Commercial 

Airplanes 777

Service Bulletin

Number: 777-28A0038

Original Issue: June 13, 2008

Revision 1: September 20, 2010

ATA System: 2822

SUBJECT: FUEL - Engine Fuel Feed System - Main Tank Boost Pump Ground Fault Protection

Change

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

CFR 730-774). An export license may be required before it is used for development, production or use by foreign

persons from specific countries. The controller of this data has the individual responsibility to abide by all export

laws.

ECCN: 9E991

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Copyright © 2008 The Boeing Company

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BLANK PAGE
Table of Contents

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

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

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

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

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

2. Spares Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14

B. Concurrent Requirements . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14

C. Reason . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 16

D. Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 16

E. Compliance . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17

F. Approval . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17

G. Manpower . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17

H. Weight and Balance Changes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 18

I. Electrical Load Data . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19

J. References . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19

1. Existing Data: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19

2. Data supplied with this Service Bulletin: . . . . . . . . . . . . . . . . . . . . . . . . . . . 19

3. Installation Drawings Used in the Preparation of this Service Bulletin: . . . . . . . . . . . 19

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

L. Interchangeability and Intermixability of Parts . . . . . . . . . . . . . . . . . . . . . . . . . . . 20

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

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

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

C. Parts Necessary For Each Airplane . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21

1. Kits/Parts: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21

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 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 23

FIGURE 1: P110, P210 AND P320 PANEL MODIFICATION [Group 1] . . . . . . . . . . . . . . . . . 28

FIGURE 2: P110, P210 AND P320 PANEL MODIFICATION [Group 2] . . . . . . . . . . . . . . . . . 30

FIGURE 3: P110, P210 AND P320 PANEL MODIFICATION [Group 3] . . . . . . . . . . . . . . . . . 32

FIGURE 4: P110, P210 AND P320 PANEL MODIFICATION [Group 4] . . . . . . . . . . . . . . . . . 34

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BLANK PAGE
Commercial 

Airplanes 777

Service Bulletin

Revision Transmittal Sheet Number: 777-28A0038

Original Issue: June 13, 2008

Revision 1: September 20, 2010

ATA System: 2822

SUBJECT: FUEL - Engine Fuel Feed System - Main Tank Boost Pump Ground Fault Protection

Change

This revision includes all pages of the service bulletin.

COMPLIANCE INFORMATION RELATED TO THIS REVISION

No more work is necessary on airplanes changed in accordance with the original issue of this service bulletin.

Airplane WD796 was added to Group 2 of this service bulletin effectivity.

REASON FOR REVISION

This revision is sent to correct discrepancies and typographical errors found in this service bulletin. Airplane

WD796 was included in the effectivity of the original issue of this service bulletin, but it was not shown in Paragraph

1.A.1 Airplanes.

Terminology has been changed in the Work Instructions to agree with the terminology defined in Paragraph

3.A., General Information - Notes.

These sections were changed:

1. In Paragraph 1.D., Description, added Affected Maintenance Zones tables.

2. In Paragraph 1.J.1., Existing Data, Group 3, changed incorrect supplier service bulletin numbers.

3. In Paragraph 3.B., Work Instructions, steps 4.b.(1), and 4.d.(1), changed incorrect circuit breaker location

data.

Vertical lines are put on the left edge of each page, except in Paragraph 1.A., Effectivity, to show the location

of important changes.

Pages with no vertical lines have no important changes.

REVISION HISTORY

Original Issue: June 13, 2008

Revision 1: September 20, 2010

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BLANK PAGE
Commercial 

Airplanes 777

Service Bulletin

Summary Number: 777-28A0038

Original Issue: June 13, 2008

Revision 1: September 20, 2010

ATA System: 2822

SUBJECT: FUEL - Engine Fuel Feed System - Main Tank Boost Pump Ground Fault Protection

Change

CONCURRENT REQUIREMENTS

Refer to Paragraph 1.B., Concurrent Requirements.

