# Boeing Alert Service Bulletin MD11-28A148: Revision 1 - Rights: © The Boeing Company. Filed by the FAA in regulations.gov docket FAA-2015-3637; AD 2017-14-10 incorporates this document by reference. Not covered by OpenAirDocs’ CC0 dedication. - Document: [Boeing Alert Service Bulletin MD11-28A148](https://openairdocs.org/service-documents/boeing/md11-28a148.md) - Title as filed: U.S. DOT/FAA - Boeing MD11 SB MD11-28A148 - Pages: 46 - PDF: https://openairdocs.org/files/sha256/c6/37/c6375f4188f4099951217f06d8bdd618647606380070b20439790de090c27211 - Page: https://openairdocs.org/service-documents/boeing/md11-28a148/file/c6375f4188f4 ## Text This text is OCR from a scan. OCR can misread letters and numbers. Each page's text from the PDF; open the PDF at a page with #page=N. ### Page 1 (OCR) Commercial A BOEING Airplanes MD11 Service Bulletin ALERT Number: MD11-28A148 Original Issue: August 29, 2014 ATA System: 2825 SUBJECT: FUEL - Shroud Fuel Drain (All) - Pressure Check/Inspect/Repair Fuel Line Shrouds 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. ECCN: 9E991 BOEING PROPRIETARY, CONFIDENTIAL AND/OR TRADE SECRET Copyright © 2014 Boeing. Unpublished Work. All Rights Reserved. Treatment of this document and its content is governed by contract with Boeing. Rights to use this document are licensed on a per aircraft basis and such rights may not be transferable. For more information, contact The Boeing Company. Boeing, the Boeing signature, the Boeing symbol, 707, 717, 727, 737, 747, 757, 767, 777, 787, Dreamliner, BBJ, DC-8, DC-9, DC-10, KC-10, KC-46, KDC-10, MD-10, MD-11, MD-80, MD-88, MD-90, P-8, Poseidon and Boeing liveries are all trademarks owned by The Boeing Company; and no trademark license is granted in connection with this document unless provided in writing by Boeing. Original Issue: August 29, 2014 MD11-28A148 1 of 46 3.0 ### Page 2 (OCR) BOEING SERVICE BULLETIN MD11-28A148 ALERT ALERT ТЗЯО ДВОАЯТ ЛОИА ЗАІТИ УАТВІРОЯ ВИІВОВ STOLenO B1587707 BLANK PAGE rsad se Original Issue: August 29, 2014 Export Controlled ECCN: 9E991 - BOEING MD11-28A148 PROPRIETARY - Copyright © Unpublished 2 of 46 Work - See page 1 for details. ### Page 3 (OCR) BOEING SERVICE BULLETIN MD11-28A148 ALERT ALERT Table of Contents Summary 5 1. PLANNING INFORMATION 9 Effectivity . 9 1. Airplanes 9 2. Spares Affected 10 Concurrent Requirements 10 Reason 10 Description 10 Compliance . 11 Approval 13 Manpower 13 Weight and Balance Changes 14 Electrical Load Data 14 References 14 1. Existing Data: 14 2. Data Supplied with this Service Bulletin: 15 3. Installation Drawings Used in the Preparation of this Service Bulletin: 15 K. Publications Affected . 15 L. Interchangeability and Intermixability of Parts 15 M. Software Accomplishment Summary 15 2. MATERIAL INFORMATION. 17 A. Material - Price and Availability . 17 B. Industry Support Information. 17 C. Parts Necessary for Each Airplane 17 1. Kits/Parts . 17 2. Parts and Materials Supplied by the Operator. 17 3. Parts Modified and Reidentified 18 4. Parts Removed and Not Replaced 18 D. Parts Necessary to Change Spares 18 Special Tooling - Price and Availability 18 F. Special Tooling Necessary to do this Service Bulletin. 18 ACCOMPLISHMENT INSTRUCTIONS 19 GENERAL INFORMATION . 19 B. WORK INSTRUCTIONS. 20 FIGURE 1: CENTER CARGO COMPARTMENT LEFT TUNNEL - FUEL LINE SHROUDS - INSPECTION 23 APPENDIX A: CHECK FOR PRESENCE OF FUEL AT THE FUEL SHROUD DRAIN VALVES. 25 APPENDIX B: PRESSURE TEST OF THE TAIL TANK FUEL SHROUD DRAIN SYSTEM. 35 APPENDIX C: PRESSURE TEST OF THE AFT FUSELAGE FUEL SHROUD DRAIN SYSTEM 44 Original Issue: August 29, 2014 Export Controlled ECCN: 9E991 - BOEING MD11-28A148 PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 3 of 46 ### Page 4 (OCR) BOEING SERVICE BULLETIN MD11-28A148 ALERT ALERT BLANK PAGE Original Issue: August 29, 2014 Export Controlled ECCN: 9E991 - BOEING MD11-28A148 PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 4 of 46 ### Page 5 (OCR) Commercial A BOEING Airplanes MD11 Service Bulletin - ALERT Number: MD11-28A148 Summary Original Issue: August 29, 2014 ATA System: 2825 SUBJECT: FUEL - Shroud Fuel Drain (All) - Pressure Check/Inspect/Repair Fuel Line Shrouds THIS BULLETIN IS SENT TO THE OPERATORS OF RECORD OF THE AIRPLANES SHOWN IN PARAGRAPH 1.A., EFFECTIVITY. IF AN AIRPLANE HAS BEEN LEASED OR SOLD, SEND THIS SERVICE BULLETIN TO THE NEW OPERATOR. IF APPLICABLE SPARES HAVE BEEN SOLD, SEND THIS SERVICE BULLETIN TO THE NEW OWNER. CONCURRENT REQUIREMENTS None. BACKGROUND An operator reported fuel odor in the cabin. Fuel was found leaking from a cracked fuel line shroud in the left cargo compartment equipment tunnel. There have been a minimum of 10 fuel shroud leaks in the same area since 2001. The Continued Operational Safety Program has made this an "airplane level safety issue" because of the quantity of fuel found below the cargo compartment floor. The current maintenance planning document recommends a check of the fuel shroud system drains at each 1 A check and an air pressure leak check of the fuel shroud system at each 2 C check. Increasing the frequency of the fuel shroud system drain checks and adding an eddy current inspection of the fuel line shrouds between the existing air pressure leak checks will determine the condition of the fuel shrouds. If a cracked condition of a fuel shroud is not corrected, continued operation of an airplane could result in fuel accumulation below the cargo compartment floor and consequent increased risk of fire. This table is provided to operators for planning purposes only. Refer to the applicable sections for more information. Planning Data Affected Reference Spares Affected No Paragraph 1.A.2., Spares Affected AD Related Yes Paragraph 1.E., Compliance and Paragraph 1.F., Approval Weight and Balance Change No Paragraph 1.H., Weight and Balance Changes Electrical Load Changed No Paragraph 1.l., Electrical Load Data Publications Affected Yes Paragraph 1.K., Publications Affected Airplane Flight Operations Affected (Flight Crew No Paragraph 1.K., Publications Affected Operations Manual and/or FAA Approved Air- plane Flight Manual) Original Issue: August 29, 2014 Export Controlled ECCN: 9E991 - BOEING MD11-28A148 PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 5 of 46 ### Page 6 (OCR) BOEING SERVICE BULLETIN MD11-28A148 ALERT ALERT Planning Data Affected Reference Kits/Parts Required No Paragraph 2.C.1., Kits/Parts Operator Supplied Parts/Material Yes Paragraph 2.C.2., Parts and Materials Supplied by the Operator Special Tooling Required Yes Paragraph 2.F., Special Tooling Necessary to do this Service Bulletin ACTION There are two options to do this service bulletin. Choose an option to best fit maintenance capabilities or schedule. This service bulletin gives instructions to do as follows: OPTION 1: 1. Do the following: a. Check for presence of fuel at the fuel shroud drain valves and do maintenance/repairs based on condition found. b. Do a High Frequency Eddy Current Inspection of the engine feed and tail tank transfer fuel line shrouds and do action based on condition found. c. Pressure test the engine feed and tail tank transfer fuel line shrouds and do maintenance/repairs based on condition found. 