A320 Type Rating Preparation PDF

A320 Type RatingPreparation Chapter 1 AFS FMEC 1 2 Composed of FMGS Guidance System flight Management MCDU 1 MCDUZ...

A320 Type RatingPreparation Chapter 1 AFS FMEC 1 2 Composed of FMGS Guidance System flight Management MCDU 1 MCDUZ FCU Nav Info Database or m an Aircraft Performance FDS AP FEE Eda ATHR ADIRS GPS Clock INPUTS EFIS Radio Navs  FMGS Segmentation FMGS FLIGHT FLIGHT FLIGHT MANAGTIENT GUIDANCE AUGMENTATION Commands Navigation AP Flight Évelope Computation FlightPlanning AT ManeuveringSpeedComputation rutom9lands Perf Opt WindshearDetection Prediction α FloorProtection Display Management MCDU1 MCDU 1 FCU L FMGC 1 FMGC 1 V E hasten'aster's  FCU Complement When a knob engagethe selected indication you pull push a knob engage the Managed mode directed by FMGS Short term action on the FCU long term actionfor MCDO Both crosscheck withthe FMA FMA Details CAPTURE PHASE ENGAGE ARMED REMINDER mg THRUST VERTICAL HORIZONTAL APPCAPABILITY RADIO BARO Can be Combined for AUTOPILOT the common modes APP flare FLIGHT DIRECTORS ATHR ENGAGMENT STATUS AP Supplement Can be engaged above 100ft Engage on the side ofthe PF For an ILS CAT II engage both APIand 2 after Loc or APP After AP disconnect CAT 1 only API 2 disappear  When AP and FD are Off ATHR switch to SPEED mode orMACH When oneofthem is back ON again Basic Mode HDGandUS Both FD shouldbe ONor OFF at thesame time In case FPVmode revert to FDbars of GOAROUND FMposition is calculated from a mix between IRSposition Each FMGS has its own FMposition 9 11 118 ituses a MIXfrom the 3IRS ifone IRS fails itwilluse its associated IRS or IRS 3 FMGC compute GPRS positionfor each IRSbutonlyone is selected ifone doesn't comply with integritycriteria REJECTED GPS andRadioposupdated isused BIAS is a vector between GIRS and MIX IRS if one is lost BIAS is memorized andadded to theMIX IRS to compute FMposition Position accuracy crosscheck using raw data has to be done During flight unless GPS is primary when GPS primary lost msgcomes up when NAVACCURACYDOWNGRADE comes EPE RNP up to do so compare computed data BRGDIST on theMCDO with the raw data corner the ND of Monitor theTOWPT caner oftheND withnext WPT inFPL keep FPL Discontinuity onlywhen desired Anticipate actions on MCDU Predictions Rules for fuel time speed predictions FMS assumes that the aircraftflies alongtrackin Manage if another mode is selected the FMSconsidertheshortest realistic route to gobackon track NAVmode intercept when 41NMfrom route NDARC ROSE canbe used withoutany restriction if FM accuracy is negative use rawdata VOR onND When NAV is engaged monitorND engaged monitor altitude aimed speed and pseudo WPT onND when DES CLB in EOD ms 1 AP and ATHR relation SPEED mode when are engaged which means ATHR MACH YE adjust thrust to acheive a speed FINAL APP THRCLIMBmode when CLB is engaged which means speed target FENGES is acheive adjuting pitch FITFEE SRS CLB is always associated with ALTmode that's why it switches from THR CLB to SPEED SRS speed reference system is a vertical mode to maintain V2 10kt or V2 in case of en ENG FAILUREup to ACC ALT NAV activate at 30ft when a FPL isinserted  APPROACHES 20CandGS can be armed with APPR when ILS and RA are not faulty Is ffq and course are set identically on both receivers In case of ILS ground transmitterfailure APFDremainsin LOC FD Loc and GS deviation are lost and FDbarsflash In case of dual receiver failure LOC GS HDG US APturn off and Its scales are removed CANCEL APP or land if runway is in sight Below 400Ft and if LOL and GS are engaged it switches to LAND can onlybe desengaged by a GA Below 30ft FLARE AUTOLAND triggered below 200ft if_both APs trip off excess deviation in LOC 15ft excess deviation in Is 100ft LOCsignallost above 15ft GISsignal lost above 100ft difference between both RA occurs In case of NPA AP disconnect when400ft MDH a MDA 50 ft is reached or AGL when no MDAH is set If ACCURACY is low you must fly NPA USHDG or TRACK FPA In case of NPA push APPR arm FINALandAPPNAU if USHDGTRKFPA APP NAV if NAV was engage clear WPT that don't