spaschal on DSK3GDR082PROD with CFR

Section 25.737

14 CFR Ch. I (1-1-19 Edition)

(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 tire assembly must be determined.
It must be substantiated by dynamometer testing that the wheel, brake and
tire 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 airplane
manufacturer-s braking requirements
must be achieved. The mean deceleration must not be less than 10 fps 2.
(2) Maximum kinetic energy acceleratestop. The maximum kinetic energy accelerate-stop is a rejected takeoff for
the most critical combination of airplane takeoff weight and speed. The accelerate-stop brake kinetic energy absorption requirement of each wheel,
brake, and tire assembly must be determined. It must be substantiated by
dynamometer testing that the wheel,
brake, and tire 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 airplane manufacturer-s braking requirements must be achieved. The mean deceleration must not be less than 6 fps2.
(3) Most severe landing stop. The most
severe landing stop is a stop at the
most critical combination of airplane
landing weight and speed. The most severe landing stop brake kinetic energy
absorption requirement of each wheel,
brake, and tire 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 tire 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 paragraph (f)
of this section, 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 tire or wheel and brake assembly,
that could prejudice the safe and complete evacuation of the airplane.
(h) Stored energy systems. An indication to the flightcrew of the usable
stored energy must be provided if a
stored energy system is used to show
compliance with paragraph (b)(1) of
this section. The available stored energy must be sufficient for:
(1) At least 6 full applications of the
brakes when an antiskid system is not
operating; and
(2) Bringing the airplane to a complete stop when an antiskid system is
operating, under all runway surface
conditions for which the airplane 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) Overtemperature burst prevention.
Means must be provided in each braked
wheel to prevent a wheel failure, a tire
burst, or both, that may result from
elevated brake temperatures. Additionally, all wheels must meet the requirements of Section 25.731(d).
(k) Compatibility. Compatibility of
the wheel and brake assemblies with
the airplane and its systems must be
substantiated.
[Doc. No. FAA-1999-6063, 67 FR 20420, Apr. 24,
2002, as amended by Amdt. 25-108, 67 FR
70827, Nov. 26, 2002; 68 FR 1955, Jan. 15, 2003]

Section 25.737

Skis.

Each ski must be approved. The maximum limit load rating of each ski
must equal or exceed the maximum
limit load determined under the applicable ground load requirements of this
part.

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