(2)
An altimeter(sensitive).
(3)
A rate-of-climbindicator(vertical speed).
(4)
Agyroscopicrate-of-turnindicatorcombined with anintegral slip-skidindica-tor(turn-and-bankindicator) except that only a slip-skidindicatoris requi-red on large airplanes with a third attitude instrument system usable through .ight attitudes of 360'ofpitch and roll andinstalledin accordancewith[Sec. 121.305(k)] of this title.
(5)
Abank andpitchindicator(gyroscopically stabilized).
(6)
Adirectionindicator(gyroscopically stabilized, magnetic or nonmagnetic).
(c)
The following .ight and navigation instruments are required as prescribed in this paragraph :
(1)
A speed warning device is required for turbine engine powered airplanes and for airplanes with VMO/MMO greater than0.8VDF/MDF or0.8 VD/MD.The speed warningdevicemustgivee.ective aural warning(di.ering distinctively from auralwarnings usedfor otherpurposes)to thepilots, whenever the speed exceeds VMO,plus 6 knots or MMO +0.01.The upperlimit of theproduction tolerancefor the warningdevice may not exceed theprescribed warning speed.
(2)
Amachmeteris required at eachpilot stationfor airplanes with compressibility limitations not otherwise indicated to the pilot by the airspeed indicating system required underparagraph(b)(1) of this section.
Amdt. 25-90, E.. 3/12/97
′
Elodie Roux. Septembre 2003
Subpart F : Equipment
FAR 25.1305 : Powerplant instruments.
The following are required powerplant instruments :
(a)
For all airplanes.
(1)
Afuelpressurewarning meansforeach engine, oramaster warning meansfor all engines withprovisionforisolating theindividual warning meansfromthe master warning means.
(2)
A fuel quantity indicator for each fuel tank.
(3)
An oil quantity indicator for each oil tank.
(4)
An oil pressure indicator for each independent pressure oil system of each engine.
(5)
An oilpressurewarning meansforeach engine, oramasterwarning meansfor all engines withprovisionforisolating theindividual warning meansfromthe master warning means.
(6)
An oil temperature indicator for each engine.
(7)
Fire-warning indicators.
(8)
An augmentation liquid quantity indicator (appropriate for the manner in which the liquid is to be used in operation) for each tank.
(b)
For reciprocating engine-powered airplanes. In addition to the powerplant instru-ments requiredbyparagraph(a) of this section, thefollowingpowerplantinstru-ments are required :
(1)
A carburetor air temperature indicator for each engine.
(2)
A cylinder head temperature indicator for each air-cooled engine.
(3)
A manifold pressure indicator for each engine.
(4)
Afuelpressureindicator(toindicate thepressure atwhich thefuelis supplied) for each engine.
(5)
A fuel .owmeter, or fuel mixture indicator, for each engine without an auto-matic altitude mixture control.
(6)
A tachometer for each engine.
(7)
Adevicethatindicates,tothe .ightcrew(during .ight),any changeinthe power output, for each engine with–
(i)
An automaticpropellerfeathering system,whoseoperationisinitiatedby a power output measuring system; or
(ii)
A total engine piston displacement of 2,000 cubic inches or more.
(8)
A means to indicate to thepilot when thepropellerisin reversepitch,for each reversingpropeller.
(c)
For turbine engine-powered airplanes. In addition to the powerplant instruments requiredbyparagraph(a) of this section, the followingpowerplantinstruments are required :
(1)
A gas temperature indicator for each engine.
(2)
A fuel .owmeter indicator for each engine.
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本文鏈接地址：FAA規(guī)章 美國聯(lián)邦航空規(guī)章 Federal Aviation Regulations 4(15)
