Number: MD11-28A148 

Original Issue: August 29, 2014 

AT A System: 2825 

Commercial 

Airplanes 

ALERT 

MD11 

Service Bulletin 

SUBJECT: FUEL- Shroud Fuel Drain (All) - Pressure Check/lnspecVRepair Fuel Line Shrouds 

Export of this technology is controlled under the United States Export Administration Regulations (EAR) (15 

CFR 300-77 4 ). 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Unpublished Work.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 

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Table of Contents 

Summary ................................. . ................. . .. 5 

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 . . . . . . . . . . . . . . . . . . . . . . . . 13 

G. Manpower . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13 

H. Weight and Balance Changes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14 

I. Electrical Load Data . 14 

J. 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 lntermixability 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 

E. Special Tooling- Price and Availability ....... . . 

F. Special Tooling Necessary to do this Service Bulletin . 

3. ACCOMPLISHMENT INSTRUCTIONS . . . . . . . . . ... 

18 

18 

19 

A. 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 

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MD11-28A148 

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rti-IIIIEIND 

Number: MD11-28A148 

Original Issue: August 29, 2014 

AT A System: 2825 

Commercial 

Airplanes 

ALERT 

MD11 

Service Bulletin 

Summary 

SUBJECT: FUEL- Shroud Fuel Drain (All)- Pressure CheckllnspecURepair Fuel Line Shrouds 

THIS BULLETIN IS SENT TO THE OPERA TORS 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 1.1., 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 Airplane Flight Manual) 

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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-11 F 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. 

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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. 

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ALERT 

PRESSURE 

CHECK/INSPECT/REPAIR 

FUEL LINE SHROUDS 

MD11-28A148 

8 of46 
rti-IIIIEING 

Number: MD11-28A148 

Original Issue: August 29, 2014 

AT A System: 2825 

Commercial 

Airplanes 

ALERT 

MD11 

Service Bulletin 

SUBJECT: FUEL- Shroud Fuel Drain (All)- Pressure Check/Inspect/Repair Fuel Line Shrouds 

THIS BULLETIN IS SENT TO THE OPERA TORS 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 -

Airplane Models: 

MD-11 , MD-11F 

Original Issue: August 29, 2014 

MD-11 and MD-11 F Airplanes. 

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 

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Fuselage Num- Group 

ber 

530- 539 1 

540-549 1 

550-559 1 

560-569 1 

570-579 1 

580-589 1 

590- 599 1 

600-609 1 

610- 619 1 

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: 

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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-11 F 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. 

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BOEING SERVICE BULLETIN MD11-28A148 

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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 bulletin. (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 qui red. 

Frequency Eddy Current 

Inspection or Pressure 

Test 

CONDITION 3: Crack(s) Repair crack(s). Before further flight. - Found by High Frequency Eddy Current lnspection or Pressure Test 

(a) When a pressure test of the fuel shroud drain system is performed, it can be used as an acceptable 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. 

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Option 2 - Table 2 - Check Fuel Shroud Drain Valyes 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 bulAft 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 approved 

airplanes listed in the service bulletin effectivity. This service bulletin and Its approval were based on 

the airplane in its original Boeing delivery configuration or as modified by other approved Boeing 

changes. 

If an airplane has a non-Boeing modification or repair that affects a component or system also affected 

by this service bulletin, the operator is responsible for obtaining appropriate regulatory agency approval 

before incorporating this service bulletin. 

G. Manpower 

The table below shows an estimate of the task hours necessary to do this 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 

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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 1.0 1.0 

Pressure test fuel shroud 2.0 2.0 

Close Access 1 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 

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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 OTis are not necessary. 

L. Interchangeability and lntermixability of Parts 

Accomplishment of this service bulletin does not affect interchangeability or intermixability of parts. 

M. Software Accomplishment Summary 

Not affected. 

