# Boeing Alert Requirements Bulletin 757-57A0073 RB: Revision 3 - Rights: © The Boeing Company. Filed by the FAA in regulations.gov docket FAA-2023-2395; AD 2024-12-09 incorporates this document by reference. Not covered by OpenAirDocs’ CC0 dedication. - Document: [Boeing Alert Requirements Bulletin 757-57A0073 RB](https://openairdocs.org/service-documents/boeing/757-57a0073-rb.md) - Title as filed: 757-57A0073 RB Rev03-- - Pages: 161 - PDF: https://openairdocs.org/files/sha256/47/e6/47e68ea01e5d6614e58fe1f593390777398f0b2d03e9a6917f24ac63494fdad6 - Page: https://openairdocs.org/service-documents/boeing/757-57a0073-rb/file/47e68ea01e5d ## 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 757 Requirements Bulletin ALERT Number: 757-57A0073 RB Original Issue: July 14, 2017 Revision 3: May 05, 2023 ATA System: 5720 SUBJECT: WINGS - Outer Wing - Upper Skin, Drag Fittings and Diagonal Brace Fastener and Shim Inspections EXPORT CONTROLLED - This technology or software is subject to the U.S. Export Administration Regulations (EAR), (15 C.F.R. Parts 730-774). No authorization from the U.S. Department of Commerce is required for export, re-export, in-country transfer, or access EXCEPT to country group E:1 or E:2 countries/persons per Supp.1 to Part 740 of the EAR. 9E991ECCN: Copyright © 2023 The Boeing Company 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: July 14, 2017 757-57A0073 RBRevision 3: May 05, 2023 1 of 161 4.0 ### Page 2 Export Controlled ECCN: 9E991 See page 1 for details Original Issue: July 14, 2017 757-57A0073 RBRevision 3: May 05, 2023 2 of 161 REQUIREMENTS BULLETIN 757-57A0073 ALERTALERT BLANK PAGE ### Page 3 Table of Contents Revision Transmittal Sheet ............................................ 5 1 . E F F E C T I V I T Y ................................................ 7 A. Airplanes ................................................ 7 B . S p a r e s A f f e c t e d ........................................... 1 0 2. CONCURRENT REQUIREMENTS .................................... 1 0 3 . C O M P L I A N C E ............................................... 1 0 4. APPROVAL ................................................ 6 6 5. ACCOMPLISHMENT INSTRUCTIONS .................................. 6 7 A. General Information ......................................... 6 7 B. Work Instructions ........................................... 6 9 FIGURE 1: LEFT WING - DRAG FITTINGS AND WING UPPER SKIN - LOOSE FASTENER INSPECTION ................................................. 1 0 2 FIGURE 2: RIGHT WING - DRAG FITTINGS AND WING UPPER SKIN - LOOSE FASTENER INSPECTION ................................................. 1 0 4 FIGURE 3: LEFT WING - DRAG FITTINGS AND WING UPPER SKIN - SHIM MIGRATION INSPECTION ................................................. 1 0 6 FIGURE 4: RIGHT WING - DRAG FITTINGS AND WING UPPER SKIN - SHIM MIGRATION INSPECTION ................................................. 1 1 0 FIGURE 5: LEFT WING - DRAG FITTINGS AND WING UPPER SKIN - FASTENER 1-10 OPEN-HOLE HFEC INSPECTION ..................................... 1 1 4 FIGURE 6: RIGHT WING - DRAG FITTINGS AND WING UPPER SKIN - FASTENER 1-10 OPEN-HOLE HFEC INSPECTION ..................................... 1 1 6 FIGURE 7: LEFT WING - DRAG FITTINGS AND WING UPPER SKIN - LOOSE FASTENER 11-18 OPEN-HOLE HFEC INSPECTION .............................. 1 1 8 FIGURE 8: RIGHT WING - DRAG FITTINGS AND WING UPPER SKIN - LOOSE FASTENER 11-18 OPEN-HOLE HFEC INSPECTION .............................. 1 2 0 FIGURE 9: LEFT WING- DIAGONAL BRACE AND DIAGONAL BRACE FITTINGS - GENERAL VISUAL INSPECTION FOR CRACKS ................................. 1 2 2 FIGURE 10: RIGHT WING- DIAGONAL BRACE AND DIAGONAL BRACE FITTINGS - GENERAL VISUAL INSPECTION FOR CRACKS ................................. 1 2 5 FIGURE 11: LEFT WING - WING UPPER SKIN - DETAILED INSPECTION FOR CRACKS ...... 1 2 8 FIGURE 12: RIGHT WING - WING UPPER SKIN - DETAILED INSPECTION FOR CRACKS ..... 1 3 0 FIGURE 13: LEFT WING - DRAG FITTINGS - INBOARD SHIM BOLT TORQUE CHECK [Group 1-9, 12-13] ................................................. 1 3 2 FIGURE 14: RIGHT WING - DRAG FITTINGS - INBOARD SHIM BOLT TORQUE CHECK [Group 1-9, 12-13] ................................................. 1 3 4 FIGURE 15: LEFT WING - DRAG FITTINGS - OUTBOARD SHIM BOLT TORQUE CHECK [Group 1-9, 1 2 - 1 3 ] ............................................. 1 3 6 FIGURE 16: RIGHT WING - DRAG FITTINGS - OUTBOARD SHIM BOLT TORQUE CHECK [Group 1-9, 1 2 - 1 3 ] ............................................. 1 3 8 FIGURE 17: LEFT WING - DRAG FITTINGS - INBOARD SHIM BOLT TORQUE CHECK [Group 10-11] . 140 FIGURE 18: RIGHT WING - DRAG FITTINGS - INBOARD SHIM BOLT TORQUE CHECK [Group 10-11] ................................................. 1 4 2 FIGURE 19: LEFT WING - DRAG FITTINGS - OUTBOARD SHIM BOLT TORQUE CHECK [Group 10-11] ................................................. 1 4 4 FIGURE 20: RIGHT WING - DRAG FITTINGS - OUTBOARD SHIM BOLT TORQUE CHECK [Group 10-11] ................................................. 1 4 6 Export Controlled ECCN: 9E991 See page 1 for details Original Issue: July 14, 2017 757-57A0073 RBRevision 3: May 05, 2023 3 of 161 REQUIREMENTS BULLETIN 757-57A0073 ALERTALERT ### Page 4 FIGURE 21: LEFT WING - DRAG FITTINGS AND WING UPPER SKIN - FASTENER 11-18 OPEN-HOLE HFEC INSPECTION ..................................... 1 4 8 FIGURE 22: RIGHT WING - DRAG FITTINGS AND WING UPPER SKIN - FASTENER 11-18 OPEN-HOLE HFEC INSPECTION ..................................... 1 5 1 FIGURE 23: LEFT WING - WING UPPER SKIN - GENERAL VISUAL INSPECTION FOR EXISTING REPAIRS [Group 1, Configuration 2; Group 2-4; Group 5, Configuration 2; Group 6-11; Group 12-13, Configuration 2] ........................................ 1 5 4 FIGURE 24: RIGHT WING - WING UPPER SKIN - GENERAL VISUAL INSPECTION FOR EXISTING REPAIRS [Group 1, Configuration 2; Group 2-4; Group 5, Configuration 2; Group 6-11; Group 12-13, Configuration 2] .................................... 1 5 6 FIGURE 25: LEFT WING - WING UPPER SKIN - ULTRASONIC INSPECTION AT REPAIR LOCATIONS [Group 1, Configuration 2; Group 2-4; Group 5, Configuration 2; Group 6-8; Group 12-13, Configuration 2] ........................................ 1 5 8 FIGURE 26: RIGHT WING - WING UPPER SKIN - ULTRASONIC INSPECTION AT REPAIR LOCATIONS [Group 1, Configuration 2; Group 2-4; Group 5, Configuration 2; Group 6-8; Group 12-13, Configuration 2] ........................................ 1 6 0 Export Controlled ECCN: 9E991 See page 1 for details Original Issue: July 14, 2017 757-57A0073 RBRevision 3: May 05, 2023 4 of 161 REQUIREMENTS BULLETIN 757-57A0073 ALERTALERT ### Page 5 Commercial Airplanes 757 Requirements Bulletin ALERT Revision Transmittal SheetNumber: 757-57A0073 RBOriginal Issue: July 14, 2017 Revision 3: May 05, 2023 ATA System: 5720 SUBJECT: WINGS - Outer Wing - Upper Skin, Drag Fittings and Diagonal Brace Fastener and Shim Inspections This revision includes all pages of the requirements bulletin. COMPLIANCE INFORMATION RELATED TO THIS REVISION Effects of this Revision on airplanes on which the Original Issue, Revision 1 or Revision 2 of this Service Bulletin was previously done: ActionConditionGroup Repeat open-hole HFEC inspection of fastener holes 1-10 for any crack at the revised times specified in Compliance. Airplanes that did an open-hole HFEC inspec- tion of fastener holes 1-10 for any crack and no crack was found. Group 1 Configuration 2, Group 2-4, Group 12 Configuration 2 Repeat open-hole HFEC inspection of fastener holes 11-18 for any crack at the revised times specified in Compliance. Airplanes that did an open-hole HFEC inspec- tion of fastener holes 11-18 for any crack and no crack was found. Group 1 Configuration 2, Group 2-4, Group 9-10, Group 12 Configuration 2 Do open-hole HFEC inspection of fastener holes 1-18 for any crack. Airplanes that did a General Visual Inspec- tion of fastener location 1-18 for loose fasten- er and no open hole HFEC inspection was done. Group 10-11 Do initial inspection and mainte- nance records check of the wing upper skin looking for existing re- pairs. All airplanes.Group 1 Configuration 2, Group 2-4, Group 5 Configuration 2, Group 6-10, Group 12 Configuration 2, Group 13 Configuration 2 Repeat general visual inspection of the diagonal brace and diagonal brace fittings for any crack at the revised times specified in Compli- ance. Airplanes that did a General Visual Inspec- tion of the diagonal brace and diagonal brace fittings for any crack and no crack was found. Group 2-4, Group 6-8, Group 12 Configuration 2, Group 13 Configuration 2 Airplane Line Numbers 610-735 were moved from Groups 1 and 5 to new Groups 12 and 13. Export Controlled ECCN: 9E991 See page 1 for details Original Issue: July 14, 2017 757-57A0073 RBRevision 3: May 05, 2023 5 of 161 ### Page 6 REASON FOR REVISION This revision is sent to update compliance times for the inspection on the wing upper skin and diagonal brace for drag fittings that are possibly made out of different materials. The new compliance times are necessary to maintain structural integrity. This revision is also sent to add new inspection requirements to inspect for existing repairs and move airplanes from Groups 1 and 5 to new Groups 12 and 13. These sections were changed: – Compliance, updated entry conditions and compliance times, added new compliance tables for looking for existing repairs and new Groups 12 and 13. – Approval, added new AMOC statement. – Work Instructions, updated work instructions applicability, existing tables entry conditions and added new tables to do General Visual Inspection or maintenance records check, open-hole HFEC inspection and Ultrasonic inspection for existing repairs and new Groups 12 and 13. – FIGURE 7-8 and FIGURE13-16, updated applicability. – FIGURE 23-26, added new figures. REVISION HISTORY Service BulletinService BulletinRequirement BulletinRequirement Bulletin 757-57A0073757-57A0073757-57A0073 RB757-57A0073 RB Issue DateIssue Date July 14, 2017Original Issue:July 14, 2017Original Issue: August 01, 2019Revision 1:August 01, 2019Revision 1: March 01, 2021Revision 2:March 01, 2021Revision 2: May 05, 2023Revision 3:May 05, 2023Revision 3: Export Controlled ECCN: 9E991 See page 1 for details Original Issue: July 14, 2017 757-57A0073 RBRevision 3: May 05, 2023 6 of 161 REQUIREMENTS BULLETIN 757-57A0073 ALERTALERT ### Page 7 Commercial Airplanes 757 Requirements Bulletin ALERT Number: 757-57A0073 RB Original Issue: July 14, 2017 Revision 3: May 05, 2023 ATA System: 5720 SUBJECT: WINGS - Outer Wing - Upper Skin, Drag Fittings and Diagonal Brace Fastener and Shim Inspections THIS DOCUMENT 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 DOCUMENT TO THE NEW OPERATOR. IF APPLICABLE SPARES HAVE BEEN SOLD, SEND THIS DOCUMENT TO THE NEW OWNER. THIS IS AN ENHANCED REQUIRED FOR COMPLIANCE DOCUMENT. THE BOEING PROCESSES USED TO CREATE THE SERVICE BULLETIN (SB) AND THE REQUIREMENTS BULLETIN (RB) ENSURE THAT THE INFORMATION BETWEEN "RC START" AND "RC END" IN THE SB ARE IDENTICAL TO THE INFORMATION IN THE SAME SECTIONS (COMPLIANCE, WORK INSTRUCTIONS…) OF THE RB WHICH THE SB REFERS TO AS THE RELATED DOCUMENT. 