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accessory gearbox torque sensing port. This signal 1).
provides the FADEC system with the power turbine
output torque. The FADEC system will reduce fuel flow ( 1 ) Impending Bypass i n d i c a t o r . The
to prevent a shaft torque limit exceedance. The power impending bypass indicator is a red button that extends
turbine output torque threshold limit is 131%. The when an impending bypass condition exists. Notify
torque override limit is 167%. This feature is not maintenance personnel if indicator extends.
available in the manual mode. (2) Filter Element. The filter element is a 10
micron, disposable filter element.
(12) Surge Detection/Avoidance. The FADEC
system detects engine surge events. Without pilot (3) Filter Bypass Valve. The filter bypass valve
action, the FADEC system will schedule fuel flow for opens when the filter element is clogged.
zero acceleration in order to quickly recover from the
surge. The system will attempt to avoid another surge d. Fuel Pressure Differential Switch. The switch is
by reducing the maximum acceleration schedule in the located on the bottom of the power and accessory
NG range where the surge occurred. The ECU engine gearbox. It activates the FUEL/FILTER BYP caution
monitoring function will record the number of surges in message when the fuel filter is clogged.
non-volatile memory and displays them on the FADEC
e. Fuel Injector. The fuel injector is mounted in the
monitor page.
aft end of the outer combustion case. The fuel injector
The maximum acceleration schedule is reset to the sprays metered fuel into the combustion section of the
original schedule when FADEC system power is cycled engine where it is mixed with air for combustion.
or when the AUTO/MAN select switch is cycled. This
feature is not available in manual mode. 2-25. OIL SUPPLY SYSTEM.
(13) Flameout Detection/Auto-Relight. The
FADEC system incorporates an automatic relight a. General. The engine oil lubrication system is a
feature that detects an engine flameout and activates circulating dry sump type with an external reservoir and
the automatic relight circuitry. The ENGINE OUT heat exchanger. The major components of the engine
warning will be annunciated to the pilot via the CDS. oil lubrication system are the engine oil filter assembly,
Without pilot action, the FADEC will initiate a restart an in-line oil filter assembly, pressure/scavenge oil
sequence. This includes scheduling the appropriate pump, engine oil tank, engine oil cooler, oil cooler
restart fuel flow, activating the ignition system and bypass valve, and two electromagnetic chip detector
engaging the starter if required. Relight will be detected drain plugs.
by the FADEC system and TGT will be limited. The b. Filter Assemblies.
engine should smoothly accelerate back to the
commanded operating condition. This feature is not (1) The internal engine oil filter assembly
available in the manual mode. consists of an oil filter element, impending oil bypass
2-30
TM 1-1520-248-10
indicator (2, fig. 2-11), filter bypass valve, and pressure BYPASS switch in the AUTO position has no effect on
regulating valve. The assembly is located on the upper, engine oil flow.
left side of the power and accessories gearbox and is
accessible from the top of the engine. e. Chip Detectors. Two electromagnetic chip
detectors are located in the engine oil system. The
(2) The in-line oil filter assembly is located aft of lower chip detector is located at the bottom of the
the engine aft firewall on the left side. The in-line oil accessory gearbox; the upper chip detector is adjacent
filter assembly consists of a filter element, oil bypass to the oil tank return line.
indicator, and bypass valve. When the filter element
becomes clogged, it will give a warning by extending
the oil bypass (red) indicator. The indicator extends 2-26. IGNITION.
when a set differential pressure across the filter is
exceeded. When in the reset position, the indicator will The engine ignition system has two basic components,
be hidden from view. If the indicator is extended, it can a low voltage, capacitor discharge ignition exciter
be reset by pressing in. An extended indicator is not assembly and a spark igniter lead assembly with a
sufficient reason to ground the helicopter. shunted surface gap igniter plug. The ignition exciter is
located on the lower left bottom side of the power and
c. Oil Tank. The engine oil tank is located aft of accessories gearbox. The igniter plug (10, fig. 2-11) is
the engine oil cooler, above the aft fuselage. A sight located on the lower right rear area of the combustion
glass is located on the left side of the tank. Normal oil chamber.
level is indicated when oil fills the sight glass and the
　
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