# Boeing Alert Service Bulletin 747-53A2837: No revision named - Rights: © The Boeing Company. Filed by the FAA in regulations.gov docket FAA-2013-0425; AD 2014-07-01 incorporates this document by reference. Not covered by OpenAirDocs’ CC0 dedication. - Document: [Boeing Alert Service Bulletin 747-53A2837](https://openairdocs.org/service-documents/boeing/747-53a2837.md) - Title as filed: U.S. DOT/FAA - Service Bulletin - Pages: 250 - PDF: https://openairdocs.org/files/sha256/6e/13/6e133c9fc4cf44eb72cd4f668d037b26e73e2197bf077ccfa879de25f9efe1c0 - Page: https://openairdocs.org/service-documents/boeing/747-53a2837/file/6e133c9fc4cf ## 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: 747-53A2837 Original Issue: July 13, 2012 ATA System: 5313 SUBJECT: FUSELAGE - Section 48 - Body Station 2598 Bulkhead - Horizontal Stabilizer Hinge Support Frame Cracking - Modification and Repair Export of this technology is controlled under the United States Export Administration Regulations (EAR) (15 CFR 730-774). An export license may be required before it is used for development, production or use by foreign persons from specific countries. The controller of this data has the individual responsibility to abide by all export laws. 9E991ECCN: BOEING PROPRIETARY, CONFIDENTIAL, AND/OR TRADE SECRET Copyright © 2012 The Boeing Company Unpublished Work - All Rights Reserved Boeing claims copyright in each page of this document only to the extent that the page contains copyrightable subject matter. Boeing also claims copyright in this document as a compilation and/or collective work. This document includes proprietary information owned by The Boeing Company and/or one or more third parties. Treatment of the document and the information it contains is governed by contract with Boeing. For more information, contact The Boeing Company, P.O. Box 3707, Seattle, Washington 98124. Boeing, the Boeing signature, the Boeing symbol, 707, 717, 727, 737, 747, 757, 767, 777, 787, Dreamliner, BBJ, DC-8, DC-9, DC-10, KC-10, KDC-10, MD-10, MD-11, MD-80, MD-88, MD-90, P-8A, Poseidon and the Boeing livery are all trademarks owned by The Boeing Company; and no trademark license is granted in connection with this document unless provided in writing by Boeing. BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 13, 2012 747-53A2837 1 of 250 2.0 ### Page 2 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 13, 2012 747-53A2837 2 of 250 BOEING SERVICE BULLETIN 747-53A2837 ALERTALERT BLANK PAGE ### Page 3 Table of Contents Summary ...................................................... 7 1. PLANNING INFORMATION ........................................ 1 1 A. Effectivity ............................................... 1 1 1. Airplanes ............................................ 1 1 2. Spares Affected ........................................ 2 1 B. Concurrent Requirements ...................................... 2 1 C. Reason ................................................ 2 2 D. Description .............................................. 2 2 E. Compliance .............................................. 2 4 F. Approval ............................................... 3 5 G. Manpower .............................................. 3 6 H. Weight and Balance Changes .................................... 3 7 I. Electrical Load Data ......................................... 3 7 J. References .............................................. 3 7 1. Existing Data .......................................... 3 7 2. Data supplied with this Service Bulletin ............................ 3 7 3. Installation Drawings Used in the Preparation of this Service Bulletin ............ 3 8 K. Publications Affected ........................................ 3 8 L. Interchangeability and Intermixability of Parts ........................... 3 9 2. MATERIAL INFORMATION ........................................ 4 1 A. Material - Price and Availability ................................... 4 1 B. Industry Support Information .................................... 4 1 C. Parts Necessary For Each Airplane ................................. 4 1 1. Kits/Parts ............................................ 4 1 2. Parts and Materials Supplied by the Operator ........................ 6 0 3. Parts Modified and Reidentified ................................ 6 0 4. Parts Removed and Not Replaced .............................. 6 0 D. Parts Necessary to Change Spares ................................. 6 0 E. Special Tooling - Price and Availability ............................... 6 0 F. Special Tooling Necessary to do this Service Bulletin ....................... 6 0 3. ACCOMPLISHMENT INSTRUCTIONS .................................. 6 1 A. GENERAL INFORMATION ..................................... 6 1 B. WORK INSTRUCTIONS ....................................... 6 2 FIGURE 1: ACCESS FOR MODIFICATION OF THE LEFT SIDE OF THE STA 2598 BULKHEAD . . 72 FIGURE 2: ACCESS FOR MODIFICATION OF THE RIGHT SIDE OF THE STA 2598 BULKHEAD . 74 FIGURE 3: REMOVAL OF EXISTING MODIFICATION - LEFT SIDE [Group 1-7, Configuration 1] . . 76 FIGURE 4: REMOVAL OF EXISTING MODIFICATION - RIGHT SIDE [Group 1, 4, 6, Configuration 1] . 78 FIGURE 5: REMOVAL OF EXISTING MODIFICATION - RIGHT SIDE [Group 2, Configuration 1] . . . 80 FIGURE 6: REMOVAL OF EXISTING MODIFICATION - RIGHT SIDE [Group 3, 5, 7, Configuration 1] . 82 FIGURE 7: LEFT SIDE MODIFICATION ON PREVIOUSLY MODIFIED AIRPLANES [Group 1-3, 7, Configuration 1] ......................................... 8 4 FIGURE 8: RIGHT SIDE MODIFICATION ON PREVIOUSLY MODIFIED AIRPLANES [Group 1, Configuration 1 ] ................................................ 8 9 FIGURE 9: RIGHT SIDE MODIFICATION ON PREVIOUSLY MODIFIED AIRPLANES [Group 2, Configuration 1 ] ................................................ 9 5 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 13, 2012 747-53A2837 3 of 250 BOEING SERVICE BULLETIN 747-53A2837 ALERTALERT ### Page 4 FIGURE 10: RIGHT SIDE MODIFICATION ON PREVIOUSLY MODIFIED AIRPLANES [Group 3, 7, Configuration 1] ........................................ 1 0 1 FIGURE 11: EXISTING PARTS REMOVAL - LEFT SIDE [Group 4-6, Configuration 1] ......... 1 0 7 FIGURE 12: LEFT SIDE MODIFICATION [Group 4-6, Configuration 1] ................. 1 1 0 FIGURE 13: EXISTING PARTS REMOVAL - RIGHT SIDE [Group 4-6, Configuration 1] ........ 1 1 5 FIGURE 14: RIGHT SIDE MODIFICATION [Group 4, 6, Configuration 1] ................ 1 1 7 FIGURE 15: RIGHT SIDE MODIFICATION [Group 5, Configuration 1] ................. 1 2 2 FIGURE 16: EXISTING PARTS REMOVAL - LEFT SIDE [Group 1-3, 7, Configuration 2] ....... 1 2 8 FIGURE 17: LEFT SIDE MODIFICATION [Group 1-3, 7, Configuration 2] ................ 1 3 0 FIGURE 18: EXISTING PARTS REMOVAL - RIGHT SIDE [Group 1, Configuration 2] ......... 1 3 5 FIGURE 19: RIGHT SIDE MODIFICATION [Group 1, Configuration 2] ................. 1 3 7 FIGURE 20: EXISTING PARTS REMOVAL - RIGHT SIDE [Group 2, Configuration 2] ......... 1 4 3 FIGURE 21: RIGHT SIDE MODIFICATION [Group 2, Configuration 2] ................. 1 4 5 FIGURE 22: EXISTING PARTS REMOVAL - RIGHT SIDE [Group 3, 7, Configuration 2] ........ 1 5 1 FIGURE 23: RIGHT SIDE MODIFICATION [Group 3, 7, Configuration 2] ................ 1 5 3 FIGURE 24: EXISTING PARTS REMOVAL - LEFT SIDE [Group 4-6, Configuration 2] ......... 1 5 9 FIGURE 25: LEFT SIDE MODIFICATION [Group 4-6, Configuration 2] ................. 1 6 1 FIGURE 26: EXISTING PARTS REMOVAL - RIGHT SIDE [Group 4, 6, Configuration 2] ........ 1 6 6 FIGURE 27: RIGHT SIDE MODIFICATION [Group 4, 6, Configuration 2] ................ 1 6 8 FIGURE 28: EXISTING PARTS REMOVAL - RIGHT SIDE [Group 5, Configuration 2] ......... 1 7 3 FIGURE 29: RIGHT SIDE MODIFICATION [Group 5, Configuration 2] ................. 1 7 5 FIGURE 30: MODIFICATION FASTENER DIFFERENCES IF A PREVIOUSLY ACCOMPLISHED LOCAL WEB REPAIR OR INTERIM MODIFICATION EXISTS AT THE UPPER CORNER OF THE STA 2598 BULKHEAD ....................................... 1 8 0 FIGURE 31: MODIFICATION FASTENER DIFFERENCES IF PREVIOUSLY ACCOMPLISHED LOCAL WEB REPAIR OR INTERIM MODIFICATION AND CHORD REPAIR EXISTS AT THE UPPER CORNER OF THE STA 2598 BULKHEAD [Group 1-7, Configuration 2] .......... 1 8 4 FIGURE 32: RESTORATION AFTER MODIFICATION OF THE LEFT SIDE OF THE STA 2598 BULKHEAD ................................................. 1 8 8 FIGURE 33: RESTORATION AFTER MODIFICATION OF THE RIGHT SIDE OF THE STA 2598 BULKHEAD ................................................. 1 9 1 FIGURE 34: WEB TRIM AND FILLER FABRICATION AT THE UPPER LEFT AND RIGHT CORNERS OF THE STA 2598 BULKHEAD [Group 1-3, 7] ......................... 1 9 4 FIGURE 35: WEB TRIM AND FILLER FABRICATION AT THE LOWER LEFT CORNER OF THE STA 2598 BULKHEAD .......................................... 1 9 8 FIGURE 36: WEB TRIM AND FILLER FABRICATION AT THE UPPER LEFT AND RIGHT CORNERS OF THE STA 2598 BULKHEAD [Group 4-6] ........................... 2 0 1 FIGURE 37: MODIFICATION OF AN EXISTING REPAIR AT THE LOWER LEFT CORNER OF THE STA 2598 BULKHEAD [Group 1-5, 7, Configuration 1] ...................... 2 0 5 FIGURE 38: MODIFICATION OF AN EXISTING REPAIR AT THE LOWER LEFT CORNER OF THE STA 2598 BULKHEAD [Group 6, Configuration 1] ........................ 