# Boeing Alert Service Bulletin MD90-53A031: No revision named

- Rights: © The Boeing Company. Filed by the FAA in regulations.gov docket FAA-2009-0783; AD 2010-05-04 incorporates this document by reference. Not covered by OpenAirDocs’ CC0 dedication.
- Document: [Boeing Alert Service Bulletin MD90-53A031](https://openairdocs.org/service-documents/boeing/md90-53a031.md)
- Title as filed: U.S. DOT/FAA - Boeing Service Bulletin
- Pages: 35
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## Text

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### Page 1

McDonnell DouglasCommercial 
Airplanes
MD90
Service Bulletin
ALERT
Number: MD90-53A031
Original Issue: April 10, 2009
ATA System: 5310
SUBJECT: FUSELAGE - Fuselage Main Frame - Inspect Overwing Frames for Cracks
Export of this technology is controlled under the United States Export Administration Regulations (EAR) (15
CFR 730-774). 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 © 2009 The Boeing Company
Unpublished Work - All Rights Reserved
Boeing claims copyright in each page of this document only to the extent that the page contains copyrightable
subject matter. Boeing also claims copyright in this document as a compilation and/or collective work.
This document includes proprietary information owned by The Boeing Company and/or one or more third parties.
Treatment of the document and the information it contains is governed by contract with Boeing. For more
information, contact The Boeing Company, P .O. Box 3707, Seattle, Washington 98124.
Boeing, the Boeing signature, the Boeing symbol, 707, 717, 727, 737, 747, 757, 767, 777, 787, Dreamliner,
BBJ, DC-8, DC-9, DC-10, MD-10, MD-11, MD-80, MD-88, MD-90, P-8A, Poseidon and the Boeing livery 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.
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Table of Contents
Summary ..................................................... 5
1. PLANNING INFORMATION ......................................... 9
A. Effectivity ................................................ 9
1. Airplanes ............................................. 9
2. Spares Affected ........................................ 1 1
B. Concurrent Requirements ...................................... 1 1
C. Reason ................................................ 1 1
D. Description .............................................. 1 1
E. Compliance .............................................. 1 2
F . Approval ............................................... 1 3
G. Manpower .............................................. 1 3
H. Weight and Balance Changes .................................... 1 4
I. Electrical Load Data ......................................... 1 5
J. References .............................................. 1 5
1. Existing Data .......................................... 1 5
2. Data supplied with this Service Bulletin ............................ 1 5
3. Installation Drawings Used in the Preparation of this Service Bulletin ............ 1 5
K. Publications Affected ......................................... 1 5
L. Interchangeability and Intermixability of Parts ........................... 1 6
2. MATERIAL INFORMATION ........................................ 1 7
A. Material - Price and Availability ................................... 1 7
B. Industry Support Information .................................... 1 7
C. Parts Necessary For Each Airplane ................................. 1 8
1. Kits/Parts ............................................ 1 8
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 4
3. ACCOMPLISHMENT INSTRUCTIONS .................................. 2 5
A. GENERAL INFORMATION ..................................... 2 5
B. WORK INSTRUCTIONS ....................................... 2 6
FIGURE 1: DETAILED VISUAL INSPECTION - OVERWING FRAMES ................. 2 9
FIGURE 2: EDDY CURRENT, HIGH FREQUENCY INSPECTION - OVERWING FRAMES ...... 3 1
FIGURE 3: BLEND-OUT REPAIR - FRAME TAB UPPER RADIUS .................... 3 3
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McDonnell DouglasCommercial 
Airplanes
MD90
Service Bulletin
ALERT
SummaryNumber: MD90-53A031Original Issue: April 10, 2009
ATA System: 5310
SUBJECT: FUSELAGE - 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 no report of a cracked overwing frame on an MD-90 airplane but due
to similarity in frame design, the MD-90's 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 MD-90
overwing frames at Stations 883, 902, 924, 943 and 962 are also susceptible to this type of failure. All the noted
frames are a part of MD-90 Principal Structural Element (PSE) 53.12.09.1 Inspection of the overwing frames
from Station 883 to 962 on 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.
