### Commercial Airplanes 

# 767 Service Bulletin ALERT Number: 767-53A0267 Original Issue: August 13, 2015 Revision 1: August 04, 2016 ATA System: 5380 SUBJECT:FUSELAGE - Aft Pressure Bulkhead - Replacement of Station 1582 Aft Pressure Bulkhead 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 © 2015 Boeing. Unpublished Work. All Rights Reserved. Treatment of this document and its content is governed by contract with Boeing. Rights to use this document are licensed on a per aircraft basis and such rights may not be transferable. For more information, contact The Boeing Company. Boeing, the Boeing signature, the Boeing symbol, 707, 717, 727, 737, 747, 757, 767, 777, 787, Dreamliner, BBJ, DC-8, DC-9, DC-10, KC-10, KC-46, KDC-10, MD-10, MD-11, MD-80, MD-88, MD-90, P-8, Poseidon and Boeing liveries are all trademarks owned by The Boeing Company; and no trademark license is granted in connection with this document unless provided in writing by Boeing.

Original Issue: August 13, 2015 767-53A0267 Revision 1: August 04, 2016 1 of 206 2.0Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 13, 2015 767-53A0267 Revision 1: August 04, 2016 2 of 206 BOEING SERVICE BULLETIN 767-53A0267 ALERT ALERT

BLANK PAGETable of Contents Revision Transmittal Sheet............................................ 5 Summary . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7 1. PLANNING INFORMATION. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11 A. Effectivity . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11 1. Airplanes. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11 2. Spares Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13 B. Concurrent Requirements. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13 C. Reason. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14 D. Description. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14 E. Compliance. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15 F. Approval . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15 G. Manpower. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 16 H. Weight and Balance Changes. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 18 I. Electrical Load Data. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 18 J. References . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 18 1. Existing Data:. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 18 2. Data Supplied with this Service Bulletin:. . . . . . . . . . . . . . . . . . . . . . . . . . . 18 3. Installation Drawings Used in the Preparation of this Service Bulletin:. . . . . . . . . . . 21 K. Publications Affected. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 22 L. Interchangeability and Intermixability of Parts. . . . . . . . . . . . . . . . . . . . . . . . . . . 22 M. Software Accomplishment Summary. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 22 2. MATERIAL INFORMATION. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 23 A. Material - Price and Availability. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 23 B. Industry Support Information. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 23 C. Parts Necessary for Each Airplane. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 23 1. Kits/Parts . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 23 2. Parts and Materials Supplied by the Operator. . . . . . . . . . . . . . . . . . . . . . . . 34 3. Parts Modified and Reidentified. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 35 4. Parts Removed and Not Replaced. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 35 D. Parts Necessary to Change Spares. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 35 E. Special Tooling - Price and Availability. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 35 F. Special Tooling Necessary to do this Service Bulletin. . . . . . . . . . . . . . . . . . . . . . . 38 3. ACCOMPLISHMENT INSTRUCTIONS. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 39 A. GENERAL INFORMATION. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 39 B. WORK INSTRUCTIONS. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 40 FIGURE 1: AFT PRESSURE BULKHEAD ASSEMBLY PREPARATION. . . . . . . . . . . . . . . . 55 FIGURE 2: AFT PRESSURE BULKHEAD ASSEMBLY PREPARATION. . . . . . . . . . . . . . . . 60 FIGURE 3: REMOVAL OF AUXILIARY PITOT SYSTEM TUBES AND SEALS. . . . . . . . . . . . . 62 FIGURE 4: REMOVAL OF PRESSURE SEALS. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 66 FIGURE 5: APU FUEL LINE BULKHEAD FITTING REMOVAL. . . . . . . . . . . . . . . . . . . . . 69 FIGURE 6: APU FUEL LINE BULKHEAD FITTING INSTALLATION. . . . . . . . . . . . . . . . . . . 72 FIGURE 7: AFT SECTION 48 (TAIL CONE) FASTENER REMOVAL. . . . . . . . . . . . . . . . . . 75 FIGURE 8: STA 1809.5 CENTER BULKHEAD REMOVAL. . . . . . . . . . . . . . . . . . . . . . . . 78 FIGURE 9: FORWARD SECTION 48 PARTS REMOVAL. . . . . . . . . . . . . . . . . . . . . . . . 85 FIGURE 10: AFT PRESSURE BULKHEAD PRESSURE RING FASTENER REMOVAL . . . . . . . . . 87
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 13, 2015 767-53A0267 Revision 1: August 04, 2016 3 of 206 BOEING SERVICE BULLETIN 767-53A0267 ALERT ALERTFIGURE 11: AFT PRESSURE BULKHEAD ATTACHMENT TO THE PRESSURE RING AT STA 1582 . 89 FIGURE 12: FORWARD SECTION 48 INSTALLATION. . . . . . . . . . . . . . . . . . . . . . . . . . 91 FIGURE 13: LEFT STA 1809.5 CENTER BULKHEAD INSTALLATION. . . . . . . . . . . . . . . . . 110 FIGURE 14: RIGHT STA 1809.5 CENTER BULKHEAD INSTALLATION. . . . . . . . . . . . . . . . 122 FIGURE 15: AFT SECTION 48 (TAIL CONE) INSTALLATION. . . . . . . . . . . . . . . . . . . . . . 134 FIGURE 16: PRESSURE SEAL INSTALLATION. . . . . . . . . . . . . . . . . . . . . . . . . . . . . 139 FIGURE 17: INSTALLATION OF AUXILIARY PITOT SYSTEM TUBES AND PRESSURE SEALS . . 142 FIGURE 18: MAKE AND INSTALL STA 1809.5 BULKHEAD STABILIZATION TOOLS. . . . . . . . . 146 FIGURE 19: REMOVE STA 1809.5 BULKHEAD STABILIZATION TOOLS. . . . . . . . . . . . . . . 156 FIGURE 20: STA 1582 FLOOR BEAM DETACHMENT. . . . . . . . . . . . . . . . . . . . . . . . . . 158 FIGURE 21: STA 1582 FLOOR BEAM SUPPORT. . . . . . . . . . . . . . . . . . . . . . . . . . . . 162 FIGURE 22: STA 1582 FLOOR BEAM ATTACHMENT. . . . . . . . . . . . . . . . . . . . . . . . . . 165 FIGURE 23: LEFT SIDE HORIZONTAL STABILIZER FAIRING SKIN REMOVAL. . . . . . . . . . . 170 FIGURE 24: LEFT SIDE HORIZONTAL STABILIZER FAIRING SKIN INSTALLATION. . . . . . . . . 173 FIGURE 25: RIGHT SIDE HORIZONTAL STABILIZER FAIRING SKIN REMOVAL. . . . . . . . . . . 177 FIGURE 26: RIGHT SIDE HORIZONTAL STABILIZER FAIRING SKIN INSTALLATION. . . . . . . . 180 FIGURE 27: PREPARATION OF THE VERTICAL FIN. . . . . . . . . . . . . . . . . . . . . . . . . . 183 FIGURE 28: INSTALLATION OF THE VERTICAL FIN. . . . . . . . . . . . . . . . . . . . . . . . . . 190 APPENDIX A: APU WIRING TEST PROCEDURE. . . . . . . . . . . . . . . . . . . . . . . . . . . . . 199 APPENDIX B: ALIGNMENT PINS. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 204 APPENDIX C: LOGIC DIAGRAM FOR PARAGRAPH 1.E. COMPLIANCE: TABLE 1: REPLACEMENT OF THE STA 1582 AFT PRESSURE BULKHEAD. . . . . . . . . . . . . . . . . . . . . . . . . . 205 APPENDIX D: PART DEMAND INTENT. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 206

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 13, 2015 767-53A0267 Revision 1: August 04, 2016 4 of 206 BOEING SERVICE BULLETIN 767-53A0267 ALERT ALERT

### Commercial Airplanes 

# 767 Service Bulletin ALERT Revision Transmittal Sheet Number: 767-53A0267 Original Issue: August 13, 2015 Revision 1: August 04, 2016 ATA System: 5380 SUBJECT:FUSELAGE - Aft Pressure Bulkhead - Replacement of Station 1582 Aft Pressure Bulkhead This revision includes all pages of the service bulletin. COMPLIANCE INFORMATION RELATED TO THIS REVISION None. REASON FOR REVISION Revision 1 is sent to replace kit number 015T1812-2 with 015T1907-1, and add five airplanes to the effectivity that were inadvertently omitted at initial release. These sections were changed: 1. 1.A. Effectivity, added airplane Variable Numbers VN018, VN092, VN191, VN371, and VN537. 2. 1.K.1 Publications Affected - Publications, included additional publications that are affected by this service bulletin. 3. 2.A. Material - Price and Availability, updated kit number and Re-Order Lead Time (ROLT) information. 4. 2.C.1 Kits/Parts, replaced kit 015T1812-2 with kit number 015T1907-1. Vertical lines are put on the left edge of each page, except in Paragraph 1.A., Effectivity and format changes, to show the location of all content changes. Pages with no vertical lines have no changes. REVISION HISTORY August 13, 2015 Original Issue: August 04, 2016 Revision 1:

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 13, 2015 767-53A0267 Revision 1: August 04, 2016 5 of 206Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 13, 2015 767-53A0267 Revision 1: August 04, 2016 6 of 206 BOEING SERVICE BULLETIN 767-53A0267 ALERT ALERT

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### Commercial Airplanes 

# 767 Service Bulletin ALERT Summary Number: 767-53A0267 Original Issue: August 13, 2015 Revision 1: August 04, 2016 ATA System: 5380 SUBJECT:FUSELAGE - Aft Pressure Bulkhead - Replacement of Station 1582 Aft Pressure Bulkhead THIS BULLETIN IS SENT TO THE OPERATORS OF RECORD OF THE AIRPLANES SHOWN IN PARAGRAPH 1.A., EFFECTIVITY. IF AN AIRPLANE HAS BEEN LEASED OR SOLD, SEND THIS SERVICE BULLETIN TO THE NEW OPERATOR. IF APPLICABLE SPARES HAVE BEEN SOLD, SEND THIS SERVICE BULLETIN TO THE NEW OWNER. CONCURRENT REQUIREMENTS None. BACKGROUND This service bulletin gives instruction for the replacement of the Station (STA) 1582 aft pressure bulkhead due to Widespread Fatigue Damage (WFD). The WFD analysis of the 767, as required by 14 CFR 26.21(b), has resulted in the conclusion that the existing MPD Section 9, Airworthiness Limitation Item (ALI) inspection program is not sufficient to preclude the occurrence of WFD in the aft pressure bulkhead before the Limit of Validity (LOV) as the airplane ages. If widespread fatigue cracking at aft pressure bulkhead radial web lap splices is not found and repaired, the cracks can rapidly link up and become large, and can result in possible rapid decompression and loss of structural integrity. Boeing has not received any reports of cracks in the aft pressure bulkhead web on line number 176 through 423. The Aft Pressure Bulkhead has been determined to be structure that is susceptible to Widespread Fatigue Damage (WFD). Federal Aviation Administration (FAA) AD 2012-09-08 was released to mandate replacement of the initial configuration aft pressure bulkhead which was installed on line number 1 through 175 per service bulletin 767-53A0139. Design changes were made to improve the durability of the bulkhead in production at line number 176, and again at line number 424. However, the configuration of aft pressure bulkheads installed on line number 176 through 423, have the same web gage of 0.032 inch as the initial configuration aft pressure bulkhead and does not provide adequate strength to preclude WFD before the Limit of Validity (LOV). Boeing Service Related Problem (SRP) 767-SRP-53-0469 is related to this service bulletin. Accomplishment of the aft pressure bulkhead replacement given in this service bulletin will end the inspections at aft pressure bulkhead web for indications of "oil cans" and previous "oil can" repairs currently required by Boeing Service Bulletin 767-53A0105 and AD 2004-14-19.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 13, 2015 767-53A0267 Revision 1: August 04, 2016 7 of 206Accomplishment of the aft pressure bulkhead replacement given in this service bulletin will end the repeat inspections at aft pressure bulkhead web lap splices currently required by Boeing Service Bulletin 767-53A0147 and AD 2009-06-19. Accomplishment of the aft pressure bulkhead replacement given in this service bulletin will also end the repeat inspections of web at pressure chord joint currently required by Boeing Service Bulletin 767-53A0087 and AD 2004-05-16. 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 Paragraph 1.E., Compliance and Paragraph 1.F., Approval Yes AD Related Paragraph 1.H., Weight and Balance Changes Yes Weight and Balance Change Paragraph 1.I., Electrical Load Data No Electrical Load Changed Paragraph 1.K., Publications Affected Yes 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 Parts/Material Paragraph 2.F., Special Tooling Necessary to do this Service Bulletin Yes Special Tooling Required ACTION Remove equipment for access to the forward and aft sides of the STA 1582 aft pressure bulkhead. Remove the vertical fin, the tail cone (with the APU installed), the left and right STA 1809.5 center bulkhead, and the horizontal stabilizer. Disconnect and remove the forward portion of Section 48 (with the aft pressure bulkhead attached) from Section 46 at STA 1582. Remove the aft pressure bulkhead from Section 48 and install a new aft pressure bulkhead in accordance with this service bulletin. Attach the modified forward part of Section 48 to Section 46 at STA 1582. Reinstall the horizontal stabilizer and reassemble the STA 1809.5 bulkhead. Reinstall the tail cone and the vertical fin. Install the equipment that was removed for access to the aft pressure bulkhead. Test disturbed systems in accordance with this service bulletin. EFFECTIVITY 767-200 and 767-300 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.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 13, 2015 767-53A0267 Revision 1: August 04, 2016 8 of 206 BOEING SERVICE BULLETIN 767-53A0267 ALERT ALERTFederal Aviation Administration (FAA) Airworthiness Directive AD 2004-14-19 is related to this service bulletin. The effective date of AD 2004-14-19 is August 20, 2004. Federal Aviation Administration (FAA) Airworthiness Directive AD 2009-06-19 is related to this service bulletin. The effective date of AD 2009-06-19 is April 28, 2009. Federal Aviation Administration (FAA) Airworthiness Directive AD 2004-05-16 is related to this service bulletin. The effective date of AD 2004-05-16 is April 13, 2004. Refer to Paragraph 1.E., Compliance. INDUSTRY SUPPORT INFORMATION Boeing warranty remedies are not available for the configuration changes given in this service bulletin. MANPOWER Refer to Paragraph 1.G., Manpower. MATERIAL INFORMATION Boeing Supplied Kits/Parts. Refer to Paragraph 2.A., Material - Price and Availability. Operators are encouraged to complete the survey provided in APPENDIX D of this service bulletin to help Boeing predict the quantity and timing of the Boeing Supplied Kits/Parts.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 13, 2015 767-53A0267 Revision 1: August 04, 2016 9 of 206 BOEING SERVICE BULLETIN 767-53A0267 ALERT ALERTExport Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 13, 2015 767-53A0267 Revision 1: August 04, 2016 10 of 206 BOEING SERVICE BULLETIN 767-53A0267 ALERT ALERT

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### Commercial Airplanes 

# 767 Service Bulletin ALERT Number: 767-53A0267 Original Issue: August 13, 2015 Revision 1: August 04, 2016 ATA System: 5380 SUBJECT:FUSELAGE - Aft Pressure Bulkhead - Replacement of Station 1582 Aft Pressure Bulkhead THIS BULLETIN IS SENT TO THE OPERATORS OF RECORD OF THE AIRPLANES SHOWN IN PARAGRAPH 1.A., EFFECTIVITY. IF AN AIRPLANE HAS BEEN LEASED OR SOLD, SEND THIS SERVICE BULLETIN TO THE NEW OPERATOR. IF APPLICABLE SPARES HAVE BEEN SOLD, SEND THIS SERVICE BULLETIN TO THE NEW OWNER. 1. PLANNING INFORMATION A. Effectivity 1. Airplanes Refer to Service Bulletin Index D624T001 Part 3 for Airplane Variable Number, Line Number, and Serial Number data. This service bulletin is applicable to 767-200 and -300 Airplanes, line numbers 176 - 423 in 3 Groups. The Variable Numbers and Group Information for the applicable airplanes are given below. DESCRIPTION CONFIGURATION GROUP Airplane Line numbers 176-401 with Non-Dual bottle fire extinguisher - 1 Airplane Line numbers 186-416 with APC Dual Bottle fire extinguisher - 2 Airplane Line numbers 202-423 which have dedicated Static pressure inputs - 3
Airplane Models: 767-200, 767-300 Group Variable Number1 VA527 - VA5301 VA713 - VA719

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 13, 2015 767-53A0267 Revision 1: August 04, 2016 11 of 206Group Variable Number1 VB325 2 VB326 1 VB327 - VB3321 VE003 1 VE069 1 VE085 - VE0861 VE104 1 VE118 1 VE124 - VE1261 VE143 - VE151 1 VE171 - VE1723 VF001 - VF002 3 VF041 - VF042 3 VF051 3 VF061 - VF062 3 VF071 - VF072 3 VF091 - VF093 3 VF101 - VF102 2 VF161 2 VK005 - VK011 2 VK021 - VK0222 VK038 - VK0531 VK081 - VK0991 VK131 - VK1331 VK141 - VK1422 VL002 - VL006 3 VN001 - VN0193 VN051 - VN0623 VN081 - VN0923 VN111 - VN1243 VN130 - VN1323 VN151 - VN1583 VN163 - VN168

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 13, 2015 767-53A0267 Revision 1: August 04, 2016 12 of 206 BOEING SERVICE BULLETIN 767-53A0267 ALERT ALERTGroup Variable Number3 VN171 - VN1733 VN191 - VN1932 VN211 - VN2122 VN221 - VN2243 VN231 - VN2342 VN241 2 VN251 - VN2593 VN291 2 VN301 - VN3063 VN371 - VN3723 VN376 3 VN381 3 VN471 - VN4723 VN491 - VN4963 VN531 - VN5323 VN536 - VN5373 VN541 - VN5423 VN551 3 VN631 - VN6333 VN651 - VN6522 VN671 - VN6723 VN681 - VN6832 VN731 3 VN751 - VN753 2. Spares Affected None. B. Concurrent Requirements None.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 13, 2015 767-53A0267 Revision 1: August 04, 2016 13 of 206 BOEING SERVICE BULLETIN 767-53A0267 ALERT ALERTC. Reason This service bulletin gives instruction for the replacement of the Station (STA) 1582 aft pressure bulkhead due to Widespread Fatigue Damage (WFD). The WFD analysis of the 767, as required by 14 CFR 26.21(b), has resulted in the conclusion that the existing MPD Section 9, Airworthiness Limitation Item (ALI) inspection program is not sufficient to preclude the occurrence of WFD in the aft pressure bulkhead before the Limit of Validity (LOV) as the airplane ages. If widespread fatigue cracking at aft pressure bulkhead radial web lap splices is not found and repaired, the cracks can rapidly link up and become large, and can result in possible rapid decompression and loss of structural integrity. Boeing has not received any reports of cracks in the aft pressure bulkhead web on line number 176 through 423. The Aft Pressure Bulkhead has been determined to be structure that is susceptible to Widespread Fatigue Damage (WFD). Federal Aviation Administration (FAA) AD 2012-09-08 was released to mandate replacement of the initial configuration aft pressure bulkhead which was installed on line number 1 through 175. Design changes were made to improve the durability of the bulkhead in production at line number 176, and again at line number 424. However, the configuration of aft pressure bulkheads installed on line number 176 through 423, have the same web gage of 0.032 inch as the initial configuration aft pressure bulkhead and does not provide adequate strength to preclude WFD before the Limit of Validity (LOV). Boeing Service Related Problem (SRP) 767-SRP-53-0469 is related to this service bulletin. Accomplishment of the aft pressure bulkhead replacement given in this service bulletin will end the inspections at aft pressure bulkhead web for indications of "oil cans" and previous "oil can" repairs currently required by Boeing Service Bulletin 767-53A0105 and AD 2004-14-19. Accomplishment of the aft pressure bulkhead replacement given in this service bulletin will end the repeat inspections at aft pressure bulkhead web lap splices currently required by Boeing Service Bulletin 767-53A0147 and AD 2009-06-19. Accomplishment of the aft pressure bulkhead replacement given in this service bulletin will also end the repeat inspections of web at pressure chord joint currently required by Boeing Service Bulletin 767-53A0087 and AD 2004-05-16. D. Description Remove equipment for access to the forward and aft sides of the STA 1582 aft pressure bulkhead. Remove the vertical fin, the tail cone (with the APU installed), the left and right STA 1809.5 center bulkhead, and the horizontal stabilizer. Disconnect and remove the forward portion of Section 48 (with the aft pressure bulkhead attached) from Section 46 at STA 1582. Remove the aft pressure bulkhead from Section 48 and install a new aft pressure bulkhead in accordance with this service bulletin. Attach the modified forward part of Section 48 to Section 46 at STA 1582. Reinstall the horizontal stabilizer and reassemble the STA 1809.5 bulkhead. Reinstall the tail cone and the vertical fin. Install the equipment that was removed for access to the aft pressure bulkhead. Test disturbed systems in accordance with this service bulletin. The work in this service bulletin is done in the maintenance zone(s) given below.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 13, 2015 767-53A0267 Revision 1: August 04, 2016 14 of 206 BOEING SERVICE BULLETIN 767-53A0267 ALERT ALERTAffected Maintenance ZonesZone Model 165, 166, 251, 252, 253, 254, 311, 312, 313, 314, 315, 316, 321, 322, 323, 324, 325, 326, 331, 332, 333, 334, 335, 336, 337, 338, 341, 342, 343, 344, 345, 346, 347, 348 767-200, 767-300
E. Compliance The Federal Aviation Administration (FAA) will possibly release an additional Airworthiness Directive related to this service bulletin. The Airworthiness Directive will make the compliance tasks and times given in this service bulletin mandatory. Federal Aviation Administration (FAA) Airworthiness Directive AD 2004-14-19 is related to this service bulletin. The effective date of AD 2004-14-19 is August 20, 2004. Federal Aviation Administration (FAA) Airworthiness Directive AD 2009-06-19 is related to this service bulletin. The effective date of AD 2009-06-19 is April 28, 2009. Federal Aviation Administration (FAA) Airworthiness Directive AD 2004-05-16 is related to this service bulletin. The effective date of AD 2004-05-16 is April 13, 2004. Do the required actions in accordance with Paragraph 3. Accomplishment Instructions. Table 1: Replacement of the STA 1582 Aft Pressure Bulkhead Repeat Interval (Not to Exceed) Compliance Time (Whichever Occurs Later) Action Condition

- Within 36 months after the original issuedate of this service bulletin. Before 60,000 total flight cycles but no earlierthan 37,500 total flight cycles.Do PART 2: AFT PRESSURE BULKHEAD REPLACEMENT All Airplanes

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.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 13, 2015 767-53A0267 Revision 1: August 04, 2016 15 of 206 BOEING SERVICE BULLETIN 767-53A0267 ALERT ALERTThe Manager of the FAA Seattle Aircraft Certification Office approves the modification defined in this service bulletin as an alternative method of compliance to the requirements of paragraph (b), (c) and (d) of AD 2004-14-19. All provisions of AD 2004-14-19 that are not specifically referenced in the above statement remain fully applicable and must be complied with. In addition, the Manager of the FAA Seattle Aircraft Certification Office approves the modification defined in this service bulletin as an alternative method of compliance to the requirements of paragraph (f) of AD 2009-06-19. All provisions of AD 2009-06-19 that are not specifically referenced in the above statement remain fully applicable and must be complied with. In addition, the Manager of the FAA Seattle Aircraft Certification Office approves the modification defined in this service bulletin as an alternative method of compliance to the requirements of paragraph (a) and (b) of AD 2004-05-16. All provisions of AD 2004-05-16 that are not specifically referenced in the above statement remain fully applicable and must be complied with. G. Manpower The table below shows an estimate of the task hours necessary to do this change for each airplane. This estimate is for direct labor only, done by an experienced crew. Adjust the estimate with operator task hour data if necessary. The estimate does not include lost time. These are some examples of lost time: • Time to adjust to the workplace • Time to schedule the work • Time to inspect the work • Time to cure the materials • Time to make the parts • Time to find the tools AFT PRESSURE BULKHEAD REPLACEMENT Elapsed Hours Task Hours Number of Persons Task 3.00 6.00 2 Prepare the new bulkhead (Paragraph 3.B., Part 1) 38.00 228.00 6 Get Access (Para- graph 3.B., Part 2, through Step 21) 36.00 216.00 6 Remove the vertical fin (Paragraph 3.B., Part 2, Step 22) 33.50 201.00 6 Remove the horizon-tal stabilizer (Paragraph 3.B., Part 2, Step 35)

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 13, 2015 767-53A0267 Revision 1: August 04, 2016 16 of 206 BOEING SERVICE BULLETIN 767-53A0267 ALERT ALERTAFT PRESSURE BULKHEAD REPLACEMENT Elapsed Hours Task Hours Number of Persons Task 15.00 90.00 6 Remove the forward part of Section 48 (Paragraph 3.B., Part 2, Step 32 through Step 34) 3.25 13.00 4 Remove the aft pres- sure bulkhead from the forward part ofSection 48 (Paragraph 3.B., Part 2, Step 35) 3.25 13.00 4 Install the new aft pressure bulkhead in the forward part ofSection 48 (Paragraph 3.B., Part 2, Step 36) 15.00 90.00 6 Install the forward part of Section 48 (Paragraph 3.B., Part 2, Step 20.50 123.00 6 Install the horizontal stabilizer (Paragraph 3.B., Part 2, Steps 39 through 44) 13.50 81.00 6 Install the tail cone (Paragraph 3.B., Part 2, Steps 45 through 49) 36.00 216.00 6 Install the vertical fin (Paragraph 3.B., Part 2, Step 50 39.50 237.00 6 Restore Access (Paragraph 3.B., Part 2, Step 51 through Step 69) 9.00 27.00 3 Test disturbed sys- tems (Paragraph 3.B., Part 3) 265.50 1541.00 TOTAL FOR EACH AIRPLANE

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 13, 2015 767-53A0267 Revision 1: August 04, 2016 17 of 206 BOEING SERVICE BULLETIN 767-53A0267 ALERT ALERTH. Weight and Balance Changes Change in Moment (Pound-Inches) Change in Weight (Pounds) Airplane +98084.0 +62.0 767-200 +106268.0 +62.0 767-300 I. Electrical Load Data Not changed. J. References 1. Existing Data: a. Boeing Service Bulletin 767-25A0300, 767-53A0078, 767-53A0085, 767-53A0087, 767-53A0105, 767-53A0131, 767-53A0139, 767-53A0147 b. Boeing Service Letter 767-SL-00-014, 767-SL-51-008-B, 767-SL-51-036 c. Federal Aviation Administration (FAA) Airworthiness Directive (AD) 2003-10-11, 2003-13-03, 2004-05-16, 2004-14-19, 2005-11-02, 2009-06-19, 2011-14-02, 2012-09-08 d. Service Bulletin Index D624T001 e. Standard Overhaul Practices Manual (SOPM) 20-10-02, 20-30-03, 20-41-01, 20-41-02, 20-50-01, 20-50-19 f. Standard Wiring Practices Manual (SWPM) 20-10-11, 20-10-12, 20-10-19 g. 767 Aircraft Maintenance Manual (AMM) 05-51-24, 07-11-03, 12-15-01, 12-15-02, 20-10-03, 20-10-04, 20-10-09, 22-10-00, 22-21-00, 23-11-00, 23-41-00, 24-22-00, 25-21-01, 25-21-05, 25-22-01, 25-22-02, 25-22-10, 25-25-01, 25-25-04, 25-27-02, 25-31-04, 25-41-04, 25-52-03, 25-55-01, 27-21-00, 27-21-11, 27-21-13, 27-23-00, 27-28-00, 27-31-00, 27-31-01, 27-31-02, 27-32-00, 27-41-00, 27-41-10, 27-48-00, 27-58-01, 28-25-05, 29-11-00, 31-31-00, 31-51-04, 32-00-20, 33-31-00, 33-45-00, 34-11-01, 36-11-01, 38-11-01, 38-32-11, 38-32-51, 51-24-09, 53-01-01, 53-66-02, 55-10-01, 55-10-02, 55-17-51, 55-36-02 h. 767 Aircraft Recovery Document (ARD) i. 767-200 Structural Repair Manual (SRM) 51-20-01, 51-50-02 j. 767-300 Structural Repair Manual (SRM) 51-20-01, 51-50-02 2. Data Supplied with this Service Bulletin: a. Drawings:

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 13, 2015 767-53A0267 Revision 1: August 04, 2016 18 of 206 BOEING SERVICE BULLETIN 767-53A0267 ALERT ALERTADCN DCN/REV Sheet Title Drawing No

- J 1 Section 48/72 Integration 100T3480

- C PSDL

- - 1 Shim Details - Section 48/72 100T3481

- C 1 Corrosion Inhibiting Compound Installation - Fuselage 140T6000

- A 1 Mechanical Equipment Forward 48 Section Stand 2ME148T0200PBR

- A 2

- A 1 Mechanical Equipment Aft 48 Section Stand 2ME148T0600PBR

- A 2

- - 1 Mechanical Equipment Strongback, Pres-sure Bulkhead Transportation and Installation 2ME148T2610PBR

- A 2

- A 3

- A 4

- A 5

- - 1 Miscellaneous Tool Torque Multiplier and Adapter, Vertical Fin 2MIT100T3480PBR

- A 2

- A 3

- - 4

- - 5

- - 6

- A 1 Overhead Mechanical Equipment Vertical Fin Assembly Sling 2OHME100T3480PBR

- - 1 Mechanical Equip Sling and Strongback Fwd 48 Section Pressure Bulkhead 3ME140T0140PBR

- - 2

- - 3

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 13, 2015 767-53A0267 Revision 1: August 04, 2016 19 of 206 BOEING SERVICE BULLETIN 767-53A0267 ALERT ALERTADCN DCN/REV Sheet Title Drawing No

- - 1 Aft Pressure Bulkhead Parts Removal 624T0020

- A 10

- - 11

- A 12

- A 13

- A 14

- A 15

- A 16

- A 17

- - 2

- - 3

- - 4

- - 5

- A 6

- A 7

- B 8

- A 9

- B 1 Mechanical Equipment Vertical Fin Lift Fit- tings ME100T3480PBR

- - 1 Mechanical Equipment Forward 48 Section Handling Fitting ME148T0200PBR

- A 1 Mechanical Equipment Aft 48 Section Han- dling Fitting ME148T0600PBR

- - 1 Mechanical Equipment Strongback Pressure Bulkhead Removal ME148T2610PBR

- A 2

- A 3

- A 5

- A 1 Mechanical Equipment Vert Fin Stand Floor Mounted ME170T0100PBR

- A 2

- A 1 Mechanical Equipment Floor Mounted Stand Horizontal Stabilizer ME180T0000PBR

- - 1 Mechanical Equipment Lift Fittings Front and Rear Spar Horizontal Stabilizer ME182T0000PBR

- - 1 Misc Tool Alignment Pins Vertical Fin Body Join MIT100T3480PBR

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- - 1 Overhead Mech Equip Pressure Dome Sling Fwd 48 Section OHME148T2610PBR

- - 2

- - 1 Overhead Mech Equip Horizontal Stabilizer Complete OHME180T0100PBR

- - 2

- - 1 Portable Mechanical Equipment Forward 48 Section Internal Scaffolding PME148T0010PBR

