# Boeing Alert Service Bulletin 777-55A0018: Revision 1

- Rights: © The Boeing Company. Filed by the FAA in regulations.gov docket FAA-2011-1259; AD 2012-10-10 incorporates this document by reference. Not covered by OpenAirDocs’ CC0 dedication.
- Document: [Boeing Alert Service Bulletin 777-55A0018](https://openairdocs.org/service-documents/boeing/777-55a0018.md)
- Title as filed: U.S. DOT/FAA - Service Information
- Pages: 47
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## Text

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### Page 1

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.
9E991ECCN:
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Unpublished Work - All Rights Reserved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
Boeing livery are all trademarks owned by The Boeing Company; and no trademark license is granted in
connection with this document unless provided in writing by Boeing.
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Table of Contents
Revision Transmittal Sheet ............................................ 5
Summary ...................................................... 9
1. PLANNING INFORMATION ........................................ 1 3
A. Effectivity ............................................... 1 3
1. Airplanes ............................................ 1 3
2. Spares Affected ........................................ 1 8
B. Concurrent Requirements ...................................... 1 8
C. Reason ................................................ 1 8
D. Description .............................................. 1 9
E. Compliance .............................................. 1 9
F. Approval ............................................... 2 1
G. Manpower .............................................. 2 1
H. Weight and Balance Changes .................................... 2 2
I. Electrical Load Data ......................................... 2 2
J. References .............................................. 2 2
1. Existing Data .......................................... 2 2
2. Data supplied with this Service Bulletin ............................ 2 2
3. Installation Drawings Used in the Preparation of this Service Bulletin ............ 2 2
K. Publications Affected ........................................ 2 3
L. Interchangeability and Intermixability of Parts ........................... 2 3
2. MATERIAL INFORMATION ........................................ 2 5
A. Material - Price and Availability ................................... 2 5
B. Industry Support Information .................................... 2 5
C. Parts Necessary For Each Airplane ................................. 2 5
1. Kits/Parts ............................................ 2 5
2. Parts and Materials Supplied by the Operator ........................ 2 7
3. Parts Modified and Reidentified ................................ 2 7
4. Parts Removed and Not Replaced .............................. 2 8
D. Parts Necessary to Change Spares ................................. 2 8
E. Special Tooling - Price and Availability ............................... 2 8
F. Special Tooling Necessary to do this Service Bulletin ....................... 2 8
3. ACCOMPLISHMENT INSTRUCTIONS .................................. 2 9
A. GENERAL INFORMATION ..................................... 2 9
B. WORK INSTRUCTIONS ....................................... 3 0
FIGURE 1: 182W6401-1 OUTER PIVOT PIN REWORK ......................... 3 8
FIGURE 2: 182W6401-2 OR 182W6401-301 INNER PIVOT PIN REWORK .............. 4 2
FIGURE 3: 182W6403-1 ANTI-ROTATION PLATE REWORK [Group 1] ................ 4 4
APPENDIX A: HORIZONTAL STABILIZER TEMPORARY PIVOT PIN FABRICATION/INSTALLATION . 46
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Commercial 
Airplanes
777
Service Bulletin
ALERT
Revision Transmittal SheetNumber: 777-55A0018Original 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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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
July 27, 2011Original Issue:
March 06, 2012Revision 1:
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Commercial 
Airplanes
777
Service Bulletin
ALERT
SummaryNumber: 777-55A0018Original 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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ReferenceAffectedPlanning Data
Paragraph 1.A.2., Spares AffectedNoSpares Affected
Paragraph 1.E., ComplianceYesAD Related
Paragraph 1.H., Weight and Balance ChangesNoWeight and Balance Change
Paragraph 1.I., Electrical Load DataNoElectrical Load Changed
Paragraph 1.K., Publications AffectedYesPublications Affected
Paragraph 1.K., Publications AffectedNoAirplane Flight Operations Affected (Flight Crew
Operations Manual and/or FAA Approved Air-
plane Flight Manual)
Paragraph 2.C.1., Kits/PartsYesKits/Parts Required
Paragraph 2.C.2., Parts and Materials Supplied
by the Operator
YesOperator Supplied Material
Paragraph 2.F., Special Tooling Necessary to
do this Service Bulletin
NoSpecial Tooling Required
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
Elapsed HoursTotal Task HoursAirplanes
9.5038.00All airplanes.
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BOEING SERVICE BULLETIN 777-55A0018
ALERT  ALERT
MATERIAL INFORMATION
Boeing Supplied Kits/Parts.
Refer to Paragraph 2.A., Material - Price and Availability.
Operator Supplied Materials.
HORIZONTAL STABILIZER
REMOVE THE HORIZONTAL STABILIZER INNER AND OUTER  PIVOT JOINT
PIVOT PINS. INSTALL NEW PIVOT PINS THAT HAVE  REWORK AND RE-INSTALL THE EXISTING PIVOT PINS OR  IMPROVED RESISTANCE TO CORROSION. ALTERNATIVELY,  RIGHT SIDE SIMILAR)  (LEFT SIDE SHOWN  ineD
INSTALL SPARE PIVOT PINS THAT HAVE ALREADY BEEN
REWORKED IN ACCORDANCE WITH THIS SERVICE
BULLETIN. DO AFTER REPLACEMENT INSPECTIONS OF THE
HORIZONTAL STABILIZER PIVOT PINS. ACCOMPLISH ALL  2043045
ACTIONS IN ACCORDANCE WITH PARAGRAPH 1.E.,
COMPLIANCE.
Original Issue: July 27, 2011
Revision 1: March 06, 2012  777-55A0018
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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.
DESCRIPTIONCONFIGURATIONGROUP
777-200 and 777-300 airplanes, line numbers 1 through 422.-1
777-200LR, 777-300ER, and 777F airplanes, line numbers 423
through 919.
-2
777-200 and 777-300 airplanes, line numbers 424 through 868.-3
Airplane Models:
777-200, 777-200LR, 777-300, 777-300ER, 777F
GroupVariable Number
1WA001 - WA017
1WA076 - WA080
1WA086 - WA093
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GroupVariable Number
1WA101 - WA104
1WA116 - WA119
1WA131 - WA137
1WA171 - WA175
1WA196 - WA198
1WA206 - WA212
1WA221 - WA223
1WA231 - WA232
1WA241 - WA250
1WA261 - WA266
3WA281 - WA283
3WA301 - WA304
1WB001 - WB021
1WB031 - WB046
1WB051 - WB088
1WB101 - WB106
1WB121 - WB125
1WB131 - WB138
3WB139 - WB148
1WB151 - WB155
1WB161 - WB175
3WB176 - WB177
1WB181 - WB190
3WB191 - WB194
1WB201 - WB212
3WB213 - WB215
1WB231 - WB242
3WB243 - WB247
1WB271 - WB273
1WB276 - WB286
1WB291 - WB302
1WB306 - WB307
1WB311 - WB337
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GroupVariable Number
1WB341 - WB342
1WB366 - WB367
3WB368
1WB371 - WB388
1WB406
1WB411 - WB413
1WB416 - WB435
3WB436 - WB439
1WB446 - WB453
1WB476
1WB481 - WB484
1WB501 - WB507
3WB508 - WB512
1WB531 - WB535
3WB536 - WB537
1WB551 - WB554
1WB591 - WB595
3WB596 - WB597
1WB601 - WB606
1WB611 - WB618
3WB619 - WB622
1WB631 - WB638
1WB646
3WB647 - WB649
1WC051 - WC073
1WC101 - WC104
1WC111 - WC114
3WC115 - WC120
3WC221 - WC224
1WC241 - WC242
3WC243
1WC281 - WC282
3WC283 - WC290
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GroupVariable Number
3WC301 - WC308
3WC361 - WC364
3WC371 - WC374
3WC381 - WC395
3WC441
3WC446 - WC449
3WC456 - WC459
3WC486 - WC493
3WC506 - WC508
3WC521 - WC522
3WC531 - WC536
3WC546 - WC548
3WC556
3WC566 - WC567
3WC571 - WC574
3WC581
2WD001 - WD002
2WD011 - WD018
2WD031 - WD036
2WD046 - WD055
2WD066 - WD075
2WD081 - WD088
2WD091
2WD096
2WD101 - WD103
2WD501 - WD513
2WD521 - WD541
2WD546 - WD554
2WD561 - WD573
2WD581 - WD599
2WD606 - WD609
2WD621 - WD632
2WD651 - WD665
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GroupVariable Number
