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all times. If the switch is at OFF, the aft auxiliary tanks will
not fill, the remaining four tanks will fill to maximum, the
refuel station quantity indicator is inoperative, and there
is no precheck capability.
2-4-14. Fuel Quantity Indicator and Selector
Switch.
The pressure refueling station fuel quantity indicator and
selector switch (fig. 2-4-4) are identical to those in the
cockpit. The indicator at the refueling station indicates
fuel quantity only when the REFUEL STA switch on the
cockpit FUEL CONTR panel (fig. 2-4-1) is at ON and the
PWR switch on the refueling station panel (fig. 2-4-6) is
at PWR ON. Electrical power to drive the indicator is AC
from a solid-state inverter in the cabin at sta 220. The
inverter, in turn, is powered by the DC switched battery
bus through the FUEL REFUEL circuit breaker on the No.
1 PDP.
2-4-15. FUEL CELL SHUTOFF VALVE TEST
Switches.
Seven three-position FUEL CELL SHUTOFF VALVE
TEST switches are on the refueling control panel (fig.
TM 1-1520-240-10
2-4-5
2-4-6). The switches are used to test the automatic shutoff
features in each tank and to stop refueling when the
desired fuel level is attained in each or all tanks. Six of the
seven switched are connected to fuel level control valves
in a specific tank. The seventh switch, labeled ALL TEST,
is electrically connected to the fuel level control valves in
all six tanks. Setting any of the six switches to PRI OFF
or SEC OFF raises the corresponding primary or secondary
float in the fuel level control valve. This action simulates
a high fuel level and causes the fuel shutoff valve
in that tank to close. Setting the ALL TEST switch to PRI
OFF or SEC OFF raises the corresponding float in all six
tanks and shuts off the fuel flow into all tanks simultaneously.
2-4-16. REFUEL VALVE POSN Indicating Lights.
The two amber PRESS-TO-TEST REFUEL VALVE
POSN (position) lights (fig. 2-4-6) indicates the status of
the two refueling valves in the pressure refueling system.
The valves are normally closed and prevent fuel feedback
into the aft auxiliary tanks when the aft tank pumps
are operating. While pressure refueling the valves are
opened and allow fuel flow from the refueling system into
the aft tank.
The valves are controlled by the refueling station PWR
ON switch. When the switch is ON, the valves are
opened and the indicating lights will illuminate momentarily
indicating valve transition from close to open. Conversely,
when the switch is OFF, the valves are closed
and the indicating lights will illuminate momentarily indicating
valve transition from open to close. A continuously
illuminated light, with the switch at OFF, indicates the
associated valve is opened and the fuel in the tank will
not be available.
TM 1-1520-240-10
2-4-6
Figure 2-4-6. Pressure Refueling Station
TM 1-1520-240-10
2-5-1
SECTION V. FLIGHT CONTROLS
2-5-1. Flight Control System.
The helicopter is controlled by changing the pitch of the
blades either collectively or cyclically. Pitch changes are
made by the pilot’s movement of the flight control which
include a THRUST CONT (control) lever, a cyclic control
stick, and directional pedals. The pilot’s controls are interconnected
with the copilot’s controls.
Flight control movements are transmitted through a system
of bellcranks, push-pull tubes, and actuators to a
mixing unit just aft of the cockpit, next to the forward
transmission. The control movements are mixed to give
the correct lateral cyclic and collective pitch motions to
the rotors through dual hydraulic actuators. These dual
boost actuators are under each swashplate. Each set of
dual boost actuators is normally powered by both flight
control hydraulic systems.
The helicopter is vertically controlled with the THRUST
CONT lever through application of equal pitch to all blades.
Directional control is obtained with the directional
pedals by imputting equal but opposite lateral cyclic pitch
to the blades. Lateral control is obtained by application
of equal lateral cyclic pitch to the blades with the cyclic
control stick. The helicopter is controlled longitudinally
with the cyclic stick through application of differential
collective pitch.
In addition, the helicopter has an advanced flight control
system (AFCS). AFCS provides the following features:
a. Rate damping in all axes and sideslip stability.
b. Pitch and roll attitude hold and heading hold.
c. Airspeed hold.
d. Improved control response in pitch, roll, and
yaw.
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