- - 2

- - 3

- - 4

- - 5

- - 6

- - 1 Protective Equipment Pressure Bulkhead Cover PRE148T2610PBR

- - 1 Shipping Mech Equip Ground Transporta- tion Aft Pressure Bulkhead SME148T2610PBR

- - 2

- - 3

- - 4 3. Installation Drawings Used in the Preparation of this Service Bulletin: Title Drawing Number Section 48/72 Integration 100T3480 Monocoque Integration - Section 46/48 140T0140 Floor System Integration Section 46 - 48 140T0540 Seal Application Section 48 Integration 140T4800 Stanchion Installation - Sect 46 146T5500 Support Instl - Galley Tie Down Fittings, Sect 46 146T5604 Fastener Instl Bulkhead Splice STA 1809.5 148T0006 Fastener Instl 148T0007 Fastener Instl - STA 1809.5 Splice, Sect 48 148T0008 Frame Instl - Pivot Bulkhead 148T1150 Bulkhead End Item - Center, Horiz Stab Pivot, STA 1809.5 148T2740 Seal Instl - Pitot/Static Tubing Pressure Dome 233T9112 Pressure Seal Instl - Pressure Dome STA 1582.0 255T4821 Retainer Instl - Pressure Seal, Hydraulic Tubing 272T4831

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 13, 2015 767-53A0267 Revision 1: August 04, 2016 21 of 206 BOEING SERVICE BULLETIN 767-53A0267 ALERT ALERTTitle Drawing Number Tubing Instl - APU Fuel Feed, Body Sections 45, 46 and 48 346T0003 Corrosion Inhibiting Compound Installation - Fuselage 140T6000 Shim Details - Section 48/72 100T3481NOTE:These drawings were used to prepare this service bulletin. These drawings are not necessary to make the specified changes, and are not supplied with this service bulletin. These drawings may not be applicable to all airplane configurations or operators. K. Publications Affected 1. Publications: Chapter-Section Publication 28-25, 29-11, 34-11, 53-80 767 Illustrated Parts Catalog 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: August 13, 2015 767-53A0267 Revision 1: August 04, 2016 22 of 206 BOEING SERVICE BULLETIN 767-53A0267 ALERT ALERT2. MATERIAL INFORMATION A. Material - Price and Availability Boeing can supply the kits/parts shown in Paragraph 2.C., Parts Necessary for Each Airplane. Operators are encouraged to share schedule requirements with Boeing for incorporation of the service bulletin. The kits/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 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 issuedate of this Service Bulletin (US Dollars) ROLT as of the original issuedate of this Service Bulletin (Calendar Days) Name Kit Number
$86,435.00 550 Top Kit - STA 1582 Aft Pressure Bulkhead Replacement 015T1907-1 $578,050.00 450 Aft Pressure Bulkhead 691T0103-1 Operators are encouraged to complete the survey provided in APPENDIX D of this service bulletin to help Boeing predict the quantity and timing of the Boeing Supplied Kits/Parts. B. Industry Support Information Boeing warranty remedies are not available for the configuration changes given in this service bulletin. 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, one aft bulkhead assembly and the items shown in Paragraph 2.C.2., Parts and Materials Supplied by the Operator, are necessary for each airplane. The Top Kit is divided into Figure kits for each installation figure shown in the table below. Kit 691T0103 Quantity Part Number 1 691T0103-1

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 13, 2015 767-53A0267 Revision 1: August 04, 2016 23 of 206 BOEING SERVICE BULLETIN 767-53A0267 ALERT ALERTFigure Kit 14 13 12 11 6 1 Top Kit 1 1 1 1 1 1 015T1907-1 Figure Kit 26 24 22 17 16 15 Top Kit 1 1 1 1 1 1 015T1907-1 Figure Kit 28 Top Kit 1 015T1907-1 ALL KIT 015T1907-1

Notes Existing Part Number Name Figure New Part Number 14 13 12 11 6 1 Qty (a) WASHER
. . 2 . . . 140T0140-5 (b) CLIP
. . 1 . . . 140T0142U1(140T0142-1 optional) (b) CLIP
. . 1 . . . 140T0142U2(140T0142-2 optional)

- FITTING ASSY
. . 2 . . . 140T0169-7

- COVER PLATE
. . . . . 1 140T0345-1

- SEAL BLOCK AS- SY . . . . . 1 140T0345-3

- FILLER 2 2 . . . . 148T0012-2

- FILLER 2 2 . . . . 148T0012-3

- SHIM 1 1 . . . . 148T0012-4

- SHIM 1 1 . . . . 148T0012-5

- FILLER 1 1 . . . . 148T0012-11

- SHIM 2 . . . . . 148T0012-18

- SHIM
. 2 . . . . 148T0012-19

- SPLICE-STRAP 2 2 . . . . 148T0015-1

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 13, 2015 767-53A0267 Revision 1: August 04, 2016 24 of 206 BOEING SERVICE BULLETIN 767-53A0267 ALERT ALERTALL KIT 015T1907-1

Notes Existing Part Number Name Figure New Part Number 14 13 12 11 6 1 Qty

- SEAL BLOCK AS- SY . . . . . 1 148T2629-2

- BRACKET ASSY-
. . 1 . . . 272T4825-9

- SEAL
. . . . 1 . 40345 (678782 optional)

- FITTING ASSY
. . 2 . . . 412T3106-406

- fitting assy
. . 1 . . . 412T3106-408 (a) BOLT, PROTRUD- ING HD 8 8 . . . . BACB30MY10K10X (a) BOLT TITANIUM O/S 10 10 . . . . BACB30MY10K3X (a) BOLT, PROTRUD- ING HD 5 5 . . . . BACB30MY10K5X (a) BOLT, PROTRUD- ING HD 1 1 . . . . BACB30MY10K6X (a) BOLT, PROTRUD- ING HD 11 11 . . . . BACB30MY10K7X (a) BOLT, PROTRUD- ING HD 14 14 . . . . BACB30MY10K8X (a) BOLT, PROTRUD- ING HD 4 4 . . . . BACB30MY12K10X (a) BOLT, PROTRUD- ING HD 2 2 . . . . BACB30MY12K6X (a) BOLT, PROTRUD- ING HD 4 4 . . . . BACB30MY12K7X (a) BOLT, PROTRUD- ING HD 4 4 . . . . BACB30MY12K8X (a) BOLT, PROTRUD- ING HD 7 7 . . . . BACB30MY8K10X (a) BOLT, PROTRUD- ING HD 3 3 . . . . BACB30MY8K11X (a) BOLT, PROTRUD- ING HD 4 4 . . . . BACB30MY8K12X

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 13, 2015 767-53A0267 Revision 1: August 04, 2016 25 of 206 BOEING SERVICE BULLETIN 767-53A0267 ALERT ALERTALL KIT 015T1907-1

Notes Existing Part Number Name Figure New Part Number 14 13 12 11 6 1 Qty (a) BOLT, PROTRUD- ING HD 35 35 . . . . BACB30MY8K5X (a) BOLT, PROTRUD- ING HD 1 1 . . . . BACB30MY8K6X (a) BOLT, PROTRUD- ING HD 65 65 . . . . BACB30MY8K7X (a) BOLT, PROTRUD- ING HD 3 3 . . . . BACB30MY8K8X (a) BOLT, PROTRUD- ING HD 1 1 . . . . BACB30MY8K9X (a) BOLT, HEX HEAD
. . . . . 16 BACB30NM4K14 (a) BOLT, 100 DEG HEX DR 4 4 . . . . BACB30NW8K13X (a) BOLT, 100 DEG HEX DR 2 2 . . . . BACB30NW8K5X (a) BOLT, 100 DEG HEX DR 2 2 . . . . BACB30NW8K7X (a) BOLT, 100 DEG HEX DR 4 4 . . . . BACB30NW8K8X (a) BOLT, PROTRUD- ING HD 4 4 . . . . BACB30NX10K11X (a) BOLT, PROTRUD- ING HD 4 4 . . . . BACB30NX10K12X (a) BOLT, PROTRUD- ING HD 2 2 . . . . BACB30NX10K8X (a) BOLT, PROTRUD- ING HD 2 2 . . . . BACB30NX10K9X (a) BOLT, PROTRUD- ING HD 4 4 . . . . BACB30NX12K12X (a) BOLT, PROTRUD- ING HD . . 2 . . . BACB30NX6K10X (a) BOLT, PROTRUD- ING HD . . 20 . . . BACB30NX6K4X (a) BOLT, PROTRUD- ING HD . . 2 . . . BACB30NX6K5X

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 13, 2015 767-53A0267 Revision 1: August 04, 2016 26 of 206 BOEING SERVICE BULLETIN 767-53A0267 ALERT ALERTALL KIT 015T1907-1

Notes Existing Part Number Name Figure New Part Number 14 13 12 11 6 1 Qty (a) BOLT, 12 PT HEAD . . 26 . . . BACB30US5K16 (a) BOLT, 12 PT HEAD . . 58 . . . BACB30US5K17 (a) BOLT, 12 PT HEAD . . 40 . . . BACB30US5K18 (a) BOLT, 12 PT HEAD . . 24 . . . BACB30US5K19 (a) BOLT, 12 PT HEAD . . 10 . . . BACB30US5K21 (a) BOLT, 12 PT HEAD . . 6 . . . BACB30US5K25 (a) BOLT, 12 PT HEAD . . 4 . . . BACB30US6K31 (a) BOLT, 12 PT HEAD . . 40 . . . BACB30US6K33 (a) BOLT, 12 PT HEAD . . 32 . . . BACB30US6K34 (a) BOLT, 12 PT HEAD . . 8 . . . BACB30US6K35 (a) BOLT, 12 PT HEAD . . 8 . . . BACB30US6K36 (a) BOLT, 12 PT HEAD . . 20 . . . BACB30US7K35 (a) BOLT, 12 PT HEAD . . 12 . . . BACB30US7K39 (a) BOLT, 12 PT HEAD . . 16 . . . BACB30US7K40 (a) BOLT, 12 PT HEAD . . 16 . . . BACB30US8K42 (a) COLLAR 14 14 . . . . BACC30BH10 (a) COLLAR 4 4 . . . . BACC30BH12 (a) COLLAR
. . 24 . . . BACC30BH6 (a) COLLAR 49 49 . . . . BACC30M10

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 13, 2015 767-53A0267 Revision 1: August 04, 2016 27 of 206 BOEING SERVICE BULLETIN 767-53A0267 ALERT ALERTALL KIT 015T1907-1

Notes Existing Part Number Name Figure New Part Number 14 13 12 11 6 1 Qty (a) COLLAR 14 14 . . . . BACC30M12 (a) COLLAR 145 145 . . . . BACC30M8 (a) NUT . . 156 . . . BACN10HR5CD (a) SELF-LOCKING NUT . . 92 . . . BACN10HR6CD (a) NUT . . 44 . . . BACN10HR7CD (a) NUT . . 16 . . . BACN10HR8CD (a) NUT, SELF-LOCK
. . . . . 15 BACN11AG3 (a) RIVET, UNIVER- SAL HD . . . . . 50 BACR15BB5A7C (a) RIVET, UNIVER- SAL HD . . . . . 5 BACR15BB6A8C (a) RIVET . . . . . 8 BACR15FT6KE7C (a) RIVET 5 5 . . . . BACR15FV7KE7 (a) RIVET 1 1 . . . . BACR15FV7KE8 (a) BOLT
. . . . . 15 BACS12HN3-7

- SHIM, LAMINAT- ED . . 2 . . . BACS40R011B012F

- SHIM,LAMINATED 2 2 . . . . BACS40R011B027F

- SHIM, LAMINAT- ED 2 2 . . . . BACS40R012B027F

- SHIM, LAMINAT- ED 1 1 . . . . BACS40R016B098F

- SHIM, LAMINAT- ED 1 1 . . . . BACS40R027C030F (a) CSK WASHER
. . 156 . . . BACW10BP5CD (a) WASHER-PLAIN
. . 154 . . . BACW10BP5DP (a) WASHER, PLAIN
. . 92 . . . BACW10BP6CD (a) WASHER
. . 92 . . . BACW10BP6DP (a) WASHER
. . 44 . . . BACW10BP7CD (a) WASHER
. . 44 . . . BACW10BP7DP

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Notes Existing Part Number Name Figure New Part Number 14 13 12 11 6 1 Qty (a) WASHER
. . 16 . . . BACW10BP8CD (a) WASHER
. . 16 . . . BACW10BP8DP (a) WASHER
. . . . 8 . NAS1149D0316J (a) WASHER
. . . . . 30 NAS1149D0332J (a) WASHER, FLAT
. . . . . 5 NAS1149D0363J (a) RIVET, BLIND . . . 31 . . NAS1399D6A10 (NAS1399D6AB10 optional)

- SPACERS FOR RIVETS . . . . . 1 NAS42DD3-44FC

- SPACERS FOR RIVETS . . . . . 1 NAS42DD3-48FC

- SPACERS FOR RIVETS . . . . . 1 NAS42DD3-64FC (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. (b) To make installation easier, some Boeing parts are sent in an 'interim' configuration. Boeing will identify these interim configurations with a 'U', 'W' or 'Y' in place of the '-' (dash) in the part number. Interim parts are changed to the 'dash' configuration when installed as given in the Accomplishment Instructions of this service bulletin. Refer to Boeing Drawing 005W0900 "INTERIM PARTS - SPARES" and Boeing Service Letter 767-SL-00-014 for more information. ALL KIT 015T1907-1

Notes Existing Part Number Name Figure New Part Number 26 24 22 17 16 15 Qty (a) washer . . . . . 2 148T2746-1

- filler
. . . . . 2 148T2746-2

- TUBE ASSY
. . . 1 . . 233T9110-566

- TUBE ASSEMBLY
. . . 1 . . 233T9110-665

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Notes Existing Part Number Name Figure New Part Number 26 24 22 17 16 15 Qty

- PLATER RETAIN- ER . . . 2 . . 233T9113-4

- SEAL
. . . . 3 . 270T0004-1101

- SEAL
. . . . 1 . 270T0004-1102

- RETAINER- . . . . 1 . 272T4830-1

- RETAINER ASSY-
. . . . 1 . 272T4830-2

- SEAL-
. . . 1 . . 69B41314-6 (a) BOLT
. . . 24 . . BACB30LM3-3 (a) BOLT, 12 PT HEAD . . . . . 10 BACB30LT5-12 (a) BOLT, 12 PT HEAD . . . . . 8 BACB30LT7-12 (a) BOLT, PROTRUD- ING HD . . 12 . . . BACB30MY8K4X (a) BOLT, 100 DEG HEX DR 6 6 . . . . BACB30NW8K8X (a) HEX DRIVE BOLT
. . . . . 44 BACB30NX10K10 (a) BOLT
. . . . . 54 BACB30NX10K7 (a) BOLT
. . . . . 8 BACB30NX14K16 (a) BOLT, PROTRUD- ING HD . . 3 . . . BACB30NX6K4X (a) BOLT
. . . . . 8 BACB30NX6K5 (a) BOLT, PROTRUD- ING HD . . 5 . . . BACB30NX6K6X (a) HI LOK
. . . . . 8 BACB30NX8K5 (a) BOLT, PROTRUD- ING HD . . 22 . . . BACB30NX8K5X (a) BOLT, PROTRUD- ING HD . . 6 . . . BACB30NX8K6X (a) BOLT, HEX DRIVE
. . . . . 76 BACB30NX8K7 (a) BOLT, PROTRUD- ING HD . . 14 . . . BACB30NX8K7X

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 13, 2015 767-53A0267 Revision 1: August 04, 2016 30 of 206 BOEING SERVICE BULLETIN 767-53A0267 ALERT ALERTALL KIT 015T1907-1

Notes Existing Part Number Name Figure New Part Number 26 24 22 17 16 15 Qty (a) BOLT, 12 PT HEAD . . . . . 4 BACB30US12K37 (a) BOLT, 12 PT HEAD . . . . . 4 BACB30US12K40 (a) BOLT, 12 PT HEAD . . . . . 22 BACB30US7K24 (a) BOLT, 12 PT HEAD . . . . . 2 BACB30US7K26 (a) BOLT, 12 PT HEAD . . . . . 4 BACB30US7K27 (a) BOLT, 12 PT HEAD . . . . . 32 BACB30US7K28 (a) BOLT, 12 PT HEAD . . . . . 2 BACB30US8K30 (a) BOLT, 12 PT HEAD . . . . . 4 BACB30US8K31 (a) BOLT, 100 DEG HEAD 10 10 . . . . BACB30VF3K5 (a) BOLT 3 3 . . . . BACB30VF3K7

- CLAMP, LOOP
. . . 10 . . BACC10DK6 (a) COLLAR
. . . . . 107 BACC30BH10 (a) COLLAR, PRELOAD . . . . . 8 BACC30BH14 (a) COLLAR
. . . . . 8 BACC30BH6 (a) COLLAR
. . 42 . . 84 BACC30BH8 (a) COLLAR
. . 8 . . . BACC30M6 (a) COLLAR 6 6 12 . . . BACC30M8 (a) SELF-LOCKING NUT . . . . . 8 BACN10HR12CD (a) NUT . . . . . 60 BACN10HR7CD (a) NUT . . . . . 4 BACN10HR8CD (a) NUT . . . . 18 . BACN10JC3CD

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 13, 2015 767-53A0267 Revision 1: August 04, 2016 31 of 206 BOEING SERVICE BULLETIN 767-53A0267 ALERT ALERTALL KIT 015T1907-1

Notes Existing Part Number Name Figure New Part Number 26 24 22 17 16 15 Qty (a) SELF-LOCKING NUT . . . . . 10 BACN10JC5CD (a) SELF-LOCKING NUT . . . . . 8 BACN10JC7CD (a) RIVET, UNIVER- SAL HD 2 2 . . . . BACR15FT5KE9C (a) RIVET 5 5 . . . . BACR15FV6KE7 (a) RIVET 1 1 . . . . BACR15FV6KE8 (a) BOLT
. . . . 24 . BACS12HN3-9

- SHIM, LAMINAT- ED . . 2 . . . BACS40R040C095F (a) WASHER, PLAIN
. . . . . 8 BACW10BP12CD (a) WASHER, PLAIN
. . . . . 8 BACW10BP12DP (a) CSK WASHER
. . . . . 10 BACW10BP5CD (a) WASHER-PLAIN
. . . . . 12 BACW10BP5DP (a) WASHER
. . . . . 68 BACW10BP7CD (a) WASHER
. . . . . 68 BACW10BP7DP (a) WASHER
. . . . . 4 BACW10BP8DP (a) WASHER
. . . . 24 . NAS1149D0316J (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. ALL KIT 015T1907-1

Notes Existing Part Number Name Figure New Part Number28Qty (a) BOLT, PROTRUD- ING HD 6 BACB30NX10K10X (a) BOLT, PROTRUD- ING HD 6 BACB30NX10K12X

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 13, 2015 767-53A0267 Revision 1: August 04, 2016 32 of 206 BOEING SERVICE BULLETIN 767-53A0267 ALERT ALERTALL KIT 015T1907-1

Notes Existing Part Number Name Figure New Part Number28Qty (a) BOLT, PROTRUD- ING HD 2 BACB30NX10K13X (a) BOLT, PROTRUD- ING HD 2 BACB30NX10K15X (a) BOLT, PROTRUD- ING HD 4 BACB30NX12K11X (a) BOLT, PROTRUD- ING HD 10 BACB30NX12K14X (a) BOLT TIANIUM O/S 58 BACB30NX12K15X (a) BOLT, HEX DRIVE 14 BACB30NX12K9X (a) BOLT, PROTRUD- ING HD 4 BACB30NX16K11X (a) BOLT, PROTRUD- ING HD 8 BACB30NX6K19X (a) BOLT, PROTRUD- ING HD 4 BACB30NX6K6X (a) BOLT, PROTRUD- ING HD 4 BACB30NX8K16X (a) BOLT, PROTRUD- ING HD 28 BACB30NX8K5X (a) BOLT, PROTRUD- ING HD 6 BACB30NX8K9X (a) BOLT, 12 PT HEAD 4 BACB30US16K47 (a) BOLT, 12 PT HEAD 4 BACB30US16K48 (a) BOLT, 12 PT HEAD 2 BACB30US16K50 (a) BOLT, 12 PT HEAD 2 BACB30US16K51 (a) BOLT, 12 PT HEAD 4 BACB30US18K52 (a) COLLAR 16 BACC30BH10

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 13, 2015 767-53A0267 Revision 1: August 04, 2016 33 of 206 BOEING SERVICE BULLETIN 767-53A0267 ALERT ALERTALL KIT 015T1907-1

Notes Existing Part Number Name Figure New Part Number28Qty (a) COLLAR 86 BACC30BH12 (a) COLLAR 12 BACC30BH6 (a) COLLAR 38 BACC30BH8 (a) COLLAR 4 BACC30X16 (a) BARREL NUT 12 BACN11B16CS (a) BARREL NUT 4 BACN11B18CS (a) WASHER, PLAIN 12 BACW10BP16CD (a) WASHER, PLAIN 4 BACW10BP18CD (a) WASHER 16 NAS1149E1632P (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. Notes Name Qty Part Number/Specifica- tion

- Plate 1 A

- Plate 1 B

- Bolt 8 BACB30NM4K4

- Bolt 120 BACB30NX6K5

- Bolt 18 BACB30NX6K8

- Collar 138 BACC30BH6SW

- Bolt 8 BACB30LM3-3

- Epoxy Adhesive 2 Oz BMS 5-25

- Sealant 2 Oz BMS 5-95

- Sealant 2 Oz BMS 5-125 Type II

- Sealant 2 Oz BMS 5-142

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 13, 2015 767-53A0267 Revision 1: August 04, 2016 34 of 206 BOEING SERVICE BULLETIN 767-53A0267 ALERT ALERTNotes Name Qty Part Number/Specifica- tion

- Sealant 2 Oz BMS 3-27

- Sealant 2 Oz BMS 3-38

- Primer 2 Oz BMS 10-11

- Angle 6 C

- Angle 2 D

- Angle 2 E

- Plate 2 F

- Angle 2 G 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 Boeing can supply the tool(s) shown in Paragraph 2.F., Special Tooling Necessary to do this Service Bulletin. Operators are encouraged to share schedule requirements with Boeing for incorporation of the service bulletin by e-mail to ServiceBulletinRentalLoanTools@boeing.com. The tool(s) are subject to the terms and conditions of the Boeing standard purchase order acknowledgement. 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 Boeing Part Page 2. Fax to (425) 965-8237 Rental Data: Daily Price as of the Original Issuedate of this service bulletin (US Dollars) Name Tool Kit Number
$550.00 Forward 48 Section Internal Scaffolding PME148T0010PBR

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 13, 2015 767-53A0267 Revision 1: August 04, 2016 35 of 206 BOEING SERVICE BULLETIN 767-53A0267 ALERT ALERTRental Data: Daily Price as of the Original Issuedate of this service bulletin (US Dollars) Name Tool Kit Number
$224.00 Pressure Bulkhead Cover PRE148T2610PBR $200.00 Vertical Fin Alignment Pins MIT100T3480PBR $260.00 Vertical Fin Floor Stand ME170T0100PBR $420.00 Pressure Dome Sling OHME148T2610PBR $260.00 Vertical Fin Lift Sling 2OHME100T3480PBR $380.00 Vertical Fin Lift Fittings ME100T3480PBR $200.00 Horizontal Stabilizer Lift Fittings ME182T0000PBR $380.00 Horizontal Stabilizer Lift Sling OHME180T0100PBR $260.00 Forward 48 Section Sling and Strongback 3ME140T0140PBR $550.00 Vertical Fin Torque Multiplier and Adapter 2MIT100T3480PBR $400.00 Aft 48 Section Lift Sling and At- tach Fittings ME148T0600PBR (a) Pressure Bulkhead Removal Strongback ME148T2610PBR $240.00 Horizontal Stabilizer Floor Stand ME180T0000PBR $380.00 Aft 48 Section Stand 2ME148T0600PBR $420.00 Forward 48 Section Attach Fit- tings ME148T0200PBR $440.00 Forward 48 Section Stand 2ME148T0200PBR $400.00 Pressure Bulkhead Transporta- tion Removal Strongback 2ME148T2610PBR $460.00 Pressure Bulkhead Ground Transportation Fixture 2SME148T2610PBR A $150.00 handling is added to all tool rentals (a) Rental price data for this tool was not available at the time this service bulletin was issued.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 13, 2015 767-53A0267 Revision 1: August 04, 2016 36 of 206 BOEING SERVICE BULLETIN 767-53A0267 ALERT ALERTREFER 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 Purchase Data: Unit Price as of the Original Issuedate of this Service Bulletin (US Dollars) Name Tool Kit Number
$192,263.00 Forward 48 Section internal Scaffolding PME148T0010PBR $24,471.00 Pressure Bulkhead Cover PRE148T2610PBR $12,818.00 Vertical Fin Alignments Pins MIT100T3480PBR $27,104.00 Vertical Fin Floor Stand ME170T0100PBR $82,322.00 Pressure Dome Sling OHME148T2610PBR $28,371.00 Vertical Fin Lift Sling 2OHME100T3480PBR $60,331.00 Vertical Fin Lift Sling ME100T3480PBR $12,819.00 Horizontal Stabilizer Lift Fittings ME182T0000PBR $64,089.00 Horizontal Stabilizer Lift Sling OHME180T0100PBR $28,680.00 Forward 48 Section Sling and Strongback 3ME140T0140PBR $192,263.00 Vertical Fin Torque Multiplier and Adapter 2MIT100T3480PBR $74,129.00 Aft 48 Section Lift Sling and At- tach Fittings ME148T0600PBR $62,077.00 Aft 48 Section Stand 2ME148T0600PBR $81,929.00 Forward 48 Section Attach fit- tings ME148T0200PBR $94,649.00 Forward 48 Section Stand 2ME148T0200PBR $21,600.00 Horizontal Stabilizer Floor Stand ME180T0000PBR $72,810.00 Pressure Bulkhead Transporta- tion 2ME148T2610PBR (a) Pressure Dome Removal Strongback ME148T2610PBR $105,508.00 Pressure Bulkhead Ground Transportation Fixture 2SME148T2610PBR (a) Purchase price data for this tool was not available at the time this service bulletin was issued.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 13, 2015 767-53A0267 Revision 1: August 04, 2016 37 of 206 BOEING SERVICE BULLETIN 767-53A0267 ALERT ALERTF. Special Tooling Necessary to do this Service Bulletin To get the tools shown below, refer to Paragraph 2.E., Special Tooling - Price and Availability. Maintenance and overhaul tools in the manuals shown in Paragraph 1.J., References, can also be necessary. Examine operator tool supply to make sure all necessary tools are available. Name Tool Kit NumberForward 48 Section Internal Scaffolding PME148T0010PBRPressure Bulkhead Cover PRE148T2610PBRVertical Fin Alignment Pins MIT100T3480PBRVertical Fin Floor Stand ME170T0100PBRPressure Dome Sling OHME148T2610PBRPressure Dome Removal Strongback ME148T2610PBRVertical Fin Lift Sling 2OHME100T3480PBRVertical Fin Lift Fittings ME100T3480PBRHorizontal Stabilizer Lift Fittings ME182T0000PBRHorizontal Stabilizer Lift Sling OHME180T0100PBRForward 48 Section Sling and Strongback 3ME140T0140PBRVertical Fin Torque Multiplier and Adapter 2MIT100T3480PBRAft 48 Section Lift Sling and Attach Fittings ME148T0600PBRHorizontal Stabilizer Floor Stand ME180T0000PBRAft 48 Section Stand 2ME148T0600PBRForward 48 Section Attach Fittings ME148T0200PBRForward 48 Section Stand 2ME148T0200PBRPressure Bulkhead Transportation 2ME148T2610PBRPressure Bulkhead Ground Transportation Fixture 2SME148T2610PBR

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 13, 2015 767-53A0267 Revision 1: August 04, 2016 38 of 206 BOEING SERVICE BULLETIN 767-53A0267 ALERT ALERT3. ACCOMPLISHMENT INSTRUCTIONS A. GENERAL INFORMATION 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 Values: — Values for structural fasteners are given in 767 Structural Repair Manual, Chapter 51. 4. Use the approved fastener, process and 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. 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. Refer to SOPM 20-50-01 for alternate full threaded fasteners (screws) needed for installation in this service bulletin. 7. 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. 8. 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. 9. Refer to Appendix C for logic diagrams. Logic diagrams are provided as an aid only. Information contained in Paragraph 1.E., Compliance is the primary source for compliance times. Information in Paragraph 3.B., Work Instructions is the primary source for tasks required for compliance.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 13, 2015 767-53A0267 Revision 1: August 04, 2016 39 of 206 BOEING SERVICE BULLETIN 767-53A0267 ALERT ALERT10. 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. 11. 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. 12. 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. 13. This service bulletin includes functional test procedures for the systems changed by this service bulletin. More functional tests can possibly be necessary in accordance with standard maintenance practices because of interruption to other airplane systems. 14. When more than one OPTION is given for a CONDITION, do only one of the OPTION numbers. When more than one ACTION is given for a CONDITION number or an OPTION number, do all of the ACTION numbers for that CONDITION number or OPTION number. 15. The compliance times for the actions in Paragraph 3.B., WORK INSTRUCTIONS are in Paragraph 1.E., Compliance. 16. Use of colors in Figures is based on guidance from the ATA e-Business Program (ATA) iSpec 2200. 17. Some steps in the Work Instructions are labeled as Required for Compliance (RC). If this service bulletin is mandated by an Airworthiness Directive (AD), then the steps labeled as RC, including sub-steps under an RC step and any figures identified in an RC step, must be done to comply with the AD. An Alternative Method of Compliance (AMOC) is required for any deviations to RC steps, including sub-steps and identified figures. Steps not labeled as RC may be deviated from using accepted methods in accordance with the operator's maintenance or inspection program without obtaining approval of an AMOC. This is provided that the RC steps, including sub-steps and identified figures, can still be done as specified, and the airplane can be put back in an airworthy condition. B. WORK INSTRUCTIONS 1. Do PART 1: BULKHEAD PREPARATION 2. Do PART 2: AFT PRESSURE BULKHEAD REPLACEMENT 3. Do PART 3: SYSTEM TESTS 4. Put the airplane back to a serviceable condition PART 1: BULKHEAD PREPARATION 1. Prepare the new aft pressure bulkhead assembly in accordance with FIGURE 1.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 13, 2015 767-53A0267 Revision 1: August 04, 2016 40 of 206 BOEING SERVICE BULLETIN 767-53A0267 ALERT ALERT2.Group 2: Do additional preparation of the new aft pressure bulkhead assembly in accordance with FIGURE 2. PART 2: AFT PRESSURE BULKHEAD REPLACEMENT 1. Supply airplane electrical power. Refer to 767 AMM 24-22-00 as an accepted procedure. 2. Pressurize the center hydraulic system. Refer to 767 AMM 29-11-00 as an accepted procedure. 3. Use the STAB TRIM levers or switches to move the horizontal stabilizer to the neutral position (2 units of trim on the position indicator). 4. Remove the pressure from the center, right, and left hydraulic systems. Refer to 767 AMM 29-11-00 as an accepted procedure. 5. Set the C, R, and L STAB TRIM switches on the P10 Panel to the CUTOUT position and attach DO-NOT-OPERATE tags. 6. On the P61 right side panel, put these switches in the OFF position and attach DO-NOT-OPERATE tags: S2 RIGHT TAIL HD SHUT OFF VALVE SWITCH S4 CENTER TAIL HD SHUT OFF VALVE SWITCH S6 LEFT TAIL HD SHUT OFF VALVE SWITCH 7. Open the following circuit breakers and attach DO-NOT-CLOSE tags: a. On the P11 Overhead Circuit Breaker Panel: (1) For the APU Fuel System: 11B36, APU START 11D34, FUEL DC PUMP PWR 11D35, FUEL DC PUMP CONT 11M25, FUEL PUMPS L FWD R AFT (2) For the horizontal stabilizer ballscrew and pivot pins: 11A36, ALT STAB TRIM (if installed) 11C12, STAB TRIM SHUTOFF L 11C13, STAB TRIM SHUTOFF CENTER 11H17, FLT CONT SHUTOFF TAIL LEFT

