### Commercial **Airplanes** 

# 777 Service Bulletin **SPECIAL ATTENTION Number: 777-28-0083**  Original Issue: September 08, 2014 Revision 1: March 06, 2015 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. 9E991 ECCN: 

## BOEING PROPRIETARY, CONFIDENTIAL AND/OR TRADE SECRET Copyright © 2014 Boeing. Unpublished Work. All Rights Reserved. Treatment of this document and its content is governed by contract with Boeing. Rights to use this document are licensed on a per aircraft basis and such rights may not be transferable. For more information, contact The Boeing Company. Boeing, the Boeing signature, the Boeing symbol, 707, 717, 727, 737, 747, 757, 767, 777, 787, Dreamliner, BBJ, DC-8, DC-9, DC-10, KC-10, KC-46, KDC-10, MD-10, MD-11, MD-80, MD-88, MD-90, P-8, Poseidon and Boeing liveries are all trademarks owned by The Boeing Company; and no trademark license is granted in connection with this document unless provided in writing by Boeing.

Original Issue: September 08, 2014 777-28-0083 Revision 1: March 06, 2015 1 of 72 5.0Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 08, 2014 777-28-0083 Revision 1: March 06, 2015 2 of 72 **BOEING SERVICE BULLETIN 777-28-0083**

BLANK PAGE**Table of Contents** Revision Transmittal Sheet............................................ 5 Summary...................................................... 9 1. PLANNING INFORMATION. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13 A. Effectivity. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13 1. Airplanes. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13 2. Spares Affected. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 16 B. Concurrent Requirements. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 16 C. Reason. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 16 D. Description. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17 E. Compliance. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 18 F. Approval. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19 G. Manpower. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19 H. Weight and Balance Changes. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21 I. Electrical Load Data. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 22 J. References. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 22 1. Existing Data:. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 22 2. Data Supplied with this Service Bulletin:. . . . . . . . . . . . . . . . . . . . . . . . . . . 23 3. Installation Drawings Used in the Preparation of this Service Bulletin:. . . . . . . . . . . 23 K. Publications Affected. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 23 L. Interchangeability and Intermixability of Parts. . . . . . . . . . . . . . . . . . . . . . . . . . . 24 M. Software Accomplishment Summary. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 24 2. MATERIAL INFORMATION. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25 A. Material - Price and Availability. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25 B. Industry Support Information. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 27 C. Parts Necessary for Each Airplane. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 27 1. Kits/Parts. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 27 2. Parts and Materials Supplied by the Operator. . . . . . . . . . . . . . . . . . . . . . . . 30 3. Parts Modified and Reidentified. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 31 4. Parts Removed and Not Replaced. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 31 D. Parts Necessary to Change Spares. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 32 E. Special Tooling - Price and Availability. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 32 F. Special Tooling Necessary to do this Service Bulletin. . . . . . . . . . . . . . . . . . . . . . . 32 3. ACCOMPLISHMENT INSTRUCTIONS. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 33 A. GENERAL INFORMATION. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 33 B. WORK INSTRUCTIONS. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 34 FIGURE 1: LEFT WING REAR SPAR IN THE LEFT MAIN LANDING GEAR BAY - PLACARD - REMOVAL [Group 1-2]. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 37 FIGURE 2: RIGHT WING REAR SPAR IN THE RIGHT MAIN LANDING GEAR BAY - PLACARD - REMOVAL [Group 1-2]. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 39 FIGURE 3: MAIN EQUIPMENT CENTER - WIRE BUNDLE W5732 - WIRE ROUTING [Group 1, 3] . 41 FIGURE 4: MAIN EQUIPMENT CENTER - WIRE BUNDLE W5732 - WIRING CHANGE [Group 1, 3] . 45 FIGURE 5: MAIN EQUIPMENT CENTER - WIRE BUNDLE W8327 - WIRE ROUTING [Group 2, 4] . 48 FIGURE 6: MAIN EQUIPMENT CENTER - WIRE BUNDLE W8327 - WIRING CHANGE [Group 2, 4] . 52 FIGURE 7: MAIN EQUIPMENT CENTER - WIRE BUNDLE W5829 - WIRE ROUTING [Group 1-4] . . 55 FIGURE 8: MAIN EQUIPMENT CENTER - WIRE BUNDLE W5829 - WIRING CHANGE [Group 2, 4] . 60

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 08, 2014 777-28-0083 Revision 1: March 06, 2015 3 of 72 **BOEING SERVICE BULLETIN 777-28-0083**FIGURE 9: MAIN EQUIPMENT CENTER - WIRE BUNDLE W5829 - WIRING CHANGE [Group 1, 3] . 62 APPENDIX A: ELECTRICAL LOAD MANAGEMENT SYSTEM 2 (ELMS2) SOFTWARE INSTALLATION . 64 APPENDIX B: FUNCTIONAL TEST. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 66 APPENDIX C: PART DEMAND INTENT. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 72

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 08, 2014 777-28-0083 Revision 1: March 06, 2015 4 of 72 **BOEING SERVICE BULLETIN 777-28-0083**

### Commercial **Airplanes** 

# 777 Service Bulletin **SPECIAL ATTENTION Revision Transmittal Sheet**  **Number: 777-28-0083** Original Issue: September 08, 2014 Revision 1: March 06, 2015 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 This revision includes all pages of the service bulletin. **COMPLIANCE INFORMATION RELATED TO THIS REVISION** Federal Aviation Administration (FAA) Notice of Proposed Rule Making NPRM 2014-NM-192-AD, is related to this service bulletin. Effects of this Revision on airplanes on which the original issue was previously done: – None. **REASON FOR REVISION** This revision is sent to provide clarifications, and to correct wire length and part errors in the wire-kits. In the wire-kits, some of the wires were too short and some wrong parts or part quantities were included. The wire-kit numbers are changed for the corrected wire-kits, and thus some parts in the wire-kits that were correct now just have their part numbers updated. These sections are changed: 1. Summary Background: – Clarified. 2. Summary Action: – Clarified. 3. Summary Compliance: – Updated. 4. Summary Illustration: – Clarified. 5. Paragraph 1.A., Effectivity:

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 08, 2014 777-28-0083 Revision 1: March 06, 2015 5 of 72– Group/Configuration table: Clarified (a revision bar or vertical line is not applied). 6. Paragraph 1.B., Concurrent Requirements: – Clarified. 7. Paragraph 1.C., Reason: – Clarified. 8. Paragraph 1.D., Description: – Clarified. 9. Paragraph 1.E., Compliance: – Updated. 10. Paragraph 1.G., Manpower: – The statement regarding the General Electric service bulletins is added; – The estimates are updated. 11. Paragraph 1.J., References: – Updated and clarified. 12. Paragraph 1.K., Publications Affected: – Corrected: A row is deleted and thus a revision bar or vertical line is not applied. 13. Paragraph 1.M., Software Accomplishment Summary: – Clarified. 14. Paragraph 2.A., Material - Price and Availability: – Updated and clarified. 15. Paragraph 2.C.1., Kits/Parts: – Corrected, updated and clarified. 16. Paragraph 2.C.2., Parts and Materials Supplied by the Operator: – Removed a part and thus a revision bar or vertical line is not applied. 17. Paragraph 3.A., General Information: – Note 17: Clarified. 18. Paragraph 3.B., Work Instructions:

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 08, 2014 777-28-0083 Revision 1: March 06, 2015 6 of 72 **BOEING SERVICE BULLETIN 777-28-0083**– Step 2: Clarified; – Step 4: Clarified. 19. FIGURE 1: – Step 1: Clarified; – Footnote (b): Clarified. 20. FIGURE 2: – Step 1: Clarified; – Footnote (b): Clarified. 21. FIGURE 3: – Note added; – Step 1: Changed part number. 22. FIGURE 4: – Changed wire-kit number; – Flagnotes 4 and 5: Changed part number. 23. FIGURE 5: – Note added; – Step 1: Changed part number. 24. FIGURE 6: – Changed wire-kit number; – Flagnotes 4 and 5: Changed part number. 25. FIGURE 7: – Note added; – Step 1: Changed part number. 26. FIGURE 8: – Corrected illustration; – Changed wire-kit number; – Flagnote 2: Corrected quantity; – Flagnote 4: Changed part number. 27. FIGURE 9: – Corrected illustration; – Changed wire-kit number; – Flagnote 2: Corrected quantity; – Flagnote 4: Changed part number. 28. APPENDIX A:

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 08, 2014 777-28-0083 Revision 1: March 06, 2015 7 of 72 **BOEING SERVICE BULLETIN 777-28-0083**– Clarified. 29. APPENDIX B: – Step 5: Substeps added; A substep is removed. Vertical lines are put on the left edge of each page, except in Paragraph 1.A., Effectivity and format changes, to show the location of all content changes. Pages with no vertical lines have no changes. **REVISION HISTORY** September 08, 2014 Original Issue: March 06, 2015 Revision 1:

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 08, 2014 777-28-0083 Revision 1: March 06, 2015 8 of 72 **BOEING SERVICE BULLETIN 777-28-0083**

### Commercial **Airplanes** 

# 777 Service Bulletin **SPECIAL ATTENTION Summary**  **Number: 777-28-0083** Original Issue: September 08, 2014 Revision 1: March 06, 2015 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 potential for extended dry-running of the jettison pumps as they provide motive flow to the fuel scavenge jet pumps. The potential for 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 existing design continues to control the jettison pump(s) after the fuel level is lower than 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 potential for 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).

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 08, 2014 777-28-0083 Revision 1: March 06, 2015 9 of 72**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. This table is provided to operators for planning purposes only. Refer to the applicable sections for more information.
**Reference Affected**  **Planning Data** Paragraph 1.A.2., Spares Affected No Spares Affected Paragraph 1.E., Compliance and Paragraph 1.F., Approval Yes AD Related Paragraph 1.H., Weight and Balance Changes Yes Weight and Balance Change Paragraph 1.I., Electrical Load Data No Electrical Load Changed Paragraph 1.K., Publications Affected Yes Publications Affected Paragraph 1.K., Publications Affected No Airplane Flight Operations Affected (Flight CrewOperations Manual and/or FAA Approved Airplane Flight Manual) Paragraph 2.C.1., Kits/Parts Yes Kits/Parts Required Paragraph 2.C.2., Parts and Materials Supplied by the Operator Yes Operator Supplied Parts/Material Paragraph 2.F., Special Tooling Necessary to do this Service Bulletin No Special Tooling Required
**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 (can be done before, at the same time, or after the work in the main equipment center). **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. Do some wiring changes in the P110 and P210 panels. Install new ELMS2 software. Do a functional test.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 08, 2014 777-28-0083 Revision 1: March 06, 2015 10 of 72 **BOEING SERVICE BULLETIN 777-28-0083 EFFECTIVITY**  777-200/-200LR/-300ER/F Airplane(s). Refer to Paragraph 1.A.1., Airplanes, for the list of affected airplanes. **COMPLIANCE** The Federal Aviation Administration (FAA) will possibly release an Airworthiness Directive related to this service bulletin. The Airworthiness Directive will make the compliance tasks and times given in this service bulletin mandatory. Federal Aviation Administration (FAA) Notice of Proposed Rule Making NPRM 2014-NM-192-AD, is related to this service bulletin. **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.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 08, 2014 777-28-0083 Revision 1: March 06, 2015 11 of 72 **BOEING SERVICE BULLETIN 777-28-0083**Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 08, 2014 777-28-0083 Revision 1: March 06, 2015 12 of 72 **BOEING SERVICE BULLETIN 777-28-0083**

### Commercial **Airplanes** 

# 777 Service Bulletin **SPECIAL ATTENTION Number: 777-28-0083**  Original Issue: September 08, 2014 Revision 1: March 06, 2015 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.
**DESCRIPTION CONFIGURATION**  **GROUP** 777-200 (with extended range)/-200LR/-300ER ELMS2 Airplane line numbers after 1098 and before 1180. - 1
777F ELMS2 Airplane line numbers after 1098 and before 1180.

- 2 777-200LR/-300ER ELMS2 Airplane line numbers after 1179 and before 1206. - 3
777F ELMS2 Airplane line numbers after 1179 and before 1206.

- 4 777-300ER/F ELMS2 Airplane line numbers after 1205.

