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TECHNICAL ANNEXES: ANNEX G      209

effective warning device may be substituted in lieu of an aural device.
2.31423-T Retraction Control. The control provided for retractable gears shall be so oriented and shall operate in such a manner as to require an upward motion of the control to retract the gear. 
2.3143  Wheels. Main landing gear wheels (i.e. those nearest the airplane center of gravity) shall be of an approved type in accordance with part 5.1. The rated static load of each main wheel shall not be less than the design weight for ground loads (2.240 and 2.240-T) divided by the number of main wheels. Nose wheels shall be approved in accordance with Part 5 for an ultimate radial load not less than the nose wheel ultimate loads obtained in the ground loads requirement, 2.24, and for the corresponding side and burst loads specified in part 5.1.
2.1344 Tires. A landing gear wheel may be equipped with any type of tire constructed by a reputable maker provided that the rating of the maker is not exceeded. When specially constructed tires are used to support an airplane, the wheels shall be plainly and conspicuously marked to that effect. Such markings shall include the make, size, number of plies, and identification markings of the proper tire.
2.1345-T Brakes. Transport category airplanes shall be equipped with brakes certified in accordance with the provisions of Part 5 for the maximum certificated landing weight at sea level and the power-off stalling speed. The brake system for such airplanes shall be so designed and constructed that in the event of a single failure in any connecting or transmitting element in the brake system, (exclusive of the brake operating handle or pedal and the primary braking elements such as the drum and shoe or their equivalent) or the loss of any single source of hydraulic or other brake operating energy supply, it shall be possible as shown by suitable test or other date, to bring the airplane to rest under the conditions specified in 2.124-T with a mean negative acceleration during the landing roll of at least 50 percent of that obtained in determining the landing distance under that section.
2.315 Hulls and Floats
2.1351 Buoyancy (Main Seaplane Floats) Main seaplane floats shall have a buoyancy in excess of that required to support the gross weight of the airplane in fresh water as follows:

(a) 80 percent in the case of single floats.
(b) 90 percent in the case of double floats.

Main seaplane floats for use on aircraft of 2,500 pounds (1,134 kg.) or more maximum authorized weight shall contain at least five water-tight compartments of approximately equal volume. Main seaplane floats for use on aircraft of less than 2,500 pounds (1,134 kg.) maximum authorized weight shall contain at least four such compartments.