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

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ECCN: 9E991

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Unpublished Work.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,

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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

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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.

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MANPOWER

Airplanes Total Task Hours Elapsed Hours

717-200 30.0 15.0

MATERIAL INFORMATION

Boeing Supplied Kits/Parts.

Refer to Paragraph 2.A., Material - Price and Availability.

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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.

GROUP CONFIGURATION DESCRIPTION

1 - 717-200 Airplanes.

Airplane Models:

717-200

Fuselage Num- Group

ber

5002 - 5099 1

5100 - 5156 1

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:

Company Service Bulletin Description

The Boeing Company 717-53A0034 Inspects Overwing Frames for Cracks

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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

Model Zone

717-200 151, 161

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)

Condition Action Compliance Time

Install overwing frame(s) None -

improvement modification.

All Airplanes

(a)

Within 45,000 flight -

cycles from the

time the modification is installed.

Do High Frequency Eddy

Current (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

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BOEING SERVICE BULLETIN 717-53-0035
Table 1: Overwing Frame Modification Installation

Repeat Interval

(Not to Exceed)

Condition Action Compliance Time

Before Further -

Flight

Contact The Boeing

Company 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.

Task Number of Persons Task Hours Elapsed Hours

Change 2 30.0 15.0

TOTAL FOR EACH AIRPLANE 30.0 15.0

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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 StaAirplane tion (Inches)

717 674.00 +0.1 +65.4

Service Rework Drawing SR95530014-7003

Moment Change

(MEW) IN.-LBS

Mfr's Empty

Weight (MEW)

LBS

Approximate StaAirplane tion (Inches)

717 674.00 +0.1 +65.4

Service Rework Drawing SR95530014-7005

Moment Change

(MEW) IN.-LBS

Mfr's Empty

Weight (MEW)

LBS

Approximate StaAirplane tion (Inches)

717 696.00 +0.1 +77.8

Service Rework Drawing SR95530014-7007

Moment Change

(MEW) IN.-LBS

Mfr's Empty

Weight (MEW)

LBS

Approximate StaAirplane tion (Inches)

717 696.00 +0.1 +77.8

Service Rework Drawing SR95530014-7009

Moment Change

(MEW) IN.-LBS

Mfr's Empty

Weight (MEW)

LBS

Approximate StaAirplane tion (Inches)

717 715.00 +0.1 +87.0

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BOEING SERVICE BULLETIN 717-53-0035
Service Rework Drawing SR95530014-7011

Moment Change

(MEW) IN.-LBS

Mfr's Empty

Weight (MEW)

LBS

Approximate StaAirplane tion (Inches)

717 715.00 +0.1 +87.0

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:

Drawing No Title Sheet DCN/REV ADCN

IMPROVEMENT MODIFICATION - OVER- DWG A -

WING FRAME, STA 674.000 to 715.000

SR95530014

3. Installation Drawings Used in the Preparation of this Service Bulletin:

None.

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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.

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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 RESPONDER 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 original issue date of this

Service Bulletin (Calendar Days)

Kit Number Name

SB95530035-3 Service Kit 90 $2,727.00

SB95530035-5 Service Kit 90 2,727.00

SB95530035-7 Service Kit 90 2,771.00

SB95530035-9 Service Kit 90 2,771.00

Kit applicability is as follows:

Frame Location / Drawing Configuration Kit Number

Left Hand Side Station Y=674.000 SB95530035-3

Right Hand Side Station Y=674.000 SB95530035-5

Left Hand Side Station Y=696.000 SB95530035-7

Right Hand Side Station Y=696.000 SB95530035-9

Left Hand Side Station Y=715.000 SB95530035-9

Right Hand Side Station Y=715.000 SB95530035-7

B. Industry Support Information

Boeing warranty remedies are not available for the configuration changes given in this service bulletin.

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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

New Part Number QTY Name Notes

-3 -5 -7 -9

SB95530035-3 - . . .

SB95530035-5 . - . .

SB95530035-7 . . - .

SB95530035-9 . . . -

HLT436-10-8 1 1 . . PIN

HLT436-6-8 3 3 3 3 PIN

HLT436-8-4 2 2 2 2 PIN

HLT436-6-7 2 2 2 2 Pin (a) (b)

HLT436-8-8 2 2 2 2 PIN

MS21042L3 9 9 9 9 NUT

MS21042L4 4 4 4 4 NUT

MS21042L5 2 2 2 2 NUT

NAS1252-10L 5 5 4 4 WASHER (a) (b)

NAS1252-416L 2 2 2 2 WASHER (a) (b)

NAS1401-3D3 4 4 5 5 WASHER

NAS1401-4D3 2 2 2 2 WASHER

NAS1401-5D3 2 2 2 2 WASHER

S4931920-10-8 1 1 2 2 PIN (a)

S4931920-6-5 4 4 4 4 PIN (a)

WSP1341-1 1 . . 1 ANGLE

WSP1341-2 . 1 1 . ANGLE

(a) 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. Boeing

AEPL, Drawing 7595071 is used to determine the part numbers

used as substitutes.

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BOEING SERVICE BULLETIN 717-53-0035
Kit SB95530035

New Part Number QTY Name Notes

-3 -5 -7 -9

(b) Extra fasteners are supplied to ease reassembly during the change

done by this bulletin.

2. Parts and Materials Supplied by the Operator

Part Number / Specifica- QTY Name Notes

tion

PR-1422 Class B-2 1 Pint Sealing Compound (a)

(DMS 2082)

or

Equivalent

Koropon 515-700 with 1 Pint Primer, Fluid Resistant (a)

Catalyst 910-704

(DMS 1786)

or

Equivalent

Alodine 1200S 1 Pint Coating, Chemical Conversion (b)

(DPM 1453-1)

or

Equivalent

Can be purchased PRC-DeSoto International, Incorporated CAGE

from:

(a)

5454 San Fernando Road 92108

Glendale, California 91203

Can be purchased Henkel Corporation 1N6B3

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.

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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.

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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.

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BOEING SERVICE BULLETIN 717-53-0035
7. Refer to these 717 AMM and 717 SRM chapters for applicable operations, as

accepted procedures:

–

Reference Operation

717 AMM 20-60-01 Sealant Application

717 SRM 51-10-04 Corrosion/Erosion Control and Prevention

717 SRM 51-20-05 Repair Sealing

717 SRM 51-40-08 Drilling and Countersinking

717 SRM 51-40-09 Cold Working of Holes and Countersink

717 SRM 51-41-02 Installing and Removing Rivets

717 SRM 51-41-03 Installing and Removing Lockbolts

717 SRM 51-41-05 Installing and Removing Hi-Lok Attachments

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

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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

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BOEING SERVICE BULLETIN 717-53-0035