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This SAE Aerospace Standard (AS) defines the nomenclature for surface finishes commonly used for sheet and strip in aerospace material specifications. It is applicable to steel and to iron, nickel, cobalt, and titanium base alloys.

This SAE Aerospace Information Report (AIR) provides information to be considered when performing the safety assessment of electrified propulsion aircraft. Its main focuses are: ● Typical new technologies introduced by electrified propulsion and their impact on safety ● The failure modes of electrified propulsion systems and their components ● Potential effects of failures at system and aircraft levels ● Possible strategies to minimize failures and mitigate their effects The information in this document may be used to generate inputs for system and aircraft safety assessments based on industry standards such as SAE ARP4761. The first issue of this document addresses battery systems, power electronics, eMotors, electrical interconnects and thermal management for fully electric configurations. Future issues are expected to address other subsystems, components and configurations.

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No scope is available.

This document covers the recommended practice for determining the acceptability of the dendrite arm spacing (DAS) of D357-T6 aluminum alloy castings required to have tensile strength not lower than 50 ksi (345 MPa).

This procurement specification covers aircraft quality self-locking nuts for wrenching (hex, spline) and anchor (plate, gang channel, shank) types of nuts made from a corrosion and heat-resistant nickel-base alloy of the type identified under the Unified Numbering System as UNS N07001. Tension height nuts having overall length of threaded portion not less than 1.2 times the nominal thread diameter have 1210 MPa minimum tensile strength at room temperature. Shear height nuts having shorter threaded portion have 1100 MPa minimum tensile strength at room temperature. Maximum test temperature of parts is 730 °C.

This specification covers a magnesium alloy in the form of extruded bars, rods, wire, tubing, and profiles up to 40 square inches (258 cm2) in cross-sectional area (solids) and up to 8.5 inches (216 mm) OD by 1.188 inches (30.18 mm) wall thickness (tubing) (see 8.5).

This document covers flexible and semiflexible, reinforced and unreinforced air hoses fabricated from laminated and impregnated fabric, intended for use in aircraft heating, air conditioning, ventilating, defrosting, and/or deicing systems.

No scope available.

SCOPE IS UNAVAILABLE.

This specification covers an aluminum alloy in the form of alclad sheet and plate supplied in the -T861 temper.

This specification covers an aluminum alloy in the form of alclad coiled sheet from 0.010 to 0.128 inch (0.25 to 3.25 mm), inclusive, in thickness supplied in the -T4 temper (see 8.5).

This specification covers a titanium alloy in the form of welding wire (see 8.5).

This procurement specification covers the requirements for metal tube support clamps comprising of two spring clips made of corrosion and heat resistant steel and the associated PTFE single split cushion that supports the tube. See Figure 1.

This SAE Aerospace Information Report (AIR) lists military and industry specifications, standards, recommended practices, and information reports applicable to aerospace hydraulic and pneumatic systems and components.