Stage 1 Check Flashcards
(119 cards)
1
Q
What documents are required?
A
Government photo ID, medical certificate, student pilot certificate. For aircraft, need: registration, airworthiness cert, W/B, and operating manual
2
Q
SMILE
A
Student pilot, medical, ID, logbook, endorsements
3
Q
PAVE
A
Pilot, aircraft, environment, external
4
Q
IMSAFE
A
Illness, medications, stress, alcohol, fatigue, eating
5
Q
R22 powerplant
A
-Lycoming Oscar-360-Juliett-2-Alpha
-Four cylinder, horizontally opposed, air cooled, carbureted, normally aspirated
-rating 145 BHP, derated to 131 @ 2700 RPM
-cooling system squirrel cage blower
-wet sump oil system
6
Q
Main rotor
A
-Free to teeter and cone, rigid inplane (semi rigid articulation)
-25’2” Diameter
-Blade chord 7.2”
-Tip speed 698 fps @ 104%
7
Q
Tail rotor
A
-Free to teeter, rigid inplane
-42” diameter
-Blade chord 4”, precone angle 1 degree, 11 minutes
- Tip speed 622 fps @ 104%
8
Q
Drive System
A
- Two double Vee belts
-Upper sheave: Sprag-type overrunning clutch - Drive line: spiral-bevel gears
9
Q
Approved fuel grades
A
100LL or UL 91
10
Q
Vne - Never exceed
A
Up to 3000 DA - 102 KIAS, over 3000 DA, depends on temperature
11
Q
Rotor Speed Limits
A
Max 104%, minimum 101% (power on)
-power off max 110%, minimum 90%
12
Q
Max oil temp
A
118 degrees Celsius
13
Q
Oil pressure
A
- idle minimum 25 psi
- min during flight 55 psi
-max during flight 95 psi
14
Q
MAP schedules
A
52 degrees/11 degrees Celsius at 3459 altitude:
-21.6 and add 0.9 for 22.5 max takeoff
-With carb heat add 1.5 for 23.1 and 24
15
Q
Weight limits
A
-max 1370, minimum 920
-max per seat 240
-baggage 50
16
Q
max operating DA
A
14000
17
Q
Things that have to be operational
A
alternator, RPM governor, low roto warning, and OAT gage
18
Q
Fuel Capacity
A
18.3
19
Q
Instrument Markings
A
rotor tach
- yellow arc 60-70%
-green arc 101%-104%
Upper red line 110%
Manifold
-yellow arc 19.6 - 24.1 Hg
-Red line 24.1 Hg
Carb air temp
- yellow arc -15 - 5 degrees celsius
20
Q
Placards
A
-MAP
-Vne
-Fuel grade 100 OCT minimum
- Fuel grade 100LL
-Fuel shutoff valve
- 16.9 US Gal near fuel tank
- minimum solo pilot weight
21
Q
Power Failure above 500 AGL
A
- lower collective
- steady glide 65 KIAS
- select landing spot
-cyclic flare 40 feet AGL - level ship 8 feet AGL
22
Q
Power Failure 8 feet-500 feet AGL
A
-enter autorotation
-keep steady glide 65 KIAS
-maintain rotor RPM 97%
23
Q
Power failure below 8 AGL
A
- right pedal
-settle
-pull collective
24
Q
Max glide distance
A
- 75 KIAS
- Rotor RPM 90%
- 1 NM per 1500 feet AGL
25
Water landing - power off
- autorotation
-unlatch doors
-apply lateral cyclic upon water contact
26
Water landing - power on
- hover above water, passenger exit
- fly safe distance
-switch battery and alternator off
- roll off throttle
-keep level, apply lateral cyclic to stop rotors
27
Loss of tail rotor thrust in flight
- autorotation
-maintain 70 KIAS
- select landing site, roll throttle into travel overspring
- if no suitable landing, fly at low power settings (so it doesn’t yaw to the right too much) at 70 KIAS until finding a more suitable spot
28
Loss of tail rotor thrust in hover
-- roll throttle off
- settle
-pull collective
29
Land as soon as practical
- headset audio failure
- tach failure (tach, governor, and low RPM are on separate circuits)
- governor complete flight manual control
30
Engine fire in flight
- autorotation
-cabin heat and battery off
- if engine is running, perform normal landing and fuel mixture/ fuel valve off
-engine not running - fuel valve off, autorotation
31
Caution Low RPM warning and governor
inoperative with battery and switches both off
32
Warning/caution lights
- oil indicates loss of engine power or oil pressure; chech tachs for power loss and oil for pressure loss. Land immediately if confirmed
- MR temp, MR chip, TR chip: if warning light is accompanied by noise, vibration, temp rise, then land immediately.
