### Commercial **Airplanes** 

# 717 Service Bulletin **ALERT Number: 717-53A0036**  Original Issue: August 12, 2013 ATA System: 5310 **SUBJECT:** FUSELAGE - Main Frame - Inspect Overwing Frame 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 © 2013 Boeing. Unpublished Work. All Rights Reserved. Treatment of this document and its content is governed by contract with Boeing. Rights to use this document are licensed on a per aircraft basis and such rights may not be transferable. For more information, contact The Boeing Company. Boeing, the Boeing signature, the Boeing symbol, 707, 717, 727, 737, 747, 757, 767, 777, 787, Dreamliner, BBJ, DC-8, DC-9, DC-10, KC-10, KC-46, KDC-10, MD-10, MD-11, MD-80, MD-88, MD-90, P-8, Poseidon and Boeing liveries are all trademarks owned by The Boeing Company; and no trademark license is granted in connection with this document unless provided in writing by Boeing.

Original Issue: August 12, 2013 717-53A0036 1 of 33 3.0Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 12, 2013 717-53A0036 2 of 33 **BOEING SERVICE BULLETIN 717-53A0036 ALERT**  **ALERT**

BLANK PAGE**Table of Contents** Summary...................................................... 5 1. PLANNING INFORMATION ........................................ 9 A. Effectivity................................................ 9 1. Airplanes............................................. 9 2. Spares Affected......................................... 9 B. Concurrent Requirements. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 10 C. Reason . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 10 D. Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 10 E. Compliance. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11 F. Approval . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13 G. Manpower . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14 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 4. Process Data: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 16 K. Publications Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 16 L. Interchangeability and Intermixability of Parts. . . . . . . . . . . . . . . . . . . . . . . . . . . 16 M. Software Accomplishment Summary. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 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. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25 FIGURE 1: OVERWING FRAME - GENERAL VISUAL INSPECTION. . . . . . . . . . . . . . . . . . 30 FIGURE 2: OVERWING FRAME - EDDY CURRENT HIGH FREQUENCY INSPECTION . . . . . . . 32

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 12, 2013 717-53A0036 3 of 33 **BOEING SERVICE BULLETIN 717-53A0036 ALERT**  **ALERT**Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 12, 2013 717-53A0036 4 of 33 **BOEING SERVICE BULLETIN 717-53A0036 ALERT**  **ALERT**

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### Commercial **Airplanes** 

# 717 Service Bulletin **ALERT Summary**  **Number: 717-53A0036** Original Issue: August 12, 2013 ATA System: 5310 **SUBJECT:** FUSELAGE - Main Frame - Inspect Overwing Frame 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** Thirteen 717 airplanes have been reported with cracked overwing frames at Stations Y=674.000, Y=696.000 and Y=715.000. The airplanes had between 18,235 - 36,208 flight-hours and 11,991 - 45,091 landing cycles. These cracked frames were addressed by Boeing Alert Service Bulletin 717-53A0034. Subsequent to the issuance of Boeing Alert Service Bulletin 717-53A0034, one 717 airplane has been reported with a cracked overwing frame, on the right side, at Station Y=737 which has a similar frame design. The airplane had accumulated 31,960 flight-hours and 22,025 landing cycles. The frame crack was found during accomplishment of a scheduled maintenance task that inspects the overwing floor beam-to-frame intersection. The crack, which originated in the upper radius of the frame inboard tab just below the floor, was caused by fatigue. All the noted frames are a part of 717 Principal Structural Element (PSE) 53.30.02.11. Inspection of the overwing frame at Stations Y=737, left and right sides, will determine if cracks exist. Depending on the length of any crack found, Boeing can provide frame repair and/or replacement instructions. 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 NOTE:**  Boeing recommends Alert Service Bulletin 717-53A0034, Revision1 be accomplished in conjunction with this service bulletin due to the short compliance time and proximity of the frame inspection area. This service bulletin gives instructions to do a General Visual Inspection (GVI) and an Eddy Current High Frequency (ETHF) inspection of the overwing frame at Station Y=737, left and right sides. Based on inspection results, do as follows:

