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GK Holy Grail > Dash 1 > Flashcards

Dash 1 Flashcards

1
Q

Height (__ft __in)

A

10 8

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2
Q

Main Wheel Pressure (___ +/-_psi) or (___ +/-_psi)

A

225 5 185 5

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3
Q

Length (__ ft __in)

A

33 4

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4
Q

Wingspan (__ft __in)

A

33 5

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5
Q

Basic Empty Weight (lbs)

A

4900

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6
Q

Max Ramp Weight (lbs)

A

6550

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7
Q

Max Zero Fuel Weight (lbs)

A

5500

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8
Q

Max T/O & Land Weight (lbs)

A

6500

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9
Q

Max Baggage Weight (lbs)

A

80

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10
Q

Canopy Rating (__ lb bird weight @ __ kts)

A

4 270

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11
Q

Aileron Range (__deg up __ deg down)

A

20 11

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12
Q

Elevator Range (__ deg up __ deg down)

A

18 16

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13
Q

Bobweight Function

A

increase stick force w/ G load (balances feel and helps prevent over-G)

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14
Q

Downsprings Function

A

balance feel

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15
Q

Rudder Range (deg left/right)

A

24

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16
Q

TAD

A

Trim Aid Device

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17
Q

TAD Inputs (4)

A

Torque, Altitude, Airspeed, Pitch Rate

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18
Q

Conditions for further TAD inputs after engine start (2)

A

> 80kts, No weight on wheels

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19
Q

V_MO Max Operating Airspeed (__ KIAS __ Mach)

A

316 0.67

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20
Q

V_LE, V_FE, Max Gear/Flap Airspeed (KIAS)

A

150

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21
Q

V_G Penetration Airspeed (__ KIAS __ KIAS recommended)

A

195 180

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22
Q

V_O Maneuvering Airspeed (__ KIAS, __ KIAS Rudder)

A

227 150

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23
Q

No Flap Final Turn/Final Airspeed (__ KIAS __ KIAS)

A

120 110

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24
Q

Flaps T/O Final Turn/Final Airspeed (__ KIAS __ KIAS)

A

115 105

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25
Q

Flaps LDG Final Turn/Final Airspeed (__ KIAS __ KIAS)

A

110 100

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26
Q

IAP (KIAS)

A

110

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27
Q

Holding (KIAS)

A

150

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28
Q

Circle (KIAS)

A

120

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29
Q

Glide, Clean (KIAS)

A

125

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30
Q

Glide, Gear/Flap (KIAS)

A

120

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31
Q

Hydroplaning, Nose (KIAS)

A

85

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32
Q

Hydroplaning, Mains (KIAS)

A

115

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33
Q

Approach Speed, Gusting (KIAS)

A

APPR+1/2 Gust (up to 10 kts)

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34
Q

Controllability Check (KIAS)

A

90 / stick shaker

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35
Q

Service Ceiling (ft)

A

31,000

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36
Q

Max Icing band (ft) and type

A

5000 light rime

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37
Q

Cockpit Pressurization (ft PA)

A

0 - 8000

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38
Q

Cockpit Pressure Differential (delta P) (psi)

A

3.6 +/- 0.2

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39
Q

PA For Maximum Cockpit Pressure Differential (ft PA)

A

18,069

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40
Q

Cabin Pressure Differential at FL 310 (ft PA)

A

16,600

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41
Q

CKPT ALT (Amber Annunciator) (ft PA)

A

> 19,000

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42
Q

CKPT PX (Red Annunciator) (delta P psi)

A

> =3.9-4.0

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43
Q

Clean Glide VSI (fpm)

A

1350-1500

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44
Q

Max Crosswind Touch/Go Dry (kts)

A

20

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45
Q

Max Crosswind Form

A

15

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46
Q

Max Crosswind Wet Rwy (kts)

A

10

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47
Q

Max Crosswind Icy Rwy (kts)

A

5

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48
Q

Max Wind Canopy Open (kts)

A

40

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49
Q

Structural Ramp Wind Limit (kts)

A

80

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50
Q

Symmetric Clean G Limits

A

-3.5 7.0

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51
Q

Symmetric Gear G Limits

A

0 2.5

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52
Q

Asymmetric Clean G Limits

A

-1.0 4.7

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53
Q

Asymmetric Gear G Limits

A

0 2.0

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54
Q

Negative-G Flight Limit (sec)

A

15

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55
Q

Engine Manufacturer

A

Pratt & Whitney

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56
Q

Engine Model

A

PT6A-68

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57
Q

Power Rating (shp)

