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Airport Conversion 06−04−13
Figure 06−04−8 Net Acceleration Distance 06−04−15
ENROUTE PERFORMANCE
Figure 06−05−1 Final Segment and Enroute Climb Speed − Flaps 0° 06−05−3
Figure 06−05−2 Final Segment and Enroute Climb Gradient, Flaps 0° −
Anti-Icing Off 06−05−5
Figure 06−05−3 Final Segment and Enroute Climb Gradient, Flaps 0° −
Anti-Icing On 06−05−7
APPROACH AND LANDING CLIMB
Figure 06−06−1 Approach Climb Speed, Flaps 20° 06−06−3
Figure 06−06−2 Approach Climb Gradient, Flaps 20° − Anti-Icing Off 06−06−5
Figure 06−06−3 Approach Climb Gradient, Flaps 20° − Anti-Icing On 06−06−9
Figure 06−06−4 Landing Climb Speed, Flaps 45° 06−06−13
Figure 06−06−5 Landing Climb Gradient, Flaps 45° − Anti-Icing Off 06−06−15
Figure 06−06−6 Landing Climb Gradient, Flaps 45° − Anti-Icing On 06−06−17
LANDING PERFORMANCE
Figure 06−07−1 Landing Weight Limited by Climb Requirements −
Approach Flaps 20°/Landing Flaps 45° 06−07−3
Figure 06−07−2 Landing Field Length and Landing Speed, Flaps 45° 06−07−7
Figure 06−07−3 Maximum Permissible Quick Turn-Around Landing Weight 06−07−9
TURN-AROUND TIME
Figure 06−08−1 Landing Brake Energy, Flaps 45° 06−08−3
Figure 06−08−2 Rejected Take-Off Brake Energy, Flaps 20° 06−08−4
Figure 06−08−3 Mainwheel Brake Cooling Time 06−08−5
PERFORMANCE
Table of Contents
06−00−6
REV 74, Nov 07/08
DOT Approved
CL−604 Airplane Flight Manual
PSP 604−1
Page
1. INTRODUCTION
The data in this section present the performance information of the CL 600–2B16 (CL–604)
airplane, fitted with two General Electric CF34–3B engines.
The airspeeds and airplane configurations for take-off, climb and landing, as presented in this
chapter, must be adhered to during the appropriate phase of flight.
All performance data are based on the following conditions:
• Minimum guaranteed engine thrust with allowance made for the installation effects, including
bleed and mechanical horsepower extraction.
• Maximum nominal brake operating pressure of 3,000 psi, with anti-skid and automatic ground
lift spoilers operational.
• ICAO standard atmosphere conditions (ISA), with corrections for non-standard conditions,
when applicable.
• Dry, hard runway surface, unless otherwise noted.
• Flight spoilers deployed manually after touchdown or during a rejected take-off.
• Wind speed is measured at a height of 10 meters (33 feet) above the surface.
• The performance data in this chapter are not valid when:
• The weight exceeds the maximum weight as limited by climb requirements.
• Data is extrapolated from the values shown in the charts.
• For weights below 12,000 kg (26,455 lb) assume a weight of 12,000 kg (26,455 lb).
• For airport pressure altitudes below 0 ft, the performance may be assumed to be that
appropriate to an airport altitude of 0 ft, unless information for altitudes below 0 ft is
presented.
A number of performance charts presented in this chapter have correction grids with a reference
line. If entering the chart from the side wherein the label “Ref.” or “REFERENCE LINE” or “REF.
LINE” is encountered first (usually, from the top of the chart then downwards), then the correct
procedure is to go to the reference line first and then follow the guidelines (if necessary) towards
the appropriate condition. Conversely, if entering the chart from the opposite direction as
mentioned above, then the procedure is to go to the appropriate condition first. These procedures
are clarified by the examples on the charts.
The performance data have been based on:
• A minimum V2 speed of 1.13 VSR, and
• A minimum VREF speed of 1.23 VSR.
PERFORMANCE
General
06−01−1
REV 66, Feb 01/07
DOT Approved
CL−604 Airplane Flight Manual
PSP 604−1
2. CONVERSION DATA
A. Temperature Conversion
A table to convert air temperature at a given pressure altitude into a value of temperature
above or below the International Standard Atmosphere (ISA) is shown on Figure 06−01−1.
Example:
Figure 06−01−1 shows that at an atmosphere of ISA + 10°C and at an altitude of 29,000
　
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