STL 945.7136/97

1 STL and systemsbriefingfor pilotsTHIS BROCHURE IS PROVIDEDFOR INFORMATION PURPOSES ONLYAND ITS CONTENTSWILL NOT BE MUST NOT BE USED AS AN OFFICIAL TECHNICAL DATA OR OPERATIONAL PROCEDURES,PLEASE REFER TO THERELEVANT AIRBUS DOCUMENTATIONI ssue September 1998 STL deck power flight flight instrument management and centralized fault display system1 STL paxMax. 11in145180390220 STL weights (kg)Operation JetA320-111A320-211A320-212A320-214A320- 231A320-232A320-233A321-111A321-112A321- 131A321-211A321-231 CFMCFMCFMCFMCFMIAEIAEIAECFMIAECFMCFMCFMC FMIAEIAEIAECFMCFMIAECFMIAECFM56-5B5 CFM56-5B6 CFM565A4 CFM56-5A5 CFM56-5B7V2522-A5V2524-A5V2527-M-A5 CFM56-5-B6/5B7V2524-A5/V2527-M-A5 CFM56-5-A1 CFM56-5A1/5A3 CFM56-5A3 CFM56-5B4V2500-A1V2527-A5V2527E-A5 CFM56-5B1 CFM56-5B2V2530-A5 CFM56-5B3V2533-A564 000(options :68 000 or70 000)75 50068 00073 500(options : from68 000 up to77 000)83 000(options :78 000 or85 000)89 00061 00062 50063 00064 50073 500(option :74 500)75 00057 00058 00059 00060 500(option :61 000)69 500(option.)

2 70 50071 A319/A320/A321 are narrow body, twin-engined,short / medium-range aircraft, the A319 being theshortened version of the A320, and the A321 being thestretched version of the both offer an increased fuselage cross-sectionleading to an increased revenue potential through :-greater passenger comfort with wider seats andaisle-greater overhead baggage volume-greater cargo capacity-wide-body compatible container ,structure, systems andpowerplantoffer reduced coststhrough :-unmatched fuel efficiency-more accurate flight path control-reduced maintenance costs-increased reliability-reduced trouble-shooting for airline service in March 1988, the A320represents the largest single advance in civil aircrafttechnology since the introduction of the jet engine andresults in a major stride forward in airline against excursions outside the normal flightenvelope and greatly improves the man / A319/A320/A321flight deck layoutSTL flight deck plan / OsidestickF / Onav.

3 Bag3rdoccupant bag4thoccupantseat (optional)Coatstowage An observer seat aft of the pedestal offers maximumvisibility over all panels. A fourth occupant seats is offered as an / OSTL flight deck- general arrangementCeiling lightReading lightFowardviewSun visorAssist handleRope stowageAir conditioning outletRoller sunblindF / OboomsetstowageF / Oboomsetjack panelCup holderWindow control handleMiscellaneous stowageWaste stowageAir conditioning outletSidestickHand microphoneAshtrayOperational manualstowageCheck list stowageFlight documents stowageFlash lightBriefcaselightingNosewheelsteeringc tlBriefcasePortable fire extinguisherF / O quick donning oxygen mask3rdoccupant quick donning oxygen maskSTL flight deck- general arrangementRight cornerLeft cornerRear viewSecondarycircuit breakersPrimarycircuit breakersHat stowageBulbs, fuses stowageRain repellant bottleCoat stowageSeat unlock4thoccupant seat(optional)Life vestHat holderHand microphoneHeadset stowagePortableoxygen bottleFull face mask3rdoccupant seatJack panelAxeSafety lockerLife vestSTL flight deck pilot s field of viewWing tipvisibleAerospace standard 580 BA319/A320/A321 PilotaxisImproved pilot visionSTL flight deck pilot s field of viewVisibility Windows are designed to meet or exceed theAerospace standard 580 :- windshield panels:flat glass- lateral windows:curved acrylic.