1. Effectivity A. Airplanes This bulletin is applicable to 757-200, 757-200CB, 757-200PF, 757-300 Airplane(s), line number(s) 1-1050 in 13 Group(s). Where the effectivity is presented with hyphens between line numbers, the airplane applicability means "through" and "inclusive", e.g. line numbers 1-9 means line numbers 1 through 9 inclusive. DESCRIPTIONCONFIGURATIONGROUP 757-200/-200CB/-200PF Airplanes, Line Numbers 1-609 with Rolls-Royce engines and with cold work -1 Airplanes that have not accomplished SB 757-54-0035.1 Airplanes that have accomplished SB 757-54-0035.2 757-200/-200PF Airplanes, Line Numbers 736-802 with Rolls-Royce engines and with cold work. -2 757-200/-200PF Airplanes, Line Numbers 803-1009 with Rolls-Royce engines and without cold work -3 757-200 Airplanes, Line Numbers 1010-1050 with Rolls-Royce engines and without cold work -4 Export Controlled ECCN: 9E991 See page 1 for details Original Issue: July 14, 2017 757-57A0073 RBRevision 3: May 05, 2023 7 of 161 ### Page 8 DESCRIPTIONCONFIGURATIONGROUP 757-200/-200PF Airplanes, Line Numbers 1-609 with Pratt and Whitney engines and with cold work -5 Airplanes that have not accomplished SB 757-54-0034.1 Airplanes that have accomplished SB 757-54-0034.2 757-200 Airplanes, Line Numbers 736-802 with Pratt and Whitney engines and with cold work -6 757-200 Airplanes, Line Numbers 803-1009 with Pratt and Whitney engines and without cold work -7 757-200 Airplanes, Line Numbers 1010-1050 with Pratt and Whitney engines and without cold work -8 757-300 Airplanes, Line Numbers 804-855 with Rolls-Royce engines and shear-head bolts in the drag fitting and without cold work -9 757-300 Airplanes, Line Numbers 906-1043 with Rolls-Royce engines and tension-head bolts in the drag fitting and without cold work -10 757-300 Airplanes, Line Numbers 906-1043 with Pratt and Whitney engines and tension-head bolts in the drag fitting and without cold work -11 757-200/-200PF Airplanes, Line Numbers 610-735 with Rolls-Royce engines and with cold work -12 Airplanes that have not accomplished SB 757-54-0035.1 Airplanes that have accomplished SB 757-54-0035.2 757-200 Airplanes, Line Numbers 610-735 with Pratt and Whitney engines and with cold work -13 Airplanes that have not accomplished SB 757-54-0034.1 Airplanes that have accomplished SB 757-54-0034.2 Airplane Models: 757-200, 757-200CB, 757-200PF, 757-300 GroupVariable Number 5NA001 GroupVariable Number 1NA002 - NA028 GroupVariable Number 1NA191 - NA199 Export Controlled ECCN: 9E991 See page 1 for details Original Issue: July 14, 2017 757-57A0073 RBRevision 3: May 05, 2023 8 of 161 REQUIREMENTS BULLETIN 757-57A0073 ALERTALERT ### Page 9 GroupVariable Number 1NA201 - NA237 12NA238 - NA239 1NA301 - NA305 1NA341 - NA352 1NA391 - NA399 1NA401 - NA408 1NA441 - NA447 5NA501 - NA584 13NA585 - NA586 5NB001 - NB004 1NB021 - NB023 1NB036 - NB041 1NB051 - NB053 1NB061 - NB073 1NB079 1NB131 - NB147 12NB148 12NB161 - NB162 5NB166 - NB168 1NB201 - NB204 12NB221 - NB225 2NB226 - NB228 2NB230 12NB236 1NB239 1NB261 - NB267 1NB291 - NB295 12NB296 - NB299 12NB301 - NB302 1NB311 - NB312 1NB321 - NB331 1NB421 - NB436 12NB437 - NB438 GroupVariable Number 12NB446 1NB451 - NB453 12NB454 1NB501 - NB513 12NB514 - NB523 12NB561 2NB571 2NB581 - NB583 5NC001 - NC033 5NC041 - NC042 5NC051 - NC052 5NC056 - NC057 12NC058 - NC061 2NC062 5NC066 - NC071 13NC072 - NC076 6NC077 - NC084 6NC091 - NC094 13NC151 6NC161 5NC901 - NC935 12NC936 - NC950 5NC951 1NC971 - NC974 1ND001 - ND007 1ND011 - ND059 12ND111 - ND113 1ND161 - ND188 12ND189 - ND199 1ND201 - ND203 1ND221 - ND223 12ND224 - ND225 1ND241 - ND245 GroupVariable Number 12ND246 - ND248 12ND301 - ND317 2ND318 - ND322 2ND401 1ND891 1ND895 5NE001 - NE005 13NE006 - NE007 6NE008 5NE011 - NE088 13NE091 - NE094 5NE141 - NE150 5NE161 - NE177 5NE201 - NE204 5NE301 - NE302 13NE311 - NE325 4NJ001 - NJ004 4NJ031 - NJ032 8NJ551 - NJ555 10NL001 - NL002 10NL006 - NL017 10NL101 - NL109 10NL141 11NL601 - NL616 3NN001 - NN002 3NN051 - NN052 6NP901 - NP902 7NP903 - NP904 12NS601 - NS610 2NS611 - NS616 2NT001 - NT004 3NT005 - NT009 3NT201 - NT202 Export Controlled ECCN: 9E991 See page 1 for details Original Issue: July 14, 2017 757-57A0073 RBRevision 3: May 05, 2023 9 of 161 REQUIREMENTS BULLETIN 757-57A0073 ALERTALERT ### Page 10 GroupVariable Number 2NT231 - NT232 3NT233 - NT234 3NT237 - NT240 3NT242 3NT245 - NT248 2NT281 3NT282 - NT289 6NT341 - NT344 7NT345 - NT346 8NT347 6NT351 7NT352 - NT360 7NT371 - NT373 7NT375 - NT379 2NT381 GroupVariable Number 3NT382 - NT385 4NT386 2NT401 - NT403 3NT404 - NT409 3NT411 - NT412 3NT426 - NT427 3NT431 - NT432 3NT436 - NT438 7NT441 - NT442 3NT446 6NT701 7NT702 - NT730 3NT731 - NT750 2NT751 - NT758 3NT759 - NT769 GroupVariable Number 6NT791 - NT794 7NT795 - NT796 2NT861 3NT862 7NT881 - NT885 3NT901 - NT916 3NT971 - NT984 4NT985 7NU031 - NU035 8NU036 - NU038 9NU701 10NU702 - NU705 9NU721 - NU726 10NU727 - NU728 10NU731 - NU732 B. Spares Affected None. 2. CONCURRENT REQUIREMENTS None. 3. COMPLIANCE Federal Aviation Administration (FAA) Airworthiness Directive AD 2018-16-05 is related to Requirements Bulletin 757-57A0073 RB. The effective date of AD 2018-16-05 is September 10, 2018. Federal Aviation Administration (FAA) Airworthiness Directive AD 2020-21-17 is related to Requirements Bulletin 757-57A0073 RB Revision 1 and supersedes AD 2018-16-05. The effective date of AD 2020-21-17 is January 14, 2021. Federal Aviation Administration (FAA) Airworthiness Directive AD 2022-08-12 is related to Requirements Bulletin 757-57A0073 RB Revision 2 and supersedes AD 2020-21-17. The effective date of AD 2022-08-12 is June 10, 2022. The Federal Aviation Administration (FAA) will possibly release an additional Airworthiness Directive related to Requirements Bulletin 757-57A0073 RB Revision 3. The Airworthiness Directive will make the compliance tasks and times given in Requirements Bulletin 757-57A0073 RB Revision 03 mandatory. Accomplish the required action(s), based on the applicable condition(s) in Table(s) 1 through 20, in accordance with the Accomplishment Instructions. Export Controlled ECCN: 9E991 See page 1 for details Original Issue: July 14, 2017 757-57A0073 RBRevision 3: May 05, 2023 10 of 161 REQUIREMENTS BULLETIN 757-57A0073 ALERTALERT ### Page 11 When more than one OPTION is given for a CONDITION, do only one of the OPTION numbers. When more than one ACTION is given for a CONDITION or an OPTION, do all of the ACTION numbers for that CONDITION or OPTION. The following table shows which compliance tables apply to each Group/Configuration. Group 1, 5, 12-13, configuration 2; Group 2-4; Group 6-8: Table 19 must be done first before doing any other applicable table shown in the compliance summary table. Group 9-11: Table 20 must be done first before doing any other applicable table shown in the compliance summary table. Compliance Summary Table Applicable TablesGroups Table 7, Table 9, Table 10Group 1, Configuration 1: Table 1, Table 3, Table 11, Table 19Group 1, Configuration 2: Table 3, Table 12, Table 18, Table 19Group 2: Table 4, Table 12, Table 18, Table 19Group 3-4: Table 8, Table 9, Table 13Group 5, Configuration 1: Table 1, Table 5, Table 14, Table 19Group 5, Configuration 2: Table 5, Table 15, Table 18, Table 19Group 6: Table 6, Table 15, Table 18, Table 19Group 7-8: Table 1, Table 6, Table 16, Table 20Group 9: Table 2, Table 6, Table 16, Table 20Group 10: Table 2, Table 6, Table 15, Table 20Group 11: Table 7, Table 9, Table 10Group 12, Configuration 1: Table 3, Table 11, Table 17, Table 19Group 12, Configuration 2: Table 8, Table 9, Table 13Group 13, Configuration 1: Table 5, Table 14, Table 17, Table 19Group 13, Configuration 2: Export Controlled ECCN: 9E991 See page 1 for details Original Issue: July 14, 2017 757-57A0073 RBRevision 3: May 05, 2023 11 of 161 REQUIREMENTS BULLETIN 757-57A0073 ALERTALERT ### Page 12 Group 1, 5, Configuration 2; Group 9: Table 1: Inspection for loose fasteners, skin cracking, and shim migration at the upper link drag fittings and for cracks in the diagonal brace and diagonal brace fittings Repeat Interval (Not to Exceed) Compliance Time (Whichever Occurs Later) ActionCondition -Within 2,100 flight cycles af- ter the last gen- eral visual in- spection of the diagonal brace and diagonal brace fittings for any crack was done. Before 6,000 to- tal flight cycles. ACTION 1: Do a general visual inspection of the diagonal brace and diago- nal brace fittings for any crack. Airplanes with no repair found in Condition 21 and the inspections specified in Requirements Bulletin 757- 57A0073 RB Revision 2 have been done. OR Airplanes with no repair found in Condition 26 and the inspections specified in Requirements Bulletin 757- 57A0073 RB Revision 2 have been done. -Within 3,000 flight cycles af- ter the last in- spections for loose fasteners, skin cracks and shim migrations. ACTION 2: Do inspec- tions for loose fasteners, skin cracks, and shim mi- grations. -Within 2,100 flight cycles af- ter the Revision 1 date of Re- quirements Bul- letin 757- 57A0073 RB. Before 6,000 to- tal flight cycles. ACTION 1: Do a general visual inspection of the diagonal brace and diago- nal brace fittings for any crack. Airplanes with no repair found in Condition 21 and the inspections specified in Requirements Bulletin 757- 57A0073 RB Revision 2 have not been done. OR Airplanes with no repair found in Condition 26 and the inspections specified in Requirements Bulletin 757- 57A0073 RB Revision 2 have not been done. -Within 3,000 flight cycles af- ter the Original Issue date of Requirements Bulletin 757- 57A0073 RB. ACTION 2: Do inspec- tions for loose fasteners, skin cracks, and shim mi- grations. -Before further flight.Contact The Boeing Company for repair in- structions and do the re- pair. CONDITION 1: ANY CRACK FOUND IN DIAG- ONAL BRACE OR DIAGO- NAL BRACE FITTINGS. (a) 2,100 flight cycles.-Repeat general visual in- spection of the diagonal brace and diagonal brace fittings for any crack. CONDITION 2: NO CRACK FOUND IN DIAG- ONAL BRACE OR DIAGO- NAL BRACE FITTINGS. (a) Export Controlled ECCN: 9E991 See page 1 for details Original Issue: July 14, 2017 757-57A0073 RBRevision 3: May 05, 2023 12 of 161 REQUIREMENTS BULLETIN 757-57A0073 ALERTALERT ### Page 13 Group 1, 5, Configuration 2; Group 9: Table 1: Inspection for loose fasteners, skin cracking, and shim migration at the upper link drag fittings and for cracks in the diagonal brace and diagonal brace fittings Repeat Interval (Not to Exceed) Compliance Time (Whichever Occurs Later) ActionCondition -Before further flight.CONDITION 3 (ACTION 1): Install the Upper Link and Upper Link Pins if re- moved. CONDITION 3: NO SHIM MIGRATION, NO SKIN CRACK, AND NO LOOSE FASTENER. 3,000 flight cycles.-CONDITION 3 (ACTION 2): Repeat inspections for loose fasteners, skin cracks, and shim migra- tions. -Before further flight.Do open-hole HFEC in- spection of fastener holes 1-10 for any crack. CONDITION 4: ANY LOOSE FASTENER FOUND ON FASTENERS 1-10. (a) -Before further flight.Do open-hole HFEC in- spection on the loose bolt holes for any crack. CONDITION 5: ANY LOOSE FASTENER FOUND ON FASTENERS 11-18. (a) -Before further flight.Contact The Boeing Company for repair in- structions and do the re- pair. CONDITION 6: MAJOR SHIM MIGRATION FOUND. (a) -Before further flight.CONDITION 7 (OPTION 1): Contact The Boeing Company for repair in- structions and do the re- pair. CONDITION 7: ANY CRACK FOUND IN THE DRAG FITTINGS. (a) -Before further flight.CONDITION 7, OPTION 2 (ACTION 1): Replace any cracked drag fitting with a new part. -Before further flight.CONDITION 7, OPTION 2 (ACTION 2): Install the Upper Link and Upper Link Pins if removed. 3,000 flight cycles.-CONDITION 7, OPTION 2 (ACTION 3): Repeat in- spections for loose fasten- ers, skin cracks, and shim migrations. Export Controlled ECCN: 9E991 See page 1 for details Original Issue: July 14, 2017 757-57A0073 RBRevision 3: May 05, 2023 13 of 161 REQUIREMENTS BULLETIN 757-57A0073 ALERTALERT ### Page 14 Group 1, 5, Configuration 2; Group 9: Table 1: Inspection for loose fasteners, skin cracking, and shim migration at the upper link drag fittings and for cracks in the diagonal brace and diagonal brace fittings Repeat Interval (Not to Exceed) Compliance Time (Whichever Occurs Later) ActionCondition -Before further flight.Contact The Boeing Company for repair in- structions and do the re- pair. CONDITION 8: ANY CRACK FOUND IN SKIN. (a) -Before further flight.CONDITION 9 (ACTION 1): Install bolts, washers, and nuts for fastener holes where fasteners were removed. CONDITION 9: NO CRACK FOUND IN SKIN AND DRAG FITTINGS DURING OPEN-HOLE HFEC INSPECTION. (a) -Before further flight.CONDITION 9 (ACTION 2): Install the Upper Link and Upper Link Pins if re- moved. 3,000 flight cycles.-CONDITION 9 (ACTION 3): Repeat inspections for loose fasteners, skin cracks, and shim migra- tions. -Before further flight.Do a torque check of fas- teners on the affected shim(s). CONDITION 10: MINOR SHIM MIGRATION FOUND IN SKIN PANEL SHIM. (a) -Before further flight.CONDITION 10.1 (AC- TION 1): Trim affected shim to the edge of the fitting. Apply chemical conversion coating on the shim and fillet seal the edge of the drag fitting. CONDITION 10.1: ALL BOLTS PASSED THE TORQUE CHECK. -Before further flight.CONDITION 10.1 (AC- TION 2): Install the Upper Link and Upper Link Pins if removed. 3,000 flight cycles.-CONDITION 10.1 (AC- TION 3): Repeat inspec- tions for loose fasteners, skin cracks, and shim mi- grations. Export Controlled ECCN: 9E991 See page 1 for details Original Issue: July 14, 2017 757-57A0073 RBRevision 3: May 05, 2023 14 of 161 REQUIREMENTS BULLETIN 757-57A0073 ALERTALERT ### Page 15 Group 1, 5, Configuration 2; Group 9: Table 1: Inspection for loose fasteners, skin cracking, and shim migration at the upper link drag fittings and for cracks in the diagonal brace and diagonal brace fittings Repeat Interval (Not to Exceed) Compliance Time (Whichever Occurs Later) ActionCondition -Before further flight.Contact The Boeing Company for repair in- structions and do the re- pair. CONDITION 10.2: ANY BOLT FAILED THE TORQUE CHECK. -Before further flight.CONDITION 11 (ACTION 1): Trim affected shim to the edge of the fitting. Apply chemical conver- sion coating on the shim and fillet seal the edge of the drag fitting. CONDITION 11: MINOR SHIM MIGRATION FOUND IN SPAR SHIM. (a) -Before further flight.CONDITION 11 (ACTION 2): Install the Upper Link and Upper Link Pins if re- moved. 