### 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.9E991 ECCN: 

## 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 Unpublished Work.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2012 767-57A0131 Revision 1: May 08, 2013 1 of 75 2.0Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 30, 2012 767-57A0131 Revision 1: May 08, 2013 2 of 75 **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

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 30, 2012 767-57A0131 Revision 1: May 08, 2013 3 of 75 **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

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 30, 2012 767-57A0131 Revision 1: May 08, 2013 4 of 75 **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.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 30, 2012 767-57A0131 Revision 1: May 08, 2013 5 of 7514. 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, 2012 Original Issue: May 08, 2013 Revision 1:

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 30, 2012 767-57A0131 Revision 1: May 08, 2013 6 of 75 **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.
**Reference Affected**  **Planning Data** Paragraph 1.A.2., Spares Affected No Spares Affected

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 30, 2012 767-57A0131 Revision 1: May 08, 2013 7 of 75**Reference Affected**  **Planning Data** Paragraph 1.E., Compliance and Paragraph 1.F., Approval Yes AD Related Paragraph 1.H., Weight and Balance Changes No Weight and Balance Change Paragraph 1.I., Electrical Load Data No Electrical Load Changed Paragraph 1.K., Publications Affected No Publications Affected Paragraph 1.K., Publications Affected No Airplane Flight Operations Affected (Flight CrewOperations Manual and/or FAA Approved Airplane Flight Manual) Paragraph 2.C.1., Kits/Parts Yes Kits/Parts Required Paragraph 2.C.2., Parts and Materials Supplied by the Operator Yes Operator Supplied Material Paragraph 2.F., Special Tooling Necessary to do this Service Bulletin No Special 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.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 30, 2012 767-57A0131 Revision 1: May 08, 2013 8 of 75 **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.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 30, 2012 767-57A0131 Revision 1: May 08, 2013 9 of 75 **BOEING SERVICE BULLETIN 767-57A0131**Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 30, 2012 767-57A0131 Revision 1: May 08, 2013 10 of 75 **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.

**DESCRIPTION CONFIGURATION**  **GROUP** 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 **Group Variable Number**  1 VA001 - VA020 1 VA301 - VA315 1 VA501 - VA530

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 30, 2012 767-57A0131 Revision 1: May 08, 2013 11 of 75**Group Variable Number**  1 VA701 - VA712 2 VA713 - VA719 1 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 2 VB326 - VB332 1 VB371 - VB373 1 VB401 2 VB441 - VB444 1 VE001 - VE003 1 VE021 - VE023 1 VE041 - VE043 1 VE061 - VE069 1 VE083 - VE084 2 VE085 - VE086 1 VE101 - VE103 2 VE104 1 VE116 - VE117 2 VE118 1 VE121 - VE126 1 VE141 - VE145 2 VE146 - VE152 2 VE171 - VE172 2 VF001 - VF002 2 VF041 - VF042 2 VF051 2 VF061 - VF062

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 30, 2012 767-57A0131 Revision 1: May 08, 2013 12 of 75 **BOEING SERVICE BULLETIN 767-57A0131 Group**  **Variable Number**2 VF071 - VF072 2 VF091 - VF093 2 VF101 - VF102 2 VF161 - VF162 2 VF171 - VF172 2 VF180 - VF184 2 VF251 1 VK001 - VK006 2 VK007 - VK016 1 VK021 - VK022 1 VK031 - VK040 2 VK041 - VK056 1 VK081 - VK085 2 VK086 - VK113 2 VK131 - VK133 2 VK141 - VK148 2 VK161 - VK164 2 VK171 2 VK181 2 VK186 1 VL001 2 VL002 - VL006 1 VL011 2 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

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 30, 2012 767-57A0131 Revision 1: May 08, 2013 13 of 75 **BOEING SERVICE BULLETIN 767-57A0131 Group**  **Variable Number**2 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

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 30, 2012 767-57A0131 Revision 1: May 08, 2013 14 of 75 **BOEING SERVICE BULLETIN 767-57A0131 Group**  **Variable Number**2 VN731 - VN732 2 VN751 - VN753 2 VN791 - VN792 2 VN811 - VN813 2 VN921 - VN922 2 VN931 - VN936 2 VN951 - VN953 2 VN966 - VN972 3 VQ001 - VQ021 3 VQ071 - VQ086 2 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

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 30, 2012 767-57A0131 Revision 1: May 08, 2013 15 of 75 **BOEING SERVICE BULLETIN 767-57A0131 Group**  **Variable Number**2 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

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 30, 2012 767-57A0131 Revision 1: May 08, 2013 16 of 75 **BOEING SERVICE BULLETIN 767-57A0131 Group**  **Variable Number**2 VT501 2 VW701 - VW721 2 VW851 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 PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 30, 2012 767-57A0131 Revision 1: May 08, 2013 17 of 75 **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 Zone**  **Model** 572, 573, 672, 673 767-200, 767-300 **Group 2:**
**Affected Maintenance Zones Zone**  **Model** 572, 573, 672, 673 767-200, 767-300, 767-300F **Group 3:**
**Affected Maintenance Zones Zone**  **Model** 572, 573, 672, 673 767-400ER **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.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 30, 2012 767-57A0131 Revision 1: May 08, 2013 18 of 75 **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)**  **Compliance Time Action**  **Condition**

- Within 12 Months after the Original Issue Date of this Service BulletinDo 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

- Before further flight Do Part 2 - Fastener De- tailed InspectionPart 1, Condition 1: Damaged 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 flight Do 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 flight Do Part 3 - All Fastener 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

- Before further flight Cap Seal Nut with BMS 5-95 Part 2, Condition 5: No cracks or corrosion on the nut, bolt or washers is found -AND12 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.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 30, 2012 767-57A0131 Revision 1: May 08, 2013 19 of 75 **BOEING SERVICE BULLETIN 767-57A0131 Group 1:**  **Table 1: Outboard Flap Support Rib Fastener Inspection and Replacement Repeat Interval**  **(Not to Exceed) Compliance Time**  **Action Condition**  (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 Time Action**  **Condition**

