# Boeing Alert Service Bulletin MD90-57A030: No revision named

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- Document: [Boeing Alert Service Bulletin MD90-57A030](https://openairdocs.org/service-documents/boeing/md90-57a030.md)
- Title as filed: U.S. DOT/FAA - Service Information
- Pages: 23
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## Text

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### Page 1

Commercial 
Airplanes
MD90
Service Bulletin
ALERT
Number: MD90-57A030
Original Issue: February 14, 2012
ATA System: 5710
SUBJECT: WINGS - Main Frame - Inspect/Repair Stringer 11 at the Outboard Flap, Inboard Drive
Hinge at Station Xrs=164.000 Left and Right Wings
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 © 2012 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Unpublished Work - All Rights Reserved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, KC-10, KDC-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 ........................................ 7
A. Effectivity ................................................ 7
1. Airplanes ............................................. 7
2. Spares Affected ......................................... 9
B. Concurrent Requirements ....................................... 9
C. Reason ................................................. 9
D. Description ............................................... 9
E. Compliance .............................................. 1 0
F. Approval ............................................... 1 1
G. Manpower .............................................. 1 1
H. Weight and Balance Changes .................................... 1 2
I. Electrical Load Data ......................................... 1 2
J. References .............................................. 1 2
1. Existing Data: ......................................... 1 2
2. Data supplied with this Service Bulletin: ........................... 1 2
3. Installation Drawings Used in the Preparation of this Service Bulletin: ........... 1 3
K. Publications Affected ........................................ 1 3
L. Interchangeability and Intermixability of Parts ........................... 1 3
2. MATERIAL INFORMATION ........................................ 1 5
A. Material - Price and Availability ................................... 1 5
B. Industry Support Information .................................... 1 5
C. Parts Necessary For Each Airplane ................................. 1 5
1. Kits/Parts: ........................................... 1 5
2. Parts and Materials Supplied by the Operator: ........................ 1 7
3. Parts Modified and Reidentified: ............................... 1 8
4. Parts Removed and Not Replaced: .............................. 1 8
D. Parts Necessary to Change Spares ................................. 1 8
E. Special Tooling - Price and Availability ............................... 1 8
F. Special Tooling Necessary to do this Service Bulletin ....................... 1 8
3. ACCOMPLISHMENT INSTRUCTIONS .................................. 1 9
A. GENERAL INFORMATION ..................................... 1 9
B. WORK INSTRUCTIONS ....................................... 2 0
FIGURE 1: STRINGER 11 AT THE OUTBOARD FLAP, INBOARD DRIVE HINGE AT STATION
XRS=164.000 - EDDY CURRENT, HIGH FREQUENCY INSPECTION ........... 2 2
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Commercial 
Airplanes
MD90
Service Bulletin
ALERT
SummaryNumber: MD90-57A030Original Issue: February 14, 2012
ATA System: 5710
SUBJECT: WINGS - Main Frame - Inspect/Repair Stringer 11 at the Outboard Flap, Inboard Drive
Hinge at Station Xrs=164.000 Left and Right Wings
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
Three MD-80 operators reported four instances of cracks found in Stringer 11 at the outboard flap, inboard drive
hinge at Station Xrs=164.000. The cracking occurs at the end fastener of the wing bulkhead clip attachment to
the stringer. The cracked stringers were found by chance, during maintenance, except in one case when the
rear spar cap had been removed during a spar cap splice repair. No cracks have been reported by MD-90
operators. The MD-90 however shares the same structure design as that of the MD-80 and is thus susceptible
to cracking. Boeing investigation and analysis have shown that the Stringer 11 cracking is due to fatigue. If
undetected, a crack in the stringer may grow until the stringer severs, initiating a crack in the wing lower skin.
Continuing damage into the wing skin may result in the wing structure not being capable of sustaining the required
loads. Inspection of the affected areas will determine the condition of the stringer, prevent any crack migration,
and ensure repairs are done before additional damage occurs. A splice repair for crack found on the affected
stringer can be accomplished by installing a segment of stringer. If not corrected, fuel leaks and damage to the
wing skin or other structure may occur, resulting in possible loss of the structural integrity of the wing.
