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604−27−012 02−03−4
OPERATING LIMITATIONS
Figure 02−04−1 Altitude and Temperature Operating Limits 02−04−1
POWER PLANT
Figure 02−05−1 Engine Air Start Envelope (In Flight) 02−05−4
Figure 02−05−2 Auxiliary Tank Quantity/Tail Tank Quantity − Relation
Verses Centre of Gravity 02−05−6
Figure 02−05−3 Minimum Wing Tank Fuel Quantity for Take-Off 02−05−9
LIMITATIONS
Table of Contents
Vol. 1 02−00−4
REV 77, Oct 20/09
CL−604 Operating Manual
PSP 604−6
Page
POWER PLANT
Figure 02−05−4 Minimum Wing Tank Fuel Quantity for Take-Off
(Airplanes 5301,
5303 to 5639 NOT incorporating Service Bulletin
604–11–001) 02−05−10
Figure 02−05−5 Manual Fuel Transfer − Auxiliary Tank Quantity vs Tail
Tank Quantity 02−05−14
Figure 02−05−6 APU In-Flight Envelope 02−05−19
Figure 02−05−7 APU In−Flight Envelope
(Airplanes 5301 to 5630 NOT incorporating
SB 604−49−006 or 604−49−009) 02−05−20
OPERATING SPEEDS
Figure 02−06−1 Maximum Operating Speed and Mach Number 02−06−1
Figure 02−06−2 Design Maneuvering Speeds 02−06−2
LIMITATIONS
Table of Contents
Vol. 1 02−00−5
REV 71, Oct 31/07
CL−604 Operating Manual
PSP 604−6
Page
LIMITATIONS
Table of Contents
Vol. 1 02−00−6
REV 66, Feb 01/07
CL−604 Operating Manual
PSP 604−6
THIS PAGE INTENTIONALLY LEFT BLANK
1. GENERAL
The limitations included in this chapter contain items peculiar to the CL600, model 2B16, variant
CL–604 Challenger airplane.
Observance of these limitations is mandatory.
2. KINDS OF AIRPLANE OPERATION
The airplane is certified for operations in the following conditions, when the equipment and
instruments required by the airworthiness and operating regulations are approved, installed and
in an operable condition:
• Day and night
• VFR and IFR
• Flight in icing conditions
The airplane is certified for ditching when the safety equipment specified by the applicable
regulations is installed.
On airplanes incorporating Service Bulletin 604–34–012:
The airplane is certified capable of RVSM operations in accordance with FAA “Interim guidance
material on the approval of operations/aircraft for RVSM operations”, 91–RVSM, dated March
14, 1994.
NOTE
Compliance with the standard noted above does not constitute an
operational approval.
LIMITATIONS
Introduction
Vol. 1 02−01−1
REV 66, Feb 01/07
CL−604 Operating Manual
PSP 604−6
LIMITATIONS
Introduction
Vol. 1 02−01−2
REV 66, Feb 01/07
CL−604 Operating Manual
PSP 604−6
THIS PAGE INTENTIONALLY LEFT BLANK
1. STRUCTURAL WEIGHT LIMITATION
Maximum taxi and ramp weight: 21,909 kg (48,300 lb)
Maximum take-off weight: 21,863 kg (48,200 lb)
Maximum landing weight: 17,237 kg (38,000 lb)
Maximum zero fuel weight: 14,515 kg (32,000 lb)
Minimum flight weight: 11,794 kg (26,000 lb)
Minimum operating empty weight: 10,047 kg (22,150 lb)
NOTE
1. The maximum take-off weight (MTOW) and/or maximum landing
weight (MLW) may be further limited due to performance
considerations.
2. The maximum landing weight (MLW) is further limited when landing
at airport elevations above 10,000 feet (Refer to Chapter 6;
SUPPLEMENT 19 – OPERATION AT HIGH AIRPORT
ELEVATIONS) .
On airplanes 5301, 5303 to 5639 NOT incorporating Service Bulletin 604–11–001:
Maximum taxi and ramp weight: 21,637 kg (47,700 lb)
Maximum take-off weight: 21,591 kg (47,600 lb)
Maximum landing weight: 17,237 kg (38,000 lb)
Maximum zero fuel weight: 14,515 kg (32,000 lb)
Minimum flight weight: 11,794 kg (26,000 lb)
Minimum operating empty weight: 10,047 kg (22,150 lb)
NOTE
1. The maximum take-off weight (MTOW) and/or maximum landing
weight (MLW) may be further limited due to performance
considerations.
2. The maximum landing weight (MLW) is further limited when
landing at airport elevations above 10,000 feet (Refer to Chapter 6;
SUPPLEMENT 19 – OPERATION AT HIGH AIRPORT
ELEVATIONS) .
LIMITATIONS
Structural Weight
Vol. 1 02−02−1
REV 66, Feb 01/07
CL−604 Operating Manual
　
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