AIRBUS - SmartCockpit
AIRBUSA330Flight deck and systemsbriefing for pilotsTHIS BROCHURE IS PROVIDEDFOR INFORMATION PURPOSES ONLYAND ITS CONTENTSWILL NOT BE UPDATED.IT MUST NOT BE USED AS AN OFFICIAL REFERENCE.FOR TECHNICAL DATA OR OPERATIONAL PROCEDURES,PLEASE REFER TO THERELEVANT AIRBUS DOCUMENTATIONSTL 472.755/92 issue 4STL 472.755/92 Issue 4March 1999
STL 472.755/92 Issue 4
Contents1.General2.Flight deck layout3.Electrical system4.Hydraulic system5.Flight controls6.Landing gear7.Fuel system8.Engine controls9.Auxiliary power unit10. Automatic flight system11. Environmental control system12. Electronic instrument system13. Radio management and communication14. Central Maintenance System.STL 472.755/92 Issue 4
STL 472.755/92 Issue 4
1. GeneralSTL 472.755/92 Issue 41.1
A330 GeneralA330 general arrangementTypical cabin layoutA330-20058.37 m191ft 3inA330-200256 seats9.37m30ft 9in18 sleeperette(62 in pitch)196 Economy(32 in pitch)295 seatsA330-30060.304m198ft17.8m58ft 5in10.7m35ft 1.3in42 Business(40 in pitch)6.67m21ft 11in18 sleeperette(62 in pitch)22.18m72ft 9in49 Business(40 in pitch)228 Economy(32 in pitch)A330 fuselage cross-section208.2in5.287m63.66 m208ft 10inA330-300Passenger cabin9.37m30ft 9in65.7in1.67mz True widebodyspaciousness andadaptabilityLower cargo holds60.304m198ft16.828m55ft 2.5in10.7m35ft 1.3in91.7in2.33m6.67m21ft 11inSTL 472.755/92 Issue 425.58 m83ft 11inLD-3s125in3.18m67in1.702mz Large, efficient, fullycompatible with existingworldwide air cargosystem222in5.64m1.2
A330 GeneralIntroductionBasic data The medium to long-range A330 is an all-new, widebody, twin-engine, twin-aisle aircraft. The design combines high technology developed forthe A320 and A340 with the wide experience gainedfrom the A300 and A310 aircraft currently in worldwide service.As with the A319, A320, A321 and A340, it willincorporate all of the following features :- two-man crew operation with CRT displays- electrically signalled flight controls- sidestick controllers- full authority digital engine control (FADEC)- centralized maintenance system. Since it’s introduction in December 1993 the aircraft isthe most advanced medium to long-range airlineroffering a major stride forward in airline profitability. Certification basis includes :- JAR 25 at change 13- JAR AWO at change 1 for CAT II and CAT III andautoland.- ICAO annex 16 chapter 3 for noise.STL 472.755/92 Issue 4A330-200A330-300MTOW*MLWMZFW230 000 kg180 000 kg168 000 kg217 000 kg179 000 kg169 000 kgMax fuel capacity139 090 lit97 170litMax operatingaltitude41 100 ft41 100 ftPowerplantsGE CF6-80E1A470 000 lbGE CF6-80E1A267 500 lbRR Trent 77271 100 lbRR Trent 768 / 77267 500 lb / 71 100 lbPW 416868 000 lbPW 4164 / 416864 000 lb / 68 000 lbDesign speedsVmo/Mmo330 kt CAS/0.86330 kt CAS/0.86Underfloor cargoFrom 27LD3 to3LD3 8 pallets bulk 19.7 m332/33LD3/11 pallets bulk 19.7 m3* Max ramp weight 900 kg higher than MTOW1.3
A330 GeneralAircraft design specifications1. Design weights (see page 1.3)4. Structural life (design aims)The objectives for primary structure fatigue life are asfollows based on average block time of 4 hours :- design life goal . 20000 flights- threshold for initial inspection 8 750 flights2. Design speedsVMO 330 kt CASMMO 0.86VD 365 kt CASMD 0.93VB 260 kt CASMB 0.78VLO (landing gear) extensionretractionVLE (Landing gear extended)5. Landing gearThe design aim is 25000 cycles safe life operation inaccordance with FAR and JAR.250 kt CAS6. Cabin pressure3. Slat and flap design speedsLeverposition0Config. Design speedNo.VFE kt (CAS)Climb/cruise/holding0FunctionMax nominal operationaldifferential pressure574 mb 7 mb 8.33 psi 0.1 psiActuating cabin pressureof discharge valve610 mb 7 mb 8.85 psi 0.1 psi1Holding12401Take-off1 F2152Approach1*205Max relief valve overpressure638 mb9.25 psiTake-off2196- 70 mb1.00 psi3Take-off/approach3186Max negative differentialpressureFullLandingFull180STL 472.755/92 Issue 41.4
