# Boeing Alert Requirements Bulletin 777-57A0122 RB: No revision named - Rights: © The Boeing Company. Filed by the FAA in regulations.gov docket FAA-2022-0154; AD 2022-18-11 incorporates this document by reference. Not covered by OpenAirDocs’ CC0 dedication. - Document: [Boeing Alert Requirements Bulletin 777-57A0122 RB](https://openairdocs.org/service-documents/boeing/777-57a0122-rb.md) - Title as filed: 777-57A0122 RB - Pages: 968 - PDF: https://openairdocs.org/files/sha256/db/b3/dbb3e2845441e82c3336cd80822fb9d5df829907bbf8a824b7c2bd93ccfd2f4e - Page: https://openairdocs.org/service-documents/boeing/777-57a0122-rb/file/dbb3e2845441 ## 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 777 Requirements Bulletin ALERT Number: 777-57A0122 RB Original Issue: October 08, 2021 ATA System: 5710 5330 SUBJECT: WINGS - Center Wing - Ring Chord, Front Spar Lower Chord and Front Spar Web - Inspection and Modification Export of this technology is controlled under the United States Export Administration Regulations (EAR) (15 CFR 300-774). An export license may be required before it is used for development, production or use by foreign persons from specific countries. The controller of this data has the individual responsibility to abide by all export laws. 9E991ECCN: Copyright © 2021 Boeing. Unpublished Work. All Rights Reserved. Treatment of this document and its content is governed by contract with Boeing. Rights to use this document are licensed on a per aircraft basis and such rights may not be transferable. For more information, contact The Boeing Company. Boeing, the Boeing signature, the Boeing symbol, 707, 717, 727, 737, 747, 757, 767, 777, 787, Dreamliner, BBJ, DC-8, DC-9, DC-10, KC-10, KC-46, KDC-10, MD-10, MD-11, MD-80, MD-88, MD-90, P-8, Poseidon and Boeing liveries are all trademarks owned by The Boeing Company; and no trademark license is granted in connection with this document unless provided in writing by Boeing. Original Issue: October 08, 2021 777-57A0122 RB 1 of 968 8.0 ### Page 2 Export Controlled ECCN: 9E991 Copyright © Unpublished Work - See page 1 for details. Original Issue: October 08, 2021 777-57A0122 RB 2 of 968 REQUIREMENTS BULLETIN 777-57A0122 ALERTALERT BLANK PAGE ### Page 3 Table of Contents 1 . E F F E C T I V I T Y ............................................... 1 1 A. Airplanes ............................................... 1 1 B . S p a r e s A f f e c t e d ........................................... 3 1 2. CONCURRENT REQUIREMENTS .................................... 3 1 3 . C O M P L I A N C E ............................................... 3 2 4. APPROVAL ................................................ 1 6 5 5. ACCOMPLISHMENT INSTRUCTIONS ................................. 1 6 7 A. General Information ........................................ 1 6 7 B. Work Instructions .......................................... 1 6 8 FIGURE 1: LEFT SIDE RING CHORD - HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION . 312 FIGURE 2: LEFT SIDE FRONT SPAR LOWER CHORD - HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION [Group 1, Configuration 1-8; Group 2, Configuration 1-8; Group 3, Configuration 1-8; Group 4, Configuration 1-2; Group 5, Configuration 1-8; Group 6, Configuration 1-2; Group 7, Configuration 1-8; Group 8, Configuration 1-8; Group 9, Configuration 1-2] ...... 3 1 4 FIGURE 3: LEFT SIDE FRONT SPAR WEB - HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION [Group 1, Configuration 1-8; Group 2, Configuration 1-8; Group 3, Configuration 1-8; Group 4, Configuration 1-2; Group 5, Configuration 1-8; Group 6, Configuration 1-2; Group 7, Configuration 1-8; Group 8, Configuration 1-8; Group 9, Configuration 1-2] ................ 3 1 7 FIGURE 4: LEFT SIDE FRONT SPAR WEB - HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION [Group 1, Configuration 9-16; Group 2-9] .......................... 3 1 9 FIGURE 5: LEFT SIDE REPAIR ANGLE - HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION [Group 1, Configuration 9-16; Group 2, Configuration 9-16; Group 3, Configuration 9-16; Group 4, Configuration 3-4; Group 5, Configuration 9-16; Group 6, Configuration 3-4; Group 7, Configuration 9-16; Group 8, Configuration 9-16; Group 9, Configuration 2-3] ...... 3 2 2 FIGURE 6: LEFT SIDE FRONT SPAR LOWER CHORD - ULTRASONIC (UT) INSPECTION [Group 2, Configuration 1-8; Group 3, Configuration 1-8; Group 4, Configuration 1-2; Group 5, Configuration 1-8; Group 6, Configuration 1-2; Group 7, Configuration 1-8; Group 8, Configuration 1-8; Group 9, Configuration 1-2] ..................................... 3 2 5 FIGURE 7: LEFT SIDE RING CHORD - ULTRASONIC (UT) INSPECTION [Group 2, Configuration 1-4, 9-12; Group 3, Configuration 1-4, 9-12; Group 4, Configuration 1-2; Group 5-6; Group 7, Configuration 1-4, 9-12; Group 8, Configuration 1-4, 9-12; Group 9, Configuration 1-2] . 328 FIGURE 8: LEFT SIDE REPAIR ANGLE - ULTRASONIC INSPECTION [Group 2, Configuration 9-16; Group 3, Configuration 9-16; Group 4, Configuration 3-4; Group 5, Configuration 9-16; Group 6, Configuration 3-4; Group 7, Configuration 9-16; Group 8, Configuration 9-16; Group 9, Configuration 3-4] ....................................... 3 3 0 FIGURE 9: LEFT SIDE FRONT SPAR LOWER CHORD SEALANT APPLICATION [Group 1, Configuration 1-8; Group 2, Configuration 1-8; Group 3, Configuration 1-8; Group 4, Configuration 1-2; Group 5, Configuration 1-8; Group 6, Configuration 1-2; Group 7, Configuration 1-8; Group 8, Configuration 1-8; Group 9, Configuration 1-2] ....................... 3 3 3 FIGURE 10: LEFT SIDE REPAIR ANGLE SEALANT APPLICATION [Group 1, Configuration 9-16; Group 2 - 9 ] ............................................... 3 3 6 FIGURE 11: RIGHT SIDE RING CHORD - HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION ................................................. 3 3 9 FIGURE 12: RIGHT SIDE FRONT SPAR LOWER CHORD - HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION [Group 1, Configuration 1-2, 5-6, 9-10, 13-14; Group 2, Configuration 1-10, 13-14; Group 3, Configuration 1-10, 13-14; Group 4, Configuration 1-3; Group 5, Configuration 1-3, 5-6, 9-10, 13-14; Group 6, Configuration 1, 3; Group 7, Configuration 1-10, 13-14; Group 8, Configuration 1-10, 13-14; Group 9, Configuration 1-3] ................... 3 4 1 Export Controlled ECCN: 9E991 Copyright © Unpublished Work - See page 1 for details. Original Issue: October 08, 2021 777-57A0122 RB 3 of 968 REQUIREMENTS BULLETIN 777-57A0122 ALERTALERT ### Page 4 FIGURE 13: RIGHT SIDE FRONT SPAR WEB - HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION [Group 1, Configuration 1-2, 5-6, 9-10, 13-14; Group 2, Configuration 1-2, 5-6, 9-10, 13-14; Group 3, Configuration 1-2, 5-6, 9-10, 13-14; Group 4, Configuration 1, 3; Group 5, Configuration 1-2, 5-6, 9-10, 13-14; Group 6, Configuration 1, 3; Group 7, Configuration 1-2, 5-6, 9-10, 13-14; Group 8, Configuration 1-2, 5-6, 9-10, 13-14; Group 9, Configuration 1, 3] ........ 3 4 4 FIGURE 14: RIGHT SIDE FRONT SPAR WEB - HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION [Group 1, Configuration 3-4, 7-8, 11-12, 15-16; Group 2-9] ................. 3 4 6 FIGURE 15: RIGHT SIDE REPAIR ANGLE - HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION [Group 1, Configuration 3-4, 7-8, 11-12, 15-16; Group 2, Configuration 3-4, 7-8, 11-12, 15-16; Group 3, Configuration 3-4, 7-8, 11-12, 15-16; Group 4, Configuration 2, 4; Group 5, Configuration 3-4, 7-8, 11-12, 15-16; Group 6, Configuration 2, 4; Group 7, Configuration 3-4, 7-8, 11-12, 15-16; Group 8, Configuration 3-4, 7-8, 11-12, 15-16; Group 9, Configuration 2, 4] .... 3 4 9 FIGURE 16: RIGHT SIDE FRONT SPAR LOWER CHORD - ULTRASONIC (UT) INSPECTION [Group 2, Configuration 1-2, 5-6, 9-10, 13-14; Group 3, Configuration 1-2, 5-6, 9-10, 13-14; Group 4, Configuration 1, 3; Group 5, Configuration 1-2, 5-6, 9-10, 13-14; Group 6, Configuration 1, 3; Group 7, Configuration 1-2, 5-6, 9-10, 13-14; Group 8, Configuration 1-2, 5-6, 9-10, 13-14; Group 9, Configuration 1, 3] ..................................... 3 5 2 FIGURE 17: RIGHT SIDE RING CHORD - ULTRASONIC INSPECTION [Group 2, Configuration 1, 3, 5, 7, 9, 11, 13, 15; Group 3, Configuration 1, 3, 5, 7, 9, 11, 13, 15; Group 4, Configuration 1, 3; Group 5, Configuration 1-2, 5-6, 9-10, 13-14; Group 6, Configuration 1, 3; Group 7, Configuration 1, 3, 5, 7, 9, 11, 13, 15; Group 8, Configuration 1, 3, 5, 7, 9, 11, 13, 15; Group 9, Configuration 1, 3] ................................................. 3 5 5 FIGURE 18: RIGHT SIDE REPAIR ANGLE - ULTRASONIC INSPECTION [Group 2, Configuration 3-4, 7-8, 11-12, 15-16; Group 3, Configuration 3-4, 7-8, 11-12, 15-16; Group 4, Configuration 2, 4; Group 5, Configuration 3-4, 7-8, 11-12, 15-16; Group 6, Configuration 2, 4; Group 7, Configuration 3-4, 7-8, 11-12, 15-16; Group 8, Configuration 3-4, 7-8, 11-12, 15-16; Group 9, Configuration 2, 4] ................................................. 3 5 7 FIGURE 19: RIGHT SIDE FRONT SPAR LOWER CHORD SEALANT APPLICATION [Group 1, Configuration 1-2, 5-6, 9-10, 13-14; Group 2, Configuration 1-2, 5-6, 9-10, 13-14; Group 3, Configuration 1-2, 5-6, 9-10, 13-14; Group 4, Configuration 1, 3; Group 5, Configuration 1-2, 6-7, 9-10, 13-14; Group 6, Configuration 1, 3; Group 7, Configuration 1-2, 5-6, 9-10, 13-14; Group 8, Configuration 1-2, 5-6, 9-10, 13-14; Group 9, Configuration 1, 3] ..................... 3 6 0 FIGURE 20: RIGHT SIDE REPAIR ANGLE SEALANT APPLICATION [Group 1, Configuration 3-4, 7-8, 11-12, 15-16; Group 2; Group 3, Configuration 3-4, 7-8, 11-12, 15-16; Group 4, Configuration 2, 4; Group 5, Configuration 3-4, 7-8, 11-12, 15-16; Group 6, Configuration 2, 4; Group 7, Configuration 3-4, 7-8, 11-12, 15-16; Group 8, Configuration 3-4, 7-8, 12-13, 15-16; Group 9, Configuration 2 , 4 ] .............................................. 3 6 3 FIGURE 21: LEFT SIDE UNDERWING LONGERON REMOVAL [Group 2, Configuration 1-4; Group 3, Configuration 1-4] ....................................... 3 6 7 FIGURE 22: LEFT SIDE UNDERWING LONGERON REMOVAL [Group 2, Configuration 5-8; Group 3, Configuration 5-8; Group 4, Configuration 1-2] ....................... 3 7 0 FIGURE 23: LEFT SIDE UNDERWING LONGERON REMOVAL [Group 5, Configuration 1-4] .... 3 7 3 FIGURE 24: LEFT SIDE UNDERWING LONGERON REMOVAL [Group 5, Configuration 5-8; Group 6, Configuration 1-2] ....................................... 3 7 6 FIGURE 25: LEFT SIDE UNDERWING LONGERON REMOVAL [Group 7, Configuration 1-4; Group 8, Configuration 1-4] ....................................... 3 7 9 FIGURE 26: LEFT SIDE UNDERWING LONGERON REMOVAL [Group 7, Configuration 5-8; Group 8, Configuration 5-8; Group 9, Configuration 1-2] ....................... 3 8 2 FIGURE 27: LEFT SIDE BRACKETS REMOVAL [Group 2, Configuration 1-4] ............. 3 8 5 FIGURE 28: LEFT SIDE BRACKETS REMOVAL [Group 3, Configuration 1-4] ............. 3 8 8 FIGURE 29: LEFT SIDE BRACKETS REMOVAL [Group 2, Configuration 5-8] ............. 3 9 1 Export Controlled ECCN: 9E991 Copyright © Unpublished Work - See page 1 for details. Original Issue: October 08, 2021 777-57A0122 RB 4 of 968 REQUIREMENTS BULLETIN 777-57A0122 ALERTALERT ### Page 5 FIGURE 30: LEFT SIDE BRACKETS REMOVAL [Group 3, Configuration 5-8; Group 4, Configuration 1-2] ................................................. 3 9 4 FIGURE 31: LEFT SIDE BRACKETS REMOVAL [Group 5, Configuration 1-4] ............. 3 9 7 FIGURE 32: LEFT SIDE BRACKETS REMOVAL [Group 5, Configuration 5-8; Group 6, Configuration 1-2] ................................................. 4 0 0 FIGURE 33: LEFT SIDE BRACKETS REMOVAL [Group 7, Configuration 1-4; Group 8, Configuration 1-4] ................................................. 4 0 3 FIGURE 34: LEFT SIDE BRACKETS REMOVAL [Group 7, Configuration 5-8; Group 8, Configuration 5-8; Group 9, Configuration 1-2] .................................. 4 0 6 FIGURE 35: LEFT SIDE FUSELAGE UNDERWING LONGERON FASTENER REMOVAL AND STRINGER S-37L END FITTING REMOVAL AND OPEN HOLE INSPECTION [Group 2, Configuration 1-4] ................................................. 4 0 9 FIGURE 36: LEFT SIDE FUSELAGE UNDERWING LONGERON FASTENER REMOVAL AND OPEN HOLE INSPECTION [Group 3, Configuration 1-4] ......................... 4 1 2 FIGURE 37: LEFT SIDE FUSELAGE UNDERWING LONGERON FASTENER REMOVAL AND OPEN HOLE INSPECTION [Group 5, Configuration 1-4] ......................... 4 1 5 FIGURE 38: LEFT SIDE FUSELAGE UNDERWING LONGERON FASTENER REMOVAL AND OPEN HOLE INSPECTION [Group 7, Configuration 1-4; Group 8, Configuration 1-4] .......... 4 1 8 FIGURE 39: LEFT SIDE WING BOTTOM SKIN AT UNDERWING LONGERON LOCATION INSPECTION [Group 2, Configuration 1-8; Group 3, Configuration 1-8; Group 4, Configuration 1-2; Group 5, Configuration 1-8; Group 6, Configuration 1-2; Group 7, Configuration 1-8; Group 8, Configuration 1-8; Group 9, Configuration 1-2] ............................... 4 2 1 FIGURE 40: LEFT SIDE FUSELAGE SKIN AT UNDERWING LONGERON LOCATION INSPECTION [Group 2, Configuration 1-4] ..................................... 4 2 5 FIGURE 41: LEFT SIDE FUSELAGE SKIN AT UNDERWING LONGERON LOCATION INSPECTION [Group 3, Configuration 1-4; Group 5, Configuration 1-4] ...................... 4 3 0 FIGURE 42: LEFT SIDE FUSELAGE SKIN AT UNDERWING LONGERON LOCATION INSPECTION [Group 7, Configuration 1-4] ..................................... 4 3 5 FIGURE 43: LEFT SIDE FUSELAGE SKIN AT UNDERWING LONGERON LOCATION INSPECTION [Group 8, Configuration 1-4] ..................................... 4 4 0 FIGURE 44: LEFT SIDE UNDERWING LONGERON FUSELAGE SKIN DOUBLER INSPECTION [Group 2, Configuration 5-8; Group 3, Configuration 5-8; Group 4, Configuration 1-2; Group 5, Configuration 5-8; Group 6, Configuration 1-2; Group 7, Configuration 5-8; Group 8, Configuration 5-8; Group 9, Configuration 1-2] ..................................... 4 4 5 FIGURE 45: STRINGER S-37L END FITTING PREPARATION [Group 2, Configuration 1-4] ..... 4 4 9 FIGURE 46: LEFT SIDE FRONT SPAR LOWER CHORD FASTENER REMOVAL [Group 2, Configuration 1-4; Group 3, Configuration 1-4; Group 5, Configuration 1-4; Group 7, Configuration 1-4; Group 8, Configuration 1-4] ..................................... 4 5 2 FIGURE 47: LEFT SIDE FRONT SPAR LOWER CHORD FASTENER REMOVAL [Group 2, Configuration 5-8; Group 3, Configuration 5-8; Group 4, Configuration 1-2; Group 5, Configuration 5-8; Group 6, Configuration 1-2; Group 7, Configuration 5-8; Group 8, Configuration 5-8; Group 9, Configuration 1-2] ....................................... 4 5 6 FIGURE 48: LEFT SIDE DOUBLER AFT EDGE BLEND [Group 2, Configuration 5-8; Group 3, Configuration 5-8; Group 4, Configuration 1-2; Group 5, Configuration 5-8; Group 6, Configuration 1-2; Group 7, Configuration 5-8; Group 8, Configuration 5-8; Group 9, Configuration 1-2] ...... 4 6 1 FIGURE 49: LEFT SIDE FRONT SPAR LOWER CHORD PREPARATION [Group 2, Configuration 1-8; Group 3, Configuration 1-8; Group 4, Configuration 1-2; Group 5, Configuration 1-8; Group 6, Configuration 1-2; Group 7, Configuration 1-8; Group 8, Configuration 1-8; Group 9, Configuration 1 - 2 ] ............................................... 4 6 4 Export Controlled ECCN: 9E991 Copyright © Unpublished Work - See page 1 for details. Original Issue: October 08, 2021 777-57A0122 RB 5 of 968 REQUIREMENTS BULLETIN 777-57A0122 ALERTALERT ### Page 6 FIGURE 50: LEFT SIDE FRONT SPAR LOWER CHORD FILLERS PREPARATION [Group 2, Configuration 1-8; Group 3, Configuration 1-8; Group 4, Configuration 1-2; Group 7, Configuration 1-8; Group 8, Configuration 1-8; Group 9, Configuration 1-2] ...................... 4 6 9 FIGURE 51: LEFT SIDE FRONT SPAR LOWER CHORD FILLERS PREPARATION [Group 5, Configuration 1-8; Group 6, Configuration 1-2] ............................... 4 7 4 FIGURE 52: LEFT SIDE FRONT SPAR LOWER CHORD REPAIR ANGLE PREPARATION [Group 2, Configuration 1-4; Group 3, Configuration 1-4; Group 5, Configuration 1-4; Group 7, Configuration 1-4; Group 8, Configuration 1-4] ............................... 4 7 9 FIGURE 53: LEFT SIDE FRONT SPAR LOWER CHORD REPAIR ANGLE PREPARATION [Group 2, Configuration 5-8; Group 3, Configuration 5-8; Group 4, Configuration 1-2; Group 5, Configuration 5-8; Group 6, Configuration 1-2; Group 7, Configuration 5-8; Group 8, Configuration 5-8; Group 9, Configuration 1-2] ..................................... 