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 13, 2015 767-53A0267 Revision 1: August 04, 2016 41 of 206 BOEING SERVICE BULLETIN 767-53A0267 ALERT ALERT11H18, FLT CONT SHUTOFF TAIL CENTER 11H27, FLT CONT SHUTOFF TAIL RIGHT 11D29, ENG HYD PUMP L SUPPLY 11D30, ENG HYD. PUMP R SUPPLY 11L25, HYD ELEC PUMP L 11L16, HYD ELEC PUMP R 11L15, ELEC HYD PUMP C 111L18, HYD SYS C PRESS 11D31, AIR HYD PUMP b. On the P6 Main Power Distribution Panel: 6E3, APU FUEL VALVES 8. Remove airplane electrical power. Refer to 767 AMM 24-22-00 as an accepted procedure. 9. Support and jack the airplane indoors as follows: a. Install nose and main landing gear down locks. Refer to 767 AMM 32-00-20 as an accepted procedure. b. Deflate the nose gear and pump oil into the nose gear. Simultaneously deflate both main gears and pump oil into the main gears. When the oil flow is free of nitrogen bubbles close the valves. Pump additional oil into both the nose and main landing gear oleos to achieve one inch of chrome showing. Refer to 767 AMM 12-15-01 and 767 AMM 12-15-02 as accepted procedures. c. Partially support the airplane with nose and main landing gear/axial jacks at all five axle jackpoints. Refer to 767 AMM 07-11-03 as an accepted procedure. Apply a 10,000 - 12,000 pound load at each axial jack location. Install wheel chocks and chains at each main landing gear. NOTE:Parking brake can remain set. d. Mechanically lock all five axle jacks. 10. Disassemble and remove (or shift forward) equipment from the aft part of the passenger compartment for access to the Aft Pressure Bulkhead joint at STA 1582. This includes: a. Passenger seats. Refer to 767 AMM 25-25-01 as an accepted procedure. b. Partitions. Refer to 767 AMM 25-25-04 as an accepted procedure.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 13, 2015 767-53A0267 Revision 1: August 04, 2016 42 of 206 BOEING SERVICE BULLETIN 767-53A0267 ALERT ALERTc. Aft Galley Complex A1, A4, or A1-A3. Refer to 767 AMM 25-31-04 as an accepted procedure. d. Lavatories. Refer to 767 AMM 25-41-04 as an accepted procedure. e. Sidewall Panels. Refer to 767 AMM 25-21-01 as an accepted procedure. f. Ceiling panels. Refer to 767 AMM 25-22-01, 767 AMM 25-22-02, and/or 767 AMM 25-22-10 as accepted procedures. g. Sidewall and Ceiling Insulation. Refer to 767 AMM 25-21-05 as an accepted procedure. h. Doorway/Galley Floor Covering. Refer to 767 AMM 25-27-02 as an accepted procedure. i. Floor Panels. Refer to 767 AMM 53-01-01 as an accepted procedure. 11. Disassemble and remove (or shift forward) equipment from the aft end of the bulk cargo compartment for access to the Aft Pressure Bulkhead joint at STA 1582. This includes: a. Bulk Cargo Compartment Aft Lining. Refer to 767 AMM 25-55-01 as an accepted procedure. b. Bulk Cargo Compartment Sidewall Lining, for access to the pitot-static tubes on the left side from the aft pressure bulkhead to the bulk cargo door aft frame at STA 1461. Refer to 767 AMM 25-55-01 as an accepted procedure. c. Potable Water Tanks. Refer to 767 AMM 38-11-01 as an accepted procedure. d. Vacuum Lavatory Waste Tanks. Refer to 767 AMM 38-32-11 as an accepted procedure. e. Sidewall Insulation, which includes insulation blankets and capstrips from the sidewall, ceiling, and aft pressure bulkhead. Refer to 767 AMM 25-52-03 as an accepted procedure. NOTE:Boeing Service Bulletin 767-25A0300, "Equipment/Furnishings - Insulation - Aft Bulkhead to Floor Insulation Blankets Modification", which is mandated by FAA AD 2003-13-03, requires replacement of aft pressure bulkhead insulation blankets. 12. Disconnect the elevator (E1A/E1B/E2A/E2B), stabilizer trim (ST1A/ST1B/ ST2A/ST2B) and rudder (RA/RB) control cables. Refer to 767 AMM 20-10-03 as an accepted procedure. a. Install cable clamps. b. Disconnect the cables at any turnbuckle aft of the aft pressure bulkhead. c. Remove and salvage any air seals where the cable penetrates the aft pressure bulkhead. d. Move and coil the cable ends forward and aft of the aft pressure bulkhead. 13. Remove and salvage the control cable air seals and fasteners for the elevator (E1A/E1B/E2A/E2B), stabilizer trim (ST1A/ST1B/ ST2A/ST2B) and rudder (RA/RB) control cables. Refer to 767 AMM 20-10-04 as an accepted procedure. The salvaged air seals will be installed on the new aft pressure bulkhead assembly when the control cables are reinstalled.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 13, 2015 767-53A0267 Revision 1: August 04, 2016 43 of 206 BOEING SERVICE BULLETIN 767-53A0267 ALERT ALERT14. Disconnect and remove auxiliary pitot tubes and seals in accordance with FIGURE 3. 15. Disconnect and remove auxiliary static system tubes (if installed) and hydraulic lines as follows.
a.Group 3: Disconnect the auxiliary static system (AS1 and AS2) tubes at the junctions between STA 1605.5 and STA 1629, between stringers S-31L and S-32L. Cap the open ends of all tubes. Refer to 767 AMM 20-10-09 as an accepted procedure. b. Disconnect and cap the hydraulic lines at or near STA 1809. c. Disconnect and cap the hydraulic lines forward of the aft pressure bulkhead. d. Remove and discard the pressure seals at the aft pressure bulkhead in accordance with FIGURE 4. e. Remove hydraulic lines between the aft pressure bulkhead and STA 1809. f.Group 3: Move the auxiliary static system (AS1 and AS2) tubes forward of STA 1582. 16. Disconnect the electrical connectors from the altitude pressure switches. Refer to 767 AMM 38-32-51 as an accepted procedure. 17. Disconnect electrical systems, including: a. Lights b. APU Power c. High Frequency Communications d. Stall Warning Systems e. Interphone f. Autopilot g. Yaw Damper h. Rudder Trim Actuator i. Rudder Ratio Changer j. Rudder and Elevator Shutoff Valves k. Rudder Position Indicator l. Stabilizer Trim Control System m. Flap/Stabilizer Position Module
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 13, 2015 767-53A0267 Revision 1: August 04, 2016 44 of 206 BOEING SERVICE BULLETIN 767-53A0267 ALERT ALERTn. Flight Recorder Systems o. APU Fire Detection System 18. Disassemble and remove and keep all seal components where wires penetrate the aft pressure bulkhead. Move all loose wires forward or aft, as necessary. 19. Disconnect and remove the APU Air Supply Duct. Refer to 767 AMM 36-11-01 as an accepted procedure. 20. Disconnect the APU fuel line at the aft pressure bulkhead as follows: a. In the aft end of the bulk cargo compartment, disconnect the shroud and APU fuel line at the aft pressure bulkhead fitting. Salvage all bolts, nuts, and washers. Refer to the task "Remove the APU Fuel Line and Shroud Between the Center Compartment of the Auxiliary Fuel Tank and the Pressure Bulkhead for the Aft Cargo Compartment" in 767 AMM 28-25-05 as an accepted procedure. b. Remove the APU fuel line between the aft pressure bulkhead the APU firewall. Refer to the task "Remove the APU Fuel Line and Shroud Between the Pressure Bulkhead for the Aft Cargo Compartment and the APU Firewall Bulkhead" in 767 AMM 28-25-05 as an accepted procedure. c. Remove and keep the APU fuel line bulkhead fitting in accordance with FIGURE 5. d. Install the APU fuel line bulkhead fitting on the new aft pressure bulkhead in accordance with FIGURE 6. 21. Remove the Dorsal Fin. Refer to 767 AMM 53-66-02 as an accepted procedure.

CAUTION:SLOWLY LIFT AND REMOVE LARGE STRUCTURAL COMPONENTS TO PREVENT DAMAGE TO THE AIRPLANE OR TO PERSONS. 22. Remove the Vertical Fin. A vertical fin removal procedure is shown in 767 ARD 2-60-2. (This procedure has similarities that can be used as a guideline): a. Install internal scaffolding PME148T0010PBR inside Section 48. b. Attach vertical fin lift fittings ME100T3480PBR to the vertical fin. c. Attach vertical fin lift sling 2OHME100T3480PBR to the vertical fin and apply 1,000 pounds upward prelift tension to the sling. d. Disconnect the fin-to-body link at the leading edge of the fin. Remove the 16 tension bolts and 156 lock bolts that attach the vertical fin to the aft body. Use torque tool 2MIT100T3480PBR as necessary when removing the tension bolts. Record the locations and quantity of all shims removed at the time of the fin removal. Store the service ready shims for reuse. Lift the vertical fin off the body. A vertical fin removal procedure is shown in 767 ARD 2-60-2 for airplane recovery purposes.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 13, 2015 767-53A0267 Revision 1: August 04, 2016 45 of 206 BOEING SERVICE BULLETIN 767-53A0267 ALERT ALERTe. Without a rotating fixture, the vertical fin must be stored in an upright position. Use fin stand ME170T0100PBR or create a tool to act as a base to support the vertical fin by attaching to the four corner tension bolt locations. The vertical fin should be stored indoors. NOTE:All H-11 hardware should have been replaced at fin to body joint per Boeing Service Bulletin 767-53A0085 and FAA AD 2003-10-11 by July 1, 2006. CAUTION:THE TRAP LOCKING DEVICES MUST BE REMOVED FROM THE HORIZONTAL STABILIZER PIVOTS ON BOTH THE LEFT AND RIGHT SIDES TO DO THE PIN ROTATION CHECK 23. Support the horizontal stabilizer with 767 SRM Horizontal Stabilizer supplementary supports in accordance with 767-200 SRM 51-50-02 and 767-300 SRM 51-50-02 Detail IV on the left and right sides. The four jacks should be loaded until the horizontal stabilizer pivot fittings begin to move vertically relative to the airplane Section 48 structure (767 AMM 55-17-51) and check that the outer pin can be rotated freely. NOTE:The sum of all four jacks loads should not exceed 5,000 pounds. The center of gravity of the Horizontal Stabilizer is aft of the pivot fitting pins. The jacks at the rear spar will support greater percentage of load than jacks at the front spar. The corresponding left side and right side jacks should be uniformly loaded. 24. Remove the horizontal stabilizer-to-body seals. Refer to 767 AMM 55-10-01 as an accepted procedure. 25. Remove the horizontal stabilizer-to-body blade seals. Refer to 767 AMM 55-10-02 as an accepted procedure. 26. Remove horizontal stabilizer fairing skin panels in accordance with FIGURE 23 and FIGURE 25.

CAUTION:INSUFFICIENT OR EXCESSIVE LIFT FORCE CAN RESULT IN STRUCTURAL DAMAGE AND A SAFETY HAZARD. 27. Do one of the options that follow: a. Option 1: REMOVAL OF ALL ELEVATORS (1) Remove all the elevators installed on the horizontal stabilizer. Refer to 767 AMM 27-31-01 and 767 AMM 27-31-02 as an accepted procedure. NOTE:If the elevators are not removed, it will require installation of forward lower tool fittings on the tail cone after it is removed and prior to storing the structure on the stand. (2) Remove the rudder-to-body seal. Refer to 767 AMM 55-36-02 as an accepted procedure. (3) Install lift fittings ME148T0600PBR-1/-2/-3/-4/-5 and sling ME148T0600PBR-12. (4) Break the fay seal between the tail cone and STA 1809.5 (5) Support the tail cone between STA 1809 and STA 1952 with lift fittings and sling ME148T0600PBR.
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 13, 2015 767-53A0267 Revision 1: August 04, 2016 46 of 206 BOEING SERVICE BULLETIN 767-53A0267 ALERT ALERTNOTE:The APU will remain in place. (6) Remove the fasteners that attach the tail cone to the STA 1809 bulkhead in accordance with FIGURE 7. (7) Slowly lift the tail cone aft and up to clear the upper STA 1809.5 bulkhead structure and airplane. NOTE:Make sure not to damage the STA 1809.5 bulkhead structure, HSTAB or airplane. (8) Locate and store the tail cone on stand 2ME148T0600PBR. b. Option 2: NON REMOVAL OF ELEVATORS (1) Remove the rudder-to-body seal. Refer to 767 AMM 55-36-02 as an accepted procedure. (2) Install lift fittings ME148T0600PBR-1/-2/-5 and sling ME148T0600PBR-12. NOTE:Do not install lift fittings ME148T0600PBR-3/-4 at this time. (3) Install protective foam pads between the tail cone and HSTAB/inboard elevators. (4) Break the fay seal between the tail cone and STA 1809.5. (5) Support the tail cone between STA 1809 and STA 1952 with lift fittings and sling ME148T0600PBR. The APU will remain in place. Remove the fasteners that attach the tail cone to the STA 1809 bulkhead in accordance with FIGURE 7. (6) Prepare the tail cone between and lift fittings ME148T0600PBR-3/-4 for installation. NOTE:Do not install the lift fittings at this time. The lift fittings will be installed after the tail cone is removed from the airplane and before storing on stand. (7) Slowly lift the tail cone vertically up to clear the lower section of STA 1809.5 bulkhead structure, HSTAB and elevators and slowly move aft to clear the upper section of STA 1809.5 bulkhead structure HSTAB and elevators. NOTE:Make sure not to damage the STA 1809.5 bulkhead structure, HSTAB, elevators or airplane. (8) Install lift fittings ME148T0600PBR-3/-4. (9) Locate and store the tail cone on stand 2ME148T0600PBR. 28. Attach horizontal stabilizer lift fittings ME182T0000PBR and lift sling OHME180T0100PBR to the horizontal stabilizer and make the sling cable assembly tight. 29. Disconnect the stabilizer trim ballscrew from the horizontal stabilizer center section. Refer to 767 AMM 27-41-10 as an accepted procedure.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 13, 2015 767-53A0267 Revision 1: August 04, 2016 47 of 206 BOEING SERVICE BULLETIN 767-53A0267 ALERT ALERT30. Do not remove the horizontal stabilizer pivot pins. Make sure the horizontal stabilizer sling cable assembly is still tight. With the horizontal stabilizer vertically balanced as described in Step 23 and Step 28, complete the disassembly of the STA 1809.5 bulkhead in accordance with FIGURE 8 to allow the horizontal stabilizer to be removed. The left and right STA 1809.5 center bulkhead assemblies will remain attached to the horizontal stabilizer at the pivot pins. Make sure there is no load on the hinge pins as the center of gravity is subject to change. NOTE:Secure the jackscrew in order to prevent it swinging whilst carrying out access, inspection, repair or replacement. CAUTION:THE LEFT AND RIGHT STA 1809.5 BULKHEAD OUTER CHORDS WILL NO LONGER BE CONNECTED TO THE SURROUNDING STRUCTURE AFTER COMPLETION OF THE FASTENER REMOVALS GIVEN IN FIGURES 7 AND 8. TO PREVENT DAMAGE TO THE OUTER CHORDS, USE CARE TO REMOVE THE OUTER CHORDS WHILE THE HORIZONTAL STABILIZER (WITH THE STA 1809.5 CENTER BULKHEAD ASSEMBLIES ATTACHED) IS REMOVED. 31. Use the horizontal stabilizer lift sling to vertically lift the horizontal stabilizer a small amount to unload the 767 SRM Horizontal Stabilizer supplementary supports, then remove the supplementary supports. Remove the left and right STA 1809.5 bulkhead outer chords, which are trapped between the STA 1809.5 center bulkhead assemblies and the forward part of section 48 that remains. Move the horizontal stabilizer aft until it is clear of the STA 1809.5 bulkhead. Set the horizontal stabilizer down on a storage fixture similar to ME180T0000PBR. 32. Make and install temporary STA 1809.5 bulkhead stabilizing tools in accordance with FIGURE 18.

CAUTION:INSUFFICIENT OR EXCESSIVE LIFT FORCE CAN RESULT IN STRUCTURAL DAMAGE AND A SAFETY HAZARD. LEAVING THE PME148T0010PBR INTERNAL SCAFFOLDING INSIDE THE FORWARD PART OF SECTION 48 DURING THE OVERHEAD REMOVAL PROCESS RESULTS IN A FORWARD SHIFT IN THE CENTER OF GRAVITY OF THE FORWARD PART OF SECTION 48 THAT MAY CAUSE SEPARATION DIFFICULTIES. 33. RC - Support the forward part of Section 48 (STA 1582 to STA 1809) with lift fittings and sling 3ME140T0140PBR and handling fittings ME148T0200PBR. Remove fasteners, clips, and fittings in accordance with FIGURE 9. Detach the STA 1582 floor beam in accordance with FIGURE 20. Remove the forward part of Section 48 (the aft pressure bulkhead will remain attached to the forward part of Section 48 at this time). Remove and store the forward part of Section 48 (which includes the aft pressure bulkhead) on stand 2ME148T0200PBR. WARNING:UNTIL THE STA 1582 FLOOR BEAM TEMPORARY SUPPORTS ARE INSTALLED, DO NOT PLACE EXCESSIVE WEIGHT ON THE MAIN DECK FLOOR STRUCTURE AFT OF STA 1562. THE MAIN DECK FLOOR AFT OF STA 1562 IS NOT SUPPORTED. DO THIS TO PREVENT INJURY TO PERSONNEL AND DAMAGE TO THE FLOOR STRUCTURE. WARNING:INSTALL APPROPRIATE SAFETY BARRICADES OR SIMILAR TO BLOCK THE END OF THE MAIN DECK FLOOR AFT OF STA 1582. DO THIS TO PREVENT INJURY TO PERSONNEL. 34. Install temporary supports for the STA 1582 floor beam in accordance with FIGURE 22. Prior to installation of the supports, make sure that the floor grid is level, and not deflected down or up.
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 13, 2015 767-53A0267 Revision 1: August 04, 2016 48 of 206 BOEING SERVICE BULLETIN 767-53A0267 ALERT ALERT35. RC - Attach removal strongback ME148T2610PBR and lifting fixture OHME148T2610PBR to the existing aft pressure bulkhead in the forward part of Section 48. Remove the rivets that attach the aft pressure bulkhead to the Section 48 pressure ring in accordance with FIGURE 10. Remove the old aft pressure bulkhead from the forward part of Section 48. NOTE:Some rivets will need to be removed just prior to installation of the strongback due to the rivet location being hidden under the strongback attach location. 36. RC - Attach lifting fixture OHME148T2610PBR to installation strongback 2ME148T2610PBR (this strongback is shipped already attached to the new aft pressure bulkhead) and lift the new bulkhead into position in the forward part of Section 48. Install fasteners to attach the new aft pressure bulkhead to the Section 48 (STA 1582) pressure ring in accordance with FIGURE 11. Remove the aft pressure bulkhead lifting fixture. 37. Install protective equipment PRE148T2610PBR on the new dome.

WARNING:WITH THE STA 1582 FLOOR BEAM TEMPORARY SUPPORTS REMOVED, DO NOT PLACE EXCESSIVE WEIGHT ON THE MAIN DECK FLOOR STRUCTURE AFT OF STA 1562. THE MAIN DECK FLOOR AFT OF STA 1562 IS NOT SUPPORTED. DO THIS TO PREVENT INJURY TO PERSONNEL AND DAMAGE TO THE FLOOR STRUCTURE. CAUTION:JUST PRIOR TO FINAL POSITIONING OF THE FORWARD PART OF SECTION 48, REMOVE THE STA 1582 FLOOR BEAM TEMPORARY SUPPORTS. DO THIS TO PREVENT DAMAGE TO THE NEW AFT PRESSURE BULKHEAD FROM THE FLOOR BEAM SUPPORT FASTENERS. 38. RC - Lift the forward part of Section 48 (STA 1582 to STA 1809, including the new aft pressure bulkhead) into position from the storage stand with lift fittings and sling 3ME140T0140PBR and handling fittings ME148T0200PBR. Install fasteners in accordance with FIGURE 12 to attach the new aft pressure bulkhead and the forward part of Section 48 to Section 46 at STA 1582. Attach the STA 1582 floorbeam in accordance with FIGURE 22. Remove the sling, handling fittings, and lift fittings. 39. Remove the temporary STA 1809.5 bulkhead stabilizing tools in accordance with FIGURE 20. 40. RC - Lift the horizontal stabilizer (with the left and right STA 1809.5 center bulkheads attached at the hinge pins) from the storage fixture and move it near its final position using the lift sling and lift fittings. Before moving the horizontal stabilizer into its final position, position the previously removed left and right STA 1809.5 bulkhead outer chords between the forward part of Section 48 and the STA 1809.5 center bulkhead assemblies. The final position is set by alignment of the left and right center bulkhead fastener patterns. 41. Support the horizontal stabilizer with 767 SRM Horizontal Stabilizer supplementary supports in accordance with 767-200 SRM 51-50-02 and 767-300 SRM 51-50-02 Detail IV on the left and right sides. The four jacks should be loaded until the supports have taken the load off the horizontal stabilizer lift sling. Do not yet remove the horizontal stabilizer lift sling or lift fittings. NOTE:The sum of all four jacks loads should not exceed 5,000 pounds. The center of gravity of the Horizontal Stabilizer is aft of the pivot fitting pins. The jacks at the rear spar will support greater percentage of load than jacks at the front spar. The corresponding left side and right side jacks should be uniformly loaded.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 13, 2015 767-53A0267 Revision 1: August 04, 2016 49 of 206 BOEING SERVICE BULLETIN 767-53A0267 ALERT ALERT42. RC - Attach the left and right STA 1809.5 center bulkheads in accordance with FIGURE 13 and FIGURE 14. Use care to prevent excessive loading of the stabilizer hinge joints. 43. Connect the stabilizer trim ballscrew to the horizontal stabilizer center section. Refer to 767 AMM 27-41-10 as an accepted procedure. 44. Remove the horizontal stabilizer lift sling and lift fittings. Reinstall the production fasteners at the lift fitting attach points. 45. Lift the tail cone into position with the sling and lift fittings. Install the fasteners in accordance with FIGURE 15, to attach the tail cone to the STA 1809 bulkhead. Remove the sling and lift fittings. NOTE:Accomplishment of Part 3 Step 41 (horizontal stabilizer support), Step 42 (align and attach STA 1809.5 center bulkheads), Step 43 (stabilizer trim ballscrew attachment), Step 44 (removal of lift sling and fittings), and Step 45 (attach tail cone) should return the horizontal stabilizer to the position initially given in Step 23. 46. The horizontal stabilizer is now supported by suitable means, with trap lock devices removed. Check that the right and left horizontal stabilizer pivot pins can be rotated freely with an applied torque of 400 in-lb or less. If necessary, remove and reinstall both the left and right pivot pins. Refer to 767 AMM 55-17-51 as an accepted procedure. 47. Install horizontal stabilizer fairing skin panels in accordance with FIGURE 24 and FIGURE 26. 48. Install the horizontal stabilizer-to-body seals. Refer to 767 AMM 55-10-01 as an accepted procedure. 49. Install the horizontal stabilizer-to-body blade seals. Refer to 767 AMM 55-10-02 as an accepted procedure. 50. Prepare the Vertical Fin in accordance with FIGURE 27. 51. Install the Vertical Fin in accordance with FIGURE 28. 52. Inspect the fin-to-body joints. If there is no sealant, apply sealant in accordance with Boeing Drawing 140T4800. Do not plug drain holes. 53. Finish the fastener heads, damaged paint, bare areas and all fillet seals in the interior of the fin in accordance with SOPM 20-41-02. 54. Apply corrosion inhibiting compound in the interior of the fin with BMS 3-23 in accordance with Boeing Drawing 140T6000. Refer to 767-200 SRM 51-20-01 and 767-300 SRM 51-20-01 for additional help. 55. Connect the fin-to-body link at the leading edge of the fin. 56. Remove the internal scaffolding PME148T0010PBR from inside Section 48. 57. Remove the vertical fin lift fittings and sling. 58. Finish all bare aluminum with chemical film treatment and two coats of BMS 10-11, Type I primer. Apply corrosion inhibiting compound to both the forward and aft sides of the aft pressure bulkhead. Refer to 767 AMM 51-24-09 as an accepted procedure.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 13, 2015 767-53A0267 Revision 1: August 04, 2016 50 of 206 BOEING SERVICE BULLETIN 767-53A0267 ALERT ALERT59. Install the Dorsal Fin. Refer to 767 AMM 53-66-02 as an accepted procedure. 60. Install the APU fuel line between the aft pressure bulkhead the APU firewall. Refer to the task "Install the APU Fuel Line and Shroud Between the Pressure Bulkhead for the Aft Cargo Compartment and the APU Firewall Bulkhead" in 767 AMM 28-25-05 as an accepted procedure. 61. In the aft end of the bulk cargo compartment, attach the APU fuel line and shroud to the aft pressure bulkhead fitting. Refer to the task "Install the APU Fuel Line and Shroud Between the Center Compartment of the Auxiliary Fuel Tank and the Pressure Bulkhead for the Aft Cargo Compartment" in 767 AMM 28-25-05 as an accepted procedure. 62. Install the APU Air Supply Duct. Refer to 767 AMM 36-11-01 as an accepted procedure. 63. Connect electrical systems, including: a. Lights b. APU Power c. High Frequency Communications d. Stall Warning Systems e. Interphone f. Autopilot g. Yaw Damper h. Rudder Trim Actuator i. Rudder Ratio Changer j. Rudder and Elevator Shutoff Valves k. Rudder Position Indicator l. Stabilizer Trim Control System m. Flap/Stabilizer Position Module n. Flight Recorder Systems o. APU Fire Detection System 64. Install salvaged pressure seals where wires penetrate the aft pressure bulkhead. 65. Connect the electrical connectors for the altitude pressure switches. Refer to 767 AMM 38-32-51 as an accepted procedure. 66. Install the hydraulic lines that were removed earlier that pass through the aft pressure bulkhead.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 13, 2015 767-53A0267 Revision 1: August 04, 2016 51 of 206 BOEING SERVICE BULLETIN 767-53A0267 ALERT ALERT67.Group 3: Install the auxiliary static system tubes that were removed earlier that pass through the aft pressure bulkhead. 68. Install pressure seals at the aft pressure bulkhead in accordance with FIGURE 16. 69. Install auxiliary pitot tubes and seals in accordance with FIGURE 17. 70. Reconnect the stabilizer trim (ST1A/ST1B/ ST2A/ST2B), elevator (E1A/E1B/E2A/E2B), and rudder (RA/RB) control cables. Refer to 767 AMM 20-10-03 as an accepted procedure. a. Connect the cable ends (coiled forward and aft of the aft pressure bulkhead) through the aft pressure bulkhead at the appropriate turnbuckle. b. Install new or salvaged air seals and fasteners where cables penetrate the aft pressure bulkhead. Refer to 767 AMM 20-10-04 as an accepted procedure. c. Remove cable clamps. 71. Adjust the Stabilizer Trim System. Refer to 767 AMM 27-41-00 as an accepted procedure. 72. Adjust the Elevator System. Refer to 767 AMM 27-31-00 as an accepted procedure. 73. Adjust the Rudder System. Refer to 767 AMM 27-21-00 as an accepted procedure. 74. Install equipment in the aft end of the bulk cargo compartment that was removed for access. This includes: a. Potable Water Tanks. Refer to 767 AMM 38-11-01 as an accepted procedure. b. Vacuum Lavatory Waste Tanks. Refer to 767 AMM 38-32-11 as an accepted procedure. c. Sidewall Insulation. Refer to 767 AMM 25-52-03 as an accepted procedure. d. Bulk Cargo Compartment Aft Lining. Refer to 767 AMM 25-55-01 as an accepted procedure. e. Bulk Cargo Compartment Sidewall Lining, for access to the pitot-static tubes on the left side from the aft pressure bulkhead to the bulk cargo door aft frame at STA 1461. Refer to 767 AMM 25-55-01 as an accepted procedure. 75. Install equipment in the aft part of the passenger compartment that was removed for access. This includes: a. Floor Panels. Refer to 767 AMM 53-01-01 as an accepted procedure. b. Doorway/Galley Floor Covering. Refer to 767 AMM 25-27-02 as an accepted procedure. c. Sidewall and Ceiling Insulation. Refer to 767 AMM 25-21-05 as an accepted procedure.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 13, 2015 767-53A0267 Revision 1: August 04, 2016 52 of 206 BOEING SERVICE BULLETIN 767-53A0267 ALERT ALERTd. Ceiling panels. Refer to 767 AMM 25-22-01, 767 AMM 25-22-02, and/or 767 AMM 25-22-10 as accepted procedures. e. Sidewall Panels. Refer to 767 AMM 25-21-01 as an accepted procedure. f. Aft Galley Complex A1, A4, or A1-A3. Refer to 767 AMM 25-31-04 as an accepted procedure. g. Lavatories. Refer to 767 AMM 25-41-04 as an accepted procedure. h. Partitions. Refer to 767 AMM 25-25-04 as an accepted procedure. i. Passenger seats. Refer to 767 AMM 25-25-01 as an accepted procedure. 76. Dejack the airplane. Service the nose and main landing gears and put them in serviceable condition.

