single engine 4 seat meeting FAR 51% rule for amateur construction.
pusher propeller.
molded composite construction.
low profile pusher configuration.
minimal trim drag and power trim changes compared to other amphibians.
propeller free of water spray.
spacious cabin.
long range ferry capability.
aft fuselage platform for on water power plant access, fishing, swimming, sunbathing etc.
integrated low drag wing tip floats.
designed to FAR23/ JAR23 rules.


V tails have been around for a long time on some very successful aircraft such as the Beech Bonanza and the Fouga Moister jet trainer. It also features on the new V-jet II light twin jet aircraft , the F117 fighter and on the Learfan turboprop aircraft.
V tails are different in that the rudder and elevator functions are combined and require a control input mixer mechanism. For the pilot there is no difference in control inputs and all maneuvering behavior is the same as on aircraft with conventional tail plane layouts.
The V tail on the Shearwater was a natural development of the low profile configuration. To allow a lower position of the propeller, the fuselage had to be sculpted out to a hollow section aft of the cabin. Tapering this cross section to the aft end of the fuselage and the structural requirements for torsional and bending stiffness resulted in curved strakes on each side. Incorporating conventional tail surfaces on this structure would have resulted in relatively heavy structural support and it was decided to continue the strake profile into the tail plane surfaces. The aft fuselage platform area thus created has great benefit for access to the engine and propeller and general purposes whilst on the water.


The aircraft's successful first flight was on 26 December 2001 after the project was started in 1997.
The configuration will be frozen as early as possible in the testing program to allow design completion of the kit components.
In the meantime design optimization continues on various subassemblies including the landing gear and retractable water rudder.


( Other performance parameters to be determined during flight test programme)
Engine: Franklin ..... 210 HP 157 kW
Propeller dia: 72" 1.83 m.
Max. Take Off Weight: 3086 lbs. 1400 kg.
Empty Weight: 1874 lbs. 850 kg.
Useful load: 1213 lbs 550 kg.
Fuel capacity: 137 USG 520 liters
Wing span: 36' 1" 11.0 m.
Length: 28' 2" 8.6 m.
Height ( on landing gear): 8' 8" 2.67 m.
Wing area: 185 sq.ft 17.2 sq.m
Wing loading: 16.7 lb/sq.ft. 81.4 kg/sq.m
Power loading: 14.7 lbs/hp 8.92 kg/kW
Cabin width- front seats: 50 in. 1.27 m.
Cabin width- rear seats: 47 in. 1.19 m.
Cabin length: 90 in. 2.3 m.
Luggage capacity: 35 cu.ft. 1.3 cu.m.
Cruise speed: 155 mph. 250 km/h
Stall speed (MTOW, full flaps): 57 mph. 92 km/h