(b)
Unless otherwiseprovided,the air,ground, and waterloadsmustbeplacedin equi-librium with inertia forces, considering each item of mass in the airplane. These loads must be distributed to conservatively approximate or closely represent actual conditions. Methods used to determine load intensities and distribution on canard and tandem wing con.gurations must be validated by .ight test measurement un-less the methods used for determining those loading conditions are shown to be reliable or conservative on the con.guration under consideration.
(c)
If de.ections under load would signi.cantly change the distribution of external or internal loads, this redistribution must be taken into account.
(d)
[Simpli.edstructuraldesign criteria maybe usedifthey resultindesignloads notless than those prescribed in Secs. 23.331 through 23.521. For airplane con.gurations described in appendix A, Sec. 23.1, the design criteria of appendix A of this part are an approved equivalent of Secs. 23.321 through 23.459. If appendix A of this partis used, the entire appendix mustbe substitutedfor the correspondingsections of this part.]
Amdt. 23-48, E.. 03/11/96
FAR23.302 :[Canard or tandem wing con.gurations.]
[The forwardstructure of a canard or tandem wing con.guration must :
(a)
Meet all requirementsof subpartC and subpartD of thispart applicabletoa wing; and
(b)
Meet all requirements applicable to the function performed by these surfaces.] Amdt. 23-42, E.. 02/04/91
FAR 23.303 : Factor of safety.
Unless otherwise provided, a factor of safety of 1.5 must be used.
FAR 23.305 : Strength and deformation.
(a)
The structure must be able to support limit loads without detrimental, permanent deformation.At anyload up tolimitloads,thedeformationmay notinterferewith safe operation.
(b)
[The structure must be able to support ultimate loads without failure for at least three seconds, except local failures or structural instabilities between limit and ultimate load are acceptable only if the structure can sustain the required ultimate loadfor atleastthree seconds.However,whenproof of strengthis shownbydynamic tests simulating actual load conditions, the three second limit does not apply.]
Amdt. 23-45, E.. 09/07/93
FAR 23.307 : Proof of structure.
(a)
Compliance with the strength and deformation requirements of Sec. 23.305 must be shown for each critical load condition. Structural analysis may be used only if the structure conforms to those for which experience has shown this method to be reliable. In other cases, substantiating load tests must be made. Dynamic tests, including structural .ight tests, are acceptable if the design load conditions have been simulated.
(b)
Certainparts of the structure mustbetested as speci.edinSubpartD of thispart.
30.2 Flight Loads
FAR 23.321 : General.
(a)
Flightloadfactors representthe ratio ofthe aerodynamicforce component(acting normal to the assumed longitudinal axis of the airplane) to the weight of the air-plane. A positive .ight load factor is one in which the aerodynamic force acts upward, with respect to the airplane.
(b)
Compliance with the .ight load requirements of this subpart must be shown–
(1)
Ateach critical altitude within the rangein whichthe airplane maybe expected to operate;
(2)
At each weight from the design minimum weight to the design maximum weight; and
(3)
For eachrequired altitude and weight,for anypracticabledistribution ofdispo-sable load within the operating limitations speci.ed in Secs. 23.1583 through 23.1589.
(c)
[When signi.cant, the e.ects ofcompressibility must be taken into account] Amdt. 23-45, E.. 09/07/93
FAR 23.331 : Symmetrical .ight conditions.
(a)
The appropriate balancing horizontal tail load must be accounted for in a rational or conservative manner when determining the wing loads and linear inertia loads corresponding to any of the symmetrical .ight conditions speci.ed in Secs. 23.331 through 23.341.
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本文链接地址：FAA规章 美国联邦航空规章 Federal Aviation Regulations 1(142)
