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1. GENERAL
The limitations included in this chapter contain items peculiar to the CL600, model 2B16 Challenger airplane (Serial No. 5701 and subsequent).
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:
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Day and night
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VFR and IFR
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Flight in icing conditions
The airplane is certified for ditching when the safety equipment, specified by the applicable regulations, is installed.
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 02.01.2
Oct 05/06
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CL.605 Flight Crew Operating Manual
PSP 605.6
LIMITATIONS Structural Weight Vol. 1 02.02.1
Oct 05/06
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 – OPERATIONS AT HIGH AIRPORT ELEVATIONS) .
LIMITATIONS Structural Weight Vol. 1 02.02.2
Oct 05/06
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CL.605 Flight Crew Operating Manual
PSP 605.6
LIMITATIONS Centre of Gravity Vol. 1 02.03.1
Oct 05/06
1. CENTRE OF GRAVITY LIMITS (MTOW 48,200 LB)
The maximum permissible centre of gravity (CG) limits are as shown in Figure 02.03.1.
The airplane including interior payload, passengers and fuel (refer to Figure 02–05–2) must be loaded such that the airplane weight and centre of gravity are maintained within the specified limits (including variations due to fuel consumption, passenger movement, retraction of landing gear, etc.).
The stabilizer trim setting must be in accordance with Chapter 4; NORMAL PROCEDURES – TAXIING AND TAKE-OFF – Taxi Check.
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