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Partial Thickness Bolted Repair Procedure
Figure 7-32. Impact Damage Injection Repair

AVUM and AVIM Manual for General Aircraft Maintenance Sheet Metal Shop Volume 11
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TM 1-1500-204-23-11
(af) Install fasteners and inspect according
to paragraph 3-4g.
(ag) When repairing weight critical struc-
tures, add the weight of the repair(s)
and the zone location(s) to the applica-
ble nameplate.
(ah) Apply inish system in accordance with
paragraph 7-13b or the system speciic
technical manual.
7-8.  INJECTION  REPAIR. Advanced
composite
structures often experience damage in the form of
ply delaminations and matrix cracks. The damage
may be either open or closed to an edge (see igure
7-31). Delaminations and cracks which are not open
to an edge are dificult to repair via the injection
method. The method often suggested to repair this
type of damage is to drill a series of holes around the
cracked/delaminated area and inject those holes with
resin (see igure 7-32). This method is usually unsuc-
cessful. Matrix cracks and delaminations are often
too small and are not interconnected. The currently
available resin systems do not possess suficient low
capability to iniltrate them (see igure 7-33). Hence,
application of injection repair techniques is limited to
delaminations which are either open to an edge or
involve a clearly deined blister.
Figure 7-31. Types of Delaminations
7-57


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