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