# Boeing Alert Service Bulletin 747-53A2862: Revision 1 - Rights: © The Boeing Company. Filed by the FAA in regulations.gov docket FAA-2015-8429; AD 2016-16-10 incorporates this document by reference. Not covered by OpenAirDocs’ CC0 dedication. - Document: [Boeing Alert Service Bulletin 747-53A2862](https://openairdocs.org/service-documents/boeing/747-53a2862.md) - Title as filed: Boeing Service Information - Pages: 366 - PDF: https://openairdocs.org/files/sha256/8d/81/8d81bc5df324950879fd823f0efdff571eeabcd5a4869a5ee36c9d960338337a - Page: https://openairdocs.org/service-documents/boeing/747-53a2862/file/8d81bc5df324 ## 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 747 Service Bulletin ALERT Number: 747-53A2862 Original Issue: April 03, 2014 Revision 1: July 24, 2015 ATA System: 5300 SUBJECT: FUSELAGE - Main Frame - STA 320 Crown Frame and Window Post #3 - Inspection and Repair Export of this technology is controlled under the United States Export Administration Regulations (EAR) (15 CFR 300-774). An export license may be required before it is used for development, production or use by foreign persons from specific countries. The controller of this data has the individual responsibility to abide by all export laws. 9E991ECCN: BOEING PROPRIETARY, CONFIDENTIAL AND/OR TRADE SECRET Copyright © 2014 Boeing. Unpublished Work. All Rights Reserved. Treatment of this document and its content is governed by contract with Boeing. Rights to use this document are licensed on a per aircraft basis and such rights may not be transferable. For more information, contact The Boeing Company. Boeing, the Boeing signature, the Boeing symbol, 707, 717, 727, 737, 747, 757, 767, 777, 787, Dreamliner, BBJ, DC-8, DC-9, DC-10, KC-10, KC-46, KDC-10, MD-10, MD-11, MD-80, MD-88, MD-90, P-8, Poseidon and Boeing liveries are all trademarks owned by The Boeing Company; and no trademark license is granted in connection with this document unless provided in writing by Boeing. Original Issue: April 03, 2014 747-53A2862Revision 1: July 24, 2015 1 of 366 4.0 ### Page 2 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 03, 2014 747-53A2862Revision 1: July 24, 2015 2 of 366 BOEING SERVICE BULLETIN 747-53A2862 ALERTALERT BLANK PAGE ### Page 3 Table of Contents Revision Transmittal Sheet . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5 Summary . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9 1. PLANNING INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13 A. Effectivity . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13 1. Airplanes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13 2. Spares Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 23 B. Concurrent Requirements . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 24 C. Reason . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 24 D. Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25 E. Compliance . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 26 F. Approval . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 37 G. Manpower . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 37 H. Weight and Balance Changes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 39 I. Electrical Load Data . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 40 J. References . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 40 1. Existing Data: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 40 2. Data Supplied with this Service Bulletin: . . . . . . . . . . . . . . . . . . . . . . . . . . . 41 3. Installation Drawings Used in the Preparation of this Service Bulletin: . . . . . . . . . . . 41 K. Publications Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 41 L. Interchangeability and Intermixability of Parts . . . . . . . . . . . . . . . . . . . . . . . . . . . 42 M. Software Accomplishment Summary . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 42 2. MATERIAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 43 A. Material - Price and Availability . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 43 B. Industry Support Information . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 44 C. Parts Necessary for Each Airplane . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 45 1. Kits/Parts . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 45 2. Parts and Materials Supplied by the Operator . . . . . . . . . . . . . . . . . . . . . . . . 53 3. Parts Modified and Reidentified . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 53 4. Parts Removed and Not Replaced . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 53 D. Parts Necessary to Change Spares . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 53 E. Special Tooling - Price and Availability . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 54 F. Special Tooling Necessary to do this Service Bulletin . . . . . . . . . . . . . . . . . . . . . . . 54 3. ACCOMPLISHMENT INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 55 A. GENERAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 55 B. WORK INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 57 FIGURE 1: ACCESS WITH DRIPSHIELD MODIFICATION [Group 1-2] . . . . . . . . . . . . . . . . . 69 FIGURE 2: ACCESS WITH DRIPSHIELD MODIFICATION [Group 3-4] . . . . . . . . . . . . . . . . . 95 FIGURE 3: INSPECTION OF STA 320 CROWN FRAME, WINDOW POST#3 AND WINDOW UPPER SILL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 122 FIGURE 4: DISASSEMBLE STRUCTURE - LEFT SIDE [Group 1-2] . . . . . . . . . . . . . . . . . . 138 FIGURE 5: DISASSEMBLE STRUCTURE - RIGHT SIDE [Group 1-2] . . . . . . . . . . . . . . . . . 146 FIGURE 6: REMOVE FRAME INNER CHORD [Group 1, Configuration 1; Group 2] . . . . . . . . . 154 FIGURE 7: REMOVE FRAME INNER CHORD [Group 1, Configuration 2] . . . . . . . . . . . . . . . 158 FIGURE 8: SILL CHORD TRIM . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 162 FIGURE 9: REPLACE FRAME INNER CHORD + OUTBOARD WEB - LEFT SIDE [Group 1-2] . . . 168 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 03, 2014 747-53A2862Revision 1: July 24, 2015 3 of 366 BOEING SERVICE BULLETIN 747-53A2862 ALERTALERT ### Page 4 FIGURE 10: REPLACE FRAME INNER CHORD + OUTBOARD WEB - RIGHT SIDE [Group 1-2] . . 187 FIGURE 11: REPLACE FRAME OUTBOARD WEB ONLY - LEFT SIDE [Group 1-2] . . . . . . . . . . 206 FIGURE 12: REPLACE FRAME OUTBOARD WEB ONLY - RIGHT SIDE [Group 1-2] . . . . . . . . . 215 FIGURE 13: DISASSEMBLE STRUCTURE - LEFT SIDE [Group 3-4] . . . . . . . . . . . . . . . . . . 224 FIGURE 14: DISASSEMBLE STRUCTURE - RIGHT SIDE [Group 3-4] . . . . . . . . . . . . . . . . . 233 FIGURE 15: REMOVE FRAME INNER CHORD [Group 3, Configuration 1; Group 4] . . . . . . . . . 242 FIGURE 16: REMOVE FRAME INNER CHORD [Group 3, Configuration 2] . . . . . . . . . . . . . . . 246 FIGURE 17: REPLACE FRAME INNER CHORD + OUTBOARD WEB - LEFT SIDE [Group 3-4] . . . 250 FIGURE 18: REPLACE FRAME INNER CHORD + OUTBOARD WEB - RIGHT SIDE [Group 3-4] . . 267 FIGURE 19: REPLACE FRAME OUTBOARD WEB ONLY - LEFT SIDE [Group 3-4] . . . . . . . . . . 284 FIGURE 20: REPLACE FRAME OUTBOARD WEB ONLY - RIGHT SIDE [Group 3-4] . . . . . . . . . 293 FIGURE 21: ACCESS / RESTORE WITH DRIPSHIELD REMOVAL . . . . . . . . . . . . . . . . . . . 302 FIGURE 22: DRIPSHIELD RESTORE [Group 1-2] . . . . . . . . . . . . . . . . . . . . . . . . . . . . 307 FIGURE 23: DRIPSHIELD RESTORE [Group 3-4] . . . . . . . . . . . . . . . . . . . . . . . . . . . . 318 FIGURE 24: SILL PANEL REMOVE / REINSTALL . . . . . . . . . . . . . . . . . . . . . . . . . . . . 329 FIGURE 25: INSPECTION OF STA 340 FRAME . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 333 FIGURE 26: OVERSIZE FASTENERS FOR PART 5, PART 6 AND PART 7 REPAIRS . . . . . . . . 336 FIGURE 27: FASTENER REWORK [Group 1-2] . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 343 FIGURE 28: FASTENER REWORK [Group 3-4] . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 349 FIGURE 29: DRIPSHIELD BRACKET MODIFICATION OR FABRICATION . . . . . . . . . . . . . . . 355 APPENDIX A: PATTERN FOR FIBERGLASS PLIES OF SPLICE STRAP [Group 1-2] . . . . . . . . . . 358 APPENDIX B: PATTERN FOR FIBERGLASS PLIES OF SPLICE STRAP [Group 3-4] . . . . . . . . . . 359 APPENDIX C: LOGIC DIAGRAM SUPPLEMENT TO PARAGRAPH 1.E., COMPLIANCE . . . . . . . . 361 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 03, 2014 747-53A2862Revision 1: July 24, 2015 4 of 366 BOEING SERVICE BULLETIN 747-53A2862 ALERTALERT ### Page 5 Commercial Airplanes 747 Service Bulletin ALERT Revision Transmittal SheetNumber: 747-53A2862Original Issue: April 03, 2014 Revision 1: July 24, 2015 ATA System: 5300 SUBJECT: FUSELAGE - Main Frame - STA 320 Crown Frame and Window Post #3 - Inspection and Repair This revision includes all pages of the service bulletin. COMPLIANCE INFORMATION RELATED TO THIS REVISION Effects of this Revision on airplanes on which the Original Issue was previously accomplished: ActionConditionGroup Do PART 11 of Paragraph 3.B., Work Instructions in accordance with Paragraph 1.E., Compliance. If any of the following conditions apply: – The STA 320 crown frame outboard web, inner chord, or both were replaced in accordance with PART 5, PART 6 or PART 7 respectively of Paragraph 3.B., Work Instruc- tions of the Original Issue of this service bulletin. – An oversize fastener repair was done in accordance with PART 1 of Paragraph 3.B., Work Instructions of the Original Issue of this service bulletin at specific fastener hole(s) identified in the Original Issue of this service bulletin as follows: Group 1, 2 airplanes: Hole #11 or Hole #15. Group 3, 4 airplanes: Hole #11. All (a) (b) (a) The work given in PART 11 is to remove specific bolts installed in accordance with the Original Issue of this service bulletin and at each location to install a bolt with a countersunk washer under the head. The countersunk washer is needed to accommodate the fillet radius of the bolt. Instruction to install the coun- tersunk washer was inadvertently omitted from the Original Issue of this service bulletin. (b) The work given in PART 11 can be done with the next repeat inspection of the STA 320 crown frame. See Paragraph 1.D., Description for more information. The Federal Aviation Administration (FAA) will possibly release an Airworthiness Directive related to this service bulletin. The Airworthiness Directive will make the compliance tasks and times given in this service bulletin mandatory. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 03, 2014 747-53A2862Revision 1: July 24, 2015 5 of 366 ### Page 6 REASON FOR REVISION This revision is sent to give changed instruction and compliance times for the inspections given in this service bulletin. The inspections given in this service bulletin have been changed as a result of additional structural analysis performed by Boeing and because a frame crack has been found outside of the inspection area specified in the original issue of this service bulletin. After the original issue of this service bulletin Boeing conducted a more refined structural analysis of the fuselage crown area around STA 320 and this analysis shows that the structural integrity of the fuselage will be maintained with more crack damage than was shown by previous analysis. This result allows for an increase in the level of crack damage that must be detected with the inspections given in this service bulletin. Accordingly, the open hole High Frequency Eddy Current (HFEC) inspection for cracks in the STA 320 frame and Window Post #3 specified in the original issue of this service bulletin has been eliminated and replaced by an inspection for more extensive crack damage. Inspections accomplished in accordance with this revision will be done with Detailed and Surface HFEC inspection procedures only. Also, the compliance times for the initial and repeat inspections have been extended with this revision. Also, the area of the STA 320 crown frame to be inspected for cracks in accordance with this service bulletin has been extended inboard by approximately 6 inches because a frame crack was found outside of the inspection area specified in the original issue of this service bulletin. Also, a Surface HFEC inspection for cracks in the upper sill chord adjacent to the STA 320 crown frame has been added to this service bulletin because such cracks have been found previously and because it is necessary to consider and limit possible damage to this adjacent structure given the changes discussed above to relax the inspection of the STA 320 crown frame. This revision also gives changes to the work instruction for the dripshield modification. The dripshield modification is included in this service bulletin to give an alternative method of access for the structural inspection. The configuration created by the dripshield modification has not been changed with this revision, but the instruction for the modification has been changed to incorporate findings from the initial accomplishment of the modification which was done as a part of the service bulletin validation program. These sections were changed: 1. Paragraph 1.C., Reason: Updated service history data and added reasons for Revision 1. 2. Paragraph 1.D., Description: Revised description of inspection work and added a table to describe the effects of Revision 1 on airplanes changed in accordance with the Original Issue of this service bulletin. 3. Paragraph 1.E., Compliance: Revised Compliance Tables to reflect changes to inspection instruction and compliance times. Added Compliance Tables to cover "more work" associated with Revision 1 for airplanes changed in accordance with the Original Issue of this service bulletin. 