Abstract: An aircraft includes an airframe having an extending tail and a longitudinal axis extending from a nose of the airframe defining a length of the airframe. A counter rotating, coaxial main rotor assembly is located at the airframe and includes an upper rotor assembly and a lower rotor assembly. The upper rotor assembly and the lower rotor assembly rotate about an axis of rotation. The axis of rotation intersects the longitudinal axis forward of a midpoint of the longitudinal axis.

Abstract: An external cargo damping system includes lifting gear and a damping assembly. The lifting gear has a lifting body attachment end and an opposed external cargo end, and defines a load path that extends between the lifting body attachment and external cargo ends of the lifting gear. The damping assembly is connected in series with the lifting gear and is disposed along the load path to damp vibratory force transmitted between the lifting gear lifting body attachment and lifting gear ends.

Abstract: A method of controlling an aircraft in the event of pilot incapacity includes detecting, using at least one sensor, the occurrence of an event relating to a pilot's capacity to control the aircraft, determining whether the event justifies a controlled takeover of the aircraft from the pilot, asserting a controlled takeover of the aircraft from the pilot if it has been determined that a controlled takeover is justified, and executing a controlled landing of the aircraft without assistance of the pilot.

Abstract: A composite lug assembly includes a composite lug defining a loaded side and an unloaded side and having at least one hole extending therebetween, a shoulder bushing assembly including a first side bushing having a first cylindrical portion adapted to fit in the hole and a first shoulder portion extending from the first cylindrical portion and a second side bushing having a second cylindrical portion adapted to fit within the first cylindrical portion and a second shoulder portion extending from the second cylindrical portion wherein the first side bushing is made of a different material than the second side bushing.

Abstract: An aircraft flight mode selector assembly utilizes computer-generated menus and soft wired bezel keys to enable the use of a greater number of flight modes to be accessed in a smaller space than is presently possible with a flight mode selector consisting solely of conventional dedicated switches, switch indicator lights, and hard wired selector panel assemblies. Serial bus connections between the flight mode selector assembly and the flight control computer in the aircraft reduce the amount of wiring needed for the flight mode selector assembly, as compared to present protocol which utilizes dedicated wiring for each dedicated switch in the aircraft flight mode selector. The use of computer-generated displays and menus permits easy expansion of the flight mode selector assembly without the need to add additional switches and switch indicator lights.

Abstract: High speed machining of parts is greatly enhanced when the axial alignment between the machining tool, its tool holder assembly, and a tool driver assembly can be precisely maintained, preferably within about one ten thousandths of an inch, in order to achieve the utmost in machining precision in the parts being machined. In order to maintain this desired degree of alignment, the machining tool is mounted in an angularly adjustable holder assembly which mates with a complementary socket that forms a part of the tool driver assembly. The tool holder assembly can also be used to move the tool radially sideways in a rectilinear fashion relative to the tool driver assembly, if desired. The tool holder assembly, besides being able to adjust the alignment of the tool relative to the tool driver assembly, is also operative to securely clamp the tool to the tool driver assembly.

Abstract: A craft, such as an aircraft, landcraft, watercraft, space craft, or the like, is provided with a power transfer system which ensures an uninterrupted supply of electrical power to on board electrical equipment during normal switching from one power supply to another i.e., switching which is not due to system failure, which switching may be initiated either manually by the pilot, or automatically by the system. The power transfer system can be used with separate DC power sources, and includes a split bus assembly which ensures a continuous electrical equipment supply from a first operating power source until after a second different power source has been energized and begun to supply operating power to the electrical equipment in question. Once the second power supply is brought on line, the first power supply can be shut down. The system can be used when switching between different on board power supplies or when switching between on board and external power supplies.

Abstract: A fiberglass or other material skin is applied to a composite airfoil structure in a mold assembly having a partially compliant caul plate component which defines the shape of the lower surface of the airfoil. The caul plate component includes a first portion which is essentially rigid and which covers the leading edge of the airfoil. The rigid portion of the caul plate component provides improved conformation of the airfoil skin to the leading edge of the airfoil. The caul plate component also includes a compliant portion which covers and defines the shape of the trailing edge of the lower surface of the airfoil. The stiffness of the caul plate component also has a variable stiffness zone which interconnects the rigid and compliant portions thereof.