PART 3: SYSTEM TESTS 1. Bleed the hydraulic system. Refer to 767 AMM 29-11-00 as an accepted procedure. Do a leak check of the hydraulic lines that were removed and reinstalled. Refer to 767 AMM 20-10-09 as an accepted procedure. 2. Do a leak test of the new pitot-static tubes. Refer to 767 AMM 34-11-01 as an accepted procedure. 3. Do a test of the Autopilot. Refer to the task "AFDS Operational Test" in 767 AMM 22-10-00 as an accepted procedure. 4. Do a test of the Yaw Damper System. Refer to the task "Operational Test - Yaw Damper System" in 767 AMM 22-21-00 an accepted procedure. 5. Test the left and right High Frequency Communications Systems. Refer to the task "Operational Test - HF Communication System" in 767 AMM 23-11-00 as an accepted procedure. 6. Do a test of the Interphone system. Refer to the task "Operational Test - Service Interphone System" in 767 AMM 23-41-00 as an accepted procedure. 7. Do a test of the Stick Nudger. Refer to steps 2.A., 2.B., 2.C., 2.D., 2.G., and 2.H. in the task "Operational Test - Stall Warning System" in 767 AMM 27-32-00 as an accepted procedure. 8. Test the Horizontal Stabilizer Trim Control System. Refer to the task "Operational Test" in 767 AMM 27-41-00 as an accepted procedure. 9. Test the Stabilizer Trim System. Refer to the "Manual-Mechanical Stabilizer Trim Control Operational Test", the "Lever Force Test" and the "Horizontal Stabilizer Trim Control System Operational Test" in 767 AMM 27-41-00 as an accepted procedure. 10. Test the Elevator System. Refer to the task "System Test - Elevator Controls" in 767 AMM 27-31-00 as an accepted procedure. It is acceptable to not perform the "Elevator Position Indication Test", the "Elevator Power Control Actuators Test", the "Elevator Feel System Test", the "Stick Nudger Test", and the "Elevator Autopilot Servo Rods Test" tasks within the Systems Test. 11. Do an operational test of the Elevator Control System. Refer to the task "Operational Test - Elevator Control System" in 767 AMM 27-31-00 as an accepted procedure.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 13, 2015 767-53A0267 Revision 1: August 04, 2016 53 of 206 BOEING SERVICE BULLETIN 767-53A0267 ALERT ALERT12. Test the Rudder System. Refer to the task "System Test - Rudder and Rudder Trim Control" in 767 AMM 27-21-00. It is acceptable to not perform the "Test Rudder Pedal Adjustment Mechanism Travel", the "Test Captain's Rudder Pedal Travel", the "Test First Officer's Pedal Travel", the "Test Single Hydraulic System and PCA", the "Test Rudder Ratio-Changer System", the "Test Rudder Ration Flight Deck Annunciation", the "Test the Left RRCM", the "Test the Right RRCM", and the "Rudder Trim Authority and Rate Test" tasks within the System Test. 13. Test the Rudder Trim Actuator. Refer to the task "Rudder Trim Actuator - Test" in 767 AMM 27-21-11 as an accepted procedure. 14. Test the Rudder Ratio Changer. Refer to the task "Rudder Ratio Changer Mechanism - Test" in 767 AMM 27-21-13 as an accepted procedure. 15. Test the Rudder and Elevator Shutoff Valves. Refer to the task "Rudder and Elevator Shutoff Valves - System Test" in 767 AMM 27-23-00 as an accepted procedure. 16. Test the Rudder Position Indicator. Refer to the task "Rudder Position Indication - Operational Test" in 767 AMM 27-28-00 as an accepted procedure. 17. Test the Position Indicating System. Refer to the task "Operational Test - Position Indicating System" in 767 AMM 27-48-00 as an accepted procedure. 18. Test the Flap/Stabilizer Position Module. Refer to the task "Test for the FSPM" in 767 AMM 27-58-01 as an accepted procedure. 19. Test the Takeoff Configuration Warning Card Module. Refer to steps 4.A., 4.B., 4.C., 4.I., and 4.J.in the task "Warning Electronics Unit (WEU) Card Module Test" in 767 AMM 31-51-04 as an accepted procedure. 20. Test the Flight Data Recorder. Refer to the task "Flight Data Recorder Operational Test" in 767 AMM 31-31-00 as an accepted procedure. 21. Test the service lights. Refer to the task "Service Lights - Operational Test" in 767 AMM 33-31-00 as an accepted procedure. 22. Test the logo lights. Refer to the task "Logo Lights - Operational Test" in 767 AMM 33-45-00 as an accepted procedure. 23. Test the altitude pressure switches. Refer to 767 AMM 38-32-51 as an accepted procedure. 24. Test the APU wiring in accordance with APPENDIX A. 25. Do a cabin pressure leakage test. Refer to 767 AMM 05-51-24 as an accepted procedure.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 13, 2015 767-53A0267 Revision 1: August 04, 2016 54 of 206 BOEING SERVICE BULLETIN 767-53A0267 ALERT ALERTFIGURE 1: AFT PRESSURE BULKHEAD ASSEMBLY PREPARATION (SHEET 1 OF 5) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 13, 2015 767-53A0267 Revision 1 August 04, 2016 55 of 206 BOEING SERVICE BULLETIN 767-53A0267 ALERT ALERTFIGURE 1: AFT PRESSURE BULKHEAD ASSEMBLY PREPARATION (SHEET 2 OF 5) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 13, 2015 767-53A0267 Revision 1 August 04, 2016 56 of 206 BOEING SERVICE BULLETIN 767-53A0267 ALERT ALERTThe step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY numbers shown below are the number of parts necessary for each new aft pressure bulkhead. More Data Qty Identification Name Task Step

- 4 - Fastener Remove 1 1.19 - 1.21 inch diameter, normal tothe bulkhead surface. 125 microinchor better surface finish. 4 - Hole Drill / Ream

Break sharp edges and apply chemical film treatment and two coats of BMS10- 11, Type I primer to the bare edges of the holes. - - Finish Apply

- - 148T2629-2 SEAL BLOCK ASSY Locate 2

- 21 - Rivet Hole Drill / Ream

FIGURE 1: AFT PRESSURE BULKHEAD ASSEMBLY PREPARATION (SHEET 3 OF 5) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 13, 2015 767-53A0267 Revision 1 August 04, 2016 57 of 206 BOEING SERVICE BULLETIN 767-53A0267 ALERT ALERTMore Data Qty Identification Name Task Step Apply a pressure faying surface seal to the entire mating surface of the seal block assembly. - BMS 5-95 Sealant Apply 3

- 1 148T2629-2 SEAL BLOCK ASSY Install (New)

- 21 BACR15BB5A7C RIVET, UNIVERSAL HD Install (New)

- 4 - Fastener Remove 4

- - 140T0345-3 SEAL BLOCK ASSY Locate

- 22 - Rivet Hole Drill / Ream Apply a pressure faying surface seal to the entire mating surface of the seal block assembly. - BMS 5-95 Sealant Apply 5

- 1 140T0345-3 SEAL BLOCK ASSY Install (New)

- 18 BACR15BB5A7C RIVET, UNIVERSAL HD Install (New) 6

- 4 BACR15BB5A7C RIVET, UNIVERSAL HD Install (New) 7 Optional, if oversize rivets are necessary. 4 BACR15BB6A8C RIVET, UNIVERSAL HD Install (New) Apply a pressure faying surface seal to the entire matingsurface of the coverplate and pressure pan. - BMS 5-95 Sealant Apply 8

- 1 140T0345-1 COVER PLATE Install (New)

- 14 BACS12HN3-7 BOLT Install (New) 9 Under screw head. 14 NAS1149D0332J WASHER Install (New) Under nut. 14 NAS1149D0332J WASHER Install (New)

- 14 BACN11AG3 NUT, SELF-LOCK Install (New) Fillet seal all screw heads, nuts, and washers. - BMS 5-95 Sealant Apply 10 The parts shown in the table below are provided as extra parts for this figure. FIGURE 1: AFT PRESSURE BULKHEAD ASSEMBLY PREPARATION (SHEET 4 OF 5) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 13, 2015 767-53A0267 Revision 1 August 04, 2016 58 of 206 BOEING SERVICE BULLETIN 767-53A0267 ALERT ALERTMore Data Qty Identification Name 16 BACB30NM4K14 BOLT, HEX HEAD 1 BACN11AG3 NUT, SELF-LOCK 7 BACR15BB5A7C RIVET, UNIVERSAL HD 1 BACR15BB6A8C RIVET, UNIVERSAL HD 8 BACR15FT6KE7C RIVET 1 BACS12HN3-7 BOLT 2 NAS1149D0332J WASHER 5 NAS1149D0363J WASHER, FLAT 1 NAS42DD3-44FC SPACERS FOR RIV- ETS 1 NAS42DD3-48FC SPACERS FOR RIV- ETS 1 NAS42DD3-64FC SPACERS FOR RIV- ETS

FIGURE 1: AFT PRESSURE BULKHEAD ASSEMBLY PREPARATION (SHEET 5 OF 5) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 13, 2015 767-53A0267 Revision 1 August 04, 2016 59 of 206 BOEING SERVICE BULLETIN 767-53A0267 ALERT ALERTFIGURE 2: AFT PRESSURE BULKHEAD ASSEMBLY PREPARATION (SHEET 1 OF 2) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 13, 2015 767-53A0267 Revision 1 August 04, 2016 60 of 206 BOEING SERVICE BULLETIN 767-53A0267 ALERT ALERTThe step numbers shown below agree with the numbers shown in the circle symbols in the figure. More Data Qty Identification Name Task Step 0.530 - 0.539 inch diameter, normal tothe doubler. 125 microinch or better surface finish. 1 - Hole Drill / Ream 1
Break sharp edges and apply chemical film treatment and two coats of BMS 10-11, Type I primer to the bare edges of the holes. - - Finish Apply

FIGURE 2: AFT PRESSURE BULKHEAD ASSEMBLY PREPARATION (SHEET 2 OF 2) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 13, 2015 767-53A0267 Revision 1 August 04, 2016 61 of 206 BOEING SERVICE BULLETIN 767-53A0267 ALERT ALERTFIGURE 3: REMOVAL OF AUXILIARY PITOT SYSTEM TUBES AND SEALS (SHEET 1 OF 4) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 13, 2015 767-53A0267 Revision 1 August 04, 2016 62 of 206 BOEING SERVICE BULLETIN 767-53A0267 ALERT ALERTFIGURE 3: REMOVAL OF AUXILIARY PITOT SYSTEM TUBES AND SEALS (SHEET 2 OF 4) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 13, 2015 767-53A0267 Revision 1 August 04, 2016 63 of 206 BOEING SERVICE BULLETIN 767-53A0267 ALERT ALERTFIGURE 3: REMOVAL OF AUXILIARY PITOT SYSTEM TUBES AND SEALS (SHEET 3 OF 4) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 13, 2015 767-53A0267 Revision 1 August 04, 2016 64 of 206 BOEING SERVICE BULLETIN 767-53A0267 ALERT ALERTThe step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY numbers shown below are the number of parts necessary for each airplane. More Data Qty Identification Name Task Step From pressure dome seal retainer plates. 4 - Screw Remove 1 At approximately STA 1480 and aft of STA 1605. Cap open ends of tubes. Refer to 767 AMM20-10-09 as an accepted procedure. - 233T9110-513 Tube Assy Disconnect 2

At approximately STA 1502 and aft of STA 1605. Cap open ends of tubes. Refer to 767 AMM20-10-09 as an accepted procedure. - 233T9110-614 Tube Assy Disconnect 3

(a) 1 233T9110-513 Tube Assy Remove 4 (a) 1 233T9110-614 Tube Assy Remove

- 1 233T9113-1 Retainer Plate Remove

- 1 233T9113-2 Retainer Plate Remove

- 2 69B41314-1 Seal Remove (a) Disconnect tube assy from existing clamps, but keep existing clamp hardware for tube reinstallation.

FIGURE 3: REMOVAL OF AUXILIARY PITOT SYSTEM TUBES AND SEALS (SHEET 4 OF 4) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 13, 2015 767-53A0267 Revision 1 August 04, 2016 65 of 206 BOEING SERVICE BULLETIN 767-53A0267 ALERT ALERTFIGURE 4: REMOVAL OF PRESSURE SEALS (SHEET 1 OF 3) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 13, 2015 767-53A0267 Revision 1 August 04, 2016 66 of 206 BOEING SERVICE BULLETIN 767-53A0267 ALERT ALERTFIGURE 4: REMOVAL OF PRESSURE SEALS (SHEET 2 OF 3) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 13, 2015 767-53A0267 Revision 1 August 04, 2016 67 of 206 BOEING SERVICE BULLETIN 767-53A0267 ALERT ALERTThe step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY numbers shown below are the number of parts necessary for each airplane. More Data Qty Identification Name Task Step

- 6 - Screw Remove 1

- 6 - Washer Remove

- 16 - Screw Remove 2

- 16 - Nut Remove

- 16 - Washer Remove

- 1 - Retainer Remove 3

- 3 - Pressure Seal Remove 4

- 1 - Pressure Seal Remove 5

- 1 - Retainer Remove 6

FIGURE 4: REMOVAL OF PRESSURE SEALS (SHEET 3 OF 3) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 13, 2015 767-53A0267 Revision 1 August 04, 2016 68 of 206 BOEING SERVICE BULLETIN 767-53A0267 ALERT ALERTFIGURE 5: APU FUEL LINE BULKHEAD FITTING REMOVAL (SHEET 1 OF 3) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 13, 2015 767-53A0267 Revision 1 August 04, 2016 69 of 206 BOEING SERVICE BULLETIN 767-53A0267 ALERT ALERTFIGURE 5: APU FUEL LINE BULKHEAD FITTING REMOVAL (SHEET 2 OF 3) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 13, 2015 767-53A0267 Revision 1 August 04, 2016 70 of 206 BOEING SERVICE BULLETIN 767-53A0267 ALERT ALERTThe step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY numbers shown below are the number of parts necessary for each airplane. More Data Qty Identification Name Task Step

- 8 - Bolt Remove 1

- 8 - Washer Remove

- 1 60B92409-13 Bulkhead Fitting Remove 2

- 1 - Seal Remove 3

FIGURE 5: APU FUEL LINE BULKHEAD FITTING REMOVAL (SHEET 3 OF 3) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 13, 2015 767-53A0267 Revision 1 August 04, 2016 71 of 206 BOEING SERVICE BULLETIN 767-53A0267 ALERT ALERTFIGURE 6: APU FUEL LINE BULKHEAD FITTING INSTALLATION (SHEET 1 OF 3) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 13, 2015 767-53A0267 Revision 1 August 04, 2016 72 of 206 BOEING SERVICE BULLETIN 767-53A0267 ALERT ALERTThe step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY numbers shown below are the number of parts necessary for each airplane.
FIGURE 6: APU FUEL LINE BULKHEAD FITTING INSTALLATION (SHEET 2 OF 3) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 13, 2015 767-53A0267 Revision 1 August 04, 2016 73 of 206 BOEING SERVICE BULLETIN 767-53A0267 ALERT ALERTMore Data Qty Identification Name Task Step

- 1 40345 (678782 option- al) SEAL Install (New) 1

- 1 60B92409-13 Bulkhead Fitting Install (Kept) 2

- 8 BACB30NM4K4 Bolt Install (New) 3

- 8 NAS1149D0316J WASHER Install (New)

FIGURE 6: APU FUEL LINE BULKHEAD FITTING INSTALLATION (SHEET 3 OF 3) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 13, 2015 767-53A0267 Revision 1 August 04, 2016 74 of 206 BOEING SERVICE BULLETIN 767-53A0267 ALERT ALERTFIGURE 7: AFT SECTION 48 (TAIL CONE) FASTENER REMOVAL (SHEET 1 OF 3) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 13, 2015 767-53A0267 Revision 1 August 04, 2016 75 of 206 BOEING SERVICE BULLETIN 767-53A0267 ALERT ALERTThe step numbers shown below agree with the numbers as applicable shown in the circle symbols in the figure or related drawing sheet(s) shown in the figure. The QTY numbers shown below are the number of parts necessary for each airplane. REQUIREMENTS: 1. Some of the fastener locations identified in this figure may have been changed from the original delivered configuration during the inspection, repair, or modification given in Boeing Service Bulletin 767-53A0078, "Fuselage - Section 48 - Body station 1809.5 Bulkhead Outer Chord Inspection, Repair, and Modification." An Alternative Method of Compliance (AMOC) to the requirements of the applicable Airworthiness Directive may have been granted for configurations different than those shown in Boeing Service Bulletin 767-53A0078. These fastener locations must be maintained to the requirements of AD 2005-11-02 or to an approved AMOC to that AD. When fasteners are removed from these locations, document the fastener/nut/collar diameter, grip and type removed and the existing fastener hole diameter. Use care to not damage the fastener hole when removing fasteners. Do not clean the bores of these fastener holes with brass bottle brushed. Do an open-hole High Frequency Eddy Current (HFEC) inspection at all parts in the stack-up at these locations. Verify that there are no surface defects (such as rifling, gouging, nicks, burrs, or excessive surface roughness) in the bores of these fastener holes, other than that normally produced during a typical reaming operation. If any defect is found, contact The Boeing Company for repair instructions and do the repair. Verify that washers or fillet relief exists to accommodate the fasteners head-to-shank fillet radius. When fasteners are installed, use the same type and size fasteners that were removed earlier. 2. Some of the fastener locations identified in this figure may have been changed from the original delivered configuration during the inspection, repair, or modification given in Boeing Service Bulletin 767-53A0131, "Fuselage - Section 48 - Main Frame and Skins - STA 1809.5 Bulkhead - Forward Outer Chord, Horizontal and Vertical Inner Chord, and External Skin - Inspection." An Alternative Method of Compliance (AMOC) to the requirements of the applicable Airworthiness Directive may have been granted for configurations different than those shown in Boeing Service Bulletin 767-53A0131. These fastener locations must be maintained to the requirements of FAA AD 2011-14-02 or to an approved AMOC to that AD. When fasteners are removed from these locations, document the fasteners/nut/collar diameter, grip and type removed and the existing fastener hole diameter. Use care to not damage the fastener hole when removing fasteners. Do not clean the bored of these fastener holes with brass bottle brushes. Do an open-hole High Frequency Eddy Current (HFEC) inspection at all parts in the stack-up at these locations. Verify that there are no surface defects (such as rifling, gouging, nicks, burrs, or excessive surface roughness) in the bores of these fastener holes, other than that normally produced during a typical reaming operation. If any defect is found, contact The Boeing Company for repair instructions and do the repair. Verify that washers or fillet relief exists to accommodate the fasteners head-to-shank fillet radius. When fasteners are installed, use the same type and size fasteners that were removed earlier. However, Boeing recommends that H-11 steel bolts be replaced with Inconel bolts. Refer to Boeing Service Letter 767-SL-51-008-B. More Data Qty Identification Name Task Step

- 288 - Fastener Remove 1 (a) - - Shim Remove (a) Remove and keep any shims or fillers that are found common to the affected fastener locations. Note shim or filler locations before removal to ensure they are reinstalled in the proper locations. FIGURE 7: AFT SECTION 48 (TAIL CONE) FASTENER REMOVAL (SHEET 2 OF 3) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 13, 2015 767-53A0267 Revision 1 August 04, 2016 76 of 206 BOEING SERVICE BULLETIN 767-53A0267 ALERT ALERTThe flag note numbers shown below agree with the numbers shown in the flag symbols in this figure or the related drawing sheet. MORE DATA FLAG NOTE NUMBERThese fastener locations are also affected by Boeing Service Bulletin 767-53A0078. 1 These fastener locations are also affected by Boeing Service Bulletin 767-53A0131. 2 Note the shim size removed, and keep if correctly fitted and free of damage. 3

FIGURE 7: AFT SECTION 48 (TAIL CONE) FASTENER REMOVAL (SHEET 3 OF 3) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 13, 2015 767-53A0267 Revision 1 August 04, 2016 77 of 206 BOEING SERVICE BULLETIN 767-53A0267 ALERT ALERTFIGURE 8: STA 1809.5 CENTER BULKHEAD REMOVAL (SHEET 1 OF 7) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 13, 2015 767-53A0267 Revision 1 August 04, 2016 78 of 206 BOEING SERVICE BULLETIN 767-53A0267 ALERT ALERTFIGURE 8: STA 1809.5 CENTER BULKHEAD REMOVAL (SHEET 2 OF 7) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 13, 2015 767-53A0267 Revision 1 August 04, 2016 79 of 206 BOEING SERVICE BULLETIN 767-53A0267 ALERT ALERTFIGURE 8: STA 1809.5 CENTER BULKHEAD REMOVAL (SHEET 3 OF 7) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 13, 2015 767-53A0267 Revision 1 August 04, 2016 80 of 206 BOEING SERVICE BULLETIN 767-53A0267 ALERT ALERTFIGURE 8: STA 1809.5 CENTER BULKHEAD REMOVAL (SHEET 4 OF 7) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 13, 2015 767-53A0267 Revision 1 August 04, 2016 81 of 206 BOEING SERVICE BULLETIN 767-53A0267 ALERT ALERTFIGURE 8: STA 1809.5 CENTER BULKHEAD REMOVAL (SHEET 5 OF 7) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 13, 2015 767-53A0267 Revision 1 August 04, 2016 82 of 206 BOEING SERVICE BULLETIN 767-53A0267 ALERT ALERTThe step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY numbers shown below are the number of parts necessary for each airplane. REQUIREMENTS: 1. Some of the fastener locations identified in this figure may have been changed from the original delivered configuration during the inspection, repair, or modification given in Boeing Service Bulletin 767-53A0078, "Fuselage - Section 48 - Body Station 1809.5 Bulkhead Outer Chord Inspection, Repair, and Modification." An Alternative Method of Compliance (AMOC) to the requirements of the applicable Airworthiness Directive may have been granted for configurations different than those shown in 767-53A0078. These fastener locations must be maintained to the requirements of FAA AD 2005-11-02 or to an approved AMOC to that AD. When fasteners are removed from the locations, document the fastener/nut/collar diameter, grip and type removed and the existing fastener hole diameter. Use care to not damage the fastener hole when removing fastener hole when removing fasteners. Do not clean the bores of these fastener holes with brass bottle brushed. Do an open-hole High Frequency Eddy Current (HFEC) inspection at all parts in the stack-up at these locations. Verify that there are no surface defects (such as rifling, gouging, nicks, burrs, or excessive surface roughness) in the bores of these fastener holes, other than that normally produced during a typical reaming operation. If any defect is found, contact The Boeing Company for repair instructions and do the repair. Verify that washers or fillet relief exists to accommodate the fasteners head-to-shank fillet radius. When fasteners are installed, use the same type and size fasteners that were removed earlier. 2. Some of the fastener locations identified in this figure may have been changed from the original delivered configuration during the inspection, repair, or modification given in Boeing Service Bulletin 767-53A0131, "Fuselage - Section 48 - Main Frame and Skins - STA 1809.5 Bulkhead - Forward Outer Chord, Horizontal and Vertical Inner Chord, and External Skin - Inspection." An Alternative Method of Compliance (AMOC) to the requirements of the applicable Airworthiness Directive may have been granted for configurations different that those shown in 767-53A0131. These fastener locations must be maintained the requirements of FAA AD 2011-14-02 or to an approved AMOC to that AD. When fasteners are removed from these locations, document the fastener/nut/collar diameter, grip and type removed and the existing fastener hole diameter. Use care to not damage the fastener hole when removing fasteners. Do not clean the bores of these fastener holes with brass bottle brushes. Do an open-hole High Frequency Eddy Current (HFEC) inspection at all parts in the stack-up at these locations. Verify that there are no surface defects (such as rifling, gouging, nicks, burrs, or excessive surface roughness) in the bores of these fastener holes, other than that normally produced during a typical reaming operation. If any defect is found, contact The Boeing Company for repair instructions and do the repair. Verify that washers or fillet relief exists to accommodate the fasteners head-to-shank fillet radius. When fasteners are installed, use the same type and size fasteners that were removed earlier. However, Boeing recommends that H-11 steel bolts be replaced with Inconel bolts. Refer to Boeing Service Letter 767-SL-51-008-B More Data Qty Identification Name Task Step

- 428 - Fastener Remove 1 If installed 8 - Filler Remove / Keep 2

- 12 - Filler Remove 3

- 4 - Splice Strap Remove 4
FIGURE 8: STA 1809.5 CENTER BULKHEAD REMOVAL (SHEET 6 OF 7) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 13, 2015 767-53A0267 Revision 1 August 04, 2016 83 of 206 BOEING SERVICE BULLETIN 767-53A0267 ALERT ALERTMore Data Qty Identification Name Task Step

- 12 - Shim Remove 5 The horizontal stabilizer pivot fittings will remain attached to the center bulkhead assy. 2 - Center Bulkhead Assy Remove / Keep 6

The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure. MORE DATA FLAG NOTE NUMBERThese fastener locations are also affected by Boeing Service Bulletin 767-53A0078. 1 These fastener locations are also affected by Boeing Service Bulletin 767-53A0131. 2

FIGURE 8: STA 1809.5 CENTER BULKHEAD REMOVAL (SHEET 7 OF 7) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 13, 2015 767-53A0267 Revision 1 August 04, 2016 84 of 206 BOEING SERVICE BULLETIN 767-53A0267 ALERT ALERTFIGURE 9: FORWARD SECTION 48 PARTS REMOVAL (SHEET 1 OF 2) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 13, 2015 767-53A0267 Revision 1 August 04, 2016 85 of 206 BOEING SERVICE BULLETIN 767-53A0267 ALERT ALERTThe step numbers shown below agree with the numbers as applicable shown in the circle symbols in the figure or related drawing sheet(s) shown in the figure. The QTY numbers shown below are the number of parts necessary for each airplane. CAUTION:TO PREVENT DAMAGE, PRIOR TO REMOVAL OF THE FORWARD PART OF SECTION 48 MAKE SURE THAT THE STA 1582 FLOOR BEAM HAS BEEN DETACHED IN ACCORDANCE WITH FIGURE 21. AFTER THE FLOOR BEAM HAS BEEN DETACHED, THE EXISTING FLOOR STRUCTURE MUST BE SUPPORTED. REFER TO FIGURE 22 AS AN ACCEPTED PROCEDURE. More Data Qty Identification Name Task Step

- 308 - Nut Remove 1

- 308 - Bolt Remove

- 616 - Washer Remove

- 18 - Fastener Remove 2 Waste tank tie rod attach fittings 2 - Fitting Remove Ceiling support fittings 3 - Fitting Remove 3

- 6 - Fastener Remove 4

- 2 - Clip Remove

- 2 - Shim Remove

FIGURE 9: FORWARD SECTION 48 PARTS REMOVAL (SHEET 2 OF 2) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 13, 2015 767-53A0267 Revision 1 August 04, 2016 86 of 206 BOEING SERVICE BULLETIN 767-53A0267 ALERT ALERTFIGURE 10: AFT PRESSURE BULKHEAD PRESSURE RING FASTENER REMOVAL (SHEET 1 OF 2) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 13, 2015 767-53A0267 Revision 1 August 04, 2016 87 of 206 BOEING SERVICE BULLETIN 767-53A0267 ALERT ALERTThe step numbers shown below agree with the numbers as applicable shown in the circle symbols in the figure or related drawing sheet(s) shown in the figure. The QTY numbers shown below are the number of parts necessary for each airplane. More Data Qty Identification Name Task Step

- 31 - Blind Rivet Remove 1

- 1 - Pressure Bulkhead Remove

FIGURE 10: AFT PRESSURE BULKHEAD PRESSURE RING FASTENER REMOVAL (SHEET 2 OF 2) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 13, 2015 767-53A0267 Revision 1 August 04, 2016 88 of 206 BOEING SERVICE BULLETIN 767-53A0267 ALERT ALERTFIGURE 11: AFT PRESSURE BULKHEAD ATTACHMENT TO THE PRESSURE RING AT STA 1582 (SHEET 1 OF 2) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 13, 2015 767-53A0267 Revision 1 August 04, 2016 89 of 206 BOEING SERVICE BULLETIN 767-53A0267 ALERT ALERTThe step numbers shown below agree with the numbers as applicable shown in the circle symbols in the figure or related drawing sheet(s) shown in the figure. The QTY numbers shown below are the number of parts necessary for each airplane. NOTE:In order to align the new aft pressure bulkhead with the STA 1582 pressure ring, Boeing recommends that a series of fastener holes around the circumference of the joint (for example, bolt location numbers 16, 31, 41, 51, 76, 89, 114, 129, and 147 left and right) be selected as indexing points. At these indexing points, use locating pins such as those shown in Appendix B to assist in aligning the joint. Install temporary bushings in the full size holes in the Section 48 pressure ring. More Data Qty Identification Name Task Step

- 1 691T0103-1 Aft Bulkhead Assembly Install (New) 1

- 31 - Fastener Hole Drill / Ream

- 31 NAS1399D6A10(NAS1399D6AB10 optional) RIVET, BLIND Install (New) (a) Apply BMS 5-95 faying surface sealant to all mating surfaces of the aft pressure bulkhead failsafe chord and the pressure ring. Ensure that all fasteners listed in this figure and in Figure 12 are installed before the maximum squeeze-out life of the sealant has been reached.

FIGURE 11: AFT PRESSURE BULKHEAD ATTACHMENT TO THE PRESSURE RING AT STA 1582 (SHEET 2 OF 2) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 13, 2015 767-53A0267 Revision 1 August 04, 2016 90 of 206 BOEING SERVICE BULLETIN 767-53A0267 ALERT ALERTFIGURE 12: FORWARD SECTION 48 INSTALLATION (SHEET 1 OF 19) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 13, 2015 767-53A0267 Revision 1 August 04, 2016 91 of 206 BOEING SERVICE BULLETIN 767-53A0267 ALERT ALERTThe step numbers shown below agree with the numbers as applicable shown in the circle symbols in the figure or related drawing sheet(s) shown in the figure. The QTY numbers shown below are the number of parts necessary for each airplane. The notes below assume that the intermediate fastener holes (the fastener holes between the stringer locations) will be drilled and reamed to their final hole sizes after the forward Section 48 has been positioned against the STA 1582 frame segments. As an alternative, before the forward Section 48 is positioned, install temporary fasteners at the stringer fastener locations to ensure that the aft pressure bulkhead and pressure ring are adequately clamped together. Use pull reamers to make the intermediate fastener holes the size specified in this figure using the Section 48 pressure ring as a template and guide. Feed the reamers from the aft side of the bulkhead and attach it to a drill motor on the forward side of the bulkhead. Ensure that adequate clamping force exists to make sure that chips or burrs do not break out between the parts. The rivets that attach the aft pressure bulkhead to Section 48 do not alone provide adequate clamping force to ensure that chips and burrs do not form between the parts. NOTE: 1. In the new aft pressure bulkhead, all of the intermediate fastener holes (the fastener holes between stringer end fitting locations) are 1/16 inch diameter undersize. 2. Apply BMS 5-95 faying surface sealant to all mating surfaces of the aft pressure bulkhead pressure chord and the STA 1582 frame segment. 3. In order to align the forward part of Section 48 (with the new aft pressure bulkhead installed) with the STA 1582 forward chord, Boeing recommends that a series of fastener holes around the circumference of the joint (for example, bolt location numbers 16, 31, 41, 51, 76, 89, 114,129, and 147 left and right) be selected as indexing points. At these indexing points, use locating pins such as those shown in Appendix B to assist in aligning the joint. Install temporary bushings in undersize holes, if necessary. 4. Fasteners at stringer locations should be installed wet with BMS 5-95 sealant. Sealant should be applied under the bolt head, in the hole, under the nut, and on the bolt threads. Sealant squeeze out to be continuous from above the base of the fastener head and nut, covering the washer to the structure. Sealant squeeze out can be supplemented with the application of a brush coat of BMS 5-95 sealant. 5. Apply the initial pull up torque to the fasteners at stringer locations. Torque values and application sequence are shown in Table 13. 6. Clamp the new aft pressure bulkhead to Section 48 at the stringer bolt locations. After the aft pressure bulkhead is clamped into position, the intermediate fastener locations (the fasteners between the stringer locations) in the new aft pressure bulkhead pressure chord and failsafe chord must be drilled and reamed to the specified final hole size through the holes that exist in the STA 1582 forward chord and the Section 48 pressure ring. 7. Fasteners between stringer locations should be installed wet with BMS 5-95 sealant. Sealant should be applied under the bolt head and under the nut. Sealant squeeze out to be continuous from above the base of the fastener head and nut, covering the washer to the structure. Sealant squeeze out can be supplemented with the application of a brush coat of BMS 5-95 sealant.

