# Boeing Alert Service Bulletin 717-53A0034: Revision 1 - Rights: © The Boeing Company. Filed by the FAA in regulations.gov docket FAA-2012-0425; AD 2013-19-22 incorporates this document by reference. Not covered by OpenAirDocs’ CC0 dedication. - Document: [Boeing Alert Service Bulletin 717-53A0034](https://openairdocs.org/service-documents/boeing/717-53a0034.md) - Title as filed: U.S. DOT/FAA - 717 Service Bulletin No. 717-53A0034 - Pages: 34 - PDF: https://openairdocs.org/files/sha256/64/ce/64cef3db3c223c6fde81e03aef6b412cac5789c03a80f94efccb77cc271b0260 - Page: https://openairdocs.org/service-documents/boeing/717-53a0034/file/64cef3db3c22 ## Text This text is 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 (OCR) DULLUSULE A 10/5/2011 11-00269 Commercial D SOLING Airplanes 717 Service Bulletin — ALERT Number: 717-53A0034 Original Issue: October 05, 2011 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 730-774). 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. ECCN: 9E991 BOEING PROPRIETARY, CONFIDENTIAL, AND/OR TRADE SECRET Copyright © 2011 The Boeing Company Unpublished Work - All Rights Reserved Boeing claims copyright in each page of this document only to the extent that the page contains copyrightable subject matter. Boeing also claims copyright in this document as a compilation and/or collective work. This document includes proprietary information owned by The Boeing Company and/or one or more third parties. Treatment of the document and the information it contains is governed by contract with Boeing. For more information, contact The Boeing Company, P.O. Box 3707, Seattle, Washington 98124. 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 the Boeing livery 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 Original Issue: October 05, 2011 717-53A0034 Copyright Unpublished Work. - See page 1 for details. BOEING PROPRIETARY - 1 of 34 3.0 ### Page 2 (OCR) BOEING SERVICE BULLETIN 717-53A0034 ALERT ALERT BLANK PAGE Original Issue: October 05, 2011 717-53A0034 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 2 of 34 ### Page 3 (OCR) BOEING SERVICE BULLETIN 717-53A0034 ALERT ALERT Table of Contents summary PLANNING INFORMATION 9 Effectivity 1. Airplanes . 2. Spares Affected 9 B Concurrent Requirements . Reason 10 D. Description 10 Compliance 11 F Approval 13 Manpower 13 H. Weight and Balance Changes 15 I. Electrical Load Data 15 J. References 15 1. Existing Data . 15 2. Data supplied with this Service Bulletin 15 3. Installation Drawings Used in the Preparation of this Service Bulletin 16 K. Publications Affected 16 Interchangeability and Intermixability of Parts 16 2. MATERIAL INFORMATION 17 A. Material - Price and Availability. 17 B. Industry Support Information 17 C. Parts Necessary For Each Airplane 17 1. Kits/Parts 17 2. Parts and Materials Supplied by the Operator 20 3. Parts Modified and Reidentified. 21 4. Parts Removed and Not Replaced. 21 D. Parts Necessary to Change Spares. 21 E Special Tooling - Price and Availability. 21 F. Special Tooling Necessary to do this Service Bulletin. 21 3. ACCOMPLISHMENT INSTRUCTIONS 23 A. GENERAL INFORMATION 23 B. WORK INSTRUCTIONS..... 24 FIGURE 1: DETAILED VISUAL INSPECTION - OVERWING FRAMES. 28 FIGURE 2: EDDY CURRENT, HIGH FREQUENCY INSPECTION - OVERWING FRAMES. 30 FIGURE 3: BLEND-OUT REPAIR - FRAME TAB UPPER RADIUS. 32 Original Issue: October 05, 2011 717-53A0034 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 3 of 34 ### Page 4 (OCR) BOEING SERVICE BULLETIN 717-53A0034 ALERT ALERT BLANK PAGE Original Issue: October 05, 2011 717-53A0034 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 4 of 34 ### Page 5 (OCR) Commercial @ GOEING Airplanes 717 Service Bulletin - ALERT Number: 717-53A0034 Summary Original Issue: October 05, 2011 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 one report of a crack on a 717 airplane. The 717 airplane had 18,235 flight-hours and 14,542 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. 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 tollows: Condition 1 (No Crack Found on Any Frame) Does repetitive general visual inspections and high frequency eddy current inspections of the overwing frames for cracks and does as follows: Original Issue: October 05, 2011 717-53A0034 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 5 of 34 ### Page 6 (OCR) BOEING SERVICE BULLETIN 717-53A0034 ALERT ALERT 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 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. Original Issue: October 05, 2011 BOEING PROPRIETARY - 717-53A0034 Copyright © Unpublished Work - See page 1 for details. 