# Boeing Alert Service Bulletin 767-57A0131: Revision 1

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- Document: [Boeing Alert Service Bulletin 767-57A0131](https://openairdocs.org/service-documents/boeing/767-57a0131.md)
- Title as filed: U.S. DOT/FAA - SB-767-57A0131-01
- Pages: 75
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## Text

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### Page 1

Commercial 
Airplanes
767
Service Bulletin
Number: 767-57A0131
Original Issue: October 30, 2012
Revision 1: May 08, 2013
ATA System: 5750
SUBJECT: WINGS - Trailing Edge and Trailing Edge Devices - Outboard Flap Support Rib Nut
Fracture Inspection
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 © 2012 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Unpublished Work.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: October 30, 2012
767-57A0131Revision 1: May 08, 2013
1 of 75
2.0

### Page 2

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BOEING SERVICE BULLETIN 767-57A0131
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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 7
B. Concurrent Requirements ...................................... 1 7
C. Reason ................................................ 1 7
D. Description .............................................. 1 8
E. Compliance .............................................. 1 8
F. Approval ............................................... 2 1
G. Manpower .............................................. 2 1
H. Weight and Balance Changes .................................... 2 3
I. Electrical Load Data ......................................... 2 3
J. References .............................................. 2 3
1. Existing Data: ......................................... 2 3
2. Data Supplied with this Service Bulletin: ........................... 2 3
3. Installation Drawings Used in the Preparation of this Service Bulletin: ........... 2 3
K. Publications Affected ........................................ 2 4
L. Interchangeability and Intermixability of Parts ........................... 2 4
M. Software Accomplishment Summary ................................ 2 4
2. MATERIAL INFORMATION ........................................ 2 5
A. Material - Price and Availability ................................... 2 5
B. Industry Support Information .................................... 2 6
C. Parts Necessary for Each Airplane ................................. 2 6
1. Kits/Parts ............................................ 2 6
2. Parts and Materials Supplied by the Operator ........................ 2 8
3. Parts Modified and Reidentified ................................ 3 2
4. Parts Removed and Not Replaced .............................. 3 2
D. Parts Necessary to Change Spares ................................. 3 2
E. Special Tooling - Price and Availability ............................... 3 2
F. Special Tooling Necessary to do this Service Bulletin ....................... 3 2
3. ACCOMPLISHMENT INSTRUCTIONS .................................. 3 3
A. GENERAL INFORMATION ..................................... 3 3
B. WORK INSTRUCTIONS ....................................... 3 4
FIGURE 1: CAP SEAL DETAILED INSPECTION FOR SUPPORT RIB # 1 ............... 4 0
FIGURE 2: CAP SEAL DETAILED INSPECTION FOR SUPPORT RIB # 2 ............... 4 2
FIGURE 3: CAP SEAL DETAILED INSPECTION FOR SUPPORT RIB # 7 ............... 4 4
FIGURE 4: CAP SEAL DETAILED INSPECTION FOR SUPPORT RIB # 8 ............... 4 6
FIGURE 5: FASTENER DETAILED INSPECTION ............................ 4 8
FIGURE 6: FASTENER REPLACEMENTS FOR SUPPORT RIB # 1 .................. 4 9
FIGURE 7: FASTENER REPLACEMENTS FOR SUPPORT RIB # 2 .................. 5 3
FIGURE 8: FASTENER REPLACEMENTS FOR SUPPORT RIB # 7 .................. 5 7
FIGURE 9: FASTENER REPLACEMENTS FOR SUPPORT RIB # 8 .................. 6 1
FIGURE 10: NUT MEASUREMENT FOR CORRECT TYPE [Group 2] .................. 6 5
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FIGURE 11: NUT MEASUREMENT FOR CORRECT TYPE [Group 2-3] ................. 6 7
APPENDIX A: PART NUMBERS AND QUANTITIES BY SUPPORT RIB NUMBER ............ 6 9
APPENDIX B: NOMINAL HOLE DIAMETERS FOR OUTBOARD TRAILING EDGE FLAP SUPPORT RIB AND
ACTUATOR SUPPORT FITTINGS .............................. 7 5
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Commercial 
Airplanes
767
Service Bulletin
Revision Transmittal SheetNumber: 767-57A0131Original Issue: October 30, 2012
Revision 1: May 08, 2013
ATA System: 5750
SUBJECT: WINGS - Trailing Edge and Trailing Edge Devices - Outboard Flap Support Rib Nut
Fracture Inspection
This revision includes all pages of the service bulletin.
COMPLIANCE INFORMATION RELATED TO THIS REVISION
No more work is necessary on the airplanes changed or inspected in accordance with the original issue of this
service bulletin.
REASON FOR REVISION
This revision is sent to add new Top Kit information and to clarify access and repair procedures.
These sections were changed:
1. In Summary, Background, added validation information.
2. In Paragraph 1.C., Reason, added validation information.
3. In Paragraph 2.A., Material - Price and Availability, changed the ROLT for the two existing kits.
4. In Paragraph 2.A., Material - Price and Availability, added information about new oversized Top Kits.
5. In Paragraph 2.C.1., Kits/Parts, added detailed information about new oversized Top Kits.
6. In Paragraph 2.C.2., Parts and Material Supplied by Operator, changed footnotes (a) and (c).
7. In Paragraph 3.A., General Information, added an item about special tools.
8. In Paragraph 3.B., Work Instructions, clarified the Note in Part 3.
9. In Paragraph 3.B., Work Instructions, added information about optional access for Part 3.
10. In Paragraph 3.B., Work Instructions, added a task to Part 3.
11. In Paragraph 3.B., Work Instructions, clarified the Note in Part 5.
12. In Paragraph 3.B., Work Instructions, added information about optional access for Part 5.
13. In Paragraph 3.B., Work Instructions, added a task to Part 5.
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14. In Paragraph 3.B., Work Instructions, clarified the More Data column of Step 3, Substep 1 of Figures
6, 7, 8 and 9.
15. In Paragraph 3.B., Work Instructions, added a footnote (a) and applied it to Steps 2 and 3 of Figures
6, 7, 8 and 9.
16. In Paragraph 3.B., Work Instructions, added a footnote (b) and applied it to Step 3 of Figures 6, 7, 8
and 9.
17. In Appendix A, added a footnote about hole diameter differences and applied it to the Hole Diameter
heading for all tables.
18. In Appendix A, changed the hole diameter range for fasteners in three of the tables.
19. Added Appendix B.
The data given in Information Notice 767-57A0131 IN 01 is included in this revision.
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.
As a part of a service bulletin validation program, this inspection and change was completed on airplane VN951
by Service Bulletin 767-57A0131 Original Issue before the release of Revision 1 of this service bulletin. The
inspection and change completed on airplane VN951 by Service Bulletin 767-57A0131 Original Issue is equivalent
to the release of Revision 1 of this service bulletin. Airplane VN951 has the configuration of a Group 2 airplane.
REVISION HISTORY
October 30, 2012Original Issue:
May 08, 2013Revision 1:
Export Controlled ECCN: 9E991 - BOEING
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BOEING SERVICE BULLETIN 767-57A0131

