32.7 Induction System
FAR 23.1091 : Air induction system.
(a)
The airinduction systemfor each engine and auxiliarypower unit and their accesso-riesmust supply theairrequiredby that engineand auxiliarypowerunit and their accessories under the operating conditions for which certi.cation is requested.

(b)
Each reciprocating engine installation must have at least two separate air intake sources, and must meet the following :

(1)
Primary airintakes may open withinthe cowling if thatpartof the cowling is isolated from the engine accessory section by a .re-resistant diaphragm or if there are means to prevent the emergence of back.re .ames.

(2)
Each alternate airintake mustbelocatedin a shelteredposition and may not open within the cowling if the emergence of back.re .ames will result in a hazard.

(3)
The supplying of air to the engine through the alternate airintake system may not resultin aloss of excessivepowerin additiontothepowerlossduetothe rise in air temperature.

(4)
Each automatic alternate air door must have an override means accessible to the .ight crew.

(5)
Each automatic alternate air door must have a means to indicate to the .ight crew when it is not closed.

(c)
For turbine engine powered airplanes–

(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 airplane mustbedesignedtoprevent water or slush onthe runway,taxi-way, or other airport operating surfacesfrombeing directedinto the engine or auxiliary power unit air intake ducts in hazardous quantities. The air intake ducts must be located or protected so as to minimize the hazard of ingestion of foreign matter during takeo., landing, and taxiing.]

Amdt. 23-51, E.. 03/11/96
FAR 23.1093 : 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 air free of visible moisture at a temperature of 30'F.–

(1)
Each airplane with sea level engines using conventional venturi carburetors has a preheater that can provide a heat rise of 90'F. with the engines at 75 percent of maximum continuouspower;

(2)
Each airplane with altitude engines using conventional venturi carburetorshas a preheater that can provide a heat rise of 120'F. with the engines at 75 percent of maximum continuouspower;

(3)
Each airplane with altitude engines using fuel metering device tending to preventicinghas apreheater that, withthe engines at60percent of maximum continuous power, can provide a heat rise of–

(i)
100'F.; or

(ii)
40'F.,if a .uiddeicing systemmeeting therequirementsofSecs.23.1095 through 23.1099 is installed;

(4)
Each airplane with a sea level engine(s) using a fuel metering device tending to prevent icing has a sheltered alternate source of air with a preheat of not less than 60'F with the engines at75percent of maximum continuouspower;

(5)
Each airplane with sea level or altitude engine(s) using fuel injection systems having metering component on which impact ice may accumulate has a pre-heater capable of providing a heat rise of 75'F. with the engine is operating at75percent ofits maximum continuouspower; and

(6)
Each airplane with sea level or altitude engine(s) using fuel injection systems not having fuel metering components projecting into the airstream on which ice may form, and introducing fuel into the air induction system downstream of any components or other obstruction on whichiceproducedby fuel evapo-ration may form,has a sheltered alternate source of air with apreheat of not less than 60'F withthe engines at75percent of maximum continuouspower.
　
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本文鏈接地址：FAA規章 美國聯邦航空規章 Federal Aviation Regulations 2(69)