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 12, 2013 717-53A0036 5 of 33**CONDITION 1: NO CRACK IN FRAME FOUND** 1. Do repetitive GVI and ETHF inspections of the overwing frame at Station 737 for cracks at the intervals specified in Paragraph 1.E., Compliance. **CONDITION 2: ANY CRACK IN FRAME FOUND LESS THAN .125 INCH IN LENGTH** 1. Option 1: Frame Repair a. Contact Boeing for repair instructions and do the repair when specified in Paragraph 1.E., Compliance. b. Do repetitive GVI and ETHF inspections of the repaired overwing frame as recommended by Boeing. 2. Option 2: Frame Replacement a. Replace the cracked overwing frame when specified in Paragraph 1.E., Compliance. b. Do repetitive GVI and ETHF inspections of the replaced overwing frame when specified in Paragraph 1.E., Compliance. **CONDITION 3: ANY CRACK FOUND IN FRAME EQUAL TO OR GREATER THAN .125 INCH IN LENGTH** 1. Replace the cracked overwing frame when specified in Paragraph 1.E., Compliance. 2. Do repetitive GVI and ETHF inspections of the replaced overwing frame when specified in Paragraph 1.E., Compliance. **EFFECTIVITY** All 717-200 Airplane(s). Refer to Paragraph 1.A.1., Airplanes, for the list of affected airplane(s). **COMPLIANCE** Refer to Paragraph 1.E., Compliance. **INDUSTRY SUPPORT INFORMATION** Boeing warranty remedies are not available for the inspection procedures given in this service bulletin. **MANPOWER** Refer to Paragraph 1.G., Manpower. **MATERIAL INFORMATION** Boeing Supplied Kits. 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: August 12, 2013 717-53A0036 6 of 33 **BOEING SERVICE BULLETIN 717-53A0036 ALERT**  **ALERT**Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 12, 2013 717-53A0036 7 of 33 **BOEING SERVICE BULLETIN 717-53A0036 ALERT**  **ALERT**Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 12, 2013 717-53A0036 8 of 33 **BOEING SERVICE BULLETIN 717-53A0036 ALERT**  **ALERT**

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### Commercial **Airplanes** 

# 717 Service Bulletin **ALERT Number: 717-53A0036**  Original Issue: August 12, 2013 ATA System: 5310 **SUBJECT:** FUSELAGE - Main Frame - Inspect Overwing Frame 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 This service bulletin is for the airplanes shown below.
**DESCRIPTION CONFIGURATION**  **GROUP** 717-200 Airplanes

- 1 Airplanes Not Initially Inspected in Accordance With Multi Operator Message (MOM) MOM-MOM-13-0375-01B 1
Airplanes Initially Inspected in Accordance With Multi Operator Message (MOM) MOM-MOM-13-0375-01B 2

Airplane Models:
717-200 **Group Fuselage Num-**  **ber** 1 5002 - 5099 1 5100 - 5156 2. Spares Affected None.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 12, 2013 717-53A0036 9 of 33**B. Concurrent Requirements** None. **C. Reason** Thirteen 717 airplanes have been reported with cracked overwing frames at Stations Y=674.000, Y=696.000 and Y=715.000. The airplanes had between 18,235 - 36,208 flight-hours and 11,991 - 45,091 landing cycles. These cracked frames were addressed by Boeing Alert Service Bulletin 717-53A0034. Subsequent to the issuance of Boeing Alert Service Bulletin 717-53A0034, one 717 airplane has been reported with a cracked overwing frame, on the right side, at Station Y=737 which has a similar frame design. The airplane had accumulated 31,960 flight-hours and 22,025 landing cycles. The frame crack was found during accomplishment of a scheduled maintenance task that inspects the overwing floor beam-to-frame intersection. The crack, which originated in the upper radius of the frame inboard tab just below the floor, was caused by fatigue. All the noted frames are a part of 717 Principal Structural Element (PSE) 53.30.02.11. Inspection of the overwing frame at Stations Y=737, left and right sides, will determine if cracks exist. Depending on the length of any crack found, Boeing can provide frame repair and/or replacement instructions. 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. **D. Description NOTE:**  Boeing recommends Alert Service Bulletin 717-53A0034, Revision1 be accomplished in conjunction with this service bulletin due to the short compliance time and proximity of the frame inspection area. This service bulletin gives instructions to do a General Visual Inspection (GVI) and an Eddy Current High Frequency (ETHF) inspection of the overwing frame at Station Y=737, left and right sides. Based on inspection results, do as follows: **CONDITION 1: NO CRACK IN FRAME FOUND** 1. Do repetitive GVI and ETHF inspections of the overwing frame at Station 737 for cracks at the intervals specified in Paragraph 1.E., Compliance. **CONDITION 2: ANY CRACK IN FRAME FOUND LESS THAN .125 INCH IN LENGTH** 1. Option 1: Frame Repair a. Contact Boeing for repair instructions and do the repair when specified in Paragraph 1.E., Compliance. b. Do repetitive GVI and ETHF inspections of the repaired overwing frame as recommended by Boeing. 2. Option 2: Frame Replacement a. Replace the cracked overwing frame when specified in Paragraph 1.E., Compliance.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 12, 2013 717-53A0036 10 of 33 **BOEING SERVICE BULLETIN 717-53A0036 ALERT**  **ALERT**b. Do repetitive GVI and ETHF inspections of the replaced overwing frame when specified in Paragraph 1.E., Compliance. **CONDITION 3: ANY CRACK FOUND IN FRAME EQUAL TO OR GREATER THAN .125 INCH IN LENGTH**  1. Replace the cracked overwing frame when specified in Paragraph 1.E., Compliance. 2. Do repetitive GVI and ETHF inspections of the replaced overwing frame when specified in Paragraph 1.E., Compliance. 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** 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. Accomplish the required action(s), based on the applicable condition(s), in Table 1 or Table 2, in accordance with Paragraph 3. Accomplishment Instructions. When more than one OPTION is given for a CONDITION, do only one of the OPTION numbers. When more than one ACTION is given for a CONDITION number or an OPTION number, do all of the ACTION numbers for that CONDITION number or OPTION number. **Group 1, Configuration 1:**
**TABLE 1: LEFT AND RIGHT SIDE OVERWING FRAME AT STATION 737 - INSPECTION Repeat Interval**  **(Not to Exceed) Compliance Time (Whichever Occurs**  **Later ) Action**  **Condition**

