14 C.F.R. § 27.725 Limit drop test.
Title 14 - Aeronautics and Space
The limit drop test must be conducted as follows: (a) The drop height must be— (1) 13 inches from the lowest point of the landing gear to the ground; or (2) Any lesser height, not less than eight inches, resulting in a drop contact velocity equal to the greatest probable sinking speed likely to occur at ground contact in normal power-off landings. (b) If considered, the rotor lift specified in §27.473(a) must be introduced into the drop test by appropriate energy absorbing devices or by the use of an effective mass. (c) Each landing gear unit must be tested in the attitude simulating the landing condition that is most critical from the standpoint of the energy to be absorbed by it. (d) When an effective mass is used in showing compliance with paragraph (b) of this section, the following formula may be used instead of more rational computations:
where: W W=W W=W W=W (1) The static weight on the tailwheel with the rotorcraft resting on all wheels; or (2) The vertical component of the ground reaction that would occur at the tailwheel, assuming that the mass of the rotorcraft acts at the center of gravity and exerts a force of lg downward with the rotorcraft in the maximum nose-up attitude considered in the nose-up landing conditions. h=specified free drop height (inches). L=ration of assumed rotor lift to the rotorcraft weight. d=deflection under impact of the tire (at the proper inflation pressure) plus the vertical component of the axle travels (inches) relative to the drop mass. n=limit inertia load factor. n
Title 14: Aeronautics and Space
PART 27—AIRWORTHINESS STANDARDS: NORMAL CATEGORY ROTORCRAFT
Subpart D—Design and Construction
Landing Gear
§ 27.725 Limit drop test.