Commercial 

Airplanes 777

Service Bulletin

SPECIAL ATTENTION

Number: 777-28-0083

Original Issue: September 08, 2014

ATA System: 2822 2831 2409 2623 1120

SUBJECT: FUEL - Engine Fuel Feed System - Control of the Center Fuel Tank Fuel Scavenge

System, Wiring and Software Change

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Unpublished Work.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

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Boeing Company.

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BOEING SERVICE BULLETIN 777-28-0083

BLANK PAGE
Table of Contents

Summary ...................................................... 5

1. PLANNING INFORMATION ........................................ 9

A. Effectivity ................................................ 9

1. Airplanes ............................................. 9

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

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

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

D. Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13

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

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

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

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

I. Electrical Load Data . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 18

J. References . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 18

1. Existing Data: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 18

2. Data Supplied with this Service Bulletin: . . . . . . . . . . . . . . . . . . . . . . . . . . . 18

3. Installation Drawings Used in the Preparation of this Service Bulletin: . . . . . . . . . . . 18

K. Publications Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19

L. Interchangeability and Intermixability of Parts . . . . . . . . . . . . . . . . . . . . . . . . . . . 19

M. Software Accomplishment Summary . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19

2. MATERIAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21

A. Material - Price and Availability . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21

B. Industry Support Information . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21

C. Parts Necessary for Each Airplane . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 22

1. Kits/Parts . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 22

2. Parts and Materials Supplied by the Operator . . . . . . . . . . . . . . . . . . . . . . . . 24

3. Parts Modified and Reidentified . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25

4. Parts Removed and Not Replaced . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25

D. Parts Necessary to Change Spares . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 26

E. Special Tooling - Price and Availability . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 26

F. Special Tooling Necessary to do this Service Bulletin . . . . . . . . . . . . . . . . . . . . . . . 26

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

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

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

FIGURE 1: LEFT WING REAR SPAR IN THE LEFT MAIN LANDING GEAR BAY - PLACARD - REMOVAL

[Group 1-2] . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 31

FIGURE 2: RIGHT WING REAR SPAR IN THE RIGHT MAIN LANDING GEAR BAY - PLACARD - REMOVAL

[Group 1-2] . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 33

FIGURE 3: MAIN EQUIPMENT CENTER - WIRE BUNDLE W5732 - WIRE ROUTING [Group 1, 3] . 35

FIGURE 4: MAIN EQUIPMENT CENTER - WIRE BUNDLE W5732 - WIRING CHANGE [Group 1, 3] . 38

FIGURE 5: MAIN EQUIPMENT CENTER - WIRE BUNDLE W8327 - WIRE ROUTING [Group 2, 4] . 41

FIGURE 6: MAIN EQUIPMENT CENTER - WIRE BUNDLE W8327 - WIRING CHANGE [Group 2, 4] . 44

FIGURE 7: MAIN EQUIPMENT CENTER - WIRE BUNDLE W5829 - WIRE ROUTING [Group 1-4] . . 47

FIGURE 8: MAIN EQUIPMENT CENTER - WIRE BUNDLE W5829 - WIRING CHANGE [Group 2, 4] . 52

FIGURE 9: MAIN EQUIPMENT CENTER - WIRE BUNDLE W5829 - WIRING CHANGE [Group 1, 3] . 54

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BOEING SERVICE BULLETIN 777-28-0083
APPENDIX A: ELECTRICAL LOAD MANAGEMENT SYSTEM 2 (ELMS2) SOFTWARE . . . . . . . . . 56

APPENDIX B: FUNCTIONAL TEST . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 58

APPENDIX C: PART DEMAND INTENT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 64

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BOEING SERVICE BULLETIN 777-28-0083
Commercial 

Airplanes 777

Service Bulletin

SPECIAL ATTENTION

Summary Number: 777-28-0083

Original Issue: September 08, 2014

ATA System: 2822 2831 2409 2623 1120

SUBJECT: FUEL - Engine Fuel Feed System - Control of the Center Fuel Tank Fuel Scavenge

System, Wiring and Software Change

BOEING RECOMMENDS THAT EACH OPERATOR EXAMINE THIS SERVICE BULLETIN IMMEDIATELY.

CONCURRENT REQUIREMENTS

Refer to Paragraph 1.B., Concurrent Requirements.

BACKGROUND

This service bulletin is sent to make additional wiring changes and install updated Electrical Load Management

System 2 (ELMS2) software, for the fuel scavenge system. If this service bulletin is not done then with a single

latent failure of the auto shut off circuit there can be extended dry-running of the jettison pumps as they provide

motive flow to the fuel scavenge jet pumps. The extended dry-running of the jettison pumps does not meet

enhanced safety requirements which require that latent failures be addressed in the design. For those airplanes

that fly short missions of 4 hours or less, the present design controls the jettison pump past the pump inlet level

and uses the low pressure auto shutoff to turn off the pump which results in low pressure warning messages

displayed on the Engine Indication and Crew Alerting System (EICAS). Extended dry-running of the jettison

pumps can cause a fuel tank explosion in the extremely unlikely event that the jettison pump overheats or has

an electrical fault.

The airplanes in this service bulletin had the new fuel scavenge system installed in production. The ELMS2

software controls each main fuel tank jettison pump in driving each center fuel tank fuel scavenge jet pump. For

fuel scavenge, the jettison pumps will operate 45 minutes after the center fuel tank override/jettison pumps are

shut down and continue to operate for 4 hours. On short flights of less than 4 hours, not enough fuel is loaded

in the main fuel tanks to keep the jettison pump inlets covered for the full fuel scavenge cycle. This can result

in the extended dry-running of the jettison pumps. A minimum of approximately 2000 gallons of fuel is needed

in each main fuel tank to keep the fuel tank jettison pump inlet covered.

This service bulletin installs updated ELMS2 software, which will shut-off both main fuel tank jettison pumps

(when in fuel scavenge mode) when both the main tanks fuel quantity reduces to approximately 2500 gallons

each. Some additional wiring changes are also made in the main equipment center to improve the jettison pump

auto shut-off control. The updated ELMS2 software also includes changes to prevent one known cause of

inadvertent discharge of the Cargo Fire Suppression System (CFSS) metered bottles (there have been two

reports of an inadvertent CFSS discharge related to the ELMS discharge control logic).

Group 1-2:

It is also necessary to remove unwanted placards at the old location of the fuel scavenge jet pumps, because

the fuel scavenge jet pumps are now located in the body center fuel tank.

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Group 5:

The updated ELMS2 software is the only change that is necessary. The additional wiring changes were done

in production.

Boeing Fleet Team Digest (FTD) 777 FTD 28-07002, 777 FTD 28-09001 and 777 FTD 28-09004 are related to

this service bulletin.

The related Boeing service bulletin is 777-28-0078. SB 777-28-0078 installs the new fuel scavenge system in

ELMS2 airplanes with body center fuel tanks before line number 1099.

Boeing Service Related Problem (SRP) 777-SRP-28-0125 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 62777-79S)

Group 1-2:

At the left and right wing rear spar in the main landing gear bays. Remove the unwanted placard at the old

location of the fuel scavenge jet pump.

Group 1-4:

In the main equipment center, do some wiring changes between the P110 and P301 panels, and between the

P210 and P302 panels. Change the wiring in the P110 and P210 panels.

Install new ELMS2 software. Do a functional test.

EFFECTIVITY

777-200/-200LR/-300ER/F Airplane(s). Refer to Paragraph 1.A.1., Airplanes, for the list of affected airplanes.

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BOEING SERVICE BULLETIN 777-28-0083
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.

Group 1-4:

Boeing recommends that the change given in this service bulletin be done within 36 months after the original

issue date of this service bulletin.

