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The scope of the test method is to provide stakeholders including fluid manufacturers, brake manufacturers, aircraft constructors, aircraft operators and airworthiness authorities with a relative assessment of the effect of deicing chemicals on carbon oxidation. This test is designed to assess the relative effects of runway deicing chemicals by measuring mass change of contaminated and bare carbon samples tested under the same conditions.

This document was requested by the FAA to provide a technical update of TSO-C26d to address Electric Brake Actuation, standardize with TSO-C135a and address any remaining concerns with the current technical requirements in AIR5381.

This SAE Aerospace Standard (AS) prescribes the Minimum Performance Standards (MPS) for environmental conditions that wheel, brake, and wheel and brake assemblies to be used on aircraft certificated under 14 CFR Parts 23, 25, 27, and 29. The environmental requirements in this document shall be used in conjunction with other MPS defined in Technical Standard Orders for the applicable equipment.

This SAE Aerospace Recommended Practice (ARP) establishes a procedure for disposition of aircraft wheels that have been involved in accidents/incidents or have been exposed to overheat conditions or overload conditions from loss of adjacent tire pressure (paired wheels) or wheel tie bolts.

A panel of the SAE A-5A Committee prepared this SAE Aerospace Information Report (AIR). The document describes the design approaches used for current applications of Brake-by-Wire (BBW) control systems that are used on commercial and military airplanes. The document also discusses the experience gained during service in the commercial and military environments, and covers system, ergonomic, hardware, and development aspects. The treatment includes the lessons that have been learned during application of the technology. Although there are a variety of approaches that have been used in the design of BBW systems, the main focus of this document is on systems that use the electro-hydraulic method of control. The overall range of implementations is briefly described in 2.3. Sections 3, 4, and 5 describe the electro-hydraulic method in detail.

This specification covers minimum requirements for skid control equipment for use on all types and models of civil aircraft. It shall be the responsibility of the applicant (See Paragraph 5.1) to determine the compatibility of these requirements with the applicable aircraft and to specify requirements in excess of these minimums as necessary.

This AS applies to the cavity design and the selection of O-rings for tubeless tire wheels.

This AS applies to the cavity design and the selection of O-rings for tubeless tire wheels.

This AS applies to the cavity design and the selection of O-rings for tubeless tire wheels.

This standard applies to the cavity design and the selection of O-rings for tubeless tire wheels.

This standard applies to the cavity design and the selection of O-rings for tubeless tire wheels.

This SAE Aerospace Recommended Practice (ARP) provides recommendations for the function, design, construction, and testing of an on-aircraft Brake Temperature Monitoring System (BTMS), sometimes referred to as a Brake Temperature Indication System (BTIS). NOTE: This ARP does not address: Cockpit ergonomics and Aircraft operating procedures. Various handheld methods of temperature sensing or readouts, as these are not associated with transport aircraft during normal operation. Temperature sensitive paints as a means to indicate exceedance of a landing gear axle temperature threshold due to brake temperature.

The development and use of brakes with high temperature capabilities has resulted in instances of tire and wheel failures which were attributed to excessive brake heat. These instances have led to the establishment of more stringent wheel requirements and the addition of heat shields, safety devices, auxiliary cooling devices, brake temperature and low tire pressure indication systems. This SAE Aerospace Information Report (AIR) has been prepared to assist those who are concerned with the removal, inspection, and disposition of magnesium and aluminum wheels which may have been subjected to excessive temperatures.

This SAE Aerospace Information Report (AIR) has been prepared to assist those who are concerned with the removal, inspection, and disposition of magnesium and aluminum wheels which may have been subjected to excessive temperatures.

The landing gear is a complex multi-degree of freedom dynamic system and may encounter vibration problems induced by braking action. The vibratory modes can be induced by several frictional characteristics and brake design features. These should be assessed during the design concept and verified during the development of the hardware. This SAE Aerospace Information Report (AIR) has been prepared by a panel of the A-5A Subcommittee to present an overview of the landing gear system problems associated with aircraft brake dynamics and the approaches to the solution of these problems. In addition, facilities available for test and evaluation are presented and discussed.1

The aircraft landing gear is a complex multi-degree of freedom dynamic system, and may encounter vibration or dynamic response problems induced by braking action. The vibratory modes can be induced by brake and tire-ground frictional characteristics, antiskid operation, brake design features, landing gear design features, and tire characteristics. The impact of this vibration can range from catastrophic failure of critical system components or entire landing gears, to fatigue of small components, to passenger annoyance. It is therefore important that the vibration is assessed during the design concept phase, and verified during the development and testing phases of the system hardware. This SAE Aerospace Information Report (AIR) has been prepared by a panel of the A-5A Subcommittee to present an overview of the landing gear problems associated with aircraft braking system dynamics, and the approaches to the identification, diagnosis, and solution of these problems.