西瑞20飞机信息手册 AIRPLANE INFORMATION MANUAL for the CIRRUS DESIGN SR20_split_5.pdf50页

Fuel Flow / Manifold Pressure Gage A 2¼” combination Fuel Flow and Manifold Pressure indicator is mounted on the right instrument panel immediately below the tachometer. The indicator is internally lighted. 28 VDC for instrument operation is supplied through the 5-amp ENGINE INST circuit breaker on the Essential Bus. The Fuel Flow pointer sweeps a scale marked from 0 to 18 Gal/Hr. Refer to Section 2 (Lim itations) for instrument limit markings. The electrically operated Fuel Flow indicator receives a fuel-flow rate signal from a fuel-flow transducer installed in the fuel line between the throttle body metering valve and the injector manifold (spider). The Manifold Pressure pointer sweeps a scale marked from 10 to 35 inches Hg in 5-inch Hg increments. Refer to Section 2 (Limitations) for instrument limit markings. The electrically operated manifold pressure indicator receives a pressure signal from a pressure sensor mounted in the induction airstream on the left side of the induction air manifold. Oil Warning Light The red OIL warning light in the annunciator panel comes on to indicate either high oil temperature or low oil pressure. The light is illuminated by a switch in the il o temperature gage if the oil temperature reaches 240 F or by a switch in the oil pressure gage if q the oil pressure drops to 10 psi or less. If the OIL warning light comes on in flight, refer to the oil temperature and pressure gages to determine the cause. Typically, low oil pressure will be accompanied by a high oil temperature indication. The light is powered by 28 VDC through the 2-amp ANNUNC circuit breaker on the Essential Bus.

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