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Private Pilot Study > POH R-22 / Aircraft > Flashcards

POH R-22 / Aircraft Flashcards

1
Q

Special Flight Permits

A

Issued for an aircraft that may not currently meet applicable airworthiness requirements but is still capable of safe flight

  • flying to base where repairs, alterations, or maintenance are to be performed
  • delivering or exporting the aircraft
  • production flight testing, new aircraft, demo flights
  • Evacuating aircraft from areas of impending danger
  • authorize the operation of an aircraft at a weight in excess of its max certificated take off weight
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2
Q

Master Minimum Equipment List

MMEL

A
  • Categorized list of on-board systems, instruments, and equipment that may be inoperative during flight
  • Defined by aircraft manufacturer on a per aircraft model basis
  • FAA approved
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3
Q

Minimum Equipment List

MEL

A
  • A list of equipment that must be installed and operable for the aircraft to be considered airworthy
  • It is aircraft-specific and spells out which pieces of equipment may be inoperable while maintaining airworthiness
  • Prepared by operator of specific aircraft
  • FAA approved
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4
Q

Authority and Responsibility Inflight Emergency

A
  • PIC has responsibility and final authority for operation of aircraft
  • Can deviate from any rule or regulation in an emergency situation to meet the emergency
  • Send a written report upon request of the administration when rule is deviated
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5
Q

Documents For PIC

A
  • Pilot Certificate
  • Photo ID
  • Medical certificate
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6
Q

Eligibility and Requirements For Private Pilot

A
  • 17 years of age
  • Speak, read, write, English
  • 3rd class medical
  • M eet experience requirements
  • P ass written/oral and practical test
  • G round and flight endorsements
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7
Q

SMILE

A

Documents on person:

  • Student pilot certificate
  • Medical
  • ID
  • Logbook
  • Endorsements
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8
Q

AROW

A

Documents for airworthiness:

  • Airworthiness certificate
  • Registration
  • Operators handbook
  • Weight and balance
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9
Q

FADWAR

A

Pre-flight action 91.103:

  • Fuel
  • Alternates
  • Delays
  • Weather
  • Aircraft
  • Runway
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10
Q

NAILS or FLAPS

A

Required equipment VFR night 91.205:
-Navigation lights -Fuses
-Anti-collision lights -Landing lights
-Instrument lights -Anti-collision lights
-Landing lights -Position lights
-Source of power -Source of power
add CG/LG = Celestial or ground illumination for R22

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11
Q

CAMAFOOTS

A

Required equipment for day VFR 91.205:

  • Compass
  • Altimeter
  • Manifold pressure
  • Airspeed
  • Fuel gauge
  • Oil temp
  • Oil pressure
  • Tachometer (engine)
  • Seat belts
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12
Q

CROCWAAG

A

Required equipment POH:

  • Cylinder head temp
  • Rotor tach
  • Outside are temp
  • Warning lights
  • Carb heat
  • Alternator
  • Amp
  • Governor
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13
Q

Heli-FACTFOID

A

Immediate report to NTSB 830:

  • Heli = rotor blades or tail strikes ground
  • Fire in flight
  • Accident
  • Collision in air
  • Turbine failure not out the exhaust
  • Flight control loss
  • Overdue
  • Inability of a crew member
  • Damage to property of 25k or greater
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14
Q

100 PASTVALT

A

Required inspections

  • 100 hour inspection
  • Pitot/Static system
  • Airworthy directives
  • Service Bulletins
  • Transponder
  • VOR
  • Annual
  • Life limited parts
  • Time before overhaul
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15
Q

IMSAFE

A

Pilot self assessment:

  • Illness = any symptoms
  • Medical = prescriptions or OTC drugs
  • Stress = psychological, physiological, personal problems
  • Alcohol = drinking within the last 8hrs 24hrs
  • Fatigue = tired or not adequately rested
  • Emotions = angry, depressed, or anxious
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16
Q

PAVE

A

Personal minimum checklist for pilots:

  • Personal = hrs sleep, hrs flight, experience, meds
  • Aircraft = airworthy, inspections, fuel, w/b, performance
  • enVironment = weather, pireps, notams, airspace, terrain
  • External = stressed or anxious, pressure to perform, plan b, difficult passengers, unhealthy safety culture, abilities
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17
Q

