Because the air is less dense thus the TAS is higher for a given power setting and for this reason modern jet aircraft are designed to be most efficient at high altitude.

A swept wing makes the velocity vector normal to the leading edge a shorter distance than the chordwise resultant.

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.

Hypoxia, a lack of oxygen to tissues of the body due to low partial pressure at altitude.

Symptoms are: blue lips, apparent personality change, impaired judgement, muscular impairment, short term memory loss, sensory loss, hyperventilation, unconsciousness.

Other possible effects:

• Baurotrauma

• Lung damage

In a high bypass design, the vast majority of the thrust is derived from the ducted fan, rather than from combustion gases expanding in a nozzle.

A high bypass ratio provides a lower thrust specific fuel consumption (grams/sec fuel per unit of thrust in kN using SI units), especially at zero velocity (at takeoff) and at the cruise speed of most commercial jet aircraft.

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.

When rolling the aircraft the up-going wing will experience more drag than the down-going wing. This will result in a yawing moment that directly opposes the desired direction of turn. (i.e.: rolling left will cause a right yaw.)

Assuming I'm performing single pilot operations:

• power idle,

• max brakes (and reversers if available),

-maintain directional control using rudder input,

• After coming to a full stop set parking break.

• Inform ATC 'Stopping'.

• Initiate the appropriate process to diagnose the problem (ECAM, NITS DODAR, checklists....).

• When performing multi pilot operations the actions performed by me will depend with my current role: PF, PM and/or CM1 CM2.

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.

Apply opposite aileron to the direction of the roll.