FAA-机务基础执照题1

06/25/2009Bank:(AviationMechanicAirframe)AirmanKnowledgeTestQuestionBankTheFAAcomputer-assistedtestingsystemissupportedbyaseriesofsupplementpublications.Thesepublications,availablethroughseveralaviationpublishers,includethegraphics,legends,andmapsthatareneededtosuccessfullyrespondtocertaintestitems.UsethefollowingURLtodownloadacompletelistofassociatedsupplementbooks::)increasestrength.B)obtainuniformstrength.C)reduceweight.2.AMA021AMAThecantileverwingusesA)externalstrutsorwirebracing.B)noexternalbracing.C)theskintocarrymostoftheloadtothewingbutt.3.AMA102AMAIncasesofelongatedboltholesinawoodsparorcracksinthevicinityofboltholes,A)itispermissibletoreamthehole,plugwithhardwood,andredrill.B)thesparmaybereinforcedbyusinghardwoodreinforcingplates.C)anewsectionofsparshouldbesplicedinorthesparreplacedentirely.4.AMA102AMAThestrengthofawelldesignedandproperlypreparedwoodsplicejointisprovidedbytheA)bearingsurfaceofthewoodfibers.B)glue.C)reinforcementplates.5.AMA040AMA(1)MachinesewnseamsinaircraftcoveringfabricsmaybeofthefoldedfellorFrenchfelltypes.(2)Aplainlappedseamisneverpermissible.Regardingtheabovestatements,A)bothNo.1andNo.2aretrue.B)onlyNo.1istrue.C)onlyNo.2istrue.6.AMA040AMAWhendope-proofingthepartsoftheaircraftstructurethatcomeincontactwithdopedfabric,whichofthefollowingprovideanacceptableprotectivecoating?1.Aluminumfoil.2.Resinimpregnatedclothtape.3.Anyone-parttypemetalprimer.4.Cellulosetape.A)1and2.B)1and4.C)3and4.7.AMA040AMAThestrengthclassificationoffabricsusedinaircraftcoveringisbasedonA)bearingstrength.B)shearstrength.C)tensilestrength.8.AMA040AMAFinishingtape(surfacetape)isusedforwhatpurpose?A)Tohelpprevent'rippleformation'incoveringfabric.B)Toprovideadditionalanti-tearresistanceunderreinforcementtape.C)Toprovideadditionalwearresistanceovertheedgesoffabricformingstructures.9.AMA040AMAThedeterminingfactor(s)fortheselectionofthecorrectweightoftextilefabrictobeusedincoveringanytypeofaircraftistheA)maximumwingloading.B)speedoftheaircraft.C)speedoftheaircraftandthemaximumwingloading.10.AMA040AMABeforeapplyingaprotectivecoatingtoanyunpaintedcleanaluminum,youshouldA)wipethesurfacewithavgasorkerosene.B)removeanyconversioncoatingfilm.C)avoidtouchingthesurfacewithbarehands.11.AMA088AMAIfregistrationnumbersaretobeappliedtoanaircraftwithaletterheightof12inches,whatistheminimumspacerequiredfortheregistrationmarkN1683C?Note:2/3xheight=characterwidth.1/6xheight=widthfor1.1/4x2/3height=spacing.1/6xheight=strokeorlinewidth.A)52inches.B)48inches.C)57inches.12.AMA040AMAWhichdefectinaircraftfinishesmaybecausedbyadversehumidity,drafts,orsuddenchangesintemperature?A)Orangepeel.B)Blushing.C)Pinholes.13.AMA094AMAApieceofsheetmetalisbenttoacertainradius.ThecurvatureofthebendisreferredtoastheA)bendallowance.B)neutralline.C)bendradius.14.AMA094AMAThepurposeofajoggleistoA)allowclearanceforasheetoranextrusion.B)increaseobstructionforasheetoranextrusion.C)decreasetheweightofthepartandstillretainthenecessarystrength.15.AMA094AMA(RefertoAirframefigure6.)DeterminethedimensionsofA,B,andCintheflatlayout.Setback=.252Bendallowance=.345A)A=.748;B=2.252;C=2.004.B)A=.748;B=1.496;C=1.248.C)A=1.252;B=2.504;C=1.752.16.AMA094AMA(RefertoAirframefigure4.)ThelengthofflatAisA)3.750inches.B)3.875inches.C)3.937inches.17.AMA016AMAYoucandistinguishbetweenaluminumandaluminumalloybyA)filingthemetal.B)testingwithanaceticacidsolution.C)testingwitha10percentsolutionofcausticsoda.18.AMA037AMAOneofthebestwaystoassurethataproperlypreparedbatchofmatrixresinhasbeenachievedistoA)performachemicalcompositionanalysis.B)havemixedenoughforatestsample.C)testtheviscosityoftheresinimmediatelyaftermixing.19.AMA004AMACabinupholsterymaterialsinstalledincurrentstandardcategoryairplanesmustA)befireproof.B)beatleastflameresistant.C)meettherequirementsprescribedinPart43.20.AMA078AMAIfnoscratchesarevisibleaftertransparentplasticenclosurematerialshavebeencleaned,theirsurfacesshouldbeA)polishedwithrubbingcompoundappliedwithadampcloth.B)buffedwithaclean,soft,drycloth.C)coveredwithathincoatofwax.21.AMA078AMAWheninstallingtransparentplasticenclosureswhichareretainedbyboltsextendingthroughtheplasticmaterialandself-lockingnuts,thenutsshouldbeA)tightenedtoafirmfit,plusonefullturn.B)tightenedtoafirmfit,thenbackedoffonefullturn.C)tightenedtoafirmfit.22.AMA021AMAWhichpart(s)ofasemimonocoquefuselageprevent(s)tensionandcompressionfrombendingthefuselage?A)Thefuselagecovering.B)Longeronsandstringers.C)Bulkheadsandskin.23.AMA016AMAAircraftstructuralunits,suchasspars,enginesupports,etc.,whichhavebeenbuiltupfromsheetmetal,arenormallyA)repairable,usingapprovedmethods.B)repairable,exceptwhensubjectedtocompressiveloads.C)notrepairable,butmustbereplacedwhendamagedordeteriorat