### 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. 9E991 ECCN: 

## BOEING PROPRIETARY, CONFIDENTIAL, AND/OR TRADE SECRET Copyright © 2008 The Boeing Company Unpublished Work - All Rights Reserved Boeing claims copyright in each page of this document only to the extent that the page contains copyrightable subject matter. Boeing also claims copyright in this document as a compilation and/or collective work. This document includes proprietary information owned by The Boeing Company and/or one or more third parties. Treatment of the document and the information it contains is governed by contract with Boeing. For more information, contact The Boeing Company, P.O. Box 3707, Seattle, Washington 98124. Boeing, the Boeing signature, the Boeing symbol, 707, 717, 727, 737, 747, 757, 767, 777, 787, Dreamliner, BBJ, DC-8, DC-9, DC-10, KC-10, KDC-10, MD-10, MD-11, MD-80, MD-88, MD-90, P-8A, Poseidon and the Boeing livery are all trademarks owned by The Boeing Company; and no trademark license is granted in connection with this document unless provided in writing by Boeing.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 13, 2008 777-28A0038 Revision 1: September 20, 2010 1 of 35 2.0BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 13, 2008 777-28A0038 Revision 1: September 20, 2010 2 of 35 **BOEING SERVICE BULLETIN 777-28A0038**

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

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 13, 2008 777-28A0038 Revision 1: September 20, 2010 3 of 35 **BOEING SERVICE BULLETIN 777-28A0038**BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 13, 2008 777-28A0038 Revision 1: September 20, 2010 4 of 35 **BOEING SERVICE BULLETIN 777-28A0038**

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### 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** June 13, 2008 Original Issue: September 20, 2010 Revision 1:

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 13, 2008 777-28A0038 Revision 1: September 20, 2010 5 of 35BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 13, 2008 777-28A0038 Revision 1: September 20, 2010 6 of 35 **BOEING SERVICE BULLETIN 777-28A0038**

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### 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.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 13, 2008 777-28A0038 Revision 1: September 20, 2010 7 of 35Boeing 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 Elapsed Hours**  **Total Task Hours Airplanes**  1.25 1.25 All 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.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 13, 2008 777-28A0038 Revision 1: September 20, 2010 8 of 35 **BOEING SERVICE BULLETIN 777-28A0038**BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 13, 2008 777-28A0038 Revision 1: September 20, 2010 9 of 35 **BOEING SERVICE BULLETIN 777-28A0038**BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 13, 2008 777-28A0038 Revision 1: September 20, 2010 10 of 35 **BOEING SERVICE BULLETIN 777-28A0038**

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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.
**DESCRIPTION CONFIGURATION**  **GROUP** 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
777-200 airplanes line numbers 1- 661 with ELMS 2

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

- 4

Airplane Models: 777-200, 777-200LR, 777-300, 777-300ER **Group Variable Number**  1 WA001 - WA017 1 WA076 - WA080 1 WA086 - WA093 1 WA101 - WA104 1 WA116 - WA119

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 13, 2008 777-28A0038 Revision 1: September 20, 2010 11 of 35**Group Variable Number**  1 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 3 WA282 - WA283 3 WA301 - WA304 1 WB001 - WB021 1 WB031 - WB046 1 WB051 - WB088 1 WB101 - WB106 1 WB121 - WB125 1 WB131 - WB139 3 WB140 - WB144 1 WB151 - WB155 1 WB161 - WB175 3 WB176 - WB177 1 WB181 - WB192 3 WB193 - WB194 1 WB201 - WB214 3 WB215 1 WB231 - WB247 1 WB271 - WB273 1 WB276 - WB286 1 WB291 - WB302 1 WB306 - WB307 1 WB311 - WB337 1 WB341 - WB342 1 WB366 - WB367

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 13, 2008 777-28A0038 Revision 1: September 20, 2010 12 of 35 **BOEING SERVICE BULLETIN 777-28A0038 Group**  **Variable Number** 3 WB368 1 WB371 - WB388 1 WB406 1 WB411 - WB413 1 WB416 - WB437 3 WB438 - WB439 1 WB446 - WB453 1 WB476 1 WB481 - WB484 2 WB501 - WB512 2 WB531 - WB537 2 WB551 - WB554 2 WB591 - WB597 2 WB601 - WB606 2 WB611 - WB622 2 WB631 - WB638 2 WB646 - WB649 1 WC051 - WC073 1 WC101 - WC104 1 WC111 - WC114 3 WC115 - WC119 3 WC221 - WC222 1 WC241 - WC243 1 WC281 - WC286 3 WC287 - WC290 1 WC301 - WC302 3 WC303 - WC308 1 WC361 - WC362 3 WC363 - WC364 1 WC371 - WC372 3 WC373 - WC374 3 WC381 - WC395 3 WC441