3,000 flight cycles.-CONDITION 11 (ACTION 3): Repeat inspections for loose fasteners, skin cracks, and shim migra- tions. (a) More than one CONDITION can be applicable on each airplane. Export Controlled ECCN: 9E991 See page 1 for details Original Issue: July 14, 2017 757-57A0073 RBRevision 3: May 05, 2023 15 of 161 REQUIREMENTS BULLETIN 757-57A0073 ALERTALERT ### Page 16 Group 10-11: Table 2: Inspection for loose fasteners, skin cracking, and shim migration at the upper link drag fittings and for cracks in the diagonal brace and diagonal brace fittings Repeat Interval (Not to Exceed) Compliance Time (Whichever Occurs Later) ActionCondition -Within 2,100 flight cycles af- ter the last gen- eral visual in- spection of the diagonal brace and diagonal brace fittings for any crack was done. Before 6,000 to- tal flight cycles. ACTION 1: Do a general visual inspection of the diagonal brace and diago- nal brace fittings for any crack. Airplanes with no repair found in Condition 26 and the inspections specified in Requirements Bulletin 757- 57A0073 RB Revision 2 have been done. -Within 3,000 flight cycles af- ter the last in- spections for loose fasteners, skin cracks and shim migrations. ACTION 2: Do inspec- tions for loose fasteners, skin cracks, and shim mi- grations. -Within 2,100 flight cycles af- ter the Revision 1 date of Re- quirements Bul- letin 757- 57A0073 RB. Before 6,000 to- tal flight cycles. ACTION 1: Do a general visual inspection of the diagonal brace and diago- nal brace fittings for any crack. Airplanes with no repair found in Condition 26 and the inspections specified in Requirements Bulletin 757- 57A0073 RB Revision 2 have not been done. -Within 3,000 flight cycles af- ter the Original Issue date of Requirements Bulletin 757- 57A0073 RB. ACTION 2: Do inspec- tions for loose fasteners, skin cracks, and shim mi- grations. -Before further flight.Contact The Boeing Company for repair in- structions and do the re- pair. CONDITION 1: ANY CRACK FOUND IN DIAG- ONAL BRACE OR DIAGO- NAL BRACE FITTINGS. (a) 2,100 flight cycles.-Repeat general visual in- spection of the diagonal brace and diagonal brace fittings for any crack. CONDITION 2: NO CRACK FOUND IN DIAG- ONAL BRACE OR DIAGO- NAL BRACE FITTINGS. (a) Export Controlled ECCN: 9E991 See page 1 for details Original Issue: July 14, 2017 757-57A0073 RBRevision 3: May 05, 2023 16 of 161 REQUIREMENTS BULLETIN 757-57A0073 ALERTALERT ### Page 17 Group 10-11: Table 2: Inspection for loose fasteners, skin cracking, and shim migration at the upper link drag fittings and for cracks in the diagonal brace and diagonal brace fittings Repeat Interval (Not to Exceed) Compliance Time (Whichever Occurs Later) ActionCondition -Before further flight.CONDITION 3 (ACTION 1): Install the Upper Link and Upper Link Pins if re- moved. CONDITION 3: NO SHIM MIGRATION, NO SKIN CRACK, AND NO LOOSE FASTENER. 3,000 flight cycles.-CONDITION 3 (ACTION 2): Repeat inspections for loose fasteners, skin cracks, and shim migra- tions. -Before further flight.Do open-hole HFEC in- spection of fastener holes 1-10 for any crack. CONDITION 4: ANY LOOSE FASTENER FOUND ON FASTENERS 1-10. (a) -Before further flight.Do open-hole HFEC in- spection on the loose fastener holes for any crack. CONDITION 5: ANY LOOSE FASTENER FOUND ON FASTENERS 11-18. (a) -Before further flight.Contact The Boeing Company for repair in- structions and do the re- pair. CONDITION 6: MAJOR SHIM MIGRATION FOUND. (a) -Before further flight.CONDITION 7 (OPTION 1): Contact The Boeing Company for repair in- structions and do the re- pair. CONDITION 7: ANY CRACK FOUND IN DRAG FITTINGS. (a) -Before further flight.CONDITION 7, OPTION 2 (ACTION 1): Replace any cracked drag fitting with a new part. -Before further flight.CONDITION 7, OPTION 2 (ACTION 2): Install the Upper Link and Upper Link Pins if removed. 3,000 flight cycles.-CONDITION 7, OPTION 2 (ACTION 3): Repeat in- spections for loose fasten- ers, skin cracks, and shim migrations. Export Controlled ECCN: 9E991 See page 1 for details Original Issue: July 14, 2017 757-57A0073 RBRevision 3: May 05, 2023 17 of 161 REQUIREMENTS BULLETIN 757-57A0073 ALERTALERT ### Page 18 Group 10-11: Table 2: Inspection for loose fasteners, skin cracking, and shim migration at the upper link drag fittings and for cracks in the diagonal brace and diagonal brace fittings Repeat Interval (Not to Exceed) Compliance Time (Whichever Occurs Later) ActionCondition -Before further flight.Contact The Boeing Company for repair in- structions and do the re- pair. CONDITION 8: ANY CRACK FOUND IN SKIN. (a) -Before further flight.CONDITION 9 (ACTION 1): Install bolts, washers, and nuts for fastener holes where fasteners were removed. CONDITION 9: NO CRACK FOUND IN SKIN AND DRAG FITTINGS DURING OPEN-HOLE HFEC INSPECTION. (a) -Before further flight.CONDITION 9 (ACTION 2): Install the Upper Link and Upper Link Pins if re- moved. 3,000 flight cycles.-CONDITION 9 (ACTION 3): Repeat inspections for loose fasteners, skin cracks, and shim migra- tions. -Before further flight.Do a torque check of fas- teners on the affected shim(s). CONDITION 10: MINOR SHIM MIGRATION FOUND IN SKIN PANEL SHIM. (a) -Before further flight.CONDITION 10.1 (AC- TION 1): Trim affected shim to the edge of the fitting. Apply chemical conversion coating on the shim and fillet seal the edge of the drag fitting. CONDITION 10.1: ALL BOLTS PASSED THE TORQUE CHECK. -Before further flight.CONDITION 10.1 (AC- TION 2): Install the Upper Link and Upper Link Pins if removed. 3,000 flight cycles.-CONDITION 10.1 (AC- TION 3): Repeat inspec- tions for loose fasteners, skin cracks, and shim mi- grations. Export Controlled ECCN: 9E991 See page 1 for details Original Issue: July 14, 2017 757-57A0073 RBRevision 3: May 05, 2023 18 of 161 REQUIREMENTS BULLETIN 757-57A0073 ALERTALERT ### Page 19 Group 10-11: Table 2: Inspection for loose fasteners, skin cracking, and shim migration at the upper link drag fittings and for cracks in the diagonal brace and diagonal brace fittings Repeat Interval (Not to Exceed) Compliance Time (Whichever Occurs Later) ActionCondition -Before further flight.Contact The Boeing Company for repair in- structions and do the re- pair. CONDITION 10.2: ANY BOLT FAILED THE TORQUE CHECK. -Before further flight.CONDITION 11 (ACTION 1): Trim affected shim to the edge of the fitting. Apply chemical conver- sion coating on the shim and fillet seal the edge of the drag fitting. CONDITION 11: MINOR SHIM MIGRATION FOUND IN SPAR SHIM. (a) -Before further flight.CONDITION 11 (ACTION 2): Install the Upper Link and Upper Link Pins if re- moved. 3,000 flight cycles.-CONDITION 11 (ACTION 3): Repeat inspections for loose fasteners, skin cracks, and shim migra- tions. (a) More than one CONDITION can be applicable on each airplane. Export Controlled ECCN: 9E991 See page 1 for details Original Issue: July 14, 2017 757-57A0073 RBRevision 3: May 05, 2023 19 of 161 REQUIREMENTS BULLETIN 757-57A0073 ALERTALERT ### Page 20 Group 1, Configuration 2; Group 2; Group 12, Configuration 2: Table 3: Inspect for cracks in the wing skin and drag fittings at the upper link drag fittings (Fastener Locations 1-10) Repeat Interval (Not to Exceed) Compliance Time (Whichever Occurs Later) ActionCondition -Within 6,000 flight cycles af- ter the Revision 3 date of Re- quirements Bul- letin 757- 57A0073 RB or within 12,000 flight cycles af- ter the last open-hole HFEC inspec- tion of fastener holes 1-10 for any crack was done, whichever occurs first. Before 23,000 total flight cy- cles. Do open-hole HFEC in- spection of fastener holes 1-10 for any crack. (a)(b) Airplanes with no repair found in Condition 21 and the inspections specified in Requirements Bulletin 757- 57A0073 RB Revision 2 have been done. -Within 3,000 flight cycles af- ter the Original Issue date of Requirements Bulletin 757- 57A0073 RB. Before 23,000 total flight cy- cles. Do open-hole HFEC in- spection of fastener holes 1-10 for any crack. (a)(b) Airplanes with no repair found in Condition 21 and the inspections specified in Requirements Bulletin 757- 57A0073 RB Revision 2 have not been done. -Before further flight.CONDITION 7 (OPTION 1): Contact The Boeing Company for repair in- structions and do the re- pair. CONDITION 7: ANY CRACK FOUND IN DRAG FITTINGS. (c) -Before further flight.CONDITION 7, OPTION 2 (ACTION 1): Replace any cracked drag fitting with a new part. -Before further flight.CONDITION 7, OPTION 2 (ACTION 2): Install the Upper Link and Upper Link Pins if removed. 6,000 flight cycles.-CONDITION 7, OPTION 2 (ACTION 3): Repeat open-hole HFEC inspec- tion of fastener holes 1- 10 for any crack. (a)(b) Export Controlled ECCN: 9E991 See page 1 for details Original Issue: July 14, 2017 757-57A0073 RBRevision 3: May 05, 2023 20 of 161 REQUIREMENTS BULLETIN 757-57A0073 ALERTALERT ### Page 21 Group 1, Configuration 2; Group 2; Group 12, Configuration 2: Table 3: Inspect for cracks in the wing skin and drag fittings at the upper link drag fittings (Fastener Locations 1-10) Repeat Interval (Not to Exceed) Compliance Time (Whichever Occurs Later) ActionCondition -Before further flight.Contact The Boeing Company for repair in- structions and do the re- pair. CONDITION 8: ANY CRACK FOUND IN SKIN. (c) -Before further flight.CONDITION 9 (ACTION 1): Install bolts, washers, and nuts for fastener holes where fasteners were removed. CONDITION 9: NO CRACK FOUND IN SKIN AND DRAG FITTINGS DURING OPEN-HOLE HFEC INSPECTION. -Before further flight.CONDITION 9 (ACTION 2): Install the Upper Link and Upper Link Pins if re- moved. 6,000 flight cycles.-CONDITION 9 (ACTION 3): Repeat open-hole HFEC inspection of fas- tener holes 1-10 for any crack. (a)(b) (a) Accomplishment of an open-hole HFEC inspection of fastener holes 1-10 as a result of CONDITION 4 meets the requirements of this action. (b) On or after the Revision 1 date of 757-57A0073 RB, when this action occurs at the same time as a loose fastener inspection from Table 1 or Table 17 or Table 18, the loose fastener inspection in Table 1 or Table 17 or Table 18 must be done first. (c) More than one CONDITION can be applicable on each airplane. Export Controlled ECCN: 9E991 See page 1 for details Original Issue: July 14, 2017 757-57A0073 RBRevision 3: May 05, 2023 21 of 161 REQUIREMENTS BULLETIN 757-57A0073 ALERTALERT ### Page 22 Group 3-4: Table 4: Inspect for cracks in the wing skin and drag fittings at the upper link drag fittings (Fastener Locations 1-10) Repeat Interval (Not to Exceed) Compliance Time (Whichever Occurs Later) ActionCondition -Within 6,000 flight cycles af- ter the Revision 3 date of Re- quirements Bul- letin 757- 57A0073 RB or within 12,000 flight cycles af- ter the last open-hole HFEC inspec- tion of fastener holes 1-10 for any crack was done, whichever occurs first. Before 6,000 to- tal flight cycles. Do open-hole HFEC in- spection of fastener holes 1-10 for any crack. (a)(b) Airplanes with no repair found in Condition 21 and the inspections specified in Requirements Bulletin 757- 57A0073 RB Revision 2 have been done. -Within 3,000 flight cycles af- ter the Revision 1 date of Re- quirements Bul- letin 757- 57A0073 RB or within 2,300 flight cycles af- ter the Revision 2 date of Re- quirements Bul- letin 757- 57A0073 RB, whichever oc- curs first. Before 6,000 to- tal flight cycles. Do open-hole HFEC in- spection of fastener holes 1-10 for any crack. (a)(b) Airplanes with no repair found in Condition 21 and the inspections specified in Requirements Bulletin 757- 57A0073 RB Revision 2 have not been done. Export Controlled ECCN: 9E991 See page 1 for details Original Issue: July 14, 2017 757-57A0073 RBRevision 3: May 05, 2023 22 of 161 REQUIREMENTS BULLETIN 757-57A0073 ALERTALERT ### Page 23 Group 3-4: Table 4: Inspect for cracks in the wing skin and drag fittings at the upper link drag fittings (Fastener Locations 1-10) Repeat Interval (Not to Exceed) Compliance Time (Whichever Occurs Later) ActionCondition -Before further flight.CONDITION 7 (OPTION 1): Contact The Boeing Company for repair in- structions and do the re- pair. CONDITION 7: ANY CRACK FOUND IN DRAG FITTINGS. (c) -Before further flight.CONDITION 7, OPTION 2 (ACTION 1): Replace any cracked drag fitting with a new part. -Before further flight.CONDITION 7, OPTION 2 (ACTION 2): Install the Upper Link and Upper Link Pins if removed. 6,000 flight cycles.-CONDITION 7, OPTION 2 (ACTION 3): Repeat open-hole HFEC inspec- tion of fastener holes 1- 10 for any crack. (a)(b) -Before further flight.Contact The Boeing Company for repair in- structions and do the re- pair. CONDITION 8: ANY CRACK FOUND IN SKIN. (c) -Before further flight.CONDITION 9 (ACTION 1): Install bolts, washers, and nuts for fastener holes where fasteners were removed. CONDITION 9: NO CRACK FOUND IN SKIN AND DRAG FITTINGS DURING OPEN-HOLE HFEC INSPECTION. -Before further flight.CONDITION 9 (ACTION 2): Install the Upper Link and Upper Link Pins if re- moved. 