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PC12 > PC12 45/47 > Flashcards

PC12 45/47 Flashcards

1
Q

Length PC12

A

14,4m

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2
Q

Main Gear width

A

4,5m

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3
Q

Outside main gear radius (with & without nosewheel steering and brakes)

A

5,03m-11,7m

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4
Q

Outside wing tip radius (with & without nosewheel steering and brakes)

A

10,9m-17,5m

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5
Q

Name of engine PC12 45/47

A

PT6 67B

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6
Q

Description of engine

A

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

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7
Q

T/O Power (in shp)

A

1200 shp

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8
Q

Maximum climb/ cruise power (in shp)

A

1000shp

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9
Q

Propeller speed (Np) (in rpm)

A

1700 rpm

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10
Q

Compressor turbine (Ng) speed (at 104%) (in rpm)

A

39000rpm

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11
Q

Propeller Manufacturer

A

Hartzell

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12
Q

Propeller diameter

A

2,67m

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13
Q

Total fuel capacity

A

2736,5 lbs 1540 L

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14
Q

Usable fuel capacity

A

2703,6 lbs 1521,5 L

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15
Q

Total oil capacity Drain & refill Qty Oil Qty Operating Range

A

Total oil capacity : 13,6L Drain & refill Qty : 7,6L Oil Qty Operating Range : 3,8L

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16
Q

Maximum Ramp Weight PC12-45

A

4520 kg 9965 lbs

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17
Q

Maximum T/O Weight PC12-45

A

4500 kg 9921 lbs

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18
Q

Maximum Landing Weight

A

4500 kg 9921 lbs

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19
Q

Maximum Zero Fuel Weight PC12 -45

A

4100 kg 9039 lbs

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20
Q

Maximum baggage area weight

A

180 kg 400 lbs

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21
Q

Maximum cabin area weight

A

1500 kg 3300 lbs

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22
Q

1L = ? lbs

A

1L = 1,777 lbs

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23
Q

1 kg = ? lbs

A

1 kg = 2,2 lbs

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24
Q

Vmo

A

236 kt (under 15200ft) or 0,48M

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25
Q

Vo

A

163 kt - 4740 kg 158 kt - 4500 kg 120 kt - 2600 kg

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26
Q

Vfe 15

A

163 kt

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27
Q

Vfe 30/40

A

130 kt

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28
Q

Vlo

A

177 kt

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29
Q

Vle

A

236 kt

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30
Q

T/O Power Max (PSI & time) SHP associated Max ITT

A

44,3 PSI during 5min 1200SHP 800°C ITT

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31
Q

Max Power (climb & T/O) SHP associated Max ITT PIM Max ITT Jetfly

A

36,9 PSI 1000SHP 760°C ITT 720°C ITT

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32
Q

Wingspan PC12

A

16,3m

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33
Q

T/O ITT Max Time Max associated

A

800°C 5min

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34
Q

TQ max T/O Time Max associated

A

44,3 PSI 5min

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35
Q

TQ Max Cruise/Climb

A

36,9 PSI

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36
Q

ITT max Cruise/Climb

A

760°C (720 jetfly)

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37
Q

ITT Max Starting Engine Time associated

A

1000°C 5 sec

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38
Q

ITT Max 20sec

A

870°C

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39
Q

ITT Max Reverse

A

760°C

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40
Q

TQ max Reverse

A

34,2 PSI

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41
Q

Maximum GEN1 (Starter/Generator) continuons load factor

A

300A

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42
Q

Maximum GEN1 (Starter/Generator) load factor for 2 min (for race one hour of Ops)

A

450A

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43
Q

Maximum GEN2 (Second Generator) continuons load factor

A

115A

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44
Q

Flight Load Factor Limits flaps up

A

+3,3g -1,32g

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45
Q

Flight Load Factor Limits flaps down

A

+2,0g -0,0g

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46
Q

Range of de-ice boots operation

A

-40 degrés +40 degrés

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47
Q

Max Flap in icing condition with operational airframe pneumatic deice boots

A

Flaps 15

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48
Q

Max Flap in icing condition after failure airframe pneumatic deice boots

A

Flaps 0

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49
Q

Outside air temperature limits of operation of PC12

A

-55 degrés +50 degrés

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50
Q

Maximum cabin pressure differential

A

5,75 PSI (400mbar)

