# Boeing Alert Service Bulletin 717-55A0012: Revision 1 - Rights: © The Boeing Company. Filed by the FAA in regulations.gov docket FAA-2018-0413; AD 2018-10-08 incorporates this document by reference. Not covered by OpenAirDocs’ CC0 dedication. - Document: [Boeing Alert Service Bulletin 717-55A0012](https://openairdocs.org/service-documents/boeing/717-55a0012.md) - Title as filed: SB-717-55A0012-01-- - Pages: 65 - PDF: https://openairdocs.org/files/sha256/03/a0/03a075d7cdd03234c1644469487b9508ce6c3d95651eb4f6970c7b1981e4e871 - Page: https://openairdocs.org/service-documents/boeing/717-55a0012/file/03a075d7cdd0 ## 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 717 Service Bulletin ALERT Number: 717-55A0012 Original Issue: June 12, 2015 Revision 1: April 11, 2018 ATA System: 5532 SUBJECT: STABILIZERS - Vertical Stabilizer - Fixed Leading Edge Skin and Front Spar Cap at Station Zfs=52.267 Inspection and Repair Export of this technology is controlled under the United States Export Administration Regulations (EAR) (15 CFR 300-774). An export license may be required before it is used for development, production or use by foreign persons from specific countries. The controller of this data has the individual responsibility to abide by all export laws. 9E991ECCN: BOEING PROPRIETARY, CONFIDENTIAL AND/OR TRADE SECRET Copyright © 2015 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 Unpublished Work.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: June 12, 2015 717-55A0012Revision 1: April 11, 2018 1 of 65 4.0 ### Page 2 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 12, 2015 717-55A0012Revision 1: April 11, 2018 2 of 65 BOEING SERVICE BULLETIN 717-55A0012 ALERTALERT BLANK PAGE ### Page 3 Table of Contents Revision Transmittal Sheet . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5 Summary . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7 1. PLANNING INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11 A. Effectivity . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11 1. Airplanes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11 2. Spares Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11 B. Concurrent Requirements . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 12 C. Reason . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 12 D. Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 12 E. Compliance . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13 F. Approval . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20 G. Manpower . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21 H. Weight and Balance Changes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 22 I. Electrical Load Data . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 22 J. References . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 22 1. Existing Data: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 22 2. Data Supplied with this Service Bulletin: . . . . . . . . . . . . . . . . . . . . . . . . . . . 22 3. Installation Drawings Used in the Preparation of this Service Bulletin: . . . . . . . . . . . 22 K. Publications Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 23 L. Interchangeability and Intermixability of Parts . . . . . . . . . . . . . . . . . . . . . . . . . . . 23 M. Software Accomplishment Summary . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 23 2. MATERIAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25 A. Material - Price and Availability . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25 B. Industry Support Information . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25 C. Parts Necessary for Each Airplane . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25 1. Kits/Parts . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25 2. Parts and Materials Supplied by the Operator . . . . . . . . . . . . . . . . . . . . . . . . 25 3. Parts Modified and Reidentified . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25 4. Parts Removed and Not Replaced . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25 D. Parts Necessary to Change Spares . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25 E. Special Tooling - Price and Availability . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25 F. Special Tooling Necessary to do this Service Bulletin . . . . . . . . . . . . . . . . . . . . . . . 25 3. ACCOMPLISHMENT INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 27 A. GENERAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 27 B. WORK INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 29 FIGURE 1: LEFT SIDE VERTICAL STABILIZER LEADING EDGE STRUCTURE AT THE SPLICE AT STATION ZFS=52.267 DETAILED INSPECTION . . . . . . . . . . . . . . . . . . . . . . 33 FIGURE 2: LEFT SIDE VERTICAL STABILIZER FRONT SPAR CAP FORWARD FLANGE OPEN HOLE EDDY CURRENT, HIGH FREQUENCY (ETHF) INSPECTION . . . . . . . . . . . . . . . 35 FIGURE 3: LEFT SIDE VERTICAL STABILIZER FRONT SPAR CAP AFT FLANGES AT STATION ZFS=52.267 RADIOGRAPHIC TESTING (RT) INSPECTION . . . . . . . . . . . . . . . . 37 FIGURE 4: LEFT SIDE VERTICAL STABILIZER SIDE SKIN FRONT SPAR CAP AFT FLANGES EDDY CURRENT, HIGH FREQUENCY (ETHF) INSPECTION . . . . . . . . . . . . . . . . . . . 40 FIGURE 5: LEFT SIDE VERTICAL STABILIZER LEADING EDGE AT THE SPLICE AT STATION ZFS=52.267 (FASTENERS NOT REMOVED) DETAILED INSPECTION . . . . . . . . . . . . . . . . . 42 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 12, 2015 717-55A0012Revision 1: April 11, 2018 3 of 65 BOEING SERVICE BULLETIN 717-55A0012 ALERTALERT ### Page 4 FIGURE 6: RIGHT SIDE VERTICAL STABILIZER LEADING EDGE STRUCTURE AT THE SPLICE AT STATION ZFS=52.267 DETAILED INSPECTION . . . . . . . . . . . . . . . . . . . . . . 44 FIGURE 7: RIGHT SIDE VERTICAL STABILIZER FRONT SPAR CAP FORWARD FLANGE OPEN HOLE EDDY CURRENT, HIGH FREQUENCY (ETHF) INSPECTION . . . . . . . . . . . . . . . 46 FIGURE 8: RIGHT SIDE VERTICAL STABILIZER FRONT SPAR CAP AFT FLANGES AT STATION ZFS=52.267 RADIOGRAPHIC TESTING (RT) INSPECTION . . . . . . . . . . . . . . . . 48 FIGURE 9: RIGHT SIDE VERTICAL STABILIZER SIDE SKIN FRONT SPAR CAP AFT FLANGES EDDY CURRENT, HIGH FREQUENCY (ETHF) INSPECTION . . . . . . . . . . . . . . . . . . . 51 FIGURE 10: RIGHT SIDE VERTICAL STABILIZER LEADING EDGE AT THE SPLICE AT STATION ZFS=52.267 (FASTENERS NOT REMOVED) DETAILED INSPECTION . . . . . . . . . . 53 APPENDIX A: LOGIC DIAGRAM FOR PARAGRAPH 1.E., COMPLIANCE TABLE 1: INITIAL DETAILED INSPECTION, EDDY CURRENT HIGH FREQUENCY (ETHF) OR RADIOGRAPHIC TESTING (RT) INSPECTION: FIXED LEADING EDGE SKIN AND FRONT SPAR CAP AT STATION ZFS=52.267 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 55 APPENDIX B: LOGIC DIAGRAM FOR PARAGRAPH 1.E., COMPLIANCE TABLE 2: POST INITIAL DETAILED INSPECTION - FIXED LEADING EDGE SKIN AT STATION ZFS=52.267 . . . . . . . . . 57 APPENDIX C: LOGIC DIAGRAM FOR PARAGRAPH 1.E., COMPLIANCE TABLE 3: REPETITIVE EDDY CURRENT HIGH FREQUENCY (ETHF) OR RADIOGRAPHIC TESTING (RT) INSPECTION - FRONT SPAR CAP AT STATION ZFS=52.267 . . . . . . . . . . . . . . . . . . . . . . . 59 APPENDIX D: PREPARATION OF INSPECTION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 61 APPENDIX E: LOGIC DIAGRAM FOR PARAGRAPH 1.E., COMPLIANCE TABLE 4: INITIAL DETAILED INSPECTION, EDDY CURRENT HIGH FREQUENCY (ETHF) OR RADIOGRAPHIC TESTING (RT) INSPECTION: FIXED LEADING EDGE SKIN AND FRONT SPAR CAP AT STATION ZFS=52.267 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 62 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 12, 2015 717-55A0012Revision 1: April 11, 2018 4 of 65 BOEING SERVICE BULLETIN 717-55A0012 ALERTALERT ### Page 5 Commercial Airplanes 717 Service Bulletin ALERT Revision Transmittal SheetNumber: 717-55A0012Original Issue: June 12, 2015 Revision 1: April 11, 2018 ATA System: 5532 SUBJECT: STABILIZERS - Vertical Stabilizer - Fixed Leading Edge Skin and Front Spar Cap at Station Zfs=52.267 Inspection and Repair This revision includes all pages of the service bulletin. COMPLIANCE INFORMATION RELATED TO THIS REVISION Federal Aviation Administration (FAA) Airworthiness Directive (AD) 2016-09-05 is related to this service bulletin. Effects of this Revision on airplanes on which Original Issue was previously done: None. REASON FOR REVISION This revision is sent to revise the compliance time for operators who have not accomplished the Original Issue of this service bulletin. These sections were changed: 1. In Background, Paragraphs 1.C., Reason and 1.J. References: a. Added Boeing Service Related Problem (SRP) 717-SRP-55-0074. b. Added Boeing Fleet Team Digest (FTD) 717-FTD-55-15001. c. Updated Background Paragraph to match 1.C., Reason Paragraph. 2. Paragraph 1.A.,Group Configuration Description, added Configuration 1 and 2 information. 3. Paragraph 1.E., Compliance, was changed as follows: a. Added Federal Aviation Administration (FAA) Airworthiness Directive. b. Added new Appendix E. c. Updated compliance time from the Original Issue date of this service bulletin to the effective date of AD 2016-09-05. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 12, 2015 717-55A0012Revision 1: April 11, 2018 5 of 65 ### Page 6 d. Added Group 1, Configuration 1 to Table 1 for operators who have accomplished the Original Issue of this service bulletin. e. Added new Table 4 for Group 1, Configuration 2, to include revised compliance times for operators who have not accomplished the Original Issue of this service bulletin. 4. Paragraph 1.F., Approval, added approval information. 5. Paragraph 1.J.2., Data Supplied with this Service Bulletin, updated drawings. 