# Boeing Alert Service Bulletin 757-53A0100: Revision 1 - Rights: © The Boeing Company. Filed by the FAA in regulations.gov docket FAA-2017-0519; AD 2017-26-07 incorporates this document by reference. Not covered by OpenAirDocs’ CC0 dedication. - Document: [Boeing Alert Service Bulletin 757-53A0100](https://openairdocs.org/service-documents/boeing/757-53a0100.md) - Title as filed: SB-757-53A0100-00--BOEING - Pages: 120 - PDF: https://openairdocs.org/files/sha256/3a/29/3a29c04674c33e1c1d4e20cfd1f7599149928fa9edb604fe3650967eee6ab96e - Page: https://openairdocs.org/service-documents/boeing/757-53a0100/file/3a29c04674c3 ## Text Some pages are OCR from a scan. OCR can misread letters and numbers. Each page's text from the PDF; open the PDF at a page with #page=N. ### Page 1 Commercial Airplanes 757 Service Bulletin ALERT Number: 757-53A0100 Original Issue: November 14, 2016 ATA System: 5360 SUBJECT: FUSELAGE - Section 46 - Body Station 1681 Fuselage Frame Inspection Export of this technology is controlled under the United States Export Administration Regulations (EAR) (15 CFR 300-774). An export license may be required before it is used for development, production or use by foreign persons from specific countries. The controller of this data has the individual responsibility to abide by all export laws. 9E991ECCN: BOEING PROPRIETARY, CONFIDENTIAL AND/OR TRADE SECRET Copyright © 2016 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 Unpublished Work.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: November 14, 2016 757-53A0100 1 of 120 3.0 ### Page 2 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 14, 2016 757-53A0100 2 of 120 BOEING SERVICE BULLETIN 757-53A0100 ALERTALERT BLANK PAGE ### Page 3 Table of Contents S u m m a r y ...................................................... 5 1. PLANNING INFORMATION ........................................ 9 A . E f f e c t i v i t y ................................................ 9 1. Airplanes ............................................. 9 2 . S p a r e s A f f e c t e d ........................................ 1 3 B. Concurrent Requirements ...................................... 1 3 C. Reason ................................................ 1 3 D. Description .............................................. 1 4 E. Compliance .............................................. 1 4 F . A p p r o v a l ............................................... 3 2 G. Manpower .............................................. 3 2 H. Weight and Balance Changes .................................... 3 6 I. Electrical Load Data ......................................... 3 6 J . R e f e r e n c e s .............................................. 3 6 1. Existing Data: ......................................... 3 6 2. Data Supplied with this Service Bulletin: ........................... 3 6 3. Installation Drawings Used in the Preparation of this Service Bulletin: ........... 3 6 K. Publications Affected ........................................ 3 7 L. Interchangeability and Intermixability of Parts ........................... 3 7 M. Software Accomplishment Summary ................................ 3 7 2. MATERIAL INFORMATION ........................................ 3 9 A. Material - Price and Availability ................................... 3 9 B. Industry Support Information .................................... 3 9 C. Parts Necessary for Each Airplane ................................. 3 9 1 . K i t s / P a r t s ............................................ 3 9 2. Parts and Materials Supplied by the Operator ........................ 3 9 3. Parts Modified and Reidentified ................................ 4 0 4. Parts Removed and Not Replaced .............................. 4 0 D. Parts Necessary to Change Spares ................................. 4 0 E. Special Tooling - Price and Availability ............................... 4 0 F. Special Tooling Necessary to do this Service Bulletin ....................... 4 0 3. ACCOMPLISHMENT INSTRUCTIONS .................................. 4 1 A. GENERAL INFORMATION ..................................... 4 1 B. WORK INSTRUCTIONS ....................................... 4 2 FIGURE 1: LEFT SIDE - BODY STATION (STA) 1681 FUSELAGE FRAME ABOVE FLOOR - FORWARD INNER CHORD HIGH FREQUENCY EDDY CURRENT (HFEC) AND LOW FREQUENCY EDDY CURRENT (LFEC) INSPECTION [Group 1, Configuration 2-3; Group 2] .......... 4 8 FIGURE 2: RIGHT SIDE - BODY STATION (STA) 1681 FUSELAGE FRAME ABOVE FLOOR - FORWARD INNER CHORD HIGH FREQUENCY EDDY CURRENT (HFEC) AND LOW FREQUENCY EDDY CURRENT (LFEC) INSPECTION [Group 1, Configuration 2-3; Group 2] .......... 5 1 FIGURE 3: LEFT SIDE - BODY STATION (STA) 1681 FUSELAGE FRAME ABOVE FLOOR - AFT INNER AND OUTER CHORD HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION [Group 1, Configuration 1] ......................................... 5 4 FIGURE 4: RIGHT SIDE - BODY STATION (STA) 1681 FUSELAGE FRAME ABOVE FLOOR - AFT INNER AND OUTER CHORD HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION [Group 1, Configuration 1] ......................................... 5 7 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 14, 2016 757-53A0100 3 of 120 BOEING SERVICE BULLETIN 757-53A0100 ALERTALERT ### Page 4 FIGURE 5: LEFT SIDE - BODY STATION (STA) 1681 FUSELAGE FRAME ABOVE FLOOR - AFT INNER CHORD HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION [Group 1, Configuration 2-3; Group 2] .......................................... 6 0 FIGURE 6: RIGHT SIDE - BODY STATION (STA) 1681 FUSELAGE FRAME ABOVE FLOOR - AFT INNER CHORD HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION [Group 1, Configuration 2-3; Group 2] .......................................... 6 3 FIGURE 7: LEFT SIDE - BODY STATION (STA) 1681 FUSELAGE FRAME BELOW FLOOR - FORWARD AND AFT INNER AND OUTER CHORD HIGH FREQUENCY EDDY CURRENT (HFEC) AND LOW FREQUENCY EDDY CURRENT (LFEC) INSPECTION [Group 1, Configuration 1] . 66 FIGURE 8: RIGHT SIDE - BODY STATION (STA) 1681 FUSELAGE FRAME BELOW FLOOR - FORWARD AND AFT INNER AND OUTER CHORD HIGH FREQUENCY EDDY CURRENT (HFEC) AND LOW FREQUENCY EDDY CURRENT (LFEC) INSPECTION [Group 1, Configuration 1] . 70 FIGURE 9: LEFT SIDE - BODY STATION (STA) 1681 FUSELAGE FRAME BELOW FLOOR - AFT INNER CHORD HIGH FREQUENCY EDDY CURRENT (HFEC) AND LOW FREQUENCY EDDY CURRENT (LFEC) INSPECTION [Group 1, Configuration 2-3; Group 2] .......... 7 4 FIGURE 10: RIGHT SIDE - BODY STATION (STA) 1681 FUSELAGE FRAME BELOW FLOOR - AFT INNER CHORD HIGH FREQUENCY EDDY CURRENT (HFEC) AND LOW FREQUENCY EDDY CURRENT (LFEC) INSPECTION [Group 1, Configuration 2-3; Group 2] .......... 7 8 FIGURE 11: LEFT SIDE - BODY STATION (STA) 1681 FUSELAGE FRAME BELOW FLOOR - FORWARD AND AFT INNER AND OUTER CHORD HIGH FREQUENCY EDDY CURRENT (HFEC) AND LOW FREQUENCY EDDY CURRENT (LFEC) INSPECTION [Group 1, Configuration 1] . 82 FIGURE 12: RIGHT SIDE - BODY STATION (STA) 1681 FUSELAGE FRAME BELOW FLOOR - FORWARD AND AFT INNER AND OUTER CHORD HIGH FREQUENCY EDDY CURRENT (HFEC) AND LOW FREQUENCY EDDY CURRENT (LFEC) INSPECTION [Group 1, Configuration 1] . 86 FIGURE 13: LEFT SIDE - BODY STATION (STA) 1681 FUSELAGE FRAME BELOW FLOOR - AFT INNER CHORD HIGH FREQUENCY EDDY CURRENT (HFEC) AND LOW FREQUENCY EDDY CURRENT (LFEC) INSPECTION [Group 1, Configuration 2-3; Group 2] .......... 9 0 FIGURE 14: RIGHT SIDE - BODY STATION (STA) 1681 FUSELAGE FRAME BELOW FLOOR - AFT INNER CHORD HIGH FREQUENCY EDDY CURRENT (HFEC) AND LOW FREQUENCY EDDY CURRENT (LFEC) INSPECTION [Group 1, Configuration 2-3; Group 2] .......... 9 4 APPENDIX A: LOGIC DIAGRAM FOR COMPLIANCE TABLE 1: BODY STATION (STA) 1681 FUSELAGE FRAME HIGH FREQUENCY EDDY CURRENT (HFEC) AND LOW FREQUENCY EDDY CURRENT (LFEC) INSPECTION FOR ANY CRACK [Group 1, Configuration 1] ...... 9 8 APPENDIX B: LOGIC DIAGRAM FOR COMPLIANCE TABLE 2: BODY STATION (STA) 1681 FUSELAGE FRAME HIGH FREQUENCY EDDY CURRENT (HFEC) AND LOW FREQUENCY EDDY CURRENT (LFEC) INSPECTION FOR ANY CRACK [Group 1, Configuration 2] ..... 1 0 2 APPENDIX C: LOGIC DIAGRAM FOR COMPLIANCE TABLE 3: BODY STATION (STA) 1681 FUSELAGE FRAME HIGH FREQUENCY EDDY CURRENT (HFEC) AND LOW FREQUENCY EDDY CURRENT (LFEC) INSPECTION FOR ANY CRACK [Group 1, Configuration 3] ..... 1 0 7 APPENDIX D: LOGIC DIAGRAM FOR COMPLIANCE TABLE 4: BODY STATION (STA) 1681 FUSELAGE FRAME HIGH FREQUENCY EDDY CURRENT (HFEC) AND LOW FREQUENCY EDDY CURRENT (LFEC) INSPECTION FOR ANY CRACK [Group 2, Configuration 1] ..... 1 1 2 APPENDIX E: LOGIC DIAGRAM FOR COMPLIANCE TABLE 5: BODY STATION (STA) 1681 FUSELAGE FRAME HIGH FREQUENCY EDDY CURRENT (HFEC) AND LOW FREQUENCY EDDY CURRENT (LFEC) INSPECTION FOR ANY CRACK [Group 2, Configuration 2] ..... 1 1 7 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 14, 2016 757-53A0100 4 of 120 BOEING SERVICE BULLETIN 757-53A0100 ALERTALERT ### Page 5 Commercial Airplanes 757 Service Bulletin ALERT SummaryNumber: 757-53A0100Original Issue: November 14, 2016 ATA System: 5360 SUBJECT: FUSELAGE - Section 46 - Body Station 1681 Fuselage Frame Inspection 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. CONCURRENT REQUIREMENTS None. BACKGROUND This service bulletin provides instructions to do High Frequency Eddy Current (HFEC) and Low Frequency Eddy Current (LFEC) inspections for any crack in the fuselage frame at Body Station (STA) 1681, in the area around stringer S-17, on the left and right side of the airplane. If the work given in this service bulletin is not done, undetected cracking in the fuselage frame at STA 1681 could adversely affect the structural integrity of the airplane. One operator reported a six inch long crack in the fuselage frame web at STA 1681, below the floor line at stringer S-17L, during a routine maintenance visit. Boeing analysis has determined that the crack was caused by fatigue. The crack was not easily detected because it was significantly hidden by adjacent structure. Accomplishment of the work given in this service bulletin will mitigate the safety issue associated with cracking in the STA 1681 fuselage frame and make sure that any crack is found and repaired before the crack grows to a critical length. Boeing Fleet Team Digest (FTD) 757 FTD 53-14002 is related to this service bulletin. Boeing Service Related Problem (SRP) 757-SRP-53-0489 is related to this service bulletin. This table is provided to operators for planning purposes only. Refer to the applicable sections for more information. ReferenceAffectedPlanning Data Paragraph 1.A.2., Spares AffectedNoSpares Affected Paragraph 1.E., Compliance and Paragraph 1.F., Approval YesAD Related Paragraph 1.H., Weight and Balance ChangesNoWeight and Balance Change Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 14, 2016 757-53A0100 5 of 120 ### Page 6 ReferenceAffectedPlanning Data Paragraph 1.I., Electrical Load DataNoElectrical Load Changed Paragraph 1.K., Publications AffectedNoPublications Affected Paragraph 1.K., Publications AffectedNoAirplane Flight Operations Affected (Flight Crew Operations Manual and/or FAA Approved Air- plane Flight Manual) Paragraph 2.C.1., Kits/PartsNoKits/Parts Required Paragraph 2.C.2., Parts and Materials Supplied by the Operator YesOperator Supplied Parts/Material Paragraph 2.F., Special Tooling Necessary to do this Service Bulletin NoSpecial Tooling Required ACTION Get access to the Body Station (STA) 1681 fuselage