6 of 34 ### Page 7 (OCR) BOEING SERVICE BULLETIN 717-53A0034 ALERT ALERT 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. Original Issue: October 05, 2011 BOEING PROPRIETARY - 717-53A0034 Copyright © Unpublished Work - See page 1 for details. 7 of 34 ### Page 8 (OCR) BOEING SERVICE BULLETIN 717-53A0034 ALERT ALERT - STA Y=674.000 - STA Y=696.000 - STA Y =715.000 not 00000000000000000100000 INSPECT OVERWING FRAMES FOR CRACKS 2087528 Original Issue: October 05, 2011 717-53A0034 BOEING PROPRIETARY - Copyright © Unpublished Work. - See page 1 for details. 8 of 34 ### Page 9 (OCR) Commercial RODEINE Airplanes 717 Service Bulletin - ALERT Number: 717-53A0034 Original Issue: October 05, 2011 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 GROUP CONFIGURATION DESCRIPTION 717-200 Airplanes Airplane Models: 717-200 Fuselage Num- Group ber 5002 - 5156 2. Spares Affected None. B. Concurrent Requirements None. Original Issue: October 05; 2011 717-53A0034 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 9 of 34 ### Page 10 (OCR) BOEING SERVICE BULLETIN 717-53A0034 ALERT ALERT 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 one report of a crack on a 717 airplane. The 717 airplane had 18,235 flight-hours and 14,542 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. 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: 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 (Crack Found on Any Repaired Frame) a. Does the work of Condition 3. Original Issue: October 05, 2011 717-53A0034 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 10 of 34 ### Page 11 (OCR) BOEING SERVICE BULLETIN 717-53A0034 ALERT ALERT 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 (Any Crack Found on Any Replaced Frame) a. Establishes the length of the crack and does the work of Condition 2 or Condition 3. The work in this service bulletin is done in the maintenance zone(s) given below. Affected Maintenance Zones Model Zone 717-200 151, 161 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 Accomplish the required action(s), based on the applicable condition(s), in Table 1, in accordance with Paragraph 3. Accomplishment Instructions. Table 1: Inspect Left and Right Side Overwing Frames for Cracks from Station 674 to 715 Condition Action Compliance Time (Whichever Occurs Repeat Interval Later ) (Not to Exceed) All Airplanes Do a general visual inspec- Before the accumu- Within 8275 flight tion and a high frequency lation of 20,000 to- cycles after the eddy current inspection of tal flight cycles. original issue date the overwing frames at the on this service bul- tab upper radius for cracks. letin. Original Issue: October 05, 2011 717-53A0034 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 11 of 34 ### Page 12 (OCR) BOEING SERVICE BULLETIN 717-53A0034 ALERT ALERT Table 1: Inspect Left and Right Side Overwing Frames for Cracks from Station 674 to 715 Condition Action Compliance Time (Whichever Occurs Repeat Interval [ Later ) (Not to Exceed) Condition 1 Do repeat general visual in- 9,300 flight cycles. (No Crack Found spection and high frequency on Any Frame) eddy current inspection. AND Do the action specified by Condition 1A or 1B. Condition 1A Do repeat general visual in- 9,300 flight cycles. (No Crack Found spection and high frequency on Any Frame) eddy current inspection. Condition 1B Establish the length of the Before further (Crack Found on crack and do the work | flight. Any Frame) specified by Condition 2 or Condition 3. Condition 2 Repair the cracked over- Before further (Crack in Any wing frame. flight. Frame is Less AND Than 0.125 Inch in Length) Do a general visual inspec- | 9,300 flight cycles 9,300 flight cycles. tion and high frequency ed- after repair. dy current inspection of the repaired overwing frame. AND Do the action specified by Condition 2A or 2B. Condition 2A Do repeat general visual in- 9,300 flight cycles. (No Crack Found spection and high frequency on Any Repaired eddy current inspection of Frame) the repaired overwing frame. Condition 2B Do the work specified by Before further (Crack Found on Condition 3. | flight. Any Repaired Frame) Original Issue: October 05, 2011 717-53A0034 BOEING PROPRIETARY - Copyright © Unpüblished Work - See page 1 for details. 