PC12 45/47 Flashcards
Length PC12
14,4m
Main Gear width
4,5m
Outside main gear radius (with & without nosewheel steering and brakes)
5,03m-11,7m
Outside wing tip radius (with & without nosewheel steering and brakes)
10,9m-17,5m
Name of engine PC12 45/47
PT6 67B
Description of engine
Twin shaft turboprop engine with 4 axial & 1 centrifugal compressor stages, 1 annular combustion chamber, a 3 stage turbine where 1 stage drives the compressor & 2 stages power the propeller
T/O Power (in shp)
1200 shp
Maximum climb/ cruise power (in shp)
1000shp
Propeller speed (Np) (in rpm)
1700 rpm
Compressor turbine (Ng) speed (at 104%) (in rpm)
39000rpm
Propeller Manufacturer
Hartzell
Propeller diameter
2,67m
Total fuel capacity
2736,5 lbs 1540 L
Usable fuel capacity
2703,6 lbs 1521,5 L
Total oil capacity Drain & refill Qty Oil Qty Operating Range
Total oil capacity : 13,6L Drain & refill Qty : 7,6L Oil Qty Operating Range : 3,8L
Maximum Ramp Weight PC12-45
4520 kg 9965 lbs
Maximum T/O Weight PC12-45
4500 kg 9921 lbs
Maximum Landing Weight
4500 kg 9921 lbs
Maximum Zero Fuel Weight PC12 -45
4100 kg 9039 lbs
Maximum baggage area weight
180 kg 400 lbs
Maximum cabin area weight
1500 kg 3300 lbs
1L = ? lbs
1L = 1,777 lbs
1 kg = ? lbs
1 kg = 2,2 lbs
Vmo
236 kt (under 15200ft) or 0,48M
Vo
163 kt - 4740 kg 158 kt - 4500 kg 120 kt - 2600 kg
Vfe 15
163 kt
Vfe 30/40
130 kt
Vlo
177 kt
Vle
236 kt
T/O Power Max (PSI & time) SHP associated Max ITT
44,3 PSI during 5min 1200SHP 800°C ITT
Max Power (climb & T/O) SHP associated Max ITT PIM Max ITT Jetfly
36,9 PSI 1000SHP 760°C ITT 720°C ITT
Wingspan PC12
16,3m
T/O ITT Max Time Max associated
800°C 5min
TQ max T/O Time Max associated
44,3 PSI 5min
TQ Max Cruise/Climb
36,9 PSI
ITT max Cruise/Climb
760°C (720 jetfly)
ITT Max Starting Engine Time associated
1000°C 5 sec
ITT Max 20sec
870°C
ITT Max Reverse
760°C
TQ max Reverse
34,2 PSI
Maximum GEN1 (Starter/Generator) continuons load factor
300A
Maximum GEN1 (Starter/Generator) load factor for 2 min (for race one hour of Ops)
450A
Maximum GEN2 (Second Generator) continuons load factor
115A
Flight Load Factor Limits flaps up
+3,3g -1,32g
Flight Load Factor Limits flaps down
+2,0g -0,0g
Range of de-ice boots operation
-40 degrés +40 degrés
Max Flap in icing condition with operational airframe pneumatic deice boots
Flaps 15
Max Flap in icing condition after failure airframe pneumatic deice boots
Flaps 0
Outside air temperature limits of operation of PC12
-55 degrés +50 degrés
Maximum cabin pressure differential
5,75 PSI (400mbar)
Maximum number of cycle per hour (0 to 0) Up to 25 degrees
10
Maximum number of cycle per hour (0 to 0) 25 to 50 degrees
8
Minimum altitude select authorized
1000ft AGL
PC12 heigh
4,26m
Propeller assembly consists of
propeller assembly consists of a hub unit and 4 metal blades, is hydraulically actuated, constant speed, full feathering and reversible type
maximum cabin width
1,52m
cabin floor width
1,30m
maximum cabin lenght
5,16m
cabin floor lenght
4,68m
maximum cabin height
1,45m
size forward passenger door
width 0,61m height 1,35m
size cargo door
width 1,35m Height 1,32m
size overwing emergency exit
width 0,49m height 0,68m
green arc
91kt-236kt 93kt-236kt PC12-47
white arc
64kt-130kt 66kt PC12-47
Additive concentration in fuel
0,06%-0,15%
Propeller Operating limits (Np)
1700RPM max 1870RPM 20sec
blade angle minimum pitch in flight
6°
blade angle feather
79,6° +/- 0,5°
blade angle max reverse pitch
-17,5° +/-0,5°
blade angle fine pitch
19° +/-0,5°
starter sequence
60sec ON - 60sec OFF 60sec ON - 60sec OFF 60sec ON - 30min OFF
PCL afterwards idle detent is prohibited when :
prohibited : - when engine not running - during flight (loss of airplane control) - when MOR
Oil temp green arc, yellow arc & red radial
green arc : 10° to 105° white arc : 105° to 110° red : 110°
Oil Pressure green arc, white arc & red arc
green arc : 90 to 135 PSI white arc : 60 to 90 PSI red arc : 40 to 60 PSI
where is the datum?
