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Pressurization is achieved by the design of an airtight fuselage engineered to be pressurized, a source of compressed air and an environmental control system (ECS). The most common source of compressed air for pressurization is bleed air extracted from the compressor stage of a gas turbine or turboprop propulsion engine, usually the second or third last compressor ring. By the time the cold outside air has reached this part of the compressor it has been adiabatically heated to around 200 °C (392 °F) and is at a very high pressure. It is then expanded and cooled to a suitable temperature by passing it through a heat exchanger and air cycle machine ('the packs system'). There is no need to further heat or refrigerate the air. Typically, compressed air is bled from at least two propulsion engines each system being fully redundant. Compressed air is also obtained from the Auxiliary Power Unit (APU), if fitted, in the event of an emergency and for cabin air supply on the ground before the main engines are started. Most modern commercial aircraft today have a fully redundant, duplicated electronic controller for maintaining pressurization along with a manual back-up system.

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Normal commercial flights have a cabin pressure equal to 7,000 ft ASL. That's just enough to prevent passengers from getting altitude sickness, and the lower the cabin pressure the less stress on airframe. Just trivia for what it's worth.

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