Weight & Balance/Performance
Q 497: GIVEN: Wind 175 degrees at 20 knots Distance 135 NM True course 075 degrees True airspeed 80 kts Fuel consumption 105 lb/hr Determine the time en route and fuel consumption
1 hour 40 minutes and 175 pounds
Q 1315: (Refer to figure 33) With weight of 4,000 pounds and a pressure altitude of 4,000 feet, how much would you expect the maximum rate of climb to improve if you delayed a flight to let the temperature drop from 40 degrees C to 20 degrees C?
145 fpm
Q 1523: (Refer to figure 14) GIVEN Aircraft weight 4,000 lb Airport pressure altitude 4,000 feet Temperature at 4,000 feet 7 degrees C above standard Using a normal climb under the given conditions, how much time would be required to climb to a pressure altitude of 16,000 feet?
27 minutes
Q 1404: Your aircraft has a total weight of 3,700 pounds and a CG location of 93 inches aft of the datum. The CG limit range is 91 inches to 92 inches. What is the lightest baggage that must be shifted from station 175 to station 38 to bring the CG into the allowable range?
28 pounds
Q 1376: (Refer to figure 15) GIVEN: Airport pressure altitude 3,000 ft Airport temperature 15 degrees C Cruise pressure altitude 8,000 ft Cruise temperature -10 degrees C What will be the fuel, time, and distance required to climb to cruise altitude under the given conditions?
3 gallons, 5 minutes, 7NM
Q 467: (Refer to figure 8) GIVEN: Fuel quantity 47 gal Power-cruise (lean) 55 percent Approximately how much flight time would be available with a night VFR fuel reservation remaining?
3 hours 22 minutes
Q 1385: (Refer to figure 34) You have 80 gallons of usable avgas. You know it takes 20 gallons of avgas to start, taxi, takeoff, descent, and landing. What would be your maximum cruise flight time with day, VFR reserves? Given: Pressure altitude 6,000 ft Temperature 3 degrees C Power 2,400 RPM -24" MP
3 hours and 30 minutes
Q 636: (Refer to figure 32) GIVEN: Temperature 75 degrees F Pressure altitude 6,000 ft Weight 2,900 lb Headwind 20 kts To safely take off over a 50-foot obstacle in 1,000 feet, what weight reduction is necessary?
300 pounds
Q 488:If an airplane is consuming 9.5 gallons of fuel per hour at a cruising altitude of 6,000 feet and the groundspeed is 135 knots, how much fuel is required to travel 490 NM?
35 gallons
Q 473: (Refer to figure 9) Using normal climb, how much fuel would be used from engine start to 10,000 feet pressure altitude? Aircraft weight 3,500 lb Airport pressure altitude 4,000 ft Temperature 21 degrees C
35 pounds
Q 1377: If an aircraft is consuming 13 gallons of AvGas per hour with a groundspeed of 165 knots in a 12 knot tailwind, how much fuel is required to travel 480 NM?
37 gallons
Q 487: If an airplane is consuming 12.5 gallons of fuel per hour at a cruising altitude of 8,500 feet and the groundspeed is 145 knots, how much fuel is required to travel 435 NM?
38 gallons
Q 641: (Refer to figure 33) GIVEN: Weight 3,700 lb Pressure altitude 22,000 ft Temperature -10 degrees C What is the maximum rate of climb under the given conditions?
384 ft/min
Q 239: (Refer to figure 4) What increase in load factor would take place if the angle of bank were increased from 60 degrees to 80 degrees?
4 Gs
Q 1465: (Refer to figure 4) You are descending at a constant rate of descent. You roll into a 60 degree bank turn. How much does the stall speed increase?
40 percent
Q 475: (Refer to figure 10) Using a maximum rate of climb, how much fuel would be used from engine start to 10,000 feet pressure altitude? Aircraft weight 3,800 lb Airport pressure altitude 4,000 ft Temperature 30 degrees C
40 pounds
Q 230: (Refer to figure 3) If an airplane glides at an angle of attack of 10 degree, how much altitude will it lose in 1 mile?
