An aircraft landing gear shock absorbing strut (10) comprising: an outer cylinder (12) defining a bore; a sliding tube (16) slidably coupled within the bore to move between a first position, which corresponds to the shock absorbing strut (10) being in a compressed condition, and a second position, which corresponds to the shock absorbing strut (10) being in an extended condition, the outer cylinder (12) and sliding tube (16) together defining an internal chamber that varies in volume in accordance with the extension state of the shock absorbing strut (10), wherein the shock absorbing strut (10) is arranged to divide the internal chamber into a first spring chamber and a second spring chamber, the first spring chamber being a pneumatic chamber containing a first gas, the first spring chamber being arranged to compress the first gas when the shock absorbing strut (10) moves from the extended condition to the compressed condition to provide compression damping to the shock absorbing strut (10) as the gas is compressed during compression of the shock absorbing strut (10), the second spring chamber containing a second gas and a hydraulic liquid, the second spring chamber being arranged to compress the second gas when the shock absorbing strut (10) moves from the extended condition to the compressed condition, the second spring chamber containing one or more damping orifices through which the oil passes as the shock absorbing strut (10) extends to provide recoil damping during extension of the shock absorbing strut (10).