Maintenance Manual STEMME S10-VT
Date of Issue: Jan. 01, 1998
Page 3-1
Amendment Nr. 0
Date: --
A4011121_B23.doc
Doc. No. A40-11-121
3. Description of Assemblies
3.1 Airframe, Primary and Secondary Structure
The
Primary Structure
includes:
wing spars, root ribs, and wing spar boxes
wing shells
central fuselage framework
tail boom and vertical stabiliser
front section of fuselage
horizontal stabiliser
fittings
The
Secondary Structure
includes:
control surfaces
cowlings, cooling air system ducts, cockpit components
3.1.1 Wing
Structural design: Carbon fibre reinforced plastic (CFRP) sandwich shell, CFRP spars.
The wing consists of three sections: a central wing with a span of 9.90 m / 32.5 ft. and two outboard wing
sections with a span of 6.55 m / 21.5 ft. each. Attachment of the central wing to the fuselage is by means of
four sliding bolts, attachment of the outboard wings to the central wing is with one sliding bolt each.
A removable fairing covers the wing/fuselage combination. Beneath the fairings, free access to the wing
attachment, the control system joints and the combined aileron/flap controls is possible. For disassembly, the
central wing has to be lifted vertically.
The flaps extend to the total span of the central wing and the ailerons to the total span of the outboard wings.
The controls of flaps and ailerons are interconnected, the ailerons acting as differential flaps and the flaps
acting as differential ailerons. The flap deflection is reduced from the inner to the outer wing, the aileron
deflection is reduced from outer to the central wing and from up to down deflections.
Two-storey Schempp-Hirth air brakes are installed on the centre wing upper side.
The slots of flaps and ailerons are sealed with elastic adhesive tape and a skid layer on the upper side of the
wing and with a textile tape (elastic adhesive tape and skid layer optional) on the lower side.
A boundary layer turbulator (adhesive 60° zigzag tape, leading edge at 69% of chord, 12 x 0.5 mm / 0.47 x
0.02 in.) on the wing lower side ensures a defined flow transition.
3.1.2 Fuselage
The fuselage is a modular construction of three assemblies with bolted joints: the front fuselage section
(CFRP-Kevlar-fibreglass construction), the centre fuselage framework and the tail boom (CFRP
construction).
Loads from the fuselage front section, the wing, the landing gear, the power-plant and the tail unit are
transmitted by the central fuselage framework.
The centre fuselage framework is covered by self-supporting fairings (upper fairing and engine cowlings) of
GFRP-sandwich. The attachment of the fairings is by means of camlocks, which can be easily opened with a
screw-driver. The upper fairing includes an oil service access, which can be opened without a tool.