Group 5:

Boeing recommends that the change given in this service bulletin be done within 12 months after the original

issue date of this service bulletin.

INDUSTRY SUPPORT INFORMATION

Boeing warranty remedies are available for airplanes in warranty as of August 23, 2007. 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 C of this service bulletin to help Boeing

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

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BOEING SERVICE BULLETIN 777-28-0083
Commercial 

Airplanes 777

Service Bulletin

SPECIAL ATTENTION

Number: 777-28-0083

Original Issue: September 08, 2014

ATA System: 2822 2831 2409 2623 1120

SUBJECT: FUEL - Engine Fuel Feed System - Control of the Center Fuel Tank Fuel Scavenge

System, Wiring and Software Change

BOEING RECOMMENDS THAT EACH OPERATOR EXAMINE THIS SERVICE BULLETIN IMMEDIATELY.

1. PLANNING INFORMATION

A. Effectivity

1. Airplanes

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

Serial Number data.

This service bulletin is applicable to 777-200/-200LR/-300ER/F Airplanes, line numbers 01099-01208

01210-01215 01217-01223 01225-01230 01232-01239 01241-01245 in 5 Groups. The Variable

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

is on subsequent production airplanes. Refer to PRR 62777-79S for data about this change.

GROUP CONFIGURATION DESCRIPTION

777-200 (with extended range)/-200LR/-300ER ELMS2 Airplane line

numbers after 1098 and before 1180.

1 -

2 - 777F ELMS2 Airplane line numbers after 1098 and before 1180.

777-200LR/-300ER ELMS2 Airplane line numbers after 1179 and

before 1206.

3 -

4 - 777F ELMS2 Airplane line numbers after 1179 and before 1206.

777-300ER/F ELMS2 Airplane line numbers after 1205 that only

require the software update.

5 -

Airplane Models:

777-200, 777-200LR, 777-300ER, 777F

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Variable Number Group

WC587 1

WC594 - WC595 1

WD106 1

WD121 - WD122 3

WD820 - WD824 1

WD825 3

WD893 - WD895 1

WD896 - WD898 5

WD918 1

WD930 3

WD944 - WD945 1

WD957 1

WD994 1

WE056 - WE057 5

WE073 - WE075 1

WE076 - WE077 3

WE078 5

WE094 - WE095 1

WE138 - WE140 5

WE141 - WE144 1

WE145 3

WE146 5

WE164 - WE167 1

WE168 - WE169 3

WE170 5

WE178 3

WE207 - WE211 1

WE212 - WE213 3

WE214 - WE215 5

WE218 1

WE219 3

WE243 - WE244 1

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BOEING SERVICE BULLETIN 777-28-0083
Variable Number Group

WE265 - WE266 1

WE267 5

WE275 - WE278 1

WE291 - WE292 1

WE293 3

WE307 - WE311 1

WE312 - WE313 3

WE314 - WE315 5

WE335 - WE336 1

WE337 - WE340 3

WE352 - WE356 1

WE376 1

WE377 3

WE381 5

WE386 - WE387 1

WE396 1

WE397 - WE399 5

WE416 - WE420 1

WE426 3

WE436 3

WE437 5

WE441 1

WE442 - WE443 5

WE451 5

WE501 - WE502 5

WE556 - WE558 5

WF022 - WF023 2

WF039 - WF040 2

WF041 5

WF065 - WF066 2

WF115 2

WF116 4

WF117 5

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BOEING SERVICE BULLETIN 777-28-0083
Variable Number Group

WF133 2

WF139 2

WF156 - WF158 2

WF159 5

WF166 2

WF167 - WF168 4

WF169 - WF170 5

WF176 5

2. Spares Affected

None.

B. Concurrent Requirements

The service bulletin(s) listed below must be done at the same time as this service bulletin:

Group 1-4:

Company Service Bulletin Description

Provides instructions to revise the ELMS

P110 panels with the addition of fuel scavenge wiring

General Electric Co SB 5000ELM-28-075,

Revision 1, dated August 5, 2014

General Electric

Provides instructions to revise the ELMS

P210 panels with the addition of fuel scavenge wiring

General Electric Co SB 6000ELM-28-076,

Revision 1, dated August 5, 2014

General Electric

C. Reason

This service bulletin is sent to make additional wiring changes and install updated Electrical Load

Management System 2 (ELMS2) software, for the fuel scavenge system. If this service bulletin is not

done then with a single latent failure of the auto shut off circuit there can be extended dry-running of

the jettison pumps as they provide motive flow to the fuel scavenge jet pumps. The extended dry-running

of the jettison pumps does not meet enhanced safety requirements which require that latent failures

be addressed in the design. For those airplanes that fly short missions of 4 hours or less, the present

design controls the jettison pump past the pump inlet level and uses the low pressure auto shutoff to

turn off the pump which results in low pressure warning messages displayed on the Engine Indication

and Crew Alerting System (EICAS). Extended dry-running of the jettison pumps can cause a fuel tank

explosion in the extremely unlikely event that the jettison pump overheats or has an electrical fault.

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BOEING SERVICE BULLETIN 777-28-0083
The airplanes in this service bulletin had the new fuel scavenge system installed in production. The

ELMS2 software controls each main fuel tank jettison pump in driving each center fuel tank fuel scavenge

jet pump. For fuel scavenge, the jettison pumps will operate 45 minutes after the center fuel tank

override/jettison pumps are shut down and continue to operate for 4 hours. On short flights of less than

4 hours, not enough fuel is loaded in the main fuel tanks to keep the jettison pump inlets covered for

the full fuel scavenge cycle. This can result in the extended dry-running of the jettison pumps. A minimum

of approximately 2000 gallons of fuel is needed in each main fuel tank to keep the fuel tank jettison

pump inlet covered.

This service bulletin installs updated ELMS2 software, which will shut-off both main fuel tank jettison

pumps (when in fuel scavenge mode) when both the main tanks fuel quantity reduces to approximately

2500 gallons each. Some additional wiring changes are also made in the main equipment center to

improve the jettison pump auto shut-off control. The updated ELMS2 software also includes changes

to prevent one known cause of inadvertent discharge of the Cargo Fire Suppression System (CFSS)

metered bottles (there have been two reports of an inadvertent CFSS discharge related to the ELMS

discharge control logic).

Group 1-2:

It is also necessary to remove unwanted placards at the old location of the fuel scavenge jet pumps,

because the fuel scavenge jet pumps are now located in the body center fuel tank.

Group 5:

The updated ELMS2 software is the only change that is necessary. The additional wiring changes were

done in production.

Boeing Fleet Team Digest (FTD) 777 FTD 28-07002, 777 FTD 28-09001 and 777 FTD 28-09004 are

related to this service bulletin.

The related Boeing service bulletin is 777-28-0078. SB 777-28-0078 installs the new fuel scavenge

system in ELMS2 airplanes with body center fuel tanks before line number 1099.

Boeing Service Related Problem (SRP) 777-SRP-28-0125 is related to this service bulletin.

D. Description

Group 1-2:

At the left and right wing rear spar in the main landing gear bays. Remove the unwanted placard at the

old location of the fuel scavenge jet pump.

Group 1-4:

In the main equipment center, do some wiring changes between the P110 and P301 panels, and

between the P210 and P302 panels. Change the wiring in the P110 and P210 panels.

Install new ELMS2 software. Do a functional test.

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

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BOEING SERVICE BULLETIN 777-28-0083
Group 1:

Affected Maintenance Zones

Model Zone

777-200, 777-200LR, 777- 117, 118, 212, 551, 651

300ER

Group 2:

Affected Maintenance Zones

Model Zone

777F 117, 118, 212, 551, 651

Group 3:

Affected Maintenance Zones

Model Zone

777-200LR, 777-300ER 117, 118, 212

Group 4:

Affected Maintenance Zones

Model Zone

777F 117, 118, 212

Group 5:

Affected Maintenance Zones

Model Zone

777-300ER, 777F 212

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.