480 feet
Q 503: (Refer to figure 15) GIVEN: Airport pressure altitude 2,000 ft Airport temperature 20 degrees C Cruise pressure altitude 10,000 ft Cruise temperature 0 degrees C What will be the fuel, time, and distance required to climb to cruise altitude under the given conditions?
5 gallons, 9 minutes, 13 NM
Q 644: (Refer to figure 34) GIVEN: Pressure altitude 6,000 ft Temperature +13 degrees C Power 2,500 RPM -23"MP Usable fuel available 460 lb What is the maximum available flight time under the conditions stated?
5 hours 12 minutes
Q 481: (Refer to figure 12) GIVEN: Pressure altitude 18,000 ft Temperature -1 degrees C Power 2,200 RPM-20"MP Best fuel economy usable fuel 344 lb What is the approximate flight time available under the given conditions? (Allow for VFR day fuel reserve)
5 hours 59 minutes
Q 490: If an airplane is consuming 14.7 gallons per hour and the groundspeed is 157 knots, how much fuel is required to travel 612 NM?
58 gallons
Q 1526: (Refer tot figure 35) GIVEN Temperature 70 degrees F Pressure altitude 4,000 ft Weight 2,500 lb Headwind 20 kts Determine the approximate ground roll.
640 feet
Q 1458: (Refer to figure 35) What is the approximate ground roll under the following conditions? Temperature 60 degrees F Pressure altitude Sea Level Weight 3,000 lb Headwind 10 kts
660 feet
Q 1513: (Refer to figure 34) How many gallons of fuel are required, including day VFR reserves, for a flight with a cruise time of 4 hours and 36 minutes? Pressure altitude 6,000 ft Standard Temperature +3 degrees C Power 2,400 RPM-22" MP
67 gallons
Q 663: GIVEN: Total weight 4,137 lb CG location station 67.8 Fuel consumption 13.7 GPH Fuel CG station 68 After 1 hour 30 minutes of flight time, the CG would be located at station
67.79
Q 645: (Refer to figure 35) GIVEN: Temperature 70 degrees F Pressure altitude Sea Level Weight 3,400 lb Headwind 16 kts Determine the approximate ground roll
676 feet
Q 1514: GIVEN Total weight 4,120 lbs CG location 68.2 inches Fuel consumption 13.5 GPH Fuel CG station 68.4 After 1 hour 45 minutes of flight time, the CG would be located at station
68.2
Q 477: (Refer to figure 11) What would be the endurance at an altitude of 7,500 feet, using 52 percent power? NOTE: (With 48 gallons fuel-no reserve)
7.7 hours
Q 1333: The aircraft you are loading has the following placards: 1. Maximum load baggage Area 1= 120 pounds 2. Maximum load baggage Area 2= 50 pounds 3. The maximum total baggage load may not exceed 120 pounds. Baggage Area 2 is loaded to the maximum. How much baggage may be loaded in baggage Area 1?
70 pounds
Q 640: (Refer to figure 33) GIVEN: Weight 4,000 lb Pressure altitude 5,000 ft Temperature 30 degrees C What is the maximum rate of climb under the given conditions?
702 ft/min
Q 646: (Refer to figure 35) GIVEN: Temperature 85 degrees F Pressure altitude 6,000 ft Weight 2,800 lb Headwind 14 kts Determine the approximate ground roll
742 feet
Q 1525: (Refer to figure 11) With 48 gallons of fuel and no reserve, at a cruise altitude of 5,000 feet at 75% BHP and 2,600 RPM, what would be the airplane's fuel range?
760 miles
Q 499: (Refer to figure 13) GIVEN: Aircraft weight 4,000 lb Airport pressure altitude 2,000 ft Temperature at 2,000 feet 32 degrees C Using a maximum rate of climb under the given conditions, how much time would be required to climb to a pressure altitude of 8,000 feet?
