Chapter 14 – Airplane Performance: Know Before You Go

14-1 Chapter 14 – Airplane Performance: Know Before You Go

Air Density Density Altitude 1. [14[14[14-[14 ---1/3/3]1/3/3] 6. [14[14[14-[14 ---3/All]3/All] Anything reducing the amount of air the engine swal- Density altitude is lows diminishes its _____ output. A. the height above the standard datum plane. A. hydrocarbon B. pressure altitude corrected for nonstandard B. fuel temperature. C. power C. the altitude read directly from the altimeter. Height 2. [14[14[14-[14 ---2/1/3]2/1/3] 7. [[14141414----3/1/5]3/1/5] The higher you go the _____ dense the air is. The term _____ describes how dense the air feels to A. less the airplane, regardless of the airplane’s present B. more or less height above sea level. C. more A. density altitude Heat B. pressure altitude 3. 141414-14 ---2/1/4]2/1/4] C. true altitude Heated air is much _____ dense than colder air. A. more or less 8. [[14141414----3/1/5]3/1/5] B. more Which factor would tend to increase the density alti- C. less tude at a given airport? Humidity A. An increase in barometric pressure. 4. [14[14[14-[14 ---2/1/5]2/1/5] B. An increase in ambient temperature. What effect, if any, does high humidity have on aircraft C. A decrease in relative humidity. performance? A. It increases performance. 9. [14[14----3/2/2]3/2/2] B. It decreases performance. Density altitude, and its effect on landing perform- C. It has no effect on performance. ance, is defined by A) pressure altitude and ambient temperature. 5. [14[14[14-[14 ---3/1/1]3/1/1] B) headwind and landing weight. Which combination of atmospheric conditions will C) humidity and braking friction forces. reduce aircraft takeoff and climb performance? A. Low temperature, low relative humidity, and low 101010.10 . [14[14[14-[14 ---3/2/3]3/2/3] density altitude. What are the standard temperature and pressure val- B. High temperature, low relative humidity, and low ues for sea level? density altitude. A. 15 degrees C and 29.92" Hg. C. High temperature, high relative humidity, and high B. 59 degrees C and 1013.2 millibars. density altitude. C. 59 degrees F and 29.92 millibars.

14-2 Rod Machado’s Sport Pilot Workbook 111111.. [14[14[14-[14 ---4/1/2]4/1/2] 11171777.. [14[14[14-[14 ---7/1/6]7/1/6] What effect does high density altitude, as compared Which would provide the greatest gain in altitude in to low density altitude, have on propeller efficiency the shortest distance during climb after takeoff? and why? A. Vy A. Efficiency is increased due to less friction on the B. Va propeller blades. C. Vx Vx and Vy Change With Altitude B. Efficiency is reduced because the propeller exerts less force at high density altitudes than at low 11181888.. [. [14[ 141414----8/1/8]8/1/8] density altitudes. The best rate of climb indicated airspeed _____ with C. Efficiency is reduced due to the increased force of an increase in altitude, while the best angle of climb the propeller in the thinner air. indicated airspeed _____ with an increase in altitude. A. decreases, increases 11121222.. [14[14[14-[14 ---4/1/2]4/1/2] B. increases, decreases What effect does high density altitude have on aircraft C. increases, remains constant performance? A. It increases engine performance. Cruise Climb Speed B. It reduces climb performance. C. It increases takeoff performance. 11191999.. [. [14[ 141414----8/1/9]8/1/9] Most of the time it’s preferable to climb at some 11131333.. [. [14[ 141414----4/1/2]4/1/2] speed slightly above _____. If the outside air temperature (OAT) at a given altitude A. Vx is warmer than standard, the density altitude is B. Vy A. equal to pressure altitude. C. Va B. lower than pressure altitude. C. higher than pressure altitude. 202020.20 . [14[14[14-[14 ---8/Figure8/Figure 9] Fill in the blanks: Service Ceiling The graph below belongs to a particular model single- engine airplane. Estimate this airplane’s best angle 11141444.. [14[14[14-[14 ---5/1/1]5/1/1] and best rate of climb speeds. An airplane’s service ceiling is the height at which the Vx is ______. climb rate drops to less than _____ feet per minute. Vy is ______. A. 25 B. 50 C. 100

