Commercial 

Airplanes 777

Service Bulletin

Number: 777-54-0030

Original Issue: May 27, 2014

Revision 1: September 30, 2015

ATA System: 5452

SUBJECT: NACELLES/PYLONS - Aft Fairing - Strut Aft Fairing Lower Spar Heat Shield Insulation

Blankets Replacement

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

CFR 300-774). 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 © 2014 Boeing.

Unpublished Work. All Rights Reserved.

Treatment of this document and its content is governed by contract with Boeing. Rights to use this document

are licensed on a per aircraft basis and such rights may not be transferable. For more information, contact The

Boeing Company.

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, KC-46, KDC-10, MD-10, MD-11, MD-80, MD-88, MD-90, P-8, Poseidon and

Boeing liveries 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.

Original Issue: May 27, 2014

Revision 1: September 30, 2015 777-54-0030

1 of 81

3.0
Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: May 27, 2014

Revision 1: September 30, 2015 777-54-0030

2 of 81

BOEING SERVICE BULLETIN 777-54-0030

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 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13

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

E. Compliance . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14

F. Approval . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14

G. Manpower . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14

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

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

J. References . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 16

1. Existing Data: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 16

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

M. Software Accomplishment Summary . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17

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

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

B. Industry Support Information . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20

C. Parts Necessary for Each Airplane . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20

1. Kits/Parts . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20

2. Parts and Materials Supplied by the Operator . . . . . . . . . . . . . . . . . . . . . . . . 23

3. Parts Modified and Reidentified . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 24

4. Parts Removed and Not Replaced . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 24

D. Parts Necessary to Change Spares . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 24

E. Special Tooling - Price and Availability . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 24

F. Special Tooling Necessary to do this Service Bulletin . . . . . . . . . . . . . . . . . . . . . . . 25

3. ACCOMPLISHMENT INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 27

A. GENERAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 27

B. WORK INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 28

FIGURE 1: LEFT STRUT - HEAT SHIELD INSULATION BLANKET REMOVAL . . . . . . . . . . . . 30

FIGURE 2: RIGHT STRUT - HEAT SHIELD INSULATION BLANKET REMOVAL . . . . . . . . . . . 36

FIGURE 3: LEFT STRUT - VELCRO STRIPS REPLACEMENT . . . . . . . . . . . . . . . . . . . . . 42

FIGURE 4: RIGHT STRUT - VELCRO STRIPS REPLACEMENT . . . . . . . . . . . . . . . . . . . . 45

FIGURE 5: LEFT STRUT - DRAIN SUMP REPLACEMENT [Group 1] . . . . . . . . . . . . . . . . . . 48

FIGURE 6: RIGHT STRUT - DRAIN SUMP REPLACEMENT [Group 1] . . . . . . . . . . . . . . . . . 56

FIGURE 7: LEFT STRUT - HEAT SHIELD INSULATION BLANKET INSTALLATION . . . . . . . . . 64

FIGURE 8: RIGHT STRUT - HEAT SHIELD INSULATION BLANKET INSTALLATION . . . . . . . . . 72

APPENDIX A: MASTER FASTENER CODE TABLE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 80

APPENDIX B: PART DEMAND INTENT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 81

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: May 27, 2014

Revision 1: September 30, 2015 777-54-0030

3 of 81

BOEING SERVICE BULLETIN 777-54-0030
Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: May 27, 2014

Revision 1: September 30, 2015 777-54-0030

4 of 81

BOEING SERVICE BULLETIN 777-54-0030

BLANK PAGE
Commercial 

Airplanes 777

Service Bulletin

Revision Transmittal Sheet Number: 777-54-0030

Original Issue: May 27, 2014

Revision 1: September 30, 2015

ATA System: 5452

SUBJECT: NACELLES/PYLONS - Aft Fairing - Strut Aft Fairing Lower Spar Heat Shield Insulation

Blankets Replacement

This revision includes all pages of the service bulletin.

COMPLIANCE INFORMATION RELATED TO THIS REVISION

Federal Aviation Administration (FAA) Notice of Proposed Rule Making NPRM 2014-NM-178-AD is related to

this service bulletin.

Effects of this Revision on airplanes on which Original Issue was previously done: None.

REASON FOR REVISION

This revision is sent to change access instructions, update illustrations and revision level of the concurrent

requirement.

The data given in Information Notice 777-54-0030 IN 01 is included in this revision.

These sections were changed:

1. In Summary, Compliance, added NPRM reference.

2. In Summary, Material Information, added Boeing Supplied Kits/Parts ordering information request and

information for Operator Supplied Kits/Parts.

3. In Summary Figure, changed the locator illustration.

4. In Paragraph 1.B., Concurrent Requirements, added a new revision to an existing bulletin reference.

5. In Paragraph 1.C., Reason, added reason for revision and included statement about Information Notice.

6. In Paragraph 1.D., Description, added information for effects of this revision.

7. In Paragraph 1.E., Compliance, added NPRM reference.

8. In Paragraph 1.G., Manpower, updated task-hours.

9. In Paragraph 1.J.1., Existing Data, updated the reference list.

10. In Paragraph 1.L., Interchangeability and Intermixability of Parts, added reference for part

interchangeability and intermixability.

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: May 27, 2014

Revision 1: September 30, 2015 777-54-0030

5 of 81
11. In Paragraph 2.A., Material - Price and Availability, added reference to Boeing Supplied Kits/Parts

survey.

12. In Paragraph 2.C.1., Kits/Parts, added of part interchangeability and intermixability information.

13. In Paragraph 2.C.2., Parts and Materials Supplied by the Operator, added new operator supplied parts.

14. In Paragraph 3.B., Work Instructions, added access doors.

15. In FIGURE 1, changed access instructions and updated illustrations.

16. In FIGURE 2, changed access instructions and updated illustrations.

17. In FIGURE 3, changed engine locator illustration.

18. In FIGURE 4, changed engine locator illustration.

19. In FIGURE 5, changed access instructions and updated illustrations.

20. In FIGURE 6, changed access instructions and updated illustrations.

21. In FIGURE 7, changed instructions to restore access to the aircraft and updated illustrations.

22. In FIGURE 8, changed instructions to restore access to the aircraft and updated illustrations.

23. In APPENDIX A, added a new fastener code.

24. Added APPENDIX B, PART DEMAND INTENT, for Service Bulletin kit planning information.

Vertical lines are put on the left edge of each page, except in Paragraph 1.A., Effectivity and format changes,

to show the location of all content changes.

Pages with no vertical lines have no changes.

REVISION HISTORY

Original Issue: May 27, 2014

Revision 1: September 30, 2015

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: May 27, 2014

Revision 1: September 30, 2015 777-54-0030

6 of 81

BOEING SERVICE BULLETIN 777-54-0030
Commercial 

Airplanes 777

Service Bulletin

Summary Number: 777-54-0030

Original Issue: May 27, 2014

Revision 1: September 30, 2015

ATA System: 5452

SUBJECT: NACELLES/PYLONS - Aft Fairing - Strut Aft Fairing Lower Spar Heat Shield Insulation

Blankets Replacement

CONCURRENT REQUIREMENTS

Refer to Paragraph 1.B., Concurrent Requirements.

BACKGROUND

Accomplishment of this service bulletin will increase the thermal capability and improve the durability of the strut

aft fairing lower spar heat shield insulation blankets. Airflow into the cavity between the strut and strut aft fairing

heat shield is forced upon the forward blanket face and through the heat shield cavity, which results in accelerated

wear damage to the heat shield insulation blankets. Wear damage to insulation blankets could lead to damage

of the aft fairing lower spar web, which could result in unscheduled airplane maintenance and downtime for

repair.

Multiple operators have reported multiple cases of damage to strut aft fairing high temperature seals and heat

shield insulation blankets. Boeing performed a root cause evaluation and found that continuous exposure to

turbulent air can cause a degradation of the front face of the #1 heat shield insulation blanket and heat shield

primary seal. The degradation exposes the strut aft fairing lower spar web structure and heat shield insulation

blankets to high temperature air. New insulation blankets will provide improved durability and thermal protection.

The new design of the insulation blankets includes changes to the insulation material that improved the insulation

blankets to be resistant to higher temperatures and higher velocity air. The #1 heat shield insulation blanket

nose piece material was changed from silicone and quartz to nextel fabric, which demonstrates better performance

to resist damage from turbulent air during testing. In addition to the changes to the insulation blankets, a Nitronic

60 rub strip will be added to the seal depressor. The Nitronic 60 rub strip has improved friction characteristics

that allow for free movement and reduces wear damage to the primary seal.

This service bulletin provides instructions to replace heat shield insulation blankets and install Nitronic 60 rub

strips. Due to the new configuration of the insulation blankets, some airplanes will need new aft fairing lower

spar web drain sumps when replacing insulation blankets. Replacement of the insulation blankets will reduce

blanket wear damage due to turbulent airflow. Installation of the rub strip will provide better seal compression

and wear resistance to extend the life of the strut aft fairing lower spar primary seal.

Incorporation of the changes in accordance with this service bulletin, and a final one time inspection and corrective

actions in accordance with Service Bulletin (SB) 777-54A0031 is terminating action to the repeat inspections in

accordance with SB 777-54A0031. The Federal Aviation Administration (FAA) will possibly release an

Airworthiness Directive related to SB 777-54A0031.

Boeing Fleet Team Digest (FTD) 777 FTD 54-11003 is related to this service bulletin.

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: May 27, 2014

Revision 1: September 30, 2015 777-54-0030

7 of 81
Boeing Service Related Problem (SRP) 777-SRP-54-0137 is related to this service bulletin.

This table is provided to operators for planning purposes only. Refer to the applicable sections for more

information.

