Abstract: 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.

Abstract: 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 laser distance sensor disposed inside the first actuator 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 laser distance sensor disposed inside the second actuator 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.

Abstract: A predictive system is provided and include a torque-limiter, a sensor disposed to sense a condition of the torque-limiter and a processing system. The processing system is coupled to the sensor and configured to process readings of the sensor, to calculate whether the condition of the torque-limiter is indicative of degradation or failure incidents based on the readings being processed and to determine whether an action should be taken based on a calculation result.

Abstract: A detent alignment mechanism assembly is provided and includes a shaft, a lock mechanism configured to selectively occupy an unlocked position at which the shaft is movable and a locked position at which the shaft is immovable, a detent mechanism coupled to the shaft and formed to define detent positions for the shaft to assume and move between and a detent alignment mechanism configured to provide to an operator of the shaft feedback and assistance corresponding to assumptions of the detent positions by the shaft during movements thereof by the operator.

Abstract: A retention member monitoring system for a slat-flap control lever assembly including a control lever movable over a range of discrete angular positions. Also included is a retention member engageable with the control lever to retain the control lever in each of the discrete angular positions. Further included is at least one electric device in communication with the retention member to determine the structural integrity of the retention member.

Abstract: A retention member monitoring system for a slat-flap control lever assembly including a control lever movable over a range of discrete angular positions. Also included is a retention member engageable with the control lever to retain the control lever in each of the discrete angular positions. Further included is at least one electric device in communication with the retention member to determine the structural integrity of the retention member.

Abstract: A predictive system is provided and include a torque-limiter, a sensor disposed to sense a condition of the torque-limiter and a processing system. The processing system is coupled to the sensor and configured to process readings of the sensor, to calculate whether the condition of the torque-limiter is indicative of degradation or failure incidents based on the readings being processed and to determine whether an action should be taken based on a calculation result.

Abstract: 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 laser distance sensor disposed inside the first actuator 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 laser distance sensor disposed inside the second actuator 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.

Abstract: A selector lever includes a detent pin that travels along a shaft for being positioned within a detent slot of a detent plate for securing the selector lever in place. A magnetic detent pin alignment mechanism provides feedback to an operator for assisting in maneuvering the selector lever to a predetermined position wherein the detent pin may be positioned within a desired detent slot.

Abstract: A selector lever that comprises a shaft rotatably attached to a pivot and arranged between two detent plates, each of the detent plates having a plurality of slots arranged for receiving a detent pin located on the shaft. Each of the plurality of slots on each of the two detent plates is defined by a radial depth. One or more of the plurality of slots is a failure detection slot having an extended radial depth. When one of the detent pins has failed, the opposing detent pin is allowed to travel into the extended radial depth when placed in the failure detection slot. This action reveals a failure indicator, providing a visual indication that one of the detent pins has failed.

Abstract: A detent alignment mechanism assembly is provided and includes a shaft, a lock mechanism configured to selectively occupy an unlocked position at which the shaft is movable and a locked position at which the shaft is immovable, a detent mechanism coupled to the shaft and formed to define detent positions for the shaft to assume and move between and a detent alignment mechanism configured to provide to an operator of the shaft feedback and assistance corresponding to assumptions of the detent positions by the shaft during movements thereof by the operator.

Abstract: A selector lever includes a detent pin that travels along a shaft for being positioned within a detent slot of a detent plate for securing the selector lever in place. A magnetic detent pin alignment mechanism provides feedback to an operator for assisting in maneuvering the selector lever to a predetermined position wherein the detent pin may be positioned within a desired detent slot.

Abstract: A selector lever with redundant detent pins and detent plates and a method for using the selector lever to test for a failure of one or more detent pins. The selector lever includes at least two slides for independently moving the detent pins within the detent plates. The independent slides allow one detent pin to remain engaged. With only one detent pin engaged, the operator may test the ability to move the shaft and conclude whether or not the detent pin has failed.

Abstract: 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.

Abstract: A selector lever with two detent plates and corresponding detent pins that travel along a shaft includes a float that moves with each of the detent pins. When a detent pin fails, a float pin remains engaged with a catch, thereby preventing rotational movement of the shaft.

Abstract: A selector lever with redundant detent pins and detent plates and a method for using the selector lever to test for a failure of one or more detent pins. The selector lever includes at least two slides for independently moving the detent pins within the detent plates. The independent slides allow one detent pin to remain engaged. With only one detent pin engaged, the operator may test the ability to move the shaft and conclude whether or not the detent pin has failed.

Abstract: A selector lever that comprises a shaft rotatably attached to a pivot and arranged between two detent plates, each of the detent plates having a plurality of slots arranged for receiving a detent pin located on the shaft. Each of the plurality of slots on each of the two detent plates is defined by a radial depth. One or more of the plurality of slots is a failure detection slot having an extended radial depth. When one of the detent pins has failed, the opposing detent pin is allowed to travel into the extended radial depth when placed in the failure detection slot. This action reveals a failure indicator, providing a visual indication that one of the detent pins has failed.

Abstract: A selector lever with redundant detent pins and detent plates and a method for using the selector lever to test for a failure of one or more detent pins. The detent plates include a plurality of slots connected by a channel that corresponds to a disengaged position, enabling the detent pin to be moved from one slot to another. The selector lever includes one or more obstructing features in the channels of the detent plates. The selector lever further includes indicators for comparing the location of the shaft with the location of the obstructing features while the slide is in the disengaged position.

Abstract: A selector lever with two detent plates and corresponding detent pins that travel along a shaft includes a float that moves with each of the detent pins. When a detent pin fails, a float pin remains engaged with a catch, thereby preventing rotational movement of the shaft.

Abstract: A disclosed sensor assembly for detecting movement and a position of a wing flap includes a sensing device that generates a signal corresponding to a position of the flap. The sensor assembly includes a linkage that is attached to the movable flap for mechanically communicating movement of the flap to the sensing device. The linkage includes a first pivot shaft mounted to the flap that is disposed about a first axis and a second pivot shaft attached to the first pivot shaft for movement about a second axis transverse to the first axis.