A

1100

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58
Q

Power Rating (lbf, SL STD, 0 Airspeed)

A

2,750

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59
Q

Compressor Stages

A

4-stage axial, 1-stage centrifugal

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60
Q

ITT Max, Idle (deg C)

A

750

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61
Q

ITT Max (deg C)

A

820

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62
Q

ITT Max Transient (___ deg C, __ sec)

A

870 20

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63
Q

N1 Max (%)

A

104

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64
Q

N1 Ground Idle (__-__%)

A

60 61

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65
Q

N1 Flight Idle (%)

A

67

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66
Q

N1 Transient (%)

A

104

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67
Q

Power Norm PMA (VAC)

A

32

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68
Q

Power Sec (VDC)

A

28

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69
Q

PMU reverts to 28 VDC when NP

A

40 50

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70
Q

PMU reverts to __ VDC when NP

A

28

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71
Q

PMU Flight Mode __ % N1

A

67

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72
Q

10,000 ft PA: N1 increase so Np >__ %

A

80

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73
Q

IOAT = 121 deg C when OAT __-___ deg C

A

96 121

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74
Q

IOAT > 121 deg C

A

PMU FAIL

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75
Q

Auto Start Sequence

A

ST READY (Green Annunciator)

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76
Q

Auto Start Sequence (4)

A

Activates Starter

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77
Q

Start Sequence at ~50% N1 (4)

A

Deenergize Starter

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78
Q

PMU FAIL

A

PMU fault; offline

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79
Q

Max step change in power with a PMU Fail (___ shp increase, ___ shp decrease)

A

280

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80
Q

PMU STATUS (Yellow Annunciator) (2) in flight

A

Fault in either of WoW switches

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81
Q

PMU Abort ___C/_s, ___C/_s, ___C/__s

A

940/2 870/4 840/19

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82
Q

PMU Abort (N1)

A

N1 rise is 1/2 of normal

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83
Q

PMU Abort (light off)

A

> 10 sec

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84
Q

Prop Type

A

4-bladed Hartzell

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85
Q

Blade Length (in)

A

97

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86
Q

Blade Angle Low (deg)

A

~15

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87
Q

Blade Angle FTHR (deg)

A

86

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88
Q

RGB Ratio

A

15:01

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89
Q

Np Max (RPM)

A

2,000

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90
Q

Np Idle (__-__%)

A

46 50

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91
Q

Np Transient (___% __sec)

A

102 20

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92
Q

Np Emergency (%)

A

110

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93
Q

Np PMU Off (___+/-_%)

A

100 2

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94
Q

Np PMU On, Mechanical Overspend (%)

A

106

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95
Q

Np Prohibited Stabilized Ground Ops (__-__%)

A

62 80

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96
Q

CHIP (Red Annunciator)

A

Chip Detector in RGB detects ferrous material

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97
Q

PIU

A

Propeller Interface Unit

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98
Q

PMA

A

Permanent Magnet Alternator

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99
Q

Torque @ 100% (ft-lbs)

A

2,900

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100
Q

Oil Capacity (MIL-PRF-23699F) (US Quarts)

A

18.5 (4.5 gal)

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101
Q

Oil Pressure Normal Range (__-___ psi)

A

90 120

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102
Q

Oil Pressure Off Up to _ psi

A

4

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103
Q

Oil Pressure Start up to ___ psi

A

200

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104
Q

Oil Pressure Aerobatics/Spins __-___ psi

A

40 130

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105
Q

Oil Aerobatics/Spins at Idle __-__ psi for _ sec

A

15 40 5

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106
Q

OIL PX (Yellow Annunciator) at Idle __-__ psi _ sec

A

15 40 10

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107
Q

OIL PX (Yellow Annunciator) above Idle __-__ psi _ sec

A

40 90 10

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108
Q

OIL PX (Red Annunciator) at Idle (psi)

A
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109
Q

OIL PX (Red Annunciator) above Idle (psi)

A
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110
Q

Oil Temp Normal __-___ deg C

A

10 105

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111
Q

Oil Temp Start Min (deg C)

A

-40

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112
Q

Oil Temp Transient ___-___ deg C _ min

A

106 110 10

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113
Q

Service Oil within __ min after shutdown

A

30

114
Q

Oil Level most accurate __-__ min after shutdown

A

15-20

115
Q

Wing Fuel Tank Capacity (gal, ea)

A

79

116
Q

Fuel Collector Tank Capacity (gal)

A

7

117
Q

Fuel Weight Gravity Over-wing Refueled to base of filler neck (JP-8/Jet A, lbs)

A

1200

118
Q

JP-5/JP-8/Jet A/Jet A1 density (lbs/gal)

A

6.7

119
Q

Accepted Fuel Types (7)

A

JP-4

120
Q

Icing Inhibitor Mixture Ratio

A

1/2 pt per 50 gal (0.13% by volume)

121
Q

Fuel Auto-Balancing Threshold __ lbs for __ sec

A

20

122
Q

FUEL BAL (Amber Annunciator) after imbalance of __lbs for at least _min or fuel probe failure.