4 8 4 FIGURE 54: LEFT SIDE FRONT SPAR LOWER CHORD MODIFICATION INSTALLATION [Group 2, Configuration 1-4; Group 3, Configuration 1-4; Group 7, Configuration 1-4; Group 8, Configuration 1 - 4 ] ............................................... 4 9 0 FIGURE 55: LEFT SIDE FRONT SPAR LOWER CHORD MODIFICATION INSTALLATION [Group 2, Configuration 5-8; Group 3, Configuration 5-8; Group 4, Configuration 1-2; Group 7, Configuration 5-8; Group 8, Configuration 5-8; Group 9, Configuration 1-2] ................ 4 9 7 FIGURE 56: LEFT SIDE FRONT SPAR LOWER CHORD MODIFICATION INSTALLATION [Group 5, Configuration 1-4] ....................................... 5 0 4 FIGURE 57: LEFT SIDE FRONT SPAR LOWER CHORD MODIFICATION INSTALLATION [Group 5, Configuration 5-8; Group 6, Configuration 1-2] ....................... 5 1 1 FIGURE 58: LEFT SIDE FUSELAGE SKIN REPAIR PREPARATION [Group 2, Configuration 1-4] . . 518 FIGURE 59: LEFT SIDE FUSELAGE SKIN REPAIR PREPARATION [Group 3, Configuration 1-4; Group 5, Configuration 1-4] ....................................... 5 2 1 FIGURE 60: LEFT SIDE FUSELAGE SKIN REPAIR PREPARATION [Group 7, Configuration 1-4] . . 524 FIGURE 61: LEFT SIDE FUSELAGE SKIN REPAIR PREPARATION [Group 8, Configuration 1-4] . . 527 FIGURE 62: LEFT SIDE DOUBLER AND REPAIR FILLER INSTALLATION [Group 2, Configuration 1-4] ................................................. 5 3 0 FIGURE 63: LEFT SIDE DOUBLER AND REPAIR FILLER INSTALLATION [Group 3, Configuration 1-4] ................................................. 5 3 6 FIGURE 64: LEFT SIDE DOUBLER AND REPAIR FILLER INSTALLATION [Group 5, Configuration 1-4] ................................................. 5 4 2 FIGURE 65: LEFT SIDE DOUBLER AND REPAIR FILLER INSTALLATION [Group 7, Configuration 1-4] ................................................. 5 4 8 FIGURE 66: LEFT SIDE DOUBLER AND REPAIR FILLER INSTALLATION [Group 8, Configuration 1-4] ................................................. 5 5 3 FIGURE 67: LEFT SIDE DOUBLER INSTALLATION [Group 2, Configuration 1-4] ........... 5 5 8 FIGURE 68: LEFT SIDE DOUBLER INSTALLATION [Group 3, Configuration 1-4] ........... 5 6 4 FIGURE 69: LEFT SIDE DOUBLER INSTALLATION [Group 5, Configuration 1-4] ........... 5 6 9 FIGURE 70: LEFT SIDE DOUBLER INSTALLATION [Group 7, Configuration 1-4] ........... 5 7 4 FIGURE 71: LEFT SIDE DOUBLER INSTALLATION [Group 8, Configuration 1-4] ........... 5 7 9 FIGURE 72: LEFT SIDE UNDERWING LONGERON INSTALLATION [Group 2, Configuration 1-4] . . 584 FIGURE 73: LEFT SIDE UNDERWING LONGERON INSTALLATION [Group 3, Configuration 1-4; Group 5, Configuration 1-4] ....................................... 5 8 9 FIGURE 74: LEFT SIDE UNDERWING LONGERON INSTALLATION [Group 4, Configuration 1-2; Group 6, Configuration 1-2] ....................................... 5 9 5 FIGURE 75: LEFT SIDE UNDERWING LONGERON INSTALLATION [Group 2, Configuration 5-8; Group 3, Configuration 5-8; Group 5, Configuration 5-8] ....................... 6 0 5 Export Controlled ECCN: 9E991 Copyright © Unpublished Work - See page 1 for details. Original Issue: October 08, 2021 777-57A0122 RB 6 of 968 REQUIREMENTS BULLETIN 777-57A0122 ALERTALERT ### Page 7 FIGURE 76: LEFT SIDE UNDERWING LONGERON INSTALLATION [Group 7, Configuration 1-4] . . 615 FIGURE 77: LEFT SIDE UNDERWING LONGERON INSTALLATION [Group 7, Configuration 5-8] . . 621 FIGURE 78: LEFT SIDE UNDERWING LONGERON INSTALLATION [Group 8, Configuration 1-4] . . 631 FIGURE 79: LEFT SIDE UNDERWING LONGERON INSTALLATION [Group 9, Configuration 1-2] . . 637 FIGURE 80: LEFT SIDE UNDERWING LONGERON INSTALLATION [Group 8, Configuration 5-8] . . 647 FIGURE 81: LEFT SIDE UNDERWING LONGERON CAP SEAL APPLICATION [Group 2, Configuration 1-8; Group 3, Configuration 1-8; Group 4, Configuration 1-2; Group 5, Configuration 1-8; Group 6, Configuration 1-2] ....................................... 6 5 7 FIGURE 82: LEFT SIDE POST MODIFICATION UNDERWING LONGERON INSPECTION [Group 2, Configuration 1-8; Group 3, Configuration 1-8; Group 5, Configuration 1-8; Group 7, Configuration 1-8; Group 8, Configuration 1-8] ............................... 6 5 9 FIGURE 83: LEFT SIDE POST MODIFICATION FUSELAGE SKIN INSPECTION [Group 2, Configuration 1-8; Group 3, Configuration 1-8; Group 5, Configuration 1-8; Group 7, Configuration 1-8; Group 8, Configuration 1-8] ..................................... 6 6 2 FIGURE 84: RIGHT SIDE UNDERWING LONGERON REMOVAL [Group 2, Configuration 1, 5, 9, 13; Group 3, Configuration 1, 5, 9, 13] .................................. 6 6 5 FIGURE 85: RIGHT SIDE UNDERWING LONGERON REMOVAL [Group 2, Configuration 2, 6, 10, 14; Group 3, Configuration 2, 6, 10, 14; Group 4, Configuration 1, 3] ................. 6 6 8 FIGURE 86: RIGHT SIDE UNDERWING LONGERON REMOVAL [Group 5, Configuration 1, 5, 9, 13] . 671 FIGURE 87: RIGHT SIDE UNDERWING LONGERON REMOVAL [Group 5, Configuration 2, 6, 10, 14; Group 6, Configuration 1, 3] ..................................... 6 7 4 FIGURE 88: RIGHT SIDE UNDERWING LONGERON REMOVAL [Group 7, Configuration 1, 5, 9, 13; Group 8, Configuration 1, 5, 9, 13] .................................. 6 7 7 FIGURE 89: RIGHT SIDE UNDERWING LONGERON REMOVAL [Group 7, Configuration 2, 6, 10, 14; Group 8, Configuration 2, 6, 10, 14; Group 9, Configuration 1, 3] ................. 6 8 0 FIGURE 90: RIGHT SIDE BRACKETS REMOVAL [Group 2, Configuration 1, 5, 9, 13] ........ 6 8 3 FIGURE 91: RIGHT SIDE BRACKETS REMOVAL [Group 3, Configuration 1, 5, 9, 13] ........ 6 8 6 FIGURE 92: RIGHT SIDE BRACKETS REMOVAL [Group 2, Configuration 2, 6, 10, 14] ........ 6 8 9 FIGURE 93: RIGHT SIDE BRACKETS REMOVAL [Group 3, Configuration 2, 6, 10, 14; Group 4, Configuration 1 , 3 ] .............................................. 6 9 2 FIGURE 94: RIGHT SIDE BRACKETS REMOVAL [Group 5, Configuration 1, 5, 9, 13] ........ 6 9 5 FIGURE 95: RIGHT SIDE BRACKETS REMOVAL [Group 5, Configuration 2, 6, 10, 14; Group 6, Configuration 1 , 3 ] .............................................. 6 9 8 FIGURE 96: RIGHT SIDE BRACKETS REMOVAL [Group 7, Configuration 1, 5, 9, 13; Group 8, Configuration 1 , 5 , 9 , 1 3 ] ........................................... 7 0 1 FIGURE 97: RIGHT SIDE BRACKETS REMOVAL [Group 7, Configuration 2, 6, 10, 14; Group 8, Configuration 2, 6, 10, 14; Group 9, Configuration 1, 3] .......................... 7 0 4 FIGURE 98: RIGHT SIDE FUSELAGE UNDERWING LONGERON FASTENER REMOVAL AND STRINGER S-37L END FITTING REMOVAL AND OPEN HOLE INSPECTION [Group 2, Configuration 1, 5 , 9 , 1 3 ] ............................................ 7 0 7 FIGURE 99: RIGHT SIDE FUSELAGE UNDERWING LONGERON FASTENER REMOVAL AND OPEN HOLE INSPECTION [Group 3, Configuration 1, 5, 9, 13] .................. 7 1 0 FIGURE 100: RIGHT SIDE FUSELAGE UNDERWING LONGERON FASTENER REMOVAL AND OPEN HOLE INSPECTION [Group 5, Configuration 1, 5, 9, 13] .................. 7 1 3 FIGURE 101: RIGHT SIDE FUSELAGE UNDERWING LONGERON FASTENER REMOVAL AND OPEN HOLE INSPECTION [Group 7, Configuration 1, 5, 9, 13; Group 8, Configuration 1, 5, 9, 13] ................................................. 7 1 6 FIGURE 102: RIGHT SIDE WING BOTTOM SKIN AT UNDERWING LONGERON LOCATION INSPECTION [Group 2, Configuration 1-2, 5-6, 9-10, 13-14; Group 3, Configuration 1-2, 5-6, 9-10, 13-14; Export Controlled ECCN: 9E991 Copyright © Unpublished Work - See page 1 for details. Original Issue: October 08, 2021 777-57A0122 RB 7 of 968 REQUIREMENTS BULLETIN 777-57A0122 ALERTALERT ### Page 8 Group 5, Configuration 1-2, 5-6, 9-10, 13-14; Group 6, Configuration 1, 3; Group 7, Configuration 1-2, 5-6, 9-10, 13-14; Group 8, Configuration 1-2, 5-6, 9-10, 13-14; Group 9, Configuration 1, 3 ] ................................................ 7 1 9 FIGURE 103: RIGHT SIDE FUSELAGE SKIN AT UNDERWING LONGERON LOCATION INSPECTION [Group 2, Configuration 1, 5, 9, 13] ............................. 7 2 3 FIGURE 104: RIGHT SIDE FUSELAGE SKIN AT UNDERWING LONGERON LOCATION INSPECTION [Group 3, Configuration 1, 5, 9, 13; Group 5, Configuration 1, 5, 9, 13] .......... 7 2 8 FIGURE 105: RIGHT SIDE FUSELAGE SKIN AT UNDERWING LONGERON LOCATION INSPECTION [Group 7, Configuration 1, 5, 9, 13] ............................. 7 3 3 FIGURE 106: RIGHT SIDE FUSELAGE SKIN AT UNDERWING LONGERON LOCATION INSPECTION [Group 8, Configuration 1, 5, 9, 13] ............................. 7 3 8 FIGURE 107: RIGHT SIDE UNDERWING LONGERON FUSELAGE SKIN DOUBLER INSPECTION [Group 2, Configuration 2, 6, 10, 14; Group 3, Configuration 2, 6, 10, 14; Group 4, Configuration 1, 3; Group 5, Configuration 2, 6, 10, 14; Group 6, Configuration 1, 3; Group 7, Configuration 2, 6, 10, 14; Group 8, Configuration 2, 6, 10, 14; Group 9, Configuration 1, 3] ......... 7 4 3 FIGURE 108: STRINGER S-37R END FITTING PREPARATION [Group 2, Configuration 1, 5, 9, 13] . 747 FIGURE 109: RIGHT SIDE FRONT SPAR LOWER CHORD FASTENER REMOVAL [Group 2, Configuration 1, 5, 9, 13; Group 3, Configuration 1, 5, 9, 13; Group 5, Configuration 1, 5, 9, 13; Group 7, Configuration 1, 5, 9, 13; Group 8, Configuration 1, 5, 9, 13] ................ 7 5 0 FIGURE 110: RIGHT SIDE FRONT SPAR LOWER CHORD FASTENER REMOVAL [Group 2, Configuration 2, 6, 10, 14; Group 3, Configuration 2, 6, 10, 14; Group 4, Configuration 1, 3; Group 5, Configuration 2, 6, 10, 14; Group 6, Configuration 1, 3; Group 7, Configuration 2, 6, 10, 14; Group 8, Configuration 2, 6, 10, 14; Group 9, Configuration 1, 3] ............. 7 5 4 FIGURE 111: RIGHT SIDE DOUBLER AFT EDGE BLEND [Group 2, Configuration 2, 6, 10, 14; Group 3, Configuration 2, 6, 10, 14; Group 4, Configuration 1, 3; Group 5, Configuration 2, 6, 10, 14; Group 6, Configuration 1, 3; Group 7, Configuration 2, 6, 10, 14; Group 8, Configuration 2, 6, 10, 14; Group 9, Configuration 1, 3] ............................. 7 5 9 FIGURE 112: RIGHT SIDE FRONT SPAR LOWER CHORD PREPARATION [Group 2, Configuration 1-2, 5-6, 9-10, 13-14; Group 3, Configuration 1-2, 5-6, 9-10, 13-14; Group 4, Configuration 1, 3; Group 5, Configuration 1-2, 5-6, 9-10, 13-14; Group 6, Configuration 1, 3; Group 7, Configuration 1-2, 5-6, 9-10, 13-14; Group 8, Configuration 1-2, 5-6, 9-10, 13-14; Group 9, Configuration 1, 3] . 762 FIGURE 113: RIGHT SIDE FRONT SPAR LOWER CHORD FILLERS PREPARATION [Group 2, Configuration 1-2, 5-6, 9-10, 13-14; Group 3, Configuration 1-2, 5-6, 9-10, 13-14; Group 4, Configuration 1, 3; Group 7, Configuration 1-2, 5-6, 9-10, 13-14; Group 8, Configuration 1-2, 5-6, 9-10, 13-14; Group 9, Configuration 1, 3] ................................. 7 6 7 FIGURE 114: RIGHT SIDE FRONT SPAR LOWER CHORD FILLERS PREPARATION [Group 5, Configuration 1-2, 5-6, 9-10, 13-14; Group 6, Configuration 1, 3] ..................... 7 7 2 FIGURE 115: RIGHT SIDE FRONT SPAR LOWER CHORD REPAIR ANGLE PREPARATION [Group 2, Configuration 1, 5, 9, 13; Group 3, Configuration 1, 5, 9, 13; Group 5, Configuration 1, 5, 9, 13; Group 7, Configuration 1, 5, 9, 13; Group 8, Configuration 1, 5, 9, 13] ........... 7 7 7 FIGURE 116: RIGHT SIDE FRONT SPAR LOWER CHORD REPAIR ANGLE PREPARATION [Group 2, Configuration 2, 6, 10, 14; Group 3, Configuration 2, 6, 10, 14; Group 4, Configuration 1, 3; Group 5, Configuration 2, 6, 10, 14; Group 6, Configuration 1, 3; Group 7, Configuration 2, 6, 10, 14; Group 8, Configuration 2, 6, 10, 14; Group 9, Configuration 1, 3] ......... 7 8 2 FIGURE 117: RIGHT SIDE FRONT SPAR LOWER CHORD MODIFICATION INSTALLATION [Group 2, Configuration 1, 5, 9, 13; Group 3, Configuration 1, 5, 9, 13; Group 7, Configuration 1, 5, 9, 13; Group 8, Configuration 1, 5, 9, 13] .............................. 7 8 8 FIGURE 118: RIGHT SIDE FRONT SPAR LOWER CHORD MODIFICATION INSTALLATION [Group 2, Configuration 2, 6, 10, 14; Group 3, Configuration 2, 6, 10, 14; Group 4, Configuration 1, 3; Group 7, Configuration 2, 6, 10, 14; Group 8, Configuration 2, 6, 10, 14; Group 9, Configuration 1 , 3 ] .............................................. 7 9 5 Export Controlled ECCN: 9E991 Copyright © Unpublished Work - See page 1 for details. Original Issue: October 08, 2021 777-57A0122 RB 8 of 968 REQUIREMENTS BULLETIN 777-57A0122 ALERTALERT ### Page 9 FIGURE 119: RIGHT SIDE FRONT SPAR LOWER CHORD MODIFICATION INSTALLATION [Group 5, Configuration 1, 5, 9, 13] ................................... 8 0 2 FIGURE 120: RIGHT SIDE FRONT SPAR LOWER CHORD MODIFICATION INSTALLATION [Group 5, Configuration 2, 6, 10, 14; Group 6, Configuration 1, 3] ................... 8 0 9 FIGURE 121: RIGHT SIDE FUSELAGE SKIN REPAIR PREPARATION [Group 2, Configuration 1, 5, 9, 13] ................................................. 8 1 6 FIGURE 122: RIGHT SIDE FUSELAGE SKIN REPAIR PREPARATION [Group 3, Configuration 1, 5, 9, 13; Group 5, Configuration 1, 5, 9, 13] .............................. 8 1 9 FIGURE 123: RIGHT SIDE FUSELAGE SKIN REPAIR PREPARATION [Group 7, Configuration 1, 5, 9, 13] ................................................. 8 2 2 FIGURE 124: RIGHT SIDE FUSELAGE SKIN REPAIR PREPARATION [Group 8, Configuration 1, 5, 9, 13] ................................................. 8 2 5 FIGURE 125: RIGHT SIDE DOUBLER AND REPAIR FILLER INSTALLATION [Group 2, Configuration 1, 5, 9 , 1 3 ] .............................................. 8 2 8 FIGURE 126: RIGHT SIDE DOUBLER AND REPAIR FILLER INSTALLATION [Group 3, Configuration 1, 5, 9 , 1 3 ] .............................................. 8 3 4 FIGURE 127: RIGHT SIDE DOUBLER AND REPAIR FILLER INSTALLATION [Group 5, Configuration 1, 5, 9 , 1 3 ] .............................................. 8 4 0 FIGURE 128: RIGHT SIDE DOUBLER AND REPAIR FILLER INSTALLATION [Group 7, Configuration 1, 5, 9 , 1 3 ] .............................................. 8 4 6 FIGURE 129: RIGHT SIDE DOUBLER AND REPAIR FILLER INSTALLATION [Group 8, Configuration 1, 5, 9 , 1 3 ] .............................................. 8 5 2 FIGURE 130: RIGHT SIDE DOUBLER INSTALLATION [Group 2, Configuration 1, 5, 9, 13] ...... 8 5 8 FIGURE 131: RIGHT SIDE DOUBLER INSTALLATION [Group 3, Configuration 1, 5, 9, 13] ...... 8 6 4 FIGURE 132: RIGHT SIDE DOUBLER INSTALLATION [Group 5, Configuration 1, 5, 9, 13] ...... 8 7 0 FIGURE 133: RIGHT SIDE DOUBLER INSTALLATION [Group 7, Configuration 1, 5, 9, 13] ...... 8 7 6 FIGURE 134: RIGHT SIDE DOUBLER INSTALLATION [Group 8, Configuration 1, 5, 9, 13] ...... 8 8 2 FIGURE 135: RIGHT SIDE UNDERWING LONGERON INSTALLATION [Group 2, Configuration 1, 5, 9, 13] ................................................. 8 8 8 FIGURE 136: RIGHT SIDE UNDERWING LONGERON INSTALLATION [Group 3, Configuration 1, 5, 9, 13; Group 5, Configuration 1, 5, 9, 13] .............................. 8 9 3 FIGURE 137: RIGHT SIDE UNDERWING LONGERON INSTALLATION [Group 4, Configuration 1, 3; Group 6, Configuration 1, 3] ..................................... 8 9 9 FIGURE 138: RIGHT SIDE UNDERWING LONGERON INSTALLATION [Group 2, Configuration 2, 6, 10, 14; Group 3, Configuration 2, 6, 10, 14; Group 5, Configuration 2, 6, 10, 14] ......... 9 0 9 FIGURE 139: RIGHT SIDE UNDERWING LONGERON INSTALLATION [Group 7, Configuration 1, 5, 9, 13] ................................................. 9 1 9 FIGURE 140: RIGHT SIDE UNDERWING LONGERON INSTALLATION [Group 7, Configuration 2, 6, 10, 14] ................................................. 9 2 5 FIGURE 141: RIGHT SIDE UNDERWING LONGERON INSTALLATION [Group 8, Configuration 1, 5, 9, 13] ................................................. 9 3 5 FIGURE 142: RIGHT SIDE UNDERWING LONGERON INSTALLATION [Group 9, Configuration 1, 3] . 941 FIGURE 143: RIGHT SIDE UNDERWING LONGERON INSTALLATION [Group 8, Configuration 2, 6, 10, 14] ................................................. 9 5 1 FIGURE 144: RIGHT SIDE UNDERWING LONGERON CAP SEAL APPLICATION [Group 2, Configuration 1-2, 5-6, 9-10, 13-14; Group 3, Configuration 1-2, 5-6, 9-10, 13-14; Group 4, Configuration 1, 3; Group 5, Configuration 1-2, 5-6, 9-10, 13-14; Group 6, Configuration 1, 3] ....... 9 6 1 FIGURE 145: RIGHT SIDE POST MODIFICATION UNDERWING LONGERON INSPECTION [Group 2, Configuration 1-2, 5-6, 9-10, 13-14; Group 3, Configuration 1-2, 5-6, 9-10, 13-14; Group 5, Export Controlled ECCN: 9E991 Copyright © Unpublished Work - See page 1 for details. Original Issue: October 08, 2021 777-57A0122 RB 9 of 968 REQUIREMENTS BULLETIN 777-57A0122 ALERTALERT ### Page 10 Configuration 1-2, 5-6, 9-10, 13-14; Group 7, Configuration 1-2, 5-6, 9-10, 13-14; Group 8, Configuration 1-2, 5-6, 9-10, 13-14] ............................. 