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1、Toascertaintheperformancecapabilitiesoftheprototypedevelopmenthardwareunderthenewtwo-fail/operaterequirements,theBA609FlightControlsIPTinitiatedaprogramofpilot-in-the-looptestingofactuatorfailuremodes.ThesetestscomprisedpilotevaluationsofBA609flightcontrolsys
2、temhandlingqualitiesfollowingtheoccurrences:•Dualelectricalsystemfailures.•Dualelectricalcomponentfailures.•Dualhydraulicsystemfailures.•Dualhydrauliccomponentfailures.•Singleelectricalsystemcombinedwithsinglehydraulicsystemfailures.•Singleelectricalcomponent
3、combinedwithsinglehydraulicsystemfailures.•Singleelectricalsystemcombinedwithsinglehydrauliccomponentfailures.•Singleelectricalcomponentcombinedwithsinglehydrauliccomponentfailures.Foreachtestcondition,theworstcasesystemorcomponentfailuremodewaseitherinitiate
4、dorsimulated.ForEHSVfailures,secondstagespoolswerefailedhard-overinbothdirections,aswellasatnullposition,causingthecylindertohydraulicallylock.Solenoidswerefailedbothopenandclosed.LVDTswereshortedandcoresweresimulatedtostructurallyfail.Bypass,pressurerelief,a
5、nddeltapressuresensorhydraulicspoolsweresimulatedtobestuckinanyposition,andtheirspringsweresimulatedasfailed.Foranycomponentwhoseproperfunctioningcouldnotvalidatedeitherinflightorduringpreflightbuilt-intesting(PFBIT),thecomponentwasconsideredtobeanexistingdor
6、mantfailure.BecausetheBA609isatiltrotoraircraft,ithasthreedifferentmodesofflight:airplane,conversion,andhelicopter.Asaresult,testingofeachrelevantfailuremodeconditionineachofthethreeflightmodeswasrequired.OneareainwhichtheVMSILtestingwasnotrepresentativeofthe
7、actualaircraftwasthestructuralstrengthofthesimulatedflaperonandelevatorsurfaces.Althoughtheflaperonandelevatoractuatortestrigshadbeenmodifiedtorepresenttheaircraftstructuralstiffness,itwasimpracticaltosimulateactualaircraftstructuralstrengthwiththetestrigs.Th
8、erefore,actuatorloadsweremonitoredduringtestingtodetermineifacceptablestructuralloadswereexceeded.BasedonVMSILpilot-in-the-loopevaluations,testdatafromthefailuremodetesting,andarevisedfai