12 of 34 ### Page 13 (OCR) BOLING SERVICE BULLETIN * 717-5380034 ALERT ALERT Table 1: Inspect Left and Right Side Overwing Frames for Cracks from Station 674 to 715 Condition Action Compliance Time (Whichever Occurs Repeat Interval Later ) (Not to Exceed) Condition 3 Replace the cracked over- Before further (Crack in Any wing frame. flight. Frame is Equal To or Greater Than AND 0.125 Inch in Do a general visual inspec- Within 20,000 flight 9,300 flight cycles. Length) tion and high frequency ed- cycies after replace- dy current inspection of the | ment. replaced overwing frame. AND Do the action specified by Condition 3A or 3B. Condition 3A Do repeat general visual in- - 19,300 flight cycles. (No Crack Found spection and high frequency on Any Replaced eddy current inspection of Frame) the replaced overwing trame: Condition 3B Establish the length of the Before further (Crack Found on crack and do the work flight. Any Replaced specified by Condition 2 or Frame) Condition 3. 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 If an airplane has a non-Boeing modification or repair that affects a component or system also affected by this service bulletin, the operator is responsible for obtaining appropriate regulatory agency approval before incorporating this service bulletin. G. Manpower The table below shows an estimate of the task hours necessary to do this inspection for each airplane. This estimate is for direct labor only, done by an experienced crew. Adjust the estimate with operator task hour data if necessary. The estimate does not include lost time. These are some examples of lost time: Time to adjust to the workplace Time to schedule the work Time to inspect the work Original Issue: October 05, 2011 BOEING PROPRIETARY - 717-53A0034 Copyright © Unpublished Work - See page 1 for details. 13 of 34 ### Page 14 (OCR) BOEING SERVICE BULLETIN 717-53A0034 ALERT ALERT Time to cure the materials Time to make the parts Time to find the tools: Condition 1 Task Number of Persons Task Hours Elapsed Hours Open Access 20.0 5.0 FIGURE 1 1 3.0 | 3.0 FIGURE 2 3.0 3.0 Close Access 4 20.0 5.0 TOTAL FOR EACH AIRPLANE 46.0 16.0 NOTE: Maximum total task hours and elapsed hours are given for inspection per airplane. Condition 2 Task Number of Persons Task Hours Elapsed Hours Open Access 4 20.0 5.0 FIGURE 1 3.0 3.0 FIGURE 2 3.0 3.0 Remove Cusp Mem- 6.0 6.0 brane FIGURE 3 2.0 2.0 Install Cusp Mem- 6.0 6.0 orane Close Access 4 20.0 5.0 TOTAL FOR EACH AIRPLANE 60.0 30.0 NOTE: Maximum total task hours and elapsed hours are given for the blend-out repair of one frame. Additional task hours and elapsed hours for the repair of other cracked frames are contingent upon inspection results and are to be estimated by the operator. Condition 3 Task Number of Persons Task Hours Elapsed Hours Open Access 4 20.0 5.0 FIGURE 1 3.0 3.0 FIGURE 2 3.0 3.0 Remove Cusp Mem- 6:0 6.0 brane Original Issue: October 05, 2011 BOEING PROPRIETARY - 717-53A0034 Copyright © Unpublished Work - See page 1 for details. 14 of 34 ### Page 15 (OCR) BOEING SERVICE BULLETIN 717-53A0034 ALERT ALERT Condition 3 Task Number of Persons Task Hours Elapsed Hours Defuel 2 4.0 2.0 Remove Frame 2 20.0 10.0 Install Frame 48.0 24.0 Install Cusp Mem- 1 6.0 6.0 brane Close Access 4 20.0 5.0 TOTAL FOR EACH AIRPLANE 130.0 64.0 NOTE: Maximum total task hours and elapsed hours are given for the replacement of one frame. Additional task hours and elapsed hours for the replacement of other cracked frames, are contingent upon inspection results and are to be estimated by the operator. H. Weight and Balance Changes None. I. Electrical Load Data Not changed. J. References 1. Existing Data a. Non-Destructive Test Standard Practices Manual (NDTSPM) 06-10-01.001, 09-00-04, 09-00-06. b. Standard Overhaul Practices Manual (SOPM) 20-10-10 c. 717 Aircraft Maintenance Manual (AMM) 06-31-00, 07-11-00, 07-20-01, 08-20-00, 12-11-01, 20-60-01, 20-60-26, 25-23-05, 25-28-02, 25-82-01, 52-21-01, 53-21-01. d. 717 Structural Repair Manual (SRM) 51-10-04, 51-20-05, 51-40-03, 51-40-08, 51-41-01; 51-41-02, 51-41-03, 51-41-05. e. Boeing Drawing SE10000000. 