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184 Cards in this Set
- Front
- Back
light blue arrow
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coning hinges
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dark blue arrow
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teeter hinge
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red arrows
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blade grips
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pink arrow
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blade pitch change horn
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yellow arrows
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pitch link
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green arrow
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swash plate
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yellow arrows
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pitch link
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Attaches the rotor blade to the rotor head and includes a pitch change mechanism used to change angle of attack by feathering the blade (with the cyclic control) has multiple bearings, and is filled with a fluid similar (identical?) to automatic transmission fluid.
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Blade Grips
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major components of a helicopter 7
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1 - cabin 2 - airframe 3 - landing gear 4 - powerplant 5 - transmission 6 - main
rotor system 7 - tail rotor system |
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torque
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tendency of the helicopter to turn in the direction opposite the main rotor direction
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The purpose of the __ ___ and __ is to absorb the acceleration and deceleration of the rotor
blades |
drag hinge and dampers
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the purpose of the antitorque rotor is to
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produce thrust to oppose torque and helps prevent the helicopter from turning in the opposite direction of the main rotor
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the engine drives the __ __ through a transmission and belt drive or centrifugal clutch system
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main rotor
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The antitorque rotor is driven from the
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transmission
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The engine drives the __ __ which then transfers power directly to the main rotor system as well as the tail rotor
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main transmission
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above __ feet throttle correlation and governor are less effective - power changes should be slow and smooth
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4000
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at __ power settings above 4000 feet the throttle is frequently __ open and __ must be controlled with collective
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high wide RPM
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the governor is only active above __ % engine RPM
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80
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when operating at high density altitudes governor response rate may be __ __ to prevent overspeed during gusts pullups or when lowering collective
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too slow
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never exceed airspeed Vne
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up to 3000 ft density altitude-102 KIAS
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max rotor speed
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tach 104%-RPM 530
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max engine speed
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2652 RPM 104%
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max cylinder head temperature
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500 degrees F (206 degrees C)
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max oil temperature
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245 degrees F (118 degrees C)
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oil pressure min during idle
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25 psi red beginning
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oil pressure min during flight
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55 psi middle yellow
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oil pressure max during flight
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95 psi red
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oil pressure max during start and warmup
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115 psi red
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max gross weight
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1370 lb (622 kg)
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min gross weight
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920 lb (417 kg)
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max per seat plus baggage compartment
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240 lb (109 kg)
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max in baggage
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50 lb (23 kg)
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min solo weight __ lbs with __ fuel or __ lbs with aux fuel
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130 standard 135
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datum line is __ inches forward of main rotor shaft centerline
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100
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prohibited ___flight
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aerobatic
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prohibited __ cyclic __
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low-g pushovers
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prohibited ___ selected off with exceptions of __
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governor-(system malfuntion or emergency procedures training)
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prohibited __ conidtions
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icing
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prohibited-max operating density altitude
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14000 ft
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prohibited-operational gages required for flight
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alternator-rpm governor-low rotor rpm alarm-oat
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solo flight from __ seat only
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right
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__ seat belt must be buckled
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left
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minimum crew is __ pilot
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one
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no loose items allowed in cabin during ___ flight
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doors-off
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lights required for VFR operation at night 4
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1 landing 2 navigation 3 instrument 4 anticollision
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grade of fuel
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100 ll (low lead) light blue
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mixing wrong types of fuel will cause the resulant fuel to change color to
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white
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main tank total capacity
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198 gallons (75 liters)
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main tank usuable capacity
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192 gallons (73 liters)
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aux tank total capacity
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109 gallons (41 liters)