Planning Data Affected Reference

Spares Affected No Paragraph 1.A.2., Spares Affected

Paragraph 1.E., Compliance and Paragraph

1.F., Approval

AD Related Yes

Weight and Balance Change Yes Paragraph 1.H., Weight and Balance Changes

Electrical Load Changed No Paragraph 1.I., Electrical Load Data

Publications Affected Yes Paragraph 1.K., Publications Affected

Airplane Flight Operations Affected (Flight Crew No Paragraph 1.K., Publications Affected

Operations Manual and/or FAA Approved Airplane Flight Manual)

Kits/Parts Required Yes Paragraph 2.C.1., Kits/Parts

Paragraph 2.C.2., Parts and Materials Supplied

by the Operator

Operator Supplied Parts/Material Yes

Paragraph 2.F., Special Tooling Necessary to

do this Service Bulletin

Special Tooling Required No

ACTION (PRR 62777-92S)

Group 1:

Get access to the upper and lower aft fairing structure. Replace insulation blankets, drain sump, and velcro.

Install new rub strips to seal depressor. Close access to the upper and lower aft fairing structure.

Group 2:

Get access to the upper and lower aft fairing structure. Replace insulation blankets and velcro. Install new rub

strips to seal depressor. Close access to the upper and lower aft fairing structure.

EFFECTIVITY

777-200, -300 Airplanes with Rolls Royce Engines. Refer to Paragraph 1.A.1., Airplanes, for the list of affected

airplanes.

COMPLIANCE

Federal Aviation Administration (FAA) Notice of Proposed Rule Making NPRM 2014-NM-178-AD is related to

this service bulletin.

No compliance time is given.

Boeing recommends this service bulletin be done to introduce improvements.

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: May 27, 2014

Revision 1: September 30, 2015 777-54-0030

8 of 81

BOEING SERVICE BULLETIN 777-54-0030
INDUSTRY SUPPORT INFORMATION

Boeing warranty remedies are available for airplanes in warranty as of June 8, 2011. Please refer to Paragraph

2.B., Industry Support Information. The warranty remedies will expire eight years from the original issue date of

this service bulletin.

MANPOWER

Refer to Paragraph 1.G., Manpower.

MATERIAL INFORMATION

Boeing Supplied Kits/Parts.

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

Operators are encouraged to complete the survey provided in APPENDIX B of this service bulletin to help Boeing

predict the quantity and timing of the Boeing Supplied Kits/Parts.

Operator Supplied Parts/Materials.

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

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: May 27, 2014

Revision 1: September 30, 2015 777-54-0030

9 of 81

BOEING SERVICE BULLETIN 777-54-0030
Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: May 27, 2014

Revision 1: September 30, 2015 777-54-0030

10 of 81

BOEING SERVICE BULLETIN 777-54-0030
Commercial 

Airplanes 777

Service Bulletin

Number: 777-54-0030

Original Issue: May 27, 2014

Revision 1: September 30, 2015

ATA System: 5452

SUBJECT: NACELLES/PYLONS - Aft Fairing - Strut Aft Fairing Lower Spar Heat Shield Insulation

Blankets Replacement

1. PLANNING INFORMATION

A. Effectivity

1. Airplanes

This service bulletin is applicable to 777-200 and 777-300 Airplanes with Rolls Royce engines,

line numbers 1-796 in 2 Group(s). The Variable Numbers and Group Information for the applicable

airplanes is given below. An equivalent change is on subsequent production airplanes. Refer to

PRR 62777-92S for data about this change.

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

Serial Number data.

GROUP CONFIGURATION DESCRIPTION

777-200, 777-300 Airplanes with Rolls Royce Engines, line number

14-126, delivered with Drain Sump Assembly, Part Number

313W5816-1

1 -

777-200, 777-300 Airplanes with Rolls Royce Engines, line number

1, 128 through 796, delivered with Drain Sump Assembly, Part

Number 313W5816-5 or 313W5816-7

2 -

Airplane Models:

777-200, 777-300

Variable Number Group

WA001 2

WA086 - WA093 1

WA101 - WA104 1

WA196 - WA198 1

WB031 - WB046 2

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: May 27, 2014

Revision 1: September 30, 2015 777-54-0030

11 of 81
Variable Number Group

WB101 - WB104 1

WB105 - WB106 2

WB161 - WB165 1

WB166 - WB177 2

WB181 - WB186 1

WB187 - WB194 2

WB201 - WB215 2

WB231 - WB247 2

WB416 - WB439 2

WB446 - WB453 2

WB501 - WB503 1

WB504 - WB512 2

WB601 - WB606 2

WB611 - WB622 2

WB631 - WB638 2

WB646 - WB649 2

WC051 - WC073 2

WC101 - WC104 2

WC456 - WC459 2

WC486 - WC493 2

WC531 - WC536 2

WC566 - WC567 2

WC571 - WC574 2

2. Spares Affected

None.

B. Concurrent Requirements

The service bulletin listed below must be done before or at the same time as this service bulletin:

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: May 27, 2014

Revision 1: September 30, 2015 777-54-0030

12 of 81

BOEING SERVICE BULLETIN 777-54-0030
Company Service Bulletin Description

Inspects the strut aft fairing lower spar web

structure and heat shield primary seal for

heat damage. Corrective actions for inspections include replacement of damaged parts

and repeat inspections. Accomplishment of

Service Bulletin (SB) 777-54-0030, at the

same time as SB 777-54A0031, is terminating action to the repeat inspections in accordance with SB 777-54A0031.

The Boeing Compa- 777-54A0031 Original Issue or Revision 1

ny

C. Reason

Accomplishment of this service bulletin will increase the thermal capability and improve the durability

of the strut aft fairing lower spar heat shield insulation blankets. Airflow into the cavity between the strut

and strut aft fairing heat shield is forced upon the forward blanket face and through the heat shield

cavity, which results in accelerated wear damage to the heat shield insulation blankets. Wear damage

to insulation blankets could lead to damage of the aft fairing lower spar web, which could result in

unscheduled airplane maintenance and downtime for repair.

Multiple operators have reported multiple cases of damage to strut aft fairing high temperature seals

and heat shield insulation blankets. Boeing performed a root cause evaluation and found that continuous

exposure to turbulent air can cause a degradation of the front face of the #1 heat shield insulation

blanket and heat shield primary seal. The degradation exposes the strut aft fairing lower spar web

structure and heat shield insulation blankets to high temperature air. New insulation blankets will provide

improved durability and thermal protection.

The new design of the insulation blankets includes changes to the insulation material that improved

the insulation blankets to be resistant to higher temperatures and higher velocity air. The #1 heat shield

insulation blanket nose piece material was changed from silicone and quartz to nextel fabric, which

demonstrates better performance to resist damage from turbulent air during testing. In addition to the

changes to the insulation blankets, a Nitronic 60 rub strip will be added to the seal depressor. The

Nitronic 60 rub strip has improved friction characteristics that allow for free movement and reduces

wear damage to the primary seal.

This service bulletin provides instructions to replace heat shield insulation blankets and install Nitronic

60 rub strips. Due to the new configuration of the insulation blankets, some airplanes will need new aft

fairing lower spar web drain sumps when replacing insulation blankets. Replacement of the insulation

blankets will reduce blanket wear damage due to turbulent airflow. Installation of the rub strip will provide

better seal compression and wear resistance to extend the life of the strut aft fairing lower spar primary

seal.

Incorporation of the changes in accordance with this service bulletin, and a final one time inspection

and corrective actions in accordance with Service Bulletin (SB) 777-54A0031 is terminating action to

the repeat inspections in accordance with SB 777-54A0031. The Federal Aviation Administration (FAA)

will possibly release an Airworthiness Directive related to SB 777-54A0031.

Boeing Fleet Team Digest (FTD) 777 FTD 54-11003 is related to this service bulletin.

Boeing Service Related Problem (SRP) 777-SRP-54-0137 is related to this service bulletin.

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: May 27, 2014

Revision 1: September 30, 2015 777-54-0030

13 of 81

BOEING SERVICE BULLETIN 777-54-0030
Revision 1 is sent to change access instructions, update illustrations and revision level of the concurrent

requirement.

The data given in Information Notice 777-54-0030 IN 01 is included in this revision.

D. Description

Group 1:

Get access to the upper and lower aft fairing structure. Replace insulation blankets, drain sump, and

velcro. Install new rub strips to seal depressor. Close access to the upper and lower aft fairing structure.

Group 2:

Get access to the upper and lower aft fairing structure. Replace insulation blankets and velcro. Install

new rub strips to seal depressor. Close access to the upper and lower aft fairing structure.

Effects of Revision 1 on airplanes on which Original Issue was previously done: None

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

Affected Maintenance Zones

Model Zone

777-200, 777-300 434, 444

E. Compliance

Federal Aviation Administration (FAA) Notice of Proposed Rule Making NPRM 2014-NM-178-AD is

related to this service bulletin.

No compliance time is given.

Boeing recommends this service bulletin be done to introduce improvements.

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 replacement for each airplane.

This estimate is for direct labor only, done by an experienced crew. Adjust the estimate with operator

task hour data if necessary. The estimate does not include lost time. These are some examples of lost

time:

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: May 27, 2014

Revision 1: September 30, 2015 777-54-0030

14 of 81

BOEING SERVICE BULLETIN 777-54-0030
• Time to adjust to the workplace

• Time to schedule the work

• Time to inspect the work

• Time to cure the materials

• Time to make the parts

• Time to find the tools.

