# Boeing Alert Service Bulletin 777-78A0066: U.S. DOT/FAA - Boeing Service Bulletin

- Rights: © The Boeing Company. Filed by the FAA in regulations.gov docket FAA-2009-0430; AD 2010-26-01 incorporates this document by reference. Not covered by OpenAirDocs’ CC0 dedication.
- Document: [Boeing Alert Service Bulletin 777-78A0066](https://openairdocs.org/service-documents/boeing/777-78a0066.md)
- Title as filed: U.S. DOT/FAA - Boeing Service Bulletin
- Pages: 46
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## Text

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### Page 1

Commercial 
Airplanes
777
Service Bulletin
ALERT
Number: 777-78A0066
Original Issue: June 05, 2008
Revision 2: April 08, 2010
ATA System: 7831
SUBJECT: EXHAUST (GE90 Engine) - Thrust Reverser System - Latch Beam Firewall - Install
Insulation Blanket
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Unpublished Work - All Rights Reserved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 2
B. Concurrent Requirements ...................................... 1 2
C. Reason ................................................ 1 2
D. Description .............................................. 1 4
E. Compliance .............................................. 1 5
F. Approval ............................................... 1 5
G. Manpower .............................................. 1 5
H. Weight and Balance Changes .................................... 1 6
I. Electrical Load Data ......................................... 1 6
J. References .............................................. 1 7
1. Existing Data: ......................................... 1 7
2. Data supplied with this Service Bulletin: ........................... 1 7
3. Installation Drawings Used in the Preparation of this Service Bulletin: ........... 1 7
K. Publications Affected ........................................ 1 7
L. Interchangeability and Intermixability of Parts ........................... 1 7
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 2
F. Special Tooling Necessary to do this Service Bulletin ....................... 2 2
3. ACCOMPLISHMENT INSTRUCTIONS .................................. 2 3
A. GENERAL INFORMATION ..................................... 2 3
B. WORK INSTRUCTIONS ....................................... 2 3
FIGURE 1: THRUST REVERSER - LATCH BEAM - REMOVE AFT INSULATION BLANKET AND
INSULATION FOAM [Group 1] ................................ 2 5
FIGURE 2: LEFT THRUST REVERSER - LATCH BEAM - INSULATION BLANKET INSTALLATION [Group
1 ]  ................................................ 2 7
FIGURE 3: RIGHT THRUST REVERSER - LATCH BEAM - INSULATION BLANKET INSTALLATION [Group
1 ]  ................................................ 3 1
FIGURE 4: THRUST REVERSER - LATCH BEAM - REMOVE INSULATION FOAM [Group 2] .... 3 5
FIGURE 5: LEFT THRUST REVERSER - LATCH BEAM - INSULATION BLANKETS INSTALLATION [Group
2 ]  ................................................ 3 7
FIGURE 6: RIGHT THRUST REVERSER - LATCH BEAM - INSULATION BLANKETS INSTALLATION
[Group 2] ............................................ 4 1
Appendix A: COMPOSITE STUD - ADHESIVE BONDED INSTALLATION ................ 4 5
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Commercial 
Airplanes
777
Service Bulletin
ALERT
Revision Transmittal SheetNumber: 777-78A0066Original Issue: June 05, 2008
Revision 2: April 08, 2010
ATA System: 7831
SUBJECT: EXHAUST (GE90 Engine) - Thrust Reverser System - Latch Beam Firewall - Install
Insulation Blanket
This revision includes all pages of the service bulletin.
COMPLIANCE INFORMATION RELATED TO THIS REVISION
Federal Aviation Administration (FAA) Notice of Proposed Rule Making FAA NPRM 2008-NM-148-AD, is related
to this service bulletin.
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 add airplanes that were inadvertantly omitted in the original issue of this service bulletin,
to change information in the compliance section, and to add an optional instruction to mark the thrust reverser
identifcation plate.
The following sections have been changed:
1. Paragraph 1.A.1., Airplanes - Airplanes with variable numbers WB372-WB388 were added to Group 1.
2. In the Compliance section and Paragraph 1.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," has been changed to,
"Federal Aviation Administration Notice of Proposed Rule Making FAA NPRM 2008-NM-148-AD is related
to this service bulletin."
3. In Paragraph 3.B, Work Instructions, Step 8 - "OPTIONAL: Operators can mark the T/R identification plate
with the service bulletin number to show the change was done. Refer to SOPM 20-50-10 as an accepted
procedure," was added.
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
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REVISION HISTORY
June 05, 2008Original Issue:
March 12, 2009Revision 1:
April 08, 2010Revision 2:
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Commercial 
Airplanes
777
Service Bulletin
ALERT
SummaryNumber: 777-78A0066Original Issue: June 05, 2008
Revision 2: April 08, 2010
ATA System: 7831
SUBJECT: EXHAUST (GE90 Engine) - Thrust Reverser System - Latch Beam Firewall - Install
Insulation Blanket
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 tells the operator to add a thermal insulation blankets, and attachments, to the rear section
of the latch beam of each Thrust Reverser (T/R) half. This change will make sure that a fire can not breach the
bolt-on aluminum plate at the rear of the latch beam and move into the transcowl cavity. A fire that is not contained
could move to other cowl or strut areas. This could cause weakened structural pieces of the T/R to separate in
flight, with the result of a damaged airplane or injury to persons on the ground.
An operator performed an In Flight Shut Down (IFSD) because of an engine fire indication. An air turn back and
satisfactory landing was completed without incident. An under cowl engine fire was put out on the ground. The
cause was determined to be an uncontained failure of the starter in the engine core compartment, which
progressed into the latch beam cavity fuelled by oil supplied by a damaged Integrated Drive Generator (IDG)
oil line. The fire breached the bolt-on aluminum plate on the rear of the latch beam fire wall and moved inside
the translating sleeve. This caused damage to inner and outer walls of the T/R translating sleeve. Installation
of a thermal insulation blanket over the bolt-on aluminum plate area at the rear of the latch beam will protect
this area of the firewall so that it is not breached by a fire. This retrofit is not necessary on T/Rs after airplane
