# Boeing Alert Service Bulletin 717-53A0034: Revision 1

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- Document: [Boeing Alert Service Bulletin 717-53A0034](https://openairdocs.org/service-documents/boeing/717-53a0034.md)
- Title as filed: U.S. DOT/FAA - SB-717-53A0034-01
- Pages: 36
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## Text

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### Page 1

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.
9E991ECCN:
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Unpublished Work.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, Dreamliner™,
BBJ, DC-8, DC-9, DC-10, KC-10, KDC-10, MD-10, MD-11, MD-80, MD-88, MD-90, P-8A, Poseidon and Boeing
liveries are all trademarks owned by The Boeing Company; and no trademark license is granted in connection
with this document unless provided in writing by Boeing. BOEING is a trademark of Boeing Management
Company.
Original Issue: October 05, 2011
717-53A0034Revision 1: November 07, 2012
1 of 36
3.0

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Table of Contents
Revision Transmittal Sheet ............................................ 5
Summary ...................................................... 7
1. PLANNING INFORMATION ........................................ 1 1
A. Effectivity ............................................... 1 1
1. Airplanes ............................................ 1 1
2. Spares Affected ........................................ 1 1
B. Concurrent Requirements ...................................... 1 1
C. Reason ................................................ 1 2
D. Description .............................................. 1 2
E. Compliance .............................................. 1 3
F. Approval ............................................... 1 5
G. Manpower .............................................. 1 5
H. Weight and Balance Changes .................................... 1 7
I. Electrical Load Data ......................................... 1 7
J. References .............................................. 1 7
1. Existing Data: ......................................... 1 7
2. Data Supplied with this Service Bulletin: ........................... 1 7
3. Installation Drawings Used in the Preparation of this Service Bulletin: ........... 1 8
K. Publications Affected ........................................ 1 8
L. Interchangeability and Intermixability of Parts ........................... 1 8
M. Software Accomplishment Summary ................................ 1 8
2. MATERIAL INFORMATION ........................................ 1 9
A. Material - Price and Availability ................................... 1 9
B. Industry Support Information .................................... 1 9
C. Parts Necessary for Each Airplane ................................. 1 9
1. Kits/Parts ............................................ 1 9
2. Parts and Materials Supplied by the Operator ........................ 2 2
3. Parts Modified and Reidentified ................................ 2 3
4. Parts Removed and Not Replaced .............................. 2 3
D. Parts Necessary to Change Spares ................................. 2 3
E. Special Tooling - Price and Availability ............................... 2 3
F. Special Tooling Necessary to do this Service Bulletin ....................... 2 3
3. ACCOMPLISHMENT INSTRUCTIONS .................................. 2 5
A. GENERAL INFORMATION ..................................... 2 5
B. WORK INSTRUCTIONS ....................................... 2 6
FIGURE 1: DETAILED VISUAL INSPECTION - OVERWING FRAMES ................. 3 0
FIGURE 2: EDDY CURRENT, HIGH FREQUENCY INSPECTION - OVERWING FRAMES ...... 3 2
FIGURE 3: BLEND-OUT REPAIR - FRAME TAB UPPER RADIUS ................... 3 4
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Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
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Commercial 
Airplanes
717
Service Bulletin
ALERT
Revision Transmittal SheetNumber: 717-53A0034Original 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
October 05, 2011Original Issue:
November 07, 2012Revision 1:
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Export Controlled ECCN: 9E991 - BOEING
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ALERTALERT
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Commercial 
Airplanes
717
Service Bulletin
ALERT
SummaryNumber: 717-53A0034Original 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.
Export Controlled ECCN: 9E991 - BOEING
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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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BOEING SERVICE BULLETIN 717-53A0034
ALERT  ALERT
- STA Y=674.000
- STA Y=696.000
- STA Y=715.000
00000000000000000/0000
INSPECT OVERWING
FRAMES FOR CRACKS
2087528
Original Issue: October 05, 2011
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### Page 11

