# Boeing Alert Service Bulletin 767-56A0010: U.S. DOT/FAA - Boeing Service Bulletin - Rights: © The Boeing Company. Filed by the FAA in regulations.gov docket FAA-2007-27223, the docket of AD 2012-05-04. Not covered by OpenAirDocs’ CC0 dedication. - Document: [Boeing Alert Service Bulletin 767-56A0010](https://openairdocs.org/service-documents/boeing/767-56a0010.md) - Title as filed: U.S. DOT/FAA - Boeing Service Bulletin - Pages: 141 - PDF: https://openairdocs.org/files/sha256/ab/fc/abfce8505f86250e1e99be291eb8fd7969ac451ad93d458a7683d1988492821c - Page: https://openairdocs.org/service-documents/boeing/767-56a0010/file/abfce8505f86 ## Text Some pages are OCR from a scan. OCR can misread letters and numbers. Each page's text from the PDF; open the PDF at a page with #page=N. ### Page 1 Commercial Airplanes 767 Service Bulletin Number: 767-56A0010 Original Issue: September 07, 2006 Revision 3: March 03, 2011 ATA System: 5611 SUBJECT: WINDOWS - Flight Compartment Windows - Number 2 Openable Window - Link Arm Modification 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all export laws. 9E991ECCN: BOEING PROPRIETARY, CONFIDENTIAL, AND/OR TRADE SECRET Copyright © 2006 The Boeing Company Unpublished Work - All Rights Reserved Boeing claims copyright in each page of this document only to the extent that the page contains copyrightable subject matter.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 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.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: September 07, 2006 767-56A0010Revision 3: March 03, 2011 1 of 141 3.0 ### Page 2 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 07, 2006 767-56A0010Revision 3: March 03, 2011 2 of 141 BOEING SERVICE BULLETIN 767-56A0010 BLANK PAGE ### Page 3 Table of Contents Revision Transmittal Sheet ............................................ 5 Summary ...................................................... 7 1. PLANNING INFORMATION ........................................ 1 1 A. Effectivity ............................................... 1 1 1. Airplanes ............................................ 1 1 2. Spares Affected ........................................ 1 9 B. Concurrent Requirements ...................................... 1 9 C. Reason ................................................ 1 9 D. Description .............................................. 2 0 E. Compliance .............................................. 2 2 F. Approval ............................................... 2 3 G. Manpower .............................................. 2 3 H. Weight and Balance Changes .................................... 2 8 I. Electrical Load Data ......................................... 2 8 J. References .............................................. 2 8 1. Existing Data: ......................................... 2 8 2. Data supplied with this Service Bulletin: ........................... 2 9 3. Installation Drawings Used in the Preparation of this Service Bulletin: ........... 2 9 K. Publications Affected ........................................ 2 9 L. Interchangeability and Intermixability of Parts ........................... 3 0 2. MATERIAL INFORMATION ........................................ 3 1 A. Material - Price and Availability ................................... 3 1 B. Industry Support Information .................................... 3 2 C. Parts Necessary For Each Airplane ................................. 3 2 1. Kits/Parts: ........................................... 3 2 2. Parts and Materials Supplied by the Operator: ........................ 3 4 3. Parts Modified and Reidentified: ............................... 3 4 4. Parts Removed and Not Replaced: .............................. 3 6 D. Parts Necessary to Change Spares ................................. 3 6 E. Special Tooling - Price and Availability ............................... 3 7 F. Special Tooling Necessary to do this Service Bulletin ....................... 3 7 3. ACCOMPLISHMENT INSTRUCTIONS .................................. 3 9 A. GENERAL INFORMATION ..................................... 3 9 B. WORK INSTRUCTIONS ....................................... 4 0 FIGURE 1: NUMBER 2 WINDOW - LINK BRACKET - REMOVAL - LEFT SIDE [Group 1, 4, 6, Configuration 1 ] ................................................ 4 6 FIGURE 2: NUMBER 2 WINDOW - LINK BRACKET - REMOVAL - LEFT SIDE [Group 1, Configuration 2; Group 2-3; Group 4, Configuration 2; Group 5; Group 6, Configuration 2; Group 7] .... 5 1 FIGURE 3: NUMBER 2 WINDOW - LINK BRACKET - OPTIONAL REWORK - LEFT SIDE [Group 2, 7] . 56 FIGURE 4: NUMBER 2 WINDOW - LINK BRACKET - INSTALLATION - LEFT SIDE [Group 1, 6, Configuration 1 ] ................................................ 5 8 FIGURE 5: NUMBER 2 WINDOW - LINK BRACKET - INSTALLATION - LEFT SIDE [Group 1, Configuration 2; Group 2-3; Group 6, Configuration 2; Group 7] ...................... 6 3 FIGURE 6: NUMBER 2 WINDOW - LINK BRACKET - INSTALLATION - LEFT SIDE [Group 4, Configuration 1 ] ................................................ 6 8 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 07, 2006 767-56A0010Revision 3: March 03, 2011 3 of 141 BOEING SERVICE BULLETIN 767-56A0010 ### Page 4 FIGURE 7: NUMBER 2 WINDOW - LINK BRACKET - INSTALLATION - LEFT SIDE [Group 4, Configuration 2; Group 5] ........................................... 7 3 FIGURE 8: NUMBER 2 WINDOW - CAM BLOCK - REMOVAL - LEFT SIDE .............. 7 8 FIGURE 9: NUMBER 2 WINDOW - CAM BLOCK - OPTIONAL REWORK - LEFT SIDE ........ 8 1 FIGURE 10: NUMBER 2 WINDOW - CAM BLOCK - INSTALLATION - LEFT SIDE ........... 8 3 FIGURE 11: NUMBER 2 WINDOW - CRANK/ROLLER ASSEMBLY - REMOVAL - LEFT SIDE ..... 8 6 FIGURE 12: NUMBER 2 WINDOW - CRANK/ROLLER ASSEMBLY - OPTIONAL REWORK ...... 8 8 FIGURE 13: NUMBER 2 WINDOW - CRANK/ROLLER ASSEMBLY - OPTIONAL REWORK ...... 9 0 FIGURE 14: NUMBER 2 WINDOW - CRANK/ROLLER ASSEMBLY - INSTALLATION - LEFT SIDE . . 92 FIGURE 15: NUMBER 2 WINDOW - LINK BRACKET - REMOVAL - RIGHT SIDE [Group 1, 4, 6, Configuration 1 ] ................................................ 9 4 FIGURE 16: NUMBER 2 WINDOW - LINK BRACKET - REMOVAL - RIGHT SIDE [Group 1, Configuration 2; Group 2-3; Group 4, Configuration 2; Group 5; Group 6, Configuration 2; Group 7] . . . 99 FIGURE 17: NUMBER 2 WINDOW - LINK BRACKET - OPTIONAL REWORK - RIGHT SIDE [Group 2, 7] ................................................. 1 0 4 FIGURE 18: NUMBER 2 WINDOW - LINK BRACKET - INSTALLATION - RIGHT SIDE [Group 1, 6, Configuration 1] ........................................ 1 0 6 FIGURE 19: NUMBER 2 WINDOW - LINK BRACKET - INSTALLATION - RIGHT SIDE [Group 1, Configuration 2; Group 2-3; Group 6, Configuration 2; Group 7] ...................... 1 1 1 FIGURE 20: NUMBER 2 WINDOW - LINK BRACKET - INSTALLATION - RIGHT SIDE [Group 4, Configuration 1 ] ................................................ 1 1 6 FIGURE 21: NUMBER 2 WINDOW - LINK BRACKET - INSTALLATION - RIGHT SIDE [Group 4, Configuration 2; Group 5] .......................................... 1 2 1 FIGURE 22: NUMBER 2 WINDOW - CAM BLOCK - REMOVAL - RIGHT SIDE ............ 1 2 6 FIGURE 23: NUMBER 2 WINDOW - CAM BLOCK - OPTIONAL REWORK - RIGHT SIDE ...... 1 2 9 FIGURE 24: NUMBER 2 WINDOW - CAM BLOCK - INSTALLATION - RIGHT SIDE .......... 1 3 1 FIGURE 25: NUMBER 2 WINDOW - CRANK/ROLLER ASSEMBLY - REMOVAL - RIGHT SIDE . . . 134 FIGURE 26: NUMBER 2 WINDOW - CRANK/ROLLER ASSEMBLY - INSTALLATION - RIGHT SIDE . 136 FIGURE 27: NUMBER 2 WINDOW - LINK ARM - INSPECTION - LEFT SIDE ............. 1 3 8 FIGURE 28: NUMBER 2 WINDOW - LINK ARM - INSPECTION - RIGHT SIDE ............ 1 4 0 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 07, 2006 767-56A0010Revision 3: March 03, 2011 4 of 141 BOEING SERVICE BULLETIN 767-56A0010 ### Page 5 Commercial Airplanes 767 Service Bulletin Revision Transmittal SheetNumber: 767-56A0010Original Issue: September 07, 2006 Revision 3: March 03, 2011 ATA System: 5611 SUBJECT: WINDOWS - Flight Compartment Windows - Number 2 Openable Window - Link Arm Modification This Revision includes all pages of the service bulletin. COMPLIANCE INFORMATION RELATED TO THIS REVISION No more work is necessary on airplanes changed as given in Revision 2 of this service bulletin. However, as specified in Revision 1 and Revision 2, more work is necessary on airplanes changed as given in the original issue of this service bulletin. If not previously accomplished, Boeing recommends that operators do an inspection of the number 2 openable window mechanism to make sure that the link arm is in the over-center position, as given in paragraph 1.E., Compliance. Federal Aviation Administration (FAA) Notice of Proposed Rule Making (NPRM) 2006-NM-224-AD, is related to this service bulletin. REASON FOR REVISION This revision is sent to delete inspection/modification actions that were previously recommended to be done if a number 2 window assembly is changed or when rigging changes are made. Changes to this service bulletin include: — In the Summary Background section and in Paragraph 1.C., Reason: Revised the Background and Reason sections to clarify that accomplishment of this service bulletin will reduce the likelihood (will not ensure) that and unlatched number 2 flight compartment window will open during take off. — In Paragraph 1.D., Description: Added Revision 3 information and added maintenance zone information. — In Paragraph 1.E., Compliance: Revised compliance information to remove airplane conditions that were based on line maintenance activities. Also, condensed compliance information into one table due to removal of airplane conditions, which simplified the compliance data. — In Paragraph 1.K.1., Publications: Added 767 Component Maintenance Manual as an affected publication. — In Paragraph 2.C.3., Parts Modified and Reidentified: Changed reidentification requirement for 141T4835-47/-48 window assemblies. Clarified note (f). — In Paragraph 2.E. and paragraph 2.F., Special Tooling information: Revised note (a) to clarify that operators can use their own tool as an alternative to Boeing tool MIT141T4890. — In Paragraph 3.B., Work Instructions: Deleted variations of the inspection instructions (Parts 2, 3, 6, and 7) that are no longer necessary due to removed conditions and compliance information changes. — In