A&P - Powerplant

How is aircraft electrical power for propeller deicer systems transferred from the engine to the propeller hub assembly?. By slip rings and segment plates. By slip rings and brushes. By flexible electrical connectors.

How is anti-icing fluid ejected from the slinger ring on a propeller?. By pump pressure. By centripetal force. By centrifugal force.

On most reciprocating multiengine aircraft, automatic propeller synchronization is accomplished through the actuation of the. throttle levers. propeller governors. propeller control levers.

Propeller fluid anti-icing systems generally use which of the following?. Ethylene glycol. Isopropyl alcohol. Ethyl alcohol.

What is a function of the automatic propeller synchronizing system on multiengine aircraft?. To control the tip speed of all propellers. To control engine RPM and reduce vibration. To control the power output of all engines.

Ice formation on a propeller blade will. produce unbalance and vibration. increase thrust and drag. cause a change in blade angle.

What unit in the propeller anti-icing system controls the output of the pump?. Pressure relief valve. Rheostat. Cycling timer.

Proper operation of electric deicing boots on individual propeller blades may best be determined by. feeling the sequence of boot heating and have an assistant observe the loadmeter indications. observing the ammeter or loadmeter for current flow. feeling the boots to see if they are heating.

A propeller synchrophasing system allows a pilot to reduce noise and vibration by. adjusting the phase angle between the propellers on an aircraft's engines. adjusting the plane of rotation of all propellers. setting the pitch angle of all propellers exactly the same.

Which of the following determines oil and grease specifications for lubrication of propellers?. Lubricant manufacturer's instructions. Engine manufacturer's instructions. Propeller manufacturer's instructions.

Grease used in aircraft propellers reduces the frictional resistance of moving parts and is easily molded into any form under pressure. This statement defines. antifriction and plasticity characteristics of grease. antifriction and chemical stability of grease. viscosity and melting point of grease.

What type of imbalance will cause a two-blade propeller to have a persistent tendency to come to rest in a horizontal position (with the blades parallel to the ground) while being checked on a propeller balancing beam?. Vertical. Horizontal. Harmonic.

What is the purpose of an arbor used in balancing a propeller?. To support the propeller on the balance knives. To level the balance stand. To mark the propeller blades where weights are to be attached.

If a blade of a particular metal propeller is shortened because of damage to the tip, the remaining blade(s) must be. reset (blade angle) to compensate for the shortened blade. returned to the manufacturer for alteration. reduced to conform with the shortened blade.

The application of more protective coating on one blade than the other when refinishing a wood propeller. has little or no effect on operating characteristics. should never be done. may be necessary to achieve final balancing.

Apparent engine roughness is often a result of propeller unbalance. The effect of an unbalanced propeller will usually be. approximately the same at all speeds. greater at low RPM. greater at high RPM.

Which of the following is used to correct horizontal unbalance of a wood propeller?. Brass screws. Shellac. Solder.

Propeller aerodynamic (thrust) imbalance can be largely eliminated by. correct blade contouring and angle setting. static balancing. keeping the propeller blades within the same plane of rotation.

A powerplant using a hydraulically controlled constant-speed propeller is operating within the propeller's constant-speed range at a fixed throttle setting. If the tension of the propeller governor control spring (speeder spring) is reduced by movement of the cockpit propeller control, the propeller blade angle will. increase, engine manifold pressure will increase, and engine RPM will decrease. decrease, engine manifold pressure will increase, and engine RPM will decrease. decrease, engine manifold pressure will decrease, and engine RPM will increase.

Why is the pulley stop screw on a propeller governor adjustable?. To limit the maximum engine speed during takeoff. To maintain the proper blade angle for cruising. To limit the maximum propeller pitch for takeoff.

During engine operation at speeds lower than those for which the constant-speed propeller control can govern in the INCREASE RPM position, the propeller will. remain in the full HIGH PITCH position. maintain engine RPM in the normal manner until the HIGH PITCH stop is reached. remain in the full LOW PITCH position.

When engine power is increased, the constant-speed propeller tries to function so that it will. maintain the RPM, decrease the blade angle, and maintain a low angle of attack. increase the RPM, decrease the blade angle, and maintain a low angle of attack. maintain the RPM, increase the blade angle, and maintain a low angle of attack.

The propeller governor controls the. oil to and from the pitch changing mechanism. spring tension on the boost pump speeder spring. linkage and counterweights from moving in and out.

During the on-speed condition of a propeller, the. centrifugal force acting on the governor flyweights is greater than the tension of the speeder spring. tension on the speeder spring is less than the centrifugal force acting on the governor flyweights. centrifugal force of the governor flyweights is equal to the speeder spring force.