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aux tank usuable capacity
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105 gallons (40 liters)
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airspeed indicator green arc
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50 to 102 KIAS
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airspeed indicator red line
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102 KIAS
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rotor tach upper red line
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110%
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rotor tach yellow arc
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104 to 110%
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rotor tach green arc
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101 to 104%
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rotor tach yellow arc
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90 to 101%
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rotor tach lower red line
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90%
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rotor tach yellow arc
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60 to 70%
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engine tach upper red arc
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104 to 110%
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engine tach green arc
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101 to 104%
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engine tach lower red arc
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90 to 101%
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engine tach yellow arc
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60 to 70%
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oil pressure lower red line
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25 psi
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oil pressure lower yellow arc
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25 to 55 psi
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oil pressure green arc
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55 to 95 psi
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oil pressure upper yellow arc
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95 to 115 psi
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oil pressure upper red line
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115 psi
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oil temperature green arc
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75 to 245 degrees f (24 to 118 degrees C)
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oil temperature red line
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245 degrees F (118 degress C)
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Cylinder head temperature green arc
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200 to 500 F (93 to 260 C)
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Cylinder head temperature red arc
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500 F (260 C)
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manifold pressure yellow arc
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19.6 to 24.1 in Hg
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manifold pressure red line
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24.1 in Hg
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carburetor air temperature yellow arch
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-15 to 5 C
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below 18 in manifold pressure
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ignore gage and apply full carb heat
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prohibited solo flight when surface winds exceed __ knots
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25 gusts
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prohibited solo flight when surface wind gust spreads exceed __ knots
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15 knots
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prohibited flight turbulences 3
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1 moderate 2 severe 3 extreme
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upon encountering turbulence adjust forward airspeed to between __ knots and __ Vne but no lower than __ knots
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60 07 57
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moderate causes changes in 3
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1 altitude or attitude 2 variations in indicated airspeed 3 strain against the seat belts
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Main Rotor - Articulation
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free to teeter and cone-rigid inplane
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main rotor-tip speed
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approx 100% RPM - 672 FPS
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tail rotor - articulation
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free to teeter - rigid inplane
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tail rotor-tip speed
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approx 100% RPM - 599 FPS
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drive system - engine to upper sheave
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two double vee-belts with 85361 speed reducing ratio
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drive system - upper sheave to drive line
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sprag type overrunning clutch
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drive system - drive line to main rotor spiral-bevel gears with
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1147 speed reducing ratio
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drive system - drive line to tail rotor spiral-bevel gears with
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32 speed increasing ratio
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powerplant model
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0-360-J2A
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normal rating _ BHP (derated)approx __ RPM
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145 2700
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max continuous rating __ BHP approx __ RPM Tach percent __
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124 2652 104%
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5 minute takeoff rating __ BHP __ RPM
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131 2652
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main rotor system is able to
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Flap and Feather
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4 Cone Dimensions
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1 - SemiRidgid 2 - Underslung 3 - Asymetrical (w/ Twist) 4 - 25'2 Diameter
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Electrical System
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-12 Volt Battery- 60 Amp/14 Volt Alternator
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KIAS
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knots indicated airspeed
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KCAS
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knots calibrated airspeed-corrected for instrument and position error
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KTAS
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knots true airspeed-airspeed relative to undisturbed air-KCAS corrected for pressure altitude and temperature
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Vne
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never-exceed airspeed
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Vy
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speed for best rate of climb
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msl altitude
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set to the atmospheric pressure at sea level
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pressure altitude
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when the barometric subscale is set to 29.92 inches of mercury (10132mb)
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density altitude
