General Familiarization A318/A319/A320/A321 PDF

GENERAL FAMILIARIZATION A318/A319/A320/A321 A320 FAMILY - A subsonic, twin engine medium range aircraft with a narrow body and fly by wire. - Most advance aircraft in service today. - Two choices of engines (Pratt & Whitney and CFM) - NEO - New Engine Option - CEO -- Current Engi...

GENERAL FAMILIARIZATION A318/A319/A320/A321 A320 FAMILY - A subsonic, twin engine medium range aircraft with a narrow body and fly by wire. - Most advance aircraft in service today. - Two choices of engines (Pratt & Whitney and CFM) - NEO - New Engine Option - CEO -- Current Engine Option Aircraft Dimensions A320 - 37.57m (123ft 3in) with 180 seats A321 -- (+13 frames) 44.5m (146ft) with 220 seats A319 -- (-7 frames) 33.83m (111ft) with 145 seats A318 -- (-4.5 frames) 31.45m (103ft 2in) with 129 seats RANGE A320 -- MTOW 77tons RANGE 3600 Nm A318 -- MTOW 66tons RANGE 3900 Nm A319 -- MTOW 68Tons RANGE 4200Nm A321 -- MTOW 83tons RANGE 3100Nm MACH NUMBER -- 0.82 MAX OPERATING SPEED -- 350 kt Door Height A319/A320/A321 door height 11.91m 39ft 08in A318 12.93m 42ft 40in Fuselage Reference Point (X axis) A320 family - 2540mm (100in) Vertical Stabilizer (Z axis) A318 is longer than A319/A320/A321 to compensate its shorter fuselage. Horizontal Stabilizer (Y axis) From Aircraft structure line Wings The reference station is the wing reference axis that is located at 1868mm (73.54in) from the aircraft X-Axis. Cockpit - Third seat is behind the FO - 4^th^ seat is optional - 3^rd^ and 4^th^ seat is foldable Overhead Panel - Systems Control (FWD) - Circuit Breaker (AFT) Glare Shield - Flight Control Unit (FCU) - EFIS used for controlling and monitoring Auto Flight System (AFS) - Master Warning and Master Caution Main Instrument Panel - LCD - Integrated Standby Instruments Systems (ISIS), it replaces standby instrumentation standby horizon, airspeed indicator and altimeter. Cockpit Philosophy - Lights Off Philosophy (pop and lights up) - Pushbutton color philosophy (light and annunciator lights are in different colors according to their functions. Red (failure needing immediate action) Amber (Failure needing awareness but no immediate action) White (abnormal position or maintenance operation) Green (normal operation for backup system) Blue (normal operation of a temporary used system) Jacking - 3 points (1 at the nose, and 2 at the wings) - ADIRU pitch and roll indicator Towing WARNING: avoid injury or death to persons. CAUTION: avoid damage to equipment. Servicing Points - A320/A321 second potable water and draining panel Aircraft Servicing Arrangement - All ground support unit is on the right-hand side of the A/C because of the passengers. Electronic Instrument System (EIS) \- Electronic Flight Instrument System (EFIS) 4 displays (2 for each pilot) \- Electronic Centralized Aircraft Monitoring (ECAM) Electronic Centralized Aircraft Monitoring (ECAM) - Upper ECAM (Engine Warning Display) (EWD) - Lower ECAM (Systems Display) (SD) - Display Management Computers (DMCs) it supplies display on both ECAM - DMC 1 supplies both ECAM displays and DMC 2 is also a backup for ECAM displays. - Flight Warning Computers (Heart of the ECAM system) - Control panel is located at the center pedestal Electronic Flight Instrument System (EFIS) - It receives data from Air Data and Inertial Reference System (ADIRS) - DMC 1 supplies the CAPT EFIS displays, - DMC 2 supplies the F/O EFIS displays, - DMC 3 is available as a backup. Clock - System display (lower ECAM) - Clock CENTRALIZED FAULT DISPLAY SYSTEM (CFDS) - Centralized Fault Display Interface Unit (CFDIU) is memorizing all the faults - Reading or printing of the failure information is done in the cockpit with any Multipurpose Control and Display Unit (MCDU) ELOGBOOK - literally a laptop DIGITAL FLIGHT DATA RECORDING - To fulfill the mandatory requirements of crash recording, the FDIU acquires and