A control surface disconnect detection system includes a mechanical disconnect detection device that includes: a first contact element; a second contact element; and a mechanical fuse that includes a conduction path. In a normal operational state the conduction path creates an electrical pathway between the first contact element and second contact element and when in a control surface disconnected state the conduction path does not create an electrical pathway between the first contact element and the second contact element. The system also includes a radio frequency identification (RFID) tag connected to the first contact element and the second contact element such that when the mechanical disconnect detection device is in the normal operation state the RFID tag does not transmit information, and when the mechanical disconnect detection device is in the control surface disconnected state the RFID tag does transmit information.

A method of operating a skew detection system, configured for detecting skew in a control surface of one of wings of an aircraft, includes receiving an inboard signal from an inboard sensor and receiving an outboard signal from an outboard sensor. The inboard and outboard sensors have lines of sight intersecting toothed surfaces of gears of the inboard and outboard gears. Inboard distance and outboard distance travelled by the inboard and the outboard tracks respectively are determined using the inboard and outboard signals from the inboard and the outboard sensors. One of the inboard and the outboard distances is compared with a reference value. An alert indicative of an adverse situation is emitted if the one of the inboard and the outboard distances is different than the reference value.

An actuator system for controlling a flight surface of an aircraft includes a first actuator having a first actuator input and a first linear translation element that moves based on rotational motion received at the first actuator input and a first sensor coupled to the first linear translation element that generates a first output based on a displacement of the first linear translation element. The system also includes a second actuator having a second actuator input and a second linear translation element that moves based on rotational motion received at the second actuator input and a second sensor coupled to the second linear translation element that generates a second output based on a displacement of the second linear translation element. The system also includes a control unit that receives the first and second outputs and determines if an error condition exists for the system based on first and second output.

An actuation system for controlling flight control members of a vehicle. Each flight control member is controlled by two or more linear hydraulic actuators. Synchronization members extend between the hydraulic actuators on the same flight control members to synchronize the movements of the hydraulic actuators for consistent movement across the length of the flight control members. Brakes can maintain the positions of the synchronization members and thus the flight control members. Motors can provide for moving the synchronization members to control the positioning of the hydraulic actuators and flight control members.

A system for monitoring actuation of a flight control surface, the flight control surface being connected to a track that moves the flight control surface between at least a retracted position and an extended position, the system including a rack connected to the track, a pinion engaged with the rack and a rotation detector operatively connected to the pinion.

An actuator failure or disconnection detection device for an aircraft leading edge slat comprises a base and a biasing assembly mounted to the base and movable relative thereto. The base and biasing assembly are removably mountable between a fixed structure in the aircraft wing and the slat at an actuator location. The device further comprises an indicator for indicating the amount of movement of the biasing assembly in a direction towards the base when the slat is retracted towards the wing leading edge. The indicator may be a collar slidably mounted on the device.

An actuation system for controlling flight control members of a vehicle. Each flight control member is controlled by two or more linear hydraulic actuators. Synchronization members extend between the hydraulic actuators on the same flight control members to synchronize the movements of the hydraulic actuators for consistent movement across the length of the flight control members. Brakes can maintain the positions of the synchronization members and thus the flight control members. Motors can provide for moving the synchronization members to control the positioning of the hydraulic actuators and flight control members.

Methods and apparatus for operating flight control systems of aircrafts are disclosed. An example apparatus includes a flight control system including a processor to: based on data from first and second sensors, determine first and second values; based on the first and second values, determine a location of a jam in the flight control system, the location of the jam being determined based on a summation of the first and second values.

A sensor for detecting relative movement between two adjacent components includes a first member, a second member rotatable about an axis relative to the first member, and a fuse element including a first electrical contactor connected to the first member and a second electrical contactor connected to the second member. When the first member and the second member are skewed, the first electrical contactor and the second electrical contactor are not in electrical contact.

Methods, apparatus, and articles of manufacture for a distributed aircraft actuation system are disclosed. An example apparatus includes a non-responsive component detector to determine a position difference between a first position of a first control surface of an aircraft and a second position of a second control surface of the aircraft, the first position lagging the second position, and a command generator, in response to determining that the position difference satisfies a threshold, the command generator is to cease movement of the second control surface at the second position, attempt to move the first control surface to the second position, and cease movement of the first control surface when moved to the second position.