- 5

Airplane Models: 777-200, 777-200LR, 777-300ER, 777F

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 08, 2014 777-28-0083 Revision 1: March 06, 2015 13 of 72**Group Variable Number**  1 WC587 1 WC594 - WC595 1 WD106 3 WD121 - WD122 1 WD820 - WD824 3 WD825 1 WD893 - WD895 5 WD896 - WD898 1 WD918 3 WD930 1 WD944 - WD945 1 WD957 1 WD994 5 WE056 - WE057 1 WE073 - WE075 3 WE076 - WE077 5 WE078 1 WE094 - WE095 5 WE138 - WE140 1 WE141 - WE144 3 WE145 5 WE146 1 WE164 - WE167 3 WE168 - WE169 5 WE170 3 WE178 1 WE207 - WE211 3 WE212 - WE213 5 WE214 - WE215 1 WE218 3 WE219 1 WE243 - WE244

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 08, 2014 777-28-0083 Revision 1: March 06, 2015 14 of 72 **BOEING SERVICE BULLETIN 777-28-0083 Group**  **Variable Number** 1 WE265 - WE266 5 WE267 1 WE275 - WE278 1 WE291 - WE292 3 WE293 1 WE307 - WE311 3 WE312 - WE313 5 WE314 - WE315 1 WE335 - WE336 3 WE337 - WE340 1 WE352 - WE356 1 WE376 3 WE377 5 WE381 1 WE386 - WE387 1 WE396 5 WE397 - WE399 1 WE416 - WE420 3 WE426 3 WE436 5 WE437 1 WE441 5 WE442 - WE443 5 WE451 5 WE501 - WE502 5 WE556 - WE558 2 WF022 - WF023 2 WF039 - WF040 5 WF041 2 WF065 - WF066 2 WF115 4 WF116 5 WF117

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 08, 2014 777-28-0083 Revision 1: March 06, 2015 15 of 72 **BOEING SERVICE BULLETIN 777-28-0083 Group**  **Variable Number** 2 WF133 2 WF139 2 WF156 - WF158 5 WF159 2 WF166 4 WF167 - WF168 5 WF169 - WF170 5 WF176 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: Description**  **Service Bulletin Company**  Provides instructions to revise the ELMSP110 panel 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 ELMSP210 panel with the addition of fuel scavenge wiring General Electric Co SB 6000ELM-28-076, Revision 1, dated August 5, 2014 General Electric

**Group 5:** None. **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 potential for extended dry-running of the jettison pumps as they provide motive flow to the fuel scavenge jet pumps. The potential for 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 existing design continues to control the jettison pump(s) after the fuel level is lower than 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.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 08, 2014 777-28-0083 Revision 1: March 06, 2015 16 of 72 **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 potential for 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. Revision 1 is sent to provide clarifications, and to correct wire length and part errors in the wire-kits. In the wire-kits, some of the wires were too short and some wrong parts or part quantities were included. The wire-kit numbers are changed for the corrected wire-kits, and thus some parts in the wire-kits that were correct now just have their part numbers updated. **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 (can be done before, at the same time, or after the work in the main equipment center). **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. Do some wiring changes in the P110 and P210 panels. Install new ELMS2 software. Do a functional test. Effects of Revision 1 on airplanes on which the original issue was previously done:

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 08, 2014 777-28-0083 Revision 1: March 06, 2015 17 of 72 **BOEING SERVICE BULLETIN 777-28-0083**– None. The work in this service bulletin is done in the maintenance zone(s) given below. **Group 1:**
**Affected Maintenance Zones Zone**  **Model** 117, 118, 212, 551, 651 777-200, 777-200LR, 777- 300ER **Group 2:**
**Affected Maintenance Zones Zone**  **Model** 117, 118, 212, 551, 651 777F **Group 3:**
**Affected Maintenance Zones Zone**  **Model** 117, 118, 212 777-200LR, 777-300ER **Group 4:**
**Affected Maintenance Zones Zone**  **Model** 117, 118, 212 777F **Group 5:**
**Affected Maintenance Zones Zone**  **Model** 212 777-300ER, 777F **E. Compliance** The Federal Aviation Administration (FAA) will possibly release an Airworthiness Directive related to this service bulletin. The Airworthiness Directive will make the compliance tasks and times given in this service bulletin mandatory. Federal Aviation Administration (FAA) Notice of Proposed Rule Making NPRM 2014-NM-192-AD, is related to this service bulletin.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 08, 2014 777-28-0083 Revision 1: March 06, 2015 18 of 72 **BOEING SERVICE BULLETIN 777-28-0083 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. **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 times to make the change to the P110 panel in accordance with General Electric Co SB 5000ELM-28-075 service bulletin, and to the P210 panel in accordance with General Electric Co SB 6000ELM-28-076 service bulletin, are not included. 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: Elapsed Hours**  **Task Hours Number of Persons**  **Task** 1.00 1.00 1 Open Access 0.15 0.15 1 FIGURE 1 0.15 0.15 1 FIGURE 2 6.25 12.50 2 FIGURE 3 and FIG- URE 4

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 08, 2014 777-28-0083 Revision 1: March 06, 2015 19 of 72 **BOEING SERVICE BULLETIN 777-28-0083 Group 1:**  **Elapsed Hours Task Hours**  **Number of Persons Task**  8.45 16.90 2 FIGURE 7 and FIG- URE 9 3.00 3.00 1 Install Software 2.50 5.00 2 Test 1.00 1.00 1 Close Access 22.50 39.70 TOTAL FOR EACH AIRPLANE **Group 2: Elapsed Hours**  **Task Hours Number of Persons**  **Task** 1.00 1.00 1 Open Access 0.15 0.15 1 FIGURE 1 0.15 0.15 1 FIGURE 2 6.25 12.50 2 FIGURE 5 and FIG- URE 6 8.45 16.90 2 FIGURE 7 and FIG- URE 8 3.00 3.00 1 Install Software 2.50 5.00 2 Test 1.00 1.00 1 Close Access 22.50 39.70 TOTAL FOR EACH AIRPLANE **Group 3: Elapsed Hours**  **Task Hours Number of Persons**  **Task** 1.00 1.00 1 Open Access 6.25 12.50 2 FIGURE 3 and FIG- URE 4 8.45 16.90 2 FIGURE 7 and FIG- URE 9 3.00 3.00 1 Install Software 2.50 5.00 2 Test 1.00 1.00 1 Close Access 22.20 39.40 TOTAL FOR EACH AIRPLANE

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 08, 2014 777-28-0083 Revision 1: March 06, 2015 20 of 72 **BOEING SERVICE BULLETIN 777-28-0083 Group 4:**  **Elapsed Hours Task Hours**  **Number of Persons Task**  1.00 1.00 1 Open Access 6.25 12.50 2 FIGURE 5 and FIG- URE 6 8.45 16.90 2 FIGURE 7 and FIG- URE 8 3.00 3.00 1 Install Software 2.50 5.00 2 Test 1.00 1.00 1 Close Access 22.20 39.40 TOTAL FOR EACH AIRPLANE **Group 5: Elapsed Hours**  **Task Hours Number of Persons**  **Task** 3.00 3.00 1 Install Software 2.50 5.00 2 Test 5.50 8.00 TOTAL FOR EACH AIRPLANE **H. Weight and Balance Changes Group 1:**  **Change in Moment (Pound-Inches)**  **Change in Weight (Pounds)**  **Airplane** +328.7 +0.9 777-200 (with ex- tended range)/- 200LR +137.0 +0.9 777-300ER **Group 2: Change in Moment**  **(Pound-Inches) Change in Weight**  **(Pounds) Airplane**  +171.2 +0.5 777F **Group 3: Change in Moment**  **(Pound-Inches) Change in Weight**  **(Pounds) Airplane**  +174.4 +0.5 777-200LR