11151555.. [. [14[ 141414----5/1/1]5/1/1] If the density altitude is 13,000 feet and the airplane’s service ceiling is 13,000 feet, the airplane will most likely climb at a rate of _____ at this altitude. A. more than 100 FPM B. less than 100 FPM C. 500 fpm

Best Rate and Best Angle of Climb

11161666.. [14[14[14-[14 ---7/1/5]7/1/5] After takeoff, which airspeed would the pilot use to gain the most altitude in a given period of time? A. Vy B. Vx C. Va

14-3 Chapter 14 – Airplane Performance: Know Before You Go Takeoff Distance Chart

22212111.. [. [14[ 141414----10/1/1/Entire10/1/1/Entire section] 22232333.. [14[14[14-[14 ---10/1/1/Entire10/1/1/Entire section] Referring to the performance chart below, determine Referring to the performance chart below, determine the total distance required for takeoff to clear a 50 foot the total distance required for takeoff to clear a 50 foot obstacle. obstacle.

OAT: Standard temperature OAT: Standard temperature Pressure altitude: 5,000 ft Pressure altitude: Sea level Takeoff weight: 2,800 lb Takeoff weight: 2,700 lb Headwind component: calm Tailwind component: calm A. 1,150 feet. A. 1,000 feet. B. 1,800 feet. B. 1,300 feet. C. 2,000 feet. C. 1,700 feet.

222222.. [14[14[14-[14 ---10/1/1/Entire10/1/1/Entire section] 22242444.. [14[14[14-[14 ---10/1/1/Entire10/1/1/Entire section] Referring to the performance chart below, determine Referring to the performance chart below, determine the approximate ground roll distance required for the approximate ground roll distance required for takeoff. takeoff.

OAT: 90 degrees F OAT: 80 degrees F Pressure altitude: 2,000 ft Pressure altitude: 2,500 ft Takeoff weight: 2,500 lb Takeoff weight: 2,250 lb Headwind component: 20 kts Headwind component: 20 kts A. 700 feet. A. 900 feet. B. 850 feet. B. 500 feet. C. 1,000 feet. C. 700 feet.

14-4 Rod Machado’s Sport Pilot Workbook

22252555.. [14[14[14-[14 ---12/2/2/12/2/2/12/2/2/EntireEntire section] 22272777.. [14[14[14-[14 ---12/2/2/Entire12/2/2/Entire section] Referring to the performance chart above, determine Referring to the performance chart above, determine the total distance required for takeoff to clear a 50 foot the approximate ground roll distance required for obstacle. takeoff. OAT: 20 degrees C OAT: 10 degrees C Pressure altitude: 4000 ft Pressure altitude : 4,500 ft Takeoff weight: 1,670 lb Takeoff weight: 1,670 lb Headwind component: 9 kts Headwind component: 9 kts

A. 2,288 feet. A. 1,073 feet. B. 2080 feet. B. 965 feet. C. 1,872 feet. C. 1,180 feet.

22262666.. [. [14[ 141414----12/2/2/Entire12/2/2/Entire section] 22282888.. [. [14[ 141414----12/2/2/Entire12/2/2/Entire section] Referring to the performance chart above, determine Referring to the performance chart above, determine the total distance required for takeoff to clear a 50 foot the total distance required for takeoff to clear a 50 foot obstacle. obstacle. OAT: 10 degrees C OAT: 20 degrees C Pressure altitude: 2,000 ft Pressure altitude: 5,500 ft Takeoff weight: 1,670 lb Takeoff weight: 1,670 lb Headwind component: 0 kts Tailwind component: 4 kts Runway: dry, grass A. 2,465 feet. A. 966 feet. B. 1,972 feet. B. 1,439 feet. C. 2,958 feet. C. 1,691 feet.

