曝光臺 注意防騙 網(wǎng)曝天貓店富美金盛家居專營店坑蒙拐騙欺詐消費者

The left and right engine EPR gauges receive sensing signals from the respective engine air inlet pressure (Pt2) probe and the low pressure turbine discharge pressure (Pt7) probes. Engine pressure ratio (Pt7/Pt2) is a measure of thrust being developed by the engine that is displayed on the EPR gauge. Power to operate these gauges is provided by the respective AC bus.
The thrust rating indicator is interfaced with the ram air temperature probe and digital flight guidance computer (DFGC) 1 and 2. Ram air temperature (RAT) and EPR LIM (limit) are displayed on the indicator. Mode buttons are provided on the indicator for selection of desired mode (T.O., T.O.FLX, GA, MCT, CL, and CR). The DFGC’s supply data to the indicator for automatic display of EPR LIM for mode selected.
Continental
Rev. 12/01/00 #29 Flight Manual
The left and right N1 tachometers indicate the respective engine low-pressure compressor rotor RPM as a percentage. The left and right N2 tachometers indicate the respective engine high-pressure compressor rotor RPM as a percentage. Power to operate these gauges is self-generated.
The left and right EGT gauges indicate in degrees centigrade the temperature of the exhaust gas of the respective engine. Each gauge receives signals from temperature probes located in the exhaust gas path of each engine. Power to operate these gauges is provided by the Emergency DC bus.
The left and right FUEL FLOW gauges indicate the rate of flow in pounds per hour that fuel is being delivered to the respective engine. A FUEL USED readout on each gauge displays a digital readout of fuel used in pounds by the respective engine. A FUEL USED RESET switch is provided to reset the FUEL USED readout on both gauges to 00000. For further description of FUEL FLOW gauge/FUEL USED readout and FUEL USED RESET switch, refer to Fuel section. Power to operate these gauges is provided by the respective AC bus.
Engine Starting
Either engine may be started by using a pneumatic ground supply or by pneumatic supply from the auxiliary power unit. When one engine is operating, the opposite engine may be started by using the pneumatic crossfeed system.
An electrically controlled, pneumatically actuated starter air shutoff valve on each engine controls the starter of the respective engine. The starter air shutoff valve regulates pneumatic pressure to maintain a predetermined air pressure to the engine starter.
L and R (left and right) START switches with ON/OFF positions, are provided on the ENG (engine) panel located on the overhead. When either START switch is held in ON, the respective engine starter air shutoff valve opens. (On some aircraft, the operation of the Start switch is inhibited unless the ignition selector is not in the OFF position.) The L or R VALVE OPEN light on the annunciator panel illuminates to indicate that the applicable engine starter air shutoff valve is open. When either START switch is released, the respective engine starter air shutoff valve closes, and the L or R VALVE OPEN light, as applicable, extinguishes. To extend starter life and reduce chance of failure of the starter shear section, do not re-engage the starter (except for an abnormal or emergency condition) when the compressors are rotating.
Ignition Systems
Rotary Switch Ignition
The standard five position Rotary switch system is powered by AC power. Two independent 20-Joule ignition systems (A and B) are provided for each engine. The dual systems for each engine are controlled by a single IGN (ignition) selector located on the ENG panel. The selector has five positions, SYS A / OFF / SYS B / BOTH / OVRD, for ignition system selection.
The SYS A or SYS B positions operate the associated igniter, and BOTH position operates both igniters, if the respective engine’s FUEL lever is ON. The OVRD position will operate the both igniters of both engines, regardless of the position of the FUEL levers. Igniters are normally powered by left and right AC. If normal power is not available, the emergency inverter will automatically provide the power to the selected ignition, as long as the Battery Switch is ON.
SYS A or SYS B positions are normally used for engine starting and for operating ignition when using engine anti-ice. BOTH position is used for approach when one engine has been shutdown. This position will not provide power to the ignition of the engine with the FUEL lever in OFF. OVRD position is used for takeoff, landing, and emergency conditions.
Toggle Switch Ignition
On some airplanes two ignition systems, one 20-Joule (high-energy ignition system) and one four-Joule (low-energy continuous ignition system) are provided for each engine. An IGN (ignition) switch, with OVRD (override) / OFF / GRD START & CONTIN (ground start and continuous) positions, is provided on the ENG panel for ignition system selection.
For starting engines on the ground, the IGN switch is placed in GRD START & CONTIN. The applicable START (L or R) switch is then held in ON to open the respective engine starter air shutoff valve. To supply high-energy ignition power to both igniters on the respective engine, the respective FUEL lever is then moved to ON. When the START switch is released after engine start, continuous ignition power is supplied to one igniter on the respective engine for continuous low-energy engine ignition.
　
中國航空網(wǎng) www.k6050.com
航空翻譯 www.aviation.cn
本文鏈接地址：MD-80 Flight Manual 麥道80飛行手冊 2(188)