### Commercial **Airplanes** 

# MD11 Service Bulletin
**Number: MD11-28-132** Original Issue: November 25, 2008 Revision 1: July 06, 2010 ATA System: 2800 **SUBJECT:** FUEL - Fuel - Install Fuel Tank Float Level Switch In-line Fuses Export of this technology is controlled under the United States Export Administration Regulations (EAR) (15 CFR 730-774). An export license may be required before it is used for development, production or use by foreign persons from specific countries. The controller of this data has the individual responsibility to abide by all export laws. 9E991 ECCN: 

## BOEING PROPRIETARY, CONFIDENTIAL, AND/OR TRADE SECRET Copyright © 2008 The Boeing Company Unpublished Work - All Rights Reserved Boeing claims copyright in each page of this document only to the extent that the page contains copyrightable subject matter.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

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 25, 2008 MD11-28-132 Revision 1: July 06, 2010 1 of 45 2.0BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 25, 2008 MD11-28-132 Revision 1: July 06, 2010 2 of 45 **BOEING SERVICE BULLETIN MD11-28-132**

BLANK PAGE**Table of Contents** Revision Transmittal Sheet............................................ 5 Summary...................................................... 7 1. PLANNING INFORMATION........................................ 9 A. Effectivity................................................ 9 1. Airplanes............................................. 9 2. Spares Affected. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 10 B. Concurrent Requirements. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 10 C. Reason. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 10 D. Description. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 10 E. Compliance. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11 F. Approval. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11 G. Manpower. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 12 H. Weight and Balance Changes. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13 I. Electrical Load Data. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13 J. References. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13 1. Existing Data:. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13 2. Data supplied with this Service Bulletin:. . . . . . . . . . . . . . . . . . . . . . . . . . . 13 3. Installation Drawings Used in the Preparation of this Service Bulletin:. . . . . . . . . . . 13 4. Process Data:. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13 K. Publications Affected. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13 L. Interchangeability and Intermixability of Parts. . . . . . . . . . . . . . . . . . . . . . . . . . . 14 2. MATERIAL INFORMATION. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15 A. Material - Price and Availability. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15 B. Industry Support Information. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15 C. Parts Necessary For Each Airplane. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15 1. Kits/Parts:. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15 2. Parts and Materials Supplied by the Operator:. . . . . . . . . . . . . . . . . . . . . . . . 22 3. Parts Modified and Reidentified:. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 22 4. Parts Removed and Not Replaced:. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 23 D. Parts Necessary to Change Spares. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 23 E. Special Tooling - Price and Availability. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 23 F. Special Tooling Necessary to do this Service Bulletin. . . . . . . . . . . . . . . . . . . . . . . 23 3. ACCOMPLISHMENT INSTRUCTIONS. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25 A. GENERAL INFORMATION. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25 B. WORK INSTRUCTIONS. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 26 Appendix A: FUEL TANK 1 [Group 1-4]. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 30 Appendix B: FUEL TANK 2 [Group 1-4]. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 31 Appendix C: FUEL TANK 3 [Group 1-4]. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 32 Appendix D: UPPER AND LOWER AUXILIARY FUEL TANKS [Group 1-4]. . . . . . . . . . . . . . . . 33 Appendix E: TAIL FUEL TANK [Group 1-4]. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 34 Appendix F: FORWARD AUXILIARY FUEL TANK [Group 2]. . . . . . . . . . . . . . . . . . . . . . . 35 Appendix G: FORWARD AUXILIARY FUEL TANK [Group 3]. . . . . . . . . . . . . . . . . . . . . . . 36 Appendix H: FORWARDAUXILIARY FUEL TANK NO. 1 STATION 1044.437 AND NO. 2 STATION 1124.437 [Group 4]. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 37 Appendix I: FUEL TESTS [Group 1]. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 38

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 25, 2008 MD11-28-132 Revision 1: July 06, 2010 3 of 45 **BOEING SERVICE BULLETIN MD11-28-132**Appendix J: FUEL TESTS [Group 2]. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 40 Appendix K: FUEL TESTS [Group 3]. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 42 Appendix L: FUEL TESTS [Group 4]. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 44

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 25, 2008 MD11-28-132 Revision 1: July 06, 2010 4 of 45 **BOEING SERVICE BULLETIN MD11-28-132**

### Commercial **Airplanes** 

# MD11 Service Bulletin **Revision Transmittal Sheet Number: MD11-28-132**  Original Issue: November 25, 2008 Revision 1: July 06, 2010 ATA System: 2800 **SUBJECT:** FUEL - Fuel - Install Fuel Tank Float Level Switch In-line Fuses This revision includes all pages of the service bulletin. **COMPLIANCE INFORMATION RELATED TO THIS REVISION** No more work is necessary on the airplane(s) changed in accordance with the original issue of this service bulletin. Federal Aviation Administration (FAA) Notice of Proposed Rule Making 2010-NM-003-AD, is related to this service bulletin. Airplane fuselage number 0608 was moved to Group 1 from Group 3 of this service bulletin effectivity.

**REASON FOR REVISION** This revision is sent to incorporate changes outlined in Information Notices (IN)s MD11-28-132 IN 01, IN 02 and IN 03. The data given in Information Notices (IN)s MD11-28-132 IN 01, IN 02 and IN 03, is included in this revision. These sections were changed: 1. In Paragraph 1.D., Description, added Maintenance Zone table. 2. In Paragraph 1.E., Compliance, added Federal Aviation Administration (FAA) Notice of Proposed Rule Making 2010-NM-003-AD and changed recommended compliance statement. 3. In Paragraph 1.F., Approval, changed statement. 4. In Paragraph 1.J.1., Existing Data, added Federal Aviation Administration (FAA) Notice of Proposed Rule Making 2010-NM-003-AD. 5. In Paragraph 1.H., Weight and Balance Changes, changed values. 6. In Paragraph 1.K.1., Publications, changed Aircraft Maintenance Manual and Fault Isolation Manual chapter-section.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 25, 2008 MD11-28-132 Revision 1: July 06, 2010 5 of 457. In Paragraph 1.K.2., Damage Tolerance Based Structural Inspections, added statement. 8. In Paragraph 2.A., Material - Price and Availability, changed pricing data. 9. In Paragraph 2.C.1., Kit/Parts, changed wire kit number for Groups 1 through 4, Group 3 top kit number and AEPL drawing number. Vertical lines are put on the left edge of each page, except in Paragraph 1.A., Effectivity, to show the location of important changes. Pages with no vertical lines have no important changes.

**REVISION HISTORY** November 25, 2008 Original Issue: July 06, 2010 Revision 1:

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 25, 2008 MD11-28-132 Revision 1: July 06, 2010 6 of 45 **BOEING SERVICE BULLETIN MD11-28-132**

### Commercial **Airplanes** 

# MD11 Service Bulletin **Summary Number: MD11-28-132**  Original Issue: November 25, 2008 Revision 1: July 06, 2010 ATA System: 2800 **SUBJECT:** FUEL - Fuel - Install Fuel Tank Float Level Switch In-line Fuses **CONCURRENT REQUIREMENTS** None. **BACKGROUND** An investigation by Boeing has determined that float level switch wires located on the left and right wing forward spar, right main landing gear wheel well, horizontal stabilizer front spar, empennage, and forward cargo compartment are routed in the same bundles as power wires. If a short circuit between a float level switch wire and a power wire occurs, an over current can cause excessive temperatures in the float level switch wires, resulting in damage. Adding an in-line fuse as a self-contained component in each float level switch circuit and sleeving the wires between the fuel tank and the in-line fuse will minimize the possibility of excessive temperatures in the float level switch wires. If not corrected, and there is a short circuit of the float level switch wire to a power wire, possible damage to the float level switch wire could occur, and become a potential ignition source for the fuel tank. 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. **ACTION** This service bulletin installs fuel tank float level switch in-line fuses. **EFFECTIVITY** All MD-11 and MD-11F Airplanes. Refer to Paragraph 1.A.1., Airplanes for the list of affected airplanes. **COMPLIANCE** Federal Aviation Administration (FAA) Notice of Proposed Rule Making 2010-NM-003-AD, is related to this service bulletin. The Federal Aviation Administration (FAA) will possibly release an Airworthiness Directive related to this service bulletin. The Airworthiness Directive will make the compliance tasks and times given in this service bulletin mandatory. Boeing recommends that the operators do this service bulletin within 5 years after the original issue date on this service bulletin.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 25, 2008 MD11-28-132 Revision 1: July 06, 2010 7 of 45**INDUSTRY SUPPORT INFORMATION** Boeing warranty remedies are not available for the configuration changes given in this service bulletin. **MANPOWER** Refer to Paragraph 1.G, for Manpower information. **MATERIAL INFORMATION** Boeing Supplied Kits/Parts. Refer to Paragraph 2.A., Material - Price and Availability.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 25, 2008 MD11-28-132 Revision 1: July 06, 2010 8 of 45 **BOEING SERVICE BULLETIN MD11-28-132**