line 413, because of a design change. The design change to the T/R, integrated the bolt on the aluminum plate
area into the main latch beam casting and incorporated thermal insulation blankets across the area.
Boeing Service Related Problem (SRP) 777-SRP-78-0059 is related to this service bulletin.
ACTION (PRR 62777-57RS)
Open a T/R and accomplish the work below:
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Group 1:
1. Remove and keep the existing latch beam insulation blanket.
2. Remove insulation foam on the aft fire wall.
3. Install bonded studs on fire wall.
4. Install new thermal insulation blanket on fire wall.
5. Install removed latch beam insulation blanket.
6. Apply sealant around new thermal insulation blanket.
7. Repeat the work for the opposite T/R. Close the T/R when the work is complete.
NOTE: Service Bulletin 777-24-0058 which installs a check valve in the IDG oil supply should also be
done. The bulletin addresses the potential event of failure of the oil supply line, stopping the flow
of oil which can help feed a fire in the area of the IDG.
Group 2:
1. Remove insulation foam on the aft fire wall.
2. Install bonded studs on fire wall.
3. Install new thermal insulation blanket on fire wall.
4. Install new latch beam insulation blanket.
5. Apply sealant around new thermal insulation blanket.
6. Repeat the work for the opposite T/R. Close the T/R when the work is complete.
NOTE: Service Bulletin 777-24-0058 which installs a check valve in the IDG oil supply should also be
done. The bulletin addresses the potential event of failure of the oil supply line, stopping the flow
of oil which can help feed a fire in the area of the IDG.
EFFECTIVITY
777-200 Airplanes with GE-90 engines. Refer to Paragraph 1.A.1., Airplanes for the list of affected airplanes.
COMPLIANCE
Federal Aviation Administration Notice of Proposed Rule Making FAA NPRM 2008-NM-148-AD is related to this
service bulletin.
Boeing recommends that the change, given in this service bulletin be done within 1, 825 days or 4, 500 flight
cycles after the original issue date of this service bulletin, whichever occurs first.
INDUSTRY SUPPORT INFORMATION
Boeing warranty remedies are not available for the configuration changes given in this service bulletin.
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MANPOWER
Group 1:
EACH ENGINE
Elapsed HoursTotal Task Hours
7.507.50
Group 2:
EACH ENGINE
Elapsed HoursTotal Task Hours
7.257.25
MATERIAL INFORMATION
Boeing Supplied Kits/Parts.
Refer to Paragraph 2.A., Material - Price and Availability.
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BOEING SERVICE BULLETIN 777-78A0066
ALERT  ALERT
RIGHT LATCH BEAM
SEE
LEFT LATCH BEAM
SEE
NO. 5
LATCH
NO. 4
LATCH
NO. 3
LATCH
NO. 2
LATCH
REMOVE INSULATION
FOAM. INSTALL
BONDED STUDS,
NEW INSULATION
BLANKET AND
SEALANT.
GROUP 2 AIRPLANES:
INSTALL NEW INSULATION  LATCH ACCESS DOOR
FWD <  BLANKET
RIGHT LATCH BEAM SHOWN
LEFT LATCH BEAM SIMILAR
1493858
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Commercial 
Airplanes
777
Service Bulletin
ALERT
Number: 777-78A0066
Original Issue: June 05, 2008
Revision 2: April 08, 2010
ATA System: 7831
SUBJECT: EXHAUST (GE90 Engine) - Thrust Reverser System - Latch Beam Firewall - Install
Insulation Blanket
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 airplanes shown below. Refer to PRR 62777-57RS for data about
this change.
DESCRIPTIONCONFIGURATIONGROUP
All 777-200 airplanes with GE90 engines through line number 413
with a forward insulation blanket.
-1
All 777-200 airplanes with GE90 engines through line number 413
without a forward insulation blanket.
-2
Airplane Models:
777-200
GroupVariable Number
2WA076 - WA080
2WA116 - WA119
2WB001 - WB009
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GroupVariable Number
1WB010 - WB021
2WB121 - WB122
1WB123 - WB125
1WB271 - WB273
1WB276 - WB286
1WB291 - WB302
1WB306 - WB307
2WB311 - WB313
1WB314 - WB337
1WB341 - WB342
1WB371 - WB388
1WB406
1WB411 - WB413
1WB476
1WC241
1WC281
2. Spares Affected
Spare Thrust Reversers (T/R) are affected. Refer to Paragraph 2.C., Parts Necessary for Each
Airplane, for parts necessary to change spares.
B. Concurrent Requirements
None.
C. Reason
This service bulletin tells the operator to add a thermal insulation blankets, and attachments, to the
rear section of the latch beam of each Thrust Reverser (T/R) half. This change will make sure that a
fire can not breach the bolt-on aluminum plate at the rear of the latch beam and move into the transcowl
cavity. A fire that is not contained could move to other cowl or strut areas. This could cause weakened
structural pieces of the T/R to separate in flight, with the result of a damaged airplane or injury to
persons on the ground..
An operator performed an In Flight Shut Down (IFSD) because of an engine fire indication. An air turn
back and satisfactory landing was completed without incident. An under cowl engine fire was put out
on the ground. The cause was determined to be an uncontained failure of the starter in the engine core
compartment, which progressed into the latch beam cavity fuelled by oil supplied by a damaged
Integrated Drive Generator (IDG) oil line. The fire breached the bolt-on aluminum plate on the rear of
the latch beam fire wall and moved inside the translating sleeve. This caused damage to inner and
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outer walls of the T/R translating sleeve. Installation of a thermal insulation blanket over the bolt-on
aluminum plate area at the rear of the latch beam will protect this area of the firewall so that it is not
breached by a fire. This retrofit is not necessary on T/Rs after airplane line 413, because of a design
change. The design change to the T/R, integrated the bolt on the aluminum plate area into the main
latch beam casting and incorporated thermal insulation blankets across the area.
Boeing Service Related Problem (SRP) 777-SRP-78-0059 is related to this service bulletin.
Revision 1 is sent to change the assigned grouping of three airplanes that were assigned to the incorrect
group in the original issue of this service bulletin. Also, the Summary illustration and Figures 1 thru 6
are corrected to show and accurate view of the lower attachment points for insulation blanket assemblies
315W1654-31 and 315W1654-32.
These sections have changed:
1. Summary:
– Illustration: changed to show the correct insulation blanket attachment points.
– Compliance: changed to inform operators to do the tasks in this service bulletin within a given
time after the original issue of this service bulletin.
2. Paragragh 1.A., Effectivity: Airplanes variable numbers WB311 thru WB313 are moved from Group
1 to Group 2.
