(a) Fatigue limits must be established by tests, or analysis based on tests, for propeller:
(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 §§23.907 or 25.907 of this chapter, as applicable; or
(2) A typical airplane.
[Amdt. No. 35–8, 73 FR 63348, Oct. 24, 2008]