Abstract: An aircraft having an electric motor coupled to a rotor and an instrument electronically connected to the electric motor and configured to communicate a time available value before a motor condition reaches a motor condition limit.

Abstract: A cyclic stick for transmitting control commands to blades of a rotorcraft via at least one transmission member, including a grip configured for engagement with a pilot's hand, a control arm and at least one locking mechanism. The control arm has a bottom end configured for connection to the transmission member(s) and for rotational connection to a base support structure, and a top end pivotally connected to the grip. The control arm includes first and second arm portions pivotally connected to each other, the first arm portion defining the bottom end, the second arm portion defining the top end. The locking mechanism(s) selectively prevent a relative pivoting motion between the first and second arm portions and a relative pivoting motion between the second arm portion and the grip. A method of adjusting a position of a grip of a cyclic stick in a rotorcraft cabin is also discussed.

Abstract: Systems and methods include providing an aircraft with a fuselage, an airframe that provides structural rigidity to the fuselage, and at least one door that allows access to an interior of the fuselage through an opening in the fuselage. The aircraft includes an overlapping, tongue and groove door interface formed between a frame of the door and a portion of the airframe that at least partially borders the opening in the fuselage. At least a portion of the airframe includes a concavity. At least a portion of the door frame includes a complementary shaped profile to the concavity of the airframe. The complementary profile of the door frame and the concavity of the airframe form a seal between the door frame and the airframe when the complementary portion is at least partially received within the concavity by selectively rotating the door to its closed position.

Abstract: A helicopter includes a full authority digital engine controlled (FADEC) engine, a first two-position throttle switch disposed on a first collective control stick, the first two-position throttle switch being movable between a Fly position and an Idle position, and a second two-position throttle switch disposed on a second collective control stick, the second two-position throttle switch being movable between a Fly position and an Idle position.