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 13, 2008 777-28A0038 Revision 1: September 20, 2010 13 of 35 **BOEING SERVICE BULLETIN 777-28A0038 Group**  **Variable Number** 3 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 4 WD001 - WD002 4 WD011 - WD013 4 WD031 - WD032 4 WD046 2 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. Spares Affected None. **B. Concurrent Requirements** The service bulletins listed below must be done before or at the same time as this service bulletin:

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 13, 2008 777-28A0038 Revision 1: September 20, 2010 14 of 35 **BOEING SERVICE BULLETIN 777-28A0038 Group 1:**  **Description Service Bulletin**  **Company** Replace the main tank boost pump relays with new Ground Fault Interrupt (GFI) relays in P110 panel. 5000ELM-28-443 original issue. GE Aviation

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: Description**  **Service Bulletin Company**  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: Description**  **Service Bulletin Company**  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: Description**  **Service Bulletin Company**  Replace the main tank boost pump relays with new GFI relays in P110 panel. 5000ELM-28-463 original issue. GE Aviation 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.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 13, 2008 777-28A0038 Revision 1: September 20, 2010 15 of 35 **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 Zone**  **Model** 117, 118 777-200 **Group 2:**
**Affected Maintenance Zones Zone**  **Model** 117, 118 777-300, 777-300ER

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 13, 2008 777-28A0038 Revision 1: September 20, 2010 16 of 35 **BOEING SERVICE BULLETIN 777-28A0038 Group 4:** 
**Affected Maintenance Zones Zone**  **Model** 117, 118 777-200LR **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: Elapsed Hours**  **Task-Hours Number of Persons**  **Task** 0.25 0.25 1 Open Access (a) (a) (a) FIGURE 1 0.25 0.25 1 Close Access 0.75 0.75 1 Test

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 13, 2008 777-28A0038 Revision 1: September 20, 2010 17 of 35 **BOEING SERVICE BULLETIN 777-28A0038 Group 1:**  **Elapsed Hours Task-Hours**  **Number of Persons Task**  1.25 1.25 TOTAL FOR EACH AIRPLANE (a) Refer to instructions in the GE Aviation service bulletins for manpower requirements. **Group 2: Elapsed Hours**  **Task-Hours Number of Persons**  **Task** 0.25 0.25 1 Open Access (a) (a) (a) FIGURE 2 0.25 0.25 1 Close Access 0.75 0.75 1 Test 1.25 1.25 TOTAL FOR EACH AIRPLANE (a) Refer to instructions in the GE Aviation service bulletins for manpower requirements. **Group 3: Elapsed Hours**  **Task-Hours Number of Persons**  **Task** 0.25 0.25 1 Open Access (a) (a) (a) FIGURE 3 0.25 0.25 1 Close Access 0.75 0.75 1 Test 1.25 1.25 TOTAL FOR EACH AIRPLANE (a) Refer to instructions in the GE Aviation service bulletins for manpower requirements. **Group 4: Elapsed Hours**  **Task-Hours Number of Persons**  **Task** 0.25 0.25 1 Open Access (a) (a) (a) FIGURE 4 0.25 0.25 1 Close Access 0.75 0.75 1 Test 1.25 1.25 TOTAL FOR EACH AIRPLANE (a) Refer to instructions in the GE Aviation service bulletins for manpower requirements. **H. Weight and Balance Changes** None.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 13, 2008 777-28A0038 Revision 1: September 20, 2010 18 of 35 **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: **Chapter-Section Publication**  28-22 777 Aircraft Maintenance Manual 28-22 777 Fault Isolation Manual 28-22 777 Wiring Diagram Manual 28-22 777 Illustrated Parts Catalog

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 13, 2008 777-28A0038 Revision 1: September 20, 2010 19 of 35 **BOEING SERVICE BULLETIN 777-28A0038 Chapter-Section**  **Publication** Section 9 777 Maintenance Planning Data 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.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 13, 2008 777-28A0038 Revision 1: September 20, 2010 20 of 35 **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.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 13, 2008 777-28A0038 Revision 1: September 20, 2010 21 of 35 **BOEING SERVICE BULLETIN 777-28A0038**BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 13, 2008 777-28A0038 Revision 1: September 20, 2010 22 of 35 **BOEING SERVICE BULLETIN 777-28A0038**

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:

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 13, 2008 777-28A0038 Revision 1: September 20, 2010 23 of 35 **BOEING SERVICE BULLETIN 777-28A0038 Circuit Breaker Name**  **Circuit Breaker Number**  **Location**
**Grid Panel**  L FWD FUEL BOOST PUMP CTRL C28604 B2 P310 L FWD FUEL BOOST PUMP GND SVC C28301 G9 P320(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 Name Circuit Breaker**  **Number Location** 
**Grid Panel**  L AFT FUEL BOOST PUMP C28303 E2 P110

