For every 1kg of air passing through the combustion chamber, 11kg of air pass bypass the combustion chamber.

None. The go around procedure is distinct from the take off procedure. You will still have an acceleration altitude, but you will not have a screen height, V1, Vr, V2, flap retraction altitude, etc.

Jet engines are designed to achieve their best specific fuel consumption at high rpm, which can only be achieved at high altitudes where the air density is low.

Thrust produced will be low enough to equal the required cruising thrust. Also high altitude gives the best operating conditions for the airframe i.e. minimum drag during the cruise.

Turboprops need relatively dense air for the propellers to work efficiently and at high altitude the density would be too low.

Yes.

There are permanent jet streams in the...

When considering a volume of air, adiabatic lapse rate is the temperature change that is caused by the vertical movement of the volume, andThe Lapse Rate is the rate at which temperature changes with height in the atmosphere.

The Environmental Lapse Rate (ELR) is according to ISA 2°C per 1000 feet increasing altitude.

For unsaturated air, the lapse rate is 3°C per 1000 feet, this is called the Dry Adiabatic Lapse Rate (DALR).

The Saturated Adiabatic Lapse Rate (SALR) is the rate at which saturated air cools with height and is, at low levels and latitudes, 1.8°C per 1000 feet.

Swept wings are:

Better for high speed flight as they have minimal camber and thickness reduce drag and delay Mcrit More stable in turbulence as they produce less lift and as a result they are less responsive to updraughts

A turbo charger is externally driven by exhaust back pressure turning a turbine which in turn drives a compressor in the induction manifold to increase the air pressure (constant volume, higher pressure) and is controlled by waste gate.

A supercharger is internally driven by the propellor shaft to compress mixture and is controlled by RPM.

GPWS is a central computer system that receives various data inputs on configuration, (radio altimeter) height/altitude and instrument landing system glide slope deviation and is able to alert the pilot when a dangerous situation is about to occur.

Example answer for a candidate with previous Seneca experience:

Weights:

Max all up weight – take off 4570lbs Max all up weight – landing 4340lbs Empty weight - 2830lbs Usefull load - 1740lbs

Speeds:

Clean stall 66kts with flaps 60kts Vyse 89kts Cruise 140kts gear raising 107kts – lowering 129kts. Vne 195

The 6 cyclinder teledyne continental turbo- charged, fuel injected engines provide 200 hp at 2575.

Left engine rotated clockwise and right anti clockwise.

No critical engine, RayGay turbo’s 42” MAP, 40” limit at lower levels, cowl flaps provide cooling and has 3 positions, open mid and closed.

Avgas 100/130

Props 2 or 3 blade, constant speed, hydraulically actuated, fully feathering.

Oil keeps props at fine pitch, gas and air keep the rpm towards feather. Takes 6 seconds to feather and must happen before locks engage at 800 rpm.

Limit load factor 3.8G

Fuel 2 x 54 (64US) gallons tanks 8 quarts oil max 6 Min

Retractable gear – hydraulic pumps – electrically driven. 6-7 seconds transit

Nose gear has 27 degrees castor.

Main wheels 55psi, nose wheel 31psi

Cable operated controls, all moving stabilator with anti servo tab which acts as a trim.

Frise ailerons and differential ailerons, up more than down.

Manual flaps, 3 settings, 10, 25, 40 degrees.

4.5” – 5.2” hg suction – AH, DI.

Heated lift deflectors and stall warners, anti ice.

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

Powered by the gyro pressure system.