2 0 9 FIGURE 39: POST-MODIFICATION INSPECTION - SUPPORT FRAME AND ACCESS CUT-OUT DETAILED INSPECTION ......................................... 2 1 3 FIGURE 40: POST-MODIFICATION INSPECTION - LOWER FLOOR SUPPORT CHORD SURFACE HFEC INSPECTION ......................................... 2 1 5 FIGURE 41: POST-MODIFICATION INSPECTION - OUTER CHORD LFEC INSPECTION ...... 2 2 0 FIGURE 42: POST-MODIFICATION INSPECTION - SUPPORT FRAME OUTER CHORD AND FRAME SUPPORT FITTING INSPECTION ............................. 2 2 4 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 13, 2012 747-53A2837 4 of 250 BOEING SERVICE BULLETIN 747-53A2837 ALERTALERT ### Page 5 FIGURE 43: POST-MODIFICATION INSPECTION - HINGE SUPPORT OPEN-HOLE HFEC INSPECTION ................................................. 2 2 6 FIGURE 44: POST-MODIFICATION INSPECTION - SUPPORT FRAME INSPECTIONS [Group 1-6] . 232 FIGURE 45: POST-MODIFICATION INSPECTION - SUPPORT FRAME INSPECTIONS ....... 2 3 5 FIGURE 46: POST-MODIFICATION INSPECTION - SUPPORT FRAME INSPECTIONS [Group 7] . . 239 FIGURE 47: POST-MODIFICATION INSPECTION - SUPPORT FRAME INSPECTIONS [Group 7] . . 243 APPENDIX A: ................................................. 2 4 6 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 13, 2012 747-53A2837 5 of 250 BOEING SERVICE BULLETIN 747-53A2837 ALERTALERT ### Page 6 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 13, 2012 747-53A2837 6 of 250 BOEING SERVICE BULLETIN 747-53A2837 ALERTALERT BLANK PAGE ### Page 7 Commercial Airplanes 747 Service Bulletin ALERT SummaryNumber: 747-53A2837Original Issue: July 13, 2012 ATA System: 5313 SUBJECT: FUSELAGE - Section 48 - Body Station 2598 Bulkhead - Horizontal Stabilizer Hinge Support Frame Cracking - Modification 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 This service bulletin gives instruction for a modification to the bulkhead at Body Station 2598. This modification makes the bulkhead more resistant to fatigue cracks in the areas that must be inspected to satisfy requirements given in the FAA Airworthiness Directives and Boeing service bulletins identified below. This modification can be done to address safety issues related to Airworthiness Directive AD 2010-14-07 and Service Bulletins 747-53A2427, 747-53A2449, 747-53A2467 and 747-53A2473. However, after this modification is done inspections of the Body Station 2598 diagonal braces, bulkhead outer chord, and diagonal brace fittings and flanges continue in accordance with 747-53A2467. NoteFAA Airworthiness DirectiveBoeing Service Bulletin (a)AD 2010-14-07747-53A2427 (a)AD 2010-14-07747-53A2449 (b)AD 2010-14-07747-53A2467 (c)AD 2010-14-07747-53A2473 (a) All inspection requirements terminated - no more work necessary after this modification. (b) Inspection of the support frame aft inner chord in accordance with 747-53A2467 is not necessary after the modification; however inspection of the upper aft outer chords and the diagonal brace attachment fittings, flanges and rods in accordance with 747-53A2467 is necessary after this modification. (c) All inspection requirements terminated - no more Service Bulletin 747-53A2473 work is necessary after this modification. Post-modification inspections in accordance with this service bulletin are required. This table is provided to operators for planning purposes only. Refer to the applicable sections for more information. BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 13, 2012 747-53A2837 7 of 250 ### Page 8 ReferenceAffectedPlanning Data Paragraph 1.A.2., Spares AffectedNoSpares Affected Paragraph 1.E., ComplianceYesAD 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 Material Paragraph 2.F., Special Tooling Necessary to do this Service Bulletin YesSpecial Tooling Required Boeing Service Related Problem (SRP) 747-SRP-53-0343 is related to this service bulletin. ACTION (PRR 85901-103RS) Externally support the horizontal stabilizer to remove the load on the hinge pins. Get access to the STA 2598 bulkhead. If a modification in accordance with Boeing Service Bulletin 747-53A2473 was previously installed, remove that modification. If repairs were previously installed in accordance with Boeing Service Bulletin 747-53A2427 or the Structural Repair Manual, remove the repair parts. Remove existing parts and install a reinforcing modification in accordance with this service bulletin. EFFECTIVITY 747-100, 747-100B, 747-100B SUD, 747-200B, 747-200C, 747-200F, 747-300, 747-400, 747-400D, 747-400F, 747SP, and 747SR Airplanes. Refer to Paragraph 1.A.1., Airplanes, for the list of affected airplanes. COMPLIANCE Refer to Paragraph 1.E., Compliance. INDUSTRY SUPPORT INFORMATION Boeing warranty remedies are not available for the configuration changes or repair procedures given in this service bulletin. MANPOWER Refer to Paragraph 1.G., Manpower. MATERIAL INFORMATION Boeing Supplied Kits. BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 13, 2012 747-53A2837 8 of 250 BOEING SERVICE BULLETIN 747-53A2837 ALERTALERT ### Page 9 (OCR) BOEING SERVICE BULLETIN 747-53A2837 ALERT ALERT Refer to Paragraph 2.A., Material - Price and Availability. STA 2598 STA 2598 REINFORCE THE LEFT AND RIGHT SIDES OF THE STA 2598 BULKHEAD 2049779 Original Issue: July 13, 2012 BOEING PROPRIETARY - 747-53A2837 Copyright © Unpublished Work - See page 1 for details. 9 of 250 ### Page 10 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 13, 2012 747-53A2837 10 of 250 BOEING SERVICE BULLETIN 747-53A2837 ALERTALERT BLANK PAGE ### Page 11 Commercial Airplanes 747 Service Bulletin ALERT Number: 747-53A2837 Original Issue: July 13, 2012 ATA System: 5313 SUBJECT: FUSELAGE - Section 48 - Body Station 2598 Bulkhead - Horizontal Stabilizer Hinge Support Frame Cracking - Modification 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 Refer to Service Bulletin Index Document D6-30300 Part 3 for Airplane Variable Number, Line Number, and Serial Number data. This service bulletin is for the airplanes shown below. Refer to PRR 85901-103RS for data about this change. DESCRIPTIONCONFIGURATIONGROUP All 747 airplanes through line number 695, except Group 2, Group 3 and Group 7 airplanes. -1 Previously modified in accordance with SB 747-53A2473.1 Not previously modified in accordance with SB 747-53A2473.2 Certain 747 airplanes line number 46 through line number 380 with a variable fastener installation at the lower right inboard corner of the STA 2598 bulkhead, between RBL 30 and RBL 35. -2 Previously modified in accordance with SB 747-53A2473.1 Not previously modified in accordance with SB 747-53A2473.2 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 13, 2012 747-53A2837 11 of 250 ### Page 12 DESCRIPTIONCONFIGURATIONGROUP Certain 747 airplanes line number 116 through line number 695, except 747SP airplanes (Group 7), with a variable fastener installation, different than Group 2, at the lower right inboard corner of the STA 2598 bulkhead, between RBL 30 and RBL 35. -3 Previously modified in accordance with SB 747-53A2473.1 Not previously modified in accordance with SB 747-53A2473.2 747 airplanes line number 696 - 1101, except Group 5 airplanes and 747 Large Cargo Freighter airplanes. -4 Previously modified in accordance with SB 747-53A2473.1 Not previously modified in accordance with SB 747-53A2473.2 Certain 747 airplanes line number 697 through line number 886, with a variable fastener installation, different than Group 4, at the lower right inboard corner of the STA 2598 bulkhead, between RBL 30 and RBL 35. -5 Previously modified in accordance with SB 747-53A2473.1 Not previously modified in accordance with SB 747-53A2473.2 747 airplanes line number 1102 - 1307.-6 Previously modified in accordance with SB 747-53A2473.1 Not previously modified in accordance with SB 747-53A2473.2 All 747SP airplanes.-7 Previously modified in accordance with SB 747-53A2473.1 Not previously modified in accordance with SB 747-53A2473.2 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 1RA001 - RA034 1RA101 - RA115 1RA161 - RA164 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 13, 2012 747-53A2837 12 of 250 BOEING SERVICE BULLETIN 747-53A2837 ALERTALERT ### Page 13 GroupVariable Number 1RA201 - RA203 1RA216 - RA217 1RA245 - RA246 1RA251 - RA266 1RA301 - RA318 1RA351 - RA360 1RA369 - RA373 2RA401 - RA418 1RA501 - RA502 1RA521 - RA527 2RA528 3RA532 - RA539 1RA540 2RA541 - RA546 3RA547 - RA548 1RA551 - RA552 1RA559 - RA561 1RA581 - RA582 1RA585 1RA601 - RA602 1RA631 - RA635 1RA651 - RA652 1RA671 - RA677 1RA701 - RA702 1RA721 - RA731 1RA741 - RA745 3RA749 - RA750 2RA761 - RA762 1RA781 - RA783 3RA784 2RA901 - RA916 1RB001 - RB016 1RB041 - RB044 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 13, 2012 747-53A2837 13 of 250 BOEING SERVICE BULLETIN 747-53A2837 ALERTALERT ### Page 14 GroupVariable Number 1RB071 - RB075 1RB101 - RB102 3RB411 - RB412 5RB413 5RB421 2RB601 - RB607 3RB681 - RB697 3RB711 3RB721 - RB723 3RB741 - RB748 1RD001 - RD004 1RD021 - RD022 1RD041 - RD059 1RD071 - RD072 1RD081 3RD082 - RD083 3RD091 - RD092 1RD101 - RD104 3RD121 - RD127 3RD131 - RD144 3RD166 - RD167 3RD171 - RD172 3RD181 - RD183 3RD201 - RD204 3RD221 - RD227 3RD231 - RD234 5RD235 3RD241 - RD243 3RD251 - RD262 3RD271 - RD272 3RD291 - RD292 3RD301 - RD302 3RD311 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 13, 2012 747-53A2837 14 of 250 BOEING SERVICE BULLETIN 747-53A2837 