8.4 minutes
Q 1393: What can be found by dividing the total movement by the total weight of an aircraft?
C.G (center of gravity)
Q 1355: From what place on the aircraft should the distance to objects be measured to keep the weight and balance consistent?
Datum
Q 1334: To achieve maximum range of an aircraft, what action should be taken as fuel is consumed and the aircraft becomes lighter?
Decrease power to maintain constant airspeed
Q 1357: (Refer to figure 2) You are flying a 2,750 pound airplane with power on, gear and flaps up, in level turn at 80 knots. You roll into a 60 degree bank and simulate engine failure. Which of the following is true?
You will be below stall speed and stall
Q 1297: TAS and groundspeed are higher proportionally
at higher density altitude
Q 652: The CG of an aircraft may be determined by
dividing total moments by total weight
Q 1335: During preflight, you need to know fuel burn because this allows you to calculate
maximum endurance
Q 650: If all index units are positive when computing weight and balance, the location of the datum would be at the
nose, or out in front of the airplane
Q 1373: (Refer to figure 32) GIVEN: Temperature 80 degrees F Pressure altitude 2,000 ft Weight 3,400 lb Headwind 10 kts What is the total takeoff distance required to clear a 50-foot oil rig?
1,250 feet
Q 231: (Refer to figure 3) How much altitude will this airplane lose in 3 statute miles of gliding at an angle of attack 8 degrees?
1,320 feet
Q 638: (Refer to figure 32) GIVEN: Temperature 100 degrees F Pressure altitude 4,000 ft Weight 3,200 lb Wind Calm What is the ground roll required for takeoff over a 50-foot obstacle?
1,350 feet
Q 639: (Refer to figure 32) GIVEN: Temperature 30 degrees F Pressure altitude 6,000 ft Weight 3,300 lb Headwind 20 kts What is the total takeoff distance over a 50-foot obstacle?
1,500 feet
Q 1495: (Refer to figure 32) GIVEN Temperature 80 degrees F Pressure altitude 5,000 ft Weight 3,300 lb Headwing 15 kts What is the total takeoff distance over a 50-foot obstacle?
1,950 feet
Q 1502: (Refer to figure 15) With the following conditions, what is the required distance to climb to cruise altitude? Airport pressure altitude= 2,000 ft Airport temperature = 10 degrees C Cruise pressure altitude = 9,000 ft Cruise temperature= -5 degrees C
10 NM
Q 1391: (Refer to figure 31) Landing runway 17, with winds 140 degrees at 20 knots. What is the crosswind component?
10 knots-left crosswind
Q 482: An airplane descends to an airport under the following conditions: Cruising altitude 6,500 ft Airport elevation 700 ft Descends to 800 ft AGL Rate of descent 500 ft/min Average true airspeed 110 kts True course 335 degrees Average wind velocity 060 degrees at 15 kts Variation 3 degrees W Deviation +2 degrees Average fuel consumption 8.5 gal/hr Determine the approximate time, compass heading, distance, and fuel consumed during the descent
10 minutes, 348 degrees, 18 NM, 1.4 gallons
Q 655: GIVEN: Weight A: 135 pounds at 15 inches aft of datum Weight B: 205 pounds at 127 inches aft of datum Weight C: 85 pounds at 195 inches aft of datum Based on this information, the CG would be located how far aft of datum?
100.2 inches
Q 478: (Refer to figure 11) What would be the approximate true airspeed and fuel consumption per hour at an altitude of 7,500 feet, using 52 percent power?
105 MPH TAS, 6.2 GPH
Q 653: GIVEN: Weight A: 155 pounds at 45 inches aft of datum Weight B: 165 pounds at 145 inches aft of datum Weight C: 95 pounds at 185 inches aft of datum Based on this information, where would the CG be located aft of datum?
116.8 inches
Q 656: GIVEN: Weight A: 175 pounds at 135 inches aft of datum Weight B: 135 pounds at 115 inches aft of datum Weight C: 75 pounds at 85 inches aft of datum The CG for the combined weights would be located how far aft of datum?
