property of lear siegler

Property of Lear Siegler

1

PHYSICS OF THE ATMOSPHERE

3


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.

4

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.


5

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.”


6

29.9

2”


53,000

18,000Sea Level 50%

90%

Sea Level

7

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’


7500’ 22.42”Hg

8

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’


7500’ 0°C

9

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


10

AIR DENSITY

Press

Hum

Temp

Good Bad

H

L

L

L

H

H

12

Property of Lear SieglerProperty of Lear Siegler

MMMMMMMMOVING

13

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


MMMMMMMMOVING

14

Weight of a column of airStatic Pressure --

Impact Pressure -- Static + Dynamic


Dynamic Pressure – Additional pressure caused by aircraft in motion

15

Static pressure only

Impact pressure = Static + Dynamic


Note: Impact = Ram = Total = Pitot Pressure

17

LEFT

PITOT TUBE

RIGHT

STATIC VENTS


HEATER

Construction of the Pitot System

19


Notice that the Pitot Tube goesonly to airspeed indicator!

The Static Pressure is ventedto all three instruments.

20


The diaphragm in the Airspeed Indicatoris connected to the Pitot Tube. It

only senses Pitot Pressure. The caseis vented to Static Pressure.

21


The diaphragm in the Vertical Speed Indicator is vented to Static Pressure.The case is vented to Static Pressure

through a calibrated leak.22


The aneroids in the Altimeter are sealed. The case is vented to Static Pressure.

23


MMMMMMMMOVING

24

C: Enabling Learning Objective Action: Identify the operational characteristics of the airspeed indicator

Condition: Given information about the airspeed indicator



25

AIRSPEED INDICATOR


26

LEFT

PITOT TUBE

RIGHT

STATIC VENTS


27

STATIC VENTPITOT TUBE


28


29

Impact pressure = Static + Dynamic


30


??

?? ?

?

?

32

D: Enabling Learning Objective Action: Identify the uses of the airspeed indicator

Condition: Given information on the uses of the airspeed indicator



33

Uses for the airspeed indicator


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


MMMMMMMMOVING

35

E: Enabling Learning Objective

Action: Identify the errors associated with the airspeed indicator

Condition: Given information about airspeed indicator errors



36

ERRORS

Instrument Error – Minor, caused by friction


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

37


MMMMMMMMOVING

38

F: Enabling Learning Objective

Action: Identify the types of airspeed

Condition: Given information about types of airspeed



39

Types of Airspeed

TAS – True Airspeed - Calibrated Airspeed corrected for density error

CAS – Calibrated Airspeed – Indicated Airspeed corrected for installation error


IAS – Indicated Airspeed – read from the airspeed indicator

40

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!


41


TRUE AIRSPEED (TAS) IS THE SAME,AIR IS LESS DENSE AT ALTITUDE,

THEREFORE, CALIBRATEDAIRSPEED (CAS) IS LESS THAN TAS.

42


CAS IS THE SAME, AIR ISLESS DENSE AT ALTITUDE, THEREFORE,

TAS IS MORE THAN CAS AT ANYALTITUDE ABOVE

ZERO FEET DENSITY ALTITUDE.

43


44

Airspeed Indicator in Review…


Can you identify the pressures used, the errors and the types of airspeed?

45


MMMMMMMMOVING

46

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



47

Vertical Speed Indicator


48

LEFT

PITOT TUBE

RIGHT

STATIC VENTS


49

PITOT TUBE

STATIC VENTS


50


CalibratedCalibratedLeakLeak

51



52



53



54


MMMMMMMMOVING

56

H: Enabling Learning Objective

Action: Identify the uses of the vertical speed indicator

Condition: Given information about the uses of the vertical speed indicator



57

Uses of the vertical speed indicator


1: Determine rate of climb or descent

2: Trend instrument-shows attitude changes immediately when in level flight

58

Vertical Speed IndicatorPreflight Check


59


MMMMMMMMOVING

60

I: Enabling Learning Objective

Action: Identify the errors associated with use of the vertical speed indicator

Condition: Given information about vertical speed indicator errors



61

Errors of the vertical speed indicator


1: Six to nine second lag when leveling off from a climb or descent caused by the calibrated leak

62



64

Errors of the vertical speed indicator


1: Six to nine second lag when leveling off from a climb or descent caused by the calibrated leak

2: Erratic in rough air

65

Vertical Speed Indicator in Review…


Can you identify the pressures used, the errors and preflight procedures?

66


MMMMMMMMOVING

67

J: Enabling Learning Objective

Action: Identify the operational characteristics of the altimeter

Condition: Given information about the operational characteristics of the altimeter



69

ALTIMETER


70

LEFT

PITOT TUBE

RIGHT

STATIC VENTS


72

PITOT TUBE

STATIC VENTS


73


Aneroid wafers sealed at factory

74

Dial – three pointersHow to Read How to Read 75

10,000’ IndicatorTick marks in increments of 2000’

76

1,000’ IndicatorTick marks in increments of 200’

77

100’ IndicatorTick marks in increments of 20’

78

1,040’

79

8,000’

80

18,980’

81

Questions?


