Pipistrel LSA-MRA User manual

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R
LSA Major Repair and/or
Alteration (MRA)
Doc#: MRA011-21
Rev: A00
Replaces: n/a
Date: 16.09.2021
Title or
Task Description Hard landing repair + oil thermostat addition
(MRA request received 30th June 2021)
NOTE: Any external documents referenced on this form should include revision level, issue date, and title as appropriate.
BLOCK 1 – AIRCRAFT INFORMATION (to be filled out by the manufacturer)
S/N: 891 SNM 912 LSA
Registration: N88NN
Engine time/Hobbs: 261
BLOCK 2 – OWNER INFORMATION (to be filled out by the manufacturer)
Name:
Mr Joel Garris
Address:
129 Spinnaker Mall, Marina Del Rey, 90292 California
BLOCK 3 - AIRCRAFT DATA (to be filled out by the manufacturer)
Equipment
Manufacturer
Model
Total time
since new
Total time
since overhaul
Fuselage
Pipistrel
Sinus MAX
n/a
n/a
Powerplant
Rotax GmbH
Rotax 912 UL2
n/a
n/a
Propeller
Pipistrel
VARIO D
n/a
n/a
BLOCK 4 - MRA APPROVAL (to be filled out by the manufacturer)
The Aircraft OEM confirms the
aircraft being repaired or altered
still meets the requirements of the
applicable ASTM design and
performance specification
subsequent to completion of the
repair or alteration specified in the
MRA
Date of approval:
16th September 2021
Name:
Andrej B Horvat
DISCLAIMER: It is the responsibility of the person that performs this MRA to ensure the equipment installed or item repaired functions properly and
doesn’t negatively affect any other installations/equipment close to where the MRA was performed, as this is something the manufacture cannot check.
This MRA has been generated based on the aircraft configuration data provided by the owner/requester and is to be rendered invalid if the
owner/requester doesn’t provide the manufacturer with any/all information regarding repairs/alterations performed on the aircraft prior to the issue of
this MRA. The information provided in this MRA is, by no means, task specific training and must not be considered as such.
BLOCK 5 - CONFORMITY STATEMENT - RETURN TO SERVICE (to be filled out by the customer)
I hereby certify the repair and/or alteration has been completed in accordance with this MRA and all
the referenced documents. Potentially unclear procedures have been clarified with the Aircraft OEM.
No issues were observed that might hinder return to service.
Certificate holder’s name
and address
Required level of qualification.
(to be marked by manufacturer, multiple marks indicate
any may perform the MRA)
Rating
Pilot/Owner
LSA repairman
AMT
X
Repair station
Airframe class 1
Powerplant class 1
Propeller class 1
X
Manufacturer
Other:
Return to service declaration
Certificate type and number
I, the signee and certificate holder,
hereby confirm that I meet the
minimum required level of
qualification as outlined in this
MRA, I have indicated completion
of this MRA in the aircraft’s
logbook by referencing MRA011-21
and any/all national
requirements/regulations have
been adhered to
Date
Signature
Digitally signed by
ANDREJ BERNARD
HORVAT
Reason: Engineering office
Location: Nova Gorica,
Slovenia, EU
Date: 2021/09/16 21:59
+02'00'

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LSA Major Repair and/or
Alteration (MRA)
Doc#: MRA011-21
Rev: A00
Replaces: n/a
Date: 16.09.2021
BLOCK 6 – AIRCRAFT CONFIGURATION PREREQUISITES (to be filled out by the manufacturer)
This MRA is only valid for the aircraft identified in Blocks 1 and 3, when the configuration
conforms with the following definitions. Any listed preceding MRA, Instruction or Notification must
be complied with, prior to conducting this MRA.
N/A
BLOCK 7 - PREPARATION (to be filled out by the manufacturer)
Tools:
- Hand drill
- Accurate scale for weighing resin/hardener
- Accurate thermometer that measures up to 60 deg. C
- Allen key set
- Angled sander/grinder
- Bit set
- Heat gun
- Boxcutter
- Canister or cart to drain fuel into
- Chisel
- Clean, smooth and flat table, partially covered with PVC
foil for all resin jobs
- Long nose pliers
- Cutting pliers
- Screwdriver set
- Dremel cutting bit set, Ø40 sawtooth bit, Ø57 sawtooth
bit and a drill
- Dremel tool with Ø50 mm (or similar) diamond-coated
cutting disc
- Felt tip marker
- Flat-head screwdriver
- Flexible metal ruler
- Grinding bit set
- Hand roller to fit impregnated fabric
- Torx screwdriver set,
- Vacuum cleaner
- Measuring tape,
- Oscillating multi-tool with semi-circular diamond-coated
blade
- Paint brush with short to moderately long fibers
- Pencil
- Personal protection (gloves, glasses, mask/respirator)
- Wrench set