14-5 Chapter 14 – Airplane Performance: Know Before You Go

Landing Distance 33313111.. [. [14[ 141414----14/1/1/Entire14/1/1/Entire section] Referring to the performance chart above, determine 22292999.. [. [14[ 141414----14/1/1/Entire14/1/1/Entire section] the total distance required to land over a 50 foot ob- Referring to the performance chart above, determine stacle. the total distance required to land over a 50 foot obstacle. OAT: 90 degrees F Pressure altitude: 4,000 ft OAT: standard Weight 2,800 lb Pressure altitude: 10,000 ft Headwind component: 10 kts Weight: 2,400 lb Obstacle: 50 ft Wind component: calm A. 1,525 feet. Obstacle: 50 ft B. 1,775 feet. A. 750 feet. C. 1,950 feet. B. 1,925 feet. C. 1,450 feet. 33323222.. [. [14[ 141414----14/1/1/Entire14/1/1/Entire section] Referring to the performance chart above, determine 303030.30 . [. [14[ 141414----14/1/1/Entire14/1/1/Entire section] the total distance required to land over a 50 foot ob- Referring to the performance chart above, determine stacle. the approximate ground roll distance after landing. OAT: 90 degrees F OAT: 80 degrees F Pressure altitude: 3,000 ft Pressure altitude: 5,000 ft Weight 2,900 lb Weight: 2,600 lb Headwind component: 10 kts Tailwind component: 10 kts Obstacle: 50 ft A. 1,750 feet. A. 1,450 feet. B. 1,200 feet. B. 1,550 feet. C. 1,050 feet. C. 1,725 feet.

14-6 Rod Machado’s Sport Pilot Workbook

A Different Landing Distance Chart 33363666.. [14[14[14-[14 ---16/1/1/Entire16/1/1/Entire Section] Referring to the performance chart above, determine the approximate landing ground roll distance. 333333.. [14[14[14-[14 ---16/1/1/Entire16/1/1/Entire Section] Referring to the performance chart above, determine Pressure altitude: 1,250 ft the approximate landing ground roll distance. Headwind: 8 kts Temperature: standard Pressure altitude: sea level A. 275 feet. Headwind: 4 kts B. 366 feet. Temperature: standard C. 470 feet. A. 356 feet. B. 401 feet. 33373777.. [14[14[14-[14 ---16/1/1/Entire16/1/1/Entire Section] C. 490 feet. Referring to the performance chart above, determine the total distance required to land over a 50 foot ob- 33343444.. [. [14[ 141414----16/1/1/Entire16/1/1/Entire Section] stacle. Referring to the performance chart above, determine the approximate landing ground roll distance. Pressure altitude: 7,500 ft Headwind: 8 kts Pressure altitude: 3,750 ft Temperature: standard Headwind: 12 kts Runway: dry grass Temperature: standard A. 1,255 feet. A. 338 feet. B. 1,004 feet. B. 425 feet. C. 1,205 feet. C. 483 feet. 33383888.. [14[14[14-[14 ---16/1/1/Entire16/1/1/Entire Section] 33353555.. [14[14[14-[14 ---16/1/1/Entire16/1/1/Entire Section] Referring to the performance chart above, determine Referring to the performance chart above, determine the total distance required to land over a 50 foot ob- the total distance required to land over a 50 foot obstacle. stacle. Pressure altitude: 5,000 ft Pressure altitude: 2,500 ft Headwind: 8 kts Headwind: calm Temperature: 41 degrees F Temperature: 80 degrees F Runway: hard surface A. 1,135 feet. A. 837 feet. B. 1,192 feet. B. 956 feet. C. 1,078 feet. C. 1,076 feet.