formats various critical flight parameters and system data before supplying the Solid-State Flight Data Recorder (SSFDR). Aircraft Integrated Data System - To monitor engine condition and aircraft performance. ELECTRICAL POWER SYSTEM - There are two identical engine driven generators called Integrated Drive Generators (IDGs). They are used as the main power source to supply the A/C electrical network. Transformer Rectifier = AC -- DC Static Inverter = DC -- AC No AC bus 1, No ac bus 2, and no emer gen. Batt 1 -- AC ess bus Batt 2 -- DC ess bus The ECAM Electric System page shows all relevant data with regard to the entire A/C Electrical Power Generation and Distribution systems. 116 volts -- AC Hot bus IDG ½ 115VAC 400HZ 3 phases 90kVA APU GEN 115VAC 400HZ 3 phases 90kVA EMER GEN 115VAC 400HZ 3 phases 90kVA **Air Data / Inertial Reference System (ADIRS)** - The three ADIRUs are controlled through the single ADIRS Mode Selector Unit (MSU) installed on the overhead panel. Air Data - Pitot Probes - Static Ports - Angle of Attack Sensors - Total Air Temperature Sensors ADR (Air Data Reference) \- Supplies various air data parameters to the EFIS instruments \- Airspeed, Mach number, barometric altitude and overspeed to the (Flight Warning Computer) FWC \- TAT, Static Area Temperature, AOA to other indicators Inertial Reference System (IRS) -- Laser Gyros and Accelerometers - Altimeter - Vertical Speed - Flight Path Vector - Heading Ground Speed - Aircraft Position In case of EFIS system failures, the standby instruments can be used. \- airspeed indicator, \- altimeter, \- horizon. ISIS (Integrated Standby Instrument System) - It is installed on the instrument panel near the ECAM. It replaces the 3 conventional standby instruments. **Landing Aids** ILS and Marker System Marker Beacons Outer beacon Middle beacon Inner Beacon LS Information displayed on PFDs as 2 scales \- Horizontal scale for localizer signal \- Vertical scale for the glide slope signal ILS 1- PFD 1(CAPT) ND 2(FO) ILS 2- PFD 2(FO) ND 1(FO) **Radio Navigation** NORMAL TUNING The Flight Management and Guidance Computers (FMGCs) contain the navigation computer function that calculates the aircraft position. - MCDU Radio Nav -- Manual Tuning - Automatic Tuning -- Airline Backup Tuning Radio Management Panel (RMP) 1 and 2 are capable of tuning the down side Navigation receivers in backup mode if both FMGCs have failed or both MCDUs have failed and manual tuning is needed by the crew. - Backup -- RMP (Radio Management Panel) Enhanced Ground Proximity Warning System Launch Aural and Visual Avoidance system TCAS/T2CAS Terrain and Traffic Avoidance System. **RADIO ALTIMETER** The RAs supply accurate measurement of the A/C height above the ground during initial climb, landing and approach phases. Located at AFT Cargo Compartment Radome Wind Shear Glide Scope Weather Radar The Auto Flight System (AFS) is divided into four main parts: \- Flight Management (FM) \- Flight Guidance (FG) \- Flight Augmentation \- Fault Isolation and Detection System (FIDS) The first two functions are accomplished by the Flight Management and Guidance Computers (FMGCs). The other two functions are accomplished by the Flight Augmentation Computers (FACs). Flight Management and Guidance Computer (FMGC) Flight Management - Auto Pilot (automatic) - Flight Director (gives guidance) - Auto Thrust Sensors - FMGS - EFCS - Actuators Auto Thrust Speed or Mach Hold - speed or Mach hold (either FMGCs computed or from throttle levers position) Thrust Hold - thrust hold (either FMGS computed or from throttle lever position) Flight Augmentation Computer (FAC) - Rudder trim - Yaw Damper - Rudder Travel Limitation - Flight Envelope Protection - FIDS - The FIDS function is only active in FAC 1. FAC 1 is connected to the BITE of all the AFS computers and communicates to the Centralized Fault Display System (CFDS). FLIGHT CONTROL