### Commercial **Airplanes** 

# MD11 Service Bulletin
**Number: MD11-28-132** Original Issue: November 25, 2008 Revision 1: July 06, 2010 ATA System: 2800 **SUBJECT:** FUEL - Fuel - Install Fuel Tank Float Level Switch In-line Fuses
**1. PLANNING INFORMATION A. Effectivity**  1. Airplanes This service bulletin is for the airplanes shown below. **NOTE:** When any Group 3 or 4 passenger airplane shown below is modified to a freighter configuration by Boeing Passenger to Freighter (P to F) engineering, it will become a Group 1 airplane.
**DESCRIPTION CONFIGURATION**  **GROUP** Applicable to airplanes with fuel tanks 1, 2, 3, upper and lower auxiliary, and tail configuration. - 1
Applicable to airplanes with fuel tanks 1, 2, 3, upper and lower auxiliary, foward auxiliary, tail, and unique wiring configuration. - 2
Applicable to airplanes with fuel tanks 1, 2, 3, upper and lower auxiliary, foward auxiliary, tail, and unique wiring configuration. - 3
Applicable to airplanes with fuel tanks 1, 2, 3, upper and lower auxiliary, foward auxiliary No. 1, foward auxiliary No. 2, and tail configuration. - 4

Airplane Models: MD-11, MD-11F **Group Fuselage Num-**  **ber** 1 447 - 449 1 451 - 464 1 466 - 489

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 25, 2008 MD11-28-132 Revision 1: July 06, 2010 9 of 45**Group Fuselage Num-**  **ber** 1 491 - 517 1 519 - 531 4 532 1 533 - 543 4 544 1 545 - 552 1 554 - 589 2 590 1 591 - 596 3 597 1 598 - 646 2. Spares Affected None. **B. Concurrent Requirements** None. **C. Reason** An investigation by Boeing has determined that float level switch wires located on the left and right wing forward spar, right main landing gear wheel well, horizontal stabilizer front spar, empennage, and forward cargo compartment are routed in the same bundles as power wires. If a short circuit between a float level switch wire and a power wire occurs, an over current can cause excessive temperatures in the float level switch wires, resulting in damage. Adding an in-line fuse as a self-contained component in each float level switch circuit and sleeving the wires between the fuel tank and the in-line fuse will minimize the possibility of excessive temperatures in the float level switch wires. If not corrected, and there is a short circuit of the float level switch wire to a power wire, possible damage to the float level switch wire could occur, and become a potential ignition source for the fuel tank. 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. Revision 1 is sent to incorporate changes outlined in Information Notices (IN)s MD11-28-132 IN 01, IN 02 and IN 03. The data given in Information Notices (IN)s MD11-28-132 IN 01, IN 02 and IN 03, is included in this revision. **D. Description** This service bulletin installs fuel tank float level switch in-line fuses.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 25, 2008 MD11-28-132 Revision 1: July 06, 2010 10 of 45 **BOEING SERVICE BULLETIN MD11-28-132**Revision 1 - No more work is necessary on the airplane(s) changed in accordance with the original issue of this service bulletin. The work in this service bulletin is done in the maintenance zone(s) given below. **Group 1:**
**Affected Maintenance Zones Zone**  **Model** 144, 145, 146, 371, 516, 518, 525, 526, 527, 618, 625, 626, 627 MD-11, MD-11F

**Group 2-4:**
**Affected Maintenance Zones Zone**  **Model** 123, 144, 145, 146, 254, 371, 516, 518, 525, 526, 527, 618, 625, 626, 627 MD-11
**E. Compliance** Federal Aviation Administration (FAA) Notice of Proposed Rule Making 2010-NM-003-AD, is related to this service bulletin. The Federal Aviation Administration (FAA) will possibly release an Airworthiness Directive related to this service bulletin. The Airworthiness Directive will make the compliance tasks and times given in this service bulletin mandatory. Boeing recommends that the operators do this service bulletin within 5 years after the original issue date on this service bulletin. **F. Approval** This service bulletin was examined by the Federal Aviation Administration (FAA). The changes specified in this service bulletin comply with the applicable regulations and are FAA approved, as well as European Aviation Safety Agency (EASA)/Joint Aviation Authorities (JAA) approved for all EASA/JAA approved airplanes listed in the service bulletin effectivity. This service bulletin and its approval were based on the airplane in its original Boeing delivery configuration or as modified by other approved Boeing changes. If an airplane has a non-Boeing modification or repair that affects a component or system also affected by this service bulletin, the operator is responsible for obtaining appropriate regulatory agency approval before incorporating this service bulletin.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 25, 2008 MD11-28-132 Revision 1: July 06, 2010 11 of 45 **BOEING SERVICE BULLETIN MD11-28-132 G. Manpower**  The table below shows an estimate of the task hours necessary to do this modification for each airplane. This estimate is for direct labor only, done by an experienced crew. Adjust the estimate with operator task hour data if necessary. The estimate does not include lost time. These are some examples of lost time: — Time to adjust to the workplace — Time to schedule the work — Time to examine the work — Time to cure the materials — Time to make the parts — Time to find the tools. **Group 1: Elapsed Hours**  **Task Hours Number of Persons**  **Task** 10.5 21.0 2 Open Access 62.5 125.0 2 Change 3.0 6.0 2 Test 12.5 25.0 2 Close Access 88.5 177.0 TOTAL FOR EACH AIRPLANE **Group 2-3: Elapsed Hours**  **Task Hours Number of Persons**  **Task** 10.5 21.0 2 Open Access 66.0 132.0 2 Change 3.1 6.2 2 Test 12.5 25.0 2 Close Access 92.1 184.2 TOTAL FOR EACH AIRPLANE **Group 4: Elapsed Hours**  **Task Hours Number of Persons**  **Task** 10.5 21.0 2 Open Access 67.6 135.2 1 Change 3.3 6.6 2 Test 12.5 25.0 2 Close Access 93.9 187.8 TOTAL FOR EACH AIRPLANE

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 25, 2008 MD11-28-132 Revision 1: July 06, 2010 12 of 45 **BOEING SERVICE BULLETIN MD11-28-132 H. Weight and Balance Changes**  **Moment Change (MEW) IN.-LBS**  **Mfr's Empty Weight (MEW) LBS**  **Approximate Station (Inches)**  **Airplane Group**  +10129.1 +6.7 1511.8 1 +10787.0 +7.0 1541.0 2 and 3 +10478.2 +7.1 1475.8 4
**I. Electrical Load Data** Not changed. **J. References** 1. Existing Data: a. MD-11-1F Structural Repair Manual (SRM) 51-00-01. b. MD-11-1P Structural Repair Manual (SRM) 51-00-01. c. MD-11 Aircraft Maintenance Manual (AMM) 06-28-00, 06-32-34, 06-33-00, 06-35-00, 06-36-00, 12-11-03, 28-14-01 and 28-00-00. d. Standard Wiring Practices Manual (SWPM) 20-00-00, 20-00-09, 20-00-13, 20-00-16, 20-10-01, 20-10-04, 20-20-02, 20-20-03 and 20-40-01. e. Wire Diagram Manual (WDM) 28-21-01, 28-22-06, 28-22-07, 28-22-08, 28-43-01, 28-43-02, and 28-46-01. f. Federal Aviation Administration (FAA) Notice of Proposed Rule Making (NPRM) 2010-NM-003-AD. 2. Data supplied with this Service Bulletin: None. 3. Installation Drawings Used in the Preparation of this Service Bulletin: None. 4. Process Data: Douglas Process Specifications referred to on the drawing are not given in this service bulletin since these procedures are frequently used as standard shop practices. **K. Publications Affected** 1. Publications:

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 25, 2008 MD11-28-132 Revision 1: July 06, 2010 13 of 45 **BOEING SERVICE BULLETIN MD11-28-132 Chapter-Section**  **Publication** 28-14, 28-21, 28-30, 28-40, 28-43, 28-46 and 36-14 Aircraft Maintenance Manual
28-14, 36-23 Fault Isolation Manual 28-42 and 28-43 Illustrated Parts Catalog 28-21, 28-22, 28-43 and 28-46 Wiring Diagram 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** Accomplishment of this service bulletin does not affect interchangeability or intermixability of parts.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 25, 2008 MD11-28-132 Revision 1: July 06, 2010 14 of 45 **BOEING SERVICE BULLETIN MD11-28-132 2. MATERIAL INFORMATION**  **A. Material - Price and Availability** Boeing can supply the kits shown in Paragraph 2.C., Parts Necessary for Each Airplane. Operators are encouraged to share schedule requirements with Boeing for incorporation of the service bulletin. The kits are subject to the terms and conditions of the Boeing standard purchase order acknowledgment. Prices are in United States Dollars. Terms: Net 30 days. Reference this service bulletin and submit your purchase order by one of these methods: 1. Order on-line via ATA Spec 2000 or The Boeing PART Page 2. Fax to (206) 662-7145 **REFER TO THE BOEING PART PAGE ON MYBOEINGFLEET.COM OR CONTACT FIRST RESPONDER AT FR@BOEING.COM FOR THE LATEST REORDER LEAD TIME (ROLT) AND PRICE INFORMATION** 
**Unit Price as of Revision 1 date of** **this Service Bul letin (US Dollars)** **ROLT as of Revi sion 1 date of this** 

**Service Bulletin (Calendar Days)**  **QTY Date**  **Name Kit Number** 

$9,951.00 90 1 Service Kit SB11280132-3 10,212.00 90 1 Service Kit SB11280132-5 10,541.00 90 1 Service Kit SB11280132-7 **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. **Group 1: Kit SB11280132**  **Notes Name**  **QTY New Part Number**  **-3** (a) SCREW 7 3D0005-08-10 (a) SCREW 37 3D0005-08-8 (a) SCREW 5 3D0005-3-22 (a) SCREW 8 3D0005-3-26 (a) SCREW 3 3D0005-3-28 (a) SCREW 2 3D0005-3-8

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 25, 2008 MD11-28-132 Revision 1: July 06, 2010 15 of 45 **BOEING SERVICE BULLETIN MD11-28-132 Group 1:**  **Kit SB11280132 Notes**  **Name QTY**  **New Part Number -3**  (a) TERMINAL LUG 878 6 5D0086-3 (a) TERMINAL LUG 762 11 5D0086-6 (a) SEALING PLUG 48 5D0206-20 IN-LINE FUSE 24 65053-220 BRACKET ASSEMBLY 1 ANN0012-1 SOCKET T/C 524 3 M39029/22-192 COVER ASSEMBLY 1 MS18029-6S8 RIVET 2 MS20470AD4-5D RIVET 4 MS20470AD5-5D NUT 74 MS21042L08 NUT 2 MS21042L3 CLAMP 4 MS21919WDG10 CLAMP 6 MS21919WDG3 CLAMP 2 MS21919WDG5 CLAMP 2 MS21919WDG7 TERMINAL BOARD 1 MS27212-6-8 LOCKWASHER 37 MS35338-42 LOCKWASHER 2 MS35338-43 WASHER 6 NAS1252-10H WASHER 55 NAS1252-10L WASHER 7 NAS1252-8H WASHER 118 NAS1252-8L SPACER 5 NAS43DD3-48FC SPACER 8 NAS43DD3-64FC SPACER 3 NAS43DD3-72FC WASHER 3 NAS620A4 BOLT 3 NAS7700-3 (a) CLAMP 1 S7934111-2SA (a) CLAMP 21 S7934111-3SA (a) CLAMP 5 S7934111-4SA

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 25, 2008 MD11-28-132 Revision 1: July 06, 2010 16 of 45 **BOEING SERVICE BULLETIN MD11-28-132 Group 1:**  **Kit SB11280132 Notes**  **Name QTY**  **New Part Number -3**  (a) CLAMP 3 S7934111-5SA (a) CLAMP 1 S7934111-6SA (a) CLAMP 4 S7934111-7SA (a) CLAMP 1 S7934111-8SA (a) CLAMP 24 S7934111-9SA WIRE KIT 1 SR11280063-103 WIRE KIT 1 SR11280063-104 WIRE KIT 1 SR11280063-105 SLEEVING 136 FT X .166 I.D. SR11280063-3(DMS 2109, Type 1) or equivalent TIE TAPE 50 YD SR11280063-7 (DMS 2089) or equivalent BRACKET 1 TA4012B12 BRACKET 2 TA4012F21 (a) Or approved equivalent, refer to AEPL, Drawing 7595071. **Group 1: Wire Kit SR11280063**  **Notes Name**  **QTY QTY**  **QTY New Part Number**  **-105 -104**  **-103** SOCKET T/C 1124

- 1

- DC39-20S WIRE CODE 801 14 FT 14 FT

- DC2426-1C-20NM (DMS 2426) or equivalent WIRE CODE 801 158 FT

- 26FT DC2426-1C-22NM (DMS 2426) or equivalent SOCKET T/C 524 33 7 4 M39029/22-192 (a) TERMINAL LUG 878 4

- - 5D0086-3 (a) TERMINAL LUG 762 29 6 4 5D0086-6 (a) Or approved equivalent, refer to AEPL, Drawing 7595071.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 25, 2008 MD11-28-132 Revision 1: July 06, 2010 17 of 45 **BOEING SERVICE BULLETIN MD11-28-132 Group 2-3:**  **Kit SB11280132 Notes**  **Name QTY**  **New Part Number -5**  (a) SCREW 7 3D0005-08-10 (a) SCREW 1 3D0005-08-12 (a) SCREW 38 3D0005-08-8 (a) SCREW 5 3D0005-3-22 (a) SCREW 8 3D0005-3-26 (a) SCREW 3 3D0005-3-28 (a) SCREW 2 3D0005-3-8 (a) TERMINAL LUG 878 6 5D0086-3 (a) TERMINAL LUG 762 11 5D0086-6 (a) SEALING PLUG 50 5D0206-20 IN-LINE FUSE 25 65053-220 (a) STRAP 5 9D0254-1-1-9 BRACKET ASSEMBLY 1 ANN0012-1 SOCKET T/C 524 4 M39029/22-192 COVER ASSEMBLY 1 MS18029-6S8 RIVET 4 MS20470AD4-5D RIVET 4 MS20470AD5-5D NUT 76 MS21042L08 NUT 2 MS21042L3 CLAMP 4 MS21919WDG10 CLAMP 6 MS21919WDG3 CLAMP 2 MS21919WDG5 CLAMP 2 MS21919WDG7 TERMINAL BOARD 1 MS27212-6-8 LOCKWASHER 37 MS35338-42 LOCKWASHER 2 MS35338-43 WASHER 6 NAS1252-10H WASHER 55 NAS1252-10L WASHER 7 NAS1252-8H WASHER 122 NAS1252-8L

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 25, 2008 MD11-28-132 Revision 1: July 06, 2010 18 of 45 **BOEING SERVICE BULLETIN MD11-28-132 Group 2-3:**  **Kit SB11280132 Notes**  **Name QTY**  **New Part Number -5**  SPACER 5 NAS43DD3-48FC SPACER 8 NAS43DD3-64FC SPACER 3 NAS43DD3-72FC WASHER 3 NAS620A4 BOLT 3 NAS7700-3 (a) CLAMP 1 NMC1001-2 (a) CLAMP 1 S7934111-2SA (a) CLAMP 21 S7934111-3SA (a) CLAMP 5 S7934111-4SA (a) CLAMP 3 S7934111-5SA (a) CLAMP 1 S7934111-6SA (a) CLAMP 4 S7934111-7SA (a) CLAMP 1 S7934111-8SA (a) CLAMP 25 S7934111-9SA WIRE KIT 1 SR11280063-101 WIRE KIT 1 SR11280063-103 WIRE KIT 1 SR11280063-104 WIRE KIT 1 SR11280063-105 SLEEVING 136 FT X .166 I.D. SR11280063-3(DMS 2109, Type 1) or equivalent SLEEVE 15 FT X 3/16 I.D. SR11280063-5 (DMS 2379, Class 4) or equivalent TIE TAPE 50 YD SR11280063-7 (DMS 2089) or equivalent BRACKET 2 TA4012B12 BRACKET 2 TA4012F21 (a) Or approved equivalent, refer to AEPL, Drawing 7595071.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 25, 2008 MD11-28-132 Revision 1: July 06, 2010 19 of 45 **BOEING SERVICE BULLETIN MD11-28-132 Group 2-3:**  **Wire Kit SR11280063 Notes**  **Name QTY**  **QTY QTY**  **QTY New Part Number**  **-105 -104**  **-103 -101**  SOCKET T/C 1124

