An actuator transfer assembly comprising an actuator (18), a driven object (16, 116), a pushrod (19) or shaft (119), a disconnect housing (24, 124), a transfer member (50) movable relative to the housing from a first position in mechanical engagement with the pushrod or shaft such that the housing translates or rotates with the pushrod or shaft and a second position in mechanical disengagement from the pushrod or shaft such that the housing does not translate or rotate with the pushrod or shaft, a bias element (34) biasing the transfer member towards the first position, and a retainer (44, 53) configured to automatically retain the transfer member in the second position when the transfer member moves from the first position, wherein the transfer member is configured to move from the first position to the second position when a force on the pushrod or a torque on the shaft exceeds a predetermined threshold breakout force or torque.

An actuator transfer assembly comprising an actuator (18), a driven object (16, 116), a pushrod (19) or shaft (119), a disconnect housing (24, 124), a transfer member (50) movable relative to the housing from a first position in mechanical engagement with the pushrod or shaft such that the housing translates or rotates with the pushrod or shaft and a second position in mechanical disengagement from the pushrod or shaft such that the housing does not translate or rotate with the pushrod or shaft, a bias element (34) biasing the transfer member towards the first position, and a retainer (44, 53) configured to automatically retain the transfer member in the second position when the transfer member moves from the first position, wherein the transfer member is configured to move from the first position to the second position when a force on the pushrod or a torque on the shaft exceeds a predetermined threshold breakout force or torque.

An inceptor apparatus for an aircraft having a primary inceptor member provided in the form of a stick member having a grip portion, at which the stick member can be gripped by a pilot's hand, and a secondary inceptor member provided at an upper portion of the primary inceptor member and having an actuating portion, at which the secondary inceptor member can be manually actuated by a pilot's thumb. Both inceptor members have associated a respective sensor assembly which is provided to generate electronic flight control signals or commands in response to at least one of i) pivoting movements of the respective inceptor member around each of two independent maneuvering axes associated to the inceptor member, ii) forces acting on or via the respective inceptor member in pivoting directions with respect to each of the maneuvering axes, and iii) lateral flexing or bending of the respective inceptor member.

An inceptor apparatus for an aircraft having a primary inceptor member provided in the form of a stick member having a grip portion, at which the stick member can be gripped by a pilot's hand, and a secondary inceptor member provided at an upper portion of the primary inceptor member and having an actuating portion, at which the secondary inceptor member can be manually actuated by a pilot's thumb. Both inceptor members have associated a respective sensor assembly which is provided to generate electronic flight control signals or commands in response to at least one of i) pivoting movements of the respective inceptor member around each of two independent maneuvering axes associated to the inceptor member, ii) forces acting on or via the respective inceptor member in pivoting directions with respect to each of the maneuvering axes, and iii) lateral flexing or bending of the respective inceptor member.

Systems and methods are provided for aircraft spoiler lockout. One embodiment is a system that includes a locking device that removably engages a control member inside a cockpit of an aircraft. The locking device restricts motion of the control member to prevent movement of wing surfaces of the aircraft. The system further includes a controller in communication with a wireless transmitter. The controller determines from a signal sent by the wireless transmitter whether both handheld switches connected to the wireless transmitter are being actively held. If so, the controller directs a supply of power to the locking device thereby causing the locking device to temporarily release the control member. Otherwise, the locking device restricts motion of the control member.

Systems and methods are provided for aircraft spoiler lockout. One embodiment is a system that includes a locking device that removably engages a control member inside a cockpit of an aircraft. The locking device restricts motion of the control member to prevent movement of wing surfaces of the aircraft. The system further includes a controller in communication with a wireless transmitter. The controller determines from a signal sent by the wireless transmitter whether both handheld switches connected to the wireless transmitter are being actively held. If so, the controller directs a supply of power to the locking device thereby causing the locking device to temporarily release the control member. Otherwise, the locking device restricts motion of the control member.

An aircraft may include a control lever movable along a lever path and configured to control a system of the aircraft, and a selectively engageable detent feature configured to inhibit travel of the control lever and operable in a disengaged configuration in which the control lever is movable along the lever path without restriction by the selectively engageable detent feature, and an engaged configuration in which the selectively engageable detent feature inhibits travel of the control lever at a particular location along the lever path.

An aircraft may include a control lever movable along a lever path and configured to control a system of the aircraft, and a selectively engageable detent feature configured to inhibit travel of the control lever and operable in a disengaged configuration in which the control lever is movable along the lever path without restriction by the selectively engageable detent feature, and an engaged configuration in which the selectively engageable detent feature inhibits travel of the control lever at a particular location along the lever path.

A lever outputs a first signal level where the first signal level is based at least in part on the position of the lever and the first signal level is used to control a first set of rotors associated with a vertical propulsion system. A thumb controller (coupled to the vertical thrust lever) outputs a second signal level where the second signal level is based at least in part on the position of the thumb controller, the second signal level is used to control a second set of rotors associated with a horizontal propulsion system, and the thumb controller includes a detent associated with a recommended sustained maximum.

A lever outputs a first signal level where the first signal level is based at least in part on the position of the lever and the first signal level is used to control a first set of rotors associated with a vertical propulsion system. A thumb controller (coupled to the vertical thrust lever) outputs a second signal level where the second signal level is based at least in part on the position of the thumb controller, the second signal level is used to control a second set of rotors associated with a horizontal propulsion system, and the thumb controller includes a detent associated with a recommended sustained maximum.