BACKGROUND

This service bulletin will add an extra layer of protection to prevent possible sources of ignition in the fuel tank

caused by electrical faults in the main tank boost pumps. An ignition source in the fuel tank could result in a fire

or an explosion.

This service bulletin is the result of the safety assessments conducted by Boeing under Special Federal Aviation

Regulation 88 (SFAR 88), "Fuel Tank System Fault Tolerance Evaluation Requirements". The safety assessments

indicate that wiring deterioration or damage in the main tank boost pump wiring can result in electrical faults.

Internal electrical faults in the main tank boost pumps could cause an ignition source in the fuel tank from an

overheat condition or electrical arcs. This service bulletin provides instructions to replace the existing main tank

boost pump relays with new Ground Fault Interrupt (GFI) relays. New GFI relays monitor the electrical faults

and remove the power from the fuel pump immediately to minimize the risk of ignition source.

This change affected Section 9 of the Maintenance Planning Data (MPD) Document. New Airworthiness Limitation

(AWL) 28-AWL-18 will be added to Section 9 of the MPD to include the GFI operational check of the main tank

boost pumps.

ACTION (PRR 61998-1)

Replace four main tank boost pump relays in Electrical Management System panels P110, P210, and P320 with

new GFI relays, in accordance with the GE Aviation Service Bulletins.

EFFECTIVITY

777-200, 777-200LR, 777-300, 777-300ER Airplanes. 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.

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Boeing recommends that the change given in this service bulletin be done within 60 months after the original

issue date of this service bulletin.

INDUSTRY SUPPORT INFORMATION

Boeing warranty remedies are not available for the configuration changes given in this service bulletin.

MANPOWER

Airplanes Total Task Hours Elapsed Hours

All 1.25 1.25

The time to make the changes to the Electrical Load Management System (ELMS) panels in accordance with

the GE Aviation service bulletins is not included.

MATERIAL INFORMATION

None.

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Commercial 

Airplanes 777

Service Bulletin

Number: 777-28A0038

Original Issue: June 13, 2008

Revision 1: September 20, 2010

ATA System: 2822

SUBJECT: FUEL - Engine Fuel Feed System - Main Tank Boost Pump Ground Fault Protection

Change

1. PLANNING INFORMATION

A. Effectivity

1. Airplanes

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

Number, and Serial Number data.

This service bulletin is for the airplanes shown below. An equivalent change is on subsequent

production airplanes. Refer to PRR 61998-1, Part D for data about this change.

GROUP CONFIGURATION DESCRIPTION

777-200 airplanes line numbers 1- 661 with Electrical Load

Management System 1 (ELMS 1)

1 -

777-300 and -300ER airplanes line numbers 1- 661 with ELMS 1 or

ELMS 2

2 -

3 - 777-200 airplanes line numbers 1- 661 with ELMS 2

4 - 777-200LR airplanes line numbers 1- 661 with ELMS 2

Airplane Models:

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

Variable Number Group

WA001 - WA017 1

WA076 - WA080 1

WA086 - WA093 1

WA101 - WA104 1

WA116 - WA119 1

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Variable Number Group

WA131 - WA137 1

WA171 - WA175 1

WA196 - WA198 1

WA206 - WA212 1

WA221 - WA223 1

WA231 - WA232 1

WA241 - WA250 1

WA261 - WA266 1

WA281 1

WA282 - WA283 3

WA301 - WA304 3

WB001 - WB021 1

WB031 - WB046 1

WB051 - WB088 1

WB101 - WB106 1

WB121 - WB125 1

WB131 - WB139 1

WB140 - WB144 3

WB151 - WB155 1

WB161 - WB175 1

WB176 - WB177 3

WB181 - WB192 1

WB193 - WB194 3

WB201 - WB214 1

WB215 3

WB231 - WB247 1

WB271 - WB273 1

WB276 - WB286 1

WB291 - WB302 1

WB306 - WB307 1

WB311 - WB337 1

WB341 - WB342 1

WB366 - WB367 1

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BOEING SERVICE BULLETIN 777-28A0038
Variable Number Group

