HELI

Introduction to Rotary Wing Aircraft, Vorlesung an der ZHAW SoE, Studiengang Aviatik

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These flashcards delve into the intricate mechanics and dynamics of helicopter flight, covering topics like rotor aerodynamics, blade pitch control, and engine power management. They explore the challenges of scaling down helicopter designs, the physics behind autorotation, and the nuances of ground effect. This set is invaluable for university students and engineers studying aeronautical engineering, offering a deep understanding of helicopter operations and the forces at play during flight.

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13.06.2018 / 20.06.2018

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What are the difficulties met by the designers of a helicopter main gearbox? (A) Accommodate a reduction ratio (Untersetzung) of about 100 in limited space and mass. (B) Accommodate a reduction ratio (Untersetzung) of about 100 in limited space and mass. Additionally, the design must minimize maintenance and maximize reliability. (C) Accommodate a reduction ratio (Untersetzung) of about 100 at a limited cost. (D) Accommodate a reduction ratio (Untersetzung) of about 100 in limited space and mass. Additionally, the design must keep noise level to a minimum.

(B) Accommodate a reduction ratio (Untersetzung) of about 100 in limited space and mass. Additionally, the design must minimize maintenance and maximize reliability.

How can the reliability of the helicopter gearboxes be improved and the maintenance costs reduced? (A) By the introduction of a control system which reduces vibrations. (B) By the introduction of better suited metallic materials. (C) By the introduction of a monitoring system, which measures wear and tear (Verschleiss) in the various components and sends warnings as soon as one needs replacement. (D) By the introduction of a monitoring system, which measures vibrations in the various components and counterbalances them with small shakers.

(C) By the introduction of a monitoring system, which measures wear and tear (Verschleiss) in the various components and sends warnings as soon as one needs replacement.

What are the differences between Category A and Category B helicopters? (A) Cat A helicopters, unlike cat B, have a certain stay-up capability in case of engine failure. (B) Cat A helicopters, unlike cat. B, are always multi engine. (C) Cat A helicopters, unlike Cat. B, have a significant excess power. (D) Cat. B helicopters are always single engine.

(A) Cat A helicopters, unlike cat B, have a certain stay-up capability in case of engine failure.

Why are all single engine helicopters Cat. B? (A) Because they are less reliable. (B) Because they have less available power. (C) Because they have no stay-up capability in case of engine failure. (D) Because they have less excess power.

C) Because they have no stay-up capability in case of engine failure.

What are Performance Class 1 operations? (A) Flights, or portion of flights, during which an emergency landing may be required in the presence of an engine failure, but only when flying over hostile territory. (B) Flights, or portion of flights, during which an emergency landing may be required in the presence of an engine failure. (C) Flights, or portion of flights, during which an emergency landing is always required in the presence of an engine failure. (D) Flights, or portion of flights, during which an emergency landing is never required in the presence of an engine failure.

(D) Flights, or portion of flights, during which an emergency landing is never required in the presence of an engine failure.

What are Performance Class 2 operations? (A) Flights, or portion of flights, during which an emergency landing is never required in the presence of an engine failure. (B) Flights, or portion of flights, during which an emergency landing may be required in the presence of an engine failure. (C) Flights, or portion of flights, during which an emergency landing is always required in the presence of an engine failure. (D) Flights, or portion of flights, during which an emergency landing may be required in the presence of an engine failure, but only when flying over hostile territory.

(B) Flights, or portion of flights, during which an emergency landing may be required in the presence of an engine failure.

What are Performance Class 3 operations? (A) Flights, or portion of flights, during which an emergency landing is always required in the presence of an engine failure. (B) Flights, or portion of flights, during which an emergency landing is never required in the presence of an engine failure. (C) Flights, or portion of flights, during which an emergency landing may be required in the presence of an engine failure. (D) Flights, or portion of flights, during which an emergency landing may be required in the presence of an engine failure, but only when flying over hostile territory.

