Vulcanair S.p.A.
Service Bulletin No. VA-03 Rev.1
First issue dated 09 October 2017
Rev.1 dated 08 January 2019
Page
5
of
19
Part A - Aircraft preparation.
1.
Place the aircraft in a suitable working area for the operations to be carried out.
2.
Turn OFF all electrical switches, disconnect the battery cables (negative cable first) and the
external power unit (if connected), then ground the aircraft.
3.
Carefully remove the pilot and co-pilot seats.
4.
Remove the bench-seat.
5.
Remove the cabin moquette.
6.
Un-rivet and remove the LH cabin floor panel p/n 5750-001 near the rudder pedal.
7.
Un-rivet and remove the remaining cabin floor panels in order to gain access at the working
area under the cabin floor.
8.
Get access to the baggage compartment area and remove the inspection cover p/n 5754-001, and
the panel at fuselage frame No.2 (p/n 8203-016) to gain access to the internal fuselage rear
cone.
9.
Get access to the bottom side of the fuselage rear cone, and remove the access panel p/n 5207-
003 of the inspection hatch located between the fuselage frames No.4 and 5.
10.
Remove the tail fairings at the fuselage rear cone, after disconnecting the rear fuselage position
light.
11.
Remove the fairing at the fin forward base.
12.
Remove the fin rib nose no.0 p/n 5141-401 from the fin leading edge taking particular care to
not damage the flight control cables.
13.
Remove the screws attaching the mooring hook at the fuselage frame No.6, then remove the
mooring hook from the aircraft.
14.
Remove any trace of sealant and clean all the surfaces with Methyl-Ethyl-Ketone, or equivalent
cleaning solvent. If necessary, treat the surfaces with Alodine 1200 (MIL-C-5541) and then
with Epoxy Primer (MIL-PRF-23377).
15.
Tag a store all the removed items in a reserved area for their subsequent reinstallation.
16.
Proceed with the following Part B.
Part B - Installation of Kit SB_VA-03/A, or SB_VA-03/B, for glider towing.
1.
Get access to the aircraft cabin and referring to DWG R.0550, fit the Lever Support Welded p/n
8393-406 (item 35) to the fuselage truss.
2.
Fix the position of the Lever Support Welded on the fuselage truss as per instructions within
DWG R.0550, and tight by using bolt p/n AN4-12A, nut p/n MS21083N4 and washer p/n
NAS1149F0432P. Torque the nuts to [0.86÷0.94] kgm.
3.
Install the Lever Assy p/n 8393-402 (item 28) to the Lever Support Welded p/n 8393-406 (item
35), by using bolt p/n AN4-7A, washer p/n NAS1149F0432P, nut p/n MS21083N4 and
interposing the spacer p/n 8395-010 (item 39). Torque the nuts to [0.86÷0.94] kgm.
