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.

ECCN: 9E991

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Unpublished Work - All Rights Reserved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,

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2.0
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BOEING SERVICE BULLETIN 777-78A0066

ALERT ALERT

BLANK PAGE
Table of Contents

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

Summary ...................................................... 7

1. PLANNING INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11

A. Effectivity . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11

1. Airplanes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11

2. Spares Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 12

B. Concurrent Requirements . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 12

C. Reason . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 12

D. Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14

E. Compliance . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15

F. Approval . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15

G. Manpower . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15

H. Weight and Balance Changes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 16

I. Electrical Load Data . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 16

J. References . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17

1. Existing Data: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17

2. Data supplied with this Service Bulletin: . . . . . . . . . . . . . . . . . . . . . . . . . . . 17

3. Installation Drawings Used in the Preparation of this Service Bulletin: . . . . . . . . . . . 17

K. Publications Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17

L. Interchangeability and Intermixability of Parts . . . . . . . . . . . . . . . . . . . . . . . . . . . 17

2. MATERIAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19

A. Material - Price and Availability . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19

B. Industry Support Information . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19

C. Parts Necessary For Each Airplane . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19

1. Kits/Parts: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19

2. Parts and Materials Supplied by the Operator: . . . . . . . . . . . . . . . . . . . . . . . . 21

3. Parts Modified and Reidentified: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21

4. Parts Removed and Not Replaced: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21

D. Parts Necessary to Change Spares . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21

E. Special Tooling - Price and Availability . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 22

F. Special Tooling Necessary to do this Service Bulletin . . . . . . . . . . . . . . . . . . . . . . . 22

3. ACCOMPLISHMENT INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 23

A. GENERAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 23

B. WORK INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 23

FIGURE 1: THRUST REVERSER - LATCH BEAM - REMOVE AFT INSULATION BLANKET AND

INSULATION FOAM [Group 1] . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25

FIGURE 2: LEFT THRUST REVERSER - LATCH BEAM - INSULATION BLANKET INSTALLATION [Group

1] . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 27

FIGURE 3: RIGHT THRUST REVERSER - LATCH BEAM - INSULATION BLANKET INSTALLATION [Group

1] . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 31

FIGURE 4: THRUST REVERSER - LATCH BEAM - REMOVE INSULATION FOAM [Group 2] . . . . 35

FIGURE 5: LEFT THRUST REVERSER - LATCH BEAM - INSULATION BLANKETS INSTALLATION [Group

2] . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 37

FIGURE 6: RIGHT THRUST REVERSER - LATCH BEAM - INSULATION BLANKETS INSTALLATION

[Group 2] . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 41

Appendix A: COMPOSITE STUD - ADHESIVE BONDED INSTALLATION . . . . . . . . . . . . . . . . 45

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BOEING SERVICE BULLETIN 777-78A0066

ALERT ALERT
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BOEING SERVICE BULLETIN 777-78A0066

ALERT ALERT

BLANK PAGE
Commercial 

Airplanes 777

Service Bulletin

ALERT

Revision Transmittal Sheet 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 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

Original Issue: June 05, 2008

Revision 1: March 12, 2009

Revision 2: April 08, 2010

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BOEING SERVICE BULLETIN 777-78A0066

ALERT ALERT
Commercial 

Airplanes 777

Service Bulletin

ALERT

Summary 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.

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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BOEING SERVICE BULLETIN 777-78A0066

ALERT ALERT
MANPOWER

Group 1:

EACH ENGINE

Total Task Hours Elapsed Hours

7.50 7.50

Group 2:

EACH ENGINE

Total Task Hours Elapsed Hours

7.25 7.25

MATERIAL INFORMATION

Boeing Supplied Kits/Parts.

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

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ALERT ALERT
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BOEING SERVICE BULLETIN 777-78A0066

ALERT ALERT
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.

