An aircraft landing gear shock absorber strut (50, 70, 80, 90) comprising: an outer cylinder having an inner surface defining a cylinder bore extending into the outer cylinder from a first axial face of the outer cylinder, the cylinder bore defining an oil chamber; a sliding tube being movably mounted within the cylinder bore so as to be movable along the cylinder bore between: a compressed position in which a first free end portion of the sliding tube disposed outside of the bore is relatively close to the first axial face of the outer cylinder; and an extended position in which the first free end portion of the sliding tube is relatively far from the first axial face of the outer cylinder; a separator piston movably mounted within a blind bore to separate a gas chamber within the blind bore from the oil chamber such that, as the sliding tube moves from the extended position to the compressed position, oil within the oil chamber forces the separator piston to move to compress the gas within the gas chamber; one or more dynamic seals arranged within the cylinder bore between the inner surface of the outer cylinder and an outer surface of the sliding tube to inhibit oil within the oil chamber passing the dynamic seals as the sliding tube moves between the extended and compressed positions; a damping pin; and a flow restricting plate extending across the blind bore and having an orifice through which the damping pin axially moves as the sliding tube moves between the extended and compressed positions, wherein the damping pin is coupled to the separator piston so as to move with the separator piston, characterised in that the shock absorber strut is for damping landing loads and supporting the weight of an aircraft when it is on the ground. an outer cylinder having an inner surface defining a cylinder bore extending into the outer cylinder from a first axial face of the outer cylinder, the cylinder bore defining an oil chamber; a sliding tube being movably mounted within the cylinder bore so as to be movable along the cylinder bore between: a compressed position in which a first free end portion of the sliding tube disposed outside of the bore is relatively close to the first axial face of the outer cylinder; and an extended position in which the first free end portion of the sliding tube is relatively far from the first axial face of the outer cylinder; a compressed position in which a first free end portion of the sliding tube disposed outside of the bore is relatively close to the first axial face of the outer cylinder; and an extended position in which the first free end portion of the sliding tube is relatively far from the first axial face of the outer cylinder; a separator piston movably mounted within a blind bore to separate a gas chamber within the blind bore from the oil chamber such that, as the sliding tube moves from the extended position to the compressed position, oil within the oil chamber forces the separator piston to move to compress the gas within the gas chamber; one or more dynamic seals arranged within the cylinder bore between the inner surface of the outer cylinder and an outer surface of the sliding tube to inhibit oil within the oil chamber passing the dynamic seals as the sliding tube moves between the extended and compressed positions; a damping pin; and a flow restricting plate extending across the blind bore and having an orifice through which the damping pin axially moves as the sliding tube moves between the extended and compressed positions, wherein the damping pin is coupled to the separator piston so as to move with the separator piston, characterised in that the shock absorber strut is for damping landing loads and supporting the weight of an aircraft when it is on the ground.