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nstruments that measure relatively high fluid pressures, such as oil pressure gauges, are usually what type?. Bourdon tube. Vane with calibrated spring. Diaphragm or bellows.

Instruments that provide readings of low or negative pressure, such as manifold pressure gauges, are usually what type?. Diaphragm or bellows. Vane with calibrated spring. Bourdon tube.

In what units are gas turbine engine tachometers calibrated?. Percent of engine pressure ratio. Percent of engine RPM. Actual engine RPM.

In a turbine engine, where is the turbine discharge pressure indicator sensor located?. At a location in the exhaust cone that is determined to be subjected to the highest pressures. Immediately aft of the last turbine stage. At the aft end of the compressor section.

The exhaust gas temperature (E.G.T ) indicator on a gas turbine engine provides a relative indication of the. turbine inlet temperature. temperature of the exhaust gases as they pass the exhaust cone. exhaust temperature.

Engine pressure ratio is determined by. dividing engine inlet total pressure by turbine outlet total pressure. multiplying engine inlet total pressure by turbine outlet total pressure. dividing turbine outlet total pressure by engine inlet total pressure.

A red triangle, dot, or diamond mark on an engine instrument face or glass indicates. the maximum limit for high transients such as starting. a restricted operating range. the maximum operating limit for all normal operations.

What is the primary purpose of the tachometer on an axial compressor turbine engine?. Monitor engine RPM during cruise conditions. Monitor engine RPM during starting and to indicate overspeed conditions. It is the most accurate instrument for establishing thrust settings under all conditions.

Engine pressure ratio is the total pressure ratio between the. front of the engine inlet and the aft end of the compressor. front of the compressor and the rear of the turbine. aft end of the compressor and the aft end of the turbine.

On an aircraft turbine engine, operating at a constant power, the application of engine anti- icing will result in. an increase in E.P.R. noticeable shift in E.P.R. a false E.P.R reading.

The indicator of a tachometer system is responsive to change in. voltage. frequency. current flow.

The fuel flow indication data sent from motor driven impeller and turbine, and motorless type fuel flow transmitters is a measure of. fuel mass flow. fuel volume flow. engine burner pressure drop.

In addition to fuel quantity, a computerized fuel system (C.F.S) with a totalizer indicator provides indication of how many of the following?. Fuel flow rate, Fuel used since reset or initial start up, Fuel time remaining at current power setting. Fuel flow rate, Fuel used since reset or initial start up, Fuel time remaining at current power setting, Fuel temperature. Fuel flow rate, Fuel used since reset or initial start up, Fuel temperature.

The fuel flow indicator rotor and needle for a motor impeller and turbine indicating system is driven by. direct coupling to the motor shaft. an electrical signal. a mechanical gear train.

Motor driven impeller and turbine fuel flow transmitters are designed to transmit data. using aircraft electrical system power. mechanically. by fuel pressure.

What unit in a tachometer system sends information to the indicator?. The two phase AC generator. The three phase AC generator. The synchronous motor.

Engine oil temperature gauges indicate the temperature of the oil. entering the oil cooler. entering the engine. in the oil storage tank.

648) Thermocouple leads. may be repaired using solderless connectors. are designed for a specific installation and may not be altered. may be installed with either lead to either post of the indicator.

Why do helicopters require a minimum of two synchronous tachometer systems?. One indicates engine RPM and the other tail rotor RPM. One indicates main rotor RPM and the other tail rotor RPM. One indicates engine RPM and the other main rotor RPM.

If the thermocouple leads were inadvertently crossed at installation, what would the E.G.T gauge pointer indicate?. Moves off scale on the high side of the meter. Moves off scale on the zero side of the meter. Normal temperature for prevailing condition.

A common type of electrically operated oil temperature gauge utilizes. either a wheatstone bridge or ratiometer circuit. a thermocouple type circuit. vapour pressure and pressure switches.

The indication on a thermocouple-type E.G.T indicator is produced by. resistance changes in two dissimilar metals. a difference in the voltage between two dissimilar metals. a current generated by the temperature difference between dissimilar metal hot and cold junctions.

What is the Engine Pressure Ratio (E.P.R) used to indicate?. The power produced by the engine. The thrust produced by the engine. As a cross check for minimum acceptable thrust.

Where is Turbine Outlet Temperature (T.O.T) measured?. Upstream of the turbine. Downstream of the turbine. In the combustion chamber.

A thermocouple indicator is basically a. milliammeter. millivoltmeter. milliohmeter.

A thermocouple indicator is connected to the. cold junction. hot junction. difference between the hot junction and the cold junction.

Thrust in a high bypass fan engine is indicated by. N3 RPM or P1/P4 ratio. N1 RPM or N3 RPM. N1 RPM or E.P.R.