2WD671 - WD676
2WD691 - WD709
2WD741 - WD752
2WD761 - WD771
2WD786 - WD788
2WD796 - WD813
2WD826 - WD837
2WD846 - WD861
2WD871 - WD883
2WD911 - WD915
2WD921 - WD922
2WD936 - WD939
2WD946 - WD951
2WD966 - WD970
2WD981 - WD982
2WD986 - WD987
2WD996
2WE001 - WE004
2WE011 - WE012
2WE021 - WE025
2WE031
2WE051 - WE052
2WE071
2WE081 - WE082
2WE126 - WE133
2WF001 - WF004
2WF016 - WF020
2WF031 - WF032
2WF046 - WF054
2WF076 - WF077
2WF081 - WF088
2WF096 - WF099
2WF106 - WF107
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GroupVariable Number
2WF111 - WF112
2WF121
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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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
ZoneModel
313, 314, 331, 341777-200, 777-300
Group 2:
Affected Maintenance Zones
ZoneModel
313, 314, 331, 341777-200LR, 777-300ER, 777F
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)
ActionCondition
-Within 750 days
after the Revi-
sion 1 date of
this service bul-
letin.
Before 16,000
total flight cycles
or within 3,000
days after the
date of issuance
of the original
certificate of air-
worthiness or
the original ex-
port certificate,
whichever oc-
curs first.
Do the pivot pin replace-
ment or rework in accor-
dance 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)
ActionCondition
-Within 6,000
days after ac-
complishment of
the pivot pin re-
placement or re-
work in accor-
dance with
paragraph 3.B.,
Work Instruc-
tions, PART 1
and PART 2.
Within 32,000
flight cycles af-
ter accomplish-
ment of the piv-
ot pin replace-
ment or rework
in accordance
with paragraph
3.B., Work In-
structions,
PART 1 and
PART 2.
Do the after replacement
/ rework detailed and ultra-
sonic inspections in accor-
dance 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.
-Before further flight.Replace the pivot pin in
accordance with para-
graph 3.B., Work Instruc-
tions, PART 3.
Any crack, corrosion dam-
age, 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 para-
graph 3.B., Work Instruc-
tions, PART 3.
No crack, corrosion dam-
age, or other irregularity
found during PART 3 in-
spections, 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)
ActionCondition
-Within 6,000
days after ac-
complishment of
the pivot pin re-
placement or re-
work in accor-
dance with
paragraph 3.B.,
Work Instruc-
tions, PART 1
and PART 2.
Within 32,000
flight cycles af-
ter accomplish-
ment of the piv-
ot pin replace-
ment or rework
in accordance
with paragraph
3.B., Work In-
structions,
PART 1 and
PART 2.
Do the after replacement
/ rework detailed and ultra-
sonic inspections in accor-
dance 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.
-Before further flight.Replace the pivot pin in
accordance with para-
graph 3.B., Work Instruc-
tions, PART 3.
Any crack, corrosion dam-
age, or other irregularity
found in a pivot pin during
PART 3 inspections.
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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)
ActionCondition
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 para-
graph 3.B., Work Instruc-
tions, PART 3.
No crack, corrosion dam-
age, or other irregularity
found during PART 3 in-
spections, 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.
Elapsed HoursTask HoursNumber of PersonsTask
4.0016.004Pivot Pin Replace-
ment (PART 1 and
PART 2) (a)
5.5022.004PART 3 - After Re-
placement / Rework
Detailed and Ultra-
sonic Inspections (a)
9.50 (b)38.00 (b)TOTAL FOR EACH AIRPLANE
(a) This task includes Removal and Installation steps.
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Elapsed HoursTask HoursNumber of PersonsTask
(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.
TitleDrawing Number
Horizontal Stabilizer Top Instl180W0000
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K. Publications Affected
1. Publications:
Chapter-SectionPublication
55-10777 Illustrated Parts Catalog
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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### Page 25

