A lighted heliport may be identified by?
|
|
The color combination of green, yellow, and white flashed by beacons indicates a lighted heliport.
|
| |
|
The primary purpose of the tail rotor system is to? |
|
Counteract the torque effect of the main rotor. The Auxiliary or tail rotor is the anti-torque rotor that produces thrust in the direction opposite to the torque reaction developed by the main rotor.
|
| |
|
During a hover, a helicopter tends to drift in the direction of the tail rotor thrust. This movement is called. |
|
This movement is generally referred to as translating tendency or drift. The entire helicopter has a tendency to move in the direction of tail rotor thrust when hovering.
|
| |
|
The upward bending of the rotor blades resulting from the combined forces of lift and centrifugal force is known as. |
|
The upward bending of the rotor blades caused by the combined forces of lift and centrifugal force is called coning.
|
| |
In a helicopter, the center of gravity(CG) range is usually located.
|
|
The
exact location and length of the of the CG range is specific for each
helicopter but it usually extends a short distance fore and aft of the
main rotor mast.
|
| |
|
The lift differential that exists between the advancing main rotor blade and the retreating main rotor blade is known as |
|
Dissymmetry
of lift is created by horizontal flight or by wind during hovering
flight. It is the difference in lift(unequal lift) across the rotor disc
resulting from the difference in the velocity of air over the advancing
blade half of the disc area and retreating blade half of the disc
area.
|
| |
|
Ground resonance is most likely to develop when |
|
A series of shocks causes the rotor system to become unbalanced. Ground
resonance may develop when a series of shocks causes the rotor head to
become unbalanced. When one landing gear of the helicopter strikes the
surface first, a shock is transmitted through the fuselage to the rotor.
When one of the other landing gears strikes, the unbalance can be
aggravated and become even greater. This establishes a resonance, which
sets up a pendulum-like oscillation of the fuselage--a severe wobbling
or shaking.
|
| |
|
The proper action to initiate a quick stop is. |
|
Lower the collective, apply aft cyclic. Rapid
deceleration or quick stop is initiated by applying aft cyclic to
reduce forward speed and lowering the collective pitch to counteract
climbing.
|
| |
|
Takeoff from a slope in a helicopter with skid-type landing gear is normally accomplished by |
|
Bringing the helicopter to a level attitude before completely leaving ground. For
slope takeoff, first obtain takeoff RPM and move the cyclic stick so
that the rotor rotation is parallel to the true horizon rather than
slope apply up-collective pitch and apply pedal to maintain heading. As
the downslope skid rises and the helicopter approaches a level altitude,
move the cyclic stick back to the neutral position and take the
helicopter straight up to a hover before moving away from the slope. The
tail should not be turned upslope because of the danger of the tail
rotor striking the surface.
|
| |
|
The proper procedure for a slope landing in a helicopter with skid-type landing gear is. |
|
When parallel to the slope, slowly lower the upslope skid to the ground prior to lowering the downslope skid.The
helicopter should be landed on a cross-slope rather than on either an
upslope or downslope. As the upslope skid touches the ground, the pilot
should apply the cyclic stick in the direction of the slope. This will
hold the skid against the slope while the downslope skid continues to be
let down with the collective pitch.
|
| |
|
Density altitude refers to a theoretical air density that exists under standard conditions at a given altitude. Standard conditions at sea level are. |
|
Standard conditions at sea level are: Atmospheric pressure:29.92 in of Hg(inches of mercury); Temperature: 59F.(15C) |
| |
|
A helicopter pilot should consider using a running takeoff |
|
A running takeoff is used when conditions of load and/or density altitude prevent a sustained hover at normal hovering altitude. It is often referred to as a high-altitude takeoff. A running takeoff may be accomplished safely only if surface area of sufficient length and smoothness is available if no barriers exist in the flight-path to interfere with a shallow climb. |
| |
|
Foot pedals in the helicopter cockpit enable the pilot to |
|
Foot pedals in the cockpit permit the pilot to increase or decrease tail-rotor thrust, as needed, to neutralize/control torque effect. |
| |
|
If the helicopter is moving forward the advancing blade will be in the |
|
With a single main rotor rotating in a counterclockwise direction, the
advancing blade will be in the right half of the rotor disc during
forward flight. |
| |
|
The method of control by which the pitch of all main rotor blades is varied equally and simultaneously is the. |
|
The collective pitch control lever changes the pitch angle of the main rotor blades simultaneously and equally.
|
| |
|
The combination of factors that will reduce helicopter performance the most is |
|
High altitude, high temperature, and high moisture content contribute to a high density altitude condition that lessons helicopter performance. |
| |
|
The most favorable conditions for helicopter performance are the combination of |
|
The most favorable conditions for helicopter performance are the combination of a low-density altitude, light gross weight, and moderate-to-strong winds. The most adverse condidtions are the combination of a high denisty altitude, heavy gross weight, and calm or no wind. |
| |
|
During surface taxiing, the helicopter pilot should use the pedals to maintain heading and the cyclic to maintain |
|
The collective pitch controls starting, stopping, and rate of speed. Pedals are used to maintain heading and the cyclic is used to maintain ground track. |
| |
|
The thinner air of higher altitudes causes the airspeed indicator to read "too low" An indicated airspeed of 80mph at 5,000 feet is actually a true airspeed of approximately. |
|
True airspeed may be roughly computed by adding to the indicated airspeed, 2 percent of the indicated airspeed for each 1,000 feet of altitude above sea level. 88MPH
|
| |