R22 Operation Limitation Day/Night

A

VFR day approved
VFR Night - orientation must be maintained by visual reference to ground objects illuminated solely by lights on the ground or celestial illumination
FLAPS C/G or NAILS C/G

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18
Q

R22 VFR Equipment

A 
CAMAFOOTS
Compass
Altimeter
Manifold pressure
Airspeed
Fuel gauge
Oil temp
Oil pressure
Tachometer(engine)
Seat belts
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19
Q

R22 Night VFR Equipment

A

FLAPS C/G NAILS C/G

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20
Q

Angle Of Attack

A

Angle between the chord line(CL) and the resultant relative wind(RW)

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21
Q

H/V Diagram

A
  • Height to velocity chart

- Safe/unsafe flight operations

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22
Q

CHT Overheats

A

Cylinder Head Temperature

-blown head gasket may occur causing serious damage and engine failure

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23
Q

Engine Oil Overheats

A

Could cause serious damage and lead to engine failure

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24
Q

Danger Of Exceeding Manifold Pressure

A
  • could damage engine as well as blade failure

- Robinson safety notice SN-37 + SN-39

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25
Q

Danger If You Overspeed Engine

A

Could result in damage to the engine which could result in the engine seizing causing the pilot to perform an autorotation

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26
Q

Danger Of Flying Over Gross Weight

A
  • Illegal per FAR 91.9(a)

- Put extra stress on parts of the helicopter not designed for over gross weight operations

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27
Q

Danger If You Overspeed Main Rotor

A

Cause severe damage to the main rotor mast and may cause separation of the main rotor mass

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28
Q

Torque

A

something that produces or tends to produce torsion or rotation; a moment of a force or system of forces tending to cause rotation

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29
Q

Stall

A

Low Rotor RPM Stall - Blade Stall:

  • Rotor stall is a complete loss of lift from RPM decay
  • Recovery not possible if stalled completely

Blade Stalls at 80% RPM @ sea level:

  • Critical angle of attack is exceeded to RW coming from below
  • Increases in drag, insufficient centrifugal force for blade rigidity
  • 80% + 1% per 100ft altitude

Causes:

  • Not reacting to RPM decay quick enough
  • Reacting to low rotor RPM the wrong way
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30
Q

Basic Empty Weight

A

Starting point of weight and balance computations:

  • Weight of standard helicopter
  • Optimal Equipment
  • Unusable fuel
  • Full operating fluids(including engine oil)
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31
Q

Moment

A

Product of the weight of an object multiplied bu it’s arm and expressed in pound-inches
Weight x Arm = Moment

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32
Q

Pilot Restrictions

Drugs + Alcohol

A
  • 8 hour bottle to throttle
  • Not be over .04 blood alcohol level
  • Cannot use drugs that effect pilots faculties
  • Cannot fly under the influence
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33
Q

Intoxicated Persons?
Portable Electronic Devices?
Objects Be Dropped?

A
  • No intoxicated persons on aircraft unless they are a patient
  • No devices that can interfere with radio signals
  • Yes, if reasonable precautions are taken to protect persons and property
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34
Q

Dangers Of Using Low Octane Fuel

A
  • Poor air/fuel mixture in carburetor engines
  • Excess fuel left in cylinders causing pre-ignition and engine knock
  • Can eventually lead to engine damage
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35
Q

Redline On MAP Gauge

A

Do not exceed this number

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36
Q

Clutch Actuator

A

-Electrical system located between the two drive sheaves
-Raises upper sheave when the clutch is engaged
=Actuator senses belt tension and switches off when the V-belts are tensioned to a prescribed value

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37
Q

Cabin Heat

A
  • Fresh air vent is heated by an exhaust shroud and is directed into the cabin
  • Fresh air is mixed with the heated air thru a plunger control
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38
Q

Acrobatic Flight Is Not Permitted Where?

A

No Acrobatic Flight In R22 Allowed!

FAR 91.303

  • Over a congested city or town
  • Over an open air assembly of people
  • Within lateral boundaries of Class B,C,D, or E airspace designed for airports
  • Below altitudes of 1,500ft
  • When flight visual is less than 3 miles
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39
Q

Solo In The Left Seat?

