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PSP 604−6
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/Fuel Dump 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 Tail Tank Transfer/Fuel Dump Switch/Lights 12−10−15
Figure 12−10−13 XFLOW Switch/Lights 12−10−16
Figure 12−10−14 Fuel/Defuel Panel Operation Test 12−10−20
Figure 12−10−15 FUEL/DEFUEL Panel Pressure Refueling 12−10−22
Figure 12−10−16 Pressure Refueling (Auxiliary Tanks) 12−10−23
Figure 12−10−17 Refuel/Defuel System Schematic 12−10−24
Figure 12−10−18 Fuel Control Panel 12−10−26
Figure 12−10−19 EICAS Fuel Information Display 12−10−28
Figure 12−10−20 Interior Optional Fuel/Defuel Panel 12−10−28
Figure 12−10−21 Exterior FUEL/DEFUEL Panel 12−10−29
Figure 12−10−22 EICAS Primary Display − Fuel Readout 12−10−30
FUEL SYSTEM
Table of Contents
Vol. 2 12−00−2
REV 74, Nov 07/08
CL−604 Operating Manual
PSP 604−6
Page
GENERAL
The Challenger 604’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 system storage consists of three tank system:
• The main tanks (left and right wings)
• The auxiliary tanks (forward, center and aft tanks)
• The tail tanks (tail cone tank, left and right saddle tanks)
The total fuel capacity is 20,000 lb/9,098 kg (pressure refueling) and 15,722 lb/7,130 kg (gravity
refueling).
Fuel Tank System
Figure 12−10−1
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
REV 66, Feb 01/07
CL−604 Operating Manual
PSP 604−6
FUEL TANK SYSTEM (CONT'D)
Collector Tanks
Two collector tanks, situated at the lowest point of the center auxiliary tank, are considered
part of the main tank system.
Auxiliary Tank System
The auxiliary tank system consists of three interconnected tanks: the forward, center, and aft
auxiliary tanks. They are located in the fuselage below the cabin floor. The auxiliary tanks are
filled and drained simultaneously, and may be refueled by pressure or gravity. The auxiliary
tanks feed fuel to the main wing tanks by means of transfer ejector pumps.
Tail Tank System
The tail tank system consists of three separate tanks (the tail cone tank and two saddle tanks),
which share a common sump/manifold. The tail cone tank is a component of the fuselage tail
cone structure. The saddle tanks are located in the aft equipment bay. All three tanks are
pressure-fueled simultaneously by the refueling system through the common sump/manifold.
The tail tanks may not be gravity refueled.
During normal operations, tail tank fuel is transferred to the auxiliary tank system by electrically
operated tail transfer pumps. This transfer is scheduled and monitored by the FSCU, which
ensures the aircraft is maintained within center-of-gravity limits.
During non-normal operations, the flight crew may control tail transfer pump operation manually.
All the tail tank fuel may be dumped through a dump mast located at the sump/manifold of the
tail tank system.
Fuel Management
Fuel transfer from the auxiliary tank to the wing tank is automatically controlled by the fuel level
control valve in each main tank. When the left and/or right wing tank fuel level drops below the
preset limit, fuel transfer will start to maintain that level, until the auxiliary tank is empty.
　
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