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Pilot’s Manual
PM-132A 2-17
N2 INDICATORS
N2 is displayed for each engine as a digital readout. The display consists
of an N2 legend with digital readouts to the left and right. Refer to
the following table for N2 speeds and corresponding color display for
various conditions.
ITT INDICATORS
Interstage Turbine Temperature (ITT) is displayed for each engine as a
needle and arc with an integral digital readout for ITT. The arc is scaled
to start at 100° C. Interstage turbine temperature for each engine is
sensed by Chromel-Alumel parallel wired thermocouples positioned
between the high- and low-pressure turbine sections. The signal from
the averaging circuit of the thermocouples is carried to the DEEC and
DAU for EI display. Refer to the following table for ITT and corresponding
color display for various conditions.
% N2
WHITE
% N2
AMBER
% N2
RED
% N2
Except APR Mode 0 to 100 100.1 to 102.5 102.6 to 115*
APR Mode 0 to 101 101.1 to 102.5 102.6 to 115*
OPERATING
MODE
WHITE
°C
AMBER
°C
RED
°C
Start 0 to 941 N/A 942 to 1014
Takeoff
(no anti-ice)
(<5 minutes)
0 to 941 N/A 942 to 1014
Takeoff
(any anti-ice)
(<5 minutes)
0 to 963 N/A 942 to 1014
Takeoff or APR
(>5 minutes)
0 to 916 917 to 941 942 to 1014
APR
(<5 minutes)
0 to 963 N/A 964 to 1014
Up To MCR 0 to 900 N/A 901 to 1014
MCT (no anti-ice) 0 to 916 N/A 917 to 1014
MCT (any anti-ice) 0 to 941 N/A 942 to 1014
*Above 115% the digits are invalid.
Pilot’s Manual
2-18 PM-132A
ENGINE DIAGNOSTIC SYSTEM (EDS)
An Engine Diagnostic System (EDS) is installed to provide engine fault
recording and condition trend monitoring. The system periodically
records engine parameters and allows the crew to request that conditions
be recorded at any time. Normal use of the system entails downloading
data from the DEEC and submitting to the engine
manufacturer for timely analysis. The data may be downloaded at any
time to assist in diagnosing engine problems which may be encountered.
The EDS is intended for maintenance functions only and not for
in-flight monitoring or diagnosis by the flight crew. The system is integrated
into the DEEC of each engine.
EDS RECORD SWITCH
The EDS RECORD switch is located on the aft pedestal. The purpose of
the switch is to allow the flight crew to initiate data collection by the
EDS. When the switch is actuated, the engine parameters existing four
minutes prior to and one minute after switch actuation will be recorded
in the EDS memory.
The following CAS illuminations are specific to the engine diagnostic
system:
CAS Color Description
CHECK EDS White Indicates one of the following about the associated
(L or R) engine diagnostic system
(EDS):
• The EDS has lost power.
• The EDS built-in test equipment (BITE)
has detected a system failure.
• The EDS memory is 80% full.
• The system has detected an engine condition
which is out of acceptable parameters.
Pilot’s Manual
PM-132A 2-19
ENGINE FIRE DETECTION SYSTEM
Three heat-sensing elements connected in series are located in each engine
nacelle to detect an engine fire. One element is located around the
accessory gearbox; one is located around the engine tailcone; and another
around the engine firewall. The fire detection system is controlled
by two fire detect control boxes located in the tailcone. In the event of
an engine fire, the applicable control box will sense a resistance change
in the sensing elements and flash the master WARN lights in the
glareshield and applicable FIRE switch located within the L or R
ENGINE panel of the aft pedestal.
The FIRE red EI will flash within the arc of the ITT dial. Warning is given
if the firewall or accessory gearbox area exceeds approximately
410° F (210° C), or the engine tailcone area exceeds approximately
890° F (477° C).
Whenever an engine fire is detected a “LEFT” or “RIGHT ENGINE
FIRE” voice message will sound to both pilots’ headphones and flight
deck speakers. This voice message is continuous, but can be silenced by
depressing the mute switch located on the right thrust lever or the master
WARN light.
Electrical power for the system is 28-vdc supplied through the 1-amp L
and R FIRE DET circuit breakers located within the ENGINE group of
the pilot’s and copilot’s circuit breaker panels respectively. Fire detect
systems are powered from the respective L and R ESS buses.
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