2. Data supplied with this Service Bulletin No data is supplied with this service bulletin. To obtain the data necessary to support this service bulletin submit a data request to: Data and Services Management MS D800-0019 3855 Lakewood Boulevard Long Beach, California 90846 Phone: (562) 593-6996 Original Issue: October 05, 2011 717-53A0034 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 15 of 34 ### Page 16 (OCR) BOEING SERVICE BULLETIN 717-53A0034 ALERT ALERT Fax: (562) 593-2001 E-mail: dse.boecom@boeing.com a. Drawings: Drawing No Title Sheet DCN/REV ADCN SR95530013 FRAME INSTL - OVERWING SERVICE DWG REWORK DRAWING 3. Installation Drawings Used in the Preparation of this Service Bulletin None. K. Publications Affected 1. Publications: Publication Chapter-Section Maintenance Planning Document 53-00 2. Damage Tolerance Based Structural Inspections: Boeing has evaluated the repairs and/or changes in this service bulletin for effects on Fatigue Critical Structure (FCS) and for changes to Damage Tolerance Inspections (DTI) required in the Maintenance Program. This service bulletin affects FCS but no new DTIs are necessary. L. Interchangeability and Intermixability of Parts Accomplishment of this service bulletin does not affect interchangeability or intermixability of parts. Original Issue: October 05, 2011 717-53A0034 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 16 of 34 ### Page 17 (OCR) BOEING SERVICE BULLETIN 717-53A0034 ALERT ALERT 2. MATERIAL INFORMATION A. Material - Price and Availability Boeing can supply the kits shown in Paragraph 2.C., Parts Necessary for Each Airplane. Operators are encouraged to share schedule requirements with Boeing for incorporation of the service bulletin. The parts are subject to the terms and conditions of the Boeing standard purchase order acknowledgment. Prices are in United States Dollars. Terms: Net 30 days. Reference this service bulletin and submit your purchase order by one of these methods: 1. Order on-line via ATA Spec 2000 or The Boeing PART Page 2. Fax to (206) 662-7145 REFER TO THE BOEING PART PAGE ON MYBOEINGFLEET.COM OR CONTACT FIRST RESPONDER AT FR@BOEING.COM FOR THE LATEST REORDER LEAD TIME (ROLT) AND PRICE INFORMATION Kit Number Name ROLT as of the Unit Price as of original date of the original date this Service Bul- of this Service letin (Calendar Bulletin (US Dol- Days) lars) SA95530034-3 Service Kit 90 $38,234.00 SA95530034-5 Service Kit 90 38,213.00 SA95530034-7 Service Kit 90 43,508.00 SA95530034-9 Service Kit 90 43,469.00 SA95530034-11 Service Kit 90 43,147.00 SA95530034-13 Service Kit 90 43,469.00 B. Industry Support Information Boeing warranty remedies are not available for the inspection, and/or repair procedures given in this service bulletin. C. Parts Necessary For Each Airplane 1. Kits/Parts Relationship of Fuselage Stations to Kits is as follows: Station Frame Kit Y=674.000, Left Side SA95530034-3 Y=674.000, Right Side SA95530034-5 Y=696:000, Left Side SA95530034-7 Y=696.000, Right Side SA95530034-9 Original Issue: October 05, 2011 BOEING PROPRIETARY - 717-53A0034 Copyright © Unpublished Work - See page 1 for details. 17 of 34 ### Page 18 (OCR) BOEING SERVICE BULLETIN 717-53A0034 ALERT ALERT Station Frame Kit Y=715.000, Left. Side SA95530034-11 Y=715.000, Right Side SA95530034-13 Kit SA95530034 New Part Number QTY Name Notes -3 -5 -7 -9 -11 -13 2913797-1 CLIP 2913870-1 1 1 1 CLIP 2920753-1 1 1 CLIP 2920754-501 CLIP 19920260 1 1 CLIP 2920756-2 1 CLIP 8-900008 00L 001 86 98 101 101 NUT ASSY (a) 3D0006-4 2 2 2 NUT ASSY (a) 41-6996166 CLIP 9919669-18 CLIP 9919671-17 CLIP 81296166 CLIP 9919671-19 1 1 CLIP 171296166 1 1 CLIP 9923405-503 1 FRAME 9923405-504 1 FRAME 9923406-503 1 FRAME 9923406-504 FRAME 9923407-503 FRAME 9923407-504 FRAME 9971114-13 1 CLIP 9971114-14 CLIP 9971114-17 1 CLIP 9971114-18 1 CLIP HLT435-6-10 6 6 2 2 PIN HLT435-6-11 2 2 PIN HLT435-6-3 1 1 PIN Original Issue: October 05, 2011 BOBING PROPRIETARY - 717-53A0034 Copyright © Unpublished Work - See page 1 for details. 