### Commercial Airplanes 

# MD90 Service Bulletin
Number: MD90-28-013 Original Issue: September 27, 2013 Revision 1: August 27, 2015 ATA System: 2800 SUBJECT: FUEL - Fuel Systems - Install Ground Fault Interrupter Relays and Change Fuel Pump System Wiring 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 © 2013 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 Unpublished Work.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 27, 2013 MD90-28-013 Revision 1: August 27, 2015 1 of 140 2.0Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 27, 2013 MD90-28-013 Revision 1: August 27, 2015 2 of 140 BOEING SERVICE BULLETIN MD90-28-013

BLANK PAGETable of Contents Revision Transmittal Sheet............................................ 5 Summary . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7 1. PLANNING INFORMATION. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11 A. Effectivity . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11 1. Airplanes. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11 2. Spares Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13 B. Concurrent Requirements. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14 C. Reason. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14 D. Description. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14 E. Compliance. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15 F. Approval . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15 G. Manpower. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15 H. Weight and Balance Changes. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17 I. Electrical Load Data. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17 J. References . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 22 1. Existing Data:. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 22 2. Data Supplied with this Service Bulletin:. . . . . . . . . . . . . . . . . . . . . . . . . . . 22 3. Installation Drawings Used in the Preparation of this Service Bulletin:. . . . . . . . . . . 22 4. Process Data: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 23 K. Publications Affected. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 23 L. Interchangeability and Intermixability of Parts. . . . . . . . . . . . . . . . . . . . . . . . . . . 23 M. Software Accomplishment Summary. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 23 2. MATERIAL INFORMATION. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25 A. Material - Price and Availability. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25 B. Industry Support Information. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25 C. Parts Necessary for Each Airplane. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25 1. Kits/Parts . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25 2. Parts and Materials Supplied by the Operator. . . . . . . . . . . . . . . . . . . . . . . . 31 3. Parts Modified and Reidentified. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 31 4. Parts Removed and Not Replaced. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 32 D. Parts Necessary to Change Spares. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 32 E. Special Tooling - Price and Availability. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 32 F. Special Tooling Necessary to do this Service Bulletin. . . . . . . . . . . . . . . . . . . . . . . 33 3. ACCOMPLISHMENT INSTRUCTIONS. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 35 A. GENERAL INFORMATION. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 35 B. WORK INSTRUCTIONS. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 37 FIGURE 1: REMOVE RELAYS R2-218 AND R2-219 - FORWARD CARGO COMPARTMENT, LEFT SIDE [Group 3]. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 43 FIGURE 2: INSTALL BRACKETS AND TRACK - E/E COMPARTMENT, AFT LEFT RADIO RACK [Group 1-2] . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 45 FIGURE 3: INSTALL BRACKETS AND TRACK - E/E COMPARTMENT, AFT LEFT RADIO RACK [Group 3] . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 49 FIGURE 4: REMOVE RELAYS R2-336, R2-337 AND RECEPTACLES R5-406, R5-407 - ELECTRICAL POWER CENTER [Group 2]. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 53 FIGURE 5: CENTER TANK FUEL BOOST WIRE CHANGES [Group 1] . . . . . . . . . . . . . . . . . 55 FIGURE 6: CENTER TANK FUEL BOOST WIRE CHANGES [Group 2] . . . . . . . . . . . . . . . . . 62

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 27, 2013 MD90-28-013 Revision 1: August 27, 2015 3 of 140 BOEING SERVICE BULLETIN MD90-28-013FIGURE 7: CENTER AND AUX FUEL BOOST AND TRANSFER WIRE CHANGES [Group 3]. . . . 68 FIGURE 8: INSTALL GFI RELAYS AND RECEPTACLES - E/E COMPARTMENT, AFT LEFT RADIO RACK [Group 1]. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 81 FIGURE 9: INSTALL GFI RELAYS AND RECEPTACLES - E/E COMPARTMENT, AFT LEFT RADIO RACK [Group 2]. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 84 FIGURE 10: INSTALL GFI RELAYS AND RECEPTACLES - E/E COMPARTMENT, AFT LEFT RADIO RACK [Group 3]. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 87 APPENDIX A: GFI CENTER FUEL TANK PUMPS CONTROL CIRCUIT, AND CENTER FUEL TANK PUMPS LOW PRESSURE INDICATION SYSTEM TEST PROCEDURES [Group 1]. . . . . . . . 92 APPENDIX B: GFI CENTER FUEL TANK PUMPS CONTROL CIRCUIT, AND CENTER FUEL TANK PUMPS LOW PRESSURE INDICATION SYSTEM TEST PROCEDURES [Group 2]. . . . . . . 105 APPENDIX C: GFI CENTER/AUX FUEL TANK PUMPS CONTROL CIRCUIT, AND CENTER/AUX FUEL TANK PUMPS LOW PRESSURE INDICATION SYSTEM TEST PROCEDURES [Group 3] . . . 119 APPENDIX D: BOEING PART DEMAND INTENT. . . . . . . . . . . . . . . . . . . . . . . . . . . . . 140

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 27, 2013 MD90-28-013 Revision 1: August 27, 2015 4 of 140 BOEING SERVICE BULLETIN MD90-28-013

### Commercial Airplanes 

# MD90 Service Bulletin Revision Transmittal Sheet Number: MD90-28-013 Original Issue: September 27, 2013 Revision 1: August 27, 2015 ATA System: 2800 SUBJECT: FUEL - Fuel Systems - Install Ground Fault Interrupter Relays and Change Fuel Pump System Wiring This revision includes all pages of the service bulletin. COMPLIANCE INFORMATION RELATED TO THIS REVISION Federal Aviation Administration (FAA) Airworthiness Directive AD 2012-18-05 is related to this service bulletin. Effects of this Revision on airplanes on which Original Issue was previously done: None. REASON FOR REVISION This revision is sent to incorporate engineering released after the original issue of this service bulletin to address the no work conditions due to Ground Fault Interrupter (GFI) panel washers, GFI panel mounting holes too small, wire assembly routing and process issues encountered during validation of the original issue of this service bulletin. The data given in Information Notice MD90-28-013 IN 01 is included in this revision. As a part of a service bulletin validation program, this installation was completed on airplane fuselage number 2097 by Service Bulletin MD90-28-013 Original Issue before the release of Revision 1 of this service bulletin. The installation/change completed on airplane fuselage number 2097 by Service Bulletin MD90-28-013 Original Issue is equivalent to the release of Revision 1 of this service bulletin. Airplane fuselage number 2097 has the configuration of a Group 1 airplane. These sections were changed: 1. In Background, added Boeing Fleet Team Digest (FTD) statement. 2. In Background, added Summary Evaluation Table. 3. In Paragraph 1.C., Reason, added statements. 4. In Paragraph 1.D., Description, added Compliance statement. 5. In Paragraph 1.G., Manpower, updated Manpower. 6. In Paragraph 1.H., Weight and Balance Changes, updated Group 1 through Group 3, information.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 27, 2013 MD90-28-013 Revision 1: August 27, 2015 5 of 1407. In Paragraph 1.J.1., Existing Data: added additional references. 8. In Paragraph 1.J.2.a., Drawings: changed drawing revision. 9. In Paragraph 1.J.3., Installation Drawings Used in the preparation of this Service Bulletin: changed drawing revision. 10. In Paragraph 1.K.1., Publications: updated information. 11. In Paragraph 2.A., Material - Price and Availability, added survey information. 12. In Paragraph 2.C.1., Kits/Parts, Group 1 through Group 3, Service KIt, updated information. 13. In Paragraph 2.C.2., Parts and Materials Supplied by the Operator, added part information. 14. In Paragraph 2.C.3., Parts Modified and Reidentified, Group 1 through Group 3, added parts. 15. In Paragraph 3.A., General Information, Note: added new note. 16. In paragraph 3.B., Work Instructions, Group 1 through Group 3, added instructions. 17. In Figure 5 through Figure 7, added a reference. 18. In Figure 8, changed view A and B and added view C. 19. In Figure 8, changed part number and added footnotes (b), (c), (d) and (e). 20. In Figure 9, changed view A and B and added view C. 21. In Figure 9, changed part number and added footnotes (b), (c), (d) and (e). 22. In Figure 10, changed view A and B and added view C. 23. In Figure 10, changed part number and added footnotes (b), (c), (d) and (e). 24. Added Appendix D. 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 27, 2013 Original Issue: August 27, 2015 Revision 1:

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 27, 2013 MD90-28-013 Revision 1: August 27, 2015 6 of 140 BOEING SERVICE BULLETIN MD90-28-013

### Commercial Airplanes 

# MD90 Service Bulletin Summary Number: MD90-28-013 Original Issue: September 27, 2013 Revision 1: August 27, 2015 ATA System: 2800 SUBJECT: FUEL - Fuel Systems - Install Ground Fault Interrupter Relays and Change Fuel Pump System Wiring CONCURRENT REQUIREMENTS None. BACKGROUND Frictional heating or sparking may develop from fuel pump failure, wear of fuel pump rotating components, or ingestion of debris by the pump. Electrical faults in a fuel pump may result in electrical arc burn through of a fuel pump. Frictional heating or sparking and electrical arc burn through in fuel pump inlets or priming system outlets exposed (i.e. not covered by fuel) to the tank ullage in combination with the ullage being flammable, may result in a fuel tank ignition event. A fuel tank ignition event could develop with a pump running in an empty tank if the normal shutoff command is delayed or as a result of control system failures that keep the pump in a latent uncommanded running condition. Center wing fuel tanks and auxiliary fuel tank may be subject to this condition since they are normally pumped dry over the course of a flight. If not corrected frictional heating or sparking, electrical arc burn through, or a fuel tank pump running in an empty fuel tank may result in a fuel tank ignition event. This service bulletin is the result of the safety assessments conducted by Boeing under a Special Federal Aviation Regulation (SFAR) 88, Fuel Tank System Fault Tolerance Evaluation Requirements. Boeing Fleet Team Digest (FTD) MD90 FTD 28-03001 and MD90 FTD 28-12002 are 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 Yes Electrical Load Changed Paragraph 1.K., Publications Affected Yes Publications Affected

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 27, 2013 MD90-28-013 Revision 1: August 27, 2015 7 of 140Reference Affected Planning Data Paragraph 1.K., Publications Affected Yes 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 This service bulletin installs Ground Fault Interrupter (GFI) relays and cuts/coils/stows wires to center wing and auxiliary fuel tank pump motor neutral circuits. EFFECTIVITY MD90-30 Airplanes. Refer to Paragraph 1.A.1., Airplanes, for the list of affected airplanes. COMPLIANCE Federal Aviation Administration (FAA) Airworthiness Directive AD 2012-18-05 is related to this service bulletin. Boeing recommends that the change given in this service bulletin be done within 60 months after the effective date of AD 2012-18-05. INDUSTRY SUPPORT INFORMATION Boeing warranty remedies are not available for the configuration changes given in this service bulletin. MANPOWER Elapsed Hours Total Task Hours Group 31.0 58.0 1 24.4 45.3 2 73.7 142.7 3
MATERIAL INFORMATION Boeing Supplied Kits/Parts. Refer to Paragraph 2.A., Material - Price and Availability.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 27, 2013 MD90-28-013 Revision 1: August 27, 2015 8 of 140 BOEING SERVICE BULLETIN MD90-28-013Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 27, 2013 MD90-28-013 Revision 1: August 27, 2015 9 of 140 BOEING SERVICE BULLETIN MD90-28-013Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 27, 2013 MD90-28-013 Revision 1: August 27, 2015 10 of 140 BOEING SERVICE BULLETIN MD90-28-013

BLANK PAGE

### Commercial Airplanes 

# MD90 Service Bulletin
Number: MD90-28-013 Original Issue: September 27, 2013 Revision 1: August 27, 2015 ATA System: 2800 SUBJECT: FUEL - Fuel Systems - Install Ground Fault Interrupter Relays and Change Fuel Pump System Wiring
1. PLANNING INFORMATION A. Effectivity 1. Airplanes This service bulletin is for the airplanes shown below.
DESCRIPTION CONFIGURATION GROUP Airplanes that install GFI relays for center fuel tank boost pumps which are affected by SR90280011-7001 drawing configuration. - 1
Airplanes that install GFI relays for center fuel tank boost pumps which are affected by SR90280011-7003 drawing configuration. - 2
Airplanes that install GFI relays for center fuel tank and forward auxiliary fuel tank boost pumps which are affected by SR90280011-7005 drawing configuration. - 3

Airplane Models: MD-90-30 Group Fuselage Num- ber 1 2094 - 2099 1 2100 1 2115 1 2117 1 2120 1 2122 - 2123 1 2125 - 2126

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 27, 2013 MD90-28-013 Revision 1: August 27, 2015 11 of 140Group Fuselage Num- ber 1 2129 1 2131 1 2133 1 2136 1 2138 1 2140 - 2144 1 2146 - 2147 1 2149 - 2150 1 2153 - 2154 1 2156 - 2159 1 2161 - 2166 1 2169 - 2171 1 2173 1 2175 1 2177 1 2179 1 2181 - 2182 1 2184 1 2186 1 2190 2 2191 1 2193 - 2195 1 2197 - 2198 1 2200 1 2202 - 2203 2 2205 1 2207 2 2209 1 2210 - 2212 2 2213 2 2215 - 2216 1 2217

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 27, 2013 MD90-28-013 Revision 1: August 27, 2015 12 of 140 BOEING SERVICE BULLETIN MD90-28-013Group Fuselage Num- ber 2 2219 1 2220 2 2221 1 2222 2 2223 1 2224 2 2225 - 2227 1 2228 2 2229 - 2232 1 2233 2 2235 1 2236 2 2237 1 2238 1 2240 1 2242 3 2243 1 2245 - 2246 1 2248 2 2250 - 2251 1 2253 2 2255 - 2257 1 2258 - 2259 2 2260 1 2261 2 2262 - 2263 2 2288 - 2290 1 4001 - 4002 2. Spares Affected None.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 27, 2013 MD90-28-013 Revision 1: August 27, 2015 13 of 140 BOEING SERVICE BULLETIN MD90-28-013B. Concurrent Requirements None. C. Reason Frictional heating or sparking may develop from fuel pump failure, wear of fuel pump rotating components, or ingestion of debris by the pump. Electrical faults in a fuel pump may result in electrical arc burn through of a fuel pump. Frictional heating or sparking and electrical arc burn through in fuel pump inlets or priming system outlets exposed (i.e. not covered by fuel) to the tank ullage in combination with the ullage being flammable, may result in a fuel tank ignition event. A fuel tank ignition event could develop with a pump running in an empty tank if the normal shutoff command is delayed or as a result of control system failures that keep the pump in a latent uncommanded running condition. Center wing fuel tanks and auxiliary fuel tank may be subject to this condition since they are normally pumped dry over the course of a flight. If not corrected frictional heating or sparking, electrical arc burn through, or a fuel tank pump running in an empty fuel tank may result in a fuel tank ignition event. Revision 1 is sent to incorporate engineering released after the original issue of this service bulletin to address the no work conditions due to Ground Fault Interrupter (GFI) panel washers, GFI panel mounting holes too small, wire assembly routing and process issues encountered during validation of the original issue of this service bulletin. This service bulletin is the result of the safety assessments conducted by Boeing under a Special Federal Aviation Regulation (SFAR) 88, Fuel Tank System Fault Tolerance Evaluation Requirements. Boeing Fleet Team Digest (FTD) MD90 FTD 28-03001 and MD90 FTD 28-12002 are related to this service bulletin. The data given in Information Notice MD90-28-013 IN 01 is included in this revision. As a part of a service bulletin validation program, this installation was completed on airplane fuselage number 2097 by Service Bulletin MD90-28-013 Original Issue before the release of Revision 1 of this service bulletin. The installation completed on airplane fuselage number 2097 by Service Bulletin MD90-28-013 Original Issue is equivalent to the release of Revision 1 of this service bulletin. Airplane fuselage number 2097 has the configuration of a Group 1 airplane. D. Description Revision 1 - Effects of this Revision on airplanes on which Original Issue was previously done: None. This service bulletin installs Ground Fault Interrupter (GFI) relays and cuts/coils/stows wires to center wing and auxiliary fuel tank pump motor neutral circuits. The work in this service bulletin is done in the maintenance zone(s) given below.
Affected Maintenance ZonesZone Model 112, 114, 115, 121, 211, 221 MD-90-30

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 27, 2013 MD90-28-013 Revision 1: August 27, 2015 14 of 140 BOEING SERVICE BULLETIN MD90-28-013E. Compliance Federal Aviation Administration (FAA) Airworthiness Directive AD 2012-18-05 is related to this service bulletin. Boeing recommends that the change given in this service bulletin be done within 60 months after the effective date of AD 2012-18-05. 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. 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. In addition, the Manager of the FAA Los Angeles Aircraft Certification Office approves the action (i.e. inspection or modification) defined in this service bulletin as an Alternative Method of Compliance to the requirements of paragraph (g)(1) and (2) of AD 2012-18-05. All provisions of AD 2012-18-05 that are not specifically referenced in the above statement remain fully applicable and must be complied with. 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. Group 1: Elapsed Hours Task Hours Number of Persons Task 2.5 2.5 1 Open Access 0.3 0.3 1 FIGURE 2 23.5 47.0 2 Route and Clip Wire 2.9 5.8 2 FIGURE 5 0.6 0.6 1 FIGURE 8 2.5 2.5 1 Close Access

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 27, 2013 MD90-28-013 Revision 1: August 27, 2015 15 of 140 BOEING SERVICE BULLETIN MD90-28-013Group 1: Elapsed Hours Task Hours Number of Persons Task 0.6 1.2 2 Test 32.9 59.9 TOTAL FOR EACH AIRPLANE Group 2: Elapsed Hours Task Hours Number of Persons Task 2.0 2.0 1 Open Access 0.3 0.3 1 FIGURE 2 0.5 0.5 1 FIGURE 4 17.5 35.0 2 Route and Clip Wire 2.5 5.0 2 FIGURE 6 0.6 0.6 1 FIGURE 9 2.0 2.0 1 Close Access 0.9 1.8 2 Test 26.3 47.2 TOTAL FOR EACH AIRPLANE Group 3: Elapsed Hours Task Hours Number of Persons Task 2.5 2.5 1 Open Access 0.2 0.2 1 FIGURE 1 0.5 0.5 1 FIGURE 3 62.0 124.0 2 Route and Clip Wire 5.2 10.4 2 FIGURE 7 1.0 1.0 1 FIGURE 10 2.5 2.5 1 Close Access 1.8 3.6 2 Test 75.7 144.7 TOTAL FOR EACH AIRPLANE

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 27, 2013 MD90-28-013 Revision 1: August 27, 2015 16 of 140 BOEING SERVICE BULLETIN MD90-28-013H. Weight and Balance Changes Group 1:

Moment Change (MEW) IN.-LBS Mfr's Empty Weight (MEW) LBSApproximate Station (Inches) Airplane +257.6 +0.7 + 368.0 MD-90-30 Group 2:

Moment Change (MEW) IN.-LBS Mfr's Empty Weight (MEW) LBSApproximate Station (Inches) Airplane -87.3 -0.5 + 174.6 MD-90-30 Group 3:

Moment Change (MEW) IN.-LBS Mfr's Empty Weight (MEW) LBSApproximate Station (Inches) Airplane +571.9 +3.5 + 163.4 MD-90-30
I. Electrical Load Data
1. Direct Current (DC) Load Changes a. Add DC loads by amounts shown below: Group 1-2: No DC loads added. Group 3:

UNITS %OPR 1 100 E/NE E UNIT LOAD AMPS 0.112 NOTES (B1-903) SUPPLIERLeach International EQUIPMENT NAME PART NUMBER GFI FWD AUX Tank Fuel XFR Pump A KDG-X4L-001 ITEM R2- 1496 CHAP 280 BUS 1L