WB368 3

WB371 - WB388 1

WB406 1

WB411 - WB413 1

WB416 - WB437 1

WB438 - WB439 3

WB446 - WB453 1

WB476 1

WB481 - WB484 1

WB501 - WB512 2

WB531 - WB537 2

WB551 - WB554 2

WB591 - WB597 2

WB601 - WB606 2

WB611 - WB622 2

WB631 - WB638 2

WB646 - WB649 2

WC051 - WC073 1

WC101 - WC104 1

WC111 - WC114 1

WC115 - WC119 3

WC221 - WC222 3

WC241 - WC243 1

WC281 - WC286 1

WC287 - WC290 3

WC301 - WC302 1

WC303 - WC308 3

WC361 - WC362 1

WC363 - WC364 3

WC371 - WC372 1

WC373 - WC374 3

WC381 - WC395 3

WC441 3

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BOEING SERVICE BULLETIN 777-28A0038
Variable Number Group

WC446 - WC449 3

WC456 - WC459 3

WC486 - WC493 3

WC506 - WC508 3

WC521 - WC522 3

WC531 - WC534 3

WC546 - WC547 3

WC556 3

WC566 - WC567 3

WD001 - WD002 4

WD011 - WD013 4

WD031 - WD032 4

WD046 4

WD501 - WD506 2

WD521 - WD536 2

WD546 - WD552 2

WD561 - WD570 2

WD581 - WD592 2

WD606 - WD609 2

WD621 - WD632 2

WD651 - WD657 2

WD671 - WD675 2

WD691 - WD700 2

WD741 - WD745 2

WD761 - WD765 2

WD786 - WD787 2

WD796 2

WD826 - WD828 2

2. Spares Affected

None.

B. Concurrent Requirements

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

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BOEING SERVICE BULLETIN 777-28A0038
Group 1:

Company Service Bulletin Description

Replace the main tank boost pump relays

with new Ground Fault Interrupt (GFI) relays

in P110 panel.

GE Aviation 5000ELM-28-443 original issue.

Replace the existing main tank boost pump

relays with new GFI relays in P210 panel.

6000ELM-28-444 original issue.

Replace the main tank boost pump relays

with new GFI relays in P320 panel.

4000ELM-28-445 original issue.

Group 2:

Company Service Bulletin Description

Replace the main tank boost pump relays

with new GFI relays in P110 panel.

5000ELM-28-446 original issue thru

Revision 1.

GE Aviation

Replace the main tank boost pump relays

with new GFI relays in P210 panel.

6000ELM-28-447 original issue.

Replace the main tank boost pump relays

with new GFI relays in P320 panel.

4000ELM-28-448 original issue thru

Revision 1.

Group 3:

Company Service Bulletin Description

Replace the main tank boost pump relays

with new GFI relays in P110 panel.

5000ELM-28-449 original issue thru

Revision 1.

GE Aviation

Replace the main tank boost pump relays

with new GFI relays in P210 panel.

6000ELM-28-450 original issue.

Replace the main tank boost pump relays

with new GFI relays in P320 panel.

4000ELM-28-451 original issue thru

Revision 1.

Group 4:

Company Service Bulletin Description

Replace the main tank boost pump relays

with new GFI relays in P110 panel.

GE Aviation 5000ELM-28-463 original issue.

Replace the main tank boost pump relays

with new GFI relays in P210 panel.

6000ELM-28-464 original issue.

Replace the main tank boost pump relays

with new GFI relays in P320 panel.

4000ELM-28-465 original issue.

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BOEING SERVICE BULLETIN 777-28A0038
C. Reason

This service bulletin will add an extra layer of protection to prevent possible sources of ignition in the

fuel tank caused by electrical faults in the main tank boost pumps. An ignition source in the fuel tank

could result in a fire or an explosion.