Boeing Fleet Team Digest (FTD) MD-90 FTD MD-90-FTD-57-11001 is related to this service bulletin.
ACTION
This service bulletin provides instructions to do an Eddy Current, High Frequency (ETHF) inspection for cracks
in Stringer 11 at the outboard flap, inboard drive hinge at Station Xrs=164.000 left and right wings. Refer to
Paragraph 1.D., Description, for the required corrective action based on the results of the inspection.
EFFECTIVITY
MD-90-30 Airplanes. Refer to Paragraph 1.A.1., Airplanes, for the list of affected airplanes.
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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.
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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Commercial 
Airplanes
MD90
Service Bulletin
ALERT
Number: MD90-57A030
Original Issue: February 14, 2012
ATA System: 5710
SUBJECT: WINGS - Main Frame - Inspect/Repair Stringer 11 at the Outboard Flap, Inboard Drive
Hinge at Station Xrs=164.000 Left and Right Wings
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
Inspect/Repair Stringer 11 at the Outboard Flap, Inboard Drive Hinge
at Station Xrs=164.000 left and right wings.
-1
Airplane Models:
MD-90-30
GroupFuselage Num-
ber
12094 - 2100
12115
12117
12120
12122 - 2123
12125 - 2126
12129
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GroupFuselage Num-
ber
12131
12133
12136
12138
12140 - 2144
12146 - 2147
12149 - 2150
12153 - 2154
12156 - 2159
12161 - 2166
12168 - 2173
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 - 2238
12240
12242 - 2243
12245 - 2246
12248
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GroupFuselage Num-
ber
12250 - 2251
12253
12255 - 2263
12288 - 2290
2. Spares Affected
None.
B. Concurrent Requirements
None.
C. Reason
Three MD-80 operators reported four instances of cracks found in Stringer 11 at the outboard flap,
inboard drive hinge at Station Xrs=164.000. The cracking occurs at the end fastener of the wing bulkhead
clip attachment to the stringer. The cracked stringers were found by chance, during maintenance,
except in one case when the rear spar cap had been removed during a spar cap splice repair. No
cracks have been reported by MD-90 operators. The MD-90 however shares the same structure design
as that of the MD-80 and is thus susceptible to cracking. Boeing investigation and analysis have shown
that the Stringer 11 cracking is due to fatigue. If undetected, a crack in the stringer may grow until the
stringer severs, initiating a crack in the wing lower skin. Continuing damage into the wing skin may
result in the wing structure not being capable of sustaining the required loads. Inspection of the affected
areas will determine the condition of the stringer, prevent any crack migration, and ensure repairs are
done before additional damage occurs. A splice repair for crack found on the affected stringer can be
accomplished by installing a segment of stringer. If not corrected, fuel leaks and damage to the wing
skin or other structure may occur, resulting in possible loss of the structural integrity of the wing.
Boeing Fleet Team Digest (FTD) MD-90 FTD MD-90-FTD-57-11001 is related to this service bulletin.
D. Description
This service bulletin provides instructions to do an Eddy Current, High Frequency (ETHF) inspection
for cracks in Stringer 11 at the outboard flap, inboard drive hinge at Station Xrs=164.000 left and right
wings, and based on inspection results does as follows:
Condition 1 (No Crack Found)
1. Does repeat ETHF inspection for cracks in Stringer 11 at the outboard flap, inboard drive hinge
at Station Xrs=164.000.
Condition 2 (Crack Found)
1. Does splice repair.
2. Does ETHF inspection for cracks in Stringer 11 at the outboard flap, inboard drive hinge at Station
Xrs=164.000.
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The work in this service bulletin is done in the maintenance zone(s) given below.
Affected Maintenance Zones
ZoneModel
531, 631MD-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.
Accomplish the required actions, based on the applicable conditions, in Table 1, in accordance with
Paragraph 3. Accomplishment Instructions.
Table 1: Inspect Stringer 11 for Crack at the Outboard Flap, Inboard Drive Hinge at Station Xrs=164.000
left and right wings.
Repeat
Interval
(Not to
Exceed)
Compliance Time
(Whichever Occurs Later)
ActionCondition
-Within 9,470 flight cy-
cles after the original
issue date on this
service bulletin.
