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 fixed 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 a rear edge; (c) wherein the translating inlet cowl is configured to be movably attached to one or more stationary portions of the engine such that the inlet cowl is selectively movable in the forward and aft directions relative to the fan case between a stowed flight position and an extended service position; (d) wherein the aft inlet lip edge is adjacent to the inner barrel forward edge when the inlet lip is in the stowed flight position, and the aft inlet lip edge is remote from the inner barrel forward edge when the inlet lip is in the extended service position; (e) the nacelle further comprising at least one linear actuator (170, 172) for selectively moving the translating inlet cowl between the stowed flight position and the extended service position; (f) wherein a plurality of movable electromechanical latches are circumferentially spaced around the inner barrel forward edge and configured for selectively latching the inlet lip aft inner edge to the inlet inner barrel forward edge in the stowed flight position and to disengage from the inlet lip to allow movement of the translating inlet cowl to the service position, each of the latches having an electrical actuator; and (g) characterised by each electromechanical latch including a catch pivotally mounted on a bracket; each bracket being attached to the inlet inner barrel proximate to the inner barrel forward edge; and each electrical actuator comprising a rotary solenoid to control movement and positioning of the catch between a latched position and a fully unlatched position. (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 fixed 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 a rear edge; (c) wherein the translating inlet cowl is configured to be movably attached to one or more stationary portions of the engine such that the inlet cowl is selectively movable in the forward and aft directions relative to the fan case between a stowed flight position and an extended service position; (d) wherein the aft inlet lip edge is adjacent to the inner barrel forward edge when the inlet lip is in the stowed flight position, and the aft inlet lip edge is remote from the inner barrel forward edge when the inlet lip is in the extended service position; (e) the nacelle further comprising at least one linear actuator (170, 172) for selectively moving the translating inlet cowl between the stowed flight position and the extended service position; (f) wherein a plurality of movable electromechanical latches are circumferentially spaced around the inner barrel forward edge and configured for selectively latching the inlet lip aft inner edge to the inlet inner barrel forward edge in the stowed flight position and to disengage from the inlet lip to allow movement of the translating inlet cowl to the service position, each of the latches having an electrical actuator; and (g) characterised by each electromechanical latch including a catch pivotally mounted on a bracket; each bracket being attached to the inlet inner barrel proximate to the inner barrel forward edge; and each electrical actuator comprising a rotary solenoid to control movement and positioning of the catch between a latched position and a fully unlatched position.