Aeroelastic stability requirements.

CFR · 2024-01-01 · US · Title 14

(a) (b) (1) For normal conditions without failures, malfunctions, or adverse conditions, all combinations of altitudes and speeds encompassed by the V (2) For the conditions described in § 25.629(d) below, for all approved altitudes, any airspeed up to the greater airspeed defined by; (i) The V (ii) An altitude-airspeed envelope defined by a 15 percent increase in equivalent airspeed above V (c) (d) (1) Any critical fuel loading conditions, not shown to be extremely improbable, which may result from mismanagement of fuel. (2) Any single failure in any flutter damper system. (3) For airplanes not approved for operation in icing conditions, the maximum likely ice accumulation expected as a result of an inadvertent encounter. (4) Failure of any single element of the structure supporting any engine, independently mounted propeller shaft, large auxiliary power unit, or large externally mounted aerodynamic body (such as an external fuel tank). (5) For airplanes with engines that have propellers or large rotating devices capable of significant dynamic forces, any single failure of the engine structure that would reduce the rigidity of the rotational axis. (6) The absence of aerodynamic or gyroscopic forces resulting from the most adverse combination of feathered propellers or other rotating devices capable of significant dynamic forces. In addition, the effect of a single feathered propeller or rotating device must be coupled with the failures of paragraphs (d)(4) and (d)(5) of this

official document · source cfr-2024 · id 14:§ 25.629