frame, between stringer S-16 and S-18, on the left and right side of the airplane. Inspect for any existing frame repair and for any existing floor beam repair common to the STA 1681 frame inspection area. If any existing frame repair is found common to the STA 1681 fuselage frame inspection area, contact The Boeing Company for repair evaluation and inspection instructions and do the instructions. In areas with no existing frame repair, do High Frequency Eddy Current (HFEC) and Low Frequency Eddy Current (LFEC) inspections for any crack in the STA 1681 fuselage frame, in the area around stringer S-17. In areas with no existing floor beam repair, do the HFEC and LFEC inspections from the forward and aft side of the frame. In areas with any existing floor beam repair, do the HFEC and LFEC inspections from the aft side of the frame. If any crack is found, contact The Boeing Company for repair instructions and do the repair, and repeat the inspections in areas with no existing frame repair at the times specified in Paragraph 1.E., Compliance. If no crack is found, repeat the inspections at the times specified in Paragraph 1.E., Compliance. EFFECTIVITY 757-200, -200CB and -300 Airplanes. Refer to Paragraph 1.A.1., Airplanes, for the list of affected airplanes. COMPLIANCE The Federal Aviation Administration (FAA) will possibly release an Airworthiness Directive related to this service bulletin. The Airworthiness Directive will make the compliance tasks and times given in this service bulletin mandatory. Refer to Paragraph 1.E., Compliance. INDUSTRY SUPPORT INFORMATION Boeing warranty remedies are not available for the inspections given in this service bulletin. MANPOWER Refer to Paragraph 1.G., Manpower. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 14, 2016 757-53A0100 6 of 120 BOEING SERVICE BULLETIN 757-53A0100 ALERTALERT ### Page 7 (OCR) BOEING SERVICE BULLETIN 757-53A0100 ALERT ALERT MATERIAL INFORMATION Operator Supplied Parts/Materials. DO HIGH FREQUENCY EDDY CURRENT (HFEC) AND LOW FREQUENCY EDDY CURRENT (LFEC) INSPECTIONS FOR ANY CRACK IN THE STA 1681 FUSELAGE FRAME IN THE AREA AROUND STRINGER S-17. STA 1681 WL 208 S-17L • S-18L - FWD LEFT SIDE SHOWN RIGHT SIDE IS SIMILAR 2538018 Original Issue: November 14, 2016 Export Controlled ECCN: 9E991 - BOEING 757-53A0100 PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 7 of 120 ### Page 8 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 14, 2016 757-53A0100 8 of 120 BOEING SERVICE BULLETIN 757-53A0100 ALERTALERT BLANK PAGE ### Page 9 Commercial Airplanes 757 Service Bulletin ALERT Number: 757-53A0100 Original Issue: November 14, 2016 ATA System: 5360 SUBJECT: FUSELAGE - Section 46 - Body Station 1681 Fuselage Frame Inspection 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. 1. PLANNING INFORMATION A. Effectivity 1. Airplanes This service bulletin is applicable to 757-200, -200CB and -300 Airplanes, line numbers 1-1050 in 2 Groups. The Variable Numbers and Group Information for the applicable airplanes is given below. Refer to Service Bulletin Index D624N001 Part 3 for Airplane Variable Number, Line Number, and Serial Number data. DESCRIPTIONCONFIGURATIONGROUP 757-200 airplanes, line numbers 1-89.-1 757-200 airplanes that have not accomplished Boeing Service Bulletin (SB) 757-53-0024. 1 757-200 airplanes with less than 31,000 total flight cycles at the original issue date of this service bulletin, that have accomplished SB 757-53-0024. 2 757-200 airplanes with 31,000 total flight cycles or more at the original issue date of this service bulletin, that have accomplished SB 757-53-0024. 3 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 14, 2016 757-53A0100 9 of 120 ### Page 10 DESCRIPTIONCONFIGURATIONGROUP 757-200, -200CB and -300 airplanes, line numbers 90-1050.-2 757-200, -200CB and -300 airplanes with less than 31,000 total flight cycles at the original issue date of this service bulletin. 1 757-200, -200CB and -300 airplanes with 31,000 total flight cycles or more at the original issue date of this service bulletin. 2 Airplane Models: 757-200, 757-200CB, 757-300 GroupVariable Number 1NA001 - NA023 2NA024 - NA028 1NA191 - NA192 2NA193 - NA199 1NA201 - NA223 2NA224 - NA239 2NA301 - NA305 2NA341 - NA352 1NA391 2NA392 - NA399 1NA401 - NA404 2NA405 - NA408 2NA441 - NA447 1NA501 - NA515 2NA516 - NA586 1NB001 - NB004 1NB021 - NB023 2NB036 - NB041 2NB051 - NB053 2NB061 - NB073 2NB079 2NB131 - NB148 2NB161 - NB162 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 14, 2016 757-53A0100 10 of 120 BOEING SERVICE BULLETIN 757-53A0100 ALERTALERT ### Page 11 GroupVariable Number 2NB166 - NB168 2NB201 - NB204 2NB221 - NB228 2NB230 2NB236 2NB239 2NB261 - NB267 2NB291 - NB299 2NB301 - NB302 2NB311 - NB312 2NB321 - NB331 2NB421 - NB438 2NB446 2NB451 - NB454 2NB501 - NB523 2NB561 2NB571 2NB581 - NB583 1NC001 - NC014 2NC015 - NC033 2NC041 - NC042 2NC051 - NC052 2NC056 - NC062 2NC066 - NC084 2NC091 - NC094 2NC151 2NC161 2ND001 - ND007 2ND011 - ND059 2ND111 - ND113 2ND161 - ND199 2ND201 - ND203 2ND221 - ND225 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 14, 2016 757-53A0100 11 of 120 BOEING SERVICE BULLETIN 757-53A0100 ALERTALERT ### Page 12 GroupVariable Number 2ND241 - ND248 2ND301 - ND322 2ND401 2ND891 2ND895 2NE001 - NE008 2NE011 - NE088 2NE091 - NE094 2NE141 - NE150 2NE161 - NE177 2NE201 - NE204 2NE301 - NE302 2NE311 - NE325 2NJ001 - NJ004 2NJ031 - NJ032 2NJ551 - NJ555 2NL001 - NL002 2NL006 - NL017 2NL101 - NL109 2NL141 2NL601 - NL616 2NN001 - NN002 2NN051 - NN052 2NP901 - NP904 2NT201 - NT202 2NT231 - NT234 2NT237 - NT240 2NT242 2NT245 - NT248 2NT281 - NT289 2NT341 - NT347 2NT351 - NT360 2NT371 - NT373 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 14, 2016 757-53A0100 12 of 120 BOEING SERVICE BULLETIN 757-53A0100 ALERTALERT ### Page 13 GroupVariable Number 2NT375 - NT379 2NT381 - NT386 2NT401 - NT409 2NT411 - NT412 2NT426 - NT427 2NT431 - NT432 2NT436 - NT438 2NT441 - NT442 2NT446 2NT701 - NT769 2NT791 - NT796 2NT861 - NT862 2NT881 - NT885 2NT901 - NT916 2NT971 - NT985 2NU031 - NU038 2NU701 - NU705 2NU721 - NU728 2NU731 - NU732 2. Spares Affected None. B. Concurrent Requirements None. C. Reason This service bulletin provides instructions to do High Frequency Eddy Current (HFEC) and Low Frequency Eddy Current (LFEC) inspections for any crack in the fuselage frame at Body Station (STA) 1681, in the area around stringer S-17, on the left and right side of the airplane. If the work given in this service bulletin is not done, undetected cracking in the fuselage frame at STA 1681 could adversely affect the structural integrity of the airplane. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 14, 2016 757-53A0100 13 of 120 BOEING SERVICE BULLETIN 757-53A0100 ALERTALERT ### Page 14 One operator reported a six inch long crack in the fuselage frame web at STA 1681, below the floor line at stringer S-17L, during a routine maintenance visit. Boeing analysis has determined that the crack was caused by fatigue. The crack was not easily detected because it was significantly hidden by adjacent structure. Accomplishment of the work given in this service bulletin will mitigate the safety issue associated with cracking in the STA 1681 fuselage frame and make sure that any crack is found and repaired before the crack grows to a critical length. Boeing Fleet Team Digest (FTD) 757 FTD 53-14002 is related to this service bulletin. Boeing Service Related Problem (SRP) 757-SRP-53-0489 is related to this service bulletin. D. Description Get access to the Body Station (STA) 1681 fuselage frame, between stringer S-16 and S-18, on the left and right side of the airplane. Inspect for any existing frame repair and for any existing floor beam repair common to the STA 1681 frame inspection area. If any existing frame repair is found common to the STA 1681 fuselage frame inspection area, contact The Boeing Company for repair evaluation and inspection instructions and do the instructions. In areas with no existing frame repair, do High Frequency Eddy Current (HFEC) and Low Frequency Eddy Current (LFEC) inspections for any crack in the STA 1681 fuselage frame, in the area around stringer S-17. In areas with no existing floor beam repair, do the HFEC and LFEC inspections from the forward and aft side of the frame. In areas with any existing floor beam repair, do the HFEC and LFEC inspections from the aft side of the frame. If any crack is found, contact The Boeing Company for repair instructions and do the repair, and repeat the inspections in areas with no existing frame repair at the times specified in Paragraph 1.E., Compliance. If no crack is found, repeat the inspections at the times specified in Paragraph 1.E., Compliance. The work in this service bulletin is done in the maintenance zone(s) given below. Group 1: Affected Maintenance Zones ZoneModel 165, 166757-200 Group 2: Affected Maintenance Zones ZoneModel 165, 166757-200, 757-200CB, 757-300 E. Compliance The Federal Aviation Administration (FAA) will possibly release an Airworthiness Directive related to this service bulletin. The Airworthiness Directive will make the compliance tasks and times given in this service bulletin mandatory. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 14, 2016 757-53A0100 14 of 120 BOEING SERVICE BULLETIN 757-53A0100 ALERTALERT ### Page 15 Accomplish the required actions, based on the applicable conditions in Tables 1 through 5, in accordance with Paragraph 3. Accomplishment Instructions. A logic diagram showing compliance tasks and compliance times is included as an aid in APPENDIX A, APPENDIX B, APPENDIX C, APPENDIX D and APPENDIX E. 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 number or an OPTION number, do all of the ACTION numbers for that CONDITION number or OPTION number. Group 1, Configuration 1: Table 1: Body Station (STA) 1681 fuselage frame High Frequency Eddy Current (HFEC) and Low Frequency Eddy Current (LFEC) inspection for any crack Repeat Interval (Not to Exceed) Compliance TimeActionCondition -Within 300 flight cycles after the original issue date of this service bulletin. Inspect for any existing frame repair and for any existing floor beam re- pair common to the STA 1681 frame inspection area. All airplanes. -Before further flight.Contact The Boeing Company for repair evaluation and inspection in- structions and do the instructions. CONDITION 1: ANY EXISTING FRAME REPAIR COMMON TO THE STA 1681 FUSELAGE FRAME INSPEC- TION AREA -Within 300 flight cycles after the original issue date of this service bulletin. Do PART 3: AFT SIDE BODY STA- TION (STA) 1681 FUSELAGE FRAME HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTIONS for any crack in areas with no exist- ing frame repair. CONDITION 2: NO EXISTING FRAME REPAIR COMMON TO THE STA 1681 FUSELAGE FRAME INSPEC- TION AREA (a) -Within 300 flight cycles after the original issue date of this service bulletin. Do PART 4: BELOW THE FLOOR BODY STATION (STA) 1681 FUSELAGE FRAME HIGH FRE- QUENCY EDDY CURRENT (HFEC) AND LOW FREQUENCY EDDY CURRENT (LFEC) INSPECTIONS for any crack in areas with no exist- ing frame repair and no existing floor beam repair. CONDITION 3: NO EXISTING FLOOR BEAM REPAIR COM- MON TO THE STA 1681 FUSE- LAGE FRAME IN- SPECTION AREA (a) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 14, 2016 757-53A0100 15 of 120 BOEING SERVICE BULLETIN 757-53A0100 ALERTALERT ### Page 16 Group 1, Configuration 1: Table 1: Body Station (STA) 1681 fuselage frame High Frequency Eddy Current (HFEC) and Low Frequency Eddy Current (LFEC) inspection for any crack Repeat Interval (Not to Exceed) Compliance TimeActionCondition -Within 300 flight cycles after the original issue date of this service bulletin. Do PART 5: BELOW THE FLOOR BODY STATION (STA) 1681 FUSELAGE FRAME HIGH FRE- QUENCY EDDY CURRENT (HFEC) AND LOW FREQUENCY EDDY CURRENT (LFEC) INSPECTIONS for any crack in areas with no exist- ing frame repair. CONDITION 4: ANY EXISTING FLOOR BEAM REPAIR COM- MON TO THE STA 1681 FUSE- LAGE FRAME IN- SPECTION AREA (a) -Before further flight.