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 Ser-
vice Bulletin (US
Dollars)
ROLT as of the
original issue
date of this Ser-
vice Bulletin (Cal-
endar Days)
QTYDateNameKit Number
$12,731.0026549AvailableTOP KIT - 777 HORI-
ZONTAL STABILIZER
- PIVOT PIN - RE-
PLACEMENT
005W3480-1
$13,751.0030017October 11,
2012
TOP KIT - 777 HORI-
ZONTAL STABILIZER
- PIVOT PIN - RE-
PLACEMENT
005W3480-2
17November 8,
2012
16December 10,
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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### Page 26

Kit 005W3480
NotesExisting Part
Number
NameQTYNew Part Number
-2-1
Group 2
and
Group 3
-TOP KIT - 777
HORIZONTAL
STABILIZER - PIV-
OT PIN - RE-
PLACEMENT
.-005W3480-1
Group 1-TOP KIT - 777
HORIZONTAL
STABILIZER - PIV-
OT PIN - RE-
PLACEMENT
-.005W3480-2
(a) (c)182W6401-1OUTER PIN - PIV-
OT, HORIZONTAL
STABILIZER
22182W6401-303
(a) (c)182W6401-2, -301INNER PIN - PIV-
OT, HORIZONTAL
STABILIZER
22182W6401-304
(b)182W6402-1SPACER - PIVOT,
HORIZONTAL
STABILIZER
11182W6402-4
(b)182W6402-2SPACER - PIVOT,
HORIZONTAL
STABILIZER
22182W6402-5
(b)182W6402-3SPACER - PIVOT,
HORIZONTAL
STABILIZER
11182W6402-6
(a) (c)182W6403-1ANTI-ROTATION
PLATE - PIVOT,
HORIZONTAL
STABILIZER
2.182W6403-301
(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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2. Parts and Materials Supplied by the Operator
NotesNameQTYPart Number /
Specification
(a)Primer2 Oz.BMS 10-79, Type
III (BMS10-11,
Type I optional)
(a)Grease2 Oz.BMS 3-33
(a)Solid (Dry) Film Lubricant2 Oz.BMS 3-8
(b)Retention Pin2182W6401-5
(d)Anti-Rotation Plate2182W6403-1
(c)Anti-Rotation Plate2182W6403-301
(b)Nut2182W6404-5
(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.
NotesNew Part NumberNameQTYExisting Part
Number
(a) (b)182W6401-1SPOuter Pivot Pin2182W6401-1
(a) (b)182W6401-2SPInner Pivot Pin2182W6401-2
------------------------------------------------------------------------------OR
(a) (b)182W6401-301SPInner Pivot Pin2182W6401-301
(b) (c)005W3480-4Anti-Rotation Plate2182W6403-1
(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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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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More DataQuantity per
Airplane
Part NamePart Number
Refer to 777 IPC 55-10-00.2Outer Pivot Pin182W6401-1
2Inner Pivot Pin182W6401-2 or
182W6401-301
1Spacer182W6402-1
2Spacer182W6402-2
1Spacer182W6402-3
2Anti-Rotation Plate182W6403-1 (Group 1 on-
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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ALERTALERT

