Commercial 

Airplanes 717

Service Bulletin

ALERT

Number: 717-53A0036

Original Issue: August 12, 2013

ATA System: 5310

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

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

laws.

ECCN: 9E991

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ALERT ALERT

BLANK PAGE
Table of Contents

Summary ...................................................... 5

1. PLANNING INFORMATION ........................................ 9

A. Effectivity ................................................ 9

1. Airplanes ............................................. 9

2. Spares Affected ......................................... 9

B. Concurrent Requirements . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 10

C. Reason . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 10

D. Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 10

E. Compliance . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11

F. Approval . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13

G. Manpower . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14

H. Weight and Balance Changes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15

I. Electrical Load Data . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15

J. References . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15

1. Existing Data: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15

2. Data Supplied with this Service Bulletin: . . . . . . . . . . . . . . . . . . . . . . . . . . . 15

3. Installation Drawings Used in the Preparation of this Service Bulletin: . . . . . . . . . . . 16

4. Process Data: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 16

K. Publications Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 16

L. Interchangeability and Intermixability of Parts . . . . . . . . . . . . . . . . . . . . . . . . . . . 16

M. Software Accomplishment Summary . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 16

2. MATERIAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17

A. Material - Price and Availability . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17

B. Industry Support Information . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17

C. Parts Necessary for Each Airplane . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17

1. Kits/Parts . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17

2. Parts and Materials Supplied by the Operator . . . . . . . . . . . . . . . . . . . . . . . . 20

3. Parts Modified and Reidentified . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21

4. Parts Removed and Not Replaced . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21

D. Parts Necessary to Change Spares . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21

E. Special Tooling - Price and Availability . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21

F. Special Tooling Necessary to do this Service Bulletin . . . . . . . . . . . . . . . . . . . . . . . 21

3. ACCOMPLISHMENT INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 23

A. GENERAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 23

B. WORK INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25

FIGURE 1: OVERWING FRAME - GENERAL VISUAL INSPECTION . . . . . . . . . . . . . . . . . . 30

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

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BLANK PAGE
Commercial 

Airplanes 717

Service Bulletin

ALERT

Summary Number: 717-53A0036

Original Issue: August 12, 2013

ATA System: 5310

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

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

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

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

THE NEW OWNER.

CONCURRENT REQUIREMENTS

None.

BACKGROUND

Thirteen 717 airplanes have been reported with cracked overwing frames at Stations Y=674.000, Y=696.000

and Y=715.000. The airplanes had between 18,235 - 36,208 flight-hours and 11,991 - 45,091 landing cycles.

These cracked frames were addressed by Boeing Alert Service Bulletin 717-53A0034. Subsequent to the

issuance of Boeing Alert Service Bulletin 717-53A0034, one 717 airplane has been reported with a cracked

overwing frame, on the right side, at Station Y=737 which has a similar frame design. The airplane had

accumulated 31,960 flight-hours and 22,025 landing cycles. The frame crack was found during accomplishment

of a scheduled maintenance task that inspects the overwing floor beam-to-frame intersection. The crack, which

originated in the upper radius of the frame inboard tab just below the floor, was caused by fatigue. All the noted

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

Stations Y=737, left and right sides, will determine if cracks exist. Depending on the length of any crack found,

Boeing can provide frame repair and/or replacement instructions. If not corrected, an undetected crack may

sever the frame, which may increase the loading of adjacent frames and result in damage to adjacent structure

and extensive repair, or ultimately could lead to the loss of overall structural integrity of the airplane.

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

ACTION

NOTE: Boeing recommends Alert Service Bulletin 717-53A0034, Revision1 be accomplished in conjunction

with this service bulletin due to the short compliance time and proximity of the frame inspection area.

This service bulletin gives instructions to do a General Visual Inspection (GVI) and an Eddy Current High

Frequency (ETHF) inspection of the overwing frame at Station Y=737, left and right sides. Based on inspection

results, do as follows:

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CONDITION 1: NO CRACK IN FRAME FOUND

1. Do repetitive GVI and ETHF inspections of the overwing frame at Station 737 for cracks at the intervals

specified in Paragraph 1.E., Compliance.

CONDITION 2: ANY CRACK IN FRAME FOUND LESS THAN .125 INCH IN LENGTH

1. Option 1: Frame Repair

a. Contact Boeing for repair instructions and do the repair when specified in Paragraph 1.E.,

Compliance.

b. Do repetitive GVI and ETHF inspections of the repaired overwing frame as recommended by

Boeing.

2. Option 2: Frame Replacement

a. Replace the cracked overwing frame when specified in Paragraph 1.E., Compliance.

b. Do repetitive GVI and ETHF inspections of the replaced overwing frame when specified in Paragraph

1.E., Compliance.