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- Utility knife
- Scissors
- Vernier caliper
- Threaded drill bit set
- Threaded insert gun
- Torque wrench
- Transparent PVC stretch wrap
Required material:
- Masking tape (25 mm and 50 mm wide)
- White silicone,
- Coarse sandpaper (P40 or something similar)
- Double-sided tape,
- Loctite 243,
- Loctite 406,
- Loctite 648
- Self-tapping screws and Cleco fasteners
- Sandpaper grades 60, 80, 120, 240, 400, 800 and associated pads,
- Primer and adhesive foam tape,
- All the material stated in the Quotation Nr: 310009112-1
BLOCK 8 - ACCOMPLISHMENT INSTRUCTIONS (to be filled out by the manufacturer)
Applicable references:
[1] POM-VARIO-00-65-001 Pipistrel VARIO propeller
operators manual (latest revision)
[2] AMM-100-00-60-001 LSA maintenance manual (latest
revision)
[3] Sinus 891 SN 912 Firewall repair
[4] Sinus 891 SN 912 undercarriage repair
[5] Beringer Main Wheel Installation 23.3.2011
[6] https://www.youtube.com/watch?v=DbOB-Fo8VYQ
[7] SB-100-00-80-012 Throttle and choke cable replacement
[8] Pipistrel Online IPC: https://ipc.pipistrel.si/Shop/app
[9] SB-100-00-80-011_A01 Nose landing gear
inspection
[10] PI-121-71-00-001_A03 Navodila za sestavo
motorja
This repair is to be performed using sound mechanical methods. All new/replaced
components must not interfere with or hamper the operation of other assemblies/installations.
Aircraft logbooks must reflect this change and reference this MRA.

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Airplane preparation instructions:
a. Drain the fuel from the fuel reservoirs (See chapter 12 in [2]).
b. Remove the wings (See 57-10 in [2]).
c. Remove the horizontal stabilizer (See 55-10 in [2]).
d. Disconnect the throttle/choke cables (See 0:55 in [6]).
e. Disconnect the steering mechanism cables from the nose gear.
f. Remove all the firewall forward material (See chapters 61, 71, 75. 77, 78 in [2]). Set
aside any undamaged material and discard the rest.
NOTE: Take notes during the whole removal process for all the firewall forward parts, for easier
installation process.
g. Remove the doors (See 52-10 in [2]).
h. Remove the baggage compartment (See 25-50 in [2]).
i. Remove the fuel lines from under the seat pan (See [6] 44:40).
j. Detach any of the lines/hoses/components attached to the fuselage under the cabin
floor and under the baggage compartment. This will prevent them from being
damaged when the fuselage is cut.
k. Remove the damaged engine cowling brackets (P/N: 1255003)
l. Remove all the engine control cables and Bowden’s (See 0:55 in [6]).
m. Remove the Rudder pedals, pedal cables and front wheel steel wire under the cabin
(See 27-20 in [8]).
n. Make a template o the rudder pedals mounting holes in the seat pan (See Figure 12-
001). Make a template of the holes for of the pedals position springs in the fuselage
belly (Figure 00-001).
o. Perform 56-00:3.1.1. Windshield removal and 56-00: 3.1.3. Windshield support rod
gasket removal in [2].

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Figure 00-001: Example of template of the holes for of the rudder springs retaining fastening
material in the fuselage belly
p. Follow 31-10 in [2]: and remove the switch panel, instrument panel cover, instrument
panel and the instrument panel housing (For better visual presentation see 31-10 in
[8]). Make sure you mark, remove and /or secure all the cables, harneses, hoses and
connectors under all the indicating system panels [8] for easier installation.
q. Read these instructions throughout and determine which additional parts in the cabin
need to be removed for the process to run smoothly.
Figure 00-002: Example of stretch wrap protection.
NOTE: The picture above is for visual purposes only as the stretch foil is wrapped according to
each specific airplane cabin set up.
r. Protect the aircraft from dust by wrapping it in transparent stretch wrap. The only part
that should be left unprotected is the spot(s) where the repair will be done. Seal off as
much as possible. Do whatever is necessary to prevent dust from entering the cabin
during the sanding cutting steps. Be sure to cover the instrument panel with stretch
wrap as well and fill the lower openings of the instrument panel with foam (Figure 00-
002).

