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NAVIGATION SYSTEMS LIMITATIONS
Flight Management System 02−09−1
Navigation Operational Approvals 02−09−3
Terrain Awareness and Warning System (TAWS) 02−09−6
Mode S Surveillance 02−09−6
Mode S Elementary Surveillance 02−09−6
Mode S Enhanced Surveillance 02−09−6
Integrated Flight Information System (If installed) 02−09−6
Data Link 02−09−7
LIST OF ILLUSTRATIONS
CENTRE OF GRAVITY
Figure 02−03−1 Centre of Gravity Limits (MTOW 48,200 lb) 02−03−1
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) 02−05−5
Figure 02−05−2 Auxiliary Tank Quantity/Tail Tank Quantity – Relation
Versus Centre of Gravity 02−05−7
Figure 02−05−3 Manual Fuel Transfer − Auxiliary Tank Quantity vs Tail
Tank Quantity 02−05−11
Figure 02−05−4 APU In-Flight Envelope 02−05−14
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 02−00−4
REV 1, Dec 21/06
CL−605 Flight Crew Operating Manual
PSP 605−6
Page
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:
• 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.
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
Oct 05/06
CL−605 Flight Crew Operating Manual
PSP 605−6
LIMITATIONS
Introduction
Vol. 1 02−01−2
Oct 05/06
CL−605 Flight Crew Operating Manual
PSP 605−6
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 – OPERATIONS AT HIGH AIRPORT
ELEVATIONS) .
LIMITATIONS
Structural Weight
Vol. 1 02−02−1
Oct 05/06
CL−605 Flight Crew Operating Manual
PSP 605−6
LIMITATIONS
Structural Weight
Vol. 1 02−02−2
Oct 05/06
CL−605 Flight Crew Operating Manual
PSP 605−6
THIS PAGE INTENTIONALLY LEFT BLANK
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.
25 30 35 40
12
14
16
18
20
22
A/C CG % MAC
A/C WEIGHT (kg)
DFM0203_004 THOUSANDS
50
35
30
25
15 20
A/C WEIGHT (lb)
THOUSANDS
For zero fuel weight,
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庞巴迪挑战者605机组操作手册 CL605-LIMITATIONS(2)
