Chapter 22 Auto Flight.docx
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Chapter 22 Auto Flight.docx
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Chapter22AutoFlight
Chapter22AutoFlight
22AutoFlight
THESYMBOL>----O---- TheFlightPathDirector. TheFlightPathVector. Thepitchbar. A 22自动飞行 在主飞行显示器上显示的标记>----O----<表示 飞行轨迹指引仪 飞行轨迹矢量 俯仰操纵杆 22AutoFlight THEFLIGHTPATHDIRECTOR: ReplacesthebarsincaseofFlightDirectorfailure. IstheonlypossibledisplayforaFlightDirector. IsdisplayedwhenTRK/FPAhasbeenselectedontheFCU. C 22自动飞行 飞行轨迹指引仪 如果飞行指引仪失效,替换指引杆 是飞行指引仪唯一可能的显示 会显示,如果航迹/飞行轨迹角已经在飞行操纵组件(FCU)上选择了 22AutoFlight WITHANAPENGAGED,PRESSINGTHE"PRIORITYP/B"ONASIDESTICK: DisengagestheAP. OverridestheAPwithoutdisengagement. Thereisnoeffect. A 22AutoFlight THECONSEQUENCEOFANALPHAFLOORDETECTIONIS: TOGA(full)thrustontheengines. AnosedownordertoreducetheaircraftAOA. Anautothrustdisengagement. A 22AutoFlight ATANYTIME,TODISENGAGETHEA/THRSYSTEM: Pushtheprioritypushbuttononeithersidestick. PushtheInstinctiveDisconnectswitchoneitherthrustlever. SetthethrustlevertotheTO/GAgate. B 按下推力杆任一边的自动解脱电门按钮 22AutoFlight BOTHFLIGHTDIRECTORSAREENGAGED: BypressingeitherFDP/BontheFCU. Automaticallyatsystempowerrise. ByselectingamodeontheFCU. B 22AutoFlight THEFLIGHTPATHDIRECTOR(FPD)SYMBOLPOSITIONISCOMPUTEDBYTHE: FlightAugmentationComputers(FACs). AirDataandInertialReferenceSystem(ADIRS). FlightManagementandGuidanceComputers(FMGCs). B 22AutoFlight THEBASICFUNCTIONSOFTHEFACARE: Flightmanagementandruddertrim. Flightenvelopeandruddercontrol. Flightenvelopeandflightmanagement. B 22AutoFlight THEMULTIPURPOSECONTROLANDDISPLAYUNIT(MCDU)DISPLAYS: Airportsorwaypointsaroundtheaircraftposition. Alldatarelatedtotheflightmanagementfunctions. Thestatusofguidancefunctionsandtheirmodes. B 22AutoFlight THETHRUSTTARGETISCOMPUTEDBYTHE: FlightManagementandGuidanceComputer(FMGC). FlightAugmentationComputer(FAC). EngineInterfaceUnit(EIU). A 22AutoFlight THEBRAKING/STEERINGCONTROLUNIT(BSCU): AllowscontroloftheNoseWheelSteeringduringautomaticlandingwithordersfromtheFMGC. AutomaticallydisengagestheAPat60kts. AutomaticallydisengagestheA/THRat60kts. A 22AutoFlight THEFMGCFUNCTIONSARE: FlightManagementandFlightEnvelopeProtection. FlightManagementandFlightGuidance. FlightEnvelopeProtectionandYawaxiscontrol. B 22AutoFlight THETRIMFUNCTIONOFTHEFACIS: Pitchtrim. Ruddertrim. Ailerontrim. B 22AutoFlight THEFLIGHTGUIDANCEFUNCTIONSARE: Autopilot,FlightPlanandAutothrust. Autopilot,FlightDirectorandAutothrust. FlightManagement,AutopilotandAutothrust. B 22AutoFlight THEFLIGHTCONTROLUNIT(FCU)ISNORMALLYUSED: Foralong-termorderselection. Forashort-termorderselection. Fororderselection,iftheguidanceismanaged. B 22AutoFlight YOUCANACCESSTHEAUTOFLIGHTSYSTEM(AFS)TESTSFROMTHE: FlightControlUnit(FCU). MCDU. FlightAugmentationComputer1(FAC1). B 