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 13, 2008 777-28A0038 Revision 1: September 20, 2010 24 of 35 **BOEING SERVICE BULLETIN 777-28A0038 Circuit Breaker Name**  **Circuit Breaker Number**  **Location**
**Grid Panel**  L AFT FUEL BOOST PUMP CTRL C28607 L26 P110(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 Name Circuit Breaker**  **Number Location** 
**Grid Panel**  R FWD FUEL BOOST PUMP L AC SECT 2 C28302 C18 P110 R FWD FUEL BOOST PUMP CTRL C28606 L27 P110(2) On P5 overhead panel,

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 13, 2008 777-28A0038 Revision 1: September 20, 2010 25 of 35 **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 Name Circuit Breaker**  **Number Location** 
**Grid Panel**  R AFT FUEL BOOST PUMP C28300 E27 P210 R AFT FUEL BOOST PUMP CTRL C28609 K11 P210(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.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 13, 2008 777-28A0038 Revision 1: September 20, 2010 26 of 35 **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.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 13, 2008 777-28A0038 Revision 1: September 20, 2010 27 of 35 **BOEING SERVICE BULLETIN 777-28A0038 This Figure applies only to: Group 1.** 

**FIGURE 1: P110, P210 AND P320 PANEL MODIFICATION (SHEET 1 OF 2)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 13, 2008 777-28A0038 Revision 1 September 20, 2010 28 of 35 **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.
**MORE DATA QTY**  **IDENTIFICATION NAME**  **TASK STEP**  In accordance with GE Aviation SB 5000ELM-28-443. 1 P110 Left Power Management Panel Change 1
In accordance with GE Aviation SB 6000ELM-28-444. 1 P210 Right Power Management Panel Change 2
In accordance with GE Aviation SB 4000ELM-28-445. 1 P320 Ground Service/Handling Power Panel Change 3

**FIGURE 1: P110, P210 AND P320 PANEL MODIFICATION (SHEET 2 OF 2)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 13, 2008 777-28A0038 Revision 1 September 20, 2010 29 of 35 **BOEING SERVICE BULLETIN 777-28A0038 This Figure applies only to: Group 2.** 

**FIGURE 2: P110, P210 AND P320 PANEL MODIFICATION (SHEET 1 OF 2)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 13, 2008 777-28A0038 Revision 1 September 20, 2010 30 of 35 **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.
**MORE DATA QTY**  **IDENTIFICATION NAME**  **TASK STEP**  In accordance with GE Aviation SB 5000ELM-28-446. 1 P110 Left Power Management Panel Change 1
In accordance with GE Aviation SB 6000ELM-28-447. 1 P210 Right Power Management Panel Change 2
In accordance with GE Aviation SB 4000ELM-28-448. 1 P320 Ground Service/Handling Power Panel Change 3

**FIGURE 2: P110, P210 AND P320 PANEL MODIFICATION (SHEET 2 OF 2)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 13, 2008 777-28A0038 Revision 1 September 20, 2010 31 of 35 **BOEING SERVICE BULLETIN 777-28A0038 This Figure applies only to: Group 3.** 

**FIGURE 3: P110, P210 AND P320 PANEL MODIFICATION (SHEET 1 OF 2)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 13, 2008 777-28A0038 Revision 1 September 20, 2010 32 of 35 **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.
**MORE DATA QTY**  **IDENTIFICATION NAME**  **TASK STEP**  In accordance with GE Aviation SB 5000ELM-28-449. 1 P110 Left Power Management Panel Change 1
In accordance with GE Aviation SB 6000ELM-28-450. 1 P210 Right Power Management Panel Change 2
In accordance with GE Aviation SB 4000ELM-28-451. 1 P320 Ground Service/Handling Power Panel Change 3

**FIGURE 3: P110, P210 AND P320 PANEL MODIFICATION (SHEET 2 OF 2)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 13, 2008 777-28A0038 Revision 1 September 20, 2010 33 of 35 **BOEING SERVICE BULLETIN 777-28A0038 This Figure applies only to: Group 4.** 

**FIGURE 4: P110, P210 AND P320 PANEL MODIFICATION (SHEET 1 OF 2)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 13, 2008 777-28A0038 Revision 1 September 20, 2010 34 of 35 **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.
**MORE DATA QTY**  **IDENTIFICATION NAME**  **TASK STEP**  In accordance with GE Aviation SB 5000ELM-28-463. 1 P110 Left Power Management Panel Change 1
In accordance with GE Aviation SB 6000ELM-28-464. 1 P210 Right Power Management Panel Change 2
In accordance with GE Aviation SB 4000ELM-28-465. 1 P320 Ground Service/Handling Power Panel Change 3

**FIGURE 4: P110, P210 AND P320 PANEL MODIFICATION (SHEET 2 OF 2)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 13, 2008 777-28A0038 Revision 1 September 20, 2010 35 of 35 **BOEING SERVICE BULLETIN 777-28A0038**