Commercial 

Airplanes 777

Service Bulletin

SPECIAL ATTENTION

Number: 777-71-0055

Original Issue: June 12, 2014

Revision 1: April 15, 2015

ATA System: 7171 5455

SUBJECT: POWER PLANT - Engine Vents and Drains - Pratt & Whitney Engines - Drain Line

Replacement and Insulation Blanket Installation

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Unpublished Work.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.

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3.0
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BOEING SERVICE BULLETIN 777-71-0055

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

C. Reason . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14

D. Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15

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

F. Approval . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 16

G. Manpower . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 16

H. Weight and Balance Changes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17

I. Electrical Load Data . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17

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 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 18

L. Interchangeability and Intermixability of Parts . . . . . . . . . . . . . . . . . . . . . . . . . . . 18

M. Software Accomplishment Summary . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 18

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

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

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

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

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

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 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21

F. Special Tooling Necessary to do this Service Bulletin . . . . . . . . . . . . . . . . . . . . . . . 21

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

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

B. WORK INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 24

FIGURE 1: LEFT STRUT: FORWARD STRUT DRAIN LINE - REMOVAL . . . . . . . . . . . . . . . . 26

FIGURE 2: RIGHT STRUT: FORWARD STRUT DRAIN LINE - REMOVAL . . . . . . . . . . . . . . . 28

FIGURE 3: LEFT STRUT: FORWARD STRUT DRAIN LINE - INSTALLATION . . . . . . . . . . . . . 30

FIGURE 4: RIGHT STRUT: FORWARD STRUT DRAIN LINE - INSTALLATION . . . . . . . . . . . . 36

APPENDIX A: PART DEMAND INTENT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 42

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BOEING SERVICE BULLETIN 777-71-0055
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BOEING SERVICE BULLETIN 777-71-0055

BLANK PAGE
Commercial 

Airplanes 777

Service Bulletin

SPECIAL ATTENTION

Revision Transmittal Sheet Number: 777-71-0055

Original Issue: June 12, 2014

Revision 1: April 15, 2015

ATA System: 7171 5455

SUBJECT: POWER PLANT - Engine Vents and Drains - Pratt & Whitney Engines - Drain Line

Replacement and Insulation Blanket Installation

This revision includes all pages of the service bulletin.

COMPLIANCE INFORMATION RELATED TO THIS REVISION

Effects of this Revision on airplanes on which Original Issue was previously done:

None.

REASON FOR REVISION

This revision is sent to add validation information, related Airworthiness Directive (AD) 2014-20-10 reference,

and instructions for lockwire installation on the band clamps supporting the insulation blankets.

The data given in Alternative Method of Compliance Notice 777-71-0055-AMOC-01 is included in this revision.

These sections were changed:

1. Summary, Background - added validation information.

2. Summary, Compliance - added reference to related Airworthiness Directive (AD) 2014-20-10.

3. Paragraph 1.A.1., Airplanes - listed the affected line numbers, and changed "powered by" to "delivered

with" in the Description column of the Group and Configuration Table.

4. Paragraph 1.C., Reason - added validation information and Revision 1 information.

5. Paragraph 1.D., Description - added Revision 1 information.

6. Paragraph 1.E., Compliance - added reference to related AD 2014-20-10.

7. Paragraph 1.F., Approval - updated the alternative method of compliance paragraph to refer to

superseding AD 2014-20-10.

8. Paragraph 1.J., References - updated the reference list.

9. Paragraph 2.A., Material and Price Availability - updated retrofit kit information.

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10. Paragraph 3.A., General Information - Note 3 was deleted.

11. Figures 3 and 4 - included lockwire installation information in new view G and in the step table, steps

5 and 6.

12. Appendix A - added Boeing Part Demand Intent form.

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

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BOEING SERVICE BULLETIN 777-71-0055
Commercial 

Airplanes 777

Service Bulletin

SPECIAL ATTENTION

Summary Number: 777-71-0055

Original Issue: June 12, 2014

Revision 1: April 15, 2015

ATA System: 7171 5455

SUBJECT: POWER PLANT - Engine Vents and Drains - Pratt & Whitney Engines - Drain Line

Replacement and Insulation Blanket Installation

BOEING RECOMMENDS THAT EACH OPERATOR EXAMINE THIS SERVICE BULLETIN IMMEDIATELY.

CONCURRENT REQUIREMENTS

None.

BACKGROUND

Accomplishment of the change in this service bulletin will prevent coked hydraulic fluid blockage in the forward

strut drain lines. The forward strut drain lines are located adjacent to the hot core zone of the engine. Hydraulic

fluid at elevated temperature can coke and block the forward strut drain lines. Forward strut drain lines blocked

with coked hydraulic fluid can cause flammable fluid to back up in the strut disconnect assembly and the forward

strut dry bay, and spill onto the engine. Flammable fluid at high temperatures that spills onto the engine could

result in a fire.

