Patent ID: 7819359

Claim:
An aircraft firewall ( 12 ) separating first and second compartments ( 1 and 2 ) of said aircraft, said first compartment ( 1 ) containing a plurality of elements, the firewall ( 12 ) being provided with a first wall ( 3 ) inserted in a structure ( 5 ) of the aircraft and having a first surface ( 3 ′) facing said first compartment ( 1 ), and is provided with regulator means ( 4 , 13 ) for maintaining a maximum temperature of said first surface ( 3 ′) of the first wall ( 3 ) at a predetermined temperature value lower than a self-combustion temperature of said elements, wherein said aircraft is a rotorcraft, a power transmission gearbox being arranged in said first compartment ( 1 ), and a turboshaft engine ( 9 ) being disposed in said second compartment ( 2 ).