Dash 1 Flashcards
1
Q
Height (__ft __in)
A
10 8
2
Q
Main Wheel Pressure (___ +/-_psi) or (___ +/-_psi)
A
225 5 185 5
3
Q
Length (__ ft __in)
A
33 4
4
Q
Wingspan (__ft __in)
A
33 5
5
Q
Basic Empty Weight (lbs)
A
4900
6
Q
Max Ramp Weight (lbs)
A
6550
7
Q
Max Zero Fuel Weight (lbs)
A
5500
8
Q
Max T/O & Land Weight (lbs)
A
6500
9
Q
Max Baggage Weight (lbs)
A
80
10
Q
Canopy Rating (__ lb bird weight @ __ kts)
A
4 270
11
Q
Aileron Range (__deg up __ deg down)
A
20 11
12
Q
Elevator Range (__ deg up __ deg down)
A
18 16
13
Q
Bobweight Function
A
increase stick force w/ G load (balances feel and helps prevent over-G)
14
Q
Downsprings Function
A
balance feel
15
Q
Rudder Range (deg left/right)
A
24
16
Q
TAD
A
Trim Aid Device
17
Q
TAD Inputs (4)
A
Torque, Altitude, Airspeed, Pitch Rate
18
Q
Conditions for further TAD inputs after engine start (2)
A
> 80kts, No weight on wheels
19
Q
V_MO Max Operating Airspeed (__ KIAS __ Mach)
A
316 0.67
20
Q
V_LE, V_FE, Max Gear/Flap Airspeed (KIAS)
A
150
21
Q
V_G Penetration Airspeed (__ KIAS __ KIAS recommended)
A
195 180
22
Q
V_O Maneuvering Airspeed (__ KIAS, __ KIAS Rudder)
A
227 150
23
Q
No Flap Final Turn/Final Airspeed (__ KIAS __ KIAS)
A
120 110
24
Q
Flaps T/O Final Turn/Final Airspeed (__ KIAS __ KIAS)
A
115 105
25
Flaps LDG Final Turn/Final Airspeed (__ KIAS __ KIAS)
110 100
26
IAP (KIAS)
110
27
Holding (KIAS)
150
28
Circle (KIAS)
120
29
Glide, Clean (KIAS)
125
30
Glide, Gear/Flap (KIAS)
120
31
Hydroplaning, Nose (KIAS)
85
32
Hydroplaning, Mains (KIAS)
115
33
Approach Speed, Gusting (KIAS)
APPR+1/2 Gust (up to 10 kts)
34
Controllability Check (KIAS)
90 / stick shaker
35
Service Ceiling (ft)
31,000
36
Max Icing band (ft) and type
5000 light rime
37
Cockpit Pressurization (ft PA)
0 - 8000
38
Cockpit Pressure Differential (delta P) (psi)
3.6 +/- 0.2
39
PA For Maximum Cockpit Pressure Differential (ft PA)
18,069
40
Cabin Pressure Differential at FL 310 (ft PA)
16,600
41
CKPT ALT (Amber Annunciator) (ft PA)
>19,000
42
CKPT PX (Red Annunciator) (delta P psi)
>=3.9-4.0
43
Clean Glide VSI (fpm)
1350-1500
44
Max Crosswind Touch/Go Dry (kts)
20
45
Max Crosswind Form
15
46
Max Crosswind Wet Rwy (kts)
10
47
Max Crosswind Icy Rwy (kts)
5
48
Max Wind Canopy Open (kts)
40
49
Structural Ramp Wind Limit (kts)
80
50
Symmetric Clean G Limits
-3.5 7.0
51
Symmetric Gear G Limits
0 2.5
52
Asymmetric Clean G Limits
-1.0 4.7
53
Asymmetric Gear G Limits
0 2.0
54
Negative-G Flight Limit (sec)
15
55
Engine Manufacturer
Pratt & Whitney
56
Engine Model
PT6A-68
57
Power Rating (shp)
1100
58
Power Rating (lbf, SL STD, 0 Airspeed)
2,750
59
Compressor Stages
4-stage axial, 1-stage centrifugal
60
ITT Max, Idle (deg C)
750
61
ITT Max (deg C)
820
62
ITT Max Transient (___ deg C, __ sec)
870 20
63
N1 Max (%)
104
64
N1 Ground Idle (__-__%)
60 61
65
N1 Flight Idle (%)
67
66
N1 Transient (%)
104
67
Power Norm PMA (VAC)
32
68
Power Sec (VDC)
28
69
PMU reverts to 28 VDC when NP
40 50
70
PMU reverts to __ VDC when NP
28
71
PMU Flight Mode __ % N1
67
72
10,000 ft PA: N1 increase so Np >__ %
80
73
IOAT = 121 deg C when OAT __-___ deg C
96 121
74
IOAT > 121 deg C
PMU FAIL
75
Auto Start Sequence
ST READY (Green Annunciator)
76
Auto Start Sequence (4)
Activates Starter
77
Start Sequence at ~50% N1 (4)
Deenergize Starter
78
PMU FAIL
PMU fault; offline
79
Max step change in power with a PMU Fail (___ shp increase, ___ shp decrease)
280
80
PMU STATUS (Yellow Annunciator) (2) in flight
Fault in either of WoW switches