6,000 flight cycles.-CONDITION 9 (ACTION 3): Repeat open-hole HFEC inspection of fas- tener holes 1-10 for any crack. (a)(b) (a) Accomplishment of an open-hole HFEC inspection of fastener holes 1-10 as a result of CONDITION 4 meets the requirements of this action. (b) On or after the Revision 1 date of 757-57A0073 RB, when this action occurs at the same time as a loose fastener inspection from Table 18, the loose fastener inspection in Table 18 must be done first. Export Controlled ECCN: 9E991 See page 1 for details Original Issue: July 14, 2017 757-57A0073 RBRevision 3: May 05, 2023 23 of 161 REQUIREMENTS BULLETIN 757-57A0073 ALERTALERT ### Page 24 Group 3-4: Table 4: Inspect for cracks in the wing skin and drag fittings at the upper link drag fittings (Fastener Locations 1-10) Repeat Interval (Not to Exceed) Compliance Time (Whichever Occurs Later) ActionCondition (c) More than one CONDITION can be applicable on each airplane. Group 5, Configuration 2; Group 6; Group 13, Configuration 2: Table 5: Inspect for cracks in the wing skin and drag fittings at the upper link drag fittings (Fastener Locations 1-10) Repeat Interval (Not to Exceed) Compliance Time (Whichever Occurs Later) ActionCondition -Within 6,000 flight cycles af- ter the last open-hole HFEC inspec- tion of fastener holes 1-10 for any crack was done. Before 23,000 total flight cy- cles. Do open-hole HFEC in- spection of fastener holes 1-10 for any crack. (a)(b) Airplanes with no repair found in Condition 21 and the inspections specified in Requirements Bulletin 757- 57A0073 RB Revision 2 have been done. -Within 3,000 flight cycles af- ter the Original Issue date of Requirements Bulletin 757- 57A0073 RB. Before 23,000 total flight cy- cles. Do open-hole HFEC in- spection of fastener holes 1-10 for any crack. (a)(b) Airplanes with no repair found in Condition 21 and the inspections specified in Requirements Bulletin 757- 57A0073 RB Revision 2 have not been done. -Before further flight.CONDITION 7 (OPTION 1): Contact The Boeing Company for repair in- structions and do the re- pair. CONDITION 7: ANY CRACK FOUND IN DRAG FITTINGS. (c) -Before further flight.CONDITION 7, OPTION 2 (ACTION 1): Replace any cracked drag fitting with a new part. -Before further flight.CONDITION 7, OPTION 2 (ACTION 2): Install the Upper Link and Upper Link Pins if removed. 6,000 flight cycles.-CONDITION 7, OPTION 2 (ACTION 3): Repeat open-hole HFEC inspec- tion of fastener holes 1- 10 for any crack. (a)(b) Export Controlled ECCN: 9E991 See page 1 for details Original Issue: July 14, 2017 757-57A0073 RBRevision 3: May 05, 2023 24 of 161 REQUIREMENTS BULLETIN 757-57A0073 ALERTALERT ### Page 25 Group 5, Configuration 2; Group 6; Group 13, Configuration 2: Table 5: Inspect for cracks in the wing skin and drag fittings at the upper link drag fittings (Fastener Locations 1-10) Repeat Interval (Not to Exceed) Compliance Time (Whichever Occurs Later) ActionCondition -Before further flight.Contact The Boeing Company for repair in- structions and do the re- pair. CONDITION 8: ANY CRACK FOUND IN SKIN. (c) -Before further flight.CONDITION 9 (ACTION 1): Install bolts, washers, and nuts for fastener holes where fasteners were removed. CONDITION 9: NO CRACK FOUND IN SKIN AND DRAG FITTINGS DURING OPEN-HOLE HFEC INSPECTION. -Before further flight.CONDITION 9 (ACTION 2): Install the Upper Link and Upper Link Pins if re- moved. 6,000 flight cycles.-CONDITION 9 (ACTION 3): Repeat open-hole HFEC inspection of fas- tener holes 1-10 for any crack. (a)(b) (a) Accomplishment of an open-hole HFEC inspection of fastener holes 1-10 as a result of CONDITION 4 meets the requirements of this action. (b) On or after the Revision 1 date of 757-57A0073 RB, when this action occurs at the same time as a loose fastener inspection from Table 1 or Table 17 or Table 18, the loose fastener inspection in Table 1 or Table 17 or Table 18 must be done first. (c) More than one CONDITION can be applicable on each airplane. Export Controlled ECCN: 9E991 See page 1 for details Original Issue: July 14, 2017 757-57A0073 RBRevision 3: May 05, 2023 25 of 161 REQUIREMENTS BULLETIN 757-57A0073 ALERTALERT ### Page 26 Group 7-11: Table 6: Inspect for cracks in the wing skin and drag fittings at the upper link drag fittings (Fastener Locations 1-10) Repeat Interval (Not to Exceed) Compliance Time (Whichever Occurs Later) ActionCondition -Within 6,000 flight cycles af- ter the last open-hole HFEC inspec- tion of fastener holes 1-10 for any crack was done. Before 6,000 to- tal flight cycles. Do open-hole HFEC in- spection of fastener holes 1-10 for any crack. (a)(b) Airplanes with no repair found in Condition 21 and the inspections specified in Requirements Bulletin 757- 57A0073 RB Revision 2 have been done. OR Airplanes with no repair found in Condition 26 and the inspections specified in Requirements Bulletin 757- 57A0073 RB Revision 2 have been done. -Within 3,000 flight cycles af- ter the Original Issue date of Requirements Bulletin 757- 57A0073 RB. Before 6,000 to- tal flight cycles. Do open-hole HFEC in- spection of fastener holes 1-10 for any crack. (a)(b) Airplanes with no repair found in Condition 21 and the inspections specified in Requirements Bulletin 757- 57A0073 RB Revision 2 have not been done. OR Airplanes with no repair found in Condition 26 and the inspections specified in Requirements Bulletin 757- 57A0073 RB Revision 2 have not been done. Export Controlled ECCN: 9E991 See page 1 for details Original Issue: July 14, 2017 757-57A0073 RBRevision 3: May 05, 2023 26 of 161 REQUIREMENTS BULLETIN 757-57A0073 ALERTALERT ### Page 27 Group 7-11: Table 6: Inspect for cracks in the wing skin and drag fittings at the upper link drag fittings (Fastener Locations 1-10) Repeat Interval (Not to Exceed) Compliance Time (Whichever Occurs Later) ActionCondition -Before further flight.CONDITION 7 (OPTION 1): Contact The Boeing Company for repair in- structions and do the re- pair. CONDITION 7: ANY CRACK FOUND IN DRAG FITTINGS. (c) -Before further flight.CONDITION 7, OPTION 2 (ACTION 1): Replace any cracked drag fitting with a new part. -Before further flight.CONDITION 7, OPTION 2 (ACTION 2): Install the Upper Link and Upper Link Pins if removed. 6,000 flight cycles.-CONDITION 7, OPTION 2 (ACTION 3): Repeat open-hole HFEC inspec- tion of fastener holes 1- 10 for any crack. (a)(b) -Before further flight.Contact The Boeing Company for repair in- structions and do the re- pair. CONDITION 8: ANY CRACK FOUND IN SKIN. (c) -Before further flight.CONDITION 9 (ACTION 1): Install bolts, washers, and nuts for fastener holes where fasteners were removed. CONDITION 9: NO CRACK FOUND IN SKIN AND DRAG FITTINGS DURING OPEN-HOLE HFEC INSPECTION. -Before further flight.CONDITION 9 (ACTION 2): Install the Upper Link and Upper Link Pins if re- moved. 6,000 flight cycles.-CONDITION 9 (ACTION 3): Repeat open-hole HFEC inspection of fas- tener holes 1-10 for any crack. (a)(b) (a) Accomplishment of an open-hole HFEC inspection of fastener holes 1-10 as a result of CONDITION 4 meets the requirements of this action. (b) On or after the Revision 1 date of 757-57A0073 RB, when this action occurs at the same time as a loose fastener inspection from Table 1 or Table 2 or Table 18, the loose fastener inspection in Table 1 or Table 2 or Table 18 must be done first. Export Controlled ECCN: 9E991 See page 1 for details Original Issue: July 14, 2017 757-57A0073 RBRevision 3: May 05, 2023 27 of 161 REQUIREMENTS BULLETIN 757-57A0073 ALERTALERT ### Page 28 Group 7-11: Table 6: Inspect for cracks in the wing skin and drag fittings at the upper link drag fittings (Fastener Locations 1-10) Repeat Interval (Not to Exceed) Compliance Time (Whichever Occurs Later) ActionCondition (c) More than one CONDITION can be applicable on each airplane. Group 1, 12, Configuration 1: Table 7: Inspect for cracks in the wing skin and drag fittings at the upper link drag fittings (Fastener Locations 1-10) Repeat Interval (Not to Exceed) Compliance Time (Whichever Occurs Later) ActionCondition -Within 3,000 flight cycles af- ter the Original Issue date of Requirements Bulletin 757- 57A0073 RB. Before 8,400 to- tal flight cycles. Do open-hole HFEC in- spection of fastener holes 1-10 for any crack. (a)(b) All airplanes. -Before further flight.Contact The Boeing Company for repair in- structions and do the re- pair. CONDITION 7: ANY CRACK FOUND IN DRAG FITTINGS. (c) -Before further flight.Contact The Boeing Company for repair in- structions and do the re- pair. CONDITION 8: ANY CRACK FOUND IN SKIN. (c) -Before further flight.CONDITION 9 (ACTION 1): Install bolts, washers, and nuts for fastener holes where fasteners were removed. CONDITION 9: NO CRACK FOUND IN SKIN AND DRAG FITTINGS DURING OPEN-HOLE HFEC INSPECTION. -Before further flight.CONDITION 9 (ACTION 2): Install the Upper Link and Upper Link Pins if re- moved. 8,400 flight cycles.-CONDITION 9 (ACTION 3): Repeat open-hole HFEC inspection of fas- tener holes 1-10 for any crack. (a)(b) (a) Accomplishment of an open-hole HFEC inspection of fastener holes 1-10 as a result of CONDITION 4 meets the requirements of this action. (b) On or after the Revision 1 date of 757-57A0073 RB, when this action occurs at the same time as a loose fastener inspection from Table 9, the loose fastener inspection in Table 9 must be done first. Export Controlled ECCN: 9E991 See page 1 for details Original Issue: July 14, 2017 757-57A0073 RBRevision 3: May 05, 2023 28 of 161 REQUIREMENTS BULLETIN 757-57A0073 ALERTALERT ### Page 29 Group 1, 12, Configuration 1: Table 7: Inspect for cracks in the wing skin and drag fittings at the upper link drag fittings (Fastener Locations 1-10) Repeat Interval (Not to Exceed) Compliance Time (Whichever Occurs Later) ActionCondition (c) More than one CONDITION can be applicable on each airplane. Group 5, 13, Configuration 1: Table 8: Inspect for cracks in the wing skin and drag fittings at the upper link drag fittings (Fastener Locations 1-10) Repeat Interval (Not to Exceed) Compliance Time (Whichever Occurs Later) ActionCondition -Within 3,000 flight cycles af- ter the Original Issue date of Requirements Bulletin 757- 57A0073 RB. Before 5,500 to- tal flight cycles. Do open-hole HFEC in- spection of fastener holes 1-10 for any crack. (a)(b) All airplanes. -Before further flight.Contact The Boeing Company for repair in- structions and do the re- pair. CONDITION 7: ANY CRACK FOUND IN DRAG FITTINGS. (c) -Before further flight.Contact The Boeing Company for repair in- structions and do the re- pair. CONDITION 8: ANY CRACK FOUND IN SKIN. (c) -Before further flight.CONDITION 9 (ACTION 1): Install bolts, washers, and nuts for fastener holes where fasteners were removed. CONDITION 9: NO CRACK FOUND IN SKIN AND DRAG FITTINGS DURING OPEN-HOLE HFEC INSPECTION. -Before further flight.CONDITION 9 (ACTION 2): Install the Upper Link and Upper Link Pins if re- moved. 5,500 flight cycles.-CONDITION 9 (ACTION 3): Repeat open-hole HFEC inspection of fas- tener holes 1-10 for any crack. (a)(b) (a) Accomplishment of an open-hole HFEC inspection of fastener holes 1-10 as a result of CONDITION 4 meets the requirements of this action. (b) On or after the Revision 1 date of 757-57A0073 RB, when this action occurs at the same time as a loose fastener inspection from Table 9, the loose fastener inspection in Table 9 must be done first. Export Controlled ECCN: 9E991 See page 1 for details Original Issue: July 14, 2017 757-57A0073 RBRevision 3: May 05, 2023 29 of 161 REQUIREMENTS BULLETIN 757-57A0073 ALERTALERT ### Page 30 Group 5, 13, Configuration 1: Table 8: Inspect for cracks in the wing skin and drag fittings at the upper link drag fittings (Fastener Locations 1-10) Repeat Interval (Not to Exceed) Compliance Time (Whichever Occurs Later) ActionCondition (c) More than one CONDITION can be applicable on each airplane. Group 1, 5, 12-13, Configuration 1: Table 9: Inspection for loose fasteners, skin cracking, and shim migration at the upper link drag fittings and for cracks in the diagonal brace and diagonal brace fittings Repeat Interval (Not to Exceed) Compliance Time (Whichever Occurs Later) ActionCondition -Within 2,100 flight cycles af- ter the Revision 1 date of Re- quirements Bul- letin 757- 57A0073 RB. Before 6,000 to- tal flight cycles. ACTION 1: Do a general visual inspection of the diagonal brace and diago- nal brace fittings for any crack. All Airplanes. -Within 3,000 flight cycles af- ter the Original Issue date of Requirements Bulletin 757- 57A0073 RB. ACTION 2: Do inspec- tions for loose fasteners, skin cracks, and shim mi- grations. -Before further flight.Contact The Boeing Company for repair in- structions and do the re- pair. CONDITION 1: ANY CRACK FOUND IN DIAG- ONAL BRACE OR DIAGO- NAL BRACE FITTINGS. (a) 2,100 flight cycles.