# Boeing Service Bulletin 757-57-0061: U.S. DOT/FAA - SB-757-57-0061-03

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- Title as filed: U.S. DOT/FAA - SB-757-57-0061-03
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### Page 1

Commercial 
Airplanes
757
Service Bulletin
Number: 757-57-0061
Original Issue: February 06, 2003
Revision 3: December 07, 2012
ATA System: 5710 2810
SUBJECT: WINGS - Center Wing Box - Inspection of the Application of Secondary Fuel Barrier
on the Front Spar and Upper Panel (-300 Series)
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 © 2003 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Unpublished Work.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, KDC-10, MD-10, MD-11, MD-80, MD-88, MD-90, P-8A, 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. BOEING is a trademark of Boeing Management
Company.
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Table of Contents
Revision Transmittal Sheet ............................................ 5
Summary ...................................................... 7
1. PLANNING INFORMATION ........................................ 1 1
A. Effectivity ............................................... 1 1
1. Airplanes ............................................ 1 1
2. Spares Affected ........................................ 1 2
B. Concurrent Requirements ...................................... 1 2
C. Reason ................................................ 1 2
D. Description .............................................. 1 2
E. Compliance .............................................. 1 3
F. Approval ............................................... 1 3
G. Manpower .............................................. 1 4
H. Weight and Balance Changes .................................... 1 5
I. Electrical Load Data ......................................... 1 5
J. References .............................................. 1 5
1. Existing Data: ......................................... 1 5
2. Data Supplied with this Service Bulletin: ........................... 1 5
3. Installation Drawings Used in the Preparation of this Service Bulletin: ........... 1 6
K. Publications Affected ........................................ 1 6
L. Interchangeability and Intermixability of Parts ........................... 1 6
M. Software Accomplishment Summary ................................ 1 6
2. MATERIAL INFORMATION ........................................ 1 7
A. Material - Price and Availability ................................... 1 7
B. Industry Support Information .................................... 1 7
C. Parts Necessary for Each Airplane ................................. 1 7
1. Kits/Parts: ........................................... 1 7
2. Parts and Materials Supplied by the Operator: ........................ 1 7
3. Parts Modified and Reidentified: ............................... 1 7
4. Parts Removed and Not Replaced: .............................. 1 7
D. Parts Necessary to Change Spares ................................. 1 8
E. Special Tooling - Price and Availability ............................... 1 8
F. Special Tooling Necessary to do this Service Bulletin ....................... 1 8
3. ACCOMPLISHMENT INSTRUCTIONS .................................. 1 9
A. GENERAL INFORMATION ..................................... 1 9
B. WORK INSTRUCTIONS ....................................... 2 0
FIGURE 1: OPEN ACCESS - AIR CONDITIONING DUCT REMOVAL - GROUP 1, GROUP 2 AND GROUP
3 ................................................. 3 0
FIGURE 2: INSPECTION - SECONDARY FUEL BARRIER - FRONT SPAR - GROUP 1 AND GROUP 3,
CONFIGURATION 1 ...................................... 3 1
FIGURE 3: INSPECTION - SECONDARY FUEL BARRIER - UPPER PANEL - GROUP 1 AND GROUP 3,
CONFIGURATION 1 ...................................... 3 6
FIGURE 4: INSPECTION - THICKNESS MEASUREMENTS - FRONT SPAR - GROUP 1 AND GROUP 3
.................................................. 4 3
FIGURE 5: INSPECTION - THICKNESS MEASUREMENTS - UPPER PANEL - GROUP 1 AND GROUP
3 ................................................. 4 6
FIGURE 6: INSPECTION AND APPLICATION OF THE SECONDARY FUEL BARRIER - GROUP 2 . 51
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FIGURE 7: CLOSE ACCESS - AIR CONDITIONING DUCT INSTALLATION - GROUP 1, GROUP 2 AND
GROUP 3 ............................................ 5 3
Appendix A: RECORD OF THICKNESS MEASUREMENTS ........................ 5 4
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Commercial 
Airplanes
757
Service Bulletin
Revision Transmittal SheetNumber: 757-57-0061Original Issue: February 06, 2003
Revision 3: December 07, 2012
ATA System: 5710 2810
SUBJECT: WINGS - Center Wing Box - Inspection of the Application of Secondary Fuel Barrier
on the Front Spar and Upper Panel (-300 Series)
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 2011-NM-070-AD, is related to
this service bulletin.
No more work is necessary on the airplane(s) changed in accordance with the Revision 1 or 2, of this service
bulletin.
REASON FOR REVISION
This revision is sent to change the quantity of locations listed in Figure 5, Sheet 5 of 5, Step 2 in order to match
the view shown in Figure 5, sheet 1 of 5 and the Upper Panel (TP) Table in Appendix A.
These sections were changed:
1. In Summary Compliance, Added NPRM.
2. In Paragraph 1.C. Reason, Added Revision 3 description.
3. In Paragraph 1.E. Compliance, Added NPRM.
4. In Paragraph 1.J. References, Added NPRM.
5. In Paragraph 3.A. Updated General Notes.
6. In Figure 5, Added new View F-F and changed Step 2. PRT and LTP quantity to match locations shown
in the Figure and listed in Appendex A, Inspection Worksheet.
Vertical lines are put on the left edge of each page, except in Paragraph 1.A., Effectivity, to show the location
of important changes.
Pages with no vertical lines have no important changes.
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REVISION HISTORY
February 06, 2003Original Issue:
May 24, 2007Revision 1:
May 04, 2012Revision 2:
December 07, 2012Revision 3:
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Commercial 
Airplanes
757
Service Bulletin
SummaryNumber: 757-57-0061Original Issue: February 06, 2003
Revision 3: December 07, 2012
ATA System: 5710 2810
SUBJECT: WINGS - Center Wing Box - Inspection of the Application of Secondary Fuel Barrier
on the Front Spar and Upper Panel (-300 Series)
CONCURRENT REQUIREMENTS
None.
BACKGROUND
Inspections of the Wing Center Section at Boeing did not find the Secondary Fuel Barrier applied to the outboard
corners of the front spar. More inspections found defective examples of the Secondary Fuel Barrier applied
along the front spar and the upper panel.
The Secondary Fuel Barrier is applied to areas of the center section that are subject to cabin pressure. When
the secondary fuel barrier is applied satisfactorily, it protects the pressurized cabin areas from fuel leaks or
fumes. If the secondary fuel barrier is defective, fuel or fumes can leak through fastener holes or cracks in the
structure and pass into the passenger compartment. There are no reports of fuel leaks or fumes in the passenger
compartment.
This service bulletin will examine where and how the Secondary Fuel Barrier is applied to the front spar and
upper panel. The inspections will identify locations where the secondary fuel barrier is not satisfactory. A new
layer of secondary fuel barrier will be applied if it is necessary. A satisfactory secondary fuel barrier will keep
fuel leaks or fumes out of the pressurized cabin.
Boeing Service Related Problem (SRP) 757-SRP-28-0067 is related to this service bulletin.
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 ChangesYesWeight and Balance Change
Paragraph 1.I., Electrical Load DataNoElectrical Load Changed
Paragraph 1.K., Publications AffectedNoPublications Affected
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ReferenceAffectedPlanning Data
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
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
Get access to the front spar and the top of the Wing Center Section by removal of the seats, floor covers, floor
panels and cabin lining at, or adjacent to, Body Stations (BS) 900 thru 1040. If necessary, remove the bulkhead
lining for more access.
Examine the specified locations where the Secondary Fuel Barrier is applied. Look for examples of missing,
peeled, non-continuous or non-transparent secondary fuel barrier. Make sure the applied thickness of the
secondary fuel barrier is between the specified limits. Remove the corrosion inhibitor compound if it is necessary,
then clean the area where the new layer of secondary fuel barrier will be applied. Install all the components that
were removed for access. Do system tests as necessary.
EFFECTIVITY
Airplane Model 757-300; Line numbers 804 thru 964; divided into three groups.
COMPLIANCE
Federal Aviation Administration (FAA) Notice of Proposed Rule Making:NPRM 2011-NM-070-AD, is related to
this service bulletin.
Boeing recommends the inspection of the Secondary Fuel Barrier at the next regularly scheduled heavy
maintenance check. Apply the secondary fuel barrier, if it is necessary, no later than five years after the release
of this service bulletin.
INDUSTRY SUPPORT INFORMATION
Boeing warranty remedies are available for 757 airplanes. Please refer to Paragraph 2.B., Industry Support
Information.
MANPOWER
See Paragraph 1.G Manpower.
MATERIAL INFORMATION
Operator Supplied Parts/Materials.
Refer to Paragraph 2.A., Material - Price and Availability.
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BOEING SERVICE BULLETIN 757-57-0061
STA
90 STA
1040
EXAMINE THE UPPER PANEL AND FRONT
SPAR FOR DEFECTIVE APPLICATION OF
SECONDARY FUEL BARRIER.
IF DEFECTIVE, REMOVE AND APPLY A
NEW LAYER OF  SECONDARY FUEL BARRIER.
V87883
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Commercial 
Airplanes
757
Service Bulletin
Number: 757-57-0061
Original Issue: February 06, 2003
Revision 3: December 07, 2012
ATA System: 5710 2810
SUBJECT: WINGS - Center Wing Box - Inspection of the Application of Secondary Fuel Barrier
on the Front Spar and Upper Panel (-300 Series)
1.    PLANNING INFORMATION
A. Effectivity
1. Airplanes
Refer to Service Bulletin Index Document D6-24N001 Part 3 for Airplane Variable Number, Line
Number, and Serial Number data.
DESCRIPTIONCONFIGURATIONGROUP
757-300 Airplanes that must complete the whole bulletin-1
757-300 Airplanes that only require inspection of the front spar center
section.
-2
757-300 Airplanes previously in Group 1 that could have fuel vapor
barrier material applied that was thinned with lacquer thinner.
-3
Group 3 Airplanes that have not incorporated the previous release
of service bulletin 757-57-0061.
1
Group 3 Airplanes that have incorporated the previous release of
service bulletin 757-57-0061.
2
Airplane Models:
757-300
GroupVariable Number
2NL001 - NL002
1NU701 - NU705
1NU721 - NU723
3NU724 - NU727
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GroupVariable Number
1NU728
3NU731 - NU732
2. Spares Affected
None.
B. Concurrent Requirements
None.
C. Reason
Inspections of the Wing Center Section at Boeing did not find the Secondary Fuel Barrier applied to
the outboard corners of the front spar. More inspections found defective examples of the Secondary
Fuel Barrier applied along the front spar and the upper panel.
The Secondary Fuel Barrier is applied to areas of the center section that are subject to cabin pressure.