3. FIGURE 1: Illustration changed to show the correct view of insulation blanket installation.
4. FIGURE 2: Sheet 2 - Illustration changed to show the correct insulation blanket fastener locations.
5. FIGURE 3: Sheet 2 - Changed to show correct insulation blanket fastener locations.
6. FIGURE 4: Illustration changed to show corrected view of insulation blanket.
7. FIGURE 5: Sheet 2 - Changed to show correct insulation blanket fastener locations.
8. FIGURE 6: Sheet 2 - Changed to show correct insulation blanket fastener loactions.
The data given in Information Notice 777-78A0066 IN 01 is included in this revision.
Revision 2 is sent to add airplanes that were inadvertantly omitted in the original issue of this service
bulletin, to change information in the compliance section, and to add an optional instruction to mark
the thrust reverser identifcation plate.
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The following sections have been changed:
1. Paragraph 1.A.1., Airplanes - Airplanes with variable numbers WB372-WB388 were added to
Group 1.
2. In the Compliance section and Paragraph 1.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," has been changed to, "Federal Aviation Administration Notice of Proposed Rule
Making FAA NPRM 2008-NM-148-AD is related to this service bulletin."
3. In Paragraph 3.B, Work Instructions, Step 8 - "OPTIONAL: Operators can mark the T/R identification
plate with the service bulletin number to show the change was done. Refer to SOPM 20-50-10 as
an accepted procedure," was added.
D. Description
Open a T/R and accomplish the work below.
Group 1:
1. Remove and keep the existing latch beam insulation blanket.
2. Remove insulation foam on the aft fire wall.
3. Install bonded studs on fire wall.
4. Install new thermal insulation blanket on fire wall.
5. Install removed latch beam insulation blanket.
6. Apply sealant around new thermal insulation blanket.
7. Repeat the work for the opposite T/R. Close the T/R when the work is complete.
NOTE: Service Bulletin 777-24-0058 which installs a check valve in the IDG oil supply should
also be done. The bulletin addresses the potential event of failure of the oil supply line,
stopping the flow of oil which can help feed a fire in the area of the IDG.
Group 2:
1. Remove insulation foam on the aft fire wall.
2. Install bonded studs on fire wall.
3. Install new thermal insulation blanket on fire wall.
4. Install new latch beam insulation blanket.
5. Apply sealant around new thermal insulation blanket.
6. Repeat the work for the opposite T/R. Close the T/R when the work is complete.
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NOTE: Service Bulletin 777-24-0058 which installs a check valve in the IDG oil supply should
also be done. The bulletin addresses the potential event of failure of the oil supply line,
stopping the flow of oil which can help feed a fire in the area of the IDG.
Revision 1 - No more work is necessary on airplanes changed as shown in the original issue of this
service bulletin.
Revision 2 - Federal Aviation Administration (FAA) Notice of Proposed Rule Making FAA NPRM
2008-NM-148-AD, is related to this service bulletin.
No more work is necessary on airplanes changed as shown in the original issue of this service bulletin.
The work in this service bulletin is done in the maintenance zone(s) given below.
Affected Maintenance Zones
ZoneModel
415, 416, 425, 426777-200
E. Compliance
Federal Aviation Administration Notice of Proposed Rule Making FAA NPRM 2008-NM-148-AD is
related to this service bulletin.
Boeing recommends that the change given in this service bulletin be done within 1,825 days or 4,500
flight cycles after the original issue date of this service bulletin, whichever occurs first.
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 service bulletin for each
engine. 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
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— Time to cure the materials
— Time to make the parts
— Time to find the tools.
Group 1:
Elapsed HoursTask HoursNumber of Per-
sons
Task
0.500.501Open Access
1.001.001Figure 1
2.752.751Figure 2
2.752.751Figure 3
0.500.501Close Access
7.507.50TOTAL FOR EACH ENGINE
Group 2:
Elapsed HoursTask HoursNumber of Per-
sons
Task
0.500.501Open Access
0.750.751Figure 4
2.752.751Figure 5
2.752.751Figure 6
0.500.501Close Access
7.257.25TOTAL FOR EACH ENGINE
H. Weight and Balance Changes
Group 1:
Change in Moment
(Pound-Inches)
Change in Weight
(Pounds)
Airplane
+ 3431.7+ 3.2For Each Engine
Group 2:
Change in Moment
(Pound-Inches)
Change in Weight
(Pounds)
Airplane
+ 4288.0 Ib-in+ 4.0 IbsFor Each Engine
I. Electrical Load Data
Not changed.
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J. References
1. Existing Data:
a. Engineering Change Memo PRR 62777-57RS
b. Federal Aviation Administration (FAA) Notice of Proposed Rule Making 2008-NM-148-AD
c. Standard Overhaul Practices Manual (SOPM) 20-30-03, 20-41-02, 20-50-10, 20-50-12,
20-50-19
d. 777 Aircraft Maintenance Manual (AMM) 78-31-00
e. Boeing Drawing 012W6100
f. Boeing Parts Standards Document D-590
g. Service Related Problem (SRP) 777-SRP-78-0059
2. Data supplied with this Service Bulletin:
None.
3. Installation Drawings Used in the Preparation of this Service Bulletin:
None.
K. Publications Affected
Chapter-SectionPublication
78-31777 Maintenance Manual
78-31777 Illustrated Parts Catalog
78-31Component Maintenance Manual
L. Interchangeability and Intermixability of Parts
Accomplishment of this service bulletin does not affect interchangeability or intermixability of parts.
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2.    MATERIAL INFORMATION
A. Material - Price and Availability
Boeing can supply the kit shown in Paragraph 2.C., Parts Necessary For Each Airplane Engine and
Paragraph 2.D., Parts Necessary to Change Spares, 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.
Group 1:
Unit Price thru
December 31,
2008
ROLT
(Weeks)
QTYDateNameKit Number
$3,5463010April 14,
2008
Top Kit - GE90 Latch
Beam Insulation Blanket
005W3346-1
Group 2:
Unit Price thru
December 31,
2008
ROLT
(Weeks)
QTYDateNameKit Number
$5,2533010Nov 06,
2008
Top Kit - GE90 Latch
Beam Insulation Blanket
005W3346-4
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. 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 not available for the configuration changes given in this service bulletin.
C. Parts Necessary For Each Airplane
1. Kits/Parts:
One top kit and the items shown in Paragraph 2.C.2., Parts and Materials Supplied by the Operator,
are necessary for each airplane engine.
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### Page 20