GROUP CONFIGURATION DESCRIPTION

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

Variable Number Group

WA076 - WA080 2

WA116 - WA119 2

WB001 - WB009 2

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Variable Number Group

WB010 - WB021 1

WB121 - WB122 2

WB123 - WB125 1

WB271 - WB273 1

WB276 - WB286 1

WB291 - WB302 1

WB306 - WB307 1

WB311 - WB313 2

WB314 - WB337 1

WB341 - WB342 1

WB371 - WB388 1

WB406 1

WB411 - WB413 1

WB476 1

WC241 1

WC281 1

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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BOEING SERVICE BULLETIN 777-78A0066

ALERT ALERT
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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BOEING SERVICE BULLETIN 777-78A0066

ALERT ALERT
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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BOEING SERVICE BULLETIN 777-78A0066

ALERT ALERT
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

Model Zone

777-200 415, 416, 425, 426

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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BOEING SERVICE BULLETIN 777-78A0066

ALERT ALERT
— Time to cure the materials

— Time to make the parts

— Time to find the tools.

Group 1:

Number of Per- Task Hours Elapsed Hours

sons

Task

Open Access 1 0.50 0.50

Figure 1 1 1.00 1.00

Figure 2 1 2.75 2.75

Figure 3 1 2.75 2.75

Close Access 1 0.50 0.50

TOTAL FOR EACH ENGINE 7.50 7.50

Group 2:

Number of Per- Task Hours Elapsed Hours

sons

Task

Open Access 1 0.50 0.50

Figure 4 1 0.75 0.75

Figure 5 1 2.75 2.75

Figure 6 1 2.75 2.75

Close Access 1 0.50 0.50

TOTAL FOR EACH ENGINE 7.25 7.25

H. Weight and Balance Changes

Group 1:

Change in Moment

(Pound-Inches)

Change in Weight

(Pounds)

Airplane

For Each Engine + 3.2 + 3431.7

Group 2:

Change in Moment

(Pound-Inches)

Change in Weight

(Pounds)

Airplane

For Each Engine + 4.0 Ibs + 4288.0 Ib-in

I. Electrical Load Data

Not changed.

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BOEING SERVICE BULLETIN 777-78A0066

ALERT ALERT
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

Publication Chapter-Section

777 Maintenance Manual 78-31

777 Illustrated Parts Catalog 78-31

Component Maintenance Manual 78-31

L. Interchangeability and Intermixability of Parts

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

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BOEING SERVICE BULLETIN 777-78A0066

ALERT ALERT
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BOEING SERVICE BULLETIN 777-78A0066

ALERT ALERT

BLANK PAGE
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)

Kit Number Name Date QTY

April 14, 10 30 $3,546

2008

Top Kit - GE90 Latch

Beam Insulation Blanket

005W3346-1

Group 2:

Unit Price thru

December 31,

2008

ROLT

(Weeks)

Kit Number Name Date QTY

Nov 06, 10 30 $5,253

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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BOEING SERVICE BULLETIN 777-78A0066

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

Figure Kit

Top Kit 2 3 5 6

005W3346-1 1 1 - -

005W3346-4 - - 1 1

Group 1:

KIT 005W3346-1

NOTES

Existing Part

Name Number

Figure

New Part Number

2 3

QTY

315W1163-26 4 3 WASHER

KIT - LATCH

BEAM BLANKET

ASSY

315W1257-1 1

KIT - LATCH

BEAM BLANKET

ASSY

315W1257-2 1

BACB28AK04-030 4 3 BUSHING, PLAIN

BACN10JC3C 4 3 NUT

STUD, COMPOSITE BASECB4017C3CRA12R 4 3

Group 2:

KIT 005W3346-4

NOTES

Existing Part

Name Number

Figure

New Part Number

5 6

QTY

KIT - LATCH

BEAM BLANKET

ASSY

315W1257-1 1

KIT - LATCH

BEAM BLANKET

ASSY

315W1257-2 1

315W1654-31 1 BLANKET ASSY

315W1654-32 1 BLANKET ASSY

BACB28AK04-030 4 3 BUSHING, PLAIN

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ALERT ALERT
Group 2:

