(3)
The .ightloads,including thoseinyawed.ight,occurring with thegearexten-ded at any airspeed up to the design maximum landing gear extended speed.

(b)
Landing gear lock. A positive means must be provided to keep the gear extended.

(c)
Emergency operation. When other than manual power is used to operate the gear, emergency means must be provided for extending the gear in the event of–

(1)
Any reasonablyprobablefailureinthe normal retraction system; or

(2)
The failure of any single source of hydraulic, electric, or equivalent energy.

(d)
Operation tests.Theproperfunctioning of the retracting mechanism mustbe shown by operation tests.

(e)
Position indicator. There must be a means to indicate to the pilot when the gear is secured in the extreme positions.

(f)
Control. The location and operation of the retraction control must meet the requi-rements of Secs. 27.777 and 27.779.

(g)
Landing gear warning. An aural or equally e.ective landing gear warning device must be provided that functions continuously when the rotorcraft is in a normal landing mode and the landing gear is not fully extended and locked. A manual shuto.capability mustbeprovidedforthe warningdeviceand the warning system must automatically reset when the rotorcraft is no longer in the landing mode.]

Amdt. 27-21, E.. 12/6/84
FAR 27.731 : Wheels
(a)
Each landing gear wheel must be approved.

(b)
The maximum static load rating of each wheel may not be less than the correspon-ding static ground reaction with–

(1)
Maximum weight; and

(2)
Critical center of gravity.

(c)
The maximum limit load rating of each wheel must equal or exceed the maximum radiallimitloaddetermined underthe applicablegroundload requirementsof this part.

FAR 27.733 : Tires

(a)
Each landing gear wheel must have a tire–

(1)
Thatisaproper .tontherimof thewheel; and

(2)
Of the proper rating.

(b)
The maximum staticload rating of each tire must equal orexceed the staticground reaction obtained at its wheel, assuming–

(1)
The design maximum weight; and

(2)
The most unfavorable center of gravity.

(c)
[Eachtireinstalled on aretrackablelandinggearsystem must, atthe maximumsize of the tire type expected in service, have a clearance to surrounding structure and systems that is adequate to prevent contact between the tire and any part of the structure or systems.]

Amdt. 27-11, E.. 2/1/77
FAR 27.735 : Brakes
[For rotorcraft withwheel-typelandinggear, abraking device mustbeinstalled that is–]
(a)
Controllable by the pilot;

(b)
Usableduringpower-o.landings; and

(c)
Adequate to–

(1) Counteractany normal unbalancedtorque when starting or stoppingthe rotor; and

(2)
Holdthe rotorcraftparked on a10'slope on a dry, smooth pavement. Amdt. 27-21, E.. 12/6/84

FAR 27.737 : Skis
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.
64.5 Floats and Hulls
FAR 27.751 : Main .oat buoyancy
(a)
For main .oats, the buoyancy necessary to support the maximum weight of the rotorcraft in fresh water must be exceeded by–

(1)
50 percent, for single .oats; and

(2)
60 percent, for multiple .oats.

(b)
[Each main .oat must have enough water-tight compartments so that, with any single main .oat compartment .ooded, the main .oats will provide a margin of positive stability great enough to minimize the probability of capsizing.]

Amdt. 27-2, E.. 2/25/68
　
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本文鏈接地址：FAA規章 美國聯邦航空規章 Federal Aviation Regulations 4(93)