To get the kits/parts shown below, refer to Paragraph 2.A., Material - Price and Availability.
Figure Kit
6532Top Kit
--11005W3346-1
11--005W3346-4
Group 1:
KIT 005W3346-1
NOTES
Existing Part
NumberName
Figure
New Part Number
32
QTY
WASHER34315W1163-26
KIT - LATCH
BEAM BLANKET
ASSY
1315W1257-1
KIT - LATCH
BEAM BLANKET
ASSY
1315W1257-2
BUSHING, PLAIN34BACB28AK04-030
NUT34BACN10JC3C
STUD, COMPOS-
ITE BASE
34CB4017C3CRA12R
Group 2:
KIT 005W3346-4
NOTES
Existing Part
NumberName
Figure
New Part Number
65
QTY
KIT - LATCH
BEAM BLANKET
ASSY
1315W1257-1
KIT - LATCH
BEAM BLANKET
ASSY
1315W1257-2
BLANKET ASSY1315W1654-31
BLANKET ASSY1315W1654-32
BUSHING, PLAIN34BACB28AK04-030
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### Page 21

Group 2:
KIT 005W3346-4
NOTES
Existing Part
NumberName
Figure
New Part Number
65
QTY
NUT34BACN10JC3C
SCREW, CAP33BACS12GU3K15
WASHER, PLAIN33BACW10P392CC
WASHER34BACW10P458CD
STUD, COMPOS-
ITE BASE
34CB4017C3CRA12R
2. Parts and Materials Supplied by the Operator:
NotesNameQTYPart Number/ Specification
PRIMER1 PtBMS 10-11,TYPE 1
ADHESIVE1 PtBMS 5-109, TYPE 2, CLASS 2
SEALANT1 PtBMS 5-63, TYPE 1, CLASS B-
4
3. Parts Modified and Reidentified:
None.
4. Parts Removed and Not Replaced:
None.
D. Parts Necessary to Change Spares
To get the kit shown below, refer to Paragraph 2.A., Material - Price and Availability.
QTYNamePart Number
1(a)Top Kit - GE90 Latch Beam Insulation Blanket005W3346-1
1(a)
(b)
Top Kit - GE90 Latch Beam Insulation Blanket005W3346-4
(a) The top kit has parts to modify the left and right halves of a T/R.
(b) This kit contains the additional 315W1654-31 and 315W1654-32 insulation blankets and the attached
hardware necessary for the Group 2 airplane configuration.
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### Page 22

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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ALERTALERT

### Page 23

3.    ACCOMPLISHMENT INSTRUCTIONS
A. GENERAL INFORMATION
CAUTION: KEEP THE WORK AREA, WIRES AND ELECTRICAL BUNDLES CLEAN OF METAL
PARTICLES OR CONTAMINATION WHEN YOU USE TOOLS. UNWANTED MATERIAL,
METAL PARTICLES OR CONTAMINATION CAUGHT IN WIRE BUNDLES CAN CAUSE
DAMAGE TO THE BUNDLES. DAMAGED WIRE BUNDLES CAN CAUSE SPARKS OR
OTHER ELECTRICAL DAMAGE.
NOTE: 1. Manual titles are referred to by acronyms. Refer to Paragraph 1.J., References, for
definition of the acronyms.
2. Obey all of the warnings and cautions given in the specified manual sections.
3. Unless shown differently, these dimensions and tolerances are used:
— Torque limits to tighten nuts and bolts are given in 777 SRM, Chapter 51.
4. 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.
5. These work instructions refer to procedures included on 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.
6. This service bulletin is done on each engine's Thrust Reverser (T/R) on the airplane.
7. Refer to Appendix A as an accepted procedure to install bonded studs.
B. WORK INSTRUCTIONS
1. Open a T/R. Refer to 777 AMM 78-31-00, as an accepted procedure to open a T/R.
2. Group 1:
Remove the aft most latch beam insulation blanket and insulation foam as given in FIGURE 1.
3. Group 2:
Remove the latch beam insulation foam as given in FIGURE 4.
4. Group 1:
Install studs, blankets and sealant for the left side T/R half, as given in FIGURE 2.
5. Group 1:
Install studs, blankets and sealant for the right side T/R half, as given in FIGURE 3.
6. Group 2:
Install studs, blankets and sealant for the left side T/R half, as given in FIGURE 5.
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### Page 24

7. Group 2:
Install studs, blankets and sealant for the right side T/R half, as given in FIGURE 6.
8. OPTIONAL: Operators can mark the T/R identification plate with the service bulletin number to
show the change was done. Refer to SOPM 20-50-10 as an accepted procedure.
9. Close the T/R. Refer to 777 AMM 78-31-00, as an accepted procedure to close the T/R.
10. Put the airplane back to a serviceable condition.
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### Page 25 (OCR)

BOEING SERVICE BULLETIN 777-78A0066
ALERT  ALERT
This Figure applies only to: Group 1.
RIGHT LATCH BEAM
LEFT LATCH BEAM  SEE A
SEE
NO. 5
LATCH
NO. 4
LATCH
NO. 3
LATCH
NO. 2
LATCH
3) 4
LATCH
ACCESS
FWD <  DOOR
RIGHT LATCH BEAM SHOWN
LEFT LATCH BEAM SIMILAR
1494896
FIGURE 1: THRUST REVERSER - LATCH BEAM - REMOVE AFT INSULATION BLANKET AND INSULATION
FOAM
(SHEET 1 OF 2)
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Copyright © Unpublished Work - See page 1 for details.  BOEING PROPRIETARY -  25 of 46

### Page 26

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 both left and right T/R halves.
MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
6-SCREWRemove / Keep1
6-WASHERRemove / Keep
(a)2-BLANKET, INSULA-
TION
Remove / Keep2
(b)--INSULATIONRemove3
(c)--SCRAPED AREAClean4
(a) Carefully lift corner of the over-lapping insulation blanket to remove the aft-most insulation blanket. Loosen
other insulation blanket fasteners as necessary to remove the aft-most insulation blanket.
(b) Remove all insulation from the latch beam that the new insulation blanket will cover. Use a hard resin
phenolic scraper to remove as much as possible. Remove all loose material with a soft bristle brush or a
clean cotton wiper. If the exposed metal has hydraulic fluid on it, dry it with a cotton wiper.
(c) Refer to SOPM 20-30-03 as an accepted procedure to clean the scraped area. Make sure to dry the area
with a cotton wiper.
FIGURE 1: THRUST REVERSER - LATCH BEAM - REMOVE AFT INSULATION BLANKET AND INSULATION
FOAM
(SHEET 2 OF 2)
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BOEING SERVICE BULLETIN 777-78A0066
ALERTALERT