KIT 005W3346-4

NOTES

Existing Part

Name Number

Figure

New Part Number

5 6

QTY

BACN10JC3C 4 3 NUT

BACS12GU3K15 3 3 SCREW, CAP

BACW10P392CC 3 3 WASHER, PLAIN

BACW10P458CD 4 3 WASHER

STUD, COMPOSITE BASECB4017C3CRA12R 4 3

2. Parts and Materials Supplied by the Operator:

Part Number/ Specification QTY Name Notes

BMS 10-11,TYPE 1 1 Pt PRIMER

BMS 5-109, TYPE 2, CLASS 2 1 Pt ADHESIVE

BMS 5-63, TYPE 1, CLASS B- 1 Pt SEALANT

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.

Part Number Name QTY

005W3346-1 Top Kit - GE90 Latch Beam Insulation Blanket 1(a)

1(a)

(b)

005W3346-4 Top Kit - GE90 Latch Beam Insulation Blanket

(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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BOEING SERVICE BULLETIN 777-78A0066

ALERT ALERT
E. Special Tooling - Price and Availability

None.

F. Special Tooling Necessary to do this Service Bulletin

No special tools or equipment are necessary to do the change in this service bulletin. But, maintenance

and overhaul tools in the manuals given in Paragraph 1.J., References, can be necessary. Examine

operator tool supply to make sure all necessary tools are available.

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BOEING SERVICE BULLETIN 777-78A0066

ALERT ALERT
3. ACCOMPLISHMENT INSTRUCTIONS

A. GENERAL INFORMATION

CAUTION: KEEP THE WORK AREA, WIRES AND ELECTRICAL BUNDLES CLEAN OF METAL

PARTICLES OR CONTAMINATION WHEN YOU USE TOOLS. UNWANTED MATERIAL,

METAL PARTICLES OR CONTAMINATION CAUGHT IN WIRE BUNDLES CAN CAUSE

DAMAGE TO THE BUNDLES. DAMAGED WIRE BUNDLES CAN CAUSE SPARKS OR

OTHER ELECTRICAL DAMAGE.

NOTE: 1. Manual titles are referred to by acronyms. Refer to Paragraph 1.J., References, for

definition of the acronyms.

2. Obey all of the warnings and cautions given in the specified manual sections.

3. Unless shown differently, these dimensions and tolerances are used:

— 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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BOEING SERVICE BULLETIN 777-78A0066

ALERT ALERT
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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BOEING SERVICE BULLETIN 777-78A0066

ALERT ALERT
This Figure applies only to: Group 1.

FIGURE 1: THRUST REVERSER - LATCH BEAM - REMOVE AFT INSULATION BLANKET AND INSULATION

FOAM

(SHEET 1 OF 2)

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BOEING SERVICE BULLETIN 777-78A0066

ALERT ALERT
The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY

numbers shown below are the number of parts necessary for both left and right T/R halves.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

1 Remove / Keep SCREW - 6

Remove / Keep WASHER - 6

BLANKET, INSULA- - 2 (a)

TION

2 Remove / Keep

3 Remove INSULATION - - (b)

4 Clean SCRAPED AREA - - (c)

(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

ALERT ALERT
This Figure applies only to: Group 1.

FIGURE 2: LEFT THRUST REVERSER - LATCH BEAM - INSULATION BLANKET INSTALLATION

(SHEET 1 OF 4)

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BOEING SERVICE BULLETIN 777-78A0066

ALERT ALERT
The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY

numbers shown below are the number of parts necessary for the left T/R half.