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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 I Specification QTY Name Notes 

(OPM 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: 60892 

Option 1 and 2- Crack(s) Found· 

Part Number I Specification QTY Name Notes 

PR-1422 B-2 Sealant As Required Compound - Sealing, Integral (a) 

(OMS 2082) Fuel Tanks and Fuel Cell Cavior ties 

Equivalent 

515X347 Base with 910X527 As Required Primer, Fluid Resistant (a) 

Catalyst 

(OMS 1786) 

or 

Equivalent 

SkyKieen 1 000 

(OPM 6410) 

or 

Equivalent 

(OMS 1820 T1A2) 

or 

Equivalent 

Original Issue: August 29, 2014 

As Required Solvent, Sealant Remover 

As Required Wipers- Cleaning, Cotton, 

White 

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(b) 

(c) 

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Part Number I 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: 60892 

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. 

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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: 

Original Issue: August 29, 2014 

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 . 

Export Controlled ECCN: 9E991 - BOEING 

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MD11 -28A148 

19 of 46 
ALERT 

BOEING SERVICE BULLETIN MD11-28A148 

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. 

7. 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. 

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MD11 -28A148 

20 of 46 
ALERT 

BOEING SERVICE BULLETIN MD11-28A148 

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. 

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MD1 1-28A148 

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ALERT 

BOEING SERVICE BULLETIN MD11-28A148 

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. 

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MD11-28A148 

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ALERT 

BOEING SERVICE BULLETIN MD11-28A 148 

STA 

1761.000 

I 

STA 

1781 .000 

I 

I 

I 

STA 

1801 .000 

I 

I 

I 

STA 

1821 .000 

I 

I 

I 

ALERT 

FIGURE 1: CENTER CARGO COMPARTMENT LEFT TUNNEL - FUEL LINE SHROUDS - INSPECTION 

(SHEET 1 OF 2) 

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MD11-28A148 

23 of 46 
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) 

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MD11 -28A 148 

24 of 46 
BOEING SERVICE BULLETIN MD1 1-28A148 

ALERT ALERT 

1. CHECK FOR PRESENCE OF FUEL AT THE FUEL SHROUD DRAIN VALVES 

a. 

b. 

c. 

References 

REFERENCE TITLE 

MD-11 AMM 71-00-00 POWER PLANT 

Tools/Equipment 

DESCRIPTION SPECIFICATION 

Container - 1 Quart, Calibrated -

Consumable Materials 

N.Qif_;_ 

Equivalent replacements are permitted for the items that follow. 

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 necessary 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 I Put a 1 Quart calibrated container below the applicable drain valve (1 ). (Sheet 6 of 

1 0) 

APPENDIX A: CHECK FOR PRESENCE OF FUEL AT THE FUEL SHROUD DRAIN VALVES 

(SHEET 1 OF 1 0) 

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MD11-28A148 

25 of 46 
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. 

3 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: 

(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. 

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 1 0) 

5 Put a screwdriver in the poppet slot and push approximately 0.30 inches. Drain the 

fuel. into the container. 

6 When the fuel stops, release the poppet. 

APPENDIX A: CHECK FOR PRESENCE OF FUEL AT THE FUEL SHROUD DRAIN VALVES 

(SHEET 2 OF 1 0) 

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MD11-28A148 

26 of 46 
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 

od: CONDITION 1. 

(d) A quantity of fuel is detect- There is a leak in the sysed 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 1 0), 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 

fuel 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 period: 

(d) A quantity of fuel is detect- There is a leak in the sysed 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 1 0), 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 1 0) 

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MD1 1-28A 148 

27 of 46 
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 sysed 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 1 0), 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 period: 

{d) A quantity of fuel is detect- There is a leak in the sysed 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 1 0) 

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MD11-28A148 

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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-1 1 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 offu- 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. 