- Within 12 Months after the Original Issue Date of this Service BulletinDo Part 1 - Cap Seal Detailed Inspection All Airplanes

- Before further flight Do Part 2 - Fastener De- tailed InspectionPart 1, Condition 1: Damaged 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 BulletinDo Part 4 - Detailed Inspection for Nut Type (a)

- Before further flight Do 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 flight Do Part 5 - Singular Fas- tener Replacement at the fastener location where the corrosion was foundPart 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)

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 30, 2012 767-57A0131 Revision 1: May 08, 2013 20 of 75 **BOEING SERVICE BULLETIN 767-57A0131 Group 2-3:**  **Table 2: Outboard Flap Support Rib Fastener Inspection and Replacement Repeat Interval**  **(Not to Exceed) Compliance Time**  **Action Condition** 

- Before further flight Cap Seal Nut with BMS 5-95 Part 2, Condition 5: No cracks or corrosion on the nut, bolt or washers is found -AND12 Months (a)

- Repeat Part 1 - Cap Seal Detailed Inspection-AND- Within 48 Months after the Original Issue Date of this Service BulletinDo Part 4 - Detailed Inspection for Nut Type (a)

- Before further flight Do Part 5 - Singular Fas- tener ReplacementPart 4, Condition 6: Incorrect nut installed

- Before further flight Cap 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:

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 30, 2012 767-57A0131 Revision 1: May 08, 2013 21 of 75 **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: Elapsed Hours**  **Task Hours Number of Persons**  **Task** 0.50 0.50 1 Open Access 0.40 0.40 1 Part 1: FIGURE 1 0.40 0.40 1 Part 1: FIGURE 2 0.40 0.40 1 Part 1: FIGURE 3 0.40 0.40 1 Part 1: FIGURE 4 0.15 0.15 1 Part 2: FIGURE 5 1.80 (a) 1.80 (a) 1 Part 3: FIGURE 6 1.80 (a) 1.80 (a) 1 Part 3: FIGURE 7 1.80 (a) 1.80 (a) 1 Part 3: FIGURE 8 1.80 (a) 1.80 (a) 1 Part 3: FIGURE 9 0.50 0.50 1 Close Access 2.75 2.75 TOTAL FOR EACH AIRPLANE (a) Add time to total if repairs are required. **Group 2-3: Elapsed Hours**  **Task Hours Number of Persons**  **Task** 0.50 0.50 1 Open Access 0.40 0.40 1 Part 1: FIGURE 1 0.40 0.40 1 Part 1: FIGURE 2 0.40 0.40 1 Part 1: FIGURE 3 0.40 0.40 1 Part 1: FIGURE 4 0.15 0.15 1 Part 2: FIGURE 5 0.05 0.05 1 Part 4: FIGURE 10 0.05 0.05 1 Part 4: FIGURE 11 0.30 (a) 0.30 (a) 1 Part 5: FIGURE 6 0.30 (a) 0.30 (a) 1 Part 5: FIGURE 7 0.30 (a) 0.30 (a) 1 Part 5: FIGURE 8

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 30, 2012 767-57A0131 Revision 1: May 08, 2013 22 of 75 **BOEING SERVICE BULLETIN 767-57A0131 Group 2-3:**  **Elapsed Hours Task Hours**  **Number of Persons Task**  0.30 (a) 0.30 (a) 1 Part 5: FIGURE 9 0.50 0.50 1 Close Access 2.85 2.85 TOTAL 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.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 30, 2012 767-57A0131 Revision 1: May 08, 2013 23 of 75 **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.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 30, 2012 767-57A0131 Revision 1: May 08, 2013 24 of 75 **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 Ser vice Bulletin (US**  **Dollars) ROLT as of the**  **original issue date of this Ser** **vice Bulletin (Cal endar Days)**  **QTY Date**  **Name Kit Number** 

$2,553.00 256 1 August 30, 2012 TOP KIT - 767 WingFlap Support Nut Fracture 015T1882-1
48 February 6, 2013 $5,585.00 256 49 September 16, 2013 TOP KIT - 767 WingFlap 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 Ser vice Bulletin (US**  **Dollars) ROLT as of the**  **original issue date of this Ser** **vice Bulletin (Cal endar Days)**  **QTY Date**  **Name Kit Number** 

$2,553.00 256 1 August 30, 2012 TOP KIT - 767 WingFlap Support Nut Fracture 015T1882-3

$7,793.00 256 1 September 16, 2013 TOP KIT - 767 WingFlap Support Nut Fracture - Oversize 015T1882-4

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 30, 2012 767-57A0131 Revision 1: May 08, 2013 25 of 75 **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 Notes**  **Existing Part Number**  **Name QTY**  **New 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 . . . 2 BACB30US10K47
BOLT

. . 2

. BACB30US10K47X BOLT

. . 1

. BACB30US10K47Y BOLT, 12 PT HEAD . . . 4 BACB30US10K48 BOLT, 12 PT HEAD . . 4

. BACB30US10K48X BOLT, 12 PT HEAD . . 2

. BACB30US10K48Y

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 30, 2012 767-57A0131 Revision 1: May 08, 2013 26 of 75 **BOEING SERVICE BULLETIN 767-57A0131 Kit 015T1882**  **Notes Existing Part**  **Number Name**  **QTY New Part Number**  **-4 -3**  **-2 -1**  BOLT, 12 PT HEAD . . . 2 BACB30US10K50 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
BOLT 2