- 1

- 1 DC39-20S WIRE CODE 801 14 FT 14 FT

- - DC2426-1C-20NM (DMS 2426) or equivalent WIRE CODE 801 158 FT

- 26 FT 2 FT DC2426-1C-22NM (DMS 2426) or equivalent SOCKET T/C 524 33 7 4 1 M39029/22-192 (a) TERMINAL LUG 878 4

- - - 5D0086-3 (a) TERMINAL LUG 762 29 6 4

- 5D0086-6 (a) Or approved equivalent, refer to AEPL, Drawing 7595071. **Group 4: Kit SB11280132**  **Notes Name**  **QTY New Part Number**  **-7** (a) SCREW 7 3D0005-08-10 (a) SCREW 2 3D0005-08-12 (a) SCREW 39 3D0005-08-8 (a) SCREW 5 3D0005-3-22 (a) SCREW 8 3D0005-3-26 (a) SCREW 3 3D0005-3-28 (a) SCREW 2 3D0005-3-8 (a) TERMINAL LUG 878 6 5D0086-3 (a) TERMINAL LUG 762 11 5D0086-6 (a) SEALING PLUG 52 5D0206-20 IN-LINE FUSE 26 65053-220 (a) BRACKET 2 9D0062-1-16-10 BRACKET ASSEMBLY 1 ANN0012-1 SOCKET T/C 524 5 M39029/22-192 COVER ASSEMBLY 1 MS18029-6S8 RIVET 6 MS20470AD4-5D RIVET 4 MS20470AD5-5D NUT 78 MS21042L08

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 25, 2008 MD11-28-132 Revision 1: July 06, 2010 20 of 45 **BOEING SERVICE BULLETIN MD11-28-132 Group 4:**  **Kit SB11280132 Notes**  **Name QTY**  **New Part Number -7**  NUT 2 MS21042L3 CLAMP 4 MS21919WDG10 CLAMP 6 MS21919WDG3 CLAMP 2 MS21919WDG4 CLAMP 2 MS21919WDG5 CLAMP 2 MS21919WDG7 TERMINAL BOARD 1 MS27212-6-8 LOCKWASHER 37 MS35338-42 LOCKWASHER 2 MS35338-43 WASHER 6 NAS1252-10H WASHER 55 NAS1252-10L WASHER 7 NAS1252-8H WASHER 126 NAS1252-8L SPACER 5 NAS43DD3-48FC SPACER 8 NAS43DD3-64FC SPACER 3 NAS43DD3-72FC WASHER 3 NAS620A4 BOLT 3 NAS7700-3 (a) CLAMP 2 NMC1001-2 (a) CLAMP 1 S7934111-2SA (a) CLAMP 21 S7934111-3SA (a) CLAMP 5 S7934111-4SA (a) CLAMP 3 S7934111-5SA (a) CLAMP 1 S7934111-6SA (a) CLAMP 4 S7934111-7SA (a) CLAMP 1 S7934111-8SA (a) CLAMP 26 S7934111-9SA WIRE KIT 1 SR11280063-102 WIRE KIT 1 SR11280063-103 WIRE KIT 1 SR11280063-104

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 25, 2008 MD11-28-132 Revision 1: July 06, 2010 21 of 45 **BOEING SERVICE BULLETIN MD11-28-132 Group 4:**  **Kit SB11280132 Notes**  **Name QTY**  **New Part Number -7**  WIRE KIT 1 SR11280063-105 SLEEVING 136 FT X .166 I.D. SR11280063-3(DMS 2109, Type 1) or equivalent SLEEVE 15 FT X 3/16 I.D. SR11280063-5 (DMS 2379, Class 4) or equivalent TIE TAPE 50 YD SR11280063-7 (DMS 2089) or equivalent BRACKET 1 TA4012B12 BRACKET 2 TA4012F21 (a) Or approved equivalent, refer to AEPL, Drawing 7595071. **Group 4: Wire Kit SR11280063**  **Notes Name**  **QTY QTY**  **QTY QTY**  **New Part Number -105**  **-104 -103**  **-102** SOCKET T/C 1124

- 1

- 2 DC39-20S WIRE CODE 801 14 FT 14 FT

- - DC2426-1C-20NM (DMS 2426) or equivalent WIRE CODE 801 158 FT

- 26 FT

- DC2426-1C-22NM (DMS 2426) or equivalent WIRE CODE 801

- 4 FT DC2426-1C-24NM (DMS 2426) or equivalent SOCKET T/C 524 33 7 4 2 M39029/22-192 (a) TERMINAL LUG 878 4

- - - 5D0086-3 (a) TERMINAL LUG 762 29 6 4

- 5D0086-6 (a) Or approved equivalent, refer to AEPL, Drawing 7595071. 2. Parts and Materials Supplied by the Operator: None. 3. Parts Modified and Reidentified: None.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 25, 2008 MD11-28-132 Revision 1: July 06, 2010 22 of 45 **BOEING SERVICE BULLETIN MD11-28-132**4. Parts Removed and Not Replaced: None. **D. Parts Necessary to Change Spares** None. **E. Special Tooling - Price and Availability** None. **F. Special Tooling Necessary to do this Service Bulletin** No special tools or equipment are necessary to do the change in this service bulletin. But, maintenance and overhaul tools in the manuals given in Paragraph 1.J., References, can be necessary. Examine operator tool supply to make sure all necessary tools are available.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 25, 2008 MD11-28-132 Revision 1: July 06, 2010 23 of 45 **BOEING SERVICE BULLETIN MD11-28-132**BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 25, 2008 MD11-28-132 Revision 1: July 06, 2010 24 of 45 **BOEING SERVICE BULLETIN MD11-28-132**

BLANK PAGE**3. ACCOMPLISHMENT INSTRUCTIONS A. GENERAL INFORMATION**  **WARNING:**WHILE YOU DO WORK IN THE TAILCONE AREA, MAKE SURE THAT YOU OBEY ALL SAFETY PRECAUTIONS. IF YOU DO NOT OBEY THE PRECAUTIONS, DEATH OR INJURY TO PERSONS CAN OCCUR. **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. The instructions identified in Paragraph 3.B., Work Instructions give the recommended sequence of steps. The sequence of steps to do this service bulletin can be changed. 2. Manual titles are referred to by acronyms. Refer to Paragraph 1.J., References, for definition of the acronyms. 3. Equivalent parts are listed in the AEPL, Drawing 7595071. 4. Use the approved fastener and process material substitutions, MD-11-1F SRM 51-00-01, and MD-11-1P SRM 51-00-01. 5. Any protrusion of threads is acceptable provided that the threads do not rub or ride against nearby wire assemblies or components. 6. 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. 7. Refer to these SWPM chapters for applicable operations, as accepted procedures: Operation Chapter General - Maintenance Safety Practices SWPM 20-00-00Electrical Identification and Shop Practices SWPM 20-00-09Electrical Wire Codes SWPM 20-00-13

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 25, 2008 MD11-28-132 Revision 1: July 06, 2010 25 of 45 **BOEING SERVICE BULLETIN MD11-28-132**Electrical Wire End Termination Codes SWPM 20-00-16Fabricating and Installing Wire Harness - Commercial SWPM 20-10-01
Coil and Stow - Maintenance Practices SWPM 20-10-04Terminal Blocks - Maintenance Practices SWPM 20-20-02General Installation Hardwares - Maintenance Practices SWPM 20-20-03

Power Distribution Bus - Maintenance Practice SWPM 20-40-01

8. Obey all of the warnings and cautions given in the specified manual sections as applicable. 9. Review and understand all general notes of Service Rework Drawing SR11280063 sheets 3, 3.1, 3.2, 3.3, 3.4, 3.5, 3.6, 3.7, 3.8, 3.9, 3.10 and 7 before start of modification. 10. These work instructions refer to procedures included on other Boeing documents. When the words "refer to" are used and the operator has an accepted alternative procedure, the accepted alternative procedure can be used. When the words "In accordance with" are included in the instruction, the procedure in the Boeing document must be used. **B. WORK INSTRUCTIONS Group 1:**  1. Make fuel system safe for maintenance, open circuit breakers B1-1582 and B1-1583. Refer to MD-11 AMM 28-14-01 as an accepted procedure. 2. Gain access to area of modification, refer to Table below:
**Refer to Name/Location**  **Panel Number** MD-11 AMM 06-35-00 Access Panel Left Wing Leading Edge 516AB, 516DB, 516EB, 518AB, 518BB, 518CB, 518GB, 525DB, 526DB, 526FB, 527AB MD-11 AMM 06-36-00 Access Panel Right Wing Leading Edge 618BB, 618CB, 618GB, 625DB, 626DB, 627AB MD-11 AMM 06-28-00 Right Main Landing Gear Wheel Well Right Main Landing Gear Door MD-11 AMM 06-33-00 Horizontal Stabilizer/fuel, jack screw, and motors 311AB

