(1) At least 6 full applications of the brakes when an antiskid system is not ope-rating; and
′
Elodie Roux. Septembre 2003
Subpart D : Design and Construction
(2) Bringing the airplane to a complete stop when an antiskid systemis operating, under all runway surface conditions for which the airplane is certi.cated.
(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 Sec. 25.731(d).

(k)
Compatibility. Compatibility of the wheel and brake assemblies with the airplane andits systems mustbe substantiated.]

Amdt. 25-107, E.. 5/24/2002
FAR 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 requi-rements of this Part.
47.5 Floats and Hulls
FAR 25.751 : Main .oat buoyancy.
Each main .oat must have–
(a)
A buoyancy of80percentin excess of that required to support the maximum weight of the seaplane or amphibian in fresh water; and

(b)
Not less than .ve watertight compartments approximately equal in volume.

FAR 25.753 : Main .oat design.
Each main .oat must be approved and must meet the requirements of Sec. 25.521.
FAR 25.755 : Hulls.
(a)
Eachhullmusthave enough watertight compartments so that, with anytwo adjacent compartments .ooded, the buoyancy of the hull and auxiliary .oats (and wheel tires, if used) provides a margin of positive stability great enough to minimize the probability of capsizing in rough, fresh water.

(b)
Bulkheadswith watertightdoorsmaybeusedforcommunicationbetweencompart-ments.

47.6 Personnel and Cargo Accommodations
FAR 25.771 : Pilot compartment.
(a) Eachpilotcompartmentanditsequipmentmustallowtheminimum .ightcrew(es-tablished underSec.25.1523)toperform theirduties without unreasonable concen-tration or fatigue.
(b)
The primary controls listed in Sec. 25.779(a), excluding cables and control rods, must be located with respect to the propellers so that no member of the minimum .ight crew(established underSec.25.1523), orpart ofthe controls,liesin the region between the plane of rotation of any inboard propeller and the surface generated by a line passing through the center of the propeller hub making an angle of .ve degrees forward or aft of the plane of rotation of the propeller.

(c)
If provision is made for a second pilot, the airplane must be controllable with equal safety from either pilot seat.

(d)
Thepilotcompartmentmustbeconstructed sothat,when .ying inrainorsnow,it will not leak in a manner that will distract the crew or harm the structure.

(e)
[Vibration andnoise characteristics of cockpit equipment may notinterfere with safe operation of the airplane.]

Amdt. 25-4, E.. 4/30/65
FAR 25.772 : Pilot compartment doors.
For an airplane that has a [lockable door installed between the pilot compartment and the passenger compartment :
(a)
For airplanes with a maximumpassenger seating con.guration of more than20 seats, the emergency exit con.guration must be designed so that neither crewmembers nor passengers require use of the .ightdeck door in order to reach the emergency exits provided for them;]

(b)
Meansmustbeprovidedtoenable .ightcrewmemberstodirectly enterthepassenger compartmentfromthepilot compartmentifthe cockpitdoorbecomesjammed.

(c)
[There must be an emergencymeans to enable a .ight attendant to enter the pilot
　
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