. . . BACB30US12K47Y BOLT, 12 PT HEAD . 2

. . BACB30US12K48 BOLT, 12 PT HEAD 2

. . . BACB30US12K48X
BOLT 1

. . . BACB30US12K48Y BOLT, 12 PT HEAD . 2

. 2 BACB30US12K49
BOLT 767 2

. 2

. BACB30US12K49X BOLT 1

. 1

. BACB30US12K49Y BOLT, 12 PT HEAD . 2

. 2 BACB30US12K50 BOLT, 12 PT HEAD 2

. 2

. BACB30US12K50X BOLT, 12 PT HEAD 1

. 1

. BACB30US12K50Y BOLT, 12 PT HEAD . 4

. 4 BACB30US12K51
BOLT 4

. 4

. BACB30US12K51X BOLT 2

. 2

. BACB30US12K51Y

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 30, 2012 767-57A0131 Revision 1: May 08, 2013 27 of 75 **BOEING SERVICE BULLETIN 767-57A0131 Kit 015T1882**  **Notes Existing Part**  **Number Name**  **QTY New Part Number**  **-4 -3**  **-2 -1**  SELF-LOCKING NUT . . . 8 BACN10HR10CD
SELF-LOCKING NUT . 16

. 8 BACN10HR12CD WASHER, PLAIN

. . 8

. BACW10BP101DP WASHER, PLAIN

. . 6

. BACW10BP102DP WASHER

. . . 8 BACW10BP10DP WASHER, PLAIN 16

. 8

. BACW10BP121DP WASHER, PLAIN 12

. 6

. BACW10BP122DP WASHER, PLAIN

. 16

. 8 BACW10BP12DP WASHER, SELFALIGN . . 8

. BACW10CA101CVS WASHER, SELFALIGN . . 6

. BACW10CA102CVS WASHER, SELFALIGN . . . 8 BACW10CA10CCS WASHER, SELFALIGN . . . 8 BACW10CA10CVS WASHER, SELFALIGN 16

. 8

. BACW10CA121CVS WASHER, SELFALIGN 12

. 6

. BACW10CA122CVS WASHER, SELFALIGN . 16

. 8 BACW10CA12CCS WASHER, SELFALIGN . 16

. 8 BACW10CA12CVS (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.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 30, 2012 767-57A0131 Revision 1: May 08, 2013 28 of 75 **BOEING SERVICE BULLETIN 767-57A0131 Group 1-2:** 
**Notes Name**  **QTY Part Number /**  **Specification** (c) BOLT, 12 POINT HEAD 2 BACB30US10K47 (a) BOLT, 12 POINT HEAD 2 BACB30US10K47X (a) BOLT, 12 POINT HEAD 1 BACB30US10K47Y (c) BOLT, 12 POINT HEAD 4 BACB30US10K48 (a) BOLT, 12 POINT HEAD 4 BACB30US10K48X (a) BOLT, 12 POINT HEAD 2 BACB30US10K48Y (c) BOLT, 12 POINT HEAD 2 BACB30US10K50 (a) BOLT, 12 POINT HEAD 2 BACB30US10K50X (a) BOLT, 12 POINT HEAD 1 BACB30US10K50Y (c) WASHER, SELF-ALIGNING 8 BACW10CA10CVS (a) WASHER, SELF-ALIGNING 8 BACW10CA101CVS (a) WASHER, SELF-ALIGNING 6 BACW10CA102CVS (c) WASHER, SELF-ALIGNING 8 BACW10CA10CCS (c) WASHER, PLAIN AND COUNTER- SUNK 8 BACW10BP10DP (a) WASHER, PLAIN AND COUNTER- SUNK 8 BACW10BP101DP (a) WASHER, PLAIN AND COUNTER- SUNK 6 BACW10BP102DP (c) NUT, SELF-LOCKING 8 BACN10HR10CD (c) BOLT, 12 POINT HEAD 2 BACB30US12K49 (a) BOLT, 12 POINT HEAD 2 BACB30US12K49X (a) BOLT, 12 POINT HEAD 1 BACB30US12K49Y (c) BOLT, 12 POINT HEAD 2 BACB30US12K50 (a) BOLT, 12 POINT HEAD 2 BACB30US12K50X (a) BOLT, 12 POINT HEAD 1 BACB30US12K50Y (c) BOLT, 12 POINT HEAD 4 BACB30US12K51 (a) BOLT, 12 POINT HEAD 4 BACB30US12K51X (a) BOLT, 12 POINT HEAD 2 BACB30US12K51Y (c) WASHER, SELF-ALIGNING 8 BACW10CA12CVS (a) WASHER, SELF-ALIGNING 8 BACW10CA121CVS (a) WASHER, SELF-ALIGNING 6 BACW10CA122CVS

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 30, 2012 767-57A0131 Revision 1: May 08, 2013 29 of 75 **BOEING SERVICE BULLETIN 767-57A0131 Group 1-2:** 
**Notes Name**  **QTY Part Number /**  **Specification** (c) WASHER, SELF-ALIGNING 8 BACW10CA12CCS (c) WASHER, PLAIN AND COUNTER- SUNK 8 BACW10BP12DP (a) WASHER, PLAIN AND COUNTER- SUNK 8 BACW10BP121DP (a) WASHER, PLAIN AND COUNTER- SUNK 6 BACW10BP122DP (c) NUT, SELF-LOCKING 8 BACN10HR12CD (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:**
**Notes Name**  **QTY Part Number /**  **Specification** (c) BOLT, 12 POINT HEAD 2 BACB30US12K46 (a) BOLT, 12 POINT HEAD 2 BACB30US12K46X (a) BOLT, 12 POINT HEAD 1 BACB30US12K46Y (c) BOLT, 12 POINT HEAD 4 BACB30US12K47 (a) BOLT, 12 POINT HEAD 4 BACB30US12K47X (a) BOLT, 12 POINT HEAD 2 BACB30US12K47Y (c) BOLT, 12 POINT HEAD 2 BACB30US12K48 (a) BOLT, 12 POINT HEAD 2 BACB30US12K48X (a) BOLT, 12 POINT HEAD 1 BACB30US12K48Y (c) WASHER, SELF-ALIGNING 8 BACW10CA12CVS (a) WASHER, SELF-ALIGNING 8 BACW10CA121CVS (a) WASHER, SELF-ALIGNING 6 BACW10CA122CVS (c) WASHER, SELF-ALIGNING 8 BACW10CA12CCS (c) WASHER, PLAIN AND COUNTER- SUNK 8 BACW10BP12DP

