Maintenance Manual LS8
Issued: December 2009
Copyright DG Flugzeugbau GmbH - any copy or publishing prohibited
Manual valid with the up-to-date cover page only
11.1
11 Repairs
11.1 Composite repairs
Caution: You are only allowed to use the materials specified in section 10.
Warning: Major damage which is outside the scope of the list below should
only be repaired by an approved repair station rated for composite aircraft
structure work.
For all aircraft under EASA regulations the following applies: According to part
21, subpart M to accomplish major repairs an approved repair instruction is
required, see also TN DG-G-01 “Approved repair methods according to EU
Commission Regulation 1702/2003 part 21, subpart M”
1. The following can be repaired:
a. All damage to paint and putty.
b. Holes on the belly of the fuselage if the maximum diameter does not
exceed the following:
Forward fuselage 80 mm
Aft boom 40 mm
Cracks in the belly maximum length:
Forward fuselage 120 mm
Aft boom 80 mm
The blind glue joints of the fuselage boom must not be damaged.
c. Holes, cracks, blisters in the wings, and control surfaces not in excess
of the following dimensions:
Average Diameter Length
Wings
100 mm 150 mm
Aileron, Rudder, Elevator
50 mm 80 mm
Wings must not be damaged in the spar region.
Caution: The stabilizer is a load carrying structure without spar. Damage in the
region 600mm (23,6 in.) from the centerline need not be repaired. For control
surfaces, Limit values for Mass and Mass Balance are mandatory (see section
5.2). In case of doubt ask DG prior to repairing.
d. Replacement of bent fittings.
Note: Special hints for handling FRP repairs are found in the Petite Plane Patch
Primer (Author U. Hänle).
Caution: In the rear fuselage shell a layer of Diolen-fabric is installed between
the fibreglass-layers. In case of repair replace this layer by 2 layers of fibreglass
92125 +
45°.
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