(4)
At the end of the time interval prescribed in paragraph (a)(3) of this section, the power must be reduced to maximum continuous power and the climb must be continued for at least .ve minutes after the occurrence of the highest temperature recorded.

(5) The cooling test must be conducted at an airspeed corresponding to nor-mal operatingpracticeforthe con.gurationbeing tested.However,if the coolingprovisions are sensitiveto rotorcraft speed,the most critical airs-peed must be used, but need not exceed the speed for best rate of climb with maximum continuous power.
Amdt. 29-26, E.. 10/3/88
FAR 29.1049 : Hovering cooling test procedures.
The hovering cooling provisions must be shown–
(a)
At maximum weight or at the greatest weight at which the rotorcraft can hover(ifless), at sealevel, withthepower requiredtohoverbut not more than maximum continuous power, in the ground e.ect in still air, until at least .ve minutes after the occurrence of the highest temperature recorded; and

(b)
With maximum continuous power, maximum weight, and at the altitude re-sulting in zero rate of climb for this con.guration, until at least .ve minutes after the occurrence of the highest temperature recorded.

75.7 Induction System
FAR 29.1091 : Air induction.
(a)
[The airinduction systemfor eachengine and auxiliarypower unit must supply the air required by that engine and auxiliary power unit under the operating conditions for which certi.cation is requested.

(b)
Each engine and auxiliary power unit air induction system must provide air for proper fuel metering and mixture distribution with the induction system valves in any position.]

(c)
No air intake may open within the engine accessory section or within other areasof anypowerplant compartment whereemergenceofback.re .amewould constitute a .re hazard.

(d)
Each reciprocating engine must have an alternate air source.

(e)
Each alternate air intake must be located to prevent the entrance of rain, ice, or other foreign matter.

(f)
[For turbine engine powered rotorcraft and rotorcraft incorporating auxiliary power units–

(1)
There must be means to prevent hazardous quantities of fuel leakage or over.ow from drains, vents, or other components of .ammable .uid system from entering the engine or auxiliary power unit intake system; and]

(2)
The airducts mustbelocatedorprotected so as to minimize theingestion of foreign matter during takeo., landing, and taxiing.

Amdt. 29-17, E.. 12/1/78
′
Elodie Roux. Septembre 2003
Subpart E : Powerplant
FAR 29.1093 : Induction system icing protection.
(a)
Reciprocating engines. Each reciprocating engine air induction system must have means topreventand eliminateicing.Unless thisisdoneby other means, it must be shown that, in air free of visible moisture at a temperature of 30' F., and with the engines at 60 percent of maximum continuous power–

(1)
Each rotorcraft with sea level engines using conventional venturi carbu-retors has a preheater that can provide a heat rise of 90'F.;

(2)
Eachrotorcraft with sealevel engines using carburetorstendingtoprevent icing has a preheater that can provide a heat rise of 70'F.;

(3)
Each rotorcraft with altitude engines using conventional venturi carbure-tors has a preheater that can provide a heat rise of 120'F.; and

(4)
Eachrotorcraft with altitude engines using carburetorstending toprevent icing has a preheater that can provide a heat rise of 100'F.

(b)
Turbine engines.

(1)
[It must be shown that each turbine engine and its air inlet system can operatethroughoutthe .ightpowerrangeoftheengine(includingidling)–

(i)
Without accumulating ice on engine or inlet system components that would adversely a.ect engine operation or cause a seriousloss ofpower under the icing conditions speci.ed in Appendix C of this part; 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(77)