FIGURE 12: FORWARD SECTION 48 INSTALLATION (SHEET 2 OF 19) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 13, 2015 767-53A0267 Revision 1 August 04, 2016 92 of 206 BOEING SERVICE BULLETIN 767-53A0267 ALERT ALERT8. For sealants with squeeze-out life longer than 48 hours, reapply torque values as given in note (a) and Table 14, except start to do the torque reapplication not sooner than 60 minutes after the initial torque application as given in note (b) and Table 13 to bolt numbers 153 and 154 left and right (S-39L and S-39R). For initial torque application (note (b) and Table 13) and torque reapplication (note (a) and Table 14), maintain the sequences given in notes (a) and (b), Table 13, and Table 14, and ensure that torque is reapplied to each bolt not sooner than 60 minutes after the initial application of torque to that bolt. 9. After installation of the Section 48 forward section, fill the gap between Section 46 and Section 48 at STA 1582 with BMS 5-95 sealant. Also apply BMS 5-125 Type II levelling compound as necessary forward of any lower Section 48 drains to ensure free flow of water. More Data Qty Identification Name Task Step

- 1 140T0142U1 (140T0142-1 optional) CLIP Install (New) 1

- 1 140T0142U2 (140T0142-2 optional) CLIP Install (New) 2

- 2 140T0169-7 FITTING ASSY Install (New) 3 Maximum gap 0.010 inch. Remove 0.003 inch laminations as required. Install shims with BMS 10-11, Type I primer after delamination. 2 BACS40R011B012F SHIM, LAMINATED Install (New)

- 2 412T3106-406 FITTING ASSY Install (New) 4

- 1 412T3106-408 fitting assy Install (New) 5

FIGURE 12: FORWARD SECTION 48 INSTALLATION (SHEET 3 OF 19) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 13, 2015 767-53A0267 Revision 1 August 04, 2016 93 of 206 BOEING SERVICE BULLETIN 767-53A0267 ALERT ALERTMore Data Qty Identification Name Task Step Refer to Tables 1 -12 for specific locations (a) 23 BACB30US5K16 BOLT, 12 PT HEAD Install (New) 6 Refer to Tables 1 -12 for specific locations (a) 56 BACB30US5K17 BOLT, 12 PT HEAD Install (New) Refer to Tables 1 -12 for specific locations (a) 39 BACB30US5K18 BOLT, 12 PT HEAD Install (New) Refer to Tables 1 -12 for specific locations (a) 24 BACB30US5K19 BOLT, 12 PT HEAD Install (New) Refer to Tables 1 -12 for specific locations (a) 10 BACB30US5K21 BOLT, 12 PT HEAD Install (New) Refer to Tables 1 -12 for specific locations (a) 2 BACB30US5K25 BOLT, 12 PT HEAD Install (New) under bolt head 154 BACW10BP5CD CSK WASHER Install (New) under nut 154 BACW10BP5DP WASHER-PLAIN Install (New)

- 154 BACN10HR5CD NUT Install (New) Refer to Tables 1 -12 for specific locations (a) (b) 4 BACB30US6K31 BOLT, 12 PT HEAD Install (New) 7 Refer to Tables 1 -12 for specific locations (a) (b) 40 BACB30US6K33 BOLT, 12 PT HEAD Install (New) Refer to Tables 1 -12 for specific locations (a) (b) 32 BACB30US6K34 BOLT, 12 PT HEAD Install (New) Refer to Tables 1 -12 for specific locations (a) (b) 8 BACB30US6K35 BOLT, 12 PT HEAD Install (New) Refer to Tables 1 -12 for specific locations (a) (b) 8 BACB30US6K36 BOLT, 12 PT HEAD Install (New) under bolt head 92 BACW10BP6CD WASHER, PLAIN Install (New) under nut 92 BACW10BP6DP WASHER Install (New)

- 92 BACN10HR6CD SELF-LOCKING NUT Install (New)
FIGURE 12: FORWARD SECTION 48 INSTALLATION (SHEET 4 OF 19) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 13, 2015 767-53A0267 Revision 1 August 04, 2016 94 of 206 BOEING SERVICE BULLETIN 767-53A0267 ALERT ALERTMore Data Qty Identification Name Task Step Refer to Tables 1 -12 for specific locations (a) (b) 16 BACB30US7K35 BOLT, 12 PT HEAD Install (New) 8 Refer to Tables 1 -12 for specific locations (a) (b) 12 BACB30US7K39 BOLT, 12 PT HEAD Install (New) Refer to Tables 1 -12 for specific locations (a) (b) 16 BACB30US7K40 BOLT, 12 PT HEAD Install (New) under bolt head 44 BACW10BP7CD WASHER Install (New) under nut 44 BACW10BP7DP WASHER Install (New)

- 44 BACN10HR7CD NUT Install (New) Refer to Tables 1 -12 for specific locations (a) (b) 16 BACB30US8K42 BOLT, 12 PT HEAD Install (New) 9 under bolt head 16 BACW10BP8CD WASHER Install (New) under nut 16 BACW10BP8DP WASHER Install (New)

- 16 BACN10HR8CD NUT Install (New) Bolt numbers 046L and 046R (a) 2 BACB30US5K25 BOLT, 12 PT HEAD Install (New) 10 under bolt head 2 140T0140-5 WASHER Install (New) under nut 2 BACW10BP5CD CSK WASHER Install (New)

- 2 BACN10HR5CD NUT Install (New) (a) After the initial pull-up sequence of steps has been completed, apply the final torque values given in Table 14 to these fasteners in the sequence that follows: Begin with bolt numbers 155 L and 155 R, and apply the appropriate Table 14 torque values simultaneously to both fasteners. After bolt numbers 155 L and 155 R have been torqued to the proper values, proceed to the next bolt on each side, in descending bolt number order, and apply the appropriate Table 14 torque values simultaneously to each pair of fasteners. Continue to follow this sequence until all of these fasteners have been torqued to the appropriate Table 14 torque value. (b) Follow the initial pull-up sequence given in Table 13 when installing these fasteners. TABLE 1 - BOLT IDENTIFICATION AND INSTALLATION - S-1L TO S-5LMORE DATA HOLE DIA IDENTIFICATION BOLT NUMBER STRINGER

- 0.312 - 0.316 BACB30US5K18 001

- 0.312 - 0.316 BACB30US5K18 002 L
FIGURE 12: FORWARD SECTION 48 INSTALLATION (SHEET 5 OF 19) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 13, 2015 767-53A0267 Revision 1 August 04, 2016 95 of 206 BOEING SERVICE BULLETIN 767-53A0267 ALERT ALERTTABLE 1 - BOLT IDENTIFICATION AND INSTALLATION - S-1L TO S-5LMORE DATA HOLE DIA IDENTIFICATION BOLT NUMBER STRINGER

- 0.546 - 0.561 BACB30US8K42 003 L 1L

- 0.546 - 0.561 BACB30US8K42 004 L

- 0.312 - 0.316 BACB30US5K18 005 L

- 0.312 - 0.316 BACB30US5K18 006 L

- 0.312 - 0.316 BACB30US5K18 007 L

- 0.546 - 0.561 BACB30US8K42 008 L 2L

- 0.546 - 0.561 BACB30US8K42 009 L

- 0.312 - 0.316 BACB30US5K21 010 L

- 0.312 - 0.316 BACB30US5K21 011 L

- 0.312 - 0.316 BACB30US5K18 012 L

- 0.546 - 0.561 BACB30US8K42 013 L 3L

- 0.546 - 0.561 BACB30US8K42 014 L

- 0.312 - 0.316 BACB30US5K18 015 L

- 0.312 - 0.316 BACB30US5K18 016 L

- 0.312 - 0.316 BACB30US5K18 017 L

- 0.546 - 0.561 BACB30US8K42 018 L 4L

- 0.546 - 0.561 BACB30US8K42 019 L

- 0.312 - 0.316 BACB30US5K18 020 L

- 0.312 - 0.316 BACB30US5K21 021 L

- 0.312 - 0.316 BACB30US5K21 022 L

- 0.484 - 0.499 BACB30US7K39 023 L 5L

- 0.484 - 0.499 BACB30US7K39 024 L

- 0.312 - 0.316 BACB30US5K21 025 L

- 0.312 - 0.316 BACB30US5K21 026 L

- 0.312 - 0.316 BACB30US5K18 027 L

FIGURE 12: FORWARD SECTION 48 INSTALLATION (SHEET 6 OF 19) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 13, 2015 767-53A0267 Revision 1 August 04, 2016 96 of 206 BOEING SERVICE BULLETIN 767-53A0267 ALERT ALERTTABLE 2 - BOLT IDENTIFICATION AND INSTALLATION - S-6L TO S-11LMORE DATA HOLE DIA IDENTIFICATION BOLT NUMBER STRINGER

- 0.484 - 0.499 BACB30US7K39 028 L 6L

- 0.484 - 0.499 BACB30US7K39 029 L

- 0.312 - 0.316 BACB30US5K18 030 L

- 0.312 - 0.316 BACB30US5K18 031 L

- 0.312 - 0.316 BACB30US5K18 032 L

- 0.484 - 0.499 BACB30US7K39 033 L 7L

- 0.484 - 0.499 BACB30US7K39 034 L

- 0.312 - 0.316 BACB30US5K18 035 L

- 0.312 - 0.316 BACB30US5K19 036 L

- 0.312 - 0.316 BACB30US5K19 037 L

- 0.484 - 0.499 BACB30US7K40 038 L 8L

- 0.484 - 0.499 BACB30US7K40 039 L

- 0.312 - 0.316 BACB30US5K19 040 L

- 0.312 - 0.316 BACB30US5K19 041 L

- 0.312 - 0.316 BACB30US5K19 042 L

- 0.484 - 0.499 BACB30US7K40 043 L 9L

- 0.484 - 0.499 BACB30US7K40 044 L

- 0.312 - 0.316 BACB30US5K25 045 L

- 0.312 - 0.316 See step table, Step 10 046 L

- 0.312 - 0.316 BACB30US5K19 047 L

- 0.484 - 0.499 BACB30US7K40 048 L 10L

- 0.484 - 0.499 BACB30US7K40 049 L

- 0.312 - 0.316 BACB30US5K19 050 L

- 0.312 - 0.316 BACB30US5K19 051 L

- 0.312 - 0.316 BACB30US5K19 052 L

- 0.484 - 0.499 BACB30US7K40 053 L 11L

- 0.484 - 0.499 BACB30US7K40 054 L

FIGURE 12: FORWARD SECTION 48 INSTALLATION (SHEET 7 OF 19) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 13, 2015 767-53A0267 Revision 1 August 04, 2016 97 of 206 BOEING SERVICE BULLETIN 767-53A0267 ALERT ALERTTABLE 3 - BOLT IDENTIFICATION AND INSTALLATION - S-12L TO S-16LMORE DATA HOLE DIA IDENTIFICATION BOLT NUMBER STRINGER

- 0.312 - 0.316 BACB30US5K19 055 L

- 0.312 - 0.316 BACB30US5K19 056 L

- 0.312 - 0.316 BACB30US5K19 057 L

- 0.421 - 0.436 BACB30US6K36 058 L 12L

- 0.421 - 0.436 BACB30US6K36 059 L

- 0.312 - 0.316 BACB30US5K18 060 L

- 0.312 - 0.316 BACB30US5K18 061 L

- 0.312 - 0.316 BACB30US5K18 062 L

- 0.421 - 0.436 BACB30US6K35 063 L 13L

- 0.421 - 0.436 BACB30US6K35 064 L

- 0.312 - 0.316 BACB30US5K17 065 L

- 0.312 - 0.316 BACB30US5K17 066 L

- 0.312 - 0.316 BACB30US5K17 067 L

- 0.421 - 0.436 BACB30US6K34 068 L 14L

- 0.421 - 0.436 BACB30US6K34 069 L

- 0.312 - 0.316 BACB30US5K17 070 L

- 0.312 - 0.316 BACB30US5K17 071 L

- 0.312 - 0.316 BACB30US5K17 072 L

- 0.421 - 0.436 BACB30US6K34 073 L 15L

- 0.421 - 0.436 BACB30US6K34 074 L

- 0.312 - 0.316 BACB30US5K17 075 L

- 0.312 - 0.316 BACB30US5K17 076 L

- 0.312 - 0.316 BACB30US5K17 077 L

- 0.421 - 0.436 BACB30US6K36 078 L 16L

- 0.421 - 0.436 BACB30US6K36 079 L

- 0.312 - 0.316 BACB30US5K17 080 L

- 0.312 - 0.316 BACB30US5K17 081 L

FIGURE 12: FORWARD SECTION 48 INSTALLATION (SHEET 8 OF 19) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 13, 2015 767-53A0267 Revision 1 August 04, 2016 98 of 206 BOEING SERVICE BULLETIN 767-53A0267 ALERT ALERTTABLE 4 - BOLT IDENTIFICATION AND INSTALLATION - S-17L TO S-23LMORE DATA HOLE DIA IDENTIFICATION BOLT NUMBER STRINGER

- 0.421 - 0.436 BACB30US6K34 082 L 17L

- 0.421 - 0.436 BACB30US6K34 083 L

- 0.312 - 0.316 BACB30US5K17 084 L

- 0.312 - 0.316 BACB30US5K17 085 L

- 0.421 - 0.436 BACB30US6K34 086 L 18L

- 0.421 - 0.436 BACB30US6K34 087 L

- 0.312 - 0.316 BACB30US5K17 088 L

- 0.312 - 0.316 BACB30US5K17 089 L

- 0.421 - 0.436 BACB30US6K34 090 L 19L

- 0.421 - 0.436 BACB30US6K34 091 L

- 0.312 - 0.316 BACB30US5K17 092 L

- 0.312 - 0.316 BACB30US5K17 093 L

- 0.421 - 0.436 BACB30US6K35 094 L 20L

- 0.421 - 0.436 BACB30US6K35 095 L

- 0.312 - 0.316 BACB30US5K17 096 L

- 0.312 - 0.316 BACB30US5K17 097 L

- 0.312 - 0.316 BACB30US5K17 098 L

- 0.312 - 0.316 BACB30US5K17 099 L

- 0.421 - 0.436 BACB30US6K34 100 L 22L

- 0.421 - 0.436 BACB30US6K34 101 L

- 0.312 - 0.316 BACB30US5K17 102 L

- 0.312 - 0.316 BACB30US5K17 103 L

- 0.421 - 0.436 BACB30US6K33 104 L 23L

- 0.421 - 0.436 BACB30US6K33 105 L

- 0.312 - 0.316 BACB30US5K17 106 L

- 0.312 - 0.316 BACB30US5K17 107 L

FIGURE 12: FORWARD SECTION 48 INSTALLATION (SHEET 9 OF 19) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 13, 2015 767-53A0267 Revision 1 August 04, 2016 99 of 206 BOEING SERVICE BULLETIN 767-53A0267 ALERT ALERTTABLE 5 - BOLT IDENTIFICATION AND INSTALLATION - S-24L TO S-32LMORE DATA HOLE DIA IDENTIFICATION BOLT NUMBER STRINGER

- 0.421 - 0.436 BACB30US6K34 108 L 24L

- 0.421 - 0.436 BACB30US6K34 109 L

- 0.312 - 0.316 BACB30US5K17 110 L

- 0.312 - 0.316 BACB30US5K17 111 L

- 0.421 - 0.436 BACB30US6K34 112 L 25L

- 0.421 - 0.436 BACB30US6K34 113 L

- 0.312 - 0.316 BACB30US5K16 114 L

- 0.421 - 0.436 BACB30US6K33 115 L 26L

- 0.421 - 0.436 BACB30US6K33 116 L

- 0.312 - 0.316 BACB30US5K16 117 L

- 0.421 - 0.436 BACB30US6K33 118 L 27L

- 0.421 - 0.436 BACB30US6K33 119 L

- 0.312 - 0.316 BACB30US5K16 120 L

- 0.421 - 0.436 BACB30US6K33 121 L 28L

- 0.421 - 0.436 BACB30US6K33 122 L

- 0.312 - 0.316 BACB30US5K16 123 L

- 0.421 - 0.436 BACB30US6K33 124 L 29L

- 0.421 - 0.436 BACB30US6K33 125 L

- 0.312 - 0.316 BACB30US5K16 126 L

- 0.484 - 0.499 BACB30US7K35 127 L 30L

- 0.484 - 0.499 BACB30US7K35 128 L

- 0.312 - 0.316 BACB30US5K17 129 L

- 0.421 - 0.436 BACB30US6K33 130 L 31L

- 0.421 - 0.436 BACB30US6K33 131 L

- 0.312 - 0.316 BACB30US5K16 132 L

- 0.421 - 0.436 BACB30US6K33 133 L 32L

- 0.421 - 0.436 BACB30US6K33 134 L

FIGURE 12: FORWARD SECTION 48 INSTALLATION (SHEET 10 OF 19) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 13, 2015 767-53A0267 Revision 1 August 04, 2016 100 of 206 BOEING SERVICE BULLETIN 767-53A0267 ALERT ALERTTABLE 6 - BOLT IDENTIFICATION AND INSTALLATION - S-33L TO S-39LMORE DATA HOLE DIA IDENTIFICATION BOLT NUMBER STRINGER

- 0.312 - 0.316 BACB30US5K16 135 L

- 0.421 - 0.436 BACB30US6K33 136 L 33L

- 0.421 - 0.436 BACB30US6K33 137 L

- 0.312 - 0.316 BACB30US5K18 138 L

- 0.421 - 0.436 BACB30US6K33 139 L 34L

- 0.421 - 0.436 BACB30US6K33 140 L

- 0.312 - 0.316 BACB30US5K16 141 L

- 0.484 - 0.499 BACB30US7K35 142 L 35L

- 0.484 - 0.499 BACB30US7K35 143 L

- 0.312 - 0.316 BACB30US5K16 144 L

- 0.421 - 0.436 BACB30US6K33 145 L 36L

- 0.421 - 0.436 BACB30US6K33 146 L

- 0.312 - 0.316 BACB30US5K16 147 L

- 0.484 - 0.499 BACB30US7K35 148 L 37L

- 0.484 - 0.499 BACB30US7K35 149 L

- 0.484 - 0.499 BACB30US7K35 150 L 38L

- 0.484 - 0.499 BACB30US7K35 151 L

- 0.312 - 0.316 BACB30US5K16 152 L

- 0.421 - 0.436 BACB30US6K31 153 L 39L

- 0.421 - 0.436 BACB30US6K31 154 L

- 0.312 - 0.316 BACB30US5K16 155 TABLE 7 - BOLT IDENTIFICATION AND INSTALLATION - S-1R TO S-5RMORE DATA HOLE DIA IDENTIFICATION BOLT NUMBER STRINGER

- 0.312 - 0.316 BACB30US5K18 002 R

- 0.546 - 0.561 BACB30US8K42 003 R 1R

- 0.546 - 0.561 BACB30US8K42 004 R

FIGURE 12: FORWARD SECTION 48 INSTALLATION (SHEET 11 OF 19) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 13, 2015 767-53A0267 Revision 1 August 04, 2016 101 of 206 BOEING SERVICE BULLETIN 767-53A0267 ALERT ALERTTABLE 7 - BOLT IDENTIFICATION AND INSTALLATION - S-1R TO S-5RMORE DATA HOLE DIA IDENTIFICATION BOLT NUMBER STRINGER

- 0.312 - 0.316 BACB30US5K18 005 R

- 0.312 - 0.316 BACB30US5K18 006 R

- 0.312 - 0.316 BACB30US5K18 007 R

- 0.546 - 0.561 BACB30US8K42 008 R 2R

- 0.546 - 0.561 BACB30US8K42 009 R

- 0.312 - 0.316 BACB30US5K18 010 R

- 0.312 - 0.316 BACB30US5K18 011 R

- 0.312 - 0.316 BACB30US5K18 012 R

- 0.546 - 0.561 BACB30US8K42 013 R 3R

- 0.546 - 0.561 BACB30US8K42 014 R

- 0.312 - 0.316 BACB30US5K18 015 R

- 0.312 - 0.316 BACB30US5K18 016 R

- 0.312 - 0.316 BACB30US5K18 017 R

- 0.546 - 0.561 BACB30US8K42 018 R 4R

- 0.546 - 0.561 BACB30US8K42 019 R

- 0.312 - 0.316 BACB30US5K18 020 R

- 0.312 - 0.316 BACB30US5K21 021 R

- 0.312 - 0.316 BACB30US5K21 022 R

- 0.484 - 0.499 BACB30US7K39 023 R 5R

- 0.484 - 0.499 BACB30US7K39 024 R

- 0.312 - 0.316 BACB30US5K21 025 R

- 0.312 - 0.316 BACB30US5K21 026 R

- 0.312 - 0.316 BACB30US5K18 027 R TABLE 8 - BOLT IDENTIFICATION AND INSTALLATION - S-6R TO S-11RMORE DATA HOLE DIA IDENTIFICATION BOLT NUMBER STRINGER

- 0.484 - 0.499 BACB30US7K39 028 R 6R

- 0.484 - 0.499 BACB30US7K39 029 R

FIGURE 12: FORWARD SECTION 48 INSTALLATION (SHEET 12 OF 19) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 13, 2015 767-53A0267 Revision 1 August 04, 2016 102 of 206 BOEING SERVICE BULLETIN 767-53A0267 ALERT ALERTTABLE 8 - BOLT IDENTIFICATION AND INSTALLATION - S-6R TO S-11RMORE DATA HOLE DIA IDENTIFICATION BOLT NUMBER STRINGER

- 0.312 - 0.316 BACB30US5K18 030 R

- 0.312 - 0.316 BACB30US5K18 031 R

- 0.312 - 0.316 BACB30US5K18 032 R

- 0.484 - 0.499 BACB30US7K39 033 R 7R

- 0.484 - 0.499 BACB30US7K39 034 R

- 0.312 - 0.316 BACB30US5K18 035 R

- 0.312 - 0.316 BACB30US5K19 036 R

- 0.312 - 0.316 BACB30US5K19 037 R

- 0.484 - 0.499 BACB30US7K40 038 R 8R

- 0.484 - 0.499 BACB30US7K40 039 R

- 0.312 - 0.316 BACB30US5K19 040 R

- 0.312 - 0.316 BACB30US5K19 041 R

- 0.312 - 0.316 BACB30US5K19 042 R

- 0.484 - 0.499 BACB30US7K40 043 R 9R

- 0.484 - 0.499 BACB30US7K40 044 R

- 0.312 - 0.316 BACB30US5K25 045 R

- 0.312 - 0.316 See step table, Step 10 046 R

- 0.312 - 0.316 BACB30US5K19 047 R

- 0.484 - 0.499 BACB30US7K40 048 R 10R

- 0.484 - 0.499 BACB30US7K40 049 R

- 0.312 - 0.316 BACB30US5K19 050 R

- 0.312 - 0.316 BACB30US5K19 051 R

- 0.312 - 0.316 BACB30US5K19 052 R

- 0.484 - 0.499 BACB30US7K40 053 R 11R

- 0.484 - 0.499 BACB30US7K40 054 R

FIGURE 12: FORWARD SECTION 48 INSTALLATION (SHEET 13 OF 19) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 13, 2015 767-53A0267 Revision 1 August 04, 2016 103 of 206 BOEING SERVICE BULLETIN 767-53A0267 ALERT ALERTTABLE 9 - BOLT IDENTIFICATION AND INSTALLATION - S-12R TO S-16RMORE DATA HOLE DIA IDENTIFICATION BOLT NUMBER STRINGER

- 0.312 - 0.316 BACB30US5K19 055 R

- 0.312 - 0.316 BACB30US5K19 056 R

- 0.312 - 0.316 BACB30US5K19 057 R

- 0.421 - 0.436 BACB30US6K36 058 R 12R

- 0.421 - 0.436 BACB30US6K36 059 R

- 0.312 - 0.316 BACB30US5K18 060 R

- 0.312 - 0.316 BACB30US5K18 061 R

- 0.312 - 0.316 BACB30US5K18 062 R

- 0.421 - 0.436 BACB30US6K35 063 R 13R

- 0.421 - 0.436 BACB30US6K35 064 R

- 0.312 - 0.316 BACB30US5K17 065 R

- 0.312 - 0.316 BACB30US5K17 066 R

- 0.312 - 0.316 BACB30US5K17 067 R

- 0.421 - 0.436 BACB30US6K34 068 R 14R

- 0.421 - 0.436 BACB30US6K34 069 R

- 0.312 - 0.316 BACB30US5K17 070 R

- 0.312 - 0.316 BACB30US5K17 071 R

- 0.312 - 0.316 BACB30US5K17 072 R

- 0.421 - 0.436 BACB30US6K34 073 R 15R

- 0.421 - 0.436 BACB30US6K34 074 R

- 0.312 - 0.316 BACB30US5K17 075 R

- 0.312 - 0.316 BACB30US5K17 076 R

- 0.312 - 0.316 BACB30US5K17 077 R

- 0.421 - 0.436 BACB30US6K36 078 R 16R

- 0.421 - 0.436 BACB30US6K36 079 R

- 0.312 - 0.316 BACB30US5K17 080 R

- 0.312 - 0.316 BACB30US5K17 081 R

FIGURE 12: FORWARD SECTION 48 INSTALLATION (SHEET 14 OF 19) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 13, 2015 767-53A0267 Revision 1 August 04, 2016 104 of 206 BOEING SERVICE BULLETIN 767-53A0267 ALERT ALERTTABLE 10 - BOLT IDENTIFICATION AND INSTALLATION - S-17R TO S-23R MORE DATA HOLE DIA IDENTIFICATION BOLT NUMBER STRINGER

- 0.421 - 0.436 BACB30US6K34 082 R 17R

- 0.421 - 0.436 BACB30US6K34 083 R

- 0.312 - 0.316 BACB30US5K17 084 R

- 0.312 - 0.316 BACB30US5K17 085 R

- 0.421 - 0.436 BACB30US6K34 086 R 18R

- 0.421 - 0.436 BACB30US6K34 087 R

- 0.312 - 0.316 BACB30US5K17 088 R

- 0.312 - 0.316 BACB30US5K17 089 R

- 0.421 - 0.436 BACB30US6K34 090 R 19R

- 0.421 - 0.436 BACB30US6K34 091 R

- 0.312 - 0.316 BACB30US5K17 092 R

- 0.312 - 0.316 BACB30US5K17 093 R

- 0.421 - 0.436 BACB30US6K35 094 R 20R

- 0.421 - 0.436 BACB30US6K35 095 R

- 0.312 - 0.316 BACB30US5K17 096 R

- 0.312 - 0.316 BACB30US5K17 097 R

- 0.312 - 0.316 BACB30US5K17 098 R

- 0.312 - 0.316 BACB30US5K17 099 R

- 0.421 - 0.436 BACB30US6K34 100 R 22R

- 0.421 - 0.436 BACB30US6K34 101 R

- 0.312 - 0.316 BACB30US5K17 102 R

- 0.312 - 0.316 BACB30US5K17 103 R

- 0.421 - 0.436 BACB30US6K33 104 R 23R

- 0.421 - 0.436 BACB30US6K33 105 R

- 0.312 - 0.316 BACB30US5K17 106 R

- 0.312 - 0.316 BACB30US5K17 107 R

FIGURE 12: FORWARD SECTION 48 INSTALLATION (SHEET 15 OF 19) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 13, 2015 767-53A0267 Revision 1 August 04, 2016 105 of 206 BOEING SERVICE BULLETIN 767-53A0267 ALERT ALERTTABLE 11 - BOLT IDENTIFICATION AND INSTALLATION - S-24R TO S-32R MORE DATA HOLE DIA IDENTIFICATION BOLT NUMBER STRINGER

- 0.421 - 0.436 BACB30US6K34 108 R 24R

- 0.421 - 0.436 BACB30US6K34 109 R

- 0.312 - 0.316 BACB30US5K17 110 R

- 0.312 - 0.316 BACB30US5K17 111 R

- 0.421 - 0.436 BACB30US6K34 112 R 25R

- 0.421 - 0.436 BACB30US6K34 113 R

- 0.312 - 0.316 BACB30US5K16 114 R

- 0.421 - 0.436 BACB30US6K33 115 R 26R

- 0.421 - 0.436 BACB30US6K33 116 R

- 0.312 - 0.316 BACB30US5K16 117 R

- 0.421 - 0.436 BACB30US6K33 118 R 27R

- 0.421 - 0.436 BACB30US6K33 119 R

- 0.312 - 0.316 BACB30US5K16 120 R

- 0.421 - 0.436 BACB30US6K33 121 R 28R

- 0.421 - 0.436 BACB30US6K33 122 R

- 0.312 - 0.316 BACB30US5K16 123 R

- 0.421 - 0.436 BACB30US6K33 124 R 29R

- 0.421 - 0.436 BACB30US6K33 125 R

- 0.312 - 0.316 BACB30US5K16 126 R

- 0.484 - 0.499 BACB30US7K35 127 R 30R

- 0.484 - 0.499 BACB30US7K35 128 R

- 0.312 - 0.316 BACB30US5K17 129 R

- 0.421 - 0.436 BACB30US6K33 130 R 31R

- 0.421 - 0.436 BACB30US6K33 131 R

- 0.312 - 0.316 BACB30US5K16 132 R

- 0.484 - 0.499 BACB30US7K35 133 R 32R

- 0.484 - 0.499 BACB30US7K35 134 R

- 0.312 - 0.316 BACB30US5K16 135 R

FIGURE 12: FORWARD SECTION 48 INSTALLATION (SHEET 16 OF 19) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 13, 2015 767-53A0267 Revision 1 August 04, 2016 106 of 206 BOEING SERVICE BULLETIN 767-53A0267 ALERT ALERTTABLE 12 - BOLT IDENTIFICATION AND INSTALLATION - S-33R TO S-39R MORE DATA HOLE DIA IDENTIFICATION BOLT NUMBER STRINGER

- 0.421 - 0.436 BACB30US6K33 136 R 33R

- 0.421 - 0.436 BACB30US6K33 137 R

- 0.312 - 0.316 BACB30US5K16 138 R

- 0.421 - 0.436 BACB30US6K33 139 R 34R

- 0.421 - 0.436 BACB30US6K33 140 R

- 0.312 - 0.316 BACB30US5K16 141 R

- 0.421 - 0.436 BACB30US6K33 142 R 35R

- 0.421 - 0.436 BACB30US6K33 143 R

- 0.312 - 0.316 BACB30US5K16 144 R

- 0.421 - 0.436 BACB30US6K33 145 R 36R

- 0.421 - 0.436 BACB30US6K33 146 R

- 0.312 - 0.316 BACB30US5K16 147 R

- 0.484 - 0.499 BACB30US7K35 148 R 37R

- 0.484 - 0.499 BACB30US7K35 149 R

- 0.484 - 0.499 BACB30US7K35 150 R 38R

- 0.484 - 0.499 BACB30US7K35 151 R

- 0.312 - 0.316 BACB30US5K18 152 R

- 0.421 - 0.436 BACB30US6K31 153 R 39R

- 0.421 - 0.436 BACB30US6K31 154 R TABLE 13 - INITIAL PULL-UP SEQUENCE AND TORQUE VALUES (STRINGER LOCATIONS ONLY)TORQUE (INCHPOUNDS) STRINGER BOLT NUMBER STEP 410 - 450, simultaneously 6L and 22R 28 L, 29 L, 100 R, 101 R 1 410 - 450, simultaneously 6R and 22L 28 R, 29 R, 100 L, 101 L 2 410 - 450 (a) (b) 39L through 7L and 39R through 7R 154 L through 033 L and 154R through 033 R, at stringer locations only. 3