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
DESCRIPTIONCONFIGURATIONGROUP
717-200 Airplanes-1
Airplane Models:
717-200
GroupFuselage Num-
ber
15002 - 5099
15100 - 5156
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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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
ZoneModel
151, 161717-200
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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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 )
ActionCondition
-Within 8275 flight
cycles after the
original issue date
on this service bul-
letin.
Before the accumu-
lation of 12,000 to-
tal flight cycles.
Do a general visual inspec-
tion and a high frequency
eddy current inspection of
the overwing frames at the
tab upper radius for cracks.
All Airplanes
9,300 flight cycles.--Do repeat general visual in-
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.
9,300 flight cycles.--Do repeat general visual in-
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 over-
wing 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 inspec-
tion and high frequency ed-
dy current inspection of the
repaired overwing frame.
AND
Do the action specified by
Condition 2A or 2B.
9,300 flight cycles.--Do repeat general visual in-
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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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 )
ActionCondition
--Before further
flight.
Replace the cracked over-
wing frame.
Condition 3
(Crack in Any
Frame is Equal To
or Greater Than
0.125 Inch in
Length)
AND
9,300 flight cycles.-Within 12,000 flight
cycles after replace-
ment.
Do a general visual inspec-
tion and high frequency ed-
dy current inspection of the
replaced overwing frame.
AND
Do the action specified by
Condition 3A or 3B.
9,300 flight cycles.--Do repeat general visual in-
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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 Time to make the parts
 Time to find the tools.
Condition 1
Elapsed HoursTask HoursNumber of PersonsTask
5.020.04Open Access
3.03.01FIGURE 1
3.03.01FIGURE 2
5.020.04Close Access
16.046.0TOTAL FOR EACH AIRPLANE
NOTE: Maximum total task hours and elapsed hours are given for inspection per airplane.
Condition 2
Elapsed HoursTask HoursNumber of PersonsTask
5.020.04Open Access
3.03.01FIGURE 1
3.03.01FIGURE 2
6.06.01Remove Cusp Mem-
brane
2.02.01FIGURE 3
6.06.01Install Cusp Mem-
brane
5.020.04Close Access
30.060.0TOTAL FOR EACH AIRPLANE
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
Elapsed HoursTask HoursNumber of PersonsTask
5.020.04Open Access
3.03.01FIGURE 1
3.03.01FIGURE 2
6.06.01Remove Cusp Mem-
brane
2.04.02Defuel
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Condition 3
Elapsed HoursTask HoursNumber of PersonsTask
10.020.02Remove Frame
24.048.02Install Frame
6.06.01Install Cusp Mem-
brane
5.020.04Close Access
64.0130.0TOTAL FOR EACH AIRPLANE
NOTE: Maximum total task hours and elapsed hours are given for the replacement of one frame.
Additional task hours and elapsed hours 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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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:
ADCNDCN/REVSheetTitleDrawing No
-ADWGFRAME INSTL - OVERWING SERVICE
REWORK DRAWING
SR95530013
3. Installation Drawings Used in the Preparation of this Service Bulletin:
None.
K. Publications Affected
1. Publications:
Chapter-SectionPublication
53-00Maintenance Planning Document
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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2.    MATERIAL INFORMATION
A. Material - Price and Availability
Boeing can supply the kits shown in Paragraph 2.C., Parts Necessary for Each Airplane . Operators
are encouraged to share schedule requirements with Boeing for incorporation of the service bulletin.
The parts are subject to the terms and conditions of the Boeing standard purchase order
acknowledgment. Prices are in United States Dollars. Terms: Net 30 days.
Reference this service bulletin and submit your purchase order by one of these methods:
1. Order on-line via ATA Spec 2000 or The Boeing PART Page
2. Fax to (206) 662-7145
REFER TO THE BOEING PART PAGE ON MYBOEINGFLEET.COM OR CONTACT FIRST RESPONDER
AT FR@BOEING.COM FOR THE LATEST REORDER LEAD TIME (ROLT) AND PRICE INFORMATION
Unit Price as of
the original date
of this Service
Bulletin (US Dol-
lars)
ROLT as of the
original date of
this Service Bul-
letin (Calendar
Days)
NameKit Number
$39,389.0090Service KitSA95530034-3
39,389.0090Service KitSA95530034-5
44,270.0090Service KitSA95530034-7
44,270.0090Service KitSA95530034-9
43,988.0090Service KitSA95530034-11
43,988.0090Service KitSA95530034-13
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:
KitStation Frame
SA95530034-3Y=674.000, Left Side
SA95530034-5Y=674.000, Right Side
SA95530034-7Y=696.000, Left Side
SA95530034-9Y=696.000, Right Side
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### Page 20