A

No - Not permitted by Robinson

  • Possibility of running out of cyclic authority due to center of gravity
  • Controls/radio on left for easier access
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40
Q

Center Of Gravity

A

Point a which an aircraft will balance

Total Moment / Total Weight = CG(inches aft of datum)

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41
Q

Datum

A

Fixed starting point of a scale

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42
Q

Empty Weight

A

Airframe, engine, fixed equipment and unusable fuel and oil

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43
Q

Useful Load

A

Pilots, passengers, baggage, oil and fuel

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44
Q

Sympathetic Resonance

A
  • Occurs in the R22 between 60-70% RPM. This type of vibration occurs when the main rotor frequencies interact with the tail rotor frequencies
  • Can cause the drive shaft in the tail boom to start vibrating and oscillating causing damage
  • Keep rotor RPM out of 60-70%, hence yellow band
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45
Q

Drag

A
  • Force opposing thrust and is the retarding force created by the development of lift + movement
  • An aerodynamic force on a body acting parallel and opposite to relative wind
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46
Q

Lift

A
  • Vertical forced created by the affect of airflow as it passes around and airfoil
  • Lift counteracts weight
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47
Q

Chord Line(CL)

A

Imaginary straight line between the blades leading edge and the tailing edge of an airfoil section

48
Q

Pitch Angle

A

Angle between the chord line and the plane of rotation

49
Q

Relative Wind

A

Resultant Relative:
resultant airflow velocity as a result of blade rotation, induced flow, blade flap, along with airspeed and wind velocities

Rotational Relative:
Airflow velocity over the blades as a result of blade rotation

50
Q

Airfoil

A

Any surface that provides aerodynamic forces when moving through a stream of air

51
Q

Aircraft Speeds

A
  • Indicated: read off instrument
  • Calibrated: IAS corrected for instrument and position error
  • Equivalent: CAS corrected adiabatic compressible flow and altitude
  • True: CAS corrected for non-standard temp and pressure
  • Ground: TAS corrected for wind
52
Q

Airspeed Indicator

A

Measures difference of pressure from pitot tube and the static source

Limitations:
Getting poor flow to pitot tube

Errors:

  • Position: static port sensing erroneous atmosphere pressure
  • Density: changes in altitude and pressure
  • Compressibility: packing air in pitot tube at hi speed
53
Q

Altimeter

A

Aneroid wafers expand and contract as atmosphere pressure changes, shaft and gear linkage rotate pointers and dials

Limitation:

  • Hi-temp or pressure: altimeter indicates lower than actual altitude(low to high, nothing but sky)
  • Low-temp or pressure: altimeter indicates higher than actual altitude(high to low, look out below)
54
Q

AP WOTFEEL

off airport

A 
A  ltitude
P  ower 
W  ind
O  bstacles
T  errain
F  orced landing zone
E  ntry
E  xit
L  anding zone

High and low reconnaissance

55
Q

Preventive Maintenance

A

Oil changes, hydraulic fluids, operating fluids, wheel bearing lube, bulbs, air filter, shoes on skids, battery, chip detectors, gascolator, cotter pins/safety wires

Logbook entry required:

  • Date of work
  • Description of work
  • Total hours on aircraft
  • Pilot Certificate number
  • Signature of Pilot
56
Q

Recommended Airspeeds

A 
Takeoff and climb: 60KIAS
Max rate of climb(Vy): 53KIAS
Max range: 83KIAS
Landing approach: 60KIAS
Autorotation: 65KIAS
57
Q

Elements Of Aircraft Performance

A
  • Rate of climb
  • Ceiling
  • Payload
  • Range
  • Speed
  • Fuel economy

Takeoffs and Landings:

  • Density Altitude
  • Wind direction
  • Wind speed
  • Weight
58
Q

Factors That Effect Performance

A
  • Density Altitude, weight, wind

- Humidity effects performance because air is less dense

59
Q

Aircraft Certificates and Documents

A

AROW

60
Q

R22 Emergency Water Landing Power On

A
  1. Descend to hover above water
  2. Unlatch doors
  3. Passenger exits aircraft
  4. Fly to safe distance from passenger to avoid possible injury from rotors
  5. Switch battery and alternator OFF
  6. Roll throttle off into over travel spring
  7. Keep aircraft level and apply full collective as aircraft contacts water
  8. Apply later cyclic to stop rotors
  9. Release seat bealt and quickly clear aircraft after rotors stop
61
Q