CONDITION 3: ANY CRACK FOUND IN FRAME EQUAL TO OR GREATER THAN .125 INCH IN LENGTH

1. Replace the cracked overwing frame when specified in Paragraph 1.E., Compliance.

2. Do repetitive GVI and ETHF inspections of the replaced overwing frame when specified in Paragraph

1.E., Compliance.

EFFECTIVITY

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

COMPLIANCE

Refer to Paragraph 1.E., Compliance.

INDUSTRY SUPPORT INFORMATION

Boeing warranty remedies are not available for the inspection procedures given in this service bulletin.

MANPOWER

Refer to Paragraph 1.G., Manpower.

MATERIAL INFORMATION

Boeing Supplied Kits.

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

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BLANK PAGE
Commercial 

Airplanes 717

Service Bulletin

ALERT

Number: 717-53A0036

Original Issue: August 12, 2013

ATA System: 5310

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

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

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

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

THE NEW OWNER.

1. PLANNING INFORMATION

A. Effectivity

1. Airplanes

This service bulletin is for the airplanes shown below.

GROUP CONFIGURATION DESCRIPTION

1 - 717-200 Airplanes

Airplanes Not Initially Inspected in Accordance With Multi Operator

Message (MOM) MOM-MOM-13-0375-01B

1

Airplanes Initially Inspected in Accordance With Multi Operator

Message (MOM) MOM-MOM-13-0375-01B

2

Airplane Models:

717-200

Fuselage Num- Group

ber

5002 - 5099 1

5100 - 5156 1

2. Spares Affected

None.

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B. Concurrent Requirements

None.

C. Reason

Thirteen 717 airplanes have been reported with cracked overwing frames at Stations Y=674.000,

Y=696.000 and Y=715.000. The airplanes had between 18,235 - 36,208 flight-hours and 11,991 -

45,091 landing cycles. These cracked frames were addressed by Boeing Alert Service Bulletin

717-53A0034. Subsequent to the issuance of Boeing Alert Service Bulletin 717-53A0034, one 717

airplane has been reported with a cracked overwing frame, on the right side, at Station Y=737 which

has a similar frame design. The airplane had accumulated 31,960 flight-hours and 22,025 landing

cycles. The frame crack was found during accomplishment of a scheduled maintenance task that

inspects the overwing floor beam-to-frame intersection. The crack, which originated in the upper radius

of the frame inboard tab just below the floor, was caused by fatigue. All the noted frames are a part of

717 Principal Structural Element (PSE) 53.30.02.11. Inspection of the overwing frame at Stations

Y=737, left and right sides, will determine if cracks exist. Depending on the length of any crack found,

Boeing can provide frame repair and/or replacement instructions. If not corrected, an undetected crack

may sever the frame, which may increase the loading of adjacent frames and result in damage to

adjacent structure and extensive repair, or ultimately could lead to the loss of overall structural integrity

of the airplane.

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

D. Description

NOTE: Boeing recommends Alert Service Bulletin 717-53A0034, Revision1 be accomplished in

conjunction with this service bulletin due to the short compliance time and proximity of the

frame inspection area.

This service bulletin gives instructions to do a General Visual Inspection (GVI) and an Eddy Current

High Frequency (ETHF) inspection of the overwing frame at Station Y=737, left and right sides. Based

on inspection results, do as follows:

CONDITION 1: NO CRACK IN FRAME FOUND

1. Do repetitive GVI and ETHF inspections of the overwing frame at Station 737 for cracks at the

intervals specified in Paragraph 1.E., Compliance.

CONDITION 2: ANY CRACK IN FRAME FOUND LESS THAN .125 INCH IN LENGTH

1. Option 1: Frame Repair

a. Contact Boeing for repair instructions and do the repair when specified in Paragraph 1.E.,

Compliance.

b. Do repetitive GVI and ETHF inspections of the repaired overwing frame as recommended by

Boeing.

2. Option 2: Frame Replacement

a. Replace the cracked overwing frame when specified in Paragraph 1.E., Compliance.

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ALERT ALERT
b. Do repetitive GVI and ETHF inspections of the replaced overwing frame when specified in

Paragraph 1.E., Compliance.

CONDITION 3: ANY CRACK FOUND IN FRAME EQUAL TO OR GREATER THAN .125 INCH IN

LENGTH

1. Replace the cracked overwing frame when specified in Paragraph 1.E., Compliance.

2. Do repetitive GVI and ETHF inspections of the replaced overwing frame when specified in Paragraph

1.E., Compliance.

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

Affected Maintenance Zones

Model Zone

717-200 151, 161

E. Compliance

The Federal Aviation Administration (FAA) will possibly release an Airworthiness Directive related to

this service bulletin. The Airworthiness Directive will make the compliance tasks and times given in this

service bulletin mandatory.