6. Paragraph 3.A., General information, Note 7, added new Appendix E. 7. Appendices were changed as follows: a. Updated logic diagram in Appendix A and added new Appendix E to match new compliance information. b. Updated Appendix A, Appendix B, and Appendix C to include logic diagram note. Vertical lines are put on the left edge of each page, except in Paragraph 1.A., Effectivity and format changes, to show the location of all content changes. Pages with no vertical lines have no changes. REVISION HISTORY June 12, 2015Original Issue: April 11, 2018Revision 1: Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 12, 2015 717-55A0012Revision 1: April 11, 2018 6 of 65 BOEING SERVICE BULLETIN 717-55A0012 ALERTALERT ### Page 7 Commercial Airplanes 717 Service Bulletin ALERT SummaryNumber: 717-55A0012Original Issue: June 12, 2015 Revision 1: April 11, 2018 ATA System: 5532 SUBJECT: STABILIZERS - Vertical Stabilizer - Fixed Leading Edge Skin and Front Spar Cap at Station Zfs=52.267 Inspection and Repair 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 gives instructions to do inspections for distress and for any crack in the vertical stabilizer leading edge and front spar caps at the splice at station Zfs=52.267. Accomplishment of the inspections will determine the condition of the vertical stabilizer skin. Incorporation of the leading edge repair will minimize the possibility of crack growth. If not corrected, any crack in the vertical stabilizer leading edge and front spar cap may result in the structure unable to support limit load, and may lead to the loss of the vertical stabilizer. There have been ten cases reported of the 717 vertical stabilizer leading edge showing signs of fastener distress at the splice station Zfs=52.267. The affected 717s had accrued 22,594 through 40,985 flight-hours and 15,352 through 34,766 landing cycles. Similar reports have been found on MD-80 and MD-90 airplanes. One MD-90 operator reported finding elongated fastener holes at the leading edge of the vertical stabilizer at station Zfs=52.267. Two MD-80 operators reported finding a cracked vertical stabilizer skin at station Zfs=52.267, subsequent inspections revealed a severed front spar cap and a cracked front spar web. The affected MD-80 airplanes had accrued between 39,749 through 56,212 flight-hours and 32,176 through 44,001 landing cycles when the crack/ anomalies were found. The affected MD-90 airplane had accrued 15,555 flight-hours and 14,310 landing cycles. Missing fasteners, bushed or evidence of elongated fastener holes may be considered as an indication that there are undetected cracks in the underlying vertical stabilizer structure. Boeing investigation determined that high loading occurrences, such as, but not limited to, in-flight turbulence can adversely impact the fasteners and loading at the leading edge of the vertical stabilizer. Boeing Service Related Problem (SRP) 717-SRP-55-0074 is related to this service bulletin. Boeing Fleet Team Digest (FTD) 717 FTD 55-15001 is related to this service bulletin. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 12, 2015 717-55A0012Revision 1: April 11, 2018 7 of 65 ### Page 8 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 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 NoOperator Supplied Parts/Material Paragraph 2.F., Special Tooling Necessary to do this Service Bulletin NoSpecial Tooling Required ACTION Do a detailed inspection and Eddy Current High Frequency (ETHF) or Radiographic Testing (RT) inspection of the leading edge skin and front spar cap for any distress or any crack at station Zfs=52.267. If any distress in the leading edge is found, do the leading edge repair in accordance with service repair drawing SG95550001. If any crack in the vertical stabilizer front spar cap is found, contact The Boeing Company for Repair instructions and do the repair. EFFECTIVITY 717-200 Airplane(s). Refer to Paragraph 1.A.1., Airplanes, for the list of affected airplane(s). COMPLIANCE Federal Aviation Administration (FAA) Airworthiness Directive AD 2016-09-05 is related to this service bulletin. The effective date of AD 2016-09-05 is June 8, 2016. Refer to Paragraph 1.E., Compliance. INDUSTRY SUPPORT INFORMATION Boeing warranty remedies are not available for the inspection procedures 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: June 12, 2015 717-55A0012Revision 1: April 11, 2018 8 of 65 BOEING SERVICE BULLETIN 717-55A0012 ALERTALERT ### Page 9 (OCR) BOEING SERVICE BULLETIN 717-55A0012 ALERT ALERT MATERIAL INFORMATION None. DO A DETAILED INSPECTION AND EDDY CURRENT HIGH FREQUENCY (ETHF) OR RADIOGRAPHIC TESTING (RT) INSPECTION OF THE LEADING EDGE SKIN AND FRONT SPAR CAP FOR ANY DISTRESS OR CRACK AT STATION Zfs=52.267. IF ANY DISTRESS IN THE LEADING EDGE IS FOUND, DO THE LEADING EDGE REPAIR IN ACCORDANCE WITH SERVICE REPAIR DRAWING SG95550001. IF ANY CRACK IN THE VERTICAL STABILIZER FRONT SPAR CAP IS FOUND, CONTACT THE BOEING COMPANY FOR REPAIR INSTRUCTIONS AND DO THE REPAIR. 2397056 Original Issue: June 12, 2015 Revision 1: April 11, 2018 Export Controlled ECCN: 9E991 - BOEING 717-55A0012 PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 9 of 65 ### Page 10 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 12, 2015 717-55A0012Revision 1: April 11, 2018 10 of 65 BOEING SERVICE BULLETIN 717-55A0012 ALERTALERT BLANK PAGE ### Page 11 Commercial Airplanes 717 Service Bulletin ALERT Number: 717-55A0012 Original Issue: June 12, 2015 Revision 1: April 11, 2018 ATA System: 5532 SUBJECT: STABILIZERS - Vertical Stabilizer - Fixed Leading Edge Skin and Front Spar Cap at Station Zfs=52.267 Inspection and Repair 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 DESCRIPTIONCONFIGURATIONGROUP 717-200 airplanes. Line numbers (Fuselage) 5002-5156.-1 Airplanes that have accomplished the Original Issue of this service bulletin. 1 Airplanes that have not accomplished the Original Issue of this service bulletin. 2 Airplane Models: 717-200 GroupFuselage Num- ber 15002 - 5099 15100 - 5156 2. Spares Affected None. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 12, 2015 717-55A0012Revision 1: April 11, 2018 11 of 65 ### Page 12 B. Concurrent Requirements None. C. Reason This service bulletin gives instructions to do inspections for distress and for any crack in the vertical stabilizer leading edge and front spar caps at the splice at station Zfs=52.267. Accomplishment of the inspections will determine the condition of the vertical stabilizer skin. Incorporation of the leading edge repair will minimize the possibility of crack growth. If not corrected, any crack in the vertical stabilizer leading edge and front spar cap may result in the structure unable to support limit load, and may lead to the loss of the vertical stabilizer. There have been ten cases reported of the 717 vertical stabilizer leading edge showing signs of fastener distress at the splice station Zfs=52.267. The affected 717s had accrued 22,594 through 40,985 flight-hours and 15,352 through 34,766 landing cycles. Similar reports have been found on MD-80 and MD-90 airplanes. One MD-90 operator reported finding elongated fastener holes at the leading edge of the vertical stabilizer at station Zfs=52.267. Two MD-80 operators reported finding a cracked vertical stabilizer skin at station Zfs=52.267, subsequent inspections revealed a severed front spar cap and a cracked front spar web. The affected MD-80 airplanes had accrued between 39,749 through 56,212 flight-hours and 32,176 through 44,001 landing cycles when the crack/ anomalies were found. The affected MD-90 airplane had accrued 15,555 flight-hours and 14,310 landing cycles. Missing fasteners, bushed or evidence of elongated fastener holes may be considered as an indication that there are undetected cracks in the underlying vertical stabilizer structure. Boeing investigation determined that high loading occurrences, such as, but not limited to, in-flight turbulence can adversely impact the fasteners and loading at the leading edge of the vertical stabilizer. Boeing Service Related Problem (SRP) 717-SRP-55-0074 is related to this service bulletin. Boeing Fleet Team Digest (FTD) 717-FTD-55-15001 is related to this service bulletin. Revision 1 is sent to revise the compliance time for operators who have not accomplished the Original Issue of this service bulletin. D. Description Do a detailed inspection and Eddy Current High Frequency (ETHF) or Radiographic Testing (RT) inspection of the leading edge skin and front spar cap for any distress or any crack at station Zfs=52.267. If any distress in the leading edge is found, do the leading edge repair in accordance with service repair drawing SG95550001. If any crack in the vertical stabilizer front spar cap is found, contact The Boeing Company for Repair instructions and do the repair. Effects of this Revision on airplanes on which Original Issue was previously done: None. The work in this service bulletin is done in the maintenance zone(s) given below. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 12, 2015 717-55A0012Revision 1: April 11, 2018 12 of 65 BOEING SERVICE BULLETIN 717-55A0012 ALERTALERT ### Page 13 Affected Maintenance Zones ZoneModel 371717-200 E. Compliance Federal Aviation Administration (FAA) Airworthiness Directive AD 2016-09-05 is related to this service bulletin. The effective date of AD 2016-09-05 is June 8, 2016. 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. Do the required actions in accordance with Paragraph 3. Accomplishment Instructions. Logic diagrams showing compliance tasks and compliance times are included as an aid in APPENDIX A, APPENDIX B, APPENDIX C, and APPENDIX E. Group 1, Configuration 1: Table 1: Initial Detailed Inspection, Eddy Current High Frequency (ETHF) or Radiographic Testing (RT) Inspection: Fixed Leading Edge Skin and Front Spar Cap at Station Zfs=52.267 Repeat Inter- val (Not to Ex- ceed) Compliance Time (Whichev- er Occurs Later) ActionCondition -Within 6,200 flight cycles after the effec- tive date of AD 2016-09- 05. Before 15,000 total flight cy- cles. Do PART 1: VERTICAL STABILIZ- ER LEADING EDGE SKIN - DE- TAILED INSPECTIONS for any distress (FASTENERS RE- MOVED). All Airplanes. -Before further flight.OPTION 1:CONDITION 1: Do PART 2: VERTICAL STABILIZ- ER SPAR CAP - EDDY CUR- RENT, HIGH FREQUENCY (ETHF) and RADIOGRAPHIC TESTING (RT) INSPECTION for any crack. LEADING EDGE SKIN IS NOT DISTRESSED. -Before further flight.OPTION 2: Do PART 3: VERTICAL STABILIZ- ER SPAR CAP - EDDY CUR- RENT, HIGH FREQUENCY (ETHF) INSPECTION for any crack. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 12, 2015 717-55A0012Revision 1: April 11, 2018 13 of 65 BOEING SERVICE BULLETIN 717-55A0012 ALERTALERT ### Page 14 Group 1, Configuration 1: Table 1: Initial Detailed Inspection, Eddy Current High Frequency (ETHF) or Radiographic Testing (RT) Inspection: Fixed Leading Edge Skin and Front Spar Cap at Station Zfs=52.267 Repeat Inter- val (Not to Ex- ceed) Compliance Time (Whichev- er Occurs Later) ActionCondition -Refer to Table 2 for compli- ance information. CONDITION 1.1 (ACTION 1): Do Repetitive Detailed Inspec- tions of the Fixed Leading Edge Skin at Station Zfs=52.267. CONDITION 1.1: NO CRACK FOUND during OPTION 1 or OPTION 2 spar cap inspection. -Refer to Table 3 for compli- ance information. CONDITION 1.1 (ACTION 2): Do Repetitive Inspection of the Vertical Stabilizer Front Spar Cap at Station Zfs=52.267. -Before further flight.Contact The Boeing Company for repair instructions and do the re- pair. CONDITION 1.2: ANY CRACK FOUND dur- ing OPTION 1 or OPTION 2 spar cap inspection. -Before further flight.OPTION 1:CONDITION 2: Do PART 2: VERTICAL STABILIZ- ER SPAR CAP - EDDY CUR- RENT, HIGH FREQUENCY (ETHF) and RADIOGRAPHIC TESTING (RT) INSPECTION for any crack. LEADING EDGE SKIN IS DISTRESSED. -Before further flight.OPTION 2: Do PART 3: VERTICAL STABILIZ- ER SPAR CAP - EDDY CUR- RENT, HIGH FREQUENCY (ETHF) INSPECTION for any crack. -Before further flight.CONDITION 2.1 (ACTION 1):CONDITION 2.1: Do PART 5: VERTICAL STABILIZ- ER LEADING EDGE SKIN RE- PAIR. NO CRACK FOUND during OPTION 1 or OPTION 2 spar cap inspection. -Refer to Table 2 for compli- ance information. CONDITION 2.1 (ACTION 2): Do Repetitive Detailed Inspec- tions of the Fixed Leading Edge Skin at Station Zfs=52.267. -Refer to Table 3 for compli- ance information. CONDITION 2.1 (ACTION 3): Do Repetitive Inspection of the Vertical Stabilizer Front Spar Cap at Station Zfs=52.267. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 12, 2015 717-55A0012Revision 1: April 11, 2018 14 of 65 BOEING SERVICE BULLETIN 717-55A0012 ALERTALERT ### Page 15 Group 1, Configuration 1: Table 1: Initial Detailed Inspection, Eddy Current High Frequency (ETHF) or Radiographic Testing (RT) Inspection: Fixed Leading Edge Skin and Front Spar Cap at Station Zfs=52.267 Repeat Inter- val (Not to Ex- ceed) Compliance Time (Whichev- er Occurs Later) ActionCondition -Before further flight.CONDITION 2.2 (ACTION 1):CONDITION 2.2: Do PART 5: VERTICAL STABILIZ- ER LEADING EDGE SKIN RE- PAIR. ANY CRACK FOUND dur- ing OPTION 1 or OPTION 2 spar cap inspection. -Before further flight.CONDITION 2.2 (ACTION 2): Contact The Boeing Company for repair instructions and do the re- pair. Table 2: Post Initial Detailed Inspection - Repetitive Detailed Inspections of the Fixed Leading Edge Skin at Station Zfs=52.267 Repeat Interval (Not to Exceed) Compliance TimeActionCondition -Within 4,400 flight cycles after the initial inspection. Do PART 4: VERTICAL STABILIZ- ER LEADING EDGE SKIN - DE- TAILED INSPECTIONS (FASTEN- ERS NOT REMOVED) for any loose and missing fasteners. ALL AIRPLANES WHICH COMPLETED OPTION 1 AND NO CRACK WAS FOUND. -Within 3,000 flight cycles after the initial inspection. Do PART 4: VERTICAL STABILIZ- ER LEADING EDGE SKIN - DE- TAILED INSPECTIONS (FASTEN- ERS NOT REMOVED) for any loose and missing fasteners. ALL AIRPLANES WHICH COMPLETED OPTION 2 AND NO CRACK WAS FOUND. 4,400 flight cycles (a) -Repeat PART 4: VERTICAL STABI- LIZER LEADING EDGE SKIN - DETAILED INSPECTIONS (FAS- TENERS NOT REMOVED) for any loose and missing fasteners. CONDITION 3: NO LOOSE AND NO MISSING FASTENERS ON AIRPLANES WHICH COMPLETED OPTION 1 INSPECTIONS. 3,000 flight cycles (a) -Repeat PART 4 VERTICAL STABI- LIZER LEADING EDGE SKIN - DETAILED INSPECTIONS (FAS- TENERS NOT REMOVED) for any loose and missing fasteners. CONDITION 4: NO LOOSE AND NO MISSING FASTENERS ON AIRPLANES WHICH COMPLETED OPTION 2 INSPECTIONS. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 12, 2015 717-55A0012Revision 1: April 11, 2018 15 of 65 BOEING SERVICE BULLETIN 717-55A0012 ALERTALERT ### Page 16 Table 2: Post Initial Detailed Inspection - Repetitive Detailed Inspections of the Fixed Leading Edge Skin at Station Zfs=52.267 Repeat Interval (Not to Exceed) Compliance TimeActionCondition -Before further flight.CONDITION 5 (ACTION 1):CONDITION 5: Do PART 5: VERTICAL STABILIZ- ER LEADING EDGE SKIN RE- PAIR. ANY LOOSE OR MISSING FASTENERS ON AIRPLANES WHICH COMPLETED OPTION 1 INSPECTIONS. 4,400 flight cycles (a) -CONDITION 5 (ACTION 2): Repeat PART 4: VERTICAL STABI- LIZER LEADING EDGE SKIN - DETAILED INSPECTIONS (FAS- TENERS NOT REMOVED) for any loose and missing fasteners. -Before further flight.CONDITION 6 (ACTION 1):CONDITION 6: Do PART 5: VERTICAL STABILIZ- ER LEADING EDGE REPAIR. ANY LOOSE OR MISSING FASTENERS ON AIRPLANES WHICH COMPLETED OPTION 2 INSPECTIONS. 3,000 flight cycles(a)-CONDITION 6 (ACTION 2):Repeat PART 4: VERTICAL STABI- LIZER LEADING EDGE SKIN - DETAILED INSPECTIONS (FAS- TENERS NOT REMOVED) for any loose and missing fasteners. (a) Changing from one inspection option to another option is acceptable, provided the repeat interval require- ment is first complied with, before changing options. Table 3: Repetitive Eddy Current High Frequency (ETHF) or Radiographic Testing (RT) Inspection: Front Spar Cap at Station Zfs=52.267 Repeat Interval (Not to Exceed) Compliance TimeActionCondition -Within 4,400 flight cycles after the initial inspection. OPTION 1: Do PART 2: VERTICAL STABILIZ- ER SPAR CAP - EDDY CURRENT, HIGH FREQUENCY (ETHF) and RADIOGRAPHIC TESTING (RT) INSPECTION for any crack. ALL AIRPLANES WHICH COMPLETED OPTION 1 AND NO CRACK WAS FOUND. OPTION 2: Do PART 3: VERTICAL STABILIZ- ER SPAR CAP - EDDY CURRENT, HIGH FREQUENCY (ETHF) IN- SPECTION for any crack. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 12, 2015 717-55A0012Revision 1: April 11, 2018 16 of 65 BOEING SERVICE BULLETIN 717-55A0012 ALERTALERT ### Page 17 Table 3: Repetitive Eddy Current High Frequency (ETHF) or Radiographic Testing (RT) Inspection: Front Spar Cap at Station Zfs=52.267 Repeat Interval (Not to Exceed) Compliance TimeActionCondition -Within 3,000 flight cycles after initial in- spections. OPTION 1: Do PART 2: VERTICAL STABILIZ- ER SPAR CAP - EDDY CURRENT, HIGH FREQUENCY (ETHF) and RADIOGRAPHIC TESTING (RT) INSPECTION for any crack. ALL AIRPLANES WHICH COMPLETED OPTION 2 AND NO CRACK WAS FOUND. OPTION 2: Do PART 3: VERTICAL STABILIZ- ER SPAR CAP - EDDY CURRENT, HIGH FREQUENCY (ETHF) IN- SPECTION for any crack. 4,400 flight cycles (a) -OPTION 1: Do PART 2: VERTICAL STABILIZ- ER SPAR CAP - EDDY CURRENT, HIGH FREQUENCY (ETHF) and RADIOGRAPHIC TESTING (RT) INSPECTION for any crack. CONDITION 7: NO CRACK FOUND ON AIR- PLANES WHICH COMPLETED OPTION 1 INSPECTION. OPTION 2: Do PART 3: VERTICAL STABILIZ- ER SPAR CAP - EDDY CUR- RENT,HIGH FREQUENCY(ETHF) INSPECTION for any crack. 3,000 flight cycles (a) -OPTION 1: Do PART 2: VERTICAL STABILIZ- ER SPAR CAP - EDDY CURRENT, HIGH FREQUENCY (ETHF) and RADIOGRAPHIC TESTING (RT) INSPECTION for any crack. CONDITION 8: NO CRACK FOUND ON AIR- PLANES WHICH COMPLETED OPTION 2 INSPECTION. OPTION 2: Do PART 3: VERTICAL STABILIZ- ER SPAR CAP - EDDY CUR- RENT,HIGH FREQUENCY(ETHF) INSPECTION for any crack. -Before further flight.Contact The Boeing Company for repair instructions and do the re- pair. CONDITION 9: ANY CRACK FOUND ON AIR- PLANES WHICH COMPLETE OPTION 1 AND OPTION 2 IN- SPECTION. (a) Changing from one inspection option to another option is acceptable, provided the repeat interval require- ment is first complied with, before changing options. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 12, 2015 717-55A0012Revision 1: April 11, 2018 17 of 65 BOEING SERVICE BULLETIN 717-55A0012 ALERTALERT ### Page 18 Group 1, Configuration 2: Table 4: Initial Detailed Inspection, Eddy Current High Frequency (ETHF) or Radiographic Testing (RT) Inspection: Fixed Leading Edge Skin and Front Spar Cap at Station Zfs=52.267 Repeat Interval (Not to Exceed) Compliance Time (Whichever Occurs Later) ActionCondition -Within 500 flight cycles after the Revision 1 issue date of this service bulletin. Before 33,500 to- tal flight cycles. Or Within 6,200 flight cycles after the ef- fective date of AD 2016-09-05. Whichever occurs first. Do PART 1: VERTICAL STA- BILIZER LEADING EDGE SKIN - DETAILED INSPEC- TIONS for any distress (FAS- TENERS REMOVED). Airplanes that have not ac- complished the Original Issue of this service bulletin and have accumulated 32,500 or greater total flight cycles as of the Revision 1 issue date of this service bulletin. Or Within 6,200 flight cycles after the ef- fective date of AD 2016-09-05. Whichever occurs first. --Within 1,000 flight cycles after the Revision 1 issue date of this service bulletin. Do PART 1: VERTICAL STA- BILIZER LEADING EDGE SKIN - DETAILED INSPEC- TIONS for any distress (FAS- TENERS REMOVED). Airplanes that have not ac- complished the Original Issue of this service bulletin and have accumulated 28,000 to 32,499 total flight cycles as of the Revision 1 issue date of this service bulletin. Or Within 6,200 flight cycles after the ef- fective date of AD 2016-09-05. Whichever occurs first. -Within 6,200 flight cycles after the ef- fective date of AD 2016-09-05. Before 15,000 to- tal flight cycles. Do PART 1: VERTICAL STA- BILIZER LEADING EDGE SKIN - DETAILED INSPEC- TIONS for any distress (FAS- TENERS REMOVED). Airplanes that have not ac- complished the Original Issue of this service bulletin and have accumulated less than 28,000 total flight cycles as of the Revision 1 issue date of this service bulletin. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 12, 2015 717-55A0012Revision 1: April 11, 2018 18 of 65 BOEING SERVICE BULLETIN 717-55A0012 ALERTALERT ### Page 19 Group 1, Configuration 2: Table 4: Initial Detailed Inspection, Eddy Current High Frequency (ETHF) or Radiographic Testing (RT) Inspection: Fixed Leading Edge Skin and Front Spar Cap at Station Zfs=52.267 Repeat Interval (Not to Exceed) Compliance Time (Whichever Occurs Later) ActionCondition -Before further flight.OPTION 1:CONDITION 1: Do PART 2: VERTICAL STA- BILIZER SPAR CAP - EDDY CURRENT, HIGH FREQUEN- CY (ETHF) and RADIO- GRAPHIC TESTING (RT) IN- SPECTION for any crack. LEADING EDGE SKIN IS NOT DISTRESSED. -Before further flight.OPTION 2: Do PART 3: VERTICAL STA- BILIZER SPAR CAP - EDDY CURRENT, HIGH FREQUEN- CY (ETHF) INSPECTION for any crack. -Refer to Table 2 for compliance infor- mation. CONDITION 1.1 (ACTION 1): Do Repetitive Detailed Inspec- tions of the Fixed Leading Edge Skin at Station Zfs=52.267. CONDITION 1.1: NO CRACK FOUND during OPTION 1 or OPTION 2 spar cap inspection. -Refer to Table 3 for compliance infor- mation. CONDITION 1.1 (ACTION 2): Do Repetitive Inspection of the Vertical Stabilizer Front Spar Cap at Station Zfs=52.267. -Before further flight.Contact The Boeing Company for repair instructions and do the repair. CONDITION 1.2: ANY CRACK FOUND during OPTION 1 or OPTION 2 spar cap inspection. -Before further flight.OPTION 1:CONDITION 2: Do PART 2: VERTICAL STA- BILIZER SPAR CAP - EDDY CURRENT, HIGH FREQUEN- CY (ETHF) and RADIO- GRAPHIC TESTING (RT) IN- SPECTION for any crack. LEADING EDGE SKIN IS DISTRESSED. -Before further flight.OPTION 2: Do PART 3: VERTICAL STA- BILIZER SPAR CAP - EDDY CURRENT, HIGH FREQUEN- CY (ETHF) INSPECTION for any crack. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 12, 2015 717-55A0012Revision 1: April 11, 2018 19 of 65 BOEING SERVICE BULLETIN 717-55A0012 ALERTALERT ### Page 20 Group 1, Configuration 2: Table 4: Initial Detailed Inspection, Eddy Current High Frequency (ETHF) or Radiographic Testing (RT) Inspection: Fixed Leading Edge Skin and Front Spar Cap at Station Zfs=52.267 Repeat Interval (Not to Exceed) Compliance Time (Whichever Occurs Later) ActionCondition -Before further flight.CONDITION 2.1 (ACTION 1):CONDITION 2.1: Do PART 5: VERTICAL STA- BILIZER LEADING EDGE SKIN REPAIR. NO CRACK FOUND during OPTION 1 or OPTION 2 spar cap inspection. -Refer to Table 2 for compliance infor- mation. CONDITION 2.1 (ACTION 2): Do Repetitive Detailed Inspec- tions of the Fixed Leading Edge Skin at Station Zfs=52.267. -Refer to Table 3 for compliance infor- mation. CONDITION 2.1 (ACTION 3): Do Repetitive Inspection of the Vertical Stabilizer Front Spar Cap at Station Zfs=52.267. -Before further flight.CONDITION 2.2 (ACTION 1):CONDITION 2.2: Do PART 5: VERTICAL STA- BILIZER LEADING EDGE SKIN REPAIR. ANY CRACK FOUND during OPTION 1 or OPTION 2 spar cap inspection. -Before further flight.CONDITION 2.2 (ACTION 2): Contact The Boeing Company for repair instructions and do the repair. F. Approval This service bulletin was examined by the Federal Aviation Administration (FAA). The changes specified in this service bulletin comply with the applicable regulations and are FAA approved, as well as European Aviation Safety Agency (EASA)/Joint Aviation Authorities (JAA) approved for all EASA/JAA approved airplanes listed in the service bulletin effectivity. This service bulletin and its approval were based on the airplane in its original Boeing delivery configuration or as modified by other approved Boeing changes. If an airplane has a non-Boeing modification or repair that affects a component or system also affected by this service bulletin, the operator is responsible for obtaining appropriate regulatory agency approval before incorporating this service bulletin. In addition, the Manager of the FAA Los Angeles ACO Branch approves the inspection, related investigative and corrective actions defined in this service bulletin as an alternative method of compliance to the requirements of paragraphs (g) and (h) of AD 2016-09-05. All provisions of AD 2016-09-05 that are not specifically referenced in the above statement remain fully applicable and must be complied with. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 12, 2015 717-55A0012Revision 1: April 11, 2018 20 of 65 BOEING SERVICE BULLETIN 717-55A0012 ALERTALERT ### Page 21 G. Manpower The table below shows an estimate of the task hours necessary to do these inspections for each airplane. This estimate is for direct labor only, done by an experienced crew. Adjust the estimate with operator task hour data if necessary. The estimate does not include lost time. These are some examples of lost time: • Time to adjust to the workplace • Time to schedule the work • Time to inspect the work • Time to cure the materials • Time to make the parts • Time to find the tools. Table 1: Initial Detailed Inspection, Eddy Current High Frequency (ETHF) or Radiographic Testing (RT) Inspection: Fixed Leading Edge Skin and Front Spar Cap at Station Zfs=52.267 Elapsed HoursTask HoursNumber of PersonsTask 2.52.51FIGURE 1 2.02.01FIGURE 2 1.01.01FIGURE 3 or FIGURE 4 2.52.51FIGURE 6 2.02.01FIGURE 7 1.01.01FIGURE 8 or FIGURE 9 11.011.0TOTAL FOR EACH AIRPLANE (a)(b) (a) Inspection hours given are for each airplane. (b) Task hours required for repairs are not included and are to be determined by the operator based on in- spection results. Table 2: Post Initial Detailed Inspection, Repetitive Eddy Current High Frequency (ETHF) or Radiographic Testing (RT) Inspection: Fixed Leading Edge Skin and Front Spar Cap at Station Zfs=52.267 Elapsed HoursTask HoursNumber of PersonsTask 2.02.01FIGURE 2 1.01.01FIGURE 3 or FIGURE 4 0.50.51FIGURE 5 2.02.01FIGURE 7 1.01.01FIGURE 8 or FIGURE 9 0.50.51FIGURE 10 7.07.0TOTAL FOR EACH AIRPLANE (a)(b) (a) Inspection hours given are for each airplane. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 12, 2015 717-55A0012Revision 1: April 11, 2018 21 of 65 BOEING SERVICE BULLETIN 717-55A0012 ALERTALERT ### Page 22 Table 2: Post Initial Detailed Inspection, Repetitive Eddy Current High Frequency (ETHF) or Radiographic Testing (RT) Inspection: Fixed Leading Edge Skin and Front Spar Cap at Station Zfs=52.267 Elapsed HoursTask HoursNumber of PersonsTask (b) Task hours required for repairs are not included and are to be determined by the operator based on in- spection results. H. Weight and Balance Changes Weight and balance changes affected by incorporation of this drawing are contingent upon the modification of each particular aircraft. Weight data is to be computed by the operator by weighing parts installed or removed. Necessary revisions should be made to the appropriate weight and balance report. I. Electrical Load Data Not changed. J. References 1. Existing Data: a. Federal Aviation Administration (FAA) Airworthiness Directive (AD) 2016-09-05 b. Non-Destructive Test Standard Practices Manual (NDTSPM) 02-00-07, 06-10-01.001, 06-10-01.003, Part 01-00-03, Part 02-00-03, Part 02-00-04, Part 06-00-03, Part 06-00-04 c. 717 Fleet Team Digest (FTD) 55-15001 d. Boeing Service Related Problem (SRP) 717-SRP-55-0074 e. 717 Structural Repair Manual (SRM) 51-40-08, 51-41-01 f. Service Repair Drawing SG95550001 2. Data Supplied with this Service Bulletin: a. Drawings: ADCNDCN/REVSheetTitleDrawing No -Y1L.E. Instl. - Vert Stab5930609 -B1FIXED LEADING EDGE SKIN REPAIR - VERTICAL STABILIZER, ZFS=52.267 SG95550001 -B2 -BEO 3. Installation Drawings Used in the Preparation of this Service Bulletin: None. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 12, 2015 717-55A0012Revision 1: April 11, 2018 22 of 65 BOEING SERVICE BULLETIN 717-55A0012 ALERTALERT ### Page 23 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. DTI requirements for the structure affected are contained in Paragraph 1.E., Compliance of this service bulletin. L. Interchangeability and Intermixability of Parts Accomplishment of this service bulletin does not affect interchangeability or intermixability of parts. M. Software Accomplishment Summary Not affected. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 12, 2015 717-55A0012Revision 1: April 11, 2018 23 of 65 BOEING SERVICE BULLETIN 717-55A0012 ALERTALERT ### Page 24 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 12, 2015 717-55A0012Revision 1: April 11, 2018 24 of 65 BOEING SERVICE BULLETIN 717-55A0012 ALERTALERT BLANK PAGE ### Page 25 2. MATERIAL INFORMATION A. Material - Price and Availability None. B. Industry Support Information Boeing warranty remedies are not available for the inspection procedures given in this service bulletin. C. Parts Necessary for Each Airplane 1. Kits/Parts Based on inspection results, refer to Service General Repair Drawing SG95550001 for repair parts necessary for each airplane. 2. Parts and Materials Supplied by the Operator Based on inspection results, refer to Service General Repair Drawing SG95550001 for operator supplied parts and materials necessary to do the required repairs. 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 Inspection equipment required to accomplish this service bulletin are listed in APPENDIX D and in the NDTSPM and are to be procured from operator's stock or sources indicated. 