For the Selected Aircraft Field Elevation Runway Length Obstacle Height Ft. AGL
ID: 802236 • Letter: F
Question
For the Selected Aircraft Field Elevation Runway Length Obstacle Height Ft. AGL Obstacle Distance in Nautical Miles from Initial Runway Position 6076 ft per nautical mile Interpolateto NEXT
HIGHEST 1,000'
for DA
(highest will
be 11,000') Next higher 1,000' DA Single engine 6000 ft 3000 ft 1200 5 30,380' Airliner 6000 ft 6000 ft 2900 5 30,380' Aircraft Type Airport Temperature in degrees Celsius Airport Temperature in degrees Fahrenheit Airport Station Pressure Airport Station Pressure Corrected to Sea-Level Pressure Airport Pressure Altitude (38° F ST) Rule of Thumb Density Altitude Density Altitude Aircraft Chart Takeoff Roll Distance Aircraft Chart Rate of Climb Sufficient Runway Length for Takeoff? (Yes/No) Sufficient Climb Rate to Clear Obstacle? (Yes/No) Aircraft Altitude at Distance of Obstacle after T/O Obstacle Ht. Single engine 20 23.92 29.92 6000 7800 8008 9000 1950 230 Y N 861 1200 40 23.92 6000 10123 11000 1200 Single engine 20 22.92 7000 9380 10000 1200 30 22.92 7000 10448 11000 1200 Single engine 20 21.92 8000 10799 11000 1200 Airliner 20 23.92 6000 8008 9000 2900 30 23.92 6000 9087 10000 2900 40 23.92 6000 10123 11000 2900 Airliner 20 22.92 7000 9380 10000 2900 30 22.92 7000 10448 11000 2900 Airliner 20 21.92 8000 10799 11000 2900 In the article you read, when talking about the density altitude rule of thumb the author states that “(usually any error will be less than 300 feet).” Is the statement accurate based on your calculations? Why? 68-38 = 30F * 600/10 = 1800ft Standard Temp at Elev 86-38 = 48F * 600/10 = 2880ft Elevation ft * 3.5°F/1000ft= T; 59°F- T = St Temp @ elevation 104-38 = 66F * 600/10 = 3960ft DA ROT: 10°F St Temp, Add 600 ft to PA For the Selected Aircraft Field Elevation Runway Length Obstacle Height Ft. AGL Obstacle Distance in Nautical Miles from Initial Runway Position 6076 ft per nautical mile Interpolate
to NEXT
HIGHEST 1,000'
for DA
(highest will
be 11,000') Next higher 1,000' DA Single engine 6000 ft 3000 ft 1200 5 30,380' Airliner 6000 ft 6000 ft 2900 5 30,380' Aircraft Type Airport Temperature in degrees Celsius Airport Temperature in degrees Fahrenheit Airport Station Pressure Airport Station Pressure Corrected to Sea-Level Pressure Airport Pressure Altitude (38° F ST) Rule of Thumb Density Altitude Density Altitude Aircraft Chart Takeoff Roll Distance Aircraft Chart Rate of Climb Sufficient Runway Length for Takeoff? (Yes/No) Sufficient Climb Rate to Clear Obstacle? (Yes/No) Aircraft Altitude at Distance of Obstacle after T/O Obstacle Ht. Single engine 20 23.92 29.92 6000 7800 8008 9000 1950 230 Y N 861 1200 40 23.92 6000 10123 11000 1200 Single engine 20 22.92 7000 9380 10000 1200 30 22.92 7000 10448 11000 1200 Single engine 20 21.92 8000 10799 11000 1200 Airliner 20 23.92 6000 8008 9000 2900 30 23.92 6000 9087 10000 2900 40 23.92 6000 10123 11000 2900 Airliner 20 22.92 7000 9380 10000 2900 30 22.92 7000 10448 11000 2900 Airliner 20 21.92 8000 10799 11000 2900 In the article you read, when talking about the density altitude rule of thumb the author states that “(usually any error will be less than 300 feet).” Is the statement accurate based on your calculations? Why? 68-38 = 30F * 600/10 = 1800ft Standard Temp at Elev 86-38 = 48F * 600/10 = 2880ft Elevation ft * 3.5°F/1000ft= T; 59°F- T = St Temp @ elevation 104-38 = 66F * 600/10 = 3960ft DA ROT: 10°F St Temp, Add 600 ft to PA
Explanation / Answer
Answer:
As the density altitude is one of major important factor in flying of aircraft, it is actually an altitude where aircraft fly, and it is depend upon the pressure and temperature. Therefore, density attitude should be compensated accurately to make a flight successful.
It can be calculated as follows:
Density Altitude= Pressure altitude+[120*(outside air temperature- standard air temperature)]
Where, standard air temperature = 15 oC at sea level. And this temperature is decreases about 2 C per 1000 ft
By calculating the values of density altitude from above formula, we can conclude that the given statement is accurate (by considering the condition, that error will be less than 300 feet)