Basic Instrument Flying Flashcards
1
Q
3.1 BASIC INSTRUMENT FLYING
KEYNOTES
- Purpose
- CPL
- IFR rating
- Partial panel
A
- PURPOSE
- Provide the skill to safely recover from inadvertenly entering IMC by executoong a 180 degrees turn back toward VMC conditions
- CPL, provide the skill necessary for
- VFR OTT
- Night flying
- Possibility is high to inadvertely entering IMC
- Why instrument training for CPL is more extensive than PPL
- IFR RATING
- IFR rules in IMC conditions
- Skills complex and require extensive training
- PARTIAL PANEL
- VFR aircraft may not be equipped with full IFR panel
- Instrument can fail
2
Q
3.1.1 HUMAN FACTORS
REVIEW 2.1.10
- Student may feel
- Maintening control
A
- STUDENT MAY FEEL the aircraft is
- Climbing,
- Turning,
- Descending
- Review
- Visual illusions
- Vestibular illusion
- MAINTENING CONTROL of the aircraft
- MUST rely on their instrument to maintain control
3
Q
3.1.2 PITOT STATIC SYSTEM
STATIC AND DYNAMIC PRESSURE
- Static pressure
- Dynamic + Static pressure
- Calibration
A
- STATIC PRESSURE
- Altimeter
- Vertical speed indicator
- DYNAMIC + STATIC PRESSURE
- Aispeed indicator
- CALIBRATION
- To be used IFR flight or VFR in transponder airspace
- Static system must be calibrated within the previous 24 months
4
Q
3.1.2 PITOT STATIC SYSTEM
VSI
- Purpose
- Static port blocked
A
- PURPOSE
- Mesure the rate of change of atmospheric pressure
- Determine a vertical speed fpm
- STATIC PORT BLOCKED
- VSI will show zero fpm
5
Q
3.1.2 PITOT STATIC SYSTEM
ALTIMETER
- Purpose
A
- PURPOSE
- Mesures atmospheric pressure
- Relies on a relationship between
- Atmospheric pressure, and
- Altitude
6
Q
3.1.2 PITOT STATIC SYSTEM
AIRSPEED INDICATOR ASI
- Satic pressure
- Total pressure
- Dynamic pressure
A
- STATIC PRESSURE
- Static pressure is read at the static port
- TOTAL PRESSURE
- Total air pressure is read by the pitot tube
- Made of 2 components
- Dynamic pressure (1/2pV2), plus
- Static pressure
- DYNAMIC PRESSURE
- Mesure by ASI by subtracting
- Static pressure read at the static port, from
- Total air pressure read by the pitot tube
- Dynamic pressure = Total pressure - Static pressure
- Mesure by ASI by subtracting
7
Q
3.1.2 PITOT STATIC SYSTEM
IAS, CAS
- Purpose for ASI
- IAS readings
- CAS
- V-speeds
A
- PURPOSE FOR ASI : two
- Stay within structural and aerodynamic limit
- Related to dynamic pressure
- For navigation after some conversion
- Stay within structural and aerodynamic limit
- IAS READINGS
- IAS
- Some errors result from
- The location of the pitot tube
- Not sensing exactly the true dynamic pressure
- Friction in the IAS mechanism itself
- The location of the pitot tube
- CAS
- IAS corrected = CAS
- V-SPEEDS
- Structural + aerodynamic limits are related by dynamic pressure
- Closely approximated by IAS
- Excatl by CAS
- Limits are provided in POH/AFM in for of V-speeds
- May be in
- IAS, or
- CAS
- If CAS use, there is a chart to convert IAS to CAS in POH
- May be in
- IAS, CAS not drirectly useful for navigation
- Structural + aerodynamic limits are related by dynamic pressure
8
Q
3.1.2 PITOT STATIC SYSTEM
V-SPEEDS
- Displayed on IAS
- White arc
- Green arc
- Yellow arc
- Red radial line
- Va
- Vx
- Vy
- Vno
- Vne
- Vs1
- Vso
A
- DISPLAYED ON IAS
- Several critical are display on IAS
- WHITE ARC
- Bottom : Vso
- Top : Vfe
- GREEN ARC
- Bottom : Vs1
- Top : Vno
- YELLOW ARC
- Bottom : Vno
- Top : Vne
- RED RADIAL LINE
- Vne
- VA
- Maximum manoeuvring speed
- Reducing speed below this value in turbulence will help the ensure that the airframe stalls before it breaks
- Generally this speed decrease with decrease gross weight
- VX
- Speed for best angle (or steepest) climb
- In most piston is just above the take-off speed
- Give a descent safety margin above the stall speed
- Allow for
- Gusty condition
- Pilot handling error
- VY
- Speed for best rate of climb
- Approximately produce