What actuates the pilot valve in the governor of a constant-speed propeller?. Engine oil pressure. Governor flyweights. Governor pump oil pressure.

What action takes place when the cockpit control lever for a hydromatic, constant-speed propeller is actuated?. Compression of the speeder spring is changed. The governor booster pump pressure is varied. The governor bypass valve is positioned to direct oil pressure to the propeller dome.

What will happen to the propeller blade angle and the engine RPM if the tension on the propeller governor control spring (speeder spring) is increased?. Blade angle will decrease and RPM will decrease. Blade angle will increase and RPM will decrease. Blade angle will decrease and RPM will increase.

How is the speed of a constant-speed propeller changed in flight?. By varying the output of the governor booster pump. By advancing or retarding the throttle. By changing the load tension against the flyweights in the governor.

When the centrifugal force acting on the propeller governor flyweights overcomes the tension on the speeder spring, a propeller is in what speed condition?. On speed. Underspeed. Overspeed.

What operational force causes the greatest stress on a propeller?. Aerodynamic twisting force. Centrifugal force. Thrust bending force.

What operational force tends to increase propeller blade angle?. Centrifugal twisting force. Aerodynamic twisting force. Thrust bending force.

How is a propeller controlled in a large aircraft with a turboprop installation?. Independently of the engine. By varying the engine RPM except for feathering and reversing. By the engine power lever.

How does the aerodynamic twisting force affect operating propeller blades?. It tends to turn the blades to a high blade angle. It tends to bend the blades forward. It tends to turn the blades to a low blade angle.

Which of the following best describes the blade movement of a propeller that is in the high RPM position when reversing action is begun?. Low pitch directly to reverse pitch. Low pitch through high pitch to reverse pitch. Low pitch through feather position to reverse pitch.

Propellers exposed to salt spray should be flushed with. engine oil. fresh water. soapy water.

How can a steel propeller hub be tested for cracks?. By anodizing. By magnetic particle inspection. By etching.

Which of the following functions requires the use of a propeller blade station?. Measuring blade angle. Indexing blades. Propeller balancing.

The propeller blade angle is defined as the acute angle between the airfoil section chord line (at the blade reference station) and which of the following?. The plane of rotation. The relative wind. The axis of blade rotation during pitch change.

During which of the following conditions of flight will the blade pitch angle of a constant-speed propeller be the greatest?. Approach to landing. Climb following takeoff. High-speed, high-altitude cruising flight.

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

The pitch-changing mechanism of the hydromatic propeller is lubricated by. the pitch-changing oil. using an approved-type grease in a grease gun at intervals prescribed by the propeller manufacturer. thoroughly greasing, necessary only during propeller overhaul.

What is the result of moving the throttle on a reciprocating engine when the propeller is in the constant-speed range with the engine developing cruise power?. Opening the throttle will cause an increase in blade angle. The RPM will vary directly with any movement of the throttle. Movement of the throttle will not affect the blade angle.

Propeller blade stations are measured from the. index mark on the blade shank. hub centerline. blade base.

The thrust produced by a rotating propeller is a result of. an area of low pressure behind the propeller blades. an area of decreased pressure immediately in front of the propeller blades. the angle of relative wind and rotational velocity of the propeller.

Why is a constant-speed counterweight propeller normally placed in full HIGH PITCH position before the engine is stopped?. To prevent exposure and corrosion of the pitch changing mechanism. To prevent hydraulic lock of the piston when the oil cools. To prevent overheating of the engine during the next start.

The low pitch stop on a constant-speed propeller is usually set so that. the engine will turn at its rated takeoff RPM at sea level when the throttle is opened to allowable takeoff manifold pressure. maximum allowable engine RPM cannot be exceeded with any combination of manifold pressure, altitude, or forward speed. the limiting engine manifold pressure cannot be exceeded with any combination of throttle opening, altitude, or forward speed.

The angle-of-attack of a rotating propeller blade is measured between the blade chord or face and which of the following?. Plane of blade rotation. Full low-pitch blade angle. Relative airstream.

The centrifugal twisting moment of an operating propeller tends to. increase the pitch angle. reduce the pitch angle. bend the blades in the direction of rotation.

Which of the following is identified as the cambered or curved side of a propeller blade, corresponding to the upper surface of a wing airfoil section?. Blade back. Blade chord. Blade face.

