European Facility For Airborne Research

European Facility For Airborne Research Jan. 23, 2018, 11:15

Aircraft: Seneca - OGS

Seneca - OGS
Aircraft acronym Seneca - OGS Registration number S5-DGL
Operator National Institute for Oceanography and Experimental Geophysics Transnational Access status Closed to TA
Manufacturer Piper Aircraft, PA34-200T Seneca II Engine category Propeller
Aircraft type Research Categories Troposphere

Dimensions

  • Length: 8.7 m
  • Height: 3.0 m
  • Wingspan: 11.9 m
Airplane dimensions 8.7 m 3.0 m 11.9 m

Flying performances

Speed
Min speed 32 m/s
Max speed 99 m/s
Usual speed during measurements 40 m/s
Usual speed during transit flights 80 m/s
Ascent rate 6 m/s
Altitude
Min altitude
  • Above sea: 100 ft
  • Above ground: 100 ft
Max ceiling 25 000 ft
Usual ceiling during measurements 3 000 ft
Ceiling limitations

n/c

Payload
Empty weight 1 264 kg
Max take-off weight 2 073 kg
Max payload 809 kg
Max scientific payload 300 kg (X-coordinate of 2nd point)
Usual scientific payload during measurements 50 kg
Scientific payload for max endurance 150 kg (X-coordinate of 1st point)
Aircraft autonomy

Endurance
Max endurance at min scientific payload and max fuel 8 h (Y-coordinate of 1st point)
Endurance at max scientific payload 2 h (Y-coordinate of 2nd point)

Range
Max range 1 811 km (at min scientific payload and max fuel)
Conditions for max range

n/c

Range at max scientific payload None km
Usual range during measurement flight 1 400 km

Other
Weather conditions limitations

VFR, IFR, de-icing

Take-off runway length 0 m
Engines

2 x Continental TSIO-360-EB-L

Avionics

2 X GARMIN 428

Crew and scientists on board

Crew (pilots + operators)

1

Seats available for scientists

5

Cabin

Length 3.15 m
Width 1.23 m
Height 10.6 m
Apertures

1 door on the right side for cockpit
2 adjacent doors on the left side, for passenger/operator compartment

Cabin pressurized

no

More information

portable oxygen with four masks available

Aircraft modifications

Nose boom

no

Windows

no

Openings

Hatch: W0.20 m x L0.60 m on the rear bottom of the fuselage

Hard points

no

Inlets

air inlet via supplementary pitot tube

Additionnal systems

Acquisition systems

n/c

Electrical power

Aircraft total electrical power (kW)

2.5 kW

Electrical power (kW) and voltages (V) available for scientists

24 volts 30 Amps ; 12 volts 10 Amps

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This project has received funding from the European Union's Seventh Framework Programme for research, technological development and demonstration under grant agreement no. 312609

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