belong to the APP FINAL APP when on the decent profile disengage if LOC TRK or FPA selected Raw data VOR ADF must be displayed on ND to crosscheck  PROTECTIONS In caseof ENG failure with AP Auto Yaw compensation in all modes acheive by FAC your damper at to and GA auto rudder trim in all modes AP FD SRS pitch mode automatically adjust the reference target guidance speed LOWSPEED PROTECTION ATHR SPEED mode LOWENERGY WARNING α FLOOR protection WINDSHEAR protection ifselected speed is below VLs ATHR will not allow speed to decrease below if'speed dropsbelow aural warning SPEEDSPEEDSPEED turbulence shear ATHROFF AnENERGY LEVEL is computed bytheFACtaking into account horizontal deceleration and flightpathangle Thiswarning is triggered between 100 ft and 2000ft RA and in conf2,3FULL and justbefore floor detection It is inhibited by GPWS ALT law DIRECTlaw both RA fail If drop continues AoA increases threshold A FLOOR engage inhibit LOW ENERGY warning processed by FAC ATHR commands FULLTHRUST if ATHR was OFF turn ON automatically α Floor available from lift off to 100ftRA Floor lost in case some failures or ATHR disconnect pressed for more than 15s of also in engine out when stats flaps are extended in case of alternate or direct law when exiting floor TOGA LK mode need to turnOFF ATHR to control You can reengage it you  g g WINDSHEAR FAC redwindshear message for 15s.on bothPFDs with aural alert available from 3s after lift off to 1300ft on to From 1300Ft to 50ft on LDG with at least CONF FMGL provides TO and GA APFD in SRS mode command pitch UP to ensure a positive ROC even if speed drops In APP GSminifunction managed target speed is adjusted for wind correctionforsafegroundspeed if AoA gets tohigh Flybywire proletiondisengage APand Flybywireprotection assistpilottobestreact REVERSION NODE Allow comprehensive autoflight behavior when pilotmodifies FCU in caseofloss NAVmode Happen Ensure of a flight envelope limitspeed protection When approaching a desired flight level if pilotselect another FL US engage with the currentVSdisplayed the thepilotdecide to PULL OPENCLB orDES or US onlythen ALTmodeATC engages In case of late clearance for example NAVMODELOSS Switching from NAV to HDG will also switch CLBto OPENCLB aircraftpitch behavior is unchanged HDG willalso switch DES to Switching from NAV to USand SPEED aircraftpitch behavior is unchanged due to FPL discontinuity may be loss of NAVmode FDnot Followed Both FDs disengage when speed Vis 2kts in MAN and Us 2kt 19kts when speedbrakes are extended ATHR switch to SPEED to reach target speed Both FDs disengage when speed Vmax 4kt VFE Vie Uno ATHRswitch to SPEED to reach target speed CMF Notes Buttons philosophy Normal indication Temporary NormalOperation Maintenance information Abnormal switch position TESTResult White Failure caution Does not callforimmediate action Failure Requires immediate action MaxSpeed Cockpit Window 200bts CabinCrews can unlockthe door with code If power to thedoor fails it UNLOCK automatically There is an emergency in case pilots don'treply code green unlockedfrom cockpit or followingemergencycode alarm inthe cockpit flasing green emergencyrequest to enterfrom pilots red locked deny UNLOCK keep pushed until crewenter NORM allow crew to accesswith request a emergency access LOCK inhibitthe keypad and keepdoor locked When OPEN flasks emergency request has been made and will automatically unlock after 15 to 120 secondsif pilotdoesn'tdeny Cargo door is powered bythe yellow hydraulic system If it fails there is a manual pump to open it Ecom indication in case one door is open with one engine running Lights In electrical emergency if dome is in bright or dim onlythe right one illumina When landinglights are extended LDGLT isvisible on theECAM If strobe lights are Off in flight STROBE IT off on the ECAM If ENG are Off on the ground EMER LT are powered byfour EMERPOWER SUPPLY No smoking AUTO Off when landing gear is up Always ON forNonSmokingAirera ONwhen landing gear is down In caseofdepressurisation seatbelt on Automatically FIETIES APU Canbeused during TO to provide