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.

ECCN: 9E991

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Unpublished Work.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.

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2.0
Export Controlled ECCN: 9E991 - BOEING

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BOEING SERVICE BULLETIN 767-57A0131

BLANK PAGE
Table of Contents

Revision Transmittal Sheet ............................................ 5

Summary ...................................................... 7

1. PLANNING INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11

A. Effectivity . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11

1. Airplanes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11

2. Spares Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17

B. Concurrent Requirements . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17

C. Reason . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17

D. Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 18

E. Compliance . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 18

F. Approval . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21

G. Manpower . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21

H. Weight and Balance Changes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 23

I. Electrical Load Data . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 23

J. References . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 23

1. Existing Data: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 23

2. Data Supplied with this Service Bulletin: . . . . . . . . . . . . . . . . . . . . . . . . . . . 23

3. Installation Drawings Used in the Preparation of this Service Bulletin: . . . . . . . . . . . 23

K. Publications Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 24

L. Interchangeability and Intermixability of Parts . . . . . . . . . . . . . . . . . . . . . . . . . . . 24

M. Software Accomplishment Summary . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 24

2. MATERIAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25

A. Material - Price and Availability . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25

B. Industry Support Information . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 26

C. Parts Necessary for Each Airplane . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 26

1. Kits/Parts . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 26

2. Parts and Materials Supplied by the Operator . . . . . . . . . . . . . . . . . . . . . . . . 28

3. Parts Modified and Reidentified . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 32

4. Parts Removed and Not Replaced . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 32

D. Parts Necessary to Change Spares . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 32

E. Special Tooling - Price and Availability . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 32

F. Special Tooling Necessary to do this Service Bulletin . . . . . . . . . . . . . . . . . . . . . . . 32

3. ACCOMPLISHMENT INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 33

A. GENERAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 33

B. WORK INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 34

FIGURE 1: CAP SEAL DETAILED INSPECTION FOR SUPPORT RIB # 1 . . . . . . . . . . . . . . . 40

FIGURE 2: CAP SEAL DETAILED INSPECTION FOR SUPPORT RIB # 2 . . . . . . . . . . . . . . . 42

FIGURE 3: CAP SEAL DETAILED INSPECTION FOR SUPPORT RIB # 7 . . . . . . . . . . . . . . . 44

FIGURE 4: CAP SEAL DETAILED INSPECTION FOR SUPPORT RIB # 8 . . . . . . . . . . . . . . . 46

FIGURE 5: FASTENER DETAILED INSPECTION . . . . . . . . . . . . . . . . . . . . . . . . . . . . 48

FIGURE 6: FASTENER REPLACEMENTS FOR SUPPORT RIB # 1 . . . . . . . . . . . . . . . . . . 49

FIGURE 7: FASTENER REPLACEMENTS FOR SUPPORT RIB # 2 . . . . . . . . . . . . . . . . . . 53

FIGURE 8: FASTENER REPLACEMENTS FOR SUPPORT RIB # 7 . . . . . . . . . . . . . . . . . . 57

FIGURE 9: FASTENER REPLACEMENTS FOR SUPPORT RIB # 8 . . . . . . . . . . . . . . . . . . 61

FIGURE 10: NUT MEASUREMENT FOR CORRECT TYPE [Group 2] . . . . . . . . . . . . . . . . . . 65

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BOEING SERVICE BULLETIN 767-57A0131
FIGURE 11: NUT MEASUREMENT FOR CORRECT TYPE [Group 2-3] . . . . . . . . . . . . . . . . . 67

APPENDIX A: PART NUMBERS AND QUANTITIES BY SUPPORT RIB NUMBER . . . . . . . . . . . . 69

APPENDIX B: NOMINAL HOLE DIAMETERS FOR OUTBOARD TRAILING EDGE FLAP SUPPORT RIB AND

ACTUATOR SUPPORT FITTINGS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 75

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BOEING SERVICE BULLETIN 767-57A0131
Commercial 

Airplanes 767

Service Bulletin

Revision Transmittal Sheet 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

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

Original Issue: October 30, 2012

Revision 1: May 08, 2013

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BOEING SERVICE BULLETIN 767-57A0131
Commercial 

Airplanes 767

Service Bulletin

Summary 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

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.

Planning Data Affected Reference

Spares Affected No Paragraph 1.A.2., Spares Affected

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Planning Data Affected Reference

Paragraph 1.E., Compliance and Paragraph

1.F., Approval

AD Related Yes

Weight and Balance Change No Paragraph 1.H., Weight and Balance Changes

Electrical Load Changed No Paragraph 1.I., Electrical Load Data

Publications Affected No Paragraph 1.K., Publications Affected

Airplane Flight Operations Affected (Flight Crew No Paragraph 1.K., Publications Affected

Operations Manual and/or FAA Approved Airplane Flight Manual)

Kits/Parts Required Yes Paragraph 2.C.1., Kits/Parts

Paragraph 2.C.2., Parts and Materials Supplied

by the Operator

Operator Supplied Material Yes

Paragraph 2.F., Special Tooling Necessary to

do this Service Bulletin

Special Tooling Required No

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
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
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.

GROUP CONFIGURATION DESCRIPTION

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

Variable Number Group

VA001 - VA020 1

VA301 - VA315 1

VA501 - VA530 1

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Variable Number Group

VA701 - VA712 1

VA713 - VA719 2

VA801 - VA810 1

VB001 - VB002 1

VB051 - VB055 1

VB101 - VB125 1

VB201 - VB202 1

VB251 - VB253 1

VB281 - VB284 1

VB301 - VB302 1

VB321 - VB325 1

VB326 - VB332 2

VB371 - VB373 1

VB401 1

VB441 - VB444 2

VE001 - VE003 1

VE021 - VE023 1

VE041 - VE043 1

VE061 - VE069 1

VE083 - VE084 1

VE085 - VE086 2

VE101 - VE103 1

VE104 2

VE116 - VE117 1

VE118 2

VE121 - VE126 1

VE141 - VE145 1

VE146 - VE152 2

VE171 - VE172 2

VF001 - VF002 2

VF041 - VF042 2

VF051 2

VF061 - VF062 2

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BOEING SERVICE BULLETIN 767-57A0131
Variable Number Group