MMMMMMMMOVING

82

Kollsman window – corrects for atmospheric pressure changes

28.00”Hg to 31.00”Hg83

Set field elevation

ATIS – “Altimeter setting three zero two four”

84

1”Hg change = 1000’change in altitude .10”Hg change = 100’ change in altitude .01”Hg change = 10’ change in altitude

85

AIMS Counter Drum Pointer

ATC Radar Beacon System

Identification Friend or Foe

MARK 12

SYSTEM

86


MMMMMMMMOVING

89

K: Enabling Learning Objective

Action: Identify the uses of the altimeter

Condition: Given information about the uses of the altimeter



90

Uses of the altimeter


Terrain clearance – MEF & OROCA

Vertical separation – Hemispherical Rule

Attitude control – Instrument Flying

91


MMMMMMMMOVING

92

L: Enabling Learning Objective

Action: Identify the types of altitude

Condition: Given information about the types of altitude



93

Identify the types of altitude

a. Indicated

b. True

c. Absolute

d. Pressure (PA)

e. Density (DA)


94

Indicated Altitude

Read from instrument with correctly set Kollsman window (sea level pressure).


95

True Altitude – Altitude above Mean Sea level

MSL

1000’


96

MSL

Absolute Altitude– Altitude above the surface (AGL)


97

MSL

Pressure Altitude (PA) – Altitude above the standard datum plane

29.92 Standard datum plane

1000’


98

Max torque available, max gross weight,and performance are all

affected by Density Altitude


MMMMMMMMOVING

Density Altitude (DA) : Is the densitycorresponding to a given altitude

in a standard atmosphere.

102

Density Altitude (DA) : Pressure Altitude corrected for non standard temperature


DA = PA + (120 Tv )

PA = Pressure AltitudeTv = Temperature Variation

103

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


104

29.92”Hg 15°C 29.92”Hg 32°CMSL

2040’ PA


105

29.92”Hg 15°C 29.92”Hg 32°CMSL

2040’


106


109

PA = 0’

OAT = 36°DA = 2500’


110


DA = PA + (120 Tv )

PA = Pressure AltitudeTv = Temperature Variation

111

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’


113

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


114

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


115

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’


One hour later

OAT = 6°C

116

PA AND STAN TEMP

HIGHER THAN STAN TEMP

LOWER THAN STAN TEMP

DA = PA + (120’ TV)

DA HIGHER THAN PA

DA LOWER THAN PA

117


MMMMMMMMOVING

118

M: Enabling Learning Objective

Action: Identify the errors associated with the use of the altimeter

Condition: Given information about altimeter errors



119

Altimeter errors

a. Instrument / Mechanical Error

b. Pressure Error

c. Temperature Error


120

MSL

TrueAltitude

1000’


Instrument Error

1000’

FieldElevation

Caused by friction inside instrument

121

MSL

TrueAltitude

1000’


Instrument Error

30.24 hg”

“Altimeter three zero two four”

30.26-30.24

= .02= 20 foot error

1000’

FieldElevation

Maximum Error + / - 70 ft

122


Pressure Error – caused when flying intoareas that have different altimeter settings than those set in the Kollsman window.

123

TRUE ALT

TRUE ALT

IND ALTIND ALT


Pressure Error

124


H LIT

125


L HTI

127

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


128

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


129

TRUE ALT

TRUE ALT

IND ALTIND ALT


Pressure Error

Sta

ndar

d te

mp

28.92

28.92

War

mer

29.92 29.92 29.92

28.92

Col

der

130


132

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


133

MSL 15°C

1000’ 13°C

2000’ 11°C

3000’ 9°C

4000’ 7°C

5000’ 5°C

6000’ 3°C


OAT = 5°C

True Altitude is lower than Indicated


134

MSL 15°C

1000’ 13°C

2000’ 11°C

3000’ 9°C

4000’ 7°C

5000’ 5°C

6000’ 3°C


OAT = 5°C

Indicated Altitude = True altitude


135

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

136


MMMMMMMMOVING

137

N: Enabling Learning Objective

Action: Identify pitot static system malfunctions

Condition: Given information about pitot static system malfunctions



138

STATIC VENT PITOT TUBEProperty of Lear Siegler

Pitot Static System Malfunctions

139



140


141



142



143

Altimeter – No change in indication

144

VSI – Level off at zero

145


Airspeed Indicator – opposite of clogged pitot tube

146



147


MMMMMMMMOVING

148

The endThe end

151

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

152

0C H 0 2

M N

248.2GD

TX

156

UHF vs. VHF Frequency

Warm-up Time

Range

161

Warm-up time

Mode C Switch

Code 1200

Lost Communications Code

LEFT

PITOT TUBE

RIGHT

STATIC VENTS


HEATER

162

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

165

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


166


CAS IS THE SAME, AIR ISLESS DENSE AT ALTITUDE, THEREFORE,

TAS IS MORE THAN CAS AT ANYALTITUDE ABOVE

ZERO FEET DENSITY ALTITUDE.

168

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


171


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


172


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


173

TRUE ALT

TRUE ALT

IND ALTIND ALT


Pressure Error

175

property of lear siegler

Documents

property of lear sieglernote

property of lear siegler53

hg 9c4000

hg 15c1000

hg 13c2000

hg 11c3000

hg 7c5000

hg 15c29