Abstract: A hydraulic shock absorber suitable for use with an aircraft landing gear which includes: a first casing member telescopically and sealingly engaged with a second casing member, the second casing member having a first section of reduced diameter in comparison to a second section; and an oil reservoir defined by the first and second casing members, which is divided into two distinct volumes by a one way restrictor attached to the second casing member. The volume of the oil reservoir defined by the first casing member and the first section of the second casing member is further divided into two sections by a two-way restrictor.