Group 1:

Task Number of Persons Task Hours Elapsed Hours

Open Access 2 5.00 2.50

Remove

...Left Strut, Blankets 4 27.00 6.75

- FIGURE 1

...Right Strut, Blan- 4 27.00 6.75

kets - FIGURE 2

Replace

...Left Strut, Velcro - 2 6.50 3.25

FIGURE 3

...Right Strut, Velcro 2 6.50 3.25

- FIGURE 4

Replace

...Left Strut, Drain 2 7.00 3.50

Sump - FIGURE 5

...Right Strut, Drain 2 7.00 3.50

Sump - FIGURE 6

Install

...Left Strut, Blankets 4 31.00 7.75

- FIGURE 7

...Right Strut, Blan- 4 31.00 7.75

kets - FIGURE 8

Test 2 4.00 2.00

Close Access 2 5.00 2.50

TOTAL FOR EACH AIRPLANE 157.00 49.50

Group 2:

Task Number of Persons Task Hours Elapsed Hours

Open Access 2 5.00 2.50

Remove

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: May 27, 2014

Revision 1: September 30, 2015 777-54-0030

15 of 81

BOEING SERVICE BULLETIN 777-54-0030
Group 2:

Task Number of Persons Task Hours Elapsed Hours

...Left Strut, Blankets 4 27.00 6.75

- FIGURE 1

...Right Strut, Blan- 4 27.00 6.75

kets - FIGURE 2

Replace

...Left Strut, Velcro - 2 6.50 3.25

FIGURE 3

...Right Strut, Velcro 2 6.50 3.25

- FIGURE 4

Install

...Left Strut, Blankets 4 31.00 7.75

- FIGURE 7

...Right Strut, Blan- 4 31.00 7.75

kets - FIGURE 8

Close Access 2 5.00 2.50

TOTAL FOR EACH AIRPLANE 139.00 40.50

H. Weight and Balance Changes

Change in Moment

(Pound-Inches)

Change in Weight

Airplane (Pounds)

All + 30.8 + 36806.0

I. Electrical Load Data

Not changed.

J. References

1. Existing Data:

a. Engineering Change Memo PRR 62777-92S

b. Boeing Service Bulletin 777-54-0030, 777-54A0031

c. Boeing Service Letter 777-SL-00-007

d. Boeing Service Related Problem (SRP) 777-SRP-54-0137

e. Component Maintenance Manual (CMM) 54-52-17

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

2014-NM-178-AD

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: May 27, 2014

Revision 1: September 30, 2015 777-54-0030

16 of 81

BOEING SERVICE BULLETIN 777-54-0030
g. Service Bulletin Index D624W001

h. Standard Overhaul Practices Manual (SOPM) 20-41-02, 20-43-03, 20-50-01, 20-50-12,

20-50-19

i. 777 Aircraft Maintenance Manual (AMM) 06-43-00, 54-51-01, 54-54-01, 54-55-01

j. 777 Fleet Team Digest (FTD) 54-11003

2. Data Supplied with this Service Bulletin:

None.

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

Drawing Number Title

313W5820 Lower Heat Shield Instl - Aft Fairing

313W3410 Sealing Instl - Aft Fairing

313W5803 Drain Instl - Heat Shield, Aft Fairing

The table above lists applicable drawings used to prepare this service bulletin. The drawings are

not necessary to make the specified changes, and are not supplied with this service bulletin. The

drawings may not be applicable to all airplane configurations or operators.

K. Publications Affected

1. Publications:

Publication Chapter-Section

777 Aircraft Maintenance Manual 54-54

777 Illustrated Parts Catalog 54-54, 54-55

Component Maintenance Manual 54-52

2. Damage Tolerance Based Structural Inspections:

Boeing has evaluated the repairs and/or changes in this service bulletin for effects on Fatigue

Critical Structure (FCS) and for changes to Damage Tolerance Inspections (DTI) required in the

Maintenance Program. This service bulletin does not affect FCS, therefore DTIs are not necessary.

L. Interchangeability and Intermixability of Parts

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

information.

M. Software Accomplishment Summary

Not affected.

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: May 27, 2014

Revision 1: September 30, 2015 777-54-0030

17 of 81

BOEING SERVICE BULLETIN 777-54-0030
Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: May 27, 2014

Revision 1: September 30, 2015 777-54-0030

18 of 81

BOEING SERVICE BULLETIN 777-54-0030

BLANK PAGE
2. MATERIAL INFORMATION

A. Material - Price and Availability

Boeing can supply the kits shown in Paragraph 2.C., Parts Necessary for Each Airplane. Operators

are encouraged to share schedule requirements with Boeing for incorporation of the service bulletin.

The kits are subject to the terms and conditions of the Boeing standard purchase order acknowledgment.

Prices are in United States Dollars. Terms: Net 30 days.

Reference this service bulletin and submit your purchase order by one of these methods:

1. Order on-line via ATA Spec 2000 or The Boeing PART Page

2. Fax to (206) 662-7145

Group 1:

REFER TO THE BOEING PART PAGE ON MYBOEINGFLEET.COM OR CONTACT FIRST RESPONDER

AT FR@BOEING.COM FOR THE LATEST REORDER LEAD TIME (ROLT) AND PRICE INFORMATION

Unit Price as of

the Original Issue

date of this Service Bulletin (US

Dollars)

ROLT as of the

Original Issue

date of this Service Bulletin (Calendar Days)

Kit Number Name Date QTY

TOP KIT - RR STRUT May 27, 2015 10 390 $116,114.00

AFT FAIRING INSULATION BLANKET AND

DRAIN SUMP - REPLACEMENT

005W3563-1

Group 2:

REFER TO THE BOEING PART PAGE ON MYBOEINGFLEET.COM OR CONTACT FIRST RESPONDER

AT FR@BOEING.COM FOR THE LATEST REORDER LEAD TIME (ROLT) AND PRICE INFORMATION

Unit Price as of

the Original Issue

date of this Service Bulletin (US

Dollars)

ROLT as of the

Original Issue

date of this Service Bulletin (Calendar Days)

Kit Number Name Date QTY

TOP KIT - RR STRUT May 9, 2014 16 149 $92,879.00

AFT FAIRING INSULATION BLANKET - REPLACEMENT

005W3563-2

Operators are encouraged to complete the survey provided in APPENDIX B of this service bulletin to

help Boeing predict the quantity and timing of the Boeing Supplied Kits/Parts.

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: May 27, 2014

Revision 1: September 30, 2015 777-54-0030

19 of 81

BOEING SERVICE BULLETIN 777-54-0030
B. Industry Support Information

Boeing warranty remedies are available for 777 airplanes in warranty as of June 8, 2011. For task hour

reimbursement for airplanes in warranty as of that date, send a warranty claim to Boeing Fleet Support

Contracts - Warranty. The kits for airplanes in warranty as of that date will be supplied at no charge.

Send a purchase order for the kits to Boeing Material Management. Please refer to this service bulletin

number and reference the airplane variable numbers in your purchase order. The warranty remedies

will expire eight years from the original issue date of this service bulletin.

C. Parts Necessary for Each Airplane

1. Kits/Parts

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

NOTE: One top kit and the items shown in Paragraph 2.C.2., Parts and Materials Supplied by

the Operator, are necessary for each airplane. The Top Kit is divided into Figure kits for

each installation figure shown in the table below.

Figure Kit

Top Kit 3 4 5 6 7 8

005W3563-1 1 1 1 1 1 1

005W3563-2 1 1 - - 1 1

Group 1:

KIT 005W3563-1

Notes

Existing Part

Name Number

Figure

New Part Number

3 4 5 6 7 8

Qty

311W5585Y16 . . . . 1 1 RUB STRIP (b)

313W3410-10 . . 1 1 . . DRAIN SCREEN 313W5804-24 (a) (c)

313W5421-30 . . . . 1 1 BLANKET ASSY 313W5421-1 (a) (c)

313W5421-31 . . . . 1 1 BLANKET ASSY 313W5421-2 (a) (c)

313W5421-32 . . . . 1 1 BLANKET ASSY 313W5421-3 (a) (c)

313W5421-33 . . . . 1 1 BLANKET ASSY 313W5421-4 (a) (c)

313W5421-34 . . . . 1 1 BLANKET ASSY 313W5421-5 (a) (c)

313W5421-35 . . . . 1 1 BLANKET ASSY 313W5421-6 (a) (c)

313W5421-36 . . . . 1 1 BLANKET ASSY 313W5421-7 (a) (c)

313W5421-37 . . . . 1 1 BLANKET ASSY 313W5421-8 (a) (c)

313W5421-38 . . . . 1 1 BLANKET ASSY 313W5421-9 (a) (c)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: May 27, 2014

Revision 1: September 30, 2015 777-54-0030

20 of 81

BOEING SERVICE BULLETIN 777-54-0030
Group 1:

KIT 005W3563-1

Notes

Existing Part

Name Number

Figure

New Part Number

3 4 5 6 7 8

Qty

DRAIN TUBE AS- 313W5804-3 (a) (c)

SY

313W5804-46 . . 1 1 . .

DRAIN TUBE AS- 313W5804-2 (a) (c)

SY

313W5804-48 . . 1 1 . .

(a) (b)

(c)

DRAIN SUMP AS- 313W5816-1

SY

313W5816Y7 . . 1 1 . .

313W5820-54 4 4 . . . . VELCRO 313W5820-8 (a) (c)

313W5820-55 8 8 . . . . VELCRO 313W5820-9 (a) (c)

313W5820-56 2 2 . . . . VELCRO 313W5820-10 (a) (c)

313W5820-57 2 2 . . . . VELCRO 313W5820-11 (a) (c)

BACB30LM3-4 . . 2 2 . . BOLT, HEX HEAD

BACB30LM3-5 . . 2 2 . . BOLT

BOLT, 100 DEG

HEX DR

BACB30NW6K3X . . 8 8 . .

BOLT, 100 DEG

HEX DR

BACB30NW8K5X . . 2 2 . .

BOLT, 100 DEG

HEX DR

BACB30NW8K6X . . 2 2 . .

BOLT, PROTRUDING HDBACB30NX6K3X . . 10 10 . .

BOLT, PROTRUDING HDBACB30NX6K4X . . 3 3 . .

BACC30BH6 . . 10 10 . . COLLAR

BACC30M6 . . 8 8 . . COLLAR

BACC30M8 . . 2 2 . . COLLAR

BACN11Z3CK . . 4 4 . . NUT

RIVET, UNIVERSAL HDBACR15BB7D7C . . 7 7 . .