AC when optimum perf is required In flight backupelec sys bleed air forAC Assits ENG restart APUMaster elec powersupply Protectivefeatures start Shutdown sequences ELAMAPUdisplay automatically providedbytank pumps leftside Fuel pressure is F tankspump are OFF APUuses its ownfuelpump Fuel supply shut Off if APUmaster off APUfire is pushed APU shutoff on extpanelpushed Autoshutdowncausedbyfault APUbleed has priority over engine bleed and is AUTO it opens APU bleed value Pneumatic crossbleedvalue sys ClosesENG bleedvalue ECB electronic ControlBox regulates APUspeed at 100 Reduce to 99 1 when ACdemandand tempconditions are between 18C and35C Highest EGTMAX forstart 1090 C 11202 Amber MAX 33C Abu35000ft Highest operatingEGT Max 6751 Lowoilpress APU allowed for 10 APU Limitations Eles power up to aircraftMAXaltitude GroundOperation to 14000 up 15000ft ft Two Pack to upto One Pack 22500ft up 3 start cycle 60min cooling NMAX 1071 Autoshutdown WingAnti ice notpermittedfor Apubleed Electrical System 1151200V at 400Hz At phases 3 78dthatgetiiiai.fr 1 Emergency AC generators RAT External power DCPower Essential TR powerthe essential DCsys from the emergency gun in case of of failure threemaingenor TRT 2 IF ZENG APU driven AC genfail RAT emergency generator supplypartof AC DC sys Priorities 1 ENG generators 2 External Power GPU 3 APU 4 Emergency gen 5 DC batteries Engine drivengenerators CONTROLLEDand MONITORED Generator ControlUnit GCU APUandGPU CONTROLLED by GroundandAuxiliaryPowerUnit GAPCV  Bs GREENTriggerECAM BLACK not monitored REDCops Reset bymaintenanceonly 2 Integrated Drive Generators IDGs provide constant speed to the generators 90KVAeach 115VAC supplynormal dec components 200VAC supply higherloads hydraulicpumps APUcontrol logic prioritizeElec sys overpneumatics Each Genhas GCU Controls gen output Controls priority Protectiongen network ofgenand Supplies indicationsand warnings GAPCU Allabove Controlsexternal power contactor GENLimits When provides a NoBreakPower Transfer req Load 100 ECAM green line close Voltage 110V 120 NO line open Freq 390Hz 410 GEN1 2 OFF generator is de energized FAULT GCUdetects fault GLCopen when GEN is ON FAYE IDG outlet oiloverheat IDG oil pressure is low Disconnect mustbe held for more than 3s Reconnected by maintenanceonly Disconnect onlywhenthe engine is rotating Damages AMBER IDG over 185 c flashgreen between147C and 185 c  g if both ACBUS fail EMER GEN will automatically enable afterRATextends The RATprovides blue sys hydraulic pressure that drives an emergencygenerator if RATstalls or GS C 100kts emergency generator willno longer provideeles BATTERIES and staticinverter for AC and DC essBUS RATextension 8s ALBUS I poweredby GENI provides TRI and AC ESS BUS ACBUS 2 powered by GEN 2 provides TRZ and AC GND FLIGHTBUS ENG running APO IBus tie contactor to allowAPU to feed non powered ACBUS 1 A II II ACBUSI Fail ACESSBUS supplied by ACBUSZ ACESS FEED AUTO switch to ACBUS2 supply via ACESS FEED ACBUSFEED FAULT if not supplied by electricity ACESSSHEDBus sheds automatically when only on the batteries Main galleys shed when I GEN is lost when  Eimeria f wikipedia.org Ii t.ae DC BATBUS for APU starting 0 Battery charging of ACBUSI and 2 when Loss look 1 o of f only sourceavailable is BAT and speed 50kt STATIC INVERTER will transfer from DC to AC Below 50kt ACESS Bus shed Loss of all displays DCbus are supplied by TR DL BATBUS supplies DCESSBUS chargesbatteries if req DCBAT if voltage 25V ENER GEN can supply DCESS BUS viaESSTR Powerplant Pylont IEEE Primary Nozzle thytheverser AirIntake copy Combustion chamber 20Nozzles 2 igniters Accessory GearBox drivenbyNzrotor provides power to hydraulicpumps  fuel pump IEEE alternator starter Drain Mast collect carry wastefluids vapours FADECmanages engine thrust controls start sequence engine limit Protection ENG MAN START Manual starts Dry Cranking ENG ADIRS Sensors G MANSTART ENG COOLINGSTABCTR STERENGSTART IGN SYS sys Controller EN FUEL RETURNVALVE A START VALVE THRUST REVERSERSys ELAM Maintain Ni FMGS Limit acceleration deceleration Autothrust Avoidenginestall