118in (3m) forward of firewall
flight load factor limits
+3,3g -1,32g flaps up +2g -0g flaps down
operation range of de-ice boots
-40° +40°C
conditions to fly in icing conditions with PC12
with all ice protection systems, GEN1 & GENé serviceable flight in severe conditions should be avoided
flaps maximum extension with de-ice boots
15° flap
flaps maximum extension after failure of de-ice boots
0° flaps
flaps extension during go around with residual ice on airframe
not less than 15° flaps
Maximum fuel imbalance in flight
3LCD = 100L = 178lbs
maximum operating altitude limits
30000ft
OUtside air temperature limits
-55° to 50°C
Max cabin pressure differential
5,75 PSI
is pressurized landing approved?
no
Jetfly basic configurations used :
EX-6S-2 EX-6S-STD-2S
Stall warning/ stick pusher system Equipment limits
preflight test required before T/O system is required to function properly in normal mode for all flights and in ice mode for flight into known icing conditions
Trim Systems Equipment limits
stabilizer normal & alternate, and rudder trim systems must function properly for all flights
Heated windshield Equipment limits
LH & RH Heated Windshields must function properly for all flights. Exception for IFR flights into no icing (known or forecast) conditions at least 1 heating zone of the windshield of the side of the pilot in command must function properly
Fire Detection System Equipment limits
Preflight Function Test required for T/O System must function properly for all flights
Minimum Oxygen Supply for pressurized flight for each occupant above FL250 :
10min /pers >FL250
Flaps System Cycle Limits
25° : 8 cycles/h Note : 1 Cycle = 0° to 15° to 0° or 0° to 15° to 40° to 0°
Altitude Capture limits under AP Operations :
No Alt Select below 1000ft AGL If radar altimeter option, AP disengaged at 200ft AGL during ILS App (if AP coupled to GS vertical guidance of 6° or less)
Landing approach speed with ice accretion on the airframe after failure of de-ice boots :
134 kt (flaps to 0°) (140kt PC12-47)
Landing approach speed with ice accretion on the airframe after failure of AOA Probe de-ice or Pitot and Static Probe de-ice :
108 kt (111kt PC12-47)
Landing approach speed with ice accretion on the airframe after failure of Pusher Ice Mode :
108 kt (111kt PC12-47)
Go Around speed after failure of de-ice boots :
134 kt (flaps 0°) (140 kt PC12-47)
airspeed T/O flaps 15°
79 kt (81 kt PC12-47 at 4500kg)
airspeed T/O flaps 30°
73 kt (75kt PC12-47 at 4500kg)
Vx (=Best Angle)
110 kt
Vy (=Best Rate) flaps 0°
120 kt up to 10.000ft 115 kt up to 15.000ft & above 110 kt upt to 20.000ft
Recommended Climb speed with flaps 0° and Pusher Ice Mode
130 kt
Recommended Holding pattern Speed in icing conditions withs flaps 0°
140 to 170 kt
Landing Approach Speed Flaps 0° (at Max Landing Weight)
118 kt
Landing Approach Speed Flaps 15° (at Max Landing Weight)
98 kt
Landing Approach Speed Flaps 30° (at Max Landing Weight)
89 kt
Landing Approach Speed Flaps 40° (at Max Landing Weight)
84 kt
Landing Approach Speed with residual ice on the airframe Flaps 15° & Pusher Ice Mode (at Max Landing Weight)
108 kt
Go Around Flaps 15°
95 kt
Go Around Flaps 30°
85 kt
Go Around Flaps 40°
84 kt
Go Around Flaps 15° & Pusher Ice Mode
108 kt
Maximum demonstrated crosswind flaps 0°
30 kt
Maximum demonstrated crosswind flaps 15°
25 kt
Maximum demonstrated crosswind flaps 30°
20 kt
Maximum demonstrated crosswind flaps 40°
15 kt
maximum altitude loss during stall
300ft
when landing with flaps 30°, total landing distance will be increased by
x 1,22
when landing with flaps 15°, total landing distance will be increased by
x 1,31
when landing with flaps 0°, total landing distance will be increased by
x 1,83