4. Paragraph 1.G., Manpower: Added estimate for new Figure 25 inspection of left or right side of the STA 340 frame. Also revised estimates for the STA 320 frame inspection (Figure 3). Also revised the estimate for the dripshield modification for Group 3, 4 (Figures 2, 23) to reflect the fact that separate forward and aft splice straps are fabricated for Group 1, 2. 5. Paragraph 1.J.3.,Installation Drawings Used in the Preparation of this Service Bulletin: Added drawing reference for STA 340 frame installation. 6. Paragraph 2.C., Parts Necessary for Each Airplane: Identified superseding and supplemental fastener kits associated with changes made with Revision 1. Also added information related to the modification or change of a dripshield attachment Bracket Assembly. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 03, 2014 747-53A2862Revision 1: July 24, 2015 6 of 366 BOEING SERVICE BULLETIN 747-53A2862 ALERTALERT ### Page 7 7. Paragraph 3.B., General Information: Update notes to current standard. 8. Paragraph 3.B., Work Instructions: Changed instruction in PART 1 and PARTS 4-8 to reflect changes to the inspections and to give alternative oversize fastener installation data for repairs. Also revised PART 7 to increase the maximum width (material removed) for the frame inner chord cut from 0.060 to 0.120 inch. Also added PART 9: UPPER SILL REPAIR and PART 10: STA 340 FRAME INSPECTION. 9. Figure 1 and Figure 2: Revised instruction for the dripshield modification based on the initial accomplishment of the modification which was done as a part of the service bulletin validation program. Also added flexibility to extend the removable segment of the dripshield inboard/up to improve access to the inboard end of the STA 320 frame inspection area. 10. Figure 3: Revised instruction for the inspection of the STA 320 frame and Window Post #3 and added instruction to inspect the window upper sill for cracks and missing fasteners. Removed instruction for the open hole HFEC inspection and also the associated instruction/data for the oversize fastener repair which will not apply for the longer cracks found with the revised inspections. 11. Figure 6 and Figure 15: Increased the maximum width (material removed) for the frame inner chord cut from 0.060 to 0.120 inch. 12. Figure 9 and Figure 10: Changed minimum edge margin at cut edge of the frame inner chord from 0.40 inch to 1.7D. Also revised instruction related to a dripshield attachment Bracket Assembly located near BL 0. 13. Figures 9-12, 17-20: Added countersunk washers (under head of bolt) to fastener codes C and G. 14. Figure 22 and Figure 23: Clarified instruction for applying sealant between the splice strap and dripshield and added instruction regarding the installation of fastener #6. 15. Revised Figure 25 to give instruction for inspection of the STA 340 Frame. The inspection instruction for Group 3, 4 airplanes previously given in Figure 25 is now given in Figure 3. 16. Added Figure 26 to give oversize fastener data that can be used with a PART 5 or PART 6 repair if an oversize fastener repair was made previously. 17. Added Figure 27 (Group 1, 2) and Figure 28 (Group 3, 4) to give "more work" instruction associated with Revision 1 of this service bulletin for airplanes changed in accordance with the Original Issue of this service bulletin. 18. Added Figure 29 to give instruction to modify/fabricate a dripshield attachment Bracket Assembly located near BL 0. 19. Added Appendix C to give a logic diagram representation of the information given in the Compliance paragraph. As a part of a service bulletin validation program, the dripshield modification given in this service bulletin was completed on airplane RL430 by the original issue of this service bulletin. The dripshield modification completed on airplane RL430 is equivalent to a modification completed by Revision 1 of this service bulletin. Airplane RL430 has the configuration of a Group 2 airplane. Vertical lines are put on the left edge of each page, except in Paragraph 1.A., Effectivity and format changes, to show the location of all content changes. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 03, 2014 747-53A2862Revision 1: July 24, 2015 7 of 366 BOEING SERVICE BULLETIN 747-53A2862 ALERTALERT ### Page 8 Pages with no vertical lines have no changes. REVISION HISTORY April 03, 2014Original Issue: July 24, 2015Revision 1: Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 03, 2014 747-53A2862Revision 1: July 24, 2015 8 of 366 BOEING SERVICE BULLETIN 747-53A2862 ALERTALERT ### Page 9 Commercial Airplanes 747 Service Bulletin ALERT SummaryNumber: 747-53A2862Original Issue: April 03, 2014 Revision 1: July 24, 2015 ATA System: 5300 SUBJECT: FUSELAGE - Main Frame - STA 320 Crown Frame and Window Post #3 - Inspection and Repair THIS BULLETIN IS SENT TO THE OPERATORS OF RECORD OF THE AIRPLANES SHOWN IN PARAGRAPH 1.A., EFFECTIVITY. IF AN AIRPLANE HAS BEEN LEASED OR SOLD, SEND THIS SERVICE BULLETIN TO THE NEW OPERATOR. IF APPLICABLE SPARES HAVE BEEN SOLD, SEND THIS SERVICE BULLETIN TO THE NEW OWNER. CONCURRENT REQUIREMENTS None. BACKGROUND The inspections given in this service bulletin are necessary to make sure that cracks that could exist in the STA 320 crown frame, Window Post #3 and the window upper sill will be found and repaired before damage from the cracks can have an effect on flight safety. Fatigue cracks that start at fastener holes in the frame inner chord can cause cracks to start in the frame web and together these cracks can extend with continued operation of the airplane to fully sever the frame. Also, cracks in the inner chord of Window Post #3 can extend and fully sever the post. Operation of the airplane with either condition could damage the body skin and cause in-flight decompression and a loss of structural integrity. Fatigue cracks have been found in the STA 320 crown frame inspection area specified in this service bulletin by operators inspecting the frame inner chord in accordance with Boeing service bulletin 747-53A2784 (which addresses a production issue applicable to the Group 1 airplanes of this service bulletin). Service bulletin 747-53A2784 is applicable to only 747-400 model airplanes, so all the cracks reported by operators have been found on 747-400 airplanes. Models other than 747-400 are included in the effectivity of this service bulletin because the STA 320 crown frame in the included airplanes is of a similar configuration. Frame inner chord cracks 0.03 - 0.22 inch in length have been found on 15 airplanes at flight cycles ranging from 11,498 to 31,315. Also, a 1.8 inch crack was found in the outboard web of the frame on one airplane with 14,749 flight cycles. Cracks have also been found in Window Post #3 which connects to the lower end of the inner chord of the STA 320 crown frame. Cracks 0.03 - 0.11 inch in length have been found in Window Post #3 on five airplanes at flight cycles ranging from 12,329 to 15,772. Also, fatigue cracks which had extended to fully sever the inner chord and outboard web of the frame were found on the 747-400 fatigue test airplane at 38,333 pressure cycles and significant cracks were found in both the frame inner chord and outboard web at 30,500 pressure cycles on the 747-100SR fatigue test airplane. The inspections specified in this service bulletin are given to make sure that the airplane is not operated with a severely damaged or severed frame or window post. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 03, 2014 747-53A2862Revision 1: July 24, 2015 9 of 366 ### Page 10 After the original issue of this service bulletin, frame inner chord cracks were found at the two upper fastener holes common to the STA 320 frame reinforcement strap on an airplane with 16,854 flight cycles. These cracks were located outside of the inspection area specified in the original issue of this service bulletin. As a result of this finding, the Surface HFEC inspection for cracks in the frame inner chord was extended inboard to include the area of these cracks with Revision 1 to this service bulletin. Also, after the original issue of this service bulletin Boeing conducted a more refined structural analysis of the fuselage crown area around STA 320 and this analysis showed that the structural integrity of the fuselage will be maintained with more crack damage than was shown by previous analysis. This result allowed for an increase in the level of crack damage that must be detected with the inspections given in this service bulletin. Accordingly, the open hole HFEC inspection for cracks in the STA 320 frame and Window Post #3 specified in the original issue of this service bulletin were eliminated with Revision 1 and replaced by inspections for more extensive crack damage done with Detailed and Surface HFEC inspection procedures only. As a part of a service bulletin validation program, the dripshield modification given in this service bulletin was accomplished on airplane RL430 by the original issue of this service bulletin. The dripshield modification accomplished on airplane RL430 is equivalent to a modification completed by Revision 1 of this service bulletin. Airplane RL430 has the configuration of a Group 2 airplane. Boeing Service Related Problem (SRP) 747-SRP-53-0404 and 747-SRP-53-0462 are related to this service bulletin. Boeing Fleet Team Digest (FTD) 747 FTD FTD-53-12005 is related to this service bulletin. The table below is provided to operators for planning purposes only. Refer to the applicable sections for more information. ReferenceAffectedPlanning Data Paragraph 1.A.2., Spares AffectedNoSpares Affected Paragraph 1.E., Compliance and Paragraph 1.F., Approval YesAD Related Paragraph 1.H., Weight and Balance ChangesYesWeight and Balance Change Paragraph 1.I., Electrical Load DataNoElectrical Load Changed Paragraph 1.K., Publications AffectedNoPublications Affected Paragraph 1.K., Publications AffectedNoAirplane Flight Operations Affected (Flight Crew Operations Manual and/or FAA Approved Air- plane Flight Manual) Paragraph 2.C.1., Kits/PartsYesKits/Parts Required Paragraph 2.C.2., Parts and Materials Supplied by the Operator YesOperator Supplied Parts/Material Paragraph 2.F., Special Tooling Necessary to do this Service Bulletin NoSpecial Tooling Required Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 03, 2014 747-53A2862Revision 1: July 24, 2015 10 of 366 BOEING SERVICE BULLETIN 747-53A2862 ALERTALERT ### Page 11 ACTION Detailed and Surface HFEC inspections for cracks in the inner chord and outboard webs of the STA 320 crown frame and in the left and right side Window Post #3 and upper sill structure are to be accomplished by a specified number of flight-cycles. Also, an inspection for missing fasteners is to be accomplished with the initial crack inspection of the frame and the upper sill. A repair is to be accomplished if there is any crack or missing fastener and repeat inspections for cracks in the frame, Window Post #3 and the upper sill are to be accomplished at specified intervals. The time to the next inspection of the STA 320 crown frame can be extended by replacing the inner chord of the frame and further extended by replacing both the inner chord and outboard webs of the frame. A repair accomplished in accordance with this service bulletin can include replacement of the left or right side outboard web only, the left or right side frame inner chord segment only, or replacement of any combination of these components. EFFECTIVITY 747-100, 747-100B, 747-100B SUD, 747-200B, 747-200C, 747-200F, 747-300, 747-400, 747-400D, 747-400F, 747SP, 747SR airplanes. Refer to Paragraph 1.A.1., Airplanes, for the list of affected airplanes. COMPLIANCE Federal Aviation Administration (FAA) Airworthiness Directive AD 2005-08-01 is related to this service bulletin. The effective date of AD 2005-08-01 is April 26, 2005. Federal Aviation Administration (FAA) Airworthiness Directive AD 2009-19-05 is related to this service bulletin. The effective date of AD 2009-19-05 is October 27, 2009. Federal Aviation Administration (FAA) Airworthiness Directive AD 2012-22-02 is related to this service bulletin. The effective date of AD 2012-22-02 is December 26, 2012. The Federal Aviation Administration (FAA) will possibly release an additional Airworthiness Directive related to this service bulletin. The Airworthiness Directive will make the compliance tasks and times given in this service bulletin mandatory. Refer to Paragraph 1.E., Compliance. INDUSTRY SUPPORT INFORMATION Boeing warranty remedies are not available for the inspection and repair procedures given in this service bulletin. MANPOWER Refer to Paragraph 1.G., Manpower. MATERIAL INFORMATION Boeing Supplied Kits/Parts. Refer to Paragraph 2.A., Material - Price and Availability. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 03, 2014 747-53A2862Revision 1: July 24, 2015 11 of 366 BOEING SERVICE BULLETIN 747-53A2862 ALERTALERT ### Page 12 (OCR) BOEING SERVICE BULLETIN 747-53A2862 ALERT ALERT WINDOW UPPER SILL UPPER SILL INSPECTION AREA STA 320 OUTBOARD WEB FWD INBOARD + 61 WEB RIGHT SIDE (RS) FRAME INSPECTION AREA WINDOW INNER POST #3 CHORD INSPECT THE OUTBOARD WEBS AND THE INNER CHORD OF THE STA 320 FRAME AND ALSO WINDOW POST #3 AND THE WINDOW UPPER SILL FOR CRACKS AND MISSING FASTENERS USING DETAILED AND WEB OUTBOARD SURFACE HFEC INSPECTION PROCEDURES. DO REPAIRS FOR CRACKS OR MISSING FASTENERS N ACCORDANCE WITH THIS SERVICE BULLETIN LEFT SIDE (LS) FRAME INSPECTION WINDOW POST #3 AREA 2188342 Original Issue: April 03, 2014 Revision 1: July 24, 2015 PROPRIETARY - Copyright © Unpublished Export Controlled ECCN: 9E991 - BOEING 747-53A2862 Work - See page 1 for detalls. 12 of 366 ### Page 13 Commercial Airplanes 747 Service Bulletin ALERT Number: 747-53A2862 Original Issue: April 03, 2014 Revision 1: July 24, 2015 ATA System: 5300 SUBJECT: FUSELAGE - Main Frame - STA 320 Crown Frame and Window Post #3 - Inspection and Repair THIS BULLETIN IS SENT TO THE OPERATORS OF RECORD OF THE AIRPLANES SHOWN IN PARAGRAPH 1.A., EFFECTIVITY. IF AN AIRPLANE HAS BEEN LEASED OR SOLD, SEND THIS SERVICE BULLETIN TO THE NEW OPERATOR. IF APPLICABLE SPARES HAVE BEEN SOLD, SEND THIS SERVICE BULLETIN TO THE NEW OWNER. 