Turbine engine comprising an actuator and aircraft comprising such a turbine engine, and corresponding actuation method

Turbine engine comprising an actuator comprising a cylinder comprising a rod provided with a piston defining at least partially within the cylinder a first chamber and a second chamber, the actuator comprising a first fluid line and a second fluid line both fluidly connected to the first chamber, a resilient return means in a predetermined position disposed in one of the first chamber or the second chamber and configured to exert a force on the piston, the first fluid line comprising a calibrated port, the actuator comprising a two-way servo-valve fluidly connected to the second fluid line, a cross-sectional area of the two-way servo-valve being greater than or equal to ten times a cross-sectional area of the calibrated port or a head loss in the first fluid line being greater than or equal to ten times a head loss in the second fluid line, the turbine engine comprising a first fluid source and a second fluid source, wherein an element chosen from among the first fluid line and the second fluid line is configured to receive a first fluid from the first fluid source, and wherein a remaining element chosen among the first fluid line and the second fluid line is configured to take a second fluid from the second fluid source, a pressure of the first fluid being greater than a pressure of the second fluid, wherein the first fluid source comprises a compressor of the turbine engine, the second fluid comprising air under atmospheric pressure.