AVERAGE AMPS % TIME OPR 15/30 M 2/5 M 5 S 15/30 M 2/5 M CONDITION 0 0 0 0 0 LOADING 0 0 0 0 0 START 0 0 0 0 0 TAXI

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 27, 2013 MD90-28-013 Revision 1: August 27, 2015 17 of 140 BOEING SERVICE BULLETIN MD90-28-013Group 3:

UNITS %OPR 1 100 E/NE E UNIT LOAD AMPS 0.112 NOTES (B1-903) SUPPLIERLeach International EQUIPMENT NAME PART NUMBER GFI FWD AUX Tank Fuel XFR Pump A KDG-X4L-001 ITEM R2- 1496 CHAP 280 BUS 1L

AVERAGE AMPS % TIME OPR 15/30 M 2/5 M 5 S 15/30 M 2/5 M CONDITION 0.112 0.112 0.112 100 100 TAKEOFF & CLIMB 0.112 0.112 0.112 100 100 CRUISE COLD 0.112 0.112 0.112 100 100 CRUISE HOT 0.056 0.056 0.112 50 50 DESCENT & LAND 0 0 0 0 0 EMERGENCY 0 0 0 0 0 GROUND SERVICE Group 3:

UNITS %OPR 1 100 E/NE E UNIT LOAD AMPS 0.112 NOTES (B1-904) SUPPLIERLeach International EQUIPMENT NAME PART NUMBER GFI FWD AUX Tank Fuel XFR Pump B KDG-X4L-001 ITEM R2- 1497 CHAP 280 BUS 2R

AVERAGE AMPS % TIME OPR 15/30 M 2/5 M 5 S 15/30 M 2/5 M CONDITION 0 0 0 0 0 LOADING 0 0 0 0 0 START 0 0 0 0 0 TAXI 0.112 0.112 0.112 100 100 TAKEOFF & CLIMB 0.112 0.112 0.112 100 100 CRUISE COLD 0.112 0.112 0.112 100 100 CRUISE HOT 0.056 0.056 0.112 50 50 DESCENT & LAND 0 0 0 0 0 EMERGENCY 0 0 0 0 0 GROUND SERVICE b. Delete DC loads by amounts shown below: Group 1-2: No DC loads deleted.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 27, 2013 MD90-28-013 Revision 1: August 27, 2015 18 of 140 BOEING SERVICE BULLETIN MD90-28-013Group 3:

UNITS %OPR 1 100 E/NE E UNIT LOAD AMPS 0.37 NOTES (B1-907) SUPPLIERLeach International EQUIPMENT NAME PART NUMBER FWD AUX Tank Fuel XFR Pump A 5D0281-1 ITEM R2-218 CHAP 280 BUS 1L

AVERAGE AMPS % TIME OPR 15/30 M 2/5 M 5 S 15/30 M 2/5 M CONDITION 0 0 0 0 0 LOADING 0 0 0 0 0 START 0 0 0 0 0 TAXI 0.37 0.37 0.37 100 100 TAKEOFF & CLIMB 0.37 0.37 0.37 100 100 CRUISE COLD 0.37 0.37 0.37 100 100 CRUISE HOT 0.19 0.19 0.37 50 50 DESCENT & LAND 0 0 0 0 0 EMERGENCY 0 0 0 0 0 GROUND SERVICE Group 3:

UNITS %OPR 1 100 E/NE E UNIT LOAD AMPS 0.37 NOTES (B1-908) SUPPLIERLeach International EQUIPMENT NAME PART NUMBER FWD AUX Tank Fuel XFR Pump B 5D0281-1 ITEM R2-219 CHAP 280 BUS 2R

AVERAGE AMPS % TIME OPR 15/30 M 2/5 M 5 S 15/30 M 2/5 M CONDITION 0 0 0 0 0 LOADING 0 0 0 0 0 START 0 0 0 0 0 TAXI 0.37 0.37 0.37 100 100 TAKEOFF & CLIMB 0.37 0.37 0.37 100 100 CRUISE COLD 0.37 0.37 0.37 100 100 CRUISE HOT 0.19 0.19 0.37 50 50 DESCENT & LAND 0 0 0 0 0 EMERGENCY 0 0 0 0 0 GROUND SERVICE

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 27, 2013 MD90-28-013 Revision 1: August 27, 2015 19 of 140 BOEING SERVICE BULLETIN MD90-28-0132. Alternating Current (AC) Load Changes a. Add AC loads by amounts shown below:

UNITS %OPR 1 100 E/NE/M PHASE E A VAC PF 115 1 UNIT LOAD (W) 5.75 NOTES (B1-922) SUPPLIERLeach International EQUIPMENT NAME PART NUMBER Center FWD Boost Pump GFI Relay KDAG-X4F-001 ITEM R2- 1494 CHAP 280 BUS 1L

AVERAGE WATTS % TIME OPR 15/30 M 2/5 M 5 S 15/30 M 2/5 M CONDITION 0.115 0.345 5.75 2 6 LOADING 0 0 0 0 0 START 0 0 0 0 0 TAXI 5.75 5.75 5.75 100 100 TAKEOFF & CLIMB 5.75 5.75 5.75 100 100 CRUISE COLD 5.75 5.75 5.75 100 100 CRUISE HOT 2.9 2.9 5.75 50 50 DESCENT & LAND 0 0 0 0 0 EMERGENCY 0 0 0 0 0 GROUND SERVICE

UNITS %OPR 1 100 E/NE/M PHASE E A VAC PF 115 1 UNIT LOAD (W) 5.75 NOTES (B1-923) SUPPLIERLeach International EQUIPMENT NAME PART NUMBER Center AFT Boost Pump GFI Relay KDAG-X4F-001 ITEM R2- 1495 CHAP 280 BUS 2R

AVERAGE WATTS % TIME OPR 15/30 M 2/5 M 5 S 15/30 M 2/5 M CONDITION 0.115 0.345 5.75 2 6 LOADING 0 0 0 0 0 START 0 0 0 0 0 TAXI 5.75 5.75 5.75 100 100 TAKEOFF & CLIMB 5.75 5.75 5.75 100 100 CRUISE COLD 5.75 5.75 5.75 100 100 CRUISE HOT 2.9 2.9 5.75 50 50 DESCENT & LAND 0 0 0 0 0 EMERGENCY 0 0 0 0 0 GROUND SERVICE

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 27, 2013 MD90-28-013 Revision 1: August 27, 2015 20 of 140 BOEING SERVICE BULLETIN MD90-28-013b. Delete AC loads shown below: Group 1, 3: No AC loads deleted. Group 2:
UNITS %OPR 1 100 E/NE/M PHASE E A VAC PF 115 1 UNIT LOAD (W) 11.5 NOTES (B1-922) SUPPLIERLeach International EQUIPMENT NAME PART NUMBER CNTR FWD BOOST PUMP 5D0024-1 ITEM R2- 336 CHAP 280 BUS 1L

AVERAGE WATTS % TIME OPR 15/30 M 2/5 M 5 S 15/30 M 2/5 M CONDITION 0 0 0 0 0 LOADING 0 0 0 0 0 START 0 0 0 0 0 TAXI 11.5 11.5 11.5 100 100 TAKEOFF & CLIMB 11.5 11.5 11.5 100 100 CRUISE COLD 11.5 11.5 11.5 100 100 CRUISE HOT 5.75 5.75 5.75 50 50 DESCENT & LAND 0 0 0 0 0 EMERGENCY 0 0 0 0 0 GROUND SERVICE Group 2:
UNITS %OPR 1 100 E/NE/M PHASE E A VAC PF 115 1 UNIT LOAD (W) 11.5 NOTES (B1-923) SUPPLIERLeach International EQUIPMENT NAME PART NUMBER CNTR AFT BOOST PUMP 5D0024-1 ITEM R2- 337 CHAP 280 BUS 2R

AVERAGE WATTS % TIME OPR 15/30 M 2/5 M 5 S 15/30 M 2/5 M CONDITION 0 0 0 0 0 LOADING 0 0 0 0 0 START 0 0 0 0 0 TAXI 11.5 11.5 11.5 100 100 TAKEOFF & CLIMB 11.5 11.5 11.5 100 100 CRUISE COLD 11.5 11.5 11.5 100 100 CRUISE HOT 5.75 5.75 5.75 50 50 DESCENT & LAND

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UNITS %OPR 1 100 E/NE/M PHASE E A VAC PF 115 1 UNIT LOAD (W) 11.5 NOTES (B1-923) SUPPLIERLeach International EQUIPMENT NAME PART NUMBER CNTR AFT BOOST PUMP 5D0024-1 ITEM R2- 337 CHAP 280 BUS 2R

AVERAGE WATTS % TIME OPR 15/30 M 2/5 M 5 S 15/30 M 2/5 M CONDITION 0 0 0 0 0 EMERGENCY 0 0 0 0 0 GROUND SERVICE
J. References 1. Existing Data: a. Federal Aviation Administration (FAA) Airworthiness Directive (AD) 2012-18-05. b. Standard Wiring Practices Manual (SWPM) 20-00-00, 20-00-09, 20-00-16, 20-10-01, 20-10-02, 20-10-04, 20-20-02, 20-20-03, 20-31-00, 20-40-01 and 20-50-01. c. MD-90 Aircraft Maintenance Manual (AMM) MD90 AMM 06-31-00, 06-32-00, 08-10-00, 12-11-03, 12-11-07, 24-00-00, 25-23-01, 25-50-01, 27-50-00, 31-00-02, 31-14-00, 32-00-00, 32-11-01 and 52-63-00 . d. Structural Repair Manual (SRM) Chapter 51. e. Boeing Fleet Team Digest (FTD) 28-03001 and MD90 FTD 28-12002. 2. Data Supplied with this Service Bulletin: a. Drawings:
ADCN DCN/REV Sheet Title Drawing No

- - DWG ELEC INSTL - CTR & AUX TANKS FUEL BOOST & TRANSFER SR90280010

- G DWG SFAR 88 FUEL PUMP FRICTIONAL HEATING SR90280011

- C DWG CTR & AUX TANKS FUEL BOOST & TRANSFER SR90280012

3. Installation Drawings Used in the Preparation of this Service Bulletin: Change Title Document Number

- ELEC INSTL - CTR & AUX TANKS FUEL BOOST & TRANSFER SR90280010

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 27, 2013 MD90-28-013 Revision 1: August 27, 2015 22 of 140 BOEING SERVICE BULLETIN MD90-28-013Change Title Document Number G SFAR 88 FUEL PUMP FRICTIONAL HEATING SR90280011

C CTR & AUX TANKS FUEL BOOST & TRANSFER SR90280012

These drawings were used to prepare this service bulletin. These drawings are necessary to make the specified changes, and are supplied with this service bulletin. These drawings may not be applicable to all airplane configurations or operators. 4. Process Data: Douglas Process Specifications referred to on the drawings are not given in this service bulletin since these procedures are frequently used as standard shop practices. K. Publications Affected 1. Publications: Chapter-Section Publication Section 1 and 3 FAA Approved Airplane Flight Manual FCOM Advisory Bulletin 2-007 Flight Crew Operations Manual 24-50, 25-57 Illustrated Parts Catalog 28-22 Aircraft Maintenance Manual MDC-92K9145 (CDCCL 28-8) Special Compliance Item Report 28-22 Fault Isolation Manual 28-21, 28-24, 28-25, 28-42 Wiring Diagram Manual 25-57, 28-22, 28-23, 28-25, 91-12 System Schematic Manual 2. Damage Tolerance Based Structural Inspections: Boeing has evaluated the repairs and/or changes in this service bulletin for effects on Fatigue Critical Structure (FCS) and for changes to Damage Tolerance Inspections (DTI) required in the Maintenance Program. This service bulletin does not affect FCS, therefore DTIs are not necessary. L. Interchangeability and Intermixability of Parts Refer to Paragraph 2.C., Parts Necessary for Each Airplane, for interchangeability and intermixability information. NOTE:This service bulletin replaces existing relays with GFI relays. After accomplishment of this service bulletin airplanes cannot revert to the previously installed non-GFI relays. M. Software Accomplishment Summary Not affected.

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BLANK PAGE2. 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) 662-7145REFER TO THE BOEING PART PAGE ON MYBOEINGFLEET.COM OR CONTACT FIRST RESPONDER AT FR@BOEING.COM FOR THE LATEST REORDER LEAD TIME (ROLT) AND PRICE INFORMATION Unit Price as of the original issue date of this Service Bulletin (US Dollars) ROLT as of the original issue date of this Service Bulletin (Calendar Days) Name Kit Number

$12,392.00 150 Service Kit SB90280013-3 $13,043.00 150 Service Kit SB90280013-5 $36,978.00 150 Service Kit SB90280013-7 Operators are encouraged to complete the survey provided in APPENDIX D of this service bulletin to help Boeing predict the quantity and timing of the Boeing Supplied Kits/Parts. 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 To get the kits/parts shown below, refer to Paragraph 2.A., Material - Price and Availability. NOTE:One top kit and the items shown in Paragraph 2.C.2., Parts and Materials Supplied by the Operator, are necessary for each airplane. Group 1:
SB90280013-3 Service Kit Notes Name QTY New Part Number (a) WIRE KIT 1 SB90280013-101 (b) TERM BLOCK 2 5D0010-15

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 27, 2013 MD90-28-013 Revision 1: August 27, 2015 25 of 140 BOEING SERVICE BULLETIN MD90-28-013Group 1:
SB90280013-3 Service Kit Notes Name QTY New Part Number (b) END CLAMP 2 5D0101-2 (b) TERM BLOCK L 9 5D0107-3 (b) TRACK 1 9D0090-12U (b) STRAP 6 9D0254-1-1-9 BRACKET 2 ABN7294-629 MOUNT 6 CSCS-M GFI RELAY 2 KDAG-X4F-001 NUT 2 MS21042L08 NUT 4 MS21042L3 SCREW 2 MS35206-242 LOCKWASHER 1 MS35338-43 SCREW 1 NAS1096-3-11 SCREW 4 NAS1096-3-6 WASHER 1 NAS1149F0332P WASHER 4 NAS1252-10L (b) WASHER 2 S124682-3D8-3 RELAY SOCKET 2 SO-1061-8916 (c) (d) WASHER 8 NAS620C10 (.063 Thickness) (a) Refer to SB90280013-101 Wire Kit table for Wire Kit contents. (b) Or approved equivalent. Refer to AEPL Drawing 7595071. (c) Boeing furnished part. (d) NAS620C10L Washers are furnished with Relay Socket and are not used in this installation. Keep the washers if there are other uses for them. Group 1:
SB90280013-101 Wire Kit Notes Name QTY New Part Number (a) WIRE CODE 801 175 FT. D2426-1C-16NM (a) WIRE CODE 801 369 FT. D2426-1C-18NM

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SB90280013-101 Wire Kit Notes Name QTY New Part Number (a) WIRE CODE 801 96 FT. D2426-1C-20NM (a) WIRE CODE 801 57 FT. D2426-1C-24NM (b) TERM LUG, T/C 888 2 5D0086-17 (b) TERM LUG, T/C 889 6 5D0086-18 (b) TERM LUG, T/C 890 2 5D0086-19 PIN, T/C 1131 28 DC38-16P PIN, T/C 1126 10 DC38-20P SOCKET, T/C 706 6 LRC16M-32DJ5 SOCKET, T/C 604 1 LRC22M-1DE5 SOCKET, T/C 1268 8 M39029/92-533 SOCKET, T/C 1266B 12 M39029/92-535 (b) SOCKET, T/C 602/702 5 S00023-20S (a) Or approved alternate. Refer to SWPM 20-00-13. (b) Or approved equivalent. Refer to AEPL Drawing 7595071. Group 2:
SB90280013-5 Service Kit Notes Name QTY New Part Number (a) WIRE KIT 1 SB90280013-102 (b) TERM BLOCK 1 5D0010-15 (b) END CLAMP 2 5D0101-2 (b) TERM BLOCK L 10 5D0107-3 (b) TRACK 1 9D0090-12U (b) STRAP 6 9D0254-1-1-9 BRACKET 2 ABN7294-629 NUT 2 AN315-3R MOUNT 6 CSCS-M GFI RELAY 2 KDAG-X4F-001 NUT 2 MS21042L08 NUT 4 MS21042L3

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SB90280013-5 Service Kit Notes Name QTY New Part Number SCREW 2 MS35206-242 LOCKWASHER 2 MS35338-43 SCREW 1 NAS1096-3-11 SCREW 4 NAS1096-3-6 WASHER 3 NAS1149F0332P WASHER 4 NAS1252-10L (b) WASHER 2 S124682-3D8-3 RELAY SOCKET 2 SO-1061-8916 (c) (d) WASHER 8 NAS620C10 (.063 Thickness) (a) Refer to SB90280013-102 Wire Kit table for Wire Kit contents. (b) Or approved equivalent. Refer to AEPL Drawing 7595071. (c) Boeing furnished part. (d) NAS620C10L Washers are furnished with Relay Socket and are not used in this installation. Keep the washers if there are other uses for them. Group 2:
SB90280013-102 Wire Kit Notes Name QTY New Part Number (a) WIRE CODE 801 175 FT. D2426-1C-16NM (a) WIRE CODE 801 115 FT. D2426-1C-18NM (a) WIRE CODE 801 210 FT. D2426-1C-20NM (b) TERM LUG, T/C 762 2 5D0086-6 PIN, T/C 1131 32 DC38-16P PIN, T/C 1126 8 DC38-20P SOCKET, T/C 1268 8 M39029/92-533 SOCKET, T/C 1266B 12 M39029/92-535 (b) SOCKET, T/C 602/702 6 S00023-20S

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SB90280013-102 Wire Kit Notes Name QTY New Part Number PIN, T/C 612 12 YHMM16-3F50 (a) Or approved alternate. Refer to SWPM 20-00-13. (b) Or approved equivalent. Refer to AEPL Drawing 7595071. Group 3:
SB90280013-7 Service Kit Notes Name QTY New Part Number (a) WIRE KIT 1 SB90280013-103 (b) TERM BLOCK 2 5D0010-15 (b) END CLAMP 4 5D0101-2 (b) TERM BLOCK 2 5D0107-1 (b) TERM BLOCK L 18 5D0107-3 (b) TRACK 2 9D0090-12U (b) STRAP 6 9D0254-1-1-9 BRACKET 3 ABN7294-629 MOUNT 6 CSCS-M GFI RELAY 2 KDAG-X4F-001 GFI RELAY 2 KDG-X4L-001 NUT 4 MS21042L08 NUT 6 MS21042L3 SCREW 4 MS35206-242 LOCKWASHER 1 MS35338-43 SCREW 1 NAS1096-3-11 SCREW 6 NAS1096-3-6 WASHER 1 NAS1149F0332P WASHER 6 NAS1252-10L RELAY SOCKET 2 RSE500311 (b) WASHER 4 S124682-3D8-3 RELAY SOCKET 2 SO-1061-8916 (c) (d) WASHER 8 NAS620C10 (.063 Thickness)

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 27, 2013 MD90-28-013 Revision 1: August 27, 2015 29 of 140 BOEING SERVICE BULLETIN MD90-28-013Group 3:
SB90280013-7 Service Kit Notes Name QTY New Part Number (a) Refer to SB90280013-103 Wire Kit table for Wire Kit contents. (b) Or approved equivalent. Refer to AEPL Drawing 7595071. (c) Boeing furnished part. (d) NAS620C10L Washers are furnished with Relay Socket and are not used in this installation. Keep the washers if there are other uses for them. Group 3:
SB90280013-103 Wire Kit Notes Name QTY New Part Number (a) WIRE CODE 801 350 FT. D2426-1C-16NM (a) WIRE CODE 801 369 FT. D2426-1C-18NM (a) WIRE CODE 801 1003 FT. D2426-1C-20NM (a) WIRE CODE 801 57 FT. D2426-1C-24NM (b) TERM LUG, T/C 888 2 5D0086-17 (b) TERM LUG, T/C 889 6 5D0086-18 (b) TERM LUG, T/C 890 2 5D0086-19 (b) TERM LUG, T/C 761 10 5D0086-5 (b) TERM LUG, T/C 762 8 5D0086-6 PIN, T/C 1131 62 DC38-16P PIN, T/C 1126 10 DC38-20P SOCKET, T/C 706 12 LRC16M-32DJ5 SOCKET, T/C 604 1 LRC22M-1DE5 SOCKET, T/C 1268 16 M39029/92-533 SOCKET, T/C 1266B 24 M39029/92-535 (b) PIN, T/C 601/701 16 S00023-20P (b) SOCKET, T/C 602/702 19 S00023-20S (a) Or approved alternate. Refer to SWPM 20-00-13. (b) Or approved equivalent. Refer to AEPL Drawing 7595071.

