Chapter 8- weight and balance

(Refer to Figure 60.) How should the 500-pound weight be shifted to balance the plank on the fulcrum?

1 inch to the left.

(Refer to Figure 8.) What is the effect of a temperature increase from 35 to 50°F on the density altitude if the pressure altitude remains at 3,000 feet MSL?

1,000-foot increase.

(Refer to Figure 38.) Determine the total distance required to land over a 50-foot obstacle. Pressure altitude 7,500 ft Headwind 8 kts Temperature 32°FRunway Hard surface

1,004 feet.

(Refer to Figure 40.) Determine the approximate ground roll distance required for takeoff. OAT 100°FPressure altitude 2,000 ft Takeoff weight 2,750 lb Headwind component Calm

1,150 feet.

(Refer to Figure 8.) Determine the pressure altitude at an airport that is 1,386 feet MSL with an altimeter setting of 29.97.

1,341 feet MSL

(Refer to Figure 37.) Determine the total distance required to land. OAT 32°FPressure altitude 8,000 ft Weight 2,600 lb Headwind component 20 kts Obstacle 50 ft

1,400 feet.

(Refer to Figure 40.) Determine the total distance required for takeoff to clear a 50-foot obstacle. OAT Std Pressure altitude Sea level Takeoff weight 2,700 lb Headwind component Calm

1,400 feet.

(Refer to Figure 8.) What is the effect of a temperature increase from 25 to 50°F on the density altitude if the pressure altitude remains at 5,000 feet?

1,650-foot increase

(Refer to Figure 8.) What is the effect of a temperature increase from 25 to 50°F on the density altitude if the pressure altitude remains at 5,000 feet?

1,650-foot increase.

(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 feet pressure altitude to 55°F and 1,750 feet pressure altitude?

1,700-foot decrease.

(Refer to Figure 37.) Determine the total distance required to land .OAT 90°FPressure altitude 3,000 ft Weight 2,900 lb Headwind component 10 kts Obstacle 50 ft

1,725 feet.

(Refer to Figure 40.) Determine the total distance required for takeoff to clear a 50-foot obstacle. OAT Std Pressure altitude 4,000 ft Takeoff weight 2,800 lb Headwind component Calm View Figures

1,750 feet.

(Refer to Figure 37.) Determine the approximate total distance required to land over a 50-foot obstacle. OAT 90°FPressure altitude 4,000 ft Weight 2,800 lb Headwind component 10 kts

1,775 feet.

(Refer to Figure 37.) Determine the total distance required to land. OAT Std Pressure altitude 10,000 ft Weight 2,400 lb Wind component Calm Obstacle 50 ft

1,925 feet.

(Refer to Figure 34.) What is the maximum amount of baggage that may be loaded aboard the airplane for the CG to remain within the moment envelope? WEIGHT (LB) MOM/1000Empty weight 1,350 51.5Pilot and front passenger 250 --Rear passengers 400 --Baggage -- --Fuel, 30 gal -- --Oil, 8 qt -- -0.2 View Figures

105 pounds.

(Refer to Figure 35.) What fuel flow should a pilot expect at 11,000 feet on a standard day with 65 percent maximum continuous power?

11.2 gallons per hour.

(Refer to Figure 35.) Approximately what true airspeed should a pilot expect with full throttle at 10,500 feet with a temperature of 36 degrees F above standard?

165 knots.

(Refer to Figure 36.) What is the crosswind component for a landing on Runway 18 if the tower reports the wind as 220° at 30 knots?

19 knots.

(Refer to Figure 8.) Determine the density altitude for these conditions: Altimeter setting 30.35 Runway temperature +25°F Airport elevation 3,894 ft MSL

2,000 feet MSL.

(Refer to Figure 8.) Determine the pressure altitude with an indicated altitude of 1,380 feet MSL with an altimeter setting of 28.22 at standard temperature.

2,991 feet MSL.

(Refer to Figures 32 and 33.) Determine if the airplane weight and balance is within limits. Front seat occupants 340 lb Rear seat occupants 295 lb Fuel (main wing tanks) 44 gal Baggage 56 lb

20 pounds overweight, CG within limits.

(Refer to Figure 35.) Determine the approximate manifold pressure setting with 2,450 RPM to achieve 65 percent maximum continuous power at 6,500 feet with a temperature of 36°F higher than standard.

21.0" Hg.

(Refer to Figure 36.) What is the headwind component for a landing on Runway 18 if the tower reports the wind as 220° at 30 knots?

23 knots.

(Refer to Figure 36.) What is the maximum wind velocity for a 30° crosswind if the maximum crosswind component for the airplane is 12 knots?

24 knots.

(Refer to Figure 8.) Determine the pressure altitude at an airport that is 3,563 feet MSL with an altimeter setting of 29.96.

3,527 feet MSL

(Refer to figure 61.) If 50 pounds of weight is located at point X and 100 pounds at point Z, how much weight must be located at point Y to balance the plank?

300 pounds.

(Refer to Figure 36.) Determine the maximum wind velocity for a 45° crosswind if the maximum crosswind component for the airplane is 25 knots.

35 knots.

(Refer to Figure 35.) What is the expected fuel consumption for a 500-nautical mile flight under the following conditions?Pressure altitude 4,000 ftTemperature + 29°CManifold pressure 21.3" HgWind Calm

36.1 gallons.

(Refer to Figure 38.) Determine the approximate landing ground roll distance. Pressure altitude 1,250 ft Headwind 8 kts Temperature Std

366 feet.