- break in fuzz - clean and hover for 30 minutes
33
Low Fuel light
low fuel - indicates 1.5 GAL usable fuel remaining, leaving only 10 minutes left
34
Clutch light
-clutch - indicates clutch actuator circuit is on or engaging; light stays o until belts are tensioned
if clutch light stays on 10 seconds, pull clutch circuit breaker and land as soon as practical
35
ALT light
-ALT - indicates low voltage and possible alternator failure
turn off nonessential electrical equipment and switch ALT off and back on to reset. If light stays on, land as soon as practical
36
Starter ON
Indicates starter motor engaged, If it does not go off, pull mixture off and turn battery switch off
37
Low RPM light
Indicates rotor speed below 97%
-lower collective roll throttle on, apply aft cyclic
38
Carbon Monoxide detector
Shut off heater open vents; if CO poisoning symptoms occur, land immediately
39
Low RPM horn
- provided through audio system
40
LOW G
aft cyclic and then correct the roll
41
Uncommanded pitch in turbulence
Apply controls to maintain rotor RPM, positive G forces; minimize cyclic controls in turbulence
42
Inadvertent turbulence
depart the area or land as soon as practical
43
Recommended airspeeds
-Takeoff 60 KIAS
- Max rate of climb 53 KIAS
- Max range 83 KIAS
- Turbulence 60-70 KIAS
-Landing 60 KIAS
- Auto 60-70 KIAS
44
Carburetor Heat Usage
Carb ice most likley forms between OAT -4 degrees C and 30 degrees C and difefrence between OAT and dewpoint is 15 degrees
Use carb heat during autos of MAP below 18
45
Rotor System
Two all-metal blades mounted to the hub by coning hinges. The hub is mounted to the shaft by a teeter hinge
46
Drive System
A vee-belt sheave is bolted directly to the engine output shaft. Vee-belts transmit power to the upper sheave which has an overrunning clutch contained in its hub. Transmits power forward to the main rotor and aft to the tail rotor
47
Flight controls
Primary controls are actuated through push-pull tube systems and bellcranks
engine throttle is correlated to the collective inputs through a mechanical linkage
48
Electrical System
14 volt DC system and a lead-acid battery
49
Pitot-static system
supplies air pressure to operate the airspeed indicator, altimeter, and VSI
50
Requirements before solo
-Pre-solo written
-Pre-solo flight
-SFAR 73 Awareness and solo (20 hour dual)
-Solo (90 days renewal)
-SFAR 73 PIC
51
PIC requirements
Endorsement to act as a PIC, 200 flight hours, 50 of which in that aircraft, 10 hours of dual
Flight review in preceding 12 months
52
Rotor RPM decay
leads to blade/rotor stall
usually the result of improperly coordinating the collective and throttle
Can happen on approaches
53
Retreating blade stall
-the retreating rotor blade has a lower relative blade speed, combined with an increased angle of attack, causing a stall and loss of lift. Retreating blade stall is the primary limiting factor of a helicopter's never exceed speed, VNE
- only the retreating half of the helicopter's rotor disc experiences a stall. The advancing blade continues to generate lift, but the retreating blade enters a stall condition, usually resulting in an uncommanded increase in pitch of the nose and a roll in the direction of the retreating side of the rotor disc
- High gross weight
- High airspeed
- Low rotor RPM
- High density altitude
- Steep or abrupt turns
- Turbulent ambient air
54
Low RPM/ blade stall speed
80% + 1%/1000 ft DA
Source of energy potential, kinetic, inertia
too much coning - centrifugal force
55
Low G effects
Right roll and mast bumping
56
Frequencies
KBDN CTAF 123.0
57
W/B - standard weight
This weight consists of the airframe, engines, and all items of operating equipment that have fixed, permanently installed locations in the airplane, including fixed ballast, hydraulic fluid, unusable fuel, and full engine oil
58
W/B - basic empty
optional equipment, unusable fuel (fuel that cannot be drained), and full operating fluids, including full engine oil
59
Weight and Balance
Weight and balance is measured against a reference datum, an imaginary vertical plane from which all horizontal distances are measured (firewall, leading edge, etc.)
