Reference airspeed
Airspeed indication
CAS (kts)
TAS (kts)
Mach
Display
IAS (kts)
TAS (kts)
Mach
150
150
NIV
PFD ADI
151 ±2
PFD HSI
151 ±8
PFD HSI
NIV
Thales ESIS
151 ±2.5
NIV
L3 ESIS
151 ±2.5
NIV
2.15
On the pitot static test set, adjust the static pressure to make the altitude indication show 25000 feet.
2.16
Make sure that the pilot PFD, copilot PFD (if installed) and the ESIS airspeed displays are within the
limits.
Note
The Mach indication is applicable only to the Thales ESIS.
Reference airspeed
Airspeed indication
CAS (kts)
TAS (kts)
Mach
Display
IAS (kts)
TAS (kts)
Mach
200
0.49
PFD ADI
201 ±2
PFD HSI
PFD HSI
0.490 ±0.005
Thales ESIS
201 ±5
0.49 ±0.01
L3 ESIS
201 ±3
NIV
3
Close Up
3.1
On the pitot static test set, decrease the pitot pressure and the static pressure to ambient.
3.2
On the maintenance panel, set the AIR/GND switch to GND.
3.3
De-energize the aircraft electrical system, refer to AMM 12-B-24-00-00-00A-901A-A.
3.4
Remove the safety clip and close the circuit breakers:
−
XPNDR 1 (AVIONIC 1 BUS)
−
XPNDR 2 (AVIONIC 2 BUS)
−
RAD ALT 1 (AVIONICS 1 BUS).
3.5
Disconnect the pitot static test set from the static ports and the pitot heads.
3.6
Install the protective covers on the left and right pitot heads.
3.7
Remove all the equipment, tools and materials from the work area. Make sure that the work area is
clean.
Requirements after job completion
Required Conditions
Table 6 Required Conditions
Action / Condition
Data module/Technical publication
None
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-34-16-00-00A-903A-A
End of data module
UNCLASSIFIED
2021-12-04 Page 4