3.1.13
Remove the exhaust duct cap Figure 1 [20] from the union Figure 1 [21].
3.1.14
Aircraft pre SB 71-012:
3.1.14.1
Remove and discard the lockwire from the blanking cap Figure 1 [19].
3.1.14.2
Remove the blanking cap Figure 1 [19] from the wash ring Figure 1 [18].
3.1.14.3
Connect the wash rig to the wash ring Figure 1 [18].
3.1.15
Aircraft post SB 71-012:
3.1.15.1
Remove the protective cap Figure 2 [1] from the compressor wash coupling Figure 2 [2].
3.1.15.2
Connect the engine wash rig to the compressor wash coupling Figure 2 [2] with the Compressor wash
rig fitting (Pt.No. T71-025).
3.1.16
Remove the safety clip and close the circuit breaker:
−
STARTER (ESSENTIAL BUS).
3.2
CAUTION
OBEY THE STARTER MOTOR OPERATION LIMITS. THIS WILL HELP PREVENT DAMAGE TO
THE STARTER MOTOR.
Procedure
3.2.1
Energize the aircraft electrical system, refer to AMM 12-B-24-00-00-00A-901A-A.
3.2.2
Do the dry motor of the engine, refer to AMM 12-B-71-00-00-00A-901A-A. When the Ng increases to
5% operate the wash rig to supply the wash solution to the engine at a rate of 7,6 to 11,3 liter/min (2 to
3 gal/min).
3.2.3
Use the chronograph in the cockpit to measure the time of the operation.
3.2.4
Stop the starter motor after 30 seconds.
3.2.5
When the Ng decreases to 5% stop the supply of wash solution to the engine.
3.2.6
Let the wash solution stay in the engine for between 15 and 30 minutes.
3.2.7
Do the dry motor of the engine, refer to AMM 12-B-71-00-00-00A-901A-A. When the Ng increases
to 5% operate the wash rig to supply half of the rinse solution to the engine at a rate of 7,6 to 11,3
liter/min (2 to 3 gal/min).
3.2.8
Use the chronograph in the cockpit to measure the time of the operation.
3.2.9
Stop the starter motor after 30 seconds.
3.2.10
When the Ng decreases to 5% stop the supply of rinse solution to the engine.
3.2.11
Do Step 3.2.7 thru Step 3.2.10 again.
3.2.12
If a water/methyl alcohol solution was used do a dry motor of the engine, refer to AMM 12-B-71-00-00-
00A-901A-A.
3.2.13
De-energize the aircraft electrical system, refer to AMM 12-B-24-00-00-00A-901A-A.
3.3
Close Up
3.3.1
Open and install a Safety clip - Circuit breaker hold open (Pt.No. T12-030) on this circuit breaker:
−
STARTER (ESSENTIAL BUS).
3.3.2
Aircraft pre SB 71-012:
3.3.2.1
Disconnect the wash rig from the wash ring Figure 1 [18].
3.3.2.2
Install the blanking cap Figure 1 [19] on the wash ring Figure 1 [18].
3.3.2.3
Torque the blanking cap Figure 1 [19] to between 12,4 and 13,5 Nm (110 and 120 lbf in).
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-71-00-00-00A-250A-A
UNCLASSIFIED
2021-12-04 Page 6