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Commercial 
Airplanes
767
Service Bulletin
SummaryNumber: 767-57A0131Original Issue: October 30, 2012
Revision 1: May 08, 2013
ATA System: 5750
SUBJECT: WINGS - Trailing Edge and Trailing Edge Devices - Outboard Flap Support Rib Nut
Fracture Inspection
CONCURRENT REQUIREMENTS
None.
BACKGROUND
Accomplishment of this service bulletin will find and replace any cracked, corroded or incorrect nuts and bolts
on the #1, #2, #7 and #8 outboard flap support ribs. Cracked, corroded or incorrect nuts and bolts could lead to
additional nut and bolt damage in the joint which could result in loss of the outboard flap. Continued safe flight
and landing could be affected after the departure of a flap during takeoff or landing.
An operator reported two fractured and corroded nuts on the outboard flap, support rib #2 on an airplane with
54,953 hours and 49,519 cycles. It was found that the incorrect nuts (QTY 8) were installed on support ribs #2
and #7. The correct nuts for this installation are BACN10HR12 nuts while NAS1804-12 nuts were found to have
been installed. The torque for the BACN10HR12 nuts is 3300 to 4300 in-lbs while the torque for the NAS1804-12
nuts is 2400 to 3500 in-lbs. Overtorqued NAS1804-12 nuts are at risk of fracture. Fractured nuts may create a
breach in the cap seal and allow moisture to contact the nuts, resulting in corrosion. Nut fractures could lead to
additional nut or bolt fractures within that support rib. Additional fractures can cause the joint to be compromised.
This service bulletin provides instructions to inspect the nuts and bolts common to the #1, #2, #7 and #8 outboard
flap support ribs and replaces any cracked, corroded or incorrect nuts and/or bolts that are found.
Boeing Fleet Team Digest (FTD) 767 FTD 57-12003 is related to this service bulletin.
Boeing Service Related Problem (SRP) 767-SRP-57-0257 is related to this service bulletin.
As a part of a service bulletin validation program, this inspection and change was completed on airplane VN951
by Service Bulletin 767-57A0131 Original Issue before the release of Revision 1 of this service bulletin. The
inspection and change completed on airplane VN951 by Service Bulletin 767-57A0131 Original Issue is equivalent
to the release of Revision 1 of this service bulletin. Airplane VN951 has the configuration of a Group 2 airplane.
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
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ReferenceAffectedPlanning Data
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 AffectedNoPublications 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/PartsYesKits/Parts Required
Paragraph 2.C.2., Parts and Materials Supplied
by the Operator
YesOperator Supplied Material
Paragraph 2.F., Special Tooling Necessary to
do this Service Bulletin
NoSpecial Tooling Required
ACTION
Group 1:
Do a Detailed Inspection of the sealant on the nuts common to Outboard Flap Support Ribs #1, #2, #7 and #8.
Remove sealant if damaged and do a Detailed Inspection of the fasteners for cracks and corrosion. If any cracked
or corroded fasteners are found, replace all four fasteners on that Support Rib. Repeat the Detailed Inspection.
Install new bolts, washers and nuts.
Group 2-3:
Do a Detailed Inspection of the sealant on the nuts common to Outboard Flap Support Ribs #1, #2, #7 and #8.
Remove sealant if damaged and do a Detailed Inspection of the fasteners for cracks and corrosion. If any
corroded fasteners are found, replace that fastener. If any cracked fasteners are found, replace all four fasteners
on that Support Rib. Repeat the Detailed Inspection. Make sure the correct nuts are installed. If any incorrect
nuts are found, replace the nut, bolt and washers.
EFFECTIVITY
767-200, -300, -300F and -400ER airplanes. Refer to Paragraph 1.A.1., Airplanes, for the list of affected airplanes.
COMPLIANCE
The Federal Aviation Administration (FAA) will possibly release an Airworthiness Directive related to this service
bulletin. The Airworthiness Directive will make the compliance tasks and times given in this service bulletin
mandatory.
Refer to Paragraph 1.E., Compliance.
INDUSTRY SUPPORT INFORMATION
Boeing warranty remedies are available for airplanes in warranty as of May 29, 2012. Please refer to Paragraph
2.B., Industry Support Information.
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BOEING SERVICE BULLETIN 767-57A0131

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MANPOWER
Refer to Paragraph 1.G., Manpower.
MATERIAL INFORMATION
Boeing Supplied Kits/Parts.
Refer to Paragraph 2.A., Material - Price and Availability.
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BOEING SERVICE BULLETIN 767-57A0131
REAR SPAR
GROUP1:
DO A DETAILED INSPECTION OF THE SEALANT  INBD
ON THE NUTS COMMON TO THE OUTBOARD
FLAP SUPPORT RIBS 1, 2, 7 AND 8. REMOVE
SEALANT IF DAMAGED AND DO A DETAILED  FWD
INSPECTION OF THE FASTENERS FOR CRACKS
AND CORROSION. IF ANY CRACKED OR
CORRODED FASTENERS ARE FOUND, REPLACE
ALL FOUR FASTENERS ON THAT SUPPORT RIB.
REPEAT THE DETAILED INSPECTION. INSTALL  LEFT SIDE SHOWN, RIGHT SIDE OPPOSITE
NEW BOLTS, WASHERS AND NUTS.
GROUP 2 AND 3:
DO A DETAILED INSPECTION OF THE SEALANT ON THE NUTS
COMMON TO THE OUTBOARD FLAP SUPPORT RIBS 1, 2, 7 AND 8.
REMOVE SEALANT IF DAMAGED AND DO A DETAILED INSPECTION
OF THE FASTENERS FOR CRACKS AND CORROSION. IF ANY
CORRODED FASTENERS ARE FOUND, REPLACE THAT FASTENER.
IF ANY CRACKED FASTENERS ARE FOUND, REPLACE ALL FOUR
FASTENERS ON THAT SUPPORT RIB. REPEAT THE DETAILED
INSPECTION. MAKE SURE THE CORRECT NUTS ARE INSTALLED. IF  2183013
ANY INCORRECT NUTS ARE FOUND, REPLACE THE NUT, BOLT AND
WASHERS.
Original Issue: October 30, 2012
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Commercial 
Airplanes
767
Service Bulletin
Number: 767-57A0131
Original Issue: October 30, 2012
Revision 1: May 08, 2013
ATA System: 5750
SUBJECT: WINGS - Trailing Edge and Trailing Edge Devices - Outboard Flap Support Rib Nut
Fracture Inspection
1.    PLANNING INFORMATION
A. Effectivity
1. Airplanes
This service bulletin is for the airplane(s) shown below.
Refer to Service Bulletin Index D624T001 Part 3 for Airplane Variable Number, Line Number, and
Serial Number data.
DESCRIPTIONCONFIGURATIONGROUP
767-200 and-300 Airplanes that have a line number 1 through 200.
These airplanes were delivered with H-11 bolts installed in the
Outboard Flap Support Ribs.
-1
767-200, -300 and -300F Airplanes that have a line number 201
through 920. These airplanes were delivered with BACB30US* bolts
installed in the Outboard Flap Support Ribs.
-2
767-400ER Airplanes that have a line number 758 through 878. These
airplanes were delivered with BACB30US* bolts installed in the
Outboard Flap Support Ribs.
-3
Airplane Models:
767-200, 767-300, 767-300F, 767-400ER
GroupVariable Number
1VA001 - VA020
1VA301 - VA315
1VA501 - VA530
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GroupVariable Number
1VA701 - VA712
2VA713 - VA719
1VA801 - VA810
1VB001 - VB002
1VB051 - VB055
1VB101 - VB125
1VB201 - VB202
1VB251 - VB253
1VB281 - VB284
1VB301 - VB302
1VB321 - VB325
2VB326 - VB332
1VB371 - VB373
1VB401
2VB441 - VB444
1VE001 - VE003
1VE021 - VE023
1VE041 - VE043
1VE061 - VE069
1VE083 - VE084
2VE085 - VE086
1VE101 - VE103
2VE104
1VE116 - VE117
2VE118
1VE121 - VE126
1VE141 - VE145
2VE146 - VE152
2VE171 - VE172
2VF001 - VF002
2VF041 - VF042
2VF051
2VF061 - VF062
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GroupVariable Number
2VF071 - VF072
2VF091 - VF093
2VF101 - VF102
2VF161 - VF162
2VF171 - VF172
2VF180 - VF184
2VF251
1VK001 - VK006
2VK007 - VK016
1VK021 - VK022
1VK031 - VK040
2VK041 - VK056
1VK081 - VK085
2VK086 - VK113
2VK131 - VK133
2VK141 - VK148
2VK161 - VK164
2VK171
2VK181
2VK186
1VL001
2VL002 - VL006
1VL011
2VL701 - VL703
2VL751 - VL755
2VL806 - VL807
2VL871 - VL873
2VL891 - VL900
2VL911 - VL914
2VL931 - VL932
2VL941
2VN001 - VN041
2VN051 - VN064
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GroupVariable Number
2VN081 - VN099
2VN111 - VN127
2VN130 - VN137
2VN151 - VN158
2VN163 - VN168
2VN171 - VN174
2VN191 - VN198
2VN211 - VN212
2VN221 - VN225
2VN231 - VN234
2VN241 - VN243
2VN251 - VN276
2VN291 - VN293
2VN301 - VN314
2VN371 - VN372
2VN376
2VN381 - VN388
2VN421 - VN427
2VN436
2VN471 - VN472
2VN491 - VN513
2VN531 - VN532
2VN536 - VN537
2VN541 - VN542
2VN546 - VN547
2VN551
2VN556 - VN557
2VN561 - VN562
2VN631 - VN638
2VN651 - VN658
2VN671 - VN672
2VN676
2VN681 - VN691
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GroupVariable Number
2VN731 - VN732
2VN751 - VN753
2VN791 - VN792
2VN811 - VN813
2VN921 - VN922
2VN931 - VN936
2VN951 - VN953
2VN966 - VN972
3VQ001 - VQ021
3VQ071 - VQ086
2VR051 - VR060
2VR081
2VR084
2VR086
2VR201 - VR211
2VR251
2VR256 - VR260
2VR401
2VR421 - VR423
2VR426
2VR441
2VR461
2VR471 - VR472
2VS051 - VS056
2VS061
2VS066 - VS070
2VS073 - VS078
2VS091 - VS104
2VS111 - VS113
2VS131 - VS133
2VS136 - VS137
2VS176 - VS177
2VS186 - VS187
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GroupVariable Number
2VS196 - VS203
2VS206 - VS208
2VS211
2VS216 - VS217
2VS231
2VS246 - VS248
2VS261 - VS263
2VS266 - VS274
2VS291 - VS293
2VS301 - VS303
2VS306 - VS311
2VS316
2VS321 - VS324
2VS331 - VS333
2VS336 - VS337
2VS366 - VS367
2VS381 - VS382
2VS391 - VS392
2VS401
2VS426 - VS428
2VS466 - VS472
2VS486
2VS496 - VS497
2VS506 - VS507
2VS526
2VS546 - VS549
2VS701 - VS708
2VS721 - VS730
2VS751 - VS759
2VS821 - VS825
2VS841 - VS844
2VS861
2VS881
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GroupVariable Number
2VT501
2VW701 - VW721
2VW851
2. Spares Affected
None.
B. Concurrent Requirements
None.
C. Reason
Accomplishment of this service bulletin will find and replace any cracked, corroded or incorrect nuts
and bolts on the #1, #2, #7 and #8 outboard flap support ribs. Cracked, corroded or incorrect nuts and
bolts could lead to additional nut and bolt damage in the joint which could result in loss of the outboard
flap. Continued safe flight and landing could be affected after the departure of a flap during takeoff or
landing.
An operator reported two fractured and corroded nuts on the outboard flap, support rib #2 on an airplane
with 54,953 hours and 49,519 cycles. It was found that the incorrect nuts (QTY 8) were installed on
support ribs #2 and #7. The correct nuts for this installation are BACN10HR12 nuts while NAS1804-12
nuts were found to have been installed. The torque for the BACN10HR12 nuts is 3300 to 4300 in-lbs
while the torque for the NAS1804-12 nuts is 2400 to 3500 in-lbs. Overtorqued NAS1804-12 nuts are
at risk of fracture. Fractured nuts may create a breach in the cap seal and allow moisture to contact
the nuts, resulting in corrosion. Nut fractures could lead to additional nut or bolt fractures within that
support rib. Additional fractures can cause the joint to be compromised.
This service bulletin provides instructions to inspect the nuts and bolts common to the #1, #2, #7 and
#8 outboard flap support ribs and replaces any cracked, corroded or incorrect nuts and/or bolts that
are found.
Boeing Fleet Team Digest (FTD) 767 FTD 57-12003 is related to this service bulletin.
Boeing Service Related Problem (SRP) 767-SRP-57-0257 is related to this service bulletin.
Revision 1 is sent to add new Top Kit information and to clarify access and repair procedures.
The data given in Information Notice 767-57A0131 IN 01 is included in Revision 1.
As a part of a service bulletin validation program, this inspection and change was completed on airplane
VN951 by Service Bulletin 767-57A0131 Original Issue before the release of Revision 1 of this service
bulletin. The inspection and change completed on airplane VN951 by Service Bulletin 767-57A0131
Original Issue is equivalent to the release of Revision 1 of this service bulletin. Airplane VN951 has
the configuration of a Group 2 airplane.
Export Controlled ECCN: 9E991 - BOEING
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BOEING SERVICE BULLETIN 767-57A0131