Hydraulic fluid contamination, including hydraulic fluid in its liquid, vapor and/or solid (coked) form, of the titanium

forward engine mount bulkhead fitting in the strut forward dry bay and the titanium strut disconnect assembly,

at high temperature can result in hydrogen embrittlement and in potential cracking of these parts. A cracked

bulkhead fitting in the strut forward dry bay can result in the loss of design load capability, which can lead to

departure of an engine. Inspection of the forward dry bay and the forward engine mount bulkhead are addressed

by service bulletin 777-54-0028. Cracks in the system disconnect assembly may allow any potential fire in the

engine area to enter the strut. This could result in an uncontained engine and strut fire. Inspection of the system

disconnect assembly is addressed by service bulletin 777-54A0024. Service bulletin 777-54-0023 does a one

time inspection of the forward strut drain lines connected to the right (fluid) side of the strut disconnect assembly,

with subsequent inspections at regular intervals as indicated in 777 Maintenance Planning Data (MPD) Item

Number 54-210-01 and 777 MPD Item Number 54-210-02. Service bulletin 777-54-0027 provides inspections

of the forward strut drain lines at intervals shorter than 777 MPD Item Number 54-210-01 and 777 MPD Item

Number 54-210-02.

Subsequent to the release of the service bulletins mentioned above, Boeing received two additional reports of

forward strut drain lines blocked with coked hydraulic fluid. The two airplanes accumulated 24900 and 11800

total flight cycles, respectively. On the first airplane, blockage with coked hydraulic fluid was found in the right

(fluid) disconnect drain line at 882 flight cycles from the operator's previous routine strut drain line inspection.

On the second airplane, blockage with coked hydraulic fluid was found in the right (fluid) disconnect drain line

at 924 flight cycles from the previous forward strut drain line inspection in accordance with service bulletin

777-54-0027. The right (fluid) side of the strut disconnect box was contaminated with hydraulic fluid in both

airplanes. Neither airplane had hydraulic fluid contamination in the electrical (left) side of the strut disconnect

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box. Inspection of the forward engine mount bulkhead fitting in the strut forward dry bay were accomplished on

both airplanes in accordance with service bulletin 777-54-0028. The first airplane had no contamination of

hydraulic fluid on the forward engine mount bulkhead fitting in the strut forward dry bay. The second airplane

had hydraulic fluid vapor contamination accompanied by primer blistering on the forward engine mount bulkhead

fitting in the strut forward dry bay.

This service bulletin gives instructions to replace the strut drain lines connected to the right (fluid) side of the

strut disconnect box, install new insulation blankets on the strut drain lines that are close to the hot core zone

of the engine, and clean the drain lines connected to the electrical (left) side of the strut disconnect box, the

strut forward dry bay and the forward fireseal pan inlet. This will ensure that the drain lines are clean and it will

prevent the occurrence of coked hydraulic fluid in the forward strut drain lines. This service bulletin also gives

instructions to update the airplane scheduled maintenance program to incorporate 777 Airworthiness Limitation

(AWL) 54-AWL-01. This service bulletin will also prevent a possible engine fire hazard and any cracking of the

forward engine mount bulkhead fitting and strut disconnect assembly caused by blocked drain lines and

contamination with hydraulic fluid at high temperature.

As a part of a service bulletin validation program, this change was completed on airplane WA304 by Service

Bulletin 777-71-0055 Original Issue before the release of Revision 1 of this service bulletin. The change completed

on airplane WA304 by Service Bulletin 777-71-0055 Original Issue is equivalent to the release of Revision 1 of

this service bulletin. Airplane WA304 has the configuration of a Group 1 airplane.

Boeing Service Related Problem (SRP) 777-SRP-71-0053 is related to this service bulletin.

Boeing 777 Maintenance Review Board Report (MRBR) Item Numbers 54-210-01 and 54-210-02 are 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 Material Yes

Paragraph 2.F., Special Tooling Necessary to

do this Service Bulletin

Special Tooling Required No

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BOEING SERVICE BULLETIN 777-71-0055
ACTION (PRR 62777-74S)

Remove the forward strut drain lines connected to the right (fluid) systems disconnect inlet. Clean the left

(electrical) systems disconnect, the strut forward lower spar and the forward fireseal pan drain lines. Install new

forward strut drain lines and insulation blankets. Do a leak check of the forward strut drain lines for any leak.

Update the airplane scheduled maintenance program to incorporate 777 Airworthiness Limitation (AWL)

54-AWL-01.

EFFECTIVITY

777-200/-300 Airplanes delivered with Pratt and Whitney engines. Refer to Paragraph 1.A.1., Airplanes, for the

list of affected airplanes.

COMPLIANCE

The Federal Aviation Administration (FAA) will possibly release an Airworthiness Directive related to this service

bulletin. The Airworthiness Directive will make the compliance tasks and times given in this service bulletin

mandatory.

Federal Aviation Administration (FAA) Airworthiness Directive AD 2014-20-10 is related to this service bulletin.

The effective date of AD 2014-20-10 is October 22, 2014.

Boeing recommends that the change given in this service bulletin be done within 4000 flight cycles or 750 days

after the original issue date of this service bulletin, whichever occurs later.