When the secondary fuel barrier is applied satisfactorily, it protects the pressurized cabin areas from
fuel leaks or fumes. If the secondary fuel barrier is defective, fuel or fumes can leak through fastener
holes or cracks in the structure and pass into the passenger compartment. There are no reports of fuel
leaks or fumes in the passenger compartment.
This service bulletin will examine where and how the Secondary Fuel Barrier is applied to the front
spar and upper panel. The inspections will identify locations where the secondary fuel barrier is not
satisfactory. A new layer of secondary fuel barrier will be applied if it is necessary. A satisfactory
secondary fuel barrier will keep fuel leaks or fumes out of the pressurized cabin.
NOTE: A satisfactory secondary fuel barrier is described in the Accomplishment Instructions.
Boeing Service Related Problem (SRP): 757-SRP-28-0067 is related to this service bulletin.
Revision 1 is sent to add a group of airplanes that may have been delivered with improperly mixed
secondary fuel vapor barrier sealant and to provide new thickness measurement inspection limits. This
revision includes the correct special tooling requirements for the accomplishment of the service bulletin,
and provides clarifications and corrections to inspection points on the Front Spar and Upper Panel.
Revision 2 is sent to reference possibly release an Airworthiness Directive, to revise the Industry
Support information, to add Damage Tolerance Information, to remove the title of Part III, and the Group
2 from the title of Part III, IV, and V, to delete "and upper panel" from step 1 of Part VI of the work
Instructions and to correct a typographical error from Part VI and Part V.
Revision 3 is sent to change the quantity of locations listed in Figure 5, Sheet 5 of 5, Step 2 in order
to match the view shown in Figure 5, sheet 1 of 5 and the Upper Panel (TP) Table in Appendix A.
D. Description
Get access to the front spar and the top of the Wing Center Section by removal of the seats, floor
covers, floor panels and cabin lining at, or adjacent to, Body Stations (BS) 900 thru 1040. If necessary,
remove the bulkhead lining for more access.
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Examine the specified locations where the Secondary Fuel Barrier is applied. Look for examples of
missing, peeled, non-continuous or non-transparent secondary fuel barrier. Make sure the applied
thickness of the secondary fuel barrier is between the specified limits. Remove the corrosion inhibitor
compound if it is necessary, then clean the area where the new layer of secondary fuel barrier will be
applied. Install all the components that were removed for access. Do system tests as necessary.
The airplane effectivity is divided into three groups. The airplanes in Group 1 and Group 3, Configuration
1 must complete all of the service bulletin. The airplanes in Group 2 will only do work on the Front Spar.
The airplanes in Group 3, Configuration 2 must be checked to determine if the vapor barrier meets the
new thickness requirements.
Revision 1 - More work is necessary on airplanes changed as shown in the initial release of this service
bulletin. The airplanes in Group 3, Configuration 2 must be checked to determine if the vapor barrier
meets the new thickness requirements.
PLEASE SEND A REPORT OF YOUR INSPECTION PROGRAM. ALSO, SEND THE INSPECTION
RESULTS WHEN EACH INSPECTION IS COMPLETE
Send your report to: BOEING COMMERCIAL AIRPLANES GROUP ATTENTION: MANAGER, AIRLINE
SUPPORT
The work in this service bulletin is done in the maintenance zone(s) given below.
Affected Maintenance Zones
ZoneModel
133, 134757-300
E. Compliance
Federal Aviation Administration (FAA) Notice of Proposed Rule Making NPRM 2011-NM-070-AD, is
related to this service bulletin.
Boeing recommends the inspection of the Secondary Fuel Barrier at the next regularly scheduled heavy
maintenance check. Apply the secondary fuel barrier, if it is necessary, no later than five years after
the release of this service bulletin.
F. Approval
This service bulletin was examined by the Federal Aviation Administration (FAA). The changes specified
in this service bulletin comply with the applicable regulations and are FAA approved, as well as European
Aviation Safety Agency (EASA)/Joint Aviation Authorities (JAA) approved for all EASA/JAA approved
airplanes listed in the service bulletin effectivity. This service bulletin and its approval were based on
the airplane in its original Boeing delivery configuration or as modified by other approved Boeing
changes.
If an airplane has a non-Boeing modification or repair that affects a component or system also affected
by this service bulletin, the operator is responsible for obtaining appropriate regulatory agency approval
before incorporating this service bulletin.
NOTE: Joint Airworthiness Requirements (JAR) compliance status may be found in the Service Bulletin
Index, Part 1.
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G. Manpower
The table below shows an estimate of the task-hours necessary to do this bulletin for each airplane.
This estimate is for direct labor only, done by an experienced crew. Adjust the estimate with operator
task-hour data if necessary. The estimate does not include lost time. These are some examples of lost
time:
— Time to adjust to the workplace
— Time to schedule the work
— Time to examine the work
— Time to cure the materials
— Time to make the parts
— Time to find the tools.
Group 1 and Group 3, Configuration 1 ONLY
Elapsed HoursTask-HoursNumber of Per-
sons
Task
6.513.02Open Access
4.08.02Inspection
6.06.01Thickness Measurement
6.56.51Secondary Fuel Barrier Ap-
plication
7.515.02Close Access
30.548.5TOTAL FOR EACH AIRPLANE
Group 2 ONLY
Elapsed HoursTask-HoursNumber of Per-
sons
Task
2.04.02Open Access
4.08.02Inspection
6.56.51Secondary Fuel Barrier Ap-
plication
3.06.02Close Access
15.524.5TOTAL FOR EACH AIRPLANE
Group 3, Configuration 2 ONLY
Elapsed HoursTask-HoursNumber of Per-
sons
Task
6.513.02Open Access
6.06.01Thickness Measurement
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Elapsed HoursTask-HoursNumber of Per-
sons
Task
6.56.51Secondary Fuel Barrier Ap-
plication
7.515.02Close Access
26.540.5TOTAL FOR EACH AIRPLANE
H. Weight and Balance Changes
Change in Moment
(Pound-Inches)
Change in Weight
(Pounds)
Airplane
+ 1, 000+ 1757-300
I. Electrical Load Data
Not changed.
J. References
1. Existing Data:
a. Miscellaneous Retrofit Requirement (MRR) MRR 5574-1067
b. Service Related Problem (SRP): 757-SRP-28-0067
c. Boeing Document D6-56722, Customer Cost Benefit Methodology Guide
d. 757 Maintenance Manual (AMM) Subjects 20-10-11, 20-10-12, 21-00-00, 21-00-01, 21-21-00,
21-23-06, 24-41-00, 25-21-02, 25-25-01, 25-27-01, 25-50-03, 25-50-04, 28-11-00, 36-00-00
and 53-01-01.
e. 757 Structural Repair Manual (SRM) Subject 57-10-10
f. Boeing Standard Overhaul Practices Manual (BSOPM) 20-41-05, 20-50-19 and 20-60-01
g. 757 Maintenance Planning Document (MPD) Item Number CP53-124-01I
h. FAA Airworthiness Directive 98-19-05, Amendment 39-10747
i. Boeing Parts Standards Document D-590
j. Boeing Drawing 65-88700
k. Federal Aviation Administration (FAA) Notice of Proposed Rule Making NPRM
2011-NM-070-AD, is related to this service bulletin.
2. Data Supplied with this Service Bulletin:
None.
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3. Installation Drawings Used in the Preparation of this Service Bulletin:
TitleDrawing Number
Seal Application - Secondary Fuel Barrier Coating, Wing, Center
Section
110N0004
Terminal Fitting Installation - Wing / Body Joint, Front Spar112N2010
Bulkhead Installation, Front Spar Body Station 900144N2101
Corrosion Inhibiting Compound Instl - Fuselage140N3002
These drawings were used to prepare this service bulletin. These drawings are not necessary to
make the specified changes, and are not supplied with this service bulletin. These drawings may
not be applicable to all airplane configurations or operators.
K. Publications Affected
1. Publications:
None.
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 available for Group 1, Group 2, and Group 3 - Configuration 1, 757
airplanes in warranty as of September 22, 2000. Boeing warranty remedies are available for Group 3-
Configuration 2, 757 airplanes in warranty as of October 8, 2004. For inspection man-hour reimbursement
for airplanes in warranty as of that date, send a warranty claim to Boeing Commercial Airplanes Group
- Warranties. If the condition described in this service bulletin is found during the inspection for airplanes
in warranty as of that date and additional man-hours and kits, parts, and/or special tools are required,
send a warranty claim to Boeing Commercial Airplanes Group - Warranties. Please refer to this service
bulletin number and reference the airplane variable numbers in your purchase order.
C. Parts Necessary for Each Airplane
1. Kits/Parts:
None.
2. Parts and Materials Supplied by the Operator:
NotesNameQTYPart Number / Specification
Abrasive Paper, Aluminum Oxide20 Sheets180 to 400 grit
(a)Sealant, Secondary Fuel Barrier40 oz.BMS 5-81, Type II
(a)Organic Corrosion Inhibiting Compound1 PintBMS 3-23, Type II, Class 2
(a)Advanced Organic Corrosion Inhibiting Com-
pounds (CIC)
1 PintBMS 3-29
(a)Heavy Duty Corrosion Inhibiting Compound1 PintBMS 3-35
(a)Chemical and Solvent Resistant Finish1 PintBMS 10-11, Type I
(a) (b)Pressure and Environmental Sealant - Chro-
mate Type
1 PintBMS 5-95, Type 1, Class B-1/2,
B-2 or B-4
(a) See the Qualified Products List at the end of the Boeing Material Specification (BMS) for supplier
data.
(b) Refer to BSOPM 20-50-19
3. Parts Modified and Reidentified:
None.
4. Parts Removed and Not Replaced:
None.
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D. Parts Necessary to Change Spares
None.
E. Special Tooling - Price and Availability
The operator can supply the tools shown in Paragraph 2.F., Special Tooling Necessary to do this
Service Bulletin. Tool price and supply data are not given.
F. Special Tooling Necessary to do this Service Bulletin
To get the Non-Conductive Coating Thickness Gage shown below, 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.
NameTool Number
Dualscope MP20 (a) (b)602-816
ETA 3.3H Probe (a) (b)602-128
(a) (a) The Dualscope with probe are an example of a Non-Conductive Coating Thickness
Gage (NCCTG). The use of any NCCTG is permitted, but it must have a thickness range
from 0.001 - 0.045 inches.
(b) (b) Fisher Technology (9U437) 750 Marshall Phelps Rd. Windsor, CT 06095-2199
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3.    ACCOMPLISHMENT INSTRUCTIONS
A. GENERAL INFORMATION
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. Obey all of the warnings and cautions given in the specified manual sections.
3. The work instructions are divided into work packages. Task Hours and Elapsed Hours
for each package are given in Paragraph 1.G., Manpower. You can do each work
package independently.
4. Unless shown differently, these dimensions and tolerances are used:
– Linear dimensions are in inches
– Tolerance on linear dimensions, other than rivet and bolt edge margins, is plus
or minus 0.03 inch
– Tolerance on rivet and bolt edge margin is plus or minus 0.05 inch
– Angular tolerance is plus or minus 2 degrees
– Hole dimensions for standard solid rivets and fasteners are in Structural Repair
Manual (SRM) Chapter 51
– Torque limits to tighten nuts and bolts are in SRM Chapter 51
5. Use the approved fastener and process material substitutions in accordance with
