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the engine nacelle with an adapter. During engine operation,
exhaust gases are cooled by air drawn through
the transmission area by a low pressure area created by
the eduction action of the primary nozzle. The angles of
the primary and three secondary nozzles prevents a direct
view of the hot internal engine components. This
also creates a low pressure area which causes an eduction
action by drawing cooling air through the system.
The cool air is mixed with the hot air in the three secondary
nozzles which results in cooling the exhaust
gases.
2-22
TM 1-1520-238-10
Figure 2-16. T700-GE-701/T700-GE-701C Engine (Sheet 1 of 2)
2-23
TM 1-1520-236-10
Figure 2-16 T700-GE-701/T700-GE-701C Engine (Sheet 2 of 2)
2.25 ENGINE AND ENGINE INLET ANTI-ICE
SYSTEM.
To prevent damage to engines, the engine
anti-ice system shall be activated
when the aircraft is flown in
visible moisture and the outside air
temperature (OAT) is less than +5 °C
(+41°F).
The engine anti-ice system includes the engine inlet
fairings, and the nose gearbox fairings. Engine fifth
stage bleed air is used to heat the swirl vanes, nose
splitter, and engine inlet guide vanes of each engine.
The nose gearbox fairing is an electrically heated fairing
to prevent the formation of ice on each engine nose
gearbox fairing.
2.25.1 Engine and Engine Inlet Anti-Ice Operation.
The engine anti-ice system is controlled by a
two-position ON/OFF toggle switch located on the pilot
ANTI ICE panel (fig 2-17). When the switch is placed
to the ON position, the ENG 1 ANTI ICE and ENG 2
ANTI ICE advisory lights will illuminate and remain
on during normal operation of the system. The ENG 1
ANTI ICE and ENG 2 ANTI ICE fail lights on the pilots
caution/warning panel and the ENG ANTI ICE
fail light on the CPG’s caution/warning panel will illuminate
until the nose gearbox fairing electrical heaters
reach 205 °F and the temperature sensors within the
engine inlets reach 150 °F. The time required to reach
these temperatures will vary with OAT. When the nose
gearbox fairings and the bleed air heated engine inlet
reach operating temperatures, the caution/warning
lights will extinguish. When the engine anti-ice system
is turned off, the ANTI ICE panel advisory lights will
extinguish and the caution/warning ENG ANTI ICE
fail lights will illuminate and remain on until the engine
inlet temperature sensors cool below 150 °F. The
amount of time required for sensors to cool is dependent
on OAT and the length of time the engine anti-ice
system has been operating. The ENG ANTI ICE fail
lights may remain illuminated for several minutes after
the switch is placed in the OFF position. When the
switch is OFF, the advisory lights on the pilot ANTI
ICE panel indicate when the engine bleed-air valves
are open. These lights will illuminate when engine
speed is below 91% NG (bleed valve open) and will extinguish
when engine is above 91% NG (bleed valve
closed). When the switch is ON, the advisory lights will
2-24 Change 2
TM 1-1520-236-10
remain continuously illuminated unless the nose gearbox
fairings overheat +121°C (250 °F) or under heat 96
°C (205 °F) or if the engine inlet section receives antiice
air at less than 150 °F. If any of these three conditions
occur, the advisory lights extinguish and the ENG
ANTI-ICE fail lights illuminate.
Figure 2-17. Pilot/Engine Anti-Ice Panel
2.26 ENGINE FUEL CONTROL SYSTEM.
The engine has a conventional fuel control system:
PWR lever position and the degree of collective pitch
basically establish the power output demands placed
on the engines. Engine power is trimmed automatically
through interaction of the engine HMU and the ECU
701 or DECU 701. The ECU/DECU of each engine exchanges
torque signals with the opposite engine to
achieve automatic load-sharing between engines.
2.26.1 Fuel Boost Pump. A low-pressure suction fuel
boost pump is installed on the front face of the engine
accessory gearbox. It ensures that the airframe fuel
supply system is under negative pressure, thus reducing
the danger of fire in case of fuel system damage. If
the FUEL PSI ENG 1 or FUEL PSI ENG 2 segment
on the pilot caution/warning panel illuminates at idle
speed and above, it could indicate a leak or restriction
in the helicopter fuel system or a failed engine boost
pump.
2.26.2 Fuel Filter. A fuel filter is located between the
fuel boost pump and the high-pressure pump in the
HMU. If this filter becomes clogged and impedes the
　
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