An internal structural reinforcement element for fuselages, where the internal structural reinforcement element has a longitudinal direction adapted for its placement in the longitudinal direction of the fuselage and a transversal direction perpendicular to the longitudinal direction, comprising:



an external reinforcement element,
an internal reinforcement element, located internally to the external reinforcement element in the transversal direction of the structural element,
where both reinforcement elements are manufactured from resin-impregnated fibre, and
an intermediate element, located between the external reinforcement element and the internal reinforcement element in the transversal direction of the structural element, the intermediate element being manufactured from pre-impregnated composite material.