Patent ID: 8256709

Claim:
An aircraft propeller-engine layout, comprising: an aircraft having a fuselage, the fuselage having a tail; first and second engines, each having a driving shaft, each engine being positionable in a tail of a fuselage of an aircraft; first and second propeller shafts; one propeller arrangement attached to each propeller shaft; first and second transfer shafts connecting the first and second propeller shafts respectively to the driving shafts of the first and second engines; wherein each propeller arrangement is disposed in a nacelle, connected to the fuselage of the aircraft via at least one pylon; wherein each pylon includes an air inlet for at least one of the first and second engines, the air inlet being remote from the first and second engines positionable in the tail of the fuselage of the aircraft; wherein an exhaust gas outlet of each of the first and second engines is arranged in the tail of the aircraft fuselage; and further comprising a reduction gear drive arranged in each nacelle, which is driven by one of the first and second shafts and connected to one of the first and second propeller shafts.