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

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

   1. (1) Hubs.
   2. (2) Blades.
   3. (3) Blade retention components.
   4. (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.

2. (b) The fatigue limits must take into account:

   1. (1) All known and reasonably foreseeable vibration and cyclic load patterns that are expected in service; and
   2. (2) Expected service deterioration, variations in material properties, manufacturing variations, and environmental effects.

3. (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. (1) The intended airplane by complying with § 23.2400(c) or § 25.907 of this chapter, as applicable; or
   2. (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]