3. Install fuel tank float level switch In-line fuses, in the locations shown below relative to appendices:

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 25, 2008 MD11-28-132 Revision 1: July 06, 2010 26 of 45 **BOEING SERVICE BULLETIN MD11-28-132 In Accordance with Appendix**  **Location** A Fuel Tank 1 B Fuel Tank 2 C Fuel Tank 3 D Upper and Lower Auxiliary Fuel Tanks E Tail Fuel Tank 4. Do return-to-service test of the fuel tanks float switches in accordance with Appendix I. 5. Close access to area of modification. 6. Put the airplane back to a serviceable condition. **Group 2:** 1. Make fuel system safe for maintenance, open circuit breakers B1-1582 and B1-1583. Refer to MD-11 AMM 28-14-01 as an accepted procedure. 2. Gain access to area of modification, refer to Table below:
**Refer to Name/Location**  **Panel Number** MD-11 AMM 06-35-00 Access Panel Left Wing Leading Edge 516AB, 516DB, 516EB, 518AB, 518BB, 518CB, 518GB, 525DB, 526DB, 526FB, 527AB MD-11 AMM 06-36-00 Access Panel Right Wing Leading Edge 618BB, 618CB, 618GB, 625DB, 626DB, 627AB MD-11 AMM 06-28-00 Right Main Landing Gear Wheel Well Right Main Landing Gear Door MD-11 AMM 06-33-00 Horizontal Stabilizer/fuel, jack screw, and motors 311AB
MD-11 AMM 06-32-34 Cabin Floor Panels Station 979 to 6-70 253GF, 253HF

3. Install fuel tank float level switch In-line fuses, in the locations shown below relative to appendices: **In accordance with Appendix Location**  A Fuel Tank 1 B Fuel Tank 2 C Fuel Tank 3 D Upper and Lower Auxiliary Fuel Tanks E Tail Fuel Tank

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 25, 2008 MD11-28-132 Revision 1: July 06, 2010 27 of 45 **BOEING SERVICE BULLETIN MD11-28-132 In accordance with Appendix**  **Location** F Forward Auxiliary Fuel Tank 4. Do return-to-service test of the fuel tanks float switches in accordance with Appendix J. 5. Close access to area of modification. 6. Put the airplane back to a serviceable condition. **Group 3:** 1. Make fuel system safe for maintenance, open circuit breakers B1-1582 and B1-1583. Refer to MD-11 AMM 28-14-01 as an accepted procedure. 2. Gain access to area of modification, refer to Table below:
**Refer to Name/Location**  **Panel Number** MD-11 AMM 06-35-00 Access Panel Left Wing Leading Edge 516AB, 516DB, 516EB, 518AB, 518BB, 518CB, 518GB, 525DB, 526DB, 526FB, 527AB MD-11 AMM 06-36-00 Access Panel Right Wing Leading Edge 618BB, 618CB, 618GB, 625DB, 626DB, 627AB MD-11 AMM 06-28-00 Right Main Landing Gear Wheel Well Right Main Landing Gear Door MD-11 AMM 06-33-00 Horizontal Stabilizer/fuel, jack screw, and motors 311AB
MD-11 AMM 06-32-34 Cabin Floor Panels Station 979 to 6-70 253GF, 253HF

3. Install fuel tank float level switch In-line fuses, in the locations shown below relative to appendices: **In accordance with Appendix Location**  A Fuel Tank 1 B Fuel Tank 2 C Fuel Tank 3 D Upper and Lower Auxiliary Fuel Tanks E Tail Fuel Tank G Forward Auxiliary Fuel Tank 4. Do return-to-service test of the fuel tanks float switches in accordance with Appendix K. 5. Close access to area of modification. 6. Put the airplane back to a serviceable condition.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 25, 2008 MD11-28-132 Revision 1: July 06, 2010 28 of 45 **BOEING SERVICE BULLETIN MD11-28-132 Group 4:**  1. Make fuel system safe for maintenance, open circuit breakers B1-1582 and B1-1583. Refer to MD-11 AMM 28-14-01 as an accepted procedure. 2. Gain access to area of modification, refer to Table below:
**Refer to Name/Location**  **Panel Number** MD-11 AMM 06-35-00 Access Panel Left Wing Leading Edge 516AB, 516DB, 516EB, 518AB, 518BB, 518CB, 518GB, 525DB, 526DB, 526FB, 527AB MD-11 AMM 06-36-00 Access Panel Right Wing Leading Edge 618BB, 618CB, 618GB, 625DB, 626DB, 627AB MD-11 AMM 06-28-00 Right Main Landing Gear Wheel Well Right Main Landing Gear Door MD-11 AMM 06-33-00 Horizontal Stabilizer/fuel, jack screw, and motors 311AB
MD-11 AMM 06-32-34 Cabin Floor Panels Station 979 to 6-70 253DF, 253EF, 253GF, 253HF 3. Install fuel tank float level switch In-line fuses, in the locations shown below relative to appendices: **In accordance with Appendix Location**  A Fuel Tank 1 B Fuel Tank 2 C Fuel Tank 3 D Upper and Lower Auxiliary Fuel Tanks E Tail Fuel Tank H Forward Auxiliary Fuel Tanks No. 1 and 2 4. Do return-to-service test of the fuel tanks float switches in accordance with Appendix L. 5. Close access to area of modification. 6. Put the airplane back to a serviceable condition.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 25, 2008 MD11-28-132 Revision 1: July 06, 2010 29 of 45 **BOEING SERVICE BULLETIN MD11-28-132 This Appendix applies only to: Group 1-4.** 
**MORE DATA DESCRIPTION OF TASK**  **STEP** In accordance with Drawing SR11280063 sheets 10, 11, 3, 3.1, 3.2, 3.3, 3.4, 3.5, 3.6, 3.7, 3.8, 9.7, 9.8, 105.201 and 305.201. Install fuel tank float level switch In-line fuse, reference designator F1-119 within float level switch reference designator S1-119 wiring. 1

In accordance with Drawing SR11280063 sheets 10, 15, 15.1, 3, 3.1, 3.2, 3.3, 3.4, 3.5, 3.6, 3.7, 3.8, 9.7, 9.8, 105.201, 305.201 and 306.201. Install fuel tank float level switch In-line fuse, reference designator F1-120 within float level switch reference designator S1-120 wiring. 2

In accordance with Drawing SR11280063 sheets 10, 15, 15.1, 3, 3.1, 3.2, 3.3, 3.4, 3.5, 3.6, 3.7, 3.8, 9.7, 9.8, 105.201 and 305.201. Install fuel tank float level switch In-line fuse, reference designator F1-121 within float level switch reference designator S1-121 wiring. 3

In accordance with Drawing SR11280063 sheets 10, 15, 15.1, 3, 3.1, 3.2, 3.3, 3.4, 3.5, 3.6, 3.7, 3.8, 9.7, 9.9, 105.201, 305.202 and 306.201. Install fuel tank float level switch In-line fuse, reference designator F1-176 within float level switch reference designator S1-176 wiring. 4

In accordance with Drawing SR11280063 sheets 10, 14, 3, 3.1, 3.2, 3.3, 3.4, 3.5, 3.6, 3.7, 3.8, 9.7, 9.9, 105.201 and 306.201. Install fuel tank float level switch In-line fuse, reference designator F1-1391within float level switch reference designator S1-1391 wiring. 5

In accordance with Drawing SR11280063 sheets 10, 13, 3, 3.1, 3.2, 3.4, 3.5, 3.6, 3.7, 3.8, 9.7, 9.9, 105.201 and 305.201. Install fuel tank float level switch In-line fuse, reference designator F1-1392within float level switch reference designator S1-1392 wiring. 6

