# 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: FAA-2015-3637_SB-MD11-28A148-Rev 01
- Pages: 39
- PDF: https://openairdocs.org/files/sha256/ab/be/abbe2af610fd60bfd5247f9893c95314b573a08704abbb1f1538d293d753284c
- Page: https://openairdocs.org/service-documents/boeing/md11-28a148/file/abbe2af610fd

## Text

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### Page 1

Commercial 
Airplanes
MD11
Service Bulletin
ALERT
Number: MD11-28A148
Original Issue: August 29, 2014
Revision 1: March 24, 2017
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.
9E991ECCN:
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Unpublished Work.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
MD11-28A148Revision 1: March 24, 2017
1 of 39
3.0

### Page 2

Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: August 29, 2014
MD11-28A148Revision 1: March 24, 2017
2 of 39
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ALERTALERT
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### Page 3

Table of Contents
Revision Transmittal Sheet . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5
Summary . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7
1. PLANNING INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11
A. Effectivity . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11
1. Airplanes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11
2. Spares Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 12
B. Concurrent Requirements . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 12
C. Reason . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 12
D. Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13
E. Compliance . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14
F. Approval . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 16
G. Manpower . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 16
H. Weight and Balance Changes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17
I. Electrical Load Data . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17
J. References . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17
1. Existing Data: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17
2. Data Supplied with this Service Bulletin: . . . . . . . . . . . . . . . . . . . . . . . . . . . 17
3. Installation Drawings Used in the Preparation of this Service Bulletin: . . . . . . . . . . . 17
K. Publications Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 18
L. Interchangeability and Intermixability of Parts . . . . . . . . . . . . . . . . . . . . . . . . . . . 18
M. Software Accomplishment Summary . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 18
2. MATERIAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19
A. Material - Price and Availability . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19
B. Industry Support Information . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19
C. Parts Necessary for Each Airplane . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19
1. Kits/Parts . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19
2. Parts and Materials Supplied by the Operator . . . . . . . . . . . . . . . . . . . . . . . . 19
3. Parts Modified and Reidentified . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20
4. Parts Removed and Not Replaced . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20
D. Parts Necessary to Change Spares . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20
E. Special Tooling - Price and Availability . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20
F. Special Tooling Necessary to do this Service Bulletin . . . . . . . . . . . . . . . . . . . . . . . 20
3. ACCOMPLISHMENT INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21
A. GENERAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21
B. WORK INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 23
FIGURE 1: CENTER CARGO COMPARTMENT LEFT TUNNEL - FUEL LINE SHROUDS - INSPECTION
. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25
APPENDIX A: CHECK FOR PRESENCE OF FUEL AT THE FUEL SHROUD DRAIN VALVES . . . . . . 27
APPENDIX B: PRESSURE TEST OF THE TAIL TANK FUEL SHROUD DRAIN SYSTEM . . . . . . . . 30
APPENDIX C: PRESSURE TEST OF THE ENGINE NUMBER 2 FUEL SHROUD DRAIN SYSTEM . . . 35
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: August 29, 2014
MD11-28A148Revision 1: March 24, 2017
3 of 39
BOEING SERVICE BULLETIN MD11-28A148
ALERTALERT

### Page 4

Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: August 29, 2014
MD11-28A148Revision 1: March 24, 2017
4 of 39
BOEING SERVICE BULLETIN MD11-28A148
ALERTALERT
BLANK PAGE

### Page 5

Commercial 
Airplanes
MD11
Service Bulletin
ALERT
Revision Transmittal SheetNumber: MD11-28A148Original Issue: August 29, 2014
Revision 1: March 24, 2017
ATA System: 2825
SUBJECT: FUEL - Shroud Fuel Drain (All) - Pressure Check/Inspect/Repair Fuel Line Shrouds
This revision includes all pages of the service bulletin.
COMPLIANCE INFORMATION RELATED TO THIS REVISION
Federal Aviation Administration (FAA) Notice of Proposed Rule Making NPRM 2014-NM-219-AD, is related to
this service bulletin.
Effects of this Revision on airplanes on which original issue was previously done:
None.
REASON FOR REVISION
This revision is sent to standardize and simplify the fuel shroud drain line test procedures for the MD-11 and
MD-11F airplanes in this service bulletin effectivity. The appendices in this service bulletin, which are used to
do the tests, have now been changed. The service bulletin also adds reference to FAA Notice of Proposed Rule
Making NPRM 2014-NM-219-AD and makes some minor format changes throughout the service bulletin.
These sections were changed:
1. In Summary BACKGROUND: Removed the Maintenance Planning Document (MPD) reference for the
fuel shroud drain test.
2. In Summary ACTION: Added new notes, changed the option titles, and clarified the test requirements.
3. In Summary COMPLIANCE: Added reference to Notice of Proposed Rule Making NPRM
2014-NM-219-AD.
4. In Paragraph 1.C., Reason, removed the Maintenance Planning Document (MPD) reference for the
fuel shroud drain test, and added Revision 1 data.
5. In Paragraph 1.D., Description, added new notes, changed the option titles and maintenance zones,
and clarified the test requirements.
6. In Paragraph 1.E., Compliance, added reference to Notice of Proposed Rule Making NPRM
2014-NM-219-AD, changed table titles, format and text within the action column. Renumbered and
changed the Conditions, Compliance Time and footnote for the Option 1 table.
Export Controlled ECCN: 9E991 - BOEING
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Original Issue: August 29, 2014
MD11-28A148Revision 1: March 24, 2017
5 of 39