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: June 12, 2015 717-55A0012Revision 1: April 11, 2018 25 of 65 BOEING SERVICE BULLETIN 717-55A0012 ALERTALERT ### Page 26 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 12, 2015 717-55A0012Revision 1: April 11, 2018 26 of 65 BOEING SERVICE BULLETIN 717-55A0012 ALERTALERT BLANK PAGE ### Page 27 3. ACCOMPLISHMENT INSTRUCTIONS A. GENERAL INFORMATION IF ELECTRICAL POWER IS APPLIED TO THE AIRPLANE, MAKE SURE YOU OBEY ALL PRECAUTIONS WHILE YOU DO WORK. IF YOU DO NOT OBEY THE PRECAUTIONS, DEATH OR INJURY TO PERSONS, AND DAMAGE TO THE AIRPLANE CAN OCCUR. WARNING ELECTRICALLY GROUND THE AIRPLANE. THIS WILL HELP TO PREVENT DAMAGE TO THE AIRPLANE OR EQUIPMENT. 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. CAUTION NOTE: 1. Manual titles are referred to by acronyms. Refer to Paragraph 1.J., References, for definition of the acronyms. 2. Equivalent parts are listed in the AEPL, Drawing 7595071. 3. Use the approved fastener and process material substitutions, in accordance with 717 SRM 51-41-01. 4. 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 are in 717 SRM 51-40-08 – Torque Values: — Values for structural fasteners are given in 717 Structural Repair Manual, Chapter 51. — Values for airframe maintenance tasks are included in Chapter 20 of 717 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 717 Aircraft Maintenance Manual (AMM). — Non-standard torque values for maintenance tasks are included in the applicable installation step. 5. Obey all of the warnings and cautions given in the specified manual sections. 6. Refer to APPENDIX D for preparation of inspection. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 12, 2015 717-55A0012Revision 1: April 11, 2018 27 of 65 BOEING SERVICE BULLETIN 717-55A0012 ALERTALERT ### Page 28 7. Refer to APPENDIX A, APPENDIX B, APPENDIX C, and APPENDIX E for logic diagram(s). Logic diagrams are provided as an aid only. Information contained in Paragraph 1.E., Compliance is the primary source for compliance times. Information contained in Paragraph 3.B., Work Instructions is the primary source for tasks required for compliance. 8. A Detailed Inspection is defined as: An intensive examination of a specific item, installation, or assembly to detect damage, failure, or irregularity. Available lighting is normally supplemented with a direct source of good lighting at an intensity deemed appropriate. Inspection aids such as mirrors, magnifying lenses, etc. may be necessary. Surface cleaning and elaborate procedures may be required. 9. 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. 10. 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. 11. 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. 12. If shading is used, shaded areas in Figures are reference only. Shaded areas in Figures may look different than your airplane. 13. Use of colors in Figures is based on guidance from the ATA e-Business Program (ATA) iSpec 2200. 14. 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. 15. The compliance times for the actions in Paragraph 3.B., WORK INSTRUCTIONS are in Paragraph 1.E., Compliance. 16. Some steps in the Work Instructions are labeled as Required for Compliance (RC). If this service bulletin is mandated by an Airworthiness Directive (AD), then the steps labeled as RC, including sub-steps under an RC step and any figures identified in an RC step, must be done to comply with the AD. An Alternative Method of Compliance (AMOC) is required for any deviations to RC steps, including sub-steps 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. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 12, 2015 717-55A0012Revision 1: April 11, 2018 28 of 65 BOEING SERVICE BULLETIN 717-55A0012 ALERTALERT ### Page 29 B. WORK INSTRUCTIONS 1. RC - Do PART 1: VERTICAL STABILIZER LEADING EDGE SKIN - DETAILED INSPECTIONS for any distress (FASTENERS REMOVED). a. CONDITION 1: LEADING EDGE SKIN IS NOT DISTRESSED. (1) OPTION 1: Do PART 2: VERTICAL STABILIZER SPAR CAP - EDDY CURRENT, HIGH FREQUENCY (ETHF) and RADIOGRAPHIC TESTING (RT) INSPECTION for any crack. (a) CONDITION 1.1: NO CRACK FOUND. 1) Put airplane back to a serviceable condition. 2) CONDITION 1.1 (ACTION 1): Do Repetitive Detailed Inspections of the Fixed Leading Edge Skin at Station Zfs=52.267. 3) CONDITION 1.1 (ACTION 2): Do Repetitive Inspection of the Vertical Stabilizer Front Spar Cap at Station Zfs=52.267. (b) CONDITION 1.2: ANY CRACK FOUND. 1) Contact The Boeing Company for repair instructions and do the repair. (2) OPTION 2: Do PART 3: VERTICAL STABILIZER SPAR CAP - EDDY CURRENT, HIGH FREQUENCY (ETHF) INSPECTION for any crack. (a) CONDITION 1.1: NO CRACK FOUND. 1) Put airplane back to a serviceable condition. 2) CONDITION 1.1 (ACTION 1): Do Repetitive Detailed Inspections of the Fixed Leading Edge Skin at Station Zfs=52.267. 3) CONDITION 1.1 (ACTION 2): Do Repetitive Inspection of the Vertical Stabilizer Front Spar Cap at Station Zfs=52.267. (b) CONDITION 1.2: ANY CRACK FOUND. 1) Contact The Boeing Company for repair instructions and do the repair. b. CONDITION 2: LEADING EDGE SKIN IS DISTRESSED. (1) OPTION 1: Do PART 2: VERTICAL STABILIZER SPAR CAP - EDDY CURRENT, HIGH FREQUENCY (ETHF) and RADIOGRAPHIC TESTING (RT) INSPECTION for any crack. (a) CONDITION 2.1: NO CRACK FOUND. 1) CONDITION 2.1 (ACTION 1): Do PART 5: VERTICAL STABILIZER LEADING EDGE SKIN REPAIR. 2) CONDITION 2.1 (ACTION 2): Do Repetitive Detailed Inspections of the Fixed Leading Edge Skin at Station Zfs=52.267. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 12, 2015 717-55A0012Revision 1: April 11, 2018 29 of 65 BOEING SERVICE BULLETIN 717-55A0012 ALERTALERT ### Page 30 3) CONDITION 2.1 (ACTION 3): Do Repetitive Inspection of the Vertical Stabilizer Front Spar Cap at Station Zfs=52.267. (b) CONDITION 2.2: ANY CRACK FOUND. 1) CONDITION 2.2 (ACTION 1): Do PART 5: VERTICAL STABILIZER LEADING EDGE SKIN REPAIR. 2) CONDITION 2.2 (ACTION 2): Contact Boeing to get instructions for the repair for this service bulletin, and do the work instructed by Boeing. (2) OPTION 2: Do PART 3: VERTICAL STABILIZER SPAR CAP - EDDY CURRENT, HIGH FREQUENCY (ETHF) INSPECTION for any crack. (a) CONDITION 2.1: NO CRACK FOUND. 1) CONDITION 2.1 (ACTION 1): Do PART 5: VERTICAL STABILIZER LEADING EDGE SKIN REPAIR. 2) CONDITION 2.1 (ACTION 2): Do Repetitive Detailed Inspections of the Fixed Leading Edge Skin at Station Zfs=52.267. 3) CONDITION 2.1 (ACTION 3): Do Repetitive Inspection of the Vertical Stabilizer Front Spar Cap at Station Zfs=52.267. (b) CONDITION 2.2: ANY CRACK FOUND. 1) CONDITION 2.2 (ACTION 1): Do PART 5: VERTICAL STABILIZER LEADING EDGE SKIN REPAIR. 2) CONDITION 2.2 (ACTION 2): Contact The Boeing Company for repair instructions and do the repair. 2. Put the airplane back to a serviceable condition. 3. Repetitive Detailed Inspections of the Fixed Leading Edge Skin at Station Zfs=52.267: a. RC - Do PART 4: VERTICAL STABILIZER SPAR CAP - DETAILED INSPECTION (FASTENERS NOT REMOVED) for any loose fasteners and missing fasteners. (1) CONDITION 3 or CONDITION 4: NO LOOSE AND NO MISSING FASTENERS ON AIRPLANES WHICH COMPLETED OPTION 1 OR OPTION 2 INSPECTION. (a) Put airplane back to a serviceable condition. (b) REPEAT PART 4: VERTICAL STABILIZER LEADING EDGE SKIN - DETAILED INSPECTION (FASTENERS NOT REMOVED) for any loose fasteners and missing fasteners. (2) CONDITION 5 or CONDITION 6: ANY LOOSE OR MISSING FASTENERS FOUND ON AIRPLANES WHICH COMPLETED OPTION 1 OR OPTION 2 INSPECTION. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 12, 2015 717-55A0012Revision 1: April 11, 2018 30 of 65 BOEING SERVICE BULLETIN 717-55A0012 ALERTALERT ### Page 31 (a) CONDITION 5 or CONDITION 6 (ACTION 1): Do PART 5: VERTICAL STABILIZER LEADING EDGE SKIN REPAIR. (b) CONDITION 5 or CONDITION 6 (ACTION 2): REPEAT PART 4: VERTICAL STABILIZER LEADING EDGE SKIN - DETAILED INSPECTION (FASTENERS NOT REMOVED) for any loose fasteners and missing fasteners. 4. Repetitive Inspection of the Vertical Stabilizer Front Spar Cap at Station Zfs=52.267 a. RC - OPTION 1: Do PART 2: VERTICAL STABILIZER SPAR CAP - EDDY CURRENT, HIGH FREQUENCY (ETHF) and RADIOGRAPHIC TESTING (RT) INSPECTION for any crack. (1) CONDITION 7: NO CRACK FOUND ON AIRPLANES WHICH COMPLETED OPTION 1 INSPECTION. (a) Put airplane back to a serviceable condition. (b) Repeat OPTION 1 or Do OPTION 2 inspection for any crack: (2) CONDITION 9: ANY CRACK FOUND ON AIRPLANES WHICH COMPLETE OPTION 1 OR OPTION 2 INSPECTION. (a) Contact Boeing to get instructions for the repair for this service bulletin, and do the work instructed by Boeing. b. RC - OPTION 2: Do PART 3: VERTICAL STABILIZER SPAR CAP- EDDY CURRENT, HIGH FREQUENCY (ETHF) INSPECTION for any crack. (1) CONDITION 8: NO CRACK FOUND ON AIRPLANES WHICH COMPLETED OPTION 2 INSPECTION. (a) Put airplane back to a serviceable condition. (b) Do OPTION 1 or Repeat OPTION 2 inspection for any crack. (2) CONDITION 9: ANY CRACK FOUND ON AIRPLANES WHICH COMPLETED OPTION 1 OR OPTION 2 INSPECTION. (a) Contact The Boeing Company for repair instructions and do the repair. 5. Put airplane back to a serviceable condition. PART 1: VERTICAL STABILIZER LEADING EDGE SKIN – DETAILED INSPECTIONS for any distress (FASTENERS REMOVED) 1. Do a detailed inspection of the left and right side vertical stabilizer leading edge structure at the splice at Station Zfs=52.267 in accordance with FIGURE 1 and FIGURE 6. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 12, 2015 717-55A0012Revision 1: April 11, 2018 31 of 65 BOEING SERVICE BULLETIN 717-55A0012 ALERTALERT ### Page 32 PART 2: VERTICAL STABILIZER SPAR CAP – EDDY CURRENT, HIGH FREQUENCY (ETHF) and RADIOGRAPHIC TESTING (RT) INSPECTION for any crack 1. Do an open hole Eddy Current, High Frequency (ETHF) inspection of the left and right side vertical stabilizer front spar cap forward flanges for any crack in accordance with FIGURE 2 and FIGURE 7. 