VF071 - VF072 2

VF091 - VF093 2

VF101 - VF102 2

VF161 - VF162 2

VF171 - VF172 2

VF180 - VF184 2

VF251 2

VK001 - VK006 1

VK007 - VK016 2

VK021 - VK022 1

VK031 - VK040 1

VK041 - VK056 2

VK081 - VK085 1

VK086 - VK113 2

VK131 - VK133 2

VK141 - VK148 2

VK161 - VK164 2

VK171 2

VK181 2

VK186 2

VL001 1

VL002 - VL006 2

VL011 1

VL701 - VL703 2

VL751 - VL755 2

VL806 - VL807 2

VL871 - VL873 2

VL891 - VL900 2

VL911 - VL914 2

VL931 - VL932 2

VL941 2

VN001 - VN041 2

VN051 - VN064 2

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BOEING SERVICE BULLETIN 767-57A0131
Variable Number Group

VN081 - VN099 2

VN111 - VN127 2

VN130 - VN137 2

VN151 - VN158 2

VN163 - VN168 2

VN171 - VN174 2

VN191 - VN198 2

VN211 - VN212 2

VN221 - VN225 2

VN231 - VN234 2

VN241 - VN243 2

VN251 - VN276 2

VN291 - VN293 2

VN301 - VN314 2

VN371 - VN372 2

VN376 2

VN381 - VN388 2

VN421 - VN427 2

VN436 2

VN471 - VN472 2

VN491 - VN513 2

VN531 - VN532 2

VN536 - VN537 2

VN541 - VN542 2

VN546 - VN547 2

VN551 2

VN556 - VN557 2

VN561 - VN562 2

VN631 - VN638 2

VN651 - VN658 2

VN671 - VN672 2

VN676 2

VN681 - VN691 2

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BOEING SERVICE BULLETIN 767-57A0131
Variable Number Group

VN731 - VN732 2

VN751 - VN753 2

VN791 - VN792 2

VN811 - VN813 2

VN921 - VN922 2

VN931 - VN936 2

VN951 - VN953 2

VN966 - VN972 2

VQ001 - VQ021 3

VQ071 - VQ086 3

VR051 - VR060 2

VR081 2

VR084 2

VR086 2

VR201 - VR211 2

VR251 2

VR256 - VR260 2

VR401 2

VR421 - VR423 2

VR426 2

VR441 2

VR461 2

VR471 - VR472 2

VS051 - VS056 2

VS061 2

VS066 - VS070 2

VS073 - VS078 2

VS091 - VS104 2

VS111 - VS113 2

VS131 - VS133 2

VS136 - VS137 2

VS176 - VS177 2

VS186 - VS187 2

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BOEING SERVICE BULLETIN 767-57A0131
Variable Number Group

VS196 - VS203 2

VS206 - VS208 2

VS211 2

VS216 - VS217 2

VS231 2

VS246 - VS248 2

VS261 - VS263 2

VS266 - VS274 2

VS291 - VS293 2

VS301 - VS303 2

VS306 - VS311 2

VS316 2

VS321 - VS324 2

VS331 - VS333 2

VS336 - VS337 2

VS366 - VS367 2

VS381 - VS382 2

VS391 - VS392 2

VS401 2

VS426 - VS428 2

VS466 - VS472 2

VS486 2

VS496 - VS497 2

VS506 - VS507 2

VS526 2

VS546 - VS549 2

VS701 - VS708 2

VS721 - VS730 2

VS751 - VS759 2

VS821 - VS825 2

VS841 - VS844 2

VS861 2

VS881 2

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BOEING SERVICE BULLETIN 767-57A0131
Variable Number Group

VT501 2

VW701 - VW721 2

VW851 2

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.

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BOEING SERVICE BULLETIN 767-57A0131
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

Model Zone

767-200, 767-300 572, 573, 672, 673

Group 2:

Affected Maintenance Zones

Model Zone

767-200, 767-300, 767-300F 572, 573, 672, 673

Group 3:

Affected Maintenance Zones

Model Zone

767-400ER 572, 573, 672, 673

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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BOEING SERVICE BULLETIN 767-57A0131
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)

Condition Action Compliance Time

Within 12 Months -

after the Original

Issue Date of this

Service Bulletin

Do Part 1 - Cap Seal Detailed Inspection

-ORDo Part 3 - All Fastener

Replacement within a

Support Rib for #1, #2, #7

and #8 Support Ribs (a)

All Airplanes

Do Part 2 - Fastener De- Before further flight -

tailed Inspection

Part 1, Condition 1: Damaged sealant found

Repeat Part 1 - Cap Seal - 12 Months (b)

Detailed Inspection

Part 1, Condition 2: No

damaged sealant found

-ANDWithin 36 Months -

after the Original

Issue Date of this

Service Bulletin

Do Part 3 - All Fastener

Replacement within a

Support Rib (b)

Do Part 3 - All Fastener Before further flight -

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

Do Part 3 - All Fastener Before further flight -

Replacement within a

Support Rib where the

corroded nut, bolt or

washer was found (b)

Part 2, Condition 4: Corrosion is found on the nut,

bolt or washers and no

crack found

Cap Seal Nut with BMS Before further flight -

5-95

Part 2, Condition 5: No

cracks or corrosion on the

nut, bolt or washers is

found -ANDRepeat Part 1 - Cap Seal - 12 Months (b)

Detailed Inspection

-ANDWithin 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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Group 1:

Table 1: Outboard Flap Support Rib Fastener Inspection and Replacement

Repeat Interval

(Not to Exceed)

Condition Action Compliance Time

(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)

Condition Action Compliance Time

Within 12 Months -

after the Original

Issue Date of this

Service Bulletin

Do Part 1 - Cap Seal Detailed Inspection

All Airplanes

Do Part 2 - Fastener De- Before further flight -

tailed Inspection

Part 1, Condition 1: Damaged sealant found

Repeat Part 1 - Cap Seal - 12 Months (a)

Detailed Inspection

Part 1, Condition 2: No

damaged sealant found

-ANDWithin 48 Months -

after the Original

Issue Date of this

Service Bulletin

Do Part 4 - Detailed Inspection for Nut Type (a)

Do Part 3 - All Fastener Before further flight -

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

Do Part 5 - Singular Fas- Before further flight -

tener Replacement at the

fastener location where

the corrosion was found

Part 2, Condition 4: Corrosion is found on the nut,

bolt or washers and no

crack found

-ANDDo Part 4 - Detailed Inspection for Nut Type on

all other fasteners within

the affected Support Rib

(c)