Group 1-4:

Boeing recommends that the change given in this service bulletin be done within 36 months after the

original issue date of this service bulletin.

Group 5:

Boeing recommends that the change given in this service bulletin be done within 12 months after the

original issue date of this service bulletin.

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BOEING SERVICE BULLETIN 777-28-0083
F. Approval

This service bulletin was examined by the Federal Aviation Administration (FAA). The changes specified

in this service bulletin comply with the applicable regulations and are FAA approved, as well as European

Aviation Safety Agency (EASA)/Joint Aviation Authorities (JAA) approved for all EASA/JAA approved

airplanes listed in the service bulletin effectivity. This service bulletin and its approval were based on

the airplane in its original Boeing delivery configuration or as modified by other approved Boeing

changes.

If an airplane has a non-Boeing modification or repair that affects a component or system also affected

by this service bulletin, the operator is responsible for obtaining appropriate regulatory agency approval

before incorporating this service bulletin.

G. Manpower

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

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

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

time:

• Time to adjust to the workplace

• Time to schedule the work

• Time to inspect the work

• Time to cure the materials

• Time to make the parts

• Time to find the tools.

The estimate below gives general service bulletin incorporation time. The specific software data transfer

times can be found in 777 AMM 20-15-11.

Group 1:

Task Number of Persons Task Hours Elapsed Hours

Open Access 1 1.00 1.00

FIGURE 1 1 0.15 0.15

FIGURE 2 1 0.15 0.15

FIGURE 3 and FIG- 1 0.30 0.30

URE 4

FIGURE 7 and FIG- 2 10.90 5.45

URE 9

Install Software 1 3.00 3.00

Test 2 5.00 2.50

Close Access 1 1.00 1.00

TOTAL FOR EACH AIRPLANE 21.50 13.55

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BOEING SERVICE BULLETIN 777-28-0083
Group 2:

Task Number of Persons Task Hours Elapsed Hours

Open Access 1 1.00 1.00

FIGURE 1 1 0.15 0.15

FIGURE 2 1 0.15 0.15

FIGURE 5 and FIG- 2 9.90 4.95

URE 6

FIGURE 7 and FIG- 2 10.90 5.45

URE 8

Install Software 1 3.00 3.00

Test 2 5.00 2.50

Close Access 1 1.00 1.00

TOTAL FOR EACH AIRPLANE 31.10 18.20

Group 3:

Task Number of Persons Task Hours Elapsed Hours

Open Access 1 1.00 1.00

FIGURE 3 and FIG- 1 0.30 0.30

URE 4

FIGURE 7 and FIG- 2 10.90 5.45

URE 9

Install Software 1 3.00 3.00

Test 2 5.00 2.50

Close Access 1 1.00 1.00

TOTAL FOR EACH AIRPLANE 21.20 13.25

Group 4:

Task Number of Persons Task Hours Elapsed Hours

Open Access 1 1.00 1.00

FIGURE 5 and FIG- 2 9.90 4.95

URE 6

FIGURE 7 and FIG- 2 10.90 5.45

URE 8

Install Software 1 3.00 3.00

Test 2 5.00 2.50

Close Access 1 1.00 1.00

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Group 4:

Task Number of Persons Task Hours Elapsed Hours

TOTAL FOR EACH AIRPLANE 30.80 17.90

Group 5:

Task Number of Persons Task Hours Elapsed Hours

Install Software 1 3.00 3.00

Test 2 5.00 2.50

TOTAL FOR EACH AIRPLANE 8.00 5.50

H. Weight and Balance Changes

Group 1:

Change in Moment

(Pound-Inches)

Change in Weight

Airplane (Pounds)

777-200 (with ex- +0.9 +328.7

tended range)/-

200LR

777-300ER +0.9 +137.0

Group 2:

Change in Moment

(Pound-Inches)

Change in Weight

Airplane (Pounds)

777F +0.5 +171.2

Group 3:

Change in Moment

(Pound-Inches)

Change in Weight

Airplane (Pounds)

777-200LR +0.5 +174.4

777-300ER +0.5 +72.7

Group 4:

Change in Moment

(Pound-Inches)

Change in Weight

Airplane (Pounds)

777F +0.9 +323.5

Group 5:

None.

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I. Electrical Load Data

Not changed.

J. References

1. Existing Data:

a. Engineering Change Memo PRR 62777-79S

b. Boeing Service Bulletin 777-28-0078

c. Boeing Service Related Problem (SRP) 777-SRP-28-0125

d. Service Bulletin Index D624W001

e. Standard Overhaul Practices Manual (SOPM) 20-30-03, 20-41-01, 20-41-02, 20-43-03,

20-50-01

f. Standard Wiring Practices Manual (SWPM) 20-10-11, 20-10-12, 20-10-19, 20-30-12, 20-30-16,

20-41-01, 20-61-11, 20-81-12

g. 777 Aircraft Maintenance Manual (AMM) 06-41-00, 06-44-00, 12-11-01, 20-15-11, 24-09-00,

24-22-00, 27-51-00, 28-31-00, 28-42-01, 31-61-00, 32-00-15, 32-00-30

h. 777 Fleet Team Digest (FTD) 28-07002, 28-09001, 28-09004

i. 777 Wiring Diagram Manual (WDM) 28-31-11, 28-31-21

j. 777-200 Structural Repair Manual (SRM) 51-20-01

k. 777-300 Structural Repair Manual (SRM) 51-20-01

l. 777F Structural Repair Manual (SRM) 51-20-01

m. General Electric Co Service Bulletin 5000ELM-28-075, 6000ELM-28-076

2. Data Supplied with this Service Bulletin:

None.

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

Drawing Number Title

340W0401 MARKING INSTALLATION - FUEL SYSTEMS

288W9105 WIRE BUNDLE INSTALLATION P105 ELECTRONICS SHELF

288W4106 WIRE BUNDLE INSTL - BULKHEAD (STA 332.5)

WIRE BUNDLE INSTL - FWD W/W & AFT W/W BLKHD (PRESS)

(STA 180.5 - 332.5)

288W4113

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Drawing Number Title

WIRE BUNDLE INSTL - L.S. CAB FLOOR & FWD PASS FLR (STA

209.5 - 379)

288W4115

WIRE BUNDLE INSTL - R.S. CAB & FWD PASS FLR (STA 209.5

- 379)

288W4116

WIRE BUNDLE INSTL - L.S. LWR SDWL FWD W/W BLKHD (STA

180.5 - 414)

288W4117

WIRE BUNDLE INSTL - R.S. LWR SDWL FWD W/W BLKHD (STA

180.5 - 414)

288W4118

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 26-23, 28-22, 28-31

777 Wiring Diagram Manual 28-31, Equipment List

777 Fault Isolation Manual 28-31

777 Illustrated Parts Catalog 11-24

777 System Schematic Manual 28-31

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

1. Systems affected by this change: Electrical Load Management System (ELMS), Center Tank Fuel

Scavenge System, Main Tank Jettison Pumps, Cargo Fire Suppression System.

2. Software changes which affect operational procedures: None.

3. Other software improvements:

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a. Revised logic to add a minimum main tank fuel quantity required for pump operation, to prevent

uncovering of the jettison pump inlets and activation of the auto-shutoff relay during short

flights with light fuel loads.

b. Added an automated BITE test of the auto shutoff relays near the end of the jettison BITE

test, to address latent failures of the auto shutoff system.

c. Added a time delay to start the fuel scavenge system 13 minutes after takeoff, after the BITE

test.

d. Added a computed airspeed input to prevent the fuel scavenge system from commanding the

jettison pumps ON during maintenance actions.

e. Revised logic to prevent accidental discharge of Halon into a cargo compartment. The new

logic makes sure that depressing the DISCH switch does not cause the discharge signal to

be latched in the ELMS non-volatile memory (NVM) unless either the FWD ARM or AFT ARM

switch is also depressed.

