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(for first 2 min.)
–
– 0 to 928
900
(for next 3 min.)
0 to 900
–Maximum
Continuous
Thrust
(MCT)
900
–
0 to 900
N2 % RPM:
– wing anti-ice
on
99.3 0 to 77.9 78 to 99.2
– wing anti-ice
off
99.3 – 0 to 99.2
OIL TEMP °C 163 155 to 162 –40 to 154
OIL PRESS psi 0 to 25 116 to 156 26 to 115
15/05/95
CL-604 Airplane Flight Manual
PSP 604–1
DOT Approved
Sep 20/95
LIMITATIONS
Power Plant
02–05–2
3. ENGINE OPERATING LIMITS
A. Engine Operating Limits Table
Condition Core RPM
N2 %
Fan RPM
N1 %
ITT °C
Start 20 903 (50 seconds)
Acceleration 930 (5 seconds)
Max Continuous 99.2 98.6 899
Normal Take-Off 98.3 96.2 884 (5 minutes)*
900 (2 minutes out of
5 total transient)*
Maximum Take-Off
(APR operating)
99.4 98.6 899 (5 minutes)*
928 (2 minutes out of
5 total transient)*
* Transient limits.
NOTE
1. The take-off, go-around and maximum continuous thrust
N1 values for the CF34-3B engine are presented on the
appropriate engine thrust setting charts contained in
Chapter 6; PERFORMANCE - THRUST SETTINGS of
this manual.
2. If above 40,000 feet one air-conditioning unit or cowl
anti-ice must be selected on for each engine.
B. Airplane Cold Soak
Before the first flight of a day, when the airplane is cold-soaked at an ambient temperature
of –30 °C (–22 °F) or below for more than 8 hours, the engines must be motored for 60
seconds and fan rotation must be verified before the engine start is initiated.
Thrust reversers must be actuated until the deploy and stow cycles are less than 5 seconds.
15/05/95
CL-604 Airplane Flight Manual
PSP 604–1
DOT Approved
REV 19, Mar 06/97
LIMITATIONS
Power Plant
02–05–3
3. ENGINE OPERATING LIMITS (CONT’D)
C. Oil Temperature
Minimum for starting –40 °C
Maximum Continuous +155 °C
Maximum Permissible +163 °C (15 minutes maximum)
D. Oil Pressure
Steady state idle 25 psi minimum
Take-off power 45 psi minimum
Maximum continuous 110 psi maximum
Maximum transient
After cold start 115 psi (transmitter limit)
(10 minutes maximum) NOTE: Engine must remain at idle until oil
pressure returns to normal range.
4. CONTINUOUS ENGINE IGNITION
Continuous engine ignition must be used during the following:

Take-offs and landings on contaminated runways;

Take-offs with high crosswind components;

Flight through moderate or heavier intensity rain;

Flight through moderate or heavier intensity turbulence;

Flight in the vicinity of thunderstorms.
5. AUTOMATIC PERFORMANCE RESERVE (APR)
A. If take-off performance is predicated upon the use of APR, the APR system must be
verified operative prior to take-off.
B. The APR system must be selected off, if an APR INOP caution message is displayed on
EICAS.
C. APR OFF Performance must be used if an APR INOP caution message is displayed.
15/05/95
CL-604 Airplane Flight Manual
PSP 604–1
DOT Approved
REV 26, Apr 20/98
LIMITATIONS
Power Plant
02–05–4
6. STARTER CRANKING LIMITS (GROUND AND AIR)
The starter must not be used if indicated N2 rpm exceeds 55%.
A. Engine Start
Normal engine start - Three consecutive engine start cycles with 5 minutes cooling between
additional cycles.
B. Associated Conditions
At initiation of thrust lever movement from SHUT OFF to IDLE:
(1) ITT must be 120 °C or less for all ground starts.
(2) ITT must be 90 °C or less for all air starts.
C. Dry Motoring Cycle
Dry motoring is performed with ignition OFF and thrust levers at SHUT OFF.
Dry motoring may be used for engine ground starts and engine airstarts.
Start Maximum Time On Followed By
1 90 seconds 5 minutes off
2 and subsequent 30 seconds 5 minutes off
7. ENGINE RELIGHT
Engine starting in-flight is only permitted within the envelope defined in Figure 02–05–1:
RELIGHT TYPE ENVELOPE (Figure 02–05–1)
Windmilling Altitude from 21,000 to 10,000 feet:
Airspeed from 300 to 348 KIAS, and
from 12 to 55 % N2.
Altitude from 10,000 to 8,000 feet:
Airspeed from 300 to 348 KIAS, and
from 10 to 55 % N2.
Altitude from sea level to 8,000 feet:
Airspeed 300 KIAS and
from 10 to 55 % N2
NOTE
N2 should be stable or increasing.
Starter-assisted Cross Bleed Altitude from 21,000 feet to 15,000 feet:
　
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