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BOEING SERVICE BULLETIN 767-57A0131
Group 2-3:

Table 2: Outboard Flap Support Rib Fastener Inspection and Replacement

Repeat Interval

(Not to Exceed)

Condition Action Compliance Time

Cap Seal Nut with BMS Before further flight -

5-95

Part 2, Condition 5: No

cracks or corrosion on the

nut, bolt or washers is

found -ANDRepeat Part 1 - Cap Seal - 12 Months (a)

Detailed Inspection

-ANDWithin 48 Months -

after the Original

Issue Date of this

Service Bulletin

Do Part 4 - Detailed Inspection for Nut Type (a)

Do Part 5 - Singular Fas- Before further flight -

tener Replacement

Part 4, Condition 6: Incorrect nut installed

Cap Seal Nut with BMS Before further flight -

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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BOEING SERVICE BULLETIN 767-57A0131
• 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:

Task Number of Persons Task Hours Elapsed Hours

Open Access 1 0.50 0.50

Part 1: FIGURE 1 1 0.40 0.40

Part 1: FIGURE 2 1 0.40 0.40

Part 1: FIGURE 3 1 0.40 0.40

Part 1: FIGURE 4 1 0.40 0.40

Part 2: FIGURE 5 1 0.15 0.15

Part 3: FIGURE 6 1 1.80 (a) 1.80 (a)

Part 3: FIGURE 7 1 1.80 (a) 1.80 (a)

Part 3: FIGURE 8 1 1.80 (a) 1.80 (a)

Part 3: FIGURE 9 1 1.80 (a) 1.80 (a)

Close Access 1 0.50 0.50

TOTAL FOR EACH AIRPLANE 2.75 2.75

(a) Add time to total if repairs are required.

Group 2-3:

Task Number of Persons Task Hours Elapsed Hours

Open Access 1 0.50 0.50

Part 1: FIGURE 1 1 0.40 0.40

Part 1: FIGURE 2 1 0.40 0.40

Part 1: FIGURE 3 1 0.40 0.40

Part 1: FIGURE 4 1 0.40 0.40

Part 2: FIGURE 5 1 0.15 0.15

Part 4: FIGURE 10 1 0.05 0.05

Part 4: FIGURE 11 1 0.05 0.05

Part 5: FIGURE 6 1 0.30 (a) 0.30 (a)

Part 5: FIGURE 7 1 0.30 (a) 0.30 (a)

Part 5: FIGURE 8 1 0.30 (a) 0.30 (a)

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Group 2-3:

Task Number of Persons Task Hours Elapsed Hours

Part 5: FIGURE 9 1 0.30 (a) 0.30 (a)

Close Access 1 0.50 0.50

TOTAL FOR EACH AIRPLANE 2.85 2.85

(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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BOEING SERVICE BULLETIN 767-57A0131
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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BOEING SERVICE BULLETIN 767-57A0131
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 Service Bulletin (US

Dollars)

ROLT as of the

original issue

date of this Service Bulletin (Calendar Days)

Kit Number Name Date QTY

August 30, 1 256 $2,553.00

2012

TOP KIT - 767 Wing

Flap Support Nut Fracture

015T1882-1

February 6, 48

2013

September 16, 49 256 $5,585.00

2013

TOP KIT - 767 Wing

Flap Support Nut Fracture - 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 Service Bulletin (US

Dollars)

ROLT as of the

original issue

date of this Service Bulletin (Calendar Days)

Kit Number Name Date QTY

August 30, 1 256 $2,553.00

2012

TOP KIT - 767 Wing

Flap Support Nut Fracture

015T1882-3

September 16, 1 256 $7,793.00

2013

TOP KIT - 767 Wing

Flap Support Nut Fracture - Oversize

015T1882-4

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BOEING SERVICE BULLETIN 767-57A0131
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

Existing Part Notes

Number

New Part Number QTY Name

-1 -2 -3 -4

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

BACB30US10K47 2 . . .

BACB30US10K47X . 2 . . BOLT

BACB30US10K47Y . 1 . . BOLT

BOLT, 12 PT

HEAD

BACB30US10K48 4 . . .

BOLT, 12 PT

HEAD

BACB30US10K48X . 4 . .

BOLT, 12 PT

HEAD

BACB30US10K48Y . 2 . .

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BOEING SERVICE BULLETIN 767-57A0131
Kit 015T1882

Existing Part Notes

Number

New Part Number QTY Name

-1 -2 -3 -4

BOLT, 12 PT

HEAD

BACB30US10K50 2 . . .

BOLT, 12 PT

HEAD

BACB30US10K50X . 2 . .

BOLT, 12 PT

HEAD

BACB30US10K50Y . 1 . .

BACB30US12K46 . . 2 . BOLT

BOLT, 12 PT

HEAD

BACB30US12K46X . . . 2

BOLT, 12 PT

HEAD

BACB30US12K46Y . . . 1

BOLT, 12 PT

HEAD

BACB30US12K47 . . 4 .

BOLT, 12 PT

HEAD

BACB30US12K47X . . . 4

BACB30US12K47Y . . . 2 BOLT

BOLT, 12 PT

HEAD

BACB30US12K48 . . 2 .

BOLT, 12 PT

HEAD

BACB30US12K48X . . . 2

BACB30US12K48Y . . . 1 BOLT

BOLT, 12 PT

HEAD

BACB30US12K49 2 . 2 .

BACB30US12K49X . 2 . 2 BOLT 767

BACB30US12K49Y . 1 . 1 BOLT

BOLT, 12 PT

HEAD

BACB30US12K50 2 . 2 .

BOLT, 12 PT

HEAD

BACB30US12K50X . 2 . 2

BOLT, 12 PT

HEAD

BACB30US12K50Y . 1 . 1

BOLT, 12 PT

HEAD

BACB30US12K51 4 . 4 .

BACB30US12K51X . 4 . 4 BOLT

BACB30US12K51Y . 2 . 2 BOLT

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Kit 015T1882

Existing Part Notes

Number

New Part Number QTY Name

-1 -2 -3 -4

SELF-LOCKING

NUT

BACN10HR10CD 8 . . .