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Notes Name QTY Part Number / Specifica- tion (a) Tie Tape As Required 18XTZ, 23XTZ (DMS 2089) or Equivalent (b) Chemical Conversion Coating As Required Alodine 1200S (DPM 1453-5) or Equivalent End Cap 2 CYW20 (b) Primer, Fluid Resistant As Required Koropon 515-700 with Cata- lyst 910-704 (DMS 1786) or Equivalent (c) (d) Strap As Required 9D0254-1-1-9 (PLT2S-9)(SST2S) or Equivalent Spacer As Required 2712453-BN Sleeve As Required DMS 2109 (a) Can be purchased from: Gudebrod Incorporated, 274 Shoemaker Road, Pottstown, Pennsylvania, 19464, CAGE 82110. (b) Can be purchased from: Henkel Corporation, 32100 Stephenson Highway, Madison Heights, Michigan, 48071, CAGE 1N6B3. (c) Can be purchased from: Panduit Corporation, 17301 Ridgeland Avenue, Tinley Park, Illinois, 60477, CAGE 06383. (d) Or approved equivalent. Refer to AEPL Drawing 7595071.
3. Parts Modified and Reidentified Group 1:
Name New Part Number Name QTY Existing Part Number

Bracket SR90280011-3 Clip Assembly 1 7927157-707

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New Part Number Name QTY Existing Part Num- ber SR90280011-5 Bracket 1 7961078-795 Group 3:
New Part Number Name QTY Existing Part Num- ber SR90280011-7 Bracket 1 7927157-707 4. Parts Removed and Not Replaced Group 1: None. Group 2:
Notes QTY Name Existing Part Number R2-336 and R2-337 (a) (b) 2 RELAY 5D0024-1 R5-406 and R5-407 (a) (b) 2 RELAY SOCKET 5D0020-10 (a) Keep the part if there are other uses for it. (b) Or approved equivalent. Refer to AEPL Drawing 7595071. Group 3:
Notes QTY Name Existing Part Number R2-218 and R2-219 (a) (b) 2 RELAY 5D0281-1 (a) 1 BRACKET ABN7294-627 (a) Keep the part if there are other uses for it. (b) Or approved equivalent. Refer to AEPL Drawing 7595071. D. Parts Necessary to Change Spares None. E. Special Tooling - Price and Availability None.

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BLANK PAGE3. ACCOMPLISHMENT INSTRUCTIONS A. GENERAL INFORMATION WARNING:IF ELECTRICAL POWER IS APPLIED TO THE AIRPLANE, MAKE SURE YOU OBEY ALL PRECAUTIONS WHILE YOU DO WORK. IF YOU DO NOT OBEY THE PRECAUTIONS, DEATH OR INJURY TO PERSONS, AND DAMAGE TO THE AIRPLANE CAN OCCUR. CAUTION:ELECTRICALLY GROUND THE AIRPLANE. THIS WILL HELP TO PREVENT DAMAGE TO THE AIRPLANE OR EQUIPMENT. 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. Equivalent parts are listed in the AEPL, Drawing 7595071. 3. Use the approved fastener and process material substitutions, in accordance with Structural Repair Manual (SRM) 51. 4. 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. 5. A 1/8-inch thick stack of the same type washers called for in this service bulletin is the maximum thickness which may be used under fastener head or nut to counteract accumulation of tolerances. EXCEPTION: When the available fastener length increments are greater than 1/16-inch, a 3/16-inch thick stack of the same type washers may be used. 6. 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 limits to tighten nuts and bolts are in SRM Chapter 51. 7. Refer to these SWPM chapters for applicable operations, as accepted procedures:

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 27, 2013 MD90-28-013 Revision 1: August 27, 2015 35 of 140 BOEING SERVICE BULLETIN MD90-28-013Title Chapter General - Maintenance Safety Practices SWPM 20-00-00General Maintenance Practices - Electrical SWPM 20-00-09Electrical Wire Codes SWPM 20-00-13Electrical Wire End Termination Codes and Tool Codes SWPM 20-00-16Wiring Installation - Maintenance Practices SWPM 20-10-01Shielding - Maintenance Practices SWPM 20-10-02Coil and Stow - Maintenance Practices SWPM 20-10-04Terminal Blocks - Maintenance Practices SWPM 20-20-02General Installations Hardware - Maintenance Practices SWPM 20-20-03Electrical Connectors - Maintenance Practices SWPM 20-31-00Power Distribution Bus - Maintenance Practices SWPM 20-40-01Electrical Bonding - Maintenance Practices SWPM 20-50-01

8. Obey all of the warnings and cautions given in the specified manual sections. 9. Review and understand all general notes of Service Rework Drawing SR90280011 sheets 3.0, 3.1, 3.2, 3.3, 3.4 and 3.5. 10. If an existing clamp specified in this service bulletin is too large or too small, a smaller or larger clamp with the same basic part number can be used to provide a snug fit. 11. Mark electrical item numbers on structure adjacent to part. Refer to SWPM 20-00-09 as an accepted procedure. 12. The modules on a terminal block are controlled by the wire data. Verify/Install terminal block modules and end clamps to agree with the wire data, refer to SWPM 20-20-02 as an accepted procedure. Use the following parts as required: Part Number Terminal Block ID Letter5D0010-15 B 5D0010-13 J 5D0107-3 L 5D0106-1 CC 5D0107-1 DD 5D0010-11 HH 5D0101-2 EE (End Clamp)

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 27, 2013 MD90-28-013 Revision 1: August 27, 2015 36 of 140 BOEING SERVICE BULLETIN MD90-28-01313. Install terminal block at noted position. If noted position is occupied with a spare terminal block replace it with a specified terminal block. If specified terminal block is same type as existing spare terminal block it is not necessary to replace the terminal block. 14. Perform continuity checks on changed wires after completion of electrical wiring changes. 15. 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. 16. 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. 17. 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. 18. 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. 19. Use DMS 2109 Sleeve as required. Refer to SWPM 20-10-01. B. WORK INSTRUCTIONS Group 1: 1. Remove electrical power from the airplane. Refer to MD90 AMM 24-00-00 as an accepted procedure. 2. Gain access to areas of change as follows: a. Open access doors listed in the table as follows: Refer to MD90 AMM 06-31-00.
Location Access DoorElectrical/Electronics (E/E) Compartment 110BL Forward Accessory Compartment 115AZ Right Wing Leading Edge 610BB b. Open Equipment Panel Cover Assembly. Refer to MD90 AMM 06-31-00 as an accepted procedure. c. Open Forward Stairwell Door. Refer to MD90 AMM 52-63-00 as an accepted procedure. d. Open overhead circuit breaker panel and overhead switch panel. Refer to MD90 AMM 31-00-02 as an accepted procedure.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 27, 2013 MD90-28-013 Revision 1: August 27, 2015 37 of 140 BOEING SERVICE BULLETIN MD90-28-013e. Remove and keep left cockpit sidewall panels. Refer to MD90 AMM 06-32-00 as an accepted procedure. f. Remove and keep left console. Refer to MD90 AMM 31-14-00 as an accepted procedure. g. Remove and keep forward cargo compartment left outboard side panel 121AL and attaching parts. Refer to MD90 AMM 25-50-01 as an accepted procedure. h. Remove and keep cargo compartment ceiling panels between stations Y=218.000 and Y=256.000. Refer to MD90 AMM 25-50-01 as an accepted procedure. i. Remove and keep forward cabin attendant's seat and attaching parts. Refer to MD90 AMM 25-23-01 as an accepted procedure. j. Remove and keep aft Electrical Power Center (EPC) panel 221CL and attaching parts. Refer to MD90 AMM 06-32-00. 3. Install brackets and track in accordance with FIGURE 2. 4. Enlarge holes and identify as Bracket, install Ground Fault Interrupter (GFI) relays and receptacles in accordance with FIGURE 8. 5. Route and clip wire in accordance with Service Rework Drawing SR90280011 sheets 6.0, 7.0, 7.2, 7.5, 7.6, 7.7, 7.8, 7.9, 8.0, 8.2, 8.3, 8.4, 9.0, 9.1, 10.0, 10.1, 10.2, 10.3, 10.4, 11.0, 11.1 and 11.10. 6. Make wire changes in accordance with FIGURE 5. 7. Close access to areas of change as follows: a. Replace kept aft EPC panel 221CL and attaching parts. Refer to MD90 AMM 06-32-00. b. Replace kept forward cabin attendant's seat and attaching parts. Refer to MD90 AMM 25-23-01 as an accepted procedure. c. Replace kept cargo compartment ceiling panels between stations Y=218.000 and Y=256.000. Refer to MD90 AMM 25-50-01 as an accepted procedure. d. Replace kept forward cargo compartment left outboard side panel 121AL and attaching parts. Refer to MD90 AMM 25-50-01 as an accepted procedure. e. Replace kept left console. Refer to MD90 AMM 31-14-00 as an accepted procedure. f. Replace kept left cockpit sidewall panels. Refer to MD90 AMM 06-32-00 as an accepted procedure. g. Close Forward Stairwell Door. Refer to MD90 AMM 52-63-00 as an accepted procedure. h. Close Equipment Panel Cover Assembly. Refer to MD90 AMM 06-31-00 as an accepted procedure. i. Close overhead circuit breaker panel and overhead switch panel. Refer to MD90 AMM 31-00-02 as an accepted procedure.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 27, 2013 MD90-28-013 Revision 1: August 27, 2015 38 of 140 BOEING SERVICE BULLETIN MD90-28-013j. Close access doors listed in the table as follows: Refer to MD90 AMM 06-31-00.
Location Access DoorElectrical/Electronics (E/E) Compartment 110BL Forward Accessory Compartment 115AZ Right Wing Leading Edge 610BB 8. Do GFI Center Fuel Tank Pumps Control Circuit, and Center Fuel Tank Pumps Low Pressure Indication System Test Procedures in accordance with APPENDIX A. 9. Put the airplane back to a serviceable condition. Group 2: 1. Remove electrical power from the airplane. Refer to MD90 AMM 24-00-00 as an accepted procedure. 2. Gain access to areas of change as follows: a. Open access doors listed in the following table. Refer to MD90 AMM 06-31-00.
Location Access DoorElectrical/Electronics (E/E) Compartment 110BL Forward Accessory Compartment 115AZ Right Wing Leading Edge 610BB b. Open Equipment Panel Cover Assembly. Refer to MD90 AMM 06-31-00 as an accepted procedure. c. Open Forward Stairwell Door. Refer to MD90 AMM 52-63-00 as an accepted procedure. d. Remove and keep left console. Refer to MD90 AMM 31-14-00 as an accepted procedure. e. Remove and keep forward cabin attendant's seat and attaching parts. Refer to MD90 AMM 25-23-01 as an accepted procedure. f. Remove and keep aft Electrical Power Center (EPC) panel 221CL and attaching parts. Refer to MD90 AMM 06-32-00. 3. Remove relays R2-336 and R2-337 and corresponding relay sockets R5-406 and R5-407 in accordance with FIGURE 4. 4. Install brackets and track in accordance with FIGURE 2. 5. Enlarge holes and identify as Bracket, install Ground Fault Interrupter (GFI) relays and receptacles in accordance with FIGURE 9.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 27, 2013 MD90-28-013 Revision 1: August 27, 2015 39 of 140 BOEING SERVICE BULLETIN MD90-28-0136. Route and clip wire in accordance with Service Rework Drawing SR90280011 sheets 6.0, 7.0, 7.3, 7.5, 7.6, 7.8, 8.0, 8.1, 8.2, 8.4, 9.0, 10.0, 10.1, 10.2 and 11.10. 7. Make wire changes in accordance with FIGURE 6. 8. Close access to areas of change as follows: a. Replace kept aft EPC panel 221CL and attaching parts. Refer to MD90 AMM 06-32-00. b. Replace kept forward cabin attendant's seat and attaching parts. Refer to MD90 AMM 25-23-01 as an accepted procedure. c. Replace kept left console. Refer to MD90 AMM 31-14-00 as an accepted procedure. d. Close Forward Stairwell Door. Refer to MD90 AMM 52-63-00 as an accepted procedure. e. Close Equipment Panel Cover Assembly. Refer to MD90 AMM 06-31-00 as an accepted procedure. f. Close access doors listed in the table as follows: Refer to MD90 AMM 06-31-00.
Location Access DoorElectrical/Electronics (E/E) Compartment 110BL Forward Accessory Compartment 115AZ Right Wing Leading Edge 610BB 9. Do GFI Center Fuel Tank Pumps Control Circuit, and Center Fuel Tank Pumps Low Pressure Indication System Test Procedures in accordance with APPENDIX B. 10. Put the airplane back to a serviceable condition.

Group 3: 1. Remove electrical power from the airplane. Refer to MD90 AMM 24-00-00 as an accepted procedure. 2. Gain access to areas of change as follows: a. Open access doors listed in the table as follows: Refer to MD90 AMM 06-31-00.
Location Access DoorElectrical/Electronics (E/E) Compartment 110BL Forward Accessory Compartment 115AZ Right Wing Leading Edge 610BB b. Open Equipment Panel Cover Assembly. Refer to MD90 AMM 06-31-00 as an accepted procedure.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 27, 2013 MD90-28-013 Revision 1: August 27, 2015 40 of 140 BOEING SERVICE BULLETIN MD90-28-013c. Open Forward Stairwell Door. Refer to MD90 AMM 52-63-00 as an accepted procedure. d. Open overhead circuit breaker panel and overhead switch panel. Refer to MD90 AMM 31-00-02 as an accepted procedure. e. Remove and keep left cockpit sidewall panels. Refer to MD90 AMM 06-32-00 as an accepted procedure. f. Remove and keep left console. Refer to MD90 AMM 31-14-00 as an accepted procedure. g. Gain access to forward cargo compartment. Remove and keep forward cargo compartment left outboard side panel 121AL and attaching parts. Refer to MD90 AMM 25-50-01 as an accepted procedure. h. Remove and keep cargo compartment ceiling panels between stations Y=218.000 and Y=879.000. Refer to MD90 AMM 25-50-01 as an accepted procedure. i. Remove and keep cargo compartment aft panel at station Y=879.000. Refer to MD90 AMM 25-50-01 as an accepted procedure. j. Remove and keep forward cabin attendant's seat and attaching parts. Refer to MD90 AMM 25-23-01 as an accepted procedure. k. Remove and keep aft Electrical Power Center (EPC) panel 221CL and attaching parts. Refer to MD90 AMM 06-32-00. 3. Remove Relays R2-218 and R2-219 in accordance with FIGURE 1. 4. Remove bracket, install brackets and track in accordance with FIGURE 3. 5. Enlarge holes and identify as Bracket, install Ground Fault Interrupter (GFI) relays and receptacles in accordance with FIGURE 10. 6. Route and clip wire in accordance with Service Rework Drawing SR90280011 sheets 6.0, 7.0, 7.4, 7.5, 7.6, 7.7, 7.8, 7.9, 8.0, 8.2, 8.3, 8.4, 9.0, 9.1, 10.0, 10.1, 10.2, 10.3, 10.4, 11.0, 11.1, 11.2, 11.3, 11.4, 11.8, 11.9 and 11.10. 7. Make wire changes in accordance with FIGURE 7. 8. Close access to areas of change as follows: a. Replace kept aft EPC panel 221CL and attaching parts. Refer to MD90 AMM 06-32-00. b. Replace kept forward cabin attendant's seat and attaching parts. Refer to MD90 AMM 25-23-01 as an accepted procedure. c. Replace kept cargo compartment aft panel at station Y=879.000. Refer to MD90 AMM 25-50-01 as an accepted procedure. d. Replace kept cargo compartment ceiling panels between stations Y=218.000 and Y=879.000. Refer to MD90 AMM 25-50-01 as an accepted procedure.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 27, 2013 MD90-28-013 Revision 1: August 27, 2015 41 of 140 BOEING SERVICE BULLETIN MD90-28-013e. Replace kept forward cargo compartment left outboard side panel 121AL and attaching parts. Refer to MD90 AMM 25-50-01 as an accepted procedure. f. Replace kept left console. Refer to MD90 AMM 31-14-00 as an accepted procedure. g. Replace kept left cockpit sidewall panels. Refer to MD90 AMM 06-32-00 as an accepted procedure. h. Close Forward Stairwell Door. Refer to MD90 AMM 52-63-00 as an accepted procedure. i. Close Equipment Panel Cover Assembly. Refer to MD90 AMM 06-31-00 as an accepted procedure. j. Close overhead circuit breaker panel and overhead switch panel. Refer to MD90 AMM 31-00-02 as an accepted procedure. k. Close access doors listed in the table as follows: Refer to MD90 AMM 06-31-00.
Location Access DoorElectrical/Electronics (E/E) Compartment 110BL Forward Accessory Compartment 115AZ Right Wing Leading Edge 610BB 9. Restore electrical power to the airplane. Refer to MD90 AMM 24-00-00 as an accepted procedure. 10. Do GFI Center/Aux Fuel Tank Pumps Control Circuit, and Center/Aux Fuel Tank Pumps Low Pressure Indication System Test Procedures in accordance with APPENDIX C. 11. 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 27, 2013 MD90-28-013 Revision 1: August 27, 2015 42 of 140 BOEING SERVICE BULLETIN MD90-28-013This Figure applies only to: Group 3.

FIGURE 1: REMOVE RELAYS R2-218 AND R2-219 - FORWARD CARGO COMPARTMENT, LEFT SIDE (SHEET 1 OF 2)
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 27, 2013 MD90-28-013 Revision 1 August 27, 2015 43 of 140 BOEING SERVICE BULLETIN MD90-28-013The 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 8 NAS1096-2-8 Screw Remove 1 8 NAS1149DN816H Washer R2-218, R2-219 (a) 2 5D0281-1 Relay (a) Or approved equivalent. Refer to AEPL Drawing 7595071.

FIGURE 1: REMOVE RELAYS R2-218 AND R2-219 - FORWARD CARGO COMPARTMENT, LEFT SIDE (SHEET 2 OF 2)
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 27, 2013 MD90-28-013 Revision 1 August 27, 2015 44 of 140 BOEING SERVICE BULLETIN MD90-28-013This Figure applies only to: Group 1-2.

FIGURE 2: INSTALL BRACKETS AND TRACK - E/E COMPARTMENT, AFT LEFT RADIO RACK (SHEET 1 OF 4)
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 27, 2013 MD90-28-013 Revision 1 August 27, 2015 45 of 140 BOEING SERVICE BULLETIN MD90-28-013FIGURE 2: INSTALL BRACKETS AND TRACK - E/E COMPARTMENT, AFT LEFT RADIO RACK (SHEET 2 OF 4)
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 27, 2013 MD90-28-013 Revision 1 August 27, 2015 46 of 140 BOEING SERVICE BULLETIN MD90-28-013FIGURE 2: INSTALL BRACKETS AND TRACK - E/E COMPARTMENT, AFT LEFT RADIO RACK (SHEET 3 OF 4)
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 27, 2013 MD90-28-013 Revision 1 August 27, 2015 47 of 140 BOEING SERVICE BULLETIN MD90-28-013The 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 (a) 2 ABN7294-629 Bracket Install/New 1 4 NAS1096-3-6 Screw 2 4 NAS1252-10L Washer 4 MS21042L3 Nut (b) 1 9D0090-12U Track Install/New 3 2 MS35206-242 Screw 4 2 S124682-3D8-3 Washer 2 MS21042L08 Nut (a) Electrical bond between surfaces common to bracket and mating structure. Refer to SWPM 20-50-01 as an accepted procedure. (b) Item number S30-236 must be adjacent and visible after equipment is installed. Refer to SWPM 20-00- 09 as an accepted procedure.