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s. Take measure of the distance between engine mount reinforcements on the firewall
(port and starboard side) and the fwd fuselage edge. See Figure 00-003. The
measured value will be a reference at firewall inserts installation.
t. Make a template out of a cardboard or similar material, in the shape of a firewall. Try
to pull the damaged material in its original form, place the template on the firewall
and mark all the bolts and holes on the firewall for later re-installation (See
Modification 13).
Figure 00-003: Measuring the distance between engine mount reinforcements
on the firewall and the fwd fuselage edge.
Modification 1 – FUSELAGE BELLY REMOVAL
a. Turn the aircraft upside-down.
b. Follow 32-10: 2.1.3. MLG strut removal in [2].
c. Perform steps 14 to 19 in [4].
NOTE: For torque values throughout this document refer to standard torque values stated in
20-30 in [2], u nless differently stated in this document.

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Modification 2 – AFT SEAT PAN AND SEAT BACKREST REPAIR
a. Through the hole in the fuselage belly grind/trim 3cm to each side along the crack(s)
in the aft seat pan and on the seat backrest. Grind all the way to the fibre structure
and determine the amount of the damage.
b. Blow surface clean with compressed air, wipe away dust/debris with acetone and
allow to dry for 30 minutes.
c. Inside the cabin and from the baggage compartment create support plates over the
damaged areas. Apply a 3mm airex foam (P/N 5079026) covered with resin non-
stick material (for example heavy duty brown packaging tape). Secure the foam over
the damaged area with firmly applied stretch wrap and with double sided Tesa
adhesive tape shown in Figure 02-001 part 1.
NOTE: In place of airex foam a different 3mm type of PVC foam can be used.
NOTE: Crack extend also to the area where a support plate cannot be satisfyingly applied.
There the repair will have to be run only from one side.
d. To prevent bubbles forming first apply a smaller amount of microbaloons compound
through the hole in the fuselage belly over the support plate on seat pan and on seat
backrest as shown in Figure 02-001 part 2.
e. Prepare some resin and cut the plies of 92125 ((Pipistrel P/N 5071006) 0°/90° and
top layer 1x 92110 (Pipistrel P/N 5071002) 0°/90° so that they extend beyond the
damaged and grinded area by 2 cm.
f. Apply the plies and resin over the cracks and damaged area on the seat pan and on
the seat backrest from the hole in the fuselage belly (Figure 02-001 part 2). Allow to
cure for 8 hours at 56°C.
g. Sand the repair area to make it flush with the rest of the surface (Figure 02-001 part
3).
h. Turn the airplane right side up. Remove the support plate and sand the inside the
cabin and baggage compartment repair surfaces.
i. From inside the cabin and the baggage compartment, apply 1:50 taper to the edges
and sand until whole repair surface (Fuselage edges, microbaloons and inner layers)
are smooth (Figure 02-001 part 3).
j. Blow surface clean with compressed air, wipe away dust/debris with acetone and
allow to dry for 30 minutes.
k. Prepare some resin and according to the damage on the airplane bottom, cut the
plies according to the repair laminate plan.

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Seat pan laminate plan from inner ply to outer:
1x 92125 (Pipistrel P/N 5071006) 45°/45°
1x 92110 (Pipistrel P/N 5071002) 45°/45°
1x GG200P (Pipistrel P/N 5072006) 45°/45°
1x KK300T (Pipistrel P/N 5073003) 45°/45°
1x 92110 (Pipistrel P/N 5071002) 45°/45°
Seat backrest laminate plan from inner ply to outer:
1x 92110 (Pipistrel P/N 5071002) 45°/45°
1x Kevlar 200 g/m2 twill (Pipistrel P/N: 5073002) 45°/45°
1x C160 (8048) – GG160P (Pipistrel P/N: 5072005) 45°/45°
1x 92125 (Pipistrel P/N 5071006) 45°/45°
Figure 02-001: Seat pan and seat backrest repair process.