### Page 6

7. In Paragraph 1.G., Manpower, changed table format, and task hours. Also changed text within the
Task column.
8. In Paragraph 1.J., References, updated.
9. In Paragraph 2.C., Material Information, changed the materials and updated the tables.
10. In Paragraph 3.A., General Information, added a Detailed Inspection note.
11. In Paragraph 3.B., Work Instructions updated to agree with the Compliance tables.
12. FIGURE 1: Added a footnote to the step table, and added text to the illustration.
13. Appendix A: Updated an illustration, and changed and updated procedures. Removed illustrations that
are no longer required.
14. Appendix B: Added new data and test procedures.
15. Appendix C: Added new data and test procedures.
Vertical lines are put on the left edge of each page, except in Paragraph 1.A., Effectivity and format changes,
to show the location of all content changes.
Pages with no vertical lines have no changes.
REVISION HISTORY
August 29, 2014Original Issue:
March 24, 2017Revision 1:
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: August 29, 2014
MD11-28A148Revision 1: March 24, 2017
6 of 39
BOEING SERVICE BULLETIN MD11-28A148
ALERTALERT

### Page 7

Commercial 
Airplanes
MD11
Service Bulletin
ALERT
SummaryNumber: MD11-28A148Original Issue: August 29, 2014
Revision 1: March 24, 2017
ATA System: 2825
SUBJECT: FUEL - Shroud Fuel Drain (All) - Pressure Check/Inspect/Repair Fuel Line Shrouds
THIS DOCUMENT 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 DOCUMENT
TO THE NEW OPERATOR. IF APPLICABLE SPARES HAVE BEEN SOLD, SEND THIS DOCUMENT 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. Increasing the frequency of the fuel shroud
system drain checks and adding a high frequency 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.
ReferenceAffectedPlanning Data
Paragraph 1.A.2., Spares AffectedNoSpares Affected
Paragraph 1.E., Compliance and Paragraph
1.F., Approval
YesAD Related
Paragraph 1.H., Weight and Balance ChangesNoWeight and Balance Change
Paragraph 1.I., Electrical Load DataNoElectrical Load Changed
Paragraph 1.K., Publications AffectedYesPublications Affected
Paragraph 1.K., Publications AffectedNoAirplane Flight Operations Affected (Flight Crew
Operations Manual and/or FAA Approved Air-
plane Flight Manual)
Paragraph 2.C.1., Kits/PartsNoKits/Parts Required
Export Controlled ECCN: 9E991 - BOEING
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Original Issue: August 29, 2014
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7 of 39

### Page 8

ReferenceAffectedPlanning Data
Paragraph 2.C.2., Parts and Materials Supplied
by the Operator
YesOperator Supplied Parts/Material
Paragraph 2.F., Special Tooling Necessary to
do this Service Bulletin
YesSpecial Tooling Required
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: FUEL SHROUD DRAIN VALVES CHECK FOR PRESENCE OF FUEL, PRESSURE CHECK
FUEL LINE SHROUDS, AND FUEL LINE SHROUDS HIGH FREQUENCY EDDY CURRENT INSPECTION
1. Do the following:
NOTE: The Option 2 Fuel Shroud Drain System Pressure test can be used as an acceptable alternative
test for the Option 1 High Frequency Eddy Current (HFEC) Inspection.
NOTE: If a tail tank transfer or engine number 2 fuel shroud line has been repaired in accordance
with MD-11 Structural Repair Manual (SRM) 53-00-01, Repair 3, only Option 2 can be used
for checking the fuel shroud line for leaks.
a. Check for presence of fuel at the fuel shroud drain valves and do maintenance/repairs based on
condition found.
b. Do a HFEC Inspection of the engine number 2 feed and tail tank transfer fuel line shrouds and do
action based on condition found.
c. Pressure Test the Aft Fuselage Tail Tank Fuel Shroud Drain System and do maintenance/repairs
based on condition found.
d. Pressure Test the Engine Number 2 Fuel Shroud Drain System and do maintenance/repairs based
on condition found.
e. Continue with repetitive tests/inspections described in Paragraph 1.E., Compliance, Table 1.
OPTION 2: FUEL SHROUD DRAIN VALVES CHECK FOR PRESENCE OF FUEL, AND FUEL LINE
SHROUD DRAIN SYSTEM PRESSURE TEST
1. Do the following:
NOTE: The Option 1 HFEC Inspection cannot be used as an alternative test for the Option 2 Fuel
Shroud Pressure Test.
a. Check for presence of fuel at the fuel shroud drain valves and do maintenance/repairs based on
condition found.
b. Pressure Test the Aft Fuselage Tail Tank Fuel Shroud Drain System and do maintenance/repairs
based on condition found.
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: August 29, 2014
MD11-28A148Revision 1: March 24, 2017
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BOEING SERVICE BULLETIN MD11-28A148
ALERTALERT

### Page 9

c. Pressure Test the Engine Number 2 Fuel Shroud Drain System and do maintenance/repairs based
on condition found.
d. 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
Federal Aviation Administration (FAA) Notice of Proposed Rule Making NPRM 2014-NM-219-AD, is related to
this service bulletin.
Refer to Paragraph 1.E., Compliance.
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.
Export Controlled ECCN: 9E991 - BOEING
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Work - See page 1 for details.
Original Issue: August 29, 2014
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BOEING SERVICE BULLETIN MD11-28A148
ALERTALERT

### Page 10 (OCR)

BOEING SERVICE BULLETIN MD11-28A148
ALERT  ALERT
PRESSURE
CHECK/INSPECT/REPAIR
FUEL LINE SHROUDS
200  ....
2323667
Original Issue: August 29, 2014
Revision 1: March 24, 2017  PROPRIETARY - Copyright © Unpublished  Export Controlled ECCN: 9E991 - BOEING  MD11-28A148
Work - See page 1 for details.  10 of 39

