LSEDPROPILEH

What is the primary function of a helicopter main rotor?. Produce thrust only. Produce lift and control aircraft motion. Reduce aircraft weight. Generate electrical power.

The helicopter rotor blade functions like a: Car tire. Wing (airfoil). Engine piston. Fuel tank.

What motion allows a helicopter to move forward?. Yaw. Pitch. Cyclic control. Collective control.

What control changes lift for all rotor blades equally?. Cyclic. Collective. Yaw pedal. Throttle only.

The tail rotor is mainly used to: Generate lift. Control forward speed. Counter main rotor torque. Increase fuel efficiency.

The leading edge of a rotor blade is: The rear part of the blade. The front edge that first meets airflow. The blade root. The tail section.

The blade root is located at: The tip of the blade. The center hub attachment. The trailing edge. The airflow exit.

Blade flapping in helicopters helps to: Increase fuel flow. Reduce lift imbalance. Stop engine vibration. Reverse airflow.

Retreating blade stall occurs when: Blade tip speed is too high. Airflow is equal on both sides. Retreating blade loses lift at high speed. Engine stops.

Autorotation happens when: Engine increases power. Rotor is driven by airflow only. Tail rotor fails. Fuel increases.

What type of airfoil motion primarily produces lift in a helicopter rotor?. Rotational motion through air. Linear forward motion only. Engine combustion. Fuel compression.

The angle between the rotor blade chord line and the relative wind is called: Blade twist. Angle of attack. Rotor span. Tip speed ratio.

Increasing angle of attack generally: Decreases lift. Increases lift up to stall point. Stops rotation. Reduces RPM only.

The main rotor system is best described as a: Fixed engine. Rotating wing system. Fuel system. Electrical generator.

Blade tip vortices mainly contribute to: Induced drag. Engine power. Fuel combustion. Tail torque.

The purpose of rotor blade twist is to: Equalize lift along span. Increase engine RPM. Reduce fuel flow. Stop vibration.

Which part of the rotor system supports blade rotation?. Engine mount. Hub assembly. Fuel tank. Tail boom.

Retreating blade stall is most likely to occur during: High forward speed. Hover. Ground taxi. Engine idle.

The dissymmetry of lift is corrected by: Blade flapping. Fuel increase. Engine shutdown. Tail rotor speed.

The lift force on a rotor blade is perpendicular to: Engine shaft. Relative wind. Fuel line. Blade root.

The drag force on a rotor blade acts: Perpendicular to lift. Opposite motion of blade. Along blade span. Vertically upward.

Which force supports helicopter weight in hover?. Thrust only. Lift from main rotor. Drag force. Tail rotor force.

Induced velocity is: Airflow through rotor disk. Engine RPM. Fuel flow rate. Blade thickness.

The rotor disk is defined as: Engine casing. Swept area of rotor blades. Fuel tank area. Tail surface.

In momentum theory, the rotor is treated as: Solid disk actuator. Jet engine. Fuel pump. Wing tip.

Blade element theory assumes the blade is divided into: Engine parts. Small aerodynamic sections. Fuel cells. Electrical units.

The hub-and-blade system is primarily designed to handle: Fuel load. Aerodynamic and centrifugal forces. Electrical load. Temperature only.

Centrifugal force on rotor blades acts: Inward toward hub. Outward from hub. Downward only. Upward only.

Blade root stress is highest because of: Lowest speed. Highest structural load. No airflow. Fuel pressure.

The purpose of lead-lag motion is to: Control fuel flow. Relieve in-plane stresses. Increase lift. Stop rotation.

Coriolis effect in rotor blades is caused by: Change in blade radius. Engine failure. Fuel variation. Wind direction only.

Feathering motion refers to: Blade pitch change. Blade bending. Engine rotation. Fuel injection.

The retreating blade experiences: Higher airflow. Lower airflow. No motion. Engine power increase.

The advancing blade experiences: Lower relative wind. Higher relative wind. No airflow. Zero lift.

Translational lift improves efficiency because: Rotor stops. Airflow becomes cleaner. Fuel increases. Engine slows.

Ground effect reduces: Lift. Induced drag. Engine power. Blade speed.

The main rotor produces thrust that acts: Horizontally only. Vertically and horizontally depending on tilt. Only downward. Only upward.

The tail boom supports: Main rotor. Tail rotor. Fuel tank only. Landing gear only.

Rotor RPM stability is maintained by: Pilot only. Governor system. Fuel pump. Blade shape.

If rotor RPM decreases, lift will: Increase. Decrease. Stay constant. Reverse.

High rotor RPM increases risk of: Noise and stress. Fuel saving. Lift loss only. Weight reduction.

The blade tip speed is important because it affects: Fuel color. Compressibility effects. Engine oil. Landing gear.

Rotor efficiency is highest when: Induced drag is low. RPM is zero. Fuel is high. Weight is high.

The main rotor produces torque reaction that: Stops helicopter. Rotates fuselage opposite direction. Increases lift. Reduces fuel.

Blade chord line is: Engine axis. Straight line from leading to trailing edge. Rotor shaft. Fuel line.

