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SAE AS5714

Revision A, August 1, 2017

Complete Document

Minimum Performance Standard for Parts 23, 27, and 29 Aircraft Wheels, Brakes, and Wheel and Brake Assemblies

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Product Details:

  • Revision: Revision A, August 1, 2017
  • Published Date: August 2017
  • Status: Active, Most Current
  • Document Language: English
  • Published By: SAE International (SAE)
  • Page Count: 19
  • ANSI Approved: No
  • DoD Adopted: No

Description / Abstract:

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.

Application Compliance with this minimum specification by the TSO applicant is required as a means of assuring that the equipment will have the capability to satisfactorily perform its intended function(s).

NOTE: Certain performance capabilities may be affected by aircraft operational characteristics and other external influences. Consequently, anticipated aircraft braking performance should be verified by aircraft testing.

Composition of Equipment

The words “equipment” or “brake assembly” or “wheel assembly” or “wheel and brake assembly” as used in this document, include all components that form part of the particular unit.

For example, a wheel assembly typically includes a hub or hubs, bearings, flanges, drive bars, heat shields, and fuse plugs. A hydraulically actuated brake assembly typically includes a backing plate, torque tube, cylinder assemblies, pressure plate, wear pin, heat sink, and other axle mounted components integral to the braking activity.

Also as an example, an electrically actuated brake assembly typically includes a backing plate, torque tube, electromechanical actuators, pressure plate, wear indicator, heat sink, and other axle mounted components integral to the braking activity.

It should not be inferred from these examples that each wheel assembly and brake assembly will necessarily include either all or any of the above example components; the actual assembly will depend on the specific design chosen by the TSO applicant.

For the purpose of this specification, the interface boundaries of the equipment are the wheel and brake attachments to the landing gear and the electrical connectors to the aircraft brake control system. The aircraft brake control system is a reference to any equipment related to the control of wheel braking that is not assembled to the brake on axle and provides either hydraulic energy to the hydraulic actuators or electrical energy to the Electro Mechanical Actuators (EMAs) and/or monitors sensors mounted in or on the brake assembly. This may also include hydraulic lines and fittings or wiring and connectors as applicable, if not integral to the brake.
AIA/NAS Aerospace Standards