The Omsider is an amphibious aircraft developped and designed in cooperation with Nordic Aircraft company (Norway). The aircraft is made of composite materials using carbon and cork processed by the highest technology of production.
Omsider is designed in the category of ultralight non-certified aircraft.
You can see the Omsider prototype flying over the landscape here: Omsider. This amphibian is now enjoying flights from the water of Norwegian Hardangerfjord - see the video: Omsider at Hardangerfjord.
The wings are the same designed as applied on ATEC Faeta.The tailplane is in "T" configuration. Small sliding rudder, which is installed inside the tail rudder enables comfortable control under the aircraft on water surface. Easy electric system of tricycle retractable gear enables to keep its low weight. Seats are installed behind. Double control and double glasscockpit systems are available as optional equipment. Small removable rear windows provide wide view, possibility of taking pictures during the flight, but serves also as emergency exit. The propulsion unit is Rotax 912 SUL engine in pusher configuration.
The fuel tanks with 2 x 50L capacity are installed in the bottom extensions of the fuselage. The removable sponsons mounted on both sides of the bottom part of fuselage help to keep the stability of the aircraft on water level.
|Wing span||11 m|
|Wing area||10,1 m2|
|Tail span||2,4 m|
|Empty weight||320 kg|
|Max. take-off weight||495 kg|
|Fuel capacity||2x 50 L|
Flight characteristics (ROTAX 912 UL, 100 hp)
|G-limits||+4g / -2g|
|Stall speed||64 km/h / 35 kt|
|Min. no-flap speed||85 km/h / 46 kt|
|Cruising speed||175 km/h / 95 kt|
|Mx. level speed||195 km/h / 105kt|
|Never exceed speed||210 km/h / 114 kt|
|Rate of climb||6 m/s / 1181 ft/min|
|Fuel consumption (150/180 km/h)||14/18 L/h|
is well-proven design used from our ATEC 321 FAETA aircraft.
The cantilever tapered backswept wing with SM 701 airfoil is a reinforced shell of carbon-fibre sandwich with carbon-fibre coating. The wing spar is made of laminated hard beech wood saturated with synthetic resin and is situated in 30% of wing depth. The ailerons are hinged on the rear spar. Slotted flaps are hinged on fiberglass hinges. Ailerons and flaps are all composite structure. Wing root ribs are made of carbon sandwich, other ribs are made of plastic foam. The main spar is welded of high quality CrMo steel tubes.
The fuselage consists of carbon-fiber sandwich. The bottom part is adapted to water operation. There are two seats in the cabin for the crew of 2 people seating behind. The front seat is the main pilot seat. The back seat is accessible after tilting the main seat forward. Both hand and foot control are double. The canopy is hinged on the nose and opens upward and forward. The dashboard with flight and engine instruments and flaps control are situated in front of the main seat. The backside of the front seat headrest is fitted with additional small dashboard with basic flight instruments. Two fuel tanks are each situated on the left and right hand side of the fuselage in the area of its extended lower surface. The covers of retracted main landing gear are the part of the rear surface of such extensions. The lower surface of the fuselage is fitted with sponsons with small nacelles on their ends to provide lateral stability on water and to avoid dipping of wingtips. Removable sponsons are made of composite. The centerwing is made of steel spar.
The tapered horizontal tailplane is made of all-composite structure. The spar consists of carbon spar cap. The coating of horizontal tail and rudder is made of carbon sandwich. The whole horizontal tail is taken from the certified ATEC Faeta ultralight aircraft. The tail fin of the vertical surface is an integral part of the fuselage. It has a wide sweep angle of 45°. The vertical tail rudder is made of all-carbon sandwich. Inside the vertical tail rudder is installed small sliding rudder which enables better control of the aircraft on the water level. The rudder steering is installed inside the cabin and is accessible from the main pilot´s seat.
The undercarriage intended for ground operation consists of tricycle retractable landing gear. The nose gear is steerable and electrically retractable forward. The nose gear consists of steel struts and carbon composite wheel fork with 4“ wheel. The shock absorber is made of compressive rubber spring. The main gear consists of steel frame on torsion tube. Swinging arms are damped by rubber silentblocks. The main gear is electrically retractable into the side extensions of the lower part of the fuselage. It is fitted with 4“ wheels with hydraulic brakes. The brakes control is mounted on control stick of the pilot. For water take-off and landing is intended hull-shaped bottom part of the fuselage with landing gear retracted.
Hand steering and pedals are doubled. Ailerons are controlled by duraluminium rods. The elevator is controlled by the rod leading from control stick to the engine wall, and then by stainless steel ropes. The elevator trim is electrical. The tail rudder is controlled by ropes leading to rear pedals and then connected to duraluminium rods leading to front pedals. The nose wheel is controlled by rods leading from rear pedals to the bushing in waterproof engine wall, and then by stainless steel ropes from the wall to the nose wheel control lever. The small sliding rudder is steered by stainless steel wire and operated from the main front seat. Slotted flaps are controlled electrically.
The propulsion unit and fuel system
The propulsion unit consists of Rotax 912 SUL engine in pusher configuration and the 2- or 3- blades propeller by FITI. Fuel tanks capacity is 2 x 50L. The fuel valve is operated from the main front seat. Additional electric fuel pump is a part of the fuel system. The fuel amount in tanks is measured by the capacity fuel gauges.
There is a lot of options and alternative solutions available to install according to customer´s requirements. The aircraft can be equipped same with usual basic analog instruments as with the most advanced electronic flight and engine monitoring systems and GPS navigation. The aircraft can be equipped with flight recorder, autopilot and with wide range of various types of radios, transponders, ELT transmitters etc...The static and dynamic pressure is detected by Pitot tube installed on the underside of the left wing.