Multi-engineSERVICELETTERCessnaATextronCompanyMEL:.54-01TITLENACELLES/PYLONS-ENGINEBEAMINSPECTIONEFFECTIVITYREASONMODEL402C414ASERIALNUMBERS402C0001thru402C1020414A0001thru414A1212Crackshavebeendiscoveredonsomeenginebeams.Thecracksextendfrombehindthedoublerlocatedforwardoftheaftenginemountoraftoftheforwardenginemount.DESCRIPTIONThisserviceletterprovidesinstructionstodoaradiographic(x-ray)andeddycurrentinspectionoftheenginebeamsfortheleftandrightenginenacelles.NOTE:Thisx-rayinspectionwillrequirearadiographerthatisqualifiedandcertifiedtoLevel2or3pertherequirementsofNAS410orequivalent.NOTE:TheeddycurrenttechnicianmustbequalifiedandcertifiedtoLevel2or3pertherequirementsofNAS410orequivalent.COMPLIANCEMANDATORY.Thisservicelettermustbeaccomplishedonenginebeams(5654109-X)with15,000ormoreflighthoursaslistedinthetablethatfollows,andthenevery200flighthoursuntilallfourenginebeams(5654109-X)arereplaced.AirplaneFlightHoursFlightHoursandDaystocomplyOver30,00025flighthoursor30days,whicheveroccursfirst25,000-30,00050flighthoursor45days,whicheveroccursfirst20,000-24,99975flighthoursor60days,whicheveroccursfirst15,000-19,999100flighthoursor90days,whicheveroccursfirstNOTE:Aftertheinitialinspection,thisserviceletterinspectionmustbecompletedevery200flighthoursuntilallfourenginebeams(5654109-X)arereplaced.March20,2015MEL-54-01Page1of12CessnaAircraftCompany,CessnaCustomerService,P.O.Box7706,Wichita,KS67277,U.S.A.1-316-517-5800ThisdocumentcontainstechnicaldataandissubjecttoU.S.exportregulations.ThisinformationhasbeenexportedfromtheUnitedStatesinaccordancewithexportadministrationregulations.DiversioncontrarytoU.S.lawisprohibited.ECCN:9E991COPYRIGHT©2015Multi-engineSERVICELETTERCessnaATextronCompanyMEL-54-01TOOLINGNAMENUMBERMANUFACTURERUSEX-rayTubeCommerciallyAvailableX-rayExposureX-rayFilmKodakMCommerciallyAvailable5x7X-rayFilm0.12StainlessSteelCommerciallyAvailableTomeasurethepenetratingPenetrameterpoweroftheX-ray.LeadExposureCommerciallyAvailableProtectionfromX-rayScreensExposure.0.12"AI.ShimBlockFabricateLocallyToshimthepenetrameter.0.10"SSShimBlockFabricateLocallyToshimthepenetrameter.EddycurrentNortec500OlympusEddyCurrentTestsystem.instrument48WoerdAveWaltham,MA024530.125in.DiameterMP905-60FX-OlympusProbeforEddyCurrentTestrightangleprobe1-3Msystem.StainlessSteelVMSS3RS-1.0VMProductsTotesttheEddycurrentReferenceStandard1120862ndAve.E.SystemCalibration.(Note)Puyallup,WA98373NOTE:IfanequivalentisusedinplaceoftheStainlessSteelReferenceStandard,theequivalentstandardsmusthavea0.020"deepsurfaceEDMnotch.Ifastainlesssteelreferencestandardisnotavailable,a6AL4Vtitaniumreferencestandard maybeused.REFERENCESCessnaModel402CMaintenanceManualCessnaModel414MaintenanceManualPUBLICATIONSAFFECTEDNoneACCOMPLISHMENTINSTRUCTIONS1.Preparetheairplaneformaintenance.A.Makesurethattheairplaneiselectricallygrounded.B.MakesurethatallswitchesareintheOFF/NORMposition.C.Disconnectelectricalpowerfromtheairplane.(1)Disconnecttheairplanebattery.(2)Disconnectexternalelectricalpower.D.Attachmaintenancewarningtagstothebatteryandexternalpowerreceptaclethathave"DONOTCONNECTELECTRICALPOWER-MAINTENANCEINPROGRESS"writtenonthem.2.Openthecowldoorsforeachenginenacelle.(RefertotheappropriatesectionsintheModel402Cand414MaintenanceManual.)3.Removetheuppercowlingfromeachenginenacelle.(RefertotheappropriatesectionsintheModel402Cand414MaintenanceManual.)4.Disconnectorremovecomponentsasrequiredtogainaccesstotheenginebeam.A.Securedisconnectedorremovedcomponentssotheydonotinterferewiththeinspection.MEL-54-01Page2March20,2015