Flameon Linnitman N N2 Maintain airbledpress req 2 channels of FADEC Iused I backup FLX value not entered on TO THR LVR on FLX willproduce MCT AutoStart Monitor Ni NzEGT FF FADEC can abort or recycle an enginestart It alsomonitorthemanualstart seq Aircraftpower FADEC is supplied for5min to perform a selftest shutdown when IGN START up byElecSys FADEC supplied When Nz 12 FADEC supplied by its own EleaAlternator mounted ongearbox ACBUS Sys Thrustlevernotaligned MSGASYM or LVRASTM willapear on the FMA  FADEC adjusts fuelFlow Thrust lever act as thrust limiter THR LK message when ATAR is disconnected AUTO or with disconnectbutton on FCU itslocked at its currentsetting untilpilotmovesit out CL detente of N rating limit display on upperECAM is the upperdetentepoint With ATHR active greentrend indicator appears NTREND Engine fuel system is designed to provide fuel to engine combustion chamber IDG Coolingsystem actuator compressor flow of control rotorblade clearance sys Fuelpump assembly mounted on accessory gearbox Fuel tank LPshut offvalue LPstageofthemain fuelpump fueloilheatex HPstageofthe fuelpump Fuel divides into fitered flow servofuelheater serve values HMU unfilteredflowfor FMV HMU of HPshutoff burnerrozz of Entitled.by 0 LPe COLD HP used to 0 limitNz in caseof 8 89pass 0 overspeed pre Controlled by FAEC IDG 6 For required fuelflow Cooler we to the fuel nozzle W'Fhn fuelreturn valve closed ENGshutdown TO LDG fueltankwing 52.5C FADEC CONTROL  CLOG indicationwhen a filer is clogged ECAMENGpage GilQuantity 9 In EE Gilpressure 90psi or216ps pulsegreen 13psi RED Quantity 3quarts 5quarts pulsegreen Temperature 140 C pulsegreen EIE.EE iEEaaontntene Variable BleedValue controlled by FADEC At low ENGRPM ENGSTART FAST ACCELERATION To deployed REVERSE Thrustlever signal TLA left right main gear compressed fromLGCIU Spoiler Elevator SEC Thrust lever FADEC HCV Doors Reverse Indication Amber In transit Green Open FADEC Restow protection IDLE protectionfunction Auto IGNITIONSYSTEM Controlled 115V AC to highvoltageenergy by FADEC 2 igniterboxesperengine AutoSTART OneIgnited ON when Nz 16 OFF when Nz 50 if it fails FADEC uses 2 igniters ManualStart Bothigniters ONwhen MASTER switchON OFF when Nz 50 ENG MODE NORM Provide Continious Ignition ONwith ENG Flame out EIUFailure ENGMODEselector IGN START Ignition AUTOturn offby FADEC 501 Nz ifwe want continious ignition BACKNORM THENIGNSTART LP Fuel value opens startvalueopens Nz oil oress 1 I fd.IE jeopens 1151inflight StartFaults Fault messages to ECAM MASTER CAUTION FAULT light ENG panel lightson Controlled by FADEC AUTOstart aborded due to E.ggIcA 4EHI ndRaIticipatemarginalstartpress USEMANUALSTART Withselectorset to CRANK MANSTARTON weengagethestarter todrycrank DONOT reengagethe startle when Nz 720 DRY CRANKING PROCEDURE stops when MANSTARTOFF DryCrankingwhen MANSTART is aborted Uses EGTLimits 5min 10min ENGfailure TYGA I 9,5 FART I  alternative hi Ti aI n stasis BLEED PRESS 21Psi when Nz 10 STARTER LIMITATIONS 4 consecutive cycles 12min 20s betweencycles to allowfor starterlab Cool 15min after 4 consecutive cycles DON'TENGAGE STARTERWHEN Nz 20 MAX REVERSE 70kts Beforetake off select IGN start when HeavyRain Runway contaminated Severe turbulence Fuel System A320fuelsystem cools the IDG exchanger fuel storage TOTAL 19004kg 5573 6476 5573 transfervalue Controlled FLSWs 69 691 by 1 111 opens AUTO when INNER 750 kg Vent tanks 190L BLEEDAIR System operation is AUTO IAS Cord service air system ILS InertGas Gen System Center tankwithoxygendepleted air FRU return fuel 100c FRV closes if fuel temp 52.5C high FF demand from ENG gravity feedonly wingtank kg 300 fuel in vent tank if pump overheat 175C stopsandmustbe replaced Center tank pumps run 2min afterENGstart slatsretracted 500kg usedfromwingstank 5min after centertank empty With IDG recirculation wing tank can overfill stopsthe center tank until 500kg in wingtanks RESTART FUSED auto reset during ENG START In case offuelpump fail in wing tank suctionvalue feed bygravity NO SUCTION VALVES IN CENTER TANKS APU fuel pump autostart when