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l. Apply the plies and resin over the tapered and sanded area on the seat pan and on
the seat backrest from the cabin and baggae compartment side (Figure 02-001 part
3). Allow to cure for 8 hours at 56°C.
m. Sand all sides of the repair area and make them flush with the rest of the surface. On the
bottom side of the sat pan and on the seat backrest a light bulge can be left for additional
material strength.
n. Blow surface clean with compressed air, wipe away dust/debris with acetone and allow to
dry for 30 minutes.
o. From the cabin side of the seat pan and from the baggage compartment side apply rough
polyester kit and grind/sand down. Apply fine polyester kit and grind/sand down using
sandpaper no finer than P600.
p. Paint the newly processed cabin side seat pan surfaces with FIAT grey 025A acrylic paint
(Figure 02-001 part 4).
q. Sand down with P2000 sandpaper and polish with polishing disk.
Modification 3 – FUSELAGE BELLY INSTALLATION
a. Perform steps 20 to 53 in [4].
Modification 4 – UNDERCARRIAGE STRUT INSTALLATION
NOTE: Selection of appropriate drill bits is critical in order to drill the main holes in the
undercarriage strut. Please refer to the diagram in Figure 04-002 entitled “Identification of drill
geometry” below. Be sure to select drill bits with a lip relief angle that is as small as possible
(<1o). This will ensure gradual feed and prevent wobbling of the drill bit. This will also prevent
the strut’s structure from being damaged. Feel free to sharpen/adjust the drill bit/lip relief
angle if need be.
a. Begin by resting the fuselage right side up on the strut and making sure the strut is
oriented correctly (see Figure 04-002).
b. Center it longitudinally and laterally using some cardboard spacers. Once centered,
use some tape or polyester resin to fasten it to the fuselage temporarily and ensure it
won’t shift out of place.
c. Drill the fore port and aft starboard holes using an 8 mm drill bit and the holes
already drilled in the seat pan as a guide. Then temporarily fasten the strut to the
fuselage through these holes using two M8 bolts.
d. Continue by drilling the aft port and fore starboard holes using a 10 mm drill bit.
e. Apply silicone around the newly drilled holes on the undercarriage strut (Figure 04-
001).

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Figure 04-001: White silicone application and M14 nuts, hexagon socket bolts and
conical washers installation.
f. Apply to M10 bolts to the holes drilled earlier and apply some Loctite 243 to the nut
thread. Then remove the two M8 bolts from before. Ream the two 8 mm holes with
the 10 mm drill bit, fit the last two M10 bolts and once again apply some Loctite 243
to the nut thread. Torque to 45 Nm (See 32-10 in [8] and Figure 04-001).
Figure 04-002: Identification of drill geometry and proper undercarriage strut
orientation.
g. Run the brake hoses from the undercarriage strut through the holes in the fuselage.
h. Prepare the bottom cover plate by placing it in place and determine the right length.
Cut the cover plate with the scissor (Figure 04-003 step 1).
i. Apply primer on the cover plate outer edge, let it dry and apply the double-sided self-
adhesive tape (Figure 04-003 step 2).
j. Install the cover plate into previously determined position. Mind the alignment (Figure
04-003 step 3).
k. Tape the edges with white self-adhesive tape. Carefully cut the redundant tape on the
corners (04-004 step 4).

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Figure 04-003: Bottom cover preparation.
l. Drill ø3.2mm holes on all four corners and in the middle too. 6 holes in total (Figure
04-004 step 5).
m. Drill a M4 thread into the ø3.2mm holes with tap drill & taps bit and fasten the M4
button bolts (Figure 04-004 step 5).
Figure 04-004: Bottom cover installation.