In accordance with Drawing SR11280063 sheets 10, 12, 3, 3.1, 3.2, 3.3, 3.4, 3.5, 3.6, 3.7, 3.8, 9.7, 9.10, 105.201 and 305.202. Install fuel tank float level switch In-line fuse, reference designator F1-735 within float level switch reference designator S1-735 wiring. 7

**Appendix A: FUEL TANK 1 (SHEET 1 OF 1)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 25, 2008 MD11-28-132 Revision 1 July 06, 2010 30 of 45 **BOEING SERVICE BULLETIN MD11-28-132 This Appendix applies only to: Group 1-4.** 
**MORE DATA DESCRIPTION OF TASK**  **STEP** In accordance with Drawing SR11280063 sheets 16, 16.3, 3, 3.1, 3.3, 3.5, 3.6 and 3.8. Install new Terminal Board, item number S3-454. 1 In accordance with Drawing SR11280063 sheets 10, 16, 16.1, 3, 3.1, 3.2, 3.3, 3.4, 3.5, 3.6, 3.7, 3.8, 9.7, 9.11, 105.201 and 305.201. Install fuel tank float level switch In-line fuse, reference designator F1-90 within float level switch reference designator S1- 90 wiring. 2

In accordance with Drawing SR11280063 sheets 10, 16, 16.1, 3, 3.1, 3.2, 3.3, 3.4, 3.5, 3.6, 3.7, 3.8, 9.7, 9.11, 105.201 and 305.202. Install fuel tank float level switch In-line fuse, reference designator F1-177 within float level switch reference designator S1- 177 wiring. 3

In accordance with Drawing SR11280063 sheets 10, 16, 16.1, 16.2, 3, 3.1, 3.2, 3.3, 3.4, 3.5, 3.6, 3.7, 9.7, 9.11, 105.201 and 305.201. Install fuel tank float level switch In-line fuse, reference designator F1-1363 within float level switch reference designator S1- 1363 wiring. 4

In accordance with Drawing SR11280063 sheets 10, 16, 16.1, 16.2, 3, 3.1, 3.2, 3.3, 3.4, 3.5, 3.6, 3.7, 3.8, 9.7, 9.12, 105.201 and 305.201. Install fuel tank float level switch In-line fuse, reference designator F1-1393 within float level switch reference designator S1- 1393 wiring. 5

**Appendix B: FUEL TANK 2 (SHEET 1 OF 1)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 25, 2008 MD11-28-132 Revision 1 July 06, 2010 31 of 45 **BOEING SERVICE BULLETIN MD11-28-132 This Appendix applies only to: Group 1-4.** 
**MORE DATA DESCRIPTION OF TASK**  **STEP** In accordance with Drawing SR11280063 sheets 10, 17, 3, 3.1, 3.2, 3.3, 3.4, 3.5, 3.6, 3.7, 3.8, 9.7, 9.13, 105.201 and 305.201. Install fuel tank float level switch In-line fuse, reference designator F1-124 within level switch reference designator S1-124 wiring. 1

In accordance with Drawing SR11280063 sheets 10, 21, 21.1, 3, 3.1, 3.2, 3.3, 3.4, 3.5, 3.6, 3.7, 3.8, 9.7, 9.13, 105.201 and 305.201. Install fuel tank float level switch In-line fuse, reference designator F1-122within float level switch reference designator S1-122 wiring. 2

In accordance with Drawing SR11280063 sheets 10, 21, 21.1, 3, 3.1, 3.2, 3.3, 3.4, 3.5, 3.6, 3.7, 3.8, 9.7, 9.13, 105.201 305.201 and 307.201. Install fuel tank float level switch In-line fuse, reference designator F1-123within float level switch reference designator S1-123 wiring. 3

In accordance with Drawing SR11280063 sheets 10, 21, 21.1, 3, 3.1, 3.2, 3.3, 3.4, 3.5, 3.6, 3.7, 3.8, 9.7, 9.14, 105.201, 305.202 and 307.201. Install fuel tank float level switch In-line fuse, reference designator F1-178within float level switch reference designator S1-178 wiring. 4

In accordance with Drawing SR11280063 sheets 10, 20, 3, 3.1, 3.2, 3.3, 3.4, 3.5, 3.6, 3.7, 3.8, 9.7, 9.14, 105.201 and 307.201. Install fuel tank float level switch In-line fuse, reference designator F1-1394within float level switch reference designator S1-1394 wiring. 5

In accordance with Drawing SR11280063 sheets 10, 19, 3, 3.1, 3.2, 3.3, 3.4, 3.5, 3.6, 3.7, 3.8, 9.7, 9.15, 105.201 and 305.201. Install fuel tank float level switch In-line fuse, reference designator F1-1395within float level switch reference designator S1-1395 wiring. 6

In accordance with Drawing SR11280063 sheets 10, 18, 3, 3.1, 3.2, 3.3, 3.4, 3.5, 3.6, 3.7, 3.8, 9.7, 9.15, 105.201 and 305.202. Install fuel tank float level switch In-line fuse, reference designator F1-734within float level switch reference designator S1-734 wiring. 7

**Appendix C: FUEL TANK 3 (SHEET 1 OF 1)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 25, 2008 MD11-28-132 Revision 1 July 06, 2010 32 of 45 **BOEING SERVICE BULLETIN MD11-28-132 This Appendix applies only to: Group 1-4.** 

**MORE DATA DESCRIPTION OF TASK**  **STEP** In accordance with Drawing SR11280063 sheets 10, 22, 3, 3.1, 3.2, 3.3, 3.4, 3.5, 3.6, 3.7, 3.8, 9.7, 9.16, 103.201 and 303.201. Install fuel tank float level switch In-line fuse, reference designator F1-1359 within float level switch reference designator S1- 1359 wiring. 1

In accordance with Drawing SR11280063 sheets 10, 23, 3, 3.1, 3.2, 3.3, 3.4, 3.5, 3.6, 3.7, 3.8, 3.9, 9.7, 9.16, 103.201 and 303.201. Install fuel tank float level switch In-line fuse, reference designator F1-1360 within float level switch reference designator S1- 1360 wiring. 2

**Appendix D: UPPER AND LOWER AUXILIARY FUEL TANKS (SHEET 1 OF 1)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 25, 2008 MD11-28-132 Revision 1 July 06, 2010 33 of 45 **BOEING SERVICE BULLETIN MD11-28-132 This Appendix applies only to: Group 1-4.** 

**MORE DATA DESCRIPTION OF TASK**  **STEP** In accordance with Drawing SR11280063 sheets 10, 24, 24.1, 3, 3.1, 3.2, 3.3, 3.4, 3.5, 3.6, 3.7, 3.8, 9.7, 9.17, 104.201 and 304.201. Install fuel tank float level switch In-line fuse, reference designator F1-1396 within float level switch reference designator S1- 1396 wiring. 1

In accordance with Drawing SR11280063 sheets 10, 24, 24.2, 3, 3.1, 3.2, 3.4, 3.5, 3.6, 3.7, 3.8, 9.7, 9.17, 104.201 and 304.201. Install fuel tank float level switch In-line fuse, reference designator F1-1397 within float level switch reference designator S1- 1397 wiring. 2

Install fuel tank float level switch In-line fuse, reference designator F1-1398 within float level switch reference designator S1- 1398 wiring. 3

In accordance with Drawing SR11280063 sheets 10, 25, 3, 3.1, 3.2, 3.3, 3.4, 3.5, 3.6, 3.7, 3.8, 9.7, 9.18, 104.201 and 304.201. Install fuel tank float level switch In-line fuse, reference designator F1-1399 within float level switch reference designator S1- 1399 wiring. 4

**Appendix E: TAIL FUEL TANK (SHEET 1 OF 1)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 25, 2008 MD11-28-132 Revision 1 July 06, 2010 34 of 45 **BOEING SERVICE BULLETIN MD11-28-132 This Appendix applies only to: Group 2.** 

**MORE DATA DESCRIPTION OF TASK**  **STEP** In accordance with Drawing SR11280063 sheets 10, 26, 26.1, 3, 3.1, 3.2, 3.3, 3.4, 3.5, 3.6, 3.7, 3.8, 3.10, 9.7, 9.20, 101.201 and 302.201. Install fuel tank float level switch In-line fuse, reference designator F1-631 within float level switch reference designator S1-631 wiring. 1

**Appendix F: FORWARD AUXILIARY FUEL TANK (SHEET 1 OF 1)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 25, 2008 MD11-28-132 Revision 1 July 06, 2010 35 of 45 **BOEING SERVICE BULLETIN MD11-28-132 This Appendix applies only to: Group 3.** 

