3272-17 Prop (17.3)

The holding coil of a hydromatic propeller feathering button switch holds a relay closed that applies. dome feathering mechanism. feathering pump motor. governor.

The primary purpose of the front and rear cones for propellers that are installed on splined shafts is to. prevent metal-to-metal contact between the propeller and the splined shaft. reduce stresses between the splines of the propeller and the splines of the shaft. position the propeller hub on the splined shaft.

The constant-speed control unit is also called a. propeller pitch control. accumulator. governor.

When the compressive force on a speeder spring is reduced, the propeller blades will. remain fixed. fine off. coarsen.

A hydraulic pitch lock is utilised in a hydromatic propeller to. lock out the course pitch oil line in the event of underspeeding. lock out the fine pitch oil line in the event of overspeeding. prevent the propeller overspeeding in the event of oil supply failure.

When in the beta range, the propeller pitch is controlled. directly from the power lever. indirectly from the power lever. directly from the pitch change mechanism to the PCU.

The advantage of the beta range is it allows. high power settings with higher than normal pitch settings when in flight. low fine pitch settings with high power. low power settings with higher than normal pitch setting for ground manoeuvres.

If the speeder spring pressure of a CSU is increased the blade will. fine off. coarsen off. will not move.

On an underspeed condition the blades are turned to. fine. feather. coarse.

In a hydromatic propeller with counterweights, what is used to make the propeller move to fine pitch?. A T M. engine oil. centrifugal force acting on the counterweight.

Relaxing tension on the governor spring will result in the blade coarsening and. RPM decreasing, manifold pressure increasing. RPM increasing, manifold pressure increasing. manifold pressure constant, RPM decreasing.

The ground fine pitch stop is. never removed. removed on the ground. removed during flight.

If governor flywheel overcomes the speeder spring, it indicates. overspeed. underspeed. onspeed.

Pitch control using torque measuring is for. reducing drag in engine failure. increasing drag. reducing drag in binding.

If force is applied to the speeder spring by control lever, what will happen?. Blade angle is frozen in last known position. Blade angle finer. Blade angle coarsen.

When is superfine pitch used?. Landing and takeoff. In cruise. Engine starting to reduce propeller torque loading on starter motor.

When the flyweights fly outwards in a PCU, this is known as. onspeed. overspeed. low power settings with higher than normal pitch setting for ground manoeuvres.

On a reversing propeller moving to the maximum reversing angle, the propeller goes. from fine pitch through plane of rotation, course reverse then fine reverse. from course pitch through plane of rotation course, fine reverse then course reverse. from fine pitch through plane of rotation, fine reverse then course reverse.

If pressure is increased on the speeder spring, rpm increases. What happens to the blade angle?. Remains unchanged. Increases. Decreases.

In a prop with counterweights, what is used to make it move to fine pitch?. ATM. Centrifugal force acting on the counterweight. Governor oil pressure.

If a propeller is in fine pitch and then moves to feather it will pass throug. reverse. coarse. flight fine only.

A "double" acting propeller has. nitrogen or air on one side of piston. oil pressure on one side of piston. oil pressure on two sides of piston.

During normal propeller operation, oil pressure for the governor is provided by. a pump in the governor. a variable volume pump. the engine driven pump.

Oil for an on-speed condition passes through. the coarse pitch line. the fine pitch line. neither of the lines.

If the spur gear pump in a single acting propeller governor failed, the. blades would turn to a coarse pitch. blades would rotate to a fine pitch. blades would move to the feather position.

The hydromatic variable pitch propeller is operated on the principle of. an electrical motor moving a gear segment. oil pressure moving a piston. a venturi or 'u' tube with mercury.

The constant speed unit (C.S.U.) governor works on the principle of. manual selection through a gearbox. centrifugal twisting moments. spring pressure acting against centrifugal force.

The purpose of the pitch change cams is to. convert rotary motion to linear motion. prevent windmilling. convert linear motion to rotary motion.

The gear type pump in a C.S.U. or P.C.U. lubricates the entire propeller system. boosts engine oil system pressure. assist the governor valve to move.

When an engine fails. the propeller is feathered using an electrical feathering pump. the propeller is feathered using the propeller governor pump. the propeller is feathered using counterweights.

The purpose of an accumulator in a single acting propeller system is to. accelerate the unfeathering process. to port oil to the coarse pitch oil line to assist in feathering the propeller. provide back up to the governor pump.

When auto feathering has taken place the feathering pump is switched off by. pressure control drop switch. removing the pump circuit breaker or fuse. carrying out the manual feather drill.

On a free turbine engine it is possible to vary the propeller RPM whilst the engine RPM remains constant. by operating the PCU control Lever. it is not possible to vary the propeller RPM. by operating the Power lever.

A propeller control unit hydraulic system is supplied with oil from the. engine lubrication oil tank. aircraft hydraulic System. PCU oil tank.

Low torque sensing is used to initiate. relighting. fine pitch selection. auto feathering.

What is the purpose of the auto coarsening system?. To prevent overspeeding in the event of the flight fine pitch stop failing. To reduce drag during power loss. To save the pilot making minor changes when changing altitude.

In a single acting propeller, blade angle is increased by. counterweights and a feathering spring. CTM. oil pressure.

The function of a propeller pitch lock is to prevent the propeller from. coarsening. reducing below flight fine pitch. fining off in the event of pitch lock mechanism failure.

The minimum propeller pitch is established by the. superfine pitch stop. flight fine pitch stop. pitch lock.

Oil for the feathering system is taken from. a separate feathering oil tank. a feathering reserve in the engine oil tank. the engine lubrication system.

What are the centrifugal latches in a single acting propeller used for?. Prevent CTM. Prevent feathering of the prop on shutdown. Prevent Propeller moving to superfine.

In a two position propeller. ATM turns the prop to fine. oil pushes the prop to fine. oil pushes the prop to coarse.

An overspeed condition causes governor spring pressure to be. the same as centrifugal force. more than centrifugal force. less than centrifugal force.

When the engine is running, the CSU is sensing. propeller tip speed. propeller blade angle. engine RPM.

An accumulator may be fitted to. feather the propeller. unfeather the propeller. provide emergency control.

If governor weight spring pressure is reduced. governor weights will pivot inwards raising the governor valve allowing the blades to move to a coarser pitch. governor weights will spring outwards raising the governor valve allowing the blades to move to a finer pitch. governor weights will spring outwards raising the governor valve allowing the blades to move to a coarser pitch.

A constant speed variable pitch propeller is running whilst stationary on the ground. If it is facing into a headwind it will. slow down. remain constant. speed up.

If the TAS of an aircraft increases, the CSU will. increase the blade angle to provide constant RPM. decrease the blade angle to provide constant RPM. change the blade angle to provide constant RPM.

When governor spring load is less than governor weights, the CSU is in. underspeed. normal. overspeed.

An aircraft`s propeller system beta range. refers to the most fuel efficient pitch range to use at a given engine RPM. is used to achieve maximum thrust during take-off. is used to produce zero or negative thrust.