Set of flashcards 032 Fragen

Flashcards	14
Language	Deutsch
Category	Technology
Level	University
Created / Updated	05.06.2025 / 12.06.2025
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Considering TAS for maximum range and maximum endurance, other factors remaining constant:

Both will stay constant regardless of altitude.

Both will increase with increasing altitude.

Both will decrease with increasing altitude.

TAS for maximum range will increase with increased altitude while TAS for maximum endurance will decrease with increased altitude.

Keyboard commands:

= turn,

= for-/backward,

= scroll

Both will stay constant regardless of altitude.

Both will increase with increasing altitude.

Both will decrease with increasing altitude.

TAS for maximum range will increase with increased altitude while TAS for maximum endurance will decrease with increased altitude.

The Density Altitude is ...

... equal to the pressure altitude.

... used to establish minimum clearance of 2'000 feet over mountains.

... used to determine the aeroplane performance.

... used to calculate the FL above the Transition Altitude.

Keyboard commands:

= turn,

= for-/backward,

= scroll

... equal to the pressure altitude.

... used to establish minimum clearance of 2'000 feet over mountains.

... used to determine the aeroplane performance.

... used to calculate the FL above the Transition Altitude.

A twin engine aeroplane in cruise flight with one engine inoperative has to fly over high ground. In order to maintain the highest possible altitude the pilot should choose the ...

... long range speed.

... speed at the maximum lift.

... speed corresponding to the maximum value of the lift / drag ratio.

... speed corresponding to the minimum value of (lift / drag)^3/2.

Keyboard commands:

= turn,

= for-/backward,

= scroll

... long range speed.

... speed at the maximum lift.

... speed corresponding to the maximum value of the lift / drag ratio.

... speed corresponding to the minimum value of (lift / drag)^3/2.

The pilot of a light twin engine aircraft has calculated a 4'000 m service ceiling, based on a takeoff mass of 3'250 kg. If the takeoff mass is 3'000 kg, the service ceiling will ...

... have to be calculated again in order to determine if the service ceiling is higher or lower than 4'000 m.

... be less than 4'000 m.

... be higher than 4'000 m.

... be unchanged, equal to 4'000 m.

Keyboard commands:

= turn,

= for-/backward,

= scroll

... have to be calculated again in order to determine if the service ceiling is higher or lower than 4'000 m.

... be less than 4'000 m.

... be higher than 4'000 m.

... be unchanged, equal to 4'000 m.

Consider the range and endurance of a piston powered single-engined aeroplane. Which of the following statements is correct about the power setting?

Endurance decreases if the power is increased from a given power setting

Maximum range is achieved with the power setting for maximum endurance

The power setting for maximum range is higher than for maximum endurance

Increasing the power from a given power setting increases the range

Keyboard commands:

= turn,

= for-/backward,

= scroll

Endurance decreases if the power is increased from a given power setting

Maximum range is achieved with the power setting for maximum endurance

The power setting for maximum range is higher than for maximum endurance

Increasing the power from a given power setting increases the range

What conditions would the aeroplane have to be flown in order to achieve maximum aircraft speed?

The thrust set for best Specific Fuel Consumption

The thrust set for minimum drag

The angle of attack for best endurance with maximum thrust

Maximum thrust equal to total drag

Keyboard commands:

= turn,

= for-/backward,

= scroll

The thrust set for best Specific Fuel Consumption

The thrust set for minimum drag

The angle of attack for best endurance with maximum thrust

Maximum thrust equal to total drag

When calculating the landing distance, what percentage of the reported wind component must be allowed for?

100% of a headwind, and 100% of a tailwind

50% of a headwind, and 150% of a tailwind

50% of a headwind, and 100% of a tailwind

150% of a headwind, and 50% of a tailwind

Keyboard commands:

= turn,

= for-/backward,

= scroll

100% of a headwind, and 100% of a tailwind

50% of a headwind, and 150% of a tailwind

50% of a headwind, and 100% of a tailwind

150% of a headwind, and 50% of a tailwind

In the climb, an aircraft has a thrust to weight ratio of 1:4 and a lift to drag ratio of 12:1.While ignoring the slight difference between lift and weight in the climb, the climb gradient will be:

8.3%

3.0%

16.7%

3.3%

Keyboard commands:

= turn,

= for-/backward,

= scroll

8.3%

3.0%

16.7%

3.3%

An aeroplane is climbing at a constant power setting and a speed of Vx. If the speed is reduced and power setting maintained, the climb gradient will ...

increase and the rate of climb will decrease

decrease and the rate of climb will decrease

increase and the rate of climb will increase

decrease and the rate of climb will increase

Keyboard commands:

= turn,

= for-/backward,

= scroll

increase and the rate of climb will decrease

decrease and the rate of climb will decrease

increase and the rate of climb will increase

decrease and the rate of climb will increase

In order to achieve the maximum rate of climb, aeroplane should be flown at the indicated airspeed which gives ...

... maximum excess power.

... the best speed / drag ratio.

... the best lift / drag ratio.

... the best thrust / drag ratio.

Keyboard commands:

= turn,

= for-/backward,

= scroll

... maximum excess power.

... the best speed / drag ratio.

... the best lift / drag ratio.

... the best thrust / drag ratio.

Region of "reversed command" means?

The thrust required is independent of the airspeed.

A thrust reduction results in an acceleration of the aeroplane.

A lower airspeed requires more thrust.

A momentary increase of airspeed has no influence on the thrust required.

The thrust required is independent of the airspeed.

A thrust reduction results in an acceleration of the aeroplane.

A lower airspeed requires more thrust.

A momentary increase of airspeed has no influence on the thrust required.

Consider a glide with all engines off. Initial conditions are zero wind and the attitude of the aeroplane gives maximum range. A headwind arises and initially the aeroplane attitude is not changed. After some time has passed the glide range ...

... increases when the CL is reduced

... decreases when the CL is reduced

... remains maximum when the CL remains the same

... remains the same when the CL is reduced

... increases when the CL is reduced

... decreases when the CL is reduced

... remains maximum when the CL remains the same

... remains the same when the CL is reduced

The effect an increase of mass has on the value of stalling speed (IAS) is that Vs:

Increases or decreases, depending on the amount of weight increase

Decreases

Increases

Remains constant

Increases or decreases, depending on the amount of weight increase

Decreases

Increases

Remains constant

A multi engine aeroplane is flying at the minimum control speed (VMCA). Which parameter(s) must be maintainable after engine failure?

Straight flight

Straight flight and altitude

Heading, altitude and a positive rate of climb of 100 ft/min

Altitude

Straight flight

Straight flight and altitude

Heading, altitude and a positive rate of climb of 100 ft/min

Altitude

032 Fragen

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