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Commercial Airplanes 717 Service Bulletin ALERT Number: 717-55A0012 Original Issue: June 12, 2015 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Unpublished Work.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 717-55A0012 1 of 55
4.0
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
Original Issue: June 12, 2015 717-55A0012 2 of 55 BOEING SERVICE BULLETIN 717-55A0012
ALERTALERT
BLANK PAGE
Table of Contents
Summary5
1. PLANNING INFORMATION9
A. Effectivity9
1. Airplanes9
2. Spares Affected9
B. Concurrent Requirements9
C. Reason10
D. Description10
E. Compliance10
F. Approval15
G. Manpower15
H. Weight and Balance Changes16
I. Electrical Load Data16
J. References17
1. Existing Data:17
2. Data Supplied with this Service Bulletin:17
3. Installation Drawings Used in the Preparation of this Service Bulletin:17
K. Publications Affected17
L. Interchangeability and Intermixability of Parts17
M. Software Accomplishment Summary17
2. MATERIAL INFORMATION19
A. Material - Price and Availability19
B. Industry Support Information19
C. Parts Necessary for Each Airplane19
1. Kits/Parts19
2. Parts and Materials Supplied by the Operator19
3. Parts Modified and Reidentified19
4. Parts Removed and Not Replaced19
D. Parts Necessary to Change Spares19
E. Special Tooling - Price and Availability19
F. Special Tooling Necessary to do this Service Bulletin19
3. ACCOMPLISHMENT INSTRUCTIONS21
A. GENERAL INFORMATION21
B. WORK INSTRUCTIONS22
FIGURE 1: LEFT SIDE VERTICAL STABILIZER LEADING EDGE STRUCTURE AT THE SPLICE AT
STATION ZFS=52.267 DETAILED INSPECTION27
FIGURE 2: LEFT SIDE VERTICAL STABILIZER FRONT SPAR CAP FORWARD FLANGE OPEN HOLE
EDDY CURRENT, HIGH FREQUENCY (ETHF) INSPECTION29
FIGURE 3: LEFT SIDE VERTICAL STABILIZER FRONT SPAR CAP AFT FLANGES AT STATION
ZFS=52.267 RADIOGRAPHIC TESTING (RT) INSPECTION31
FIGURE 4: LEFT SIDE VERTICAL STABILIZER SIDE SKIN FRONT SPAR CAP AFT FLANGES EDDY
CURRENT, HIGH FREQUENCY (ETHF) INSPECTION34
FIGURE 5: LEFT SIDE VERTICAL STABILIZER LEADING EDGE AT THE SPLICE AT STATION ZFS=52.267
(FASTENERS NOT REMOVED) DETAILED INSPECTION36
FIGURE 6: RIGHT SIDE VERTICAL STABILIZER LEADING EDGE STRUCTURE AT THE SPLICE AT
STATION ZFS=52.267 DETAILED INSPECTION38
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
Original Issue: June 12, 2015 717-55A0012 3 of 55 BOEING SERVICE BULLETIN 717-55A0012
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FIGURE 7: RIGHT SIDE VERTICAL STABILIZER FRONT SPAR CAP FORWARD FLANGE OPEN HOLE
EDDY CURRENT, HIGH FREQUENCY (ETHF) INSPECTION40
FIGURE 8: RIGHT SIDE VERTICAL STABILIZER FRONT SPAR CAP AFT FLANGES AT STATION
ZFS=52.267 RADIOGRAPHIC TESTING (RT) INSPECTION42
FIGURE 9: RIGHT SIDE VERTICAL STABILIZER SIDE SKIN FRONT SPAR CAP AFT FLANGES EDDY
CURRENT, HIGH FREQUENCY (ETHF) INSPECTION45
FIGURE 10: RIGHT SIDE VERTICAL STABILIZER LEADING EDGE AT THE SPLICE AT STATION
ZFS=52.267 (FASTENERS NOT REMOVED) DETAILED INSPECTION47
APPENDIX A: INITIAL DETAILED INSPECTION, EDDY CURRENT HIGH FREQUENCY (ETHF) OR RADIOGRAPHIC TESTING (RT) INSPECTION: FIXED LEADING EDGE SKIN AND FRONT
SPAR CAP AT STATION ZFS=52.26749
APPENDIX B: POST INITIAL DETAILED INSPECTION - FIXED LEADING EDGE SKIN AT STATION
ZFS=52.26751
APPENDIX C: REPETITIVE EDDY CURRENT HIGH FREQUENCY (ETHF) OR RADIOGRAPHIC TESTING
(RT) INSPECTION - FRONT SPAR CAP AT STATION ZFS=52.26753
APPENDIX D: PREPARATION OF INSPECTION55
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
Original Issue: June 12, 2015 717-55A0012 4 of 55 BOEING SERVICE BULLETIN 717-55A0012
ALERTALERT
Commercial Airplanes 717 Service Bulletin ALERT SummaryNumber: 717-55A0012Original Issue: June 12, 2015 ATA System: 5532 SUBJECT: STABILIZERS - Vertical Stabilizer - Fixed Leading Edge Skin and Front Spar Cap at Station Zfs=52.267 Inspection and Repair
THIS BULLETIN 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 SERVICE BULLETIN TO THE NEW OPERATOR. IF APPLICABLE SPARES HAVE BEEN SOLD, SEND THIS SERVICE BULLETIN 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 could adversely affect the structural integrity of the airplane.