R22 Emergency Water Landing Power Off

A
  1. Follow same procedures as far as power failure over land until contacting water. If time permits unlatch doors
  2. Apply lateral cyclic when aircraft contacts the water to stop rotors
  3. Release seat belt and quickly clear aircraft when rotors stop
62
Q

R22 Engine De-rated, why?

A
  • Achieves acceptable high-altitude performance
  • Saves weight
  • Increased engine life
63
Q

RPM Of Main Rotor

Why different with power off then power on?

A

Main rotor can safely handle the RPM’s at those given RPM’s, where as the engine cannot

Power On Power Off
Max: 104% Max: 110%
Min: 101% 0-360 Min: 90%
Min: 97% 0-320

64
Q

R22 Tachometer/Governor Failure

A

Tach:
if rotor/engine tach malfunctions in flight, use remaining tach to monitor RPM. If not clear or both fail, allow governor to control RPM and land as soon as practical

Governor:
Engine RPM governor malfunctions, grip throttle firmly to override governor, then switch governor off. Complete flight using manual throttle control

65
Q

R22 Electrical Fire In Flight

A
  1. Master battery switch -OFF
  2. Alternator switch - OFF
  3. Land immediately
  4. Extinguish fire and inspect for damage
66
Q

R22 Loss Of Tail Rotor Thrust

Hover

A
  1. Failure is usually indicated by nose right yaw which cannot be stopped by applying left pedal
  2. Immediately roll throttle off into over travel spring and allow aircraft to settle
  3. Raise collective just before touchdown to cushion landing
67
Q

R22 Fire In Flight

A
  1. Enter autorotation
  2. Master battery switch OFF(if time permits)
  3. Cabin heat OFF(if time permits)
  4. Cabin vent - ON(if time permits)
  5. If engine is running, perform normal landing and immediately shut off fuel valve
  6. If engine stops running, shut off fuel valve and execute autorotation landing
68
Q

R22 Loss Of Tail Rotor Thrust

Forward Flight

A
  1. Failure indicated by nose right yaw which cannot be corrected by applying left pedal
  2. Immediately enter autorotation
  3. Maintain at least a 70KIAS airpseed if practical
  4. Select landing spot, roll throttle off into over travel spring and perform autorotation landing

When suitable landing site is not available, vertical fin may permit limited control at very low power settings and 70KIAS

69
Q

Full Throttle Line

MAP Chart

A

Achieving this altitude is theoretical and most likely unattainable at the current temperature

70
Q

R22 Power Failure

Above 500ft AGL

A

1.Lower collective immediately to maintain rotor RPM
2.Steady glide at 65KIAS
3.Adjust collective to keep RPM between 97-110%
Apply full down if light weight prevents 97%
4.Select landing spot, if altitude permits land into wind
5.Restart attempt at pilots discretion
6.No restart, turn off unnecessary switches and fuel valve
7.About 40ft AGL, begin cyclic flare to reduce rate of descent/speed
8.About 8ft AGL, apply forward cyclic to level, pull collective to cushion

71
Q

R22 Max/Min Gross Weight

A 
Max gross: Standard + HP = 1300lbs
Max Gross: Alpha, Beta, Beta II =1370lbs
Min Gross: 920lbs
Max Per Seat: 240lbs(including baggage compartment)
Max either baggage compartment: 50lbs
72
Q

R22 V(ne)

A

102 KIAS

up to 3000ft

73
Q

R22 Power Failure

8ft - 500ft AGL

A
  1. Lower collective immediately to maintain rotor RPM
  2. Adjust collective to keep RPM between 97-110% or full down if light weight prevents reaching 97%
  3. Maintain airspeed until ground is approached, then begin cyclic flare to reduce rate of descent and speed
  4. About 8ft AGL, apply forward cyclic to level ship and raise collective just before touchdown to cushion landing
74
Q