A330 GeneralAircraft design specifications7. Fuel capacityA330-200LitresUS gallonsLitresUS gallons42 00042 0003 6503 6506 23041 56011 09511 0959649641 64610 98041 90441 9043 6243 6246 230-11 07011 0709579571 646-139 09036 74597 28625 700Inner tank LHInner tank RHOuter tank LHOuter tank RHCenter tankTrim tankTotalA330-3008. Pavement strengthMax ramp weight and max aft CG.ACNFlexible pavementRigid pavementCat ACat BCat CCat DCat ACat BCat CCat Tyres radial- main gear 1400 mm x 530 mm x R23- nose gear 1050 mm x 395 mm x R16STL 472.755/92 Issue 41.5
A330 GeneralWeight and balanceA330-200 CG limitsSTL 472.755/92 Issue 4A330-300 CG limits1.6
A330 GeneralGround maneuvre capabilityEffectiveturn angleR5Minimum turning radiusR3TowingThe A330 can be towed or pushed up to a nosewheelangle of 78 from the aircraft centre line at all weights upto maximum ramp weight without disconnecting thesteering.10,684mTaxiingYAMinimum turning radii (with tyre slip) and minimumMin. turning widthfor 180 turnR4pavement width for 180 turn are as shown.R6Outsideface of tireA330-200Type of turn 1Effective turn angle78 (Feet)MeterType of turn 2Effective turn angle62.3 (Feet)MeterType of turn 1Effective turn angle77.95 (Feet)MeterA330-300Type of turn 2Effective turn angle64.5 R634.60113.538.01124.7X 22.19 m / 72.8 ftSTL 472.755/92 Issue 4X 27.50 m / 90.23 ftType of turn 1 : Asymmetric thrust differential braking (pivoting on one main gear)Type of turn 2 : Symmetric thrust no braking1.7
STL 472.755/92 Issue 4
2. Flight deck layoutSTL 472.755/92 Issue 42.1
A330 flight deck layoutGeneral provisions As the A330 is a medium long-range aircraft thecockpit offers full provision for a 3rd occupant seat aswell as a folding 4th occupant seat.First officer's sidestickCaptain's sidestickSliding window(Emergency evacuation)Sliding window(Emergencyevacuation)First officer'sseatCaptain's seatFirst officer'sbriefcaseCaptain'sbriefcaseThird occupantseatDocumentationstowageFourthoccupant seatCoat room/suitcasestowageRear consoleSTL 472.755/92 Issue 42.2
A330 flight deck layoutForward viewOverhead outlet Assist handle Ceiling lightSliding tablesFO boomset stowageFO boomset jack panelReading lightWindow controlhandleEscape rope stowageLoudspeakersSidestickNose wheelsteering CTLHand microphoneAshtrayChecklist stowageOxygen maskRoller sunblindOxygen maskAir conditioningoutletWaste binWaste binFlight documentsstowageSTL 472.755/92 Issue 4Checklist stowage Flash lightWindow outletsNormal checkliststorageBriefcase stowage2.3
A330 flight deck layoutRear view : right aft cornerRAIN REPELLENT BOTTLE(OPTION)OXY MASK4th OCCUPANTCONSOLEAXEOXY MASKRear view : left aft cornerLIFE VESTLIFE VESTJACK PANELHEADSETBOOMSETSTL 472.755/92 Issue 43rdOCCUPANTCONSOLE2.4
A330 flight deck layoutPilots’ field of visionVisibility Windows are designed to meet or exceed theAerospace standard. Geometry :- windshield panels : flat glass- lateral windows: curved acrylic.Pilots’ vision envelope140 130 120 110 100 90 80 70 60 50 40 30 20 10010 20 30 40 50 50 40302010Wingtipvisible0102030Aerospace standard 580 BBinocular visionPilot’s axisDownward visibility inthe pilot axis : 20 STL 472.755/92 Issue 42.5
A330 flight deck layoutPilots’ field of visionPilot’s eye position25 19 20’7ft 10.7in2.40m45ft 1.3in13.75m21ft 10.6in6.67m111 Max. aft visionwith head rotatedabout spinal column135 Pilot’s eye position115 1ft 9in0.53m62 With headmoved 5 inchesoutboard62 42 30 36 STL 472.755/92 Issue 4135 42 30 36 2.6
A330 flight deck layoutPilots’ field of vision - landingconfiguration CAT II DH 100 ft This geometry improves external aircraft monitoring,thereby increasing safety standards.- Downward visibility in the pilot axis is 20 .- Wing tips are visible from respective pilot stations.AircraftθA330-200m (ft)5 AV0RVR SVR39.7 120 150 270 273(132) (394) (493) (887) (897)A330-300 2.1 38.2 120 120 240 243m (ft)(127) (394) (394) (788) (798)2.1 pitchPilot’s eyesθ20 cockpitcut-off angleA 100ft30mSVRBCV (Visual segment)O (Obscured)RVRSTL 472.755/92 Issue 42.7