Before the accumula-
tion of 14,000 total
flight cycles.
Do Eddy Current, High Frequency
(ETHF) inspection for cracks in
Stringer 11 at the outboard flap,
inboard drive hinge at Station
Xrs=164.000.
All airplanes
31,000 flight
cycles.
--Do ETHF inspection for cracks in
Stringer 11 at the outboard flap,
inboard drive hinge at Station
Xrs=164.000. (a)
Condition 1:
(No Crack
Found)
--Before further flight.Do splice repair.Condition 2:
(Crack Found) AND
31,000 flight
cycles.
-42,000 flight cycles
after splice repair.
Do ETHF inspection for cracks in
Stringer 11 at the outboard flap,
inboard drive hinge at Station
Xrs=164.000. (b)
(a) If any crack is found, do the actions specified by Condition 2.
(b) If any crack is found, contact The Boeing Company for repair instructions and do the repair.
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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 the inspection/repair for each
wing. 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 examine the work
— Time to cure the materials
— Time to make the parts
— Time to find the tools.
— Time to make reference standards.
Condition 1 (No Crack Found)
Elapsed HoursTask HoursNumber of PersonsTask
4.04.01Defuel Tank
8.08.01Purge Tank
1.01.01FIGURE 1
13.013.0TOTAL FOR EACH WING
Condition 2 (Crack Found)
Elapsed HoursTask HoursNumber of PersonsTask
4.04.01Defuel Tank
8.08.01Purge Tank
1.01.01FIGURE 1
40.080.02Splice Repair
53.093.0TOTAL FOR EACH WING
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H. Weight and Balance Changes
Condition 1 (No Crack Found)
None.
Condition 2 (Crack Found)
Moment Change
(MEW) IN.-LBS
Mfr's Empty
Weight (MEW)
LBS
Approximate Sta-
tion (Inches)Airplane
+ 7562.8+ 7.4+ 1022.0MD-90-30 (Left Wing Only)
+ 7562.8+ 7.4+ 1022.0MD-90-30 (Right Wing Only)
+ 15525.6+ 14.8+ 1022.0MD-90-30 (Both Wings)
I. Electrical Load Data
Not changed.
J. References
1. Existing Data:
a. Non-Destructive Test Standard Practices Manual (NDTSPM) 06-10-01.001.
b. MD-90 Aircraft Maintenance Manual (AMM) 06-35-00, 06-36-00, 12-11-01, 28-00-00, 28-10-01.
c. MD-90 Fleet Team Digest (FTD) MD-90-FTD-57-11001.
d. MD-90 Structural Repair Manual (SRM) 51, 51-10-09 Volume II
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
--DWGSTRG 11 REPAIR, LWR WING, XRS
164.000
SR90570009
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3. Installation Drawings Used in the Preparation of this Service Bulletin:
None.
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.
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2.    MATERIAL INFORMATION
A. Material - Price and Availability
Boeing can supply the kit 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
kit is subject to the terms and conditions of the Boeing standard purchase order acknowledgment.
Prices are in United States Dollars. Terms: Net 30 days.
Reference this service bulletin and submit your purchase order by one of these methods:
1. Order on-line via ATA Spec 2000 or The Boeing PART Page
2. Fax to (206) 662-7145
REFER TO THE BOEING PART PAGE ON MYBOEINGFLEET.COM OR CONTACT FIRST RESPONDER
AT FR@BOEING.COM FOR THE LATEST REORDER LEAD TIME (ROLT) AND PRICE INFORMATION
Unit Price as of
the original issue
date of this Ser-
vice Bulletin (US
Dollars)
ROLT as of the
original issue
date of this Ser-
vice Bulletin (Cal-
endar Days)
NameKit Number
$28,126.00119Service KitSB90570030-3
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:
To get the kits/parts shown below, refer to Paragraph 2.A., Material - Price and Availability.
Condition 1 (No Crack Found)
a. None.
Condition 2 (Crack Found)
a. One top kit per wing and the items shown in Paragraph 2.C.2., Parts and Materials Supplied
by the Operator, are necessary for each airplane.
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ALL
Kit SB90570030
NotesExisting Part
Number
NameQTYNew Part Number
-3
-SB90570030-3
(a)NUT ASSY403D0006-3
(a)NUT ASSY643D0006-4
PIN1HLT435-8-13
PIN2HLT435-8-15
PIN3HLT436-10-12
PIN1HLT436-10-21
PIN2HLT436-6-14
PIN2HLT436-8-5
PIN4HLT436-8-7
PIN12HLT439-6-10
PIN4HLT439-6-11
PIN4HLT439-6-12
PIN1HLT439-6-14
PIN2HLT439-6-15
PIN4HLT439-8-8
PIN10HLT639-8-11
PIN13HLT639-8-12
PIN18HLT639-8-13
PIN8HLT639-8-14
PIN, OVERSIZE2HST112-8-14
NUT13MS21042L3
NUT2MS21042L4
NUT4MS21042L5
WASHER2NAS1252-416L
WASHER4NAS1252-516L
WASHER17NAS1401-3D3
WASHER52NAS1401-4D3
(a)PIN8S4931920-6-6
(a)PIN7S4931920-6-7
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ALL
Kit SB90570030
NotesExisting Part
Number
NameQTYNew Part Number
-3
(a)PIN13S4931920-6-8
(a)PIN2S4931920-8-4
STRINGER1SR09570100-3
ANGLE2SR09570100-7
CHANNEL2SR09570100-9
ANGLE1SR09570100-11
ANGLE1SR09570100-12
(a) Or approved equivalent. Refer to the AEPL, Drawing 7595071.
2. Parts and Materials Supplied by the Operator:
Condition 1 (No Crack Found)
a. None.
Condition 2 (Crack Found)
a. Materials necessary to complete the action in this service bulletin.
NotesNameQTYPart Number / Specifica-
tion
(a)Sealant1 QuartPR-1422 B-2
(DMS 2082)
or
Equivalent
(b)MC Coating, Chemical
Film
1 QuartAlodine 1200S
(DPM 1453-5)
or
Equivalent
(b)Coating, Fuel Tank, Inte-
gral
1 Pint#833K086 Base;
#930K088 Curing Solution
(DMS 1850 Type 4
Composition C)
or
Equivalent
(a) Can be purchased from: PRC - DeSoto International, Incorporated (CAGE: 85570), 11601 United Street,
Mojave, California 93501.
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NotesNameQTYPart Number / Specifica-
tion
(b) Can be purchased from: Henkel Corporation (CAGE 1N6B3), 32100 Stephenson Highway, Madison
Heights, Michigan 48071.
3. Parts Modified and Reidentified:
None.
4. Parts Removed and Not Replaced:
None.
D. Parts Necessary to Change Spares
None.
E. Special Tooling - Price and Availability
Condition 1 (No Crack Found)
1. None.
Condition 2 (Crack Found)
1. The MD-90 SRM 51-10-09 Volume II gives data about cold working tools and sleeves necessary
to do the work given in this service bulletin. These tools are available from industry sources.
F. Special Tooling Necessary to do this Service Bulletin
Condition 1 (No Crack Found)
1. 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.
Condition 2 (Crack Found)
1. Cold working tools are necessary to do the change given in this service bulletin. Refer to Service
Rework Drawing SR90570009. To get the cold working tools, refer to Paragraph 2.E., Special
Tooling - Price and Availability.
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### Page 19

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: 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.
CAUTION: ELECTRICALLY GROUND THE AIRPLANE. THIS WILL HELP TO PREVENT DAMAGE
TO THE AIRPLANE OR EQUIPMENT.
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
MD-90 SRM 51.
4. If the length of any fastener specified in this service bulletin does not meet installation
standards given in Structural Repair Manual (SRM) Chapter 51, then a fastener of
the same specification, or an approved substitute, with a length which meets the
installation standards given in MD-90 SRM 51 may be used. In addition, washers
may be installed for fastener grip length in accordance with MD-90 SRM 51.
5. A 1/8-inch thick stack of the same type washers called for in this service bulletin is
the maximum thickness which may be used under fastener head or nut to counteract
accumulation of tolerances.
EXCEPTION: When the available fastener length increments are greater than
1/16-inch, a 3/16-inch thick stack of the same type washers may be used.
