cfr_sections: 14:14:1.0.1.3.15.3.169.19

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section_id	title_number	title_name	chapter	subchapter	part_number	part_name	subpart	subpart_name	section_number	section_heading	agency	authority	source_citation	amendment_citations	full_text
14:14:1.0.1.3.15.3.169.19	14	Aeronautics and Space	I	C	27	PART 27—AIRWORTHINESS STANDARDS: NORMAL CATEGORY ROTORCRAFT	C	Subpart C—Strength Requirements	27.473	§ 27.473 Ground loading conditions and assumptions.	FAA	49 U.S.C. 106(f), 106(g), 40113, 44701-44702, 44704.	Docket No. 5074, 29 FR 15695, Nov. 24, 1964, unless otherwise noted.	[Amdt. 27-2, 33 FR 963, Jan. 26, 1968]	(a) For specified landing conditions, a design maximum weight must be used that is not less than the maximum weight. A rotor lift may be assumed to act through the center of gravity throughout the landing impact. This lift may not exceed two-thirds of the design maximum weight. (b) Unless otherwise prescribed, for each specified landing condition, the rotorcraft must be designed for a limit load factor of not less than the limit inertia load factor substantiated under § 27.725.