Commercial – Chapter 5 – Airplane Performance and Weight and Balance

Question 1 of 65

1. Question

The performance tables of an aircraft for takeoff and climb are based on

pressure/density altitude.
cabin altitude.
true altitude.

Question 2 of 65

2. Question

Density altitude is the vertical distance above mean sea level in the standard atmosphere at which

pressure altitude is corrected for standard temperature.
a given atmospheric density is to be found.
temperature, pressure, altitude, and humidity are considered.

Question 3 of 65

3. Question

To determine pressure altitude prior to takeoff, the altimeter should be set to

the current altimeter setting.
29.92" Hg and the altimeter indication noted.
the field elevation and the pressure reading in the altimeter setting window noted.

Question 4 of 65

4. Question

At higher elevation airports the pilot should know that indicated airspeed

will be unchanged, but groundspeed will be faster.
will be higher, but groundspeed will be unchanged.
should be increased to compensate for the thinner air.

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:

11,900 feet.
14,130 feet.
18,150 feet.

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

7,800 feet.
7,200 feet.
9,000 feet.

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:

9,000 feet.
5,500 feet.
5,000 feet.

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

11,900 feet.
14,130 feet.
18,150 feet.

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:

5,000 feet.
8,500 feet.
9,500 feet.

Question 10 of 65

10. Question

What effect does an uphill runway slope have on takeoff performance?

increases takeoff speed.
increases takeoff distance.
decreases takeoff distance.

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 50-foot obstacle?

1,100 feet.
1,300 feet.
1,500 feet.

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 50-foot obstacle?

1,180 feet.
1,350 feet.
1,850 feet.

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 50-foot obstacle?

800 feet.
650 feet.
1,050 feet.

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 50-foot obstacle in 1,000 feet, what weight reduction is necessary?

50 pounds.
100 pounds
300 pounds.

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?

7 minutes.
8.4 minutes.
11.2 minutes.

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?

43 pounds.
45 pounds.
49 pounds.

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?

30 pounds.
37 pounds.
46 pounds.

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?

4 to 8 minutes.
5 minutes.
5.5 minutes.

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?

6 miles.
8.5 miles.
11 miles.

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?

5 gallons, 9 minutes, 13 NM.
6 gallons, 11 minutes, 16 NM.
7 gallons, 12 minutes, 18 NM.

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.

46 pounds.
51 pounds.
58 pounds.

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.

23 pounds.
31 pounds.
35 pounds.

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.

10 pounds.
14 pounds.
24 pounds.

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.

26 pounds.
35 pounds.
40 pounds.

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?

305 ft./min.
320 ft./min.
384 ft./min.

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?

655 ft./min.
702 ft./min.
774 ft./min.

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?

635 miles.
645 miles.
810 miles.

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.

6.1 hours.
7.7 hours.
8.0 hours.

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?

103 MPH TAS, 6.3 GPH.
105 MPH TAS, 6.6 GPH.
105 MPH TAS, 6.2 GPH.

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.)

3 hours 46 minutes.
4 hours 1 minute.
4 hours 31 minutes.

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.)

2 hours 27 minutes.
3 hours 12 minutes.
3 hours 42 minutes.

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.)

4 hours 50 minutes.
5 hours 20 minutes.
5 hours 59 minutes.

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?

6 hours 27 minutes.
6 hours 39 minutes.
6 hours 56 minutes.

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?

4 hours 20 minutes.
4 hours 30 minutes.
4 hours 50 minutes.

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?

4 hours 58 minutes.
5 hours 7 minutes
5 hours 12 minutes.

Question 36 of 65

36. Question

Which maximum range factor decreases as weight decreases?

Altitude.
Airspeed.
Angle of attack.

Question 37 of 65

37. Question

Refer to figure 8 below. GIVEN: Fuel quantity is 47 gallons, Power-cruise (lean) is 55%. Approximately how much flight time would be available with a night VFR fuel reserve remaining?

3 hours 8 minutes.
3 hours 22 minutes.
3 hours 43 minutes.