9 6 3 FIGURE 146: RIGHT SIDE POST MODIFICATION FUSELAGE SKIN INSPECTION [Group 2, Configuration 1-2, 5-6, 9-10, 13-14; Group 3, Configuration 1-2, 5-6, 9-10, 13-14; Group 5, Configuration 1-2, 5-6, 9-10, 13-14; Group 7, Configuration 1-2, 5-6, 9-10, 13-14; Group 8, Configuration 1-2, 5-6, 9 - 1 0 , 1 3 - 1 4 ] .......................................... 9 6 6 Export Controlled ECCN: 9E991 Copyright © Unpublished Work - See page 1 for details. Original Issue: October 08, 2021 777-57A0122 RB 10 of 968 REQUIREMENTS BULLETIN 777-57A0122 ALERTALERT ### Page 11 Commercial Airplanes 777 Requirements Bulletin ALERT Number: 777-57A0122 RB Original Issue: October 08, 2021 ATA System: 5710 5330 SUBJECT: WINGS - Center Wing - Ring Chord, Front Spar Lower Chord and Front Spar Web - Inspection and Modification 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 777-200, 777-200LR, 777-300, 777-300ER, 777F Airplane(s), line number(s) 41, 43, 47, 49, 52-67, 69-71, 73-74, 76, 78, 80, 82-88, 90-94, 96-99, 101-106, 108-112, 114-130, 132-133, 135-136, 138-140, 142-145, 147-158, 160-167, 169-172, 174-178, 180-212, 215-239, 241-263, 265-279, 281, 283-289, 291-292, 294, 298-337, 339-343, 345-348, 350-436, 438-481, 483-494, 496-506, 508, 510-522, 524-634, 636-1566, 1568-1573, 1575-1580, 1582-1586, 1588-1604, 1606-1610, 1612-1614, 1616-1619, 1621-1623, 1625-1628, 1630-1632, 1634-1637, 1639-1641, 1643-1646, 1648-1650, 1652-1655, 1657-1658, 1660-1667, 1669, 1671, 1673, 1675-1676, 1678-1679, 1681, 1683-1684, 1686-1687, 1689-1712, 1714-1715, 1718-1719, 1721-1722 in 9 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. NOTE: The Variable Number table below includes all affected airplanes up to Line Number 1722. Affected airplanes after Line Number 1722 will be added to the service bulletin's MyBoeingFleet.com (MBF) "get effectivity" result when they are added to the MBF Fleet Profile Page. Export Controlled ECCN: 9E991 Copyright © Unpublished Work - See page 1 for details. Original Issue: October 08, 2021 777-57A0122 RB 11 of 968 ### Page 12 DESCRIPTIONCONFIGURATIONGROUP 777-200 and 777-300 Airplanes.- 1 777-200 and 777-300 Airplanes with left and right side Front Spar Lower Chord (FSLC) that have not been repaired in accordance with Structural Repair Manual (SRM) 57-10-10 or similar Boeing ODA approved repair and left and right Under Wing Longeron (UWL) that has not been modified in accordance with 777-53-0084 or 777-53-0087. 1 777-200 and 777-300 Airplanes with right side Under Wing Longeron (UWL) only modified in accordance with Service Bulletin (SB) 777-53-0084 or SB 777-53-0087, and left and right side Front Spar Lower Chord (FSLC) that have not been repaired in accordance with Structural Repair Manual (SRM) 57-10-10 or similar Boeing ODA approved repair. 2 777-200 and 777-300 Airplanes with right side Front Spar Lower Chord (FSLC) only repaired in accordance with Structural Repair Manual (SRM) 57-10-10 or similar Boeing ODA approved repair, and left and right Under Wing Longeron (UWL) that has not been modified in accordance with 777-53-0084 or 777-53-0087. 3 777-200 and 777-300 Airplanes with right side Front Spar Lower Chord (FSLC) only repaired in accordance with Structural Repair Manual (SRM) 57-10-10 or similar Boeing ODA approved repair and right side Under Wing Longeron (UWL) only modified in accordance with Service Bulletin (SB) 777-53-0084 or SB 777-53-0087. 4 777-200 and 777-300 Airplanes with left side Under Wing Longeron (UWL) only modified in accordance with Service Bulletin (SB) 777-53-0084 or SB 777-53-0087, and left and right side Front Spar Lower Chord (FSLC) that have not been repaired in accordance with Structural Repair Manual (SRM) 57-10-10 or similar Boeing ODA approved repair. 5 777-200 and 777-300 Airplanes with left and right side Under Wing Longeron (UWL) modified in accordance with Service Bulletin (SB) 777-53-0084 or SB 777-53-0087, and left and right side Front Spar Lower Chord (FSLC) that have not been repaired in accordance with Structural Repair Manual (SRM) 57-10-10 or similar Boeing ODA approved repair. 6 777-200 and 777-300 Airplanes with right side Front Spar Lower Chord (FSLC) only repaired in accordance with Structural Repair Manual (SRM) 57-10-10 or similar Boeing ODA approved repair and left side Under Wing Longeron (UWL) only modified in accordance with Service Bulletin (SB) 777-53-0084 or SB 777-53-0087. 7 8 Export Controlled ECCN: 9E991 Copyright © Unpublished Work - See page 1 for details. Original Issue: October 08, 2021 777-57A0122 RB 12 of 968 REQUIREMENTS BULLETIN 777-57A0122 ALERTALERT ### Page 13 DESCRIPTIONCONFIGURATIONGROUP 777-200 and 777-300 Airplanes with right side Front Spar lower Chord (FSLC) only repaired in accordance with Structural Repair Manual (SRM) 57-10-10 or similar Boeing ODA approved repair and left and right side Under Wing Longeron (UWL) modified in accordance with Service Bulletin (SB) 777-53-0084 or SB 777-53-0087. 777-200 and 777-300 Airplanes with left side Front Spar Lower Chord (FSLC) only repaired in accordance with Structural Repair Manual (SRM) 57-10-10 or similar Boeing ODA approved repair, and left and right side Under Wing Longeron (UWL) not modified in accordance with Service Bulletin (SB) 777-53-0084 or SB 777-53-0087. 9 777-200 and 777-300 Airplanes with left side Front Spar Lower Chord (FSLC) only repaired in accordance with Structural Repair Manual (SRM) 57-10-10 or similar Boeing ODA approved repair and right side Under Wing Longeron (UWL) only modified in accordance with Service Bulletin (SB) 777-53-0084 or SB 777-53-0087. 10 777-200 and 777-300 Airplanes with left and right side Front Spar Lower Chord (FSLC) repaired in accordance with Structural Repair Manual (SRM) 57-10-10 or similar Boeing ODA approved repair, and left and right side Under Wing Longeron (UWL) not modified in accordance with Service Bulletin (SB) 777-53-0084 or SB 777-53-0087. 11 777-200 and 777-300 Airplanes with left and right side Front Spar Lower Chord (FSLC) repaired in accordance with Structural Repair Manual (SRM) 57-10-10 or similar Boeing ODA approved repair and right side Under Wing Longeron (UWL) only modified in accordance with Service Bulletin (SB) 777-53-0084 or SB 777-53-0087. 12 777-200 and 777-300 Airplanes with left side Front Spar Lower Chord (FSLC) only repaired in accordance with Structural Repair Manual (SRM) 57-10-10 or similar Boeing ODA approved repair and left side Under Wing Longeron (UWL) only modified in accordance with Service Bulletin (SB) 777-53-0084 or SB 777-53-0087. 13 777-200 and 777-300 Airplanes with left side Front Spar lower Chord (FSLC) only repaired in accordance with Structural Repair Manual (SRM) 57-10-10 or similar Boeing ODA approved repair and left and right side Under Wing Longeron (UWL) modified in accordance with Service Bulletin (SB) 777-53-0084 or SB 777-53-0087. 14 777-200 and 777-300 Airplanes with left and right side Front Spar Lower Chord (FSLC) repaired in accordance with Structural Repair Manual (SRM) 57-10-10 or similar Boeing ODA approved repair and left side Under Wing Longeron (UWL) only modified in accordance with Service Bulletin (SB) 777-53-0084 or SB 777-53-0087. 15 Export Controlled ECCN: 9E991 Copyright © Unpublished Work - See page 1 for details. Original Issue: October 08, 2021 777-57A0122 RB 13 of 968 REQUIREMENTS BULLETIN 777-57A0122 ALERTALERT ### Page 14 DESCRIPTIONCONFIGURATIONGROUP 777-200 and 777-300 Airplanes with left and right side Front Spar Lower Chord (FSLC) repaired in accordance with Structural Repair Manual (SRM) 57-10-10 or similar Boeing ODA approved repair and left and right side Under Wing Longeron (UWL) modified in accordance with Service Bulletin (SB) 777-53-0084 or SB 777-53-0087. 16 Export Controlled ECCN: 9E991 Copyright © Unpublished Work - See page 1 for details. Original Issue: October 08, 2021 777-57A0122 RB 14 of 968 REQUIREMENTS BULLETIN 777-57A0122 ALERTALERT ### Page 15 DESCRIPTIONCONFIGURATIONGROUP 777-200LR Airplanes Line Numbers with Stringer S-36 and S-37 End Fittings. - 2 777-200LR Airplanes with left and right side Front Spar Lower Chord (FSLC) that have not been repaired in accordance with Structural Repair Manual (SRM) 57-10-10 or similar Boeing ODA approved repair and left and right Under Wing Longeron (UWL) that has not been modified in accordance with 777-53-0087. 1 777-200LR Airplanes with right side Under Wing Longeron (UWL) only modified in accordance with Service Bulletin (SB) 777-53-0084 or SB 777-53-0087, and left and right side Front Spar Lower Chord (FSLC) that have not been repaired in accordance with Structural Repair Manual (SRM) 57-10-10 or similar Boeing ODA approved repair. 2 777-200LR Airplanes with right side Front Spar Lower Chord (FSLC) only repaired in accordance with Structural Repair Manual (SRM) 57-10-10 or similar Boeing ODA approved repair, and left and right Under Wing Longeron (UWL) that has not been modified in accordance with 777-53-0084 or 777-53-0087. 3 777-200LR Airplanes with right side Front Spar Lower Chord (FSLC) only repaired in accordance with Structural Repair Manual (SRM) 57-10-10 or similar Boeing ODA approved repair and right side Under Wing Longeron (UWL) only modified in accordance with Service Bulletin (SB) 777-53-0084 or SB 777-53-0087. 4 777-200LR Airplanes with left side Under Wing Longeron (UWL) only modified in accordance with Service Bulletin (SB) 777-53-0084 or SB 777-53-0087, and left and right side Front Spar Lower Chord (FSLC) that have not been repaired in accordance with Structural Repair Manual (SRM) 57-10-10 or similar Boeing ODA approved repair. 5 777-200LR Airplanes with left and right side Under Wing Longeron (UWL) modified in accordance with Service Bulletin (SB) 777-53-0084 or SB 777-53-0087, and left and right side Front Spar Lower Chord (FSLC) that have not been repaired in accordance with Structural Repair Manual (SRM) 57-10-10 or similar Boeing ODA approved repair. 6 777-200LR Airplanes with right side Front Spar Lower Chord (FSLC) only repaired in accordance with Structural Repair Manual (SRM) 57-10-10 or similar Boeing ODA approved repair and left side Under Wing Longeron (UWL) only modified in accordance with Service Bulletin (SB) 777-53-0084 or SB 777-53-0087. 7 8 Export Controlled ECCN: 9E991 Copyright © Unpublished Work - See page 1 for details. Original Issue: October 08, 2021 777-57A0122 RB 15 of 968 REQUIREMENTS BULLETIN 777-57A0122 ALERTALERT ### Page 16 DESCRIPTIONCONFIGURATIONGROUP 777-200LR Airplanes with right side Front Spar lower Chord (FSLC) only repaired in accordance with Structural Repair Manual (SRM) 57-10-10 or similar Boeing ODA approved repair and left and right side Under Wing Longeron (UWL) modified in accordance with Service Bulletin (SB) 777-53-0084 or SB 777-53-0087. 777-200LR Airplanes with left side Front Spar Lower Chord (FSLC) only repaired in accordance with Structural Repair Manual (SRM) 57-10-10 or similar Boeing ODA approved repair, and left and right side Under Wing Longeron (UWL) not modified in accordance with Service Bulletin (SB) 777-53-0084 or SB 777-53-0087. 9 777-200LR Airplanes with left side Front Spar Lower Chord (FSLC) only repaired in accordance with Structural Repair Manual (SRM) 57-10-10 or similar Boeing ODA approved repair and right side Under Wing Longeron (UWL) only modified in accordance with Service Bulletin (SB) 777-53-0084 or SB 777-53-0087. 10 777-200LR Airplanes with left and right side Front Spar Lower Chord (FSLC) repaired in accordance with Structural Repair Manual (SRM) 57-10-10 or similar Boeing ODA approved repair, and left and right side Under Wing Longeron (UWL) not modified in accordance with Service Bulletin (SB) 777-53-0084 or SB 777-53-0087. 11 777-200LR Airplanes with left and right side Front Spar Lower Chord (FSLC) repaired in accordance with Structural Repair Manual (SRM) 57-10-10 or similar Boeing ODA approved repair and right side Under Wing Longeron (UWL) only modified in accordance with Service Bulletin (SB) 777-53-0084 or SB 777-53-0087. 12 777-200LR Airplanes with left side Front Spar Lower Chord (FSLC) only repaired in accordance with Structural Repair Manual (SRM) 57-10-10 or similar Boeing ODA approved repair and left side Under Wing Longeron (UWL) only modified in accordance with Service Bulletin (SB) 777-53-0084 or SB 777-53-0087. 13 777-200LR Airplanes with left side Front Spar lower Chord (FSLC) only repaired in accordance with Structural Repair Manual (SRM) 57-10-10 or similar Boeing ODA approved repair and left and right side Under Wing Longeron (UWL) modified in accordance with Service Bulletin (SB) 777-53-0084 or SB 777-53-0087. 14 777-200LR Airplanes with left and right side Front Spar Lower Chord (FSLC) repaired in accordance with Structural Repair Manual (SRM) 57-10-10 or similar Boeing ODA approved repair and left side Under Wing Longeron (UWL) only modified in accordance with Service Bulletin (SB) 777-53-0084 or SB 777-53-0087. 15 16 Export Controlled ECCN: 9E991 Copyright © Unpublished Work - See page 1 for details. Original Issue: October 08, 2021 777-57A0122 RB 16 of 968 REQUIREMENTS BULLETIN 777-57A0122 ALERTALERT ### Page 17 DESCRIPTIONCONFIGURATIONGROUP 777-200LR Airplanes with left and right side Front Spar Lower Chord (FSLC) repaired in accordance with Structural Repair Manual (SRM) 57-10-10 or similar Boeing ODA approved repair and left and right side Under Wing Longeron (UWL) modified in accordance with Service Bulletin SB 777-53-0087. Export Controlled ECCN: 9E991 Copyright © Unpublished Work - See page 1 for details. Original Issue: October 08, 2021 777-57A0122 RB 17 of 968 REQUIREMENTS BULLETIN 777-57A0122 ALERTALERT ### Page 18 DESCRIPTIONCONFIGURATIONGROUP 777-200LR Airplanes without Stringer S-36 and S-37 End Fittings.- 3 777-200LR Airplanes with left and right side Front Spar Lower Chord (FSLC) that have not been repaired in accordance with Structural Repair Manual (SRM) 57-10-10 or similar Boeing ODA approved repair and left and right Under Wing Longeron (UWL) that has not been modified in accordance with 777-53-0087. 1 777-200LR Airplanes with right side Under Wing Longeron (UWL) only modified in accordance with Service Bulletin (SB) 777-53-0084 or SB 777-53-0087, and left and right side Front Spar Lower Chord (FSLC) that have not been repaired in accordance with Structural Repair Manual (SRM) 57-10-10 or similar Boeing ODA approved repair. 2 777-200LR Airplanes with right side Front Spar Lower Chord (FSLC) only repaired in accordance with Structural Repair Manual (SRM) 57-10-10 or similar Boeing ODA approved repair, and left and right Under Wing Longeron (UWL) that has not been modified in accordance with 777-53-0084 or 777-53-0087. 3 777-200LR Airplanes with right side Front Spar Lower Chord (FSLC) only repaired in accordance with Structural Repair Manual (SRM) 57-10-10 or similar Boeing ODA approved repair and right side Under Wing Longeron (UWL) only modified in accordance with Service Bulletin (SB) 777-53-0084 or SB 777-53-0087. 4 777-200LR Airplanes with left side Under Wing Longeron (UWL) only modified in accordance with Service Bulletin (SB) 777-53-0084 or SB 777-53-0087, and left and right side Front Spar Lower Chord (FSLC) that have not been repaired in accordance with Structural Repair Manual (SRM) 57-10-10 or similar Boeing ODA approved repair. 5 777-200LR Airplanes with left and right side Under Wing Longeron (UWL) modified in accordance with Service Bulletin (SB) 777-53-0084 or SB 777-53-0087, and left and right side Front Spar Lower Chord (FSLC) that have not been repaired in accordance with Structural Repair Manual (SRM) 57-10-10 or similar Boeing ODA approved repair. 6 777-200LR Airplanes with right side Front Spar Lower Chord (FSLC) only repaired in accordance with Structural Repair Manual (SRM) 57-10-10 or similar Boeing ODA approved repair and left side Under Wing Longeron (UWL) only modified in accordance with Service Bulletin (SB) 777-53-0084 or SB 777-53-0087. 