Weight and Balance & Air Performance (From Class Handouts)
(fig 61) How should the 500 pound weight be shifted to balance the plank on the fulcrum?
1 in to the left
What is the effect of 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
Determine the pressure altitude at an airport that is 1,386 feet MSK with an altimeter setting of 29.97:
1,341 feet MSL
(Fig 41) Determine the total distance required for takeoff to clear a 50 foot obstacle OAT standard Pressure altitude 4,000 ft Takeoff weight 2,800 lb Headwind component Calm
1,750 feet
(Fig 39) Determine the total distance required to land over a 50 ft obstacle Pressure altitude 5,000 ft Headwind 8 kts Temperature 41 F Runway Hardware Surface
956 feet
(Fig 37) 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
Which factor would tend to increase the density altitude at a given airport?
Increase in ambient temperature
What effect does high density altitude have on aircraft performance?
It reduces climb performance
(fig 68) 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
(Fig 37) What is the crosswind component for a landing on Runway 18 if the tower reports the wind is 220 at 30 knots?
19 knots
(fig 62) 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
(Fig 37) Determine the maximum wind velocity for a 45 crosswind if the maximum crosswind component for the airplane is 25 knots.
35 knots
(Fig 36) 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
(Fig 39) Determine the approximate landing ground roll distance Pressure altitude 1,250 ft Headwind 8 kts Temperature Standard
366 feet
(fig 35) What is the maximum amount of fuel that may be aboard the airplane on takeoff if loaded as follows? Weight MOM/1000 Empty weight 1,340 51.5 Pilot and front passenger 340 ---- Rear passengers 310 --- Baggage 45 --- Oil, 8 qt ---- ---
40 gallons
(Fig 39) Determine the approximate landing ground roll distance Pressure altitude sea level Headwind 4 kts Temperature Standard
401 feet
(fig 33, fig 34) 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
(fig 35) What is the maximum amount of baggage that may be loaded aboard the airplane for the CG to remain within the moment envelope Weight MOM/1000 Empty weight 1,350 51.5 Pilot and front passenger 250 ----- Rear passengers 400 ----- Baggage ----- ----- Fuel, 30 gal ----- ---- Oil, 8 qt ----- ----
105 pounds
(Fig 36) 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
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
(Fig 36) 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?
158 kts
What are the standard temperature and pressure values at sea level?
15⁰ C and 29.92" HG
(Fig 36) 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
An aircraft is loaded 110 pounds over maximum certification gross weight. If fuel (gasoline) is drained to bring the aircraft weight within limits, how much fuel should be drained?
18.4 gallons
(fig 68) Determine the condition of the airplane: Pilot and copilot 375 lb Passenger - aft position 245 lb Baggage 64 lb Fuel 70 gal
185 pounds under allowable gross weight; CG is located within limits
(Fig 39) Determine the approximate landing ground roll distance Pressure altitude 5000 feet Headwind Calm Temperature 101 F
545 feet
(fig 68) 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
(Fig 8) Determine the density altitude for these conditions: Altimeter setting 30.35 Runway temperature +25 F Airport Elevator 3,894 ft MSL
2,000 feet MSL
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
(fig 33, fig 34) 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
(Fig 36) Determine the approximate manifold pressure setting with 2,450 RPM to achieve 65 percent maximum continue power at 6,500 feet with a temperature of 36 F higher than standard.
21.0" Hg
(Fig 37) What is the headwind component for a landing on Runway 18 if the tower reports the wind as 220 at 30 knots?
23 knots
(Fig 37) What is the maximum wind velocity for a 30 crosswind if the maximum crosswind component for the airplane is 12 knots?
24 knots
(Fig 41) Determine the approximate ground roll distance required for takeoff. OAT 90 F Pressure altitude 2,000 ft Takeoff weight 2,500 lb Headwind component 20knts
650 feet
(Fig 36) 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
(fig 35) Determine the moment with the following data Weight MOM/1000 Empty weight 1,350 lb 51.5 Pilot and front passenger 340 ---- Fuel (std tanks) capacity ---- Oil, 8 qt ----- -----
74.9 pound-inches
(fig 35) Determine the aircraft loaded moment and the aircraft category Weight MOM/1000 Empty weight 1,350 51.5 Pilot and front passenger 380 ---- Fuel, 48 gal 288 ---- Oil, 8 qt ---- ----
79.2 normal category
(Fig 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
(fig 35) Calculate the moment of the airplane and determine which category is applicable Weight MOM/1000 Empty weight 1,350 lbs 52.5 Pilot and front passenger 310 lbs ---- Rear passengers 96 ---- Fuel 38 gal ------- ---- Oil, 8 qt ------- ----
80.8 utility category
(Fig 39) Determine the total distance required to land over a 50 ft obstacle: Pressure altitude 3,750 ft Headwind 12 kts Temperature Standard
816 feet
(fig 33, fig 34) 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 100-pound weight to the baggage compartment
Determine the pressure altitude at an airport that is 3,563 feet MSL with an altimeter setting of 29.96.
3,527 feet MSL
What is the effect of a temperature increase from 35 to 50 on density altitude if the pressure altitude remains at 3,000 feet MSL?
1,000 foot increase
(Fig 39) 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
(Fig 41) Determine the approximate ground roll distance for takeoff: OAT: 100 F Pressure altitude 2,000 ft Takeoff Weight 2,750 lb Headwind component Calm
1,150 feet
(Fig 38) Determine the total distance required to land OAT 90 F Pressure Altitude 3,000 ft Weight 2,900 ft Headwind component 10 kts Obstacle 50 ft
1,400 feet
(Fig 41) Determine the total distance required for takeoff to clear a 50 foot obstacle: OAT standard Pressure altitude Sea level Takeoff weight 2,700 lb Headwind component Calm
1,400 feet
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
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
(Fig 38) Determine the approximate total distance required to land over a 50 ft obstacle OAT 90 F Pressure altitude 4,000 ft Weight 2,800 lb Headwind component 10 kts
1,775 feet
(Fig 38) Determine the total distance required to land OAT standard Pressure altitude 10,000 ft Weight 2,400 lb Wind component Calm Obstacle 50 ft
1,925 feet
(fig 33, fig 34) 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
What effect does high density altitude, as compared to low density altitude, have on propeller efficacy and why?
Efficiency is reduced because the propeller exerts less force at high density altitudes than at low density altitudes
(fig 33, fig 34) 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
(fig 33, fig 34) 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
CG 83.4, within limits
Given: weight arm moment Empty weight : 1,495.0 101.4 151.593.0 Pilot and passengers 380.0 64.0 ---- Fuel (30 gal usable no reserve) ----- ---- --- The CG is located how far aft of datum?
CG 94.01
What effect, if any, does high humidity have on aircraft performance?
Decrease performance
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.
Which combination of atmospheric conditions will reduce aircraft takeoff and climb performance?
High temperature, high relative humidity, and high density altitude
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.
(Fig 37) 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
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 the takeoff distance over a 50 foot obstacle is 1,980 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 decreases, and recalculate the takeoff performance.
(fig 33, fig 34) 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
(fig 33, fig 34) 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.