### Page 11

Commercial 
Airplanes
MD11
Service Bulletin
ALERT
Number: MD11-28A148
Original Issue: August 29, 2014
Revision 1: March 24, 2017
ATA System: 2825
SUBJECT: FUEL - Shroud Fuel Drain (All) - Pressure Check/Inspect/Repair Fuel Line Shrouds
THIS DOCUMENT 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 DOCUMENT
TO THE NEW OPERATOR. IF APPLICABLE SPARES HAVE BEEN SOLD, SEND THIS DOCUMENT TO THE
NEW OWNER.
1.    PLANNING INFORMATION
A. Effectivity
1. Airplanes
This service bulletin is for the airplanes shown below.
DESCRIPTIONCONFIGURATIONGROUP
MD-11 and MD-11F Airplanes.-1
Airplane Models:
MD-11, MD-11F
GroupFuselage Num-
ber
1447 - 449
1450 - 459
1460 - 469
1470 - 479
1480 - 489
1490 - 499
1500 - 509
1510 - 519
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PROPRIETARY - Copyright © Unpublished
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Original Issue: August 29, 2014
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### Page 12

GroupFuselage Num-
ber
1520 - 529
1530 - 539
1540 - 549
1550 - 559
1560 - 569
1570 - 579
1580 - 589
1590 - 599
1600 - 609
1610 - 619
1620 - 629
1630 - 639
1640 - 646
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. Increasing
the frequency of the fuel shroud system drain checks and adding a high frequency 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.
Revision 1 is sent to standardize and simplify the fuel shroud drain line test procedures for the MD11
and MD11F airplanes in this service bulletin effectivity. The appendices in this service bulletin, which
used to do these tests, have now been changed. The service bulletin also adds reference to FAA Notice
of Proposed Rule Making NPRM 2014-NM-219-AD and makes some minor format changes throughout
the service bulletin.
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: August 29, 2014
MD11-28A148Revision 1: March 24, 2017
12 of 39
BOEING SERVICE BULLETIN MD11-28A148
ALERTALERT

### Page 13

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: FUEL SHROUD DRAIN VALVES CHECK FOR PRESENCE OF FUEL, PRESSURE
CHECK FUEL LINE SHROUDS, AND FUEL LINE SHROUDS HIGH FREQUENCY EDDY CURRENT
INSPECTION
1. Do the following:
NOTE: The Option 2 Fuel Shroud Pressure test can be used as an acceptable alternative test
for the Option 1 High Frequency Eddy Current (HFEC) Inspection.
NOTE: If a tail tank transfer or engine number 2 fuel shroud line has been repaired in accordance
with MD-11 Structural Repair Manual (SRM) 53-00-01, Repair 3, or equivalent repair,
only Option 2 can be used for checking the fuel shroud line for leaks.
a. Check for presence of fuel at the fuel shroud drain valves and do maintenance/repairs based
on condition found.
b. Do a HFEC Inspection of the engine feed and tail tank transfer fuel line shrouds and do action
based on condition found.
c. Pressure Test the Aft Fuselage Tail Tank Fuel Shroud Drain System and do
maintenance/repairs based on condition found.
d. Pressure Test the Engine Number 2 Fuel Shroud Drain System and do maintenance/repairs
based on condition found.
e. Continue with repetitive tests/inspections described in Paragraph 1.E., Compliance, Table 1.
OPTION 2: FUEL SHROUD DRAIN VALVES CHECK FOR PRESENCE OF FUEL, AND FUEL LINE
SHROUD DRAIN SYSTEM PRESSURE TEST
1. Do the following:
NOTE: The Option 1 High Frequency Eddy Current Inspection cannot be used as an alternative
test for the Option 2 Fuel Shroud Pressure Test.
a. Check for presence of fuel at the fuel shroud drain valves and do maintenance/repairs based
on condition found.
b. Pressure Test the Aft Fuselage Tail Tank Fuel Shroud Drain System and do
maintenance/repairs based on condition found.
c. Pressure Test the Engine Number 2 Fuel Shroud Drain System and do maintenance/repairs
based on condition found.
d. Continue with repetitive tests/inspections described in Paragraph 1.E., Compliance, Table 2.
Effects of Revision 1 on airplanes on which the original issue was previously done:
Export Controlled ECCN: 9E991 - BOEING
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Original Issue: August 29, 2014
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ALERTALERT

### Page 14

None.
The work in this service bulletin is done in the maintenance zone(s) given below.
Affected Maintenance Zones
ZoneModel
181, 311MD-11, MD-11F
E. Compliance
Federal Aviation Administration (FAA) Notice of Proposed Rule Making NPRM 2014-NM-219-AD, is
related to this service bulletin.
Do the required actions in accordance with Paragraph 3. Accomplishment Instructions.
Select one of the following Compliance Tables:
Table 1 - Option 1 - FUEL SHROUD DRAIN VALVES CHECK FOR PRESENCE OF FUEL, PRES-
SURE CHECK FUEL LINE SHROUDS, AND FUEL LINE SHROUDS HIGH FREQUENCY EDDY
CURRENT INSPECTION
Repeat Interval
(Whichever Occurs
First)
Compliance Time
(Whichever Occurs
First)
ActionCondition
10 days.Within 6 months after
the original issue date of
this service bulletin.
Check Fuel Shroud
Drain Valves for Pres-
ence of Fuel.
All Airplanes.
7,500 flight hours. (a)Within 7,500 flight hours
from the original issue
date of this service bul-
letin. (a)
Do High Frequency Ed-
dy Current Inspection of
fuel line shrouds.
15,000 flight hours. (a)Within 15,000 flight
hours from the original
issue date of this service
bulletin. (a)
Pressure Test of the Tail
Tank Fuel Shroud Drain
System and the Aft
Fuselage Fuel Shroud
Drain System.
-Before further flight.Repair leak(s).CONDITION 1: Leakage
rate becomes more than
32.0 fluid-ounces in a 24
hour period
--No further action re-
quired.
CONDITION 2: No
Crack(s) or Leaks(s)
Found by High Frequen-
cy Eddy Current Inspec-
tion or Pressure Test
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### Page 15