(ACTION 1): Contact The Boeing Company for repair instructions and do the repair. CONDITION 7: ANY CRACK FOUND DURING PART 3 INSPEC- TION 3,200 flight cy-cles.-(ACTION 2): Repeat PART 3: AFTSIDE BODY STATION (STA) 1681 FUSELAGE FRAME HIGH FRE- QUENCY EDDY CURRENT (HFEC) INSPECTIONS for any crack in ar- eas with no existing frame repair. 3,200 flight cy- cles. -Repeat PART 3: AFT SIDE BODY STATION (STA) 1681 FUSELAGE FRAME HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTIONS for any crack in areas with no exist- ing frame repair. CONDITION 8: NO CRACK FOUND DURING PART 3 INSPEC- TION -Before further flight.(ACTION 1): Contact The Boeing Company for repair instructions and do the repair. CONDITION 9: ANY CRACK FOUND DURING PART 4 INSPEC- TION 3,200 flight cy-cles.-(ACTION 2): Repeat PART 4: BE-LOW THE FLOOR BODY STATION (STA) 1681 FUSELAGE FRAME HIGH FREQUENCY EDDY CUR- RENT (HFEC) AND LOW FRE- QUENCY EDDY CURRENT (LFEC) INSPECTIONS for any crack in ar- eas with no existing frame repair and no existing floor beam repair. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 14, 2016 757-53A0100 16 of 120 BOEING SERVICE BULLETIN 757-53A0100 ALERTALERT ### Page 17 Group 1, Configuration 1: Table 1: Body Station (STA) 1681 fuselage frame High Frequency Eddy Current (HFEC) and Low Frequency Eddy Current (LFEC) inspection for any crack Repeat Interval (Not to Exceed) Compliance TimeActionCondition 3,200 flight cy- cles. -Repeat PART 4: BELOW THE FLOOR BODY STATION (STA) 1681 FUSELAGE FRAME HIGH FREQUENCY EDDY CURRENT (HFEC) AND LOW FREQUENCY EDDY CURRENT (LFEC) INSPEC- TIONS for any crack in areas with no existing frame repair and no ex- isting floor beam repair. CONDITION 10: NO CRACK FOUND DURING PART 4 INSPEC- TION -Before further flight.(ACTION 1): Contact The Boeing Company for repair instructions and do the repair. CONDITION 11: ANY CRACK FOUND DURING PART 5 INSPEC- TION 1,600 flight cy-cles.-(ACTION 2): Repeat PART 5: BE-LOW THE FLOOR BODY STATION (STA) 1681 FUSELAGE FRAME HIGH FREQUENCY EDDY CUR- RENT (HFEC) AND LOW FRE- QUENCY EDDY CURRENT (LFEC) INSPECTIONS for any crack in ar- eas with no existing frame repair. 1,600 flight cy- cles. -Repeat PART 5: BELOW THE FLOOR BODY STATION (STA) 1681 FUSELAGE FRAME HIGH FREQUENCY EDDY CURRENT (HFEC) AND LOW FREQUENCY EDDY CURRENT (LFEC) INSPEC- TIONS for any crack in areas with no existing frame repair. CONDITION 12: NO CRACK FOUND DURING PART 5 INSPEC- TION (a) More than one CONDITION can be applicable in areas with no existing frame repair. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 14, 2016 757-53A0100 17 of 120 BOEING SERVICE BULLETIN 757-53A0100 ALERTALERT ### Page 18 Group 1, Configuration 2: Table 2: Body Station (STA) 1681 fuselage frame High Frequency Eddy Current (HFEC) and Low Frequency Eddy Current (LFEC) inspection for any crack Repeat Interval (Not to Exceed) Compliance Time (Whichever Occurs Later) ActionCondition -Within 3,000 flight cycles after the original issue date of this ser- vice bulletin, or before 31,500 to- tal flight cycles, whichever oc- curs first. Before 25,000 total flight cycles. Inspect for any existing frame repair and for any existing floor beam re- pair common to the STA 1681 frame inspection area. 757-200 airplanes with less than 31,000 total flight cycles at the origi- nal issue date of this service bul- letin, that have ac- complished SB 757-53-0024. -Before further flight.Contact The Boeing Company for repair evaluation and inspection in- structions and do the instructions. CONDITION 1: ANY EXISTING FRAME REPAIR COMMON TO THE STA 1681 FUSELAGE FRAME INSPEC- TION AREA -Within 3,000 flight cycles after the original issue date of this ser- vice bulletin, or before 31,500 to- tal flight cycles, whichever oc- curs first. Before 25,000 total flight cycles. OPTION 1: Do PART 2: FORWARD SIDE BODY STATION (STA) 1681 FUSELAGE FRAME HIGH FRE- QUENCY EDDY CURRENT (HFEC) AND LOW FREQUENCY EDDY CURRENT (LFEC) INSPECTIONS for any crack in areas with no exist- ing frame repair. CONDITION 2: NO EXISTING FRAME REPAIR COMMON TO THE STA 1681 FUSELAGE FRAME INSPEC- TION AREA (a) -Within 3,000 flight cycles after the original issue date of this ser- vice bulletin, or before 31,500 to- tal flight cycles, whichever oc- curs first. Before 25,000 total flight cycles. OPTION 2: Do PART 3: AFT SIDE BODY STATION (STA) 1681 FUSELAGE FRAME HIGH FRE- QUENCY EDDY CURRENT (HFEC) INSPECTIONS for any crack in ar- eas with no existing frame repair. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 14, 2016 757-53A0100 18 of 120 BOEING SERVICE BULLETIN 757-53A0100 ALERTALERT ### Page 19 Group 1, Configuration 2: Table 2: Body Station (STA) 1681 fuselage frame High Frequency Eddy Current (HFEC) and Low Frequency Eddy Current (LFEC) inspection for any crack Repeat Interval (Not to Exceed) Compliance Time (Whichever Occurs Later) ActionCondition -Within 3,000 flight cycles after the original issue date of this ser- vice bulletin, or before 31,500 to- tal flight cycles, whichever oc- curs first. Before 25,000 total flight cycles. Do PART 4: BELOW THE FLOOR BODY STATION (STA) 1681 FUSELAGE FRAME HIGH FRE- QUENCY EDDY CURRENT (HFEC) AND LOW FREQUENCY EDDY CURRENT (LFEC) INSPECTIONS for any crack in areas with no exist- ing frame repair and no existing floor beam repair. CONDITION 3: NO EXISTING FLOOR BEAM REPAIR COM- MON TO THE STA 1681 FUSE- LAGE FRAME IN- SPECTION AREA (a) -Within 3,000 flight cycles after the original issue date of this ser- vice bulletin, or before 31,500 to- tal flight cycles, whichever oc- curs first. Before 25,000 total flight cycles. Do PART 5: BELOW THE FLOOR BODY STATION (STA) 1681 FUSELAGE FRAME HIGH FRE- QUENCY EDDY CURRENT (HFEC) AND LOW FREQUENCY EDDY CURRENT (LFEC) INSPECTIONS for any crack in areas with no exist- ing frame repair. CONDITION 4: ANY EXISTING FLOOR BEAM REPAIR COM- MON TO THE STA 1681 FUSE- LAGE FRAME IN- SPECTION AREA (a) -Before further flight.(ACTION 1): Contact The Boeing Company for repair instructions and do the repair. CONDITION 5: ANY CRACK FOUND DURING PART 2 INSPEC- TION 1,300 flight cy-cles.-(ACTION 2): Repeat PART 2: FOR-WARD SIDE BODY STATION (STA) 1681 FUSELAGE FRAME HIGH FREQUENCY EDDY CURRENT (HFEC) AND LOW FREQUENCY EDDY CURRENT (LFEC) INSPEC- TIONS for any crack in areas with no existing frame repair. (b) 1,300 flight cy- cles. -Repeat PART 2: FORWARD SIDE BODY STATION (STA) 1681 FUSELAGE FRAME HIGH FRE- QUENCY EDDY CURRENT (HFEC) AND LOW FREQUENCY EDDY CURRENT (LFEC) INSPECTIONS for any crack in areas with no exist- ing frame repair. (b) CONDITION 6: NO CRACK FOUND DURING PART 2 INSPEC- TION Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 14, 2016 757-53A0100 19 of 120 BOEING SERVICE BULLETIN 757-53A0100 ALERTALERT ### Page 20 Group 1, Configuration 2: Table 2: Body Station (STA) 1681 fuselage frame High Frequency Eddy Current (HFEC) and Low Frequency Eddy Current (LFEC) inspection for any crack Repeat Interval (Not to Exceed) Compliance Time (Whichever Occurs Later) ActionCondition -Before further flight.(ACTION 1): Contact The Boeing Company for repair instructions and do the repair. CONDITION 7: ANY CRACK FOUND DURING PART 3 INSPEC- TION 5,800 flight cy-cles.-(ACTION 2): Repeat PART 3: AFTSIDE BODY STATION (STA) 1681 FUSELAGE FRAME HIGH FRE- QUENCY EDDY CURRENT (HFEC) INSPECTIONS for any crack in ar- eas with no existing frame repair. (b) 5,800 flight cy- cles. -Repeat PART 3: AFT SIDE BODY STATION (STA) 1681 FUSELAGE FRAME HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTIONS for any crack in areas with no exist- ing frame repair. (b) CONDITION 8: NO CRACK FOUND DURING PART 3 INSPEC- TION -Before further flight.(ACTION 1): Contact The Boeing Company for repair instructions and do the repair. CONDITION 9: ANY CRACK FOUND DURING PART 4 INSPEC- TION 4,100 flight cy-cles.-(ACTION 2): Repeat PART 4: BE-LOW THE FLOOR BODY STATION (STA) 1681 FUSELAGE FRAME HIGH FREQUENCY EDDY CUR- RENT (HFEC) AND LOW FRE- QUENCY EDDY CURRENT (LFEC) INSPECTIONS for any crack in ar- eas with no existing frame repair and no existing floor beam repair. 4,100 flight cy- cles. -Repeat PART 4: BELOW THE FLOOR BODY STATION (STA) 1681 FUSELAGE FRAME HIGH FREQUENCY EDDY CURRENT (HFEC) AND LOW FREQUENCY EDDY CURRENT (LFEC) INSPEC- TIONS for any crack in areas with no existing frame repair and no ex- isting floor beam repair. CONDITION 10: NO CRACK FOUND DURING PART 4 INSPEC- TION Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 14, 2016 757-53A0100 20 of 120 BOEING SERVICE BULLETIN 757-53A0100 ALERTALERT ### Page 21 Group 1, Configuration 2: Table 2: Body Station (STA) 1681 fuselage frame High Frequency Eddy Current (HFEC) and Low Frequency Eddy Current (LFEC) inspection for any crack Repeat Interval (Not to Exceed) Compliance Time (Whichever Occurs Later) ActionCondition -Before further flight.(ACTION 1): Contact The Boeing Company for repair instructions and do the repair. CONDITION 11: ANY CRACK FOUND DURING PART 5 INSPEC- TION 3,000 flight cy-cles.-(ACTION 2): Repeat PART 5: BE-LOW THE FLOOR BODY STATION (STA) 1681 FUSELAGE FRAME HIGH FREQUENCY EDDY CUR- RENT (HFEC) AND LOW FRE- QUENCY EDDY CURRENT (LFEC) INSPECTIONS for any crack in ar- eas with no existing frame repair. 3,000 flight cy- cles. -Repeat PART 5: BELOW THE FLOOR BODY STATION (STA) 1681 FUSELAGE FRAME HIGH FREQUENCY EDDY CURRENT (HFEC) AND LOW FREQUENCY EDDY CURRENT (LFEC) INSPEC- TIONS for any crack in areas with no existing frame repair. CONDITION 12: NO CRACK FOUND DURING PART 5 INSPEC- TION (a) More than one CONDITION can be applicable in areas with no existing frame repair. (b) It is acceptable to change the repeat inspection method from PART 2 to PART 3 or from PART 3 to PART 2 provided the repeat interval for the previously accomplished inspection method is complied with. Group 1, Configuration 3: Table 3: Body Station (STA) 1681 fuselage frame High Frequency Eddy Current (HFEC) and Low Frequency Eddy Current (LFEC) inspection for any crack Repeat Interval (Not to Exceed) Compliance TimeActionCondition -Within 500 flight cycles after the original issue date of this service bulletin. Inspect for any existing frame repair and for any existing floor beam re- pair common to the STA 1681 frame inspection area. 757-200 airplanes with 31,000 total flight cycles or more at the origi- nal issue date of this service bul- letin, that have ac- complished SB 757-53-0024. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 14, 2016 757-53A0100 21 of 120 BOEING SERVICE BULLETIN 757-53A0100 ALERTALERT ### Page 22 Group 1, Configuration 3: Table 3: Body Station (STA) 1681 fuselage frame High Frequency Eddy Current (HFEC) and Low Frequency Eddy Current (LFEC) inspection for any crack Repeat Interval (Not to Exceed) Compliance TimeActionCondition -Before further flight.Contact The Boeing Company for repair evaluation and inspection in- structions and do the instructions. CONDITION 1: ANY EXISTING FRAME REPAIR COMMON TO THE STA 1681 FUSELAGE FRAME INSPEC- TION AREA -Within 500 flight cycles after the original issue date of this service bulletin. OPTION 1: Do PART 2: FORWARD SIDE BODY STATION (STA) 1681 FUSELAGE FRAME HIGH FRE- QUENCY EDDY CURRENT (HFEC) AND LOW FREQUENCY EDDY CURRENT (LFEC) INSPECTIONS for any crack in areas with no exist- ing frame repair. CONDITION 2: NO EXISTING FRAME REPAIR COMMON TO THE STA 1681 FUSELAGE FRAME INSPEC- TION AREA (a) -Within 500 flight cycles after the original issue date of this service bulletin. OPTION 2: Do PART 3: AFT SIDE BODY STATION (STA) 1681 FUSELAGE FRAME HIGH FRE- QUENCY EDDY CURRENT (HFEC) INSPECTIONS for any crack in ar- eas with no existing frame repair. -Within 500 flight cycles after the original issue date of this service bulletin. Do PART 4: BELOW THE FLOOR BODY STATION (STA) 1681 FUSELAGE FRAME HIGH FRE- QUENCY EDDY CURRENT (HFEC) AND LOW FREQUENCY EDDY CURRENT (LFEC) INSPECTIONS for any crack in areas with no exist- ing frame repair and no existing floor beam repair. CONDITION 3: NO EXISTING FLOOR BEAM REPAIR COM- MON TO THE STA 1681 FUSE- LAGE FRAME IN- SPECTION AREA (a) -Within 500 flight cycles after the original issue date of this service bulletin. Do PART 5: BELOW THE FLOOR BODY STATION (STA) 1681 FUSELAGE FRAME HIGH FRE- QUENCY EDDY CURRENT (HFEC) AND LOW FREQUENCY EDDY CURRENT (LFEC) INSPECTIONS for any crack in areas with no exist- ing frame repair. CONDITION 4: ANY EXISTING FLOOR BEAM REPAIR COM- MON TO THE STA 1681 FUSE- LAGE FRAME IN- SPECTION AREA (a) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 14, 2016 757-53A0100 22 of 120 BOEING SERVICE BULLETIN 757-53A0100 ALERTALERT ### Page 23 Group 1, Configuration 3: Table 3: Body Station (STA) 1681 fuselage frame High Frequency Eddy Current (HFEC) and Low Frequency Eddy Current (LFEC) inspection for any crack Repeat Interval (Not to Exceed) Compliance TimeActionCondition -Before further flight.(ACTION 1): Contact The Boeing Company for repair instructions and do the repair. CONDITION 5: ANY CRACK FOUND DURING PART 2 INSPEC- TION 1,300 flight cy-cles.-(ACTION 2): Repeat PART 2: FOR-WARD SIDE BODY STATION (STA) 1681 FUSELAGE FRAME HIGH FREQUENCY EDDY CURRENT (HFEC) AND LOW FREQUENCY EDDY CURRENT (LFEC) INSPEC- TIONS for any crack in areas with no existing frame repair. (b) 1,300 flight cy- cles. -Repeat PART 2: FORWARD SIDE BODY STATION (STA) 1681 FUSELAGE FRAME HIGH FRE- QUENCY EDDY CURRENT (HFEC) AND LOW FREQUENCY EDDY CURRENT (LFEC) INSPECTIONS for any crack in areas with no exist- ing frame repair. (b) CONDITION 6: NO CRACK FOUND DURING PART 2 INSPEC- TION -Before further flight.(ACTION 1): Contact The Boeing Company for repair instructions and do the repair. CONDITION 7: ANY CRACK FOUND DURING PART 3 INSPEC- TION 5,800 flight cy-cles.-(ACTION 2): Repeat PART 3: AFTSIDE BODY STATION (STA) 1681 FUSELAGE FRAME HIGH FRE- QUENCY EDDY CURRENT (HFEC) INSPECTIONS for any crack in ar- eas with no existing frame repair. (b) 5,800 flight cy- cles. -Repeat PART 3: AFT SIDE BODY STATION (STA) 1681 FUSELAGE FRAME HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTIONS for any crack in areas with no exist- ing frame repair. (b) CONDITION 8: NO CRACK FOUND DURING PART 3 INSPEC- TION Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 14, 2016 757-53A0100 23 of 120 BOEING SERVICE BULLETIN 757-53A0100 ALERTALERT ### Page 24 Group 1, Configuration 3: Table 3: Body Station (STA) 1681 fuselage frame High Frequency Eddy Current (HFEC) and Low Frequency Eddy Current (LFEC) inspection for any crack Repeat Interval (Not to Exceed) Compliance TimeActionCondition -Before further flight.(ACTION 1): Contact The Boeing Company for repair instructions and do the repair. CONDITION 9: ANY CRACK FOUND DURING PART 4 INSPEC- TION 4,100 flight cy-cles.-(ACTION 2): Repeat PART 4: BE-LOW THE FLOOR BODY STATION (STA) 1681 FUSELAGE FRAME HIGH FREQUENCY EDDY CUR- RENT (HFEC) AND LOW FRE- QUENCY EDDY CURRENT (LFEC) INSPECTIONS for any crack in ar- eas with no existing frame repair and no existing floor beam repair. 4,100 flight cy- cles. -Repeat PART 4: BELOW THE FLOOR BODY STATION (STA) 1681 FUSELAGE FRAME HIGH FREQUENCY EDDY CURRENT (HFEC) AND LOW FREQUENCY EDDY CURRENT (LFEC) INSPEC- TIONS for any crack in areas with no existing frame repair and no ex- isting floor beam repair. CONDITION 10: NO CRACK FOUND DURING PART 4 INSPEC- TION -Before further flight.(ACTION 1): Contact The Boeing Company for repair instructions and do the repair. CONDITION 11: ANY CRACK FOUND DURING PART 5 INSPEC- TION 3,000 flight cy-cles.-(ACTION 2): Repeat PART 5: BE-LOW THE FLOOR BODY STATION (STA) 1681 FUSELAGE FRAME HIGH FREQUENCY EDDY CUR- RENT (HFEC) AND LOW FRE- QUENCY EDDY CURRENT (LFEC) INSPECTIONS for any crack in ar- eas with no existing frame repair. 3,000 flight cy- cles. -Repeat PART 5: BELOW THE FLOOR BODY STATION (STA) 1681 FUSELAGE FRAME HIGH FREQUENCY EDDY CURRENT (HFEC) AND LOW FREQUENCY EDDY CURRENT (LFEC) INSPEC- TIONS for any crack in areas with no existing frame repair. CONDITION 12: NO CRACK FOUND DURING PART 5 INSPEC- TION (a) More than one CONDITION can be applicable in areas with no existing frame repair. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 14, 2016 757-53A0100 24 of 120 BOEING SERVICE BULLETIN 757-53A0100 ALERTALERT ### Page 25 Group 1, Configuration 3: Table 3: Body Station (STA) 1681 fuselage frame High Frequency Eddy Current (HFEC) and Low Frequency Eddy Current (LFEC) inspection for any crack Repeat Interval (Not to Exceed) Compliance TimeActionCondition (b) It is acceptable to change the repeat inspection method from PART 2 to PART 3 or from PART 3 to PART 2 provided the repeat interval for the previously accomplished inspection method is complied with. Group 2, Configuration 1: Table 4: Body Station (STA) 1681 fuselage frame High Frequency Eddy Current (HFEC) and Low Frequency Eddy Current (LFEC) inspection for any crack Repeat Interval (Not to Exceed) Compliance Time (Whichever Occurs Later) ActionCondition -Within 3,000 flight cycles after the original issue date of this ser- vice bulletin, or before 31,500 to- tal flight cycles, whichever oc- curs first. Before 25,000 total flight cycles. Inspect for any existing frame repair and for any existing floor beam re- pair common to the STA 1681 frame inspection area. 757-200, -200CB and -300 airplanes with less than 31,000 total flight cycles at the origi- nal issue date of this service bul- letin. -Before further flight.Contact The Boeing Company for repair evaluation and inspection in- structions and do the instructions. CONDITION 1: ANY EXISTING FRAME REPAIR COMMON TO THE STA 1681 FUSELAGE FRAME INSPEC- TION AREA Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 14, 2016 757-53A0100 25 of 120 BOEING SERVICE BULLETIN 757-53A0100 ALERTALERT ### Page 26 Group 2, Configuration 1: Table 4: Body Station (STA) 1681 fuselage frame High Frequency Eddy Current (HFEC) and Low Frequency Eddy Current (LFEC) inspection for any crack Repeat Interval (Not to Exceed) Compliance Time (Whichever Occurs Later) ActionCondition -Within 3,000 flight cycles after the original issue date of this ser- vice bulletin, or before 31,500 to- tal flight cycles, whichever oc- curs first. Before 25,000 total flight cycles. OPTION 1: Do PART 2: FORWARD SIDE BODY STATION (STA) 1681 FUSELAGE FRAME HIGH FRE- QUENCY EDDY CURRENT (HFEC) AND LOW FREQUENCY EDDY CURRENT (LFEC) INSPECTIONS for any crack in areas with no exist- ing frame repair. CONDITION 2: NO EXISTING FRAME REPAIR COMMON TO THE STA 1681 FUSELAGE FRAME INSPEC- TION AREA (a) -Within 3,000 flight cycles after the original issue date of this ser- vice bulletin, or before 31,500 to- tal flight cycles, whichever oc- curs first. Before 25,000 total flight cycles. OPTION 2: Do PART 3: AFT SIDE BODY STATION (STA) 1681 FUSELAGE FRAME HIGH FRE- QUENCY EDDY CURRENT (HFEC) INSPECTIONS for any crack in ar- eas with no existing frame repair. -Within 3,000 flight cycles after the original issue date of this ser- vice bulletin, or before 31,500 to- tal flight cycles, whichever oc- curs first. Before 25,000 total flight cycles. Do PART 4: BELOW THE FLOOR BODY STATION (STA) 1681 FUSELAGE FRAME HIGH FRE- QUENCY EDDY CURRENT (HFEC) AND LOW FREQUENCY EDDY CURRENT (LFEC) INSPECTIONS for any crack in areas with no exist- ing frame repair and no existing floor beam repair. CONDITION 3: NO EXISTING FLOOR BEAM REPAIR COM- MON TO THE STA 1681 FUSE- LAGE FRAME IN- SPECTION AREA (a) -Within 3,000 flight cycles after the original issue date of this ser- vice bulletin, or before 31,500 to- tal flight cycles, whichever oc- curs first. Before 25,000 total flight cycles. Do PART 5: BELOW THE FLOOR BODY STATION (STA) 1681 FUSELAGE FRAME HIGH FRE- QUENCY EDDY CURRENT (HFEC) AND LOW FREQUENCY EDDY CURRENT (LFEC) INSPECTIONS for any crack in areas with no exist- ing frame repair. CONDITION 4: ANY EXISTING FLOOR BEAM REPAIR COM- MON TO THE STA 1681 FUSE- LAGE FRAME IN- SPECTION AREA (a) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 14, 2016 757-53A0100 26 of 120 BOEING SERVICE BULLETIN 757-53A0100 ALERTALERT ### Page 27 Group 2, Configuration 1: Table 4: Body Station (STA) 1681 fuselage frame High Frequency Eddy Current (HFEC) and Low Frequency Eddy Current (LFEC) inspection for any crack Repeat Interval (Not to Exceed) Compliance Time (Whichever Occurs Later) ActionCondition -Before further flight.(ACTION 1): Contact The Boeing Company for repair instructions and do the repair. CONDITION 5: ANY CRACK FOUND DURING PART 2 INSPEC- TION 2,200 flight cy-cles.-(ACTION 2): Repeat PART 2: FOR-WARD SIDE BODY STATION (STA) 1681 FUSELAGE FRAME HIGH FREQUENCY EDDY CURRENT (HFEC) AND LOW FREQUENCY EDDY CURRENT (LFEC) INSPEC- TIONS for any crack in areas with no existing frame repair. (b) 2,200 flight cy- cles. -Repeat PART 2: FORWARD SIDE BODY STATION (STA) 1681 FUSELAGE FRAME HIGH FRE- QUENCY EDDY CURRENT (HFEC) AND LOW FREQUENCY EDDY CURRENT (LFEC) INSPECTIONS for any crack in areas with no exist- ing frame repair. (b) CONDITION 6: NO CRACK FOUND DURING PART 2 INSPEC- TION -Before further flight.(ACTION 1): Contact The Boeing Company for repair instructions and do the repair. CONDITION 7: ANY CRACK FOUND DURING PART 3 INSPEC- TION 6,700 flight cy-cles.-(ACTION 2): Repeat PART 3: AFTSIDE BODY STATION (STA) 1681 FUSELAGE FRAME HIGH FRE- QUENCY EDDY CURRENT (HFEC) INSPECTIONS for any crack in ar- eas with no existing frame repair. (b) 6,700 flight cy- cles. -Repeat PART 3: AFT SIDE BODY STATION (STA) 1681 FUSELAGE FRAME HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTIONS for any crack in areas with no exist- ing frame repair. (b) CONDITION 8: NO CRACK FOUND DURING PART 3 INSPEC- TION Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 14, 2016 757-53A0100 27 of 120 BOEING SERVICE BULLETIN 757-53A0100 ALERTALERT ### Page 28 Group 2, Configuration 1: Table 4: Body Station (STA) 1681 fuselage frame High Frequency Eddy Current (HFEC) and Low Frequency Eddy Current (LFEC) inspection for any crack Repeat Interval (Not to Exceed) Compliance Time (Whichever Occurs Later) ActionCondition -Before further flight.