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Commercial Airplanes 717 Service Bulletin ALERT Number: 717-53A0034 Original Issue: October 05, 2011 Revision 1: November 07, 2012 ATA System: 5310 SUBJECT: FUSELAGE - Main Frame - Inspect Overwing Frames for Cracks 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 © 2011 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Unpublished Work.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, KDC-10, MD-10, MD-11, MD-80, MD-88, MD-90, P-8A, 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. BOEING is a trademark of Boeing Management Company.
Original Issue: October 05, 2011 717-53A0034Revision 1: November 07, 2012 1 of 36
3.0
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
Original Issue: October 05, 2011 717-53A0034Revision 1: November 07, 2012 2 of 36 BOEING SERVICE BULLETIN 717-53A0034
ALERTALERT
BLANK PAGE
Table of Contents
Revision Transmittal Sheet5
Summary7
1. PLANNING INFORMATION ........................................ 1 1 A. Effectivity ............................................... 1 1
1. Airplanes ............................................ 1 1
2. Spares Affected ........................................ 1 1 B. Concurrent Requirements ...................................... 1 1 C. Reason ................................................ 1 2 D. Description .............................................. 1 2 E. Compliance .............................................. 1 3 F. Approval ............................................... 1 5 G. Manpower .............................................. 1 5 H. Weight and Balance Changes .................................... 1 7 I. Electrical Load Data ......................................... 1 7 J. References .............................................. 1 7
1. Existing Data: ......................................... 1 7
2. Data Supplied with this Service Bulletin: ........................... 1 7
3. Installation Drawings Used in the Preparation of this Service Bulletin: ........... 1 8 K. Publications Affected ........................................ 1 8 L. Interchangeability and Intermixability of Parts ........................... 1 8 M. Software Accomplishment Summary ................................ 1 8
2. MATERIAL INFORMATION ........................................ 1 9 A. Material - Price and Availability ................................... 1 9 B. Industry Support Information .................................... 1 9 C. Parts Necessary for Each Airplane ................................. 1 9
1. Kits/Parts ............................................ 1 9
2. Parts and Materials Supplied by the Operator ........................ 2 2
3. Parts Modified and Reidentified ................................ 2 3
4. Parts Removed and Not Replaced .............................. 2 3 D. Parts Necessary to Change Spares ................................. 2 3 E. Special Tooling - Price and Availability ............................... 2 3 F. Special Tooling Necessary to do this Service Bulletin ....................... 2 3
3. ACCOMPLISHMENT INSTRUCTIONS .................................. 2 5 A. GENERAL INFORMATION ..................................... 2 5 B. WORK INSTRUCTIONS ....................................... 2 6 FIGURE 1: DETAILED VISUAL INSPECTION - OVERWING FRAMES ................. 3 0 FIGURE 2: EDDY CURRENT, HIGH FREQUENCY INSPECTION - OVERWING FRAMES ...... 3 2 FIGURE 3: BLEND-OUT REPAIR - FRAME TAB UPPER RADIUS ................... 3 4 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
Original Issue: October 05, 2011 717-53A0034Revision 1: November 07, 2012 3 of 36 BOEING SERVICE BULLETIN 717-53A0034
ALERTALERT
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
Original Issue: October 05, 2011 717-53A0034Revision 1: November 07, 2012 4 of 36 BOEING SERVICE BULLETIN 717-53A0034
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Commercial Airplanes 717 Service Bulletin ALERT Revision Transmittal SheetNumber: 717-53A0034Original Issue: October 05, 2011 Revision 1: November 07, 2012 ATA System: 5310 SUBJECT: FUSELAGE - Main Frame - Inspect Overwing Frames for Cracks This revision includes all pages of the service bulletin.
COMPLIANCE INFORMATION RELATED TO THIS REVISION Federal Aviation Administration (FAA) Notice of Proposed Rule Making (NPRM) 2011-NM-273-AD is related to this service bulletin.
No more work is necessary on airplanes changed in accordance with the original issue of this service bulletin.
REASON FOR REVISION This revision is sent to change the initial inspection compliance time threshold and add alternate parts to kits.