Table 1 - Option 1 - FUEL SHROUD DRAIN VALVES CHECK FOR PRESENCE OF FUEL, PRES-
SURE CHECK FUEL LINE SHROUDS, AND FUEL LINE SHROUDS HIGH FREQUENCY EDDY
CURRENT INSPECTION
Repeat Interval
(Whichever Occurs
First)
Compliance Time
(Whichever Occurs
First)
ActionCondition
-Before further flight.Repair leaks(s) or
crack(s) and pressure
test the Tail Tank Fuel
Shroud Drain System or
the Aft Fuselage and
Engine Number 2 Fuel
Shroud Drain System.
CONDITION 3: Any
Crack(s) or Leak(s)
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 alternative method to the eddy current inspection provided the next eddy current inspection
is done within 7,500 flight hour interval. However, performing an eddy current inspection cannot
be used as an acceptable alternative method for the pressure test of the fuel shroud drain system.
Table 2 - Option 2 FUEL SHROUD DRAIN VALVES CHECK FOR PRESENCE OF FUEL, AND FUEL
LINE SHROUD DRAIN SYSTEM PRESSURE TEST
Repeat Interval
(Whichever Occurs
First)
Compliance Time
(Whichever Occurs
First)
ActionCondition
10 days.Within 6 months after
the original issue date of
this service bulletin.
Check Fuel Shroud
Drain Valves for Pres-
ence of Fuel.
All Airplanes.
7,500 flight hours.Within 7,500 flight hours
from the original issue
date of this service bul-
letin.
Pressure Test of the Tail
Tank Fuel Shroud Drain
System and the Aft
Fuselage and Engine
Number 2 Fuel Shroud
Drain System.
-Before further flight.Repair leak(s).CONDITION 4: Leakage
rate becomes more than
32.0 fluid-ounces in a 24
hour period
--No further action re-
quired.
CONDITION 5: No
Leak(s) Found by Pres-
sure Test
-Before further flight.Repair leak(s) or
crack(s), and pressure
test the Tail Tank Fuel
Shroud Drain System or
the Aft Fuselage and
Engine Number 2 Fuel
Shroud Drain System.
CONDITION 6: Pres-
sure decrease is more
than 1.0 PSI in 5 min-
utes
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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
• Time to find the tools.
Option 1 - FUEL SHROUD DRAIN VALVES CHECK FOR PRESENCE OF FUEL, PRESSURE CHECK
FUEL LINE SHROUDS, AND FUEL LINE SHROUDS HIGH FREQUENCY EDDY CURRENT INSPEC-
TION
Elapsed HoursTask HoursNumber of PersonsTask
0.50.51Open Access
1.01.01Fuel Shroud Drain Valve Check
(APPENDIX A)
4.04.01High Frequency Eddy Current In-
spection FIGURE 1
3.53.51Pressure Test of the Aft Fuselage
Tail Tank and Engine Number 2
Fuel Shroud Drain System (AP-
PENDIX B and APPENDIX C)
0.50.51Close Access
9.5 (a)9.5 (a)TOTAL FOR EACH AIRPLANE
(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.
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Option 2 - FUEL SHROUD DRAIN VALVES CHECK FOR PRESENCE OF FUEL, AND FUEL LINE
SHROUD DRAIN SYSTEM PRESSURE TEST
Elapsed HoursTask HoursNumber of PersonsTask
0.50.51Open Access
1.01.01Fuel Shroud Drain Valve Check
(APPENDIX A)
3.53.51Pressure Test of the Aft Fuselage
Tail Tank and Engine Number 2
Fuel Shroud Drain System (AP-
PENDIX B and APPENDIX C)
0.50.51Close Access
5.5 (a)5.5 (a)TOTAL FOR EACH AIRPLANE
(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. Federal Aviation Administration (FAA) Notice of Proposed Rule Making (NPRM)
2014-NM-219-AD
b. Non-Destructive Test Standard Practices Manual (NDTSPM) 06-00-04, 06-10-01.001
c. Standard Overhaul Practices Manual (SOPM) 20-50-01
d. MD-11 Aircraft Maintenance Manual (AMM) 06-21-00, 32-34-00, 71-00-00
e. MD-11 Structural Repair Manual (SRM) 51, 53-00-01
2. Data Supplied with this Service Bulletin:
None.
3. Installation Drawings Used in the Preparation of this Service Bulletin:
None.
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K. Publications Affected
1. Publications:
Chapter-SectionPublication
28-25Aircraft Maintenance Manual
2. Damage Tolerance Based Structural Inspections:
Boeing has evaluated the repairs and/or changes in this service bulletin for effects on Fatigue
Critical Structure (FCS) and for changes to Damage Tolerance Inspections (DTI) required in the
Maintenance Program. This service bulletin does not affect FCS, therefore DTIs are not necessary.
L. Interchangeability and Intermixability of Parts
Accomplishment of this service bulletin does not affect interchangeability or intermixability of parts.
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:
NotesNameQTYPart Number / Specification
(a)Bag - Polyethylene, Self-sealingAs RequiredDPM 660-1
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) or Leak(s) Found:
NotesNameQTYPart Number / Specification
(a)Compound - Sealing, Integral
Fuel Tanks and Fuel Cell Cavi-
ties
As RequiredPR-1422 B-2 Sealant
(DMS 2082)
or
Equivalent
(a)Primer, Fluid ResistantAs RequiredDMS 1786
(b)Solvent, Sealant Remover,
Hand Wipe Cleaner
As RequiredSkyKleen 1000
(DPM 6410)
or
Equivalent
(a)Wipers - Cleaning, Cotton,
White
As RequiredDMS 1820 Type 1, Class A,
Grade 2
(DMS 1820 T1A2)
or
Equivalent
(c)Bag - Polyethylene, Self-sealingAs RequiredDPM 660-1
or
Equivalent
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NotesNameQTYPart Number / Specification
(a) Refer to the Qualified Product List (QPL) at the end of the Douglas Material Specification
(DMS) or Douglas Process Material Index for supplier data.
(b) Can be purchased from: Solutia Incorporated, 8201 Idaho Avenue, Saint Louis, Missouri,
63111, CAGE: 1MFY8.
(c) 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.
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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.
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– 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. A Detailed Inspection is defined as: An intensive examination of a specific item,
installation, or assembly to detect damage, failure, or irregularity. Available lighting
is normally supplemented with a direct source of good lighting at an intensity deemed
appropriate. Inspection aids such as mirrors, magnifying lenses, etc. may be
necessary. Surface cleaning and elaborate procedures may be required.
13. Use of colors in Figures is based on guidance from the ATA e-Business Program
(ATA) iSpec 2200.
14. 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.
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15. The compliance times for the actions in Paragraph 3.B., WORK INSTRUCTIONS
are in Paragraph 1.E., Compliance.
B. WORK INSTRUCTIONS
OPTION 1: FUEL SHROUD DRAIN VALVES CHECK FOR PRESENCE OF FUEL, PRESSURE
CHECK FUEL LINE SHROUDS, AND FUEL LINE SHROUDS HIGH FREQUENCY EDDY CURRENT
INSPECTION
1. Check for presence of fuel at the Fuel Shroud Drain Valves in accordance with APPENDIX A.
a. CONDITION 1 - LEAKAGE RATE BECOMES MORE THAN 32.0 FLUID-OUNCES IN A 24
HOUR PERIOD
(1) Repair leak(s).
2. Do the following:
NOTE: The Option 2 Fuel Shroud Pressure Test can be used as an accepted alternative test for
the Option 1 High Frequency Eddy Current (HFEC) Inspection.
NOTE: If a tail tank transfer or engine number 2 fuel shroud line has been repaired in accordance
with MD-11 Structural Repair Manual (SRM) 53-00-01, Repair 3, only Option 2 can be
used for checking that fuel line shroud line for leaks.
- Do a HFEC Inspection for cracked fuel line shrouds in accordance with FIGURE 1.
- Pressure Test of the Aft Fuselage Tail Tank Fuel Shroud Drain System in accordance with
APPENDIX B.
- Pressure Test Engine Number 2 Fuel Shroud Drain System in accordance with APPENDIX C.
a. CONDITION 2 - NO CRACK(S) OR LEAK(S)FOUND BY HFEC INSPECTION OR PRESSURE
TEST
(1) No further action required.
b. CONDITION 3 - ANY CRACK(S) OR LEAK(S) FOUND BY HFEC INSPECTION OR
PRESSURE TEST
(1) Repair crack(s) found in fuel line shrouds in accordance with MD-11 SRM 53-00-01
"Repair 3 - Fuel Line Shroud Repair", and test in accordance with APPENDIX B or
APPENDIX C as applicable until no leaks are found.
(2) Identify the source of the leak(s), check fittings and fuel shroud connections. Repair
leak(s) found in fuel line shroud drain system and test in accordance with APPENDIX B
or APPENDIX C as applicable until no leak(s) are found.
3. Close access.
4. Put the airplane back to a serviceable condition.
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OPTION 2: FUEL SHROUD DRAIN VALVES CHECK FOR PRESENCE OF FUEL, AND FUEL LINE
SHROUD DRAIN SYSTEM PRESSURE TEST
1. Check for presence of fuel at the Fuel Shroud Drain Valves in accordance with APPENDIX A.
a. CONDITION 4 - LEAKAGE RATE BECOMES MORE THAN 32.0 FLUID-OUNCES IN A 24
HOUR PERIOD
(1) Repair leaks.
2. Do the following pressure tests:
NOTE: The Option 1 High Frequency Eddy Current Inspection cannot be used as an alternative
for the Option 2 shroud pressure test.
- Pressure Test of the Aft Fuselage Tail Tank Fuel Shroud Drain System in accordance with
APPENDIX B.
- Pressure Test Engine Number 2 Fuel Shroud Drain System in accordance with APPENDIX C.
a. CONDITION 5 - NO LEAK(S) FOUND
(1) No further action required.
b. CONDITION 6 - IF THE PRESSURE DECREASE IS MORE THAN 1.0 PSI IN 5 MINUTES
(1) Identify the source of the leak(s), check fittings and fuel shroud connections and repair
leak(s) found, or repair any crack(s) found in fuel line shroud drain system in accordance
with MD-11 SRM 53-00-01 "Repair 3 - Fuel Line Shroud Repair", and test in accordance
with APPENDIX B or APPENDIX C as applicable until no leaks are found.
3. Close access.
4. Put the airplane back to a serviceable condition.
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BOEING SERVICE BULLETIN MD11-28A148
ALERT  ALERT
...0•00 / 0000.  STA
,1821.000
STA
1801.000
STA
1781.000
STA
1761.000
TAIL TANK FUEL
TRANSFER PIPE
6 INCHES AFT
(+0.5/-0.0)
OF STATION 1801
FUEL SUPPLY PIPE  ENGINE NUMBER 2  6 INCHES FORWARD  (+0.5/-0.0)
OF STATION 1781
2323199
FIGURE 1: CENTER CARGO COMPARTMENT LEFT TUNNEL - FUEL LINE SHROUDS - INSPECTION
(SHEET 1 OF 2)
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### Page 26

