### Commercial **Airplanes** 

# 767 Service Bulletin **Number: 767-57A0100** Original Issue: August 21, 2006 Revision 3: July 28, 2011 ATA System: 5720 2811 **SUBJECT:** WINGS - Outer Wing - Change to Fasteners in Fuel Tank Walls - Application of Sealant Export of this technology is controlled under the United States Export Administration Regulations (EAR) (15 CFR 730-774). 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## BOEING PROPRIETARY, CONFIDENTIAL, AND/OR TRADE SECRET Copyright © 2006 The Boeing Company Unpublished Work - All Rights Reserved Boeing claims copyright in each page of this document only to the extent that the page contains copyrightable subject matter. Boeing also claims copyright in this document as a compilation and/or collective work. This document includes proprietary information owned by The Boeing Company and/or one or more third parties. Treatment of the document and the information it contains is governed by contract with Boeing. For more information, contact The Boeing Company, P.O. Box 3707, Seattle, Washington 98124. Boeing, the Boeing signature, the Boeing symbol, 707, 717, 727, 737, 747, 757, 767, 777, 787, Dreamliner, BBJ, DC-8, DC-9, DC-10, KC-10, KDC-10, MD-10, MD-11, MD-80, MD-88, MD-90, P-8A, Poseidon and the Boeing livery are all trademarks owned by The Boeing Company; and no trademark license is granted in connection with this document unless provided in writing by Boeing.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 21, 2006 767-57A0100 Revision 3: July 28, 2011 1 of 46 2.0BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 21, 2006 767-57A0100 Revision 3: July 28, 2011 2 of 46 **BOEING SERVICE BULLETIN 767-57A0100**

BLANK PAGE**Table of Contents** Revision Transmittal Sheet............................................ 5 Summary...................................................... 7 1. PLANNING INFORMATION. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11 A. Effectivity. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11 1. Airplanes. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11 2. Spares Affected. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17 B. Concurrent Requirements. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17 C. Reason. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17 D. Description. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 18 E. Compliance. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19 F. Approval. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19 G. Manpower. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20 H. Weight and Balance Changes. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21 I. Electrical Load Data. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21 J. References. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 22 1. Existing Data:. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 22 2. Data supplied with this Service Bulletin:. . . . . . . . . . . . . . . . . . . . . . . . . . . 22 3. Installation Drawings Used in the Preparation of this Service Bulletin:. . . . . . . . . . . 22 K. Publications Affected. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 22 L. Interchangeability and Intermixability of Parts. . . . . . . . . . . . . . . . . . . . . . . . . . . 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:. . . . . . . . . . . . . . . . . . . . . . . . 23 3. Parts Modified and Reidentified:. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 24 4. Parts Removed and Not Replaced:. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 24 D. Parts Necessary to Change Spares. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 24 E. Special Tooling - Price and Availability. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 24 F. Special Tooling Necessary to do this Service Bulletin. . . . . . . . . . . . . . . . . . . . . . . 24 3. ACCOMPLISHMENT INSTRUCTIONS. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25 A. GENERAL INFORMATION. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25 B. WORK INSTRUCTIONS. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25 FIGURE 1: SEAL OF THE FASTENERS [Group 1-2; Group 3, Configuration 1]. . . . . . . . . . . . 29 FIGURE 2: UPPER WING SKIN - LEFT MAIN TANK - LOCATION OF THE FASTENERS [Group 1-2; Group 3, Configuration 1]. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 31 FIGURE 3: UPPER WING SKIN - RIGHT MAIN TANK - LOCATION OF THE FASTENERS [Group 1-2; Group 3, Configuration 1]. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 33 FIGURE 4: REAR SPAR - LEFT MAIN TANK AND SURGE TANK - LOCATION OF THE FASTENERS [Group 2]. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 35 FIGURE 5: GROUP 2 - REAR SPAR - RIGHT MAIN TANK AND SURGE TANK - LOCATION OF THE FASTENERS [Group 2]. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 39 FIGURE 6: INSPECTION OF THE VORTEX GENERATORS - UPPER WING SKIN - LEFT WING [Group 3] . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 43

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 21, 2006 767-57A0100 Revision 3: July 28, 2011 3 of 46 **BOEING SERVICE BULLETIN 767-57A0100**FIGURE 7: INSPECTION OF THE VORTEX GENERATORS - UPPER WING SKIN - RIGHT WING [Group 3] . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 45

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 21, 2006 767-57A0100 Revision 3: July 28, 2011 4 of 46 **BOEING SERVICE BULLETIN 767-57A0100**

### Commercial **Airplanes** 

# 767 Service Bulletin **Revision Transmittal Sheet Number: 767-57A0100**  Original Issue: August 21, 2006 Revision 3: July 28, 2011 ATA System: 5720 2811 **SUBJECT:** WINGS - Outer Wing - Change to Fasteners in Fuel Tank Walls - Application of Sealant This revision includes all pages of the service bulletin. **COMPLIANCE INFORMATION RELATED TO THIS REVISION** No more work is necessary on airplanes changed in accordance with the original issue, Revision 1 or Revision 2 of this service bulletin. Federal Aviation Administration (FAA) Airworthiness Directive AD 2009-18-02 is related to this service bulletin. **REASON FOR REVISION** This revision is sent to correct the quantity of the fasteners specified in Figure 5. The figure incorrectly shows 15 fasteners that must be sealed at Rear Spar Station (RSS) 468.06. The correct fastener quantity for RSS 468.06 is 14. Also clarification was added to show that Figure 1 is a typical view of a fastener that was intended to apply to rivets or bolts with collars. These sections were changed: 1. In Figure 1, added the text rivet or bolt with a collar to the illustration and to footnotes (a), (c), (e), and (f). 2. In Figure 5, updated the illustration text to specify 14 locations at RSS 468.06 and update the total fastener quantity in the table. Vertical lines are put on the left edge of each page, except in Paragraph 1.A., Effectivity, to show the location of important changes. Pages with no vertical lines have no important changes. **REVISION HISTORY** August 21, 2006 Original Issue: June 19, 2008 Revision 1: May 20, 2010 Revision 2: July 28, 2011 Revision 3:

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 21, 2006 767-57A0100 Revision 3: July 28, 2011 5 of 46BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 21, 2006 767-57A0100 Revision 3: July 28, 2011 6 of 46 **BOEING SERVICE BULLETIN 767-57A0100**

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### Commercial **Airplanes** 

# 767 Service Bulletin **Summary Number: 767-57A0100**  Original Issue: August 21, 2006 Revision 3: July 28, 2011 ATA System: 5720 2811 **SUBJECT:** WINGS - Outer Wing - Change to Fasteners in Fuel Tank Walls - Application of Sealant **CONCURRENT REQUIREMENTS** None. **BACKGROUND** Accomplishment of the modifications within this service bulletin will help prevent possible ignition sources in the main fuel tanks, and the surge tanks caused by a lightning strike on certain wing surfaces. An ignition source in a fuel tank could result in a fire or an explosion. A review by Boeing identified a certain fastener type in the fuel tank walls that have an insufficient bond to the structure. If energy from lightning strike goes through these fasteners, arcing can occur at the ends of the fasteners in the fuel tank. The ends of the fasteners in the fuel tank do not have sufficient electrical insulation to contain the energy from the arcs. This Service Bulletin gives the instructions to seal the end of certain fasteners in the fuel tank walls. These changes make sure that the risk of an ignition source in the fuel tank from a lightning strike on the wing is kept to a minimum. This service bulletin is the result of the safety assessments conducted by Boeing under SFAR 88, "Fuel Tank System Fault Tolerance Evaluation Requirements". **ACTION (PRR B13421-10) Group 1:**  Prepare the main fuel tanks for entry. Get access to the left main tank. Seal the ends of the fasteners on the brackets that hold the vortex generators. Get access to the right main tank. Seal the ends of the fasteners on the brackets that hold the vortex generators. Close access to the main fuel tanks. **Group 2:** Prepare the main fuel tanks for entry. Get access to the left main tank. Seal the ends of the fasteners on the brackets that hold the vortex generators. Seal the ends of fasteners on certain stiffeners on the rear spar. Get access to the right main tank. Seal the ends of the fasteners on the brackets that hold the vortex generators. Seal the ends of fasteners on certain stiffeners on the rear spar. Close access to the main fuel tanks.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 21, 2006 767-57A0100 Revision 3: July 28, 2011 7 of 46**Group 3:** Get access to the outer surface of the upper wing panel on the left wing. Do a General Visual Inspection of the specified vortex generators on the upper wing panel of the left wing. Get access to the outer surface of the upper wing panel on the right wing. Do a General Visual Inspection of the specified vortex generators on the upper wing panel on the right wing. If the vortex generators are attached with adhesive alone, no more work is necessary. If the vortex generators are attached with fasteners, do the following steps: Prepare the main fuel tanks for entry. Get access to the left main tank. Seal the ends of the fasteners on the brackets that hold the vortex generators. Get access to the right main tank. Seal the ends of the fasteners on the brackets that hold the vortex generators. Close access to the main fuel tanks. Service Bulletin 767-57A0102 has similar access requirements as this bulletin and can be incorporated at the same time or separately. Service Bulletin 767-57A0102 is separate from this bulletin because it makes improvements to existing design and does not have warranty remedies. **EFFECTIVITY** 767-200/-300/-300F/-400ER Airplanes. Refer to Paragraph 1.A.1., Airplanes, for the list of affected airplanes. **COMPLIANCE** Federal Aviation Administration (FAA) Airworthiness Directive AD 2009-18-02 is related to this service bulletin. Boeing recommends that this service bulletin be incorporated within 60 months from the effective date of FAA AD 2009-18-02. **INDUSTRY SUPPORT INFORMATION** Boeing warranty remedies are available for airplanes in warranty as of July 16, 2004. Please refer to Paragraph 2.B., Industry Support Information. **MANPOWER Elapsed Hours**  **Total Task Hours Airplanes**  10.00 29.25 Group 1 38.81 143.24 Group 2 10.05 29.75 Group 3, Config- uration 1 0.50 0.50 Group 3, Config- uration 2
**MATERIAL INFORMATION** Operator Supplied Parts/Materials. Refer to Paragraph 2.A., Material - Price and Availability.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 21, 2006 767-57A0100 Revision 3: July 28, 2011 8 of 46 **BOEING SERVICE BULLETIN 767-57A0100**BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 21, 2006 767-57A0100 Revision 3: July 28, 2011 9 of 46 **BOEING SERVICE BULLETIN 767-57A0100**BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 21, 2006 767-57A0100 Revision 3: July 28, 2011 10 of 46 **BOEING SERVICE BULLETIN 767-57A0100**

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### Commercial **Airplanes** 

# 767 Service Bulletin **Number: 767-57A0100** Original Issue: August 21, 2006 Revision 3: July 28, 2011 ATA System: 5720 2811 **SUBJECT:** WINGS - Outer Wing - Change to Fasteners in Fuel Tank Walls - Application of Sealant **1. PLANNING INFORMATION A. Effectivity**  1. Airplanes This service bulletin is for the airplanes shown below. An equivalent change is on subsequent production airplanes. Refer to PRRB13421-10 for data about this change. Refer to Service Bulletin Index Document D624T001 Part 3 for Airplane Variable Number, Line Number, and Serial Number data.
**DESCRIPTION CONFIGURATION**  **GROUP** 767-200/300/300F airplanes

