Commercial – Chapter 5 – Airplane Performance and Weight and Balance
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Question 1 of 65
1. Question
The performance tables of an aircraft for takeoff and climb are based on
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Question 2 of 65
2. Question
Density altitude is the vertical distance above mean sea level in the standard atmosphere at which
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Question 3 of 65
3. Question
To determine pressure altitude prior to takeoff, the altimeter should be set to
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Question 4 of 65
4. Question
At higher elevation airports the pilot should know that indicated airspeed
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Question 5 of 65
5. Question
GIVEN: Pressure altitude is 12,000 ft., True air temperature is 50 degrees F. From the conditions given, the approximate density altitude is:
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Question 6 of 65
6. Question
GIVEN: Pressure altitude is 5,000 feet and true air temperature is 30 degrees C. From the conditions given, the approximate density altitude is
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Question 7 of 65
7. Question
GIVEN: Pressure altitude is 6,000 feet and true air temperature is 30 degrees F. From the conditions given, the approximate density altitude is:
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Question 8 of 65
8. Question
GIVEN: Pressure altitude is 12,000 feet and true air temperature is 15 degrees F. From the conditions given, the approximate density altitude is
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Question 9 of 65
9. Question
GIVEN: Pressure altitude is 7,000 feet and true air temperature is 15 degrees C. From the conditions given, the approximate density altitude is:
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Question 10 of 65
10. Question
What effect does an uphill runway slope have on takeoff performance?
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Question 11 of 65
11. Question
Refer to figure 32 below. GIVEN: Temperature is 30 degrees F, pressure altitude is 6,000 feet, weight is 3,300 lbs., headwind is 20 kts. What is the total takeoff distance over a 50foot obstacle?
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Question 12 of 65
12. Question
Refer to figure 32 below. GIVEN: Temperature is 100 degrees F, pressure altitude is 4,000 feet, weight is 3,200 lbs., wind is calm. What is the ground roll required for takeoff over a 50foot obstacle?
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Question 13 of 65
13. Question
Refer to figure 32 below. GIVEN: Temperature is 50 degrees F, pressure altitude is 2,000 feet, weight is 2,700 lbs., wind is calm. What is the total takeoff distance over a 50foot obstacle?
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Question 14 of 65
14. Question
Refer to figure 32 below. GIVEN: Temperature is 75 degrees F, pressure altitude is 6,000 feet, weight is 2,900 lbs., wind is 20 kts. To safely take off over a 50foot obstacle in 1,000 feet, what weight reduction is necessary?
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Question 15 of 65
15. Question
Refer to figure 13 below. GIVEN: Aircraft weight is 4,000 lb., airport pressure altitude is 2,000 feet, temperature at 2,000 feet is 32 degrees C. Using a maximum rate of climb under the given conditions, how much time would be required to climb to a pressure altitude of 8,000 feet?
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Question 16 of 65
16. Question
Refer to figure 13 below. GIVEN: Aircraft weight is 3,400 lb., airport pressure altitude is 6,000 feet, temperature at 6,000 feet is 10 degrees C. Using a maximum rate of climb under the given conditions, how much fuel would be used from engine start to a pressure altitude of 16,000 feet?
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Question 17 of 65
17. Question
Refer to figure 14 below. GIVEN: Aircraft weight is 3,700 lb., airport pressure altitude is 4,000 feet, temperature at 4,000 feet is 21 degrees C. Using a normal climb under the given conditions, how much fuel would be used from engine start to a pressure altitude of 12,000 feet?
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Question 18 of 65
18. Question
Refer to figure 14 below. GIVEN: Aircraft weight is 3,400 lb., airport pressure altitude is 4,000 feet, temperature at 4,000 feet is 14 degrees C. Using a normal climb under the given conditions, how much time would be required to climb to a pressure altitude of 8,000 feet?
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Question 19 of 65
19. Question
Refer to figure 15 below. GIVEN: Airport pressure altitude is 4,000 ft., airport temperature is 12 degrees C, cruise pressure altitude is 9,000 ft., cruise temperature is 4 degrees C. What will be the distance required to climb to cruise altitude under the given conditions?
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Question 20 of 65
20. Question
Refer to figure 15 below. GIVEN: Airport pressure altitude is 2,000 ft., airport temperature is 20 degrees C, cruise pressure altitude is 10,000 ft., cruise temperature is 0 degrees C. What will be the fuel, time, and distance required to climb to cruise altitude under the given conditions?
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Question 21 of 65
21. Question
Refer to figure 9 below. Using a normal climb (100 KIAS), how much fuel would be used from engine start to 12,000 feet pressure altitude? Aircraft weight is 3,800 lb., airport pressure altitude is 4,000 ft., and temperature is 26 degrees C.
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Question 22 of 65
22. Question
Refer to figure 9 below. Using a normal climb (100 KIAS), how much fuel would be used from engine start to 10,000 feet pressure altitude? Aircraft weight is 3,500 lb., airport pressure altitude is 4,000 feet and temperature is 21 degrees C.