### Page 18

D. Description
Group 1:
Do a Detailed Inspection of the sealant on the nuts common to Outboard Flap Support Ribs #1, #2, #7
and #8. Remove sealant if damaged and do a Detailed Inspection of the fasteners for cracks and
corrosion. If any cracked or corroded fasteners are found, replace all four fasteners on that Support
Rib. Repeat the Detailed Inspection. Install new bolts, washers and nuts.
Group 2-3:
Do a Detailed Inspection of the sealant on the nuts common to Outboard Flap Support Ribs #1, #2, #7
and #8. Remove sealant if damaged and do a Detailed Inspection of the fasteners for cracks and
corrosion. If any corroded fasteners are found, replace that fastener. If any cracked fasteners are found,
replace all four fasteners on that Support Rib. Repeat the Detailed Inspection. Make sure the correct
nuts are installed. If any incorrect nuts are found, replace the nut, bolt and washers.
Revision 1 - No more work is necessary on the airplanes changed or inspected in accordance with the
original issue of this service bulletin.
The work in this service bulletin is done in the maintenance zone(s) given below.
Group 1:
Affected Maintenance Zones
ZoneModel
572, 573, 672, 673767-200, 767-300
Group 2:
Affected Maintenance Zones
ZoneModel
572, 573, 672, 673767-200, 767-300, 767-300F
Group 3:
Affected Maintenance Zones
ZoneModel
572, 573, 672, 673767-400ER
E. Compliance
The Federal Aviation Administration (FAA) will possibly release an Airworthiness Directive related to
this service bulletin. The Airworthiness Directive will make the compliance tasks and times given in this
service bulletin mandatory.
Accomplish the required actions, based on the applicable conditions, in Tables 1 and 2, in accordance
with Paragraph 3. Accomplishment Instructions.
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Evaluate the condition of each fastener of the #1, #2, #7 and #8 Support Ribs separately in Parts 1, 2
and 4. The conditions shown are for each fastener.
Group 1:
Table 1: Outboard Flap Support Rib Fastener Inspection and Replacement
Repeat Interval
(Not to Exceed)
Compliance TimeActionCondition
-Within 12 Months
after the Original
Issue Date of this
Service Bulletin
Do Part 1 - Cap Seal De-
tailed Inspection
-OR-
Do Part 3 - All Fastener
Replacement within a
Support Rib for #1, #2, #7
and #8 Support Ribs (a)
All Airplanes
-Before further flightDo Part 2 - Fastener De-
tailed Inspection
Part 1, Condition 1: Dam-
aged sealant found
12 Months (b)-Repeat Part 1 - Cap Seal
Detailed Inspection
Part 1, Condition 2: No
damaged sealant found
-AND-
-Within 36 Months
after the Original
Issue Date of this
Service Bulletin
Do Part 3 - All Fastener
Replacement within a
Support Rib (b)
-Before further flightDo Part 3 - All Fastener
Replacement within a
Support Rib where the
cracked nut, bolt or
washer was found (b)
Part 2, Condition 3:
Cracked nut, bolt or washer
found
-Before further flightDo Part 3 - All Fastener
Replacement within a
Support Rib where the
corroded nut, bolt or
washer was found (b)
Part 2, Condition 4: Corro-
sion is found on the nut,
bolt or washers and no
crack found
-Before further flightCap Seal Nut with BMS
5-95
Part 2, Condition 5: No
cracks or corrosion on the
nut, bolt or washers is
found -AND-
12 Months (b)-Repeat Part 1 - Cap Seal
Detailed Inspection
-AND-
-Within 36 Months
after the Original
Issue Date of this
Service Bulletin
Do Part 3 - All Fastener
Replacement within a
Support Rib (b)
(a) Terminating Action is complete once Part 3 has been done on each Support Rib.
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### Page 20

Group 1:
Table 1: Outboard Flap Support Rib Fastener Inspection and Replacement
Repeat Interval
(Not to Exceed)
Compliance TimeActionCondition
(b) Terminating Action to the Part 1 inspections of each Support Rib is accomplishment of
Part 3 on each Support Rib.
Group 2-3:
Table 2: Outboard Flap Support Rib Fastener Inspection and Replacement
Repeat Interval
(Not to Exceed)
Compliance TimeActionCondition
-Within 12 Months
after the Original
Issue Date of this
Service Bulletin
Do Part 1 - Cap Seal De-
tailed Inspection
All Airplanes
-Before further flightDo Part 2 - Fastener De-
tailed Inspection
Part 1, Condition 1: Dam-
aged sealant found
12 Months (a)-Repeat Part 1 - Cap Seal
Detailed Inspection
Part 1, Condition 2: No
damaged sealant found
-AND-
-Within 48 Months
after the Original
Issue Date of this
Service Bulletin
Do Part 4 - Detailed In-
spection for Nut Type (a)
-Before further flightDo Part 3 - All Fastener
Replacement within a
Support Rib where the
cracked nut, bolt or
washer was found (b)
Part 2, Condition 3:
Cracked nut, bolt or washer
found
-Before further flightDo Part 5 - Singular Fas-
tener Replacement at the
fastener location where
the corrosion was found
Part 2, Condition 4: Corro-
sion is found on the nut,
bolt or washers and no
crack found
-AND-
Do Part 4 - Detailed In-
spection for Nut Type on
all other fasteners within
the affected Support Rib
(c)
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### Page 21

