(b)
Turbine engines.
(1)
[Each turbine engine must operate throughout the .ight power range of the engine(includingidling), without the accumulation ofice on the engine,in-let system components, or airframe components that would adversely a.ect engine operation or cause a serious loss of power or thrust–
(i)
Under the icing conditions speci.ed in Appendix C, and
(ii)
In falling and blowing snow within the limitations established for the airplane for such operation.]
(2)
Each turbine engine must idlefor30 minutes on theground, with the airbleed available for engine icing protection at its critical condition, without adverse a.ect, in an atmosphere that is at a temperature between 15'and 30'F. (between-9 'and -1 'C) andhas aliquid water content notless than0.3grams per cubic meter in the form of drops having a mean e.ective diameter not less than 20 microns, followed by momentary operation at takeo. power or
′
Elodie Roux. Septembre 2003
Subpart E : Powerplant
thrust. During the 30 minutes of idle operation, the engine may be run up periodically to a moderate power or thrust setting in a manner acceptable to the Administrator.
(c) Supercharged reciprocating engines. For each engine having a supercharger to pres-surize the air before it enters the carburetor, the heat rise in the air caused by thatsupercharging atany altitude maybe utilizedindetermining compliancewith paragraph(a) ofthis sectioniftheheat rise utilizedisthat which willbe avai-lable, automatically, for the applicable altitude and operating condition because of supercharging.
Amdt. 25-72, E.. 8/20/90
FAR 25.1101 : Carburetor air preheater design.
Each carburetor airpreheater mustbedesigned and constructed to–
(a)
Ensure ventilation of the preheater when the engine is operated in cold air;
(b)
Allow inspection of the exhaust manifold parts that it surrounds; and
(c)
Allow inspection of critical parts of the preheater itself.
FAR25.1103:[Inductionsystemductsandairduct systems.]
(a)
[Each induction system duct upstream of the .rst stage of the engine supercharger and of the auxiliary power unit compressor must have a drain to prevent the ha-zardous accumulation of fuel and moisture in the ground attitude. No drain may discharge where it might cause a .re hazard.]
(b)
Each induction system duct must be–
(1)
Strongenoughtopreventinduction systemfailures resultingfrom normalback-.re conditions; and
(2)
[Fire resistant if it is in any .re zone for whicha .re-extinguishing system is required,exceptthatductsforauxiliarypowerunitsmustbe .reproof within the auxiliarypower unit .re zone.]
(c)
Eachduct connected to componentsbetween which relative motion could exist must have means for .exibility.
(d)
[Forturbine engine andauxiliarypowerunitbleed airduct systems, nohazard may result if a duct failure occurs at any point between the air duct source and the airplane unit served by the air.
(e)
Each auxiliary power unit induction system duct must be .reproof for a su.cient distance upstream of the auxiliary power unit compartment to prevent hot gas reverse .ow from burning through auxiliary power unit ducts and entering any other compartment or area of the airplane in which a hazard would be created resulting fromthe entry ofhotgases.The materials used toformthe remainder of the induction system duct and plenum chamber of the auxiliary power unit must be capable of resisting the maximum heat conditions likely to occur.
(f)
Each auxiliary power unit induction system duct must be constructed of materials thatwill notabsorb ortrap hazardousquantitiesof .ammable .uidsthatcouldbe ignited in the event of a surge or reverse .ow condition.]
Amdt. 25-46, E.. 12/1/78
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本文链接地址：FAA规章 美国联邦航空规章 Federal Aviation Regulations 4(5)