BACR15CE5M5 . . . . 24 24 RIVET, 100 DEG

BACS12CK3U7 . . 3 3 . . SCREW

BACW10BP3ACU . . 4 4 . . WASHER

NAS1149C0332R . . 7 7 . . WASHER

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: May 27, 2014

Revision 1: September 30, 2015 777-54-0030

21 of 81

BOEING SERVICE BULLETIN 777-54-0030
Group 1:

KIT 005W3563-1

Notes

Existing Part

Name Number

Figure

New Part Number

3 4 5 6 7 8

Qty

(a) Discard the existing part.

(b) To make installation easier, some Boeing parts are sent in an 'interim' configuration. Boeing will identify

these interim configurations with a 'U', 'W' or 'Y' in place of the '-' (dash) in the part number. Interim parts

are changed to the 'dash' configuration when installed as given in the Accomplishment Instructions of this

service bulletin. Refer to Boeing Drawing 005W0900 "INTERIM PARTS - SPARES" and Boeing Service

Letter 777-SL-00-007 for more information.

(c) You cannot use the existing part to replace the new or changed part.

Group 2:

KIT 005W3563-2

Notes

Existing Part

Name Number

Figure

New Part Number

3 4 7 8

Qty

311W5585Y16 . . 1 1 RUB STRIP (b)

313W5421- (a) (c)

11,313W5421-21

313W5421-30 . . 1 1 BLANKET ASSY

313W5421- (a) (c)

12,313W5421-22

313W5421-31 . . 1 1 BLANKET ASSY

313W5421- (a) (c)

13,313W5421-23

313W5421-32 . . 1 1 BLANKET ASSY

313W5421- (a) (c)

14,313W5421-24

313W5421-33 . . 1 1 BLANKET ASSY

313W5421- (a) (c)

15,313W5421-25

313W5421-34 . . 1 1 BLANKET ASSY

313W5421- (a) (c)

16,313W5421-26

313W5421-35 . . 1 1 BLANKET ASSY

313W5421- (a) (c)

17,313W5421-27

313W5421-36 . . 1 1 BLANKET ASSY

313W5421- (a) (c)

18,313W5421-28

313W5421-37 . . 1 1 BLANKET ASSY

313W5421- (a) (c)

19,313W5421-29

313W5421-38 . . 1 1 BLANKET ASSY

313W5820-54 4 4 . . VELCRO 313W5820-19 (a) (c)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: May 27, 2014

Revision 1: September 30, 2015 777-54-0030

22 of 81

BOEING SERVICE BULLETIN 777-54-0030
Group 2:

KIT 005W3563-2

Notes

Existing Part

Name Number

Figure

New Part Number

3 4 7 8

Qty

313W5820-55 8 8 . . VELCRO 313W5820-20 (a) (c)

313W5820-56 2 2 . . VELCRO 313W5820-21 (a) (c)

313W5820-57 2 2 . . VELCRO 313W5820-22 (a) (c)

BACR15CE5M5 . . 24 24 RIVET, 100 DEG

(a) Discard the existing part.

(b) To make installation easier, some Boeing parts are sent in an 'interim' configuration. Boeing

will identify these interim configurations with a 'U', 'W' or 'Y' in place of the '-' (dash) in the

part number. Interim parts are changed to the 'dash' configuration when installed as given

in the Accomplishment Instructions of this service bulletin. Refer to Boeing Drawing 005W0900

"INTERIM PARTS - SPARES" and Boeing Service Letter 777-SL-00-007 for more information.

(c) You cannot use the existing part to replace the new or changed part.

2. Parts and Materials Supplied by the Operator

The following parts or materials are necessary to do the change in this service bulletin. Parts and

materials in the manuals given in Paragraph 1.J., References, can also be necessary. Examine

operator part and material supply to make sure all necessary parts and materials are available.

Group 1:

Part Number / QTY Name Notes

Specification

1 ADHESIVE (a)

quart

BMS 5-141

1 SEALANT (a)

quart

BMS 5-63 (BMS 5-

63, Type II, Class

B-4 Optional)

1 LEVELING COMPOUND (b)

quart

DC 3110 (RTV 60

optional)

1 cu- FOAM (c)

bic

feet

BMS 8-133,Type 1,

Class 2 Foam A-1,

Grade No 10 to 15

CHEMICAL CONVERSION COAT- (d)

ING

- 1 pint

1 PRIMER (a)

quart

BMS10-11, Type 1

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: May 27, 2014

Revision 1: September 30, 2015 777-54-0030

23 of 81

BOEING SERVICE BULLETIN 777-54-0030
Group 1:

Part Number / QTY Name Notes

Specification

BACB30VT6K3 4 BOLT, PROTRUDING HEAD (e)

BACC30BS6S 4 COLLAR (e)

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

for supplier data.

(b) Dow Corning, Corporate Center, PO Box 994, Midland, MI 48686-0994, United States

(c) Material only necessary if used to displace volume when applying leveling compound.

(d) Refer to SOPM 20-43-03 for a list of acceptable materials.

(e) This part is related to a bracket in the aft pan casting if additional access is needed.

Group 2:

Part Number / QTY Name Notes

Specification

1 ADHESIVE (a)

quart

BMS 5-141

BACB30VT6K3 4 BOLT, PROTRUDING HEAD (b)

BACC30BS6S 4 COLLAR (b)

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

for supplier data.

(b) This part is related to a bracket in the aft pan casting if additional access is needed.

3. Parts Modified and Reidentified

None.

4. Parts Removed and Not Replaced

None.

D. Parts Necessary to Change Spares

None.

E. Special Tooling - Price and Availability

None.

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: May 27, 2014

Revision 1: September 30, 2015 777-54-0030

24 of 81

BOEING SERVICE BULLETIN 777-54-0030
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.

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: May 27, 2014

Revision 1: September 30, 2015 777-54-0030

25 of 81

BOEING SERVICE BULLETIN 777-54-0030
Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: May 27, 2014

Revision 1: September 30, 2015 777-54-0030

26 of 81

BOEING SERVICE BULLETIN 777-54-0030

BLANK PAGE
3. ACCOMPLISHMENT INSTRUCTIONS

A. GENERAL INFORMATION

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

PARTICLES OR CONTAMINATION WHEN YOU USE TOOLS. UNWANTED MATERIAL,

METAL PARTICLES OR CONTAMINATION CAUGHT IN WIRE BUNDLES CAN CAUSE

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

OTHER ELECTRICAL DAMAGE.

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

definition of the acronyms.

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

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

– Linear dimensions are in inches

– Tolerance on linear dimensions, other than rivet and bolt edge margins, is plus

or minus 0.03 inch

– Tolerance on rivet and bolt edge margin is plus or minus 0.05 inch

– Angular tolerance is plus or minus 2 degrees

– Hole dimensions for standard solid rivets and fasteners are in Structural Repair

Manual (SRM) Chapter 51

– Torque Values:

— Values for structural fasteners are given in 777-200/ 777-300 Structural

Repair Manual, Chapter 51.

— Values for airframe maintenance tasks are included in Chapter 20 of 777

Airplane Maintenance Manual (AMM).

— Values for electrical maintenance tasks are included in Chapter 20 of

Standard Wiring Practices Manual (SWPM).

— Values for engine maintenance tasks are included in Chapter 70 of 777

Airplane Maintenance Manual (AMM).

— Non-standard torque values for maintenance tasks are included in the

applicable installation step.

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

SRM Chapter 51.

5. If the length of any fastener specified in this service bulletin does not meet installation

standards given in SRM Chapter 51, then a fastener of the same specification, or

an approved substitute, with a length which meets the installation standards given

in SRM Chapter 51 may be used. In addition, washers may be installed for fastener

grip length in accordance with SRM Chapter 51. Refer to SOPM 20-50-01 for alternate

full threaded fasteners (screws) needed for installation in this service bulletin.

6. These work instructions refer to procedures included in other Boeing documents.

When the words "refer to" are used and the operator has an accepted alternative

procedure, the accepted alternative procedure can be used. When the words "in

accordance with" are included in the instruction, the procedure in the Boeing document

must be used.

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: May 27, 2014

Revision 1: September 30, 2015 777-54-0030

27 of 81

BOEING SERVICE BULLETIN 777-54-0030
7. If it is necessary to remove more parts for access, you can remove those parts. If

you can get access without removing identified parts, it is not necessary to remove

all of the identified parts. Jacking and shoring limitations must be observed.

8. Where the work instructions include installation of a kept part, a new or serviceable

part with the same part number can be installed as an alternative to the kept part.

9. This service bulletin includes functional test procedures for the systems changed by

this service bulletin. More functional tests can possibly be necessary in accordance

with standard maintenance practices because of interruption to other airplane systems.

10. Some Boeing parts are supplied in a temporary configuration. Those parts are

identified with a 'U', 'W', or 'Y' in place of the '-' (dash) in the part number. It is

permitted to install parts identified with a 'U', 'W', or 'Y' as an alternative to the '-'

(dash) part number. Boeing Drawing 005W0900 contains more data.

11. If shading is used, shaded areas in Figures are to separate the non-critical and

non-authoritative information from the critical and authoritative information.

B. WORK INSTRUCTIONS

1. Prepare the strut for maintenance operations. Refer to 777 AMM 54-51-01 as an accepted

procedure.

2. Open the strut aft fairing side access doors shown in the table below. Refer to 777 AMM 06-43-00

for the location of these doors.

Left Wing Right Wing

Outboard Inboard Inboard Outboard

434BL 434BR 444BL 444BR

434CL 434CR 444CL 444CR

434DL 434DR 444DL 444DR

434EL 434ER 444EL 444ER

3. Remove heat shield pan casting and insulation blankets in accordance with the figures below:

Left Strut Right Strut

FIGURE 1 FIGURE 2

4. Replace Velcro strips in accordance with the figures below:

Left Strut Right Strut

FIGURE 3 FIGURE 4

5. Group 1:

Replace aft fairing web drain sump, drain screen, and drain tubes in accordance with the figures

below:

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: May 27, 2014

Revision 1: September 30, 2015 777-54-0030

28 of 81

BOEING SERVICE BULLETIN 777-54-0030
Left Strut Right Strut

FIGURE 5 FIGURE 6

6. Install rub strips, heat shield pan casting, and insulation blankets in accordance with the figures

below:

Left Strut Right Strut

FIGURE 7 FIGURE 8

7. Group 1:

Do a test to make sure the aft fairing drain tubes are not blocked, not leaking, and drains fluid

correctly. Refer to CMM 54-52-17, Repair 4-1 or 777 AMM 54-55-01 as an accepted procedure.

