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Standard

Rings, Sealing, Butadiene-Acrylonitrile (Nbr) Rubber Synthetic Lubricant Resistant 67-75

2018-10-09
WIP
AMS7272H
This specification covers a butadiene-acrylonitrile (NBR) rubber in the form of molded rings. These rings have been used typically as sealing rings in contact with diester synthetic lubricants in service up 150 degrees C (302 degrees F), but usage is not limited to such applications. The cross-section of such rings is usually not over 0.275 inch (6.98 mm) in diameter or thickness.
Standard

Rubber: Flourocarbon (FKM), High Temperature/Fluid Resistant, Low Compression Set/ 85 to 95 Hardness, For Seals in Fuel Systems and Specific Engine Oil Systems

2018-10-09
WIP
AMS7259F
This specification covers a fluorocarbon (FKM) rubber in the form of O-rings, O-ring cord, compression seals, and molded-in-place gaskets for aeronautical and aerospace applications. These products have been used typically as sealing rings, compression seals, O-ring cord, and molded-in-place gaskets in contact with air and a wide variety of fuels, lubricants, and specific hydraulic fluids but usage is not limited to such applications. Each application should be considered individually. This class of fluoroelastomers is not recommended for use in high temperature stabilized, “HTS”, engine oils. Each “HTS” oil should be evaluated separately. This fluorocarbon rubber has a typical service temperature range of -20 to +400 °F (-29 to +204 °C) in air.
Standard

Quality Program Guidelines for Deicing/Anti-Icing of Aircraft on the Ground

2018-10-07
WIP
ARP5646A
The scope of the Quality Program Guidelines, in the format of a checklist, is to help ensure compliance with the current documents as listed in §2 "Applicable Documents " that meet Airline Operator's and regulatory requirements. It is the responsibility of all other personnel that performs the deicing/anti-icing task to adhere to these requirements.
Standard

Steel, Corrosion Resistant, Wire, 17Cr - 7.1Ni - 1.1Al, Cold Drawn, Precipitation-Hardenable

2018-10-05
WIP
AMS5678G
This specification covers a corrosion-resistant steel in the form of wire, cold drawn to condition C and capable of being precipitation heat treated to condition CH900.

This wire has been used typically for springs requiring corrosion resistance and resistance set up to 600 °F (316 °C), but usage is not limited to such applications. Where parts require welding during fabrication, strength of this cold-drawn wire will be impaired.

Standard

Heat Treatment Wrought Nickel Alloy and Cobalt Alloy Parts

2018-10-05
WIP
AMS2774F
This specification specifies the engineering requirements for heat treatment, by part fabricators (users) or their vendors or subcontractors, of parts made of wrought nickel or cobalt alloys, of raw materials during fabrication, and of fabricated assemblies in which wrought nickel or cobalt alloys are the primary structural components.
Standard

Terminal Junction System (TJS), Environment Resistant General Specification For

2018-10-04
WIP
AS81714C
This specification covers Terminal Junction System (TJS) components which are used for interconnection of wiring and incorporation of passive components (see 6.1). These environment resistant components have in common the use of crimp type external pin contacts in accordance with AS39029/1 for Series I or crimp type external socket contacts in accordance with AS39029/22 for Series II. This family of TJS components is designed to operate continuously over a temperature range of -65 to 200 °C, using any combination of temperatures generated by the electrical load and ambient temperature so that the maximum internal hot spot, combined temperature, will not exceed the maximum specified for the class of TJS component, unless otherwise specified.
Standard

In-Flight Thrust Determination

2018-10-04
WIP
AIR1703B
In-Flight Thrust Determination, SAE AIR1703 reviews the major aspects of processes that may be used for the determination of in-flight thrust (IFT). It includes discussions of basic definitions, analytical and ground test methods to predict installed thrust of a given propulsion system, and methods to gather data and calculate thrust of the propulsion system during the flight development program of the aircraft. Much of the treatment is necessarily brief due to space limitations. This document and the British Ministry/Industry Drag Analysis Panel (MIDAP) Guide (Reference 1.11), which SAE Committee E-33 used as a starting point, can be used to understand the processes and limitations involved in the determination of in-flight thrust. Application to a specific in-flight thrust determination program will require the use of many important assumptions not fully developed in this document, and these assumptions must be evaluated during the conduct of the program.
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