Gleim Su 5: Airplane Performance and Weight and Balance

Question 1

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

Answer 1

15 C and 29.92 Hg

Question 2

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

Answer 2

It decreases performance

Question 3

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

Answer 3

A decrease in relative humidity

Question 4

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

Answer 4

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

Question 5

What effect does high density altitude have on aircraft performance?

Answer 5

It reduces climb performance

Question 6

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

Answer 6

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

Question 7

As air temperature increases, density altitude will

Answer 7

increase

Question 8

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 14,00 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

Answer 8

Replan your journey to avoid the mountain pass

Question 9

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 the 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?

Answer 9

Wait until the temperature decrease, and recalculate the takeoff performance

Question 10

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

Answer 10

higher than pressure altitude

Question 11

Refer to Figure 8 on page 215.) Determine the density altitude for these conditions:

Answer 11

2,000 feet MSL

Question 12

(Refer to Figure 8 on page 215.) 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?

Answer 12

1,300-foot increase

Question 13

Refer to Figure 8 on page 215. 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?

Answer 13

1,000-foot increase

Question 14

(Refer to figure 8 on page 215.) Determine the pressure altitude at an airport that is 1,386 feet MSL with an altimeter setting of 29.97

Answer 14

1,341 feet MSL

Question 15

(Refer to Figure 8 below.) 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?

Answer 15

1,700-foot decrease

Question 16

(Refer to Figure 8 on page 217.) Determine the pressure altitude at an airport that is 3,563 feet MSL with an altimeter setting of 29.96.

Answer 16

3,527 feet MSL

Question 17

(Refer to Figure 8 on page 217.) Determine the pressure altitude with an indicated altitude of 1,380 feet MSL with an altimeter setting of 28.22 at standard temperature.

Answer 17

2,991 feet MSL

Question 18

(Refer to Figure 8 on page 217.) Determine the density altitude for these conditions:
Altimeter setting=29.25
Runway temperature= +81 F
Airport elevation= 5,250 ft MSL

Answer 18

8,500 feet MSL

Question 19

(Refer to Figure 8 below.) 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?

Answer 19

1,650-foot increases

Question 20

(refer to Figure 40 below.) Determine the approximate ground roll distance required for takeoff.
OAT=38 C
Pressure altitude= 2,000 ft
Takeoff weight=2,750 lb
Headwind component=calm

Answer 20

1,150 feet

Question 21

(Refer to Figure 40 on page 218.) 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

Answer 21

1,400 feet

Question 22

(Refer to Figure 40 on page 218.) 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

Answer 22

1,750 feet

Question 23

Refer to figure 40 on page 218.) 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

Answer 23

650 feet

Question 24

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

Answer 24

11.2 gallons per hour

Question 25

(Refer to Figure 35 below.) What is the expected fuel consumption for a 1,000-nautical mile flight under the following conditions? Pressure altitude= 8,000 ft Temperature= 22C Manifold pressure= 20.8" hg Wind=Calm

Answer 25

70.1 gallons

Question 26

(Refer to Figure 35 on page 220.) What is the expected fuel consumption for a 500-nautical mile flight under the following conditions? Pressure altitude= 4,000 ft Temperature= +29C Manifold Pressure= 21.3" Hg Wind= Calm

Answer 26

36.1 gallons

Question 27

(Refer to Figure 35 on page 220.) 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.

Answer 27

21.0" Hg

Question 28

(Refer to Figure 35 on page 220.) 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?

Answer 28

183 MPH

Question 29

(Refer to Figure 35 on page 220.) Approximately what true airspeed should a pilot expect with full throttle at 10,500 feet with a temperature of 36 F above standard?

Answer 29

165 KTS

Question 30

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

Answer 30

19 knots

Question 31

(Refer to Figure 36 on page 222.) What is the headwind component for a landing on Runway 18 if the tower reports the wind as 220 at 30 knots

Answer 31

23 knots

Question 32

(Refer to Figure 36 on page 222.) Determine the maximum wind velocity for a 45 crosswind if the maximum crosswind component for the airplane is 25 knots.

Answer 32

35 knots

Question 33

(Refer to Figure 36 on page 222.) 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

Answer 33

Runway 32

Question 34

(Refer to Figure 36 on page 222.) With a reported wind of south at 20 knots, which runway is appropriate for an airplane with a 13-knot maximum crosswind component?

