The invention relates to a configuration of engines (3) for aircraft located in the rear part of the fuselage (2) of said aircraft, the engines (3) being attached in a fixed manner by pylons (5) to the structure of the aircraft, said structure comprising a torsion box (14) which traverses the fuselage (2) and is used to attach the pylons (5), the fuselage (2) comprising an opening (4) allowing the passage of the suspension pylons (5) for the engines (3), said configuration further comprising a pivoting area (8), an actuator (7) and a fitting (6) through which the actuator (7) is attached to the suspension pylons (5) and to the torsion box (14) of the aircraft, such that the assembly formed by the actuator (7) and the fitting (6) allow balancing the pylon (5) and engine (3) assembly of the aircraft through the pivoting area (8), thus achieving controllable and optimal thrust vectoring of the aircraft for each flight phase.
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