Vulcanair S.p.A.
Service Bulletin No. VA-03 Rev.1
First issue dated 09 October 2017
Rev.1 dated 08 January 2019
Page
12
of
19
86.
Route the Rear Cable Assy p/n 8393-409 (item 9) throughout the Tow Hook Glider Welded
Assembly p/n 8393-401, leaving the concerning terminal out of the tow bar for subsequent
installation to the Hook Support Welded Assembly p/n 8393-403 (item 2).
87.
Route the Rear Cable Assy p/n 8393-409 (item 9) through the bracket previously installed in
correspondence of the fuselage frame No.3; install the grommet p/n MS35489-4 to the bracket
hole before routing the cable.
88.
Install the Front Cable Assy p/n 8393-408 (item 11) to the Cable Support Welded Assy p/n
8393-405 (item 15, previously installed to the fuselage ventral skin), using screw p/n AN24-
11A, washer p/n NAS1149F0432P and nut MS21083N4. Torque the nut to [0.86÷0.94] kgm.
89.
Route the Front Cable Assy p/n 8393-408 (item 11) through the bracket previously installed in
correspondence of the fuselage frame No.1; install the grommet p/n MS35489-4 to the bracket
hole before routing the cable.
90.
Temporarily connect the front with the rear cables (respectively p/n 8393-408 and p/n 8393-
409) using the turnbuckle p/n MS21251-5S.
91.
On workbench, drill the Hook Support Welded Assembly p/n 8393-403 (item 2) to Ø6.35H8
where the rear cable assy p/n 8393-409 is to be installed.
92.
Put in place the Hook Support Welded Assembly p/n 8393-403 (item 2) and install the Rear
Cable Assy p/n 8393-409 (item 9) using the bolt p/n AN4-14A, the washer p/n
NAS1149F0432P and the nut p/n MS21083N4. Torque the nut to [0.86÷0.94] kgm.
93.
On workbench, referring to DWG R.0550, carry out the cut-out on the access panel p/n 5207-
003, previously removed from the ventral side of fuselage rear cone.
94.
Put in place the access panel p/n 5207-003 between the fuselage frames No.4 and 5, and install
the clamp p/n MS21919WDG5 at the afterward attaching screw.
95.
Take the Bowden Cable Assy p/n 8395-401 (item 27), mark the external sleeve at the side
where the eye-end terminal is installed, and pull out the inner solid wire from the external
sleeve.
96.
Accommodate the Bowden external sleeve in the fuselage rear cone, and then route the side
previously marked through the access panel cut-out, the clamp and throughout the Tow Hook
Glider Welded Assy.
97.
Route the Bowden inner solid wire in the Bowden housing welded on the Hook Support Welded
Assembly p/n 8393-403 (item 2) and then push-in the Bowden inner solid wire throughout the
external sleeve, so to restore Bowden cable assy. Add grease, as required.
98.
Fit the Bowden external sleeve in the Bowden housing welded on the Hook Support Welded
Assembly (item 2).
99.
Get access onboard fuselage rear cone and fix the Bowden cable to the concerned bracket on the
fuselage frame No.4 using the clamp p/n MS21919WDG5, the spacer p/n 2.2539-6 and the bolt
p/n AN3-12A.
100.
Fix the Bowden cable to the LH stringer between the fuselage frames No.3 and 4 at the hole
previously drilled, using the clamp p/n MS21919WDG5, the bolt p/n AN3-3A, the washer p/n
NAS1149F0332P and the nut p/n MS21083N3.
