the longitudinal axis x of the rear fuselage 11 and also comprises a shield 41 located in the vertical plane of symmetry a a of the rear fuselage configured for avoiding the risk of an impact of a detached part of one engine on the opposite engine the shield 41 has a suitable geometric configuration so that the possible trajectories of a detached part of one engine that would potentially reach the critical components of the opposite engine will cross the shield 41 and a suitable energy absorption capability to stop said detached part to avoid that it can reach the opposite engine fig4 a and 4 b show a geometric configuration of a shield 41 obtained as an envelope of straight borders of the intersections of the vertical plane of symmetry of the aircraft with those possible trajectories of detached fragments of one engine that impact on critical elements of the opposite engine the set of possible trajectories 51 see fig5 of detached fragments to be considered is obtained associating to a pre selection of fragments taking into account all engine stages rotor turbine propellers their possible trajectories in a failure event the critical elements of the opposite engine are defined as those elements that cannot.