(A) Flights, or portion of flights, during which an emergency landing is always required in the presence of an engine failure.

Which physical phenomena can limit the maximum forward speed of helicopters? (A) Retreating blade stall. (B) Compressibility effects on advancing blade. (C) Compressibility effects on advancing blade and retreating blade stall. (D) Compressibility effects and stall of advancing blade.

Conventional helicopters need a tail rotor for directional control. How does the power required by the tail rotor relate to the total power required? (A) It may require up to approximately 50% of the total power required, depending on the flight condition. (B) It may require up to approximately 10% of the total power required, depending on the flight condition. (C) It may require up to approximately 1% of the total power required, depending on the flight condition. (D) Tail Rotor normally works in windmilling condition and does not require any power to work.

(B) It may require up to approximately 10% of the total power required, depending on the flight condition.

What are the main contributions to the power required of a helicopter? (A) Induced power, parasitic power, viscous losses, losses in the gearboxes. (B) Induced power, parasitic power, air conditioning, anti-torque system power, transmission losses. (C) Induced power, parasitic power, viscous losses, anti-torque system power, transmission losses. (D) Induced power, parasitic power, viscous losses, air conditioning, hydraulic power, transmission losses.

What is the largest contribution to the power required of a helicopter in hover flight? (A) Induced power only out-of-ground-effect. Parasitic power when hovering in-ground-effect. (B) Induced power. (C) Aircraft systems (air conditioning etc). (D) Viscous losses or compressibility effects, depending on the blade section aerofoils.

(B) Induced power.

What is Ground Effect (GE) in a conventional helicopter and what are the consequences on power required? (A) GE generates high-energy vortexes between rotor and ground. As a consequence, the power required to generate a Thrust force T is normally smaller. (B) GE generates a low-pressure air cushion between rotor and ground. As a consequence, the power required to generate a Thrust force T is normally smaller. (C) GE generates a high-pressure air cushion between rotor and ground. As a consequence, the power required to generate a Thrust force T is normally larger. (D) GE generates a high-pressure air cushion between rotor and ground. As a consequence, the power required to generate a Thrust force T is normally smaller.

(D) GE generates a high-pressure air cushion between rotor and ground. As a consequence, the power required to generate a Thrust force T is normally smaller.

What may be the most important advantage - beside the absence of a Tail Rotor - of co-axial rotors in forward flight at high advance ratio? (A) The retreating blades of each rotor happen to be on opposite sides (left / right), causing the asymmetric lift distribution over the two rotor discs to compensate each other. (B) The compressibility effects on the advancing blades of each rotor are much smaller due to the rotors geometry. (C) The retreating blades of each rotor happen to be on the same side (left / right), causing the asymmetric lift distribution over the two rotor discs to compensate each other. (D) The retreating blades of each rotor happen to be on opposite sides (left / right), causing the problems due to excessive flapping to compensate each other.

(A) The retreating blades of each rotor happen to be on opposite sides (left / right), causing the asymmetric lift distribution over the two rotor discs to compensate each other.

In which phases can Autorotation be broken down into (sequence is relevant)? (A) Engine(s) disconnection, violent collective pull-up, stabilized descent, final flare, touchdown with (small) residual kinetic energy. (B) Reduction of collective pitch until rate of descent stabilises, stabilized descent, engine(s) disconnection, final flare, touchdown with (small) residual kinetic energy. (C) Engine(s) disconnection, reduction of collective pitch until rate of descent stabilises, stabilized descent, final flare, touchdown with (small) residual kinetic energy (D) Engine(s) disconnection, activation of the automatic autorotative system, stabilized descent, final flare, touchdown with large residual kinetic energy.

(C) Engine(s) disconnection, reduction of collective pitch until rate of descent stabilises, stabilized descent, final flare, touchdown with (small) residual kinetic energy

During the stabilized descent phase of an Autorotation, what can be said about potential and kinetic energy? (A) Kinetic energy is zero during Autorotation, as engines are shut off. (B) Kinetic energy of the helicopter and of the rotor, as well as the potential energy, continuously decrease. (C) All energies remain constant at all times. (D) Kinetic energy of the helicopter and of the rotor is kept constant, whereas potential energy reduces.