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 883, 902, 924, 943 and 962 on 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)
1. Does repetitive inspections of the overwing frames for cracks.
Condition 2 (Crack Less than 0.125 Inch in Depth)
1. Does a blend-out repair of the crack.
2. Does repetitive inspections of the overwing frames for cracks.
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Condition 3 (Crack is Equal To or Greater Than 0.125 Inch in Depth)
1. Replaces the cracked overwing frame.
2. Does repetitive inspections of the overwing frames for cracks.
EFFECTIVITY
All MD-90-30 Airplanes. Refer to Paragraph 1.A.1., Airplanes for the list of affected airplanes.
COMPLIANCE
Refer to Paragraph 1.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.
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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### Page 7 (OCR)

BOEING SERVICE BULLETIN MD90-534031
ALERT  ALERT
STA Y=962.000
STA Y=943.000
STA Y=924.000
STA Y=902.000
STA Y=883.000
D0000 000
INSPECT OVERWING
FRAMES FOR CRACKS
1732686
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McDonnell DouglasCommercial 
Airplanes
MD90
Service Bulletin
ALERT
Number: MD90-53A031
Original Issue: April 10, 2009
ATA System: 5310
SUBJECT: FUSELAGE - 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
This service bulletin is for the airplanes shown below.
DESCRIPTIONCONFIGURATIONGROUP
All MD-90 Airplanes-1
Airplane Models:
MD-90-30
GroupFuselage Num-
ber
12094 - 2100
12115
12117
12120
12122 - 2123
12125 - 2126
12129
12131
12133
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GroupFuselage Num-
ber
12136
12138
12140 - 2144
12146 - 2147
12149 - 2150
12153 - 2154
12156 - 2159
12161 - 2166
12169 - 2171
12173
12175
12177
12179
12181 - 2182
12184
12186
12190 - 2191
12193 - 2195
12197 - 2198
12200
12202 - 2203
12205
12207
12209 - 2213
12215 - 2217
12219 - 2233
12235 - 2237
12240
12243
12245
12248
12250 - 2251
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GroupFuselage Num-
ber
12253
12255 - 2263
12288 - 2290
14001 - 4002
2. Spares Affected
None.
B. Concurrent Requirements
None.
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 no report of a cracked overwing frame on an MD-90
airplane but due to similarity in frame design, the MD-90's 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 MD-90 overwing frames at Stations 883, 902, 924, 943 and 962 are also
susceptible to this type of failure. All the noted frames are a part of MD-90 Principal Structural Element
(PSE) 53.12.09.1 Inspection of the overwing frames from Station 883 to 962 on 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.
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 883, 902, 924, 943 and 962 on 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, does as follows:
Condition 1 (No Crack)
1. Does repetitive inspections of the overwing frames for cracks.
Condition 2 (Crack Less than 0.125 Inch in Depth)
1. Does a blend-out repair of the crack.
2. Does repetitive inspections of the overwing frames for cracks.
Condition 3 (Crack is Equal To or Greater Than 0.125 Inch in Depth)
1. Replaces the cracked overwing frame.
2. Does repetitive inspections of the overwing frames for cracks.
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The work in this service bulletin is done in the maintenance zone(s) given below.
Affected Maintenance Zones
ZoneModel
151, 161MD-90-30
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.
Table 1: Inspect Left and Right Side Overwing Frames for Cracks from Station 883 to 962
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever Occurs
Later )
ActionCondition
-Within 60 months
after the original is-
sue date on this
service bulletin.
Before the accumu-
lation of 20,000 to-
tal flight cycles.
Do a general visual inspec-
tion and a high frequency
eddy current inspection of
the overwing frames in ac-
cordance with Accomplish-
ment Instructions 3.B.
All Airplanes
5,900 flight cycles.--Do repeat general visual in-
spection and high frequency
eddy current inspection of
the overwing frames in ac-
cordance with Accomplish-
ment Instructions 3.B.
Condition 1
(No Crack Found)
--Before further
flight.
Repair the cracked over-
wing frame in accordance
with Accomplishment In-
structions 3.B.
Condition 2
(Crack Found is
Less Than 0.125
Inch in Depth)
AND
5,900 flight cycles.--Do a general visual inspec-
tion and high frequency ed-
dy current inspection of the
repaired overwing frame in
accordance with Accom-
plishment Instructions 3.B.
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Table 1: Inspect Left and Right Side Overwing Frames for Cracks from Station 883 to 962
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever Occurs
Later )
ActionCondition
--Before further
flight.
