SIMUFLIGHT Pilatus PC-12/47 Technical and Limitations

Practice vocabulary flashcards detailing the technical specifications, operating limitations, and systems thresholds for the Pilatus PC-12/47 aircraft.

Pilatus PC-12/47 Maximum Ramp Weight

$$4520\,\text{kg} / 9965\,\text{lbs}$$

Pilatus PC-12/47 Maximum Take-off and Landing Weight

$$4500\,\text{kg} / 9921\,\text{lbs}$$

Pilatus PC-12/47 Maximum Zero Fuel Weight

$$4100\,\text{kg} / 9039\,\text{lbs}$$

PT6A-67P Compressor Stage Architecture

4 axial-flow stages and 1 centrifugal stage driven by a dedicated compressor shaft.

PT6A-67P Auto-Ignition Activation Conditions

Automatically activated during engine start when $N_g \ge 10\%$ and $\text{ITT} < 500^\circ\text{C}$.

PT6A-67P Engine Start ITT Exceedance Limits

$800\text{--}870^\circ\text{C}$ for up to $20\,\text{seconds}$, $870\text{--}1000^\circ\text{C}$ for up to $5\,\text{seconds}$, and strictly outside limitations above $1000^\circ\text{C}$.

PT6A-67P Takeoff ITT Limit

$800^\circ\text{C}$, limited to a maximum continuous duration of $5\,\text{minutes}$.

Propeller Fine Pitch Setting (42" Station)

$$19.0^\circ \pm 0.2^\circ$$

Propeller Feathered Pitch Setting (42" Station)

$$+79.6^\circ \pm 0.5^\circ$$

Propeller Overspeed Limit

$1802\,\text{rpm}$ (overspeed condition begins at $> 1760\,\text{rpm}$).

Propeller Underspeed Limits

$< 1640\,\text{rpm}$ in flight, and $< 950\,\text{rpm}$ on the ground.

Propeller Rotation ($N_p$) in Maximum Reverse

$$1650\,\text{rpm}$$

Take-off and Maximum Continuous Torque Limit

$44.34\,\text{psi}$ ($1200\,\text{SHP}$ within the $1000\text{--}1700\,\text{rpm}$ propeller speed range; limited to $23.9\,\text{psi}$ below $1000\,\text{rpm}$).

Engine Oil Pressure Relief Valve Threshold

Relief valve opens at pressures $> 160\,\text{psi}$.

Engine Oil Quantity Check Window

Between $10$ and $20\,\text{minutes}$ after engine shutdown.

Starter / Generator Continuous Load Limit

$300\,\text{amps}$ continuous load, with a maximum transient allowance of $450\,\text{amps}$ for up to $2\,\text{minutes}$ within a 1-hour period.

Dual Battery Emergency Power Time Limit

$40\,\text{minutes}$ if the electrical load is $< 60\,\text{amps}$, and $60\,\text{minutes}$ if the electrical load is $< 50\,\text{amps}$.

Battery Start Sequence Limits

First sequence requires $60\,\text{seconds}$ OFF, second sequence requires $60\,\text{seconds}$ OFF, and third sequence requires $30\,\text{minutes}$ OFF.

Hydraulic System Operating Pressure Range

$2725\text{--}2875\,\text{psi}$ (power pack pump activates at $< 2450\,\text{psi}$).

HYDR Caution Light Illumination Threshold

Illuminates when hydraulic system pressure drops below $1800\,\text{psi}$.

Total Usable Fuel Capacity (PC-12/47)

$1540\,\text{ltr} / 406\,\text{USG}$ total ($770\,\text{ltr} / 203\,\text{USG}$ per wing).

Fuel Imbalance Caution Threshold (Airborne)

A difference of $3$ LCD segments or more between the left and right tanks ($100\,\text{ltr} / 26.4\,\text{USG}$ maximum imbalance), which requires landing as soon as possible.

Maximum Operating Speeds ($V_{MO}$ and $M_{MO}$)

$V_{MO} = 236\,\text{kts}$ and $M_{MO} = 0.48\,\text{M}$.

Maximum Flap Extension Speeds ($V_{FE}$)

$163\,\text{kts}$ for Flaps $15^\circ$, $130\,\text{kts}$ for Flaps $30^\circ$, and $130\,\text{kts}$ for Flaps $40^\circ$.

Landing Gear Operating Speeds ($V_{LO}$)

$177\,\text{kts}$ for gear extension and retraction; $110\,\text{kts}$ for emergency gear extension.

White Arc Airspeed Range

$64\text{--}130\,\text{kts}$, spanning from $V_{SO}$ at maximum weight, full flaps, and idle power to $V_{FE}$ for full flaps.

Green Arc Airspeed Range

$91\text{--}236\,\text{kts}$, spanning from $V_S$ at maximum weight, $0^\circ$ flaps, and idle power to $V_{MO}$.

Maximum Cabin Differential Pressure

$$5.75\,\text{psi}$$

CAB PRESS Warning Light Trigger Thresholds

Illuminates when cabin altitude exceeds $10\,700\,\text{ft}$ or when maximum cabin differential pressure is exceeded.

Maximum Operational Altitude (PC-12/47)

$$30\,000\,\text{ft}$$

Starter-Assisted Engine Relight Limitations

Maximum altitude of $20\,000\,\text{ft}$, maximum airspeed of $237\,\text{kts}$, and restricted to a single attempt.

In-Flight and Ground Icing Condition Threshold

Outside Air Temperature (OAT) of $+10^\circ\text{C}$ or colder in the presence of visible moisture.

Flight Load Factor Limitations (Flaps Up vs Flaps Down)

$-1.36g\text{ to }+3.40g$ with flaps retracted (up), and $-0.0g\text{ to }+2.0g$ with flaps extended (down).

Propeller Deice Mode 2 Cycle

Active between $0^\circ\text{C}$ and $-16^\circ\text{C}$ IOAT; blades 1 and 3 are heated for $45\,\text{seconds}$, blades 2 and 4 for $45\,\text{seconds}$, followed by all blades off for $90\,\text{seconds}$.

Wing Deice 1-Minute Timer Sequence

Each deice valve opens for $8\,\text{seconds}$ with a $20\,\text{second}$ dwell period, completing a total inflation and deflation cycle in $40\,\text{seconds}$.

Brake Pad Wear Limitation

Minimum thickness limit of $6\,\text{mm} / \frac{1}{4}\,\text{inch}$, measured with the parking brake set to ON.

Flap Asymmetry Caution Warning Threshold

Activates when flap asymmetry or twist exceeds $> 2^\circ$.

Fuel Low Caution Light Illumination Threshold

Illuminates when usable fuel drops to $20\,\text{USG}$ in either the left or right tank.

Oxygen Cylinder Full Charge Pressure

$1841\,\text{psi}$ at $20^\circ\text{C}$ (minimum charge pressure is $265\,\text{psi}$).

Environmental Control System (ECS) Automatic Shutdown Triggers

Duct pressure $> 33\,\text{psi}$ or $> 40\,\text{psi}$ depending on mod status; duct temperature upstream of the primary shutoff valve $> 290^\circ\text{C}$; or duct temperature downstream of the water separator $> 105^\circ\text{C}$.