Abstract: An integrated power plant installation system for underwing high-bypass mid-length fan air duct core-mounted engines readily permits disconnection of the entire powerplant at the wing thereby virtually eliminating the necessity of disconnecting the engine and complex systems per se from the support strut when engine replacement or removal proves necessary. Excessive congestion within the vicinity of the strut box structure is eliminated by disposing the engine accessories, and auxiliary equipment and system lines, within the lower quadrant of the powerplant assembly in both a laterally and longitudinally distributed array. Potential catastrophic fire hazards within the nacelle are substantially eliminated by routing the fluid lines and electrical conduits axially aft and upwardly around the circumference of the engine within the nozzle section of the powerplant aft of all rotating discs.

Abstract: There is disclosed a simplified, lightweight, easily stowed thrust control device for the hot core exhaust flow of a jet engine. The device is mounted in the engine strut fairing, downstream of the nozzle exit plane to reduce exposure to the high exhaust temperatures. In a blocking position, the mounting hardware, actuator and actuator linkage is located so as to be cooled by both free stream and fan air, providing a longer operating life, less maintenance and more reliable operation. Simplified construction and mounting arrangement permit the device to be readily retrofitted on existing installations.

Abstract: A nacelle assembly including an inlet channel, an exterior cowl, a fan channel, and a turbine exhaust nozzle is directly mounted on a turbofan jet propulsion engine. The engine in turn is shock mounted directly on a strut, in turn affixed to an aircraft. A central portion of the outer cowl is hinged to open in a clam shell manner about hinges positioned adjacent the strut location to expose the fan casing and engine accessories for maintenance and removal. A rearward portion of the nacelle assembly is formed in two D-duct structures that are also hinged to open in a clam shell manner about hinges positioned adjacent the strut location. The D-duct structures include portions of the outer cowl and of the fan duct walls. When the D-duct structures are open, the turbine casing of the turbofan engine is exposed for maintenance, repair and removal. A pair of beams, affixed at one end to the aircraft fuselage, and enclosed by an aerodynamic fairing, constitute the mounting strut.