Page 2-23
Pilot’s Operating Manual
Revision A1: Nov, 2002
Sub-section 2
ENGINES
Hawker 800XP Pro Line 21
Section III - SYSTEMS DESCRIPTION
FUEL CONTROL
The engine fuel control system consists of:
• Fuel Pump Assembly (Figure 5)
• Hydro-mechanical Fuel Control Unit (FCU)
• Digital Electronic Engine Control (DEEC)
• Fuel Flow Divider Assembly
• Fuel Atomizers
The fuel control system pumps, filters, meters and atomizes the airplane fuel before the ignition system
ignites it to produce thrust.
Fuel Pump (Figure 5)
An engine-driven fuel pump on the rear of the accessory gearbox provides high pressure fuel to the fuel
control system. The pump assembly consists of:
• Booster Pump Element
• Fuel Filter
• Filter Bypass Valve
• High Pressure Pump Element
• Relief Valve
• FCU - attached to the rear of the pump
Anti-Ice Valve
An anti-icing valve is provided within the fuel pump assembly to mix warm fuel from the fuel heater with
the discharge flow of the booster pump to prevent icing of the fuel filter element.
Filter Bypass
The filter bypass valve allows fuel to bypass the filter if an excessive pressure drop across the filter
occurs. When an excessive differential pressure condition exists, an electrical pressure switch will
cause the respective annunciator on the overhead roof panel to illuminate, accompanied by a repeater
annunciator on the MWS panel.
ENG 1
FUEL
and/or
ENG 2
FUEL
FUEL
MWS Panel
Overhead Roof Panel