PPL 5 Performance and 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 F Runway.................................................................................................... Hard surface

1,004 feet.

(Refer to Figure 8.) What is the effect of a temperature increase from 30 to 50 F on the density altitude if the pressure altitude remains at 3,000 feet MSL ?

1,300-foot increase.

(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 f Pressure 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.............................................................................. 2,700lb 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 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 F Pressure 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.............................................................................. 2,800lb Headwind component............................................................. Calm

1,750 feet.

(Refer to Figure 37.) Determine the approximate total distance required to land over a 50-ft. obstacle. OAT.......................................................................................................... 90 F Pressure altitude............................................................................... 4000 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 fuel that may be aboard the airplane on takeoff if loaded as follows ? ......................................................................... Weight (LB) ...... MOM/1000 Empty weight............................................ 1,350...................... 51.5 Pilot and front passengers................... 250......................... —- Rear passengers........................................ 400 ...........................—- Baggage........................................................ —-..............................—- Fuel, 30 gal. ................................................ —-..............................—- Oil, 8 qt. ........................................................ —-.............................. -0.2

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.

What are the standard temperature and pressure values for sea level ?

15 C and 29.92" Hg.

If an aircraft is loaded 90 pounds over maximum certificated gross weight and fuel (gasoline) is drained to bring the aircraft weight within limits, how much fuel should be drained ?

15 gallons.

An aircraft is loaded 110 pounds over maximum certificated gross weight. If fuel (gasoline) is drained to bring the aircraft weight within limits, how much fuel should be drained ?

16.2 gallons.

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

165 KTS.

(Refer to Figure 67.) Determine the condition of the airplane: Pilot and copilot............................................................ 400 lb Passengers — aft position......................................... 240 lb Baggage............................................................................ 20 lb Fuel...................................................................................... 75 gal

180 pounds under allowable gross weight; CG is located within limits.

(Refer to Figure 35.) Approximately what true airspeed should a pilot expect with 65 percent maximum continuous power at 9,500 feet with a temperature of 36 F below standard ?

183 MPH.

(Refer to Figure 67.) Determine the condition of the airplane: Pilot and copilot............................................................ 375 lb Passengers — aft position......................................... 245 lb Baggage............................................................................ 65 lb Fuel...................................................................................... 70 gal

185 pounds under allowable gross weight; CG is located within limits.

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

19 knots.

(Refer to Figure 67.) Determine the condition of the airplane: Pilot and copilot............................................................ 316 lb Passengers Fwd position.................................................................... 130 lb Aft position...................................................................... 147 lb Baggage............................................................................ 50 lb Fuel...................................................................................... 75 gal

197 pounds under allowable gross weight; CG 83.6 inches aft of datum.

(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 Figure 32, Figure 33.) Determine if the airplane weight and balance is within limits. Front seat occupants........................................................................... 411 lb Rear seat occupants............................................................................ 100 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 degrees at 30 knots ?

23 knots.

(Refer to Figure 36.) What is the maximum wind velocity for a 30 degree 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 degree 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 ft Temperature.............................................................................. +29 C Manifold Pressure................................................................... 21.3" Hg Wind............................................................................................... 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/1000 Empty weight............................................ 1,350........................ 51.5 Pilot and front passengers................... 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 Figure 32, Figure 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 Main wing tanks..................................................................................... 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.................................................................................................... 32 C Pressure 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 ft Temperature.............................................................................. 22 C Manifold Pressure................................................................... 20.8" Hg Wind............................................................................................... Calm

70.1 gallons.

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

75.4 pound-inches.

(Refer to Figure 34.) Determine the aircraft loaded moment and the aircraft category. ......................................................................... Weight (LB) .......MOM/1000 Empty weight............................................ 1,350......................... 51.5 Pilot and front passengers................... 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 elevation .................................................................................+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/1000 Empty weight............................................ 1,350......................... 51.5 Pilot and front passengers................... 310.......................... —- Rear passengers........................................ 96............................ —- Fuel, 38 gal. ................................................ —-............................ —- Oil, 8 qt. ........................................................ —-............................ -0.2

80.8, utility category.

(Refer to Figure 38.) Determine the total distance required to land over a 50-ft. 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 F Runway.................................................................................................... Hard surface

956 feet.

(Refer to Figure 32, Figure 33.) With the airplane loaded as follows, what action can be taken to balance the airplane ? Front seat occupants........................................................................... 411 lb Rear seat occupants............................................................................ 100 lb Main wing tanks..................................................................................... 44 gal

Add a 1.00-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 Figure 32, Figure 33.) Calculate the weight and balance and Determine if the CG and weight of the airplane are within limits. Front seat occupants........................................................................... 411 lb Rear seat occupants............................................................................ 100 lb Baggage.................................................................................................... 27 lb Fuel.............................................................................................................. 35 gal

CG 83.4, within limits.

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

CG 94.01.

(Refer to Figure 32, Figure 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 wing 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.

If an emergency situation requires a downwind landing, pilots should expect a faster

Groundspeed at touchdown, a longer fortune roll, and the likelihood of overshooting the desired touchdown point.

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

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

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

Higher than pressure altitude.

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

It decreases performance.

What effects does high density altitude have on aircraft performance ?

It reduces climb performance.

You have planned a cross-country flight on a warm spring morning. Your course includes a mountain pass, which is at 11,500 feet MSL. The service ceiling of your airplane is 14,000 feet MSL. After checking the local weather report, you are able to calculate the density altitude of the mountain pass as 14,800 feet MSL. Which of the following is the correct action to take ?

Replan your journey to avoid the mountain pass.

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

Runway 32.

(Refer to Figure 32, Figure 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 ?

The CG moves forward approximately 3 inches.

Which items are included in the empty weight of an aircraft ?

Unusable fuel and undrainable oil

A pilot and two passengers landed on a 2,100 foot east-west gravel strip with an elevation of 1,800 feet. The temperature is warmer than expected and after computing the density altitude it is determined that takeoff distance over a 50 foot obstacle is 1,980 feet. The airplane is 75 pounds under gross weight. What would be the best choice ?

Wait until the temperature decreases, and recalculate the takeoff performance.

(Refer to Figure 32, Figure 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 Figure 32, Figure 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.