Which of the following best describes the blade movement of a full-feathering, constant-speed propeller that is in the LOW RPM position when the feathering action is begun?. High pitch through low pitch to feather position. High pitch directly to feather position. Low pitch through high pitch to feather position.

The holding coil on a hydromatic propeller feathering button switch holds a solenoid relay closed that applies power to the propeller. governor. dome feathering mechanism. feathering pump motor.

What is the primary purpose of the metal tipping which covers the blade tips and extends along the leading edge of each wood propeller blade?. To increase the lateral strength of the blade. To prevent impact damage to the tip and leading edge of the blade. To increase the longitudinal strength of the blade.

Blade angle is an angle formed by a line perpendicular to the crankshaft and a line formed by the. relative wind. chord of the blade. blade face.

Propeller blade station numbers increase from. hub center line to tip. tip to hub center line. blade shank butt to tip.

The aerodynamic force acting on a rotating propeller blade operating at a normal pitch angle tends to. reduce the pitch angle. increase the pitch angle. bend the blades rearward in the line of flight.

Which of the following forces or combination of forces operates to move the blades of a constant-speed counterweight-type propeller to the HIGH PITCH position?. Engine oil pressure acting on the propeller piston-cylinder arrangement and centrifugal force acting on the counterweights. Centrifugal force acting on the counterweights. Prop governor oil pressure acting on the propeller piston-cylinder arrangement.

The purpose of permanently sealing and partially filling some models of McCauley propeller hubs with dyed oil is to. provide an always clean separate lubrication of the internal parts. dampen pressure surges and prevent too rapid changes in propeller blade angle. make the location of cracks readily apparent.

Which of the following best describes the blade movement of a feathering propeller that is in the HIGH RPM position when the feathering action is begun?. High pitch through low pitch to feather position. Low pitch through reverse pitch to feather position. Low pitch through high pitch to feather position.

The blade angle of a fixed-pitch propeller. is greatest at the tip. is smallest at the tip. increases in proportion to the distance each section is from the hub.

During operational check of an aircraft using hydromatic full-feathering propellers, the following observations are made: The feather button, after being pushed, remains depressed until the feather cycle is complete, then opens. When unfeathering, it is necessary to manually hold the button down until unfeathering is accomplished. Both feather cycle and unfeather cycle are functioning properly. Both feather and unfeather cycles indicate malfunctions. The feather cycle is correct. The unfeather cycle indicates a malfunction.

Inspection of propeller blades by dye-penetrant inspection is accomplished to detect. fatigue failure. material de-bond. warpage.

What controls the constant-speed range of a constant-speed propeller?. Engine RPM. Angle of climb and descent with accompanying changes in airspeed. The mechanical limits in the propeller pitch range.

For takeoff, a constant-speed propeller is normally set in the. HIGH PITCH, high RPM position. HIGH PITCH, low RPM position. LOW PITCH, high RPM position.

Where are the high and low pitch stops of a Hamilton Standard constant-speed or two-position counterweight propeller located?. In the hub and blade assembly. In the counterweight assembly. In the dome assembly.

Which of the following statements about constant-speed counterweight propellers is also true when referring to two-position counterweight propellers?. Blade angle changes are accomplished by the use of two forces, one hydraulic and the other centrifugal. Since an infinite number of blade angle positions are possible during flight, propeller efficiency is greatly improved. The pilot selects the RPM and the propeller changes pitch to maintain the selected RPM.

Most engine-propeller combinations have one or more critical ranges within which continuous operation is not permitted. Critical ranges are established to avoid. severe propeller vibration. low or negative thrust conditions. inefficient propeller pitch angles.

Which of the following defects is cause for rejection of wood propellers?. Solder missing from screw heads securing metal tipping. An oversize hub or bolthole, or elongated boltholes. No protective coating on propeller.

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

The primary purpose of a cuff on a propeller is to. distribute anti-icing fluid. strengthen the propeller. increase the flow of cooling air to the engine nacelle.

The purpose of a three-way propeller valve is to. direct oil from the engine oil system to the propeller cylinder. direct oil from the engine through the governor to the propeller. permit constant-speed operation of the propeller.

The primary purpose of a propeller is to. create lift on the fixed airfoils of an aircraft. change engine horsepower to thrust. provide static and dynamic stability of an aircraft in flight.

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

The centrifugal twisting force acting on a propeller blade is. greater than the aerodynamic twisting force and tends to move the blade to a higher angle. less than the aerodynamic twisting force and tends to move the blade to a lower angle. greater than the aerodynamic twisting force and tends to move the blade to a lower angle.

Geometric pitch of a propeller is defined as the. effective pitch minus slippage. effective pitch plus slippage. angle between the blade chord and the plane of rotation.

