Pilatus PC-12/47E MSN-1001-UP, Руководство по обслуживанию

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4.4 Remove the two cotter pins Figure 2 [8] from the control cables Figure 2 [9]. Discard the cotter pins.
4.5 Disconnect the rudder cables Figure 2 [9] from the cable quadrant Figure 2 [2].
4.6 Remove the cotter pin Figure 2 [7] nut Figure 2 [6] bolt Figure 2 [1] and washer Figure 2 [2].
4.7 Remove the cable quadrant Figure 2 [3]. Discard the nut Figure 2 [6], bolt Figure 2 [1] and washer
Figure 2 [2].
4.8 Remove the bearing Figure 2 [4] from the cable quadrant Figure 2 [3]. Discard the bearing Figure 2 [4]
and the retaining ring Figure 2 [5].
4.9 Remove the nuts Figure 3 [7] washers Figure 3 [6] bolts Figure 3 [2] and bonding leads Figure 3 [3].
Remove the rudder stop fitting/assembly Figure 3 [1].
4.10 Disassemble the rudder stop Figure 3 [15].
4.11 Remove the hinge bracket Figure 3 [4].
4.12 Remove the hinge support fitting Figure 3 [5]. Discard the bolt Figure 3 [12], nut Figure 3 [10] and
washer Figure 3 [11].
5 Required Inspection
Note
NDT inspection (eddy current or dye penetrant) is used to detect surface cracks in metals. No cracks
are allowed. If cracks are found, replace the component or contact Pilatus. For information on the NDT
inspection procedure, refer to SRM
12-B-51-00-00-00A-353A-A .
Note
Crack inspection by NDT (eddy current or dye penetrant) is required for specific items as identified with
(NDT) in the following procedure. In addition to the specific NDT inspection all items must have a visual
inspection. If a crack is suspected from visual inspection, do the NDT inspection to confirm the result.
Note
If composite material has minor damage, such as cracks, scratches, surface delamination and/or
abrasion, use the standard repair procedures given in SRM
12-B-51-70-04-00A-663A-A .
5.1 Examine the cable quadrant and bearing housing for cracks (NDT) , deformation and/or distortion.
5.2 Examine the rudder stop fitting/assembly Figure 3 [1] for cracks (NDT) or any damage.
5.3 Examine the rudder for signs of cracks or deformation.
5.4 Examine the hinge bracket Figure 3 [4] for signs of cracks (NDT) and/or distortion.
5.5 Examine the hinge support fitting Figure 3 [5] for signs of cracks (NDT) and/or distortion.
5.6 Examine the strakes for damage. Use the SRM 12-B-53-30-20-00A-664A-A to repair any damage or
to replace the strakes.
5.7 Examine the internal structure where the strake spigot beams attach to the fuselage frames, FR 38 to
FR 40. Check for cracks and/or deformation.
5.8 Examine the lower fuselage area for damage. Examine the antenna(s) to make sure they did not hit
the ground and do not have damage.
5.9 Examine the sidewalls of the rear fuselage structure and the rear fuselage at frame 43 for signs of
cracks and/or deformation.
5.10 Examine the top hinge bracket Figure 4 [3] for cracks (NDT), deformation and/or displacement.
Examine the bearing Figure 4 [4] and the attachment of the top hinge bracket to the structure.
5.11 Examine the vertical stabilizer spars for cracks (NDT) and/or deformation in the attachment area at
frame 43.
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-05-50-11-00A-282A-A
UNCLASSIFIED 2021-12-04 Page 4