This service bulletin is the result of the safety assessments conducted by Boeing under Special Federal

Aviation Regulation 88 (SFAR 88), "Fuel Tank System Fault Tolerance Evaluation Requirements". The

safety assessments indicate that wiring deterioration or damage in the main tank boost pump wiring

can result in electrical faults . Internal electrical faults in the main tank boost pumps could cause an

ignition source in the fuel tank from an overheat condition or electrical arcs. This service bulletin provides

instructions to replace the existing main tank boost pump relays with new Ground Fault Interrupt (GFI)

relays. New GFI relays monitor the electrical faults and remove the power from the fuel pump immediately

to minimize the risk of ignition source.

This change affected Section 9 of the Maintenance Planning Data (MPD) Document. New Airworthiness

Limitation (AWL) 28-AWL-18 will be added to Section 9 of the MPD to include the GFI operational

check of the main tank boost pumps.

Revision 1 is sent to correct discrepancies and typographical errors found in this service bulletin.

Airplane WD796 was included in the effectivity of the original issue of this service bulletin, but it was

not shown in Paragraph 1.A.1 Airplanes.

Terminology has been changed in the Work Instructions to agree with the terminology defined in

Paragraph 3.A., General Information - Notes.

D. Description

Replace four main tank boost pump relays in Electrical Management System (ELMS) panels P110,

P210, and P320 with new GFI relays, in accordance with the GE Aviation Service Bulletins.

Revision 1 - No more work is necessary on airplanes changed in accordance with the original issue of

this service bulletin.

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

Group 1, 3:

Affected Maintenance Zones

Model Zone

777-200 117, 118

Group 2:

Affected Maintenance Zones

Model Zone

777-300, 777-300ER 117, 118

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BOEING SERVICE BULLETIN 777-28A0038
Group 4:

Affected Maintenance Zones

Model Zone

777-200LR 117, 118

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.

Boeing recommends that the change given in this service bulletin be done within 60 months after the

original issue date of this service bulletin.

F. Approval

This service bulletin was examined by the 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 examine the work

— Time to cure the materials

— Time to make the parts

— Time to find the tools.

Group 1:

Task Number of Persons Task-Hours Elapsed Hours

Open Access 1 0.25 0.25

FIGURE 1 (a) (a) (a)

Close Access 1 0.25 0.25

Test 1 0.75 0.75

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BOEING SERVICE BULLETIN 777-28A0038
Group 1:

Task Number of Persons Task-Hours Elapsed Hours

TOTAL FOR EACH AIRPLANE 1.25 1.25

(a) Refer to instructions in the GE Aviation service bulletins for manpower requirements.

Group 2:

Task Number of Persons Task-Hours Elapsed Hours

Open Access 1 0.25 0.25

FIGURE 2 (a) (a) (a)

Close Access 1 0.25 0.25

Test 1 0.75 0.75

TOTAL FOR EACH AIRPLANE 1.25 1.25

(a) Refer to instructions in the GE Aviation service bulletins for manpower requirements.

Group 3:

Task Number of Persons Task-Hours Elapsed Hours

Open Access 1 0.25 0.25

FIGURE 3 (a) (a) (a)

Close Access 1 0.25 0.25

Test 1 0.75 0.75

TOTAL FOR EACH AIRPLANE 1.25 1.25

(a) Refer to instructions in the GE Aviation service bulletins for manpower requirements.

Group 4:

Task Number of Persons Task-Hours Elapsed Hours

Open Access 1 0.25 0.25

FIGURE 4 (a) (a) (a)

Close Access 1 0.25 0.25

Test 1 0.75 0.75

TOTAL FOR EACH AIRPLANE 1.25 1.25

(a) Refer to instructions in the GE Aviation service bulletins for manpower requirements.

H. Weight and Balance Changes

None.

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BOEING SERVICE BULLETIN 777-28A0038
I. Electrical Load Data

Not changed.