(ACTION 1): Contact The Boeing Company for repair instructions and do the repair. CONDITION 9: ANY CRACK FOUND DURING PART 4 INSPEC- TION 5,000 flight cy-cles.-(ACTION 2): Repeat PART 4: BE-LOW THE FLOOR BODY STATION (STA) 1681 FUSELAGE FRAME HIGH FREQUENCY EDDY CUR- RENT (HFEC) AND LOW FRE- QUENCY EDDY CURRENT (LFEC) INSPECTIONS for any crack in ar- eas with no existing frame repair and no existing floor beam repair. 5,000 flight cy- cles. -Repeat PART 4: BELOW THE FLOOR BODY STATION (STA) 1681 FUSELAGE FRAME HIGH FREQUENCY EDDY CURRENT (HFEC) AND LOW FREQUENCY EDDY CURRENT (LFEC) INSPEC- TIONS for any crack in areas with no existing frame repair and no ex- isting floor beam repair. CONDITION 10: NO CRACK FOUND DURING PART 4 INSPEC- TION -Before further flight.(ACTION 1): Contact The Boeing Company for repair instructions and do the repair. CONDITION 11: ANY CRACK FOUND DURING PART 5 INSPEC- TION 3,700 flight cy-cles.-(ACTION 2): Repeat PART 5: BE-LOW THE FLOOR BODY STATION (STA) 1681 FUSELAGE FRAME HIGH FREQUENCY EDDY CUR- RENT (HFEC) AND LOW FRE- QUENCY EDDY CURRENT (LFEC) INSPECTIONS for any crack in ar- eas with no existing frame repair. 3,700 flight cy- cles. -Repeat PART 5: BELOW THE FLOOR BODY STATION (STA) 1681 FUSELAGE FRAME HIGH FREQUENCY EDDY CURRENT (HFEC) AND LOW FREQUENCY EDDY CURRENT (LFEC) INSPEC- TIONS for any crack in areas with no existing frame repair. CONDITION 12: NO CRACK FOUND DURING PART 5 INSPEC- TION (a) More than one CONDITION can be applicable in areas with no existing frame repair. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 14, 2016 757-53A0100 28 of 120 BOEING SERVICE BULLETIN 757-53A0100 ALERTALERT ### Page 29 Group 2, Configuration 1: Table 4: Body Station (STA) 1681 fuselage frame High Frequency Eddy Current (HFEC) and Low Frequency Eddy Current (LFEC) inspection for any crack Repeat Interval (Not to Exceed) Compliance Time (Whichever Occurs Later) ActionCondition (b) It is acceptable to change the repeat inspection method from PART 2 to PART 3 or from PART 3 to PART 2 provided the repeat interval for the previously accomplished inspection method is complied with. Group 2, Configuration 2: Table 5: Body Station (STA) 1681 fuselage frame High Frequency Eddy Current (HFEC) and Low Frequency Eddy Current (LFEC) inspection for any crack Repeat Interval (Not to Exceed) Compliance TimeActionCondition -Within 500 flight cycles after the original issue date of this service bulletin. Inspect for any existing frame repair and for any existing floor beam re- pair common to the STA 1681 frame inspection area. 757-200, -200CB and -300 airplanes with 31,000 total flight cycles or more at the origi- nal issue date of this service bul- letin. -Before further flight.Contact The Boeing Company for repair evaluation and inspection in- structions and do the instructions. CONDITION 1: ANY EXISTING FRAME REPAIR COMMON TO THE STA 1681 FUSELAGE FRAME INSPEC- TION AREA -Within 500 flight cycles after the original issue date of this service bulletin. OPTION 1: Do PART 2: FORWARD SIDE BODY STATION (STA) 1681 FUSELAGE FRAME HIGH FRE- QUENCY EDDY CURRENT (HFEC) AND LOW FREQUENCY EDDY CURRENT (LFEC) INSPECTIONS for any crack in areas with no exist- ing frame repair. CONDITION 2: NO EXISTING FRAME REPAIR COMMON TO THE STA 1681 FUSELAGE FRAME INSPEC- TION AREA (a) -Within 500 flight cycles after the original issue date of this service bulletin. OPTION 2: Do PART 3: AFT SIDE BODY STATION (STA) 1681 FUSELAGE FRAME HIGH FRE- QUENCY EDDY CURRENT (HFEC) INSPECTIONS for any crack in ar- eas with no existing frame repair. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 14, 2016 757-53A0100 29 of 120 BOEING SERVICE BULLETIN 757-53A0100 ALERTALERT ### Page 30 Group 2, Configuration 2: Table 5: Body Station (STA) 1681 fuselage frame High Frequency Eddy Current (HFEC) and Low Frequency Eddy Current (LFEC) inspection for any crack Repeat Interval (Not to Exceed) Compliance TimeActionCondition -Within 500 flight cycles after the original issue date of this service bulletin. Do PART 4: BELOW THE FLOOR BODY STATION (STA) 1681 FUSELAGE FRAME HIGH FRE- QUENCY EDDY CURRENT (HFEC) AND LOW FREQUENCY EDDY CURRENT (LFEC) INSPECTIONS for any crack in areas with no exist- ing frame repair and no existing floor beam repair. CONDITION 3: NO EXISTING FLOOR BEAM REPAIR COM- MON TO THE STA 1681 FUSE- LAGE FRAME IN- SPECTION AREA (a) -Within 500 flight cycles after the original issue date of this service bulletin. Do PART 5: BELOW THE FLOOR BODY STATION (STA) 1681 FUSELAGE FRAME HIGH FRE- QUENCY EDDY CURRENT (HFEC) AND LOW FREQUENCY EDDY CURRENT (LFEC) INSPECTIONS for any crack in areas with no exist- ing frame repair. CONDITION 4: ANY EXISTING FLOOR BEAM REPAIR COM- MON TO THE STA 1681 FUSE- LAGE FRAME IN- SPECTION AREA (a) -Before further flight.(ACTION 1): Contact The Boeing Company for repair instructions and do the repair. CONDITION 5: ANY CRACK FOUND DURING PART 2 INSPEC- TION 2,200 flight cy-cles.-(ACTION 2): Repeat PART 2: FOR-WARD SIDE BODY STATION (STA) 1681 FUSELAGE FRAME HIGH FREQUENCY EDDY CURRENT (HFEC) AND LOW FREQUENCY EDDY CURRENT (LFEC) INSPEC- TIONS for any crack in areas with no existing frame repair. (b) 2,200 flight cy- cles. -Repeat PART 2: FORWARD SIDE BODY STATION (STA) 1681 FUSELAGE FRAME HIGH FRE- QUENCY EDDY CURRENT (HFEC) AND LOW FREQUENCY EDDY CURRENT (LFEC) INSPECTIONS for any crack in areas with no exist- ing frame repair. (b) CONDITION 6: NO CRACK FOUND DURING PART 2 INSPEC- TION Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 14, 2016 757-53A0100 30 of 120 BOEING SERVICE BULLETIN 757-53A0100 ALERTALERT ### Page 31 Group 2, Configuration 2: Table 5: Body Station (STA) 1681 fuselage frame High Frequency Eddy Current (HFEC) and Low Frequency Eddy Current (LFEC) inspection for any crack Repeat Interval (Not to Exceed) Compliance TimeActionCondition -Before further flight.(ACTION 1): Contact The Boeing Company for repair instructions and do the repair. CONDITION 7: ANY CRACK FOUND DURING PART 3 INSPEC- TION 6,700 flight cy-cles.-(ACTION 2): Repeat PART 3: AFTSIDE BODY STATION (STA) 1681 FUSELAGE FRAME HIGH FRE- QUENCY EDDY CURRENT (HFEC) INSPECTIONS for any crack in ar- eas with no existing frame repair. (b) 6,700 flight cy- cles. -Repeat PART 3: AFT SIDE BODY STATION (STA) 1681 FUSELAGE FRAME HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTIONS for any crack in areas with no exist- ing frame repair. (b) CONDITION 8: NO CRACK FOUND DURING PART 3 INSPEC- TION -Before further flight.(ACTION 1): Contact The Boeing Company for repair instructions and do the repair. CONDITION 9: ANY CRACK FOUND DURING PART 4 INSPEC- TION 5,000 flight cy-cles.-(ACTION 2): Repeat PART 4: BE-LOW THE FLOOR BODY STATION (STA) 1681 FUSELAGE FRAME HIGH FREQUENCY EDDY CUR- RENT (HFEC) AND LOW FRE- QUENCY EDDY CURRENT (LFEC) INSPECTIONS for any crack in ar- eas with no existing frame repair and no existing floor beam repair. 5,000 flight cy- cles. -Repeat PART 4: BELOW THE FLOOR BODY STATION (STA) 1681 FUSELAGE FRAME HIGH FREQUENCY EDDY CURRENT (HFEC) AND LOW FREQUENCY EDDY CURRENT (LFEC) INSPEC- TIONS for any crack in areas with no existing frame repair and no ex- isting floor beam repair. CONDITION 10: NO CRACK FOUND DURING PART 4 INSPEC- TION Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 14, 2016 757-53A0100 31 of 120 BOEING SERVICE BULLETIN 757-53A0100 ALERTALERT ### Page 32 Group 2, Configuration 2: Table 5: Body Station (STA) 1681 fuselage frame High Frequency Eddy Current (HFEC) and Low Frequency Eddy Current (LFEC) inspection for any crack Repeat Interval (Not to Exceed) Compliance TimeActionCondition -Before further flight.(ACTION 1): Contact The Boeing Company for repair instructions and do the repair. CONDITION 11: ANY CRACK FOUND DURING PART 5 INSPEC- TION 3,700 flight cy-cles.-(ACTION 2): Repeat PART 5: BE-LOW THE FLOOR BODY STATION (STA) 1681 FUSELAGE FRAME HIGH FREQUENCY EDDY CUR- RENT (HFEC) AND LOW FRE- QUENCY EDDY CURRENT (LFEC) INSPECTIONS for any crack in ar- eas with no existing frame repair. 3,700 flight cy- cles. -Repeat PART 5: BELOW THE FLOOR BODY STATION (STA) 1681 FUSELAGE FRAME HIGH FREQUENCY EDDY CURRENT (HFEC) AND LOW FREQUENCY EDDY CURRENT (LFEC) INSPEC- TIONS for any crack in areas with no existing frame repair. CONDITION 12: NO CRACK FOUND DURING PART 5 INSPEC- TION (a) More than one CONDITION can be applicable in areas with no existing frame repair. (b) It is acceptable to change the repeat inspection method from PART 2 to PART 3 or from PART 3 to PART 2 provided the repeat interval for the previously accomplished inspection method is complied with. F. Approval This service bulletin was examined by the Federal Aviation Administration (FAA). The changes specified in this service bulletin comply with the applicable regulations and are FAA approved, as well as European Aviation Safety Agency (EASA)/Joint Aviation Authorities (JAA) approved for all EASA/JAA approved airplanes listed in the service bulletin effectivity. This service bulletin and its approval were based on the airplane in its original Boeing delivery configuration or as modified by other approved Boeing changes. If an airplane has a non-Boeing modification or repair that affects a component or system also affected by this service bulletin, the operator is responsible for obtaining appropriate regulatory agency approval before incorporating this service bulletin. G. Manpower The tables below show an estimate of the task hours necessary to do this inspection for each airplane. This estimate is for direct labor only, done by an experienced crew. Adjust the estimate with operator task hour data if necessary. The estimate does not include lost time. These are some examples of lost time: Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 14, 2016 757-53A0100 32 of 120 BOEING SERVICE BULLETIN 757-53A0100 ALERTALERT ### Page 33 • Time to adjust to the workplace • Time to schedule the work • Time to inspect the work • Time to cure the materials • Time to make the parts • Time to find the tools Group 1, Configuration 1: Body Station (STA) 1681 fuselage frame High Frequency Eddy Current (HFEC) and Low Frequency Eddy Current (LFEC) inspection for airplanes with no existing floor beam repair in the STA 1681 frame inspection area Elapsed HoursTask HoursNumber of PersonsTask 3.507.002Open Access (a)(a)(a)Aft Galley and Aft Lavatory Removal 3.303.301FIGURE 3 3.303.301FIGURE 4 5.605.601FIGURE 7 5.605.601FIGURE 8 (a)(a)(a)Aft Galley and Aft Lavatory Installation 3.507.002Close Access 24.8031.80TOTAL FOR EACH AIRPLANE (a) If a step or sub-step is labeled "RC Exempt" then the RC requirement is re- moved from that step or sub-step. Group 1, Configuration 1: Body Station (STA) 1681 fuselage frame High Frequency Eddy Current (HFEC) and Low Frequency Eddy Current (LFEC) inspection for airplanes with any existing floor beam repair in the STA 1681 frame inspection area Elapsed HoursTask HoursNumber of PersonsTask 3.507.002Open Access (a)(a)(a)Aft Galley and Aft Lavatory Removal 3.303.301FIGURE 3 3.303.301FIGURE 4 5.605.601FIGURE 11 5.605.601FIGURE 12 (a)(a)(a)Aft Galley and Aft Lavatory Installation Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 14, 2016 757-53A0100 33 of 120 BOEING SERVICE BULLETIN 757-53A0100 ALERTALERT ### Page 