System Description; Fuel Tanks; Fuel Pumps; Ejector Boost Pumps - Eclipse 500 System Manual

Section 7. Fuel

7.5 System Description

7.5.1 Fuel Tanks

Fuel is contained within each wing in a "wet wing" design. Each wing is separated
into two tanks, a wing tank (outer portion of the wing) and a sump tank (inner portion
of the wing). Fuel flows from the wing tanks to the sump tanks by gravity, aided by

ejector transfer pumps.

7.5.2 Fuel Pumps

There are ten fuel pumps on the airplane.
Two ejector boost fuel pumps (one per wing)
Two ejector transfer fuel pumps (one per wing)
Two electric fuel pumps (one per wing)
Four engine driven fuel pumps (two per engine)

7.5.3 Ejector Boost Pumps

An ejector boost pump is located in each sump tank to pump fuel from the sump tank
to the Fuel Metering Unit (FMU).
The ejector boost pumps are venturi type that have no moving parts and do not
require electrical power to operate. Pressurized return fuel from the engines flows
through the ejector boost pump venturi, pulling fuel from the sump tank. Return fuel
is also called "motive fuel" since it causes the pumping action.
7.5.4 Ejector Transfer Pumps
An ejector transfer pump is located in each sump tank to aid gravity flow by pumping
fuel from the wing tank to the sump tank to keep the sump tank full whenever the
associated engine is running. The ejector transfer pumps are also a venturi design,
and are operated with motive fuel discharged from the ejector boost pumps.
If an ejector transfer pump fails, gravity transfer from the outboard wing tank to the
inboard sump tank is adequate to keep fuel supplied to the engine.
If there is a failure of internal wing transfer or fuel becomes trapped outboard a L (R)
FUEL UNUSABLE caution message appears and the total amount of unusable fuel
for flight should be increased to 50 lbs.
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Copyright © — Eclipse Aviation Corporation
Eclipse 5OO Systems Manual
Version 2.0 April 2007