PROPULSIVE ASSEMBLY FOR AIRCRAFT

A propulsive assembly for aircraft comprising an engine, a nacelle arranged around the engine and a pylon supporting the engine, the nacelle including two engine cowls and reversing cowls, each cowl having an internal skin, characterized in that at least one of the cowls of the nacelle comprises at least one box arranged in a space situated between the internal skin of the cowl and the engine, the box delimiting a volume of inert material, the inert material being flame retardant foam. This box partially blocks a zone of the engine where a fire is likely to begin, which makes it possible to limit the volume of a fire zone of the engine, and thus reduce the quantity of extinguishing agent which is necessary to extinguish a fire in the zone of the engine concerned.