### 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. 9E991 ECCN: 

## 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 Unpublished Work.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, DreamlinerTM, 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 717-53A0034 Revision 1: November 07, 2012 1 of 36 3.0Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 05, 2011 717-53A0034 Revision 1: November 07, 2012 2 of 36 **BOEING SERVICE BULLETIN 717-53A0034 ALERT**  **ALERT**

BLANK PAGE**Table of Contents** Revision Transmittal Sheet............................................ 5 Summary...................................................... 7 1. PLANNING INFORMATION. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11 A. Effectivity. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11 1. Airplanes. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11 2. Spares Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11 B. Concurrent Requirements. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11 C. Reason. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 12 D. Description. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 12 E. Compliance. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13 F. Approval . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15 G. Manpower . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15 H. Weight and Balance Changes. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17 I. Electrical Load Data. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17 J. References. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17 1. Existing Data: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17 2. Data Supplied with this Service Bulletin:. . . . . . . . . . . . . . . . . . . . . . . . . . . 17 3. Installation Drawings Used in the Preparation of this Service Bulletin:. . . . . . . . . . . 18 K. Publications Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 18 L. Interchangeability and Intermixability of Parts. . . . . . . . . . . . . . . . . . . . . . . . . . . 18 M. Software Accomplishment Summary. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 18 2. MATERIAL INFORMATION. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19 A. Material - Price and Availability. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19 B. Industry Support Information. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19 C. Parts Necessary for Each Airplane. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19 1. Kits/Parts. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19 2. Parts and Materials Supplied by the Operator. . . . . . . . . . . . . . . . . . . . . . . . 22 3. Parts Modified and Reidentified. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 23 4. Parts Removed and Not Replaced. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 23 D. Parts Necessary to Change Spares. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 23 E. Special Tooling - Price and Availability. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 23 F. Special Tooling Necessary to do this Service Bulletin. . . . . . . . . . . . . . . . . . . . . . . 23 3. ACCOMPLISHMENT INSTRUCTIONS. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25 A. GENERAL INFORMATION. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25 B. WORK INSTRUCTIONS. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 26 FIGURE 1: DETAILED VISUAL INSPECTION - OVERWING FRAMES. . . . . . . . . . . . . . . . . 30 FIGURE 2: EDDY CURRENT, HIGH FREQUENCY INSPECTION - OVERWING FRAMES. . . . . . 32 FIGURE 3: BLEND-OUT REPAIR - FRAME TAB UPPER RADIUS. . . . . . . . . . . . . . . . . . . 34

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 05, 2011 717-53A0034 Revision 1: November 07, 2012 3 of 36 **BOEING SERVICE BULLETIN 717-53A0034 ALERT**  **ALERT**Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 05, 2011 717-53A0034 Revision 1: November 07, 2012 4 of 36 **BOEING SERVICE BULLETIN 717-53A0034 ALERT**  **ALERT**

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### Commercial **Airplanes** 

# 717 Service Bulletin **ALERT Revision Transmittal Sheet**  **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 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, 2011 Original Issue: November 07, 2012 Revision 1:

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 05, 2011 717-53A0034 Revision 1: November 07, 2012 5 of 36Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 05, 2011 717-53A0034 Revision 1: November 07, 2012 6 of 36 **BOEING SERVICE BULLETIN 717-53A0034 ALERT**  **ALERT**

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### Commercial **Airplanes** 

# 717 Service Bulletin **ALERT Summary**  **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. **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 717-53A0034 Revision 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 717-53A0034 Revision 1: November 07, 2012 8 of 36 **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.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 05, 2011 717-53A0034 Revision 1: November 07, 2012 9 of 36 **BOEING SERVICE BULLETIN 717-53A0034 ALERT**  **ALERT**Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 05, 2011 717-53A0034 Revision 1: November 07, 2012 10 of 36 **BOEING SERVICE BULLETIN 717-53A0034 ALERT**  **ALERT**