Group 2-3:
Table 2: Outboard Flap Support Rib Fastener Inspection and Replacement
Repeat Interval
(Not to Exceed)
Compliance TimeActionCondition
-Before further flightCap Seal Nut with BMS
5-95
Part 2, Condition 5: No
cracks or corrosion on the
nut, bolt or washers is
found -AND-
12 Months (a)-Repeat Part 1 - Cap Seal
Detailed Inspection
-AND-
-Within 48 Months
after the Original
Issue Date of this
Service Bulletin
Do Part 4 - Detailed In-
spection for Nut Type (a)
-Before further flightDo Part 5 - Singular Fas-
tener Replacement
Part 4, Condition 6: Incor-
rect nut installed
-Before further flightCap Seal Nut with BMS
5-95
Part 4, Condition 7: Correct
nut installed
(a) Terminating Action to the Part 1 inspections of each Support Rib is accomplishment of
Part 3 on each Support Rib or accomplishment of Part 4 and its follow on actions from
Condition 6 or Condition 7, as applicable, on each Support Rib.
(b) Terminating Action for affected Support Rib.
(c) Terminating Action for affected Support Rib requires accomplishment of Part 5 at affected
fastener locations and accomplishment of Part 4 and its follow on actions from Condition
6 or Condition 7, as applicable, at all other locations.
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 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:
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### Page 22

 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.
Group 1:
Elapsed HoursTask HoursNumber of PersonsTask
0.500.501Open Access
0.400.401Part 1: FIGURE 1
0.400.401Part 1: FIGURE 2
0.400.401Part 1: FIGURE 3
0.400.401Part 1: FIGURE 4
0.150.151Part 2: FIGURE 5
1.80 (a)1.80 (a)1Part 3: FIGURE 6
1.80 (a)1.80 (a)1Part 3: FIGURE 7
1.80 (a)1.80 (a)1Part 3: FIGURE 8
1.80 (a)1.80 (a)1Part 3: FIGURE 9
0.500.501Close Access
2.752.75TOTAL FOR EACH AIRPLANE
(a) Add time to total if repairs are required.
Group 2-3:
Elapsed HoursTask HoursNumber of PersonsTask
0.500.501Open Access
0.400.401Part 1: FIGURE 1
0.400.401Part 1: FIGURE 2
0.400.401Part 1: FIGURE 3
0.400.401Part 1: FIGURE 4
0.150.151Part 2: FIGURE 5
0.050.051Part 4: FIGURE 10
0.050.051Part 4: FIGURE 11
0.30 (a)0.30 (a)1Part 5: FIGURE 6
0.30 (a)0.30 (a)1Part 5: FIGURE 7
0.30 (a)0.30 (a)1Part 5: FIGURE 8
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Group 2-3:
Elapsed HoursTask HoursNumber of PersonsTask
0.30 (a)0.30 (a)1Part 5: FIGURE 9
0.500.501Close Access
2.852.85TOTAL FOR EACH AIRPLANE
(a) Add time to total if repairs are required.
H. Weight and Balance Changes
None.
I. Electrical Load Data
Not changed.
J. References
1. Existing Data:
a. Boeing Service Letter 767-SL-51-036
b. Boeing Service Related Problem (SRP) 767-SRP-57-0257
c. Service Bulletin Index D624T001
d. Standard Overhaul Practices Manual (SOPM) 20-50-19
e. Standard Wiring Practices Manual (SWPM) 20-10-11, 20-10-12, 20-10-19
f. 767 Aircraft Maintenance Manual (AMM) 27-51-00, 27-51-22, 27-51-27, 28-11-00, 28-21-06,
28-22-07, 28-26-00
g. 767 Fleet Team Digest (FTD) 57-12003
h. 767 Non-Destructive Testing (NDT) Manual Part 6, Subject 51-00-04, Part 6, Subject 51-00-11,
Part 6, Subject 51-00-16
i. 767-400 Aircraft Maintenance Manual (AMM) 27-51-00, 27-51-27, 28-11-00, 28-26-00
2. Data Supplied with this Service Bulletin:
None.
3. Installation Drawings Used in the Preparation of this Service Bulletin:
None.
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### Page 24

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 affects FCS but no new DTIs are 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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### Page 25

2.    MATERIAL INFORMATION
A. Material - Price and Availability
The operator can supply the parts and materials shown in the kits in Paragraph 2.C., Parts Necessary
for Each Airplane . As an alternative, operators can purchase the parts from Boeing Spares. The Boeing
price data shown below is given for planning purposes. Supply data can be given if requested. The
parts are subject to the terms and conditions of the Boeing standard purchase order acknowledgment.
Prices are in United States Dollars. Terms: Net 30 days
Reference this service bulletin and submit your purchase order by one of these methods:
1. Order on-line via ATA Spec 2000 or The Boeing PART Page
2. Fax to (206) 662-7145
Group 1-2:
REFER TO THE BOEING PART PAGE ON MYBOEINGFLEET.COM OR CONTACT FIRST RESPONDER
AT FR@BOEING.COM FOR THE LATEST REORDER LEAD TIME (ROLT) AND PRICE INFORMATION
Unit Price as of
the original issue
date of this Ser-
vice Bulletin (US
Dollars)
ROLT as of the
original issue
date of this Ser-
vice Bulletin (Cal-
endar Days)
QTYDateNameKit Number
$2,553.002561August 30,
2012
TOP KIT - 767 Wing
Flap Support Nut Frac-
ture
015T1882-1
48February 6,
2013
$5,585.0025649September 16,
2013
TOP KIT - 767 Wing
Flap Support Nut Frac-
ture - Oversize
015T1882-2
Group 3:
REFER TO THE BOEING PART PAGE ON MYBOEINGFLEET.COM OR CONTACT FIRST RESPONDER
AT FR@BOEING.COM FOR THE LATEST REORDER LEAD TIME (ROLT) AND PRICE INFORMATION
Unit Price as of
the original issue
date of this Ser-
vice Bulletin (US
Dollars)
ROLT as of the
original issue
date of this Ser-
vice Bulletin (Cal-
endar Days)
QTYDateNameKit Number
$2,553.002561August 30,
2012
TOP KIT - 767 Wing
Flap Support Nut Frac-
ture
015T1882-3
$7,793.002561September 16,
2013
TOP KIT - 767 Wing
Flap Support Nut Frac-
ture - Oversize
015T1882-4
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### Page 26

B. Industry Support Information
Boeing warranty remedies are available for 767 airplanes in warranty as of May 29, 2012. For task
hour reimbursement for airplanes in warranty as of that date, send a warranty claim to Boeing
Commercial Airplanes Group - Warranties. The kits for airplanes in warranty as of that date will be
supplied at no charge. Send a purchase order for the kits to Boeing Spares. 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
To get the kits/parts shown below, refer to Paragraph 2.A., Material - Price and Availability.
NOTE: One top kit and the items shown in Paragraph 2.C.2., Parts and Materials Supplied by
the Operator, are necessary for each airplane. One oversized kit may be necessary if
repairs are required.
Kit 015T1882
NotesExisting Part
Number
NameQTYNew Part Number
-4-3-2-1
TOP KIT - 767
Wing Flap Support
Nut Fracture
...-015T1882-1
TOP KIT - 767
Wing Flap Support
Nut Fracture -
OVERSIZE
..-.015T1882-2
TOP KIT - 767
Wing Flap Support
Nut Fracture
.-..015T1882-3
TOP KIT - 767
Wing Flap Support
Nut Fracture -
OVERSIZE
-...015T1882-4
BOLT, 12 PT
HEAD
...2BACB30US10K47
BOLT..2.BACB30US10K47X
BOLT..1.BACB30US10K47Y
BOLT, 12 PT
HEAD
...4BACB30US10K48
BOLT, 12 PT
HEAD
..4.BACB30US10K48X
BOLT, 12 PT
HEAD
..2.BACB30US10K48Y
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### Page 27