R22 Power Failure

Below 8ft

A
  1. Apply right pedal as required to prevent yawing
  2. Allow aircraft to settle
  3. Raise collective just before touchdown to cushion landing
75
Q

R22 Max Glide Distance

A
  1. Airspeed appx 75KIAS
  2. Rotor RPM appx 90%
  3. Best glide ratio is about 4:1 or one nautical mile per 1500ft
76
Q

R22 Air-restart Procedure

A
  1. Mixture - full rich
  2. Primer(if installed) - down and locked
  3. Throttle - closed, then cracked slightly
  4. Actuate starter with left hand
77
Q

Rigid Rotor System

A
  • Made up of three or more blades
  • Feathers on hinges
  • Blades absorb the operating loads of flapping and lead/lag through bending rather than hinges
  • They are mechanically more simple but more expensive due to the structural complexity of the blades

Advantages:

  • no mast bumping
  • reliable and easy to maintain

Disadvantages:

  • expensive
  • more vibration
78
Q

Semi-rigid Rotor System

A
  • consists of two or more blades
  • able to feather independently and teeter/flap as a unit
  • type of rotor system on the R22
  • R22 different than others because of coning hinges

Advantages:

  • cheap and easy to maintain
  • small storage space
  • light

Disadvantages:
-low-g mast bumping

79
Q

Fully Articulated Rotor System

A
  • made up of three or more blades
  • able to feather, flap, and lead and lag independent of each other

Advantages:

  • smooth flight conditions
  • no mast bumping

Disadvantages:

  • ground resonance
  • high maintenance
  • heavy
80
Q

Blade Flapping

A

-the way the rotor system compensates for the dissymmetry of lift and creates equal amount of lift across the rotor system

  • more lift on the advancing blade causes the blade to flap up, decreasing the AoA(CL)
  • less lift on the retreating blade side causes the blade to flap down, increasing the AoA(CL)
81
Q

Retreating Blade Stall

A
  • potentially hazardous condition caused by excessive forward speed which causes an excessive angle of attack on the retreating blade
  • stall begins at the tips of the retreating blades due to high AoA

Cause: Indications:
Exceeding Vne -vibrations
high weight -pitching up of the nose(gyro pro)
low rotor RPM -rolling motion(twrd rtring blade)
high DA
steep abrupt turns

Recovery:
Lower collective to decrease the AoA, ensure RPM 104%, gentle aft cyclic

82
Q

Settling With Power

A
  • helicopter settles into its own downwash and vortices
  • state of powered flight where the heli descends rapidly even with power

3 requirements:

  • Vertical descent of 300ft/min or greater
  • must have power applied (20% or more)
  • A/S is less than ETL

Indications:

  • increased vibrations
  • uncommanded pitch, roll and yawing
  • little cyclic authority
  • OGE hover with descent rate
  • Tail wind approach
  • steep approach with high descent rate

Recovery(eliminate one of 3 req.):

  • forward cyclic for airspeed
  • ASI and trim come alive, climb profile, pitch for power
83
Q

Loss Of Tail Rotor Effectiveness

LTE

A

-tail rotor is unable to provide adequate thrust to maintain directional control; not a tail rotor failure

3 types of wind induced LTE:
-main rotor interference = wind from NW into heli
-weather cock = wind from behind
tail rotor cortex ring state = wind from rotor side of heli

84
Q

Autorotation

A

-state of flight in which the rotor blades are driven solely by the aerodynamic forces resulting from the rate of descent and an upward flow of air through the rotor disc

-sprag clutch:
allows for an autorotation by automatically disengaging the rotor system from the engine
direction of airflow:
airflow is from below the disc no longer being pulled down from above by the rotors

85
Q

Mast Bumping

A
  • when the rotor hub teeters/flaps so great that it contacts the rotor mast
  • can occur in an unloaded rotor system by applying lateral cyclic during the rolling movement of the fuselage
  • severe damage likely, even potentially chopping off the rotor hub

Causes:

  • incorrect inputs or no inputs during low-g conditions
  • excessive blade teetering/flapping
  • gust, wind, turbulence
  • abrupt cyclic inputs

Correction:

  • light aft cyclic
  • left cyclic for roll
86
Q

AvGas Colors

A

91/96 Purple (all engines)
100LL Blue (all engines)
100/130 Green (320-b2c + 360 j2a)

Weighs 6lbs a gallon

87
Q

Ground Resonance

A
  • vibration of large amplitude resulting from a deliberate or unintentional oscillation of the helicopter from the ground contact or when resting on the ground
  • on set recognizable by slow rocking of the fuselage
  • initiate lift off if power and rotor RPM permit
  • not able, shut down and immediately apply rotor brake
88
Q

ARM

A

-horizontal distance measured in inches from the datum line to a point on the aircraft

+ Positive if move aft
- Negative if moved forward

89
Q

Electrical System

A

Battery:
12volt 25 amp
-starts engine
-store energy = 20 minutes worth if power failure

Alternator:
14volt 60amp
-primary source for power to electrical system, charge battery

Circuit Breakers:
-protects against over voltage, push to reset

Magnetos(x2)

90
Q

Fuel System

A

Two Tanks:

  • main(19.8/19.2)
  • aux(10.9/10.5)
  • gravity fed
  • shut off valve behind left seat
  • gascolator = sediment bowl or fuel strainer
  • tank air vent = prevents vacuum from developing in tanks, in main mast
91
Q

Ignition System

A

Magnetos:
small electrical generators driven by crankshaft rotation to provide voltage for spark plugs

Why two?

  1. Redundancy: two if aircraft loses one magneto, still has another to run off
  2. Performance: two sparks allow more complete combustion
92
Q

Oil System

A

Two types:

  1. Mineral oil: for engine break in purposes, no additions
  2. Ashless dispersant: mineral oil with additives, multi viscosity, suspends contamination

Quantity:
4-6 quarts

Weight:
7.5lbs per gallon

93
Q

Carb Ice + Indications

A
  • moisture in air freezes in the carburetor due to the low pressure/low temp
  • indicated by RPM drop
  • RPM will go back up if the carb heat is applied
  • warm/cool air, high moisture content
94
Q

Engine Fire On Ground

A
  1. Continue to start engine
  2. If it starts, run at 50-60% then shut off
  3. If it doesn’t, turn off fuel and battery
  4. Put out fire
  5. Inspect for damage
95
Q

Instruments On Pitot/Static System

A
  1. Altimeter
  2. Vertical airspeed
  3. Airspeed indicator
96
Q

Landing Gear On R22

A

Spring and Yield

  • will absorb most landings
  • hard landings will hinge up and outward
97
Q

Flight Review R22

A

-energy management
-mast bumping
-low rotor RPM
-low-g hazards
rotor RPM decay

98
Q

Limitations Not On Airspeed Indicator

A 
V(A):design maneuvering speed
V(LO):landing gear operating speed
V(LE):landing gear extended speed
V(X):best angle of climb speed
V(y):best rate of climb
V(ySE):single engine best rate of climb
V(MC):minimum control speed
99
Q

R22 MAP Limitation

A

Standard:
yellow - 23.2-25.9
red - 25.9

HP+Alpha(o-320-b2c):
yellow - 21.0 -24.1
red - 24.1

Beta(0-320-b2c)
yellow - 21.0 - 25.2
red - 25.2

Beta II(0-360-j2a)
yellow - 19.6-24.1
red - 24.1

100
Q

R22 Temperature Limitations

A

Oil temp:
green 75-245°
red 245°F

CHT:
green 200-500°
red 500°F

Carb Temp:
yellow arc: -15°-5°sC

101
Q

Lift Equation

A

Lift = CL 1/2p V2 S

CL= coefficent of lift
1/2p = half rho(rho relates to air density)
V2 = velocity squared (velocity is a vector quantity made up of speed and direction)
s = surface area of wing
102
Q

Define:
Category
Class
Type

A 
Category:
airplane, rotorcraft, glider
Class:
helicopter, gyroplane
Type:
specific model
103
Q

Center Of Pressure

A

-imaginary point on the chord line where the resultants of all aerodynamic forces are supposed to be concentrated