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.
MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
(a) (b)2AAL7288-1Engine Feed and Tail Tank
Fuel Drain Shroud Assem-
blies
Inspect1
and
AAL7289-1
(a) Do High Frequency Eddy Current Inspection of the highlighted areas of the engine feed and tail tank
transfer fuel line shrouds from 6 inches forward (+0.5 / -0.0 Inches) of Station 1781 to 6 inches aft (+0.5
/ -0.0 Inches) of station 1801 in accordance with NDTSPM 06-10-01.001 (ETHF Procedure 1).
(b) Before doing the inspection, calibrate the equipment as follows:
1. Find the material type being inspected by doing a conductivity check on an area of the material.
2. Calibrate using EDM notch N2 or N6 of the applicable DAC GSET: either DAC GSET.AL.01 (for alu-
minum) or DAC GSET SS.01 (for stainless steel).
3. Use Probe Scan Method C or F to find the correct sensitivity level.
4. Use Inspection Probe Scan Method 78 to check for relevant indications (cracks or pitting holes).
FIGURE 1: CENTER CARGO COMPARTMENT LEFT TUNNEL - FUEL LINE SHROUDS - INSPECTION
(SHEET 2 OF 2)
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1. CHECK FOR PRESENCE OF FUEL AT THE FUEL SHROUD DRAIN VALVES
a. References
TITLEREFERENCE
POWER PLANTMD-11 AMM 71-00-00
b. Tools/Equipment
SPECIFICATIONDESCRIPTION
-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.
SPECIFICATIONDESCRIPTION
DPM 660-1Bag - Polyethylene, Self-sealing
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:
REMARKSMAXIMUM SERVICE-
ABLE LIMITS
CHECK
Put a 1 Quart calibrated container below the applicable drain valve (1). (Sheet 3 of
3)
1
APPENDIX A:  CHECK FOR PRESENCE OF FUEL AT THE FUEL SHROUD DRAIN VALVES
(SHEET 1 OF 3)
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REMARKSMAXIMUM SERVICE-
ABLE LIMITS
CHECK
Push in the poppet and drain the fuel into the container if necessary.2
When the fuel stops, release the poppet.3
Make a record to monitor
the leak.
If the quantity is less than
8.0 fluid-ounces in a 24
hour period from either
drain valve (1):
Use the container to mea-
sure the quantity of fuel
drained from the shroud.
(a)
Make repair at the next
convenient maintenance
period.
If the quantity is 8.0 fluid-
ounces to 32.0 fluid-
ounces in a 24 hour period
from either drain valve (1):
(b)
Repair leak(s) before fur-
ther flight. See Paragraph
1.E., Compliance for CON-
DITION 1 and CONDITION
4.
If the leakage rate be-
comes more than 32.0 flu-
id-ounces in a 24 hour peri-
od from either drain valve
(1):
(c)
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.
APPENDIX A:  CHECK FOR PRESENCE OF FUEL AT THE FUEL SHROUD DRAIN VALVES
(SHEET 2 OF 3)
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BOEING SERVICE BULLETIN MD11-28A148
ALERT  ALERT
ENGINE NUMBER 2 FUEL
SHROUD DRAIN VALVE
TAIL TANK FUF
SHROUD DRAIN VALV
FUEL SHROUD DRAIN VALVE
(TYPICAL)
2345183
APPENDIX A: CHECK FOR PRESENCE OF FUEL AT THE FUEL SHROUD DRAIN VALVES
(SHEET 3 OF 3)
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### Page 30

