d :de.ection underimpact ofthetire(attheproperin.ation pressure) plus the vertical component of the axle travels (inches)relative to the drop mass.

n : limit inertia load factor.

nj :theloadfactordeveloped,duringimpact, onthemassused inthedrop test(i.e.,the accelerationdv/dting’srecorded in the drop test plus 1.0).
Amdt. 29-3, E.. 2/25/68
FAR 29.727 : Reserve energy absorption drop test.
The reserve energy absorption drop test must be conducted as follows :
(a)
The drop height must be 1.5 times that speci.ed in Sec. 29.725(a).

(b)
Rotorlift, where consideredin a manner similar to thatprescribedinSec.29.725(b), may not exceed 1.5 times the lift allowed under that paragraph.

(c)
[Thelandinggear mustwithstandthistest without collapsing.Collapse ofthelanding gear occurs when a member of the nose, tail, or main gear will not support the rotorcraft in the proper attitude or allows the rotorcraft structure, other than landing gear and external accessories, to impact the landing surface.]

Amdt. 29-30, E.. 4/5/90
FAR 29.729 : Retracting mechanism.
[For rotorcraft withretractable landing gear, the following apply :
(a)
Loads.] The landing gear, retracting mechanism, wheel well doors, and supporting structure must be designed for–

(1)
The loads occurring in any maneuvering condition with the gear retracted;

(2)
The combined friction, inertia, and air loads occurring during retraction and extension at any airspeed up to the design maximum landing gear operating speed; and

(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 mechanismmustbeshown by operation tests.

(e)
Position indicator. There must be 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. 29.777 and 29.779.

(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. 29-24, E.. 12/6/84
FAR 29.731 : 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 29.733 : Tires.
Each landing gear wheel must have a tire–
(a)
That is a proper .t on the rim of the wheel; and

(b)
Of a rating that is not exceeded under–

′
Elodie Roux. Septembre 2003
Subpart D : Design and Construction
(1)
The design maximum weight;

(2)
　
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本文鏈接地址：FAA規(guī)章 美國聯(lián)邦航空規(guī)章 Federal Aviation Regulations 5(41)