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Modification 5 – BERRINGER MAIN UNDERCARRIGE WHEELS INSTALLATION
a. Reinstall the wheel/brake system according to [5].
CORRECTION: Be sure to tighten the M14 nut at the end of the wheel axle to 55 Nm instead
of the 40 Nm indicated on page 2 of [5]
b. Run the brake lines down the hole in the strut and connect them to the hydraulics
connector.
c. Temporarily place the fairings on the wheel and fix them to the wheel fairing spacer
(Figure 05-002).
d. Correctly position the fairing so that adequate clearance exists between the it and the
strut. This will prevent it from getting damaged when landing. The fairing must be aligned
with the longitudinal axis of the aircraft, and the aft tip of the fairing must lay at 200-220
mm from the ground (Figure 05-002). Once the positioning is satisfactory, temporarily fix
the fairing in place with some adhesive tape.
e. Obtain the fixing hole position as indicated in the picture (Figure 05-002). Mark the hole
positions with a pen and drill the holes through the fairing/plate at the same time, using a
2 mm drill bit. Be careful not to damage the wheel while drilling.
Figure 05-001: Alignment of the support plates and fairing position.
f. Remove the fairings and enlarge the holes with a larger Ø5,5 mm drill bit. Enlarge the
holes in the plates to Ø7 mm.
g. Install the four threaded insert nuts (P/N: 5017011) on each plate, applying Loctite 648
first.
h. Install the fairings, fixing them to the plates with four M5 bolt´s and washers (P/N:
5010228 and P/N: 5012026), and with a M6 hex head bolt and washer (P/N: 5010236
and P/N: 5012040) to the spacer. Apply Loctite 243 on the M6 bolt.

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Figure 05-002 Whell fairing alignment and installation.
Modification 6 – FIREWALL REMOVAL
a. Keep the aircraft in right side up position
b. Perform steps 12 to 16 in [3].
Modification 7 –SEAT PAN INSERT REMOVAL AND FWD FUSELAGE BELLY
REPAIR.
a. Using seat pan insert (Figure 07-001) measure and draw the line on the seat-pan
where the cut on the needs to be made (Figure 07-002).
NOTE: Cut made in the seat-pan needs to be as accurate as possible for the seat-pan insert
to fit well. Manufacturing a template of the seat-pan insert can greatly reduce the margin of
error.
Figure 07-001: Seat pan insert.
b. Cut along the seat-pan outer edge (Figure 07-002) and remove the cut-out.
c. Detach the front seat-pan remains from the fuselage with chisel.
NOTE: If at any point the removal requires the amount of force that could damage the
fuselage grind and sand the seat-pan remains away.
d. Trim/Grind away all the damaged front edge of the fuselage belly.

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Figure 07-002: Seat pan cut out.
e. Grind/Trim 3cm to each side along the crack/damage in the fwd fuselage belly. Grind
all the way to the fibre structure and determine the amount of the damage. Lightly
abrade the fuselage belly 2 cm along all the trimmed edge.
f. Lightly abrade the fuselage on the seat-pan bonding area.
g. Lightly abrade also the seat pan 2 cm aft of the cut made in step b.
h. Blow surface clean with compressed air, wipe away dust/debris with acetone and
allow to dry for 30 minutes.
i. Create support plate(s) over the bottom of the damaged area. Apply a 3 mm airex
foam (P/N 5079026) covered with resin non-stick material (for example heavy duty
brown packaging tape).
j. Secure the foam over the damaged area with firmly applied stretch wrap and with
double sided Tesa adhesive tape shown in Figure 07-003 Step 1.
NOTE: In place of airex foam a different 3mm type of PVC foam can be used.
k. To prevent air bubbles forming first apply a smaller amount of microbaloons compound
over the support plate (Figure 07-003 Step 2).
NOTE: The airex foam has to be firmly pressed to the fuselage and has to form the crease in the
fwd fuselage belly.
l. Prepare some resin and cut the plies of 92125 (Pipistrel P/N 5071006) 0°/90° and top
layer 1x 92110 (Pipistrel P/N 5071002) 0°/90° so that they extend beyond the damaged
area by 2cm inside the fuselage (Figure 07-003 Step 2).

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NOTE: Make sure the length of the newly formed fwd fuselage belly is exactly the length of the
original.
m. Apply the plies and resin over the crack and damaged area on the front edge of the
fuselage belly. Allow to cure for 8 hours at 56°C (Figure 07-003 step 2).
n. Sand the inside repair area to make it flush with the rest of the surface.
o. Turn the airplane upside down. Remove the support plate and sand the outside repair
surfaces. Apply 1:50 taper to the fuselage edges and sand until whole repair surface
(Fuselage edges, microbaloons and inner layers) is smooth (Figure 07-003 step 3).
p. Blow surface clean with compressed air, wipe away dust/debris with acetone and allow to
dry for 30 minutes.
q. Prepare some resin and according to the damage on the airplane bottom, cut the plies
according to the fuselage repair laminate plan.
NOTE: The first repair ply laid up is always the biggest. Each ply that follows should be 7 mm
smaller than the last. The smallest ply should cover an area with a radius of at least 20 mm
around the damage.
Figure 07-003: Fuselage front edge belly repair

