Landing gear for an aircraft provided with a first longitudinal support skid and a second longitudinal support skid together with a cross-member referred to as a "front cross-member " and a cross-member referred to as a "rear cross-member ", each extending transversely between the first skid and the second skid, the landing gear comprising at least one damping device arranged on at least one of said cross-members called a "damped cross-member ", said damping device comprising a damper, characterised in that said damping device comprises: - a demultiplication means referred to as a "first demultiplication means " and a demultiplication means referred to as a "second demultiplication means ", each demultiplication means (30,40) being articulated to said damped cross-member and being suitable for being articulated to a fuselage of said aircraft, - each demultiplication means (30, 40) comprising: ∘ a bell-crank (50, 50') articulated to said damped cross-member by an articulation referred to as a "first articulation (81, 81')" defining a first longitudinal axis of rotation (810,810'), said bell-crank (50, 50') being provided with a first segment (51, 51') extending from a first free end (53, 53') to a first root (54, 54'), said bell-crank (50, 50') being provided with a second segment (52, 52') extending from a second free end (55, 55') to a second root (56, 56') secured to the first root, said first free end comprising an articulation referred to as a "second articulation (82, 82')" defining a second longitudinal axis of rotation (820, 820'), ∘ a link rod (60, 60') extending from a first end zone (61, 61') to a second end zone (62, 62'), said first end zone (61, 61') being articulated to said second free end (55, 55') by an articulation referred to as a "third articulation (83, 83')" defining a third longitudinal axis of rotation (830, 830'), said second end zone (62, 62') comprising an articulation suitable for being fastened to said fuselage and referred to as a "fourth articulation (84, 84')" which defines a fourth longitudinal axis of rotation (840, 840'), - the damper articulated to the second articulation of the first demultiplication means and to the second articulation of the second demultiplication means. - a demultiplication means referred to as a "first demultiplication means " and a demultiplication means referred to as a "second demultiplication means ", each demultiplication means (30,40) being articulated to said damped cross-member and being suitable for being articulated to a fuselage of said aircraft, - each demultiplication means (30, 40) comprising: ∘ a bell-crank (50, 50') articulated to said damped cross-member by an articulation referred to as a "first articulation (81, 81')" defining a first longitudinal axis of rotation (810,810'), said bell-crank (50, 50') being provided with a first segment (51, 51') extending from a first free end (53, 53') to a first root (54, 54'), said bell-crank (50, 50') being provided with a second segment (52, 52') extending from a second free end (55, 55') to a second root (56, 56') secured to the first root, said first free end comprising an articulation referred to as a "second articulation (82, 82')" defining a second longitudinal axis of rotation (820, 820'), ∘ a link rod (60, 60') extending from a first end zone (61, 61') to a second end zone (62, 62'), said first end zone (61, 61') being articulated to said second free end (55, 55') by an articulation referred to as a "third articulation (83, 83')" defining a third longitudinal axis of rotation (830, 830'), said second end zone (62, 62') comprising an articulation suitable for being fastened to said fuselage and referred to as a "fourth articulation (84, 84')" which defines a fourth longitudinal axis of rotation (840, 840'), ∘ a bell-crank (50, 50') articulated to said damped cross-member by an articulation referred to as a "first articulation (81, 81')" defining a first longitudinal axis of rotation (810,810'), said bell-crank (50, 50') being provided with a first segment (51, 51') extending from a first free end (53, 53') to a first root (54, 54'), said bell-crank (50, 50') being provided with a second segment (52, 52') extending from a second free end (55, 55') to a second root (56, 56') secured to the first root, said first free end comprising an articulation referred to as a "second articulation (82, 82')" defining a second longitudinal axis of rotation (820, 820'), ∘ a link rod (60, 60') extending from a first end zone (61, 61') to a second end zone (62, 62'), said first end zone (61, 61') being articulated to said second free end (55, 55') by an articulation referred to as a "third articulation (83, 83')" defining a third longitudinal axis of rotation (830, 830'), said second end zone (62, 62') comprising an articulation suitable for being fastened to said fuselage and referred to as a "fourth articulation (84, 84')" which defines a fourth longitudinal axis of rotation (840, 840'), - the damper articulated to the second articulation of the first demultiplication means and to the second articulation of the second demultiplication means.