时间：2011-04-18 00:52来源：蓝天飞行翻译 作者：航空 点击：次
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1. En Route/Arrivals. Advise pilots to remain set on 31.00 inches until reaching the final approach segment. 2. Departures. Advise pilots to set 31.00 inch-es prior to reaching any mandatory/crossing altitude or 1,500 feet, whichever is lower. c. The altimeter error caused by the high pressure will be in the opposite direction to the error caused by the cold temperature. 7.2.5. Low Barometric Pressure When abnormally low barometric pressure condi-tions occur (below 28.00), flight operations by aircraft unable to set the actual altimeter setting are not recommended. NOTE. The true altitude of the aircraft is lower than the indicated altitude if the pilot is unable to set the actual altimeter setting. 7.2.4 Altimeter Setting Procedures Section 3. Wake Turbulence 7.3.1. General a.Every aircraft generates a wake while in flight. Initially, when pilots encountered this wake in flight, the disturbance was attributed to “prop wash.” It is known, however, that this disturbance is caused by a pair of counter.rotating vortices trailing from the wing tips. The vortices from larger aircraft pose problems to encountering aircraft. For instance, the wake of these aircraft can impose rolling moments exceeding the roll-control authority of the encounter-ing aircraft. Further, turbulence generated within the vortices can damage aircraft components and equipment if encountered at close range. The pilot must learn to envision the location of the vortex wake generated by larger (transport category) aircraft and adjust the flight path accordingly. b.During ground operations and during takeoff, jet engine blast (thrust stream turbulence) can cause damage and upsets if encountered at close range. Exhaust velocity versus distance studies at various thrust levels have shown a need for light aircraft to maintain an adequate separation behind large turbojet aircraft. Pilots of larger aircraft should be particularly careful to consider the effects of their “jet blast” on other aircraft, vehicles, and maintenance equipment during ground operations. 7.3.2. Vortex Generation Lift is generated by the creation of a pressure differential over the wing surface. The lowest pressure occurs over the upper wing surface and the highest pressure under the wing. This pressure differential triggers the roll up of the airflow aft of the wing resulting in swirling air masses trailing downstream of the wing tips. After the roll up is completed, the wake consists of two counter.rotating cylindrical vortices. (See FIG 7.3.1.) Most of the energy is within a few feet of the center of each vortex, but pilots should avoid a region within about 100 feet of the vortex core. FIG 7.3.1 Wake Vortex Generation 7.3.3. Vortex Strength a.The strength of the vortex is governed by the weight, speed, and shape of the wing of the generating aircraft. The vortex characteristics of any given aircraft can also be changed by extension of flaps or other wing configuring devices as well as by change in speed. However, as the basic factor is weight, the vortex strength increases proportionately. Peak vortex tangential speeds exceeding 300 feet per second have been recorded. The greatest vortex strength occurs when the generating aircraft is HEAVY, CLEAN, and SLOW. b.Induced Roll 1. In rare instances a wake encounter could cause inflight structural damage of catastrophic proportions. However, the usual hazard is associated with induced rolling moments which can exceed the roll-control authority of the encountering aircraft. In flight experiments, aircraft have been intentionally flown directly up trailing vortex cores of larger aircraft. It was shown that the capability of an aircraft to counteract the roll imposed by the wake vortex primarily depends on the wingspan and counter-control responsiveness of the encountering aircraft. Wake Turbulence 7.3.1 2. Counter control is usually effective and induced roll minimal in cases where the wingspan and ailerons of the encountering aircraft extend beyond the rotational flow field of the vortex. It is more difficult for aircraft with short wingspan (relative to the generating aircraft) to counter the imposed roll induced by vortex flow. Pilots of short span aircraft, even of the high performance type, must be especially alert to vortex encounters. (See FIG 7.3.2.)FIG 7.3.2 Wake Encounter Counter Control 3. The wake of larger aircraft requires the respect of all pilots. 7.3.4. Vortex Behavior a. Trailing vortices have certain behavioral characteristics which can help a pilot visualize the wake location and thereby take avoidance precau-tions. 1.Vortices are generated from the moment aircraft leave the ground, since trailing vortices are a by-product of wing lift. Prior to takeoff or touchdown pilots should note the rotation or touchdown point of the preceding aircraft. (See FIG 7.3.4.)2.The vortex circulation is outward, upward and around the wing tips when viewed from either ahead or behind the aircraft. Tests with large aircraft have shown that the vortices remain spaced a bit less than a wingspan apart, drifting with the wind, at altitudes greater than a wingspan from the ground. In view of this, if persistent vortex turbulence is encountered, a slight change of altitude and lateral position (preferably upwind) will provide a flight path clear of the turbulence. 3.Flight tests have shown that the vortices from larger (transport category) aircraft sink at a rate of several hundred feet per minute, slowing their descent and diminishing in strength with time and distance behind the generating aircraft. Atmospheric turbulence hastens breakup. Pilots should fly at or above the preceding aircraft’s flight path, altering course as necessary to avoid the area behind and below the generating aircraft. (See FIG 7.3.3.) However, vertical separation of 1,000 feet may be considered safe. 4.When the vortices of larger aircraft sink close to the ground (within 100 to 200 feet), they tend to move laterally over the ground at a speed of 2 or 3 knots. (See FIG 7.3.5.)FIG 7.3.3 Wake Ends/Wake Begins Wake Ends Wake Begins Wake Turbulence |