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Question 23 of 65
23. Question
Refer to figure 10 below. Using a maximum rate of climb, how much fuel would be used from engine start to 6,000 feet pressure altitude? Aircraft weight is 3,200 lb., airport pressure altitude is 2,000 feet and temperature is 27 degrees C.
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Question 24 of 65
24. Question
Refer to figure 10 below. Using a maximum rate of climb, how much fuel would be used from engine start to 10,000 feet pressure altitude? Aircraft weight is 3,800 lb., airport pressure altitude is 4,000 feet and temperature is 30 degrees C.
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Question 25 of 65
25. Question
Refer to figure 33 below. GIVEN: Weight is 3,700 lb., pressure altitude is 22,000 feet, temperature is 10 degrees C. What is the maximum rate of climb under the given conditions?
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Question 26 of 65
26. Question
Refer to figure 33 below. GIVEN: Weight is 4,000 lb., pressure altitude is 5,000 feet, temperature is 30 degrees C. What is the maximum rate of climb under the given conditions?
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Question 27 of 65
27. Question
Refer to figure 11 below. If the cruise altitude is 7,500 feet, using 64 percent power at 2,500 RPM, what would be the range with 48 gallons of usable fuel?
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Question 28 of 65
28. Question
Refer to figure 11 below. What would be the endurance at an altitude of 7,500 feet, using 52 percent power? NOTE: With 48 gallons of fuel and no reserve.
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Question 29 of 65
29. Question
Refer to figure 11 below. What would be the approximate true airspeed and fuel consumption per hour at an altitude of 7,500 feet, using 52 percent power?
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Question 30 of 65
30. Question
Refer to figure 12 below. GIVEN: Pressure altitude is 18,000 feet, temperature is 21 degrees C, Power is 2,400 RPM – 28″ MP, Recommended lean mixture usable fuel is 425 lb. What is the approximate flight time available under the given conditions? (Allow for VFR day fuel reserve.)
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Question 31 of 65
31. Question
Refer to figure 12 below. GIVEN: Pressure altitude is 18,000 feet, temperature is 41 degrees C, Power is 2,500 RPM – 26″ MP, Recommended lean mixture usable fuel is 318 lb. What is the approximate flight time available under the given conditions? (Allow for VFR night fuel reserve.)
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Question 32 of 65
32. Question
Refer to figure 12 below. GIVEN: Pressure altitude is 18,000 feet, temperature is 1 degrees C, Power is 2,200 RPM – 20″ MP, Best fuel economy usable fuel is 344 lb. What is the approximate flight time available under the given conditions? (Allow for VFR day fuel reserve.)
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Question 33 of 65
33. Question
Refer to figure 34 below. GIVEN: Pressure altitude is 6,000 feet, temperature is 3 degrees C, Power is 2,200 RPM – 22″ MP, Usable fuel available is 465 lb. What is the maximum available flight time under the given conditions stated?
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Question 34 of 65
34. Question
Refer to figure 34 below. GIVEN: Pressure altitude is 6,000 feet, temperature is 17 degrees C, Power is 2,300 RPM – 23″ MP, Usable fuel available is 370 lb. What is the maximum available flight time under the given conditions stated?
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Question 35 of 65
35. Question
Refer to figure 34 below. GIVEN: Pressure altitude is 6,000 feet, temperature is 13 degrees C, Power is 2,500 RPM – 23″ MP, Usable fuel available is 460 lb. What is the maximum available flight time under the given conditions stated?
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Question 36 of 65
36. Question
Which maximum range factor decreases as weight decreases?
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Question 37 of 65
37. Question
Refer to figure 8 below. GIVEN: Fuel quantity is 47 gallons, Powercruise (lean) is 55%. Approximately how much flight time would be available with a night VFR fuel reserve remaining?
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Question 38 of 65
38. Question
Refer to figure 8 below. GIVEN: Fuel quantity is 65 gallons, best power (level flight) is 55%. Approximately how much flight time would be available with a day VFR fuel reserve remaining?
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Question 39 of 65
39. Question
Refer to figure 8 below. Determine the amount of fuel consumer during takeoff and climb at 75 percent power for 7 minutes.
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Question 40 of 65
40. Question
Refer to figure 8 below. Determine the amount of fuel consumed during takeoff and climb at 70% power for 10 minutes.
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Question 41 of 65
41. Question
Refer to figure 8 below. With 38 gallons of fuel aboard at cruise power (55 percent), how much flight time is available with night .VFR fuel reserve still remaining?
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Question 42 of 65
42. Question
Refer to figure 31 below. Rwy 30 is being used for landing. Which surface wind would exceed the airplane’s crosswind capability of 0.2 Vso, if Vso is 60 knots?
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Question 43 of 65
43. Question
Refer to figure 31 below. The surface wind is 180 degrees at 25 knots. What is the crosswind component for a Rwy 13 landing?
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Question 44 of 65
44. Question
Refer to figure 31 below. What is the headwind component for a Rwy 13 takeoff if the surface winds is 190 degrees at 15 knots?
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Question 45 of 65
45. Question
Refer to figure 31 below. If the towerreported surface wind is 010 degrees at 18 knots, what is the crosswind component for a Rwy 08 landing?