2. Do a Radiographic Testing (RT) inspection of the left and right side vertical stabilizer front spar cap aft flanges at Station Zfs=52.267 for any crack in accordance with FIGURE 3 and FIGURE 8. PART 3: VERTICAL STABILIZER SPAR CAP – EDDY CURRENT, HIGH FREQUENCY (ETHF) INSPECTION for any crack 1. Do an open hole ETHF inspection of the left and right side vertical stabilizer front spar cap forward flanges for any crack in accordance with FIGURE 2 and FIGURE 7. 2. Do an ETHF surface inspection of the side skin at the left and right side vertical stabilizer front spar cap aft flanges within the specified dimensions in accordance with FIGURE 4 and FIGURE 9. PART 4: VERTICAL STABILIZER LEADING EDGE SKIN - DETAILED INSPECTION (FASTENERS NOT REMOVED) for any loose and missing fasteners 1. Do a detailed inspection of the vertical stabilizer leading edge at the splice at Station Zfs=52.267 (fasteners not removed) for any loose or missing fasteners in accordance with FIGURE 5 and FIGURE 10. NOTE: The inspection area is two rows of fasteners above the splice and two rows of fasteners below the splice at Station Zfs=52.267. PART 5: VERTICAL STABILIZER - LEADING EDGE SKIN REPAIR 1. Do leading edge repair in accordance with Service Repair Drawing SG95550001. NOTE: As an option to the repair, replace 9911813-503 vertical stabilizer leading edge splice band with new 9911813-503 vertical stabilizer leading edge splice band in accordance with drawing 5930609. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 12, 2015 717-55A0012Revision 1: April 11, 2018 32 of 65 BOEING SERVICE BULLETIN 717-55A0012 ALERTALERT ### Page 33 (OCR) BOEING SERVICE BULLETIN 717-55A0012 ALERT ALERT VERTICAL STABILIZER LEADING FRONT SPAR CAP EDGE PANEL Zfs = 52.267 - - o SIDE SKIN DORSAL FIN LOWER ASSEMBLY VIEW LOOKING INBOARD FROM OUTSIDE VERTICAL STABILIZER A-A 2396691 FIGURE 1: LEFT SIDE VERTICAL STABILIZER LEADING EDGE STRUCTURE AT THE SPLICE AT STATION ZFS-52.267 DETAILED INSPECTION (SHEET 1 OF 2) Original Issue: June 12, 2015 Revision 1 April 11, 2018 Export Controlled ECCN: 9E991 - BOEING 717-55A0012 PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 33 of 65 ### Page 34 The step numbers shown below agree with the numbers shown in the circle symbols in the figure. More DataQTYIdentificationNameTaskStep (a)(b)--SkinInspect1 (b)(c)(d)3-FastenersRemove/keep2 -HolesInspect 3FastenersInstall/kept (b)(c)(d)4-FastenersRemove/keep3 -HolesInspect 4FastenersInstall/kept (b)(c)(d)4-FastenersRemove/keep4 -HolesInspect 4FastenersInstall/kept (b)(c)(d)3-FastenersRemove/keep5 -HolesInspect 3FastenersInstall/kept (a) Do a detailed inspection for any "distress" in the vertical stabilizer leading edge structure at the splice at Station Zfs=52.267. (b) "Distress" is defined as deformed holes, elongated holes, oversized holes or any crack in the leading edge skin and splice. (c) Remove and keep one row of fasteners. To prevent damage to the tail plane, only remove one row of fasteners at a time. (d) Do a detailed inspection for distress in each fastener hole location. FIGURE 1: LEFT SIDE VERTICAL STABILIZER LEADING EDGE STRUCTURE AT THE SPLICE AT STATION ZFS=52.267 DETAILED INSPECTION (SHEET 2 OF 2) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 12, 2015 717-55A0012Revision 1 April 11, 2018 34 of 65 BOEING SERVICE BULLETIN 717-55A0012 ALERTALERT ### Page 35 (OCR) BOEING SERVICE BULLETIN 717-55A0012 ALERT ALERT LEADING VERTICAL STABILIZER EDGE FRONT SPAR CAP PANEL 12.75 12.25 _ SIDE SKIN Zts = 52.267 - CRACK (TYPICAL) 2.1 DORSAL FIN LOWER ASSEMBLY VIEW LOOKING INBOARD FROM OUTSIDE VERTICAL STABILIZER A-A HIGH FREQUENCY EDDY CURRENT INSPECTION OF SPAR CAP FORWARD FLANGE AT STATION Zfs = 52.267 FIGURE 2: LEFT SIDE VERTICAL STABILIZER FRONT SPAR CAP FORWARD FLANGE OPEN HOLE EDDY CURRENT, HIGH FREQUENCY (ETHF) INSPECTION (SHEET 1 OF 2) Original Issue: June 12, 2015 Revision 1 April 11, 2018 Export Controlled ECCN: 9E991 - BOEING 717-55A0012 PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 35 of 65 ### Page 36 The step numbers shown below agree with the numbers shown in the circle symbols in the figure. More DataQTYIdentificationNameTaskStep (a)(b)(c)--FastenersRemove/keep1 HoleInspect FastenersInstall/kept (a) Remove and keep fasteners common to the left side leading edge panel, the dorsal fin lower assembly and vertical stabilizer front spar cap forward flanges, above and below the leading edge skin splice at Station Zfs=52.267. (b) Do an open hole ETHF inspection of the left side vertical stabilizer front spar cap forward flanges at the fastener holes above and below the leading edge skin splice at Station Zfs=52.267 within the specified dimensions. Scan the circumference of the holes in accordance with the Non-destructive Testing Standard Practice Manual NDTSPM 06-10-01.003 (ETHF - Procedure 3). (c) Scoring of the fastener hole bore caused by the removal of fasteners may cause crack-like indications. Removal of nut plate may be necessary for proper clean up of the hole. Refer to NDTSPM 06-10-01.003 "Access" and "Preparation and Cleaning" for more information. The nut plate may also interfere with the probe scan with some open hole eddy current probe designs. FIGURE 2: LEFT SIDE VERTICAL STABILIZER FRONT SPAR CAP FORWARD FLANGE OPEN HOLE EDDY CURRENT, HIGH FREQUENCY (ETHF) INSPECTION (SHEET 2 OF 2) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 12, 2015 717-55A0012Revision 1 April 11, 2018 36 of 65 BOEING SERVICE BULLETIN 717-55A0012 ALERTALERT ### Page 37 (OCR) BOEING SERVICE BULLETIN 717-55A0012 ALERT ALERT LEADING EDGE VERTICAL STABILIZER PANEL FRONT SPAR CAP 3 TO 4 INCHES * OVERLAP FILM PLACEMENT 1.5 INCHES ‡0.25 SIDE SKIN (4 PLACES) B FILM PLACEMENT EXPOSURE 1 (SHOWN 10.25 TRANSPARENT) 9.75 12.75 12.25 FILM PLACEMENT EXPOSURE 2 (SHOWN 5.25 4.75 TRANSPARENT) Zts = 52.267- FILM PLACEMENT EXPOSURE 3 SHOWN 5.25 TRANSPARENT) 4.75 FILM PLACEMENT EXPOSURE 4 12.75 10.25 (SHOWN 12.25 9.75 TRANSPARENT FILM PLACEMENT EXPOSURE 5 (SHOWN TRANSPAREN!) • INDICATES THE TARGET LOCATION OF THE X-RAY TUBE HEAD PORT AT THE DORSAL FIN OPPOSITE SIDE OF THE VERTICAL LOWER ASSEMBLY STABILIZER TO THE CENTER OF THE AREA BEING INSPECTED VIEW LOOKING INBOARD FROM OUTSIDE VERTICAL STABILIZER * TARGET SHOULD BE AFT OF AFT A-A FLANGE AND SLIGHTLY OBLIQUE, SO THE FIRST FLANGE IS NOT SUPERIMPOSED OVER THE FLANGE RADIOGRAPHIC TESTING AT AFT FLANGE AT BEING INSPECTED 2396698 STATION Zfs = 52.267 FIGURE 3: LEFT SIDE VERTICAL STABILIZER FRONT SPAR CAP AFT FLANGES AT STATIONZFS-52.267 RADIOGRAPHIC TESTING (RT) INSPECTION (SHEET 1 OF 3) Original Issue: June 12, 2015 Revision 1 April 11, 2018 Export Controlled ECCN: 9E991 - BOEING 717-55A0012 PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 37 of 65 ### Page 38 The step numbers shown below agree with the numbers shown in the circle symbols in the figure. More DataQTYIdentificationNameTaskStep (a)(b)(c)(d)(e)(f)(g)--SkinInspect1 (a) Do a Radiographic Testing (RT) surface inspection of the vertical stabilizer front spar cap aft flange at station Zfs=52.267 for any crack. (b) Prepare exposure radiographic identification tag with the data as follows, using operator's shop practice: – Service Bulletin number – Exposure number and left side – Aircraft I.D. – Date (c) Attach the identification tag of each of the 5 exposures to the respective film pack using operator's shop practice. (d) Use masking tape to attach film to inspection element for the 5 exposures. (e) Expose film in accordance with x-ray parameters in exposure table below. (f) Any indication is considered a crack which exhibits the same relative phase angle and an amplitude of 50 percent or greater than the indication obtained from the calibration notch in the reference standard. (g) Any crack indications found during RT inspection shall be verified. Refer to NDTSPM 02-00-07 for appli- cable Crack/Defect Evaluation/Verification section(s). FIGURE 3: LEFT SIDE VERTICAL STABILIZER FRONT SPAR CAP AFT FLANGES AT STATION ZFS=52.267 RADIOGRAPHIC TESTING (RT) INSPECTION (SHEET 2 OF 3) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 12, 2015 717-55A0012Revision 1 April 11, 2018 38 of 65 BOEING SERVICE BULLETIN 717-55A0012 ALERTALERT ### Page 39 Exposure Table REMARKSFILMDIM "A"mas (a)kVEXPOSURE NUMBER SIZE (Inch)QTYASTM TYPE 5 X 721 (b)36+/-0.5600801 5 X 721 and 2 (c)36+/-0.5600802 5 X 721 and 2 (c)36+/-0.5600803 5 X 721 (b)36+/-0.5600804 5 X 721 (b)36+/-0.5600805 (a) Adjust mas to get a 1.7 to 3.5 H & D density in the area of interest. (b) Kodak M or equivalent type with similar speed. (c) Kodak M and AA or equivalent type with similar speed (double load film pack). FIGURE 3: LEFT SIDE VERTICAL STABILIZER FRONT SPAR CAP AFT FLANGES AT STATION ZFS=52.267 RADIOGRAPHIC TESTING (RT) INSPECTION (SHEET 3 OF 3) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 12, 2015 717-55A0012Revision 1 April 11, 2018 39 of 65 BOEING SERVICE BULLETIN 717-55A0012 ALERTALERT ### Page 40 (OCR) BOEING SERVICE BULLETIN 717-55A0012 ALERT ALERT VERTICAL STABILIZER FRONT SPAR CAP LEADING EDGE PANEL 12.75 12.25 SIDE SKIN Zfs = 52.267 - CRACK (TYPICAL) 12.75 12.25 DORSAL FIN LOWER ASSEMBLY VIEW LOOKING INBOARD FROM OUTSIDE VERTICAL STABILIZER A-A HIGH FREQUENCY EDDY CURRENT INSPECTION OF 2396709 SPAR CAP AFT FLANGE AT STATION Zfs = 52.267 FIGURE 4: LEFT SIDE VERTICAL STABILIZER SIDE SKIN FRONT SPAR CAP AFT FLANGES EDDY CURRENT, HIGH FREQUENCY (ETHF) INSPECTION (SHEET 1 OF 2) Original Issue: June 12, 2015 Revision 1 April 11, 2018 PROPRIETARY - Copyright © Unpublished Export Controlled ECCN: 9E991 - BOEING 717-55A0012 Work - See page 1 for details. 