FIGURE 12: FORWARD SECTION 48 INSTALLATION (SHEET 17 OF 19) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 13, 2015 767-53A0267 Revision 1 August 04, 2016 107 of 206 BOEING SERVICE BULLETIN 767-53A0267 ALERT ALERTTABLE 13 - INITIAL PULL-UP SEQUENCE AND TORQUE VALUES (STRINGER LOCATIONS ONLY)TORQUE (INCHPOUNDS) STRINGER BOLT NUMBER STEP 1000 - 1050 (a) (c) 5L through 1L and 5R through 1R 024 L through 003 L and 024 R through 003 R, at stringer locations only. 4 (a) At stringer locations only. Do not apply this torque to the 5/16 inch diameter bolts in between the stringer locations. (b) Apply torque simultaneously to matching left and right bolt locations (example: bolt number 154 L and bolt 154 R), in order, beginning with bolt numbers 154 L and 154 R and ending with bolt numbers 033 L and 033 R. (c) Apply torque simultaneously to matching left and right bolt locations (example: bolt number 024 L and bolt 024 R), in order, beginning with bolt numbers 024 L and 024 R and ending with bolt numbers 003 L and 003 R. TABLE 14 - FINAL TORQUE VALUES TORQUE APPLIED TO NUT (INCHPOUNDS) TORQUE APPLIED TO BOLT HEAD (INCH-POUNDS) BOLT PART NUMBER 180 - 250 225 - 275 BACB30US5K( ) 300 - 500 450 - 550 BACB30US6K( ) 510 - 840 756 - 924 BACB30US7K( ) 870 - 1300 1170 - 1430 BACB30US8K( )

The codes shown below agree with the letter shown in the upper left corner of the fastener symbols in the figure. A number in the lower right corner gives the grip length of the fastener. The QTY numbers shown below are the number of fasteners necessary for this figure. FIGURE 12: FORWARD SECTION 48 INSTALLATION (SHEET 18 OF 19) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 13, 2015 767-53A0267 Revision 1 August 04, 2016 108 of 206 BOEING SERVICE BULLETIN 767-53A0267 ALERT ALERTMore Data Hole Dia Qty Identification Name Code

- 0.200-0.203 20 BACB30NX6K4X BOLT, PROTRUDING HD A

- - 20 BACC30BH6 COLLAR

- 0.200-0.203 2 BACB30NX6K5X BOLT, PROTRUDING HD B

- - 2 BACC30BH6 COLLAR

- 0.200-0.203 2 BACB30NX6K10X BOLT, PROTRUDING HD C

- - 2 BACC30BH6 COLLAR The parts shown in the table below are provided as extra parts for this figure. MORE DATA QTY IDENTIFICATION NAME

- 1 272T4825-9 BRACKET ASSY-

- 3 BACB30US5K16 BOLT, 12 PT HEAD

- 2 BACB30US5K17 BOLT, 12 PT HEAD

- 1 BACB30US5K18 BOLT, 12 PT HEAD

- 2 BACB30US5K25 BOLT, 12 PT HEAD

- 4 BACB30US7K35 BOLT, 12 PT HEAD

FIGURE 12: FORWARD SECTION 48 INSTALLATION (SHEET 19 OF 19) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 13, 2015 767-53A0267 Revision 1 August 04, 2016 109 of 206 BOEING SERVICE BULLETIN 767-53A0267 ALERT ALERTFIGURE 13: LEFT STA 1809.5 CENTER BULKHEAD INSTALLATION (SHEET 1 OF 12) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 13, 2015 767-53A0267 Revision 1 August 04, 2016 110 of 206 BOEING SERVICE BULLETIN 767-53A0267 ALERT ALERTFIGURE 13: LEFT STA 1809.5 CENTER BULKHEAD INSTALLATION (SHEET 2 OF 12) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 13, 2015 767-53A0267 Revision 1 August 04, 2016 111 of 206 BOEING SERVICE BULLETIN 767-53A0267 ALERT ALERTFIGURE 13: LEFT STA 1809.5 CENTER BULKHEAD INSTALLATION (SHEET 3 OF 12) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 13, 2015 767-53A0267 Revision 1 August 04, 2016 112 of 206 BOEING SERVICE BULLETIN 767-53A0267 ALERT ALERTFIGURE 13: LEFT STA 1809.5 CENTER BULKHEAD INSTALLATION (SHEET 4 OF 12) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 13, 2015 767-53A0267 Revision 1 August 04, 2016 113 of 206 BOEING SERVICE BULLETIN 767-53A0267 ALERT ALERTFIGURE 13: LEFT STA 1809.5 CENTER BULKHEAD INSTALLATION (SHEET 5 OF 12) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 13, 2015 767-53A0267 Revision 1 August 04, 2016 114 of 206 BOEING SERVICE BULLETIN 767-53A0267 ALERT ALERTFIGURE 13: LEFT STA 1809.5 CENTER BULKHEAD INSTALLATION (SHEET 6 OF 12) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 13, 2015 767-53A0267 Revision 1 August 04, 2016 115 of 206 BOEING SERVICE BULLETIN 767-53A0267 ALERT ALERTThe step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY numbers shown below are the number of parts necessary for one side of the airplane. NOTE:Many of the affected fastener locations have been cold worked during production. If any of the fastener locations need to be made larger than specified in this figure, contact The Boeing Company to determine if additional cold work is necessary and do all additional work that The Boeing Company determines to be necessary. REQUIREMENTS: 1. Some of the fastener locations identified in this figure may have been changed from the original delivered configuration during the inspection, repair, or modification given in Boeing Service Bulletin 767-53A0078, "Fuselage - Section 48 - Body Station 1809.5 Bulkhead Outer Chord Inspection, Repair, and Modification." An Alternative Method of Compliance (AMOC) to the requirements of the applicable Airworthiness Directive may have been granted for configurations different than those shown in 767-53A0078. These fastener locations must be maintained to the requirements of FAA AD 2005-11-02 or to an approved AMOC to that AD. When fasteners are removed from these locations, document the fastener/nut/collar diameter, grip and type removed and the existing fastener hole diameter. Use care to not damage the fastener hole when removing fasteners. Do not clean the bores of these fastener holes with brass bottle brushes. Do an open-hole High Frequency Eddy Current (HFEC) inspection at all parts in the stack-up at these locations. Verify that there are no surface defects (such as rifling, gouging, nicks, burrs, or excessive surface roughness) in the bores of these fastener holes, other than that normally produced during a typical reaming operation. If any defect is found, contact The Boeing Company for repair instructions and do the repair. Verify that washers or fillet relief exists to accommodate the fasteners head-to-shank fillet radius. When fasteners are installed, use the same type and size fasteners that were removed earlier. 2. Some of the fastener locations identified in this figure may have been changed from the original delivered configuration during the inspection, repair, or modification given in Boeing Service Bulletin 767-53A0131, "Fuselage - Section 48 - Main Frame and Skins - STA 1809.5 Bulkhead - Forward Outer Chord, Horizontal and Vertical Inner Chord, and External Skin - Inspection." An Alternative Method of Compliance (AMOC) to the requirements of the applicable Airworthiness Directive may have been granted for configurations different than those shown in 767-53A0131. These fastener locations must be maintained to the requirements of FAA AD 2011-14-02 or to an approved AMOC to that AD. When fasteners are removed from these locations, document the fastener/nut/collar diameter, grip and type removed and the existing fastener hole diameter. Use care to not damage the fastener hole when removing fasteners. Do not clean the bores of these fastener holes with brass bottle brushes. Do an open-hole High Frequency Eddy Current (HFEC) inspection at all parts in the stack-up at these locations. Verify that there are no surface defects (such as rifling, gouging, nicks, burrs, or excessive surface roughness) in the bores of these fastener holes, other than that normally produced during a typical reaming operation. If any defect is found, contact The Boeing Company for repair instructions and do the repair. Verify that washers or fillet relief exists to accommodate the fasteners head-to-shank fillet radius. When fasteners are installed, use the same type and size fasteners that were removed earlier. However, Boeing recommends that H-11 steel bolts be replaced with Inconel bolts. Refer to Boeing Service Letter 767-SL-51-008-B More Data Qty Identification Name Task Step

- 1 - Center Bulkhead Assy Install (Kept) 1
FIGURE 13: LEFT STA 1809.5 CENTER BULKHEAD INSTALLATION (SHEET 7 OF 12) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 13, 2015 767-53A0267 Revision 1 August 04, 2016 116 of 206 BOEING SERVICE BULLETIN 767-53A0267 ALERT ALERTMore Data Qty Identification Name Task Step If removed earlier 4 - Filler Install (Kept) 2

- 2 148T0012-2 FILLER Install (New) 3

- 2 148T0012-3 FILLER Install (New) 4 (a) (b) 1 148T0012-4 SHIM Install (New) 5

- - BMS 5-25 Epoxy Adhesive Bond (a) (b) 1 148T0012-5 SHIM Install (New) 6

- - BMS 5-25 Epoxy Adhesive Bond

- 1 148T0012-11 FILLER Install (New) 7

- 2 148T0015-1 SPLICE-STRAP Install (New) 8 (a) 2 BACS40R011B027F SHIM,LAMINATED Install (New) 9 (a) 2 BACS40R012B027F SHIM, LAMINATED Install (New) 10 (a) 1 BACS40R016B098F SHIM, LAMINATED Install (New) 11 (a) 1 BACS40R027C030F SHIM, LAMINATED Install (New) 12 See Fastener DataTable for part numbers and final hole diameters. 214 - Fastener Install (New) 13 (a) Remove 0.003 inch laminations as necessary to achieve maximum allowable pull-up of 0.005 inch. After adjustment, apply one coat of BMS 10-11 Type I primer. (b) Bond into position with BMS 5-25, Type II, Grade I epoxy adhesive.

The codes shown below agree with the letter shown in the upper left corner of the fastener symbols in the figure. The QTY numbers shown below are the number of fasteners necessary for this figure.
FIGURE 13: LEFT STA 1809.5 CENTER BULKHEAD INSTALLATION (SHEET 8 OF 12) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 13, 2015 767-53A0267 Revision 1 August 04, 2016 117 of 206 BOEING SERVICE BULLETIN 767-53A0267 ALERT ALERTNOTE:Install all bolts wet with BMS 5-95 sealant. More Data Hole Dia Qty Identification Name Code

- 0.263-0.266 35 BACB30MY8K5X BOLT, PROTRUDING HD A

- - 35 BACC30M8 COLLAR

- 0.263-0.266 1 BACB30MY8K6X BOLT, PROTRUDING HD B

- - 1 BACC30M8 COLLAR (b) 0.263-0.266 65 BACB30MY8K7X BOLT, PROTRUDING HD C (b) - 65 BACC30M8 COLLAR

- 0.263-0.266 3 BACB30MY8K8X BOLT, PROTRUDING HD D

- - 3 BACC30M8 COLLAR

- 0.263-0.266 1 BACB30MY8K9X BOLT, PROTRUDING HD E

- - 1 BACC30M8 COLLAR

- 0.263-0.266 7 BACB30MY8K10X BOLT, PROTRUDING HD F

- - 7 BACC30M8 COLLAR

- 0.263-0.266 3 BACB30MY8K11X BOLT, PROTRUDING HD G

- 3 BACC30M8 COLLAR

- 0.263-0.266 4 BACB30MY8K12X BOLT, PROTRUDING HD H

- - 4 BACC30M8 COLLAR

- 0.325-0.328 10 BACB30MY10K3X BOLT TITANIUM O/S I

- - 10 BACC30M10 COLLAR

- 0.325-0.328 5 BACB30MY10K5X BOLT, PROTRUDING HD J

- - 5 BACC30M10 COLLAR

- 0.325-0.328 1 BACB30MY10K6X BOLT, PROTRUDING HD K

- - 1 BACC30M10 COLLAR

FIGURE 13: LEFT STA 1809.5 CENTER BULKHEAD INSTALLATION (SHEET 9 OF 12) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 13, 2015 767-53A0267 Revision 1 August 04, 2016 118 of 206 BOEING SERVICE BULLETIN 767-53A0267 ALERT ALERTMore Data Hole Dia Qty Identification Name Code

- 0.325-0.328 11 BACB30MY10K7X BOLT, PROTRUDING HD L

- - 11 BACC30M10 COLLAR

- 0.325-0.328 14 BACB30MY10K8X BOLT, PROTRUDING HD M

- - 14 BACC30M10 COLLAR

- 0.325-0.328 8 BACB30MY10K10X BOLT, PROTRUDING HD N

- - 8 BACC30M10 COLLAR

- 0.388-0.391 2 BACB30MY12K6X BOLT, PROTRUDING HD O

- - 2 BACC30M12 COLLAR

- 0.388-0.391 4 BACB30MY12K7X BOLT, PROTRUDING HD P

- - 4 BACC30M12 COLLAR (b) 0.388-0.391 4 BACB30MY12K8X BOLT, PROTRUDING HD Q (b) - 4 BACC30M12 COLLAR (b) 0.388-0.391 4 BACB30MY12K10X BOLT, PROTRUDING HD R (b) - 4 BACC30M12 COLLAR

- 0.325-0.328 2 BACB30NX10K8X BOLT, PROTRUDING HD S

- - 2 BACC30BH10 COLLAR

- 0.325-0.328 2 BACB30NX10K9X BOLT, PROTRUDING HD T

- - 2 BACC30BH10 COLLAR (b) 0.325-0.328 4 BACB30NX10K11X BOLT, PROTRUDING HD U (b) - 4 BACC30BH10 COLLAR (b) 0.325-0.328 4 BACB30NX10K12X BOLT, PROTRUDING HD V (b) - 4 BACC30BH10 COLLAR

FIGURE 13: LEFT STA 1809.5 CENTER BULKHEAD INSTALLATION (SHEET 10 OF 12) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 13, 2015 767-53A0267 Revision 1 August 04, 2016 119 of 206 BOEING SERVICE BULLETIN 767-53A0267 ALERT ALERTMore Data Hole Dia Qty Identification Name Code (b) 0.388-0.391 4 BACB30NX12K12X BOLT, PROTRUDING HD W (b) - 4 BACC30BH12 COLLAR

- - 5 BACR15FV7KE7 RIVET X

- - 1 BACR15FV7KE8 RIVET Y

- 0.263-0.266 2 BACB30NW8K5X BOLT, 100 DEG HEX DR Z

- - 2 BACC30M8 COLLAR (a) 0.263-0.266 2 BACB30NW8K7X BOLT, 100 DEG HEX DR AA (a) - 2 BACC30M8 COLLAR (a) 0.263-0.266 4 BACB30NW8K8X BOLT, 100 DEG HEX DR AB (a) - 4 BACC30M8 COLLAR (a) 0.263-0.266 4 BACB30NW8K13X BOLT, 100 DEG HEX DR AC (a) - 4 BACC30M8 COLLAR (a) If the repair or modification given in Service Bulletin 767-53A0078 was previously installed, install new fasteners of the same type and size specified in Service Bulletin 767-53A0078, FAA AD 2005-11-02 or approved AMOC instead of the fasteners specified in this table. If any fastener holes have been damaged and the fasteners specified in 767-53A0078, FAA AD 2005-11-02 or approved AMOC cannot be reinstalled, Contact The Boeing Company for repair instructions and do the repair. (b) Some of these fasteners may have been replaced in accordance with Service Bulletin 767-53A0131. If the repair given in Service Bulletin 767-53A0131 was previously installed, install new fasteners of the same type and size specified in Service Bulletin 767-53A0131, FAA AD 2011-14-02 or approved AMOC instead of the fasteners specified in this table. If any fastener holes have been damaged and the fasteners specified in 767-53A0131, FAA AD 2011-14-02 or approved AMOC cannot be reinstalled, Contact The Boeing Company for repair instructions and do the repair. The parts shown in the table below are provided as extra parts for this figure. MORE DATA QTY IDENTIFICATION NAME

- 2 148T0012-19 SHIM

- 2 BACC30BH10 COLLAR

- 14 BACC30M8 COLLAR The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure.

FIGURE 13: LEFT STA 1809.5 CENTER BULKHEAD INSTALLATION (SHEET 11 OF 12) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 13, 2015 767-53A0267 Revision 1 August 04, 2016 120 of 206 BOEING SERVICE BULLETIN 767-53A0267 ALERT ALERTMORE DATA FLAG NOTE The fasteners in this area may have been replaced with oversize fasteners as part of the repair or modification in Service Bulletin 767-53A0078, "Fuselage - Section 48 - Body Station 1809.5 Bulkhead Outer Chord Inspection, Repair, and Modification". 1 The fasteners in this area may have been replaced with oversize fasteners as part of the repair in Boeing Service Bulletin 767- 53A0131, "Fuselage - Section 48 - Main Frame and Skins - STA 1809.5 Bulkhead - Forward Outer Chord, Horizontal and Vertical Inner Chord, and External Skin - Inspection". 2

FIGURE 13: LEFT STA 1809.5 CENTER BULKHEAD INSTALLATION (SHEET 12 OF 12) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 13, 2015 767-53A0267 Revision 1 August 04, 2016 121 of 206 BOEING SERVICE BULLETIN 767-53A0267 ALERT ALERTFIGURE 14: RIGHT STA 1809.5 CENTER BULKHEAD INSTALLATION (SHEET 1 OF 12) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 13, 2015 767-53A0267 Revision 1 August 04, 2016 122 of 206 BOEING SERVICE BULLETIN 767-53A0267 ALERT ALERTFIGURE 14: RIGHT STA 1809.5 CENTER BULKHEAD INSTALLATION (SHEET 2 OF 12) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 13, 2015 767-53A0267 Revision 1 August 04, 2016 123 of 206 BOEING SERVICE BULLETIN 767-53A0267 ALERT ALERTFIGURE 14: RIGHT STA 1809.5 CENTER BULKHEAD INSTALLATION (SHEET 3 OF 12) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 13, 2015 767-53A0267 Revision 1 August 04, 2016 124 of 206 BOEING SERVICE BULLETIN 767-53A0267 ALERT ALERTFIGURE 14: RIGHT STA 1809.5 CENTER BULKHEAD INSTALLATION (SHEET 4 OF 12) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 13, 2015 767-53A0267 Revision 1 August 04, 2016 125 of 206 BOEING SERVICE BULLETIN 767-53A0267 ALERT ALERTFIGURE 14: RIGHT STA 1809.5 CENTER BULKHEAD INSTALLATION (SHEET 5 OF 12) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 13, 2015 767-53A0267 Revision 1 August 04, 2016 126 of 206 BOEING SERVICE BULLETIN 767-53A0267 ALERT ALERTFIGURE 14: RIGHT STA 1809.5 CENTER BULKHEAD INSTALLATION (SHEET 6 OF 12) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 13, 2015 767-53A0267 Revision 1 August 04, 2016 127 of 206 BOEING SERVICE BULLETIN 767-53A0267 ALERT ALERTThe step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY numbers shown below are the number of parts necessary for one side of the airplane. NOTE:Many of the affected fastener locations have been cold worked during production. If any of the fastener locations need to be made larger than specified in this figure, contact The Boeing Company to determine if additional cold work is necessary and do all additional work that The Boeing Company determines to be necessary. REQUIREMENTS: 1. Some of the fastener locations identified in this figure may have been changed from the original delivered configuration during the inspection, repair, or modification given in Boeing Service Bulletin 767-53A0078, "Fuselage - Section 48 - Body Station 1809.5 Bulkhead Outer Chord Inspection, Repair, and Modification." An Alternative Method of Compliance (AMOC) to the requirements of the applicable Airworthiness Directive may have been granted for configurations different than those shown in 767-53A0078. These fastener locations must be maintained to the requirements of FAA AD 2005-11-02 or to an approved AMOC to that AD. When fasteners are removed from these locations, document the fastener/nut/collar diameter, grip and type removed and the existing fastener hole diameter. Use care to not damage the fastener hole when removing fasteners. Do not clean the bores of these fastener holes with brass bottle brushes. Do an open-hole High Frequency Eddy Current (HFEC) inspection at all parts in the stack-up at these locations. Verify that there are no surface defects (such as rifling, gouging, nicks, burrs, or excessive surface roughness) in the bores of these fastener holes, other than that normally produced during a typical reaming operation. If any defect is found, contact The Boeing Company for repair instructions and do the repair. Verify that washers or fillet relief exists to accommodate the fasteners head-to-shank fillet radius. When fasteners are installed, use the same type and size fasteners that were removed earlier. 2. Some of the fastener locations identified in this figure may have been changed from the original delivered configuration during the inspection, repair, or modification given in Boeing Service Bulletin 767-53A0131, "Fuselage - Section 48 - Main Frame and Skins - STA 1809.5 Bulkhead - Forward Outer Chord, Horizontal and Vertical Inner Chord, and External Skin - Inspection." An Alternative Method of Compliance (AMOC) to the requirements of the applicable Airworthiness Directive may have been granted for configurations different than those shown in 767-53A0131. These fastener locations must be maintained to the requirements of FAA AD 2011-14-02 or to an approved AMOC to that AD. When fasteners are removed from these locations, document the fastener/nut/collar diameter, grip and type removed and the existing fastener hole diameter. Use care to not damage the fastener hole when removing fasteners. Do not clean the bores of these fastener holes with brass bottle brushes. Do an open-hole High Frequency Eddy Current (HFEC) inspection at all parts in the stack-up at these locations. Verify that there are no surface defects (such as rifling, gouging, nicks, burrs, or excessive surface roughness) in the bores of these fastener holes, other than that normally produced during a typical reaming operation. If any defect is found, contact The Boeing Company for repair instructions and do the repair. Verify that washers or fillet relief exists to accommodate the fasteners head-to-shank fillet radius. When fasteners are installed, use the same type and size fasteners that were removed earlier. However, Boeing recommends that H-11 steel bolts be replaced with Inconel bolts. Refer to Boeing Service Letter 767-SL-51-008-B. More Data Qty Identification Name Task Step

- 1 - Center Bulkhead Assy Install (Kept) 1 FIGURE 14: RIGHT STA 1809.5 CENTER BULKHEAD INSTALLATION (SHEET 7 OF 12) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 13, 2015 767-53A0267 Revision 1 August 04, 2016 128 of 206 BOEING SERVICE BULLETIN 767-53A0267 ALERT ALERTMore Data Qty Identification Name Task Step If removed earlier 4 - Filler Install (Kept) 2

- 2 148T0012-2 FILLER Install (New) 3

- 2 148T0012-3 FILLER Install (New) 4 (a) (b) 1 148T0012-4 SHIM Install (New) 5

- - BMS 5-25 Epoxy Adhesive Bond (a) (b) 1 148T0012-5 SHIM Install (New) 6

- - BMS 5-25 Epoxy Adhesive Bond

- 1 148T0012-11 FILLER Install (New) 7

- 2 148T0015-1 SPLICE-STRAP Install (New) 8 (a) 2 BACS40R011B027F SHIM,LAMINATED Install (New) 9 (a) 2 BACS40R012B027F SHIM, LAMINATED Install (New) 10 (a) 1 BACS40R016B098F SHIM, LAMINATED Install (New) 11 (a) 1 BACS40R027C030F SHIM, LAMINATED Install (New) 12 See Fastener DataTable for part numbers and final hole diameters. 214 - Fastener Install (New) 13 (a) Remove 0.003 inch laminations as necessary to achieve maximum allowable pull-up of 0.005 inch. After adjustment, apply one coat of BMS 10-11 Type I primer. (b) Bond into position with BMS 5-25, Type II, Grade I epoxy adhesive.

The codes shown below agree with the letter shown in the upper left corner of the fastener symbols in the figure. The QTY numbers shown below are the number of fasteners necessary for this figure. NOTE:Install all bolts wet with BMS 5-95 sealant.

FIGURE 14: RIGHT STA 1809.5 CENTER BULKHEAD INSTALLATION (SHEET 8 OF 12) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 13, 2015 767-53A0267 Revision 1 August 04, 2016 129 of 206 BOEING SERVICE BULLETIN 767-53A0267 ALERT ALERTMore Data Hole Dia Qty Identification Name Code

- 0.263-0.266 35 BACB30MY8K5X BOLT, PROTRUDING HD A

- - 35 BACC30M8 COLLAR

- 0.263-0.266 1 BACB30MY8K6X BOLT, PROTRUDING HD B

- - 1 BACC30M8 COLLAR (b) 0.263-0.266 65 BACB30MY8K7X BOLT, PROTRUDING HD C (b) - 65 BACC30M8 COLLAR

- 0.263-0.266 3 BACB30MY8K8X BOLT, PROTRUDING HD D

- - 3 BACC30M8 COLLAR

- 0.263-0.266 1 BACB30MY8K9X BOLT, PROTRUDING HD E

- - 1 BACC30M8 COLLAR

- 0.263-0.266 7 BACB30MY8K10X BOLT, PROTRUDING HD F

- - 7 BACC30M8 COLLAR

- 0.263-0.266 3 BACB30MY8K11X BOLT, PROTRUDING HD G

- - 3 BACC30M8 COLLAR

- 0.263-0.266 4 BACB30MY8K12X BOLT, PROTRUDING HD H

- - 4 BACC30M8 COLLAR

- 0.325-0.328 10 BACB30MY10K3X BOLT TITANIUM O/S I

- - 10 BACC30M10 COLLAR

- 0.325-0.328 5 BACB30MY10K5X BOLT, PROTRUDING HD J

- - 5 BACC30M10 COLLAR

- 0.325-0.328 1 BACB30MY10K6X BOLT, PROTRUDING HD K

- - 1 BACC30M10 COLLAR

- 0.325-0.328 11 BACB30MY10K7X BOLT, PROTRUDING HD L

- - 11 BACC30M10 COLLAR
FIGURE 14: RIGHT STA 1809.5 CENTER BULKHEAD INSTALLATION (SHEET 9 OF 12) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 13, 2015 767-53A0267 Revision 1 August 04, 2016 130 of 206 BOEING SERVICE BULLETIN 767-53A0267 ALERT ALERTMore Data Hole Dia Qty Identification Name Code

- 0.325-0.328 14 BACB30MY10K8X BOLT, PROTRUDING HD M

- - 14 BACC30M10 COLLAR

- 0.325-0.328 8 BACB30MY10K10X BOLT, PROTRUDING HD N

- - 8 BACC30M10 COLLAR

- 0.388-0.391 2 BACB30MY12K6X BOLT, PROTRUDING HD O

- - 2 BACC30M12 COLLAR

- 0.388-0.391 4 BACB30MY12K7X BOLT, PROTRUDING HD P

- - 4 BACC30M12 COLLAR (b) 0.388-0.391 4 BACB30MY12K8X BOLT, PROTRUDING HD Q (b) - 4 BACC30M12 COLLAR (b) 0.388-0.391 4 BACB30MY12K10X BOLT, PROTRUDING HD R (b) - 4 BACC30M12 COLLAR

- 0.325-0.328 2 BACB30NX10K8X BOLT, PROTRUDING HD S

- - 2 BACC30BH10 COLLAR

- 0.325-0.328 2 BACB30NX10K9X BOLT, PROTRUDING HD T

- - 2 BACC30BH10 COLLAR (b) 0.325-0.328 4 BACB30NX10K11X BOLT, PROTRUDING HD U (b) - 4 BACC30BH10 COLLAR (b) 0.325-0.328 4 BACB30NX10K12X BOLT, PROTRUDING HD V (b) - 4 BACC30BH10 COLLAR (b) 0.388-0.391 4 BACB30NX12K12X BOLT, PROTRUDING HD W (b) - 4 BACC30BH12 COLLAR

- - 5 BACR15FV7KE7 RIVET X

- - 1 BACR15FV7KE8 RIVET Y
FIGURE 14: RIGHT STA 1809.5 CENTER BULKHEAD INSTALLATION (SHEET 10 OF 12) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 13, 2015 767-53A0267 Revision 1 August 04, 2016 131 of 206 BOEING SERVICE BULLETIN 767-53A0267 ALERT ALERTMore Data Hole Dia Qty Identification Name Code

- 0.263-0.266 2 BACB30NW8K5X BOLT, 100 DEG HEX DR Z

- - 2 BACC30M8 COLLAR (a) 0.263-0.266 2 BACB30NW8K7X BOLT, 100 DEG HEX DR AA (a) - 2 BACC30M8 COLLAR (a) 0.263-0.266 4 BACB30NW8K8X BOLT, 100 DEG HEX DR AB (a) - 4 BACC30M8 COLLAR (a) 0.263-0.266 4 BACB30NW8K13X BOLT, 100 DEG HEX DR AC (a) - 4 BACC30M8 COLLAR (a) If the repair or modification given in Service Bulletin 767-53A0078 was previously installed, install new fasteners of the same type and size specified in Service Bulletin 767-53A0078, FAA AD 2005-11-02 or approved AMOC instead of the fasteners specified in this table. If any fastener holes have been damaged and the fasteners specified in 767-53A0078, FAA AD 2005-11-02 or approved AMOC cannot be reinstalled, Contact The Boeing Company for repair instructions and do the repair. (b) Some of these fasteners may have been replaced in accordance with Service Bulletin 767-53A0131. If the repair given in Service Bulletin 767-53A0131 was previously installed, install new fasteners of the same type and size specified in Service Bulletin 767-53A0131, FAA AD 2011-14-02 or approved AMOC instead of the fasteners specified in this table. If any fastener holes have been damaged and the fasteners specified in 767-53A0131, FAA AD 2011-14-02 or approved AMOC cannot be reinstalled, Contact The Boeing Company for repair instructions and do the repair. The parts shown in the table below are provided as extra parts for this figure. MORE DATA QTY IDENTIFICATION NAME

- 2 148T0012-18 SHIM

- 2 BACC30BH10 COLLAR

- 14 BACC30M8 COLLAR The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure. MORE DATA FLAG NOTE The fasteners in this area may have been replaced with oversize fasteners as part of the repair or modification in Service Bulletin 767-53A0078, "Fuselage - Section 48 - Body Station 1809.5 Bulkhead Outer Chord Inspection, Repair, and Modification". 1

FIGURE 14: RIGHT STA 1809.5 CENTER BULKHEAD INSTALLATION (SHEET 11 OF 12) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 13, 2015 767-53A0267 Revision 1 August 04, 2016 132 of 206 BOEING SERVICE BULLETIN 767-53A0267 ALERT ALERTMORE DATA FLAG NOTE The fasteners in this area may have been replaced with oversize fasteners as part of the repair in Boeing Service Bulletin 767- 53A0131, "Fuselage - Section 48 - Main Frame and Skins - STA 1809.5 Bulkhead - Forward Outer Chord, Horizontal and Vertical Inner Chord, and External Skin - Inspection". 2

