Dimensions: Length: 14.39 m; Height: 4.57 m; Wingspan: 15.90 m; Flying performances: Speed: Min speed: 44 m/s Max speed: 197 m/s Usual speed during transit flights: 160 m/s Ascent rate: 15 m/s Altitude: (1 ft = 0.31 m) Min altitude: Above sea: 100 ft Above ground: 100 ft Max ceiling: 43000 ft Usual ceiling during measurements: 43000 ft Ceiling limitations: To be defined. Payload: Empty weight: 3725 kg Max take-off weight: 6620 kg Max payload: 1300 kg Usual scientific payload during measurements: 1150 kg Endurance: Max endurance: 6 h (at min scientific payload and max fuel) (Y-coordinate of 1st point) Range: Max range: 3000 km (at min scientific payload and max fuel) Range at max scientific payload: 1100 km Other: Weather conditions limitations: IFR, VFR Approved for flight into known icing conditions Take-off runway length: 1050 m Engines: 2 engines Pratt & Whitney CANADA JT 15D-4; Avionics: On-board OEM equipment includes a three-tube Electronic Flight Instrument System (EFIS), a Flight Management System (FMS) with a Global Positioning System (GPS) sensor and a Flight Director / Autopilot Crew and scientists on board: Crew (pilots + operators): 2 pilots 1 flight test engineer in case of standart experiment; Seats available for scientists: 8 cabin seats Cabin: Length: 4.78 m Width: max 1.49 mfloor 0.96 m Height: 4.57 m Apertures: Entrance door, left forward side fuselage Size : width top : 0.50 m ; width bottom : 0.60 m ; height 1.29 m Emergency exit : right forward side fuselage; Cabin pressurized: 8.7 PSI MAX (cabin 8000 ft at 43000 ft altitude) More information: Cabine volume: 10.7 m3 Distance underside fuselage - ground : 0.44 m; Aircraft modifications: Nose boom: length 2.3 m Windows: 5 left hand side (with sun shades) 5 right hand side (with sun shades) Openings: Hatch in bottom fuselage for feedthrough experiment cables etc : 10 x 20 cm Hard points: fuselage stations : 134, 168 and 207 2 attach points per fuselage station Max load : 200 kg per hard point Inlets: Provisions for inlets on experimental emergency door. Additionnal systems: An additional stand-alone 3000 psi hydraulic system for operating test equipment on research actuators. Numerous facilities in the cockpit and cabin for accomodating test equipment. A "roof rack" on top of the fuselage that can accommodate multiple antennas. Acquisition systems: A multi-channel digital data acquisition and recording system that can handle a large number of parameters with high accuracy at a high sample rate is available. Datalink facilities can be provided. Electrical power: Aircraft total electrical power (kW): 2 x 400 A, 28 VDC Electrical power (kW) and voltages (V) available for scientists: A separate electrical system dedicated to powering on-board test equipment, isolated from the aircraft electrical system for added safety (28 VDC, 115 VAC 400 Hz, 220 VAC)Total availab