40 of 65 ### Page 41 The step numbers shown below agree with the numbers shown in the circle symbols in the figure. More DataQTYIdentificationNameTaskStep (a)--SkinInspect1 (a) Do an ETHF surface inspection of the side skin at the left side vertical stabilizer front spar cap aft flanges within the specified dimensions. Scan around the fasteners for any crack in the forward and aft direction. Scan around the fasteners in accordance with the Non-destructive Testing Standard Practice Manual NDTSPM 06-10-01.001 (ETHF - Procedure 1). Use Calibration Method "P" and Scan Method "47". FIGURE 4: LEFT SIDE VERTICAL STABILIZER SIDE SKIN FRONT SPAR CAP AFT FLANGES EDDY CURRENT, HIGH FREQUENCY (ETHF) INSPECTION (SHEET 2 OF 2) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 12, 2015 717-55A0012Revision 1 April 11, 2018 41 of 65 BOEING SERVICE BULLETIN 717-55A0012 ALERTALERT ### Page 42 (OCR) BOEING SERVICE BULLETIN 717-55A0012 ALERT ALERT VERTICAL STABILIZER LEADING FRONT SPAR CAP EDGE PANEL 1 14 LOCATIONS + + Zfs = 52.267 - _ SIDE SKIN DORSAL FIN LOWER ASSEMBLY VIEW LOOKING INBOARD FROM OUTSIDE VERTICAL STABILIZER A-A 2398129 FIGURE 5: LEFT SIDE VERTICAL STABILIZER LEADING EDGE AT THE SPLICE AT STATION ZFS=52.267 (FASTENERS NOT REMOVED) DETAILED INSPECTION (SHEET 1 OF 2) Original Issue: June 12, 2015 Revision 1 April 11, 2018 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished 717-55A0012 Work - See page 1 for details. 42 of 65 ### Page 43 The step numbers shown below agree with the numbers shown in the circle symbols in the figure. More DataQTYIdentificationNameTaskStep (a)--SkinInspect1 (a) Do a detailed inspection of the vertical stabilizer leading edge at the splice at Station Zfs=52.267 (fasteners not removed) for any loose or missing fasteners. FIGURE 5: LEFT SIDE VERTICAL STABILIZER LEADING EDGE AT THE SPLICE AT STATION ZFS=52.267 (FASTENERS NOT REMOVED) DETAILED INSPECTION (SHEET 2 OF 2) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 12, 2015 717-55A0012Revision 1 April 11, 2018 43 of 65 BOEING SERVICE BULLETIN 717-55A0012 ALERTALERT ### Page 44 (OCR) BOEING SERVICE BULLETIN 717-55A0012 ALERT ALERT VERTICAL STABILIZER FRONT SPAR CAP LEADING EDGE PANEL Zfs = 52.267 SIDE SKIN DORSAL FIN LOWER ASSEMBLY VIEW LOOKING INBOARD FROM OUTSIDE VERTICAL STABILIZER A-A 2398155 FIGURE 6: RIGHT SIDE VERTICAL STABILIZER LEADING EDGE STRUCTURE AT THE SPLICE AT STATION ZFS=52.267 DETAILED INSPECTION (SHEET 1 OF 2) Original Issue: June 12, 2015 Revision 1 April 11, 2018 PROPRIETARY - Copyright © Unpublished Export Controlled ECCN: 9E991 - BOEING 717-55A0012 Work - See page 1 for details. 44 of 65 ### Page 45 The step numbers shown below agree with the numbers shown in the circle symbols in the figure. More DataQTYIdentificationNameTaskStep (a)(b)--SkinInspect1 (b)(c)(d)3-FastenersRemove/keep2 -HolesInspect 3FastenersInstall/kept (b)(c)(d)4-FastenersRemove/keep3 -HolesInspect 4FastenersInstall/kept (b)(c)(d)4-FastenersRemove/keep4 -HolesInspect 4FastenersInstall/kept (b)(c)(d)3-FastenersRemove/keep5 -HolesInspect 3FastenersInstall/kept (a) Do a detailed inspection for any "distress" in the vertical stabilizer leading edge structure at the splice at Station Zfs=52.267. (b) "Distress" is defined as deformed holes, elongated holes, oversized holes or any crack in the leading edge skin and splice. (c) Remove and keep one row of fasteners. To prevent damage to the tail plane, only remove one row of fasteners at a time. (d) Do a detailed inspection for distress in each fastener hole location. FIGURE 6: RIGHT SIDE VERTICAL STABILIZER LEADING EDGE STRUCTURE AT THE SPLICE AT STATION ZFS=52.267 DETAILED INSPECTION (SHEET 2 OF 2) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 12, 2015 717-55A0012Revision 1 April 11, 2018 45 of 65 BOEING SERVICE BULLETIN 717-55A0012 ALERTALERT ### Page 46 (OCR) BOEING SERVICE BULLETIN 717-55A0012 ALERT ALERT LEADING VERTICAL STABILIZER EDGE PANEL FRONT SPAR CAP 12.75 12.25 SIDE SKIN Zfs = 52.267 CRACK (TYPICAL) 12.75 12.25 DORSAL FIN LOWER ASSEMBLY VIEW LOOKING INBOARD FROM OUTSIDE VERTICAL STABILIZER A-A HIGH FREQUENCY EDDY CURRENT INSPECTION OF 2398159 SPAR CAP FORWARD FLANGE AT STATION Zfs = 52.267 FIGURE 7: RIGHT SIDE VERTICAL STABILIZER FRONT SPAR CAP FORWARD FLANGE OPEN HOLE EDDY CURRENT, HIGH FREQUENCY (ETHF) INSPECTION (SHEET 1 OF 2) Original Issue: June 12, 2015 Revision 1 April 11, 2018 PROPRIETARY - Copyright © Unpublished Export Controlled ECCN: 9E991 - BOEING 717-55A0012 Work - See page 1 for details. 46 of 65 ### Page 47 The step numbers shown below agree with the numbers shown in the circle symbols in the figure. More DataQTYIdentificationNameTaskStep (a)(b)(c)--FastenersRemove/Keep1 HolesInspect FastenersInstall/kept (a) Remove and keep fasteners common to the right side leading edge panel, the dorsal fin lower assembly and vertical stabilizer front spar cap forward flanges, above and below the leading edge skin splice at Station Zfs=52.267. (b) Do an open hole ETHF inspection of the right side vertical stabilizer front spar cap forward flanges at the fastener holes above and below the leading edge skin splice at Station Zfs=52.267 within the specified dimensions. Scan the circumference of the holes in accordance with the Non-destructive Testing Standard Practice Manual NDTSPM 06-10-01.003 (ETHF - Procedure 3). (c) Scoring of the fastener hole bore caused by the removal of fasteners may cause crack-like indications. Removal of nut plate may be necessary for proper clean up of the hole. Refer to NDTSPM 06-10-01.003 "Access" and "Preparation and Cleaning" for more information. The nut plate may also interfere with the probe scan with some open hole eddy current probe designs. FIGURE 7: RIGHT SIDE VERTICAL STABILIZER FRONT SPAR CAP FORWARD FLANGE OPEN HOLE EDDY CURRENT, HIGH FREQUENCY (ETHF) INSPECTION (SHEET 2 OF 2) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 12, 2015 717-55A0012Revision 1 April 11, 2018 47 of 65 BOEING SERVICE BULLETIN 717-55A0012 ALERTALERT ### Page 48 (OCR) BOEING SERVICE BULLETIN 717-55A0012 ALERT ALERT LEADING VERTICAL STABILIZER EDGE FRONT SPAR CAP PANEL 3 TO 4 INCHES * OVERLAP FILM PLACEMENT SIDE SKIN 1.5 INCHES ‡0.25 (4 PLACES) FILM PLACEMENT- EXPOSURE 1 SHOWN +L TRANSPARENT) 12.75 FILM PLACEMENT 12.25 EXPOSURE 2 (SHOWN TRANSPARENT) 5.25 .75 FILM PLACEMENT -Zfs = 52.267 EXPOSURE 3 SHOWN TRANSPARENT) FILM PLACEMENT TRANSPARENT) EXPOSURE 4 (SHOWN 10,25 12.75 12.25 FILM PLACEMENT EXPOSURE 5 (SHOWN TRANSPARENT) • INDICATES THE TARGET LOCATION OF THE X-RAY TUBE HEAD PORT AT THE OPPOSITE SIDE OF THE VERTICAL DORSAL FIN AREA BEING INSPECTED STABILIZER TO THE CENTER OF THE LOWER ASSEMBLY VIEW LOOKING INBOARD FROM OUTSIDE * TARGET SHOULD BE AFT OF AFT VERTICAL STABILIZER FLANGE AND SLIGHTLY OBLIQUE, SO THE FIRST FLANGE IS NOT A-A SUPERIMPOSED OVER THE FLANGE BEING INSPECTED RADIOGRAPHIC TESTING AT AFT FLANGE AT 2398157 STATION Zfs = 52.267 FIGURE 8: RIGHT SIDE VERTICAL STABILIZER FRONT SPAR CAP AFT FLANGES AT STATION ZFS-52.267 RADIOGRAPHIC TESTING (RT) INSPECTION (SHEET 1 OF 3) Original Issue: June 12, 2015 Revision 1 April 11, 2018 PROPRIETARY - Copyright © Unpublished Export Controlled ECCN: 9E991 - BOEING 717-55A0012 Work - See page 1 for details. 48 of 65 ### Page 49 The step numbers shown below agree with the numbers shown in the circle symbols in the figure. More DataQTYIdentificationNameTaskStep (a)(b)(c)(d)(e)(f)(g)--SkinInspect1 (a) Do a Radiographic Testing (RT) surface inspection of the vertical stabilizer front spar cap aft flange at station Zfs=52.267 for any crack. (b) Prepare exposure radiographic identification tag with the data as follows, using operator's shop practice: – Service Bulletin number – Exposure number and right side – Aircraft I.D. – Date (c) Attach the identification tag of each of the 5 exposures to the respective film pack using operator's shop practice. (d) Use masking tape to attach film to inspection element for the 5 exposures. (e) Expose film in accordance with x-ray parameters in exposure table below. (f) Any indication is considered a crack which exhibits the same relative phase angle and an amplitude of 50 percent or greater than the indication obtained from the calibration notch in the reference standard. (g) Any crack indications found during RT inspection shall be verified. Refer to NDTSPM 02-00-07 for appli- cable Crack/Defect Evaluation/Verification section(s). FIGURE 8: RIGHT SIDE VERTICAL STABILIZER FRONT SPAR CAP AFT FLANGES AT STATION ZFS=52.267 RADIOGRAPHIC TESTING (RT) INSPECTION (SHEET 2 OF 3) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 12, 2015 717-55A0012Revision 1 April 11, 2018 49 of 65 BOEING SERVICE BULLETIN 717-55A0012 ALERTALERT ### Page 50 Exposure Table REMARKSFILMDIM "A"mas (a)kVEXPOSURE NUMBER SIZE (Inch)QTYASTM TYPE 5 X 721 (b)36+/-0.5600801 5 X 721 and 2 (c)36+/-0.5600802 5 X 721 and 2 (c)36+/-0.5600803 5 X 721 (b)36+/-0.5600804 5 X 721 (b)36+/-0.5600805 (a) Adjust mas to get a 1.7 to 3.5 H & D density in the area of interest. (b) Kodak M or equivalent type with similar speed. (c) Kodak M and AA or equivalent type with similar speed (double load film pack). FIGURE 8: RIGHT SIDE VERTICAL STABILIZER FRONT SPAR CAP AFT FLANGES AT STATION ZFS=52.267 RADIOGRAPHIC TESTING (RT) INSPECTION (SHEET 3 OF 3) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 12, 2015 717-55A0012Revision 1 April 11, 2018 50 of 65 BOEING SERVICE BULLETIN 717-55A0012 ALERTALERT ### Page 51 (OCR) BOEING SERVICE BULLETIN 717-55A0012 ALERT ALERT LEADING VERTICAL STABILIZER FRONT SPAR CAP PANEL EDGE 12.75 12.25 SIDE SKIN CRACK + _+. • Zfs = 52.267 (TYPICAL) 12.75 12.25 + i DORSAL FIN LOWER ASSEMBLY VIEW LOOKING INBOARD FROM OUTSIDE VERTICAL STABILIZER A-A HIGH FREQUENCY EDDY CURRENT INSPECTION OF SPAR CAP AFT FLANGE AT STATION Zfs = 52.267 FIGURE 9: RIGHT SIDE VERTICAL STABILIZER SIDE SKIN FRONT SPAR CAP AFT FLANGES EDDY