Download - Property of Lear Siegler
Property of Lear Siegler
TERMINAL LEARNING OBJECTIVE
At the completion of this lesson, the student will:
ACTION: Demonstrate an understanding of theatmosphere’s physical properties and their impacton the operation of the TH-67 pressure instruments.
CONDITION: In a classroom environment giveninformation on the pressure instruments and the atmosphere.
STANDARD: Answer questions pertaining to theatmosphere’s physical properties and their impact on the operation of the TH-67 pressure instruments. Receive a “GO” by correctly answering the required number of questions on criterion referenced examination 011-0050.
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A: Enabling Learning Objective
Action: Identify the characteristics of the standard atmosphere
Condition: Given information about the standard atmosphere
Standard: IAW FM 3-04.240 and FAA-H-8083-25A,Pilot’s Handbook of Aeronautical Knowledge.
Property of Lear Siegler
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The “Standard Atmosphere”
“A hypothetical vertical distribution of atmospheric temperature, pressure, and density which by
international or national agreement is taken to be representative of the atmosphere for the purpose
of altimeter calibrations, aircraft design, performance calculations, etc.”
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MSL 29.92”Hg
1000’ 28.92”Hg
2000’ 27.92”Hg
3000’ 26.92”Hg
4000’ 25.92”Hg
5000’ 24.92”Hg
Standard Pressure Lapse Rate
1” Hg per 1000’
Property of Lear Siegler
7500’ 22.42”Hg
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MSL 15°C
1000’ 13°C
2000’ 11°C
3000’ 9°C
4000’ 7°C
5000’ 5°C
Standard Temp Lapse Rate
2°C per 1000’
Property of Lear Siegler
7500’ 0°C
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29.92”Hg 15°C
AIR DENSITY
29.92”Hg 15°C29.92”Hg 15°C 28.92”Hg 15°C29.92”Hg 23°C
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B: Enabling Learning Objective
Action: Identify the pressures used in the pitot static system
Condition: Given information about the pitot static system pressures
Standard: IAW FM 3-04.240
Property of Lear SieglerProperty of Lear Siegler
MMMMMMMMOVING
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Weight of a column of airStatic Pressure --
Impact Pressure -- Static + Dynamic
Property of Lear SieglerProperty of Lear Siegler
Dynamic Pressure – Additional pressure caused by aircraft in motion
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Static pressure only
Impact pressure = Static + Dynamic
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Note: Impact = Ram = Total = Pitot Pressure
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LEFT
PITOT TUBE
RIGHT
STATIC VENTS
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HEATER
Construction of the Pitot System
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Construction of the Pitot System
Notice that the Pitot Tube goesonly to airspeed indicator!
The Static Pressure is ventedto all three instruments.
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Construction of the Pitot System
The diaphragm in the Airspeed Indicatoris connected to the Pitot Tube. It
only senses Pitot Pressure. The caseis vented to Static Pressure.
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Construction of the Pitot System
The diaphragm in the Vertical Speed Indicator is vented to Static Pressure.The case is vented to Static Pressure
through a calibrated leak.22
Construction of the Pitot System
The aneroids in the Altimeter are sealed. The case is vented to Static Pressure.
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C: Enabling Learning Objective Action: Identify the operational characteristics of the airspeed indicator
Condition: Given information about the airspeed indicator
Standard: IAW FM 3-04.240
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D: Enabling Learning Objective Action: Identify the uses of the airspeed indicator
Condition: Given information on the uses of the airspeed indicator
Standard: IAW FM 3-04.240
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Uses for the airspeed indicator
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1: Keep aircraft within “Never Exceed Speed"
2: Determine best operational speed for best climb, best endurance, and best range
3: Determine rate of movement for navigation
4: Aircraft attitude
Airspeed fast-Pitch attitude low
Airspeed low-Pitch attitude high34
E: Enabling Learning Objective
Action: Identify the errors associated with the airspeed indicator
Condition: Given information about airspeed indicator errors
Standard: IAW FM 3-04.240
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ERRORS
Instrument Error – Minor, caused by friction
Property of Lear Siegler
Installation Error – Caused by misalignment of the pitot tube and/or the static vents with the relative wind
Density Error – Caused by changes in air density
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F: Enabling Learning Objective
Action: Identify the types of airspeed
Condition: Given information about types of airspeed
Standard: IAW FM 3-04.240
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Types of Airspeed
TAS – True Airspeed - Calibrated Airspeed corrected for density error
CAS – Calibrated Airspeed – Indicated Airspeed corrected for installation error
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IAS – Indicated Airspeed – read from the airspeed indicator
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Estimating True Airspeed
True Air Speed (TAS) increases over Indicated Air Speed (IAS) at the rate of two percent per thousand feet
“Aircraft climbing at a constant IAS will be increasing its velocity or TAS because of decreasing air density.” FM 3-04.203
REMEMBER…True airspeed will always be more than IAS with altitude!