APPENDIX A: CHECK FOR PRESENCE OF FUEL AT THE FUEL SHROUD DRAIN VALVES 

(SHEET 5 OF 1 0) 

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MD11-28A148 

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BOEING SERVICE BULLETIN MD11-28A148 

ALERT ALERT 

SHROUD FUEL DRAIN 

APPENDIX A: CHECK FOR PRESENCE OF FUEL AT THE FU,EL SHROUD DRAIN VALVES 

(SHEET 6 OF 10) 

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MD11 -28A148 

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ALERT 

BOEING SERVICE BULLETIN MD11-28A148 

A-A 

VIEW LOOKING DOWN 

2 

HORIZONTAL TANK FUEL SHROUD 

CHECK DRAIN VALVE - LOCATION 

POSTMD11-28·115 

ALERT 

S13 

B-B 

APPENDIX A: CHECK FOR PRESENCE OF FUEL AT THE FUEL SHROUD DRAIN VALVES 

(SHEET 7 OF 1 0) 

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ALERT 

BOEING SERVICE BULLETIN MD11-28A148 

I 

INBOARD 

END OF 

TUBE 

ASSY I 

X=O.OOO 

AIRPLANE 

CENTERLINE 

CENTER TANK FUEL SHROUD 

CHECK DRAIN VALVE - LOCATION 

POST MD11-28-115 

ALERT 

APPENDIX A: CHECK FOR PRESENCE OF FUEL AT THE FUEL SHROUD DRAIN VALVES 

(SHEET 8 OF 1 0) 

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BOEING SERVICE BULLETIN MD11 -28A148 

ALERT 

I 

I 

I 

I 

I 

____________ L__ ___________ _ I 

I 

I 

I 

AFT LEFT WING FUEL SHROUD 

CHECK DRAIN VALVE - LOCATION 

POST MD11 -28-115 

Xors= 130.400 

LOOKING DOWN 

ROTATED60° 

COUNTERCLOCKWISE 

ALERT 

APPENDIX A: CHECK FOR PRESENCE OF FUEL AT THE FUEL SHROUD DRAIN VALVES 

(SHEET 9 OF 1 0) 

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ALERT 

BOEING SERVICE BULLETIN MD11-28A148 

AFT FUSELAGE FUEL SHROUD 

CHECK DRAIN VALVE- LOCATION 

POST MD11-28-115 

ALERT 

APPENDIX A: CHECK FOR PRESENCE OF FUEL AT THE FUEL SHROUD DRAIN VALVES 

(SHEET 10 OF 10) 

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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. 

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) 

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ALERT 

BOEING SERVICE BULLETIN MD11-28A148 

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). 

(j) 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) 

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ALERT 

BOEING SERVICE BULLETIN MD11-28A148 

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. 

U) 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) 

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ALERT 

BOEING SERVICE BULLETIN MD11-28A148 

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. 

APPENDIX B: PRESSURE TEST OF THE TAIL TANK FUEL SHROUD DRAIN SYSTEM 

(SHEET 4 OF 9) 

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ALERT 

CHECK 

VALVE 

DRAIN 

LINE 

STA 

Xch=-20.00 

BOEING SERVICE BULLETIN MD11-28A148 

STA 

Xch=-1 0.00 

STA 

Xch=O.OO 

STA 

Xch=20.00 

STA 

Xch=20.00 

ALERT 

CLAMP 

ti I I k ~~ 

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 

PROPRIETARY- Copyright C> Unpublished 

Work - See page 1 for details. 

MD11-28A148 

39 of 46 
ALERT 

STA 

Xch=-20.00 

BOEING SERVICE BULLETIN MD11-28A148 

STA 

Xch=-10.00 

STA 

Xch=O.OO 

STA 

Xch=20.00 

STA 

Xch=20.00 

-----, 

~ 

~· 

A-A 

(LOOKING AFT AT TAIL TANK FRONT SPAR) 

TAIL TANK FRONT SPAR LINE CONNECTIONS 

POST MD11-28A056 

APPENDIX B: PRESSURE TEST OF THE TAIL TANK FUEL SHROUD DRAIN SYSTEM 

(SHEET 6 OF 9) 

ALERT 

CAP 

Original Issue: August 29, 2014 

Export Controlled ECCN: 9E991 - BOEING 

PROPRIETARY- Copyright IC) Unpublished 

Work - See page 1 for details. 