Accomplish the required action(s), based on the applicable condition(s), in Table 1 or Table 2, in

accordance with Paragraph 3. Accomplishment Instructions.

When more than one OPTION is given for a CONDITION, do only one of the OPTION numbers. When

more than one ACTION is given for a CONDITION number or an OPTION number, do all of the ACTION

numbers for that CONDITION number or OPTION number.

Group 1, Configuration 1:

TABLE 1: LEFT AND RIGHT SIDE OVERWING FRAME AT STATION 737 - INSPECTION

Repeat Interval

(Not to Exceed)

Compliance Time (Whichever Occurs

Later )

Condition Action

Within 6000 flight -

cycles after the

original issue date

of this service bulletin.

Before 12,000 total

flight cycles.

Do a General Visual Inspection and a Eddy Current

High Frequency inspection

of the left and right side

overwing frames at Sta. 737

for cracks.

ALL AIRPLANES

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

cycles after initial

inspection.

Do General Visual Inspections and Eddy Current

High Frequency inspections

of the left and right side

overwing frames at Sta. 737

for cracks.

CONDITION 1: NO

CRACK IN FRAME

FOUND

(a)

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ALERT ALERT
Group 1, Configuration 1:

TABLE 1: LEFT AND RIGHT SIDE OVERWING FRAME AT STATION 737 - INSPECTION

Repeat Interval

(Not to Exceed)

Compliance Time (Whichever Occurs

Later )

Condition Action

Repeat inspection

of repaired overwing frame as recommended by

Boeing.

Before further -

flight.

OPTION 1: Contact Boeing

for repair instructions and

do the repair.

CONDITION 2:

ANY CRACK IN

FRAME FOUND

LESS THAN .125

INCH IN LENGTH

Before further - -

flight.

OPTION 2 (ACTION 1):

Replace the cracked overwing frame.

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

cycles after replacement.

OPTION 2 (ACTION 2): Do

General Visual Inspections

and Eddy Current High Frequency inspections of the

replaced overwing frame.

(a)

Before further - -

flight.

(ACTION 1) Replace the

cracked overwing frame.

CONDITION 3:

ANY CRACK

FOUND IN FRAME

EQUAL TO OR

GREATER THAN

.125 INCH IN

LENGTH

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

cycles after replacement.

(ACTION 2) Do General Visual Inspections and Eddy

Current High Frequency inspections of the replaced

overwing frame.

(a)

(a) If cracks are found during the repetitive inspections, do the work specified in Condition 2 or Condition 3.

Group 1, Configuration 2:

TABLE 2: LEFT AND RIGHT SIDE OVERWING FRAME AT STATION 737 - INSPECTION

Repeat Interval

(Not to Exceed)

Condition Action Compliance Time

Within 9,300 flight - -

cycles after overwing frame inspection at Sta. 737 or

within 12,000 flight

cycles after replacement.

Do a General Visual Inspection and a Eddy Current

High Frequency inspection

of the left and right side

overwing frame at Sta. 737

for cracks.

ALL AIRPLANES

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ALERT ALERT
Group 1, Configuration 2:

TABLE 2: LEFT AND RIGHT SIDE OVERWING FRAME AT STATION 737 - INSPECTION

Repeat Interval

(Not to Exceed)

Condition Action Compliance Time

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

cycles after initial

inspection.

Do General Visual Inspections and Eddy Current

High Frequency inspections

of the left and right side

overwing frame at Sta. 737

for cracks.

CONDITION 1: NO

CRACK IN FRAME

FOUND

(a)

Repeat inspection

of repaired overwing frame as recommended by

Boeing.

Before further -

flight.

OPTION 1: Contact Boeing

for repair instructions and

do the repair.

CONDITION 2:

ANY CRACK IN

FRAME FOUND

LESS THAN .125

INCH IN LENGTH

Before further - -

flight.

OPTION 2 (ACTION 1):

Replace the cracked overwing frame.

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

cycles after replacement.

OPTION 2 (ACTION 2): Do

General Visual Inspections

and Eddy Current High Frequency inspections of the

replaced overwing frame.

(a)

Before further - -

flight.

(ACTION 1) Replace the

cracked overwing frame.

CONDITION 3:

ANY CRACK

FOUND IN FRAME

EQUAL TO OR

GREATER THAN

.125 INCH IN

LENGTH

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

cycles after replacement.

(ACTION 2) Do General Visual Inspections and Eddy

Current High Frequency inspections of the replaced

overwing frame.

(a)

(a) If cracks are found during the repetitive inspections, do the work specified in Condition 2 or Condition 3.

F. Approval

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

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

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

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

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

changes.

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

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

before incorporating this service bulletin.

