Supersonic Transport Development Program. Phase Iii. Boeing Model 2707. Accessory Drive Subsystem Specification PDF Download
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Author: BOEING CO SEATTLE WA SUPERSONIC TRANSPORT DIV.
Publisher:
ISBN:
Category :
Languages : en
Pages : 54
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Book Description
This specification defines the objectives, criteria, and configuration and establishes the requirements for performance, design, test, and qualification of the accessory drive subsystem (ADS) for the prototype model supersonic transport airplane. Differences between the prototype and production airplanes are described. There are four ADS per airplane, one for each engine. The ADS is the power link between the engine, the starter, and the accessories.
Author: BOEING CO SEATTLE WA SUPERSONIC TRANSPORT DIV.
Publisher:
ISBN:
Category :
Languages : en
Pages : 54
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Book Description
This specification defines the objectives, criteria, and configuration and establishes the requirements for performance, design, test, and qualification of the accessory drive subsystem (ADS) for the prototype model supersonic transport airplane. Differences between the prototype and production airplanes are described. There are four ADS per airplane, one for each engine. The ADS is the power link between the engine, the starter, and the accessories.
Author: Grant W. Ort
Publisher:
ISBN:
Category :
Languages : en
Pages : 41
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Book Description
This specification defines the objectives, criteria, and configuration, and establishes the requirements for performance, design, test and qualification of the starting subsystem (SS) for the prototype model supersonic transport airplane. Differences between the prototype and production airplanes are described in Supplement I. The SS provides for starting and windmill braking of the engine, drives the accessory drive subsystem (ADS) and its attached accessories in the engine disconnect mode, and supplies ground source or engine bleed air to the environmental control subsystem (ECS).
Author: L. A. Jones
Publisher:
ISBN:
Category :
Languages : en
Pages : 75
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Book Description
This specification defines the objectives, criteria, and configuration and establishes the requirements for performance, design, test, and qualification of the primary ac, primary dc and standby electrical power systems for the prototype model supersonic transport airplane. Differences between the prototype and production electrical power subsystems are described in Supplement I. It covers the generation, conversion, control, protection, energy storage, monitoring, and distribution of electric power to all equipment that requires such power for proper functioning of the airplane. The primary ac electric power source of the airplane requires a mechanical power input from the accessory drive defined by specification D6A10089-1. Performance of the electric utilization equipment associated with other aircraft subsystems is defined in those subsystem specifications. Performance of the lighting subsystem is defined in Part II of this specification.
Author: BOEING CO SEATTLE WA SUPERSONIC TRANSPORT DIV.
Publisher:
ISBN:
Category :
Languages : en
Pages : 33
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Book Description
Contents: Requirements; Performance; Subsystem Definition; Design and Construction; Quality Assurance Provisions; Engineering Test and Evaluation; Preliminary Qualification Test; Formal Qualification Tests; Reliability Test and Analysis; and Product Performance and Configuration Requirements/Quality Verification Cross Reference Index.
Author: George G. Burton
Publisher:
ISBN:
Category :
Languages : en
Pages : 163
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Book Description
Author: L. G. Dhoors
Publisher:
ISBN:
Category :
Languages : en
Pages : 69
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Book Description
This specification defines the objectives, criteria, and configuration, and establishes the requirements for performance, design, test, and qualification for the Aircraft Engine Installation Subsystem (AEIS) for the prototype model supersonic transport airplane. Differences between the prototype and production airplanes are described. The subsystem provides the total propulsive power required by the airplane for accomplishing its intended functions. The subsystem also provides mechanical and pneumatic power for supporting airframe accessory, environmental and air inlet subsystems. The subsystem contains the engine, exhaust and thrust reverser assembly, engine accessories, engine mounting provisions, engine controls, cowling, bleed air ducting, instrumentation plumbing and wiring.
Author: John Katzinski
Publisher:
ISBN:
Category :
Languages : en
Pages : 76
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Book Description
This specification establishes the requirements for performance, design, test, and qualification for the Airframe Subsystem as applied to the prototype model supersonic transport airplanes. The airframe subsystem consists of the fuselage, empennage, wing and control surfaces.
Author: S. E. Lindstrom
Publisher:
ISBN:
Category :
Languages : en
Pages : 47
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Book Description
This specification defines the objectives, criteria, and configuration and establishes the requirements for performance, design, test, and qualification of the fuel subsystem for the prototype model supersonic transport airplane. This subsystem provides for the storage, distribution and management of fuel.
Author: George G. Burton
Publisher:
ISBN:
Category :
Languages : en
Pages : 126
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Book Description
This specification defines the objectives, criteria and configuration and establishes the requirements for performance, design, test, and qualification of the flight deck subsystem as applicable to the prototype supersonic transport airplane. Differences between the prototype and production airplanes are described in Supplement I. (Author).
Author: E. See
Publisher:
ISBN:
Category :
Languages : en
Pages : 143
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Book Description
This specification defines the objectives, criteria, and configuration and establishes the requirements for performance, design, test, and qualification of the flight controls and hydraulic subsystem for the B-2707 supersonic transport airplane. Differences between the prototype and production airplanes are described in Supplement I. This subsystem shall provide control of the airplane in response to pilot or guidance-navigation commands and furnish hydraulic power to the landing gear subsystem. This subsystem shall consist of primary flight controls, secondary flight controls, automatic flight controls and hydraulic power. (Author).
