TM 1-1500-204-23-11
(1) Facilities, Equipment and Materials. The
following equipment and materials are required: Vac-
uum Cleaner, HEPA Filter, Dual Action Sander or
90 degree die-grinder and sanding mandrel, Tem-
Reduced strength will result if the incorrect
perature/Vacuum Controller, Heat Blanket, Scissors,
mix ratio is used, if an excessive amount
Marker, Flash breaker Tape, Silicon Carbide Abrasive
of air is introduced into the adhesive during
Paper, Wiping Cloth, Release Film, Spatula, Adhe-
mixing, or if mixing is inadequate and may
sive, Liquid (See System Speciic Technical Manual),
result in loss of structural integrity.
Fabric (See System Speciic Technical Manual), Light-
ning Mesh (See System Speciic Technical Manual),
Pressure must be applied to adhesive within
Vacuum Bag Repair Materials Kit, Copper Sheet.
the pot life of the resin. For ambient temper-
atures in excess of 90 F, decrease this time
(2) Full thickness Scab Repair Procedure.
by 50%. An unsatisfactory repair will result
if the resin gels before adequate pressure is
applied and may result in loss of structural
integrity. Select and prepare a heat blanket
(if required) and all necessary vacuum bag
DO NOT use oil or oil based materials
materials prior to mixing resin.
as NDI couplants on advanced composite
components. Use only water or water based
Failure to observe the correct number of repair
materials. Disbonds may result and loss of
plies, the correct repair ply orientation, the
structural integrity may occur.
correct repair ply overlap and removal of all
(a) Remove dirt, grease and aircraft luids
pieces of vacuum bagging ilm will reduce the
from repair area as described in para-
strength of the repair and may result in the
loss of structural integrity.
(b) Deine both the depth and extent of the
(i)
Prepare the repair plies in accordance
damage using NDI according to para-
with paragraph 6-16, Wet Layup, and
graph 5-2 and the system speciic tech-
place stacked, oriented patch on the
nical manual. Lay out the damage as
damaged site. Refer to the system spe-
described in paragraph 6-4 .
ciic technical manual for the repair iber,
resin, number of plies, ply orientation,
(c) Remove NDI couplant by wiping with
ply size and overlap.
clean, water moistened cloth.
(j)
Determine and apply cure hardware
(d) Remove paint from skin in the repair
and vacuum bagging materials in accor-
area by sanding as described in para-
dance with paragraph 6-18. Refer to
the system speciic technical manual for
the porous release ilm, bleeder mate-
(e) Remove damage as described in para-
rial and the number of bleeder plies.
Failure to properly cure adhesive in accor-
DO NOT sand into laminate near patch edge
dance with the speciied cure cycle will result in
when sanding adhesive squeeze out.
reduced repair strength may not be detectable
by visual or nondestructive inspection. This
(f)
Dry repair area as described in para-
may result in loss of structural integrity.
graph 6-6 using a heat blanket to
remove subsurface moisture.
(k) Cure the repair patch in accordance
with paragraph 6-19, Curing Advanced
(g) Clean the repair area in accordance
Composites.
with paragraph 6-7 in preparation for
replacement of the plies.
(l)
NDI Patch Bond(s).
(h) Seal the backside of the damaged area,
1
Visually inspect adhesive squeeze
if applicable, according to paragraph
out at patch edge as described in
6-18e and the system speciic technical
paragraph 5-2. See igure 6-45 .
manual.
7-16
