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11. MAXIMUM CROSSWIND COMPONENT
AR Certified Airplanes
The maximum crosswind component for take-off and landing is 24 knots (12 meters/sec).
SAAU Certified Airplanes
The maximum crosswind component for take-off and landing on a dry runway is 24 knots
(12 meters/sec).
The maximum crosswind component for take-off and landing on a wet runway with water depth
no more than 3.00 mm (0.125 inch) is defined in the following table for different values of the
coefficient of friction:
REPORTED COEFFICIENT OF FRICTION MAXIMUM CROSSWIND COMPONENT
0.3 (poor braking) 10 knots (5 meters/sec)
0.4 (average braking) 15 knots (8 meters/sec)
0.5 (good braking, equivalent to dry) 24 knots (12 meters/sec)
The maximum crosswind component for take-off and landing on a contaminated runway is
10 knots (5 meters/sec).
Operation on runways with a coefficient of friction less than 0.3 is prohibited.
SAAU Certified Airplanes
12. GROUND OPERATIONS IN HIGH WIND CONDITIONS
In the event that the airplane is parked and sustains winds or gust loads in excess of
27 meters/second, an inspection and functional check of the aileron, elevator and rudder
power control units is required.
SAAU Certified Airplanes
13. MINIMUM ENROUTE CLEARANCE
It is recommended that all terrain and/or obstacles be cleared by at least 1300 feet along the
enroute flight path.
SAAU Certified Airplanes
14. MINIMUM GO-AROUND ALTITUDE
Demonstrated minimum altitude for all engines go-around without touching the ground is
50 feet and for single engine go-around is 100 feet.
LIMITATIONS
Operating Limitations
Vol. 1 02−04−8
REV 77, Oct 20/09
CL−604 Operating Manual
PSP 604−6
1. ENGINES
Type: General Electric CF34–3B, quantity two.
2. ENGINE INDICATIONS
The engine limit display markings on EICAS must be used to determine compliance with the
maximum/minimum Limits and precautionary ranges. If EICAS markings show more conservative
Limits than those specified below, the limit markings on the EICAS must be used.
INDICATION RED
(MAX/MIN LIMITS)
AMBER
(CAUTION RANGE)
GREEN
(NORMAL RANGE)
N1 % RPM 98.6 – 0 to 98.5
ITT °C:
– APR not operating
900
(for first 2 min.) – 0 to 900
884
(for next 3 min.) – 0 to 884
– APR operating
928
(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
LIMITATIONS
Power Plant
Vol. 1 02−05−1
REV 66, Feb 01/07
CL−604 Operating Manual
PSP 604−6
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 the Airplane Flight 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.
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.
LIMITATIONS
Power Plant
Vol. 1 02−05−2
　
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