### Commercial **Airplanes** 

# 717 Service Bulletin
**Number: 717-53-0035** Original Issue: June 08, 2012 ATA System: 5310 **SUBJECT:** FUSELAGE - Fuselage Main Frame - Install Overwing Frame Improvement Modification 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 © 2012 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 Unpublished Work.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Original Issue: June 08, 2012 717-53-0035 1 of 19 2.0Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 08, 2012 717-53-0035 2 of 19 **BOEING SERVICE BULLETIN 717-53-0035**

BLANK PAGE**Table of Contents** Summary...................................................... 5 1. PLANNING INFORMATION ........................................ 7 A. Effectivity................................................ 7 1. Airplanes............................................. 7 2. Spares Affected ......................................... 7 B. Concurrent Requirements....................................... 7 C. Reason................................................. 8 D. Description............................................... 8 E. Compliance .............................................. 8 F. Approval ................................................ 9 G. Manpower ............................................... 9 H. Weight and Balance Changes. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 10 I. Electrical Load Data . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11 J. References . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11 1. Existing Data: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11 2. Data Supplied with this Service Bulletin:. . . . . . . . . . . . . . . . . . . . . . . . . . . 11 3. Installation Drawings Used in the Preparation of this Service Bulletin:. . . . . . . . . . . 11 K. Publications Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 12 L. Interchangeability and Intermixability of Parts . . . . . . . . . . . . . . . . . . . . . . . . . . . 12 M. Software Accomplishment Summary . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 12 2. MATERIAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13 A. Material - Price and Availability . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13 B. Industry Support Information . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13 C. Parts Necessary for Each Airplane . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14 1. Kits/Parts . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14 2. Parts and Materials Supplied by the Operator. . . . . . . . . . . . . . . . . . . . . . . . 15 3. Parts Modified and Reidentified. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15 4. Parts Removed and Not Replaced . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15 D. Parts Necessary to Change Spares. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15 E. Special Tooling - Price and Availability. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 16 F. Special Tooling Necessary to do this Service Bulletin. . . . . . . . . . . . . . . . . . . . . . . 16 3. ACCOMPLISHMENT INSTRUCTIONS. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17 A. GENERAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17 B. WORK INSTRUCTIONS. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 18

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 08, 2012 717-53-0035 3 of 19 **BOEING SERVICE BULLETIN 717-53-0035**Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 08, 2012 717-53-0035 4 of 19 **BOEING SERVICE BULLETIN 717-53-0035**

BLANK PAGE

### Commercial **Airplanes** 

# 717 Service Bulletin **Summary Number: 717-53-0035**  Original Issue: June 08, 2012 ATA System: 5310 **SUBJECT:** FUSELAGE - Fuselage Main Frame - Install Overwing Frame Improvement Modification **CONCURRENT REQUIREMENTS** Refer to Paragraph 1.B., Concurrent Requirements. **BACKGROUND** One report of a cracked overwing frame was reported on an 717 airplane with 14,542 flight cycles. 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=674.00, Y=696.000 and Y=715.000 are susceptible to this type of failure. Installing the improvement modification in this service bulletin on each uncracked or replaced frame will increase the compliance time threshold required for the repetitive inspections called for in service bulletin 717-53A0034. The FAA may issue an Airworthiness Directive mandating the accomplishment of Service Bulletin 717-53A0034. Following installation, the inspections noted by 717 Principal Structural Element (PSE) 53.20.02.11 are still required. 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 install an improvement modification on frames with no cracks or replaced overwing frames from Station Y=674.000 to Y=715.000 on left and right sides. **EFFECTIVITY** 717-200 Airplanes. Refer to Paragraph 1.A.1., Airplanes, for the list of affected airplanes. **COMPLIANCE** Refer to Paragraph 1.E., Compliance. **INDUSTRY SUPPORT INFORMATION** Boeing warranty remedies are not available for the configuration changes given in this service bulletin.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 08, 2012 717-53-0035 5 of 19**MANPOWER Elapsed Hours**  **Total Task Hours Airplanes**  15.0 30.0 717-200
**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: June 08, 2012 717-53-0035 6 of 19 **BOEING SERVICE BULLETIN 717-53-0035**

