Commercial 

Airplanes 717

Service Bulletin

ALERT

Number: 717-53A0034

Original Issue: October 05, 2011

Revision 1: November 07, 2012

ATA System: 5310

SUBJECT: FUSELAGE - Main Frame - Inspect Overwing Frames for Cracks

Export of this technology is controlled under the United States Export Administration Regulations (EAR) (15

CFR 300-774). An export license may be required before it is used for development, production or use by foreign

persons from specific countries. The controller of this data has the individual responsibility to abide by all export

laws.

ECCN: 9E991

BOEING PROPRIETARY, CONFIDENTIAL AND/OR TRADE SECRET

Copyright © 2011 Boeing.

Unpublished Work. All Rights Reserved.

Treatment of this document and its content is governed by contract with Boeing. Rights to use this document

are licensed on a per aircraft basis and such rights may not be transferable. For more information, contact The

Boeing Company.

Boeing, the Boeing signature, the Boeing symbol, 707, 717, 727, 737, 747, 757, 767, 777, 787, DreamlinerTM,

BBJ, DC-8, DC-9, DC-10, KC-10, KDC-10, MD-10, MD-11, MD-80, MD-88, MD-90, P-8A, Poseidon and Boeing

liveries are all trademarks owned by The Boeing Company; and no trademark license is granted in connection

with this document unless provided in writing by Boeing. BOEING is a trademark of Boeing Management

Company.

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ALERT ALERT

BLANK PAGE
Table of Contents

Revision Transmittal Sheet ............................................ 5

Summary ...................................................... 7

1. PLANNING INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11

A. Effectivity . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11

1. Airplanes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11

2. Spares Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11

B. Concurrent Requirements . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11

C. Reason . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 12

D. Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 12

E. Compliance . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13

F. Approval . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15

G. Manpower . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15

H. Weight and Balance Changes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17

I. Electrical Load Data . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17

J. References . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17

1. Existing Data: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17

2. Data Supplied with this Service Bulletin: . . . . . . . . . . . . . . . . . . . . . . . . . . . 17

3. Installation Drawings Used in the Preparation of this Service Bulletin: . . . . . . . . . . . 18

K. Publications Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 18

L. Interchangeability and Intermixability of Parts . . . . . . . . . . . . . . . . . . . . . . . . . . . 18

M. Software Accomplishment Summary . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 18

2. MATERIAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19

A. Material - Price and Availability . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19

B. Industry Support Information . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19

C. Parts Necessary for Each Airplane . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19

1. Kits/Parts . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19

2. Parts and Materials Supplied by the Operator . . . . . . . . . . . . . . . . . . . . . . . . 22

3. Parts Modified and Reidentified . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 23

4. Parts Removed and Not Replaced . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 23

D. Parts Necessary to Change Spares . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 23

E. Special Tooling - Price and Availability . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 23

F. Special Tooling Necessary to do this Service Bulletin . . . . . . . . . . . . . . . . . . . . . . . 23

3. ACCOMPLISHMENT INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25

A. GENERAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25

B. WORK INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 26

FIGURE 1: DETAILED VISUAL INSPECTION - OVERWING FRAMES . . . . . . . . . . . . . . . . . 30

FIGURE 2: EDDY CURRENT, HIGH FREQUENCY INSPECTION - OVERWING FRAMES . . . . . . 32

FIGURE 3: BLEND-OUT REPAIR - FRAME TAB UPPER RADIUS . . . . . . . . . . . . . . . . . . . 34

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BLANK PAGE
Commercial 

Airplanes 717

Service Bulletin

ALERT

Revision Transmittal Sheet Number: 717-53A0034

Original Issue: October 05, 2011

Revision 1: November 07, 2012

ATA System: 5310

SUBJECT: FUSELAGE - Main Frame - Inspect Overwing Frames for Cracks

This revision includes all pages of the service bulletin.

COMPLIANCE INFORMATION RELATED TO THIS REVISION

Federal Aviation Administration (FAA) Notice of Proposed Rule Making (NPRM) 2011-NM-273-AD is related to

this service bulletin.

No more work is necessary on airplanes changed in accordance with the original issue of this service bulletin.

REASON FOR REVISION

This revision is sent to change the initial inspection compliance time threshold and add alternate parts to kits.

These sections were changed:

1. In Paragraph 1.C., Reason, changed statement and added Fleet Team Digest article.

2. In Paragraph 1.E., Compliance, added NPRM and changed Table 1.

3. In Paragraph 1.J.1., Existing Data, added NPRM and Fleet Team Digest article.

4. In Paragraph 1.J.2.a., Drawings, changed drawing revision level.

5. In Paragraph 2.A., Material - Price and Availability, changed kit pricing data.

6. In Paragraph 2.C.1, Kits/Parts, added alternate parts to kits.

Vertical lines are put on the left edge of each page, except in Paragraph 1.A., Effectivity, to show the location

of important changes.

Pages with no vertical lines have no important changes.

REVISION HISTORY

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ALERT ALERT

BLANK PAGE
Commercial 

Airplanes 717

Service Bulletin

ALERT

Summary Number: 717-53A0034

Original Issue: October 05, 2011

Revision 1: November 07, 2012

ATA System: 5310

SUBJECT: FUSELAGE - Main Frame - Inspect Overwing Frames for Cracks

THIS BULLETIN IS SENT TO THE OPERATORS OF RECORD OF THE AIRPLANES SHOWN IN PARAGRAPH

1.A., EFFECTIVITY. IF AN AIRPLANE HAS BEEN LEASED OR SOLD, SEND THIS SERVICE BULLETIN TO

THE NEW OPERATOR. IF APPLICABLE SPARES HAVE BEEN SOLD, SEND THIS SERVICE BULLETIN TO

THE NEW OWNER.

