# Boeing Alert Service Bulletin 777-55A0014: Revision 1

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## Text

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### Page 1

Commercial 
Airplanes
777
Service Bulletin
Number: 777-55A0014
Original Issue: May 08, 2008
Revision 1: April 01, 2010
ATA System: 5500
SUBJECT: STABILIZERS - Elevator and Rudder Bond Jumper Bracket 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 © 2008 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Unpublished Work - All Rights Reserved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 ...................................................... 7
1. PLANNING INFORMATION ........................................ 1 1
A. Effectivity ............................................... 1 1
1. Airplanes ............................................ 1 1
2. Spares Affected ........................................ 1 3
B. Concurrent Requirements ...................................... 1 3
C. Reason ................................................ 1 4
D. Description .............................................. 1 5
E. Compliance .............................................. 1 6
F. Approval ............................................... 1 6
G. Manpower .............................................. 1 6
H. Weight and Balance Changes .................................... 1 7
I. Electrical Load Data ......................................... 1 7
J. References .............................................. 1 7
1. Existing Data: ......................................... 1 7
2. Data supplied with this Service Bulletin: ........................... 1 8
3. Installation Drawings Used in the Preparation of this Service Bulletin: ........... 1 8
K. Publications Affected ........................................ 1 8
L. Interchangeability and Intermixability of Parts ........................... 1 8
2. MATERIAL INFORMATION ........................................ 1 9
A. Material - Price and Availability ................................... 1 9
B. Industry Support Information .................................... 1 9
C. Parts Necessary For Each Airplane ................................. 1 9
1. Kits/Parts: ........................................... 1 9
2. Parts and Materials Supplied by the Operator: ........................ 2 1
3. Parts Modified and Reidentified: ............................... 2 1
4. Parts Removed and Not Replaced: .............................. 2 1
D. Parts Necessary to Change Spares ................................. 2 1
E. Special Tooling - Price and Availability ............................... 2 1
F. Special Tooling Necessary to do this Service Bulletin ....................... 2 1
3. ACCOMPLISHMENT INSTRUCTIONS .................................. 2 3
A. GENERAL INFORMATION ..................................... 2 3
B. WORK INSTRUCTIONS ....................................... 2 4
FIGURE 1: LEFT ELEVATOR - BOND JUMPER BRACKET REPLACEMENT [Group 1] ........ 2 6
FIGURE 2: LEFT ELEVATOR - BOND JUMPER BRACKET REPLACEMENT [Group 2] ........ 3 6
FIGURE 3: RIGHT ELEVATOR - BOND JUMPER BRACKET REPLACEMENT [Group 1] ....... 4 6
FIGURE 4: RIGHT ELEVATOR - BOND JUMPER BRACKET REPLACEMENT [Group 2] ....... 5 6
FIGURE 5: RUDDER - BOND JUMPER BRACKET REPLACEMENT [Group 1] ............ 6 6
FIGURE 6: RUDDER - BOND JUMPER BRACKET REPLACEMENT [Group 2] ............ 7 7
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Commercial 
Airplanes
777
Service Bulletin
Revision Transmittal SheetNumber: 777-55A0014Original Issue: May 08, 2008
Revision 1: April 01, 2010
ATA System: 5500
SUBJECT: STABILIZERS - Elevator and Rudder Bond Jumper Bracket Replacement
This revision includes all pages of the service bulletin.
COMPLIANCE INFORMATION RELATED TO THIS REVISION
No more work is necessary on airplanes changed as shown in the original issue of this service bulletin.
REASON FOR REVISION
This revision is sent to incorporate improvements noted during the validation of this service bulletin.
These sections were changed:
1. Summary and Paragraph 1.E, Compliance: Clarified the recommended compliance time.
2. Summary and Paragraph 2.B, Industry Support Information: Revised the warranty statement.
3. Summary and Paragraph 1.G, Manpower: Increased the number of persons and the task-hour estimate for
each figure.
4. Paragraph 1.J, References: Added the manuals referenced in the new figure steps.
5. Paragraph 1.K, Publications Affected: Added 777 Maintenance Manual 27-31 and Damage Tolerance Based
Structural Inspection statement.
6. Paragraph 2.A, Material - Price and Availability: Updated kit availability, ROLT, and price.
7. Paragraph 2.C.1, Kits/Parts: Added optional part numbers for jumper brackets.
8. Paragraph 2.C.2, Parts and Materials Supplied by the Operator:
a. Specified that the BMS 5-95 sealant should be Class B.
b. Added materials used to restore the airplane's finish.
9. Paragraph 3.B, Work Instructions, Work Packages 1 and 2: Added the upper trailing edge panel to the list
of items removed for access.
10. All Figures:
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a. Changed illustrations to better show the task steps.
b. Replaced bracket dimension references with a picture of a typical bracket installation.
c. Combined steps 1 through 5 into new steps 1 and 5.
d. Added steps to remove tee assemblies and trailing edge beams to improve access.
e. Changed the order of the steps to install the jumpers on the bracket before installing the bracket on
the elevator or rudder, for ease of installation.
f. Added optional part numbers for jumper brackets.
g. Step 5: Added note “if installed" next to “Remove Shim".
h. Step 6: Added sub-step “Drill Shim".
i. Added steps to the end of the procedure to cap seal the bracket bolt heads and restore the airplane's
finish.
j. Note (d): Clarified the requirement for and location of the shim.
k. Note (h): Clarified the assembly order of the jumpers and fasteners.
l. Note (j): Clarified where the resistance measurement is to be made.
m. Notes (h), (i), and (j): Updated SWPM references.
As a part of a service bulletin validation program, this change was completed on airplane WB186 by Service
Bulletin 777-55A0014 Original Issue before the release of Revision 1 of this service bulletin. The change
completed on airplane WB186 by Service Bulletin 777-55A0014 Original Issue is equivalent to the release of
Revision 1 of this service bulletin. Airplane WB186 has the configuration of a Group 1 airplane.
The intent of Information Notice 777-55A0014 IN 01 is incorporated in this revision.
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
May 08, 2008Original Issue:
April 01, 2010Revision 1:
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777-55A0014Revision 1: April 01, 2010
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Commercial 
Airplanes
777
Service Bulletin
SummaryNumber: 777-55A0014Original Issue: May 08, 2008
Revision 1: April 01, 2010
ATA System: 5500
SUBJECT: STABILIZERS - Elevator and Rudder Bond Jumper Bracket Replacement
CONCURRENT REQUIREMENTS
Refer to Paragraph 1.B., Concurrent Requirements
BACKGROUND
This service bulletin gives instructions to replace single-tabbed bond jumper brackets on the elevators and
rudder with two-tabbed brackets. These brackets are part of the lightning protection ground path for the horizontal
and vertical stabilizers. At this time, two bond jumpers are attached to the single tab, which creates a single
high-resistance ground path. If this ground path is lost because the tab is broken or damaged, a lightning strike
could cause excessive current in the adjacent structure, hinges, and hydraulic tubes, which could cause them
to fail. More importantly, a lightning strike could cause excessively high voltage transients in the Actuator Control
Electronics (ACE) wire bundles, which could cause damage to the ACE units or unwanted effects such as
uncommanded motion of the flight control surfaces. No ACE failures have been reported as a result of a lightning
strike. However, if these brackets are not replaced, loss of the lightning protection ground path could result in
possible loss of airplane control in the event of a lightning strike.
An operator reported two failures of the single-tabbed bracket on the rudder. In the most recent case, the bracket
was discolored and melted, the tab was completely severed and burned, and the bond jumpers were detached
from the bracket. The operator also reported a similar failure of the ground clip that connects the other end of
the jumpers to the vertical stabilizer. Boeing determined that the root cause of these failures was a combination
of electromagnetic forces on the jumpers and resistive heating of the bracket and ground clip during lightning
strikes. Fatigue loading after initial damage from the lightning strikes could also have contributed to the failures.
When tested in the lightning lab, multiple large-magnitude lightning strikes were necessary to cause the
single-tabbed bracket to fail, but the two-tabbed bracket survived many more large-magnitude lightning strikes
with almost no damage. The two-tabbed bracket will provide a second ground path and reduce the current flow
and mass at each tab. This will lower the overall resistance of the lightning protection ground path and reduce
the possibility of total loss of the ground path due to failure of a single tab.
Boeing Service Related Problem (SRP) 777-SRP-55-0037 is related to this service bulletin.
ACTION
Get access to the single-tabbed brackets on the elevators and rudder. Remove the bond jumpers, replace the
single-tabbed brackets with two-tabbed brackets, and install new bond jumpers. Do resistance tests of the new
brackets and bond jumpers.
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EFFECTIVITY
777-200/-300 Airplanes. Refer to Paragraph 1.A.1., Airplanes for the list of affected airplanes.
COMPLIANCE
The Federal Aviation Administration (FAA) will possibly release an Airworthiness Directive related to this service
bulletin. The Airworthiness Directive will make the compliance tasks and times given in this service bulletin
mandatory.
Boeing recommends that the change given in this service bulletin be done within 4 years after the original issue
date of this service bulletin.
INDUSTRY SUPPORT INFORMATION
Boeing warranty remedies are available for airplanes in warranty as of March 22, 1999. Please refer to Paragraph
2.B., Industry Support Information.
MANPOWER
Elapsed HoursTotal Task HoursAirplanes
10.521.0All
MATERIAL INFORMATION
Boeing Supplied Kits/Parts.
Refer to Paragraph 2.A., Material - Price and Availability.
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BOEING SERVICE BULLETIN 777-55A0014
REMOVE BOND JUMPERS, REPLACE SINGLE-TABBED BRACKETS
WITH TWO-TABBED BRACKETS, AND INSTALL NEW BOND JUMPERS.  1457014
DO RESISTANCE TESTS OF THE NEW BRACKETS AND BOND JUMPERS.
Original Issue: May 08, 2008
Revision 1: April 01, 2010  777-55A0014
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777-55A0014Revision 1: April 01, 2010
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Commercial 
Airplanes
777
Service Bulletin
Number: 777-55A0014
Original Issue: May 08, 2008
Revision 1: April 01, 2010
ATA System: 5500
SUBJECT: STABILIZERS - Elevator and Rudder Bond Jumper Bracket Replacement
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 airplanes shown below.
DESCRIPTIONCONFIGURATIONGROUP
777-200/-300 airplanes, line numbers 2-155-1
777-200/-300 airplanes, line numbers 1, 156-309-2
Airplane Models:
777-200, 777-300
GroupVariable Number
2WA001
1WA002 - WA017
1WA076 - WA080
1WA086 - WA093
1WA101 - WA104
1WA116 - WA119
1WA131 - WA137
1WA171 - WA175
1WA196 - WA198
1WA206 - WA210
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GroupVariable Number
2WA211 - WA212
1WA221 - WA223
1WA231 - WA232
2WA241 - WA247
2WA261 - WA266
