Dimensions: Length: 17.15 m; Height: 5.32 m; Wingspan: 16.32 m; Flying performances: Speed: Min speed: 82 m/s Max speed: 254 m/s Usual speed during measurements: 200 m/s Usual speed during transit flights: 240 m/s Ascent rate: 13 m/s Altitude: (1 ft = 0.31 m) Min altitude: Above sea: 200 ft Above ground: 300 ft Max ceiling: 39000 ft Usual ceiling during measurements: 39000 ft Ceiling limitations: tbd Payload: Empty weight: 8500 kg Max take-off weight: 14500 kg Max payload: 6000 kg Max scientific payload: 1200 kg ... (X-coordinate of 2nd point) Usual scientific payload during measurements: 1200 kg Scientific payload for max endurance: 1200 kg ... (X-coordinate of 1st point) Endurance: Max endurance: 5 h (at min scientific payload and max fuel) (Y-coordinate of 1st point) Endurance at max scientific payload: 5 h ... (Y-coordinate of 2nd point) Range: Max range: 4100 km (at min scientific payload and max fuel) Conditions for max range: FL400 at max fuel. Speed=414 KTAS Range at max scientific payload: 3200 km Usual range during measurement flight: 3200 km Other: Weather conditions limitations: VFR (2 pilots); IFR (2 pilots); certified for known icing conditions Take-off runway length: 1400 m Engines: Honeywell/Allied Signal ATF3-6A-4C (2*5200 lbs); Avionics: Universal EFIS and Flight Management Systems. Crew and scientists on board: Crew (pilots + operators): 2 pilots for all operations + 1 Flight engineer; Seats available for scientists: From 1 to 4 depending on missions Cabin: Length: 7.26 m Width: 1.79 m Height: 1.70 m Apertures: Main door: 1.5 m * 0.8 m; Cabin pressurized: Cabin pressurised Aircraft modifications: Nose boom: length 1.8 m carrying measuring probe (e.g. five holes probe for turbulence measurements) Windows: 2 coverable photo windows in the bottom (diameter 515 mm each) and 2 on top of the fuselage (diameter 320 mm each) Openings: 4 openings (diameter 80 mm each) on top of the fuselage, and 1 opening (diameter 150 mm) in the bottom of the fuselage. Hard points: 4 hardpoint stations (2 under each wing) to carry loads up to 500 kg each (using standard 14" NATO attachment system) but has to stay within the maximum payload limitation. Inlets: chemistry inflow or reverse flow inlets Additionnal systems: Provision for up and down-looking radiometers (core instrumentation). Dropsonde launching system (Vaisala AVAPS GPS system for RD93 dropsondes) Acquisition systems: Data acquisition is centralised and displayed on all screens. Time series of all data are provided after each flight within 2 hours. Electrical power: Aircraft total electrical power (kW): 28 V / max 285 A conversion to 220V / 50 Hz. -> 8 kW available for science Electrical power (kW) and voltages (V) available for scientists: 8 kW (28V)