Code of Federal Regulations

Title 14 - Aeronautics and Space
Volume: 1Date: 2021-01-01Original Date: 2021-01-01Title: Section § 29.725 - Limit drop test.Context: Title 14 - Aeronautics and Space. CHAPTER I - FEDERAL AVIATION ADMINISTRATION, DEPARTMENT OF TRANSPORTATION. SUBCHAPTER C - AIRCRAFT. PART 29 - AIRWORTHINESS STANDARDS: TRANSPORT CATEGORY ROTORCRAFT. Subpart D - Design and Construction. - Landing Gear.
§ 29.725 Limit drop test. The limit drop test must be conducted as follows: (a) The drop height must be at least 8 inches. (b) If considered, the rotor lift specified in § 29.473(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 formulae may be used instead of more rational computations. [Please see PDF for Formula: EC28SE91.089] where: W e = the effective weight to be used in the drop test (lbs.). W = W M for main gear units (lbs.), equal to the static reaction on the particular unit with the rotorcraft in the most critical attitude. A rational method may be used in computing a main gear static reaction, taking into consideration the moment arm between the main wheel reaction and the rotorcraft center of gravity. W = W N for nose gear units (lbs.), equal to the vertical component of the static reaction that would exist at the nose wheel, assuming that the mass of the rotorcraft acts at the center of gravity and exerts a force of 1.0 g downward and 0.25 g forward. W = W t for tailwheel units (lbs.) equal to whichever of the following is critical— (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 1 g downward with the rotorcraft in the maximum nose-up attitude considered in the nose-up landing conditions. h = specified free drop height (inches). L = ratio 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 travel (inches) relative to the drop mass. n = limit inertia load factor. n j = the load factor developed, during impact, on the mass used in the drop test (i.e., the acceleration dv/dt in g 's recorded in the drop test plus 1.0). [Doc. No. 5084, 29 FR 16150, Dec. 3, 1964, as amended by Amdt. 29-3, 33 FR 967, Jan. 26, 1968]