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Crew2 Passengers525, max. 853 Propulsion4 Turbofan Engines Engine ModelsRolls-Royce / Engine Alliance Trent 900 / GP7200 Engine Power (each)311 kN 69916 lbf Max Operating Speed945 km/h 510 kts  587 mph 510 knots Max Design Speed1020 km/h 510 kts  634 mph 551 knots Mmo (max. Mach)Mach 0.89 Service Ceiling 13.106 m 43.000 ft Range15.199 km 8.207 NM 9.444 mi. Thrust Range311 kN Empty Weight276.800 kg 610.239 lbs max. Takeoff Weight569.000 kg 1.254.429 lbs max. Landing Weight391.000 kg 862.006 lbs Wing Span79,80 m, 261,8 ft Wing Area845,0 m, 9096 ft Length73,00 m, 239,5 ft Height24,10 m, 79,1 ft Wheel Base31.88 m, 104,7 ft First Flight27.04.2005
Overhead(Click)
AIRBUS A380
Sidestick Priority Logic (CLICK BACKGROUND TO CLOSE) The Sidestick pushbutton (pb) is used as priority takeover pushbutton:◆ The pilot can deactivate the other Sidestick and take full                 control by pressing and keeping pressed his Sidestick                 pushbutton.◆ If the Sidestick pushbutton is pressed for more than 30                 seconds, the priority is latched and the other Sidestick is                 maintained deactivated◆ At any time, a deactivated Sidestick can be reactivated by                 momentarily pressing the Sidestick pushbutton
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(CLICK BACKGROUND TO CLOSE) Reconfiguration Each pilot can cycles through the different output each display on his side uses. Brightness Knobs Brightness Knobs for the Primary Flight Display (PFD), Navigation Display (ND), Flight Management System (FMS) and the Onboard Information Terminals(OIT).
Glareshield
The Airbus A380 is a four-engined, long-range, wide-body airliner with two full length passenger decks. It is the largest passenger jet ever built -- so huge that airports have to be redesigned to accommodate it.  It has a wingspan of 261.8 feet (79.8 meters), a length of 239.5 feet (73 meters) and a maximum take-off weight of more than 1.2 million pounds (569,000 kg). The A380 has an improved glass cockpit, using fly-by-wire flight controls linked to side-sticks.   It has eight 15 by 20 cm (5.9 by 7.9 in) liquid crystal displays, all physically identical and interchangeable; comprising two primary flight displays, two navigation displays, one engine parameter display, one system display and two multi-function displays, augmented by a HUD (head-up display) that increases pilot situational awareness.  With pull-out keyboards for the pilots, it's cockpit layout, procedures and handling characteristics are similar to other Airbus aircraft, which reduces the cost of crew training. The switches and knobs maybe slightly different for each airline that orders a A380.
Main Instruments
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Maintenance Panel
Circuit Breakers .
WipersThe Captain / First Officer each have a electric wiper control that can be used during taxi, takeoff, holding, approach and landing.
The Airbus A380 is a four-engined, long-range, wide-body airliner with two full length passenger decks. It is the largest passenger jet ever built -- so huge that airports have to be redesigned to accommodate it.  It has a wingspan of 261.8 feet (79.8 meters), a length of 239.5 feet (73 meters) and a maximum take-off weight of more than 1.2 million pounds (569,000 kg). The A380 has an improved glass cockpit, using fly-by-wire flight controls linked to side-sticks.   It has eight 15 by 20 cm (5.9 by 7.9 in) liquid crystal displays, all physically identical and interchangeable; comprising two primary flight displays, two navigation displays, one engine parameter display, one system display and two multi-function displays, augmented by a HUD (head-up display) that increases pilot situational awareness.  With pull-out keyboards for the pilots, it's cockpit layout, procedures and handling characteristics are similar to other Airbus aircraft, which reduces the cost of crew training.
(CLICK BACKGROUND TO CLOSE) Engine Fire The Fire Detection Unit monitors all sensitive zones of each engine.The flight crew can isolate and extinguish the fire from this panel with two extinguisher bottles per engine.
Emergency Locater Transmitter (ELT) A tracking transmitter which can aid in the detection and location of the aircraft. Can be Manually or Automatically set to transmit a distress signal if certain G loads are exceeded.  The signal is process as follows:1. ELT transmit signals in case of emergency;2. Instruments on board geostationary and low-orbiting satellites                 detecting signals transmitted by the ELTs;3. Local User Terminals (LUT), receive and process signals                 transmitted via the satellite down-link to generate distress alerts;4. Mission Control Centers (MCC) which receive alerts from LUTs                 and send them to a Rescue Coordination Center (RCC)
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(CLICK BACKGROUND TO CLOSE) Radio Management Panel You will find more information about this panel, on the Pedestal.