### Commercial **Airplanes** 

# 717 Service Bulletin
**Number: 717-53-0035** Original Issue: June 08, 2012 ATA System: 5310 **SUBJECT:** FUSELAGE - Fuselage Main Frame - Install Overwing Frame Improvement Modification
**1. PLANNING INFORMATION A. Effectivity**  1. Airplanes This service bulletin is for the airplanes shown below. **NOTE:** The intent of this change was done on fuselage number 5126 prior to the original issue of this service bulletin in accordance with Service Rework Drawing SR95530014, Revision A.
**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** The service bulletin listed below must be done before or at the same time as this service bulletin: **Description Service Bulletin**  **Company** Inspects Overwing Frames for Cracks 717-53A0034 The Boeing Company

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 08, 2012 717-53-0035 7 of 19**C. Reason** One report of a cracked overwing frame was reported on an 717 airplane with 14,542 flight cycles. 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=674.00, Y=696.000 and Y=715.000 are susceptible to this type of failure. Installing the improvement modification in this service bulletin on each uncracked or replaced frame will increase the compliance time threshold required for the repetitive inspections called for in service bulletin 717-53A0034. The FAA may issue an Airworthiness Directive mandating the accomplishment of Service Bulletin 717-53A0034. Following installation, the inspections noted by 717 Principal Structural Element (PSE) 53.30.02.11 are still required. 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** This service bulletin provides instructions to install an improvement modification on frames with no cracks or replaced overwing frames from Station Y=674.000 to Y=715.000 on left and right sides. 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** Accomplish the required action(s), based on the applicable condition(s), in Table(s) 1, in accordance with Paragraph 3. Accomplishment Instructions. **Table 1: Overwing Frame Modification Installation Repeat Interval**  **(Not to Exceed) Compliance Time**  **Action Condition** 

- None Install overwing frame(s)improvement modification. All Airplanes (a)

- Within 45,000 flight cycles from thetime the modification is installed. Do High Frequency EddyCurrent (HFET) inspection of overwing frame(s) for cracks. Any overwing frame with modification installed

15,000 flight cycles. - Do repeat High Frequen- cy Eddy Current (HFET) inspection of overwing frame(s) for cracks. No crack found

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 08, 2012 717-53-0035 8 of 19 **BOEING SERVICE BULLETIN 717-53-0035 Table 1: Overwing Frame Modification Installation**  **Repeat Interval (Not to Exceed)**  **Compliance Time Action**  **Condition**

- Before Further Flight Contact The BoeingCompany for FAA approved repair instructions and do the repair. Any crack found

(a) Boeing recommends this service bulletin be done to introduce improvements. Performing the modification in this service bulletin on each uncracked or replaced frame will increase the compliance time threshold required for the repetitive inspections called for in service bulletin 717-53A0034 that may possibly be mandated by a FAA Airworthiness Directive. **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 configuration change 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. **NOTE:** The manpower estimate only lists the modification installation. It assumes that the access to do this change is accomplished concurrently with Service Bulletin 717-53A0034. **Elapsed Hours Task Hours**  **Number of Persons Task**  15.0 30.0 2 Change 15.0 30.0 TOTAL FOR EACH AIRPLANE

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 08, 2012 717-53-0035 9 of 19 **BOEING SERVICE BULLETIN 717-53-0035 H. Weight and Balance Changes**  **NOTE:** Weight and balance changes affected by incorporation of this service bulletin are contingent upon the changes to each particular airplane. The data given in the tables below is applicable to a specific Service Rework Drawing configuration at each frame station. Weight data is to be computed by the operator by using the data below as applicable to individual airplanes. Necessary revisions should be made to the appropriate airplane weight and balance report. **Service Rework Drawing SR95530014-7001**
**Moment Change (MEW) IN.-LBS**  **Mfr's Empty Weight (MEW)**  **LBS Approximate Sta**  **tion (Inches) Airplane**  +65.4 +0.1 674.00 717 **Service Rework Drawing SR95530014-7003**
**Moment Change (MEW) IN.-LBS**  **Mfr's Empty Weight (MEW)**  **LBS Approximate Sta**  **tion (Inches) Airplane**  +65.4 +0.1 674.00 717 **Service Rework Drawing SR95530014-7005**
**Moment Change (MEW) IN.-LBS**  **Mfr's Empty Weight (MEW)**  **LBS Approximate Sta**  **tion (Inches) Airplane**  +77.8 +0.1 696.00 717 **Service Rework Drawing SR95530014-7007**
**Moment Change (MEW) IN.-LBS**  **Mfr's Empty Weight (MEW)**  **LBS Approximate Sta**  **tion (Inches) Airplane**  +77.8 +0.1 696.00 717 **Service Rework Drawing SR95530014-7009**
**Moment Change (MEW) IN.-LBS**  **Mfr's Empty Weight (MEW)**  **LBS Approximate Sta**  **tion (Inches) Airplane**  +87.0 +0.1 715.00 717