**MORE DATA DESCRIPTION OF TASK**  **STEP** In accordance with Drawing SR11280063 sheets 10, 26, 26.1, 3, 3.1, 3.2, 3.3, 3.4, 3.5, 3.6, 3.7, 3.8, 3.10, 9.7, 9.20, 101.201 and 301.201. Install fuel tank float level switch In-line fuse, reference designator F1-631 within float level switch reference designator S1-631 wiring. 1

**Appendix G: FORWARD AUXILIARY FUEL TANK (SHEET 1 OF 1)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 25, 2008 MD11-28-132 Revision 1 July 06, 2010 36 of 45 **BOEING SERVICE BULLETIN MD11-28-132 This Appendix applies only to: Group 4.** 

**MORE DATA DESCRIPTION OF TASK**  **STEP** In accordance with Drawing SR11280063 sheets 10, 27, 27.1, 27.2, 27.3, 3, 3.1, 3.2, 3.3, 3.4, 3.5, 3.6, 3.7, 3.8, 9.7, 9.19, 102.201 and 308.201. Install bracket and fuel tank float level switch In-line fuse, reference designatorF1-191 within float level switch reference designator S1-191 wiring. 1

In accordance with Drawing SR11280063 sheets 10, 27, 27.1, 27.2, 27.3, 3, 3.1, 3.2, 3.3, 3.4, 3.5, 3.6, 3.7, 3.8, 9.7, 9.19, 102.201 and 308.201. Install bracket and fuel tank float level switch In-line fuse, reference designatorF1-243 within float level switch reference designator S1-243 wiring. 2

**Appendix H: FORWARD AUXILIARY FUEL TANK NO. 1 STATION 1044.437 AND NO. 2 STATION 1124.437 (SHEET 1 OF 1)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 25, 2008 MD11-28-132 Revision 1 July 06, 2010 37 of 45 **BOEING SERVICE BULLETIN MD11-28-132 This Appendix applies only to: Group 1.** 
**RETURN-TO-SERVICE TEST OF THE FUEL TANKS FLOAT SWITCHES** This test can be performed for each float switch circuit independently as the fuse is installed. REFERENCES (AMM) Tasks: MD-11 AMM 12-11-03 - PRESSURE DEFUELING OF THE AIRCRAFT This procedure should be used as necessary. Depower the Fuel system and open the related C/Bs. After fuse installation do a continuity test as shown in the table below. Note: For some fuses check continuity between two pins, for others check continuity to ground. REMARKS PINS TERMINAL TEST TYPE FUSE TO BE TESTED TANK 1 7 & 8 S3-450 LOOP CONTINUITY F1-176 - TANK 1 DUMP 1 & 6 S3-450 LOOP CONTINUITY F1-121 Tank 1 4000 lb 4 & 5 S3-450 LOOP CONTINUITY F1-120 Tank 1 6000 lb 1 & 2 S3-1301 LOOP CONTINUITY F1-1391 TK 1 INBD FULL 1 & 2 S3-1300 LOOP CONTINUITY F1-1392 TK 1 OUTBD FULL 1 & 3 S3-366 LOOP CONT NOT FULL F1-119 TK 1 TIP VENT BOX 1 & 2 S3-684 LOOP CONTINUITY F1-735 L WING OVERFILL TANK 3 7 & 8 S3-451 LOOP CONTINUITY F1-178 - TANK 3 DUMP 6 & 2 S3-451 LOOP CONTINUITY F1-122 Tank 3 4000 lb 4 & 5 S3-451 LOOP CONTINUITY F1-123 Tank 3 6000 lb 1 & 2 S3-1302 LOOP CONTINUITY F1-1394 TK 3 INBD FULL 1 & 2 S3-1303 LOOP CONTINUITY F1-1395 TK 3 OUTBD FULL 2 & 3 S3-452 LOOP CONT NOT FULL F1-124 TK 3 TIP VENT BOX 1 & 2 S3-683 LOOP CONTINUITY F1-734 R WING OVERFILL TANK 2 1 & 5 S3-454 LOOP CONTINUITY F1-177 TK 2 DUMP 4 & 6 S3-454 LOOP CONTINUITY F1-90 TK 2 40000 LB 3 S3-454 CONT TO GND ON EMPTY F1-1363 TK 2 10000 LB 2 & 7 S3-454 LOOP CONTINUITY F1-1393 TK 2 FULL

**Appendix I: FUEL TESTS (SHEET 1 OF 2)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 25, 2008 MD11-28-132 Revision 1 July 06, 2010 38 of 45 **BOEING SERVICE BULLETIN MD11-28-132 RETURN-TO-SERVICE TEST OF THE FUEL TANKS FLOAT SWITCHES**  TAIL TANK 1 & 3 S3-756 LOOP CONTINUITY F1-1396 TAIL TK EMPTY 1 & 3 S3-758 LOOP CONTINUITY F1-1397 TAIL L FULL 2 & 3 S3-759 LOOP CONTINUITY F1-1398 TAIL R FULL VENT BOX PIN 1JX S3-739 CONT BTW CONNECT F1-1399 Tail Tank Vent box PIN 3 P1-930 AUX TANKS 1 & 2 S3-1186 LOOP CONTINUITY F1-1359 UPPR AUX FULL 4 & 5 S3-805 LOOP CONTINUITY F1-1360 LWR AUX FULL

**Appendix I: FUEL TESTS (SHEET 2 OF 2)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 25, 2008 MD11-28-132 Revision 1 July 06, 2010 39 of 45 **BOEING SERVICE BULLETIN MD11-28-132 This Appendix applies only to: Group 2.** 
**RETURN-TO-SERVICE TEST OF THE FUEL TANKS FLOAT SWITCHES** This test can be performed for each float switch circuit independently as the fuse is installed. REFERENCES (AMM) Tasks: MD-11 AMM 12-11-03 - PRESSURE DEFUELING OF THE AIRCRAFT This procedure should be used as necessary. Depower the Fuel system and open the related C/Bs. After fuse installation do a continuity test as shown in the table below. Note: For some fuses check continuity between two pins, for others check continuity to ground. REMARKS PINS TERMINAL TEST TYPE FUSE TO BE TESTED TANK 1 7 & 8 S3-450 LOOP CONTINUITY F1-176 - TANK 1 DUMP 1 & 6 S3-450 LOOP CONTINUITY F1-121 Tank 1 4000 lb 4 & 5 S3-450 LOOP CONTINUITY F1-120 Tank 1 6000 lb 1 & 2 S3-1301 LOOP CONTINUITY F1-1391 TK 1 INBD FULL 1 & 2 S3-1300 LOOP CONTINUITY F1-1392 TK 1 OUTBD FULL 1 & 3 S3-366 LOOP CONT NOT FULL F1-119 TK 1 TIP VENT BOX 1 & 2 S3-684 LOOP CONTINUITY F1-735 L WING OVERFILL TANK 3 7 & 8 S3-451 LOOP CONTINUITY F1-178 - TANK 3 DUMP 6 & 2 S3-451 LOOP CONTINUITY F1-122 Tank 3 4000 lb 4 & 5 S3-451 LOOP CONTINUITY F1-123 Tank 3 6000 lb 1 & 2 S3-1302 LOOP CONTINUITY F1-1394 TK 3 INBD FULL 1 & 2 S3-1303 LOOP CONTINUITY F1-1395 TK 3 OUTBD FULL 2 & 3 S3-452 LOOP CONT NOT FULL F1-124 TK 3 TIP VENT BOX 1 & 2 S3-683 LOOP CONTINUITY F1-734 R WING OVERFILL TANK 2 1 & 5 S3-454 LOOP CONTINUITY F1-177 TK 2 DUMP 4 & 6 S3-454 LOOP CONTINUITY F1-90 TK 2 40000 LB 3 S3-454 CONT TO GND ON EMPTY F1-1363 TK 2 10000 LB 2 & 7 S3-454 LOOP CONTINUITY F1-1393 TK 2 FULL

