Geophysical Survey Aircraft
Cessna 404 Titan

Registration: C-GBWE
Serial #: 404-0624

The model 404 Titan Courier is an all metal, low wing, twin-engined aircraft powered by two turbocharged engines that drive constant speed, full-feathering propellers. The aircraft has fully retractable tricycle landing gear, extendable flaps and manually adjustable trim tabs on the primary controls for all three flight axes. The aircraft is equipped with full de-icing equipment and sufficient avionics for instrument flying. Supplementary fuel can be added for trans-oceanic flight.

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

The airframe has been extensively modified to reduce the magnetic signature of the aircraft by replacing ferromagnetic parts with those made from special non-magnetic stainless steel or aluminum. Several wiring changes have also been made to the electrical system to reduce the magnetic field variations around the aircraft.

404a-new.jpg (305032 bytes)

CESSNA 404 SPECIFICATIONS

Crew capacity:

  • 2 pilots, 1 operator (optional)

Fuselage:

  • semi-monocoque

Wings:

  • cantilever, low wing
  • outboard ailerons with trim tab
  • single-slotted inboard flaps

Tail:

  • conventional stabilizers
  • elevators and rudder with trim tabs

Powerplants:

  • 2 Teledyne Continental GTSIO-520-M, 375 hp, six cylinder, horizontally- opposed, air-cooled, fuel-injected, turbocharged, reciprocating engines
  • 2 three-blade, fully-feathering, constant-speed propellers

Systems:

  • dual flight controls with IFR instruments and avionics
  • integrated flight control system with 3 axis autopilot
  • full airframe and propeller de-icing
  • weather radar

Dimensions:

wing span 46 ft. 8 in. 14.23 m
exterior length 39 ft. 6 in. 12.05 m plus stinger
exterior height 13 ft. 3 in. 4.04 m
interior usable length length 11 ft. 3 in. 3.40 m
interior usable width 4 ft. 6 in. 1.40 m
interior height 4 ft. 3 in. 1.30 m
fuel capacity, no ferry tank 344 US gallons 1,300 l usable
removable aux fuel tank 53 US gallons 200 l
removable ferry tanks 150 US gallons 567 l
type of aviation fuel 100 LL Avgas  

Weights:

empty 5,410 lbs. 2,454 kg
maximum take off 8,400 lbs. 3,810 kg

Performance:

(sea level, standard day, maximum takeoff weight, no aux or ferry fuel tanks)
range at 65% power 1,380 nm 2,550 km plus reserve
cruise airspeed 65% power 167 kts. 309 km/hr
fuel flow at 65% power 38 US gallons/hr. 144 l/hr
stall airspeed 70 kts. 130 km/hr
service ceiling 25,000 ft. 7,625 m
minimum required runway length 3,500 ft. 1,067 m
two engine rate of climb 1,650 ft/min. 503 m/min
maximum sustained climb gradient 460 ft/nm 76 m/km 76 m/km
single engine rate of climb 230 ft/min. 70 m/min

Maximum endurance:

  • 8 hours 25 minutes plus 45 minutes reserve at 65% power

Engine overhaul:

  • 1,600 hours

Propeller overhaul:

  • 1,600 hours or 5 years

PROVISIONS FOR GEOPHYSICAL SURVEYING

  • Tail stinger2.54 m long and 21 cm in diameter, capable of housing a 5.5 kg sensor
  • HF radio
  • Video Camera Mount with 8 cm diameter glass covered opening in the belly of the aircraft
  • 2 instrument racks, standard 48 cm (19 inch) width
  • Radar altimeter, 0-3,000 m
  • Electrical power capacity 28 VDC at 200 amp
  • Static inverter, 115 VAC - 400 Hz
  • Provisions to mount an Inertial Navigation System
  • Provisions to mount a GPS receiver and antenna plus data link for real time corrections
  • Provisions to mount gamma-ray spectrometer with up to 63 litres (3840 in3) of detector crystals

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