# Multi-engine



# SERVICE

LETTER



# ~

Cessna A Textron Company 

# MEL-54-01 5

. Remove

soils

and contaminates

from

the four engine

beams

paying particular

attention

to the forward

and aft engine

mount locations

. 6. (Refer

to Figure

1

. ) Take

x-ray images

of

all four engine

beams,

one image forward

of the

aft engine mount

and

one image

aft

of the

aft engine

mount. NOTE:



# The steps

that follow

are required

for each engine

beam

. Each engine

beam

will have

two

X

- Ray images

. One image

will

be forward

of the

aft engine

mount

and

the second

image

will

be

aft

of the aft engine

mount.

There

will

be

a total

of eight X-Ray

images

. NOTE:



# The radiographer

must

be qualified

and certified

to Level

2

or

3 per

the requirements

of NAS41

0 or equivalent. A. (Refer

to Table

1

. ) Place identification

tape

to the cassette. B. (Refer

to Figure

1

. ) Place

0.12

inch stainless

steel penetrameter

on engine

beam

just forward

or aft

of the angle

as shown. (1)

(For

the location

forward

of the

aft engine

mount.)

Place

shim blocks

of

0

. 12 inch aluminum and

0.10

inch

of stainless

steel

on

top

of penetrameter. (2)

(For

the location

aft

of the

aft engine

mount.)

Place

a shim

block

of 0.10

inch

of stainless steel

on

top

of penetrameter

. C. (Refer

to Figure

1

. ) Position

the

5x7

film cassette

on

top

of the engine

beam

and against

the forward or

aft side

of the

aft engine

mount. D. (Refer

to Figure

1.) Locate

the x-ray

tube

as follows: 24 inches

below

the engine

beam

. Primary

x-ray

beam

to

be perpendicular

to the upper surface

of the engine

beam. The

focal

point

is

in the middle

of the engine

beam centerline

and centered

on

the

last

row of fasteners

that attach

the upper

angle

to the beam (approximately

2 inches forward

or

aft of the

aft engine

mount). 

# WARNING:

WARNING: X-RADIATION

PRESENTS

A HAZARD

TO HUMANS. FOLLOW

ALL APPLICABLE

FEDERAL,

STATE

AND LOCAL REGULATIONS

FOR SAFE OPERATIONS

OF X-RAY PRODUCING EQUIPMENT. 

# E. (Refer

to Table

1.) Expose

film

per Table

1 requirements. NOTE:



# Film density

in the area

of interest

must

be

1

. 8

to 3.5 H&D. Satisfactory

sensitivity

will

be indicated

by the penetrameters

2-2T

hole. March

20, 2015

MEL-54-01 Page

3

# ~ Multi-engine



# SERVICE

LETTER

Cessna A Textron

Co mpany 

# MEL-54-01

. TABLE

1 Engine

Film (Note

1) Film

Material

SFD

kV (Note

2)

MAS Beam

View

Screens

Pb Thickness 1F

LH

OB

5x7

0

. 005F/

0

. 3 inch

24 inch

115

300 0.010B 1A

LH

OB

5x7

0

. 005F/

0

. 3 inch

24 inch

115

300 0

. 010B 2F

LH INBD

5x7

0

. 005F/

0.3

inch

24 inch

115

300 0

. 010B 2A

LH INBD

5x7

0

. 005F/

0

. 3 inch

24 inch

115

300 0

. 010B 3F

RH INBD

5x7

0

. 005F/

0.3

inch

24 inch

115

300 0

. 010B 3A

RH INBD

5x7

0

. 005F/

0

. 3 inch

24 inch

115

300 0

. 010B 4F

RH

OB

5x7

0

. 005F/

0.3

inch

24 inch

115

300 0

. 010B 4A

RH

OB

5x7

0

. 005F/

0

. 3 inch

24 inch

115

300 0

. 010B NOTE:

1

. Kodak

M film

was

used

to test

this technique

. Equivalent

films

may

be used

. NOTE:

2

. 1.5

mm

2 

# focal

spot constant

potential

x-ray

tube

. Larger

focal

spot

x-ray

tube

is acceptable

if the 2-2T penetrameter

sensitivity

is attained

. 7

.