14-7 Chapter 14 – Airplane Performance: Know Before You Go

Time, Fuel and Distance to Climb 44414111.. [. [14[ 141414----17/1/1]17/1/1] 33393999.. [14[14[14-[14 ---17/1/1]17/1/1] Referring to the performance chart above, estimate Referring to the performance chart above, estimate the amount of time and fuel consumed to climb from the amount of time and fuel consumed to climb from 2,000 feet to 9,000 feet pressure altitude under stan- sea level to 7,000 feet pressure altitude under standard temperature conditions. dard temperature conditions. A. 21 minutes, 2.3 gallons. A. 13 minutes, 14 gallons. B. 25 minutes, 2.7 gallons. B. 13 minutes, 1.7 gallons. C. 15 minutes, 1.9 gallons. C. 13 minutes, 2.5 gallons. 44424222.. [14[14[14-[14 ---17/1/1]17/1/1] 40. [14[14----17/1/1]17/1/1] Referring to the performance chart above, estimate Referring to the performance chart above, estimate the amount of time and fuel consumed to climb from the amount of time and fuel consumed to climb from 3,000 feet to 8,000 feet pressure altitude at 10 de- sea level to 5,500 feet pressure altitude at a tempera- grees Celsius above standard temperature condi- ture 10 degrees Celsius above standard. tions. A. 10 minutes, 1.4 gallons. A. 16.5 minutes, 2.2 gallons. B. 9 minutes, 1.3 gallons. B. 5.5 minutes, .7 gallons. C. 9 minutes, 2.1 gallons. C. 11 minutes, 1.4 gallons.

14-8 Rod Machado’s Sport Pilot Workbook

Cruise Performance Chart

44434333.. [. [14[ 141414----18/1/1/Entire18/1/1/Entire section] Referring to the performance chart above, what fuel 44464666.. [. [14[ 141414----18/1/1/Entire18/1/1/Entire section] flow should a pilot expect at 10,000 feet on a standard Referring to the performance chart above, determine day with 65 percent maximum continuous power? the approximate manifold pressure setting with 2,450 A. 19.9 gallons per hour. RPM to achieve 65 percent maximum continuous B. 11.5 gallons per hour. power at 6,500 feet with a temperature 36 degrees F C. 6.6 gallons per hour. higher than standard. A. 19.8" Hg. 444444.. [14[14[14-[14 ---18/1/1/Entire18/1/1/Entire section] B. 20.8" Hg. Referring to the performance chart above, what is the C. 21.0" Hg. expected fuel consumption for a 1,000 nautical mile flight under the following conditions? 44474777.. [14[14[14-[14 ---18/1/1/Entire18/1/1/Entire section] Referring to the performance chart above, approxi- Pressure altitude: 6,000 ft mately what true airspeed should a pilot expect with Temperature: 22 degrees C 65 percent maximum continuous power at 9,500 feet Manifold pressure: 20.8" Hg with a temperature 36 degrees F below standard? Wind: calm A. 178 MPH. A. 72.3 gallons. B. 181 MPH. B. 41.5 gallons. C. 183 MPH. C. 56.0 gallons.

44454555.. [14[14[14-[14 ---18/1/1/Entire18/1/1/Entire section] 44484888.. [. [14[ 141414----18/1/1/Entire18/1/1/Entire section] Referring to the performance chart above, what is the Referring to the performance chart above, what is the expected fuel consumption for a 500 nautical mile expected fuel consumption for an 850 nautical mile flight under the following conditions? flight under the following conditions?

Pressure altitude: 4,000 ft Pressure altitude: 9,500 ft Temperature: +29 degrees C Temperature: standard conditions Manifold pressure: 21.3" Hg Manifold pressure: 20.0" Hg Wind: calm Wind: calm A. 31.4 gallons. A. 60.3 gallons. B. 36.1 gallons. B. 31.4 gallons. C. 40.1 gallons. C. 11.5 gallons.