SELF-LOCKING

NUT

BACN10HR12CD 8 . 16 .

BACW10BP101DP . 8 . . WASHER, PLAIN

BACW10BP102DP . 6 . . WASHER, PLAIN

BACW10BP10DP 8 . . . WASHER

BACW10BP121DP . 8 . 16 WASHER, PLAIN

BACW10BP122DP . 6 . 12 WASHER, PLAIN

BACW10BP12DP 8 . 16 . WASHER, PLAIN

WASHER, SELFALIGNBACW10CA101CVS . 8 . .

WASHER, SELFALIGNBACW10CA102CVS . 6 . .

WASHER, SELFALIGNBACW10CA10CCS 8 . . .

WASHER, SELFALIGNBACW10CA10CVS 8 . . .

WASHER, SELFALIGNBACW10CA121CVS . 8 . 16

WASHER, SELFALIGN

BACW10CA122CVS . 6 . 12

WASHER, SELFALIGNBACW10CA12CCS 8 . 16 .

WASHER, SELFALIGNBACW10CA12CVS 8 . 16 .

(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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BOEING SERVICE BULLETIN 767-57A0131
Group 1-2:

Part Number / QTY Name Notes

Specification

BACB30US10K47 2 BOLT, 12 POINT HEAD (c)

BACB30US10K47X 2 BOLT, 12 POINT HEAD (a)

BACB30US10K47Y 1 BOLT, 12 POINT HEAD (a)

BACB30US10K48 4 BOLT, 12 POINT HEAD (c)

BACB30US10K48X 4 BOLT, 12 POINT HEAD (a)

BACB30US10K48Y 2 BOLT, 12 POINT HEAD (a)

BACB30US10K50 2 BOLT, 12 POINT HEAD (c)

BACB30US10K50X 2 BOLT, 12 POINT HEAD (a)

BACB30US10K50Y 1 BOLT, 12 POINT HEAD (a)

BACW10CA10CVS 8 WASHER, SELF-ALIGNING (c)

BACW10CA101CVS 8 WASHER, SELF-ALIGNING (a)

BACW10CA102CVS 6 WASHER, SELF-ALIGNING (a)

BACW10CA10CCS 8 WASHER, SELF-ALIGNING (c)

WASHER, PLAIN AND COUNTER- (c)

SUNK

BACW10BP10DP 8

WASHER, PLAIN AND COUNTER- (a)

SUNK

BACW10BP101DP 8

WASHER, PLAIN AND COUNTER- (a)

SUNK

BACW10BP102DP 6

BACN10HR10CD 8 NUT, SELF-LOCKING (c)

BACB30US12K49 2 BOLT, 12 POINT HEAD (c)

BACB30US12K49X 2 BOLT, 12 POINT HEAD (a)

BACB30US12K49Y 1 BOLT, 12 POINT HEAD (a)

BACB30US12K50 2 BOLT, 12 POINT HEAD (c)

BACB30US12K50X 2 BOLT, 12 POINT HEAD (a)

BACB30US12K50Y 1 BOLT, 12 POINT HEAD (a)

BACB30US12K51 4 BOLT, 12 POINT HEAD (c)

BACB30US12K51X 4 BOLT, 12 POINT HEAD (a)

BACB30US12K51Y 2 BOLT, 12 POINT HEAD (a)

BACW10CA12CVS 8 WASHER, SELF-ALIGNING (c)

BACW10CA121CVS 8 WASHER, SELF-ALIGNING (a)

BACW10CA122CVS 6 WASHER, SELF-ALIGNING (a)

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Group 1-2:

Part Number / QTY Name Notes

Specification

BACW10CA12CCS 8 WASHER, SELF-ALIGNING (c)

WASHER, PLAIN AND COUNTER- (c)

SUNK

BACW10BP12DP 8

WASHER, PLAIN AND COUNTER- (a)

SUNK

BACW10BP121DP 8

WASHER, PLAIN AND COUNTER- (a)

SUNK

BACW10BP122DP 6

BACN10HR12CD 8 NUT, SELF-LOCKING (c)

BMS 5-95 - Sealant (b)

BMS 5-45 (BMS 5- - Fuel Tank Sealant (b)

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:

Part Number / QTY Name Notes

Specification

BACB30US12K46 2 BOLT, 12 POINT HEAD (c)

BACB30US12K46X 2 BOLT, 12 POINT HEAD (a)

BACB30US12K46Y 1 BOLT, 12 POINT HEAD (a)

BACB30US12K47 4 BOLT, 12 POINT HEAD (c)

BACB30US12K47X 4 BOLT, 12 POINT HEAD (a)

BACB30US12K47Y 2 BOLT, 12 POINT HEAD (a)

BACB30US12K48 2 BOLT, 12 POINT HEAD (c)

BACB30US12K48X 2 BOLT, 12 POINT HEAD (a)

BACB30US12K48Y 1 BOLT, 12 POINT HEAD (a)

BACW10CA12CVS 8 WASHER, SELF-ALIGNING (c)

BACW10CA121CVS 8 WASHER, SELF-ALIGNING (a)

BACW10CA122CVS 6 WASHER, SELF-ALIGNING (a)

BACW10CA12CCS 8 WASHER, SELF-ALIGNING (c)

WASHER, PLAIN AND COUNTER- (c)

SUNK

BACW10BP12DP 8

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Group 3:

Part Number / QTY Name Notes

Specification

WASHER, PLAIN AND COUNTER- (a)

SUNK

BACW10BP121DP 8

WASHER, PLAIN AND COUNTER- (a)

SUNK

BACW10BP122DP 6

BACN10HR12CD 8 NUT, SELF-LOCKING (c)

BACB30US12K49 2 BOLT, 12 POINT HEAD (c)

BACB30US12K49X 2 BOLT, 12 POINT HEAD (a)

BACB30US12K49Y 1 BOLT, 12 POINT HEAD (a)

BACB30US12K50 2 BOLT, 12 POINT HEAD (c)

BACB30US12K50X 2 BOLT, 12 POINT HEAD (a)

BACB30US12K50Y 1 BOLT, 12 POINT HEAD (a)

BACB30US12K51 4 BOLT, 12 POINT HEAD (c)

BACB30US12K51X 4 BOLT, 12 POINT HEAD (a)

BACB30US12K51Y 2 BOLT, 12 POINT HEAD (a)