Replace the cracked over-
wing frame in accordance
with Accomplishment In-
structions 3.B.
Condition 3
(Crack Found is
Equal To
OR
Greater Than 0.125
Inch in Depth) AND
5,900 flight cycles.-Within 20,000 flight
cycles after replace-
ment.
Do a general visual inspec-
tion and high frequency ed-
dy current inspection of the
replacement overwing
frame in accordance with
Accomplishment Instruc-
tions 3.B.
F. Approval
The resultant modification described in Paragraph 1.D has been shown to comply with the applicable
Federal Aviation Regulations and is approved by the Manager, Los Angeles Aircraft Certification Office,
FAA Northwest Mountain Region.
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
 Time to make the parts
 Time to find the tools.
Condition 1
Elapsed HoursTask HoursNumber of PersonsTask
8.032.04Open Access
5.05.01Visual Inspect
5.05.01ETHF Inspect
8.032.04Close Access
26.074.0TOTAL FOR EACH AIRPLANE
NOTE: Maximum total task hours and elapsed hours are given for inspection per airplane.
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Condition 2
Elapsed HoursTask HoursNumber of PersonsTask
8.032.04Open Access
5.05.01Visual Inspect
5.05.01ETHF Inspect
8.08.01Remove Cusp
Membrane
2.02.01Blendout Repair
8.08.01Install Cusp Mem-
brane
8.032.04Close Access
44.092.0TOTAL FOR EACH AIRPLANE
NOTE: Maximum total task hours and elapsed hours are given for the blendout 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
8.032.04Open Access
5.05.01Visual Inspect
5.05.01ETHF Inspect
8.08.01Remove Cusp
Membrane
10.020.02Remove Frame
24.048.02Install Frame
8.08.01Install Cusp Mem-
brane
8.032.04Close Access
76.0158.0TOTAL 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.
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I. Electrical Load Data
Not changed.
J. References
1. Existing Data
a. Non-Destructive Test Standard Practices Manual (NDTSPM) 06-10-01.001, 09-00-04 and
09-00-06.
b. Standard Overhaul Practices Manual (SOPM) 20-10-10.
c. MD90 Aircraft Maintenance Manual (AMM) 06-31-00, 07-10-00, 07-20-00, 08-10-00, 12-11-10,
20-20-03, 25-21-00, 25-21-03, 25-23-00, 25-27-00, 52-21-00 and 53-21-01.
d. MD90 Structural Repair Manual (SRM), Volume 2, 51-10-03, 51-10-05, 51-20-00, 51-30-01,
51-30-02, 51-30-03, 51-30-05 and 51-40-00.
2. Data supplied with this Service Bulletin
No data is supplied with this service bulletin. To obtain the data necessary to support this service
bulletin submit a data request to:
Data and Services Management
MS D800-0019
3855 Lakewood Boulevard
Long Beach, California 90846
Phone: (562) 593-6996
Fax: (562) 593-2001
E-mail: dse.boecom@boeing.com
a. Drawings:
ADCNDCN/REVSheetTitleDrawing No
--DWGFRAME INSTALLATION - OVERWING
REPLACEMENT
SR90530027
3. Installation Drawings Used in the Preparation of this Service Bulletin
None.
K. Publications Affected
1. Publications:
Chapter-SectionPublication
Maintenance Planning Document
2. Damage Tolerance Based Structural Inspections:
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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.
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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 as shown
below. Kit availability is shown in the Reorder Lead Time (ROLT). ROLT is calculated from the date
Boeing gets the purchase order.
A limited quantity of kits are available. Once consumed, refer to the standard ROLT listed below.
Unit Price thru
December 31, 2009
ROLT (Weeks)NameNumber
$32,200.0017Service KitSA90530031-3
32,200.0017Service KitSA90530031-5
33,157.0017Service KitSA90530031-7
33,156.0017Service KitSA90530031-9
33,192.0017Service KitSA90530031-11
33,192.0017Service KitSA90530031-13
37,096.0017Service KitSA90530031-15
37,096.0017Service KitSA90530031-17
36,851.0017Service KitSA90530031-19
36,851.0017Service KitSA90530031-21
The kits are subject to the terms and conditions of the Boeing standard purchase order acknowledgment.
After the Unit Price date, new price and ROLT data is applicable. Prices are in United States dollars.
Terms: Net 30 days.