From that datum, an arm, which is the distance from the datum, can be measured
60
Exceeding max weight limit
structural overloads, performance issues, controllability
61
Finding pressure altitude
29.92 - (current alt setting) * 1000) + 3459
62
Vne
Never exceed speed - causes retreating blade stall and damage to components due to high stress
63
Wind limits R22
Surface winds exceeding 25 Kts, gust spread 15 kts, moderate and severe turbulence
64
Types of Drag
Profile, parasite, and induced
- parasite drag - caused by structure/materials
-profile drag - form drag + interference drag (frictional resistance of blades passing through air)
-Induced drag - Downwash is another source of lift-induced drag
65
Airfoils
Symmetrical airfoils have identical upper and lower surfaces. They are suited to rotary-wing applications because they have almost no center of pressure travel.
Advantages of the nonsymmetrical airfoil are increased lift-drag ratios and more desirable stall characteristics.
66
Coning
The tips of the helicopter rotor blades move faster through the air than the parts of the blades near the hub, so they generate more lift, which pushes the tips of the blades upwards, resulting in a slight cone shape to the rotor disc
67
Effective translational lift
The additional lift obtained.
when entering forward flight,
due to the increased efficiency
of the rotor system.
-between 16-24 knots
-apply forward and left lateral cyclic
-combined effects of dissymmetry of lift, transverse flow, and gyroscopic precession
68
Translating tendency
The tendency of the single rotor helicopter to move
laterally (right, direction of tail rotor thrust) during hovering flight.
69
Dissymmetry of Lift
The unequal lift across the rotor
disk resulting from the
difference in the velocity of air
over the advancing blade half
and the velocity of air over the
retreating blade half of the rotor
disk area.
Advancing Blade - upflap/downward flow of air - decreased AOA
Retreating Blade - downflap/upward flow of air - increased AOA
L=CL*1/2P*S*V^2
70
Gyroscopic Precession
An inherent quality of rotating bodies,
which causes an applied force to be
manifested 90° in the direction of rotation
from the point where the force is applied
71
Coriolis Effect (conservation of angular momentum)
The tendency of a rotor blade to
increase or decrease its velocity
in its plane of rotation when the
center of mass moves closer to or
farther from the axis of rotation.
72
Pendular Action
The lateral or longitudinal
oscillation of the fuselage due
to its suspension from the
rotor system.
73
Torque
In helicopters with a single,
main rotor system, the
tendency of the helicopter to
turn in the opposite direction
of the main rotor rotation
74
Retreating Blade Stall
A stall that begins at or near
the tip of a blade in a
helicopter because of the high
angles of attack required to
compensate for dissymmetry
of lift.
75
Ground Effect
It is due to the interference of the surface with the airflow pattern of the rotor system, and it is more pronounced the nearer the ground is approached. Increased blade efficiency while operating in ground effect is due to two separate and distinct phenomena
- reduction of velocity of induced airflow - The result is less induced drag and a more vertical lift vector
76
Transverse Flow Effect
encountered when a helicopter moves horizontally (typically forward) through the air, which causes the rotor disc to roll to the side
-when the helicopter starts moving into undisturbed air, a portion of the disc is in clean, unaccelerated air, while the remaining portion of the rotor disc is still working on descending air. The part of the disc working on clean air therefore sees a higher angle of attack than the portion of the disc which is working on descending air
-clean air develops more lift
77
Vortex Ring State
A vortex ring state sets in when the airflow around a helicopter's main rotor assumes a rotationally symmetrical form over the tips of the blades, supported by a laminar flow over the blade tips, and a countering upflow of air outside and away from the rotor. In this condition, the rotor falls into a new topological state of the surrounding flow field, induced by its own downwash, and suddenly loses lift. Since vortex rings are surprisingly stable fluid dynamical phenomena