1WB001 - WB013
2WB014 - WB021
2WB031 - WB039
1WB051 - WB068
2WB069 - WB076
1WB101 - WB104
2WB105 - WB106
1WB121 - WB125
1WB131 - WB133
2WB134 - WB135
1WB151 - WB153
1WB161 - WB169
2WB170 - WB171
1WB181 - WB186
2WB187 - WB188
1WB231 - WB234
2WB235
1WB271
2WB272
1WB276 - WB286
2WB291 - WB300
1WB306 - WB307
1WB311 - WB313
2WB314 - WB323
1WB336
2WB337
2WB366 - WB367
2WB371 - WB386
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GroupVariable Number
2WB406
2WB411 - WB413
2WB416 - WB433
2WB446 - WB452
2WB476
2WB481 - WB484
1WB501 - WB504
2WB505 - WB507
1WB531 - WB533
2WB534 - WB535
1WB551
2WB552 - WB554
1WB591
2WB592 - WB595
2WB601 - WB605
2WB611 - WB615
2WB631 - WB632
2WB636
2WC051 - WC056
2. Spares Affected
None.
B. Concurrent Requirements
Group 1:
The service bulletin listed below must be done before or at the same time as this service bulletin:
Group 1:
DescriptionService BulletinCompany
Installs additional bond jumpers in the eleva-
tors and rudder. The ground clips installed
in SB 777-55A0010 are required for installa-
tion of the bond jumpers in this service bul-
letin.
777-55A0010, original issue or Revision 1Boeing
Group 2:
None.
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C. Reason
This service bulletin gives instructions to replace single-tabbed bond jumper brackets on the elevators
and rudder with two-tabbed brackets. These brackets are part of the lightning protection ground path
for the horizontal and vertical stabilizers. At this time, two bond jumpers are attached to the single tab,
which creates a single high-resistance ground path. If this ground path is lost because the tab is broken
or damaged, a lightning strike could cause excessive current in the adjacent structure, hinges, and
hydraulic tubes, which could cause them to fail. More importantly, a lightning strike could cause
excessively high voltage transients in the Actuator Control Electronics (ACE) wire bundles, which could
cause damage to the ACE units or unwanted effects such as uncommanded motion of the flight control
surfaces. No ACE failures have been reported as a result of a lightning strike. However, if these brackets
are not replaced, loss of the lightning protection ground path could result in possible loss of airplane
control in the event of a lightning strike.
An operator reported two failures of the single-tabbed bracket on the rudder. In the most recent case,
the bracket was discolored and melted, the tab was completely severed and burned, and the bond
jumpers were detached from the bracket. The operator also reported a similar failure of the ground clip
that connects the other end of the jumpers to the vertical stabilizer. Boeing determined that the root
cause of these failures was a combination of electromagnetic forces on the jumpers and resistive
heating of the bracket and ground clip during lightning strikes. Fatigue loading after initial damage from
the lightning strikes could also have contributed to the failures.
When tested in the lightning lab, multiple large-magnitude lightning strikes were necessary to cause
the single-tabbed bracket to fail, but the two-tabbed bracket survived many more large-magnitude
lightning strikes with almost no damage. The two-tabbed bracket will provide a second ground path
and reduce the current flow and mass at each tab. This will lower the overall resistance of the lightning
protection ground path and reduce the possibility of total loss of the ground path due to failure of a
single tab.
Boeing Service Related Problem (SRP) 777-SRP-55-0037 is related to this service bulletin.
Revision 1 is sent to incorporate improvements noted during the validation of this service bulletin. These
sections were changed:
1. Summary and Paragraph 1.E, Compliance: Clarified the recommended compliance time.
2. Summary and Paragraph 2.B, Industry Support Information: Revised the warranty statement.
3. Summary and Paragraph 1.G, Manpower: Increased the number of persons and the task-hour
estimate for each figure.
4. Paragraph 1.J, References: Added the manuals referenced in the new figure steps.
5. Paragraph 1.K, Publications Affected: Added 777 Maintenance Manual 27-31 and Damage
Tolerance Based Structural Inspection statement.
6. Paragraph 2.A, Material - Price and Availability: Updated kit availability, ROLT, and price.
7. Paragraph 2.C.1, Kits/Parts: Added optional part numbers for jumper brackets.
8. Paragraph 2.C.2, Parts and Materials Supplied by the Operator:
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a. Specified that the BMS 5-95 sealant should be Class B.
b. Added materials used to restore the airplane's finish.
9. Paragraph 3.B, Work Instructions, Work Packages 1 and 2: Added the upper trailing edge panel
to the list of items removed for access.
10. All Figures:
a. Changed illustrations to better show the task steps.
b. Replaced bracket dimension references with a picture of a typical bracket installation.
c. Combined steps 1 through 5 into new steps 1 and 5.
d. Added steps to remove tee assemblies and trailing edge beams to improve access.
e. Changed the order of the steps to install the jumpers on the bracket before installing the
bracket on the elevator or rudder, for ease of installation.
f. Added optional part numbers for jumper brackets.
g. Step 5: Added note “if installed" next to “Remove Shim".
h. Step 6: Added sub-step “Drill Shim".
i. Added steps to the end of the procedure to cap seal the bracket bolt heads and restore the
airplane's finish.
j. Note (d): Clarified the requirement for and location of the shim.
k. Note (h): Clarified the assembly order of the jumpers and fasteners.
l. Note (j): Clarified where the resistance measurement is to be made.
m. Notes (h), (i), and (j): Updated SWPM references.
As a part of a service bulletin validation program, this change was completed on airplane WB186 by
Service Bulletin 777-55A0014 Original Issue before the release of Revision 1 of this service bulletin.
The change completed on airplane WB186 by Service Bulletin 777-55A0014 Original Issue is equivalent
to the release of Revision 1 of this service bulletin. Airplane WB186 has the configuration of a Group
1 airplane.
The intent of Information Notice 777-55A0014 IN 01 is incorporated in this revision.
D. Description
Get access to the single-tabbed brackets on the elevators and rudder. Remove the bond jumpers,
replace the single-tabbed brackets with two-tabbed brackets, and install new bond jumpers. Do resistance
tests of the new brackets and bond jumpers.
Revision 1 - No more work is necessary on airplanes changed in accordance with the original issue of
this service bulletin.
BOEING PROPRIETARY -
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Original Issue: May 08, 2008
777-55A0014Revision 1: April 01, 2010
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The work in this service bulletin is done in the maintenance zone(s) given below.
Affected Maintenance Zones
ZoneModel
324, 335, 345777-200, 777-300
E. Compliance
The Federal Aviation Administration (FAA) will possibly release an Airworthiness Directive related to
this service bulletin. The Airworthiness Directive will make the compliance tasks and times given in this
service bulletin mandatory.
Boeing recommends that the change given in this service bulletin be done within 4 years after the
original issue date of this service bulletin.
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 this change for each airplane.
This estimate is for direct labor only, done by an experienced crew. Adjust the estimate with operator
task hour data if necessary. The estimate does not include lost time. These are some examples of lost
time:
— Time to adjust to the workplace
— Time to schedule the work
— Time to inspect the work
— Time to cure the materials
— Time to make the parts
— Time to find the tools.
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Work Package 1 - Left Elevator
Elapsed HoursTask HoursNumber of Per-
sons
Task
0.250.502Open Access
3.006.002Figure 1 or 2
0.250.502Close Access
3.507.00TOTAL FOR EACH AIRPLANE
Work Package 2 - Right Elevator
Elapsed HoursTask HoursNumber of Per-
sons
Task
0.250.502Open Access
3.006.002Figure 3 or 4
0.250.502Close Access
3.507.00TOTAL FOR EACH AIRPLANE
Work Package 3 - Rudder
Elapsed HoursTask HoursNumber of Per-
sons
Task
0.250.502Open Access
3.006.002Figure 5 or 6
0.250.502Close Access
3.507.00TOTAL FOR EACH AIRPLANE
H. Weight and Balance Changes
None.
I. Electrical Load Data
Not applicable.
J. References
1. Existing Data:
a. Boeing Service Bulletin 777-55A0010
b. Boeing Service Related Problem (SRP) 777-SRP-55-0037
c. Standard Overhaul Practices Manual (SOPM) 20-41-02
d. Standard Wiring Practices Manual (SWPM) 20-10-11, 20-10-12, 20-20-00, 20-20-10
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e. 777 Aircraft Maintenance Manual (AMM) 06-42-00, 29-11-00, 51-21-10, 51-31-01
f. 777-200 Structural Repair Manual (SRM) 51-20-01, 51-20-11, 51-30-01, 51-40-02
g. 777-300 Structural Repair Manual (SRM) 51-20-01, 51-20-11, 51-30-01, 51-40-02
2. Data supplied with this Service Bulletin:
None.
3. Installation Drawings Used in the Preparation of this Service Bulletin:
TitleDrawing Number
Rudder Installation173W0012
Rudder Assembly173W0061
Front Spar Installation - Rudder173W2200
Lightning Protection Details - Rudder173W3200
Elevator Installation183W0001
Elevator Assembly183W0061
Spar Installation - Elevator183W1001
Bond Jumper Bracket - Elevator183W8101
These drawings were used to prepare this service bulletin. These drawings are not necessary to
make the specified changes, and are not supplied with this service bulletin. These drawings may
not be applicable to all airplane configurations or operators.
K. Publications Affected
1. Publications:
Chapter-SectionPublication
55-11, 55-31777 Illustrated Parts Catalog
55-20, 55-40Component Maintenance Manual
27-31777 Maintenance Manual
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 does not affect FCS, therefore DTIs are not necessary.
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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2.    MATERIAL INFORMATION
A. Material - Price and Availability
Boeing can supply the kits shown in Paragraph 2.C., Parts Necessary for Each Airplane as shown
below. If there is a limit to the quantity (QTY) of available kits, a supply sequence is given by Spares.
More kits become available as shown in the Reorder Lead Time (ROLT). ROLT is calculated from the
date Boeing gets the purchase order.
Unit Price thru
December 31,
2009
ROLT
(Weeks)
QTYDateNameKit Number
$1235.006910Aug 26/09Top Kit - Elevator and
Rudder Bond Jumper
Replacement
005W3336-1
10Sep 24/09
10Oct 22/09
10Nov 19/09
5Dec 22/09
The kits are subject to the terms and conditions of the Boeing standard purchase order acknowledgment.
After the Unit Price date, new price and ROLT data is applicable. Prices are in United States dollars.
Terms: Net 30 days.
REFERENCE THIS SERVICE BULLETIN AND SUBMIT YOUR PURCHASE ORDER BY ONE OF
THE METHODS THAT FOLLOW:
1. Order on-line via ATA Spec 2000 or Boeing Part Page
2. Fax to (206) 662-7145
3. Mail to:
Spares Customer Support - MC 36-65
Boeing Spares Department
P.O. Box 3707
Seattle, Washington 98124-2207 USA
B. Industry Support Information
Boeing warranty remedies are available for 777 airplanes in warranty as of March 22, 1999. For task
hour reimbursement for airplanes in warranty as of that date, send a warranty claim to Boeing
Commercial Airplanes Group - Warranties. The kits for airplanes in warranty as of that date will be
supplied at no charge. Send a purchase order for the kits to Boeing Spares. Please refer to this service
bulletin number and reference the airplane variable numbers in your purchase order.
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.
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### Page 20