Paragraph 3. B., Work Instructions: The words "as given in" have been changed to "refer to" throughout the Work Instructions when referencing the Aircraft Maintenance Manual (AMM). Also, PART 4 and PART 8 modification instructions have been revised to separate changes to the airplane and changes to the window assembly. BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 07, 2006 767-56A0010Revision 3: March 03, 2011 5 of 141 ### Page 6 — In Paragraph 3.B., Work Instructions: Revised PART 4, step 4 (previously step 16) and PART 8, step 4 (previously step 16) to clarify that fay surface sealing at the cam block is only required on the shim, if a shim is installed. — In Figure 3: Clarified dimensions for chamfer and clarified note (b) for shot peen requirement. — In Figures 8 and 22: Deleted note (a) regarding removal of washers. In Revision 1, the intent of note (a) was to give instructions for removal of adjustment washers that may be installed under the cam block. In Revision 2, note (b) was revised to give instructions for removal of adjustment washers. Note (a) should have been deleted in Revision 2. — In Figures 10 and 24: Deleted note (d) regarding installation of washers. In Revision 1, the intent of note (d) was to give instructions for installation of adjustment washers under the cam block. In Revision 2, note (e) was revised to give instructions for installation of adjustment washers. Note (d) should have been deleted in Revision 2. — In Figure 12: Clarified step 3 and note (d) for location of new hole. Also, added step 9 and notes (e) and (f) for identification of reworked crank/roller assembly. — In Figure 13: Clarified step 3 and note (c) for location of new hole. Also, added step 8 and notes (d) and (e) for identification of reworked crank/roller assembly. — In Figures 14 and 26: Deleted note (b) and revised note (c) to refer to Paragraph 2.C.3 for re-identification of the window assembly after modification. — In Figure 17: Clarified dimensions for chamfer and clarified note (b) for shot peen requirement. — In Figures 4, 5, 6, 7, 18, 19, 20, 21: Revised note (c) regarding installation of lockwire. — In Figures 1, 2, 4, 5, 6, 7, 15, 16, 18, 19, 20, and 21: Clarified which steps are not required if MIT141T4890 tool, or equivalent, is used to remove the link bracket. Also, clarified that operators can use their own tool, instead of MIT141T4890, during removal/installation of the link bracket. Paragraph 1.A., Effectivity, shows changes of airplane operators. Each operator should examine the Effectivity paragraph for changes. 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 September 07, 2006Original Issue: January 24, 2008Revision 1: June 18, 2009Revision 2: March 03, 2011Revision 3: BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 07, 2006 767-56A0010Revision 3: March 03, 2011 6 of 141 BOEING SERVICE BULLETIN 767-56A0010 ### Page 7 Commercial Airplanes 767 Service Bulletin SummaryNumber: 767-56A0010Original Issue: September 07, 2006 Revision 3: March 03, 2011 ATA System: 5611 SUBJECT: WINDOWS - Flight Compartment Windows - Number 2 Openable Window - Link Arm Modification CONCURRENT REQUIREMENTS None. BACKGROUND Accomplishment of this service bulletin will reduce the likelihood that a number 2 flight compartment window will open during take off, if the window is not latched. If a number 2 flight compartment window opens during take off, a high speed aborted takeoff or an unscheduled landing will be necessary. In addition, the ability of the flight crew to perform critical take off communication will be adversely affected. Note that proper latching of the number 2 flight compartment windows by the flight crew is required, prior to flight, in order to ensure that a number 2 window will not open during take off. The modification shown in this service bulletin will allow the number 2 window link arm to be positioned at an angle less than 90 degrees (over-center), in reference to the track roller, when the window is closed. Boeing has received six reports of the Number 2 windows opening during takeoff roll. This has resulted in aborted takeoffs, which have occurred at speeds up to 140 knots. The number 2 windows are opened and closed by rotating an operating crank. When closing the window the crank/roller assembly at the end of the torque tube will move and engage the cam block at the top aft corner of the window. On airplanes before line number 930, except line number 923, the crank roller can move at 18 degree increments with one gear tooth rotation. Airplane line number 923 and airplanes after line number 929, have the modification given in this service bulletin installed in production. Accomplishment of this service bulletin will allow the crank roller to move at 9 degree increments with a change of position of a retaining pin, instead of one gear tooth rotation of 18 degree increments. The link arm that drives the window shut will be positioned at an angle less than 90 degrees (over-center), in reference to the track roller, when the window is closed. Boeing Service Related Problem (SRP) 767-SRP-56-0012 and 767-SRP-56-0023 are related to this service bulletin. As a part of a service bulletin validation program, this change was completed on airplane VS078 by the original issue of Service Bulletin 767-56A0010 before the release of Revision 01 of this service bulletin. The change completed on airplane VS078 by the original issue of Service Bulletin 767-56A0010 is equivalent to the release of Revision 01 of this service bulletin. Airplane VS078 has the configuration of a Group 3 airplane. BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 07, 2006 767-56A0010Revision 3: March 03, 2011 7 of 141 ### Page 8 ACTION (PRR 12901-58S) INSPECTION: Do a general visual inspection to determine if the link arm on the number 2 window is in an over-center position when the window is closed. If the link arm is not in an over-center position when the window is closed, re-rig the window. If the link arm cannot be rigged to get the over-center position, do the modification as given in this service bulletin. MODIFICATION: Remove the link brackets from the carriage assembly lower track operating system, left and right. Remove the cam blocks from the window number 2 upper sill, left and right. Remove the crank/roller assembly from the number 2 window assemblies, left and right. Operators can do one of the two options that follow: 1. Option 1: Replace the link brackets, cam blocks and crank/roller assemblies with new parts. Install the number 2 windows, left and right. 2. Option 2: Rework and replace the cam blocks and crank/roller assemblies. Rework and replace, or install new link brackets. Operators who have older link brackets installed will not be able to rework the link brackets and will need to install new link brackets. Refer to Paragraph 3.B., Work Instructions for reworking existing parts or new part installation applicability. Group 1-2: It is recommended that operators accomplish service bulletin 767-56-0002, "WINDOWS - Flight Compartment Windows - Openable Windows Number 2 - Latch Hook and Striker Plate Installation", due to common access. Group 1, 4, 6: It is recommended that operators accomplish service bulletin 767-56-0004, "WINDOWS - Number 2 Openable Window- Window Stop Installation", due to common access. EFFECTIVITY 767-200, -300, -300F and -400ER Airplanes. Refer to Paragraph 1.A.1., Airplanes for the list of affected airplanes. COMPLIANCE Refer to Paragraph 1.E., Compliance. Federal Aviation Administration (FAA) Notice of Proposed Rule Making 2006-NM-224-AD is related to this service bulletin. INDUSTRY SUPPORT INFORMATION Boeing warranty remedies are not available for the configuration changes, inspection and/or repair procedures given in this service bulletin. MANPOWER Refer to Paragraph 1.G., Manpower. MATERIAL INFORMATION Boeing Supplied Kits/Parts. BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 07, 2006 767-56A0010Revision 3: March 03, 2011 8 of 141 BOEING SERVICE BULLETIN 767-56A0010 ### Page 9 (OCR) BOEING SERVICE BULLETIN 767-56A0010 Refer to Paragraph 2.A., Material - Price and Availability. OPENABLE WINDOW MODIFICATION: NUMBER 2 REWORK OR INSTALL NEW LATCH CAM BLOCK LOCK HANDLE MODIFICATION: REWORK OR INSTALL NEW CRANK/ROLLER ASSEMBLY ' FWD SEE A MODIFICATION: REWORK OR INSTALL NEW LINK BRACKET D58609 Original Issue: September 07, 2006 Revision 3: March 03, 2011 767-56A0010 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 9 of 141 ### Page 10 (OCR) BOEING SERVICE BULLETIN 767-56A0010 CENTER LINE OF LINK ARM REFERENCE LINE (90° FROM CENTER LINE OF TRACK) INSPECTION: DO A GENERAL VISUAL INSPECTION TO DETERMINE IF MINIMUM THE LINK ARM IS IN AN 2 DEGREES WINDOW OVERCENTER POSITION WHEN THE OVERCENTER ASSEMBLY WINDOW IS CLOSED. IF THE LINK ARM IS NOT IN AN OVERCENTER POSITION, RIG THE WINDOW AS GIVEN IN THE AMM AND IF NECESSARY DO THE MODIFICATION 82-88 AS GIVEN IN THIS SERVICE DEGREES BULLETIN. LOWER AFT TRACK LINK ARM CENTER LINE OF TRACK INBD LINK BRACKET LOOKING OUTBOARD (LEFT SIDE SHOWN, RIGHT SIDE OPPOSITE) 1501063 Original Issue: September 07, 2006 Revision 3: March 03, 2011 767-56A0010 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 10 of 141 ### Page 11 Commercial Airplanes 767 Service Bulletin Number: 767-56A0010 Original Issue: September 07, 2006 Revision 3: March 03, 2011 ATA System: 5611 SUBJECT: WINDOWS - Flight Compartment Windows - Number 2 Openable Window - Link Arm Modification 1. PLANNING INFORMATION A. Effectivity 1. Airplanes Refer to Service Bulletin Index Document D624T001 Part 3 for Airplane Variable Number, Line Number, and Serial Number data. This service bulletin is for the airplanes shown below. An equivalent change is on subsequent production airplanes. Refer to PRR B12901-58S for data about this change. DESCRIPTIONCONFIGURATIONGROUP 767-200 airplane, line numbers 2 through 114 with short grip length bolts installed on the window operating mechanism with common effectivity to Boeing Service Bulletins 767-56-0002 and 767-56-0004. -1 Group 1 airplanes that HAVE NOT accomplished Boeing Service Bulletin 767-56-0004. 1 Group 1 airplanes that HAVE accomplished Boeing Service Bulletin 767-56-0004. 