(ii)
For the rear wheel, 0.8 times the vertical reaction.

(2)
Theloads speci.edin subparagraph(1) of thisparagraph mustbe applied–

(i)
Attheground contactpointwiththe wheelinthetrailingposition(for non-full swiveling landing gear or for full swiveling landing gear with a lock, steering device, or shimmy damper to keep the wheel in the trailing position); or

(ii)
At the center of the axle(forfull swivelinglandinggear without alock, steering device, or shimmy damper).

(g)
Braked roll conditions in the level landing attitude. In the attitudes speci.ed in paragraphs(b) and(c) of this section, and with the shock absorbersintheir static positions, the rotorcraft must be designed for braked roll loads as follows :

′
Elodie Roux. Septembre 2003
Subpart C : Strength Requirements
(1)
Thelimit verticalload mustbebased onalimit verticalloadfactorof notless than–

(i)
1.0,forthe attitude speci.edinparagraph(b) of this section; and

(ii)
1.33,forthe attitude speci.edinparagraph(c) of this section.

(2)
For eachwheel withbrakes, adragload mustbe applied, at theground contact point, of not less than the lesser of–

(i)
0.8 times the vertical load; and

(ii)
The maximum based on limiting brake torque.

(h)
Rear wheel turning loads in the static ground attitude. Inthe staticground attitude, and with the shock absorbers and tiresin their staticpositions, the rotorcraft must be designed for rear wheel turning loads as follows :

(1)
A vertical ground reaction equal to the static load on the rear wheel must be combined with an equal sideload.

(2)
Theload speci.edin subparagraph(1) of thisparagraph mustbe applied to the rear landing gear–

(i)
Through the axle,if thereis a swivel(the rearwheelbeing assumed tobe swiveled 90 degrees to the longitudinal axis of the rotorcraft); or

(ii)
Attheground contactpoint,if thereis alock, steering device or shimmy damper(the rear wheelbeing assumed tobeinthetrailingposition).

(i)
Taxiing condition. The rotorcraft and its landing gear must be designed for loads that would occur whenthe rotorcraftistaxied overthe roughestground that may reasonably be expected in normal operation.

FAR 27.501 : Ground loading conditions : landing gear with skids

(a)
General. Rotorcraft with landing gear with skids must be designed for the loading conditions speci.ed in this section. In showing compliance with this section, the following apply :

(1)
Thedesign maximum weight,center ofgravity,andloadfactormustbedeter-mined under Secs. 27.471 through 27.475.

(2)
Structural yielding of elastic spring members under limit loads is acceptable.

(3)
Design ultimate loads for elastic spring members need not exceed those obtai-ned in a drop test of the gear with–

(i)
A drop height of 1.5 times that speci.ed in Sec. 27.725; and

(ii)
An assumed rotor lift of not more than 1.5 times that used in the limit drop tests prescribed in Sec. 27.725.

(4)
Compliance withparagraphs(b) through(e) ofthis section mustbe shown with–

(i)
Thegearinits most critically de.ectedpositionforthelanding condition being considered; and

(ii)
Theground reactions rationally distributed along thebottom of the skid tube.

(b)
Vertical reactions in the level landing attitude. In the level attitude, and with the ro-torcraft contactingtheground alongthebottom ofboth skids, the vertical reactions mustbe applied asprescribedinparagraph(a) of this section.

(c)
Drag reactions in the level landing attitude. In the level attitude, and with the rotor-craft contacting the ground along the bottom of both skids, the following apply :
　
中國航空網 www.k6050.com
航空翻譯 www.aviation.cn
本文鏈接地址：FAA規章 美國聯邦航空規章 Federal Aviation Regulations 4(79)