Abstract: This hydraulic directional valve for an aircraft servo-control, for example for controlling the air brake flaps of the wings of an aircraft, comprises a plug 12 rotatively mounted in a fixed liner 13 disposed in a body 15 and connected to a control device, and an annular sleeve 14 interposed between the plug 12 and the liner 13, ports 19, 23, 26 for the inlet under pressure and the outlet of a hydraulic fluid being provided in the liner 14 and the sleeve 13, and passages being provided on the periphery of the plug 12 for ensuring the circulation of the hydraulic fluid. According to the invention, the sleeve 14 is rotatively mounted in the body 15 and projects outside the body 15 and is connected to rotate with a lateral lever 32 associated with a feedback device constituting a feedback loop which is capable of causing the sleeve 14 to copy automatically the angular position of the plug 12 after the pilot of the aircraft has commanded a rotation of the plug 12.