CONCURRENT REQUIREMENTS

None.

BACKGROUND

There have been over forty reports of overwing frames cracking on MD-80 airplanes having logged between

19,876 and 41,166 flight cycles. There is one report of a cracked overwing frame on an MD-90 airplane, and

two 717 airplanes have been reported with cracked frames. The first 717 airplane had 18,235 flight-hours and

14,542 landing cycles and the second 717 airplane had 22,053 flight-hours and 11,991 landing cycles. Due to

similarity in frame design, the 717 airplanes are susceptible to cracks. The cracks, which originate in the upper

radius of the frame inboard tab just below the floor, were caused by fatigue. Boeing has determined that 717

overwing frames at Stations Y=674.000, Y=696.000 and Y=715.000 are also susceptible to this type of failure.

All the noted frames are a part of 717 Principal Structural Element (PSE) 53.30.02.11. Inspection of the overwing

frames at Stations Y=674.000, Y=696.000 and Y=715.000, left and right sides will determine if cracks exist. If

not corrected, an undetected crack may sever the frame, which may increase the loading of adjacent frames

and result in damage to adjacent structure and extensive repair, or ultimately could lead to the loss of overall

structural integrity of the airplane.

Boeing Fleet Team Digest (FTD) 717 FTD 53-09003 is related to this service bulletin.

ACTION

This service bulletin provides instructions to do a general visual inspection and a high frequency eddy current

inspection of the overwing frames at Stations Y=674.000, Y=696.000 and Y=715.000, left and right sides. The

purpose of these inspections is to detect fatigue cracks in the upper radius of the frame tab. Based on inspection

results, do as follows:

Condition 1 (No Crack Found on Any Frame)

1. Does repetitive general visual inspections and high frequency eddy current inspections of the overwing

frames for cracks and does as follows:

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Condition 1A (No Crack Found on Any Frame)

a. Does repetitive general visual inspections and high frequency eddy current inspections of the

overwing frames for cracks.

Condition 1B (Crack Found on Any Frame)

a. Establishes the length of the crack and does the work of Condition 2 or Condition 3.

Condition 2 (Crack in Any Frame is Less Than 0.125 Inch in Length)

1. Does a blend-out repair of the crack.

2. Does repetitive general visual inspections and high frequency eddy current inspections of the repaired

overwing frame for cracks and does as follows:

Condition 2A (No Crack Found on Any Repaired Frame)

a. Does repetitive general visual inspections and high frequency eddy current inspections of the

repaired overwing frame for cracks.

Condition 2B (Any Crack Found on Any Repaired Frame)

a. Does the work of Condition 3.

Condition 3 (Crack in Any Frame is Equal To or Greater Than 0.125 Inch in Length)

1. Replaces the cracked overwing frame.

2. Does repetitive general visual inspections and high frequency eddy current inspections of the replaced

overwing frame for cracks and does as follows:

Condition 3A (No Crack Found on Any Replaced Frame)

a. Does repetitive general visual inspections and high frequency eddy current inspections of the

replaced overwing frame for cracks.

Condition 3B (Crack Found on Any Replaced Frame)

a. Establishes the length of the crack and does the work of Condition 2 or Condition 3.

EFFECTIVITY

All 717-200 Airplanes. Refer to Paragraph 1.A.1., Airplanes, for the list of affected airplane(s).

COMPLIANCE

Federal Aviation Administration (FAA) Notice of Proposed Rule Making (NPRM) 2011-NM-273-AD is related to

this service bulletin.

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BOEING SERVICE BULLETIN 717-53A0034

ALERT ALERT
Refer to Paragraph 1.E., Compliance.

INDUSTRY SUPPORT INFORMATION

Boeing warranty remedies are not available for the inspection and/or repair procedures given in this service

bulletin.

MANPOWER

Refer to Paragraph 1.G., Manpower.

MATERIAL INFORMATION

Boeing Supplied Kits/Parts.

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

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ALERT ALERT
Commercial 

Airplanes 717

Service Bulletin

ALERT

Number: 717-53A0034

Original Issue: October 05, 2011

Revision 1: November 07, 2012

ATA System: 5310

SUBJECT: FUSELAGE - Main Frame - Inspect Overwing Frames for Cracks

THIS BULLETIN IS SENT TO THE OPERATORS OF RECORD OF THE AIRPLANES SHOWN IN PARAGRAPH

1.A., EFFECTIVITY. IF AN AIRPLANE HAS BEEN LEASED OR SOLD, SEND THIS SERVICE BULLETIN TO

THE NEW OPERATOR. IF APPLICABLE SPARES HAVE BEEN SOLD, SEND THIS SERVICE BULLETIN TO

THE NEW OWNER.

1. PLANNING INFORMATION

A. Effectivity

1. Airplanes

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

None.

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C. Reason

There have been over forty reports of overwing frames cracking on MD-80 airplanes having logged

between 19,876 and 41,166 flight cycles. There is one report of a cracked overwing frame on an MD-90

airplane, and two 717 airplanes have been reported with cracked frames. The first 717 airplane had

18,235 flight-hours and 14,542 landing cycles and the second 717 airplane had 22,053 flight-hours

and 11,991 landing cycles. Due to similarity in frame design, the 717 airplanes are susceptible to cracks.

