(2)
The altimeter must be a sensitive type.
(3)
Having a passenger seating con.guration of 10 or more, excluding the pilot’s seats and that are approved for IFR operations, a third attitude instrument must be provided that :
(i)
Ispoweredfromasourceindependent of the electricalgenerating system;
(ii)
Continues reliable operation for a minimum of 30 minutes after total failure of the electricalgenerating system;
′
Elodie Roux. Septembre 2003
Subpart F : Equipment
(iii) Operates independently of any other attitude indicating system;
(iv)
Is operative without selection after total failure of the electrical genera-ting system;
(v)
Islocated ontheinstrumentpanelin aposition acceptabletotheAdmi-nistrator that will make it plainly visible to and usable by any pilot at the pilot’s station; and
(vi) Is appropriately lighted during all phases of operation.] Amdt. 23-49, E.. 03/11/96
FAR 23.1305 : Powerplant instruments.
The following are required powerplant instruments :
(a)
For all airplanes.
(1)
A fuel quantity indicator for each fuel tank, installed in accordance with Sec. 23.1337(b).
(2)
An oil pressure indicator for each engine.
(3)
An oil temperature indicator for each engine.
(4)
An oil quantity measuring device for each oil tank which meets the require-ments of Sec. 23.1337(d).
(5)
A .rewarning meansforthoseairplanesrequired tocomply withSec.23.1203.
(b)
For reciprocating engine-powered airplanes. In addition to the powerplant instru-ments requiredbyparagraph(a) of this section, thefollowingpowerplantinstru-ments are required :
(1)
An induction system air temperature indicator for each engine equipped with a preheater and having induction air temperature limitations that can be exceeded with preheat.
(2)
A tachometer indicator for each engine.
(3)
A cylinder head temperature indicator for–
(i)
Each air-cooled engine with cowl .aps;
(ii)
Removed and reserved.
(iii) Each commuter category airplane.
(4)
[For each pump-fedengine, a means :
(i)
Thatcontinuouslyindicates,tothepilot,thefuelpressureorfuel .ow; or
(ii)
That continuously monitors the fuel system and warns the pilot of any fuel .ow trend that could lead to engine failure.]
(5)
A manifoldpressureindicatorfor each altitude engine andfor each engine with a controllablepropeller.
(6)
For each turbocharger installation :
(i)
Iflimitations are establishedfor either carburetor(or manifold) airinlet temperature or exhaust gas or turbocharger turbine inlet temperature, indicators mustbefurnishedfor eachtemperaturefor whichthelimitation is established unless it is shown that the limitation will not be exceeded in all intended operations.
(ii) If its oil system is separate from the engine oil system, oil pressure and oil temperature indicators must be provided.
(7) A coolant temperature indicator for each liquid-cooled engine.
(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.
(3)
A fuel low pressure warning means for each engine.
(4)
A fuel low level warning means for any fuel tank that should not be depleted of fuel in normal operations.
(5)
Atachometerindicator(toindicatethe speed ofthe rotorswith established limiting speeds) for each engine.
(6)
An oil low pressure warning means for each engine.
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 2(80)