Reference this service bulletin and submit your purchase order by one of the methods that follow:
1. Order on-line via ATA Spec 2000 or Boeing Part Page
2. Fax to (206) 662-7145
3. Mail to:
Spares Customer Support - MC 36-65
Boeing Spares Department
P .O. Box 3707
Seattle, Washington 98124-2207 USA
B. Industry Support Information
Boeing warranty remedies are not available for the inspection and/or repair procedures given in this
service bulletin.
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C. Parts Necessary For Each Airplane
1. Kits/Parts
To get the kits/parts shown below, refer to Paragraph 2.A., Material - Price and Availability.
NOTE: One top kit and the items shown in Paragraph 2.C.2., Parts and Materials Supplied by
the Operator, are necessary for each airplane.
Service Kit Matrix
Station LocationPositionDrawing ConfigurationService Kit
Y= 883.000LeftSR90530027-7001SA90530031-3
RightSR90530027-7003SA90530031-5
Y= 902.000LeftSR90530027-7005SA90530031-7
RightSR90530027-7007SA90530031-9
Y= 924.000LeftSR90530027-7009SA90530031-11
RightSR90530027-7011SA90530031-13
Y= 943.000LeftSR90530027-7013SA90530031-15
RightSR90530027-7015SA90530031-17
Y= 962.000LeftSR90530027-7017SA90530031-19
RightSR90530027-7019SA90530031-21
Kit SA90530031
NotesExisting Part
Number
NameQTYNew Part Number
-13-11-9-7-5-3
CLIP..11..2913797-1
CLIP1111..2913870-1
CLIP11....2920753-1
CLIP..11..2920754-1
CLIP1.1...2920756-1
CLIP.1.1..2920756-2
NUT ASSY5858585824243D0006-3
NUT ASSY....223D0006-4
PIN..11..3D0010-6-6
PIN12121414..3D0010-6-7
PIN131355..3D0010-6-8
PIN1166..3D0010-6-9
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Kit SA90530031
NotesExisting Part
Number
NameQTYNew Part Number
-13-11-9-7-5-3
CLIP...1..9919669-17
CLIP..1...9919669-18
FRAME...1..9923405-505
FRAME..1...9923405-506
FRAME1.....9923405-507
FRAME.1....9923405-508
CLIP....449935997-7
FRAME.....19936471-501
FRAME....1.9936471-502
CLIP....119957901-9
CLIP1.....9964454-17
CLIP.1....9964454-18
CLIP11....9964454-19
CLIP11....9964454-21
PIN1111..HL329-6-11
PIN1111..HLT425-6-5
PIN1111..HLT425-6-6
PIN4444..HLT425-6-7
PIN111111HLT426-10-10
O/S FASTENER....22HLT426-12-11
O/S FASTENER22....HLT426-12-13
PIN..22..HLT426-12-9
PIN1111..HLT426-6-10
PIN191988..HLT426-6-3
PIN1313202022HLT426-6-4
PIN111111112222HLT426-6-5
PIN1111111199HLT426-6-6
PIN....11HLT426-6-7
PIN999999HLT426-6-8
PIN1111..HLT426-6-9
PIN333333HLT426-8-10
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Kit SA90530031
NotesExisting Part
Number
NameQTYNew Part Number
-13-11-9-7-5-3
PIN1111..HLT426-8-7
PIN....11HLT426-8-8
PIN333322HLT426-8-9
PIN111111HLT435-6-10
PIN....11HLT435-6-11
PIN22221818HLT435-6-6
PIN585858582727HLT435-6-7
PIN111166HLT435-6-8
PIN....11HLT435-6-9
RIVET1010102033MS20470AD5-10D
RIVET21211133MS20470AD5-11D
RIVET112020..MS20470AD5-12D
RIVET....2424MS20470AD5-6D
RIVET....66MS20470AD5-7D
RIVET....33MS20470AD5-8D
RIVET..11..MS20470AD5-9D
RIVET11....MS20470AD6-12D
RIVET..11..MS20470AD6-14D
NUT10110197977373MS21042L3
NUT777722MS21042L4
NUT111111MS21042L5
NUT222222MS21042L6
WASHER979793934141NAS1252-10H
WASHER55553232NAS1252-10L
WASHER777722NAS1252-416H
WASHER111111NAS1252-516H
WASHER222222NAS1252-616H
NUT1111..NAS679A3
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Kit SA90530031
NotesExisting Part
Number
NameQTYNew Part Number
-21-19-17-15
CLIP11112913870-1
CLIP11112920753-1
CLIP1..12920756-1
CLIP.11.2920756-2