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 08, 2014 777-28-0083 Revision 1: March 06, 2015 21 of 72 **BOEING SERVICE BULLETIN 777-28-0083 Group 3:**  **Change in Moment (Pound-Inches)**  **Change in Weight (Pounds)**  **Airplane** +72.7 +0.5 777-300ER **Group 4: Change in Moment**  **(Pound-Inches) Change in Weight**  **(Pounds) Airplane**  +323.5 +0.9 777F **Group 5:** None. **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. Federal Aviation Administration (FAA) Notice of Proposed Rule Making (NPRM) 2014-NM-192-AD e. Service Bulletin Index D624W001 f. Standard Overhaul Practices Manual (SOPM) 20-30-03, 20-41-01, 20-41-02, 20-43-03, 20-50-01 g. 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 h. 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 i. 777 Fleet Team Digest (FTD) 28-07002, 28-09001, 28-09004 j. 777 Wiring Diagram Manual (WDM) 28-31-11, 28-31-21 k. 777-200 Structural Repair Manual (SRM) 51-20-01 l. 777-300 Structural Repair Manual (SRM) 51-20-01

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 08, 2014 777-28-0083 Revision 1: March 06, 2015 22 of 72 **BOEING SERVICE BULLETIN 777-28-0083**m. 777F Structural Repair Manual (SRM) 51-20-01 n. General Electric Co Service Bulletin 5000ELM-28-075, 6000ELM-28-076 **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:
**Title Drawing Number**  MARKING INSTALLATION - FUEL SYSTEMS 340W0401 WIRE BUNDLE INSTALLATION P105 ELECTRONICS SHELF 288W9105 WIRE BUNDLE INSTL - BULKHEAD (STA 332.5) 288W4106 WIRE BUNDLE INSTL - FWD W/W & AFT W/W BLKHD (PRESS) (STA 180.5 - 332.5) 288W4113 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: **Chapter-Section**

**Publication** 28-31, Equipment List 777 Wiring Diagram Manual 28-31 777 Fault Isolation Manual 11-24 777 Illustrated Parts Catalog 28-31 777 System Schematic Manual 2. Damage Tolerance Based Structural Inspections:

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 08, 2014 777-28-0083 Revision 1: March 06, 2015 23 of 72 **BOEING SERVICE BULLETIN 777-28-0083**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: 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, to ensure the Jettison BITE test is completed prior to scavenge. d. Jettison pump pressure switch failed High failure mode was elevated to an EICAS level fault. e. Added a computed airspeed input to prevent the fuel scavenge system from commanding the jettison pumps ON during maintenance actions. f. Logic change to inhibit scavenge due to either jettison nozzle valve open, instead of by jettison arm switch. g. 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.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 08, 2014 777-28-0083 Revision 1: March 06, 2015 24 of 72 **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 **Group 1, 3: 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 Revision 1** **date of this Ser vice Bulletin (US**  **Dollars) ROLT as of the**  **Revision 1 date of this Service Bul** 

**letin (Calendar Days)**  **QTY Date**  **Name Kit Number** 

656.00 149 5 Apr 29, 2015 WIRE KIT SUBASSEM- BLY 280W5134-126 (a) 5 Jul 29, 2015 5 Oct 28, 2015 5 Jan 08, 2016 5 Feb 24, 2016 5 Apr 27, 2016 5 Jun 29, 2016 5 Jul 27, 2016 5 Sep 29, 2016 5 Nov 28, 2016 5 Feb 01, 2017 5 Mar 29, 2017 5 May 24, 2017 3 Jul 21, 2017 (a) Replaces wire kit 280W5134-106. If you have previously ordered a -106 wire kit, then order a -126 wire kit.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 08, 2014 777-28-0083 Revision 1: March 06, 2015 25 of 72 **BOEING SERVICE BULLETIN 777-28-0083 Group 1-4:**  **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 Revision 1** **date of this Ser vice Bulletin (US**  **Dollars) ROLT as of the**  **Revision 1 date of this Service Bul** 

**letin (Calendar Days)**  **QTY Date**  **Name Kit Number** 

735.00 149 5 Apr 01, 2015 WIRE KIT SUBASSEM- BLY 280W5134-127 (a) 5 Jul 01, 2015 5 Sep 30, 2015 3 Nov 25, 2015 5 Jan 27, 2016 5 Mar 23, 2016 5 May 25, 2016 5 Aug 31, 2016 5 Oct 27, 2016 5 Jan 04, 2017 5 Mar 01, 2017 5 Apr 26, 2017 5 Jun 22, 2017 5 Aug 18, 2017 5 Oct 16, 2017 5 Dec 13, 2017 2 Feb 16, 2018 (a) Replaces wire kit 280W5134-107. If you have previously ordered a -107 wire kit, then order a -127 wire kit.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 08, 2014 777-28-0083 Revision 1: March 06, 2015 26 of 72 **BOEING SERVICE BULLETIN 777-28-0083 Group 2, 4:**  **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 Revision 1** **date of this Ser vice Bulletin (US**  **Dollars) ROLT as of the**  **Revision 1 date of this Service Bul** 

**letin (Calendar Days)**  **QTY Date**  **Name Kit Number** 

726.00 149 5 May 28, 2015 WIRE KIT SUBASSEM- BLY 280W5134-128 (a) 5 Aug 26, 2015 2 Nov 25, 2015 (a) Replaces wire kit 280W5134-108. If you have previously ordered a -108 wire kit, then order a -128 wire kit.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. In addition, 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. **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:**Wire kits and the items shown in Paragraph 2.C.2., Parts and Materials Supplied by the Operator, are necessary for each airplane. The parts in the kits are used in production. Some parts in the wire kits are more than necessary or are not used (they are used for when the wire kits are ordered for service bulletin 777-28-0078).