### 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

**DESCRIPTION CONFIGURATION**  **GROUP** 717-200 Airplanes

- 1

Airplane Models: 717-200 **Group Fuselage Num-**  **ber** 1 5002 - 5099 1 5100 - 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 717-53A0034 Revision 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 717-53A0034 Revision 1: November 07, 2012 12 of 36 **BOEING SERVICE BULLETIN 717-53A0034 ALERT**  **ALERT 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. **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. Revision 1 - No more work is necessary on airplanes changed in accordance with the original issue of this service bulletin. The work in this service bulletin is done in the maintenance zone(s) given below.
**Affected Maintenance Zones Zone**  **Model** 151, 161 717-200 **E. Compliance** Federal Aviation Administration (FAA) Notice of Proposed Rule Making (NPRM) 2011-NM-273-AD is related to this service bulletin. Accomplish the required action(s), based on the applicable condition(s), in Table 1, in accordance with Paragraph 3. Accomplishment Instructions.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 05, 2011 717-53A0034 Revision 1: November 07, 2012 13 of 36 **BOEING SERVICE BULLETIN 717-53A0034 ALERT**  **ALERT Table 1: Inspect Left and Right Side Overwing Frames for Cracks from Station 674 to 715**  **Repeat Interval (Not to Exceed)**  **Compliance Time (Whichever Occurs Later )**  **Action Condition** 

- Within 8275 flight cycles after the original issue dateon this service bulletin.Before the accumulation of 12,000 total flight cycles.Do a general visual inspection and a high frequency eddy current inspection of the overwing frames at the tab upper radius for cracks. All Airplanes

9,300 flight cycles.

- - Do repeat general visual in- spection and high frequency eddy current inspection. Condition 1 (No Crack Found on Any Frame) AND Do the action specified by Condition 1A or 1B. 9,300 flight cycles.

- - Do repeat general visual in- spection and high frequency eddy current inspection. Condition 1A (No Crack Found on Any Frame)

- - Before further flight. Establish the length of the crack and do the work specified by Condition 2 or Condition 3. Condition 1B (Crack Found on Any Frame)

- - Before further flight.Repair the cracked overwing frame. Condition 2 (Crack in Any Frame is Less Than 0.125 Inch in Length) AND 9,300 flight cycles.

- 9,300 flight cycles after repair.Do a general visual inspection and high frequency eddy current inspection of the repaired overwing frame. AND Do the action specified by Condition 2A or 2B. 9,300 flight cycles.

- - Do repeat general visual in- spection and high frequency eddy current inspection of the repaired overwing frame. Condition 2A (No Crack Found on Any Repaired Frame)

- - Before further flight. Do the work specified by Condition 3. Condition 2B (Crack Found on Any Repaired Frame)

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 05, 2011 717-53A0034 Revision 1: November 07, 2012 14 of 36 **BOEING SERVICE BULLETIN 717-53A0034 ALERT**  **ALERT Table 1: Inspect Left and Right Side Overwing Frames for Cracks from Station 674 to 715**  **Repeat Interval (Not to Exceed)**  **Compliance Time (Whichever Occurs Later )**  **Action Condition** 

- - Before further flight.Replace the cracked overwing frame. Condition 3 (Crack in Any Frame is Equal To or Greater Than 0.125 Inch in Length) AND 9,300 flight cycles.

- Within 12,000 flightcycles after replacement.Do a general visual inspection and high frequency eddy current inspection of the replaced overwing frame. AND Do the action specified by Condition 3A or 3B. 9,300 flight cycles.

- - Do repeat general visual in- spection and high frequency eddy current inspection of the replaced overwing frame. Condition 3A (No Crack Found on Any Replaced Frame)

- - Before further flight. Establish the length of the crack and do the work specified by Condition 2 or Condition 3. Condition 3B (Crack Found on Any Replaced Frame) **F. Approval** This service bulletin was examined by the Federal Aviation Administration (FAA). The changes specified in this service bulletin comply with the applicable regulations and are FAA approved, as well as European Aviation Safety Agency (EASA)/Joint Aviation Authorities (JAA) approved for all EASA/JAA approved airplanes listed in the service bulletin effectivity. This service bulletin and its approval were based on the airplane in its original Boeing delivery configuration or as modified by other approved Boeing changes. If an airplane has a non-Boeing modification or repair that affects a component or system also affected by this service bulletin, the operator is responsible for obtaining appropriate regulatory agency approval before incorporating this service bulletin. **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 • Time to cure the materials

