(1)
A single engine excluding turbine powerplants;
(2)
A main wing located closer to the airplane’s center of gravity than to the aft, fuselage-mounted, empennage;
(3)
A main wing that contains a quarter-chord sweep angle of not more than 15 degreesfore or aft;
(4)
Amainwing thatisequipped with trailing-edgecontrols(aileronsor .aps,or both);
(5)
A main wing aspect ratio not greater than 7;
(6)
A horizontal tail aspect ratio not greater than 4;
(7)
A horizontal tail volume coe.cient not less than 0.34;
(8)
A vertical tail aspect ratio notgreaterthan2;
(9)
A vertical tailplatform area notgreaterthan10percent of the wingplatform area; and
(10)
Symmetrical airfoils must be used in both the horizontal and vertical tail designs.
(b)
Appendix A criteria may not be used on any airplane con.guration that contains any of the following design features :
(1)
Canard, tandem-wing, close-coupled, or tailless arrangements of the lifting surfaces;
(2)
Biplane or multiplane wing arrangements;
(3)
T-tail,V-tail, or cruciform-tail(+) arrangements;
(4)
Highly-swept wing platform (more than 15-degrees of sweep at the quarter-chord), delta planforms, or slatted lifting surfaces; or
(5)
Winglets or other wing tip devices, or outboard .ns.] Amdt. 23-48, E.. 03/11/96
FAR 23.A3 : Special symbols.
n1 :Airplane Positive Maneuvering Limit Load Factor.
n2 :Airplane Negative Maneuvering Limit Load Factor.
n3 :Airplane Positive Gust Limit Load Factor at VC.
n4 :Airplane Negative Gust Limit Load Factor at VC.
nflap :Airplane Positive Limit Load Factor with Flaps Fully Extended at VF.
W
[.VFmin :MinimumDesignFlap Speed =11.0 n1 kts.
S W
.VAmin :MinimumDesignManeuvering Speed =15.0 n1 S kts.
W
.VCmin :MinimumDesignCruising Speed =17.0 n1 S kts.
W
.VDmin :MinimumDesignDiveSpeed =24.0 n1 S kts.]
. :Also see paragraph A23.7(e)(2) of this Appendix.
Amdt. 23-28, E.. 04/28/82
FAR 23.A5 : Certi.cation in more than one category.
The criteria in this appendix may be used for certi.cation in the normal, utility, and acrobatic categories, or in any combination of these categories. If certi.cation in morethan one categoryisdesired,thedesign category weightsmustbe selected to make the term “n1 W” constant for all categories or greater for one desired category than for others. The wings and control surfaces (including wing .aps and tabs) need only be investigated for the maximum value of “n1 W”, or for the category corresponding to the maximum design weight, where “n1 W” is constant. If the acrobatic category is selected, a special unsymmetrical .ight load investigation in accordance with subpara-graphs A23.9(c)(2) and A23.11(c)(2) of this appendix must be completed. The wing, wing carrythrough,and thehorizontal tail structuresmustbe checkedforthiscondition. The basic fuselage structure need only be investigated for the highest load factor design category selected. The local supporting structure for dead weight items need only be designed for the highest load factor imposed when the particular items are installed in the airplane. The engine mount, however, must be designed for a higher side load factor, if certi.cation in the acrobatic category is desired, than that required for certi.cation in the normal and utility categories. When designing for landing loads, the landing gear and the airplane as a whole need only be investigated for the category corresponding to the maximum design weight. These simpli.cations apply to single-engine aircraft of conventional types for which experience is available, and the Administrator may require additional investigations for aircraft with unusual design features.
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本文鏈接地址：FAA規章 美國聯邦航空規章 Federal Aviation Regulations 3(7)