Kit 005W3336
NotesNameQTYNew Part Number
-4-3-2-1
TOP KIT - ELEVATOR AND RUDDER BOND
JUMPER BRACKET REPLACEMENT
...-005W3336-1
SUBKIT - LEFT ELEVATOR BOND JUMPER
BRACKET REPLACEMENT
..-1005W3336-2
SUBKIT - RIGHT ELEVATOR BOND JUMPER
BRACKET REPLACEMENT
.-.1005W3336-3
SUBKIT - RUDDER BOND JUMPER BRACKET
REPLACEMENT
-..1005W3336-4
JUMPER BRACKET1...173W3200-14
(173W3200U14,
173W3200Y14 option-
al)
BRACKET..1.183W8101-3
(183W8101Y3 optional)
BRACKET.1..183W8101-4
(183W8101Y4 optional)
BOLT, HEX HEAD222.BACB30LJ4-4
BOLT, HEX HEAD222.BACB30LJ4U5
BOLT, HEX DRIVE.88.BACB30VG6-5
(183W8101-5,
183W8101-6 optional)
BOLT, HEX DRIVE8...BACB30VG10-9
JUMPER.22.BACJ40E20-26
JUMPER ASSY2...BACJ40E20-33
NUT222.BACN10JC4CM
NUT222.BACN10YR4CD
NUT, SELF-LOCK, HEX.88.BACN10YT3CSA
NUT8...BACN10YT5CSA
WASHER666.BACW10BP4APU
SHIM, LAMINATED111.BACS40V007C054
WASHER, FLAT444.NAS1149D0416H
WASHER, PLAIN222.NAS1149D0463H
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### Page 21

2. Parts and Materials Supplied by the Operator:
NotesNameQTYPart Number / Specification
Optional (a)SHIM STOCK, LAMINATED-BAC1535-60
(b) (c)SEALANT1 QtBMS5-95, CLASS B
(c)PRIMER1 PtBMS10-11, TYPE 1
(c)CORROSION INHIBITING COMPOUND1 PtBMS3-23
(a) This material can be used to make shims as an alternative to the shims supplied in the parts kit. Three
shims are necessary, 5.4" by 0.7" each.
(b) Make sure to use Class B sealant. Other classes of BMS5-95 do not have the correct consistency for
this application.
(c) See the Qualified Products List at the end of the Boeing Material Specification (BMS) for supplier data.
3. Parts Modified and Reidentified:
None.
4. Parts Removed and Not Replaced:
None.
D. Parts Necessary to Change Spares
None.
E. Special Tooling - Price and Availability
None.
F. Special Tooling Necessary to do this Service Bulletin
No special tools or equipment are necessary to do the change in this service bulletin. But, maintenance
and overhaul tools in the manuals given in Paragraph 1.J., References, can be necessary. Examine
operator tool supply to make sure all necessary tools are available.
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### Page 22

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BOEING SERVICE BULLETIN 777-55A0014
BLANK PAGE

### Page 23

3.    ACCOMPLISHMENT INSTRUCTIONS
A. GENERAL INFORMATION
WARNING: YOU MUST PREVENT ALL POSSIBLE OPERATION OF THE HORIZONTAL STABILIZER
AND RUDDER WHEN YOU WORK ON OR NEAR THEM. THE HORIZONTAL
STABILIZER AND RUDDER MOVE QUICKLY AND WITH FORCE. IF THE STABILIZER
OR RUDDER MOVES WHEN PERSONS ARE NEAR IT, YOU CAN CAUSE INJURY
TO THEM.
WARNING: MAKE SURE THAT PERSONNEL AND EQUIPMENT ARE CLEAR OF THE ELEVATOR
AND RUDDER SURFACES BEFORE YOU REMOVE HYDRAULIC PRESSURE TO
THE POWER CONTROL UNITS. WHEN YOU REMOVE HYDRAULIC PRESSURE, THE
SURFACE WILL LOWER SLOWLY. ACCIDENTAL MOVEMENT OF ELEVATOR AND
RUDDER SURFACES CAN CAUSE INJURIES TO PERSONS AND DAMAGE TO
EQUIPMENT.
WARNING: ATTACH A SAFETY HARNESS WHEN YOU DO WORK ON TOP OF THE HORIZONTAL
STABILIZER OR VERTICAL FIN. FAILURE TO DO THIS CAN CAUSE INJURY OR
DAMAGE.
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. The work instructions are divided into work packages. Task Hours and Elapsed Hours
for each package are given in Paragraph 1.G., Manpower. You can do each work
package independently.
4. 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 are given in 777 SRM, Chapter 51
– Torque limits to tighten nuts and bolts are given in 777 SRM, Chapter 51
5. For approved fastener and process material substitutions, refer to 777 SRM, Chapter
51. Alternate fasteners are given in 777 SRM Chapter 51 and Boeing Drawing
012W6100.
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### Page 24

