If a propeller that has been operating at a high rpm is feathered It will move from coarse through fine to the feather position It will move from coarse direct to the feather position It will move from fine through coarse to the feather position.
The blade angle of a fully feather propeller is approximately 45 degrees 55 degrees 90 degrees.
If a variable pitch propeller does not have the facility to fully feather, what is the most favorable pitch position to select in the event of an engine failure
Fully fine Fully coarse Midway between a & b.
In a CSU, blades are moved into fined pitched by oil pressure from The governor pump The auxiliary feathering oil pump The engine oil pump.
To check the operation of a CSU Set the propeller pitch control to the required position, Advance the throttle until the propeller enters the constant speed range. Any further small movement of the throttle lever should give no change in rpm Select the pitch control to the fully fine position. Open the throttle until the manifold pressure reading is equal to the indicated RPM Select the pitch control to the position corresponding to maximum RPM. Open the throttle to the position required .Any small throttle movements should give no change in RPM.
A constant speed unit is one in which Reduction gearing between the engine and the propeller maintains a constant speed RPM with changing engine RPM The blade angle of the propeller is varied to maintain the forward speed of the aircraft constant in different flight configuration The blade angle of the propeller is automatically adjusted so that a constant RPM is maintained
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Which of the following is correct The blade is moved from coarse to fine by governor flyweights as a result of extra centrifugal force created at high RPM The blade is moved from coarse to fine pitch by use of high-pressure engine oil The blade is moved from fine to coarse by use of high-pressure engine oil.
A reversible propeller is one that Will deliver negative thrust Can be fitted either way around Can be operated in either direction of operation.
The combination of propeller pitch and the aircraft speed that will result in the greatest angle of attack of the blades is Fine pitch and high speed Fine pitch and low speed Coarse pitch and low speed.
The typical pitch range of a variable pitch propeller fitted to a modern turbo prop aircraft is 0° to 40° 0° to 90° 20° to 90°.
The blades of a reverse pitch propeller move into the reverse pitch position Through coarse and return through coarse Through fine and return through fine Through coarse and return through fine.
Increasing the tension of the governor speed spring on a CSU operated propeller causes An increase in blade angle and a decrease in RPM An increase in blade angle and an increase in RPM A decrease in blade angle and an increase in RPM.
Reverse pitch is selected To feather the blades and prevent wind milling To provide aerodynamic braking after landing To prevent an over speed in flight.
A propeller is selected to fine pitch for take-off because This allows the engine to develop maximum rated power A coarse pitch setting reduces aerodynamic efficiency at all low altitudes There is a danger that the propeller will move from coarse pitch into feather on
the take off run.
A single acting variable pitch propeller is feathered by means of The centrifugal weight of the blades Engine oil pressure A control spring.
The purpose of the oil booster pump in a CSU is To operate the feathering circuit when required To keep the accumulator charged at all times during ground operation To provide sufficient oil pressure to turn the blades into fine pitch.
Constant speed with reference to propellers means Power output can be maintained at all times The propeller maintains a constant RPM at all times The engine maintains constant RPM in normal conditions.
An engine fitted with a constant speed propeller is warmed up for five minutes at 2000 RPM .A small advancement of the throttle lever only will cause the RPM To increase To decrease To remain the same.
If the governor control spring in a CSU breaks during flight, the propeller is most likely to Go into feather Go into fine pitch Go into coarse pitch.
The CSU governor works on the principle of Spring pressure acting against centrifugal force All position set and adjusted manually The propeller centrifugal twisting moment.
Feathering stops are fitted to Prevent the propeller from moving out of the feather position Prevent the propeller from moving into feather in the event of an engine failure Prevent the propeller from moving past the feather position.
With a constant speed unit fitted, the pitch of the propeller blade at fully fine, and feathered is limited by The propeller lever Mechanical pitch stops Engine oil forming a hydraulic lock.
A double acting variable pitch propeller is normally feathered by means of Engine oil pressure An auxiliary oil pump system Centrifugal loads on the blades.
The purpose of reduction gearing between the engine and a variable pitch propeller is to allow The propeller to operate at the most efficient pitch angle for all phase of flight The rotational velocity of the propeller to be maintain relatively high, while
engine RPM is relatively low, thus increasing engine life. The rotational velocity of the propeller to be maintain relatively low, while engine RPM is relatively high
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A geared propeller has a rotational speed that is Slower than that of the engine Faster than that of the engine Exactly the same as that of the engine.
When selected to the feather position, the propeller blades go from Coarse through fine to feather Fine through reverse to feather Fine through coarse to feather.
A double acting propeller is feathered by means of The centrifugal twisting moment of the blades Spring pressure on the centrifugal flyweights A separate feathering oil pump.
The torque meter transmitter is fitted to The propeller control unit The reduction gearing The engine crankshaft.
The beta range of a variable pitch propeller is used for Flight feathering Ground Feathering Ground Maneuvering.
If the engine drive to a constant speed unit fails The blades will turn to feather The blades will move to the fully fine position Pitch locks will prevent either a) or b).
An oil booster pump is incorporated in a CSU to Boost engine oil pressure in order to move the blades to coarse pitch Lubricate all moving parts and to assist in the feathering process Boost engine oil pressure in order to move blades to the fine pitch.
A constant speed propeller, maximum RPM is set by A fine pitch stop in the hub assembly A mechanical stop in the control lever A screw in the governor head.
The function of the governor on a constant speed propeller is To regulate the amount of oil being directed to and from the propeller To open and control the pump-feathering outlet To regulate the amount of fuel to the fuel injector according to the RPM of the
propeller.
If an unfeathering accumulator is fitted to a constant speed propeller, what position should the propeller control be placed in at the start of the unfeathering process? Maximum RPM Fine pitch stops Minimum RPM.
If the tension of the governor spring is increased Blade angle increases with RPM Blade angle increases and RPM decreases Blade angle remains the same and RPM decreases.
If the aircraft’s TAS increases the CSU operates to give A coarser pitch The same pitch A finer pitch.
A double acting propeller operates due to Oil pressure on one side of the pitch change piston and air pressure on the other side Oil pressure on one side of the pitch change piston and air pressure on the other side Oil pressure on both sides of the pitch change piston.
A double acting propeller operates due to Oil pressure on one side of the pitch change piston and air pressure on the other side Oil pressure on one side of the pitch change piston and air pressure on the other side Oil pressure on both sides of the pitch change piston
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If an aircraft’s TAS is reduced a constant speed unit will select the blades to Remain at the same pitch A finer pitch A coarser pitch.
Feathering a variable pitch propeller driven by a turbine engine is most commonly achieved by Closing all the control levers Selecting the high-pressure fuel controls to off Selecting the ignition system to off.
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