Propeller blade angle is the angle between the. chord of the blade and the relative wind. relative wind and the rotational plane of the propeller. chord of the blade and the rotational plane of the propeller.

What operational force causes propeller blade tips to lag in the opposite direction of rotation?. Thrust-bending force. Aerodynamic-twisting force. Torque-bending force.

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

What are the rotational speed and blade pitch angle requirements of a constant-speed propeller during takeoff?. Low-speed and high-pitch angle. High-speed and low-pitch angle. High-speed and high-pitch angle.

(1) A mechanic certificate with a powerplant rating authorizes the holder to repair deep scars, nicks, and dents on aluminum propeller blades. (2) A mechanic certificate with a powerplant rating authorizes the holder to perform minor straightening of steel propeller blades. Regarding the above statements,. only No. 1 is true. both No. 1 and No. 2 are true. neither No. 1 nor No. 2 is true.

(1) During takeoff, propeller thrust (pull) is greatest if the blade angle of attack is low and the engine power setting is high. (2) With the aircraft stationary, propeller thrust is greatest if the blade angle of attack is high and the engine power setting is high. Regarding the above statements,. only No. 1 is true. only No. 2 is true. both No. 1 and No. 2 are true.

Longitudinal (fore and aft) clearance of constant-speed propeller blades or cuffs must be at least 1/2 inch (12.7 mm) between propeller parts and stationary parts of the aircraft. This clearance is with the propeller blades. at takeoff pitch (maximum thrust) angle. feathered or in the most critical pitch configuration. at the lowest pitch angle.

Constant-speed non-feathering McCauley, Hartzell, and other propellers of similar design without counterweights increase pitch angle using. oil pressure. spring pressure. centrifugal twisting moment.

Counterweights on constant-speed propellers are generally used to aid in. increasing blade angle. decreasing blade angle. unfeathering the propellers.

When lubricating a Hartzell propeller blade with grease, to prevent damage to the blade seals, the service manual may recommend on some models to. pump grease into both zerk fittings for the blade simultaneously. remove the seals prior to greasing and reinstall them afterwards. remove one of the two zerk fittings for the blade and grease the blade through the remaining fitting.

The primary purpose of a feathering propeller is to. prevent further engine damage when an engine fails in flight. prevent propeller damage when an engine fails in flight. eliminate the drag created by a windmilling propeller when an engine fails in flight.

What normally prevents a Hartzell Compact propeller from going to feather when the engine is shut down on the ground?. Propeller cylinder air pressure. A latch mechanism composed of springs and lock pins. Accumulator provided oil pressure.

When running-up an engine and testing a newly installed hydromatic propeller, it is necessary to exercise the propeller by moving the governor control through its entire travel several times to. seat the blades fully against the low pitch stop. free the dome of any entrapped air. test the maximum RPM setting of the governor.

Which of the following occurs to cause front cone bottoming during propeller installation?. The front cone becomes bottomed in the front propeller hub cone seat before the rear propeller hub cone seat has engaged the rear cone. The front cone enters the front propeller hub cone seat at an angle causing the propeller retaining nut to appear tight when it is only partially tightened. The front cone contacts the ends of the shaft splines, preventing the front and rear cones from being tightened against the cone seats in the propeller hub.

What is indicated when the front cone bottoms while installing a propeller?. Propeller-dome combination is incorrect. Blade angles are incorrect. Rear cone should be moved forward.

How is the oil pressure delivery on a hydromatic propeller normally stopped after the blades have reached their full-feathered position?. Pulling out the feathering push button. Electric cutout pressure switch. Stop lugs in the teeth of the rotating cam.

The primary purpose of the front and rear cones for propellers that are installed on splined shafts is to. position the propeller hub on the splined shaft. 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.

Which of the following statements concerning the installation of a new fixed-pitch wood propeller is true?. Inspect the bolts for proper torque after every 50 hours and annual inspection. Install and tighten the bolts to the proper torque during installation; no inspection interval after that.q. Inspect the bolts for proper torque after the first flight and after the first 25 hours of flying.

If propeller cones or hub cone seats show evidence of galling and wear, the most likely cause is. the pitch change stops were located incorrectly, causing the cone seats to act as the high pitch stop. the propeller retaining nut was not tight enough during previous operation. the front cone was not fully bottomed against the crankshaft splines during installation.

On aircraft equipped with hydraulically operated constant-speed propellers, all ignition and magneto checking is done with the propeller in which position?. High RPM. Low RPM. High pitch range.

