Gleim Su 5: Airplane Performance and Weight and Balance Flashcards
What are the standard temperature and pressure values for sea level?
15 C and 29.92 Hg
What effect, if any, does high humidity have on aircraft performance?
It decreases performance
Which factor would tend to increase the density altitude at a given airport?
A decrease in relative humidity
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
What effect does high density altitude have on aircraft performance?
It reduces climb performance
Which combination of atmosphere conditions will reduce aircraft takeoff and climb performance?
High temperature, high relative humidity, and high-density altitude
As air temperature increases, density altitude will
increase
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
Replan your journey to avoid the mountain pass
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?
Wait until the temperature decrease, and recalculate the takeoff performance
If the outside air temperature (OAT) at a given altitude is warmer than standard, the density altitude is?
higher than pressure altitude
Refer to Figure 8 on page 215.) Determine the density altitude for these conditions:
2,000 feet MSL
(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?
1,300-foot increase
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?
1,000-foot increase
(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
1,341 feet MSL
(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?
1,700-foot decrease
(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.
3,527 feet MSL
(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.
2,991 feet MSL
(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
8,500 feet MSL
(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?
1,650-foot increases
(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
1,150 feet
(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
1,400 feet
(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
1,750 feet
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
650 feet
(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?
11.2 gallons per hour
(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
70.1 gallons
(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
36.1 gallons
(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.
21.0” Hg
(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?
183 MPH
(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?
165 KTS
(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?
19 knots
(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
23 knots
(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.
35 knots
(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
Runway 32
(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?
Runway 14
(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
1,925 feet
(refer to Figure 37 on page 224.) Determine the approximate total distance required to land over a 50-ft obstacle
1,775 feet
(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
1,725 feet
(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
1,400 feet
If an emergency situation requires a downwind landing, pilots should expect a faster
Groundspeed at touchdown, a longer ground roll, and the likelihood of overshooting the desired touchdown point
(refer to Figure 38 on page 227.) determine the approximate landing ground roll distance.
Pressure altitude= Sea level
Headwind= 4 kts
Temperature= Std
401 feet
(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
816 feet
(Refer to Figure 38 on page 227.) Determine the approximate landing ground roll distance.
Pressure altitude = 5,000 ft
Headwind=Calm
Temperature= 101 F
545 feet
(Refer to Figure 38 on page 227.) Determine the approximate landing ground roll distance.
Pressure altitude= 1,250 ft
Headwind=8 kts
Temperature= Std
366 feet
(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
956 feet
(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
1,004 feet
Which items are included in the standard empty weight of an aircraft?
Unusable fuel and full engine oil.
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?
18.4 gallons
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
15 gallons
Given: The CG is located how far aft of datum
CG 94.01.
(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
40 gallons
(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?
300 pounds
(Refer to Figure 60 above.) How should the 500-pond weight be shifted to balance the plank on the fulcrum?
1 inch to the left
(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?
105 pounds
(Refer to Figure 34 on page 235.) Calculate the moment of the airplane and determine which category is applicable.
80.8, utility category
(Refer to Figure 34 on page 235.) Determine the moment with the following data:
75.1 pound-inches
(Refer to Figure 34 on page 235.) Determine the aircraft loaded moment and the aircraft category.
79.2, normal category
(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
Add a 100-pound weight to the baggage compartment
(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
Add a 100-pound weight to the baggage compartment
(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
20 pounds overweight, CG within limits
(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
CG 83.4, within limits
(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
45 pounds
(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
The CG moves approximately 3 inches
(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?
Weight is reduced by 210 pounds and the CG is aft of limits
(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
weight within limits, CG out of limits
(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
Drain 9 gallons of fuel
(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
185 pounds under allowable gross weight; CG is located within limits
(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
180 pounds under allowable gross weight; CG is located within limits
(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
197 pounds under allowable gross weight CG 83.6 inches aft of datum