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 08, 2014 777-28-0083 Revision 1: March 06, 2015 27 of 72 **BOEING SERVICE BULLETIN 777-28-0083 Group 1, 3:** 
**Kit 280W5134 Notes**  **Name QTY**  **New Part Number -126** Wire Kit Subassembly - 280W5134-126
Wire List 1 280W5134-126W ID - CONNECTOR 1 280W5134-12201 ID - CONNECTOR 1 280W5134-12202 ID SLEEVE - SP684 1 280W5134-12203
ID SLEEVE - SP683 1 280W5134-12303 CONTACT, SOCKET 1 BACC47CP1S CONTACT, SOCKET 10 BACC47DJ1
RELAY SOCKET 1 BACS16W5A RELAY SOCKET 1 BACS16X1A TERMINAL, LUG 1 BACT12AC3 CONTACT, SOCKET, SIZE 20 1 CTA-0165
SPLICE 7 D-436-37 SPLICE 1 D-436-43 **Group 1-4:**
**Kit 280W5134 Notes**  **Name QTY**  **New Part Number -127** Wire Kit Subassembly - 280W5134-127
Wire List 1 280W5134-127W ID - CONNECTOR 1 280W5134-12301 ID - CONNECTOR 1 280W5134-12302 ID SLEEVE - SP683 1 280W5134-12303

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 08, 2014 777-28-0083 Revision 1: March 06, 2015 28 of 72 **BOEING SERVICE BULLETIN 777-28-0083 Group 1-4:** 
**Kit 280W5134 Notes**  **Name QTY**  **New Part Number -127** ID SLEEVE - SP689 1 280W5134-12304 CONTACT, PIN 1 BACC47CN1S CONTACT, SOCKET 1 BACC47CP1S CONTACT, SOCKET 10 BACC47DJ1
RELAY SOCKET 1 BACS16W5A RELAY SOCKET 1 BACS16X1A TERMINAL, LUG 1 BACT12AC3 SLEEVE, HEAT SHRINK 1 BACT63D1 CONTACT, SOCKET, SIZE 20 1 CTA-0165
SPLICE 5 D-436-37 SPLICE 1 D-436-43 **Group 2, 4:**
**Kit 280W5134 Notes**  **Name QTY**  **New Part Number -128** Wire Kit Subassembly - 280W5134-128
Wire List 1 280W5134-128W ID - CONNECTOR 1 280W5134-12201 ID - CONNECTOR 1 280W5134-12202 ID SLEEVE - SP684 1 280W5134-12203
ID SLEEVE - SP683 1 280W5134-12303 CONTACT, SOCKET 1 BACC47CP1S

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 08, 2014 777-28-0083 Revision 1: March 06, 2015 29 of 72 **BOEING SERVICE BULLETIN 777-28-0083 Group 2, 4:** 
**Kit 280W5134 Notes**  **Name QTY**  **New Part Number -128** CONTACT, SOCKET 10 BACC47DJ1
RELAY SOCKET 1 BACS16W5A RELAY SOCKET 1 BACS16X1A TERMINAL, LUG 1 BACT12AC3 CONTACT, SOCKET, SIZE 20 1 CTA-0165
SPLICE 6 D-436-37 SPLICE 1 D-436-43 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:**
**Notes Name**  **QTY Part Number /**  **Specification** Refer to SOPM 20-43-03 for materials. (a) Chemical Conversion Coating 0.5 PintsChemical Conversion Coating Type 2 Class A (b) Primer 0.5 Pints BMS 10-11 Type 1 (b) Gloss Enamel 0.5 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.
**Notes Software Name**  **Software Part Number Media Set Name**  **Media Set Part Number** (b) (c) ELMS OPS and OPC (a) 24 ELMS OPS/OPC (a) (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.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 08, 2014 777-28-0083 Revision 1: March 06, 2015 30 of 72 **BOEING SERVICE BULLETIN 777-28-0083 Notes**  **Software Name Software Part Number**  **Media Set Name Media Set Part Number**  (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:**
**Notes Name**  **QTY Part Number /**  **Specification** (a) (d) (f) STRAP - YELLOW

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

- BACS38K( )B (a) (b) (e) (f) LACING TAPE - YELLOW

- BMS 13-54, TYPEIII, CLASS 1, FINISH C, GRADE D (a) (c) (e) (f) LACING TAPE - BROWN

- BMS 13-54, TYPEIII, CLASS 1, FINISH C, GRADE D (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:**
**Notes QTY**  **Name Existing Part**  **Number**

- 1 PLACARD BAC27WFS14

- 1 PLACARD BAC27WFS15 **Group 3-5:** None.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 08, 2014 777-28-0083 Revision 1: March 06, 2015 31 of 72 **BOEING SERVICE BULLETIN 777-28-0083 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.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 08, 2014 777-28-0083 Revision 1: March 06, 2015 32 of 72 **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.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 08, 2014 777-28-0083 Revision 1: March 06, 2015 33 of 72 **BOEING SERVICE BULLETIN 777-28-0083**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. If a step in the Work Instructions identified as RC has substeps, then all of the substeps in the RC step must also be done. 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 and that are not a substep of an RC step. **B. WORK INSTRUCTIONS** 1. Open Access:

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 08, 2014 777-28-0083 Revision 1: March 06, 2015 34 of 72 **BOEING SERVICE BULLETIN 777-28-0083**a. **Group 1-2:** Deactivate the trailing edge flaps. Refer to 777 AMM 27-51-00 as an accepted procedure. 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 (this step can be done before, at the same time, or after Step 3): – 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.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 08, 2014 777-28-0083 Revision 1: March 06, 2015 35 of 72 **BOEING SERVICE BULLETIN 777-28-0083**b. RC - Install new Electrical Load Management System 2 (ELMS2) software in accordance with APPENDIX A. c. 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.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 08, 2014 777-28-0083 Revision 1: March 06, 2015 36 of 72 **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)**  Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 08, 2014 777-28-0083 Revision 1 March 06, 2015 37 of 72 **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.
**More Data Qty**  **Identification Name**  **Task Step**  The location is onthe rear spar between rib 2 and rib 6. 1 BAC27WFS14 PLACARD Remove 1

on the airplane where the placard was removed. (a) - - SURFACE Clean 2

on the airplane where the placardwas removed, to restore any removed finish. (b) - - FINISH Apply 3

(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 (finish code F-14.9813) as an accepted procedure.