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ALERT ALERT
G. Manpower

The tables below show an estimate of the task hours necessary to do the inspections and frame

replacement for each airplane. This estimate is for direct labor only, done by an experienced crew.

Adjust the estimate with operator task hour data if necessary. The estimate does not include lost time.

These are some examples of lost time:

• Time to adjust to the workplace

• Time to schedule the work

• Time to inspect the work

• Time to cure the materials

• Time to make the parts

• Time to find the tools.

CONDITION 1:

Task Number of Persons Task Hours Elapsed Hours

Open Access 4 10.0 2.5

FIGURE 1 1 1.0 1.0

FIGURE 2 1 1.0 1.0

Close Access 4 10.0 2.5

TOTAL FOR EACH AIRPLANE 22.0 7.0

NOTE: Maximum total Task Hours and Elapsed Hours are given for the initial and repetitive inspection

of each airplane.

Condition 2, Option 1: Maximum total Task Hours and Elapsed Hours are based on repair instructions

from Boeing and are to be estimated by the operator.

Condition 2, Option 2 or Condition 3:

Task Number of Persons Task Hours Elapsed Hours

Open Access 4 20.0 5.0

FIGURE 1 1 1.0 1.0

FIGURE 2 1 1.0 1.0

Remove Cusp Mem- 1 6.0 6.0

brane

Defuel 2 4.0 2.0

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

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ALERT ALERT
Condition 2, Option 2 or Condition 3:

Task Number of Persons Task Hours Elapsed Hours

TOTAL FOR EACH AIRPLANE 126.0 60.0

NOTE: Maximum total Task Hours and Elapsed Hours are given for the replacement of one frame.

Additional Task Hours and Elapsed Hours to replace the other frame are contingent upon

inspection results and are to be estimated by the operator.

H. Weight and Balance Changes

None.

I. Electrical Load Data

Not changed.

J. References

1. Existing Data:

a. Multi Operator Message (MOM) MOM-MOM-13-0375-01B

b. Boeing Service Bulletin 717-53A0034, Revision 1

c. Boeing Drawings, 5940477, 7595071, 9910151, SE10000000

d. Non-Destructive Test Standard Practices Manual (NDTSPM), Document Number MDC93K0393,

Part 06 Eddy Current: 06-10-01.001 (Procedure 1 - Surface Defect Detection), Part 09

Visual/Optical: 09-00-04 (Suppliers/Vendors), Part 09 Visual/Optical: 09-00-06 (Process

Examples), Part 09 Visual/Optical: 09-00-07 (Evaluation/Verification)

e. 717 Aircraft Maintenance Manual (AMM) 07-20-01, 12-11-01, 20-60-01, 20-60-26, 25-23-05,

25-28-02, 25-82-01, 52-21-01, 53-21-01, 53-53-01

f. 717 Fleet Team Digest (FTD) 53-09003

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

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

2. Data Supplied with this Service Bulletin:

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

bulletin submit a data request to:

Data and Services Management

MS D800-0019

3855 Lakewood Boulevard

Long Beach, California 90846

Phone: (562) 593-6996

Fax: (562) 593-2001

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ALERT ALERT
E-mail: dse.boecom@boeing.com

a. Drawings:

Drawing No Title Sheet DCN/REV ADCN

5940477 COVER INSTL CUSP HOLE DWG B -

CUSP AND MEMBRANE INSTL - STA 484 DWG CH -

TO 623

9910151

FRAME INSTL - OVERWING SERVICE DWG - -

REWORK DRAWING

SR95530016

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

None.

4. Process Data:

Douglas Process Specifications referred to on the drawings and in the Work Instructions are not

given in this service bulletin since these procedures are frequently used as standard shop practices.

K. Publications Affected

1. Publications:

None.

2. Damage Tolerance Based Structural Inspections:

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

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

Maintenance Program. This service bulletin affects FCS. DTI requirements for the structure affected

are contained in Paragraph 1.E., Compliance of this service bulletin.

L. Interchangeability and Intermixability of Parts

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

M. Software Accomplishment Summary

Not affected.

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BOEING SERVICE BULLETIN 717-53A0036

ALERT ALERT
2. MATERIAL INFORMATION

A. Material - Price and Availability

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

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

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

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

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

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

2. Fax to (206) 662-7145

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

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

Unit Price as of

the original date

of this Service

Bulletin (US Dollars)

ROLT as of the

original date of

this Service Bulletin (Calendar

Days)

Kit Number Name

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

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

B. Industry Support Information

Boeing warranty remedies are not available for the inspection procedures given in this service bulletin.

C. Parts Necessary for Each Airplane

1. Kits/Parts

Condition 1, Condition 2, Option 1

None.

Condition 2, Option 2 and Condition 3

Kit SA95530036

Existing Part Notes

Number

New Part Number QTY Name

-3 -5

Frame Instl Kit -

LHS - Station 737

SA95530036-3 - .

