{"data":{"id":"us/14-cfr-35.37","jurisdiction":"us","citation":"14 CFR 35.37","heading":"Fatigue limits and evaluation.","body":"This section does not apply to fixed-pitch wood propellers of conventional design.\n(a) Fatigue limits must be established by tests, or analysis based on tests, for propeller:\n(1) Hubs.\n(2) Blades.\n(3) Blade retention components.\n(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.\n(b) The fatigue limits must take into account:\n(1) All known and reasonably foreseeable vibration and cyclic load patterns that are expected in service; and\n(2) Expected service deterioration, variations in material properties, manufacturing variations, and environmental effects.\n(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:\n(1) The intended airplane by complying with § 23.2400(c) or § 25.907 of this chapter, as applicable; or\n(2) A typical airplane.","path":["Title 14—Aeronautics and Space","CHAPTER I—FEDERAL AVIATION ADMINISTRATION, DEPARTMENT OF TRANSPORTATION","SUBCHAPTER C—AIRCRAFT","PART 35—AIRWORTHINESS STANDARDS: PROPELLERS","Subpart C—Tests and Inspections"],"source_url":"https://www.ecfr.gov/api/versioner/v1/full/2026-08-25/title-14.xml","current_through":"2026-08-25","vintage":"","retrieved_at":"2026-08-27T02:24:20Z","sha256":"decf8059cd345c37854bb75291728c981fd79686cf89036ee8db2da55ef7071a","source_id":"us-cfr","stale":true,"prev":"us/14-cfr-35.36","next":"us/14-cfr-35.38"},"notice":"GroundRules: Original legal text. Not legal advice."}