Fusible plugs offer protection from tire blowouts caused by thermal expansion that is generated in the tire under extra hard braking conditions.

Vref = 1.3 x Vs0 (stall speed in the landing configuration).

The position of the CG directly influences the fuel consumption of an aircraft. An aft position of the CG makes the aircraft less stable, requiring less lift to be generated in both the horizontal stabilizer and wings, reducing the overall drag of the aircraft, and increasing the max range.

You want to load the the aircraft so that the CG is at, or as close as possible, to the aft limit (Without exceeding it).

Mach number describes the speed of sound, which changes with the density of the medium it is travelling through.

When you reach the speed of sound, the compressibility effect creates a supersonic flow along the wing if you exceed a certain mach number.

This causes airflow separation and flutter.

It is therefore much safer and much easier to use a Mach number to express a limit at which compressibility effects start to tear the aircraft apart, as it is a constant value at all altitudes.

Forward motion forces air into the intake which is a convergent duct where it is compressed (causing a temperature rise).

Fuel is added and combustion takes place increasing the volume. The expanding gasses accelerate to the atmosphere through the exhaust duct nozzle producing a propulsive jet.

Carb icing can occur with temperatures as high 30°C and humidity as low as 50%, but it is more likely when below 20°C and high humidity, especially during low power settings.

Asymmetric Committal Altitude/Height is the minimum height needed to establish a positive climb whilst maintaining adequate speed for control and removal of drag during an approach to a landing.

In the Seneca at Oxford we used 200ft AGL. At this altitude when continuing for landing you selected the landing flaps (check clear runway, on speed, on altitude, landing clearance received).

You now are committed to land, single engine G/A with flaps 40 and gear down is not possible in a Seneca.

An IRS is an Inertial Reference System  which consists of accelerometers, gyroscopes (laser) and a position computer.

The computer calculates the aircrafts position by direction and velocity sensed by the accelerometers from the initial latitude and longitude input.

An IRS enables the aircraft to fly great circle tracks and to navigate accurately across vast expanses where no ground based navigation aids are available.

The speed is too low for an indication.

Swept back wings