DOCUMENT NUMBER:
L500-912.820 ISSUE JUL 20, 2016
AMENDMENT: 00
DATE: 
CHAPTERPAGE 316
MAINTENANCE MANUAL STEMME S12
3.4.6.2 FUEL SYSTEM DESIGN
WING FUEL SYSTEM
Both wing tanks are located in the outer sections of the wing center section. The ends of the vent
lines are located at the lower, outer ends of the wing center section. The ller caps are located
on the upper surface of the wing center section. The fuel line from each tank includes a strainer,
a ne lter and quick drain as well as a piston pump including a fuel-check valve for each tank.
All these components are accessible through an opening in the lower wing skin near the root rib.
Depending on the position of the fuel selector switch and a oat switch in the feeder tank, the
feeder receives fuel from either the right or the left tank separately, or from both tanks simulta-
neously. A single quick release connector is located between the fuel line from the wing and the
corresponding connection in the fuselage.
3.4.6.3 FUEL SYSTEM OF THE FUSELAGE
FUEL SYSTEM OF THE FUSELAGE
Beginning at the quick release connector, fuel ows directly to the feeder tank. A oat switch in
the feeder tank prevents feeder tank overlling. The feeder tank is vented through the right shell
of the forward fuselage above the landing gear door at the rear edge. The feeder tank has a sump
at its bottom that is connected to a quick drain. From the lower part of the feeder tank (approxi-
mately 1 cm above the bottom) the fuel is pumped by the main fuel pump (powered by the engine
electric system) or the auxiliary fuel pump (powered by the main electric system) to the engine.
The main pump runs continuously whenever the engine electrical system is powered (nose-cone
is pushed forward and locked). A fuel return line delivers surplus fuel back to the feeder tank.
Contaminated fuel (i.e. particles, water, etc.) from the sumps can be drained by use of the quick
drain in the landing gear bay or by the two quick drains in the wing tanks.
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