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The hydraulic system is also used to extend and retract landing gear, operate flaps and slats, operate the wheel brakes and steering systems. Hydraulic systems consist of engine driven pumps, fluid reservoirs, oil coolers, valves and actuators. Redundancy for safety is often provided by the use of multiple, isolated systems. [3]
In aviation, a power transfer unit (PTU) is a device that transfers hydraulic power from one of an aircraft's hydraulic systems to another in the event that the other system has failed or been turned off. The PTU is used when, for example, there is right hydraulic system pressure but no left hydraulic system pressure.
The systems evolved, replacing the mechanical linkages to the valves with electrical controls, producing the "fly-by-wire" design, [3] and more recently, optical networking systems called "fly-by-light". All these systems require three separate components, the hydraulic supply system, the valves and associated control network, and the actuators.
An oleo strut is a pneumatic air–oil hydraulic shock absorber used on the landing gear of most large aircraft and many smaller ones. [1] This design cushions the impacts of landing and damps out vertical oscillations.
hydraulic hoses, hydraulic fluid from the aircraft hydraulic system has to be supplied to engine-mounted pumps and then returned under high pressure to the aircraft. High pressure fluid is returned to the nacelle for actuating a thrust reverser. fuel tube, fuel has to get from the aircraft tanks to the engine fuel pump.
In aircraft design and aerospace engineering, a high-lift device is a component or mechanism on an aircraft's wing that increases the amount of lift produced by the wing. The device may be a fixed component, or a movable mechanism which is deployed when required. Common movable high-lift devices include wing flaps and slats.
An autobrake is a type of automatic wheel-based hydraulic brake system for advanced airplanes. [1] The autobrake is normally enabled during takeoff and landing procedures, when the aircraft's longitudinal deceleration system can be handled by the automated systems of the aircraft itself in order to keep the pilot free to perform other tasks.
The vertical fin separated from the airplane. Hydraulic components located in the aft body were also severed, leading to a rapid depletion of all four hydraulic systems. The loss of the vertical fin, coupled with the loss of all four hydraulic systems, left the airplane extremely difficult, if not impossible, to control in all three axes.