(D) Kinetic energy of the helicopter and of the rotor is kept constant, whereas potential energy reduces.

In which of the following cases must an emergency landing be performed? (A) Engine failure in a twin engined helicopter. (B) Engine failure in a twin engined helicopter during take-off. (C) Tail rotor complete failure in a twin engined helicopter. (D) Engine failure in a twin engined helicopter during landing.

(B) Engine failure in a twin engined helicopter during take-off.

Every point in the “AVOID” areas in the Height-Velocity diagrams (also said “dead man curves”) indicate a combination of height and horizontal speed. What is the use of such a diagramme? (A) Help the pilot avoiding inefficient flight conditions. (B) Indicate the height-speed combinations, where flight is legal. (C) Indicate the height-speed combinations, where an emergency landing would prove difficult for the average pilot. (D) Indicate the height-speed combinations, where an emergency landing would be easy even for the inexperienced pilot.

What must be the pilot’s reaction to the development of Ground Resonance? (A) Immediately interrupt the contact with the ground, if the rotor RPM are high enough, otherwise stop the rotor. (B) Immediately switch on the stability augmentation system. (C) Immediately reduce collective pitch. (D) Immediately stop the rotor by starting the rotor brake.

(A) Immediately interrupt the contact with the ground, if the rotor RPM are high enough, otherwise stop the rotor.

Speaking of scaling down an aircraft design, we might recall that the mass are proportional to the cube of the scale of length, l3; the aerodynamic forces are proportional to l2. What can be said about the development of smaller scale helicopters? (A) Sizing of load-carrying components may become impossible. (B) Sizing of load-carrying components is more problematic. (C) Sizing of load-carrying components is less problematic. (D) Sizing of load-carrying components is trivial.

What can be said about the aerodynamics of smaller scale helicopters as compared to full scale ones? (A) Since Reynolds number is much smaller, the aerodynamic effects may also be very different. (B) Since Reynolds number is much bigger, the aerodynamic effects may also be very different. (C) Given the special nature of helicopters, no significant changes are expected. (D) Since Reynolds number does not change much, no significant changes are expected.

(A) Since Reynolds number is much smaller, the aerodynamic effects may also be very different.

Why is the generation of an induced velocity a consequence of the generation of lift (by a heli rotor)?A. Because of the conservation of momentum B. Because of the conservation of energy C. Because of air viscosity D. Because of rotation speed Omega

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A. Because of the conservation of momentum

In hover, induced velocity is inversely proportional to rotor area. This means, with respect to a reference radius: A. That a rotor with a smaller radius will generate a higher induced velocity but will have the same efficiency – while generating the same thrust force B. That a rotor with a smaller radius will generate a smaller induced velocity – while generating the same thrust force C. That a rotor with a smaller radius will generate the same induced velocity – while generating the same thrust force D. That a rotor with a smaller radius will generate a higher induced velocity – while generating the same thrust force

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D. That a rotor with a smaller radius will generate a higher induced velocity – while generating the same thrust force

Induced velocity in autorotation is: A. Zero B. Equal to descent velocity, without considering the final flare C. Smaller than descent velocity, without considering the final flare D. Larger than descent velocity, without considering the final flare

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C. Smaller than descent velocity, without considering the final flare

Induced velocity in autogyrus / gyroplanes is: A. Zero because the rotor is windmilling B. Non-zero because the rotor does generate lift C. Zero because the rotor is not driven by the engine D. Non-zero because the rotor turns

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B. Non-zero because the rotor does generate lift

What is normally meant by “vortex ring”? A. A working state of a rotor characterized by stable re-circulation through rotor disc B. A working state of a rotor characterized by a strong wake C. A working state of a rotor characterized by circulation D. A working state of a rotor characterized by unstable re-circulation through rotor disc

