The mode control panel is used to select the autothrottle, autopilot, and flight director operating modes. The flight mode annunciator displays current flight modes.

Fuel injection provides:

• Fuel free from vaporization ice

• Better economy through metered delivery

• More responsive and efficient engine

• Less maintenance

Induced drag and its wing tip vortices are a direct consequence of the creation of lift by the wing.

Since the Coefficient of Lift is large when the Angle of Attack is large, induced drag is inversely proportional to the square of the speed whereas all other drag is directly proportional to the square of the speed.

The effect of this is that induced drag is relatively unimportant at high speed in the cruise and descent where it probably represents less than 10% of total drag. In the climb, it is more important representing at least 20% of total drag. At slow speeds just after take off and in the initial climb, it is of maximum importance and may produce as much as 70% of total drag.

Finally, when looking at the potential strength of wing tip vortices, all this theory on induced drag must be moderated by the effect of aircraft weight. Induced drag will always increase with aircraft weight.

Downward inclination of a wing from the root to the tip.

8.000ft

Radiation fog forms on cloudless nights with only very light winds and high relative humidity when the cold ground cools the air above it to its dew point causing condensation (fog).

Usually occurs inland in valleys and low lying areas (as these areas tend to have more moisture) and usually occurs in a high pressure system.

Angle of attack is the angle between the chord of the aerofoil and the relative airflow.

Angle of incidence is the angle between the chord and the aircrafts longitudinal datum.

When an aircraft climbs, the static pressure in the instrument case decreases, which allows the enclosed capsule to expand.

This in turn moves the needle on the instrument to indicate a corresponding altitude.

During descent, the opposite function applies.

Altimeter errors can originate and vary from:

Instrument Pressure Time-lag Barometric Density Temperature Blocked static port

Boots on the leading edges inflate (6 seconds) to break the ice dissipating it into the airflow.

Powered by the gyro pressure system.

Mostly in the fan, but also from the exhaust nozzle duct.