Kit 015T1882
NotesExisting Part
Number
NameQTYNew Part Number
-4-3-2-1
BOLT, 12 PT
HEAD
...2BACB30US10K50
BOLT, 12 PT
HEAD
..2.BACB30US10K50X
BOLT, 12 PT
HEAD
..1.BACB30US10K50Y
BOLT.2..BACB30US12K46
BOLT, 12 PT
HEAD
2...BACB30US12K46X
BOLT, 12 PT
HEAD
1...BACB30US12K46Y
BOLT, 12 PT
HEAD
.4..BACB30US12K47
BOLT, 12 PT
HEAD
4...BACB30US12K47X
BOLT2...BACB30US12K47Y
BOLT, 12 PT
HEAD
.2..BACB30US12K48
BOLT, 12 PT
HEAD
2...BACB30US12K48X
BOLT1...BACB30US12K48Y
BOLT, 12 PT
HEAD
.2.2BACB30US12K49
BOLT 7672.2.BACB30US12K49X
BOLT1.1.BACB30US12K49Y
BOLT, 12 PT
HEAD
.2.2BACB30US12K50
BOLT, 12 PT
HEAD
2.2.BACB30US12K50X
BOLT, 12 PT
HEAD
1.1.BACB30US12K50Y
BOLT, 12 PT
HEAD
.4.4BACB30US12K51
BOLT4.4.BACB30US12K51X
BOLT2.2.BACB30US12K51Y
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### Page 28

Kit 015T1882
NotesExisting Part
Number
NameQTYNew Part Number
-4-3-2-1
SELF-LOCKING
NUT
...8BACN10HR10CD
SELF-LOCKING
NUT
.16.8BACN10HR12CD
WASHER, PLAIN..8.BACW10BP101DP
WASHER, PLAIN..6.BACW10BP102DP
WASHER...8BACW10BP10DP
WASHER, PLAIN16.8.BACW10BP121DP
WASHER, PLAIN12.6.BACW10BP122DP
WASHER, PLAIN.16.8BACW10BP12DP
WASHER, SELF-
ALIGN
..8.BACW10CA101CVS
WASHER, SELF-
ALIGN
..6.BACW10CA102CVS
WASHER, SELF-
ALIGN
...8BACW10CA10CCS
WASHER, SELF-
ALIGN
...8BACW10CA10CVS
WASHER, SELF-
ALIGN
16.8.BACW10CA121CVS
WASHER, SELF-
ALIGN
12.6.BACW10CA122CVS
WASHER, SELF-
ALIGN
.16.8BACW10CA12CCS
WASHER, SELF-
ALIGN
.16.8BACW10CA12CVS
(a) If grip length shown is not available at Boeing, fasteners supplied in kits may be one grip
length longer than indicated. Also, if any fasteners part numbers listed are not available or
have been superseded, substitute fasteners may be supplied in kits.
2. Parts and Materials Supplied by the Operator
The following parts or materials are necessary to do the change in this service bulletin. Parts and
materials in the manuals given in Paragraph 1.J., References, can also be necessary. Examine
operator part and material supply to make sure all necessary parts and materials are available.
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### Page 29

Group 1-2:
NotesNameQTYPart Number /
Specification
(c)BOLT, 12 POINT HEAD2BACB30US10K47
(a)BOLT, 12 POINT HEAD2BACB30US10K47X
(a)BOLT, 12 POINT HEAD1BACB30US10K47Y
(c)BOLT, 12 POINT HEAD4BACB30US10K48
(a)BOLT, 12 POINT HEAD4BACB30US10K48X
(a)BOLT, 12 POINT HEAD2BACB30US10K48Y
(c)BOLT, 12 POINT HEAD2BACB30US10K50
(a)BOLT, 12 POINT HEAD2BACB30US10K50X
(a)BOLT, 12 POINT HEAD1BACB30US10K50Y
(c)WASHER, SELF-ALIGNING8BACW10CA10CVS
(a)WASHER, SELF-ALIGNING8BACW10CA101CVS
(a)WASHER, SELF-ALIGNING6BACW10CA102CVS
(c)WASHER, SELF-ALIGNING8BACW10CA10CCS
(c)WASHER, PLAIN AND COUNTER-
SUNK
8BACW10BP10DP
(a)WASHER, PLAIN AND COUNTER-
SUNK
8BACW10BP101DP
(a)WASHER, PLAIN AND COUNTER-
SUNK
6BACW10BP102DP
(c)NUT, SELF-LOCKING8BACN10HR10CD
(c)BOLT, 12 POINT HEAD2BACB30US12K49
(a)BOLT, 12 POINT HEAD2BACB30US12K49X
(a)BOLT, 12 POINT HEAD1BACB30US12K49Y
(c)BOLT, 12 POINT HEAD2BACB30US12K50
(a)BOLT, 12 POINT HEAD2BACB30US12K50X
(a)BOLT, 12 POINT HEAD1BACB30US12K50Y
(c)BOLT, 12 POINT HEAD4BACB30US12K51
(a)BOLT, 12 POINT HEAD4BACB30US12K51X
(a)BOLT, 12 POINT HEAD2BACB30US12K51Y
(c)WASHER, SELF-ALIGNING8BACW10CA12CVS
(a)WASHER, SELF-ALIGNING8BACW10CA121CVS
(a)WASHER, SELF-ALIGNING6BACW10CA122CVS
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### Page 30

Group 1-2:
NotesNameQTYPart Number /
Specification
(c)WASHER, SELF-ALIGNING8BACW10CA12CCS
(c)WASHER, PLAIN AND COUNTER-
SUNK
8BACW10BP12DP
(a)WASHER, PLAIN AND COUNTER-
SUNK
8BACW10BP121DP
(a)WASHER, PLAIN AND COUNTER-
SUNK
6BACW10BP122DP
(c)NUT, SELF-LOCKING8BACN10HR12CD
(b)Sealant-BMS 5-95
(b)Fuel Tank Sealant-BMS 5-45 (BMS 5-
26 optional)
(a) Part is in kit 015T1882-2.
(b) Refer to the Qualified Products List at the end of the Boeing Material Specification (BMS)
for supplier data.
(c) Part is in kit 015T1882-1.
Group 3:
NotesNameQTYPart Number /
Specification
(c)BOLT, 12 POINT HEAD2BACB30US12K46
(a)BOLT, 12 POINT HEAD2BACB30US12K46X
(a)BOLT, 12 POINT HEAD1BACB30US12K46Y
(c)BOLT, 12 POINT HEAD4BACB30US12K47
(a)BOLT, 12 POINT HEAD4BACB30US12K47X
(a)BOLT, 12 POINT HEAD2BACB30US12K47Y
(c)BOLT, 12 POINT HEAD2BACB30US12K48
(a)BOLT, 12 POINT HEAD2BACB30US12K48X
(a)BOLT, 12 POINT HEAD1BACB30US12K48Y
(c)WASHER, SELF-ALIGNING8BACW10CA12CVS
(a)WASHER, SELF-ALIGNING8BACW10CA121CVS
(a)WASHER, SELF-ALIGNING6BACW10CA122CVS
(c)WASHER, SELF-ALIGNING8BACW10CA12CCS
(c)WASHER, PLAIN AND COUNTER-
SUNK
8BACW10BP12DP
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### Page 31