BACW10CA12CVS 8 WASHER, SELF-ALIGNING (c)

BACW10CA121CVS 8 WASHER, SELF-ALIGNING (a)

BACW10CA122CVS 6 WASHER, SELF-ALIGNING (a)

BACW10CA12CCS 8 WASHER, SELF-ALIGNING (c)

WASHER, PLAIN AND COUNTER- (c)

SUNK

BACW10BP12DP 8

WASHER, PLAIN AND COUNTER- (a)

SUNK

BACW10BP121DP 8

WASHER, PLAIN AND COUNTER- (a)

SUNK

BACW10BP122DP 6

BACN10HR12CD 8 NUT, SELF-LOCKING (c)

BMS 5-95 - Sealant (b)

BMS 5-45 (BMS 5- - Fuel Tank Sealant (b)

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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BOEING SERVICE BULLETIN 767-57A0131
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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BOEING SERVICE BULLETIN 767-57A0131
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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BOEING SERVICE BULLETIN 767-57A0131
{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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BOEING SERVICE BULLETIN 767-57A0131
Left Wing Right Wing

Support Rib #1 Support Rib #2 Support Rib #7 Support Rib #8

FIGURE 1 FIGURE 2 FIGURE 3 FIGURE 4

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):

Left Wing Right Wing

Support Rib #1 Support Rib #2 Support Rib #7 Support Rib #8

FIGURE 6 FIGURE 7 FIGURE 8 FIGURE 9

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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BOEING SERVICE BULLETIN 767-57A0131
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:

Left Wing Right Wing

Support Rib #1 Support Rib #2 Support Rib #7 Support Rib #8

FIGURE 10 FIGURE 11 FIGURE 11 FIGURE 10

Group 3:

Left Wing Right Wing

Support Rib #1 Support Rib #2 Support Rib #7 Support Rib #8

FIGURE 11 FIGURE 11 FIGURE 11 FIGURE 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:

Left Wing Right Wing

Support Rib #1 Support Rib #2 Support Rib #7 Support Rib #8

FIGURE 6 FIGURE 7 FIGURE 8 FIGURE 9

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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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BOEING SERVICE BULLETIN 767-57A0131
FIGURE 1: CAP SEAL DETAILED INSPECTION FOR SUPPORT RIB # 1

(SHEET 1 OF 2)

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BOEING SERVICE BULLETIN 767-57A0131
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.

Step Task Name Identification Qty More Data

Do a Detailed Inspection of the sealant

around the nut for

damage. (a)

1 Inspect Cap Seal - 4

(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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FIGURE 2: CAP SEAL DETAILED INSPECTION FOR SUPPORT RIB # 2

(SHEET 1 OF 2)

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BOEING SERVICE BULLETIN 767-57A0131
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.

Step Task Name Identification Qty More Data

Do a Detailed Inspection of the sealant

around the nut for

damage. (a)

1 Inspect Cap Seal - 4

(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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FIGURE 3: CAP SEAL DETAILED INSPECTION FOR SUPPORT RIB # 7

(SHEET 1 OF 2)

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BOEING SERVICE BULLETIN 767-57A0131
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.

Step Task Name Identification Qty More Data

Do a Detailed Inspection of the sealant

around the nut for

damage. (a)

1 Inspect Cap Seal - 4

(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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FIGURE 4: CAP SEAL DETAILED INSPECTION FOR SUPPORT RIB # 8

(SHEET 1 OF 2)

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BOEING SERVICE BULLETIN 767-57A0131
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.

Step Task Name Identification Qty More Data

Do a Detailed Inspection of the sealant

around the nut for

damage. (a)

1 Inspect Cap Seal - 4

(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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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.

Step Task Name Identification Qty More Data

only from fastener

locations where

damaged sealant

was found.

1 Remove Cap Seal - 1

Do a Detailed Inspection for corrosion

and cracks on the

nut, bolt and washers.

2 Inspect Fastener - 1

FIGURE 5: FASTENER DETAILED INSPECTION

(SHEET 1 OF 1)

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FIGURE 6: FASTENER REPLACEMENTS FOR SUPPORT RIB # 1

(SHEET 1 OF 4)

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BOEING SERVICE BULLETIN 767-57A0131
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.

Step Task Name Identification Qty More Data

1 Remove Fastener - 4

FIGURE 6: FASTENER REPLACEMENTS FOR SUPPORT RIB # 1

(SHEET 2 OF 4)

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Step Task Name Identification Qty More Data

Do a High Frequency Eddy Current Inspection of the fastener hole for cracks

and corrosion in accordance 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)

2 Inspect Fastener Hole - 4

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)

3 Ream Fastener Hole - 4

Do a High Frequency Eddy Current Inspection of the fastener hole to make

sure all cracks and

corrosion has been

removed in accordance 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. (b)

Inspect Fastener Hole - 4

FIGURE 6: FASTENER REPLACEMENTS FOR SUPPORT RIB # 1

(SHEET 3 OF 4)

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Step Task Name Identification Qty More Data

wet with BMS 5-95

sealant. Refer to

APPENDIX A for applicable bolt part

numbers.

4 Install (New) Bolt - 4

Refer to APPENDIX

A for washer quantities and applicable

part numbers.

Install (New) Washer - -

Refer to APPENDIX

A for applicable nut

part numbers.

Install (New) Nut - 4

Cap seal nuts external to the wing fuel

tank. Refer to SOPM

20-50-19 as an accepted procedure.

5 Apply Sealant BMS 5-95 4

Cap seal bolt heads

internal to the wing

fuel tank. Refer to

SOPM 20-50-19 as

an accepted procedure.

BMS 5-45 (BMS 5-26 4

optional)

Apply Sealant

(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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FIGURE 7: FASTENER REPLACEMENTS FOR SUPPORT RIB # 2

(SHEET 1 OF 4)

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BOEING SERVICE BULLETIN 767-57A0131
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.