The cracks, which originate in the upper radius of the frame inboard tab just below the floor, were

caused by fatigue. Boeing has determined that 717 overwing frames at Stations Y=674.000, Y=696.000

and Y=715.000 are also susceptible to this type of failure. All the noted frames are a part of 717 Principal

Structural Element (PSE) 53.30.02.11. Inspection of the overwing frames at Stations Y=674.000,

Y=696.000 and Y=715.000, left and right sides will determine if cracks exist. If not corrected, an

undetected crack may sever the frame, which may increase the loading of adjacent frames and result

in damage to adjacent structure and extensive repair, or ultimately could lead to the loss of overall

structural integrity of the airplane.

Boeing Fleet Team Digest (FTD) 717 FTD 53-09003 is related to this service bulletin.

This revision is sent to change the initial inspection compliance time threshold and add alternate parts

to kits.

D. Description

This service bulletin provides instructions to do a general visual inspection and a high frequency eddy

current inspection of the overwing frames at Stations Y=674.000, Y=696.000 and Y=715.000, left and

right sides. The purpose of these inspections is to detect fatigue cracks in the upper radius of the frame

tab. Based on inspection results, do as follows:

Condition 1 (No Crack Found on Any Frame)

1. Does repetitive general visual inspections and high frequency eddy current inspections of the

overwing frames for cracks and does as follows:

Condition 1A (No Crack Found on Any Frame)

a. Does repetitive general visual inspections and high frequency eddy current inspections of the

overwing frames for cracks.

Condition 1B (Crack Found on Any Frame)

a. Establishes the length of the crack and does the work of Condition 2 or Condition 3.

Condition 2 (Crack in Any Frame is Less Than 0.125 Inch in Length)

1. Does a blend-out repair of the crack.

2. Does repetitive general visual inspections and high frequency eddy current inspections of the

repaired overwing frame for cracks and does as follows:

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ALERT ALERT
Condition 2A (No Crack Found on Any Repaired Frame)

a. Does repetitive general visual inspections and high frequency eddy current inspections of the

repaired overwing frame for cracks.

Condition 2B (Crack Found on Any Repaired Frame)

a. Does the work of Condition 3.

Condition 3 (Crack in Any Frame is Equal To or Greater Than 0.125 Inch in Length)

1. Replaces the cracked overwing frame.

2. Does repetitive general visual inspections and high frequency eddy current inspections of the

replaced overwing frame for cracks and does as follows:

Condition 3A (No Crack Found on Any Replaced Frame)

a. Does repetitive general visual inspections and high frequency eddy current inspections of the

replaced overwing frame for cracks.

Condition 3B (Any Crack Found on Any Replaced Frame)

a. Establishes the length of the crack and does the work of Condition 2 or Condition 3.

Revision 1 - No more work is necessary on airplanes changed in accordance with the original issue of

this service bulletin.

The work in this service bulletin is done in the maintenance zone(s) given below.

Affected Maintenance Zones

Model Zone

717-200 151, 161

E. Compliance

Federal Aviation Administration (FAA) Notice of Proposed Rule Making (NPRM) 2011-NM-273-AD is

related to this service bulletin.

Accomplish the required action(s), based on the applicable condition(s), in Table 1, in accordance with

Paragraph 3. Accomplishment Instructions.

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BOEING SERVICE BULLETIN 717-53A0034

ALERT ALERT
Table 1: Inspect Left and Right Side Overwing Frames for Cracks from Station 674 to 715

Repeat Interval

(Not to Exceed)

Compliance Time (Whichever Occurs

Later )

Condition Action

Within 8275 flight -

cycles after the

original issue date

on this service bulletin.

Before the accumulation of 12,000 total flight cycles.Do a general visual inspection and a high frequency

eddy current inspection of

the overwing frames at the

tab upper radius for cracks.

All Airplanes

Do repeat general visual in- - - 9,300 flight cycles.

spection and high frequency

eddy current inspection.

Condition 1

(No Crack Found

on Any Frame)

AND

Do the action specified by

Condition 1A or 1B.

Do repeat general visual in- - - 9,300 flight cycles.

spection and high frequency

eddy current inspection.

Condition 1A

(No Crack Found

on Any Frame)

Before further - -

flight.

Establish the length of the

crack and do the work

specified by Condition 2 or

Condition 3.

Condition 1B

(Crack Found on

Any Frame)

Before further - -

flight.

Repair the cracked overwing frame.Condition 2

(Crack in Any

Frame is Less

Than 0.125 Inch in

Length)

AND

9,300 flight cycles - 9,300 flight cycles.

after repair.

Do a general visual inspection and high frequency eddy current inspection of the

repaired overwing frame.

AND

Do the action specified by

Condition 2A or 2B.

Do repeat general visual in- - - 9,300 flight cycles.

spection and high frequency

eddy current inspection of

the repaired overwing

frame.

Condition 2A

(No Crack Found

on Any Repaired

Frame)

Before further - -

flight.

Do the work specified by

Condition 3.

Condition 2B

(Crack Found on

Any Repaired

Frame)

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BOEING SERVICE BULLETIN 717-53A0034

ALERT ALERT
Table 1: Inspect Left and Right Side Overwing Frames for Cracks from Station 674 to 715

Repeat Interval

(Not to Exceed)

Compliance Time (Whichever Occurs

Later )

Condition Action

Before further - -

flight.

Replace the cracked overwing frame.Condition 3

(Crack in Any

Frame is Equal To

or Greater Than

0.125 Inch in

Length)

AND

Within 12,000 flight - 9,300 flight cycles.

cycles after replacement.

Do a general visual inspection and high frequency eddy current inspection of the

replaced overwing frame.

AND

Do the action specified by

Condition 3A or 3B.

Do repeat general visual in- - - 9,300 flight cycles.

spection and high frequency

eddy current inspection of

the replaced overwing

frame.