FIGURE 2: INSTALL BRACKETS AND TRACK - E/E COMPARTMENT, AFT LEFT RADIO RACK (SHEET 4 OF 4)
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 27, 2013 MD90-28-013 Revision 1 August 27, 2015 48 of 140 BOEING SERVICE BULLETIN MD90-28-013This Figure applies only to: Group 3.

FIGURE 3: INSTALL BRACKETS AND TRACK - E/E COMPARTMENT, AFT LEFT RADIO RACK (SHEET 1 OF 4)
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 27, 2013 MD90-28-013 Revision 1 August 27, 2015 49 of 140 BOEING SERVICE BULLETIN MD90-28-013FIGURE 3: INSTALL BRACKETS AND TRACK - E/E COMPARTMENT, AFT LEFT RADIO RACK (SHEET 2 OF 4)
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 27, 2013 MD90-28-013 Revision 1 August 27, 2015 50 of 140 BOEING SERVICE BULLETIN MD90-28-013FIGURE 3: INSTALL BRACKETS AND TRACK - E/E COMPARTMENT, AFT LEFT RADIO RACK (SHEET 3 OF 4)
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 27, 2013 MD90-28-013 Revision 1 August 27, 2015 51 of 140 BOEING SERVICE BULLETIN MD90-28-013The 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 2 NAS1096-3-7 Screw Remove 1 2 NAS1252-10L Washer 2 MS21042L3 Nut 1 ABN7294-627 Bracket (a) 3 ABN7294-629 Bracket Install/New 2 6 NAS1096-3-6 Screw 3 6 NAS1252-10L Washer 6 MS21042L3 Nut (b) (c) 2 9D0090-12U Track Install/New 4 4 MS35206-242 Screw 5 4 S124682-3D8-3 Washer 4 MS21042L08 Nut (a) Electrical bond between surfaces common to bracket and mating structure. Refer to SWPM 20-50-01 as an accepted procedure. (b) Item numbers S30-236 and S30-237 must be adjacent and visible after equipment is installed. Refer to SWPM 20-00-09 as an accepted procedure. (c) Or approved equivalent. Refer to AEPL Drawing 7595071.

FIGURE 3: INSTALL BRACKETS AND TRACK - E/E COMPARTMENT, AFT LEFT RADIO RACK (SHEET 4 OF 4)
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 27, 2013 MD90-28-013 Revision 1 August 27, 2015 52 of 140 BOEING SERVICE BULLETIN MD90-28-013This Figure applies only to: Group 2.

FIGURE 4: REMOVE RELAYS R2-336, R2-337 AND RECEPTACLES R5-406, R5-407 - ELECTRICAL POWER CENTER (SHEET 1 OF 2)
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 27, 2013 MD90-28-013 Revision 1 August 27, 2015 53 of 140 BOEING SERVICE BULLETIN MD90-28-013The 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 (a) (b) 1 5D0024-1 RELAY (R2-336) Remove 1 1 5D0020-10 RECEPTACLE (R5- 406) (a) (b) 1 5D0024-1 RELAY (R2-337) Remove 2 1 5D0020-10 RECEPTACLE (R5- 407) (a) And attaching hardware. (b) Or approved equivalent. Refer to AEPL Drawing 7595071.

FIGURE 4: REMOVE RELAYS R2-336, R2-337 AND RECEPTACLES R5-406, R5-407 - ELECTRICAL POWER CENTER (SHEET 2 OF 2)
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 27, 2013 MD90-28-013 Revision 1 August 27, 2015 54 of 140 BOEING SERVICE BULLETIN MD90-28-013This Figure applies only to: Group 1.

FIGURE 5: CENTER TANK FUEL BOOST WIRE CHANGES (SHEET 1 OF 7)
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 27, 2013 MD90-28-013 Revision 1 August 27, 2015 55 of 140 BOEING SERVICE BULLETIN MD90-28-013FIGURE 5: CENTER TANK FUEL BOOST WIRE CHANGES (SHEET 2 OF 7)
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 27, 2013 MD90-28-013 Revision 1 August 27, 2015 56 of 140 BOEING SERVICE BULLETIN MD90-28-013FIGURE 5: CENTER TANK FUEL BOOST WIRE CHANGES (SHEET 3 OF 7)
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 27, 2013 MD90-28-013 Revision 1 August 27, 2015 57 of 140 BOEING SERVICE BULLETIN MD90-28-013FIGURE 5: CENTER TANK FUEL BOOST WIRE CHANGES (SHEET 4 OF 7)
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 27, 2013 MD90-28-013 Revision 1 August 27, 2015 58 of 140 BOEING SERVICE BULLETIN MD90-28-013FIGURE 5: CENTER TANK FUEL BOOST WIRE CHANGES (SHEET 5 OF 7)
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 27, 2013 MD90-28-013 Revision 1 August 27, 2015 59 of 140 BOEING SERVICE BULLETIN MD90-28-013FIGURE 5: CENTER TANK FUEL BOOST WIRE CHANGES (SHEET 6 OF 7)
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 27, 2013 MD90-28-013 Revision 1 August 27, 2015 60 of 140 BOEING SERVICE BULLETIN MD90-28-013Reference: MD90 WDM 28-42-00 and MD90 WDM 28-25-11. The term code numbers shown below agree with the numbers shown in the term code symbols in the figure.
MORE DATA QTY PART NUMBER NAME TERM CODE 10 DC38-20P PIN, T/C 1126 1126 28 DC38-16P PIN, T/C 1131 1131 12 M39029/92-535 SOCKET, T/C 1266B 1266B 8 M39029/92-533 SOCKET, T/C 1268 1268 (a) 5 S00023-20S SOCKET, T/C 602/702 702 1 LRC22M-1DE5 SOCKET, T/C 604 604 6 LRC16M-32DJ5 SOCKET, T/C 706 706 (a) 2 5D0086-17 TERM LUG, T/C 888 888 (a) 6 5D0086-18 TERM LUG, T/C 889 889 (a) 2 5D0086-19 TERM LUG, T/C 890 890 (b) 2 CYW20 END CAP 914 (a) 2 5D0010-15 TERM BLOCK (a) 2 5D0101-2 END CLAMP (a) 9 5D0107-3 TERM BLOCK L (a) Or approved equivalent. Refer to AEPL Drawing 7595071. (b) Operator supplied parts.

FIGURE 5: CENTER TANK FUEL BOOST WIRE CHANGES (SHEET 7 OF 7)
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 27, 2013 MD90-28-013 Revision 1 August 27, 2015 61 of 140 BOEING SERVICE BULLETIN MD90-28-013This Figure applies only to: Group 2.

FIGURE 6: CENTER TANK FUEL BOOST WIRE CHANGES (SHEET 1 OF 6)
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 27, 2013 MD90-28-013 Revision 1 August 27, 2015 62 of 140 BOEING SERVICE BULLETIN MD90-28-013FIGURE 6: CENTER TANK FUEL BOOST WIRE CHANGES (SHEET 2 OF 6)
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 27, 2013 MD90-28-013 Revision 1 August 27, 2015 63 of 140 BOEING SERVICE BULLETIN MD90-28-013FIGURE 6: CENTER TANK FUEL BOOST WIRE CHANGES (SHEET 3 OF 6)
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 27, 2013 MD90-28-013 Revision 1 August 27, 2015 64 of 140 BOEING SERVICE BULLETIN MD90-28-013FIGURE 6: CENTER TANK FUEL BOOST WIRE CHANGES (SHEET 4 OF 6)
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 27, 2013 MD90-28-013 Revision 1 August 27, 2015 65 of 140 BOEING SERVICE BULLETIN MD90-28-013FIGURE 6: CENTER TANK FUEL BOOST WIRE CHANGES (SHEET 5 OF 6)
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 27, 2013 MD90-28-013 Revision 1 August 27, 2015 66 of 140 BOEING SERVICE BULLETIN MD90-28-013Reference: MD90 WDM 28-42-00 and MD90 WDM 28-25-11. The term code numbers shown below agree with the numbers shown in the term code symbols in the figure.
MORE DATA QTY PART NUMBER NAME TERM CODE 8 DC38-20P PIN, T/C 1126 1126 32 DC38-16P PIN, T/C 1131 1131 12 M39029/92-535 SOCKET, T/C 1266B 1266B 8 M39029/92-533 SOCKET, T/C 1268 1268 (a) 6 S00023-20S SOCKET, T/C 602/702 702 12 YHMM16-3F50 PIN, T/C 612 612 (a) 2 5D0086-6 TERM LUG, T/C 762 762 (b) 2 CYW20 END CAP 914 (a) 1 5D0010-15 TERM BLOCK (a) 2 5D0101-2 END CLAMP (a) 10 5D0107-3 TERM BLOCK L (a) Or approved equivalent. Refer to AEPL Drawing 7595071. (b) Operator supplied parts.

FIGURE 6: CENTER TANK FUEL BOOST WIRE CHANGES (SHEET 6 OF 6)
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 27, 2013 MD90-28-013 Revision 1 August 27, 2015 67 of 140 BOEING SERVICE BULLETIN MD90-28-013This Figure applies only to: Group 3.

FIGURE 7: CENTER AND AUX FUEL BOOST AND TRANSFER WIRE CHANGES (SHEET 1 OF 13)
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 27, 2013 MD90-28-013 Revision 1 August 27, 2015 68 of 140 BOEING SERVICE BULLETIN MD90-28-013FIGURE 7: CENTER AND AUX FUEL BOOST AND TRANSFER WIRE CHANGES (SHEET 2 OF 13)
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 27, 2013 MD90-28-013 Revision 1 August 27, 2015 69 of 140 BOEING SERVICE BULLETIN MD90-28-013FIGURE 7: CENTER AND AUX FUEL BOOST AND TRANSFER WIRE CHANGES (SHEET 3 OF 13)
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 27, 2013 MD90-28-013 Revision 1 August 27, 2015 70 of 140 BOEING SERVICE BULLETIN MD90-28-013FIGURE 7: CENTER AND AUX FUEL BOOST AND TRANSFER WIRE CHANGES (SHEET 4 OF 13)
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 27, 2013 MD90-28-013 Revision 1 August 27, 2015 71 of 140 BOEING SERVICE BULLETIN MD90-28-013FIGURE 7: CENTER AND AUX FUEL BOOST AND TRANSFER WIRE CHANGES (SHEET 5 OF 13)
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 27, 2013 MD90-28-013 Revision 1 August 27, 2015 72 of 140 BOEING SERVICE BULLETIN MD90-28-013FIGURE 7: CENTER AND AUX FUEL BOOST AND TRANSFER WIRE CHANGES (SHEET 6 OF 13)
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 27, 2013 MD90-28-013 Revision 1 August 27, 2015 73 of 140 BOEING SERVICE BULLETIN MD90-28-013FIGURE 7: CENTER AND AUX FUEL BOOST AND TRANSFER WIRE CHANGES (SHEET 7 OF 13)
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 27, 2013 MD90-28-013 Revision 1 August 27, 2015 74 of 140 BOEING SERVICE BULLETIN MD90-28-013FIGURE 7: CENTER AND AUX FUEL BOOST AND TRANSFER WIRE CHANGES (SHEET 8 OF 13)
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 27, 2013 MD90-28-013 Revision 1 August 27, 2015 75 of 140 BOEING SERVICE BULLETIN MD90-28-013FIGURE 7: CENTER AND AUX FUEL BOOST AND TRANSFER WIRE CHANGES (SHEET 9 OF 13)
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 27, 2013 MD90-28-013 Revision 1 August 27, 2015 76 of 140 BOEING SERVICE BULLETIN MD90-28-013FIGURE 7: CENTER AND AUX FUEL BOOST AND TRANSFER WIRE CHANGES (SHEET 10 OF 13)
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 27, 2013 MD90-28-013 Revision 1 August 27, 2015 77 of 140 BOEING SERVICE BULLETIN MD90-28-013FIGURE 7: CENTER AND AUX FUEL BOOST AND TRANSFER WIRE CHANGES (SHEET 11 OF 13)
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 27, 2013 MD90-28-013 Revision 1 August 27, 2015 78 of 140 BOEING SERVICE BULLETIN MD90-28-013FIGURE 7: CENTER AND AUX FUEL BOOST AND TRANSFER WIRE CHANGES (SHEET 12 OF 13)
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 27, 2013 MD90-28-013 Revision 1 August 27, 2015 79 of 140 BOEING SERVICE BULLETIN MD90-28-013Reference: MD90 WDM 28-42-00 and MD90 WDM 28-25-11. The term code numbers shown below agree with the numbers shown in the term code symbols in the figure.
MORE DATA QTY PART NUMBER NAME TERM CODE 10 DC38-20P PIN, T/C 1126 1126 62 DC38-16P PIN, T/C 1131 1131 24 M39029/92-535 SOCKET, T/C 1266B 1266B 16 M39029/92-533 SOCKET, T/C 1268 1268 (a) 16 S00023-20P PIN, T/C 601/701 601/701 (a) 19 S00023-20S SOCKET, T/C 602/702 702 1 LRC22M-1DE5 SOCKET, T/C 604 604 12 LRC16M-32DJ5 SOCKET, T/C 706 706 (a) 10 5D0086-5 TERM LUG, T/C 761 761 (a) 8 5D0086-6 TERM LUG, T/C 762 762 (a) 2 5D0086-17 TERM LUG, T/C 888 888 (a) 6 5D0086-18 TERM LUG, T/C 889 889 (a) 2 5D0086-19 TERM LUG, T/C 890 890 (b) 2 CYW20 END CAP 914 (a) 2 5D0010-15 TERM BLOCK (a) 4 5D0101-2 END CLAMP (a) 2 5D0107-1 TERM BLOCK (a) 18 5D0107-3 TERM BLOCK L (a) Or approved equivalent. Refer to AEPL Drawing 7595071. (b) Operator supplied parts.

FIGURE 7: CENTER AND AUX FUEL BOOST AND TRANSFER WIRE CHANGES (SHEET 13 OF 13)
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 27, 2013 MD90-28-013 Revision 1 August 27, 2015 80 of 140 BOEING SERVICE BULLETIN MD90-28-013This Figure applies only to: Group 1.

FIGURE 8: INSTALL GFI RELAYS AND RECEPTACLES - E/E COMPARTMENT, AFT LEFT RADIO RACK (SHEET 1 OF 3)
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 27, 2013 MD90-28-013 Revision 1 August 27, 2015 81 of 140 BOEING SERVICE BULLETIN MD90-28-013FIGURE 8: INSTALL GFI RELAYS AND RECEPTACLES - E/E COMPARTMENT, AFT LEFT RADIO RACK (SHEET 2 OF 3)
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 27, 2013 MD90-28-013 Revision 1 August 27, 2015 82 of 140 BOEING SERVICE BULLETIN MD90-28-013The 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 (e) 1 7927157-707 Clip Assembly Drill 1 (f) 1 SR90280011-3 Bracket Identify (not shown) 2 R2-1495 (a) (b) 1 KDAG-X4F-001 RELAY Install/New 3 R5-1495 1 SO-1061-8916 RECEPTACLE 4 (c) (d) 4 NAS620C10 (.063 Thickness) WASHER 5 (b) 4 002-9559-000-000 SPACER 6 (b) 4 NAS620C4L WASHER 7 (b) 4 NAS1291C04CM NUT 8 R2-1494 (a) (b) 1 KDAG-X4F-001 RELAY Install/New 9 R5-1494 1 SO-1061-8916 RECEPTACLE 10 (c) (d) 4 NAS620C10 (.063 Thickness) WASHER 11 (b) 4 002-9559-000-000 SPACER 12 (b) 4 NAS620C4L WASHER 13 (b) 4 NAS1291C04CM NUT 14 (a) Applicable item number must be adjacent and visible after equipment is installed. Refer to SWPM 20-00- 09 as an accepted procedure. (b) Mounting Hardware vendor furnished. (c) Boeing furnished part. (d) NAS620C10L Washers are furnished with Receptacle and are not used in this installation. Keep the washers if there are other uses for them. (e) Drill .199-.202 diameter holes, 8 places. (f) Reidentify Clip Assembly 7927157-707 as SR90280011-3 Bracket.

FIGURE 8: INSTALL GFI RELAYS AND RECEPTACLES - E/E COMPARTMENT, AFT LEFT RADIO RACK (SHEET 3 OF 3)
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 27, 2013 MD90-28-013 Revision 1 August 27, 2015 83 of 140 BOEING SERVICE BULLETIN MD90-28-013This Figure applies only to: Group 2.

FIGURE 9: INSTALL GFI RELAYS AND RECEPTACLES - E/E COMPARTMENT, AFT LEFT RADIO RACK (SHEET 1 OF 3)
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 27, 2013 MD90-28-013 Revision 1 August 27, 2015 84 of 140 BOEING SERVICE BULLETIN MD90-28-013FIGURE 9: INSTALL GFI RELAYS AND RECEPTACLES - E/E COMPARTMENT, AFT LEFT RADIO RACK (SHEET 2 OF 3)
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 27, 2013 MD90-28-013 Revision 1 August 27, 2015 85 of 140 BOEING SERVICE BULLETIN MD90-28-013The 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 (e) 1 7961078-795 Clip Assembly Drill 1 (f) 1 SR90280011-5 Bracket Identify (not shown) 2 R2-1495 (a) (b) 1 KDAG-X4F-001 RELAY Install/New 3 R5-1495 1 SO-1061-8916 RECEPTACLE 4 (c) (d) 4 NAS620C10 (.063 Thickness) WASHER 5 (b) 4 002-9559-000-000 SPACER 6 (b) 4 NAS620C4L WASHER 7 (b) 4 NAS1291C04CM NUT 8 R2-1494 (a) (b) 1 KDAG-X4F-001 RELAY Install/New 9 R5-1494 1 SO-1061-8916 RECEPTACLE 10 (c) (d) 4 NAS620C10(.063 Thickness) WASHER 11 (b) 4 002-9559-000-000 SPACER 12 (b) 4 NAS620C4L WASHER 13 (b) 4 NAS1291C04CM NUT 14 (a) Applicable item number must be adjacent and visible after equipment is installed. Refer to SWPM 20-00- 09 as an accepted procedure. (b) Mounting Hardware vendor furnished. (c) Boeing furnished part. (d) NAS620C10L Washers are furnished with Receptacle and are not used in this installation. Keep the washers if there are other uses for them. (e) Drill .199-.202 diameter holes, 8 places. (f) Reidentify Clip Assembly 7961078-795 as SR90280011-5 Bracket.

FIGURE 9: INSTALL GFI RELAYS AND RECEPTACLES - E/E COMPARTMENT, AFT LEFT RADIO RACK (SHEET 3 OF 3)
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 27, 2013 MD90-28-013 Revision 1 August 27, 2015 86 of 140 BOEING SERVICE BULLETIN MD90-28-013This Figure applies only to: Group 3.