MD11-28A148 

40 of 46 
BOEING SERVICE BULLETIN MD11-28A148 

ALERT 

5v · 

TAIL 

FILU ISOL 

VALVE 

SHROUD 

CAN 

L _____ J 

I 

3/f! 

A-A 

6 

FORWARD 

SPAR OF 

TAIL TANK 

TAIL TANK SHROUD SYSTEM- PRESSURE TEST 

PRE MD11-28A056 OR PRE MD11-28-115 

ALERT 

APPENDIX B: PRESSURE TEST OF THE TAIL TANK FUEL SHROUD DRAIN SYSTEM 

(SHEET 7 OF 9) 

Original Issue: August 29, 2014 

Export Controlled ECCN: 9E991 -BOEING 

PROPRIETARY - Copyrig ~ Unpublished 

Work - See page 1 for details. 

MD11-28A148 

41 of 46 
ALERT 

TAIL 

FILUISOL 

VALVE 

SHROUD 

CAN 

TAIL TANK 

RIGHT 

TRANSFER 

PUMP 

BOEING SERVICE BULLETIN MD11-28A148 

INSTALL 

CAP HERE 

A-A 

4 

3 

8-8 

5 

TAIL FILL S/0 

CONTROLLER 

SHROUD CAN 

FORWARD 

SPAR OF 

TAIL TANK 

r--------, I 

0 0 lQJ----l_ l 

TAIL TANK SHROUD SYSTEM - PRESSURE TEST 

POST MD11·28A056 OR POST MD11·28-115 

TAIL 

TANK 

ALT 

PUMP 

TAIL TANK 

LEFT 

TRANSFER 

PUMP 

ALERT 

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 C Unpublished 

Work • See page 1 for details. 

MD11-28A148 

42 of 46 
BOEING SERVICE BULLETIN MD11-28A148 

ALERT 

TAIL 

FILU ISOL 

VALVE 

SHROUD 

CAN 

TAIL TANK 

RIGHT 

TRANSFER 

PUMP 

INSTALL 

CAP HERE 

A-A 

4 

3 

8-B 

5 

FORWARD 

SPAR OF 

TAIL TANK 

TAIL TANK SHROUD SYSTEM - PRESSURE TEST 

POST MD11-28A056 AND PRE MD11-28-115 

r---- l I 

0 0 lQN__ I 

TAIL 

TANK 

ALT 

PUMP 

TAIL TANK 

LEFT 

TRANSFER 

PUMP 

ALERT 

APPENDIX B: PRESSURE TEST OF THE TAIL TANK FUEL SHROUD DRAIN SYSTEM 

(SHEET 9 OF 9) 

Original Issue: August 29, 2014 

Export Controlled ECCN: gEgg1 -BOEING 

PROPRIETARY - Copyright @ Unpublished 

Work - See page 1 ror details. 

MD11-28A148 

43 of 46 
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 

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 12ft 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 

Export Controlled ECCN: 9E991 -BOEING 

PROPRIETARY- Copyright C Unpublished 

Work - See page 1 for details. 

MD11-28A148 

44 of46 
ALERT 

BOEING SERVICE BULLETIN MD11-28A148 

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 C> Unpublished 

Work - See page 1 for details. 

MD11-28A148 

45 of 46 
ALERT 

BOEING SERVICE BULLETIN MD11-28A148 

AFT FUSELAGE FUEL SHROUD DRAIN 

SYSTEM - PRESSURE TEST 

POST MD11-28-115 

3 

ALERT 

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 C Unpublished 

Work - See page 1 for details. 

MD11-28A148 

46 of 46