Drain
Vent Reservoir
Pump
Pressure
Regulator
Valve
Quick
Disconnects
Filter
Solenoid
Valve
Servo
Actuator,
Lateral
Cyclic
Servo
Actuator,
Fore and
Aft
Cyclic
Servo
Actuator,
Collective
Pilot
Input
Rotor
Control
Figure 5-13. A typical hydraulic system for helicopters in the light to medium range is shown here.
5-10
igation capabilities, such as VOR, ILS, and GPS
intercept and tracking, which is especially useful in
IFR conditions. The most advanced autopilots can
fly an instrument approach to a hover without any
additional pilot input once the initial functions have
been selected.
The autopilot system consists of electric actuators or
servos connected to the flight controls. The number and
location of these servos depends on the type of system
installed. A two-axis autopilot controls the helicopter
in pitch and roll; one servo controls fore and aft cyclic,
and another controls left and right cyclic. A three-axis
autopilot has an additional servo connected to the antitorque
pedals and controls the helicopter in yaw. A
four-axis system uses a fourth servo which controls the
collective. These servos move the respective flight controls
when they receive control commands from a central
computer. This computer receives data input from
the flight instruments for attitude reference and from
the navigation equipment for navigation and tracking
reference. An autopilot has a control panel in the cockpit
that allows you to select the desired functions, as
well as engage the autopilot.
For safety purposes, an automatic disengage feature is
usually included which automatically disconnects the
autopilot in heavy turbulence or when extreme flight
attitudes are reached. Even though all autopilots can be
overridden by the pilot, there is also an autopilot disengage
button located on the cyclic or collective which
allows you to completely disengage the autopilot without
removing your hands from the controls. Because
autopilot systems and installations differ from one helicopter
to another, it is very important that you refer to
the autopilot operating procedures located in the
Rotorcraft Flight Manual.
ENVIRONMENTAL SYSTEMS
Heating and cooling for the helicopter cabin can be
provided in different ways. The simplest form of cooling
is ram air cooling. Air ducts in the front or sides of
the helicopter are opened or closed by the pilot to let
ram air into the cabin. This system is limited as it
requires forward airspeed to provide airflow and also
servos, on each flight control, a pump which is usually
driven by the main rotor gearbox, and a reservoir to
store the hydraulic fluid. A switch in the cockpit can
turn the system off, although it is left on under normal
conditions. Apressure indicator in the cockpit may also
be installed to monitor the system.
When you make a control input, the servo is activated
and provides an assisting force to move the respective
flight control, thus lightening the force required by the
pilot. These boosted flight controls ease pilot workload
and fatigue. In the event of hydraulic system failure,
you are still able to control the helicopter, but the control
forces will be very heavy.
In those helicopters where the control forces are so
high that they cannot be moved without hydraulic
assistance, two or more independent hydraulic systems
may be installed. Some helicopters use hydraulic accumulators
to store pressure, which can be used for a
short period of time in an emergency if the hydraulic
pump fails. This gives you enough time to land the helicopter
with normal control
STABILITY AUGMENTATIONS SYSTEMS
Some helicopters incorporate stability augmentations
systems (SAS) to aid in stabilizing the helicopter in
flight and in a hover. The simplest of these systems is a
force trim system, which uses a magnetic clutch and
springs to hold the cyclic control in the position where
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