22AutoFlight THEINTERFACEBETWEENTHEAUTOFLIGHTSYSTEM(AFS)COMPUTERSANDTHECENTRALIZEDFAULTDISPLAYSYSTEM(CFDS)IS: TheFlightAugmentationComputer1(FAC1). TheMCDU. TheFlightManagementandGuidanceComputer(FMGC)2. A 22AutoFlight THEAUTOMATICFLIGHTSYSTEM(AFS)COMPUTERSARETHEFLIGHTMANAGEMENTANDGUIDANCECOMPUTERS(FMGC)AND: ELevatorAileronComputers(ELACs). SpoilerElevatorComputers(SECs). FlightAugmentationComputers(FACs). C 22AutoFlight ONTHEFLIGHTCONTROLUNIT(FCU)THESPEED/MACHSWITCHING: Isautomatic. Mustbeperformedbythecrewfortheclimbphaseonly. Mustbeperformedbythecrewbothfortheclimbanddescentphases. A 22AutoFlight PRESSINGTHEHEADING-VERTICALSPEED/TRACK-FLIGHTPATHANGLE(HDG-V/S/TRK-FPA)P/BONTHEFLIGHTCONTROLUNIT(FCU): ChangestheTRK-V/SintoTRK-FPAonthePFD. ChangestheFlightDirector(FD)symbolsintoFlightPathVector(FPV)andFlightPathDirector(FPD)andviceversaonthePFD. Hasnoeffectontheindications. B 按下飞行控制组件(FCU)上的HEADING-VERTICALSPEED/TRACK-FLIGHTPATHANGLE(HDG-V/S/TRK-FPA)P/B按钮 在主飞行显示器上变TRK-V/S为TRK-FPA 改变飞行导向仪信号(FD)为飞行轨迹矢量(FPV)和飞行轨迹导向仪,在主飞行显示器上反之亦然 在显示上没有效果 22AutoFlight THETHRUSTLIMITISCOMPUTEDBY: TheFMGCaccordingtotheAP/FDmode. TheECU(CFM)/EEC(V2500)accordingtotheThrustleverposition. TheECU(CFM)/EEC(V2500)accordingtoAP/FDmode. B 推力限制由 飞行管理导向计算机据自动飞行/飞行指引仪模式计算 ECU(CFM)/EEC(V2500)据推力杆位置计算 TheECU(CFM)/EEC(V2500)据自动飞行/飞行指引仪模式计算 22AutoFlight WITHTHEA/CINFLIGHT,THEAPENGAGEDANDTHEA/THRACTIVE,THEA/THRMODE: CanbechosendirectlybythepilotontheMCDU. DependsontheAP/FDlateral(ROLL)mode. DependsontheAP/FDvertical(PITCH)mode. C 飞机在飞行中,实施了自动飞行,飞机推力活跃,飞机推力模式 飞行员可以直接在多功能控制显示组件上选择 取决于AP/FD横轴(横滚)模式 取决于AP/FD纵轴(俯仰)模式 22AutoFlight WHENTHEFDTAKE-OFFMODEENGAGES,THEA/THR: Automaticallyengagesandisactive. Automaticallyengagesandisnotactive. Doesnotautomaticallyengageandtheenginesarecontrolledbythethrustlevers. B 22AutoFlight WITHTHEA/CINFLIGHT,THEA/THRNOTENGAGED,THETHRUSTLEVERSINCLBGATE,ANALPHAFLOORISDETECTED: TheA/THRwillnotengagebecausetheenginesarealreadyinCLBthrust. TheA/THRautomaticallyengagesbutisnotactive. TheA/THRautomaticallyengagesandcontrolstheengineswithaTOGAthrusttarget. C 22AutoFlight THEFCUALLOWS: SelectionofFGmodes(functions). Selectionofradio-navfrequencies. IRSalignment. A 22AutoFlight WHENFAC1P/B"FAULT"LIGHTIS"ON": TheFAC1ruddercontrolfunctionshavefailed. Thespeedlimitcomputationhasbeenlost. FAC1hasfailed. C 22AutoFlight THECOMPUTERSCHECKEDDURINGAUTOFLIGHTSYSTEM(AFS)TEST,ARETHE: FlightManagementandGuidanceComputers(FMGCs)only. AFSLinearreplaceableUnits(LRUs). FMGCsandFlightControlDataConcentrators(FCDCs). B 22AutoFlight WITHAP1ANDAP2NOTENGAGED,FD1ANDFD2ENGAGEDANDA/THRACTIVE: FMGC1controlsengine1andFMGC2controlsengine2. FMGC1controlsbothengines. FMGC2controlsbothengines. B 22AutoFlight INNORMALOPERATION,WITHBOTHMCDUSSHOWINGTHESAMEPAGE,AMODIFICATIONMADEBYTHEPILOTONMCDU1ISSENTTOMCDU2: Directly. FromFMGC1throughFMGC2. FromFMGC1,FMGC2andRMP2. B 22AutoFlight INCASEOFFMGC1FAILURE,FMGC2AUTOTUNES: Side2NavReceiversthroughRMP2andside1NavReceiversthroughRMP1. Side2NavReceiversthroughRMP2andside1NavReceiversdirectly. Side1andside2NavReceiversdirectly. B 22AutoFlight WITHAPENGAGED,THEFLIGHTAUGMENTATIONCOMPUTER(FAC)COMPUTESTHETURNCOORDINATIONORDERFROMTHE: A/Clateralacceleration. FlightManagementandGuidanceComputer(FMGC)rollorder. FMGCyaworder. B 22AutoFlight INFLIGHT,INCASEOFATEMPORARYLOSSOFELECTRICALPOWERTOFAC2,FAC2P/B"FAULT"LIGHTCOMESONAND: FAC2canbemanuallyresetusingFAC1P/B. FAC2canbemanuallyresetusingFAC2P/B. ThereisnowaytoresetFAC2. B 22AutoFlight THEPOSITIONOFTHEAIRCRAFT,USEDINTHEFLIGHTPLAN,ISCOMPUTEDBY: TheFGpartoftheFMGC. TheFMpartoftheFMGC. TheDMC. B 22AutoFlight THEFLIGHTPLANNINGIS: Thefunctionthatintegratestheroutestheaircraftmustfollowandtheconstraintstoconstructaflightplan. Thefunctionthatgivestheaircraftpositionandthefollow-upoftheflightplan. Theratioofthecostoftimetothecostoffuel. 22自动飞行 A 飞行计划 其功能结合了飞机必须遵循的航路和制定飞行计划的约束 它的作用就是为飞机提供位置及此飞行计划的后续工作 是花费的时间与消耗的燃油之间的比率 22AutoFlight ONTHENAVIGATIONDISPLAY(ND),THEAIRCRAFTMODELISREPRESENTEDFIXED: WhateverROSE-NAV,ARC,orPLANmodesareselectedontheFlightControlUnit(FCU). InPLANmodeonly. AllthetimeexceptinPLANmode. C 22AutoFlight THEYAMDAMPERACTUATORSENDSAMECHANICALFEEDBACKTOTHEPEDALS: Fordutchrolldamping. Forenginefailrecovery. Never. C 偏航阻尼器作动筒发送一个机械的反馈到踏板上 为了阻尼荷兰横滚 为了恢复发生故障的发动机 从不发送反馈 22AutoFlight WHENTHEAPISNOTENGAGED,THEYAWDAMPERORDERSARENORMALLYCOMPUTEDBYTHE: ElevatorAileronComputer(ELAC). FlightManagementandGuidanceComputer(FMGC). SpoilerElevatorComputer(SEC). A 未使用自动驾驶时,偏航阻尼器指令正常情况下是由什么来计算的? 升降舵副翼计算机(ELAC) 飞行管理和导向计算机(FMGC) 扰流板升降舵计算机(SEC) 22AutoFlight THEMANDATORYPARAMETERUSEDBYTHEALPHAFLOORDETECTIONIS: A/Cselectedspeed. A/Cweightandselectedspeed. A/CAngleOfAttackandslat/flapconfiguration. C 迎角基线探测所使用的强制性参数是 飞机选择的速度 飞机重量和选择的速度 飞机迎角和襟缝翼构型 22AutoFlight ONTHEPFD,THEPREDICTEDVFE(MAXIMUMFLAPEXTENDEDSPEED)IS: Onlydisplayedwhenaircraftaltitudeisbelow15000ft. Shownbyanamberstripalongthespeedscale. Thespeedcorrespondingtothebestlifttodragratio. A 在主飞行显示器上(PFD),可预测的VFE(副翼最大可延展速度)是 只有当飞机高度低于15000英尺才显示 沿着速度标尺显示的琥珀色线条 对应于最大升力与阻力比率的速度 22AutoFlight THETARGETAIRSPEEDSYMBOLISDISPLAYEDONTHEPFD: InmagentawhenitismanuallyenteredontheFlightControlUnit(FCU). Eitherinmagentaorcyanorinnumericformwhenoutofthespeedscale. Asacyandoublebar. B 目标空速标记显示在主飞行显示(PFD)上 当它被人工录入飞行控制组件(FCU)时,是红紫色的。 当其超出速度刻度时,可呈现为红紫色,青色或以数字式方式。 作为一个青色的双条线 22AutoFlight THESTALLWARNINGSPEED(VSW)ISCOMPUTED: Continuously. BytheFlightAugmentationComputers(FACs)inrollalternatelaw. BytheFACsinpitchalternatelaworpitchdirectlaw. C 失速警告(VSW)的速度 被连续地计算 由飞行增压计算机按照横滚转变规则计算 由飞行增压计算机按照横滚转变规则或俯仰引导规则计算 22AutoFlight ON
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- Chapter 22 Auto Flight