Abstract: A ram air turbine (RAT) is provided and includes a turbine assembly including blades and a hub to which the blades are connected, a generator or a pump and a drivetrain mechanically interposed between the turbine assembly and the generator or the pump. Each blade includes an exterior, airfoil-shaped structure defining an interior and support structures disposed within the interior which connect with an inner surface of the exterior, airfoil-shaped structure and which define hollow regions within the interior.

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 ram air turbine has turbine blades connected to rotate a transmission shaft. The transmission shaft is connected to drive a first gear which is engaged to drive a second gear. The second gear is connected to rotate an output shaft extending through a strut away from the transmission shaft. A governor arrangement is configured to change a pitch angle of the blades in response to speed, and includes counterweights acting on a spring in the governor arrangement. The governor spring is positioned on an opposed side of the strut relative to the turbine.

Abstract: A ram air turbine (RAT) is provided and includes a turbine assembly including blades and a hub to which the blades are connected, a generator or a pump and a drivetrain mechanically interposed between the turbine assembly and the generator or the pump. Each blade includes an exterior, airfoil-shaped structure defining an interior and support structures disposed within the interior which connect with an inner surface of the exterior, airfoil-shaped structure and which define hollow regions within the interior.

Abstract: A ram air turbine has turbine blades connected to rotate a transmission shaft. The transmission shaft is connected to drive a first gear which is engaged to drive a second gear. The second gear is connected to rotate an output shaft extending through a strut away from the transmission shaft. A governor arrangement is configured to change a pitch angle of the blades in response to speed, and includes counterweights acting on a spring in the governor arrangement. The governor spring is positioned on an opposed side of the strut relative to the turbine.

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 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 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 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 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 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 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.

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.

Abstract: A sensor assembly for sensing relative movement between adjacent panels includes a base and first and second arms pivotally mounted to the base. An electrical connecting element is attached to the first and second arms and holds the first and second arms in a first position to indicate a first condition. When the first and second arms have moved relative to each other by a predetermined amount, the electrical connecting element breaks to indicate a second condition.

Abstract: A sensor assembly for sensing relative movement between adjacent panels includes a base and first and second arms pivotally mounted to the base. An electrical connecting element is attached to the first and second arms and holds the first and second arms in a first position to indicate a first condition. When the first and second arms have moved relative to each other by a predetermined amount, the electrical connecting element breaks to indicate a second condition.