Rotorcraft Flying Handbook, FAA-H-8083-21
Rotorcraft Flying Handbook, FAA-H-8083-21
Rotorcraft Flying Handbook, FAA-H-8083-21
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aligned with the touchdown point, and if the rotor<br />
r.p.m. and/or airspeed is not within proper limits.<br />
From this point, complete the procedure as if it were a<br />
straight-in autorotation.<br />
POWER FAILURE IN A HOVER<br />
Power failures in a hover, also called hovering autorotations,<br />
are practiced so that you automatically make<br />
the correct response when confronted with engine<br />
stoppage or certain other emergencies while hovering.<br />
The techniques discussed in this section refer to helicopters<br />
with a counter-clockwise rotor system and an<br />
antitorque rotor.<br />
TECHNIQUE<br />
To practice hovering autorotations, establish a normal<br />
hovering altitude for the particular helicopter being<br />
used, considering load and atmospheric conditions.<br />
Keep the helicopter headed into the wind and hold<br />
maximum allowable r.p.m.<br />
To simulate a power failure, firmly roll the throttle into<br />
the spring loaded override position, if applicable. This<br />
disengages the driving force of the engine from the<br />
rotor, thus eliminating torque effect. As the throttle is<br />
closed, apply proper antitorque pedal to maintain heading.<br />
Usually, a slight amount of right cyclic control is<br />
necessary to keep the helicopter from drifting to the<br />
left, to compensate for the loss of tail rotor thrust.<br />
However, use cyclic control, as required, to ensure a<br />
vertical descent and a level attitude. Leave the collective<br />
pitch where it is on entry.<br />
Helicopters with low inertia rotor systems will begin to<br />
settle immediately. Keep a level attitude and ensure a<br />
vertical descent with cyclic control while maintaining<br />
heading with the pedals. At approximately 1 foot above<br />
the surface, apply upward collective pitch control, as<br />
necessary, to slow the descent and cushion the landing.<br />
Usually the full amount of collective pitch is required.<br />
As upward collective pitch control is applied, the throttle<br />
has to be held in the closed position to prevent the<br />
rotor from re-engaging.<br />
Helicopters with high inertia rotor systems will maintain<br />
altitude momentarily after the throttle is closed. Then, as<br />
the rotor r.p.m. decreases, the helicopter starts to settle.<br />
When the helicopter has settled to approximately 1 foot<br />
above the surface, apply upward collective pitch control<br />
while holding the throttle in the closed position to slow<br />
the descent and cushion the landing. The timing of collective<br />
pitch control application, and the rate at which it<br />
is applied, depends upon the particular helicopter being<br />
used, its gross weight, and the existing atmospheric conditions.<br />
Cyclic control is used to maintain a level attitude<br />
and to ensure a vertical descent. Maintain heading with<br />
antitorque pedals.<br />
When the weight of the helicopter is entirely on the<br />
skids, cease the application of upward collective. When<br />
the helicopter has come to a complete stop, lower the<br />
collective pitch to the full down position.<br />
The timing of the collective pitch is a most important<br />
consideration. If it is applied too soon, the remaining<br />
r.p.m. may not be sufficient to make a soft landing. On<br />
the other hand, if collective pitch control is applied too<br />
late, surface contact may be made before sufficient<br />
blade pitch is available to cushion the landing.<br />
COMMON ERRORS<br />
1. Failing to use sufficient proper antitorque pedal<br />
when power is reduced.<br />
2. Failing to stop all sideward or backward movement<br />
prior to touchdown.<br />
3. Failing to apply up-collective pitch properly,<br />
resulting in a hard touchdown.<br />
4. Failing to touch down in a level attitude.<br />
5. Not rolling the throttle completely to idle.<br />
HEIGHT/VELOCITY DIAGRAM<br />
A height/velocity (H/V) diagram, published by the<br />
manufacturer for each model of helicopter, depicts the<br />
critical combinations of airspeed and altitude should an<br />
engine failure occur. Operating at the altitudes and airspeeds<br />
shown within the crosshatched or shaded areas<br />
of the H/V diagram may not allow enough time for the<br />
critical transition from powered flight to autorotation.<br />
[Figure 11-2]<br />
An engine failure in a climb after takeoff occurring in<br />
section A of the diagram is most critical. During a<br />
climb, a helicopter is operating at higher power settings<br />
and blade angle of attack. An engine failure at this point<br />
causes a rapid rotor r.p.m. decay because the upward<br />
movement of the helicopter must be stopped, then a<br />
descent established in order to drive the rotor. Time is<br />
also needed to stabilize, then increase the r.p.m. to the<br />
normal operating range. The rate of descent must reach<br />
a value that is normal for the airspeed at the moment.<br />
Since altitude is insufficient for this sequence, you end<br />
up with decaying r.p.m., an increasing sink rate, no<br />
deceleration lift, little translational lift, and little<br />
response to the application of collective pitch to cushion<br />
the landing.<br />
It should be noted that, once a steady state autorotation<br />
has been established, the H/V diagram no longer<br />
applies. An engine failure while descending through<br />
section A of the diagram, is less critical, provided a safe<br />
landing area is available.<br />
11-4