(3)
Afuelquantity indicatorfor eachfueltank;

(4)
Alowfuel warningdevicefor eachfuel tank whichfeeds an engine.Thisdevice must–

(i)
Provide a warning to the crew when approximately 10 minutes of usable fuel remainsinthetank; and

(ii)
Be independent of the normal fuel quantity indicating system.

(5)
A manifold pressure indicator, for each reciprocating engine of the altitude type;

(6)
[An oilpressureindicatorfor eachpressure-lubricatedgearbox.

(7)
]An oilpressure warning devicefor eachpressure-lubricatedgearboxtoindi-cate whenthe oilpressurefallsbelow a safe value; [(8) ]An oil quantity indicator for each oil tank and each rotor drive gearbox, if lubricant is self-contained; [(9) ]An oil temperature indicator for each engine;

[(10) ] An oil temperature warning device to indicate unsafe oil temperatures in each main rotor drive gearbox, including gearboxes necessary for rotor pha-sing;
[(11) ]Agastemperatureindicatorfor each turbine engine;
[(12) ]Agasproducer rotortachometerfor each turbine engine;
[(13) ] A tachometer for each engine that, if combined with the applicable ins-
trument requiredbyparagraph[(a)(14)] of this section,indicates rotorr.p.m. during autorotation. [(14) ]At least one tachometer to indicate, as applicable–
(i)
The r.p.m. of single main rotor;

(ii)
The common r.p.m. of any main rotors whose speeds cannot vary appre-ciably with respectto each other; and

(iii) The r.p.m. of each main rotor whose speed can vary appreciably with respect to that of another main rotor;
[(15) ]A free power turbine tachometer for each turbine engine;
[(16) ]A means, for each turbine engine, to indicate power for that engine;
[(17) ] For each turbine engine, an indicator to indicate the functioning of the powerplanticeprotection system;
[(18) ]Anindicatorforthe .lterrequiredbySec.29.997toindicatetheoccurrence of contaminationof the .ltertothedegreeestablishedincompliancewithSec. 29.955;
[(19) ]Foreachturbineengine,awarning meansfortheoil straineror .lterrequi-redby Sec.29.1019,ifithas nobypass,to warnthepilot of the occurrenceof contaminationofthestraineror .lterbeforeit reachesthecapacity established in accordance with Sec. 29.1019(a)(2);
[(20) ] An indicator to indicate the functioning of any selectable or controllable heater used to prevent ice clogging of fuel system components;
[(21) ] An individual fuel pressure indicator for each engine, unless the fuel sys-tem which supplies that engine does not employ any pumps, .lters, or other components subject to degradation or failure which may adversely a.ect fuel pressure atthe engine;
[(22) ]Ameanstoindicatetothe .ightcrewthefailureof anyfuelpump installed to show compliance with Sec. 29.955;
[(23) ]Warning or caution devices to signal to the .ightcrew when ferromagnetic particles are detected by the chip detector required by Sec. 29.1337(e); and
[(24) ]For auxiliary power units, an individual indicator, warning or caution de-vice, or other means to advise the .ightcrew that limits are being exceeded, if exceeding these limits can be hazardous, for–
(i)
Gas temperature;

(ii)
Oil pressure; and

(iii) Rotor speed.
[(25) ]For rotorcraftfor which a30-second/2-minuteOEIpower rating is reques-ted, a means must be provided to alert the pilot when the engine is at the 30-second and 2-minute OEI power levels, when the event begins, and when the time interval expires.
[(26) ]For each turbine engine utilizing 30-second/2-minute OEI power, a device or system mustbeprovidedfor usebygroundpersonnel which–
(i)
Automatically recordseach usage andduration ofpoweratthe30-second and 2-minute OEI levels;

(ii)
Permits retrieval of the recorded data;

(iii) Can be reset only by ground maintenance personnel; and
　
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本文鏈接地址：FAA規章 美國聯邦航空規章 Federal Aviation Regulations 5(87)