8. Close the strut aft fairing side access doors shown in the table below. Refer to 777 AMM 06-43-00

for the location of these doors.

Left Wing Right Wing

Outboard Inboard Inboard Outboard

434BL 434BR 444BL 444BR

434CL 434CR 444CL 444CR

434DL 434DR 444DL 444DR

434EL 434ER 444EL 444ER

9. Put the strut back to its usual condition. Refer to 777 AMM 54-51-01 as an accepted procedure.

10. Put the airplane back to a serviceable condition.

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: May 27, 2014

Revision 1: September 30, 2015 777-54-0030

29 of 81

BOEING SERVICE BULLETIN 777-54-0030
FIGURE 1: LEFT STRUT - HEAT SHIELD INSULATION BLANKET REMOVAL

(SHEET 1 OF 6)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: May 27, 2014

Revision 1 September 30, 2015 777-54-0030

30 of 81

BOEING SERVICE BULLETIN 777-54-0030
FIGURE 1: LEFT STRUT - HEAT SHIELD INSULATION BLANKET REMOVAL

(SHEET 2 OF 6)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: May 27, 2014

Revision 1 September 30, 2015 777-54-0030

31 of 81

BOEING SERVICE BULLETIN 777-54-0030
FIGURE 1: LEFT STRUT - HEAT SHIELD INSULATION BLANKET REMOVAL

(SHEET 3 OF 6)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: May 27, 2014

Revision 1 September 30, 2015 777-54-0030

32 of 81

BOEING SERVICE BULLETIN 777-54-0030
FIGURE 1: LEFT STRUT - HEAT SHIELD INSULATION BLANKET REMOVAL

(SHEET 4 OF 6)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: May 27, 2014

Revision 1 September 30, 2015 777-54-0030

33 of 81

BOEING SERVICE BULLETIN 777-54-0030
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 strut.

Step Task Name Identification Qty More Data

Make note of fastener location for Blanket Assembly installation.1 Remove / Keep FASTENER - 70

FIGURE 1: LEFT STRUT - HEAT SHIELD INSULATION BLANKET REMOVAL

(SHEET 5 OF 6)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: May 27, 2014

Revision 1 September 30, 2015 777-54-0030

34 of 81

BOEING SERVICE BULLETIN 777-54-0030
Step Task Name Identification Qty More Data

Refer to CMM 54-

52-17, Repair 4-1 or

777 AMM 54-54-01

as an accepted procedure.

2 Remove / Keep PAN CASTING - 5

Remove BLANKET ASSEMBLY - 7

3 Remove / Keep CLAMP - 2 (a)

4 Remove FASTENER - 2 (b)

Make note of fastener location for Blanket Assembly installation.5 Remove / Keep FASTENER - 14

Refer to CMM 54-

52-17, Repair 4-1 or

777 AMM 54-54-01

as an accepted procedure.

6 Remove / Keep PAN CASTING - 1

Remove BLANKET ASSEMBLY - 2

(a) If the clamp common to the upper drain tube cannot be removed due to limited access, remove the two

fasteners common to the bracket assembly and pan casting as given in the next step and do not do this

step.

(b) This step is provided as an alternative method to help remove the pan casting and prevent damage to

the insulation blanket and drain tubes.

This step is not necessary if both clamps common to the drain tubes can be removed in step 3. The fastener and clamp common to the upper drain tube may be difficult to remove due to limited access.

FIGURE 1: LEFT STRUT - HEAT SHIELD INSULATION BLANKET REMOVAL

(SHEET 6 OF 6)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: May 27, 2014

Revision 1 September 30, 2015 777-54-0030

35 of 81

BOEING SERVICE BULLETIN 777-54-0030
FIGURE 2: RIGHT STRUT - HEAT SHIELD INSULATION BLANKET REMOVAL

(SHEET 1 OF 6)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: May 27, 2014

Revision 1 September 30, 2015 777-54-0030

36 of 81

BOEING SERVICE BULLETIN 777-54-0030
FIGURE 2: RIGHT STRUT - HEAT SHIELD INSULATION BLANKET REMOVAL

(SHEET 2 OF 6)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: May 27, 2014

Revision 1 September 30, 2015 777-54-0030

37 of 81

BOEING SERVICE BULLETIN 777-54-0030
FIGURE 2: RIGHT STRUT - HEAT SHIELD INSULATION BLANKET REMOVAL

(SHEET 3 OF 6)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: May 27, 2014

Revision 1 September 30, 2015 777-54-0030

38 of 81

BOEING SERVICE BULLETIN 777-54-0030
FIGURE 2: RIGHT STRUT - HEAT SHIELD INSULATION BLANKET REMOVAL

(SHEET 4 OF 6)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: May 27, 2014

Revision 1 September 30, 2015 777-54-0030

39 of 81

BOEING SERVICE BULLETIN 777-54-0030
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 strut.

Step Task Name Identification Qty More Data

Make note of fastener location for Blanket Assembly installation.1 Remove / Keep FASTENER - 70

FIGURE 2: RIGHT STRUT - HEAT SHIELD INSULATION BLANKET REMOVAL

(SHEET 5 OF 6)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: May 27, 2014

Revision 1 September 30, 2015 777-54-0030

40 of 81

BOEING SERVICE BULLETIN 777-54-0030
Step Task Name Identification Qty More Data

Refer to CMM 54-

52-17, Repair 4-1 or

777 AMM 54-54-01

as an accepted procedure.

2 Remove / Keep PAN CASTING - 5

Remove BLANKET ASSEMBLY - 7

3 Remove / Keep CLAMP - 2 (a)

4 Remove FASTENER - 2 (b)

Make note of fastener location for Blanket Assembly installation.5 Remove / Keep FASTENER - 14

Refer to CMM 54-

52-17, Repair 4-1 or

777 AMM 54-54-01

as an accepted procedure.

6 Remove / Keep PAN CASTING - 1

Remove BLANKET ASSEMBLY - 2

(a) If the clamp common to the upper drain tube cannot be removed due to limited access, remove the two

fasteners common to the bracket assembly and pan casting as given in the next step and do not do this

step.

(b) This step is provided as an alternative method to help remove the pan casting and prevent damage to

the insulation blanket and drain tubes.

This step is not necessary if both clamps common to the drain tubes can be removed in step 3. The fastener and clamp common to the upper drain tube may be difficult to remove due to limited access.

FIGURE 2: RIGHT STRUT - HEAT SHIELD INSULATION BLANKET REMOVAL

(SHEET 6 OF 6)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: May 27, 2014

Revision 1 September 30, 2015 777-54-0030

41 of 81

BOEING SERVICE BULLETIN 777-54-0030
FIGURE 3: LEFT STRUT - VELCRO STRIPS REPLACEMENT

(SHEET 1 OF 3)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: May 27, 2014

Revision 1 September 30, 2015 777-54-0030

42 of 81

BOEING SERVICE BULLETIN 777-54-0030
FIGURE 3: LEFT STRUT - VELCRO STRIPS REPLACEMENT

(SHEET 2 OF 3)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: May 27, 2014

Revision 1 September 30, 2015 777-54-0030

43 of 81

BOEING SERVICE BULLETIN 777-54-0030
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 strut.

Step Task Name Identification Qty More Data

on the aft fairing

lower spare web at

all locations.

1 Remove VELCRO - -

2 Install (New) VELCRO 313W5820-54 4 (a)

3 Install (New) VELCRO 313W5820-55 8 (a)

4 Install (New) VELCRO 313W5820-56 2 (a)

5 Install (New) VELCRO 313W5820-57 2 (a)

(a) Clean and prepare aft fairing lower spar web before installing velcro. Install velcro by bonding velcro to

aft fairing lower spar web with BMS 5-141. Refer to SOPM 20-50-12, Type 111 as an accepted procedure.

FIGURE 3: LEFT STRUT - VELCRO STRIPS REPLACEMENT

(SHEET 3 OF 3)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: May 27, 2014

Revision 1 September 30, 2015 777-54-0030

44 of 81

BOEING SERVICE BULLETIN 777-54-0030
FIGURE 4: RIGHT STRUT - VELCRO STRIPS REPLACEMENT

(SHEET 1 OF 3)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: May 27, 2014

Revision 1 September 30, 2015 777-54-0030

45 of 81

BOEING SERVICE BULLETIN 777-54-0030
FIGURE 4: RIGHT STRUT - VELCRO STRIPS REPLACEMENT

(SHEET 2 OF 3)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: May 27, 2014

Revision 1 September 30, 2015 777-54-0030

46 of 81

BOEING SERVICE BULLETIN 777-54-0030
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 strut.

Step Task Name Identification Qty More Data

on the aft fairing

lower spare web at

all locations.

1 Remove VELCRO - -

2 Install (New) VELCRO 313W5820-54 4 (a)

3 Install (New) VELCRO 313W5820-55 8 (a)

4 Install (New) VELCRO 313W5820-56 2 (a)

5 Install (New) VELCRO 313W5820-57 2 (a)

(a) Clean and prepare aft fairing lower spar web before installing velcro. Install velcro by bonding velcro to

aft fairing lower spar web with BMS 5-141. Refer to SOPM 20-50-12, Type 111 as an accepted procedure.

FIGURE 4: RIGHT STRUT - VELCRO STRIPS REPLACEMENT

(SHEET 3 OF 3)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: May 27, 2014

Revision 1 September 30, 2015 777-54-0030

47 of 81

BOEING SERVICE BULLETIN 777-54-0030
This Figure applies only to: Group 1.

