GENERAL
General 01−10−1
Wing 01−10−3
Description 01−10−3
Components 01−10−3
Fuselage 01−10−3
Description 01−10−3
Components 01−10−3
Pro Line 21 Data Management 01−10−4
Integrated Flight Information System (IFIS) 01−10−5
Cabin Electronic System 01−10−6
Doors and Emergency Exit 01−10−7
Description 01−10−7
Components and Operation 01−10−8
Service Panels and Accesses 01−10−17
Airplane Antennas 01−10−18
Controls and Indicators 01−10−18
Crew Seats 01−10−35
Description 01−10−35
Taxiing and Turning Radii 01−10−39
Hazard Areas 01−10−40
EICAS Messages 01−10−41
LIST OF ILLUSTRATIONS
GENERAL
Figure 01−10−1 Airplane Basic Dimensions 01−10−2
Figure 01−10−2 Display Control Panel (DCP) 01−10−5
Figure 01−10−3 Cursor Control Panel 01−10−5
Figure 01−10−4 Integrated Flight Information System (IFIS) 01−10−6
Figure 01−10−5 Cabin Electronic System 01−10−7
Figure 01−10−6 Doors and Emergency Exit − Location 01−10−8
Figure 01−10−7 Passenger Door 01−10−10
AIRPLANE GENERAL
Table of Contents
Vol. 2 01−00−1
Oct 05/06
CHAPTER 1 - AIRPLANE GENERAL
01−00−1
CL−605 Flight Crew Operating Manual
PSP 605−6
TABLE OF CONTENTS
Page
TABLE OF CONTENTS
LIST OF ILLUSTRATIONS
GENERAL
Figure 01−10−8 Cargo/Baggage Door 01−10−12
Figure 01−10−9 Aft Equipment Bay Door 01−10−14
Figure 01−10−10 Emergency Exit 01−10−16
Figure 01−10−11 Service Doors and Panels − Location 01−10−17
Figure 01−10−12 Airplane Antennas 01−10−18
Figure 01−10−13 General Arrangement 01−10−21
Figure 01−10−14 Overhead Panel 01−10−23
Figure 01−10−15 Center Pedestal 01−10−25
Figure 01−10−16 Glareshield and Side Panels 01−10−27
Figure 01−10−17 Instrument Panels 01−10−29
Figure 01−10−18 Side Consoles 01−10−31
Figure 01−10−19 DCP/CCP Menus 01−10−33
Figure 01−10−20 Seat/Harness Assembly 01−10−36
Figure 01−10−21 Eye Locator − Seat Adjustement 01−10−38
Figure 01−10−22 Taxiing and Turning Radii 01−10−39
Figure 01−10−23 Hazard Areas − Engines and APU 01−10−40
AIRPLANE GENERAL
Table of Contents
Vol. 2 01−00−2
Oct 05/06
CL−605 Flight Crew Operating Manual
PSP 605−6
Page
GENERAL
The Challenger 605 is a sweptwing, twin-engine monoplane, certified as a CL–600, model 2B16
Challenger airplane (Serial No. 5701 and subsequent), in accordance with FAR 25, FAR 36 and their
amendments. Maximum ramp and takeoff weights are 48,300 and 48,200 lb respectively. The
airplane is designed for two crew members, with accommodation for up to 19 passengers, and is
powered by two General Electric CF34−3B engines.
The airplane is certified capable of RVSM operation in accordance with FAA "interim guidance
material on the approval of operations/aircraft for RVSM operations" 91− RVSM, dated March 14,
1994.
The following sections will be addressed:
• Wings
• Fuselage
• Doors and emergency exits
• Service panels and accesses
• Antennas
• Cockpit controls and indicators
• Crew seats and eye locator
• Taxiing and turning radii
• Hazard areas
AIRPLANE GENERAL
General
Vol. 2 01−10−1
Oct 05/06
CL−605 Flight Crew Operating Manual
PSP 605−6
GENERAL (CONT'D)
Airplane Basic Dimensions
Figure 01−10−1
AIRPLANE GENERAL
General
Vol. 2 01−10−2
Oct 05/06
CL−605 Flight Crew Operating Manual
PSP 605−6
WING
Description
The wing is an all-metal, advanced-technology airfoil, manufactured as a single unit and bolted to
the bottom of the fuselage. The wing incorporates ailerons, flaps, flight and ground spoilers,
internal fuel tanks, and the support structure for the main landing gear. Thermal anti-icing is
　
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