Patent ID: 8667802

Claim:
A nacelle inner cowl configured for placement between an outer cowl and an aircraft engine, the inner cowl comprising: a forward portion having a first front edge and a first aft edge; an aft portion having a second front edge and a second aft edge, wherein a largest radial distance between the inner cowl and a center axis of the inner cowl occurs at or forward of a location in which the forward portion and the aft portion meet or overlap; an actuator having a first element fixed relative to the forward portion and a second element configured to translate the aft portion in a forward-to-aft direction to decrease an exit area between the inner and outer cowl; and a first inner cowl half and a second inner cowl half, each comprising: a top edge extending from the forward portion's first front edge to the aft portion's second aft edge and configured to pivotally attach to opposing sides of a pylon, and a bottom edge extending from the forward portion's first front edge to the aft portion's second aft edge and configured to mechanically fasten and unfasten with each other.