FIGURE 2: LEFT THRUST REVERSER - LATCH BEAM - INSULATION BLANKET INSTALLATION

(SHEET 2 OF 4)

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BOEING SERVICE BULLETIN 777-78A0066

ALERT ALERT
STEP TASK NAME IDENTIFICATION QTY MORE DATA

1 Apply PRIMER BMS 10-11,TYPE 1 - (a)

KIT - LATCH BEAM 315W1257-1 1 (b)

BLANKET ASSY

2 Put / Hold

3 Apply MARK - 3 (c)

KIT - LATCH BEAM 315W1257-1 1

BLANKET ASSY

4 Remove / Keep

5 Remove PIN, PILOT - 3 (d)

STUD, COMPOSITE CB4017C3CRA12R 4 (e) (f) (g)

BASE

6 Install (New)

BMS 5-109, TYPE 2, - (e)

CLASS 2

Apply ADHESIVE

7 Install (New) BUSHING, PLAIN BACB28AK04-030 4 (g)

KIT - LATCH BEAM 315W1257-1 1

BLANKET ASSY

8 Install (New)

9 Install (New) WASHER 315W1163-26 4 (g) (h)

10 Install (New) NUT BACN10JC3C 4 (g) (i)

BLANKET, INSULA- - 1 (j)

TION

11 Install (Kept)

12 Install (Kept) WASHER - 3

13 Install (Kept) SCREW - 3 (i)

BMS 5-63, TYPE 1, - (k)

CLASS B-4

14 Apply SEALANT

(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.

FIGURE 2: LEFT THRUST REVERSER - LATCH BEAM - INSULATION BLANKET INSTALLATION

(SHEET 3 OF 4)

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ALERT ALERT
STEP TASK NAME IDENTIFICATION QTY MORE DATA

(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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BOEING SERVICE BULLETIN 777-78A0066

ALERT ALERT
This Figure applies only to: Group 1.

FIGURE 3: RIGHT THRUST REVERSER - LATCH BEAM - INSULATION BLANKET INSTALLATION

(SHEET 1 OF 4)

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BOEING SERVICE BULLETIN 777-78A0066

ALERT ALERT
The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY

numbers shown below are the number of parts necessary for the rightft T/R half.

FIGURE 3: RIGHT THRUST REVERSER - LATCH BEAM - INSULATION BLANKET INSTALLATION

(SHEET 2 OF 4)

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BOEING SERVICE BULLETIN 777-78A0066

ALERT ALERT
STEP TASK NAME IDENTIFICATION QTY MORE DATA

1 Apply PRIMER BMS 10-11,TYPE 1 - (a)

KIT - LATCH BEAM 315W1257-2 1 (b)

BLANKET ASSY

2 Put / Hold

3 Apply MARK - 3 (c)

KIT - LATCH BEAM 315W1257-2 1

BLANKET ASSY

4 Remove / Keep

5 Remove / Keep PIN, PILOT - 3 (d)

STUD, COMPOSITE CB4017C3CRA12R 3 (e) (f)

BASE

6 Install (New)

BMS 5-109, TYPE 2, - (e)

CLASS 2

Apply ADHESIVE

7 Install (New) BUSHING, PLAIN BACB28AK04-030 3

KIT - LATCH BEAM 315W1257-2 1

BLANKET ASSY

8 Install (New)

9 Install (New) WASHER 315W1163-26 3 (g)

10 Install (New) NUT BACN10JC3C 3 (h)

BLANKET, INSULA- - 1 (i)

TION

11 Install (Kept)

12 Install (Kept) WASHER - 3

13 Install (Kept) SCREW - 3 (h)

BMS 5-63, TYPE 1, - (j)

CLASS B-4

14 Apply SEALANT

(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.

FIGURE 3: RIGHT THRUST REVERSER - LATCH BEAM - INSULATION BLANKET INSTALLATION

(SHEET 3 OF 4)

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BOEING SERVICE BULLETIN 777-78A0066

ALERT ALERT
STEP TASK NAME IDENTIFICATION QTY MORE DATA

(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)

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BOEING SERVICE BULLETIN 777-78A0066

ALERT ALERT
This Figure applies only to: Group 2.

FIGURE 4: THRUST REVERSER - LATCH BEAM - REMOVE INSULATION FOAM

(SHEET 1 OF 2)

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BOEING SERVICE BULLETIN 777-78A0066

ALERT ALERT
The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY

numbers shown below are the number of parts necessary for both the left and right T/R halves..

