The turbine-engine inlet flow distortion methodology addressed in this document applies only to the effects of inlet total-pressure distortion. Practices employed to quantify these effects are developing and therefore, periodic updates are anticipated. The effects of other forms of distortion on flow stability and performance and of any distortion on aeroelastic stability are not addressed. The guidelines can be used as necessary to create a development method to minimize the risk of inlet/engine compatibility problems. The degree to which guidelines for descriptor use, assessment techniques, and testing outlined in this document are applied to a specific program should be consistent with the expected severity of the compatibility problem.
This document covers bolts and screws made from a corrosion and heat resistant precipitation hardenable iron base alloy of the type identified under the Unified Numbering System as UNS S66286. The following specification designations and their properties are covered: AS7477: 130 ksi minimum ultimate tensile strength at room temperature 70 ksi stress-rupture strength at 1200 degrees F; and AS7477-1 130 ksi minimum ultimate tensile strength at room temperature 85 ksi minimum ultimate shear strength at room temperature. Primarily for aerospace propulsion system applications where a good combination of fatigue resistance, tensile strength, and resistance to relaxation at elevated temperatures is required.
This document describes the initial development, evolution, and use of reticulated polyurethane foam as an explosion suppression material in fuel tanks and dry bays. It provides historical data, design practice guidelines, references, laboratory test data, and service data gained from past experience. The products discussed in this document may be referred to as "Safety Foam," "Reticulated Polyurethane Foam," "Baffle and Inerting Material," "Electrostatic Suppression Material," or "SAFOAM." These generic terms for the products discussed in this document are not meant to imply any safety warranty. Each individual design application should be thoroughly proof tested prior to production installation.
This SAE Aerospace Recommended Practice (ARP) provides technical and application information needed by the designers of aircraft electric systems and support equipment for the selection of overcurrent protective devices. It provides definitions to permit comparisons of various electric circuit protective devices. Included also are recommended procedures for periodic visual and mechanical inspection criteria.
This SAE Aerospace Recommended Practice (ARP) addresses the general requirements for data recording procedures, packaging, and storing of aerospace elastomeric seals and seal assemblies which include an elastomeric element prior to the seal being assembled into hardware components. The requirement for packaging is an integral part of the controlled storage procedure and provides a means of positive product identity from the time of manufacture to the time of assembly into a component.