- Within 6000 flight cycles after the original issue dateof this service bulletin. Before 12,000 total flight cycles.Do a General Visual Inspection and a Eddy Current High Frequency inspection of the left and right side overwing frames at Sta. 737 for cracks. ALL AIRPLANES

9,300 flight cycles.

- Within 9,300 flight cycles after initial inspection.Do General Visual Inspections and Eddy Current High Frequency inspections of the left and right side overwing frames at Sta. 737 for cracks. CONDITION 1: NO CRACK IN FRAME FOUND

(a)

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 12, 2013 717-53A0036 11 of 33 **BOEING SERVICE BULLETIN 717-53A0036 ALERT**  **ALERT Group 1, Configuration 1:** 
**TABLE 1: LEFT AND RIGHT SIDE OVERWING FRAME AT STATION 737 - INSPECTION Repeat Interval**  **(Not to Exceed) Compliance Time (Whichever Occurs**  **Later ) Action**  **Condition** Repeat inspectionof repaired overwing frame as recommended by Boeing. - Before further flight. OPTION 1: Contact Boeing for repair instructions and do the repair. CONDITION 2: ANY CRACK IN FRAME FOUND LESS THAN .125 INCH IN LENGTH

- - Before further flight. OPTION 2 (ACTION 1):Replace the cracked overwing frame. 9,300 flight cycles.

- Within 12,000 flightcycles after replacement. OPTION 2 (ACTION 2): Do General Visual Inspectionsand Eddy Current High Frequency inspections of the replaced overwing frame. (a)

- - Before further flight. (ACTION 1) Replace the cracked overwing frame. CONDITION 3: ANY CRACK FOUND IN FRAME EQUAL TO OR GREATER THAN .125 INCH IN LENGTH 9,300 flight cycles.

- Within 12,000 flightcycles after replacement.(ACTION 2) Do General Visual Inspections and EddyCurrent High Frequency inspections of the replaced overwing frame. (a) (a) If cracks are found during the repetitive inspections, do the work specified in Condition 2 or Condition 3. **Group 1, Configuration 2:**
**TABLE 2: LEFT AND RIGHT SIDE OVERWING FRAME AT STATION 737 - INSPECTION Repeat Interval**  **(Not to Exceed) Compliance Time**  **Action Condition** 

- - Within 9,300 flightcycles after overwing frame inspection at Sta. 737 or within 12,000 flightcycles after replacement.Do a General Visual Inspection and a Eddy Current High Frequency inspection of the left and right side overwing frame at Sta. 737 for cracks. ALL AIRPLANES

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 12, 2013 717-53A0036 12 of 33 **BOEING SERVICE BULLETIN 717-53A0036 ALERT**  **ALERT Group 1, Configuration 2:** 
**TABLE 2: LEFT AND RIGHT SIDE OVERWING FRAME AT STATION 737 - INSPECTION Repeat Interval**  **(Not to Exceed) Compliance Time**  **Action Condition**  9,300 flight cycles.

- Within 9,300 flight cycles after initial inspection.Do General Visual Inspections and Eddy Current High Frequency inspections of the left and right side overwing frame at Sta. 737 for cracks. CONDITION 1: NO CRACK IN FRAME FOUND

(a) Repeat inspectionof repaired overwing frame as recommended by Boeing. - Before further flight. OPTION 1: Contact Boeing for repair instructions and do the repair. CONDITION 2: ANY CRACK IN FRAME FOUND LESS THAN .125 INCH IN LENGTH

- - Before further flight. OPTION 2 (ACTION 1):Replace the cracked overwing frame. 9,300 flight cycles.

- Within 12,000 flightcycles after replacement. OPTION 2 (ACTION 2): Do General Visual Inspectionsand Eddy Current High Frequency inspections of the replaced overwing frame. (a)

- - Before further flight. (ACTION 1) Replace the cracked overwing frame. CONDITION 3: ANY CRACK FOUND IN FRAME EQUAL TO OR GREATER THAN .125 INCH IN LENGTH 9,300 flight cycles.