### Page 34

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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ALERTALERT

### Page 35

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.
More DataQuantity per
Airplane
Part NamePart Number
Refer to 777 IPC 55-10-00.2Outer Pivot Pin182W6401-303 or
182W6401-1SP
2Inner Pivot Pin182W6401-304 or
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.
BOEING PROPRIETARY -
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777-55A0018Revision 1: March 06, 2012
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ALERTALERT

### Page 36

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.
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: July 27, 2011
777-55A0018Revision 1: March 06, 2012
36 of 47
BOEING SERVICE BULLETIN 777-55A0018
ALERTALERT

### Page 37

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.
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: July 27, 2011
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ALERTALERT

### Page 38 (OCR)

BOEING SERVICE BULLETIN 777-55A0018
ALERT  ALERT
110
0.08 MAX CHROME PLATE RUNOUT
- 0.08 MAX CHROME PLATE RUNOUT
63  - 2.7395  2.7370 DIA BEFORE  PLATING  (ROTATED 45° CCW)  A-A
16/
2.7470  DIA AFTER
2.7455  PLATING
OUTER PIVOT PIN
FIGURE 1: 182W6401-1 OUTER PIVOT PIN REWORK
(SHEET 1 OF 4)
Original Issue: July 27, 2011
Revision 1 March 06, 2012  BOEING PROPRIETARY -  777-55A0018
Copyright © Unpublished Work - See page 1 for details.  38 of 47

### Page 39 (OCR)

BOEING SERVICE BULLETIN 777-55A0018
ALERT  ALERT
0.070 R
0.050
(2)
2049467
FIGURE 1: 182W6401-1 OUTER PIVOT PIN REWORK
(SHEET 2 OF 4)
Original Issue: July 27, 2011
Revision 1 March 06, 2012  BOEING PROPRIETARY -  777-55A0018
Copyright © Unpublished Work - See page 1 for details.  39 of 47

### Page 40

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.
MORE DATAQTYIDENTIFICA-
TION
NAMETASKSTEP
Refer to SOPM
20-30-02 as an
accepted proce-
dure.
--Existing Chrome
Plate
Remove1
(a)--Existing Solid
(Dry) Film Lubri-
cant
Remove2
Do a magnetic
particle inspec-
tion of the pin. (b)
--Outer Pivot PinInspect3
(c)--Outer Pivot PinMachine4
(d)--Outer Pivot PinHeat Treat5
(e)--Outer Pivot PinShot Peen6
(f)-F-15.34Chromium PlateApply7
(g)--Outer Pivot PinGrind8
(h)-BMS3-8Solid Film Lubri-
cant
Apply9
(i)1 Oz.BMS10-79, Type
III
PrimerApply10
BMS10-11, Type
I (optional)
(j)--MarkingApply11
(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 inspec-
tion, 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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BOEING SERVICE BULLETIN 777-55A0018
ALERTALERT

### Page 41

MORE DATAQTYIDENTIFICA-
TION
NAMETASKSTEP
(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)
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: July 27, 2011
777-55A0018Revision 1 March 06, 2012
41 of 47
BOEING SERVICE BULLETIN 777-55A0018
ALERTALERT

### Page 42

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.
MORE DATAQTYIDENTIFICA-
TION
NAMETASKSTEP
Refer to SOPM
20-30-02 as an
accepted proce-
dure.
--Existing Chrome
Plate
Remove1
(a)--Existing Solid
(Dry) Film Lubri-
cant
Remove2
Do a magnetic
particle inspec-
tion of the pin. (b)
--Inner Pivot PinInspect3
FIGURE 2: 182W6401-2 OR 182W6401-301 INNER PIVOT PIN REWORK
(SHEET 1 OF 2)
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: July 27, 2011
777-55A0018Revision 1 March 06, 2012
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BOEING SERVICE BULLETIN 777-55A0018
ALERTALERT