FIGURE 10: INSTALL GFI RELAYS AND RECEPTACLES - E/E COMPARTMENT, AFT LEFT RADIO RACK (SHEET 1 OF 5)
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 27, 2013 MD90-28-013 Revision 1 August 27, 2015 87 of 140 BOEING SERVICE BULLETIN MD90-28-013FIGURE 10: INSTALL GFI RELAYS AND RECEPTACLES - E/E COMPARTMENT, AFT LEFT RADIO RACK (SHEET 2 OF 5)
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 27, 2013 MD90-28-013 Revision 1 August 27, 2015 88 of 140 BOEING SERVICE BULLETIN MD90-28-013FIGURE 10: INSTALL GFI RELAYS AND RECEPTACLES - E/E COMPARTMENT, AFT LEFT RADIO RACK (SHEET 3 OF 5)
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 27, 2013 MD90-28-013 Revision 1 August 27, 2015 89 of 140 BOEING SERVICE BULLETIN MD90-28-013The 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 (e) 1 7927157-707 Clip Assembly Drill 1 (f) 1 SR90280011-7 Bracket Identify (not shown) 2 R2-1495 (a) (b) 1 KDAG-X4F-001 RELAY Install/New 3 R5-1495 1 SO-1061-8916 RECEPTACLE 4 (c) (d) 4 NAS620C10 (.063 Thickness) WASHER 5 (b) 4 002-9559-000-000 SPACER 6 (b) 4 NAS620C4L WASHER 7 (b) 4 NAS1291C04CM NUT 8 R2-1494 (a) (b) 1 KDAG-X4F-001 RELAY Install/New 9 R5-1494 1 SO-1061-8916 RECEPTACLE 10 (c) (d) 4 NAS620C10 (.063 Thickness) WASHER 11 (b) 4 002-9559-000-000 SPACER 12 (b) 4 NAS620C4L WASHER 13 (b) 4 NAS1291C04CM NUT 14 R2-1497 (a) (b) 1 KDG-X4L-001 RELAY Install/New 15 R5-1497(b) 1 RSE500311 RECEPTACLE 16 (b) 3 002-9653-000-000 SCREW 17 (b) 3 MS35338-135 SPLIT WASHER 18 (b) 3 NAS620C4L WASHER 19 (b) 3 002-9447-000-000 SPACER 20 (b) 3 200500101 MOUNTING STUD 21 (b) 3 200500401 WASHER 22 (b) 3 NAS679C04W LOCK-NUT 23

FIGURE 10: INSTALL GFI RELAYS AND RECEPTACLES - E/E COMPARTMENT, AFT LEFT RADIO RACK (SHEET 4 OF 5)
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 27, 2013 MD90-28-013 Revision 1 August 27, 2015 90 of 140 BOEING SERVICE BULLETIN MD90-28-013MORE DATA QTY IDENTIFICATION NAME TASK STEP R2-1496 (a) (b) 1 KDG-X4L-001 RELAY Install/New 24 R5-1496(b) 1 RSE500311 RECEPTACLE 25 (b) 3 002-9653-000-000 SCREW 26 (b) 3 MS35338-135 SPLIT WASHER 27 (b) 3 NAS620C4L WASHER 28 (b) 3 002-9447-000-000 SPACER 29 (b) 3 200500101 MOUNTING STUD 30 (b) 3 200500401 WASHER 31 (b) 3 NAS679C04W LOCK-NUT 32 (a) Applicable item number must be adjacent and visible after equipment is installed. Refer to SWPM 20-00- 09 as an accepted procedure. (b) Mounting Hardware vendor furnished. (c) Boeing furnished part. (d) NAS620C10L Washers are furnished with Receptacle and are not used in this installation. Keep the washers if there are other uses for them. (e) Drill .199-.202 diameter holes, 14 places. (f) Reidentify Clip Assembly 7927157-707 as SR90280011-7 Bracket.

FIGURE 10: INSTALL GFI RELAYS AND RECEPTACLES - E/E COMPARTMENT, AFT LEFT RADIO RACK (SHEET 5 OF 5)
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 27, 2013 MD90-28-013 Revision 1 August 27, 2015 91 of 140 BOEING SERVICE BULLETIN MD90-28-013This Appendix applies only to: Group 1. WARNING:DO NOT OPERATE A FUEL PUMP IN AN EMPTY FUEL TANK. PROLONGED DRY RUNNING OF A FUEL PUMP IN AN EMPTY TANK CAN DEGRADE INTERNAL PUMP COMPONENTS AND INCREASE THE RISK OF DEVELOPING A FUEL TANK IGNITION SOURCE. WARNING:MONITOR THE CENTER AND MAIN TANK FUEL QUANTITIES AND MAKE SURE THE AIRPLANE BALANCE IS MAINTAINED. REFER TO MD90 AMM 12-11-03 AS AN ACCEPTED PROCEDURE. WARNING:BEFORE EACH TEST MAKE SURE THE AFFECTED TANKS CONTAIN ENOUGH FUEL FOR THE TRANSFER REQUIREMENTS. 1. GROUND FAULT INTERRUPTER (GFI) CENTER FUEL TANK PUMPS CONTROL CIRCUIT, AND CENTER FUEL TANK PUMPS LOW PRESSURE INDICATION SYSTEM TEST PROCEDURES
a. Apply electrical power. Refer to MD90 AMM 24-40-00 as an accepted procedure. b. Make sure the center tank has a minimum of 1000 pounds. of fuel. Refer to MD90 AMM 12-11-07 as an accepted procedure. c. Open access panel 610TB. Refer to MD90 AMM 06-36-00. d. Close circuit breakers as follow: LOWER EPC, XFER BUS Name Number Column Row CENTER FUEL LOW PRESSURE B1-994 41 T UPPER EPC, FUEL Name Number Column Row FUEL QUANTITY POWER TRANSFER B1-822 17 J UPPER EPC, FUEL - LEFT AC BUS Name Number Column Row FWD RIGHT FUEL TANK BOOST PUMP B1-918 19 H FWD CENTER FUEL TANK BOOST PUMP B1-922 21 H AFT LEFT FUEL TANK BOOST PUMP B1-921 23 H

APPENDIX A: GFI CENTER FUEL TANK PUMPS CONTROL CIRCUIT, AND CENTER FUEL TANK PUMPS LOW PRESSURE INDICATION SYSTEM TEST PROCEDURES (SHEET 1 OF 13)
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 27, 2013 MD90-28-013 Revision 1 August 27, 2015 92 of 140 BOEING SERVICE BULLETIN MD90-28-013UPPER EPC, FUEL - R AC BUSName Number Column Row AFT CENTER FUEL TANK BOOST PUMP B1-923 21 J FWD LEFT FUEL TANK BOOST PUMP B1-920 23 J UPPER EPC, GND SERV Name Number Column Row AFT RIGHT FUEL TANK BOOST PUMP B1-919 19 J UPPER EPC, LEFT AC BUS Name Number Column Row FUEL QUANTITY POWER TRANSFER B1-955 14 H e. Make sure the landing gear is safe for maintenance. Refer to MD90 AMM 32-00-00 as an accepted procedure. f. Do the Center Fuel Pressure Low Indication System Functional Test as follows: (1) Position the FLAP/SLAT handle (1) to the UP/RET position. Refer to MD90 AMM 27-50-00 as an accepted procedure. (2) Position LEFT AFT PUMPS switch (5) to the OFF position. (3) Position CTR AFT PUMPS switch (6) to the OFF position. (4) Position RIGHT AFT PUMPS switch (7) to the OFF position. (5) Position LEFT FWD PUMPS switch (8) to the OFF position. (6) Position CTR FWD PUMPS switch (9) to the OFF position. (7) Position RIGHT FWD PUMPS switch (10) to the OFF position. Verify as follows: (a) Electronic Overhead Annunciator Panel (EOAP) (4) CENTER FUEL PRESS LO indication is OFF. (b) MASTER CAUTION (13) indication is OFF. (8) Position the CTR FWD PUMPS switch (9) to the ON position. After 12 to 32 seconds verify as follows: (a) EOAP (4) CENTER FUEL PRESS LO indication is ON. (b) MASTER CAUTION (13) indication is ON.

APPENDIX A: GFI CENTER FUEL TANK PUMPS CONTROL CIRCUIT, AND CENTER FUEL TANK PUMPS LOW PRESSURE INDICATION SYSTEM TEST PROCEDURES (SHEET 2 OF 13)
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 27, 2013 MD90-28-013 Revision 1 August 27, 2015 93 of 140 BOEING SERVICE BULLETIN MD90-28-013(9) Position the CTR FWD PUMPS switch (9) to the OFF position. Verify as follows: (a) EOAP (4) CENTER FUEL PRESS LO indication is OFF. (b) MASTER CAUTION (13) indication is OFF. (10) Position the CTR AFT PUMPS switch (6) to the ON position. After 12 to 32 seconds verify as follows: (a) EOAP (4) CENTER FUEL PRESS LO indication is ON. (b) MASTER CAUTION (13) indication is ON. (11) Position the CTR AFT PUMPS switch (6) to the OFF position. Verify as follows: (a) EOAP (4) CENTER FUEL PRESS LO indication is OFF. (b) MASTER CAUTION (13) indication is OFF. 2. CENTER TANK GFI BUILT IN TEST (BIT) a. Do a test of the center tank GFI BIT as follows: (1) Make sure the center tank has a minimum of 1000 pounds of fuel. Refer to MD90 AMM 12-11-07 as an accepted procedure. (2) Position FLAP/SLAT handle (1) to the UP/RET position. Refer to MD90 AMM 27-50-00 as an accepted procedure. (3) Position LEFT AFT PUMPS switch (5) to the OFF position. (4) Position CTR AFT PUMPS switch (6) to the OFF position. (5) Position RIGHT AFT PUMPS switch (7) to the OFF position. (6) Position LEFT FWD PUMPS switch (8) to the OFF position. (7) Position CTR FWD PUMPS switch (9) to the OFF position. (8) Position RIGHT FWD PUMPS switch (10) to the OFF position. Verify as follows: (a) Electronic Overhead Annunciator Panel (EOAP) (4) CENTER FUEL PRESS LO indication is OFF. (b) MASTER CAUTION (13) indication is OFF. (9) Close circuit breakers as follows:

APPENDIX A: GFI CENTER FUEL TANK PUMPS CONTROL CIRCUIT, AND CENTER FUEL TANK PUMPS LOW PRESSURE INDICATION SYSTEM TEST PROCEDURES (SHEET 3 OF 13)
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 27, 2013 MD90-28-013 Revision 1 August 27, 2015 94 of 140 BOEING SERVICE BULLETIN MD90-28-013UPPER EPC, FUEL - LEFT AC BUS Name Number Column Row FWD CENTER FUEL TANK BOOST PUMP B1-922 21 H AFT CENTER FUEL TANK BOOST PUMP B1-923 21 J (10) Position the CTR FWD PUMPS switch (9) and the CTR AFT PUMPS switch (6) to the ON position. After 12 to 32 seconds verify as follows: (a) EOAP (4) CENTER FUEL PRESS LO indication is OFF. (b) MASTER CAUTION (13) indication is OFF. (11) Press the CENTER FWD PUMP GFI Relay (R2-1494) TEST (23) button. The CENTER FWD PUMP is disabled, verify as follows: (a) CENTER FWD PUMP GFI Relay (R2-1494) reset indicator (24) has popped up and the white band on the indicator is visible. (b) After 12 to 32 seconds: 1) The EOAP (4) CENTER FUEL PRESS LO indication is ON. 2) The MASTER CAUTION (13) indication is ON. (12) Position the CTR AFT PUMPS switch (6) to the OFF position. Verify as follows: (a) EOAP (4) CENTER FUEL PRESS LO indication is OFF. (b) MASTER CAUTION (13) indication is OFF. (13) Position the CTR FWD PUMPS switch (9) to the OFF position. (14) Press the CENTER FWD PUMP GFI Relay (R2-1494) RESET (24) button. Verify as follows: (a) CENTER FWD PUMP GFI Relay (R2-1494) RESET (24) button remains depressed and the white band is no longer visible. (b) EOAP (4) CENTER FUEL PRESS LO indication is OFF. (c) MASTER CAUTION (13) indication is OFF. (15) Position the CTR FWD PUMPS switch (9) to the ON position. After 12 to 32 seconds verify as follows: (a) EOAP (4) CENTER FUEL PRESS LO indication is ON. (b) MASTER CAUTION (13) indication is ON.

APPENDIX A: GFI CENTER FUEL TANK PUMPS CONTROL CIRCUIT, AND CENTER FUEL TANK PUMPS LOW PRESSURE INDICATION SYSTEM TEST PROCEDURES (SHEET 4 OF 13)
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 27, 2013 MD90-28-013 Revision 1 August 27, 2015 95 of 140 BOEING SERVICE BULLETIN MD90-28-013(16) Position the CTR AFT PUMPS switch (6) to the ON position. Verify as follows: (a) EOAP (4) CENTER FUEL PRESS LO indication is OFF. (b) MASTER CAUTION (13) indication is OFF. (17) Press the CENTER AFT PUMP GFI Relay (R2-1495) TEST (23) button. The CENTER AFT PUMP is disabled, verify as follows: (a) CENTER AFT PUMP GFI Relay (R2-1495) reset indicator (24) has popped up and the white band on the indicator is visible. (b) After 12 to 32 seconds: 1) The EOAP (4) CENTER FUEL PRESS LO indication is ON. 2) The MASTER CAUTION (13) indication is ON. (18) Position the CTR FWD PUMPS switch (9) to the OFF position. Verify as follows: (a) EOAP (4) CENTER FUEL PRESS LO indication is OFF. (b) MASTER CAUTION (13) indication is OFF. (19) Position the CTR AFT PUMPS switch (6) to the OFF position. (20) Press the CENTER AFT PUMP GFI Relay (R2-1495) RESET (24) button. Verify as follows: (a) CENTER AFT PUMP GFI Relay (R2-1495) RESET (24) button remains depressed and the white band is no longer visible. (b) EOAP (4) CENTER FUEL PRESS LO indication is OFF. (c) MASTER CAUTION (13) indication is OFF. (21) Position the CTR AFT PUMPS switch (6) to the ON position. After 12 to 32 seconds verify as follows: (a) EOAP (4) CENTER FUEL PRESS LO indication is ON. (b) MASTER CAUTION (13) indication is ON. (22) Position the CTR FWD PUMPS switch (9) to the ON position. Verify as follows: (a) EOAP (4) CENTER FUEL PRESS LO indication is OFF. (b) MASTER CAUTION (13) indication is OFF. (23) Position the CTR FWD PUMPS switch (9) and CTR AFT PUMPS switch (6) to the OFF position.

APPENDIX A: GFI CENTER FUEL TANK PUMPS CONTROL CIRCUIT, AND CENTER FUEL TANK PUMPS LOW PRESSURE INDICATION SYSTEM TEST PROCEDURES (SHEET 5 OF 13)
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 27, 2013 MD90-28-013 Revision 1 August 27, 2015 96 of 140 BOEING SERVICE BULLETIN MD90-28-0133. ALTERNATE FUEL BURN SYSTEM TEST a. Place aircraft in attitude of -0.75 to -1.25 degree pitch and -.25 to .25 degree roll. Refer to MD90 AMM 08-10-00 as an accepted procedure. b. Make sure fuel tank levels are as follows:Quantity Tank 5500-5700 pounds Left Main 5500-5700 pounds Right Main 3400-3600 pounds Center
c. Position controls as follows: (1) On the center console do what follows: (a) Position the FUEL X FEED lever (3) to the OFF position. (b) Position the FUEL switches (2) to the OFF position. (2) On the overhead switch panel, do what follows: (a) Position the START PUMP switch (11) to the OFF position. (b) Position the FUEL TANKS PUMPS switches (5)(6)(7)(8)(9)(10) to the OFF position. (c) Position the APU MASTER switch (12) to the OFF position. (d) Position the FLAP/SLAT handle (1) to the UP/RET position. Refer to MD90 AMM 27-50-00 as an accepted procedure. d. Close circuit breaker as follows: LOWER EPC, DC Name Number Column Row ALT FUEL BURN B1-1007 37 M e. Do a functional test of the alternate fuel burn test system as follows: (1) On the Load Selector Display Unit (LSDU) (18), do what follows: (a) Position the POWER switch (19) to the ON position. (b) Position the AUTO/OVERRIDE switch (20) to the OVERRIDE position. (2) Open defueling shutoff valve (22).

APPENDIX A: GFI CENTER FUEL TANK PUMPS CONTROL CIRCUIT, AND CENTER FUEL TANK PUMPS LOW PRESSURE INDICATION SYSTEM TEST PROCEDURES (SHEET 6 OF 13)
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 27, 2013 MD90-28-013 Revision 1 August 27, 2015 97 of 140 BOEING SERVICE BULLETIN MD90-28-013(3) Open left main tank fill valve (14). (4) Open right main tank fill valve (15). (5) On the Overhead Fuel Panel, do what follows: (a) Position CTR AFT PUMPS switch (6) and CTR FWD PUMPS switch (9) to the AUTO position. NOTE:This initiates the transfer of fuel from the center tank to the left and right main tanks. (b) On the EOAP (4), when either the L INLET FUEL PRESS LOW or the R INLET FUEL PRESS LOW warning indication occurs, position the CTR AFT PUMPS switch (6) and CTR FWD PUMPS switch (9) to the OFF position. (c) Position CTR AFT PUMPS (6) and CTR FWD PUMPS (9) switches to the ON position. (d) After 50 - 100 pounds of fuel has been removed from the center tank, position the CTR AFT PUMPS switch (6) and CTR FWD PUMPS switch (9) to the OFF position. (e) At the right wing fuel control station, close the left main tank fill valve (14). (f) At the center console fuel controls, position the crossfeed lever (3) to the ON position. (g) Position the CTR AFT PUMPS switch (6) and CTR FWD PUMPS switch (9) to the AUTO position. (h) Open circuit breaker as follows: UPPER EPC, FUEL - LEFT AC BUS Name Number Column Row FWD CENTER FUEL TANK BOOST PUMP B1-922 21 H1) Verify that EOAP (4) CENTER FUEL PRESS LO warning indication does not appear. (i) Position the LEFT AFT PUMPS switch (5) and LEFT FWD PUMPS switch (8) to the ON position. (j) On the EOAP (4), when the CENTER FUEL PRESS LO warning indication appears, immediately place LEFT AFT PUMPS switch (5), CTR AFT PUMPS switch (6), LEFT FWD PUMPS switch (8), and CTR FWD PUMPS switch (9) to the OFF position. (k) Close circuit breaker as follows:

APPENDIX A: GFI CENTER FUEL TANK PUMPS CONTROL CIRCUIT, AND CENTER FUEL TANK PUMPS LOW PRESSURE INDICATION SYSTEM TEST PROCEDURES (SHEET 7 OF 13)
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 27, 2013 MD90-28-013 Revision 1 August 27, 2015 98 of 140 BOEING SERVICE BULLETIN MD90-28-013UPPER EPC, FUEL - LEFT AC BUS Name Number Column Row FWD CENTER FUEL TANK BOOST PUMP B1-922 21 H (l) Open circuit breaker as follows: UPPER EPC, FUEL - R AC BUSName Number Column Row AFT CENTER FUEL TANK BOOST PUMP B1-923 21 J (m) At the right wing fuel control station, close the right main tank fill valve (15). (n) At the right wing fuel control station, open the left main tank fill valve (14). (o) Position RIGHT AFT PUMPS switch (7) and RIGHT FWD PUMPS switch (10) to the ON position. (p) Position CTR AFT PUMPS switch (6) and CTR FWD PUMPS switch (9) to the AUTO position. (q) When EOAP (4) CENTER FUEL PRESS LOW warning indication reappears, immediately place RIGHT AFT PUMPS switch (7), RIGHT FWD PUMPS switch (10), CTR AFT PUMPS switch (6) and CTR FWD PUMPS switch (9) to the OFF position. (r) Close circuit breaker as follows: UPPER EPC, FUEL - R AC BUSName Number Column Row AFT CENTER FUEL TANK BOOST PUMP B1-923 21 J (s) On the right wing, close defueling shutoff valve (22) and left main tank fill valve (14). CAUTION:ENSURE CENTER TANK HAS SUFFICIENT FUEL TO TRANSFER TO MAIN TANKS. VERIFY MAIN TANKS CAN ACCEPT TRANSFERRED FUEL QUANTITY TO AVOID FUEL SPILLAGE VIA THE VENT SYSTEM. 4. Do CENTER FUEL TANK TRANSFER (AT REFUEL STATION). Refer to MD90 AMM 12-11-03 as an accepted procedure. 5. Close access panel 610TB. Refer to MD90 AMM 06-36-00.