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 05, 2011 717-53A0034 Revision 1: November 07, 2012 15 of 36 **BOEING SERVICE BULLETIN 717-53A0034 ALERT**  **ALERT**• Time to make the parts • Time to find the tools. **Condition 1 Elapsed Hours**  **Task Hours Number of Persons**  **Task** 5.0 20.0 4 Open Access 3.0 3.0 1 FIGURE 1 3.0 3.0 1 FIGURE 2 5.0 20.0 4 Close Access 16.0 46.0 TOTAL FOR EACH AIRPLANE
**NOTE:** Maximum total task hours and elapsed hours are given for inspection per airplane. **Condition 2 Elapsed Hours**  **Task Hours Number of Persons**  **Task** 5.0 20.0 4 Open Access 3.0 3.0 1 FIGURE 1 3.0 3.0 1 FIGURE 2 6.0 6.0 1 Remove Cusp Mem- brane 2.0 2.0 1 FIGURE 3 6.0 6.0 1 Install Cusp Mem- brane 5.0 20.0 4 Close Access 30.0 60.0 TOTAL FOR EACH AIRPLANE
**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 Elapsed Hours**  **Task Hours Number of Persons**  **Task** 5.0 20.0 4 Open Access 3.0 3.0 1 FIGURE 1 3.0 3.0 1 FIGURE 2 6.0 6.0 1 Remove Cusp Mem- brane 2.0 4.0 2 Defuel

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 05, 2011 717-53A0034 Revision 1: November 07, 2012 16 of 36 **BOEING SERVICE BULLETIN 717-53A0034 ALERT**  **ALERT Condition 3**  **Elapsed Hours Task Hours**  **Number of Persons Task**  10.0 20.0 2 Remove Frame 24.0 48.0 2 Install Frame 6.0 6.0 1 Install Cusp Mem- brane 5.0 20.0 4 Close Access 64.0 130.0 TOTAL FOR EACH AIRPLANE
**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. Boeing Fleet Team Digest (FTD) 717 FTD 53-09003. b. Boeing Drawing SE10000000. c. Federal Aviation Administration (FAA) Notice of Proposed Rule Making (NPRM) 2011-NM-273-AD. d. Non-Destructive Test Standard Practices Manual (NDTSPM) 06-10-01.001, 09-00-04, 09-00-06. e. Standard Overhaul Practices Manual (SOPM) 20-10-10. f. 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. g. 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. 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

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 05, 2011 717-53A0034 Revision 1: November 07, 2012 17 of 36 **BOEING SERVICE BULLETIN 717-53A0034 ALERT**  **ALERT**MS D800-0019 3855 Lakewood Boulevard Long Beach, California 90846 Phone: (562) 593-6996 Fax: (562) 593-2001 E-mail: dse.boecom@boeing.com a. Drawings:
**ADCN DCN/REV**  **Sheet Title**  **Drawing No**

- A DWG FRAME INSTL - OVERWING SERVICE REWORK DRAWING SR95530013
3. Installation Drawings Used in the Preparation of this Service Bulletin: None. **K. Publications Affected** 1. Publications: **Chapter-Section Publication**  53-00 Maintenance Planning Document 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. **M. Software Accomplishment Summary**

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 05, 2011 717-53A0034 Revision 1: November 07, 2012 18 of 36 **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** 
**Unit Price as of the original date** 

**of this Service Bulletin (US Dol**  **lars) ROLT as of the**  **original date of this Service Bul** 

**letin (Calendar Days)**  **Name Kit Number** 

$39,389.00 90 Service Kit SA95530034-3 39,389.00 90 Service Kit SA95530034-5 44,270.00 90 Service Kit SA95530034-7 44,270.00 90 Service Kit SA95530034-9 43,988.00 90 Service Kit SA95530034-11 43,988.00 90 Service Kit SA95530034-13 **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:
**Kit Station Frame**  SA95530034-3 Y=674.000, Left Side SA95530034-5 Y=674.000, Right Side SA95530034-7 Y=696.000, Left Side SA95530034-9 Y=696.000, Right Side

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 05, 2011 717-53A0034 Revision 1: November 07, 2012 19 of 36 **BOEING SERVICE BULLETIN 717-53A0034 ALERT**  **ALERT Kit**  **Station Frame** SA95530034-11 Y=715.000, Left Side SA95530034-13 Y=715.000, Right Side
**Kit SA95530034 Notes**  **Name QTY**  **New Part Number -13**  **-11 -9**  **-7 -5**  **-3** CLIP