6. Refer to the SWPM 20-10-11 and SWPM 20-10-12 for the wire installation procedures.
7. If the length of any fastener specified in this service bulletin does not meet the
installation standards given in SRM Chapter 51, then a fastener of the same
specification, or an approved substitute, with a length which meets the installation
standards given in SRM Chapter 51 may be used.
8. 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 "as
given in" are included in the instruction, the procedure in the Boeing document must
be used.
B. WORK INSTRUCTIONS
WORK PACKAGE 1 - LEFT ELEVATOR
1. Remove hydraulic power to the left elevator. Refer to 777 AMM 29-11-00 as an accepted procedure.
2. Move the FLT CONTROL HYD VALVE POWER - TAIL L, C, and R switches on the P61 Pilot's
Overhead Panel to the SHUT OFF position and attach a DO-NOT-OPERATE tag. Make sure that
the amber VALVE CLOSED lights come on.
3. Remove access panel 335LB, trailing edge seal 335FBX, and upper trailing edge panel 335JT.
Refer to 777 AMM 06-42-00 for locations.
4. Group 1:
Replace the bond jumper bracket as given in FIGURE 1.
Group 2:
Replace the bond jumper bracket as given in FIGURE 2.
5. Install access panel 335LB, trailing edge seal 335FBX, and upper trailing edge panel 335JT.
6. Remove the DO-NOT-OPERATE tag from the FLT CONTROL HYD VALVE POWER - TAIL L, C,
and R switches and move them to the NORM position.
7. Put the airplane back to a serviceable condition.
WORK PACKAGE 2 - RIGHT ELEVATOR
1. Remove hydraulic power to the right elevator. Refer to 777 AMM 29-11-00 as an accepted
procedure.
2. Move the FLT CONTROL HYD VALVE POWER - TAIL L, C, and R switches on the P61 Pilot's
Overhead Panel to the SHUT OFF position and attach a DO-NOT-OPERATE tag. Make sure that
the amber VALVE CLOSED lights come on.
3. Remove access panel 345LB, trailing edge seal 345FBX, and upper trailing edge panel 345JT.
Refer to 777 AMM 06-42-00 for locations.
4. Group 1:
Replace the bond jumper bracket as given in FIGURE 3.
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### Page 25

Group 2:
Replace the bond jumper bracket as given in FIGURE 4.
5. Install access panel 345LB, trailing edge seal 345FBX, and upper trailing edge panel 345JT.
6. Remove the DO-NOT-OPERATE tag from the FLT CONTROL HYD VALVE POWER - TAIL L, C,
and R switches and move them to the NORM position.
7. Put the airplane back to a serviceable condition.
WORK PACKAGE 3 - RUDDER
1. Remove hydraulic power to the rudder. Refer to 777 AMM 29-11-00 as an accepted procedure.
2. Move the FLT CONTROL HYD VALVE POWER - TAIL L, C, and R switches on the P61 Pilot's
Overhead Panel to the SHUT OFF position and attach a DO-NOT-OPERATE tag. Make sure that
the amber VALVE CLOSED lights come on..
3. Remove access panels 324KAL and 324KAR and trailing edge seals 324WL and 324WR. Refer
to 777 AMM 06-42-00 for locations.
4. Group 1:
Replace the bond jumper bracket as given in FIGURE 5.
Group 2:
Replace the bond jumper bracket as given in FIGURE 6.
5. Install access panels 324KAL and 324KAR and trailing edge seals 324WL and 324WR.
6. Remove the DO-NOT-OPERATE tag from the FLT CONTROL HYD VALVE POWER - TAIL L, C,
and R switches and move them to the NORM position.
7. Put the airplane back to a serviceable condition.
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### Page 26 (OCR)

BOEING SERVICE BULLETIN 777-55A0014
This Figure applies only to: Group 1.
SEE A
TIP FAIRING
SEE DOG  →FWD
1457026
FIGURE 1: LEFT ELEVATOR - BOND JUMPER BRACKET REPLACEMENT
(SHEET 1 OF 10)
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### Page 27 (OCR)

BOEING SERVICE BULLETIN 777-55A0014
- 190
5
8 LOCATIONS  (4)
3
4 LOCATIONS
2) 4 LOCATIONS
ELEVATOR
FRONT
SPAR
FWD
(VIEW LOOKING UP)
1457104
FIGURE 1: LEFT ELEVATOR - BOND JUMPER BRACKET REPLACEMENT
(SHEET 2 OF 10)
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### Page 28 (OCR)

BOEING SERVICE BULLETIN 777-55A0014
UPPER  ELEVATOR
SKIN PANEL  M2 4 LOCATIONS
LIGHTNING DIVERTER
STRIP
CLEANED
SURFACE U
(4 LOCATIONS)
SHIM  (IF NECESSARY)  64 LOCATIONS
CLEANED
SURFACE  M1213 8 LOCATIONS
(UNDERSIDE)
(4 LOCATIONS)  1B0D SEE Đ0
2 LOCATIONS
SEE  12
(6) 4 LOCATIONS
LOWER
ELEVATOR
SKIN PANEL
CLEANED  SURFACE  11)
(UNDERSIDE)  (4 LOCATIONS)  FWD  4 LOCATIONS (1112  CLEANED  SURFACE  (4 LOCATIONS)  STRIP  DIVERTER  LIGHTNING  1758235
FIGURE 1: LEFT ELEVATOR - BOND JUMPER BRACKET REPLACEMENT
(SHEET 3 OF 10)
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### Page 29 (OCR)

BOEING SERVICE BULLETIN 777-55A0014
BRACKET  LOCATION OF
EXISTING HOLES IN
THE STRUCTURE
2D
SAME
DIMENSION
TYPICAL BRACKET INSTALLATION
8 17 WASHER A
2 LOCATIONS
DO 82 LOCAMPONS>
WASHER B
161 (2 LOCATIONS)
1[2 LOCATIONS)
17 (2 LOCATIONS)  WASHER C  X18)
1457434
FIGURE 1: LEFT ELEVATOR - BOND JUMPER BRACKET REPLACEMENT
(SHEET 4 OF 10)
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### Page 30 (OCR)

BOEING SERVICE BULLETIN 777-55A0014
SEE €€  16 1) 18 19
LOCATIONS
1333
15
ELEVATOR  8 LOCATIONS (13
FRONT
SPAR
4 LOCATIONS
20 4 LOCATIONS
2 LOCATIONS
218 LOCATIONS
FWD  SEE H
22) 2 LOCATIONS
0.050  (VIEW LOOKING UP)
TYPICAL
-0.10
TYPICAL
SHIM
(IF NECESSARY)
BRACKET
1457236
FIGURE 1: LEFT ELEVATOR - BOND JUMPER BRACKET REPLACEMENT
(SHEET 5 OF 10)
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Revision 1 April 01, 2010  777-55A0014
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### Page 31

The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY
numbers shown below are the number of parts necessary for this figure.
MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
Remove sealant as
necessary.
2-FASTENERSRemove1
2-JUMPERSDisconnect
to get access to the
bracket.
4-FASTENERSRemove / Keep2
1189W4000-27
(189W4000-37 or
189W4000-5 optional)
SUPPORT TEERemove / Keep
if necessary for ac-
cess.
4-FASTENERSRemove / Keep3
Do not disconnect
the third jumper.
Support the tee
against structure to
prevent damage.
1189W4000-29
(189W4000-11 option-
al)
TEE ASSYRemove / Keep
8BACC30AB6SCOLLARRemove4
8BACB30VG6K5BOLTRemove
Remove sealant
around bracket, if
necessary.
1183W8101-1BRACKETRemove5
if installed.1BACS40V007C054SHIM, LAMINATEDRemove
Discard jumpers and
fasteners with
bracket.
2-JUMPERSRemove
Drill 8 holes in
bracket, 3/16 inch
diameter. (a)
-183W8101-3
(183W8101Y3 optional)
BRACKETDrill6
(d)1BACS40V007C054
(BAC1535-60 optional)
SHIM, LAMINATEDDrill
Clean tabs with sol-
vent. (b)
1183W8101-3
(183W8101Y3 optional)
BRACKETClean7
Clean terminals with
solvent. (b)
2BACJ40E20-26JUMPERClean
Washer B. Use sol-
vent. (b)
2BACW10BP4APUWASHERClean
FIGURE 1: LEFT ELEVATOR - BOND JUMPER BRACKET REPLACEMENT
(SHEET 6 OF 10)
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### Page 32

MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
(h)2BACJ40E20-26JUMPERInstall (New)8
(h)2BACB30LJ4U5BOLT, HEX HEADInstall (New)
(h)6BACW10BP4APUWASHERInstall (New)
(h)2BACN10JC4CMNUTInstall (New)
Torque nuts to be-
tween 90 and 105
inch-pounds. (i)
2BACN10JC4CMNUTTorque9
1.0 milliohm maxi-
mum. (j)
--RESISTANCEMeasure10
Clean the inner sur-
faces of the flanges
with solvent. (b)
1183W8101-3
(183W8101Y3 optional)
BRACKETClean11
Use solvent. (b)8BACB30VG6-5
(183W8101-5 or
183W8101-6 optional)
BOLT, HEX DRIVEClean
Use solvent. (b)8BACN10YT3CSANUT, SELF-LOCK,
HEX
Clean
Clean the areas that
the bolt heads will
touch. Use abrasive,
then solvent. (b) (c)
2-LIGHTNING DIVERT-
ER STRIPS
Clean
1183W8101-3
(183W8101Y3 optional)
BRACKETInstall (New)12
(d)1BACS40V007C054
(BAC1535-60 optional)
SHIM, LAMINATEDInstall (New)
Install wet with
BMS5-95, CLASS B
sealant. (e)
8BACB30VG6-5
(183W8101-5 or
183W8101-6 optional)
BOLT, HEX DRIVEInstall (New)
8BACN10YT3CSANUT, SELF-LOCK,
HEX
Install (New)
Torque nuts to be-
tween 32 and 38
inch-pounds. (f)
8BACN10YT3CSANUT, SELF-LOCK,
HEX
Torque13
5.0 milliohms maxi-
mum. (g)
--RESISTANCEMeasure14
if removed for ac-
cess.
1189W4000-29
(189W4000-11 option-
al)
TEE ASSYInstall (Kept)15
4-FASTENERSInstall (Kept)
FIGURE 1: LEFT ELEVATOR - BOND JUMPER BRACKET REPLACEMENT
(SHEET 7 OF 10)
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### Page 33

MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
Clean tabs with
abrasive, then sol-
vent. (b) (c)
1189W4000U31GROUND CLIPClean16
Clean terminals with
solvent. (b)
2BACJ40E20-26JUMPERClean
Washer B. Use sol-
vent. (b)
2NAS1149D0416HWASHER, FLATClean
(h)2BACJ40E20-26JUMPERConnect17
(h)2BACB30LJ4-4BOLT, HEX HEADInstall (New)
Washer A (h)2NAS1149D0463HWASHER, PLAINInstall (New)
Washers B and C
(h)
4NAS1149D0416HWASHER, FLATInstall (New)
(h)2BACN10YR4CDNUTInstall (New)
Torque nuts to be-
tween 78 and 82
inch-pounds. (i)
2BACN10YR4CDNUTTorque18
1.0 milliohm maxi-
mum. (j)
--RESISTANCEMeasure19
1189W4000-27
(189W4000-37 or
189W4000-5 optional)
SUPPORT TEEInstall (Kept)20
4-FASTENERSInstall (Kept)
Cap seal the bolt
heads. Refer to 777
AMM 51-31-01 as
an accepted proce-
dure.
-BMS5-95, CLASS BSEALANTApply21
FIGURE 1: LEFT ELEVATOR - BOND JUMPER BRACKET REPLACEMENT
(SHEET 8 OF 10)
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### Page 34

MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
to bare aluminum
surfaces as neces-
sary. Refer to 777-
200 SRM 51-20-01
or 777-300 SRM 51-
20-01 as an accept-
ed procedure.
--CHEMICAL CONVER-
SION COATING
Apply22
Apply 2 layers of
primer over the
chemical conversion
coating. Refer to
SOPM 20-41-02 as
an accepted proce-
dure.
-BMS10-11, TYPE 1PRIMERApply
as necessary. Refer
to 777 AMM 51-21-
10 as an accepted
procedure.
--DECORATIVE EXTERI-
OR PAINT
Apply
as necessary. Refer
to 777-200 SRM 51-
20-01 or 777-300
SRM 51-20-01 as an
accepted procedure.
-BMS3-23CORROSION INHIBIT-
ING COMPOUND
Apply
(a) Use of the existing holes in the structure is recommended to find the correct hole positions. Removal of
the bracket from the structure is recommended before drilling holes to full size. If necessary, holes can
be drilled up to 0.030 inch larger to align with the holes in the structure. Refer to 777-200 SRM 51-30-01
or 777-300 SRM 51-30-01, Titanium Alloys, as an accepted procedure.
(b) Refer to SWPM 20-20-00, Cleaning Procedure 5 as an accepted procedure.
(c) Refer to SWPM 20-20-00, Cleaning Procedure 1 or 2 as an accepted procedure.
(d) Use shim if necessary to fill the gap between the bracket and the structure. The shim can be installed
between the bracket and either skin panel. Remove laminations as necessary. Maximum shim thickness
is 0.060 inch, maximum gap is 0.016 inch. Refer to 777-200 SRM 51-20-11 or 777-300 SRM 51-20-11
as an accepted procedure.
(e) Refer to 777 AMM 51-31-01, Fastener Sealing for Corrosion Prevention Procedure 3, as an accepted
procedure. It is not necessary to apply sealant around the bracket.
(f) After initial torque, wait 5 minutes minimum, but no longer than the squeeze-out life of the sealant. Then
torque the nuts again. Make sure that the sealant squeezes out from under the bolt head. Use the
squeezed-out sealant to make a smooth fillet around each bolt head. Refer to 777-200 SRM 51-40-02 or
777-300 SRM 51-40-02 as an accepted procedure.
(g) Measure the resistance between the bracket and both the upper and lower lightning diverter strips ("picture
frames"). Make sure that each resistance is 5.0 milliohms maximum. Refer to SWPM 20-20-00, Test
Procedures for Electrical Bonds, as an accepted procedure. If one or both resistances are more than the
FIGURE 1: LEFT ELEVATOR - BOND JUMPER BRACKET REPLACEMENT
(SHEET 9 OF 10)
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BOEING SERVICE BULLETIN 777-55A0014

### Page 35

MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
maximum, then for each applicable side, remove the four nuts and bolts and do steps 11 through 14
again.
(h) Refer to SWPM 20-20-10, Category 2 Fay Sealed Direct Ground Stud Installation, as an accepted proce-
dure, except assemble the jumpers and fasteners in the order shown in View E.
(i) Torque nuts and smooth out sealant. Refer to SWPM 20-20-10, Category 2 Fay Sealed Direct Ground
Stud Installation, as an accepted procedure.
(j) Measure the resistance between each jumper terminal and its tab. Make sure that each resistance is 1.0
milliohm maximum. Refer to SWPM 20-20-10, Maximum Permitted Resistance and Test Procedures for
Ground Studs, and Category 2 Fay Sealed Direct Ground Stud Installation, as accepted procedures.
FIGURE 1: LEFT ELEVATOR - BOND JUMPER BRACKET REPLACEMENT
(SHEET 10 OF 10)
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### Page 36 (OCR)

BOEING SERVICE BULLETIN 777-55A0014
This Figure applies only to: Group 2.
SEE A
TIP FAIRING
SEE BOO  AFWD
1458377
FIGURE 2: LEFT ELEVATOR - BOND JUMPER BRACKET REPLACEMENT
(SHEET 1 OF 10)
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### Page 37 (OCR)

BOEING SERVICE BULLETIN 777-55A0014
8 LOCATIONS
4 LOCATIONS
) 4 LOCATIONS
ELEVATOR
FRONT SPAR
FWD
(VIEW LOOKING UP)
1458406
FIGURE 2: LEFT ELEVATOR - BOND JUMPER BRACKET REPLACEMENT
(SHEET 2 OF 10)
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### Page 38 (OCR)

BOEING SERVICE BULLETIN 777-55A0014
UPPER  ELEVATOR
SKIN PANEL  M2 4 LOCATIONS
LIGHTNING DIVERTER
STRIP
CLEANED
SURFACE U
(4 LOCATIONS)
SHIM  (IF NECESSARY)  64 LOCATIONS
CLEANED
SURFACE  M1213 8 LOCATIONS
(UNDERSIDE)
(4 LOCATIONS)  180D SEE CO
2 LOCATIONS
SEE
12
(6) 4 LOCATIONS
LOWER
ELEVATOR
SKIN PANEL
CLEANED
SURFACE
(UNDERSIDE)  4 LOCATIONS (1112  CLEANED  LIGHTNING
(4 LOCATIONS)  FWD  SURFACE  (4 LOCATIONS)  STRIP  DIVERTER  1758533
FIGURE 2: LEFT ELEVATOR - BOND JUMPER BRACKET REPLACEMENT
(SHEET 3 OF 10)
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Revision 1 April 01, 2010  BOEING PROPRIETARY -  777-55A0014
Copyright © Unpublished Work - See page 1 for details.  38 of 87

### Page 39 (OCR)

BOEING SERVICE BULLETIN 777-55A0014
BRACKET  LOCATION OF
EXISTING HOLES IN
THE STRUCTURE
2D
SAME
DIMENSION
TYPICAL BRACKET INSTALLATION
817 (2 LOCATIONS)  WASHER A
X16 17 BOND PER  (2 LOCATIONS.  10/19
WASHER B
6U (2 LOCATIONS)
® [2 LOCATIONS)
WASHER C  18
17 (2 LOCATIONS)
1458423
FIGURE 2: LEFT ELEVATOR - BOND JUMPER BRACKET REPLACEMENT
(SHEET 4 OF 10)
Original Issue: May 08, 2008
Revision 1 April 01, 2010  BOEING PROPRIETARY -  777-55A0014
Copyright © Unpublished Work - See page 1 for details.  39 of 87