34 Group 1, Configuration 1: Body Station (STA) 1681 fuselage frame High Frequency Eddy Current (HFEC) and Low Frequency Eddy Current (LFEC) inspection for airplanes with any existing floor beam repair in the STA 1681 frame inspection area Elapsed HoursTask HoursNumber of PersonsTask 3.507.002Close Access 24.8031.80TOTAL FOR EACH AIRPLANE (a) If a step or sub-step is labeled "RC Exempt" then the RC requirement is re- moved from that step or sub-step. Group 1, Configuration 2-3; Group 2: Body Station (STA) 1681 fuselage frame High Frequency Eddy Current (HFEC) and Low Frequency Eddy Current (LFEC) inspection for airplanes with no existing floor beam repair in the STA 1681 frame inspection area - OPTION 1 Elapsed HoursTask HoursNumber of PersonsTask 3.507.002Open Access 3.703.701FIGURE 1 3.703.701FIGURE 2 3.403.401FIGURE 9 3.403.401FIGURE 10 3.507.002Close Access 21.2028.20TOTAL FOR EACH AIRPLANE Group 1, Configuration 2-3; Group 2: Body Station (STA) 1681 fuselage frame High Frequency Eddy Current (HFEC) and Low Frequency Eddy Current (LFEC) inspection for airplanes with no existing floor beam repair in the STA 1681 frame inspection area - OPTION 2 Elapsed HoursTask HoursNumber of PersonsTask 3.507.002Open Access (a)(a)(a)Aft Galley and Aft Lavatory Removal 2.502.501FIGURE 5 2.502.501FIGURE 6 3.403.401FIGURE 9 3.403.401FIGURE 10 (a)(a)(a)Aft Galley and Aft Lavatory Installation 3.507.002Close Access Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 14, 2016 757-53A0100 34 of 120 BOEING SERVICE BULLETIN 757-53A0100 ALERTALERT ### Page 35 Group 1, Configuration 2-3; Group 2: Body Station (STA) 1681 fuselage frame High Frequency Eddy Current (HFEC) and Low Frequency Eddy Current (LFEC) inspection for airplanes with no existing floor beam repair in the STA 1681 frame inspection area - OPTION 2 Elapsed HoursTask HoursNumber of PersonsTask 18.8025.80TOTAL FOR EACH AIRPLANE (a) If a step or sub-step is labeled "RC Exempt" then the RC requirement is re- moved from that step or sub-step. Group 1, Configuration 2-3; Group 2: Body Station (STA) 1681 fuselage frame High Frequency Eddy Current (HFEC) and Low Frequency Eddy Current (LFEC) inspection for airplanes with any existing floor beam repair in the STA 1681 frame inspection area - OPTION 1 Elapsed HoursTask HoursNumber of PersonsTask 3.507.002Open Access 3.703.701FIGURE 1 3.703.701FIGURE 2 3.403.401FIGURE 13 3.403.401FIGURE 14 3.507.002Close Access 21.2028.20TOTAL FOR EACH AIRPLANE Group 1, Configuration 2-3; Group 2: Body Station (STA) 1681 fuselage frame High Frequency Eddy Current (HFEC) and Low Frequency Eddy Current (LFEC) inspection for airplanes with any existing floor beam repair in the STA 1681 frame inspection area - OPTION 2 Elapsed HoursTask HoursNumber of PersonsTask 3.507.002Open Access (a)(a)(a)Aft Galley and Aft Lavatory Removal 2.502.501FIGURE 5 2.502.501FIGURE 6 3.403.401FIGURE 13 3.403.401FIGURE 14 (a)(a)(a)Aft Galley and Aft Lavatory Installation 3.507.002Close Access 18.8025.80TOTAL FOR EACH AIRPLANE Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 14, 2016 757-53A0100 35 of 120 BOEING SERVICE BULLETIN 757-53A0100 ALERTALERT ### Page 36 Group 1, Configuration 2-3; Group 2: Body Station (STA) 1681 fuselage frame High Frequency Eddy Current (HFEC) and Low Frequency Eddy Current (LFEC) inspection for airplanes with any existing floor beam repair in the STA 1681 frame inspection area - OPTION 2 Elapsed HoursTask HoursNumber of PersonsTask (a) If a step or sub-step is labeled "RC Exempt" then the RC requirement is re- moved from that step or sub-step. H. Weight and Balance Changes None. I. Electrical Load Data Not changed. J. References 1. Existing Data: a. Boeing Service Bulletin 757-53-0024 b. Boeing Service Letter 757-SL-51-022 c. Boeing Service Related Problem (SRP) 757-SRP-53-0489 d. Service Bulletin Index D624N001 e. Standard Overhaul Practices Manual (SOPM) 20-50-12 f. 757 Aircraft Maintenance Manual (AMM) 25-21-02, 25-21-05, 25-21-06, 25-31-04, 25-41-04, 25-50-07, 25-55-00, 25-55-07, 53-01-01, 53-13-01 g. 757 Fleet Team Digest (FTD) 53-14002 h. 757 Non-Destructive Testing (NDT) Manual Part 6, 51-00-01, Part 6, 51-00-11, Part 6, 51-00-16, Part 6, 51-00-19, Part 6, 51-00-23 2. Data Supplied with this Service Bulletin: None. 3. Installation Drawings Used in the Preparation of this Service Bulletin: TitleDrawing Number AFT FRAME INSTL, STA1681.80 - NO.4 PASSENGER DOOR146N8712 LWR MAIN SILL INSTL NO.4 PASSENGER DOOR146N8722 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 14, 2016 757-53A0100 36 of 120 BOEING SERVICE BULLETIN 757-53A0100 ALERTALERT ### Page 37 The table above lists applicable drawings used to prepare this service bulletin. The drawings are not necessary to make the specified changes, and are not supplied with this service bulletin. The drawings may not be applicable to all airplane configurations or operators. K. Publications Affected 1. Publications: None. 2. Damage Tolerance Based Structural Inspections: Boeing has evaluated the repairs and/or changes in this service bulletin for effects on Fatigue Critical Structure (FCS) and for changes to Damage Tolerance Inspections (DTI) required in the Maintenance Program. This service bulletin affects FCS but no new DTIs are necessary. L. Interchangeability and Intermixability of Parts Accomplishment of this service bulletin does not affect interchangeability or intermixability of parts. M. Software Accomplishment Summary Not affected. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 14, 2016 757-53A0100 37 of 120 BOEING SERVICE BULLETIN 757-53A0100 ALERTALERT ### Page 38 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 14, 2016 757-53A0100 38 of 120 BOEING SERVICE BULLETIN 757-53A0100 ALERTALERT BLANK PAGE ### Page 39 2. MATERIAL INFORMATION A. Material - Price and Availability The operator can supply the parts and materials shown in Paragraph 2.C., Parts Necessary for Each Airplane. As an alternative, operators can purchase the parts from Boeing Spares. This service bulletin does not show the Boeing price and supply data. B. Industry Support Information Boeing warranty remedies are not available for the inspections given in this service bulletin. C. Parts Necessary for Each Airplane 1. Kits/Parts None. 2. Parts and Materials Supplied by the Operator The following parts or materials are necessary to do the change in this service bulletin. Parts and materials in the manuals given in Paragraph 1.J., References, can also be necessary. Examine operator part and material supply to make sure all necessary parts and materials are available. NotesNameQTYPart Number / Specification (a) (b) (c)Liner Retainer Stud12045081-1 (OP1913-1 optional) (d) (g)Sealant1 OzBMS5-95, Class B (e) (g)Sealant1 OzBMS 5-44, Class B (BMS 5-45, Class B optional) (f)Adhesive1 OzPR 2701, Class A (a) This part is only necessary to replace a damaged part. Quantity given is for one location. (b) 2045081-1 can be purchased from: Southco, Inc., 210 North Brinton Lake Road, Con- cordville, Pennsylvania 19331, USA. CAGE code: 94222. (c) OP1913-1 can be purchased from: NMC Group, Inc. 2755 Thompson Creek Road, Pomona, California 91767-1861, USA. CAGE code: 03296. (d) This material is only necessary if a liner retainer stud is replaced and the bonding procedure used is SOPM 20-50-12, Type 93. Quantity given is for one location. (e) This material is only necessary if a liner retainer stud is replaced and the bonding procedure used is SOPM 20-50-12, Type 44. Quantity given is for one location. (f) This material is only necessary if a liner retainer stud is replaced and the bonding procedure used is SOPM 20-50-12, Type 121. Quantity given is for one location. This material can be purchased from: PRC - Desoto International, Inc., PPG Aerospace ASC - Los Angeles, 24811 Avenue Rockefeller, Valencia, California 91355-3468, USA. CAGE code: 83574. (g) Refer to the Qualified Products List at the end of the Boeing Material Specification (BMS) for supplier data. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 14, 2016 757-53A0100 39 of 120 BOEING SERVICE BULLETIN 757-53A0100 ALERTALERT ### Page 40 3. Parts Modified and Reidentified None. 4. Parts Removed and Not Replaced None. D. Parts Necessary to Change Spares None. E. Special Tooling - Price and Availability None. F. Special Tooling Necessary to do this Service Bulletin No special tools or equipment are necessary to do the change in this service bulletin. But, maintenance and overhaul tools in the manuals given in Paragraph 1.J., References, can be necessary. Examine operator tool supply to make sure all necessary tools are available. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 14, 2016 757-53A0100 40 of 120 BOEING SERVICE BULLETIN 757-53A0100 ALERTALERT ### Page 41 3. ACCOMPLISHMENT INSTRUCTIONS A. GENERAL INFORMATION CAUTION: KEEP THE WORK AREA, WIRES AND ELECTRICAL BUNDLES CLEAN OF METAL PARTICLES OR CONTAMINATION WHEN YOU USE TOOLS. UNWANTED MATERIAL, METAL PARTICLES OR CONTAMINATION CAUGHT IN WIRE BUNDLES CAN CAUSE DAMAGE TO THE BUNDLES. DAMAGED WIRE BUNDLES CAN CAUSE SPARKS OR OTHER ELECTRICAL DAMAGE. NOTE: 1. Manual titles are referred to by acronyms. Refer to Paragraph 1.J., References, for definition of the acronyms. 2. Obey all of the warnings and cautions given in the specified manual sections. 3. Unless shown differently, these dimensions and tolerances are used: – Linear dimensions are in inches – Tolerance on linear dimensions, other than rivet and bolt edge margins, is plus or minus 0.03 inch – Tolerance on rivet and bolt edge margin is plus or minus 0.05 inch – Angular tolerance is plus or minus 2 degrees – Hole dimensions for standard solid rivets and fasteners are in Structural Repair Manual (SRM) Chapter 51 – Torque Values: — Values for structural fasteners are given in 757 Structural Repair Manual, Chapter 51. — Values for airframe maintenance tasks are included in Chapter 20 of 757 Aircraft Maintenance Manual (AMM). — Values for electrical maintenance tasks are included in Chapter 20 of Standard Wiring Practices Manual (SWPM). — Values for engine maintenance tasks are included in Chapter 70 of 757 Aircraft Maintenance Manual (AMM). — Non-standard torque values for maintenance tasks are included in the applicable installation step. 4. These work instructions refer to procedures included in other Boeing documents. When the words "refer to" are used and the operator has an accepted alternative procedure, the accepted alternative procedure can be used. When the words "in accordance with" are included in the instruction, the procedure in the Boeing document must be used. 5. Boeing Service Letter 757-SL-51-022, Damage Reporting and Repair Plan/Design Guidelines, is an acceptable procedure to request information from Boeing for additional structural repair instructions. The Service Letter describes what information must be provided to Boeing before a structural repair can be provided. 6. Refer to Appendix A, B, C, D and E for logic diagrams. Logic diagrams are provided as an aid only. Information contained in Paragraph 1.E., Compliance is the primary source for compliance times. Information in Paragraph 3.B., Work Instructions is the primary source for tasks required for compliance. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 14, 2016 757-53A0100 41 of 120 BOEING SERVICE BULLETIN 757-53A0100 ALERTALERT ### Page 42 7. If it is necessary to remove more parts for access, you can remove those parts. If you can get access without removing identified parts, it is not necessary to remove all of the identified parts. Jacking and shoring limitations must be observed. 8. Where the work instructions include installation of a kept part, a new or serviceable part with the same part number can be installed as an alternative to the kept part. 9. Use of colors in Figures is based on guidance from the ATA e-Business Program (ATA) iSpec 2200. 10. 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 number or an OPTION number, do all of the ACTION numbers for that CONDITION number or OPTION number. 11. The compliance times for the actions in Paragraph 3.B., WORK INSTRUCTIONS are in Paragraph 1.E., Compliance. 12. Some steps in the Work Instructions are labeled as Required for Compliance (RC). If this service bulletin is mandated by an Airworthiness Directive (AD), then the steps labeled as RC, including sub-steps under an RC step and any figures identified in an RC step, must be done to comply with the AD. If a step or sub-step is labeled "RC Exempt," then the RC requirement is removed from that step or sub-step. An Alternative Method of Compliance (AMOC) is required for any deviations to RC steps, including sub-steps and identified figures. Steps not labeled as RC may be deviated from using accepted methods in accordance with the operator's maintenance or inspection program without obtaining approval of an AMOC. This is provided that the RC steps, including sub-steps and identified figures, can still be done as specified, and the airplane can be put back in an airworthy condition. B. WORK INSTRUCTIONS 1. Do PART 1: ACCESS. 2. RC - Inspect for any existing frame repair and for any existing floor beam repair common to the STA 1681 frame inspection area. a. CONDITION 1: ANY EXISTING FRAME REPAIR COMMON TO THE STA 1681 FUSELAGE FRAME INSPECTION AREA (1) Contact The Boeing Company for repair evaluation and inspection instructions and do the instructions. b. CONDITION 2: NO EXISTING FRAME REPAIR COMMON TO THE STA 1681 FUSELAGE FRAME INSPECTION AREA NOTE: More than one CONDITION can be applicable in areas with no existing frame repair. (1) Group 1, Configuration 1: Do PART 3: AFT SIDE BODY STATION (STA) 1681 FUSELAGE FRAME HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTIONS for any crack in areas with no existing frame repair. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 14, 2016 757-53A0100 42 of 120 BOEING SERVICE BULLETIN 757-53A0100 ALERTALERT ### Page 43 (a) CONDITION 7: ANY CRACK FOUND DURING PART 3 INSPECTION 1) (ACTION 1): Contact The Boeing Company for repair instructions and do the repair. 2) (ACTION 2): Repeat PART 3: AFT SIDE BODY STATION (STA) 1681 FUSELAGE FRAME HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTIONS for any crack in areas with no existing frame repair, at the times specified in Paragraph 1.E., Compliance. (b) CONDITION 8: NO CRACK FOUND DURING PART 3 INSPECTION 1) Repeat PART 3: AFT SIDE BODY STATION (STA) 1681 FUSELAGE FRAME HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTIONS for any crack in areas with no existing frame repair, at the times specified in Paragraph 1.E., Compliance. (2) Group 1, Configuration 2-3; Group 2: Do one of the options that follow: (a) OPTION 1: PART 2: FORWARD SIDE BODY STATION (STA) 1681 FUSELAGE FRAME HIGH FREQUENCY EDDY CURRENT (HFEC) AND LOW FREQUENCY EDDY CURRENT (LFEC) INSPECTIONS for any crack in areas with no existing frame repair. 1) CONDITION 5: ANY CRACK FOUND DURING PART 2 INSPECTION a) (ACTION 1): Contact The Boeing Company for repair instructions and do the repair. b) (ACTION 2): Repeat PART 2: FORWARD SIDE BODY STATION (STA) 1681 FUSELAGE FRAME HIGH FREQUENCY EDDY CURRENT (HFEC) AND LOW FREQUENCY EDDY CURRENT (LFEC) INSPECTIONS for any crack in areas with no existing frame repair, at the times specified in Paragraph 1.E., Compliance. NOTE: It is acceptable to change the repeat inspection method from PART 2 to PART 3 or from PART 3 to PART 2 provided the repeat interval for the previously accomplished inspection method is complied with. 2) CONDITION 6: NO CRACK FOUND DURING PART 2 INSPECTION a) Repeat PART 2: FORWARD SIDE BODY STATION (STA) 1681 FUSELAGE FRAME HIGH FREQUENCY EDDY CURRENT (HFEC) AND LOW FREQUENCY EDDY CURRENT (LFEC) INSPECTIONS for any crack in areas with no existing frame repair, at the times specified in Paragraph 1.E., Compliance. NOTE: It is acceptable to change the repeat inspection method from PART 2 to PART 3 or from PART 3 to PART 2 provided the repeat interval for the previously accomplished inspection method is complied with. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 14, 2016 757-53A0100 43 of 120 BOEING SERVICE BULLETIN 757-53A0100 ALERTALERT ### Page 44 (b) OPTION 2: PART 3: AFT SIDE BODY STATION (STA) 1681 FUSELAGE FRAME HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTIONS for any crack in areas with no existing frame repair. 1) CONDITION 7: ANY CRACK FOUND DURING PART 3 INSPECTION a) (ACTION 1): Contact The Boeing Company for repair instructions and do the repair. b) (ACTION 2): Repeat PART 3: AFT SIDE BODY STATION (STA) 1681 FUSELAGE FRAME HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTIONS for any crack in areas with no existing frame repair, at the times specified in Paragraph 1.E., Compliance. NOTE: It is acceptable to change the repeat inspection method from PART 2 to PART 3 or from PART 3 to PART 2 provided the repeat interval for the previously accomplished inspection method is complied with. 2) CONDITION 8: NO CRACK FOUND DURING PART 3 INSPECTION a) Repeat PART 3: AFT SIDE BODY STATION (STA) 1681 FUSELAGE FRAME HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTIONS for any crack in areas with no existing frame repair, at the times specified in Paragraph 1.E., Compliance. NOTE: It is acceptable to change the repeat inspection method from PART 2 to PART 3 or from PART 3 to PART 2 provided the repeat interval for the previously accomplished inspection method is complied with. c. CONDITION 3: NO EXISTING FLOOR BEAM REPAIR COMMON TO THE STA 1681 FUSELAGE FRAME INSPECTION AREA NOTE: More than one CONDITION can be applicable in areas with no existing frame repair. (1) Do PART 4: BELOW THE FLOOR BODY STATION (STA) 1681 FUSELAGE FRAME HIGH FREQUENCY EDDY CURRENT (HFEC) AND LOW FREQUENCY EDDY CURRENT (LFEC) INSPECTIONS for any crack in areas with no existing frame repair and no existing floor beam repair. (a) CONDITION 9: ANY CRACK FOUND DURING PART 4 INSPECTION 1) (ACTION 1): Contact The Boeing Company for repair instructions and do the repair. 2) (ACTION 2): Repeat PART 4: BELOW THE FLOOR BODY STATION (STA) 1681 FUSELAGE FRAME HIGH FREQUENCY EDDY CURRENT (HFEC) AND LOW FREQUENCY EDDY CURRENT (LFEC) INSPECTIONS for any crack in areas with no existing frame repair and no existing floor beam repair, at the times specified in Paragraph 1.E., Compliance. (b) CONDITION 10: NO CRACK FOUND DURING PART 4 INSPECTION Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 14, 2016 757-53A0100 44 of 120 BOEING SERVICE BULLETIN 757-53A0100 ALERTALERT ### Page 45 1) Repeat PART 4: BELOW THE FLOOR BODY STATION (STA) 1681 FUSELAGE FRAME HIGH FREQUENCY EDDY CURRENT (HFEC) AND LOW FREQUENCY EDDY CURRENT (LFEC) INSPECTIONS for any crack in areas with no existing frame repair and no existing floor beam repair, at the times specified in Paragraph 1.E., Compliance. d. CONDITION 4: ANY EXISTING FLOOR BEAM REPAIR COMMON TO THE STA 1681 FUSELAGE FRAME INSPECTION AREA NOTE: More than one CONDITION can be applicable in areas with no existing frame repair. (1) Do PART 5: BELOW THE FLOOR BODY STATION (STA) 1681 FUSELAGE FRAME HIGH FREQUENCY EDDY CURRENT (HFEC) AND LOW FREQUENCY EDDY CURRENT (LFEC) INSPECTIONS for any crack in areas with no existing frame repair. (a) CONDITION 11: ANY CRACK FOUND DURING PART 5 INSPECTION 1) (ACTION 1): Contact The Boeing Company for repair instructions and do the repair. 2) (ACTION 2): Repeat PART 5: BELOW THE FLOOR BODY STATION (STA) 1681 FUSELAGE FRAME HIGH FREQUENCY EDDY CURRENT (HFEC) AND LOW FREQUENCY EDDY CURRENT (LFEC) INSPECTIONS for any crack in areas with no existing frame repair, at the times specified in Paragraph 1.E., Compliance. (b) CONDITION 12: NO CRACK FOUND DURING PART 5 INSPECTION 1) Repeat PART 5: BELOW THE FLOOR BODY STATION (STA) 1681 FUSELAGE FRAME HIGH FREQUENCY EDDY CURRENT (HFEC) AND LOW FREQUENCY EDDY CURRENT (LFEC) INSPECTIONS for any crack in areas with no existing frame repair, at the times specified in Paragraph 1.E., Compliance. 3. Do PART 6: CLOSE ACCESS 4. Put the airplane back to a serviceable condition. PART 1: ACCESS 1. Remove and keep the left and right side number 4 doorway lining. Refer to 757 AMM 25-21-06 as an accepted procedure. 2. Remove and keep the sidewall panels, adjacent to the number 4 doorway at STA 1681, left and right side. Refer to 757 AMM 25-21-02 as an accepted procedure for passenger airplanes. Refer to 757 AMM 25-55-00 as an accepted procedure for freighter airplanes. 3. Remove and keep the insulation blankets, at STA 1681, between stringer S-16 and S-18, left and right side. Refer to 757 AMM 25-21-05 and 757 AMM 25-50-07 as accepted procedures for passenger airplanes. Refer to 757 AMM 25-55-07 and 757 AMM 25-50-07 as accepted procedures for freighter airplanes. 4. Remove and keep the floor panels and lower doorsill scuff plate, at STA 1681, left and right side. Refer to 757 AMM 53-01-01 and 757 AMM 53-13-01 as accepted procedures. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 14, 2016 757-53A0100 45 of 120 BOEING SERVICE BULLETIN 757-53A0100 ALERTALERT ### Page 46 Group 1, Configuration 2-3; Group 2: PART 2: FORWARD SIDE BODY STATION (STA) 1681 FUSELAGE FRAME HIGH FREQUENCY EDDY CURRENT (HFEC) AND LOW FREQUENCY EDDY CURRENT (LFEC) INSPECTIONS 1. Do HFEC and LFEC inspections of the left side STA 1681 fuselage frame inner chord, in accordance with FIGURE 1. 2. Do HFEC and LFEC inspections of the right side STA 1681 fuselage frame inner chord, in accordance with FIGURE 2. PART 3: AFT SIDE BODY STATION (STA) 1681 FUSELAGE FRAME HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTIONS 1. RC Exempt - Remove and keep the aft galley and the aft lavatory aft of STA 1681. Refer to 757 AMM 25-31-04 and 757 AMM 25-41-04 as accepted procedures. 2. Group 1, Configuration 1: Do a HFEC inspection of the left side STA 1681 fuselage frame inner chord and outer chord, in accordance with FIGURE 3. 3. Group 1, Configuration 1: Do a HFEC inspection of the right side STA 1681 fuselage frame inner chord and outer chord, in accordance with FIGURE 4. 4. Group 1, Configuration 2-3; Group 2: Do a HFEC inspection of the left side STA 1681 fuselage frame inner chord, in accordance with FIGURE 5. 5. Group 1, Configuration 2-3; Group 2: Do a HFEC inspection of the right side STA 1681 fuselage frame inner chord, in accordance with FIGURE 6. PART 4: BELOW THE FLOOR BODY STATION (STA) 1681 FUSELAGE FRAME HIGH FREQUENCY EDDY CURRENT (HFEC) AND LOW FREQUENCY EDDY CURRENT (LFEC) INSPECTIONS 1. Group 1, Configuration 1: Do HFEC and LFEC inspections of the left side STA 1681 fuselage frame inner chord and outer chord, below the floor, in accordance with FIGURE 7. 