1. PLANNING INFORMATION A. Effectivity 1. Airplanes This service bulletin is applicable to 747 Airplanes, line numbers 1-1419 in four Groups. The Variable Numbers and Group Information for the applicable airplanes is given below. Refer to Service Bulletin Index D6-30300 Part 3 for Airplane Variable Number, Line Number, and Serial Number data. DESCRIPTIONCONFIGURATIONGROUP 747-400, -400D, and -400F airplanes in the effectivity of Service Bulletin 747-53A2784 ( line numbers 696 through 991) -1 No change per Service Bulletin 747-53A27841 Inboard web replaced per Service Bulletin 747-53A27842 747-400, -400D, and -400F airplanes NOT in the effectivity of Service Bulletin 747-53A2784 ( line numbers 992 through 1419) -2 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 03, 2014 747-53A2862Revision 1: July 24, 2015 13 of 366 ### Page 14 DESCRIPTIONCONFIGURATIONGROUP 747-100, 747-100B, 747-100B SUD, 747-200B, 747-200C, 747-200F, 747-300, 747SP, 747SR airplanes in the effectivity of Service Bulletin 747-53-2272 (line numbers 1-661) -3 No change per Service Bulletin 747-53-22721 Frame inner chord replaced per Service Bulletin 747-53-22722 747-200B, 747-200C, 747-200F, 747-300, 747SP airplanes NOT in the effectivity of Service Bulletin 747-53-2272 -4 Airplane Models: 747-100, 747-100B, 747-100B SUD, 747-200B, 747-200C, 747-200F, 747-300, 747-400, 747-400D, 747-400F, 747SP, 747SR GroupVariable Number 3RA001 - RA034 3RA101 - RA115 3RA161 - RA164 3RA201 - RA203 3RA216 - RA217 3RA245 - RA246 3RA251 - RA266 3RA301 - RA318 3RA351 - RA360 3RA369 - RA373 3RA401 - RA418 3RA501 - RA502 3RA521 - RA528 3RA532 - RA548 3RA551 - RA552 3RA559 - RA561 3RA581 - RA582 3RA585 3RA601 - RA602 3RA631 - RA635 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 03, 2014 747-53A2862Revision 1: July 24, 2015 14 of 366 BOEING SERVICE BULLETIN 747-53A2862 ALERTALERT ### Page 15 GroupVariable Number 3RA651 - RA652 3RA671 - RA677 3RA701 - RA702 3RA721 - RA731 3RA741 - RA745 3RA749 - RA750 3RA761 - RA762 3RA781 - RA784 3RA901 - RA916 3RB001 - RB016 3RB041 - RB044 3RB071 - RB075 3RB101 - RB102 4RB411 - RB413 4RB421 3RB601 - RB607 3RB681 - RB697 3RB711 3RB721 - RB723 3RB741 - RB748 3RD001 - RD004 3RD021 - RD022 3RD041 - RD059 3RD071 - RD072 3RD081 - RD083 3RD091 - RD092 3RD101 - RD104 3RD121 - RD127 3RD131 - RD144 4RD166 - RD167 3RD171 - RD172 3RD181 - RD183 3RD201 - RD204 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 03, 2014 747-53A2862Revision 1: July 24, 2015 15 of 366 BOEING SERVICE BULLETIN 747-53A2862 ALERTALERT ### Page 16 GroupVariable Number 3RD221 - RD227 3RD231 - RD232 4RD233 - RD235 3RD241 - RD243 3RD251 - RD262 3RD271 - RD272 3RD291 4RD292 4RD301 - RD302 4RD311 3RD351 - RD358 3RD361 - RD366 3RD381 - RD383 3RD411 - RD414 3RD421 - RD426 3RD431 - RD435 3RD441 - RD442 3RD451 - RD456 3RD461 3RD471 - RD475 3RD513 - RD519 3RD531 - RD533 3RD551 3RD561 3RD571 3RD581 - RD583 3RD591 - RD593 3RD601 - RD607 3RD621 - RD623 3RD641 - RD649 3RD651 - RD659 3RD661 3RD671 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 03, 2014 747-53A2862Revision 1: July 24, 2015 16 of 366 BOEING SERVICE BULLETIN 747-53A2862 ALERTALERT ### Page 17 GroupVariable Number 3RD681 - RD682 3RD691 - RD692 3RD701 - RD702 3RD721 - RD722 3RD741 - RD742 3RD751 - RD755 3RD761 3RD771 - RD774 4RD775 3RD781 - RD782 4RD783 3RD791 4RD792 3RE001 2RF001 - RF006 3RG001 - RG009 3RG091 3RG095 3RG101 - RG104 3RG121 - RG126 3RG141 - RG142 3RG161 - RG164 3RG171 - RG174 3RG191 - RG193 3RG211 - RG213 3RG221 - RG222 3RH101 4RH102 3RH111 - RH112 3RH121 - RH122 3RJ131 - RJ133 3RJ151 - RJ152 3RJ301 - RJ303 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 03, 2014 747-53A2862Revision 1: July 24, 2015 17 of 366 BOEING SERVICE BULLETIN 747-53A2862 ALERTALERT ### Page 18 GroupVariable Number 4RJ321 - RJ322 3RJ331 - RJ333 2RL401 - RL403 2RL411 - RL436 2RL451 - RL456 2RL461 - RL462 2RL471 - RL481 2RL491 - RL492 2RL501 - RL502 2RL511 - RL516 2RL521 - RL522 2RL531 - RL534 2RL551 2RL561 - RL568 2RL571 - RL572 2RL576 - RL577 2RL579 2RL581 - RL586 2RL651 - RL655 2RL671 - RL675 2RL681 - RL684 2RL751 - RL752 2RM001 - RM007 2RM010 - RM013 2RM021 - RM024 2RM026 - RM030 2RM036 - RM045 2RM051 - RM053 2RM071 2RM081 - RM084 2RM091 2RM096 - RM097 2RM116 - RM117 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 03, 2014 747-53A2862Revision 1: July 24, 2015 18 of 366 BOEING SERVICE BULLETIN 747-53A2862 ALERTALERT ### Page 19 GroupVariable Number 2RM126 - RM132 2RM136 - RM147 2RM156 - RM158 2RM166 - RM177 2RM191 - RM192 2RM231 - RM233 2RM241 - RM246 2RM261 - RM264 2RM316 - RM318 2RM331 - RM333 2RM341 2RM351 - RM355 2RM366 - RM367 2RM401 - RM403 2RM426 2RM431 2RM441 - RM443 2RM445 2RM801 - RM803 2RM811 - RM813 2RM851 - RM859 2RM861 - RM863 2RM871 - RM899 2RM901 - RM906 2RM911 3RR001 - RR005 3RR021 - RR023 4RR024 - RR025 3RR031 3RR201 - RR205 4RR206 3RR221 - RR226 3RR261 - RR266 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 03, 2014 747-53A2862Revision 1: July 24, 2015 19 of 366 BOEING SERVICE BULLETIN 747-53A2862 ALERTALERT ### Page 20 GroupVariable Number 4RR267 3RR301 - RR306 4RR307 - RR310 3RR331 - RR332 3RR336 3RR341 - RR345 3RR361 - RR362 3RR421 - RR422 4RR431 - RR432 4RR441 - RR442 4RR451 3RR501 - RR504 3RR521 4RR522 4RR526 3RR531 3RR551 - RR553 4RR554 - RR556 3RR561 4RR566 1RR701 2RR721 - RR724 2RR746 - RR748 2RR851 - RR856 2RR861 - RR862 2RR951 - RR952 3RS001 - RS002 3RS201 3RS211 - RS212 3RS221 - RS222 3RS231 - RS241 3RS251 - RS256 4RS257 - RS259 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 03, 2014 747-53A2862Revision 1: July 24, 2015 20 of 366 BOEING SERVICE BULLETIN 747-53A2862 ALERTALERT ### Page 21 GroupVariable Number 4RS263 4RS265 - RS268 3RS271 - RS274 4RS275 - RS276 3RS291 - RS292 3RS301 - RS303 4RS304 - RS306 3RS311 - RS320 4RS331 - RS333 4RS341 - RS342 3RS699 3RS701 - RS702 4RS703 3RS711 - RS713 3RS721 - RS722 4RS731 - RS732 3RS741 - RS742 4RS743 3RS751 - RS752 3RS761 4RS762 3RS771 4RS781 - RS782 4RS786 1RT001 - RT009 2RT010 - RT014 1RT021 - RT022 1RT031 - RT033 2RT034 - RT035 1RT041 - RT047 1RT061 1RT071 - RT075 1RT101 - RT103 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 03, 2014 747-53A2862Revision 1: July 24, 2015 21 of 366 BOEING SERVICE BULLETIN 747-53A2862 ALERTALERT ### Page 22 GroupVariable Number 1RT121 1RT131 - RT133 2RT134 - RT137 2RT151 - RT152 2RT161 - RT168 1RT401 - RT412 1RT431 - RT441 2RT442 - RT447 1RT451 - RT465 2RT466 - RT469 1RT471 - RT496 2RT497 - RT499 1RT501 - RT520 2RT521 - RT530 1RT531 - RT535 1RT551 - RT568 1RT571 - RT581 2RT582 - RT590 1RT591 1RT601 - RT622 2RT623 - RT630 1RT631 - RT635 2RT636 - RT640 1RT641 - RT657 1RT671 - RT673 1RT681 - RT682 1RT691 - RT696 2RT697 - RT699 1RT701 - RT704 1RT711 - RT717 1RT741 - RT745 2RT746 - RT750 1RT751 - RT755 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 03, 2014 747-53A2862Revision 1: July 24, 2015 22 of 366 BOEING SERVICE BULLETIN 747-53A2862 ALERTALERT ### Page 23 GroupVariable Number 2RT756 - RT757 1RT776 - RT777 1RT781 - RT783 2RT784 2RT801 - RT803 2RT811 - RT814 2RT831 - RT837 1RT861 - RT864 1RT876 - RT878 2RT879 - RT880 1RT931 - RT932 2RT945 - RT949 1RT951 - RT954 2RT955 2RT966 - RT967 1RU001 2RU002 - RU006 2RU016 - RU017 1RU031 2RU032 2RU051 - RU052 2RU059 - RU062 2RU081 - RU083 2RU101 - RU102 2RU121 - RU132 1RU801 - RU808 2RU809 1RU831 - RU838 2RU839 - RU841 2. Spares Affected None. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 03, 2014 747-53A2862Revision 1: July 24, 2015 23 of 366 BOEING SERVICE BULLETIN 747-53A2862 ALERTALERT ### Page 24 B. Concurrent Requirements None. C. Reason The inspections given in this service bulletin are necessary to make sure that cracks that could exist in the STA 320 crown frame, Window Post #3 and the window upper sill will be found and repaired before damage from the cracks can have an effect on flight safety. Fatigue cracks that start at fastener holes in the frame inner chord can cause cracks to start in the frame web and together these cracks can extend with continued operation of the airplane to fully sever the frame. Also, cracks in the inner chord of Window Post #3 can extend and fully sever the post. Operation of the airplane with either condition could damage the body skin and cause in-flight decompression and a loss of structural integrity. Fatigue cracks have been found in the STA 320 crown frame inspection area specified in this service bulletin by operators inspecting the frame inner chord in accordance with Boeing service bulletin 747-53A2784 (which addresses a production issue applicable to the Group 1 airplanes of this service bulletin). Service bulletin 747-53A2784 is applicable to only 747-400 model airplanes, so all the cracks reported by operators have been found on 747-400 airplanes. Models other than 747-400 are included in the effectivity of this service bulletin because the STA 320 crown frame in the included airplanes is of a similar configuration. Frame inner chord cracks 0.03 - 0.22 inch in length have been found on 15 airplanes at flight cycles ranging from 11,498 to 31,315. Also, a 1.8 inch crack was found in the outboard web of the frame on one airplane with 14,749 flight cycles. Cracks have also been found in Window Post #3 which connects to the lower end of the inner chord of the STA 320 crown frame. Cracks 0.03 - 0.11 inch in length have been found in Window Post #3 on five airplanes at flight cycles ranging from 12,329 to 15,772. Also, fatigue cracks which had extended to fully sever the inner chord and outboard web of the frame were found on the 747-400 fatigue test airplane at 38,333 pressure cycles and significant cracks were found in both the frame inner chord and outboard web at 30,500 pressure cycles on the 747-100SR fatigue test airplane. The inspections specified in this service bulletin are given to make sure that the airplane is not operated with a severely damaged or severed frame or window post. After the original issue of this service bulletin, frame inner chord cracks were found at the two upper fastener holes common to the STA 320 frame reinforcement strap on an airplane with 16,854 flight cycles. These cracks were located outside of the inspection area specified in the original issue of this service bulletin. As a result of this finding, the Surface HFEC inspection for cracks in the frame inner chord was extended inboard to include the area of these cracks with Revision 1 to this service bulletin. Also, after the original issue of this service bulletin Boeing conducted a more refined structural analysis of the fuselage crown area around STA 320 and this analysis showed that the structural integrity of the fuselage will be maintained with more crack damage than was shown by previous analysis. This result allowed for an increase in the level of crack damage that must be detected with the inspections given in this service bulletin. Accordingly, the open hole HFEC inspection for cracks in the STA 320 frame and Window Post #3 specified in the original issue of this service bulletin were eliminated with Revision 1 and replaced by an inspections for more extensive crack damage done with Detailed and Surface HFEC inspection procedures only. As a part of a service bulletin validation program, the dripshield modification given in this service bulletin was accomplished on airplane RL430 by the original issue of this service bulletin. The dripshield modification accomplished on airplane RL430 is equivalent to a modification completed by Revision 1 of this service bulletin. Airplane RL430 has the configuration of a Group 2 airplane. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 03, 2014 747-53A2862Revision 1: July 24, 2015 24 of 366 BOEING SERVICE BULLETIN 747-53A2862 ALERTALERT ### Page 25 Revision 1 changed work instruction and compliance times for the inspections given in this service bulletin as noted above. Also, with Revision 1 changes were made to the work instruction for the dripshield modification to incorporate findings from the initial accomplishment of the modification which was done as a part of the service bulletin validation program. Boeing Service Related Problem (SRP) 747-SRP-53-0404 and 747-SRP-53-0462 are related to this service bulletin. Boeing Fleet Team Digest (FTD) 747 FTD FTD-53-12005 is related to this service bulletin. D. Description Detailed and Surface HFEC inspections for cracks in the inner chord and outboard webs of the STA 320 crown frame and in the left and right side Window Post #3 and upper sill structure are to be accomplished by a specified number of flight-cycles. Also, an inspection for missing fasteners is to be accomplished with the initial crack inspection of the frame and the upper sill. A repair is to be accomplished if there is any crack or missing fastener and repeat inspections for cracks in the frame, Window Post #3 and the upper sill are to be accomplished at specified intervals. The time to the next inspection of the STA 320 crown frame can be extended by replacing the inner chord of the frame and further extended by replacing both the inner chord and outboard webs of the frame. A frame repair accomplished in accordance with this service bulletin can include replacement of the left or right side outboard web only, the left or right side frame inner chord segment only, or replacement of any combination of these components. Effects of this Revision on airplanes on which the Original Issue was previously accomplished: ActionConditionGroup Do PART 11 of Paragraph 3.B., Work Instructions in accordance with Paragraph 1.E., Compliance. (a) If any of the following conditions apply: – The STA 320 crown frame outboard web, inner chord, or both were replaced in accordance with PART 5, PART 6 or PART 7 respectively of Paragraph 3.B., Work Instruc- tions of the Original Issue of this service bulletin. – An oversize fastener repair was done in accordance with PART 1 of Paragraph 3.B., Work Instructions of the Original Issue of this service bulletin at specific fastener hole(s) identified in the Original Issue of this service bulletin as follows: Group 1, 2 airplanes: Hole #11 or Hole #15. Group 3, 4 airplanes: Hole #11. All (a) The work given in PART 11 is to remove specific bolts installed in accordance with the Original Issue of this service bulletin and at each location to install a bolt with a countersunk washer under the head. The countersunk washer is needed to accommodate the fillet radius of the bolt. Instruction to install the coun- tersunk washer was inadvertently omitted from the Original Issue of this service bulletin. Before the bolt and countersunk washer are installed, a Detailed inspection is to be done to confirm that the hole condition is satisfactory. If the condition of the fastener hole is not satisfactory, the hole is to be oversized to a satisfactory condition and an Open Hole HFEC inspection is to be done to confirm a crack free condition. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 03, 2014 747-53A2862Revision 1: July 24, 2015 25 of 366 BOEING SERVICE BULLETIN 747-53A2862 ALERTALERT ### Page 26 The work in this service bulletin is done in the maintenance zone(s) given below. Group 1-2: Affected Maintenance Zones ZoneModel 221, 222747-400, 747-400D, 747-400F Group 3: Affected Maintenance Zones ZoneModel 221, 222747-100, 747-100B, 747-100B SUD, 747-200B, 747-200C, 747-200F, 747-300, 747SP, 747SR Group 4: Affected Maintenance Zones ZoneModel 221, 222747-200B, 747-200C, 747-200F, 747-300, 747SP E. Compliance Federal Aviation Administration (FAA) Airworthiness Directive AD 2005-08-01 is related to this service bulletin. The effective date of AD 2005-08-01 is April 26, 2005. Federal Aviation Administration (FAA) Airworthiness Directive AD 2009-19-05 is related to this service bulletin. The effective date of AD 2009-19-05 is October 27, 2009. Federal Aviation Administration (FAA) Airworthiness Directive AD 2012-22-02 is related to this service bulletin. The effective date of AD 2012-22-02 is December 26, 2012. The Federal Aviation Administration (FAA) will possibly release an additional Airworthiness Directive related to this service bulletin. The Airworthiness Directive will make the compliance tasks and times given in this service bulletin mandatory. A logic diagram showing compliance tasks and compliance times is included as an aid in APPENDIX C. Accomplish all the action(s) for the applicable condition(s) given in the compliance tables identified in Table 1 below. Accomplish these actions in accordance with the identified PART of Paragraph 3.B., Work Instructions. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 03, 2014 747-53A2862Revision 1: July 24, 2015 26 of 366 BOEING SERVICE BULLETIN 747-53A2862 ALERTALERT ### Page 27 NOTE: After changes have been made in accordance with this service bulletin, the condition and compliance times applicable to the left side structure could be different than for the right side structure. The applicable conditions and compliance times given in the Compliance tables are to be determined for each side of the structure. For each table, actions are to be accomplished as specified for the condition(s) that are applicable. Table 1: Compliance Table Applicability Applicable Compliance TablesTask Group 4Group 3Group 2Group 1 Table 3Table 4Table 3Table 2Initial Inspection and Repair (a) Table 5Table 5Table 5Table 5Repeat Inspections (b) Table 7Table 7Table 6Table 6One-Time Work Associated with Revision 1 (c) (a) This task is applicable for airplanes that have not been inspected in accordance with either the original issue or Revision 1 of this service bulletin. Go to the Repeat Inspections task below if an inspection has already been done in accordance with either the original issue or Revision 1 of this service bulletin. (b) This task applies for airplanes that have been inspected in accordance with the original issue or Revision 1 of this service bulletin. (c) This work is applicable one-time and only if one or more of the following changes have been made: – The STA 320 crown frame outboard web, inner chord, or both were replaced in accordance with PART 5, PART 6 or PART 7 respectively of Paragraph 3.B., Work Instructions of the Original Issue of this service bulletin. – Group 1, 2 only: an oversize fastener repair was done in accordance with PART 1 of Paragraph 3.B., Work Instructions of the Original Issue of this service bulletin at the fastener hole identified in the Original Issue of this service bulletin as Hole #11 or Hole #15. – Group 3, 4 only: an oversize fastener repair was done in accordance with PART 1 of Paragraph 3.B., Work Instructions of the Original Issue of this service bulletin at the fastener hole identified in the Original Issue of this service bulletin as Hole #11. Group 1: Table 2: Inspection and Repair of STA 320 Frame, Window Post #3 and Window Upper Sill Repeat Interval (Not to Exceed) Compliance TimeActionCondition -Before 16,000 total flight cycles, or within 2,200 flight cycles after the original issue date of this ser- vice bulletin, or within 8,000 flight cycles after the open hole inspec- tion was accomplished in accor- dance with Boeing Service Bulletin 747-53A2784,whichever occurs later. Do a Detailed inspection of the STA 320 crown frame for any crack and missing fastener in accor- dance with PART 1. Also, do a Surface HFEC in- spection for any crack in the STA 320 crown frame in accordance with PART 1. (a) STA 320 CROWN FRAME: An Open Hole HFEC in- spection of the STA 320 crown frame inner chord in accordance with Boeing Service Bulletin 747- 53A2784 has been done and no crack was found. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 03, 2014 747-53A2862Revision 1: July 24, 2015 27 of 366 BOEING SERVICE BULLETIN 747-53A2862 ALERTALERT ### Page 28 Group 1: Table 2: Inspection and Repair of STA 320 Frame, Window Post #3 and Window Upper Sill Repeat Interval (Not to Exceed) Compliance TimeActionCondition -Before 16,000 total flight cycles, or within 2,200 flight cycles after the original issue date of this ser- vice bulletin, whichever occurs later. Do a Detailed inspection of the STA 320 crown frame for any crack and missing fastener in accor- dance with PART 1. Also, do a Surface HFEC in- spection for any crack in the STA 320 crown frame in accordance with PART 1. (a) STA 320 CROWN FRAME: An Open Hole HFEC in- spection of the STA 320 crown frame inner chord in accordance with Boeing Service Bulletin 747- 53A2784 has not been done, or the inspection was done and any crack found was repaired, but the inner chord was not replaced. -Before 16,000 total flight cycles, or within 2,200 flight cycles after the original issue date of this ser- vice bulletin, or within 9,000 flight cycles after the new inner chord was installed, whichever occurs later. Do a Detailed inspection of the STA 320 crown frame for any crack and missing fastener in accor- dance with PART 1. Also, do a Surface HFEC in- spection for any crack in the STA 320 crown frame in accordance with PART 1. (a) STA 320 CROWN FRAME: The frame inner chord has been replaced with a new inner chord. -Before 16,000 total flight cycles, or within 2,200 flight cycles after the original issue date of this ser- vice bulletin, or within 8,000 flight cycles after the open hole HFEC inspection of Window Post #3, whichever occurs later. Do a Surface HFEC in- spection for any crack in Window Post #3 in accor- dance with PART 1. (e) WINDOW POST #3: An Open Hole HFEC in- spection of Window Post #3 at the four fastener holes common to the inner chord of the STA 320 crown frame has been ac- complished and no crack was found. -Before 16,000 total flight cycles, or within 2,200 flight cycles after the original issue date of this ser- vice bulletin, whichever occurs later. Do a Surface HFEC in- spection for any crack in Window Post #3 in accor- dance with PART 1. (e) WINDOW POST #3: An Open Hole HFEC in- spection of Window Post #3 at the four fastener holes common to the inner chord of the STA 320 crown frame has not been accomplished, or the in- spection was accomplished and any crack found was repaired. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 03, 2014 747-53A2862Revision 1: July 24, 2015 28 of 366 BOEING SERVICE BULLETIN 747-53A2862 ALERTALERT ### Page 29 Group 1: Table 2: Inspection and Repair of STA 320 Frame, Window Post #3 and Window Upper Sill Repeat Interval (Not to Exceed) Compliance TimeActionCondition -Before 16,000 total flight cycles, or within 2,200 flight cycles after the Revision 1 date of this service bulletin, whichever occurs later. Do a Detailed inspection of the window upper sill for any missing fastener and a Surface HFEC in- spection of the window upper sill for any crack in accordance with PART 1. (a) WINDOW UPPER SILL: All Group 1 airplanes. NOTE: The conditions below are based on the findings from the inspections given above. If there is any crack or missing fastener, either CONDITION 1 or CONDITION 2 will apply. -Before further flight. Do a Surface HFEC in- spection for any crack in the STA 340 frame in ac- cordance with PART 10. CONDITION 1: FINDINGS NECESSITATE INSPEC- TION OF STA 340 FRAME. (b) -Before further flight. Repair any crack or missing fastener in accor- dance with PART 1. (d) -Before further flight.Repair any crack or missing fastener in accor- dance with PART 1. CONDITION 2: FINDINGS DO NOT NECESSITATE INSPECTION OF STA 340 FRAME. (c) See Table 5.See Table 5.See Table 5.No crack or missing fasten- er, or any crack or missing fastener repaired in accor- dance with PART 1. (a) The Detailed inspection for any missing fastener is a one time inspection necessary with the initial inspec- tion only. (b) The inspection findings that determine CONDITION 1 are types of crack damage specified in PART 1. (c) CONDITION 2 applies if there is any crack or missing fastener finding(s) and CONDITION 1 does not apply. The inspection findings that determine CONDITION 1 are types of crack damage specified in PART 1. (d) This action applies for any crack or missing fastener finding from any inspection done in accordance with PART 1, including any crack found with the inspection of the STA 340 frame. (e) The area of Window Post #3 to be inspected is accessible from the cockpit without removing or cutting the dripshield. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 03, 2014 747-53A2862Revision 1: July 24, 2015 29 of 366 BOEING SERVICE BULLETIN 747-53A2862 ALERTALERT ### Page 30 Group 2, 4: Table 3: Inspection and Repair of STA 320 Frame, Window Post #3 and Window Upper Sill Repeat Interval (Not to Exceed) Compliance TimeActionCondition -Before 16,000 total flight cycles, or within 2,200 flight cycles after the original issue date of this ser- vice bulletin, whichever occurs later. Do a Detailed inspection of the STA 320 crown frame for any crack and missing fastener in accor- dance with PART 1. Also, do a Surface HFEC in- spection for any crack in the STA 320 crown frame in accordance with PART 1. (a) STA 320 CROWN FRAME: All Group 2, 4 airplanes. -Before 16,000 total flight cycles, or within 2,200 flight cycles after the original issue date of this ser- vice bulletin, whichever occurs later. Do a Surface HFEC in- spection for any crack in Window Post #3 in accor- dance with PART 1. (e) WINDOW POST #3: All Group 2, 4 airplanes. -Before 16,000 total flight cycles, or within 2,200 flight cycles after the Revision 1 date of this service bulletin, whichever occurs later. Do a Detailed inspection of the window upper sill for any missing fastener and a Surface HFEC in- spection of the window upper sill for any crack in accordance with PART 1. (a) WINDOW UPPER SILL: All Group 2, 4 airplanes. NOTE: The conditions below are based on the findings from the inspections given above. If there is any crack or missing fastener, either CONDITION 1 or CONDITION 2 will apply. -Before further flight.Do a Surface HFEC in- spection for any crack in the STA 340 frame in ac- cordance with PART 10. CONDITION 1: FINDINGS NECESSITATE INSPEC- TION OF STA 340 FRAME. (b) -Before further flight.Repair any crack or missing fastener in accor- dance with PART 1. (d) -Before further flight.Repair any crack or missing fastener in accor- dance with PART 1. CONDITION 2: FINDINGS DO NOT NECESSITATE INSPECTION OF STA 340 FRAME. (c) See Table 5.See Table 5.See Table 5.No crack or missing fasten- er, or any crack or missing fastener repaired in accor- dance with PART 1. (a) The Detailed inspection for any missing fastener is a one time inspection necessary with the initial inspec- tion only. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 03, 2014 747-53A2862Revision 1: July 24, 2015 30 of 366 BOEING SERVICE BULLETIN 747-53A2862 ALERTALERT ### Page 31 Group 2, 4: Table 3: Inspection and Repair of STA 320 Frame, Window Post #3 and Window Upper Sill Repeat Interval (Not to Exceed) Compliance TimeActionCondition (b) The inspection findings that determine CONDITION 1 are types of crack damage specified in PART 1. (c) CONDITION 2 applies if there is any crack or missing fastener finding(s) and CONDITION 1 does not apply. The inspection findings that determine CONDITION 1 are types of crack damage specified in PART 1. (d) This action applies for any crack or missing fastener finding from any inspection done in accordance with PART 1, including any crack found with the inspection of the STA 340 frame. (e) The area of Window Post #3 to be inspected is accessible from the cockpit without removing or cutting the dripshield. Group 3: Table 4: Inspection and Repair of STA 320 Frame, Window Post #3 and Window Upper Sill Repeat Interval (Not to Exceed) Compliance TimeActionCondition -Before 16,000 total flight cycles, or within 2,200 flight cycles after the original issue date of this ser- vice bulletin, or within 9,000 flight cycles after the new inner chord was installed, whichever occurs later. Do a Detailed inspection of the STA 320 crown frame for any crack and missing fastener in accor- dance with PART 1. Also do a Surface HFEC in- spection for any crack in the STA 320 crown frame in accordance with PART 1. (a) STA 320 Crown Frame: The STA 320 crown frame inner chord has been re- placed in accordance with Boeing Service Bulletin 747-53-2272. -Before 16,000 total flight cycles, or within 2,200 flight cycles after the original issue date of this ser- vice bulletin, whichever occurs later. Do a Detailed inspection of the STA 320 crown frame for any crack and missing fastener in accor- dance with PART 1. Also do a Surface HFEC in- spection for any crack in the STA 320 crown frame in accordance with PART 1. (a) STA 320 CROWN FRAME: The STA 320 crown frame inner chord has NOT been replaced in accordance with Boeing Service Bul- letin 747-53-2272. -Before 16,000 total flight cycles, or within 2,200 flight cycles after the original issue date of this ser- vice bulletin, whichever occurs later. Do a Surface HFEC in- spection for any crack in Window Post #3 in accor- dance with PART 1. (e) WINDOW POST #3: All Group 3 airplanes. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 03, 2014 747-53A2862Revision 1: July 24, 2015 31 of 366 BOEING SERVICE BULLETIN 747-53A2862 ALERTALERT ### Page 32 Group 3: Table 4: Inspection and Repair of STA 320 Frame, Window Post #3 and Window Upper Sill Repeat Interval (Not to Exceed) Compliance TimeActionCondition -Before 16,000 total flight cycles, or within 2,200 flight cycles after the Revision 1 date of this service bulletin, whichever occurs later. Do a Detailed inspection of the window upper sill for any missing fastener and a Surface HFEC in- spection of the window upper sill for any crack in accordance with PART 1. (a) WINDOW UPPER SILL: All Group 3 airplanes. NOTE: The conditions below are based on the findings from the inspections given above. If there is any crack or missing fastener, either CONDITION 1 or CONDITION 2 will apply. -Before further flight.Do a Surface HFEC in- spection for any crack in the STA 340 frame in ac- cordance with PART 10. CONDITION 1: FINDINGS NECESSITATE INSPEC- TION OF STA 340 FRAME. (b) -Before further flight.Repair any crack or missing fastener in accor- dance with PART 1. (d) -Before further flight.Repair any crack or missing fastener in accor- dance with PART 1. CONDITION 2: FINDINGS DO NOT NECESSITATE INSPECTION OF STA 340 FRAME. (c) See Table 5.See Table 5.See Table 5.No crack or missing fasten- er, or any crack or missing fastener repaired in accor- dance with PART 1. (a) The Detailed inspection for any missing fastener is a one time inspection necessary with the initial inspec- tion only. (b) The inspection findings that determine CONDITION 1 are types of crack damage specified in PART 1. (c) CONDITION 2 applies if there is any crack or missing fastener finding(s) and CONDITION 1 does not apply. The inspection findings that determine CONDITION 1 are types of crack damage specified in PART 1. (d) This action applies for any crack or missing fastener finding from any inspection done in accordance with PART 1, including any crack found with the inspection of the STA 340 frame. (e) The area of Window Post #3 to be inspected is accessible from the cockpit without removing or cutting the dripshield. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 03, 2014 747-53A2862Revision 1: July 24, 2015 32 of 366 BOEING SERVICE BULLETIN 747-53A2862 ALERTALERT ### Page 33 Table 5: Repeat Inspection of STA 320 Frame, Window Post #3 and Window Upper Sill Structure Repeat Interval (Not to Exceed) Compliance TimeActionCondition 8,000 flight cycles.Within 16,000 flight cycles after the new inner chord was installed. Do Detailed and Surface HFEC inspections for any crack in the STA 320 crown frame in accor- dance with PART 1. STA 320 CROWN FRAME: The frame inner chord HAS been replaced in accor- dance with PART 7 WITH COLD WORK. (a) 8,000 flight cycles.Within 9,000 flight cycles after the new inner chord was installed. Do Detailed and Surface HFEC inspections for any crack in the STA 320 crown frame in accor- dance with PART 1. STA 320 CROWN FRAME: The frame inner chord HAS been replaced in accor- dance with PART 6 or PART 7 WITHOUT COLD WORK. (a) 8,000 flight cycles.Within 8,000 flight cycles after the previous inspection of the STA 320 crown frame. Do Detailed and Surface HFEC inspections for any crack in the STA 320 crown frame in accor- dance with PART 1. STA 320 CROWN FRAME: The frame inner chord has NOT been replaced in ac- cordance with PART 6 or PART 7. (e) 8,000 flight cycles.Within 8,000 flight cycles after the previous inspection was done in accordance with this service bul- letin. Do a Surface HFEC in- spections for any crack in Window Post #3 in accor- dance with PART 1. (d) WINDOW POST #3: All airplanes. (e) 8,000 flight cycles.Within 8,000 flight cycles after the previous inspection of the window upper sill. Do Detailed and Surface HFEC inspections for any crack in the window up- per sill in accordance with PART 1. WINDOW UPPER SILL: The sill has not been re- paired in accordance with PART 9. 8,000 flight cycles.Within 8,000 flight cycles after ac- complishment of the PART 9 re- pair. Do post-repair inspec- tions for any crack in the window upper sill in accor- dance with the applicable SRM repair identified in PART 9. WINDOW UPPER SILL: The sill has been repaired in accordance with PART 9. NOTE: The conditions below are based on the findings from the inspections given above. If any crack is found, either CONDITION 1 or CONDITION 2 will apply. -Before further flight.Do a Surface HFEC in- spection for any crack in the STA 340 frame in ac- cordance with PART 10. CONDITION 1: FINDINGS NECESSITATE INSPEC- TION OF STA 340 FRAME. (b) -Before further flight.Repair any crack or missing fastener in accor- dance with PART 1. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 03, 2014 747-53A2862Revision 1: July 24, 2015 33 of 366 BOEING SERVICE BULLETIN 747-53A2862 ALERTALERT ### Page 34 Table 5: Repeat Inspection of STA 320 Frame, Window Post #3 and Window Upper Sill Structure Repeat Interval (Not to Exceed) Compliance TimeActionCondition -Before further flight.Repair any crack or missing fastener in accor- dance with PART 1. CONDITION 2: FINDINGS DO NOT NECESSITATE INSPECTION OF STA 340 FRAME. (c) In accordance with this table. In accordance with this table.Do the next inspection for cracks in the STA 320 crown frame, Window Post #3 and the window upper sill in accordance with this table. No crack found or any crack found repaired in ac- cordance with PART 1. (a) The repair given in PART 7: REPLACE FRAME INNER CHORD + OUTBOARD WEB includes an optional step to cold work the inner chord at all fastener holes common to the inboard and outboard webs and to cold work the outboard webs at all fastener holes common to the inner chord. The condition description in the table that includes "WITH COLD WORK" applies only if this optional step was accomplished. The condition description in the table that includes "WITHOUT COLD WORK" applies when this optional step was not accomplished. (b) The inspection findings that determine CONDITION 1 are types of crack damage specified in PART 1. (c) CONDITION 2 applies if there is any crack or missing fastener finding(s) and CONDITION 1 does not apply. The inspection findings that determine CONDITION 1 are types of crack damage specified in PART 1. (d) The area of Window Post #3 to be inspected is accessible from the cockpit without removing or cutting the dripshield. (e) This condition can include oversize fastener repairs accomplished in accordance with the original issue of this service bulletin. The original issue of this service bulletin included instruction for oversize fastener repairs at fastener holes common to the inner chord and outboard web of the STA320 crown frame and at fastener holes common to Window Post #3 and the STA320 crown frame inner chord. Group 1-2: Table 6: One Time Work Associated with Revision 1 of this Service Bulletin Repeat Interval (Not to Exceed) Compliance TimeActionCondition -Within 16,000 flight cycles after the new inner chord was installed. Do PART 11: MORE WORK ASSOCIATED WITH REVISION 1. (b) The STA 320 crown frame inner chord was replaced WITH COLD WORK in ac- cordance with PART 7 of Paragraph 3.B., Work In- structions of the Original Issue of this service bul- letin. (a) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 03, 2014 747-53A2862Revision 1: July 24, 2015 34 of 366 BOEING SERVICE BULLETIN 747-53A2862 ALERTALERT ### Page 35 Group 1-2: Table 6: One Time Work Associated with Revision 1 of this Service Bulletin Repeat Interval (Not to Exceed) Compliance TimeActionCondition -Within 9,000 flight cycles after the new inner chord was installed. Do PART 11: MORE WORK ASSOCIATED WITH REVISION 1. (b) The STA 320 crown frame inner chord was replaced in accordance with PART 6 or PART 7 WITHOUT COLD WORK of Paragraph 3.B., Work Instructions of the Original Issue of this service bulletin. (a) -Within 8,000 flight cycles after the previous inspection of the STA 320 crown frame. Do PART 11: MORE WORK ASSOCIATED WITH REVISION 1. (b) The STA 320 crown frame outboard web was replaced in accordance with PART 5 of Paragraph 3.B., Work Instructions of the Original Issue of this service bul- letin, and/or, An oversize fastener repair was done in accordance with PART 1 of Paragraph 3.B., Work Instructions of the Original Issue of this service bulletin at the fas- tener hole identified as Hole #11 and/or Hole #15 in the Original Issue of this service bulletin. (a) The repair given in PART 7: REPLACE FRAME INNER CHORD + OUTBOARD WEB includes an optional step to cold work the inner chord at all fastener holes common to the inboard and outboard webs and to cold work the outboard webs at all fastener holes common to the inner chord. The condition description in the table that includes "WITH COLD WORK" applies if this optional step was accomplished. The condition description in the table that includes "WITHOUT COLD WORK" applies when this optional step was not accomplished. (b) This action is not necessary if PART 11 has been done previously. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 03, 2014 747-53A2862Revision 1: July 24, 2015 35 of 366 BOEING SERVICE BULLETIN 747-53A2862 ALERTALERT ### Page 36 Group 3-4: Table 7: One Time Work Associated with Revision 1 of this Service Bulletin Repeat Interval (Not to Exceed) Compliance TimeActionCondition -Within 16,000 flight cycles after the new inner chord was installed. Do PART 11: MORE WORK ASSOCIATED WITH REVISION 1. (b) The STA 320 crown frame inner chord was replaced WITH COLD WORK in ac- cordance with PART 7 of Paragraph 3.B., Work In- structions of the Original Issue of this service bul- letin. (a) -Within 9,000 flight cycles after the new inner chord was installed. Do PART 11: MORE WORK ASSOCIATED WITH REVISION 1. (b) The STA 320 crown frame inner chord was replaced in accordance with PART 6 or PART 7 WITHOUT COLD WORK of Paragraph 3.B., Work Instructions of the Original Issue of this service bulletin. (a) -Within 8,000 flight cycles after the previous inspection of the STA 320 crown frame. Do PART 11: MORE WORK ASSOCIATED WITH REVISION 1. (b) The STA 320 crown frame outboard web was replaced in accordance with PART 5 of Paragraph 3.B., Work Instructions of the Original Issue of this service bul- letin, and/or, An oversize fastener repair was done in accordance with PART 1 of Paragraph 3.B., Work Instructions of the Original Issue of this service bulletin at the fas- tener hole identified as Hole #11 in the Original Is- sue of this service bulletin. (a) The repair given in PART 7: REPLACE FRAME INNER CHORD + OUTBOARD WEB includes an optional step to cold work the inner chord at all fastener holes common to the inboard and outboard webs and to cold work the outboard webs at all fastener holes common to the inner chord. The condition description in the table that includes "WITH COLD WORK" applies if this optional step was accomplished. The condition description in the table that includes "WITHOUT COLD WORK" applies when this optional step was not accomplished. (b) This action is not necessary if PART 11 has been accomplished previously. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 03, 2014 747-53A2862Revision 1: July 24, 2015 36 of 366 BOEING SERVICE BULLETIN 747-53A2862 ALERTALERT ### Page 37 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 accomplishment of the inspection, repair and post-repair inspections with the corresponding compliance times given in Service Bulletin 747-53A2862, Revision 1, as an alternative method of compliance (AMOC) to the corresponding inspection and repair requirements of paragraph (f) of AD 2005-08-01. This AMOC applies only to the areas inspected in accordance with this service bulletin. Where this service bulletin instructs to contact Boeing for repair instructions, the repair instructions must be approved by the FAA in accordance with paragraph (t) of the AD. All provisions of AD 2005-08-01 that are not specifically referenced in this paragraph remain fully applicable and must be complied with accordingly. In addition, the Manager of the FAA Seattle Aircraft Certification Office approves the accomplishment of the inspection, repair and post-repair inspections with the corresponding compliance times given in Service Bulletin 747-53A2862, Revision 1, as an alternative method of compliance (AMOC) to the corresponding inspection and repair requirements of paragraph (g) of AD 2009-19-05. This AMOC applies only to the areas inspected in accordance with this service bulletin. Where this service bulletin instructs to contact Boeing for repair instructions, the repair instructions must be approved by the FAA in accordance with paragraph (j) of the AD. All provisions of AD 2009-19-05 that are not specifically referenced in this paragraph remain fully applicable and must be complied with accordingly. In addition, the Manager of the FAA Seattle Aircraft Certification Office approves the accomplishment of the inspection, repair and post-repair inspections with the corresponding compliance times given in Service Bulletin 747-53A2862, Revision 1, as an alternative method of compliance (AMOC) to the corresponding post-replacement repetitive inspection requirements of paragraph (j) of AD 2012-22-02. This AMOC applies only to the areas inspected in accordance with this service bulletin. Where this service bulletin instructs to contact Boeing for repair instructions, the repair instructions must be approved by the FAA in accordance with paragraph (m) of the AD. All provisions of AD 2012-22-02 that are not specifically referenced in this paragraph remain fully applicable and must be complied with accordingly. G. Manpower The table below shows an estimate of the task hours necessary to do the inspections and repairs given in this service bulletin. These estimate are for direct labor only, done by an experienced crew. Adjust the estimate with operator task hour data if necessary. The estimate does not include lost time. These are some examples of lost time: • Time to adjust to the workplace • Time to schedule the work • Time to inspect the work • Time to cure the materials • Time to make the parts • Time to find the tools. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 03, 2014 747-53A2862Revision 1: July 24, 2015 37 of 366 BOEING SERVICE BULLETIN 747-53A2862 ALERTALERT ### Page 38 The Figures listed in the table below contain work instruction applicable to Group 1, 2 airplanes. Group 1-2: Elapsed HoursTask HoursNumber of PersonsTask 20.0040.002FIGURE 1 4.258.52FIGURE 3 4.754.751FIGURE 4 or FIG- URE 5 (L/R) 2.002.001FIGURE 6 2.702.701FIGURE 7 0.750.751FIGURE 8 3.006.002FIGURE 9 or FIG- URE 10 (L/R) 3.503.501FIGURE 11 or FIG- URE 12 (L/R) 26.5053.002FIGURE 21 12.0024.002FIGURE 22 2.002.001FIGURE 24 2.505.002FIGURE 25 (L or R side inspection) (a)(a)TOTAL FOR EACH AIRPLANE (a) This service bulletin gives alternative methods of access and repair and differ- ent tasks can be accomplished on each side of the airplane. Total hours de- pend on the tasks accomplished. In any case, the tasks given in only some of the figures listed will be applicable. The Figures listed in the table below contain work instruction applicable to Group 3, 4 airplanes. Group 3-4: Elapsed HoursTask HoursNumber of PersonsTask 35.0070.002FIGURE 2 4.258.502FIGURE 3 0.750.751FIGURE 8 4.754.751FIGURE 13 or FIG- URE 14 (L/R) 2.002.001FIGURE 15 2.702.701FIGURE 16 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 03, 2014 747-53A2862Revision 1: July 24, 2015 38 of 366 BOEING SERVICE BULLETIN 747-53A2862 ALERTALERT ### Page 39 Group 3-4: Elapsed HoursTask HoursNumber of PersonsTask 3.006.002FIGURE 17 or FIG- URE 18 (L/R) 3.503.501FIGURE 19 or FIG- URE 20 (L/R) 26.5053.002FIGURE 21 18.0036.002FIGURE 23 2.505.002FIGURE 25 (L or R side inspection) (a)(a)TOTAL FOR EACH AIRPLANE (a) This service bulletin gives alternative methods of access and repair and differ- ent tasks can be accomplished on each side of the airplane. Total hours de- pend on the tasks accomplished. In any case, the tasks given in only some of the figures listed will be applicable. H. Weight and Balance Changes Change in Moment (Pound-Inches) Change in Weight (Pounds)Airplane +509.2+1.6Group 1, Configura- tion 1 and Group 2 (a) No change (b)No change (b)Group 1, Configura- tion 2 +509.2+1.6Group 3, Configura- tion 1 and Group 4, non-747SP model airplanes (a) +827.4+1.6Group 3, Configura- tion 1 and Group 4, 747SP model air- planes only (a) No Change (b)No Change (b)Group 3, Configura- tion 2 (a) The specified weight and balance change is applicable only if the repair given in Paragraph 3.B., Work Instructions, PART 6 or PART 7 is accomplished. The change is due to a splice added to the inner chord of the STA 320 crown frame. This change does not include the effect of changes made to the cockpit overhead dripshield per Paragraph 3.B., Work Instruc- tions, PART 3. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 03, 2014 747-53A2862Revision 1: July 24, 2015 39 of 366 BOEING SERVICE BULLETIN 747-53A2862 ALERTALERT ### Page 40 Change in Moment (Pound-Inches) Change in Weight (Pounds)Airplane (b) The repair/modification given in this service bulletin does not give a weight or balance change for airplanes that have a previously added splice on the inner chord of the STA 320 crown frame. The table below gives the weight and balance changes that result from optional changes made to the cockpit overhead dripshield to incorporate access segments that can be removed to accomplish the inspections given in this service bulletin. Change in Moment (Pound-Inches) Change in Weight (Pounds)Airplane +197.7+0.6All non-747SP air- planes (a) +321.3+0.6747SP model air- planes (a) (a) The specified weight and balance change is applicable only if the work given in Paragraph 3.B., Work Instructions, PART 3 is accomplished. The change is due to a modification to the cockpit overhead dripshield to add removable segments to the left and right side of the dripshield. I. Electrical Load Data Not changed. J. References 1. Existing Data: a. Boeing Service Bulletin 747-25-3253, 747-53-2272, 747-53A2784 b. Boeing Service Letter 747-SL-747-SL-51-048 c. Boeing Service Related Problem (SRP) 747-SRP-53-0404, 747-SRP-53-0462 d. Federal Aviation Administration (FAA) Airworthiness Directive (AD) 2005-08-01, 2005-17-09, 2009-19-05, 2012-22-02 e. Service Bulletin Index D6-30300 f. Standard Overhaul Practices Manual (SOPM) 20-30-03, 20-30-99, 20-41-02, 20-43-03, 20-50-01, 20-50-10, 20-50-12, 20-50-19 g. 747 Fleet Team Digest (FTD) FTD-53-12005 h. 747 Non-Destructive Testing (NDT) Manual Part 6, 51-00-00 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 03, 2014 747-53A2862Revision 1: July 24, 2015 40 of 366 BOEING SERVICE BULLETIN 747-53A2862 ALERTALERT ### Page 41 i. 747-100/200/300 Aircraft Maintenance Manual (AMM) 24-27-04, 25-00-00, 25-11-01, 25-14-00, 25-14-01, 25-14-02, 25-15-00, 26-15-01, 31-00-00 j. 747-100/200/300 Structural Repair Manual (SRM) 51-30-05, 51-30-09, 53-10-04, Fig. 118 k. 747-400 Aircraft Maintenance Manual (AMM) 25-00-00, 25-11-01, 25-14-00, 25-14-01, 25-14-02, 25-15-00, 31-00-00 l. 747-400 Structural Repair Manual (SRM) 51-30-10, 51-40-05, 51-40-09, 53-10-07-2R-2 m. 747-400F Structural Repair Manual (SRM) 51-30-10, 51-40-05, 51-40-09, 53-10-07-2R-2 n. 747-400LCF Structural Repair Manual (SRM) 51-30-10, 51-40-05, 51-40-09 o. 747-400SF Structural Repair Manual (SRM) 51-30-10, 51-40-05, 51-40-09, 53-10-07-2R-2 p. 747-SP Structural Repair Manual (SRM) 51-30-05, 51-30-09 2. Data Supplied with this Service Bulletin: None. 3. Installation Drawings Used in the Preparation of this Service Bulletin: TitleDrawing Number Frame Installation - Upper Crown, CAB Station 32065B07603 Frame Installation - Station 340, Body Cab65B10334 Sill Installation - Upper, Crown, CAB, Section 4165B07616 No. 3 Post Instl - Cabin Window65B07613 Intercostal Instl - Upper Crown, CAB, BL 7.50 & BL 15.0065B07617 Duct Instl - Air Conditioning, Flight Deck214U1002 Dripshield Instl - Overhead, Pilots232U1301 The table above lists applicable drawings used to prepare this service bulletin. The drawings are not necessary to make the specified changes, and are not supplied with this service bulletin. The drawings may not be applicable to all airplane configurations or operators. K. Publications Affected 1. Publications: None. 2. Damage Tolerance Based Structural Inspections: Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 03, 2014 747-53A2862Revision 1: July 24, 2015 41 of 366 BOEING SERVICE BULLETIN 747-53A2862 ALERTALERT ### Page 42 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. DTI requirements for the structure affected are contained in Paragraph 1.E., Compliance of this service bulletin. L. Interchangeability and Intermixability of Parts Accomplishment of this service bulletin does not affect interchangeability or intermixability of parts. M. Software Accomplishment Summary Not affected. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 03, 2014 747-53A2862Revision 1: July 24, 2015 42 of 366 BOEING SERVICE BULLETIN 747-53A2862 ALERTALERT ### Page 43 2. MATERIAL INFORMATION A. Material - Price and Availability Boeing can supply the kits shown in Paragraph 2.C., Parts Necessary for Each Airplane. Operators are encouraged to share schedule requirements with Boeing for incorporation of the service bulletin. The kits are subject to the terms and conditions of the Boeing standard purchase order acknowledgment. Prices are in United States Dollars. Terms: Net 30 days. Reference this service bulletin and submit your purchase order by one of these methods: 1. Order on-line via ATA Spec 2000 or The Boeing PART Page 2. Fax to (206) 662-7145 REFER TO THE BOEING PART PAGE ON MYBOEINGFLEET.COM OR CONTACT FIRST RESPONDER AT FR@BOEING.COM FOR THE LATEST REORDER LEAD TIME (ROLT) AND PRICE INFORMATION Unit Price as of the original issue date of this Ser- vice Bulletin (US Dollars) ROLT as of the original issue date of this Ser- vice Bulletin (Cal- endar Days) QTYDateNameKit Number 7,843.0019611/17/2014Kit - Parts015U1928-3 103/14/2014 104/11/2014 105/9/2014 106/9/2014 107/8/2014 108/5/2014 3,009.00196103/14/2014Kit - Fasteners015U1928-4 (a) 104/11/2014 105/9/2014 5,492.0019655/16/2014Kit - Fasteners015U1928-5 (b) 268.0019613/14/2014Kit - Parts015U1928-6 807.0019613/14/2014Kit - Fasteners015U1928-7 (c) 1,946.0019615/16/2014Kit - Fasteners015U1928-8 (d) 5,659.00196103/14/2014Kit - Parts015U1928-9 104/11/2014 1,133.00196103/27/2014Kit - Fasteners015U1928-10 2,407.0019615/16/2014Kit - Fasteners015U1928-11 878.0019613/14/2014Kit - Fasteners015U1928-12 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 03, 2014 747-53A2862Revision 1: July 24, 2015 43 of 366 BOEING SERVICE BULLETIN 747-53A2862 ALERTALERT ### Page 44 REFER TO THE BOEING PART PAGE ON MYBOEINGFLEET.COM OR CONTACT FIRST RESPONDER AT FR@BOEING.COM FOR THE LATEST REORDER LEAD TIME (ROLT) AND PRICE INFORMATION Unit Price as of the original issue date of this Ser- vice Bulletin (US Dollars) ROLT as of the original issue date of this Ser- vice Bulletin (Cal- endar Days) QTYDateNameKit Number 978.0019615/16/2014Kit - Fasteners015U1928-13 128.00196203/14/2014Kit - fasteners/nutplates015U1928-14 204/11/2014 105/9/2014 106/9/2014 107/8/2014 108/5/2014 (e)(e)(e)(e)Kit - Fasteners015U1928-17 (a) (e)(e)(e)(e)Kit - Fasteners015U1928-18 (b) (e)(e)(e)(e)Kit - Fasteners015U1928-19 (c) (e)(e)(e)(e)Kit - Fasteners015U1928-20 (d) (e)(e)(e)(e)Kit - Supplemental015U1928-21 (a) (e)(e)(e)(e)Kit - Supplemental015U1928-22 (b) (e)(e)(e)(e)Kit - Supplemental015U1928-23 (c) (e)(e)(e)(e)Kit - Supplemental015U1928-24 (d) (a) Kit 015U1928-4 is obsolete and has been replaced by kit 015U1928-17. Kit 015U1928-21 is a supplemental kit for kit 015U1928-4. Supplemental kit 015U1928-21 plus kit 015U1928-4 is equivalent to replacement kit 015U1928-17. (b) Kit 015U1928-5 is obsolete and has been replaced by kit 015U1928-18. Kit 015U1928-22 is a supplemental kit for kit 015U1928-5. Supplemental kit 015U1928-22 plus kit 015U1928-5 is equivalent to replacement kit 015U1928-18. (c) Kit 015U1928-7 is obsolete and has been replaced by kit 015U1928-19. Kit 015U1928-23 is a supplemental kit for kit 015U1928-7. Supplemental kit 015U1928-23 plus kit 015U1928-7 is equivalent to replacement kit 015U1928-19. (d) Kit 015U1928-8 is obsolete and has been replaced by kit 015U1928-20. Kit 015U1928-24 is a supplemental kit for kit 015U1928-8. Supplemental kit 015U1928-24 plus kit 015U1928-8 is equivalent to replacement kit 015U1928-20. (e) Contact Boeing for price and availability information. B. Industry Support Information Boeing warranty remedies are not available for the inspection, and/or repair procedures given in this service bulletin. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 03, 2014 747-53A2862Revision 1: July 24, 2015 44 of 366 BOEING SERVICE BULLETIN 747-53A2862 ALERTALERT ### Page 45 C. Parts Necessary for Each Airplane 1. Kits/Parts To get the kits shown below, refer to Paragraph 2.A., Material - Price and Availability. ContentsKit 015U1928- ( )Application Parts only.-3Accomplish PART 7: REPLACE INNER CHORD + OUTBOARD WEB on a Group 1 or Group 2 airplane. Fasteners for Group 1, Configuration 1and Group 2.-17 (a) Fasteners for Group 1, Configuration 2.-18 (b) Parts only.-6Accomplish PART 5: REPLACE FRAME OUTBOARD WEB ONLY on a Group 1 or Group 2 airplane. Fasteners for Group 1, Configuration 1and Group 2.-19 (c) Fasteners for Group 1, Configuration 2.-20 (d) Click Bond Nutplates and fasteners.-14Restore the dripshield per Figure 22. (a) Obsolete kit 015U1928-4 plus supplemental kit 015U1928-21 is equivalent to kit 015U1928-17. (b) Obsolete kit 015U1928-5 plus supplemental kit 015U1928-22 is equivalent to kit 015U1928-18. (c) Obsolete kit 015U1928-7 plus supplemental kit 015U1928-23 is equivalent to kit 015U1928-19. (d) Obsolete kit 015U1928-8 plus supplemental kit 015U1928-24 is equivalent to kit 015U1928-20. ContentsKit 015U1928- ( )Application Parts only.-9Accomplish PART 7: REPLACE INNER CHORD + OUTBOARD WEB on a Group 3 or Group 4 airplane. Fasteners for Group 3, Configuration 1and Group 4.