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Question 46 of 65
46. Question
Refer to figure 35 below. GIVEN: Temperature is 50 degrees F, Pressure altitude is sea level, Weight is 3,000 lb., headwind is 10 kts. Determine the approximate ground roll.
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Question 47 of 65
47. Question
Refer to figure 35 below. GIVEN: Temperature is 80 degrees F, Pressure altitude is 4,000 feet, Weight is 2,800 lb., headwind is 24 kts. Determine the approximate ground roll.
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Question 48 of 65
48. Question
Refer to figure 35 below. GIVEN: Temperature is 70 degrees F, Pressure altitude is sea level, Weight is 3,400 lb., headwind is 16 kts. Determine the approximate ground roll.
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Question 49 of 65
49. Question
Refer to figure 35 below. GIVEN: Temperature is 85 degrees F, Pressure altitude is 6,000 feet, Weight is 2,800 lb., headwind is 14 kts. Determine the approximate ground roll.
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Question 50 of 65
50. Question
When computing weight and balance, the basic empty weight includes the weight of the airframe, engine(s), and all installed optional equipment. Basic empty weight also includes
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Question 51 of 65
51. Question
The CG of an aircraft may be determined by which of the following methods?
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Question 52 of 65
52. Question
The CG of an aircraft may be determined by
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Question 53 of 65
53. Question
If all index units are positive when computing weight and balance, the location of the datum would be at the
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Question 54 of 65
54. Question
GIVEN:
Weight A – 155 pounds at 45 inches, aft of datum
Weight B – 165 pounds at 145 inches aft of datum
Weight C – 95 pounds at 185 inches aft of datumBased on the above information, the CG would be located how far aft of datum?
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Question 55 of 65
55. Question
GIVEN:
Weight A – 140 pounds at 17 inches after of datum.
Weight B – 120 pounds at 110 inches aft of datum.
Weight C – 85 pounds at 210 inches aft of datum.Based on the above information, the CG would be located how far aft of datum?
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Question 56 of 65
56. Question
GIVEN:
Empty weight is 957, ARM is 29.07
Pilot (Fwd. seat) is 140, ARM is 45.30
Passenger (aft seat) is 170, ARM is 1.60
Ballast is 15, ARM is 45.30
The moment is unknownThe CG is located at station
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Question 57 of 65
57. Question
An aircraft is loaded with a ramp weight of 3,650 pounds and having a CG of 94.0, approximately how much baggage would have to be moved from the rear baggage area at station 180 to the forward baggage area at station 40 in order to move the CG to 92.0?
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Question 58 of 65
58. Question
An airplane is loaded to a gross weight of 4,800 pounds, with three pieces of luggage in the rear baggage compartment. The CG is located 98 inches aft of datum, which is 1 inch aft of limits. If luggage which weighs 90 pounds is moved from the rear baggage compartment (145 inches aft of datum) to the front compartment (45 inches aft of datum), what is the new CG?
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Question 59 of 65
59. Question
GIVEN:
Weight A – 135 pounds at 15 inches aft of datum.
Weight B – 205 pounds at 117 inches aft of datum.
Weight C – 85 pounds at 195 inches aft of datum.Based on the above information, the CG would be located how far aft of datum?
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Question 60 of 65
60. Question
GIVEN:
Weight A – 175 pounds at 135 inches aft of datum.
Weight B – 135 pounds at 115 inches aft of datum.
Weight C – 75 pounds at 85 inches aft at datum
The CG for the combined weights would be located how far aft of datum?CorrectIncorrect 
Question 61 of 65
61. Question
Refer to figure 38 below.
GIVEN:
Empty weight (oil is included) – 1,271 lb.
Empty weight moment (inlb./1,000) – 102.04
Pilot and copilot – 400 lb.
Rear seat passenger – 140 lb.
Cargo – 100 lb.
Fuel – 37 gallonsIs the airplane loaded within limits?
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Question 62 of 65
62. Question
Refer to figure 38 below.
GIVEN:
Empty weight (oil is included) – 1,271 lb.
Empty weight moment (inlb./1,000) – 102.04
Pilot and copilot – 260 lb.
Rear seat passenger – 120 lb.
Cargo – 60 lb.
Fuel – 37 gallonsUnder these conditions, the CG is determined to be located
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Question 63 of 65
63. Question
Refer to figure 38 below.
GIVEN:
Empty weight (oil is included) – 1,271 lb.
Empty weight moment (inlb./1,000) – 102.04
Pilot and copilot – 360 lb.
Cargo – 340 lb.
Fuel – 37 gallonsWill the CG remain within limits after 30 gallons of fuel has been used in flight?
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Question 64 of 65
64. Question
GIVEN:
Total weight – 4,137 lb.
CG location – Station 6.78
Fuel consumption – 13.7 GPH
Fuel CG – Station 68.0After 1 hour 30 minutes of flight time, the CG would be located at station
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Question 65 of 65
65. Question
GIVEN:
Total weight – 3,037 lb.
CG location – Station 68.8
Fuel consumption – 127.7 GPH
Fuel CG – Station 68.0After 1 hour 45 minutes of flight time, the CG would be located at station:
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