18 of 34 ### Page 19 (OCR) BOEING SERVICE BULLETIN 717-53A0034 ALERT ALERT Kit SA95530034 New Part Number QTY Name Notes -3 -5 -7 -9 -11 -13 HLT435-6-4 3 3 3 3 PIN HLT435-6-5 1 2 2 2 2 SPIN HLT435-6-6 23 23 36 36 36 36 PIN HLT435-6-7 4 4 2 2 PIN HLT435-6-8 16 16 15 15 12 12 PIN HLT435-6-9 8 8 5 5 9 9 PIN HLT436-10-8 1 1 PIN HLT436-12-10 2 2 2 PIN HLT436-12-11 2 2 PIN HLT436-6-2 5 5 9 PIN HLT436-6-3 11 11 14 PIN HLT436-6-4 15 15 15 PIN HLT436-6-5 15 15 19 PIN HLT436-6-6 8 8 8 PIN HLT436-6-7 1 2 2 2 PIN HLT436-6-8 2 2 PIN HLT436-6-9 † PIN HLT436-8-6 1 PIN HLT436-8-7 2 2 3 4 4 PIN HLT436-8-8 4 4 4 4 PIN HLT436-8-9 1 PIN HLT439-6-4 1 1 PIN HLT439-6-5 1 PIN HLT439-6-8 3 PIN MS20470AD5-10D 6 10 10 4 RIVET MS20470AD5-11D 6 6 21 21 15 15 RIVET MS20470AD5-12D 13 13 1 1 1 RIVET MS20470AD5-13D 1 1 RIVET MS20470AD5-8D 11 11 RIVET MS20470AD5-9D 6 6 1 RIVET MS20470AD6-12D 1 1 RIVET Original Issue: October 05, 2011 717-53A0034 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 19 of 34 ### Page 20 (OCR) BOEING SERVICE BULLETIN 717-53A0034 ALERT ALERT Kit SA95530034 New Part Number QTY Name Notes -3 -5 -11 -13 MS20470AD6-13D 1 1 RIVET MS20470AD6-14D RIVET MS21042L3 56 56 70 70 65 65 NUT MS21042L4 5 5 6 6 6 6 NUT MS21042L5 1 NUT MS21042L6 2 2 2 2 2 2 NUT NAS1252-10L 56 56 70 70 65 65 WASHER NAS1252-416L 5 5 6 6 6 WASHER NAS1252-516L 1 WASHER NAS1252-616L 2 2 2 2 2 2 WASHER S4931920-6-3 4 PIN S4931920-6-4 4 4 4 4 PIN S4931920-6-5 2 2 PIN S4931920-6-6 10 10 16 16 PIN S4931920-6-7 12 12 25 25 8 8 PIN S4931920-6-8 4 4 PIN (a) Or Approved Equivalent. Refer to AEPL Drawing 7595071. 2. Parts and Materials Supplied by the Operator Part Number / Specification QTY Name Notes PC21F 1 Roll Tape, Cloth Coated (a) (DMS 1968 Type 2) OR Equivalent PR-1422 Class B-2 1 Quart Sealing Compound | (b) (DMS 2082) OR Equivalent Part Number 235 1 Roll Tape, Adhesive, Double Faced | (c) (DMS 1971) OR Equivalent Original Issue: October 05, 2011 717-53A0034 Copyright © Unpublished Work - See page 1 for details. BOEING PROPRIETARY - 20 of 34 ### Page 21 (OCR) BOEING SERVICE BULLETIN 717-53A0034 ALERT ALERT (a) Can be purchased from: Shurtape Technologies, Limited Liability CAGE Corporation (LLC) 4LOSO 1506 Highland Avenue North East Hickory, North Carolina 28601 (b) Can be purchased from: PRC-DeSoto International, Incorporated 92108 P.O. Box 1800 Sylmar, California 91342 (C) Can be purchased from: Ideal Tape Company 3X706 1400 Middlesex Street Lowell, Massachusetts 01851 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 General visual inspection equipment and high frequency eddy current inspection equipment required to accomplish this service bulletin are listed in the Non-Destructive Testing Standard Practice Manual (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 too supply to make sure all necessary tools are available. Original Issue: October 05, 2011 717-53A0034 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 21 of 34 ### Page 22 (OCR) BOEING SERVICE BULLETIN 717-53A0034 ALERT ALERT BLANK PAGE Original Issue: October 05, 2011 BOEING PROPRIETARY - 717-53A0034 Copyright © Unpublished Work - See page 1 for details. 22 of 34 ### Page 23 (OCR) BOEING SERVICE BULLETIN 717-53A0034 ALERT ALERT 3. ACCOMPLISHMENT INSTRUCTIONS A. GENERAL INFORMATION WARNING: IF ELECTRICAL POWER IS APPLIED TO THE AIRPLANE, MAKE SURE YOU OBEY ALL PREÇAUȚIONS WHILE YOU DO WORK. IF YOU DO NOT OBEY THE PRECAUTIONS, DEATH OR INJURY TO PERSONS, AND DAMAGE TO THE AIRPLANE CAN OCCUR. CAUTION: _ 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. 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 Structural Repair Manual (SRM).. 4. If the length of any fastener specified in this service bulletin does not meet installation standards given in SRM Chapter 51, then a fastener of the same specification, or an approved substitute, with a length which meets the installation standards given in SRM Chapter 51 may be used. In addition, washers may be installed for fastener 5. A 1/8-inch thick stack of the same type washers called for in this service bulletin is the maximum thickness which may be used under fastener head or nut to counteract accumulation of tolerances. EXCEPTION: When the available fastener length increments are greater than 1/16-inch, a 3/16-inch thick stack of the same type washers may be used. 6. Oversize fasteners must be used when hole diameter exceeds the maximum diameter specified. 7. Obey all of the warnings and cautions given in the specified manual sections. 