Rotor blade stall begins when: Angle of attack is too high. RPM is low. Fuel is high. Drag is zero.

The main rotor mast connects: Engine to rotor hub. Fuel tank to engine. Tail rotor to cockpit. Landing gear to body.

Helicopter maneuvering is controlled by: Only throttle. Combination of cyclic, collective, pedals. Only engine RPM. Only tail rotor.

Blade span refers to: Rotor diameter direction. Root-to-tip length. Engine size. Fuel capacity.

Helicopter rotor design mainly focuses on: Maximizing lift and efficiency. Increasing fuel color. Reducing cockpit size. Changing landing gear.

What is the primary function of a helicopter main rotor?. Produce lift and control aircraft motion. Produce only forward thrust. Reduce engine load. Stabilize fuel consumption.

A rotor blade is best described as what type of aerodynamic surface?. Flat plate. Airfoil. Cylinder. Radial arm.

What is the function of collective pitch control in helicopters?. Changes blade angle equally for all blades. Changes yaw direction. Controls engine RPM only. Adjusts tail rotor speed.

What happens when cyclic control is applied forward?. Rotor thrust increases vertically. Rotor disk tilts forward. Engine shuts down. Tail rotor stops.

What is the main function of the tail rotor?. Increase lift. Counter main rotor torque. Increase fuel efficiency. Reduce drag on fuselage.

Blade flapping primarily helps to: Increase RPM. Balance lift dissymmetry. Reduce fuel burn. Increase engine power.

Retreating blade stall occurs when: Blade tip speed increases too much. Retreating blade loses lift at high speed. Engine overpowers rotor. Collective is lowered.

Autorotation happens when: Engine increases power. Rotor is driven by airflow only. Tail rotor fails. Collective is fully raised.

The advancing blade is the blade that: Moves opposite airflow. Moves in same direction as aircraft motion. Stops rotating. Produces no lift.

Dissymmetry of lift is caused by: Engine power imbalance. Difference in relative wind speed on rotor blades. Fuel imbalance. Tail rotor thrust.

Blade tip speed is highest at: Root. Mid-span. Tip. Hub.

What is the purpose of blade twist?. Reduce structural weight. Maintain uniform angle of attack. Increase engine power. Reduce RPM.

What is induced flow in a rotor system?. Fuel flow. Airflow through rotor disk. Electrical current. Engine exhaust.

What increases rotor efficiency most effectively?. High disk loading. Low induced drag. High RPM only. Heavy blades.

What is the main effect of ground effect?. Increased fuel consumption. Reduced induced drag near ground. Increase engine temperature. Reduced RPM.

Blade root is primarily designed for: High speed airflow. Structural load transfer to hub. Lift generation. Drag reduction.

FAA: What is the main advantage of constant-speed propeller?. Fixed RPM operation. Automatic blade pitch adjustment. No governor required. Manual control only.

FAA: What is blade angle?. Angle between chord line and rotation plane. Angle of aircraft climb. Engine torque angle. Air density angle.

FAA: Propeller thrust is primarily produced by: Pressure difference across blades. Fuel combustion. Electrical force. Gear rotation.

FAA: Increasing blade pitch generally results in: Lower thrust. Higher drag and thrust capability. No change. Reduced RPM only.

FAA: What controls propeller RPM in constant-speed systems?. Carburetor. Governor. Flaps. Rudder.

EASA: Main rotor RPM is typically kept: Variable during flight. Constant within narrow range. Zero during cruise. Random for efficiency.

EASA: Retreating blade stall limits: Maximum forward speed. Maximum altitude only. Fuel consumption. Engine RPM.

EASA: Main rotor torque reaction is countered by: Fuselage shape. Tail rotor. Wing flaps. Engine RPM.

EASA: What improves rotor lift efficiency most?. Higher density altitude. Increased blade area. Reduced blade angle. Engine shutdown.

Rotor momentum theory relates lift to: Pressure difference only. Mass flow and velocity change. Fuel consumption. Blade color.

Higher rotor RPM generally results in: Lower lift. Higher lift capability. No change. Engine failure.

What reduces rotor vibration most effectively?. Proper blade tracking. Higher fuel flow. Lower air density. Increase torque.

What is blade tracking?. Fuel alignment. Same tip path for all blades. Engine timing. Electrical sync.

FAA: What is propeller slip?. Difference between theoretical and actual motion. Fuel leakage. Blade failure. Engine delay.

Blade element theory divides rotor blade into: Engine parts. Small elements along span. Fuel sections. Electrical zones.

FAA: Feathering of propeller means: Increase RPM. Align blade with airflow. Remove blades. Reverse engine.

FAA: Reverse thrust is used for: Takeoff. Landing deceleration. Climb. Cruise.

FAA: Propeller efficiency is highest at: Zero speed. Moderate forward speed. Maximum RPM always. Idle power.

FAA: Blade erosion mainly occurs at: Root. Leading edge. Trailing edge. Hub center.

What causes helicopter torque effect?. Engine combustion imbalance. Rotor reaction force. Fuel distribution. Wing lift.