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D. A working state of a rotor characterized by unstable re-circulation through rotor disc

What is meant with the term windmilling? A. Windmilling is the working state of a rotor in which the flow gives energy to the rotor system – i.e it is the state in which wind turbines work when they generate power B. Windmilling is the working state of a rotor in which the rotor accelerates its rotation speed C. Windmilling is the working state of a rotor in which the rotor system gives energy to the flow- i.e it is the state in which wind turbines work when they generatie power D. WIndmilling is the working state of a rotor in which the flow gives energy to the rotor system – i.e it is the state in which helicopter rotors work

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A. Windmilling is the working state of a rotor in which the flow gives energy to the rotor system – i.e it is the state in which wind turbines work when they generate power

Why is a rotor less efficient than a wing in forward flight at high speed, at an advance ratio mü=V/(Omega x R) = 0.40 for instance? A. Because the flow around the retreating blade is disturbed by compressibility effects and the advancing blade experiences inverse flow or very high angle of attack B. Because the flow around the blades is disturbed by compressibility effects C. Because the flow around the advancing blade is disturbed by compressibility effects and the retreating blade experiences inverse flow or very high angle of attack D. Because wing increase their efficiency as speed increases

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C. Because the flow around the advancing blade is disturbed by compressibility effects and the retreating blade experiences inverse flow or very high angle of attack

What is the physical phenomenon at the origin of ground effect? A. While flying close to the ground a high-pressure cushion appears between rotor and ground B. While flying close to the ground a high-pressure cushion appears above the rotor C. While flying close to the ground a high-pressure cushion appears between rotor and ground D. While flying close to the ground a high-pressure cushion appears above the rotor

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A. While flying close to the ground a high-pressure cushion appears between rotor and ground

How would you describe the effects of ground effect on a helicopter performances? A. Power required and lift decrease proportionally B. Power required decreases while generating the same lift C. Power required increases while generating the same lift D. Power required and lift increase proportionally

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B. Power required decreases while generating the same lift

Why is forward speed of conventional helicopter limited about 150 – 160kt? A. Fuselage drag B. Compressibility effects on retreating blade and stall of advancing blade C. Fuselage drag and tail rotor stall D. Compressibility effects on advancing blade and stall of retreating blade

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D. Compressibility effects on advancing blade and stall of retreating blade

Why does the above limitation not apply to tilt-rotors such as Bell-Boeing MV22? A. Because the rotors are tilted forward at high-speed B. Because the fuselage has a much smaller drag coefficient C. Because the radius of the rotors is much smaller than a conventional helicopter D. Because the rotors are tilted forward at high-speed interference between rotor downwash and fuselage is reduced

A. Because the rotors are tilted forward at high-speed

Why does the above limitation not apply to compound helicopters such as the Eurocopter X3 (= helicopters with a main rotor but also a small wing and propellers)? A. Because at high speed the main rotor is partially unloaded since wing and propellers generate most of the necessary forces (forward thrust) B. Because at high speed the main rotor is partially unloaded since wing and propellers generate most of the necessary forces (lift) C. Because at high speed the main rotor is partially unloaded since wing and propellers generate most of the necessary forces (forward thrust and lift) D. Because at high speed the main rotor is partially unloaded since wing and propellers generate most of the necessary forces (drag and lift)

C. Because at high speed the main rotor is partially unloaded since wing and propellers generate most of the necessary forces (forward thrust and lift)

The main rotor head types are: A. Semi-rigid (also called “see-saw”), semi articulated, articulated, hingeless and bearlingless B. Semi-rigid (also called “see-saw”), articulated, hingeless and bearingless C. Semi-rigid (also called “see-saw”), articulated, hingeless D. Rigid, hingeless and bearingless

B. Semi-rigid (also called “see-saw”), articulated, hingeless and bearingless

What are hingeless rotor heads? A. Rotor heads without mechanical hinges around flap and lead/lag axes B. Rotor heads without hinges around flap and lead/lad axes C. Rotor heads with rigid connections to blades, like propellers D. Rotor heads without mechanical hinges

