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How does propeller produce thrust? (1.2). By increasing the air pressure behind the propeller rotating plane. By accelerating large mass of air rearwards. By decelerating large mass of air rearwards.

What is the usual power setting pitch (max pitch) of a propeller? (1.2). 10° to 12°. 85° to 90°. 20° to 35°.

A fixed pitch propeller is normally more efficient at: (1.6). medium to high speeds at high altitudes. low to high speeds at high altitude. low to medium speeds at low altitudes.

Angle of attack on propeller is the angle: (1.3). between propeller chord line and direction of flight. between propeller chord line and relative wind direction. between propeller chord line axis of propeller.

between propeller chord line axis of propeller. between propeller chord line and relative wind direction. between propeller chord line axis of propeller. propeller chord line and rotation plane of propeller.

There is (1.6). less pitch at the shank of propeller blade than at blade tip. less pitch at the tip of propeller blade than at blade shank. larger pitch at the end of propeller blade than at blade shank.

Characteristic positions of the propeller blade angle (blade station) in most cases is measured from: (1.5). 2 inches from the blade root. centerline of the engine. root of the blade.

The centrifugal force is acting on a propeller blade in the following manner: (1.9). It tends to pull out the blade and increase the blade pitch. It tends to pull out the blade and decrease the blade pitch. It tends to pull out the blade, without affect on the blade pitch.

Thrust bending force (1.9). bends propeller blades backward. bends propeller blades forward. pulls propeller blades out of hub.

For aircraft cruise, the following propeller pitch angle is mostly used: (1.9). Low pitch. Medium pitch. Feather.

The chord line of a propeller is: (1.6). a line joining the leading and trailing edge of a blade. a line joining tip and root of a blade. a line joining blade trailing edge and propeller hub axis.

The primary purpose of propeller is to (1.2). change engine horsepower to thrust. provide static and dynamic stability to aircraf. create lift on the fixed aerofoils of an aircraf.

Reverse blade pitch is (1.2). from -2° to -8°. from 2° to 8°. from -2° to 0°.

) What is effective pitch stands for? (1.4). It is same as geometric pitch. It is geometric pitch minus slip. It is geometric pitch plus slip.

What is the "P-Effect" on a propeller aircraft? (1.10). It is the propeller assimetric disk loading which occurrs only during climb or descent. It is the propeller assimetric disk loading which occurrs only in cruise. It is the propeller assimetric disk loading which occurrs only during the thrust reverse application.

Torque on an aircraft with propeller engine acts (1.11). opposite the direction of propeller pitch. the same direction as it is the direction of propeller rotation. opposite the direction of propeller rotation.

Feather position of the fan blade is at (1.2). 80° to 85°. 85° to 90°. exactly at 90°.

What is the variable pitch propeller? (1.3). It is a propeller where blade pitch angle can be adjusted by maintenance crew before flight depending on the type of flight operation. It is a propeller where blade angle can be changed automatically during the operation, depending on command levers position. It is a propeller where the pitch is changing by using the basic propeller forces: mainly centrifugal and torque forces which change blade angle as required.

The actual distance a propeller moves forward through the air during one revolution is known as the: (1.4). relative pitch. effective pitch. geometric pitch.

A constant speed propeller provides maximum efficiency by: (1.2). increasing blade pitch as the aircraft speed decreases. increasing the lift coefficient of the blade. adjusting blade angle for most conditions encountered in flight.

What operational force tends to bend the propeller blades forward at the tip? (1.9). Thrust bending force. Torque bending force. Centrifugal twisting force.

A fiberglass composite blade (2.6). could not be struck by lighting, since fibreglass is not an electricity conductor. could not be struck by lighting due fast turning of the blades. requires lightning strike protection.

) Centrifugal latches are fitted to lock the propeller (2.9). in feathered position in case of engine failure. in feathered position in case of propeller failure. in fine pitch position (usually before the engine shutdown).

During normal propeller operation, oil pressure for propeller operation is provided by: (2.8). the oil pump in the propeller governor. the oil pump in the propeller hub. the engine oil pressure pump.

) The constant-speed control unit is also called: (2.8). propeller governor. ) propeller synchrophase control unit. propeller accumulator.

The following materials are mostly used for manufacture of modern propellers: (2.6). Wooden. Steel (hollow steel blades), composites (with or without metal spar) and aluminum blades. Composites (with or without metal spar) only.

The wood most often used today for propeller construction is (2.2). Balsa. Spruce. Birch.

What are the advantages of aluminium propellers? (2.5). Low cost of maintenance and the low weight. The resistance to acid and caustic solutions. Quick removal and installation and good resistance to the foreign object damage.