2. Continue with repetitive tests/inspections described in Paragraph 1.E., Compliance, Table 1. OPTION 2: 1. Do the following: a. Check for presence of fuel at the fuel shroud drain valves and do maintenance/repairs based on condition found. b. Pressure test the engine feed and tail tank transfer fuel line shrouds and do maintenance/repairs based on condition found. 2. Continue with repetitive tests/inspections described in Paragraph 1.E., Compliance, Table 2. EFFECTIVITY MD-11 and MD-11F Airplane(s). Refer to Paragraph 1.A.1., Airplanes, for the list of affected airplane(s). COMPLIANCE The Federal Aviation Administration (FAA) will possibly release an Airworthiness Directive related to this service bulletin. The Airworthiness Directive will make the compliance tasks and times given in this service bulletin mandatory. Refer to Paragraph 1.E., Compliance. Original Issue: August 29, 2014 Export Controlled ECCN: 9E991 - BOEING MD11-28A148 PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 6 of 46 ### Page 7 (OCR) BOEING SERVICE BULLETIN MD11-28A148 ALERT ALERT INDUSTRY SUPPORT INFORMATION Boeing warranty remedies are not available for the inspection and/or repair procedures given in this service bulletin. MANPOWER Refer to Paragraph 1.G., Manpower. MATERIAL INFORMATION Operator Supplied Parts/Materials. Refer to Paragraph 2.A., Material - Price and Availability. АЯВИКТО ЗАВИНКОЗНО Original Issue: August 29, 2014 BrOS RS 18U0UA Export Controlled ECCN: 9E991 - BOEING MD11-28A148 PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 7 of 46 ### Page 8 (OCR) BOEING SERVICE BULLETIN MD11-28A148 ALERT ALERT PRESSURE CHECK/INSPECT/REPAIR FUEL LINE SHROUDS 2323667 Original Issue: August 29, 2014 PROPRIETARY - Copyright © Unpublished Export Controlled ECCN: 9E991 - BOEING Work - See page 1 for details. MD11-28A148 8 of 46 ### Page 9 (OCR) Commercial A BOEING Airplanes MD11 Service Bulletin • ALERT Number: MD11-28A148 Original Issue: August 29, 2014 ATA System: 2825 SUBJECT: FUEL - Shroud Fuel Drain (All) - Pressure Check/Inspect/Repair Fuel Line Shrouds THIS BULLETIN IS SENT TO THE OPERATORS OF RECORD OF THE AIRPLANES SHOWN IN PARAGRAPH 1.A., EFFECTIVITY. IF AN AIRPLANE HAS BEEN LEASED OR SOLD, SEND THIS SERVICE BULLETIN TO THE NEW OPERATOR. IF APPLICABLE SPARES HAVE BEEN SOLD, SEND THIS SERVICE BULLETIN TO THE NEW OWNER. 1. PLANNING INFORMATION A. Effectivity 1. Airplanes This service bulletin is for the airplanes shown below. GROUP CONFIGURATION DESCRIPTION 1 MD-11 and MD-11F Airplanes. Airplane Models: MD-11, MD-11F Fuselage Num- Group ber 447 - 449 1 450 - 459 1 460 - 469 1 470 - 479 1 480 - 489 1 490 - 499 1 500 - 509 1 510 - 519 1 520 - 529 1 Original Issue: August 29, 2014 Export Controlled ECCN: 9E991 - BOEING MD11-28A148 PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 9 of 46 ### Page 10 (OCR) BOEING SERVICE BULLETIN MD11-28A148 ALERT ALERT Fuselage Num- Group ber 530 - 539 1 540 - 549 1 550 - 559 1 560 - 569 1 BATASS-ITOM 570 - 579 1 PRIVE ATA 580 - 589 590 - 599 1 600 - 609 1 610 - 619 1 КВИА ЯТА МА ЧІ УПМТОЗВУ АТ SUBADURA RI ROTARERO WS BET 620 - 629 1 630 - 639 1 640 - 646 1 2. Spares Affected None. B. Concurrent Requirements None. C. Reason An operator reported fuel odor in the cabin. Fuel was found leaking from a cracked fuel line shroud in the left cargo compartment equipment tunnel. There have been a minimum of 10 fuel shroud leaks in the same area since 2001. The Continued Operational Safety Program has made this an "airplane level safety issue" because of the quantity of fuel found below the cargo compartment floor. The current maintenance planning document recommends a check of the fuel shroud system drains at each 1 A check and an air pressure leak check of the fuel shroud system at each 2 C check. Increasing the frequency of the fuel shroud system drain checks and adding an eddy current inspection of the fuel line shrouds between the existing air pressure leak checks will determine the condition of the fuel shrouds. If a cracked condition of a fuel shroud is not corrected, continued operation of an airplane could result in fuel accumulation below the cargo compartment floor and consequent increased risk of fire. D. Description There are two options to do this service bulletin. Choose an option to best fit maintenance capabilities or schedule. This service bulletin gives instructions to do as follows: OPTION 1: 1. Do the following: Original Issue: August 29, 2014 Export Controlled ECCN: 9E991 - BOEING MD11-28A148 PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 10 of 46 ### Page 11 (OCR) BOEING SERVICE BULLETIN MD11-28A148 ALERT ALERT a. Check for presence of fuel at the fuel shroud drain valves and do maintenance/repairs based on condition found. b. Do a High Frequency Eddy Current Inspection of the engine feed and tail tank transfer fuel line shrouds and do action based on condition found. c. Pressure test the engine feed and tail tank transfer fuel line shrouds and do maintenance/repairs based on condition found. 2. Continue with repetitive tests/inspections described in Paragraph 1.E., Compliance, Table 1. OPTION 2: 1. Do the following: a. Check for presence of fuel at the fuel shroud drain valves and do maintenance/repairs based on condition found. b. Pressure test the engine feed and tail tank transfer fuel line shrouds and do maintenance/repairs based on condition found. 2. Continue with repetitive tests/inspections described in Paragraph 1.E., Compliance, Table 2. The work in this service bulletin is done in the maintenance zone(s) given below. Affected Maintenance Zones Model Zone MD-11, MD-11F 181, 316 E. Compliance The Federal Aviation Administration (FAA) will possibly release an Airworthiness Directive related to this service bulletin. The Airworthiness Directive will make the compliance tasks and times given in this service bulletin mandatory. Do the required actions in accordance with Paragraph 3. Accomplishment Instructions. noute aani anemun gobe bran an bebivoo holdeden ine nua yabe na primohao put or to lael enuadeng and ? Original Issue: August 29, 2014 PROPRIETARY - Copyright © Unpublished Export Controlled ECCN: 9E991 - BOEING MD11-28A148 Work - See page 1 for details. 