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The AutoRelight
function is enabled when the engine is at or above Idle and the ENGINE RUN
switch is ON.
Two methods are used to detect a flameout at all engine speeds at or above Idle:
· By monitoring the rate of change of N2. The threshold for the rate of change is calculated as
a function of HP compressor pressure exit (P30) and altitude. A flameout is assumed to
have occurred if N2 decelerates at a rate greater than this threshold.
· By monitoring the difference between commanded Idle N2 and actual N2. If the difference is
greater than a preset threshold, a flameout is assumed to have occurred. This method is
suppressed for 15 seconds, following a transition from low idle to high idle.
When a flameout is detected, the EEC will energize both igniters and schedule fuel flow until the
engine relights. The igniters are energized for 20 seconds after an engine relight.
If the engine continues to run down (no relight), then the EEC will close the HPSOV at 35% N2
and deenergize
the igniters and an EICAS message is posted.
GF1810_094
L ENG FLAMEOUT
R ENG FLAMEOUT
Quick Relight
The EEC provides a Quick Relight function which automatically relights the engine if the ENGINE
RUN switch has been momentarily selected to OFF then reselected
to ON.
The Quick Relight functionality is defined as follows:
· Enabled only if inflight.
· Activated when ENGINE RUN switch is reselected ON within 30 seconds after selecting
ENGINE RUN switch to OFF and N2 greater than or equal to Idle (42% N2).
· When Quick Relight activated, fuel is commanded ON and both ignition systems ON.
If N2 continues to fall below Idle speed, Quick Relight will maintain both the ignition systems and
fuel ON until the engine speed is regained for up to 20 seconds.
The crew can cancel Quick Relight by selecting the ENGINE RUN back to OFF.
POWER PLANT
Flight Crew Operating Manual Rev 2A, Apr 11, 2005
CSP 700−5000−6
Volume 2
18−10−66
ENGINE FIRE DETECTION SYSTEM
Engine fire detection is provided by a dualloop
system; each loop consisting of sensing elements.
Each zone’s elements are mounted on support tubes.
The Fire Detection and Extinguishing (FIDEEX) system provides fire detection and extinguishing to
both main engine zones.
GF1810_095
SENSOR ELEMENTS
(2 Ea. PER ASSEMBLY)
ENGINE FIRE DETECTOR ELEMENTS
The detection loops of both zones are monitored as a single zone and the fire extinguishing system
when discharged, supplies both zones simultaneously.
DISCHARGE INTO
FIRE ZONE
FEED TO THE
RIGHT ENGINE
FIRE BOTTLES
DISCHARGE INTO
FIRE ZONE
DISCHARGE INTO
FIRE ZONE
GF1810_096
For more information, see Chapter 9, FIRE PROTECTION.
POWER PLANT
Rev 2A, Apr 11, 2005 Flight Crew Operating Manual
CSP 700−5000−6
Volume 2
18−10−67
ENGINE LIMIT EXCEEDANCE DISPLAY
Any engine exceedance is displayed in the MFD MENU window page 3/3 (on the ground only). The
exceedance display window shall present data from the last recorded engine exceedance.
The presented data consists of the following:
· Date of exceedance.
· Maximum L−R N1 speed.
· Maximum L−R ITT.
· Maximum oil temperature.
· Maximum L−R N2 vibration.
· Time of exceedance.
· Maximum L−R N2 speed.
· Maximum oil pressure.
· Maximum L−R N1 vibration.
· Time in exceedance for each parameter.
· Source of the event that triggered the
exceedance.
GF1810_097a
ETE1+36
12.5
KDVT
NM
WX SAT
GSPD
−56
TAT
TAS
−40
0
0
HDG
315
FMS1
360
N
50 50
KPHX
TOC
LUF
KDVT
KSRP
30
6
33
3
Selecting MENU will display engine EXCEEDANCE
display (on ground only).
NOTE
EXCEEDANCE 3/3
DATE: 10 /12/98 TIME: 10:45
LH RH
MAX TIME MAX TIME
N1 :
N2 :
ITT :
OIL P :
OIL T :
N1 VIB :
N2 VIB :
TRIGGERED BY : L N1
120 2:15 95 0:00
85 0:00 80 0:00
790 0:00 800 0:00
50 0:00 50 0:00
85 0:00 88 0:00
0.6 0:00 0.6 0:00
0.6 0:00 0.6 0:00
If no engine exceedance has occurred:
EXCEEDANCE 3/3
NO EXCEEDANCE RECORDED
1
The maximum value data shall be the maximum value the parameter achieved during the
exceedance event, regardless of whether it was within the exceedance band. The time in
　
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