(d)
Correction factor for cylinder barrel temperatures. Cylinder barrel temperatures mustbe correctedby adding to them0.7 times thedi.erencebetween the[maxi-mum ambient atmospheric temperature] and the temperature of the ambient air at the time of the .rst occurrence of the maximum cylinder barrel temperature recorded during the cooling test.
Amdt. 27-14, E.. 3/1/78
FAR 27.1045 : Cooling test procedures
(a)
General. For each stage of .ight, the cooling tests must be conducted with the rotorcraft–
(1)
In the con.guration most critical for cooling; and
(2)
Under the conditions most critical for cooling.
(b)
Temperature stabilization. For the purpose of the cooling tests, a temperature is ”stabilized” when its rate of change is less than two degrees F. per minute. The following component and engine .uid temperature stabilization rules apply :
(1)
For each rotorcraft, and for each stage of .ight–
(i)
The temperatures must be stabilized under the conditions from which entry is made into the stage of .ight being investigated; or
(ii)
If the entry condition normally does not allow temperatures to stabilize, operationthroughthefuel entry condition mustbe conductedbefore entry into the stage of .ight being investigated in order to allow the tempera-tures to attain their natural levels at the time of entry.
(2)
Foreachhelicopterduringthetakeo.stageof.ight,theclimb attakeo.power must be preceded by a period of hover during which the temperatures are stabilized.
(c)
Duration of test. For each stage of .ight the tests must be continued until–
(1)
[The temperatures stabilize or 5 minutes after the occurrence of the highest temperature recorded, as appropriatetothetest condition;]
(2)
Thatstageof .ightiscompleted; or
(3)
An operating limitation is reached. Amdt. 27-23, E.. 10/3/88
65.7 Induction System
FAR 27.1091 : Air induction
(a) The airinduction systemfor each engine must supply the air requiredby that engine under the operating conditions and maneuvers for which certi.cation is requested.
′
Elodie Roux. Septembre 2003
Subpart E : Powerplant
(b)
Eachcold airinductionsystemopening mustbeoutsidethecowlingifback.re .ames can emerge.
(c)
If fuel can accumulate in any air induction system, that system must have drains that discharge fuel–
(1)
Clear of the rotorcraft; and
(2)
Out of the path of exhaust .ames.
(d)
[For turbine engine poweredrotorcraft–
(1)
There must be means to prevent hazardous quantities of fuel leakage or over-.ow from drains, vents, or other components of .ammable .uid systems from entering the engineintake system; and
(2)
The airinletducts mustbelocatedorprotected so as to minimize theingestion of foreign matter during takeo., landing, and taxiing.]
Amdt. 27-23, E.. 10/3/88
FAR 27.1093 : Induction system icing protection
(a)
Reciprocating engines. Each reciprocating engine air induction system must have means to prevent and eliminate icing. Unless this is done by other means, it must be shown that, in airfree of visible moisture at a temperature of 30degreesF., and with the engines at 75 percent of maximum continuous power–
(1)
Each rotorcraft with sea level engines using conventional venturi carburetors has apreheaterthat canprovide aheat rise of90degreesF.;
(2)
Each rotorcraft with sea level engines using carburetors tending to prevent icing has a sheltered alternate source of air, and that the preheat supplied to the alternate air intake is not less than that provided by the engine cooling air downstream of the cylinders;
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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(115)