11 of 46 ### Page 12 (OCR) BOEING SERVICE BULLETIN MD11-28A148 ALERT ALERT Select one of the following Compliance Tables: Option 1 - Table 1 - Check Fuel Shroud Drain Valves for Presence of Fuel, Pressure Check Fuel Line Shrouds and Eddy Current Inspect Fuel Line Shrouds for Cracks Condition Action Compliance Time Repeat Interval (Whichever Occurs (Whichever Occurs First) First) All Airplanes. Check Fuel Shroud Within 6 months after 10 days Drain Valves for Pres- the original issue date of ence of Fuel. this service bulletin. Pressure Tests of the Within 15,000 flight 15,000 flight hours (a) Tail Tank Fuel Shroud hours from the original Drain System and the issue date of this service Aft Fuselage Fuel bulletin. (a) Shroud Drain System Do High Frequency Ed- Within 7,500 flight hours 7,500 flight hours (a) dy Current Inspection of from the original issue fuel line shrouds. date of this service bul- letin. (a) CONDITION 1: Leakage Repair leaking Before further flight rate becomes more than 32.0 fluid-ounces in a 24 hour period CONDITION 2: No No further action re- Crack(s) Found by High quired. Frequency Eddy Current Inspection or Pressure Test CONDITION 3: Crack(s) Repair crack(s). Before further flight. Found by High Frequen- cy Eddy Current Inspec- tion or Pressure Test (a) When a pressure test of the fuel shroud drain system is performed, it can be used as an accept- able alternate method to the eddy current inspection provided the next eddy current inspection is done within the 7,500 flight hour interval. However, performing an eddy current inspection cannot be used as an acceptable alternate method for the pressure test of the fuel shroud drain system. Original Issue: August 29, 2014 PROPRIETARY - Copyright © Unpublished Export Controlled ECCN: 9E991 - BOEING MD11-28A148 Work - See page 1 for details. 12 of 46 ### Page 13 (OCR) BOEING SERVICE BULLETIN MD11-28A148 ALERT ALERT Option 2 - Table 2 - Check Fuel Shroud Drain Valves for Presence of Fuel and Pressure Check Fuel Line Shrouds Condition Action Compliance Time Repeat Interval (Whichever Occurs (Whichever Occurs First) First) All Airplanes. Check Fuel Shroud Within 6 months after 10 days Drain Valves for Pres- the original issue date of ence of Fuel. this service bulletin. Pressure Tests of the Within 7,500 flight hours 7,500 flight hours Tail Tank Fuel Shroud from the original issue Drain System and the date of this service bul- Aft Fuselage Fuel letin. Shroud Drain System. CONDITION 1: Leakage Repair leaking Before further flight rate becomes more than 32.0 fluid-ounces in a 24 hour period CONDITION 2: No No further action re- Crack(s) Found by quired. Pressure Test CONDITION 3: Crack(s) Repair crack(s). Before further flight. Found by Pressure Test 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 approvec 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 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 inspection/repair 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 Original Issue: August 29, 2014 Export Controlled ECCN: 9E991 - BOEING MD11-28A148 PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 13 of 46 ### Page 14 (OCR) BOEING SERVICE BULLETIN MD11-28A148 ALERT ALERT • Time to find the tools. Option 1 Task Number of Persons Task Hours Elapsed Hours Open Access 1 0.5 0.5 Check drain valves 1 1.0 1.0 FIGURE 1 (Inspection) 4.0 4.0 Pressure test fuel shroud 2.0 2.0 Close Access 1 0.5 0.5 TOTAL FOR EACH AIRPLANE 2.0 - 5.0 (a) 2.0 - 5.0 (a) (a) A range of Task Hours and Elapsed Hours are given to do the tasks outlined in this service bulletin for airplanes with no repairs necessary. Actual Task Hours and Elapsed Hours are contingent upon compliance interval and any repairs that may be necessary. Option 2 Task Number of Persons Task Hours Elapsed Hours Open Access 1 0.5 0.5 Check drain valves 1.0 1.0 Pressure test fuel shroud 2.0 2.0 Close Access 0.5 0.5 TOTAL FOR EACH AIRPLANE 2.0 - 3.0 (a) 2.0 - 3.0 (a) (a) A range of Task Hours and Elapsed Hours are given to do the tasks outlined in this service bulletin for airplanes with no repairs necessary. Actual Task Hours and Elapsed Hours are contingent upon compliance interval and any repairs that may be necessary. H. Weight and Balance Changes None. I. Electrical Load Data Not changed. J. References 1. Existing Data: a. MD-11 Aircraft Maintenance Manual (AMM) 06-21-00, 28-25-06, 71-00-00 b. MD-11 Structural Repair Manual (SRM) 51, 53-00-01 c. Non-Destructive Test Standard Practices Manual (NDTSPM) 06-00-04, 06-10-01.001 d. Standard Overhaul Practices Manual (SOPM) 20-50-01 Original Issue: August 29, 2014 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished MD11-28A148 Work - See page 1 for details. 14 of 46 ### Page 15 (OCR) BOEING SERVICE BULLETIN MD11-28A148 ALERT ALERT 2. Data Supplied with this Service Bulletin: None. 3. Installation Drawings Used in the Preparation of this Service Bulletin: None. K. Publications Affected 1. Publications: Publication Chapter-Section Aircraft Maintenance Manual 28-25 Maintenance Planning Document 28 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. M. Software Accomplishment Summary Not affected. Original Issue: August 29, 2014 B105 8S R Export Controlled ECCN: 9E991 - BOEING MD11-28A148 PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 15 of 46 ### Page 16 (OCR) BOEING SERVICE BULLETIN MD11-28A148 ALERT ALERT Bobbalda? cut hated ver omena 10y endanent emeral spared HE EO SURE BOO maad teet openeranese! chain bre wideonna bastard BLANK PAGE Original Issue: August 29, 2014 Export Controlled ECCN: 9E991 - BOEING MD11-28A148 PROPRIETARY - Copyright © Unpublished 16 of 46 Work - See page 1 for details. ### Page 17 (OCR) BOEING SERVICE BULLETIN MD11-28A148 ALERT ALERT 2. MATERIAL INFORMATION A. Material - Price and Availability None. B. Industry Support Information Boeing warranty remedies are not available for the inspection and/or repair procedures given in this service bulletin. C. Parts Necessary for Each Airplane 1. Kits/Parts None. 2. Parts and Materials Supplied by the Operator Option 1 and 2 - No Crack(s) Found: None. Part Number / Specification QTY Name Notes (DPM 660-1) As Required Bag - Polyethylene, Self-sealing (a) or Equivalent (a) Can