Page
16
of
33
Fuselage repair laminate plan from inner ply to outer:
2x 92125 (Pipistrel P/N 5071006) 0°/90°
1x 92125 (Pipistrel P/N 5071006) 45°/45°
1x 92125 (Pipistrel P/N 5071006) 0°/90°
1x 92110 (Pipistrel P/N 5071002) 0°/90°
r. Apply resin and first four plies from the fuselage repair laminate plan over the crack on
the fuselage belly and damaged area on the front edge of the fuselage belly (Figure 07-
003 Step 3). Allow to cure for 8 hours at 56°C.
s. Sand the repair area to make it flush with the rest of the surface. Blow surface clean with
compressed air, wipe away dust/debris with acetone and allow to dry for 30 minutes.
t. Apply last outer ply layer from the fuselage repair laminate plan over all the damaged
area (Figure 07-003 step 4). Allow to cure for 8 hours at 56°C.
u. Sand the repair area to make it flush with the rest of the surface. Blow surface clean with
compressed air, wipe away dust/debris with acetone and allow to dry for 30 minutes.
v. Apply rough polyester kit and grind/sand down.
w. Apply fine polyester kit and grind/sand down using sandpaper no finer than P600.
x. Paint the newly processed fuselage surfaces with white acrylic paint, sand down with
P2000 sandpaper and polish with polishing disk.
Modification 8 – SEAT PAN INSERT INSTALLATION.
a. Insert the seat pan insert (Figure 07-001) into the fuselage and inspect the alignment
between seat pan and seat pan insert.
b. Inspect also how far forward the seat pan insert reaches (considering the thickness of the
firewall repeat and compare step 00-s) since the firewall insert must later be in the exact
angle.
c. Abrade the bottom part of the seat pan cut, blow surface clean with compressed air, wipe
away dust/debris with acetone and allow to dry for 30 minutes.
d. Prepare some flox and apply it along the support plate and the seat pan cut (Figure 08-
001 step 1). Allow to cure for 8 hours at 56°C.
NOTE:
Support plate can be made of more pieces. Make sure its upper surface is well abraded
and that the support plate material is similar to seat pan.
e. Prepare some flox and apply it along all the seat-pan insert bonding area (along the
fuselage and newly applied support plate).
f. Install the seat pan insert and allow to cure for 8 hours at 56°C