KitStation Frame
SA95530034-11Y=715.000, Left Side
SA95530034-13Y=715.000, Right Side
Kit SA95530034
NotesNameQTYNew Part Number
-13-11-9-7-5-3
CLIP....112913797-1
CLIP1111112913870-1
CLIP1111..2920753-1
CLIP....112920754-501
CLIP1..11.2920756-1
CLIP.11..12920756-2
(a)NUT ASSY10110198981001003D0006-3
(a)NUT ASSY2222223D0006-4
CLIP.....19919669-17
CLIP....1.9919669-18
CLIP.11...9919671-17
CLIP1..1..9919671-18
CLIP1111..9919671-19
CLIP1111..9919671-21
FRAME.....19923405-503
FRAME....1.9923405-504
FRAME...1..9923406-503
FRAME..1...9923406-504
FRAME.1....9923407-503
FRAME1.....9923407-504
CLIP...1..9971114-13
CLIP..1...9971114-14
CLIP.1....9971114-17
CLIP1.....9971114-18
PIN22..66HLT435-6-10
PIN....22HLT435-6-11
PIN111111HLT435-6-3
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Kit SA95530034
NotesNameQTYNew Part Number
-13-11-9-7-5-3
PIN333333HLT435-6-4
PIN222211HLT435-6-5
PIN363636362323HLT435-6-6
PIN223344HLT435-6-7
PIN121215151616HLT435-6-8
PIN995588HLT435-6-9
PIN....11HLT436-10-8
PIN2222..HLT436-12-10
PIN....22HLT436-12-11
PIN995555HLT436-6-2
PIN141418181111HLT436-6-3
PIN151518181515HLT436-6-4
PIN191921211515HLT436-6-5
PIN888888HLT436-6-6
PIN222211HLT436-6-7
PIN221111HLT436-6-8
PIN....11HLT436-6-9
PIN..11..HLT436-8-6
PIN443322HLT436-8-7
PIN444444HLT436-8-8
PIN....11HLT436-8-9
PIN....11HLT439-6-4
PIN....11HLT439-6-5
PIN....33HLT439-6-8
RIVET44101066MS20470AD5-10D
RIVET1515212166MS20470AD5-11D
RIVET11111313MS20470AD5-12D
RIVET....11MS20470AD5-13D
RIVET1111....MS20470AD5-8D
RIVET11..66MS20470AD5-9D
RIVET..11..MS20470AD6-12D
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Kit SA95530034
NotesNameQTYNew Part Number
-13-11-9-7-5-3
RIVET11....MS20470AD6-13D
RIVET....11MS20470AD6-14D
NUT656570705656MS21042L3
NUT666655MS21042L4
NUT....11MS21042L5
NUT222222MS21042L6
(b)BOLT2222..NAS8803-4
WASHER656570705656NAS1252-10L
WASHER666655NAS1252-416L
WASHER....11NAS1252-516L
WASHER222222NAS1252-616L
PIN....44S4931920-6-3
PIN4444..S4931920-6-4
PIN22....S4931920-6-5
PIN1616..1010S4931920-6-6
PIN8825251212S4931920-6-7
PIN..1144S4931920-6-8
(a) Or Approved Equivalent. Refer to AEPL Drawing 7595071.
(b) Alternate part based on existing bolts.
2. Parts and Materials Supplied by the Operator
NotesNameQTYPart Number / Specification
(a)Tape, Cloth Coated1 RollPC21F
(DMS 1968 Type 2)
OR
Equivalent
(b)Sealing Compound1 QuartPR-1422 Class B-2
(DMS 2082)
OR
Equivalent
(c)Tape, Adhesive, Double Faced1 RollPart Number 235
(DMS 1971)
OR
Equivalent
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### Page 23

CAGEShurtape Technologies, Limited Liability
Corporation (LLC)
Can be purchased from:(a)
4L0S0
1506 Highland Avenue North East
Hickory, North Carolina 28601
92108PRC-DeSoto International, IncorporatedCan be purchased from:(b)
P.O. Box 1800
Sylmar, California 91342
3X706Ideal Tape CompanyCan be purchased from:(c)
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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BLANK PAGE