be purchased from: Landsberg, Kent H. Company, 1640 South Greenwood Street, Montebello, California, 90640, CAGE: 6D892 Option 1 and 2 - Crack(s) Found: Part Number / Specification QTY Name Notes PR-1422 B-2 Sealant As Required Compound - Sealing, Integral (a) (DMS 2082) Fuel Tanks and Fuel Cell Cavi- or ties Equivalent 515X347 Base with 910X527 As Required Primer, Fluid Resistant (a) Catalyst (DMS 1786) or Equivalent SkyKleen 1000 As Required Solvent, Sealant Remover (b) (DPM 6410) or Equivalent (DMS 1820 T1A2) As Required Wipers - Cleaning, Cotton, (c) or White Equivalent Original Issue: August 29, 2014 Export Controlled ECCN: 9E991 - BOEING MD11-28A148 PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 17 of 46 ### Page 18 (OCR) BOEING SERVICE BULLETIN MD11-28A148 ALERT ALERT Part Number / Specification QTY Name Notes (DPM 660-1) As Required Bag - Polyethylene, Self-sealing (d) or Equivalent (a) Can be purchased from: PRC-Desoto International, Incorporated, 11601 United Street, Mojave, California 93501, CAGE: 85570 (b) Can be purchased from: Solutia Incorporated, 8201 Idaho Avenue, Saint Louis, Missouri, 63111, CAGE: 1MFY8 (c) Can be purchased from: Sandler Brothers Incorporated, 3621 Medford Street, Los Angeles, California, 90063, CAGE: 019H7 (d) Can be purchased from: Landsberg, Kent H. Company, 1640 South Greenwood Street, Montebello, California, 90640, CAGE: 6D892 3. Parts Modified and Reidentified None. 4. Parts Removed and Not Replaced None. D. Parts Necessary to Change Spares None. E. Special Tooling - Price and Availability Test equipment required to perform eddy current inspections, including procurement sources, is listed in the Non-Destructive Test Standard Practices Manual (NDTSPM). Choice of special equipment or optional test equipment and respective suppliers is at operator's option. Refer to NDTSPM 06-00-04 for additional supplier/vendor information. F. Special Tooling Necessary to do this Service Bulletin To get the test equipment required, refer to Paragraph 2.E., Special Tooling - Price and Availability. Maintenance and overhaul tools in the manuals shown in Paragraph 1.J., References, can also be necessary. Examine operator tool supply to make sure all necessary tools are available. Original Issue: August 29, 2014 Export Controlled ECCN: 9E991 - BOEING MD11-28A148 PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 18 of 46 ### Page 19 (OCR) BOEING SERVICE BULLETIN MD11-28A148 ALERT ALERT 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. 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 MD-11 SRM 51. 4. If the length of any fastener specified in this service bulletin does not meet installation standards given in Structural Repair Manual (SRM) Chapter 51, then a fastener of the same specification, or an approved substitute, with a length which meets the installation standards given in SRM Chapter 51 may be used. In addition, washers may be installed for fastener grip length in accordance with SRM Chapter 51. Refer to SOPM 20-50-01 for alternate full threaded fasteners (screws) needed for installation in this service bulletin. 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 are in MD-11 SRM 51. Original Issue: August 29, 2014 Export Controlled ECCN: 9E991 - BOEING MD11-28A148 PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 19 of 46 ### Page 20 (OCR) BOEING SERVICE BULLETIN MD11-28A148 ALERT ALERT Torque Values: - Values for structural fasteners are given in MD-11 Structural Repair Manual, Chapter 51. Values for airframe maintenance tasks are included in Chapter 20 of MD-11 Airplane Maintenance Manual (AMM). Values for electrical maintenance tasks are included in Chapter 20 of Standard Wiring Practices Manual (SWPM). Values for engine maintenance tasks are included in Chapter 70 of MD-11 Airplane Maintenance Manual (AMM). Non-standard torque values for maintenance tasks are included in the applicable installation step. Obey all of the warnings and cautions given in the specified manual sections. 8. 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. 9. 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. 10. 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. 11. 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. 12. Use of colors in Figures is based on guidance from the ATA e-Business Program (ATA) iSpec 2200. 13. When more than one OPTION is given for a CONDITION, do only one of the OPTION numbers. When more than one ACTION is given for a CONDITION number or an OPTION number, do all of the ACTION numbers for that CONDITION number or OPTION number. 14. The compliance times for the actions in Paragraph 3.B., WORK INSTRUCTIONS are in Paragraph 1.E., Compliance. B. WORK INSTRUCTIONS OPTION 1: 1. Check for Presence of Fuel at the Fuel Shroud Drain Valves at intervals specified by Paragraph 1.E., Compliance, Option 1 - Table 1 in accordance with APPENDIX A. 2. Do the following: a. Gain access to area 181, center cargo left tunnel. Refer to MD-11 AMM 06-21-00. Original Issue: August 29, 2014 MD11-28A148 Work - See page 1 for details. 20 of 46 ### Page 21 (OCR) BOEING SERVICE BULLETIN MD11-28A148 ALERT ALERT Do High Frequency Eddy Current Inspection for cracked fuel line shrouds at intervals specified by Paragraph 1.E., Compliance, Option 1 - Table 1 in accordance with FIGURE 1. b. Do Pressure Test of the Tail Tank Fuel Shroud Drain System at intervals specified by Paragraph 1.E., Compliance Option 1 - Table 1 in accordance with APPENDIX B. If the pressure decrease is more than 1.0 PSI in 5 minutes, there is a crack. c. Do Pressure Test of the Aft Fuselage Fuel Shroud Drain System at intervals specified by Paragraph 1.E., Compliance, Option 1 - Table 1 in accordance with APPENDIX C. If the pressure decrease is more than 1.0 PSI in 5 minutes, there is a crack. CONDITION 1: Leakage rate becomes more than 32.0 fluid-ounces in a 24 hour period Repair leaking. CONDITION 2: No Crack(s) Found No further action required. CONDITION 3: Crack(s) Found Repair cracks found in fuel line shrouds in accordance with "Repair 3 - Fuel Line Shroud Repair" MD-11 SRM 53-00-01. 3. Close access. 