FAR 27.1401 : Anticollision light system . . . . . . . . . . . . 879
66.5SafetyEquipment ......................... 880 FAR27.1411:General . . . . . . . . . . . . . . . . . . . . . . 880 FAR27.1413:Safetybelts ................... 880 FAR27.1415:Ditching equipment . . . . . . . . . . . . . . . 880 FAR27.1419:[Iceprotection.] . . . . . . . . . . . . . . . . . 881 FAR27.1435:Hydraulicsystems . . . . . . . . . . . . . . . . 881 FAR27.1457:[Cockpitvoicerecorders.] . . . . . . . . . . . . 881 FAR27.1459:[Flightrecorders.] . . . . . . . . . . . . . . . . 883 FAR27.1461:[Equipmentcontaininghigh energy rotors.] . . 884
66.1 General
FAR 27.1301 : Function and installation
Each item of installed equipment must–
(a)
Be of akind anddesign appropriatetoitsintendedfunction;
(b)
Be labeled as to its identi.cation, function, or operating limitations, or any appli-cable combination of these factors;
(c)
Beinstalled according tolimitations speci.edforthat equipment; and
(d)
Function properly when installed.
FAR 27.1303 : Flight and navigation instruments
The following are the required .ight and navigation instruments :
(a)
An airspeed indicator.
(b)
An altimeter.
(c)
A magnetic direction indicator.
FAR 27.1305 : Powerplant instruments
Thefollowing arethe requiredpowerplantinstruments:
(a)
A carburetorairtemperatureindicator,for each enginehaving apreheaterthat can provide a heat rise in excess of 60'F.
(b)
A cylinder head temperature indicator, for each–
(1)
Air cooled engine;
(2)
Rotorcraft with cooling shutters; and
(3)
Rotorcraft for which compliance with Sec. 27.1043 is shown in any condition other than the most critical .ight condition with respect to cooling.
(c)
Afuelpressureindicator,for eachpump-fed engine.
(d)
A fuel quantity indicator, for each fuel tank.
(e)
A manifold pressure indicator, for each altitude engine.
(f)
An oil temperature warning device to indicate when the temperature exceeds a safe valuein each main rotordrivegearbox(including anygearboxes essential to rotor phasing) having an oil system independent of the engine oil system.
(g)
An oilpressurewarningdevicetoindicatewhenthepressurefallsbelowasafevalue in eachpressure-lubricated main rotordrivegearbox(including anygearboxes es-sential to rotorphasing)having an oil systemindependent of the engine oil system.
(h)
An oil pressure indicator for each engine.
(i)
An oil quantity indicator for each oil tank.
(j)
An oil temperature indicator for each engine.
(k)
At least one tachometer to indicate the r.p.m. of each engine and, as applicable–
(1)
The r.p.m. of the single main rotor;
(2)
The common r.p.m. of any main rotors whose speeds cannot vary appreciably with respectto each other; or
中国航空网 www.aero.cn 航空翻译 www.aviation.cn 本文链接地址：FAA规章 美国联邦航空规章 Federal Aviation Regulations 4(120)
