1. HOMEWORK PHAK CHAPTER 10 JEPPESEN Chapter 8 section A GLEIM CHAPTER 5
ASA CHAPTER 8
8-21 TO 8-35
The next test will be 100% ASA

2. Private Pilot Ground School Class #7

3. Content of Lesson
Meterlogical conditions and their effect on performance.
Density altitude effect on takeoff and climb.
Use of Various performance charts.
Safe and efficient operation of aircraft

4. Meterological Conditions
Weather greatly effects aircraft performance.
Wind, Atmospheric Pressure, Temperature, Humidity all affect how an aircraft performs.

5. Terms
Density altitude; measurement of the density of the air expressed in terms of altitude. Density altitude is pressure altitude corrected for a non standard temperature.
High density altitude; a condition in which the air is less dense

6. High Density Altitude 4 things contribute to a high density altitude:
1. High field elevation
Density altitude is increased by an increase in field elevation i.e. Seattle to Denver
18,000 feet atmospheric pressure is roughly halved

7. High Density Altitude 2. Low pressure system
Density altitude is increased by a decrease in pressure
Low pressure weather system = lower pressure

8. High Density Altitude 3. High temperature
Density altitude is increased by an increase in temperature
Spreads out molecules makes air less dense

9. High Density Altitude 4. High humidity
Density altitude is increased by an increase in humidity
A given volume of dry air is more dense than the same volume of moist air

10. High Density Altitude
The atmosphere is 78% nitrogen 21% oxygen 1% inert gases
Water vapor varies from almost none to 5% by volume
Water vapor then displaces oxygen molecules

11. High vs. Low Density Altitude
Hot, humid, high elevation and low pressure = High density altitude
Cold, dry, low elevation and high pressure = Low density altitude

12. High Density Altitude Airplane effected several ways:
1. Wing is less effective
2. Propeller is less effective
3. Engine puts out less horsepower

13. Performance is effected High Density Altitude:
1. Rate of climb is lower
2. Time to climb is longer
3. Takeoff roll is longer
4. Acceleration is slower
5. Higher true airspeed means faster approach
6. Longer landing roll

14. So how can the pilot minimize the effects of High density altitude?
1. Leave in the morning when its cooler
2. Off load some baggage and or passengers
3. Make two trips
4. Take a higher performing aircraft

15. Continued
5. Lean the engine for more horsepower unless POH says not to
6. Do your calculations ahead of time and make the go, no go decision early.
Do not let the people you travel with or Boss make you compromise safety

16. Density Altitude
The primary reason for computing density altitude is to determine aircraft performance
Remember Density altitude is Pressure altitude corrected for nonstandard temperature

17. Density Altitude It can be found 2 ways 1. Use the chart
2. Use the computer

18. Standard Atmosphere
29.92, millibars, psi standard sea level
59 F or 15 C standard temp. at sea level

19. Computing Density Altitude
1st step: convert elevation or altitude to pressure altitude.
can be done by setting into altimeter or by subtracting from the current pressure then multiplying by 1000 then either adding or subtracting from the current pressure value

20. Computing Density Altitude
E.G. Field elevation 1185 pressure 30.55
29.92
x 1000 = -630’
= 555’ Pressure Altitude

21. Computing Density Altitude
So the airplane thinks its flying at 555 feet because of the extra pressure
555 is closer to sea level than 1185

22. Computing Density Altitude
E.G. Field elevation 1185 pressure 29.62
29.92
-29.62
.30 x 1000 = = 1485

23. Computing Density Altitude
So the airplane thinks its flying at 1485 feet because of the decrease in atmospheric pressure
2nd step: Take the pressure altitude and the temperature at your elevation or altitude and follow the lines on the density altitude chart until they intersect.

24. DENSITY ALTITUDE CHART

25. Summary of Effects of Density Altitude (P153)
Low-Density Altitude - made with Low temperature, Dry air and High Pressure
High-Density Altitude - made with high temperature, humid air, low pressure.

26. Performance Charts Conversion charts Wind component chart
Take-off distance chart
Climb chart
Time, Fuel and distance to Climb chart
Cruise Power Settings
Cruise Speeds
Range/Endurance Charts
Landing Distance Chart

27. Crosswind chart

28. B-19 CROSSWIND

29. DENSITY ALTITUDE CHART

30. Takeoff distance chart

31. Cruise Performance Chart

32. Landing Distance Chart

33. Landing Distance

34. Vy & Vx Vy=best rate of climb (most altitude over any unit of time)
Vx=best angle of clime (most altitude over a given distance)
B-19 Vy=72 knots
Vx=65 knots

35. Maximum Range & Endurance
Maximum Range=gives longest distance for a given amount of fuel.
Maximum Endurance=gives you most time for a given amount of fuel.

36. PERFORMANCE #2

37. B-19 CHARTS Airspeed Calibration Altimeter Correction Crosswind
Takeoff Distance
Climb charts
Cruise
Landing distance charts
BRING A CALCULATOR, B-19 MANUAL AND SECTIONAL CHART NEXT CLASS PLEASE

38. AIRSPEED CALIBRATION

39. ALTIMETER CORRECTION

40. CROSSWIND CHART B-19

41. Sample X-Wind problems
Runway 18, Wind
What is the headwind & crosswind components?
Runway 22, wind knots
What is the headwind and crosswind components?

42. Sample X-Wind problems
Runway 18, Wind
What is the headwind & crosswind components?
Runway 22, wind knots
What is the headwind and crosswind components?
H.W. = knots
C.W. = 12.5 knots
H.W. = 5.56 knots
C.W. = knots

43. Takeoff Distance B19

44. Takeoff Distance B19 Given
Wind 0 knots, Temp. 7 degrees C, Pressure Altitude 2000 ft
What is the Takeoff distance?

45. Takeoff Distance B19 1 degree = 1062 11 degrees = 1178
7 degrees = ? (you need to interpolate)

46. Takeoff Distance B19 1 degree = 1062 11 degrees = 1178
7 degrees = ? (you need to interpolate)
11-1= =116
11-7= x.4=46.4
4/10 or =1131.6

47. Takeoff Distance B19 1 degree = 1062 11 degrees = 1178
7 degrees = ? (you need to interpolate)
11-1= =116
7-1= x.6=69.6
6/10 or =1131.6

48. Takeoff Distance B19
What if the Pressure Altitude was 1000 feet instead of 2000 feet
We have already solved for 2000 feet the next step would be to solve for sea level for 7 degrees C.
15-5= =100
15-7= x.8=80
8/10 or =950

49. Takeoff Distance B19 (7 Degrees)
Takeoff distance at 2000 feet Pressure altitude =
Takeoff distance at sea level = 950
Last step is to interpolate for 1000 feet Pressure altitude
2000-0= =181.6
= x.5=90.8
1000/2000 or =1040.8

50. CLIMB CHARTS B19

51. CRUISE CHART B19

52. LANDING DISTANCE CHART B19