SCHEMPP-HIRTH FLUGZEUGBAU GmbH, KIRCHHEIM/TECK
Arcus M
FLIGHT MANUAL
7.11 Fuel system
A view of the fuel system is given on page 7.11.2 – for a specification of the fuel to
be used refer to page 2.4
Up to two flexible tanks may be used inside left and right wing optionally.
Instructions on how to refuel the aircraft are found on page 4.2.2.1 through 4.2.2.3.
Fuel from the fuselage tank is drained via a valve situated on the right side of the
u/c housing.
Fuel to the engine is always supplied from the fuselage tank, which is filled by the
optional wing tanks by means of an interconnecting line featuring a quick-
disconnect coupling.
Fuel from the fuselage tank is fed via a strainer, the electrical pump, a flow meter, a
filter element and the shut-off valve to the injection system, which is connected to
the carburetors on the engine.
Total fuel contents (in fuselage and wing panel(s)) are displayed by the engine
control unit MCU II – its fuel quantity indicator is adjustable.
The vent line of the fuselage tank extends via an expansion reservoir overboard at
the top of the fin (on the right side).
WARNING
:
In order to prevent that the engine stops due to the lack of the fuel,
the opening of the vent line must never be taped closed!
Each wing tank has a vent line – routed to the expansion tank – featuring a
pressure relief valve and a connecting nipple for the coupling on the fuselage.
Refueling system
The connecting point (with ON/OFF switch) for the refueling system is on the left
side of the GFRP panel above the front transverse tube.
The additional electrical fuel pump (with strainer) is found below the seat pan – see
page 7.11.2.
October
2011
Revision --
7.11.1