Answer 34

Runway 14

Question 35

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

Answer 35

1,925 feet

Question 36

(refer to Figure 37 on page 224.) Determine the approximate total distance required to land over a 50-ft obstacle

Answer 36

1,775 feet

Question 37

(Refer to figure 37 on page 224.) Determine the total distance required to land. OAT= 90 F Pressure altitude= 3,000 ft Weight= 2,900 lb Headwind component= 10 kts Obstacle= 50ft

Answer 37

1,725 feet

Question 38

(Refer to Figure 37 on page 224.) 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

Answer 38

1,400 feet

Question 39

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

Answer 39

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

Question 40

(refer to Figure 38 on page 227.) determine the approximate landing ground roll distance. Pressure altitude= Sea level Headwind= 4 kts Temperature= Std

Answer 40

401 feet

Question 41

(Refer to Figure 38 on page 227.) Determine the total distance required to land over a 50-ft. obstacle. Pressure altitude= 3,750 ft Headwind= 12kts Temperature=Std

Answer 41

816 feet

Question 42

(Refer to Figure 38 on page 227.) Determine the approximate landing ground roll distance. Pressure altitude = 5,000 ft Headwind=Calm Temperature= 101 F

Answer 42

545 feet

Question 43

(Refer to Figure 38 on page 227.) Determine the approximate landing ground roll distance. Pressure altitude= 1,250 ft Headwind=8 kts Temperature= Std

Answer 43

366 feet

Question 44

(Refer to Figure 38 on page 227.) 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

Answer 44

956 feet

Question 45

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

Answer 45

1,004 feet

Question 46

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

Answer 46

Unusable fuel and full engine oil.

Question 47

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

Answer 47

18.4 gallons

Question 48

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

Answer 48

15 gallons

Question 49

Given: The CG is located how far aft of datum

Answer 49

CG 94.01.

Question 50

(Refer to Figure 34 on page 229.) What is the maximum amount of fuel that may be aboard the airplane on takeoff if loaded as follows

Answer 50

40 gallons

Question 51

(Refer to Figure 61 above.) If 50 ponds 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?

Answer 51

300 pounds

Question 52

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

Answer 52

1 inch to the left

Question 53

(Refer to Figure 34 on page 233.) What us the maximum amount of baggage that may be loaded aboard the airplane for the CG to remain within the moment envelope?

Answer 53

105 pounds

Question 54

(Refer to Figure 34 on page 235.) Calculate the moment of the airplane and determine which category is applicable.

Answer 54

80.8, utility category

Question 55

(Refer to Figure 34 on page 235.) Determine the moment with the following data:

Answer 55

75.1 pound-inches

Question 56

(Refer to Figure 34 on page 235.) Determine the aircraft loaded moment and the aircraft category.

Answer 56

79.2, normal category

Question 57

(Refer to Figure 32 n page 237 and Figure 33 on page 237.) With the airplane loaded as follows, what action can be taken to balance the airplane? Front seat occupants= 411 lb Rear seat occupants= 100lb Main wing tanks= 44 gal

Answer 57

Add a 100-pound weight to the baggage compartment

Question 58

(Refer to Figure 32 on page 237 and Figure 33 on page 237.) With the airplane loaded as follows, what action can be taken to balance the airplane? Front Seat occupants= 441 lb Rear seat occupants= 100 lb Main wing tanks= 44 gal

Answer 58

Add a 100-pound weight to the baggage compartment

Question 59

(Refer to Figure 32 on page 239 and Figure 33 on page 239.) 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

Answer 59

20 pounds overweight, CG within limits

Question 60

(Refer to Figure 32 on page 239 and Figure 33 on page 239.) Calculate the weight and balance and determine if the CG and the weight of the airplane are within limits. Front seat occupants= 350lb Rear seat occupants = 325 lb Baggage=27 lb Fuel= 35 gal

Answer 60

CG 83.4, within limits

Question 61

(refer to Figure 32 on page 241 and Figure 33 on page 241.) 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

Answer 61

45 pounds

Question 62

(Refer to Figure 32 on page 241 and Figure 33 on page 241) 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

Answer 62

The CG moves approximately 3 inches

Question 63

(Refer to Figure 32 on page 241 and Figure 33 on page 241.) 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 takeoff?

Answer 63

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

Question 64

(Refer to Figure 32 on page 243 and Figure 33 on page 243.) Determine if the airplane weight and balance is within limits. Front seat occupants= 415lb Rear seat occupants= 100 lb Fuel, main tanks = 44 gal Fuel, aux, tanks= 19 gal Baggage=32 lb

Answer 64

weight within limits, CG out of limits

Question 65

(Refer to Figure 32 on page 243 and Figure 33 on page 243.) 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

Answer 65

Drain 9 gallons of fuel

Question 66

(Refer to Figure 67 on page 245.) Determine the condition of the airplane: Pilot and copilot= 375 lb Passengers--aft position= 245 lb Fuel=70 gal

Answer 66

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

Question 67

(Refer to Figure 67 on page 245.) Determine the condition of the airplane: Pilot and copilot= 400 lb Passengers-- aft position= 240 lb Baggage=20 lb Fuel= 75 gal

Answer 67

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

Question 68

(Refer to Figure 67 on page 247.) Determine the condition of the airplane: Pilot and copilot=316lb Passengers Fwd position= 130lb Aft position= 147 lb Baggage=50 lb Fuel= 75 gal

Answer 68

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