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BOEING SERVICE BULLETIN 777-28-0083
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

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)

Airplane Kit Number Name Date QTY

Group

Number

WIRE KIT SUBASSEM- (a) 68 149 630.00

BLY

1, 3 280W5134-106

WIRE KIT SUBASSEM- (a) 80 149 655.00

BLY

1-4 280W5134-107

WIRE KIT SUBASSEM- (a) 12 149 634.00

BLY

2, 4 280W5134-108

(a) Not known at the release of this service bulletin.

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

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

The operator can supply the parts and materials shown in Paragraph 2.C.2., Parts and Materials

Supplied by the Operator. Refer to General Electric Co SB 5000ELM-28-075 and General Electric Co

SB 6000ELM-28-076.

B. Industry Support Information

Boeing warranty remedies are available for 777 airplanes in warranty as of August 23, 2007. For task

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

Support Contracts - Warranty. The kits/parts for airplanes in warranty as of that date will be supplied

at no charge. Send a purchase order for the kits/parts 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.

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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: Keep existing parts if there are other uses for them.

The parts in the kits are used in production.

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

Some parts in the wire kits are not used.

Group 1, 3:

KIT 280W5134-106

New Part Number Qty Name Notes

280W5134-106W 1 Wire List

280W5134-10201 1 ID - CONNECTOR

280W5134-10202 1 ID - CONNECTOR

ID SLEEVE -

SP684

280W5134-10203 1

ID SLEEVE -

SP683

280W5134-10303 1

CONTACT, SOCKETBACC47CP1S 1

CONTACT, SOCKETBACC47DJ1 10

BACS16W5A 1 RELAY SOCKET

BACS16X1A 1 RELAY SOCKET

BACT12AR123 1 TERMINAL

CONTACT, SOCKET, SIZE 20CTA-0165 1

D-436-38 2 SPLICE

D-436-43 4 SPLICE

Group 1-4:

KIT 280W5134-107

New Part Number Qty Name Notes

280W5134-107W 1 Wire List

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Group 1-4:

KIT 280W5134-107

New Part Number Qty Name Notes

280W5134-10301 1 ID - CONNECTOR

280W5134-10302 1 ID - CONNECTOR

ID SLEEVE -

SP683

280W5134-10303 1

ID SLEEVE -

SP689

280W5134-10304 1

BACC47CN1S 1 CONTACT, PIN

CONTACT, SOCKETBACC47CP1S 1

CONTACT, SOCKETBACC47DJ1 10

BACS16W5A 1 RELAY SOCKET

BACS16X1A 1 RELAY SOCKET

BACT12AR123 1 TERMINAL

SLEEVE, HEAT

SHRINK

BACT63D1 1

CONTACT, SOCKET, SIZE 20CTA-0165 1

D-436-38 2 SPLICE

D-436-43 3 SPLICE

Group 2, 4:

KIT 280W5134-108

New Part Number Qty Name Notes

280W5134-108W 1 Wire List

280W5134-10201 1 ID - CONNECTOR

280W5134-10202 1 ID - CONNECTOR

ID SLEEVE -

SP684

280W5134-10203 1

ID SLEEVE -

SP683

280W5134-10303 1

CONTACT, SOCKETBACC47CP1S 1

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Group 2, 4:

KIT 280W5134-108

New Part Number Qty Name Notes

CONTACT, SOCKETBACC47DJ1 10

BACS16W5A 1 RELAY SOCKET

BACS16X1A 1 RELAY SOCKET

BACT12AR123 1 TERMINAL

CONTACT, SOCKET, SIZE 20CTA-0165 1

D-436-38 2 SPLICE

D-436-43 4 SPLICE

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 1-2:

Part Number / QTY Name Notes

Specification

Refer to SOPM 20-43-03 for

materials. (a)

0.5 Chemical Conversion Coating

Pints

Chemical Conversion Coating Type

2 Class A

0.5 Primer (b)

Pints

BMS 10-11 Type 1

0.5 Gloss Enamel (b)

Pints

BMS 10-60 Type 1,

Boeing color 707

gray

(a) Or refer to 777-200 SRM 51-20-01, 777-300 SRM 51-20-01 or 777F SRM 51-20-01 for

materials.

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

for supplier data.

Media Set Part Number Media Set Name Software Part Number Software Name Notes

(a) 24 ELMS OPS/OPC (a) ELMS OPS and OPC (b) (c)

(a) Refer to APPENDIX A for the media set and software part numbers necessary for each airplane.

(b) Do not install previous versions of this software after installation of the new software part number.

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Media Set Part Number Media Set Name Software Part Number Software Name Notes

(c) The media set can be obtained directly from the supplier: GE Aviation Systems (K5294), Bishops Cleeve,

Cheltenham, Gloucestershire, GL52 8SF, United Kingdom.

Group 1-4:

Part Number / QTY Name Notes

Specification

BACS38K( )E - STRAP - YELLOW (a) (d) (f)

BACS38K( )B - STRAP - BROWN (a) (d) (f)

BMS 13-54, TYPE - LACING TAPE - YELLOW (a) (b) (e) (f)

III, CLASS 1, FINISH C, GRADE D

BMS 13-54, TYPE - LACING TAPE - BROWN (a) (c) (e) (f)

III, CLASS 1, FINISH C, GRADE D

D-436-37 6 SPLICE (a)

(a) Use for wire installation.

(b) Use as a satisfactory alternative to strap BACS38K( )E.

(c) Use as a satisfactory alternative to strap BACS38K( )B.

(d) Spares Customer Support - MC 36-65 Boeing Spares Department P.O. Box 3707 Seattle,Washington 98124-2207 USA.

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

for supplier data.

(f) Use the quantity/length needed to accomplish the changes given in this service bulletin.

For additional material and parts, refer to General Electric Co SB 5000ELM-28-075 and General

Electric Co SB 6000ELM-28-076.

3. Parts Modified and Reidentified

None.

4. Parts Removed and Not Replaced

Group 1-2:

Existing Part Name QTY Notes

Number

BAC27WFS14 PLACARD 1 -

BAC27WFS15 PLACARD 1 -

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Group 3-5:

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 777-28-0083
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 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 and process material substitutions in accordance with

SRM Chapter 51.

5. 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.

6. Refer to the SWPM 20-41-01 for the general conditions for working with Electrostatic

Discharge Sensitive (ESDS) devices, as an accepted procedure.

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. 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.

9. 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.

10. Refer to 777 AMM 20-15-11 for on-airplane software installation maintenance

practices and data transfer times, as accepted procedures.

11. 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.

12. 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.

13. 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.

14. 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.

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

non-authoritative information from the critical and authoritative information.

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

are in Paragraph 1.E., Compliance.

17. 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 Access:

a. Group 1-2:

Deactivate the trailing edge flaps. Refer to 777 AMM 27-51-00 as an accepted procedure.

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b. Group 1-2:

Install the nose and main landing gear downlock pins. Refer to 777 AMM 32-00-30 as an

accepted procedure.

c. Group 1-2:

Install the landing gear door safety pins. Refer to 777 AMM 32-00-15 as an accepted procedure.

d. Group 1-4:

Open access door 117AL to the main equipment center. Refer to 777 AMM 06-41-00 for the

location.

e. Group 1-4:

Remove electrical power from the airplane. Refer to 777 AMM 24-22-00 as an accepted

procedure.

f. Get access to the flight deck or an alternative software installation location.