Oil leakage around the rear cone of a hydromatic propeller usually indicates a defective. piston gasket. spider-shaft oil seal. dome-barrel oil seal.

Maximum taper contact between crankshaft and propeller hub is determined by using. bearing blue color transfer. a micrometer. a surface gauge.

Propeller blade tracking is the process of determining. the plane of rotation of the propeller with respect to the aircraft longitudinal axis. that the blade angles are within the specified tolerance of each other. the positions of the tips of the propeller blades relative to each other.

What is the basic purpose of the three small holes (No. 60 drill) in the tipping of wood propeller blades?. To provide a means for inserting balancing shot when necessary. To provide a means for periodically impregnating the blade with preservation materials. To allow the moisture which may collect between the tipping and the wood to escape (vent the tipping).

A fixed-pitch wooden propeller that has been properly installed and the attachment bolts properly torqued exceeds the out-of-track allowance by 1/16 inch. The excessive out-of-track condition may be corrected by. slightly overtightening the attachment bolts adjacent to the most forward blade. discarding the propeller since out-of-track conditions cannot be corrected. placing shims between the inner flange and the propeller.

Manually feathering a hydromechanical propeller means to. block governor oil pressure to the cylinder of the propeller. port governor oil pressure to the cylinder of the propeller. port governor oil pressure from the cylinder of the propeller.

In what position is the constant-speed propeller control placed to check the magnetos?. Full decrease, low propeller blade pitch angle. Full increase, high propeller blade pitch angle. Full increase, low propeller blade pitch angle.

If a flanged propeller shaft has dowel pins. install the propeller so that the blades are positioned for hand propping. the propeller can only be installed in a given position. the front cone should be checked for bottoming against the pins.

Repairs of aluminum alloy adjustable pitch propellers are not permitted to be made on which of the following propeller blade areas?. Shank. Face. Back.

Which of the following methods is used to straighten a bent aluminum propeller blade that is within repairable limits?. Careful heating to accomplish straightening, followed by heat treatment to restore original strength. Either hot or cold straightening, depending on the location and severity of damage. Cold straightening only.

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

Generally, unless otherwise specified by the manufacturer, repairs of nicks, scratches, gouges, etc. on aluminum propeller blades must be made. parallel to the length of the blade. perpendicular to the blade axis. so as to return the damaged area to the original dimensions.

Minor surface damage located in a repairable area, but not on the leading or trailing edges of aluminum blades, may be repaired by first. filing with a riffle file. filing with a half round or flat file. rough sanding and applying a proper filler.

After proper removal of aluminum blade damage, the affected surface should be polished with. fine steel wool or scotch-brite. very fine sandpaper or crocus cloth. soapstone or wire brush.

When preparing a propeller blade for inspection it should be cleaned with. mild soap and water. steel wool. methyl ethyl ketone.

What method would be used to inspect an aluminum propeller blade when a crack is suspected?. Use a bright light. Magnetic particle. Dye-penetrant.

Removal of propeller blade tips within Type Certificate Data Sheet limits when correcting a defect is. a major alteration. a major repair. permitted under the privileges and limitations of a powerplant rating.

Surface treatment to counter the effects of dye-penetrant inspection on a propeller is accomplished by. washing off with solvent. wiping with alcohol. rinse the blade in alodine solution.

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

The primary reason for careful inspection and prompt repairing of minor surface defects such as scratches, nicks, gouges, etc. on aluminum alloy propellers is to prevent. corrosion. unbalanced aerodynamics. fatigue failure.

Which of the following generally renders an aluminum alloy propeller unrepairable?. Blade face surface damage. Leading or trailing edge damage. Transverse cracks of any size.

Cold straightening a bent aluminum propeller blade may be accomplished by. the holder of a mechanic certificate with a powerplant rating. an appropriately rated repair station or the manufacturer. a person working under the supervision of the holder of a mechanic certificate with both airframe and powerplant ratings.

How does the propeller overspeed governor on a turboprop engine decrease propeller RPM?. When oil pressure is decreased, the return spring and counterweights force the oil out of the servo piston. As oil pressure increases, the servo piston is pushed forward, and the feather spring is compressed. When oil pressure is increased, the return spring and counterweights force the oil out of the servo piston.

Which of the following defects is cause for rejection of wood propellers?. Dye penetrant inspection failure. Bonding or separation of the trailing edge of the propeller blade. Delamination found by conducting a tap test.

When lubricating a newly overhauled steel hub propeller, you should lubricate the propeller. after 10 hours of operation. at the next 100-hour inspection. after one to two hours of operation.