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Aviation History
1969
1969 - 0126.PDF
RIGHT Internationa/, U January 1969 PART ONE ttM-LAST (WATER) OBSERVERS SEATS 0000 WL 200 (REE) SECTION 41- FWD ELECTRONICS VHFAlARKER. ANTENNA.. -SECTION 45- Si niii'iniiiTrrirV, II^.IIIJ TV CAMER CONTAINERIZED BA6GAGE* CARGO THE CONFIGURATION of the Boeing 2707-300 is the result of a re-evaluation of the SST programme objectives that was conducted during 1968. The 2707-300. it is claimed, provides the most balanced combination of performance, flying qualities and operational characteristics of all configurations considered during the re-evaluation. It represents a departure from previous SST designs because of the incorporation of a high-lift delta wing of moderate span in contrast to either a variable-sweep or a tailless-delta design of previous proposals. The use of a horizontal tail for longitudinal trim and control permits the use of high-lift devices and of increased span to assist in meeting the take-off and landing-performance objec tives. The structure is primarily of titanium alloy to permit cruising flight at Mach 2.7 at altitudes of 60,000ft to 70,000ft. Power is by four General Elecrtic GE4/J5P afterburning turbojets. each delivering 63,0001b thrust at take-off. The 2707-300 design is the result of an integrated effort to provide a balanced combination of high- and low-speed performance, flying characteristics, passenger safety and com fort, and adaptability to expected airline and airport opera tional requirements. The passenger cabin is 176ft long of constant width for five-abreast over most of its length, permitting an a!l-tourist seating arrangement for 234 passengers and accommodating the installation of five lavatory and five galley compartments. A lower forward containerised cargo compartment provides 1.053 cu ft of volume and an aft lower compartment provides an additional 300 cu ft of bulk cargo capacity. A conventional flight deck is arranged for operation by two pilots and a flight engineer, with seating provided behind the captain for two observers. A pivoting forebody with sliding visor is installed to meet requirements for forward vision at low speeds. Advanced instrumentation for all-weather landing is included. The engines are installed in separate pods incorporating associated inlet and nozzle components. The inlet is of the axisymmetric translating-spike type. An ADS (accessory drive system) consisting of a gearbox, shaft-powered from the engine power take-off, mounted in the wing trailing-edge adjacent to each engine. Each ADS serves two hydraulic pumps and an electrical generator. The engine starter and a boost compressor for the environmental control system are separately mounted directly to an engine-driven gearbox within each nacelle. The fuel system consists of integral tanks within the wing and tailcone. The aircraft will be trimmed during transonic flight by a
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