- Within 12,000 flightcycles after replacement.(ACTION 2) Do General Visual Inspections and EddyCurrent High Frequency inspections of the replaced overwing frame. (a) (a) If cracks are found during the repetitive inspections, do the work specified in Condition 2 or 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 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.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 12, 2013 717-53A0036 13 of 33 **BOEING SERVICE BULLETIN 717-53A0036 ALERT**  **ALERT G. Manpower**  The tables below show an estimate of the task hours necessary to do the inspections and frame replacement 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 • Time to make the parts • Time to find the tools. **CONDITION 1: Elapsed Hours**  **Task Hours Number of Persons**  **Task** 2.5 10.0 4 Open Access 1.0 1.0 1 FIGURE 1 1.0 1.0 1 FIGURE 2 2.5 10.0 4 Close Access 7.0 22.0 TOTAL FOR EACH AIRPLANE
**NOTE:** Maximum total Task Hours and Elapsed Hours are given for the initial and repetitive inspection of each airplane. Condition 2, Option 1: Maximum total Task Hours and Elapsed Hours are based on repair instructions from Boeing and are to be estimated by the operator. **Condition 2, Option 2 or Condition 3: Elapsed Hours**  **Task Hours Number of Persons**  **Task** 5.0 20.0 4 Open Access 1.0 1.0 1 FIGURE 1 1.0 1.0 1 FIGURE 2 6.0 6.0 1 Remove Cusp Mem- brane 2.0 4.0 2 Defuel 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

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 12, 2013 717-53A0036 14 of 33 **BOEING SERVICE BULLETIN 717-53A0036 ALERT**  **ALERT Condition 2, Option 2 or Condition 3:**  **Elapsed Hours Task Hours**  **Number of Persons Task**  60.0 126.0 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 to replace the other frame 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. Multi Operator Message (MOM) MOM-MOM-13-0375-01B b. Boeing Service Bulletin 717-53A0034, Revision 1 c. Boeing Drawings, 5940477, 7595071, 9910151, SE10000000 d. Non-Destructive Test Standard Practices Manual (NDTSPM), Document Number MDC93K0393, Part 06 Eddy Current: 06-10-01.001 (Procedure 1 - Surface Defect Detection), Part 09 Visual/Optical: 09-00-04 (Suppliers/Vendors), Part 09 Visual/Optical: 09-00-06 (Process Examples), Part 09 Visual/Optical: 09-00-07 (Evaluation/Verification) e. 717 Aircraft Maintenance Manual (AMM) 07-20-01, 12-11-01, 20-60-01, 20-60-26, 25-23-05, 25-28-02, 25-82-01, 52-21-01, 53-21-01, 53-53-01 f. 717 Fleet Team Digest (FTD) 53-09003 g. 717 Structural Repair Manual (SRM) 51, 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 MS D800-0019 3855 Lakewood Boulevard Long Beach, California 90846 Phone: (562) 593-6996 Fax: (562) 593-2001

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 12, 2013 717-53A0036 15 of 33 **BOEING SERVICE BULLETIN 717-53A0036 ALERT**  **ALERT**E-mail: dse.boecom@boeing.com a. Drawings:
**ADCN DCN/REV**  **Sheet Title**  **Drawing No**

- B DWG COVER INSTL CUSP HOLE 5940477

- CH DWG CUSP AND MEMBRANE INSTL - STA 484 TO 623 9910151

- - DWG FRAME INSTL - OVERWING SERVICE REWORK DRAWING SR95530016

3. Installation Drawings Used in the Preparation of this Service Bulletin: None. 4. Process Data: Douglas Process Specifications referred to on the drawings and in the Work Instructions are not given in this service bulletin since these procedures are frequently used as standard shop practices.

**K. Publications Affected** 1. Publications: None. 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. DTI requirements for the structure affected are contained in Paragraph 1.E., Compliance of this service bulletin. **L. Interchangeability and Intermixability of Parts** Accomplishment of this service bulletin does not affect interchangeability or intermixability of parts. **M. Software Accomplishment Summary** Not affected.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 12, 2013 717-53A0036 16 of 33 **BOEING SERVICE BULLETIN 717-53A0036 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** 

$41,530.00 90 Days Frame Instl Kit - LHS - Station 737 SA95530036-3 $41,530.00 90 Days Frame Instl Kit - RHS - Station 737 SA95530036-5

**B. Industry Support Information** Boeing warranty remedies are not available for the inspection procedures given in this service bulletin. **C. Parts Necessary for Each Airplane** 1. Kits/Parts Condition 1, Condition 2, Option 1 None. Condition 2, Option 2 and Condition 3
**Kit SA95530036 Notes**  **Existing Part Number**  **Name QTY**  **New Part Number -5**  **-3** Frame Instl Kit - LHS - Station 737 . - SA95530036-3

Frame Instl Kit - RHS - Station 737 - . SA95530036-5

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 12, 2013 717-53A0036 17 of 33 **BOEING SERVICE BULLETIN 717-53A0036 ALERT**  **ALERT Kit SA95530036**  **Notes Existing Part**  **Number Name**  **QTY New Part Number**  **-5 -3**  (a) CLIP 1 1 2913870-1 CLIP

