DESCRIPTION
General 12−10−1
Fuel Tank System 12−10−1
Description 12−10−1
Components and Operation 12−10−1
Fuel Distribution 12−10−5
Description 12−10−5
Components and Operation 12−10−5
Fuel Transfer 12−10−10
Description 12−10−10
Components and Operation 12−10−11
Refueling/Defueling System 12−10−16
Description 12−10−16
Components and Operation 12−10−18
Controls and Indicators 12−10−25
Fuel Control Panel 12−10−25
Fuel Quantity Indicators 12−10−25
Bulk Fuel Temperature Indication 12−10−26
Engine Fuel Temperature Indications 12−10−26
Fuel Flow Indications 12−10−26
EICAS Messages 12−10−30
SUMMARY
Power Supply and Circuit Breaker Summary 12−20−1
LIST OF ILLUSTRATIONS
DESCRIPTION
Figure 12−10−1 Fuel Tank System 12−10−1
Figure 12−10−2 Water Drains Arrangement 12−10−3
Figure 12−10−3 Fuel Vent System (Manual Vent Relief Valves) 12−10−4
Figure 12−10−4 Tail Tank Relief Valve 12−10−4
Figure 12−10−5 BOOST PUMP Switch/Lights 12−10−5
Figure 12−10−6 Main Ejector and Ejector Operation 12−10−7
FUEL SYSTEM
Table of Contents
Vol. 2 12−00−1
Oct 05/06
CHAPTER 12 - FUEL SYSTEM
12−00−1
CL−605 Flight Crew Operating Manual
PSP 605−6
TABLE OF CONTENTS
Page
TABLE OF CONTENTS
LIST OF ILLUSTRATIONS
DESCRIPTION
Figure 12−10−7 Fuel Distribution Schematic Legend 12−10−9
Figure 12−10−8 Fuel Distribution Schematic 12−10−10
Figure 12−10−9 TAIL TANK TRANSFER Switch/Lights 12−10−12
Figure 12−10−10 Fuel Transfer Schematic Legend 12−10−13
Figure 12−10−11 Fuel Transfer Schematic 12−10−14
Figure 12−10−12 Fuel DUMP Switch/Light 12−10−15
Figure 12−10−13 XFLOW Switch/Lights 12−10−16
Figure 12−10−14 Fuel/Defuel Panel Operation Test 12−10−19
Figure 12−10−15 FUEL/DEFUEL Panel Pressure Refueling 12−10−21
Figure 12−10−16 Pressure Refueling (Auxiliary Tanks) 12−10−22
Figure 12−10−17 Refuel/Defuel System Schematic 12−10−23
Figure 12−10−18 FUEL Control Panel 12−10−25
Figure 12−10−19 EICAS Fuel Information Display 12−10−27
Figure 12−10−20 Interior Optional Fuel/Defuel Panel 12−10−27
Figure 12−10−21 Exterior FUEL/DEFUEL Panel 12−10−28
Figure 12−10−22 EICAS Page − Fuel Readout 12−10−29
FUEL SYSTEM
Table of Contents
Vol. 2 12−00−2
Oct 05/06
CL−605 Flight Crew Operating Manual
PSP 605−6
Page
GENERAL
The Challenger 605’s fuel system consists of a fuel tank system, a fuel distribution system, a fuel
transfer system, and a refuelling/defueling system. A fuel system computer unit (FSCU) monitors fuel
quantity, and controls fuel transfer and refueling/defueling. During normal flight operations fuel
management is automatic, requiring no input from the flight crew.
FUEL TANK SYSTEM
Description
The fuel storage system consists of three tank systems:
• The main tanks (left and right wing);
• The auxiliary tanks (forward, center and aft tanks); and
• The tail tanks (tail cone tank, left and right saddle tanks).
Fuel Tank System
Figure 12−10−1
The total fuel capacity is 20,000 lb/9,098 kg (pressure refueling) and 15,722 lb/7,130 kg (gravity
refueling).
Components and Operation
Main Tank System
The left and right main tanks are integral-type fuel tanks (wet wings), that supply fuel to their
respective engines via two collector tanks. Flapper valves in the wing ribs prevent fuel from
surging toward the wing tips. The main tanks may be refueled by pressure or gravity. The APU’s
normal fuel supply is from the right main tank.
FUEL SYSTEM
Description
Vol. 2 12−10−1
Oct 05/06
CL−605 Flight Crew Operating Manual
PSP 605−6
FUEL TANK SYSTEM (CONT'D)
Collector Tanks
Two collector tanks, situated at the lowest point of the center auxiliary tank, are considered
　
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