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POWER PLANT
Starting and Ignition Systems
Flight Crew Operating Manual MASTER
CSP A--013
Continuous ignition is also activated automatically by the stall protection computer,
when an impending stall is detected.
2. START SEQUENCE
When the engine START switchlight is pushed:
S The 10th--stage bleed isolation valve and the left and right bleed shutoff valves
open.
S The start valve on the associated engine opens to allow air pressure to the starter.
S When the start valve opens, the white START switchlight illuminates and the L or R
ENGINE START status message is displayed on the EICAS status page.
S At 55% N2, power is removed from the start valve and the starter disengages. The
white START switchlight goes out and the status message is removed.
A. Starter Limitations
START # TIME ON TIME OFF
1 60 seconds 10 seconds
2 60 seconds 10 seconds
3 and subsequent 60 seconds 5 minutes
Dry Motoring TIME ON TIME OFF
1 90 seconds 5 minutes
2 and subsequent 30 seconds 5 minutes
Vol. 1 20--30--3
REV 56, Jan 31/03
POWER PLANT
Starting and Ignition Systems
Flight Crew Operating Manual
CSP A--013
MASTER
Starting and Ignition Systems --- Block Schematic
Figure 20---30---1
115 VAC
28 VDC
28 VDC
REV 56, Jan 31/03
Vol. 1 20--30--4
POWER PLANT
Starting and Ignition Systems
Flight Crew Operating Manual MASTER
CSP A--013
Starting and Ignition Systems --- Control Panel
Figure 20---30---2
L ENG and R ENG STOP
Used to stop engine start
sequence.
STOP (white) light indicates stop
is selected.
Engine Start/Ignition Panel
Overhead Panel
L ENG and R ENG START
Used to initiate engine start sequence.
START (white) light indicates start
is selected.
IGNITION
ARM (green) -- Arms respective
ignition system on both engines.
ON (white) -- Indicates that the
ignition system is activated.
IGNITION CONT
Used to select
continuous ignition of
both ignitors on both
engines.
ON (white) light
indicates continuous
ignition is selected on.
Vol. 1 20--30--5
REV 56, Jan 31/03
POWER PLANT
Starting and Ignition Systems
Flight Crew Operating Manual
CSP A--013
MASTER
Starting and Ignition Systems --- L or R Start Abort Caution <MST>
Figure 20---30---3
L or R ENGINE START status (white)
Indicates that engine start has been
selected.
NO STRTR CUTOUT
caution (amber)
Indicates that the starter valve is not
closed when engine running.
CONT IGNITION status (white)
Indicates that all ignitors have been
selected on.
IGNITION A/B advisory (green)
Comes on to indicate that both
ignitors are inoperative on
one engine.
Status Page
IGNITION A
IGNITION B
IGNITION A/B
CONT IGNITION
L ENGINE START
R ENGINE START
Primary Page
BRT
IGNITION A,B advisory (white)
Comes on to indicate that at least
one ignitor is in use on
each engine.
<0039>
<0006>
<0039>
<0039>
<0039>
IGNITION A,B advisory (green)
Comes on to indicate that one
ignitor is inoperative on one or
both engines.
<0039>
REV 56, Jan 31/03
Vol. 1 20--30--6
POWER PLANT
Starting and Ignition Systems
Flight Crew Operating Manual MASTER
CSP A--013
B. System Circuit Breakers
SYSTEM SUB--SYSTEM CB NAME BUS BAR CB
PANEL
CB
LOCATION
NOTES
ENG IGN A
AC ESS BUS 3 B7
Ignition
1
M2
Power Plant
System
ENG IGN B BATT BUS
M3
5 B1
Starter ENG START L
1
M5
System ENG START R
M4
Vol. 1 20--40--1
REV 56, Jan 31/03
POWER PLANT
Oil System
Flight Crew Operating Manual
CSP A--013
MASTER
1. OIL SYSTEM
Each engine has an independent lubrication supply system consisting of an oil pump and an
oil reservoir which is integral to the accessory gearbox. The pressure pump draws oil from
the reservoir and supplies it to the various engine components for cooling and lubrication.
The usable oil quantity is 7 U.S. quarts (6.6 liters).
The lubrication system is pressurized by the main lube pump. Oil flows from the main pump,
passes through an oil filter and the oil/fuel heat exchanger. The oil then continues through
the engine, for cooling and lubricating, then to the engine sumps. Scavenge pumps return
the oil to the reservoir after passing through a chip detector and de-aerator.
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