7 8 Export Controlled ECCN: 9E991 Copyright © Unpublished Work - See page 1 for details. Original Issue: October 08, 2021 777-57A0122 RB 18 of 968 REQUIREMENTS BULLETIN 777-57A0122 ALERTALERT ### Page 19 DESCRIPTIONCONFIGURATIONGROUP 777-200LR Airplanes with right side Front Spar lower Chord (FSLC) only repaired in accordance with Structural Repair Manual (SRM) 57-10-10 or similar Boeing ODA approved repair and left and right side Under Wing Longeron (UWL) modified in accordance with Service Bulletin (SB) 777-53-0084 or SB 777-53-0087. 777-200LR Airplanes with left side Front Spar Lower Chord (FSLC) only repaired in accordance with Structural Repair Manual (SRM) 57-10-10 or similar Boeing ODA approved repair, and left and right side Under Wing Longeron (UWL) not modified in accordance with Service Bulletin (SB) 777-53-0084 or SB 777-53-0087. 9 777-200LR Airplanes with left side Front Spar Lower Chord (FSLC) only repaired in accordance with Structural Repair Manual (SRM) 57-10-10 or similar Boeing ODA approved repair and right side Under Wing Longeron (UWL) only modified in accordance with Service Bulletin (SB) 777-53-0084 or SB 777-53-0087. 10 777-200LR Airplanes with left and right side Front Spar Lower Chord (FSLC) repaired in accordance with Structural Repair Manual (SRM) 57-10-10 or similar Boeing ODA approved repair, and left and right side Under Wing Longeron (UWL) not modified in accordance with Service Bulletin (SB) 777-53-0084 or SB 777-53-0087. 11 777-200LR Airplanes with left and right side Front Spar Lower Chord (FSLC) repaired in accordance with Structural Repair Manual (SRM) 57-10-10 or similar Boeing ODA approved repair and right side Under Wing Longeron (UWL) only modified in accordance with Service Bulletin (SB) 777-53-0084 or SB 777-53-0087. 12 777-200LR Airplanes with left side Front Spar Lower Chord (FSLC) only repaired in accordance with Structural Repair Manual (SRM) 57-10-10 or similar Boeing ODA approved repair and left side Under Wing Longeron (UWL) only modified in accordance with Service Bulletin (SB) 777-53-0084 or SB 777-53-0087. 13 777-200LR Airplanes with left side Front Spar lower Chord (FSLC) only repaired in accordance with Structural Repair Manual (SRM) 57-10-10 or similar Boeing ODA approved repair and left and right side Under Wing Longeron (UWL) modified in accordance with Service Bulletin (SB) 777-53-0084 or SB 777-53-0087. 14 777-200LR Airplanes with left and right side Front Spar Lower Chord (FSLC) repaired in accordance with Structural Repair Manual (SRM) 57-10-10 or similar Boeing ODA approved repair and left side Under Wing Longeron (UWL) only modified in accordance with Service Bulletin (SB) 777-53-0084 or SB 777-53-0087. 15 16 Export Controlled ECCN: 9E991 Copyright © Unpublished Work - See page 1 for details. Original Issue: October 08, 2021 777-57A0122 RB 19 of 968 REQUIREMENTS BULLETIN 777-57A0122 ALERTALERT ### Page 20 DESCRIPTIONCONFIGURATIONGROUP 777-200LR Airplanes with left and right side Front Spar Lower Chord (FSLC) repaired in accordance with Structural Repair Manual (SRM) 57-10-10 or similar Boeing ODA approved repair and left and right side Under Wing Longeron (UWL) modified in accordance with Service Bulletin SB 777-53-0087. 777-200LR Airplanes with new production Underwing Longeron.- 4 777-200LR Airplanes with left and right side Front Spar Lower Chord (FSLC) that have not been repaired in accordance with Structural Repair Manual (SRM) 57-10-10 or similar Boeing ODA approved repair. 1 777-200LR Airplanes with right side Front Spar Lower Chord (FSLC) repaired in accordance with Structural Repair Manual (SRM) 57-10-10 or similar Boeing ODA approved repair. 2 777-200LR Airplanes with left side Front Spar Lower Chord (FSLC) repaired in accordance with Structural Repair Manual (SRM) 57-10-10 or similar Boeing ODA approved repair. 3 777-200LR Airplanes with left and right side Front Spar Lower Chord (FSLC) repaired in accordance with Structural Repair Manual (SRM) 57-10-10 or similar Boeing ODA approved repair. 4 Export Controlled ECCN: 9E991 Copyright © Unpublished Work - See page 1 for details. Original Issue: October 08, 2021 777-57A0122 RB 20 of 968 REQUIREMENTS BULLETIN 777-57A0122 ALERTALERT ### Page 21 DESCRIPTIONCONFIGURATIONGROUP 777F Airplanes with original production Underwing Longeron.- 5 777F Airplanes with left and right side Front Spar Lower Chord (FSLC) that have not been repaired in accordance with Structural Repair Manual (SRM) 57-10-10 or similar Boeing ODA approved repair and left and right Under Wing Longeron (UWL) that has not been modified in accordance with 777-53-0087. 1 777F Airplanes with right side Under Wing Longeron (UWL) only modified in accordance with Service Bulletin (SB) 777-53-0084 or SB 777-53-0087, and left and right side Front Spar Lower Chord (FSLC) that have not been repaired in accordance with Structural Repair Manual (SRM) 57-10-10 or similar Boeing ODA approved repair. 2 777F Airplanes with right side Front Spar Lower Chord (FSLC) only repaired in accordance with Structural Repair Manual (SRM) 57-10-10 or similar Boeing ODA approved repair, and left and right Under Wing Longeron (UWL) that has not been modified in accordance with 777-53-0084 or 777-53-0087. 3 777F Airplanes with right side Front Spar Lower Chord (FSLC) only repaired in accordance with Structural Repair Manual (SRM) 57-10-10 or similar Boeing ODA approved repair and right side Under Wing Longeron (UWL) only modified in accordance with Service Bulletin (SB) 777-53-0084 or SB 777-53-0087. 4 777F Airplanes with left side Under Wing Longeron (UWL) only modified in accordance with Service Bulletin (SB) 777-53-0084 or SB 777-53-0087, and left and right side Front Spar Lower Chord (FSLC) that have not been repaired in accordance with Structural Repair Manual (SRM) 57-10-10 or similar Boeing ODA approved repair. 5 777F Airplanes with left and right side Under Wing Longeron (UWL) modified in accordance with Service Bulletin (SB) 777-53-0084 or SB 777-53-0087, and left and right side Front Spar Lower Chord (FSLC) that have not been repaired in accordance with Structural Repair Manual (SRM) 57-10-10 or similar Boeing ODA approved repair. 6 777F Airplanes with right side Front Spar Lower Chord (FSLC) only repaired in accordance with Structural Repair Manual (SRM) 57-10-10 or similar Boeing ODA approved repair and left side Under Wing Longeron (UWL) only modified in accordance with Service Bulletin (SB) 777-53-0084 or SB 777-53-0087. 7 8 Export Controlled ECCN: 9E991 Copyright © Unpublished Work - See page 1 for details. Original Issue: October 08, 2021 777-57A0122 RB 21 of 968 REQUIREMENTS BULLETIN 777-57A0122 ALERTALERT ### Page 22 DESCRIPTIONCONFIGURATIONGROUP 777F Airplanes with right side Front Spar lower Chord (FSLC) only repaired in accordance with Structural Repair Manual (SRM) 57-10-10 or similar Boeing ODA approved repair and left and right side Under Wing Longeron (UWL) modified in accordance with Service Bulletin (SB) 777-53-0084 or SB 777-53-0087. 777F Airplanes with left side Front Spar Lower Chord (FSLC) only repaired in accordance with Structural Repair Manual (SRM) 57-10-10 or similar Boeing ODA approved repair, and left and right side Under Wing Longeron (UWL) not modified in accordance with Service Bulletin (SB) 777-53-0084 or SB 777-53-0087. 9 777F Airplanes with left side Front Spar Lower Chord (FSLC) only repaired in accordance with Structural Repair Manual (SRM) 57-10-10 or similar Boeing ODA approved repair and right side Under Wing Longeron (UWL) only modified in accordance with Service Bulletin (SB) 777-53-0084 or SB 777-53-0087. 10 777F Airplanes with left and right side Front Spar Lower Chord (FSLC) repaired in accordance with Structural Repair Manual (SRM) 57-10-10 or similar Boeing ODA approved repair, and left and right side Under Wing Longeron (UWL) not modified in accordance with Service Bulletin (SB) 777-53-0084 or SB 777-53-0087. 11 777F Airplanes with left and right side Front Spar Lower Chord (FSLC) repaired in accordance with Structural Repair Manual (SRM) 57-10-10 or similar Boeing ODA approved repair and right side Under Wing Longeron (UWL) only modified in accordance with Service Bulletin (SB) 777-53-0084 or SB 777-53-0087. 12 777F Airplanes with left side Front Spar Lower Chord (FSLC) only repaired in accordance with Structural Repair Manual (SRM) 57-10-10 or similar Boeing ODA approved repair and left side Under Wing Longeron (UWL) only modified in accordance with Service Bulletin (SB) 777-53-0084 or SB 777-53-0087. 13 777F Airplanes with left side Front Spar lower Chord (FSLC) only repaired in accordance with Structural Repair Manual (SRM) 57-10-10 or similar Boeing ODA approved repair and left and right side Under Wing Longeron (UWL) modified in accordance with Service Bulletin (SB) 777-53-0084 or SB 777-53-0087. 14 777F Airplanes with left and right side Front Spar Lower Chord (FSLC) repaired in accordance with Structural Repair Manual (SRM) 57-10-10 or similar Boeing ODA approved repair and left side Under Wing Longeron (UWL) only modified in accordance with Service Bulletin (SB) 777-53-0084 or SB 777-53-0087. 15 16 Export Controlled ECCN: 9E991 Copyright © Unpublished Work - See page 1 for details. Original Issue: October 08, 2021 777-57A0122 RB 22 of 968 REQUIREMENTS BULLETIN 777-57A0122 ALERTALERT ### Page 23 DESCRIPTIONCONFIGURATIONGROUP 777F Airplanes with left and right side Front Spar Lower Chord (FSLC) repaired in accordance with Structural Repair Manual (SRM) 57-10-10 or similar Boeing ODA approved repair and left and right side Under Wing Longeron (UWL) modified in accordance with Service Bulletin SB 777-53-0087. 777F Airplanes with new production Underwing Longeron.- 6 777F Airplanes with left and right side Front Spar Lower Chord (FSLC) that have not been repaired in accordance with Structural Repair Manual (SRM) 57-10-10 or similar Boeing ODA approved repair. 1 777F Airplanes with right side Front Spar Lower Chord (FSLC) repaired in accordance with Structural Repair Manual (SRM) 57-10-10 or similar Boeing ODA approved repair. 2 777F Airplanes with left side Front Spar Lower Chord (FSLC) repaired in accordance with Structural Repair Manual (SRM) 57-10-10 or similar Boeing ODA approved repair. 3 777F Airplanes with left and right side Front Spar Lower Chord (FSLC) repaired in accordance with Structural Repair Manual (SRM) 57-10-10 or similar Boeing ODA approved repair. 4 Export Controlled ECCN: 9E991 Copyright © Unpublished Work - See page 1 for details. Original Issue: October 08, 2021 777-57A0122 RB 23 of 968 REQUIREMENTS BULLETIN 777-57A0122 ALERTALERT ### Page 24 DESCRIPTIONCONFIGURATIONGROUP 777-300ER Airplanes with Stringer S-36 and S-37 End Fittings.- 7 777-300ER Airplanes with left and right side Front Spar Lower Chord (FSLC) that have not been repaired in accordance with Structural Repair Manual (SRM) 57-10-10 or similar Boeing ODA approved repair and left and right Under Wing Longeron (UWL) that has not been modified in accordance with 777-53-0084. 1 777-300ER Airplanes with right side Under Wing Longeron (UWL) only modified in accordance with Service Bulletin (SB) 777-53-0084 or SB 777-53-0087, and left and right side Front Spar Lower Chord (FSLC) that have not been repaired in accordance with Structural Repair Manual (SRM) 57-10-10 or similar Boeing ODA approved repair. 2 777-300ER Airplanes with right side Front Spar Lower Chord (FSLC) only repaired in accordance with Structural Repair Manual (SRM) 57-10-10 or similar Boeing ODA approved repair, and left and right Under Wing Longeron (UWL) that has not been modified in accordance with 777-53-0084 or 777-53-0087. 3 777-300ER Airplanes with right side Front Spar Lower Chord (FSLC) only repaired in accordance with Structural Repair Manual (SRM) 57-10-10 or similar Boeing ODA approved repair and right side Under Wing Longeron (UWL) only modified in accordance with Service Bulletin (SB) 777-53-0084 or SB 777-53-0087. 4 777-300ER Airplanes with left side Under Wing Longeron (UWL) only modified in accordance with Service Bulletin (SB) 777-53-0084 or SB 777-53-0087, and left and right side Front Spar Lower Chord (FSLC) that have not been repaired in accordance with Structural Repair Manual (SRM) 57-10-10 or similar Boeing ODA approved repair. 5 777-300ER Airplanes with left and right side Under Wing Longeron (UWL) modified in accordance with Service Bulletin (SB) 777-53-0084 or SB 777-53-0087, and left and right side Front Spar Lower Chord (FSLC) that have not been repaired in accordance with Structural Repair Manual (SRM) 57-10-10 or similar Boeing ODA approved repair. 6 777-300ER Airplanes with right side Front Spar Lower Chord (FSLC) only repaired in accordance with Structural Repair Manual (SRM) 57-10-10 or similar Boeing ODA approved repair and left side Under Wing Longeron (UWL) only modified in accordance with Service Bulletin (SB) 777-53-0084 or SB 777-53-0087. 7 8 Export Controlled ECCN: 9E991 Copyright © Unpublished Work - See page 1 for details. Original Issue: October 08, 2021 777-57A0122 RB 24 of 968 REQUIREMENTS BULLETIN 777-57A0122 ALERTALERT ### Page 25 DESCRIPTIONCONFIGURATIONGROUP 777-300ER Airplanes with right side Front Spar lower Chord (FSLC) only repaired in accordance with Structural Repair Manual (SRM) 57-10-10 or similar Boeing ODA approved repair and left and right side Under Wing Longeron (UWL) modified in accordance with Service Bulletin (SB) 777-53-0084 or SB 777-53-0087. 777-300ER Airplanes with left side Front Spar Lower Chord (FSLC) only repaired in accordance with Structural Repair Manual (SRM) 57-10-10 or similar Boeing ODA approved repair, and left and right side Under Wing Longeron (UWL) not modified in accordance with Service Bulletin (SB) 777-53-0084 or SB 777-53-0087. 9 777-300ER Airplanes with left side Front Spar Lower Chord (FSLC) only repaired in accordance with Structural Repair Manual (SRM) 57-10-10 or similar Boeing ODA approved repair and right side Under Wing Longeron (UWL) only modified in accordance with Service Bulletin (SB) 777-53-0084 or SB 777-53-0087. 10 777-300ER Airplanes with left and right side Front Spar Lower Chord (FSLC) repaired in accordance with Structural Repair Manual (SRM) 57-10-10 or similar Boeing ODA approved repair, and left and right side Under Wing Longeron (UWL) not modified in accordance with Service Bulletin (SB) 777-53-0084 or SB 777-53-0087. 11 777-300ER Airplanes with left and right side Front Spar Lower Chord (FSLC) repaired in accordance with Structural Repair Manual (SRM) 57-10-10 or similar Boeing ODA approved repair and right side Under Wing Longeron (UWL) only modified in accordance with Service Bulletin (SB) 777-53-0084 or SB 777-53-0087. 12 777-300ER Airplanes with left side Front Spar Lower Chord (FSLC) only repaired in accordance with Structural Repair Manual (SRM) 57-10-10 or similar Boeing ODA approved repair and left side Under Wing Longeron (UWL) only modified in accordance with Service Bulletin (SB) 777-53-0084 or SB 777-53-0087. 13 777-300ER Airplanes with left side Front Spar lower Chord (FSLC) only repaired in accordance with Structural Repair Manual (SRM) 57-10-10 or similar Boeing ODA approved repair and left and right side Under Wing Longeron (UWL) modified in accordance with Service Bulletin (SB) 777-53-0084 or SB 777-53-0087. 14 777-300ER Airplanes with left and right side Front Spar Lower Chord (FSLC) repaired in accordance with Structural Repair Manual (SRM) 57-10-10 or similar Boeing ODA approved repair and left side Under Wing Longeron (UWL) only modified in accordance with Service Bulletin (SB) 777-53-0084 or SB 777-53-0087. 15 16 Export Controlled ECCN: 9E991 Copyright © Unpublished Work - See page 1 for details. Original Issue: October 08, 2021 777-57A0122 RB 25 of 968 REQUIREMENTS BULLETIN 777-57A0122 ALERTALERT ### Page 26 DESCRIPTIONCONFIGURATIONGROUP 777-300ER Airplanes with left and right side Front Spar Lower Chord (FSLC) repaired in accordance with Structural Repair Manual (SRM) 57-10-10 or similar Boeing ODA approved repair and left and right side Under Wing Longeron (UWL) modified in accordance with Service Bulletin (SB) 777-53-0084. Export Controlled ECCN: 9E991 Copyright © Unpublished Work - See page 1 for details. Original Issue: October 08, 2021 777-57A0122 RB 26 of 968 REQUIREMENTS BULLETIN 777-57A0122 ALERTALERT ### Page 27 DESCRIPTIONCONFIGURATIONGROUP 777-300ER Airplanes without Stringer S-36 and S-37 End Fittings.