(Refer to Figure 34.) What is the maximum amount of fuel that may be aboard the airplane on takeoff if loaded as follows? WEIGHT (LB) MOM/1000Empty weight 1,350 51.5Pilot and front passenger 340 --Rear passengers 310 --Baggage 45 --Oil, 8 qt -- --

40 gallons.

(Refer to Figure 38.) Determine the approximate landing ground roll distance.Pressure altitude Sea level Headwind 4 kts Temperature Std

401 feet.

(Refer to Figures 32 and 33.) What is the maximum amount of baggage that can be carried when the airplane is loaded as follows? Front seat occupants 387 lb Rear seat occupants 293 lb Fuel 35 gal

45 pounds

(Refer to Figure 38.) Determine the approximate landing ground roll distance. Pressure altitude 5,000 ft Headwind Calm Temperature 101°F

545 feet.

(Refer to Figure 40.) Determine the approximate ground roll distance required for takeoff. OAT 95°FPressure altitude 2,000 ft Takeoff weight 2,500 lb Headwind component 20 kts

650 feet.

(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 ftTemperature 22°CManifold pressure 20.8" HgWind Calm

70.1 gallons.

(Refer to Figure 34.) Determine the moment with the following data: WEIGHT (LB) MOM/1000Empty weight 1,350 51.5Pilot and front passenger 340 --Fuel (std tanks) Capacity --Oil, 8 qt -- --

74.9 pound-inches.

(Refer to Figure 34.) Determine the aircraft loaded moment and the aircraft category. WEIGHT (LB) MOM/1000Empty weight 1,350 51.5Pilot and front passenger 380 --Fuel, 48 gal 288 --Oil, 8 qt -- --

79.2, normal category.

(Refer to Figure 8.) Determine the density altitude for these conditions: Altimeter setting 29.25 Runway temperature + 81°F Airport elevation 5,250 ft MSL

8,500 feet MSL.

(Refer to Figure 34.) Calculate the moment of the airplane and determine which category is applicable. WEIGHT (LB) MOM/1000Empty weight 1,350 51.5Pilot and front passenger 310 --Rear passengers 96 --Fuel, 38 gal -- --Oil, 8 qt -- -0.2 View Figures

80.8, utility category.

(Refer to Figure 38.) Determine the total distance required to land over a 50-foot obstacle. Pressure altitude 3,750 ft Headwind 12 kts Temperature Std

816 feet.

(Refer to Figure 38.) Determine the total distance required to land over a 50-foot obstacle. Pressure altitude 5,000 ft Headwind 8 kts Temperature 41°FRunway Hard surface

956 feet.

(Refer to Figures 32 and 33.) With the airplane loaded as follows, what action can be taken to balance the airplane?Front seat occupants 411 lbRear seat occupants 100 lbMain wing tanks 44 gal

Add a 100-pound weight to the baggage compartment.

Which factor would tend to increase the density altitude at a given airport?

An increase in ambient temperature.

(Refer to Figures 32 and 33.) Calculate the weight and balance and determine if the CG and the weight of the airplane are within limits. Front seat occupants 350 lb Rear seat occupants 325 lb Baggage 27 lbFuel 35 gal

CG 83.4, within limits.

GIVEN:WEIGHT ARM MOMENT(LB) (IN) (LB-IN)Empty weight 1,495.0 101.4 151,593.0Pilot and passengers 380.0 64.0 --Fuel (30 gal usable-no reserve) -- 96.0 --The CG is located how far aft of datum?

CG 94.01.

(Refer to Figures 32 and 33.) Which action can adjust the airplane's weight to maximum gross weight and the CG within limits for takeoff? Front seat occupants 425 lb Rear seat occupants 300 lb Fuel, main tanks 44 gal

Drain 9 gallons of fuel.

What effect does high density altitude, as compared to low density altitude, have on propeller efficiency and why?

Efficiency is reduced because the propeller exerts less force at high density altitudes than at low density altitudes.

Which combination of atmospheric conditions will reduce aircraft takeoff and climb performance?

High temperature, high relative humidity, and high density altitude.

What effect, if any, does high humidity have on aircraft performance?

It decreases performance.

What effect does high density altitude have on aircraft performance?

It reduces climb performance.

(Refer to Figure 67.) What effect does a 30-gallon fuel burn have on the weight and balance if the airplane weighed 2,784 pounds and the MOM/100 was 2,222 at takeoff?

Moment will decrease to 2,087 lbs-in.

(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?

Runway 14.

(Refer to Figure 36.) With a reported wind of north at 20 knots, which runway (6, 29, or 32) is acceptable for use for an airplane with a 13-knot maximum crosswind component?

Runway 32.

(Refer to Figures 32 and 33.) Upon landing, the front passenger (180 pounds) departs the airplane. A rear passenger (204 pounds) moves to the front passenger position. What effect does this have on the CG if the airplane weighed 2,690 pounds and the MOM/100 was 2,260 just prior to the passenger transfer? View Figures

The CG moves forward approximately 3 inches.

(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?

Weight is reduced by 210 pounds and the CG is aft of limits.

(Refer to Figures 32 and 33.) Determine if the airplane weight and balance is within limits. Front seat occupants 415 lb Rear seat occupants 110 lb Fuel, main tanks 44 gal Fuel, aux. tanks 19 gal Baggage 32 lb

Weight within limits, CG out of limits.

If the outside air temperature (OAT) at a given altitude is warmer than standard, the density altitude is

higher than pressure altitude