4 Clear surface of each window :Windshield sliding rear deck This geometry improves external aircraft monitoring,thereby increasing safety standards :- downward visibility in the pilot axis is 20 - wing tips visible from respective pilot flight deck main featuresControl and indication panels in bold outlineSTL flight deck main features The main features :-sidestickcontrollers which leave the maininstrument panel unobstructed-six display units(DU)interchangeable,switchableand integrated 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 forboth crewmembers-philosophy of panels ( , lights out philosophyfor overhead panel)-principles of presentation on information ( need toknow concept)-monitoring of systems through an ElectronicCentralized Aircraft Monitor (ECAM)-coherent system ofcolourcoding for EFIS, ECAMand panel flight deck sidestickarrangement Sidesticksare installed on the CAPT and F / Oforward lateral consoles.

5 Anadjustable armrestto facilitate free wristmovement is fitted on each seat. Thesidestickworksagainstaspring forceproportional to the angular displacement. Sidestickincludes :-radio communication trigger-a take-over button for autopilot disconnection andpriority controlHeight adjustmentArmrest memory position displayTake-over buttonRadioNeutralSTL flight deck sidestickoperation Moving thesidestickresults in setting the aircrafttrajectory with a certain level of g for the requestedmanoeuvredepending on the amount ofsidestickmovement. Movement is very precise since back lash and frictionare negligible. Control of the flight path is performed by theElectronic Flight Control System(EFCS)which linksthe trajectory order withaerodynamicdatatostabilize the aircraft and protect it from :return to neutralSidestickpushedSidestickreleased :return to neutral10101010101010101010101010101010 STL flight deck main instruments panelsSTL flight deck CAPT and F/O panels The CAPT and F / O panels are mirror image of eachother ; both incorporate two side-by-side DisplayUnits(DU s)( x ) :-a Primary Flight Display(PFD)-a Navigation Display(ND).

6 This arrangement facilitates :-a better visibility on allDusin normal configurationand in case of reconfiguration (PFD ND or ECAMND)-The possibility to install a sliding table (option) anda footrest in front of each pilot. Primary flight displayincludes the complete BasicTwith :-attitude-airspeed / Mach (with all upper ad lower limits)-altitude / vertical speed-heading-AFS status-ILS deviation / maker-radio altitude Navigation displayoffers three modes :-ROSE mode (ILS, VOR or NAV): heading up,aircraft symbol in screencentre, with radaravailable,-ARCmode : heading up, horizon limited to a 90 forward sector, with radar available,-PLAN mode : north up, display centered onselected :In ROSE-NAV, ARC, and PLAN modes, MAPdata from FMS is flight deck centrepanelSTL flight deck centrepanelThecentrepanel groups :-twoDus, one above the other, same size andinterchangeable with the CAPT and F / ODus: Engine Display(DU 1), showing :-the main engine parameters : N1, EGT; N2 (CFM)or EPR, EGT, N1, N2 (IAE)-thrust limit and command-total fuel-the flaps and slats position-memo and warning.

7 System Display(DU 2) showing :-presentation of system synoptic diagrams-status of the aircraft (list of all operationallysignificant items)-standby instruments-landing gear control and indications (includingbrakes)-clockSTL flight deck glareshieldSTL flight deck glareshield The Flight Control Unit(FCU)provides short-terminterface between the FMGC and crew for :-engagement of A / P, FD, ATHR-selection of required guidance modes-manual selection of flight parameters SPD, MACH,ALT, VSPD, HDG or track. The EFIS control panels for :-selection of desired ND modes (ROSE-ILS,-VOR,ARC, PLAN) and ranges,-selection ofbarosetting. The master warning, master caution,autolandandsidestickpriority flight deck pedestalPitch trim wheelLanding geargravityextension handleThrust and thrustreverse control leversSTL flight deck pedestalIn addition to the thrust levers and the engine controlfunctions, the main features on the pedestal are : The Multipurpose Control and Display Units(MCDU)for flight management functions and various otherfunctions such as data link, maintenance The Radio Management Panel(RMP)for tuning of :all radio communications and the radio navigation asa back-up to the normal operation through the FlightManagement and Guidance Computers(FMGC).

