Christavia MK I

Christavia was designed as a mission field workhorse. Design requirements were short takeoff and landing, small engine (low fuel consumption), low stall speed, good cruise speed and rate of climb, large cabin area, low maintenance and a high safety factor. It is a conventional high-wing monoplane that easily converts from wheels to floats or skis. Fuselage construction is conventional steel tube, wings are two-spar Sitka spruce. Both fuselage and wings are covered in Dacron and finished in dope. Engines can range from 50-150 HP. The Continental A65 is the most popular powerplant. Features include dual controls, complete instrument panel, landing lights, strobes, 12V electrical system, tandem seats and a large baggage area. The Christavia is easy to fly and the large cabin makes long flights comfortable.

specifications
 
powerplant
propeller
length
height
wing span
wing area
seats
empty weight
useful load
gross weight
fuel capacity
range
Cont. HP Range 65/65-100
x
21ft
7ft
32.5ft
146.2sq. ft
2
740lb
x

1500lb
19gal
315n.m

performance

takeoff distance, ground roll
rate of climb
max speed
cruise speed
landing distance, ground roll
service ceiling
300ft
900fpm
118mph
105mph
 800ft
14,000ft

limiting and recommended speeds

design manoeuvring speed (Va)
never exceed speed (Vne)
stall, power off (Vsl)
landing approach speed
x
x
40mph
x

All specifications are based on manufacturer's calculations

Canadian taildragger utilizes conventional steel lube, wood and fabric structure. Fuel is figured in imperial gallons. First flew in 1983.