Accelerate Stop Distance PC12-45 flaps 30° at Max Weight, Std T°, 0 ft, no Wind, no slope
approx 860m
Accelerate Stop Distance PC12-45 flaps 15° at Max Weight, Std T°, 0 ft, no Wind, no slope
approx 1000m
T/O Total Distance PC12-45 flaps 15° at Max Weight, Std T°, 0 ft, no Wind, no slope
approx 900m
Consumption at Maximum endurance cruise, T° ISA, 4000ft at max weight PC12-45 (=115kt)
350lbs/h (11 TRQ)
Power Off Glide Time & NM for PC12 45 max weight FL100 ISA
12min = 26Nm
Landing Total Distance PC12-45 flaps 40° no reverse at Max Weight, Std T°, 0 ft, no Wind, no slope
approx 660m
Landing Total Distance PC12-45 flaps 40° with reverse at Max Weight, Std T°, 0 ft, no Wind, no slope
approx 560m
Stall speed flaps 0° icing conditions
102 kt (105 kt 4740kg)
Stall speed flaps 0° boots failure
105 kt (108 kt 4740kg)
Stall speed flaps 15° icing conditions
83 kt (85 kt 4740kg)
Stall speed flaps 15°
74 kt (76 kt 4740kg)
T/O Speed into known icing conditions and take off distance increased by :
flaps 15° and + 9 kt x 1,32 %
engine fuel flow consumption during holding in icing conditions
+ 25 to 50%
Landing distance with ice accretion, 15° flaps 108kt increased by :
+55% no reverse +45% reverse
Landing distance with ice accretion & de-ice boots failure, 0° flaps 134kt increased by :
+90% no reverse +75% reverse
Maximum Ramp Weight PC12-47
4760 kg 10495 lbs
Max T/O weight PC12-47
4740 kg 10450 lbs
Max Landing Weight PC12-47
4500 kg 9921 lbs
Best Glide
116 kt PC12-47 4740 kg
Final approach speed, 4740kg, gear down, engine failure after rotation :
86 kt
Final approach speed, flaps 15°, 4740kg, gear up, engine failure after rotation:
100kt
Final approach speed, flaps 30°, 4740kg, gear up, engine failure after rotation :
91 kt
Final approach speed, flaps 40°, 4740kg, gear up, engine failure after rotation :
86 kt
Définition FCWU
Flap Control and Warning Unit
Definition PDU
Power Drive Unit
Usable Oil Qty
5,7L
What is the maximum allowed flap position for T/O with De-ice boots ON in icing conditions?
Flaps 15
What is the minimum recommended speed for landing in icing conditions, flaps 0, with a de-ice boots failure in Pusher Ice Mode?
134 kt
Name the rotation speed of the Power Section?
Nf
Name the rotation speed of the Propeller
Np
Name the rotation speed of the Gas Generator
Ng
What do you find on the accessory gearbox?
Oil pumps Low pressure fuel pumps High pressure fuel pumps Electrical generators
The pressure regulating valve of the oil system gives a nominal pressure in the system of :
90 to 135 PSI
How does the torque limiter reduce engine power in case of an over torque?
It reduces the Py sensed by the FCU
What is the compression ratio of the reduction gearbox?
Approx 18 : 30.000 to 1.700 RPM
What is the aim of the bleed valve?
Spills excess of air to prevent compressor stall
When is it recommended to check the oil?
Within 10min after engine shutdown
Usable Oil Qty
5,7L
What is the maximum allowed flap position for T/O with De-ice boots ON in icing conditions?
Flaps 15
What is the minimum recommended speed for landing in icing conditions, flaps 0, with a de-ice boots failure in Pusher Ice Mode?
134 kt
Name the rotation speed of the Power Section?
Nf
Name the rotation speed of the Propeller
Np
Name the rotation speed of the Gas Generator
Ng
What do you find on the accessory gearbox?
Oil pumps Low pressure fuel pumps High pressure fuel pumps Electrical generators
The pressure regulating valve of the oil system gives a nominal pressure in the system of :
90 to 135 PSI
How does the torque limiter reduce engine power in case of an over torque?
It reduces the Py sensed by the FCU
What is the compression ratio of the reduction gearbox?
Approx 18 : 30.000 to 1.700 RPM
What is the aim of the bleed valve?
