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treatment before take-off.
When the OAT is 5°C (41°F) or below the wing anti-ice
system must be selected ON for take-off, just prior to thrust
increase for take-off.
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.
(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.
LIMITATIONS
Operating Limitations
02−04−6
REV 77, Oct 20/09
DOT Approved
CL−604 Airplane Flight Manual
PSP 604−1
5. ENHANCED TAKE-OFF PROCEDURES AND WINTER OPERATIONS TRAINING
Take-offs conducted where the OAT is 5°C (41°F) or below, are subject to the following training
limitations:
• the wing anti-ice system must be selected ON for take-off, just prior to thrust increase for
take-off, if the OAT is 5°C (41°F) or below, or
• the Aircraft Commander has successfully completed specific training, within the preceding
12 calendar months, for take-off procedures, ground icing conditions and cold weather
operations.
Additionally, no take-off shall be conducted by the First Officer where the OAT is 5°C (41°F) or
below, unless that pilot has successfully completed the specific training within the preceding
12 calendar months, for take-off procedures, ground icing conditions and cold weather
operations.
6. RUNWAY SLOPES
The maximum runway slopes approved for take-off and landing are:
+2% (uphill)
–2% (downhill)
7. TAILWIND CONDITIONS
The maximum tailwind component approved for take-off and landing is 10 knots.
8. APPROACHES
Operations and limitations with a glidepath angle that exceeds 3.5 degrees are described in the
following supplements:
• Supplement 11 − Approaches below 4.5 Degrees
• Supplement 12 − Steep Approaches up to 5.5 Degrees
9. MINIMUM FLIGHT CREW
The minimum flight crew is one pilot and one copilot.
10. 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
02−04−7
REV 77, Oct 20/09
DOT Approved
CL−604 Airplane Flight Manual
PSP 604−1
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.
LIMITATIONS
Operating Limitations
02−04−8
REV 77, Oct 20/09
DOT Approved
CL−604 Airplane Flight Manual
PSP 604−1
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
　
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