**FIGURE 1: LEFT WING REAR SPAR IN THE LEFT MAIN LANDING GEAR BAY - PLACARD - REMOVAL (SHEET 2 OF 2)**  Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 08, 2014 777-28-0083 Revision 1 March 06, 2015 38 of 72 **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)**  Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 08, 2014 777-28-0083 Revision 1 March 06, 2015 39 of 72 **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.
**More Data Qty**  **Identification Name**  **Task Step**  The location is onthe rear spar between rib 2 and rib 6. 1 BAC27WFS15 PLACARD Remove 1

on the airplane where the placard was removed. (a) - - SURFACE Clean 2

on the airplane where the placardwas removed, to restore any removed finish. (b) - - FINISH Apply 3

(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 (finish code F-14.9813) as an accepted procedure.

**FIGURE 2: RIGHT WING REAR SPAR IN THE RIGHT MAIN LANDING GEAR BAY - PLACARD - REMOVAL (SHEET 2 OF 2)**  Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 08, 2014 777-28-0083 Revision 1 March 06, 2015 40 of 72 **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 4)**  Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 08, 2014 777-28-0083 Revision 1 March 06, 2015 41 of 72 **BOEING SERVICE BULLETIN 777-28-0083 FIGURE 3: MAIN EQUIPMENT CENTER - WIRE BUNDLE W5732 - WIRE ROUTING**  **(SHEET 2 OF 4)** Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 08, 2014 777-28-0083 Revision 1 March 06, 2015 42 of 72 **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. **NOTE:**Get the parts given below from kit 280W5134-126.

**FIGURE 3: MAIN EQUIPMENT CENTER - WIRE BUNDLE W5732 - WIRE ROUTING (SHEET 3 OF 4)**  Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 08, 2014 777-28-0083 Revision 1 March 06, 2015 43 of 72 **BOEING SERVICE BULLETIN 777-28-0083 More Data**  **Qty Identification**  **Name Task**  **Step** Route with existing W5732 wire bundle. Refer to SWPM 20- 10-11 and SWPM20-10-12 as accepted procedures. 1 280W5134-126W Wire List Install (New) 1

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

**FIGURE 3: MAIN EQUIPMENT CENTER - WIRE BUNDLE W5732 - WIRE ROUTING (SHEET 4 OF 4)**  Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 08, 2014 777-28-0083 Revision 1 March 06, 2015 44 of 72 **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)**  Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 08, 2014 777-28-0083 Revision 1 March 06, 2015 45 of 72 **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 280W5134-126.

**More Data Qty**  **Identification Name**  **Flag Note**  Refer to SWPM 20-61-11 as an accepted procedure. 1 BACC47CP1S CONTACT, SOCKET 1
Refer to SWPM 20-81-12 as an accepted procedure. 1 BACC47DJ1 CONTACT, SOCKET 2
Refer to SWPM 20-30-12 as an accepted procedure. (a) (b) (c) (d) 4 D-436-37 SPLICE 3
Refer to SWPM 20-10-11 as an accepted procedure. 1 280W5134-12203 ID SLEEVE - SP684 4
Refer to SWPM 20-10-11 as an accepted procedure. 1 280W5134-12303 ID SLEEVE - SP683 5 Splice SP689 is replaced in another figure. - - SPLICE 6

**FIGURE 4: MAIN EQUIPMENT CENTER - WIRE BUNDLE W5732 - WIRING CHANGE (SHEET 2 OF 3)**  Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 08, 2014 777-28-0083 Revision 1 March 06, 2015 46 of 72 **BOEING SERVICE BULLETIN 777-28-0083 More Data**  **Qty Identification**  **Name 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)**  Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 08, 2014 777-28-0083 Revision 1 March 06, 2015 47 of 72 **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 4)**  Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 08, 2014 777-28-0083 Revision 1 March 06, 2015 48 of 72 **BOEING SERVICE BULLETIN 777-28-0083 FIGURE 5: MAIN EQUIPMENT CENTER - WIRE BUNDLE W8327 - WIRE ROUTING**  **(SHEET 2 OF 4)** Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 08, 2014 777-28-0083 Revision 1 March 06, 2015 49 of 72 **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. **NOTE:**Get the parts given below from kit 280W5134-128.

**FIGURE 5: MAIN EQUIPMENT CENTER - WIRE BUNDLE W8327 - WIRE ROUTING (SHEET 3 OF 4)**  Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 08, 2014 777-28-0083 Revision 1 March 06, 2015 50 of 72 **BOEING SERVICE BULLETIN 777-28-0083 More Data**  **Qty Identification**  **Name Task**  **Step** Route with existing W8327 wire bundle. Refer to SWPM 20- 10-11 and SWPM20-10-12 as accepted procedures. 1 280W5134-128W Wire List Install (New) 1

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

**FIGURE 5: MAIN EQUIPMENT CENTER - WIRE BUNDLE W8327 - WIRE ROUTING (SHEET 4 OF 4)**  Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 08, 2014 777-28-0083 Revision 1 March 06, 2015 51 of 72 **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)**  Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 08, 2014 777-28-0083 Revision 1 March 06, 2015 52 of 72 **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 280W5134-128.

**More Data Qty**  **Identification Name**  **Flag Note**  Refer to SWPM 20-61-11 as an accepted procedure. 1 BACC47CP1S CONTACT, SOCKET 1
Refer to SWPM 20-81-12 as an accepted procedure. 1 BACC47DJ1 CONTACT, SOCKET 2
Refer to SWPM 20-30-12 as an accepted procedure. (a) (b) (c) (d) 4 D-436-37 SPLICE 3
Refer to SWPM 20-10-11 as an accepted procedure. 1 280W5134-12203 ID SLEEVE - SP684 4
Refer to SWPM 20-10-11 as an accepted procedure. 1 280W5134-12303 ID SLEEVE - SP683 5 Splice SP689 is replaced in another figure. - - SPLICE 6

**FIGURE 6: MAIN EQUIPMENT CENTER - WIRE BUNDLE W8327 - WIRING CHANGE (SHEET 2 OF 3)**  Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 08, 2014 777-28-0083 Revision 1 March 06, 2015 53 of 72 **BOEING SERVICE BULLETIN 777-28-0083 More Data**  **Qty Identification**  **Name 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)**  Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 08, 2014 777-28-0083 Revision 1 March 06, 2015 54 of 72 **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)**  Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 08, 2014 777-28-0083 Revision 1 March 06, 2015 55 of 72 **BOEING SERVICE BULLETIN 777-28-0083 FIGURE 7: MAIN EQUIPMENT CENTER - WIRE BUNDLE W5829 - WIRE ROUTING**  **(SHEET 2 OF 5)** Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 08, 2014 777-28-0083 Revision 1 March 06, 2015 56 of 72 **BOEING SERVICE BULLETIN 777-28-0083 FIGURE 7: MAIN EQUIPMENT CENTER - WIRE BUNDLE W5829 - WIRE ROUTING**  **(SHEET 3 OF 5)** Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 08, 2014 777-28-0083 Revision 1 March 06, 2015 57 of 72 **BOEING SERVICE BULLETIN 777-28-0083 FIGURE 7: MAIN EQUIPMENT CENTER - WIRE BUNDLE W5829 - WIRE ROUTING**  **(SHEET 4 OF 5)** Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 08, 2014 777-28-0083 Revision 1 March 06, 2015 58 of 72 **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. **NOTE:**Get the parts given below from kit 280W5134-127.
**More Data Qty**  **Identification Name**  **Task Step**  Route with existing W5829 wire bundle. Refer to SWPM 20- 10-11 and SWPM20-10-12 as accepted procedures. 1 280W5134-127W Wire List Install (New) 1