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 30, 2012 767-57A0131 Revision 1: May 08, 2013 30 of 75 **BOEING SERVICE BULLETIN 767-57A0131 Group 3:** 
**Notes Name**  **QTY Part Number /**  **Specification** (a) WASHER, PLAIN AND COUNTER- SUNK 8 BACW10BP121DP (a) WASHER, PLAIN AND COUNTER- SUNK 6 BACW10BP122DP (c) NUT, SELF-LOCKING 8 BACN10HR12CD (c) BOLT, 12 POINT HEAD 2 BACB30US12K49 (a) BOLT, 12 POINT HEAD 2 BACB30US12K49X (a) BOLT, 12 POINT HEAD 1 BACB30US12K49Y (c) BOLT, 12 POINT HEAD 2 BACB30US12K50 (a) BOLT, 12 POINT HEAD 2 BACB30US12K50X (a) BOLT, 12 POINT HEAD 1 BACB30US12K50Y (c) BOLT, 12 POINT HEAD 4 BACB30US12K51 (a) BOLT, 12 POINT HEAD 4 BACB30US12K51X (a) BOLT, 12 POINT HEAD 2 BACB30US12K51Y (c) WASHER, SELF-ALIGNING 8 BACW10CA12CVS (a) WASHER, SELF-ALIGNING 8 BACW10CA121CVS (a) WASHER, SELF-ALIGNING 6 BACW10CA122CVS (c) WASHER, SELF-ALIGNING 8 BACW10CA12CCS (c) WASHER, PLAIN AND COUNTER- SUNK 8 BACW10BP12DP (a) WASHER, PLAIN AND COUNTER- SUNK 8 BACW10BP121DP (a) WASHER, PLAIN AND COUNTER- SUNK 6 BACW10BP122DP (c) NUT, SELF-LOCKING 8 BACN10HR12CD (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.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 30, 2012 767-57A0131 Revision 1: May 08, 2013 31 of 75 **BOEING SERVICE BULLETIN 767-57A0131**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.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 30, 2012 767-57A0131 Revision 1: May 08, 2013 32 of 75 **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.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 30, 2012 767-57A0131 Revision 1: May 08, 2013 33 of 75 **BOEING SERVICE BULLETIN 767-57A0131**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

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 30, 2012 767-57A0131 Revision 1: May 08, 2013 34 of 75 **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

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 30, 2012 767-57A0131 Revision 1: May 08, 2013 35 of 75 **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:

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 30, 2012 767-57A0131 Revision 1: May 08, 2013 36 of 75 **BOEING SERVICE BULLETIN 767-57A0131 Right Wing**  **Left Wing Support Rib #8**  **Support Rib #7 Support Rib #2**  **Support Rib #1** FIGURE 4 FIGURE 3 FIGURE 2 FIGURE 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 Wing Left Wing**  **Support Rib #8 Support Rib #7**  **Support Rib #2 Support Rib #1**  FIGURE 9 FIGURE 8 FIGURE 7 FIGURE 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.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 30, 2012 767-57A0131 Revision 1: May 08, 2013 37 of 75 **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: Right Wing**  **Left Wing Support Rib #8**  **Support Rib #7 Support Rib #2**  **Support Rib #1** FIGURE 10 FIGURE 11 FIGURE 11 FIGURE 10 **Group 3: Right Wing**  **Left Wing Support Rib #8**  **Support Rib #7 Support Rib #2**  **Support Rib #1** 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: **Right Wing Left Wing**  **Support Rib #8 Support Rib #7**  **Support Rib #2 Support Rib #1**  FIGURE 9 FIGURE 8 FIGURE 7 FIGURE 6

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 30, 2012 767-57A0131 Revision 1: May 08, 2013 38 of 75 **BOEING SERVICE BULLETIN 767-57A0131**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.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 30, 2012 767-57A0131 Revision 1: May 08, 2013 39 of 75 **BOEING SERVICE BULLETIN 767-57A0131 FIGURE 1: CAP SEAL DETAILED INSPECTION FOR SUPPORT RIB # 1**  **(SHEET 1 OF 2)** Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 30, 2012 767-57A0131 Revision 1 May 08, 2013 40 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 the number of parts necessary for this figure.
**More Data Qty**  **Identification Name**  **Task Step**  Do a Detailed Inspection of the sealant around the nut for damage. (a) 4
- Cap Seal Inspect 1

(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)**  Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 30, 2012 767-57A0131 Revision 1 May 08, 2013 41 of 75 **BOEING SERVICE BULLETIN 767-57A0131 FIGURE 2: CAP SEAL DETAILED INSPECTION FOR SUPPORT RIB # 2**  **(SHEET 1 OF 2)** Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 30, 2012 767-57A0131 Revision 1 May 08, 2013 42 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 the number of parts necessary for this figure.
**More Data Qty**  **Identification Name**  **Task Step**  Do a Detailed Inspection of the sealant around the nut for damage. (a) 4
- Cap Seal Inspect 1

(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)**  Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 30, 2012 767-57A0131 Revision 1 May 08, 2013 43 of 75 **BOEING SERVICE BULLETIN 767-57A0131 FIGURE 3: CAP SEAL DETAILED INSPECTION FOR SUPPORT RIB # 7**  **(SHEET 1 OF 2)** Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 30, 2012 767-57A0131 Revision 1 May 08, 2013 44 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 the number of parts necessary for this figure.
**More Data Qty**  **Identification Name**  **Task Step**  Do a Detailed Inspection of the sealant around the nut for damage. (a) 4
- Cap Seal Inspect 1

(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)**  Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 30, 2012 767-57A0131 Revision 1 May 08, 2013 45 of 75 **BOEING SERVICE BULLETIN 767-57A0131 FIGURE 4: CAP SEAL DETAILED INSPECTION FOR SUPPORT RIB # 8**  **(SHEET 1 OF 2)** Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 30, 2012 767-57A0131 Revision 1 May 08, 2013 46 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 the number of parts necessary for this figure.
**More Data Qty**  **Identification Name**  **Task Step**  Do a Detailed Inspection of the sealant around the nut for damage. (a) 4
- Cap Seal Inspect 1

(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)**  Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 30, 2012 767-57A0131 Revision 1 May 08, 2013 47 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.
**More Data Qty**  **Identification Name**  **Task Step**  only from fastener locations where damaged sealant was found. 1
- Cap Seal Remove 1

Do a Detailed Inspection for corrosion and cracks on thenut, bolt and washers. 1
- Fastener Inspect 2

**FIGURE 5: FASTENER DETAILED INSPECTION (SHEET 1 OF 1)**  Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 30, 2012 767-57A0131 Revision 1 May 08, 2013 48 of 75 **BOEING SERVICE BULLETIN 767-57A0131 FIGURE 6: FASTENER REPLACEMENTS FOR SUPPORT RIB # 1**  **(SHEET 1 OF 4)** Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 30, 2012 767-57A0131 Revision 1 May 08, 2013 49 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.
**More Data Qty**  **Identification Name**  **Task Step**  4
- Fastener Remove 1

**FIGURE 6: FASTENER REPLACEMENTS FOR SUPPORT RIB # 1 (SHEET 2 OF 4)**  Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 30, 2012 767-57A0131 Revision 1 May 08, 2013 50 of 75 **BOEING SERVICE BULLETIN 767-57A0131 More Data**  **Qty Identification**  **Name Task**  **Step** Do a High Frequency Eddy Current Inspection of the fastener hole for cracksand 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) 4
- Fastener Hole Inspect 2

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 Hole Ream 3

Do a High Frequency Eddy Current Inspection of the fastener hole to make sure all cracks and corrosion has beenremoved in accordance with 767 NDTManual Part 6, Subject 51-00-04, 767 NDT Part 6, Subject 51-00-11 or 767 NDT Part 6, Subject 51-00-16. (b) 4
- Fastener Hole Inspect

**FIGURE 6: FASTENER REPLACEMENTS FOR SUPPORT RIB # 1 (SHEET 3 OF 4)**  Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 30, 2012 767-57A0131 Revision 1 May 08, 2013 51 of 75 **BOEING SERVICE BULLETIN 767-57A0131 More Data**  **Qty Identification**  **Name Task**  **Step** wet with BMS 5-95 sealant. Refer toAPPENDIX A for applicable bolt part numbers. 4
- Bolt Install (New) 4

Refer to APPENDIXA for washer quantities and applicable part numbers. - - Washer Install (New)

Refer to APPENDIX A for applicable nut part numbers. 4
- Nut Install (New)

Cap seal nuts external to the wing fuel tank. Refer to SOPM20-50-19 as an accepted procedure. 4 BMS 5-95 Sealant Apply 5

Cap seal bolt heads internal to the wing fuel tank. Refer to SOPM 20-50-19 asan accepted procedure. 4 BMS 5-45 (BMS 5-26 optional) Sealant Apply

(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)**  Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 30, 2012 767-57A0131 Revision 1 May 08, 2013 52 of 75 **BOEING SERVICE BULLETIN 767-57A0131 FIGURE 7: FASTENER REPLACEMENTS FOR SUPPORT RIB # 2**  **(SHEET 1 OF 4)** Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 30, 2012 767-57A0131 Revision 1 May 08, 2013 53 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.
**More Data Qty**  **Identification Name**  **Task Step**  4
- Fastener Remove 1

**FIGURE 7: FASTENER REPLACEMENTS FOR SUPPORT RIB # 2 (SHEET 2 OF 4)**  Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 30, 2012 767-57A0131 Revision 1 May 08, 2013 54 of 75 **BOEING SERVICE BULLETIN 767-57A0131 More Data**  **Qty Identification**  **Name Task**  **Step** Do a High Frequency Eddy Current Inspection on the fastener hole for cracksand 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) 4
- Fastener Hole Inspect 2

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 Hole Ream 3

Do a High Frequency Eddy Current Inspection of the fastener hole to make sure all cracks and corrosion has beenremoved in accordance with 767 NDTManual Part 6, Subject 51-00-04, 767 NDT Part 6, Subject 51-00-11 or 767 NDT Part 6, Subject 51-00-16. (b) 4
- Fastener Hole Inspect

**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 767-57A0131 Revision 1 May 08, 2013 55 of 75 **BOEING SERVICE BULLETIN 767-57A0131 More Data**  **Qty Identification**  **Name Task**  **Step** wet with BMS 5-95 sealant. Refer toAPPENDIX A for applicable bolt part numbers. 4
- Bolt Install (New) 4

Refer to APPENDIXA for washer quantities and applicable part numbers. - - Washer Install (New)

Refer to APPENDIX A for applicable nut part numbers. 4
- Nut Install (New)

Cap seal nuts external to the wing fuel tank. Refer to SOPM20-50-19 as an accepted procedure. 4 BMS 5-95 Sealant Apply 5

Cap seal bolt heads internal to the wing fuel tank. Refer to SOPM 20-50-19 asan accepted procedure. 4 BMS 5-45 (BMS 5-26 optional) Sealant Apply

