Free Printable PPLGS Module 08

1.

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

a)

Efficiency is increased due to less friction on the propeller blades.

b)

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

c)

Efficiency is reduced due to the increased force of the propeller in the thinner air.

2.

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

a)

equal to pressure altitude.

b)

lower than pressure altitude.

c)

higher than pressure altitude.

3.

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

a)

Low temperature, low relative humidity, and low density altitude.

b)

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

c)

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

4.

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.

5.

(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?

a)

1,200-foot increase.

b)

1,400-foot increase.

c)

1,650-foot increase.

6.

(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.

a)

2,991 feet MSL.

b)

2,913 feet MSL.

c)

3,010 feet MSL.

7.

(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

a)

4,600 feet MSL.

b)

5,877 feet MSL.

c)

8,500 feet MSL.

8.

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

a)

3,527 feet MSL.

b)

3,556 feet MSL.

c)

3,639 feet MSL.

9.

(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?

a)

1,000-foot increase.

b)

1,100-foot decrease.

c)

1,300-foot increase.

10.

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

a)

1,341 feet MSL.

b)

1,451 feet MSL.

c)

1,562 feet MSL.

11.

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

a)

2,000 feet MSL.

b)

2,900 feet MSL.

c)

3,500 feet MSL.

12.

(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?

a)

1,700-foot increase

b)

1,300-foot decrease

c)

1,700-foot decrease.

13.

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

a)

It increases performance

b)

It decreases performance.

c)

It has no effect on performance.

14.

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

a)

15°C and 29.92 "Hg.

b)

59°C and 1013.2 millibars.

c)

59°F and 29.92 millibar

15.

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

a)

An increase in barometric pressure.

b)

An increase in ambient temperature.

c)

A decrease in relative humidity.

16.

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

a)

Unusable fuel and undrainable oil.

b)

Only the airframe, powerplant, and optional equipment.

c)

Full fuel tanks and engine oil to capacity.

17.

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?

a)

15.7 gallons.

b)

16.2 gallons.

c)

18.4 gallons.

18.

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?

a)

10 gallons.

b)

12 gallons.

c)

15 gallons.

19.

(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?

a)

30 pounds.

b)

50 pounds.

c)

300 pounds.

20.

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

a)

1 inch to the left.

b)

1 inch to the right.

c)

4.5 inches to the right.

21.

21. (3664) 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 datum?

a)

CG 92.44.

b)

CG 94.01.

c)

CG 119.8.

22.

(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

a)

20 pounds overweight, CG aft of aft limits.

b)

20 pounds overweight, CG within limits.

c)

20 pounds overweight, CG forward of forward limits.

23.

(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

a)

45 pounds.

b)

63 pounds.

c)

220 pounds.

24.

(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 lb

Fuel 35 gal

a)

CG 81.7, out of limits forward.

b)

CG 83.4, within limits.

c)

CG 84.1, within limits.

25.

(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

a)

19 pounds overweight, CG within limits.

b)

19 pounds overweight, CG out of limits forward.

c)

Weight within limits, CG out of limits.

26.

(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/1000

Empty weight 1,350 51.5

Pilot and front passenger 250 –

Rear passengers 400 –

Baggage -- –

Fuel, 30 gal -- –

Oil, 8 qt -- -0.2

a)

105 pounds.

b)

110 pounds.

c)

120 pounds

27.

(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 passenger 310 –

Rear passengers 96 –

Fuel, 38 gal -- –

Oil, 8 qt -- -0.2

a)

79.2, utility category.

b)

80.8, utility category.

c)

81.2, normal category.

28.

(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 passenger 340 –

Rear passengers 310 –

Baggage 45 –

Oil, 8 qt -- --

a)

24 gallons.

b)

32 gallons.

c)

40 gallons.

29.

(Refer to Figure 34.) Determine the moment with the following data:

WEIGHT (LB) MOM/1000

Empty weight 1,350 51.5

Pilot and front passenger 340 –

Fuel (std tanks) Capacity –

Oil, 8 qt -- --

a)

69.9 pound-inches.

b)

74.9 pound-inches.

c)

77.6 pound-inches.

30.

(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 passenger 380 –

Fuel, 48 gal 288 –

Oil, 8 qt -- --

a)

78.2, normal category.

b)

79.2, normal category.

c)

80.4, utility category.

PPLGS Module 08

Total questions: 30

Worksheet time: 15mins

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