ALERTALERT ### Page 15 GroupVariable Number 3RD351 - RD358 3RD361 - RD366 3RD381 - RD383 3RD411 - RD414 3RD421 - RD426 3RD431 - RD435 3RD441 - RD442 3RD451 - RD456 3RD461 3RD471 - RD475 1RD513 - RD516 3RD517 - RD519 2RD531 3RD532 - RD533 3RD551 3RD561 3RD571 3RD581 - RD583 3RD591 - RD593 3RD601 - RD607 3RD621 - RD623 3RD641 - RD649 3RD651 - RD659 3RD661 3RD671 3RD681 - RD682 3RD691 - RD692 3RD701 - RD702 3RD721 - RD722 3RD741 - RD742 3RD751 - RD755 3RD761 3RD771 - RD775 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 13, 2012 747-53A2837 15 of 250 BOEING SERVICE BULLETIN 747-53A2837 ALERTALERT ### Page 16 GroupVariable Number 3RD781 - RD783 3RD791 5RD792 3RE001 7RG001 - RG009 7RG091 7RG095 7RG101 - RG104 7RG121 - RG126 7RG141 - RG142 7RG161 - RG164 7RG171 - RG174 7RG191 - RG193 7RG211 - RG213 7RG221 - RG222 7RH101 - RH102 7RH111 - RH112 7RH121 - RH122 1RJ131 - RJ133 3RJ151 - RJ152 3RJ301 - RJ303 3RJ321 5RJ322 3RJ331 - RJ333 6RL401 - RL402 6RL411 - RL419 6RL651 - RL654 6RL751 6RM001 - RM007 6RM010 - RM013 6RM021 - RM024 6RM026 - RM029 6RM036 - RM045 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 13, 2012 747-53A2837 16 of 250 BOEING SERVICE BULLETIN 747-53A2837 ALERTALERT ### Page 17 GroupVariable Number 6RM051 - RM052 6RM071 6RM081 - RM084 6RM091 6RM096 - RM097 6RM116 - RM117 6RM126 - RM132 6RM136 - RM147 6RM156 - RM158 6RM166 - RM177 6RM191 - RM192 6RM231 - RM233 6RM241 - RM246 6RM261 - RM264 6RM316 - RM318 6RM331 - RM333 6RM341 6RM351 - RM355 6RM366 - RM367 6RM801 - RM803 6RM811 - RM813 6RM851 - RM858 6RM861 - RM862 6RM871 - RM876 6RM881 - RM886 6RM891 - RM899 6RM901 - RM905 6RM911 3RR001 - RR005 3RR021 - RR023 5RR024 - RR025 3RR031 1RR201 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 13, 2012 747-53A2837 17 of 250 BOEING SERVICE BULLETIN 747-53A2837 ALERTALERT ### Page 18 GroupVariable Number 3RR202 - RR205 5RR206 3RR221 - RR226 3RR261 - RR267 3RR301 - RR306 5RR307 - RR310 3RR331 - RR332 3RR336 3RR341 - RR345 3RR361 - RR362 3RR421 - RR422 3RR431 - RR432 3RR441 5RR442 5RR451 3RR501 - RR504 3RR521 5RR522 5RR526 3RR531 3RR551 - RR554 5RR555 - RR556 3RR561 5RR566 4RR701 4RR721 - RR722 6RR723 - RR724 4RR746 - RR748 4RR851 - RR855 6RR856 4RR861 6RR862 4RR951 - RR952 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 13, 2012 747-53A2837 18 of 250 BOEING SERVICE BULLETIN 747-53A2837 ALERTALERT ### Page 19 GroupVariable Number 3RS001 - RS002 3RS201 3RS211 - RS212 3RS221 - RS222 3RS231 - RS241 3RS251 - RS259 5RS263 3RS265 - RS268 3RS271 - RS276 3RS291 - RS292 3RS301 - RS305 5RS306 3RS311 - RS320 5RS331 - RS333 3RS341 - RS342 3RS699 3RS701 - RS703 3RS711 - RS713 3RS721 - RS722 5RS731 - RS732 3RS741 - RS743 3RS751 - RS752 3RS761 5RS762 3RS771 5RS781 - RS782 5RS786 4RT001 - RT012 6RT013 - RT014 4RT021 - RT022 4RT031 - RT033 6RT034 - RT035 4RT041 - RT047 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 13, 2012 747-53A2837 19 of 250 BOEING SERVICE BULLETIN 747-53A2837 ALERTALERT ### Page 20 GroupVariable Number 4RT061 4RT071 - RT075 4RT101 - RT103 4RT121 4RT131 - RT135 6RT136 - RT137 4RT151 - RT152 4RT161 - RT168 4RT401 - RT412 4RT431 - RT442 6RT443 - RT447 4RT451 - RT469 4RT471 - RT499 4RT501 - RT535 4RT551 - RT568 4RT571 - RT591 4RT601 - RT624 6RT625 - RT630 4RT633 - RT636 6RT637 - RT640 4RT641 - RT657 4RT671 - RT673 4RT681 - RT682 4RT691 - RT699 4RT701 - RT704 4RT711 - RT717 4RT741 - RT742 4RT744 - RT755 6RT756 - RT757 4RT776 - RT777 4RT781 - RT784 4RT801 6RT802 - RT803 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 13, 2012 747-53A2837 20 of 250 BOEING SERVICE BULLETIN 747-53A2837 ALERTALERT ### Page 21 GroupVariable Number 4RT811 - RT812 6RT813 - RT814 4RT831 - RT837 4RT861 - RT864 4RT877 - RT880 4RT931 - RT932 4RT945 - RT948 6RT949 4RT951 - RT954 6RT955 4RT966 - RT967 4RU001 - RU006 4RU016 6RU017 4RU031 - RU032 4RU051 - RU052 4RU059 - RU062 4RU081 - RU083 6RU101 - RU102 4RU121 - RU125 6RU126 - RU132 4RU801 - RU809 4RU831 - RU841 2. Spares Affected None. B. Concurrent Requirements None. BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 13, 2012 747-53A2837 21 of 250 BOEING SERVICE BULLETIN 747-53A2837 ALERTALERT ### Page 22 C. Reason This service bulletin gives instruction for a modification to the bulkhead at Body Station 2598. This modification makes the bulkhead more resistant to fatigue cracks in the areas that must be inspected to satisfy requirements given in the FAA Airworthiness Directives and Boeing service bulletins identified below. This modification can be done to address safety issues related to Airworthiness Directive AD 2010-14-07 and Service Bulletins 747-53A2427, 747-53A2449, 747-53A2467 and 747-53A2473. However, after this modification is done inspections of the Body Station 2598 diagonal braces, bulkhead outer chord, and diagonal brace fittings and flanges continue in accordance with 747-53A2467. NoteFAA Airworthiness DirectiveBoeing Service Bulletin (a)AD 2010-14-07747-53A2427 (a)AD 2010-14-07747-53A2449 (b)AD 2010-14-07747-53A2467 (c)AD 2010-14-07747-53A2473 (a) All inspection requirements terminated - no more work necessary after this modification. (b) Inspection of the support frame aft inner chord in accordance with 747-53A2467 is not necessary after the modification; however inspection of the upper aft outer chords and the diagonal brace attachment fittings, flanges and rods in accordance with 747-53A2467 is necessary after this modification. (c) All inspection requirements terminated - no more Service Bulletin 747-53A2473 work necessary after this modification. Post-modification inspections in accordance with this service bulletin are required. Boeing Service Related Problem (SRP) 747-SRP-53-0343 is related to this service bulletin. D. Description Externally support the horizontal stabilizer to remove the load on the hinge pins. Get access to the STA 2598 bulkhead. If a modification in accordance with Boeing Service Bulletin 747-53A2473 was previously installed, remove that modification. If repairs were previously installed in accordance with Boeing Service Bulletin 747-53A2427 or the Structural Repair Manual, remove the repair parts. Remove existing parts and install a reinforcing modification in accordance with this service bulletin. NOTE: The modification in this service bulletin is similar to the modification in Boeing Service Bulletin 747-53A2473 Revision 3 or later, except that the profile of the modification doubler installed by this service bulletin is larger. 1. 2. If the damaged area is more than the specified limits, write to Boeing for repair instructions. Give the size and location of the damage. When possible, send sketches and photographs. If the damage includes corrosion, send data on the length, width, and largest depth of clean up. Send to: BOEING COMMERCIAL AIRPLANES GROUP ATTENTION: MANAGER, AIRLINE SUPPORT The work in this service bulletin is done in the maintenance zone(s) given below. BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 13, 2012 747-53A2837 22 of 250 BOEING SERVICE BULLETIN 747-53A2837 ALERTALERT ### Page 23 Group 1: Affected Maintenance Zones ZoneModel 315, 316747-100, 747-200B, 747-200C, 747-200F Group 2: Affected Maintenance Zones ZoneModel 315, 316747-100, 747-200B, 747SR Group 3: Affected Maintenance Zones ZoneModel 315, 316747-100B, 747-100B SUD, 747- 200B, 747-200C, 747-200F, 747-300, 747SR Group 4: Affected Maintenance Zones ZoneModel 315, 316747-400, 747-400D, 747-400F Group 5: Affected Maintenance Zones ZoneModel 315, 316747-200B, 747-200C, 747-200F, 747-300 Group 6: Affected Maintenance Zones ZoneModel 315, 316747-400, 747-400F BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 13, 2012 747-53A2837 23 of 250 BOEING SERVICE BULLETIN 747-53A2837 ALERTALERT ### Page 24 Group 7: Affected Maintenance Zones ZoneModel 315, 316747SP E. Compliance Federal Aviation Administration (FAA) Airworthiness Directives AD 2004-07-22R1 and AD 2010-14-07 are related to this service bulletin. No compliance time is given. Boeing recommends that the modification in this service bulletin be done at the operator's discretion. After the modification has been done, Boeing recommends that inspections be done in accordance with the tables that follow: Compliance Table Index Modification installed in accordance with this service bulletinAirplane See Tables 1, 2, 4, 6 and 10Group 1-6, Configuration 1 See Tables 1, 2, 4, 8 and 11Group 1-6, Configuration 2 See Tables 1, 3, 5, 7, 12 and 14Group 7, Configuration 1 See Tables 1, 3, 5, 9, 13 and 15Group 7, Configuration 1 Table 1: Post-Modification Support Frame and Access Cutout Detailed Inspections Repeat Interval (Not to Exceed) Compliance TimeActionCondition -within 3,000 flight-cycles after installation of the modification. Do a detailed inspection of the STA 2598 bulkhead access hole cut out and the support frame for cracks in accordance with Paragraph 3.B., Work Instructions, PART 5. All airplanes previously modified in accordance with this service bulletin -Before further flightAsk Boeing for repair data and install the repair, and Crack found 3,000 flight-cycles.within 3,000 flight-cycles after the last inspection. Repeat the detailed inspection of the STA 2598 bulkhead access hole cut out and the support frame for cracks in accordance with Paragraph 3.B., Work Instructions, PART 5. 