A system for a fault tolerant strut shrink, comprising: an aircraft having an airframe and a wheel well comprising an envelope; a landing gear (12, 14, 16) comprising a trunnion and a shrink strut having a strut piston coupled to an axle having wheels, wherein the landing gear pivots at the trunnion about a trunnion axis; a controller in communication with the landing gear (12, 14, 16); the system further comprising a latch, comprising: a first rocker arm; a first inboard pivot coupled to a first end of the first rocker arm, wherein the first rocker arm is coupled to the airframe within the envelope of the wheel well via the first inboard pivot; a first outboard pivot coupled to a second end of the first rocker arm opposite the first end of the first rocker arm; a second rocker arm; a second inboard pivot coupled to a first end the second rocker arm, wherein the second rocker arm is coupled to the airframe within the envelope of the wheel well via the second inboard pivot; a second outboard pivot coupled to a second end of the second rocker arm opposite the first end of the second rocker arm; and a cradle coupled to the first rocker arm at the first outboard pivot joint and to the second rocker arm at the second outboard pivot joint, the cradle comprising stirrups located relatively inboard of the wheels; wherein the cradle is configured to retain the wheels in response to an extension of the shrink strut generating a contact between the wheel and the stirrups; and wherein the latch is configured such that, in response an uncommanded unshrink event, the first rocker arm and the second rocker arm are compressed due to the wheels being driven into contact with the stirrups by the strut piston, and wherein the contact between the stirrups and the wheels drives the axle toward the trunnion axis and compresses the strut piston during a deployment of the landing gear such that the wheels clear the envelope of the wheel well during the deployment of the landing gear. an aircraft having an airframe and a wheel well comprising an envelope; a landing gear (12, 14, 16) comprising a trunnion and a shrink strut having a strut piston coupled to an axle having wheels, wherein the landing gear pivots at the trunnion about a trunnion axis; a controller in communication with the landing gear (12, 14, 16); the system further comprising a latch, comprising: a first rocker arm; a first inboard pivot coupled to a first end of the first rocker arm, wherein the first rocker arm is coupled to the airframe within the envelope of the wheel well via the first inboard pivot; a first outboard pivot coupled to a second end of the first rocker arm opposite the first end of the first rocker arm; a second rocker arm; a second inboard pivot coupled to a first end the second rocker arm, wherein the second rocker arm is coupled to the airframe within the envelope of the wheel well via the second inboard pivot; a second outboard pivot coupled to a second end of the second rocker arm opposite the first end of the second rocker arm; and a cradle coupled to the first rocker arm at the first outboard pivot joint and to the second rocker arm at the second outboard pivot joint, the cradle comprising stirrups located relatively inboard of the wheels; wherein the cradle is configured to retain the wheels in response to an extension of the shrink strut generating a contact between the wheel and the stirrups; and wherein the latch is configured such that, in response an uncommanded unshrink event, the first rocker arm and the second rocker arm are compressed due to the wheels being driven into contact with the stirrups by the strut piston, and wherein the contact between the stirrups and the wheels drives the axle toward the trunnion axis and compresses the strut piston during a deployment of the landing gear such that the wheels clear the envelope of the wheel well during the deployment of the landing gear.