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This document describes the Boeing Model 2707 Warranty Program that will be offered to airline customers for the United States Supersonic Transport (SST). During Phase II-C, Boeing solicited the airlines for their warranty recommendations. Airline suggesstions, coupled with Boeing's subsonic warranty experience and comprehensive analysis of supersonic warranty needs and the presently planned development program for the SST, provided the basis for the B-2707 Warranty Program set forth. This program will minimize financial risks associated with introducing the supersonic transport and will provide a further incentive for the manufacturer to design, develop, and build an airplane that is safe, reliable, and economically attractive.
This specification establishes the requirements for performance, design, test, and qualification of the Ground Support Equipment (GSE) required for the B-2707. Included are the general design requirements applicable to all GSE designed for the B-2702, a consolidated list of the GSE arranged by system requirements, and individual specification data for each item of equipment. This combined specification provides requirements planning information and technical data on all of the GSE presently identified. A prime consideration in GSE planning and definition has been to use existing inventory, existing standard, or modified standard GSE whenever possible. The extensive use of equipment in these categories for B-2707 support is indicated on the consolidated list. GSE identification is an output of the system engineering analysis process, which is continuously applied to define and verify the B-2707 support requirements. The specification will be refined and updated throughout the prototype development program to provide a current definition of the GSE requirements for effective and efficient air carrier ground operations.
This appendix to Volume M-II, provides the evaluation team with detail PERT programming data. Appendix A contains Documentation Working Data and current PERT Networks used in developing the proposed Master Plan for the SST Program. Appendix B contains the latest printouts available at the time of proposal submittal. (Author).
Detail PERT programming data is provided. Appendix A contains Documentation Working Data and current PERT Networks used in developing the proposed Master Plan for the SST Program. Appendix B contains the latest computer printouts available at the time of proposal submittal.
Includes a mid-December issue called Buyer guide edition.
The NACA and aircraft propulsion, 1915-1958 -- NASA gets to work, 1958-1975 -- The shift toward commercial aviation, 1966-1975 -- The quest for propulsive efficiency, 1976-1989 -- Propulsion control enters the computer era, 1976-1998 -- Transiting to a new century, 1990-2008 -- Toward the future
The purpose of this manual is to provide recovery system engineers in government and industry with tools to evaluate, analyze, select, and design parachute recovery systems. These systems range from simple, one-parachute assemblies to multiple-parachute systems, and may include equipment for impact attenuation, flotation, location, retrieval, and disposition. All system aspects are discussed, including the need for parachute recovery, the selection of the most suitable recovery system concept, concept analysis, parachute performance, force and stress analysis, material selection, parachute assembly and component design, and manufacturing. Experienced recovery system engineers will find this publication useful as a technical reference book; recent college graduates will find it useful as a textbook for learning about parachutes and parachute recovery systems; and technicians with extensive practical experience will find it useful as an engineering textbook that includes a chapter on parachute- related aerodynamics. In this manual, emphasis is placed on aiding government employees in evaluating and supervising the design and application of parachute systems. The parachute recovery system uses aerodynamic drag to decelerate people and equipment moving in air from a higher velocity to a lower velocity and to a safe landing. This lower velocity is known as rate of descent, landing velocity, or impact velocity, and is determined by the following requirements: (1) landing personnel uninjured and ready for action, (2) landing equipment and air vehicles undamaged and ready for use or refurbishment, and (3) impacting ordnance at a preselected angle and velocity.