A lock-detecting system is configured to be installed in an aircraft to determine if a gust lock is emplaced on a flight control surface. The lock-detecting system includes at least one servo actuator and a computing device. The at least one servo actuator is associated with the flight control surface of the aircraft such that the servo actuator is configured to supply a force to a flight control surface when engaged. The computing device is configured to instruct the at least one servo actuator to actuate the flight control surface, acquire an indication that the flight control surface did not move in response to said actuation by the servo actuator, and alert a pilot to remove the gust lock from the flight control surface.

A high-lift actuation system for differentially actuating a plurality of high-lift surfaces of an aircraft is disclosed. An exemplary high-lift actuation system includes a plurality of independent drive devices for individually actuating the plurality of high-lift surfaces. The independent drive devices may include a power drive unit (PDU) arranged between an inboard actuator and an outboard actuator of a respective high-lift surface and an interconnecting driveline. The PDU of at least one independent drive device may include two motors having a respective motor output coupled together in a torque summing arrangement. A controller may be implemented with two independent control channels respectively coupled to one of the two motors.

A high-lift actuation system for differentially actuating a plurality of high-lift surfaces of an aircraft is disclosed. An exemplary high-lift actuation system includes a plurality of independent drive devices for individually actuating the plurality of high-lift surfaces. The independent drive devices may include a power drive unit (PDU) arranged between an inboard actuator and an outboard actuator of a respective high-lift surface and an interconnecting driveline. The PDU of at least one independent drive device may include two motors having a respective motor output coupled together in a torque summing arrangement. A controller may be implemented with two independent control channels respectively coupled to one of the two motors.

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.

Disclosed herein is a monobloc and removable pedal module for an aircraft rudder bar. The pedal module, which is intended for a rudder bar, includes a pedal, at least one integrated adjustment system, and a connection device which enables a removable connection of the pedal module to be produced. The pedal module is a monobloc component in order to simplify and facilitate its replacement via the removable connection obtained by the connection device.

Selector lever systems of aircraft are provided. The selector lever systems include a selector lever configured to control operation of one or more aircraft control surfaces, the selector lever having a handle configured to enable manual operation of the selector lever, a touch sensor arranged on the handle, and a controller arranged in communication with the touch sensor, the controller configured to at least one of generate a notification when a signal is received from the touch sensor and unlock the selector lever from a locked state.

Selector lever systems of aircraft are provided. The selector lever systems include a selector lever configured to control operation of one or more aircraft control surfaces, the selector lever having a handle configured to enable manual operation of the selector lever, a touch sensor arranged on the handle, and a controller arranged in communication with the touch sensor, the controller configured to at least one of generate a notification when a signal is received from the touch sensor and unlock the selector lever from a locked state.

A control input operable by a user for controlling movement of an aircraft includes a base portion configured for coupling to a support surface, the base portion biased towards a neutral position defined along a central axis and pivotable to a plurality of angular positions relative to the central axis. The control input also includes a grip portion having inputs for controlling movement of the aircraft and pivotally coupled to the base portion, the grip portion pivotable between a first position in which the grip portion extends from the base portion and a second position in which the grip portion is pivoted relative to the base portion. Further, the control input includes a lock mechanism for locking the grip portion in the first position wherein releasing the lock mechanism allows the grip portion to move to the second position.

A control input operable by a user for controlling movement of an aircraft includes a base portion configured for coupling to a support surface, the base portion biased towards a neutral position defined along a central axis and pivotable to a plurality of angular positions relative to the central axis. The control input also includes a grip portion having inputs for controlling movement of the aircraft and pivotally coupled to the base portion, the grip portion pivotable between a first position in which the grip portion extends from the base portion and a second position in which the grip portion is pivoted relative to the base portion. Further, the control input includes a lock mechanism for locking the grip portion in the first position wherein releasing the lock mechanism allows the grip portion to move to the second position.