Condition 3A

(No Crack Found

on Any Replaced

Frame)

Before further - -

flight.

Establish the length of the

crack and do the work

specified by Condition 2 or

Condition 3.

Condition 3B

(Crack Found on

Any Replaced

Frame)

F. Approval

This service bulletin was examined by the Federal Aviation Administration (FAA). The changes specified

in this service bulletin comply with the applicable regulations and are FAA approved, as well as European

Aviation Safety Agency (EASA)/Joint Aviation Authorities (JAA) approved for all EASA/JAA approved

airplanes listed in the service bulletin effectivity. This service bulletin and its approval were based on

the airplane in its original Boeing delivery configuration or as modified by other approved Boeing

changes.

If an airplane has a non-Boeing modification or repair that affects a component or system also affected

by this service bulletin, the operator is responsible for obtaining appropriate regulatory agency approval

before incorporating this service bulletin.

G. Manpower

The table below shows an estimate of the task hours necessary to do this inspection for each airplane.

This estimate is for direct labor only, done by an experienced crew. Adjust the estimate with operator

task hour data if necessary. The estimate does not include lost time. These are some examples of lost

time:

• Time to adjust to the workplace

• Time to schedule the work

• Time to inspect the work

• Time to cure the materials

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BOEING SERVICE BULLETIN 717-53A0034

ALERT ALERT
• Time to make the parts

• Time to find the tools.

Condition 1

Task Number of Persons Task Hours Elapsed Hours

Open Access 4 20.0 5.0

FIGURE 1 1 3.0 3.0

FIGURE 2 1 3.0 3.0

Close Access 4 20.0 5.0

TOTAL FOR EACH AIRPLANE 46.0 16.0

NOTE: Maximum total task hours and elapsed hours are given for inspection per airplane.

Condition 2

Task Number of Persons Task Hours Elapsed Hours

Open Access 4 20.0 5.0

FIGURE 1 1 3.0 3.0

FIGURE 2 1 3.0 3.0

Remove Cusp Mem- 1 6.0 6.0

brane

FIGURE 3 1 2.0 2.0

Install Cusp Mem- 1 6.0 6.0

brane

Close Access 4 20.0 5.0

TOTAL FOR EACH AIRPLANE 60.0 30.0

NOTE: Maximum total task hours and elapsed hours are given for the blend-out repair of one frame.

Additional task hours and elapsed hours for the repair of other cracked frames are contingent

upon inspection results and are to be estimated by the operator.

Condition 3

Task Number of Persons Task Hours Elapsed Hours

Open Access 4 20.0 5.0

FIGURE 1 1 3.0 3.0

FIGURE 2 1 3.0 3.0

Remove Cusp Mem- 1 6.0 6.0

brane

Defuel 2 4.0 2.0

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BOEING SERVICE BULLETIN 717-53A0034

ALERT ALERT
Condition 3

Task Number of Persons Task Hours Elapsed Hours

Remove Frame 2 20.0 10.0

Install Frame 2 48.0 24.0

Install Cusp Mem- 1 6.0 6.0

brane

Close Access 4 20.0 5.0

TOTAL FOR EACH AIRPLANE 130.0 64.0

NOTE: Maximum total task hours and elapsed hours are given for the replacement of one frame.

Additional task hours and elapsed hours for the replacement of other cracked frames, are

contingent upon inspection results and are to be estimated by the operator.

H. Weight and Balance Changes

None.

I. Electrical Load Data

Not changed.

J. References

1. Existing Data:

a. Boeing Fleet Team Digest (FTD) 717 FTD 53-09003.

b. Boeing Drawing SE10000000.

c. Federal Aviation Administration (FAA) Notice of Proposed Rule Making (NPRM)

2011-NM-273-AD.

d. Non-Destructive Test Standard Practices Manual (NDTSPM) 06-10-01.001, 09-00-04, 09-00-06.

e. Standard Overhaul Practices Manual (SOPM) 20-10-10.

f. 717 Aircraft Maintenance Manual (AMM) 06-31-00, 07-11-00, 07-20-01, 08-20-00, 12-11-01,

20-60-01, 20-60-26, 25-23-05, 25-28-02, 25-82-01, 52-21-01, 53-21-01.

g. 717 Structural Repair Manual (SRM) 51-10-04, 51-20-05, 51-40-03, 51-40-08, 51-41-01,

51-41-02, 51-41-03, 51-41-05.

2. Data Supplied with this Service Bulletin:

No data is supplied with this service bulletin. To obtain the data necessary to support this service

bulletin submit a data request to:

Data and Services Management

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BOEING SERVICE BULLETIN 717-53A0034

ALERT ALERT
MS D800-0019

3855 Lakewood Boulevard

Long Beach, California 90846

Phone: (562) 593-6996

Fax: (562) 593-2001

E-mail: dse.boecom@boeing.com

a. Drawings:

Drawing No Title Sheet DCN/REV ADCN

FRAME INSTL - OVERWING SERVICE DWG A -

REWORK DRAWING

SR95530013

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

None.

K. Publications Affected

1. Publications:

Publication Chapter-Section

Maintenance Planning Document 53-00

2. Damage Tolerance Based Structural Inspections:

Boeing has evaluated the repairs and/or changes in this service bulletin for effects on Fatigue

Critical Structure (FCS) and for changes to Damage Tolerance Inspections (DTI) required in the

Maintenance Program. This service bulletin affects FCS but no new DTIs are necessary.

L. Interchangeability and Intermixability of Parts

Accomplishment of this service bulletin does not affect interchangeability or intermixability of parts.

