Patent ID: 8181905

Claim:
A nacelle for a turbofan aircraft engine having a fan case with a fan case forward edge, the nacelle comprising: (a) an inlet inner barrel having an inner barrel forward edge and an inner barrel aft edge, the inner barrel aft edge being configured to be affixed to the fan case forward edge in a stationary position on the engine; (b) a translating inlet cowl having an inlet lip with an aft inlet lip edge and an outer skin with rear edge, the inlet cowl configured to be selectively movable in the forward and aft directions relative to the fan case, between a stowed flight position and an extended service position; c) at least two circumferentially spaced actuators constructed and arranged to generate an output for causing the translating inlet cowl to move in the forward and aft directions; and d) a plurality of electromechanical latches circumferentially spaced around the inner barrel forward edge and configured to engage an aft inner edge periphery of the inlet lip in the stowed flight position and to disengage from the inlet lip in the extended service position, each of the latches having an electrical actuator.