preventative. Put the installation tools Figure 1 [30] and Figure 1 [31] in the ends of the short bolt
Figure 1 [18].
2.1.13
Install the rear bottom short bolt Figure 1 [18] and the torlon plates Figure 1 [19] through the wing
and fuselage fittings Figure 1 [20]. Use only hand force to install the short bolt Figure 1 [18]. Remove
the installation tools Figure 1 [30] and Figure 1 [31] from the short bolt Figure 1 [18]. If the short
bolt Figure 1 [18] cannot be fully installed by hand force, it is permitted to use the bolt removal tool
Figure 1 [28] (with hand force only to turn the knurled nut) to fully install the short bolt.
2.1.14
Use the hoist as necessary to carefully align the forward bottom bushes in the wing fittings and the
fuselage fittings.
2.1.15
Apply a layer of Corrosion preventive (Pt.No. P04-039) to the outer surface of the long bolt
Figure 1 [11]. Make sure the outer surface of the bolt is completely covered with the corrosion
preventative. Put the installation tools Figure 1 [30] and Figure 1 [31] in the ends of the long bolt
Figure 1 [11].
2.1.16
Install the forward bottom long bolt Figure 1 [11] and the torlon plates Figure 1 [13] and Figure 1 [14]
through the wing and fuselage fittings Figure 1 [10]. Use only hand force to install the long bolt
Figure 1 [11]. The torlon plates Figure 1 [13] and Figure 1 [14] have a different thickness, make sure
they are installed correctly. Remove the installation tools Figure 1 [30] and Figure 1 [31] from the long
bolt Figure 1 [11]. If the long bolt Figure 1 [11] cannot be fully installed by hand force, it is permitted to
use the bolt removal tool Figure 1 [28] (with hand force only to turn the knurled nut) to fully install the
long bolt.
2.1.17
Remove all the unwanted corrosion preventative material from the wing and fuselage fittings.
2.1.18
Install the forward top bolt Figure 1 [1] that was removed during the wing removal, washer Figure 1 [2],
washer Figure 1 [3] with the chamfer towards the bolt Figure 1 [1] head, washers Figure 1 [3] and
Figure 1 [2], and the nut Figure 1 [6]. Torque the nut Figure 1 [6] to 50 Nm (443 lbf in). Remove the
nut Figure 1 [6], washers Figure 1 [3], Figure 1 [2] and the bolt Figure 1 [1]. Discard the used bolt
Figure 1 [1].
Note
is a tension bolt which can only be torque tightened once. It is used in the above
step as a tool with a high torque value to correctly position the bushes that are not bonded. The bolt is
then removed and discarded.
2.1.19
Make sure the flange of the bushes have moved to touch the wing/fuselage fitting as shown by
Section A-A Fig. 1 .
2.1.20
Use Grease (Pt.No. P04-029) to lubricate the parts. Install the new forward top bolt Figure 1 [1],
washer Figure 1 [2], washer Figure 1 [3] with the chamfer towards the bolt Figure 1 [1] head, washers
Figure 1 [3] and Figure 1 [2] and the new nut Figure 1 [6]. Torque the nut Figure 1 [6] to between 24
and 25,6 Nm (213 and 226 lbf in) plus the nut friction torque.
2.1.21
Use Grease (Pt.No. P04-029) to lubricate the parts. Install the new forward bottom bolt Figure 1 [7],
washers Figure 1 [8] and Figure 1 [9] with the chamfer towards the bolt head, washers Figure 1 [9] and
Figure 1 [8], and the new nut Figure 1 [12]. Torque the nut Figure 1 [12] to between 14,4 and 16,8 Nm
(128 and 149 lbf in) plus the nut friction torque.
2.1.22
Use Grease (Pt.No. P04-029) to lubricate the parts. Install the new rear bottom bolt Figure 1 [21],
washer Figure 1 [17] with the chamfer towards the bolt Figure 1 [21] head, washers Figure 1 [17] and
Figure 1 [16] and the new nut Figure 1 [15]. Torque the nut Figure 1 [15] to between 14,4 and 16,8 Nm
(128 and 149 lbf in) plus the nut friction torque.
2.1.23
If a new wing is installed, release the lift force from the sling and carefully lower the jack that supports
the wing until the wing is not supported on the jack. If you install the wing that was removed, go to
Step 2.1.25.
2.1.24
Use a feeler gage to measure the gap between the fuselage frame 24 and the wing rear spar:
PC-12/47E AMM Doc No 02300, ISSUE 01 REVISION 26 MSN 545, 1001-1719,
1721-1999
12-B-AM-00-00-00-I
UNCLASSIFIED
Effectivity: All
12-B-57-00-00-00A-720B-A
UNCLASSIFIED
2021-12-04 Page 5
