Vulcanair S.p.A.
Service Bulletin No. VA-03 Rev.1
First issue dated 09 October 2017
Rev.1 dated 08 January 2019
Page
7
of
19
20.
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).
21.
Install the bracket p/n NOR7.077-1 to the fuselage frame No.4 by using blind rivets p/n 1661-
0410.
22.
Get access to the fuselage truss in the cabin. Referring to DWG R.0550, fit the clamp p/n 8395-
004 (item 16) to the fuselage truss and interpose the shim p/n 8395-005 (item 20) between the
clamp and the ventral skin. Temporarily fix them in place as per instructions within DWG
R.0550 and use the clamp with the shim as a drilling mask for the ventral skin.
23.
Remove the clamp with the shim and drill the fuselage ventral skin to Ø4.82mm diameter holes
as per instructions within DWG R.0550.
24.
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).
25.
Put in place the clamp p/n 8395-004 to the fuselage truss and interpose the shim p/n 8395-005
between the clamp and the ventral skin (onboard side).
26.
Put in place the Cable Support Welded Assy p/n 8393-405 (item 15) to the fuselage ventral skin
(outboard side), then install it definitively to the fuselage and to the internal clamp and shim by
using 6 (six) screws p/n AN23-10A, washers p/n NAS1149F0332P and nuts p/n MS21042-3.
Torque the nuts to [0.48÷0.52] kgm.
NOTE
Interpose a film of Single-component polyurethane
sealant “POLIBOND” manufactured by SARATOGA
or other equivalent product between the faying
surfaces of the cable support welded and the fuselage
skin, then carry out the installation.
NOTE
During installation, impregnate the shank of the
bolts with a film of corrosion inhibitive compound
Mastinox D40 (Specification MIL-PRF-8116C), or
equivalent.
27.
Referring to DWG R.0550, put temporarily in place the bracket p/n 8395-015 (item 13) at the
aircraft center line in correspondence of fuselage frame No.1, unriveting the existing two
attaching items.
28.
Drill the ventral fuselage skin with the fuselage lower frame No.1 and the bracket to Ø3.2mm
diameter hole, as per instructions within DWG R.0550.
29.
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).
30.
Referring to DWG R.0550, install the bracket p/n 8395-015 to the fuselage ventral skin by using
blind rivets p/n 4801-0407.
