An aircraft turbomachine module, comprising a first tubular casing with axis X, equipped with a first annular flange, and a second tubular casing with axis X, equipped with a second annular flange, assembled to the first annular flange by a plurality of studs (24, 24a, 24b) with axes C parallel to the axis X, distributed around the axis X, each stud passing through the second flange and comprising an end which projects from an external face of the second flange and which is able to receive a tightening nut, each stud (24, 24a, 24b) further comprising an intermediate stretch (34, 34a, 34b) of hexagonal shape, said turbomachine module comprising at least one locking plate applied to the second annular flange, which comprises a first orifice (38, 38a) received on said intermediate stretch (34, 34a) and at least two opposite walls (58, 58a) of which cooperate with said intermediate stretch (34, 34a) of hexagonal shape, said fitted plate comprising a body extending transversely with respect to the axis C, which is immobilised to prevent the rotation of said plate and that of the stud (24, 24a, 24b) about its axis, each plate being fitted on two immediately adjacent studs (24a, 24b) and the body comprising for this purpose, opposite the first orifice, a second orifice which is received on an intermediate stretch of an immediately adjacent stud and at least two opposite walls of which cooperate with said intermediate stretch of hexagonal shape of the immediately adjacent stud, characterised in that it comprises an annular sheet-metal attached between said first and second flanges (16, 18) by screws of axes B which are distributed around the axis X parallel to said axis X, and which are each arranged angularly between two consecutive studs, said screws each comprising an end projecting from an external face of the second flange, which is received with clearance in a recess formed in said body extending transversely of each fitted locking plate. said turbomachine module comprising at least one locking plate applied to the second annular flange, which comprises a first orifice (38, 38a) received on said intermediate stretch (34, 34a) and at least two opposite walls (58, 58a) of which cooperate with said intermediate stretch (34, 34a) of hexagonal shape, said fitted plate comprising a body extending transversely with respect to the axis C, which is immobilised to prevent the rotation of said plate and that of the stud (24, 24a, 24b) about its axis, each plate being fitted on two immediately adjacent studs (24a, 24b) and the body comprising for this purpose, opposite the first orifice, a second orifice which is received on an intermediate stretch of an immediately adjacent stud and at least two opposite walls of which cooperate with said intermediate stretch of hexagonal shape of the immediately adjacent stud, characterised in that it comprises an annular sheet-metal attached between said first and second flanges (16, 18) by screws of axes B which are distributed around the axis X parallel to said axis X, and which are each arranged angularly between two consecutive studs, said screws each comprising an end projecting from an external face of the second flange, which is received with clearance in a recess formed in said body extending transversely of each fitted locking plate.