3,000 flight-cycles.within 3,000 flight-cycles after the last inspection. Repeat the detailed inspection of the STA 2598 bulkhead access hole cut out and the support frame for cracks in accordance with Paragraph 3.B., Work Instructions, PART 5. No crack found BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 13, 2012 747-53A2837 24 of 250 BOEING SERVICE BULLETIN 747-53A2837 ALERTALERT ### Page 25 Group 1-6: Table 2: Post-Modification Lower Floor Support Chord and Support Frame Outer Chord Eddy Current Inspections Repeat Interval (Not to Exceed) Compliance TimeActionCondition -Within 20,000 total air- plane cycles, or within 3,000 flight-cycles after installation of the modifi- cation, whichever occurs later. Do eddy current inspections for cracks in accordance with Paragraph 3.B., Work Instructions, PART 5. All airplanes previously modified in accordance with this service bulletin -Before further flightAsk Boeing for repair data and install the repair, and Crack found 1,500 flight-cycles.within 1,500 flight-cycles after the last inspection. Repeat the surface HFEC and LFEC inspections for cracks in accordance with Paragraph 3.B., Work Instruc- tions, PART 5. and 6,000 flight-cycles.within 6,000 flight-cycles after the last inspection. Repeat any open-hole HFEC inspec- tions for cracks done as an alterna- tive to the surface HFEC or LFEC inspections specified in Paragraph 3.B., Work Instructions, PART 5. 1,500 flight-cycles.within 1,500 flight-cycles after the last inspection. Repeat the surface HFEC and LFEC inspections for cracks in accordance with Paragraph 3.B., Work Instruc- tions, PART 5. No crack found 6,000 flight-cycles.within 6,000 flight-cycles after the last inspection. Repeat any open-hole HFEC inspec- tions for cracks done as an alterna- tive to the surface HFEC or LFEC inspections specified in Paragraph 3.B., Work Instructions, PART 5. Group 7: Table 3: Post-Modification Lower Floor Support Chord and Support Frame Outer Chord Eddy Current Inspections Repeat Interval (Not to Exceed) Compliance TimeActionCondition -Within 12,000 total air- plane cycles, or within 1,500 flight-cycles after installation of the modifi- cation, whichever occurs later. Do eddy current inspections for cracks in accordance with Paragraph 3.B., Work Instructions, PART 5. All airplanes previously modified in accordance with this service bulletin BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 13, 2012 747-53A2837 25 of 250 BOEING SERVICE BULLETIN 747-53A2837 ALERTALERT ### Page 26 Group 7: Table 3: Post-Modification Lower Floor Support Chord and Support Frame Outer Chord Eddy Current Inspections Repeat Interval (Not to Exceed) Compliance TimeActionCondition -Before further flightAsk Boeing for repair data and install the repair, and Crack found 1,000 flight-cycles.within 1,000 flight-cycles after the last inspection. Repeat the surface HFEC and LFEC inspections for cracks in accordance with Paragraph 3.B., Work Instruc- tions, PART 5. 4,000 flight-cycles.within 4,000 flight-cycles after the last inspection. Repeat any open-hole HFEC inspec- tions for cracks done as an alterna- tive to the surface HFEC or LFEC inspections specified in Paragraph 3.B., Work Instructions, PART 5. 1,000 flight-cycles.within 1,000 flight-cycles after the last inspection. Repeat the surface HFEC and LFEC inspections for cracks in accordance with Paragraph 3.B., Work Instruc- tions, PART 5. No crack found 4,000 flight-cycles.within 4,000 flight-cycles after the last inspection. Repeat any open-hole HFEC inspec- tions for cracks done as an alterna- tive to the surface HFEC or LFEC inspections specified in Paragraph 3.B., Work Instructions, PART 5. Group 1-6: Table 4: Post-Modification Support Frame Outer Chord and Fitting Eddy Current and Ultrasonic Inspec- tions Repeat Interval (Not to Exceed) Compliance TimeActionCondition -Within 20,000 total air- plane cycles, or within 3,000 flight-cycles after installation of the modifi- cation, whichever occurs later. Do eddy current and ultrasonic in- spections of the STA 2598 bulkhead support frame outer chord for cracks in accordance with Paragraph 3.B., Work Instructions, PART 5. All airplanes previously modified in accordance with this service bulletin BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 13, 2012 747-53A2837 26 of 250 BOEING SERVICE BULLETIN 747-53A2837 ALERTALERT ### Page 27 Group 1-6: Table 4: Post-Modification Support Frame Outer Chord and Fitting Eddy Current and Ultrasonic Inspec- tions Repeat Interval (Not to Exceed) Compliance TimeActionCondition -Before further flightAsk Boeing for repair data and install the repair, and Crack found 3,000 flight-cycles.within 3,000 flight-cycles after the last inspection. Repeat the surface HFEC and ultra- sonic inspections of the STA 2598 bulkhead support frame outer chord for cracks Paragraph 3.B., Work In- structions, PART 5. 6,000 flight-cycleswithin 6,000 flight-cycles after the last inspection. Repeat any open-hole HFEC inspec- tions for cracks specified in Para- graph 3.B., Work Instructions, PART 5. 3,000 flight-cycles.within 3,000 flight-cycles after the last inspection. Repeat the surface HFEC and ultra- sonic inspections of the STA 2598 bulkhead support frame outer chord for cracks in accordance with Para- graph 3.B., Work Instructions, PART 5. No crack found 6,000 flight-cycleswithin 6,000 flight-cycles after the last inspection. Repeat any open-hole HFEC inspec- tions for cracks specified in Para- graph 3.B., Work Instructions, PART 5. Group 7: Table 5: Post-Modification Support Frame Outer Chord and Fitting Eddy Current and Ultrasonic Inspec- tions Repeat Interval (Not to Exceed) Compliance TimeActionCondition -Within 12,000 total air- plane cycles, or within 1,500 flight-cycles after installation of the modifi- cation, whichever occurs later. Do eddy current and ultrasonic in- spections of the STA 2598 bulkhead support frame outer chord for cracks in accordance with Paragraph 3.B., Work Instructions, PART 5. All airplanes previously modified in accordance with this service bulletin BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 13, 2012 747-53A2837 27 of 250 BOEING SERVICE BULLETIN 747-53A2837 ALERTALERT ### Page 28 Group 7: Table 5: Post-Modification Support Frame Outer Chord and Fitting Eddy Current and Ultrasonic Inspec- tions Repeat Interval (Not to Exceed) Compliance TimeActionCondition -Before further flightAsk Boeing for repair data and install the repair, and Crack found 1,500 flight-cycles.within 1,500 flight-cycles after the last inspection. Repeat the surface HFEC and ultra- sonic inspections of the STA 2598 bulkhead support frame outer chord for cracks Paragraph 3.B., Work In- structions, PART 5. 4,000 flight-cycleswithin 4,000 flight-cycles after the last inspection. Repeat any open-hole HFEC inspec- tions for cracks specified in Para- graph 3.B., Work Instructions, PART 5. 1,500 flight-cycles.within 1,500 flight-cycles after the last inspection. Repeat the surface HFEC and ultra- sonic inspections of the STA 2598 bulkhead support frame outer chord for cracks in accordance with Para- graph 3.B., Work Instructions, PART 5. No crack found 4,000 flight-cycleswithin 4,000 flight-cycles after the last inspection. Repeat any open-hole HFEC inspec- tions for cracks specified in Para- graph 3.B., Work Instructions, PART 5. Group 1-6, Configuration 1: Table 6: Post-Modification Hinge Support Inspections Repeat Interval (Not to Exceed) Compliance TimeActionCondition -within 20,000 flight-cycles after installation of the 747-53A2473 modification. Do open-hole High Fre- quency Eddy Current (HFEC) inspections of the hinge support fitting bolt holes for cracks in accor- dance with Paragraph 3.B., Work Instructions, PART 5. All airplanes previously modified in accordance with this service bulletin BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 13, 2012 747-53A2837 28 of 250 BOEING SERVICE BULLETIN 747-53A2837 ALERTALERT ### Page 29 Group 1-6, Configuration 1: Table 6: Post-Modification Hinge Support Inspections Repeat Interval (Not to Exceed) Compliance TimeActionCondition -Before further flightAsk Boeing for repair da- ta and install the repair, and Crack found 6,000 flight-cycles.within 6,000 flight-cycles after the last inspection. Repeat the open-hole High Frequency Eddy Current (HFEC) inspec- tions of the hinge support fitting bolt holes for cracks in accordance with Paragraph 3.B., Work In- structions, PART 5. 6,000 flight-cycles.within 6,000 flight-cycles after the last inspection. Repeat the open-hole High Frequency Eddy Current (HFEC) inspec- tions of the hinge support fitting bolt holes for cracks Paragraph 3.B., Work Instructions, PART 5. No crack found Group 7, Configuration 1: Table 7: Post-Modification Hinge Support Inspections Repeat Interval (Not to Exceed) Compliance TimeActionCondition -within 12,000 flight-cycles after installation of the 747-53A2473 modification. Do open-hole High Fre- quency Eddy Current (HFEC) inspections of the hinge support fitting bolt holes for cracks in accor- dance with Paragraph 3.B., Work Instructions, PART 5. All airplanes previously modified in accordance with this service bulletin BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 13, 2012 747-53A2837 29 of 250 BOEING SERVICE BULLETIN 747-53A2837 ALERTALERT ### Page 30 Group 7, Configuration 1: Table 7: Post-Modification Hinge Support Inspections Repeat Interval (Not to Exceed) Compliance TimeActionCondition -Before further flightAsk Boeing for repair da- ta and install the repair, and Crack found 6,000 flight-cycles.within 6,000 flight-cycles after the last inspection. Repeat the open-hole High Frequency Eddy Current (HFEC) inspec- tions of the hinge support fitting bolt holes for cracks in accordance with Paragraph 3.B., Work In- structions, PART 5. 