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.

ECCN: 9E991

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Unpublished Work - All Rights Reserved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

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2.0
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BLANK PAGE
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 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 10

F. Approval . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11

G. Manpower . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11

H. Weight and Balance Changes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 12

I. Electrical Load Data . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 12

J. References . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 12

1. Existing Data: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 12

2. Data supplied with this Service Bulletin: . . . . . . . . . . . . . . . . . . . . . . . . . . . 12

3. Installation Drawings Used in the Preparation of this Service Bulletin: . . . . . . . . . . . 13

K. Publications Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13

L. Interchangeability and Intermixability of Parts . . . . . . . . . . . . . . . . . . . . . . . . . . . 13

2. MATERIAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15

A. Material - Price and Availability . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15

B. Industry Support Information . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15

C. Parts Necessary For Each Airplane . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15

1. Kits/Parts: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15

2. Parts and Materials Supplied by the Operator: . . . . . . . . . . . . . . . . . . . . . . . . 17

3. Parts Modified and Reidentified: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 18

4. Parts Removed and Not Replaced: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 18

D. Parts Necessary to Change Spares . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 18

E. Special Tooling - Price and Availability . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 18

F. Special Tooling Necessary to do this Service Bulletin . . . . . . . . . . . . . . . . . . . . . . . 18

3. ACCOMPLISHMENT INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19

A. GENERAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19

B. WORK INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20

FIGURE 1: STRINGER 11 AT THE OUTBOARD FLAP, INBOARD DRIVE HINGE AT STATION

XRS=164.000 - EDDY CURRENT, HIGH FREQUENCY INSPECTION . . . . . . . . . . . 22

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BOEING SERVICE BULLETIN MD90-57A030

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BLANK PAGE
Commercial 

Airplanes MD90

Service Bulletin

ALERT

Summary 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.

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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MD90-57A030

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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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BOEING SERVICE BULLETIN MD90-57A030

ALERT ALERT
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.

GROUP CONFIGURATION DESCRIPTION

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

Fuselage Num- Group

ber

2094 - 2100 1

2115 1

2117 1

2120 1

2122 - 2123 1

2125 - 2126 1

2129 1

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Fuselage Num- Group

ber

2131 1

2133 1

2136 1

2138 1

2140 - 2144 1

2146 - 2147 1

2149 - 2150 1

2153 - 2154 1

2156 - 2159 1

2161 - 2166 1

2168 - 2173 1

2175 1

2177 1

2179 1

2181 - 2182 1

2184 1

2186 1

2190 - 2191 1

2193 - 2195 1

2197 - 2198 1

2200 1

2202 - 2203 1

2205 1

2207 1

2209 - 2213 1

2215 - 2217 1

2219 - 2233 1

2235 - 2238 1

2240 1

2242 - 2243 1

2245 - 2246 1

2248 1

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BOEING SERVICE BULLETIN MD90-57A030

ALERT ALERT
Fuselage Num- Group

ber

2250 - 2251 1

2253 1

2255 - 2263 1

2288 - 2290 1

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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BOEING SERVICE BULLETIN MD90-57A030

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

Affected Maintenance Zones

Model Zone

MD-90-30 531, 631

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)

Condition Action

Within 9,470 flight cy- -

cles after the original

issue date on this

service bulletin.

Before the accumulation 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)

Condition 2: Do splice repair. Before further flight. - -

(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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BOEING SERVICE BULLETIN MD90-57A030

ALERT ALERT
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)

Task Number of Persons Task Hours Elapsed Hours

Defuel Tank 1 4.0 4.0

Purge Tank 1 8.0 8.0

FIGURE 1 1 1.0 1.0

TOTAL FOR EACH WING 13.0 13.0

Condition 2 (Crack Found)

Task Number of Persons Task Hours Elapsed Hours

Defuel Tank 1 4.0 4.0

Purge Tank 1 8.0 8.0

FIGURE 1 1 1.0 1.0

Splice Repair 2 80.0 40.0

TOTAL FOR EACH WING 93.0 53.0

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BOEING SERVICE BULLETIN MD90-57A030

ALERT ALERT
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 StaAirplane tion (Inches)

MD-90-30 (Left Wing Only) + 1022.0 + 7.4 + 7562.8

MD-90-30 (Right Wing Only) + 1022.0 + 7.4 + 7562.8

MD-90-30 (Both Wings) + 1022.0 + 14.8 + 15525.6

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:

Drawing No Title Sheet DCN/REV ADCN

STRG 11 REPAIR, LWR WING, XRS DWG - -

164.000

SR90570009

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MD90-57A030

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BOEING SERVICE BULLETIN MD90-57A030

ALERT ALERT
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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BOEING SERVICE BULLETIN MD90-57A030

ALERT ALERT

BLANK PAGE
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 Service Bulletin (US

Dollars)

ROLT as of the

original issue

date of this Service Bulletin (Calendar Days)

Kit Number Name

SB90570030-3 Service Kit 119 $28,126.00

B. Industry Support Information

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

service bulletin.

C. Parts Necessary For Each Airplane

1. Kits/Parts:

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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BOEING SERVICE BULLETIN MD90-57A030

ALERT ALERT
ALL

Kit SB90570030

Existing Part Notes

Number

New Part Number QTY Name

-3

SB90570030-3 -

3D0006-3 40 NUT ASSY (a)

3D0006-4 64 NUT ASSY (a)

HLT435-8-13 1 PIN

HLT435-8-15 2 PIN

HLT436-10-12 3 PIN

HLT436-10-21 1 PIN

HLT436-6-14 2 PIN

HLT436-8-5 2 PIN

HLT436-8-7 4 PIN

HLT439-6-10 12 PIN

HLT439-6-11 4 PIN

HLT439-6-12 4 PIN

HLT439-6-14 1 PIN

HLT439-6-15 2 PIN

HLT439-8-8 4 PIN

HLT639-8-11 10 PIN

HLT639-8-12 13 PIN

HLT639-8-13 18 PIN

HLT639-8-14 8 PIN

HST112-8-14 2 PIN, OVERSIZE

MS21042L3 13 NUT

MS21042L4 2 NUT

MS21042L5 4 NUT

NAS1252-416L 2 WASHER

NAS1252-516L 4 WASHER

NAS1401-3D3 17 WASHER

NAS1401-4D3 52 WASHER

S4931920-6-6 8 PIN (a)

S4931920-6-7 7 PIN (a)

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BOEING SERVICE BULLETIN MD90-57A030

ALERT ALERT
ALL

Kit SB90570030

Existing Part Notes

Number

New Part Number QTY Name

-3

S4931920-6-8 13 PIN (a)

S4931920-8-4 2 PIN (a)

SR09570100-3 1 STRINGER

SR09570100-7 2 ANGLE

SR09570100-9 2 CHANNEL

SR09570100-11 1 ANGLE

SR09570100-12 1 ANGLE

(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.

Part Number / Specifica- QTY Name Notes

tion

PR-1422 B-2 1 Quart Sealant (a)

(DMS 2082)

or

Equivalent

MC Coating, Chemical (b)

Film

Alodine 1200S 1 Quart

(DPM 1453-5)

or

Equivalent

Coating, Fuel Tank, Inte- (b)

gral

#833K086 Base; 1 Pint

#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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ALERT ALERT
Part Number / Specifica- QTY Name Notes

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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BOEING SERVICE BULLETIN MD90-57A030

ALERT ALERT
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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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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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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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)

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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.

Step Task Name Identification QTY More Data

1 Inspect Stringer 5919236-507 1 (a)

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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ALERT ALERT