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

**FIGURE 7: MAIN EQUIPMENT CENTER - WIRE BUNDLE W5829 - WIRE ROUTING (SHEET 5 OF 5)**  Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 08, 2014 777-28-0083 Revision 1 March 06, 2015 59 of 72 **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 280W5134-127.

**FIGURE 8: MAIN EQUIPMENT CENTER - WIRE BUNDLE W5829 - WIRING CHANGE (SHEET 1 OF 2)**  Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 08, 2014 777-28-0083 Revision 1 March 06, 2015 60 of 72 **BOEING SERVICE BULLETIN 777-28-0083 More Data**  **Qty Identification**  **Name Flag**  **Note** Refer to SWPM 20-61-11 as an accepted procedure. 1 BACC47CP1S CONTACT, SOCKET 1
Refer to SWPM 20-81-12 as an accepted procedure. 1 BACC47DJ1 CONTACT, SOCKET 2
Refer to SWPM 20-30-12 as an accepted procedure. (a) (b) 2 D-436-37 SPLICE 3
Refer to SWPM 20-30-12 as an accepted procedure. 1 280W5134-12304 ID SLEEVE - SP689 4
Refer to SWPM 20-30-16 as an accepted procedure. 1 BACT63D1 SLEEVE, HEAT SHRINK 5 (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)**  Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 08, 2014 777-28-0083 Revision 1 March 06, 2015 61 of 72 **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 280W5134-127.

**FIGURE 9: MAIN EQUIPMENT CENTER - WIRE BUNDLE W5829 - WIRING CHANGE (SHEET 1 OF 2)**  Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 08, 2014 777-28-0083 Revision 1 March 06, 2015 62 of 72 **BOEING SERVICE BULLETIN 777-28-0083 More Data**  **Qty Identification**  **Name Flag**  **Note** Refer to SWPM 20-61-11 as an accepted procedure. 1 BACC47CP1S CONTACT, SOCKET 1
Refer to SWPM 20-81-12 as an accepted procedure. 1 BACC47DJ1 CONTACT, SOCKET 2
Refer to SWPM 20-30-12 as an accepted procedure. (a) (b) 2 D-436-37 SPLICE 3
Refer to SWPM 20-30-12 as an accepted procedure. 1 280W5134-12304 ID SLEEVE - SP689 4
Refer to SWPM 20-30-16 as an accepted procedure. 1 BACT63D1 SLEEVE, HEAT SHRINK 5 (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)**  Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 08, 2014 777-28-0083 Revision 1 March 06, 2015 63 of 72 **BOEING SERVICE BULLETIN 777-28-0083**Install the ELMS2 Operational Program Software (OPS) and Operational Program Configuration (OPC) software, shown below, into electronics unit channel A (install OPS and OPC) and channel B (install OPS and OPC) in each of the ELMS P110, P210 and P310 power management panels. Refer to 777 AMM 24-09-00 as an accepted procedure.
**OPC Software Part Number**  **OPS Software Part Number**  **Media Set Part Number**  **Effectivity**
2416-SMI-M08-31 2466-SMI-500-13 S281W601-B3R WC587 2411-SMI-M08-27 2466-SMI-500-13 S281W601-B3L WC594-WC595 2417-SMI-M08-30 2466-SMI-500-13 S281W601-B3P WD106 2417-SMI-M08-12 2466-SMI-500-13 S281W601-B1Y WD121-WD122 2414-SMI-M09-01 2466-SMI-500-13 S281W601-B33 WD820-WD825 2416-SMI-M09-03 2466-SMI-500-13 S281W601-B30 WD893-WD898 241E-SMI-M08-28 2466-SMI-500-13 S281W601-B3M WD918 2410-SMI-M09-14 2466-SMI-500-13 S281W601-B39 WD930 2415-SMI-M08-32 2466-SMI-500-13 S281W601-B3T WD944-WD945 241F-SMI-M08-29 2466-SMI-500-13 S281W601-B3N WD957 2412-SMI-M08-24 2466-SMI-500-13 S281W601-B37 WD994 2415-SMI-M09-11 2466-SMI-500-13 S281W601-B2G WE056-WE057 241E-SMI-M08-39 2466-SMI-500-13 S281W601-B2C WE073-WE078 2414-SMI-M08-33 2466-SMI-500-13 S281W601-B3U WE094-WE095 241D-SMI-M09-08 2466-SMI-500-13 S281W601-B2E WE138-WE140 241C-SMI-M09-09 2466-SMI-500-13 S281W601-B3F WE141-WE146 2416-SMI-M09-12 2466-SMI-500-13 S281W601-B3H WE164-WE170 2414-SMI-M08-22 2466-SMI-500-13 S281W601-B2P WE178 2417-SMI-M09-02 2466-SMI-500-13 S281W601-B2M WE207-WE215 2412-SMI-M08-35 2466-SMI-500-13 S281W601-B2Y WE218-WE219 2414-SMI-M09-01 2466-SMI-500-13 S281W601-B33 WE243-WE244 2414-SMI-M09-10 2466-SMI-500-13 S281W601-B3G WE265-WE267 2410-SMI-M09-05 2466-SMI-500-13 S281W601-B3D WE275-WE278 2412-SMI-M09-16 2466-SMI-500-13 S281W601-B3K WE291-WE293 2417-SMI-M09-13 2466-SMI-500-13 S281W601-B3E WE307-WE315 2410-SMI-M08-26 2466-SMI-500-13 S281W601-B3B WE335-WE340 2413-SMI-M08-25 2466-SMI-500-13 S281W601-B3A WE352-WE356