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in (ISA) International Standard Atmosphere conditions at which the air would have the same density (it is the pressure corrected for (OAT) outside air temperature
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ISA
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international standard atmosphere-sea level 29.92 temp 15 degrees and temp decreases 198 degress per 1000 ft of altitude
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BHP
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brake horsepower is the actual output of the engine
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MAP
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manifold pressure is the absolute pressure in inches of mercury in the engine intake manifold
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MCP
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maximum continuous power
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TOP
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takeoff power-continuous of 5 minutes
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msl altitude
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set to the atmospheric pressure at sea level
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pressure altitude
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when the barometric subscale is set to 2992 inches of mercury (10132mb)
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density altitude
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in (ISA) International Standard Atmosphere conditions at which the air would have the same density (it is the pressure corrected for (OAT) outside air temperature
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critical altitude
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altitude at which full throttle produces maximum allowable power (MCP or TOP)
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TOGW
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takeoff gross weight
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OAT
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outside air temperature
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CAT
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caburetor air temperature
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CHT
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cylinder head temperature
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GPH
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gallons per hour
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AGL
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above ground level
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IGE
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in ground effect
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OGE
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out of ground effect
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ALT
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alternator
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reference datum
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an imaginary vertical plane from which all horizontal distances are measured for balance purposes
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station
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a fore-and-aft location along the helicopter fuselage usually given in terms of distance in inches from the reference datum
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moment
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the product of the weight of an item multiplied by its arm
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center of gravity
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the point at which a helicopter would balance if suspended
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cg arm
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the arm from the reference datum obtained by adding the helicopter's individual moments and dividing the sum by the total weight
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cg limits
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the exteme center of gravity locations within which the helicopter must be operated at a given weight
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usable fuel
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fuel available for flight planning
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ususable fuel
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fuel remaining after a runout test has been completed in accordance with governmental regulations
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standard empty weight
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weight of a standard helicopter including unusable fuel-full operating fluids-and full oil
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basic empty weight
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standard empty weight pule weight of installed optional equipment
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payload
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weight of occupants- cargo- and baggage
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useful load
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difference between maximum takeoff weight and basic empty weight
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POH Emergency
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POH Emergency
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Land Immediately
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Land On The Nearest Clear Area
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2 Land Immediately
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Where A Safe / Normal Landing Can Be Performed- Be Prepared To Auto
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2 Land As Soon As Practical
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1 - Land @ The Nearest Airport Or Facility 2 - Where Emergency Maintainence Can Be Performed
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2 Power Failure General May Be Caused By
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1 - Engine Failure or 2 - Drive System Failure
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5 Engine Failure Symptoms
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1 - Left Nose Yaw 2 - Change In Noise Level 3 - Low H/L Warning 4 - Oil Light 5 - Tachs
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4 Drive System Failure Symptoms
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1 - Unusual Noise 2 - Right/Left Nose Yaw 3 - Low Rotor RPM 4 - High Engine RPM (Wined Up)
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6 Power Failure @ 500 ft AGL Procedures
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1 - Immediate Down Collective/Maintain Rotor RPM/enter auto 2 - Establish A Steady Glide/About 65 KIAS 3 - Adjust Collective/Keep Rotor RPM In Green Arch 4 - Choose A Landing Area/Maneuver Into Wind If Alt Permits 5 - Restart or No Restart 6 - Raise Collective Just Before Impact/To Cushion Landing (Touchdown In Level Attitude)
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if power failure occurs at night-dont turn on __ __ above 1000 ft AGL to preserve battery power
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landing lights
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5 Restart Procedure
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1 - Mixture Full Rich 2 - Primer Down/Locked 3 - Throttle Closed 4- Then Slightly Cracked4 5 - Actuate Starter w/ Left Hand
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2 No Restart procedure
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1 - Turn Off All Unnecessary Switches 2 - Shut Off Fuel
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2 Landing @ 40' AGL
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1 - Start Cyclic Flare 2 - To Reduce ROD & FWD Airspeed
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2 Landing @ 8' AGL
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1 - FWD Cyclic 2 - To Level Ship
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7 Power Failure Between 8' & 500' AGL
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1 - Takeoff Should Be Conducted-Per Hight/Velocity Diagram 2 - Immediate Down Collective-Maintain Rotor RPM 3 - Adjust Collective-Keep Rotor RPM In Green Arch 4 - Maintain Airspeed Until Ground Approaches 5. As Ground Approaches-Start Cyclic Flare To Reduce ROD & FWD Airspeed 6. @ 8' AGL-FWD Cyclic To Level Ship 7. Raise Collective Just Before Impact