APPENDIX A: GFI CENTER FUEL TANK PUMPS CONTROL CIRCUIT, AND CENTER FUEL TANK PUMPS LOW PRESSURE INDICATION SYSTEM TEST PROCEDURES (SHEET 8 OF 13)
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 27, 2013 MD90-28-013 Revision 1 August 27, 2015 99 of 140 BOEING SERVICE BULLETIN MD90-28-013APPENDIX A: GFI CENTER FUEL TANK PUMPS CONTROL CIRCUIT, AND CENTER FUEL TANK PUMPS LOW PRESSURE INDICATION SYSTEM TEST PROCEDURES (SHEET 9 OF 13)
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 27, 2013 MD90-28-013 Revision 1 August 27, 2015 100 of 140 BOEING SERVICE BULLETIN MD90-28-013APPENDIX A: GFI CENTER FUEL TANK PUMPS CONTROL CIRCUIT, AND CENTER FUEL TANK PUMPS LOW PRESSURE INDICATION SYSTEM TEST PROCEDURES (SHEET 10 OF 13)
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 27, 2013 MD90-28-013 Revision 1 August 27, 2015 101 of 140 BOEING SERVICE BULLETIN MD90-28-013APPENDIX A: GFI CENTER FUEL TANK PUMPS CONTROL CIRCUIT, AND CENTER FUEL TANK PUMPS LOW PRESSURE INDICATION SYSTEM TEST PROCEDURES (SHEET 11 OF 13)
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 27, 2013 MD90-28-013 Revision 1 August 27, 2015 102 of 140 BOEING SERVICE BULLETIN MD90-28-013APPENDIX A: GFI CENTER FUEL TANK PUMPS CONTROL CIRCUIT, AND CENTER FUEL TANK PUMPS LOW PRESSURE INDICATION SYSTEM TEST PROCEDURES (SHEET 12 OF 13)
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 27, 2013 MD90-28-013 Revision 1 August 27, 2015 103 of 140 BOEING SERVICE BULLETIN MD90-28-013APPENDIX A: GFI CENTER FUEL TANK PUMPS CONTROL CIRCUIT, AND CENTER FUEL TANK PUMPS LOW PRESSURE INDICATION SYSTEM TEST PROCEDURES (SHEET 13 OF 13)
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 27, 2013 MD90-28-013 Revision 1 August 27, 2015 104 of 140 BOEING SERVICE BULLETIN MD90-28-013This Appendix applies only to: Group 2. WARNING:DO NOT OPERATE A FUEL PUMP IN AN EMPTY FUEL TANK. PROLONGED DRY RUNNING OF A FUEL PUMP IN AN EMPTY TANK CAN DEGRADE INTERNAL PUMP COMPONENTS AND INCREASE THE RISK OF DEVELOPING A FUEL TANK IGNITION SOURCE. WARNING:MONITOR THE CENTER AND MAIN TANK FUEL QUANTITIES AND MAKE SURE THE AIRPLANE BALANCE IS MAINTAINED. REFER TO MD90 AMM 12-11-03 AS AN ACCEPTED PROCEDURE. WARNING:BEFORE EACH TEST MAKE SURE THE AFFECTED TANKS CONTAIN ENOUGH FUEL FOR THE TRANSFER REQUIREMENTS. 1. GROUND FAULT INTERRUPTER (GFI) CENTER FUEL TANK PUMPS CONTROL CIRCUIT, AND CENTER FUEL TANK PUMPS LOW PRESSURE INDICATION SYSTEM TEST PROCEDURES a. Apply electrical power. Refer to MD90 AMM 24-40-00 as an accepted procedure. b. Make sure the center tank has a minimum of 1000 pounds of fuel. Refer to MD90 AMM 12-11-07 as an accepted procedure. c. Open access panel 610TB. Refer to MD90 AMM 06-36-00. d. Close circuit breakers as follow: UPPER EPC, FUEL Name Number Column Row FUEL QUANTITY POWER TRANSFER B1-822 17 J UPPER EPC, FUEL - LEFT AC BUS Name Number Column Row FWD RIGHT FUEL TANK BOOST PUMP B1-918 19 H FWD CENTER FUEL TANK BOOST PUMP B1-922 21 H AFT LEFT FUEL TANK BOOST PUMP B1-921 23 H UPPER EPC, FUEL - R AC BUSName Number Column Row AFT CENTER FUEL TANK BOOST PUMP B1-923 21 J FWD LEFT FUEL TANK BOOST PUMP B1-920 23 J

APPENDIX B: GFI CENTER FUEL TANK PUMPS CONTROL CIRCUIT, AND CENTER FUEL TANK PUMPS LOW PRESSURE INDICATION SYSTEM TEST PROCEDURES (SHEET 1 OF 14)
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 27, 2013 MD90-28-013 Revision 1 August 27, 2015 105 of 140 BOEING SERVICE BULLETIN MD90-28-013UPPER EPC, GND SERV Name Number Column Row AFT RIGHT FUEL TANK BOOST PUMP B1-919 19 J UPPER EPC, LEFT AC BUS Name Number Column Row FUEL QUANTITY POWER TRANSFER B1-955 14 H e. Set the Electronic Instrument System (EIS) controls as follows: (1) Turn the six BRT knobs (1) on the system control panel (3) to the middle position. (2) Position the FUEL switchlight (2) on the system control panel (3) to the ON position. (3) The FUEL synoptic page will come into view on the System Display (SD) (31). f. Make the landing gear safe for maintenance. Refer to MD90 AMM 32-00-00 as an accepted procedure. g. Do the Center Fuel Pressure Low Indication System Functional Test as follows: (1) Position the FLAP/SLAT handle (6) on the center console to the UP/RET position. Refer to MD90 AMM 27-50-00 as an accepted procedure. (2) Position the L AFT PUMP switchlight (13) on the FUEL panel to the OFF position. (3) Position the C AFT PUMP switchlight (17) on the FUEL panel to the OFF position. After 1.5 to 2.5 minutes verify as follows: (a) CTR AFT PUMP LO alert on the SD (31) is not illuminated. (4) Position the R AFT PUMP switchlight (15) on the FUEL panel to the OFF position. (5) Position the L FWD PUMP switchlight (12) on the FUEL panel to the OFF position. (6) Position the C FWD PUMP switchlight (16) on the FUEL panel to the OFF position. After 1.5 to 2.5 minutes verify as follows: (a) CTR FWD PUMP LO alert on the SD (31) is not illuminated. (7) Position the R FWD PUMP switchlight (14) on the FUEL panel to the OFF position. (8) Position the C FWD PUMP switch (16) to the ON position. Verify as follows: (a) C FWD PUMP switchlight (16) illuminates. (b) After 1.5 to 2.5 minutes verify as follows:

APPENDIX B: GFI CENTER FUEL TANK PUMPS CONTROL CIRCUIT, AND CENTER FUEL TANK PUMPS LOW PRESSURE INDICATION SYSTEM TEST PROCEDURES (SHEET 2 OF 14)
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 27, 2013 MD90-28-013 Revision 1 August 27, 2015 106 of 140 BOEING SERVICE BULLETIN MD90-28-0131) On the SD (31), the CTR FWD PUMP LO alert comes on. 2) On the Engine and Alert Display (EAD) (32) and SD (31), the CTR FUEL PRES LO alert comes on. (9) Position the C FWD PUMP switch (16) to the OFF position. Verify as follows: (a) C FWD PUMP switchlight (16) is OFF. (b) On the SD (31), the CTR FWD PUMP LO alert is off. (c) On the EAD (32) and SD (31), the CTR FUEL PRES LO alert is OFF. (10) Position the C AFT PUMP switchlight (17) to the ON position. Verify as follows: (a) C AFT PUMP switchlight (17) illuminates. (b) After 1.5 to 2.5 minutes verify as follows: 1) On the SD (31), the CTR AFT PUMP LO alert comes on. 2) On the EAD (32) and SD (31), the CTR FUEL PRES LO alert comes on. (11) Position the C AFT PUMP switchlight (17) to the OFF position. Verify as follows: (a) C AFT PUMP switchlight (17) is OFF. (b) On the SD (31), the CTR AFT PUMP LO alert is off. (c) On the EAD (32) and SD (31), the CTR FUEL PRES LO alert is off. 2. CENTER TANK GFI BUILT IN TEST (BIT) a. Do a test of the center tank GFI BIT as follows: (1) Position the FLAP/SLAT handle (6) to the UP/RET position. Refer to MD90 AMM 27-50-00 as an accepted procedure. (2) Make sure the center tank has a minimum of 1000 pounds of fuel. Refer to MD90 AMM 12-11-07 as an accepted procedure. (3) Close circuit breakers as follow: UPPER EPC, FUEL - LEFT AC BUS Name Number Column Row FWD CENTER FUEL TANK BOOST PUMP B1-922 21 H AFT CENTER FUEL TANK BOOST PUMP B1-923 21 J

APPENDIX B: GFI CENTER FUEL TANK PUMPS CONTROL CIRCUIT, AND CENTER FUEL TANK PUMPS LOW PRESSURE INDICATION SYSTEM TEST PROCEDURES (SHEET 3 OF 14)
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 27, 2013 MD90-28-013 Revision 1 August 27, 2015 107 of 140 BOEING SERVICE BULLETIN MD90-28-013(4) Position the C FWD PUMP switchlight (16) and C AFT PUMP switchlight (17) to the ON position. Verify as follows: (a) C FWD PUMP switchlight (16) and C AFT PUMP switchlight (17) illuminate. (b) After 1.5 to 2.5 minutes verify as follows: 1) On the SD (31), the CTR FWD PUMP LO and CTR AFT PUMP LO alerts are off. 2) On the EAD (32) and SD (31), the CTR FUEL PRES LO alert is off. (5) Press the CENTER FWD PUMP GFI Relay (R2-1494) TEST button (33). The CENTER FWD PUMP is disabled, verify as follows: (a) CENTER FWD PUMP GFI Relay (R2-1494) reset indicator (34) has popped up and the white band on the indicator is visible. (b) After 1 to 15 seconds, verify the FUEL synoptic page on the SD (31) will show an amber vaned circle and amber (P) as low pressure indication for the center forward pump. (c) After 1.5 to 2.5 minutes verify as follows: 1) On the SD (31), the CTR FWD PUMP LO alert comes on. 2) On the EAD (32) and SD (31), the CTR FUEL PRES LO alert comes on. (6) Position the C FWD PUMP switchlight (16) and C AFT PUMP switchlight (17) to the OFF position. Verify as follows: (a) On the SD (31), the CTR FWD PUMP LO alert is off. (b) On the EAD (32) and SD (31), the CTR FUEL PRES LO alert is off. (7) Press the CENTER FWD PUMP GFI Relay (R2-1494) RESET button (34). Verify as follows: (a) CENTER FWD PUMP GFI Relay (R2-1494) RESET button (34) remains depressed and that the white band is no longer visible. (8) Position the C FWD PUMP switchlight (16) to the ON position. The CENTER FWD PUMP is enabled, verify as follows: (a) After 1 to 15 seconds, the FUEL synoptic page on the SD (31) will show a green vaned circle for the CENTER FWD PUMP. (b) After 1.5 to 2.5 minutes verify as follows: 1) On the SD (31), the CTR FWD PUMP LO alert comes on. 2) On the EAD (32) and SD (31), the CTR FUEL PRES LO alert comes on.

APPENDIX B: GFI CENTER FUEL TANK PUMPS CONTROL CIRCUIT, AND CENTER FUEL TANK PUMPS LOW PRESSURE INDICATION SYSTEM TEST PROCEDURES (SHEET 4 OF 14)
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 27, 2013 MD90-28-013 Revision 1 August 27, 2015 108 of 140 BOEING SERVICE BULLETIN MD90-28-013(9) Position the C AFT PUMP switchlight (17) to the ON position. Verify as follows: (a) On the SD (31), the CTR FWD PUMP LO alert is off. (b) On the EAD (32) and SD (31), the CTR FUEL PRES LO alert is off. (10) Press the CENTER AFT PUMP GFI Relay (R2-1495) TEST button (33). The CENTER AFT PUMP is disabled, verify as follows: (a) CENTER AFT PUMP GFI Relay (R2-1495) reset indicator (34) has popped up and the white band on the indicator is visible. (b) After 1 to 15 seconds, the FUEL synoptic page on the SD (31) will show an amber vaned circle and amber (P) as low pressure indication for the center aft pump. (c) After 1.5 to 2.5 minutes verify as follows: 1) On the SD (31), the CTR AFT PUMP LO alert comes on. 2) On the EAD (32) and SD (31), the CTR FUEL PRES LO alert comes on. (11) Position the C FWD PUMP switchlight (16) and C AFT PUMP switchlight (17) to the OFF position. Verify as follows: (a) On the SD (31), the CTR AFT PUMP LO alert is off. (b) On the EAD (32) and SD (31), the CTR FUEL PRES LO alert is off. (12) Press the CENTER AFT PUMP GFI Relay (R2-1495) RESET button (34). Verify as follows: (a) CENTER AFT PUMP GFI Relay (R2-1495) RESET button (34) remains depressed and that the white band is no longer visible. (13) Position the C AFT PUMP switchlight (17) to the ON position. The CENTER AFT PUMP is enabled, verify as follows: (a) After 1 to 15 seconds, the FUEL synoptic page on the SD (31) will show a green vaned circle for the CENTER AFT PUMP. (b) After 1.5 to 2.5 minutes verify as follows: 1) On the SD (31), the CTR AFT PUMP LO alert comes on. 2) On the EAD (32) and SD (31), the CTR FUEL PRES LO alert comes on. (14) Position the C FWD PUMP switchlight (16) to the ON position. Verify as follows: (a) On the SD (31), the CTR AFT PUMP LO alert is off. (b) On the EAD (32) and SD (31), the CTR FUEL PRES LO alert is off.

APPENDIX B: GFI CENTER FUEL TANK PUMPS CONTROL CIRCUIT, AND CENTER FUEL TANK PUMPS LOW PRESSURE INDICATION SYSTEM TEST PROCEDURES (SHEET 5 OF 14)
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 27, 2013 MD90-28-013 Revision 1 August 27, 2015 109 of 140 BOEING SERVICE BULLETIN MD90-28-013(15) Position the C FWD PUMP switchlight (16) and C AFT PUMP switchlight (17) to the OFF position. 3. ALTERNATE FUEL BURN SYSTEM TEST a. Place aircraft in attitude of -0.75 to -1.25 degree pitch and -.25 to .25 degree roll. Refer to MD90 AMM 08-10-00 as an accepted procedure. b. Make sure fuel tank levels are as follows:Quantity Tank 6100-6300 pounds Left Main 6100-6300 pounds Right Main 3300-3500 pounds Center c. Set the Electronic Instrument System (EIS) controls as follows: (1) Turn the six BRT knobs (1) on the system control panel (3) to the middle position. (2) Position the FUEL switchlight (2) on the system control panel (3) to the ON position. (3) The FUEL synoptic page will come into view on the SD (31). (4) Position controls as follows: (a) Position the FUEL X FEED lever (4) on the center console to the OFF position. (b) Position the FUEL shutoff switches (5) on the center console to the OFF position. (c) Position the START PUMP switchlight (11) on the FUEL panel to the OFF position. (d) Position the L FWD PUMP switchlight (12) and L AFT PUMP switchlight (13) to the OFF position. (e) Position the R FWD PUMP switchlight (14) and R AFT PUMP switchlight (15) to the OFF position. (f) Position the C FWD PUMP switchlight (16) and C AFT PUMP switchlight (17) to the OFF position. (g) Position the APU MASTER switchlight (9) on the overhead panel to the OFF position. (h) Position the FLAP/SLAT handle (6) to the UP/RET position. (i) Push the MENU switch (7) on the Multifunction Control Display Unit (MCDU) (8).

APPENDIX B: GFI CENTER FUEL TANK PUMPS CONTROL CIRCUIT, AND CENTER FUEL TANK PUMPS LOW PRESSURE INDICATION SYSTEM TEST PROCEDURES (SHEET 6 OF 14)
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 27, 2013 MD90-28-013 Revision 1 August 27, 2015 110 of 140 BOEING SERVICE BULLETIN MD90-28-013WARNING:MAKE SURE THE APPLICABLE CIRCUIT BREAKERS ARE OPEN, TAGGED, AND SAFETIED BEFORE YOU TURN THE FIRE CONTROL HANDLES. YOU CAN ACCIDENTALLY OPERATE THE FIREX AGENT CONTAINERS AND CAUSE INJURIES TO PERSONS AND DAMAGE TO EQUIPMENT. (j) Pull the LEFT and RIGHT ENG FIRE shutoff handles (21) out. d. Close circuit breaker as follows: LOWER EPC, DC Name Number Column Row ALT FUEL BURN B1-1007 37 M e. Do a functional test of the alternate fuel burn test system as follows: (1) Position the POWER switch (28) on the Load Selector Display Unit (LSDU) (26) to the ON position. (2) Position the AUTO/OVERRIDE switch (28) on the LSDU (26) to the OVERRIDE position. (3) Position the defueling shutoff valve (25) at the right wing refueling station to the OPEN position. (4) Position the LEFT MAIN TANK fill valve switch (29) on the right wing refueling panel to the AUTO FILL position. (5) Position the RIGHT MAIN TANK fill valve switch (30) on the right wing refueling panel to the AUTO FILL position. (6) Position the ALTN FUEL BURN switchlight (22) on the FUEL panel to the ON position. Verify as follows: (a) Fuel begins to transfer from the center fuel tank to the left and right main fuel tanks. (b) The FUEL synoptic page on the SD (31) shows a green circle with green vanes for the FWD and AFT boost pumps in the center fuel tank. (7) When the FWD and AFT boost pumps in the center fuel tank turn to white circles with the letter A inside, and fuel stops transferring from the center tank, place the ALTN FUEL BURN switchlight (22) in the OFF position. (a) FWD and AFT boost pumps in the center fuel tank turn to white circles without the letter A inside. (8) Position the LEFT MAIN TANK fill valve switch (29) to the CLOSED position. Verify as follows: (a) Left Main Tank fill valve (23) override handle at the right wing refueling station moves to the closed position.