FIGURE 14: RIGHT STA 1809.5 CENTER BULKHEAD INSTALLATION (SHEET 12 OF 12) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 13, 2015 767-53A0267 Revision 1 August 04, 2016 133 of 206 BOEING SERVICE BULLETIN 767-53A0267 ALERT ALERTFIGURE 15: AFT SECTION 48 (TAIL CONE) INSTALLATION (SHEET 1 OF 5) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 13, 2015 767-53A0267 Revision 1 August 04, 2016 134 of 206 BOEING SERVICE BULLETIN 767-53A0267 ALERT ALERTThe step numbers shown below agree with the numbers as applicable shown in the circle symbols in the figure or related drawing sheet(s) shown in the figure. The QTY numbers shown below are the number of parts necessary for each airplane. REQUIREMENTS: 1. Some of the fastener locations identified in this figure may have been changed from the original delivered configuration during the inspection, repair, or modification given in Boeing Service Bulletin 767-53A0078, "Fuselage - Section 48 - Body Station 1809.5 Bulkhead Outer Chord Inspection, Repair, and Modification." An Alternative Method of Compliance (AMOC) to the requirements of the applicable Airworthiness Directive may have been granted for configurations different than those shown in Boeing Service Bulletin 767-53A0078. These fastener locations must be maintained to the requirements of FAA AD 2005-11-02 or to an approved AMOC to that AD. When fasteners are removed from these locations, document the fastener/nut/collar diameter, grip and type removed and the existing fastener hole diameter. Use care to not damage the fastener hole when removing fasteners. Do not clean the bores of these fastener holes with brass bottle brushes. Do an open-hole High Frequency Eddy Current (HFEC) inspection at all parts in the stack-up at these locations. Verify that there are no surface defects (such as rifling, gouging, nicks, burrs, or excessive surface roughness) in the bores of these fastener holes, other than that normally produced during a typical reaming operation. If any defect is found, contact The Boeing Company for repair instructions and do the repair. Verify that washers or fillet relief exists to accommodate the fasteners head-to-shank fillet radius. When fasteners are installed, use the same type and size fasteners that were removed earlier. 2. Some of the fastener locations identified in this figure may have been changed from the original delivered configuration during the inspection, repair, or modification given in Boeing Service Bulletin 767-53A0131, "Fuselage - Section 48 - Main Frame and Skins - STA 1809.5 Bulkhead - Forward Outer Chord, Horizontal and Vertical Inner Chord, and External Skin - Inspection." An Alternative Method of Compliance (AMOC) to the requirements of the applicable Airworthiness Directive may have been granted for configurations different than those shown in Boeing Service Bulletin 767-53A0131. These fastener locations must be maintained to the requirements of FAA AD 2011-14-02 or to an approved AMOC to that AD. When fasteners are removed from these locations, document the fastener/nut/collar diameter, grip and type removed and the existing fastener hole diameter. Use care to not damage the fastener hole when removing fasteners. Do not clean the bores of these fastener holes with brass bottle brushes. Do an open-hole High Frequency Eddy Current (HFEC) inspection at all parts in the stack-up at these locations. Verify that there are no surface defects (such as rifling, gouging, nicks, burrs, or excessive surface roughness) in the bores of these fastener holes, other than that normally produced during a typical reaming operation. If any defect is found, contact The Boeing Company for repair instructions and do the repair. Verify that washers or fillet relief exists to accommodate the fasteners head-to-shank fillet radius. When fasteners are installed, use the same type and size fasteners that were removed earlier. However, Boeing recommends that H-11 steel bolts be replaced with Inconel bolts. Refer to Boeing Service Letter 767-SL-51-008-B More Data Qty Identification Name Task Step Refer to the fastener data table. 288 - Fastener Install (New) 1

FIGURE 15: AFT SECTION 48 (TAIL CONE) INSTALLATION (SHEET 2 OF 5) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 13, 2015 767-53A0267 Revision 1 August 04, 2016 135 of 206 BOEING SERVICE BULLETIN 767-53A0267 ALERT ALERTThe codes shown below agree with the letter shown in the upper left corner of the fastener symbols in the figure. A number in the lower right corner gives the grip length of the fastener. The QTY numbers shown below are the number of fasteners necessary for this figure. More Data Hole Dia Qty Identification Name Code

- 0.312-0.316 10 BACB30LT5-12 BOLT, 12 PT HEAD A under bolt head - 10 BACW10BP5CD CSK WASHER under nut - 10 BACW10BP5DP WASHER-PLAIN

- - 10 BACN10JC5CD SELF-LOCKING NUT

- 0.437-0.442 8 BACB30LT7-12 BOLT, 12 PT HEAD B under bolt head - 8 BACW10BP7CD WASHER under nut - 8 BACW10BP7DP WASHER

- - 8 BACN10JC7CD SELF-LOCKING NUT (a) 0.250-0.254 8 BACB30NX8K5 HI LOK C (a) - 8 BACC30BH8 COLLAR (a) 0.250-0.254 76 BACB30NX8K7 BOLT, HEX DRIVE D (a) - 76 BACC30BH8 COLLAR (a) 0.312-0.316 54 BACB30NX10K7 BOLT E (a) - 54 BACC30BH10 COLLAR (a) (b) 0.312-0.316 44 BACB30NX10K10 HEX DRIVE BOLT F (a) (b) - 44 BACC30BH10 COLLAR

- 0.778-0.797 4 BACB30US12K37 BOLT, 12 PT HEAD G under bolt head - 4 BACW10BP12CD WASHER, PLAIN under nut - 4 BACW10BP12DP WASHER, PLAIN

- - 4 BACN10HR12CD SELF-LOCKING NUT FIGURE 15: AFT SECTION 48 (TAIL CONE) INSTALLATION (SHEET 3 OF 5) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 13, 2015 767-53A0267 Revision 1 August 04, 2016 136 of 206 BOEING SERVICE BULLETIN 767-53A0267 ALERT ALERTMore Data Hole Dia Qty Identification Name Code

- 0.778-0.797 4 BACB30US12K40 BOLT, 12 PT HEAD H under bolt head - 4 BACW10BP12CD WASHER, PLAIN under nut - 4 BACW10BP12DP WASHER, PLAIN

- - 4 BACN10HR12CD SELF-LOCKING NUT

- 0.467-0.479 22 BACB30US7K24 BOLT, 12 PT HEAD I under bolt head - 22 BACW10BP7CD WASHER under nut - 22 BACW10BP7DP WASHER

- - 22 BACN10HR7CD NUT

- 0.467-0.479 2 BACB30US7K26 BOLT, 12 PT HEAD J under bolt head - 2 BACW10BP7CD WASHER under nut - 2 BACW10BP7DP WASHER

- - 2 BACN10HR7CD NUT (b) 0.467-0.479 32 BACB30US7K28 BOLT, 12 PT HEAD K under bolt head (b) - 32 BACW10BP7CD WASHER under bolt head (b) - 32 BACW10BP7DP WASHER (b) - 32 BACN10HR7CD NUT

- 0.500-0.505 2 BACB30US8K31 BOLT, 12 PT HEAD L under bolt head - 2 148T2746-1 washer under nut - 2 BACW10BP8DP WASHER

- - 2 BACN10HR8CD NUT

- 0.500-0.505 2 BACB30US8K31 BOLT, 12 PT HEAD M under bolt head - 2 148T2746-2 filler under nut - 2 BACW10BP8DP WASHER

- - 2 BACN10HR8CD NUT

- - 8 BACB30NX6K5 BOLT N

- - 8 BACC30BH6 COLLAR

- - 8 BACB30NX14K16 BOLT O

- - 8 BACC30BH14 COLLAR, PRELOAD

FIGURE 15: AFT SECTION 48 (TAIL CONE) INSTALLATION (SHEET 4 OF 5) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 13, 2015 767-53A0267 Revision 1 August 04, 2016 137 of 206 BOEING SERVICE BULLETIN 767-53A0267 ALERT ALERTMore Data Hole Dia Qty Identification Name Code

- 0.467-0.479 4 BACB30US7K27 BOLT, 12 PT HEAD P under bolt head - 4 BACW10BP7CD WASHER under nut - 4 BACW10BP7DP WASHER

- - 4 BACN10HR7CD NUT (a) Flag Note 1 regions only: If the repair or modification given in Boeing Service Bulletin 767-53A0078 was previously installed, install new fasteners of the same type and size as specified in Boeing Service Bulletin 767-53A0078, FAA AD 2005-11-02 or approved AMOC instead of the fasteners specified in this table. If any of these fastener holes have been damaged and the fasteners specified in Boeing Service Bulletin767-53A0078, FAA AD 2005-11-02 or approved AMOC cannot be reinstalled, Contact The Boeing Company for repair instructions and do the repair. (b) Flag Note 2 regions only: If the repair given in Boeing Service Bulletin 767-53A0131 was previously installed, install new fasteners of the same type and size as specified in Boeing Service Bulletin 767-53A0131, FAA AD 2011-14-02 or approved AMOC instead of the fasteners specified in this table. If any of these fastener holes have been damaged and the fasteners specified in Boeing Service Bulletin 767-53A0131 , FAA AD 2011-14-02 or approved AMOC cannot be reinstalled, Contact The Boeing Company for repair instructions and do the repair. The parts shown in the table below are provided as extra parts for this figure. MORE DATA QTY IDENTIFICATION NAME

- 2 BACB30US8K30 BOLT, 12 PT HEAD

- 9 BACC30BH10 COLLAR

- 2 BACW10BP5DP WASHER-PLAIN The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure. MORE DATA FLAG NOTE The fasteners in this area may have been replaced with oversize fasteners as part of the repair or modification in Service Bulletin 767-53A0078, "Fuselage - Section 48 - Body Station 1809.5 Bulkhead Outer Chord Inspection, Repair, and Modification". 1 The fasteners in this area may have been replaced with oversize fasteners as part of the repair in Boeing Service Bulletin 767- 53A0131, "Fuselage - Section 48 - Main Frame and Skins - STA 1809.5 Bulkhead - Forward Outer Chord, Horizontal and Vertical Inner Chord, and External Skin - Inspection". 2

FIGURE 15: AFT SECTION 48 (TAIL CONE) INSTALLATION (SHEET 5 OF 5) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 13, 2015 767-53A0267 Revision 1 August 04, 2016 138 of 206 BOEING SERVICE BULLETIN 767-53A0267 ALERT ALERTFIGURE 16: PRESSURE SEAL INSTALLATION (SHEET 1 OF 3) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 13, 2015 767-53A0267 Revision 1 August 04, 2016 139 of 206 BOEING SERVICE BULLETIN 767-53A0267 ALERT ALERTFIGURE 16: PRESSURE SEAL INSTALLATION (SHEET 2 OF 3) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 13, 2015 767-53A0267 Revision 1 August 04, 2016 140 of 206 BOEING SERVICE BULLETIN 767-53A0267 ALERT ALERTThe step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY numbers shown below are the number of parts necessary for each airplane. More Data Qty Identification Name Task Step 1 272T4830-2 RETAINER ASSY- Install (New) 1 3 270T0004-1101 SEAL Install (New) 2 1 270T0004-1102 SEAL Install (New) 3 1 272T4830-1 RETAINER- Install (New) 4 6 BACS12HN3-9 BOLT Install (New) 5 6 NAS1149D0316J WASHER Install (New) 16 BACS12HN3-9 BOLT Install (New) 6 16 NAS1149D0316J WASHER Install (New) 16 BACN10JC3CD NUT Install (New)

- BMS 5-95 Sealant Apply 7 The parts shown in the table below are provided as extra parts for this figure. MORE DATA QTY IDENTIFICATION NAME

- 2 BACN10JC3CD NUT

- 2 BACS12HN3-9 BOLT

- 2 NAS1149D0316J WASHER

FIGURE 16: PRESSURE SEAL INSTALLATION (SHEET 3 OF 3) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 13, 2015 767-53A0267 Revision 1 August 04, 2016 141 of 206 BOEING SERVICE BULLETIN 767-53A0267 ALERT ALERTFIGURE 17: INSTALLATION OF AUXILIARY PITOT SYSTEM TUBES AND PRESSURE SEALS (SHEET 1 OF 4) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 13, 2015 767-53A0267 Revision 1 August 04, 2016 142 of 206 BOEING SERVICE BULLETIN 767-53A0267 ALERT ALERTFIGURE 17: INSTALLATION OF AUXILIARY PITOT SYSTEM TUBES AND PRESSURE SEALS (SHEET 2 OF 4) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 13, 2015 767-53A0267 Revision 1 August 04, 2016 143 of 206 BOEING SERVICE BULLETIN 767-53A0267 ALERT ALERTFIGURE 17: INSTALLATION OF AUXILIARY PITOT SYSTEM TUBES AND PRESSURE SEALS (SHEET 3 OF 4) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 13, 2015 767-53A0267 Revision 1 August 04, 2016 144 of 206 BOEING SERVICE BULLETIN 767-53A0267 ALERT ALERTThe step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY numbers shown below are the number of parts necessary for each airplane. More Data Qty Identification Name Task Step 1 233T9110-566 TUBE ASSY Install (New) 1 1 233T9110-665 TUBE ASSEMBLY Install (New) 2

- 233T9110-566 TUBE ASSY Install (New) 3

- 233T9110-665 TUBE ASSEMBLY Route 1 233T9113-4 PLATER RETAINER Install (New) 4 1 69B41314-6 SEAL- Install (New) 5 1 233T9113-4 PLATER RETAINER Install (New) 6 8 BACB30LM3-3 BOLT Install (New) 7

- 233T9110-566 TUBE ASSY Connect 8

- 233T9110-665 TUBE ASSEMBLY Connect

- BMS 5-142 Sealant Apply 9 The parts shown in the table below are provided as extra parts for this figure. MORE DATA QTY IDENTIFICATION NAME

- 16 BACB30LM3-3 BOLT

- 10 BACC10DK6 CLAMP, LOOP

FIGURE 17: INSTALLATION OF AUXILIARY PITOT SYSTEM TUBES AND PRESSURE SEALS (SHEET 4 OF 4) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 13, 2015 767-53A0267 Revision 1 August 04, 2016 145 of 206 BOEING SERVICE BULLETIN 767-53A0267 ALERT ALERTFIGURE 18: MAKE AND INSTALL STA 1809.5 BULKHEAD STABILIZATION TOOLS (SHEET 1 OF 10) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 13, 2015 767-53A0267 Revision 1 August 04, 2016 146 of 206 BOEING SERVICE BULLETIN 767-53A0267 ALERT ALERTFIGURE 18: MAKE AND INSTALL STA 1809.5 BULKHEAD STABILIZATION TOOLS (SHEET 2 OF 10) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 13, 2015 767-53A0267 Revision 1 August 04, 2016 147 of 206 BOEING SERVICE BULLETIN 767-53A0267 ALERT ALERTFIGURE 18: MAKE AND INSTALL STA 1809.5 BULKHEAD STABILIZATION TOOLS (SHEET 3 OF 10) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 13, 2015 767-53A0267 Revision 1 August 04, 2016 148 of 206 BOEING SERVICE BULLETIN 767-53A0267 ALERT ALERTFIGURE 18: MAKE AND INSTALL STA 1809.5 BULKHEAD STABILIZATION TOOLS (SHEET 4 OF 10) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 13, 2015 767-53A0267 Revision 1 August 04, 2016 149 of 206 BOEING SERVICE BULLETIN 767-53A0267 ALERT ALERTFIGURE 18: MAKE AND INSTALL STA 1809.5 BULKHEAD STABILIZATION TOOLS (SHEET 5 OF 10) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 13, 2015 767-53A0267 Revision 1 August 04, 2016 150 of 206 BOEING SERVICE BULLETIN 767-53A0267 ALERT ALERTFIGURE 18: MAKE AND INSTALL STA 1809.5 BULKHEAD STABILIZATION TOOLS (SHEET 6 OF 10) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 13, 2015 767-53A0267 Revision 1 August 04, 2016 151 of 206 BOEING SERVICE BULLETIN 767-53A0267 ALERT ALERTFIGURE 18: MAKE AND INSTALL STA 1809.5 BULKHEAD STABILIZATION TOOLS (SHEET 7 OF 10) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 13, 2015 767-53A0267 Revision 1 August 04, 2016 152 of 206 BOEING SERVICE BULLETIN 767-53A0267 ALERT ALERTThe step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY numbers shown below are the number of parts necessary for each airplane. More Data Qty Identification Name Task Step From 6061-T6 aluminum alloy sheet, 0.125 inch thick. 1 A Plate Make 1 From 6061-T6 aluminum alloy sheet, 0.125 inch thick. 1 B Plate Make 2 From 6061-T6 aluminum angle or extrusion, 0.1875 inch thick. 6 C Angle Make 3
From 6061-T6 aluminum angle or extrusion, 0.1875 inch thick. 2 D Angle Make 4
From 6061-T6 aluminum angle or extrusion, 0.1875 inch thick. 2 E Angle Make 5

- 1 A Plate Install (New) 6

- 3 C Angle Install (New)

- 1 D Angle Install (New)

- 1 E Angle Install (New) Mark the aft side of the tool and place orientation arrows on the aft side of the tool. - - Left STA 1809.5 Bulk- head Tool Identify

Mark the tool as the left 1809.5 bulkhead stabilization tool. 1 - Left STA 1809.5 Bulk- head Tool Identify

FIGURE 18: MAKE AND INSTALL STA 1809.5 BULKHEAD STABILIZATION TOOLS (SHEET 8 OF 10) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 13, 2015 767-53A0267 Revision 1 August 04, 2016 153 of 206 BOEING SERVICE BULLETIN 767-53A0267 ALERT ALERTMore Data Qty Identification Name Task Step

- 1 B Plate Install (New) 7

- 3 C Angle Install (New)

- 1 D Angle Install (New)

- 1 E Angle Install (New) Mark the tool as theright 1809.5 bulkhead stabilization tool. 1 - Right STA 1809.5 Bulk- head Tool Identify
Mark the aft side of the tool and place orientation arrows on the aft side of the tool. - - Right STA 1809.5 Bulk- head Tool Identify

Attach the tool to the upper and lowerSTA 1809.5 bulkhead using temporary fasteners. 1 - Left STA 1809.5 Bulk- head Tool Attach 8

- 8 - Temporary Fastener Install (New) Attach the tool to the upper and lowerSTA 1809.5 bulkhead using temporary fasteners. 1 - Right STA 1809.5 Bulk- head Tool Attach 9

- 8 - Temporary Fastener Install (New)

FIGURE 18: MAKE AND INSTALL STA 1809.5 BULKHEAD STABILIZATION TOOLS (SHEET 9 OF 10) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 13, 2015 767-53A0267 Revision 1 August 04, 2016 154 of 206 BOEING SERVICE BULLETIN 767-53A0267 ALERT ALERTThe codes shown below agree with the letter shown in the upper left corner of the fastener symbols in the figure. A number in the lower right corner gives the grip length of the fastener. The QTY numbers shown below are the number of fasteners necessary for this figure. NOTE:The fasteners identified in the table below are for reference only. Any available lock bolt/collar combination of the specified size is an acceptable substitute. More Data Hole Dia Qty Identification Name Code

- - 120 BACB30NX6K5 Bolt A

- - 120 BACC30BH6SW Collar

- - 18 BACB30NX6K8 Bolt B

- - 18 BACC30BH6SW Collar

FIGURE 18: MAKE AND INSTALL STA 1809.5 BULKHEAD STABILIZATION TOOLS (SHEET 10 OF 10) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 13, 2015 767-53A0267 Revision 1 August 04, 2016 155 of 206 BOEING SERVICE BULLETIN 767-53A0267 ALERT ALERTFIGURE 19: REMOVE STA 1809.5 BULKHEAD STABILIZATION TOOLS (SHEET 1 OF 2) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 13, 2015 767-53A0267 Revision 1 August 04, 2016 156 of 206 BOEING SERVICE BULLETIN 767-53A0267 ALERT ALERTThe step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY numbers shown below are the number of parts necessary for each airplane. More Data Qty Identification Name Task Step

- 8 - Temporary Fastener Remove 1

- 1 - Left STA 1809.5 Bulk- head Tool Remove

- 8 - Temporary Fastener Remove 2

- 1 - Right STA 1809.5 Bulk- head Tool Remove

FIGURE 19: REMOVE STA 1809.5 BULKHEAD STABILIZATION TOOLS (SHEET 2 OF 2) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 13, 2015 767-53A0267 Revision 1 August 04, 2016 157 of 206 BOEING SERVICE BULLETIN 767-53A0267 ALERT ALERTFIGURE 20: STA 1582 FLOOR BEAM DETACHMENT (SHEET 1 OF 4) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 13, 2015 767-53A0267 Revision 1 August 04, 2016 158 of 206 BOEING SERVICE BULLETIN 767-53A0267 ALERT ALERTFIGURE 20: STA 1582 FLOOR BEAM DETACHMENT (SHEET 2 OF 4) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 13, 2015 767-53A0267 Revision 1 August 04, 2016 159 of 206 BOEING SERVICE BULLETIN 767-53A0267 ALERT ALERTFIGURE 20: STA 1582 FLOOR BEAM DETACHMENT (SHEET 3 OF 4) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 13, 2015 767-53A0267 Revision 1 August 04, 2016 160 of 206 BOEING SERVICE BULLETIN 767-53A0267 ALERT ALERTThe step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY numbers shown below are the number of parts necessary for each airplane. NOTE:Before removing any fasteners from the floor beams or stanchions, establish the STA 1582 floor beam Water Line datum. This datum must be established to ensure that when the STA 1582 floor beam is reattached it has not been deflected up or down, which can alter the aft galley monument shimming/joint requirements. Several different methods can be used to verify and maintain this datum. Possible methods include: 1. Optical planizer; 2. Projection of WL datum using multiple floor beams forward of STA 1582 using a straight edge at a minimum of two locations; 3. Application of witness marks (using acceptable non-damaging marks that may be removed by cleaning after the floor beam has been reattached) at the positions of the STA 1582 floor beam upper and lower chords and the inboard and outboard flanges of the stanchions on the forward surface of the frame segments (attached to the Section 46 skin panels). More Data Qty Identification Name Task Step

- 21 - Fastener Remove 1 If installed. 1 - Shim Remove

- 8 - Fastener Remove 2

- 21 - Fastener Remove 3 If installed. 1 - Shim Remove

- 12 - Fastener Remove 4

FIGURE 20: STA 1582 FLOOR BEAM DETACHMENT (SHEET 4 OF 4) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 13, 2015 767-53A0267 Revision 1 August 04, 2016 161 of 206 BOEING SERVICE BULLETIN 767-53A0267 ALERT ALERTFIGURE 21: STA 1582 FLOOR BEAM SUPPORT (SHEET 1 OF 3) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 13, 2015 767-53A0267 Revision 1 August 04, 2016 162 of 206 BOEING SERVICE BULLETIN 767-53A0267 ALERT ALERTFIGURE 21: STA 1582 FLOOR BEAM SUPPORT (SHEET 2 OF 3) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 13, 2015 767-53A0267 Revision 1 August 04, 2016 163 of 206 BOEING SERVICE BULLETIN 767-53A0267 ALERT ALERTThe step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY numbers shown below are the number of parts necessary for each airplane. NOTE:Before installing the supports shown in this figure, make sure that the STA 1582 floor beam is aligned with the WL datum established prior to floor beam detachment in accordance with FIGURE 20. More Data Qty Identification Name Task Step From 6061-T6 aluminum, 0.5 inch thick. 2 F Plate Make 1 From 6061-T6 aluminum, at least 0.5 inch thick. Each flange should be at least 4 inches wide and 4 inches deep. 2 G Angle Make 2

On the left side. (a) 1 F Plate Install (New) 3 On the left side. (b) 1 G Angle Install (New) 4 On the right side. (a) 1 F Plate Install (New) 5 On the right side. (b) 1 G Angle Install (New) 6 (a) Make 0.312 - 0.316 inch diameter holes to match fastener locations 102, 103, 110, 111, and 117 in theSTA 1582 forward chord. Attach the plate to the STA 1582 forward chord with temporary 5/16 inch diameter fasteners. Make sure that no fastener threads are in bearing common to the STA 1582 frame segments. (b) Place the vertical flange of the angle against the plate, and the horizontal flange of the angle against the lower chord of the STA 1582 floor beam and clamp in place. Attach the angle to the plate using a minimum of four 1/4 inch diameter bolts.

FIGURE 21: STA 1582 FLOOR BEAM SUPPORT (SHEET 3 OF 3) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 13, 2015 767-53A0267 Revision 1 August 04, 2016 164 of 206 BOEING SERVICE BULLETIN 767-53A0267 ALERT ALERTFIGURE 22: STA 1582 FLOOR BEAM ATTACHMENT (SHEET 1 OF 5) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 13, 2015 767-53A0267 Revision 1 August 04, 2016 165 of 206 BOEING SERVICE BULLETIN 767-53A0267 ALERT ALERTFIGURE 22: STA 1582 FLOOR BEAM ATTACHMENT (SHEET 2 OF 5) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 13, 2015 767-53A0267 Revision 1 August 04, 2016 166 of 206 BOEING SERVICE BULLETIN 767-53A0267 ALERT ALERTFIGURE 22: STA 1582 FLOOR BEAM ATTACHMENT (SHEET 3 OF 5) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 13, 2015 767-53A0267 Revision 1 August 04, 2016 167 of 206 BOEING SERVICE BULLETIN 767-53A0267 ALERT ALERTThe step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY numbers shown below are the number of parts necessary for each airplane. NOTE:Before attaching the STA 1582 floor beam to the aft pressure bulkhead inner chord, make sure that the STA 1582 floor beam is aligned with the WL datum established prior to floor beam detachment in accordance with FIGURE 20. More Data Qty Identification Name Task Step If necessary. (a) 1 BACS40R040C095F SHIM, LAMINATED Install (New) 1

- 21 - Hole Drill / Ream

- 21 - Fastener Install (New)

- 8 - Hole Drill / Ream 2

- 8 - Fastener Install (New) If necessary. (a) 1 BACS40R040C095F SHIM, LAMINATED Install (New) 3

- 21 - Hole Drill / Ream

- 21 - Fastener Install (New)

- 12 - Hole Drill / Ream 4

- 12 - Fastener Install (New) (a) Remove solid section or laminations as necessary. Maximum gap without a shim is 0.02 inch. Maximum thickness of the laminated section of the shim is 0.02 inch. Maximum total shim thickness is 0.06 inch. After thickness adjustment, apply chemical film treatment to bare aluminum surfaces and apply one coat of BMS 10-11, Type I primer.

The codes shown below agree with the letter shown in the upper left corner of the fastener symbols in the figure. A number in the lower right corner gives the grip length of the fastener. The QTY numbers shown below are the number of fasteners necessary for this figure.

FIGURE 22: STA 1582 FLOOR BEAM ATTACHMENT (SHEET 4 OF 5) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 13, 2015 767-53A0267 Revision 1 August 04, 2016 168 of 206 BOEING SERVICE BULLETIN 767-53A0267 ALERT ALERTMore Data Hole Dia Qty Identification Name Code

- 0.263-0.266 22 BACB30NX8K5X BOLT, PROTRUDING HD A

- - 22 BACC30BH8 COLLAR

- 0.263-0.266 6 BACB30NX8K6X BOLT, PROTRUDING HD B

- - 6 BACC30BH8 COLLAR

- 0.263-0.266 14 BACB30NX8K7X BOLT, PROTRUDING HD C

- - 14 BACC30BH8 COLLAR

- 0.200-0.203 3 BACB30NX6K4X BOLT, PROTRUDING HD D

- - 3 BACC30M6 COLLAR

- 0.200-0.203 5 BACB30NX6K6X BOLT, PROTRUDING HD E

- - 5 BACC30M6 COLLAR

- 0.263-0.266 12 BACB30MY8K4X BOLT, PROTRUDING HD F

- - 12 BACC30M8 COLLAR

FIGURE 22: STA 1582 FLOOR BEAM ATTACHMENT (SHEET 5 OF 5) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 13, 2015 767-53A0267 Revision 1 August 04, 2016 169 of 206 BOEING SERVICE BULLETIN 767-53A0267 ALERT ALERTFIGURE 23: LEFT SIDE HORIZONTAL STABILIZER FAIRING SKIN REMOVAL (SHEET 1 OF 3) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 13, 2015 767-53A0267 Revision 1 August 04, 2016 170 of 206 BOEING SERVICE BULLETIN 767-53A0267 ALERT ALERTFIGURE 23: LEFT SIDE HORIZONTAL STABILIZER FAIRING SKIN REMOVAL (SHEET 2 OF 3) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 13, 2015 767-53A0267 Revision 1 August 04, 2016 171 of 206 BOEING SERVICE BULLETIN 767-53A0267 ALERT ALERTThe 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 (a) 8 - Fastener Remove 1

- 1 - SKIN - CHEM MILLED Remove / Keep (c) 6 - Fastener Remove 2 (b) 13 - Fastener Remove 3

- 1 - SKIN - CHEM MILLED Remove / Keep 4

- 1 - SKIN - CHEM MILLED Remove / Keep (a) Remove fasteners common to the upper aft fairing skin panel and chord. (b) Remove fasteners common to the lower aft fairing skin panel and cord. (c) Remove and keep fasteners common to the lower aft fairing skin panels.

FIGURE 23: LEFT SIDE HORIZONTAL STABILIZER FAIRING SKIN REMOVAL (SHEET 3 OF 3) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 13, 2015 767-53A0267 Revision 1 August 04, 2016 172 of 206 BOEING SERVICE BULLETIN 767-53A0267 ALERT ALERTFIGURE 24: LEFT SIDE HORIZONTAL STABILIZER FAIRING SKIN INSTALLATION (SHEET 1 OF 4) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 13, 2015 767-53A0267 Revision 1 August 04, 2016 173 of 206 BOEING SERVICE BULLETIN 767-53A0267 ALERT ALERTFIGURE 24: LEFT SIDE HORIZONTAL STABILIZER FAIRING SKIN INSTALLATION (SHEET 2 OF 4) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 13, 2015 767-53A0267 Revision 1 August 04, 2016 174 of 206 BOEING SERVICE BULLETIN 767-53A0267 ALERT ALERTThe 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. NOTE:Install fasteners wet with BMS 5-95 sealant. More Data Qty Identification Name Task Step

- 1 - SKIN - CHEM MILLED Install (Kept) 1 (a) 8 - Fastener Install (New)

- 1 - SKIN - CHEM MILLED Install (Kept) 2

- 1 - SKIN - CHEM MILLED Install (Kept) (b) 6 - Fastener Install (New) 3

- 13 - Fastener Install (New) 4 (a) Install fasteners common to the upper aft fairing skin panel and chord. (b) Install fasteners common to the upper aft fairing skin panel and chord.