118.24 inches
Q 1379: (Refer to figure 14) GIVEN Aircraft weight 3,700 lb Airport pressure altitude Sea Level Temperature at Sea Level 14 degrees C above standard Using a normal climb under the given conditions, how much AvGas would be used from engine start to a pressure altitude of 16,000 feet?
13 gallons
Q 484: An airplane descends to an airport under the following conditions: Cruising altitude 10,500 ft Airport elevation 1,700 ft Descends to 1,000 ft AGL Rate of descent 600 ft/min Average true airspeed 135 kts True course 263 degrees Average wind velocity 330 degrees at 30 kts Variation 7 degrees E Deviation +3 degrees Average fuel consumption 11.5 gal/hr Determine the approximate time, compass heading, distance, and fuel consumed during the descent
13 minutes, 271 degrees, 26 NM, 2.5 gallons
Q 1353: Your aircraft has a total weight of 3,700 pounds and a CG location of 92.5 inches aft of the datum. The CG limit range is 90 inches to 92 inches. How much weight must be shifted from station 170 to station 40 to bring the CG into the allowable range?
15 pounds
Q 505: An airplane departs an airport under the following conditions: Airport elevation 1,500 ft Cruise altitude 9,500 ft Rate of climb 500 ft/min Average true airspeed 160 kts True Course 145 degrees Average wind velocity 080 degrees at 15 kts Variation 5 degrees E Deviation -3 degrees Average fuel consumption 14 gal/hr Determine the approximate time, compass heading, distance, and fuel consumed during the climb
16 minutes, 132 degrees, 41 NM, 3.7 gallons
Q 232: (Refer to figure 3) The L/D ratio at a 2 degree angle of attack is approximately the same as the L/D ratio for a
16.5 degree angle of attack
Q 1449: (Refer to figure 8) Using the line for Best Power Level Flight, what is the fuel flow at 75% power?
17 gallons per hour
Q 633: (Refer to figure 31) If the tower-reported surface wind is 010 degrees at 18 knots, what is the crosswind component for a Rwy 08 landing?
17 knots
Q 504: An airplane departs an airport under the following conditions: Airport elevation 1,000 ft Cruise altitude 9,500 ft Rate of climb 500 ft/min Average true airspeed 135 kts True Course 215 degrees Average wind velocity 290 degrees at 20 kts Variation 3 degrees W Deviation -2 degrees Average fuel consumption 13 gal/hr Determine the approximate time, compass heading, distance, and fuel consumed during the climb
17 minutes, 224 degrees, 36 NM, 3.7 gallons
Q 483: An airplane descends to an airport under the following conditions: Cruising altitude 7,500 ft Airport elevation 1,300 ft Descends to 800 ft AGL Rate of descent 300 ft/min Average true airspeed 120 kts True course 165 degrees Average wind velocity 240 degrees at 20 kts Variation 4 degrees E Deviation -2 degrees Average fuel consumption 9.6 gal/hr Determine the approximate time, compass heading, distance, and fuel consumed during the descent
18 minutes, 168 degrees, 34 NM, 2.9 gallons
Q 634: (Refer to figure 31) The surface wind is 180 degrees at 25 knots. What is the crosswind component for a Rwy 13 landing?
19 knots
Q 480: (Refer to figure 12) GIVEN: Pressure altitude 18,000 ft Temperature -44 degrees C Power 2,500 RPM-26"MP Recommended lean mixture usable fuel 318 lb What is the approximate flight time available under the given conditions? (Allow for VFR night fuel reserve)
2 hours 27 minutes
Q 471: (Refer to figure 8) With 38 gallons of fuel aboard at cruise power (55 percent), how much flight time is available with night VFR fuel reserve still remaining?