- helo developing power, descent rate exceed 300 fpm, and aircraft below ETL
78
Vuichard Recovery
For helicopters with a counterclockwise rotating main rotor, pull the collective to climb power, and apply right cyclic and left pedal
79
Required Equipment (Night)
FLAPS
-Fuses
-Landing lights
-Anticollision lights
-Position Lights
-Source of power
-5 SM of viz
80
MATSFOOL-MATS
-Mag heading
-Airspeed
-Temp gauge
-Seatbelts
-Fuel gauge
-Oil temp
-Oil pressure
-Landing gear
-Manifold pressure
-Altimeter
-Tachs
-Shoulder harness
81
GOAL-H
-Governor
-OAT
-Altimeter
-Low RPM & lights
-Headset
82
NAIL-C
-Nav lights
-Anti-collision lights
-Instrument lights
-Landing lights
-Celestial illumination
83
Airspace (local)
KBDN - class Echo, not controlled
KRDM, class Delta, controlled
-initial callups to ATIS
Class Golf is 1/2 SM of viz
84
GELL
Flight review at 12 months
-Governor off
-Enhanced autos
-Low rotor RPM
-Low G
85
ATIS
Automatic terminal information service. Want the weather at a major airport and its local notices to airmen (notams)
86
AROW
A – Airworthiness Certificate
R – Registration Certificate
O – Operating Limitations
W – Weight and Balance
87
PL(ease!) START
PL(ease!) START - Engine-out emergency memory aid.
Pitch for best glide, Landing site, Seat belts, Troubleshoot, Approach, Radios, Turn off.
88
NW-KRAFT - preflight
-Notams
-Weather
-Known ATC delays
-Runway lengths
-Alternates
-Fuel requirements
-Take-off distances
89
DECIDE
Detect,
Estimate,
Choose a course of action, Identify solutions,
Do the necessary actions, and Evaluate the effects of the actions
90
PIC requirements 61 subpart E
3 takeoffs, 3 landings in preceding 90 days
no night carrying passnegers wihtin 1 hour of sunrise/sunset unless 3 TO/landings at nights
91
Newton Laws
Newton's 3rd law on lift:
-What the wing does to the air is the action while lift is the reaction.
-Newton’s first law says that there must be a force on the air to bend it down (the action). Newton’s third law says that there must be an equal and opposite force (up) on the wing (the reaction). To generate lift a wing must divert lots of air down.
92
Bernoulli's Principle
Bernoulli's principle states that an increase in the speed of a fluid occurs simultaneously with a decrease in static pressure or the fluid's potential energy
-The simple form of Bernoulli's equation is valid for incompressible flows (low Mach numbers)
-only applicable for isentropic flows: when the effects of irreversible processes (like turbulence) and non-adiabatic processes (e.g. thermal radiation) are small and can be neglected.
-Newton's Second Law - F=ma
93
Light Gun Signals
-Steady Green: cleared to land
- Flashing green: means “return for landing” (in a pattern)
-A steady red light means that you must give way to other aircraft and continue circling.
-A flashing red signal is definitely one to watch out for. It is safety-related. It means that the airport is, at present, unsafe, and an approach to landing should not be made.
A flashing white light sent to aircraft on the ground means that the airplane must return to its starting point at the airport.
94
NASA reporting system
report to the National Aeronautics and Space Administration (NASA) actual or potential discrepancies and deficiencies in aviation safety.
95
Class A airspace
airspace from 18,000 feet MSL up to and including FL 600, including the airspace overlying the waters within 12 nautical miles off the coast of the 48 contiguous States and Alaska
-IFR
96
Class B airspace
airspace from the surface to 10,000 feet MSL surrounding the nation's busiest airports in terms of IFR operations or passenger enplanements. The configuration of each Class B airspace area is individually tailored and consists of a surface area and two or more layers
-ATC clearance
-Clear of Clouds
-Radio and ADS-B Out
- 30 NM
97
Class C airspace
airspace from the surface to 4,000 feet above the airport elevation (charted in MSL) surrounding those airports that have an operational control tower, are serviced by a radar approach control, and that have a certain number of IFR operations or passenger enplanements
- 5 NM
- Radio and ADS-B Out
98
Class D airspace
Class D airspace extends upward from the surface to 2,500 feet above the airport elevation (charted in MSL) surrounding those airports that have an operational control tower.