- 8 777-300ER Airplanes with left and right side Front Spar Lower Chord (FSLC) that have not been repaired in accordance with Structural Repair Manual (SRM) 57-10-10 or similar Boeing ODA approved repair and left and right Under Wing Longeron (UWL) that has not been modified in accordance with 777-53-0084. 1 777-300ER Airplanes with right side Under Wing Longeron (UWL) only modified in accordance with Service Bulletin (SB) 777-53-0084 or SB 777-53-0087, and left and right side Front Spar Lower Chord (FSLC) that have not been repaired in accordance with Structural Repair Manual (SRM) 57-10-10 or similar Boeing ODA approved repair. 2 777-300ER Airplanes with right side Front Spar Lower Chord (FSLC) only repaired in accordance with Structural Repair Manual (SRM) 57-10-10 or similar Boeing ODA approved repair, and left and right Under Wing Longeron (UWL) that has not been modified in accordance with 777-53-0084 or 777-53-0087. 3 777-300ER Airplanes with right side Front Spar Lower Chord (FSLC) only repaired in accordance with Structural Repair Manual (SRM) 57-10-10 or similar Boeing ODA approved repair and right side Under Wing Longeron (UWL) only modified in accordance with Service Bulletin (SB) 777-53-0084 or SB 777-53-0087. 4 777-300ER Airplanes with left side Under Wing Longeron (UWL) only modified in accordance with Service Bulletin (SB) 777-53-0084 or SB 777-53-0087, and left and right side Front Spar Lower Chord (FSLC) that have not been repaired in accordance with Structural Repair Manual (SRM) 57-10-10 or similar Boeing ODA approved repair. 5 777-300ER Airplanes with left and right side Under Wing Longeron (UWL) modified in accordance with Service Bulletin (SB) 777-53-0084 or SB 777-53-0087, and left and right side Front Spar Lower Chord (FSLC) that have not been repaired in accordance with Structural Repair Manual (SRM) 57-10-10 or similar Boeing ODA approved repair. 6 777-300ER Airplanes with right side Front Spar Lower Chord (FSLC) only repaired in accordance with Structural Repair Manual (SRM) 57-10-10 or similar Boeing ODA approved repair and left side Under Wing Longeron (UWL) only modified in accordance with Service Bulletin (SB) 777-53-0084 or SB 777-53-0087. 7 8 Export Controlled ECCN: 9E991 Copyright © Unpublished Work - See page 1 for details. Original Issue: October 08, 2021 777-57A0122 RB 27 of 968 REQUIREMENTS BULLETIN 777-57A0122 ALERTALERT ### Page 28 DESCRIPTIONCONFIGURATIONGROUP 777-300ER Airplanes with right side Front Spar lower Chord (FSLC) only repaired in accordance with Structural Repair Manual (SRM) 57-10-10 or similar Boeing ODA approved repair and left and right side Under Wing Longeron (UWL) modified in accordance with Service Bulletin (SB) 777-53-0084 or SB 777-53-0087. 777-300ER Airplanes with left side Front Spar Lower Chord (FSLC) only repaired in accordance with Structural Repair Manual (SRM) 57-10-10 or similar Boeing ODA approved repair, and left and right side Under Wing Longeron (UWL) not modified in accordance with Service Bulletin (SB) 777-53-0084 or SB 777-53-0087. 9 777-300ER Airplanes with left side Front Spar Lower Chord (FSLC) only repaired in accordance with Structural Repair Manual (SRM) 57-10-10 or similar Boeing ODA approved repair and right side Under Wing Longeron (UWL) only modified in accordance with Service Bulletin (SB) 777-53-0084 or SB 777-53-0087. 10 777-300ER Airplanes with left and right side Front Spar Lower Chord (FSLC) repaired in accordance with Structural Repair Manual (SRM) 57-10-10 or similar Boeing ODA approved repair, and left and right side Under Wing Longeron (UWL) not modified in accordance with Service Bulletin (SB) 777-53-0084 or SB 777-53-0087. 11 777-300ER Airplanes with left and right side Front Spar Lower Chord (FSLC) repaired in accordance with Structural Repair Manual (SRM) 57-10-10 or similar Boeing ODA approved repair and right side Under Wing Longeron (UWL) only modified in accordance with Service Bulletin (SB) 777-53-0084 or SB 777-53-0087. 12 777-300ER Airplanes with left side Front Spar Lower Chord (FSLC) only repaired in accordance with Structural Repair Manual (SRM) 57-10-10 or similar Boeing ODA approved repair and left side Under Wing Longeron (UWL) only modified in accordance with Service Bulletin (SB) 777-53-0084 or SB 777-53-0087. 13 777-300ER Airplanes with left side Front Spar lower Chord (FSLC) only repaired in accordance with Structural Repair Manual (SRM) 57-10-10 or similar Boeing ODA approved repair and left and right side Under Wing Longeron (UWL) modified in accordance with Service Bulletin (SB) 777-53-0084 or SB 777-53-0087. 14 777-300ER Airplanes with left and right side Front Spar Lower Chord (FSLC) repaired in accordance with Structural Repair Manual (SRM) 57-10-10 or similar Boeing ODA approved repair and left side Under Wing Longeron (UWL) only modified in accordance with Service Bulletin (SB) 777-53-0084 or SB 777-53-0087. 15 16 Export Controlled ECCN: 9E991 Copyright © Unpublished Work - See page 1 for details. Original Issue: October 08, 2021 777-57A0122 RB 28 of 968 REQUIREMENTS BULLETIN 777-57A0122 ALERTALERT ### Page 29 DESCRIPTIONCONFIGURATIONGROUP 777-300ER Airplanes with left and right side Front Spar Lower Chord (FSLC) repaired in accordance with Structural Repair Manual (SRM) 57-10-10 or similar Boeing ODA approved repair and left and right side Under Wing Longeron (UWL) modified in accordance with Service Bulletin (SB) 777-53-0084. 777-300ER Airplanes with new production Underwing Longeron.- 9 777-300ER Airplanes with left and right side Front Spar Lower Chord (FSLC) that have not been repaired in accordance with Structural Repair Manual (SRM) 57-10-10 or similar Boeing ODA approved repair. 1 777-300ER Airplanes with right side Front Spar Lower Chord (FSLC) repaired in accordance with Structural Repair Manual (SRM) 57-10-10 or similar Boeing ODA approved repair. 2 777-300ER Airplanes with left side Front Spar Lower Chord (FSLC) repaired in accordance with Structural Repair Manual (SRM) 57-10-10 or similar Boeing ODA approved repair. 3 777-300ER Airplanes with left and right side Front Spar Lower Chord (FSLC) repaired in accordance with Structural Repair Manual (SRM) 57-10-10 or similar Boeing ODA approved repair. 4 Airplane Models: 777-200, 777-200LR, 777-300, 777-300ER, 777F GroupVariable Number 1WB001 - WB021 1WB031 - WB046 1WB051 - WB088 1WB101 - WB106 1WB121 - WB125 1WB131 - WB148 1WB151 - WB155 1WB161 - WB177 1WB181 - WB194 1WB201 - WB215 1WB231 - WB247 GroupVariable Number 1WB271 - WB273 1WB276 - WB286 1WB291 - WB302 1WB306 - WB307 1WB311 - WB337 1WB341 - WB342 1WB366 - WB368 1WB371 - WB388 1WB406 1WB411 - WB413 1WB416 - WB439 GroupVariable Number 1WB446 - WB453 1WB476 1WB481 - WB484 1WB501 - WB512 1WB531 - WB537 1WB551 - WB554 1WB591 - WB597 1WB601 - WB606 1WB611 - WB622 1WB631 - WB638 1WB646 - WB649 Export Controlled ECCN: 9E991 Copyright © Unpublished Work - See page 1 for details. Original Issue: October 08, 2021 777-57A0122 RB 29 of 968 REQUIREMENTS BULLETIN 777-57A0122 ALERTALERT ### Page 30 GroupVariable Number 1WC051 - WC073 1WC101 - WC104 1WC111 - WC120 1WC221 - WC224 1WC241 - WC243 1WC281 - WC290 1WC301 - WC308 1WC361 - WC364 1WC371 - WC374 1WC381 - WC395 1WC441 1WC446 - WC449 1WC456 - WC459 1WC486 - WC493 1WC506 - WC508 1WC521 - WC522 1WC531 - WC536 1WC546 - WC548 1WC556 1WC566 - WC567 1WC571 - WC574 1WC581 1WC586 - WC587 1WC591 - WC595 2WD001 - WD002 2WD011 - WD013 3WD014 - WD018 3WD031 - WD036 3WD046 - WD055 3WD066 - WD075 3WD081 - WD089 3WD091 3WD096 GroupVariable Number 3WD101 - WD106 3WD111 - WD112 3WD116 - WD117 3WD121 - WD122 4WD123 4WD156 7WD501 - WD506 8WD507 - WD513 7WD521 - WD534 8WD535 - WD541 7WD546 - WD551 8WD552 - WD554 7WD561 - WD568 8WD569 - WD573 7WD581 - WD591 8WD592 - WD599 7WD606 - WD609 7WD621 - WD631 8WD632 7WD651 - WD655 8WD656 - WD665 7WD671 - WD675 8WD676 - WD677 7WD691 - WD699 8WD700 - WD709 7WD741 - WD742 8WD743 - WD752 7WD761 8WD762 - WD771 7WD786 - WD787 8WD788 8WD796 - WD837 8WD846 - WD867 GroupVariable Number 8WD871 - WD906 9WD907 - WD910 8WD911 - WD918 8WD921 - WD957 8WD966 - WD970 8WD981 - WD982 8WD986 - WD987 8WD991 - WD996 8WE001 - WE007 8WE011 - WE012 8WE021 - WE026 8WE031 - WE040 8WE051 - WE057 8WE071 - WE078 8WE081 - WE084 8WE091 - WE095 8WE126 - WE178 8WE186 - WE219 8WE226 - WE231 8WE236 - WE253 8WE261 - WE267 8WE271 - WE278 8WE291 - WE298 8WE301 - WE320 8WE331 - WE346 9WE347 - WE350 8WE351 - WE356 9WE366 - WE368 8WE376 - WE377 8WE381 8WE386 - WE387 8WE391 - WE392 8WE396 - WE405 Export Controlled ECCN: 9E991 Copyright © Unpublished Work - See page 1 for details. Original Issue: October 08, 2021 777-57A0122 RB 30 of 968 REQUIREMENTS BULLETIN 777-57A0122 ALERTALERT ### Page 31 GroupVariable Number 9WE406 - WE411 8WE416 - WE420 8WE426 - WE431 8WE436 - WE446 8WE451 - WE478 9WE479 - WE484 8WE486 - WE493 8WE495 - WE499 8WE501 - WE504 8WE511 - WE516 8WE526 - WE528 8WE536 - WE549 8WE556 - WE571 9WE572 - WE573 8WE576 - WE583 9WE584 - WE587 8WE591 8WE601 - WE605 8WE626 - WE627 8WE631 8WE641 - WE642 8WE646 - WE647 8WE651 - WE661 8WE666 - WE677 8WE681 9WE682 - WE689 8WE701 - WE705 8WE711 - WE712 8WE731 - WE732 GroupVariable Number 8WE736 - WE740 8WE746 - WE764 9WE765 - WE772 8WE776 - WE786 8WE791 - WE792 8WE796 9WE797 - WE798 9WE801 - WE806 8WE811 - WE812 8WE826 9WE827 - WE828 9WE831 - WE835 9WE851 - WE853 9WE856 - WE857 9WE861 - WE863 9WE866 - WE868 9WE871 5WF001 - WF004 5WF016 - WF027 6WF028 - WF029 5WF031 - WF043 5WF046 - WF069 6WF070 - WF074 5WF075 - WF077 5WF081 - WF088 5WF096 - WF101 5WF106 - WF109 5WF111 - WF124 5WF131 - WF144 GroupVariable Number 5WF146 - WF147 5WF151 - WF152 5WF156 - WF160 6WF161 - WF165 5WF166 - WF173 5WF176 - WF179 6WF180 5WF181 - WF184 5WF191 6WF201 5WF206 - WF208 6WF209 - WF215 5WF216 - WF217 6WF221 - WF228 6WF231 - WF248 6WF256 - WF258 6WF261 - WF262 6WF266 - WF288 6WF296 6WF301 - WF305 6WF311 - WF314 6WF321 6WF326 6WF336 - WF338 6WF340 - WF341 6WF367 6WF371 - WF372 -- -- B. Spares Affected None. 2. CONCURRENT REQUIREMENTS None. Export Controlled ECCN: 9E991 Copyright © Unpublished Work - See page 1 for details. Original Issue: October 08, 2021 777-57A0122 RB 31 of 968 REQUIREMENTS BULLETIN 777-57A0122 ALERTALERT ### Page 32 3. COMPLIANCE The Federal Aviation Administration (FAA) will possibly release an Airworthiness Directive related to Requirements Bulletin 777-57A0122 RB. The Airworthiness Directive will make the compliance tasks and times given in Requirements Bulletin 777-57A0122 RB mandatory. Accomplish the required actions, based on the applicable conditions in Tables 1 through 50, in accordance with Accomplishment Instructions. 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. Group 1, Configuration 1-4: Table 1: Wing - Front Spar at Station (STA) 1035, Left Body Line (LBL) 84 - High Frequency Eddy Current (HFEC) Inspection. Repeat Interval (Not to Exceed) Boeing Recommended Compliance Time (Whichever Oc- curs Later) ActionCondition -Within 4,500 flight cycles or 12,000 flight hours after the original issue date of Require- ments Bulletin 777-57A0122 RB, whichever occurs first. Before 16,000 total flight cycles or 50,000 total flight hours, whichever occurs first. ACTION 1: Do a surface High Frequency Eddy Cur- rent (HFEC) inspection of the left side ring chord for any crack. All Airplanes. ACTION 2: Do a surface High Frequency Eddy Cur- rent (HFEC) inspection of the left side front spar lower chord and front spar web for any crack. 10,000 flight cycles or 37,500 flight hours, whichever occurs first. -CONDITION 1 (ACTION 1): Repeat the surface High Frequency Eddy Current (HFEC) inspection of the left side ring chord for any crack. (a) CONDITION 1: NO CRACK FOUND. 16,000 flight cycles or 50,000 flight hours, whichever occurs first. -CONDITION 1 (ACTION 2): Repeat the surface High Frequency Eddy Current (HFEC) inspection of the left side front spar lower chord and front spar web for any crack. (a) Export Controlled ECCN: 9E991 Copyright © Unpublished Work - See page 1 for details. Original Issue: October 08, 2021 777-57A0122 RB 32 of 968 REQUIREMENTS BULLETIN 777-57A0122 ALERTALERT ### Page 33 Group 1, Configuration 1-4: Table 1: Wing - Front Spar at Station (STA) 1035, Left Body Line (LBL) 84 - High Frequency Eddy Current (HFEC) Inspection. Repeat Interval (Not to Exceed) Boeing Recommended Compliance Time (Whichever Oc- curs Later) ActionCondition -Before further flight.CONDITION 2 (ACTION 1): Contact The Boeing Compa- ny for repair instructions and do the repair. CONDITION 2: ANY CRACK FOUND. 10,000 flight cycles or 37,500 flight hours, whichever occurs first. -CONDITION 2 (ACTION 2): Repeat the surface High Frequency Eddy Current (HFEC) inspection of the left side ring chord for any crack. (a) 16,000 flight cycles or 64,000 flight hours, whichever occurs first. -CONDITION 2 (ACTION 3): Repeat the surface High Frequency Eddy Current (HFEC) inspection of the left side front spar lower chord and front spar web for any crack. (a) (a) It is not required to do the repeat inspections of the ring chord, front spar lower chord or front spar web in areas where a repair covers the affected inspection zone provided: 1. The repair is the corrective action to the crack condition identified in Requirements Bulletin 777- 57A0122 RB and installed after the Original Issue date of Requirements Bulletin 777-57A0122 RB, AND 2. The installed repair was approved by the Boeing Company Organization Designation Authorization (ODA) via a FAA Form 8100-9. Export Controlled ECCN: 9E991 Copyright © Unpublished Work - See page 1 for details. Original Issue: October 08, 2021 777-57A0122 RB 33 of 968 REQUIREMENTS BULLETIN 777-57A0122 ALERTALERT ### Page 34 Group 1, Configuration 1, 5, 9, 13: Table 2: Wing - Front Spar at Station (STA) 1035, Right Body Line (RBL) 84 - High Frequency Eddy Current (HFEC) Inspection. Repeat Interval (Not to Exceed) Boeing Recommended Compliance Time (Whichever Oc- curs Later) ActionCondition -Within 4,500 flight cycles or 12,000 flight hours after the original issue date of Require- ments Bulletin 777-57A0122 RB, whichever occurs first. Before 16,000 total flight cycles or 50,000 total flight hours, whichever occurs first. ACTION 1: Do a surface High Frequency Eddy Cur- rent (HFEC) inspection of the right side ring chord for any crack. All Airplanes. ACTION 2: Do a surface High Frequency Eddy Cur- rent (HFEC) inspection of the right side front spar lower chord and front spar web for any crack. 10,000 flight cycles or 37,500 flight hours, whichever occurs first. -CONDITION 3 (ACTION 1): Repeat the surface High Frequency Eddy Current (HFEC) inspection of the right side ring chord for any crack. (a) CONDITION 3: NO CRACK FOUND. 16,000 flight cycles or 50,000 flight hours, whichever occurs first. -CONDITION 3 (ACTION 2): Repeat the surface High Frequency Eddy Current (HFEC) inspection of the right side front spar lower chord and front spar web for any crack. (a) -Before further flight.CONDITION 4 (ACTION 1): Contact The Boeing Compa- ny for repair instructions and do the repair. CONDITION 4: ANY CRACK FOUND. 