UNIT The FCU front face includes an AFS control panel between two EFIS control panels. EFIS DISPLAYS Four EFIS displays, i.e. two PFDs and two NDs. Flight parameters are displayed on the PFDs while the flight plan and navigation data are displayed on the NDs. PRIMARY FLIGHT DISPLAY As the main guidance instrument, the PFD displays various speeds and reference parameters used for short term flight guidance. \- the AP, FD and A/THR engagement status, \- the AP/FD and A/THR modes, \- the landing category. SIDE STICKS When the AP is engaged, the side sticks are locked in the neutral position, by solenoids. THROTTLE LEVERS The engines are manually controlled by throttle levers, which are located on the center pedestal, or automatically controlled by the A/THR system. Communication System Service interphone (ground) -- Communication at the cockpit Flight Interphone -- Capt and F/O Passenger Address -- Announcements Admin Interphone -- Crew only Solid State Cockpit Voice Recorders Records the last 2 hours of the flight crew conversations and communications and aural Warnings CIDS (cabin intercommunication data system) Two touch screen flight attendant panel Purser Station FAP (Flight Attendant Panel) -- Monitoring, Control and Testing. Area Call Panel Crew Calls (pink steady or Flashing) Passenger Call (Blue Steady) Lavatory Call (Amber Steady) Lavatory Smoke Detection (Amber flashing) Light Systems Cockpit lights Cabin lighting and signs Emergency Lighting Cargo and Service Compartment Lighting Exterior lights Taxi Turn off lights Navigation, Strobe, beacon, Wing Lights Take off and landing lights (under the wings) Structure ATA Breakdown ATA 52 Doors ATA 53 Fuselage ATA 54 Pylons ATA 56 Windows ATA 57 Wings Wing Movable Surface Five slats made of aluminum alloy In board flap and out board flap (made of CFRP) Hydraulic Power System Green 3000 psi Yellow 3000 psi Blue 3000 psi Green Hydraulic System Green is pressurized by Engine Driven Pump 1 Can transfer pressure to yellow Servicing panels are located at aft main landing gear bay (LH side) Yellow Hydraulic pump Yellow may also be pressurized by Electric Pump Yellow has an hand pump for Cargo Door Yellow is pressurized by engine Driven Pump 2 Yellow can transfer pressure to green using the PTU Servicing panels are located at aft main landing gear bay (RH side) Blue Hydraulic System Blue Hydraulic System (backup) Blue and yellow electric pump are not interchangeable Servicing panels are located at aft main landing gear bay (LH side) RAT PTU (power Transfer Unit) It transfers pressure from Yellow to green (vise versa) but not its fluid. RAT (Ram Air Turbine) - Last option - 2500 psi (Emergency) Landing Gear Main landing Gear (MLG) Nose landing Gear (NLG) Landing Gear Control and Interface Unit (LGCIU) LGCIU 1 and 2 controls the up and down sequence. OR Gate -- Either 1 or 2 computers, it will function. Braking Normal Braking System - Green hydraulic system powers the normal Braking system - Electrical Braking orders are sent by the Brake pedals to the BSCU (Braking/Steering control Unit) Alternate Braking System - Yellow Hydraulic system Powers the alternate Braking system - Alternate Braking Control Unit (ABCU) Electrically controls the alternating braking with A/SKID or without A/SKID Flight Controls - Flight Controls Flight control Surface are made of Composite Materials. PITCH - Elevator for short term - Trimmable Horizontal Stabilizer (THS) for long term ROLL - Aileron and spoilers 2 to 5 YAW - Rudder - Two sets of pedals enable the rudder mechanical control. - The rudder trim control switch operates the electrical trim actuator tomove the rudder to a new neutral position. Speed Brakes The speed brake lever controls the position of the speed brake surfaces and pre selection of the ground spoiler function. Landing -- 1-5 Roll -- 2-5 Inflight -- 2-4 Pylons forward and aft attachment fittings Mechanical