(3)
Each rotorcraft with altitude engines using conventional venturi carburetors has apreheater capable ofproviding aheat rise of120degreesF.; and

(4)
Eachrotorcraft with altitude engines using carburetorstendingtopreventicing has a preheater that can provide a heat rise of–

(i)
100degreesF.; or

(ii)
If a .uid deicing system is used, at least 40 degrees F.

(b)
Turbine engines.

(1)
[Itmustbe shown that each turbine engine andits airinlet system can operate throughoutthe .ightpowerrangeof theengine(includingidling)–

(i)
Without accumulating ice on engine or inlet system components that would adversely a.ect engine operation or cause a serious loss of po-wer under the icing conditions speci.ed in Appendix C of Part 29 of this chapter; and

(ii)
In snow, both falling and blowing, without adverse e.ect on engine ope-ration, within the limitations established for the rotorcraft.]

(2)
Each turbine engine must idle for 30 minutes on the ground, with the air bleed available for engine icing protection at its critical condition, without

''
adverse e.ect, in an atmosphere that is at a temperature between 15and 30
''
F (between -9and -1 C) and has a liquid water content not less than 0.3
grams per cubic meter in the form of drops having a mean e.ective diameter of notless than20 microns,followedby momentary operation at takeo.power or 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 superchargers to pres-surize the air before it enters the carburetor, the heat rise in the air caused by that supercharging atany altitude maybe utilizedindetermining compliancewith paragraph(a) of this section if the heat rise utilized is that which will be avai-lable, automatically, for the applicable altitude and operating condition because of supercharging.
Amdt. 27-23, E.. 10/3/88
65.8 Exhaust System
FAR 27.1121 : General
For each exhaust system–
(a)
There mustbe meansforthermal expansion of manifolds andpipes;

(b)
There must be means to prevent local hot spots;

(c)
Exhaustgases must discharge clear of the engine airintake,fuel system components, and drains;

(d)
[Each exhaust system part with a surface hot enough to ignite .ammable .uids or vapors must be located or shielded so that leakage from any system carrying .ammable .uids or vapors will not result in a .re caused by impingement of the .uids or vapors on anypart of the exhaust systemincluding shields for the exhaust system;]

(e)
Exhaust gases may not impair pilot vision at night due to glare;

(f)
If signi.cant traps exist, each turbine engine exhaust system must have drains di-scharging clear of the rotorcraft, in any normal ground and .ight attitudes, to prevent fuel accumulation after the failure of an attempted engine start;

(g)
[Each exhaust heat exchanger must incorporate means to prevent blockage of the exhaust port after any internal heat exchanger failure.]

Amdt. 27-12, E.. 5/2/77
FAR27.1123 :[Exhaustpiping.]
(a)
[Exhaust pipingmust be heat and corrosion resistant, and must have provisions to prevent failure due to expansion by operating temperatures.

(b)
Exhaust piping must be supported to withstand any vibration and inertia loads to which it would be subjected in operations.

(c)
Exhaustpiping connected to componentsbetween which relative motion could exist must have provisions for .exibility.]

Amdt. 27-11, E.. 2/1/77
′
Elodie Roux. Septembre 2003
Subpart E : Powerplant
65.9 Powerplant Controls and Accessories
　
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本文鏈接地址：FAA規(guī)章 美國聯(lián)邦航空規(guī)章 Federal Aviation Regulations 4(116)