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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
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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.
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