Airbus A320 Family Maintenance Notes PDF

# Airbus A320 Family Maintenance Notes ## General Family Notes - A321 and A319 are assembled in Germany at a purpose built Deutsch Airbus plant. - A321 has low cost per passenger mile. - A319 has lowest fuel consumption. - A320, A319, A321, and A318 have the same system. - A320: Added 13 frames to...

# Airbus A320 Family Maintenance Notes ## General Family Notes - A321 and A319 are assembled in Germany at a purpose built Deutsch Airbus plant. - A321 has low cost per passenger mile. - A319 has lowest fuel consumption. - A320, A319, A321, and A318 have the same system. - A320: Added 13 frames to become A321. - Subtracted 7 frames to become A319. - Subtracted 4.5 frames to become A318. - **MTOW (Maximum Takeoff Weight)** - A318: 166 tons (195,500 lbs) - A319: 148 tons (150,000 lbs) - A320: 77 tons (170,000 lbs) - A321: 83 tons (183,000 lbs) - Radom is made of Quartz Fiber Reinforced Plastic (QFRP) ## Aircraft Dimensions - X = 2.54 m, FWD NOSE (datum line) - Y = H.S, Horizontal Stabilizer - Z = V.S, Vertical Stabilizer ## Cockpit - Wing is connected to the "wing box". - Cockpit seats are not interchangeable. - 5 point seat belt. - Folded seat for 3rd or 4th occupant. - Overhead panel: - Sub panels: Systems and Circuit Breaker Panels - Glare shield Panel: - Master warning and master caution is located in the glareshield panel. - Main Instrument Panel - Electronic Flight Instrument System - Capt. (Primary Flight Display/Navigation Display) - F.O. (ND/PFD) - Electronic Centralized Aircraft Monitoring (ECAM) - Upper - Engine Warning Display (EWD) - Lower - System Display (SD) - The C6 Display is Electronic Instrument System (EIS). - Electrical lock. - Landing Gear Lever. - Integrated Stand by Instrument System (1515) - Center Pedestal: - Multi purpose control display unit (MCDU), used for troubleshooting. - Radio Management Panel (RMP) - Radio and on-board comms. - Audio Control Panel (ACP) - Thrust lever. ## Cockpit Light Philosophy - **Pressed in:** - **No light/System active/correct operation** - **Light on/System active/faulty condition** - **Released out:** - **"OFF" light on (System deactivated)** ## Light Meaning - **Red -** Failure/Needing immediate action. - **Amber -** Needing awareness but no immediate action. - **White -** Used to indicate a push button in an abnormal position or maintenance operation. - **Green -** Normal operation of a back up system. - **Blue -** Normal operation of a temporarily used system. ## Safety Warnings - **Warning -** To avoid injury or death to persons. - **Caution -** To avoid damage to equipment. - **Note -** To ease the job. ## Electronic Centralized Aircraft Monitoring (ECAM) System **Diagram:** - **ECAM** - **Capt** - **PFD/ND** - **ECAM** - **ECAM** - **F.O.** - **ND/PFD** - **Display Management Computer** - **DMC3** - **DMC2** - **Backup** - **System Data Acquisition Concentrator** - **SDAC2** - **Flight Warning Computer** - **FWC2** ## Clock System - **Clock** - **Electrical clock** - **SD** - **MMEL** - **Mam** - **A = 1 day** - **B = 3 days** - **C = 10 days** - **D = 20 days** - **MEL** - **AOL** - **CFDU** - *Centralized Fault Display Unit (Hardware)* - *FDIS System (Software)* ## Built-in Test Equipment (BITE) - MCDU can be accessed in-flight and on-ground. - Post Flight Report = Printed. - Linear accelerometer - xy, 2 axis of the aircraft. - 5 mins after the first engine start, the solid State Flight Data Recorder will start. ## Flight Data Interface and Management Unit (FDIMU) - **Data Management Unit (DMU)** - Collects data. - **Flight Data Interface Unit (FDIU)** - Sends data to SSFOR. - **DMU** is the heart of aircraft Integrated Data System (AIDS). - **AIDS** is used to monitor engine performance, all performance, and ACC condition. ## Air Data/Inertial Reference System (ADIRS) - **ADIRS** - **ADIRU (Unit)** - **ADDRU** - **Air Data Reference (ADK)** - Total Air Temp Sensor (PAT), Pitot probes, static ports, AOA. - **Inertial Reference (IR)** - **ADR** - Airspeed, Mach Number, barometric altitude, overspeed warnings, total air temp., static