Name
Identifications/References
Qty
Reference
Remark
Locking clips
CSN 27-20-00-01-065
4
Retaining ring
CSN 55-40-00-02-110
1
Washer
CSN 55-30-00-01-145
1
Washer
CSN 55-40-00-01-065
1
Safety Conditions
Note
To identify the AGE and tools used in this procedure refer to the list of AGE and tools, TEM
12-B-00-00-00-00A-
060A-A
.
Procedure
1
General
The aircraft tail may hit the ground when loading the aircraft without the tail support stand in position. As
a consequence of a tail-down incidence, the rear fuselage and rudder mounting structure require a detailed
inspection.
This inspection procedure gives the inspection procedure for aircraft that have experienced a tail-down
incidence when on the ground.
To find, identify and make an estimate of the damage to the aircraft structure, refer to SRM 12-B-51-10-00-
00A-041A-A.
For small damage repairs and approved repairs to the aircraft structure and to composite parts, refer to SRM
12-B-51-70-00-00A-041A-A.
Even if there is no damage, do the functional test of the rudder control system, refer to AMM 12-B-27-20-00-
00A-903A-A.
2
During the Inspection Procedure
If you find damage during this procedure, you must contact Pilatus Aircraft Ltd.
3
Preparation
3.1 Lift the aircraft on jacks, refer to AMM 12-B-07-10-00-00A-901A-A.
3.2 Make sure the flaps are set to 0°.
3.3 Open and install a Safety clip (circuit breaker hold open) (Pt.No. T12-030) on this circuit breaker:
−
A/P SERVO (AVIONIC 1 BUS)
3.4 Put up a Warning sign (DO NOT OPERATE THE FLIGHT CONTROLS) (Pt.No. Local supply) in the flight
compartment.
3.5 Remove the horizontal stabilizer fairing and the rear vertical stabilizer fairing (32CT).
3.6 Open access panels 11AL, 31AB, 32AL, 32AR, 32CL and 32CR.
4
Procedure
4.2 Loosen the turnbuckles Figure 1 [2].
4.3 Remove the rudder from the aircraft, refer to AMM 12-B-55-40-01-00A-920A-A.
PC-12/47E AMM Doc No 02300, ISSUE 01 REVISION 27 MSN 545, 1001-1719, 1721-1942
12-B-AM-00-00-00-I
UNCLASSIFIED
Effectivity: All
12-B-05-50-11-00A-282A-A
UNCLASSIFIED
04.12.2021 Page 3