2 767-200 airplane, line number 1 with short grip length bolts installed on the window operating mechanism and have link brackets that can be reworked installed on the airplane with common effectivity to Boeing Service Bulletin 767-56-0002. -2 767-200, -300 and -300F airplanes, line numbers 710 through 929 with short grip length bolts installed on the window operating mechanism and have link brackets that can not be reworked installed on the airplane. -3 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 07, 2006 767-56A0010Revision 3: March 03, 2011 11 of 141 ### Page 12 DESCRIPTIONCONFIGURATIONGROUP 767-200 and -300 airplanes, line numbers 213 through 418 with long grip length bolts installed on the window operating mechanism with common effectivity to Boeing Service Bulletin 767-56-0004. -4 Group 4 airplanes that HAVE NOT accomplished Boeing Service Bulletin 767-56-0004. 1 Group 4 airplanes that HAVE accomplished Boeing Service Bulletin 767-56-0004. 2 767-200 and -300 airplanes, line numbers 419 through 665 with long grip length bolts installed on the window operating mechanism. -5 767-200 and -300 airplanes, line numbers 115 through 375 with short grip length bolts installed on the window operating mechanism with common effectivity to Boeing Service Bulletin 767-56-0004. -6 Group 6 airplanes that HAVE NOT accomplished Boeing Service Bulletin 767-56-0004. 1 Group 6 airplanes that HAVE accomplished Boeing Service Bulletin 767-56-0004. 2 767-200, -300, -300F and -400ER airplanes, line numbers 528 through 878 with short grip length bolts installed on the window operating mechanism and have link brackets that can be reworked installed on the airplane. -7 Airplane Models: 767-200, 767-300, 767-300F, 767-400ER GroupVariable Number 2VA001 1VA002 - VA020 1VA301 - VA315 1VA501 - VA513 6VA514 - VA530 1VA701 - VA712 6VA713 - VA719 1VA801 - VA810 1VB001 - VB002 1VB051 - VB055 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 07, 2006 767-56A0010Revision 3: March 03, 2011 12 of 141 BOEING SERVICE BULLETIN 767-56A0010 ### Page 13 GroupVariable Number 1VB101 - VB117 6VB118 - VB125 1VB201 - VB202 1VB251 - VB253 1VB281 - VB284 1VB301 - VB302 1VB321 - VB324 6VB325 - VB332 6VB371 - VB373 6VB401 5VB441 - VB442 7VB443 - VB444 1VE001 - VE002 6VE003 1VE021 - VE023 6VE041 - VE043 6VE061 - VE069 6VE083 - VE086 6VE101 - VE104 6VE116 - VE118 6VE121 - VE126 6VE141 - VE150 4VE151 5VE152 6VE171 - VE172 6VF001 - VF002 6VF041 - VF042 6VF051 6VF061 - VF062 6VF071 - VF072 6VF091 - VF093 6VF101 - VF102 4VF161 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 07, 2006 767-56A0010Revision 3: March 03, 2011 13 of 141 BOEING SERVICE BULLETIN 767-56A0010 ### Page 14 GroupVariable Number 5VF162 5VF171 - VF172 5VF180 7VF181 - VF184 7VF251 6VK001 - VK011 7VK012 - VK016 6VK021 - VK022 6VK031 - VK051 4VK052 - VK053 5VK054 - VK056 6VK081 - VK098 4VK099 5VK100 - VK107 7VK108 - VK113 6VK131 - VK133 6VK141 - VK142 5VK143 7VK144 - VK148 5VK161 - VK162 7VK163 - VK164 7VK171 7VK181 7VK186 6VL001 - VL006 6VL011 7VL701 - VL703 7VL751 - VL755 7VL806 - VL807 7VL871 - VL873 7VL891 - VL900 7VL911 - VL914 7VL931 - VL932 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 07, 2006 767-56A0010Revision 3: March 03, 2011 14 of 141 BOEING SERVICE BULLETIN 767-56A0010 ### Page 15 GroupVariable Number 7VL941 6VN001 - VN015 4VN016 - VN018 5VN019 - VN041 4VN051 - VN062 5VN063 - VN064 4VN081 - VN092 5VN093 - VN099 4VN111 - VN122 5VN123 - VN127 4VN130 - VN132 5VN133 - VN137 6VN151 - VN157 4VN158 6VN163 - VN167 4VN168 6VN171 - VN173 7VN174 6VN191 - VN192 4VN193 5VN194 - VN195 7VN196 - VN198 6VN211 - VN212 6VN221 - VN222 4VN223 - VN224 7VN225 6VN231 - VN234 6VN241 5VN242 - VN243 6VN251 - VN259 5VN260 - VN264 7VN265 - VN276 6VN291 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 07, 2006 767-56A0010Revision 3: March 03, 2011 15 of 141 BOEING SERVICE BULLETIN 767-56A0010 ### Page 16 GroupVariable Number 7VN292 - VN293 6VN301 - VN303 4VN304 - VN306 5VN307 - VN312 7VN313 - VN314 4VN371 - VN372 4VN376 5VN381 - VN387 7VN388 7VN421 - VN427 7VN436 6VN471 - VN472 6VN491 - VN494 4VN495 5VN496 - VN513 6VN531 4VN532 6VN536 4VN537 6VN541 4VN542 5VN546 - VN547 4VN551 5VN556 - VN557 5VN561 - VN562 6VN631 4VN632 - VN633 5VN634 - VN635 7VN636 - VN638 6VN651 4VN652 5VN653 7VN654 - VN658 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 07, 2006 767-56A0010Revision 3: March 03, 2011 16 of 141 BOEING SERVICE BULLETIN 767-56A0010 ### Page 17 GroupVariable Number 4VN671 - VN672 7VN676 4VN681 - VN683 5VN684 - VN688 7VN689 - VN691 4VN731 7VN732 4VN751 - VN753 5VN791 - VN792 5VN811 - VN813 5VN921 - VN922 5VN931 7VN932 - VN936 7VN951 - VN953 7VN966 - VN972 7VQ001 - VQ021 7VQ071 - VQ086 3VR051 - VR060 3VR081 3VR084 3VR086 7VR201 3VR202 - VR211 3VR251 3VR256 - VR260 7VR401 7VR421 3VR422 - VR423 7VR426 3VR441 7VR461 3VR471 - VR472 7VS051 - VS052 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 07, 2006 767-56A0010Revision 3: March 03, 2011 17 of 141 BOEING SERVICE BULLETIN 767-56A0010 ### Page 18 GroupVariable Number 3VS053 - VS056 3VS061 7VS066 - VS070 7VS073 3VS074 - VS078 7VS091 3VS092 - VS104 7VS111 3VS112 - VS113 7VS131 - VS132 3VS133 3VS136 - VS137 7VS176 - VS177 3VS186 - VS187 7VS196 - VS199 3VS200 - VS203 7VS206 - VS207 3VS208 3VS211 3VS216 - VS217 3VS231 7VS246 - VS248 3VS261 - VS263 3VS266 - VS274 3VS291 - VS293 3VS301 - VS303 3VS306 - VS311 3VS316 3VS321 - VS324 3VS331 - VS333 3VS336 - VS337 3VS366 - VS367 3VS381 - VS382 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 07, 2006 767-56A0010Revision 3: March 03, 2011 18 of 141 BOEING SERVICE BULLETIN 767-56A0010 ### Page 19 GroupVariable Number 3VS391 - VS392 3VS401 3VS426 - VS428 3VS466 - VS472 3VS486 3VS496 - VS497 3VS506 - VS507 3VS526 3VS546 - VS549 3VS701 - VS712 3VS721 - VS731 3VS751 - VS759 3VS821 - VS825 3VS841 - VS844 3VS861 3VS881 - VS882 3VS891 3VS896 3VT501 7VW701 - VW721 7VW851 2. Spares Affected Examine your spares supply for the parts or components identified in Paragraph 2.C., Parts Necessary for Each Airplane. If any parts or components are found, refer to Paragraph 2.C. for the recommended use. B. Concurrent Requirements None. C. Reason Accomplishment of this service bulletin will reduce the likelihood that a number 2 flight compartment window will open during take off, if the window is not latched. If a number 2 flight compartment window opens during take off, a high speed aborted takeoff or an unscheduled landing will be necessary. In addition, the ability of the flight crew to perform critical take off communication will be adversely affected. Note that proper latching of the number 2 flight compartment windows by the flight crew is required, prior to flight, in order to ensure that a number 2 window will not open during take off. BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 07, 2006 767-56A0010Revision 3: March 03, 2011 19 of 141 BOEING SERVICE BULLETIN 767-56A0010 ### Page 20 The modification shown in this service bulletin will allow the number 2 window link arm to be positioned at an angle less than 90 degrees (over-center), in reference to the track roller, when the window is closed. Boeing has received six reports of the Number 2 windows opening during takeoff roll. This has resulted in aborted takeoffs, which have occurred at speeds up to 140 knots. The number 2 windows are opened and closed by rotating an operating crank. When closing the window the crank roller at the end of the torque tube will move and engage the cam block at the top aft corner of the window. On airplanes before line number 930, except line number 923, the crank/roller assembly can move at 18 degree increments with one gear tooth rotation. Airplane line number 923 and airplanes after line number 929, have the modification given in this service bulletin installed in production. Accomplishment of this service bulletin will allow the crank roller to move at 9 degree increments with a change of position of a retaining pin, instead of one gear tooth rotation of 18 degree increments. The link arm that drives the window shut will be positioned at an angle less than 90 degrees (over-center), in reference to the track roller, when the window is closed. Boeing Service Related Problem (SRP) 767-SRP-56-0012 and 767-SRP-56-0023 are related to this service bulletin. Revision 1 is sent to add instructions to inspect the link arm on the number 2 openable window to determine if an over-center position exists when the window is fully closed. The new inspection will determine if the modification shown in this service bulletin will be necessary. This revision is also sent to improve access to the link arm after observations from the service bulletin validation. A detailed list of changes is given in the Revision Transmittal Sheet section of Revision 1. Revision 2 is sent to clarify airplane/window assembly configurations that do not require on-going link arm inspections as given in this service bulletin. Revision 2 also corrects and/or clarifies part numbers, part identifications, and other data given in the service bulletin Figures. A detailed list of changes is given in the Revision Transmittal Sheet section of Revision 2. Revision 3 is sent to delete inspection/modification actions that were previously recommended to be done if a number 2 window assembly is changed or when rigging changes are made. Other changes have also been made. A detailed list of changes is given in the Revision Transmittal Sheet section of Revision 3. As a part of a service bulletin validation program, this change was completed on airplane VS078 by the original issue of Service Bulletin 767-56A0010 before the release of Revision 01 of this service bulletin. The change completed on airplane VS078 by the original issue of Service Bulletin 767-56A0010 is equivalent to the release of Revision 01 of this service bulletin. Airplane VS078 has the configuration of a Group 3 airplane. D. Description INSPECTION: Do a general visual inspection to determine if the link arm on the number 2 window is in an over-center position when the window is closed. If the link arm is not in an over-center position when the window is closed, re-rig the window. If the link arm cannot be rigged to get the over-center position, do the modification as given in this service bulletin. MODIFICATION: Remove the link brackets from the carriage assembly lower track operating system, left and right. Remove the cam blocks from the window number 2 upper sill, left and right. Remove the crank/roller assembly from the number 2 window assemblies, left and right. BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 07, 2006 767-56A0010Revision 3: March 03, 2011 20 of 141 BOEING SERVICE BULLETIN 767-56A0010 ### Page 21 Operators can do one of the two options that follow: 1. Option 1: Replace the link brackets, cam blocks and crank/roller assemblies with new parts. Install the number 2 windows, left and right. 