8. A General Visual Inspection is defined as: A visual examination of an interior or exterior area, installation or assembly to detect obvious damage, failure or irregularity. This level of inspection is made from within touching distance unless otherwise specified. A mirror may be necessary to enhance visual access to all exposed surfaces in the inspection area. This level of inspection is made under normally available lighting conditions such as daylight, hangar lighting, flashlight or drop-light and may require removal or opening of access panels or doors. Stands, ladders or platforms may be required to gain proximity to the area being checked Original Issue: October 05, 2011 717-53A0034 BOEING PROPRIETARY - Copyright @ Unpublished Work - See page 1 for details. 23 of 34 ### Page 24 (OCR) BOEING SERVICE BULLETIN 717-53A0034 ALERT ALERT 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. Some Boeing parts are supplied in a temporary configuration. Those parts are identified with a 'U' or 'Y' in place of the '-' (dash) in the part number. It is permitted to install parts identified with a 'U' or "Y' as an alternative to the ' (dash) number part. Boeing Drawing SE10000000, Sheets 5.0 and 6.0 contain more data. 11. The instructions in Paragraph 3.B., Work Instructions and the figures can include operation of tools or test equipment. Boeing Engineering Tool Drawings, the Illustrated Tool and Equipment Manual, and the Special Tool and Ground Handling Drawing Index contain data on versions of the tools or test equipment that you can use. It is permitted to use replaced tools. It is not permitted to use superseded tools. 12. 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. The removed part can be discarded if a new or serviceable part is installed. 13. Refer to the manuals that follow as accepted procedures: Accepted Procedure Operation 717 AMM 20-60-01 Sealant - Maintenance Practices 717 SRM 51-10-04 Corrosion/Erosion Control and Prevention 717 SRM 51-40-08 Drilling and Countersinking 717 SRM 51-20-05 Repair Sealing 717 SRM 51-41-01 Installing Bolts, Screws, and Washers 717 SRM 51-41-02 Installing and Removing Rivets 717 SRM 51-41-03 Installing and Removing Lockbolts 717 SRM 51-41-05 Installing and Removing HI-Lok Attachments 717 SRM 51-40-03 Fastener Substitution and Interchangeability B. WORK INSTRUCTIONS 1. Remove and keep the items and attaching parts, as applicable, to get access to the left and right side overwing frames at Stations Y=674.000, Y=696.000 and Y=715.000 as follows: Item Accepted Procedure Passenger Seats 717 AMM 25-23-05 Panel, Cabin Sidewall 717 AMM 25-28-02 Passenger Compartment Insulation 717 AMM 25-82-01 Original Issue: October 05, 2011 717-53A0034 BOEING PROPRIETARY - Copyright Unpublished Work - See page 1 for details. 24 of 34 ### Page 25 (OCR) BOEING SERVICE BULLETIN 717-53A0034 ALERT ALERT Item Accepted Procedure Overwing Emergency Exit Doors 717 AMM 52-21-01 2. Remove and keep the passenger floor coverings (carpet) by pulling one corner to peel the double sided tape off the floor. 3. Remove and keep passenger compartment floor panels to gain access to the fuselage frames between Stations Y=674.000 and Y=715.000. Refer to 717 AMM 53-21-01 as an accepted procedure. 4. Remove tape from the cutout between the cusp membrane and frame to get access to the frame inspection area. 5. Remove and keep the cusp membrane, as necessary, to get access to the frame inspection area. 6. Do a General Visual inspection and an Eddy Current, High Frequency (ETHF) inspection of the upper radius of the frame tab on the left and right sides of the overwing frames at Stations Y=674.000, Y=696.000 and Y=715.000 in accordance with Figures 1 and 2. Based on findings do Condition 1 (No Crack Found on Any Frame) a. Do repeat General Visual inspection and an Eddy Current, High Frequency (ETHF) inspections of the overwing frames in accordance with Figures 1 and 2 at intervals specified in Paragraph 1.E., Compliance. Condition 1A (No Crack Found on Any Frame) (1) Do repeat General Visual inspection and an Eddy Current, High Frequency (ETHF) inspections of the overwing frames in accordance with Figures 1 and 2 at intervals specified in Paragraph 1.E., Compliance. Condition 1B (Crack Found on Any Frame) (1) Establish the length of the crack and do the work of Condition 2 or Condition 3. Condition 2 (Crack in Any Frame is Less Than 0.125 Inch in Length) a. If installed, remove and keep the cusp membrane to get access to the cracked frame. b. Do a blend-out repair of the crack in accordance with Figure 3. c. Do repeat General Visual inspection and an Eddy Current, High Frequency (ETHF) inspections of the repaired overwing frame in accordance with Figures 1 and 2 at intervals specified in Paragraph 1.E., Compliance. Based on findings do as follows: Original Issue: October 05; 2011 BOEING PROPRIETARY - 717-53A0034 Copyright © Unpublished Work - See page 1 for details. 