amphibious aircraft 10 according to one embodiment of the invention in this embodiment the aircraft 10 features a power plant 12 mounted to an aft portion of fuselage 14 the fuselage 14 includes a wing 16 a float 18 is cantilevered from the wing 16 a vertical fin 20 is coupled to the aft end of each float 18 a horizontal stabilizer 22 is coupled to the vertical fins 20 preferably but not necessarily near the top of the fins 20 to complete a tail portion 24 a nosewheel 26 is coupled to the front of the fuselage 14 in some embodiments the fuselage 14 is configured for appropriate hydrodynamic effects both statically and dynamically during all phases of taxiing takeoff and landing the fuselage 14 may feature any desired shape length width and height to accomplish the result of appropriate aerodynamic and hydrodynamic performance for a general aviation class amphibious aircraft with favorable stability airspeed range and maneuverability characteristics the fuselage 14 may be assembled in a stress skin monocoque semimonocoque or longitudinal member design or a combination of any or all of these designs a skin 27 is fastened to the design and carries primarily the shear load tension and bending stresses the fuselage 14 may be formed of any suitable material including but not limited to aluminum aluminum alloys other metallic materials composite materials or other similar materials the horizontal stabilizer 22 may be included as shown in fig1 4 the horizontal stabilizer 22 generally.