2. Group 1-2:

RC - In the left and right main landing gear bays, remove the unwanted placard at the old location

of the fuel scavenge jet pump:

– From the left wing rear spar in accordance with FIGURE 1;

– From the right wing rear spar in accordance with FIGURE 2.

3. Group 1-4:

RC - Main Equipment Center Electrical Changes:

a. Group 1, 3:

Between the P110 and P301 panels, do the wiring change to wire bundle W5732 in accordance

with FIGURE 3 and FIGURE 4.

b. Group 2, 4:

Between the P110 and P301 panels, do the wiring change to wire bundle W8327 in accordance

with FIGURE 5 and FIGURE 6.

c. Group 2, 4:

Between the P210 and P302 panels, do the wiring change to wire bundle W5829 in accordance

with FIGURE 7 and FIGURE 8.

d. Group 1, 3:

Between the P210 and P302 panels, do the wiring change to wire bundle W5829 in accordance

with FIGURE 7 and FIGURE 9.

e. Change the P110 and P210 panels in accordance with General Electric Co SB

5000ELM-28-075 and General Electric Co SB 6000ELM-28-076.

4. Software Installation and Functional Test:

a. Make sure there is electrical power to the airplane. Refer to 777 AMM 24-22-00 as an accepted

procedure.

b. RC - Install new ELMS2 software in accordance with APPENDIX A.

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c. Remove electrical power from the airplane. Refer to 777 AMM 24-22-00 as an accepted

procedure.

d. RC - Do the Functional Test in accordance with APPENDIX B.

– If the functional test fails, accomplish corrective actions and repeat the functional test

and applicable corrective actions until the functional test is passed.

5. Close Access:

a. Make sure electrical power is restored to the airplane. Refer to 777 AMM 24-22-00 as an

accepted procedure.

b. Group 1-4:

Close access door 117AL to the main equipment center. Refer to 777 AMM 06-41-00 for the

location.

c. Group 1-2:

Remove the landing gear door safety pins. Refer to 777 AMM 32-00-15 as an accepted

procedure.

d. Group 1-2:

Remove the nose and main landing gear downlock pins. Refer to 777 AMM 32-00-30 as an

accepted procedure.

e. Group 1-2:

Activate the trailing edge flaps. Refer to 777 AMM 27-51-00 as an accepted procedure.

6. Put the airplane back to a serviceable condition.

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BOEING SERVICE BULLETIN 777-28-0083
This Figure applies only to: Group 1-2.

FIGURE 1: LEFT WING REAR SPAR IN THE LEFT MAIN LANDING GEAR BAY - PLACARD - REMOVAL

(SHEET 1 OF 2)

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BOEING SERVICE BULLETIN 777-28-0083
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

1 Remove PLACARD BAC27WFS14 1 -

on the airplane

where the placard

was removed. (a)

2 Clean SURFACE - -

on the airplane

where the placard

was removed, to restore any removed

finish. (b)

3 Apply FINISH - -

(a) Refer to SOPM 20-30-03 as an accepted procedure.

(b) Manually apply Chemical Conversion Coating Type 2 Class A, refer to SOPM 20-43-03 as an accepted

procedure; Then apply one layer of BMS 10-11 Type 1 primer, refer to SOPM 20-41-02 as an accepted

procedure. Then apply BMS 10-60 Type 1, Boeing color 707 gray, gloss enamel, refer to SOPM 20-41-

01 as an accepted procedure.

FIGURE 1: LEFT WING REAR SPAR IN THE LEFT MAIN LANDING GEAR BAY - PLACARD - REMOVAL

(SHEET 2 OF 2)

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BOEING SERVICE BULLETIN 777-28-0083
This Figure applies only to: Group 1-2.

FIGURE 2: RIGHT WING REAR SPAR IN THE RIGHT MAIN LANDING GEAR BAY - PLACARD - REMOVAL

(SHEET 1 OF 2)

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BOEING SERVICE BULLETIN 777-28-0083
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

1 Remove PLACARD BAC27WFS15 1 -

on the airplane

where the placard

was removed. (a)

2 Clean SURFACE - -

on the airplane

where the placard

was removed, to restore any removed

finish. (b)

3 Apply FINISH - -

(a) Refer to SOPM 20-30-03 as an accepted procedure.

(b) Manually apply Chemical Conversion Coating Type 2 Class A, refer to SOPM 20-43-03 as an accepted

procedure; Then apply one layer of BMS 10-11 Type 1 primer, refer to SOPM 20-41-02 as an accepted

procedure. Then apply BMS 10-60 Type 1, Boeing color 707 gray, gloss enamel, refer to SOPM 20-41-

01 as an accepted procedure.

FIGURE 2: RIGHT WING REAR SPAR IN THE RIGHT MAIN LANDING GEAR BAY - PLACARD - REMOVAL

(SHEET 2 OF 2)

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BOEING SERVICE BULLETIN 777-28-0083
This Figure applies only to: Group 1, 3.

FIGURE 3: MAIN EQUIPMENT CENTER - WIRE BUNDLE W5732 - WIRE ROUTING

(SHEET 1 OF 3)

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BOEING SERVICE BULLETIN 777-28-0083
FIGURE 3: MAIN EQUIPMENT CENTER - WIRE BUNDLE W5732 - WIRE ROUTING

(SHEET 2 OF 3)

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36 of 64

BOEING SERVICE BULLETIN 777-28-0083
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

Route with existing W5732 wire

bundle. Refer to SWPM 20-10-11

and SWPM 20-10-12 as accepted

procedures.

1 Install (New) Wire List 280W5134-106W 1

Install (New) STRAP - YELLOW BACS38K( )E - Operator supplied part.

FIGURE 3: MAIN EQUIPMENT CENTER - WIRE BUNDLE W5732 - WIRE ROUTING

(SHEET 3 OF 3)

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BOEING SERVICE BULLETIN 777-28-0083
This Figure applies only to: Group 1, 3.

FIGURE 4: MAIN EQUIPMENT CENTER - WIRE BUNDLE W5732 - WIRING CHANGE

(SHEET 1 OF 3)

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BOEING SERVICE BULLETIN 777-28-0083
REFERENCE: 777 WDM 28-31-11

The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure.

NOTE: Get the parts given below from kit 280W5134-106.

Name Identification Qty More Data

Flag

Note

Refer to SWPM 20-61-11 as an

accepted procedure.

1 CONTACT, SOCKET BACC47CP1S 1

Refer to SWPM 20-81-12 as an

accepted procedure.

2 CONTACT, SOCKET BACC47DJ1 1

Refer to SWPM 20-30-12 as an

accepted procedure. (a) (b) (c) (d)

3 SPLICE D-436-37 4

Refer to SWPM 20-10-11 as an

accepted procedure.

4 ID SLEEVE - SP684 280W5134-10203 1

Refer to SWPM 20-10-11 as an

accepted procedure.

5 ID SLEEVE - SP683 280W5134-10303 1

Splice SP689 is replaced in another figure.6 SPLICE - -

FIGURE 4: MAIN EQUIPMENT CENTER - WIRE BUNDLE W5732 - WIRING CHANGE

(SHEET 2 OF 3)

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BOEING SERVICE BULLETIN 777-28-0083
Name Identification Qty More Data

Flag

Note

(a) Reterminate wires W5732-0604-22, W5732-0671-22 and W5732-0676-22 to replaced splice SM21.

(b) Install wires W5732-0604-22 and W5732-0684-22 at one end of splice SM21, and install the remaining

wires at the opposite end of splice SM21.

(c) Reterminate wires W5141-0111-22, W5232-0109-22, W5829-0678-22 and W5829-0735-22 to replaced

splice SP683.