(CLICK BACKGROUND TO CLOSE) Top to Bottom1. Flight Controls (F/CTL)2. Fuel3. Evacuation (EVAC)4. Emergency Electrical Power (EMER ELEC PWR)5. Enterainment6. Oxygen7. Calls
Cockpit Voice Recorder (CVR)Records all conversations in the cockpit.
(CLICK BACKGROUND TO CLOSE) Electrical115 V Alternating Current (AC) power can be provided by three types of power sources:• Engine-Driven Generators• Auxiliary Power Unit (APU) Generators• External Power Units AIRThe Air Conditioning system is fully automatic. It provides continuous air renewal and maintains a constant selected temperature and airflow in the cabin and cockpit zones.
(CLICK GREEN TO CLOSE)Anti IceThe Anti Ice system protects the aircraft against ice by using:• Hot bleed air for:⁃ Engine anti-ice⁃ Wing anti-ice• Electrical power for:⁃ Window heating⁃ Water/waste drain masts heating⁃ Probe heating ENG StartEngine Start Mode Selector Cabin PressureThe flight crew can manually operate the cabin air pressurization system, by selecting the cabin Altitude Target and/or the cabin pressure Vertical Speed. Exterior LightsInterior LightsGives flight crew control over all Interior/Exterior lighting. APU• On ground⁃ Bleed air for engine start and for air conditioning⁃ Electrical power via two generators• During takeoff:⁃ Bleed air for air conditioning• In flight:⁃ A backup for air conditioning up to an altitude of 22 500 ft⁃ A backup for electrical power for the entire flight envelope⁃ Bleed air for engine start
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(CLICK BACKGROUND TO CLOSE) HydraulicThere are two identical and independent Hydraulic circuits: YELLOW and GREEN. They operate continuously and power the flight controls, the landing gear system, and the cargo doors at a nominal pressure of 5000 psi instead of 3000 psi on previous Airbus aircrafts. FuelThe Fuel System stores fuel, monitors the quantity of fuel in each tank and controls fuel transfers, in order to:• Supply fuel to the engines and to the Auxiliary Power Unit (APU)• Maintain the Center of Gravity (CG) within limits• Alleviate structural loads• Control refueling and defueling• Enable fuel jettison, if necessary
AIRBUS A380 Overhead
(CLICK BACKGROUND TO CLOSE) Auxiliary Power Unit (APU):◦ The Fire Detection Unit monitors the APU◦ Flight crew can isolate and extinguish the fire using this panel. The APU has                 one extinguisher bottle. Air Data and Inertial Reference System (ADIRS) Is the aircraft navigation center. It is composed of three Air Data and Inertial Reference Units (ADIRUs):• The Air Data (AD): Computes primary Air Data parameters data from                 different probes installed on fuselage:       ⁃ One Multi-Function Probe (MFP) per Unit: Provides total pressure (Pt),                         Total Air Temperature (TAT) and Angle-of-Attack (AOA) measurements       ⁃ One Side Slip Angle (SSA) probe per Unit: Provides sideslip angle       ⁃ Two Integrated Static Probes (ISPs) per Unit: Provide the Static                         Pressure (Ps)• The Inertial Reference (IR): Computes primary Inertial Reference information                 using data from internal Accelerometers and Gyros. Probe / Window Heat▪ Aircraft probes are electrically heated to prevent icing.▪ Cockpit Windows (windshield and side windows) are electrically heated to                 prevent icing and to defog.
Printer.
Engine Master Switch .
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(CLICK BACKGROUND TO CLOSE) Surveillance SystemThe purpose of the SURVeillance (SURV) is to regroup all the aircraft surveillance functions into one system with one integrated control panel.The SURV provides: • The Terrain Awareness and Warning System (TAWS) function for terrain proximity hazards• The Weather Radar (WXR) function for atmospheric disturbance hazards• The Traffic Collision Avoidance System (TCAS) function for airborne collision hazards and a transponder (XPDR) function.
Speed Brake LeverWell, if you're going to fast, then you'll need to slow down.
AIRBUS A380 Pedestal
PITCH TRIM & RUDDER TRIM The A380 is the first Airbus that does not have a tailplane trim wheel on the centre console. The wheel is replaced by this Pitch Trim switch.