2. Option 2: Rework and replace the cam blocks and crank/roller assemblies. Rework and replace, or install new link brackets. Operators who have older link brackets installed will not be able to rework the link brackets and will need to install new link brackets. Refer to Paragraph 3.B., Work Instructions for reworking existing parts or new part installation applicability. Group 1-2: It is recommended that operators accomplish service bulletin 767-56-0002, "WINDOWS - Flight Compartment Windows - Openable Windows Number 2 - Latch Hook and Striker Plate Installation", due to common access. Group 1, 4, 6: It is recommended that operators accomplish service bulletin 767-56-0004, "WINDOWS - Number 2 Openable Window- Window Stop Installation", due to common access. Revision 1 - More work is necessary on airplanes changed as given in the original issue of this service bulletin. Boeing recommends that operators do an inspection of the number 2 openable window mechanism to make sure that the link arm is in a over-center position when the window is fully closed. If the link arm is not in an over-center position when the window is fully closed, the window should be re-rigged as given in the Aircraft Maintenance Manual (AMM). Revision 2 - No more work is necessary on airplanes changed as given in Revision 1. However, as specified in Revision 1, more work is necessary on airplanes changed as given in the original issue of this service bulletin. Boeing recommends that operators do an inspection of the number 2 openable window mechanism to make sure that the link arm is in an over-center position when the window is fully closed. If the link arm is not in an over-center position, the window should be re-rigged as given in the AMM. Revision 3 - No more work is necessary on airplanes changed as given in Revision 2 of this service bulletin. However, as specified in Revision 1 and Revision 2, more work is necessary on airplanes changed as given in the original issue of this service bulletin. If not previously accomplished, Boeing recommends that operators do an inspection of the number 2 openable window mechanism to make sure that the link arm is in the over-center position, in accordance with paragraph 1.E., Compliance. The work in this service bulletin is done in the maintenance zone(s) given below. Group 1-2: Affected Maintenance Zones ZoneModel 211, 212767-200 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 07, 2006 767-56A0010Revision 3: March 03, 2011 21 of 141 BOEING SERVICE BULLETIN 767-56A0010 ### Page 22 Group 3: Affected Maintenance Zones ZoneModel 211, 212767-200, 767-300, 767-300F Group 4-6: Affected Maintenance Zones ZoneModel 211, 212767-200, 767-300 Group 7: Affected Maintenance Zones ZoneModel 211, 212767-200, 767-300, 767-300F, 767-400ER E. Compliance Boeing recommends that operators do the inspections in this service bulletin at the times specified in the table below: Federal Aviation Administration (FAA) Notice of Proposed Rule Making 2006-NM-224-AD is related to this service bulletin. Table 1: Compliance Times for Inspections and Modifications Repeat Interval (Not to Exceed) Compliance TimeActionCondition -Within 60 months after the Revision 1 date of this service bulletin. Do a general visual inspection of the left side number 2 window as given in Paragraph 3.B., PART 1 - INSPECTION - LEFT SIDE. (b) -AND- All Airplanes. Do a general visual inspection of the right side number 2 window as given in Paragraph 3.B., PART 5 - INSPECTION - RIGHT SIDE. (c) --No further action is required.Inspection result: Link arm IS over- center. -Before further flight.Rig the window. Refer to 767 AMM 56-11-02 as an accepted procedure. Inspection result: Link arm IS NOT over-center. BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 07, 2006 767-56A0010Revision 3: March 03, 2011 22 of 141 BOEING SERVICE BULLETIN 767-56A0010 ### Page 23 Table 1: Compliance Times for Inspections and Modifications Repeat Interval (Not to Exceed) Compliance TimeActionCondition --No further action is required.Rigging result: Link arm IS over- center. -Before further flight.For left side windows: Do modifications as given in Paragraph 3.B., PART 4 - MODIFICATION - LEFT SIDE. (d) Rigging result: Link arm IS NOT over-center. (a) -OR- For right side windows: Do modifications as given in Paragraph 3.B., PART 8 - MODIFICATION - RIGHT SIDE. (d) (a) The action for this condition assumes that the window link arm cannot be rigged over-center due to physical limitations of existing components. Modification will be required in order to allow the link arm to be adjusted to the over-center position. If maintenance records show that modifications have already been done as a previous action for this service bulletin, then an unmodified window assembly could have been installed since the last inspection. Modification or replacement of the window assembly with a modified (or equivalent) window assembly may be required in order to allow the link arm to be adjusted to the over-center position. (b) As an option to initial inspection, do all the modification steps as given in Paragraph 3.B., Part 4. (c) As an option to initial inspection, do all the modification steps as given in Paragraph 3.B., Part 8. (d) Airplane modification and window assembly modification steps are given in PART 4 and PART 8. Operators are only required to do the modification steps as necessary to achieve the over-center position of the link arm. F. Approval This service bulletin was examined by the Federal Aviation Administration (FAA). The changes specified in this service bulletin comply with the applicable regulations and are FAA approved, as well as European Aviation Safety Agency (EASA)/Joint Aviation Authorities (JAA) approved for all EASA/JAA approved airplanes listed in the service bulletin effectivity. This service bulletin and its approval were based on the airplane in its original Boeing delivery configuration or as modified by other approved Boeing changes. If an airplane has a non-Boeing modification or repair that affects a component or system also affected by this service bulletin, the operator is responsible for obtaining appropriate regulatory agency approval before incorporating this service bulletin. G. Manpower The table below shows an estimate of the task-hours necessary to do this service bulletin 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 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 07, 2006 767-56A0010Revision 3: March 03, 2011 23 of 141 BOEING SERVICE BULLETIN 767-56A0010 ### Page 24 — Time to cure the materials — Time to make the parts — Time to find the tools. Group 1-7: Inspection Elapsed HoursTask HoursNumber of Per- sons Task 0.25 (a)0.251Figure 27 0.25 (a)0.251Figure 28 0.500.50TOTAL FOR EACH AIRPLANE (a) The AMM Adjustment/Test will be necessary if the link arm is not in a over-center position when the window is fully closed. Task hours are not given for the AMM Adjustment/Test. Group 1, 6, Configuration 1: Modification Elapsed HoursTask-HoursNumber of Per- sons Task 2.002.001Open Access 0.500.501Figure 1 0.750.751Figure 4 0.500.501Figure 8 1.001.001Figure 9 (a) 0.250.251Figure 10 0.250.251Figure 11 0.500.501Figure 12 (a) 0.500.501Figure 13 (a) 0.250.251Figure 14 0.500.501Figure 15 0.750.751Figure 18 0.500.501Figure 22 1.001.001Figure 23 (a) 0.250.251Figure 24 0.250.251Figure 25 0.250.251Figure 26 3.57.02Close Access 13.5017.0TOTAL FOR EACH AIRPLANE (a) BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 07, 2006 767-56A0010Revision 3: March 03, 2011 24 of 141 BOEING SERVICE BULLETIN 767-56A0010 ### Page 25 Group 1, 6, Configuration 1: Modification Elapsed HoursTask-HoursNumber of Per- sons Task 10.5014.0TOTAL FOR EACH AIRPLANE (b) (a) This estimate is for the rework option only. (b) This estimate is for the replacement option only. Group 1, Configuration 2; Group 3; Group 6, Configuration 2: Modification Elapsed HoursTask-HoursNumber of Per- sons Task 2.002.001Open Access 0.500.501Figure 2 0.750.751Figure 5 0.500.501Figure 8 1.001.001Figure 9 (a) 0.250.251Figure 10 0.250.251Figure 11 0.500.501Figure 12 (a) 0.500.501Figure 13 (a) 0.250.251Figure 14 0.500.501Figure 16 0.750.751Figure 19 0.500.501Figure 22 1.001.001Figure 23 (a) 0.250.251Figure 24 0.250.251Figure 25 0.250.251Figure 26 3.57.02Close Access 13.5017.0TOTAL FOR EACH AIRPLANE (a) 10.5014.0TOTAL FOR EACH AIRPLANE (b) (a) This estimate is for the rework option only. (b) This estimate is for the replacement option only. BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 07, 2006 767-56A0010Revision 3: March 03, 2011 25 of 141 BOEING SERVICE BULLETIN 767-56A0010 ### Page 26 Group 2, 7: Modification Elapsed HoursTask-HoursNumber of Per- sons Task 2.002.001Open Access 0.500.501Figure 2 1.001.001Figure 3 (a) 0.750.751Figure 5 0.500.501Figure 8 1.001.001Figure 9 (a) 0.250.251Figure 10 0.250.251Figure 11 0.500.501Figure 12 (a) 0.500.501Figure 13 (a) 0.250.251Figure 14 0.500.501Figure 16 1.001.001Figure 17 (a) 0.750.751Figure 19 0.500.501Figure 22 1.001.001Figure 23 (a) 0.250.251Figure 24 0.250.251Figure 25 0.250.251Figure 26 3.57.02Close Access 15.5019.0TOTAL FOR EACH AIRPLANE (a) 10.5014.0TOTAL FOR EACH AIRPLANE (b) (a) This estimate is for the rework option only. (b) This estimate is for the replacement option only. Group 4, Configuration 1: Modification Elapsed HoursTask-HoursNumber of Per- sons Task 2.002.001Open Access 0.500.501Figure 1 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 07, 2006 767-56A0010Revision 3: March 03, 2011 26 of 141 BOEING SERVICE BULLETIN 767-56A0010 ### Page 27 Group 4, Configuration 1: Modification Elapsed HoursTask-HoursNumber of Per- sons Task 0.750.751Figure 6 0.500.501Figure 8 1.001.001Figure 9 (a) 0.250.251Figure 10 0.250.251Figure 11 0.500.501Figure 12 (a) 