You would expect to have to decrease the engine thrust to stay on the correct flight path because with the

headwind the ground path will tend to decrease.

You would expect to have to decrease the engine thrust to stay on the correct flight path because with the

headwind the ground path will tend to increase.

You would expect to have to increase the engine thrust to stay on the correct flight path because with the

headwind the ground path will tend to decrease.

You would expect to have to increase the engine thrust to stay on the correct flight path because with the

headwind the ground path will tend to increase.

the altitude in the standard atmosphere at which the prevailing density occurs.

the height obtained by setting the subscale of an altimeter to ONE.

the altitude obtained by setting the subscale of an altimeter to QNH.

the height in the standard atmosphere at which the prevailing density occurs.

SRincreases slowly with altitude up to full throttle height.

SR and SFC (Specific Fuel Consumption) increase slowly with altitude up to full throttle height.

SR and SFC (Specific Fuel Consumption) decrease slowly with altitude up to full throttle height.

SR decreases slowly with altitude up to throttle height.

The higher the gross mass the greater is the speed for descent.

The higher the average temperature (OAT) the lower is the speed for descent.

The mass of an aeroplane does not have any effect on the speed for descent.

The higher the gross mass the lower is the speed for descent.

Max Endurance, because fuel flow is proportional to thrust at the minimum.

Max Range, because fuel flow is proportional to lift to drag ratio.

Max Range, because this speed corresponds to the maximum lift to drag ratio at the minimum.

Max Endurance, because fuel flow is proportional to power required.

Increase until transition altitude and remains constant thereafter.

Decrease until transition altitude and remains constant thereafter

Increase with altitude.

Decrease with altitude.

True Airspeed must be low, and the fuel flow must be low.

True Airspeed must be high, and the fuel flow must be low.

True Airspeed must be low, and the fuel flow must be high

True Airspeed must be high, and the fuel flow must be high.

2780 m

2300 m

3 060 m

2580 m

VMP

1.32VMD

VMD

1.32VMP

30%

21.8%

18.5%

 8%