M. Software Accomplishment Summary

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BOEING SERVICE BULLETIN 717-53A0034

ALERT ALERT
2. MATERIAL INFORMATION

A. Material - Price and Availability

Boeing can supply the kits shown in Paragraph 2.C., Parts Necessary for Each Airplane . Operators

are encouraged to share schedule requirements with Boeing for incorporation of the service bulletin.

The parts are subject to the terms and conditions of the Boeing standard purchase order

acknowledgment. Prices are in United States Dollars. Terms: Net 30 days.

Reference this service bulletin and submit your purchase order by one of these methods:

1. Order on-line via ATA Spec 2000 or The Boeing PART Page

2. Fax to (206) 662-7145

REFER TO THE BOEING PART PAGE ON MYBOEINGFLEET.COM OR CONTACT FIRST RESPONDER

AT FR@BOEING.COM FOR THE LATEST REORDER LEAD TIME (ROLT) AND PRICE INFORMATION

Unit Price as of

the original date

of this Service

Bulletin (US Dollars)

ROLT as of the

original date of

this Service Bulletin (Calendar

Days)

Kit Number Name

SA95530034-3 Service Kit 90 $39,389.00

SA95530034-5 Service Kit 90 39,389.00

SA95530034-7 Service Kit 90 44,270.00

SA95530034-9 Service Kit 90 44,270.00

SA95530034-11 Service Kit 90 43,988.00

SA95530034-13 Service Kit 90 43,988.00

B. Industry Support Information

Boeing warranty remedies are not available for the inspection, and/or repair procedures given in this

service bulletin.

C. Parts Necessary for Each Airplane

1. Kits/Parts

Relationship of Fuselage Stations to Kits is as follows:

Station Frame Kit

Y=674.000, Left Side SA95530034-3

Y=674.000, Right Side SA95530034-5

Y=696.000, Left Side SA95530034-7

Y=696.000, Right Side SA95530034-9

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BOEING SERVICE BULLETIN 717-53A0034

ALERT ALERT
Station Frame Kit

Y=715.000, Left Side SA95530034-11

Y=715.000, Right Side SA95530034-13

Kit SA95530034

New Part Number QTY Name Notes

-3 -5 -7 -9 -11 -13

2913797-1 1 1 . . . . CLIP

2913870-1 1 1 1 1 1 1 CLIP

2920753-1 . . 1 1 1 1 CLIP

2920754-501 1 1 . . . . CLIP

2920756-1 . 1 1 . . 1 CLIP

2920756-2 1 . . 1 1 . CLIP

3D0006-3 100 100 98 98 101 101 NUT ASSY (a)

3D0006-4 2 2 2 2 2 2 NUT ASSY (a)

9919669-17 1 . . . . . CLIP

9919669-18 . 1 . . . . CLIP

9919671-17 . . . 1 1 . CLIP

9919671-18 . . 1 . . 1 CLIP

9919671-19 . . 1 1 1 1 CLIP

9919671-21 . . 1 1 1 1 CLIP

9923405-503 1 . . . . . FRAME

9923405-504 . 1 . . . . FRAME

9923406-503 . . 1 . . . FRAME

9923406-504 . . . 1 . . FRAME

9923407-503 . . . . 1 . FRAME

9923407-504 . . . . . 1 FRAME

9971114-13 . . 1 . . . CLIP

9971114-14 . . . 1 . . CLIP

9971114-17 . . . . 1 . CLIP

9971114-18 . . . . . 1 CLIP

HLT435-6-10 6 6 . . 2 2 PIN

HLT435-6-11 2 2 . . . . PIN

HLT435-6-3 1 1 1 1 1 1 PIN

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ALERT ALERT
Kit SA95530034

New Part Number QTY Name Notes

-3 -5 -7 -9 -11 -13

HLT435-6-4 3 3 3 3 3 3 PIN

HLT435-6-5 1 1 2 2 2 2 PIN

HLT435-6-6 23 23 36 36 36 36 PIN

HLT435-6-7 4 4 3 3 2 2 PIN

HLT435-6-8 16 16 15 15 12 12 PIN

HLT435-6-9 8 8 5 5 9 9 PIN

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

HLT436-12-10 . . 2 2 2 2 PIN

HLT436-12-11 2 2 . . . . PIN

HLT436-6-2 5 5 5 5 9 9 PIN

HLT436-6-3 11 11 18 18 14 14 PIN

HLT436-6-4 15 15 18 18 15 15 PIN

HLT436-6-5 15 15 21 21 19 19 PIN

HLT436-6-6 8 8 8 8 8 8 PIN

HLT436-6-7 1 1 2 2 2 2 PIN

HLT436-6-8 1 1 1 1 2 2 PIN

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

HLT436-8-6 . . 1 1 . . PIN

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

HLT436-8-8 4 4 4 4 4 4 PIN

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

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

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

HLT439-6-8 3 3 . . . . PIN

MS20470AD5-10D 6 6 10 10 4 4 RIVET

MS20470AD5-11D 6 6 21 21 15 15 RIVET

MS20470AD5-12D 13 13 1 1 1 1 RIVET

MS20470AD5-13D 1 1 . . . . RIVET

MS20470AD5-8D . . . . 11 11 RIVET

MS20470AD5-9D 6 6 . . 1 1 RIVET

MS20470AD6-12D . . 1 1 . . RIVET

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ALERT ALERT
Kit SA95530034

New Part Number QTY Name Notes

-3 -5 -7 -9 -11 -13

MS20470AD6-13D . . . . 1 1 RIVET

MS20470AD6-14D 1 1 . . . . RIVET

MS21042L3 56 56 70 70 65 65 NUT

MS21042L4 5 5 6 6 6 6 NUT

MS21042L5 1 1 . . . . NUT

MS21042L6 2 2 2 2 2 2 NUT

NAS8803-4 . . 2 2 2 2 BOLT (b)

NAS1252-10L 56 56 70 70 65 65 WASHER

NAS1252-416L 5 5 6 6 6 6 WASHER

NAS1252-516L 1 1 . . . . WASHER

NAS1252-616L 2 2 2 2 2 2 WASHER

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

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

S4931920-6-5 . . . . 2 2 PIN

S4931920-6-6 10 10 . . 16 16 PIN

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

S4931920-6-8 4 4 1 1 . . PIN

(a) Or Approved Equivalent. Refer to AEPL Drawing 7595071.