Step Task Name Identification Qty More Data

1 Remove Fastener - 4

FIGURE 7: FASTENER REPLACEMENTS FOR SUPPORT RIB # 2

(SHEET 2 OF 4)

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Step Task Name Identification Qty More Data

Do a High Frequency Eddy Current Inspection on the fastener hole for cracks

and corrosion in accordance 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)

2 Inspect Fastener Hole - 4

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)

3 Ream Fastener Hole - 4

Do a High Frequency Eddy Current Inspection of the fastener hole to make

sure all cracks and

corrosion has been

removed in accordance 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. (b)

Inspect Fastener Hole - 4

FIGURE 7: FASTENER REPLACEMENTS FOR SUPPORT RIB # 2

(SHEET 3 OF 4)

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BOEING SERVICE BULLETIN 767-57A0131
Step Task Name Identification Qty More Data

wet with BMS 5-95

sealant. Refer to

APPENDIX A for applicable bolt part

numbers.

4 Install (New) Bolt - 4

Refer to APPENDIX

A for washer quantities and applicable

part numbers.

Install (New) Washer - -

Refer to APPENDIX

A for applicable nut

part numbers.

Install (New) Nut - 4

Cap seal nuts external to the wing fuel

tank. Refer to SOPM

20-50-19 as an accepted procedure.

5 Apply Sealant BMS 5-95 4

Cap seal bolt heads

internal to the wing

fuel tank. Refer to

SOPM 20-50-19 as

an accepted procedure.

BMS 5-45 (BMS 5-26 4

optional)

Apply Sealant

(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)

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BOEING SERVICE BULLETIN 767-57A0131
FIGURE 8: FASTENER REPLACEMENTS FOR SUPPORT RIB # 7

(SHEET 1 OF 4)

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57 of 75

BOEING SERVICE BULLETIN 767-57A0131
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.

Step Task Name Identification Qty More Data

1 Remove Fastener - 4

FIGURE 8: FASTENER REPLACEMENTS FOR SUPPORT RIB # 7

(SHEET 2 OF 4)

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58 of 75

BOEING SERVICE BULLETIN 767-57A0131
Step Task Name Identification Qty More Data

Do a High Frequency Eddy Current Inspection on the fastener hole for cracks

and corrosion in accordance 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)

2 Inspect Fastener Hole - 4

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)

3 Ream Fastener Hole - 4

Do a High Frequency Eddy Current Inspection of the fastener hole to make

sure all cracks and

corrosion has been

removed in accordance 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. (b)

Inspect Fastener Hole - 4

FIGURE 8: FASTENER REPLACEMENTS FOR SUPPORT RIB # 7

(SHEET 3 OF 4)

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59 of 75

BOEING SERVICE BULLETIN 767-57A0131
Step Task Name Identification Qty More Data

wet with BMS 5-95

sealant. Refer to

APPENDIX A for applicable bolt part

numbers.

4 Install (New) Bolt - 4

Refer to APPENDIX

A for washer quantities and applicable

part numbers.

Install (New) Washer - -

Refer to APPENDIX

A for applicable nut

part numbers.

Install (New) Nut - 4

Cap seal nuts external to the wing fuel

tank. Refer to SOPM

20-50-19 as an accepted procedure.

5 Apply Sealant BMS 5-95 4

Cap seal bolt heads

internal to the wing

fuel tank. Refer to

SOPM 20-50-19 as

an accepted procedure.

BMS 5-45 (BMS 5-26 4

optional)

Apply Sealant

(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)

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BOEING SERVICE BULLETIN 767-57A0131
FIGURE 9: FASTENER REPLACEMENTS FOR SUPPORT RIB # 8

(SHEET 1 OF 4)

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61 of 75

BOEING SERVICE BULLETIN 767-57A0131
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.

Step Task Name Identification Qty More Data

1 Remove Fastener - 4

FIGURE 9: FASTENER REPLACEMENTS FOR SUPPORT RIB # 8

(SHEET 2 OF 4)

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62 of 75

BOEING SERVICE BULLETIN 767-57A0131
Step Task Name Identification Qty More Data

Do a High Frequency Eddy Current Inspection on the fastener hole for cracks

and corrosion in accordance 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)

2 Inspect Fastener Hole - 4

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)

3 Ream Fastener Hole - 4

Do a High Frequency Eddy Current Inspection of the fastener hole to make

sure all cracks and

corrosion has been

removed in accordance 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. (b)

Inspect Fastener Hole - 4

FIGURE 9: FASTENER REPLACEMENTS FOR SUPPORT RIB # 8

(SHEET 3 OF 4)

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63 of 75

BOEING SERVICE BULLETIN 767-57A0131
Step Task Name Identification Qty More Data

wet with BMS 5-95

sealant. Refer to

APPENDIX A for applicable bolt part

numbers.

4 Install (New) Bolt - 4

Refer to APPENDIX

A for washer quantities and applicable

part numbers.

Install (New) Washer - -

Refer to APPENDIX

A for applicable nut

part numbers.

Install (New) Nut - 4

Cap seal nuts external to the wing fuel

tank. Refer to SOPM

20-50-19 as an accepted procedure.

5 Apply Sealant BMS 5-95 4

Cap seal bolt heads

internal to the wing

fuel tank. Refer to

SOPM 20-50-19 as

an accepted procedure.

BMS 5-45 (BMS 5-26 4

optional)

Apply Sealant

(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 9: FASTENER REPLACEMENTS FOR SUPPORT RIB # 8

(SHEET 4 OF 4)

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BOEING SERVICE BULLETIN 767-57A0131
This Figure applies only to: Group 2.

FIGURE 10: NUT MEASUREMENT FOR CORRECT TYPE

(SHEET 1 OF 2)

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65 of 75

BOEING SERVICE BULLETIN 767-57A0131
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.

Step Task Name Identification Qty More Data

and compare to examples above to find

if correct or incorrect

nut is installed.

1 Measure Nut - 1

FIGURE 10: NUT MEASUREMENT FOR CORRECT TYPE

(SHEET 2 OF 2)

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BOEING SERVICE BULLETIN 767-57A0131
This Figure applies only to: Group 2-3.

FIGURE 11: NUT MEASUREMENT FOR CORRECT TYPE

(SHEET 1 OF 2)

Export Controlled ECCN: 9E991 - BOEING

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67 of 75

BOEING SERVICE BULLETIN 767-57A0131
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.

Step Task Name Identification Qty More Data

and compare to examples above to find

if correct or incorrect

nut is installed.

1 Measure Nut - 1

FIGURE 11: NUT MEASUREMENT FOR CORRECT TYPE

(SHEET 2 OF 2)

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BOEING SERVICE BULLETIN 767-57A0131
GROUP 1-2: Support Rib # 1 and # 8

CODE Identification QTY Name Hole Dia (a) More Data

0.6245 -

0.6255

A BACB30US10K47 1 BOLT, 12 POINT HEAD

0.6401 - Optional.