CURRENT, HIGH FREQUENCY (ETHF) INSPECTION (SHEET 1 OF 2) Original Issue: June 12, 2015 Revision 1 April 11, 2018 Export Controlled ECCN: 9E991 - BOEING 717-55A0012 PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 51 of 65 ### Page 52 The step numbers shown below agree with the numbers shown in the circle symbols in the figure. More DataQTYIdentificationNameTaskStep (a)--SkinInspect1 (a) Do an ETHF surface inspection of the side skin at the right side vertical stabilizer front spar cap aft flanges within the specified dimensions. Scan around the fasteners for any crack in the forward and aft direction. Scan around the fasteners in accordance with the Non-destructive Testing Standard Practice Manual NDTSPM 06-10-01.001 (ETHF - Procedure 1). Use Calibration Method "P" and Scan Method "47". FIGURE 9: RIGHT SIDE VERTICAL STABILIZER SIDE SKIN FRONT SPAR CAP AFT FLANGES EDDY CURRENT, HIGH FREQUENCY (ETHF) INSPECTION (SHEET 2 OF 2) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 12, 2015 717-55A0012Revision 1 April 11, 2018 52 of 65 BOEING SERVICE BULLETIN 717-55A0012 ALERTALERT ### Page 53 (OCR) BOEING SERVICE BULLETIN 717-55A0012 ALERT ALERT VERTICAL STABILIZER FRONT SPAR CAP LEADING EDGE PANEL 14 LOCATIONS (1 - - Zfs = 52.267 SIDE SKIN DORSAL FIN LOWER ASSEMBLY VIEW LOOKING INBOARD FROM OUTSIDE VERTICAL STABILIZER A-A 2398160 FIGURE 10: RIGHT SIDE VERTICAL STABILIZER LEADING EDGE AT THE SPLICE AT STATION ZFS-52.267 (FASTENERS NOT REMOVED) DETAILED INSPECTION (SHEET 1 OF 2) Original Issue: June 12, 2015 Revision 1 April 11, 2018 PROPRIETARY - Copyright © Unpublished Export Controlled ECCN: 9E991 - BOEING 717-55A0012 Work - See page 1 for details. 53 of 65 ### Page 54 The step numbers shown below agree with the numbers shown in the circle symbols in the figure. More DataQTYIdentificationNameTaskStep (a)--SkinInspect1 (a) Do a detailed inspection of the vertical stabilizer leading edge at the splice at Station Zfs=52.267 (fasteners not removed) for any loose or missing fasteners. FIGURE 10: RIGHT SIDE VERTICAL STABILIZER LEADING EDGE AT THE SPLICE AT STATION ZFS=52.267 (FASTENERS NOT REMOVED) DETAILED INSPECTION (SHEET 2 OF 2) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 12, 2015 717-55A0012Revision 1 April 11, 2018 54 of 65 BOEING SERVICE BULLETIN 717-55A0012 ALERTALERT ### Page 55 Logic diagrams are provided as an aid only. Information contained in Paragraph 1.E., Compliance is the primary source for compliance times. Information contained in Paragraph 3.B., Work Instructions is the primary source for tasks required for compliance. DescriptionTitle VERTICAL STABILIZER LEADING EDGE SKIN - DE- TAILED INSPECTIONS for any distress (FASTENERS REMOVED). PART 1 VERTICAL STABILIZER SPAR CAP - EDDY CUR- RENT, HIGH FREQUENCY (ETHF) and RADIOGRAPH- IC TESTING (RT) INSPECTION for any crack. PART 2 VERTICAL STABILIZER SPAR CAP - EDDY CUR- RENT, HIGH FREQUENCY (ETHF) INSPECTION for any crack. PART 3 VERTICAL STABILIZER LEADING EDGE SKIN RE- PAIR. PART 5 LEADING EDGE SKIN IS NOT DISTRESSED.CONDITION 1 NO CRACK FOUND.CONDITION 1.1 ANY CRACK FOUND.CONDITION 1.2 LEADING EDGE SKIN IS DISTRESSED.CONDITION 2 NO CRACK FOUND.CONDITION 2.1 ANY CRACK FOUND.CONDITION 2.2 APPENDIX A: LOGIC DIAGRAM FOR PARAGRAPH 1.E., COMPLIANCE TABLE 1: INITIAL DETAILED INSPECTION, EDDY CURRENT HIGH FREQUENCY (ETHF) OR RADIOGRAPHIC TESTING (RT) INSPECTION: FIXED LEADING EDGE SKIN AND FRONT SPAR CAP AT STATION ZFS=52.267 (SHEET 1 OF 2) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 12, 2015 717-55A0012Revision 1 April 11, 2018 55 of 65 BOEING SERVICE BULLETIN 717-55A0012 ALERTALERT ### Page 56 (OCR) BOEING SERVICE BULLETIN 717-55A0012 ALERT ALERT BEFORE 15,000 TOTAL FLIGHT CYCLES OR WITHIN 6,200 FLIGHT CYCLES AFTER THE EFFECTIVE DATE OF AD 2016-09-05, WHICHEVER OCCURS LATER DO PART 1 CONDITION 1 CONDITION 2 BEFORE FURTHER BEFORE FURTHER FLIGHT FLIGHT OPTION 1: DO OPTION 2: DO OPTION 1: DO OPTION 2: DO PART 2 PART 3 PART 2 PART 3 CONDITION 1.1 CONDITION 1.2 CONDITION 2.1 CONDITION 2.2 BEFORE FURTHER FLIGHT BEFORE FURTHER FLIGH BEFORE FURTHER ACTION 1: DO POST FLIGHT INITIAL INSPECTION. CONTACT BOEING FOR ACTION 1: DO REFER TO APPENDIX B, REPAIR INSTRUCTIONS PART 5 LOGIC DIAGRAM TABLE AND DO THE REPAIR 2 FOR COMPLIANCE ACTION 1: DO PART 5 INFORMATION ACTION 2: DO POST INITIAL INSPECTION ACTION 2: DO REFER TO APPENDIX B, ACTION 2 CONTACT REPETITIVE LOGIC DIAGRAM TABLE BOEING FOR INSPECTION, REFER 2 FOR COMPLIANCE REPAIR TO APPENDIX C, LOGIC INFORMATION INSTRUCTIONS AND DO THE DIAGRAM TABLE 3 FOR REPAIR COMPLIANCE INFORMATION ACTION 3: DO REPETITIVE INSPECTION, REFER TO APPENDIX C, LOGIC DIAGRAM TABLE 3 FOR COMPLIANCE INFORMATION 2404303 APPENDIX A: LOGIC DIAGRAM FOR PARAGRAPH 1.E., COMPLIANCE TABLE 1: INITIAL DETAILED INSPECTION, EDDY CURRENT HIGH FREQUENCY (ETHF) OR RADIOGRAPHIC TESTING (RT) INSPECTION: FIXED LEADING EDGE SKIN AND FRONT SPAR CAP AT STATION ZFS-52.267 (SHEET 2 OF 2) Original Issue: June 12, 2015 Revision 1 April 11, 2018 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished 717-55A0012 Work - See page 1 for details. 56 of 65 ### Page 57 Logic diagrams are provided as an aid only. Information contained in Paragraph 1.E., Compliance is the primary source for compliance times. Information contained in Paragraph 3.B., Work Instructions is the primary source for tasks required for compliance. DescriptionTitle VERTICAL STABILIZER LEADING EDGE SKIN - DE- TAILED INSPECTION (FASTENERS NOT REMOVED) for any loose and missing fasteners. PART 4 VERTICAL STABILIZER LEADING EDGE SKIN RE- PAIR. PART 5 NO LOOSE AND NO MISSING FASTENERS FOUND ON AIRPLANES WHICH COMPLETED OPTION 1 INSPECTIONS. CONDITION 3 NO LOOSE AND NO MISSING FASTENERS FOUND ON AIRPLANES WHICH COMPLETED OPTION 2 INSPECTIONS. CONDITION 4 ANY LOOSE OR MISSING FASTENERS FOUND ON AIRPLANES WHICH COMPLETED OPTION 1 INSPEC- TIONS. CONDITION 5 ANY LOOSE OR MISSING FASTENERS FOUND ON AIRPLANES WHICH COMPLETED OPTION 2 INSPEC- TIONS. CONDITION 6 More DataFlag Note Changing from one inspection option to another option is acceptable, provided the repeat interval requirement is first complied with, before changing options. (a) APPENDIX B: LOGIC DIAGRAM FOR PARAGRAPH 1.E., COMPLIANCE TABLE 2: POST INITIAL DETAILED INSPECTION - FIXED LEADING EDGE SKIN AT STATION ZFS=52.267 (SHEET 1 OF 2) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 12, 2015 717-55A0012Revision 1 April 11, 2018 57 of 65 BOEING SERVICE BULLETIN 717-55A0012 ALERTALERT ### Page 58 (OCR) BOEING SERVICE BULLETIN 717-55A0012 ALERT ALERT ALL AIRPLANES WHICH COMPLETED OPTION 1 WITHIN 4,400 FLIGHT CYCLES AFTER COMPLETING INSPECTION OPTION 1 ALL AIRPLANES WHICH COMPLETED OPTION 2 WITHIN 3,000 FLIGHT CYCLES AFTER COMPLETING INSPECTION OPTION 2 DO PART 4 CONDITION 3 CONDITION 5 CONDITION 6 CONDITION 4 BEFORE FURTHER FLIGHT WITHIN 4,400 WITHIN 3,000 FLIGHT CYCLES FLIGHT CYCLES AFTER AFTER DO PART 5 COMPLETING COMPLETING INSPECTION INSPECTION OPTION 1 OPTION 2 a) REPEAT PART 4 REPEAT PART 4 2404561 APPENDIX B: LOGIC DIAGRAM FOR PARAGRAPH 1.E., COMPLIANCE TABLE 2: POST INITIAL DETAILED INSPECTION - FIXED LEADING EDGE SKIN AT STATION ZFS=52.267 (SHEET 2 OF 2) Original Issue: June 12, 2015 Revision 1 April 11, 2018 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished 717-55A0012 Work - See page 1 for details. 58 of 65 ### Page 59 Logic diagrams are provided as an aid only. Information contained in Paragraph 1.E., Compliance is the primary source for compliance times. Information contained in Paragraph 3.B., Work Instructions is the primary source for tasks required for compliance. DescriptionTitle VERTICAL STABILIZER SPAR CAP - EDDY CUR- RENT, HIGH FREQUENCY (ETHF) and RADIOGRAPH- IC TESTING (RT) INSPECTION for any crack. PART 2 VERTICAL STABILIZER SPAR CAP - EDDY CUR- RENT, HIGH FREQUENCY (ETHF) INSPECTION for any crack. PART 3 NO CRACK FOUND ON AIRPLANES WHICH COM- PLETED OPTION 1 INSPECTION. CONDITION 7 NO CRACK FOUND ON AIRPLANES WHICH COM- PLETED OPTION 2 INSPECTION. CONDITION 8 ANY CRACK FOUND ON AIRPLANES WHICH COM- PLETED OPTION 1 OR OPTION 2 INSPECTION. CONDITION 9 More DataFlag Note Changing from one inspection option to another option is acceptable, provided the repeat interval requirement is first complied with, before changing options. (a) APPENDIX C: LOGIC DIAGRAM FOR PARAGRAPH 1.E., COMPLIANCE TABLE 3: REPETITIVE EDDY CURRENT HIGH FREQUENCY (ETHF) OR RADIOGRAPHIC TESTING (RT) INSPECTION - FRONT SPAR CAP AT STATION ZFS=52.267 (SHEET 1 OF 2) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 12, 2015 717-55A0012Revision 1 April 11, 2018 59 of 65 BOEING SERVICE BULLETIN 717-55A0012 ALERTALERT ### Page 60 (OCR) BOEING SERVICE BULLETIN 717-55A0012 ALERT ALERT ALL AIRPLANES WHICH COMPLETED OPTION 1 WITHIN 4,400 FLIGHT CYCLES AFTER COMPLETING INSPECTION OPTION 1 ALL AIRPLANES WHICH COMPLETED OPTION 2 WITHIN 3,000 FLIGHT CYCLES AFTER COMPLETING INSPECTION OPTION 2 OPTION 1: OPTION 2: DO PART 2 DO PART 3 CONDITION 7 CONDITION 9 CONDITION 8 WITHIN 4,400 WITHIN 3,000 FLIGHT CYCLES FLIGHT CYCLES AFTER BEFORE AFTER COMPLETING FURTHER FLIGHT COMPLETING INSPECTION INSPECTION OPTION 1 OPTION 2 (a) CONTACT THE DO OPTION 1 BOEING COMPANY DO OPTION 1 OR OPTION 2 FOR REPAIR OR OPTION 2 INSTRUCTIONS AND DO THE REPAIR 2404562 APPENDIX C: LOGIC DIAGRAM FOR PARAGRAPH 1.E., COMPLIANCE TABLE 3: REPETITIVE EDDY CURRENT HIGH FREQUENCY (ETHF) OR RADIOGRAPHIC TESTING (RT) INSPECTION - FRONT SPAR CAP AT STATION ZFS=52.267 (SHEET 2 OF 2) Original Issue: June 12, 2015 Revision 1 April 11, 2018 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished 717-55A0012 Work - See page 1 for details. 60 of 65 The text continues at https://openairdocs.org/service-documents/boeing/717-55a0012/file/03a075d7cdd0.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.