2. Group 1, Configuration 1: Do HFEC and LFEC inspections of the right side STA 1681 fuselage frame inner chord and outer chord, below the floor, in accordance with FIGURE 8. 3. Group 1, Configuration 2-3; Group 2: Do HFEC and LFEC inspections of the left side STA 1681 fuselage frame inner chord, below the floor, in accordance with FIGURE 9. 4. Group 1, Configuration 2-3; Group 2: Do HFEC and LFEC inspections of the right side STA 1681 fuselage frame inner chord, below the floor, in accordance with FIGURE 10. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 14, 2016 757-53A0100 46 of 120 BOEING SERVICE BULLETIN 757-53A0100 ALERTALERT ### Page 47 PART 5: BELOW THE FLOOR BODY STATION (STA) 1681 FUSELAGE FRAME HIGH FREQUENCY EDDY CURRENT (HFEC) AND LOW FREQUENCY EDDY CURRENT (LFEC) INSPECTIONS 1. Group 1, Configuration 1: Do HFEC and LFEC inspections of the left side STA 1681 fuselage frame inner chord and outer chord, below the floor, in accordance with FIGURE 11. 2. Group 1, Configuration 1: Do HFEC and LFEC inspections of the right side STA 1681 fuselage frame inner chord and outer chord, below the floor, in accordance with FIGURE 12. 3. Group 1, Configuration 2-3; Group 2: Do HFEC and LFEC inspections of the left side STA 1681 fuselage frame inner chord, below the floor, in accordance with FIGURE 13. 4. Group 1, Configuration 2-3; Group 2: Do HFEC and LFEC inspections of the right side STA 1681 fuselage frame inner chord, below the floor, in accordance with FIGURE 14. PART 6: CLOSE ACCESS 1. Install kept floor panels and lower doorsill scuff plate. Refer to 757 AMM 53-01-01 and 757 AMM 53-13-01 as accepted procedures. 2. Install kept insulation blankets. Refer to 757 AMM 25-21-05 and 757 AMM 25-50-07 as accepted procedures for passenger airplanes. Refer to 757 AMM 25-55-07 and 757 AMM 25-50-07 as accepted procedures for freighter airplanes. 3. Install kept sidewall panels. Refer to 757 AMM 25-21-02 as an accepted procedure for passenger airplanes. Refer to 757 AMM 25-55-00 as an accepted procedure for freighter airplanes. 4. Install kept aft galley and aft lavatory, if removed for access. Refer to 757 AMM 25-31-04 and 757 AMM 25-41-04 as accepted procedures. 5. Install kept number 4 doorway lining. Refer to 757 AMM 25-21-06 as an accepted procedure. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 14, 2016 757-53A0100 47 of 120 BOEING SERVICE BULLETIN 757-53A0100 ALERTALERT ### Page 48 (OCR) BOEING SERVICE BULLETIN 757-53A0100 ALERT ALERT This Figure applies only to: Group 1, Configuration 2-3; Group 2. LAVATORY • OR GALLEY (TYPICAL) 2535567 FIGURE 1: LEFT SIDE - BODY STATION (STA) 1681 FUSELAGE FRAME ABOVE FLOOR - FORWARD INNER CHORD HIGH FREQUENCY EDDY CURRENT (HFEC) AND LOW FREQUENCY EDDY CURRENT (LFEC) INSPECTION (SHEET 1 OF 3) Original Issue: November 14, 2016 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished 757-53A0100 Work - See page 1 for details. 48 of 120 ### Page 49 (OCR) BOEING SERVICE BULLETIN 757-53A0100 ALERT ALERT 3) 4 LOCATIONS FLOOR BEAM FLANGE STA STA 1681 VIEW LOOKING AFT 1681 A-A FWD VIEW ROTATED 90 DEGREES CLOCKWISE VIEW ROTATED 90 DEGREES CLOCKWISE B-B C-C LFEC INSPECTION AREA HFEC INSPECTION AREA FIGURE 1: LEFT SIDE - BODY STATION (STA) 1681 FUSELAGE FRAME ABOVE FLOOR - FORWARD INNER CHORD HIGH FREQUENCY EDDY CURRENT (HFEC) AND LOW FREQUENCY EDDY CURRENT (LFEC) INSPECTION (SHEET 2 OF 3) Original Issue: November 14, 2016 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished 757-53A0100 Work - See page 1 for details. 49 of 120 ### Page 50 The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY numbers shown below are the number of parts necessary for this figure. More DataQtyIdentificationNameTaskStep (a)--Frame WebInspect1 (a)--Frame Forward Outer Radius Inspect (b)--Frame WebInspect2 (a) Do a HFEC inspection of the fuselage frame for any crack, along the sill web, above the angle and along the frame forward outer radius from the sill web to 5 inches above the floor beam flange, in accordance with 757 NDT Manual Part 6, 51-00-01 or 757 NDT Manual Part 6, 51-00-19. (b) Do a LFEC inspection of the fuselage frame for any crack, in the frame web around the fasteners through the angle, in accordance with 757 NDT Manual Part 6, 51-00-23. FIGURE 1: LEFT SIDE - BODY STATION (STA) 1681 FUSELAGE FRAME ABOVE FLOOR - FORWARD INNER CHORD HIGH FREQUENCY EDDY CURRENT (HFEC) AND LOW FREQUENCY EDDY CURRENT (LFEC) INSPECTION (SHEET 3 OF 3) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 14, 2016 757-53A0100 50 of 120 BOEING SERVICE BULLETIN 757-53A0100 ALERTALERT ### Page 51 (OCR) BOEING SERVICE BULLETIN 757-53A0100 ALERT ALERT This Figure applies only to: Group 1, Configuration 2-3; Group 2. LAVATORY OR GALLEY (TYPICAL) 2538269 FIGURE 2: RIGHT SIDE - BODY STATION (STA) 1681 FUSELAGE FRAME ABOVE FLOOR - FORWARD INNER CHORD HIGH FREQUENCY EDDY CURRENT (HFEC) AND LOW FREQUENCY EDDY CURRENT (LFEC) INSPECTION (SHEET 1 OF 3) Original Issue: November 14, 2016 Export Controlled ECCN: 9E991 - BOEING 757-53A0100 PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 51 of 120 ### Page 52 (OCR) BOEING SERVICE BULLETIN 757-53A0100 ALERT ALERT 4 LOCATIONS g 5.00 FLOOR BEAM FLANGE STA STA 1681 VIEW LOOKING AFT 1681 A-A VIEW ROTATED 90 DEGREES COUNTERCLOCKWISE VIEW ROTATED 90 DEGREES COUNTERCLOCKWISE B-B C-C LFEC INSPECTION AREA HFEC INSPECTION AREA FIGURE 2: RIGHT SIDE - BODY STATION (STA) 1681 FUSELAGE FRAME ABOVE FLOOR - FORWARD INNER CHORD HIGH FREQUENCY EDDY CURRENT (HFEC) AND LOW FREQUENCY EDDY CURRENT (LFEC) INSPECTION (SHEET 2 OF 3) Original Issue: November 14, 2016 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished 757-53A0100 Work - See page 1 for details. 52 of 120 ### Page 53 The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY numbers shown below are the number of parts necessary for this figure. More DataQtyIdentificationNameTaskStep (a)--Frame WebInspect1 (a)--Frame Forward Outer Radius Inspect (b)--Frame WebInspect2 (a) Do a HFEC inspection of the fuselage frame for any crack, along the sill web, above the angle and along the frame forward outer radius from the sill web to 5 inches above the floor beam flange, in accordance with 757 NDT Manual Part 6, 51-00-01 or 757 NDT Manual Part 6, 51-00-19. (b) Do a LFEC inspection of the fuselage frame for any crack, in the frame web around the fasteners through the angle, in accordance with 757 NDT Manual Part 6, 51-00-23. FIGURE 2: RIGHT SIDE - BODY STATION (STA) 1681 FUSELAGE FRAME ABOVE FLOOR - FORWARD INNER CHORD HIGH FREQUENCY EDDY CURRENT (HFEC) AND LOW FREQUENCY EDDY CURRENT (LFEC) INSPECTION (SHEET 3 OF 3) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 14, 2016 757-53A0100 53 of 120 BOEING SERVICE BULLETIN 757-53A0100 ALERTALERT ### Page 54 (OCR) BOEING SERVICE BULLETIN 757-53A0100 ALERT ALERT This Figure applies only to: Group 1, Configuration 1. STA 1681 • 8 LOCATIONS 5.00 FLOOR BEAM FLANGE B B INBD VIEW LOOKING FORWARD HFEC INSPECTION AREA A-A 2535570 FIGURE 3: LEFT SIDE - BODY STATION (STA) 1681 FUSELAGE FRAME ABOVE FLOOR - AFT INNER AND OUTER CHORD HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION (SHEET 1 OF 3) Original Issue: November 14, 2016 PROPRIETARY - Copyright © Unpublished Export Controlled ECCN: 9E991 - BOEING 757-53A0100 Work - See page 1 for details. 54 of 120 ### Page 55 (OCR) BOEING SERVICE BULLETIN 757-53A0100 ALERT ALERT STA 1681 VIEW ROTATED 90 DEGREES COUNTERCLOCKWISE B-B FWD VIEW ROTATED 90 DEGREES COUNTERCLOCKWISE C-C FIGURE 3: LEFT SIDE - BODY STATION (STA) 1681 FUSELAGE FRAME ABOVE FLOOR - AFT INNER AND OUTER CHORD HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION (SHEET 2 OF 3) Original Issue: November 14, 2016 Export Controlled ECCN: 9E991 - BOEING 757-53A0100 PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 55 of 120 ### Page 56 The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY numbers shown below are the number of parts necessary for this figure. More DataQtyIdentificationNameTaskStep (a)--Frame WebInspect1 (a)--Frame Forward Inner Radius Inspect (a)--Frame Aft Inner RadiusInspect (a)--Frame Outer ChordInspect (a) Do a HFEC inspection of the fuselage frame for any crack, along the sill web and around fasteners common to forward angle, outer chord around fasteners common to the web, and frame forward and aft inner radii from sill to 5 inches above the floor beam flange, in accordance with 757 NDT Manual Part 6, 51-00-01 or 757 NDT Manual Part 6, 51-00-19. FIGURE 3: LEFT SIDE - BODY STATION (STA) 1681 FUSELAGE FRAME ABOVE FLOOR - AFT INNER AND OUTER CHORD HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION (SHEET 3 OF 3) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 14, 2016 757-53A0100 56 of 120 BOEING SERVICE BULLETIN 757-53A0100 ALERTALERT ### Page 57 (OCR) BOEING SERVICE BULLETIN 757-53A0100 ALERT ALERT This Figure applies only to: Group 1, Configuration 1. STA 1681 8 LOCATIONS ТУКУ 5.00 FLOOR BEAM FLANGE B INBD VIEW LOOKING FORWARD A-A 2538272 HFEC INSPECTION AREA FIGURE 4: RIGHT SIDE - BODY STATION (STA) 1681 FUSELAGE FRAME ABOVE FLOOR - AFT INNER AND OUTER CHORD HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION (SHEET 1 OF 3) Original Issue: November 14, 2016 Export Controlled ECCN: 9E991 - BOEING 757-53A0100 PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 57 of 120 ### Page 58 (OCR) BOEING SERVICE BULLETIN 757-53A0100 ALERT ALERT STA 1681 STA VIEW ROTATED 90 DEGREES CLOCKWISE 1681 B-B VIEW ROTATED 90 DEGREES CLOCKWISE C-C 2538273 FIGURE 4: RIGHT SIDE - BODY STATION (STA) 1681 FUSELAGE FRAME ABOVE FLOOR - AFT INNER AND OUTER CHORD HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION (SHEET 2 OF 3) Original Issue: November 14, 2016 PROPRIETARY - Copyright © Unpublished Export Controlled ECCN: 9E991 - BOEING 757-53A0100 Work - See page 1 for details. 58 of 120 ### Page 59 The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY numbers shown below are the number of parts necessary for this figure. More DataQtyIdentificationNameTaskStep (a)--Frame WebInspect1 (a)--Frame Forward Inner Radius Inspect (a)--Frame Aft Inner RadiusInspect (a)--Frame Outer ChordInspect (a) Do a HFEC inspection of the fuselage frame for any crack, along the sill web and around fasteners common to forward angle, outer chord around fasteners common to the web, and frame forward and aft inner radii from sill to 5 inches above the floor beam flange, in accordance with 757 NDT Manual Part 6, 51-00-01 or 757 NDT Manual Part 6, 51-00-19. FIGURE 4: RIGHT SIDE - BODY STATION (STA) 1681 FUSELAGE FRAME ABOVE FLOOR - AFT INNER AND OUTER CHORD HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION (SHEET 3 OF 3) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 14, 2016 757-53A0100 59 of 120 BOEING SERVICE BULLETIN 757-53A0100 ALERTALERT ### Page 60 (OCR) BOEING SERVICE BULLETIN 757-53A0100 ALERT ALERT This Figure applies only to: Group 1, Configuration 2-3; Group 2. 2535573 FIGURE 5: LEFT SIDE - BODY STATION (STA) 1681 FUSELAGE FRAME ABOVE FLOOR - AFT INNER CHORD HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION (SHEET 1 OF 3) Original Issue: November 14, 2016 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished 757-53A0100 Work - See page 1 for details. 60 of 120 The text continues at https://openairdocs.org/service-documents/boeing/757-53a0100/file/3a29c04674c3.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.