0.6411

BACB30US10K47X 1 BOLT, 12 POINT HEAD

0.6557 - Optional.

0.6567

BACB30US10K47Y 1 BOLT, 12 POINT HEAD

0.6245 -

0.6255

B BACB30US10K48 2 BOLT, 12 POINT HEAD

0.6401 - Optional.

0.6411

BACB30US10K48X 2 BOLT, 12 POINT HEAD

0.6557 - Optional.

0.6567

BACB30US10K48Y 1 BOLT, 12 POINT HEAD

0.6245 -

0.6255

C BACB30US10K50 1 BOLT, 12 POINT HEAD

0.6401 - Optional.

0.6411

BACB30US10K50X 1 BOLT, 12 POINT HEAD

0.6557 - Optional.

0.6567

BACB30US10K50Y 1 BOLT, 12 POINT HEAD

MATING WASHERS AND NUTS

Use with BACB30US10K*

bolt. Install under head of

bolt.

WASHER, SELF-ALIGN- -

ING

BACW10CA10CVS 4

APPENDIX A: PART NUMBERS AND QUANTITIES BY SUPPORT RIB NUMBER

(SHEET 1 OF 6)

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BOEING SERVICE BULLETIN 767-57A0131
GROUP 1-2: Support Rib # 1 and # 8

CODE Identification QTY Name Hole Dia (a) More Data

Use with BACB30US10K*X

bolt. Install under head of

bolt.

WASHER, SELF-ALIGN- -

ING

BACW10CA101CVS 4

Use with BACB30US10K*Y

bolt. Install under head of

bolt.

WASHER, SELF-ALIGN- -

ING

BACW10CA102CVS 3

Use with any

BACB30US10K bolt. Install

under head of bolt.

WASHER, SELF-ALIGN- -

ING

BACW10CA10CCS 4

Use with BACB30US10K*

bolt. Install under nut.

WASHER, PLAIN AND -

COUNTERSUNK

BACW10BP10DP 4

Use with BACB30US10K*X

bolt. Install under nut.

WASHER, PLAIN AND -

COUNTERSUNK

BACW10BP101DP 4

Use with BACB30US10K*Y

bolt. Install under nut.

WASHER, PLAIN AND -

COUNTERSUNK

BACW10BP102DP 3

Use with any

BACB30US10K bolt.

Torque to 1900 - 2300 inlbs.

BACN10HR10CD 4 NUT, SELF-LOCKING -

(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.

GROUP 1-2: Support Rib # 2 and # 7

CODE Identification QTY Name Hole Dia (a) More Data

0.7495 -

0.7505

A BACB30US12K49 1 BOLT, 12 POINT HEAD

0.7651 - Optional.

0.7661

BACB30US12K49X 1 BOLT, 12 POINT HEAD

0.7807 - Optional.

0.7817

BACB30US12K49Y 1 BOLT, 12 POINT HEAD

0.7495 -

0.7505

B BACB30US12K50 1 BOLT, 12 POINT HEAD

0.7651 - Optional.

0.7661

BACB30US12K50X 1 BOLT, 12 POINT HEAD

0.7807 - Optional.

0.7817

BACB30US12K50Y 1 BOLT, 12 POINT HEAD

APPENDIX A: PART NUMBERS AND QUANTITIES BY SUPPORT RIB NUMBER

(SHEET 2 OF 6)

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BOEING SERVICE BULLETIN 767-57A0131
GROUP 1-2: Support Rib # 2 and # 7

CODE Identification QTY Name Hole Dia (a) More Data

0.7495 -

0.7505

C BACB30US12K51 2 BOLT, 12 POINT HEAD

0.7651 - Optional.

0.7661

BACB30US12K51X 2 BOLT, 12 POINT HEAD

0.7807 - Optional.

0.7817

BACB30US12K51Y 1 BOLT, 12 POINT HEAD

MATING WASHERS AND NUTS

Use with BACB30US12K*

bolt. Install under head of

bolt.

WASHER, SELF-ALIGN- -

ING

BACW10CA12CVS 4

Use with BACB30US12K*X

bolt. Install under head of

bolt.

WASHER, SELF-ALIGN- -

ING

BACW10CA121CVS 4

Use with BACB30US12K*Y

bolt. Install under head of

bolt.

WASHER, SELF-ALIGN- -

ING

BACW10CA122CVS 3

Use with any

BACB30US12K bolt. Install

under head of bolt.

WASHER, SELF-ALIGN- -

ING

BACW10CA12CCS 4

Use with BACB30US12K*

bolt. Install under nut.

WASHER, PLAIN AND -

COUNTERSUNK

BACW10BP12DP 4

Use with BACB30US12K*X

bolt. Install under nut.

WASHER, PLAIN AND -

COUNTERSUNK

BACW10BP121DP 4

Use with BACB30US12K*Y

bolt. Install under nut.

WASHER, PLAIN AND -

COUNTERSUNK

BACW10BP122DP 3

Use with any

BACB30US12K bolt.

Torque to 3300 - 4300 inlbs.

BACN10HR12CD 4 NUT, SELF-LOCKING -

(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.

APPENDIX A: PART NUMBERS AND QUANTITIES BY SUPPORT RIB NUMBER

(SHEET 3 OF 6)

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BOEING SERVICE BULLETIN 767-57A0131
GROUP 3: Support Rib # 1 and # 8

CODE Identification QTY Name Hole Dia (a) More Data

0.7495 -

0.7505

A BACB30US12K46 1 BOLT, 12 POINT HEAD

0.7651 - Optional.

0.7661

BACB30US12K46X 1 BOLT, 12 POINT HEAD

0.7807 - Optional.

0.7817

BACB30US12K46Y 1 BOLT, 12 POINT HEAD

0.7495 -

0.7505

B BACB30US12K47 2 BOLT, 12 POINT HEAD

0.7651 - Optional.

0.7661

BACB30US12K47X 2 BOLT, 12 POINT HEAD

0.7807 - Optional.

0.7817

BACB30US12K47Y 1 BOLT, 12 POINT HEAD

0.7495 -

0.7505

C BACB30US12K48 1 BOLT, 12 POINT HEAD

0.7651 - Optional.

