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14 CFR Ch. I (1–1–08 Edition) § 33.19

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14 CFR Ch. I (1–1–08 Edition) § 33.19 § 33.19 14 CFR Ch. I (1–1–08 Edition) (e) Unwanted accumulation of flam- ment must include provisions for seal- mable fluid and vapor must be pre- ing to prevent contamination of, or un- vented by draining and venting. acceptable leakage from, the engine in- terior. A drive and mounting attach- (Secs. 313(a), 601, and 603, 72 Stat. 759, 775, 49 U.S.C. 1354(a), 1421, and 1423; sec. 6(c), 49 ment requiring lubrication for external U.S.C. 1655(c)) drive splines, or coupling by engine oil, must include provisions for sealing to [Amdt. 33–6, 39 FR 35464, Oct. 1, 1974, as prevent unacceptable loss of oil and to amended by Amdt. 33–8, 42 FR 15047, Mar. 17, 1977; Amdt. 33–10, 49 FR 6850, Feb. 23, 1984] prevent contamination from sources outside the chamber enclosing the § 33.19 Durability. drive connection. The design of the en- gine must allow for the examination, (a) Engine design and construction adjustment, or removal of each acces- must minimize the development of an sory required for engine operation. unsafe condition of the engine between overhaul periods. The design of the [Amdt. 33–10, 49 FR 6851, Feb. 23, 1984] compressor and turbine rotor cases must provide for the containment of § 33.27 Turbine, compressor, fan, and damage from rotor blade failure. En- turbosupercharger rotors. ergy levels and trajectories of frag- (a) Turbine, compressor, fan, and tur- ments resulting from rotor blade fail- bosupercharger rotors must have suffi- ure that lie outside the compressor and cient strength to withstand the test turbine rotor cases must be defined. conditions specified in paragraph (c) of (b) Each component of the propeller this section. blade pitch control system which is a (b) The design and functioning of en- part of the engine type design must gine control devices, systems, and in- meet the requirements of § 35.42 of this struments must give reasonable assur- chapter. ance that those engine operating limi- tations that affect turbine, compressor, [Doc. No. 3025, 29 FR 7453, June 10, 1964, as fan, and turbosupercharger rotor struc- amended by Amdt. 33–9, 45 FR 60181, Sept. 11, 1980; Amdt. 33–10, 49 FR 6851, Feb. 23, 1984] tural integrity will not be exceeded in service. § 33.21 Engine cooling. (c) The most critically stressed rotor component (except blades) of each tur- Engine design and construction must bine, compressor, and fan, including in- provide the necessary cooling under tegral drum rotors and centrifugal conditions in which the airplane is ex- compressors in an engine or turbo- pected to operate. supercharger, as determined by anal- § 33.23 Engine mounting attachments ysis or other acceptable means, must and structure. be tested for a period of 5 minutes— (1) At its maximum operating tem- (a) The maximum allowable limit perature, except as provided in para- and ultimate loads for engine mount- graph (c)(2)(iv) of this section; and ing attachments and related engine (2) At the highest speed of the fol- structure must be specified. lowing, as applicable: (b) The engine mounting attach- (i) 120 percent of its maximum per- ments and related engine structure missible r.p.m. if tested on a rig and must be able to withstand— equipped with blades or blade weights. (1) The specified limit loads without (ii) 115 percent of its maximum per- permanent deformation; and missible r.p.m. if tested on an engine. (2) The specified ultimate loads with- (iii) 115 percent of its maximum per- out failure, but may exhibit permanent missible r.p.m. if tested on turbo- deformation. supercharger driven by a hot gas sup- [Amdt. 33–10, 49 FR 6851, Feb. 23, 1984] ply from a special burner rig. (iv) 120 percent of the r.p.m. at § 33.25 Accessory attachments. which, while cold spinning, it is subject The engine must operate properly to operating stresses that are equiva- with the accessory drive and mounting lent to those induced at the maximum attachments loaded. Each engine ac- operating temperature and maximum cessory drive and mounting attach- permissible r.p.m. 810 VerDate Aug<31>2005 14:04 Feb 28, 2008 Jkt 214043 PO 00000 Frm 00820 Fmt 8010 Sfmt 8010 Y:\SGML\214043.XXX 214043 rfrederick on PROD1PC67 with CFR.
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