Engine Blade Out Test.


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EASA : Module17 Propeller Question - Answer

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EASA : Module17 Propeller Question - Answer On which type of turbo-propeller would you expect to find a parking brake a) compounded twin spool b) free turbine c) direct coupled twin spool Ans:b * Propeller blade angle a) increases from root to tip b) decreases from root to tip c) is constant along the blade length Ans:b * The purpose of the pitch change cams is to a) convert linear motion to rotary motion. b) convert rotary motion to linear motion. c) prevent windmilling Ans:a * What does the torque meter reading indicate in a gas turbine engine? a) Torque reaction at the reduction gear b)  Engine torque c) The ratio between engine thrust and engine torque Ans:a * The gear type pump in a C.S.U. or P.C.U a) lubricates the entire propeller system b)  boosts engine oil system pressure c) assist the governor valve to move Ans:b * The gear segments on the blade roots of a hydromatic propeller mesh with the a) stationary cam b)  torque tubes and eye b...
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Adverse yaw!!! Roll causes Yaw and Yaw causes Roll...

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Do you know what adverse yaw is and how to solve it? To understand what adverse yaw is, we need to first explain the axes of motion for an  airplane. An aircraft in flight can rotate around three different axes, as illustrated below. Aircraft control surfaces However, the effect of one control surface is not always limited to just pitch, roll, or yaw  alone. When the deflection of one control surface affects more than one of these  orientations, we say that the orientations are coupled. The most important of these  coupled interactions is adverse yaw. To better understand the concept, let's study a  picture of what happens when the pilot deflects the ailerons to roll the aircraft. As you can see, the aircraft rolls because one aileron is deflected downward while the other is deflected upward. Lift increases on the wing with the downward-deflected aileron because the deflection effectively increases the camber of that portion of the wing. Conversely, lift decreas...
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Canted Vertical Tails - Why are the stabilizers on planes like the F-18 and F-22 slanted?

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Why are the stabilizers on planes like the F-18 and F-22 slanted? The tail configuration is usually referred to as canted vertical tails, since the vertical stabilizers are canted away from being 90° straight up and down. As illustrated in the below photo of the F-18 Hornet, this design has become increasingly common on modern military aircraft. Canted vertical stabilizers on the F-18 Other well-known examples of this trend include the F-22 Raptor, F-117 Nighthawk stealth fighter, and F-35 Joint Strike Fighter. The feature traces its roots back to the 1960s when canted tails were incorporated into the SR-71 Blackbird and its predecessors, as shown below. Canted vertical stabilizers on the SR-71 Lockheed designers included these canted tails based on early research into stealth technology. As far back as the 1940s, engineers had realized that perpendicular surfaces, like vertical tails, generated strong radar returns. By canting the tails away from 90°, the radar cross-section (RCS) of ...
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