FAA Federal Aviation Regulations (FARS, 14 CFR)

The following durability requirements apply to propeller blade pitch control system components:

(a) Except as provided in paragraph (b) of this section, each propeller blade pitch control system component, including governors, pitch change assemblies, pitch locks, mechanical stops, and feathering system components, must be subjected in tests to cyclic loadings that simulate the frequency and amplitude those to which the component would be subjected during 1,000 hours of propeller operation.

(b) Compliance with paragraph (a) of this section may be shown by a rational analysis based on the results of tests on similar components.

[Amdt. 35-5, 45 FR 60182, Sept. 11, 1980]