(b) Alternate part based on existing bolts.

2. Parts and Materials Supplied by the Operator

Part Number / Specification QTY Name Notes

PC21F 1 Roll Tape, Cloth Coated (a)

(DMS 1968 Type 2)

OR

Equivalent

PR-1422 Class B-2 1 Quart Sealing Compound (b)

(DMS 2082)

OR

Equivalent

Part Number 235 1 Roll Tape, Adhesive, Double Faced (c)

(DMS 1971)

OR

Equivalent

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BOEING SERVICE BULLETIN 717-53A0034

ALERT ALERT
Shurtape Technologies, Limited Liability CAGE

Corporation (LLC)

(a) Can be purchased from:

4L0S0

1506 Highland Avenue North East

Hickory, North Carolina 28601

(b) Can be purchased from: PRC-DeSoto International, Incorporated 92108

P.O. Box 1800

Sylmar, California 91342

(c) Can be purchased from: Ideal Tape Company 3X706

1400 Middlesex Street

Lowell, Massachusetts 01851

3. Parts Modified and Reidentified

None.

4. Parts Removed and Not Replaced

None.

D. Parts Necessary to Change Spares

None

E. Special Tooling - Price and Availability

General visual inspection equipment and high frequency eddy current inspection equipment required

to accomplish this service bulletin are listed in the Non-Destructive Testing Standard Practice Manual

(NDTSPM) and are to be procured from operator's stock or sources indicated.

F. Special Tooling Necessary to do this Service Bulletin

No special tools or equipment are necessary to do the change in this service bulletin. But, maintenance

and overhaul tools in the manuals given in Paragraph 1.J., References, can be necessary. Examine

operator tool supply to make sure all necessary tools are available.

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ALERT ALERT
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ALERT ALERT

BLANK PAGE
3. ACCOMPLISHMENT INSTRUCTIONS

A. GENERAL INFORMATION

WARNING: IF ELECTRICAL POWER IS APPLIED TO THE AIRPLANE, MAKE SURE YOU OBEY

ALL PRECAUTIONS WHILE YOU DO WORK. IF YOU DO NOT OBEY THE

PRECAUTIONS, DEATH OR INJURY TO PERSONS, AND DAMAGE TO THE AIRPLANE

CAN OCCUR.

CAUTION: ELECTRICALLY GROUND THE AIRPLANE. THIS WILL HELP TO PREVENT DAMAGE

TO THE AIRPLANE OR EQUIPMENT.

CAUTION: KEEP THE WORK AREA, WIRES AND ELECTRICAL BUNDLES CLEAN OF METAL

PARTICLES OR CONTAMINATION WHEN YOU USE TOOLS. UNWANTED MATERIAL,

METAL PARTICLES OR CONTAMINATION CAUGHT IN WIRE BUNDLES CAN CAUSE

DAMAGE TO THE BUNDLES. DAMAGED WIRE BUNDLES CAN CAUSE SPARKS OR

OTHER ELECTRICAL DAMAGE.

NOTE: 1. Manual titles are referred to by acronyms. Refer to Paragraph 1.J., References, for

definition of the acronyms.

2. Equivalent parts are listed in the AEPL, Drawing 7595071.

3. Use the approved fastener and process material substitutions, in accordance with

717 Structural Repair Manual (SRM). .

4. If the length of any fastener specified in this service bulletin does not meet installation

standards given in SRM Chapter 51, then a fastener of the same specification, or

an approved substitute, with a length which meets the installation standards given

in SRM Chapter 51 may be used. In addition, washers may be installed for fastener

grip length in accordance with SRM Chapter 51.

5. A 1/8-inch thick stack of the same type washers called for in this service bulletin is

the maximum thickness which may be used under fastener head or nut to counteract

accumulation of tolerances.

EXCEPTION: When the available fastener length increments are greater than

1/16-inch, a 3/16-inch thick stack of the same type washers may be used.

6. Oversize fasteners must be used when hole diameter exceeds the maximum diameter

specified.

7. Obey all of the warnings and cautions given in the specified manual sections.

8. A General Visual Inspection is defined as: A visual examination of an interior or

exterior area, installation or assembly to detect obvious damage, failure or irregularity.

This level of inspection is made from within touching distance unless otherwise

specified. A mirror may be necessary to enhance visual access to all exposed surfaces

in the inspection area. This level of inspection is made under normally available

lighting conditions such as daylight, hangar lighting, flashlight or drop-light and may

require removal or opening of access panels or doors. Stands, ladders or platforms

may be required to gain proximity to the area being checked.

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ALERT ALERT
9. These work instructions refer to procedures included in other Boeing documents.

When the words "refer to" are used and the operator has an accepted alternative

procedure, the accepted alternative procedure can be used. When the words "in

accordance with" are included in the instruction, the procedure in the Boeing document

must be used.