### Page 27 (OCR)

BOEING SERVICE BULLETIN 777-78A0066
ALERT  ALERT
This Figure applies only to: Group 1.
LEFT LATCH BEAM
SEE
NO. 5
LATCH
BOLT  NO. 4
LATCH
BOLT
NO. 3
LATCH
BOLT
NO. 2
LATCH
BOLT
SEE
→FWD
LATCH BEAM
FAIRING
LEFT LATCH BEAM
1494910
FIGURE 2: LEFT THRUST REVERSER - LATCH BEAM - INSULATION BLANKET INSTALLATION
(SHEET 1 OF 4)
Original Issue: June 05, 2008
Revision 2 April 08, 2010  BOEING PROPRIETARY -  777-78A0066
Copyright © Unpublished Work - See page 1 for details.  27 of 46

### Page 28 (OCR)

BOEING SERVICE BULLETIN 777-78A0066
ALERT  ALERT
→→FWD
USE ADHESIVE
HERE BETWEEN
BLANKETS
LEFT LATCH BEAM
1495409
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 the left T/R half.
FIGURE 2: LEFT THRUST REVERSER - LATCH BEAM - INSULATION BLANKET INSTALLATION
(SHEET 2 OF 4)
Original Issue: June 05, 2008
Revision 2 April 08, 2010  BOEING PROPRIETARY -  777-78A0066
Copyright © Unpublished Work - See page 1 for details.  28 of 46

### Page 29

MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
(a)-BMS 10-11,TYPE 1PRIMERApply1
(b)1315W1257-1KIT - LATCH BEAM
BLANKET ASSY
Put / Hold2
(c)3-MARKApply3
1315W1257-1KIT - LATCH BEAM
BLANKET ASSY
Remove / Keep4
(d)3-PIN, PILOTRemove5
(e) (f) (g)4CB4017C3CRA12RSTUD, COMPOSITE
BASE
Install (New)6
(e)-BMS 5-109, TYPE 2,
CLASS 2
ADHESIVEApply
(g)4BACB28AK04-030BUSHING, PLAINInstall (New)7
1315W1257-1KIT - LATCH BEAM
BLANKET ASSY
Install (New)8
(g) (h)4315W1163-26WASHERInstall (New)9
(g) (i)4BACN10JC3CNUTInstall (New)10
(j)1-BLANKET, INSULA-
TION
Install (Kept)11
3-WASHERInstall (Kept)12
(i)3-SCREWInstall (Kept)13
(k)-BMS 5-63, TYPE 1,
CLASS B-4
SEALANTApply14
(a) If the removal of the insulation material removed primer, touch up the latch beam as necessary. Refer to
SOPM 20-41-02 as an accepted procedure to apply primer.
(b) Position the latch beam insulation blanket in the latch beam to mark the locations for the studs. The part
name indicates a kit, but the part is supplied assembled
(c) Use the insulation blanket holes to locate and mark the location for the three studs that will be bonded to
the latch beam. Center a Pressure Application Fixture (PAF), supplied with a composite stud, over the
hole marks and mark the latch beam around the bottom of the PAF. This mark will be used to locate the
PAF and composite stud with adhesive. Refer to APPENDIX A for PAF description.
(d) Cut off the pilot pin from the stud base of the composite stud as close as possible to the stud base. Abrade
or scrape the stud base if necessary to give a flat base.
(e) Clean stud base and latch beam mating area. Apply BMS 5-109, Type 2, Class 2, adhesive. Put, hold,
and cure stud to the latch beam with a PAF. Refer to Appendix A and SOPM 20-50-12, Type 94, as ac-
cepted procedures to install composite studs.
(f) Composite studs are supplied with a Pressure Application Fixture (PAF). Refer to APPENDIX A to see
how the PAF is used.
FIGURE 2: LEFT THRUST REVERSER - LATCH BEAM - INSULATION BLANKET INSTALLATION
(SHEET 3 OF 4)
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Copyright © Unpublished Work - See page 1 for details.
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777-78A0066Revision 2 April 08, 2010
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BOEING SERVICE BULLETIN 777-78A0066
ALERTALERT

### Page 30

MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
(g) The qty given is one more than necessary. Return part to your stores if it is not used
(h) Washer BACW10P458CD is optional to 315W1163-26.
(i) Torque to 20-25 in-lb. Make sure other insulation blanket fasteners that were loosened to remove the
kept insulation blanket, are tightened.
(j) Clean the mating areas of the two insulation blankets. Apply BMS 5-109, Type 2, Class 2, adhesive. Refer
to SOPM 20-50-12, Type 94, as an accepted procedure to apply the adhesive. Make sure the insulation
blanket that is forward of this insulation blanket, overlaps it.
(k) Seal where shown in bold line. Seal edge common to both blankets. Seal new blanket edges common to
the latch beam. Seal gap that forms next to the two blankets and the forward stiffener. Seal gap that forms
at the lower end of the stiffeners. DO NOT SEAL edges of new blanket that are directly above the access
door. DO NOT SEAL edges of new blanket around the upper end of the stiffeners. Be careful to not plug
drain holes when the sealant is applied. Refer to SOPM 20-50-19 as an accepted procedure to seal the
blanket.
FIGURE 2: LEFT THRUST REVERSER - LATCH BEAM - INSULATION BLANKET INSTALLATION
(SHEET 4 OF 4)
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Copyright © Unpublished Work - See page 1 for details.
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BOEING SERVICE BULLETIN 777-78A0066
ALERTALERT

### Page 31 (OCR)

BOEING SERVICE BULLETIN 777-78A0066
ALERT  ALERT
This Figure applies only to: Group 1.
RIGHT LATCH BEAM
SEE A
NO. 5
LATCH
NO. 4
LATCH
NO. 3
LATCH
NO. 2
LATCH
SEE B
LATCH
ACCESS
FWD <  DOOR
RIGHT LATCH BEAM
1494933
FIGURE 3: RIGHT THRUST REVERSER - LATCH BEAM - INSULATION BLANKET INSTALLATION
(SHEET 1 OF 4)
Original Issue: June 05, 2008
Revision 2 April 08, 2010  BOEING PROPRIETARY -  777-78A0066
Copyright © Unpublished Work - See page 1 for details.  31 of 46

### Page 32 (OCR)

BOEING SERVICE BULLETIN 777-78A0066
ALERT  ALERT
FWD_
10
USE ADHESIVE
HERE BETWEEN
BLANKETS
RIGHT  LATCH BEAM
1494976
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 the rightft T/R half.
FIGURE 3: RIGHT THRUST REVERSER - LATCH BEAM - INSULATION BLANKET INSTALLATION
(SHEET 2 OF 4)
Original Issue: June 05, 2008
Revision 2 April 08, 2010  BOEING PROPRIETARY -  777-78A0066
Copyright © Unpublished Work - See page 1 for details.  32 of 46