6. Unless shown differently, these dimensions and tolerances are used:
– Linear dimensions are in inches
– Tolerance on linear dimensions, other than rivet and bolt edge margins, is plus
or minus 0.03 inch.
– Tolerance on rivet and bolt edge margin is plus or minus 0.05 inch
– Angular tolerance is plus or minus 2 degrees
– Hole dimensions for standard solid rivets are in MD-90 SRM 51.
– Torque limits to tighten nuts and bolts are in MD-90 SRM 51.
7. Obey all of the warnings and cautions given in the specified manual sections.
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### Page 20

8. 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.
9. 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.
10. 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.
11. 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.
12. This service bulletin includes functional test procedures for the systems changed by
this service bulletin. More functional tests can possibly be necessary in accordance
with standard maintenance practices because of interruption to other airplane systems.
B. WORK INSTRUCTIONS
WARNING: BEFORE MOVING FLAP/SLAT HANDLE, MAKE CERTAIN THAT AREAS AROUND
FLAPS AND SLATS ARE CLEAR OF PERSONNEL AND EQUIPMENT.
1. Defuel and purge left and right fuel tanks. Refer to MD-90 AMM 12-11-01, MD-90 AMM 28-00-00
and MD-90 AMM 28-10-01 as accepted procedures.
2. Remove/keep door numbers 520DT and 520CB on the left wing main tank and door numbers
620DT and 620CB on the right wing main tank and attaching parts. Refer to MD-90 AMM 06-35-00
and MD-90 AMM 06-36-00.
3. Prepare fuel tank for entry and gain access to the area of inspection of Stringer 11 at the outboard
flap, inboard drive hinge at Station Xrs=164.000.
4. Do an in-tank Eddy Current, High Frequency (ETHF) inspection for cracks in Stringer 11 at the
outboard flap, inboard drive hinge at Station Xrs=164.000 left and right wings in accordance with
FIGURE 1, and based on inspection results do as follows:
Condition 1 (No Crack Found)
a. Do repeat ETHF inspection for cracks in Stringer 11 at the outboard flap, inboard drive hinge
at Station Xrs=164.000 in accordance with FIGURE 1, at intervals specified in Paragraph 1.E.,
Compliance.
Condition 2 (Crack Found)
a. Do splice repair in accordance with Service Rework SR90570009.
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### Page 21

b. Do ETHF inspection for cracks in Stringer 11 at the outboard flap, inboard drive hinge at
Station Xrs=164.000 in accordance with Service Rework Drawing SR90570009, Zone 15, at
intervals specified in Paragraph 1.E., Compliance.
5. Put the airplane back to a serviceable condition.
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### Page 22 (OCR)

BOEING SERVICE BULLETIN MD90-57A030
ALERT  ALERT
Xrs=164.000  Xrs=164.000
A
Xrs=164.000
• STRINGER 11
ANGLE
CRACK
(TYPICAL)  A-A
VIEW LOOKING AFT  ANGLE  2120836
LEFT SIDE SHOWN
RIGHT SIDE OPPOSITE
FIGURE 1: STRINGER 11 AT THE OUTBOARD FLAP, INBOARD DRIVE HINGE AT STATION XRS=164.000
- EDDY CURRENT, HIGH FREQUENCY INSPECTION
(SHEET 1 OF 2)
Original Issue: February 14, 2012
MD90-57A030
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### Page 23

The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY
numbers shown below are the number of parts necessary for each airplane.
More DataQTYIdentificationNameTaskStep
(a)15919236-507StringerInspect1
and
5919236-508
(a) Perform an Eddy Current, High Frequency (ETHF) surface inspection of Stringer 11 in the area of the
bulkhead at Station Xrs = 164.000. Scan the forward face of the vertical flange of the stringer, around
the four fasteners common with the angles shown. Scan looking for cracks originating at the fastener
holes and propagating in the vertical direction. Scan around fasteners in accordance with NDTSPM
06-10-01.001, Procedure 1. Use calibration scan method "K" and Scan Method 44.
FIGURE 1: STRINGER 11 AT THE OUTBOARD FLAP, INBOARD DRIVE HINGE AT STATION XRS=164.000
- EDDY CURRENT, HIGH FREQUENCY INSPECTION
(SHEET 2 OF 2)
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