DOCUMENT NUMBER:
L500-912.820 ISSUE JUL 20, 2016
AMENDMENT: 00
DATE:
CHAPTERPAGE 21
MAINTENANCE MANUAL STEMME S12
2. DESCRIPTION
The STEMME S12 is a twin-seat, self-launching motorglider, constructed mostly from carbon ber
and is aerodynamically optimized for high performance. The two seats are arranged side-by-side
(forward of the wing) and the S12 is equipped with dual controls.
The wing is shoulder mounted and consists of a center section with aps and Schempp-Hirth air
brakes, two outer wing sections with continuous ailerons, two wing extensions with ailerons and
two winglets. The aps and ailerons of inner and outer wing/wing extension are interconnected
(“aperons”).
The motorglider is in “T”-tail design.
The retractable two-wheel main landing gear is electrically operated and is equipped with
hydraulic wheel brakes.
The engine of the STEMME S12 is based on the ROTAX 914 F2-01, which has been certicated by
BRP-ROTAX® GmbH & Co.KG, Austria. STEMME modied the arrangement of some accessories
(induction and exhaust system including turbo-charger, engine mounts etc.) to adapt the systems
to specic installation requirements of the S12. These modications are certied in the STEMME
S12 as engine model ROTAX 914 F2-01/S1.
ENGINE DESCRIPTION
Four-cylinder, four-stroke opposed type Otto-engine, turbocharged with electronic manifold pres-
sure control (TCU); a center cam shaft and tappets; OHV; liquid cooled cylinder heads, cylinder
barrels cooled by ram air; dry-sump lubrication; Dual Capacitive Discharge Ignition (DCDI); 2
CD-carburetors (variable-choke); integrated reduction gear with mechanical vibration absorber
and overload clutch.
The engine is mounted in the fuselage in a center steel frame near the aircraft´s CG. Engine pow-
er is transmitted via a propeller shaft made of composites and a spur gear to the variable pitch
propeller in the fuselage nose.
When the aircraft is in gliding conguration, the propeller blades are folded and covered by a
movable nose cone (nose-cone). Propeller pitch change from take-o into cruise position is
accomplished by electrically heated expansion elements, and from cruise back to take-o position
(elements unheated) by springs as well as aerodynamic and centrifugal forces.
A fuel tank is located at each outboard end of the wing center section. Each tank supplies the
feeder tank in the fuselage by use of electrically driven fuel pumps. From the feeder tank the fuel
is supplied by two fuel pumps (one main and one auxiliary) to the engine to provide required
redundancy.
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