C.F.R. » Title 14 » CHAPTER I—FEDERAL AVIATION ADMINISTRATION, DEPARTMENT OF TRANSPORTATION › SUBCHAPTER C—AIRCRAFT › PART 33—AIRWORTHINESS STANDARDS: AIRCRAFT ENGINES › Subpart B—Design and Construction; General

14 C.F.R. § 33.19

Durability

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(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.

[Doc. No. 3025, 29 FR 7453, June 10, 1964, as amended by Amdt. 33-9, 45 FR 60181, Sept. 11, 1980; Amdt. 33-10, 49 FR 6851, Feb. 23, 1984; Amdt. 33-28, 73 FR 63346, Oct. 24, 2008]
Notes of Decisions
Cited in 1 case, 2012–2012 · leading case: Sikkelee v. Precision Airmotive, Corp., 876 F. Supp. 2d 479 (M.D. Penn. 2012).
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Sikkelee v. Precision Airmotive, Corp., 876 F. Supp. 2d 479 (M.D. Penn. 2012). “101, and by willfully concealing the same from the FAA in violation of mandatory reporting requirements — knowingly designing or constructing an engine part which permits an unsafe condition of the engine between overhaul periods in violation of 14 C.F.R. § 33.19 and Civil Air…”
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