### Page 40 (OCR)

BOEING SERVICE BULLETIN 777-55A0014
SEE CO  D 11819
_OCATIONS
8 LOCATIONS 13
15)
4 LOCATIONS
20
4 LOCATIONS
ELEVATOR  (20
FRONT
SPAR
2 LOCATIONS (14  21) 8 LOCATIONS
SEE H
22) 2 LOCATIONS
0.050  (VIEW LOOKING UP)
TYPICAL
0.10
TYPICAL
SHIM
(IF NECESSARY)
BRACKET  1458421
FIGURE 2: LEFT ELEVATOR - BOND JUMPER BRACKET REPLACEMENT
(SHEET 5 OF 10)
Original Issue: May 08, 2008
Revision 1 April 01, 2010  BOEING PROPRIETARY -  777-55A0014
Copyright © Unpublished Work - See page 1 for details.  40 of 87

### Page 41

The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY
numbers shown below are the number of parts necessary for this figure.
MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
2-FASTENERSRemove1
2-JUMPERSDisconnect
4-FASTENERSRemove / Keep2
1189W4000-27
(189W4000-37 or
189W4000-5 optional)
SUPPORT TEERemove / Keep
4-FASTENERSRemove / Keep3
1189W4000-29
(189W4000-11 option-
al)
TEE ASSYRemove / Keep
8BACC30AB6SCOLLARRemove4
8BACB30VG6K5BOLTRemove
Remove sealant
around bracket, if
necessary.
1183W8101-1BRACKETRemove5
if installed.1BACS40V007C054SHIM, LAMINATEDRemove
Discard jumpers and
fasteners with
bracket.
2-JUMPERSRemove
Drill 8 holes in
bracket, 3/16 inch
diameter. (a)
-183W8101-3
(183W8101Y3 optional)
BRACKETDrill6
(d)1BACS40V007C054
(BAC1535-60 optional)
SHIM, LAMINATEDDrill
Clean tabs with sol-
vent. (b)
1183W8101-3
(183W8101Y3 optional)
BRACKETClean7
Clean terminals with
solvent. (b)
2BACJ40E20-26JUMPERClean
Washer B. Use sol-
vent. (b)
2BACW10BP4APUWASHERClean
(h)2BACJ40E20-26JUMPERInstall (New)8
(h)2BACB30LJ4U5BOLT, HEX HEADInstall (New)
(h)6BACW10BP4APUWASHERInstall (New)
(h)2BACN10JC4CMNUTInstall (New)
FIGURE 2: LEFT ELEVATOR - BOND JUMPER BRACKET REPLACEMENT
(SHEET 6 OF 10)
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: May 08, 2008
777-55A0014Revision 1 April 01, 2010
41 of 87
BOEING SERVICE BULLETIN 777-55A0014

### Page 42

MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
Torque nuts to be-
tween 90 and 105
inch-pounds. (i)
2BACN10JC4CMNUTTorque9
1.0 milliohm maxi-
mum. (j)
--RESISTANCEMeasure10
Clean the inner sur-
faces of the flanges
with solvent. (b)
1183W8101-3
(183W8101Y3 optional)
BRACKETClean11
Use solvent. (b)8BACB30VG6-5
(183W8101-5 or
183W8101-6 optional)
BOLT, HEX DRIVEClean
Use solvent. (b)8BACN10YT3CSANUT, SELF-LOCK,
HEX
Clean
Clean the areas that
the bolt heads will
touch. Use abrasive,
then solvent. (b) (c)
2-LIGHTNING DIVERT-
ER STRIPS
Clean
1183W8101-3
(183W8101Y3 optional)
BRACKETInstall (New)12
(d)1BACS40V007C054
(BAC1535-60 optional)
SHIM, LAMINATEDInstall (New)
Install wet with
BMS5-95, CLASS B
sealant. (e)
8BACB30VG6-5
(183W8101-5 or
183W8101-6 optional)
BOLT, HEX DRIVEInstall (New)
8BACN10YT3CSANUT, SELF-LOCK,
HEX
Install (New)
Torque nuts to be-
tween 32 and 38
inch-pounds. (f)
8BACN10YT3CSANUT, SELF-LOCK,
HEX
Torque13
5.0 milliohms maxi-
mum. (g)
--RESISTANCEMeasure14
if removed for ac-
cess.
1189W4000-29
(189W4000-11 option-
al)
TEE ASSYInstall (Kept)15
4-FASTENERSInstall (Kept)
FIGURE 2: LEFT ELEVATOR - BOND JUMPER BRACKET REPLACEMENT
(SHEET 7 OF 10)
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: May 08, 2008
777-55A0014Revision 1 April 01, 2010
42 of 87
BOEING SERVICE BULLETIN 777-55A0014

### Page 43

MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
Clean tabs with
abrasive, then sol-
vent. (b) (c)
2189W4000-13GROUND CLIPClean16
Clean terminals with
solvent. (b)
2BACJ40E20-26JUMPERClean
Washer B. Use sol-
vent. (b)
2NAS1149D0416HWASHER, FLATClean
(h)2BACJ40E20-26JUMPERConnect17
(h)2BACB30LJ4-4BOLT, HEX HEADInstall (New)
Washer A (h)2NAS1149D0463HWASHER, PLAINInstall (New)
Washers B and C
(h)
4NAS1149D0416HWASHER, FLATInstall (New)
(h)2BACN10YR4CDNUTInstall (New)
Torque nuts to be-
tween 78 and 82
inch-pounds. (i)
2BACN10YR4CDNUTTorque18
1.0 milliohm maxi-
mum. (j)
--RESISTANCEMeasure19
1189W4000-27
(189W4000-37 or
189W4000-5 optional)
SUPPORT TEEInstall (Kept)20
4-FASTENERSInstall (Kept)
Cap seal the bolt
heads. Refer to 777
AMM 51-31-01 as
an accepted proce-
dure.
-BMS5-95, CLASS BSEALANTApply21
FIGURE 2: LEFT ELEVATOR - BOND JUMPER BRACKET REPLACEMENT
(SHEET 8 OF 10)
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: May 08, 2008
777-55A0014Revision 1 April 01, 2010
43 of 87
BOEING SERVICE BULLETIN 777-55A0014

### Page 44

MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
to bare aluminum
surfaces as neces-
sary. Refer to 777-
200 SRM 51-20-01
or 777-300 SRM 51-
20-01 as an accept-
ed procedure.
--CHEMICAL CONVER-
SION COATING
Apply22
Apply 2 layers of
primer over the
chemical conversion
coating. Refer to
SOPM 20-41-02 as
an accepted proce-
dure.
-BMS10-11, TYPE 1PRIMERApply
as necessary. Refer
to 777 AMM 51-21-
10 as an accepted
procedure.
--DECORATIVE EXTERI-
OR PAINT
Apply
as necessary. Refer
to 777-200 SRM 51-
20-01 or 777-300
SRM 51-20-01 as an
accepted procedure.
-BMS3-23CORROSION INHIBIT-
ING COMPOUND
Apply
(a) Use of the existing holes in the structure is recommended to find the correct hole positions. Removal of
the bracket from the structure is recommended before drilling holes to full size. If necessary, holes can
be drilled up to 0.030 inch larger to align with the holes in the structure. Refer to 777-200 SRM 51-30-01
or 777-300 SRM 51-30-01, Titanium Alloys, as an accepted procedure.
(b) Refer to SWPM 20-20-00, Cleaning Procedure 5 as an accepted procedure.
(c) Refer to SWPM 20-20-00, Cleaning Procedure 1 or 2 as an accepted procedure.
(d) Use shim if necessary to fill the gap between the bracket and the structure. The shim can be installed
between the bracket and either skin panel. Remove laminations as necessary. Maximum shim thickness
is 0.060 inch, maximum gap is 0.016 inch. Refer to 777-200 SRM 51-20-11 or 777-300 SRM 51-20-11
as an accepted procedure.
(e) Refer to 777 AMM 51-31-01, Fastener Sealing for Corrosion Prevention Procedure 3, as an accepted
procedure. It is not necessary to apply sealant around the bracket.
(f) After initial torque, wait 5 minutes minimum, but no longer than the squeeze-out life of the sealant. Then
torque the nuts again. Make sure that the sealant squeezes out from under the bolt head. Use the
squeezed-out sealant to make a smooth fillet around each bolt head. Refer to 777-200 SRM 51-40-02 or
777-300 SRM 51-40-02 as an accepted procedure.
(g) Measure the resistance between the bracket and both the upper and lower lightning diverter strips ("picture
frames"). Make sure that each resistance is 5.0 milliohms maximum. Refer to SWPM 20-20-00, Test
Procedures for Electrical Bonds, as an accepted procedure. If one or both resistances are more than the
FIGURE 2: LEFT ELEVATOR - BOND JUMPER BRACKET REPLACEMENT
(SHEET 9 OF 10)
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: May 08, 2008
777-55A0014Revision 1 April 01, 2010
44 of 87
BOEING SERVICE BULLETIN 777-55A0014