J. References

1. Existing Data:

a. 777 Aircraft Maintenance Manual (AMM) 24-22-00, 28-22-05

b. Engineering Change Memo PRR 61998-1

c. Group 1:

GE Aviation Service Bulletin 5000ELM-28-443, 6000ELM-28-444, 4000ELM-28-445

NOTE: The supplier was told to send copies of the service bulletin to each operator.

d. Group 2:

GE Aviation Service Bulletin 5000ELM-28-446, 6000ELM-28-447, 4000ELM-28-448

NOTE: The supplier was told to send copies of the service bulletin to each operator.

e. Group 3:

GE Aviation Service Bulletin 5000ELM-28-449, 6000ELM-28-450, 4000ELM-28-451

NOTE: The supplier was told to send copies of the service bulletin to each operator.

f. Group 4:

GE Aviation Service Bulletin 5000ELM-28-463, 6000ELM-28-464, 4000ELM-28-465

NOTE: The supplier was told to send copies of the service bulletin to each operator.

2. Data supplied with this Service Bulletin:

None.

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

None.

K. Publications Affected

1. Publications:

Publication Chapter-Section

777 Aircraft Maintenance Manual 28-22

777 Fault Isolation Manual 28-22

777 Wiring Diagram Manual 28-22

777 Illustrated Parts Catalog 28-22

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BOEING SERVICE BULLETIN 777-28A0038
Publication Chapter-Section

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.

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BOEING SERVICE BULLETIN 777-28A0038
2. MATERIAL INFORMATION

A. Material - Price and Availability

None.

B. Industry Support Information

Boeing warranty remedies are not available for the configuration changes given in this service bulletin.

C. Parts Necessary For Each Airplane

1. Kits/Parts:

None.

2. Parts and Materials Supplied by the Operator:

None.

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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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. The instructions identified in Paragraph 3.B., Work Instructions and the Figure(s)

give the recommended sequence of steps. The sequence of steps to do this service

bulletin can be changed.

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

definition of the acronyms.

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

4. These work instructions refer to procedures included on other Boeing documents.

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

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

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

must be used.

B. WORK INSTRUCTIONS

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

2. Do the applicable step:

a. Group 1:

Change the P110, P210 and P320 panels in accordance with FIGURE 1.

b. Group 2:

Change the P110, P210 and P320 panels in accordance with FIGURE 2.

c. Group 3:

Change the P110, P210 and P320 panels in accordance with FIGURE 3.

d. Group 4:

Change the P110, P210 and P320 panels in accordance with FIGURE 4.

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

4. Do these tests:

a. Do a operational test of the main tank boost pumps. Refer to 777 AMM 28-22-05 as an

accepted procedure.

b. Do this test to check the GFI functionality of the left main tank forward boost pump.

(1) Make sure that the following circuit breakers are closed:

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BOEING SERVICE BULLETIN 777-28A0038
Circuit Breaker Circuit Breaker Name

Number

Location

Panel Grid

P310 B2 C28604 L FWD FUEL BOOST PUMP CTRL

P320 G9 C28301 L FWD FUEL BOOST PUMP GND SVC

(2) On P5 overhead panel,

(a) Make sure that the APU control switch is in the OFF position.

(b) Make sure that the amber PRESS light for the L FWD PUMP switch is on.

(c) Set the L FWD PUMP switch to the ON position.

(d) Make sure that the amber PRESS light for the L FWD PUMP switch is off.

(3) Press the BITE test button on the left main tank forward boost pump relay K28121 in the

P320 panel.

(4) Make sure that the RESET button on the K28121 relay has popped up, showing a white

line on the side of the button.

(5) On the P5 overhead panel, make sure that the amber PRESS light for the L FWD PUMP

is on.

(6) On the P5 overhead panel, set the L FWD PUMP switch to the OFF position.

(7) Push the RESET button on the K28121 relay and make sure that the RESET button stays

in.