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 08, 2012 717-53-0035 10 of 19 **BOEING SERVICE BULLETIN 717-53-0035 Service Rework Drawing SR95530014-7011** 
**Moment Change (MEW) IN.-LBS**  **Mfr's Empty Weight (MEW)**  **LBS Approximate Sta**  **tion (Inches) Airplane**  +87.0 +0.1 715.00 717
**I. Electrical Load Data** Not changed. **J. References** 1. Existing Data: a. Boeing Service Bulletin 717-53A0034 b. Non-Destructive Test Standard Practices Manual (NDTSPM) 06-10-01.001 c. 717 Aircraft Maintenance Manual (AMM) 20-60-01 d. 717 Fleet Team Digest (FTD) 53-09003 e. 717 Structural Repair Manual (SRM) 51, 51-10-04, 51-20-05, 51-40-08, 51-40-09, 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 E-mail: dse.boecom@boeing.com a. Drawings:
**ADCN DCN/REV**  **Sheet Title**  **Drawing No**

- A DWG IMPROVEMENT MODIFICATION - OVER- WING FRAME, STA 674.000 to 715.000 SR95530014
3. Installation Drawings Used in the Preparation of this Service Bulletin: None.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 08, 2012 717-53-0035 11 of 19 **BOEING SERVICE BULLETIN 717-53-0035 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 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** Not affected.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 08, 2012 717-53-0035 12 of 19 **BOEING SERVICE BULLETIN 717-53-0035 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 kits 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 RE SPONDER AT FR@BOEING.COM FOR THE LATEST REORDER LEAD TIME (ROLT) AND**  **PRICE INFORMATION**
**Unit Price as of the original issue date of**  **this Service Bulletin (US Dollars)** **ROLT as of the origi nal issue date of this** **Service Bulletin (Cal endar Days)**  **Name Kit Number** 

$2,727.00 90 Service Kit SB95530035-3 2,727.00 90 Service Kit SB95530035-5 2,771.00 90 Service Kit SB95530035-7 2,771.00 90 Service Kit SB95530035-9 Kit applicability is as follows:
**Kit Number Frame Location / Drawing Configuration**  SB95530035-3 Left Hand Side Station Y=674.000 SB95530035-5 Right Hand Side Station Y=674.000 SB95530035-7 Left Hand Side Station Y=696.000 SB95530035-9 Right Hand Side Station Y=696.000 SB95530035-9 Left Hand Side Station Y=715.000 SB95530035-7 Right Hand Side Station Y=715.000
**B. Industry Support Information** Boeing warranty remedies are not available for the configuration changes given in this service bulletin.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 08, 2012 717-53-0035 13 of 19 **BOEING SERVICE BULLETIN 717-53-0035 C. Parts Necessary for Each Airplane**  1. Kits/Parts To get the kits/parts shown below, refer to Paragraph 2.A., Material - Price and Availability. **NOTE:** One top kit and the items shown in Paragraph 2.C.2., Parts and Materials Supplied by the Operator, are necessary for each airplane.
**Kit SB95530035 Notes**  **Name QTY**  **New Part Number -9**  **-7 -5**  **-3**

. . . - SB95530035-3

. . - . SB95530035-5

. - . . SB95530035-7

- . . . SB95530035-9 PIN

. . 1 1 HLT436-10-8 PIN 3 3 3 3 HLT436-6-8 PIN 2 2 2 2 HLT436-8-4 (a) (b) Pin 2 2 2 2 HLT436-6-7 PIN 2 2 2 2 HLT436-8-8 NUT 9 9 9 9 MS21042L3 NUT 4 4 4 4 MS21042L4 NUT 2 2 2 2 MS21042L5 (a) (b) WASHER 4 4 5 5 NAS1252-10L (a) (b) WASHER 2 2 2 2 NAS1252-416L WASHER 5 5 4 4 NAS1401-3D3 WASHER 2 2 2 2 NAS1401-4D3 WASHER 2 2 2 2 NAS1401-5D3 (a) PIN 2 2 1 1 S4931920-10-8 (a) PIN 4 4 4 4 S4931920-6-5 ANGLE 1

