CHAPTER 51
PAGE 33
PAGE DATE: 1. March 2011
MAINTENANCE MANUAL EXTRA 330LX
5 Apply suction with a vacuum pump (pressure difference
approx. 0.7bar / 10psi).
6 Curing cycle.
7 Following the curing cycle carefully remove vacuum
bagging material and peel nylon fabric.
After the pre-curing period at room temperature, the re-
paired area has to be cured according the temperature cycle
as shown on figure 3.
After the curing process is completed, the repair area can be
sanded level to the surrounding area.
N O T I C E Sand only the edge thickness of repair laminate!
Refinish the surface according chapter 51-10-06.
51-70-04 Repair of Spars
The spars consists of carbon roving caps, glass or carbon
fibre webs and PVC foam cores.
I M P O R T A N T The spars are highly stressed; a failure of this bonded
structure can result in loss of the aircraft! In all cases,
the repair of a spar must be considered as a large-scale
repair with a Damage Class 1 (Refer to chapter 51-10-
01 Damage Classification"). EXTRA Flugzeugproduk-
tions- und Vertriebs- GmbH has to be contacted prior
to repair!
51-70-05 Structural Repair of Steel Components
Restoration of a damaged fuselage to its original design
strength, shape and alignment involves careful evaluation of
the damage, followed by exact workmanship in performing
the repairs.
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