APUMASTERON TANKPUMPOFF APULP VALUE CONTROLLED BY APUMASTER APUFIRE pb APOshut off FOI fuelquantity indicatorsystem fuelquantityprobes dual channel Effusions tanks FLSCU fuellevelsys computerunit openstransfer values control FRU ELAM FLSS fuel level sensing system fuel bedsensor temperature 2FISCUS 5435 FQI inaccurate 390kg to 750kg 5435 transfer values fail to open ECAN advisory 1500kgdiff if in wingsquantity higherfuellevels pulse pumpsfail or OFF Both FOB 2580KG Center transfervalues fail to open Minfuel for TO 1500kg MAX ftp.LALFYCE TANK QUANTITY MAX IMBALANCE 1500kg 4355kg 2250kg I 1 19 outer 690kg TO with center pump ON is prohibited fuel temperature IF 1 I Fuel pressure MAX fueling 50 psi MAXdefueling lipsi Donot correct fuel imbalance before ECAM advasory When turnoff FUELMODE MANUAL Fuel in wings 750kg L R WINGTK 20 LVL Fireprotection Both need to detect fire fire warning loop A B to trigger if one fail only one willtriggerthealert if both fail trigger fire warning ENG fire close LPfuelvalue close engine bleed packflowvalve  De energizegenerator Closes green yellow hydraulic shutoffvalve Arm fire extinguisher Illuminate SQUIBlights I Cuts offthe FADECpowersupply 2 Smoke detector in the FWD cargo 4 Smoke detector in the AFTcargo Dual loop systems 1 fire discharge bottle for both compartments Smokedetector default when both detector fails FAULT Autoflight flight directors ifboth FD turnedOFF withAPengaged FDbarsdisappear APremainsengaged intheactivemodes ifboth FDturnedOFF with AP OFF FDbars disappear HEY In started if one FMGC Fail the remainingone display on bothPFDS 11,11 With APPRmode engaged FDs Flash if revert to HDG US FD GS LOC Flash if signal fromILS is lost duringthe APPR AP can be engaged 5s after lift off AP is engaged ftp.theagff FD mode or When it engages When one AP is engage its associative FMGC is engaged During CAT111dual the second one take over automatically APwilldisengage if overspeed excessive AoA Bank Angle 45 push ATHR pb for 15s disconnected for entire flight THRLK flash when disconnected due to failure or ATHR FCUpb thrustlock at current position NAVmode activates at 30ftRA Manage lat mode mustbeengage before managedvert mode Aircraft speed managed in mayvary 20kts forwind correction descent ALT has priority on speed In case of ENG failure monitor speed 2min after cruise altitude SOFTALTMODE ENGAGE allowthe aircraft to deviate 50ft to maintain MACH minimisethrust variation and reduce fuel consumption 50 V CE 2 min 50 To cancel expeditemode push altitude formanaged pressing 2x the expedite doesn't disengage the mode SRS speed reference system RWY when loc is tuned for dep Avail to 30ft NAV ifNAVnot armed prior to TO engage above 30ft RWY TRK SRS mode maintain Yt.lkrent speed ENGfailure pitch limit 18 min US 120Fpm LOC mustbe captured before GS Autolandlights Flash below 200ftAGLif Both AP drop OFF LOC deviation 1 4 dot GS deviation 1 dot Loss LOC GS signal LOC GS scale flashes of RAdiff 15Ft GOAROUND if flashes or visual NO AUTOTRIM in LAND mode Flareonly with elevator ATHR reduce powerto IDLE When RETARDsound pilot must move lever to IDLE to disable the ATHR APsmustbe disconnect at the end the AUTOLAND APwillsteer back the aircraft to the centerline of Otherwise On NPA I 100ft deviation FINAL mode guide the aircraft until MAP Then US 900fpm HDG VAPP over threshold MagentaTargetspeed compensatefor wind Can differ from VAPPbutnotlower Ground speed mini function difference withtowerreportedwindand actualwine maintain constantground speed GOAROUNDmode engage SRS GATRACK mustbe at least Flaps1 on ground for 30s or in flight SRS maintain VAPP or speed aircraft if greater GATRK disengage of when selectanother mode above100ftRA Engage APafter 5s and 100ft AGL for SRS  CAT1 disengage AP at 160ft AGL NPA disengage AP at 250ftAGL APwith CLIMB CRUISE DESCENT needs 500FtAGL NAVmode GPSPRIMARY HIGH accuracy is displayed and RNPchecked APPNAVOr FINALAPP if GPSprimary available ifnottune raw data monitor CAT2 APP DA 100 Ft AGL APOFF 80FtAGL if no AUTOLAND CAT3APP visibility 75 m DA 22ftAGL if AUTOLANDwithout