0.7661

BACB30US12K48X 1 BOLT, 12 POINT HEAD

0.7807 - Optional.

0.7817

BACB30US12K48Y 1 BOLT, 12 POINT HEAD

MATING WASHERS AND NUTS

Use with BACB30US12K*

bolt. Install under head of

bolt.

WASHER, SELF-ALIGN- -

ING

BACW10CA12CVS 4

Use with BACB30US12K*X

bolt. Install under head of

bolt.

WASHER, SELF-ALIGN- -

ING

BACW10CA121CVS 4

Use with BACB30US12K*Y

bolt. Install under head of

bolt.

WASHER, SELF-ALIGN- -

ING

BACW10CA122CVS 3

Use with any

BACB30US12K bolt. Install

under head of bolt.

WASHER, SELF-ALIGN- -

ING

BACW10CA12CCS 4

Use with BACB30US12K*

bolt. Install under nut.

WASHER, PLAIN AND -

COUNTERSUNK

BACW10BP12DP 4

Use with BACB30US12K*X

bolt. Install under nut.

WASHER, PLAIN AND -

COUNTERSUNK

BACW10BP121DP 4

Use with BACB30US12K*Y

bolt. Install under nut.

WASHER, PLAIN AND -

COUNTERSUNK

BACW10BP122DP 3

APPENDIX A: PART NUMBERS AND QUANTITIES BY SUPPORT RIB NUMBER

(SHEET 4 OF 6)

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BOEING SERVICE BULLETIN 767-57A0131
GROUP 3: Support Rib # 1 and # 8

CODE Identification QTY Name Hole Dia (a) More Data

Use with any

BACB30US12K bolt.

Torque to 3300 - 4300 inlbs.

BACN10HR12CD 4 NUT, SELF-LOCKING -

(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.

GROUP 3: Support Rib # 2 and # 7

CODE Identification QTY Name Hole Dia (a) More Data

0.7495 -

0.7505

A BACB30US12K49 1 BOLT, 12 POINT HEAD

0.7651 - Optional.

0.7661

BACB30US12K49X 1 BOLT, 12 POINT HEAD

0.7807 - Optional.

0.7817

BACB30US12K49Y 1 BOLT, 12 POINT HEAD

0.7495 -

0.7505

B BACB30US12K50 1 BOLT, 12 POINT HEAD

0.7651 - Optional.

0.7661

BACB30US12K50X 1 BOLT, 12 POINT HEAD

0.7807 - Optional.

0.7817

BACB30US12K50Y 1 BOLT, 12 POINT HEAD

0.7495 -

0.7505

C BACB30US12K51 2 BOLT, 12 POINT HEAD

0.7651 - Optional.

0.7661

BACB30US12K51X 2 BOLT, 12 POINT HEAD

0.7807 - Optional.

0.7817

BACB30US12K51Y 1 BOLT, 12 POINT HEAD

MATING WASHERS AND NUTS

Use with BACB30US12K*

bolt. Install under head of

bolt.

WASHER, SELF-ALIGN- -

ING

BACW10CA12CVS 4

Use with BACB30US12K*X

bolt. Install under head of

bolt.

WASHER, SELF-ALIGN- -

ING

BACW10CA121CVS 4

Use with BACB30US12K*Y

bolt. Install under head of

bolt.

WASHER, SELF-ALIGN- -

ING

BACW10CA122CVS 3

APPENDIX A: PART NUMBERS AND QUANTITIES BY SUPPORT RIB NUMBER

(SHEET 5 OF 6)

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BOEING SERVICE BULLETIN 767-57A0131
GROUP 3: Support Rib # 2 and # 7

CODE Identification QTY Name Hole Dia (a) More Data

Use with any

BACB30US12K bolt. Install

under head of bolt.

WASHER, SELF-ALIGN- -

ING

BACW10CA12CCS 4

Use with BACB30US12K*

bolt. Install under nut.

WASHER, PLAIN AND -

COUNTERSUNK

BACW10BP12DP 4

Use with BACB30US12K*X

bolt. Install under nut.

WASHER, PLAIN AND -

COUNTERSUNK

BACW10BP121DP 4

Use with BACB30US12K*Y

bolt. Install under nut.

WASHER, PLAIN AND -

COUNTERSUNK

BACW10BP122DP 3

Use with any

BACB30US12K bolt.

Torque to 3300 - 4300 inlbs.

BACN10HR12CD 4 NUT, SELF-LOCKING -

(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.

APPENDIX A: PART NUMBERS AND QUANTITIES BY SUPPORT RIB NUMBER

(SHEET 6 OF 6)

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BOEING SERVICE BULLETIN 767-57A0131
Nominal hole diameters in the outboard trailing edge flap support rib and the actuator backup fittings are slightly

larger in diameter than the nominal hole diameters in the rear spar and lower chord and the fastener diameters.

These nominal hole diameters are per production and part drawings.

GROUP 1-2: Support Rib # 1 and # 8

Name Identification Nominal Hole Diameter

Outboard Trailing Edge Flap Support Rib 113T1345 0.650 - 0.660

Actuator Backup Fitting 112T5121 0.650 - 0.660

GROUP 1-2: Support Rib # 2 and # 7

Name Identification Nominal Hole Diameter

Outboard Trailing Edge Flap Support Rib 113T1345 0.780 - 0.790

Actuator Backup Fitting 112T5122 0.780 - 0.790

GROUP 3: Support Rib # 1 and # 8

Name Identification Nominal Hole Diameter

Outboard Trailing Edge Flap Support Rib 113T1345 0.780 - 0.790

Actuator Backup Fitting 112T5121 0.780 - 0.790

GROUP 3: Support Rib # 2 and # 7

Name Identification Nominal Hole Diameter

Outboard Trailing Edge Flap Support Rib 113T1345 0.780 - 0.790

Actuator Backup Fitting 112T5122 0.780 - 0.790

APPENDIX B: NOMINAL HOLE DIAMETERS FOR OUTBOARD TRAILING EDGE FLAP SUPPORT RIB

AND ACTUATOR SUPPORT FITTINGS

(SHEET 1 OF 1)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: October 30, 2012

Revision 1 May 08, 2013 767-57A0131

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BOEING SERVICE BULLETIN 767-57A0131