-Repeat general visual in- spection of the diagonal brace and diagonal brace fittings for any crack. CONDITION 2: NO CRACK FOUND IN DIAG- ONAL BRACE OR DIAGO- NAL BRACE FITTINGS. (a) -Before further flight.CONDITION 3 (ACTION 1): Install the Upper Link and Upper Link Pins if re- moved. CONDITION 3: NO SHIM MIGRATION, NO SKIN CRACK, AND NO LOOSE FASTENER. 3,000 flight cycles.-CONDITION 3 (ACTION 2): Repeat inspections for loose fasteners, skin cracks, and shim migra- tions. Export Controlled ECCN: 9E991 See page 1 for details Original Issue: July 14, 2017 757-57A0073 RBRevision 3: May 05, 2023 30 of 161 REQUIREMENTS BULLETIN 757-57A0073 ALERTALERT ### Page 31 Group 1, 5, 12-13, Configuration 1: Table 9: Inspection for loose fasteners, skin cracking, and shim migration at the upper link drag fittings and for cracks in the diagonal brace and diagonal brace fittings Repeat Interval (Not to Exceed) Compliance Time (Whichever Occurs Later) ActionCondition -Before further flight.Do open-hole HFEC in- spection of fastener holes 1-10 for any crack. CONDITION 4: ANY LOOSE FASTENER FOUND ON FASTENERS 1-10. (a) -Before further flight.Do open-hole HFEC in- spection on the loose bolt holes for any crack. CONDITION 5: ANY LOOSE FASTENER FOUND ON FASTENERS 11-18. (a) -Before further flight.Contact The Boeing Company for repair in- structions and do the re- pair. CONDITION 6: MAJOR SHIM MIGRATION FOUND. (a) -Before further flight.Contact The Boeing Company for repair in- structions and do the re- pair. CONDITION 7: ANY CRACK FOUND IN DRAG FITTINGS. (a) -Before further flight.Contact The Boeing Company for repair in- structions and do the re- pair. CONDITION 8: ANY CRACK FOUND IN SKIN. (a) -Before further flight.CONDITION 9 (ACTION 1): Install bolts, washers, and nuts for fastener holes where fasteners were removed. CONDITION 9: NO CRACK FOUND IN SKIN AND DRAG FITTINGS DURING OPEN-HOLE HFEC INSPECTION. -Before further flight.CONDITION 9 (ACTION 2): Install the Upper Link and Upper Link Pins if re- moved. 3,000 flight cycles.-CONDITION 9 (ACTION 3): Repeat inspections for loose fasteners, skin cracks, and shim migra- tions. -Before further flight.Do a torque check of fas- teners on the affected shim(s). CONDITION 10: MINOR SHIM MIGRATION FOUND IN SKIN PANEL SHIM. (a) Export Controlled ECCN: 9E991 See page 1 for details Original Issue: July 14, 2017 757-57A0073 RBRevision 3: May 05, 2023 31 of 161 REQUIREMENTS BULLETIN 757-57A0073 ALERTALERT ### Page 32 Group 1, 5, 12-13, Configuration 1: Table 9: Inspection for loose fasteners, skin cracking, and shim migration at the upper link drag fittings and for cracks in the diagonal brace and diagonal brace fittings Repeat Interval (Not to Exceed) Compliance Time (Whichever Occurs Later) ActionCondition -Before further flight.CONDITION 10.1 (AC- TION 1): Trim affected shim to the edge of the fitting. Apply chemical conversion coating on the shim and fillet seal the edge of the drag fitting. CONDITION 10.1: ALL BOLTS PASSED THE TORQUE CHECK. -Before further flight.CONDITION 10.1 (AC- TION 2): Install the Upper Link and Upper Link Pins if removed. 3,000 flight cycles.-CONDITION 10.1 (AC- TION 3): Repeat inspec- tions for loose fasteners, skin cracks, and shim mi- grations. -Before further flight.Contact The Boeing Company for repair in- structions and do the re- pair. CONDITION 10.2: ANY BOLT FAILED THE TORQUE CHECK. -Before further flight.CONDITION 11 (ACTION 1): Trim affected shim to the edge of the fitting. Apply chemical conver- sion coating on the shim and fillet seal the edge of the drag fitting. CONDITION 11: MINOR SHIM MIGRATION FOUND IN SPAR SHIM. (a) -Before further flight.CONDITION 11 (ACTION 2): Install the Upper Link and Upper Link Pins if re- moved. 3,000 flight cycles.-CONDITION 11 (ACTION 3): Repeat inspections for loose fasteners, skin cracks, and shim migra- tions. (a) More than one CONDITION can be applicable on each airplane. Export Controlled ECCN: 9E991 See page 1 for details Original Issue: July 14, 2017 757-57A0073 RBRevision 3: May 05, 2023 32 of 161 REQUIREMENTS BULLETIN 757-57A0073 ALERTALERT ### Page 33 Group 1, 12, Configuration 1: Table 10: Inspect for cracks in the wing skin and drag fittings at the upper link drag fittings (Fastener Locations 11-18) Repeat Interval (Not to Exceed) Compliance Time (Whichever Occurs Later) ActionCondition -Within 3,000 flight cycles af- ter the Revision 1 date of Re- quirements Bul- letin 757- 57A0073 RB. Before 8,400 to- tal flight cycles. Do an open-hole HFEC inspection of fastener holes 11-18 for any crack. (a)(b) All airplanes. -Before further flight.Contact The Boeing Company for repair in- structions and do the re- pair. CONDITION 7: ANY CRACK FOUND IN DRAG FITTINGS. (c) -Before further flight.Contact The Boeing Company for repair in- structions and do the re- pair. CONDITION 8: ANY CRACK FOUND IN SKIN. (c) -Before further flight.CONDITION 14 (ACTION 1): Install bolts, washers, and nuts for fastener holes where fasteners were removed. CONDITION 14: NO CRACK FOUND IN SKIN AND DRAG FITTINGS. -Before further flight.CONDITION 14 (ACTION 2): Install the Upper Link and Upper Link Pins if re- moved. 8,400 flight cycles.-CONDITION 14 (ACTION 3): Repeat open hole HFEC inspection of fas- tener holes 11-18 for any crack. (a)(b) (a) Accomplishment of an open-hole HFEC inspection of loose fastener hole(s) as a result of CONDITION 5 meets the requirements of this action for only the fastener hole(s) inspected. (b) On or after the Revision 1 date of 757-57A0073 RB,when this action occurs at the same time as a loose fastener inspection from Table 9, the loose fastener inspection in Table 9 must be done first. (c) More than one CONDITION can be applicable on each airplane. Export Controlled ECCN: 9E991 See page 1 for details Original Issue: July 14, 2017 757-57A0073 RBRevision 3: May 05, 2023 33 of 161 REQUIREMENTS BULLETIN 757-57A0073 ALERTALERT ### Page 34 Group 1, 12, Configuration 2: Table 11: Inspect for cracks in the wing skin and drag fittings at the upper link drag fittings (Fastener Locations 11-18) Repeat Interval (Not to Exceed) Compliance Time (Whichever Occurs Later) ActionCondition -Within 6,000 flight cycles af- ter the Revision 3 date of Re- quirements Bul- letin 757- 57A0073 RB or within 12,000 flight cycles af- ter the last open-hole HFEC inspec- tion of fastener holes 11-18 for any crack was done, whichever occurs first. Before 14,000 total flight cy- cles. Do an open-hole HFEC inspection of fastener holes 11-18 for any crack. (a)(b) Airplanes with no repair found in Condition 21 and the inspections specified in Requirements Bulletin 757- 57A0073 RB Revision 2 have been done. -Within 3,000 flight cycles af- ter the Revision 1 date of Re- quirements Bul- letin 757- 57A0073. Before 14,000 total flight cy- cles. Do an open-hole HFEC inspection of fastener holes 11-18 for any crack. (a)(b) Airplanes with no repair found in Condition 21 and the inspections specified in Requirements Bulletin 757- 57A0073 RB Revision 2 have not been done. -Before further flight.CONDITION 13 (OPTION 1): Contact The Boeing Company for repair in- structions and do the re- pair. CONDITION 13: ANY CRACK FOUND IN THE DRAG FITTINGS DURING OPEN-HOLE INSPEC- TIONS. (c) -Before further flight.CONDITION 13, OPTION 2 (ACTION 1): Replace any cracked drag fitting with a new part. -Before further flight.CONDITION 13, OPTION 2 (ACTION 2): Install the Upper Link and Upper Link Pins if removed. 6,000 flight cycles.-CONDITION 13, OPTION 2 (ACTION 3): Repeat open hole HFEC inspec- tion of fastener holes 11- 18 for any crack. (a)(b) Export Controlled ECCN: 9E991 See page 1 for details Original Issue: July 14, 2017 757-57A0073 RBRevision 3: May 05, 2023 34 of 161 REQUIREMENTS BULLETIN 757-57A0073 ALERTALERT ### Page 35 Group 1, 12, Configuration 2: Table 11: Inspect for cracks in the wing skin and drag fittings at the upper link drag fittings (Fastener Locations 11-18) Repeat Interval (Not to Exceed) Compliance Time (Whichever Occurs Later) ActionCondition -Before further flight.Contact The Boeing Company for repair in- structions and do the re- pair. CONDITION 8: ANY CRACK FOUND IN SKIN. (c) -Before further flight.CONDITION 14 (ACTION 1): Install bolts, washers, and nuts for fastener holes where fasteners were removed. CONDITION 14: NO CRACK FOUND IN SKIN AND DRAG FITTINGS -Before further flight.CONDITION 14 (ACTION 2): Install the Upper Link and Upper Link Pins if re- moved. 6,000 flight cycles.-CONDITION 14 (ACTION 3): Repeat open hole HFEC inspection of fas- tener holes 11-18 for any crack. (a)(b) (a) Accomplishment of an open-hole HFEC inspection of loose fastener hole(s) as a result of CONDITION 5 meets the requirements of this action for only the fastener hole(s) inspected. (b) On or after the Revision 1 date of 757-57A0073 RB, when this action occurs at the same time as a loose fastener inspection from Table 1 or Table 17, the loose fastener inspection in Table 1 or Table 17 must be done first. (c) More than one CONDITION can be applicable on each airplane. Group 2-4: Table 12: Inspect for cracks in the wing skin and drag fittings at the upper link drag fittings (Fastener Locations 11-18) Repeat Interval (Not to Exceed) Compliance TimeActionCondition -Within 6,000 flight cycles after the Revision 3 date of Requirements Bulletin 757-57A0073 RB or within 12,000 flight cycles after the last open-hole HFEC inspection of fastener holes 11-18 for any crack was done, whichever occurs first. Do an open-hole HFEC inspection of fastener holes 11-18 for any crack. (a)(b) Airplanes with no repair found in Condition 21 and the inspections specified in Requirements Bulletin 757- 57A0073 RB Revision 2 have been done. Export Controlled ECCN: 9E991 See page 1 for details Original Issue: July 14, 2017 757-57A0073 RBRevision 3: May 05, 2023 35 of 161 REQUIREMENTS BULLETIN 757-57A0073 ALERTALERT ### Page 36 Group 2-4: Table 12: Inspect for cracks in the wing skin and drag fittings at the upper link drag fittings (Fastener Locations 11-18) Repeat Interval (Not to Exceed) Compliance TimeActionCondition -Within 3,000 flight cycles after the Revision 1 date of Requirements Bulletin 757-57A0073 RB. Do an open-hole HFEC inspection of fastener holes 11-18 for any crack. (a)(b) Airplanes with no repair found in Condition 21 and the inspections specified in Requirements Bulletin 757- 57A0073 RB Revision 2 have not been done. -Before further flight.CONDITION 13 (OPTION 1): Contact The Boeing Company for repair in- structions and do the re- pair. CONDITION 13: ANY CRACK FOUND IN THE DRAG FITTINGS DURING OPEN-HOLE INSPEC- TIONS. (c) -Before further flight.CONDITION 13, OPTION 2 (ACTION 1): Replace any cracked drag fitting with a new part. -Before further flight.CONDITION 13, OPTION 2 (ACTION 2): Install the Upper Link and Upper Link Pins if removed. 6,000 flight cycles.-CONDITION 13, OPTION 2 (ACTION 3): Repeat open-hole HFEC inspec- tion of fastener holes 11- 18 for any crack. (a)(b) -Before further flight.Contact The Boeing Company for repair in- structions and do the re- pair. CONDITION 8: ANY CRACK FOUND IN SKIN. (c) Export Controlled ECCN: 9E991 See page 1 for details Original Issue: July 14, 2017 757-57A0073 RBRevision 3: May 05, 2023 36 of 161 REQUIREMENTS BULLETIN 757-57A0073 ALERTALERT ### Page 37 Group 2-4: Table 12: Inspect for cracks in the wing skin and drag fittings at the upper link drag fittings (Fastener Locations 11-18) Repeat Interval (Not to Exceed) Compliance TimeActionCondition -Before further flight.CONDITION 14 (ACTION 1): Install bolts, washers, and nuts for fastener holes where fasteners were removed. CONDITION 14: NO CRACK FOUND IN SKIN AND DRAG FITTINGS. -Before further flight.CONDITION 14 (ACTION 2): Install the Upper Link and Upper Link Pins if re- moved. 6,000 flight cycles.