(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 767-57A0131 Revision 1 May 08, 2013 56 of 75 **BOEING SERVICE BULLETIN 767-57A0131 FIGURE 8: FASTENER REPLACEMENTS FOR SUPPORT RIB # 7**  **(SHEET 1 OF 4)** Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 30, 2012 767-57A0131 Revision 1 May 08, 2013 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.
**More Data Qty**  **Identification Name**  **Task Step**  4
- Fastener Remove 1

**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 767-57A0131 Revision 1 May 08, 2013 58 of 75 **BOEING SERVICE BULLETIN 767-57A0131 More Data**  **Qty Identification**  **Name Task**  **Step** Do a High Frequency Eddy Current Inspection on the fastener hole for cracksand 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) 4
- Fastener Hole Inspect 2

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 Hole Ream 3

Do a High Frequency Eddy Current Inspection of the fastener hole to make sure all cracks and corrosion has beenremoved in accordance with 767 NDTManual Part 6, Subject 51-00-04, 767 NDT Part 6, Subject 51-00-11 or 767 NDT Part 6, Subject 51-00-16. (b) 4
- Fastener Hole Inspect

**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 767-57A0131 Revision 1 May 08, 2013 59 of 75 **BOEING SERVICE BULLETIN 767-57A0131 More Data**  **Qty Identification**  **Name Task**  **Step** wet with BMS 5-95 sealant. Refer toAPPENDIX A for applicable bolt part numbers. 4
- Bolt Install (New) 4

Refer to APPENDIXA for washer quantities and applicable part numbers. - - Washer Install (New)

Refer to APPENDIX A for applicable nut part numbers. 4
- Nut Install (New)

Cap seal nuts external to the wing fuel tank. Refer to SOPM20-50-19 as an accepted procedure. 4 BMS 5-95 Sealant Apply 5

Cap seal bolt heads internal to the wing fuel tank. Refer to SOPM 20-50-19 asan accepted procedure. 4 BMS 5-45 (BMS 5-26 optional) Sealant Apply

(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 767-57A0131 Revision 1 May 08, 2013 60 of 75 **BOEING SERVICE BULLETIN 767-57A0131 FIGURE 9: FASTENER REPLACEMENTS FOR SUPPORT RIB # 8**  **(SHEET 1 OF 4)** Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 30, 2012 767-57A0131 Revision 1 May 08, 2013 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.
**More Data Qty**  **Identification Name**  **Task Step**  4
- Fastener Remove 1

**FIGURE 9: FASTENER REPLACEMENTS FOR SUPPORT RIB # 8 (SHEET 2 OF 4)**  Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 30, 2012 767-57A0131 Revision 1 May 08, 2013 62 of 75 **BOEING SERVICE BULLETIN 767-57A0131 More Data**  **Qty Identification**  **Name Task**  **Step** Do a High Frequency Eddy Current Inspection on the fastener hole for cracksand 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) 4
- Fastener Hole Inspect 2

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 Hole Ream 3

Do a High Frequency Eddy Current Inspection of the fastener hole to make sure all cracks and corrosion has beenremoved in accordance with 767 NDTManual Part 6, Subject 51-00-04, 767 NDT Part 6, Subject 51-00-11 or 767 NDT Part 6, Subject 51-00-16. (b) 4
- Fastener Hole Inspect

**FIGURE 9: FASTENER REPLACEMENTS FOR SUPPORT RIB # 8 (SHEET 3 OF 4)**  Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 30, 2012 767-57A0131 Revision 1 May 08, 2013 63 of 75 **BOEING SERVICE BULLETIN 767-57A0131 More Data**  **Qty Identification**  **Name Task**  **Step** wet with BMS 5-95 sealant. Refer toAPPENDIX A for applicable bolt part numbers. 4
- Bolt Install (New) 4

Refer to APPENDIXA for washer quantities and applicable part numbers. - - Washer Install (New)

Refer to APPENDIX A for applicable nut part numbers. 4
- Nut Install (New)

Cap seal nuts external to the wing fuel tank. Refer to SOPM20-50-19 as an accepted procedure. 4 BMS 5-95 Sealant Apply 5

Cap seal bolt heads internal to the wing fuel tank. Refer to SOPM 20-50-19 asan accepted procedure. 4 BMS 5-45 (BMS 5-26 optional) Sealant Apply

(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)**  Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 30, 2012 767-57A0131 Revision 1 May 08, 2013 64 of 75 **BOEING SERVICE BULLETIN 767-57A0131 This Figure applies only to: Group 2.** 

**FIGURE 10: NUT MEASUREMENT FOR CORRECT TYPE (SHEET 1 OF 2)**  Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 30, 2012 767-57A0131 Revision 1 May 08, 2013 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.
**More Data Qty**  **Identification Name**  **Task Step**  and compare to examples above to find if correct or incorrect nut is installed. 1
- Nut Measure 1

**FIGURE 10: NUT MEASUREMENT FOR CORRECT TYPE (SHEET 2 OF 2)**  Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 30, 2012 767-57A0131 Revision 1 May 08, 2013 66 of 75 **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 PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 30, 2012 767-57A0131 Revision 1 May 08, 2013 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.
**More Data Qty**  **Identification Name**  **Task Step**  and compare to examples above to find if correct or incorrect nut is installed. 1
- Nut Measure 1