2 hours 34 minutes
Q 1438: (Refer to figure 12) Under the conditions listed in the chart, what is the aircraft's endurance at cruise altitude with a usable fuel load (AvGas) of 425 pounds under the following conditions (no reserve)? Engine start, taxi, takeoff, and climb: 100 pound, 10 minutes Temperature: Standard RPM: 2300 Manifold Pressure: 30" Descent, landing, and taxi: 60 pounds, 8 minutes
2 hours and 44 minutes
Q 1419: (Refer to figure 34) You are planning a flight in an airplane that has been fueled with 375 pounds of usable AvGas. If the performance charts indicate that you will use 50 pounds of fuel for other than cruise portions of the flight, how long can you cruise and still meet the night VFR fuel requirements under the following conditions? Given: Pressure altitude 6,000 ft Temperature 3 degrees C RPM 2,500 Manifold Pressure 24" MP
2 hours and 48 minutes
Q 1310: (Refer to figure 32) GIVEN: Temperature 90 degrees F Pressure altitude 4,000 ft Weight 3,400 lb Wind Calm What is the required distance for takeoff over a 50-foot obstacle?
2,000 feet
Q 1066: (Refer to figure 3) If an airplane glides at an angle of attack of 10 degrees, how much altitude will it lose in 6 miles?
2,830 feet
Q 469: (Refer to figure 8) Approximately how much fuel would be consumed when climbing at 75 percent power for 7 minutes?
2.15 gallons
Q 470: (Refer to figure 8) Determine the amount of fuel consumed during takeoff and climb at 70 percent power for 10 minutes.
2.88 gallons
Q 1311: (Refer to figure 33) GIVEN: Rate of climb: 745 fpm Pressure altitude 6,000 ft Weight 4,000 lb What is the maximum temperature for takeoff?
20 degrees C
Q 1390:(Refer to figure 31) Landing runway 22, with winds 140 degrees at 20 knots. What is the crosswind component?
20 knots-left crosswind
Q 1378: If an aircraft is consuming 80 pounds of AvGas per hour with a groundspeed of 180 knots in a 15 knot tailwind, how much fuel is required to travel 460 NM? Taxi, takeoff, and climb: 70 NM and 10 minutes Descent, approach, and landing: 50 NM and 7 minutes
205 pounds
Q 485: If fuel consumption is 80 pounds per hour and groundspeed is 180 knots, how much fuel is required for an airplane to travel 460 NM?
205 pounds
Q 1049: (Refer to figure 31) The surface wind is 180 degrees at 27 knots. What is the crosswind component for a Rwy 13 landing?
21 knots
Q 1410: How many pounds of AvGas is required to go 350 NM, plus day VFR fuel reserve, with a groundspeed of 150 knots, fuel consumption of 80 pounds per hour, and an altitude of 5,500 feet?
226 pounds
Q 474: (Refer to figure 10) Using a maximum rate of climb, how much fuel would be used from engine start to 6,000 feet pressure altitude? Aircraft weight 3,200 lb Airport pressure altitude 2,000 ft Temperature 27 degrees C
24 pounds
Q 486: If an airplane is consuming 95 pounds of fuel per hour at a cruising altitude of 6,500 feet and the groundspeed is 173 knots, how much fuel is required to travel 450 NM?
248 pounds
Q 632: (Refer to figure 31) Rwy 30 is being used for landing. Which surface wind would exceed the airplane's crosswind capability of .2 VSO, if VSO is 60 knots?
260 degrees at 20 knots
Q 479: (Refer to figure 12) GIVEN: Pressure altitude 18,000 ft Temperature -21 degrees C Power 2,400 RPM-28"MP Recommended lean mixture usable fuel 425 lb What is the approximate flight time available under the given conditions? (Allow for VFR day fuel reserve)
4 hours 1 minute
Q 468: (Refer to figure 8) GIVEN: Fuel quantity 65 gal Power-cruise (lean) 55 percent Approximately how much flight time would be available with a night VFR fuel reservation remaining?