These sections were changed:
1. In Paragraph 1.C., Reason, changed statement and added Fleet Team Digest article.
2. In Paragraph 1.E., Compliance, added NPRM and changed Table 1.
3. In Paragraph 1.J.1., Existing Data, added NPRM and Fleet Team Digest article.
4. In Paragraph 1.J.2.a., Drawings, changed drawing revision level.
5. In Paragraph 2.A., Material - Price and Availability, changed kit pricing data.
6. In Paragraph 2.C.1, Kits/Parts, added alternate parts to kits.
Vertical lines are put on the left edge of each page, except in Paragraph 1.A., Effectivity, to show the location of important changes.
Pages with no vertical lines have no important changes.
REVISION HISTORY October 05, 2011Original Issue:
November 07, 2012Revision 1:
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
Original Issue: October 05, 2011 717-53A0034Revision 1: November 07, 2012 5 of 36
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
Original Issue: October 05, 2011 717-53A0034Revision 1: November 07, 2012 6 of 36 BOEING SERVICE BULLETIN 717-53A0034
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BLANK PAGE
Commercial Airplanes 717 Service Bulletin ALERT SummaryNumber: 717-53A0034Original Issue: October 05, 2011 Revision 1: November 07, 2012 ATA System: 5310 SUBJECT: FUSELAGE - Main Frame - Inspect Overwing Frames for Cracks
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 There have been over forty reports of overwing frames cracking on MD-80 airplanes having logged between 19,876 and 41,166 flight cycles. There is one report of a cracked overwing frame on an MD-90 airplane, and two 717 airplanes have been reported with cracked frames. The first 717 airplane had 18,235 flight-hours and 14,542 landing cycles and the second 717 airplane had 22,053 flight-hours and 11,991 landing cycles. Due to similarity in frame design, the 717 airplanes are susceptible to cracks. The cracks, which originate in the upper radius of the frame inboard tab just below the floor, were caused by fatigue. Boeing has determined that 717 overwing frames at Stations Y=674.000, Y=696.000 and Y=715.000 are also susceptible to this type of failure.
All the noted frames are a part of 717 Principal Structural Element (PSE) 53.30.02.11. Inspection of the overwing frames at Stations Y=674.000, Y=696.000 and Y=715.000, left and right sides will determine if cracks exist. If not corrected, an undetected crack may sever the frame, which may increase the loading of adjacent frames and result in damage to adjacent structure and extensive repair, or ultimately could lead to the loss of overall structural integrity of the airplane.
Boeing Fleet Team Digest (FTD) 717 FTD 53-09003 is related to this service bulletin.
ACTION This service bulletin provides instructions to do a general visual inspection and a high frequency eddy current inspection of the overwing frames at Stations Y=674.000, Y=696.000 and Y=715.000, left and right sides. The purpose of these inspections is to detect fatigue cracks in the upper radius of the frame tab. Based on inspection results, do as follows:
Condition 1 (No Crack Found on Any Frame)
1. Does repetitive general visual inspections and high frequency eddy current inspections of the overwing frames for cracks and does as follows:
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
Original Issue: October 05, 2011 717-53A0034Revision 1: November 07, 2012 7 of 36
Condition 1A (No Crack Found on Any Frame)
a. Does repetitive general visual inspections and high frequency eddy current inspections of the overwing frames for cracks.
Condition 1B (Crack Found on Any Frame)
a. Establishes the length of the crack and does the work of Condition 2 or Condition 3.
Condition 2 (Crack in Any Frame is Less Than 0.125 Inch in Length)
1. Does a blend-out repair of the crack.
2. Does repetitive general visual inspections and high frequency eddy current inspections of the repaired overwing frame for cracks and does as follows:
Condition 2A (No Crack Found on Any Repaired Frame)
a. Does repetitive general visual inspections and high frequency eddy current inspections of the repaired overwing frame for cracks.
Condition 2B (Any Crack Found on Any Repaired Frame)
a. Does the work of Condition 3.
Condition 3 (Crack in Any Frame is Equal To or Greater Than 0.125 Inch in Length)
1. Replaces the cracked overwing frame.
2. Does repetitive general visual inspections and high frequency eddy current inspections of the replaced overwing frame for cracks and does as follows:
Condition 3A (No Crack Found on Any Replaced Frame)
a. Does repetitive general visual inspections and high frequency eddy current inspections of the replaced overwing frame for cracks.
Condition 3B (Crack Found on Any Replaced Frame)
a. Establishes the length of the crack and does the work of Condition 2 or Condition 3.
EFFECTIVITY All 717-200 Airplanes. Refer to Paragraph 1.A.1., Airplanes, for the list of affected airplane(s).