A

30

123
Q

FUEL PX (Red Annunciator) motive flow/return flow supply line

A
124
Q

BOOST PUMP (Green Annunciator)

A

BOOST PUMP switch ON

125
Q

M FUEL BAL (Green Annunciator)

A

fuel balance switch MAN/RESET

126
Q

L/R FUEL LO (Amber Annunciator) (lbs in wing tank) (optical sensor)

A

~110

127
Q

Fuel Pump Pressure, High (psi)

A

400

128
Q

Fuel Pump Pressure, Low (psi)

A

40

129
Q

Total Capacitance-based Fuel Probes

A

7

130
Q

Outer Fuel Probe Range (____-___ lbs +/-__)

A

527 445 50

131
Q

Middle Fuel Probe Range (___-___ lbs +/-__)

A

445 308 50

132
Q

Inner Fuel Probe Range (___-__ lbs)

A

308 20

133
Q

Normal Recovery Fuel (lbs)

A

200

134
Q

Min Fuel (___lbs Dual/___lbs Solo)

A

150 200

135
Q

Emergency Fuel (__lbs Dual/___lbs Solo)

A

100 100

136
Q

Min Fuel for Aerobatics (___lbs/side)

A

150

137
Q

Ejection Seat Operating Mins (_ft/_KIAS)

A

0 0

138
Q

Ejection Seat Operating Max (FL___/___KIAS)

A

350 370

139
Q

Seat Separation Altitude (_____-_____ft)

A

14,000 16,000

140
Q

Front Seat Ejection Delay from pull (sec)

A

0.54

141
Q

Front/Rear Ejection Delay (sec)

A

0.37

142
Q

Starter/Generator Rating (__VDC,___A)

A

28 300

143
Q

Starter Max Continuous Operation (sec)

A

20

144
Q

Starter Cool-Down Times (__ sec, _ min, _ min, __ min)

A

30

145
Q

Min Battery Voltage for Start (VDC)

A

23.5

146
Q

Voltage for External Power Start, Off-Station (__-___ VDC)

A

24 29.5

147
Q

Min Gen Voltage for Battery Charge (VDC)

A

25

148
Q

Gen Limits (___-__A in flight)

A

48

149
Q

Gen Limits (__-___V)

A

28 28.5

150
Q

Battery Rating (__VDC, __A)

A

24 42

151
Q

Bat life w/ BUS TIE Open, BAT BUS only (min)

A

30

152
Q

Bat Powers Which Electronics (BUS TIE switch NORM)?

A

All but air conditioner (reduced time)

153
Q

Aux Battery Rating (__VDC, _A)

A

24 5

154
Q

Aux Battery Standby Life (min)

A

30

155
Q

Aux Battery Powers Which Electronics? (5)

A

Standby Instruments

156
Q

GPU Rating (__-___VDC)

A

28

157
Q

ADC

A

Air Data Computer

158
Q

ADC Inputs

A

Pitot/Static (Primary - Right, Secondary - Left)

159
Q

ADC Outputs (3)

A

Airspeed

160
Q

Standby ADI Performance After all power lost (+/-_deg for _min)

A

6 9

161
Q

Nose Wheel Pressure (___ +/-_psi)

A

120 5

162
Q

GPU Power Requirements (3) (A, time)

A

1000 5 sec

163
Q

Stall AOA

A

~18

164
Q

Optimum AOA, on speed (Green arc)

A

11-Oct

165
Q

Endurance AOA (White Diamond)

A

8.8

166
Q

Range AOA (White Triangle)

A

4.9

167
Q

Stick Shaker AOA

A

15-16

168
Q

Stick Shaker Airspeed (kts above stall)

A

~5-10

169
Q

Buffet Airspeed (kts above stall)

A

~3

170
Q

FDR (Yellow Annunciator)

A

> 80% Full

171
Q

Hydraulic System Capacity (US qts)

A

5

172
Q

Hydraulic Reservoir (gal)

A

0.6

173
Q

Normal Pressure (____+/-___psi)