The codes shown below agree with the letter shown in the upper left corner of the fastener symbols in the figure. A number in the lower right corner gives the grip length of the fastener. The QTY numbers shown below are the number of fasteners necessary for this figure. More Data Hole Dia Qty Identification Name Code

- 0.263-0.266 6 BACB30NW8K8X BOLT, 100 DEG HEX DR A

- - 6 BACC30M8 COLLAR

- - 2 BACR15FT5KE9C RIVET, UNIVERSAL HD B

- - 5 BACR15FV6KE7 RIVET C

- - 1 BACR15FV6KE8 RIVET D

FIGURE 24: LEFT SIDE HORIZONTAL STABILIZER FAIRING SKIN INSTALLATION (SHEET 3 OF 4) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 13, 2015 767-53A0267 Revision 1 August 04, 2016 175 of 206 BOEING SERVICE BULLETIN 767-53A0267 ALERT ALERTMore Data Hole Dia Qty Identification Name Code Apply 18 - 25 in-lbs of torque. - 10 BACB30VF3K5 BOLT, 100 DEG HEAD E Apply 18 - 25 in-lbs of torque. - 3 BACB30VF3K7 BOLT F

FIGURE 24: LEFT SIDE HORIZONTAL STABILIZER FAIRING SKIN INSTALLATION (SHEET 4 OF 4) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 13, 2015 767-53A0267 Revision 1 August 04, 2016 176 of 206 BOEING SERVICE BULLETIN 767-53A0267 ALERT ALERTFIGURE 25: RIGHT SIDE HORIZONTAL STABILIZER FAIRING SKIN REMOVAL (SHEET 1 OF 3) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 13, 2015 767-53A0267 Revision 1 August 04, 2016 177 of 206 BOEING SERVICE BULLETIN 767-53A0267 ALERT ALERTFIGURE 25: RIGHT SIDE HORIZONTAL STABILIZER FAIRING SKIN REMOVAL (SHEET 2 OF 3) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 13, 2015 767-53A0267 Revision 1 August 04, 2016 178 of 206 BOEING SERVICE BULLETIN 767-53A0267 ALERT ALERTThe 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

- 8 - Fastener Remove 1 (a) 1 - SKIN - CHEM MILLED Remove / Keep

- 6 - Fastener Remove 2

- 13 - Fastener Remove 3 (b) 1 - SKIN - CHEM MILLED Remove / Keep 4 (b) 1 - SKIN - CHEM MILLED Remove / Keep (a) These are the Upper Aft Fairing Skin. (b) These fairing skin panels are fastened together. These are the Lower Aft Fairing Skin.

FIGURE 25: RIGHT SIDE HORIZONTAL STABILIZER FAIRING SKIN REMOVAL (SHEET 3 OF 3) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 13, 2015 767-53A0267 Revision 1 August 04, 2016 179 of 206 BOEING SERVICE BULLETIN 767-53A0267 ALERT ALERTFIGURE 26: RIGHT SIDE HORIZONTAL STABILIZER FAIRING SKIN INSTALLATION (SHEET 1 OF 3) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 13, 2015 767-53A0267 Revision 1 August 04, 2016 180 of 206 BOEING SERVICE BULLETIN 767-53A0267 ALERT ALERTFIGURE 26: RIGHT SIDE HORIZONTAL STABILIZER FAIRING SKIN INSTALLATION (SHEET 2 OF 3) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 13, 2015 767-53A0267 Revision 1 August 04, 2016 181 of 206 BOEING SERVICE BULLETIN 767-53A0267 ALERT ALERTThe 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. NOTE:Install fasteners wet with BMS 5-95 sealant. More Data Qty Identification Name Task Step

- 1 - SKIN - CHEM MILLED Install (Kept) 1 (a) 8 - Fastener Install (New)

- 1 - SKIN - CHEM MILLED Install (Kept) 2

- 1 - SKIN - CHEM MILLED Install (Kept) (b) 6 - Fastener Install (New) 3

- 13 - Fastener Install (New) 4 (a) Install fasteners common to the upper aft fairing skin panel and chord. (b) Install fasteners common to the lower aft fairing skin panel and chord. The codes shown below agree with the letter shown in the upper left corner of the fastener symbols in the figure. A number in the lower right corner gives the grip length of the fastener. The QTY numbers shown below are the number of fasteners necessary for this figure. More Data Hole Dia Qty Identification Name Code

- 0.263-0.266 6 BACB30NW8K8X BOLT, 100 DEG HEX DR A

- - 6 BACC30M8 COLLAR

- - 2 BACR15FT5KE9C RIVET, UNIVERSAL HD B

- - 5 BACR15FV6KE7 RIVET C

- - 1 BACR15FV6KE8 RIVET D Apply 18 - 25 in-lbs of torque. - 10 BACB30VF3K5 BOLT, 100 DEG HEAD E Apply 18 - 25 in-lbs of torque. - 3 BACB30VF3K7 BOLT F

FIGURE 26: RIGHT SIDE HORIZONTAL STABILIZER FAIRING SKIN INSTALLATION (SHEET 3 OF 3) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 13, 2015 767-53A0267 Revision 1 August 04, 2016 182 of 206 BOEING SERVICE BULLETIN 767-53A0267 ALERT ALERTFIGURE 27: PREPARATION OF THE VERTICAL FIN (SHEET 1 OF 7) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 13, 2015 767-53A0267 Revision 1 August 04, 2016 183 of 206 BOEING SERVICE BULLETIN 767-53A0267 ALERT ALERTFIGURE 27: PREPARATION OF THE VERTICAL FIN (SHEET 2 OF 7) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 13, 2015 767-53A0267 Revision 1 August 04, 2016 184 of 206 BOEING SERVICE BULLETIN 767-53A0267 ALERT ALERTFIGURE 27: PREPARATION OF THE VERTICAL FIN (SHEET 3 OF 7) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 13, 2015 767-53A0267 Revision 1 August 04, 2016 185 of 206 BOEING SERVICE BULLETIN 767-53A0267 ALERT ALERTFIGURE 27: PREPARATION OF THE VERTICAL FIN (SHEET 4 OF 7) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 13, 2015 767-53A0267 Revision 1 August 04, 2016 186 of 206 BOEING SERVICE BULLETIN 767-53A0267 ALERT ALERTFIGURE 27: PREPARATION OF THE VERTICAL FIN (SHEET 5 OF 7) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 13, 2015 767-53A0267 Revision 1 August 04, 2016 187 of 206 BOEING SERVICE BULLETIN 767-53A0267 ALERT ALERTThe 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 (a) (e) - BMS 3-38 (BMS 3-27 OPTIONAL) Corrosion Inhibiting Compound Apply 1 (b) - - Alignment Pins Locate 2 Install with the fastener head against the body bulkhead surface (f) 4 - Bolt Install (Temporary) 3

- 4 - Barrel Nut Install (Temporary) (c) 8 - Fastener Install (Temporary) 4 (d) - - Crane Sling Remove 5 (a) APPLY 0.001-0.005 INCHES OF BMS3-38 TO BASE OF VERTICAL FIN. (SOPM 20-41-01 states: Applya thin layer of BMS 3-38 corrosion inhibiting compound to indicated surfaces). During installation, squeezeout of corrosion inhibiting compound is allowed, but not required. (b) Lower the vertical fin using the alignment pins and L-pins to position the fin and set it on the fuselage. (c) Install hex head bolts or similar to BACB30NF() or BACB30NM(). Use non self locking compatible nuts. No shimming required, torque to 50/65 inch-lb. (d) Remove all vertical tension from the crane sling. Visually review the fin attach angle hole pattern for correct alignment with the fastener holes in the fin deck of the fuselage. If the holes are aligned correctly, remove the crane sling. If necessary, restore vertical tension to the crane sling and reposition the vertical fin until fastener holes are correctly aligned. If this is required, all temporary bolts must be removed before lifting the fin. (e) Use shims kept during removal of the vertical fin. If kept shims are no longer serviceable, replace with new shims. (f) The purpose of having these bolts installed now is to safely ensure the vertical fin remains in position during bolt/barrel nut and hi-lok installation process given in Figure 28. The bolts which were removed during vertical fin removal process can be re-used for this temporary installation. Do not use new bolts and barrel nuts in the kit for this temporary installation to prevent damage to the new bolts and barrel nuts prior to installation.

FIGURE 27: PREPARATION OF THE VERTICAL FIN (SHEET 6 OF 7) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 13, 2015 767-53A0267 Revision 1 August 04, 2016 188 of 206 BOEING SERVICE BULLETIN 767-53A0267 ALERT ALERTThe codes shown below agree with the letter shown in the upper left corner of the fastener symbols in the figure. A number in the lower right corner gives the grip length of the fastener. The QTY numbers shown below are the number of fasteners necessary for this figure. More Data Hole Dia Qty Identification Name Code 1,000 - 1,100 in-lbs torque - 2 - BOLT, 12 PT HEAD A

- - 2 - WASHER, PLAIN

- - 2 - WASHER

- - 2 - BARREL NUT 1,000 - 1,100 in-lbs torque - 1 - BOLT, 12 PT HEAD B

- - 1 - WASHER, PLAIN

- - 1 - WASHER

- - 1 - BARREL NUT 1,000 - 1,100 in-lbs torque - 1 - BOLT, 12 PT HEAD C

- - 1 - WASHER, PLAIN

- - 1 - WASHER

- - 1 - BARREL NUT

FIGURE 27: PREPARATION OF THE VERTICAL FIN (SHEET 7 OF 7) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 13, 2015 767-53A0267 Revision 1 August 04, 2016 189 of 206 BOEING SERVICE BULLETIN 767-53A0267 ALERT ALERTFIGURE 28: INSTALLATION OF THE VERTICAL FIN (SHEET 1 OF 9) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 13, 2015 767-53A0267 Revision 1 August 04, 2016 190 of 206 BOEING SERVICE BULLETIN 767-53A0267 ALERT ALERTFIGURE 28: INSTALLATION OF THE VERTICAL FIN (SHEET 2 OF 9) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 13, 2015 767-53A0267 Revision 1 August 04, 2016 191 of 206 BOEING SERVICE BULLETIN 767-53A0267 ALERT ALERTFIGURE 28: INSTALLATION OF THE VERTICAL FIN (SHEET 3 OF 9) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 13, 2015 767-53A0267 Revision 1 August 04, 2016 192 of 206 BOEING SERVICE BULLETIN 767-53A0267 ALERT ALERTFIGURE 28: INSTALLATION OF THE VERTICAL FIN (SHEET 4 OF 9) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 13, 2015 767-53A0267 Revision 1 August 04, 2016 193 of 206 BOEING SERVICE BULLETIN 767-53A0267 ALERT ALERTFIGURE 28: INSTALLATION OF THE VERTICAL FIN (SHEET 5 OF 9) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 13, 2015 767-53A0267 Revision 1 August 04, 2016 194 of 206 BOEING SERVICE BULLETIN 767-53A0267 ALERT ALERTThe 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 (a) - - Fin Terminal Fittings Inspect 1 (b) - BMS 5-95 Sealant Apply 2 1000-1100 in-lbs torque. This is an initial torque (c) 8 - Bolt Install (New) 3

- 8 - Barrel Nut Install (New) (d) - - Shear Fastener Loca- tions Inspect 4 (e) - - Fastener Hole Ream 5

- - - Fastener Hole Deburr (f) 16 - Shear Fastener Install (New) 6 See Fastener codetable for torque values. - - Bolt Torque 7 These are the temporary bolts installed in Figure 27. 4 - Bolt Remove 8

- 4 - Barrel Nut Remove (a) - - Fin Terminal Fittings Inspect 9 (b) - BMS 5-95 Sealant Apply 10 See fastener codetable for torque values. (c) 8 - Bolt Install (New) 11

- 8 - Barrel Nut Install (New) (d) - - Shear Fastener Loca- tions Inspect 12 (e) (h) - - Fastener Hole Ream 13

- - - Fastener Hole Deburr Install sequentially, in both directions, starting at tension bolt locations. See fastener code table. (f) (i) 148 - Fastener Install (New) 14

- 8 - Temporary Fastener Remove 15 FIGURE 28: INSTALLATION OF THE VERTICAL FIN (SHEET 6 OF 9) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 13, 2015 767-53A0267 Revision 1 August 04, 2016 195 of 206 BOEING SERVICE BULLETIN 767-53A0267 ALERT ALERTMore Data Qty Identification Name Task Step (f) (i) 8 - Fastener Install (New) 16 (a) Determine the gap at fin terminal fittings in accordance with Boeing Drawing 100T3480, sheet 1. Shimusing predrilled shims, with oversized holes in accordance with Boeing Drawing 100T3481 sheet 1. Precoat shims with 0.001-0.005 inches of BMS3-38 (BMS3-27 optional). (b) Apply sealant to the bolt thread, shanks, under the bolt head, the barrel nut, washer mating surfaces and to all areas of the barrel nut that contacts vertical fin structure. Refer to SOPM 20-50-19 as an accepted procedure. Solvent clean all applicable surfaces, prior to application of sealant, to make sure all corrosion inhibiting compound is removed. Refer to SOPM 20-30-03 as an accepted procedure. (c) Fastener head must sit against body bulkhead structure. Check for a small bead of sealant around the bolt head after installation. (d) Determine the gap at fastener locations. Shim, if required using predrilled shim in accordance with Boeing Drawing 100T3481 sheet 1, to maintain a maximum gap of 0.008 inches. Pre-coat shims with 0.001-0.005 inches of BMS3-38 (BMS3-27 optional). (e) Ream to 1/64 inch oversize. Refer to SOPM 20-10-02 as an accepted procedure. (f) Solvent clean all applicable surfaces prior to application of sealant. Apply sealant to the shear fastener thread, shanks and under the shear fastener head. Refer to SOPM 20-50-19 as an accepted procedure. Solvent clean all applicable surfaces, prior to application of sealant, to make sure all corrosion inhibiting compound is removed. Refer to SOPM 20-30-03 as an accepted procedure. (g) Apply sealant to the bolt thread, shanks and under the bolt head. Refer to SOPM 20-50-19 as an accepted procedure. (h) If any Fastener locations "B" exceeds 1/64 oversize, contact The Boeing Company for repair instructions and do the repair. Fastener "B" locations are class 1 cold worked. (i) All H-11 hardware should have been replaced at fin to body joint in accordance with Boeing Service Bulletin 767-53A0085 and AD 2003-10-11 by July 1, 2006.

The codes shown below agree with the letter shown in the upper left corner of the fastener symbols in the figure. A number in the lower right corner gives the grip length of the fastener. The QTY numbers shown below are the number of fasteners necessary for this figure.

FIGURE 28: INSTALLATION OF THE VERTICAL FIN (SHEET 7 OF 9) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 13, 2015 767-53A0267 Revision 1 August 04, 2016 196 of 206 BOEING SERVICE BULLETIN 767-53A0267 ALERT ALERTMore Data Hole Dia Qty Identification Name Code

- 0.200-0.203 4 BACB30NX6K6X BOLT, PROTRUDING HD A

- - 4 BACC30BH6 COLLAR

- 0.200-0.203 8 BACB30NX6K19X BOLT, PROTRUDING HD B

- - 8 BACC30BH6 COLLAR

- 0.263-0.266 28 BACB30NX8K5X BOLT, PROTRUDING HD C

- - 28 BACC30BH8 COLLAR

- 0.263-0.266 6 BACB30NX8K9X BOLT, PROTRUDING HD D

- - 6 BACC30BH8 COLLAR

- 0.263-0.266 4 BACB30NX8K16X BOLT, PROTRUDING HD E

- - 4 BACC30BH8 COLLAR

- 0.325-0.328 6 BACB30NX10K10X BOLT, PROTRUDING HD F

- - 6 BACC30BH10 COLLAR

- 0.325-0.328 6 BACB30NX10K12X BOLT, PROTRUDING HD G

- - 6 BACC30BH10 COLLAR

- 0.325-0.328 2 BACB30NX10K13X BOLT, PROTRUDING HD H

- - 2 BACC30BH10 COLLAR

- 0.325-0.328 2 BACB30NX10K15X BOLT, PROTRUDING HD I

- - 2 BACC30BH10 COLLAR

- 0.388-0.391 14 BACB30NX12K9X BOLT, HEX DRIVE J

- - 14 BACC30BH12 COLLAR

- 0.388-0.391 4 BACB30NX12K11X BOLT, PROTRUDING HD K

- - 4 BACC30BH12 COLLAR

- 0.388-0.391 10 BACB30NX12K14X BOLT, PROTRUDING HD L

- - 10 BACC30BH12 COLLAR
FIGURE 28: INSTALLATION OF THE VERTICAL FIN (SHEET 8 OF 9) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 13, 2015 767-53A0267 Revision 1 August 04, 2016 197 of 206 BOEING SERVICE BULLETIN 767-53A0267 ALERT ALERTMore Data Hole Dia Qty Identification Name Code

- 0.388-0.391 58 BACB30NX12K15X BOLT TIANIUM O/S M

- - 58 BACC30BH12 COLLAR

- 0.513-0.516 4 BACB30NX16K11X BOLT, PROTRUDING HD N

- - 4 BACC30X16 COLLAR 7,800 - 8,800 in-lbs torque (a) - 4 BACB30US16K47 BOLT, 12 PT HEAD O

- - 4 BACW10BP16CD WASHER, PLAIN

- - 4 NAS1149E1632P WASHER

- - 4 BACN11B16CS BARREL NUT 7,800 - 8,800 in-lbs torque (a) - 4 BACB30US16K48 BOLT, 12 PT HEAD P

- - 4 BACW10BP16CD WASHER, PLAIN

- - 4 NAS1149E1632P WASHER

- - 4 BACN11B16CS BARREL NUT 7,800 - 8,800 in-lbs torque (a) - 2 BACB30US16K50 BOLT, 12 PT HEAD Q

- - 2 BACW10BP16CD WASHER, PLAIN

- - 2 NAS1149E1632P WASHER

- - 2 BACN11B16CS BARREL NUT 7,800 - 8,800 in-lbs torque (a) - 2 BACB30US16K51 BOLT, 12 PT HEAD R

- - 2 BACW10BP16CD WASHER, PLAIN

- - 2 NAS1149E1632P WASHER

- - 2 BACN11B16CS BARREL NUT 10,450 - 11,500 in-lbs torque (a) - 4 BACB30US18K52 BOLT, 12 PT HEAD S

- - 4 BACW10BP18CD WASHER, PLAIN

- - 4 NAS1149E1632P WASHER

- - 4 BACN11B18CS BARREL NUT (a) Torque the 12 point bolts using the 2MIT100T3480PBR torque multiplier.

FIGURE 28: INSTALLATION OF THE VERTICAL FIN (SHEET 9 OF 9) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 13, 2015 767-53A0267 Revision 1 August 04, 2016 198 of 206 BOEING SERVICE BULLETIN 767-53A0267 ALERT ALERTCAUTION:ELECTRICAL POWER - POTENTIAL ELECTRICAL POWER HAZARDS EXIST WHEN PERFORMING THIS TEST. USE APPLICABLE SHOP PROCEDURES AS REQUIRED. Reference Wiring Diagrams 49-14-11, 49-15-11, 49-41-11, 49-94-11, and 49-94-14. A Multimeter, such as a Triplett 630A, Fluke 77, or other equivalent model, capable of reading resistance from 1 milliohm to 1,000 ohms is necessary. A jumper wire is necessary to provide a path to aircraft ground from each of the connector pins that will be tested. NOTE:The circuit breaker locations that follow are typical. Circuit breaker locations may vary with the airplane configuration. 1. On the P11-4 Panel, open the circuit breakers that follow and attach DO-NOT-CLOSE tags: Name Location CB Number APU ALTN CONT B35 C1391 FUEL DC PUMP CONT D35 C1052 IND LIGHTS 1 A33 C1306 LANDING GEAR POSITION AIR/GND SYS 2 ALT C29 C1575 FUEL DC PUMP PWR D34 C1058 APU REMOTE FIRE IND B34 C0796 2. On the P11-5 Panel, open the circuit breaker that follows and attach DO-NOT-CLOSE tags: Name Location CB Number FUEL PUMPS L FWD R AFT M25 C1055 3. On the P11-6 Panel, open the circuit breakers that follow and attach DO-NOT-CLOSE tags: Name Location CB Number PNEUMATIC AIR SUPPLY APU BLEED CONT S24 C1333 PNEUMATIC AIR SUPPLY APU BLEED PWR S23 C1336 RIGHT IND LTS 1 R28 C1273 TRU APU START CONTROL (a) T35 C0865 (a) If the airplane is equipped with TRU START. 4. If the airplane is equipped with TRU START, on the P32 Panel, open the circuit breaker that follows and attach DO-NOT-CLOSE tags:

APPENDIX A: APU WIRING TEST PROCEDURE (SHEET 1 OF 5) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 13, 2015 767-53A0267 Revision 1 August 04, 2016 199 of 206 BOEING SERVICE BULLETIN 767-53A0267 ALERT ALERTName Location CB Number TRU APU START R32 C303 5. If the airplane is equipped with TRU START, on the P49 Panel, open the circuit breaker that follows and attach DO-NOT-CLOSE tags: Name Location CB Number TRU FAN D03 C89 6. On the E6/P49 Panel, open the circuit breakers that follow and attach DO-NOT-CLOSE tags: Name Location CB Number APU PRIME CONT C02 C1383 APU START C03 C20 APU BAT CHGR E04 C868 APU BAT BUS E03 C869 7. On the P6-1 Panel, open the circuit breakers that follow and attach DO-NOT-CLOSE tags: Name Location CB Number FIRE EXT APU 1 G01 C780 FIRE EXT APU 2 (a) G02 C782 FUEL VALVES APU E03 C1063 GEN CONT UNIT APU B03 C806 (a) If the airplane is equipped with dual APU fire bottles. 8. On the P6-4 Panel, open the circuit breaker that follows and attach DO-NOT-CLOSE tags: Name Location CB Number L FWD FUEL BOOST PUMP G24 C372 9. On the P33 Panel, open the circuit breakers that follow and attach DO-NOT-CLOSE tags: Name Location CB Number GROUND SERVICE BUS P-6 B07 C321 APU BAT CHGR E05 C302

10. On the P34 Panel, open the circuit breaker that follows and attach DO-NOT-CLOSE tags:
APPENDIX A: APU WIRING TEST PROCEDURE (SHEET 2 OF 5) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 13, 2015 767-53A0267 Revision 1 August 04, 2016 200 of 206 BOEING SERVICE BULLETIN 767-53A0267 ALERT ALERTName Location CB Number APU GND SVCE BUS M12 C322

11. On the P5 Panel, set the MAIN BATTERY switch (S2) on the M1OO62 module to "OFF". 12. On the P5 Panel, set the APU START switch (S1) on the M1 Module to "OFF". 13. On the P5 Panel, set the APU BLEED AIR switch (S5) on the M15 module to "OFF". 14. On the P8 Panel, set the APU FIRE switch (S39) on the M1O444 module to "OFF". 15. On the P61 Panel, set the APU MAINT switch (S3) on the M1390 module to "NORM". 16. Disconnect the APU Battery, located in the E6 rack in the aft cargo compartment. 17. Remove the APU Controller (ECU) located in the E6 rack in the aft cargo compartment. 18. In the P49 Panel, disconnect connector D6396P. 19. Depending on the oil level indication chosen, disconnect the applicable connector in the P49 Panel: D4040P (airplanes with APU oil quantity switch indication), or D6424P (airplanes with APU oil level indication). 20. Disconnect connectors D4024P, D4030P, and D4138P on the APU firewall. 21. Disconnect the D502 connector on the APU Inlet Door Actuator. 22. Do the wiring continuity test as follows: a. Set the Multimeter in the proper range to read resistance in the range of 0 to 100 Ohms. b. Verify that the resistance from pin 2 of ECU connector D408C to airplane ground is less than 1 Ohm. For most of the continuity checks of the wiring, a jumper wire will be placed in the pin of the firewall connector and the jumper wire will then also be connected to airplane ground. c. Do wiring checks as given in the table that follows: Resistance Jumper Wire Multimeter Probes 10 Ohms or less airplane ground D4030J pin 23 D408C pin 2 D408B pin E7 10 Ohms or less airplane ground D4030J pin 9 D408C pin 2 D408B pin E6 10 Ohms or less airplane ground D4030J pin 27 D408C pin 2 D408B pin B6 10 Ohms or less airplane ground D4030J pin 13 D408C pin 2 D408B pin B5
APPENDIX A: APU WIRING TEST PROCEDURE (SHEET 3 OF 5) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 13, 2015 767-53A0267 Revision 1 August 04, 2016 201 of 206 BOEING SERVICE BULLETIN 767-53A0267 ALERT ALERTResistance Jumper Wire Multimeter Probes 10 Ohms or less airplane ground D4030J pin 26 D408C pin 2 D408B pin A11 10 Ohms or less airplane ground D4030J pin 12 D408C pin 2 D408B pin A10 10 Ohms or less airplane ground D4030J pin 25 D408C pin 2 D408B pin A9 10 Ohms or less airplane ground D4030J pin 11 D408C pin 2 D408B pin A8 10 Ohms or less airplane ground D4030J pin 24 D408C pin 2 D408B pin A7 10 Ohms or less airplane ground D4030J pin 10 D408C pin 2 D408B pin A6 10 Ohms or less airplane ground D4030J pin 9 D408C pin 2 D408B pin B10 10 Ohms or less airplane ground D4030J pin 8 D408C pin 2 D408B pin G7 10 Ohms or less airplane ground D4030J pin 7 D408C pin 2 D408B pin G6 10 Ohms or less airplane ground D4030J pin 4 D408C pin 2 D408B pin G9 10 Ohms or less airplane ground D4030J pin 3 D408C pin 2 D408B pin G8 10 Ohms or less airplane ground D4030J pin 5 D408C pin 2 D408B pin F11 10 Ohms or less airplane ground D4030J pin 6 D408C pin 2 D408B pin F8 10 Ohms or less airplane ground D4030J pin 14 D408C pin 2 D408B pin F9 10 Ohms or less airplane ground D4030J pin 15 D408C pin 2 D408B pin F10 10 Ohms or less airplane ground D4030J pin 2 D408C pin 2 D408B pin H11 10 Ohms or less airplane ground D4030J pin 1 D408C pin 2 D408B pin H10 10 Ohms or less airplane ground D4030J pin 38 D408C pin 2 D408B pin C9 10 Ohms or less airplane ground D4030J pin 37 D408C pin 2 D408B pin C8 10 Ohms or less airplane ground D4030J pin 17 D408C pin 2 D408B pin B4 10 Ohms or less airplane ground D4030J pin 16 D408C pin 2 D408B pin B3 10 Ohms or less airplane ground D4030J pin 35 D408C pin 2 D408B pin A4 10 Ohms or less airplane ground D4030J pin 18 D408C pin 2 D408B pin A3 10 Ohms or less airplane ground D4030J pin 32 D408C pin 2 D408B pin A2 10 Ohms or less airplane ground D4030J pin 34 D408C pin 2 D408B pin A1 10 Ohms or less airplane ground D4030J pin 6 D408C pin 2 D408B pin J5 10 Ohms or less airplane ground D4030J pin 5 D408C pin 2 D408B pin J4 10 Ohms or less airplane ground D4030J pin 16 D408C pin 2 D408B pinD11 10 Ohms or less airplane ground D4030J pin 8 D408C pin 2 D408B pin F7 10 Ohms or less airplane ground D4030J pin 7 D408C pin 2 D408B pin F6 10 Ohms or less airplane ground D4030J pin 12 D408C pin 2 D408B pin E5
APPENDIX A: APU WIRING TEST PROCEDURE (SHEET 4 OF 5) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 13, 2015 767-53A0267 Revision 1 August 04, 2016 202 of 206 BOEING SERVICE BULLETIN 767-53A0267 ALERT ALERTResistance Jumper Wire Multimeter Probes 10 Ohms or less airplane ground D4030J pin 11 D408C pin 2 D408B pin E4 10 Ohms or less airplane ground D4030J pin 3 D408C pin 2 D408B pin C5 10 Ohms or less airplane ground D4030J pin 2 D408C pin 2 D408B pin J8 10 Ohms or less airplane ground D4030J pin 1 D408C pin 2 D408B pin J7 10 Ohms or less airplane ground D4030J pin 13 D408C pin 2 D408B pin J10 10 Ohms or less airplane ground D4030J pin 20 D408C pin 2 D408C pin 6 10 Ohms or less airplane ground D4030J pin 19 D408C pin 2 D408C pin 4 10 Ohms or less - - airplane ground D4024J pin 17 10 Ohms or less - - airplane ground D4024J pin 4 10 Ohms or less airplane ground D502 pin 10 airplane ground D6396P pin 26 10 Ohms or less airplane ground D502 pin 1 airplane ground D6396P pin 24 10 Ohms or less airplane ground D502 pin 5 airplane ground D6396P pin 21 10 Ohms or less airplane ground D502 pin 7 airplane ground D6396P pin 23 10 Ohms or less airplane ground D502 pin 24 airplane ground D6396P pin 8 10 Ohms or less airplane ground D502 pin 2 airplane ground D6396P pin 27 10 Ohms or less airplane ground S506 pin B airplane ground D6396P pin 28 10 Ohms or less D4138J pin C D4138J pin A airplane ground K117 pin A1 10 Ohms or less D4138J pin D D4138J pin A airplane ground K117 pin A1 AIRPLANES WITH OIL QUANTITY SWITCH: Resistance Jumper Wire Multimeter Probes 10 Ohms or less airplane ground D4024J pin 14 airplane ground D4040J pin 12 AIRPLANES WITH OIL LEVEL INDICATION: Resistance Jumper Wire Multimeter Probes 10 Ohms or less airplane ground D4024J pin 21 airplane ground D6424J pin 1 10 Ohms or less airplane ground D4024J pin 22 airplane ground D6424J pin 2 10 Ohms or less airplane ground D4024J pin 23 airplane ground D6424J pin 3 23. Restore all systems to their normal configuration.

APPENDIX A: APU WIRING TEST PROCEDURE (SHEET 5 OF 5) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 13, 2015 767-53A0267 Revision 1 August 04, 2016 203 of 206 BOEING SERVICE BULLETIN 767-53A0267 ALERT ALERTNOTE: Make alignment pins from case-hardened AISI 1144 or equivalent steel. 1. 2. The pin segment of the alignment pin should have a 100 microinch or better surface finish. The handle should have a 250 microinch or better surface finish. Boeing recommends that pins have a black oxide penetrant finish or equivalent. 3. The alignment pins are not intended to be used for lifting. 4. These alignment pins are similar to Boeing tools UT-7039-7, UT-7039-38, and UT-7039-39.

APPENDIX B: ALIGNMENT PINS (SHEET 1 OF 1) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 13, 2015 767-53A0267 Revision 1 August 04, 2016 204 of 206 BOEING SERVICE BULLETIN 767-53A0267 ALERT ALERTLogic diagrams are provided as an aid only. Information contained in Paragraph 1.E., Compliance is the primary source for compliance times. Information contained in Paragraph 3.B., Work Instructions is the primary source for tasks required for compliance. 1. The table below gives the description for the parts and conditions called out in the logic diagrams. Description Title AFT PRESSURE BULKHEAD REPLACEMENT PART 2

APPENDIX C: LOGIC DIAGRAM FOR PARAGRAPH 1.E. COMPLIANCE: TABLE 1: REPLACEMENT OF THE STA 1582 AFT PRESSURE BULKHEAD (SHEET 1 OF 1) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 13, 2015 767-53A0267 Revision 1 August 04, 2016 205 of 206 BOEING SERVICE BULLETIN 767-53A0267 ALERT ALERTAPPENDIX D: PART DEMAND INTENT (SHEET 1 OF 1) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 13, 2015 767-53A0267 Revision 1 August 04, 2016 206 of 206 BOEING SERVICE BULLETIN 767-53A0267 ALERT ALERT