NUT ASSY656564643D0006-3
PIN11..3D0010-6-5
PIN99..3D0010-6-6
PIN66..3D0010-6-7
PIN1010..3D0010-6-8
CLIP.11.9919671-17
CLIP1..19919671-18
CLIP11119919671-19
CLIP11119919671-21
FRAME...19923406-503
FRAME..1.9923406-504
FRAME.1..9923407-503
FRAME1...9923407-504
PIN11..HL329-6-10
PIN, OVERSIZE2222HLT426-12-10
PIN..11HLT426-6-10
PIN15151515HLT426-6-3
PIN14141414HLT426-6-4
PIN12121313HLT426-6-5
PIN16162121HLT426-6-6
PIN101022HLT426-6-7
PIN1177HLT426-6-8
PIN1111HLT426-6-9
PIN4444HLT426-8-10
PIN11..HLT426-8-8
PIN3344HLT426-8-9
PIN..11HLT435-6-10
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Kit SA90530031
NotesExisting Part
Number
NameQTYNew Part Number
-21-19-17-15
PIN223232HLT435-6-6
PIN57572828HLT435-6-7
PIN5533HLT435-6-8
PIN11..HLT435-6-9
RIVET..33MS20470AD5-10D
RIVET181833MS20470AD5-11D
RIVET22..MS20470AD5-12D
RIVET..3636MS20470AD5-6D
RIVET..1212MS20470AD5-7D
RIVET1010..MS20470AD5-8D
RIVET22..MS20470AD5-9D
RIVET11..MS20470AD6-13D
NUT95957474MS21042L3
NUT8888MS21042L4
NUT2222MS21042L6
WASHER95957474NAS1252-10H
WASHER11..NAS1252-10L
WASHER8888NAS1252-416H
WASHER2222NAS1252-616H
NUT11..NAS679A3
2. Parts and Materials Supplied by the Operator
NOTE: Refer to Non-Destructive Testing Standard Practice Manual (NDTSPM) Part 06 and Part
09 for the required materials to be used in the inspections.
NotesNameQTYPart Number / Specification
(a)Tape, Cloth Coated1 RollPC21F
(DMS 1968 Type 2)
OR
(b)Tape, Cloth Coated1 RollPolyken 225
(DMS 1968 Type 2)
OR
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NotesNameQTYPart Number / Specification
(c)Tape, Adhesive1 Roll770-3 FRD
(DMS 1984 Type 6 Class 2)
OR
(d)Tape, Adhesive1 RollOT -16A
(DMS 1984 Type 6 Class 2)
(e)Sealing Compound1 QuartPR-1422 Class B-2
(DMS 2082)
OR
Equivalent
CAGEShurtape Technologies, LLCMay be purchased from:(a)
4L0S01506 Highland Avenue
Hickory, North Carolina 28601
80769Covalence Specialty AdhesivesMay be purchased from:(b)
2320 Bowling Green Road
Franklin, Massachusetts 02038
9U930Annitti Enterprises IncorporatedMay be purchased from:(c)
138 Grand Street
Paterson, New Jersey 07501
23788Orcon CorporationMay be purchased from:(d)
251 rope Mill Parkway STE 1
Woodstock, Georgia 30188
92108PRC-DeSoto International, IncorporatedMay be purchased from:(e)
5454 San Fernando Road
Glendale, California 91203
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.
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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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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: ELECTRICALL Y 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. The instructions identified in Paragraph 3.B., Work Instructions and the Figure(s)
give the recommended sequence of steps. The sequence of steps to do this service
bulletin can be changed.
2. Manual titles are referred to by acronyms. Refer to Paragraph 1.J., References, for
definition of the acronyms.
3. Equivalent parts are listed in the AEPL, Drawing 7595071.
4. Use the approved fastener and process material substitutions, in accordance with
MD90 SRM, Chapter 51, Volume 2.
5. If the length of any fastener specified in this service bulletin does not meet the
installation standards in MD90 SRM Chapter 51, then a fastener of the same
specification, or an approved substitute, with a length which meets the installation
standards in MD90 SRM Chapter 51, Volume 2, may be used.