14-9 Chapter 14 – Airplane Performance: Know Before You Go

44494999.. [. [14[ 141414----19/1/4]19/1/4] Endurance and Range Profile Charts Referring to the performance chart above, determine the expected fuel consumption and true airspeed for 55525222.. [14[14[14-[14 ---20/Figure20/Figure 27] a flight at a pressure altitude of 8,000 feet at 2,300 Referring to the performance chart above, determine RPM at 20 degrees Celsius below standard condi- the airplane’s endurance at 6,000 feet at 65% power tions. with 24.5 gallons of useable fuel and a 45 minute A. 4.5 GPH, 93 knots. reserve. B. 5.5 GPH, 90 knots. A. 3:38 C. 5.0 GPH, 95 knots. B. 3:58 C. 3:00 505050.50 . [. [14[ 141414----19/1/4]19/1/4] Referring to the performance chart above, determine 55535333.. [. [14[ 141414----20/Figure20/Figure 27] the expected fuel consumption and true airspeed for Referring to the performance chart above, determine a flight at a pressure altitude of 5,000 feet at 2,400 the airplane’s endurance at 4,000 feet at 75% power RPM under standard conditions. with 24.5 gallons of useable fuel and a 45 minute A. 5.4 GPH, 101 knots. reserve. B. 5.5 GPH, 100 knots. A. 3:10 C. 4.7 GPH, 105 knots. B. 3:14 C. 3:25 55515111.. [14[14[14-[14 ---19/1/4]19/1/4] Referring to the performance chart above, determine 55545444.. [14[14[14-[14 ---20/Figure20/Figure 27] the expected fuel consumption and true airspeed for Referring to the performance chart above, determine a flight at a pressure altitude of 3,000 feet at 2,200 the airplane’s endurance at 10,000 feet at 65% power RPM at 20 degrees Celsius above standard condi- with 24.5 gallons of useable fuel and a 45 minute re- tions. serve. A. 4.5 GPH, 90 knots. A. 3:36 B. 4.6 GPH, 83 knots. B. 3:20 C. 4.5 GPH, 95 knots. C. 3:50

14-10 Rod Machado’s Sport Pilot Workbook

55585888.. [. [14[ 141414----21/21/21/EntireEntire section] Referring to the crosswind component chart above, what is the crosswind component for a landing on Runway 18 if the tower reports the wind as 220 degrees at 30 knots? A. 19 knots. B. 23 knots. C. 30 knots.

55595999.. [. [14[ 141414----21/Entire21/Entire section] Referring to the crosswind component chart above, 555555.. [14[14[14-[14 ---20/20/20/FigureFigure 28] determine the maximum wind velocity for a 45 degree Referring to the performance chart above, determine crosswind if the maximum crosswind component for the airplane’s range at 8,000 feet at 65% power with the airplane is 25 knots. 24.5 gallons of useable fuel and a 45 minute reserve. A. 25 knots. A. 350 nm. B. 29 knots. B. 353 nm. C. 35 knots. C. 390 nm. 606060.60 . [14[14[14-[14 ---21/Entire21/Entire section] 55565666.. [. [14[ 141414----20/Figure20/Figure 28] Referring to the crosswind component chart above, Referring to the performance chart above, determine with a reported wind of north at 20 knots, which run- the airplane’s range at 8,000 feet at 75% power with way (6, 29, or 32) is acceptable for use for an air- 24.5 gallons of useable fuel and a 45 minute reserve. plane with a 13 knot maximum crosswind compo- A. 319 nm. nent? B. 340 nm. A. Runway 6. C. 300 nm. B. Runway 29. C. Runway 32. 55575777.. [14[14[14-[14 ---20/Figure20/Figure 28] Referring to the performance chart above, determine 66616 111. . [14[14[14-[14 ---21/Entire21/Entire section] the airplane’s range at 10,000 feet at 45% power with Referring to the crosswind component chart above, 24.5 gallons of useable fuel and a 45 minute reserve. what is the maximum wind velocity for a 40 degree A. 415 nm. crosswind if the maximum crosswind component for B. 400 nm. the airplane is 12 knots? C. 450 nm. A. 18 knots. B. 22 knots. C. 12 knots.