1. PRESSURE TEST OF THE TAIL TANK FUEL DRAIN SHROUD SYSTEM
a. References
TITLEREFERENCE
OPERATION OF THE MAIN LANDING GEAR DOOR GEAR-
WELL DOORS
MD-11 AMM 32-34-00
REPAIR 3, FUEL LINE SHROUD REPAIRMD-11 SRM 53-00-01
b. Fixtures, Tools, Test and Support Equipment
NOTE: Equivalent replacements are permitted for the items that follow:
DESIGNATIONREFERENCE
Ladder or work platform 7 ft minimumNot specified
Ladder or work platform 12 ft minimumNot specified
Tester, fuel tank and drain shroud systemDZZ7379-501
Dry air source, regulated 6.0 psi, minimumNot specified
c. Access Panels
Name/LocationNumber
AFT FUSELAGE311AB
d. Job Set-up - Tail Tank Fuel Shroud Drain System Pressure Test
(1) Open this access panel:
Name/LocationNumber
AFT FUSELAGE311AB
(2) If necessary, lower the left side main landing gear door and install the landing gear downlock
pins. Refer to MD-11 AMM 32-34-00 as an accepted procedure.
e. Procedure - Tail Tank Fuel Shroud Drain System Pressure Test - Pressure Test Between Stations
(STA No. 1521 thru 2007)
(1) Do a pressure test of the Tail Tank fuel shroud drain system as follows:
APPENDIX B:  PRESSURE TEST OF THE TAIL TANK FUEL SHROUD DRAIN SYSTEM
(SHEET 1 OF 5)
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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) Get access to the aft fuselage area through access panel 311AB.
(b) Locate two fuel pipes that enter the AFT fuselage through the aft pressure bulkhead (STA
No. 2007) on the left side. The Inboard fuel pipe is the Tail Tank fuel transfer pipe (See
Figure A).
(c) Disconnect the Inboard Tail Tank transfer fuel pipe shroud coupling drain line on the Aft
side of the pressure bulkhead area (STA No. 2007) (See Figure A).
(d) Connect pressure tester equipment part number DZZ7379-501, or equivalent pressure
tester to the Tail Tank transfer fuel pipe shroud coupling drain fitting (See Figure A).
(e) Connect a 0 to 10 psi dry air source to the pressure test equipment part number
DZZ7379-501, or equivalent pressure tester.
(f) Pressurize the Tail Tank fuel transfer piping shroud system to 4.5 to 5.0 psi.
NOTE: Push the Tail Tank fuel shroud drain valve (See Figure B) to make sure that air
is flowing, release the valve and make sure that air stops flowing.
CAUTION: DO NOT PRESSURIZE THE SHROUD DRAIN LINE MORE THAN 5.3 PSI.
TOO MUCH PRESSURE CAN CAUSE DAMAGE TO THE SHROUD DRAIN
LINE.
(g) Close the air supply valve and check the system for pressure decrease for 5 minutes.
NOTE: If the pressure decrease is more than the maximum allowable 1.0 psi in 5 minutes
the test is not passed.
1) If the pressure test passes, no further work is required, refer to step (i).
(h) If the pressure leakage rate is more than the maximum allowable 1.0 psi in 5 minutes,
identify leak(s), remove pressure and repair leak(s).
1) Repeat pressure test as necessary to identify and repair all air leaks in the Tail Tank
shroud drain system until the pressure test passes. Retest in accordance with steps
(f) thru (g).
NOTE: If a Tail Tank fuel pipe shroud crack is identified, refer to MD-11 SRM
53-00-01, Repair 3, for repair instructions. After repairing a fuel shroud
crack, retest in accordance with steps (f) thru (g).
APPENDIX B:  PRESSURE TEST OF THE TAIL TANK FUEL SHROUD DRAIN SYSTEM
(SHEET 2 OF 5)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: August 29, 2014
MD11-28A148Revision 1 March 24, 2017
31 of 39
BOEING SERVICE BULLETIN MD11-28A148
ALERTALERT