Group 3:
NotesNameQTYPart Number /
Specification
(a)WASHER, PLAIN AND COUNTER-
SUNK
8BACW10BP121DP
(a)WASHER, PLAIN AND COUNTER-
SUNK
6BACW10BP122DP
(c)NUT, SELF-LOCKING8BACN10HR12CD
(c)BOLT, 12 POINT HEAD2BACB30US12K49
(a)BOLT, 12 POINT HEAD2BACB30US12K49X
(a)BOLT, 12 POINT HEAD1BACB30US12K49Y
(c)BOLT, 12 POINT HEAD2BACB30US12K50
(a)BOLT, 12 POINT HEAD2BACB30US12K50X
(a)BOLT, 12 POINT HEAD1BACB30US12K50Y
(c)BOLT, 12 POINT HEAD4BACB30US12K51
(a)BOLT, 12 POINT HEAD4BACB30US12K51X
(a)BOLT, 12 POINT HEAD2BACB30US12K51Y
(c)WASHER, SELF-ALIGNING8BACW10CA12CVS
(a)WASHER, SELF-ALIGNING8BACW10CA121CVS
(a)WASHER, SELF-ALIGNING6BACW10CA122CVS
(c)WASHER, SELF-ALIGNING8BACW10CA12CCS
(c)WASHER, PLAIN AND COUNTER-
SUNK
8BACW10BP12DP
(a)WASHER, PLAIN AND COUNTER-
SUNK
8BACW10BP121DP
(a)WASHER, PLAIN AND COUNTER-
SUNK
6BACW10BP122DP
(c)NUT, SELF-LOCKING8BACN10HR12CD
(b)Sealant-BMS 5-95
(b)Fuel Tank Sealant-BMS 5-45 (BMS 5-
26 optional)
(a) Part is in kit 015T1882-4.
(b) Refer to the Qualified Products List at the end of the Boeing Material Specification (BMS)
for supplier data.
(c) Part is in kit 015T1882-3.
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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
None.
F. Special Tooling Necessary to do this Service Bulletin
No special tools or equipment are necessary to do the change in this service bulletin. But, maintenance
and overhaul tools in the manuals given in Paragraph 1.J., References, can be necessary. Examine
operator tool supply to make sure all necessary tools are available.
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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. 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
4. Use the approved fastener and process material substitutions in accordance with
SRM Chapter 51.
5. 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.
6. 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.
7. 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.
8. 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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9. 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.
10. Boeing Service Letter 767-SL-51-036 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.
11. Refer to Appendix A for Applicable Part Numbers and Quantities.
12. 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.
13. 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.
14. 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.
15. Shaded areas in Figures are reference only. Shaded areas in Figures may look
different than your airplane.
16. The term "fastener" used in this service bulletin is defined as the combination of a
bolt, two washers and a nut.
17. Evaluate the condition of each fastener of the #1, #2, #7 and #8 Support Ribs
separately in Parts 1, 2 and 4. The conditions shown are for each fastener.
Terminating Action applies to each Support Rib separately.
18. There is no Boeing special tool available for replacing the support rib fastener to
support the bolt head. It may be necessary to manufacture a tool to hold the bolt
head during nut installation.
B. WORK INSTRUCTIONS
1. Extend and deactivate the trailing edge flaps. Refer to 767 AMM 27-51-00 or 767-400 AMM
27-51-00 as an accepted procedure, as applicable.
2. Do Part 1 - Cap Seal Detailed Inspection.
a. Condition 1: Damaged sealant found
(1) Do Part 2 - Fastener Detailed Inspection.
(a) Condition 3: Cracked nut, bolt or washer found
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1) Do Part 3 - All Fastener Replacement within a Support Rib on the Support Rib
where the cracked nut, bolt or washer was found. (Terminating Action for affected
Support Rib)
(b) Condition 4: Corrosion is found on the nut, bolt or washers and no crack found
1) Group 1:
Do Part 3 - All Fastener Replacement within a Support Rib on the Support Rib
where the corroded nut, bolt or washer was found. (Terminating Action for
affected Support Rib)
2) Group 2-3:
Do Part 5 - Singular Fastener Replacement at the fastener location where the
corrosion was found.
AND
Do Part 4 - Detailed Inspection for Nut Type on all other fasteners within the
Support Rib.
a) Condition 6: Incorrect nut installed
{1} Do Part 5 - Singular Fastener Replacement. (Terminating Action to
Part 1 Inspection for affected fastener location)
b) Condition 7: Correct nut installed
{1} Cap seal the nut with BMS 5-95. Refer to SOPM 20-50-19 as an
accepted procedure. (Terminating Action to Part 1 Inspection for
affected fastener location)
NOTE: Terminating Action for affected Support Rib requires
accomplishment of Part 5 at affected fastener locations and
accomplishment of Part 4 and its follow on actions from
Condition 6 or Condition 7, as applicable, at all other locations.
(c) Condition 5: No cracks or corrosion on the nut, bolt or washers is found
1) Cap seal the nut with BMS 5-95. Refer to SOPM 20-50-19 as an accepted
procedure.
2) Repeat Part 1 - Cap Seal Detailed Inspection at the time given in Paragraph
1.E., Compliance.
3) Group 1:
Do Part 3 - All Fastener Replacement within a Support Rib at the time given in
Paragraph 1.E., Compliance. (Terminating Action for affected Support Rib)
4) Group 2-3:
Do Part 4 - Detailed Inspection for Nut Type at the time given in Paragraph 1.E.,
Compliance.
a) Condition 6: Incorrect nut installed
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{1} Do Part 5 - Singular Fastener Replacement. (Terminating Action to
Part 1 Inspection for affected fastener location)
b) Condition 7: Correct nut installed
{1} Cap seal the nut with BMS 5-95. Refer to SOPM 20-50-19 as an
accepted procedure. (Terminating Action to Part 1 Inspection for
affected fastener location)
NOTE: Terminating Action for affected Support Rib requires
accomplishment of Terminating Action for every fastener
location within the Support Rib.
b. Condition 2: No damaged sealant found
(1) Repeat Part 1 - Cap Seal Detailed Inspection at the time given in Paragraph 1.E.,
Compliance.
(2) Group 1:
Do Part 3 - All Fastener Replacement within a Support Rib at the time given in Paragraph
1.E., Compliance. (Terminating Action for affected Support Rib)
(3) Group 2-3:
Do Part 4 - Detailed Inspection for Nut Type at the time given in Paragraph 1.E.,
Compliance.
(a) Condition 6: Incorrect nut installed
1) Do Part 5 - Singular Fastener Replacement. (Terminating Action to Part 1
Inspection for affected fastener location)
(b) Condition 7: Correct nut installed
1) Cap seal the nut with BMS 5-95. Refer to SOPM 20-50-19 as an accepted
procedure. (Terminating Action to Part 1 Inspection for affected fastener location)
NOTE: Terminating Action for affected Support Rib requires accomplishment of
Terminating Action for every fastener location within the Support Rib.
3. Activate and retract the trailing edge flaps. Refer to 767 AMM 27-51-00 or 767-400 AMM 27-51-00
as an accepted procedure, as applicable.
4. Put the airplane back to a serviceable condition.
Part 1 - Cap Seal Detailed Inspection
1. Do a Detailed Inspection of the cap seal on the nuts common to the Outboard Flap Support Ribs
by support rib number for damaged sealant in accordance with the figures below:
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### Page 37

Right WingLeft Wing
Support Rib #8Support Rib #7Support Rib #2Support Rib #1
FIGURE 4FIGURE 3FIGURE 2FIGURE 1
Part 2 - Fastener Detailed Inspection
1. Do a Detailed Inspection of the affected fastener for cracks and corrosion in accordance with
FIGURE 5.
Part 3 - All Fastener Replacement within a Support Rib
1. Defuel and Purge fuel tank as required for entry. Refer to 767 AMM 28-26-00 and 767 AMM
28-11-00 or 767-400 AMM 28-26-00 and 767-400 AMM 28-11-00 as accepted procedures, as
applicable.
2. Optional: Remove the trailing edge rotary actuators. Refer to 767 AMM 27-51-22 as an accepted
procedure.
3. Optional: Remove the fuel line tubing near the flap support ribs. Refer to 767 AMM 28-22-07 as
an accepted procedure.
4. Optional: Remove the swing check valve tubing near the flap support ribs. Refer to 767 AMM
28-21-06 as an accepted procedure.
5. Remove the Outboards Flaps. Refer to 767 AMM 27-51-27 or 767-400 AMM 27-51-27 as an
accepted procedure, as applicable.
NOTE: The outboard flaps do not need to be removed if only one fastener at a time is removed
and replaced. If reaming of either of the two center-most bolts of the fitting is required,
the outboard flaps will need to be removed.
6. Replace all four fasteners for the affected Support Rib in accordance with the figures below, as
applicable (Terminating Action for affected Support Rib):
Right WingLeft Wing
Support Rib #8Support Rib #7Support Rib #2Support Rib #1
FIGURE 9FIGURE 8FIGURE 7FIGURE 6
7. Install the swing check valve tubing near the flap support ribs, if removed. Refer to 767 AMM
28-21-06 as an accepted procedure.
8. Install the fuel line tubing near the flap support ribs, if removed. Refer to 767 AMM 28-22-07 as
an accepted procedure.
9. Install the trailing edge rotary actuators, if removed. Refer to 767 AMM 27-51-22 as an accepted
procedure.
10. Do a fuel leak check around the flap support ribs. Refer to 767 AMM 28-11-00 as an accepted
procedure.
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11. Install the Outboards Flaps. Refer to 767 AMM 27-51-27 or 767-400 AMM 27-51-27 as an accepted
procedure, as applicable.
Group 2-3:
Part 4 - Detailed Inspection for Nut Type
1. Measure the dimensions of the nut for the correct type in accordance with the figures below, as
applicable:
Group 2:
Right WingLeft Wing
Support Rib #8Support Rib #7Support Rib #2Support Rib #1
FIGURE 10FIGURE 11FIGURE 11FIGURE 10
Group 3:
Right WingLeft Wing
Support Rib #8Support Rib #7Support Rib #2Support Rib #1
FIGURE 11FIGURE 11FIGURE 11FIGURE 11
Part 5 - Singular Fastener Replacement
1. Defuel and Purge fuel tank as required for entry. Refer to 767 AMM 28-26-00 and 767 AMM
28-11-00 or 767-400 AMM 28-26-00 and 767-400 AMM 28-11-00 as accepted procedures, as
applicable.
2. Optional: Remove the trailing edge rotary actuators. Refer to 767 AMM 27-51-22 as an accepted
procedure.
3. Optional: Remove the fuel line tubing near the flap support ribs. Refer to 767 AMM 28-22-07 as
an accepted procedure.
4. Optional: Remove the swing check valve tubing near the flap support ribs. Refer to 767 AMM
28-21-06 as an accepted procedure.
5. Remove the Outboards Flaps. Refer to 767 AMM 27-51-27 or 767-400 AMM 27-51-27 as an
accepted procedure, as applicable.
NOTE: The outboard flaps do not need to be removed if only one fastener at a time is removed
and replaced. If reaming of either of the two center-most bolts of the fitting is required,
the outboard flaps will need to be removed.
6. Replace the affected fastener in accordance with the figures below, as applicable:
Right WingLeft Wing
Support Rib #8Support Rib #7Support Rib #2Support Rib #1
FIGURE 9FIGURE 8FIGURE 7FIGURE 6
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### Page 39