- 1 767-400ER airplanes

- 2 767-200/300 airplanes that have vortex fasteners installed with or without fasteners - 3
Airplanes that have vortex generators installed with fasteners 1 Airplanes that have vortex generators installed with adhesive alone 2

Airplane Models: 767-200, 767-300, 767-300F, 767-400ER **Group Variable Number**  1 VA001 - VA020 1 VA301 - VA315 1 VA501 - VA515 3 VA516 - VA519 1 VA520 - VA530

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 21, 2006 767-57A0100 Revision 3: July 28, 2011 11 of 46**Group Variable Number**  1 VA701 - VA719 1 VA801 - VA810 1 VB001 - VB002 1 VB051 - VB055 1 VB101 - VB121 3 VB122 - VB123 1 VB124 - VB125 1 VB201 - VB202 1 VB251 - VB253 1 VB281 - VB284 1 VB301 - VB302 1 VB321 - VB332 1 VB371 - VB373 1 VB401 1 VB441 - VB444 1 VE001 - VE003 1 VE021 - VE023 3 VE041 1 VE042 - VE043 1 VE061 - VE066 3 VE067 - VE068 1 VE069 1 VE083 - VE086 1 VE101 3 VE102 - VE103 1 VE104 3 VE116 - VE117 1 VE118 1 VE121 - VE126 1 VE141 - VE152 1 VE171 - VE172 1 VF001 - VF002 1 VF041 - VF042

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 21, 2006 767-57A0100 Revision 3: July 28, 2011 12 of 46 **BOEING SERVICE BULLETIN 767-57A0100 Group**  **Variable Number** 1 VF051 1 VF061 - VF062 1 VF071 - VF072 1 VF091 - VF093 1 VF101 - VF102 1 VF161 - VF162 1 VF171 - VF172 1 VF180 - VF184 1 VF251 3 VK001 - VK003 1 VK004 - VK016 1 VK021 - VK022 3 VK031 1 VK032 - VK056 1 VK081 - VK113 1 VK131 - VK133 1 VK141 - VK148 1 VK161 - VK164 1 VK171 1 VK181 1 VK186 1 VL001 - VL006 1 VL011 1 VL701 - VL703 1 VL751 - VL755 1 VL806 - VL807 1 VL871 - VL873 1 VL891 - VL900 1 VL911 - VL914 1 VL931 - VL932 1 VL941 1 VN001 - VN041 1 VN051 - VN064

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 21, 2006 767-57A0100 Revision 3: July 28, 2011 13 of 46 **BOEING SERVICE BULLETIN 767-57A0100 Group**  **Variable Number** 1 VN081 - VN099 1 VN111 - VN127 1 VN130 - VN137 1 VN151 - VN158 1 VN163 - VN168 1 VN171 - VN174 1 VN191 - VN198 1 VN211 - VN212 1 VN221 - VN225 1 VN231 - VN234 1 VN241 - VN243 1 VN251 - VN276 1 VN291 - VN293 1 VN301 - VN314 1 VN371 - VN372 1 VN376 1 VN381 - VN388 1 VN421 - VN427 1 VN436 1 VN471 - VN472 1 VN491 - VN513 1 VN531 - VN532 1 VN536 - VN537 1 VN541 - VN542 1 VN546 - VN547 1 VN551 1 VN556 - VN557 1 VN561 - VN562 1 VN631 - VN638 1 VN651 - VN658 1 VN671 - VN672 1 VN676 1 VN681 - VN691

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 21, 2006 767-57A0100 Revision 3: July 28, 2011 14 of 46 **BOEING SERVICE BULLETIN 767-57A0100 Group**  **Variable Number** 1 VN731 - VN732 1 VN751 - VN753 1 VN791 - VN792 1 VN811 - VN813 1 VN921 - VN922 1 VN931 - VN936 1 VN951 - VN953 1 VN966 - VN972 2 VQ001 - VQ021 2 VQ071 - VQ086 1 VR051 - VR060 1 VR081 1 VR084 1 VR086 - VR087 1 VR106 1 VR201 - VR211 1 VR251 1 VR256 - VR260 1 VR401 1 VR421 - VR423 1 VR426 1 VR441 1 VR461 1 VR471 - VR472 1 VS051 - VS056 1 VS061 1 VS066 - VS070 1 VS073 - VS078 1 VS091 - VS104 1 VS111 - VS113 1 VS131 - VS133 1 VS136 - VS137 1 VS176 - VS177

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 21, 2006 767-57A0100 Revision 3: July 28, 2011 15 of 46 **BOEING SERVICE BULLETIN 767-57A0100 Group**  **Variable Number** 1 VS186 - VS187 1 VS196 - VS203 1 VS206 - VS208 1 VS211 1 VS216 - VS217 1 VS231 1 VS246 - VS248 1 VS261 - VS263 1 VS266 - VS274 1 VS291 - VS293 1 VS301 - VS303 1 VS306 - VS311 1 VS316 1 VS321 - VS324 1 VS331 - VS333 1 VS336 - VS337 1 VS366 - VS367 1 VS381 - VS382 1 VS391 - VS392 1 VS401 1 VS426 - VS428 1 VS466 - VS472 1 VS486 1 VS496 - VS497 1 VS506 - VS507 1 VS526 1 VS546 - VS549 1 VS701 - VS712 1 VS721 - VS732 1 VS751 - VS759 1 VS821 - VS825 1 VS841 - VS844 1 VS861