A330 flight deck layoutControl and indication panels (shaded)STL 472.755/92 Issue 42.8
A330 flight deck layoutMain features The main features are common with those developed forthe A320 and A340 families :- sidestick controllers which leave the main instrumentpanel unobstructed- six display units (DU) interchangeable, switchable andintegrated into the same system architecture(EFIS/ECAM). The other features evolve directly from the conceptsintroduced with the A300/A310 family :- ergonomic layout of panels, synoptically arrangedaccording to frequency of use (normal, abnormal,emergency) within easy reach and visibility for both crewmembers- philosophy of panels (e.g., “lights out” philosophy foroverhead panel)- principles of presentation of information (“need to know”concept)- monitoring of systems through an Electronic CentralizedAircraft Monitor (ECAM)- coherent system of colour coding for EFIS, ECAM andpanel lights.STL 472.755/92 Issue 42.9
A330 flight deck layoutSidestick arrangement Sidesicks are installed on the Captain’s and FirstOfficer’s forward lateral consoles. A dual pivot adjustable armrest behind each sidestick tofacilitate control is fitted on each seat, with positionindicators.Pitch adjustmentPosition indicatorThe handgrip includes two switches :- A/P disconnect/sidestick priority push-button- Push-to-talk buttonNeutralRadioTake-over PB(A/P disconnection or take-overfrom opposite sidestick)STL 472.755/92 Issue 42.10
A330 flight deck layoutSidestick operation Moving the sidestick results in “setting the aircrafttrajectory” with a certain level of “g” for the requestedmanoeuvre depending on the amount of sidestickmovement. Control of the flight path is performed by the ElectronicFlight Control System(EFCS) which links thetrajectory order with aerodynamic data to stabilize theaircraft and protect it from prohibited attitudes. Accuracy of movements is very precise sincebacklash and friction are negligible.Sidestick released :return to neutral10101010STL 472.755/92 Issue 41010101010101010Sidestick released :return to neutral101010102.11
A330 flight deck layoutMain instrument panelsSTL 472.755/92 Issue 42.12
A330 flight deck layoutCaptain and First Officer panels The CAPT and F/O panels are mirror images of eachother :both incorporate two side-by-side Display Units (DUs)(7.25 in x 7.25 in) :. a Primary Flight Display (PFD). a Navigation Display (ND). This arrangement provides :- better visibility on all DUs in normal configuration and incase of reconfiguration (PFD ND or ECAM ND)- the option to install a sliding table and a footrest in frontof each pilot. The PFD includes the complete Basic T with :- attitude- airspeed/Mach (with all upper and lower limits)- altitude/vertical speed- heading- AFS status- ILS deviation/marker- radio altitude. The ROSE mode (ILS, VOR or NAV) : aircraft symbol inscreen centre, with radar availability- ARC mode : heading up, horizon limited to a 90 forward sector, with radar availability- PLAN mode : north up, display centered on selectedwaypoint. Engine display : in case of a total DMC/ECAM failure,each pilot may display the ENG STBY page on his ND.Note : In ROSE-NAV, ARC, and PLAN modes, MAP datafrom FMS is presented.STL 472.755/92 Issue 42.13
A330 flight deck layoutSTL 472.755/92 Issue 42.14
A330 flight deck layoutMain centre panelThe centre panel groups :- two DUs, one above the other, whichinterchangeable with the CAPT and F/O DUs :are Engine Display (DU 1), showing :- the main engine parameters (N1, EGT, N2 for GEengines ;EPR, EGT, N1, N2 for PW engines ; (EPR, TGT, N1,N3 for RR engines)- N1 (EPR) limit, N1 (EPR) command- total fuel- the flaps and slats position- memo and warning System Display (DU 2) showing :- an aircraft system synoptic diagrams page- or the aircraft status (list of all operationally significantitems)- standby instruments- landing gear control and indications (including brakes)- clock.STL 472.755/92 Issue 42.15
