(b)
As used in this section, drag limiting systems include manual or automatic devices that, when actuated after enginepowerloss, can movethepropellerbladestoward the feather position to reduce windmilling drag to a safe level.]
Amdt. 23-43, E.. 05/10/93
′
Elodie Roux. Septembre 2003
Subpart E : Powerplant
FAR 23.939 : Powerplant operating characteristics.
(a)
Turbine engine powerplant operating characteristics must be investigated in .ight todeterminethatnoadversecharacteristics(such asstall,surge,or .ameout) are present, to a hazardous degree, during normal and emergency operations within the range of operating limitations of the airplane and of the engine.
(b)
[Turbocharged reciprocating engine operating characteristics must be investigated in .ight to assure that no adverse characteristics, as a result of an inadvertent overboost, surge, .ooding, or vapor lock, are present during normal or emergency operation of the engine(s) throughout the range of operating limitations of both airplane and engine.
(c)
For turbine engines, the air inlet system must not, as a result of air.ow distortion during normal operation, cause vibration harmful to the engine.]
Amdt. 23-42, E.. 02/04/91
FAR 23.943 : Negative acceleration.
[No hazardous malfunction ofan engine, an auxiliary power unit approved for use in .ight, or any component or system associated with the powerplant or auxiliary power unit may occur when the airplane is operated at the negative accelerations within the .ight envelopesprescribedinSec.23.333.This mustbe shownforthegreatest value and duration of the acceleration expected in service.] Amdt. 23-43, E.. 05/10/93
32.2 Fuel System
FAR 23.951 : General.
(a)
[Eachfuelsystemmustbeconstructed and arrangedtoensurefuel .owat arateand pressure established for proper engine and auxiliary power unit functioning under each likely operating condition, including any maneuver for which certi.cation is requested and during which the engine or auxiliary power unit is permitted to be in operation.]
(b)
Each fuel system must be arranged so that–
(1)
Nofuelpump candrawfuelfrom morethan onetank at atime; or
(2)
There are means to prevent introducing air into the system.
(c)
Each fuel system for a turbine engine must be capable of sustained operation throu-ghoutits .owandpressurerangewithfuelinitially saturated with waterat80'F. and having 0.75cc of free water per gallon added and cooled to the most critical condition for icing likely to be encountered in operation.
(d)
Each fuel system for a turbine engine powered airplane must meet the applicable fuel venting requirements of part 34 of this chapter.
Amdt. 23-43, E.. 05/10/93
FAR 23.953 : Fuel system independence.
(a) Eachfuel systemfor a multiengine airplane mustbe arranged so that,in atleast one system con.guration,thefailure of any one component(otherthan afueltank) will not result in the loss of power of more than one engine or require immediate actionby thepilottopreventtheloss ofpower of morethan one engine.
(b) If asinglefuel tank(orseriesoffuel tanksinterconnected tofunction asasinglefuel tank) is used on a multiengine airplane, the following must be provided :
(1)
Independent tank outlets for each engine, each incorporating a shuto. valve at the tank. This shuto. valve may also serve as the .rewall shuto. valve required if the line between the valve and the engine compartment does not contain more than onequart offuel( or anygreater amount shown to be safe) that can[escape] intothe engine compartment.
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本文鏈接地址：FAA規(guī)章 美國(guó)聯(lián)邦航空規(guī)章 Federal Aviation Regulations 2(56)