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51
Q

Maximum number of cycle per hour (0 to 0) Up to 25 degrees

A

10

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52
Q

Maximum number of cycle per hour (0 to 0) 25 to 50 degrees

A

8

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53
Q

Minimum altitude select authorized

A

1000ft AGL

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54
Q

PC12 heigh

A

4,26m

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55
Q

Propeller assembly consists of

A

propeller assembly consists of a hub unit and 4 metal blades, is hydraulically actuated, constant speed, full feathering and reversible type

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56
Q

maximum cabin width

A

1,52m

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57
Q

cabin floor width

A

1,30m

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58
Q

maximum cabin lenght

A

5,16m

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59
Q

cabin floor lenght

A

4,68m

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60
Q

maximum cabin height

A

1,45m

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61
Q

size forward passenger door

A

width 0,61m height 1,35m

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62
Q

size cargo door

A

width 1,35m Height 1,32m

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63
Q

size overwing emergency exit

A

width 0,49m height 0,68m

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64
Q

green arc

A

91kt-236kt 93kt-236kt PC12-47

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65
Q

white arc

A

64kt-130kt 66kt PC12-47

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66
Q

Additive concentration in fuel

A

0,06%-0,15%

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67
Q

Propeller Operating limits (Np)

A

1700RPM max 1870RPM 20sec

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68
Q

blade angle minimum pitch in flight

A

6°

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69
Q

blade angle feather

A

79,6° +/- 0,5°

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70
Q

blade angle max reverse pitch

A

-17,5° +/-0,5°

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71
Q

blade angle fine pitch

A

19° +/-0,5°

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72
Q

starter sequence

A

60sec ON - 60sec OFF 60sec ON - 60sec OFF 60sec ON - 30min OFF

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73
Q

PCL afterwards idle detent is prohibited when :

A

prohibited : - when engine not running - during flight (loss of airplane control) - when MOR

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74
Q

Oil temp green arc, yellow arc & red radial

A

green arc : 10° to 105° white arc : 105° to 110° red : 110°

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75
Q

Oil Pressure green arc, white arc & red arc

A

green arc : 90 to 135 PSI white arc : 60 to 90 PSI red arc : 40 to 60 PSI

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76
Q

where is the datum?

A

118in (3m) forward of firewall

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77
Q

flight load factor limits

A

+3,3g -1,32g flaps up +2g -0g flaps down

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78
Q

operation range of de-ice boots

A

-40° +40°C

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79
Q

conditions to fly in icing conditions with PC12

A

with all ice protection systems, GEN1 & GENé serviceable flight in severe conditions should be avoided

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80
Q

flaps maximum extension with de-ice boots

A

15° flap

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81
Q

flaps maximum extension after failure of de-ice boots

A

0° flaps

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82
Q

flaps extension during go around with residual ice on airframe

A

not less than 15° flaps

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83
Q

Maximum fuel imbalance in flight

A

3LCD = 100L = 178lbs

84
Q

maximum operating altitude limits

A

30000ft

85
Q

OUtside air temperature limits

A

-55° to 50°C

86
Q

Max cabin pressure differential

A

5,75 PSI

87
Q

is pressurized landing approved?

A

no

88
Q

Jetfly basic configurations used :

A

EX-6S-2 EX-6S-STD-2S

89
Q

Stall warning/ stick pusher system Equipment limits

A

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

90
Q

Trim Systems Equipment limits

A

stabilizer normal & alternate, and rudder trim systems must function properly for all flights

91
Q

Heated windshield Equipment limits

A

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

92
Q

Fire Detection System Equipment limits

A

Preflight Function Test required for T/O System must function properly for all flights

93
Q

Minimum Oxygen Supply for pressurized flight for each occupant above FL250 :

A

10min /pers >FL250

94
Q

Flaps System Cycle Limits

A

25° : 8 cycles/h Note : 1 Cycle = 0° to 15° to 0° or 0° to 15° to 40° to 0°

95
Q

Altitude Capture limits under AP Operations :

A

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)

96
Q

Landing approach speed with ice accretion on the airframe after failure of de-ice boots :

A

134 kt (flaps to 0°) (140kt PC12-47)