. . . . 1 1 2913797-1 CLIP 1 1 1 1 1 1 2913870-1 CLIP 1 1 1 1

. . 2920753-1 CLIP

. . . . 1 1 2920754-501 CLIP 1

. . 1 1

. 2920756-1 CLIP

. 1 1

. . 1 2920756-2 (a) NUT ASSY 101 101 98 98 100 100 3D0006-3 (a) NUT ASSY 2 2 2 2 2 2 3D0006-4 CLIP

. . . . . 1 9919669-17 CLIP

. . . . 1

. 9919669-18 CLIP

. 1 1

. . . 9919671-17 CLIP 1

. . 1

. . 9919671-18 CLIP 1 1 1 1

. . 9919671-19 CLIP 1 1 1 1

. . 9919671-21 FRAME

. . . . . 1 9923405-503 FRAME

. . . . 1

. 9923405-504 FRAME

. . . 1

. . 9923406-503 FRAME

. . 1

. . . 9923406-504 FRAME

. 1

. . . . 9923407-503 FRAME 1

. . . . . 9923407-504 CLIP

. . . 1

. . 9971114-13 CLIP

. . 1

. . . 9971114-14 CLIP

. 1

. . . . 9971114-17 CLIP 1

. . . . . 9971114-18 PIN 2 2

. . 6 6 HLT435-6-10 PIN

. . . . 2 2 HLT435-6-11 PIN 1 1 1 1 1 1 HLT435-6-3

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 05, 2011 717-53A0034 Revision 1: November 07, 2012 20 of 36 **BOEING SERVICE BULLETIN 717-53A0034 ALERT**  **ALERT Kit SA95530034**  **Notes Name**  **QTY New Part Number**  **-13 -11**  **-9 -7**  **-5 -3**  PIN 3 3 3 3 3 3 HLT435-6-4 PIN 2 2 2 2 1 1 HLT435-6-5 PIN 36 36 36 36 23 23 HLT435-6-6 PIN 2 2 3 3 4 4 HLT435-6-7 PIN 12 12 15 15 16 16 HLT435-6-8 PIN 9 9 5 5 8 8 HLT435-6-9 PIN

. . . . 1 1 HLT436-10-8 PIN 2 2 2 2

. . HLT436-12-10 PIN

. . . . 2 2 HLT436-12-11 PIN 9 9 5 5 5 5 HLT436-6-2 PIN 14 14 18 18 11 11 HLT436-6-3 PIN 15 15 18 18 15 15 HLT436-6-4 PIN 19 19 21 21 15 15 HLT436-6-5 PIN 8 8 8 8 8 8 HLT436-6-6 PIN 2 2 2 2 1 1 HLT436-6-7 PIN 2 2 1 1 1 1 HLT436-6-8 PIN

. . . . 1 1 HLT436-6-9 PIN

. . 1 1

. . HLT436-8-6 PIN 4 4 3 3 2 2 HLT436-8-7 PIN 4 4 4 4 4 4 HLT436-8-8 PIN

. . . . 1 1 HLT436-8-9 PIN

. . . . 1 1 HLT439-6-4 PIN

. . . . 1 1 HLT439-6-5 PIN

. . . . 3 3 HLT439-6-8 RIVET 4 4 10 10 6 6 MS20470AD5-10D RIVET 15 15 21 21 6 6 MS20470AD5-11D RIVET 1 1 1 1 13 13 MS20470AD5-12D RIVET

. . . . 1 1 MS20470AD5-13D RIVET 11 11

. . . . MS20470AD5-8D RIVET 1 1

. . 6 6 MS20470AD5-9D RIVET

. . 1 1

. . MS20470AD6-12D

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 05, 2011 717-53A0034 Revision 1: November 07, 2012 21 of 36 **BOEING SERVICE BULLETIN 717-53A0034 ALERT**  **ALERT Kit SA95530034**  **Notes Name**  **QTY New Part Number**  **-13 -11**  **-9 -7**  **-5 -3**  RIVET 1 1

