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Christavia Experimental Aircraft

The Christavia MK1 is a single engine, high wing, conventional landing gear-equipped aircraft. The fuselage is of 4130 steel tube construction. The wings are flapless, predominantly wooden, use a custom Mason airfoil design and are supported by dual wing struts. The exterior is finished with aircraft fabric covering. The acceptable power range is 65 to 100 hp (48 to 75 kW) and the standard powerplant used is the 65 hp (48 kW) Continental A65 four stroke four cylinder horizontally opposed piston aircraft engine.

General characteristics Christavia MK1

  • Crew: 1
  • Capacity: 1 passenger
  • Length: 20 ft 8 in (6.30 m)
  • Wingspan: 32 ft 6 in (9.91 m)
  • Height: 7 ft 0 in (2.13 m)
  • Wing area: 146.25 sq ft (13.587 m2)
  • Airfoil: Mason
  • Empty weight: 745 lb (338 kg)
  • Gross weight: 1,300–1,500 lb (590–680 kg)
  • Fuel capacity: 18 US gallons (68 l; 15 imp gal)
  • Powerplant: 1 × Continental 65 hp (48 kW) or Subaru EJ16 90 hp (66 kW)
  • Propellers: 2 or 3 bladed fixed pitch

Performance

  • Maximum speed: 120 mph (193 km/h; 104 kn)
  • Cruise speed: 105 mph (91 kn; 169 km/h)
  • Stall speed: 40 mph (35 kn; 64 km/h)
  • Range: 350 mi (304 nmi; 563 km)
  • Service ceiling: 15,000 ft (4,572 m)
  • Rate of climb: 1,000 ft/min (5.1 m/s)

 

Designed for African missionary work the Mark IV is a development of the Christavia Mk I, with greater wingspan, a longer fuselage and two additional seats. The aircraft features a strut-braced high-wing, a four seat enclosed cabin with doors, fixed conventional landing gear and a single engine in tractor configuration.

The aircraft fuselage is made from welded 4130 steel tubing, while the wing is of all-wooden construction, with all surfaces covered with doped aircraft fabric. Later models have an aluminum wing spar. Its 35.50 ft (10.8 m) span wing employs a custom Mason airfoil, mounts flaps and has a wing area of 177.3 sq ft (16.47 m2). The wing is supported by "V" struts with jury struts. The standard engine used is the 150 hp (112 kW) Lycoming O-320 powerplant but a Subaru EJ22 140 hp (100 kW) is also approved.

The Christavia Mk IV has a typical empty weight of 1,100 lb (500 kg) and a gross weight of 2,200 lb (1,000 kg), giving a useful load of 1,100 lb (500 kg). With full fuel of 41 U.S. gallons (160 L; 34 imp gal) the payload for crew, passengers and baggage is 854 lb (387 kg).

Plans are marketed by Aircraft Spruce & Specialty Co. For Europe we have acquired the rights to act as distributor and support center for the Christavia.

Ron Mason from Elmwood Aviation Ontario Canada is the original designer.

He estimates the construction time from the supplied plans as 2000 hours for the Christavia MK1 and 2600 hours for the Christavia MK4.

 

General characteristics Christavia MK4

 

  • Crew: one
  • Capacity: three passengers
  • Length: 22 ft 3 in (6.78 m)
  • Wingspan: 25 ft 6 in (7.77 m)
  • Wing area: 177.3 sq ft (16.47 m2)
  • Airfoil Mason
  • Empty weight: 1,100 lb (499 kg)
  • Gross weight: 2,200 lb (998 kg)
  • Fuel capacity: 41 U.S. gallons (160 L; 34 imp gal)
  • Powerplant: 1 × Lycoming O-320 air-cooled, 150 hp (110 kW) or 1x Subaru EJ22 liquid cooled 140 hp (100 kW)
  • Propellers: 2 or 3 bladed fixed pitch

 

Performance

 

  • Maximum speed: 130 mph (209 km/h; 113 kn)
  • Cruise speed: 120 mph (104 kn; 193 km/h)
  • Stall speed: 48 mph (42 kn; 77 km/h)
  • Range: 400 mi (348 nmi; 644 km)
  • Service ceiling: 19,000 ft (5,791 m)
  • Rate of climb: 800 ft/min (4.1 m/s)
  • Wing loading: 12.4 lb/sq ft (61 kg/m2)

 

 

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