(d) Reterminate wires W5141-0112-22, W5232-0116-22, W5732-0672-22 and W5732-0673-22 to replaced

splice SP684.

FIGURE 4: MAIN EQUIPMENT CENTER - WIRE BUNDLE W5732 - WIRING CHANGE

(SHEET 3 OF 3)

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BOEING SERVICE BULLETIN 777-28-0083
This Figure applies only to: Group 2, 4.

FIGURE 5: MAIN EQUIPMENT CENTER - WIRE BUNDLE W8327 - WIRE ROUTING

(SHEET 1 OF 3)

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BOEING SERVICE BULLETIN 777-28-0083
FIGURE 5: MAIN EQUIPMENT CENTER - WIRE BUNDLE W8327 - WIRE ROUTING

(SHEET 2 OF 3)

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BOEING SERVICE BULLETIN 777-28-0083
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

Route with existing

W8327 wire bundle.

Refer to SWPM 20-

10-11 and SWPM

20-10-12 as accepted procedures.

1 Install (New) Wire List 280W5134-108W 1

Operator supplied

part.

Install (New) STRAP - YELLOW BACS38K( )E -

FIGURE 5: MAIN EQUIPMENT CENTER - WIRE BUNDLE W8327 - WIRE ROUTING

(SHEET 3 OF 3)

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BOEING SERVICE BULLETIN 777-28-0083
This Figure applies only to: Group 2, 4.

FIGURE 6: MAIN EQUIPMENT CENTER - WIRE BUNDLE W8327 - WIRING CHANGE

(SHEET 1 OF 3)

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BOEING SERVICE BULLETIN 777-28-0083
REFERENCE: 777 WDM 28-31-11

The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure.

NOTE: Get the parts given below from kit 280W5134-108.

Name Identification Qty More Data

Flag

Note

Refer to SWPM 20-61-11 as an

accepted procedure.

1 CONTACT, SOCKET BACC47CP1S 1

Refer to SWPM 20-81-12 as an

accepted procedure.

2 CONTACT, SOCKET BACC47DJ1 1

Refer to SWPM 20-30-12 as an

accepted procedure. (a) (b) (c) (d)

3 SPLICE D-436-37 4

Refer to SWPM 20-10-11 as an

accepted procedure.

4 ID SLEEVE - SP684 280W5134-10203 1

Refer to SWPM 20-10-11 as an

accepted procedure.

5 ID SLEEVE - SP683 280W5134-10303 1

Splice SP689 is replaced in another figure.6 SPLICE - -

FIGURE 6: MAIN EQUIPMENT CENTER - WIRE BUNDLE W8327 - WIRING CHANGE

(SHEET 2 OF 3)

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BOEING SERVICE BULLETIN 777-28-0083
Name Identification Qty More Data

Flag

Note

(a) Reterminate wires W8327-0604-22, W8327-0671-22 and W8327-0676-22 to replaced splice SM21.

(b) Install wires W8327-0604-22 and W8327-0684-22 at one end of splice SM21, and install the remaining

wires at the opposite end of splice SM21.

(c) Reterminate wires W5141-0111-22, W5232-0109-22, W5829-0678-22 and W5829-0735-22 to replaced

splice SP683.

(d) Reterminate wires W5141-0112-22, W5232-0116-22, W8327-0672-22 and W8327-0673-22 to replaced

splice SP684.

FIGURE 6: MAIN EQUIPMENT CENTER - WIRE BUNDLE W8327 - WIRING CHANGE

(SHEET 3 OF 3)

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BOEING SERVICE BULLETIN 777-28-0083
This Figure applies only to: Group 1-4.

FIGURE 7: MAIN EQUIPMENT CENTER - WIRE BUNDLE W5829 - WIRE ROUTING

(SHEET 1 OF 5)

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BOEING SERVICE BULLETIN 777-28-0083
FIGURE 7: MAIN EQUIPMENT CENTER - WIRE BUNDLE W5829 - WIRE ROUTING

(SHEET 2 OF 5)

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BOEING SERVICE BULLETIN 777-28-0083
FIGURE 7: MAIN EQUIPMENT CENTER - WIRE BUNDLE W5829 - WIRE ROUTING

(SHEET 3 OF 5)

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BOEING SERVICE BULLETIN 777-28-0083
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.

FIGURE 7: MAIN EQUIPMENT CENTER - WIRE BUNDLE W5829 - WIRE ROUTING

(SHEET 4 OF 5)

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BOEING SERVICE BULLETIN 777-28-0083
Step Task Name Identification Qty More Data

Route with existing W5829 wire

bundle. Refer to SWPM 20-10-11

and SWPM 20-10-12 as accepted

procedures.

1 Install (New) Wire List 280W5134-107W 1

Install (New) STRAP - BROWN BACS38K( )B - Operator supplied part.

FIGURE 7: MAIN EQUIPMENT CENTER - WIRE BUNDLE W5829 - WIRE ROUTING

(SHEET 5 OF 5)

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BOEING SERVICE BULLETIN 777-28-0083
This Figure applies only to: Group 2, 4.

REFERENCE: 777 WDM 28-31-21

The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure.

NOTE: Get the parts given below from kit 280W5134-107.

FIGURE 8: MAIN EQUIPMENT CENTER - WIRE BUNDLE W5829 - WIRING CHANGE

(SHEET 1 OF 2)

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BOEING SERVICE BULLETIN 777-28-0083
Name Identification Qty More Data

Flag

Note

Refer to SWPM 20-61-11 as an

accepted procedure.

1 CONTACT, SOCKET BACC47CP1S 1

Refer to SWPM 20-81-12 as an

accepted procedure.

2 CONTACT, SOCKET BACC47DJ1 2

Refer to SWPM 20-30-12 as an

accepted procedure. (a) (b)

3 SPLICE D-436-37 2

Refer to SWPM 20-30-12 as an

accepted procedure.

4 ID SLEEVE - SP689 280W5134-10304 1

Refer to SWPM 20-30-16 as an

accepted procedure.

5 SLEEVE, HEAT SHRINK BACT63D1 1

(a) Reterminate wires W5829-0505-22, W5829-0671-22 and W5829-0676-22 to replaced splice SM21.

(b) Install wires W5829-0505-22 and W5829-0684-22 at one end of splice SM21, and install the remaining

wires at the opposite end of splice SM21.

FIGURE 8: MAIN EQUIPMENT CENTER - WIRE BUNDLE W5829 - WIRING CHANGE

(SHEET 2 OF 2)

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BOEING SERVICE BULLETIN 777-28-0083
This Figure applies only to: Group 1, 3.

REFERENCE: 777 WDM 28-31-21

The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure.

NOTE: Get the parts given below from kit 280W5134-107.

FIGURE 9: MAIN EQUIPMENT CENTER - WIRE BUNDLE W5829 - WIRING CHANGE

(SHEET 1 OF 2)

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BOEING SERVICE BULLETIN 777-28-0083
Name Identification Qty More Data

Flag

Note

Refer to SWPM 20-61-11 as an

accepted procedure.

1 CONTACT, SOCKET BACC47CP1S 1

Refer to SWPM 20-81-12 as an

accepted procedure.

2 CONTACT, SOCKET BACC47DJ1 2

Refer to SWPM 20-30-12 as an

accepted procedure. (a) (b)

3 SPLICE D-436-37 2

Refer to SWPM 20-30-12 as an

accepted procedure.

4 ID SLEEVE - SP689 280W5134-10304 1

Refer to SWPM 20-30-16 as an

accepted procedure.

5 SLEEVE, HEAT SHRINK BACT63D1 1

(a) Reterminate wires W5829-0505-22, W5829-0671-22 and W5829-0676-22 to replaced splice SM21.