Frame Instl Kit -

RHS - Station 737

SA95530036-5 . -

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ALERT ALERT
Kit SA95530036

Existing Part Notes

Number

New Part Number QTY Name

-3 -5

2913870-1 1 1 CLIP (a)

2920756-1 1 . CLIP

2920756-2 . 1 CLIP

3D0006-3 94 94 NUT ASSY (c)

3D0006-4 3 3 NUT ASSY (c)

9919672-19 1 1 CLIP (a)

9919672-23 1 . CLIP

9919672-24 . 1 CLIP

9919672-63 1 1 CLIP

9919672-7 1 1 SPACER

9923408-503 1 . FRAME

9923408-504 . 1 FRAME

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ALERT ALERT
Kit SA95530036

Existing Part Notes

Number

New Part Number QTY Name

-3 -5

HLT435-6-4 4 4 PIN (b)

HLT435-6-7 1 1 PIN

HLT435-6-8 5 5 PIN

HLT435-8-6 1 1 PIN

HLT435-8-7 2 2 PIN

HLT436-6-2 2 2 PIN

HLT436-6-3 11 11 PIN

HLT436-6-4 4 4 PIN

HLT436-6-5 22 22 PIN

HLT436-6-6 4 4 PIN

HLT436-6-7 4 4 PIN

HLT436-6-8 4 4 PIN

HLT436-6-9 4 4 PIN

HLT436-8-5 9 9 PIN

HLT436-8-7 2 2 PIN

HLT439-6-5 2 2 PIN

HLT439-6-6 29 29 PIN

HLT439-6-7 8 8 PIN

HLT439-6-8 15 15 PIN

MS20470AD5-10D 2 2 RIVET

MS20470AD5-11D 12 12 RIVET

MS20470AD5-12D 5 5 RIVET

MS20470AD5-13D 13 13 RIVET

MS20470AD6-14D 1 1 RIVET

MS21042L3 55 55 NUT

MS21042L4 11 11 NUT

NAS1097AD6-12D 1 1 RIVET (b)

NAS1252-10L 55 55 WASHER

NAS1252-416L 11 11 WASHER

S4931920-6-6 4 4 PIN (b) (c)

S4931920-6-8 26 26 PIN

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ALERT ALERT
Kit SA95530036

Existing Part Notes

Number

New Part Number QTY Name

-3 -5

(a) 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.

(b) If grip length shown is not available at Boeing, fasteners supplied in kits may

be one grip length longer than indicated. Also, if any fasteners part numbers

listed are not available or have been superseded, substitute fasteners may be

supplied in kits.

(c) Or approved equivalent. Refer to Approved Equivalent Parts List Drawing (AEPL)

7595071.

2. Parts and Materials Supplied by the Operator

NOTE: If removal of the 9910151 Membranes are necessary for overwing frame

inspection/replacement, operator's should refer to the 9910151 Drawing for the fasteners

and materials necessary to reinstall the membranes.

Part Number / Specification QTY Name Notes

Tape, Cloth Coated, Pressure Sensi- (a)

tive

Polyken 225 or Polyken 225FR 1 Roll

(DMS 1968-2, Type 2)

OR

Equivalent

OR

Tape, Adhesive, Insulation Cover (b)

Splicing

Orcon OT-16A

(DMS 1984, Type 6, Class 2)

OR

Equivalent

1 Sealing Compound (c)

Quart

PR-1422 Class B-2

(DMS 2082)

OR

Equivalent

235 1 Roll Tape, Adhesive, Double Faced (d)

(DMS 1971)

OR

Equivalent

(a) Can be purchased from: Covalence Specialty Adhesives Limited Liability Corporation

(LLC) (CAGE: 80769), 25 Forge Parkway, Franklin, Massachusetts 02038.

(b) Can be purchased from: Orcon Corporation (CAGE: 1WFJ0), 1570 Atlantic Street, Union

City, California 94587.

(c) Can be purchased from: PRC-DeSoto International, Incorporated (CAGE: 92108), 12780

San Fernando Road, Sylmar, California 91342.

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ALERT ALERT
Part Number / Specification QTY Name Notes

(d) Can be purchased from: Ideal Tape Company (CAGE:3X706), 1400 Middlesex Street,

Lowell, Massachusetts 01851.

3. Parts Modified and Reidentified

None.

4. Parts Removed and Not Replaced

None.

D. Parts Necessary to Change Spares

None

E. Special Tooling - Price and Availability

The operator can supply the tools shown in Paragraph 2.F., Special Tooling Necessary to do this

Service Bulletin. Tool price and supply data are not given.