14-11 Chapter 14 – Airplane Performance: Know Before You Go

66626222.. [14[14[14-[14 ---24/24/24/PostflightPostflight Briefing #1#144445555----1]1]1]1] 66636333.. [14[14[14-[14 ---24/Postflight24/Postflight Briefing #15#154444----1]1]1]1] Referring to the density altitude chart above, deter- Referring to the density altitude chart above, what is mine the density altitude for these conditions: the effect of a temperature decrease and a pressure altitude increase on the density altitude from 90 de- Altimeter setting 30.35 grees F and 1,250 feet pressure altitude to 60 de- Runway temperature +25 degrees F grees F and 1,750 feet pressure altitude? Airport elevation 3,894 ft MSL A. 500 foot increase. A. 2,000 feet MSL. B. 1,300 foot decrease. B. 2,900 feet MSL. C. 1,300 foot increase. C. 3,500 feet MSL.

14-12 Rod Machado’s Sport Pilot Workbook

66646444.. [. [14[ 141414----24/24/24/PostflightPostflight Briefing #1#144445555----1]1]1]1] 66676777.. [14[14[14-[14 ---24/Postflight24/Postflight Briefing #1#144445555----1]1]1]1] Referring to the density altitude chart above, Referring to the density altitude chart above, what is determine the pressure altitude at an airport the effect of a temperature increase from 25 to 50 de- that is at 3,563 feet MSL with an altimeter grees F on the density altitude if the pressure altitude setting of 29.96. remains at 5,000 feet? A. 3,527 feet MSL. A. 1,200 foot increase. B. 3,556 feet MSL. B. 1,400 foot increase. C. 3,639 feet MSL. C. 1,650 foot increase.

66656555.. [. [14[ 141414----24/Postflight24/Postflight Briefing #1#144445555----1]1]1]1] 66686888.. [14[14[14-[14 ---24/Postflight24/Postflight Briefing #1#144445555----1]1]1]1] Under what condition are pressure altitude Referring to the density altitude chart above, deter- and density altitude the same value? mine the pressure altitude with an indicated altitude A. At sea level, when the temperature is 0 degrees F. of 1,380 feet MSL and an altimeter setting of 28.22 at B. When the altimeter has no installation error. standard temperature. C. At standard temperature. A. 1,250 feet MSL. B. 3,010 feet MSL. 666666.. [14[14[14-[14 ---24/Postflight24/Postflight Briefing #1#144445555----1]1]1]1] C. 1,373 feet MSL. Referring to the density altitude chart above, determine the pressure altitude at an airport 66696999.. [. [14[ 141414----24/Postflight24/Postflight Briefing #1#144445555----1]1]1]1] that is 1,386 feet MSL with an altimeter Referring to the density altitude chart above, what is setting of 29.97. the effect of a temperature increase from 30 to 50 de- A. 1,341 feet MSL. grees F on the density altitude if the pressure altitude B. 1,451 feet MSL. remains at 3,000 feet MSL? C. 1,562 feet MSL. A. 900 foot increase. B. 1,100 foot decrease. C. 1,300 foot increase.

14-13 Chapter 14 – Airplane Performance: Know Before You Go 1. C 54. A 2. A 21. C 55. B 3. C 56. A 4. B 57. A 5. C 58. A 6. B 59. C 7. A 60. C 8. B 61. A 9. A 62. A 10. A 63. B 11. B 64. A 12. B 65. C 13. C 66. A 14. C 67. C 15. B 22. A 68. B 16. A 69. C 17. C 18. A 19. B 20. Vx is 71 knots Vy is 81 knots 21. See solution to right 22. See solution to right 23. See solution to right 24. See solution to right 25. C 26. C 23. B 27. B

28. C 29. See solution next page 30. See solution next page 31. See solution next page 32. See solution next page 33. B 34. A 35. B 36. B 37. A 38. B 39. B 24. B 40. A 41. C 42. C 43. B 44. A 45. B 46. C 47. C 48. A 49. C 50. B 51. A 52. A 53. A

14-14 Rod Machado’s Sport Pilot Workbook 29. B

30. A

31. B

32. C