8 The electrical rudder trim. A handle at the rear of the pedestal enables thegravity landing gear function, to be operated easilyand flight deck overhead panel3rdand 4thoccupantair outletsFire controlsFlight controlStandby electricsCVR microphoneAPU controlMaintenance panelPedestal light3rdaudio control3rdRMP (option)Flight controlCargo smokeOptionsInternal lights and signsCabin pressureWiperSpareSpareCircuitbreakersSp areSpareADIRSCPEVACGPWSRCDRO xygenCallsWiperEng 1 APU Eng LTSpareFMSloadCargoheatVentEngineSTL flight deck overhead panel The overhead panel is single slope and one inchhigher than on previous Airbus aircraft. All controls on the overhead panel can be reachedbyeither pilot. Two main zones are separated by protective padding :-Forward zone :-for most frequently used functions at the front ofthe panel-for system controls : arranged in three mainrows :center row for engine related systemsarranged in a logical waylateral rows for other systems-Aft zone,not used in flight, mainly :-for circuit breakers corresponding to essentialsystems necessitating segregation-for a small maintenance panel corresponding tosome systems not linked to the CentralizedFault and Display System(CFDS).

9 The push-button philosophyis identical to thatalreadyapplied on existing Airbus aircraft. STL electrical system architectureSTL electrical system architectureThe electrical power generation comprises : Twoengine-driven AC generators, nominal power90kVA One auxiliary power unit(APU) AC generatornominalpower 90kVA Oneemergency generatornominal power 5kVA,hydraulically driven by the Ram Air Turbine(RAT),automatically deployed in case of main generatorsloss Oneground connector, power 90kVA. DC network supplied via three identical Transformer /Rectifier Units(TRU):- two of them are normally used- the third is used :in emergency configuration (loss of main ACgenerators)in case of TR 1 or TR 2 failure Twobatteries, nominal capacity 23Ah each-on ground : to provide an autonomous sourcemainly for APU starting-in emergency configuration to feed someequipment :during RAT deploymentafter landing gear extension (only for A320).

10 STL normal electrical flight configurationSTL normal electrical flight configuration In normal configuration, both normal AC systems aresplit Each engine-driven generator supplies its associatedAC BUS via its Generator Line Contactor (GLC). AC ESS BUS is normally supplied from AC BUS via acontactor. DC BAT BUS and the DC ESS BUS are normallypowered by the TR 1. Two batteries are connected to the DC BAT BUS viathe Battery Charge Limiter (BCL). Each battery has its own HOT BUS bar (engine / APUfiresquib, ADIRS, CIDS, ELAC 1, SEC 1, slidewarnings, parking brake etc).STL normal electrical flight configurationLoss of main electrical generators EMER GEN runningSTL normal electrical flight configuration In case of failure, the failed generator is automaticallyreplaced by :- the APU generator if available- the other main generator with automatic partialgalley load shedding. In case of total loss of all main generators, the RAT isautomatically extended and drives the emergencygenerator via a hydraulic EMER GEN supplies the AC ESS BUS and theDC ESS BUS via the ESS ECAM WD remains powered, with associatedprocedures law is operative through ELAC 1 and SEC electrical control and displaySystem display :ELEC system pageNormal configurationControl panelBatteries indicationBuses indicationTransformer / RectifierGenerator indicationIntegrate DriveGenerator indicationsSTL cockpit circuit- breakersOverhead panelEmergency circuit breakerRear right panelSecondary circuit breakers(aircraft systems)Primary circuit breakers(electrical generation) Circuit breakers (C / Bs) are constantly monitored andthetripping of a C / B will be clearly indicated :either through-activation of a system warning-a failure test-an abnormal instrument configurationor, for C / Bs monitored by the ECAM system.