air temp., AOA. - **IR** - Attitude, Vertical speed, Flight path vector, Heading, Ground speed, aircraft position. ## Airborne Standby Instruments - Standby instruments include: - Standby Airspeed Indicator. - Standby Altimeter. - Standby Horizon. - **Integrated Standby Instrument System (1515)** - - An 3 standby instruments combined. ## Landing Aids - **Instrument Landing System (ILS)** - Marker beacons. - **Head-up Display (HUD)** - Is optional. ## Radio Navigation System - Tuning. - **Auto/Normal =** FMGC (Flight Management Guidance Computer). - **Manual =** MEDU. - **Backup =** RMP (Radio Management Panel). - GPS has 24 satellites. ## Traffic Collision Avoidance System (TCAS) - At least one (1) transponder operative. - **Terrain and Traffic Collision Avoidance System (TCAS).** ## Enhanced Ground Proximity Warning System (EGPWS) - **Radio Altimeter (RA)** gives the exact measurement of the A/C height. - **RA** is located in the aft cargo. ## Autoflight System (AFS) - **Flight Management and Guidance Computer (FMGC)** - **Flight Augmentation Computer (FAC)** - **Fault Isolation and Detection System (FIDS)** - Is the only that collects faults. - **Electrical Flight Control System (EFCS)** - Prevents excessive maneuvering. - Electrically controlled, hydraulically operated. - **Full Authority Digital Engine Control (FADEC)** ## Flight Management Guidance Computer (FMGC) - **Management** - Autopilot - Flight Director - Flight Director - Auto thrust - **Flight Plan** - Lateral - Vertical - **Guidance** - Holding of flight paths. - Guidance of the A/C after take off. - **Auto thrust** - Engine = FADEC - **Engine Interface Unit (EIU)** - Hydraulics - Fuel - Oil - Electronics ## Flight Augmentation - Rudder trim, yaw damper, rudder, and limitation. - Flight envelope protection. - Speed computation. - Alpha floor and wind shear protection. - Low energy awareness. - **FIDS** is only available in FACI. ## Side Sticks - Throttle levers. - **Instictive Disconnect** - Allows the autothrust to de-engaged. ## Air Traffic Information Management System (ATIMS) - **SATCOM** is optional. - Pre-Fans. - ATC and Air ground comm. ## Fans - **Fans A** - Pre-Fans and ATC FUNC. - **Fans B** - Fans A and improvement of comm. network. - **Future Air Navigation System (FANS)** - **Pre-FANS** - Does not have ATC FUNC. - **Heart of ATIMS** - ATSU (Air Traffic Service Unit). ## Communications System - **Radio Comm. Sys** - VHF Transceivers are identical and interchangeable. - VOR3 = ATSU - VDR1 and 2 = Voice Comms. - **On-board Comms.** - Cabin InterCommunication Data System (CIDS). - Is controlled by Flight Attendant Panel (FAP). - The heart of the audio Comms. is Audio Management Unit (AMU). ## Cockpit Voice Recorder (CVR) - The last 2 hours of flight is automatically recorded. - It records automatically in flight and on-ground. - When at least 1 engine is running and for 5 mins after the last engine is shut down and also 5 mins after A/C energization. ## Cabin Intercommunication Data System (CIDS) - Software - Director Land 2 (Hard wire) - FAP - Decoder/Encoder Unit (DEU A & B) - DEU A = Passenger func. - DEU B = Cabin/crew func. ## Area Call Panel (ACP) - **Pink (steady/flashing)** - Crew call. - **Blue -** Passenger call. - **Amber -** Lavatory call. - **Amber (flashing)** - Lavatory smoke. - **Vacuum System Control (VSC)** is installed to CIDS. ## Cockpit Lighting System - **Cockpit Lighting System** - Dome lights are directed to the battery (FO only). - **Cabin Lighting** - **Emergency Fout lights/Signs** can be powered by emergency power supply unit (EPSU) - **Cargo and service compartment lighting** - It automatically opens using proximity switch/sensors - **Exterior Lighting** ## Aircraft Structures - **ATA 51: Structures** - **Metallic -** Monolithic - **Composite -** Honey Comb - **ATA 52 -** Doors - **ATA 53 -** Fuselage - **ATA 54 -** Pylons - **ATA 55 -** Stabilizers - **ATA 56 -** Windows - **ATA 57 -** Wings - Forward and Aft Mount (Pylons to Engine) ## Hydraulic Power System - **ATA 29: Hydraulic Power System** - **Green Hydraulics** - Eng/APU