Thrust & Thrust Reverser Control Levers The flight crew uses the thrust levers to:▫ Manually select the engine thrust▫ Arm and activate the autothrust▫ Engage the takeoff and go-around modesThere are 4 detents:• TO GA: Maximum takeoff thrust• FLX MCT: Maximum continuous thrust• CL: Maximum climb thrust• IDLE: Idle thrust.
(CLICK BACKGROUND TO CLOSE) Flaps & SlatsThe flight crew uses the FLAPS lever to manually select the position of the slats and flaps. High lift control is achieved on each wing by:✓ 3 flaps✓ 8 slats✓ 3 ailerons, via the aileron droop functionFor redundancy purposes, each slats/flaps control unit can also control the other slats/flaps motor, in case the other slats/flaps control unit fails.
1. Aircraft Condition Monitoring System (ACMS): Records data and information from aircraft systems: parameters at takeoff, flight speed, engine temperature etc. 2. Cabin Alert 3. Digital Flight Data Recorder (DFDR) Event 4. Cockpit (CKPT) Door
Parking Brake & Cabin Lights
Keyboard & Cursor Control Units (KCCU) The cockpit is equipped with two KCCU. They enables the flight crew to directly interact with the onside ND, MFD and the mailbox section of the SD. Flight crew uses the KCCU to:◦ Navigate through the FMS pages on the MFD◦ Enter and modify data on the MFD◦ Modity Electronic Flight Instrument System (EFIS) data◦ Perform some flight plan revisions on the lateral ND
(CLICK BACKGROUND TO CLOSE) Electronic Centralized Aircraft Monitoring (ECAM)Displays data concerning aircraft system and failures and corrective action to be taken by the pilots, as well as system limitations after failures. In normal operation, the ECAM provides the necessary information to assist the flight crew to operate and monitor the aircraft systems:• Primary Flight Display (PFD): Slats/Flaps/Trim/Memos and Limitations, in lower part of PFD.• System Display (SD): System Synoptic and Status pages. • Engine Warning Display E/WD) Displays normal checklists Warning/Caution & Procedures,                 Abnormal Procedures and Memos/Limitations.In Abnormal operation, the ECAM Alerts conditions by:     • Producing visual and aural warnings and cautions, if failures are detected     • Providing associated procedures and associated limitations and memos    • Displaying the applicable system synoptic pages    • Providing ABNORMAL not sensed procedures, on flight crew request
Flight Interphone Handset.
(CLICK BACKGROUND TO CLOSE) Radio Management Panel (RMP)There are 3 RMPs, 2 located on the Pedestal and a third one on the Overhead Panel. The RMPs can be used:◦ Select the way of communication (radio communication, SATCOM, interphones)◦ Tune the radio frequencies◦ Dial SATCOM Telephone (TEL) numbers◦ Select voice or data mode communication◦ Monitor and select data communication parameters◦ Enter the squawk (SQWK) code◦ Select standby (STBY) radio navigation◦ Adjust the volume for communication and NAVAID identificationImages1. Radio Management Panel2. Radio System3. Radio Synchronization
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AIRBUS A380 Cockpit Layout
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AIRBUS A380 Displays
(CLICK BACKGROUND TO CLOSE) Primary Flight Display (PFD): Displays short-term graphical/textual flight information. Navigation Display (ND): Displays long-term lateral and vertical flight information. Flight Management System (FMS): Displays more than 50 pages of information on the flight plan, aircraft position and flight performance. Engine/Warning Display (E/WD): Displays Normal/Abnormal Engine Primary Parameters, Checklist/Items requested by the flight crew and memos. System Display (SD): Displays System Synoptic and More Information pages, Temperature, time and Aircraft Weight data and Air Traffic Control (ATC) Mailbox
AIRBUS A380 Auto Flight System (AFS)
(CLICK BACKGROUND TO CLOSE) Auto Flight System (AFS) includes: • Flight Guidance (FG) System: Provides short- term lateral/vertical guidance based on parameters                  selected by flight crew or managed by the FMS        ⁃   Three Primary Flight Control and Guidance Computers (PRIMs) that operate the AP, FD and A/THR • Flight Management System (FMS): Provides long-term guidance by sending targets to the FG       ⁃   Three Flight Management Computers (FMCs) that operate 2 FMSs