### Page 25

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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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:
OperationAccepted Procedure
Sealant - Maintenance Practices717 AMM 20-60-01
Corrosion/Erosion Control and Prevention717 SRM 51-10-04
Drilling and Countersinking717 SRM 51-40-08
Repair Sealing717 SRM 51-20-05
Installing Bolts, Screws, and Washers717 SRM 51-41-01
Installing and Removing Rivets717 SRM 51-41-02
Installing and Removing Lockbolts717 SRM 51-41-03
Installing and Removing Hi-Lok Attachments717 SRM 51-41-05
Fastener Substitution and Interchangeability717 SRM 51-40-03
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:
Accepted ProcedureItem
717 AMM 25-23-05Passenger Seats
717 AMM 25-28-02Panel,Cabin Sidewall
717 AMM 25-82-01Passenger Compartment Insulation
717 AMM 52-21-01Overwing Emergency Exit Doors
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### Page 27

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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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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### Page 29

11. Install all kept items and attaching parts, as applicable from Stations Y=674.000 to Y=715.000
Accepted ProcedureItem
717 AMM 25-23-05Passenger Seats
717 AMM 25-28-02Passenger Compartment Lining
717 AMM 25-82-01Passenger Compartment Insulation
717 AMM 52-21-01Overwing Emergency Exit Doors
12. Put the airplane back to a serviceable condition.
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### Page 30 (OCR)

BOEING SERVICE BULLETIN 717-53A0034
ALERT  ALERT
STA Y=674.000
STA Y=696.000
STA Y=715.000
STATION FRAME
TYPICAL
CRACK
FRP
INSPECTION
AREA
LEFT SIDE SHOWN
RIGHT SIDE OPPOSITE  2087537
FIGURE 1: DETAILED VISUAL INSPECTION - OVERWING FRAMES
(SHEET 1 OF 2)
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### Page 31

The step number shown below agrees with the number shown in the circle symbol in the figure.
MORE DA-
TA
IDENTIFICATIONSTATION LOCA-
TION
NAMEPROCEDURETASKSTEP
(a) (b) (c)9923405-503/-504Sta. Y=674.000FrameGeneral VisualInspect1
9923406-503/-504Sta. Y=696.000
9923407-503/-504Sta. Y=715.000
(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 suppli-
er/vendor information.
FIGURE 1: DETAILED VISUAL INSPECTION - OVERWING FRAMES
(SHEET 2 OF 2)
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### Page 32 (OCR)

BOEING SERVICE BULLETIN 717-53A0034
ALERT  ALERT
STA Y=674.000
STA Y=696.000
STA Y=715.000
EDDY CURRENT
PROBE
STATION FRAME
TYPICAL
CRACK
INSPECTION
AREA
FRP
FRAME
TAB
RIGHT SIDE OPPOSITE  LEFT SIDE SHOWN  2087539
FIGURE 2: EDDY CURRENT, HIGH FREQUENCY INSPECTION - OVERWING FRAMES
(SHEET 1 OF 2)
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### Page 33

The step number shown below agrees with the number shown in the circle symbol in the figure.
MORE DA-
TA
IDENTIFICATIONSTATION LOCA-
TION
NAMEPROCEDURETASKSTEP
(a) (b) (c)9923405-503/-504Sta. Y=674.000FrameEddy Current,
High Frequency
Inspect1
9923406-503/-504Sta. Y=696.000
9923407-503/-504Sta. Y=715.000
(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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### Page 34 (OCR)

BOEING SERVICE BULLETIN 717-53A0034
ALERT  ALERT
STA Y=674.000
STA Y=696.000
STA Y=715.000
STATION FRAME
B
FRP
FRAME
TAB
PET Toure
LEFT SIDE SHOWN
RIGHT SIDE OPPOSITE  2087535
FIGURE 3: BLEND-OUT REPAIR - FRAME TAB UPPER RADIUS
(SHEET 1 OF 3)
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### Page 35 (OCR)

BOEING SERVICE BULLETIN 717-53A0034
ALERT  ALERT
0.060
- MAX  AREA OF POSSIBLE  CRACK
FRP —
0.125
MAX
0.56/0.44R
INBD
B-B
TYPICAL FRAME LOOKING FORWARD
2087538
FIGURE 3: BLEND-OUT REPAIR - FRAME TAB UPPER RADIUS
(SHEET 2 OF 3)
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### Page 36

The step number shown below agrees with the number shown in the circle symbol in the figure.
MORE DATAQTYIDENTIFICA-
TION
NAMETASKSTEP
(a) (b) (c) (d) (e)
(f)
--FrameRepair1
(a) Repairable crack limit: Blend-out not deeper than 0.125 inch with minimum 0.44R and verify crack is re-
moved.
(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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