A

3000 120

174
Q

Hydraulic Pressure Relief Valves Threshold (____-____ psi)

A

3250 3500

175
Q

Min Hydraulic Pressure for Operation (psi)

A

1800

176
Q

HYDR FL LO

A
177
Q

EHYD PX LO

A
178
Q

Hydraulic Fuse (Flow from emer to main system) Limit

A

0.25 GPM / Max 20-30 cubic in (0.5 qt loss)

179
Q

Hydraulic System Users (5)

A

Landing Gear

180
Q

Normal LDG GR extension/retraction time (sec)

A

~6

181
Q

LDG GR warning tone (___hz tone, _hz)

A

250 5

182
Q

Nose Wheel Total Castor Range (deg)

A

160

183
Q

Gear Warning Tone Criteria (3)

A

Handle not DOWN with PCL Mid-Range (N1

184
Q

Max Touchdown 185 psi +/-5 (___fpm/__G)

A

600 3.7

185
Q

Max Touchdown 225 psi +/-5 (___fpm/__G)

A

780 5.1

186
Q

Speed Brake Deflection (deg)

A

70

187
Q

Speed Brake Retraction Triggers (3)

A

Switch

188
Q

Flap Angle, T/O (deg)

A

23

189
Q

Flap Angle, LDG (deg)

A

50

190
Q

True/False: Flaps require main battery power to extend.

A

TRUE

191
Q

OBOGS

A

On-Board Oxygen Generating System

192
Q

OBOGS Normal, SL-150 (%O2)

A

25-70

193
Q

OBOGS Normal 150-310 (%O2)

A

45-95

194
Q

OBOGS MAX (%O2)

A

95

195
Q

O2 Emergency Cylinder Pressure (psi)

A

1800-2500

196
Q

O2 Emergency Cylinder Duration (min)

A

10

197
Q

OBOGS TEMP (Amber Annunciator) (F)

A

Ducting >200

198
Q

OBOGS BIT Test Length (min)

A

~3

199
Q

ECS DUCT TEMP (Amber Annunciator) (F)

A

> 300

200
Q

Bleed Air P3 Right Side Users (4)

A

Cabin Pressure

201
Q

Bleed Air P3 Left Side User

A

OBOGS

202
Q

Cabin Auto Select Range (F)

A

60-90

203
Q

A/C Refrigerant Qty (lb)

A

3.1

204
Q

A/C Bleed Air Bypass (ft)

A

7500

205
Q

Blower Rating HI setting (volumetric flow rate)

A

350 cfpm

206
Q

Anti-G Suit Over-Pressure Valve Rating

A

7 psig

207
Q

Ground Ops Temp Limits (deg C)

A

-66

208
Q

RCR Dry

A

23

209
Q

RCR Wet

A

12

210
Q

RCR Icy

A

5

211
Q

Takeoff Distance Calculation Method

A

Ground run +50’ obstacle clearance

212
Q

V_B Definition

A

Max speed braking can be applied without exceeding brake energy limits

213
Q

Brake Energy Limits (M ft-lbs)

A

3.96

214
Q

Max Abort Calculation Method

A

3-sec decision

215
Q

Landing Data Calculation Method

A

3-deg approach

216
Q

100% Torque Available Surface to (ft)

A

12000-16000

217
Q

Mechanical Governor Np limit (PMU NORM) (%)

A

106

218
Q

Electrical Governor Np limit (PMU OFF) (%)o

A

100 +/-2

219
Q

Rear Seat Ejection Delay from Pull (sec)

A

0.17

220
Q

FMU

A

Fuel Management Unit

221
Q

EDM

A

Engine Data Manager

222
Q

Emergency Engine Shutdown on the Ground Triggers (6)

A

Prop Strike

223
Q

PMU Start Auto shutoff feature available in flight mode. T/F

A

FALSE

224
Q

Min time with green ST READY Annunciator to initiate auto start (sec)

A

3

225
Q

Start Abort (PMU RESET) methods after green ST READY Annunciator extinguished (2)

A

PCL back to OFF

226
Q

PMU reverts to manual mode when (3)

A

Faults prevent setting requested power

227
Q

PMU manual mode Indicators (2)

A

PMU FAIL (red annunciator)

228
Q

Fire Warning System gases and locations (2)

A

Helium (outer)

229
Q

Fire Warning System Helium Function

A

Sensor’s overall threshold temp

230
Q

Fire Warning System Hydrogen Function

A

Highly localized heat releases core hydrogen, increasing overall helium region’s pressure

