§35.37. Fatigue limits and evaluation.
14 C.F.R. § 35.37
This section does not apply to fixed-pitch wood propellers of conventional design.
Fatigue limits must be established by tests, or analysis based on tests, for propeller:
Hubs.
Blades.
Blade retention components.
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.
The fatigue limits must take into account:
All known and reasonably foreseeable vibration and cyclic load patterns that are expected in service; and
Expected service deterioration, variations in material properties, manufacturing variations, and environmental effects.
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:
The intended airplane by complying with § 23.2400(c) or § 25.907 of this chapter, as applicable; or
A typical airplane.
Notes, amendments, and revision history
Amendments
[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]
Authority
Authority: 49 U.S.C. 106(f), 106(g), 40113, 44701-44702, 44704.
Source
Source: Docket No. 2095, 29 FR 7458, June 10, 1964, unless otherwise noted.
Amendments
[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]