### Page 33

MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
(a)-BMS 10-11,TYPE 1PRIMERApply1
(b)1315W1257-2KIT - LATCH BEAM
BLANKET ASSY
Put / Hold2
(c)3-MARKApply3
1315W1257-2KIT - LATCH BEAM
BLANKET ASSY
Remove / Keep4
(d)3-PIN, PILOTRemove / Keep5
(e) (f)3CB4017C3CRA12RSTUD, COMPOSITE
BASE
Install (New)6
(e)-BMS 5-109, TYPE 2,
CLASS 2
ADHESIVEApply
3BACB28AK04-030BUSHING, PLAINInstall (New)7
1315W1257-2KIT - LATCH BEAM
BLANKET ASSY
Install (New)8
(g)3315W1163-26WASHERInstall (New)9
(h)3BACN10JC3CNUTInstall (New)10
(i)1-BLANKET, INSULA-
TION
Install (Kept)11
3-WASHERInstall (Kept)12
(h)3-SCREWInstall (Kept)13
(j)-BMS 5-63, TYPE 1,
CLASS B-4
SEALANTApply14
(a) If the removal of the insulation material removed primer then apply primer to the latch beam as necessary.
Refer to SOPM 20-41-02 as an accepted procedure to apply primer.
(b) Position the latch beam insulation blanket in the latch beam to mark the locations for the studs. The part
name indicates a kit, but the part is supplied assembled
(c) Use the insulation blanket holes to locate and mark the location for the three studs that will be bonded to
the latch beam. Center a Pressure Application Fixture (PAF), supplied with a composite stud, over the
hole marks and mark the latch beam around the bottom of the PAF. This mark will be used to locate the
PAF and composite stud with adhesive. Refer to APPENDIX A for PAF description.
(d) Cut off the pilot pin from the stud base of the composite stud as close as possible to the stud base. Abrade
or scrape the stud base if necessary to give a flat base.
(e) Clean stud base and latch beam mating area. Apply BMS 5-109, Type 2, Class 2, adhesive. Put, hold,
and cure stud to the latch beam with a PAF. Refer to Appendix A and SOPM 20-50-12, Type 94, as ac-
cepted procedures to install composite studs.
(f) Composite studs are supplied with a Pressure Application Fixture (PAF). Refer to APPENDIX A to see
how the PAF is used.
FIGURE 3: RIGHT THRUST REVERSER - LATCH BEAM - INSULATION BLANKET INSTALLATION
(SHEET 3 OF 4)
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: June 05, 2008
777-78A0066Revision 2 April 08, 2010
33 of 46
BOEING SERVICE BULLETIN 777-78A0066
ALERTALERT

### Page 34

MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
(g) Washer BACW10P458CD is optional to 315W1163-26.
(h) Torque to 20-25 in-lb. Make sure that other insulation blanket fasteners that were loosened to remove
the kept insulation blanket, are tightened.
(i) Clean the mating areas of the two insulation blankets. Apply BMS 5-109, Type 2, Class 2, adhesive. Refer
to SOPM 20-50-12, Type 94 as an accepted procedure to install the adhesive. Make sure the insulation
blanket that is forward of this insulation blanket, overlaps it.
(j) Seal where shown in bold line. Seal edge common to both blankets. Seal new blanket edges common to
the latch beam. Seal gap that forms next to the two blankets and the forward stiffener. Seal gap that forms
at the lower end of the stiffeners. DO NOT SEAL edges of new blanket that are directly above the access
door. DO NOT SEAL edges of new blanket around the upper end of the stiffeners. Be careful to not plug
drain holes when the sealant is applied. Refer to SOPM 20-50-19 as an accepted procedure to seal the
blanket.
FIGURE 3: RIGHT THRUST REVERSER - LATCH BEAM - INSULATION BLANKET INSTALLATION
(SHEET 4 OF 4)
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: June 05, 2008
777-78A0066Revision 2 April 08, 2010
34 of 46
BOEING SERVICE BULLETIN 777-78A0066
ALERTALERT

### Page 35 (OCR)

BOEING SERVICE BULLETIN 777-78A0066
ALERT  ALERT
This Figure applies only to: Group 2.
RIGHT LATCH BEAM
LEFT LATCH BEAM  SEE A
SEE
NO. 5
LATCH
NO. 4
LATCH
NO. 3
LATCH
NO. 2
LATCH
LATCH
ACCESS
FWD <  DOOR
RIGHT LATCH BEAM SHOWN
LEFT LATCH BEAM SIMILAR
1541685
FIGURE 4: THRUST REVERSER - LATCH BEAM - REMOVE INSULATION FOAM
(SHEET 1 OF 2)
Original Issue: June 05, 2008
Revision 2 April 08, 2010  777-78A0066
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.  35 of 46

### Page 36

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 both the left and right T/R halves..
MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
(a)--INSULATIONRemove1
(b)--SCRAPED AREAClean2
(a) Remove all insulation from the latch beam that the new insulation blanket will cover. Use a hard resin
phenolic scraper to remove as much as possible. Remove all loose material with a soft bristle brush or a
clean cotton wiper. If the exposed metal has hydraulic fluid on it, dry it with a cotton wiper.
(b) Refer to SOPM 20-30-03 as an accepted procedure to clean the scraped area. Make sure to dry the area
with a cotton wiper.
FIGURE 4: THRUST REVERSER - LATCH BEAM - REMOVE INSULATION FOAM
(SHEET 2 OF 2)
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: June 05, 2008
777-78A0066Revision 2 April 08, 2010
36 of 46
BOEING SERVICE BULLETIN 777-78A0066
ALERTALERT

### Page 37 (OCR)

BOEING SERVICE BULLETIN 777-78A0066
ALERT  ALERT
This Figure applies only to: Group 2.
LEFT LATCH BEAM
SEE
NO. 5
LATCH
BOLT  NO. 4
LATCH
BOLT
NO. 3
LATCH
BOLT
NO. 2
LATCH
BOLT
SEE
→FWD
LATCH BEAM
FAIRING
LEFT LATCH BEAM
1541686
FIGURE 5: LEFT THRUST REVERSER - LATCH BEAM - INSULATION BLANKETS INSTALLATION
(SHEET 1 OF 4)
Original Issue: June 05, 2008
Revision 2 April 08, 2010  BOEING PROPRIETARY -  777-78A0066
Copyright © Unpublished Work - See page 1 for details.  37 of 46