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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

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NOTE: Make sure the alignment between the seat pan and seat pan insert matches as much as
possible.
g. Sand along the bonding area between the seat pan and seat pan insert, apply 1:50 taper
to both seat pan sides edges and sand until whole repair surface is smooth (Figure 08-
001 step 3). Blow surface clean with compressed air, wipe away dust/debris with acetone
and allow to dry for 30 minutes.
h. Prepare some resin and, cut the plies that reach 3 cm over the seat pan and seat pan
insert bonding line and extends all long the bonding line. Cut plies according to the seat
pan repair laminate plan.
Seat pan laminate plan from inner ply to outer:
1x 92125 (Pipistrel P/N 5071006) 45°/45°
1x 92110 (Pipistrel P/N 5071002) 45°/45°
1x GG200P (Pipistrel P/N 5072006) 45°/45°
1x KK300T (Pipistrel P/N 5073003) 45°/45°
1x 92110 (Pipistrel P/N 5071002) 45°/45°
NOTE: The first repair ply laid up is always the biggest. Each ply that follows should be 7 mm
smaller than the last. The smallest ply should cover an area with a radius of at least 20 mm
around the damage.
i. Apply resin and all the plies from the seat pan repair laminate plan over the seat pan and
seat pan insert bonding line as shown in Figure 08-001 step 3. Allow to cure for 8 hours
at 56°C.
j. 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.
k. Apply rough polyester kit and grind/sand down.
l. Apply fine polyester kit and grind/sand down using sandpaper no finer than P600.
m. Paint the newly processed seat pan surfaces with FIAT grey 025A acrylic paint.
n. Sand down with P2000 sandpaper and polish with polishing disk.

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Figure 08-001: Seat pan insert repair.
Modification 9 – WINDSHIELD REPLACEMENT and CABIN SUPPORT ASSEMBLY
WITH BUSHINGS REPAIR
a. Assemble the cabin support assembly with bushing levelling tool (Figure 09-001) as
shown in the Figure 09-002
Figure 09-001: Cabin support assembly with bushing levelling tool (Pipistrel P/N:
1190613).

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b. Determine the amount, location and direction of the damage on the cabin support
assembly and accordingly apply force in the opposite direction by tightening the central
bolt.
NOTE: First bring the cabin support assembly with bushing to a levelled position and then apply
slightly more force. The rod needs to be slightly bent over its limit or will otherwise return to its
previous position.
Figure 09-002: Cabin support assembly and bushing levelling process.

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c. Release the tools force and inspect if the cabin support assembly with bushing rod is
levelled. Inspection of the cabin support assembly with bushing rod is run by looking
through the bushings (Figure 09-003). Rod is levelled when during the inspection whole
circle of the other side of the tube is visible (Figure 09-003).
d. Repeat step c and d with required force in needed directions until the cabin support
assembly with bushing rod is levelled.
NOTE: Inspect the bushing rod from outside for any cracks or spaces between fuselage and
bushing rod. Repair with a small amount of flox.
NOTE: Inspect the bushing rod reinforcement from inside the cabin with a tap test (See 51-10:
2.2. in [2]). Run a tap test with a smaller metal rod and if any hollow sounds can be heard the
fuselage has been damaged. Please contact [e-mail] for information
about how to proceed.
e. With all new parts perform 56-00: 3.1.4. Windshield support rod gasket installation and
56-00:3.1.2. Windshield installation in [2].
Figure 09-003: Inspection of the cabin support assembly with bushing rod.
Modification 10 – FIREWALL INSERT INSTALLATION
a. Perform steps 48 to 55 in [3].
NOTE: Make sure the distance between engine mount reinforcements on the firewall (port and
starboard side) of the newly installed firewall insert and the fwd fuselage edge is the same as the
distance measured in step 00-s (See Figure 00-003).
NOTE: Make sure as much flox as possible remains on the bonding area between the fuselage
and the firewall insert.
b. Perform steps 56 to 67 in [3].