-full time or part time (reverts to class E or G)
-KRDM initial callup on ATIS and tail number
99
Class E airspace
airspace extending upward from 14,500 feet MSL to, but not including, 18,000 feet MSL overlying the 48 contiguous states, the District of Columbia and Alaska
-airspace above FL 600
100
Class G airspace
uncontrolled, at surface and up to 14,500 unless other airspace layered over it
101
VFR Wx minimums
Class B, C, D, E airspace:
- 3 SM
1000 feet above
-500 below
-2000 horizontal
Class E above 10,000 MSL
- 5 SM/1000/1000/ 1 mile horizontal
Class G
- 1/2 SM (1 SM at night), COC
Class G over 1200 feet MSL
- 1 SM (3 SM at night)
- 1000 above/500 below/2000 horizontal
102
Loss of tail rotor effectiveness LTE
Weathervaning. Left crosswind tail - rotor vortex ring state. Left quartering headwind -main rotor vortex interference. High altitude
103
LTE recovery
Full left pedal, forward airspeed, reduce collective
104
EP power failure >500 AGL
1. Lower collective to maintain rotor RPM.
2. Establish steady glide T 65 KIAS
3. Adjust collective to keep RPM 96-110%
4. Select landing spot
5. Restart may be attempted if sufficient time available
6. If not restarted, turn unnecessary switches and fuel valve off
7. At 40 feet AGL begin cyclic flare to reduce rate of descent and forward speed
8. At 8 feet AGL apply forward cyclic to level ship and raise collective to cushion landing
105
Power failure 8 feet-500 feet AGL
1. Lower collective immediately
2. Adjust collective to maintain RPM between 97-110%
3. Maintain airspeed until ground approached, then begin cyclic flare
4. At 8 feet AGL forward cyclic to level airship, raise collective to cushion landing
106
Power FaIlure below 8 feet AGL
1. Apply right pedal to prevent yawing
2. Allow to settle
3. Raise collective to cushion landing
107
Max glide distance
75 KIAS
Rotor RPM 90%
Glide ration 4:1 or 1 NM per 1500 AGL
108
Air restart procedure
Mixture full rich
Primer down and locked
Throttle closed, crack slightly
Actuate starter with left hand
Only do if engine not malfunctioned or safe autorotation is established
109
Loss of tail rotor thrust in forward flight
Indicates by right nose yaw that can’t be corrected
1. enter autorotation
2. 70 KIAS
3. Select landing site, roll throttle off into over spring, perform auto landing
Vertical stabilizers might permit limited controlled flight at low power settings and airspeeds above 70 KIAS
110
Loss of tail rotor thrust in hover
Nose right yaw
Roll throttle off into over spring
Raise collective to cushion landing
111
Headset failure
Land as soon as practical
112
Engine fire on ground
Continue to start to suck flames and excess fuel into engine
If starts, run at 50-60 RPM
Fuel mixture off
Fuel valve off
Battery off
Apply rotor brake
Exit
113
Engine fire in flight
Enter autorotation
Cabin heat off
Cabin vent on
If engine running perform normal landing
If engine stops, fuel valve off and complete an autorotation
Battery off
Rotor brake and exit
114
Electrical fire in flight
Battery and alternator off
Cabin vents
Land immediately
Fuel mixture off
Fuel valve off
115
Tach failure
Use remaining tach to monitor RPM
Allow governor to control RPM and land as soon as practical
116
Governor failure
Override governor, switch it off and complete flight with manual control
117
Warming lights
Oil - land immediately of pressure loss confirmed
MR Temp , MR chip, TR chip - if light accompanied by secondary indications of moused temp rising, vibrations then land immediately
Otherwise as soon as practical
118
Warning lights 2
Low fuel - 1.5 gallon usable remaining
10 min left
Clutch - clutch actuator circuit is on
10 seconds, pull circuit breaker and land as soon as practical
If second indications of drive system failure then reduce power and land immediately
ALT - low voltage so turn off unnecessary electrical equipment and switch ALT off and on to reset. Light stays in land as soon as practical
Starter on - pull mixture and turn battery off
Low RPM - lower collective, roll throttle on, apply aft cyclic
CO - shit off heater and open vents
119
GIML
Governor off
Inputs to avoid/undershoot in an auto
Max glide auto
Low RPM recognition & recovery