What is the benefit of contra-rotating propellers? (2.10). Les noise produced. Eliminates single propeller torque which acts on the aircraf. Decreased pitch of each propeller.

30) Propeller bolts when tightening propeller hub should be tightened using: (2.4). any tightening method. circle pattern. star pattern.

Propeller back is the side with: (2.7). Lower camber. Higher camber. Depends on the type of propeller (pusher or puller).

Ground-adjustable propellers (2.8). pitch can be changed while propeller is rotating. pitch can not be changed at all. pitch can be changed while propeller is not rotating.

) What is the meaning of propeller blade "back" and "face"? (2.7). Both of them are blade areas away from the engine. The back faces away from the engine and is the cambered side. The face is in the direction of the engine and is the flat side. The face faces away from the engine and is the cambered side. The back is in the direction of the engine and is the flat side.

Tractor propeller is mounted (2.10). In front of the engine. At the back of the engine. In front or at the back of the engine.

) While installing propeller mechanic should: (2.12). align index marks on spinner bulkhead and engine cowl. align index marks on spinner and engine cowl. align index marks on spinner bulkhead and spinner.

) Oil pressure increase in governor means (2.8). no propeller pitch change. lower propeller pitch. higher propeller pitch.

What will happen if the CSU on twin engine turboprop aircraft leaks oil? (3.22). Propeller blades will go to higher pitch and RPM will fall. ) Propeller blades will go to lower pitch and RPM will fall. Propeller will go to higher pitch and RPM will increase.

38) When does the aerodynamic imbalance appear? (3.4). It is the imbalance which occurs when the center of gravity of the propeller does not coincide with the axis of rotation. When the thrust (or pull) of the blades is unequal. It is imbalance of the propeller when the centers of gravity of propeller elements (for example: counterweights or blades) do not follow the same plane of rotation.

During the operation in beta range, the propeller pitch is controlled (3.18. by power lever. by condition lever. by overspeed governor lever.

) Which acts on a blade in direction of blade pitch decrease? (3.4). Centrifugal twisting moment (CTM). Thrust and torque force. Drag and lift force.

Why is feathering necessary on multi-engine aircraft? (3.8). To prevent the engine rotation, since its oil system is not functioning, the engine and propeller bearings could be damaged. To prevent the propeller turning and decrease of drag in case of engine failure. To enable the engine further operation in case of propeller failure.

Why, on some engines, the propeller is normally positioned to low pitch before the engine is stopped? (3.19). to prevent the moisture to enter in the propeller cylinder. to enable oil to remain in the propeller cylinder. to prevent overheating of the engine starter during next start.

Electrically controlled propeller use DC power and rotation: (3.26). to turn the propeller. electrically controled propellers do not exists. to control propeller blade pitch.

Which of these statements applies to a propeller that has been “feathered”? (3.15). Its leading edges are facing forwards in the direction of flight. It is operating at its maximum rotational speed. Its leading edges are facing 90 degrees to the direction of flight.

What device push propeller against the hydraulic pressure to high pitch? (3.4). Low pitch stop. Governor pilot valve. propeller counterweights.

If propeller blade angle is decreased and engine power remains the same, the RPM will: Decrease. remain the same. increase.

If the engine power increases, the CSU (Propeller Governor) will retain the same RPM by : (3.2). increasing the blade angles. keeping constant blade angles. decreasing the blade angles.

Propeller auto feathering function is disarmed by pilot: (3.11). during landing. during T/O. in cruise.

How does the crew change the propeller RPM on a constant speed propeller? (3.3). Propeller RPMs are constantly changing during the flight (automatically). By moving the condition lever which changes the CSU speeder spring tension. By moving the power lever which changes the CSU speeder spring tension.

) On most single acting propellers (on multi-engine aircraft) the following is correct: (3.4). Oil pressure moves the blades in direction of low pitch, spring in the direction of high pitch. Oil pressure moves the blades in direction of high pitch, spring in the direction of low pitch. Oil pressure moves the blades in direction of high pitch, pressurized nitrogen in the direction of low pitch.

) Reduction gearbox allows the (3.19). blade tips to operate below the speed of sound. blade tips to operate above the speed of sound. In beta range the propeller pitch is:.

blade tips to rotate slower than the root of the propeller blade (3.18). not changing at all. not changed by governor but by fuel mixing lever. not changed by governor but by power lever position.

The governor oil pressure is approximately: (3.22). 200 psi. 300 psi. 40 psi.

As over speed protection the governor - when RPM becomes to high: (3.25). bleed off propeller servo oil into reduction gearbox sump and decrease the blade pitch. bleed off propeller servo oil into reduction gearbox sump and increase the blade pitch. increase servo oil pressure in reduction gearbox and increase the blade pitch.