4 hours 30 minutes
Q 643: (Refer to figure 34) GIVEN: Pressure altitude 6,000 ft Temperature -17 degrees C Power 2,300 RPM -23"MP Usable fuel available 370 lb What is the maximum available flight time under the conditions stated?
4 hours 30 minutes
Q 498: (Refer to figure 13) GIVEN: Aircraft weight 3,400 lb Airport pressure altitude 6,000 ft Temperature at 6,000 feet 10 degrees C Using a maximum rate of climb under the given conditions, how much fuel would be used from engine start to pressure altitude of 16,000 feet?
43 pounds
Q 1488: You have loaded the aircraft and are computing the weight and balance with the following information. Where is the center of gravity. Empty Weight: 1681 lbs at CG 40.1 Pilot (fwd seat): 220 lbs at CG 38.1 Passenger (aft seat): 180 lbs at CG 72.0 Baggage: 44lbs at CG 95.2 Fuel: 30 gallons of AvGas at CG 47.0
44.0 inches aft of datum
Q 1365: You have loaded the aircraft and are computing the weight and balance. Empty weight =1705 lbs at CG 39.2 Pilot (fwd seat)=190 lbs at CG 38.1 Passenger (aft seat)=210 lbs at CG 73 Baggage=55 lbs at CG 95.5 Fuel=40 gallons Avgas at CG 48 Where is the center of gravity?
44.24
Q 1474: What is the CG under the following conditions? Empty weight: 1710 lbs at 41.1 CG Pilot: 230 lbs at 38.9 CG Passenger: 210 lbs at 72.5 CG Baggage: 20 lbs at 95.2 CG AvGAs: 50 gallons at 48.5 CG
44.9 inches aft of datum
Q 500: (Refer to figure 14) GIVEN: Aircraft weight 3,700 lb Airport pressure altitude 4,000 ft Temperature at 4,000 feet 21 degrees C Using a normal rate of climb under the given conditions, how much fuel would be used from engine start to pressure altitude of 12,000 feet?
46 pounds
Q 501: (Refer to figure 14) GIVEN: Aircraft weight 3,400 lb Airport pressure altitude 4,000 ft Temperature at 4,000 feet 14 degrees C Using a normal rate of climb under the given conditions, how much time would be required to climb to a pressure altitude of 8,,000 feet?
5.5 minutes
Q 489: If an airplane is consuming 14.8 gallons of fuel per hour at a cruising altitude of 7,500 feet and the groundspeed is 167 knots, how much fuel is required to travel 560NM?
50 gallons
Q 664: An aircraft is loaded with a ramp weight of 3,650 pounds and having a CG of 94 approximately how much baggage would have to be moved from the rear baggage area at station 180 to the forward baggage area at station 40 in order to move the CG to 92?
52.14 pounds
Q 1374 (Refer to figure 34) Given the following conditions, how much AvGas will you burn in 4 hours? Pressure altitude 6,000 ft Standard Temperature +3 degrees C Power 2,300 RPM -24" MP
56 gallons
Q 1375: (Refer to figure 12) Under the given conditions of flight, how much AvGas is required to fly 600 NM with a 15 knot headwind? Pressure altitude 18,000 ft Temperature -21 degrees C Power 2,400 RPM -26"MP
57 gallons of AvGas
Q 472: (Refer to figure 9) Using a normal climb, how much fuel would be used from engine start to 12,000 feet pressure altitude? Aircraft weight 3,800 lb Airport pressure altitude 4,000 ft Temperature 26 degrees C
58 pounds
Q 1524: (Refer to figure 8) Approximately how much fuel would be consumed when climbing at 75 percent power for 20 minutes?
6 gallons
Q 642: (Refer to figure 34) GIVEN: Pressure altitude 6,000 ft Temperature +3 degrees C Power 2,200 RPM -22"MP Usable fuel available 465 lb What is the maximum available flight time under the conditions stated?
6 hours 39 minutes
Q 1498: (Refer to figure 11) With 38 gallons of fuel and no reserve, at a cruise altitude of 7,500 feet and 2,700 RPM, using 8.4 gallons per hour and 133 TAS MPH, what would be the airplane's fuel range?