97
Q

Landing approach speed with ice accretion on the airframe after failure of AOA Probe de-ice or Pitot and Static Probe de-ice :

A

108 kt (111kt PC12-47)

98
Q

Landing approach speed with ice accretion on the airframe after failure of Pusher Ice Mode :

A

108 kt (111kt PC12-47)

99
Q

Go Around speed after failure of de-ice boots :

A

134 kt (flaps 0°) (140 kt PC12-47)

100
Q

airspeed T/O flaps 15°

A

79 kt (81 kt PC12-47 at 4500kg)

101
Q

airspeed T/O flaps 30°

A

73 kt (75kt PC12-47 at 4500kg)

102
Q

Vx (=Best Angle)

A

110 kt

103
Q

Vy (=Best Rate) flaps 0°

A

120 kt up to 10.000ft 115 kt up to 15.000ft & above 110 kt upt to 20.000ft

104
Q

Recommended Climb speed with flaps 0° and Pusher Ice Mode

A

130 kt

105
Q

Recommended Holding pattern Speed in icing conditions withs flaps 0°

A

140 to 170 kt

106
Q

Landing Approach Speed Flaps 0° (at Max Landing Weight)

A

118 kt

107
Q

Landing Approach Speed Flaps 15° (at Max Landing Weight)

A

98 kt

108
Q

Landing Approach Speed Flaps 30° (at Max Landing Weight)

A

89 kt

109
Q

Landing Approach Speed Flaps 40° (at Max Landing Weight)

A

84 kt

110
Q

Landing Approach Speed with residual ice on the airframe Flaps 15° & Pusher Ice Mode (at Max Landing Weight)

A

108 kt

111
Q

Go Around Flaps 15°

A

95 kt

112
Q

Go Around Flaps 30°

A

85 kt

113
Q

Go Around Flaps 40°

A

84 kt

114
Q

Go Around Flaps 15° & Pusher Ice Mode

A

108 kt

115
Q

Maximum demonstrated crosswind flaps 0°

A

30 kt

116
Q

Maximum demonstrated crosswind flaps 15°

A

25 kt

117
Q

Maximum demonstrated crosswind flaps 30°

A

20 kt

118
Q

Maximum demonstrated crosswind flaps 40°

A

15 kt

119
Q

maximum altitude loss during stall

A

300ft

120
Q

when landing with flaps 30°, total landing distance will be increased by

A

x 1,22

121
Q

when landing with flaps 15°, total landing distance will be increased by

A

x 1,31

122
Q

when landing with flaps 0°, total landing distance will be increased by

A

x 1,83

123
Q

Accelerate Stop Distance PC12-45 flaps 30° at Max Weight, Std T°, 0 ft, no Wind, no slope

A

approx 860m

124
Q

Accelerate Stop Distance PC12-45 flaps 15° at Max Weight, Std T°, 0 ft, no Wind, no slope

A

approx 1000m

125
Q

T/O Total Distance PC12-45 flaps 15° at Max Weight, Std T°, 0 ft, no Wind, no slope

A

approx 900m

126
Q

Consumption at Maximum endurance cruise, T° ISA, 4000ft at max weight PC12-45 (=115kt)

A

350lbs/h (11 TRQ)

127
Q

Power Off Glide Time & NM for PC12 45 max weight FL100 ISA

A

12min = 26Nm

128
Q

Landing Total Distance PC12-45 flaps 40° no reverse at Max Weight, Std T°, 0 ft, no Wind, no slope

A

approx 660m

129
Q

Landing Total Distance PC12-45 flaps 40° with reverse at Max Weight, Std T°, 0 ft, no Wind, no slope

A

approx 560m

130
Q

Stall speed flaps 0° icing conditions

A

102 kt (105 kt 4740kg)

131
Q

Stall speed flaps 0° boots failure

A

105 kt (108 kt 4740kg)

132
Q

Stall speed flaps 15° icing conditions

A

83 kt (85 kt 4740kg)

133
Q

Stall speed flaps 15°

A

74 kt (76 kt 4740kg)

134
Q

T/O Speed into known icing conditions and take off distance increased by :

A

flaps 15° and + 9 kt x 1,32 %

135
Q

engine fuel flow consumption during holding in icing conditions

A

+ 25 to 50%

136
Q

Landing distance with ice accretion, 15° flaps 108kt increased by :