FIGURE 5: LEFT STRUT - DRAIN SUMP REPLACEMENT

(SHEET 1 OF 8)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: May 27, 2014

Revision 1 September 30, 2015 777-54-0030

48 of 81

BOEING SERVICE BULLETIN 777-54-0030
FIGURE 5: LEFT STRUT - DRAIN SUMP REPLACEMENT

(SHEET 2 OF 8)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: May 27, 2014

Revision 1 September 30, 2015 777-54-0030

49 of 81

BOEING SERVICE BULLETIN 777-54-0030
FIGURE 5: LEFT STRUT - DRAIN SUMP REPLACEMENT

(SHEET 3 OF 8)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: May 27, 2014

Revision 1 September 30, 2015 777-54-0030

50 of 81

BOEING SERVICE BULLETIN 777-54-0030
FIGURE 5: LEFT STRUT - DRAIN SUMP REPLACEMENT

(SHEET 4 OF 8)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: May 27, 2014

Revision 1 September 30, 2015 777-54-0030

51 of 81

BOEING SERVICE BULLETIN 777-54-0030
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 strut.

NOTE: If Drain Sump on Left Strut Aft Fairing Lower Spar Web was replaced with a Drain Sump Part Number

313W5816-5 or 313W5816-7 prior to incorporation of this service bulletin, then the intent of this Figure

has been accomplished.

Step Task Name Identification Qty More Data

1 Remove / Keep CLAMP - 3

2 Remove / Keep CLAMP - 2 (g)

Remove / Keep BRACKET ASSEMBLY - 1 (g)

3 Remove FASTENER - 3

Remove SCREEN ASSY 313W5804-24 1

4 Remove FASTENER - 4

Remove DRAIN TUBE ASSY 313W5804-2 1

5 Remove DRAIN TUBE ASSY 313W5804-3 1

6 Remove SEALANT - -

Remove FASTENER - 27

Remove / Keep STIFFENER - 1

Remove DRAIN SUMP 313W5816-1 1 (f)

7 Locate DRAIN SUMP ASSY 313W5816Y7 1

Locate STIFFENER - 1

on aft fairing heat

shield and stiffener

for drain sump assembly installation.

8 Locate FASTENER HOLE - 27

on drain sump assembly. (a)Drill FASTENER HOLE - 27

on aft fairing heat

shield and stiffener

for drain sump assembly installation.

9 Locate FASTENER HOLE - 6

on drain sump assembly. Fastener

hole size is 0.255

inch to 0.261 inch.

Drill FASTENER HOLE - 6

FIGURE 5: LEFT STRUT - DRAIN SUMP REPLACEMENT

(SHEET 5 OF 8)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: May 27, 2014

Revision 1 September 30, 2015 777-54-0030

52 of 81

BOEING SERVICE BULLETIN 777-54-0030
Step Task Name Identification Qty More Data

Not shown. Clean

and deburr fastener

holes.

DRAIN SUMP ASSEM- - 1

BLY AND STIFFENER

10 Remove / Keep

to all bare metal surfaces. Not shown.

Refer to SOPM 20-

43-03 as an accepted procedure.

CHEMICAL CONVER- - -

SION COATING

11 Apply

to all bare metal surfaces. Not shown.

Refer to SOPM 20-

41-02 as an accepted procedure.

Apply PRIMER BMS 10-11, TYPE 1 -

12 Install (New) DRAIN SUMP ASSY 313W5816Y7 1

Install (Kept) STIFFENER - 1

Install (New) FASTENER - 27 (a)

Fillet seal at interface of the drain

sump assembly and

the aft fairing frame,

stiffener, and

chords. (e)

13 Apply SEALANT BMS 5-63 -

14 Install (New) DRAIN TUBE ASSY 313W5804-46 1 (d)

Clean bottom inside

of drain sump assembly for leveling compound application.

Refer to SOPM 20-

50-19 as an accepted procedure.

15 Clean DRAIN SUMP ASSY 313W5816Y7 1

Refer to CMM 54-

52-17 as an accepted procedure. (b) (c)

DC 3110 (RTV 60 op- -

tional)

LEVELING COMPOUNDApply

16 Install (New) DRAIN TUBE ASSY 313W5804-48 1 (d)

Wet install by applying BMS 5-63. Refer

to SOPM 20-50-19,

Method 3 as an accepted procedure.

Install (New) BOLT BACB30LM3-5 2

Install (New) WASHER BACW10BP3ACU 2

FIGURE 5: LEFT STRUT - DRAIN SUMP REPLACEMENT

(SHEET 6 OF 8)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: May 27, 2014

Revision 1 September 30, 2015 777-54-0030

53 of 81

BOEING SERVICE BULLETIN 777-54-0030
Step Task Name Identification Qty More Data

Wet install by applying BMS 5-63. Refer

to SOPM 20-50-19,

Method 3 as an accepted procedure.

17 Install (New) BOLT, HEX HEAD BACB30LM3-4 2

Install (New) WASHER BACW10BP3ACU 2

18 Install (New) WASHER NAS1149C0332R 4

Install (New) NUT BACN11Z3CK 4

19 Install (New) DRAIN SCREEN 313W3410-10 1

Install (New) WASHER NAS1149C0332R 3

Install (New) SCREW BACS12CK3U7 3

Wet install clamp

fasteners using BMS

5-63.

20 Install (Kept) CLAMP - 3

21 Install (Kept) CLAMP - 2 (h)

Install (Kept) BRACKET ASSEMBLY - 1 (h)

(a) Refer to Fastener Code Table.

(b) Aft fairing structure must be oriented in aircraft ground attitude (looking FWD rotate clockwise 5.9 degrees

and 1.7 degrees nose up measured from SAF STA 46.35 to SAF STA 78.85) before leveling compound

can be applied. Aft fairing structure shall not be moved during working life of leveling compound. Apply

leveling compound until it meets the bottom of all drain holes and not block any drain tube openings or

passageways.

(c) An excessive amount of leveling compound is not recommended in one pour. The use of foam to displace

a large volume is optional, cut BMS 8-133,Type 1, Class 2 Foam A-1, Grade No 10 to 15, Rigid Foam to

suitable size where needed to minimize leveling compound usage. Coat bottom of foam with leveling

compound before installation to minimize trapped air, recommend securing foam by partially filling area

with leveling compound and allowing to gel before completing pour.

(d) Make sure drainage hole is clear and free of sealant.

(e) It is acceptable to fay surface seal between mating surfaces using BMS 5-63, Type II, Class B-4. Clean

and prime all surfaces prior to sealing. Refer to SOPM 20-50-19 as an accepted procedure.

(f) It is recommended to slide the drain sump forward and then up to remove the drain sump from the fairing.

Make sure not to damage the surrounding structure when removing the drain sump. Make sure to remove

any remaining sealant from the area where the drain sump was removed.

(g) If these parts are already removed, do not do this step. The bracket assembly may have been removed

from the pan casting for additional access. If the clamps need to be removed from the bracket, remove

and keep the clamps and the bracket.

(h) Do not do this step if the bracket is installed on the pan casting. If the bracket is installed on the pan

casting, these clamps will be installed later. Wet install clamp fasteners using BMS 5-63.

FIGURE 5: LEFT STRUT - DRAIN SUMP REPLACEMENT

(SHEET 7 OF 8)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: May 27, 2014

Revision 1 September 30, 2015 777-54-0030

54 of 81

BOEING SERVICE BULLETIN 777-54-0030
The codes shown below agree with the letter shown in the upper left corner of the fastener symbols in the figure.

A number in the lower right corner gives the grip length of the fastener. The QTY numbers shown below are the

number of fasteners necessary for this figure.

Code Name Identification Qty Hole Dia More Data

BOLT, PROTRUDING BACB30NX6K3X 7 0.200-0.203 (a)

HD

A

COLLAR BACC30BH6 7 -

BOLT, PROTRUDING BACB30NX6K3X 3 0.200-0.203 (a)

HD

B

BOLT, PROTRUDING BACB30NX6K4X 3 - (a)

HD

COLLAR BACC30BH6 3 -

Countersink 100 degrees.

(a)

BOLT, 100 DEG HEX BACB30NW6K3X 8 0.200-0.203

DR

C

COLLAR BACC30M6 8 -

Countersink 100 degrees.

(a)

BOLT, 100 DEG HEX BACB30NW8K5X 2 0.263-0.266

DR

D

Countersink 100 degrees.

(a)

BOLT, 100 DEG HEX BACB30NW8K6X 2 -

DR

COLLAR BACC30M8 2 -

RIVET, UNIVERSAL BACR15BB7D7C 7 0.221-0.233

HD

F

(a) Wet install by applying BMS 5-63 to threads and shank.

FIGURE 5: LEFT STRUT - DRAIN SUMP REPLACEMENT

(SHEET 8 OF 8)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: May 27, 2014

Revision 1 September 30, 2015 777-54-0030

55 of 81

BOEING SERVICE BULLETIN 777-54-0030
This Figure applies only to: Group 1.

FIGURE 6: RIGHT STRUT - DRAIN SUMP REPLACEMENT

(SHEET 1 OF 8)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: May 27, 2014

Revision 1 September 30, 2015 777-54-0030

56 of 81

BOEING SERVICE BULLETIN 777-54-0030
FIGURE 6: RIGHT STRUT - DRAIN SUMP REPLACEMENT

(SHEET 2 OF 8)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: May 27, 2014

Revision 1 September 30, 2015 777-54-0030

57 of 81

BOEING SERVICE BULLETIN 777-54-0030
FIGURE 6: RIGHT STRUT - DRAIN SUMP REPLACEMENT

(SHEET 3 OF 8)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: May 27, 2014

Revision 1 September 30, 2015 777-54-0030

58 of 81

BOEING SERVICE BULLETIN 777-54-0030
FIGURE 6: RIGHT STRUT - DRAIN SUMP REPLACEMENT

(SHEET 4 OF 8)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: May 27, 2014

Revision 1 September 30, 2015 777-54-0030

59 of 81

BOEING SERVICE BULLETIN 777-54-0030
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 strut.