### Page 45

MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
maximum, then for each applicable side, remove the four nuts and bolts and do steps 11 through 14
again.
(h) Refer to SWPM 20-20-10, Category 2 Fay Sealed Direct Ground Stud Installation, as an accepted proce-
dure, except assemble the jumpers and fasteners in the order shown in View E.
(i) Torque nuts and smooth out sealant. Refer to SWPM 20-20-10, Category 2 Fay Sealed Direct Ground
Stud Installation, as an accepted procedure.
(j) Measure the resistance between each jumper terminal and its tab. Make sure that each resistance is 1.0
milliohm maximum. Refer to SWPM 20-20-10, Maximum Permitted Resistance and Test Procedures for
Ground Studs, and Category 2 Fay Sealed Direct Ground Stud Installation, as accepted procedures.
FIGURE 2: LEFT ELEVATOR - BOND JUMPER BRACKET REPLACEMENT
(SHEET 10 OF 10)
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: May 08, 2008
777-55A0014Revision 1 April 01, 2010
45 of 87
BOEING SERVICE BULLETIN 777-55A0014

### Page 46 (OCR)

BOEING SERVICE BULLETIN 777-55A0014
This Figure applies only to: Group 1.
SEE ®
TIP FAIRING
FWD  SEE DOO
1458429
FIGURE 3: RIGHT ELEVATOR - BOND JUMPER BRACKET REPLACEMENT
(SHEET 1 OF 10)
Original Issue: May 08, 2008
Revision 1 April 01, 2010  BOEING PROPRIETARY -  777-55A0014
Copyright © Unpublished Work - See page 1 for details.  46 of 87

### Page 47 (OCR)

BOEING SERVICE BULLETIN 777-55A0014
(4) 8 LOCATIONS
ELEVATOR
FRONT SPAR
4 LOCATIONS
4 LOCATIONS
FWD
(VIEW LOOKING UP)
B  1458456
FIGURE 3: RIGHT ELEVATOR - BOND JUMPER BRACKET REPLACEMENT
(SHEET 2 OF 10)
Original Issue: May 08, 2008
Revision 1 April 01, 2010  BOEING PROPRIETARY -  777-55A0014
Copyright © Unpublished Work - See page 1 for details.  47 of 87

### Page 48 (OCR)

BOEING SERVICE BULLETIN 777-55A0014
UPPER  ELEVATOR
4 LOCATIONS 1112  SKIN PANEL
LIGHTNING DIVERTER
STRIP
(4 LOCATIONS)
4 LOCATIONS 6  2 (IF NECESSARY)
8 LOCATIONS 11 12 13  CLEANED SURFACE
(11 (UNDERSIDE)
(4 LOCATIONS)
SEE 101BOU
2 LOCATIONS
SEE
4 LOCATIONS 6
LOWER
ELEVATOR
SKIN PANEL
CLEANED
CLEANED 11  1 SURFACE
LIGHTNING  STRIP  DIVERTER  SURFACE  (4 LOCATIONS)  11 12 4 LOCATIONS  FWD  (UNDERSIDE)  (4 LOCATIONS)
FIGURE 3: RIGHT ELEVATOR - BOND JUMPER BRACKET REPLACEMENT
(SHEET 3 OF 10)
Original Issue: May 08, 2008
Revision 1 April 01, 2010  BOEING PROPRIETARY -  777-55A0014
Copyright © Unpublished Work - See page 1 for details.  48 of 87

### Page 49 (OCR)

BOEING SERVICE BULLETIN 777-55A0014
BRACKET  LOCATION OF
EXISTING HOLES IN
THE STRUCTURE
2D
SAME
DIMENSION
TYPICAL BRACKET INSTALLATION
8) 17 (2 LOCATIONS  WASHER
) 1617 (2 LOCATIONS  BOND JUMPER
10 19)
1617 (2 LOCATIONS)  WASHER B
1(2 LOCATIONS)
WASHER C  18
17 (2 LOCATIONS)
1458556
FIGURE 3: RIGHT ELEVATOR - BOND JUMPER BRACKET REPLACEMENT
(SHEET 4 OF 10)
Original Issue: May 08, 2008
Revision 1 April 01, 2010  777-55A0014
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.  49 of 87

### Page 50 (OCR)

BOEING SERVICE BULLETIN 777-55A0014
1 17 18 19 SEE
2 LOCATIONS
(13) 8 LOCATIONS
• ELEVATOR
FRONT SPAR
4 LOCATIONS
4 LOCATIONS
8 LOCATIONS 21
SEE CH  14 2 LOCATIONS
FWD
2 LOCATIONS 22
0.050  (VIEW LOOKING UP)
TYPICAL
-0.10
TYPICAL
SHIM
(IF NECESSARY)
BRACKET  1458519
FIGURE 3: RIGHT ELEVATOR - BOND JUMPER BRACKET REPLACEMENT
(SHEET 5 OF 10)
Original Issue: May 08, 2008
Revision 1 April 01, 2010  BOEING PROPRIETARY -  777-55A0014
Copyright © Unpublished Work - See page 1 for details.  50 of 87

### Page 51

The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY
numbers shown below are the number of parts necessary for this figure.
MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
Remove sealant as
necessary.
2-FASTENERSRemove1
2-JUMPERSDisconnect
to get access to the
bracket.
4-FASTENERSRemove / Keep2
1189W4000-28
(189W4000-38 or
189W4000-6 optional)
SUPPORT TEERemove / Keep
if necessary for ac-
cess.
4-FASTENERSRemove / Keep3
Do not disconnect
the third jumper.
Support the tee
against structure to
prevent damage.
1189W4000-30
(189W4000-12 option-
al)
TEE ASSYRemove / Keep
8BACC30AB6SCOLLARRemove4
8BACB30VG6K5BOLTRemove
Remove sealant
around bracket, if
necessary.
1183W8101-2BRACKETRemove5
if installed.1BACS40V007C054SHIM, LAMINATEDRemove
Discard jumpers and
fasteners with
bracket.
2-JUMPERSRemove
Drill 8 holes in
bracket, 3/16 inch
diameter. (a)
-183W8101-4
(183W8101Y4 optional)
BRACKETDrill6
(d)1BACS40V007C054
(BAC1535-60 optional)
SHIM, LAMINATEDDrill
Clean tabs with sol-
vent. (b)
1183W8101-4
(183W8101Y4 optional)
BRACKETClean7
Clean terminals with
solvent. (b)
2BACJ40E20-26JUMPERClean
Washer B. Use sol-
vent. (b)
2BACW10BP4APUWASHERClean
FIGURE 3: RIGHT ELEVATOR - BOND JUMPER BRACKET REPLACEMENT
(SHEET 6 OF 10)
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: May 08, 2008
777-55A0014Revision 1 April 01, 2010
51 of 87
BOEING SERVICE BULLETIN 777-55A0014

### Page 52

MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
(h)2BACJ40E20-26JUMPERInstall (New)8
(h)2BACB30LJ4U5BOLT, HEX HEADInstall (New)
(h)6BACW10BP4APUWASHERInstall (New)
(h)2BACN10JC4CMNUTInstall (New)
Torque nuts to be-
tween 90 and 105
inch-pounds. (i)
2BACN10JC4CMNUTTorque9
1.0 milliohm maxi-
mum. (j)
--RESISTANCEMeasure10
Clean the inner sur-
faces of the flanges
with solvent. (b)
1183W8101-4
(183W8101Y4 optional)
BRACKETClean11
Use solvent. (b)8BACB30VG6-5
(183W8101-5 or
183W8101-6 optional)
BOLT, HEX DRIVEClean
Use solvent. (b)8BACN10YT3CSANUT, SELF-LOCK,
HEX
Clean
Clean the areas that
the bolt heads will
touch. Use abrasive,
then solvent. (b) (c)
2-LIGHTNING DIVERT-
ER STRIPS
Clean
1183W8101-4
(183W8101Y4 optional)
BRACKETInstall (New)12
(d)1BACS40V007C054
(BAC1535-60 optional)
SHIM, LAMINATEDInstall (New)
Install wet with
BMS5-95, CLASS B
sealant. (e)
8BACB30VG6-5
(183W8101-5 or
183W8101-6 optional)
BOLT, HEX DRIVEInstall (New)
8BACN10YT3CSANUT, SELF-LOCK,
HEX
Install (New)
Torque nuts to be-
tween 32 and 38
inch-pounds. (f)
8BACN10YT3CSANUT, SELF-LOCK,
HEX
Torque13
5.0 milliohms maxi-
mum. (g)
--RESISTANCEMeasure14
if removed for ac-
cess.
1189W4000-30
(189W4000-12 option-
al)
TEE ASSYInstall (Kept)15
4-FASTENERSInstall (Kept)
FIGURE 3: RIGHT ELEVATOR - BOND JUMPER BRACKET REPLACEMENT
(SHEET 7 OF 10)
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: May 08, 2008
777-55A0014Revision 1 April 01, 2010
52 of 87
BOEING SERVICE BULLETIN 777-55A0014