10,000 flight cycles or 37,500 flight hours, whichever occurs first. -CONDITION 4 (ACTION 2): Repeat the surface High Frequency Eddy Current (HFEC) inspection of the right side ring chord for any crack. (a) 16,000 flight cycles or 64,000 flight hours, whichever occurs first. -CONDITION 4 (ACTION 3): Repeat the surface High Frequency Eddy Current (HFEC) inspection of the right side front spar lower chord and front spar web for any crack. (a) Export Controlled ECCN: 9E991 Copyright © Unpublished Work - See page 1 for details. Original Issue: October 08, 2021 777-57A0122 RB 34 of 968 REQUIREMENTS BULLETIN 777-57A0122 ALERTALERT ### Page 35 Group 1, Configuration 1, 5, 9, 13: Table 2: Wing - Front Spar at Station (STA) 1035, Right Body Line (RBL) 84 - High Frequency Eddy Current (HFEC) Inspection. Repeat Interval (Not to Exceed) Boeing Recommended Compliance Time (Whichever Oc- curs Later) ActionCondition (a) It is not required to do the repeat inspections of the ring chord, front spar lower chord or front spar web in areas where a repair covers the affected inspection zone provided: 1. The repair is the corrective action to the crack condition identified in Requirements Bulletin 777- 57A0122 RB and installed after the Original Issue date of Requirements Bulletin 777-57A0122 RB, AND 2. The installed repair was approved by the Boeing Company Organization Designation Authorization (ODA) via a FAA Form 8100-9. Group 1, Configuration 9-12: Table 3: Wing - Front Spar at Station (STA) 1035, Left Body Line (LBL) 84 - High Frequency Eddy Current (HFEC) Inspection. Repeat Interval (Not to Exceed) Boeing Recommended Compliance Time (Whichever Oc- curs Later) ActionCondition -Within 4,500 flight cycles or 12,000 flight hours after the original issue date of Require- ments Bulletin 777-57A0122 RB, whichever occurs first. Within 16,000 flight cycles or 64,000 flight hours after the left side front spar lower chord is repaired by SRM- 57-10-10, whichev- er occurs first. ACTION 1: Do a surface High Frequency Eddy Cur- rent (HFEC) inspection of the left side ring chord for any crack. All Airplanes. ACTION 2: Do a surface High Frequency Eddy Cur- rent (HFEC) inspection of the left side repair angle and front spar web for any crack. 10,000 flight cycles or 37,500 flight hours, whichever occurs first. -CONDITION 5 (ACTION 1): Repeat the surface High Frequency Eddy Current (HFEC) inspection of the left side ring chord for any crack. (a) CONDITION 5: NO CRACK FOUND. 16,000 flight cycles or 64,000 flight hours, whichever occurs first. -CONDITION 5 (ACTION 2): Repeat the surface High Frequency Eddy Current (HFEC) inspection of the left side repair angle and front spar web for any crack. (a) Export Controlled ECCN: 9E991 Copyright © Unpublished Work - See page 1 for details. Original Issue: October 08, 2021 777-57A0122 RB 35 of 968 REQUIREMENTS BULLETIN 777-57A0122 ALERTALERT ### Page 36 Group 1, Configuration 9-12: Table 3: Wing - Front Spar at Station (STA) 1035, Left Body Line (LBL) 84 - High Frequency Eddy Current (HFEC) Inspection. Repeat Interval (Not to Exceed) Boeing Recommended Compliance Time (Whichever Oc- curs Later) ActionCondition -Before further flight.CONDITION 6 (ACTION 1): Contact The Boeing Compa- ny for repair instructions and do the repair. CONDITION 6: ANY CRACK FOUND. 10,000 flight cycles or 37,500 flight hours, whichever occurs first. -CONDITION 6 (ACTION 2): Repeat the surface High Frequency Eddy Current (HFEC) inspection of the left side ring chord for any crack. (a) 16,000 flight cycles or 64,000 flight hours, whichever occurs first. -CONDITION 6 (ACTION 3): Repeat the surface High Frequency Eddy Current (HFEC) inspection of the left side repair angle and front spar web for any crack. (a) (a) It is not required to do the repeat inspections of the ring chord, front spar lower chord or front spar web in areas where a repair covers the affected inspection zone provided: 1. The repair is the corrective action to the crack condition identified in Requirements Bulletin 777- 57A0122 RB and installed after the Original Issue date of Requirements Bulletin 777-57A0122 RB, AND 2. The installed repair was approved by the Boeing Company Organization Designation Authorization (ODA) via a FAA Form 8100-9. Export Controlled ECCN: 9E991 Copyright © Unpublished Work - See page 1 for details. Original Issue: October 08, 2021 777-57A0122 RB 36 of 968 REQUIREMENTS BULLETIN 777-57A0122 ALERTALERT ### Page 37 Group 1, Configuration 3, 7, 11, 15: Table 4: Wing - Front Spar at Station (STA) 1035, Right Body Line (RBL) 84 - High Frequency Eddy Current (HFEC) Inspection. Repeat Interval (Not to Exceed) Boeing Recommended Compliance Time (Whichever Oc- curs Later) ActionCondition -Within 4,500 flight cycles or 12,000 flight hours after the original issue date of Require- ments Bulletin 777-57A0122 RB, whichever occurs first. Within 16,000 flight cycles or 64,000 flight hours after the right side front spar lower chord is repaired by SRM- 57-10-10, whichev- er occurs first. ACTION 1: Do a surface High Frequency Eddy Cur- rent (HFEC) inspection of the right side ring chord for any crack. All Airplanes. ACTION 2: Do a surface High Frequency Eddy Cur- rent (HFEC) inspection of the right side repair angle and front spar web for any crack. 10,000 flight cycles or 37,500 flight hours, whichever occurs first. -CONDITION 7 (ACTION 1): Repeat the surface High Frequency Eddy Current (HFEC) inspection of the right side ring chord for any crack. (a) CONDITION 7: NO CRACK FOUND. 16,000 flight cycles or 64,000 flight hours, whichever occurs first. -CONDITION 7 (ACTION 2): Repeat the surface High Frequency Eddy Current (HFEC) inspection of the right side repair angle and front spar web for any crack. (a) -Before further flight.CONDITION 8 (ACTION 1): Contact The Boeing Compa- ny for repair instructions and do the repair. CONDITION 8: ANY CRACK FOUND. 10,000 flight cycles or 37,500 flight hours, whichever occurs first. -CONDITION 8 (ACTION 2): Repeat the surface High Frequency Eddy Current (HFEC) inspection of the right side ring chord for any crack. (a) 16,000 flight cycles or 64,000 flight hours, whichever occurs first. -CONDITION 8 (ACTION 3): Repeat the surface High Frequency Eddy Current (HFEC) inspection of the right side repair angle and front spar web for any crack. (a) Export Controlled ECCN: 9E991 Copyright © Unpublished Work - See page 1 for details. Original Issue: October 08, 2021 777-57A0122 RB 37 of 968 REQUIREMENTS BULLETIN 777-57A0122 ALERTALERT ### Page 38 Group 1, Configuration 3, 7, 11, 15: Table 4: Wing - Front Spar at Station (STA) 1035, Right Body Line (RBL) 84 - High Frequency Eddy Current (HFEC) Inspection. Repeat Interval (Not to Exceed) Boeing Recommended Compliance Time (Whichever Oc- curs Later) ActionCondition (a) It is not required to do the repeat inspections of the ring chord, front spar lower chord or front spar web in areas where a repair covers the affected inspection zone provided: 1. The repair is the corrective action to the crack condition identified in Requirements Bulletin 777- 57A0122 RB and installed after the Original Issue date of Requirements Bulletin 777-57A0122 RB, AND 2. The installed repair was approved by the Boeing Company Organization Designation Authorization (ODA) via a FAA Form 8100-9. Group 1, Configuration 5-8: Table 5: Wing - Front Spar at Station (STA) 1035, Left Body Line (LBL) 84 - High Frequency Eddy Current (HFEC) Inspection. Repeat Interval (Not to Exceed) Boeing Recommended Compliance Time (Whichever Oc- curs Later) ActionCondition -Within 4,500 flight cycles or 12,000 flight hours after the original issue date of Require- ments Bulletin 777-57A0122 RB, whichever occurs first. Before 16,000 total flight cycles or 50,000 total flight hours, whichever occurs first. ACTION 1: Do a surface High Frequency Eddy Cur- rent (HFEC) inspection of the left side front spar lower chord and front spar web for any crack. All Airplanes. ACTION 2: Do a surface High Frequency Eddy Cur- rent (HFEC) inspection of the left side ring chord for any crack. 16,000 flight cycles or 50,000 flight hours, whichever occurs first. -CONDITION 9 (ACTION 1): Repeat the surface High Frequency Eddy Current (HFEC) inspection of the left side front spar lower chord and front spar web for any crack. (a) CONDITION 9: NO CRACK FOUND. 16,000 flight cycles or 60,000 flight hours, whichever occurs first. -CONDITION 9 (ACTION 2): Repeat the surface High Frequency Eddy Current (HFEC) inspection of the left side ring chord for any crack. (a) Export Controlled ECCN: 9E991 Copyright © Unpublished Work - See page 1 for details. Original Issue: October 08, 2021 777-57A0122 RB 38 of 968 REQUIREMENTS BULLETIN 777-57A0122 ALERTALERT ### Page 39 Group 1, Configuration 5-8: Table 5: Wing - Front Spar at Station (STA) 1035, Left Body Line (LBL) 84 - High Frequency Eddy Current (HFEC) Inspection. Repeat Interval (Not to Exceed) Boeing Recommended Compliance Time (Whichever Oc- curs Later) ActionCondition -Before further flight.CONDITION 10 (ACTION 1): Contact The Boeing Compa- ny for repair instructions and do the repair. CONDITION 10: ANY CRACK FOUND. 16,000 flight cycles or 60,000 flight hours, whichever occurs first. -CONDITION 10 (ACTION 2): Repeat the surface High Frequency Eddy Current (HFEC) inspection of the left side ring chord for any crack. (a) 16,000 flight cycles or 64,000 flight hours, whichever occurs first. -CONDITION 10 (ACTION 3): Repeat the surface High Frequency Eddy Current (HFEC) inspection of the left side front spar lower chord and front spar web for any crack. (a) (a) It is not required to do the repeat inspections of the ring chord, front spar lower chord or front spar web in areas where a repair covers the affected inspection zone provided: 1. The repair is the corrective action to the crack condition identified in Requirements Bulletin 777- 57A0122 RB and installed after the Original Issue date of Requirements Bulletin 777-57A0122 RB, AND 2. The installed repair was approved by the Boeing Company Organization Designation Authorization (ODA) via a FAA Form 8100-9. Export Controlled ECCN: 9E991 Copyright © Unpublished Work - See page 1 for details. Original Issue: October 08, 2021 777-57A0122 RB 39 of 968 REQUIREMENTS BULLETIN 777-57A0122 ALERTALERT ### Page 40 Group 1, Configuration 2, 6, 10, 14: Table 6: Wing - Front Spar at Station (STA) 1035, Right Body Line (RBL) 84 - High Frequency Eddy Current (HFEC) Inspection. Repeat Interval (Not to Exceed) Boeing Recommended Compliance Time (Whichever Oc- curs Later) ActionCondition -Within 4,500 flight cycles or 12,000 flight hours after the original issue date of Require- ments Bulletin 777-57A0122 RB, whichever occurs first. Before 16,000 total flight cycles or 50,000 total flight hours, whichever occurs first. ACTION 1: Do a surface High Frequency Eddy Cur- rent (HFEC) inspection of the right side front spar lower chord and front spar web for any crack. All Airplanes. ACTION 2: Do a surface High Frequency Eddy Cur- rent (HFEC) inspection of the right side ring chord for any crack. 16,000 flight cycles or 50,000 flight hours, whichever occurs first. -CONDITION 11 (ACTION 1): Repeat the surface High Frequency Eddy Current (HFEC) inspection of the right side front spar lower chord and front spar web for any crack. (a) CONDITION 11: NO CRACK FOUND. 16,000 flight cycles or 60,000 flight hours, whichever occurs first. -CONDITION 11 (ACTION 2): Repeat the surface High Frequency Eddy Current (HFEC) inspection of the right side ring chord for any crack. (a) -Before further flight.CONDITION 12 (ACTION 1): Contact The Boeing Compa- ny for repair instructions and do the repair. CONDITION 12: ANY CRACK FOUND. 16,000 flight cycles or 60,000 flight hours, whichever occurs first. -CONDITION 12 (ACTION 2): Repeat the surface High Frequency Eddy Current (HFEC) inspection of the right side ring chord for any crack. (a) 16,000 flight cycles or 64,000 flight hours, whichever occurs first. -CONDITION 12 (ACTION 3): Repeat the surface High Frequency Eddy Current (HFEC) inspection of the right side front spar lower chord and front spar web for any crack. (a) Export Controlled ECCN: 9E991 Copyright © Unpublished Work - See page 1 for details. Original Issue: October 08, 2021 777-57A0122 RB 40 of 968 REQUIREMENTS BULLETIN 777-57A0122 ALERTALERT ### Page 41 Group 1, Configuration 2, 6, 10, 14: Table 6: Wing - Front Spar at Station (STA) 1035, Right Body Line (RBL) 84 - High Frequency Eddy Current (HFEC) Inspection. Repeat Interval (Not to Exceed) Boeing Recommended Compliance Time (Whichever Oc- curs Later) ActionCondition (a) It is not required to do the repeat inspections of the ring chord, front spar lower chord or front spar web in areas where a repair covers the affected inspection zone provided: 1. The repair is the corrective action to the crack condition identified in Requirements Bulletin 777- 57A0122 RB and installed after the Original Issue date of Requirements Bulletin 777-57A0122 RB, AND 2. The installed repair was approved by the Boeing Company Organization Designation Authorization (ODA) via a FAA Form 8100-9. Group 1, Configuration 13-16: Table 7: Wing - Front Spar at Station (STA) 1035, Left Body Line (LBL) 84 - High Frequency Eddy Current (HFEC) Inspection. Repeat Interval (Not to Exceed) Boeing Recommended Compliance Time (Whichever Oc- curs Later) ActionCondition -Within 4,500 flight cycles or 12,000 flight hours after the original issue date of Require- ments Bulletin 777-57A0122 RB, whichever occurs first. Within 16,000 flight cycles or 64,000 flight hours after the left side front spar lower chord is repaired by SRM- 57-10-10, whichev- er occurs first. ACTION 1: Do a surface High Frequency Eddy Cur- rent (HFEC) inspection of the left side ring chord for any crack. All Airplanes. ACTION 2: Do a surface High Frequency Eddy Cur- rent (HFEC) inspection of the left side repair angle and front spar web for any crack. 16,000 flight cycles or 60,000 flight hours, whichever occurs first. -CONDITION 13 (ACTION 1): Repeat the surface High Frequency Eddy Current (HFEC) inspection of the left side ring chord for any crack. (a) CONDITION 13: NO CRACK FOUND. 16,000 flight cycles or 64,000 flight hours, whichever occurs first. -CONDITION 13 (ACTION 2): Repeat the surface High Frequency Eddy Current (HFEC) inspection of the left side repair angle and front spar web for any crack. (a) Export Controlled ECCN: 9E991 Copyright © Unpublished Work - See page 1 for details. Original Issue: October 08, 2021 777-57A0122 RB 41 of 968 REQUIREMENTS BULLETIN 777-57A0122 ALERTALERT ### Page 42 Group 1, Configuration 13-16: Table 7: Wing - Front Spar at Station (STA) 1035, Left Body Line (LBL) 84 - High Frequency Eddy Current (HFEC) Inspection. Repeat Interval (Not to Exceed) Boeing Recommended Compliance Time (Whichever Oc- curs Later) ActionCondition -Before further flight.CONDITION 14 (ACTION 1): Contact The Boeing Compa- ny for repair instructions and do the repair. CONDITION 14: ANY CRACK FOUND. 16,000 flight cycles or 60,000 flight hours, whichever occurs first. -CONDITION 14 (ACTION 2): Repeat the surface High Frequency Eddy Current (HFEC) inspection of the left side ring chord for any crack. (a) 16,000 flight cycles or 64,000 flight hours, whichever occurs first. -CONDITION 14 (ACTION 3): Repeat the surface High Frequency Eddy Current (HFEC) inspection of the left side repair angle and front spar web for any crack. (a) (a) It is not required to do the repeat inspections of the ring chord, front spar lower chord or front spar web in areas where a repair covers the affected inspection zone provided: 1. The repair is the corrective action to the crack condition identified in Requirements Bulletin 777- 57A0122 RB and installed after the Original Issue date of Requirements Bulletin 777-57A0122 RB, AND 2. The installed repair was approved by the Boeing Company Organization Designation Authorization (ODA) via a FAA Form 8100-9. Export Controlled ECCN: 9E991 Copyright © Unpublished Work - See page 1 for details. Original Issue: October 08, 2021 777-57A0122 RB 42 of 968 REQUIREMENTS BULLETIN 777-57A0122 ALERTALERT ### Page 43 Group 1, Configuration 4, 8, 12, 16: Table 8: Wing - Front Spar at Station (STA) 1035, Right Body Line (RBL) 84 - High Frequency Eddy Current (HFEC) Inspection. Repeat Interval (Not to Exceed) Boeing Recommended Compliance Time (Whichever Oc- curs Later) ActionCondition -Within 4,500 flight cycles or 12,000 flight hours after the original issue date of Require- ments Bulletin 777-57A0122 RB, whichever occurs first. Within 16,000 flight cycles or 64,000 flight hours after the right side front spar lower chord is repaired by SRM- 57-10-10, whichev- er occurs first. ACTION 1: Do a surface High Frequency Eddy Cur- rent (HFEC) inspection of the right side ring chord for any crack. All Airplanes. ACTION 2: Do a surface High Frequency Eddy Cur- rent (HFEC) inspection of the right side repair angle and front spar web for any crack. 