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?

4 hours 17 minutes.
4 hours 30 minutes.
5 hours 4 minutes.

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.

1.82 gallons.
1.97 gallons.
2.12 gallons.

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.

2.66 gallons.
2.88 gallons.
3.2 gallons.

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?

2 hours 34 minutes.
2 hours 49 minutes.
3 hours 18 minutes.

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?

260 degrees at 20 knots.
275 degrees at 25 knots.
315 degrees at 35 knots.

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?

19 knots.
21 knots.
23 knots.

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?

7 knots.
13 knots.
15 knots.

Question 45 of 65

45. Question

Refer to figure 31 below. If the tower-reported surface wind is 010 degrees at 18 knots, what is the crosswind component for a Rwy 08 landing?

7 knots.
15 knots.
17 knots.

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.

425 feet.
636 feet.
836 feet.

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.

1,125 feet.
1,250 feet.
1,325 feet.

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.

689 feet.
716 feet.
1,275 feet.

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.

742 feet.
1,200 feet.
1,400 feet.

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

Dividing total arms by total moments.
Multiplying total arms by total weight.
all usable fuel and oil, but does not include any radio equipment or instruments that were installed by someone other than the manufacturer.

Question 51 of 65

51. Question

The CG of an aircraft may be determined by which of the following methods?

dividing total arms by total moments.
multiplying total arms by total weight.
dividing total moments by total weight.

Question 52 of 65

52. Question

The CG of an aircraft may be determined by

dividing total arms by total moments.
dividing total moments by total weight.
multiplying total weight by total moments.

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

centerline of the main wheels.
nose, or out in front of the airplane.
centerline of the nose or tailwheel, depending on the type of airplane.

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 datum

Based on the above information, the CG would be located how far aft of datum?

86.0 inches.
116.8 inches.
125.0 inches.

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?

89.11 inches.
96.89 inches.
106.92 inches.

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 unknown

The CG is located at station

-6.43
16.43
27.38

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?

52.14 pounds.
62.24 pounds.
78.14 pounds.

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?

96.13 inches aft of datum.
95.50 inches aft of datum.
99.87 inches aft of datum.

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?

100.2 inches.
109.0 inches.
121.7 inches.

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?

91.76 inches.
111.67 inches.
118.24 inches.

Question 61 of 65

61. Question

Refer to figure 38 below.
GIVEN:
Empty weight (oil is included) – 1,271 lb.
Empty weight moment (in-lb./1,000) – 102.04
Pilot and copilot – 400 lb.
Rear seat passenger – 140 lb.
Cargo – 100 lb.
Fuel – 37 gallons

Is the airplane loaded within limits?

Yes, the weight and CG is within limits.
No, the weight exceeds the maximum allowable.
No, the weight is acceptable, but the CG is aft of the aft limit.

Question 62 of 65

62. Question

Refer to figure 38 below.
GIVEN:
Empty weight (oil is included) – 1,271 lb.
Empty weight moment (in-lb./1,000) – 102.04
Pilot and copilot – 260 lb.
Rear seat passenger – 120 lb.
Cargo – 60 lb.
Fuel – 37 gallons

Under these conditions, the CG is determined to be located

within the CG envelope.
on the forward limit of the CG envelope.
within the shaded area of the CG envelope.

Question 63 of 65

63. Question

Refer to figure 38 below.
GIVEN:
Empty weight (oil is included) – 1,271 lb.
Empty weight moment (in-lb./1,000) – 102.04
Pilot and copilot – 360 lb.
Cargo – 340 lb.
Fuel – 37 gallons

Will the CG remain within limits after 30 gallons of fuel has been used in flight?

Yes, the CG will remain within limits.
No, the CG will be located aft of the aft CG limit.
Yes, but the CG will be located in the shaded area of the CG envelope.

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 68.0

After 1 hour 30 minutes of flight time, the CG would be located at station

67.79
68.79
70.78

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 68.0

After 1 hour 45 minutes of flight time, the CG would be located at station:

68.77
68.83
69.77