7. Install the swing check valve tubing near the flap support ribs, if removed. Refer to 767 AMM
28-21-06 as an accepted procedure.
8. Install the fuel line tubing near the flap support ribs, if removed. Refer to 767 AMM 28-22-07 as
an accepted procedure.
9. Install the trailing edge rotary actuators, if removed. Refer to 767 AMM 27-51-22 as an accepted
procedure.
10. Do a fuel leak check around the flap support ribs. Refer to 767 AMM 28-11-00 as an accepted
procedure.
11. Install the Outboards Flaps. Refer to 767 AMM 27-51-27 or 767-400 AMM 27-51-27 as an accepted
procedure, as applicable.
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### Page 40 (OCR)

BOEING SERVICE BULLETIN 767-57A0131
REAR SPAR
DHOR
INBD
2183014
FIGURE 1: CAP SEAL DETAILED INSPECTION FOR SUPPORT RIB # 1
(SHEET 1 OF 2)
Original Issue: October 30, 2012
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Work - See page 1 for details.  9L 10 Ot

### Page 41

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 this figure.
More DataQtyIdentificationNameTaskStep
Do a Detailed Inspec-
tion of the sealant
around the nut for
damage. (a)
4-Cap SealInspect1
(a) Damaged sealant includes sealant that is cracked, missing, wrinkled, loose or separated.
FIGURE 1: CAP SEAL DETAILED INSPECTION FOR SUPPORT RIB # 1
(SHEET 2 OF 2)
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### Page 42 (OCR)

BOEING SERVICE BULLETIN 767-57A0131
REAR SPAR
DHOR
INBD
2183015
FIGURE 2: CAP SEAL DETAILED INSPECTION FOR SUPPORT RIB # 2
(SHEET 1 OF 2)
Original Issue: October 30, 2012
Revision 1 May 08, 2013  Export Controlled ECCN: 9E991 - BOEING  PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.

### Page 43

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 this figure.
More DataQtyIdentificationNameTaskStep
Do a Detailed Inspec-
tion of the sealant
around the nut for
damage. (a)
4-Cap SealInspect1
(a) Damaged sealant includes sealant that is cracked, missing, wrinkled, loose or separated.
FIGURE 2: CAP SEAL DETAILED INSPECTION FOR SUPPORT RIB # 2
(SHEET 2 OF 2)
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### Page 44 (OCR)

BOEING SERVICE BULLETIN 767-57A0131
REAR SPAR
INBD
FWD
2183018
FIGURE 3: CAP SEAL DETAILED INSPECTION FOR SUPPORT RIB # 7
(SHEET 1 OF 2)
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PROPRIETARY - Copyright © Unpublished
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### Page 45

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 this figure.
More DataQtyIdentificationNameTaskStep
Do a Detailed Inspec-
tion of the sealant
around the nut for
damage. (a)
4-Cap SealInspect1
(a) Damaged sealant includes sealant that is cracked, missing, wrinkled, loose or separated.
FIGURE 3: CAP SEAL DETAILED INSPECTION FOR SUPPORT RIB # 7
(SHEET 2 OF 2)
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### Page 46 (OCR)

BOEING SERVICE BULLETIN 767-57A0131
REAR SPAR
INBD
FWD
2183019
FIGURE 4: CAP SEAL DETAILED INSPECTION FOR SUPPORT RIB # 8
(SHEET 1 OF 2)
Original Issue: October 30, 2012
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PROPRIETARY - Copyright © Unpublished
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### Page 47

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 this figure.
More DataQtyIdentificationNameTaskStep
Do a Detailed Inspec-
tion of the sealant
around the nut for
damage. (a)
4-Cap SealInspect1
(a) Damaged sealant includes sealant that is cracked, missing, wrinkled, loose or separated.
FIGURE 4: CAP SEAL DETAILED INSPECTION FOR SUPPORT RIB # 8
(SHEET 2 OF 2)
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### Page 48

The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY
numbers shown below are for one fastener location. The QTY may vary from 1 to 4 on each support rib depending
on the condition of each fastener location.
More DataQtyIdentificationNameTaskStep
only from fastener
locations where
damaged sealant
was found.
1-Cap SealRemove1
Do a Detailed Inspec-
tion for corrosion
and cracks on the
nut, bolt and wash-
ers.
1-FastenerInspect2
FIGURE 5: FASTENER DETAILED INSPECTION
(SHEET 1 OF 1)
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### Page 49 (OCR)

BOEING SERVICE BULLETIN 767-57A0131
REAR SPAR
4 LOCATIONS 1
2183097
FIGURE 6: FASTENER REPLACEMENTS FOR SUPPORT RIB # 1
(SHEET 1 OF 4)
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Work - See page 1 for details.  9L10 6₺

### Page 50

The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY
numbers shown below are for one fastener location. The QTY may vary from 1 to 4 on each support rib depending
on the condition of each fastener location.
More DataQtyIdentificationNameTaskStep
4-FastenerRemove1
FIGURE 6: FASTENER REPLACEMENTS FOR SUPPORT RIB # 1
(SHEET 2 OF 4)
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### Page 51

More DataQtyIdentificationNameTaskStep
Do a High Frequen-
cy Eddy Current In-
spection of the fas-
tener hole for cracks
and corrosion in ac-
cordance with 767
NDT Manual Part 6,
Subject 51-00-04,
767 NDT Part 6,
Subject 51-00-11 or
767 NDT Part 6,
Subject 51-00-16.
(a)
4-Fastener HoleInspect2
to remove cracks
and corrosion. If no
cracks and corrosion
found, reaming is
not required  if the
hole size matches
one of the fastener
hole sizes as shown
in APPENDIX A.
Contact Boeing if
cracks and corrosion
cannot be removed
within the allowable
hole sizes and do
the repair. (a)
4-Fastener HoleReam3
Do a High Frequen-
cy Eddy Current In-
spection of the fas-
tener hole to make
sure all cracks and
corrosion has been
removed in accor-
dance with 767 NDT
Manual Part 6, Sub-
ject 51-00-04, 767
NDT Part 6, Subject
51-00-11 or 767
NDT Part 6, Subject
51-00-16. (b)
4-Fastener HoleInspect
FIGURE 6: FASTENER REPLACEMENTS FOR SUPPORT RIB # 1
(SHEET 3 OF 4)
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### Page 52