231
Q

Fire Warning System Indicators (2)

A

FIRE annunciator(s)

232
Q

Fire warning system sensor loop flattening, twisting, kinking, or denting will NOT affect test or flight operation (T/F)

A

TRUE

233
Q

FIRE 1 power location

A

Battery Bus

234
Q

FIRE 2 power location

A

Generator Bus

235
Q

Firewall Shutoff Handle Cuts off Flow of (3) to the engine

A

Fuel

236
Q

Wing Tank Capacity (lb JET A)

A

527

237
Q

Collector Tank Capacity (lb JET A)

A

47

238
Q

Fuel Auto-Balance mechanism

A

Closes motive flow line on light tank (stops transfer to collector)

239
Q

Do not attempt manual fuel balance when

A

AEDD indicates FP FAIL

240
Q

Hold AUX BAT switch on for _ sec min to get test light

A

5

241
Q

Min battery voltage to connect external power (V)

A

22

242
Q

BUS TIE (Amber Annunciator) (2)

A

BUS TIE switch OPEN

243
Q

BAT BUS (Red Annunciator) (2)

A

Battery failure

244
Q

Flap Type

A

Electronically-Controlled, Hydraulically-Operated, 4-segment split flaps

245
Q

Aileron travel on the ground for roll trim (deg)

A

+/- 6

246
Q

Ground-Adjustable aileron trim tabs travel (TE deg)

A

20 up, 8 down

247
Q

Elevator Trim Tab (right side) limits (TE deg)

A

5.5 up, 22 down

248
Q

Rudder pedal adjustment range (in)

A

7

249
Q

Control Balancing Scheme

A

Mass-balanced (cntrl surf CG shift fwd, weathercock stability)

250
Q

Rudder trim tab deflection (rudder neutral) (deg)

A

+/-9

251
Q

After engine start and TAD switch on, which trim condition is active?

A

Takeoff trim condition in yaw axis

252
Q

Data Buses (8)

A

EFIS

253
Q

CFS Explosive types (2)

A

FLSC (Front)

254
Q

FLSC

A

Flexible Linear Shaped Charge

255
Q

MDC

A

Mild Det Cord

256
Q

CFS Manual Operation Path

A

Rotate handle 90 deg counterclockwise and pull (15-20lb)

257
Q

Ejection risk chart assumptions

A

Ejection is within seat performance envelope

258
Q

Ejection LOW RISK definition

A

Major injury rate between 5-10%

259
Q

During ejection, use the MOR when

A

Over mountainous terrain >8,000 MSL

260
Q

Parachute model

A

GQ5000

261
Q

Parachute type

A

Conical

262
Q

Emergency O2 fill pressure (psi at deg F)

A

1800

263
Q

Acceptable EMER O2 pressure calculation (psi, x is temperature in deg F)

A

1800+3.5(x-70)

264
Q

SSK Separation after Pilot/Seat Separation (sec)

A

6-Apr

265
Q

Reduction in flaps UP climb performance with Defog on and PCL retarded to maintain ITT limits up to (%)

A

47

266
Q

Antennas (11)

A

2x TAS

267
Q

UHF Range and increment

A

225.000-399.975 MHz in 25 kHz Increment (7,000 freqs)

268
Q

VHF Range and increment

A

118.000-151.975 MHz in 25 kHz Increment (1,358 freqs)

269
Q

Transponder Modes (3)

A

Modes A, C, and S Altitude encoding (encodes altitude in response to airborne or ground queries)

270
Q

ELT tx freqs (2)

A

121.500 MHz (VHF Guard)

271
Q

Internal ELT battery life (hrs)

A

50

272
Q

TAS Normal Mode Band (ft)

A

+/- 2700

273
Q

TAS Above Mode Band (ft)

A

-11400

274
Q

TAS Below Mode Band (ft)

A

11400

275
Q

TAS Processing Volume

A

+/-10,000 ft, 40 nmi radius

276
Q

NWS Range (deg)

A

+/- 12

277
Q

AUX BAT test switch light on

A

Charged to acceptable flight level

278
Q

AUX BAT test switch light off

A
279
Q

Overspeed Warning Tone (freq, tones)

A

1600 Hz, 5 Hz

280
Q

OBOGS FAIL (Red Annunciator) (2)

A

Low bleed air pressure upstream of concentrator

281
Q

Air Conditioning Refrigerant (HFC-134A) (lb)

A

3.1

282
Q

Brake Fluid (MIL-H-5606E) (pint)

A

0.5

GK Holy Grail (2 decks)

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