Accomplishment of this service bulletin terminates service bulletin 777-54-0027.

Accomplishment of this service bulletin terminates the repeat Part 1 - Strut Forward Dry Bay Hydraulic Fluid

Contamination GVI Inspection actions in service bulletin 777-54-0028 if service bulletin 777-54-0028 is done at

the same time as this service bulletin or, if a final one time accomplishment of Part 1 - Strut Forward Dry Bay

Hydraulic Fluid Contamination GVI Inspection and the applicable corrective actions are accomplished in

accordance with service bulletin 777-54-0028 after the incorporation of service bulletin 777-71-0055.

INDUSTRY SUPPORT INFORMATION

Boeing warranty remedies are available for airplanes in warranty as of January 25, 2006. Please refer to

Paragraph 2.B., Industry Support Information.

MANPOWER

Airplanes Total Task Hours Elapsed Hours

All Airplanes 14.75 11.75

MATERIAL INFORMATION

Boeing Supplied Kits/Parts.

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

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BOEING SERVICE BULLETIN 777-71-0055
Export Controlled ECCN: 9E991 - BOEING

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BOEING SERVICE BULLETIN 777-71-0055
Commercial 

Airplanes 777

Service Bulletin

SPECIAL ATTENTION

Number: 777-71-0055

Original Issue: June 12, 2014

Revision 1: April 15, 2015

ATA System: 7171 5455

SUBJECT: POWER PLANT - Engine Vents and Drains - Pratt & Whitney Engines - Drain Line

Replacement and Insulation Blanket Installation

BOEING RECOMMENDS THAT EACH OPERATOR EXAMINE THIS SERVICE BULLETIN IMMEDIATELY.

1. PLANNING INFORMATION

A. Effectivity

1. Airplanes

This service bulletin is applicable to 777-200/-300 Airplanes delivered with Pratt and Whitney

engines, line numbers 2-5, 7-9, 11-13, 16, 21-23, 26-27, 29, 34-40, 43, 45, 50, 52, 57, 59-60, 62,

68-69, 71-73, 75, 77, 79-82, 85, 88, 92-93, 96-97, 104-105, 107-108, 112, 116, 120, 123, 131-132,

134, 137, 139, 141-142, 146, 148, 152, 158-160, 162, 168, 172-173, 178-179, 191, 196, 205,

212-214, 216, 229, 232, 238, 240, 246-247, 254, 259, 264, 278, 280, 282, 286, 288, 290-291,

293-297, 302, 305, 309, 317-318, 322, 338, 340, 344, 347, 349, 352, 356-357, 359, 362, 368, 375,

377, 380-381, 384, 388, 400, 403, 411, 416, 437, 440, 442, 450, 452-453, 458, 460, 481-482, 486,

491, 495, 507, 509, 517, 520, 523, 526, 528, 553, 563, 574, 580, 584, 633, 635, 646, 657, 659,

682, 684, 711, 730, 738, 853, 1005, 1016, 1027, 1090, 1102, 1112, 1117 in 1 Group. The Variable

Numbers and Group Information for the applicable airplanes is given below. An equivalent change

is on subsequent production airplanes. Refer to PRR 62777-74S 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 Airplanes, line numbers 2 through 1117, delivered with Pratt and

Whitney engines.

1 -

Airplane Models:

777-200, 777-300

Variable Number Group

WA002 - WA017 1

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Variable Number Group

WA131 - WA137 1

WA171 - WA175 1

WA206 - WA212 1

WA221 - WA223 1

WA231 - WA232 1

WA241 - WA250 1

WA261 - WA266 1

WA281 - WA283 1

WA301 - WA304 1

WB051 - WB088 1

WB131 - WB148 1

WB151 - WB155 1

WB366 - WB368 1

WB481 - WB484 1

WB531 - WB537 1

WB551 - WB554 1

WB591 - WB597 1

WC111 - WC120 1

WC371 - WC374 1

WC506 - WC508 1

WC581 1

WC586 - WC587 1

WC591 - WC595 1

2. Spares Affected

Examine your Quick Engine Change (QEC) kits for parts or components changed as shown in this

service bulletin. If any parts or components are found, refer to Paragraph 2.C., Parts Necessary

for Each Airplane, for the recommended use.

Part Number Serial Number

QECPW777 -1

654W0002-53 A0028

654W0002-54 A0029

654W0002-56 A0049

QECPW777 -11

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BOEING SERVICE BULLETIN 777-71-0055
Part Number Serial Number

654W0002-6 A0005, A0011

654W0002-42 A0021, A0035, A0039

-12, -15, -17, -18, -21,

-22

QECPW777

654W0002-78 A0041, A0045

654W0002-33 A0016, A0017, A0048

654W0002-26 A0012

654W0002-23 A0004

654W0002-24 A0010

654W0002-51 A0023, A0032

QECPW777 -4

654W0002-29 A0013, A0024

654W0002-31 A0038

654W0002-3001 A0025, A0026

A0006, A0007, A0008,

A0009

654W0002-9

A0014, A0015, A0044,

A0046

654W0002-10

654W0002-73 A0033

QECPW777 -14

654W0002-3013 A0036

QECPW777 -5, -9, -7, -13

654W0002-2 A0001, A0002, A0003

A0018, A0019, A0020,

A0022, A0027, A0030,

A0031

654W0002-37

654W0002-82 A0047

B. Concurrent Requirements

None.