The most efficient AOA varying from: (3.2). 10° to 12°. 5 a 7. 2 a 4.

What is the purpose of pilot valve within the CSU. (3.22). to receive the inputs from the pilot through the power lever in the cockpit. to receive the inputs from the pilot through the power lever in the cockpit auto feather the propeller in case of it's failure. it supplies the oil to the blade change mechanism, allows the oil to flow back into the scavenge oil system or it locks the system to keep the blade pitch constant.

What will happen if pilot adds power to the engine (by power lever) during the flight and the propeller lever remains at the same position. (3.22). Propeller blade angle will be positioned to the higher angle in order to keep the requested propeller RPM constant. Propeller blade angle will be positioned to the lower angle in order to keep the requested propeller RPM constant. Propeller blade angle will remain at the same angle in order to keep the requested propeller RPM constant.

Propeller synchronisation for Type I is used (4.2). on the ground. in flight except landing and take of. during the beta range operation.

Synchronisation is used to (4.2). reduce vibration and noise. reduce pitch of the fastest running blades. reduce the engine load and improve its cooling.

Type II synchronization principle is (4.2). lower rpm engine will synchronize to higher rpm engine. slave engine will synchronize on master engine. higher rpm engine will synchronize on lower rpm engine.

Propeller synchrophasing system (4.2). controls the EGT relationship between both engines. controls rpm relationship between both engines. controls the phase relationship between blades on both engines.

Propeller synchrophasing system principle is: (4.4). Slave engine propeller follows master's rpm. Master engine propeller follows slave's propeller blade position. Slave engine propeller follows master's propeller blade position.

Synchrophasing reduces vibration by the use of (4.5). ) pulse probes and a single synchrophase unit. pulse probe and multiple synchrophase units. tachometers and electrical motors.

Synchronising can only be achieved if the slave propeller is (4.2). at the same speed as the master propeller. within 200 rpm of the master propeller. within 100 rpm of the master propeller.

Synchronising is carried out to (4.2). match propeller tip speed. match engine rpm. match blade phase angle difference.

The synchronisation governor monitors (4.2). ) Propeller RPM. propeller tip speeds. Engine RPM.

Active noise and suppression system is used for: (4.6). keep noise level as low as possible. keep synchronization as high as possible. keep blade tips of left and right propeller as at the same phase position as possible.

You can test the synchrophasing system (4.5). when engines are running on ground only. when aircraft in the air only. when engines are not running only.

Propeller anti-icing system usually works on the following basis: (5.2). engine hot air blowing over the blade leading edges. engine hot air blowing over the blade leading edges. electrical resistance heating or chemical action of glycol/ alcohol.

The flow rate of isopropyl alcohol in anti-ice propeller assures: (5.6). from 1 to 3,5 hours of operation. from 2 to 5 hours of operation. from 0,5 to 2,5 hours of operation.

How is aircraft electrical power for propeller deicer systems transferred from the engine to the propeller hub assembly? (5.4). By flexible electrical connectors. By slip rings and brushes. By slip rings and flexible electrical pulse transmitters.

inboard and outboard heat elements on one propeller are: (5.4). in operation all the time with no cool down period in between. in operation in sequence for defined time period. in operation at the same time.

Removing overshoes on propeller blade is allowed by: (5.9). Non metallic scraper. Metallic scraper. Aluminum scraper.

hay do you need to use only non-metalic roller for overshoes installation? (5.10). To prevent proper installation. To install it faster. To prevent heat element damage.

A metal propeller may be statically balanced by (6.10). adding varnish to the lighter blade root. removing metal from the opposite blade root. adding or removing permanent weight loads.

adding or removing permanent weight loads. adding or removing permanent weight loads. It is not allowed since that action could change the blade pitch angle and cause imbalance. Yes, if the permissible bending is not exceeded.

Metal propeller inspection - in order to distinguish between scratch and crack the one should use: (6.4). magnifying glass. dye penetrant inspection. Both other answers are correct.

Ultrasonic inspection can be done on: (6.5). metal, wooden and composite materials. metal materials only. composite materials only.

) How can steel propeller hub be tested for cracks? (6.5). visually. by magnetic particle inspection. by a spectrographic inspection.

How is the knife- edge method of propeller static balancing accomplished? (6.9). The test stand has 2 knife- edged steel edges and assembled propeller is positioned between them: the propeller must be free of any rotating tendency (in all positions) if no imbalance is present. Blades of the propeller must be positioned on knife edges (on their reference mark) and propeller must show no tendency to move. Front and aft side of propeller are attached to the knife edges and slowly rotated by a motor, while electrical pickup measures the imballance.