DAenter NO in RA Calloutat 100 Below safe landing is possible even with one failure In of CAT3 single minimum 50ft case made but deviation can occur AUTOLAND canbe CAT 2 3 MAX HW 30kt W 20kt TW 10 kt Recording and monitoring PFDI NDI S EWD s ND2 PFD2 s s s ACSYSSENSORS 1 Display Monitor Computer Drics Drills Dricz SystemData AcquisitionComputer FWCIs SDACT SDACZ Fact FlightWarning Computer n r Caution ACSYS SENSORS AC SYS SENSORS YeahEnoInsa Each DM has IEEEEither Drill usually drive both Upper andlowerECAM Cruise cruise on ANNLTEST pageonly in if on ECANpbFail prees ALL to show all pages Is internals if one ECAMFail you can display a system page by pressing thesystempb and holding it MAX3min PFD automatically transferred on ND if it fails DFDR last25hours start at firstENGstart a 5minafterelecnetwork energized stops5min after2ⁿᵈ ENGstops landing meme 2000ft Disappear 80kt 3 Failures types level 3 REDWARNING Level 2 AMBER CAUTION Level 1 AMBER CAUTION Use STS to review anything at anytime Primary Failure impact othersystem PRIMARY FAILURE Recall pb is used to show cleared failures If there is nothing upper ecamdisplays NORMAL Pressing RCL for 3s displays cleared itemsby EMERCANCELpb Yellow speed trend Speed the aircraft will reach in 10s Green Dot Best lift todrag ratio Maneuvering speed in cleanconf Also with one engine out  S speed Slat Retract on To Maneuvering speed in CONFI on APPR F Speed Flaps Retractspeedon TO Maneuvering speed in CONF2 3 onAPPR if 3 ADRs fail Backup speed scale withcolorsbased on AOA CONF RA amber 100ft above DH if NODH 400ft Navigation GPS is initialized by completion of INITA on MCDU if ItselffifthingFav ADIRS I can be recoverby selectingATT VOR DME 2 ILS RECEIVER DME PFDI NDI NDZ PFD VOR n a ILSA ILSZ NAV on RMPs gives control of radio tuning to the RMPs Selecting Both NAV mustbe selected eliminatecontrolby FRAC If Both FMAC Fail RMP1 RMP2 VORZ 9k ADFZ ILS on both TRANPONDER Saffo gpqpen.es on theground OPERATES INFLIGHT ONLY 2x RA failure AircraftFalls from NORMAL to DIRECT LAW with landing down  CAT1 ILS only APPR pb not usable PWS AUTO 1500ftRA even if weather radar is OFF Active Weather radar displays in all modes except PLAN GPWS MODE1 ROD MODE2 TERRAIN CLOSURERATE RA 30ft 2450ft MODE3 ALT LOSS TO or GA MODEL TERRAIN CLEARANCE INNOTLANDINGCONE MODES TOO FAR BELOW GLIDE SLOPE EGPWS Terrain Awareness display Terrain Clearance floor use of database Controlled GPWC by FLAP MODE when landing with flaps failed FLAM3 inhibit alert for flaps 3 landing TCAS n 9900ft 100mm 9900ft 2TCAS Antenna 1 channel computer 2 ATCTransponder TCASInterrogate Transponder reply 1 Proximate 1200ft 1 6 NM TA 40s RA no 25s Others 2700ft Traffi selector THRT TA RA only ALL 2700ft ABV 2700ft 9900ft BLW 9900ft 2700ft if intrudder has MODE C S ALTdisplays if US I 500Fpm ARROW willdisplay COMMUNICATION OR retain only last 2Hof Crewmember conversation Cockpit Aural Warnings Radio Communications PA Announcements ECT transmits on 121.5 406MHz Activates AUTO after impact or from the cockpit 243MHz ACARS com to ground via VHF SATCOM via ATSU 3VHF transceivers 3ʳᵈ for ACARS or BACKUP SELCAL Call light in AMBER flashes on the desired system Can be reset with RESETpb on the RMP RMPI RMP2 are connected to all HFVHFreceivers RMP3 is connected to RAPI RMP2 MCDU ACARS VHF3 In case ofENYERELEC RMPI is the only one usable When BOTH RNP are on the same VHFHF SEE light turnsON You can LOAD a Frg sent from CPDLC with LOADpb ON VOICEpb will inhibit the nav radio IDENTsignal allowonlyvoicereception from those stations  Radio has priority over INT OUR record last 2 of Direct Aural flight crew conversation warnings Radio communications Grew Communication PA announcements whenanyACPPAON CVRis only powered for thefirst 5minafter power supplied to AC after I eng running 5 min aftershutdown use GNDCONTROLpb to use it on theground CURERASEpb erase all coms CURTEST needs GNDCTR ON PARKBRAKEON ACARS STBY lossof communication Press ALERTpb to turn off the buzzer if ELT is unduly triggered in ARMED mode crew can RESET it withthe switch Hydraulics