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Property of Lear Siegler
TRUE AIRSPEED (TAS) IS THE SAME,AIR IS LESS DENSE AT ALTITUDE,
THEREFORE, CALIBRATEDAIRSPEED (CAS) IS LESS THAN TAS.
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Property of Lear Siegler
CAS IS THE SAME, AIR ISLESS DENSE AT ALTITUDE, THEREFORE,
TAS IS MORE THAN CAS AT ANYALTITUDE ABOVE
ZERO FEET DENSITY ALTITUDE.
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Airspeed Indicator in Review…
Property of Lear Siegler
Can you identify the pressures used, the errors and the types of airspeed?
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G: Enabling Learning Objective
Action: Identify the operational characteristics of the vertical speed indicator
Condition: Given information about the operation of the vertical speed indicator
Standard: IAW FM 3-04.240
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H: Enabling Learning Objective
Action: Identify the uses of the vertical speed indicator
Condition: Given information about the uses of the vertical speed indicator
Standard: IAW FM 3-04.240
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Uses of the vertical speed indicator
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1: Determine rate of climb or descent
2: Trend instrument-shows attitude changes immediately when in level flight
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I: Enabling Learning Objective
Action: Identify the errors associated with use of the vertical speed indicator
Condition: Given information about vertical speed indicator errors
Standard: IAW FM 3-04.240
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Errors of the vertical speed indicator
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1: Six to nine second lag when leveling off from a climb or descent caused by the calibrated leak
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Errors of the vertical speed indicator
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1: Six to nine second lag when leveling off from a climb or descent caused by the calibrated leak
2: Erratic in rough air
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Vertical Speed Indicator in Review…
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Can you identify the pressures used, the errors and preflight procedures?
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J: Enabling Learning Objective
Action: Identify the operational characteristics of the altimeter
Condition: Given information about the operational characteristics of the altimeter
Standard: IAW FM 3-04.240
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1”Hg change = 1000’change in altitude .10”Hg change = 100’ change in altitude .01”Hg change = 10’ change in altitude
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K: Enabling Learning Objective
Action: Identify the uses of the altimeter
Condition: Given information about the uses of the altimeter
Standard: IAW FM 3-04.240
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Uses of the altimeter
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Terrain clearance – MEF & OROCA
Vertical separation – Hemispherical Rule
Attitude control – Instrument Flying
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L: Enabling Learning Objective
Action: Identify the types of altitude
Condition: Given information about the types of altitude
Standard: IAW FM 3-04.240
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Identify the types of altitude
a. Indicated
b. True
c. Absolute
d. Pressure (PA)
e. Density (DA)
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Indicated Altitude
Read from instrument with correctly set Kollsman window (sea level pressure).
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MSL
Pressure Altitude (PA) – Altitude above the standard datum plane
29.92 Standard datum plane
1000’
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Max torque available, max gross weight,and performance are all
affected by Density Altitude
Property of Lear SieglerProperty of Lear Siegler
MMMMMMMMOVING
Density Altitude (DA) : Is the densitycorresponding to a given altitude
in a standard atmosphere.
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Density Altitude (DA) : Pressure Altitude corrected for non standard temperature
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DA = PA + (120 Tv )
PA = Pressure AltitudeTv = Temperature Variation
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Mean Sea Level (MSL)MSL 29.92”Hg 15°C
1000’ 28.92”Hg 13°C
2000’ 27.92”Hg 11°C
3000’ 26.92”Hg 9°C
4000’ 25.92”Hg 7°C
5000’ 24.92”Hg 5°C
7500’ 22.42”Hg 0°C
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MSL 15°C
1000’ 13°C
2000’ 11°C
3000’ 9°C
4000’ 7°C
5000’ 5°C
6000’ 3°C
PA = 3000’
OAT = 0°C
Stand Temp = 9°C
Tv = OAT - Stand TempTv = 0° - 9°
Tv = -9°
2. Determine Temp Variation (Tv )
DA = PA + (120 Tv )1. Determine Standard Temp for
3000’
DA = 3000’ + (120 X - 9 )DA = 3000’ + (-1080 )DA = 1920’
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MSL 15°C
1000’ 13°C
2000’ 11°C
3000’ 9°C
4000’ 7°C
5000’ 5°C
6000’ 3°C PA = 6000’
OAT = 5°C
OAT is Higher than standardDA is Higher than PA
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MSL 15°C
1000’ 13°C
2000’ 11°C
3000’ 9°C
4000’ 7°C
5000’ 5°C
6000’ 3°C
PA = 4000’
OAT = 5°C
OAT is Lower than standardDA is Lower than PA
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MSL 15°C
1000’ 13°C
2000’ 11°C
3000’ 9°C
4000’ 7°C
5000’ 5°C
6000’ 3°C
PA = 5000’
OAT = 5°C
DA = PA +120’
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One hour later
OAT = 6°C
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PA AND STAN TEMP
HIGHER THAN STAN TEMP
LOWER THAN STAN TEMP
DA = PA + (120’ TV)
DA HIGHER THAN PA
DA LOWER THAN PA
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M: Enabling Learning Objective
Action: Identify the errors associated with the use of the altimeter
Condition: Given information about altimeter errors
Standard: IAW FM 3-04.240
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Altimeter errors
a. Instrument / Mechanical Error
b. Pressure Error
c. Temperature Error
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MSL
TrueAltitude
1000’
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Instrument Error
1000’
FieldElevation
Caused by friction inside instrument
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MSL
TrueAltitude
1000’
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Instrument Error
30.24 hg”
“Altimeter three zero two four”
30.26-30.24
= .02= 20 foot error
1000’
FieldElevation
Maximum Error + / - 70 ft
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Property of Lear Siegler
Pressure Error – caused when flying intoareas that have different altimeter settings than those set in the Kollsman window.