16,000 flight cycles or 60,000 flight hours, whichever occurs first. -CONDITION 15 (ACTION 1): Repeat the surface High Frequency Eddy Current (HFEC) inspection of the right side ring chord for any crack. (a) CONDITION 15: NO CRACK FOUND. 16,000 flight cycles or 64,000 flight hours, whichever occurs first. -CONDITION 15 (ACTION 2): Repeat the surface High Frequency Eddy Current (HFEC) inspection of the right side repair angle and front spar web for any crack. (a) -Before further flight.CONDITION 16 (ACTION 1): Contact The Boeing Compa- ny for repair instructions and do the repair. CONDITION 16: ANY CRACK FOUND. 16,000 flight cycles or 60,000 flight hours, whichever occurs first. -CONDITION 16 (ACTION 2): Repeat the surface High Frequency Eddy Current (HFEC) inspection of the right side ring chord for any crack. (a) 16,000 flight cycles or 64,000 flight hours, whichever occurs first. -CONDITION 16 (ACTION 3): Repeat the surface High Frequency Eddy Current (HFEC) inspection of the right side repair angle and front spar web for any crack. (a) Export Controlled ECCN: 9E991 Copyright © Unpublished Work - See page 1 for details. Original Issue: October 08, 2021 777-57A0122 RB 43 of 968 REQUIREMENTS BULLETIN 777-57A0122 ALERTALERT ### Page 44 Group 1, Configuration 4, 8, 12, 16: Table 8: Wing - Front Spar at Station (STA) 1035, Right Body Line (RBL) 84 - High Frequency Eddy Current (HFEC) Inspection. Repeat Interval (Not to Exceed) Boeing Recommended Compliance Time (Whichever Oc- curs Later) ActionCondition (a) It is not required to do the repeat inspections of the ring chord, front spar lower chord or front spar web in areas where a repair covers the affected inspection zone provided: 1. The repair is the corrective action to the crack condition identified in Requirements Bulletin 777- 57A0122 RB and installed after the Original Issue date of Requirements Bulletin 777-57A0122 RB, AND 2. The installed repair was approved by the Boeing Company Organization Designation Authorization (ODA) via a FAA Form 8100-9. Group 2, Configuration 1-4; Group 3, Configuration 1-4; Group 7, Configuration 1-4; Group 8, Configuration 1-4: Table 9: Wing - Front Spar at Station (STA) 1035, Left Body Line (LBL) 84 - High Frequency Eddy Current (HFEC) and Ultrasonic (UT) Inspection. Repeat Interval (Not to Exceed) Boeing Recommended Compliance Time (Whichever Oc- curs Later) ActionCondition -Within 3,000 flight cycles or 12,000 flight hours after the original issue date of Require- ments Bulletin 777-57A0122 RB, whichever occurs first. Before 8,000 total flight cycles or 25,000 total flight hours, whichever occurs first. ACTION 1: Do a surface High Frequency Eddy Cur- rent (HFEC) inspection of the left side front spar lower chord and front spar web and do an Ultrasonic (UT) inspection of the left side front spar lower chord for any crack. All Airplanes. ACTION 2: Do a surface High Frequency Eddy Cur- rent (HFEC) inspection and an Ultrasonic (UT) inspection of the left side ring chord for any crack. Export Controlled ECCN: 9E991 Copyright © Unpublished Work - See page 1 for details. Original Issue: October 08, 2021 777-57A0122 RB 44 of 968 REQUIREMENTS BULLETIN 777-57A0122 ALERTALERT ### Page 45 Group 2, Configuration 1-4; Group 3, Configuration 1-4; Group 7, Configuration 1-4; Group 8, Configuration 1-4: Table 9: Wing - Front Spar at Station (STA) 1035, Left Body Line (LBL) 84 - High Frequency Eddy Current (HFEC) and Ultrasonic (UT) Inspection. Repeat Interval (Not to Exceed) Boeing Recommended Compliance Time (Whichever Oc- curs Later) ActionCondition 8,000 flight cycles or 25,000 flight hours, whichever occurs first. -CONDITION 17 (ACTION 1): Repeat the surface High Frequency Eddy Current (HFEC) inspection of the left side front spar lower chord and front spar web and re- peat the Ultrasonic (UT) in- spection of the left side front spar lower chord for any crack. (a)(b) CONDITION 17: NO CRACK FOUND. 11,000 flight cycles or 56,000 flight hours, whichever occurs first. -CONDITION 17 (ACTION 2): Repeat the surface High Frequency Eddy Current (HFEC) inspection and Ultra- sonic (UT) inspection of the left side ring chord for any crack (a)(b) -Before further flight.CONDITION 18 (ACTION 1): Contact The Boeing Compa- ny for repair instructions and do the repair. CONDITION 18: ANY CRACK FOUND. 8,000 flight cycles or 37,500 flight hours, whichever occurs first. -CONDITION 18 (ACTION 2): Repeat the surface High Frequency Eddy Current (HFEC) inspection of the left side ring chord for any crack. (a)(b) 11,000 flight cycles or 56,000 flight hours, whichever occurs first. -CONDITION 18 (ACTION 3): Repeat the surface High Frequency Eddy Current (HFEC) inspection of the left side front spar lower chord and front spar web of the left side front spar lower chord for any crack. (a)(b) Export Controlled ECCN: 9E991 Copyright © Unpublished Work - See page 1 for details. Original Issue: October 08, 2021 777-57A0122 RB 45 of 968 REQUIREMENTS BULLETIN 777-57A0122 ALERTALERT ### Page 46 Group 2, Configuration 1-4; Group 3, Configuration 1-4; Group 7, Configuration 1-4; Group 8, Configuration 1-4: Table 9: Wing - Front Spar at Station (STA) 1035, Left Body Line (LBL) 84 - High Frequency Eddy Current (HFEC) and Ultrasonic (UT) Inspection. Repeat Interval (Not to Exceed) Boeing Recommended Compliance Time (Whichever Oc- curs Later) ActionCondition (a) It is not required to do the repeat inspections of the ring chord, front spar lower chord or front spar web in areas where a repair covers the affected inspection zone provided: 1. The repair is the corrective action to the crack condition identified in Requirements Bulletin 777- 57A0122 RB and installed after the Original Issue date of Requirements Bulletin 777-57A0122 RB, AND 2. The installed repair was approved by the Boeing Company Organization Designation Authorization (ODA) via a FAA Form 8100-9. (b) Accomplishment of the left front spar lower chord modification must be done by the times given in the corresponding table and is a terminating action for this repeat inspection. Group 2, Configuration 1, 5, 9, 13; Group 3, Configuration 1, 5, 9, 13; Group 7, Configuration 1, 5, 9, 13; Group 8, Configuration 1, 5, 9, 13: Table 10: Wing - Front Spar at Station (STA) 1035, Right Body Line (RBL) 84 - High Frequency Eddy Current (HFEC) and Ultrasonic (UT) Inspection. Repeat Interval (Not to Exceed) Boeing Recommended Compliance Time (Whichever Oc- curs Later) ActionCondition -Within 3,000 flight cycles or 12,000 flight hours after the original issue date of Require- ments Bulletin 777-57A0122 RB, whichever occurs first. Before 8,000 total flight cycles or 25,000 total flight hours, whichever occurs first. ACTION 1: Do a surface High Frequency Eddy Cur- rent (HFEC) inspection of the right side front spar lower chord and front spar web and do an Ultrasonic (UT) inspection of the right side front spar lower chord for any crack. All Airplanes. ACTION 2: Do a surface High Frequency Eddy Cur- rent (HFEC) inspection and an Ultrasonic (UT) inspection of the right side ring chord for any crack. Export Controlled ECCN: 9E991 Copyright © Unpublished Work - See page 1 for details. Original Issue: October 08, 2021 777-57A0122 RB 46 of 968 REQUIREMENTS BULLETIN 777-57A0122 ALERTALERT ### Page 47 Group 2, Configuration 1, 5, 9, 13; Group 3, Configuration 1, 5, 9, 13; Group 7, Configuration 1, 5, 9, 13; Group 8, Configuration 1, 5, 9, 13: Table 10: Wing - Front Spar at Station (STA) 1035, Right Body Line (RBL) 84 - High Frequency Eddy Current (HFEC) and Ultrasonic (UT) Inspection. Repeat Interval (Not to Exceed) Boeing Recommended Compliance Time (Whichever Oc- curs Later) ActionCondition 8,000 flight cycles or 25,000 flight hours, whichever occurs first. -CONDITION 19 (ACTION 1): Repeat the surface High Frequency Eddy Current (HFEC) inspection of the right side front spar lower chord and front spar web and repeat the Ultrasonic (UT) inspection of the right side front spar lower chord for any crack. (a)(b) CONDITION 19: NO CRACK FOUND. 11,000 flight cycles or 56,000 flight hours, whichever occurs first. -CONDITION 19 (ACTION 2): Repeat the surface High Frequency Eddy Current (HFEC) inspection and Ultra- sonic (UT) inspection of the right side ring chord for any crack. (a)(b) -Before further flight.CONDITION 20 (ACTION 1): Contact The Boeing Compa- ny for repair instructions and do the repair. CONDITION 20: ANY CRACK FOUND. 8,000 flight cycles or 37,500 flight hours, whichever occurs first. -CONDITION 20 (ACTION 2): Repeat the surface High Frequency Eddy Current (HFEC) inspection of the right side ring chord for any crack. (a)(b) 11,000 flight cycles or 56,000 flight hours, whichever occurs first. -CONDITION 20 (ACTION 3): Repeat the surface High Frequency Eddy Current (HFEC) inspection of the right side front spar lower chord and front spar web for any crack. (a)(b) Export Controlled ECCN: 9E991 Copyright © Unpublished Work - See page 1 for details. Original Issue: October 08, 2021 777-57A0122 RB 47 of 968 REQUIREMENTS BULLETIN 777-57A0122 ALERTALERT ### Page 48 Group 2, Configuration 1, 5, 9, 13; Group 3, Configuration 1, 5, 9, 13; Group 7, Configuration 1, 5, 9, 13; Group 8, Configuration 1, 5, 9, 13: Table 10: Wing - Front Spar at Station (STA) 1035, Right Body Line (RBL) 84 - High Frequency Eddy Current (HFEC) and Ultrasonic (UT) Inspection. Repeat Interval (Not to Exceed) Boeing Recommended Compliance Time (Whichever Oc- curs Later) ActionCondition (a) It is not required to do the repeat inspections of the ring chord, front spar lower chord or front spar web in areas where a repair covers the affected inspection zone provided: 1. The repair is the corrective action to the crack condition identified in Requirements Bulletin 777- 57A0122 RB and installed after the Original Issue date of Requirements Bulletin 777-57A0122 RB, AND 2. The installed repair was approved by the Boeing Company Organization Designation Authorization (ODA) via a FAA Form 8100-9. (b) Accomplishment of the right front spar lower chord modification must be done by the times given in the corresponding table and is a terminating action for this repeat inspection. Group 2, Configuration 9-12; Group 3, Configuration 9-12; Group 7, Configuration 9-12; Group 8, Config- uration 9-12: Table 11: Wing - Front Spar at Station (STA) 1035, Left Body Line (LBL) 84 - High Frequency Eddy Current (HFEC) and Ultrasonic (UT) Inspection. Repeat Interval (Not to Exceed) Boeing Recommended Compliance Time (Whichever Oc- curs Later) ActionCondition -Within 3,000 flight cycles or 12,000 flight hours after the original issue date of Require- ments Bulletin 777-57A0122 RB, whichever occurs first. Within 10,000 flight cycles or 50,000 flight hours after the left side front spar lower chord is repaired by SRM- 57-10-10, whichev- er occurs first. ACTION 1: Do a surface High Frequency Eddy Cur- rent (HFEC) inspection of the left side repair angle and front spar web and do an Ul- trasonic (UT) inspection of the left side repair angle for any crack. All Airplanes. ACTION 2: Do a surface High Frequency Eddy Cur- rent (HFEC) inspection and Ultrasonic (UT) inspection of the left side ring chord for any crack. Export Controlled ECCN: 9E991 Copyright © Unpublished Work - See page 1 for details. Original Issue: October 08, 2021 777-57A0122 RB 48 of 968 REQUIREMENTS BULLETIN 777-57A0122 ALERTALERT ### Page 49 Group 2, Configuration 9-12; Group 3, Configuration 9-12; Group 7, Configuration 9-12; Group 8, Config- uration 9-12: Table 11: Wing - Front Spar at Station (STA) 1035, Left Body Line (LBL) 84 - High Frequency Eddy Current (HFEC) and Ultrasonic (UT) Inspection. Repeat Interval (Not to Exceed) Boeing Recommended Compliance Time (Whichever Oc- curs Later) ActionCondition 11,000 flight cycles or 56,000 flight hours, whichever occurs first. -CONDITION 21 (ACTION 1): Repeat the surface High Frequency Eddy Current (HFEC) inspection of the left side repair angle and front spar web and repeat the Ul- trasonic (UT) inspection of the left side repair angle for any crack. (a) CONDITION 21: NO CRACK FOUND. 11,000 flight cycles or 56,000 flight hours, whichever occurs first. -CONDITION 21 (ACTION 2): Repeat the surface High Frequency Eddy Current (HFEC) inspection and Ultra- sonic (UT) inspection of the left side ring chord for any crack. (a) -Before further flight.CONDITION 22 (ACTION 1): Contact The Boeing Compa- ny for repair instructions and do the repair. CONDITION 22: ANY CRACK FOUND. 8,000 flight cycles or 37,500 flight hours, whichever occurs first. -CONDITION 22 (ACTION 2): Repeat the surface High Frequency Eddy Current (HFEC) inspection of the left side ring chord for any crack. (a) 11,000 flight cycles or 56,000 flight hours, whichever occurs first. -CONDITION 22 (ACTION 3): Repeat the surface High Frequency Eddy Current (HFEC) inspection of the left side repair angle and front spar web for any crack. (a) (a) It is not required to do the repeat inspections of the ring chord, front spar lower chord or front spar web in areas where a repair covers the affected inspection zone provided: 1. The repair is the corrective action to the crack condition identified in Requirements Bulletin 777- 57A0122 RB and installed after the Original Issue date of Requirements Bulletin 777-57A0122 RB, AND 2. The installed repair was approved by the Boeing Company Organization Designation Authorization (ODA) via a FAA Form 8100-9. Export Controlled ECCN: 9E991 Copyright © Unpublished Work - See page 1 for details. Original Issue: October 08, 2021 777-57A0122 RB 49 of 968 REQUIREMENTS BULLETIN 777-57A0122 ALERTALERT ### Page 50 Group 2, Configuration 3, 7, 11, 15; Group 3, Configuration 3, 7, 11, 15; Group 7, Configuration 3, 7, 11, 15; Group 8, Configuration 3, 7, 11, 15: Table 12: Wing - Front Spar at Station (STA) 1035, Right Body Line (RBL) 84 - High Frequency Eddy Current (HFEC) and Ultrasonic (UT) Inspection. Repeat Interval (Not to Exceed) Boeing Recommended Compliance Time (Whichever Oc- curs Later) ActionCondition -Within 3,000 flight cycles or 12,000 flight hours after the original issue date of Require- ments Bulletin 777-57A0122 RB, whichever occurs first. Within 10,000 flight cycles or 50,000 flight hours after the right side front spar lower chord is repaired by SRM- 57-10-10, whichev- er occurs first. ACTION 1: Do a surface High Frequency Eddy Cur- rent (HFEC) inspection of the right side repair angle and front spar web and do an Ultrasonic (UT) inspection of the right side repair angle for any crack. All Airplanes. ACTION 2: Do a surface High Frequency Eddy Cur- rent (HFEC) inspection and Ultrasonic (UT) inspection of the right side ring chord for any crack. 11,000 flight cycles or 56,000 flight hours, whichever occurs first. -CONDITION 23 (ACTION 1): Repeat the surface High Frequency Eddy Current (HFEC) inspection of the right side repair angle and front spar web and repeat the Ultrasonic (UT) inspec- tion of the right side repair angle for any crack. (a) CONDITION 23: NO CRACK FOUND. 11,000 flight cycles or 56,000 flight hours, whichever occurs first. -CONDITION 23 (ACTION 2): Repeat the surface High Frequency Eddy Current (HFEC) inspection and Ultra- sonic (UT) inspection of the right side ring chord for any crack. (a) Export Controlled ECCN: 9E991 Copyright © Unpublished Work - See page 1 for details. Original Issue: October 08, 2021 777-57A0122 RB 50 of 968 REQUIREMENTS BULLETIN 777-57A0122 ALERTALERT ### Page 51 Group 2, Configuration 3, 7, 11, 15; Group 3, Configuration 3, 7, 11, 15; Group 7, Configuration 3, 7, 11, 15; Group 8, Configuration 3, 7, 11, 15: Table 12: Wing - Front Spar at Station (STA) 1035, Right Body Line (RBL) 84 - High Frequency Eddy Current (HFEC) and Ultrasonic (UT) Inspection. Repeat Interval (Not to Exceed) Boeing Recommended Compliance Time (Whichever Oc- curs Later) ActionCondition -Before further flight.CONDITION 24 (ACTION 1): Contact The Boeing Compa- ny for repair instructions and do the repair. CONDITION 24: ANY CRACK FOUND. 