### Page 32

(i) Get access to the AFT Fuselage through access door 311AB, remove pressure and
disconnect the 0 to 10 psi dry air source from the pressure test equipment number
DZZ7379-501, or equivalent pressure tester.
(j) Disconnect pressure tester equipment part number DZZ7379-501 or equivalent pressure
tester from the disconnected (Inboard) Tail Tank transfer pipe shroud coupling drain
fitting.
(k) Reconnect the Tail Tank transfer fuel pipe shroud drain line to the Inboard fuel shroud
coupling drain fitting at station 2007 AFT pressure bulkhead.
f. Job Close-up - Tail Tank Fuel Shroud Drain System Pressure Test
(1) Close this access panel:
Name/LocationNumber
AFT FUSELAGE311AB
(2) If necessary, remove the landing gear downlock pins and raise the left side main landing gear
door and. Refer to MD-11 AMM 32-34-00 as an accepted procedure.
(3) 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 3 OF 5)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: August 29, 2014
MD11-28A148Revision 1 March 24, 2017
32 of 39
BOEING SERVICE BULLETIN MD11-28A148
ALERTALERT

### Page 33 (OCR)

BOEING SERVICE BULLETIN MD11-28A148
ALERT  ALERT
SHROUD DRAIN LINE
TAIL TANK  DRAIN LINE FITTING
SUPPLY
PRE SB MD11-28-71 CONFIGURATION
(LOOKING DOWN)
DRAIN LINE FITTING
SHROUD DRAIN LINE
FWD  STA
Y=2007.000
TAIL TANK
SUPPLY
POST SB MD11-28-71 CONFIGURATION
STA  (LOOKING DOWN)  2548841
FIGURE A  Y=2007.000
I APPENDIX B: PRESSURE TEST OF THE TAIL TANK FUEL SHROUD DRAIN SYSTEM
(SHEET 4 OF 5)
Original Issue: August 29, 2014
Revision 1 March 24, 2017  PROPRIETARY - Copyright © Unpublished  Export Controlled ECCN: 9E991 - BOEING  MD11-28A148
Work - See page 1 for details.  33 of 39

### Page 34 (OCR)

BOEING SERVICE BULLETIN MD11-28A148
ALERT  ALERT
A TAIL TANK FUEL  SHROUD DRAIN VALVE
FUEL SHROUD DRAIN VALVE
(TYPICAL)
FIGURE B  2549092
APPENDIX B: PRESSURE TEST OF THE TAIL TANK FUEL SHROUD DRAIN SYSTEM
(SHEET 5 OF 5)
Original Issue: August 29, 2014
Revision 1 March 24, 2017  Export Controlled ECCN: 9E991 - BOEING  PROPRIETARY - Copyright © Unpublished  MD11-28A148
Work - See page 1 for details.  34 of 39

### Page 35

1. PRESSURE TEST OF THE ENGINE NUMBER 2 FUEL SHROUD DRAIN SYSTEM
a. References
TITLEREFERENCE
OPERATION OF THE MAIN LANDING GEAR DOOR GEAR-
WELL DOORS
MD-11 AMM 32-34-00
REPAIR 3, FUEL LINE SHROUD REPAIRMD-11 SRM 53-00-01
b. Fixtures, Tools, Test and Support Equipment
NOTE: Equivalent replacements are permitted for the items that follow:
DESIGNATIONREFERENCE
Ladder or work platform 7 ft minimumNot specified
Ladder or work platform 12 ft minimumNot specified
Tester, fuel tank and drain shroud systemDZZ7379-501
Dry air source 10 psi, regulated 5.0 psiNot specified
c. Access Panel
Name/LocationNumber
AFT FUSELAGE311AB
d. Job Set-up - Engine Number 2 Fuel Shroud Drain System Pressure Test
(1) Open this access panel:
Name/LocationNumber
AFT FUSELAGE311AB
(2) If necessary, lower the left side main landing gear door and install the landing gear downlock
pins. Refer to MD-11 AMM 32-34-00 as an accepted procedure.
e. Procedure - Engine Number 2 Fuel Shroud - Fuel Supply Pipe - Pressure Test Between Stations
(STA) 1521 and 2007
(1) Do a pressure test of Engine Number 2 Fuel Shroud - Fuel Supply Pipe as follows:
APPENDIX C: PRESSURE TEST OF THE ENGINE NUMBER 2 FUEL SHROUD DRAIN SYSTEM
(SHEET 1 OF 5)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: August 29, 2014
MD11-28A148Revision 1 March 24, 2017
35 of 39
BOEING SERVICE BULLETIN MD11-28A148
ALERTALERT