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Temperature Error
MSL MSL
1000’ 1000’
Sta
ndar
d te
mp
29.92
28.92
29.92
28.92
Col
der
29.92
28.92
War
mer
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Temperature Error
MSL MSL
1000’ 1000’
Sta
ndar
d te
mp
29.92
28.92
29.92
28.92
Col
der
29.92
28.92
War
mer
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TRUE ALT
TRUE ALT
IND ALTIND ALT
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Pressure Error
Sta
ndar
d te
mp
28.92
28.92
War
mer
29.92 29.92 29.92
28.92
Col
der
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MSL 15°C
1000’ 13°C
2000’ 11°C
3000’ 9°C
4000’ 7°C
5000’ 5°C
6000’ 3°C
Indicated Altitude = 6000’
OAT = 20°C
True Alt. is Higher than Indicated
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MSL 15°C
1000’ 13°C
2000’ 11°C
3000’ 9°C
4000’ 7°C
5000’ 5°C
6000’ 3°C
Indicated Altitude = 4000’
OAT = 5°C
True Altitude is lower than Indicated
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MSL 15°C
1000’ 13°C
2000’ 11°C
3000’ 9°C
4000’ 7°C
5000’ 5°C
6000’ 3°C
Indicated Altitude = 5000’
OAT = 5°C
Indicated Altitude = True altitude
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IALT, STAN TEMPAND STAN PRESSURE
HIGHER THAN STAN
LOWER THAN STAN
HIGH TO LOW, LOOK OUT BELOW,LOW TO HIGH, CLEAR THE SKY!
TALT HIGHER THAN IALT
TALT LOWER THAN IALT
LOW TO HIGH
TO LOWHIGH
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N: Enabling Learning Objective
Action: Identify pitot static system malfunctions
Condition: Given information about pitot static system malfunctions
Standard: IAW FM 3-04.240
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STOPSTOP
Abandon hope all ye who enter hereAbandon hope all ye who enter here
You are entering the hidden slide ZoneYou are entering the hidden slide Zone
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PA = 6000’
OAT = 5°C
DA is Higher than PAProperty of Lear Siegler
Is the DA higher or lower than PA
MSL 15°C
1000’ 13°C
2000’ 11°C
3000’ 9°C
4000’ 7°C
5000’ 5°C
6000’ 3°C
Standard temperatures
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PA = 4000’
OAT = 5°C
DA is lower than PAProperty of Lear Siegler
Is the DA higher or lower than PA
MSL 15°C
1000’ 13°C
2000’ 11°C
3000’ 9°C
4000’ 7°C
5000’ 5°C
6000’ 3°C
Standard temperatures
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Property of Lear Siegler
CAS IS THE SAME, AIR ISLESS DENSE AT ALTITUDE, THEREFORE,
TAS IS MORE THAN CAS AT ANYALTITUDE ABOVE
ZERO FEET DENSITY ALTITUDE.
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Temperature Error
MSL MSL
1000’ 1000’
Sta
ndar
d te
mp
29.92
28.92
29.92
28.92
Col
der
29.92
28.92
War
mer
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Indicated Altitude = 6000’
OAT = 20°C
True Alt. is Higher than Indicated
Property of Lear SieglerMSL 15°C
1000’ 13°C
2000’ 11°C
3000’ 9°C
4000’ 7°C
5000’ 5°C
6000’ 3°C
Standard temperatures
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Indicated Altitude = 4000’
OAT = 5°C
True Altitude is lower than Indicated
Property of Lear SieglerMSL 15°C
1000’ 13°C
2000’ 11°C
3000’ 9°C
4000’ 7°C
5000’ 5°C
6000’ 3°C
Standard temperatures
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