(1)
Separate control of eachpropeller; and
(2)
Simultaneous control of all propellers.
(b)
The controls must allow ready synchronization of all propellers on multiengine air-planes.
FAR 23.1153 : Propeller feathering controls.
[Ifthere arepropellerfeathering controlsinstalled, it mustbepossible to feather each propeller separately. Each control must have a means to prevent inadvertent operation.] Amdt. 23-51, E.. 03/11/96
′
Elodie Roux. Septembre 2003
Subpart E : Powerplant
FAR 23.1155 : [Turbine engine reverse thrust and propeller pitch settings below the .ight regime.]
[Forturbine engineinstallations, eachcontrolfor reversethrust andforpropellerpitch settings below the .ight regime must have means to prevent its inadvertent operation. Themeansmusthaveapositivelock orstop atthe .ightidlepositionand must requirea separateanddistinctoperationby thecrewtodisplacethecontrolfromthe .ight regime (forwardthrust regime for turbojet powered airplanes).] Amdt. 23-7, E.. 09/14/69
FAR 23.1157 : Carburetor air temperature controls.
There must be a separate carburetor air temperature control for each engine.
FAR 23.1163 : Powerplant accessories.
(a)
Each engine mounted accessory must–
(1)
[Be approved for mounting on the engine involved and use the provisions on the enginesfor mounting; or
(2)
Have torque limiting means on all accessory drives in order to prevent the torquelimits establishedforthosedrivesfrombeing exceeded; and
(3)
In additiontoparagraphs(a)(1) or(a)(2) of this section,be sealed toprevent contamination of the engine oil system and the accessory system.]
(b)
Electrical equipment subject to arcing or sparking mustbeinstalled to minimize the probability of contact with any .ammable .uids or vapors that might be present in a free state.
(c)
Eachgeneratorrated at or morethan6kilowatts mustbedesigned andinstalled to minimize the probability of a .re hazard in the event it malfunctions.
(d)
[Ifthe continuedrotation of any accessory remotelydrivenbythe engineishazardous when malfunctioning occurs, a means to prevent rotation without interfering with the continued operation of the engine must be provided.
(e)
Each accessory driven by a gearbox that is not approved as part of the powerplant driving the gearbox must–
(1)
Have torque limiting means to prevent the torque limits established for the a.ected drive from being exceeded;
(2)
Usetheprovisions onthegearboxfor mounting; and
(3)
Be sealedtoprevent contamination of thegearbox oil system and the accessory system.]
Amdt. 23-42, E.. 02/04/91
FAR 23.1165 : Engine ignition systems.
(a)
Eachbatteryignition system mustbe supplementedbyagenerator thatis automati-cally available as an alternate source of electrical energy to allow continued engine operation if any battery becomes depleted.
(b)
The capacity of batteries and generators must be large enough to meet the simul-taneous demands of the engine ignition system and the greatest demands of any electrical system components that draw from the same source.
(c)
The design of the engine ignition system must account for–
(1)
The condition of an inoperative generator;
(2)
The condition of a completely depleted battery with the generator running at its normal operating speed; and
(3)
The condition of a completely depleted battery with the generator operating at idling speed, if there is only one battery.
(d)
There must be means to warn appropriate crewmembers if malfunctioning of any partof the electrical systemis causing the continuousdischarge of anybattery used for engine ignition.
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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(74)
