Patent ID: 8251313

Claim:
An aircraft, comprising: a fuselage defining a longitudinal center axis of the aircraft; first and second wings extending from opposite sides of the fuselage, each wing defining a leading edge, said each wing further defining first and second sections along a length thereof; a first engine offset from the center axis on a first side of the fuselage and generally rearward of the first wing leading edge, said first engine being disposed on a first vertical side of the first wing; a second engine offset from the center axis on a second, opposite side of the fuselage and generally rearward of the second wing leading edge, said second engine being disposed on the first vertical side of the second wing; an anti-ice subsystem configured solely along a first portion of the leading edge of the first section of each wing, wherein the first sections are aligned with the first and second engines on the first and second wings, and wherein the first portion is only on the first vertical side of the first and second wings; and a subsystem, capable of performing a de-icing function only, configured on the first section of each wing solely along a second portion, opposite the anti-ice subsystem, said second portion being on a second vertical side of the first and second wings; wherein the anti-ice subsystem prevents ice from forming on, and subsequently detaching from, the wing at a location where said detached ice can contact the first and second engines and the de-ice subsystem allows ice to form on, and be subsequently detached from the wing at a location where detaching ice passes around the first and second engines.