6. 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.
7. Oversize fasteners must be used when the hole diameter exceeds the maximum
diameter specified.
8. Refer to the manuals that follow as an accepted procedure:
OperationAccepted Procedure
Sealant ApplicationMD90 AMM 20-20-03
Corrosion/Erosion Control and PreventionMD90 SRM 51-10-03
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OperationAccepted Procedure
Drilling and CountersinkingMD90 SRM 51-10-05
Repair SealingMD90 SRM 51-20-00
Installing Bolts, Screws, and WashersMD90 SRM 51-30-01
Installing and Removing RivetsMD90 SRM 51-30-02
Installing and Removing LockboltsMD90 SRM 51-30-03
Installing and Removing Hi-Lok AttachmentsMD90 SRM 51-30-05
Substitution and InterchangeabilityMD90 SRM 51-40-00
9. Obey all of the warnings and cautions given in the specified manual sections.
10. A Detailed Inspection is defined as: An intensive examination of a specific item,
installation, or assembly to detect damage, failure, or irregularity. Available lighting
is normally supplemented with a direct source of good lighting at an intensity deemed
appropriate. Inspection aids such as mirrors, magnifying lenses, etc. may be
necessary. Surface cleaning and elaborate procedures may be required.
11. 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 ensure visual access to all surfaces in the
inspection area. This level of inspection is made under normal 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.
12. 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.
B. WORK INSTRUCTIONS
1. Remove and keep the following items and attaching parts, as applicable, to get access to the left
and right side overwing frames at Stations 883, 902, 924, 943 and 962.
Accepted ProcedureItem
MD90 AMM 25-23-00Passenger Seats
MD90 AMM 25-21-00Passenger Compartment Lining
MD90 AMM 25-21-03Passenger Compartment Insulation
MD90 AMM 25-27-00Passenger Compartment Floor Covering
MD90 AMM 53-21-01Passenger Compartment Floor Panels
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Accepted ProcedureItem
MD90 AMM 52-21-00Overwing Emergency Exit Doors
2. Remove tape from the cutout between the cusp membrane and frame to get access to the frame
inspection area.
3. Remove and keep the cusp membrane, as necessary, to get access to the frame inspection area.
4. Do a General Visual inspection and an Eddy Current, High Frequency (ETHF) inspection of the
upper radius of the frame tab of the overwing frames in accordance with Figures 1 and 2. Based
on findings do as follows:
Condition 1 (No Crack)
a. Install kept cusp membrane if it was removed to get access to the frame inspection area.
b. Install tape to seal along the cutout between the cusp membrane and frame.
c. Do repeat inspections of the overwing frames.
Condition 2 (Crack less than 0.125 Inch in Depth)
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. Install kept cusp membrane.
d. Install tape to seal along the cutout between the cusp membrane and frame.
e. Do repeat inspections of the overwing frames.
Condition 3 ( Crack 0.125 Inch in Depth or Greater)
a. Defuel the airplane. Refer to MD90 AMM 12-11-10 as an accepted procedure.
b. Raise and level the airplane. Refer to MD90 AMM 07-10-00 and MD90 AMM 08-10-00 as an
accepted procedure.
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 MD90
AMM 07-20-00 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, 150FL and 150ML on
the left side and 160CR, 160FR and 160MR on the right side to get access to the cracked
frame. Refer to MD90 AMM 06-31-00 as an accepted procedure.
e. Replace cracked overwing frame in accordance with Service Rework Drawing SR90530027.
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NOTE: Apply PR-1422 sealant on all faying surfaces and wet install all fasteners during
frame replacement.
f. Install kept cusp membrane.
g. Install tape to seal along the cutout between the cusp membrane and frame.
h. Install kept applicable wing to fuselage fillet panels 150CL, 150FL and 150ML on the left side
and 160CR, 160FR and 160MR on the right side. Refer to MD90 AMM 06-31-00.
i. Remove any shoring and lower the airplane. Refer to MD90 AMM 07-10-00 and MD90 AMM
08-10-00 as an accepted procedure.
j. Do repeat inspections of the overwing frames.