8,000 flight cycles or 37,500 flight hours, whichever occurs first. -CONDITION 24 (ACTION 3): Repeat the surface High Frequency Eddy Current (HFEC) inspection of the right side ring chord for any crack. (a) 11,000 flight cycles or 56,000 flight hours, whichever occurs first. -CONDITION 24 (ACTION 2): Repeat the surface High Frequency Eddy Current (HFEC) inspection of the right side repair angle and front spar web for any crack. (a) (a) It is not required to do the repeat inspections of the ring chord, front spar lower chord or front spar web in areas where a repair covers the affected inspection zone provided: 1. The repair is the corrective action to the crack condition identified in Requirements Bulletin 777- 57A0122 RB and installed after the Original Issue date of Requirements Bulletin 777-57A0122 RB, AND 2. The installed repair was approved by the Boeing Company Organization Designation Authorization (ODA) via a FAA Form 8100-9. Export Controlled ECCN: 9E991 Copyright © Unpublished Work - See page 1 for details. Original Issue: October 08, 2021 777-57A0122 RB 51 of 968 REQUIREMENTS BULLETIN 777-57A0122 ALERTALERT ### Page 52 Group 2, Configuration 5-8; Group 3, Configuration 5-8; Group 7, Configuration 5-8; Group 8, Configuration 5-8: Table 13: Wing - Front Spar at Station (STA) 1035, Left Body Line (LBL) 84 - High Frequency Eddy Current (HFEC) and Ultrasonic (UT) Inspection. Repeat Interval (Not to Exceed) Boeing Recommended Compliance Time (Whichever Oc- curs Later) ActionCondition -Within 3,000 flight cycles or 12,000 flight hours after the original issue date of Require- ments Bulletin 777-57A0122 RB, whichever occurs first. Before 8,000 total flight cycles or 25,000 total flight hours, whichever occurs first. ACTION 1: Do a surface High Frequency Eddy Cur- rent (HFEC) inspection of the left side front spar lower chord and front spar web and do an Ultrasonic (UT) inspection of the left side front spar lower chord for any crack. All Airplanes. ACTION 2: Do a surface High Frequency Eddy Cur- rent (HFEC) inspection of the left side ring chord for any crack. 8,000 flight cycles or 25,000 flight hours, whichever occurs first. -CONDITION 25 (ACTION 1): Repeat the surface High Frequency Eddy Current (HFEC) inspection of the left side front spar lower chord and front spar web and re- peat the Ultrasonic (UT) in- spection of the left side front spar lower chord for any crack. (a)(b) CONDITION 25: NO CRACK FOUND. 8,000 flight cycles or 37,500 flight hours, whichever occurs first. -CONDITION 25 (ACTION 2): Repeat the surface High Frequency Eddy Current (HFEC) inspection of the left side ring chord for any crack. (a)(b) Export Controlled ECCN: 9E991 Copyright © Unpublished Work - See page 1 for details. Original Issue: October 08, 2021 777-57A0122 RB 52 of 968 REQUIREMENTS BULLETIN 777-57A0122 ALERTALERT ### Page 53 Group 2, Configuration 5-8; Group 3, Configuration 5-8; Group 7, Configuration 5-8; Group 8, Configuration 5-8: Table 13: Wing - Front Spar at Station (STA) 1035, Left Body Line (LBL) 84 - High Frequency Eddy Current (HFEC) and Ultrasonic (UT) Inspection. Repeat Interval (Not to Exceed) Boeing Recommended Compliance Time (Whichever Oc- curs Later) ActionCondition -Before further flight.CONDITION 26 (ACTION 1): Contact The Boeing Compa- ny for repair instructions and do the repair. CONDITION 26: ANY CRACK FOUND. 8,000 flight cycles or 37,500 flight hours, whichever occurs first. -CONDITION 26 (ACTION 2): Repeat the surface High Frequency Eddy Current (HFEC) inspection of the left side ring chord for any crack. (a)(b) 11,000 flight cycles or 56,000 flight hours, whichever occurs first. -CONDITION 26 (ACTION 3): Repeat the surface High Frequency Eddy Current (HFEC) inspection of the left side front spar lower chord and front spar web of the left side front spar lower chord for any crack. (a)(b) (a) It is not required to do the repeat inspections of the ring chord, front spar lower chord or front spar web in areas where a repair covers the affected inspection zone provided: 1. The repair is the corrective action to the crack condition identified in Requirements Bulletin 777- 57A0122 RB and installed after the Original Issue date of Requirements Bulletin 777-57A0122 RB, AND 2. The installed repair was approved by the Boeing Company Organization Designation Authorization (ODA) via a FAA Form 8100-9. (b) Accomplishment of the left front spar lower chord modification must be done by the times given in the corresponding table and is a terminating action for this repeat inspection. Export Controlled ECCN: 9E991 Copyright © Unpublished Work - See page 1 for details. Original Issue: October 08, 2021 777-57A0122 RB 53 of 968 REQUIREMENTS BULLETIN 777-57A0122 ALERTALERT ### Page 54 Group 2, Configuration 2, 6, 10, 14; Group 3, Configuration 2, 6, 10, 14; Group 7, Configuration 2, 6, 10, 14; Group 8, Configuration 2, 6, 10, 14: Table 14: Wing - Front Spar at Station (STA) 1035, Right Body Line (RBL) 84 - High Frequency Eddy Current (HFEC) and Ultrasonic (UT) Inspection. Repeat Interval (Not to Exceed) Boeing Recommended Compliance Time (Whichever Oc- curs Later) ActionCondition -Within 3,000 flight cycles or 12,000 flight hours after the original issue date of Require- ments Bulletin 777-57A0122 RB, whichever occurs first. Before 8,000 total flight cycles or 25,000 total flight hours, whichever occurs first. ACTION 1: Do a surface High Frequency Eddy Cur- rent (HFEC) inspection of the right side front spar lower chord and front spar web and do an Ultrasonic (UT) inspection of the right side front spar lower chord for any crack. All Airplanes. ACTION 2: Do a surface High Frequency Eddy Cur- rent (HFEC) inspection of the right side ring chord for any crack. 8,000 flight cycles or 25,000 flight hours, whichever occurs first. -CONDITION 27 (ACTION 1): Repeat the surface High Frequency Eddy Current (HFEC) inspection of the right side front spar lower chord and front spar web and repeat the Ultrasonic (UT) inspection of the right side front spar lower chord for any crack. (a)(b) CONDITION 27: NO CRACK FOUND. 8,000 flight cycles or 37,500 flight hours, whichever occurs first. -CONDITION 27 (ACTION 2): Repeat the surface High Frequency Eddy Current (HFEC) inspection of the right side ring chord for any crack. (a)(b) Export Controlled ECCN: 9E991 Copyright © Unpublished Work - See page 1 for details. Original Issue: October 08, 2021 777-57A0122 RB 54 of 968 REQUIREMENTS BULLETIN 777-57A0122 ALERTALERT ### Page 55 Group 2, Configuration 2, 6, 10, 14; Group 3, Configuration 2, 6, 10, 14; Group 7, Configuration 2, 6, 10, 14; Group 8, Configuration 2, 6, 10, 14: Table 14: Wing - Front Spar at Station (STA) 1035, Right Body Line (RBL) 84 - High Frequency Eddy Current (HFEC) and Ultrasonic (UT) Inspection. Repeat Interval (Not to Exceed) Boeing Recommended Compliance Time (Whichever Oc- curs Later) ActionCondition -Before further flight.CONDITION 28 (ACTION 1): Contact The Boeing Compa- ny for repair instructions and do the repair. CONDITION 28: ANY CRACK FOUND. 8,000 flight cycles or 37,500 flight hours, whichever occurs first. -CONDITION 28 (ACTION 2): Repeat the surface High Frequency Eddy Current (HFEC) inspection of the right side ring chord for any crack. (a)(b) 11,000 flight cycles or 56,000 flight hours, whichever occurs first. -CONDITION 28 (ACTION 3): Repeat the surface High Frequency Eddy Current (HFEC) inspection of the right side front spar lower chord and front spar web for any crack. (a)(b) (a) It is not required to do the repeat inspections of the ring chord, front spar lower chord or front spar web in areas where a repair covers the affected inspection zone provided: 1. The repair is the corrective action to the crack condition identified in Requirements Bulletin 777- 57A0122 RB and installed after the Original Issue date of Requirements Bulletin 777-57A0122 RB, AND 2. The installed repair was approved by the Boeing Company Organization Designation Authorization (ODA) via a FAA Form 8100-9. (b) Accomplishment of the right front spar lower chord modification must be done by the times given in the corresponding table and is a terminating action for this repeat inspection. Export Controlled ECCN: 9E991 Copyright © Unpublished Work - See page 1 for details. Original Issue: October 08, 2021 777-57A0122 RB 55 of 968 REQUIREMENTS BULLETIN 777-57A0122 ALERTALERT ### Page 56 Group 2, Configuration 13-16; Group 3, Configuration 13-16; Group 7, Configuration 13-16; Group 8, Configuration 13-16: Table 15: Wing - Front Spar at Station (STA) 1035, Left Body Line (LBL) 84 - High Frequency Eddy Current (HFEC) and Ultrasonic (UT) Inspection. Repeat Interval (Not to Exceed) Boeing Recommended Compliance Time (Whichever Oc- curs Later) ActionCondition -Within 3,000 flight cycles or 12,000 flight hours after the original issue date of Require- ments Bulletin 777-57A0122 RB, whichever occurs first. Within 10,000 flight cycles or 50,000 flight hours after the left side front spar lower chord is repaired by SRM- 57-10-10, whichev- er occurs first. ACTION 1: Do a surface High Frequency Eddy Cur- rent (HFEC) inspection of the left side ring chord for any crack. All Airplanes. ACTION 2: Do a surface High Frequency Eddy Cur- rent (HFEC) inspection of the left side repair angle and front spar web and do an Ul- trasonic (UT) Inspection of the left side repair angle for any crack. 8,000 flight cycles or 37,500 flight hours, whichever occurs first. -CONDITION 29 (ACTION 1): Repeat the surface High Frequency Eddy Current (HFEC) inspection of the left side ring chord for any crack. (a) CONDITION 29: NO CRACK FOUND. 11,000 flight cycles or 56,000 flight hours, whichever occurs first. -CONDITION 29 (ACTION 2): Repeat the surface High Frequency Eddy Current (HFEC) inspection of the left side repair angle and front spar web and repeat the Ul- trasonic (UT) Inspection of the left side repair angle for any crack. (a) Export Controlled ECCN: 9E991 Copyright © Unpublished Work - See page 1 for details. Original Issue: October 08, 2021 777-57A0122 RB 56 of 968 REQUIREMENTS BULLETIN 777-57A0122 ALERTALERT ### Page 57 Group 2, Configuration 13-16; Group 3, Configuration 13-16; Group 7, Configuration 13-16; Group 8, Configuration 13-16: Table 15: Wing - Front Spar at Station (STA) 1035, Left Body Line (LBL) 84 - High Frequency Eddy Current (HFEC) and Ultrasonic (UT) Inspection. Repeat Interval (Not to Exceed) Boeing Recommended Compliance Time (Whichever Oc- curs Later) ActionCondition -Before further flight.CONDITION 30 (ACTION 1): Contact The Boeing Compa- ny for repair instructions and do the repair. CONDITION 30: ANY CRACK FOUND. 8,000 flight cycles or 37,500 flight hours, whichever occurs first. -CONDITION 30 (ACTION 2): Repeat the surface High Frequency Eddy Current (HFEC) inspection of the left side ring chord for any crack. (a) 11,000 flight cycles or 56,000 flight hours, whichever occurs first. -CONDITION 30 (ACTION 3): Repeat the surface High Frequency Eddy Current (HFEC) inspection of the left side repair angle and front spar web for any crack. (a) (a) It is not required to do the repeat inspections of the ring chord, front spar lower chord or front spar web in areas where a repair covers the affected inspection zone provided: 1. The repair is the corrective action to the crack condition identified in Requirements Bulletin 777- 57A0122 RB and installed after the Original Issue date of Requirements Bulletin 777-57A0122 RB, AND 2. The installed repair was approved by the Boeing Company Organization Designation Authorization (ODA) via a FAA Form 8100-9. Export Controlled ECCN: 9E991 Copyright © Unpublished Work - See page 1 for details. Original Issue: October 08, 2021 777-57A0122 RB 57 of 968 REQUIREMENTS BULLETIN 777-57A0122 ALERTALERT ### Page 58 Group 2, Configuration 4, 8, 12, 16; Group 3, Configuration 4, 8, 12, 16; Group 7, Configuration 4, 8, 12, 16; Group 8, Configuration 4, 8, 12, 16: Table 16: Wing - Front Spar at Station (STA) 1035, Right Body Line (RBL) 84 - High Frequency Eddy Current (HFEC) and Ultrasonic (UT) Inspection. Repeat Interval (Not to Exceed) Boeing Recommended Compliance Time (Whichever Oc- curs Later) ActionCondition -Within 3,000 flight cycles or 12,000 flight hours after the original issue date of Require- ments Bulletin 777-57A0122 RB, whichever occurs first. Within 10,000 flight cycles or 50,000 flight hours after the right side front spar lower chord is repaired by SRM- 57-10-10, whichev- er occurs first. ACTION 1: Do a surface High Frequency Eddy Cur- rent (HFEC) inspection of the right side ring chord for any crack. All Airplanes. ACTION 2: Do a surface High Frequency Eddy Cur- rent (HFEC) inspection of the right side repair angle and front spar web and do an Ultrasonic (UT) Inspec- tion of the right side repair angle for any crack. 8,000 flight cycles or 37,500 flight hours, whichever occurs first. -CONDITION 31 (ACTION 1): Repeat the surface High Frequency Eddy Current (HFEC) inspection of the right side ring chord for any crack. (a) CONDITION 31: NO CRACK FOUND. 11,000 flight cycles or 56,000 flight hours, whichever occurs first. -CONDITION 31 (ACTION 2): Repeat the surface High Frequency Eddy Current (HFEC) inspection of the right side repair angle and front spar web and repeat the Ultrasonic (UT) Inspec- tion of the right side repair angle for any crack. (a) Export Controlled ECCN: 9E991 Copyright © Unpublished Work - See page 1 for details. Original Issue: October 08, 2021 777-57A0122 RB 58 of 968 REQUIREMENTS BULLETIN 777-57A0122 ALERTALERT ### Page 59 Group 2, Configuration 4, 8, 12, 16; Group 3, Configuration 4, 8, 12, 16; Group 7, Configuration 4, 8, 12, 16; Group 8, Configuration 4, 8, 12, 16: Table 16: Wing - Front Spar at Station (STA) 1035, Right Body Line (RBL) 84 - High Frequency Eddy Current (HFEC) and Ultrasonic (UT) Inspection. Repeat Interval (Not to Exceed) Boeing Recommended Compliance Time (Whichever Oc- curs Later) ActionCondition -Before further flight.CONDITION 32 (ACTION 1): Contact The Boeing Compa- ny for repair instructions and do the repair. CONDITION 32: ANY CRACK FOUND. 8,000 flight cycles or 37,500 flight hours, whichever occurs first. -CONDITION 32 (ACTION 2): Repeat the surface High Frequency Eddy Current (HFEC) inspection of the right side ring chord for any crack. (a) 11,000 flight cycles or 56,000 flight hours, whichever occurs first. -CONDITION 32 (ACTION 3): Repeat the surface High Frequency Eddy Current (HFEC) inspection of the right side repair angle and front spar web for any crack. (a) (a) It is not required to do the repeat inspections of the ring chord, front spar lower chord or front spar web in areas where a repair covers the affected inspection zone provided: 1. The repair is the corrective action to the crack condition identified in Requirements Bulletin 777- 57A0122 RB and installed after the Original Issue date of Requirements Bulletin 777-57A0122 RB, AND 2. The installed repair was approved by the Boeing Company Organization Designation Authorization (ODA) via a FAA Form 8100-9. Export Controlled ECCN: 9E991 Copyright © Unpublished Work - See page 1 for details. Original Issue: October 08, 2021 777-57A0122 RB 59 of 968 REQUIREMENTS BULLETIN 777-57A0122 ALERTALERT ### Page 60 Group 2, Configuration 1-4: Table 17: Wing - Front Spar Lower Chord Modification at Station (STA) 1035, Left Body Line (LBL) 84. Repeat Interval (Not to Exceed) Boeing Recommended Compliance Time (Whichever Oc- curs Later) ActionCondition -Within 3,000 flight cycles or 12,000 flight hours after the original issue date of Require- ments Bulletin 777-57A0122 RB, whichever occurs first. Before 16,000 total flight cycles or 50,000 total flight hours, whichever occurs first. ACTION 1: Do a left side front spar lower chord modi- fication. All Airplanes. -Before further flight.Do a left side front spar low- er chord modification. CONDITION 109: ANY CRACK FOUND INSIDE THE FUSE- LAGE SKIN TRIM LINE BOUNDARY IN FIGURE 40. -Before further flight.Do a left side front spar low- er chord modification. CONDITION 110: NO CRACK FOUND IN- SIDE THE FUSE- LAGE SKIN TRIM LINE BOUNDARY IN FIGURE 40. Export Controlled ECCN: 9E991 Copyright © Unpublished Work - See page 1 for details. Original Issue: October 08, 2021 777-57A0122 RB 60 of 968 REQUIREMENTS BULLETIN 777-57A0122 ALERTALERT The text continues at https://openairdocs.org/service-documents/boeing/777-57a0122-rb/file/dbb3e2845441.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.