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 21, 2006 767-57A0100 Revision 3: July 28, 2011 16 of 46 **BOEING SERVICE BULLETIN 767-57A0100 Group**  **Variable Number** 1 VS881 - VS883 1 VS891 1 VS896 1 VT501 1 VT511 1 VV001 1 VW701 - VW721 1 VW851 2. Spares Affected None. **B. Concurrent Requirements** None. **C. Reason** Accomplishment of the modifications within this service bulletin will help prevent possible ignition sources in the main fuel tanks, and the surge tanks caused by a lightning strike on certain wing surfaces. An ignition source in a fuel tank could result in a consequent fire or explosion. A review by Boeing identified a certain fastener type in the fuel tank walls that have an insufficient bond to the structure. If energy from lightning strike goes through these fasteners, arcing can occur at the ends of the fasteners in the fuel tank. The ends of the fasteners in the fuel tank do not have sufficient electrical insulation to contain the energy from the arcs. This Service Bulletin gives the instructions to seal the end of certain fasteners in the fuel tank walls. These changes make sure that the risk of an ignition source in the fuel tank from a lightning strike on the wing is kept to a minimum. This service bulletin is the result of the safety assessments conducted by Boeing under SFAR 88, "Fuel Tank System Fault Tolerance Evaluation Requirements". Revision 1 is sent to to give instructions to do a General Visual Inspection of the vortex generators on certain airplanes. Before work is done, the vortex generators on certain airplanes must be inspected to determine if the vortex generators are installed with fasteners or adhesive alone. An operator reported that the vortex generators on some 767 airplanes are attached with adhesive alone. If fasteners are not used to install the vortex generators it is not necessary to apply sealant at these locations. A review of the engineering drawing for the upper wing inspar panel installation confirms that some airplanes in a certain line number range were delivered with vortex generators that are attached by adhesive alone. The data given in Information Notice 767-57A0100 IN 01 is included in this revision.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 21, 2006 767-57A0100 Revision 3: July 28, 2011 17 of 46 **BOEING SERVICE BULLETIN 767-57A0100**Revision 2 is sent to correct a typographical error in the quantity of fasteners specified in certain figures. Figure 4 and Figure 5 correctly shows 10 fasteners that must be sealed at Rear Spar Station (RSS) 916.70 and the text after the circle note specifies a quantity of 9 locations. Also this revision corrects discrepancies in references and specifies alternative fuel tank sealants. The data given in Information Notice 767-57A0100 IN 02 is included in this revision. Revision 3 is sent to correct the quantity of the fasteners specified in Figure 5. The figure incorrectly shows 15 fasteners that must be sealed at Rear Spar Station (RSS) 468.06. The correct fastener quantity for RSS 468.06 is 14. Also clarification was added to show that Figure 1 is a typical view of a fastener that was intended to apply to rivets or bolts with collars. **D. Description Group 1:**  Prepare the main fuel tanks for entry. Get access to the left main tank. Seal the ends of the fasteners on the brackets that hold the vortex generators. Get access to the right main tank. Seal the ends of the fasteners on the brackets that hold the vortex generators. Close access to the main fuel tanks. **Group 2:** Prepare the main fuel tanks and surge tanks for entry. Get access to the left main tank. Seal the ends of the fasteners on the brackets that hold the vortex generators. Seal the ends of fasteners on certain stiffeners on the rear spar. Get access to the right main tank. Seal the ends of the fasteners on the brackets that hold the vortex generators. Seal the ends of fasteners on certain stiffeners on the rear spar. Close access to the main fuel tanks. **Group 3:** Get access to the outer surface of the upper wing panel on the left wing. Do a General Visual Inspection of the specified vortex generators on the upper wing panel of the left wing. Get access to the outer surface of the upper wing panel on the right wing. Do a General Visual Inspection of the specified vortex generators on the upper wing panel on the right wing. If the vortex generators are attached with adhesive alone, no more work is necessary. If the vortex generators are attached with fasteners, do the following steps: Prepare the main fuel tanks for entry. Get access to the left main tank. Seal the ends of the fasteners on the brackets that hold the vortex generators. Get access to the right main tank. Seal the ends of the fasteners on the brackets that hold the vortex generators. Close access to the main fuel tanks. Service Bulletin 767-57A0102 has similar access requirements as this bulletin and can be incorporated at the same time or separately. Service Bulletin 767-57A0102 is separate from this bulletin because it makes improvements to existing design and does not have warranty remedies. Revision 1 - No more work is necessary on airplanes changed as shown in the original issue of this service bulletin. Revision 2 - No more work is necessary on airplanes changed in accordance with the original issue and Revision 1 of this service bulletin. Revision 3 - No more work is necessary on airplanes changed in accordance with the original issue, Revision1, and Revision 2 of this service bulletin. The work in this service bulletin is done in the maintenance zone(s) given below.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 21, 2006 767-57A0100 Revision 3: July 28, 2011 18 of 46 **BOEING SERVICE BULLETIN 767-57A0100 Group 1:** 
**Affected Maintenance Zones Zone**  **Model** 541, 641 767-200, 767-300, 767-300F **Group 2:**
**Affected Maintenance Zones Zone**  **Model** 541, 542, 641, 642 767-400ER **Group 3:**
**Affected Maintenance Zones Zone**  **Model** 541, 641 767-200, 767-300 **E. Compliance** Federal Aviation Administration (FAA) Airworthiness Directive AD 2009-18-02 is related to this service bulletin. Boeing recommends that this service bulletin be incorporated within 60 months from the effective date of FAA AD 2009-18-02. **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. In addition, the Manager of the FAA Seattle Aircraft Certification Office approves the action (i.e. inspection or modification) defined in this service bulletin as an alternative method of compliance to the requirements of paragraph (f) of AD 2009-18-02. All provisions of AD 2009-18-02 that are not specifically referenced in the above statement remain fully applicable and must be complied with.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 21, 2006 767-57A0100 Revision 3: July 28, 2011 19 of 46 **BOEING SERVICE BULLETIN 767-57A0100 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 examine the work — Time to cure the materials — Time to make the parts — Time to find the tools. **Group 1: Elapsed Hours**  **Task-Hours Number of Per-**  **sons Task** 
3.25 13.00 4 Prepare 1.50 3.00 2 Open Access 3.00 6.00 2 Figure 1 and Figure 2 1.80 7.25 4 Close Access 8.75 29.25 TOTAL FOR EACH AIRPLANE **Group 2: Elapsed Hours**  **Task-Hours Number of Per-**  **sons Task** 
3.25 13.00 4 Prepare 3.00 6.00 2 Open Access 3.00 6.00 2 Figure 1 and Figure 3 13.50 54.00 4 Figure 1 and Figure 4 13.50 54.00 4 Figure 1 and Figure 5 2.56 10.25 4 Close Access 38.81 143.25 TOTAL FOR EACH AIRPLANE **Group 3, Configuration 1: Elapsed Hours**  **Task Hours Number of Per-**  **sons Task** 
0.50 0.50 1 Inspect - Figure 6 and Figure 7