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BOEING SERVICE BULLETIN 777-71-0055
C. Reason

Accomplishment of the change in this service bulletin will prevent coked hydraulic fluid blockage in the

forward strut drain lines. The forward strut drain lines are located adjacent to the hot core zone of the

engine. Hydraulic fluid at elevated temperature can coke and block the forward strut drain lines. Forward

strut drain lines blocked with coked hydraulic fluid can cause flammable fluid to back up in the strut

disconnect assembly and the forward strut dry bay, and spill onto the engine. Flammable fluid at high

temperatures that spills onto the engine could result in a fire.

Hydraulic fluid contamination, including hydraulic fluid in its liquid, vapor and/or solid (coked) form, of

the titanium forward engine mount bulkhead fitting in the strut forward dry bay and the titanium strut

disconnect assembly, at high temperature can result in hydrogen embrittlement and in potential cracking

of these parts. A cracked bulkhead fitting in the strut forward dry bay can result in the loss of design

load capability, which can lead to departure of an engine. Inspection of the forward dry bay and the

forward engine mount bulkhead are addressed by service bulletin 777-54-0028. Cracks in the system

disconnect assembly may allow any potential fire in the engine area to enter the strut. This could result

in an uncontained engine and strut fire. Inspection of the system disconnect assembly is addressed

by service bulletin 777-54A0024. Service bulletin 777-54-0023 does a one time inspection of the forward

strut drain lines connected to the right (fluid) side of the strut disconnect assembly, with subsequent

inspections at regular intervals as indicated in 777 Maintenance Planning Data (MPD) Item Number

54-210-01 and 777 MPD Item Number 54-210-02. Service bulletin 777-54-0027 provides inspections

of the forward strut drain lines at intervals shorter than 777 MPD Item Number 54-210-01 and 777 MPD

Item Number 54-210-02.

Subsequent to the release of the service bulletins mentioned above, Boeing received two additional

reports of forward strut drain lines blocked with coked hydraulic fluid. The two airplanes accumulated

24900 and 11800 total flight cycles, respectively. On the first airplane, blockage with coked hydraulic

fluid was found in the right (fluid) disconnect drain line at 882 flight cycles from the operator's previous

routine strut drain line inspection. On the second airplane, blockage with coked hydraulic fluid was

found in the right (fluid) disconnect drain line at 924 flight cycles from the previous forward strut drain

line inspection in accordance with service bulletin 777-54-0027. The right (fluid) side of the strut

disconnect box was contaminated with hydraulic fluid in both airplanes. Neither airplane had hydraulic

fluid contamination in the electrical (left) side of the strut disconnect box. Inspection of the forward

engine mount bulkhead fitting in the strut forward dry bay were accomplished on both airplanes in

accordance with service bulletin 777-54-0028. The first airplane had no contamination of hydraulic fluid

on the forward engine mount bulkhead fitting in the strut forward dry bay. The second airplane had

hydraulic fluid vapor contamination accompanied by primer blistering on the forward engine mount

bulkhead fitting in the strut forward dry bay.

This service bulletin gives instructions to replace the strut drain lines connected to the right (fluid) side

of the strut disconnect box, install new insulation blankets on the strut drain lines that are close to the

hot core zone of the engine, and clean the drain lines connected to the electrical (left) side of the strut

disconnect box, the strut forward dry bay and the forward fireseal pan inlet. This will ensure that the

drain lines are clean and it will prevent the occurrence of coked hydraulic fluid in the forward strut drain

lines. This service bulletin also gives instructions to update the airplane scheduled maintenance program

to incorporate 777 Airworthiness Limitation (AWL) 54-AWL-01. This service bulletin will also prevent

a possible engine fire hazard and any cracking of the forward engine mount bulkhead fitting and strut

disconnect assembly caused by blocked drain lines and contamination with hydraulic fluid at high

temperature.

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BOEING SERVICE BULLETIN 777-71-0055
As a part of a service bulletin validation program, this change was completed on airplane WA304 by

Service Bulletin 777-71-0055 Original Issue before the release of Revision 1 of this service bulletin.

The change completed on airplane WA304 by Service Bulletin 777-71-0055 Original Issue is equivalent

to the release of Revision 1 of this service bulletin. Airplane WA304 has the configuration of a Group

1 airplane.

Boeing Service Related Problem (SRP) 777-SRP-71-0053 is related to this service bulletin.

Boeing 777 Maintenance Review Board Report (MRBR) Item Numbers 54-210-01 and 54-210-02 are

related to this service bulletin.

Revision 1 is sent to add validation information, related Airworthiness Directive (AD) 2014-20-10

reference, and instructions for lockwire installation on the band clamps supporting the insulation blankets.