A. Rotor heads without mechanical hinges around flap and lead/lag axes

What are bearingless rotor heads? A. Rotor heads without hinges around flap and lead/lag axes B. Rotor heads without mechanical hinges around flap and lead/lag axes C. Rotor heads with rigid connections to blades, like propellers D. Rotor heads without mechanical hinges

D. Rotor heads without mechanical hinges

Which type of rotor head provide the highest control moments? (A) Hingeless and bearingless, because these constructions (Bauweise) accommodate large hinge offset more conveniently. (B) Hingeless and bearingless, because these constructions (Bauweise) accommodate small hinge offset more conveniently. (C) Hingeless and bearingless, because these constructions (Bauweise) are more suitable to large size helicopters. (D) Hingeless and bearingless, because these constructions (Bauweise) do not have mechanical hinges.

A) Hingeless and bearingless, because these constructions (Bauweise) accommodate large hinge offset more conveniently.

Do rotor heads with large hinge offsets provide a lower “comfort” for passengers when flying in turbulence? (A) No, because turbulence might cause a non-symmetric loading on the rotor blades. (B) No, because aerodynamic forces generated by turbulence on the blades are transmitted to the fuselage through the rotor head. (C) Yes, because aerodynamic forces generated by turbulence on the blades are transmitted to the fuselage through the rotor head. (D) No, because turbulence does not alter (ändert) the distribution of aerodynamic forces.

(C) Yes, because aerodynamic forces generated by turbulence on the blades are transmitted to the fuselage through the rotor head.

Why is a helicopter equipped with a semi-rigid (“see-saw”) rotor slower than other rotor head types to react to pilot’s inputs? (A) Because semi-rigid rotors have large hinge offsets. (B) Because semi-rigid rotors are an old solution. (C) Because semi-rigid rotors have mechanical hinges. (D) Because the hinge offset of semi-rigid rotors is zero.

(D) Because the hinge offset of semi-rigid rotors is zero.

Which materials are commonly used on modern helicopters to manufacture main rotor blades? (A) Carbon fibers and glass fibers composite. (B) Aluminum. (C) Carbon fibers composite. (D) Wood.

(A) Carbon fibers and glass fibers composite.

What is the function of the tail rotor system? (A) Provide control around the pitch axis. (B) Preventing the helicopter from spinning around. (C) Provide control around the yaw axis. (D) Provide control around the roll axis.

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A. Because of the conservation of momentum

D. That a rotor with a smaller radius will generate a higher induced velocity – while generating the same thrust force

C. Smaller than descent velocity, without considering the final flare

B. Non-zero because the rotor does generate lift

D. A working state of a rotor characterized by unstable re-circulation through rotor disc

A. Windmilling is the working state of a rotor in which the flow gives energy to the rotor system – i.e it is the state in which wind turbines work when they generate power

C. Because the flow around the advancing blade is disturbed by compressibility effects and the retreating blade experiences inverse flow or very high angle of attack

A. While flying close to the ground a high-pressure cushion appears between rotor and ground

B. Power required decreases while generating the same lift

D. Compressibility effects on advancing blade and stall of retreating blade

A. Because the rotors are tilted forward at high-speed

C. Because at high speed the main rotor is partially unloaded since wing and propellers generate most of the necessary forces (forward thrust and lift)

B. Semi-rigid (also called “see-saw”), articulated, hingeless and bearingless

A. Rotor heads without mechanical hinges around flap and lead/lag axes

D. Rotor heads without mechanical hinges

A) Hingeless and bearingless, because these constructions (Bauweise) accommodate large hinge offset more conveniently.

(C) Yes, because aerodynamic forces generated by turbulence on the blades are transmitted to the fuselage through the rotor head.

(D) Because the hinge offset of semi-rigid rotors is zero.