### Page 38 (OCR)

BOEING SERVICE BULLETIN 777-78A0066
ALERT  ALERT
...
> FWD
USE ADHESIVE
HERE BETWEEN
BLANKETS
LEFT LATCH BEAM
1541687
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 the left T/R half.
FIGURE 5: LEFT THRUST REVERSER - LATCH BEAM - INSULATION BLANKETS INSTALLATION
(SHEET 2 OF 4)
Original Issue: June 05, 2008
Revision 2 April 08, 2010  BOEING PROPRIETARY -  777-78A0066
Copyright © Unpublished Work - See page 1 for details.  38 0f 46

### Page 39

MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
(a)-BMS 10-11,TYPE 1PRIMERApply1
(b)1315W1257-1KIT - LATCH BEAM
BLANKET ASSY
Put / Hold2
(c)3-MARKApply3
1315W1257-1KIT - LATCH BEAM
BLANKET ASSY
Remove / Keep4
(d)3-PIN, PILOTRemove5
(e) (f)4CB4017C3CRA12RSTUD, COMPOSITE
BASE
Install (New)6
(e)-BMS 5-109, TYPE 2,
CLASS 2
ADHESIVEApply
(g)4BACB28AK04-030BUSHING, PLAINInstall (New)7
1315W1257-1KIT - LATCH BEAM
BLANKET ASSY
Install (New)8
(g) (h)4BACW10P458CDWASHERInstall (New)9
(g) (i)4BACN10JC3CNUTInstall (New)10
(j)1315W1654-31BLANKET ASSYInstall (New)11
3BACW10P392CCWASHER, PLAINInstall (New)12
(i)3BACS12GU3K15SCREW, CAPInstall (New)13
(k)-BMS 5-63, TYPE 1,
CLASS B-4
SEALANTApply14
(a) If the removal of the insulation material removed primer then apply primer to the latch beam as necessary.
Refer to SOPM 20-41-02 as an accepted procedure to apply primer.
(b) Position the latch beam insulation blanket in the latch beam to mark the locations for the studs. The part
name indicates a kit, but the part is supplied assembled
(c) Use the insulation blanket holes to locate and mark the location for the three studs that will be bonded to
the latch beam. Center a Pressure Application Fixture (PAF), supplied with a composite stud, over the
hole marks and mark the latch beam around the bottom of the PAF. This mark will be used to locate the
PAF and composite stud with adhesive. Refer to APPENDIX A for PAF description.
(d) Cut off the pilot pin from the stud base of the composite stud as close as possible to the stud base. Abrade
or scrape the stud base if necessary to give a flat base.
(e) Clean stud base and latch beam mating area. Apply BMS 5-109, Type 2, Class 2, adhesive. Put, hold,
and cure stud to the latch beam with a PAF. Refer to APPENDIX A and SOPM 20-50-12, Type 94, as
accepted procedures to install composite studs.
(f) Composite studs are supplied with a Pressure Application Fixture (PAF). Refer to APPENDIX A to see
how the PAF is used.
(g) The qty given is one more than necessary. Return part to your stores if it is not used
FIGURE 5: LEFT THRUST REVERSER - LATCH BEAM - INSULATION BLANKETS INSTALLATION
(SHEET 3 OF 4)
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: June 05, 2008
777-78A0066Revision 2 April 08, 2010
39 of 46
BOEING SERVICE BULLETIN 777-78A0066
ALERTALERT

### Page 40

MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
(h) Washer 315W1163-26 is optional to BACW10P458CD.
(i) Torque to 20-25 in-lb. Make sure other insulation blanket fasteners that were loosened to remove the
kept insulation blanket, are tightened.
(j) Clean the mating areas of the two insulation blankets. Apply BMS 5-109, Type 2, Class 2, adhesive. Refer
to SOPM 20-50-12, Type 94, as an accepted procedure to apply the adhesive. Make sure the insulation
blanket that is forward of this insulation blanket, overlaps it.
(k) Seal where shown in bold line. Seal edge common to both blankets. Seal new blanket edges common to
the latch beam. Seal gap that forms next to the two blankets and the forward stiffener. Seal gap that forms
at the lower end of the stiffeners. DO NOT SEAL edges of new blanket that are directly above the access
door. DO NOT SEAL edges of new blanket around the upper end of the stiffeners. Be careful to not plug
drain holes when the sealant is applied. Refer to SOPM 20-50-19 as an accepted procedure to seal the
blanket.
FIGURE 5: LEFT THRUST REVERSER - LATCH BEAM - INSULATION BLANKETS INSTALLATION
(SHEET 4 OF 4)
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BOEING SERVICE BULLETIN 777-78A0066
ALERTALERT

### Page 41 (OCR)

BOEING SERVICE BULLETIN 777-78A0066
ALERT  ALERT
This Figure applies only to: Group 2.
RIGHT LATCH BEAM
SEE A
NO. 5
LATCH
NO. 4
LATCH
NO. 3
LATCH
NO. 2
LATCH
SEE B
LATCH
ACCESS
FWD <  DOOR
RIGHT LATCH BEAM
1541688
FIGURE 6: RIGHT THRUST REVERSER - LATCH BEAM - INSULATION BLANKETS INSTALLATION
(SHEET 1 OF 4)
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Revision 2 April 08, 2010  777-78A0066
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Copyright © Unpublished Work - See page 1 for details.  41 of 46

### Page 42 (OCR)

BOEING SERVICE BULLETIN 777-78A0066
ALERT  ALERT
(3
FWD C
USE ADHESIVE
HERE BETWEEN
BLANKETS
RIGHT  LATCH BEAM
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 the right T/R half.
FIGURE 6: RIGHT THRUST REVERSER - LATCH BEAM - INSULATION BLANKETS INSTALLATION
(SHEET 2 OF 4)
Original Issue: June 05, 2008
Revision 2 April 08, 2010  BOEING PROPRIETARY -  777-78A0066
Copyright © Unpublished Work - See page 1 for details.  42 of 46

