Patent ID: 8713911

Claim:
A thrust reverser assembly for use in a turbofan engine assembly, the engine assembly including a core gas turbine engine, a core cowl which circumscribes the core gas turbine engine, a nacelle positioned radially outward from the core cowl to define a fan nozzle duct between the core cowl and a portion of the nacelle, the nacelle including a stationary cowl, said thrust reverser assembly comprising: a first translating cowl slidably coupled to the nacelle, said first translating cowl positionable with respect to the stationary cowl; a second translating cowl slidably coupled to the nacelle such that said first translating cowl is positioned between the stationary cowl and said second translating cowl, said second translating cowl positionable with respect to said first translating cowl; an actuator coupled to a positioning assembly, said positioning assembly operatively coupled to said first translating cowl and said second translating cowl for selectively moving said first translating cowl and said second translating cowl; and an actuator lock coupled to said actuator to releasably lock said second translating cowl to the stationary cowl.