Do

an examination

of

all the films looking

for transverse

cracks

to the long

axis

of the engine

. NOTE:

If an obvious

crack

is not

v

i sible,

use

7x

to

1 Ox magnification

as necessary

. A. 

# (Refer

to the attachment)

Add notes

of any findings

to the INSPECTION

RESULTS

FORM

. B

.

If

a crack

is found

. Contact

Cessna Structures

a

t: csstructures@txtav

. com

, or phone

: 316-517-6061

. 8

. (Refer

to Figure

3.) Calibrate

the Eddy current

probe. NOTE:

The eddy current technician

must

be qualified

and certified

to Level

2

or

3 per

the requirements of NAS

4

1 0

or equivalent A. 

# Connect

the probe

to the eddy current instrument B

.

Set

the eddy current instrument

frequency

to

2

. 0 MHz

. C

. Place

the probe

on

the standard

away

from

the EDM notches

. D

. Push

the

null (balance)

button. E.

Place

the

null point

in the lower

right quadrant

of the instrument

display

at approximately

the 70% horizontal

and

20% vertical

screen

position

. 

# F. Adjust

the phase

angle

to place

the

s

i gnal

from

lift-off traveling horizontal

and

to the

left

of the null point G

. Adjust

the instrument

parameters

to achieve

a minimum

vertical separation

of

3 major screen divisions

in signal amplitude

between

the

null point

and

the 0.020

inch surface

notch

on

the

s

t andard

. MEL-54-01 Page4

NOTE:

This

is the scan reference

or sensitivity

level,

this

is not

a reject

level.

There

are

no acceptable

cracks

. All relevant

crack

ind

i cations

are suspect

and

shall

be rejected regardless

of the signal response

amplitude

.