NOTE: If Drain Sump on Right Strut Aft Fairing Lower Spar Web was replaced with a Drain Sump Part Number

313W5816-5 or 313W5816-7 prior to incorporation of this service bulletin, then the intent of this Figure

has been accomplished.

Step Task Name Identification Qty More Data

1 Remove / Keep CLAMP - 3

2 Remove / Keep CLAMP - 2 (g)

Remove / Keep BRACKET ASSEMBLY - 1 (g)

3 Remove FASTENER - 3

Remove SCREEN ASSY 313W5804-24 1

4 Remove FASTENER - 4

Remove DRAIN TUBE ASSY 313W5804-2 1

5 Remove DRAIN TUBE ASSY 313W5804-3 1

6 Remove SEALANT - -

Remove FASTENER - 27

Remove / Keep STIFFENER - 1

Remove DRAIN SUMP 313W5816-1 1 (f)

7 Locate DRAIN SUMP ASSY 313W5816Y7 1

Locate STIFFENER - 1

on aft fairing heat

shield and stiffener

for drain sump assembly installation.

8 Locate FASTENER HOLE - 27

on drain sump assembly. (a)Drill FASTENER HOLE - 27

on aft fairing heat

shield and stiffener

for drain sump assembly installation.

9 Locate FASTENER HOLE - 6

on drain sump assembly. Fastener

hole size is 0.255

inch to 0.261 inch.

Drill FASTENER HOLE - 6

FIGURE 6: RIGHT STRUT - DRAIN SUMP REPLACEMENT

(SHEET 5 OF 8)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: May 27, 2014

Revision 1 September 30, 2015 777-54-0030

60 of 81

BOEING SERVICE BULLETIN 777-54-0030
Step Task Name Identification Qty More Data

Not shown. Clean

and deburr fastener

holes.

DRAIN SUMP ASSEM- - 1

BLY AND STIFFENER

10 Remove / Keep

to all bare metal surfaces. Not shown.

Refer to SOPM 20-

43-03 as an accepted procedure.

CHEMICAL CONVER- - -

SION COATING

11 Apply

to all bare metal surfaces. Not shown.

Refer to SOPM 20-

41-02 as an accepted procedure.

Apply PRIMER BMS 10-11, TYPE 1 -

12 Install (New) DRAIN SUMP ASSY 313W5816Y7 1

Install (Kept) STIFFENER - 1

Install (New) FASTENER - 27 (a)

Fillet seal at interface of the drain

sump assembly and

the aft fairing frame,

stiffener, and

chords. (e)

13 Apply SEALANT BMS 5-63 -

14 Install (New) DRAIN TUBE ASSY 313W5804-46 1 (d)

Clean bottom inside

of drain sump assembly for leveling compound application.

Refer to SOPM 20-

50-19 as an accepted procedure.

15 Clean DRAIN SUMP ASSY 313W5816Y7 1

Refer to CMM 54-

52-17 as an accepted procedure. (b) (c)

DC 3110 (RTV 60 op- -

tional)

LEVELING COMPOUNDApply

16 Install (New) DRAIN TUBE ASSY 313W5804-48 1 (d)

Wet install by applying BMS 5-63. Refer

to SOPM 20-50-19,

Method 3 as an accepted procedure.

Install (New) BOLT BACB30LM3-5 2

Install (New) WASHER BACW10BP3ACU 2

FIGURE 6: RIGHT STRUT - DRAIN SUMP REPLACEMENT

(SHEET 6 OF 8)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: May 27, 2014

Revision 1 September 30, 2015 777-54-0030

61 of 81

BOEING SERVICE BULLETIN 777-54-0030
Step Task Name Identification Qty More Data

Wet install by applying BMS 5-63. Refer

to SOPM 20-50-19,

Method 3 as an accepted procedure.

17 Install (New) BOLT, HEX HEAD BACB30LM3-4 2

Install (New) WASHER BACW10BP3ACU 2

18 Install (New) WASHER NAS1149C0332R 4

Install (New) NUT BACN11Z3CK 4

19 Install (New) DRAIN SCREEN 313W3410-10 1

Install (New) WASHER NAS1149C0332R 3

Install (New) SCREW BACS12CK3U7 3

Wet install clamp

fasteners using BMS

5-63.

20 Install (Kept) CLAMP - 3

21 Install (Kept) CLAMP - 2 (h)

Install (Kept) BRACKET ASSEMBLY - 1 (h)

(a) Refer to Fastener Code Table.

(b) Aft fairing structure must be oriented in aircraft ground attitude (looking FWD rotate clockwise 5.9 degrees

and 1.7 degrees nose up measured from SAF STA 46.35 to SAF STA 78.85) before leveling compound

can be applied. Aft fairing structure shall not be moved during working life of leveling compound. Apply

leveling compound until it meets the bottom of all drain holes and not block any drain tube openings or

passageways.

(c) An excessive amount of leveling compound is not recommended in one pour. The use of foam to displace

a large volume is optional, cut BMS 8-133,Type 1, Class 2 Foam A-1, Grade No 10 to 15, Rigid Foam to

suitable size where needed to minimize leveling compound usage. Coat bottom of foam with leveling

compound before installation to minimize trapped air, recommend securing foam by partially filling area

with leveling compound and allowing to gel before completing pour.

(d) Make sure drainage hole is clear and free of sealant.

(e) It is acceptable to fay surface seal between mating surfaces using BMS 5-63, Type II, Class B-4. Clean

and prime all surfaces prior to sealing. Refer to SOPM 20-50-19 as an accepted procedure.

(f) It is recommended to slide the drain sump forward and then up to remove the drain sump from the fairing.

Make sure not to damage the surrounding structure when removing the drain sump. Make sure to remove

any remaining sealant from the area where the drain sump was removed.

(g) If these parts are already removed, do not do this step. The bracket assembly may have been removed

from the pan casting for additional access. If the clamps need to be removed from the bracket, remove

and keep the clamps and the bracket.

(h) Do not do this step if the bracket is installed on the pan casting. If the bracket is installed on the pan

casting, these clamps will be installed later. Wet install clamp fasteners using BMS 5-63.

FIGURE 6: RIGHT STRUT - DRAIN SUMP REPLACEMENT

(SHEET 7 OF 8)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: May 27, 2014

Revision 1 September 30, 2015 777-54-0030

62 of 81

BOEING SERVICE BULLETIN 777-54-0030
The codes shown below agree with the letter shown in the upper left corner of the fastener symbols in the figure.

A number in the lower right corner gives the grip length of the fastener. The QTY numbers shown below are the

number of fasteners necessary for this figure.

Code Name Identification Qty Hole Dia More Data

BOLT, PROTRUDING BACB30NX6K3X 7 0.200-0.203 (a)

HD

A

COLLAR BACC30BH6 7 -

BOLT, PROTRUDING BACB30NX6K3X 3 0.200-0.203 (a)

HD

B

BOLT, PROTRUDING BACB30NX6K4X 3 - (a)

HD

COLLAR BACC30BH6 3 -

Countersink 100 degrees.

(a)

BOLT, 100 DEG HEX BACB30NW6K3X 8 0.200-0.203

DR

C

COLLAR BACC30M6 8 -

Countersink 100 degrees.

(a)

BOLT, 100 DEG HEX BACB30NW8K5X 2 0.263-0.266

DR

D

Countersink 100 degrees.

(a)

BOLT, 100 DEG HEX BACB30NW8K6X 2 -

DR

COLLAR BACC30M8 2 -

RIVET, UNIVERSAL BACR15BB7D7C 7 0.221-0.233

HD

F

(a) Wet install by applying BMS 5-63 to threads and shank.

FIGURE 6: RIGHT STRUT - DRAIN SUMP REPLACEMENT

(SHEET 8 OF 8)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: May 27, 2014

Revision 1 September 30, 2015 777-54-0030

63 of 81

BOEING SERVICE BULLETIN 777-54-0030
FIGURE 7: LEFT STRUT - HEAT SHIELD INSULATION BLANKET INSTALLATION

(SHEET 1 OF 8)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: May 27, 2014

Revision 1 September 30, 2015 777-54-0030

64 of 81

BOEING SERVICE BULLETIN 777-54-0030
FIGURE 7: LEFT STRUT - HEAT SHIELD INSULATION BLANKET INSTALLATION

(SHEET 2 OF 8)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: May 27, 2014

Revision 1 September 30, 2015 777-54-0030

65 of 81

BOEING SERVICE BULLETIN 777-54-0030
FIGURE 7: LEFT STRUT - HEAT SHIELD INSULATION BLANKET INSTALLATION

(SHEET 3 OF 8)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: May 27, 2014

Revision 1 September 30, 2015 777-54-0030

66 of 81

BOEING SERVICE BULLETIN 777-54-0030
FIGURE 7: LEFT STRUT - HEAT SHIELD INSULATION BLANKET INSTALLATION

(SHEET 4 OF 8)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: May 27, 2014

Revision 1 September 30, 2015 777-54-0030

67 of 81

BOEING SERVICE BULLETIN 777-54-0030
FIGURE 7: LEFT STRUT - HEAT SHIELD INSULATION BLANKET INSTALLATION

(SHEET 5 OF 8)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: May 27, 2014

Revision 1 September 30, 2015 777-54-0030

68 of 81

BOEING SERVICE BULLETIN 777-54-0030
FIGURE 7: LEFT STRUT - HEAT SHIELD INSULATION BLANKET INSTALLATION

(SHEET 6 OF 8)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: May 27, 2014

Revision 1 September 30, 2015 777-54-0030

69 of 81

BOEING SERVICE BULLETIN 777-54-0030
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 strut.

