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This SAE Aerospace Information Report (AIR) provides information on the possible methods of sealant removal. The discussion will focus on the methods of sealant removal and give the strengths and weaknesses of each method.

This SAE Recommended Practice establishes minimum performance and test requirements for combination pelvic and upper torso occupant restraint systems provided for off-road self-propelled work machines.

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 specification establishes the requirements for a waterborne, corrosion inhibiting, chemical and solvent resistant, anodic electrodeposition epoxy primer capable of curing at 200 to 210 °F (93 to 99 °C).

This standard establishes the recommended requirements for application of AMS3144 anodic electrodeposition primer to aerospace components. Adherence to these requirements will help facilitate satisfactory performance of the applied primer.

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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 establishes the requirements for coating systems having high durability for use as aircraft exterior surface finishes. These coating systems normally are comprised of a surface treatment, a primer, and a topcoat and include a chemical stripper and a cleaning compound for topcoat washing.

This SAE Aerospace Standard (AS) establishes the minimum requirements for ground-based aircraft deicing/anti-icing methods and procedures to ensure the safe operation of aircraft during icing conditions on the ground. This document does not specify the requirements for particular aircraft models.NOTE: Refer to particular aircraft operator or aircraft manufacturer’s published manuals and procedures.The application of the procedures specified in this document are intended to effectively remove and/or prevent the accumulation of frost, snow, slush, or ice contamination which can seriously affect the aerodynamic performance and/or the controllability of an aircraft. The principal method of treatment employed is the use of fluids qualified to AMS1424 (Type I fluid) and AMS1428 (Type II, III, and IV fluids).All guidelines referred to herein are applicable only in conjunction with the applicable documents.

This recommended practice contains dimensions and tolerances for spindles in the interface area. Interfacing components include axle spindle, spindle threads, bearing cones, bearing spacer, seal, and wheel hub. This recommended practice is intended for axles commonly used on Class 7 and 8 commercial vehicles. Included are SAE axle configurations FF, FL, I80, L, N, P, R, U, and W.

Material specification for parts produced using 7A50.60L (A7050-RAM2) using the laser powder bed fusion process

This specification covers a premium aircraft-quality corrosion-resistant steel in the form of bars, forgings, and forging stock.

This specification covers a premium aircraft-quality, corrosion-resistant steel in the form of bars, wire, forgings, and forging stock.

This specification covers a premium aircraft-quality, corrosion-resistant steel in the form of bars, wire, forgings, and forging stock

This SAE Aerospace Recommended Practice (ARP) outlines the basic general design requirements for ground support equipment used in the civil air transport industry. It is intended to assist in standardizing requirements for various configurations of equipment. For procurement of equipment, sections of this document should be specified with due consideration of the functional and environmental requirements of the equipment, and to the relative cost of satisfying those requirements.

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).