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3 Power Failure Below 8' AGL
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1. Immediate Right Pedal-To Prevent Yaw 2. Allow Aircraft To Settle 3. Raise Collective Just Before Impact
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Max Glide Configuration
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- 90% Rotor RPM - 75 KIAS
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4 Ditching Power Off
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1 Follow Same Procedures As Over Land Power Failure-Until Water Contact 2 Apply Lateral Cyclic-To Stop Blades 3 Release Seat Belts 4 Clear Aircraft
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11 Ditching Power On
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1 Descend To Hover Above Water 2 Unlatch Doors 3 Allow Passengers To Exit 4 Fly To Safe Distance For Passengers 5 Switch Off-Master Battery & Alternator 6 Roll Off Throttle 7 Keep Level / Allow Aircraft To Settle 8 Pull Full Collective On Water Contact 9 Apply Lateral Cyclic-To Stop Blades 10 Release Seat Belts 11 Clear Aircraft
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Loss Of Tail Rotor Thrust In Forward Flight symptoms
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1 - Indicated By A Right Nose Yaw 2 - Can Not Be Corrected By Left Pedal
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5 Loss Of Tail Rotor Thrust In Forward Flight
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1 Immediately Enter Autorotation 2 Maintain @ Least 70 KIAS 3 Select Landing Site 4 Roll Off Throttle 5 Perform Autorotation Landing
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2 Loss Of Tail Rotor Thrust During Hover Symptoms
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1 - Indicated By A Right Nose Yaw 2 - Can Not Be Corrected By Left Pedal
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3 Loss Of Tail Rotor Thrust During Hover
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1 Roll Off Throttle 2 Allow Aircraft To Settle 3 Raise Collective Just Before Impact
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5 Engine Fire During Start at Ground (Engine Starts)
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1 - Continue Cranking/10 to 15 seconds 2 - Run @ 50% To 60% For A Short Time 3 - Shut Down 4 - Extinguish 5 - Inspect
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5 Engine Fire During Start at Ground (Engine Doesn't Start)
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1 - Continue Cranking/10 to 15 seconds 2 - Shut Off Fuel 3 - Shut Off Master Battery 4 - Extinguish 5 - Inspect
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7 Engine Fire In Flight (Smells like something burnt)
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1 - Immediately Enter Auto 2 - Master Battery Off 3 - Cabin Heat Off 3 - Cabin Vent Open 4 - Engine On/Normal Landing or Engine Off/Autorotational Landing 5 - Shut Off Fuel 6 - Extinguish 7 - Inspect
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4 Electrical Fire In Flight
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1 - Master Batter Off 2 - Alternator Off 3 - Land Immediately 4 - Extinguish/Inspect
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During and Electrical Fire In Flight what two systems will be inoperative with master battery and alternator switches off
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Governor and Low RPM Warning System
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Tach Failure (1 Of 2 Tachs Fail)
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Use Remaining Tach
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2 Both Tachs Fail
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1 - Use Governor 2- Land As Soon As Practical
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Each tach-the governor-and the low RPM warning horn are on
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separate circuits
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Either the battery or the alternator can __ supply power to the tachs
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independently
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A special circuit allows the battery to supply power to the tachs even if the __ __ __ is off
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master battery switch
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3 Governor Failure
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1 - Grip Throttle Firmly 2 - Switch Gov Off 3 - Complete Flight w/ Manual Throttle Control
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4 Oil Pressure Light
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1 - check engine tach for power loss 2 - Check oil pressure Gauge 3 - If Pressure Loss 4 - Land Immediately
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MR (Main Rotor) Temp
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indicates excessive temp of MR gearbox - land immediately if noise vibration or temp rise
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MR (Main Rotor) Chip
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indicates metallic particles in MR gearbox - land immediately if noise vibration or temp rise
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TR (Tail Rotor) Chip
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indicates metallic particles in TR gearbox - land immediately if noise vibration or temp rise
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Low fuel light warning light
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indicates approx one gallon of usable fuel remaining - will run out after five minutes at cruise power
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Clutch LightLess Than 7 Seconds
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Ignore - never take off with clutch light on
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4 Clutch light on more Then 7 Seconds
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1 - Pull Clutch Circuit Breaker 2 - Land Immediately 3 - Be Prepared To Auto 4 - inspect for malfunction
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Alternator (ALT)
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indicates low voltage and possible alternator failure
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Alternator (ALT) steps
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1 - turn off nonessential electrical equip 2 - switch ALT off and back on after on second to reset overvoltage relay 3 - land as soon as possible
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Flight without functioning alternator results
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in loss of electronic tachometer
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Brake warning light
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rotor brake engage-disengage
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Starter On warning light
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1 - immediately pull mixture to idle cut-off 2 - turn master switch off 3 - have starter motor serviced
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4 carbon monoxide light (if installed)
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1 - open nose and door vents 2 - shut off heater 3 - if hovering-land or transition to forward flight 4 - CO symptoms persist-land immediately
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LOW RPM horn warning light
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1 - restore RPM by rolling throttle on 2 - lower collective 3 - in forward flight/apply aft cyclic
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2 Right roll in low G condition
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1 - gradually apply aft cyclic to restore positive G forces and MR thrust 2 - dont apply lateral cyclic until positive G forces are established
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2 uncommanded pitch-roll-or yaw resulting from flight in trubulence
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1 - gradually apply controls to maintain rotor RPM-positive Gs-elminate sideslip 2 - minimize cyclic control inputs/dont overcontrol
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3 inadvertent encounter with mod/severe/extreme turbulence
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1 - depart area if isolated 2 - land as soon as practical
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