---
kind: "section"
citation: "14 C.F.R. § 35.37"
title: "14"
number: "35.37"
heading: "Fatigue limits and evaluation."
url: "https://uscodex.org/cfr/14/35.37"
---

# §35.37. Fatigue limits and evaluation.


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

- (a) Fatigue limits must be established by tests, or analysis based on tests, for propeller:
  - (1) **Hubs.**
  - (2) **Blades.**
  - (3) **Blade retention components.**
  - (4) Components which are affected by fatigue loads and which are shown under [§ 35.15](/cfr/14/35.15.md) 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 [§ 23.2400(c)](/cfr/14/23.2400.md?p=c) or [§ 25.907](/cfr/14/25.907.md) of this chapter, as applicable; or
  - (2) **A typical airplane.**

## Notes

### 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]