0.500.501Figure 13 (a) 0.250.251Figure 14 0.500.501Figure 15 0.750.751Figure 20 0.500.501Figure 22 1.001.001Figure 23 (a) 0.250.251Figure 24 0.250.251Figure 25 0.250.251Figure 26 3.57.02Close Access 13.5017.0TOTAL FOR EACH AIRPLANE (a) 10.5014.0TOTAL FOR EACH AIRPLANE (b) (a) This estimate is for the rework option only. (b) This estimate is for the replacement option only. Group 4, Configuration 2; Group 5: Modification Elapsed HoursTask-HoursNumber of Per- sons Task 2.002.001Open Access 0.500.501Figure 2 0.750.751Figure 7 0.500.501Figure 8 1.001.001Figure 9 (a) 0.250.251Figure 10 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 07, 2006 767-56A0010Revision 3: March 03, 2011 27 of 141 BOEING SERVICE BULLETIN 767-56A0010 ### Page 28 Group 4, Configuration 2; Group 5: Modification Elapsed HoursTask-HoursNumber of Per- sons Task 0.250.251Figure 11 0.500.501Figure 12 (a) 0.500.501Figure 13 (a) 0.250.251Figure 14 0.500.501Figure 16 0.750.751Figure 21 0.500.501Figure 22 1.001.001Figure 23 (a) 0.250.251Figure 24 0.250.251Figure 25 0.250.251Figure 26 3.57.02Close Access 13.5017.0TOTAL FOR EACH AIRPLANE (a) 10.5014.0TOTAL FOR EACH AIRPLANE (b) (a) This estimate is for the rework option only. (b) This estimate is for the replacement option only. H. Weight and Balance Changes None. I. Electrical Load Data Not changed. J. References 1. Existing Data: a. Engineering Change Memo PRR B12901-58S b. 767-200 Structural Repair Manual (SRM) 51-40-08 c. 767-300 Structural Repair Manual (SRM) 51-40-08 d. 767-300F Structural Repair Manual (SRM) 51-40-08 e. 767 Aircraft Maintenance Manual (AMM) 20-10-23, 56-11-02 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 07, 2006 767-56A0010Revision 3: March 03, 2011 28 of 141 BOEING SERVICE BULLETIN 767-56A0010 ### Page 29 f. Boeing Drawing 012W6100 g. Boeing Component Maintenance Manual 56-11-12 h. Boeing Parts Standards Document D-590 i. Boeing Service Bulletin 767-56-0002 "WINDOWS - Flight Compartment Windows - Openable Windows Number 2 - Latch Hook and Striker Plate Installation" j. Boeing Service Bulletin 767-56-0004 "WINDOWS - Number 2 Openable Window- Window Stop Installation" k. FAA Notice of Proposed Rule Making 2006-NM-224-AD l. Service Related Problem (SRP) 767-SRP-56-0012 and 767-SRP-56-0023 m. Standard Overhaul Practices Manual (SOPM) 20-10-03, 20-41-02, 20-43-03, 20-50-10, 20-50-19 2. Data supplied with this Service Bulletin: a. Drawings: ADCNDCN/REVSheetTitleDrawing No --1MISCELLANEOUS TOOL WRENCH ASSY - FLIGHT DECK WINDOW TRACK ROLLER BEARING STUD MIT141T4890 3. Installation Drawings Used in the Preparation of this Service Bulletin: TitleDrawing Number Clevis and Cam Lock Installation - Cab Structure, Number 2 Window141T4834 Operating Mechanism Installation - Number 2 Openable Window141T4843 Cover Installation - Cam Block Torque Tube232T1449 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-SectionPublication 56-11767 Maintenance Manual 56-11767 Illustrated Parts Catalog BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 07, 2006 767-56A0010Revision 3: March 03, 2011 29 of 141 BOEING SERVICE BULLETIN 767-56A0010 ### Page 30 Chapter-SectionPublication 56-11-12767 Component Maintenance Manual 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 does not affect FCS, therefore DTIs are not necessary. L. Interchangeability and Intermixability of Parts Refer to Paragraph 2.C., Parts Necessary For Each Airplane, for interchangeability and intermixability information. BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 07, 2006 767-56A0010Revision 3: March 03, 2011 30 of 141 BOEING SERVICE BULLETIN 767-56A0010 ### Page 31 2. MATERIAL INFORMATION A. Material - Price and Availability Boeing can supply the kits shown in Paragraph 2.C., Parts Necessary For Each Airplane as shown below. If there is a limit to the quantity (QTY) of available kits, a supply sequence is given by Spares. More kits become available as shown in the Reorder Lead Time (ROLT). ROLT is calculated from the date Boeing gets the purchase order. Unit Price thru May 30/08 ROLT (Weeks) QTYDateNameKit Number $4,993.0016--SUB KIT - FLIGHT DECK WINDOW #2 - LINK ARM MODIFICATION - TORQUE TUBE ASSY (CRANK/ROLLER ASSY) 015T1784-3 $719.0024--SUB KIT - FLIGHT DECK WINDOW #2 - LINK ARM MODIFICATION - CAM BLOCK 015T1784-4 $1040.0041--SUB KIT - FLIGHT DECK WINDOW #2 - LINK ARM MODIFICATION - LINK BRACKETS 015T1784-5 $261.0024--SUB KIT - FLIGHT DECK WINDOW #2 - LINK ARM MODIFICATION - MISC ITEMS 015T1784-6 $7,013.004116/20/06TOP KIT - FLIGHT DECK WINDOW #2 - LINK ARM MODIFICATION 015T1784-7 The kits are subject to the terms and conditions of the Boeing standard purchase order acknowledgment. After the Unit Price date, new price and ROLT data is applicable. Prices are in United States dollars. Terms: Net 30 days. Reference this service bulletin and submit your purchase order by one of the methods that follow: 1. Order on-line via ATA Spec 2000 or Boeing Part Page 2. Fax to (206) 662-7145 3. Spares Customer Support - MC 36-65 Boeing Spares Department P.O. Box 3707 Seattle, Washington 98124-2207 USA BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 07, 2006 767-56A0010Revision 3: March 03, 2011 31 of 141 BOEING SERVICE BULLETIN 767-56A0010 ### Page 32 B. Industry Support Information Boeing warranty remedies are not available for the configuration changes, inspection and/or repair procedures 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 015T1784-7 top kit and the items shown in Paragraph 2.C.2., Parts and Materials Supplied by the Operator, are necessary for each airplane if you want to replace all parts. NOTE: One 015T1784-6 sub kit and the items shown in Paragraph 2.C.2., Parts and Materials Supplied by the Operator, are necessary for each airplane if you want to rework all parts. OPERATOR REWORK / REPLACEMENT OPTIONS LINK BRACKET MODIFI- CATION CAM BLOCK MODIFICA- TION CRANK/ROLLER AS- SEMBLY MODIFICA- TION AIRPLANE GROUP Replace option Rework op- tion Replace option Rework op- tion Replace option Rework op- tion YES (c) (e)NO (c)YES (b)YESYES (a)YESGroup 1 YES (d) (e)YES (d)YES (b)YESYES (a)YESGroup 2 YES (c) (e)NO (c)YES (b)YESYES (a)YESGroup 3 YES (c) (e)NO (c)YES (b)YESYES (a)YESGroup 4 YES (c) (e)NO (c)YES (b)YESYES (a)YESGroup 5 YES (c) (e)NO (c)YES (b)YESYES (a)YESGroup 6 YES (d) (e)YES (d)YES (b)YESYES (a)YESGroup 7 (a) If the operator replaces the crank/roller assemblies and reworks all other parts, one 015T1784-3 sub kit, one 015T1784-6 sub kit and the items shown in Paragraph 2.C.2., Parts and Materials Supplied by the Operator, are necessary for each airplane. (b) If the operator replaces the cam blocks and reworks all other parts, one 015T1784-4 sub kit, one 015T1784-6 sub kit and the items shown in Paragraph 2.C.2., Parts and Materials Supplied by the Operator, are necessary for each airplane. (c) These airplanes do not have 141T4890-15 and 141T4890-16 link brackets installed that can be reworked. The existing link brackets will need to be replaced. (d) These airplanes have 141T4890-15 and 141T4890-16 link brackets installed that can be reworked. As an option the operator can replace the link brackets. (e) If the operator replaces the link brackets and reworks all other parts, one 015T1784-5 sub kit, one 015T1784-6 sub kit and the items shown in Paragraph 2.C.2., Parts and Materials Supplied by the Operator, are necessary for each airplane. BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 07, 2006 767-56A0010Revision 3: March 03, 2011 32 of 141 BOEING SERVICE BULLETIN 767-56A0010 ### Page 33 Kit 015T1784 NotesExisting Part Number NameQTYNew Part Num- ber -7 Sub Kit - Flight Deck Window #2 - Link Arm Modification - Torque Tube Assembly (Crank/Roller Assembly) 1015T1784-3 Sub Kit - Flight Deck Window #2 - Link Arm Modification - Cam Blocks 1015T1784-4 Sub Kit - Flight Deck Window #2 - Link Arm Modification - Link Brackets 1015T1784-5 Sub Kit - Flight Deck Window #2 - Link Arm Modification - Misc. Items 1015T1784-6 Kit 015T1784 NotesExisting Part Number NameQTYNew Part Number -3-4-5-6 Sub Kit - Flight Deck Window #2 - Link Arm Modification - Torque Tube Assy (Crank/Roller Assem- bly) -...015T1784-3 Sub Kit - Flight Deck Window #2 - Link Arm Modification - Cam Blocks .-..015T1784-4 Sub Kit - Flight Deck Window #2 - Link Arm Modification - Link Brackets ..-.015T1784-5 Sub Kit - Flight Deck Window #2 - Link Arm Modification - Misc. Items ...-015T1784-6 (a) (b)Laminated Shims...2141T4836-9 (a) (b)Torque Tube Assy (Crank/Roller Assembly) 2...141T4865-27 (a) (b) (c)Cam Block.1..141T4867-25 (a) (b) (c)Cam Block.1..141T4867-26 (a) (b)Link Bracket - LH..1.141T4890-19 (a) (b)Link Bracket - RH..1.141T4890-20 (a) (b) (d)Pin...4BACP18BC02A02P (a) Discard the existing part. (b) You cannot use the existing part to replace the new or changed part. BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 07, 2006 767-56A0010Revision 3: March 03, 2011 33 of 141 BOEING SERVICE BULLETIN 767-56A0010 ### Page 34 Kit 015T1784 NotesExisting Part Number NameQTYNew Part Number -3-4-5-6 (c) 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 Service Letter 767-SL-00- 014 for more information. (d) These parts are no longer necessary in Revision 1 of this service bulletin. 