81
PMU Abort ___C/_s, ___C/_s, ___C/__s
940/2 870/4 840/19
82
PMU Abort (N1)
N1 rise is 1/2 of normal
83
PMU Abort (light off)
> 10 sec
84
Prop Type
4-bladed Hartzell
85
Blade Length (in)
97
86
Blade Angle Low (deg)
~15
87
Blade Angle FTHR (deg)
86
88
RGB Ratio
15:01
89
Np Max (RPM)
2,000
90
Np Idle (__-__%)
46 50
91
Np Transient (___% __sec)
102 20
92
Np Emergency (%)
110
93
Np PMU Off (___+/-_%)
100 2
94
Np PMU On, Mechanical Overspend (%)
106
95
Np Prohibited Stabilized Ground Ops (__-__%)
62 80
96
CHIP (Red Annunciator)
Chip Detector in RGB detects ferrous material
97
PIU
Propeller Interface Unit
98
PMA
Permanent Magnet Alternator
99
Torque @ 100% (ft-lbs)
2,900
100
Oil Capacity (MIL-PRF-23699F) (US Quarts)
18.5 (4.5 gal)
101
Oil Pressure Normal Range (__-___ psi)
90 120
102
Oil Pressure Off Up to _ psi
4
103
Oil Pressure Start up to ___ psi
200
104
Oil Pressure Aerobatics/Spins __-___ psi
40 130
105
Oil Aerobatics/Spins at Idle __-__ psi for _ sec
15 40 5
106
OIL PX (Yellow Annunciator) at Idle __-__ psi _ sec
15 40 10
107
OIL PX (Yellow Annunciator) above Idle __-__ psi _ sec
40 90 10
108
OIL PX (Red Annunciator) at Idle (psi)
109
OIL PX (Red Annunciator) above Idle (psi)
110
Oil Temp Normal __-___ deg C
10 105
111
Oil Temp Start Min (deg C)
-40
112
Oil Temp Transient ___-___ deg C _ min
106 110 10
113
Service Oil within __ min after shutdown
30
114
Oil Level most accurate __-__ min after shutdown
15-20
115
Wing Fuel Tank Capacity (gal, ea)
79
116
Fuel Collector Tank Capacity (gal)
7
117
Fuel Weight Gravity Over-wing Refueled to base of filler neck (JP-8/Jet A, lbs)
1200
118
JP-5/JP-8/Jet A/Jet A1 density (lbs/gal)
6.7
119
Accepted Fuel Types (7)
JP-4
120
Icing Inhibitor Mixture Ratio
1/2 pt per 50 gal (0.13% by volume)
121
Fuel Auto-Balancing Threshold __ lbs for __ sec
20
122
FUEL BAL (Amber Annunciator) after imbalance of __lbs for at least _min or fuel probe failure.
30
123
FUEL PX (Red Annunciator) motive flow/return flow supply line
124
BOOST PUMP (Green Annunciator)
BOOST PUMP switch ON
125
M FUEL BAL (Green Annunciator)
fuel balance switch MAN/RESET
126
L/R FUEL LO (Amber Annunciator) (lbs in wing tank) (optical sensor)
~110
127
Fuel Pump Pressure, High (psi)
400
128
Fuel Pump Pressure, Low (psi)
40
129
Total Capacitance-based Fuel Probes
7
130
Outer Fuel Probe Range (____-___ lbs +/-__)
527 445 50
131
Middle Fuel Probe Range (___-___ lbs +/-__)
445 308 50
132
Inner Fuel Probe Range (___-__ lbs)
308 20
133
Normal Recovery Fuel (lbs)
200
134
Min Fuel (___lbs Dual/___lbs Solo)
150 200
135
Emergency Fuel (__lbs Dual/___lbs Solo)
100 100
136
Min Fuel for Aerobatics (___lbs/side)
150
137
Ejection Seat Operating Mins (_ft/_KIAS)
0 0
138
Ejection Seat Operating Max (FL___/___KIAS)
350 370
139
Seat Separation Altitude (_____-_____ft)
14,000 16,000
140
Front Seat Ejection Delay from pull (sec)
0.54
141
Front/Rear Ejection Delay (sec)
0.37
142
Starter/Generator Rating (__VDC,___A)
28 300
143
Starter Max Continuous Operation (sec)
20
144
Starter Cool-Down Times (__ sec, _ min, _ min, __ min)
30
145
Min Battery Voltage for Start (VDC)
23.5
146
Voltage for External Power Start, Off-Station (__-___ VDC)
24 29.5
147
Min Gen Voltage for Battery Charge (VDC)
25
148
Gen Limits (___-__A in flight)
48
149
Gen Limits (__-___V)
28 28.5
150
Battery Rating (__VDC, __A)
24 42
151
Bat life w/ BUS TIE Open, BAT BUS only (min)
30
152
Bat Powers Which Electronics (BUS TIE switch NORM)?
