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sleet or ice crystals), except when the SAT is –40°C (–40°F) or below.
The engine cowl anti-ice system must be on:
At or above 22,000 feet:
• when ice is indicated by the ice detection system, or
• when in icing conditions, if an ice detector has failed.
Below 22,000 feet:
• when in icing conditions, or
• when ice is indicated by the ice detection system.
B. Wing Anti-ice System
(1) Ground Operations
The wing anti-ice system must be on for take-off when the OAT is 5°C (41°F) or below
and visible moisture in any form is present (such as fog with visibility of one mile or less,
rain, snow, sleet and ice crystals).
The wing anti-ice system must also be on for take-off when the OAT is 5°C (41°F) or
below and the runway is contaminated with surface snow, slush or standing water.
When Type II, III or IV anti-icing fluids have been applied, the wing anti-ice system must
only be selected on, if required, just prior to thrust increase for take-off.
LIMITATIONS
Operating Limitations
Vol. 1 02−04−3
Oct 05/06
CL−605 Flight Crew Operating Manual
PSP 605−6
3. OPERATION IN ICING CONDITIONS (CONT'D)
B. Wing Anti-ice System (Cont’d)
(2) Flight Operations
NOTE
Icing conditions exist in flight at a TAT of 10°C (50°F) or below and
visible moisture in any form is encountered (such as clouds, rain, snow,
sleet or ice crystals), except when the SAT is –40°C (–40°F) or below.
The wing anti-ice system must be on:
At or above 22,000 feet:
• when ice is indicated by the ice detection system, or
• when in icing conditions, if an ice detector has failed.
Below 22,000 feet:
• when in icing conditions, or
• when ice is indicated by the ice detection system.
C. Super-Cooled Large Droplet Icing
Continued operation in areas where super-cooled large droplet (SLD) icing conditions exist is
prohibited.
SLD icing conditions are indicated by ice accretion on the flight compartment side windows.
• The wing anti-icing system must be ON in SLD icing conditions.
• The cowl anti-icing system must be ON in SLD icing conditions.
• Leave icing conditions when side window icing occurs.
4. RUNWAY SLOPES
The maximum runway slopes approved for take-off and landing are:
+2% (uphill)
–2% (downhill)
5. TAILWIND CONDITIONS
The maximum tailwind component approved for take-off and landing is 10 knots.
6. MINIMUM FLIGHT CREW
The minimum flight crew is one pilot and one copilot.
7. MAXIMUM OCCUPANTS
The total number of occupants, including no more than nineteen passengers, must not exceed
the lesser of the following:
• Twenty-two or,
• The number for which seating accommodation approved for take-off and landing is provided.
LIMITATIONS
Operating Limitations
Vol. 1 02−04−4
Oct 05/06
CL−605 Flight Crew Operating Manual
PSP 605−6
8. 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
9. 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
10. MINIMUM ENROUTE CLEARANCE
It is recommended that all terrain and/or obstacles be cleared by at least 1,300 feet along the
enroute flight path.
SAAU Certified Airplanes
11. 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
　
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