History of the Equator
  Number One Testbed

The first Equator testbed P-300 A1 is a 6 seater research and development engineering airplane without compromises in it's aerodynamics. 
The primary and secondary structure was made from fiber composite. 
The Lycoming IO-540 engine with 290 hp at 2575 RPM is mounted in the fuselage near the center of gravity with cooling fan and flywheel clutch to the filament winded drive shaft.

The two bladed Hoffmann wooden propeller is mounted in the vertical fin. It is a constant speed propeller with reversing capability with 90'' in diameter turning only 2160 RPM. Therefore the noise was reduced to a sound like a fan at very high efficiency. 
The wet wing at a 40' span has a Wortmann laminar airfoil, variable geometry with double slotted flaps along it's full span. It was controlled by spoilerons on the upper side. The wing had a boundary layer control by the engine cooling fan. 
  Number Two Testbed  
The second Equator testbed Turbo P-420 is a wide body 8 seater. The primary and secondary structure is made from fiber composite. The Allison turbine engine with 420 SHP is mounted in the vertical fin. The wet wing with 44 ft wingspan has a Wortmann laminar airfoil, variable geometry with slotted flaps and flaperons along it's full span. 
Propulsion above the fuselage ahead of the empenage is without any doubt the best location aerodynamically. Although, there are disadvantages not apropriate for everydays flying.  
The experience from the two testbeds above was used for todays MODULAR SYSTEM for the Equator  
Propulsion is still located above the fuselage, but now above the center of gravity. Therefore most any type of engine is available to the Equator. Piston engines were test flown, turboprop engines were evaluated sucessfully for installation.