Backup Rudder and THS (Trimmable Horizontal Stabilizer) Emergency Exit A318 A319 2 Emergency Exit (Left side and Right side) A19 4 emergency exits are optional A320 A321 4 Emergency Exits Passengers including crew members should exit evacuate the aircraft within 90 seconds Escape Slide and Slide Raft Escape Slide and sliding windows A320, A318, A319 escape slide is towed at the wing root compartment. A321 Fuselage A318, A319, A320 1 line of escape slide It can be manually operated A321 2 lines of escape slide Cargo Doors It is automated by Yellow Hydraulic AFT and FWD outward Right hand side Bulk Cargo doors is optional for A321 and A321 (inward) Avionics Compartment There are 4 avionics Compartment these doors are manually operated. Cockpit door Separated the cockpit from the cabin locked by cockpit door lock system (CDLS) Three mechanical latches engage in electrical release strikes actuated by solenoids. CDLS control unit on the overhead panel ATA 25 equipment and Furnishings Flight Deck Seats Not interchangeable Electrically and manually operated Cabin attendant seats Wall mounted seats, attached to the partitions or lavatory walls. Galleys Two types of galleys wet and dry Purser Station Flight attendant panel (FAP) it is used to control and programming. Area Call Panel Crew Communication (pink steady or flashing) Passenger call (Blue steady) Lavatory Call (amber Steady) Lavatory Smoke Detection (Amber Flashing) FWD and AFT cargo Compartment Basically, equipped to be loaded with bulk and loose baggage AFT and Bulk is separated via net Cabin altitude of 1400ft passenger oxygen will automatically fall. Passenger Oxygen Cannister and chemical reaction The mask is at the overhead panels Cockpit oxygen locations LH side of avionics compartment while the masks are at the side console ATA 38 Water and waste A320 water system can be serviced with or without electrical power 2 drain service panel with an overflow. Waste holding tank (aft cargo) Potable Water Tank (FWD cargo) A318, A319, A321 A/C is serviced from a water servicing panel and a single drain servicing panel. Gray Water The waste water drains system collects the waste water from the lavatory washbasins and the galley sinks. Vacuum toilet System Above 16,000 ft, the vacuum generator will not be started by the VSCF as the differential pressure is sufficient. Service panel Locations Potable water Righthand side (priority) Gray water Lefthand side ATA 28 Fuel System A318, A319, A320 The fuel tanks are integrated into the center fuselage area and the wings. 7 fuel pumps 2 inner cell leftwing 2 center tanks 2 inner cell right wing 1 APU The center tank is the first to be consumed A321 5 pumps, no outer, and no inner tanks 2 pumps on left wing and right wing 1 at the APU Refuel and defuel Service panel is at the right-hand side of the belly ATA 24 Fire Protection **Engine Fire Protection** Two identical detection loops (A and B) mounted in parallel When the FIRE P/B is released out, fuel supply, hydraulic supply, electrical power and bleed supply are cut off. This also arms the extinguishing system. To extinguish the fire, each engine is equipped with 2 fire bottles within its respective pylon. APU The detection system has two identical detection loops (A and B) mounted in parallel. Each loop has a single detector element. Both loops are monitored by a FDU. For the APU, there is just one fire extinguisher bottle. 