Vulcanair S.p.A.
Service Bulletin No. VA-03 Rev.1
First issue dated 09 October 2017
Rev.1 dated 08 January 2019
Page
11
of
19
70.
Get access to the fin front spar, if not already done, by removing the fin nose rib No.0, and
referring to DWG R.0550, drill the fin front spar to Ø3.2mm diameter hole.
71.
Deburr all the holes and clean all reworked surfaces with Methyl-Ethyl-Ketone or equivalent
cleaning solvent; treat them with Alodine 1200 (MIL-C-5541) and then with Epoxy Primer
(MIL-PRF-23377).
72.
Referring to DWG R.0550, install the tie mount p/n NV7.003-171A by using the rivet p/n 1661-
0410 and washer p/n NAS1149FN632P.
73.
Referring to DWG R.0550, route the cam wiring harness p/n 8391-060 (item 34) through the
fin, fixing its position to the tie mount, previously installed, by using the tie wrap p/n
NOR7.701-1E.
74.
Connect the CAM PWR JACK belonging to wiring harness p/n 8391-060, to the red colored
jack. Connect the CAM VIDEO JACK belonging to wiring harness p/n 8391-060, to the yellow
colored jack.
75.
Route the cam wiring harness p/n 8391-060 throughout the fuselage up to the rear side of the
instrument panel, fixing it with the existing wiring harness running along the aircraft.
76.
Referring to DWG R.0550, install the cam switch (provided with Cam Switch Wiring Harness
p/n 8391-061, item 55 of Kit SB_VA-03/A, item 56 of Kit SB_VA-03/B) to the instrument
panel in the position labelled “CAM”.
77.
For V1.0 aircraft up to s/n 1019, referring to DWG R.0550, install the circuit breaker in the
position labelled “CAM”, and connect the cable P152A24 belonging to wiring harness p/n
8391-061 Rev.A to the CAM circuit breaker.
78.
For V1.0 aircraft from s/n 1020 onwards, referring to DWG R.0550, install the fuse holder p/n
NV7.003-177A, and the fuse p/n NV7.003-177B-10, in the position labelled “CAM 1A” on the
bottom side of the breaker panel, and connect the cable P152A24 belonging to wiring harness
p/n 8391-061 Rev.B to the CAM fuse.
79.
Connect the cable P153A24N belonging to wiring harness p/n 8391-061 to the nearest airframe
ground point.
80.
Insert terminal belonging to cable T29B24SH into the existing connector J36 (located behind
the instrument panel), in accordance with the EWD p/n 8391-040 (inserted into DWG R.0550).
81.
Connect wiring harness p/n 8391-060 to wiring harness p/n 8391-061 through connectors
J40/P40.
82.
Ensure that wiring harness p/n 8391-060 and 8391-061 are properly routed and fixed.
83.
Ensure that all the electrical connections have been properly carried out in accordance with
EWD p/n 8391-040 and 8391-041 (inserted into DWG R.0550).
84.
Put in place the tail fairing, comprehensive of Quick Cam, and connect the cam wiring harness
p/n 8391-060 (item 34) to the quick cam wiring harness through the splices PWR CAM and
GND CAM. Re-connect the rear fuselage position light, as previously.
85.
Install the tail fairing to the fuselage rear cone, as previously. Interpose a film of single-
component polyurethane sealant “POLIBOND” manufactured by SARATOGA, or other
equivalent product, during installation.