- The best range
- The best glide ratio
- Slightly highr that the speed for minimum power consumption
- VNO
- Maximum structural cruising speed
- Kown as the top of the green arc
- Bundary with yellow arc
- Should not exceed this speed
- Except in smooth air
- VNE
- Never exceed speed
- Know as red-line speed
- Speed that should never be exceeded
- VS1
- Stall speed
- Valid only
- Straight and level
- Maximum gross weight
- CG most forward position
- Indicating stalling speed does not change with a change in altitude
- VSO
- Stall speed in the landing configuration
- Will vary according to the landing configuration used
- Bottom of the white arc only if
- Full flaps
- Maximum landing weight
- CG most forward allowable position
9
Q
3.1.2 PITOT STATIC SYSTEM
TAS
- IAS informations
- IAS indication
- Air density
- TAS
- Resume IAS,CAS,TAS
A
- IAS INFORMATIONS
- Enable to stay within the aerodynamic and structural limit of the airframe
- Provide aispeed information for navigation
- IAS indication
- From dynamic pressure
- Product of TAS2 and air density
- 1/2pV2
- From dynamic pressure
- AIR DENSITY
- Varies with altitude
- Decrease with altitude
- IAS will be less than the TAS
- IAS can not mesure density and correcting for it
- IAS = TAS only at one altitude
- Sea level
- ISO
- Varies with altitude
- TAS
- TAS increase with altitude for the same IAS
- Exemple 100 IAS =
- 100 at sea level
- 107,5 at 5000’
- 115 at 10,000’
- Rule of thumb
- 1,5 % / 1000 ft < 20,000 ft
- 2% / 1000 ft > 20,000 ft
- Using calculator
- Density
- Temperature (OAT)
- Pressure altitude
- Density
- RESUME IAS,CAS,TAS
- IAS (relate to structural limitations)
- Instrument error and position error corrections
- CAS (relate to structural limitations)
- Density correction
- TAS (used in navigation calculations)
- IAS (relate to structural limitations)
10
Q
3.1.2 PITOT STATIC SYSTEM
IAS ERRORS
- Dynamic pressure
- Blocked pitot tube
- Blocked static port
A
- DYNAMIC PREESSURE
- IAS reading (Dynamic pressure) =
- Equal
- Total pressure (Dynamic + Static)
- Pitot tube
- Total pressure (Dynamic + Static)
- Minus
- Static pressure
- Static port
- Static pressure
- Equal
- IAS reading (Dynamic pressure) =
- BLOCKED PITOT TUBE
- May result from icing
- Trapped the Total air pressure
- IAS will react like an altimeter
- Inc with inc in altitude
- Dec with dec in altitude
- IAS will react like an altimeter
- DP (60) = TP (80) (blocked) - SP (20)
- Altitude increase
- DP (70) = TP (80) (blocked) - SP (10)
- Increasing altitude raises ASI readings
- Altitude decrease
- DP (50) = TP (80) (blocked) - SP (30)
- Decreasing altitude lower ASI readings
- Altitude increase
- BLOCKED STATIC PORT
- Static pressure is fixed
- Change in altitude will only affect Total pressure
- Read a the pitot tube
- IAS error will substract incorrect SP
- DP (60) = TP (80) - SP (20) (blocked)
- Altitude increase
- DP (40) = TP (60) - SP (20) (blocked)
- Increasing altitude causes ASI to under read
- Altitude decrease
- DP (80) = TP (100) - SP (20)
- Decreasing altitude casue ASI to over read
- May cause you to slow down and you might stall
- Altitude increase
- 2 Static ports
- Most aeroplane on either side
- Eliminate incorrect reading
- Backup
- Unpressurized airplane
- Alternate staic in cockpit
- Cabin pressure will be slightly lower than the outside pressure
- Most aeroplane on either side
11
Q
3.1.3 ALTIMETRY
ORIGIN OF PRESSURE AT ANY POINT IN THE ATMOSPHERE
- Weight
- Altimeter
A
- WEIGHT
- Of the air above
- Pressure drop as you climb
- ALTIMETER
- Mechanical instrument reads atmospheric pressure
- Convert it in altitude assuming the pressure decrease in height at the ISO rate
- Reality ISO conditions are very rares
- Deviation in
- Temperature
- Pressure
- Real altomoshere deviation from standard cause errors in the altitude indicated by the altimeter
- Deviation in