All but air conditioner (reduced time)
153
Aux Battery Rating (__VDC, _A)
24 5
154
Aux Battery Standby Life (min)
30
155
Aux Battery Powers Which Electronics? (5)
Standby Instruments
156
GPU Rating (__-___VDC)
28
157
ADC
Air Data Computer
158
ADC Inputs
Pitot/Static (Primary - Right, Secondary - Left)
159
ADC Outputs (3)
Airspeed
160
Standby ADI Performance After all power lost (+/-_deg for _min)
6 9
161
Nose Wheel Pressure (___ +/-_psi)
120 5
162
GPU Power Requirements (3) (A, time)
1000 5 sec
163
Stall AOA
~18
164
Optimum AOA, on speed (Green arc)
11-Oct
165
Endurance AOA (White Diamond)
8.8
166
Range AOA (White Triangle)
4.9
167
Stick Shaker AOA
15-16
168
Stick Shaker Airspeed (kts above stall)
~5-10
169
Buffet Airspeed (kts above stall)
~3
170
FDR (Yellow Annunciator)
>80% Full
171
Hydraulic System Capacity (US qts)
5
172
Hydraulic Reservoir (gal)
0.6
173
Normal Pressure (____+/-___psi)
3000 120
174
Hydraulic Pressure Relief Valves Threshold (____-____ psi)
3250 3500
175
Min Hydraulic Pressure for Operation (psi)
1800
176
HYDR FL LO
177
EHYD PX LO
178
Hydraulic Fuse (Flow from emer to main system) Limit
0.25 GPM / Max 20-30 cubic in (0.5 qt loss)
179
Hydraulic System Users (5)
Landing Gear
180
Normal LDG GR extension/retraction time (sec)
~6
181
LDG GR warning tone (___hz tone, _hz)
250 5
182
Nose Wheel Total Castor Range (deg)
160
183
Gear Warning Tone Criteria (3)
Handle not DOWN with PCL Mid-Range (N1
184
Max Touchdown 185 psi +/-5 (___fpm/__G)
600 3.7
185
Max Touchdown 225 psi +/-5 (___fpm/__G)
780 5.1
186
Speed Brake Deflection (deg)
70
187
Speed Brake Retraction Triggers (3)
Switch
188
Flap Angle, T/O (deg)
23
189
Flap Angle, LDG (deg)
50
190
True/False: Flaps require main battery power to extend.
TRUE
191
OBOGS
On-Board Oxygen Generating System
192
OBOGS Normal, SL-150 (%O2)
25-70
193
OBOGS Normal 150-310 (%O2)
45-95
194
OBOGS MAX (%O2)
95
195
O2 Emergency Cylinder Pressure (psi)
1800-2500
196
O2 Emergency Cylinder Duration (min)
10
197
OBOGS TEMP (Amber Annunciator) (F)
Ducting >200
198
OBOGS BIT Test Length (min)
~3
199
ECS DUCT TEMP (Amber Annunciator) (F)
>300
200
Bleed Air P3 Right Side Users (4)
Cabin Pressure
201
Bleed Air P3 Left Side User
OBOGS
202
Cabin Auto Select Range (F)
60-90
203
A/C Refrigerant Qty (lb)
3.1
204
A/C Bleed Air Bypass (ft)
7500
205
Blower Rating HI setting (volumetric flow rate)
350 cfpm
206
Anti-G Suit Over-Pressure Valve Rating
7 psig
207
Ground Ops Temp Limits (deg C)
-66
208
RCR Dry
23
209
RCR Wet
12
210
RCR Icy
5
211
Takeoff Distance Calculation Method
Ground run +50' obstacle clearance
212
V_B Definition
Max speed braking can be applied without exceeding brake energy limits
213
Brake Energy Limits (M ft-lbs)
3.96
214
Max Abort Calculation Method
3-sec decision
215
Landing Data Calculation Method
3-deg approach
216
100% Torque Available Surface to (ft)
12000-16000
217
Mechanical Governor Np limit (PMU NORM) (%)
106
218
Electrical Governor Np limit (PMU OFF) (%)o
100 +/-2
219
Rear Seat Ejection Delay from Pull (sec)
0.17
220
FMU
Fuel Management Unit
221
EDM
Engine Data Manager
222
Emergency Engine Shutdown on the Ground Triggers (6)
Prop Strike
223
PMU Start Auto shutoff feature available in flight mode. T/F
FALSE
224
Min time with green ST READY Annunciator to initiate auto start (sec)
3
225
Start Abort (PMU RESET) methods after green ST READY Annunciator extinguished (2)
PCL back to OFF
226
PMU reverts to manual mode when (3)
Faults prevent setting requested power