4. Put the airplane back to a serviceable condition. OPTION 2: 1. Check for Presence of Fuel at the Fuel Shroud Drain Valves at intervals specified by Paragraph 1.E., Compliance, Option 2 - Table 2 in accordance with APPENDIX A. 2. Do the following: a. Do Pressure Test of the Tail Tank Fuel Shroud Drain System at intervals specified by Paragraph 1.E., Compliance, Option 2 - Table 2 in accordance with APPENDIX B. If the pressure decrease is more than 1.0 PSI in 5 minutes, there is a crack. b. Do Pressure Test of the Aft Fuselage Fuel Shroud Drain System at intervals specified by Paragraph 1.E., Compliance, Option 2 - Table 2 in accordance with APPENDIX C. If the pressure decrease is more than 1.0 PSI in 5 minutes, there is a crack. CONDITION 1: Leakage rate becomes more than 32.0 fluid-ounces in a 24 hour period Repair leaking. CONDITION 2: No Crack(s) Found No further action required. Original Issue: August 29, 2014 Export Controlled ECCN: 9E991 - BOEING MD11-28A148 PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 21 of 46 ### Page 22 (OCR) BOEING SERVICE BULLETIN MD11-28A148 ALERT ALERT CONDITION 3: Crack(s) Found Repair cracks found in fuel line shrouds in accordance with "Repair 3 - Fuel Line Shroud Repair" MD-11 SRM 53-00-01. 3. Close access. 4. Put the airplane back to a serviceable condition. свора повза term on AnDO TU ORTO E VOITOVO? 010:00 C M92 71 0M 0A501E SREO2 polb co eldaaolae e orbad ancia e am tuar S HOISO nae bered Balbone de nota to ove nd poa lo sat le lento aaroer aaraa priwotal ant oct nonan taboo Henotn te motane nen0 booma leu naT neta to lee T au apen coe Sata ENg ST D KOMERA nw sanita nEES nano sonatamnO ET sono n anart et om d n 1a9 O Fe etom II BERL N10 le01 e Den n3 Сойоштои і гавля В gabon Ternos (boniacn nolbe tensor ov Original Issue: August 29, 2014 send enoner Sa S0 lt Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 90 10 ZZ ### Page 23 (OCR) BOEING SERVICE BULLETIN MD11-28A148 ALERT ALERT 1 000000€ STA 1821.000 STA 1801.000 STA 1781,000 STA 1761.000 2323199 FIGURE 1: CENTER CARGO COMPARTMENT LEFT TUNNEL - FUEL LINE SHROUDS - INSPECTION (SHEET 1 OF 2) Original Issue: August 29, 2014 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished MD11-28A148 Work - See page 1 for details. 23 of 46 ### Page 24 (OCR) BOEING SERVICE BULLETIN MD11-28A148 ALERT ALERT The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY numbers shown below are the number of parts necessary for each airplane. STEP TASK NAME IDENTIFICATION QTY MORE DATA 1 Inspect Engine Feed and Tail Tank AAL7288-1 2 (a) Fuel Drain Shroud Assem- and blies AAL7289-1 (a) Do High Frequency Eddy Current Inspection of the highlighted areas of the engine feed and tail tank transfer fuel line shrouds at Stations 1781 and 1801 in accordance with NDTSPM 06-10-01.001 (ETHF Procedure 1). FIGURE 1: CENTER CARGO COMPARTMENT LEFT TUNNEL - FUEL LINE SHROUDS - INSPECTION (SHEET 2 OF 2) Original Issue: August 29, 2014 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. ### Page 25 (OCR) BOEING SERVICE BULLETIN MD11-28A148 ALERT ALERT 1. CHECK FOR PRESENCE OF FUEL AT THE FUEL SHROUD DRAIN VALVES a. References REFERENCE TITLE MD-11 AMM 71-00-00 POWER PLANT b. Tools/Equipment DESCRIPTION SPECIFICATION Container - 1 Quart, Calibrated c. Consumable Materials NOTE: Equivalent replacements are permitted for the items that follow. NOTE: It is possible that some materials in the Consumable Materials chart cannot be used for some or all of the necessary applications. Before you use the materials, make sure the types, quantities, and applications of the materials necessary are legally permitted in your location. All persons must obey all applicable federal, state, local, and provincial laws and regulations when it is nec- essary to work with these materials. DESCRIPTION SPECIFICATION Bag - Polyethylene, Self-sealing DPM 660-1 d. Procedure - Check for Presence of Fuel at the Fuel Shroud Drain Valves WARNING: MAKE SURE YOU OBEY ALL SAFETY PRECAUTIONS AND REGULATIONS DURING FUEL SYSTEM MAINTENANCE. THIS WILL PREVENT INJURY TO PERSONS AND DAMAGE TO EQUIPMENT. (1) Check for Presence of Fuel at the Fuel Shroud Drain Valves as follows: CHECK MAXIMUM SERVICE- REMARKS ABLE LIMITS 1 Put a 1 Quart calibrated container below the applicable drain valve (1). (Sheet 6 of 10) APPENDIX A: CHECK FOR PRESENCE OF FUEL AT THE FUEL SHROUD DRAIN VALVES (SHEET 1 OF 10) Original Issue: August 29, 2014 Export Controlled ECCN: 9E991 - BOEING MD11-28A148 PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 25 of 46 ### Page 26 (OCR) BOEING SERVICE BULLETIN MD11-28A148 ALERT ALERT CHECK MAXIMUM SERVICE- REMARKS ABLE LIMITS 2 Put a screwdriver in the poppet slot and push approximately 0.30 inches. Drain the fuel into the container. When the fuel stops, release the poppet. (a) Use the container to mea- If the quantity is less than Make a record to monitor sure the quantity of fuel 8.0 fluid-ounces in a 24 the leak. drained from the shroud. hour period: (D) If the quantity is 8.0 fluid- Make repair at the next ounces to 32.0 fluid- convenient maintenance ounces in a 24 hour period: period. (c) If the leakage rate be- Do the repair at the time comes more than 32.0 flu- specified in Paragraph id-ounces in a 24 hour peri- 1.E., Compliance, for od: CONDITION 1. NOTE: The requirements for the 24 hour shroud check period is as follows: The 24 hour maximum serviceable limits check requires that the airplane under inspection must have flown a minimum of one flight cycle in that 24 hour period, or pressurize the fuel system for a minimum of 2 hours using the required airplane fuel pumps and/or run Number 2 engine for approximately 25 minutes. Refer to MD-11 AMM 71-00-00. NOTE: You can do a check of the leakage for more than or less than 24 hours of time. To do so, adjust the permitted leakage rate in proportion to the quantity of the time change. For example: 4 fluid-ounces in 12 hours. NOTE: If there is leakage from the aft valve, the leak source is the tail tank shroud drain line. If there is leakage from the forward valve, the leak source is the Number 2 engine shroud drain line. POST MD11-28-115 If there is leakage from the aft drain valve (Sheet 6 of 10), do as follows: 4 Put a container below the horizontal tank fuel shroud check drain valve (2). (Sheet 7 of 10) 5 Put a screwdriver in the poppet slot and push approximately 0.30 inches. Drain the fuel into the container. When the fuel stops, release the poppet. APPENDIX A: CHECK FOR PRESENCE OF FUEL AT THE FUEL SHROUD DRAIN VALVES (SHEET 2 OF 10) Original Issue: August 29, 2014 Export Controlled ECCN: 9E991 - BOEING MD11-28A148 PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 26 of 46 ### Page 27 (OCR) BOEING SERVICE BULLETIN MD11-28A148 ALERT ALERT CHECK MAXIMUM SERVICE- REMARKS ABLE LIMITS (a) Use a container to mea- If the quantity is less than Make a record to monitor sure the quantity of fuel 8.0 fluid-ounces in a 24 the leak. drained from the shroud. hour period. (b) If the quantity is 8.0 fluid- Make repair at the next ounces to 32.0 fluid- convenient maintenance ounces in a 24 hour period: period. (c) If the leakage rate be- Do the repair at the time comes more than 32.0 flu- specified in Paragraph id-ounces in a 24 hour peri- 1.E., Compliance, for CONDITION 1. (d) A quantity of fuel is detect- There is a leak in the sys- ed at the check/drain valve. tem upstream of the check/drain valve. (e) No fuel is detected at the The leak is in system check/drain valve (4). downstream of the check/drain valve. If there is leakage from the center tank fuel shroud check drain valve (Sheet 8 of 10), do as follows: 7 Put a container below the center tank fuel shroud check drain valve (3). 