2. Parts and Materials Supplied by the Operator: NotesNameQTYPart Number / Specification (a)Chemical Conversion Coating4 ouncesType 2, Class A (b)Primer4 ouncesBMS 10-11, Type I (b)Sealant2 ouncesBMS 5-95, Type I, Class B-1/2 or B-2 (b)Flat Enamel4 ouncesBMS 10-11, Type II (c)Lockwire24 inchesMS20995C32 (a) Refer to the Boeing Standard Overhaul Practices Manual 20-43-03 or 767 Structural Repair Manual, Chapter 51, for material sources. (b) See the Qualified Products List at the end of the Boeing Material Specification (BMS) for supplier data. (c) See the Qualified Products List of the appropriate specification for supplier data. 3. Parts Modified and Reidentified: The parts shown below may be changed as shown in this service bulletin. The quantity (QTY) is the number of parts changed on each airplane. NotesNew Part NumberNameQTYExisting Part Number (a) (b) (c)141T4890-19Link Bracket1141T4890-15 (a) (b) (c)141T4890-20Link Bracket1141T4890-16 (a) (b) (d)141T4867-25Cam Block1141T4867-7 Cam Block1141T4867-9 Cam Block1141T4867-11 Cam Block1141T4867-13 Cam Block1141T4867-17 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 07, 2006 767-56A0010Revision 3: March 03, 2011 34 of 141 BOEING SERVICE BULLETIN 767-56A0010 ### Page 35 NotesNew Part NumberNameQTYExisting Part Number (a) (b) (d)141T4867-26Cam Block1141T4867-8 Cam Block1141T4867-10 Cam Block1141T4867-12 Cam Block1141T4867-14 Cam Block1141T4867-18 (a)(e)Torque Tube Assem- bly (Crank/Roller As- sembly) 1141T4865-10 Torque Tube Assem- bly (Crank/Roller As- sembly) 1141T4865-21 (a) (g)(f)No. 2 Openable Win- dow Assembly 1015T0195-7 thru -16 (a)(f)No. 2 Openable Win- dow Assembly 1141T0012-( ) (a)(f)No. 2 Openable Win- dow Assembly 1141T4835-1 thru -18 (a)(f)No. 2 Openable Win- dow Assembly 1141T4835-21, -22 (a)(f)No. 2 Openable Win- dow Assembly 1141T4835-26 thru -28 (a)(f)No. 2 Openable Win- dow Assembly 1141T4835-36 thru -38 (a)(f)No. 2 Openable Win- dow Assembly 1141T4835-41, -43 (a)(f)No. 2 Openable Win- dow Assembly 1141T4835-45, -46 (a) (b)141T4835-67No. 2 Openable Win- dow Assembly 1141T4835-47 (a) (b)141T4835-68No. 2 Openable Win- dow Assembly 1141T4835-48 (a)(f)No. 2 Openable Win- dow Assembly 1141T4835-503, -504 (a)(f)No. 2 Openable Win- dow Assembly 1141T4835-507, -508 (a) Make the change given in this service bulletin. (b) The "New Part Number" is the part number after the change given in this service bulletin. (c) This part is used in production. BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 07, 2006 767-56A0010Revision 3: March 03, 2011 35 of 141 BOEING SERVICE BULLETIN 767-56A0010 ### Page 36 NotesNew Part NumberNameQTYExisting Part Number (d) The 141T4867-25/-26 cam blocks are not installed in production. These parts are for service bulletin use only. (e) There is no new part number available for the crank/roller assembly. (f) There is no equivalent production part number for the window assembly after the change is made. Apply the service bulletin number on the window assembly to indicate that the service bulletin modification has been accomplished. Apply the service bulletin number adjacent to the existing part number, or in another operator preferred location. (g) These are rework configurations that may exist if service bulletin 767-56-0002 is incorporated on some production window assemblies. If necessary, refer to service bulletin 767-56-0002 for more information. NOTE: As of the Revision 1 date on this service bulletin, the following window assembly part numbers have been installed in production on airplanes after line number 929. These window assemblies have had changes incorporated that are equivalent to the window assembly modification given in this service bulletin. NameExisting Part Number No. 2 Openable Window Assembly141T4835-65 No. 2 Openable Window Assembly141T4835-66 No. 2 Openable Window Assembly141T4835-67 No. 2 Openable Window Assembly141T4835-68 No. 2 Openable Window Assembly141T4835-71 No. 2 Openable Window Assembly141T4835-72 No. 2 Openable Window Assembly141T4835-73 No. 2 Openable Window Assembly141T4835-74 4. Parts Removed and Not Replaced: None. D. Parts Necessary to Change Spares To get the parts shown below, refer to Paragraph 2.A., Material - Price and Availability. NotesQTYNamePart Number (a)1 for each number 2 window. Torque Tube Assembly (Crank/Roller Assembly) 141T4865-27 (a) A spare window assembly can be changed to the new configuration by replacing or reworking the crank/roller assembly. BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 07, 2006 767-56A0010Revision 3: March 03, 2011 36 of 141 BOEING SERVICE BULLETIN 767-56A0010 ### Page 37 E. Special Tooling - Price and Availability Boeing can supply the tools shown in Paragraph 2.F., Special Tooling Necessary to do this Service Bulletin. Send a Purchase Order to the Director of Spares. Give this service bulletin number and the date the tools will be used. Purchase Data: Unit Price thru May 31/2008 NameTool Kit Number $1977.00Miscellaneous Tool - Wrench Assembly - Flight Deck Window Track Roller Bearing Stud (a) MIT141T4890 (a) This tool will decrease the time necessary to access and remove/install the link bracket when you do the modification given in this service bulletin. However, this tool is not required to do the modification. Instead of purchasing the tool, operators can fabricate the tool using the tool drawing identified in paragraph 1.J.2., Data supplied with this Service Bulletin. Alternatively, operators can use their own tool. The tools are subject to the terms and conditions of the Boeing standard purchase order acknowledgement. After the Price date, new price data is applicable. Prices are in United States dollars. Terms: Net 30 days. Reference this service bulletin number and submit purchase order by one of the methods that follow: 1. Order on-line via ATA Spec 2000 or Boeing Part Page 2. Fax to (206) 662-7145 3. Spares Customer Support - MC 36-65 Boeing Spares Department P.O. Box 3707 Seattle, Washington 98124-2207 USA (Service Bulletin 767-56A0010) F. 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. NameTool Kit Number Miscellaneous Tool - Wrench Assembly - Flight Deck Window Track Roller Bearing Stud (a) MIT141T4890 (a) This tool will decrease the time necessary to access and remove/install the link bracket when you do the modification given in this service bulletin. However, this tool is not required to do the modification. Instead of purchasing the tool, operators can fabricate the tool using the tool drawing identified in paragraph 1.J.2., Data supplied with this Service Bulletin. Alternatively, operators can use their own tool. BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 07, 2006 767-56A0010Revision 3: March 03, 2011 37 of 141 BOEING SERVICE BULLETIN 767-56A0010 ### Page 38 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 07, 2006 767-56A0010Revision 3: March 03, 2011 38 of 141 BOEING SERVICE BULLETIN 767-56A0010 BLANK PAGE ### Page 39 3. ACCOMPLISHMENT INSTRUCTIONS A. GENERAL INFORMATION CAUTION: KEEP THE WORK AREA, WIRES AND ELECTRICAL BUNDLES CLEAN OF METAL PARTICLES OR CONTAMINATION WHEN YOU USE TOOLS. UNWANTED MATERIAL, METAL PARTICLES OR CONTAMINATION CAUGHT IN WIRE BUNDLES CAN CAUSE DAMAGE TO THE BUNDLES. DAMAGED WIRE BUNDLES CAN CAUSE SPARKS OR OTHER ELECTRICAL DAMAGE. NOTE: 1. Manual titles are referred to by acronyms. Refer to Paragraph 1.J., References, for definition of the acronyms. 2. Obey all of the warnings and cautions given in the specified manual sections. 3. Unless shown differently, these dimensions and tolerances are used: — Linear dimensions are in inches. — Tolerance on linear dimensions, other than rivet and bolt edge margins, is plus or minus 0.03 inch. — Tolerance on rivet and bolt edge margin is plus or minus 0.05 inch. — Angular tolerance is plus or minus 2 degrees. — Hole dimensions for standard solid rivets are given in 767 Structural Repair Manual, Chapter 51. — Torque limits to tighten nuts and bolts are given in 767 Structural Repair Manual, Chapter 51. 4. For approved fastener and process material substitutions, refer to 767 Structural Repair Manual, Chapter 51, Alternate fasteners are given in 767 Structural Repair Manual Chapter 51 and Boeing Drawing 012W6100. 5. If the length of fasteners specified in this service bulletin do not meet the installation standards, fasteners of the same specification, or an approved substitute, one grip length longer or shorter may be used. 6. These work instructions refer to procedures included on 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. BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 07, 2006 767-56A0010Revision 3: March 03, 2011 39 of 141 BOEING SERVICE BULLETIN 767-56A0010 ### Page 40 7. 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. 8. Removal of the number 2 window assembly is not necessary to perform the window assembly modifications given in this service bulletin. However, if an operator prefers to remove the window assembly to perform the modification, it is acceptable to do so. Refer to 767 AMM 56-11-02 as an accepted procedure for removal/installation of the number 2 window assembly. 9. When this service bulletin refers to modification of the airplane vs. modification of the window assembly, the Link Bracket rework/replacement and the Cam Block rework/replacement are considered the airplane modifications, while the Crank/Roller Assembly rework/replacement is considered the window assembly modification. B. WORK INSTRUCTIONS PART 1 - INSPECTION - LEFT SIDE 1. Do a general visual inspection of the Number 2 Openable Window Link Arm to determine if the Link Arm is in the over-center position when the window is fully closed as given in Figure 27. NOTE: As an option to inspection, do all the modification steps as given in "PART 4 - MODIFICATION". a. If the link arm is in the over-center position, no modification or adjustment is required. b. If the link arm is not in the over-center position, attempt to rig the window so that the link arm is over-center. Refer to 767 AMM 56-11-02 , "NO. 2 OPENABLE WINDOW - ADJUSTMENT/TEST" instructions as an accepted procedure. (1) If the over-center position of the link arm can be achieved by rigging the window, no further modification or adjustment is required. (2) If the over-center position of the link arm cannot be achieved by rigging the window, do the airplane modifications and/or window assembly modifications as given in "PART 4 - MODIFICATION". Do the modifications, as necessary, to achieve the over-center position of the link arm. 2. No further action is required for the left side of the airplane. PART 2 - (Deleted - Revision 3) 1. Part 2 steps are deleted. PART 3 - (Deleted - Revision 3) 1. Part 3 steps are deleted. BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 07, 2006 767-56A0010Revision 3: March 03, 2011 40 of 141 BOEING SERVICE BULLETIN 767-56A0010 ### Page 41 PART 4 - MODIFICATION - LEFT SIDE 1. Airplane modifications: a. Group 1, 4, 6, Configuration 1: Remove the link bracket from the carriage assembly lower track operating mechanism as given in Figure 1. b. Group 1, Configuration 2; Group 2-3; Group 4, Configuration 2; Group 5; Group 6, Configuration 2; Group 7: Remove the link bracket from the carriage assembly lower track operating mechanism as given in Figure 2. c. Remove the cam block from the upper number 2 window frame as given in Figure 