Which materials are commonly used on modern helicopters to manufacture main rotor blades? (A) Carbon fibers and glass fibers composite. (B) Aluminum. (C) Carbon fibers composite. (D) Wood.

(A) Carbon fibers and glass fibers composite.

What are the advantages of a Fenestron system with respect to conventional tail rotor systems? (A) Low noise and safety in flight. (B) Low noise and safety on the ground. (C) Low noise and higher aerodynamic efficiency at high speed. (D) Low noise and lower induced speed.

(B) Low noise and safety on the ground.

What are the disadvantages of the NOTAR system with respect to conventional tail rotor systems? (A) It is aerodynamically less efficient, less safe on ground and noisier. (B) It is aerodynamically less efficient and is less safe on the ground. (C) It is aerodynamically less efficient and generates louder noise. (D) It is aerodynamically less efficient at high speed.

(D) It is aerodynamically less efficient at high speed.

Are conventional tail rotors equipped with cyclic pitch control? (A) No, never. (B) Yes, always. (C) Yes, sometimes. (D) Yes, but it is operated automatically.

(A) No, never.

Why do gyroplanes (Tragschrauber) have no tail rotor? (A) Because the rotor of gyroplanes is not driven by the engine and operates permanently in windmilling state. (B) Because the rotor of gyroplanes is driven by a very small engine. (C) Because gyroplanes are equipped with counter-rotating rotors. (D) Because the rotor of gyroplanes does not generate lift.

(A) Because the rotor of gyroplanes is not driven by the engine and operates permanently in windmilling state.

What is the effect of a change in collective pitch (the lever on the left hand side of the pilot)? (A) Fuselage drag drops. (B) The pitch angle is changed on all blades simultaneously (C) Compressibility effects on retreating blade (rücklaufendem Blatt) and stall of advancing blade (vorlaufendes Blatt). (D) Fuselage drag and tail rotor stall.

(B) The pitch angle is changed on all blades simultaneously

What is the effect of a change in cyclic pitch (the lever on the right hand side of the pilot)? (A) The pitch angle is changed in function of the blade’s flapping angle. (B) The pitch angle is changed in function of blade aerodynamic load. (C) The pitch angle is changed in function of blade azimuthal position. (D) The pitch angle is changed in function of the blade’s angle of attack.

What does the pilot control with the pedals on a conventional helicopter? (A) Collective pitch angle of tail rotor blades. (B) Collective pitch angle of main rotor blades. (C) Orientation of the tail rotor swashplates. (D) Collective pitch angle of tail rotor blades and deflection of the rudder.

(A) Collective pitch angle of tail rotor blades.

How is a control moment around the pitch axis generated in a tandem helicopter? (A) A combination of collective, lateral and longitudinal cyclic. (B) A combination of differential collective and lateral cyclic. (C) A combination of lateral and longitudinal cyclic. (D) A combination of differential collective and longitudinal cyclic

(D) A combination of differential collective and longitudinal cyclic

How is a control moment around the pitch axis generated in a co-axial helicopter? (A) Lateral cyclic on both rotors. (B) Longitudinal cyclic on both rotors (C) Collective on both rotors. (D) A combination of differential collective, lateral and longitudinal cyclic.

(B) Longitudinal cyclic on both rotors

How much is the phase delay between the orientations (Lage) of the Swashplates (Taumelscheiben) and the tip-path-plane (Rotorebene)? (Hinweis: tip-path-plane orientation is equivalent to blade deflection around flap hinge) (A) Approximately 90 degrees. (B) Approximately zero. (C) Approximately 45 degrees. (D) Approximately 180 degrees.

(A) Approximately 90 degrees.

How much is the phase delay between the blade deflections around flap hinge and lead/lag hinge? (A) Approximately 45 degrees. (B) Approximately zero. (C) Approximately 90 degrees. (D) Approximately 180 degrees.