8 Put a screwdriver in the poppet slot and push approximately 0.30 inches. Drain the tuel into the container. 9 When the fuel stops, release the poppet. (a) Use a container to mea- If the quantity is less than Make a record to monitor sure the quantity of fuel 8.0 fluid-ounces in a 24 the leak. drained from the shroud. hour period. (b) If the quantity is 8.0 fluid- Make repair at the next ounces to 32.0 fluid- convenient maintenance ounces in a 24 hour period: period. (c) If the leakage rate be- Do the repair before the comes more than 32.0 flu- next flight. id-ounces in a 24 hour peri- od: (d) A quantity of fuel is detect- There is a leak in the sys- ed at the check/drain valve. tem upstream of the check/drain valve. If there is leakage from the aft left wing fuel shroud check drain valve (Sheet 9 of 10), do as follows: 10 Put a container below the aft left wing fuel shroud check drain valve (4). APPENDIX A: CHECK FOR PRESENCE OF FUEL AT THE FUEL SHROUD DRAIN VALVES (SHEET 3 OF 10) Original Issue: August 29, 2014 Export Controlled ECCN: 9E991 - BOEING MD11-28A148 PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 27 of 46 ### Page 28 (OCR) BOEING SERVICE BULLETIN MD11-28A148 ALERT ALERT CHECK MAXIMUM SERVICE- REMARKS ABLE LIMITS 11 Put a screwdriver in the poppet slot and push approximately 0.30 inches. Drain the fuel into the container. 12 When the fuel stops, release the poppet. (a) Use a container to mea- If the quantity is less than Make a record to monitor sure the quantity of fuel 8.0 fluid-ounces in a 24 the leak. drained from the shroud. hour period. (b) If the quantity is 8.0 fluid- Make repair at the next ounces to 32.0 fluid- convenient maintenance ounces in a 24 hour period: period. (c) If the leakage rate be- Do the repair at the time comes more than 32.0 flu- specified in Paragraph id-ounces in a 24 hour peri- 1.E., Compliance, for od: CONDITION 1. (d) A quantity of fuel is detect- There is a leak in the sys- ed at the check/drain valve. tem upstream of the check/drain valve. If there is leakage from the aft fuselage fuel shroud check drain valve (Sheet 10 of 10), do as follows: 13 Put a container below the aft fuselage fuel shroud check drain valve (5). 14 Put a screwdriver in the poppet slot and push approximately 0.30 inches. Drain the fuel into the container. 15 When the fuel stops, release the poppet. (a) Use a container to mea- If the quantity is less than Make a record to monitor sure the quantity of fuel 8.0 fluid-ounces in a 24 the leak. drained from the shroud. hour period. (b) If the quantity is 8.0 fluid- Make repair at the next ounces to 32.0 fluid- convenient maintenance ounces in a 24 hour period: period. (c) If the leakage rate be- Do the repair before the comes more than 32.0 flu- next flight. id-ounces in a 24 hour peri- od: (a) A quantity of fuel is detect- There is a leak in the sys- ed at the check/drain valve. tem upstream of the check/drain valve. 16 Remove the applicable check/drain valve in those areas where a quantity of fuel is detected. 17 Install a clear plastic bag over the applicable check/drain valve opening. APPENDIX A: CHECK FOR PRESENCE OF FUEL AT THE FUEL SHROUD DRAIN VALVES (SHEET 4 OF 10) Original Issue: August 29, 2014 PROPRIETARY - Copyright © Unpublished Export Controlled ECCN: 9E991 - BOEING MD11-28A148 Work - See page 1 for details. 28 of 46 ### Page 29 (OCR) BOEING SERVICE BULLETIN MD11-28A148 ALERT ALERT CHECK MAXIMUM SERVICE- REMARKS ABLE LIMITS 18 Pressurize the fuel system for a minimum of 2 hours, and/or run the Number 2 engine for approximately 25 minutes, refer to MD-11 AMM 71-00-00. 19 Examine the bags for fuel. NOTE: If you think there is remaining fuel in the shroud system, replace bags and repeat. (a) Measure the quantity of fu- If the quantity is less than Make a record to monitor el drained from the shroud. 8.0 fluid-ounces in a 24 the leak. hour period: If the quantity is 8.0 fluid- Make repair at the next ounces to 32.0 fluid- convenient maintenance ounces in a 24 hour period: period If the leakage rate be- Do the repair at the time comes more than 32.0 flu- specified in Paragraph id-ounces in a 24 hour peri- 1.E., Compliance, for od: CONDITION 1. MARO T APPENDIX A: CHECK FOR PRESENCE OF FUEL AT THE FUEL SHROUD DRAIN VALVES (SHEET 5 OF 10) Original Issue: August 29, 2014 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished MD11-28A148 0910 DE Work - See page 1 for details. 29 of 46 ### Page 30 (OCR) BOEING SERVICE BULLETIN MD11-28A148 ALERT ALERT ВТОЙ SHROUD FUEL DRAIN 2345183 APPENDIX A: CHECK FOR PRESENCE OF FUEL AT THE FUEL SHROUD DRAIN VALVES (SHEET 6 OF 10) Original Issue: August 29, 2014 PROPRIETARY - Copyright © Unpublished Export Controlled ECCN: 9E991 - BOEING MD11-28A148 Work - See page 1 for details. 30 of 46 ### Page 31 (OCR) BOEING SERVICE BULLETIN MD11-28A148 ALERT ALERT A - - S13 CLAMP SCREW NUT WASHER - S14 - S15 -S16 - S17 A-A VIEW LOOKING DOWN HORIZONTAL TANK FUEL SHROUD CHECK DRAIN VALVE - LOCATION POST MD11-28-115 B-B APPENDIX A: CHECK FOR PRESENCE OF FUEL AT THE FUEL SHROUD DRAIN VALVES (SHEET 7 OF 10) Original Issue: August 29, 2014 PROPRIETARY - Copyright © Unpublished Export Controlled ECCN: 9E991 - BOEING Work - See page 1 for details. MD11-28A148 31 of 46 ### Page 32 (OCR) BOEING SERVICE BULLETIN MD11-28A148 ALERT ALERT OUTBD INBOARD END OF TUBE ASSY X=0.000 AIRPLANE CENTERLINE CENTER TANK FUEL SHROUD CHECK DRAIN VALVE - LOCATION POST MD11-28-115 APPENDIX A: CHECK FOR PRESENCE OF FUEL AT THE FUEL SHROUD DRAIN VALVES (SHEET 8 OF 10) Original Issue: August 29, 2014 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. ### Page 33 (OCR) BOEING SERVICE BULLETIN MD11-28A148 ALERT ALERT Xors=97.000 • Yors=0.000 OUTBD Xors=163.800 Xors=130.400 AFT LEFT WING FUEL SHROUD LOOKING DOWN CHECK DRAIN VALVE - LOCATION ROTATED 60° POST MD11-28-115 