(ii)
Be installed and located so that the escape of .uids would not create a hazard.
(3)
Eachpowerplantand auxiliarypowerunitinstrumentthatutilizes .ammable .uidsmustbeinstalled andlocated sothattheescapeof.uid would not create a hazard.]
(b)
Fuelquantity indicator.Theremustbemeanstoindicatetothe .ight crewmembers, thequantity,ingallonsorequivalent units,of usablefuelineach tankduring.ight. In addition–
(1)
Each fuel quantity indicator must be calibrated to read ”zero” during level .ight whenthequantity offuel remaininginthetankis equal tothe unusable fuel supply determined under Sec. 25.959;
(2)
Tanks with interconnected outlets and airspaces may be treated as one tank and need not have separate indicators; and
(3)
Each exposed sightgauge, used as afuelquantityindicator, must beprotected against damage.
(c)
Fuel .owmeter system. If a fuel .owmeter system is installed, each metering com-ponent must have a means for bypassing the fuel supply if malfunction of that component severely restricts fuel .ow.
(d)
Oil quantity indicator.There mustbe a stickgauge or equivalent meanstoindicate the quantity of oil in each tank. If an oil transfer or reserve oil supply system is installed,theremustbeameanstoindicatetothe .ightcrew,in .ight,thequantity of oil in each tank.
(e)
Turbopropeller blade position indicator. Required turbopropeller bladepositionindi-cators must begin indicatingbefore the blade moves more than eightdegreesbelow the .ight low pitch stop. The source of indication must directly sense the blade position.
(f)
Fuel pressure indicator. There must be means to measure fuel pressure, in each system supplying reciprocating engines, at a point downstream of any fuel pump except fuel injection pumps. In addition–
(1)
If necessary for the maintenance of proper fuel delivery pressure, there must be a connection to transmit the carburetor air intake static pressure to the proper pump relief valve connection; and
(2)
If a connectionis required under subparagraph(1) ofthisparagraph,thegauge balancelines mustbeindependentlyconnected to the carburetorinletpressure to avoid erroneous readings.
Amdt. 25-40, E.. 5/2/77
′
Elodie Roux. Septembre 2003
Subpart F : Equipment
49.3 Electrical Systems and Equipment
FAR 25.1351 : General.
(a)
Electrical system capacity.The requiredgenerating capacity, and number andkinds of power sources must–
(1)
Be determined by an electrical load analysis; and
(2)
Meet the requirements of Sec. 25.1309.
(b)
Generating system. The generating system includes electrical power sources, main power busses, transmission cables, and associated control, regulation, and protec-tive devices. It must be designed so that–
(1)
Power sources function properly when independent and when connected in combination;
(2)
No failure or malfunction of any power source can create a hazard or impair the ability of remaining sources to supply essential loads;
(3)
The system voltageandfrequency(as applicable) attheterminals of all es-sential load equipment can be maintained within the limits for which the equipment is designed, during any probable operating condition; and
(4)
System transientsdue to switching,fault clearing, or other causesdo not make essential loads inoperative, and do not cause a smoke or .re hazard.
(5)
There are means accessible, in .ight, to appropriate crewmembers for the in-dividual and collective disconnection of the electrical power sources from the system.
(6)
There are means to indicate to appropriate crewmembers the generating sys-temquantities essentialforthe safe operation ofthe system, such asthe voltage and current supplied by each generator.
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本文链接地址：FAA规章 美国联邦航空规章 Federal Aviation Regulations 4(22)