. . . . MS20470AD6-13D RIVET

. . . . 1 1 MS20470AD6-14D NUT 65 65 70 70 56 56 MS21042L3 NUT 6 6 6 6 5 5 MS21042L4 NUT

. . . . 1 1 MS21042L5 NUT 2 2 2 2 2 2 MS21042L6 (b) BOLT 2 2 2 2

. . NAS8803-4 WASHER 65 65 70 70 56 56 NAS1252-10L WASHER 6 6 6 6 5 5 NAS1252-416L WASHER

. . . . 1 1 NAS1252-516L WASHER 2 2 2 2 2 2 NAS1252-616L PIN

. . . . 4 4 S4931920-6-3 PIN 4 4 4 4

. . S4931920-6-4 PIN 2 2

. . . . S4931920-6-5 PIN 16 16

. . 10 10 S4931920-6-6 PIN 8 8 25 25 12 12 S4931920-6-7 PIN

. . 1 1 4 4 S4931920-6-8 (a) Or Approved Equivalent. Refer to AEPL Drawing 7595071. (b) Alternate part based on existing bolts. 2. Parts and Materials Supplied by the Operator
**Notes Name**  **QTY Part Number / Specification**  (a) Tape, Cloth Coated 1 Roll PC21F (DMS 1968 Type 2) OR Equivalent (b) Sealing Compound 1 Quart PR-1422 Class B-2 (DMS 2082) OR Equivalent (c) Tape, Adhesive, Double Faced 1 Roll Part Number 235 (DMS 1971) OR Equivalent

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 05, 2011 717-53A0034 Revision 1: November 07, 2012 22 of 36 **BOEING SERVICE BULLETIN 717-53A0034 ALERT**  **ALERT**CAGE Shurtape Technologies, Limited Liability Corporation (LLC) Can be purchased from: (a) 4L0S0 1506 Highland Avenue North East Hickory, North Carolina 28601 92108 PRC-DeSoto International, Incorporated Can be purchased from: (b) P.O. Box 1800 Sylmar, California 91342 3X706 Ideal Tape Company Can be purchased from: (c) 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 tool supply to make sure all necessary tools are available.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 05, 2011 717-53A0034 Revision 1: November 07, 2012 23 of 36 **BOEING SERVICE BULLETIN 717-53A0034 ALERT**  **ALERT**Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 05, 2011 717-53A0034 Revision 1: November 07, 2012 24 of 36 **BOEING SERVICE BULLETIN 717-53A0034 ALERT**  **ALERT**

BLANK PAGE**3. ACCOMPLISHMENT INSTRUCTIONS A. GENERAL INFORMATION**  **WARNING:** IF ELECTRICAL POWER IS APPLIED TO THE AIRPLANE, MAKE SURE YOU OBEY ALL PRECAUTIONS WHILE YOU DO WORK. IF YOU DO NOT OBEY THE PRECAUTIONS, DEATH OR INJURY TO PERSONS, AND DAMAGE TO THE AIRPLANE CAN OCCUR. **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 grip length in accordance with SRM Chapter 51. 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.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 05, 2011 717-53A0034 Revision 1: November 07, 2012 25 of 36 **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: **Operation Accepted Procedure**  Sealant - Maintenance Practices 717 AMM 20-60-01 Corrosion/Erosion Control and Prevention 717 SRM 51-10-04 Drilling and Countersinking 717 SRM 51-40-08 Repair Sealing 717 SRM 51-20-05 Installing Bolts, Screws, and Washers 717 SRM 51-41-01 Installing and Removing Rivets 717 SRM 51-41-02 Installing and Removing Lockbolts 717 SRM 51-41-03 Installing and Removing Hi-Lok Attachments 717 SRM 51-41-05 Fastener Substitution and Interchangeability 717 SRM 51-40-03
**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: **Accepted Procedure Item**  717 AMM 25-23-05 Passenger Seats 717 AMM 25-28-02 Panel,Cabin Sidewall 717 AMM 25-82-01 Passenger Compartment Insulation 717 AMM 52-21-01 Overwing Emergency Exit Doors