How is the N1 and N2 measured on a triple spool engine?. Tachometer connected to the internal gearbox. Tachometer connected to the external gearbox. Pulse type speed probes.

Modern oil pressure servo transmitters sense. absolute pressure. H.P oil pressure. differential pressure.

E.G.T thermocouples are usually made of. nickel and platinum. chromel and platinum. chromel and alumel.

Thrust in a high bypass engine is indicated by measuring. N3 RPM. neither of the above, thrust is not indicated in flight. fuel flow.

What power supply is required for a thermocouple system to work?. Alternating current. Direct current. Neither of the above.

In a thermocouple temperature sensing system, what is the purpose of the compensating resistor?. To correct for varying ambient temperatures at the hot junction. To correct for varying ambient temperatures at the cold junction. To standardise the reading for different engine types.

In a tachometer generator. the frequency output is inversely proportional to engine speed. frequency output is proportional to engine speed. the frequency output is constant.

Vibration pick-ups are located. on both fan and turbine cases. on the fan/compressor case. on the turbine case.

In a capacitive type fuel quantity indicating system the tank units are connected. series. parallel. series/parallel.

Torque measurement in a gas turbine engine is. not always reliable. highly reliable. required only when the turbine drives a propeller.

Vibration signals, when picked up,. go straight to indicator. go through half wave rectifier to indicator. the frequencies are filtered to exclude unwanted frequencies.

E.G.T is displayed in. Kelvin. degrees centigrade. degrees Fahrenheit.

N2 is taken from. a speed transducer on the fan rear frame. a tachometer attached on the N1 gearbox. a tachometer on the accessory gearbox.

Engine vibration is monitored using. electromechanical devices. Fenwall type sensors. piezoelectric accelerometer.

Integrating fuel flow gives. average fuel flow. total fuel consumed. fuel flow and acceleration.

The gauge on a bulb type temperature indicator shows zero. This could be caused by. open circuit in the wiring. temperature bulb going open circuit. two cables shorting together by the sensor.

In a thermocouple system, the size of the E.M.F that is produced is a result of. the difference between the hot and cold junction. the cold junction only. the hot junction only.

A ballast resistor is fitted. in parallel, to give identical readings for all engines. in series, to give identical resistance values for all engines. in series, to give identical resistance values to all airframes.

When reheat is used, E.P.R. is reducedremains constant. is increased. remains constant.

When reheat is selected and in operation, the mass gas flow. decreases. remains the same. increases.

Screech liners in the afterburning jet pipe. prevent unstable combustion. prevent cyclic vibrations of large amplitude. acts as noise suppressors.

Water methanol for cooling is injected into the. compressor inlet or outlet. engine hot zone. combustion chamber.

On an injection system. methanol is injected neat. town water/methanol is injected. demineralized water/methanol is injected.

When using water methanol in an axial flow compressor, it is injected into the. compressor inlet or burner section. burner. intake.

The main reason for adding methanol to the water is to. temper the cooling effect of the water to prevent distortion. supply the additional heat required. prevent mixture freezing.

The primary purpose of water injection is to. decrease mass airflow. increase the calorific value of the fuel. cool the turbine.

Water used in a thrust augmentation system should be demineralised to prevent. blocking the jet. carbon formation. fouling the blades and vanes.

The quantity of water usually carried by an aircraft equipped with water injection is enough for. three take-offs. one take-off. two take-offs.

Water methanol injection will increase thrust by up to. 70%. 50%. 30%.

Injection of water/methanol into compressor inlet causes. increase in power due to the burning of methanol alone. increase in power without the need for burning extra fuel. increased efficiency of the engine due to reduced icing in the airflow.

Reheat is the term used to describe. adding fuel in the exhaust section. adding of fuel in the turbine section. adding of fuel in the compressor section.

Water/methanol is injected. at high temperatures. at high temperature, at high altitudes. at high temperatures or high altitudes.

The reheat ignition system which incorporates a platinum/rhodium element is known. catalytic ignition. hot-shot ignition system. spark ignition system.

Water or water/methanol injected into the combustion chamber inlet increases. mass airflow through the turbine. combustion chamber outlet temperatures. fuel to air ratio by up to 20%.

Water or water/methanol injected into the combustion chamber inlet increases. mass airflow through the turbine. combustion chamber outlet temperatures. fuel to air ratio by up to 20%.

Methanol is added to water when augmenting thrust in order to. increase the density of air entering the compressor. reclaim lost pressure at the compressor. reclaim lost heat at the turbines.

Afterburning is initiated in order to. heat the exhaust to prevent choking at subsonic gas velocities. burn off the fuel that is not combusted in the combustion section. increase the local speed of sound at the jet nozzle.