APPENDIX B: GFI CENTER FUEL TANK PUMPS CONTROL CIRCUIT, AND CENTER FUEL TANK PUMPS LOW PRESSURE INDICATION SYSTEM TEST PROCEDURES (SHEET 7 OF 14)
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 27, 2013 MD90-28-013 Revision 1 August 27, 2015 111 of 140 BOEING SERVICE BULLETIN MD90-28-013(9) Position the FUEL X FEED lever on the center console to the ON position. Verify as follows: (a) The FUEL synoptic page on SD (31) shows a green circle with two horizontal parallel lines for the fuel crossfeed valve. (10) Position the ALTN FUEL BURN switchlight (22) to the ON position. Verify as follows: (a) ALTN FUEL BURN switchlight (22) ON indiction is illuminated. (b) The FUEL synoptic page on the SD (31) shows white circles with letter A inside for the FWD and AFT center tank pumps. (11) Position the L FWD PUMP switchlight (12) and L AFT PUMP switchlight (13) to the ON position. Verify as follows: (a) L FWD PUMP switchlight (12) and L AFT PUMP switchlight (13) are not illuminated. (12) When the FUEL synoptic page on the SD (31) shows green circles with green vanes for the FWD and AFT center tank pumps, position the ALTN FUEL BURN switchlight (22), L FWD PUMP switchlight (12) and L AFT PUMP switchlight (13) to the OFF position. Verify as follows: (a) The ALTN FUEL BURN switchlight (22) is not illuminated. (b) L FWD PUMP switchlight (12) and L AFT PUMP switchlight (13) OFF indication is illuminated. (13) Position the RIGHT MAIN TANK fill valve switch (30) to the CLOSED position and the LEFT MAIN TANK fill valve switch (29) to the AUTOFILL position. Verify as follows: (a) Right Main Tank fill valve (24) override handle moves to the CLOSED position. (b) Left Main Tank fill valve (23) override handle moves to the OPEN position. (14) Position the FUEL X FEED lever (4) to the OFF position. Verify as follows: (a) The FUEL synoptic page on SD (31) a shows a white circle with two parallel vertical lines for the fuel crossfeed valve. (15) Position the ALTN FUEL BURN switchlight (22) to the ON position. Verify as follows: (a) ALTN FUEL BURN switchlight (22) ON indication is illuminated. (b) The FUEL synoptic page on SD (31) shows green circles with green vanes for the FWD and AFT center tank pumps. (16) When the FWD and AFT center tank pumps turn to white circles with the letter A inside, place the R FWD PUMP switchlight (14) and R AFT PUMP switchlight (15) in the ON position. Verify as follows:

APPENDIX B: GFI CENTER FUEL TANK PUMPS CONTROL CIRCUIT, AND CENTER FUEL TANK PUMPS LOW PRESSURE INDICATION SYSTEM TEST PROCEDURES (SHEET 8 OF 14)
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 27, 2013 MD90-28-013 Revision 1 August 27, 2015 112 of 140 BOEING SERVICE BULLETIN MD90-28-013(a) The FUEL synoptic page on the SD (31) shows white circles with letter A inside for the FWD and AFT center tank pumps. (b) R FWD PUMP switchlight (14) and R AFT PUMP switchlight (15) are not illuminated. (17) When the FUEL synoptic page on SD (31) shows green circles with green vanes for the FWD and AFT center tank pumps, position the ALTN FUEL BURN switchlight (22), R FWD PUMP switchlight (14) and R AFT PUMP switchlight (15) to the OFF position. Verify as follows: (a) ALTN FUEL BURN switchlight is not illuminated. (b) R FWD PUMP switchlight (14) and R AFT PUMP switchlight (15) have OFF indication illuminated. (18) Position the defueling shutoff valve (25) to the CLOSED position. (19) Position the LEFT MAIN TANK fill valve switch (29) to the CLOSED position. (20) Push the LEFT and RIGHT ENG FIRE shutoff handles (21) in. CAUTION:ENSURE CENTER TANK HAS SUFFICIENT FUEL TO TRANSFER TO MAIN TANKS. VERIFY MAIN TANKS CAN ACCEPT TRANSFERRED FUEL QUANTITY TO AVOID FUEL SPILLAGE VIA THE VENT SYSTEM. 4. Do CENTER FUEL TANK TRANSFER (AT REFUEL STATION). Refer to MD90 AMM 12-11-03 as an accepted procedure. 5. Close access panel 610TB. Refer to MD90 AMM 06-36-00.

APPENDIX B: GFI CENTER FUEL TANK PUMPS CONTROL CIRCUIT, AND CENTER FUEL TANK PUMPS LOW PRESSURE INDICATION SYSTEM TEST PROCEDURES (SHEET 9 OF 14)
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 27, 2013 MD90-28-013 Revision 1 August 27, 2015 113 of 140 BOEING SERVICE BULLETIN MD90-28-013APPENDIX B: GFI CENTER FUEL TANK PUMPS CONTROL CIRCUIT, AND CENTER FUEL TANK PUMPS LOW PRESSURE INDICATION SYSTEM TEST PROCEDURES (SHEET 10 OF 14)
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 27, 2013 MD90-28-013 Revision 1 August 27, 2015 114 of 140 BOEING SERVICE BULLETIN MD90-28-013APPENDIX B: GFI CENTER FUEL TANK PUMPS CONTROL CIRCUIT, AND CENTER FUEL TANK PUMPS LOW PRESSURE INDICATION SYSTEM TEST PROCEDURES (SHEET 11 OF 14)
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 27, 2013 MD90-28-013 Revision 1 August 27, 2015 115 of 140 BOEING SERVICE BULLETIN MD90-28-013APPENDIX B: GFI CENTER FUEL TANK PUMPS CONTROL CIRCUIT, AND CENTER FUEL TANK PUMPS LOW PRESSURE INDICATION SYSTEM TEST PROCEDURES (SHEET 12 OF 14)
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 27, 2013 MD90-28-013 Revision 1 August 27, 2015 116 of 140 BOEING SERVICE BULLETIN MD90-28-013APPENDIX B: GFI CENTER FUEL TANK PUMPS CONTROL CIRCUIT, AND CENTER FUEL TANK PUMPS LOW PRESSURE INDICATION SYSTEM TEST PROCEDURES (SHEET 13 OF 14)
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 27, 2013 MD90-28-013 Revision 1 August 27, 2015 117 of 140 BOEING SERVICE BULLETIN MD90-28-013APPENDIX B: GFI CENTER FUEL TANK PUMPS CONTROL CIRCUIT, AND CENTER FUEL TANK PUMPS LOW PRESSURE INDICATION SYSTEM TEST PROCEDURES (SHEET 14 OF 14)
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 27, 2013 MD90-28-013 Revision 1 August 27, 2015 118 of 140 BOEING SERVICE BULLETIN MD90-28-013This Appendix applies only to: Group 3. WARNING:DO NOT OPERATE A FUEL PUMP IN AN EMPTY FUEL TANK. PROLONGED DRY RUNNING OF A FUEL PUMP IN AN EMPTY TANK CAN DEGRADE INTERNAL PUMP COMPONENTS AND INCREASE THE RISK OF DEVELOPING A FUEL TANK IGNITION SOURCE. WARNING:MONITOR THE CENTER AND MAIN TANK FUEL QUANTITIES AND MAKE SURE THE AIRPLANE BALANCE IS MAINTAINED. REFER TO MD90 AMM 12-11-03 AS AN ACCEPTED PROCEDURE. WARNING:BEFORE EACH TEST MAKE SURE THE AFFECTED TANKS CONTAIN ENOUGH FUEL FOR THE TRANSFER REQUIREMENTS. 1. GROUND FAULT INTERRUPTER (GFI) CENTER FUEL TANK PUMPS CONTROL CIRCUIT, AND CENTER FUEL TANK PUMPS LOW PRESSURE INDICATION TEST PROCEDURES a. Apply electrical power. Refer to MD90 AMM 24-40-00 as an accepted procedure. b. Make sure the center tank has a minimum of 1000 pounds of fuel. Refer to MD90 AMM 12-11-07 as an accepted procedure. c. Open access panel 610TB. Refer to MD90 AMM 06-36-00. d. Close circuit breakers as follow: LOWER EPC, XFER BUS Name Number Column Row CENTER FUEL LOW PRESSURE B1-994 41 T UPPER EPC, FUEL Name Number Column Row FUEL QUANTITY POWER TRANSFER B1-822 17 J UPPER EPC, FUEL - LEFT AC BUS Name Number Column Row FWD RIGHT FUEL TANK BOOST PUMP B1-918 19 H FWD CENTER FUEL TANK BOOST PUMP B1-922 21 H AFT LEFT FUEL TANK BOOST PUMP B1-921 23 H UPPER EPC, FUEL - R AC BUSName Number Column Row AFT CENTER FUEL TANK BOOST PUMP B1-923 21 J

APPENDIX C: GFI CENTER/AUX FUEL TANK PUMPS CONTROL CIRCUIT, AND CENTER/AUX FUEL TANK PUMPS LOW PRESSURE INDICATION SYSTEM TEST PROCEDURES (SHEET 1 OF 21)
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 27, 2013 MD90-28-013 Revision 1 August 27, 2015 119 of 140 BOEING SERVICE BULLETIN MD90-28-013UPPER EPC, FUEL - R AC BUSName Number Column Row FWD LEFT FUEL TANK BOOST PUMP B1-920 23 J UPPER EPC, GND SERV Name Number Column Row AFT RIGHT FUEL TANK BOOST PUMP B1-919 19 J UPPER EPC, LEFT AC BUS Name Number Column Row FUEL QUANTITY POWER TRANSFER B1-955 14 H e. Make sure the landing gear is safe for maintenance. Refer to MD90 AMM 32-00-00 as an accepted procedure. f. Do the Center Fuel Pressure Low Indication System Functional Test as follows: (1) Position FLAP/SLAT handle (1) to the UP/RET position. Refer to MD90 AMM 27-50-00 as an accepted procedure. (2) Position LEFT AFT PUMPS switch (5) to the OFF position. (3) Position CTR AFT PUMPS switch (6) to the OFF position. (4) Position RIGHT AFT PUMPS switch (7) to the OFF position. (5) Position LEFT FWD PUMPS switch (8) to the OFF position. (6) Position CTR FWD PUMPS switch (9) ton the OFF position. (7) Position RIGHT FWD PUMPS switch (10) to the OFF position. Verify as follows: (a) Electronic Overhead Annunciator Panel (EOAP) (4) CENTER FUEL PRESS LO indication is OFF. (b) MASTER CAUTION (13) indication is OFF. (8) Position the CTR FWD PUMPS switch (9) to the ON position. After 12 to 32 seconds verify as follows: (a) EOAP (4) CENTER FUEL PRESS LO indication is ON. (b) MASTER CAUTION (13) indication is ON. (9) Position the CTR FWD PUMPS switch (9) to the OFF position. Verify as follows:

APPENDIX C: GFI CENTER/AUX FUEL TANK PUMPS CONTROL CIRCUIT, AND CENTER/AUX FUEL TANK PUMPS LOW PRESSURE INDICATION SYSTEM TEST PROCEDURES (SHEET 2 OF 21)
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 27, 2013 MD90-28-013 Revision 1 August 27, 2015 120 of 140 BOEING SERVICE BULLETIN MD90-28-013(a) EOAP (4) CENTER FUEL PRESS LO indication is OFF. (b) MASTER CAUTION (13) indication is OFF. (10) Position the CTR AFT PUMPS switch (6) to the ON position. After 12 to 32 seconds verify as follows: (a) EOAP (4) CENTER FUEL PRESS LO indication is ON. (b) MASTER CAUTION (13) indication is ON. (11) Position the CTR AFT PUMPS switch (6) to the OFF position. Verify as follows: (a) EOAP (4) CENTER FUEL PRESS LO indication is OFF. (b) MASTER CAUTION (13) indication is OFF. 2. CENTER TANK GFI BUILT IN TEST (BIT) a. Do a test of the center tank GFI BIT as follows: (1) Make sure the center tank has a minimum of 1000 pounds of fuel in center tank. (2) Position FLAP/SLAT handle (1) to the UP/RET position. Refer to MD90 AMM 27-50-00 as an accepted procedure. (3) Position LEFT AFT PUMPS switch (5) to the OFF position. (4) Position CTR AFT PUMPS switch (6) to the OFF position. (5) Position RIGHT AFT PUMPS switch (7) to the OFF position. (6) Position LEFT FWD PUMPS switch (8) to the OFF position. (7) Position CTR FWD PUMPS switch (9) ton the OFF position. (8) Position RIGHT FWD PUMPS switch (10) to the OFF position. Verify as follows: (a) Electronic Overhead Annunciator Panel (EOAP) (4) CENTER FUEL PRESS LO indication is OFF. (b) MASTER CAUTION (13) indication is OFF. (9) Close circuit breakers as follows: UPPER EPC, FUEL - LEFT AC BUS Name Number Column Row FWD CENTER FUEL TANK BOOST PUMP B1-922 21 H

APPENDIX C: GFI CENTER/AUX FUEL TANK PUMPS CONTROL CIRCUIT, AND CENTER/AUX FUEL TANK PUMPS LOW PRESSURE INDICATION SYSTEM TEST PROCEDURES (SHEET 3 OF 21)
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 27, 2013 MD90-28-013 Revision 1 August 27, 2015 121 of 140 BOEING SERVICE BULLETIN MD90-28-013UPPER EPC, FUEL - LEFT AC BUS Name Number Column Row AFT CENTER FUEL TANK BOOST PUMP B1-923 21 J (10) Position the CTR FWD PUMPS switch (9) and CTR AFT PUMPS switch (6) to the ON position. After 12 to 32 seconds verify as follows: (a) EOAP (4) CENTER FUEL PRESS LO indication is OFF. (b) MASTER CAUTION (13) indication is OFF. (11) Press the CENTER FWD PUMP GFI Relay (R2-1494) TEST (23) button. The CENTER FWD PUMP is disabled, verify as follows: (a) CENTER FWD PUMP GFI Relay (R2-1494) reset indicator (24) has popped up and the white band on the indicator is visible. (b) After 12 to 32 seconds: 1) The EOAP (4) CENTER FUEL PRESS LO indication is ON. 2) The MASTER CAUTION (13) indication is ON. (12) Position the CTR AFT PUMPS switch (6) to the OFF position. Verify as follows: (a) EOAP (4) CENTER FUEL PRESS LO indication is OFF. (b) MASTER CAUTION (13) indication is OFF. (13) Position the CTR FWD PUMPS switch (9) to the OFF position. (14) Press the CENTER FWD PUMP GFI Relay (R2-1494) RESET (24) button. Verify as follows: (a) CENTER FWD PUMP GFI Relay (R2-1494) RESET (24) button remains depressed and the white band is no longer visible. (b) EOAP (4) CENTER FUEL PRESS LO indication is OFF. (c) MASTER CAUTION (13) indication is OFF. (15) Position the CTR FWD PUMPS switch (9) to the ON position. After 12 to 32 seconds verify as follows: (a) EOAP (4) CENTER FUEL PRESS LO indication is ON. (b) MASTER CAUTION (13) indication is ON. (16) Position the CTR AFT PUMPS switch (6) to the ON position. Verify as follows:

APPENDIX C: GFI CENTER/AUX FUEL TANK PUMPS CONTROL CIRCUIT, AND CENTER/AUX FUEL TANK PUMPS LOW PRESSURE INDICATION SYSTEM TEST PROCEDURES (SHEET 4 OF 21)
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 27, 2013 MD90-28-013 Revision 1 August 27, 2015 122 of 140 BOEING SERVICE BULLETIN MD90-28-013(a) EOAP (4) CENTER FUEL PRESS LO indication is OFF. (b) MASTER CAUTION (13) indication is OFF. (17) Press the CENTER AFT PUMP GFI Relay (R2-1495) TEST (23) button. The CENTER AFT PUMP is disabled, verify as follows: (a) CENTER AFT PUMP GFI Relay (R2-1495) reset indicator (24) has popped up and the white band on the indicator is visible. (b) After 12 to 32 seconds: 1) The EOAP (4) CENTER FUEL PRESS LO indication is ON. 2) The MASTER CAUTION (13) indication is ON. (18) Position the CTR FWD PUMPS switch (9) to the OFF position. Verify as follows: (a) EOAP (4) CENTER FUEL PRESS LO indication is OFF. (b) MASTER CAUTION (13) indication is OFF. (19) Position the CTR AFT PUMPS switch (6) to the OFF position. (20) Press the CENTER AFT PUMP GFI Relay (R2-1495) RESET (24) button. Verify as follows: (a) CENTER AFT PUMP GFI Relay (R2-1495) RESET (24) button remains depressed and the white band is no longer visible. (b) EOAP (4) CENTER FUEL PRESS LO indication is OFF. (c) MASTER CAUTION (13) indication is OFF. (21) Position the CTR AFT PUMPS switch (6) to the ON position. After 12 to 32 seconds verify as follows: (a) EOAP (4) CENTER FUEL PRESS LO indication is ON. (b) MASTER CAUTION (13) indication is ON. (22) Position the CTR FWD PUMPS switch (9) to the ON position. Verify as follows: (a) EOAP (4) CENTER FUEL PRESS LO indication is OFF. (b) MASTER CAUTION (13) indication is OFF. (23) Position the CTR FWD PUMPS switch (9) and CTR AFT PUMPS switch (6) to the OFF position. 3. ALTERNATE FUEL BURN SYSTEM TEST

APPENDIX C: GFI CENTER/AUX FUEL TANK PUMPS CONTROL CIRCUIT, AND CENTER/AUX FUEL TANK PUMPS LOW PRESSURE INDICATION SYSTEM TEST PROCEDURES (SHEET 5 OF 21)
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 27, 2013 MD90-28-013 Revision 1 August 27, 2015 123 of 140 BOEING SERVICE BULLETIN MD90-28-013a. Place aircraft in attitude of -0.75 to -1.25 degree pitch and -.25 to .25 degree roll. Refer to MD90 AMM 08-10-00 as an accepted procedure. b. Make sure fuel tank levels are as follows:Quantity Tank 5500-5700 pounds Left Main 5500-5700 pounds Right Main 3400-3600 pounds Center
c. Position controls as follows: (1) On the center console do what follows: (a) Position the FUEL X FEED lever (3) to the OFF position. (b) Position the FUEL switches (2) to the OFF position. (2) On the overhead switch panel, do what follows: (a) Position the START PUMP switch (11) to the OFF position. (b) Position the FUEL TANKS PUMPS switches (5)(6)(7)(8)(9)(10) to the OFF position. (c) Position the APU MASTER switch (12) to the OFF position. (d) Position the FLAP/SLAT handle (1) to the UP/RET position. Refer to MD90 AMM 27-50-00 as an acceptable procedure. d. Close circuit breaker as follows: LOWER EPC, DC Name Number Column Row ALT FUEL BURN B1-1007 37 M e. Do a functional test of the alternate fuel burn test system as follows: (1) On the Load Selector Display Unit (LSDU) (18), do what follows: (a) Position the POWER switch (19) to the ON position. (b) Position the AUTO/OVERRIDE switch (20) to the OVERRIDE position. (2) Open defueling shutoff valve (22). (3) Open left main tank fill valve (14).