. 1 2920756-1 CLIP 1

. 2920756-2 (c) NUT ASSY 94 94 3D0006-3 (c) NUT ASSY 3 3 3D0006-4 (a) CLIP 1 1 9919672-19 CLIP

. 1 9919672-23 CLIP 1

. 9919672-24 CLIP 1 1 9919672-63 SPACER 1 1 9919672-7 FRAME

. 1 9923408-503 FRAME 1

. 9923408-504

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 12, 2013 717-53A0036 18 of 33 **BOEING SERVICE BULLETIN 717-53A0036 ALERT**  **ALERT Kit SA95530036**  **Notes Existing Part**  **Number Name**  **QTY New Part Number**  **-5 -3**  (b) PIN 4 4 HLT435-6-4 PIN 1 1 HLT435-6-7 PIN 5 5 HLT435-6-8 PIN 1 1 HLT435-8-6 PIN 2 2 HLT435-8-7 PIN 2 2 HLT436-6-2 PIN 11 11 HLT436-6-3 PIN 4 4 HLT436-6-4 PIN 22 22 HLT436-6-5 PIN 4 4 HLT436-6-6 PIN 4 4 HLT436-6-7 PIN 4 4 HLT436-6-8 PIN 4 4 HLT436-6-9 PIN 9 9 HLT436-8-5 PIN 2 2 HLT436-8-7 PIN 2 2 HLT439-6-5 PIN 29 29 HLT439-6-6 PIN 8 8 HLT439-6-7 PIN 15 15 HLT439-6-8 RIVET 2 2 MS20470AD5-10D RIVET 12 12 MS20470AD5-11D RIVET 5 5 MS20470AD5-12D RIVET 13 13 MS20470AD5-13D RIVET 1 1 MS20470AD6-14D NUT 55 55 MS21042L3 NUT 11 11 MS21042L4 (b) RIVET 1 1 NAS1097AD6-12D WASHER 55 55 NAS1252-10L WASHER 11 11 NAS1252-416L (b) (c) PIN 4 4 S4931920-6-6 PIN 26 26 S4931920-6-8

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 12, 2013 717-53A0036 19 of 33 **BOEING SERVICE BULLETIN 717-53A0036 ALERT**  **ALERT Kit SA95530036**  **Notes Existing Part**  **Number Name**  **QTY New Part Number**  **-5 -3**  (a) Some Boeing parts are supplied in a temporary configuration. Those parts areidentified 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. (b) If grip length shown is not available at Boeing, fasteners supplied in kits may be one grip length longer than indicated. Also, if any fasteners part numbers listed are not available or have been superseded, substitute fasteners may be supplied in kits. (c) Or approved equivalent. Refer to Approved Equivalent Parts List Drawing (AEPL) 7595071. 2. Parts and Materials Supplied by the Operator **NOTE:** If removal of the 9910151 Membranes are necessary for overwing frame inspection/replacement, operator's should refer to the 9910151 Drawing for the fasteners and materials necessary to reinstall the membranes.
**Notes Name**  **QTY Part Number / Specification**  (a) Tape, Cloth Coated, Pressure Sensi- tive 1 Roll Polyken 225 or Polyken 225FR (DMS 1968-2, Type 2) OR Equivalent OR (b) Tape, Adhesive, Insulation Cover Splicing Orcon OT-16A (DMS 1984, Type 6, Class 2) OR Equivalent (c) Sealing Compound 1 Quart PR-1422 Class B-2 (DMS 2082) OR Equivalent (d) Tape, Adhesive, Double Faced 1 Roll 235 (DMS 1971) OR Equivalent (a) Can be purchased from: Covalence Specialty Adhesives Limited Liability Corporation (LLC) (CAGE: 80769), 25 Forge Parkway, Franklin, Massachusetts 02038. (b) Can be purchased from: Orcon Corporation (CAGE: 1WFJ0), 1570 Atlantic Street, Union City, California 94587. (c) Can be purchased from: PRC-DeSoto International, Incorporated (CAGE: 92108), 12780 San Fernando Road, Sylmar, California 91342.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 12, 2013 717-53A0036 20 of 33 **BOEING SERVICE BULLETIN 717-53A0036 ALERT**  **ALERT Notes**  **Name QTY**  **Part Number / Specification** (d) Can be purchased from: Ideal Tape Company (CAGE: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** The operator can supply the tools shown in Paragraph 2.F., Special Tooling Necessary to do this Service Bulletin. Tool price and supply data are not given. **F. Special Tooling Necessary to do this Service Bulletin** General Visual Inspection (GVI) equipment and Eddy Current High Frequency (ETHF) inspection equipment necessary 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.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 12, 2013 717-53A0036 21 of 33 **BOEING SERVICE BULLETIN 717-53A0036 ALERT**  **ALERT**Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 12, 2013 717-53A0036 22 of 33 **BOEING SERVICE BULLETIN 717-53A0036 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 SRM 51. 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. Unless shown differently, these dimensions and tolerances are used: – Linear dimensions are in inches – Tolerance on linear dimensions, other than rivet and bolt edge margins, is plus or minus 0.03 inch. – Tolerance on rivet and bolt edge margin is plus or minus 0.05 inch – Angular tolerance is plus or minus 2 degrees – Hole dimensions for standard solid rivets are in 717 SRM 51. – Torque Values:

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 12, 2013 717-53A0036 23 of 33 **BOEING SERVICE BULLETIN 717-53A0036 ALERT**  **ALERT**— Values for structural fasteners are given in 717 Structural Repair Manual, Chapter 51. — Values for airframe maintenance tasks are included in Chapter 20 of 717 Airplane Maintenance Manual (AMM). — Values for electrical maintenance tasks are included in Chapter 20 of Standard Wiring Practices Manual (SWPM). — Values for engine maintenance tasks are included in Chapter 70 of 717 Airplane Maintenance Manual (AMM). — Non-standard torque values for maintenance tasks are included in the applicable installation step.
8. Obey all of the warnings and cautions given in the specified manual sections. 9. 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. 10. 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. 11. If it is necessary to remove more parts for access, you can remove those parts. If you can get access without removing identified parts, it is not necessary to remove all of the identified parts. Jacking and shoring limitations must be observed. 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. 13. 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. 14. If shading is used, shaded areas in Figures are reference only. Shaded areas in Figures may look different than your airplane. 15. Boeing recommends Alert Service Bulletin 717-53A0034, Revision1 be accomplished in conjunction with this service bulletin due to the short compliance time and proximity of the overwing frame inspection area.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 12, 2013 717-53A0036 24 of 33 **BOEING SERVICE BULLETIN 717-53A0036 ALERT**  **ALERT**16. Some steps in the Work Instructions are identified as Required for Compliance (RC). If this service bulletin is mandated by an Airworthiness Directive (AD), then the steps identified as RC must be done to comply with the AD. Alternative procedures for steps not identified with RC can be used if the RC steps can still be done as specified, and the airplane can be put back in a serviceable condition. An Alternative Method of Compliance (AMOC) is not necessary for deviations to steps that are not identified as RC. 17. 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 Repair Sealing 717 SRM 51-20-05 Fastener Substitution and Interchangeability 717 SRM 51-40-03 Drilling, Countersinking, and Dimpling 717 SRM 51-40-08 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 Fasteners 717 SRM 51-41-05
**B. WORK INSTRUCTIONS** 1. Remove and keep passenger compartment items and attaching parts, as necessary, to get access to the overwing frame inspection area at Station Y=737, on the left and right sides. Refer to Table 1 for a list of AMM accepted procedures:
**TABLE 1 Accepted Procedure**  **Item** 717 AMM 25-23-05 Seats, Passenger 717 AMM 25-28-02 Panel, Cabin Sidewall 717 AMM 25-82-01 Insulation, Passenger Compartment 717 AMM 52-21-01 Door, Overwing Emergency Exit 717 AMM 20-60-26 Floor Coverings 717 AMM 53-21-01 Floor Panels, Passenger Compartment 2. Remove the tape from the cutout between the cusp membrane and frame to get access to each frame inspection area. 3. Remove and keep the cusp membrane to get access to frame inspection area. Use operator's standard shop practices.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 12, 2013 717-53A0036 25 of 33 **BOEING SERVICE BULLETIN 717-53A0036 ALERT**  **ALERT NOTE:**  Removal of the cusp membrane may not be necessary if it is determined that there is sufficient access to do the inspections that follow. 4. RC - Do a General Visual Inspection (GVI) and an Eddy Current, High Frequency (ETHF) inspection of the overwing frame at Station Y=737 for cracks, on the left and right sides, in accordance with FIGURE 1 and FIGURE 2. 5. CONDITION 1: NO CRACK IN FRAME FOUND: a. If removed, install the kept cusp membrane for each frame. Use operator's standard shop practices. **NOTE:** Refer to Boeing Drawing 9910151 for installation fasteners and materials. b. Apply DMS 1968, Type 2, Cloth Coated Tape or DMS 1984, Type 6, Class 2, Adhesive Tape from the cutout in the cusp membrane to the overwing frame at Station Y=737 to control the flow of cabin air. Strips of tape may be overlapped to nest in and around the frame and extend 1 1/2 inches minimum onto the membrane and overwing frame. The tape may be split or applied in strips to close the openings around conduit passing through the membrane in the area noted on the drawing. Refer to Boeing Drawing 5940477 and DPS 2.590-4 as an accepted procedure. c. Install the kept passenger compartment items and attaching parts removed to get access to the overwing frame inspection area at Station Y=737, on the left and right sides. d. Put the airplane back to a serviceable condition. e. RC - Do repetitive GVI and ETHF inspections of the overwing frame at Station Y=737 for cracks, on the left and right sides, in accordance with FIGURE 1 and FIGURE 2. 6. CONDITION 2: ANY CRACK IN FRAME FOUND LESS THAN .125 INCH IN LENGTH a. Option 1: Frame Repair (1) RC - Contact Boeing for repair instructions and do the repair. (2) Put the airplane back to a serviceable condition. (3) RC - Do repetitive inspections of the repaired overwing frame at Station Y=737 for cracks, on the left and right sides, as recommended by Boeing. b. Option 2: Frame Replacement (1) Defuel the airplane. Refer to 717 AMM 12-11-01 as an accepted procedure. **CAUTION:** OPERATORS SHOULD SUSPEND ANY MAINTENANCE PROCEDURES THAT WOULD AFFECT THE AIRFRAME LOADS DURING THE OVERWING FRAME REPLACEMENT. IF SUCH MAINTENANCE PROCEDURES ARE NOT SUSPENDED, DAMAGE TO THE AIRFRAME CAN OCCUR. (2) Support the airplane as follows:

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 12, 2013 717-53A0036 26 of 33 **BOEING SERVICE BULLETIN 717-53A0036 ALERT**  **ALERT**(a) If both the left and right sides of the overwing frame are cracked, operators should replace the cracked frame on one side of the airplane before starting the replacement of the opposite side while the airplane is on its wheels. (b) Shoring of the airplane is necessary if the frames on both sides of the airplane are to be replaced at the same time. Refer to 717 AMM 07-20-01 as an accepted procedure. (3) In the passenger compartment, remove and keep additional interior items and attaching parts between L9 and L18, on the left and/or right sides, to get access to the cracked overwing frame at Station Y=737. (4) Remove and keep the cusp membrane to get access to overwing frame replacement area. Use operator's standard shop practices. (5) Remove and keep the applicable wing to fuselage fillet panel,150FL on the left side and/or 160FR on the right side, to get access to the cracked overwing frame exterior. Refer to 717 AMM 53-53-01 as an accepted procedure. (6) RC - Replace cracked overwing frame in accordance with Service Rework Drawing SR95530016, Revision Level New. (7) Install the kept cusp membrane for each frame. Use operator's standard shop practices. **NOTE:** Refer to Boeing Drawing 9910151 for installation fasteners and materials. (8) Apply DMS 1968, Type 2, Cloth Coated Tape or DMS 1984, Type 6, Class 2, Adhesive Tape from the cutout in the cusp membrane to the overwing frame at Station Y=737 to control the flow of cabin air. Strips of tape may be overlapped to nest in and around the frame and extend 1 1/2 inches minimum onto the membrane and overwing frame. The tape may be split or applied in strips to close the openings around conduit passing through the membrane in the area noted on the drawing. Refer to Boeing Drawing 5940477 and DPS 2.590-4 as an accepted procedure. (9) Install the kept passenger compartment items and attaching parts between L9 and L18, on the left and/or right sides, removed to get access to the cracked overwing frame at Station Y=737. Refer to Table 2 for a list of accepted AMM procedures.
**TABLE 2 Accepted Procedure**  **Item** 717 AMM 25-23-05 Seats, Passenger 717 AMM 25-28-02 Panel, Cabin Sidewall 717 AMM 25-82-01 Insulation, Passenger Compartment 717 AMM 52-21-01 Door, Overwing Emergency Exit 717 AMM 20-60-26 Floor Coverings 717 AMM 53-21-01 Floor Panels, Passenger Compartment

