An aircraft comprising: a tail cone (T); an engine compartment (C); a liquid cooled internal combustion power plant housed in the engine compartment (C) in the tail cone (T); and a cooling system for the liquid cooled internal combustion power plant , the cooling system comprising: a tail cone inlet defined through a wall (T2) of the tail cone (T) and fluidly communicating with an environment (E) outside the aircraft (A); a wall inlet (C6) defined through a firewall (C5) of the engine compartment (C), wherein the firewall (C5) is substantially transversal relative to the wall (T2) of the tail cone (T); a blower within the engine compartment (C) and having a blower inlet and a blower outlet , the blower inlet fluidly communicating with the environment (E) via the tail cone inlet , via the wall inlet (C6), and via an interior (I) of the engine compartment (C), the blower outlet defined through a wall of the aircraft (A) and fluidly communicating with the environment (E); and a cooling flow path (F1) extending from the tail cone inlet to an air outlet and across the wall inlet (C6), the cooling flow path (F1) configured for heat exchange relationship with the liquid cooled internal combustion power plant . a tail cone (T); an engine compartment (C); a liquid cooled internal combustion power plant housed in the engine compartment (C) in the tail cone (T); and a cooling system for the liquid cooled internal combustion power plant , the cooling system comprising: a tail cone inlet defined through a wall (T2) of the tail cone (T) and fluidly communicating with an environment (E) outside the aircraft (A); a wall inlet (C6) defined through a firewall (C5) of the engine compartment (C), wherein the firewall (C5) is substantially transversal relative to the wall (T2) of the tail cone (T); a blower within the engine compartment (C) and having a blower inlet and a blower outlet , the blower inlet fluidly communicating with the environment (E) via the tail cone inlet , via the wall inlet (C6), and via an interior (I) of the engine compartment (C), the blower outlet defined through a wall of the aircraft (A) and fluidly communicating with the environment (E); and a cooling flow path (F1) extending from the tail cone inlet to an air outlet and across the wall inlet (C6), the cooling flow path (F1) configured for heat exchange relationship with the liquid cooled internal combustion power plant . a tail cone inlet defined through a wall (T2) of the tail cone (T) and fluidly communicating with an environment (E) outside the aircraft (A); a wall inlet (C6) defined through a firewall (C5) of the engine compartment (C), wherein the firewall (C5) is substantially transversal relative to the wall (T2) of the tail cone (T); a blower within the engine compartment (C) and having a blower inlet and a blower outlet , the blower inlet fluidly communicating with the environment (E) via the tail cone inlet , via the wall inlet (C6), and via an interior (I) of the engine compartment (C), the blower outlet defined through a wall of the aircraft (A) and fluidly communicating with the environment (E); and a cooling flow path (F1) extending from the tail cone inlet to an air outlet and across the wall inlet (C6), the cooling flow path (F1) configured for heat exchange relationship with the liquid cooled internal combustion power plant . <EOS>