot pins are being reworked. Fabricate temporary pins from 150 ksi minimum 15-5PH stainless steel.

Fabricate temporary pins to the dimensions shown in Illustration 1. Install the temporary pins as shown in

Illustration 2.

NOTE: TEMPORARY PINS ARE NOT APPROVED FOR FLIGHT.

APPENDIX A: HORIZONTAL STABILIZER TEMPORARY PIVOT PIN FABRICATION/INSTALLATION

(SHEET 1 OF 2)

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ALERT ALERT
NOTE: RETENTION BOLT: INSTALL ANY AVAILABLE 1/4 INCH BOLT, WASHERS, AND LOCK NUT TO

ENSURE THE TEMPORARY PIN CANNOT MIGRATE OUT OF THE JOINT. IF BOLTS ARE NOT

AVAILABLE, OTHER RETENTION METHODS THAT KEEP THE PIN FROM MIGRATING ARE

ACCEPTABLE.

APPENDIX A: HORIZONTAL STABILIZER TEMPORARY PIVOT PIN FABRICATION/INSTALLATION

(SHEET 2 OF 2)

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ALERT ALERT