**FIGURE 11: NUT MEASUREMENT FOR CORRECT TYPE (SHEET 2 OF 2)**  Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 30, 2012 767-57A0131 Revision 1 May 08, 2013 68 of 75 **BOEING SERVICE BULLETIN 767-57A0131 GROUP 1-2: Support Rib # 1 and # 8**  **More Data Hole Dia (a)**  **Name QTY**  **Identification CODE**  0.6245 - 0.6255 BOLT, 12 POINT HEAD 1 BACB30US10K47 A Optional. 0.6401 - 0.6411 BOLT, 12 POINT HEAD 1 BACB30US10K47X Optional. 0.6557 - 0.6567 BOLT, 12 POINT HEAD 1 BACB30US10K47Y
0.6245 - 0.6255 BOLT, 12 POINT HEAD 2 BACB30US10K48 B Optional. 0.6401 - 0.6411 BOLT, 12 POINT HEAD 2 BACB30US10K48X Optional. 0.6557 - 0.6567 BOLT, 12 POINT HEAD 1 BACB30US10K48Y
0.6245 - 0.6255 BOLT, 12 POINT HEAD 1 BACB30US10K50 C Optional. 0.6401 - 0.6411 BOLT, 12 POINT HEAD 1 BACB30US10K50X Optional. 0.6557 - 0.6567 BOLT, 12 POINT HEAD 1 BACB30US10K50Y
MATING WASHERS AND NUTS Use with BACB30US10K* bolt. Install under head of bolt. - WASHER, SELF-ALIGN- ING 4 BACW10CA10CVS

**APPENDIX A: PART NUMBERS AND QUANTITIES BY SUPPORT RIB NUMBER (SHEET 1 OF 6)**  Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 30, 2012 767-57A0131 Revision 1 May 08, 2013 69 of 75 **BOEING SERVICE BULLETIN 767-57A0131 GROUP 1-2: Support Rib # 1 and # 8**  **More Data Hole Dia (a)**  **Name QTY**  **Identification CODE**  Use with BACB30US10K*X bolt. Install under head of bolt. - WASHER, SELF-ALIGN- ING 4 BACW10CA101CVS

Use with BACB30US10K*Y bolt. Install under head of bolt. - WASHER, SELF-ALIGN- ING 3 BACW10CA102CVS

Use with any BACB30US10K bolt. Install under head of bolt. - WASHER, SELF-ALIGN- ING 4 BACW10CA10CCS

Use with BACB30US10K* bolt. Install under nut. - WASHER, PLAIN AND COUNTERSUNK 4 BACW10BP10DP
Use with BACB30US10K*X bolt. Install under nut. - WASHER, PLAIN AND COUNTERSUNK 4 BACW10BP101DP
Use with BACB30US10K*Y bolt. Install under nut. - WASHER, PLAIN AND COUNTERSUNK 3 BACW10BP102DP Use with any BACB30US10K bolt.Torque to 1900 - 2300 inlbs. - NUT, SELF-LOCKING 4 BACN10HR10CD

(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 More Data**  **Hole Dia (a) Name**  **QTY Identification**  **CODE** 0.7495 - 0.7505 BOLT, 12 POINT HEAD 1 BACB30US12K49 A Optional. 0.7651 - 0.7661 BOLT, 12 POINT HEAD 1 BACB30US12K49X Optional. 0.7807 - 0.7817 BOLT, 12 POINT HEAD 1 BACB30US12K49Y
0.7495 - 0.7505 BOLT, 12 POINT HEAD 1 BACB30US12K50 B Optional. 0.7651 - 0.7661 BOLT, 12 POINT HEAD 1 BACB30US12K50X Optional. 0.7807 - 0.7817 BOLT, 12 POINT HEAD 1 BACB30US12K50Y

**APPENDIX A: PART NUMBERS AND QUANTITIES BY SUPPORT RIB NUMBER (SHEET 2 OF 6)**  Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 30, 2012 767-57A0131 Revision 1 May 08, 2013 70 of 75 **BOEING SERVICE BULLETIN 767-57A0131 GROUP 1-2: Support Rib # 2 and # 7**  **More Data Hole Dia (a)**  **Name QTY**  **Identification CODE**  0.7495 - 0.7505 BOLT, 12 POINT HEAD 2 BACB30US12K51 C Optional. 0.7651 - 0.7661 BOLT, 12 POINT HEAD 2 BACB30US12K51X Optional. 0.7807 - 0.7817 BOLT, 12 POINT HEAD 1 BACB30US12K51Y
MATING WASHERS AND NUTS Use with BACB30US12K* bolt. Install under head of bolt. - WASHER, SELF-ALIGN- ING 4 BACW10CA12CVS

Use with BACB30US12K*X bolt. Install under head of bolt. - WASHER, SELF-ALIGN- ING 4 BACW10CA121CVS

Use with BACB30US12K*Y bolt. Install under head of bolt. - WASHER, SELF-ALIGN- ING 3 BACW10CA122CVS

Use with any BACB30US12K bolt. Install under head of bolt. - WASHER, SELF-ALIGN- ING 4 BACW10CA12CCS

Use with BACB30US12K* bolt. Install under nut. - WASHER, PLAIN AND COUNTERSUNK 4 BACW10BP12DP
Use with BACB30US12K*X bolt. Install under nut. - WASHER, PLAIN AND COUNTERSUNK 4 BACW10BP121DP
Use with BACB30US12K*Y bolt. Install under nut. - WASHER, PLAIN AND COUNTERSUNK 3 BACW10BP122DP Use with any BACB30US12K bolt.Torque to 3300 - 4300 inlbs. - NUT, SELF-LOCKING 4 BACN10HR12CD

(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)**  Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 30, 2012 767-57A0131 Revision 1 May 08, 2013 71 of 75 **BOEING SERVICE BULLETIN 767-57A0131 GROUP 3: Support Rib # 1 and # 8**  **More Data Hole Dia (a)**  **Name QTY**  **Identification CODE**  0.7495 - 0.7505 BOLT, 12 POINT HEAD 1 BACB30US12K46 A Optional. 0.7651 - 0.7661 BOLT, 12 POINT HEAD 1 BACB30US12K46X Optional. 0.7807 - 0.7817 BOLT, 12 POINT HEAD 1 BACB30US12K46Y
0.7495 - 0.7505 BOLT, 12 POINT HEAD 2 BACB30US12K47 B Optional. 0.7651 - 0.7661 BOLT, 12 POINT HEAD 2 BACB30US12K47X Optional. 0.7807 - 0.7817 BOLT, 12 POINT HEAD 1 BACB30US12K47Y
0.7495 - 0.7505 BOLT, 12 POINT HEAD 1 BACB30US12K48 C Optional. 0.7651 - 0.7661 BOLT, 12 POINT HEAD 1 BACB30US12K48X Optional. 0.7807 - 0.7817 BOLT, 12 POINT HEAD 1 BACB30US12K48Y
MATING WASHERS AND NUTS Use with BACB30US12K* bolt. Install under head of bolt. - WASHER, SELF-ALIGN- ING 4 BACW10CA12CVS