A

+55% no reverse +45% reverse

137
Q

Landing distance with ice accretion & de-ice boots failure, 0° flaps 134kt increased by :

A

+90% no reverse +75% reverse

138
Q

Maximum Ramp Weight PC12-47

A

4760 kg 10495 lbs

139
Q

Max T/O weight PC12-47

A

4740 kg 10450 lbs

140
Q

Max Landing Weight PC12-47

A

4500 kg 9921 lbs

141
Q

Best Glide

A

116 kt PC12-47 4740 kg

142
Q

Final approach speed, 4740kg, gear down, engine failure after rotation :

A

86 kt

143
Q

Final approach speed, flaps 15°, 4740kg, gear up, engine failure after rotation:

A

100kt

144
Q

Final approach speed, flaps 30°, 4740kg, gear up, engine failure after rotation :

A

91 kt

145
Q

Final approach speed, flaps 40°, 4740kg, gear up, engine failure after rotation :

A

86 kt

146
Q

Définition FCWU

A

Flap Control and Warning Unit

147
Q

Definition PDU

A

Power Drive Unit

148
Q

Usable Oil Qty

A

5,7L

149
Q

What is the maximum allowed flap position for T/O with De-ice boots ON in icing conditions?

A

Flaps 15

150
Q

What is the minimum recommended speed for landing in icing conditions, flaps 0, with a de-ice boots failure in Pusher Ice Mode?

A

134 kt

151
Q

Name the rotation speed of the Power Section?

A

Nf

152
Q

Name the rotation speed of the Propeller

A

Np

153
Q

Name the rotation speed of the Gas Generator

A

Ng

154
Q

What do you find on the accessory gearbox?

A

Oil pumps Low pressure fuel pumps High pressure fuel pumps Electrical generators

155
Q

The pressure regulating valve of the oil system gives a nominal pressure in the system of :

A

90 to 135 PSI

156
Q

How does the torque limiter reduce engine power in case of an over torque?

A

It reduces the Py sensed by the FCU

157
Q

What is the compression ratio of the reduction gearbox?

A

Approx 18 : 30.000 to 1.700 RPM

158
Q

What is the aim of the bleed valve?

A

Spills excess of air to prevent compressor stall

159
Q

When is it recommended to check the oil?

A

Within 10min after engine shutdown

160
Q

Usable Oil Qty

A

5,7L

161
Q

What is the maximum allowed flap position for T/O with De-ice boots ON in icing conditions?

A

Flaps 15

162
Q

What is the minimum recommended speed for landing in icing conditions, flaps 0, with a de-ice boots failure in Pusher Ice Mode?

A

134 kt

163
Q

Name the rotation speed of the Power Section?

A

Nf

164
Q

Name the rotation speed of the Propeller

A

Np

165
Q

Name the rotation speed of the Gas Generator

A

Ng

166
Q

What do you find on the accessory gearbox?

A

Oil pumps Low pressure fuel pumps High pressure fuel pumps Electrical generators

167
Q

The pressure regulating valve of the oil system gives a nominal pressure in the system of :

A

90 to 135 PSI

168
Q

How does the torque limiter reduce engine power in case of an over torque?

A

It reduces the Py sensed by the FCU

169
Q

What is the compression ratio of the reduction gearbox?

A

Approx 18 : 30.000 to 1.700 RPM

170
Q

What is the aim of the bleed valve?

A

Spills excess of air to prevent compressor stall

171
Q

When is it recommended to check the oil?

A

Within 10min after engine shutdown

172
Q

The BUS TIE opens when the continuous current exceeds :

A

220 A

173
Q

The GEN2 TIE opens when the continuous current exceeds :

A

145 A

174
Q

ESNTL BUS Warning illuminates when :

A

GEN1 BUS GEN2 BUS or BAT BUS

175
Q

AV BUS Warning illuminates when :

A

AV1 BUS or AV2 BUS

176
Q

INVERTER Caution illuminates when :

A

Inverter Output

177
Q

BAT HOT Caution illuminates when :

A

Battery overtemp (>70degrees) or sensor disconnected

178
Q

FUEL PRESS Caution illuminates when :

A

Fuel Press Caution : 2 PSI but pumps stops 10” apres >3,5 PSI

179
Q

HYDR Caution illuminates when :

A

In flight : low hydraulic pressure : - Power pack Operating > 10min - OR main press

180
Q

In case of power pack failure, the ? will ensure system pressure is maintained and that the landing gear will be retracted during ? min

A

The NITROGEN CHARGED ACCUMULATOR will maintain the landing gear up during 200MIN

181
Q

When does the power pack pump starts to pressurize the hydraulic system?