D. Description

Remove the forward strut drain lines connected to the right (fluid) systems disconnect inlet. Clean the

left (electrical) systems disconnect, the strut forward lower spar and the forward fireseal pan drain lines.

Install new forward strut drain lines and insulation blankets. Do a leak check of the forward strut drain

lines for any leak. Update the airplane scheduled maintenance program to incorporate 777 Airworthiness

Limitation (AWL) 54-AWL-01.

Effects of this Revision 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, 777-300 411, 414, 416, 421, 424, 426, 432, 442

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.

Federal Aviation Administration (FAA) Airworthiness Directive AD 2014-20-10 is related to this service

bulletin. The effective date of AD 2014-20-10 is October 22, 2014.

Boeing recommends that the change given in this service bulletin be done within 4000 flight cycles or

750 days after the original issue date of this service bulletin, whichever occurs later.

Accomplishment of this service bulletin terminates service bulletin 777-54-0027.

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BOEING SERVICE BULLETIN 777-71-0055
Accomplishment of this service bulletin terminates the repeat Part 1 - Strut Forward Dry Bay Hydraulic

Fluid Contamination GVI Inspection actions in service bulletin 777-54-0028 if service bulletin 777-54-0028

is done at the same time as this service bulletin or, if a final one time accomplishment of Part 1 - Strut

Forward Dry Bay Hydraulic Fluid Contamination GVI Inspection and the applicable corrective actions

are accomplished in accordance with service bulletin 777-54-0028 after the incorporation of service

bulletin 777-71-0055.

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.

In addition, the Manager of the FAA Seattle Aircraft Certification Office approves the action (i.e. inspection

or modification) defined in this service bulletin as an alternative method of compliance to the requirements

of paragraph (g) of AD 2014-20-10 . All provisions of AD 2014-20-10 that are not specifically referenced

in the above statement remain fully applicable and must be complied with.

G. Manpower

The table below shows an estimate of the task hours necessary to do this change for each airplane.

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

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

time:

• Time to adjust to the workplace

• Time to schedule the work

• Time to inspect the work

• Time to cure the materials

• Time to make the parts

• Time to find the tools.

Task Number of Persons Task Hours Elapsed Hours

Open Access 1 2.5 2.5

FIGURE 1 1 0.5 0.5

FIGURE 2 1 0.5 0.5

Drain Clean 2 6.0 3.0

FIGURE 3 1 1.0 1.0

FIGURE 4 1 1.0 1.0

Leak Check 1 0.75 0.75

Close Access 1 2.5 2.5

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BOEING SERVICE BULLETIN 777-71-0055
Task Number of Persons Task Hours Elapsed Hours

TOTAL FOR EACH AIRPLANE 14.75 11.75

(a) The estimate assumes that no leaks are found. Additional time may be required

if repairs are necessary.

H. Weight and Balance Changes

Change in Moment

(Pound-Inches)

Change in Weight

Airplane (Pounds)

All Airplanes +1.8 +1055.7

I. Electrical Load Data

Not changed.

J. References

1. Existing Data:

a. Engineering Change Memo PRR 62777-74S

b. Boeing Service Bulletin 777-54-0023, 777-54-0027, 777-54-0028, 777-54A0024

c. Boeing Service Related Problem (SRP) 777-SRP-71-0053

d. Federal Aviation Administration (FAA) Airworthiness Directive (AD) 2014-20-10

e. Service Bulletin Index D624W001

f. Standard Overhaul Practices Manual (SOPM) 20-50-02, 20-60-03

g. Standard Wiring Practices Manual (SWPM) 20-10-11, 20-10-12, 20-10-19

h. 777 Aircraft Maintenance Manual (AMM) 20-11-00, 54-55-01, 71-71-03, 78-31-00

i. 777 Maintenance Planning Data (MPD) Item Number 54-210-01, 54-210-02, 54-AWL-01

j. 777 Maintenance Review Board Report (MRBR) Item Number 54-210-01, 54-210-02

2. Data Supplied with this Service Bulletin:

None.

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

Drawing Number Title

332W3100 Plumbing Installation EBU

332W3920 Bracket Instl - Airframe

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BOEING SERVICE BULLETIN 777-71-0055
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 N71-71

777 Illustrated Parts Catalog 71-71

777 Maintenance Planning Data Section 9

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

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

M. Software Accomplishment Summary

Not affected.

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BOEING SERVICE BULLETIN 777-71-0055
2. MATERIAL INFORMATION

A. Material - Price and Availability

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

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

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

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

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

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

2. Fax to (206) 662-7145

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

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

Unit Price as of

the original issue

date of this Service Bulletin (US

Dollars)

ROLT as of the

original issue

date of this Service Bulletin (Calendar Days)

Kit Number Name Date QTY

Top Kit - Pratt & Whit- June 11, 2014 1 218 $8,540.00

ney Engines - Forward

Strut Drain Insulation

Installation

005W3471-1

August 7, 2014 34

September 5, 18

2014

October 3, 15

2014

October 31, 15

2014

December 2, 15

2014

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

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

B. Industry Support Information

Boeing warranty remedies are available for 777 airplanes in warranty as of January 25, 2006. For task

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

Commercial Airplanes Group - Warranties. The kits for airplanes in warranty as of that date will be

supplied at no charge. Send a purchase order for the kits to Boeing Spares. Please refer to this service

bulletin number and reference the airplane variable number(s) in your purchase order.

