A control device (50) for controlling the variation of the angle of attack of the blades (8) of the anti-torque rotor (4) for an aircraft (1) capable of hovering is described, comprising a control element (16) sliding along a first axis (A) with respect to a shaft (6) of the rotor (4) and rotatable integrally therewith; the control element (16) is operatively connected to a plurality of blades (8) articulated on the shaft (6) in order to vary the angle of attack thereof following a translation of the element (16) itself along the axis (A); a control rod (10) axially sliding along the axis (A) with respect to the shaft (6) and angularly fixed with respect to the axis (A); and a rolling bearing (17) interposed between the control rod (10) and the control element (16), sliding along the axis (A) with respect to the shaft (6) and integrally with the control rod (10); the control device (50) comprises a threaded element (51) screwed onto the control rod (10) and cooperating with the bearing (17) to constrain it axially with respect to the control rod (10) and a bushing (52) coupled in an angularly and axially fixed manner to the threaded element (51), and in an angularly fixed manner to the control rod (10).