Each system has its own reservoir pump accumulator ELECPUMP ENGPUMP 000000 2500ps I RAT pressurize blue system at 2500psi ground turn ONelectric yellowpump ONLY CARGODOOR When works other functions are inhibitedexcept ALTBrakingand ENG2REVERSE ENG 1 PUMP FAULT Reservoir levellow Reservoir overheat Reservoir air low press Pump pressure low PTU turn ON automatically when difference is 500ps auto tested startingENG2 Flight Controls A320 flybywire electricallycontrolled hydraulically actuated 5 ground spoilers 3 speed brakes 4 Roll Spoilers 2trailing edge flaps 5 leading edge slats hmm woman 2FAC FlightAugmentation Computer 2ELAC ElevatorAileron Computer a one 3SEC Spoiler Elevate Computer Stick position indicator when LENG is running Turn OFF when airborn When 1 pilot takes control and the other add input GREENLIGHT on the one who has priority CAPT FO Elevators 2 servojacks Elevator 3modes Plaiting Follantedthinwheat Normal OPs 1 serve active 1 servo Damping Some maneuvers 2 servoactive AbnormalOP NOELEC 2 centringmode NOHYD 2 damping mode 1 fail deflectionof theother is limited Y G Fail dampingmode THS powered by 4 G 3 dec motors to hyd Priority ECAC2 ELAI SEC2 SECI Manual available if Y G hyd available if one fail operate at speed NORMAL TO RANGE 2.5 DN to 2.5 UP Ailerons Spoilers Priority ELACI ELACZ Deflected down 5 with flaps down Abnormal ifboth ELAC Fail Damping mode  SEC 3 Spoiler2 4 Et Speak3 if a SEC fail associeted spoiler Fail AUTO RETRACTED and held down ifHYD fail blown down by aerodynamism symmetric spoiler inhibited Rudder Fact YEETEtta b ÉÉÉi sacas Nofeed back for turn coordination youdamping FAC computes rudder deflection depending on the speed Rudder trim has 2 motors APON Ruddertrim switch RESET NOTACTIVE Speed Brakes Spoilers act as speedbrakes in fight Rollhas priorityand mayretract speed brakes Spoiler 2 has less deflection Speedbrakeswill notextend in CONFFULL or retract ifone speedbrake fail symmetric one is inhibited Inhibited if SECI SEE3 fault Elevator Fault Spoiler3 4willbeinhibited i IF protection Thrust above MCT 10 between retractation and extension 315kt retractation takesmore time withAPON Max deflection is reduced 12 by  All5 spoilers act as GNDSPLRS Rejected takeoff 72kt thrustIDLE SPOKERS DEPLOY Onlanding ARMEDspoilersdeploy when main gearstouch down NOTARMED spoilers deploywhenmain touchdown gears 1ENG REVERSE 1 ENG IDLE CROSSWIND spoilerspartiallyextend to help second wheel to touchdown Retract on IDLEwhen NOT ARMED or when disarm when ARMED Pitch trim compensation Pressure on stick can be released until 33 Auto pitch trim freezes Pilotmanual trim RA Padefather 28 After touchdown Autotrim reset to 0 Normal Law fasrpnt.EE displayedon ECAM if 1.7 0.7 Pitch Push stick furtherthanthe limit is useless Speed α APdisconnect when reaching prot 2Paramedbersmitrip Desaitivate a prot 8 forward a 0.5 for0.55 Below200ftless than NOSEUP Floor is also linked to ATHR to exit a pot Feedstick then TOGA LK to disconnect TOGA LK ATHROFF 111 7TOGA 1 α MAX High Speed protection Ilysm 1940 APOFF reduce NOSEDNauthority NOSEUPORDERS NOAUTOTRIM lowenergy warnings computed below 2000ft by FAC to 100RA with flaps2,3 SPEEDSPEEDSPEED Lateral Nomal law 70kt full authority 80kt depend on speed Flightmode 15 S BA MAX follow β target in case ofENGfailure Between 33 67 stick mustbeheld NOPITCHCOMPENSATION 0 FDbarsdisappear over450 BA67 2.54 With Flaps BA 60 2G MAX LAF load Allevation Function reduce wings load in turbulances deflecting rapidly ailerons Spoilers 4 5 deploy symmetrically when loadfactor differby 3G LAFinhibitedwith Flaps or slats 200kt VMO 10kts ALTERNATELAW load factor demand similar to NORMAL fewer protection Flightmode Flare modewhen gear down ONLY You Damping Function is available Nopitch attitude protection Artificial low speed protection replaces the AOAprotection α Floorprotection INOP pilot can override speed protections NOSEUP DOWN orders for speed protection If pressure is kept aircraft can stall loadfactor protection is alwaysavailable low or highspeed sometime NOT Direct law forexample 3Infantile