6,000 flight-cycles.within 6,000 flight-cycles after the last inspection. Repeat the open-hole High Frequency Eddy Current (HFEC) inspec- tions of the hinge support fitting bolt holes for cracks Paragraph 3.B., Work Instructions, PART 5. No crack found Group 1-6, Configuration 2: Table 8: Post-Modification Hinge Support Inspections Repeat Interval (Not to Exceed) Compliance TimeActionCondition -within 20,000 flight-cycles after installation of the modification. Do open-hole High Frequency Eddy Current (HFEC) inspections of the hinge support fitting bolt holes for cracks in accordance with Paragraph 3.B., Work Instructions, PART 5. All airplanes previously modified in accordance with this service bulletin -Before further flightAsk Boeing for repair data and install the repair, and Crack found 6,000 flight-cycles.within 6,000 flight-cycles after the last inspection. Repeat the open-hole High Frequen- cy Eddy Current (HFEC) inspections of the hinge support fitting bolt holes for cracks in accordance with Para- graph 3.B., Work Instructions, PART 5. BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 13, 2012 747-53A2837 30 of 250 BOEING SERVICE BULLETIN 747-53A2837 ALERTALERT ### Page 31 Group 1-6, Configuration 2: Table 8: Post-Modification Hinge Support Inspections Repeat Interval (Not to Exceed) Compliance TimeActionCondition 6,000 flight-cycles.within 6,000 flight-cycles after the last inspection. Repeat the open-hole High Frequen- cy Eddy Current (HFEC) inspections of the hinge support fitting bolt holes for cracks in accordance with Para- graph 3.B., Work Instructions, PART 5. No crack found Group 7, Configuration 2: Table 9: Post-Modification Hinge Support Inspections Repeat Interval (Not to Exceed) Compliance TimeActionCondition -within 12,000 flight-cycles after installation of the modification. Do open-hole High Frequency Eddy Current (HFEC) inspections of the hinge support fitting bolt holes for cracks in accordance with Paragraph 3.B., Work Instructions, PART 5. All airplanes previously modified in accordance with this service bulletin -Before further flightAsk Boeing for repair data and install the repair, and Crack found 6,000 flight-cycles.within 6,000 flight-cycles after the last inspection. Repeat the open-hole High Frequen- cy Eddy Current (HFEC) inspections of the hinge support fitting bolt holes for cracks in accordance with Para- graph 3.B., Work Instructions, PART 5. 6,000 flight-cycles.within 6,000 flight-cycles after the last inspection. Repeat the open-hole High Frequen- cy Eddy Current (HFEC) inspections of the hinge support fitting bolt holes for cracks in accordance with Para- graph 3.B., Work Instructions, PART 5. No crack found Group 1-6, Configuration 1: Table 10: Post-Modification Support Frame Surface HFEC Inspections Repeat Interval (Not to Exceed) Compliance TimeActionCondition -within 20,000 flight-cycles after installation of the 747-53A2473 modification. Do surface HFEC inspec- tions around support frame fasteners for cracks in accordance with Paragraph 3.B., Work In- structions, PART 5. All airplanes previously modified in accordance with this service bulletin BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 13, 2012 747-53A2837 31 of 250 BOEING SERVICE BULLETIN 747-53A2837 ALERTALERT ### Page 32 Group 1-6, Configuration 1: Table 10: Post-Modification Support Frame Surface HFEC Inspections Repeat Interval (Not to Exceed) Compliance TimeActionCondition -Before further flightAsk Boeing for repair da- ta and install the repair, and Crack found 3,000 flight-cycles.within 3,000 flight-cycles after the last inspection. Repeat the surface HFEC inspections around sup- port frame fasteners for cracks in accordance with Paragraph 3.B., Work In- structions, PART 5. 3,000 flight-cycles.within 3,000 flight-cycles after the last inspection. Repeat the surface HFEC inspections around sup- port frame fasteners for cracks in accordance with Paragraph 3.B., Work In- structions, PART 5. No crack found Group 1-6, Configuration 2: Table 11: Post-Modification Support Frame Surface HFEC Inspections Repeat Interval (Not to Exceed) Compliance TimeActionCondition -within 20,000 flight-cycles after installation of the modification. Do surface HFEC inspections around support frame fasteners for cracks in accordance with Paragraph 3.B., Work Instructions, PART 5. All airplanes previously modified in accordance with this service bulletin -Before further flightAsk Boeing for repair data and install the repair, and Crack found 3,000 flight-cycles.within 3,000 flight-cycles after the last inspection. Repeat the surface HFEC inspec- tions around support frame fasteners for cracks in accordance with Para- graph 3.B., Work Instructions, PART 5. 3,000 flight-cycles.within 3,000 flight-cycles after the last inspection. Repeat the surface HFEC inspec- tions around support frame fasteners for cracks in accordance with Para- graph 3.B., Work Instructions, PART 5. No crack found BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 13, 2012 747-53A2837 32 of 250 BOEING SERVICE BULLETIN 747-53A2837 ALERTALERT ### Page 33 Group 7, Configuration 1: Table 12: Post-Modification Support Frame Surface HFEC and Detailed Inspections Repeat Interval (Not to Exceed) Compliance TimeActionCondition -within 12,000 flight-cycles after installation of the 747-53A2473 modification. Do surface HFEC inspec- tions around support frame fasteners for cracks in accordance with Paragraph 3.B., Work In- structions, PART 5. All airplanes previously modified in accordance with this service bulletin -Before further flightAsk Boeing for repair da- ta and install the repair, and Crack found 3,000 flight-cycles.within 3,000 flight-cycles after the last inspection. Repeat the surface HFEC inspections around sup- port frame fasteners for cracks in accordance with Paragraph 3.B., Work In- structions, PART 5. 3,000 flight-cycles.within 3,000 flight-cycles after the last inspection. Repeat the surface HFEC inspections around sup- port frame fasteners for cracks in accordance with Paragraph 3.B., Work In- structions, PART 5. No crack found Group 7, Configuration 2: Table 13: Post-Modification Support Frame Surface HFEC and Detailed Inspections Repeat Interval (Not to Exceed) Compliance TimeActionCondition -within 12,000 flight-cycles after installation of the modification. Do surface HFEC inspections around support frame fasteners for cracks in accordance with Paragraph 3.B., Work Instructions, PART 5. All airplanes previously modified in accordance with this service bulletin -Before further flightAsk Boeing for repair data and install the repair, and Crack found 3,000 flight-cycles.within 3,000 flight-cycles after the last inspection. Repeat the surface HFEC inspec- tions around support frame fasteners for cracks in accordance with Para- graph 3.B., Work Instructions, PART 5. BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 13, 2012 747-53A2837 33 of 250 BOEING SERVICE BULLETIN 747-53A2837 ALERTALERT ### Page 34 Group 7, Configuration 2: Table 13: Post-Modification Support Frame Surface HFEC and Detailed Inspections Repeat Interval (Not to Exceed) Compliance TimeActionCondition 3,000 flight-cycles.within 3,000 flight-cycles after the last inspection. Repeat the surface HFEC inspec- tions around support frame fasteners for cracks in accordance with Para- graph 3.B., Work Instructions, PART 5. No crack found Group 7, Configuration 1: Table 14: Post-Modification Support Frame Eddy Current, Ultrasonic and Detailed Inspections Repeat Interval (Not to Exceed) Compliance TimeActionCondition -within 12,000 flight-cycles after installation of the 747-53A2473 modification. Do eddy current, ultrason- ic and detailed inspec- tions of the support frame for cracks in accordance with Paragraph 3.B., Work Instructions, PART 5. All airplanes previously modified in accordance with this service bulletin -Before further flightAsk Boeing for repair da- ta and install the repair, and Crack found 1,500 flight-cycles.within 1,500 flight-cycles after the last inspection. Repeat the eddy current, ultrasonic and detailed inspections of the support frame for cracks in accor- dance with Paragraph 3.B., Work Instructions, PART 5. 1,500 flight-cycles.within 1,500 flight-cycles after the last inspection. Repeat the eddy current, ultrasonic and detailed inspections of the support frame for cracks in accor- dance with Paragraph 3.B., Work Instructions, PART 5. No crack found BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 13, 2012 747-53A2837 34 of 250 BOEING SERVICE BULLETIN 747-53A2837 ALERTALERT ### Page 35 Group 7, Configuration 2: Table 15: Post-Modification Support Frame Eddy Current, Ultrasonic and Detailed Inspections Repeat Interval (Not to Exceed) Compliance TimeActionCondition -within 12,000 flight-cycles after installation of the modification. Do eddy current, ultrasonic and de- tailed inspections of the support frame for cracks in accordance with Paragraph 3.B., Work Instructions, PART 5. All airplanes previously modified in accordance with this service bulletin -Before further flightAsk Boeing for repair data and install the repair, and Crack found 1,500 flight-cycles.within 1,500 flight-cycles after the last inspection. Repeat the eddy current, ultrasonic and detailed inspections of the sup- port frame for cracks in accordance with Paragraph 3.B., Work Instruc- tions, PART 5. 