Step Task Name Identification Qty More Data

1 Install (New) RUB STRIP 311W5585Y16 1

Locate FASTENER HOLE - 24

Install (New) FASTENER - 24 (b)

2 Install (New) BLANKET ASSY 313W5421-38 1 (a)

Install (New) BLANKET ASSY 313W5421-35 1 (a)

Install (Kept) PAN CASTING - 1 (c)

3 Install (Kept) FASTENER - 14

If removed, wet install clamp fasteners

using BMS 5-63

4 Install (Kept) CLAMP - 2

5 Install (Kept) BRACKET ASSEMBLY - 1 If removed.

If removed. Wet install by using BMS

5-63. (b)

Install (New) FASTENER - 2

6 Install (New) BLANKET ASSY 313W5421-34 1 (a)

Install (Kept) PAN CASTING - 1 (c)

7 Install (Kept) FASTENER - 12

8 Install (New) BLANKET ASSY 313W5421-33 1 (a)

Install (Kept) PAN CASTING - 1 (c)

9 Install (Kept) FASTENER - 12

10 Install (New) BLANKET ASSY 313W5421-32 1 (a)

Install (Kept) PAN CASTING - 1 (c)

11 Install (Kept) FASTENER - 12

12 Install (New) BLANKET ASSY 313W5421-31 1 (a)

Install (Kept) PAN CASTING - 1 (c)

13 Install (Kept) FASTENER - 12

14 Install (New) BLANKET ASSY 313W5421-30 1 (a)

Install (New) BLANKET ASSY 313W5421-36 1 (a)

Install (New) BLANKET ASSY 313W5421-37 1 (a)

Install (Kept) PAN CASTING - 1 (c)

15 Install (Kept) FASTENER - 22

FIGURE 7: LEFT STRUT - HEAT SHIELD INSULATION BLANKET INSTALLATION

(SHEET 7 OF 8)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: May 27, 2014

Revision 1 September 30, 2015 777-54-0030

70 of 81

BOEING SERVICE BULLETIN 777-54-0030
Step Task Name Identification Qty More Data

(a) Refer to 777 AMM 54-54-01 as an accepted procedure. Blanket should only be installed against the web

when it is in its final position to prevent loss of peel strength of velcro. Firm pressure should be applied

to assure blanket is secured properly.

(b) Refer to Fastener Code Table.

(c) Refer to CMM 54-52-17, Repair 4-1 as an accepted procedure.

The codes shown below agree with the letter shown in the upper left corner of the fastener symbols in the figure.

A number in the lower right corner gives the grip length of the fastener. The QTY numbers shown below are the

number of fasteners necessary for this figure.

Code Name Identification Qty Hole Dia More Data

E RIVET, 100 DEG BACR15CE5M5 24 0.159-0.167 Countersink 100 degrees.

Wet install using BMS 5-

63.

BOLT, PROTRUDING BACB30VT6K3 2 -

HEAD

G

COLLAR BACC30BS6S 2 -

FIGURE 7: LEFT STRUT - HEAT SHIELD INSULATION BLANKET INSTALLATION

(SHEET 8 OF 8)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: May 27, 2014

Revision 1 September 30, 2015 777-54-0030

71 of 81

BOEING SERVICE BULLETIN 777-54-0030
FIGURE 8: RIGHT STRUT - HEAT SHIELD INSULATION BLANKET INSTALLATION

(SHEET 1 OF 8)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: May 27, 2014

Revision 1 September 30, 2015 777-54-0030

72 of 81

BOEING SERVICE BULLETIN 777-54-0030
FIGURE 8: RIGHT STRUT - HEAT SHIELD INSULATION BLANKET INSTALLATION

(SHEET 2 OF 8)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: May 27, 2014

Revision 1 September 30, 2015 777-54-0030

73 of 81

BOEING SERVICE BULLETIN 777-54-0030
FIGURE 8: RIGHT STRUT - HEAT SHIELD INSULATION BLANKET INSTALLATION

(SHEET 3 OF 8)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: May 27, 2014

Revision 1 September 30, 2015 777-54-0030

74 of 81

BOEING SERVICE BULLETIN 777-54-0030
FIGURE 8: RIGHT STRUT - HEAT SHIELD INSULATION BLANKET INSTALLATION

(SHEET 4 OF 8)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: May 27, 2014

Revision 1 September 30, 2015 777-54-0030

75 of 81

BOEING SERVICE BULLETIN 777-54-0030
FIGURE 8: RIGHT STRUT - HEAT SHIELD INSULATION BLANKET INSTALLATION

(SHEET 5 OF 8)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: May 27, 2014

Revision 1 September 30, 2015 777-54-0030

76 of 81

BOEING SERVICE BULLETIN 777-54-0030
FIGURE 8: RIGHT STRUT - HEAT SHIELD INSULATION BLANKET INSTALLATION

(SHEET 6 OF 8)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: May 27, 2014

Revision 1 September 30, 2015 777-54-0030

77 of 81

BOEING SERVICE BULLETIN 777-54-0030
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 strut.

Step Task Name Identification Qty More Data

1 Install (New) RUB STRIP 311W5585Y16 1

Locate FASTENER HOLE - 24

Install (New) FASTENER - 24 (b)

2 Install (New) BLANKET ASSY 313W5421-38 1 (a)

Install (New) BLANKET ASSY 313W5421-35 1 (a)

Install (Kept) PAN CASTING - 1 (c)

3 Install (Kept) FASTENER - 14

If removed, wet install clamp fasteners

using BMS 5-63

4 Install (Kept) CLAMP - 2

5 Install (Kept) BRACKET ASSEMBLY - 1 If removed.

If removed. Wet install by using BMS

5-63. (b)

Install (New) FASTENER - 2

6 Install (New) BLANKET ASSY 313W5421-34 1 (a)

Install (Kept) PAN CASTING - 1 (c)

7 Install (Kept) FASTENER - 12

8 Install (New) BLANKET ASSY 313W5421-33 1 (a)

Install (Kept) PAN CASTING - 1 (c)

9 Install (Kept) FASTENER - 12

10 Install (New) BLANKET ASSY 313W5421-32 1 (a)

Install (Kept) PAN CASTING - 1 (c)

11 Install (Kept) FASTENER - 12

12 Install (New) BLANKET ASSY 313W5421-31 1 (a)

Install (Kept) PAN CASTING - 1 (c)

13 Install (Kept) FASTENER - 12

14 Install (New) BLANKET ASSY 313W5421-30 1 (a)

Install (New) BLANKET ASSY 313W5421-36 1 (a)

Install (New) BLANKET ASSY 313W5421-37 1 (a)

Install (Kept) PAN CASTING - 1 (c)

FIGURE 8: RIGHT STRUT - HEAT SHIELD INSULATION BLANKET INSTALLATION

(SHEET 7 OF 8)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: May 27, 2014

Revision 1 September 30, 2015 777-54-0030

78 of 81

BOEING SERVICE BULLETIN 777-54-0030
Step Task Name Identification Qty More Data

15 Install (Kept) FASTENER - 22

(a) Refer to 777 AMM 54-54-01 as an accepted procedure. Blanket should only be installed against the web

when it is in its final position to prevent loss of peel strength of velcro. Firm pressure should be applied

to assure blanket is secured properly.

(b) Refer to Fastener Code Table.

(c) Refer to CMM 54-52-17, Repair 4-1 as an accepted procedure.

The codes shown below agree with the letter shown in the upper left corner of the fastener symbols in the figure.

A number in the lower right corner gives the grip length of the fastener. The QTY numbers shown below are the

number of fasteners necessary for this figure.

Code Name Identification Qty Hole Dia More Data

E RIVET, 100 DEG BACR15CE5M5 24 0.159-0.167 Countersink 100 degrees.

Wet install using BMS 5-

63.

BOLT, PROTRUDING BACB30VT6K3 2 -

HEAD

G

COLLAR BACC30BS6S 2 -

FIGURE 8: RIGHT STRUT - HEAT SHIELD INSULATION BLANKET INSTALLATION

(SHEET 8 OF 8)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: May 27, 2014

Revision 1 September 30, 2015 777-54-0030

79 of 81

BOEING SERVICE BULLETIN 777-54-0030
The fastener codes in this Master Fastener Code table agree with the fastener codes given in the Figures in

Paragraph 3.B, Work Instructions. This fastener code table can be used as a reference when doing the service

bulletin work. If a requirement is different in a figure, than given in this table, use the requirements given in the

figure.

MASTER FASTENER CODE TABLE

HOLE DIAME- MORE DATA

TER

CODE NAME IDENTIFICATION

A BOLT, PROTRUDING HD BACB30NX6K3X 0.200-0.203 (a)

COLLAR BACC30BH6 -

B BOLT, PROTRUDING HD BACB30NX6K3X 0.200-0.203 (a)

BOLT, PROTRUDING HD BACB30NX6K4X 0.200-0.203 (a)

COLLAR BACC30BH6 -

Countersink 100 degrees.

(a)

C BOLT, 100 DEG HEX DR BACB30NW6K3X 0.200-0.203

COLLAR BACC30M6 -

Countersink 100 degrees.

(a)

D BOLT, 100 DEG HEX DR BACB30NW8K5X 0.263-0.266

Countersink 100 degrees.

(a)

BOLT, 100 DEG HEX DR BACB30NW8K6X 0.263-0.266

COLLAR BACC30M8 -

E RIVET, 100 DEG BACR15CE5M5 0.159-0.167 Countersink 100 degrees.

F RIVET, UNIVERSAL HD BACR15BB7D7C 0.221-0.233

Bolt orientation is optional.

(a)

BOLT, PROTRUDING BACB30VT6K3 0.190-0.218

HEAD

G

COLLAR BACC30BS6S -

(a) Wet install by applying BMS 5-63 to threads and shank .

APPENDIX A: MASTER FASTENER CODE TABLE

(SHEET 1 OF 1)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: May 27, 2014

Revision 1 September 30, 2015 777-54-0030

80 of 81

BOEING SERVICE BULLETIN 777-54-0030
APPENDIX B: PART DEMAND INTENT

(SHEET 1 OF 1)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: May 27, 2014

Revision 1 September 30, 2015 777-54-0030

81 of 81

BOEING SERVICE BULLETIN 777-54-0030