A method for managing a cooling device for a turbine casing of a turbofan aircraft engine extending along an axis, the engine comprising a fan downstream of which extends a compressor, a combustion chamber and a turbine comprising a turbine casing: - a primary vein in which a primary flow circulates, said primary vein passing through, in particular, in the direction of circulation of the primary flow, a compressor, a combustion chamber and the turbine comprising a turbine casing, - a secondary vein into which flows a secondary flow from the fan and distinct from the primary flow, the secondary vein extending around the primary vein, the turbojet engine comprising a device for cooling a turbine casing of the turbine of the turbojet engine, said cooling device comprising air-distribution means configured to take in air and convey it to the casing, the air-distribution means comprising at least a first ramp (20a, 20b) and a second ramp (20a, 20b) extending circumferentially about the axis respectively on a first circumferential portion and on a second circumferential portion different from each other, each ramp (20a, 20b) comprising air ejection orifices intended to be directed towards the casing in order to cool it, the cooling device comprising adjustment means capable of adjusting the flow rate of air ejected at the first ramp (20a, 20b) with respect to the flow rate of air ejected at the second ramp (20a, 20b), each ramp (20a, 20b) extending circumferentially about the axis of the turbojet engine and being located radially outside the turbine casing, the air ejection orifices of the ramps (20a, 20b) being turned towards the said turbine casing, the air intake and supply means being capable of taking in air from the secondary vein, the method comprising the steps of: - logging along two different axes, for example two orthogonal axes, the accelerations experienced by the airframe and/or propulsion system of the aircraft, - determining the eccentricity of the rotor from the measured accelerations, - adjusting the adjusting means so as to adapt the air flow rate ejected at the first ramp (20a, 20b) to the air flow rate ejected at the second ramp (20a, 20b). - a primary vein in which a primary flow circulates, said primary vein passing through, in particular, in the direction of circulation of the primary flow, a compressor, a combustion chamber and the turbine comprising a turbine casing, - a secondary vein into which flows a secondary flow from the fan and distinct from the primary flow, the secondary vein extending around the primary vein, each ramp (20a, 20b) extending circumferentially about the axis of the turbojet engine and being located radially outside the turbine casing, the air ejection orifices of the ramps (20a, 20b) being turned towards the said turbine casing, the air intake and supply means being capable of taking in air from the secondary vein, the method comprising the steps of: - logging along two different axes, for example two orthogonal axes, the accelerations experienced by the airframe and/or propulsion system of the aircraft, - determining the eccentricity of the rotor from the measured accelerations, - adjusting the adjusting means so as to adapt the air flow rate ejected at the first ramp (20a, 20b) to the air flow rate ejected at the second ramp (20a, 20b). - logging along two different axes, for example two orthogonal axes, the accelerations experienced by the airframe and/or propulsion system of the aircraft, - determining the eccentricity of the rotor from the measured accelerations, - adjusting the adjusting means so as to adapt the air flow rate ejected at the first ramp (20a, 20b) to the air flow rate ejected at the second ramp (20a, 20b).