Airframes & Systems

Nach 3 Sekunden wird das Trimmrad gestoppt => Muss dann nochmals drücken, dass es weiter trimmt ==> Im Airbus nur Rudder and Pitch trim

Bein den Flightcontrols, wo Hydrauliccaly betrieben werden

Artificial feel ist immer in Parallel geschaltet => Wenn es in Serie wäre, würde es direkt auf die Spring wirken ==> 2 Feder steuern das Artifical feel

REVERSIBLE => Primary flight controls in a manually operated control system = a force to the control will move the control surface and a force applied to the control surface will cause the cockpit control to move

Where there is no natural feeling, it is necessary to introduce feel to the system artificically . The Artificial feel unit should increase the cockpit control load in proportion to the control deflection, and in proportion to the speed

capable of returning small amounts of fluid back into the rank and are fitted across specific services => open when system pressure reaches a present value ==> Simple ball valve which is held against its seat by a spring

generate a small vortex which causes the free stream flow of high energy air to mix with and add kinetic energy to the boundary layer. The higher energy level delays the boundary layer separation and thus the stall

occurs while the aircraft is experiencing a load factor higher than 1 => the aircraft stall at higher speed

dangerous for aircraft designs => vor allem T-Tail = the turbulent wake of a stalled main wing blankets the horizontal stabilizer, rendering the elevators ineffective and preventing the aircraft from recovering from the sat ==> AOA is 40-60 degrees

Cp moves for the whole wing inboard

CAT 1 (RVR only)

NPA (RVR and ceiling)

NPA ( RVR + 1000m, Ceiling + 200)

250 ft

300 ft

250 ft

300 ft

300 ft

at least one crash aye => Ab 200 seats am additional crash axes => in the galley area and not visible for passengers

you must write an report to the Authority when result in significant damage to the aircraft

Auf und Abwinde => verschieden stark

a= max. power available b) pitch around 15 degrees and hold that attitude c) pitch until stick speaker when you have one

1. increases headwind = increase lift 2. enter the downdraft area => abrupt tailwind = reduce lift => extremely high sink rate

a spinning often turbulent flow of air with closed streamlines => around center and forms a vortex

the region of turbulence immediately to the rear of a solid body caused by the flow of air around the body => wirbelschleppe

describe the effect of the rotating air masses generated behind the wing tips in preference to the term Wake vortex which describes the nature of the air masses !!!!

are circular flows of air behind a wig as soon as it generates lift => behind the wings (two counter-rotating)

2 -4 wingspans behind the aeroplane and within 2 minutes 900ft below

travels laterally to the left/right at 5 kts

the vortex is more intense, because more vortices are developed in the same distance with more time available

extended flaps creates several vortices at the wing trailing edge, which lowers the intensity of the tip vortices => with flaps retracted, the zone behind the aeroplane is longer

1. heavy 2. slow 3. clean configuration

1. induced roll 2. loss of height 3. possible structural stress => more difficult for aircraft with a short wing span to counter the imposed roll induced by vortex flow

Ab 560'000 kg or more