-CONDITION 14 (ACTION 3): Repeat open-hole HFEC inspection of fas- tener holes 11-18 for any crack. (a)(b) (a) Accomplishment of an open-hole HFEC inspection of loose fastener hole(s) as a result of CONDITION 5 meets the requirements of this action for only the fastener hole(s) inspected. (b) On or after the Revision 1 date of 757-57A0073 RB, when this action occurs at the same time as a loose fastener inspection from Table 18, the loose fastener inspection in Table 18 must be done first. (c) More than one CONDITION can be applicable on each airplane. Group 5, 13, Configuration 1: Table 13: Inspect for cracks in the wing skin and drag fittings at the upper link drag fittings (Fastener Locations 11-18) Repeat Interval (Not to Exceed) Compliance Time (Whichever Occurs Later) ActionCondition -Within 3,000 flight cycles af- ter the Revision 1 date of Re- quirements Bul- letin 757- 57A0073 RB. Before 5,500 to- tal flight cycles. Do an open-hole HFEC inspection of fastener holes 11-18 for any crack. (a)(b) All airplanes. -Before further flight.Contact The Boeing Company for repair in- structions and do the re- pair. CONDITION 7: ANY CRACK FOUND IN THE DRAG FITTINGS. (c) -Before further flight.Contact The Boeing Company for repair in- structions and do the re- pair. CONDITION 8: ANY CRACK FOUND IN SKIN. (c) Export Controlled ECCN: 9E991 See page 1 for details Original Issue: July 14, 2017 757-57A0073 RBRevision 3: May 05, 2023 37 of 161 REQUIREMENTS BULLETIN 757-57A0073 ALERTALERT ### Page 38 Group 5, 13, Configuration 1: Table 13: Inspect for cracks in the wing skin and drag fittings at the upper link drag fittings (Fastener Locations 11-18) Repeat Interval (Not to Exceed) Compliance Time (Whichever Occurs Later) ActionCondition -Before further flight.CONDITION 14 (ACTION 1): Install bolts, washers, and nuts for fastener holes where fasteners were removed. CONDITION 14: NO CRACK FOUND IN SKIN AND DRAG FITTINGS. -Before further flight.CONDITION 14 (ACTION 2): Install the Upper Link and Upper Link Pins if re- moved. 5,500 flight cycles.-CONDITION 14 (ACTION 3): Repeat open-hole HFEC inspection of fas- tener holes 11-18 for any crack. (a)(b) (a) Accomplishment of an open-hole HFEC inspection of loose fastener hole(s) as a result of CONDITION 5 meets the requirements of this action for only the fastener hole(s) inspected. (b) On or after the Revision 1 date of 757-57A0073 RB, when this action occurs at the same time as a loose fastener inspection from Table 9, the loose fastener inspection in Table 9 must be done first. (c) More than one CONDITION can be applicable on each airplane. Group 5, 13, Configuration 2: Table 14: Inspect for cracks in the wing skin and drag fittings at the upper link drag fittings (Fastener Locations 11-18) Repeat Interval (Not to Exceed) Compliance Time (Whichever Occurs Later) ActionCondition -Within 6,000 flight cycles af- ter the last open-hole HFEC inspec- tion of fastener holes 11-18 for any crack was done. Before 14,000 total flight cy- cles. Do an open-hole HFEC inspection of fastener holes 11-18 for any crack. (a)(b) Airplanes with no repair found in Condition 21 and the inspections specified in Requirements Bulletin 757- 57A0073 RB Revision 2 have been done. Export Controlled ECCN: 9E991 See page 1 for details Original Issue: July 14, 2017 757-57A0073 RBRevision 3: May 05, 2023 38 of 161 REQUIREMENTS BULLETIN 757-57A0073 ALERTALERT ### Page 39 Group 5, 13, Configuration 2: Table 14: Inspect for cracks in the wing skin and drag fittings at the upper link drag fittings (Fastener Locations 11-18) Repeat Interval (Not to Exceed) Compliance Time (Whichever Occurs Later) ActionCondition -Within 3,000 flight cycles af- ter the Revision 1 date of Re- quirements Bul- letin 757- 57A0073 RB. Before 14,000 total flight cy- cles. Do an open-hole HFEC inspection of fastener holes 11-18 for any crack. (a)(b) Airplanes with no repair found in Condition 21 and the inspections specified in Requirements Bulletin 757- 57A0073 RB Revision 2 have not been done. -Before further flight.CONDITION 13 (OPTION 1): Contact The Boeing Company for repair in- structions and do the re- pair. CONDITION 13: ANY CRACK FOUND IN DRAG FITTINGS DURING OPEN- HOLE INSPECTIONS. (c) -Before further flight.CONDITION 13, OPTION 2 (ACTION 1): Replace any cracked drag fitting with a new part. -Before further flight.CONDITION 13, OPTION 2 (ACTION 2): Install the Upper Link and Upper Link Pins if removed. 6,000 flight cycles.-CONDITION 13, OPTION 2 (ACTION 3): Repeat open-hole HFEC inspec- tion of fastener holes 11- 18 for any crack. (a)(b) -Before further flight.Contact The Boeing Company for repair in- structions and do the re- pair. CONDITION 8: ANY CRACK FOUND IN SKIN (c) Export Controlled ECCN: 9E991 See page 1 for details Original Issue: July 14, 2017 757-57A0073 RBRevision 3: May 05, 2023 39 of 161 REQUIREMENTS BULLETIN 757-57A0073 ALERTALERT ### Page 40 Group 5, 13, Configuration 2: Table 14: Inspect for cracks in the wing skin and drag fittings at the upper link drag fittings (Fastener Locations 11-18) Repeat Interval (Not to Exceed) Compliance Time (Whichever Occurs Later) ActionCondition -Before further flight.CONDITION 14 (ACTION 1): Install bolts, washers, and nuts for fastener holes where fasteners were removed. CONDITION 14: NO CRACK FOUND IN SKIN AND DRAG FITTINGS. -Before further flight.CONDITION 14 (ACTION 2): Install the Upper Link and Upper Link Pins if re- moved. 6,000 flight cycles.-CONDITION 14 (ACTION 3): Repeat open-hole HFEC inspection of fas- tener holes 11-18 for any crack. (a)(b) (a) Accomplishment of an open-hole HFEC inspection of loose fastener hole(s) as a result of CONDITION 5 meets the requirements of this action for only the fastener hole(s) inspected. (b) On or after the Revision 1 date of 757-57A0073 RB, when this action occurs at the same time as a loose fastener inspection from Table 1 or Table 17, the loose fastener inspection in Table 1 or Table 17 must be done first. (c) More than one CONDITION can be applicable on each airplane. Group 6-8, 11: Table 15: Inspect for cracks in the wing skin and drag fittings at the upper link drag fittings (Fastener Locations 11-18) Repeat Interval (Not to Exceed) Compliance TimeActionCondition -Within 6,000 flight cycles after the last open-hole HFEC inspection of fastener holes 11-18 for any crack was done. Do an open-hole HFEC inspection of fastener holes 11-18 for any crack. (a)(b) Airplanes with no repair found in Condition 21 and the inspections specified in Requirements Bulletin 757- 57A0073 RB Revision 2 have been done. OR Airplanes with no repair found in Condition 26 and the inspections specified in Requirements Bulletin 757- 57A0073 RB Revision 2 have been done. Export Controlled ECCN: 9E991 See page 1 for details Original Issue: July 14, 2017 757-57A0073 RBRevision 3: May 05, 2023 40 of 161 REQUIREMENTS BULLETIN 757-57A0073 ALERTALERT ### Page 41 Group 6-8, 11: Table 15: Inspect for cracks in the wing skin and drag fittings at the upper link drag fittings (Fastener Locations 11-18) Repeat Interval (Not to Exceed) Compliance TimeActionCondition -Within 3,000 flight cycles after the Revision 1 date of Requirements Bulletin 757-57A0073 RB. Do an open-hole HFEC inspection of fastener holes 11-18 for any crack. (a)(b) Airplanes with no repair found in Condition 21 and the inspections specified in Requirements Bulletin 757- 57A0073 RB Revision 2 have not been done. OR Airplanes with no repair found in Condition 26 and the inspections specified in Requirements Bulletin 757- 57A0073 RB Revision 2 have not been done. -Before further flight.CONDITION 13 (OPTION 1): Contact The Boeing Company for repair in- structions and do the re- pair. CONDITION 13: ANY CRACK FOUND IN THE DRAG FITTINGS DURING OPEN HOLE INSPEC- TIONS. (c) -Before further flight.CONDITION 13, OPTION 2 (ACTION 1): Replace any cracked drag fitting with a new part. -Before further flight.CONDITION 13, OPTION 2 (ACTION 2): Install the Upper Link and Upper Link Pins if removed. 6,000 flight cycles.-CONDITION 13, OPTION 2 (ACTION 3): Repeat open-hole HFEC inspec- tion of fastener holes 11- 18 for any crack. (a)(b) -Before further flight.Contact The Boeing Company for repair in- structions and do the re- pair. CONDITION 8: ANY CRACK FOUND IN SKIN. (c) Export Controlled ECCN: 9E991 See page 1 for details Original Issue: July 14, 2017 757-57A0073 RBRevision 3: May 05, 2023 41 of 161 REQUIREMENTS BULLETIN 757-57A0073 ALERTALERT ### Page 42 Group 6-8, 11: Table 15: Inspect for cracks in the wing skin and drag fittings at the upper link drag fittings (Fastener Locations 11-18) Repeat Interval (Not to Exceed) Compliance TimeActionCondition -Before further flight.CONDITION 14 (ACTION 1): Install bolts, washers, and nuts for fastener holes where fasteners were removed. CONDITION 14: NO CRACK FOUND IN SKIN AND DRAG FITTINGS. -Before further flight.CONDITION 14 (ACTION 2): Install the Upper Link and Upper Link Pins if re- moved. 6,000 flight cycles.-CONDITION 14 (ACTION 3): Repeat open-hole HFEC inspection of fas- tener holes 11-18 for any crack. (a)(b) (a) Accomplishment of an open-hole HFEC inspection of loose fastener hole(s) as a result of CONDITION 5 meets the requirements of this action for only the fastener hole(s) inspected. (b) On or after the Revision 1 date of 757-57A0073 RB, when this action occurs at the same time as a loose fastener inspection from Table 2 or Table 18, the loose fastener inspection in Table 2 or Table 18 must be done first. (c) More than one CONDITION can be applicable on each airplane. Group 9-10: Table 16: Inspect for cracks in the wing skin and drag fittings at the upper link drag fittings (Fastener Locations 11-18) Repeat Interval (Not to Exceed) Compliance TimeActionCondition -Within 6,000 flight cycles after the Revision 3 date of Requirements Bulletin 757-57A0073 RB or within 9,000 flight cycles after the last open-hole HFEC inspection of fastener holes 11-18 for any crack was done, whichever occurs first. Do an open-hole HFEC inspection of fastener holes 11-18 for any crack. (a)(b) Airplanes with no repair found in Condition 26 and the inspections specified in Requirements Bulletin 757- 57A0073 RB Revision 2 have been done. -Within 3,000 flight cycles after the Revision 1 date of Requirements Bulletin 757-57A0073 RB. Do an open-hole HFEC inspection of fastener holes 11-18 for any crack. (a)(b) Airplanes with no repair found in Condition 26 and the inspections specified in Requirements Bulletin 757- 57A0073 RB Revision 2 have not been done. Export Controlled ECCN: 9E991 See page 1 for details Original Issue: July 14, 2017 757-57A0073 RBRevision 3: May 05, 2023 42 of 161 REQUIREMENTS BULLETIN 757-57A0073 ALERTALERT ### Page 43 Group 9-10: Table 16: Inspect for cracks in the wing skin and drag fittings at the upper link drag fittings (Fastener Locations 11-18) Repeat Interval (Not to Exceed) Compliance TimeActionCondition -Before further flight.CONDITION 13 (OPTION 1): Contact The Boeing Company for repair in- structions and do the re- pair. CONDITION 13: ANY CRACK FOUND IN DRAG FITTINGS DURING OPEN HOLE INSPECTIONS (c) -Before further flight.CONDITION 13, OPTION 2 (ACTION 1): Replace any cracked drag fitting with a new part. -Before further flight.CONDITION 13, OPTION 2 (ACTION 2): Install the Upper Link and Upper Link Pins if removed. 6,000 flight cycles.-CONDITION 13, OPTION 2 (ACTION 3): Repeat open-hole HFEC inspec- tion of fastener holes 11- 18 for any crack. (a)(b) -Before further flight.Contact The Boeing Company for repair in- structions and do the re- pair. CONDITION 8: ANY CRACK FOUND IN SKIN. (c) -Before further flight.CONDITION 14 (ACTION 1): Install bolts, washers, and nuts for fastener holes where fasteners were removed. CONDITION 14: NO CRACK FOUND IN SKIN AND DRAG FITTINGS. -Before further flight.CONDITION 14 (ACTION 2): Install the Upper Link and Upper Link Pins if re- moved. 6,000 flight cycles.-CONDITION 14 (ACTION 3): Repeat open-hole HFEC inspection of fas- tener holes 11-18 for any crack. (a)(b) (a) Accomplishment of an open-hole HFEC inspection of loose fastener hole(s) as a result of CONDITION 5 meets the requirements of this action for only the fastener hole(s) inspected. (b) On or after the Revision 1 date of 757-57A0073 RB, when this action occurs at the same time as a loose fastener inspection from Table 1 or Table 2, the loose fastener inspection in Table 1 or Table 2 must be done first. Export Controlled ECCN: 9E991 See page 1 for details Original Issue: July 14, 2017 757-57A0073 RBRevision 3: May 05, 2023 43 of 161 REQUIREMENTS BULLETIN 757-57A0073 ALERTALERT ### Page 44 Group 9-10: Table 16: Inspect for cracks in the wing skin and drag fittings at the upper link drag fittings (Fastener Locations 11-18) Repeat Interval (Not to Exceed) Compliance TimeActionCondition (c) More than one CONDITION can be applicable on each airplane. Group 12-13, Configuration 2: Table 17: Inspection for loose fasteners, skin cracking, and shim migration at the upper link drag fittings and for cracks in the diagonal brace and diagonal brace fittings Repeat Interval (Not to Exceed) Compliance Time (Whichever Occurs Later) ActionCondition -Within 1,400 flight cycles af- ter the Revision 3 date of Re- quirements Bul- letin 757- 57A0073 RB or within 2,100 flight cycles af- ter the last gen- eral visual in- spection of the diagonal brace and diagonal brace fittings for any crack was done, whichever occurs first. Before 6,000 to- tal flight cycles. ACTION 1: Do a general visual inspection of the diagonal brace and diago- nal brace fittings for any crack. Airplanes with no repair found in Condition 21 and the inspections specified in Requirements Bulletin 757- 57A0073 RB Revision 2 have been done. -Within 3,000 flight cycles af- ter the last in- spections for loose fasteners, skin cracks and shim migrations. ACTION 2: Do inspec- tions for loose fasteners, skin cracks, and shim mi- grations. Export Controlled ECCN: 9E991 See page 1 for details Original Issue: July 14, 2017 757-57A0073 RBRevision 3: May 05, 2023 44 of 161 REQUIREMENTS BULLETIN 757-57A0073 ALERTALERT ### Page 45 Group 12-13, Configuration 2: Table 17: Inspection for loose fasteners, skin cracking, and shim migration at the upper link drag fittings and for cracks in the diagonal brace and diagonal brace fittings Repeat Interval (Not to Exceed) Compliance Time (Whichever Occurs Later) ActionCondition -Within 1,400 flight cycles af- ter the Revision 3 date of Re- quirements Bul- letin 757- 57A0073 RB or within 2,100 flight cycles af- ter the Revision 1 date of Re- quirements Bul- letin 757- 57A0073 RB, whichever oc- curs first. Before 6,000 to- tal flight cycles. ACTION 1: Do a general visual inspection of the diagonal brace and diago- nal brace fittings for any crack. Airplanes with no repair found in Condition 21 and the inspections specified in Requirements Bulletin 757- 57A0073 RB Revision 2 have not been done. -Within 3,000 flight cycles af- ter the Original Issue date of Requirements Bulletin 757- 57A0073 RB. ACTION 2: Do inspec- tions for loose fasteners, skin cracks, and shim mi- grations. -Before further flight.Contact The Boeing Company for repair in- structions and do the re- pair. CONDITION 1: ANY CRACK FOUND IN DIAG- ONAL BRACE OR DIAGO- NAL BRACE FITTINGS. (a) 1,400 flight cycles.