**Appendix J: FUEL TESTS (SHEET 1 OF 2)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 25, 2008 MD11-28-132 Revision 1 July 06, 2010 40 of 45 **BOEING SERVICE BULLETIN MD11-28-132 RETURN-TO-SERVICE TEST OF THE FUEL TANKS FLOAT SWITCHES**  TAIL TANK 1 & 3 S3-756 LOOP CONTINUITY F1-1396 TAIL TK EMPTY 1 & 3 S3-758 LOOP CONTINUITY F1-1397 TAIL L FULL 2 & 3 S3-759 LOOP CONTINUITY F1-1398 TAIL R FULL VENT BOX PIN 1JX S3-739 CONT BTW CONNECT F1-1399 Tail Tank Vent box PIN 3 P1-930 AUX TANKS 1 & 2 S3-1186 LOOP CONTINUITY F1-1359 UPPR AUX FULL 4 & 5 S3-805 LOOP CONTINUITY F1-1360 LWR AUX FULL FWD AUX TANK E R5-448 CONT TO GND ON EMPTY F1-631 FWD AUX EMPTY

**Appendix J: FUEL TESTS (SHEET 2 OF 2)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 25, 2008 MD11-28-132 Revision 1 July 06, 2010 41 of 45 **BOEING SERVICE BULLETIN MD11-28-132 This Appendix applies only to: Group 3.** 
**RETURN-TO-SERVICE TEST OF THE FUEL TANKS FLOAT SWITCHES** This test can be performed for each float switch circuit independently as the fuse is installed. REFERENCES (AMM) Tasks: MD-11 AMM 12-11-03 - PRESSURE DEFUELING OF THE AIRCRAFT This procedure should be used as necessary. Depower the Fuel system and open the related C/Bs. After fuse installation do a continuity test as shown in the table below. Note: For some fuses check continuity between two pins, for others check continuity to ground. REMARKS PINS TERMINAL TEST TYPE FUSE TO BE TESTED TANK 1 7 & 8 S3-450 LOOP CONTINUITY F1-176 - TANK 1 DUMP 1 & 6 S3-450 LOOP CONTINUITY F1-121 Tank 1 4000 lb 4 & 5 S3-450 LOOP CONTINUITY F1-120 Tank 1 6000 lb 1 & 2 S3-1301 LOOP CONTINUITY F1-1391 TK 1 INBD FULL 1 & 2 S3-1300 LOOP CONTINUITY F1-1392 TK 1 OUTBD FULL 1 & 3 S3-366 LOOP CONT NOT FULL F1-119 TK 1 TIP VENT BOX 1 & 2 S3-684 LOOP CONTINUITY F1-735 L WING OVERFILL TANK 3 7 & 8 S3-451 LOOP CONTINUITY F1-178 - TANK 3 DUMP 6 & 2 S3-451 LOOP CONTINUITY F1-122 Tank 3 4000 lb 4 & 5 S3-451 LOOP CONTINUITY F1-123 Tank 3 6000 lb 1 & 2 S3-1302 LOOP CONTINUITY F1-1394 TK 3 INBD FULL 1 & 2 S3-1303 LOOP CONTINUITY F1-1395 TK 3 OUTBD FULL 2 & 3 S3-452 LOOP CONT NOT FULL F1-124 TK 3 TIP VENT BOX 1 & 2 S3-683 LOOP CONTINUITY F1-734 R WING OVERFILL TANK 2 1 & 5 S3-454 LOOP CONTINUITY F1-177 TK 2 DUMP 4 & 6 S3-454 LOOP CONTINUITY F1-90 TK 2 40000 LB 3 S3-454 CONT TO GND ON EMPTY F1-1363 TK 2 10000 LB 2 & 7 S3-454 LOOP CONTINUITY F1-1393 TK 2 FULL

**Appendix K: FUEL TESTS (SHEET 1 OF 2)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 25, 2008 MD11-28-132 Revision 1 July 06, 2010 42 of 45 **BOEING SERVICE BULLETIN MD11-28-132 RETURN-TO-SERVICE TEST OF THE FUEL TANKS FLOAT SWITCHES**  TAIL TANK 1 & 3 S3-756 LOOP CONTINUITY F1-1396 TAIL TK EMPTY 1 & 3 S3-758 LOOP CONTINUITY F1-1397 TAIL L FULL 2 & 3 S3-759 LOOP CONTINUITY F1-1398 TAIL R FULL VENT BOX PIN 1JX S3-739 CONT BTW CONNECT F1-1399 Tail Tank Vent box PIN 3 P1-930 AUX TANKS 1 & 2 S3-1186 LOOP CONTINUITY F1-1359 UPPR AUX FULL 4 & 5 S3-805 LOOP CONTINUITY F1-1360 LWR AUX FULL FWD AUX TANK 22 P10-4410B CONT TO GND ON EMPTY F1-631 FWD AUX EMPTY

**Appendix K: FUEL TESTS (SHEET 2 OF 2)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 25, 2008 MD11-28-132 Revision 1 July 06, 2010 43 of 45 **BOEING SERVICE BULLETIN MD11-28-132 This Appendix applies only to: Group 4.** 
**RETURN-TO-SERVICE TEST OF THE FUEL TANKS FLOAT SWITCHES** This test can be performed for each float switch circuit independently as the fuse is installed. REFERENCES (AMM) Tasks: MD-11 AMM 12-11-03 - PRESSURE DEFUELING OF THE AIRCRAFT This procedure should be used as necessary. Depower the Fuel system and open the related C/Bs. After fuse installation do a continuity test as shown in the table below. Note: For some fuses check continuity between two pins, for others check continuity to ground. REMARKS PINS TERMINAL TEST TYPE FUSE TO BE TESTED TANK 1 7 & 8 S3-450 LOOP CONTINUITY F1-176 - TANK 1 DUMP 1 & 6 S3-450 LOOP CONTINUITY F1-121 Tank 1 4000 lb 4 & 5 S3-450 LOOP CONTINUITY F1-120 Tank 1 6000 lb 1 & 2 S3-1301 LOOP CONTINUITY F1-1391 TK 1 INBD FULL 1 & 2 S3-1300 LOOP CONTINUITY F1-1392 TK 1 OUTBD FULL 1 & 3 S3-366 LOOP CONT NOT FULL F1-119 TK 1 TIP VENT BOX 1 & 2 S3-684 LOOP CONTINUITY F1-735 L WING OVERFILL TANK 3 7 & 8 S3-451 LOOP CONTINUITY F1-178 - TANK 3 DUMP 6 & 2 S3-451 LOOP CONTINUITY F1-122 Tank 3 4000 lb 4 & 5 S3-451 LOOP CONTINUITY F1-123 Tank 3 6000 lb 1 & 2 S3-1302 LOOP CONTINUITY F1-1394 TK 3 INBD FULL 1 & 2 S3-1303 LOOP CONTINUITY F1-1395 TK 3 OUTBD FULL 2 & 3 S3-452 LOOP CONT NOT FULL F1-124 TK 3 TIP VENT BOX 1 & 2 S3-683 LOOP CONTINUITY F1-734 R WING OVERFILL TANK 2 1 & 5 S3-454 LOOP CONTINUITY F1-177 TK 2 DUMP 4 & 6 S3-454 LOOP CONTINUITY F1-90 TK 2 40000 LB 3 S3-454 CONT TO GND ON EMPTY F1-1363 TK 2 10000 LB 2 & 7 S3-454 LOOP CONTINUITY F1-1393 TK 2 FULL

**Appendix L: FUEL TESTS (SHEET 1 OF 2)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 25, 2008 MD11-28-132 Revision 1 July 06, 2010 44 of 45 **BOEING SERVICE BULLETIN MD11-28-132 RETURN-TO-SERVICE TEST OF THE FUEL TANKS FLOAT SWITCHES**  TAIL TANK 1 & 3 S3-756 LOOP CONTINUITY F1-1396 TAIL TK EMPTY 1 & 3 S3-758 LOOP CONTINUITY F1-1397 TAIL L FULL 2 & 3 S3-759 LOOP CONTINUITY F1-1398 TAIL R FULL VENT BOX PIN 1JX S3-739 CONT BTW CONNECT F1-1399 Tail Tank Vent box PIN 3 P1-930 AUX TANKS 1 & 2 S3-1186 LOOP CONTINUITY F1-1359 UPPR AUX FULL 4 & 5 S3-805 LOOP CONTINUITY F1-1360 LWR AUX FULL FWD AUX TANKS E R5-448 CONT TO GND ON EMPTY F1-191 FWD AUX TK 1 LOW D R5-448 CONT TO GND ON EMPTY F1-243 FWD AUX TK 2 LOW

**Appendix L: FUEL TESTS (SHEET 2 OF 2)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 25, 2008 MD11-28-132 Revision 1 July 06, 2010 45 of 45 **BOEING SERVICE BULLETIN MD11-28-132**