227
PMU manual mode Indicators (2)
PMU FAIL (red annunciator)
228
Fire Warning System gases and locations (2)
Helium (outer)
229
Fire Warning System Helium Function
Sensor's overall threshold temp
230
Fire Warning System Hydrogen Function
Highly localized heat releases core hydrogen, increasing overall helium region's pressure
231
Fire Warning System Indicators (2)
FIRE annunciator(s)
232
Fire warning system sensor loop flattening, twisting, kinking, or denting will NOT affect test or flight operation (T/F)
TRUE
233
FIRE 1 power location
Battery Bus
234
FIRE 2 power location
Generator Bus
235
Firewall Shutoff Handle Cuts off Flow of (3) to the engine
Fuel
236
Wing Tank Capacity (lb JET A)
527
237
Collector Tank Capacity (lb JET A)
47
238
Fuel Auto-Balance mechanism
Closes motive flow line on light tank (stops transfer to collector)
239
Do not attempt manual fuel balance when
AEDD indicates FP FAIL
240
Hold AUX BAT switch on for _ sec min to get test light
5
241
Min battery voltage to connect external power (V)
22
242
BUS TIE (Amber Annunciator) (2)
BUS TIE switch OPEN
243
BAT BUS (Red Annunciator) (2)
Battery failure
244
Flap Type
Electronically-Controlled, Hydraulically-Operated, 4-segment split flaps
245
Aileron travel on the ground for roll trim (deg)
+/- 6
246
Ground-Adjustable aileron trim tabs travel (TE deg)
20 up, 8 down
247
Elevator Trim Tab (right side) limits (TE deg)
5.5 up, 22 down
248
Rudder pedal adjustment range (in)
7
249
Control Balancing Scheme
Mass-balanced (cntrl surf CG shift fwd, weathercock stability)
250
Rudder trim tab deflection (rudder neutral) (deg)
+/-9
251
After engine start and TAD switch on, which trim condition is active?
Takeoff trim condition in yaw axis
252
Data Buses (8)
EFIS
253
CFS Explosive types (2)
FLSC (Front)
254
FLSC
Flexible Linear Shaped Charge
255
MDC
Mild Det Cord
256
CFS Manual Operation Path
Rotate handle 90 deg counterclockwise and pull (15-20lb)
257
Ejection risk chart assumptions
Ejection is within seat performance envelope
258
Ejection LOW RISK definition
Major injury rate between 5-10%
259
During ejection, use the MOR when
Over mountainous terrain >8,000 MSL
260
Parachute model
GQ5000
261
Parachute type
Conical
262
Emergency O2 fill pressure (psi at deg F)
1800
263
Acceptable EMER O2 pressure calculation (psi, x is temperature in deg F)
1800+3.5(x-70)
264
SSK Separation after Pilot/Seat Separation (sec)
6-Apr
265
Reduction in flaps UP climb performance with Defog on and PCL retarded to maintain ITT limits up to (%)
47
266
Antennas (11)
2x TAS
267
UHF Range and increment
225.000-399.975 MHz in 25 kHz Increment (7,000 freqs)
268
VHF Range and increment
118.000-151.975 MHz in 25 kHz Increment (1,358 freqs)
269
Transponder Modes (3)
Modes A, C, and S Altitude encoding (encodes altitude in response to airborne or ground queries)
270
ELT tx freqs (2)
121.500 MHz (VHF Guard)
271
Internal ELT battery life (hrs)
50
272
TAS Normal Mode Band (ft)
+/- 2700
273
TAS Above Mode Band (ft)
-11400
274
TAS Below Mode Band (ft)
11400
275
TAS Processing Volume
+/-10,000 ft, 40 nmi radius
276
NWS Range (deg)
+/- 12
277
AUX BAT test switch light on
Charged to acceptable flight level
278
AUX BAT test switch light off
279
Overspeed Warning Tone (freq, tones)
1600 Hz, 5 Hz
280
OBOGS FAIL (Red Annunciator) (2)
Low bleed air pressure upstream of concentrator
281
Air Conditioning Refrigerant (HFC-134A) (lb)
3.1
282
Brake Fluid (MIL-H-5606E) (pint)
0.5