### Page 43

MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
(a)-BMS 10-11,TYPE 1PRIMERApply1
(b)1315W1257-2KIT - LATCH BEAM
BLANKET ASSY
Put / Hold2
(c)3-MARKApply3
1315W1257-2KIT - LATCH BEAM
BLANKET ASSY
Remove / Keep4
3-PIN, PILOTRemove / Keep5
(e) (f)3CB4017C3CRA12RSTUD, COMPOSITE
BASE
Install (New)6
(e)-BMS 5-109, TYPE 2,
CLASS 2
ADHESIVEApply
3BACB28AK04-030BUSHING, PLAINInstall (New)7
1315W1257-2KIT - LATCH BEAM
BLANKET ASSY
Install (New)8
(g)3BACW10P458CDWASHERInstall (New)9
(h)3BACN10JC3CNUTInstall (New)10
(i)1315W1654-32BLANKET ASSYInstall (New)11
3BACW10P392CCWASHER, PLAINInstall (New)12
(h)3BACS12GU3K15SCREW, CAPInstall (New)13
(j)-BMS 5-63, TYPE 1,
CLASS B-4
SEALANTApply14
(a) If the removal of the insulation material removed primer, touch up the latch beam as necessary. Refer to
SOPM 20-41-02 as an accepted procedure to apply primer.
(b) Position the latch beam insulation blanket in the latch beam to mark the locations for the studs. The part
name indicates a kit, but the part is supplied assembled
(c) Use the insulation blanket holes to locate and mark the location for the three studs that will be bonded to
the latch beam. Center a Pressure Application Fixture (PAF), supplied with a composite stud, over the
hole marks and mark the latch beam around the bottom of the PAF. This mark will be used to locate the
PAF and composite stud with adhesive. Refer to APPENDIX A for PAF description.
(d) Cut off the pilot pin from the stud base of the composite stud as close as possible to the stud base. Abrade
or scrape the stud base if necessary to give a flat base.
(e) Clean stud base and latch beam mating area. Apply BMS 5-109, Type 2, Class 2, adhesive. Put, hold,
and cure stud to the latch beam with a PAF. Refer to APPENDIX A and SOPM 20-50-12, Type 94, as
accepted procedures to install composite studs.
(f) Composite studs are supplied with a Pressure Application Fixture (PAF). Refer to APPENDIX A to see
how the PAF is used.
(g) Washer 315W1163-26 is optional to BACW10P458CD.
FIGURE 6: RIGHT THRUST REVERSER - LATCH BEAM - INSULATION BLANKETS INSTALLATION
(SHEET 3 OF 4)
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: June 05, 2008
777-78A0066Revision 2 April 08, 2010
43 of 46
BOEING SERVICE BULLETIN 777-78A0066
ALERTALERT

### Page 44

MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
(h) Torque to 20-25 in-lb. Make sure that other insulation blanket fasteners that were loosened to remove
the kept insulation blanket, are tightened.
(i) Clean the mating areas of the two insulation blankets. Apply BMS 5-109, Type 2, Class 2, adhesive. Refer
to SOPM 20-50-12, Type 94 as an accepted procedure to install the adhesive. Make sure the insulation
blanket that is forward of this insulation blanket, overlaps it.
(j) Seal where shown in bold line. Seal edge common to both blankets. Seal new blanket edges common to
the latch beam. Seal gap that forms next to the two blankets and the forward stiffener. Seal gap that forms
at the lower end of the stiffeners. DO NOT SEAL edges of new blanket that are directly above the access
door. DO NOT SEAL edges of new blanket around the upper end of the stiffeners. Be careful to not plug
drain holes when the sealant is applied. Refer to SOPM 20-50-19 as an accepted procedure to seal the
blanket.
FIGURE 6: RIGHT THRUST REVERSER - LATCH BEAM - INSULATION BLANKETS INSTALLATION
(SHEET 4 OF 4)
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: June 05, 2008
777-78A0066Revision 2 April 08, 2010
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BOEING SERVICE BULLETIN 777-78A0066
ALERTALERT

### Page 45 (OCR)

BOEING SERVICE BULLETIN 777-78A0066
ALERT  ALERT
• PRESSURE APPLICATION
FIXTURE (PAF)
COMPOSITE STUD FIXTURE
→ PAF
(UNACTIVATED
POSITION)
- STEP 2
'RELEASE LINER
BOTTOM
OF PAF  STUD
STEP  BASE
LATCH BEAM WALL
STEP 5
DISCARD
PAF
(ACTIVATED
STEP 4  POSITION)
STEP 3
(P)  (P)  (P)
INSTALLED
COMPOSITE
STUD  1496442
LATCH BEAM WALL INSTALLATION SEQUENCE
Appendix A: COMPOSITE STUD - ADHESIVE BONDED INSTALLATION
(SHEET 1 OF 2)
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### Page 46

1. Each adhesive bonded composite stud has a Pressure Application Fixture (PAF) to aid in location and
installation. Refer to Steps 1 thru 5 in the illustration for installation.
2. Clean and prepare the base of the composite stud and the surface of the structure where the composite
stud is to be installed. Refer to Boeing Standard Operating Procedures Manual SOPM 20-50-12, Type 94
as an accepted procedure to install the composite stud, except do not remove the PAF to look for unwanted
adhesive before it has cured.
a. Apply a thin, equal coat of BMS 5-109 Type 2, Class 2, adhesive to the composite stud base and latch
beam area. Refer to step 1.
NOTE: Make sure base of composite stud is above the bottom of the PAF.
b. Remove the release liner ring to expose the pressure sensitive adhesive on the bottom of the PAF.
Refer to step 2.
c. Position the PAF centered to the area of the latch beam assembly where the composite stud is to be
installed.
d. Press down (P) around the outer edge of the PAF to bond the fixture to the structure. DO NOT apply
pressure to the center the fixture. Refer to step 3.
NOTE: Make sure that the base of the click bond stud is above the bottom of the PAF.
e. Press down (P) near the center of the fixture until a click is felt or heard. Refer to step 4.
NOTE: The above step will cause the base of the composite stud to come in contact with the structure
and apply pressure to the composite stud and will cause the adhesive to come out. No other
clamp pressure is necessary.
f. Allow adhesive to cure as given in SOPM 20-50-12, Type 94.
g. After adhesive cures, peel off and discard the PAF. Refer to step 5.
3. Look at the installation of the composite stud.
a. Make sure there is a continuous bead of adhesive all the way around the base of the composite stud.
b. Make sure that no cured adhesive is on the stud threads of the composite stud. Remove cured adhesive
from threads with Scotch-Brite or equivalent.
Appendix A: COMPOSITE STUD - ADHESIVE BONDED INSTALLATION
(SHEET 2 OF 2)
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
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777-78A0066Revision 2 April 08, 2010
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BOEING SERVICE BULLETIN 777-78A0066
ALERTALERT

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