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A pack valve on an air conditioning system incorporates a venturi to

measure the flow rate of the bleed air.

Maintenance procedures concerning a bleed air supply system, supplying air for the air conditioning system and cabin pressurisation, are found in which………….of the maintenance manual.

Chapter 36

The standard bayonet connector for ground air supply (low pressure supply) to an air conditioning system is

8 inches (200 mm) diameter.

During servicing of a vapour cycle cooling system, it is usual to

apply vacuum to remove air and moisture.

After passing through the primary heat exchanger of an air cycle system, the supply air flows to the

compressor

In pressurized aircraft which uses engine compressor bleed air as the cabin air supply, air conditioning is achieved by

extracting heat from the bleed air.

In the vapour cycle cooling, heat is removed from the charge air by

changing a liquid into a vapour.

The expansion valve in a vapour cycle cooling system is to

reduce the pressure of the refrigerant.

The turbine of an air cycle machine drives a compressor

where the charge air temperature increases.

In a vapour cycle cooling system, a variable expansion valve is controlled by the

temperature at the evaporator.

In an air cycle cooling system, the charge air is first

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

During the operation of a vapour cycle cooling system, water will condense from the air at the

evaporator

During operation of a vapour cycle cooling system, the pilot notices that the compressor is operating intermittently, switching off and on for several minutes at a time

This is normal.

The receiver/dryer in a vapour cycle cooling system removes moisture from

the refrigerant only.

An aircraft has a maximum differential pressure of 9.0 PSI at cruising altitude. If the ambient air pressure is 3.0 PSI, the pressure inside the cabin at cruising altitude must not exceed

12.0 PSI.

The differential capsule in a pneumatic cabin pressure controller is to control the

cabin differential pressure.

To avoid discomfort for the aeroplane passengers, the rate of change of cabin pressure should be as

low as possible when the aeroplane in descending.

The OFF SCHEDULE DESCENT light illuminates. This means the aircraft is

descending before it has reached cruise altitude.

During a cabin pressurisation system ground test, you should

operate the flight controls, to test the cable seals.

A pressurised aeroplane, during a normal climb from sea level, the

atmospheric pressure decreases more quickly than the cabin pressure.

If the pilot selects 8,000 feet on the cabin pressure controller prior to take-off, and provided maximum cabin pressure differential is not exceeded

8,000 feet cabin pressure will be maintained at aircraft altitudes above 8,000 feet

In a pneumatic cabin pressure controller, vacuum air is provided to operate the outflow valve,

from the aircraft’s vacuum system.

When a pressurised aircraft lands, at touch-down

the outflow valve will be partially closed.

If the cabin altitude increases above the permitted maximum

a warning horn operates in the cockpit.

If a transport category aircraft is fitted with a ‘ditching control’, the activation of this system will

close the pressurisation system outflow valves, and close all other valves to prevent water ingress.

Cabin altitude is protected from exceeding an altitude of 10 000 ft. by

an altitude sensor and flight deck warning system.

The cabin altitude warning is usually an

audible horn, which can be muted.

Outflow valves operated

electrically and pneumatically.

In the airconditioning pack the air from pneumatic system is cooled to temperature

between 2 to 60 C°.

The actual height above sea level at which on aircraft is flying is called

aircraft altitude.

In pressurization system the mode that is initiated at lift-off is

climb mode.

Cabin environmental control system regulates the

air temperature and movement and air pressure and humidity.

A refrigerant is used in

Vapour cycle.

A water separator is located

downstream of turbine

In the flightdeck of a pressurised aircraft, there is a gauge that shows

cabin differential pressure

In an air conditioning system, before distribution, the air goes through the

TCV

Cabin altitude in pressurized flight is the

altitude corresponding to cabin pressure irrespective of the altitude for the aircraft.

the rising runway appears

At 200 ft

The ACM secondary heat exchanger is located

between the compressor and the turbine.

The temperature of the refrigerant in the evaporator will

drop

Type and quantity of emergency equipment to be carried is specified in

national aviation regulation and EU –OPS document.

The number of megaphones required for aircraft the has more than 100 passengers is

The valve that senses the fuel level in the tank is

float valve

In a potable water system a full water tank is indicated by

full tank indicated light.

Fly-by-wire control system allow aircraft computers to perform tasks

without pilot input

Uncontrolled leakage is air that escapes through or around the

cabin doors and windows.

Conditioned air is

temperature and pressure adjusted

M11c1

مقطع من الاغاني عراقيه قصيره · 30 frågor · 4 mån sedan

M11c1