(b) Install wires W5829-0505-22 and W5829-0684-22 at one end of splice SM21, and install the remaining

wires at the opposite end of splice SM21.

FIGURE 9: MAIN EQUIPMENT CENTER - WIRE BUNDLE W5829 - WIRING CHANGE

(SHEET 2 OF 2)

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BOEING SERVICE BULLETIN 777-28-0083
Install the ELMS2 Operational Program Software (OPS) and Operational Program Configuration (OPC) software

shown below. Refer to 777 AMM 24-09-00 as an accepted procedure.

OPC Software

Part Number

OPS Software

Part Number

Media Set Part

Number

Effectivity

WC587 S281W601-B3R 2466-SMI-500-13 2416-SMI-M08-31

WC594-WC595 S281W601-B3L 2466-SMI-500-13 2411-SMI-M08-27

WD106 S281W601-B3P 2466-SMI-500-13 2417-SMI-M08-30

WD121-WD122 S281W601-B1Y 2466-SMI-500-13 2417-SMI-M08-12

WD820-WD825 S281W601-B33 2466-SMI-500-13 2414-SMI-M09-01

WD893-WD898 S281W601-B30 2466-SMI-500-13 2416-SMI-M09-03

WD918 S281W601-B3M 2466-SMI-500-13 241E-SMI-M08-28

WD930 S281W601-B39 2466-SMI-500-13 2410-SMI-M09-14

WD944-WD945 S281W601-B3T 2466-SMI-500-13 2415-SMI-M08-32

WD957 S281W601-B3N 2466-SMI-500-13 241F-SMI-M08-29

WD994 S281W601-B37 2466-SMI-500-13 2412-SMI-M08-24

WE056-WE057 S281W601-B2G 2466-SMI-500-13 2415-SMI-M09-11

WE073-WE078 S281W601-B2C 2466-SMI-500-13 241E-SMI-M08-39

WE094-WE095 S281W601-B3U 2466-SMI-500-13 2414-SMI-M08-33

WE138-WE140 S281W601-B2E 2466-SMI-500-13 241D-SMI-M09-08

WE141-WE146 S281W601-B3F 2466-SMI-500-13 241C-SMI-M09-09

WE164-WE170 S281W601-B3H 2466-SMI-500-13 2416-SMI-M09-12

WE178 S281W601-B2P 2466-SMI-500-13 2414-SMI-M08-22

WE207-WE215 S281W601-B2M 2466-SMI-500-13 2417-SMI-M09-02

WE218-WE219 S281W601-B2Y 2466-SMI-500-13 2412-SMI-M08-35

WE243-WE244 S281W601-B33 2466-SMI-500-13 2414-SMI-M09-01

WE265-WE267 S281W601-B3G 2466-SMI-500-13 2414-SMI-M09-10

WE275-WE278 S281W601-B3D 2466-SMI-500-13 2410-SMI-M09-05

WE291-WE293 S281W601-B3K 2466-SMI-500-13 2412-SMI-M09-16

WE307-WE315 S281W601-B3E 2466-SMI-500-13 2417-SMI-M09-13

WE335-WE340 S281W601-B3B 2466-SMI-500-13 2410-SMI-M08-26

WE352-WE356 S281W601-B3A 2466-SMI-500-13 2413-SMI-M08-25

WE376-WE377 S281W601-B38 2466-SMI-500-13 2411-SMI-M08-41

WE381 S281W601-B38 2466-SMI-500-13 2411-SMI-M08-41

APPENDIX A: ELECTRICAL LOAD MANAGEMENT SYSTEM 2 (ELMS2) SOFTWARE

(SHEET 1 OF 2)

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BOEING SERVICE BULLETIN 777-28-0083
OPC Software

Part Number

OPS Software

Part Number

Media Set Part

Number

Effectivity

WE386-WE387 S281W601-B1E 2466-SMI-500-13 2411-SMI-M08-36

WE396-WE399 S281W601-B16 2466-SMI-500-13 2413-SMI-M09-06

WE416-WE420 S281W601-B2U 2466-SMI-500-13 2415-SMI-M08-23

WE426 S281W601-B24 2466-SMI-500-13 241F-SMI-M08-38

WE436-WE437 S281W601-B24 2466-SMI-500-13 241F-SMI-M08-38

WE441-WE443 S281W601-B3D 2466-SMI-500-13 2410-SMI-M09-05

WE451 S281W601-B3J 2466-SMI-500-13 2411-SMI-M09-15

WE501-WE502 S281W601-B3C 2466-SMI-500-13 2411-SMI-M09-04

WE556-WE558 S281W601-B2M 2466-SMI-500-13 2417-SMI-M09-02

WF022-WF024 S281W601-B34 2466-SMI-500-13 2412-SMI-M09-07

WF039-WF041 S281W601-B34 2466-SMI-500-13 2412-SMI-M09-07

WF065-WF066 S281W601-B23 2466-SMI-500-13 2410-SMI-M08-37

WF115-WF117 S281W601-B34 2466-SMI-500-13 2412-SMI-M09-07

WF133 S281W601-B34 2466-SMI-500-13 2412-SMI-M09-07

WF139 S281W601-B34 2466-SMI-500-13 2412-SMI-M09-07

WF156-WF159 S281W601-B34 2466-SMI-500-13 2412-SMI-M09-07

WF166-WF170 S281W601-B34 2466-SMI-500-13 2412-SMI-M09-07

WF176 S281W601-B34 2466-SMI-500-13 2412-SMI-M09-07

APPENDIX A: ELECTRICAL LOAD MANAGEMENT SYSTEM 2 (ELMS2) SOFTWARE

(SHEET 2 OF 2)

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BOEING SERVICE BULLETIN 777-28-0083
1. General Notes:

a. Obey these precautions at all times during this test:

WARNING: DO NOT OPERATE A FUEL PUMP IF THE LOW PRESSURE LIGHT COMES ON

AND STAYS ON. THIS CONDITION CAN CAUSE THE IGNITION OF THE FUEL

FUMES IN THE FUEL TANK. A FIRE OR AN EXPLOSION CAN CAUSE INJURIES

TO PERSONNEL AND DAMAGE TO EQUIPMENT.

(1) To operate any of the fuel pumps, you must be in the flight compartment to continuously

monitor the fuel quantity and the low pressure indication in the applicable tank.

(2) Immediately set the applicable fuel pump switch(es) on the P5 overhead panel to the OFF

position if the low pressure indication light comes on and stays on.

NOTE: The FAULT light on the FUEL JETTISON ARM switch comes on to show low pressure

for the jettison pumps. Set the FUEL JETTISON ARM switch to the OFF position if

this occurs. This does not apply during sections of this test when the jettison pump

connectors are removed and jettison pumps are not powered.

b. When a test step states to make sure that there is no power to a connector, or that power is

removed from a connector, do one of the following:

(1) If a phase rotation indicator is used, make sure that the 3-phase rotator light is off.

(2) If a multimeter is used, make sure that the multimeter shows less than 20 volts AC.

c. When a test step states to make sure that there is power to a connector, do one of the following:

(1) If a phase rotation indicator is used, make sure that the 3-phase rotator light is on and displays

the correct phase sequence of A-B-C.

