Abstract: A mount for coupling an engine to a vehicle includes an engine bracket to couple to the engine. The engine bracket includes a body that has a first end opposite a second end, and the body defines an offset coupling portion between the first end and the second end. The offset coupling portion protrudes from the body between the first end and the second end to define a receptacle. The mount includes a vehicle bracket to couple to the vehicle. The vehicle bracket includes a first bracket end opposite a second bracket end. The first bracket end is offset from the second bracket end and the first bracket end is received within the receptacle to couple the engine bracket to the vehicle bracket.

Abstract: A system and method for an improved thrust reverser is provided. The provided thrust reverser employs hidden linkage assemblies to decrease drag in the engine exhaust flow and increase turbine engine performance. The hidden linkage assemblies are placed in a space between the blocker door and the transcowl, thereby not affecting the engine exhaust flow.

Abstract: A system and method for an improved thrust reverser is provided. The provided thrust reverser employs hidden linkage assemblies to decrease drag in the engine exhaust flow and increase turbine engine performance. The hidden linkage assemblies are placed in a space between the blocker door and the transcowl, thereby not affecting the engine exhaust flow.

Abstract: A thrust reverser system for a turbine engine includes a support structure, a transcowl, and a door. The transcowl is mounted on the support structure and is axially translatable, relative to the support structure, between first and second positions. The door is pivotally coupled to the support structure and is rotatable, about a pivot axis, between stowed and deployed positions when the transcowl translates between the first and second positions, respectively. The door has an internal surface and a balance plane, and pressure forces acting along the balance plane effectively creates no moment about the pivot axis. The internal surface of the door has a first surface area forward of the balance plane and a second surface area aft of the balance plane, and the second surface area substantially exceeds the first surface area.

Abstract: A torque limiter for use on an aircraft comprises a drive shaft having a toothed outer portion, an output shaft, and a spline having an aperture therethrough for receiving the toothed portion. The spline is configured to rotationally couple the drive shaft to the output shaft and to rotationally disengage from the output shaft when the torque at the drive shaft exceeds a predetermined torque threshold. The spline comprises an outer annular portion and an inner annular portion configured to receive a lubricant. The inner annular portion comprises a plurality of circumferentially-spaced tooth structures and root structures. At least one of the root structures has at least one slot therein for receiving and retaining the lubricant.