COMPLIANCE Federal Aviation Administration (FAA) Notice of Proposed Rule Making (NPRM) 2011-NM-273-AD is related to this service bulletin.
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
Original Issue: October 05, 2011 717-53A0034Revision 1: November 07, 2012 8 of 36 BOEING SERVICE BULLETIN 717-53A0034
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Refer to Paragraph 1.E., Compliance.
INDUSTRY SUPPORT INFORMATION Boeing warranty remedies are not available for the inspection and/or repair procedures given in this service bulletin.
MANPOWER Refer to Paragraph 1.G., Manpower.
MATERIAL INFORMATION Boeing Supplied Kits/Parts.
Refer to Paragraph 2.A., Material - Price and Availability.
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
Original Issue: October 05, 2011 717-53A0034Revision 1: November 07, 2012 9 of 36 BOEING SERVICE BULLETIN 717-53A0034
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BOEING SERVICE BULLETIN 717-53A0034
ALERT ALERT
- STA Y=674.000
- STA Y=696.000
- STA Y=715.000 00000000000000000/0000
INSPECT OVERWING
FRAMES FOR CRACKS 2087528 Original Issue: October 05, 2011 Revision 1: November 07, 2012 PROPRIETARY - Copyright © Unpublished Export Controlled ECCN: 9E991 - BOEING 717-53A0034 Work - See page 1 for details. 10 of 36
Commercial Airplanes 717 Service Bulletin ALERT Number: 717-53A0034 Original Issue: October 05, 2011 Revision 1: November 07, 2012 ATA System: 5310 SUBJECT: FUSELAGE - Main Frame - Inspect Overwing Frames for Cracks
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-1 Airplane Models:
717-200 GroupFuselage Number 15002 - 5099 15100 - 5156
2. Spares Affected None.
B. Concurrent Requirements None.
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
Original Issue: October 05, 2011 717-53A0034Revision 1: November 07, 2012 11 of 36
C. Reason There have been over forty reports of overwing frames cracking on MD-80 airplanes having logged between 19,876 and 41,166 flight cycles. There is one report of a cracked overwing frame on an MD-90 airplane, and two 717 airplanes have been reported with cracked frames. The first 717 airplane had 18,235 flight-hours and 14,542 landing cycles and the second 717 airplane had 22,053 flight-hours and 11,991 landing cycles. Due to similarity in frame design, the 717 airplanes are susceptible to cracks.
The cracks, which originate in the upper radius of the frame inboard tab just below the floor, were caused by fatigue. Boeing has determined that 717 overwing frames at Stations Y=674.000, Y=696.000 and Y=715.000 are also susceptible to this type of failure. All the noted frames are a part of 717 Principal Structural Element (PSE) 53.30.02.11. Inspection of the overwing frames at Stations Y=674.000, Y=696.000 and Y=715.000, left and right sides will determine if cracks exist. If not corrected, an undetected crack may sever the frame, which may increase the loading of adjacent frames and result in damage to adjacent structure and extensive repair, or ultimately could lead to the loss of overall structural integrity of the airplane.
Boeing Fleet Team Digest (FTD) 717 FTD 53-09003 is related to this service bulletin.
This revision is sent to change the initial inspection compliance time threshold and add alternate parts to kits.
D. Description This service bulletin provides instructions to do a general visual inspection and a high frequency eddy current inspection of the overwing frames at Stations Y=674.000, Y=696.000 and Y=715.000, left and right sides. The purpose of these inspections is to detect fatigue cracks in the upper radius of the frame tab. Based on inspection results, do as follows:
Condition 1 (No Crack Found on Any Frame)
1. Does repetitive general visual inspections and high frequency eddy current inspections of the overwing frames for cracks and does as follows:
Condition 1A (No Crack Found on Any Frame)
a. Does repetitive general visual inspections and high frequency eddy current inspections of the overwing frames for cracks.
Condition 1B (Crack Found on Any Frame)
a. Establishes the length of the crack and does the work of Condition 2 or Condition 3.
Condition 2 (Crack in Any Frame is Less Than 0.125 Inch in Length)
1. Does a blend-out repair of the crack.
2. Does repetitive general visual inspections and high frequency eddy current inspections of the repaired overwing frame for cracks and does as follows:
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
Original Issue: October 05, 2011 717-53A0034Revision 1: November 07, 2012 12 of 36 BOEING SERVICE BULLETIN 717-53A0034