A330 flight deck layoutGlareshield The Flight Control Unit (FCU) provides short-terminterface between the Flight Management andGuidance Computer (FMGC) and crew for :- engagement of A/P, A/THR- selection of required guidance modes- manual selection of flight parameters SPD, MACH,ALT, V/SPD, HDG or track.STL 472.755/92 Issue 4 The EFIS control panels for :- selection of desired ND modes (ROSE-ILS, -VOR, NAV, ARC, PLAN, ENG) and ranges- selection of baro settings. The master warning, master caution, autoland andsidestick priority lights.2.16
A330 flight deck layoutSwitching controlpanelCentral pedestalIn addition to the thrust levers and the engine controlfunctions, the main features on the pedestal are :- the Multipurpose Control and Display Units (MCDU) forflight management functions and various other functionssuch as data link, maintenance, etc.- the Radio Management Panels (RMP) for tuning allradio communications and the radio navigation as aback-up to the normal operation through the FlightManagement and Guidance Computers (FMGC).MultipurposeCDUECAMcontrol sRadiomanagementpanelAudio controlpanelFlood ACMS DFDRlight print eventLightingcontrol panel- the electrical rudder trim- the parking brake controlAudio controlpanelWeatherRadarEngine masterATCTCASEngine start- the speedbrake and flap control levers.SpeedbrakeFlaps/slatsParking brakeMultipurposeCDUMultipurposeprinterSpaceRudder trim panelHandsetSTL 472.755/92 Issue 42.17
A330 flight deck layoutOverhead panel The overhead panel has a “single slope”. All controls on the overhead panel can be reached by ight Two main zones are separated by protective padding.- Forward zone :- for most frequently used functions- for system controls : arranged in three main rows :- centre row for engine-related systems arranged in alogical way- lateral rows for other systems.ReadinglightMaintenance panelSpaceLightSpaceCVR panelADIRS- Aft zone, not used in flight, mainly for a smallmaintenance panel corresponding to some maintenancecontrols. The push-button philosophy is identical to that alreadyapplied on existing Airbus aircraft.ResetpanelEngine FireAudio controlpanelAPU FireHydraulic powerFlight controlFuelRadio managtpanelFlight controlFuelEVACCargoair cond.ElectricsEmer elecGPWSCargo smokeRCDR OxygenAir conditioningVentilationCallsAnti iceRain WiperRPLNTSTL 472.755/92 Issue 4EXTlightingCabin pressAPUInteriorlightingEngine startWiperRainRPLNTSigns2.18
3. Electrical systemSTL 472.755/92 Issue 43.1
A330 electrical systemElectrical power generationThe electrical power generation comprises : Two engine-driven AC generators, nominal power 115kVA One auxiliary power unit (APU) AC generator nominal115 kVA One emergency generator (Constant Speed Motor/Generator or CSM/G), nominal power 8.6 kVA,hydraulically driven by the Green system. One static inverter fed by two batteries and workingeither on the ground or when CSM/G inoperative. Two ground connectors, power 90 kVA DC network supplied via two main TransformerRectifier Units (200 A) and one essential (100 A).A fourth TR (100 A) is dedicated to APU start or APUbattery charging. Three batteries nominal capacity 37 Ah, 28 V each :- Two batteries used :. in emergency configuration to feed some equipmentduring RAT deployment or when CSM/G notoperating. On ground to provide an autonomous source.- One dedicated to APU startSTL 472.755/92 Issue 43.2
A330 electrical systemDistribution - normal configurationAC distribution networkELECDCBAT 125 V5A In normal configuration, each engine-driven generator suppliesits associated AC BUS. The AC ESS BUS is normally supplied from AC BUS 1.DC BATDC 1DC APUBAT 226 V0ADC ESSAPU BAT25 V5ADC 2STATINVDC distribution network In normal configuration, normal DC systems are split into twonetworks : DC BUS 1 in parallel with DC BAT BUS and DCBUS 2.TR 128 V50 AESS TR28 V50 ATR 228 V50 AAPU TR25 V100 AAC1AC1AC2AC2 Each DC network is supplied by its own TR. More specifically, ESS TR systematically feeds DC ESS BUS,which allows a better segregation between DC 1 and DC 2. Two batteries are connected to the DC BAT BUS via theBattery Charge Limiter (BCL). Each battery has its own HOT BUS bar (engine/APU fire squib,ADIRS, CIDS, PRIM and SEC computers, slide warnings,parking brake, etc). The third battery is dedicated to APU starting.STL 472.755/92 Issue 43.3