More DataQtyIdentificationNameTaskStep
wet with BMS 5-95
sealant. Refer to
APPENDIX A for ap-
plicable bolt part
numbers.
4-BoltInstall (New)4
Refer to APPENDIX
A for washer quanti-
ties and applicable
part numbers.
--WasherInstall (New)
Refer to APPENDIX
A for applicable nut
part numbers.
4-NutInstall (New)
Cap seal nuts exter-
nal to the wing fuel
tank. Refer to SOPM
20-50-19 as an ac-
cepted procedure.
4BMS 5-95SealantApply5
Cap seal bolt heads
internal to the wing
fuel tank. Refer to
SOPM 20-50-19 as
an accepted proce-
dure.
4BMS 5-45  (BMS 5-26
optional)
SealantApply
(a) It is normal for the holes in the stackup to have different diameters. Nominal hole diameters in the rear
spar and lower chord are close ream holes, while the nominal hole diameters in the outboard trailing edge
flap support rib and actuator backup fittings are slightly larger in diameter as shown in APPENDIX B.
(b) Most of the holes can be inspected from outside the wing tank. The inboard support rib, inboard hole will
need to be inspected from inside the wing tank in the event the outboard trailing edge flap rotary actuator,
flap position transmitters, spoiler hydraulic lines and fuel lines have not been removed.
FIGURE 6: FASTENER REPLACEMENTS FOR SUPPORT RIB # 1
(SHEET 4 OF 4)
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### Page 53 (OCR)

BOEING SERVICE BULLETIN 767-57A0131
REAR SPAR
4 LOCATIONS 1
2183168
FIGURE 7: FASTENER REPLACEMENTS FOR SUPPORT RIB # 2
(SHEET 1 OF 4)
Original Issue: October 30, 2012
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Work - See page 1 for details.  92 10 89

### Page 54

The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY
numbers shown below are for one fastener location. The QTY may vary from 1 to 4 on each support rib depending
on the condition of each fastener location.
More DataQtyIdentificationNameTaskStep
4-FastenerRemove1
FIGURE 7: FASTENER REPLACEMENTS FOR SUPPORT RIB # 2
(SHEET 2 OF 4)
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### Page 55

More DataQtyIdentificationNameTaskStep
Do a High Frequen-
cy Eddy Current In-
spection on the fas-
tener hole for cracks
and corrosion in ac-
cordance with 767
NDT Manual Part 6,
Subject 51-00-04,
767 NDT Part 6,
Subject 51-00-11 or
767 NDT Part 6,
Subject 51-00-16.
(a)
4-Fastener HoleInspect2
to remove cracks
and corrosion. If no
cracks and corrosion
found, reaming is
not required  if the
hole size matches
one of the fastener
hole sizes as shown
in APPENDIX A.
Contact Boeing if
cracks and corrosion
cannot be removed
within the allowable
hole sizes and do
the repair. (a)
4-Fastener HoleReam3
Do a High Frequen-
cy Eddy Current In-
spection of the fas-
tener hole to make
sure all cracks and
corrosion has been
removed in accor-
dance with 767 NDT
Manual Part 6, Sub-
ject 51-00-04, 767
NDT Part 6, Subject
51-00-11 or 767
NDT Part 6, Subject
51-00-16. (b)
4-Fastener HoleInspect
FIGURE 7: FASTENER REPLACEMENTS FOR SUPPORT RIB # 2
(SHEET 3 OF 4)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: October 30, 2012
767-57A0131Revision 1 May 08, 2013
55 of 75
BOEING SERVICE BULLETIN 767-57A0131

### Page 56

More DataQtyIdentificationNameTaskStep
wet with BMS 5-95
sealant. Refer to
APPENDIX A for ap-
plicable bolt part
numbers.
4-BoltInstall (New)4
Refer to APPENDIX
A for washer quanti-
ties and applicable
part numbers.
--WasherInstall (New)
Refer to APPENDIX
A for applicable nut
part numbers.
4-NutInstall (New)
Cap seal nuts exter-
nal to the wing fuel
tank. Refer to SOPM
20-50-19 as an ac-
cepted procedure.
4BMS 5-95SealantApply5
Cap seal bolt heads
internal to the wing
fuel tank. Refer to
SOPM 20-50-19 as
an accepted proce-
dure.
4BMS 5-45  (BMS 5-26
optional)
SealantApply
(a) It is normal for the holes in the stackup to have different diameters. Nominal hole diameters in the rear
spar and lower chord are close ream holes, while the nominal hole diameters in the outboard trailing edge
flap support rib and actuator backup fittings are slightly larger in diameter as shown in APPENDIX B.
(b) Most of the holes can be inspected from outside the wing tank. The inboard support rib, inboard hole will
need to be inspected from inside the wing tank in the event the outboard trailing edge flap rotary actuator,
flap position transmitters, spoiler hydraulic lines and fuel lines have not been removed.
FIGURE 7: FASTENER REPLACEMENTS FOR SUPPORT RIB # 2
(SHEET 4 OF 4)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: October 30, 2012
767-57A0131Revision 1 May 08, 2013
56 of 75
BOEING SERVICE BULLETIN 767-57A0131

### Page 57 (OCR)

BOEING SERVICE BULLETIN 767-57A0131
REAR SPAR
1) 4 LOCATIONS
PROCE
NBC
FWD
2183171
FIGURE 8: FASTENER REPLACEMENTS FOR SUPPORT RIB # 7
(SHEET 1 OF 4)
Original Issue: October 30, 2012
Revision 1 May 08, 2013  Export Controlled ECCN: 9E991 - BOEING  767-57A0131
PROPRIETARY - Copyright © Unpublished  Work - See page 1 for details.  57 of 75

### Page 58

The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY
numbers shown below are for one fastener location. The QTY may vary from 1 to 4 on each support rib depending
on the condition of each fastener location.
More DataQtyIdentificationNameTaskStep
4-FastenerRemove1
FIGURE 8: FASTENER REPLACEMENTS FOR SUPPORT RIB # 7
(SHEET 2 OF 4)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: October 30, 2012
767-57A0131Revision 1 May 08, 2013
58 of 75
BOEING SERVICE BULLETIN 767-57A0131

### Page 59

More DataQtyIdentificationNameTaskStep
Do a High Frequen-
cy Eddy Current In-
spection on the fas-
tener hole for cracks
and corrosion in ac-
cordance with 767
NDT Manual Part 6,
Subject 51-00-04,
767 NDT Part 6,
Subject 51-00-11 or
767 NDT Part 6,
Subject 51-00-16.
(a)
4-Fastener HoleInspect2
to remove cracks
and corrosion. If no
cracks and corrosion
found, reaming is
not required  if the
hole size matches
one of the fastener
hole sizes as shown
in APPENDIX A.
Contact Boeing if
cracks and corrosion
cannot be removed
within the allowable
hole sizes and do
the repair. (a)
4-Fastener HoleReam3
Do a High Frequen-
cy Eddy Current In-
spection of the fas-
tener hole to make
sure all cracks and
corrosion has been
removed in accor-
dance with 767 NDT
Manual Part 6, Sub-
ject 51-00-04, 767
NDT Part 6, Subject
51-00-11 or 767
NDT Part 6, Subject
51-00-16. (b)
4-Fastener HoleInspect
FIGURE 8: FASTENER REPLACEMENTS FOR SUPPORT RIB # 7
(SHEET 3 OF 4)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: October 30, 2012
767-57A0131Revision 1 May 08, 2013
59 of 75
BOEING SERVICE BULLETIN 767-57A0131

### Page 60

More DataQtyIdentificationNameTaskStep
wet with BMS 5-95
sealant. Refer to
APPENDIX A for ap-
plicable bolt part
numbers.
4-BoltInstall (New)4
Refer to APPENDIX
A for washer quanti-
ties and applicable
part numbers.
--WasherInstall (New)
Refer to APPENDIX
A for applicable nut
part numbers.
4-NutInstall (New)
Cap seal nuts exter-
nal to the wing fuel
tank. Refer to SOPM
20-50-19 as an ac-
cepted procedure.
4BMS 5-95SealantApply5
Cap seal bolt heads
internal to the wing
fuel tank. Refer to
SOPM 20-50-19 as
an accepted proce-
dure.
4BMS 5-45  (BMS 5-26
optional)
SealantApply
(a) It is normal for the holes in the stackup to have different diameters. Nominal hole diameters in the rear
spar and lower chord are close ream holes, while the nominal hole diameters in the outboard trailing edge
flap support rib and actuator backup fittings are slightly larger in diameter as shown in APPENDIX B.
(b) Most of the holes can be inspected from outside the wing tank. The inboard support rib, inboard hole will
need to be inspected from inside the wing tank in the event the outboard trailing edge flap rotary actuator,
flap position transmitters, spoiler hydraulic lines and fuel lines have not been removed.
FIGURE 8: FASTENER REPLACEMENTS FOR SUPPORT RIB # 7
(SHEET 4 OF 4)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: October 30, 2012
767-57A0131Revision 1 May 08, 2013
60 of 75
BOEING SERVICE BULLETIN 767-57A0131

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