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NOTE
1. Vibration may increase during the ice shedding
process.
2. Vibrations may momentarily indicate full scale during
the ice shedding process.
3. Thrust settings up to and including maximum
continuous may be required to shed ice.
(2) Engine indications ......................................Monitor ITT.
No
(1) Affected thrust lever .............................................Adjust to a setting that maintains
vibration level within normal
range.
(2) Engine ................................................................Monitor
ABNORMAL PROCEDURES
Power Plant
05−02−6
REV 66, Feb 01/07
▼
DOT Approved
CL−604 Airplane Flight Manual
PSP 604−1
1. POWER PLANT (CONT'D)
F. N1 Fan Vibration (Cont’d)
Vibration persists and the condition indicates advisability of an engine shutdown:
Yes
(3) Affected engine.......................................Shutdown Refer to In-Flight Engine
Failure/Shutdown procedure in
this section.
− END −
No
(3) No further action required.
END
G. N2 Core Vibration
Indication: VIB icon on N2 gauge.
CAUTION
It is not recommended that an engine be shut down unless there is
another indication of a severe engine abnormality, i.e., high oil
temperature, high oil pressure, high ITT, or abnormal engine vibration
is felt through the airframe.
NOTE
N2 VIB icon indicates core vibration is greater than 1.7 Mils.
Affected engine:
(1) Thrust lever ..........................................................Adjust to a setting that maintains
vibration level within normal
range.
NOTE
If engine was started within 2 hours of shutdown, allow 10
minutes for vibration levels to return to normal.
(2) Engine indications ..............................................Monitor
Vibration can be controlled or reduced:
Yes
(3) No further action required.
− END −
No
(3) Affected engine ..............................................Shutdown Refer to In-Flight Engine
Failure/Shutdown procedure in
this section.
END
ABNORMAL PROCEDURES
Power Plant
05−02−7
REV 66, Feb 01/07
DOT Approved
CL−604 Airplane Flight Manual
PSP 604−1
1. POWER PLANT (CONT'D)
H. Engine Hot Start
Indication: HOT icon displayed on ITT gauge and/or readout indicates 900°C or
greater.
Affected engine:
(1) Thrust lever ..................................................SHUT OFF
(2) IGNITION switch/lights (all) .............................Press out to turn off all ignition. ON lights
go out. IGNITION A and B
advisory messages and CONT
IGNITION light out.
(3) Dry motor..................................................... Accomplish until ITT is reduced to below
120°C or starter limit,
whichever comes first.
END
I. Engine DCU Parameter Disagreement
Indication: L (R) ENG MISCOMP caution message. Affected
engine’s (either left or right engine) DCU parameters disagree.
(N1 and N2 by 5%, and ITT by 40°C).
(1) EICAS secondary display.....................................Select to PRI (engines) page.
(2) Affected engine’s parameters
(either left or right) ......................................Cross-check to find disagreement.
(3) Affected engine ................................................ Maintain within limits, using reliable PRI
page.
END
ABNORMAL PROCEDURES
Power Plant
05−02−8
REV 69, Jun 04/07
DOT Approved
CL−604 Airplane Flight Manual
PSP 604−1
1. POWER PLANT (CONT'D)
J. Thrust Lever Inoperative
Indication: Affected thrust lever inoperative.
At a safe altitude, before commencing the approach:
(1) Affected ENG FIRE PUSH
switch/light .........................................................Press in to shutdown affected engine.
BOTTLE ARMED PUSH TO
DISCH lights and L (R) ENG
SOV CLSD advisory message
on.
NOTE
Ground spoilers may not be available upon landing.
Ground spoilers will operate only if affected engine is windmilling above
40% N1.
(2) Affected engine ..............................................Shutdown Refer to In-Flight Engine
Failure/Shutdown procedure in
this section.
(3) Actual landing distance .................................... Increase by a factor of 1.60 (60%), for a
flaps 20° landing without the
use of reverse thrust.
END
ABNORMAL PROCEDURES
Power Plant
05−02−9
REV 66, Feb 01/07
DOT Approved
　
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