### Page 36

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) Get access to the aft fuselage area through access panel 311AB.
(b) Locate two fuel pipes that enter the AFT fuselage through the aft pressure bulkhead (STA
No. 2007) on the left side. The outboard fuel pipe is the engine number 2 fuel supply pipe
(See Figure C).
(c) Disconnect the Outboard Engine Number 2 fuel pipe shroud coupling drain line on the
Aft side of the pressure bulkhead area (STA No. 2007) (See Figure C).
(d) Connect pressure tester equipment part number DZZ7379-501, or equivalent pressure
tester to the Engine Number 2 fuel pipe shroud coupling drain valve fitting (See Figure
C).
(e) Connect a 0 to 10 psi dry air source to the pressure test equipment part number
DZZ7379-501, or equivalent pressure tester.
(f) Pressurize the Engine Number 2 shroud system to 4.5 to 5.0 psi.
NOTE: Push the Engine Number 2 fuel shroud drain valve (See Figure D) to make sure
that air is flowing, release the valve and make sure that air stops flowing.
CAUTION: DO NOT PRESSURIZE THE SHROUD DRAIN LINE MORE THAN 5.3 PSI.
TOO MUCH PRESSURE CAN CAUSE DAMAGE TO THE SHROUD DRAIN
LINE.
(g) Close the air supply valve and check the system pressure decrease for 5 minutes.
NOTE: If the pressure decrease is more than the maximum allowable 1.0 psi in 5 minutes
the test is not passed.
1) If the pressure test passes, no further work is required, refer to step (i).
(h) If the pressure leakage rate is more than the maximum allowable 1.0 psi in 5 minutes,
identify leak(s), remove pressure and repair leak(s).
1) Repeat pressure test as necessary to identify and repair all air leaks in the Engine
Number 2 shroud drain system until the pressure test passes. Retest in accordance
with steps (f) thru (g).
NOTE: If an Engine Number 2 fuel pipe shroud crack is identified, refer to MD-11
SRM 53-00-01, Repair 3, for repair instructions. After repairing a fuel shroud
crack, retest in accordance with steps (f) thru (g).
APPENDIX C: PRESSURE TEST OF THE ENGINE NUMBER 2 FUEL SHROUD DRAIN SYSTEM
(SHEET 2 OF 5)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: August 29, 2014
MD11-28A148Revision 1 March 24, 2017
36 of 39
BOEING SERVICE BULLETIN MD11-28A148
ALERTALERT

### Page 37

(i) Get access to the AFT Fuselage through access door 311AB, remove pressure and
disconnect the 0 to 10 psi dry air source from the pressure test equipment part number
DZZ7379-501, or equivalent pressure tester.
(j) Disconnect pressure tester equipment part number DZZ7379-501 or equivalent pressure
tester from the disconnected (outboard) Engine Number 2 supply pipe shroud coupling
drain fitting.
(k) Reconnect the Engine Number 2 fuel supply pipe shroud drain line to the outboard fuel
shroud coupling drain fitting at station 2007 AFT pressure bulkhead.
f. Job Close-up - Engine Number 2 Fuel Shroud Drain System Pressure Test
(1) Close this access panel:
Name/LocationNumber
AFT FUSELAGE311AB
(2) If necessary, remove the landing gear downlock pins and raise the left side main landing gear
door and. Refer to MD-11 AMM 32-34-00 as an accepted procedure.
(3) Remove all the tools and equipment from the work area. Make sure that the area is clean.
APPENDIX C: PRESSURE TEST OF THE ENGINE NUMBER 2 FUEL SHROUD DRAIN SYSTEM
(SHEET 3 OF 5)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: August 29, 2014
MD11-28A148Revision 1 March 24, 2017
37 of 39
BOEING SERVICE BULLETIN MD11-28A148
ALERTALERT

### Page 38 (OCR)

BOEING SERVICE BULLETIN MD11-28A148
ALERT  ALERT
• SHROUD DRAIN LINE
DRAIN LINE FITTING
PRE SB MD11-28-71 CONFIGURATION
(LOOKING DOWN)
ENGINE
NUMBER 2
SUPPLY
FWD  STA
Y=2007.000
SHROUD DRAIN LINE
ENGINE  NUMBER 2  DRAIN LINE FITTING
SUPPLY
FWD  POST SB MD11-28-71 CONFIGURATION
STA  (LOOKING DOWN)  2549125
FIGURE C  Y=2007.000
APPENDIX C: PRESSURE TEST OF THE ENGINE NUMBER 2 FUEL SHROUD DRAIN SYSTEM
(SHEET 4 OF 5)
Original Issue: August 29, 2014
Revision 1 March 24, 2017  Export Controlled ECCN: 9E991 - BOEING  PROPRIETARY - Copyright © Unpublished  MD11-28A148
Work - See page 1 for details.  38 of 39

### Page 39 (OCR)

BOEING SERVICE BULLETIN MD11-28A148
ALERT  ALERT
ENGINE NUMBER 2 FUEL
SHROUD DRAIN VALVE
FUEL SHROUD DRAIN VALVE
(TYPICAL)
FIGURE D  2549128
APPENDIX C: PRESSURE TEST OF THE ENGINE NUMBER 2 FUEL SHROUD DRAIN SYSTEM
(SHEET 5 OF 5)
Original Issue: August 29, 2014
Revision 1 March 24, 2017  PROPRIETARY - Copyright © Unpublished  Export Controlled ECCN: 9E991 - BOEING  Work - See page 1 for details.  MD11-28A148  39 of 39

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