8. d. Group 2, 7: Rework the link bracket as given in Figure 3. NOTE: The existing link brackets can be reworked to the required new configuration or the new configuration parts can be procured from Boeing. e. Rework the cam block as given in Figure 9. NOTE: The existing cam blocks can be reworked to the required new configuration or the new configuration parts can be procured from Boeing. f. Group 1, 6, Configuration 1: Install the reworked/new link bracket on the carriage assembly lower track operating mechanism as given in Figure 4. NOTE: It is recommended that operators accomplish service bulletin 767-56-0004, "WINDOWS - Number 2 Openable Window - Window Stop Installation", due to common access. g. Group 1, Configuration 2; Group 2-3; Group 6, Configuration 2; Group 7: Install the reworked/new link bracket on the carriage assembly lower track operating mechanism as given in Figure 5. h. Group 4, Configuration 1: Install the reworked/new link bracket on the carriage assembly lower track operating mechanism as given in Figure 6. BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 07, 2006 767-56A0010Revision 3: March 03, 2011 41 of 141 BOEING SERVICE BULLETIN 767-56A0010 ### Page 42 NOTE: It is recommended that operators accomplish service bulletin 767-56-0004, "WINDOWS - Number 2 Openable Window - Window Stop Installation", due to common access. i. Group 4, Configuration 2; Group 5: Install the reworked/new link bracket on the carriage assembly lower track operating mechanism as given in Figure 7. j. Install the reworked/new cam block on the upper number 2 window frame as given in Figure 10. 2. Window assembly modifications: a. Remove the crank/roller assembly from the number 2 window as given in Figure 11. b. If the removed crank/roller assembly is part number 141T4865-21 then rework the crank/roller assembly as given in Figure 13. NOTE: The existing crank/roller assemblies can be reworked to the required new configuration or the new configuration parts can be procured from Boeing. c. If the removed crank/roller assembly is part number 141T4865-10 then rework the crank/roller assembly as given in Figure 12. NOTE: The existing crank/roller assemblies can be reworked to the required new configuration or the new configuration parts can be procured from Boeing. d. Install the reworked/new crank/roller assembly on the number 2 window as given in Figure 14. 3. Rig the window assembly and make sure the link arm is over-center. Refer to 767 AMM 56-11-02, "NO. 2 OPENABLE WINDOW - ADJUSTMENT/TEST" instructions as an accepted procedure. NOTE: The section of 767 AMM 56-11-02 titled "NO. 2 OPENABLE WINDOW - ADJUSTMENT/TEST", includes the necessary adjustment and test procedures to ensure appropriate window operation after incorporation of this service bulletin. 4. Permanently install the cam block parts using the sequence shown in Figure 10. If a shim is installed under the cam block, remove the cam block and apply BMS 5-95, Type I, Class B-1/2 or B-2 faying surface seal to the shim. Refer to SOPM 20-50-19 as an accepted procedure for sealant application. 5. Check the window assembly. Refer to 767 AMM 56-11-02, "NO. 2 INSPECTION/CHECK" instructions as an accepted procedure. NOTE: The section of 767 AMM 56-11-02 titled "NO. 2 OPENABLE WINDOW - INSPECTION/CHECK", includes the necessary inspections and checks to ensure appropriate window operation after incorporation of this service bulletin. 6. No further action is required for the left side of the airplane. BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 07, 2006 767-56A0010Revision 3: March 03, 2011 42 of 141 BOEING SERVICE BULLETIN 767-56A0010 ### Page 43 PART 5 - INSPECTION - RIGHT SIDE 1. Do a general visual inspection of the Number 2 Openable Window Link Arm to determine if the Link Arm is in the over-center position when the window is fully closed as given in Figure 28. NOTE: As an option to inspection, do all the modification steps as given in "PART 8 - MODIFICATION". a. If the link arm is in the over-center position, no modification or adjustment is required. b. If the link arm is not in the over-center position, attempt to rig the window so that the link arm is over-center. Refer to 767 AMM 56-11-02 , "NO. 2 OPENABLE WINDOW - ADJUSTMENT/TEST" instructions as an accepted procedure. (1) If the over-center position of the link arm can be achieved by rigging the window, no further modification or adjustment is required. (2) If the over-center position of the link arm cannot be achieved by rigging the window, do the airplane modifications and/or window assembly modifications as given in "PART 8 - MODIFICATION". Do the modifications, as necessary, to achieve the over-center position of the link arm. 2. No further action is required for the right side of the airplane. PART 6 - (Deleted - Revision 3) 1. Part 6 steps are deleted. PART 7 - (Deleted - Revision 3) 1. Part 7 steps are deleted. PART 8 - MODIFICATION - RIGHT SIDE 1. Airplane modifications: a. Group 1, 4, 6, Configuration 1: Remove the link bracket from the carriage assembly lower track operating mechanism as given in Figure 15. b. Group 1, Configuration 2; Group 2-3; Group 4, Configuration 2; Group 5; Group 6, Configuration 2; Group 7: Remove the link bracket from the carriage assembly lower track operating mechanism as given in Figure 16. c. Remove the cam block from the upper number 2 window frame as given in Figure 22. d. Group 2, 7: Rework the link bracket as given in Figure 17. NOTE: The existing link brackets can be reworked to the required new configuration or the new configuration parts can be procured from Boeing. BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 07, 2006 767-56A0010Revision 3: March 03, 2011 43 of 141 BOEING SERVICE BULLETIN 767-56A0010 ### Page 44 e. Rework the cam block as given in Figure 23. NOTE: The existing cam blocks can be reworked to the required new configuration or the new configuration parts can be procured from Boeing. f. Group 1, 6, Configuration 1: Install the reworked/new link bracket on the carriage assembly lower track operating mechanism as given in Figure 18. NOTE: It is recommended that operators accomplish service bulletin 767-56-0004, "WINDOWS - Number 2 Openable Window - Window Stop Installation", due to common access. g. Group 1, Configuration 2; Group 2-3; Group 6, Configuration 2; Group 7: Install the reworked/new link bracket on the carriage assembly lower track operating mechanism as given in Figure 19. h. Group 4, Configuration 1: Install the reworked/new link bracket on the carriage assembly lower track operating mechanism as given in Figure 20. NOTE: It is recommended that operators accomplish service bulletin 767-56-0004, "WINDOWS - Number 2 Openable Window - Window Stop Installation", due to common access. i. Group 4, Configuration 2; Group 5: Install the reworked/new link bracket on the carriage assembly lower track operating mechanism as given in Figure 21. j. Install the reworked/new cam block on the upper number 2 window frame as given in Figure 24. 2. Window assembly modifications: a. Remove the crank/roller assembly from the number 2 window as given in Figure 25. b. If the removed crank/roller assembly is part number 141T4865-21 then rework the crank/roller assembly as given in Figure 13. NOTE: The existing crank/roller assemblies can be reworked to the required new configuration or the new configuration parts can be procured from Boeing. c. If the removed crank/roller assembly is part number 141T4865-10 then rework the crank/roller assembly as given in Figure 12. NOTE: The existing crank/roller assemblies can be reworked to the required new configuration or the new configuration parts can be procured from Boeing. d. Install the reworked/new crank/roller assembly on the number 2 window as given in Figure 26. 3. Rig the window assembly and make sure the link arm is over-center. Refer to 767 AMM 56-11-02, "NO. 2 OPENABLE WINDOW - ADJUSTMENT/TEST" instructions as an accepted procedure. BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 07, 2006 767-56A0010Revision 3: March 03, 2011 44 of 141 BOEING SERVICE BULLETIN 767-56A0010 ### Page 45 NOTE: The section of 767 AMM 56-11-02 titled "NO. 2 OPENABLE WINDOW - ADJUSTMENT/TEST", includes the necessary adjustment and test procedures to ensure appropriate window operation after incorporation of this service bulletin. 4. Permanently install the cam block parts using the sequence shown in Figure 24. If a shim is installed under the cam block, remove the cam block and apply BMS 5-95, Type I, Class B-1/2 or B-2 faying surface seal to the shim. Refer to SOPM 20-50-19 as an accepted procedure for sealant application. 5. Check the window assembly. Refer to 767 AMM 56-11-02, "NO. 2 INSPECTION/CHECK" instructions as an accepted procedure. NOTE: The section of 767 AMM 56-11-02 titled "NO. 2 OPENABLE WINDOW - INSPECTION/CHECK", includes the necessary inspections and checks to ensure appropriate window operation after incorporation of this service bulletin. 6. No further action is required for the right side of the airplane. PART 9 - CLOSE ACCESS 1. Put the airplane back to a serviceable condition. 2. This step is deleted. 