How is the propeller blade angle checked? (6.7). During the propeller operation at speed between 1200 and 1500 RPM. By a propeller protractor when the propeller is operating at low speed. By a propeller protractor: when the propeller is on a stand or installed on the engine.

What is the minimum radius of propeller blade leading edge repair? (6.18). 3/8 inch. 3/16 inch. 1 inch.

Coin Tap test is used on (6.6). wooden propellers only. composite propellers and wooden propellers. metal propellers.

No repair is allowed: (6.4). On the blade root. On the de-icing heater and composite structure. On electrical cables that bring power to the blade heater.

Powerplant technician can perform the following works on the propeller: (6.5). Only removal and installation of the propeller. Inspection, adjustment, removal/ installation, minor repair. All works described in MM and CMM.

Prior to using the universal propeller protractor (6.7). ensure the propeller blade is in horizontal position. determine the reference blade station. ) remove the blade from propeller.

) What action is required if the propeller track is out of limits? (6.6). ) What action is required if the propeller track is out of limits? (6.6). The cause should be investigated: first action should be to check the propeller attach bolts torque, or to remove the propeller and inspect it for dirt or damage and to check the crankshaft for alignment. The blade tracking must be adjusted by bending the blade to the required radial distance.

The blade tracking must be adjusted by bending the blade to the required radial distance. delamination. Internal cracks. Bent propeller.

) After FOD blade minor repair (6.18). protective finish for corrosion protection shall be applied. weighing of propeller is mandatory. static balancing is mandatory.

What must be done if a crack is suspected on a metal propeller blade? (6.5). Coin tap test. Any NDT applicable inspection . Visual inspection is enough.

What must be done if a damage on a blade shank is found? (6.4). No action is required since the blade shank is over-dimensioned due to this possibility. Propeller blade must be sent for repair to an overhaul facility. It can always be repaired even installed on the engine.

At what point of propeller blade the pitch angle is measured? (6.7). At reference location. At blade root. At blade tip.

What must be done if the dynamic imbalance is over the MM limits? (6.11). Dynamic balance check of the propeller (using electronic equipment), without spinner and related equipment. Static balancing of the propeller (using electronic equipment). Dynamic balance check with propeller, spinner and related equipment installed on the aircraft with the engine running (using electronic equipment).

) Where must be the propeller protractor installed on a blade? (6.7). Four inches from the blade root. Four inches from the blade tip. Only on a reference blade station mentioned in the MM.

Why must the blades be carefully inspected? (6.17). Because the damage could result in blade failure. Because damage could cause the reposition of the blade reference mark at 75% distance. Because any damage can cause imbalance which could ground the aircraft.

) What tool is used to determine propeller blade angle? (6.7). Propeller tracking meter. A universal propeller protractor. Propeller balancer.

One of the advantages of inspecting an aluminum propeller utilizing dye-penetrant inspection procedure is that: (6.5). it indicates overspeed condition. defects below the surface could be detected. it shows whether visible lines and other marks are actually cracks rather than scratches.

Repairs of aluminum alloy adjustable pitch propellers are not permitted to be made on which of the following propeller blade areas? (6.17). FACE. SHANK. BACK.

It is important that nicks in aluminum alloy propeller blades be repaired as soon as possible in order to: (6.17). equalize the centrifugal loads between the blades. eliminate stress concentration points. maintain equal aerodynamic characteristics between the blades.

Tachometer check is successful if results are within (6.17). +-20 rpm. +-100 rpm. +-10 rpm.

propeller periodic greasing should occur at least (7.2). every day. once in six months. once in 3 years.

Storage of wooden propeller shall (7.3). has no special required conditions. should especially take into consideration temperature conditions. should especially take into consideration humidity conditions.

For long term storage the governor shall be filled up with (7.3). some mineral oil. conservation oil. no oil.

Engine and Propeller when in flyable condition: (7.2). Should be flying at least 30 minutes per year. Should be flying at least 30 minutes per month. Should be flying at least 30 hours per month.

The best storage position when removed from aircraft is: (7.2). Not important. Vertical position. Horizontal position.

Temporary storage is treated as non-use of aircraft for up to (7.2). 1 year. 90 days. A week.

For indefinite (long term storage) storage engine shall be filled up with conservation oil and (7.2). then operate for 30 minutes. then just be left as it is. and oil drained again and filled up with normal oil.

For long term storage the best way is (7.3). to keep propeller on the engine. to keep propeller parts in original package. o send propeller back to manufacturer.

Metal propellers shall be for long term storage (7.3). left fully dry. coated with thin coat of conservation oil. coated with fish oil.