§3.185 Maneuvering envelope.

The airplane shall be assumed to subjected to symmetrical maneuvers resulting in the following limit load factors, except where limited by maximum (static) lift coefficients: (a) The positive maneuvering load factor specified in § 3.186 at all speeds up to Vd, (b) The negative maneuvering load factor specified in § 3.188 at speed Vc; and factors varying linearly with speed from the specified value at Vc to 0.0 at Vd for the N category and - 1.0 at Vd for the A and U categories. § 3.186 Maneuvering load factors. (a) The positive limit maneuvering load factors shall not be less than the following values (see Fig. 3-2): except that n need not be greater than 3.8 and shall not be less than 2.5. For airplanes certificated as characteristically incapable of spinning, n need not exceed 3.5. nel + KLEv... STS WAS where: Ko» YO WeS1 (for WS <. 16 p.s.ti = 133 - 267 ifor WS > lh p.s.tj iWsjs n = 4.4--------------------------------Category U n = 6.0--------------------------------Category A (b) The negative limit maneuvering load factors shall not be less than -0.4 times the positive load factor for the N and U categories, and shall not be less than -0.5 times the positive load factor for the A category. (c) Lower values of maneuvering load factor may be employed only if it be proven that the airplane embodies features of design which make it impossible to exceed such values in flight. (See also § 3.106.)