F. Special Tooling Necessary to do this Service Bulletin

General Visual Inspection (GVI) equipment and Eddy Current High Frequency (ETHF) inspection

equipment necessary to accomplish this service bulletin are listed in the Non-Destructive Testing

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

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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 SRM 51.

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

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

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

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

grip length in accordance with SRM Chapter 51.

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

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

accumulation of tolerances.

EXCEPTION: When the available fastener length increments are greater than

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

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

specified.

7. Unless shown differently, these dimensions and tolerances are used:

– Linear dimensions are in inches

– Tolerance on linear dimensions, other than rivet and bolt edge margins, is plus

or minus 0.03 inch.

– Tolerance on rivet and bolt edge margin is plus or minus 0.05 inch

– Angular tolerance is plus or minus 2 degrees

– Hole dimensions for standard solid rivets are in 717 SRM 51.

– Torque Values:

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ALERT ALERT
— Values for structural fasteners are given in 717 Structural Repair Manual,

Chapter 51.

— Values for airframe maintenance tasks are included in Chapter 20 of 717

Airplane Maintenance Manual (AMM).

— Values for electrical maintenance tasks are included in Chapter 20 of

Standard Wiring Practices Manual (SWPM).

— Values for engine maintenance tasks are included in Chapter 70 of 717

Airplane Maintenance Manual (AMM).

— Non-standard torque values for maintenance tasks are included in the

applicable installation step.

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

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

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

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

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

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

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

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

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

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

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

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

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

must be used.

11. If it is necessary to remove more parts for access, you can remove those parts. If

you can get access without removing identified parts, it is not necessary to remove

all of the identified parts. Jacking and shoring limitations must be observed.

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

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

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

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

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

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

14. If shading is used, shaded areas in Figures are reference only. Shaded areas in

Figures may look different than your airplane.

15. Boeing recommends Alert Service Bulletin 717-53A0034, Revision1 be accomplished

in conjunction with this service bulletin due to the short compliance time and proximity

of the overwing frame inspection area.

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ALERT ALERT
16. Some steps in the Work Instructions are identified as Required for Compliance (RC).

If this service bulletin is mandated by an Airworthiness Directive (AD), then the steps

identified as RC must be done to comply with the AD. Alternative procedures for

steps not identified with RC can be used if the RC steps can still be done as specified,

and the airplane can be put back in a serviceable condition. An Alternative Method

of Compliance (AMOC) is not necessary for deviations to steps that are not identified

as RC.

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

Accepted Procedure Operation

717 AMM 20-60-01 Sealant - Maintenance Practices

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

717 SRM 51-20-05 Repair Sealing

717 SRM 51-40-03 Fastener Substitution and Interchangeability

717 SRM 51-40-08 Drilling, Countersinking, and Dimpling

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 Fasteners

B. WORK INSTRUCTIONS

1. Remove and keep passenger compartment items and attaching parts, as necessary, to get access

to the overwing frame inspection area at Station Y=737, on the left and right sides. Refer to Table

1 for a list of AMM accepted procedures:

TABLE 1

Item Accepted Procedure

Seats, Passenger 717 AMM 25-23-05

Panel, Cabin Sidewall 717 AMM 25-28-02

Insulation, Passenger Compartment 717 AMM 25-82-01

Door, Overwing Emergency Exit 717 AMM 52-21-01

Floor Coverings 717 AMM 20-60-26

Floor Panels, Passenger Compartment 717 AMM 53-21-01

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

frame inspection area.

3. Remove and keep the cusp membrane to get access to frame inspection area. Use operator's

standard shop practices.

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ALERT ALERT
NOTE: Removal of the cusp membrane may not be necessary if it is determined that there is

sufficient access to do the inspections that follow.

4. RC - Do a General Visual Inspection (GVI) and an Eddy Current, High Frequency (ETHF) inspection

of the overwing frame at Station Y=737 for cracks, on the left and right sides, in accordance with

FIGURE 1 and FIGURE 2.

5. CONDITION 1: NO CRACK IN FRAME FOUND:

a. If removed, install the kept cusp membrane for each frame. Use operator's standard shop

practices.

NOTE: Refer to Boeing Drawing 9910151 for installation fasteners and materials.

b. Apply DMS 1968, Type 2, Cloth Coated Tape or DMS 1984, Type 6, Class 2, Adhesive Tape

from the cutout in the cusp membrane to the overwing frame at Station Y=737 to control the

flow of cabin air. Strips of tape may be overlapped to nest in and around the frame and extend

1 1/2 inches minimum onto the membrane and overwing frame. The tape may be split or

applied in strips to close the openings around conduit passing through the membrane in the

area noted on the drawing. Refer to Boeing Drawing 5940477 and DPS 2.590-4 as an accepted

procedure.

c. Install the kept passenger compartment items and attaching parts removed to get access to

the overwing frame inspection area at Station Y=737, on the left and right sides.

d. Put the airplane back to a serviceable condition.

e. RC - Do repetitive GVI and ETHF inspections of the overwing frame at Station Y=737 for

cracks, on the left and right sides, in accordance with FIGURE 1 and FIGURE 2.