. . 1 WSP1341-1 ANGLE

. 1 1

. WSP1341-2 (a) If grip length shown is not available at Boeing, fasteners supplied in kits may be one grip length longer than indicated. Also, if anyfasteners part numbers listed are not available or have been superseded, substitute fasteners may be supplied in kits. Boeing AEPL, Drawing 7595071 is used to determine the part numbers used as substitutes.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 08, 2012 717-53-0035 14 of 19 **BOEING SERVICE BULLETIN 717-53-0035 Kit SB95530035**  **Notes Name**  **QTY New Part Number**  **-9 -7**  **-5 -3**  (b) Extra fasteners are supplied to ease reassembly during the change done by this bulletin.
2. Parts and Materials Supplied by the Operator
**Notes Name**  **QTY Part Number / Specifica-**  **tion** (a) Sealing Compound 1 Pint PR-1422 Class B-2 (DMS 2082) or Equivalent (a) Primer, Fluid Resistant 1 Pint Koropon 515-700 with Catalyst 910-704 (DMS 1786) or Equivalent (b) Coating, Chemical Conversion 1 Pint Alodine 1200S (DPM 1453-1) or Equivalent
CAGE PRC-DeSoto International, Incorporated Can be purchased from: (a) 92108 5454 San Fernando Road Glendale, California 91203 1N6B3 Henkel Corporation Can be purchased from: (b) 32100 Stephenson Highway Madison Heights, Michigan 48071

3. Parts Modified and Reidentified None. 4. Parts Removed and Not Replaced None. **D. Parts Necessary to Change Spares** None.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 08, 2012 717-53-0035 15 of 19 **BOEING SERVICE BULLETIN 717-53-0035 E. Special Tooling - Price and Availability**  717 SRM 51-40-09 gives data about cold working tools and sleeves necessary to do the work given in this service bulletin. These tools are available from industry sources. **F. Special Tooling Necessary to do this Service Bulletin** Cold working tools are necessary to do the change given in this service bulletin. To get the cold working tools, refer to Paragraph 2.E., Special Tooling - Price and Availability.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 08, 2012 717-53-0035 16 of 19 **BOEING SERVICE BULLETIN 717-53-0035 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 Structural Repair Manual (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 717 SRM 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. 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 Chapter 51. – Torque limits to tighten nuts and bolts are in 717 SRM Chapter 51.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 08, 2012 717-53-0035 17 of 19 **BOEING SERVICE BULLETIN 717-53-0035**7. Refer to these 717 AMM and 717 SRM chapters for applicable operations, as accepted procedures:

– **Operation Reference**  Sealant Application 717 AMM 20-60-01 Corrosion/Erosion Control and Prevention 717 SRM 51-10-04 Repair Sealing 717 SRM 51-20-05 Drilling and Countersinking 717 SRM 51-40-08 Cold Working of Holes and Countersink 717 SRM 51-40-09 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
8. Obey all of the warnings and cautions given in the specified manual sections. 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. 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. This service bulletin includes functional test procedures for the systems changed by this service bulletin. More functional tests can possibly be necessary in accordance with standard maintenance practices because of interruption to other airplane systems. 14. This service bulletin assumes that the access to do this change is accomplished concurrently with Service Bulletin 717-53A0034. **B. WORK INSTRUCTIONS** 1. Remove and keep the cusp membrane(s), if required. 2. Install frame(s) improvement modification in accordance with Service Rework Drawing SR95530014.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 08, 2012 717-53-0035 18 of 19 **BOEING SERVICE BULLETIN 717-53-0035 NOTE:**  Ink Stamp reworked frames in accordance with Service Rework Drawing SR95530014, General Note 31. **NOTE:** Additional fasteners, not required to accomplish the modification but that may have been removed to allow access are included in the parts kits for each station. 3. Do High Frequency Eddy Current (HFET) inspection on any overwing frame with modification installed for cracks in accordance with NDTSPM 06-10-01.001 HFET Procedure 1, Calibration Method "K" and Scan Method "44" and Service Rework Drawing SR95530014 at intervals specified in Paragraph 1.E., Compliance.
**Condition 1 (No Crack Found)** a. Repeat High Frequency Eddy Current (HFET) inspection for cracks in accordance with NDTSPM 06-10-01.001 HFET Procedure 1, Calibration Method "K" and Scan Method "44" and Service Rework Drawing SR95530014 at intervals specified in Paragraph 1.E., Compliance. **Condition 2 (Any Crack Found)** a. Contact The Boeing Company for FAA approved repair instructions and do the repair. 4. Install kept cusp membrane(s) if required.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 08, 2012 717-53-0035 19 of 19 **BOEING SERVICE BULLETIN 717-53-0035**