COUNTERCLOCKWISE APPENDIX A: CHECK FOR PRESENCE OF FUEL AT THE FUEL SHROUD DRAIN VALVES (SHEET 9 OF 10) Original Issue: August 29, 2014 PROPRIETARY - Copyright © Unpublished Export Controlled ECCN: 9E991 - BOEING Work - See page 1 for details. MD11-28A148 33 of 46 ### Page 34 (OCR) BOEING SERVICE BULLETIN MD11-28A148 ALERT ALERT AFT FUSELAGE FUEL SHROUD CHECK DRAIN VALVE - LOCATION POST MD11-28-115 2345515 APPENDIX A: CHECK FOR PRESENCE OF FUEL AT THE FUEL SHROUD DRAIN VALVES (SHEET 10 OF 10) Original Issue: August 29, 2014 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. ### Page 35 (OCR) BOEING SERVICE BULLETIN MD11-28A148 ALERT ALERT 1. PRESSURE TEST OF THE TAIL TANK FUEL DRAIN SHROUD SYSTEM a. Fixtures, Tools, Test and Support Equipment. NOTE: Equivalent replacements are permitted for the items that follow: REFERENCE DESIGNATION Not specified Ladder or work platform 12 ft minimum AN929-6 Cap DZZ7379-501 Tester, fuel tank and drain shroud system Not specified Dry air source, regulated 6.0 psi, minimum b. Access Panels Number Name/Location 316AB AFT FUSELAGE c. Job Set-up - Tail Tank Fuel Shroud Drain System Pressure Test (1) Open this access panel: Number Name/Location 316AB AFT FUSELAGE d. Procedure - Tail Tank Fuel Shroud Drain System Pressure Test PRE MD11-28A056 NOTE: There are two drain lines and one extended drain line on the right side of the tail tank front spar. There is one drain line on the left side of the tail tank front spar. The drain lines have check valves attached. (Sheet 5 of 9) POST MD11-28A056 NOTE: There are not two drain lines and one extended drain line on the right side at the tail-tank front spar. They are sealed with caps. The drain line on the left side is sealed with a cap. The check valves are removed. (Sheet 6 of 9) PRE MD11-28-115 NOTE: There are no check/drain valves added to the fuel shroud drain system. APPENDIX B: PRESSURE TEST OF THE TAIL TANK FUEL SHROUD DRAIN SYSTEM (SHEET 1 OF 9) Original Issue: August 29, 2014 PROPRIETARY - Copyright © Unpublished Export Controlled ECCN: 9E991 - BOEING MD11-28A148 Work - See page 1 for details. 35 of 46 ### Page 36 (OCR) BOEING SERVICE BULLETIN MD11-28A148 ALERT ALERT POST MD11-28-115 NOTE: There are check/drain valves added to the fuel shroud drain system. These check/drain valves help the personnel find the leaks quickly. PRE MD11-28A056 OR PRE MD11-28-115 (1) Do a pressure test of the tail tank fuel shroud drain system (Sheet 7 of 9) as follows: (a) In the aft fuselage, disconnect the tail tank fuel drain line (1) at the drain mast (2). (b) Disconnect the fuel drain lines (3) at the check valves (4) and install the plugs (5). (c) Connect the 0-10 psi regulated dry-air source and the manometer to the drain line (1). (d) On the forward spar of the tail tank, install a cap on the fill valve controller shroud can vent (6). CAUTION: DO NOT PRESSURIZE THE SHROUD DRAIN LINE MORE THAN 5.3 PSI. TOO MUCH PRESSURE CAN CAUSE DAMAGE TO THE SHROUD DRAIN LINE. (e) Pressurize the system to 4.5-5.0 psi. (f) Close the air supply valve and monitor the air supply gage for the shroud drain system pressure decrease. 1) The pressure decrease must not be more than 1.0 psi in 5 minutes. (g) Release the system pressure. (h) Disconnect the regulated dry-air source and the manometer from the drain line (1). (i) On the forward spar of the tail tank remove the cap from the fill valve controller shroud can vent (6). i) Remove the plugs (5) from the drain lines (3). Connect the drain lines (3) to the check valves (4). (k) Connect the fuel drain line (1) to the drain mast (2). POST MD11-28A056 OR POST MD11-28-115 (1) Do a pressure test of the tail tank fuel shroud drain system as follows: (Sheet 8 or 9 of 9) APPENDIX B: PRESSURE TEST OF THE TAIL TANK FUEL SHROUD DRAIN SYSTEM (SHEET 2 OF 9) Original Issue: August 29, 2014 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished MD11-28A148 Work - See page 1 for details. 36 of 46 ### Page 37 (OCR) BOEING SERVICE BULLETIN MD11-28A148 ALERT ALERT POST MD11-28-115 NOTE: This procedure examines only the system downstream of the check/drain valve. Additional pressure tests are necessary to examine the drains which are now isolated by the one way check/drain valve. POST MD11-28A056 OR MD11-28-115 (a) In the aft fuselage, disconnect the tail tank fuel drain line (1) at the drain mast (2). (b) Disconnect the in-line tee (3) upper fuel drain line (4) and cap the opening on the in-line tee (3). (c) Connect the 0-10 psi regulated dry-air source and the manometer to the disconnected fuel drain line (1) located near the drain mast (2). (d) On the forward spar of the tail tank, install a cap on the fill valve controller can vent (6). POST MD11-28-115 NOTE: Because of a drain/check valves, it possibly is not necessary to install the cap. POST MD11-28A056 OR MD11-28-115 CAUTION: DO NOT PRESSURIZE THE SHROUD DRAIN LINE MORE THAN 5.3 PSI. TOO MUCH PRESSURE CAN CAUSE DAMAGE TO THE SHROUD DRAIN LINE. (e) Pressurize the system to 4.5-5.0 psi. (f) Momentarily open the tail tank fuel drain valve (6) at poppet slot (7) to make sure air goes out. (g) Close the air supply valve and monitor the air supply gage for the shroud drain system pressure decrease. 1) The pressure decrease must not be more than 1.0 psi in 5 minutes. (h) Release the system pressure. (i) Push up and turn the poppet slot (7) 90 degrees to lock open. Let air flow from the tail tank fuel drain valve (6) for a 15 minutes or more to remove water. 0) Disconnect the regulated dry-air source and the manometer from the drain line (1). (k) Remove the cap on the in-line tee (3) and connect the upper drain line (4) to the opening on the in-line tee (3). (I) Remove the cap on the fill valve controller can vent (5). APPENDIX B: PRESSURE TEST OF THE TAIL TANK FUEL SHROUD DRAIN SYSTEM (SHEET 3 OF 9) Original Issue: August 29, 2014 Export Controlled ECCN: 9E991 - BOEING MD11-28A148 PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 37 of 46 ### Page 38 (OCR) BOEING SERVICE BULLETIN MD11-28A148 ALERT ALERT (m) Close the poppet slot (7). (n) Connect the fuel drain line (1) to the drain mast (2). e. Job Close-up - Tail Tank Fuel Shroud Drain System Pressure Test (1) Close this access panel: Number Name/Location 316AB AFT FUSELAGE (2) Remove all the tools and equipment from the work area. Make sure that the area is clean. PRESS LEOM HO BROARS LION TROS остреча нант звом вишивно дровка внт азіяцваляя той об котома PE 000 81097010 Balmime then of nart piom ed fon team eaten husseig ent APPENDIX B: PRESSURE TEST OF THE TAIL TANK FUEL SHROUD DRAIN SYSTEM (SHEET 4 OF 9) Original Issue: August 29, 2014 PROPRIETARY - Copyright © Unpublished Export Controlled ECCN: 9E991 - BOEING MD11-28A148 Work - See page 1 for details. 