**APPENDIX A: ELECTRICAL LOAD MANAGEMENT SYSTEM 2 (ELMS2) SOFTWARE INSTALLATION (SHEET 1 OF 2)**  Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 08, 2014 777-28-0083 Revision 1 March 06, 2015 64 of 72 **BOEING SERVICE BULLETIN 777-28-0083 OPC Software**  **Part Number OPS Software**  **Part Number Media Set Part**  **Number Effectivity** 
2411-SMI-M08-41 2466-SMI-500-13 S281W601-B38 WE376-WE377 2411-SMI-M08-41 2466-SMI-500-13 S281W601-B38 WE381 2411-SMI-M08-36 2466-SMI-500-13 S281W601-B1E WE386-WE387 2413-SMI-M09-06 2466-SMI-500-13 S281W601-B16 WE396-WE399 2415-SMI-M08-23 2466-SMI-500-13 S281W601-B2U WE416-WE420 241F-SMI-M08-38 2466-SMI-500-13 S281W601-B24 WE426 241F-SMI-M08-38 2466-SMI-500-13 S281W601-B24 WE436-WE437 2410-SMI-M09-05 2466-SMI-500-13 S281W601-B3D WE441-WE443 2411-SMI-M09-15 2466-SMI-500-13 S281W601-B3J WE451 2411-SMI-M09-04 2466-SMI-500-13 S281W601-B3C WE501-WE502 2417-SMI-M09-02 2466-SMI-500-13 S281W601-B2M WE556-WE558 2412-SMI-M09-07 2466-SMI-500-13 S281W601-B34 WF022-WF024 2412-SMI-M09-07 2466-SMI-500-13 S281W601-B34 WF039-WF041 2410-SMI-M08-37 2466-SMI-500-13 S281W601-B23 WF065-WF066 2412-SMI-M09-07 2466-SMI-500-13 S281W601-B34 WF115-WF117 2412-SMI-M09-07 2466-SMI-500-13 S281W601-B34 WF133 2412-SMI-M09-07 2466-SMI-500-13 S281W601-B34 WF139 2412-SMI-M09-07 2466-SMI-500-13 S281W601-B34 WF156-WF159 2412-SMI-M09-07 2466-SMI-500-13 S281W601-B34 WF166-WF170 2412-SMI-M09-07 2466-SMI-500-13 S281W601-B34 WF176

**APPENDIX A: ELECTRICAL LOAD MANAGEMENT SYSTEM 2 (ELMS2) SOFTWARE INSTALLATION (SHEET 2 OF 2)**  Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 08, 2014 777-28-0083 Revision 1 March 06, 2015 65 of 72 **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)**  Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 08, 2014 777-28-0083 Revision 1 March 06, 2015 66 of 72 **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:
**Circuit Breaker Location**  **Name Number**  **Column Row**  **Panel** CTR L OVRD FUEL PUMP CTRL C28647 21 L P110 L FUEL JETT ISLN VLV C28631 24 L L FUEL JETT NOZ VLV C28621 25 L R FUEL JETT NOZ VLV C28620 12 K P210 R FUEL JETT ISLN VLV C28630 13 K CTR R OVRD FUEL PUMP CTRL C28644 2 L

**APPENDIX B: FUNCTIONAL TEST (SHEET 2 OF 6)**  Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 08, 2014 777-28-0083 Revision 1 March 06, 2015 67 of 72 **BOEING SERVICE BULLETIN 777-28-0083**b. Open these circuit breakers and attach DO NOT CLOSE tags:
**Circuit Breaker Location**  **Name Number**  **Column Row**  **Panel** L FUEL JETT PUMP CTRL C28645 22 L P110 R FUEL JETT PUMP CTRL C28646 14 K P210 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:
**Electrical Connector Phase Rotation Indicator**  Pin B Phase A Pin D Phase B Pin F Phase C (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:
**Circuit Breaker Location**  **Name Number**  **Column Row**  **Panel** L FUEL JETT PUMP CTRL C28645 22 L P110 R FUEL JETT PUMP CTRL C28646 14 K P210
b. Make sure that this circuit breaker is closed:
**Circuit Breaker Location**  **Name Number**  **Column Row**  **Panel** DEFUEL VLV C28637 10 J P310

**APPENDIX B: FUNCTIONAL TEST (SHEET 3 OF 6)**  Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 08, 2014 777-28-0083 Revision 1 March 06, 2015 68 of 72 **BOEING SERVICE BULLETIN 777-28-0083**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:
**Circuit Breaker Location**  **Name Number**  **Column Row**  **Panel** DEFUEL VLV C28637 10 J P310 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 (SHEET 4 OF 6)**  Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 08, 2014 777-28-0083 Revision 1 March 06, 2015 69 of 72 **BOEING SERVICE BULLETIN 777-28-0083**v. Make sure that there is power to connector DM28204. w. Remove the DO NOT CLOSE tag and close this circuit breaker:
**Circuit Breaker Location**  **Name Number**  **Column Row**  **Panel** DEFUEL VLV C28637 10 J P310 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. On the Fuel Management Maintenance page, make sure that the COMMAND and STATUS indications for L JETT NOZ VLV and R JETT NOZ VLV all show CLOSED. ah. Open these circuit breakers and attach DO NOT CLOSE tags:
**Circuit Breaker Location**  **Name Number**  **Column Row**  **Panel** L FUEL JETT NOZ VLV C28621 25 L P110 R FUEL JETT NOZ VLV C28620 12 K P210 ai. 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.

**APPENDIX B: FUNCTIONAL TEST (SHEET 5 OF 6)**  Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 08, 2014 777-28-0083 Revision 1 March 06, 2015 70 of 72 **BOEING SERVICE BULLETIN 777-28-0083**(2) On the P5 Overhead Panel, set the FUEL JETTISON ARM switch to the ARMED position. aj. Operate the pumps for a minimum of one minute. ak. 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. al. Remove DO NOT CLOSE tags and close these circuit breakers:
**Circuit Breaker Location**  **Name Number**  **Column Row**  **Panel** L FUEL JETT NOZ VLV C28621 25 L P110 R FUEL JETT NOZ VLV C28620 12 K P210 am. Close refueling station door 521DB.

**APPENDIX B: FUNCTIONAL TEST (SHEET 6 OF 6)**  Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 08, 2014 777-28-0083 Revision 1 March 06, 2015 71 of 72 **BOEING SERVICE BULLETIN 777-28-0083 APPENDIX C: PART DEMAND INTENT**  **(SHEET 1 OF 1)** Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 08, 2014 777-28-0083 Revision 1 March 06, 2015 72 of 72 **BOEING SERVICE BULLETIN 777-28-0083**