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 05, 2011 717-53A0034 Revision 1: November 07, 2012 26 of 36 **BOEING SERVICE BULLETIN 717-53A0034 ALERT**  **ALERT**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 as follows:
**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: **Condition 2A (No Crack Found on Any Repaired Frame)** (1) 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. **Condition 2B (Crack Found on Any Repaired Frame)** (1) Do the work of Condition 3.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 05, 2011 717-53A0034 Revision 1: November 07, 2012 27 of 36 **BOEING SERVICE BULLETIN 717-53A0034 ALERT**  **ALERT 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. 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.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 05, 2011 717-53A0034 Revision 1: November 07, 2012 28 of 36 **BOEING SERVICE BULLETIN 717-53A0034 ALERT**  **ALERT**11. Install all kept items and attaching parts, as applicable from Stations Y=674.000 to Y=715.000 **Accepted Procedure Item**  717 AMM 25-23-05 Passenger Seats 717 AMM 25-28-02 Passenger Compartment Lining 717 AMM 25-82-01 Passenger Compartment Insulation 717 AMM 52-21-01 Overwing Emergency Exit Doors 12. Put the airplane back to a serviceable condition.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 05, 2011 717-53A0034 Revision 1: November 07, 2012 29 of 36 **BOEING SERVICE BULLETIN 717-53A0034 ALERT**  **ALERT FIGURE 1: DETAILED VISUAL INSPECTION - OVERWING FRAMES**  **(SHEET 1 OF 2)**
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 05, 2011 717-53A0034 Revision 1 November 07, 2012 30 of 36 **BOEING SERVICE BULLETIN 717-53A0034 ALERT**  **ALERT**The step number shown below agrees with the number shown in the circle symbol in the figure.
**MORE DA TA**  **IDENTIFICATION STATION LOCA-**  **TION NAME**  **PROCEDURE TASK**  **STEP** (a) (b) (c) 9923405-503/-504 Sta. Y=674.000 Frame General Visual Inspect 1 9923406-503/-504 Sta. Y=696.000 9923407-503/-504 Sta. Y=715.000 (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 supplier/vendor information.

**FIGURE 1: DETAILED VISUAL INSPECTION - OVERWING FRAMES (SHEET 2 OF 2)** 
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 05, 2011 717-53A0034 Revision 1 November 07, 2012 31 of 36 **BOEING SERVICE BULLETIN 717-53A0034 ALERT**  **ALERT FIGURE 2: EDDY CURRENT, HIGH FREQUENCY INSPECTION - OVERWING FRAMES**  **(SHEET 1 OF 2)**
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 05, 2011 717-53A0034 Revision 1 November 07, 2012 32 of 36 **BOEING SERVICE BULLETIN 717-53A0034 ALERT**  **ALERT**The step number shown below agrees with the number shown in the circle symbol in the figure.
**MORE DA TA**  **IDENTIFICATION STATION LOCA-**  **TION NAME**  **PROCEDURE TASK**  **STEP** (a) (b) (c) 9923405-503/-504 Sta. Y=674.000 Frame Eddy Current, High Frequency Inspect 1 9923406-503/-504 Sta. Y=696.000 9923407-503/-504 Sta. Y=715.000 (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)** 
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 05, 2011 717-53A0034 Revision 1 November 07, 2012 33 of 36 **BOEING SERVICE BULLETIN 717-53A0034 ALERT**  **ALERT FIGURE 3: BLEND-OUT REPAIR - FRAME TAB UPPER RADIUS**  **(SHEET 1 OF 3)**
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 05, 2011 717-53A0034 Revision 1 November 07, 2012 34 of 36 **BOEING SERVICE BULLETIN 717-53A0034 ALERT**  **ALERT FIGURE 3: BLEND-OUT REPAIR - FRAME TAB UPPER RADIUS**  **(SHEET 2 OF 3)**
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 05, 2011 717-53A0034 Revision 1 November 07, 2012 35 of 36 **BOEING SERVICE BULLETIN 717-53A0034 ALERT**  **ALERT**The step number shown below agrees with the number shown in the circle symbol in the figure.
**MORE DATA QTY**  **IDENTIFICA- TION**  **NAME TASK**  **STEP** (a) (b) (c) (d) (e) (f) - - Frame Repair 1(a) Repairable crack limit: Blend-out not deeper than 0.125 inch with minimum 0.44R and verify crack is removed. (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)** 
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: October 05, 2011 717-53A0034 Revision 1 November 07, 2012 36 of 36 **BOEING SERVICE BULLETIN 717-53A0034 ALERT**  **ALERT**