SRM Chapter 51.
6. Refer to the SWPM 20-10-11 and SWPM 20-10-12 for the wire installation procedures,
and SWPM 20-10-19 for the wire separation requirements, as accepted procedures.
7. The necessary conditions for selection of clamp type and size are included in SWPM
20-10-12. If any wire bundle support clamp specified in this service bulletin does not
make a correct fit on the wire bundle, refer to SWPM 20-10-12 as an accepted
procedure to select a clamp that fits correctly.
8. If the length of any fastener specified in this service bulletin does not meet installation
standards given in SRM Chapter 51, then a fastener of the same specification, or
an approved substitute, with a length which meets the installation standards given
in SRM Chapter 51 may be used. In addition, washers may be installed for fastener
grip length in accordance with SRM Chapter 51.
9. 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.
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10. 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 "as
given" or "in accordance with" are included in the instruction, the procedure in the
Boeing document must be used.
11. Boeing Service Letter 757-SL-51-022, Damage Reporting and Repair Plan/Design
Guidelines, is an acceptable procedure to request information from Boeing for
additional structural repair instructions. The Service Letter describes what information
must be provided to Boeing before a structural repair can be provided.
12. Refer to Appendix A for Thickness Measurments- Upper Panel -Group 1 and Group
3 Airplanes.
13. The instructions in Paragraph 3.B., Work Instructions and the figures can include
operation of tools or test equipment. Boeing Engineering Tool Drawings, the Illustrated
Tool and Equipment Manual, and the Special Tool and Ground Handling Drawing
Index contain data on versions of the tools or test equipment that you can use. It is
permitted to use replaced tools. It is not permitted to use superseded tools.
14. 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.
15. 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.
16. 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.
17. Some Boeing parts are supplied in a temporary configuration. Those parts are
identified with a 'U', 'W', or 'Y' in place of the '-' (dash) in the part number. It is
permitted to install parts identified with a 'U', 'W', or 'Y' as an alternative to the '-'
(dash) part number. Boeing Drawing 005W0900 contains more data.
B. WORK INSTRUCTIONS
1. For Group 1, Group 2 and Group 3, Configuration 1 airplanes, do Part I through Part VIII as
applicable.
2. For Group 3, Configuration 2 airplanes, do Part IX.
PART I - Open Access - Group 1 and Group 3, Configuration 1
1. Supply external power to the airplane, as given in 757 AMM 24-41-00.
2. Release the pressure from the pneumatic system; refer to 757 AMM 36-00-00 .
3. Set the L And R Pack selectors to the OFF position, on the pilot's overhead panel P5. Refer to
757 AMM 21-00-00.
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a. Make sure the PACK OFF lights come on.
b. Put a DO-NOT-OPERATE tag on the selectors.
4. Set the L And R RECIRC FAN switch-lights to the OFF position, on the pilot's overhead panel P5.
Refer to 757 AMM 21-00-01.
a. Make sure the INOP lights go on, and the ON lights go off.
b. Put a DO-NOT-OPERATE tag on the switch-lights.
5. Get access to the forward side of the Front Spar and the Upper Panel of the Wing Center Section.
a. Between BS 900 and 1040, remove:
(1) The passenger seats, as referenced in 757 AMM 25-25-01.
(2) The floor covering, as referenced in 757 AMM 25-27-01.
(3) The floor panels, as referenced in 757 AMM 25-50-04 and 757 AMM 53-01-01.
(4) The sidewall lining (panels and carpet risers), as referenced in 757 AMM 25-21-02.
b. Remove the air conditioning ducts from the mix manifold at the locations shown in Figure 1.
c. Remove the aft bulkhead lining from the forward cargo compartment, as referenced in 757
AMM 25-50-03.
PART II - Open Access - Group 2
1. Supply external power to the airplane, as given in 757 AMM 24-41-00.
2. Release the pressure from the pneumatic system; refer to 757 AMM 36-00-00.
3. Set the L And R Pack selectors to the OFF position, on the pilot's overhead panel P5. Refer to
757 AMM 21-00-00.
a. Make sure the PACK OFF lights come on.
b. Put a DO-NOT-OPERATE tag on the selectors.
4. Set the L And R RECIRC FAN switch-lights to the OFF position, on the pilot's overhead panel P5.
Refer to AMM 757 AMM 21-00-01.
a. Make sure the INOP lights go on, and the ON lights go off.
b. Put a DO-NOT-OPERATE tag on the switch-lights.
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5. Get access to the forward side of the Front Spar and the Upper Panel of the Wing Center Section.
a. Remove the air conditioning ducts from the mix manifold at the locations shown in Figure 1.
b. Remove the aft bulkhead lining from the forward cargo compartment, as referenced in 757
AMM 25-50-03.
Part III - Inspection of the Secondary Fuel Barrier - Group 1, and Group 3, Configuration 1
1. Do a Detailed Visual Inspection of the Front Spar and the Upper Panel. Refer to Figure 2 and
Figure 3 for the specified location of the application.
a. Look for signs of missing, peeled, non-continuous or non-transparent secondary fuel barrier.
(1) If no defective surfaces are found, the secondary fuel barrier is permitted. Continue to
examine in Paragraph 1.b.
(2) If defective surfaces are found, the secondary fuel barrier is NOT permitted. Record the
location. Repair as given in Part V - Repair of the Secondary Fuel Barrier - Group 1, and
Group 3, Configuration 1.
b. Look for small air bubbles, air pockets or blister-like areas, or solid particles in the secondary
fuel barrier or between the secondary fuel barrier and the structure.
(1) If no defective surfaces are found, the secondary fuel barrier is permitted. Continue to
examine the surface as directed in Paragraph 1.c.
(2) If some small air bubbles or non-metallic solid particles are found, they must NOT break
the continuity of the application of the secondary fuel barrier. If there are no more than 2
(two) occurrences in a 12 inch by 12 inch area the application is permitted. Continue to
examine the surface as directed in Paragraph 1.c if this statement is correct.
(3) Air pockets or blister-like areas between the secondary fuel barrier and the structure are
NOT permitted. Record the location and repair as given in Part V - Repair of the Secondary
Fuel Barrier - Group 1, and Group 3, Configuration 1.
NOTE: Solid metallic particles are not acceptable. Record the location and repair as
given in Part V - Repair of the Secondary Fuel Barrier - Group 1, and Group 3,
Configuration 1.
(4) If small air bubbles, air pockets or non-metallic solid particles break the continuity of the
application of the secondary fuel barrier, the application is NOT permitted. Record the
location. Repair as given in Part V - Repair of the Secondary Fuel Barrier - Group 1, and
Group 3, Configuration 1. Continue to examine in the surface as directed in Paragraph
1.c.
c. Look for fillet sealant, primer, corrosion inhibiting compound or other finishes that are applied
on top of the Secondary Fuel Barrier.
(1) If no defective surfaces are found, the secondary fuel barrier is permitted. Continue to
do the Accomplishment Instructions.
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(2) If defective surfaces are found, and the structure below can be seen, it is a permitted
secondary fuel barrier. Continue to do the Accomplishment Instructions.
(3) If defective surfaces are found, but the structure below cannot be seen, it is NOT a
permitted secondary fuel barrier. Record the location and repair as given in Part V - Repair
of the Secondary Fuel Barrier - Group 1and Group 3, Configuration 1.
d. Look for missing fillet (cap) seals common to the fastener locations shown in Figure 2, View
J-J.
(1) If all the locations are cap sealed, no work is necessary. Continue to do the
Accomplishment Instructions.
(2) If there are locations that are not cap sealed, record the location. Repair as given in Part
V - Repair of the Secondary Fuel Barrier - Group 1 and Group 3, Configuration 1.
Part IV - Thickness Measurement Inspection - Group 1
1. Measure the thickness of the secondary fuel barrier applied to the locations specified in Figures
4 and 5.
2. Make sure the thickness is 0.007 - 0.022 inch. (This includes a 0.002 inch layer of primer.) Refer
to Figure 2.
a. If the thickness is less than 0.007 inch, apply more Secondary Fuel Barrier as given in Part
X - Application of More Secondary Fuel Barrier.
b. If the thickness is more than 0.022 inch, it must have a transparent quality. A transparent
quality makes it easy to see a crack that starts below the structure. An applied secondary fuel
barrier that is not transparent must be removed. Repair as given in Part V - Repair of Secondary
Fuel Barrier - Group 1, and Group 3, Configuration 1.
c. If the thickness is more than 0.042 inch, the secondary fuel barrier is NOT permitted. Repair
as given in Part V - Repair of the Secondary Fuel Barrier - Group 1, and Group 3, Configuration
1.
NOTE: Do NOT measure on top of the other sealants. There is no limit to the thickness of
secondary fuel barrier applied on top of BMS 5-95 (Pressure and Environmental Sealant,
Chromate Type) and BMS 5-142 (Low -Density Sealant).
3. Record the thickness data in the Inspection Worksheets given in Appendix A and keep the worksheet
with the airplane maintenance records for future reference.
Part IV(a) - Thickness Measurement Inspection - Group 3, Configuration 1
1. Measure the thickness of the secondary fuel barrier applied to the locations specified in Figure 4
and Figure 5.
NOTE: The thickness measurements below includes a 0.002 inch layer of primer.
a. If the thickness is less than 0.007 inch, apply a minimum of 0.005 inch new Secondary Fuel
Barrier as given in Part X - Application of More Secondary Fuel Barrier.
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b. If the thickness is greater than 0.012 inch, but less than or equal to 0.017 inch, apply a minimum
of 0.005 inch new Secondary Fuel Barrier as given in Part X - Application of More Secondary
Fuel Barrier.
NOTE: Thicknesses between 0.007 inch and 0.012 inch do not require the application of
the additional 0.005 inch secondary fuel barrier. Overcoating is allowed in this
thickness range to make the repair of adjacent areas more efficient.
c. If the thickness is greater than 0.017 inch, but less than or equal to 0.037 inch it must have a
transparent quality and it must be overcoated with a minimum of 0.005 inch of new Secondary
Fuel Barrier as given in Part X - Application of More Secondary Fuel Barrier.
NOTE: A transparent quality makes it easy to see a crack in the structure. An applied
secondary fuel barrier that is not transparent must be removed. Repair as given in
Part V - Repair of Secondary Fuel Barrier - Group 1, and Group 3 - Configuration 1.
d. If the thickness is more than 0.037 inch, the secondary fuel barrier is NOT permitted. Repair
as given in Part V - Repair of the Secondary Fuel Barrier - Group 1, and Group 3 - Configuration
1.
NOTE: Do NOT measure on top of the other sealants. There is no limit to the thickness of
secondary fuel barrier applied on top of BMS 5-95 (Pressure and Environmental Sealant,
Chromate Type) and BMS 5-142 (Low -Density Sealant).
2. Record the thickness data in the Inspection Worksheets given in Appendix A and keep the worksheet