-Repeat general visual in- spection of the diagonal brace and diagonal brace fittings for any crack. CONDITION 2: NO CRACK FOUND IN DIAG- ONAL BRACE OR DIAGO- NAL BRACE FITTINGS. (a) -Before further flight.CONDITION 3 (ACTION 1): Install the Upper Link and Upper Link Pins if re- moved. CONDITION 3: NO SHIM MIGRATION, NO SKIN CRACK, AND NO LOOSE FASTENER. 3,000 flight cycles.-CONDITION 3 (ACTION 2): Repeat inspections for loose fasteners, skin cracks, and shim migra- tions. Export Controlled ECCN: 9E991 See page 1 for details Original Issue: July 14, 2017 757-57A0073 RBRevision 3: May 05, 2023 45 of 161 REQUIREMENTS BULLETIN 757-57A0073 ALERTALERT ### Page 46 Group 12-13, Configuration 2: Table 17: Inspection for loose fasteners, skin cracking, and shim migration at the upper link drag fittings and for cracks in the diagonal brace and diagonal brace fittings Repeat Interval (Not to Exceed) Compliance Time (Whichever Occurs Later) ActionCondition -Before further flight.Do open-hole HFEC in- spection of fastener holes 1-10 for any crack. CONDITION 4: ANY LOOSE FASTENER FOUND ON FASTENERS 1-10. (a) -Before further flight.Do open-hole HFEC in- spection on the loose bolt holes for any crack. CONDITION 5: ANY LOOSE FASTENER FOUND ON FASTENERS 11-18. (a) -Before further flight.Contact The Boeing Company for repair in- structions and do the re- pair. CONDITION 6: MAJOR SHIM MIGRATION FOUND. (a) -Before further flight.CONDITION 7 (OPTION 1): Contact The Boeing Company for repair in- structions and do the re- pair. CONDITION 7: ANY CRACK FOUND IN THE DRAG FITTINGS. (a) -Before further flight.CONDITION 7, OPTION 2 (ACTION 1): Replace any cracked drag fitting with a new part. -Before further flight.CONDITION 7, OPTION 2 (ACTION 2): Install the Upper Link and Upper Link Pins if removed. 3,000 flight cycles.-CONDITION 7, OPTION 2 (ACTION 3): Repeat in- spections for loose fasten- ers, skin cracks, and shim migrations. -Before further flight.Contact The Boeing Company for repair in- structions and do the re- pair. CONDITION 8: ANY CRACK FOUND IN SKIN. (a) Export Controlled ECCN: 9E991 See page 1 for details Original Issue: July 14, 2017 757-57A0073 RBRevision 3: May 05, 2023 46 of 161 REQUIREMENTS BULLETIN 757-57A0073 ALERTALERT ### Page 47 Group 12-13, Configuration 2: Table 17: Inspection for loose fasteners, skin cracking, and shim migration at the upper link drag fittings and for cracks in the diagonal brace and diagonal brace fittings Repeat Interval (Not to Exceed) Compliance Time (Whichever Occurs Later) ActionCondition -Before further flight.CONDITION 9 (ACTION 1): Install bolts, washers, and nuts for fastener holes where fasteners were removed. CONDITION 9: NO CRACK FOUND IN SKIN AND DRAG FITTINGS DURING OPEN-HOLE HFEC INSPECTION. (a) -Before further flight.CONDITION 9 (ACTION 2): Install the Upper Link and Upper Link Pins if re- moved. 3,000 flight cycles.-CONDITION 9 (ACTION 3): Repeat inspections for loose fasteners, skin cracks, and shim migra- tions. -Before further flight.Do a torque check of fas- teners on the affected shim(s). CONDITION 10: MINOR SHIM MIGRATION FOUND IN SKIN PANEL SHIM. (a) -Before further flight.CONDITION 10.1 (AC- TION 1): Trim affected shim to the edge of the fitting. Apply chemical conversion coating on the shim and fillet seal the edge of the drag fitting. CONDITION 10.1: ALL BOLTS PASSED THE TORQUE CHECK. -Before further flight.CONDITION 10.1 (AC- TION 2): Install the Upper Link and Upper Link Pins if removed. 3,000 flight cycles.-CONDITION 10.1 (AC- TION 3): Repeat inspec- tions for loose fasteners, skin cracks, and shim mi- grations. -Before further flight.Contact The Boeing Company for repair in- structions and do the re- pair. CONDITION 10.2: ANY BOLT FAILED THE TORQUE CHECK. Export Controlled ECCN: 9E991 See page 1 for details Original Issue: July 14, 2017 757-57A0073 RBRevision 3: May 05, 2023 47 of 161 REQUIREMENTS BULLETIN 757-57A0073 ALERTALERT ### Page 48 Group 12-13, Configuration 2: Table 17: Inspection for loose fasteners, skin cracking, and shim migration at the upper link drag fittings and for cracks in the diagonal brace and diagonal brace fittings Repeat Interval (Not to Exceed) Compliance Time (Whichever Occurs Later) ActionCondition -Before further flight.CONDITION 11 (ACTION 1): Trim affected shim to the edge of the fitting. Apply chemical conver- sion coating on the shim and fillet seal the edge of the drag fitting. CONDITION 11: MINOR SHIM MIGRATION FOUND IN SPAR SHIM. (a) -Before further flight.CONDITION 11 (ACTION 2): Install the Upper Link and Upper Link Pins if re- moved. 3,000 flight cycles.-CONDITION 11 (ACTION 3): Repeat inspections for loose fasteners, skin cracks, and shim migra- tions. (a) More than one CONDITION can be applicable on each airplane. Export Controlled ECCN: 9E991 See page 1 for details Original Issue: July 14, 2017 757-57A0073 RBRevision 3: May 05, 2023 48 of 161 REQUIREMENTS BULLETIN 757-57A0073 ALERTALERT ### Page 49 Group 2-4, 6-8: Table 18: Inspection for loose fasteners, skin cracking, and shim migration at the upper link drag fittings and for cracks in the diagonal brace and diagonal brace fittings Repeat Interval (Not to Exceed) Compliance Time (Whichever Occurs Later) ActionCondition -Within 1,700 flight cycles af- ter the Revision 3 date of Re- quirements Bul- letin 757- 57A0073 RB or within 2,100 flight cycles af- ter the last gen- eral visual in- spection of the diagonal brace and diagonal brace fittings for any crack was done, whichever occurs first. Before 6,000 to- tal flight cycles. ACTION 1: Do a general visual inspection of the diagonal brace and diago- nal brace fittings for any crack. Airplanes with no repair found in Condition 21 and the inspections specified in Requirements Bulletin 757- 57A0073 RB Revision 2 have been done. -Within 3,000 flight cycles af- ter the Original Issue date of Requirements Bulletin 757- 57A0073 RB ACTION 2: Do inspec- tions for loose fasteners, skin cracks, and shim mi- grations. Export Controlled ECCN: 9E991 See page 1 for details Original Issue: July 14, 2017 757-57A0073 RBRevision 3: May 05, 2023 49 of 161 REQUIREMENTS BULLETIN 757-57A0073 ALERTALERT ### Page 50 Group 2-4, 6-8: Table 18: Inspection for loose fasteners, skin cracking, and shim migration at the upper link drag fittings and for cracks in the diagonal brace and diagonal brace fittings Repeat Interval (Not to Exceed) Compliance Time (Whichever Occurs Later) ActionCondition -Within 1,700 flight cycles af- ter the Revision 3 date of Re- quirements Bul- letin 757- 57A0073 RB or within 2,100 flight cycles af- ter the Revision 1 date of Re- quirements Bul- letin 757- 57A0073 RB, whichever oc- curs first. Before 6,000 to- tal flight cycles. ACTION 1: Do a general visual inspection of the diagonal brace and diago- nal brace fittings for any crack. Airplanes with no repair found in Condition 21 and the inspections specified in Requirements Bulletin 757- 57A0073 RB Revision 2 have not been done. -Within 3,000 flight cycles af- ter the Original Issue date of Requirements Bulletin 757- 57A0073 RB. ACTION 2: Do inspec- tions for loose fasteners, skin cracks, and shim mi- grations. -Before further flight.Contact The Boeing Company for repair in- structions and do the re- pair. CONDITION 1: ANY CRACK FOUND IN DIAG- ONAL BRACE OR DIAGO- NAL BRACE FITTINGS (a) 1,700 flight cycles.-Repeat general visual in- spection of the diagonal brace and diagonal brace fittings for any crack. CONDITION 2: NO CRACK FOUND IN DIAG- ONAL BRACE OR DIAGO- NAL BRACE FITTINGS (a) -Before further flight.CONDITION 3 (ACTION 1): Install the Upper Link and Upper Link Pins if re- moved. CONDITION 3: NO SHIM MIGRATION, NO SKIN CRACK, AND NO LOOSE FASTENER. 3,000 flight cycles.-CONDITION 3 (ACTION 2): Repeat inspections for loose fasteners, skin cracks, and shim migra- tions. Export Controlled ECCN: 9E991 See page 1 for details Original Issue: July 14, 2017 757-57A0073 RBRevision 3: May 05, 2023 50 of 161 REQUIREMENTS BULLETIN 757-57A0073 ALERTALERT ### Page 51 Group 2-4, 6-8: Table 18: Inspection for loose fasteners, skin cracking, and shim migration at the upper link drag fittings and for cracks in the diagonal brace and diagonal brace fittings Repeat Interval (Not to Exceed) Compliance Time (Whichever Occurs Later) ActionCondition -Before further flight.Do open-hole HFEC in- spection of fastener holes 1-10 for any crack. CONDITION 4: ANY LOOSE FASTENER FOUND ON FASTENERS 1-10. (a) -Before further flight.Do open-hole HFEC in- spection on the loose bolt holes for any crack. CONDITION 5: ANY LOOSE FASTENER FOUND ON FASTENERS 11-18. (a) -Before further flight.Contact The Boeing Company for repair in- structions and do the re- pair. CONDITION 6: MAJOR SHIM MIGRATION FOUND. (a) -Before further flight.CONDITION 7 (OPTION 1): Contact The Boeing Company for repair in- structions and do the re- pair. CONDITION 7: ANY CRACK FOUND IN THE DRAG FITTINGS. (a) -Before further flight.CONDITION 7, OPTION 2 (ACTION 1): Replace any cracked drag fitting with a new part. -Before further flight.CONDITION 7, OPTION 2 (ACTION 2): Install the Upper Link and Upper Link Pins if removed. 3,000 flight cycles.-CONDITION 7, OPTION 2 (ACTION 3): Repeat in- spections for loose fasten- ers, skin cracks, and shim migrations. -Before further flight.Contact The Boeing Company for repair in- structions and do the re- pair. CONDITION 8: ANY CRACK FOUND IN SKIN. (a) Export Controlled ECCN: 9E991 See page 1 for details Original Issue: July 14, 2017 757-57A0073 RBRevision 3: May 05, 2023 51 of 161 REQUIREMENTS BULLETIN 757-57A0073 ALERTALERT ### Page 52 Group 2-4, 6-8: Table 18: Inspection for loose fasteners, skin cracking, and shim migration at the upper link drag fittings and for cracks in the diagonal brace and diagonal brace fittings Repeat Interval (Not to Exceed) Compliance Time (Whichever Occurs Later) ActionCondition -Before further flight.CONDITION 9 (ACTION 1): Install bolts, washers, and nuts for fastener holes where fasteners were removed. CONDITION 9: NO CRACK FOUND IN SKIN AND DRAG FITTINGS DURING OPEN-HOLE HFEC INSPECTION. (a) -Before further flight.CONDITION 9 (ACTION 2): Install the Upper Link and Upper Link Pins if re- moved. 3,000 flight cycles-CONDITION 9 (ACTION 3): Repeat inspections for loose fasteners, skin cracks, and shim migra- tions. -Before further flight.Do a torque check of fas- teners on the affected shim(s). CONDITION 10: MINOR SHIM MIGRATION FOUND IN SKIN PANEL SHIM. (a) -Before further flight.CONDITION 10.1 (AC- TION 1): Trim affected shim to the edge of the fitting. Apply chemical conversion coating on the shim and fillet seal the edge of the drag fitting. CONDITION 10.1: ALL BOLTS PASSED THE TORQUE CHECK. -Before further flight.CONDITION 10.1 (AC- TION 2): Install the Upper Link and Upper Link Pins if removed. 3,000 flight cycles.