### Page 43

MORE DATAQTYIDENTIFICA-
TION
NAMETASKSTEP
(c)--Inner Pivot PinMachine4
(d)--Inner Pivot PinHeat Treat5
(e)--Inner Pivot PinShot Peen6
(f)-F-15.34Chromium PlateApply7
(g)--Inner Pivot PinGrind8
(h)-BMS3-8Solid Film Lubri-
cant
Apply9
(i)1 Oz.BMS10-79, Type
III
PrimerApply10
BMS10-11, Type
I (optional)
(j)--MarkingApply11
(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 inspec-
tion, 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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Copyright © Unpublished Work - See page 1 for details.
Original Issue: July 27, 2011
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BOEING SERVICE BULLETIN 777-55A0018
ALERTALERT

### Page 44 (OCR)

BOEING SERVICE BULLETIN 777-55A0018
ALERT  ALERT
This Figure applies only to: Group 1.
J000
0.02 X 43° CHAMFER  0.04  47°
DIA 1.125  DIA 0.90
0.88
R 0.07  0.05
* RO.060
BEFORE  AFTER
A-A
FIGURE 3: 182W6403-1 ANTI-ROTATION PLATE REWORK
(SHEET 1 OF 2)
Original Issue: July 27, 2011
Revision 1 March 06, 2012  BOEING PROPRIETARY -  777-55A0018
Copyright © Unpublished Work - See page 1 for details.  44 of 47

### Page 45

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.
MORE DATAQTYIDENTIFICA-
TION
NAMETASKSTEP
(a)--Anti-rotation
Plate
Clean1
(b)--Anti-rotation
Plate
Machine2
as shown.--Anti-rotation
Plate
Chamfer3
Do a magnetic
particle inspec-
tion of the part.
(c)
--Anti-rotation
Plate
Inspect4
(d)--FinishApply5
(e)--MarkingApply6
(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 ex-
isting 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 inspec-
tion, 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)
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: July 27, 2011
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45 of 47
BOEING SERVICE BULLETIN 777-55A0018
ALERTALERT

### Page 46 (OCR)

BOEING SERVICE BULLETIN 777-55A0018
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.
0.250-0.261 HOLE
(TO ATTACH "REMOVE BEFORE FLIGHT" TAG)
OPTIONAL HOLLOW PIN
0.75 MINIMUM WALL
0.6250 -
32 OR BETTER FINISH
0.3125→  0.3125
2.7455 - 2.747
12.00 +/- 0.500
0.02 X 0.25  0.02 X 0.25
LEAD IN  LEAD IN
CHAMFER  CHAMFER
0.250-0.261 HOLE
(2 LOCATIONS)
DRAWING NOT TO SCALE
ALL DIMENSIONS IN INCHES
ILLUSTRATION 1  2042876
APPENDIX A: HORIZONTAL STABILIZER TEMPORARY PIVOT PIN FABRICATION/INSTALLATION
(SHEET 1 OF 2)
Original Issue: July 27, 2011
Revision 1 March 06, 2012  BOEING PROPRIETARY -  777-55A0018
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### Page 47 (OCR)

BOEING SERVICE BULLETIN 777-55A0018
ALERT  ALERT
RETENTION BOLT  RETENTION BOLT
REMOVE  BEFORE  FLIGHT
RIGHT SIDE SHOWN
LEFT SIDE SIMILAR
ILLUSTRATION 2  2042941
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
APPENDIX A: HORIZONTAL STABILIZER TEMPORARY PIVOT PIN FABRICATION/INSTALLATION
(SHEET 2 OF 2)
Original Issue: July 27, 2011
Revision 1 March 06, 2012  BOEING PROPRIETARY -  777-55A0018
Copyright © Unpublished Work - See page 1 for details.  47 of 47

---
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