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 21, 2006 767-57A0100 Revision 3: July 28, 2011 20 of 46 **BOEING SERVICE BULLETIN 767-57A0100 Group 3, Configuration 1:**  **Elapsed Hours Task Hours**  **Number of Per- sons**  **Task**
3.25 13.00 4 Prepare 1.50 3.00 2 Open Access 3.00 6.00 2 Figure 1 and Figure 2 1.80 7.25 4 Close Access 10.05 29.75 TOTAL FOR EACH AIRPLANE **Group 3, Configuration 2: Elapsed Hours**  **Task Hours Number of Per-**  **sons Task** 
0.50 0.50 1 Inspect - Figure 6 and Figure 7 0.50 0.50 TOTAL FOR EACH AIRPLANE **H. Weight and Balance Changes Group 1; Group 3, Configuration 1:**  **Change in Moment (Pound-Inches)**  **Change in Weight (Pounds)**  **Airplane**
+152.6 +0.14 Group 1 **Group 2: Change in Moment**  **(Pound-Inches) Change in Weight**  **(Pounds) Airplane** 
+1526 +1.4 Group 2 **Group 3, Configuration 2:** None. **I. Electrical Load Data** Not changed.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 21, 2006 767-57A0100 Revision 3: July 28, 2011 21 of 46 **BOEING SERVICE BULLETIN 767-57A0100 J. References**  1. Existing Data: a. Engineering Change Memo PRR B13421-10 b. 767 Aircraft Maintenance Manual (AMM) 28-11-00, 28-11-01, 28-11-02, 28-11-03, 28-26-00 c. Boeing Service Bulletin 767-57A0102 d. Boeing Standard Overhaul Practices Manual SOPM 20-30-93 e. Federal Aviation Administration (FAA) Airworthiness Directive 2009-18-02 2. Data supplied with this Service Bulletin: None. 3. Installation Drawings Used in the Preparation of this Service Bulletin:
**Title Drawing Number**  Rear Spar Inst - Wing 112T1901 Panel Installation, Inspar Wing, Upper 112T3000 These drawings were used to prepare this service bulletin. These drawings are not necessary to make the specified changes, and are not supplied with this service bulletin. These drawings may not be applicable to all airplane configurations or operators. **K. Publications Affected** 1. Publications: None. 2. Damage Tolerance Based Structural Inspections: Boeing has evaluated the repairs and/or changes in this service bulletin for effects on Fatigue Critical Structure (FCS) and for changes to Damage Tolerance Inspections (DTI) required in the Maintenance Program. This service bulletin 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.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 21, 2006 767-57A0100 Revision 3: July 28, 2011 22 of 46 **BOEING SERVICE BULLETIN 767-57A0100 2. MATERIAL INFORMATION**  **A. Material - Price and Availability** The operator can supply the parts and materials shown in Paragraph 2.C., Parts Necessary For Each Airplane. As an alternative, operators can purchase the parts from Boeing Spares. This service bulletin does not show the Boeing price and supply data. **B. Industry Support Information** Boeing warranty remedies are available for 767 airplanes in warranty as of July 16, 2004. For man-hour and material reimbursement for airplanes in warranty as of that date, send a warranty claim to Boeing Commercial Airplanes Group - Warranties. **C. Parts Necessary For Each Airplane** 1. Kits/Parts: None. 2. Parts and Materials Supplied by the Operator: **Group 1-2; Group 3, Configuration 1:**
**Notes Name**  **QTY Part Number /**  **Specification** (a) (b) SOLVENT 10 fl. oz. BMS 11-7 (SOL- VENTS IN SOPM 20-30-93optional) (a) (b) SEALANT 7 fl. oz. BMS 5-45, CLASS A-2, GRADE1(PERMITTED ALTERNATIVE FUEL TANK SEALANTS IN 767 AMM 28- 11-01 optional) (a) (b) SEALANT 28 fl. oz. BMS 5-45, CLASS B-2 (PERMITTED ALTERNATIVE FUEL TANK SEALANTS IN 767AMM 28-11-01 optional) (a) WIPER, ABSORBENT