104
Q

Magnus Effect

A

-cylinder rotating in an airstream in the same direction of airflow, local velocity is high on top and low on the bottom

high velocity = low pressure
low velocity = high pressure

Air always moves to areas of low pressure

105
Q

Bernouilli’s Principle

A
  • as air velocity increases the pressure decreases
  • air traveling over the upper surface of the airfoil moves faster
  • creates a lower pressure on the upper surface than the lower surface, thus creating lift
106
Q

Dissymmetry Of Lift

A
  • difference in lift between the advancing and retreating halves of the rotor disc due to different velocities of relative wind
  • counterclockwise rotating rotor systems advance on the right and retreat on the left

Advancing side:
-Res. RW = tip speed + relative wind(forward airspeed and/or wind)

Retreating side:
Res. RW = tip speed - relative wind(forward airsseed and/or wind)

107
Q

Effective Translational Lift

A

The increase in rotor system efficiency due to an increase in horizontal relative wind across the entire rotor disc

  • occurs with relative winds of about 16-24KIAS
  • horizontal RW allows both the MR and TR to outrun vortices
  • Rotor system is more efficient due to smaller vertical IF, increases AoA for the same collective pitch
  • efficiency continues to increase until the L/D max 53KIAS where the total drag is at its lowest point
  • recognized by a left yaw and nose pitch up, heli tries to climb
  • correct by giving right pedal and forward/left cyclic inputs
108
Q

Transverse Flow Effect

TFE

A
  • the difference in lift between the fore and aft portions of the disc
  • acceleration in forward A/S causes vertical IF to drop significantly in the fore portion of the rotor disc and remain the same in aft
  • due to gyroscopic tendency, max lift is felt 90° in direction of rotation causing the tendency for the heli to roll slightly to the right as it accelerates through 20KIAS
  • recognized bu increased vibrations at airspeeds just less than ETL
  • as A/S increases, heli responds with a right roll and pitch up of the nose
  • correct by giving forward/left cyclic inputs to push thru into ETL
109
Q

Translational Lift

A

-additional lift gained due to horizontal movement of the aircraft or surface winds
-any movement or wind creates a more horizontal airflow across both the MR and TR systems
-vertical induced flow decreases as airflow becomes more horizontal, creating a greater AoA for the same collective pitch
MR system vortices begin to recede in the forward portion of the disc

110
Q

Gyroscopic Procession

A
  • when force is applied to a rotating body, the deflection will manifest 90° later in the direction of rotation
  • pitch angle change applied at the 3 o’clock position will manifest at the 12 o’clock position in a rotor system rotating counter clockwise
111
Q

Ground Effect

A
  • any increase in rotor efficiency due to the proximity of the ground
  • occurs when the aircraft is within 1 rotor diameter of the ground due to the change in induced flow

Out of ground effect(OGE):
-greater than 1 rotor diameter from ground, allows full vortex
In ground effect(IGE):
-less than 1 rotor diameter above the ground over a hard smooth surface 2 diameters wider
-increases AoA for the same pitch angle

112
Q

Coriolis Effect

A
  • tendency of a rotor blade to change its rotational velocity(RPM) in its plane of rotation when the Center of Mass(CM) moves closer or further from the Axis of Rotation(AoR)
  • blade flaps center of mass moves closer to the AoR causing an increase in RPM (ice skater)
113
Q

Blade Coning

A
  • an upward sweep of the rotor blades as a result of lift and centrifugal force
  • angle determined by the resultant force of lift and centrifugal force
  • allowed through blade bending, the flapping hinge, the coning hinge, or a combo of both
  • accentuated by - low RPM, high GW +load factor
114
Q

Translating Tendency

A

-tendency for a helicopter to drift in the direction of the tail rotor thrust during hovering flight

Compensated by:

  • manual inputs
  • main rotor mast rigging
  • flight controls rigging
  • tail rotor location
115
Q

Light Gun Signals

A

Steady Green:
G = cleared for takeoff
A = Cleared to land

Flashing Green:
G = cleared to taxi
A = return for landing

Steady Red:
G = stop
A = give way to other aircraft

Flashing Red:
G = taxi clear of runway
A = airport is unsafe / do not land

Flashing White:
G = return to starting point

Alternating Green/Red:
A = exercise extreme caution

Private Pilot Study (2 decks)

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