A330 electrical systemDistribution - abnormal configurationsELECDCBAT 125 V0A- if one generator fails, another will automatically take over :DC APUDC BATGenerator failureBAT 226 V0AAPU BAT25 V0A if APU operative, APU generator will take overDC 1 if APU generator not available, the other engine generatorwill take over.- In case of total loss of all main generators : the EMER GEN will deliver 8.6 kVA since the Greenhydraulic system is still powered by engine-driven pumpsor- In case of loss of all engines : the EMER GEN will deliver 3.5 kVA since the Greenhydraulic system is then powered by the RAT ; in thiscase the batteries take over when slats are extended.DC ESSDC 2SHEDLND RCVRYTR 10V0AESS TR0V100 ATR 20V0AAPU TR0V0AAC1EMER GENAC2AC2TOTALLOSS OFALL MAINGENTR failure- if one TR fails, the other will automatically take over itscorresponding DC network via DC BAT BUS,- In case of double TR failure : TR 1 and 2 : DC BUS 1 and DC BUS 2 are lost TR 1 (or 2) and ESS TR : The remaining TR suppliesDC BUS 1 2 and DC BAT BUS ; the DC ESS BUS islost.STL 472.755/92 Issue 43.4
A330 electrical systemControl and displayOverhead panelBAT12APUEMER ELEC PWREMER GEN TESTMAN ONLANDRECOVERY26.8 vBAT1BAT2 APU BATFAULTFAULTFAULTOFF/ROFF/ROFF/RGALLEY COMMERCIALAC ESS FEEDOFFAC ESS BUSONAUTOOFFFAULTEMER GENFAULTFAULTAUTOELECOFFIDGALTNBUS TIEAC BUS 1APU GEN1GENFAULTFAULTOFFOFF/RFAULTOFFELECAC BUS 2AUTOEXT BEXT AAVAILAVAILAUTOONIDG 2GENFAULTFAULTOFFOFF/RECAMELECDCDC BATBAT 125 V5ADC 1DC APUBAT 226 V0ADC ESSAPU BAT25 V5ADC 2STATINVSTL 472.755/92 Issue 4TR 128 V50 AESS TR28 V50 ATR 228 V50 AAPU TR25 V100 AAC1AC1AC2AC23.5
A330 electrical systemCircuit - breaker monitoring Circuit-breakers are installed in the avionics bay areabelow the cockpit. Circuit-breakers are monitored by the CBMU (CircuitBreaker Monitoring Units) which output the identificationand status of each circuit-breaker. A specific C/B page is provided on the ECAM. Computer resets can be performed via system controls.STL 472.755/92 Issue 4C/BECMU1 VOLT SNSG .SFCC1 NORM DCBUS AVAI .HYD PUMP G ENG2 .ANTI ICE ENG2 .DU SWTG CAPT ND .HYD PUMP B ENG1 .ADIRU1 155VAC ANTI ICE PITOT 1 OR 3 .303PP .BUS 1/3 TIE CNTOR .ANTI ICE 1 OR 3 PHC .EXTRACT FAN AVNCS .ADIRU1 AOA1 26VAC .APU TR .SWTG FUEL BUS .AUDIO ACP CAPT .AIR BLEED VLV ENG2 .XFEED VLV ENG1 MOT1-2 5FP13PU38PR4RN13HA240E13.6
4. Hydraulic systemSTL 472.755/92 Issue 44.1
A330 hydraulic systemArchitecture*STL 472.755/92 Issue 44.2
A330 hydraulic systemGeneral Three fully independent systems : Green, Blue, Yellow(nominal pressure at 3000 psi). Normal operation :- four engine-driven pumps, two of which are for theGreen system- three electrical pumps that can act automatically as backupThey are managed by the HSMU (Hydraulic SystemMonitoring Unit) which ensures all autofunctions (electricalpumps, RAT, monitoring, etc) ; manual override isavailable on the overhead panel. Abnormal operation :- in the event of one engine failure, the Greenelectrical pump runs automatically for 25 secondswhen landing gear lever is selected up.- in the event of engine 2 failure, the Yellow electricalpump runs automatically when flaps are notretracted.- In the event of both engine failure, RAT deploymentwill be automatically controlled by the HSMU topressurize the Green system.HYD- one handpump on the Yellow system for cargo doorsoperation when no electrical power is available.GREEN3000BLUE3000 2LO AIRPRESSOVHTSTL 472.755/92 Issue 44.3
STL 472.755/92 Issue 4
5. Flight controlsSTL 472.755/92 Issue 45.1
A330 flight controls - EFCSElectronic Flight Control System (EFCS)Surfaces : all hydraulically activated all electrically controlled mechanical back-up control :- rudder- Trimmable Horizontal sSTL 472.755/92 Issue 4TrimmableHorizontalStabiliser (THS)5.2