3 ways to extinguish Auto, cockpit, outside Avionics Compartment Smoke Detection The cooling system is controlled and monitored by the Avionics Equipment Ventilation Controller (AEVC). The air is circulated through the system by a blower fan (cool air supply) working together with an extraction fan (warm air removal). The extraction airflow is downstream of the avionics equipment, so the avionics SMOKE detector is installed in the extraction duct and will detect smoke coming from the computers and control boxes. Cargo Each cargo compartment has cavities, and each cavity holds 2 smoke detectors. The cargo compartments are ventilated by an air extraction system. The cargo compartment fire extinguishing agent is discharged into the FWD compartment through one nozzle (two for the A321) or into the AFT compartment using two nozzles (three for the A321). Lavatory Smoke Each lavatory has one smoke detector. The lavatories and galleys on the aircraft are ventilated by an air extraction system. Air continuously circulates through the lavatories and is extracted out through the ceiling and across the smoke detectors. ATA 49 APU Located at the aft of the aircraft (unpressurized) It can supply electrical power, bleed air for engine starting and air conditioning on the ground Pressurization and anti-ice system on wings. Electronic Control Box - Starting - Acceleration - Speed governing - Indication - Fault monitoring - Interface with aircraft systems ECAM APU page It is displayed on the ECAM APU page. The APU generator parameters are duplicated on the ECAM ELEG page. APU generator 115 volts and 400 Hz ECB is located at the right-hand side cargo ECB manages and control of the APU Power Plant CFM56-5B - Dual Rotor, variable Stator, High Bypass Ratio Turbo fan powerplant. - Programming plug on the Electronic Control unit (ECU) - CFM56-5B is a modular concept Low Pressure Rotor (LP) (N1) - First Stage Compressor, 4 stage booster compressor, 4 stages of LP turbine Drives. High Pressure Rotor (N2) - Made up of 9 stages HP compressor - The LP shaft in inside the HP rotor Shaft - Run by HP turbine - Source of customer Bleed air - 20 fuel nozzles and 2 igniter plugs Transfer and accessory gearbox - The fuel pumps, oil pumps, hydraulic pumps, integrated drive generator and Fadec alternators are all driven by the Gearbox. APU -\> Centrifugal Clutch -\> HP Comp -\> HP tur -\> LP tur -\> Lp Comp -\> Fuel Flow -\> engine start FADEC (full authority Digital Engine Control) - Each engine is controlled by ECU, a dual channel computer is located on the engine fan case. Thrust reverser System - The spoiler Elevator Computer (SEC) opens the hydraulic shut-off valve to enable operation of the thrust. - Center pedestal ECU Located at the RHside of the fan case FADEC accessory gearbox. Dry -- right hand side Wet -- Left hand side Fuel Driven by the gear box, the filter is installed within the pump. Oil It is located at the Left-hand side of the Fan case ATA 36 Pneumatics - Air condition - Wing ice protection - Water Pressurizatio9n - Hydraulic reservoir pressurization - Engine starting 2 computers Bleed monitoring Computers (BMC) ATA 36 PNEUMATICS -airconditioning -pressurization of water system -anti icing -engine starting bleed air can be extracted from -engine (primary source) -APU AIR CYCLE MACHINE -HEART of PACK LOCATION Aft forward cargo -mixer and recirculation system Belly -Pack VENTILATION SYSTEM COMPONENT LOCATION The skin air inlet valve is located on the LH side of the fuselage. The skin air outlet valve is on the RH side of the fuselage. A small auxiliary flap will open for the intermediate circuit configuration. This is thought to be the partially open position. Both skin valves have a manual override and deactivation device there is no way to to cool cabin air but there is a way to heat it ATA 30 ICE AND RAIN PROTECTION SYSTEM located in -windshield -probes -drain mast --engine air intake -wing -the WAI(wing anti ice) can be selected on the ground but will be automatically limited to 30 seconds operation to prevent damage to the wing leading edge. WHC1 Left hand Side (captain side) WHD2 Right hand side side window/slide window- defogging only windshield window- defogging and anti icing Drain Mast -electrically heated computer related in cargo ATA 05 Time Limits and maintenance checks 2 Types of Maintenance \* Scheduled \* Unscheduled