Author : W. H. Burrell
Publisher :
Page : 25 pages
File Size : 13,34 MB
Release : 1966
Category :
ISBN :
Contents: Requirements; Performance; Subststem Definition; Design and Construction; Quality Assurance Provisions; Engineering Test and Evaluation; Preliminary Qualification Tests; Formal Qualification/Certification Tests; Reliability tests and Analyses; Product Performance and Configuration Requirements/Quality Verification Crossreference Index.
Author : Paul E. Johnson
Publisher :
Page : 54 pages
File Size : 15,81 MB
Release : 1966
Category :
ISBN :
This specification establishes the requirements for the performance, test and qualification of the B-2707 (G.E.) propulsion subsystem. The General Electric GE4/J5G engine performance data is the primary data for the propulsion subsystem performance specification. Subsystem performance requirements established herein are design objectives for the prototype airplane. Application of these requirements to production airplane design will be established after prototype flight testing and evaluation.
Author : Paul E. Johnson
Publisher :
Page : 52 pages
File Size : 37,67 MB
Release : 1966
Category :
ISBN :
This specification establishes the requirements for the performance, test and qualification of the B-2707 (P and W) propulsion subsystem. The Pratt and Whitney JTF17A-20B engine performance data is the primary data for the propulsion subsystem performance specification. Subsystem performance requirements established herein are design objectives for the prototype airplane. Application of these requirements to production airplane design will be established after prototype flight testing and evaluation.
Author : R. E. Ensley
Publisher :
Page : 21 pages
File Size : 15,94 MB
Release : 1966
Category :
ISBN :
This specification establishes the requirements for performance, design, test and qualification of the Air Induction Subsystem. This subsystem shall provide the engine with the quantity of air demanded within the flow distortion limits of the engine. This subsystem requires a control subsystem and an anti-icing subsystem, and provides for high pressure recovery within the flow. The installation of the subsystem is defined by the Aircraft Engine Installation Subsystem Specification (D6A10113-1).
Author : Stanley E. Lindstrom
Publisher :
Page : 37 pages
File Size : 19,14 MB
Release : 1966
Category :
ISBN :
This specification establishes the requirements for performance design, test and qualification of the fuel system as applied to the prototype airplanes. This subsystem will provide for the storage, distribution and management of fuel. (Author).
Author : BOEING CO SEATTLE WA SUPERSONIC TRANSPORT DIV.
Publisher :
Page : 167 pages
File Size : 25,54 MB
Release : 1966
Category :
ISBN :
Author : Joseph Harris
Publisher :
Page : 47 pages
File Size : 47,28 MB
Release : 1966
Category :
ISBN :
Author : O. J. Olson
Publisher :
Page : 75 pages
File Size : 47,19 MB
Release : 1966
Category :
ISBN :
Contents: Applicable Documents, Requirements, Quality Assurance Provisions, Additional Data.
Author : BOEING CO SEATTLE WA SUPERSONIC TRANSPORT DIV.
Publisher :
Page : 41 pages
File Size : 15,26 MB
Release : 1966
Category :
ISBN :
This specification establishes the requirements for performance, design, test and qualification for the Aircraft engine Installation Subsystem. The subsystem is used to provide the total propulsive power required by the airplane for accomplishing its intended functions. The subsystem is also used to provide mechanical and pneumatic power for supporting airframe accessory, environmental and air inlet subsystems. The subsystem requires fuel, air flow, electrical and airframe support and control inputs for its operation. These are provided by the airframe fuel, air inlet, air inlet control, electrical, flight control, and airframe structure subsystems.
Author : E. J. Overmyer
Publisher :
Page : 41 pages
File Size : 47,86 MB
Release : 1966
Category :
ISBN :
This specification establishes the requirements for performance, design, test and qualification of the environmental control subsystem (hereinafter called the ECS), as applied to the prototype airplanes. The ECS consists of air source equipment, air conditioning equipment, cabin temperature and cabin pressure control equipment, and the air distribution system. The ECS shall provide a comfortable and safe environment for the crew and passengers, and shall provide the required cooling for the airplane equipment and cargo areas. (Author).