A330 flight controls - EFCSGeneralThe A330 fly-by-wire system is being designed to makethis new aircraft more cost effective, safer and morepleasant to fly, and more comfortable to travel in thanconventional aircraft.Basic principles A330 flight control surfaces are all :- electrically controlled- hydraulically activated Stabilizer and rudder can be mechanically controlled. Sidesticks are used to fly the aircraft in pitch and roll(and indirectly through turn coordination, in yaw). Pilot inputs are interpreted by the EFCS computers formoving the flying controls as necessary to achieve thedesired pilot commands. Regardless of pilot inputs, the computers will prevent :- excessive maneuvres- exceedance of the safe flight envelope.STL 472.755/92 Issue 45.3
A330 flight controls - EFCSComputersElectrical control of the main surfaces is achieved by twotypes of computers : three flight control primary computers (PRIM) which canprocess all three types of control laws (Normal,Alternate, Direct) two flight control secondary computers (SEC) which canprocess the Direct Control Law.These computers perform additional functions including : speebrakes and ground spoiler command characteristic speed computation (PRIM only).High-lift devices are commanded by two Slat/Flap ControlComputers (SFCC).The SFCCs also command the aileron droop via theprimary or secondary computers.In order to provide all required monitoring information tothe crew and to the Central Maintenance System (CMS),two Flight Control Data Concentrators (FCDC) acquire theoutputs from the various computers to be sent to theECAM and Flight Data Interface Unit (FDIU). These twoFCDCs ensure the electrical isolation of the flight controlcomputers from the other systems.STL 472.755/92 Issue 45.4
A330 flight controls - EFCSPower sourcesElectrical power supplyThe flight control computers (primary, secondary and FlightControl Data Concentrator) are fed by various DC busbars.This ensures that at least two flight control computers arepowered in the event of major electrical power losses such as- failure of two main systems or- electrical emergency configuration (CSM-G) or- battery-only supply.NormalACEmergencyDCPrimary 1Primary 2XPrimary 3XSecondary 1Secondary 2XSTL 472.755/92 Issue 4DC ESSHOTXX(BACK UP)XX(BACK UP)X(BACK UP)X(SHED)FCDC 1FCDC 2AC ESSX5.5
A330 flight controls - EFCSPower sourcesHydraulic power supplyThree hydraulic circuits (Green, Yellow, Blue) power theflight controls.System circuitPower sourceGreen2 engine (N 1 and 2) - driven pumps1 electropump1 RATYellow1 engine (N 2) - driven pump1 electropumpBlue1 engine (N 1) - driven pump1 electopumpThe distribution to the various control surfaces is designedto cover multiple failure cases.STL 472.755/92 Issue 45.6
A330 flight controls - EFCSSafety objectivesSafeguards were designed for protection against :Loss of pitch control- extremely improbable ( 10-9)Loss of elevators- extremely remote ( 10-7)Loss of roll control- extremely improbablePermanent loss of THS - extremely improbableRudder loss or runaway - extremely improbableIn order to satisfy these objectives, the following architectureapplies :- electrical signalling for spoilers, elevators and ailerons- electrical and mechanical signalling in parallel for rudderand THS.STL 472.755/92 Issue 45.7
A330 flight controls - EFCSDispatch objectivesThe basic objective is to allow dispatch of the aircraft with atleast one peripheral or computer failed in order to increasethe dispatch reliability without impairing flight safety.SystemsDispatch situation3 IRS2 yaw rate gyros3 PRIM2 SECMaximum 1 inoperative or “off”3 ADRMaximum 1 inoperative or “off”3 IR - 2 Nz accelerometersMaximum 1 inoperative or “off”2 FCDCMaximum 1 inoperative or “off”3 PRIM/2 SECElectro hydraulic and electro actuatorsMaximum 1 inoperative or “off”Maximum 1 inoperative if it is not connected to 2 computersNo-go items are inboard aileron, elevator and yaw damperactuators.STL 472.755/92 Issue 45.8