-CONDITION 10.1 (AC- TION 3): Repeat inspec- tions for loose fasteners, skin cracks, and shim mi- grations. -Before further flight.Contact The Boeing Company for repair in- structions and do the re- pair. CONDITION 10.2: ANY BOLT FAILED THE TORQUE CHECK. Export Controlled ECCN: 9E991 See page 1 for details Original Issue: July 14, 2017 757-57A0073 RBRevision 3: May 05, 2023 52 of 161 REQUIREMENTS BULLETIN 757-57A0073 ALERTALERT ### Page 53 Group 2-4, 6-8: Table 18: Inspection for loose fasteners, skin cracking, and shim migration at the upper link drag fittings and for cracks in the diagonal brace and diagonal brace fittings Repeat Interval (Not to Exceed) Compliance Time (Whichever Occurs Later) ActionCondition -Before further flight.CONDITION 11 (ACTION 1): Trim affected shim to the edge of the fitting. Apply chemical conver- sion coating on the shim and fillet seal the edge of the drag fitting. CONDITION 11: MINOR SHIM MIGRATION FOUND IN SPAR SHIM. (a) -Before further flight.CONDITION 11 (ACTION 2): Install the Upper Link and Upper Link Pins if re- moved. 3,000 flight cycles.-CONDITION 11 (ACTION 3): Repeat inspections for loose fasteners, skin cracks, and shim migra- tions. (a) More than one CONDITION can be applicable on each airplane. Group 1, Configuration 2; Group 2-4; Group 5, Configuration 2; Group 6-8; Group 12-13, Configuration 2: Table 19: Initial inspection and maintenance records check of the wing upper skin looking for existing repairs Repeat Interval (Not to Exceed) Compliance Time (Whichever Occurs Later) ActionCondition -Within 1,400 flight cycles af- ter the Revision 3 date of Re- quirements Bul- letin 757- 57A0073 RB. Before 6,000 to- tal flight cycles. Do a general visual in- spection or maintenance records check of the wing upper skin at the drag fit- ting attachment holes for any existing repair. All Airplanes. -Within 1,400 flight cycles af- ter the Revision 3 date of Re- quirements Bul- letin 757- 57A0073 RB. Before 6,000 to- tal flight cycles. Contact The Boeing Company for alternative inspection(s) of Require- ments Bulletin 757- 57A0073 RB, and do the inspection(s) and applica- ble on-condition action(s). CONDITION 15: ANY EX- ISTING REPAIR FOUND WITHOUT BOEING ORGA- NIZATION DESIGNATION AUTHORIZATION (ODA) APPROVAL. Export Controlled ECCN: 9E991 See page 1 for details Original Issue: July 14, 2017 757-57A0073 RBRevision 3: May 05, 2023 53 of 161 REQUIREMENTS BULLETIN 757-57A0073 ALERTALERT ### Page 54 Group 1, Configuration 2; Group 2-4; Group 5, Configuration 2; Group 6-8; Group 12-13, Configuration 2: Table 19: Initial inspection and maintenance records check of the wing upper skin looking for existing repairs Repeat Interval (Not to Exceed) Compliance Time (Whichever Occurs Later) ActionCondition -Within 1,400 flight cycles af- ter the Revision 3 date of Re- quirements Bul- letin 757- 57A0073 RB. Before 6,000 to- tal flight cycles. Contact The Boeing Company for alternative inspection(s) of Require- ments Bulletin 757- 57A0073 RB, and do the inspection(s) and applica- ble on-condition action(s). CONDITION 16: ANY EX- ISTING REPAIR FOUND WITH BOEING ODA AP- PROVAL DATED BEFORE 03/01/2021. -At the specified times in the FAA form 8100-9 given for the repair. Do the Inspection(s) and on conditions in accor- dance with FAA form 8100-9 given for the re- pair. CONDITION 17: ANY EX- ISTING REPAIR FOUND WITH BOEING ODA AP- PROVAL DATED ON OR AFTER 03/01/21. -Within 1 month after the Revi- sion 3 date of Requirements Bulletin 757- 57A0073 RB. Within 1,300 flight cycles af- ter the last gen- eral visual in- spection of the diagonal brace and diagonal brace fittings for any crack was done. CONDITION 18 (ACTION 1): Do a general visual inspection of the diagonal brace and diagonal brace fittings for any crack. CONDITION 18: ANY EX- ISTING 757-200 SRM 57- 20-01 REPAIR 8, ALTER- NATIVE 1 DONE BEFORE THE REVISION 3 DATE OF 757-57A0073 RB. --Within 3,000 flight cycles af- ter the repair was done. CONDITION 18 (ACTION 2): Do inspections for loose fasteners, skin cracks, and shim migra- tions. CONDITION 18 (ACTION 3): Do open-hole HFEC inspection of fastener holes 1-18 for any crack. (a)(b) -Before further flight.Contact The Boeing Company for repair in- structions and do the re- pair. CONDITION 18.1: ANY CRACK FOUND IN DIAG- ONAL BRACE OR DIAGO- NAL BRACE FITTINGS. (c) 1,300 flight cycles.-Repeat general visual in- spection of the diagonal brace and diagonal brace fittings for any crack. CONDITION 18.2: NO CRACK FOUND IN DIAG- ONAL BRACE OR DIAGO- NAL BRACE FITTINGS. (c) Export Controlled ECCN: 9E991 See page 1 for details Original Issue: July 14, 2017 757-57A0073 RBRevision 3: May 05, 2023 54 of 161 REQUIREMENTS BULLETIN 757-57A0073 ALERTALERT ### Page 55 Group 1, Configuration 2; Group 2-4; Group 5, Configuration 2; Group 6-8; Group 12-13, Configuration 2: Table 19: Initial inspection and maintenance records check of the wing upper skin looking for existing repairs Repeat Interval (Not to Exceed) Compliance Time (Whichever Occurs Later) ActionCondition -Before further flight.CONDITION 18.3 (AC- TION 1): Install the Upper Link and Upper Link Pins if removed. CONDITION 18.3: NO SHIM MIGRATION AND NO WING UPPER SKIN CRACK AND NO LOOSE FASTENER FOUND. 3,000 flight cycles.-CONDITION 18.3 (AC- TION 2): Repeat inspec- tions for loose fasteners, skin cracks, and shim mi- grations. -Before further flight.Do an open-hole HFEC inspection of fastener holes 1-10 for any crack. CONDITION 18.4: ANY LOOSE FASTENER FOUND AT FASTENER LOCATIONS 1-10. (c) -Before further flight.Do open-hole HFEC in- spection on the loose fastener holes for any crack. CONDITION 18.5: ANY LOOSE FASTENER FOUND AT FASTENER LOCATIONS 11-18. (c) -Before further flight.Contact The Boeing Company for repair in- structions and do the re- pair. CONDITION 18.6: MAJOR SHIM MIGRATION FOUND. (c) Export Controlled ECCN: 9E991 See page 1 for details Original Issue: July 14, 2017 757-57A0073 RBRevision 3: May 05, 2023 55 of 161 REQUIREMENTS BULLETIN 757-57A0073 ALERTALERT ### Page 56 Group 1, Configuration 2; Group 2-4; Group 5, Configuration 2; Group 6-8; Group 12-13, Configuration 2: Table 19: Initial inspection and maintenance records check of the wing upper skin looking for existing repairs Repeat Interval (Not to Exceed) Compliance Time (Whichever Occurs Later) ActionCondition -Before further flight.CONDITION 18.7 OP- TION 1: CONDITION 18.7: ANY CRACK FOUND IN THE DRAG FITTINGS. (c) Contact The Boeing Company for repair in- structions and do the re- pair. -Before further flight.CONDITION 18.7 OP- TION 2 (ACTION 1): Replace any cracked drag fitting with a new part. Before further flight.CONDITION 18.7 OP- TION 2 (ACTION 2): Install the Upper Link and Upper Link Pins if re- moved. 3,000 flight cycles.-CONDITION 18.7 OP- TION 2 (ACTION 3): Repeat inspections for loose fasteners, skin cracks, and shim migra- tions. -CONDITION 18.7 OP- TION 2 (ACTION 4): Repeat open-hole HFEC inspection of fastener holes 1-18 for any crack. (a)(b) -Before further flight.Contact The Boeing Company for repair in- structions and do the re- pair. CONDITION 18.8: ANY CRACK FOUND IN SKIN. (c) Export Controlled ECCN: 9E991 See page 1 for details Original Issue: July 14, 2017 757-57A0073 RBRevision 3: May 05, 2023 56 of 161 REQUIREMENTS BULLETIN 757-57A0073 ALERTALERT ### Page 57 Group 1, Configuration 2; Group 2-4; Group 5, Configuration 2; Group 6-8; Group 12-13, Configuration 2: Table 19: Initial inspection and maintenance records check of the wing upper skin looking for existing repairs Repeat Interval (Not to Exceed) Compliance Time (Whichever Occurs Later) ActionCondition -Before further flight.CONDITION 18.9 (AC- TION 1): CONDITION 18.9: NO CRACK FOUND IN SKIN AND DRAG FITTINGS DURING OPEN-HOLE HFEC INSPECTION. Install bolts, washers, and nuts for fastener holes where fasteners were re- moved. -Before further flight.CONDITION 18.9 (AC- TION 2): Install the Upper Link and Upper Link Pins if re- moved. 3,000 flight cycles.-CONDITION 18.9 (AC- TION 3): Repeat inspections for loose fasteners, skin cracks, and shim migra- tions. -CONDITION 18.9 (AC- TION 4): Repeat open-hole HFEC inspection of fastener holes 1-18 for any crack. (a)(b) -Before further flight.Do a torque check of fas- teners on the affected shim(s). CONDITION 18.10: MI- NOR SHIM MIGRATION FOUND IN SKIN PANEL SHIM. (c) Export Controlled ECCN: 9E991 See page 1 for details Original Issue: July 14, 2017 757-57A0073 RBRevision 3: May 05, 2023 57 of 161 REQUIREMENTS BULLETIN 757-57A0073 ALERTALERT ### Page 58 Group 1, Configuration 2; Group 2-4; Group 5, Configuration 2; Group 6-8; Group 12-13, Configuration 2: Table 19: Initial inspection and maintenance records check of the wing upper skin looking for existing repairs Repeat Interval (Not to Exceed) Compliance Time (Whichever Occurs Later) ActionCondition -Before further flight.CONDITION 18.10.1 (ACTION 1): CONDITION 18.10.1: ALL BOLTS PASSED THE TORQUE CHECK. Trim affected shim to the edge of the fitting. Apply chemical conversion coating on the shim and fillet seal the edge of the drag fitting. -Before further flight.CONDITION 18.10.1 (ACTION 2): Install the Upper Link and Upper Link Pins if re- moved. 3,000 flight cycles.-CONDITION 18.10.1 (ACTION 3): Repeat inspections for loose fasteners, skin cracks, and shim migra- tions. -Before further flight.Contact The Boeing Company for repair in- structions and do the re- pair. CONDITION 18.10.2: ANY BOLT FAILED THE TORQUE CHECK. Export Controlled ECCN: 9E991 See page 1 for details Original Issue: July 14, 2017 757-57A0073 RBRevision 3: May 05, 2023 58 of 161 REQUIREMENTS BULLETIN 757-57A0073 ALERTALERT ### Page 59 Group 1, Configuration 2; Group 2-4; Group 5, Configuration 2; Group 6-8; Group 12-13, Configuration 2: Table 19: Initial inspection and maintenance records check of the wing upper skin looking for existing repairs Repeat Interval (Not to Exceed) Compliance Time (Whichever Occurs Later) ActionCondition -Before further flight.CONDITION 18.11 (AC- TION 1): CONDITION 18.11: MI- NOR SHIM MIGRATION FOUND IN SPAR SHIM. Trim affected shim to the edge of the fitting. Apply chemical conversion coating on the shim and fillet seal the edge of the drag fitting. -Before further flight.CONDITION 18.11 (AC- TION 2): Install the Upper Link and Upper Link Pins if re- moved. 3,000 flight cycles.-CONDITION 18.11 (AC- TION 3): Repeat inspections for loose fasteners, skin cracks, and shim migra- tions. -Within 650 flight cycles after the last general visual inspection of the diagonal brace and diagonal brace fittings for any crack was done. CONDITION 19 (ACTION 1): Do a general visual in- spection of the diagonal brace and diagonal brace fittings for any crack. CONDITION 19: ANY EX- ISTING 757-200 SRM 57- 20-01 REPAIR 8, ALTER- NATIVE 2 DONE BEFORE THE REVISION 3 DATE OF 757-57A0073 RB. --Within 3,000 flight cycles af- ter the repair was done. CONDITION 19 (ACTION 2): Do inspections for loose fasteners, skin cracks, and shim migrations. CONDITION 19 (ACTION 3): Do open-hole HFEC in- spection of fastener holes 1-18 for any crack. (a)(b) CONDITION 19 (ACTION 4): Do ultrasonic inspection of upper wing skin at re- pair location for any crack. Export Controlled ECCN: 9E991 See page 1 for details Original Issue: July 14, 2017 757-57A0073 RBRevision 3: May 05, 2023 59 of 161 REQUIREMENTS BULLETIN 757-57A0073 ALERTALERT ### Page 60 Group 1, Configuration 2; Group 2-4; Group 5, Configuration 2; Group 6-8; Group 12-13, Configuration 2: Table 19: Initial inspection and maintenance records check of the wing upper skin looking for existing repairs Repeat Interval (Not to Exceed) Compliance Time (Whichever Occurs Later) ActionCondition -Before further flight.Contact The Boeing Company for repair in- structions and do the re- pair. CONDITION 19.1: ANY CRACK FOUND IN DIAG- ONAL BRACE OR DIAGO- NAL BRACE FITTINGS. 650 flight cycles.-Repeat general visual in- spection of the diagonal brace and diagonal brace fittings for any crack. CONDITION 19.2: NO CRACK FOUND IN DIAG- ONAL BRACE OR DIAGO- NAL BRACE FITTINGS. -Before further flight.CONDITION 19.3 (AC- TION 1): Install the Upper Link and Upper Link Pins if removed. CONDITION 19.3: NO SHIM MIGRATION, NO SKIN CRACK, AND NO LOOSE FASTENER. 3,000 flight cycles.-CONDITION 19.3 (AC- TION 2): Repeat inspections for loose fasteners, skin cracks, and shim migra- tions. -Before further flight.Do open-hole HFEC in- spection of fastener holes 1-10 for any crack. CONDITION 19.4: ANY LOOSE FASTENER FOUND ON FASTENERS 1-10. (c) -Before further flight.Do open-hole HFEC in- spection on any loose fastener hole for any crack. CONDITION 19.5: ANY LOOSE FASTENER FOUND ON FASTENERS 11-18. (c) -Before further flight.Contact The Boeing Company for repair in- structions and do the re- pair. CONDITION 19.6: MAJOR SHIM MIGRATION FOUND. (c) Export Controlled ECCN: 9E991 See page 1 for details Original Issue: July 14, 2017 757-57A0073 RBRevision 3: May 05, 2023 60 of 161 REQUIREMENTS BULLETIN 757-57A0073 ALERTALERT The text continues at https://openairdocs.org/service-documents/boeing/757-57a0073-rb/file/47e68ea01e5d.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.