(CLICK BACKGROUND TO CLOSE) Controls and displays flight parameters and navigation data on four display units: 1. Two Primary Flight Display (PFD) units: Provides short-term flight information       • Upper Section of the PFD Displays               ⁃ Attitude               ⁃ Airspeed/Mach               ⁃ Altitude/Verticalspeed               ⁃ Heading (HDG)       • Lower Section Displays:               ⁃ Memos and limitations               ⁃ Slat/Flap/Trim positions2. Two Navigation Display (ND) units: Provides long-term flight information       • Upper Section of the ND, called ND Main Zone, displays:               ⁃ Aircraft position with respect to navigation aids, FMS flight plan and map data               ⁃ Weather radar information               ⁃ SURV information       • Lower Section of the ND, called Vertical Display (VD) Zone, displays:               ⁃ Weather radar information               ⁃ Surveillance (SURV) system vertical information combined with the vertical flight profile to                                  provide a synthetic view of the aircraft’s vertical situation The flight crew interacts with the EFIS displays through the:◦ Keyboard and Cursor Unit (KCCU)s◦ EFIS control panels◦ Control and Display System (CDS) Reconfiguration (RECONF) control panels
AIRBUS A380 Electronic Flight Instrument System (EFIS)
AIRBUS A380 ISIS & LDG Gear Panels
Triple Pressure Indicator • Displays the Hydraulic System Pressure that                  is supplied to the Brakes.Landing Gear Indicators◦ Monitor and electrically control the extension                 and retraction sequences.Auto Brakes• The brakes can be applied either manually or                 automatically via the Autobrake.Anti-Skid• Brake pressure is automatically limited to                 avoid skidding.Landing Gear Lever◦ Hydraulically extends and retracts the                 Landing Gear.ClockOperates independently of other systems and provides time data to all aircraft systems that require a time and date reference.
Integrated Standby Instrument System (ISIS) • Provides backup flight and navigation                  displays in the case of an ADIRS, FMS or                 CDS failure.Landing Gear Gravity Extension◦ If the normal extension and retraction system                is not available, gravity-assisted landing                gear extension can be performed. Attitude (ATT) Heading (HDG)/Air Data Switching Selector FMS Source Selector• Allows the flight crew to link all flight                 management interfaces on both sides with                  the FMC on Captain's side (BOTH ON 1), or                  on the F/O's side (BOTH ON 2).           
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AIRBUS A380 Onboard Information System (OIS)
(CLICK BACKGROUND TO CLOSE) Is a set of Equipment, Electronic Documentation and Applications for Flight Operations and Maintenance.The OIS applications can be divided into:1. Tools for Flight Operations support      ◆ Performance Computation Tools for takeoff, in-flight and landing      ◆ A Weight & Balance (W&B) computation tool      ◆ Electronic Documentations:               ⁃ Flight Crew Operating Manual (FCOM)               ⁃ Aircraft Flight Manual (AFM)               ⁃ Configuration Deviation List (CDL)               ⁃ Minimum Equipment List (MEL)               ⁃ Flight Crew Training Manual (FCTM)      ◆ Contact Manager      ◆ Navigation and Weather Charts      ◆ Electronic Flight Folder (EFF)      ◆ Flight Follow Up (FFU) tool2. Tools for Cabin Operations support      ◆ Services for passengers:               ⁃ Worldwide electronic mail (wired or wireless)               ⁃ Credit Card banking      ◆ Tools to support Maintenance Operations dedicated to the cabin      ◆ Qireless area Network Manager application3. Tools for Maintenance Operations support      ◆ Onboard Maintenance Terminal (OMT) is installed in the rear part of the cockpit4. Services for Passengers, Flight Crew and Cabin Crew      ◆ Flight Attendant Panel (FAP): Used by the Cabin Crew for Cabin Operations Scroll Image
AIRBUS A380 Steering System
(CLICK BACKGROUND TO CLOSE) The Steering System provides directional control of the aircraft on ground, and combines:• Nose Wheel Steering (NWS)• Body Wheel Steering (BWS) The Steering System has two redundant Steering Control Systems (SCS).◦ Nose Wheel Steering (NWS) - The NWS has two modes:       ⁃ Normal Mode: NWS is powered by the GREEN hydraulic system       ⁃ Alternate Mode: NWS has degraded performance and is powered by its own LEHGS and NWS                        accumulator◦ Body Wheel Steering (BWS)       ⁃ BWS is powered by the YELLOW hydraulic circuit NWS is not available when the engines are shut downBWS is available only during taxi, pushback and towing