A330 flight controls - EFCSDesign principlesTwo types of flight control computers : PRIM (two channels with different software forcontrol/monitoring).SEC (two channels with different software forcontrol/monitoring). Each one of these computers can perform two tasks :- process orders to be sent to other computers as afunction of various inputs (sidestick, autopilot )- execute orders received from other computers so asto control their own servo-loop.The three primary or main computers (PRIM) : process all control laws (Normal, Alternate, Direct) asthe flight control orders. One of the three PRIM is selected to be the master ;it processes the orders and outputs them to the othercomputers PRIM 1, 2 and 3, SEC 1 and 2) which willthen execute them on their related servo-loop. The master checks that its orders are fulfilled bycomparing them with feedback received ; this allowsself-monitoring of the master which can detect amalfunction and cascade control to the nextcomputer.The two secondary computers (SEC) : are able to process direct laws only either SEC can be the master in case of loss of allprimary computers each SEC can control up to 10 servo-loopssimultaneously ; each can provide complete aircraftcontrol.Electrically controlled hydraulic servo-jacks canoperate in one of three control modes dependingupon computer status and type of control surface : Active: the servo-jack position is electricallycontrolled Damping: the servo-jack position follows thesurface movement Centering : the servo-jack position is maintainedneutral. Each PRIM is able to control up to eight servo-loopssimultaneously ; each can provide complete aircraftcontrol under normal laws.STL 472.755/92 Issue 45.9
A330 flight controls - EFCSSchematic diagramSTL 472.755/92 Issue 45.10
A330 flight controls - EFCSEFCS - Computers and actuatorsSTL 472.755/92 Issue 45.11
A330 flight controls - EFCSPitch controlSTL 472.755/92 Issue 45.12
A330 flight controls - EFCSPitch controlPitch control is provided by two elevators and the THS :- elevator deflections30 nose up - 15 nose down- THS deflections14 nose up - 2 nose down.Each elevator is actuated by two independent hydraulicservo control units ;L ELEV is driven by Green and Blue hydraulic jacksR ELEV is driven by Green and Yellow hydraulic jacksone servo control is in active mode while the other is indamping mode.In case of a failure on the active servo-jack, it reverts todamping mode while the other becomes active.In case of electrical supply failure to both servo-jacks of oneelevator, these revert to centering mode which commands a0 position of the related elevator.Autoflight orders are processed by one of the primarycomputers.Sidestick signals, in manual flight, are processed by eitherone of PRIM 1 and 2 or SEC 1 and 2The THS is driven by two hydraulic motors supplied by Blueand Yellow systems ; these motors are controlled :- either of the three electrical motors with their associatedelectronics controlled by one primary computer each- or by mechanical command from control wheels locatedon the central pedestal.The control wheels are used in case of major failure (DirectLaw or mechanical back-up) and have priority over anyother command.STL 472.755/92 Issue 45.13
A330 flight controls - EFCSRoll controlGYBG65432Aileronshyd jacksSpoilers1AutopilotcommandsSPLRS 2, 4 ,5PRIM(1) (2)(3)NORM3 PRIMFAIL123456BGGYSidestickcommandsSTL 472.755/92 Issue 4SEC(1) (2)SPLRS 3, 65.14