1,500 flight-cycles.within 1,500 flight-cycles after the last inspection. Repeat the eddy current, ultrasonic and detailed inspections of the sup- port frame for cracks in accordance with Paragraph 3.B., Work Instruc- tions, PART 5. No crack found 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. This service bulletin has been approved by the FAA. In addition, the Manager of the FAA Seattle Aircraft Certification Office also approves the accomplishment of the STA 2598 bulkhead modification and inspection procedures of this service bulletin as an AMOC to the STA 2598 bulkhead inspection and repair requirements of paragraph (i), (j), (k)(1), (m), (n), (o), (p), (q), (r), (s), (t), (u) and (v) of AD 2010-14-07. When this service bulletin specifies contacting Boeing for repair instructions, the repair instructions must be approved by the FAA in accordance with paragraph (x) of AD 2010-14-07. All provisions of AD 2010-14-07 that are not specifically referenced in the above statement remain fully applicable and must be complied with. In addition, the Manager of the FAA Seattle ACO approves the accomplishment of the STA 2598 bulkhead modification and inspection procedures of this service bulletin as an alternative method of compliance (AMOC) to the corresponding inspection and repair requirements of paragraphs (h), (i), and (j) of FAA AD 2004-07-22 R1, for the inspection of Structural Significant Items (SSI) F-49A, F-49B, F-49C, F-49D, F-49E, F-49F, F-49G, F-49H, F-49I and F-49J of Supplemental Structural Inspection BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 13, 2012 747-53A2837 35 of 250 BOEING SERVICE BULLETIN 747-53A2837 ALERTALERT ### Page 36 Document (SSID) D6-35022, Revision G, dated December 2000. This AMOC approval is for the inspection areas, methods, and repeat intervals only. The initial inspection threshold given in AD 2004-07-22 R1, paragraph (i) remains in effect and is not altered by this AMOC approval unless the modification is already accomplished. This AMOC only applies to the areas inspected as given in this service bulletin. When this service bulletin specifies contacting Boeing for repair instructions, the repair instructions must be approved by the FAA in accordance with paragraph (l) of the AD. All provisions of AD 2004-07-22 R1 that are not specifically referenced in this paragraph, including the initial inspection threshold per paragraph (i) of AD 2004-07-22 R1, remain fully applicable and must be complied with. G. Manpower The table below shows an estimate of the task hours necessary to do this modification for each airplane. This estimate is for direct labor only, done by an experienced crew. Adjust the estimate with operator task hour data if necessary. The estimate does not include lost time. These are some examples of lost time:  Time to adjust to the workplace  Time to schedule the work  Time to inspect the work  Time to cure the materials  Time to make the parts  Time to find the tools. Table 1 - Modification Elapsed HoursTask HoursNumber of PersonsTask 4.008.002Prepare the airplane and externally sup- port the horizontal stabilizer 4.008.002Open access to one side of the STA 2598 bulkhead 60.00120.002Change one side of the STA 2598 bulk- head 4.0012.003Install equipment re- moved for access 4.008.002Open access to the other side of the STA 2598 bulkhead 60.00120.002Change the other side of the STA 2598 bulkhead 4.0012.003Install equipment re- moved for access 140.00288.00TOTAL FOR EACH AIRPLANE BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 13, 2012 747-53A2837 36 of 250 BOEING SERVICE BULLETIN 747-53A2837 ALERTALERT ### Page 37 H. Weight and Balance Changes Change in Moment (Pound-Inches) Change in Weight (Pounds)Airplane ++747SP ++All other 747 I. Electrical Load Data Not changed. J. References 1. Existing Data a. Engineering Change Memo PRR 85901-103RS b. Boeing Service Bulletin 747-53A2332, 747-53A2427, 747-53A2449, 747-53A2467, 747-53A2473 c. Boeing Service Letter 747-SL-51-048 d. Boeing Service Related Problem (SRP) 747-SRP-53-0343 e. Federal Aviation Administration (FAA) Airworthiness Directive (AD) 2004-07-22R1, 2004-07-22 R1, 2010-14-07 f. Standard Overhaul Practices Manual (SOPM) 20-41-02, 20-43-03, 20-50-12, 20-50-19 g. 747 Illustrated Tool and Equipment Lists (ITEL) 27-40, 55-10 h. 747 Non-Destructive Testing (NDT) Manual Part 4, 53-10-10, Part 6, 51-00-00, Part 6, 53-10-50, Part 6, 53-30-00 i. 747-100/200/300 Aircraft Maintenance Manual (AMM) 24-22-00, 27-41-02, 29-11-00 j. 747-400 Aircraft Maintenance Manual (AMM) 24-22-00, 27-41-02, 28-17-00, 28-26-00, 29-11-00 2. Data supplied with this Service Bulletin a. Drawings: BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 13, 2012 747-53A2837 37 of 250 BOEING SERVICE BULLETIN 747-53A2837 ALERTALERT ### Page 38 ADCNDCN/REVSheetTitleDrawing No --1Bulkhead Reinforcement STA 2598624U0072 --10 --11 --12 --13 --14 --15 --2 --3 --4 --5 --6 --7 --8 --9 3. Installation Drawings Used in the Preparation of this Service Bulletin None. K. Publications Affected 1. Publications: Chapter-SectionPublication 747 Aircraft Maintenance Manual 747 Corrosion Prevention Manual 747 Structural Repair Manual 747 Weight and Balance Manual Component Maintenance Manual Overhaul Manual 2. Damage Tolerance Based Structural Inspections: Boeing has evaluated the repairs and/or changes in this service bulletin for effects on Fatigue Critical Structure (FCS) and for changes to Damage Tolerance Inspections (DTI) required in the Maintenance Program. This service bulletin affects FCS. DTI requirements for the structure affected are contained in Paragraph 1.E., Compliance of this service bulletin. BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 13, 2012 747-53A2837 38 of 250 BOEING SERVICE BULLETIN 747-53A2837 ALERTALERT ### Page 39 L. Interchangeability and Intermixability of Parts Accomplishment of this service bulletin does not affect interchangeability or intermixability of parts. BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 13, 2012 747-53A2837 39 of 250 BOEING SERVICE BULLETIN 747-53A2837 ALERTALERT ### Page 40 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 13, 2012 747-53A2837 40 of 250 BOEING SERVICE BULLETIN 747-53A2837 ALERTALERT BLANK PAGE ### Page 41 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 $74, 983.005501June 22, 2012Top Kit - Group 1, 2, 3 and 7 015U1890-1 $74, 983.00(a)1June 22, 2012Top Kit - Group 1, 2, 3 and 7 015U1890-2 $74, 983.00(a)--Top Kit - Group 4, 5 and 6 015U1890-3 $74, 983.00(a)1June 22, 2012Top Kit - Group 4, 5 and 6 015U1890-4 $145.00(a)-(a)Fastener Kit - Upper Corner Web Repair 015U1890-47 $376.00(a)-(a)Fastener Kit - Lower Corner Web Repair 015U1890-50 (a) Availability and ROLT data was not available at the time of release of this service bulletin. B. Industry Support Information Boeing warranty remedies are not available for the configuration changes given in this service bulletin. C. Parts Necessary For Each Airplane 1. Kits/Parts To get the kits shown below, refer to Paragraph 2.A., Material - Price and Availability. BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 13, 2012 747-53A2837 41 of 250 BOEING SERVICE BULLETIN 747-53A2837 ALERTALERT ### Page 42 NOTE: One top kit and the items shown in Paragraph 2.C.2., Parts and Materials Supplied by the Operator, are necessary for each airplane. In addition, one 148U0001-50 repair kit may be necessary if a previous local web repair was installed at the lower left corner of the STA 2598 bulkhead. A total of two 148U0001-47 repair kits may be necessary if previous local web repairs were installed at the both the left and right upper corners of the STA 2598 bulkhead. 1. 2. If grip length shown is not available at Boeing, fasteners supplied in kits may be one grip length longer than indicated. 3. If any fastener part numbers listed are not available or have been superseded, substitute fasteners may be supplied in kits. Boeing Document D-590 and Boeing Drawing 012W6100 are used to determine the part numbers used as substitutes. 4. To make installation easier, some Boeing parts are sent in an 'interim' configuration. Boeing will identify these interim configurations with a 'U', 'W' or 'Y' in place of the '-' (dash) in the part number. Interim parts are changed to the 'dash' configuration when installed as given in the Accomplishment Instructions of this service bulletin. Refer to Boeing Drawing 005W0900 "INTERIM PARTS - SPARES" and Boeing Service Letter 747-SL-00-018 for more information. Use Top KitConfigurationGroup 015U1890-11: Service Bulletin 747-53A2473 previously accomplished on both sides of the airplane. 1, 2, 3, and 7 015U1890-22: Service Bulletin 747-53A2473 NOT previously accomplished on either side of the airplane. 