10. Some Boeing parts are supplied in a temporary configuration. Those parts are

identified with a 'U' or 'Y' in place of the '-' (dash) in the part number. It is permitted

to install parts identified with a 'U' or 'Y' as an alternative to the '-' (dash) number

part. Boeing Drawing SE10000000, Sheets 5.0 and 6.0 contain more data.

11. The instructions in Paragraph 3.B., Work Instructions and the figures can include

operation of tools or test equipment. Boeing Engineering Tool Drawings, the Illustrated

Tool and Equipment Manual, and the Special Tool and Ground Handling Drawing

Index contain data on versions of the tools or test equipment that you can use. It is

permitted to use replaced tools. It is not permitted to use superseded tools.

12. Where the work instructions include installation of a kept part, a new or serviceable

part with the same part number can be installed as an alternative to the kept part.

The removed part can be discarded if a new or serviceable part is installed.

13. Refer to the manuals that follow as accepted procedures:

Accepted Procedure Operation

717 AMM 20-60-01 Sealant - Maintenance Practices

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

717 SRM 51-40-08 Drilling and Countersinking

717 SRM 51-20-05 Repair Sealing

717 SRM 51-41-01 Installing Bolts, Screws, and Washers

717 SRM 51-41-02 Installing and Removing Rivets

717 SRM 51-41-03 Installing and Removing Lockbolts

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

717 SRM 51-40-03 Fastener Substitution and Interchangeability

B. WORK INSTRUCTIONS

1. Remove and keep the items and attaching parts, as applicable, to get access to the left and right

side overwing frames at Stations Y=674.000, Y=696.000 and Y=715.000 as follows:

Item Accepted Procedure

Passenger Seats 717 AMM 25-23-05

Panel,Cabin Sidewall 717 AMM 25-28-02

Passenger Compartment Insulation 717 AMM 25-82-01

Overwing Emergency Exit Doors 717 AMM 52-21-01

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ALERT ALERT
2. Remove and keep the passenger floor coverings (carpet) by pulling one corner to peel the double

sided tape off the floor.

3. Remove and keep passenger compartment floor panels to gain access to the fuselage frames

between Stations Y=674.000 and Y=715.000. Refer to 717 AMM 53-21-01 as an accepted

procedure.

4. Remove tape from the cutout between the cusp membrane and frame to get access to the frame

inspection area.

5. Remove and keep the cusp membrane, as necessary, to get access to the frame inspection area.

6. Do a General Visual inspection and an Eddy Current, High Frequency (ETHF) inspection of the

upper radius of the frame tab on the left and right sides of the overwing frames at Stations

Y=674.000, Y=696.000 and Y=715.000 in accordance with Figures 1 and 2. Based on findings do

as follows:

Condition 1 (No Crack Found on Any Frame)

a. Do repeat General Visual inspection and an Eddy Current, High Frequency (ETHF) inspections

of the overwing frames in accordance with Figures 1 and 2 at intervals specified in Paragraph

1.E., Compliance.

Condition 1A (No Crack Found on Any Frame)

(1) Do repeat General Visual inspection and an Eddy Current, High Frequency (ETHF)

inspections of the overwing frames in accordance with Figures 1 and 2 at intervals specified

in Paragraph 1.E., Compliance.

Condition 1B (Crack Found on Any Frame)

(1) Establish the length of the crack and do the work of Condition 2 or Condition 3.

Condition 2 (Crack in Any Frame is Less Than 0.125 Inch in Length)

a. If installed, remove and keep the cusp membrane to get access to the cracked frame.

b. Do a blend-out repair of the crack in accordance with Figure 3.

c. Do repeat General Visual inspection and an Eddy Current, High Frequency (ETHF) inspections

of the repaired overwing frame in accordance with Figures 1 and 2 at intervals specified in

Paragraph 1.E., Compliance. Based on findings do as follows:

Condition 2A (No Crack Found on Any Repaired Frame)

(1) Do repeat General Visual inspection and an Eddy Current, High Frequency (ETHF)

inspections of the repaired overwing frame in accordance with Figures 1 and 2 at intervals

specified in Paragraph 1.E., Compliance.

Condition 2B (Crack Found on Any Repaired Frame)

(1) Do the work of Condition 3.

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BOEING SERVICE BULLETIN 717-53A0034

ALERT ALERT
Condition 3 (Crack in Any Frame is Equal To or Greater Than 0.125 Inch in Length)

a. Defuel the airplane. Refer to 717 AMM 12-11-01 as an accepted procedure.

b. Raise and level the airplane. Refer to 717 AMM 07-11-00 and 717 AMM 08-20-00 as accepted

procedures.

NOTE: Boeing recommends each frame be replaced separately. If two or more frames are

replaced at the same time, shoring the airplane is recommended. Refer to 717 AMM

07-20-01 as an accepted procedure.

c. If installed, remove and keep the cusp membrane to get access to the cracked frame.

d. Remove and keep the applicable wing to fuselage fillet panels 150CL and 150FL on the left

side and/or 160CR and 160FR on the right side to get access to the cracked frame. Refer to

717 AMM 06-31-00 for fillet panel locations.

e. Replace cracked overwing frame in accordance with Service Rework Drawing SR95530013.