A
182
Q

When does the power pack pump stops to pressurize the hydraulic system?

A

Between 2725 and 2875 PSI

183
Q

When does the audible warning “GEAR” and the 3 red lights of the gear will illuminate?

A

Flaps more 15° OR speed less 130 kt AND PCL idle unable to silence tone if flaps more than 15°

184
Q

Emergency Gear Extension Procedure ?

A

* HYDR CTL Breaker pulled * less 110kt * Gear Down if not locked, yaw the Aircraft. if needed, 60 stokes with of hand pump.

185
Q

A failure of The Air Ground System will be followed by the Cautions and Warning of :

A

CAB PRESS PROP LOW P STAB TRIM HYDR a subsequent failure of one of these systems will not be annunciated

186
Q

A failure of The Air Ground System will have the following effect on the Stick Pusher on flight :

A

Stick Pusher INOP Shaker and Aural “Stall” Warning still OPERATIVE

187
Q

A failure of The Air Ground System will have the following effect on the Cabin Pressurization on flight :

A

NO EFFECT as long as Condition Lever not set to Ground Idle

188
Q

A failure of The Air Ground System will have the following effect on the Hydraulic System Control in flight :

A

NO EFFECT as long as engine is running. IF engine stops, the landing gear must be extended with Emergency Extension Procedure

189
Q

A failure of The Air Ground System will have the following effect on the Landing Gear Indication in flight :

A

Selector Handle solenoid will go to the locked position PREVENTING GEAR RETRACTION Landing Gear may be extended by normal operation

190
Q

A failure of The Air Ground System will have the following effect on the Transponder in flight :

A

XPDR will not be activated

191
Q

A failure of The Air Ground System will have the following effect on the EIS in flight :

A

RPM indications CORRECT BUT associated Warnings and Cautions ERRONEOUS

192
Q

Tire Pressure

A

60 PSI +3-0 PSI

193
Q

Maximum fuel imbalanced for T/O

A

T/O prohibited with 4 LCD difference

194
Q

Nosewheel turn from center without differential breaking :

A

+-12 degrees

195
Q

Nosewheel turn from center with differential breaking :

A

+-60 degrees

196
Q

Number of Forward Cabin Door locking pins

A

6

197
Q

Wen will the temperature sensor of the windshield disconnect the heat circuit to avoid an overheat condition?

A

> 60 degrees

198
Q

Temperature of fuel for opening of the bypass of the oil in the oil to fuel heat exchanger?

A

Bypass opens at 21 degrees Fully opened at 37 degrees and oil bypasses oil to fuel heater

199
Q

Pressure of opening of oil pressure relief valve ?

A

160 PSI

200
Q

When IGNITION AUTO, when will it automatically activate?

A

ITT less 500° and NG more than 10% Stops when ITT more than 500°

201
Q

Propeller Speed on the ground at idle?

A

1060 RPM

202
Q

How does the PROP DE-ICE work when IOAT > 0 degrees?

A

Timer in stand by mode and none of the blades are heated

203
Q

How does the PROP DE-ICE work when 0 > IOAT > -16 degrees?

A

Blade 1+3 heated 45” Blades 2+4 heated 45” Off 90”

204
Q

How does the PROP DE-ICE work when IOAT

A

Blades 1+3 heated 90” Blades 2+4 heated 90”

205
Q

Which failures can illuminate an amber PROP DEICE caption + aural sound?

A
  • 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
206
Q

Temperature of fuel for opening of the bypass of the oil in the oil to fuel heat exchanger?

A

Bypass opens at 21 degrees Fully opened at 37 degrees and oil bypasses oil to fuel heater

207
Q

How does the PROP DE-ICE work when IOAT > 0 degrees?

A

Timer in stand by mode and none of the blades are heated

PC12 (2 decks)

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