14 CFR 33.19
§ 33.19 Durability.
United States · 14 CFR — Aeronautics and Space · Status: effective
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- Citation
- 14 CFR 33.19, § 33.19 Durability, United States, version 1 as recorded 2026-07-09, yourstate.us, https://yourstate.us/provision/55052
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Full text
(a) Engine design and construction must minimize the development of an unsafe condition of the engine between overhaul periods. The design of the compressor and turbine rotor cases must provide for the containment of damage from rotor blade failure. Energy levels and trajectories of fragments resulting from rotor blade failure that lie outside the compressor and turbine rotor cases must be defined.
(b) Each component of the propeller blade pitch control system which is a part of the engine type design must meet the requirements of §§ 35.21, 35.23, 35.42 and 35.43 of this chapter.
Legislative history
This is a federal regulation, adopted through agency rulemaking under the Administrative Procedure Act — not enacted by a recorded vote of Congress.