25 of 34 ### Page 26 (OCR) BOEING SERVICE BULLETIN 717-53A0034 ALERT ALERT Condition 2A (No Crack Found on Any Repaired Frame) (1) Do repeat repeat General Visual inspection and an Eddy Current, High Frequency (ETHF) inspections of the repaired overwing frame in accordance with Figures 1 and 2 at intervals specified in Paragraph 1.E., Compliance. Condition 2B (Crack Found on Any Repaired Frame) (1) Do the work of Condition 3. Condition 3 (Crack in Any Frame is Equal To or Greater Than 0.125 Inch in Length) a. Defuel the airplane. Refer to 717 AMM 12-11-01 as an accepted procedure. b. Raise and level the airplane. Refer to 717 AMM 07-11-00 and 717 AMM 08-20-00 as accepted procedures. NOTE: Boeing recommends each frame be replaced separately. If two or more frames are replaced at the same time, shoring the airplane is recommended. Refer to 717 AMM 07-20-01 as an accepted procedure. c. If installed, remove and keep the cusp membrane to get access to the cracked frame. d. Remove and keep the applicable wing to fuselage fillet panels 150CL and 150FL on the left side and/or 160CR and 160FR on the right side to get access to the cracked frame. Refer to 717 AMM 06-31-00 for fillet panel locations. e. Replace cracked overwing frame in accordance with Service Rework Drawing SR95530013. NOTE: Apply PR-1422 sealant on all faying surfaces and wet install all fasteners during frame replacement. f. Install kept applicable wing to fuselage fillet panels 150CL and 150FL on the left side and/or 160CR and 160FR on the right side. Refer to 717 AMM 06-31-00 for locations. g. Remove any shoring and lower the airplane. Refer to 717 AMM 07-11-00 and 717 AMM 08-20-00 as accepted procedures. h. Do repeat General Visual inspection and an Eddy Current, High Frequency (ETHF) inspections of the replaced overwing frame in accordance with Figures 1 and 2 at intervals specified in Paragraph 1.E., Compliance. Based on findings do as follows: Condition 3A (No Crack Found on Any Replaced Frame) (1) Do repeat General Visual inspection and an Eddy Current, High Frequency (ETHF) inspections of the replaced overwing frame in accordance with Figures 1 and 2 at intervals specified in Paragraph 1.E., Compliance Condition 3B (Crack Found on Any Replaced Frame) (1) Establish the length of the crack and do the work of Condition 2 or Condition 3 7. If removed, install kept cusp membrane Original Issue: October 05, 2011 717-53A0034 BOEING PROPRIETARY . Copyright © Unpublished Work - See page 1 for details. 26 of 34 ### Page 27 (OCR) BOEING SERVICE BULLETIN 717-53A0034 ALERT ALERT 8. Install tape to seal along the cutout between the cusp membrane and frame. 9. Install all kept passenger compartment floor panels removed to gain access to the fuselage frames between Stations Y=674.000 and Y=715.000. Refer to 717 AMM 53-21-01 as an accepted procedure 10. Install kept passenger compartment floor covering (carpet) by placing a strip of DMS 1971 double sided adhesive tape around the perimeter of the carpet, and pressing the carpet to the floor. Refer to 717 AMM 20-60-26 as an accepted procedure. 11. Install all kept items and attaching parts, as applicable from Stations Y=674.000 to Y=715.000 Item Accepted Procedure Passenger Seats 717 AMM 25-23-05 Passenger Compartment Lining 717 AMM 25-28-02 Passenger Compartment Insulation 717 AMM 25-82-01 Overwing Emergency Exit Doors 717 AMM 52-21-01 12. Put the airplane back to a serviceable condition. Original Issue: October 05, 2011 717-53A0034 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 27 of 34 ### Page 28 (OCR) BOEING SERVICE BULLETIN 717-53A0034 ALERT ALERT STA Y-674.000 STA Y=696.000 STA Y=715.000 STATION FRAME TYPICAL CRACK INSPECTION AREA LEFT SIDE SHOWN RIGHT SIDE OPPOSITE 2087537 FIGURE 1: DETAILED VISUAL INSPECTION - OVERWING FRAMES (SHEET 1 OF 2) Original Issue: October 05: 2011 Copyright © Unpublished Work - See page 1 for details. BOEING