600 miles
Q 647: (Refer to figure 35) GIVEN: Temperature 50 degrees F Pressure altitude Sea Level Weight 3,000 lb Headwind 10 kts Determine the approximate ground roll
636 feet
Q 1479: GIVEN Total weight 2,950 lbs CG location 68.5 inches Fuel consumption 13 GPH Fuel CG station 68.2 After 1 hour 45 minutes of flight time, the CG would be located at station
68.5
Q 666: GIVEN: Total weight 3,037 lbs CG location station 68.8 Fuel consumption 12.7 GPH Fuel CG station 68 After 1 hour 45 minutes of flight time, the CG would be located at station
68.83
Q 635: (Refer to figure 31) What is the headwind component for a Rwy 13 takeoff if the surface wind is 190 degree at 15 knots?
7 knots
Q 1499: (Refer to figure 14) GIVEN Aircraft weight: 3,700 lb Airport pressure altitude Sea Level Temperature at Sea Level 14 C degrees above standard Using a normal climb under the given conditions, how much AvGas would be used to a pressure altitude of 12,000 feet?
8 gallons
Q 502: (Refer to figure 15) GIVEN: Airport pressure altitude 4,000 ft Airport temperature 12 degrees C Cruise pressure altitude 9,000 ft Cruise temperature -4 degrees C What will be the distance required to climb to cruise altitude under the given conditions?
8.5 miltes
Q 637: (Refer to figure 32) GIVEN: Temperature 50 degrees F Pressure altitude 2,000 ft Weight 2,700 lb Wind Calm What is the total takeoff distance over a 50-foot obstacle?
800 feet
Q 1362: (Refer to figure 2) With the power off and gear and flaps down, you overshoot the turn from base to final. Instead of performing an immediate go around, you increase the angle of bank to 60 degrees to complete the turn. At what airspeed would you expect the airplane to stall?
81 kts
Q 1482: After all aircraft loading is complete for the flight, the total weight is 3,510 lbs and the total moment is 284,620 in-lbs. How far aft is the center of gravity located from the datum?
81.1 inches
Q 476: (Refer to figure 11) If the cruise altitude is 7,500 feet, using 64 percent power at 2,500 RPM, what would be the range with 48 gallons of usable fuel?
810 miles
Q 1387: (Refer to figure 34) Determine how much AvGas is required to takeoff and cruise to the destination. Engine start/taxi/takeoff/climb distance and fuel-20 NM and 140 lbs Cruise distance 500 NM Altitude 6,000 feet RPM 2,550 MP -21" Temperature -20 degrees C above standard Groundspeed 110 knots Descent and landing distance and fuel- 15 NM and 40 lbs
84 gallons
Q 1307: (Refer to figure 33) What is the maximum rate of climb given a weight of 3,700 pounds, pressure altitude of 4,000 feet, and temperature of 30 degrees C?
850 feet per minute
Q 1484: (Refer to figure 32) GIVEN Temperature 80 degrees F Pressure altitude 2,000 ft Weight 3,200 lb Headwind 10 kts What is the ground roll required for takeoff over a 50-foot obstacle?
900 feet
Q 238: (Refer to figure 4) What is the stall speed of an airplane under a load factor of 2 G's if the unaccelerated stall speed is 65 knots?
91 knots
Q 1383: An aircraft is loaded with a weight of 4,700 pounds and a CG of 97. The CG limit ranges from 93 to 96. If 80 pounds is moved from the rear baggage compartment (142 inches aft of the datum) to the front compartment (44 inches aft of the datum), what is the new CG?
95.3
Q 665: An airplane is loaded to a gross weight of 4,800 pounds, with three pieces of luggage in the rear baggage compartment. The CG is located 98 inches aft of datum, which is 1 inch aft of limits. If luggage which weighs 90 pounds is moved from the rear baggage compartment (145inches aft of datum) to the front compartment (45 inches aft of datum), what is the new CG?
