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standby engine indicator when the indicator panel switch is placed in
MAN or AUTO mode when EICAS is not operational.
(3) Engine Fuel Low Pressure Indication:
R FUEL PRESS LOW and L FUEL PRESS LOW readouts are
provided through the EICAS to inform the aircrew of an engine fuel
low pressure condition. On airplanes having SPZ-8000, R FUEL
PRESS and L FUEL PRESS warning lights (located on the standby
warning lights panel) will also alert the aircrew to this low pressure
condition if the standby warning lights panel switch is placed in MAN
or AUTO mode when EICAS is not operational. These two warning
systems are controlled by their respective pressure switches
mounted on low the pressure fuel filter and by outputs from the fuel
boost pump logic unit. The low fuel pressure switch monitors outlet
pressure at the fuel filter. If fuel pressure falls below 15 ±0.40 PSI,
an electrical circuit is completed to the appropriate warning indicator
in the cockpit. Power for this system comes from the essential 28V
DC bus.
(4) Fuel Temperature Indication:
A fuel temperature bulb installed in the low pressure fuel outlet of the
engine oil cooler gives an indication of engine fuel temperature
through the EICAS. The temperature bulb contains a platinum
element housed in a tube which is connected to an electrical
receptacle. This receptacle then connects to the indicator circuit.
The resistance value of the bulb element changes with an increase
or decrease in fuel temperature. A proportionate change in current is
then transmitted to the EICAS with signals from the right engine fuel
temperature bulb sent to the DAU #2 and signals from the left
engine fuel temperature bulb sent to DAU #1.
F. Engine Oil Indication System:
(1) Engine Oil Temperature:
Engine oil temperature indication is displayed on the center
instrument panel on the EICAS. An oil temperature bulb is located
on the outlet side of each engine oil cooler to transmit signals to the
EICAS. The temperature bulb contains a platinum element housed
in a tube which is connected to an electrical receptacle which
connects to the indicator circuit.
The resistance value of the bulb element changes with an increase
or decrease in oil temperature. A proportional change in current is
then transmitted to the EICAS with signals from right engine oil
temperature bulb sent to DAU #2 and signals from left engine oil
temperature bulb sent to DAU #1.
(2) Engine Oil Pressure:
Oil pressure indication is displayed by the EICAS. Each engine is
equipped with an oil pressure transmitter mounted on rear of the oil
OPERATING MANUAL
PRODUCTION AIRCRAFT SYSTEMS 2A-77-00
Page 5
May 31/01
Revision 4
tank. The transmitters provide electrical signals to a dual signal
conditioner located in the left hand radio rack, top shelf. From here,
signal outputs are routed to EICAS.
The engine oil pressure transmitter consists of a twin stator
armature connected to a bellows housed in a cylindrical case.
Engine oil is admitted to the bellows chamber. Variations in the
pressure of the oil system causes the bellows to expand or contract.
This acts upon and causes movement of the armature assembly
thereby causing changes in the ratio of the voltage in the two legs of
the transmitter. The dual signal conditioner then outputs a linear DC
analog signal to the EICAS, proportional to the ratio of the voltage
from the transmitter.
Power for the signal conditioners is derived from the Essential #2
26V AC transformer bus via the R ENG OIL PRESS circuit breaker
and from the Essential #1 26V AC transformer bus via the L ENG
OIL PRESS circuit breaker. Both circuit breakers are located on the
copilot’s circuit breaker panel. The signal conditioner output is a
linear analog voltage of 0-10V DC representing 0-75 PSI into a load
of 10K ohms, with an accuracy of ±2% over the full range of 0-75
PSI. The output is routed to the EICAS DAU #2 for right engine
indication and DAU #1 for left engine indication.
(3) Engine Low Oil Pressure Warning:
R OIL PRESS LOW and L OIL PRESS LOW readouts are provided
through the EICAS to inform the aircrew of an engine oil low
pressure condition. On airplanes having SPZ-8000, R OIL PRESS
and L OIL PRESS warning lights (located on standby warning lights
panel) will also alert crew to this low pressure condition if standby
warning lights panel switch is placed in MAN or AUTO mode when
EICAS is not operational. These two warning systems are controlled
by their respective pressure switches mounted on rear of the oil
tank.
The engine low oil pressure warning switch consists of a diaphragm,
　
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