Geophysical Survey Aircraft
Britten-Norman BN2B-21 Islander


Registration:
C-GSGX
C-GSGR
Serial #:
596
2107

The BN-2B Islander is an all metal, high wing, twin-engine, short take-off and landing aircraft powered by two fuel injected engines which drive constant speed, fully feathering propellers. The aircraft has fixed tricycle landing gear, extendable flaps and manually adjustable trim tabs on the rudder and elevator. The aircraft is equipped with de-icing equipment and sufficient avionics for instrument flying. Because of its low takeoff speed, high wing, ample propeller clearance, and sturdy fixed landing gear, the Islander is capable of operating from relatively short and rough airstrips. Its excellent low speed capabilities enable it to safely contour much steeper terrain than most other fixed wing aircraft. Supplementary fuel can be added for trans-oceanic flight.

The aircraft has an aluminum and composite 2.5 m tail stinger designed to accommodate the magnetometer sensor and wiring. The stinger can be easily removed and the aircraft returned to its original configuration. There is a camera hole in the belly and provisions for numerous other survey and navigation systems.

The electrical system has been modified to reduce the magnetic field variations around the aircraft.

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BRITTEN NORMAN ISLANDER BN2B-21 SPECIFICATIONS

Crew capacity:

  • 2 pilots, 1 operator (optional)

Fuselage:

  • semi-monocoque

Wings:

  • cantilever, high-wing
  • outboard ailerons
  • single-slotted inboard flaps

Tail:

  • conventional stabilizers
  • elevator and rudder with trim tabs

Powerplants:

  • 2 Lycoming IO-540, 300 hp, six cylinder, horizontally-opposed air-cooled, fuel-injected, reciprocating engines
  • Hartzell two-blade, fully-feathering, constant-speed propellers

Systems:

  • dual flight controls, IFR instruments and avionics
  • full airframe and propeller de-icing 2-axis autopilot

Dimensions:

wing span 53 ft. 16.15 m
exterior length 35 ft. 8 in. 10.9 m plus stinger
exterior height 13 ft. 9 in. 4.18 m
interior usable length 15 ft. 2 in. 4.62 m
interior usable width 3 ft. 7 in. 1.09 m
interior height 4 ft. 2 in. 1.26 m
fuel capacity 189 US gallons 700 l usable
type of aviation fuel LL Avgas  

Weights:

empty 4,190 lbs 1,900 kg
maximum take off 6,600 lbs 3,000 kg

Performance:

( sea level, standard day, maximum take off weight )
range at 60% power 760 nm 1,400 km plus reserve
cruise airspeed at 60% power 121 kt 224 km/hr
fuel flow at 60% power 25.5 US gallons/hr 97 l/hr
stall airspeed, landing config 40 kt 74 km/hr
service ceiling 17,200 ft. 5,242 m
minimum required runway length 2,000 ft. 610 m
two engine rate of climb 1,130 ft/min 345 m/min
maximum sustained climb gradient 700 ft/nm 115 m/km
single engine rate of climb 223 ft/min 69 m/min

Maximum endurance:

  • 6 hours 40 minutes plus 45 minutes reserve at 60% power

Engine overhaul:

  • 2,000 hours

Propeller overhaul:

  • 2,000 hours or 5 years

PROVISIONS FOR GEOPHYSICAL SURVEYING

  • Tail stinger, 2.5 m long, 21 cm in diam., capable of housing a 5.5 kg sensor
  • HF radio
  • Video Camera Mount with glass covered opening in aircraft belly
  • 2 instrument racks, standard 48 cm (19 inch) width
  • Radar altimeter, 0-3,000 m
  • Electrical power capacity 28 VDC at 140 amp
  • Provisions to mount a GPS receiver and antenna plus data link for real time corrections
  • Provisions to mount gamma-ray spectrometer with up to 42 litres (2560 in3) of detector crystals

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