38 of 46 ### Page 39 (OCR) BOEING SERVICE BULLETIN MD11-28A148 ALERT ALERT STA STA STA STA STA Xch=-20.00 Xch=-10.00 Xch=0.00 Xch=20.00 Xch=20.00 EXTENDED DRAIN ' LINE , CLAMP CHECK VALVE CHECK DRAIN VALVE _INE DRAIN -LINE A-A (LOOKING AFT AT TAIL TANK FRONT SPAR) TAIL TANK FRONT SPAR LINE CONNECTIONS PRE MD11-28A056 APPENDIX B: PRESSURE TEST OF THE TAIL TANK FUEL SHROUD DRAIN SYSTEM (SHEET 5 OF 9) Original Issue: August 29, 2014 Export Controlled ECCN: 9E991 - BOEING MD11-28A148 PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 39 of 46 ### Page 40 (OCR) BOEING SERVICE BULLETIN MD11-28A148 ALERT ALERT STA STA STA STA STA Xch=-20.00 Xch=-10.00 Xch=0.00 Xch=20.00 Xch=20.00 CAP „CAP A-A (LOOKING AFT AT TAIL TANK FRONT SPAR) TAIL TANK FRONT SPAR LINE CONNECTIONS 2345607 POST MD11-28A056 APPENDIX B: PRESSURE TEST OF THE TAIL TANK FUEL SHROUD DRAIN SYSTEM (SHEET 6 OF 9) Original Issue: August 29, 2014 Export Controlled ECCN: 9E991 - BOEING MD11-28A148 PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 40 of 46 ### Page 41 (OCR) BOEING SERVICE BULLETIN MD11-28A148 ALERT ALERT TAIL FILL/ISOL VALVE TAIL FILL S/C SHROUD CONTROLLER CAN SHROUD CAN •TAIL TANK ALT PUMP TAIL TANK LEFT TOANSFER TAIL TANK FORWARD RIGHT SPAR OF TRANSFER TAIL TANK PUMP A-A TAIL TANK FWD TAIL TANK SHROUD SYSTEM - PRESSURE TEST PRE MD11-28A056 OR PRE MD11-28-115 APPENDIX B: PRESSURE TEST OF THE TAIL TANK FUEL SHROUD DRAIN SYSTEM (SHEET 7 OF 9) Original Issue: August 29, 2014 PROPRIETARY - Copyright © Unpublished Export Controlled ECCN: 9E991 - BOEING Work - See page 1 for details. MD11-28A148 41 of 46 ### Page 42 (OCR) BOEING SERVICE BULLETIN MD11-28A148 ALERT ALERT TAIL VALVE FILL/ISOL SHROUD CAN , INSTALL SHROUD CAN TAIL FILL S/O CONTROLLER CAP HERE TAIL TANK ALT PUMP TAIL TANK LEFT TUANSFER CHECK/DRAIN TAIL TANK VALVE A-A FORWARD RIGHT SPAR OF TRANSFER TAIL TANK PUMP TAIL B -B TANK FWD TAIL TANK SHROUD SYSTEM - PRESSURE TEST 2345547 POST MD11-28A056 OR POST MD11-28-115 APPENDIX B: PRESSURE TEST OF THE TAIL TANK FUEL SHROUD DRAIN SYSTEM (SHEET 8 OF 9) Original Issue: August 29, 2014 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. ### Page 43 (OCR) BOEING SERVICE BULLETIN MD11-28A148 ALERT ALERT TAIL FILLISOL VALVE TAIL FILL S/O SHROUD CAN INSTALL CAP HERE \ 5 SHROUD CAN CONTROLLER •TAIL TANK ALT PUMP TAIL TANK LEFT JOANSFER TAIL TANK A -A FORWARD B RIGHT SPAR OF TRANSFER TAIL TANK PUMP TAIL TANK B -B 13 a FWD TAIL TANK SHROUD SYSTEM - PRESSURE TEST POST MD11-28A056 AND PRE MD11-28-115 APPENDIX B: PRESSURE TEST OF THE TAIL TANK FUEL SHROUD DRAIN SYSTEM (SHEET 9 OF 9) Original Issue: August 29, 2014 Export Controlled ECCN: 9E991 - BOEING MD11-28A148 PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 43 of 46 ### Page 44 (OCR) BOEING SERVICE BULLETIN MD11-28A148 ALERT ALERT POST MD11-28-115 1. PRESSURE TEST OF THE AFT FUSELAGE FUEL SHROUD DRAIN SYSTEM a. References REFERENCE TITLE MD-11 AMM 28-25-06-000-802 REMOVAL OF THE FUEL SHROUD DRAIN LINE CHECK/DRAIN VALVE MD-11 AMM 28-25-06-400-802 INSTALLATION OF THE FUEL SHROUD DRAIN LINE CHECK/DRAIN VALVE b. Access Panels Number Name/Location 316AB AFT FUSELAGE c. Job Set-up Information - Aft Fuselage Fuel Shroud Drain System Pressure Test (1) Fixtures, Tools, Test and Support Equipment NOTE: Equivalent replacements are permitted for the items that follow. REFERENCE DESIGNATION Not specified Ladder or work platform 7 ft minimum Not specified Ladder or work platform 12 ft minimum DZZ7379-501 Tester, fuel tank and drain shroud system Not specified Dry air source, regulated 6.0 psi, minimum d. Job Set-up - Aft Fuselage Fuel Shroud Drain System Pressure Test (1) Open this access panel: Number Name/Location 316AB AFT FUSELAGE e. Procedure - Aft Fuselage Fuel Shroud Drain System Pressure Test (1) Pressure test the aft fuselage fuel shroud drain system (Sheet 3 of 3) as follows: APPENDIX C: PRESSURE TEST OF THE AFT FUSELAGE FUEL SHROUD DRAIN SYSTEM (SHEET 1 OF 3) Original Issue: August 29, 2014 PROPRIETARY - Copyright © Unpublished Export Controlled ECCN: 9E991 - BOEING MD11-28A148 Work - See page 1 for details. 44 of 46 ### Page 45 (OCR) BOEING SERVICE BULLETIN MD11-28A148 ALERT ALERT WARNING: MAKE SURE YOU OBEY ALL SAFETY PRECAUTIONS AND REGULATIONS DURING FUEL SYSTEM MAINTENANCE. THIS WILL PREVENT INJURY TO PERSONS AND DAMAGE TO EQUIPMENT. (a) Remove the check/drain valve (1), refer to MD-11 AMM 28-25-06-000-802. (b) Connect the drain shroud tester to the drain line (2). 1) If necessary, install a cap on the vent valve (3). (c) Connect the regulated dry air source to the drain shroud tester. CAUTION: DO NOT PRESSURIZE THE SHROUD DRAIN LINE MORE THAN 5.3 PSI. TOO MUCH PRESSURE CAN CAUSE DAMAGE TO THE SHROUD DRAIN LINE. (d) Pressurize the system to 4.5-5.0 psi. (e) Close the air supply valve and monitor the air supply gage for the shroud drain system pressure decrease. 1) The pressure decrease must not be more than 1.0 psi in 5 minutes. (f) Release the system pressure. (g) Disconnect the regulated dry-air source from the drain shroud tester. (h) Disconnect the drain shroud tester from the drain line (2). 1) If installed, remove the cap from the vent valve (3). (i) Install the check/drain valve (1), refer to MD-11 AMM 28-25-06-400-802. f. Job Close-up - Aft Fuselage Fuel Shroud Drain System Pressure Test (1) Close this access panel: Number Name/Location 316AB AFT FUSELAGE (2) Remove all the tools and equipment from the work area. Make sure that the area is clean. APPENDIX C: PRESSURE TEST OF THE AFT FUSELAGE FUEL SHROUD DRAIN SYSTEM (SHEET 2 OF 3) Original Issue: August 29, 2014 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. MD11-28A148 45 of 46 ### Page 46 (OCR) BOEING SERVICE BULLETIN MD11-28A148 ALERT ALERT 80 DOY BRUS SHAM MIAM METEYE 1BUR luper art loanno Tal 2 B NUT FWD AFT FUSELAGE FUEL SHROUD DRAIN SYSTEM - PRESSURE TEST 2345608 POST MD11-28-115 APPENDIX C: PRESSURE TEST OF THE AFT FUSELAGE FUEL SHROUD DRAIN SYSTEM (SHEET 3 OF 3) Original Issue: August 29, 2014 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 46 of 46 --- OpenAirDocs.org is an independent research project of [Contrail Labs](https://contraillabs.com/). It is not affiliated with the FAA or the NTSB. Source documents are U.S. government works in the public domain, except the copies of manufacturers’ service documents, which belong to their rights holders.