How much is the phase delay between the orientation of the swashplate and the blade deflection around the lead/lag hinge? (A) Approximately 45 degrees. (B) Approximately zero. (C) Approximately 90 degrees. (D) Approximately 180 degrees.

(D) Approximately 180 degrees.

What is the main advantage of retractable landing gear? (A) Smaller drag force . (B) Weight. (C) Smaller drag force in hover. (D) Additional lift force in forward flight.

(A) Smaller drag force .

What is the most popular remedy against ground resonance? (A) Dampers on blades (affecting rotation around lead/lag axis) and landing gear. (B) Dampers on blades (affecting all blade’s degrees of freedom) and landing gear. (C) Dampers on landing gear only. (D) Dampers on blades (affecting rotation around lead/lag axis).

(A) Dampers on blades (affecting rotation around lead/lag axis) and landing gear.

When might ground resonance occur? (A) While taking off or touching down. (B) When starting or slowing down the main rotor with helicopter on ground. (C) When starting or slowing down the main rotor with helicopter in flight. (D) When the main rotor reaches full rotational speed but helicopter is still on ground.

(B) When starting or slowing down the main rotor with helicopter on ground.

Indicate the most critical requirements for a helicopter engine. (A) (1) Long time at high power setting, (2) no fixed airflow to rely on for cooling, (3) long time at high pitch and / or bank angles (B) (1) Very high max power available, (2) no fixed airflow to rely on for cooling, (3) long time at high pitch and / or bank angles, (4) low costs (C) (1) Very high max power available, (2) no fixed airflow to rely on for cooling, (3) long time at high pitch and / or bank angles, (4) low specific consumption (D) (1) Long time at high power setting, (2) no fixed airflow to rely on for cooling, (3) very low specific consumption

(A) (1) Long time at high power setting, (2) no fixed airflow to rely on for cooling, (3) long time at high pitch and / or bank angles

What are category A and B helicopters? (A) Category A are helicopters with at least two engines and two gearboxes for redundancy. Category B helicopters have only one engine and one gearbox. (B) Category A are all helicopters with more than one engine. Cat. B helicopters are all single engine helicopters. (C) Category A are helicopters with “stay-up” capability in case of engine failure. Cat. B helicopter must perform an emergency landing if an engine failure occurs. (D) Category A are helicopters with turbine engines. Category B helicopters have piston engines.

(C) Category A are helicopters with “stay-up” capability in case of engine failure. Cat. B helicopter must perform an emergency landing if an engine failure occurs

What are category C helicopters? (A) JAR-OPS 3 only mentions Category 1, 2 and 3 helicopters. (B) Category C helicopters are the ones that my only operate in Performance Class 3. (C) Category C helicopters are the ones that may not operate in hostile territory. (D) JAR-OPS 3 does not mention any Category C helicopter.

(D) JAR-OPS 3 does not mention any Category C helicopter

What are Performance Class 1 flights? (A) A flight in which an engine failure - except in the early take-off and late landing phases - would not force the pilot to perform an emergency landing. (B) A flight in which an engine failure - occurring at any moment of the flight - would not force the pilot to perform an emergency landing. (C) A flight in which an engine failure - except flight in hostile territory - would not force the pilot to perform an emergency landing. (D) A flight in which a transmission failure (Getriebe, Kraftübertragung)

(B) A flight in which an engine failure - occurring at any moment of the flight - would not force the pilot to perform an emergency landing.

What are Performance Class 2 flights? (A) A flight in which an engine failure - except in the early take-off and late landing phases - would not force the pilot to perform an emergency landing. (B) A flight in which an engine failure - occurring at any moment of the flight - would not force the pilot to perform an emergency landing. (C) A flight in which an engine failure - depending on pilot’s ability and experience - might force the pilot to perform an emergency landing. (D) A flight in which a transmission failure (Getriebe, Kraftübertragung) - occurring at any moment of the flight - would not force the pilot to perform an emergency landing.

(A) A flight in which an engine failure - except in the early take-off and late landing phases - would not force the pilot to perform an emergency landing.

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