5. Install all kept items and attaching parts, as applicable from Station 883.000 to 962.000.
Accepted ProcedureItem
MD90 AMM 25-23-00Passenger Seats
MD90 AMM 25-21-00Passenger Compartment Lining
MD90 AMM 25-21-03Passenger Compartment Insulation
MD90 AMM 25-27-00Passenger Compartment Floor Covering
MD90 AMM 53-21-01Passenger Compartment Floor Panels
MD90 AMM 52-21-00Overwing Emergency Exit Doors
6. Put the airplane back to a serviceable condition.
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BOEING SERVICE BULLETIN MD90-53A031
ALERT  ALERT
STA Y=883.000
STA Y=902.000
•STA Y=924.000
•STA Y=943.000
STA Y=962.000
STATION FRAME
TYPICAL
CRACK
FRP
INSPECTION
AREA
LEFT SIDE SHOWN
RIGHT SIDE OPPOSITE
FIGURE 1: DETAILED VISUAL INSPECTION - OVERWING FRAMES
(SHEET 1 OF 2)
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### Page 30

The step numbers shown below agree with the numbers shown in the circle symbols in the figure.
MORE
DATA
IDENTIFICATIONSTATION LOCA-
TION
NAMEPROCEDURETASKSTEP
(a) (b)
(c)
9936471-501/-502Station 883FrameDetailed VisualInspect1
9923405-505/-506Station 902
9923405-507/-508Station 924
9923406-503/-504Station 943
9923407-503/-504Station 962
(a) Do a Detailed inspection the frame in the shaded area at all accessible locations using remote visual devices
at Stations 883, 902, 924, 943 and 962 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 Non-Destructive Testing Standard Practice Manual 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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BOEING SERVICE BULLETIN MD90-53A031
ALERT  ALERT
STA Y=883.000
STA Y=902.000
STA Y=924.000
STA Y=943.000
- STA Y=962.000
EDDY CURRENT
PROBE
STATION FRAME
TYPICAL
CRACK
INSPECTION
AREA
FRAME  FRP
TAB
LEFT SIDE SHOWN
RIGHT SIDE OPPOSITE
FIGURE 2: EDDY CURRENT, HIGH FREQUENCY INSPECTION - OVERWING FRAMES
(SHEET 1 OF 2)
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### Page 32

The step numbers shown below agree with the numbers shown in the circle symbols in the figure.
MORE
DATA
IDENTIFICATIONSTATION LOCA-
TION
NAMEPROCEDURETASKSTEP
(a) (b)9936471-501/-502Station 883FrameEddy Current, High
Frequency
Inspect1
9923405-505/-506Station 902
9923405-507/-508Station 924
9923406-503/-504Station 943
9923407-503/-504Station 962
(a) Do a Detailed inspection the upper radius of the frame tab in the shaded area looking for cracks propagating
in the forward and aft direction. Refer to Non-Destructive Testing Standard Practice Manual NDTSPM 06-
10-01.001, Procedure 1, Calibration Method "G" and Scan Method "69".
(b) 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 33 (OCR)

BOEING SERVICE BULLETIN MD90-53A031
ALERT  ALERT
•STA Y=883.000
STA Y=902.000
STA Y=924.000
STA Y=943.000
STA Y=962.000
STATION FRAME
FRP
FRAME
TAB
LEFT SIDE SHOWN
RIGHT SIDE OPPOSITE  1732753
FIGURE 3: BLEND-OUT REPAIR - FRAME TAB UPPER RADIUS
(SHEET 1 OF 3)
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### Page 34 (OCR)

BOEING SERVICE BULLETIN MD90-53A031
ALERT  ALERT
0.060  AREA OF POSSIBLE
CRACK
FRP -
0.125
MAX
0.56/0.44R
INBD
B-B
TYPICAL FRAME LOOKING FORWARD
1732755
FIGURE 3: BLEND-OUT REPAIR - FRAME TAB UPPER RADIUS
(SHEET 2 OF 3)
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The step numbers shown below agree with the numbers shown in the circle symbols in the figure.
MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
(a) (b) (c) (d) (e)--FrameRepair1
(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.
(c) Surface finish 63 micro-inch finish or better.
(d) Glass bead peen or flap peen the frame tab surfaces. Refer to SOPM 20-10-10 as an accepted
procedure.
(e) Apply Alodine and FR Primer on all bare metal surfaces.
FIGURE 3: BLEND-OUT REPAIR - FRAME TAB UPPER RADIUS
(SHEET 3 OF 3)
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