with the airplane maintenance record for future reference.
Part V - Repair of the Secondary Fuel Barrier - Group 1, and Group 3, Configuration 1
1. Repair the Secondary Fuel Barrier at the locations noted in Part III - Inspection of the Secondary
Fuel Barrier - Group 1, and Group 3, Configuration 1; and in Part IV - Thickness Measurement
Inspection - Group 1; and in Part IV(a) - Thickness Measurement Inspection - Group 3, Configuration
1.
a. Remove the secondary fuel barrier as given in 757 AMM 28-11-00.
NOTE: 757 AMM 28-11-00 does not directly address removal of large areas of BMS 5-81
sealant. It is permissible to remove the bulk of the sealant with the use of plastic or
wooden scrapers. Boeing production typically uses plastic scrapers.
b. If not already applied, apply a cap seal to the top side of the fasteners as specified in BSOPM
20-50-19. Refer to Figure 2, View J-J.
c. Apply the secondary fuel barrier as given in 757 AMM 28-11-00.
Part VI - Inspection and Application of the Secondary Fuel Barrier - Group 2
1. Do a Detailed Visual Inspection of the Front spar to ensure that the application covers the minimum
area specified in Figure 6.
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a. Make sure the Secondary Fuel Barrier is applied a minimum of 1.50 inches below the lowest
fastener that passes through the front spar web and the lower chord.
b. If the Secondary Fuel Barrier does not cover the minimum specified area, apply as given in
757 AMM 28-11-00.
Part VII - Close Access - Group 1 and Group 3 - Configuration 1
1. Close access to the forward side of the Front Spar and the Upper Panel of the Wing Center Section.
a. Install the air conditioning ducts on the mix manifold as shown in Figure 7.
b. Do a leak test of the air conditioning ducts as given in 757 AMM 21-23-06 "Do the Riser Duct
Installation Test", except feel for leaks at the duct joints at the mix manifold, and at the riser
duct.
c. Install the aft bulkhead lining from the forward cargo compartment, as referenced in 757 AMM
25-50-03.
d. Between BS 900 and 1040, install:
(1) The sidewall lining (panels and carpet risers), as referenced in 757 AMM 25-21-02.
(2) The floor panels, as referenced in 757 AMM 25-50-04 and 757 AMM 53-01-01.
(3) The floor covering, as referenced in 757 AMM 25-27-01.
(4) The passenger seats, as referenced in 757 AMM 25-25-01.
2. Set the L And R RECIRC FAN switch-lights to the ON position, on the pilot's overhead panel P5.
Refer to 757 AMM 21-00-01.
a. Remove the DO-NOT-OPERATE tag from the switch-lights.
b. Make sure the INOP lights go off, and the ON lights go on.
3. Set the L And R Pack selectors to the ON position, on the pilot's overhead panel P5. Refer to AMM
21-00-00.
a. Remove the DO-NOT-OPERATE tag from the selectors.
b. Make sure the PACK OFF lights go off.
4. Put the pneumatic system back to service condition. Refer to 757 AMM 36-00-00.
5. Put the electrical power back to service condition, as given in 757 AMM 24-41-00.
6. Put the airplane back to a serviceable condition.
Part VIII - Close Access - Group 2
1. Close access to the forward side of the Front Spar and the Upper Panel of the Wing Center Section.
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a. Install the air conditioning ducts on the mix manifold as shown in Figure 7.
b. Do a leak test of the air conditioning ducts as given in 757 AMM 21-23-06 "Do the Riser Duct
Installation Test", except feel for leaks at the duct joints at the mix manifold, and at the riser
duct.
c. Install the aft bulkhead lining from the forward cargo compartment, as referenced in 757 AMM
25-50-03.
2. Set the L And R RECIRC FAN switch-lights to the ON position, on the pilot's overhead panel P5.
Refer to 757 AMM 21-00-01.
a. Remove the DO-NOT-OPERATE tag from the switch-lights.
b. Make sure the INOP lights go off, and the ON lights go on.
3. Set the L And R Pack selectors to the ON position, on the pilot's overhead panel P5. Refer to 757
AMM 21-00-00.
a. Remove the DO-NOT-OPERATE tag from the selectors.
b. Make sure the PACK OFF lights go off.
4. Put the pneumatic system back to service condition. Refer to 757 AMM 36-00-00.
5. Put the electrical power back to service condition, as given in 757 AMM 24-41-00.
6. Put the airplane back to a serviceable condition.
PART IX - Thickness Measurement Inspection - Group 3 - Configuration 2 Airplanes
1. Review the maintenance records for the airplane to determine if there was a minimum of 0.005
inch new Secondary Fuel Barrier applied. If a minimum of 0.005 inch new Secondary Fuel Barrier
was applied, then no further action is required in that area.
2. If the thickness of the Secondary Fuel Barrier can not be determined from the maintenance records,
or if there was not a minimum of 0.005 inch of new Secondary Fuel Barrier added, then go to Step
3.
3. Supply external power to the airplane, as given in 757 AMM 24-41-00.
4. Release the pressure from the pneumatic system; refer to 757 AMM 36-00-00.
5. Set the L And R Pack selectors to the OFF position, on the pilot's overhead panel P5. Refer to
757 AMM 21-00-00.
a. Make sure the PACK OFF lights come on.
b. Put a DO-NOT-OPERATE tag on the selectors.
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6. Set the L And R RECIRC FAN switch-lights to the OFF position, on the pilot's overhead panel P5.
Refer to 757 AMM 21-00-01.
a. Make sure the INOP lights go on, and the ON lights go off.
b. Put a DO-NOT-OPERATE tag on the switch-lights.
7. Get access to the forward side of the Front Spar and the Upper Panel of the Wing Center Section.
a. Between BS 900 and 1040, remove:
(1) The passenger seats, as referenced in 757 AMM 25-25-01.
(2) The floor covering, as referenced in 757 AMM 25-27-01.
(3) The floor panels, as referenced in 757 AMM 25-50-04 and 757 AMM 53-01-01.
(4) The sidewall lining (panels and carpet risers), as referenced in 757 AMM 25-21-02.
b. Remove the air conditioning ducts from the mix manifold at the locations shown in Figure 1.
c. Remove the aft bulkhead lining from the forward cargo compartment, as referenced in 757
AMM 25-50-03.
8. Measure the thickness of the secondary fuel barrier applied to the locations specified in Figure 4
and Figure 5.
NOTE: The thickness measurements below includes a 0.002 inch layer of primer.
a. If the thickness is less than 0.007 inch, apply a minimum of 0.005 inch new Secondary Fuel
Barrier as given in Part X - Application of More Secondary Fuel Barrier.
b. If the thickness is greater than 0.012 inch, but less than or equal to 0.017 inch, apply a minimum
of 0.005 inch new Secondary Fuel Barrier as given in Part X - Application of More Secondary
Fuel Barrier.
NOTE: Thicknesses between 0.007 inch and 0.012 inch do not require the application of
the additional 0.005 inch secondary fuel barrier. Overcoating is allowed in this
thickness range to make the repair of adjacent areas more efficient.
c. If the thickness is greater than 0.017 inch, but less than or equal to 0.037 inch it must have a
transparent quality and it must be overcoated with a minimum of 0.005 inch of new Secondary
Fuel Barrier as given in Part X - Application of More Secondary Fuel Barrier.
NOTE: A transparent quality makes it easy to see a crack in the structure. An applied
secondary fuel barrier that is not transparent must be removed. Repair as given in
Step 10.
d. If the thickness is more than 0.037 inch, the secondary fuel barrier is NOT permitted. Repair
as given in Step 10.
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NOTE: Do NOT measure on top of the other sealants. There is no limit to the thickness of
secondary fuel barrier applied on top of BMS 5-95 (Pressure and Environmental Sealant,
Chromate Type) and BMS 5-142 (Low -Density Sealant).
9. Record the thickness data in the Inspection Worksheets given in Appendix A and keep the worksheet
with the airplane maintenance records for future reference.
10. Repair the Secondary Fuel Barrier where removal and reapplication is required.
a. Remove the secondary fuel barrier as given in 757 AMM 28-11-00.
NOTE: 757 AMM 28-11-00 does not directly address removal of large areas of BMS 5-81
sealant. It is permissible to remove the bulk of the sealant with the use of plastic or
wooden scrapers. Boeing production typically uses plastic scrapers.
b. If not already applied, apply a cap seal to the top side of the fasteners as specified in BSOPM
20-50-19. Refer to Figure 2, View J-J.
c. Apply the secondary fuel barrier as given in 757 AMM 28-11-00.
11. Close access to the forward side of the Front Spar and the Upper Panel of the Wing Center Section.
a. Install the air conditioning ducts on the mix manifold as shown in Figure 7.
b. Do a leak test of the air conditioning ducts as given in 757 AMM 21-23-06"Do the Riser Duct
Installation Test", except feel for leaks at the duct joints at the mix manifold, and at the riser
duct.
c. Install the aft bulkhead lining from the forward cargo compartment, as referenced in 757 AMM
25-50-03.
d. Between BS 900 and 1040, install:
(1) The sidewall lining (panels and carpet risers), as referenced in 757 AMM 25-21-02.
(2) The floor panels, as referenced in 757 AMM 25-50-04 and 757 AMM 53-01-01.
(3) The floor covering, as referenced in 757 AMM 25-27-01.
(4) The passenger seats, as referenced in 757 AMM 25-25-01.
12. Set the L And R RECIRC FAN switch-lights to the ON position, on the pilot's overhead panel P5.
Refer to 757 AMM 21-00-01.
a. Remove the DO-NOT-OPERATE tag from the switch-lights.
b. Make sure the INOP lights go off, and the ON lights go on.
13. Set the L And R Pack selectors to the ON position, on the pilot's overhead panel P5. Refer to 757
AMM 21-00-00.
a. Remove the DO-NOT-OPERATE tag from the selectors.
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b. Make sure the PACK OFF lights go off.
14. Put the pneumatic system back to service condition. Refer to 757 AMM 36-00-00.
15. Put the electrical power back to service condition, as given in 757 AMM 24-41-00.
16. Put the airplane back to a serviceable condition.
PART X - Application of More Secondary Fuel Barrier
1. Lightly sand the area with 180 grit aluminum oxide or finer abrasive paper. Remove as little of the
sealant film as possible. Do not sand to bare metal.
2. Remove residue with clean wipers.
3. Prepare the secondary fuel barrier sealant (BMS 5-81, Type II) as given in 757 AMM 28-11-00.
4. Apply one or two layers of BMS 5-81, Type II sealant with a flat, bristle brush. Take all reasonable
precautions to prevent or minimize sag areas.
a. For horizontal surfaces, let the sealant dry a minimum of 1/2 hour between layers.
b. For vertical surfaces, let the sealant dry a minimum of 2 hours between layers.
5. Refer to 757 AMM 28-11-00 for cure rates.
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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 one airplane.
NOTESQTYREFERENCESNAMETASKSTEP
At each end; put covers
over all open duct ends.
221-21-00Duct AssemblyDisconnect1
-2-Duct AssemblyRemove2
FIGURE 1: OPEN ACCESS - AIR CONDITIONING DUCT REMOVAL - GROUP 1, GROUP 2 AND GROUP 3
(SHEET 1 OF 1)
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BOEING SERVICE BULLETIN 757-57-0061
STA
900
RBL  STA
45.50  900
BL
LBL
45.50
FWD '
70.50  RBL  70.50
RBL  RBL  BL  LBI  LBL
45.50  24.75  24.75  45.50
• FRONT
SPAR
3 FUEL BARRIER  SECONDARY
A-A
FIGURE 2: INSPECTION - SECONDARY FUEL BARRIER - FRONT SPAR - GROUP 1 AND GROUP 3,
CONFIGURATION 1
(SHEET 1 OF 5)
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### Page 32 (OCR)

BOEING SERVICE BULLETIN 757-57-0061
- SHEAR
FITTING
SECONDARY
FUEL BARRIER  SECONDARY
FUEL BARRIER
1.00  13
MIN
UPPER PANEL  B-B  INBD
TYPICAL
1.0  SECONDARY
MIN  FRONT  FUEL BARRIER
SPAR WEB
SIDE
FITTING
1.0
MIN
1.0  1.50
MIN  FRONT SPAR  MIN
LOWER CHORD
SECONDARY
FUEL BARRIER
→ FWD
1.0  CAP SEAL
MIN
D-D
> FWD  TYPICAL
C-C
TYPICAL
V87885
FIGURE 2: INSPECTION - SECONDARY FUEL BARRIER - FRONT SPAR - GROUP 1 AND GROUP 3,
CONFIGURATION 1
(SHEET 2 OF 5)
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### Page 33 (OCR)

BOEING SERVICE BULLETIN 757-57-0061
1.00
- STIFFENER
MIN
1.00
MIN
- STIFFENER
FRONT SPAR
LOWER CHORD
FRONT
SPAR  SECONDARY
FUEL BARRIER
\ SECONDARY
FUEL BARRIER  1.50
FRONT
• CHORD-BODY  SPAR  CHORD-BODY
> FWD  → FWD
0.50 MIN
F-F
E-E
TYPICAL OUTBOARD OF BBL 45.50  TYPICAL INBOARD OF BBL 45.50
FRONT SPAR
SECONDARY
FUEL BARRIER
1.00  1.00
• SIDE  MIN  MIN  > INBD
FITTING
SKIN  G-G  FWD
TYPICAL
V87886
FIGURE 2: INSPECTION - SECONDARY FUEL BARRIER - FRONT SPAR - GROUP 1 AND GROUP 3,
CONFIGURATION 1
(SHEET 3 OF 5)
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### Page 34 (OCR)