PROPRIETARY - 717-53A0034 28 of 34 ### Page 29 (OCR) BOEING SERVICE BULLETIN 717-53A0034 ALERT ALERT The step number shown below agrees with the number shown in the circle symbol in the figure. STEP TASK PROCEDURE NAME STATION LOCA- IDENTIFICATION | MORE DA- TION TA 1 Inspect General Visual Frame Sta. Y=674.000 9923405-503/-504 (a) (b) (c) Sta. Y=696.000 9923406-503/-504 Sta. Y=715.000 9923407-503/-504 (a) Do a General Visual inspection of the frame in the shaded area at all accessible locations using remote visual devices at Stations Y=674.000, Y=696.000 and Y=715.000 left and right sides. (b) Utilize adjacent lightening holes for the remote visual inspection looking for cracks propagating inboard and down from the upper radius of the frame tab. (c) Refer to NDTSPM 09-00-06 for remote visual device usage and NDTSPM 09-00-04 for current suppli- er/vendor information. FIGURE 1: DETAILED VISUAL INSPECTION - OVERWING FRAMES (SHEET 2 OF 2) Original Issue: October 05, 2011 717-53A0034 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 29 of 34 ### Page 30 (OCR) BOEING SERVICE BULLETIN 717-53A0034 ALERT ALERT STA Y=674:000 STA Y=696.000 - STA Y= 715.000 EDDY CURRENT PROBE STATION FRAME TYPICAL CRACK INSPECTON AREA FRP FRAME TAB LEFT SIDE SHOWN RIGHT SIDE OPPOSITE 2087539 FIGURE 2: EDDY CURRENT, HIGH FREQUENCY INSPECTION - OVERWING FRAMES (SHEET 1 OF 2) Original Issue: October 05, 2011 717-53A0034 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 30 of 34 ### Page 31 (OCR) BOEING SERVICE BULLETIN 717-53A0034 ALERT ALERT The step number shown below agrees with the number shown in the circle symbol in the figure. STEP TASK PROCEDURE NAME STATION LOCA- IDENTIFICATION ¡ MORE DA- TION TA Inspect Eddy Current, Frame Sta. Y=674.000 9923405-503/-504 (a) (b) (c) High Frequency Sta. Y=696.000 9923406-503/-504 Sta. Y=715.000 9923407-503/-504 (a) Do a ETHF inspection of the upper radius of the frame tab in the shaded area at Stations Y=674.000. Y=696.000 and Y=715.000 left and right sides. (b) Look for cracks propagating in the forward and aft direction. Refer to NDTSPM 06-10-01.001, Procedure 1, Calibration Method "G" and Scan Method "69". (c) Any indication 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 is considered a crack. FIGURE 2: EDDY CURRENT, HIGH FREQUENCY INSPECTION - OVERWING FRAMES (SHEET 2 OF 2) Original Issue: October 05, 2011 717-53A0034 Copyright © Unpublished Work - See page 1 for details. BOEING PROPRIETARY - 31 of 34 ### Page 32 (OCR) BOEING SERVICE BULLETIN 717-53A0034 ALERT ALERT • STA Y=674.000 - STA Y=696.000 STA Y= 715.000 STATION FRAME B FRP FRAME TAB LEFT SIDE SHOWN RIGHT SIDE OPPOSITE 2087535 FIGURE 3: BLEND-OUT REPAIR - FRAME TAB UPPER RADIUS (SHEET 1 OF 3) Original Issue: October 05, 2011 717-53A0034 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 32 of 34 ### Page 33 (OCR) BOEING SERVICE BULLETIN 717-53A0034 ALERT ALERT MAX 0.060 AREA OF POSSIBLE CRACK FRP _ 0.125 MAX 0.56/0.44R INBD B-B TYPICAL FRAME LOOKING FORWARD 2087538 FIGURE 3: BLEND-OUT REPAIR - FRAME TAB UPPER RADIUS (SHEET 2 OF 3) Original Issue: October 05, 2011 BOEING PROPRIETARY - 717-53A0034 Copyright © Unpublished Work - See page 1 for details. 33 of 34 ### Page 34 (OCR) BOEING SERVICE BULLETIN 717-53A0034 ALERT ALERT The step number shown below agrees with the number shown in the circle symbol in the figure. STEP TASK NAME IDENTIFICA- I QTY MORE DATA TION 1 Repair Frame (a) (b) (c) (d) (e) (1) (a) Repairable crack limit: Blend-out not deeper than 0.125 inch with minimum 0.44R and verify crack is re- moved. (b) Radius corners 0.060 / 0.030 Inch. (c) Surface finish: 63 micro-inch finish or better. (d) Glass bead peen or flap peen the frame tab surfaces following blend-out operation. Refer to SOPM 20- 10-10, as an accepted procedure. (e) For glass bead peening, it is recommended that the intensity should not be greater than 0.005A (0.015N) and the size of the glass beads shall be in the range of 83-165 (0.0083-0.016). (f) Apply Alodine and FR Primer on all bare metal surfaces. Refer to 717 SRM 51-10-04 as an accepted procedure. FIGURE 3: BLEND-OUT REPAIR - FRAME TAB UPPER RADIUS (SHEET 3 OF 3) Original Issue: October 05, 2011 BOEING PROPRIETARY - 717-53A0034 Copyright © Unpublished Work - See page 1 for details. 34 of 34 --- 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.