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Standard

Sizing of Emergency Braking Systems

2018-04-18
WIP
ARP6952
The pupose of this SAE AIR is to provide guidelines for sizing stored energy systems in use in emergency braking systems, in light of their intended purpose and applicable certification regulations.
Standard

Aircraft Brake Temperature Measurement

2017-10-26
WIP
ARP6812
This SAE Aerospace Recommended Practice (ARP) covers the functional, design, construction, and test requirements for Brake Temperature Monitoring Systems (BTMS), and sometimes referred to as Brake Temperature Indication Systems (BTIS). The BTMS is limited to aircraft where a dispatch indication and brake temperature indication is required. The scope of this BTMS equipment shall be limited to the 1) brake temperature sensor or indicator, 2) temperature reference measurement, if required, and 3) processing and communication of brake temperature. This recommended practice will not address cockpit ergonomics and aircraft operating procedures.
Standard

Test Method for Catalytic Carbon Brake Disk Oxidation

2013-12-04
WIP
AS6289
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.
Standard

USAF Aircraft Wheels

2006-02-09
HISTORICAL
AIR4012B
This SAE Aerospace Information Report (AIR) documents general technical data associated with many of the wheels used in the Air Force.
Standard

USAF Aircraft Wheels

2012-07-19
CURRENT
AIR4012C
This SAE Aerospace Information Report (AIR) documents general technical data associated with many of the wheels used in the Air Force.
Standard

Valve, Inflation, Aircraft Wheel

2019-11-14
CURRENT
AS6817
This SAE Aerospace Standard (AS) defines the configuration of aircraft wheel inflation valve assemblies, including required tolerances, materials, and appropriate finishes.
Standard

Minimum Performance Requirements for Transport Airplane Wheel and Brake Assemblies Using Electric Power Actuation

2007-01-23
HISTORICAL
AS5663
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.
Standard

Minimum Performance Requirements for Transport Airplane Wheel and Brake Assemblies Using Electric Power Actuation

2012-07-11
CURRENT
AS5663A
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.
Standard

BRAKE DYNAMICS

1997-01-01
HISTORICAL
AIR1064C
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
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