14 C.F.R. § 23.341 Gust loads factors.
Title 14 - Aeronautics and Space
(a) Each airplane must be designed to withstand loads on each lifting surface resulting from gusts specified in §23.333(c). (b) The gust load for a canard or tandem wing configuration must be computed using a rational analysis, or may be computed in accordance with paragraph (c) of this section, provided that the resulting net loads are shown to be conservative with respect to the gust criteria of §23.333(c). (c) In the absence of a more rational analysis, the gust load factors must be computed as follows—
Where— K µg=2(W/S)/ρ Cag=airplane mass ratio; U ρ=Density of air (slugs/cu.ft.); W/S=Wing loading (p.s.f.) due to the applicable weight of the airplane in the particular load case. W/S=Wing loading (p.s.f.); C=Mean geometric chord (ft.); g=Acceleration due to gravity (ft./sec.2 ) V=Airplane equivalent speed (knots); and a=Slope of the airplane normal force coefficient curve C [Amdt. 23–7, 34 FR 13088, Aug. 13, 1969, as amended by Amdt. 23–42, 56 FR 352, Jan. 3, 1991; Amdt. 23–48, 61 FR 5144, Feb. 9, 1996]
Title 14: Aeronautics and Space
PART 23—AIRWORTHINESS STANDARDS: NORMAL, UTILITY, ACROBATIC, AND COMMUTER CATEGORY AIRPLANES
Subpart C—Structure
Flight Loads
§ 23.341 Gust loads factors.