BOEING SERVICE BULLETIN 757-57-0061
FRONT
SPAR
0.50
MIN
SECONDARY
FUEL BARRIER
SPLICE
ANGLE  SECONDARY
FUEL BARRIER
FRONT SPAR WEB
CHORD
FWD
H-H
TYPICAL OUTBOARD
OF BBL 45.50  1.00  1.00
MIN  MIN
INBD C  • STIFFENER
SECONDARY
FUEL BARRIER  FWD  I-I
TYPICAL
(2)  3)
4 (7 PLACES)  CAP SEAL
FWD
TYPICAL  J-J  N78545
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 one airplane.
FIGURE 2: INSPECTION - SECONDARY FUEL BARRIER - FRONT SPAR - GROUP 1 AND GROUP 3,
CONFIGURATION 1
(SHEET 4 OF 5)
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### Page 35

NOTESQTYREFERENCESNAMETASKSTEP
Remove dirt/debris from
the area
-Front SparClean1
(a)-Visual InspectionSecondary Fuel
Barrier
Identify2
(b) (c)-Detailed Visual In-
spection
Front SparExamine3
This is only necessary if
it is difficult to identify a
layer of Secondary Fuel
Barrier. Refer to BSOPM
20-41-05 and 20-60-01
for removal.
-BMS 3-23 or BMS
3-29 or BMS 3-35
Corrosion Inhibiting
Compound
Remove
See View J-J7Cap SealVerify4
(a) Look for a glossy finish, a clear to brown (or yellow) color, and a rubber-like texture.
(b) Use a flashlight. Hold it 10 to 20 degrees to the inspection area.
(c) Look for defective layers of secondary fuel barrier as specified in Part III of the Work Instructions.
FIGURE 2: INSPECTION - SECONDARY FUEL BARRIER - FRONT SPAR - GROUP 1 AND GROUP 3,
CONFIGURATION 1
(SHEET 5 OF 5)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: February 06, 2003
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BOEING SERVICE BULLETIN 757-57-0061

### Page 36 (OCR)

BOEING SERVICE BULLETIN 757-57-0061
STA
1040
STÁ
900
STA
1040
RBL  RBL
,70.50  ,45.50
RBL
→24.75
STA
900  BL
LBL
24.75  LBL
45.50
TOP PANEL  FWD I
WL
70.50  LBL  208.1  V87887
FIGURE 3: INSPECTION - SECONDARY FUEL BARRIER - UPPER PANEL - GROUP 1 AND GROUP 3,
CONFIGURATION 1
(SHEET 1 OF 7)
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### Page 37 (OCR)

BOEING SERVICE BULLETIN 757-57-0061
CREASE
SKIN  BEAM  1.00
PANEL  →  MIN  FLOOR
BEAM
SECONDARY  WEB
FUEL BARRIER
0.75  3)
MIN  SECONDARY
FUEL BARRIER
23
PLUS
CHORD  INBD  UPPER
PANEL
A-A
TYPICAL EDGE
RIGHT SIDE SHOWN, LEFT SIDE SAME  UPPER  PANEL  FLOOR BEAM  LOWER CHORD
B-B
TYPICAL BEAM
STA 975.5 TO 1040
PLUG
ASSEMBLY
• SUPPORT
0.50  1.00  BRACKET
MIN  MIN
* UPPER
PANEL
UPPER  SECONDARY
FWDE  PANEL  FUEL BARRIER  FWD <
SECONDARY
FUEL BARRIER
D-D  V87888
TYPICAL ALL BRACKETS
FIGURE 3: INSPECTION - SECONDARY FUEL BARRIER - UPPER PANEL - GROUP 1 AND GROUP 3,
CONFIGURATION 1
(SHEET 2 OF 7)
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### Page 38 (OCR)

BOEING SERVICE BULLETIN 757-57-0061
RBL  STUB  SECONDARY  RBL
70.50  BEAM  FUEL BARRIER  70.50  STUB  UPPER
BEAM  PANEL
0.25
MIN
1.00
PLUS  PANEL  UPPER  EXISTING  SEALANT  MIN  PLUS  CHORD  SECONDARY
CHORD  → INBD  FUEL BARRIER
E—E  → INBD
FWD
F-F
STA
900
BODY
SKIN  ~ FRAME
LONGERON  WL
SPLICE  - 208.10
EXISTING  2.00  UPPER
COMPOUND  MIN  PANEL
AND SEALANT
PLUS
CHORD  → INBD
SECONDARY  • FRONT
FUEL BARRIER  SPAR
G-G
LEFT SIDE SHOWN,  V87889
RIGHT SIDE SAME
FIGURE 3: INSPECTION - SECONDARY FUEL BARRIER - UPPER PANEL - GROUP 1 AND GROUP 3,
CONFIGURATION 1
(SHEET 3 OF 7)
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### Page 39 (OCR)

BOEING SERVICE BULLETIN 757-57-0061
BL  LBL  LBL  LBL
24.75  1.00  45.50  70.50
MIN  • FRAME
(2) 3
STA
1040
STA
1024
'FLOOR  UPPER  \FLOOR  \ FLOOR
BEAM  PANEL  BEAM  BEAM
PLUS
INBD  CHORD
H~H
FWD
STA
1040
1.00
1.00 MIN  MIN
1.00 MIN  1.00
MIN
LBL
70.50
FRAME
FRAME  KICK  _1.00
MIN
UPPER  FITTING  1.00
PANEL  MIN  2.00
MIN
DRAIN PATH  REAR SPAR
DO NOT BLOCK  FWD
I-I  - STA
TYPICAL OUTSIDE WALLS  1040
OF KICK FITTING
EXISTING
SEALANT
UPPER
PANEL
REAR SPAR  KICK FITTING  INBD
UPPER CHORD
J-J
FIGURE 3: INSPECTION - SECONDARY FUEL BARRIER - UPPER PANEL - GROUP 1 AND GROUP 3,
CONFIGURATION 1
(SHEET 4 OF 7)
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### Page 40 (OCR)

BOEING SERVICE BULLETIN 757-57-0061
STA
KICK  1040  1.00
FITTING  1.00  1.00_  MIN
MIN  MIN
→ SPACER
- FRAME
UPPER  EXISTING
PANEL  FILLET AND
INJECTION
SEAL
FLOOR  STA  DRAIN PATH -
FITTING  BEAM WEB  1040  DO NOT BLOCK  - REAR
1.00  SPAR
MIN  K—K  WD C
PRE-PACK
SEAL  TYPICAL, INSIDE WALLS
OF KICK FITTING
•PRESSURE
UPPER  DECK
PANEL  REAR  SPAR  DRAIN PATH -  - 1.00  MIN  ATTACH  ANGLE
DO NOT BLOCK
FWD <
L-L
PLUS CHORD  DOUBLE  900  STA  EXISTING  FILLET AND  EXISTING  1040  STA  DOUBLE  PLUS CHORD
INJECTION  FILLET AND
SEAL  INJECTION
SEAL
0.75  2.00  2.00  0.75
MIN  MIN  UPPER  PANEL  FRONT  SPAR  REAR  SPAR  PANEL  UPPER  MIN  MIN
• FWD  > FWD
1.00
MIN
M-M  N-N
LEFT SIDE SHOWN,  LEFT SIDE SHOWN,
RIGHT SIDE SAME  RIGHT SIDE SAME
FIGURE 3: INSPECTION - SECONDARY FUEL BARRIER - UPPER PANEL - GROUP 1 AND GROUP 3,
CONFIGURATION 1
(SHEET 5 OF 7)
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### Page 41 (OCR)

