Technical Specific — Sample Paper 2

The engine control unit self-test on the ground is carried out:

The minimum and maximum engine oil quantities are:

The minimum and maximum system voltages are:

The reduction gearbox ratio between engine and propeller is:

Following an engine failure in flight, the correct sequence of actions is:

When the lower white flap indicator light is illuminated, the flaps are in the:

VNO, the maximum structural cruising speed, is:

How many low-pressure fuel pumps supply each engine?

The maximum take-off RPM and its time limit are:

VYSE, the best rate-of-climb speed with one engine inoperative, is:

The usable fuel in each optional auxiliary tank is approximately:

The external power socket accepts:

The red radial line at the low-speed end of the ASI represents:

The maximum zero fuel mass of the standard aircraft is:

An engine should be shut down using:

The maximum flaps extended speed with APPROACH flap is:

The failed engine is identified by:

The variable elevator stop limits elevator up-travel when both engines are above approximately:

The overall length of the aircraft is:

VMCA, the minimum control speed airborne with flaps UP, is:

The wheel base of the landing gear is:

The maximum operating altitude is:

Fuel information shown on the fuel calculation page:

In a strong crosswind, steering during the take-off roll may be augmented using:

Inadvertent gear retraction on the ground is prevented by:

The positive manoeuvring load factor with flaps UP is:

Before take-off, the fuel pumps should be:

The caution CHECK GEAR indicates:

If one engine is inoperative, its fuel selector must be placed:

If the oil pressure has not risen into the green range shortly after starting, you should:

The engines are shut down using:

The maximum permitted fuel quantity difference between the left and right main tanks is:

Before moving a fuel selector between ON and CROSSFEED you must ensure that:

The wing span of the DA-42 NG is:

A loss of gearbox oil pressure will drive the propeller:

The white arc on the ASI covers:

The maximum speed at which the landing gear may be extended (VLO extension) is:

Fuel burn during a long flight will:

The fuel tanks are located:

The warning L/R OIL PRES indicates that oil pressure has fallen below:

The landing gear is:

The rating of each alternator is:

The permitted negative load factor at VNE is:

Three green lights beside the gear selector indicate:

The rudder area is:

Emergency extension of the landing gear is achieved by:

If a take-off is inadvertently commenced with the canopy in the cooling-gap position, you should:

Increasing the oil pressure into the propeller hub causes the blade pitch to:

Cabin heating is supplied from:

The maximum flaps extended speed with LANDING flap is: