The purpose of the blow-in-doors at the air inlets is to:

In order to enable a fire to be controlled as quickly as possible, the fire detectors are located in the highest risk compartments. Theses compartments are : 1. the main landing gear wheel wells 2. the fuel tanks 3. the oil tanks 4. the auxiliary power unit 5. around the engines The combination regrouping all the correct statements is:

In transport aeroplanes overheat detection systems are installed in the:

The indication of the fire detection systems is performed by a:

Turbine blade stages may be classed as either "impulse" or "reaction". In an impulse blade section :

The primary purpose of the bleed valves fitted to axial flow compressors is to :

The fan in a high by- pass ratio turbo-jet engine produces:

At constant fuel flow, if engine compressor air is bled off for engine anti-icing or a similar system, the turbine temperature:

A reverse thrust door warning light on the flight deck instrument panel illuminates when:

In a single spool gas turbine engine, the compressor rpm is :

When the combustion gases pass through a turbine the :

The primary reason for a limitation being imposed on the temperature of gas flow is to :

In a gas turbine engine, compressor blades, which are not rigidly fixed in position when the engine is stationary, take up a rigid position when the engine is running due to :

If air is tapped from a gas turbine HP compressor, the effect on the engine pressure ratio (EPR) and the exhaust gas temperature (EGT) is that :

A "fan" stage of a ducted-fan turbine engine is driven by:

In a free turbine engine:

Continuous loop fire detector systems operate on the principle that an increase in temperature produces :

On an aircraft provided with resistance and capacitance variation type fire detection loops, a fire alarm is initiated by a temperature increase detected:

On a multi-engined aircraft a fire detection system includes :

In a gas turbine engine, the maximum gas temperature is attained:

Concerning the centrifugal compressor, the compressor diffuser is a device in which the:

When a continuous element of a fire detection system is heated: 1. its resistance decreases. 2. its resistance increases. 3. the leakage current increases. 4. the leakage current decreases. The combination regrouping all the correct statements is :

In a compressor stage of a jet engine, the sequence is:

The accessory units driven by the accessory gearbox of a turbo-jet engine are the : 1. tacho-generator N1 2. tacho-generator N2 3. thrust reverser pneumatic motors 4. AC generator and its Constant Speed Unit (CSD) 5. oil pumps 6. hydraulic pumps 7. high pressure fuel pumps The combination regrouping all the correct statements is :

The wing of an aircraft in flight, powered by engines located under the wing, is subjected to a bending moment which causes its leading edge, from the wing root to the wing tip, to operate in:

In the axial flow compressor of a turbo- jet engine, the flow duct is tapered. Its shape is calculated so as to:

In the stator of a turbine, the speed V and static pressure Ps vary as follows:

A fault protection circuit in a fire detection system will:

In a fire detection system with single-loop continuous components (with no fault protection), if the line is accidently grounded:

When a wire type fire system is tested:

In flight the wing of an aircraft containing fuel is subjected to vertical loads that produce a bending moment which is:

The Maximum Zero Fuel Mass: 1 Is a limitation set by regulation. 2 Is designed for a maximum load factor. 3 Is due to the maximum bending moment at wing root. 4 Requires to empty external tanks first. 5 Requires to empty internal tanks first. The correct combination of true statements is :

The compressor surge effect during acceleration is prevented by the :

For a fan jet engine, the by-pass ratio is the:

A gaseous sensor/responder tube fire sensor is tested by

A stage in an axial compressor:

When a bimetallic strip is used as a switch in a fire detection loop, a fire alarm is triggered after a delay. The purpose of this delay is to:

The disadvantages of axial flow compressors compared to centrifugal flow compressors are : 1 - expensive to manufacture 2 - limited airflow 3 - greater vulnerability to foreign object damage 4 - limited compression ratio The combination of correct answers is :

On a non-stressed skin type wing, the wing structure elements which take up the vertical bending moments Mx are:

An impulse turbine is a turbine in which the expansion takes place: