A gas turbine engine assembly comprising: a gas turbine engine comprising a compressor section and a turbine section; and a nacelle surrounding the gas turbine engine, wherein the compressor section or the turbine section comprises a plurality of stages that define a blade-off zone extending substantially radially from the compressor section or the turbine section and across the nacelle, the nacelle comprising: a thrust reverser movable between a stowed position and a deployed position; and a locking system configured to selectively prevent movement of the thrust reverser from the stowed position, the locking system comprising a locking mechanism and an actuator configured to actuate the locking mechanism, wherein the locking mechanism is positioned aft of the blade-off zone defined across the nacelle and the actuator is positioned fore of, or at least partially within, the blade-off zone, and the actuator is engaged with the locking mechanism via a rotatable transmission shaft, wherein: the blade-off zone extends at a 5° angle forward of a first stage and at a 5° angle aft of a final stage of said plurality of stages; or the blade-off zone extends at a 15° angle forward of a first stage and at a 15° angle aft of a final stage of said plurality of stages; or the compressor section comprises the plurality of stages and the blade-off zone extends at a 10° angle forward of a first stage and at a 10° angle aft of a final stage of said plurality of stages. a gas turbine engine comprising a compressor section and a turbine section; and a nacelle surrounding the gas turbine engine, wherein the compressor section or the turbine section comprises a plurality of stages that define a blade-off zone extending substantially radially from the compressor section or the turbine section and across the nacelle, the nacelle comprising: a thrust reverser movable between a stowed position and a deployed position; and a locking system configured to selectively prevent movement of the thrust reverser from the stowed position, the locking system comprising a locking mechanism and an actuator configured to actuate the locking mechanism, wherein the locking mechanism is positioned aft of the blade-off zone defined across the nacelle and the actuator is positioned fore of, or at least partially within, the blade-off zone, and the actuator is engaged with the locking mechanism via a rotatable transmission shaft, wherein: the blade-off zone extends at a 5° angle forward of a first stage and at a 5° angle aft of a final stage of said plurality of stages; or the blade-off zone extends at a 15° angle forward of a first stage and at a 15° angle aft of a final stage of said plurality of stages; or the compressor section comprises the plurality of stages and the blade-off zone extends at a 10° angle forward of a first stage and at a 10° angle aft of a final stage of said plurality of stages. a thrust reverser movable between a stowed position and a deployed position; and a locking system configured to selectively prevent movement of the thrust reverser from the stowed position, the locking system comprising a locking mechanism and an actuator configured to actuate the locking mechanism, wherein the locking mechanism is positioned aft of the blade-off zone defined across the nacelle and the actuator is positioned fore of, or at least partially within, the blade-off zone, and the actuator is engaged with the locking mechanism via a rotatable transmission shaft, wherein: the blade-off zone extends at a 5° angle forward of a first stage and at a 5° angle aft of a final stage of said plurality of stages; or the blade-off zone extends at a 15° angle forward of a first stage and at a 15° angle aft of a final stage of said plurality of stages; or the compressor section comprises the plurality of stages and the blade-off zone extends at a 10° angle forward of a first stage and at a 10° angle aft of a final stage of said plurality of stages. the blade-off zone extends at a 5° angle forward of a first stage and at a 5° angle aft of a final stage of said plurality of stages; or the blade-off zone extends at a 15° angle forward of a first stage and at a 15° angle aft of a final stage of said plurality of stages; or the compressor section comprises the plurality of stages and the blade-off zone extends at a 10° angle forward of a first stage and at a 10° angle aft of a final stage of said plurality of stages.