-10 Fasteners for Group 3, Configuration 2.-11 Parts only.-6Accomplish PART 5: REPLACE FRAME OUTBOARD WEB ONLY on a Group 3 or Group 4 airplane. Fasteners for Group 3, Configuration 1and Group 4.-12 Fasteners for Group 3, Configuration 2.-13 Click Bond Nutplates and fasteners.-14Restore the dripshield per Figure 23. ALL Kit 015U1928 NotesExisting Part Number NameQtyNew Part Number -12-11-10-9-6-3 Kit - STA 320 Crown Frame Mod- ification .....-015U1928-3 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 03, 2014 747-53A2862Revision 1: July 24, 2015 45 of 366 BOEING SERVICE BULLETIN 747-53A2862 ALERTALERT ### Page 46 ALL Kit 015U1928 NotesExisting Part Number NameQtyNew Part Number -12-11-10-9-6-3 Kit - STA 320 Crown Frame Mod- ification ....-.015U1928-6 Kit - STA 320 Crown Frame Mod- ification ...-..015U1928-9 Kit - STA 320 Crown Frame Mod- ification ..-...015U1928-10 Kit - STA 320 Crown Frame Mod- ification .-....015U1928-11 Kit - STA 320 Crown Frame Mod- ification -.....015U1928-12 SPLICE PLATE.....1141U0058-15 SPLICE STRAP.....1141U0058-17 SPLICE STRAP.....1141U0058-19 SPLICE STRAP.....1141U0058-20 SPLICE PLATE...1..141U1006-3 SPLICE PLATE...2..141U1006-5 SPLICE PLATE...1..141U1006-7 SPLICE PLATE...1..141U1006-13 CHORD RIGHT...1..141U1006-15 CHORD LEFT...1..141U1006-17 WEB...21265B07603-12 FILLER...21265B07603-25 STRAP.....165B07603-53 STRAP.....165B07603-54 CHORD ASSY.....165B07603-61 STRAP...1..69B12990-7 STRAP...1..69B12990-8 BOLT, PROTRUD- ING HD 444...BACB30MY8K8X Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 03, 2014 747-53A2862Revision 1: July 24, 2015 46 of 366 BOEING SERVICE BULLETIN 747-53A2862 ALERTALERT ### Page 47 ALL Kit 015U1928 NotesExisting Part Number NameQtyNew Part Number -12-11-10-9-6-3 BOLT, HEX HEAD51010...BACB30NM3K12X BOLT, HEX HEAD6.12...BACB30NM3K10X BOLT TITANIUM O/S .12....BACB30NM3K10Y BOLT, HEX HEAD122...BACB30NR4K6X BOLT, 100 DEG HEX DR 41010...BACB30NW6K6X BOLT, PROTRUD- ING HD 112638...BACB30NX6K4X BOLT, PROTRUD- ING HD .4424...BACB30NX6K4Y BOLT, PROTRUD- ING HD 41814...BACB30NX6K5X BOLT, PROTRUD- ING HD .1816...BACB30NX6K5Y BOLT, PROTRUD- ING HD 183036...BACB30NX6K6X BOLT, PROTRUD- ING HD 54632...BACB30NX6K6Y BOLT, PROTRUD- ING HD 388...BACB30NX6K7X BOLT, PROTRUD- ING HD 448...BACB30NX6K8X BOLT, PROTRUD- ING HD 4410...BACB30NX6K9X BOLT, PROTRUD- ING HD .1....BACB30NX6K9Y BOLT.816...BACB30VT6K4 BOLT..8...BACB30VT6K5 BOLT.210...BACB30VT6K6 BOLT.2....BACB30VT8K5 BOLT SHEAR LIGHT .4....BACB30VT8K8 BOLT HI-LOK.4....BACB30VT8K9 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 03, 2014 747-53A2862Revision 1: July 24, 2015 47 of 366 BOEING SERVICE BULLETIN 747-53A2862 ALERTALERT ### Page 48 ALL Kit 015U1928 NotesExisting Part Number NameQtyNew Part Number -12-11-10-9-6-3 COLLAR511072...BACC30AC6 COLLAR4490114...BACC30BH6 COLLAR.1034...BACC30BL6 COLLAR.10....BACC30BL8 COLLAR41010...BACC30M6 COLLAR244...BACC30M8 NUT112222...BACN10JC3CD NUT122...BACN10JC4CD SHIM, LAMINAT- ED .....2BACS40R010B010F WASHER111022...BACW10BP31CD WASHER111022...BACW10BP31DP WASHER.12....BACW10BP32CD WASHER.12....BACW10BP32DP WASHER122...NAS1149D0432J (a) If grip length shown is not available at Boeing, fasteners supplied in kits may be one grip length longer than indicated. Also, if any fasteners part numbers listed are not available or have been superseded, substitute fasteners may be supplied in kits. ALL Kit 015U1928 NotesExisting Part Number NameQtyNew Part Number -20-19-18-17-14-13 Kit - STA 320 Crown Frame Mod- ification .....-015U1928-13 Kit - STA 320 Crown Frame Mod- ification ....-.015U1928-14 Kit - Retrofit - STA 320 Crown Frame Modification - Fas- teners ...-..015U1928-17 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 03, 2014 747-53A2862Revision 1: July 24, 2015 48 of 366 BOEING SERVICE BULLETIN 747-53A2862 ALERTALERT ### Page 49 ALL Kit 015U1928 NotesExisting Part Number NameQtyNew Part Number -20-19-18-17-14-13 Kit - Retrofit - STA 320 Crown Frame Modification - Fas- teners ..-...015U1928-18 Kit - Retrofit - STA 320 Crown Frame Modification - Fas- teners .-....015U1928-19 Kit - Retrofit - STA 320 Crown Frame Modification - Fas- teners -.....015U1928-20 BOLT, PROTRUD- ING HD ..44..BACB30MY10K6X BOLT, PROTRUD- ING HD ...4..BACB30MY10K8X BOLT, PROTRUD- ING HD ..4...BACB30MY10K8Y BOLT, PROTRUD- ING HD ...2..BACB30MY8K11X BOLT, PROTRUD- ING HD ..2...BACB30MY8K11Y BOLT, PROTRUD- ING HD ...24..BACB30MY8K5X BOLT, PROTRUD- ING HD ..24...BACB30MY8K5Y BOLT, HEX DRIVE..10...BACB30MY8K6 BOLT, PROTRUD- ING HD ...30..BACB30MY8K6X BOLT, PROTRUD- ING HD 5.30...BACB30MY8K6Y BOLT, PROTRUD- ING HD ...6..BACB30MY8K7X BOLT, PROTRUD- ING HD ..6...BACB30MY8K7Y BOLT, PROTRUD- ING HD .2.16.2BACB30MY8K8X Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 03, 2014 747-53A2862Revision 1: July 24, 2015 49 of 366 BOEING SERVICE BULLETIN 747-53A2862 ALERTALERT ### Page 50 ALL Kit 015U1928 NotesExisting Part Number NameQtyNew Part Number -20-19-18-17-14-13 BOLT, PROTRUD- ING HD 2.16...BACB30MY8K8Y BOLT, PROTRUD- ING HD ...20..BACB30MY8K9X BOLT, PROTRUD- ING HD ..20...BACB30MY8K9Y BOLT, HEX HEAD.1.2..BACB30NM3K11X BOLT, HEX HEAD1.2...BACB30NM3K11Y BOLT, HEX HEAD.5.10.5BACB30NM3K12X BOLT, HEX HEAD5.10...BACB30NM3K12Y BOLT.6.2..BACB30NM3K13X BOLT6.12...BACB30NM3K13Y BOLT TITANIUM O/S .....6BACB30NM3K10Y BOLT...2..BACB30NR4K11X BOLT, HEX HEAD..2...BACB30NR4K11Y BOLT, HEX HEAD.168.1BACB30NR4K6X BOLT, HEX HEAD1.2...BACB30NR4K6Y BOLT, HEX HEAD...2..BACB30NR4K8X BOLT, HEX HEAD..2...BACB30NR4K8Y BOLT, 100 DEG HEX DR .....4BACB30NW6K6X BOLT, PROTRUD- ING HD .111214.11BACB30NX6K4X BOLT, PROTRUD- ING HD 11.14...BACB30NX6K4Y BOLT, PROTRUD- ING HD 44208.4BACB30NX6K5X BOLT, PROTRUD- ING HD 14214040.18BACB30NX6K6X BOLT, PROTRUD- ING HD 751210.5BACB30NX6K6Y BOLT, PROTRUD- ING HD 3366.3BACB30NX6K7X Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 03, 2014 747-53A2862Revision 1: July 24, 2015 50 of 366 BOEING SERVICE BULLETIN 747-53A2862 ALERTALERT ### Page 51 ALL Kit 015U1928 NotesExisting Part Number NameQtyNew Part Number -20-19-18-17-14-13 BOLT, PROTRUD- ING HD 24288.2BACB30NX6K8X BOLT, PROTRUD- ING HD 2.4...BACB30NX6K8Y BOLT, PROTRUD- ING HD 2448.3BACB30NX6K9X BOLT, PROTRUD- ING HD 2.4...BACB30NX6K9Y BOLT, PROTRUD- ING HD ...2..BACB30NX8K11X BOLT, PROTRUD- ING HD ..2...BACB30NX8K11Y BOLT, PROTRUD- ING HD ...2..BACB30NX8K8X BOLT, PROTRUD- ING HD ..2...BACB30NX8K8Y BOLT..820..BACB30VT6K4 BOLT...12..BACB30VT6K5 BOLT..214..BACB30VT6K6 BOLT...24..BACB30VT6K8 BOLT SHEAR LIGHT .....2BACB30VT8K8 BOLT HI-LOK.....1BACB30VT8K9 COLLAR2253410.5BACC30AC6 COLLAR..4...BACC30AC8 COLLAR254711084.41BACC30BH6 COLLAR...4..BACC30BH8 COLLAR..1070..BACC30BL6 COLLAR.....3BACC30BL8 COLLAR..48..BACC30M10 COLLAR.....4BACC30M6 COLLAR521098.2BACC30M8 COLLAR..4...BACC30R10 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 03, 2014 747-53A2862Revision 1: July 24, 2015 51 of 366 BOEING SERVICE BULLETIN 747-53A2862 ALERTALERT ### Page 52 ALL Kit 015U1928 NotesExisting Part Number NameQtyNew Part Number -20-19-18-17-14-13 COLLAR2.98...BACC30R8 NUT12122424.11BACN10JC3CD NUT,SELF-LOCK- ING 111212.1BACN10JC4CD FAIRING SCREWS....25.BACS12FA3K5 FAIRING SCREWS....25.BACS12FA3K6 WASHER, PLAIN.12.24.5BACW10BP31CD WASHER, PLAIN.12.24.5BACW10BP31DP WASHER, PLAIN12.24..6BACW10BP32CD WASHER, PLAIN12.24..6BACW10BP32DP WASHER, SELF- ALIGN 2244..BACW10CA104CC WASHER.244..BACW10CA31CV WASHER2.....BACW10CA32CV WASHER, SELF- ALIGN ..44..BACW10CA41CV WASHER..44..BACW10CA5CC NUTPLATE, MINIATURE, FLOATING ....25.CB6014CR3-1P WASHER.1612.1NAS1149D0432J WASHER1.6...NAS1149D0532J (a) If grip length shown is not available at Boeing, fasteners supplied in kits may be one grip length longer than indicated. Also, if any fasteners part numbers listed are not available or have been superseded, substitute fasteners may be supplied in kits. ALL Kit 015U1928 NotesExisting Part Number NameQtyNew Part Number -24-23-22-21 Kit - Retrofit - Sup- plemental Fasten- ers ...-015U1928-21 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 03, 2014 747-53A2862Revision 1: July 24, 2015 52 of 366 BOEING SERVICE BULLETIN 747-53A2862 ALERTALERT ### Page 53 ALL Kit 015U1928 NotesExisting Part Number NameQtyNew Part Number -24-23-22-21 Kit - Retrofit - Sup- plemental Fasten- ers ..-.015U1928-22 Kit - Retrofit - Sup- plemental Fasten- ers .-..015U1928-23 Kit - Retrofit - Sup- plemental Fasten- ers -...015U1928-24 BOLT.6.12BACB30NM3K13X BOLT6.12.BACB30NM3K13Y WASHER, PLAIN.12.24BACW10BP31CD WASHER, PLAIN.12.24BACW10BP31DP WASHER, PLAIN12.24.BACW10BP32CD WASHER, PLAIN12.24.BACW10BP32DP (a) If grip length shown is not available at Boeing, fasteners supplied in kits may be one grip length longer than indicated. Also, if any fasteners part numbers listed are not available or have been superseded, substitute fasteners may be supplied in kits. 2. Parts and Materials Supplied by the Operator The following parts or materials are necessary to do the change in this service bulletin. Parts and materials in the manuals given in Paragraph 1.J., References, can also be necessary. Examine operator part and material supply to make sure all necessary parts and materials are available. 3. Parts Modified and Reidentified The parts shown below are changed as shown in this service bulletin. The quantity (QTY) is the number of parts changed on each airplane. 4. Parts Removed and Not Replaced None. D. Parts Necessary to Change Spares None. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 03, 2014 747-53A2862Revision 1: July 24, 2015 53 of 366 BOEING SERVICE BULLETIN 747-53A2862 ALERTALERT ### Page 54 E. Special Tooling - Price and Availability The 747-400 SRM 51-40-09, 747-400F SRM 51-40-09, 747-400SF SRM 51-40-09, 747-400LCF SRM 51-40-09 and the 747-100/200/300 SRM 51-30-09 and 747-SP SRM 51-30-09 give data about cold working tools and sleeves necessary to do the work given in this service bulletin. These tools are available from industry sources. Engineering, service, and a kit of cold working tools made for this change are available from Fatigue Technology, Inc. or West Coast Industries, Inc. • Refer To: FTI Kit Number:FTI-747-53A-2862-1 Fatigue Technology, Inc. P.O. Box C-88388 Seattle, WA 98188 USA Phone Number (206) 246-2010 Fax (206) 244-9886 • Refer To: WCI Kit Number: WCI-747-53A-2862 West Coast Industries, Inc. 14900 Whitman Avenue North Seattle, WA 98133-6532 USA Phone Number (206) 365-7513 Fax (206) 365-7483 F. Special Tooling Necessary to do this Service Bulletin Cold working tools are necessary to do a change given in this service bulletin. To get the cold working tools, refer to Paragraph 2.E., Special Tooling - Price and Availability. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 03, 2014 747-53A2862Revision 1: July 24, 2015 54 of 366 BOEING SERVICE BULLETIN 747-53A2862 ALERTALERT ### Page 55 3. ACCOMPLISHMENT INSTRUCTIONS A. GENERAL INFORMATION CAUTION: KEEP THE WORK AREA, WIRES AND ELECTRICAL BUNDLES CLEAN OF METAL PARTICLES OR CONTAMINATION WHEN YOU USE TOOLS. UNWANTED MATERIAL, METAL PARTICLES OR CONTAMINATION CAUGHT IN WIRE BUNDLES CAN CAUSE DAMAGE TO THE BUNDLES. DAMAGED WIRE BUNDLES CAN CAUSE SPARKS OR OTHER ELECTRICAL DAMAGE. NOTE: 1. Manual titles are referred to by acronyms. Refer to Paragraph 1.J., References, for definition of the acronyms. 2. Obey all of the warnings and cautions given in the specified manual sections. 3. Unless shown differently, these dimensions and tolerances are used: – Linear dimensions are in inches – Tolerance on linear dimensions, other than rivet and bolt edge margins, is plus or minus 0.03 inch – Tolerance on rivet and bolt edge margin is plus or minus 0.05 inch – Angular tolerance is plus or minus 2 degrees – Hole dimensions for standard solid rivets and fasteners are in Structural Repair Manual (SRM) Chapter 51 – Torque Values: — Values for structural fasteners are given in 747 Structural Repair Manual, Chapter 51. — Values for airframe maintenance tasks are included in Chapter 20 of 747 Aircraft Maintenance Manual (AMM). — Non-standard torque values for maintenance tasks are included in the applicable installation step. 4. Use the approved fastener, process and material substitutions in accordance with SRM Chapter 51. 5. If the length of any fastener specified in this service bulletin does not meet installation standards given in SRM Chapter 51, then a fastener of the same specification, or an approved substitute, with a length which meets the installation standards given in SRM Chapter 51 may be used. In addition, washers may be installed for fastener grip length in accordance with SRM Chapter 51. Refer to SOPM 20-50-01 for alternate full threaded fasteners (screws) needed for installation in this service bulletin. 6. A Detailed Inspection is defined as: An intensive examination of a specific item, installation, or assembly to detect damage, failure, or irregularity. Available lighting is normally supplemented with a direct source of good lighting at an intensity deemed appropriate. Inspection aids such as mirrors, magnifying lenses, etc. may be necessary. Surface cleaning and elaborate procedures may be required. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 03, 2014 747-53A2862Revision 1: July 24, 2015 55 of 366 BOEING SERVICE BULLETIN 747-53A2862 ALERTALERT ### Page 56 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 enhance visual access to all exposed surfaces in the inspection area. This level of inspection is made under normally 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. These work instructions refer to procedures included in other Boeing documents. When the words "refer to" are used and the operator has an accepted alternative procedure, the accepted alternative procedure can be used. When the words "in accordance with" are included in the instruction, the procedure in the Boeing document must be used. 9. Boeing Service Letter 747-SL-747-SL-51-048, Damage Reporting and Repair Plan/Design Guidelines, is an acceptable procedure to request information from Boeing for additional structural repair instructions. The Service Letter describes what information must be provided to Boeing before a structural repair can be provided. 