3. This step is deleted. BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 07, 2006 767-56A0010Revision 3: March 03, 2011 45 of 141 BOEING SERVICE BULLETIN 767-56A0010 ### Page 46 (OCR) BOEING SERVICE BULLETIN 767-56A0010 This Figure applies only to: Group 1, 4, 6, Configuration 1. OPERATING CRANK SEE → FWD INBD FIGURE 1: NUMBER 2 WINDOW - LINK BRACKET - REMOVAL - LEFT SIDE (SHEET 1 OF 5) Original Issue: September 07, 2006 Revision 3 March 03, 2011 767-56A0010 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 46 of 141 ### Page 47 (OCR) BOEING SERVICE BULLETIN 767-56A0010 LOWER TRACK CLOSURE TRACK SUPPORT ASSEMBLY (GASPER AIR) SEE CHANNEL ASSEMBLY SEE C OPERATING MECHANISM BALL SCREW BEARING BLOCK ASSEMBLY FWD CHANNEL ASSEMBLY NYLON BLOCK (IF INSTALLED) LOWER TRACK • FWD D59128 FIGURE 1: NUMBER 2 WINDOW - LINK BRACKET - REMOVAL - LEFT SIDE (SHEET 2 OF 5) Original Issue: September 07, 2006 Revision 3 March 03, 2011 767-56A0010 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 47 of 141 ### Page 48 FIGURE 1: NUMBER 2 WINDOW - LINK BRACKET - REMOVAL - LEFT SIDE (SHEET 3 OF 5) BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 07, 2006 767-56A0010Revision 3 March 03, 2011 48 of 141 BOEING SERVICE BULLETIN 767-56A0010 ### Page 49 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 one side of the airplane. NOTE: Tool number MIT141T4890 or similar tool can be used to remove the link bracket. If MIT141T4890 or similar tool is used, steps 1 through 12, 16, and 17 of the following procedure will not be necessary. Tool MIT141T4890 is designed to hold the heads of the roller bolts so that the link bracket can be removed from the carriage assembly without removing the carriage assembly from the airplane. Tool MIT141T4890 is available for purchase from Boeing. Refer to paragraph 2.E., Special Tooling - Price and Availability for more information. Instead of purchasing the tool, operators can fabricate the tool using the tool drawing identified in paragraph 1.J.2., Data supplied with this Service Bulletin. Alternatively, operators can use their own tool to hold the heads of the roller bolts. MORE DATAQTYIDENTIFICATIONNAMETASKSTEP 1232T1429-31Support Assembly (Gasper Air) Remove / Keep1 4-Fastener 1232T1430-11Closure TrackRemove / Keep2 8-Screw Washers not shown.4AN960JD10LLWasherRemove / Keep3 4BACS12FA3K8Screw 1-BoltRemove / Keep4 1-WasherRemove / Keep5 1-Nylon BlockRemove / Keep6 1141T4887-( )Bearing Block As- sembly Remove / Keep7 Keep all attaching fas- teners from the forward and aft end of the channel assembly. 1141T4879-( )Channel AssemblyRemove / Keep8 --Fasteners Move the operating mechanism to the fur- thest aft position. 1-Window Operating Mechanism Move9 From flange (ball nut mounting). 2141T4923-1Bolt - Shoulder At- tachment Remove / Keep10 Refer to 767 AMM 20- 10-23 as an accepted procedure. 2MS20995C32LockwireRemove 2AN960-416LWasherRemove / Keep11 1141T4883Carriage AssemblyRemove / Keep12 2BACN10JC5CDNutRemove / Keep13 FIGURE 1: NUMBER 2 WINDOW - LINK BRACKET - REMOVAL - LEFT SIDE (SHEET 4 OF 5) BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 07, 2006 767-56A0010Revision 3 March 03, 2011 49 of 141 BOEING SERVICE BULLETIN 767-56A0010 ### Page 50 MORE DATAQTYIDENTIFICATIONNAMETASKSTEP Quantity will depend on the type of bearing that is installed. -NAS1149D0563J or AN960PD516 WasherRemove / Keep14 (a) 1141T4890-( )Link BracketRemove / Keep15 NOTE: The 141T4890-1/-9/-501 Link Brackets can not be reworked and will need to be discarded. 2NAS43DD5-13FCSleeveRemove / Keep16 2MS21432-5R14A or BACB10AF5N14HSA or HRS3CAR16 Bearing (roller bolt)Remove / Keep17 (a) Record the number of washers under each nut. This information will be used during installation. The number of washers under each nut will depend on which bearing exists (see Step 17). If MS21432-5R14A or BACB10AF5N14HSA bearing is installed, one washer is expected under each nut (as shown). If HRS3CAR16 bearing is installed, three washers are expected under each nut (not shown). FIGURE 1: NUMBER 2 WINDOW - LINK BRACKET - REMOVAL - LEFT SIDE (SHEET 5 OF 5) BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 07, 2006 767-56A0010Revision 3 March 03, 2011 50 of 141 BOEING SERVICE BULLETIN 767-56A0010 ### Page 51 (OCR) BOEING SERVICE BULLETIN 767-56A0010 This Figure applies only to: Group 1, Configuration 2; Group 2-3; Group 4, Configuration 2; Group 5; Group 6, Configuration 2; Group 7. OPERATING CRANK 75778 SEE UP → FWD INBD D59677 FIGURE 2: NUMBER 2 WINDOW - LINK BRACKET - REMOVAL - LEFT SIDE (SHEET 1 OF 5) Original Issue: September 07, 2006 Revision 3 March 03, 2011 767-56A0010 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 51 of 141 ### Page 52 (OCR) BOEING SERVICE BULLETIN 767-56A0010 LOWER TRACK CLOSURE TRACK 2 SUPPORT ASSEMBLY (GASPER AIR) SEE CHANNEL ASSEMBLY OPERATING SEE C MECHANISM BALL SCREW BEARING BLOCK ASSEMBLY → FWD CHANNEL ASSEMBLY LOWER TRACK → FWD D59682 FIGURE 2: NUMBER 2 WINDOW - LINK BRACKET - REMOVAL - LEFT SIDE (SHEET 2 OF 5) Original Issue: September 07, 2006 Revision 3 March 03, 2011 767-56A0010 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 52 of 141 ### Page 53 FIGURE 2: NUMBER 2 WINDOW - LINK BRACKET - REMOVAL - LEFT SIDE (SHEET 3 OF 5) BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 07, 2006 767-56A0010Revision 3 March 03, 2011 53 of 141 BOEING SERVICE BULLETIN 767-56A0010 ### Page 54 The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY numbers shown below are the number of parts necessary for one side of the airplane. NOTE: Tool number MIT141T4890 or similar tool can be used to remove the link bracket. If MIT141T4890 or similar tool is used, steps 1 through 12, 16, and 17 of the following procedure will not be necessary. Tool MIT141T4890 is designed to hold the heads of the roller bolts so that the link bracket can be removed from the carriage assembly without removing the carriage assembly from the airplane. Tool MIT141T4890 is available for purchase from Boeing. Refer to paragraph 2.E., Special Tooling - Price and Availability for more information. Instead of purchasing the tool, operators can fabricate the tool using the tool drawing identified in paragraph 1.J.2., Data supplied with this Service Bulletin. Alternatively, operators can use their own tool to hold the heads of the roller bolts. MORE DATAQTYIDENTIFICATIONNAMETASKSTEP 1232T1429-31Support Assembly (Gasper Air) Remove / Keep1 4-Fastener 1232T1430-11Closure TrackRemove / Keep2 8-Screw Washers not shown.4AN960JD10LLWasherRemove / Keep3 4BACS12FA3K8Screw 1-BoltRemove / Keep4 1-WasherRemove / Keep5 1141T4921-9Stop AssemblyRemove / Keep6 1141T4887-( )Bearing Block As- sembly Remove / Keep7 Keep all attaching fas- teners from the forward and aft end of the channel assembly. 1141T4879-( )Channel AssemblyRemove / Keep8 --Fasteners Move the operating mechanism to the fur- thest aft position. 1-Window Operating Mechanism Move9 From flange (ball nut mounting). 2141T4923-1Bolt - Shoulder At- tachment Remove / Keep10 Refer to 767 AMM 20- 10-23 as an accepted procedure. 2MS20995C32LockwireRemove 2AN960-416LWasherRemove / Keep11 1141T4883Carriage AssemblyRemove / Keep12 2BACN10JC5CDNutRemove / Keep13 FIGURE 2: NUMBER 2 WINDOW - LINK BRACKET - REMOVAL - LEFT SIDE (SHEET 4 OF 5) BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 07, 2006 767-56A0010Revision 3 March 03, 2011 54 of 141 BOEING SERVICE BULLETIN 767-56A0010 ### Page 55 MORE DATAQTYIDENTIFICATIONNAMETASKSTEP Quantity will depend on the type of bearing that is installed. -NAS1149D0563J or AN960PD516 WasherRemove / Keep14 (a) 1141T4890-( )Link BracketRemove / Keep15 NOTE: The 141T4890-1/-9/-501 Link Brackets can not be reworked and will need to be discarded. 2NAS43DD5-13FCSleeveRemove / Keep16 2MS21432-5R14A or BACB10AF5N14HSA or HRS3CAR16 Bearing (roller bolt)Remove / Keep17 (a) Record the number of washers under each nut. This information will be used during installation. The number of washers under each nut will depend on which bearing exists (see Step 17). If MS21432-5R14A or BACB10AF5N14HSA bearing is installed, one washer is expected under each nut (as shown). If HRS3CAR16 bearing is installed, three washers are expected under each nut (not shown). FIGURE 2: NUMBER 2 WINDOW - LINK BRACKET - REMOVAL - LEFT SIDE (SHEET 5 OF 5) BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 07, 2006 767-56A0010Revision 3 March 03, 2011 55 of 141 BOEING SERVICE BULLETIN 767-56A0010 ### Page 56 (OCR) BOEING SERVICE BULLETIN 767-56A0010 This Figure applies only to: Group 2, 7. SEE I A 0.080 0.100 RADIUS B D59161 A-A FIGURE 3: NUMBER 2 WINDOW - LINK BRACKET - OPTIONAL REWORK - LEFT SIDE (SHEET 1 OF 2) Original Issue: September 07, 2006 Revision 3 March 03, 2011 767-56A0010 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 56 of 141 ### Page 57 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 one side of the airplane. MORE DATAQTYIDENTIFICATIONNAMETASKSTEP (a)1141T4890-15Link BracketChamfer1 (b)1141T4890-15Link BracketShot Peen2 To chamfered area. Refer to SOPM 20-43-03 as an accepted procedure. -Type 2, Class AChemical Conver- sion Coating Apply3 Refer to SOPM 20-41-02 as an accepted procedure. 1 coatBMS 10-11, Type IPrimerApply4 Refer to SOPM 20-41-02 as an accepted procedure. 1 coatBMS 10-11, Type IIFlat EnamelApply5 Part mark as 141T4890-19. Refer to SOPM 20-50-10 as an accepted procedure. 1141T4890-15Link BracketIdentify6 (a) Chamfer as shown. Break sharp edges. Surface roughness 125 RA. (b) Shot peen the chamfered area. Self-contained (manual) shot peening optional. Intensity 0.006 Almen to 0.011 Almen. Coverage 1.0 automated, 2.0 manual. Refer to SOPM 20-10-03 as an accepted procedure. FIGURE 3: NUMBER 2 WINDOW - LINK BRACKET - OPTIONAL REWORK - LEFT SIDE (SHEET 2 OF 2) BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 07, 2006 767-56A0010Revision 3 March 03, 2011 57 of 141 BOEING SERVICE BULLETIN 767-56A0010 ### Page 58 (OCR) BOEING SERVICE BULLETIN 767-56A0010 This Figure applies only to: Group 1, 6, Configuration 1. OPERATING _CRANK SEE > FWD INBD FIGURE 4: NUMBER 2 WINDOW - LINK BRACKET - INSTALLATION - LEFT SIDE (SHEET 1 OF 5) Original Issue: September 07, 2006 Revision 3 March 03, 2011 767-56A0010 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 58 of 141 ### Page 59 (OCR) BOEING SERVICE BULLETIN 767-56A0010 LOWER TRACK CLOSURE TRACK SUPPORT ASSEMBLY (GASPER AIR) SEE B CHANNEL ASSEMBLY OPERATING SEE C MECHANISM BALL SCREW BEARING BLOCK ASSEMBLY • FWD CHANNEL ASSEMBLY NYLON BLOCK (13 LOWER TRACK • FWD D59699 FIGURE 4: NUMBER 2 WINDOW - LINK BRACKET - INSTALLATION - LEFT SIDE (SHEET 2 OF 5) Original Issue: September 07, 2006 Revision 3 March 03, 2011 767-56A0010 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 59 of 141 ### Page 60 FIGURE 4: NUMBER 2 WINDOW - LINK BRACKET - INSTALLATION - LEFT SIDE (SHEET 3 OF 5) BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: September 07, 2006 767-56A0010Revision 3 March 03, 2011 60 of 141 BOEING SERVICE BULLETIN 767-56A0010 The text continues at https://openairdocs.org/service-documents/boeing/767-56a0010/file/abfce8505f86.md?from=61 --- OpenAirDocs.org is an independent research project of [Contrail Labs](https://contraillabs.com/). It is not affiliated with the FAA or the NTSB. Source documents are U.S. government works in the public domain, except the copies of manufacturers’ service documents, which belong to their rights holders.