§ 35.37. Fatigue limits and evaluation.

174 words·~1 min read·/us/cfr/t14/s§ 35.37·

A research copy — for the controlling text, always check the official state or federal source. Not legal advice.

This section does not apply to fixed-pitch wood propellers of conventional design.

(a)Fatigue limits must be established by tests, or analysis based on tests, for propeller:

(1)Hubs.

(2)Blades.

(3)Blade retention components.

(4)Components which are affected by fatigue loads and which are shown under § 35.15 to have a fatigue failure mode leading to hazardous propeller effects.

(b)The fatigue limits must take into account:

(1)All known and reasonably foreseeable vibration and cyclic load patterns that are expected in service; and

(2)Expected service deterioration, variations in material properties, manufacturing variations, and environmental effects.

(c)A fatigue evaluation of the propeller must be conducted to show that hazardous propeller effects due to fatigue will be avoided throughout the intended operational life of the propeller on either:

(1)The intended airplane by complying with § 23.2400(c) or § 25.907 of this chapter, as applicable; or

(2)A typical airplane. [Amdt. 35-8, 73 FR 63348, Oct. 24, 2008, as amended by Doc. FAA-2015-1621, Amdt. 35-10, 81 FR 96700, Dec. 30, 2016]