STEP TASK NAME IDENTIFICATION QTY MORE DATA

1 Remove INSULATION - - (a)

2 Clean SCRAPED AREA - - (b)

(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)

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BOEING SERVICE BULLETIN 777-78A0066

ALERT ALERT
This Figure applies only to: Group 2.

FIGURE 5: LEFT THRUST REVERSER - LATCH BEAM - INSULATION BLANKETS INSTALLATION

(SHEET 1 OF 4)

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37 of 46

BOEING SERVICE BULLETIN 777-78A0066

ALERT ALERT
The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY

numbers shown below are the number of parts necessary for the left T/R half.

FIGURE 5: LEFT THRUST REVERSER - LATCH BEAM - INSULATION BLANKETS INSTALLATION

(SHEET 2 OF 4)

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38 of 46

BOEING SERVICE BULLETIN 777-78A0066

ALERT ALERT
STEP TASK NAME IDENTIFICATION QTY MORE DATA

1 Apply PRIMER BMS 10-11,TYPE 1 - (a)

KIT - LATCH BEAM 315W1257-1 1 (b)

BLANKET ASSY

2 Put / Hold

3 Apply MARK - 3 (c)

KIT - LATCH BEAM 315W1257-1 1

BLANKET ASSY

4 Remove / Keep

5 Remove PIN, PILOT - 3 (d)

STUD, COMPOSITE CB4017C3CRA12R 4 (e) (f)

BASE

6 Install (New)

BMS 5-109, TYPE 2, - (e)

CLASS 2

Apply ADHESIVE

7 Install (New) BUSHING, PLAIN BACB28AK04-030 4 (g)

KIT - LATCH BEAM 315W1257-1 1

BLANKET ASSY

8 Install (New)

9 Install (New) WASHER BACW10P458CD 4 (g) (h)

10 Install (New) NUT BACN10JC3C 4 (g) (i)

11 Install (New) BLANKET ASSY 315W1654-31 1 (j)

12 Install (New) WASHER, PLAIN BACW10P392CC 3

13 Install (New) SCREW, CAP BACS12GU3K15 3 (i)

BMS 5-63, TYPE 1, - (k)

CLASS B-4

14 Apply SEALANT

(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)

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BOEING SERVICE BULLETIN 777-78A0066

ALERT ALERT
STEP TASK NAME IDENTIFICATION QTY MORE DATA

(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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ALERT ALERT
This Figure applies only to: Group 2.

FIGURE 6: RIGHT THRUST REVERSER - LATCH BEAM - INSULATION BLANKETS INSTALLATION

(SHEET 1 OF 4)

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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)

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STEP TASK NAME IDENTIFICATION QTY MORE DATA

1 Apply PRIMER BMS 10-11,TYPE 1 - (a)

KIT - LATCH BEAM 315W1257-2 1 (b)

BLANKET ASSY

2 Put / Hold

3 Apply MARK - 3 (c)

KIT - LATCH BEAM 315W1257-2 1

BLANKET ASSY

4 Remove / Keep

5 Remove / Keep PIN, PILOT - 3

STUD, COMPOSITE CB4017C3CRA12R 3 (e) (f)

BASE

6 Install (New)

BMS 5-109, TYPE 2, - (e)

CLASS 2

Apply ADHESIVE

7 Install (New) BUSHING, PLAIN BACB28AK04-030 3

KIT - LATCH BEAM 315W1257-2 1

BLANKET ASSY

8 Install (New)

9 Install (New) WASHER BACW10P458CD 3 (g)

10 Install (New) NUT BACN10JC3C 3 (h)

11 Install (New) BLANKET ASSY 315W1654-32 1 (i)

12 Install (New) WASHER, PLAIN BACW10P392CC 3

13 Install (New) SCREW, CAP BACS12GU3K15 3 (h)

BMS 5-63, TYPE 1, - (j)

CLASS B-4

14 Apply SEALANT

(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)

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STEP TASK NAME IDENTIFICATION QTY MORE DATA

(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)

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Appendix A: COMPOSITE STUD - ADHESIVE BONDED INSTALLATION

(SHEET 1 OF 2)

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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)

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ALERT ALERT