Spills excess of air to prevent compressor stall
When is it recommended to check the oil?
Within 10min after engine shutdown
The BUS TIE opens when the continuous current exceeds :
220 A
The GEN2 TIE opens when the continuous current exceeds :
145 A
ESNTL BUS Warning illuminates when :
GEN1 BUS GEN2 BUS or BAT BUS
AV BUS Warning illuminates when :
AV1 BUS or AV2 BUS
INVERTER Caution illuminates when :
Inverter Output
BAT HOT Caution illuminates when :
Battery overtemp (>70degrees) or sensor disconnected
FUEL PRESS Caution illuminates when :
Fuel Press Caution : 2 PSI but pumps stops 10” apres >3,5 PSI
HYDR Caution illuminates when :
In flight : low hydraulic pressure : - Power pack Operating > 10min - OR main press
In case of power pack failure, the ? will ensure system pressure is maintained and that the landing gear will be retracted during ? min
The NITROGEN CHARGED ACCUMULATOR will maintain the landing gear up during 200MIN
When does the power pack pump starts to pressurize the hydraulic system?
When does the power pack pump stops to pressurize the hydraulic system?
Between 2725 and 2875 PSI
When does the audible warning “GEAR” and the 3 red lights of the gear will illuminate?
Flaps more 15° OR speed less 130 kt AND PCL idle unable to silence tone if flaps more than 15°
Emergency Gear Extension Procedure ?
* HYDR CTL Breaker pulled * less 110kt * Gear Down if not locked, yaw the Aircraft. if needed, 60 stokes with of hand pump.
A failure of The Air Ground System will be followed by the Cautions and Warning of :
CAB PRESS PROP LOW P STAB TRIM HYDR a subsequent failure of one of these systems will not be annunciated
A failure of The Air Ground System will have the following effect on the Stick Pusher on flight :
Stick Pusher INOP Shaker and Aural “Stall” Warning still OPERATIVE
A failure of The Air Ground System will have the following effect on the Cabin Pressurization on flight :
NO EFFECT as long as Condition Lever not set to Ground Idle
A failure of The Air Ground System will have the following effect on the Hydraulic System Control in flight :
NO EFFECT as long as engine is running. IF engine stops, the landing gear must be extended with Emergency Extension Procedure
A failure of The Air Ground System will have the following effect on the Landing Gear Indication in flight :
Selector Handle solenoid will go to the locked position PREVENTING GEAR RETRACTION Landing Gear may be extended by normal operation
A failure of The Air Ground System will have the following effect on the Transponder in flight :
XPDR will not be activated
A failure of The Air Ground System will have the following effect on the EIS in flight :
RPM indications CORRECT BUT associated Warnings and Cautions ERRONEOUS
Tire Pressure
60 PSI +3-0 PSI
Maximum fuel imbalanced for T/O
T/O prohibited with 4 LCD difference
Nosewheel turn from center without differential breaking :
+-12 degrees
Nosewheel turn from center with differential breaking :
+-60 degrees
Number of Forward Cabin Door locking pins
6
Wen will the temperature sensor of the windshield disconnect the heat circuit to avoid an overheat condition?
> 60 degrees
Temperature of fuel for opening of the bypass of the oil in the oil to fuel heat exchanger?
Bypass opens at 21 degrees Fully opened at 37 degrees and oil bypasses oil to fuel heater
Pressure of opening of oil pressure relief valve ?
160 PSI
When IGNITION AUTO, when will it automatically activate?
ITT less 500° and NG more than 10% Stops when ITT more than 500°
Propeller Speed on the ground at idle?
1060 RPM
How does the PROP DE-ICE work when IOAT > 0 degrees?
Timer in stand by mode and none of the blades are heated
How does the PROP DE-ICE work when 0 > IOAT > -16 degrees?
Blade 1+3 heated 45” Blades 2+4 heated 45” Off 90”
How does the PROP DE-ICE work when IOAT
Blades 1+3 heated 90” Blades 2+4 heated 90”
Which failures can illuminate an amber PROP DEICE caption + aural sound?
- inhibit input open - failure of OAT sensor - heater supply Voltage out of tolerance - heater current out of tolerance - built in test for Propeller De Ice Controller internal failure
Temperature of fuel for opening of the bypass of the oil in the oil to fuel heat exchanger?
Bypass opens at 21 degrees Fully opened at 37 degrees and oil bypasses oil to fuel heater
How does the PROP DE-ICE work when IOAT > 0 degrees?
Timer in stand by mode and none of the blades are heated
