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Aircraft Tire Wear Profile Development and Execution for Laboratory Testing

This SAE Aerospace Information Report (AIR) describes the current process for performing comparative wear testing on aircraft tires in a laboratory environment. This technique is applicable to both radial and bias tires, and is pertinent for all aircraft tire sizes. This AIR describes a technique based upon “wear” energy. In this technique, side wear energy and drag wear energy are computed as the tire is run through a prescribed test program. The specifics that drive the test setup conditions are discussed in Sections 4 through 7. In general, the technique follows this process: - A test profile is developed from measured mechanical property data of the tires under study. - Each tire is repeatedly run to the test profile until it is worn to the maximum wear limit (MWL). Several tires, typically 5 to 10, of each tire design are tested. - Wear energy is computed for each test cycle and then summed to determine total absorbed wear energy. - An index is calculated for each tire design.

Fittings, Tube, Fluid Systems, Separable, Beam Seal, 3000/4000 psi, General Specification For

This specification covers the design requirements and test procedures for separable beam seal fittings which includes end fittings (see 2.3.4), fitting bodies (see 2.3.7), and boss fittings (see 2.3.2) for use in aerospace fluid systems. Design requirements are for class 3000 in corrosion resistant steel (15-5 PH, 17-4 PH CRES) only and for class 4000 in titanium alloy (Ti) and corrosion and heat-resistant steel (Nickel Alloy 718 CRES) only. Definition of fittings and related terms are defined in 2.3.

Minimum Performance Standard for Airborne Multipurpose Electronic Displays

This SAE Aerospace Standard (AS) specifies minimum performance standards for all types of electronic displays and electronic display systems that are intended for use in the flight deck by the flight crew in all 14 CFR Part 23, 25, 27, and 29 aircraft. The requirements and recommendations in this document are intended to apply to all installed electronic displays and electronic display systems including those that have a touch screen interface within the flight deck, regardless of intended function, criticality, or location within the flight deck, but may also be used for non-installed electronic displays. This document provides baseline requirements and recommendations (see 2.3 for definitions of “shall” and “should”). This document primarily addresses hardware requirements, such as electrical, mechanical, optical, and environmental. It does not address system specific functions.

External Hydraulic Fluid Leakage Definition for Landing Gear Shock Absorbers

The purpose of this SAE Aerospace Recommended Practice (ARP) is to provide a practical definition of external hydraulic fluid leakage exhibited by landing gear shock absorbers/struts. The definition will outline normal (acceptable weepage) and excessive leakage (unacceptable leakage) of shock absorbers/struts that is measurable. The definition of leakage is applicable to new gear assemblies, refurbished/remanufactured (overhauled) shock absorbers/struts, leakage of shock absorbers/struts encountered during acceptance flights, newly delivered and in-service aircraft. This ARP is intended to provide guidelines for acceptable leakage of landing gear shock absorbers/struts between the ambient temperatures of 65 °F (-54 °C) and 130 °F (54 °C) and to outline the procedure for measuring such leakage. The specific limits that are applied to any particular aircraft shall be adjusted by the aircraft manufacturer before inclusion in the applicable maintenance manual.