The invention relates to a structural configuration of the rear fuselage (4) of an aircraft with propeller engines (1) comprising propellers (23) formed in turn by blades (3), the mentioned propeller engines (1) being located at the rear part of the aircraft and the empennage (5) of the aircraft in turn being located behind the plane of the propellers (23), characterized in that the structural configuration of the rear fuselage (4) comprises an outer skin (6) and an inner skin (7), both skins (6, 7) being joined by means of radial elements (13) configuring cells (14), such that the obtained structural configuration maximizes the torsional strength of the rear fuselage (4) of the aircraft in the event of damage of the mentioned rear fuselage (4) due to the detachment of one of the blades (3) of the propeller engines (1).
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