### Page 53

MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
Clean tabs with
abrasive, then sol-
vent. (b) (c)
1189W4000U31GROUND CLIPClean16
Clean terminals with
solvent. (b)
2BACJ40E20-26JUMPERClean
Washer B. Use sol-
vent. (b)
2NAS1149D0416HWASHER, FLATClean
(h)2BACJ40E20-26JUMPERConnect17
(h)2BACB30LJ4-4BOLT, HEX HEADInstall (New)
Washer A (h)2NAS1149D0463HWASHER, PLAINInstall (New)
Washers B and C
(h)
4NAS1149D0416HWASHER, FLATInstall (New)
(h)2BACN10YR4CDNUTInstall (New)
Torque nuts to be-
tween 78 and 82
inch-pounds. (i)
2BACN10YR4CDNUTTorque18
1.0 milliohm maxi-
mum. (j)
--RESISTANCEMeasure19
1189W4000-28
(189W4000-38 or
189W4000-6 optional)
SUPPORT TEEInstall (Kept)20
4-FASTENERSInstall (Kept)
Cap seal the bolt
heads. Refer to 777
AMM 51-31-01 as
an accepted proce-
dure.
-BMS5-95, CLASS BSEALANTApply21
FIGURE 3: RIGHT ELEVATOR - BOND JUMPER BRACKET REPLACEMENT
(SHEET 8 OF 10)
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: May 08, 2008
777-55A0014Revision 1 April 01, 2010
53 of 87
BOEING SERVICE BULLETIN 777-55A0014

### Page 54

MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
to bare aluminum
surfaces as neces-
sary. Refer to 777-
200 SRM 51-20-01
or 777-300 SRM 51-
20-01 as an accept-
ed procedure.
--CHEMICAL CONVER-
SION COATING
Apply22
Apply 2 layers of
primer over the
chemical conversion
coating. Refer to
SOPM 20-41-02 as
an accepted proce-
dure.
-BMS10-11, TYPE 1PRIMERApply
as necessary. Refer
to 777 AMM 51-21-
10 as an accepted
procedure.
--DECORATIVE EXTERI-
OR PAINT
Apply
as necessary. Refer
to 777-200 SRM 51-
20-01 or 777-300
SRM 51-20-01 as an
accepted procedure.
-BMS3-23CORROSION INHIBIT-
ING COMPOUND
Apply
(a) Use of the existing holes in the structure is recommended to find the correct hole positions. Removal of
the bracket from the structure is recommended before drilling holes to full size. If necessary, holes can
be drilled up to 0.030 inch larger to align with the holes in the structure. Refer to 777-200 SRM 51-30-01
or 777-300 SRM 51-30-01, Titanium Alloys, as an accepted procedure.
(b) Refer to SWPM 20-20-00, Cleaning Procedure 5 as an accepted procedure.
(c) Refer to SWPM 20-20-00, Cleaning Procedure 1 or 2 as an accepted procedure.
(d) Use shim if necessary to fill the gap between the bracket and the structure. The shim can be installed
between the bracket and either skin panel. Remove laminations as necessary. Maximum shim thickness
is 0.060 inch, maximum gap is 0.016 inch. Refer to 777-200 SRM 51-20-11 or 777-300 SRM 51-20-11
as an accepted procedure.
(e) Refer to 777 AMM 51-31-01, Fastener Sealing for Corrosion Prevention Procedure 3, as an accepted
procedure. It is not necessary to apply sealant around the bracket.
(f) After initial torque, wait 5 minutes minimum, but no longer than the squeeze-out life of the sealant. Then
torque the nuts again. Make sure that the sealant squeezes out from under the bolt head. Use the
squeezed-out sealant to make a smooth fillet around each bolt head. Refer to 777-200 SRM 51-40-02 or
777-300 SRM 51-40-02 as an accepted procedure.
(g) Measure the resistance between the bracket and both the upper and lower lightning diverter strips ("picture
frames"). Make sure that each resistance is 5.0 milliohms maximum. Refer to SWPM 20-20-00, Test
Procedures for Electrical Bonds, as an accepted procedure. If one or both resistances are more than the
FIGURE 3: RIGHT ELEVATOR - BOND JUMPER BRACKET REPLACEMENT
(SHEET 9 OF 10)
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: May 08, 2008
777-55A0014Revision 1 April 01, 2010
54 of 87
BOEING SERVICE BULLETIN 777-55A0014

### Page 55

MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
maximum, then for each applicable side, remove the four nuts and bolts and do steps 11 through 14
again.
(h) Refer to SWPM 20-20-10, Category 2 Fay Sealed Direct Ground Stud Installation, as an accepted proce-
dure, except assemble the jumpers and fasteners in the order shown in View E.
(i) Torque nuts and smooth out sealant. Refer to SWPM 20-20-10, Category 2 Fay Sealed Direct Ground
Stud Installation, as an accepted procedure.
(j) Measure the resistance between each jumper terminal and its tab. Make sure that each resistance is 1.0
milliohm maximum. Refer to SWPM 20-20-10, Maximum Permitted Resistance and Test Procedures for
Ground Studs, and Category 2 Fay Sealed Direct Ground Stud Installation, as accepted procedures.
FIGURE 3: RIGHT ELEVATOR - BOND JUMPER BRACKET REPLACEMENT
(SHEET 10 OF 10)
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: May 08, 2008
777-55A0014Revision 1 April 01, 2010
55 of 87
BOEING SERVICE BULLETIN 777-55A0014

### Page 56 (OCR)

BOEING SERVICE BULLETIN 777-55A0014
This Figure applies only to: Group 2.
SEE ®
TIP FAIRING
FWD  SEE DOO
1458559
FIGURE 4: RIGHT ELEVATOR - BOND JUMPER BRACKET REPLACEMENT
(SHEET 1 OF 10)
Original Issue: May 08, 2008
Revision 1 April 01, 2010  BOEING PROPRIETARY -  777-55A0014
Copyright © Unpublished Work - See page 1 for details.  56 of 87

### Page 57 (OCR)

BOEING SERVICE BULLETIN 777-55A0014
(4) 8 LOCATIONS  ELEVATOR
FRONT SPAR
4 LOCATIONS
4 LOCATIONS 2
FWD
(VIEW LOOKING UP)
B  1458563
FIGURE 4: RIGHT ELEVATOR - BOND JUMPER BRACKET REPLACEMENT
(SHEET 2 OF 10)
Original Issue: May 08, 2008
Revision 1 April 01, 2010  BOEING PROPRIETARY -  777-55A0014
Copyright © Unpublished Work - See page 1 for details.  57 of 87

### Page 58 (OCR)

BOEING SERVICE BULLETIN 777-55A0014
UPPER  ELEVATOR
4 LOCATIONS 1112  SKIN PANEL
LIGHTNING DIVERTER
4 LOCATIONS 6  2 (IF NECESSARY)
8 LOCATIONS 11 12 13  CLEANED SURFACE
(11 (UNDERSIDE)
SEE 1O1300  (4 LOCATIONS)
2 LOCATIONS
SEE
4 LOCATIONS 6
LOWER
ELEVATOR
SKIN PANEL
CLEANED
CLEANED (11)  1 SURFACE
LIGHTNING  DIVERTER  SURFACE  (4 LOCATIONS)  11 12 4 LOCATIONS  FWD  (UNDERSIDE)  (4 LOCATIONS)
STRIP
FIGURE 4: RIGHT ELEVATOR - BOND JUMPER BRACKET REPLACEMENT
(SHEET 3 OF 10)
Original Issue: May 08, 2008
Revision 1 April 01, 2010  BOEING PROPRIETARY -  777-55A0014
Copyright © Unpublished Work - See page 1 for details.  58 of 87

### Page 59 (OCR)

BOEING SERVICE BULLETIN 777-55A0014
LOCATION OF
BRACKET
EXISTING HOLES IN
THE STRUCTURE
D
2D
SAME
DIMENSION
TYPICAL BRACKET INSTALLATION
& 17 WASHER A  (2 LOCATIONS
3116,17 BOND JUMPER  (2 LOCATIONS  10 19
1017 (2 LOCATIONS)  WASHER B
16 TAB  (2 LOCATIONS
WASHER C  X18)
(2 LOCATIONS)
1458570
FIGURE 4: RIGHT ELEVATOR - BOND JUMPER BRACKET REPLACEMENT
(SHEET 4 OF 10)
Original Issue: May 08, 2008
Revision 1 April 01, 2010  777-55A0014
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.  59 of 87

### Page 60 (OCR)

BOEING SERVICE BULLETIN 777-55A0014
DOGO SEE OO  LOCATIONS
13)8 LOCATIONS  ELEVATOR
FRONT
SPAR
4 LOCATIONS
4 LOCATIONS 20
8 LOCATIONS 21  (14) 2 LOCATIONS
FWD
2 LOCATIONS 22
(VIEW LOOKING UP)  0.050
TYPICAL
-0.10
TYPICAL
SHIM
(IF NECESSARY)
BRACKET
FIGURE 4: RIGHT ELEVATOR - BOND JUMPER BRACKET REPLACEMENT
(SHEET 5 OF 10)
Original Issue: May 08, 2008
Revision 1 April 01, 2010  777-55A0014
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.  60 of 87

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