Use with BACB30US12K*X bolt. Install under head of bolt. - WASHER, SELF-ALIGN- ING 4 BACW10CA121CVS

Use with BACB30US12K*Y bolt. Install under head of bolt. - WASHER, SELF-ALIGN- ING 3 BACW10CA122CVS

Use with any BACB30US12K bolt. Install under head of bolt. - WASHER, SELF-ALIGN- ING 4 BACW10CA12CCS

Use with BACB30US12K* bolt. Install under nut. - WASHER, PLAIN AND COUNTERSUNK 4 BACW10BP12DP
Use with BACB30US12K*X bolt. Install under nut. - WASHER, PLAIN AND COUNTERSUNK 4 BACW10BP121DP
Use with BACB30US12K*Y bolt. Install under nut. - WASHER, PLAIN AND COUNTERSUNK 3 BACW10BP122DP

**APPENDIX A: PART NUMBERS AND QUANTITIES BY SUPPORT RIB NUMBER (SHEET 4 OF 6)**  Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 30, 2012 767-57A0131 Revision 1 May 08, 2013 72 of 75 **BOEING SERVICE BULLETIN 767-57A0131 GROUP 3: Support Rib # 1 and # 8**  **More Data Hole Dia (a)**  **Name QTY**  **Identification CODE**  Use with any BACB30US12K bolt.Torque to 3300 - 4300 inlbs. - NUT, SELF-LOCKING 4 BACN10HR12CD

(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 More Data**  **Hole Dia (a) Name**  **QTY Identification**  **CODE** 0.7495 - 0.7505 BOLT, 12 POINT HEAD 1 BACB30US12K49 A Optional. 0.7651 - 0.7661 BOLT, 12 POINT HEAD 1 BACB30US12K49X Optional. 0.7807 - 0.7817 BOLT, 12 POINT HEAD 1 BACB30US12K49Y
0.7495 - 0.7505 BOLT, 12 POINT HEAD 1 BACB30US12K50 B Optional. 0.7651 - 0.7661 BOLT, 12 POINT HEAD 1 BACB30US12K50X Optional. 0.7807 - 0.7817 BOLT, 12 POINT HEAD 1 BACB30US12K50Y
0.7495 - 0.7505 BOLT, 12 POINT HEAD 2 BACB30US12K51 C Optional. 0.7651 - 0.7661 BOLT, 12 POINT HEAD 2 BACB30US12K51X Optional. 0.7807 - 0.7817 BOLT, 12 POINT HEAD 1 BACB30US12K51Y
MATING WASHERS AND NUTS Use with BACB30US12K* bolt. Install under head of bolt. - WASHER, SELF-ALIGN- ING 4 BACW10CA12CVS

Use with BACB30US12K*X bolt. Install under head of bolt. - WASHER, SELF-ALIGN- ING 4 BACW10CA121CVS

Use with BACB30US12K*Y bolt. Install under head of bolt. - WASHER, SELF-ALIGN- ING 3 BACW10CA122CVS

**APPENDIX A: PART NUMBERS AND QUANTITIES BY SUPPORT RIB NUMBER (SHEET 5 OF 6)**  Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 30, 2012 767-57A0131 Revision 1 May 08, 2013 73 of 75 **BOEING SERVICE BULLETIN 767-57A0131 GROUP 3: Support Rib # 2 and # 7**  **More Data Hole Dia (a)**  **Name QTY**  **Identification CODE**  Use with any BACB30US12K bolt. Install under head of bolt. - WASHER, SELF-ALIGN- ING 4 BACW10CA12CCS

Use with BACB30US12K* bolt. Install under nut. - WASHER, PLAIN AND COUNTERSUNK 4 BACW10BP12DP
Use with BACB30US12K*X bolt. Install under nut. - WASHER, PLAIN AND COUNTERSUNK 4 BACW10BP121DP
Use with BACB30US12K*Y bolt. Install under nut. - WASHER, PLAIN AND COUNTERSUNK 3 BACW10BP122DP Use with any BACB30US12K bolt.Torque to 3300 - 4300 inlbs. - NUT, SELF-LOCKING 4 BACN10HR12CD

(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)**  Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 30, 2012 767-57A0131 Revision 1 May 08, 2013 74 of 75 **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 Nominal Hole Diameter**  **Identification Name**  0.650 - 0.660 113T1345 Outboard Trailing Edge Flap Support Rib 0.650 - 0.660 112T5121 Actuator Backup Fitting **GROUP 1-2: Support Rib # 2 and # 7 Nominal Hole Diameter**  **Identification Name**  0.780 - 0.790 113T1345 Outboard Trailing Edge Flap Support Rib 0.780 - 0.790 112T5122 Actuator Backup Fitting **GROUP 3: Support Rib # 1 and # 8 Nominal Hole Diameter**  **Identification Name**  0.780 - 0.790 113T1345 Outboard Trailing Edge Flap Support Rib 0.780 - 0.790 112T5121 Actuator Backup Fitting **GROUP 3: Support Rib # 2 and # 7 Nominal Hole Diameter**  **Identification Name**  0.780 - 0.790 113T1345 Outboard Trailing Edge Flap Support Rib 0.780 - 0.790 112T5122 Actuator Backup Fitting

**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 767-57A0131 Revision 1 May 08, 2013 75 of 75 **BOEING SERVICE BULLETIN 767-57A0131**