(2) If a multimeter is used, make sure that the multimeter shows between 180 and 220 volts AC.

d. Refer to these manuals for locations of items referenced in this test:

(1) Access panels: 777 AMM 06-44-00

(2) P5 Overhead Panel, P28 Integrated Refuel Panel, P110/P210/P310 Power Management

Panels: 777 AMM 28-31-00

(3) Jettison pumps and pressure switches: 777 AMM 28-42-01

e. The following equipment is needed for this test:

(1) Digital Multimeter

(2) Phase Rotation Indicators, quantity 2

- OR -

APPENDIX B: FUNCTIONAL TEST

(SHEET 1 OF 6)

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BOEING SERVICE BULLETIN 777-28-0083
One more Digital Multimeter

(3) Stopwatch (timer)

2. Access:

a. Open access to the flight compartment and the Main Equipment Center.

b. On the left wing, open refueling station door 521DB to get access to the P28 Integrated Refuel

Panel (IRP).

c. On the right wing, make sure that refueling station door 621DB is closed, if installed.

d. Make sure that electrical power is removed.

3. Continuity Test:

a. Set a digital multimeter to measure zero ohms resistance.

b. In the Main Equipment Center, left side, on the P110 panel, disconnect electrical connector D11007.

c. Measure the resistance between pins 4 and 7 of D11007. Make sure that the resistance is less

than 10 ohms.

d. Connect electrical connector D11007.

e. In the Main Equipment Center, right side, on the P210 panel, disconnect electrical connectors

D21004 and D21007.

f. Measure the resistance between pin 48 of D21004 and pin 5 of D21007. Make sure that the

resistance is less than 10 ohms.

g. Connect electrical connectors D21004 and D21007.

4. Test Setup:

a. Make sure that these circuit breakers are closed:

Location Circuit Breaker

Panel Row Column Number Name

P110 L 21 C28647 CTR L OVRD FUEL PUMP CTRL

L 24 C28631 L FUEL JETT ISLN VLV

L 25 C28621 L FUEL JETT NOZ VLV

P210 K 12 C28620 R FUEL JETT NOZ VLV

K 13 C28630 R FUEL JETT ISLN VLV

L 2 C28644 CTR R OVRD FUEL PUMP CTRL

APPENDIX B: FUNCTIONAL TEST

(SHEET 2 OF 6)

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BOEING SERVICE BULLETIN 777-28-0083
b. Open these circuit breakers and attach DO NOT CLOSE tags:

Location Circuit Breaker

Panel Row Column Number Name

P110 L 22 C28645 L FUEL JETT PUMP CTRL

P210 K 14 C28646 R FUEL JETT PUMP CTRL

c. Supply electrical power to the airplane. Refer to 777 AMM 24-22-00 as an accepted procedure.

d. On the rear spar, disconnect electrical connectors DM28104 from the left main tank jettison pump

and DM28204 from the right main tank jettison pump.

e. Do the applicable step below to prepare for a check of power in the electrical connectors DM28104

and DM28204.

(1) If phase rotation indicators are used, connect a phase rotation indicator to each connector as

shown in the table below:

Phase Rotation Indicator Electrical Connector

Phase A Pin B

Phase B Pin D

Phase C Pin F

(2) If digital multimeters are used, connect one to each connector, between any two of the pins

in the table above. Set each multimeter to measure 200 volts AC.

5. Fast Defueling and Auto Shutoff Operational Test:

a. Remove the DO NOT CLOSE tags and close these circuit breakers:

Location Circuit Breaker

Panel Row Column Number Name

P110 L 22 C28645 L FUEL JETT PUMP CTRL

P210 K 14 C28646 R FUEL JETT PUMP CTRL

b. Make sure that this circuit breaker is closed:

Location Circuit Breaker

Panel Row Column Number Name

P310 J 10 C28637 DEFUEL VLV

APPENDIX B: FUNCTIONAL TEST

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c. In the flight compartment, show the Fuel Management Maintenance page on the Multi-Function

Display. Refer to 777 AMM 31-61-00 as an accepted procedure.

d. On the Fuel Management Maintenance page, for MAIN JET PUMP L and R, make sure that the

COMMAND indications show OFF and that the STATUS indications show NO PRESS.

e. On the rear spar, disconnect electrical connectors DS28111 from the left main tank jettison pump

pressure switch and DS28211 from the right main tank jettison pump pressure switch.

f. On the Fuel Management Maintenance page, for MAIN JET PUMP L and R, make sure that the

COMMAND indications show OFF and that the STATUS indications show PRESS.

g. On the P28 IRP, set the DEFUEL VALVE switch to OPEN.

h. On the rear spar, make sure that there is no power to electrical connectors DM28104 and DM28204.

i. On the P5 Overhead Panel, set the FUEL JETTISON ARM switch to the ARMED position.

j. On the rear spar, make sure that there is power to electrical connectors DM28104 and DM28204.

k. On the Fuel Management Maintenance page, for MAIN JET PUMP L and R, make sure that the

COMMAND indications show ON and that the STATUS indications show PRESS.

l. Open this circuit breaker and attach a DO NOT CLOSE tag:

Location Circuit Breaker

Panel Row Column Number Name

P310 J 10 C28637 DEFUEL VLV

m. On the rear spar, make sure that there is power to electrical connectors DM28104 and DM28204.

n. Prepare to start the stopwatch.

o. On the left rear spar, connect electrical connector DS28111 to the left main tank jettison pump

pressure switch and start the stopwatch.

p. Make sure that power is removed from connector DM28104 in 20 seconds or less.

q. Disconnect connector DS28111 from the left main tank jettison pump pressure switch.

r. Make sure that there is power to connector DM28104.

s. On the right rear spar, connect electrical connector DS28211 to the right main tank jettison pump

pressure switch and start the stopwatch.

t. Make sure that power is removed from connector DM28204 in 20 seconds or less.

u. Disconnect connector DS28211 from the right main tank jettison pump pressure switch.

APPENDIX B: FUNCTIONAL TEST

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v. Make sure that there is power to connector DM28204.

w. Remove the DO NOT CLOSE tag and close this circuit breaker:

Location Circuit Breaker

Panel Row Column Number Name

P310 J 10 C28637 DEFUEL VLV

x. On the P28 IRP, set the DEFUEL VALVE switch to the CLOSE position.

y. Make sure that there is power to connectors DM28104 and DM28204.

NOTE: This is a special sequence to test the wiring. Usually, the FUEL JETTISON ARM switch

is set to OFF before the DEFUEL VALVE switch is set to CLOSE.

z. On the P5 Overhead Panel, set the FUEL JETTISON ARM switch to the OFF position.

aa. On the rear spar, make sure that there is no power to connectors DM28104 and DM28204.

ab. Disconnect the phase rotation indicator or multimeter from connector DM28104.

ac. Connect DM28104 to the left main tank jettison pump and DS28111 to the left main tank jettison

pump pressure switch.

ad. Disconnect the phase rotation indicator or multimeter from connector DM28204.

ae. Connect DM28204 to the right main tank jettison pump and DS28211 to the right main tank jettison

pump pressure switch.

af. Make sure that there is a minimum of 15,000 pounds (6804 kilograms) of fuel in each main fuel

tank. Add fuel if necessary. Refer to 777 AMM 12-11-01, Pressure Refueling, as an accepted

procedure.

ag. Do these steps to turn on the main tank jettison pumps in the fast defuel mode:

(1) On the P28 IRP, set the DEFUEL VALVE switch to the OPEN position.

(2) On the P5 Overhead Panel, set the FUEL JETTISON ARM switch to the ARMED position.

ah. Operate the pumps for a minimum of one minute.

ai. Do these steps to turn off the main tank jettison pumps:

(1) On the P5 Overhead Panel, set the FUEL JETTISON ARM switch to the OFF position.

(2) On the P28 IRP, set the DEFUEL VALVE switch to the CLOSE position.

aj. On the flight deck, on the EICAS display, make sure that no ATA 28 messages show.

APPENDIX B: FUNCTIONAL TEST

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ak. Close refueling station door 521DB.

APPENDIX B: FUNCTIONAL TEST

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APPENDIX C: PART DEMAND INTENT

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