BOEING SERVICE BULLETIN 757-57-0061
RBL
24.75
WL
208.1
→ FLOOR
BEAM
1.00
MIN
UPPER PANEL
0-0
TYPICAL FROM STA 900 TO STA 975.5
— FLOOR
TENSION  BEAM
FITTING
1.00
MIN  1.00
MIN
•UPPER PANEL
P-P
TYPICAL AT TENSION TIE FITTINGS  N78557
(15 PLACES)
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 one airplane.
FIGURE 3: INSPECTION - SECONDARY FUEL BARRIER - UPPER PANEL - GROUP 1 AND GROUP 3,
CONFIGURATION 1
(SHEET 6 OF 7)
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### Page 42

NOTESQTYREFERENCESNAMETASKSTEP
Remove dirt/debris from
the area
-Upper PanelClean1
(a)-Visual InspectionSecondary Fuel
Barrier
Identify2
(b) (c)-Detailed Visual In-
spection
Upper PanelExamine3
This is only necessary if
it is difficult to identify a
layer of Secondary Fuel
Barrier. Refer to BSOPM
20-41-05 and 20-60-01
for removal.
-BMS 3-23 or BMS
3-29 or BMS 3-35
Corrosion Inhibiting
Compound
Remove
(a) Look for a glossy finish, clear to brown (or yellow) color, and a rubber-like texture.
(b) Use a flashlight. Hold it 10 to 20 degrees to the inspection area.
(c) Look for defective layers of secondary fuel barrier as specified in Part III - of the Work Instructions.
FIGURE 3: INSPECTION - SECONDARY FUEL BARRIER - UPPER PANEL - GROUP 1 AND GROUP 3,
CONFIGURATION 1
(SHEET 7 OF 7)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
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BOEING SERVICE BULLETIN 757-57-0061

### Page 43 (OCR)

BOEING SERVICE BULLETIN 757-57-0061
INSPECTION POINTS
(SEE APPENDIX A)
• FSW (FRONT SPAR WEB)
STA
900  • FSS (FRONT SPAR STIFFENER)
A BFS (BODY FRAME STIFFENER)
O BFAW (BODY FRAME ASSEMBLY WEB)
900 BFAW 1  STA
B  FSS 60  4.0
FSS 56  5.0
(TYPICAL BETWEEN
RBL  FSS 51  FSW INSPECTION POINTS)
70.50  FSS 46
/ FSS 41  FSS 36
FSW  BL  1 FRONT SPAR
14
FSS 31
BFS 1  FSS 26
FSS 21
FSS 64  FSS 16
- FSS 11
BFS 2 C
- FSS 6
FSS 59  • FSS 1  LBL
70.50
FSS 55
FSS 50
• BFAW 2
FSS  45  •
- FSW 1
FSS 40
FWD C  FSS 35  • FSS 5  • BFS 4
FSS 25
FSS 10
FSS 30  FSS 20  BFS 3  V87892
FSS 15
FIGURE 4: INSPECTION - THICKNESS MEASUREMENTS - FRONT SPAR - GROUP 1 AND GROUP 3
(SHEET 1 OF 3)
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### Page 44 (OCR)

BOEING SERVICE BULLETIN 757-57-0061
INSPECT THIS SIDE
OF STIFFENER ONLY
FRONT SPAR WEB
x/2
- STIFFENER
STIFFENER  2) TYPICAL FSS  (2) TYPICAL FSW
(64 PLACES)  (14 PLACES)
A-A
TYPICAL
FRONT
FRAME  UPPER  SPAR
ASSY  PANEL
CAP
SEAL
TYPICAL BFAW
(2 PLACES)
x/2
FWD C  FRONT  SPAR  _INBD  • FRAME  ASSY
B-B  SKIN
TYPICAL  FWD
C-C
TYPICAL
CAP SEAL  FRONT  SPAR  1X2 (4 PLACES)  TYPICAL BFS
(TYPICAL)
FRAME
ASSY
• STRINGER
(TYPICAL)
SKIN
D-D  V87893
TYPICAL
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 one airplane.
FIGURE 4: INSPECTION - THICKNESS MEASUREMENTS - FRONT SPAR - GROUP 1 AND GROUP 3
(SHEET 2 OF 3)
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### Page 45

NOTESQTYREFERENCESNAMETASKSTEP
Remove dirt/debris from
the area
Front SparClean1
(a) (b) (c)Secondary Fuel
Barrier
Measure/ Make
Sure/ Record
2
See View A-A14FSWFront Spar Web
See View A-A64FSSFront Spar Stiffen-
ers
See View B-B2BFAWBody Frame Assy
Web
See Views C-C and D-D4BFSBody Frame Stiffen-
er
(a) Use a Non-Conductive Coating Thickness Gage to measure the thickness of the applied secondary
fuel barrier. (Refer to Paragraph 2.F., Special Tooling Necessary to do this Service Bulletin.)
(b) Deleted - See Accomplishment Instructions for thickness limits.
(c) Record the measurements on the Inspection Worksheets in Appendix A.
FIGURE 4: INSPECTION - THICKNESS MEASUREMENTS - FRONT SPAR - GROUP 1 AND GROUP 3
(SHEET 3 OF 3)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
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BOEING SERVICE BULLETIN 757-57-0061

### Page 46 (OCR)

BOEING SERVICE BULLETIN 757-57-0061
INSPECTION POINTS
(SEE APPENDIX A)
STA  + RSOB (RIGHT SIDE OF BODY)
1040
.  * LSOB (LEFT SIDE OF BODY)
STA
900
• RTP (RIGHT TOP PANEL)
• LTP (LEFT TOP PANEL)
• FB (FLOOR BEAM)
RTP 6  1040  STA  FB 10
RSOB 10  RTP. 10  70.50  RBL  45.50  RBL
TOP PANEL  $ FB 20 24.75
RTP 14  BL
FB 1  FB 30  <0  LBL
RSOB 1  RTP 7  ,LTP 4  .24.75  LBL
STA  RTP 1  FB 40  FB 50  45.50
900
À 70.50  LBL
LSOB 10
FB 11
LTP 14
RTP '11  LTP 8
FB 21
LTP 1
FB  31  •LTP 9
LTP 5 /  WL  LSOB 1
FB 41  208.1
V87894
FIGURE 5: INSPECTION - THICKNESS MEASUREMENTS - UPPER PANEL - GROUP 1 AND GROUP 3
(SHEET 1 OF 5)
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### Page 47 (OCR)

BOEING SERVICE BULLETIN 757-57-0061
STA  STA  STA  STA  STA  STA  STA  STA STA
900  920  940  960  984  996  1020 1032.3 1040
-11.0-
13.0  →B
(TYPICAL)  10 PLACES PER  11.0→
-3.0  FLOOR BEAM  FWDS  13.0
5.0  (TYPICAL)
A-A  3.0  T
TYPICAL FLOOR BEAM  5.0
INSPECTION POINTS
INSPECT THIS SIDE
OF THE WEB ONLY
0.50  12
FLOOR BEAM  UPPER PANEL
→INBD
B-B
TYPICAL FLOOR BEAM INSPECTION POINT
V87895
FIGURE 5: INSPECTION - THICKNESS MEASUREMENTS - UPPER PANEL - GROUP 1 AND GROUP 3
(SHEET 2 OF 5)
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### Page 48 (OCR)

BOEING SERVICE BULLETIN 757-57-0061
FRONT  REAR
SPAR  STA  STA  STA  STUB  STA  STA  STA  SPAR
920  940  960  BEAM  980  1000  1020
LSOB 1  LSOB 10
•11.0 →  D  •11.0
13.0  UPPER  INBD  | 13.0
(TYPICAL)  PANEL  PLUS  CHORD  10 PLACES  (TYPICAL)
-3.0  FWD C  3.0 -
5.0  5.0
TYPICAL SIDE-OF-BODY INSPECTION POINTS
LEFT SIDE SHOWN, RIGHT SIDE OPPOSITE
UPPER PANEL OF
CREASE  CENTER SECTION
BEAM
BODY
SKIN  0.5
INBD
PLUS
CHORD
D-D  V87896
FIGURE 5: INSPECTION - THICKNESS MEASUREMENTS - UPPER PANEL - GROUP 1 AND GROUP 3
(SHEET 3 OF 5)
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### Page 49 (OCR)

