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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.

This document provides information on contamination and its effects on brakes having carbon-carbon composite friction materials (carbon). Carbon is hygroscopic and porous, and therefore readily absorbs liquids and contaminants. Some of the contaminants can impact intended performance of the brake. This document is intended to raise awareness of the effects of carbon brake contamination and provide recommendations for its prevention. Although not addressed in this report, contaminants can cause problems with other landing system components including tires.

This document provides information on contamination and its effects on brakes having carbon-carbon composite friction materials (carbon). Carbon is hygroscopic and porous, and therefore readily absorbs liquids and contaminants. Some of the contaminants can impact intended performance of the brake. This document is intended to raise awareness of the effects of carbon brake contamination and provide information on industry practices for its prevention. Although not addressed in this report, contaminants can cause problems with other landing system components including tires.

This document recommends minimum requirements for antiskid brake control to provide total aircraft systems compatibility. Design and operational goals, general theory, and functions, which should be considered by the aircraft brake system engineer to attain the most effective skid control performance, are covered in detail. Methods of determining and evaluating antiskid system performance are discussed. While this document specifically addresses antiskid systems which are a part of a hydraulically actuated brake system, the recommended practices are equally applicable to brakes actuated by other means, such as electrically actuated brakes.

This document covers the general requirements for aircraft skid control systems and their components. Methods of defining skid control system performance criteria for design and evaluation purposes are outlined and recommended. Design and operational goals, general theory, and functions, which should be considered by the aircraft brake system engineer to attain the most effective skid control performance, are covered in detail. Recommended methods for measuring performance of a skid control system are included.

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.

This Aerospace Information Report (AIR) has been prepared by a panel of the SAE A-5 Committee and is presented to document the design approaches and service experience from various applications of antiskid systems. This experience includes commercial and military applications.

This SAE Aerospace Information Report (AIR) has been prepared by a panel of the SAE A-5A Committee and is presented to document the design approaches and service experience from various applications of antiskid systems. This experience includes commercial and military applications.

This Minimum Performance Document defines the testing required for wheels, brakes, and wheel and brake assemblies to be used on civil aircraft certified under 14 Code of Federal Regulations (CFR) Part 23, 27, and 29. Compliance with this document is recommended to assure that the equipment supplied will meet the intended design function when installed on aircraft. Compliance with this document does not constitute authorization for installation on an aircraft. The combined recommendations of this document provide an acceptable practice, but not the only practice, for obtaining authorization to apply TSO markings on the equipment.

This Minimum Performance Document defines the testing required for wheels, brakes, and wheel and brake assemblies to be used on civil aircraft certified under 14 Code of Federal Regulations (CFR) Part 23, 27, and 29. Compliance with this document is recommended to assure that the equipment supplied will meet the intended design function when installed on aircraft. Compliance with this document does not constitute authorization for installation on an aircraft. The combined recommendations of this document provide an acceptable practice, but not the only practice, for obtaining authorization to apply TSO markings on the equipment.

In lieu of TSO-C135, this SAE Aerospace Standard (AS) prescribes the minimum performance standards for wheels, brakes, and wheel and brake assemblies using electric power actuation for transport category (14 CFR Part 25) airplanes. Testing is limited to that necessary to establish minimum performance related to strength, robustness, stopping capability, and energy absorption to ensure measurable, repeatable industry accepted standards for these aspects of wheel and brake performance. The test parameters associated with electric braking actuation are defined around the state of the technology at this time, typically comprised of an Electro-Mechanical Actuator (EMA) controlled by a control system delivering electric power and effecting motor control.

In lieu of TSO-C135, this SAE Aerospace Standard (AS) prescribes the minimum performance standards for wheels, brakes, and wheel and brake assemblies using electric power actuation for transport category (14 CFR Part 25) airplanes. Testing is limited to that necessary to establish minimum performance related to strength, robustness, stopping capability, and energy absorption to ensure measurable, repeatable industry accepted standards for these aspects of wheel and brake performance. The test parameters associated with electric braking actuation are defined around the state of the technology at this time, typically comprised of an Electro-Mechanical Actuator (EMA) controlled by a control system delivering electric power and effecting motor control.

This SAE Aerospace Standard (AS) prescribes the Minimum Performance Standards (MPS) for wheel, brake, and wheel and brake assemblies to be used on aircraft certificated under 14 CFR Parts 23, 27, and 29. Compliance with this specification is not considered approval for installation on any aircraft.

This SAE Aerospace Standard (AS) prescribes the Minimum Performance Standards (MPS) for wheel, brake, and wheel and brake assemblies to be used on aircraft certificated under 14 CFR Parts 23, 27, and 29. Compliance with this specification is not considered approval for installation on any aircraft.

This SAE Aerospace Information Report (AIR) identifies current nondestructive inspection (NDI) methods used to insure product integrity and maximize "in service" life of the major structural components of aircraft wheel and brake assemblies.

This SAE Aerospace Information Report (AIR) identifies current nondestructive inspection (NDI) methods used to ensure product integrity and maximize "in service" life of the major structural components of aircraft wheel and brake assemblies.

This SAE Aerospace Information Report (AIR) identifies current nondestructive inspection (NDI) methods used to ensure product integrity and maximize "in service" life of the major structural components of aircraft wheel and brake assemblies.

This SAE Aerospace Information Report (AIR) identifies current nondestructive inspection (NDI) methods used to insure product integrity and maximize "in service" life of the major structural components of aircraft wheel and brake assemblies.