Methods and apparatus for detecting airflow control surface skew conditions are disclosed herein. An example apparatus includes an aircraft wing, a support linkage, and a flap coupled to the aircraft wing via the support linkage. The example apparatus includes a sensor coupled to the flap at a location proximate to the support linkage. The sensor is configured to generate vibration data for the location. The example apparatus includes a detector communicatively coupled to the sensor. The detector is to detect a skew condition of the flap based on the vibration data.

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.

Methods and apparatus for detecting airflow control surface skew conditions are disclosed herein. An example apparatus includes an aircraft wing, a support linkage, and a flap coupled to the aircraft wing via the support linkage. The example apparatus includes a sensor coupled to the flap at a location proximate to the support linkage. The sensor is configured to generate vibration data for the location. The example apparatus includes a detector communicatively coupled to the sensor. The detector is to detect a skew condition of the flap based on the vibration data.

Disclosed is a system for monitoring wing control on an aircraft that includes a plurality of radio frequency identification device (RFID) tags attachable to a movable wing portion. The system includes a RFID reader attachable to a stationary wing portion and configured to communicate with at least two RFID tags, and a controller. The controller includes a processor connected to the RFID reader. The processor transmits at least two carrier signals via the RFID reader to the at least two RFID tags. Each of the transmitted carrier signals have a different carrier frequency. The processor also receives at least two reflected signals from the at least two RFID tags. The processor determines, based on the reflected signal from the at least two RFID tags, at least one of a motion of the movable wing portion and a distance of the movable wing portion.

To provide an improved monitoring, a monitoring arrangement for adaptable segments of an airfoil includes sensor cable segments, cable connections, and a signal data processor. The sensor cable segments are each configured to be attached between adjacent adaptable segments and to detect a spatial relative movement of the adjacent adaptable segments and to generate a signal representing the relative movement. The cable connections are configured to supply the signals of the sensor cable segments to the data processor. The data processor is configured to determine relative changes in a spatial arrangement of the adaptable segments based on the supplied signals.

A jam detection system for a flap of a wing of an aircraft includes a linkage coupled to the flap and a support of the wing, and a sensor configured to detect a position of at least a portion of the linkage. The sensor is further configured to compare the position of the least a portion of the linkage to a jam threshold to determine if a jam condition exists. The linkage can also be coupled to a carriage moveably coupled to the support.

A system for monitoring asymmetry between two components includes a comparator having a first input to receive a signal indicative of a position of a first component and a second input to receive a signal indicative of a position of a second component. The system also includes means for performing an integration of a plurality of output signals from the comparator indicative of the difference exceeding the threshold and means for outputting a command signal to actuate a brake in response to the integrating means determining that the number of times the difference exceeds the threshold is in excess of a given value.

A sensor system for a wing panel assembly of an aircraft includes a first end of a linkage assembly operatively coupled to a first slat panel. Also included is a second end of the linkage assembly operatively coupled to a second slat panel with a first ball joint. Further included is a block having a cutout portion surrounding the first ball joint. Yet further included is a sensing element disposed proximate the block to detect rotation of the block beyond a predetermined angle.

A flap skew detection system is configured to detect flap skew of one or more flaps moveably secured to one or more wings of an aircraft. The flap skew detection system includes a flap support assembly that couples a flap to a wing. The flap support assembly includes a fixed portion that is configured to secure to the wing, a moveable portion that is moveably coupled to the fixed portion and configured to securely support the flap, and a link moveably coupled to the fixed portion and the moveable portion. The link includes a cylinder defining an internal chamber including a hydraulic fluid chamber, a piston having a piston head within the internal chamber, and hydraulic fluid retained within the hydraulic fluid chamber. A pressure detector is fluidly coupled to the hydraulic fluid chamber. The pressure detector is configured to detect a fluid pressure of the hydraulic fluid pressure within the hydraulic fluid chamber. The fluid pressure detected by the pressure detector is used to determine existence of flap skew.

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.