BOEING SERVICE BULLETIN 757-57-0061
BEAM  FLOOR  12) TYPICAL  STA  984  STA  996  REAR  SPAR
RBL
70.50
x/2  x/2
0000000000
FWD <
* Y/2 →  Y/2 →
FLOOR
• BEAM
UPPER
PANEL
RBL
FB  45.50
(TYPICAL)
F—
TYPICAL (OUTBOARD) UPPER PANEL  INSPECTION POINTS
(RIGHT SIDE SHOWN, LEFT  SIDE SAME)
(12 PLACES)
BEAM  FLOOR  STA  984  FLOOR BEAM  WEB TO FLOOR  996  STA  FB  (TYPICAL) SPAR  REAR
BEAM WEB
RBL
45.50
TYPICAL
24.0  24.0  UPPER
FWD<  26.0  26.0  PANEL
FLOOR
BEAM
x/2  x/2
RBL
24.75
E—E
TYPICAL (INBOARD) UPPER PANEL INSPECTION POINTS
(RIGHT SIDE SHOWN, LEFT SIDE SAME)
(16 PLACES)
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 one airplane.
FIGURE 5: INSPECTION - THICKNESS MEASUREMENTS - UPPER PANEL - GROUP 1 AND GROUP 3
(SHEET 4 OF 5)
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Work - See page 1 for details.  49 of 56

### Page 50

NOTESQTYREFERENCESNAMETASKSTEP
Remove dirt/debris from
the area
Front Spar and
Upper Panel
Clean1
(a) (b) (c)-Secondary Fuel
Barrier
Measure/ Make
Sure/ Record
2
10 locations each, on the
right and left side. See
View A-A and B-B
50FBFloor Beam
10 locations each, on the
right and left side. See
Views C-C and D-D
20RSOB and LSOBSide of Body
14 locations each, on the
right and left side. See
View E-E and View F-F
28RTP and LTPUpper Panel
(a) Use a Non-Conductive Coating Thickness Gage to measure the thickness of the applied secondary
fuel barrier. (Refer to Paragraph 2.F., Special Tooling Necessary to do this Service Bulletin.)
(b) Deleted - See Accomplishment Instructions for thickness limits.
(c) Record the measurements on the Inspection Worksheets in Appendix A.
FIGURE 5: INSPECTION - THICKNESS MEASUREMENTS - UPPER PANEL - GROUP 1 AND GROUP 3
(SHEET 5 OF 5)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: February 06, 2003
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BOEING SERVICE BULLETIN 757-57-0061

### Page 51 (OCR)

BOEING SERVICE BULLETIN 757-57-0061
STA
900
RBL  STA
79.50  900
RBL
45.50
RBL
' 24.75
LBL
=24.75  LBL
/ 45.50
LBL
70.50
FWD <
SECONDARY
ALLOWED  OVERSPRAY  FRONT  FUEL BARRIER
FRONT  SPAR WEB
SPAR  WL
166
FRONT SPAR  1.5
LOWER CHORD  BL  FRONT SPAR WEB  MIN
RBL  LBL  FRONT SPAR
24.75  24.75  LOWER CHORD
1.5
MIN
→→FWD
B-B
TYPICAL MINIMUM COVERAGE COMMON
TO FRONT SPAR WEB AND LOWER CHORD
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 one airplane.
FIGURE 6: INSPECTION AND APPLICATION OF THE SECONDARY FUEL BARRIER - GROUP 2
(SHEET 1 OF 2)
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### Page 52

NOTESQTYPART NUMBERNAMETASKSTEP
It must be a minimum of
1.50 inches
-BMS 5-81Secondary Fuel
Barrier
Measure / Make
Sure
1
FIGURE 6: INSPECTION AND APPLICATION OF THE SECONDARY FUEL BARRIER - GROUP 2
(SHEET 2 OF 2)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
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BOEING SERVICE BULLETIN 757-57-0061

### Page 53

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 one airplane.
NOTESQTYREFERENCESNAMETASKSTEP
-221-21-00Duct AssemblyInstall1
At each end; put covers
over all open duct ends.
2-Duct AssemblyConnect2
FIGURE 7: CLOSE ACCESS - AIR CONDITIONING DUCT INSTALLATION - GROUP 1, GROUP 2 AND
GROUP 3
(SHEET 1 OF 1)
Export Controlled ECCN: 9E991 - BOEING
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BOEING SERVICE BULLETIN 757-57-0061

### Page 54

Record the thickness measurements from Figures 3 and 4 on the following worksheets.
FRONT SPAR - STIFFENERS (FSS)
0. in.FSS 490. in.FSS 330. in.FSS 170. in.FSS 1
0. in.FSS 500. in.FSS 340. in.FSS 180. in.FSS 2
0. in.FSS 510. in.FSS 350. in.FSS 190. in.FSS 3
0. in.FSS 520. in.FSS 360. in.FSS 200. in.FSS 4
0. in.FSS 530. in.FSS 370. in.FSS 210. in.FSS 5
0. in.FSS 540. in.FSS 380. in.FSS 220. in.FSS 6
0. in.FSS 550. in.FSS 390. in.FSS 230. in.FSS 7
0. in.FSS 560. in.FSS 400. in.FSS 240. in.FSS 8
0. in.FSS 570. in.FSS 410. in.FSS 250. in.FSS 9
0. in.FSS 580. in.FSS 420. in.FSS 260. in.FSS 10
0. in.FSS 590. in.FSS 430. in.FSS 270. in.FSS 11
0. in.FSS 600. in.FSS 440. in.FSS 280. in.FSS 12
0. in.FSS 610. in.FSS 450. in.FSS 290. in.FSS 13
0. in.FSS 620. in.FSS 460. in.FSS 300. in.FSS 14
0. in.FSS 630. in.FSS 470. in.FSS 310. in.FSS 15
0. in.FSS 640. in.FSS 480. in.FSS 320. in.FSS 16
FRONT SPAR - WEB (FSW)
0. in.FSW 80. in.FSW 1
0. in.FSW 90. in.FSW 2
0. in.FSW 100. in.FSW 3
0. in.FSW 110. in.FSW 4
0. in.FSW 120. in.FSW 5
0. in.FSW 130. in.FSW 6
0. in.FSW 140. in.FSW 7
BODY FRAME - STIFFENER (BFS)
Right SideLeft Side
0. in.BFS 10. in.BFS 3
0. in.BFS 20. in.BFS 4
Appendix A: RECORD OF THICKNESS MEASUREMENTS
(SHEET 1 OF 3)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: February 06, 2003
757-57-0061Revision 3 December 07, 2012
54 of 56
BOEING SERVICE BULLETIN 757-57-0061

### Page 55

BODY FRAME ASSEMBLY WEB (BFAW)
Right SideLeft Side
0. in.BFAW 10. in.BFAW 2
SIDE OF BODY (SOB)
Right SideLeft Side
0. in.RSOB 10. in.LSOB 1
0. in.RSOB 20. in.LSOB 2
0. in.RSOB 30. in.LSOB 3
0. in.RSOB 40. in.LSOB 4
0. in.RSOB 50. in.LSOB 5
0. in.RSOB 60. in.LSOB 6
0. in.RSOB 70. in.LSOB 7
0. in.RSOB 80. in.LSOB 8
0. in.RSOB 90. in.LSOB 9
0. in.RSOB 100. in.LSOB 10
UPPER PANEL (TP)
Right SideLeft Side
0. in.RTP 10. in.LTP 1
0. in.RTP 20. in.LTP 2
0. in.RTP 30. in.LTP 3
0. in.RTP 40. in.LTP 4
0. in.RTP 50. in.LTP 5
0. in.RTP 60. in.LTP 6
0. in.RTP 70. in.LTP 7
0. in.RTP 80. in.LTP 8
0. in.RTP 90. in.LTP 9
0. in.RTP 100. in.LTP 10
0. in.RTP 110. in.LTP 11
0. in.RTP 120. in.LTP 12
0. in.RTP 130. in.LTP 13
Appendix A: RECORD OF THICKNESS MEASUREMENTS
(SHEET 2 OF 3)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: February 06, 2003
757-57-0061Revision 3 December 07, 2012
55 of 56
BOEING SERVICE BULLETIN 757-57-0061

### Page 56

Right SideLeft Side
0. in.RTP 140. in.LTP 14
FLOOR BEAM (FB)
0.FB 410.FB 310.FB 210.FB 110.FB 1
0.FB 420.FB 320.FB 220.FB 120.FB 2
0.FB 430.FB 330.FB 230.FB 130.FB 3
0.FB 440.FB 340.FB 240.FB 140.FB 4
0.FB 450.FB 350.FB 250.FB 150.FB 5
0.FB 460.FB 360.FB 260.FB 160.FB 6
0.FB 470.FB 370.FB 270.FB 170.FB 7
0.FB 480.FB 380.FB 280.FB 180.FB 8
0.FB 490.FB 390.FB 290.FB 190.FB 9
0.FB 500.FB 400.FB 300.FB 200.FB 10
Appendix A: RECORD OF THICKNESS MEASUREMENTS
(SHEET 3 OF 3)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: February 06, 2003
757-57-0061Revision 3 December 07, 2012
56 of 56
BOEING SERVICE BULLETIN 757-57-0061

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