10. Refer to APPENDIX C for a logic diagram. The Logic diagram is provided as an aid only. Information contained in Paragraph 1.E., Compliance is the primary source for compliance times. Information in Paragraph 3.B., Work Instructions is the primary source for tasks required for compliance. 11. The instructions in Paragraph 3.B., Work Instructions and the figures can include operation of tools or test equipment. Boeing Engineering Tool Drawings, the Illustrated Tool and Equipment Manual, and the Special Tool and Ground Handling Drawing Index contain data on versions of the tools or test equipment that you can use. It is permitted to use replaced tools. It is not permitted to use superseded tools. 12. If it is necessary to remove more parts for access, you can remove those parts. If you can get access without removing identified parts, it is not necessary to remove all of the identified parts. Jacking and shoring limitations must be observed. 13. Where the work instructions include installation of a kept part, a new or serviceable part with the same part number can be installed as an alternative to the kept part. 14. Some Boeing parts are supplied in a temporary configuration. Those parts are identified with a 'U', 'W', or 'Y' in place of the '-' (dash) in the part number. It is permitted to install parts identified with a 'U', 'W', or 'Y' as an alternative to the '-' (dash) part number. Boeing Drawing 005W0900 contains more data. 15. The compliance times for the actions in Paragraph 3.B., WORK INSTRUCTIONS are in Paragraph 1.E., Compliance. 16. Some steps in the Work Instructions are labeled as Required for Compliance (RC). If this service bulletin is mandated by an Airworthiness Directive (AD), then the steps labeled as RC, including sub-steps under an RC step and any figures identified in an RC step, must be done to comply with the AD. An Alternative Method of Compliance (AMOC) is required for any deviations to RC steps, including sub steps Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 03, 2014 747-53A2862Revision 1: July 24, 2015 56 of 366 BOEING SERVICE BULLETIN 747-53A2862 ALERTALERT ### Page 57 and identified figures. Steps not labeled as RC may be deviated from using accepted methods in accordance with the operator's maintenance or inspection program without obtaining approval of an AMOC. This is provided that the RC steps, including sub-steps and identified figures, can still be done as specified, and the airplane can be put back in an airworthy condition. B. WORK INSTRUCTIONS PART 1: INSPECTION AND REPAIR OF STA 320 CROWN FRAME, WINDOW POST #3 AND WINDOW UPPER SILL 1. Get access to the STA 320 crown frame inspection area on the left and right side of the airplane. NOTE: An overhead dripshield prevents direct access to the frame and upper sill inspection areas and to remove the dripshield it is necessary to first remove overhead equipment panels, air conditioning ducts/hoses, wire bundles, etc. If the dripshield is removed, no additional access work will be necessary to do any of the repairs given in this service bulletin; however, to restore access, it will be necessary to restore all the airplane systems affected by the access work. – – As an alternative to removing the dripshield, the dripshield can be modified to include segments that can be removed to get access to the inspection areas. Note that this method will not give sufficient access to replace the frame inner chord which could be necessary due to a crack finding. If the dripshield is removed from the airplane, the dripshield can be modified to include the removable segments while it is out of the airplane. This will permit future inspections to be accomplished without removing the entire dripshield. – The area of Window Post #3 to be inspected is accessible from the cockpit without removing or cutting the dripshield. To get instruction for access to the inspection areas via removal of the dripshield, refer to Paragraph 3.B., Work Instructions, PART 2. To get instruction for access to the inspection areas via modification of the dripshield, refer to Paragraph 3.B., Work Instructions, PART 3. If additional clear space is needed/desired around the work area, remove the pilot's seat(s). Refer to 747-400 AMM 25-11-01 or 747-100/200/300 AMM 25-11-01 as applicable for pilot's seat removal instruction. To get access and disassembly instructions for the repairs given in this service bulletin, refer to Paragraph 3.B., Work Instructions PART 4. 2. RC - Inspect the STA 320 crown frame, Window Post #3 and the window upper sill for any crack. With the initial inspection of the STA 320 crown frame and window upper sill for any crack, also inspect the STA 320 crown frame and window upper sill for any missing fastener. Do these inspections on the left and right sides of the airplane/frame in accordance with FIGURE 3. If no crack is found and there is no missing fastener, go to step 5. 3. RC - a. After all the inspection work given in FIGURE 3 is accomplished, determine which CONDITION described in the table below is applicable: Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 03, 2014 747-53A2862Revision 1: July 24, 2015 57 of 366 BOEING SERVICE BULLETIN 747-53A2862 ALERTALERT ### Page 58 Description of Finding(s)Condition On the same side of the airplane, both the inner chord of the STA 320 crown frame and the window upper sill chord are fully severed by cracks, CONDITION 1: FINDINGS NECESSITATE INSPEC- TION OF STA 340 FRAME or, On the same side of the airplane, the window upper sill chord is fully severed and Window Post #3 has any crack that extends beyond the crack boundary line shown in FIGURE 3. Any crack or missing fastener is found and CONDITION 1 does not apply. CONDITION 2: FINDINGS DO NOT NECESSITATE INSPECTION OF STA 340 FRAME b. If CONDITION 1 applies: (1) Do PART 10: STA 340 FRAME INSPECTION. (2) Do PART 8: SPECIAL INSTRUCTION REPAIR and then go to step 5. c. If CONDITION 2 applies, go to step 4. 4. RC- For any crack or missing fastener, do a repair in accordance with an applicable PART of Paragraph 3.B., Work Instructions as identified in the table below. Applicable Repair AlternativesFinding PART 5: REPLACE FRAME OUTBOARD WEB ONLYAny crack in the STA 320 crown frame outboard web only. PART 7: REPLACE FRAME INNER CHORD + OUT- BOARD WEB (a) PART 6: REPLACE FRAME INNER CHORD ONLYAny crack in the STA 320 crown frame inner chord only. PART 7: REPLACE FRAME INNER CHORD + OUT- BOARD WEB (b) PART 7: REPLACE FRAME INNER CHORD + OUT- BOARD WEB Any crack in the STA 320 crown frame outboard web where there is also any crack in the STA 320 crown frame inner chord. PART 9: UPPER SILL REPAIRAny crack in the window upper sill chord and all cracks in the window upper sill chord are contained within the SRM repair area defined in FIGURE 3. PART 8: SPECIAL INSTRUCTION REPAIRAny crack in a window upper sill that is not contained within the SRM repair area defined in FIGURE 3. (c) PART 8: SPECIAL INSTRUCTION REPAIRAny crack in Window Post #3. PART 8: SPECIAL INSTRUCTION REPAIRAny crack in the STA 340 frame. PART 8: SPECIAL INSTRUCTION REPAIRAny missing fastener or any crack that will not be re- paired by doing PART 5, PART 6, PART 7 or PART 9. (a) PART 7 is an alternative to PART 5. Accomplishment of PART 7 may extend the compliance time for the next inspection as shown in Paragraph 1.E., Compliance. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 03, 2014 747-53A2862Revision 1: July 24, 2015 58 of 366 BOEING SERVICE BULLETIN 747-53A2862 ALERTALERT ### Page 59 Applicable Repair AlternativesFinding (b) PART 7 is an alternative to PART 6. Accomplishment of PART 7 may extend the compliance time for the next inspection as shown in Paragraph 1.E., Compliance. (c) This condition applies if the crack is found in an unrepaired window upper sill, or the crack is found after the window upper sill has been repaired in accordance with PART 9. 5. Put the airplane back to a servicable condition. 6. RC - REPEAT / POST-REPAIR INSPECTIONS: a. If PART 9: UPPER SILL REPAIR has NOT been done: (1) Repeat the Detailed and Surface HFEC inspections for cracks in the STA 320 crown frame, window upper sill and Window Post #3 and repair any crack found in accordance with Paragraph 1.E., Compliance and Paragraph 3.B., Work Instructions, PART 1. b. If PART 9: UPPER SILL REPAIR has been done: (1) Repeat the Detailed and Surface HFEC inspections for cracks in the STA 320 crown frame, window upper sill and Window Post #3 and repair any crack found in accordance with Paragraph 1.E., Compliance and Paragraph 3.B., Work Instructions, PART 1. Also, do Detailed and Surface HFEC post-repair inspections for cracks in the repaired window upper sill in accordance with Paragraph 1.E., Compliance and the applicable SRM repair identified in PART 9. Repair any crack found in accordance with Paragraph 1.E., Compliance and Paragraph 3.B., Work Instructions, PART 1. 7. RC - CONDITIONAL, ONE-TIME WORK ASSOCIATED WITH REVISION 1: Do PART 11: MORE WORK ASSOCIATED WITH REVISION 1 in accordance with Paragraph 1.E., Compliance if any of the following conditions apply and the work given in PART 11 has not been accomplished previously: – The STA 320 crown frame outboard web, inner chord, or both were replaced in accordance with PART 5, PART 6 or PART 7 respectively of Paragraph 3.B., Work Instructions of the Original Issue of this service bulletin. – An oversize fastener repair was done in accordance with PART 1 of Paragraph 3.B., Work Instructions of the Original Issue of this service bulletin at specific fastener hole(s) identified in the Original Issue of this service bulletin as follows: Group 1, 2 airplanes: Hole #11 or Hole #15. Group 3, 4 airplanes: Hole #11. PART 2: ACCESS / RESTORE ACCESS FOR INSPECTION AND REPAIR OF STA 320 CROWN FRAME VIA REMOVAL OF THE DRIPSHIELD 1. GAIN ACCESS: Get access to the STA 320 crown frame and window upper sill inspection areas by removing the overhead dripshield(s) and sill parts. Refer to FIGURE 21 for instruction. Also remove the pilot's seat(s) if additional clear space is needed/desired around the work area. Refer to 747-400 AMM 25-11-01 or 747-100/200/300 AMM 25-11-01 as applicable for pilot's seat removal instruction. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 03, 2014 747-53A2862Revision 1: July 24, 2015 59 of 366 BOEING SERVICE BULLETIN 747-53A2862 ALERTALERT ### Page 60 NOTE: An overhead dripshield prevents direct access to the inspection areas and to remove the dripshield it is necessary to first remove overhead equipment panels, air conditioning ducts/hoses, wire bundles, etc. With access via removal of the dripshield, no additional access work will be necessary to do any of the repairs given in this service bulletin; however, to restore access, it will be necessary to restore all the airplane systems affected by the access work. – – An alternative access procedure is given in Paragraph 3.B., Work Instructions, PART 3. With the alternative procedure, openings are cut into the dripshield and the dripshield is then restored to a configuration with segments that can be removed to get access for future inspections. The alternative procedure will not give sufficient access to replace the frame inner chord which could be necessary due to a crack finding. – If the dripshield is removed, it can be modified to include the removable segments in accordance with Paragraph 3.B., Work Instructions, PART 3 while it is out of the airplane, or the work given in PART 3 can be partially accomplished in the cockpit on an installed dripshield and completed while the dripshield is removed from the airplane. For Group 3, 4 airplanes only, remove the M0176 APU Control Module Assembly and the M0177 Auxiliary Power Control Module Assembly from the P4 flight engineers panel to get access to attachment fasteners at the aft end of the dripshield. Refer to 747-100/200/300 AMM 26-15-01 and 747-100/200/300 AMM 24-27-04 respectively for removal instruction. 2. RESTORE ACCESS: After the inspection and repair work is complete, reinstall parts removed to get access. For applicable instruction, refer to FIGURE 21. For Group 3, 4 airplanes, reinstall the M0176 APU Control Module Assembly and the M0177 Auxiliary Power Control Module Assembly. Refer to 747-100/200/300 AMM 26-15-01 and 747-100/200/300 AMM 24-27-04 respectively for accepted installation and test procedures. 3. Test any airplane system disturbed by the access work to verify satisfactory system operation. 4. Put the airplane back to a servicable condition. PART 3: ACCESS / RESTORE ACCESS FOR INSPECTION OF STA 320 CROWN FRAME VIA MODIFICATION OF THE DRIPSHIELD 1. GAIN ACCESS: Remove ceiling and sidewall panels from the cockpit. Refer to FIGURE 1 (Group 1, 2 airplanes) or FIGURE 2 (Group 3, 4 airplanes) for applicable instruction. NOTE: – With this access procedure, openings are cut into the dripshield and the dripshield is then restored to a configuration with segments that can be removed to get access for future inspections. This procedure will not provide sufficient access to replace the frame inner chord which could be necessary due to a crack finding. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 03, 2014 747-53A2862Revision 1: July 24, 2015 60 of 366 BOEING SERVICE BULLETIN 747-53A2862 ALERTALERT The text continues at https://openairdocs.org/service-documents/boeing/747-53a2862/file/8d81bc5df324.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.