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BOEING SERVICE BULLETIN 777-71-0055
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

005W3471-1 1 1

ALL

KIT 005W3471-1

Notes

Existing Part

Name Number

Figure

New Part Number

3 4

Qty

332W3710-22 1 1 TUBE ASSY 332W3710-22 (a)

332W3710-24 1 1 TUBE ASSY 332W3710-24 (a)

INSULATION - (a)

BLANKET FLEXIBLE DRAINLINE

49M1201-101 1 1

INSULATION - (a)

BLANKET DRAINLINE COVER

49M1201-103 1 1

UNION, BULK- MS21924J12 (a)

HEAD

AS1007J1212 1 1

(MS21924J12 optional)

HOSE, STR TO AS136-12S0177L (a)

STR

AS136-12S2- 1 1

0177L (AS136-

12S0177L optional)

AS4139J120612 1 1 TEE BACT16BR120612J (a)

(BACT16BR120612J

or

BACT16BR120612JN

optional)

NUT, TUBE, AN924-12J (a)

BULKHEAD

AS5178J12 1 1

(AN924-12J optional)

NAS1149C1732R 1 1 WASHER, PLAIN NAS1149C1732R (a)

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BOEING SERVICE BULLETIN 777-71-0055
ALL

KIT 005W3471-1

Notes

Existing Part

Name Number

Figure

New Part Number

3 4

Qty

NAS1922-0100-3H 1 1 CLAMP, HOSE - (a)

NAS1922-0125-3H 1 1 CLAMP, HOSE - (a)

NAS1922-0150-3H 3 3 CLAMP, HOSE - (a)

(a) This part is used in production.

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.

Part Number / Specification QTY Name Notes

MS20995NC32 (MS20995C32) As Required LOCKWIRE

NEVER-SEEZ PURE NICKEL 3 OZ LUBRICANT (a)

SPECIAL

(a) Refer to SOPM 20-60-03 for supplier data.

3. Parts Modified and Reidentified

None.

4. Parts Removed and Not Replaced

None.

D. Parts Necessary to Change Spares

None.

E. Special Tooling - Price and Availability

None.

F. Special Tooling Necessary to do this Service Bulletin

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

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

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

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BOEING SERVICE BULLETIN 777-71-0055

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. This information was deleted.

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

– Linear dimensions are in inches

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

or minus 0.03 inch

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

– Angular tolerance is plus or minus 2 degrees

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

Manual (SRM) Chapter 51

– Torque Values:

— Values for structural fasteners are given in 777 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.

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

SRM Chapter 51.

6. Refer to the SWPM 20-10-11 and SWPM 20-10-12 for the wire installation procedures,

and SWPM 20-10-19 for the wire separation requirements, as accepted procedures.

7. The necessary conditions for selection of clamp type and size are included in SWPM

20-10-12. If any wire bundle support clamp specified in this service bulletin does not

make a correct fit on the wire bundle, refer to SWPM 20-10-12 as an accepted

procedure to select a clamp that fits correctly.

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

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

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

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

must be used.

9. The instructions in Paragraph 3.B., Work Instructions and the figures can include

operation of tools or test equipment. Boeing Engineering Tool Drawings, the Illustrated

Tool and Equipment Manual, and the Special Tool and Ground Handling Drawing

Index contain data on versions of the tools or test equipment that you can use. It is

permitted to use replaced tools. It is not permitted to use superseded tools.

10. 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.

11. 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.

12. 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.

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

non-authoritative information from the critical and authoritative information.

14. The compliance times for the actions in Paragraph 3.B., WORK INSTRUCTIONS

are in Paragraph 1.E., Compliance.

15. Some steps in the Work Instructions are identified as Required for Compliance (RC).

If this service bulletin is mandated by an Airworthiness Directive (AD), then the steps

identified as RC must be done to comply with the AD. Alternative procedures for

steps not identified with RC can be used if the RC steps can still be done as specified,

and the airplane can be put back in a serviceable condition. An Alternative Method

of Compliance (AMOC) is not necessary for deviations to steps that are not identified

as RC.

B. WORK INSTRUCTIONS

1. Open the thrust reversers on the left and the right engines. Refer to 777 AMM 78-31-00 as an

accepted procedure.

2. RC - Disconnect and remove the forward strut drain lines in accordance with the Figures below:

Left Strut Right Strut

FIGURE 1 FIGURE 2

3. RC - Clean the left systems disconnect, the strut forward lower spar and the forward fireseal pan

drain lines, on the left and the right strut. Refer to 777 AMM 54-55-01, Strut Forward Drain Clean,

as an accepted procedure.

