§29.337. Limit maneuvering load factor.

14 C.F.R. § 29.337

The rotorcraft must be designed for—

(a)

A limit maneuvering load factor ranging from a positive limit of 3.5 to a negative limit of −1.0; or

(b)

Any positive limit maneuvering load factor not less than 2.0 and any negative limit maneuvering load factor of not less than −0.5 for which—

(1)

The probability of being exceeded is shown by analysis and flight tests to be extremely remote; and

(2)

The selected values are appropriate to each weight condition between the design maximum and design minimum weights.

Notes, amendments, and revision history

[Doc. No. 5084, 29 FR 16150, Dec. 3, 1964, as amended by Amdt. 27-26, 55 FR 8002, Mar. 6, 1990]

Authority: 49 U.S.C. 106(f), 106(g), 40113, 44701-44702, 44704.

Source: Docket No. 5084, 29 FR 16150, Dec. 3, 1964, unless otherwise noted.

[Doc. No. 5084, 29 FR 16150, Dec. 3, 1964, as amended by Amdt. 27-26, 55 FR 8002, Mar. 6, 1990]