APPENDIX C: GFI CENTER/AUX FUEL TANK PUMPS CONTROL CIRCUIT, AND CENTER/AUX FUEL TANK PUMPS LOW PRESSURE INDICATION SYSTEM TEST PROCEDURES (SHEET 6 OF 21)
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 27, 2013 MD90-28-013 Revision 1 August 27, 2015 124 of 140 BOEING SERVICE BULLETIN MD90-28-013(4) Open right main tank fill valve (15). (5) On the Overhead Fuel Panel, do what follows: (a) Position CTR AFT PUMPS switch (6) and CTR FWD PUMPS switch (9) to the AUTO position. NOTE:This initiates the transfer of fuel from the center tank to the left and right main tanks. (b) On the EOAP (4), when either the L INLET FUEL PRESS LOW or the R INLET FUEL PRESS LOW warning indication occurs, position the CTR AFT PUMPS switch (6) and CTR FWD PUMPS switch (9) to the OFF position. (c) Position CTR AFT PUMPS switch (6) and CTR FWD PUMPS (9) switches to the ON position. (d) After 50 - 100 pounds of fuel has been removed from the center tank, position the CTR AFT PUMPS switch (6) and CTR FWD PUMPS switch (9) to the OFF position. (e) At the right wing fuel control station, close the left main tank fill valve (14). (f) At the center console fuel controls, position the crossfeed lever (3) to the ON position. (g) Position the CTR AFT PUMPS switch (6) and CTR FWD PUMPS switch (9) to the AUTO position. (h) Open circuit breaker as follows: UPPER EPC, FUEL - LEFT AC BUS Name Number Column Row FWD CENTER FUEL TANK BOOST PUMP B1-922 21 H1) Verify that EOAP (4) CENTER FUEL PRESS LO warning indication does not appear. (i) Position the LEFT AFT PUMPS switch (5) and LEFT FWD PUMPS switch (8) to the ON position. (j) On the EOAP (4), when the CENTER FUEL PRESS LO warning indication appears, immediately place LEFT AFT PUMPS switch (5), CTR AFT PUMPS switch (6), LEFT FWD PUMPS switch (8), and CTR FWD PUMPS switch (9) to the OFF position. (k) Close circuit breaker as follows: UPPER EPC, FUEL - LEFT AC BUS Name Number Column Row FWD CENTER FUEL TANK BOOST PUMP B1-922 21 H

APPENDIX C: GFI CENTER/AUX FUEL TANK PUMPS CONTROL CIRCUIT, AND CENTER/AUX FUEL TANK PUMPS LOW PRESSURE INDICATION SYSTEM TEST PROCEDURES (SHEET 7 OF 21)
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 27, 2013 MD90-28-013 Revision 1 August 27, 2015 125 of 140 BOEING SERVICE BULLETIN MD90-28-013(l) Open circuit breaker as follows: UPPER EPC, FUEL - R AC BUSName Number Column Row AFT CENTER FUEL TANK BOOST PUMP B1-923 21 J (m) At the right wing fuel control station, close the right main tank fill valve (15). (n) At the right wing fuel control station, open the left main tank fill valve (14). (o) Position RIGHT AFT PUMPS switch (7) and RIGHT FWD PUMPS switch (10) to the ON position. (p) Position CTR AFT PUMPS switch (6) and CTR FWD PUMPS switch (9) to the AUTO position. (q) When EOAP (4) CENTER FUEL PRESS LOW warning indication reappears, immediately place RIGHT AFT PUMPS switch (7), RIGHT FWD PUMPS switch (10), CTR AFT PUMPS switch (6) and CTR FWD PUMPS switch (9) to the OFF position. (r) Close circuit breaker as follows: UPPER EPC, FUEL - R AC BUSName Number Column Row AFT CENTER FUEL TANK BOOST PUMP B1-923 21 J (s) On the right wing, close defueling shutoff valve (22) and left main tank fill valve (14). CAUTION:ENSURE CENTER TANK HAS SUFFICIENT FUEL TO TRANSFER TO MAIN TANKS. VERIFY MAIN TANKS CAN ACCEPT TRANSFERRED FUEL QUANTITY TO AVOID FUEL SPILLAGE VIA THE VENT SYSTEM. 4. Do CENTER FUEL TANK TRANSFER (AT REFUEL STATION). Refer to MD90 AMM 12-11-03 as an accepted procedure. 5. FUNCTIONAL TEST OF THE FORWARD AUXILIARY TANK FEED SYSTEM a. Make sure the center fuel tank is refueled between 18,500 and 19,000 pounds. Refer to MD90 AMM 12-11-07 as an accepted procedure. CAUTION:TO PREVENT FUEL SPILLAGE, ENSURE LEFT AND RIGHT MAIN FUEL TANKS WILL ACCOMMODATE THE FUEL TO BE TRANSFERRED TO THEM. b. Place aircraft in attitude of -0.75 to -1.25 degree pitch and -.25 to .25 degree roll. Refer to MD90 AMM 08-10-00 as an accepted procedure.

APPENDIX C: GFI CENTER/AUX FUEL TANK PUMPS CONTROL CIRCUIT, AND CENTER/AUX FUEL TANK PUMPS LOW PRESSURE INDICATION SYSTEM TEST PROCEDURES (SHEET 8 OF 21)
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 27, 2013 MD90-28-013 Revision 1 August 27, 2015 126 of 140 BOEING SERVICE BULLETIN MD90-28-013NOTE:The landing gear struts can be deflated to establish the necessary attitude and roll. Refer to MD90 AMM 32-11-01 as an accepted procedure. c. Close circuit breakers as follow: UPPER EPC, BATT DIR BUS Name Number Column Row GROUND REFUELING B1-106 16 B UPPER EPC, ENGINE - LEFT DC BUS Name Number Column Row AUX FUEL XFER CONTROL A B1-903 36 S
UPPER EPC, ENGINE - RIGHT DC BUS Name Number Column Row AUX FUEL XFER CONTROL B B1-904 36 T UPPER EPC, FUEL Name Number Column Row FUEL QUANTITY POWER TRANSFER B1-822 17 J UPPER EPC, FUEL - LEFT AC BUS Name Number Column Row FWD RIGHT FUEL TANK BOOST PUMP B1-918 19 H FWD CENTER FUEL TANK BOOST PUMP B1-922 21 H AFT LEFT FUEL TANK BOOST PUMP B1-921 23 H FWD AUX TANK FUEL XFER PUMP A B1-907 25 H UPPER EPC, FUEL - R AC BUSName Number Column Row AFT CENTER FUEL TANK BOOST PUMP B1-923 21 J FWD LEFT FUEL TANK BOOST PUMP B1-920 23 J FWD AUX TANK FUEL XFER PUMP B B1-908 25 J

APPENDIX C: GFI CENTER/AUX FUEL TANK PUMPS CONTROL CIRCUIT, AND CENTER/AUX FUEL TANK PUMPS LOW PRESSURE INDICATION SYSTEM TEST PROCEDURES (SHEET 9 OF 21)
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 27, 2013 MD90-28-013 Revision 1 August 27, 2015 127 of 140 BOEING SERVICE BULLETIN MD90-28-013UPPER EPC, GND SERV Name Number Column Row AFT RIGHT FUEL TANK BOOST PUMP B1-919 19 J
WARNING:DO NOT OPERATE A FUEL PUMP IN AN EMPTY FUEL TANK. PROLONGED DRY RUNNING OF A FUEL PUMP IN AN EMPTY TANK CAN DEGRADE INTERNAL PUMP COMPONENTS AND INCREASE THE RISK OF DEVELOPING A FUEL TANK IGNITION SOURCE. d. Do Forward Auxiliary Tank Feed System Test as follows: (1) You must continuously monitor pump operation to make sure that the pump does not run dry. (2) If it is necessary to operate a pump that is not continuously monitored, make sure that there is sufficient fuel in the related tank that the pump will not run dry. (3) The pump must be turned off when you get to the necessary fuel level, or before, if the related low pressure indication comes on. (4) On the overhead switch panel, do what follows: (a) Position the FWD AUX TRANS A switch (25) to the TEST position. Verify as follows: 1) On the Electronic Overhead Annunciator panel (EOAP) (4), the FWD AUX FUEL PRESS LO message comes on momentarily and then goes out. (b) Position the FWD AUX TRANS A switch (25) to the OFF position. (c) Position the FWD AUX TRANS B switch (26) to the TEST position. Verify as follows: 1) On the EOAP (4), FWD AUX FUEL PRESS LO message comes on momentarily and then goes out. (d) Position the FWD AUX TRANS B switch (26) to the OFF position. (e) Position the FWD AUX TRANS A switch (25) and FWD AUX TRANS B switch (26) to the AUTO position. Verify as follows: 1) FWD AUX FUEL PRESS LO message is not displayed on the EOAP (4). 2) FWD tank on the COCKPIT DISPLAY UNIT (CDU) (27) does not decrease in fuel level. (f) Position the FWD CTR PUMP switch (9) and AFT CTR PUMP switch (6) to the ON position. (5) On the refuel control panel, do what follows:

APPENDIX C: GFI CENTER/AUX FUEL TANK PUMPS CONTROL CIRCUIT, AND CENTER/AUX FUEL TANK PUMPS LOW PRESSURE INDICATION SYSTEM TEST PROCEDURES (SHEET 10 OF 21)
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 27, 2013 MD90-28-013 Revision 1 August 27, 2015 128 of 140 BOEING SERVICE BULLETIN MD90-28-013(a) Open the defueling shutoff valve (22). (b) Position the POWER switch (19) to the ON position. (c) Position the LEFT MAIN TANK fill valve switch (28) and RIGHT MAIN TANK fill valve switch (29) to the AUTOFILL position. (d) Position the AUTO OVERRIDE switch (20) to the OVERRIDE position. (6) On the main instrument panel, do what follows: (a) On the CDU (27), verify that fuel in the CTR tank decreases. (b) Monitor the fuel quantity in the CTR tank until the fuel level decreases to 16,600 to 18,400 pounds. (c) When the fuel quantity reaches 16,600 to 18,400 pounds, verify that FWD AUX FUEL PRES LO message comes on momentarily on the EOAP (4). (d) When the forward auxiliary tank starts to transfer fuel, make a note of the fuel quantity in the center tank. (e) Monitor the CDU (27) and verify that the fuel quantity in the FWD tank decreases. (7) On the overhead switch panel, position the FWD CTR PUMP switch (9) and AFT CTR PUMP switch (6) to the OFF position. (8) On the refuel control panel, do what follows: (a) Close the defueling shutoff valve (22). (b) Position the LEFT MAIN TANK fill valve switch (28) and RIGHT MAIN TANK fill valve switch (29) to the CLOSED position. (9) On the CDU (27), verify that fuel quantity in the CTR tank increases and the fuel quantity in the FWD tank decreases. (10) On the overhead switch panel, do what follows: (a) Position the FWD AUX TRANS A switch (25) in the OFF position. Verify as follows: 1) The fuel quantity in the CTR tank on the CDU (27) continues to increase. 2) The fuel quantity in the FWD tank on the CDU (27) continues to decrease. NOTE:Do not place both AUX TRANS switches in the OFF position at the same time. At least one pump must remain ON to keep the pump holding relays closed. (b) Position the FWD AUX TRANS A switch (25) to the AUTO position. Verify as follows:

APPENDIX C: GFI CENTER/AUX FUEL TANK PUMPS CONTROL CIRCUIT, AND CENTER/AUX FUEL TANK PUMPS LOW PRESSURE INDICATION SYSTEM TEST PROCEDURES (SHEET 11 OF 21)
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 27, 2013 MD90-28-013 Revision 1 August 27, 2015 129 of 140 BOEING SERVICE BULLETIN MD90-28-0131) FWD AUX FUEL PRESS LO message on the EOAP (4) remains off. (c) Position FWD AUX TRANS B switch (26) to the off position. Verify as follows: 1) The fuel quantity in the CTR tank on the CDU (27) continues to increase. 2) The fuel quantity in the FWD tank on the CDU (27) continues to decrease. (d) Position the FWD AUX TRANS B switch (26) to the AUTO position. Verify as follows: 1) FWD AUX FUEL PRESS LO message on the EOAP (4) remains off. (e) Open circuit breakers as follow: LOWER EPC, FUEL LEFT AC BUS Name Number Column Row AUX FUEL XFER CONTROL A B1-907 25 H LOWER EPC, FUEL - R AC BUSName Number Column Row AUX FUEL XFER CONTROL B B1-908 25 J1) Verify the FWD AUX FUEL PRESS LO message on the EOAP (4) comes on. 6. FORWARD AUX TANK GROUND FAULT INTERRUPTER (GFI) BUILT IN TEST (BIT) AND ALTERNATE ENABLE TEST WARNING:BE SURE THE CENTER FUEL TANK QUANTITY IS BELOW 17,500 POUNDS DURING THE TEST THAT FOLLOWS, THE CENTER FUEL TANK SHOULD REMAIN BELOW 17,500 POUNDS. REFER TO MD90 AMM 12-11-07 AS AN ACCEPTED PROCEDURE. a. Open circuit breakers as follow: LOWER EPC, FUEL LEFT AC BUS Name Number Column Row AUX FUEL XFER CONTROL A B1-907 25 H LOWER EPC, FUEL - R AC BUSName Number Column Row AUX FUEL XFER CONTROL B B1-908 25 J b. On the overhead switch panel, do what follows:

APPENDIX C: GFI CENTER/AUX FUEL TANK PUMPS CONTROL CIRCUIT, AND CENTER/AUX FUEL TANK PUMPS LOW PRESSURE INDICATION SYSTEM TEST PROCEDURES (SHEET 12 OF 21)
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 27, 2013 MD90-28-013 Revision 1 August 27, 2015 130 of 140 BOEING SERVICE BULLETIN MD90-28-013(1) Position the FWD AUX TRANS A switch (25) and FWD AUX TRANS B switches (26) to the AUTO position. Verify as follows: (a) FWD AUX FUEL PRESS LO message on the EOAP (4) comes on and remains on. (2) Position the FWD AUX TRANS A switch (25) and FWD AUX TRANS B switch (26) to the OFF position. Verify as follows: (a) FWD AUX FUEL PRESS LO message on the EOAP (4) goes off. c. Close circuit breaker as follows: LOWER EPC, FUEL LEFT AC BUS Name Number Column Row AUX FUEL XFER CONTROL A B1-907 25 H d. On the overhead switch panel, position the FWD AUX TRANS A switch (25) to the AUTO position. Verify as follows: (1) FWD AUX FUEL PRESS LO message on the EOAP (4) remains off. e. Press the FWD AUX TRANS A GFI Relay (R2-1496) TEST (23) button. Verify what follows: (1) FWD AUX TRANS A GFI Relay (R2-1496) reset indicator (24) has popped up and that the white band on the indicator is visible. (2) FWD AUX FUEL PRESS LO message on the EOAP (4) comes on and remains on. (3) On the CDU (27), the transfer of fuel from the FWD tank to the CTR tank ceases. f. On the overhead switch panel, position the FWD AUX TRANS A switch (25) to the OFF position. Verify as follows: (1) FWD AUX FUEL PRESS LO message on the EOAP (4) goes off. g. Press the FWD AUX TRANS A GFI Relay (R2-1496) RESET (24) button. Verify as follows: (1) FWD AUX TRANS A GFI Relay (R2-1496) RESET (24) button remains depressed and the white band is no longer visible. (2) FWD AUX FUEL PRESS LO message on the EOAP (4) remains off. h. On the overhead switch panel, do as follows: (1) Position the FWD AUX TRANS A switch (25) to the TEST position. Verify as follows: (a) On the EOAP (4), the FWD AUX FUEL PRESS LO message comes on momentarily and then goes out.

APPENDIX C: GFI CENTER/AUX FUEL TANK PUMPS CONTROL CIRCUIT, AND CENTER/AUX FUEL TANK PUMPS LOW PRESSURE INDICATION SYSTEM TEST PROCEDURES (SHEET 13 OF 21)
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 27, 2013 MD90-28-013 Revision 1 August 27, 2015 131 of 140 BOEING SERVICE BULLETIN MD90-28-013(2) Place the FWD AUX TRANS A switch (25) to OFF position. Verify as follows: (a) On the EOAP (4), verify the FWD AUX FUEL PRESS LO message remains off. i. On the overhead switch panel, place the FWD AUX TRANS A switch (25) and FWD AUX TRANS B switch (26) to the AUTO position. j. Open circuit breaker as follows: LOWER EPC, FUEL LEFT AC BUS Name Number Column Row AUX FUEL XFER CONTROL A B1-907 25 H (1) Verify FWD AUX FUEL PRESS LO message on the EOAP (4) comes on and remains on. k. On the overhead switch panel, position the FWD AUX TRANS A switch (25) and FWD AUX TRANS B switch (26) to the OFF position. Verify as follows: (1) FWD AUX FUEL PRESS LO message on the EOAP (4) goes off. l. Close circuit breaker as follows: LOWER EPC, FUEL LEFT AC BUS Name Number Column Row AUX FUEL XFER CONTROL B B1-908 25 J m. On the overhead switch panel, position the FWD AUX TRANS B switch (26) to the AUTO position. Verify as follows: (1) FWD AUX FUEL PRESS LO message on the EOAP (4) remains off. n. Press the FWD AUX TRANS B GFI Relay (R2-1497) TEST (23) button. Verify as follows: (1) FWD AUX TRANS B GFI Relay (R2-1497) reset indicator (24) has popped up and the white band on the indicator is visible. (2) FWD AUX FUEL PRESS LO message on the EOAP (4) comes on and remains on. (3) On the CDU (27), the transfer of fuel from the FWD tank to the CTR tank ceases. o. On the overhead switch panel, position the FWD AUX TRANS B switch (26) to the OFF position. Verify as follows: (1) FWD AUX FUEL PRESS LO message on the EOAP (4) goes off. p. Press the FWD AUX TRANS B GFI Relay (R2-1497) RESET (24) button. Verify as follows:

APPENDIX C: GFI CENTER/AUX FUEL TANK PUMPS CONTROL CIRCUIT, AND CENTER/AUX FUEL TANK PUMPS LOW PRESSURE INDICATION SYSTEM TEST PROCEDURES (SHEET 14 OF 21)
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 27, 2013 MD90-28-013 Revision 1 August 27, 2015 132 of 140 BOEING SERVICE BULLETIN MD90-28-013(1) FWD AUX TRANS B GFI Relay (R2-1497) RESET (24) button remains depressed and the white band is no longer visible. (2) FWD AUX FUEL PRESS LO message on the EOAP (4) remains off. q. On the overhead switch panel, do as follows: (1) Position the FWD AUX TRANS B switch (26) to the TEST position. Verify as follows: (a) On the EOAP (4), the FWD AUX FUEL PRESS LO message comes on momentarily and then goes out. (2) Position the FWD AUX TRANS B switch (26) to the OFF position. Verify as follows: (a) On the EOAP (4), verify the FWD AUX FUEL PRESS LO message remains off. 7. Close access panel 610TB. Refer to MD90 AMM 06-36-00.

APPENDIX C: GFI CENTER/AUX FUEL TANK PUMPS CONTROL CIRCUIT, AND CENTER/AUX FUEL TANK PUMPS LOW PRESSURE INDICATION SYSTEM TEST PROCEDURES (SHEET 15 OF 21)
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 27, 2013 MD90-28-013 Revision 1 August 27, 2015 133 of 140 BOEING SERVICE BULLETIN MD90-28-013APPENDIX C: GFI CENTER/AUX FUEL TANK PUMPS CONTROL CIRCUIT, AND CENTER/AUX FUEL TANK PUMPS LOW PRESSURE INDICATION SYSTEM TEST PROCEDURES (SHEET 16 OF 21)
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 27, 2013 MD90-28-013 Revision 1 August 27, 2015 134 of 140 BOEING SERVICE BULLETIN MD90-28-013APPENDIX C: GFI CENTER/AUX FUEL TANK PUMPS CONTROL CIRCUIT, AND CENTER/AUX FUEL TANK PUMPS LOW PRESSURE INDICATION SYSTEM TEST PROCEDURES (SHEET 17 OF 21)
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 27, 2013 MD90-28-013 Revision 1 August 27, 2015 135 of 140 BOEING SERVICE BULLETIN MD90-28-013APPENDIX C: GFI CENTER/AUX FUEL TANK PUMPS CONTROL CIRCUIT, AND CENTER/AUX FUEL TANK PUMPS LOW PRESSURE INDICATION SYSTEM TEST PROCEDURES (SHEET 18 OF 21)
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 27, 2013 MD90-28-013 Revision 1 August 27, 2015 136 of 140 BOEING SERVICE BULLETIN MD90-28-013APPENDIX C: GFI CENTER/AUX FUEL TANK PUMPS CONTROL CIRCUIT, AND CENTER/AUX FUEL TANK PUMPS LOW PRESSURE INDICATION SYSTEM TEST PROCEDURES (SHEET 19 OF 21)
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 27, 2013 MD90-28-013 Revision 1 August 27, 2015 137 of 140 BOEING SERVICE BULLETIN MD90-28-013APPENDIX C: GFI CENTER/AUX FUEL TANK PUMPS CONTROL CIRCUIT, AND CENTER/AUX FUEL TANK PUMPS LOW PRESSURE INDICATION SYSTEM TEST PROCEDURES (SHEET 20 OF 21)
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 27, 2013 MD90-28-013 Revision 1 August 27, 2015 138 of 140 BOEING SERVICE BULLETIN MD90-28-013APPENDIX C: GFI CENTER/AUX FUEL TANK PUMPS CONTROL CIRCUIT, AND CENTER/AUX FUEL TANK PUMPS LOW PRESSURE INDICATION SYSTEM TEST PROCEDURES (SHEET 21 OF 21)
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 27, 2013 MD90-28-013 Revision 1 August 27, 2015 139 of 140 BOEING SERVICE BULLETIN MD90-28-013APPENDIX D: BOEING PART DEMAND INTENT (SHEET 1 OF 1)
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 27, 2013 MD90-28-013 Revision 1 August 27, 2015 140 of 140 BOEING SERVICE BULLETIN MD90-28-013