- BMS 15-5 (a) See the Qualified Products List at the end of the Boeing Material Specification (BMS) for supplier data. (b) Quantity is approximate.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 21, 2006 767-57A0100 Revision 3: July 28, 2011 23 of 46 **BOEING SERVICE BULLETIN 767-57A0100 Group 3, Configuration 2:**  None. 3. Parts Modified and Reidentified: None. 4. Parts Removed and Not Replaced: None. **D. Parts Necessary to Change Spares** None. **E. Special Tooling - Price and Availability** None. **F. Special Tooling Necessary to do this Service Bulletin** No special tools or equipment are necessary to do the change in this service bulletin. But, maintenance and overhaul tools in the manuals given in Paragraph 1.J., References, can be necessary. Examine operator tool supply to make sure all necessary tools are available.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 21, 2006 767-57A0100 Revision 3: July 28, 2011 24 of 46 **BOEING SERVICE BULLETIN 767-57A0100 3. ACCOMPLISHMENT INSTRUCTIONS**  **A. GENERAL INFORMATION CAUTION:**  KEEP THE WORK AREA, WIRES AND ELECTRICAL BUNDLES CLEAN OF METAL PARTICLES OR CONTAMINATION WHEN YOU USE TOOLS. UNWANTED MATERIAL, METAL PARTICLES OR CONTAMINATION CAUGHT IN WIRE BUNDLES CAN CAUSE DAMAGE TO THE BUNDLES. DAMAGED WIRE BUNDLES CAN CAUSE SPARKS OR OTHER ELECTRICAL DAMAGE. **NOTE:** 1. Manual titles are referred to by acronyms. Refer to Paragraph 1.J., References, for definition of the acronyms. 2. Obey all of the warnings and cautions given in the specified manual sections. 3. A General Visual Inspection is defined as: A visual examination of an interior or exterior area, installation or assembly to detect obvious damage, failure or irregularity. This level of inspection is made from within touching distance unless otherwise specified. A mirror may be necessary to ensure visual access to all surfaces in the inspection area. This level of inspection is made under normal available lighting conditions such as daylight, hangar lighting, flashlight or drop-light and may require removal or opening of access panels or doors. Stands, ladders or platforms may be required to gain proximity to the area being checked. 4. These work instructions refer to procedures included in other Boeing documents. When the words "refer to" are used and the operator has an accepted alternative procedure, the accepted alternative procedure can be used. When the words "as given in" are included in the instruction, the procedure in the Boeing document must be used. **B. WORK INSTRUCTIONS WARNING:**  KEEP PERSONS AND EQUIPMENT AWAY FROM ALL CONTROL SURFACES WHEN HYDRAULIC POWER IS SUPPLIED. AILERONS, ELEVATORS, RUDDER, FLAPS, SLATS, SPOILERS, AND STABILIZER ARE FULLY POWERED SURFACES. INJURY TO PERSONS OR DAMAGE TO EQUIPMENT CAN OCCUR WHEN HYDRAULIC POWER IS SUPPLIED. 1. **Group 3:** Get access to the outer surface of the upper wing panel on the left wing. 2. **Group 3:** Do a General Visual Inspection of the specified vortex generators on the upper wing panel on the left wing as given in FIGURE 6. **WARNING:** KEEP PERSONS AND EQUIPMENT AWAY FROM ALL CONTROL SURFACES WHEN HYDRAULIC POWER IS SUPPLIED. AILERONS, ELEVATORS, RUDDER, FLAPS, SLATS, SPOILERS, AND STABILIZER ARE FULLY POWERED SURFACES. INJURY TO PERSONS OR DAMAGE TO EQUIPMENT CAN OCCUR WHEN HYDRAULIC POWER IS SUPPLIED. 3. **Group 3:** Get access to the outer surface of the upper wing panel on the right wing.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 21, 2006 767-57A0100 Revision 3: July 28, 2011 25 of 46 **BOEING SERVICE BULLETIN 767-57A0100**4. **Group 3:** Do a General Visual Inspection of the specified vortex generators on the upper wing panel on the right wing as given in FIGURE 7. 5. **Group 3:** If the vortex generators are attached with adhesive alone, no more work is necessary. If the vortex generators are attached with fasteners, go to the next step. **NOTE:** Airplanes with vortex generators that are attached with fasteners are in Group 3, Configuration 1. **NOTE:** Airplanes with vortex generators that are attached with adhesive alone are in Group 3, Configuration 2. 6. **Group 1-2; Group 3, Configuration 1:** Defuel the left and right main fuel tank. Refer to 767 AMM 28-26-00, Page Block 201 as an accepted procedure.
7. **Group 1; Group 3, Configuration 1:** Prepare the left and right main fuel tanks for entry. Refer to 767 AMM 28-11-00 Page Block 201 as an accepted procedure. 8. **Group 2:** Prepare the left and right main fuel tanks and surge tanks for entry. Refer to 767 AMM 28-11-00 Page Block 201 as an accepted procedure. 9. **Group 1; Group 3, Configuration 1:** Get access to the left main fuel tank. Remove and keep the access doors as shown in the table below. Refer to 767 AMM 28-11-01 as an accepted procedure. **Gives Access to Rear or Front Spar Area between Rib Number**  **Access Door**
Ribs 10 and 11 541AB Ribs 11 and 12 541BB Ribs 12 and 13 541CB
10.**Group 1; Group 3, Configuration 1:** Get access to the right main fuel tank. Remove and keep the access doors as shown in the table below. Refer to 767 AMM 28-11-01 as an accepted procedure. **Gives Access to Rear or Front Spar Area between Rib Number**  **Access Door**
Ribs 10 and 11 641AB Ribs 11 and 12 641BB Ribs 12 and 13 641CB