015U1890-31: Service Bulletin 747-53A2473 previously accomplished on both sides of the airplane. 4, 5 and 6 015U1890-42: Service Bulletin 747-53A2473 NOT previously accomplished on either side of the airplane. Kit 015U1890 NotesExisting Part Number NameQTYNew Part Number -4-3-2-1 (a)Top Kit - Group 1, 2, 3 and 7 ...-015U1890-1 (b)Top Kit - Group 1, 2, 3 and 7 ..-.015U1890-2 (a)Top Kit - Group 4, 5 and 6 .-..015U1890-3 (b)Top Kit - Group 4, 5 and 6 -...015U1890-4 KIT - LEFT SIDE...1148U0001-17 KIT - RIGHT SIDE...1148U0001-18 KIT - LEFT SIDE.1..148U0001-19 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 13, 2012 747-53A2837 42 of 250 BOEING SERVICE BULLETIN 747-53A2837 ALERTALERT ### Page 43 Kit 015U1890 NotesExisting Part Number NameQTYNew Part Number -4-3-2-1 KIT - RIGHT SIDE.1..148U0001-20 KIT - LEFT SIDE..1.148U0001-21 KIT - RIGHT SIDE..1.148U0001-22 KIT - LEFT SIDE1...148U0001-23 KIT - RIGHT SIDE1...148U0001-24 KIT - RIGHT SIDE1111148U0001-27 (a) Use this Top Kit if the modification shown in Boeing Service Bulletin 747-53A2473 was done at an earlier time. (b) Use this Top Kit if the modification shown in Boeing Service Bulletin 747-53A2473 was not done at an earlier time. Kit 148U0001 NotesExisting Part Number NameQTYNew Part Number -20-19-18-17 (a)KIT - LEFT SIDE...-148U0001-17 (a)KIT - RIGHT SIDE..-.148U0001-18 (a)KIT - LEFT SIDE.-..148U0001-19 (a)KIT - RIGHT SIDE-...148U0001-20 -DOUBLER.1.1148U0011-17 -DOUBLER1.1.148U0011-18 -TRIPLER1111148U0011-21 -STRUCTURAL FILLER # 1 ..11148U0011-22 -FILLER #11111148U0011-23 -FILLER #211..148U0011-24 -FILLER #3.1.1148U0011-25 -FILLER #31.1.148U0011-26 -FILLER #41111148U0011-27 -FILLER #51111148U0011-28 -FILLER #2..11148U0011-29 -UPPER SPACER1111148U0011-30 -LOWER SPACER1111148U0011-31 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 13, 2012 747-53A2837 43 of 250 BOEING SERVICE BULLETIN 747-53A2837 ALERTALERT ### Page 44 Kit 148U0001 NotesExisting Part Number NameQTYNew Part Number -20-19-18-17 -FILLER #71.1.148U0011-32 -FILLER #61.1.148U0011-33 -MACHINED FILLER 1.1.148U0011-34 -AFT INNER CHORD .1.1148U0011-39 -AFT INNER CHORD 1.1.148U0011-40 -SHIM.1.1148U0011-41 -SHIM1.1.148U0011-42 -STRUCTURAL FILLER # 2 ..11148U0011-43 -ANGLE.1..251U2216U2 -ANGLE1...251U2216U3 -FITTING.1.165B02875U27 -FITTING1.1.65B02875U28 -FITTING.1.165B02875U29 -FITTING1.1.65B02875U30 -FITTING.1.165B02875U31 -FITTING1.1.65B02875U32 -FITTING.1.165B02875U33 -FITTING1.1.65B02875U34 -BOLT..66BACB30LT5K14 -BOLT66..BACB30LT5K15 -BOLT.1.1BACB30NM8K16 -BOLT1111BACB30NM8K17 -BOLT1.1.BACB30NM8K20 -BOLT1111BACB30NW6K4Y -BOLT4444BACB30NW6K5Y -BOLT11..BACB30NW6K7X -BOLT1111BACB30NW6K7Y -BOLT.1.1BACB30NW6K8Y BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 13, 2012 747-53A2837 44 of 250 BOEING SERVICE BULLETIN 747-53A2837 ALERTALERT ### Page 45 Kit 148U0001 NotesExisting Part Number NameQTYNew Part Number -20-19-18-17 -BOLT.1.1BACB30NW6K9Y -BOLT1111BACB30NW8K10Y -BOLT1.1.BACB30NW8K11 -BOLT1.1.BACB30NW8K12Y -BOLT.5.5BACB30NW8K7 -BOLT1...BACB30NW8K7Y -BOLT5555BACB30NW8K8 -BOLT5151BACB30NW8K9 -BOLT2222BACB30NX10K10 -BOLT2222BACB30NX10K11X -BOLT.12.12BACB30NX10K12 -BOLT88..BACB30NX10K13Y -BOLT8.8.BACB30NX10K14 -BOLT..11BACB30NX10K14X -BOLT..22BACB30NX10K14Y -BOLT2.2.BACB30NX10K15 -BOLT1.1.BACB30NX10K16 -BOLT1.1.BACB30NX10K17 -BOLT4444BACB30NX10K8 -BOLT2222BACB30NX12K14 -BOLT..11BACB30NX12K14X -BOLT6622BACB30NX12K14Y -BOLT5555BACB30NX12K15 -BOLT1111BACB30NX12K16 -BOLT1111BACB30NX6K10 -BOLT1717BACB30NX6K10X -BOLT918918BACB30NX6K10Y -BOLT.2.2BACB30NX6K11X -BOLT142142BACB30NX6K11Y -BOLT.1.1BACB30NX6K12Y -BOLT1.1.BACB30NX6K14Y BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 13, 2012 747-53A2837 45 of 250 BOEING SERVICE BULLETIN 747-53A2837 ALERTALERT ### Page 46 Kit 148U0001 NotesExisting Part Number NameQTYNew Part Number -20-19-18-17 -BOLT.151432BACB30NX6K2 -BOLT23..BACB30NX6K2X -BOLT..11BACB30NX6K3 -BOLT102099BACB30NX6K4 -BOLT11..BACB30NX6K4X -BOLT413518BACB30NX6K4Y -BOLT2.11BACB30NX6K5 -BOLT33..BACB30NX6K5X -BOLT31443347BACB30NX6K5Y -BOLT661111BACB30NX6K6 -BOLT2016..BACB30NX6K6X -BOLT4151428BACB30NX6K6Y -BOLT..99BACB30NX6K7 -BOLT1618.2BACB30NX6K7X -BOLT12281733BACB30NX6K7Y -BOLT..44BACB30NX6K8 -BOLT11113.BACB30NX6K8X -BOLT18912295BACB30NX6K8Y -BOLT.7.7BACB30NX6K9X -BOLT15351535BACB30NX6K9Y -BOLT1111BACB30NX8K10 -BOLT37313731BACB30NX8K10X -BOLT43364336BACB30NX8K10Y -BOLT9999BACB30NX8K11X -BOLT36313631BACB30NX8K11Y -BOLT11.11.BACB30NX8K12Y -BOLT..22BACB30NX8K13X -BOLT1171915BACB30NX8K13Y -BOLT6666BACB30NX8K14Y -BOLT16.16.BACB30NX8K15Y -BOLT6.6.BACB30NX8K16Y BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 13, 2012 747-53A2837 46 of 250 BOEING SERVICE BULLETIN 747-53A2837 ALERTALERT ### Page 47 Kit 148U0001 NotesExisting Part Number NameQTYNew Part Number -20-19-18-17 -BOLT2.2.BACB30NX8K17Y -BOLT3.3.BACB30NX8K18Y -BOLT2.2.BACB30NX8K19Y -BOLT2.2.BACB30NX8K20Y -BOLT38404949BACB30NX8K3 -BOLT54695469BACB30NX8K4 -BOLT60836083BACB30NX8K5 -BOLT36503650BACB30NX8K5X -BOLT.60.60BACB30NX8K6 -BOLT21212121BACB30NX8K6X -BOLT.2.2BACB30NX8K6Y -BOLT18241824BACB30NX8K7 -BOLT20162016BACB30NX8K7X -BOLT50505050BACB30NX8K8X -BOLT.3.3BACB30NX8K8Y -BOLT4.2.BACB30NX8K9X -BOLT18321832BACB30NX8K9Y -BOLT12121212BACB30US4K14 -BOLT..44BACB30US9K33 -BOLT8844BACB30US9K37 -BOLT6666BACB30UU5K17 -BOLT2222BACB30UU5K19 -BOL8888BACB30UU7K17 -BOLT4444BACB30UU8K17 -BOL..11BACB30YP6K7 -BOLT.1.1BACB30YP8K7 -COLLAR8822BACC30AC10 -COLLAR6622BACC30AC12 -COLLAR116250140279BACC30AC6 -COLLAR163118172127BACC30AC8 -COLLAR20202121BACC30BH10 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 13, 2012 747-53A2837 47 of 250 BOEING SERVICE BULLETIN 747-53A2837 ALERTALERT ### Page 48 Kit 148U0001 NotesExisting Part Number NameQTYNew Part Number -20-19-18-17 -COLLAR8899BACC30BH12 -COLLAR811216095BACC30BH6 -COLLAR351458364469BACC30BH8 -COLLAR..11BACC30BL6 -COLLAR.1.1BACC30BL8 -COLLAR11..BACC30M6 -COLLAR11111111BACC30M8 -COLLAR6868BACC30R6 -COLLAR2121BACC30R8 -FILLER, FLAT1111BACF3F008E083NN -FILLER, FLAT..11BACF3F083D090NN -FILLER, FLAT11..BACF3F083E090NN -FILLER, RECTAN- GULAR 1111BACF3H33LH352HN -FILLER, TAPERED1.1.BACF3T01G34-78 -FILLER3333BACF3T01H10-08 -NUT12121212BACN10HR4CD -NUT8888BACN10HR9CD -NUT4444BACN10JC8CD -NUT14141414BACN10YR5CD -NUT8888BACN10YR7CD -NUT2222BACN11Z8CD -SHIM-LAMINATED1.1.BACS40R010B028F -SHIM, LAMINAT- ED 4444BACS40R012B037F -SHIM - LAMINAT- ED 4444BACS40R012B041F -SHIM, LAMINAT- ED 1111BACS40R012B076F -SHIM, LAMINAT- ED 1111BACS40R012B081F -SHIM, LAMINAT- ED 2222BACS40R012D037F BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 13, 2012 747-53A2837 48 of 250 BOEING SERVICE BULLETIN 747-53A2837 ALERTALERT ### Page 49 Kit 148U0001 NotesExisting Part Number NameQTYNew Part Number -20-19-18-17 -SHIM, LAMINAT- ED 2222BACS40R012D041F -SHIM, LAMINAT- ED 2222BACS40R016B081F -SHIM, LAMINAT- ED ..11BACS40R046A083F -WASHER14141414BACW10BN5AC -WASHER8888BACW10BN7AC -WASHER4444BACW10BN8AC -WASHER12121212BACW10BP4CD -WASHER12121212BACW10BP4DP -WASHER1212BACW10BP8CD -WASHER2222BACW10BP8DP -WASHER8888BACW10BP9CD -WASHER8888BACW10BP9DP -WASHER, SELF- ALIGN 864864BACW10CA104CC -WASHER, SELF- ALIGN .40.40BACW10CA104PV -WASHER, SELF- ALIGN 822822BACW10CA32PV -WASHER, SELF- ALIGNING 7.7.BACW10CA41PV -WASHER, SELF- ALIGN 4.4.BACW10CA42PV -WASHER15.15.BACW10CA5CC -WASHER, SELF- ALIGN 4.4.BACW10CA5PV -WASHER, SELF- ALIGN 1.1.BACW10CA8CC -WASHER, SELF- ALIGN 1.1.BACW10CA8CV -WASHER14141414NAS1149D0563J -WASHER8888NAS1149D0763J -WASHER4444NAS1149D0863J BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 13, 2012 747-53A2837 49 of 250 BOEING SERVICE BULLETIN 747-53A2837 ALERTALERT ### Page 50 Kit 148U0001 NotesExisting Part Number NameQTYNew Part Number -20-19-18-17 (a) There are more parts than are necessary Kit 148U0001 NotesExisting Part Number NameQTYNew Part Number -27-24-23-22-21 (a)KIT - LEFT SIDE....-148U0001-21 (a)KIT - RIGHT SIDE...-.148U0001-22 (a)KIT - LEFT SIDE..-..148U0001-23 (a)KIT - RIGHT SIDE.