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4. RC - Install new forward strut drain lines and insulation blankets in accordance with the Figures

below:

Left Strut Right Strut

FIGURE 3 FIGURE 4

5. RC - Do a leak check of the forward strut drain lines, for any leak, on the left and the right strut,

and repair if any leaking is found. Refer to 777 AMM 54-55-01, Forward Strut Drain Line - Functional

Check, as an accepted procedure.

6. Close the thrust reversers on the left and the right engines. Refer to 777 AMM 78-31-00 as an

accepted procedure.

7. Put the airplane back to a serviceable condition.

8. RC - Update the airplane scheduled maintenance program to incorporate 777 Airworthiness

Limitation (AWL) 54-AWL-01.

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FIGURE 1: LEFT STRUT: FORWARD STRUT DRAIN LINE - REMOVAL

(SHEET 1 OF 2)

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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 this figure.

Step Task Name Identification Qty More Data

from the lower tee.

Refer to 777 AMM

71-71-03 as an accepted procedure. It

may be necessary to

remove one or both

clamps and the attaching hardware.

Keep any removed

clamp and the attaching hardware.

1 Disconnect TUBE ASSY 332W3710-16 1

and the attaching

hardware. Refer to

777 AMM 71-71-03

as an accepted procedure. Keep the attaching clamp and

hardware.

2 Remove TUBE ASSY - 3

FIGURE 1: LEFT STRUT: FORWARD STRUT DRAIN LINE - REMOVAL

(SHEET 2 OF 2)

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FIGURE 2: RIGHT STRUT: FORWARD STRUT DRAIN LINE - REMOVAL

(SHEET 1 OF 2)

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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 this figure.

Step Task Name Identification Qty More Data

from the lower tee.

Refer to 777 AMM

71-71-03 as an accepted procedure. It

may be necessary to

remove one or both

clamps and the attaching hardware.

Keep any removed

clamp and the attaching hardware.

1 Disconnect TUBE ASSY 332W3710-16 1

and the attaching

hardware. Refer to

777 AMM 71-71-03

as an accepted procedure. Keep the attaching clamp and

hardware.

2 Remove TUBE ASSY - 3

FIGURE 2: RIGHT STRUT: FORWARD STRUT DRAIN LINE - REMOVAL

(SHEET 2 OF 2)

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FIGURE 3: LEFT STRUT: FORWARD STRUT DRAIN LINE - INSTALLATION

(SHEET 1 OF 6)

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FIGURE 3: LEFT STRUT: FORWARD STRUT DRAIN LINE - INSTALLATION

(SHEET 2 OF 6)

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FIGURE 3: LEFT STRUT: FORWARD STRUT DRAIN LINE - INSTALLATION

(SHEET 3 OF 6)

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BOEING SERVICE BULLETIN 777-71-0055
The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY

numbers shown below are the number of parts necessary for this figure.

Step Task Name Identification Qty More Data

AS136-12S2-0177L 1 (a)

(AS136-12S0177L optional)

1 Install (New) HOSE, STR TO STR

AS1007J1212 1 (a)

(MS21924J12 optional)

Install (New) UNION, BULKHEAD

AS5178J12 (AN924- 1

12J optional)

NUT, TUBE, BULKHEADInstall (New)

Install (New) WASHER, PLAIN NAS1149C1732R 1

2 Install (New) TUBE ASSY 332W3710-22 1 (a)

AS4139J120612 1

(BACT16BR120612J or

BACT16BR120612JN

optional)

Install (New) TEE

FIGURE 3: LEFT STRUT: FORWARD STRUT DRAIN LINE - INSTALLATION

(SHEET 4 OF 6)

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Step Task Name Identification Qty More Data

Install with the kept

clamp and hardware.

3 Install (New) TUBE ASSY 332W3710-24 1

(a)

with the kept clamp

and hardware.

4 Connect TUBE ASSY 332W3710-16 1

(a)

Make sure that the

insulation blanket is

oriented between

the tube assembly

and the pneumatic

duct. Maintain a

minimum of 0.25

inch clearance

around the insulation

blanket.

INSULATION BLAN- 49M1201-101 1

KET FLEXIBLE

DRAINLINE

5 Install (New)

Torque to 5.7 in-lb to

6.3 in-lb. Make sure

that the screw housing is oriented away

from the spray

shield, to prevent

any damage to the

spray shield.

Install (New) CLAMP, HOSE NAS1922-0150-3H 3

at three locations

corresponding to

each of the three

hose clamps. For

each of the three

hose clamps, wrap

the lockwire around

the loose end of the

clamp strap. Refer

to SOPM 20-50-02

as an accepted procedure.

MS20995NC32 3

(MS20995C32 optional)

Install (New) LOCKWIRE

FIGURE 3: LEFT STRUT: FORWARD STRUT DRAIN LINE - INSTALLATION

(SHEET 5 OF 6)

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Step Task Name Identification Qty More Data

Maintain a minimum

of 0.06 inch clearance between the

insulation blanket

and the bleed valve.

INSULATION BLAN- 49M1201-103 1

KET DRAINLINE COVER

6 Install (New)

Torque to 5.7 in-lb to

6.3 in-lb.