6. CONDITION 2: ANY CRACK IN FRAME FOUND LESS THAN .125 INCH IN LENGTH

a. Option 1: Frame Repair

(1) RC - Contact Boeing for repair instructions and do the repair.

(2) Put the airplane back to a serviceable condition.

(3) RC - Do repetitive inspections of the repaired overwing frame at Station Y=737 for cracks,

on the left and right sides, as recommended by Boeing.

b. Option 2: Frame Replacement

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

CAUTION: OPERATORS SHOULD SUSPEND ANY MAINTENANCE PROCEDURES

THAT WOULD AFFECT THE AIRFRAME LOADS DURING THE OVERWING

FRAME REPLACEMENT. IF SUCH MAINTENANCE PROCEDURES ARE NOT

SUSPENDED, DAMAGE TO THE AIRFRAME CAN OCCUR.

(2) Support the airplane as follows:

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ALERT ALERT
(a) If both the left and right sides of the overwing frame are cracked, operators should

replace the cracked frame on one side of the airplane before starting the replacement

of the opposite side while the airplane is on its wheels.

(b) Shoring of the airplane is necessary if the frames on both sides of the airplane are

to be replaced at the same time. Refer to 717 AMM 07-20-01 as an accepted

procedure.

(3) In the passenger compartment, remove and keep additional interior items and attaching

parts between L9 and L18, on the left and/or right sides, to get access to the cracked

overwing frame at Station Y=737.

(4) Remove and keep the cusp membrane to get access to overwing frame replacement

area. Use operator's standard shop practices.

(5) Remove and keep the applicable wing to fuselage fillet panel,150FL on the left side and/or

160FR on the right side, to get access to the cracked overwing frame exterior. Refer to

717 AMM 53-53-01 as an accepted procedure.

(6) RC - Replace cracked overwing frame in accordance with Service Rework Drawing

SR95530016, Revision Level New.

(7) Install the kept cusp membrane for each frame. Use operator's standard shop practices.

NOTE: Refer to Boeing Drawing 9910151 for installation fasteners and materials.

(8) Apply DMS 1968, Type 2, Cloth Coated Tape or DMS 1984, Type 6, Class 2, Adhesive

Tape from the cutout in the cusp membrane to the overwing frame at Station Y=737 to

control the flow of cabin air. Strips of tape may be overlapped to nest in and around the

frame and extend 1 1/2 inches minimum onto the membrane and overwing frame. The

tape may be split or applied in strips to close the openings around conduit passing through

the membrane in the area noted on the drawing. Refer to Boeing Drawing 5940477 and

DPS 2.590-4 as an accepted procedure.

(9) Install the kept passenger compartment items and attaching parts between L9 and L18,

on the left and/or right sides, removed to get access to the cracked overwing frame at

Station Y=737. Refer to Table 2 for a list of accepted AMM procedures.

TABLE 2

Item Accepted Procedure

Seats, Passenger 717 AMM 25-23-05

Panel, Cabin Sidewall 717 AMM 25-28-02

Insulation, Passenger Compartment 717 AMM 25-82-01

Door, Overwing Emergency Exit 717 AMM 52-21-01

Floor Coverings 717 AMM 20-60-26

Floor Panels, Passenger Compartment 717 AMM 53-21-01

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ALERT ALERT
(10) Install the kept applicable wing to fuselage fillet panel,150FL on the left side and/or 160FR

on the right side, removed to get access to the cracked overwing frame exterior. Refer

to 717 AMM 53-53-01 as an accepted procedure.

(11) Put the airplane back to a serviceable condition.

(12) RC - Do repetitive GVI and ETHF inspections of the overwing frame at Station Y=737 for

cracks, on the left and right sides, in accordance with FIGURE 1 and FIGURE 2.

7. CONDITION 3: ANY CRACK FOUND IN FRAME EQUAL TO OR GREATER THAN .125 INCH

IN LENGTH

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

CAUTION: OPERATORS SHOULD SUSPEND ANY MAINTENANCE PROCEDURES THAT

WOULD AFFECT THE AIRFRAME LOADS DURING THE OVERWING FRAME

REPLACEMENT. IF SUCH MAINTENANCE PROCEDURES ARE NOT

SUSPENDED, DAMAGE TO THE AIRFRAME CAN OCCUR.

b. Support the airplane as follows:

(1) If both the left and right sides of the overwing frame are cracked, operators should replace

the cracked frame on one side of the airplane before starting the replacement of the

opposite side while the airplane is on its wheels.