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.
This table is provided to operators for planning purposes only. Refer to the applicable sections for more information.
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
Original Issue: June 12, 2015 717-55A0012 5 of 55
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 The Federal Aviation Administration (FAA) will possibly release an airworthiness directive related to this service bulletin. The airworthiness directive will make the compliance tasks and times given in this service bulletin mandatory.
Refer to Paragraph 1.E., Compliance.
INDUSTRY SUPPORT INFORMATION Boeing warranty remedies are not available for the inspection procedures given in this service bulletin.
MANPOWER Refer to Paragraph 1.G., Manpower.
MATERIAL INFORMATION None.
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
Original Issue: June 12, 2015 717-55A0012 6 of 55 BOEING SERVICE BULLETIN 717-55A0012
ALERTALERT
BOEING SERVICE BULLETIN 717-55A0012
ALERT ALERT
DO A DETAILED INSPECTION AND EDDY CURRENT HIGH -REQUENCY (ETHF) OR RADIOGRAPHIC TESTING (RT) INSPECTION OF THE • LEADING EDGE SKIN AND FRONT
SPAR CAP FOR ANY DIS OR CRACK AT STATION Zfs=52.267. IF ANY DIS ADING EDGE IS
FOUND, DO THE IR IN ACCORDANCE WITH SERVICE REPA 95550001.
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 Export Controlled ECCN: 9E991 - BOEING 717-55A0012 PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 7 of 55
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
Original Issue: June 12, 2015 717-55A0012 8 of 55 BOEING SERVICE BULLETIN 717-55A0012
ALERTALERT
BLANK PAGE
Commercial Airplanes 717 Service Bulletin ALERT Number: 717-55A0012 Original Issue: June 12, 2015 ATA System: 5532 SUBJECT: STABILIZERS - Vertical Stabilizer - Fixed Leading Edge Skin and Front Spar Cap at Station Zfs=52.267 Inspection and Repair
THIS BULLETIN 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 SERVICE BULLETIN TO THE NEW OPERATOR. IF APPLICABLE SPARES HAVE BEEN SOLD, SEND THIS SERVICE BULLETIN TO THE NEW OWNER.
1. PLANNING INFORMATION A. Effectivity
1. Airplanes
DESCRIPTIONCONFIGURATIONGROUP 717-200 airplanes. Line numbers 2 - 156.-1 Airplane Models:
717-200 GroupFuselage Number 15002 - 5099 15100 - 5156
2. Spares Affected None.
B. Concurrent Requirements None.
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Original Issue: June 12, 2015 717-55A0012 9 of 55
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.
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.
The work in this service bulletin is done in the maintenance zone(s) given below.
Affected Maintenance Zones ZoneModel 371717-200 E. Compliance The Federal Aviation Administration (FAA) will possibly release an airworthiness directive related to this service bulletin. The airworthiness directive will make the compliance tasks and times given in this service bulletin mandatory.
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.
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Original Issue: June 12, 2015 717-55A0012 10 of 55 BOEING SERVICE BULLETIN 717-55A0012
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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 Interval (Not to Exceed) Compliance Time (Whichever Occurs Later) ActionCondition -Within 6,200 flight cycles after the original issue date of this service bulletin.
Before 15,000 total flight cycles.
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.
-Refer to Table 2 for compliance information.
CONDITION 1.1 (ACTION 1):
Do Repetitive Detailed Inspections 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 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 repair.
CONDITION 1.2:
ANY CRACK FOUND during OPTION 1 or OPTION 2 spar cap inspection.
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Original Issue: June 12, 2015 717-55A0012 11 of 55 BOEING SERVICE BULLETIN 717-55A0012
ALERTALERT
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 Interval (Not to Exceed) Compliance Time (Whichever Occurs Later) ActionCondition -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 compliance information.
CONDITION 2.1 (ACTION 2):
Do Repetitive Detailed Inspections of the Fixed Leading Edge Skin at Station Zfs=52.267.
-Refer to Table 3 for compliance information.
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 STABILIZ-
ER LEADING EDGE SKIN RE- PAIR.
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.
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Original Issue: June 12, 2015 717-55A0012 12 of 55 BOEING SERVICE BULLETIN 717-55A0012