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Private Pilot, Aircraft Performance, Chapter 8
Aircraft Performance - Weight and Balance,
chapter 8 aircraft performance, ASA Test Prep
2025 Private Pilot Chapter 9: "Enroute Flight",
Private Pilot - Aircraft Performance/Aircraft
Performance, Enroute flight, FAA, ASA Private
Pilot ch. 4, 6, 7, 11, airspace (Enroute Flight)
Exam All Versions
Private Pilot, Aircraft Performance Answered
Chapter 8 Aircraft Performance - Weight and Balance Answered
Chapter 8 aircraft performance Answered
ASA Test Prep 2025 Private Pilot Chapter 9: "Enroute Flight" Answered
Private Pilot - Aircraft Performance/Aircraft Performance Answered
Enroute flight Answered
FAA, ASA Private Pilot ch. 4, 6, 7, 11, airspace (Enroute Flight) Answered
pg. 1
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(Refer to Figure 36.) With a reported wind of south at 20 knots, which
runway (10, 14, or 24) is appropriate for an airplane with a 13-knot
maximum crosswind component?
A) Runway 10.
B) Runway 14.
C) Runway 24.
B) Runway 14.
(Refer to Figure 35.) What is the expected fuel consumption for a 1,000-
nautical mile flight under the following conditions?
Pressure altitude 8,000 ft
Temperature 22°C
Manifold pressure 20.8" HgWind Calm
A) 60.2 gallons.
B) 70.1 gallons.
C) 73.2 gallons.
B) 70.1 gallons.
pg. 2
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What effect does high density altitude have on aircraft performance?
A) It increases engine performance.
B) It reduces climb performance.
C) It increases takeoff performance.
B) It reduces climb performance.
(Refer to Figure 37.) Determine the total distance required to land.OAT
32°FPressure altitude 8,000 ftWeight 2,600 lbHeadwind component 20
ktsObstacle 50 ft
A) 850 feet.
B) 1,400 feet.
C) 1,750 feet.
B) 1,400 feet.
(Refer to Figures 32 and 33.) What effect does a 35-gallon fuel burn (main
tanks) have on the weight and balance if the airplane weighed 2,890
pounds and the MOM/100 was 2,452 at takeoff?
pg. 3
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A) Weight is reduced by 210 pounds and the CG is aft of limits.
B) Weight is reduced by 210 pounds and the CG is unaffected.
C) Weight is reduced to 2,680 pounds and the CG moves forward.
A) Weight is reduced by 210 pounds and the CG is aft of limits.
(Refer to Figure 37.) Determine the total distance required to land.OAT
StdPressure altitude 10,000 ftWeight 2,400 lbWind component
CalmObstacle 50 ft
A) 750 feet.
B) 1,925 feet.
C) 1,450 feet.
B) 1,925 feet.
(Refer to Figure 38.) Determine the approximate landing ground roll
distance.Pressure altitude 5,000 ftHeadwind CalmTemperature 101°F
A) 495 feet.
B) 545 feet.
C) 445 feet.
B) 545 feet.
(Refer to Figure 8.) What is the effect of a temperature decrease and a
pressure altitude increase on the density altitude from 90°F and 1,250
pg. 4
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Private Pilot, Aircraft Performance, Chapter 8
Aircraft Performance - Weight and Balance,
chapter 8 aircraft performance, ASA Test Prep
2025 Private Pilot Chapter 9: "Enroute Flight",
Private Pilot - Aircraft Performance/Aircraft
Performance, Enroute flight, FAA, ASA Private
Pilot ch. 4, 6, 7, 11, airspace (Enroute Flight)
Exam All Versions
Private Pilot, Aircraft Performance Answered
Chapter 8 Aircraft Performance - Weight and Balance Answered
Chapter 8 aircraft performance Answered
ASA Test Prep 2025 Private Pilot Chapter 9: "Enroute Flight" Answered
Private Pilot - Aircraft Performance/Aircraft Performance Answered
Enroute flight Answered
FAA, ASA Private Pilot ch. 4, 6, 7, 11, airspace (Enroute Flight) Answered
pg. 1
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(Refer to Figure 36.) With a reported wind of south at 20 knots, which
runway (10, 14, or 24) is appropriate for an airplane with a 13-knot
maximum crosswind component?
A) Runway 10.
B) Runway 14.
C) Runway 24.
B) Runway 14.
(Refer to Figure 35.) What is the expected fuel consumption for a 1,000-
nautical mile flight under the following conditions?
Pressure altitude 8,000 ft
Temperature 22°C
Manifold pressure 20.8" HgWind Calm
A) 60.2 gallons.
B) 70.1 gallons.
C) 73.2 gallons.
B) 70.1 gallons.
pg. 2
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What effect does high density altitude have on aircraft performance?
A) It increases engine performance.
B) It reduces climb performance.
C) It increases takeoff performance.
B) It reduces climb performance.
(Refer to Figure 37.) Determine the total distance required to land.OAT
32°FPressure altitude 8,000 ftWeight 2,600 lbHeadwind component 20
ktsObstacle 50 ft
A) 850 feet.
B) 1,400 feet.
C) 1,750 feet.
B) 1,400 feet.
(Refer to Figures 32 and 33.) What effect does a 35-gallon fuel burn (main
tanks) have on the weight and balance if the airplane weighed 2,890
pounds and the MOM/100 was 2,452 at takeoff?
pg. 3
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A) Weight is reduced by 210 pounds and the CG is aft of limits.
B) Weight is reduced by 210 pounds and the CG is unaffected.
C) Weight is reduced to 2,680 pounds and the CG moves forward.
A) Weight is reduced by 210 pounds and the CG is aft of limits.
(Refer to Figure 37.) Determine the total distance required to land.OAT
StdPressure altitude 10,000 ftWeight 2,400 lbWind component
CalmObstacle 50 ft
A) 750 feet.
B) 1,925 feet.
C) 1,450 feet.
B) 1,925 feet.
(Refer to Figure 38.) Determine the approximate landing ground roll
distance.Pressure altitude 5,000 ftHeadwind CalmTemperature 101°F
A) 495 feet.
B) 545 feet.
C) 445 feet.
B) 545 feet.
(Refer to Figure 8.) What is the effect of a temperature decrease and a
pressure altitude increase on the density altitude from 90°F and 1,250
pg. 4
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