-...148U0001-24 (a)KIT - RIGHT SIDE-....148U0001-27 DOUBLER..1.1148U0011-19 DOUBLER.1.1.148U0011-20 STRUCTURAL FILLER # 1 ...11148U0011-22 FILLER #1.1111148U0011-23 FILLER #2.11..148U0011-24 FILLER #3..1.1148U0011-25 FILLER #3.1.1.148U0011-26 FILLER #4.1111148U0011-27 FILLER #5.1111148U0011-28 FILLER #2...11148U0011-29 UPPER SPACER.1111148U0011-30 LOWER SPACER.1111148U0011-31 FILLER #7.1.1.148U0011-32 FILLER #6.1.1.148U0011-33 MACHINED FILLER .1.1.148U0011-34 TRIPLER.1111148U0011-35 SPACER #11....148U0011-36 SPACER #21....148U0011-37 SPACER #31....148U0011-38 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 13, 2012 747-53A2837 50 of 250 BOEING SERVICE BULLETIN 747-53A2837 ALERTALERT ### Page 51 Kit 148U0001 NotesExisting Part Number NameQTYNew Part Number -27-24-23-22-21 AFT INNER CHORD ..1.1148U0011-39 AFT INNER CHORD .1.1.148U0011-40 SHIM..1.1148U0011-41 SHIM.1.1.148U0011-42 STRUCTURAL FILLER # 2 ...11148U0011-43 ANGLE..1..251U2216U2 ANGLE.1...251U2216U3 FITTING..1.165B02875U27 FITTING.1.1.65B02875U28 FITTING..1.165B02875U29 FITTING.1.1.65B02875U30 FITTING..1.165B02875U31 FITTING.1.1.65B02875U32 FITTING..1.165B02875U33 FITTING.1.1.65B02875U34 BOLT, 12 PT HEAD ...66BACB30LT5K14 BOLT, 12 PT HEAD .66..BACB30LT5K15 BOLT, HEX HEAD..1.1BACB30NM8K16 BOLT, HEX HEAD.1111BACB30NM8K17 BOLT, HEX HEAD.1.1.BACB30NM8K20 BOLT, 100 DEG HEX DR .1.1.BACB30NW6K11Y BOLT, 100 DEG HEX DR .1.1.BACB30NW6K12X BOLT, 100 DEG HEX DR ..111BACB30NW6K4X BOLT, 100 DEG HEX DR .4444BACB30NW6K5Y BOLT, 100 DEG HEX DR .11..BACB30NW6K7X BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 13, 2012 747-53A2837 51 of 250 BOEING SERVICE BULLETIN 747-53A2837 ALERTALERT ### Page 52 Kit 148U0001 NotesExisting Part Number NameQTYNew Part Number -27-24-23-22-21 BOLT, 100 DEG HEX DR .1717BACB30NW6K7Y BOLT, 100 DEG HEX DR .5656BACB30NW6K8Y BOLT, 100 DEG HEX DR .5252BACB30NW6K9Y BOLT, 100 DEG HEX DR .1111BACB30NW8K10X HEX DRIVE BOLT.2222BACB30NX10K10 BOLT, PROTRUD- ING HD .2222BACB30NX10K11 BOLT, PROTRUD- ING HD ..12.12BACB30NX10K12 BOLT, PROTRUD- ING HD .88..BACB30NX10K13X BOLT, PROTRUD- ING HD .8.91BACB30NX10K14 BOLT, PROTRUD- ING HD ...22BACB30NX10K14X BOLT, PROTRUD- ING HD .2.2.BACB30NX10K15 BOLT, PROTRUD- ING HD .1.1.BACB30NX10K16 BOLT, PROTRUD- ING HD .1.1.BACB30NX10K17 BOLT.3333BACB30NX10K6 BOLT.7777BACB30NX10K7 BOLT PROTRUDE TENSN .4444BACB30NX10K8 BOLT.2233BACB30NX12K14 BOLT, PROTRUD- ING HD .6622BACB30NX12K14X BOLT.5555BACB30NX12K15 BOLT, HEX DRIVE.1111BACB30NX12K16 HEX DRIVE BOLT.1111BACB30NX6K10 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 13, 2012 747-53A2837 52 of 250 BOEING SERVICE BULLETIN 747-53A2837 ALERTALERT ### Page 53 Kit 148U0001 NotesExisting Part Number NameQTYNew Part Number -27-24-23-22-21 BOLT, PROTRUD- ING HD .13171317BACB30NX6K10X BOLT, PROTRUD- ING HD .613613BACB30NX6K10Y BOLT, PROTRUD- ING HD 2146146BACB30NX6K11X BOLT, PROTRUD- ING HD ..1.1BACB30NX6K12X BOLT, PROTRUD- ING HD .1.1.BACB30NX6K14X BOLT, PROTRUD- ING HD ..151432BACB30NX6K2 BOLT, PROTRUD- ING HD .23..BACB30NX6K2X BOLT, PROTRUD- ING HD ...11BACB30NX6K3 BOLT, PROTRUD- ING HD ...44BACB30NX6K3X BOLT, PROTRUD- ING HD ...44BACB30NX6K3Y BOLT, PROTRUD- ING HD .102099BACB30NX6K4 BOLT, PROTRUD- ING HD .11..BACB30NX6K4X BOLT, PROTRUD- ING HD .413518BACB30NX6K4Y BOLT.2.11BACB30NX6K5 BOLT, PROTRUD- ING HD .33..BACB30NX6K5X BOLT, PROTRUD- ING HD .31443347BACB30NX6K5Y BOLT.661212BACB30NX6K6 BOLT, PROTRUD- ING HD .2016..BACB30NX6K6X BOLT, PROTRUD- ING HD .4151324BACB30NX6K6Y HI-LOK...99BACB30NX6K7 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 13, 2012 747-53A2837 53 of 250 BOEING SERVICE BULLETIN 747-53A2837 ALERTALERT ### Page 54 Kit 148U0001 NotesExisting Part Number NameQTYNew Part Number -27-24-23-22-21 BOLT, PROTRUD- ING HD .1619.3BACB30NX6K7X BOLT, PROTRUD- ING HD .12331739BACB30NX6K7Y BOLT, PROTRUD- ING HD ...44BACB30NX6K8 BOLT, PROTRUD- ING HD .1124316BACB30NX6K8X BOLT, PROTRUD- ING HD .29853390BACB30NX6K8Y BOLT, PROTRUD- ING HD .18291829BACB30NX6K9X BOLT, PROTRUD- ING HD ..12.12BACB30NX6K9Y HEX DRIVE BOLT.24242424BACB30NX8K10 BOLT, PROTRUD- ING HD .39363936BACB30NX8K10X BOLT, PROTRUD- ING HD .9999BACB30NX8K11 BOLT, PROTRUD- ING HD .36293629BACB30NX8K11X BOLT, PROTRUD- ING HD .11.11.BACB30NX8K12X BOLT, PROTRUD- ING HD ...22BACB30NX8K13 BOLT, PROTRUD- ING HD .971715BACB30NX8K13X BOLT, PROTRUD- ING HD .8686BACB30NX8K14X BOLT, PROTRUD- ING HD .16.16.BACB30NX8K15X BOLT, PROTRUD- ING HD .6.6.BACB30NX8K16X BOLT, HEX DRIVE22.2.BACB30NX8K17X BOLT, PROTRUD- ING HD 2....BACB30NX8K17Y BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 13, 2012 747-53A2837 54 of 250 BOEING SERVICE BULLETIN 747-53A2837 ALERTALERT ### Page 55 Kit 148U0001 NotesExisting Part Number NameQTYNew Part Number -27-24-23-22-21 BOLT, PROTRUD- ING HD .3.3.BACB30NX8K18X BOLT, PROTRUD- ING HD 22.2.BACB30NX8K19X BOLT, PROTRUD- ING HD 12.2.BACB30NX8K20X BOLT, PROTRUD- ING HD 1....BACB30NX8K20Y BOLT, PROTRUD- ING HD 1....BACB30NX8K21X BOLT, PROTRUD- ING HD 1....BACB30NX8K21Y HI-LOK.38404949BACB30NX8K3 HI-LOK.54695469BACB30NX8K4 HI LOK.109147109147BACB30NX8K5 BOLT, PROTRUD- ING HD .1111BACB30NX8K5Y BOLT.32923292BACB30NX8K6 BOLT, PROTRUD- ING HD ..2.2BACB30NX8K6Y BOLT, HEX DRIVE.47424742BACB30NX8K7 BOLT, PROTRUD- ING HD ..2.2BACB30NX8K7X BOLT.44444444BACB30NX8K8 BOLT, PROTRUD- ING HD ..3.3BACB30NX8K8Y HEX DRIVE BOLT.102102BACB30NX8K9 BOLT, PROTRUD- ING HD .15301530BACB30NX8K9X BOLT, 12 PT HEAD .12121212BACB30US4K14 BOLT, 12 PT HEAD ...44BACB30US9K33 BOLT, 12 PT HEAD .8844BACB30US9K37 BOLT.6666BACB30UU5K17 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 13, 2012 747-53A2837 55 of 250 BOEING SERVICE BULLETIN 747-53A2837 ALERTALERT ### Page 56 Kit 148U0001 NotesExisting Part Number NameQTYNew Part Number -27-24-23-22-21 BOLT, 12 PT HEAD .2222BACB30UU5K19 BOLT, 12 PT HEAD .8888BACB30UU7K17 BOLT.4444BACB30UU8K17 BOLT, 100 DEG HEX DR ...11BACB30YP6K7 COLLAR.88220116252BACC30AC6 COLLAR41616BACC30AC8 COLLAR.42423737BACC30BH10 COLLAR.14141111BACC30BH12 COLLAR2130174115153BACC30BH6 COLLAR6524580546600BACC30BH8 COLLAR...11BACC30BL6 COLLAR.2221BACC30M6 COLLAR.1111BACC30M8 COLLAR.16191619BACC30R6 FILLER, FLAT...11BACF3F083D099NN FILLER, FLAT.11..BACF3F083E099NN FILLER, RECTAN- GULAR .1111BACF3H33LH352HN FILLER, TAPERED.1.1.BACF3T01G34-78 FILLER.8888BACF3T01H10-08 NUT.12121212BACN10HR4CD NUT.8888BACN10HR9CD NUT.4444BACN10JC8CD NUT.14141414BACN10YR5CD NUT.8888BACN10YR7CD NUT.2222BACN11Z8CD RIVET, UNIVER- SAL HD ...88BACR15BB6D5C RIVET, 100 DEG.2222BACR15GF3D4 RIVET, 100 DEG.2222BACR15GF3D5 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 13, 2012 747-53A2837 56 of 250 BOEING SERVICE BULLETIN 747-53A2837 ALERTALERT ### Page 57 Kit 148U0001 NotesExisting Part Number NameQTYNew Part Number -27-24-23-22-21 SHIM-LAMINATED.1.1.BACS40R010B028F SHIM, LAMINAT- ED .4444BACS40R012B037F SHIM - LAMINAT- ED .4444BACS40R012B041F SHIM, LAMINAT- ED .1111BACS40R012B076F SHIM, LAMINAT- ED .1111BACS40R012B081F SHIM, LAMINAT- ED .2222BACS40R012D037F SHIM, LAMINAT- ED .2222BACS40R012D041F SHIM, LAMINAT- ED .2222BACS40R016B081F SHIM, LAMINAT- ED ...11BACS40R055A083F WASHER, COUN- TERSUNK, OVER- SIZE .14141414BACW10BN5AC WASHER, COUN- TERSUNK, OVER- SIZE .8888BACW10BN7AC WASHER, COUN- TERSUNK, OVER- SIZE .4444BACW10BN8AC WASHER.12121212BACW10BP4CD WASHER.12121212BACW10BP4DP WASHER.1212BACW10BP8CD WASHER.2222BACW10BP8DP WASHER.8888BACW10BP9CD WASHER.8888BACW10BP9DP WASHER, SELF- ALIGN .18641864BACW10CA104CC WASHER, SELF- ALIGN .10401040BACW10CA104PV BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 13, 2012 747-53A2837 57 of 250 BOEING SERVICE BULLETIN 747-53A2837 ALERTALERT ### Page 58 Kit 148U0001 NotesExisting Part Number NameQTYNew Part Number -27-24-23-22-21 WASHER, SELF- ALIGN .8.8.BACW10CA31PV WASHER, SELF- ALIGN ..22.22BACW10CA32PV WASHER, SELF- ALIGNING 24.4.BACW10CA41PV WASHER, SELF- ALIGN 2....BACW10CA42PV WASHER48.8.BACW10CA5CC WASHER, SELF- ALIGN .4.4.BACW10CA5PV WASHER, SELF- ALIGN .1.1.BACW10CA8CC WASHER, SELF- ALIGN .1.1.BACW10CA8CV WASHER.14141414NAS1149D0563J WASHER.8888NAS1149D0763J WASHER, PLAIN.4444NAS1149D0863J SCREW4....NAS1801-3-12 (a) There are more parts than are necessary Kit 148U0001 NotesExisting Part Number NameQTYNew Part Number -50-47 (a)FASTENER KIT - UPPER CORNER WEB REPAIR .-148U0001-47 (a)FASTENER KIT - LOWER LEFT CORNER WEB REPAIR -.148U0001-50 -BOLT1.BACB30NW10K8 -BOLT.2BACB30NW6K5X -BOLT.2BACB30NW6K5Y -BOLT1.BACB30NW6K9Y -BOLT61BACB30NW8K7X BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 13, 2012 747-53A2837 58 of 250 BOEING SERVICE BULLETIN 747-53A2837 ALERTALERT ### Page 59 Kit 148U0001 NotesExisting Part Number NameQTYNew Part Number -50-47 -BOLT1.BACB30NW8K9X -BOLT.2BACB30NX10K10X -BOLT.2BACB30NX10K10Y -BOLT3.BACB30NX10K11 -BOLT8.BACB30NX10K12X -BOLT2.BACB30NX10K13 -BOLT.4BACB30NX10K8X -BOLT.4BACB30NX10K8Y -BOLT14.BACB30NX10K9 -BOLT.10BACB30NX6K5 -BOLT.9BACB30NX6K5X -BOLT.9BACB30NX6K5Y -BOLT4.BACB30NX6K6 -BOLT3.BACB30NX6K6Y -BOLT7.BACB30NX6K9Y -BOLT7.BACB30NX8K10 -BOLT.2BACB30NX8K11X -BOLT.1BACB30NX8K11Y -BOLT1.BACB30NX8K12 -BOLT3.BACB30NX8K5Y -BOLT16BACB30NX8K7 -BOLT62BACB30NX8K7X -BOLT10.BACB30NX8K7Y -BOLT51BACB30NX8K8 -BOLT4.BACB30NX8K9 -BOLT.1BACB30YP8K7 -COLLAR.6BACC30AC10 -COLLAR109BACC30AC6 -COLLAR131BACC30AC8 -COLLAR306BACC30BH10 -COLLAR415BACC30BH6 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 13, 2012 747-53A2837 59 of 250 BOEING SERVICE BULLETIN 747-53A2837 ALERTALERT ### Page 60 Kit 148U0001 NotesExisting Part Number NameQTYNew Part Number -50-47 -COLLAR249BACC30BH8 -COLLAR.1BACC30BL8 -COLLAR1.BACC30M10 -COLLAR.2BACC30M6 -COLLAR71BACC30M8 -COLLAR12BACC30R6 (a) There are more parts than are necessary 2. Parts and Materials Supplied by the Operator NotesNameQTYPart Number / Specification (a)Sealant1 quart BMS 5-95, Class B or Class C (a)Primer8 ounces BMS 10-11, Type I (a) Refer to the Qualified Products List at the end of the Boeing Material Specification (BMS) for supplier data. 3. Parts Modified and Reidentified None. 4. Parts Removed and Not Replaced None. D. Parts Necessary to Change Spares None. E. Special Tooling - Price and Availability None. F. Special Tooling Necessary to do this Service Bulletin No special tools or equipment are necessary to do the change in this service bulletin. But, maintenance and overhaul tools in the manuals given in Paragraph 1.J., References, can be necessary. Examine operator tool supply to make sure all necessary tools are available. BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 13, 2012 747-53A2837 60 of 250 BOEING SERVICE BULLETIN 747-53A2837 ALERTALERT The text continues at https://openairdocs.org/service-documents/boeing/747-53a2837/file/6e133c9fc4cf.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.