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left and right.
Refer to the following table for pressure ranges and corresponding color
display during normal engine operation:
FUEL FLOW INDICATOR
Fuel flow is displayed for each engine as a white digital readout on
EICAS. The display consists of a FF PPH legend with flow rates to the
left and right. The fuel flow rates are presented in Pounds-Per-Hour
(PPH). A fuel flow transmitter located in the main fuel line of each engine
supplies fuel flow signals to the DAU via a fuel flow converter. The
DAU then provides a fuel flow rate value for EICAS presentation.
N1 INDICATORS
The fan speed (N1) analog EI for each engine consists of a needle, arc,
and N1 bug with integral digital readouts for N1 and N1 setting. The N1
sensor is mounted in the engine’s rear bearing support housing and
senses low-pressure fan speed. The sensor provides signals to the
DEEC and DAU. Refer to the following table for N1 speeds and corresponding
color display.
(% N2) WHITE
PSIG
AMBER
PSIG
RED
PSIG
<80% and up to
3 minutes after
engine start
65 to 80 50 to 64
0 to 49
and
126 to 150
>80% or more
than 3 minutes
after engine start
65 to 80 50 to 64
0 to 49
and
101 to 150
WHITE
% N1
AMBER
% N1
RED
% N1
0 to 100.0 N/A 100.1 to 115*
*Above 115% the digits are invalid.
Pilot’s Manual
PM-126A 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.
Aircraft 45-002 & Subsequent not modified by SB 45-72-1:
% 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
(<5 minutes)
0 to 941 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-126A
Aircraft 45-002 & Subsequent modified by SB 45-72-1:
OPERATING
MODE
WHITE
°C
AMBER
°C
RED
°C
Start 0 to 991 N/A 992 to 1014
Takeoff
(no anti-ice)
(<5 minutes)
0 to 991 N/A 992 to 1014
Takeoff
(any anti-ice)
(<5 minutes)
0 to 991 N/A 992 to 1014
Takeoff or APR
(>5 minutes)
0 to 1013 N/A 1014
APR
(<5 minutes)
0 to 1013 N/A 1014
Up To MCR 0 to 974 N/A 975 to 1014
MCT (no anti-ice) 0 to 991 N/A 992 to 1014
MCT (any anti-ice) 0 to 991 N/A 992 to 1014
Pilot’s Manual
PM-126A 2-19
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
　
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