CS 25.735 Brakes and braking systems

ED Decision 2013/033/R

(See AMC 25.735)

(a)     Approval. Each assembly consisting of a wheel(s) and brake(s) must be approved.

(b)     Brake system capability. The brake system, associated systems and components must be designed and constructed so that:

(1)     If any electrical, pneumatic, hydraulic, or mechanical connecting or transmitting element fails, or if any single source of hydraulic or other brake operating energy supply is lost, it is possible to bring the aeroplane to rest with a braked roll stopping distance of not more than two times that obtained in determining the landing distance as prescribed in CS 25.125.

(2)     Fluid lost from a brake hydraulic system following a failure in, or in the vicinity of, the brakes is insufficient to cause or support a hazardous fire on the ground or in flight.

(c)      Brake controls. The brake controls must be designed and constructed so that:

(1)     Excessive control force is not required for their operation.

(2)     If an automatic braking system is installed, means are provided to:

(i)      Arm and disarm the system, and

(ii)     Allow the pilot(s) to override the system by use of manual braking.

(d)     Parking brake. The aeroplane must have a parking brake control that, when selected on, will, without further attention, prevent the aeroplane from rolling on a dry and level paved runway when the most adverse combination of maximum thrust on one engine and up to maximum ground idle thrust on any, or all, other engine(s) is applied. The control must be suitably located or be adequately protected to prevent inadvertent operation. There must be indication in the cockpit when the parking brake is not fully released.

(e)     Anti-skid system. If an anti-skid system is installed:

(1)     It must operate satisfactorily over the range of expected runway conditions, without external adjustment.

(2)     It must, at all times, have priority over the automatic braking system, if installed.

(f)      Kinetic energy capacity –

(1)     Design landing stop. The design-landing stop is an operational landing stop at maximum landing weight. The design landing stop brake kinetic energy absorption requirement of each wheel, brake, and tyre assembly must be determined. It must be substantiated by dynamometer testing that the wheel, brake and tyre assembly is capable of absorbing not less than this level of kinetic energy throughout the defined wear range of the brake. The energy absorption rate derived from the aeroplane manufacturer’s braking requirements must be achieved. The mean deceleration must not be less than 3.1 m/s² (10 fps²).

(2)     Maximum kinetic energy accelerate-stop. The maximum kinetic energy accelerate-stop is a rejected take-off for the most critical combination of aeroplane take-off weight and speed. The accelerate-stop brake kinetic energy absorption requirement of each wheel, brake, and tyre assembly must be determined. It must be substantiated by dynamometer testing that the wheel brake and tyre assembly is capable of absorbing not less than this level of kinetic energy throughout the defined wear range of the brake. The energy absorption rate derived from the aeroplane's braking requirements must be achieved. The mean deceleration must not be less than 1.8 m/s² (6 fps²).

(3)     Most severe landing stop. The most severe landing stop is a stop at the most critical combination of aeroplane landing weight and speed. The most severe landing stop brake kinetic energy absorption requirement of each wheel, brake, and tyre assembly must be determined. It must be substantiated by dynamometer testing that, at the declared fully worn limit(s) of the brake heat sink, the wheel, brake and tyre assembly is capable of absorbing not less than this level of kinetic energy. The most severe landing stop need not be considered for extremely improbable failure conditions or if the maximum kinetic energy accelerate-stop energy is more severe.

(g)     Brake condition after high kinetic energy dynamometer stop(s). Following the high kinetic energy stop demonstration(s) required by sub-paragraph (f) of this paragraph, with the parking brake promptly and fully applied for at least 3 minutes, it must be demonstrated that for at least 5 minutes from application of the parking brake, no condition occurs (or has occurred during the stop), including fire associated with the tyre or wheel and brake assembly, that could prejudice the safe and complete evacuation of the aeroplane.

(h)     Stored energy systems. An indication to the flight crew of the usable stored energy must be provided if a stored energy system is used to show compliance with sub-paragraph (b)(1) of this paragraph. The available stored energy must be sufficient for:

(1)     At least 6 full applications of the brakes when an anti-skid system is not operating; and

(2)     Bringing the aeroplane to a complete stop when an anti-skid system is operating, under all runway surface conditions for which the aeroplane is certificated.

(i)      Brake wear indicators. Means must be provided for each brake assembly to indicate when the heat sink is worn to the permissible limit. The means must be reliable and readily visible.

(j)      Over-temperature burst prevention. Means must be provided in each braked wheel to prevent a wheel failure, a tyre burst, or both, that may result from elevated brake temperatures. Additionally, all wheels must meet the requirements of CS 25.731(d).

(k)     Compatibility. Compatibility of the wheel and brake assemblies with the aeroplane and its systems must be substantiated.

(l)      Wheel brake temperature. Equipment and structure that are essential to the safe operation of the aeroplane and that are located on the landing gear and in wheel wells must be protected from the damaging effects of possible wheel brake temperatures.

[Amdt 25/2]

[Amdt 25/14]