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The rule affected only those aircraft operating under IFR when in level flight above 3,000 ft above mean sea level, or above the appropriate transition altitude, whichever is the higher, and when below FL195 (19,500 ft above the 1013.2 hPa datum in the UK, or with the altimeter set according to the system published by the competent authority in ...
It is the setting that causes an altimeter to read the aircraft's flight level (FL). Flight levels are given in hundreds of feet (for example: FL100 = 10 000 ft). Atmospheric pressure changes over time and position. Thus, the flight level is not "straight", because it has a different altitude (elevation above the mean sea level).
Data from Jane's All the World's Aircraft 2000–2001, Jane's All the World's Aircraft 2010–2011, Apache AH-64 Boeing (McDonnell Douglas) 1976–2005
In aviation (particularly in air navigation), lowest safe altitude (LSALT) is an altitude that is at least 500 feet above any obstacle or terrain within a defined safety buffer region around a particular route that a pilot might fly. The safety buffer allows for errors in the air by including an additional area that a pilot might stray into by ...
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Typically, the transition level is the lowest flight level (according to the semi-circular or quadrantical rule) that is actually above the transition altitude, and thus actually usable as a flight level. The transition layer is the layer between the TA and the TL. It's sort of a no-mans-land where you should not be flying for long periods of time.
In the 1940s (original ICAO regulations), standard separation was 1000 feet except in specific circumstances, when it was 500 feet. [2] In 1958 the standard vertical separation of aircraft in controlled airspace was set at 1,000 feet from ground level or sea level to flight level 290, and at 2,000 feet above flight level 290. [3]
The maximum endurance condition would be obtained at the point of minimum power required since this would require the lowest fuel flow to keep the airplane in a steady, level flight. Maximum range condition would occur where the ratio of speed to power required is greatest.