UGdown Abnormal Attitude law Bth 1591 30 speed 440kt M91 60 90kt Autatrim inhibited pitch alternate law  Roll Direct law Mechanical You Flaps slats 2 SFCC Slats Flaps Control Computer flaps lever SFCC PCU Power controlunit 18 pressure offBrakes failure of 1 SFCC speedoperation WTB wingtip brakes block unwanted position Slats Flaps independent SFCC Monitors continuously APPU Asymmetry Position Unit FPPU Feedback Position PickoffUnit if bothSFCC detectsfailure WTBblock ECAN IPPV Indication Position PickoffUnit position of flapsshot on ELAM flapsextended ailerons 5 lock prevent slatsretraction at highAoA from 1 to 0 only flaps retract MAX ALT For flapsslats is 20 000 ft Procedures Never attempt to movethe trim wheels withoutpressure After landing slats Flapsmust stay extended in caseoficing conditions ice snow slushcontaminated landing gear 2 LGCIUS landing gear control and interface Unit controlsextension retraction supply informations to ECAN Electrically controlled hydraulically powered Geardoors operated mechanically GREEN HYD NORM BRAKES YELLOWHYD NWS ALTPARKBRAKES NWS Rudderpedals are electrically controlled byYellowsystem Powered HYD or EZEC Power lost Gravity extension Yellow HYDPRESS forParkBrakes ALTBrakingSystem LGCIU 1022 switch ateach cycle Above 260kt Safetyvalue for extension closes gear limitations Y Tintin not BSCV BrakeandSteeringControlUnit is dual channel it checks residual pressure monitor brakes temp channel changes at each DOWN LDGGEAR REJETED TO 72hts IDLE spoilers out AUTOBRK On slippery runway youmay not reach 80 NO DECEL Accumulator maintain PARKBRK for 12ᵗʰ 300C AMBER  In caseof Normal Braking systemfailure revertto Alternate Braking with SKID ABCU BSCU ANTI With hit Dottakumulator pressure ABCUI WhenGREENsystem fail preesthepedals turn the Dual Value to allow YELLOW system to take over Limitpress to 1000psi Atleast 7 fullbrake application Autobrake NOT Available Antiskid Nosewheelsteeringstillavailable ASKID NWSTRG Green system shut off Yellow systemsuppliesbrakes Askid NWSTRG deactivated Handwheels 75 RUDDER 6 80kts 130kts NWSTRG DISC MEMO when oneengine is running When weight 76000 nomore than 20kts in a turn kg Pneumatic System provide Air conditioning ENG STARTING WINGANTI ICING Water system pressurization Hydraulicreservoir pressurisation AFTFWD cargo heating 2 Bleed Monitoring Computer BMC ENG Bleed System Selects compressorstage as a source bleed of air air temperature pressure Regulate When IP is low HPvalvesopens ENG limits temperature at 200 C ENG Bleed Value opens if ENGpress 8psi APUbleed closed  Nofaultdetected ENGFIREpbswitch in ENGstartvalue closed ENGBleedpbFAULT Bleed overpressure Bleed overheat Wing pylon pneumatic leak ENGbleedvaluenot causedduring ENGstart APUBleedpb ON APU value open if speed 951 ON APUbleedvalue open when APUNormalspeed No leak detected APUBleedpb ON X Bleed value openwithAPUBleed Q OPEN Double leak detection loop in wings Single anywhereelse leakdetected FAULT Leah in wingarea FAULT on associated ENGBLEEDpb if on leftside APUBLEED FAULT External AirStart StartENG opposite ofthe ground unit side ENGBleed112 OFF XBleed if starting ENG2 First  g ENG2 BLEED ON Ground disconnected STARTOTHERENGINE ENG112BLEED ON X BLEED AUTO Pneumatic and Air Conditioning THAAR REGVALUE PREE O O p O Mix Cabin BothPACK Air PACKS failon smoke 1 1 Allowgroundextair Ram airfor outlow valypen 0 emergency 2 Air Conditioning SysControllers Sys 1 Cockpit Sys 2 FWDAFTCabine PACKS Components Air Cycle Machine Ram Air Primary HeatExchanger Main Heat Exchanger  517 r 3 4 00 0 ANY Heat Condense Extract Any Moisture drivesthe compress and coolingFan BypassValuemodulate AntiIcevalve temperature PackFlowControlvalue closes AUTO 0 airpress Pack overheat ENG start ENG firepb Ditching pb pneumatically operated electrically controlled If pack flow is not enough Zone Controller willsend demand to both EIUS Engine InterfaceUnit to increase ENGIDLE raise pressure If air cycle machine ACM fail due to compressor turbineseizure the affected pack revert to heat exchanger cooling modewith reduced flow