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 21, 2006 767-57A0100 Revision 3: July 28, 2011 26 of 46 **BOEING SERVICE BULLETIN 767-57A0100**11.**Group 2:** Get access to the left main fuel tank and the surge tank. Remove and keep the access doors as shown in the table below. Refer to 767 AMM 28-11-01 and 767 AMM 28-11-03 as an accepted procedure. **Gives Access to Rear or Front Spar Area between Rib Number**  **Access Door**
Ribs 11 and 12 541BB Ribs 12 and 13 541CB Ribs 28 and 29 541VB Ribs 30 and 31 541XB Ribs 32 and 33 542BB
12.**Group 2:** Get access to the right main fuel tank and the surge tank. Remove and keep the access doors as shown in the table below. Refer to 767 AMM 28-11-01 and 767 AMM 28-11-03 as an accepted procedure. **Gives Access to Rear or Front Spar Area between Rib Number**  **Access Door**
Ribs 11 and 12 641BB Ribs 12 and 13 641CB Ribs 28 and 29 641VB Ribs 30 and 31 641XB Ribs 32 and 33 642BB
13.**Group 1-2; Group 3, Configuration 1:** Find and seal the fasteners for the brackets that hold the vortex generators on the upper wing skin in the main tank in as given in: — FIGURE 1 for the seal of the fastener — FIGURE 2 for the location of the fasteners in the left main tank — FIGURE 3 for the location of the fasteners in the right main tank. 14.**Group 2:** Find and seal the fasteners for the stiffeners on the rear spar in the main tank and the surge tank as given in: — FIGURE 1 for the seal of the fastener — FIGURE 4 for the location of the fasteners in the left main tank and surge tank — FIGURE 5 for the location of the fasteners in the right main tank and surge tank.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 21, 2006 767-57A0100 Revision 3: July 28, 2011 27 of 46 **BOEING SERVICE BULLETIN 767-57A0100**15.**Group 1; Group 3, Configuration 1:** Close access to the fuel tanks. Install the access doors that were removed. Refer to 767 AMM 28-11-01 as an accepted procedure. 16.**Group 2:** Close access to the fuel tanks. Install the access doors that were removed. Refer to 767 AMM 28-11-01 and 767 AMM 28-11-03 as an accepted procedure. 17.**Group 1-2; Group 3, Configuration 1:** Put the airplane back to a serviceable condition.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 21, 2006 767-57A0100 Revision 3: July 28, 2011 28 of 46 **BOEING SERVICE BULLETIN 767-57A0100 This Figure applies only to: Group 1-2; Group 3, Configuration 1.** 

The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY numbers shown below are the number of parts necessary for this figure.
**MORE DATA QTY**  **IDENTIFICATION NAME**  **TASK STEP**  Make sure that the debris around the areas to be sealed is removed. - - DEBRIS Remove 1

Use a BMS 15-5wiper wet with solvent. (a) - BMS 11-7 (SOL- VENTS IN BSOPM 20- 30-93 optional) SOLVENT Apply 2

Use a non-metallic brush. - - FASTENERS Clean The remaining solvent must be removed while wet with a clean, dry BMS 15-5 wiper. (b) - - SOLVENT Remove

Use a BMS 15-5wiper wet with solvent. (a)(c) - BMS 11-7 (SOL- VENTS IN BSOPM 20- 30-93 optional) SOLVENT Apply 3

Use a non-metallic brush. - - FASTENERS Clean The remaining solvent must be removed while wet with a clean, dry BMS 15-5 wiper.(b) - - SOLVENT Remove

**FIGURE 1: SEAL OF THE FASTENERS (SHEET 1 OF 2)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 21, 2006 767-57A0100 Revision 3 July 28, 2011 29 of 46 **BOEING SERVICE BULLETIN 767-57A0100 MORE DATA**  **QTY IDENTIFICATION**  **NAME TASK**  **STEP** Precoat sealant. (d)(e) - BMS 5-45, CLASS A-2,GRADE 1 (PERMITTED ALTERNATIVE FUEL TANK SEALANTS IN 767AMM 28-11-00 optional) SEALANT Apply 4

Fillet sealant. (d)(f)

- BMS 5-45, CLASS B-2,GRADE 1 (PERMITTED ALTERNATIVE FUEL TANK SEALANTS IN 767AMM 28-11-00 optional) SEALANT Apply 5

(a) Make sure that an area approximately 0.5 inch from the base of the fastener (rivet or bolt with a collar) is clean. The cleaned area must be larger than the area that has sealant. (b) Make sure that the wiper has no visible soil remaining after the area is cleaned. (c) It is not necessary to apply solvent, clean the fasteners (rivets or bolts with collars) and remove the solvent again if Step 2 is done immediately before the precoat sealant is applied. (d) Make sure to use the sealants specified in this table or specified alternatives. (e) Make sure to apply the precoat sealant on the fastener (rivet or bolt with a collar). Refer to 767 AMM 28- 11-00 as an accepted procedure. (f) Make sure to apply the fillet sealant on the fastener (rivet or bolt with a collar). Refer to 767 AMM 28-11- 00 as an accepted procedure.

**FIGURE 1: SEAL OF THE FASTENERS (SHEET 2 OF 2)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 21, 2006 767-57A0100 Revision 3 July 28, 2011 30 of 46 **BOEING SERVICE BULLETIN 767-57A0100 This Figure applies only to: Group 1-2; Group 3, Configuration 1.** 

**FIGURE 2: UPPER WING SKIN - LEFT MAIN TANK - LOCATION OF THE FASTENERS (SHEET 1 OF 2)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 21, 2006 767-57A0100 Revision 3 July 28, 2011 31 of 46 **BOEING SERVICE BULLETIN 767-57A0100**The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY numbers shown below are the number of parts necessary for this figure.
**MORE DATA QTY**  **IDENTIFICATION NAME**  **TASK STEP**  Get access. Find the location of the fasteners that must be sealed. 8
- FASTENERS Locate 1

**FIGURE 2: UPPER WING SKIN - LEFT MAIN TANK - LOCATION OF THE FASTENERS (SHEET 2 OF 2)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 21, 2006 767-57A0100 Revision 3 July 28, 2011 32 of 46 **BOEING SERVICE BULLETIN 767-57A0100 This Figure applies only to: Group 1-2; Group 3, Configuration 1.** 

**FIGURE 3: UPPER WING SKIN - RIGHT MAIN TANK - LOCATION OF THE FASTENERS (SHEET 1 OF 2)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 21, 2006 767-57A0100 Revision 3 July 28, 2011 33 of 46 **BOEING SERVICE BULLETIN 767-57A0100**The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY numbers shown below are the number of parts necessary for this figure.
**MORE DATA QTY**  **IDENTIFICATION NAME**  **TASK STEP**  Get access. Find the location of the fasteners that must be sealed. 8
- FASTENERS Locate 1

