The invention concerns an aircraft turbomachine propeller comprising a plurality of blades (1) each comprising a root (20) mounted on a hub (2) rotating about the rotation axis of the propeller (I-I), and its purpose is to reduce the risks of loss of the entire blade (1) following an impact by a foreign body.To achieve this, at least one blade (1) comprises a means (30) of retaining the blade in an outwards radial direction, said retaining means (30) being engaged in a housing (5) of said blade (1) opening radially inwards at the root of the blade (20), and fixed in translation in said outwards radial direction.