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HP
L R
HP
LP
COND
AIR
BLEED/ANTIICE
40
PSI
40
PSI
APU STARTER AIR VALVE
Air Turbine Starter (ATS)
The ATS rotates the HP compressor to enable engine start.
The ATS comprises a single stage turbine, a tungsten cutter (to cut off turbine, if rotor bearings
fail), a sprag type clutch, an output drive shaft decoupler (prevents driving the turbine, in the event
the sprag clutch seizes) and an output drive shaft shear neck (protects the gearbox, in the event
the starter overtorques or seizes).
At starter cutout speed, the SAV is closed, the turbine loses speed and this disengages the sprag
clutch.
POWER PLANT
Flight Crew Operating Manual Rev 2A, Apr 11, 2005
CSP 700−5000−6
Volume 2
18−10−54
STARTING AND IGNITION (CONT'D)
Air Turbine Starter (ATS) (Cont’d)
The START message is displayed on EICAS and on the BLEED/ANTIICE
synoptic page.
FGF1810_008
START
TOTALFUEL(LBS) 41550
20 789
14600 10000 14600 ND
STAB
NU
NL RUDDER
LWD RWD
NR
TRIMS
7.2
N2
FF (PPH)
OIL TEMP
OIL PRESS
10.2
0
20
0
93.4
5750
115
81
ITT
AIL
START
START
Annunciation
START
Annunciation APU
HP
LP OFF LP
HP
R
45
PSI
45
PSI
L
Ignition System
The ignition system ignites the fuel/air mixture in the combustion chamber, as commanded by
either of the two channels of the EEC, during the start sequence and to maintain combustion
during critical phases of flight (stall).
The ignition system comprises two exciter boxes, two igniter leads and two igniter plugs. Power is
supplied from 28VDC and is controlled from channel A or B in the EEC.
For consecutive ground start attempts the EEC alternates channels and igniters as follows:
· EEC channel A − Igniter 1
· EEC channel B − Igniter 1
· EEC channel A − Igniter 2
· EEC channel B − Igniter 2
The above only applies if there are no failures within the FADEC, which prevents alternate
selection.
In the event that the ground start (AUTO) has been aborted, the EEC will automatically select the
other igniter on the following ground start.
During air starts (AUTO), the EEC will select both igniter channels.
During manual ground and air starts, the EEC will select both igniters, as commanded by the
IGNITION switch.
POWER PLANT
Rev 2A, Apr 11, 2005 Flight Crew Operating Manual
CSP 700−5000−6
Volume 2
18−10−55
STARTING AND IGNITION (CONT'D)
Ignition System (Cont’d)
The crew can manually select the ignition system energized continuously on the ENGINE panel,
located on the overhead panel. Upon selection of the ignition switch, the EEC will arm the igniter
unit for start and energize the igniter unit on the operating engine. Crew selection of ignition is not
time limited, but will reduce overall igniter life.
GF1810_077
IGNITION Select Switch
Used to select all 4 igniters
(2 per engine).
mode of operation. The EEC
controls ignition.
ON
that the switch has been
selected ON and igniters are
firing continuously. ENGINE START Selector
Used to start both engines.
NOTE
There is a timed out limit (30 seconds), for igniter operation on the
ground, (with engines not operating), for maintenance purposes.
Normal (dark) − Default
(illuminated) − Indicates
ENGINE
IGNITION L CRANK L CRANK
AUTO
ENG START
AUTO
starts for either engine
L−R CRANK
rotation of the left or right
engine for dry or wet cranking
or manual start.
− Selects automatic
− Initiates
An EICAS message is displayed when IGNITION is selected ON.
GF1810_078
L−R IGNITION ON
Engine Run Switches
The ENGINE RUN switch(es), when selected by the crew to either the ON or OFF position, will
inhibit or allow the EEC to control the engine. The switch(es) interfaces with both EEC and the HP
Fuel ShutOff
(HPSOV) to:
· Manually control closing and opening of the HPSOV.
POWER PLANT
Flight Crew Operating Manual Rev 2A, Apr 11, 2005
CSP 700−5000−6
Volume 2
18−10−56
STARTING AND IGNITION (CONT'D)
Engine Run Switches (Cont’d)
· Indicate to the EEC the Engine Run switch position and perform a dual channel reset and to
close the HPSOV in the Fuel Management Unit (FMU).
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