Install (New) CLAMP, HOSE NAS1922-0100-3H 1

Torque to 5.7 in-lb to

6.3 in-lb. Maintain a

minimum of 0.25

inch clearance between the clamp and

the adjacent structure and systems.

Install (New) CLAMP, HOSE NAS1922-0125-3H 1

at two locations corresponding to each

of the two hose

clamps, and at one

location between the

two capstans on the

insulation blanket.

For each of the two

hose clamps, wrap

the lockwire around

the loose end of the

clamp strap. Refer

to SOPM 20-50-02

as an accepted procedure.

MS20995NC32 3

(MS20995C32 optional)

Install (New) LOCKWIRE

(a) Refer to 777 AMM 71-71-03 as an accepted procedure, except lubricate the threads with Never-Seez

Pure Nickel Special. Refer to 777 AMM 20-11-00 as an accepted procedure.

FIGURE 3: LEFT STRUT: FORWARD STRUT DRAIN LINE - INSTALLATION

(SHEET 6 OF 6)

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FIGURE 4: RIGHT STRUT: FORWARD STRUT DRAIN LINE - INSTALLATION

(SHEET 1 OF 6)

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FIGURE 4: RIGHT STRUT: FORWARD STRUT DRAIN LINE - INSTALLATION

(SHEET 2 OF 6)

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BOEING SERVICE BULLETIN 777-71-0055
FIGURE 4: RIGHT STRUT: FORWARD STRUT DRAIN LINE - INSTALLATION

(SHEET 3 OF 6)

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BOEING SERVICE BULLETIN 777-71-0055
The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY

numbers shown below are the number of parts necessary for this figure.

Step Task Name Identification Qty More Data

AS136-12S2-0177L 1 (a)

(AS136-12S0177L optional)

1 Install (New) HOSE, STR TO STR

AS1007J1212 1 (a)

(MS21924J12 optional)

Install (New) UNION, BULKHEAD

AS5178J12 (AN924- 1

12J optional)

NUT, TUBE, BULKHEADInstall (New)

Install (New) WASHER, PLAIN NAS1149C1732R 1

2 Install (New) TUBE ASSY 332W3710-22 1 (a)

AS4139J120612 1

(BACT16BR120612J or

BACT16BR120612JN

optional)

Install (New) TEE

FIGURE 4: RIGHT STRUT: FORWARD STRUT DRAIN LINE - INSTALLATION

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Step Task Name Identification Qty More Data

Install with the kept

clamp and hardware.

3 Install (New) TUBE ASSY 332W3710-24 1

(a)

with the kept clamp

and hardware.

4 Connect TUBE ASSY 332W3710-16 1

(a)

Make sure that the

insulation blanket is

oriented between

the tube assembly

and the pneumatic

duct. Maintain a

minimum of 0.25

inch clearance

around the insulation

blanket.

INSULATION BLAN- 49M1201-101 1

KET FLEXIBLE

DRAINLINE

5 Install (New)

Torque to 5.7 in-lb to

6.3 in-lb. Make sure

that the screw housing is oriented away

from the spray

shield, to prevent

any damage to the

spray shield.

Install (New) CLAMP, HOSE NAS1922-0150-3H 3

at three locations

corresponding to

each of the three

hose clamps. For

each of the three

hose clamps, wrap

the lockwire around

the loose end of the

clamp strap. Refer

to SOPM 20-50-02

as an accepted procedure.

MS20995NC32 3

(MS20995C32 optional)

Install (New) LOCKWIRE

FIGURE 4: RIGHT STRUT: FORWARD STRUT DRAIN LINE - INSTALLATION

(SHEET 5 OF 6)

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BOEING SERVICE BULLETIN 777-71-0055
Step Task Name Identification Qty More Data

Maintain a minimum

of 0.06 inch clearance between the

insulation blanket

and the bleed valve.

INSULATION BLAN- 49M1201-103 1

KET DRAINLINE COVER

6 Install (New)

Torque to 5.7 in-lb to

6.3 in-lb.

Install (New) CLAMP, HOSE NAS1922-0100-3H 1

Torque to 5.7 in-lb to

6.3 in-lb. Maintain a

minimum of 0.25

inch clearance between the clamp and

the adjacent structure and systems.

Install (New) CLAMP, HOSE NAS1922-0125-3H 1

at two locations corresponding to each

of the two hose

clamps, and at one

location between the

two capstans on the

insulation blanket.

For each of the two

hose clamps, wrap

the lockwire around

the loose end of the

clamp strap. Refer

to SOPM 20-50-02

as an accepted procedure.

MS20995NC32 3

(MS20995C32 optional)

Install (New) LOCKWIRE

(a) Refer to 777 AMM 71-71-03 as an accepted procedure, except lubricate the threads with Never-Seez

Pure Nickel Special. Refer to 777 AMM 20-11-00 as an accepted procedure.

FIGURE 4: RIGHT STRUT: FORWARD STRUT DRAIN LINE - INSTALLATION

(SHEET 6 OF 6)

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APPENDIX A: PART DEMAND INTENT

(SHEET 1 OF 1)

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BOEING SERVICE BULLETIN 777-71-0055