96.13 inches aft of datum
Q 1268: You are taking off on a downscoping runway. How is performance affected.
Decrease takeoff distance
Q 1224: Why does the pilot expect lower aircraft performance at a higher relative humidity?
Moisture content is lighter than air, so the air is less dense
Q 1101: As you place an 80 pound bag in the baggage compartment, you see a placard stating that the maximum weight limit for the compartment is 60 pounds. Can you leave the bag in the compartment?
No, because the bag is heavier than the baggage compartment weight limit
Q 1337: What items should be added to the basic empty weight when calculating weight and balance?
Optional equipment
Q 1197: When a headwind shears to a tailwind, how does it affect the performance of an airplane?
Performance will decrease
Q 1389: (Refer to figure 31) Given winds of 180 at 25 knots, and an airport with runway 03/21, which runway do the winds favor, and what is the crosswind component?
Runway 21 with a 13 knot left crosswind
Q 1372: (Refer to figure 31) Given winds of 010 at 18 knots, and an airport with runway 16/34, which runway do the winds favor, and what is the crosswind component?
Runway 34 with a 9 knot right crosswind
Q 1338: An aircraft is equipped with an air conditioner labeled 'for ground use only'. What will happen to the takeoff roll distance if the air conditioner remains on?
Takeoff distance increaes
Q 1105: What is 'static load'?
The load imposed on an aircraft structure due to the weight of the aircraft and its contents
Q 1360: Is it permissible to have a published ramp weight that exceeds the published maximum takeoff weight?
Yes, fuel burned on the ground reduces the weight to takeoff
Q 1527: (Refer to figure 38) GIVEN Empty weight (oil is included) 1,270 lbs Empty weight moment (in-lb/1000) 102.01 Pilot and copilot 355 lb Rear seat passenger 150 lb Cargo 90 lb Fuel 36 gal Is the airplane loaded within limits?
Yes, the CG is within the limits of the envelope
Q 669: (Refer to figure 38) GIVEN: Empty weight (oil is included) 1,271 lbs Empty weight moment (in-lb/1,000) 102.04 Pilot and copilot 360 lb Cargo 340 lb Fuel 37 gal Will the CG remain within limits after 30 gallons of fuel has been used in flight?
Yes, the CG will remain within limits
Q 667: (Refer to figure 38) GIVEN: Empty weight (oil is included) 1,271 lbs Empty weight moment (in-lb/1,000) 102.04 Pilot and copilot 400 lb Rear seat passenger 140 lb Cargo 100 lb Fuel 37 gal Is the airplane loaded within limits?
Yes, the weight and CG is within limits
Q 1314: (Refer to figure 2) An airplane weighing 2,750 pounds is flying with power on and gear and flaps up. If bank is increased to 60 degrees and 75 knots is maintained, it will
be below stall speed
Q 662: (Refer to figure 37) GIVEN: Weight Moment Gyroplane basic weight 1,315 154.0 (oil included) Pilot weight 145 ? Passenger weight 153 ? 27 gal fuel 162 ? The CG is located
outside the CG envelope; but the maximum gross weight is not exceeded
Q 251: The performance tables of an aircraft for takeoff and climb are based on
pressure/density altitude
Q 1336: Ensuring the maximum zero fuel weight is within range is important to
reduce the potential for structural damage
Q 1358: Density altitude is equal to field elevation when
standard atmospheric conditions exist
Q 649: When computing weight and balance, the basic empty weight includes the weight of the airframe, engine(s), and all installed optional equipment. Basic empty weight also includes
the unusable fuel, full operating fluids, and full oil
Q 668: (Refer to figure 38) GIVEN: Empty weight (oil is included) 1,271 lbs Empty weight moment (in-lb/1,000) 102.04 Pilot and copilot 260 lb Rear seat passenger 120 lb Cargo 60 lb Fuel 37 gal Under these conditions, the CG is determined to be located
within the CG envelope
