曝光台 注意防骗
网曝天猫店富美金盛家居专营店坑蒙拐骗欺诈消费者
2.27.1 Engine Oil Temperature Indicator. Each en-gine has an oil temperature sensor wired through the signal data converter to a vertical scale instrument, marked ENG OIL TEMP, on the central display unit; and to an engine oil temperature caution light, marked ENGINE OIL TEMP.
2.27.2 Engine Oil Pressure Indicator. Each engine has an engine oil pressure transmitter, downstream of the oil .lter, that sends readings to a vertical scale indicator, marked ENG OIL PRESS, on the instrument display panel; and to an engine oil pressure caution legend, marked ENG OIL PRESS. The lower precautionary and prohibited ranges will go out when reaching the bottom of the normal range. It may be possible that during IDLE operations, the ENG OIL PRESS caution legend will go on. If ENG OIL PRESS caution legend comes on at IDLE, verify oil pres-sure is acceptable by setting Ng SPEED at 90%, check that engine oil pressure is at least 35 psi. As pressure increases above 100 psi the respective prohibited scale changes to red.
2.27.3 TGT Temperature Indicator. The TGT indicat-ing system consists of thermocouples transmitting to a TGT TEMP indicator. The indicator assembly has two digital readouts that indicate precise temperatures.
2.27.4 Gas Generator Speed (Ng) Indicator. The Ng speed indicating system shows Ng speed for each engine. The system consists of one alternator winding and Ng SPEED vertical scale instrument, on the instrument panel, giving percent rpm. Digital readouts for Ng SPEED are at the lower section of the instrument face plate. The three-digit readouts provide a closer indication of Ng SPEED.
2.27.5 Engine Power Turbine/Rotor Speed Indica-tor. Power turbine and rotor speed are indicated for each engine on a single instrument marked %RPM 1 R 2 on the display panel with three vertical scales (Figure 5-1). Power turbine speed is indicated in % RPM 1 or 2 and rotor speed % RPM R. Rotor speed is sensed by a speed sensor on the right accessory module. Power turbine speed is sensed by a speed sensor on the engine exhaust frame. At the top of the panel are three warning lights that indicate varying degrees of rotor overspeed. These lights remain on, once tripped, and must be manually reset.
2.27.6 Torque Indicator. The torque system shows the amount of power the engine is delivering to the main trans-mission. A torque sensor mounted on the exhaust case mea-sures the twist of the power turbine shaft, and transmits this signal to the ECU and signal data converter into the torque indicator marked % TRQ on the display panel, displaying readings for both engines. Digital readouts giving torques for each engine are at the top of the indicator. A photocell on the lower center of the display will automatically adjust the lighting of the % RPM and % TRQ indicators with respect to ambient light.
Change 4 2-27
Section IV FUEL SYSTEM
2.28 FUEL SUPPLY SYSTEM.
A separate suction fuel system is provided for each engine. Fuel is stored in two interchangeable, crashworthy, ballistic-resistant tanks. The fuel system consists of lines from the main fuel tanks, .rewall-mounted selector valves, prime/boost pump and fuel tanks, and engine-driven suc-tion pumps. The prime/boost pump primes all fuel lines if prime is lost, and also acts as an APU boost for APU starts and operation. A selector valve, driven by cable from the ENG FUEL SYS selector lever on the engine control quadrant (Figure 2-10) permits operation of either engine from either fuel tank. The engines and APU are suction fed, the APU is fed from the left main fuel tank by a separate fuel line. All fuel lines are routed in the most direct man-ner. The fuel line network includes self-sealing breakaway valves that contain fuel in case of helicopter crash or mal-function. All engine fuel lines are self-sealing with the exception of the APU fuel line.
2.28.1 Fuel Tanks. Both main fuel tanks are crashwor-thy, self-sealing and interchangeable. Each tank contains a pressure refuel/defuel valve, fuel quantity and low-level sensors, high-level shutoff valve, low-level shutoff valve, check valve sump drain, and a self-sealing breakaway vent valve. (Refer to Table 2-4 for tank capacity.) Fuel tank drains are in the sumps to permit removal of sediment and water and provide fuel sampling.
中国航空网 www.aero.cn
航空翻译 www.aviation.cn
本文链接地址：UH-60Q 直升机技术手册 直升机操作手册 1(25)