Fire push button switch - red. - Master Warning - red. - CRC - red - FIRE - red - EWD - **Blue** - Flight Controls - Constant Speed Generator - **Yellow** - Flight Controls - Brakes - Nose wheel steer - Parking Brake - Thrust reversers 2 - RAT - Only produces 2500 PSI. - Fleс. pump - Is the main pump for BLUE SYS. - EDP - Is located at the accessory gearbox. ## Landing Gear - **ATA 32: Landing Gear ** - Main door of nose and main landing gears - Are the only hydraulically operated. ## Steering and Braking Systems - **Braking** - **Braking Steering Control Unit (BSW) -** Auto brake. - **Alternate Braking Control Unit (AB (U) -** Anti skid - **Parking Brake** - Yellow Hyd. Sys. ## Steerable Control Surfaces - **Steering** - Rudder Pedals and Autopilot = 6 degrees. - Hand wheel = 74 degrees ## Flight Controls - **ATA 27: Flight Controls** - Rudder and the trim able horizontal stabilizer only have the mechanical linkage. - **Flight Control Laws** - **Normal Law -** Provide full flight phase envelope protection (Full protection). - **Alternate Law -** Reduced protection. - **Direct Law - ** All protection is lost. ## Slat and Flap Systems - **Pressure Off Braking (POB)** locks the transmission when the slat and flap surface have reached the selected position or if hydraulic power fails. - Ground = 1-5 - Roll = 2-4 - Speed brakes = 3.5 - Spoilers ## Door Systems - **Part 2** - **ATA 52: Doors** - **Passenger Doors** - 4 passenger doors operate manually. - Opening sequence - upward, outward, then forward parallel. - (W) Steady white = Armed door. - E.R. Flashing Red = Residual Pressure. - **Emergency Exit Doors** - Off-wing Emergency Exit Doors. - A318/319/320 = 2 Emergency Exit Doors (optional additional doors). - Nitrogen bottle is located in aft cargo - A321 = 4 Emergency Exit Doors (not off wing) - Automatically Armed. - **Cargo Doors** - Forward and Aft Cargo Doors. - Bulk Cargo Doors (optional) - Hydraulically Operated (yellow Hyd. Sys.) - Forward and Aft opens outward the, upward. - Bulk opens inward. - **Avionics compartment doors ** - 4 Avionics compartment doors. - Manually operated, opens inward. - **Cockpit Door** - Armored and bullet proof - Cockpit Door Lock System (CDLS) - 3 electrical latches. - CDLS has 2 modes: - Normal Routine Access Mode. - Emergency Access Mode. ## Indicating Systems - **Control and Indicating** - Passenger doors have mechanical and electrical indicating systems. ## Airbus Equipment and Furnishing - **ATA 25: Equipment/Furnishing** - Cockpit Seats. - Passenger Seats. - Galley: - Dry = Storage - Wet = Storage & Prep. - Lavatories - Curtains & Partitions - Cabin Panel Layout: - "Dado" panel. - Lower side wall panels - Used to provide rapid decompression. - Upper side wall panels - Windows. - Love light panels. - Overhead Storage Compartment. - Passenger Service Unit (PSU) - Passenger Door & Escape slide. - Emergency Exits. - Emergency Equipment - Cockpit Emergency Equipment List. - Cabin Emergency Equipment List. - Manual Release Tool (MRT) - located in upper station ## Oxygen System - **ATA 35: Oxygen System** - Cockpit Crew Oxygen System. - N = Normal, pure O₂ & Cabin Air. - 100% = 100% Pure O₂. - Cabin Oxygen System. - Chemical O₂ generator - 12-15 mins. - Portable Oxygen Sys. ## Water and Waste System - **ATA 38: Water and Waste** - Portable water sys. - A320 - 1 Water Servicing Panel and 2 Drain Servicing Panel. - A 318/319/321 - 1 Water Servicing Panel and 1 Drain Servicing Panel. - A 320 water tank is located in forward fuselage. - A 318/319/321 = 4 - water tank is located in Aft Fuselage on waste ramp. - Water Waste Sys. - Drain Mast is electrically heated. - Vacuum Toilet System - CDLS is used for the controlling and monitoring of toilets. ## Fuel System - **ATA 28: Fuel System** - A318/319/320 = - 4 Fuel tanks (Integral Fuel tank), center & outer - 2 booster pumps (2 pumps per tank) - Center tank supplies fuel first. - Once the right and left wing reach low level, inter-call transfer valve opens. - Center tank > outer cell > inner cell (Fuel comp) - Outer cell > inner cell > Center tank (Refueling) - A321 = - 3 Fuel Tanks - 4 booster pumps - **Critical Design Configuration Control Limitations (CDCCL)** - <S VDL (Volts DC) - Required by CDCCL - Fuel pump (155V AC) ## Fire Protection - **ATA 24: Fire Protection** - Engine and APU (detection and extinguishing) - Lavatory and Cargo (smoke detection and extinguishing). - Avionics (Smoke Detection). ## Engine - **Fire Detection Unit (FDU) 1 & 2** - Loop A & B (parallel connection) - 3 Detector element (intake, pylons, and outer center wing). - 2 Fire Extinguishing bottles, located @ pylons. ## Auxiliary Power Unit (APU) - **APU Fire Detection Unit (FDU)** - Loop A&B - Fire extinguishing bottle (located behind fire wall) - Automatic extinguishing on ground (When used APU shut off) - **Avionics** - Avionics Equipment Ventilation Controller (AEVC) - **Cargo** - CIDS - smoke detection function (CIDS - SDF) - **Lavatory** - CIDS - SDF - Automatic fire extinguishing (77 °C). ## APU System - **ATA 49: APU** - Provides elec. for the A/C system - Honeywell & APIC - Electronic Control Box (ECB), located @ aft cargo - Turbo shaft. ## Power Plant (CFM54-58) - **ATA 70-80: Power Plant (CFM54-58)** - CFM 54-5B is dual-rotor, variable stator, high bypass ratio turbo fan power plant. - A programming plug on the electronic control unit (ECU) changes the available thrust. - **Low pressure (LP) Rotor** - N. - LP compressor + 1 turbine blades = 5 LP Comp - Bearings = Cooled and lubricated, roller bearings, ball. - LP shaft - LP turbine (4) - LP turbine powers the LP compressor. - Bypass air = combustion air. - Primary airflow = bypass air. - Secondary airflow = gives the highest power. - 5:1 Ratio (5 Secondary Air: 1 Primary Air). - **High Pressure (HP) Rotor** - 9 HP compressor - N2 - ball/Roller bearings. - HP Shaft - HP Turbine (1). - SLPC + 9 HPL + 2 HPT + ALPT. - Annular Combustion Chamber, powered by exciter. - 20 Fuel Nozzle & igniter plug - HP compressor is the source of blend air (5th and 9th stage) ## Accessory Gearbox - **Transfer Accessory Gearbox** - N₂ = 60%-80% - Integrated Driven Generator (IDG) ## Engine Interface Unit (EIV) - **FADEL** - Sub-system = EIV (Engine Interface Unit). - Engine Vibration Monitor Unit (EVMU) - Max: 0.6. - Thrust Reverser System. - Green Hydraulic Sys. ## Pneumatic Bleed Monitoring Computer (BMC) - **ATA 36: Pneumatic Bleed Monitoring Computer (BMC)** - Bleed monitoring. - Cross bleed valve - **Leak Detection** - Loop A = BMC1 - Loop B = BMC2 ## Air Conditioning System - **ATA 21: Air Conditioning** - Air from Pack 1 or 2 goes to the mixer unit. - Cabin air - Bleed air. - Air should exit outplow valve to neutralize the pressure of the A/C. - **PACK** - Air Conditioning System Controller (ACSC), 1 & 2 - Hot air > and Heat Exchanger > 2lst heat exchange. - Air cycle Machine > Cabin - **Zone Regulation System**. - **Ventilation** - Avionics Equipment Ventilation Computer (AAVC). - Can have ventilation without heating but cannot have heating without ventilation. ## Pressurizing System - **Pressurization** - Cockpit, avionics bay, cabin, and cargo compartments are pressurized. - Cabin Pressure Controller (CPC) 1 & 2 - Auto Mode. - ADIRU and FMGC - System alternates each flight. ## Ice and Rain Protection - **ATA 30: Ice and Rain Protection** - Wing Anti-Ice - Used bleed air (from HP compressor). - Stats 34.5 - **Probes** - Electrically heated. - Probes Heating Computer (PHC) 1, 2, & 3 - **Windows** - Window heating computer (WHC) 1 & 2 - **Wiper** - Can work efficiently up to 200 knots all speeds. ## Drain Mast - **Drain Mast** - Electrically heated (CIDS) ## Ice Detection System - **Ice Detection** - Electronic Ice Detection System. - Visual Ice Indicator. ## Maintenance Schedules - **ATA 65: Time Limits & Maintenance Checks** - Maintenance Planning Document (MPD) comes from manufacturer. - Scheduled & unscheduled maintenance. - Leaks. - Hard Landing/Tail Strike - Bird Strike - Lightning Strike/Hailstorm - **Task No.** - 24-21-00 - **ATA Section Subject** - A/C Maintenance Test Oriented Support System (AMTOSS) - **24-21-00 - xxxx - xxx** - Functional Code.