What is advance ratio?. Blade length ratio. Forward speed / tip speed. Fuel ratio. Engine ratio.

What is cyclic feathering used for?. Increase fuel flow. Change rotor disk tilt. Stop engine. Lock rotor.

What is the main function of a swashplate?. Transfer control to rotating blades. Control fuel. Control tail rotor speed. Reduce vibration only.

What limits helicopter maximum speed?. Fuel type. Retreating blade stall. Engine oil. Rotor color.

FAA: What is propeller governor purpose?. Control RPM. Increase fuel flow. Reduce drag only. Control landing gear.

FAA: What is feathering mainly used for?. Cruise efficiency. Engine failure drag reduction. Takeoff boost. Stall prevention.

FAA: Propeller blade angle is measured relative to: Aircraft body. Plane of rotation. Ground. Engine mount.

FAA: What happens if RPM increases in fixed pitch prop?. Thrust decreases. Thrust increases. No change. Engine stops.

FAA: Propeller efficiency depends on: Air density only. Advance ratio. Engine color. Fuel type.

EASA: What is autorotation used for?. Normal cruise. Emergency landing. Takeoff only. Hovering only.

EASA: What is vortex ring state?. Increased lift. Loss of lift and control. Higher RPM. Engine boost.

EASA: Main rotor converts engine power into: Electrical energy. Lift and thrust. Fuel pressure. Heat.

EASA: Tail rotor failure results in: Increased lift. Uncontrolled yaw. Faster climb. Reduced drag.

EASA: Articulated rotor system allows: Fuel efficiency. Blade flapping, lead, lag motion. Higher RPM. Weight reduction only.

In helicopter laboratory propeller/rotor design studies, blade aerodynamic data is primarily validated using: POH performance charts. AMM lubrication charts. SRM damage limits only. Airport charts.

Mandatory corrective actions affecting helicopter propeller systems issued by CAAP are called: Service Bulletins. Airworthiness Directives. Maintenance Advisories. Flight Permits.

Certification of helicopter rotor blade design under CAAP jurisdiction follows: CAR Part 21 Subpart C. CAR Part 2 Subpart A. CAR Part 8 Subpart B. CAR Part 145 Subpart D.

The acceptable practices for helicopter rotor balancing in absence of manufacturer data may be referenced from: FAA AC 43.13-1B (adopted guidance). ICAO Annex 14. CAR Part 66 only. Pilot License Manual.

CAAP maintenance rules requiring inspection of helicopter rotor systems are mainly governed by: CAR Part 5. CAR Part 9. CAR Part 11. CAR Part 4.

Structural inspection and repair limits for helicopter rotor blades are commonly found in the: Pilot Operating Handbook (POH). Structural Repair Manual (SRM). Navigation Logbook. Flight Plan.

For helicopter propeller (rotor blade) maintenance procedures in CAAP operations, the primary reference document is: Aircraft Maintenance Manual (AMM). Flight Operations Manual (FOM). Air Traffic Manual (ATM). Aerodrome Manual.

The component that transfers engine power to the main rotor system is the: Tail rotor shaft. Main gearbox. Collective lever. Swashplate.

The tendency of a rotor blade to twist due to aerodynamic forces is called: Torsional effect. Gyroscopic effect. Flapping equilibrium. Induced drag effect.

The main parameter considered in Prandtl–Glauert correction is: Air density. Mach number. Temperature gradient. Reynolds number.

The tip loss effect in rotor theory refers to: Increase in blade stiffness. Loss of lift near blade tips due to vortex formation. Increase in engine power. Reduction in chord length only.

According to blade element theory, a rotor blade is analyzed by: Treating the entire blade as one rigid body. Dividing the blade into small aerodynamic sections. Ignoring lift distribution. Assuming constant chord only.

The induced velocity in rotor theory is defined as: Blade structural deflection. Downwash velocity through the rotor disk. Engine exhaust velocity. Forward flight speed only.

Changes in magnitude of total rotor thrust of the main rotor during cruise are achieved by _______. Combined rotor speed change and blade pitch angle. Altering collective blade pitch while rotor speed is constant. Varying rotor speed while blade pitch is constant. Changing air velocity around the blade.

In a fixed propeller, what happens to the angle of attack of the blade if forward speed increases?. Goes to zero. Increases. Decreases. Remains fixed.

The drag force of a rotor blade is opposed by _______. Torque. Rotor vibration. Rotor RPM. Blade flapping.

Activity factor, airfoils, pitch distribution, tip Mach number, and disk loading affect _______. Propulsion efficiency. Engine efficiency. Propeller efficiency. Airfoil efficiency.

Thrust produced by a rotating propeller is a result of _______. Angle of attack of propeller and plane of rotation. Area of decreased pressure immediately in front of blades. Area of low pressure behind blades. Angle of relative wind and rotational velocity.

(1) During takeoff, propeller thrust 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 first statement is true. Only second statement is true. Both statements are true. Neither statement is true.

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

Propeller efficiency is highest when _______. High exhaust velocity compared to free-stream velocity. Low exhaust velocity compared to free-stream velocity. Zero velocity condition. Constant velocity condition.