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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Unpublished Work.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
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.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
Table of Contents
Revision Transmittal Sheet5
Summary7
1. PLANNING INFORMATION11
A. Effectivity11
1. Airplanes11
2. Spares Affected11
B. Concurrent Requirements12
C. Reason12
D. Description12
E. Compliance13
F. Approval20
G. Manpower21
H. Weight and Balance Changes22
I. Electrical Load Data22
J. References22
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 Affected23
L. Interchangeability and Intermixability of Parts23
M. Software Accomplishment Summary23
2. MATERIAL INFORMATION25
A. Material - Price and Availability25
B. Industry Support Information25
C. Parts Necessary for Each Airplane25
1. Kits/Parts25
2. Parts and Materials Supplied by the Operator25
3. Parts Modified and Reidentified25
4. Parts Removed and Not Replaced25
D. Parts Necessary to Change Spares25
E. Special Tooling - Price and Availability25
F. Special Tooling Necessary to do this Service Bulletin25
3. ACCOMPLISHMENT INSTRUCTIONS27
A. GENERAL INFORMATION27
B. WORK INSTRUCTIONS29
FIGURE 1: LEFT SIDE VERTICAL STABILIZER LEADING EDGE STRUCTURE AT THE SPLICE AT
STATION ZFS=52.267 DETAILED INSPECTION33
FIGURE 2: LEFT SIDE VERTICAL STABILIZER FRONT SPAR CAP FORWARD FLANGE OPEN HOLE
EDDY CURRENT, HIGH FREQUENCY (ETHF) INSPECTION35
FIGURE 3: LEFT SIDE VERTICAL STABILIZER FRONT SPAR CAP AFT FLANGES AT STATION
ZFS=52.267 RADIOGRAPHIC TESTING (RT) INSPECTION37
FIGURE 4: LEFT SIDE VERTICAL STABILIZER SIDE SKIN FRONT SPAR CAP AFT FLANGES EDDY
CURRENT, HIGH FREQUENCY (ETHF) INSPECTION40
FIGURE 5: LEFT SIDE VERTICAL STABILIZER LEADING EDGE AT THE SPLICE AT STATION ZFS=52.267
(FASTENERS NOT REMOVED) DETAILED INSPECTION42
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
FIGURE 6: RIGHT SIDE VERTICAL STABILIZER LEADING EDGE STRUCTURE AT THE SPLICE AT
STATION ZFS=52.267 DETAILED INSPECTION44
FIGURE 7: RIGHT SIDE VERTICAL STABILIZER FRONT SPAR CAP FORWARD FLANGE OPEN HOLE
EDDY CURRENT, HIGH FREQUENCY (ETHF) INSPECTION46
FIGURE 8: RIGHT SIDE VERTICAL STABILIZER FRONT SPAR CAP AFT FLANGES AT STATION
ZFS=52.267 RADIOGRAPHIC TESTING (RT) INSPECTION48
FIGURE 9: RIGHT SIDE VERTICAL STABILIZER SIDE SKIN FRONT SPAR CAP AFT FLANGES EDDY
CURRENT, HIGH FREQUENCY (ETHF) INSPECTION51
FIGURE 10: RIGHT SIDE VERTICAL STABILIZER LEADING EDGE AT THE SPLICE AT STATION
ZFS=52.267 (FASTENERS NOT REMOVED) DETAILED INSPECTION53
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=52.26755
APPENDIX B: LOGIC DIAGRAM FOR PARAGRAPH 1.E., COMPLIANCE TABLE 2: POST INITIAL DETAILED
INSPECTION - FIXED LEADING EDGE SKIN AT STATION ZFS=52.26757
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=52.26759
APPENDIX D: PREPARATION OF INSPECTION61
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=52.26762
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
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
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
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
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 Airplane 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
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
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
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 Number 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
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