Part66EASA Module11A.4.2 Air Conditioning (2of2)

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When carrying out a ground pressure test, you should use the aircraft engines because you can test the
whole.
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1 point

Option A. the aircraft engines because you can test the whole system.

Option B. ground trolley and clean air.

Option C. a G.P.U. and A.P.U. combination.

The ventilation air in the aircraft cabin must have a minimum humidity of.

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Option A. 60 percent.

Option B. 30 percent.

Option C. 20 percent.

In a Boot-Strap Air Conditioning supply system the source of compressed air is from.
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Option A. ram air at the wing leading edge.

Option B. gas turbine intake ram air.

Option C. gas turbine compressor bleed air.

The temperature within the cabin of the aircraft is normally maintained at.
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Option A. 12ºC to 18ºC.

Option B. 18ºC to 24ºC.

Option C. 20ºC to 24ºC.

In a 'bootstrap' cooling system the supply of air is first passes across an expansion turbine, then directly
to the.
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Option A. heat exchanger.

Option B. passed across an expansion turbine, then compressed and passed through a heat exchanger.

Option C. compressed then passed through a heat exchanger and across an expansion turbine.

The humidity within a passenger cabin should.
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Option A. not be less than 60%.

Option B. not be greater than 40%.

Option C. be between 30% and 70%.

One of the principles of cooling employed in an air cycle system is.
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Option A. by compression of ambient air across a turbine.

Option B. conversion of heat energy to mechanical energy in the C.A.U.

Option C. by surface heat exchange in the C.A.U.

Before filling a vapour cycle cooling system.
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Option A. flush the system with a solvent.

Option B. apply suction to remove air and moisture.

Option C. pre-heat the system to 100°F.

The rate of flow of air from the punkha louvers should not be less than.
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Option A. 300 ft/min.

Option B. 25 ft/min.

Option C. 200 ft/min.

Correct Answer is. 25 ft/min.

An aircraft cabin is air conditioned and pressurized in order to.
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Option A. maintain human efficiency and comfort during flights at high altitudes.

Option B. ensure that the air density within the cabin is maintained at a lower figure than outside the cabin in order to prevent moisture precipitation during rapid decompression.

Option C. ensure that the pressure within the fuselage is always less than the ambient pressure, thus increasing the fatigue life of the fuselage.

In the case of a vapour cycle cooling, system heat is removed from the charge air by.
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Option A. reducing the pressure of a vapour.

Option B. changing a vapour into a liquid.

Option C. changing a liquid into a vapour.

Subsequent to passing through the primary heat exchanger, the supply air in a turbo-fan cold air system
flows to the.
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Option A. inter cooler or secondary heat exchanger.

Option B. turbine.

Option C. fan.

The heat exchanger in a turbo-fan system is cooled by.
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Option A. engine bleed air or blower air.

Option B. air bled from the main cabin supply duct.

Option C. ambient ram air.

The effective temperature of a cabin is given by.
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Option A. temperature, humidity, thermal inertia and heat load.

Option B. temperature only.

Option C. temperature and humidity.

When dissipating heat in a vapour cycle system.
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Option A. vapour converts to a liquid.

Option B. the liquid sublimates.

Option C. liquid converts to a vapour.

International markings for air conditioning pipelines are.
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Option A. triangles.

Option B. dots.

Option C. rectangles.

A cabin humidifier is operated.
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Option A. at high altitudes.

Option B. at low altitudes.

Option C. on the ground.

In an air conditioning system, heat is added to the air by.
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Option A. restricting duct outlets.

Option B. restricting compressor inlet.

Option C. restricting compressor outlet.

A turbo fan CAU used for air cycle cooling will.
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Option A. not affect the charge air pressure.

Option B. increase the pressure but decrease the temperature.

Option C. decrease pressure and temperature of the charge air.

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