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a push rod and electrical contacts. Holes in the mounting flange
allow oil to enter from the diaphragm chamber. At and above the
switch setting of 15 ±0.40 PSI, oil pressure is sufficient to move
diaphragm and push rod arrangement holding the electrical contacts
of the switch open. When oil pressure drops, the switch closes.
Power from essential 28V DC bus comes through WARN LTS PWR
#14 and WARN LTS PWR #15 circuit breaker to right and left oil
pressure warning switches, respectively. Both circuit breakers are
located on the pilot’s circuit breaker panel. When oil pressure falls
below 15 PSI and the switch closes, a circuit will then exist to EICAS
to provide a L or R OIL PRESS LOW readout from the Essential 28V
DC bus. On airplanes having SPZ-8000, a circuit will also exist to
standby warning lights panel L OIL PRESS or R OIL PRESS light, if
OPERATING MANUAL
2A-77-00 PRODUCTION AIRCRAFT SYSTEMS
Page 6
May 31/01
Revision 4
standby warning lights panel switch is in MAN or AUTO mode and
EICAS is not operational.
NOTE:
For Flight Data Recorder System (FDRS), airplanes
1183 and Subsequent, a signal path branches from
right and left oil pressure warning switches. This signal
controls the on an off power to FDRS.
(4) Engine Oil Filter Warning:
An engine oil filter Differential Pressure Indicator (DPI) assembly
installed at the rear face of the engine oil tank contains two separate
indicator assemblies, a sensing switch assembly and a filter
maintenance indicator (pop-out indicator) assembly. If there is a
blockage in the engine oil filter, the switch assembly sends an
electrical signal to the EICAS, providing L OIL FILT BPASS and R
OIL FILT BPASS warning displays.
If the oil filter becomes blocked, pressure of the high pressure oil
(from upstream side of the engine oil filter) will increase and
pressure of the low pressure oil (from the oil filters on the
downstream side) will decrease. This causes a piston/magnet in the
assembly to compress its spring and move away from an actuating
lever which operates a microswitch completing a circuit to the
EICAS. When pressure drop across filter is more than 30 ±4.5 PSI,
the actuating lever is free to operate the microswitch. The assembly
has a thermal lockout leaf which ensures that the sensing switch
does not operate below 29°C.
G. Standby Engine Instruments (Digital) Indication System:
Engine pressure ratio, LP tachometer, HP tachometer, fuel flow and turbine
gas temperature indications for the left and right engine are displayed on
the standby engine instruments indicator located on the pilot’s instrument
panel. Signals from each indication system are transmitted to a signal
conditioner where they are converted to a digital readout for display on the
standby engine instruments indicator. The instrument digital display
brightness is controlled by STBY INSTR control knob on the copilot’s
cockpit lighting control panel. Clockwise rotation of knob increases light
intensity and counterclockwise rotation decreases intensity.
Power for operation is derived from Emergency 28V DC bus through the R
STBY ENG INSTR and L STBY ENG INSTR circuit breakers, both located
on copilot’s circuit breaker panel.
Signals from each indication system (EPR, LP tach, HP tach, fuel flow and
TGT) are transmitted to the standby engine instrument signal conditioner to
provide a digital display on the standby engine instruments indicator when
OPERATING MANUAL
PRODUCTION AIRCRAFT SYSTEMS 2A-77-00
Page 7
May 31/01
Revision 4
the indicator switch is placed in MAN or AUTO mode when the EICAS is
not operational.
NOTE:
The digital readouts on the standby engine
instruments indicator are tested by operation of WARN
LT-TEST switch on pilot’s or copilot’s lighting control
panel. When this switch is depressed, left and right
digital readouts of 1888 and decimals are displayed for
EPR, LP tach, HP tach and TGT and an 8888 readout
is displayed for fuel flow.
3. Controls and Indications:
A. Circuit Breakers (CBs):
The Engine Indication system is protected by the following CBs:
Circuit Breaker Name: CB Panel: Location: Power Source:
ENG VIB MONITOR CP B-8 L MAIN AC Bus
L ENG OIL PRESS CP A-12 ESS AC Bus
R ENG OIL PRESS CP B-12 ESS AC Bus
L STBY ENG INSTR CP A-11 AFT E-BAT Bus
R STBY ENG INSTR CP B-11 R MAIN DC Bus
WARN LTS PWR #14 P I-4 or I-5 (1) ESS DC Bus
WARN LTS PWR #15 P I-5 or J-5 (1) ESS DC Bus
NOTE(S):
(1) Depending on effectivity.
B. Crew Alerting System (CAS) Messages:
　
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