(2)
If a lock, steering device, or shimmy damper is used, the tail wheel is also assumed tobeinthetrailingposition with the sideload acting attheground contactpoint; and
(3)
The shock absorber and tire are assumed to be in their static positions.
(c)
[If a tail wheel, bumper, or an energy absorption device is provided to show com-pliance with Sec. 23.925(b), the following apply :
(1)
Suitabledesignloads mustbe establishedfor the tail wheel,bumper, or energy absorption device; and
(2)
The supportingstructure ofthetail wheel,bumper, or energy absorptiondevice mustbedesignedto withstand theloads establishedinparagraph(c)(1) ofthis section.]
Amdt. 23-48, E.. 03/11/96
FAR 23.499 : Supplementary conditions for nose wheels.
In determining the ground loads on nose wheels and a.ected supporting structures, and assumingthat the shock absorbers andtires arein their staticpositions, thefollowing conditions must be met :
(a)
For aft loads, the limit force components at the axle must be–
(1)
A vertical component of2.25 timesthe staticload onthe wheel; and
(2)
A drag component of 0.8 times the vertical load.
(b)
For forward loads, the limit force components at the axle must be–
(1)
A vertical component of2.25 timesthe staticload onthe wheel; and
(2)
A forward component of 0.4 times the vertical load.
(c)
For side loads, the limit force components at ground contact must be–
(1)
A vertical component of2.25 timesthe staticload onthe wheel; and
(2)
A side component of 0.7 times the vertical load.
(d)
[For airplanes with a steerable nose wheel that is controlled by hydraulic or other power, at design takeo. weight with the nose wheel in any steerable position, the application of 1.33 times the full steering torque combined with a vertical reaction equal to1.33times the maximum static reaction on the nosegear mustbe assumed. However,if atorquelimitingdeviceisinstalled,the steering torquecanbe reduced to the maximum value allowed by that device.
(e)
For airplanes with a steerable nose wheel that has a direct mechanical connection to the rudder pedals, the mechanism must be designed to withstand the steering torque for the maximum pilot forces speci.ed in Sec. 23.397(b).]
Amdt. 23-48, E.. 03/11/96
FAR 23.505 : Supplementary conditions for skiplanes.
[In determining ground loads for skiplanes, andassuming that the airplane is resting on the ground with one main ski frozen at rest and the other skis free to slide, a limit side force equal to 0.036 times the design maximum weight must be applied near the tail assembly, with a factor of safety of 1.] Amdt. 23-7, E.. 09/14/69
FAR23.507 :[Jackingloads.]
(a)
[The airplane mustbedesignedfortheloadsdevelopedwhen the aircraftis supported on jacks at the design maximum weight assuming the following load factors for landinggearjackingpointsatathree-point attitudeandforprimary.ight structure jackingpointsinthelevelattitude:
(1)
Vertical-load factor of 1.35 times the static reactions.
(2)
Fore, aft, and lateral load factors of 0.4 times the vertical static reactions.
(b)
The horizontal loads at the jack points must be reacted by inertia forces so as to resultin no changeinthedirection of the resultantloads atthejackpoints.
(c)
The horizontal loads must be considered in all combinations with the vertical load.] Amdt. 23-14, E.. 12/20/73
FAR23.509 :[Towingloads.]
[The towing loads of this section must be applied to the design of tow .ttings and their immediate attaching structure.
(a) The towingloads speci.edinparagraph(d) of this section mustbe considered se-parately. These loads must be applied at the towing .ttings and must act parallel to the ground. In addition–
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本文鏈接地址：FAA規章 美國聯邦航空規章 Federal Aviation Regulations 2(11)