(8) On the P5 overhead panel, do these steps:

(a) Set the L FWD PUMP switch to the ON position.

(b) Make sure that the amber PRESS light for the L FWD PUMP is off.

(c) Set the L FWD PUMP switch to the OFF position.

(d) Make sure that the amber PRESS light for the L FWD PUMP is on.

c. Do this test to check the GFI functionality of the left aft fuel boost pump.

(1) Make sure that the following circuit breaker is closed:

Circuit Breaker Circuit Breaker Name

Number

Location

Panel Grid

P110 E2 C28303 L AFT FUEL BOOST PUMP

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BOEING SERVICE BULLETIN 777-28A0038
Circuit Breaker Circuit Breaker Name

Number

Location

Panel Grid

P110 L26 C28607 L AFT FUEL BOOST PUMP CTRL

(2) On P5 overhead panel,

(a) Make sure that the amber PRESS light for the L AFT PUMP switch is on.

(b) Set the L AFT PUMP switch to the ON position.

(c) Make sure that the amber PRESS light for the L AFT PUMP switch is off.

(3) Press the BITE test button on the left main tank aft boost pump relay K28123 in the P110

panel.

(4) Make sure that the RESET button on the K28123 relay has popped up, showing a white

line on the side of the button.

(5) On the P5 overhead panel, make sure that the amber PRESS light for the L AFT PUMP

is on.

(6) On the P5 overhead panel, set the L AFT PUMP switch to the OFF position.

(7) Push the RESET button on the K28123 relay and make sure that the RESET button stays

in.

(8) On the P5 overhead panel, do these steps:

(a) Set the L AFT PUMP switch to the ON position.

(b) Make sure that the amber PRESS light for the L AFT PUMP is off.

(c) Set the L AFT PUMP switch to the OFF position.

(d) Make sure that the amber PRESS light for the L AFT PUMP is on.

d. Do this test to check the GFI functionality of the right main tank forward boost pump.

(1) Make sure that the following circuit breakers are closed:

Circuit Breaker Circuit Breaker Name

Number

Location

Panel Grid

P110 C18 C28302 R FWD FUEL BOOST PUMP L AC SECT 2

P110 L27 C28606 R FWD FUEL BOOST PUMP CTRL

(2) On P5 overhead panel,

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BOEING SERVICE BULLETIN 777-28A0038
(a) Make sure that the amber PRESS light for the R FWD PUMP switch is on.

(b) Set the R FWD PUMP switch to the ON position.

(c) Make sure that the amber PRESS light for the R FWD PUMP switch is off.

(3) Press the BITE test button on the right main tank forward boost pump relay K28241 in

the P110 panel.

(4) Make sure that the RESET button on the K28241 relay has popped up, showing a white

line on the side of the button.

(5) On the P5 overhead panel, make sure that the amber PRESS light for the R FWD PUMP

is on.

(6) On the P5 overhead panel, set the R FWD PUMP switch to the OFF position.

(7) Push the RESET button on the K28241 relay and make sure that the RESET button stays

in.

(8) On the P5 overhead panel, do these steps:

(a) Set the R FWD PUMP switch to the ON position.

(b) Make sure that the amber PRESS light for the R FWD PUMP is off.

(c) Set the R FWD PUMP switch to the OFF position.

(d) Make sure that the amber PRESS light for the R FWD PUMP is on.

e. Do this test to check the GFI functionality of the right main tank aft boost pump.

(1) Make sure that the following circuit breakers are closed:

Circuit Breaker Circuit Breaker Name

Number

Location

Panel Grid

P210 E27 C28300 R AFT FUEL BOOST PUMP

P210 K11 C28609 R AFT FUEL BOOST PUMP CTRL

(2) On P5 overhead panel,

(a) Make sure that the amber PRESS light for the R AFT PUMP switch is on.

(b) Set the R AFT PUMP switch to the ON position.

(c) Make sure that the amber PRESS light for the R AFT PUMP switch is off.