NOTE: Apply PR-1422 sealant on all faying surfaces and wet install all fasteners during

frame replacement.

f. Install kept applicable wing to fuselage fillet panels 150CL and 150FL on the left side and/or

160CR and 160FR on the right side. Refer to 717 AMM 06-31-00 for locations.

g. Remove any shoring and lower the airplane. Refer to 717 AMM 07-11-00 and 717 AMM

08-20-00 as accepted procedures.

h. Do repeat General Visual inspection and an Eddy Current, High Frequency (ETHF) inspections

of the replaced overwing frame in accordance with Figures 1 and 2 at intervals specified in

Paragraph 1.E., Compliance. Based on findings do as follows:

Condition 3A (No Crack Found on Any Replaced Frame)

(1) Do repeat General Visual inspection and an Eddy Current, High Frequency (ETHF)

inspections of the replaced overwing frame in accordance with Figures 1 and 2 at intervals

specified in Paragraph 1.E., Compliance.

Condition 3B (Crack Found on Any Replaced Frame)

(1) Establish the length of the crack and do the work of Condition 2 or Condition 3.

7. If removed, install kept cusp membrane.

8. Install tape to seal along the cutout between the cusp membrane and frame.

9. Install all kept passenger compartment floor panels removed to gain access to the fuselage frames

between Stations Y=674.000 and Y=715.000. Refer to 717 AMM 53-21-01 as an accepted procedure

10. Install kept passenger compartment floor covering (carpet) by placing a strip of DMS 1971 double

sided adhesive tape around the perimeter of the carpet, and pressing the carpet to the floor. Refer

to 717 AMM 20-60-26 as an accepted procedure.

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ALERT ALERT
11. Install all kept items and attaching parts, as applicable from Stations Y=674.000 to Y=715.000

Item Accepted Procedure

Passenger Seats 717 AMM 25-23-05

Passenger Compartment Lining 717 AMM 25-28-02

Passenger Compartment Insulation 717 AMM 25-82-01

Overwing Emergency Exit Doors 717 AMM 52-21-01

12. Put the airplane back to a serviceable condition.

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ALERT ALERT
FIGURE 1: DETAILED VISUAL INSPECTION - OVERWING FRAMES

(SHEET 1 OF 2)

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ALERT ALERT
The step number shown below agrees with the number shown in the circle symbol in the figure.

MORE DATASTATION LOCA- IDENTIFICATION

TION

STEP TASK PROCEDURE NAME

1 Inspect General Visual Frame Sta. Y=674.000 9923405-503/-504 (a) (b) (c)

Sta. Y=696.000 9923406-503/-504

Sta. Y=715.000 9923407-503/-504

(a) Do a General Visual inspection of the frame in the shaded area at all accessible locations using remote

visual devices at Stations Y=674.000, Y=696.000 and Y=715.000 left and right sides.

(b) Utilize adjacent lightening holes for the remote visual inspection looking for cracks propagating inboard

and down from the upper radius of the frame tab.

(c) Refer to NDTSPM 09-00-06 for remote visual device usage and NDTSPM 09-00-04 for current supplier/vendor information.

FIGURE 1: DETAILED VISUAL INSPECTION - OVERWING FRAMES

(SHEET 2 OF 2)

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ALERT ALERT
FIGURE 2: EDDY CURRENT, HIGH FREQUENCY INSPECTION - OVERWING FRAMES

(SHEET 1 OF 2)

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BOEING SERVICE BULLETIN 717-53A0034

ALERT ALERT
The step number shown below agrees with the number shown in the circle symbol in the figure.

MORE DATASTATION LOCA- IDENTIFICATION

TION

STEP TASK PROCEDURE NAME

Eddy Current, Frame Sta. Y=674.000 9923405-503/-504 (a) (b) (c)

High Frequency

1 Inspect

Sta. Y=696.000 9923406-503/-504

Sta. Y=715.000 9923407-503/-504

(a) Do a ETHF inspection of the upper radius of the frame tab in the shaded area at Stations Y=674.000,

Y=696.000 and Y=715.000 left and right sides.

(b) Look for cracks propagating in the forward and aft direction. Refer to NDTSPM 06-10-01.001, Procedure

1, Calibration Method "G" and Scan Method "69".

(c) Any indication which exhibits the same relative phase angle and an amplitude of 50 percent or greater

than the indication obtained from the calibration notch in the reference standard is considered a crack.

FIGURE 2: EDDY CURRENT, HIGH FREQUENCY INSPECTION - OVERWING FRAMES

(SHEET 2 OF 2)

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ALERT ALERT
FIGURE 3: BLEND-OUT REPAIR - FRAME TAB UPPER RADIUS

(SHEET 1 OF 3)

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ALERT ALERT
FIGURE 3: BLEND-OUT REPAIR - FRAME TAB UPPER RADIUS

(SHEET 2 OF 3)

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ALERT ALERT
The step number shown below agrees with the number shown in the circle symbol in the figure.

IDENTIFICA- QTY MORE DATA

TION

STEP TASK NAME

(a) (b) (c) (d) (e)

(f)

1 Repair Frame - -

(a) Repairable crack limit: Blend-out not deeper than 0.125 inch with minimum 0.44R and verify crack is removed.

(b) Radius corners 0.060 / 0.030 Inch.

(c) Surface finish: 63 micro-inch finish or better.

(d) Glass bead peen or flap peen the frame tab surfaces following blend-out operation. Refer to SOPM 20-

10-10, as an accepted procedure.

(e) For glass bead peening, it is recommended that the intensity should not be greater than 0.005A (0.015N)

and the size of the glass beads shall be in the range of 83-165 (0.0083-0.016).

(f) Apply Alodine and FR Primer on all bare metal surfaces. Refer to 717 SRM 51-10-04 as an accepted

procedure.

FIGURE 3: BLEND-OUT REPAIR - FRAME TAB UPPER RADIUS

(SHEET 3 OF 3)

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BOEING SERVICE BULLETIN 717-53A0034

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