**FIGURE 3: UPPER WING SKIN - RIGHT MAIN TANK - LOCATION OF THE FASTENERS (SHEET 2 OF 2)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 21, 2006 767-57A0100 Revision 3 July 28, 2011 34 of 46 **BOEING SERVICE BULLETIN 767-57A0100 This Figure applies only to: Group 2.** 

**FIGURE 4: REAR SPAR - LEFT MAIN TANK AND SURGE TANK - LOCATION OF THE FASTENERS (SHEET 1 OF 4)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 21, 2006 767-57A0100 Revision 3 July 28, 2011 35 of 46 **BOEING SERVICE BULLETIN 767-57A0100 FIGURE 4: REAR SPAR - LEFT MAIN TANK AND SURGE TANK - LOCATION OF THE FASTENERS**  **(SHEET 2 OF 4)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 21, 2006 767-57A0100 Revision 3 July 28, 2011 36 of 46 **BOEING SERVICE BULLETIN 767-57A0100 FIGURE 4: REAR SPAR - LEFT MAIN TANK AND SURGE TANK - LOCATION OF THE FASTENERS**  **(SHEET 3 OF 4)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 21, 2006 767-57A0100 Revision 3 July 28, 2011 37 of 46 **BOEING SERVICE BULLETIN 767-57A0100**The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY numbers shown below are the number of parts necessary for this figure.
**MORE DATA QTY**  **IDENTIFICATION NAME**  **TASK STEP**  Get access. Find the location of the fasteners that must be sealed. 72
- FASTENERS Locate 1

**FIGURE 4: REAR SPAR - LEFT MAIN TANK AND SURGE TANK - LOCATION OF THE FASTENERS (SHEET 4 OF 4)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 21, 2006 767-57A0100 Revision 3 July 28, 2011 38 of 46 **BOEING SERVICE BULLETIN 767-57A0100 This Figure applies only to: Group 2.** 

**FIGURE 5: GROUP 2 - REAR SPAR - RIGHT MAIN TANK AND SURGE TANK - LOCATION OF THE FASTENERS**  **(SHEET 1 OF 4)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 21, 2006 767-57A0100 Revision 3 July 28, 2011 39 of 46 **BOEING SERVICE BULLETIN 767-57A0100 FIGURE 5: GROUP 2 - REAR SPAR - RIGHT MAIN TANK AND SURGE TANK - LOCATION OF THE**  **FASTENERS (SHEET 2 OF 4)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 21, 2006 767-57A0100 Revision 3 July 28, 2011 40 of 46 **BOEING SERVICE BULLETIN 767-57A0100 FIGURE 5: GROUP 2 - REAR SPAR - RIGHT MAIN TANK AND SURGE TANK - LOCATION OF THE**  **FASTENERS (SHEET 3 OF 4)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 21, 2006 767-57A0100 Revision 3 July 28, 2011 41 of 46 **BOEING SERVICE BULLETIN 767-57A0100**The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY numbers shown below are the number of parts necessary for this figure.
**MORE DATA QTY**  **IDENTIFICATION NAME**  **TASK STEP**  Get access. Find the location of the fasteners that must be sealed. 71
- FASTENERS Locate 1

**FIGURE 5: GROUP 2 - REAR SPAR - RIGHT MAIN TANK AND SURGE TANK - LOCATION OF THE FASTENERS**  **(SHEET 4 OF 4)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 21, 2006 767-57A0100 Revision 3 July 28, 2011 42 of 46 **BOEING SERVICE BULLETIN 767-57A0100 This Figure applies only to: Group 3.** 

**FIGURE 6: INSPECTION OF THE VORTEX GENERATORS - UPPER WING SKIN - LEFT WING (SHEET 1 OF 2)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 21, 2006 767-57A0100 Revision 3 July 28, 2011 43 of 46 **BOEING SERVICE BULLETIN 767-57A0100**The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY numbers shown below are the number of parts necessary for this figure.
**MORE DATA QTY**  **IDENTIFICATION NAME**  **TASK STEP**  4
- VORTEX GENERA- TOR Locate 1 (a) 4
- VORTEX GENERA- TOR Inspect (a) Do a General Visual Inspection to find if the vortex generator is installed with fasteners or adhesive alone.

**FIGURE 6: INSPECTION OF THE VORTEX GENERATORS - UPPER WING SKIN - LEFT WING (SHEET 2 OF 2)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 21, 2006 767-57A0100 Revision 3 July 28, 2011 44 of 46 **BOEING SERVICE BULLETIN 767-57A0100 This Figure applies only to: Group 3.** 

**FIGURE 7: INSPECTION OF THE VORTEX GENERATORS - UPPER WING SKIN - RIGHT WING (SHEET 1 OF 2)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 21, 2006 767-57A0100 Revision 3 July 28, 2011 45 of 46 **BOEING SERVICE BULLETIN 767-57A0100**The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY numbers shown below are the number of parts necessary for this figure.
**MORE DATA QTY**  **IDENTIFICATION NAME**  **TASK STEP**  4
- VORTEX GENERA- TOR Locate 1 (a) 4
- VORTEX GENERA- TOR Inspect (a) Do a General Visual Inspection to find if the vortex generator is installed with fasteners or adhesive alone.

**FIGURE 7: INSPECTION OF THE VORTEX GENERATORS - UPPER WING SKIN - RIGHT WING (SHEET 2 OF 2)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 21, 2006 767-57A0100 Revision 3 July 28, 2011 46 of 46 **BOEING SERVICE BULLETIN 767-57A0100**