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and thrust lever not at shut--off.
L or R THROTTLE caution (amber)
Indicates failure of respective thrust lever.
FADEC will maintain last power level setting
until approach.
L or R ENG SRG CLSD caution (amber)
Indicates that respective operability bleed valve
has failed closed.
L or R ENG SHUTDOWN status (white)
Indicates that respective engine has shut
down.
L or R THROTTLE FAULT status (white)
Indicates a fault in respective thrust lever.
Primary Page
Status Page
L or R ENG SRG OPEN caution (amber)
Indicates that respective operability bleed valve
has failed open.
Vol. 1 20--20--10
POWER PLANT
Thrust Control REV 3, May 03/05
Flight Crew Operating Manual
CSP C--013--067
Thrust Control APR CDM Set Caution <1001>
Figure 20---20---10
APR CMD SET
L FADEC
R FADEC
L ENG DEGRADED
R ENG DEGRADED
L FADEC OVHT
R FADEC OVHT
APR CMD SET caution (amber)
Indicates an uncommanded APR activation.
L or R FADEC caution (amber)
Indicates overspeed test failed or a
combination of faults that may affect
engine in--flight performance.
L or R FADEC OVHT caution (amber)
Indicates an overheat condition of respective
FADEC.
L or R ENG DEGRADED caution (amber)
Indicates that FADEC detected a combination
of faults that may result in reduced engine
control authority.
ENGS HI PWR SCHED advisory (green)
Indicates that both engines are at a high
power schedule.
ENG SYNC OFF status (white)
Indicates that engine synchronization
manually selected off by flight crew.
L or R FADEC FAULT 1 status (white)
Indicates that one FADEC channel is
inoperative or a combination of faults
that may affect flight performance.
L or R FADEC FAULT 2 status (white)
Indicates a combination of faults that are less
serious than the faults covered by a FAULT 1
status message.
Vol. 1 20--20--11
POWER PLANT
Thrust Control REV 3, May 03/05
Flight Crew Operating Manual
CSP C--013--067
H. System Circuit Breakers
SYSTEM SUB--SYSTEM CB NAME BUS BAR CB
PANEL
CB
LOCATION
NOTES
FADEC R CH A B6
Thrust FADEC
FADEC R CH B BATTERY
5
B7
Control FADEC L CH A
BUS B8
FADEC L CH B B9
Vol. 1 20--20--12
POWER PLANT
Thrust Control REV 3, May 03/05
Flight Crew Operating Manual
CSP C--013--067
THIS PAGE IS INTENTIONALLY LEFT BLANK
Vol. 1 20--30--1
POWER PLANT
Starting and Ignition Systems REV 3, May 03/05
Flight Crew Operating Manual
CSP C--013--067
1. STARTING AND IGNITION SYSTEMS
The starting and ignition systems are controlled by the Full Authority Digital Electronic
Control (FADEC).
A. Starting System
Pressurized air and DC electrical power are required for starter operation. The engines
can be started using air from the auxiliary power unit, from a ground source, or by using
cross bleed air from a running engine. Pneumatic pressure indications are shown on
the EICAS ECS synoptic page. Engine starting is initiated by respective START
switchlights on the Start/Ignition panel, located on the overhead panel. The start
sequence may be terminated at any time by pressing the engine STOP switchlight.
When the engine START switchlight is pressed, the FADEC opens the starter control
valve which allows pressure from the pneumatic manifold to rotate the starter. The
starter drives the engine accessory gearbox, which in turn drives the engine N2 core
section. When the engine has accelerated to 20% N2 rpm, the thrust lever is advanced
to the idle position to turn the fuel on. The FADEC will then enable the ignition system
for engine light--off. As the engine accelerates to the idle speed condition, the starter
will cut-out at 50% N2 rpm.
Starting and Ignition Systems Block Diagram
Figure 20---30---1
ENGINE
AIR TURBINE
STARTER
ENGINE EXITERS
AND IGNITERS
FADEC
ENGINE STARTER
CONTROL VALVE
BLEED AIR
SYSTEM
STARTER
CIRCUITRY
IGNITION
CIRCUITRY
DATA
CONCENTRATOR
UNIT
INVERTER
RH ENG
FIRE
PUSH
LH ENG
FIRE
PUSH
STALL
115 VAC
28 VDC
28 VDC
Vol. 1 20--30--2
POWER PLANT
Starting and Ignition Systems REV 3, May 03/05
Flight Crew Operating Manual
CSP C--013--067
B. Ignition System
The engine ignition system provides high--energy electrical sparking to ignite the fuel/air
mixture in the combustion chamber during start. The system also provides continuous
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