(3) Press the BITE test button on the right aft fuel boost pump relay K28242 in the P210

panel.

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BOEING SERVICE BULLETIN 777-28A0038
(4) Make sure that the RESET button on the K28242 relay has popped up, showing a white

line on the side of the button.

(5) On the P5 overhead panel, make sure that the amber PRESS light for the R AFT PUMP

is on.

(6) On the P5 overhead panel, set the R AFT PUMP switch to the OFF position.

(7) Push the RESET button on the K28242 relay and make sure that the RESET button stays

in.

(8) On the P5 overhead panel, do these steps:

(a) Set the R AFT PUMP switch to the ON position.

(b) Make sure that the amber PRESS light for the R AFT PUMP is off.

(c) Set the R AFT PUMP switch to the OFF position.

(d) Make sure that the amber PRESS light for the R AFT PUMP is on.

5. Put the airplane back to a serviceable condition.

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BOEING SERVICE BULLETIN 777-28A0038
This Figure applies only to: Group 1.

FIGURE 1: P110, P210 AND P320 PANEL MODIFICATION

(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 each airplane.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

In accordance with GE Aviation

SB 5000ELM-28-443.

Left Power Management P110 1

Panel

1 Change

In accordance with GE Aviation

SB 6000ELM-28-444.

Right Power Management P210 1

Panel

2 Change

In accordance with GE Aviation

SB 4000ELM-28-445.

Ground Service/Handling P320 1

Power Panel

3 Change

FIGURE 1: P110, P210 AND P320 PANEL MODIFICATION

(SHEET 2 OF 2)

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BOEING SERVICE BULLETIN 777-28A0038
This Figure applies only to: Group 2.

FIGURE 2: P110, P210 AND P320 PANEL MODIFICATION

(SHEET 1 OF 2)

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BOEING SERVICE BULLETIN 777-28A0038
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 each airplane.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

In accordance with GE Aviation

SB 5000ELM-28-446.

Left Power Management P110 1

Panel

1 Change

In accordance with GE Aviation

SB 6000ELM-28-447.

Right Power Management P210 1

Panel

2 Change

In accordance with GE Aviation

SB 4000ELM-28-448.

Ground Service/Handling P320 1

Power Panel

3 Change

FIGURE 2: P110, P210 AND P320 PANEL MODIFICATION

(SHEET 2 OF 2)

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BOEING SERVICE BULLETIN 777-28A0038
This Figure applies only to: Group 3.

FIGURE 3: P110, P210 AND P320 PANEL MODIFICATION

(SHEET 1 OF 2)

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BOEING SERVICE BULLETIN 777-28A0038
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 each airplane.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

In accordance with GE Aviation

SB 5000ELM-28-449.

Left Power Management P110 1

Panel

1 Change

In accordance with GE Aviation

SB 6000ELM-28-450.

Right Power Management P210 1

Panel

2 Change

In accordance with GE Aviation

SB 4000ELM-28-451.

Ground Service/Handling P320 1

Power Panel

3 Change

FIGURE 3: P110, P210 AND P320 PANEL MODIFICATION

(SHEET 2 OF 2)

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BOEING SERVICE BULLETIN 777-28A0038
This Figure applies only to: Group 4.

FIGURE 4: P110, P210 AND P320 PANEL MODIFICATION

(SHEET 1 OF 2)

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BOEING SERVICE BULLETIN 777-28A0038
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 each airplane.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

In accordance with GE Aviation

SB 5000ELM-28-463.

Left Power Management P110 1

Panel

1 Change

In accordance with GE Aviation

SB 6000ELM-28-464.

Right Power Management P210 1

Panel

2 Change

In accordance with GE Aviation

SB 4000ELM-28-465.

Ground Service/Handling P320 1

Power Panel

3 Change

FIGURE 4: P110, P210 AND P320 PANEL MODIFICATION

(SHEET 2 OF 2)

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BOEING SERVICE BULLETIN 777-28A0038