(b)
Except asprovidedinparagraphs(c),(d),and(e) of this section,each externalline, .tting, and other component, which contains or conveys .ammable .uid must be .re resistant. Components must be shielded or located to safeguard against the ignition of leaking .ammable .uid.

(c)
Flammable .uid tanks and supports which are part of and attached to the engine must be .reproof or be enclosed by a .reproof shield unless damage by .re to any non-.reproof part will not cause leakage or spillage of .ammable .uid. For a reciprocating engine having an integral oil sump of less than [25-quart] capacity, the oil sump need not be .reproof nor be enclosed by a .reproof shield.

(d)
For turbine engines type certi.cated for use in supersonic aircraft, each external component which conveys or contains .ammable .uid must be .reproof.

(e) Unwantedaccumulationof.ammable .uid and vapormustbepreventedbydraining and venting.
Amdt. 33-10, E.. 3/26/84
FAR 33.19 : Durability.
(a)
Engine design and construction must minimize the development of an unsafe condi-tion 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 andtrajectories offragments resulting from rotorbladefai-lure that lie outside the compressor and turbine rotor cases must be de.ned.]

(b)
Each component of the propeller blade pitch control system which is a part of the engine type design must meet the requirements of Sec. 35.42 of this chapter.

Amdt. 33-10, E.. 3/26/84
FAR 33.21 : Engine cooling.
Enginedesign and construction mustprovidethe necessary cooling under conditions in which the airplane is expected to operate.
FAR 33.23 : Engine mounting attachments and structure.
(a)
[The maximum allowable limit andultimate loads for engine mounting attachments and related engine structure must be speci.ed.

(b)
The engine mounting attachments and related engine structure must be able to withstand–

(1)
The speci.ed limit loads without permanent deformation; and

(2)
The speci.ed ultimate loads without failure, but may exhibit permanent de-formation.]

Amdt. 33-10, E.. 3/26/84
FAR 33.25 : Accessory attachments.
The engine mustoperateproperly withthe accessorydrive and mounting attachments loaded.[Each engine accessory drive and mounting attachment mustincludeprovisions for sealingtoprevent contamination of, or unacceptableleakagefrom, the engineinterior. A drive and mounting attachment requiring lubrication for external drive splines, or coupling by engine oil, must include provisions for sealing to prevent unacceptable loss of oil and toprevent contaminationfrom sources outside the chamber enclosing the drive connection. The design of the engine must allow for the examination, adjustment, or removal of each accessory required for engine operation.] Amdt. 33-10, E.. 3/26/84
FAR33.27:[Turbine,compressor,fan, andturbosuperchargerrotors.]
(a) [Turbine, compressor,fan, andturbosuperchargerrotors musthave su.cientstrength to withstandthetest conditions speci.edinparagraph(c) ofthis section.
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Elodie Roux. Septembre 2003
SubpartB :Design andConstruction;General
(b)
The design and functioning of engine control devices, systems, and instruments must give reasonable assurance that those engine operating limitations that a.ect turbine, compressor, and turbosupercharger rotor structural integrity will not be exceeded in service.

(c)
The most critically stressed rotor component(exceptblades) of eachturbine, com-pressor, and fan, including integral drum rotors and centrifugal compressors in an engine or turbosupercharger, as determined by analysis or other acceptable means, must be tested for a period of 5 minutes–

(1)
At its maximum operating temperature, except as provided in paragraph (c)(2)(iv)ofthis section; and
　
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本文鏈接地址：FAA規章 美國聯邦航空規章 Federal Aviation Regulations 5(127)