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 12, 2013 717-53A0036 27 of 33 **BOEING SERVICE BULLETIN 717-53A0036 ALERT**  **ALERT**(10) Install the kept applicable wing to fuselage fillet panel,150FL on the left side and/or 160FR on the right side, removed to get access to the cracked overwing frame exterior. Refer to 717 AMM 53-53-01 as an accepted procedure. (11) Put the airplane back to a serviceable condition. (12) RC - Do repetitive GVI and ETHF inspections of the overwing frame at Station Y=737 for cracks, on the left and right sides, in accordance with FIGURE 1 and FIGURE 2. 7. CONDITION 3: ANY CRACK FOUND IN FRAME EQUAL TO OR GREATER THAN .125 INCH IN LENGTH a. Defuel the airplane. Refer to 717 AMM 12-11-01 as an accepted procedure. **CAUTION:** OPERATORS SHOULD SUSPEND ANY MAINTENANCE PROCEDURES THAT WOULD AFFECT THE AIRFRAME LOADS DURING THE OVERWING FRAME REPLACEMENT. IF SUCH MAINTENANCE PROCEDURES ARE NOT SUSPENDED, DAMAGE TO THE AIRFRAME CAN OCCUR. b. Support the airplane as follows: (1) If both the left and right sides of the overwing frame are cracked, operators should replace the cracked frame on one side of the airplane before starting the replacement of the opposite side while the airplane is on its wheels. (2) Shoring of the airplane is necessary if the frames on both sides of the airplane are to be replaced at the same time. Refer to 717 AMM 07-20-01 as an accepted procedure. c. In the passenger compartment, remove and keep additional interior items and attaching parts between L9 and L18, on the left and/or right sides, to get access to the cracked overwing frame at Station Y=737. d. Remove and keep the cusp membrane to get access to frame replacement area. Use operator's standard shop practices. e. Remove and keep the applicable wing to fuselage fillet panel,150FL on the left side and/or 160FR on the right side, to get access to the cracked overwing frame exterior. Refer to 717 AMM 53-53-01 as an accepted procedure. f. RC - Replace cracked overwing frame in accordance with Service Rework Drawing SR95530016, Revision Level New. g. Install the kept cusp membrane for each frame. Use operator's standard shop practices. **NOTE:** Refer to Boeing Drawing 9910151 for installation fasteners and materials. h. Apply DMS 1968, Type 2, Cloth Coated Tape or DMS 1984, Type 6, Class 2, Adhesive Tape from the cutout in the cusp membrane to the overwing frame at Station Y=737 to control the flow of cabin air. Strips of tape may be overlapped to nest in and around the frame and extend 1 1/2 inches minimum onto the membrane and overwing frame. The tape may be split or applied in strips to close the openings around conduit passing through the membrane in the area noted on the drawing. Refer to Boeing Drawing 5940477 and DPS 2.590-4 as an accepted procedure.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 12, 2013 717-53A0036 28 of 33 **BOEING SERVICE BULLETIN 717-53A0036 ALERT**  **ALERT**i. Install the kept passenger compartment items and attaching parts between L9 and L18, on the left and/or right sides, removed to get access to the cracked overwing frame at Station Y=737. Refer to Table 2 for a list of accepted AMM procedures.
**TABLE 2 Accepted Procedure**  **Item** 717 AMM 25-23-05 Seats, Passenger 717 AMM 25-28-02 Panel, Cabin Sidewall 717 AMM 25-82-01 Insulation, Passenger Compartment 717 AMM 52-21-01 Door, Overwing Emergency Exit 717 AMM 20-60-26 Floor Coverings 717 AMM 53-21-01 Floor Panels, Passenger Compartment j. Install the kept applicable wing to fuselage fillet panel,150FL on the left side and/or 160FR on the right side, removed to get access to the cracked overwing frame exterior. Refer to 717 AMM 53-53-01 as an accepted procedure. k. Put the airplane back to a serviceable condition. l. RC - Do repetitive GVI and ETHF inspections of the overwing frame at Station Y=737 for cracks, on the left and right sides, in accordance with FIGURE 1 and FIGURE 2.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 12, 2013 717-53A0036 29 of 33 **BOEING SERVICE BULLETIN 717-53A0036 ALERT**  **ALERT FIGURE 1: OVERWING FRAME - GENERAL VISUAL INSPECTION**  **(SHEET 1 OF 2)**
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 12, 2013 717-53A0036 30 of 33 **BOEING SERVICE BULLETIN 717-53A0036 ALERT**  **ALERT**The step number shown below agrees with the number shown in the circle symbol in the figure.
**MORE DATA IDENTIFICATION**  **NAME PROCEDURE**  **TASK STEP**  (a) (b) (c) (d) 9923408-503/-504 Frame General Visual (GVI) Inspect 1 (a) Do a General Visual Inspection of the overwing frame in the inspection area. Use of remote visual devices to access all locations is acceptable. (b) Use adjacent lightening holes for the remote visual inspection. Look for cracks that start inboard and down from the upper radius of the frame tab. (c) Refer to NDTSPM Part 09 Visual/Optical: 09-00-06 (Process Examples) for remote visual deviceusage and NDTSPM Part 09 Visual/Optical: 09-00-04 (Suppliers/Vendors) for current supplier/vendor information.(d) Refer to NDTSPM Part 09 Visual/Optical: 09-00-07 (Evaluation/Verification) for general information on how to evaluate a suspect indication of a defect. Refer to Owner Operator Manual of specific device on its operation to aid in the discovery and sizing of any suspected defect.

**FIGURE 1: OVERWING FRAME - GENERAL VISUAL INSPECTION (SHEET 2 OF 2)** 
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 12, 2013 717-53A0036 31 of 33 **BOEING SERVICE BULLETIN 717-53A0036 ALERT**  **ALERT FIGURE 2: OVERWING FRAME - EDDY CURRENT HIGH FREQUENCY INSPECTION**  **(SHEET 1 OF 2)**
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 12, 2013 717-53A0036 32 of 33 **BOEING SERVICE BULLETIN 717-53A0036 ALERT**  **ALERT**The step number shown below agrees with the number shown in the circle symbol in the figure.
**MORE DATA IDENTIFICATION**  **NAME PROCEDURE**  **TASK STEP**  (a) (b) (c) 9923408-503/-504 Frame Eddy Current, High Frequency (ETHF) Inspect 1

(a) Do an ETHF inspection of the upper radius of the frame tab in the inspection area in accordance with NDTSPM Part 06 Eddy Current: 06-10-01.001 (Procedure 1 - Surface Defect Detection), Procedure 1, Calibration Method "G" and Scan Method "69". (b) Look for cracks that start in the forward and aft direction. (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: OVERWING FRAME - EDDY CURRENT HIGH FREQUENCY INSPECTION (SHEET 2 OF 2)** 
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 12, 2013 717-53A0036 33 of 33 **BOEING SERVICE BULLETIN 717-53A0036 ALERT**  **ALERT**