Aircraft turbine engine comprising variable-pitch propeller blades

An assembly comprising a propeller vane and a system for setting the pitch of the vane about a pitch setting axis, for an aircraft turbine engine, the vane having a root extending from an upper end connected to a blade of the vane to a free lower end, the system for setting the pitch of the vane comprising a cup which is radially delimited by an annular wall extending around the pitch setting axis, the cup comprising a bottom wall and an upper opening through which the root is intended to be inserted axially into the cup, the free lower end of the root being nested axially into a housing of the bottom wall having a cross-section complementary to that of the free lower end of the root in order to connect the cup and the vane in rotation about the pitch setting axis,

• wherein the root of the vane comprises at least one radial limiting face which is intended to cooperate with at least one associated radial stop face of the cup in order to limit the rotation of the vane in an orientation about the pitch setting axis with respect to the cup in the event of failure of the lower end of the root.