(2) Shoring of the airplane is necessary if the frames on both sides of the airplane are to be

replaced at the same time. Refer to 717 AMM 07-20-01 as an accepted procedure.

c. In the passenger compartment, remove and keep additional interior items and attaching parts

between L9 and L18, on the left and/or right sides, to get access to the cracked overwing

frame at Station Y=737.

d. Remove and keep the cusp membrane to get access to frame replacement area. Use operator's

standard shop practices.

e. Remove and keep the applicable wing to fuselage fillet panel,150FL on the left side and/or

160FR on the right side, to get access to the cracked overwing frame exterior. Refer to 717

AMM 53-53-01 as an accepted procedure.

f. RC - Replace cracked overwing frame in accordance with Service Rework Drawing

SR95530016, Revision Level New.

g. Install the kept cusp membrane for each frame. Use operator's standard shop practices.

NOTE: Refer to Boeing Drawing 9910151 for installation fasteners and materials.

h. Apply DMS 1968, Type 2, Cloth Coated Tape or DMS 1984, Type 6, Class 2, Adhesive Tape

from the cutout in the cusp membrane to the overwing frame at Station Y=737 to control the

flow of cabin air. Strips of tape may be overlapped to nest in and around the frame and extend

1 1/2 inches minimum onto the membrane and overwing frame. The tape may be split or

applied in strips to close the openings around conduit passing through the membrane in the

area noted on the drawing. Refer to Boeing Drawing 5940477 and DPS 2.590-4 as an accepted

procedure.

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ALERT ALERT
i. Install the kept passenger compartment items and attaching parts between L9 and L18, on

the left and/or right sides, removed to get access to the cracked overwing frame at Station

Y=737. Refer to Table 2 for a list of accepted AMM procedures.

TABLE 2

Item Accepted Procedure

Seats, Passenger 717 AMM 25-23-05

Panel, Cabin Sidewall 717 AMM 25-28-02

Insulation, Passenger Compartment 717 AMM 25-82-01

Door, Overwing Emergency Exit 717 AMM 52-21-01

Floor Coverings 717 AMM 20-60-26

Floor Panels, Passenger Compartment 717 AMM 53-21-01

j. Install the kept applicable wing to fuselage fillet panel,150FL on the left side and/or 160FR

on the right side, removed to get access to the cracked overwing frame exterior. Refer to 717

AMM 53-53-01 as an accepted procedure.

k. Put the airplane back to a serviceable condition.

l. RC - Do repetitive GVI and ETHF inspections of the overwing frame at Station Y=737 for

cracks, on the left and right sides, in accordance with FIGURE 1 and FIGURE 2.

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ALERT ALERT
FIGURE 1: OVERWING FRAME - GENERAL VISUAL INSPECTION

(SHEET 1 OF 2)

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BOEING SERVICE BULLETIN 717-53A0036

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

STEP TASK PROCEDURE NAME IDENTIFICATION MORE DATA

General Visual Frame 9923408-503/-504 (a) (b) (c) (d)

(GVI)

1 Inspect

(a) Do a General Visual Inspection of the overwing frame in the inspection area. Use of remote

visual devices to access all locations is acceptable.

(b) Use adjacent lightening holes for the remote visual inspection. Look for cracks that start inboard

and down from the upper radius of the frame tab.

(c) Refer to NDTSPM Part 09 Visual/Optical: 09-00-06 (Process Examples) for remote visual device

usage and NDTSPM Part 09 Visual/Optical: 09-00-04 (Suppliers/Vendors) for current supplier/vendor information.

(d) Refer to NDTSPM Part 09 Visual/Optical: 09-00-07 (Evaluation/Verification) for general information on how to evaluate a suspect indication of a defect. Refer to Owner Operator Manual

of specific device on its operation to aid in the discovery and sizing of any suspected defect.

FIGURE 1: OVERWING FRAME - GENERAL VISUAL INSPECTION

(SHEET 2 OF 2)

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ALERT ALERT
FIGURE 2: OVERWING FRAME - EDDY CURRENT HIGH FREQUENCY INSPECTION

(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.

STEP TASK PROCEDURE NAME IDENTIFICATION MORE DATA

Eddy Current, Frame 9923408-503/-504 (a) (b) (c)

High Frequency

(ETHF)

1 Inspect

(a) Do an ETHF inspection of the upper radius of the frame tab in the inspection area in accordance

with NDTSPM Part 06 Eddy Current: 06-10-01.001 (Procedure 1 - Surface Defect Detection),

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

(b) Look for cracks that start in the forward and aft direction.

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

greater than the indication obtained from the calibration notch in the reference standard is

considered a crack.

FIGURE 2: OVERWING FRAME - EDDY CURRENT HIGH FREQUENCY INSPECTION

(SHEET 2 OF 2)

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