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14 CFR Ch. I (1–1–02 Edition)

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14 CFR Ch. I (1–1–02 Edition) § 33.7 14 CFR Ch. I (1–1–02 Edition) (a) Installation instructions. (1) The lo- (ii) Oil at the oil inlet; and cation of engine mounting attach- (iii) Turbosupercharger turbine wheel ments, the method of attaching the en- inlet gas. gine to the aircraft, and the maximum (5) Pressure of— allowable load for the mounting at- (i) Fuel at the fuel inlet; and tachments and related structure. (ii) Oil at the main oil gallery. (2) The location and description of (6) Accessory drive torque and over- engine connections to be attached to hang moment. accessories, pipes, wires, cables, ducts, (7) Component life. and cowling. (8) Turbosupercharger turbine wheel (3) An outline drawing of the engine r.p.m. including overall dimensions. (c) For turbine engines, ratings and (b) Operation instructions. (1) The op- operating limitations are established erating limitations established by the relating to the following: Administrator. (1) Horsepower, torque, or thrust, (2) The power or thrust ratings and r.p.m., gas temperature, and time for— procedures for correcting for nonstand- (i) Rated maximum continuous power ard atmosphere. or thrust (augmented); (3) The recommended procedures, (ii) Rated maximum continuous under normal and extreme ambient power or thrust (unaugmented); conditions for— (iii) Rated takeoff power or thrust (i) Starting; (augmented); (ii) Operating on the ground; and (iv) Rated takeoff power or thrust (iii) Operating during flight. (unaugmented); [Amdt. 33–6, 39 FR 35463, Oct. 1, 1974, as (v) Rated 30-minute OEI power; amended by Amdt. 33–9, 45 FR 60181, Sept. 11, (vi) Rated 21⁄2-minute OEI power; 1980] (vii) Rated continuous OEI power; and § 33.7 Engine ratings and operating (viii) Rated 2-minute OEI Power; limitations. (ix) Rated 30-second OEI power; and (a) Engine ratings and operating lim- (x) Auxiliary power unit (APU) mode itations are established by the Admin- of operation. istrator and included in the engine cer- (2) Fuel designation or specification. tificate data sheet specified in § 21.41 of (3) Oil grade or specification. this chapter, including ratings and lim- (4) Hydraulic fluid specification. itations based on the operating condi- (5) Temperature of— tions and information specified in this (i) Oil at a location specified by the section, as applicable, and any other applicant; information found necessary for safe (ii) Induction air at the inlet face of operation of the engine. a supersonic engine, including steady (b) For reciprocating engines, ratings state operation and transient over- and operating limitations are estab- temperature and time allowed; lished relating to the following: (iii) Hydraulic fluid of a supersonic (1) Horsepower or torque, r.p.m., engine; manifold pressure, and time at critical (iv) Fuel at a location specified by pressure altitude and sea level pressure the applicant; and altitude for— (v) External surfaces of the engine, if (i) Rated maximum continuous power specified by the applicant. (relating to unsupercharged operation (6) Pressure of— or to operation in each supercharger (i) Fuel at the fuel inlet; mode as applicable); and (ii) Oil at a location specified by the (ii) Rated takeoff power (relating to applicant; unsupercharged operation or to oper- (iii) Induction air at the inlet face of ation in each supercharger mode as ap- a supersonic engine, including steady plicable). state operation and transient over- (2) Fuel grade or specification. pressure and time allowed; and (3) Oil grade or specification. (iv) Hydraulic fluid. (4) Temperature of the— (7) Accessory drive torque and over- (i) Cylinder; hang moment. 738 VerDate 11<MAY>2000 06:37 Jan 18, 2002 Jkt 197040 PO 00000 Frm 00738 Fmt 8010 Sfmt 8010 Y:\SGML\197040T.XXX pfrm01 PsN: 197040T Federal Aviation Administration, DOT § 33.17 (8) Component life. or an equivalent representation of en- (9) Fuel filtration. gine usage. It includes starting the en- (10) Oil filtration. gine, accelerating to maximum rated (11) Bleed air. power or thrust, decelerating, and stop- (12) The number of start-stop stress ping. For each cycle, the rotor struc- cycles approved for each rotor disc and tural parts must reach stabilized tem- spacer. perature during engine operation at a (13) Inlet air distortion at the engine maximum rate power or thrust and inlet. after engine shutdown, unless it is (14) Transient rotor shaft overspeed shown that the parts undergo the same r.p.m., and number of overspeed occur- stress range without temperature sta- rences. bilization. (15) Transient gas overtemperature, and number of overtemperature occur- [Amdt. 33–10, 49 FR 6850, Feb. 23, 1984] rences. § 33.15 Materials. (16) For engines to be used in super- sonic aircraft, engine rotor The suitability and durability of ma- windmilling rotational r.p.m. terials used in the engine must— (a) Be established on the basis of ex- [Amdt. 33–6, 39 FR 35463, Oct. 1, 1974, as perience or tests; and amended by Amdt. 33–10, 49 FR 6850, Feb. 23, 1984; Amdt. 33–11, 51 FR 10346, Mar. 25, 1986; (b) Conform to approved specifica- Amdt. 33–12, 53 FR 34220, Sept. 2, 1988; Amdt. tions (such as industry or military 33–18, 61 FR 31328, June 19, 1996] specifications) that ensure their having the strength and other properties as- § 33.8 Selection of engine power and sumed in the design data. thrust ratings. Secs. 313(a), 601, and 603, 72 Stat. 759, 775, 49 (a) Requested engine power and U.S.C. 1354(a), 1421, and 1423; sec. 6(c), 49 thrust ratings must be selected by the U.S.C. 1655(c)) applicant. (b) Each selected rating must be for [Amdt. 33–8, 42 FR 15047, Mar. 17, 1977, as amended by Amdt. 33–10, 49 FR 6850, Feb. 23, the lowest power or thrust that all en- 1984] gines of the same type may be expected to produce under the conditions used to § 33.17 Fire prevention. determine that rating. (a) The design and construction of [Amdt. 33–3, 32 FR 3736, Mar. 4, 1967] the engine and the materials used must minimize the probability of the occur- Subpart B—Design and rence and spread of fire. In addition, Construction; General the design and construction of turbine engines must minimize the probability § 33.11 Applicability. of the occurrence of an internal fire This subpart prescribes the general that could result in structural failure, design and construction requirements overheating, or other hazardous condi- for reciprocating and turbine aircraft tions. engines. (b) Except as provided in paragraphs (c), (d), and (e) of this section, each ex- § 33.13 [Reserved] ternal line, fitting, and other compo- nent, which contains or conveys flam- § 33.14 Start-stop cyclic stress (low- mable fluid must be fire resistant. cycle fatigue). Components must be shielded or lo- By a procedure approved by the FAA, cated to safeguard against the ignition operating limitations must be estab- of leaking flammable fluid. lished which specify the maximum al- (c) Flammable fluid tanks and sup- lowable number of start-stop stress cy- ports which are part of and attached to cles for each rotor structural part the engine must be fireproof or be en- (such as discs, spacers, hubs, and shafts closed by a fireproof shield unless dam- of the compressors and turbines), the age by fire to any non-fireproof part failure of which could produce a hazard will not cause leakage or spillage of to the aircraft. A start-stop stress flammable fluid. For a reciprocating cycle consists of a flight cycle profile engine having an integral oil sump of 739 VerDate 11<MAY>2000 06:37 Jan 18, 2002 Jkt 197040 PO 00000 Frm 00739 Fmt 8010 Sfmt 8010 Y:\SGML\197040T.XXX pfrm01 PsN: 197040T.
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