A330 flight controls - EFCSRoll controlRoll control is provided two ailerons and five spoilers (2 to 6) perwing :- aileron deflection is 25 - spoiler max deflection is -35 . Deflection is reduced in CONF 2and 3.Each aileron is driven by two electrically signalled servo-controlswhich are connected to :- two computers for the inboard ailerons (PRIM 1 or 2 and SEC1 or 2)- one computer for the outboard ailerons (PRIM 3, SEC 1 or 2)- one servo-control is in active mode while the other is indamping mode.In manual mode, above 190 kt the outboard ailerons arecentered to prevent any twisting moment.In AP mode or in certain failure cases the outboard ailerons areused up to 300 Kt. Each spoiler is driven by one electrohydraulic servo-control which is connected to one specificcomputer.In the event of a failure being detected on one spoiler, theopposite spoiler is retracted and maintained in a retractedposition.Autopilot orders are processed by one of the primary computers.Sidestick signals, in manual flight, are processed by either oneof the primary or secondary computers.Note : If the RAT is deployed to provide Green hydraulic power,the outboard ailerons servo-controls revert to dampingmode in order to minimize hydraulic demands.STL 472.755/92 Issue 45.15
A330 flight controls - EFCSYaw controlSTL 472.755/92 Issue 45.16
A330 flight controls - EFCSYaw controlYaw control is provided by one rudder surface :- rudder deflection 31.6 .The r
- nose gear 1050 mm x 395 mm x R16 1.5 Inner tank LH Inner tank RH Outer tank LH Outer tank RH Center tank Trim tank Total 42 000 42 000 3 650 3 650 6 230 41 560 139 090 Litres US gallons Litres US gallons 7. Fuel capacity A330-200 A330-300 41 904 41 904 3 624 3 624 6 230-97 286 11 070 11 070 957 957 1 646-25 700
HL7538 Airbus A330-200 1998-07 HL7539 Airbus A330-200 1998-08 HL7552 Airbus A330-200 1999-02 HL8211 Airbus A330-200 2010-06 HL8212 Airbus A330-200 2010-08 HL8227 Airbus A330-200 2011-01 HL8228 Airbus A330-200 2011-01 HL8276 Airbus A330-200 2013-02 HL7550 Airbus A330-300 1997-01 HL7551 Airbus A330-300 1997-04
which are 10 Airbus A320-200, 4 Airbus A321-200, 7 Airbus A330-200 and 3 Airbus A330-300. In our package you ll find the modern fleet of an: Airbus A320-200 and Airbus A321-200. To select one of these aircraft go to „Select Aircraft“. From the list „Aircraft manufacturer“ choose the entry „AIRBUS BY AEROSOFT“. TheFile Size: 1MBPage Count: 35
Airbus Commercial Aircraft Specification / Nadcap commodity Cross Table issued Januar 25, 2021 Sorted by Airbus Specification Reference Foreword: This table is given for information only and shall not be considered as a reference. It is an help for establishing the link betweeen Airbus specifications and Nadcap commodities mandated by Airbus.
such as the Boeing 737-800 or Airbus A380. This is likely to lead to an overestimate in emissions as newer, more efficient planes are not represented. 0 200 400 600 800 1000 1200 0 2000 4000 6000 8000 10000 12000 Distance flown (km) kg CO 2 per seat Airbus A310 Airbus A320 Airbus A330 Airbus A340 Boeing737-400 Boeing 747-200 Boeing 747-400 .
Abbreviation Domain Term Remarks 3D General Three Dimensional (Lat, Long, Alt) 4D General Four Dimensional (Lat, Long, Alt, Time) A None Ampere A None Alternate Lexinet - Airbus Reference Language Abbreviations (Approved and For Information) ABEC None Airbus (Beijing) Engineering Centre Company Limited ABM Non
Nadcap Subscribers {309th Maintenance Wing – Hill AFB {Aeroject Rocketdyne {Airbus Group Airbus Airbus Defence and Space Airbus Helicopters Premium Aerotec Stelia Aerospace {Air Force (WPAFB) {BAE Systems – Military Air & Information (MAI) {BAE Systems {The Boeing Company {Bombardier Inc. {COMAC (SADRI, SAMC) {Defense .
Airbus Helicopters AS350, Soloy Aviation Solutions STC Canada TCCA SR01647SE Accepted Airbus Helicopters AS350, Soloy Aviation Solutions STC European Union EASA EASA.IM.R.S.01222 Airbus Helicopters AS350, Soloy Aviation Solutions STC Brazil ANAC 2008S01-13 parts@kadexaero.com / Peterborough 1-705-742-9725 / Calgary 1-403-250-5241 / .
200/250-seaters like the Airbus A300, A310 and smaller model A330s 1,127 3,046 Larger twin-aisles like the Airbus A330-300 and A340 1,083 2,118 Very large and economical aircraft like the Airbus A3XX 360 1,235 Mainline single-aisle types like the Airbus A318, A319, A320 and A321 4,330 7,570 70- & 85-seater regional jets 437* 692* 2000 - 2009 .
