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14 CFR Ch. I (1–1–16 Edition) § 23.1589

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14 CFR Ch. I (1–1–16 Edition) § 23.1589 § 23.1589 14 CFR Ch. I (1–1–16 Edition) (11) The altimeter system calibration (1) Canard, tandem-wing, close-coupled, or required by § 23.1325(e). tailless arrangements of the lifting surfaces; (2) Biplane or multiplane wing arrange- [Doc. No. 27807, 61 FR 5194, Feb. 9, 1996, as ments; amended by Amdt. 23–62, 76 FR 75763, Dec. 2, (3) T-tail, V-tail, or cruciform-tail ( + ) ar- 2011] rangements; (4) Highly-swept wing platform (more than § 23.1589 Loading information. 15-degrees of sweep at the quarter-chord), The following loading information delta planforms, or slatted lifting surfaces; or must be furnished: (5) Winglets or other wing tip devices, or (a) The weight and location of each outboard fins. item of equipment that can be easily removed, relocated, or replaced and A23.3 Special symbols. that is installed when the airplane was n1 = Airplane Positive Maneuvering Limit weighed under the requirement of Load Factor. § 23.25. n2 = Airplane Negative Maneuvering Limit (b) Appropriate loading instructions Load Factor. for each possible loading condition be- n3 = Airplane Positive Gust Limit Load Fac- tor at VC. tween the maximum and minimum n = Airplane Negative Gust Limit Load Fac- weights established under § 23.25, to fa- 4 tor at VC. cilitate the center of gravity remain- nflap = Airplane Positive Limit Load Factor ing within the limits established under With Flaps Fully Extended at VF. § 23.23. [Doc. No. 4080, 29 FR 17955, Dec. 18, 1964, as amended by Amdt. 23–45, 58 FR 42167, Aug. 6, 1993; Amdt. 23–50, 61 FR 5195, Feb. 9, 1996] APPENDIX A TO PART 23—SIMPLIFIED DESIGN LOAD CRITERIA A23.1 General. (a) The design load criteria in this appen- dix are an approved equivalent of those in §§ 23.321 through 23.459 of this subchapter for an airplane having a maximum weight of 6,000 pounds or less and the following con- figuration: (1) A single engine excluding turbine pow- A23.5 Certification in more than one category. erplants; The criteria in this appendix may be used (2) A main wing located closer to the air- for certification in the normal, utility, and plane’s center of gravity than to the aft, fu- acrobatic categories, or in any combination selage-mounted, empennage; of these categories. If certification in more (3) A main wing that contains a quarter- than one category is desired, the design cat- chord sweep angle of not more than 15 de- egory weights must be selected to make the grees fore or aft; term n1W constant for all categories or (4) A main wing that is equipped with trail- greater for one desired category than for ing-edge controls (ailerons or flaps, or both); others. The wings and control surfaces (in- (5) A main wing aspect ratio not greater cluding wing flaps and tabs) need only be in- than 7; vestigated for the maximum value of n1W, or (6) A horizontal tail aspect ratio not great- for the category corresponding to the max- er than 4; imum design weight, where n1W is constant. (7) A horizontal tail volume coefficient not If the acrobatic category is selected, a spe- less than 0.34; cial unsymmetrical flight load investigation (8) A vertical tail aspect ratio not greater in accordance with paragraphs A23.9(c)(2) than 2; and A23.11(c)(2) of this appendix must be (9) A vertical tail platform area not great- completed. The wing, wing carrythrough, er than 10 percent of the wing platform area; and the horizontal tail structures must be and checked for this condition. The basic fuse- (10) Symmetrical airfoils must be used in lage structure need only be investigated for both the horizontal and vertical tail designs. the highest load factor design category se- (b) Appendix A criteria may not be used on lected. The local supporting structure for any airplane configuration that contains any dead weight items need only be designed for of the following design features: the highest load factor imposed when the 338 VerDate Sep<11>2014 09:15 Mar 11, 2016 Jkt 238046 PO 00000 Frm 00348 Fmt 8010 Sfmt 8002 Y:\SGML\238046.XXX 238046 jstallworth on DSK7TPTVN1PROD with CFR EC28SE91.020</MATH>.
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