March

20, 2015Multi-engineSERVICELETTERCessnaATextronCompanyMEL-54-019.(RefertoFigure2.)Doaneddycurrentexaminationofthefourenginebeamsattheforwardmountlocations.NOTE:TheeddycurrenttechnicianmustbequalifiedandcertifiedtoLevel2or3pertherequirementsofNAS410orequivalent.A.Inserttheeddycurrentprobeintothelightninghole.CAUTION:Thereisatoolingholeontheforwardsideoftheforwardnutplate.Theproximityoftheholetothenutplatemaybecloseenoughtoinfluencetheeddycurrentprobe.B.Scanaroundeachofthenutplateassemblies(2eachperbeam)commontotheforwardenginemountinstallation.C.Ifthetoolingholeinfluencestheinspection,carefullyscanuptothetoolingholefrombothdirectionsandmonitortheinstrumentdisplay.D.Ifyouareunsureifyouhaveanindicationfromthetoolingholeoracrackuseavisualaidesuchasavideo-probetoinspecttheareaadjacenttothehole.E.Ifacrackisfound.ContactCessnaStructuresat:csstructures@txtav.com,orphone:316-517-6061.F.(Refertotheattachment)AddnotesofanyfindingstotheINSPECTIONRESULTSFORM.10.Doadetailedvisualinspectionoftheexternalsurfacesofeachenginebeamforcracks,corrosionandloosefasteners.Useaflashlightandamirrororaflexiblebaroscopeasnecessarytocompleteadetailedvisualinspection.NOTE:Adetailedvisualinspectionisdescribedasanintensivevisualexaminationofaspecificstructuralarea,system,installation,orassemblytodetectdamage,failure,orirregularity.Availablelightingisnormallysupplementedwithadirectsourceofgoodlightingatanintensitydeemedappropriatebytheinspector.Inspectionaidssuchasmirrors,magnifyinglenses,etc.maybeused.SurfacecleaningandelaborateaccessproceduresmaybenecessaryA.Ifacrackorseverecorrosionisfound.ContactCessnaStructuresat:csstructures@txtav.com,orphone:316-517-6061.B.(Refertotheattachment)AddnotesofanyfindingstotheINSPECTIONRESULTSFORM.11.(Refertotheattachment)CompletetheINSPECTIONRESULTSFORMandreturntoCessnaatcsstructures@txtav.com.12.InstallanycomponentsthatwereremovedtogainaccesstotheenginebeaminStep4.13.Installtheupperenginecowlingforeachnacelle.14.Closethecowldoorsforeachenginenacelle.15.Removethemaintenancewarningtagsandconnecttheairplanebattery.16.SendtheINSPECTIONRESULTSFORMtocsstructures@txtav.com.17.Makeanentryintheairplanelogbookthatstatescomplianceandmethodofcompliancewiththisserviceletter.March20,2015MEL-54-01Page5Multi-engine820650MEL-54-01Page6SERVICELETTERX-RayFilm(Forward)DETAILAVIEWA-AFigure1.EngineBeamX-Ray,AftEngineMount(Sheet1)CessnaATextronCompanyMEL:.54-01X-RayFilm(Aft)5210T1014March20,2015Multi-engineSERVICELETTERCessnaATextronCompany820651MEL-54-01X-RayFilm(Forward)AftEngineMount(Reference)X-RayFilm(Aft)ci-+++++iO++++X-RaySource(Forward)VIEW8-8PenetrameterandShims(Forward)X-RayFilmPosition(Forward)FocalPoint(Forward)LastFastenerRowOnAngleAsShownVIEWC-C(Typical,AllLocations)0-___PenetrameterandShim(Aft)cX-RaySourcePosition(Aft)PenetrameterandShim(Aft)X-RayFilmPosition(Aft)Figure1.EngineBeamX-Ray,AftEngineMount(Sheet2)March20,2015MEL-54-01Page7Multi-engine820683241nchesSERVICELETTERAnglesInstalledBySK414-17X-RayFilm(Reference)J..---EngineBeam___.--(Reference)PrimaryX-RayBeam(Reference)X-RaySourcePosition(Reference)VIEW0-0Figure1.EngineBeamX-Ray,AftEngineMount(Sheet3)MEL-54-01Page8CessnaATextronCompanyMEL-54-01March20,2015Multi-engineSERVICELETTER820687FWDtPenetrameterFigure1.EngineBeamX-Ray,AftEngineMount(Sheet4)March20,2015CessnaATextronCompanyMEL-54-01MEL-54-01Page9Multi-engine820684SERVICELETTEREddyCurrentProbeAccessEddyCurrentProbeAccessFigure2.EngineBeamEddyCurrent,ForwardEngineMount(Sheet1)MEL-54-01Page10CessnaATextronCompanyMEL-54-01March20,2015Multi-engineSERVICELETTERCessnaATextronCompany'MEL-54-01820685ToolingHoleScanAroundBothNutplates(MayCauseEdgeEffectSignals)March20,2015EddyCurrentProbeAccess.-----'--------JFigure2.EngineBeamEddyCurrent,ForwardEngineMount(Sheet2)MEL-54-01Page11Multi-engine820686MEL-54-01Page12Lift-OffSERVICELETTERFigure3.EddyCurrentCalibration(Sheet1)CessnaATextronCompany.MEL-54-01MinimumSensitivityLevelNullPointMarch20,2015Multi-engineATTACHMENTCessnaATextronCompanyMEL-54-01INSPECTIONRESULTSFORMAirplaneSerialLeftEngineHoursNumberTotalAirframeHoursRightEngineHoursOwner'sNameInspectionFacilityNameOwner'saddressInspectionFacilityAddressListallSTCinstalledontheairplaneInthetablethatfollowspleaseprovidedetailedanddimensioneddescriptionsofanycrack(s).Attachpicturestothisformasnecessary.Multi-engineATTACHMENTCessnaATextronCompanyMEL-54-01INSPECTIONRESULTSFORMCONTINUEDLEFTOUTBOARDENGINEBEAMLEFTINBOARDENGINEBEAMWasacrackfoundYes/No?WasacrackfoundYes/No?Detaileddescription:(AttachpicturesandadditionalDetaileddescription:(Attachpicturesandadditionaldetailsasnecessary)detailsasnecessary)RIGHTINBOARDENGINEBEAMRIGHTOUTBOARDENGINEBEAMWasacrackfoundYes/No?Wasa crackfoundYes/No?Detaileddescription:(AttachpicturesandadditionalDetaileddescription:(Attachpicturesandadditionaldetailsasnecessary)detailsasnecessary)-Sendcompletedform/attachmentstoCessnaStructuresatcsstructures@txtav.com