8 Aircraft Performance

5632. 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. A— the unusable fuel, full operating fluids, and full oil. B— all usable fuel, full oil, hydraulic fluid, but does not include the weight of pilot, passengers, or baggage. C— all usable fuel and oil, but does not include any radio equipment or instruments that were installed by someone other than the manufacturer.

5633. If all index units are positive when computing weight and balance, the location of the datum would be at the. A— centerline of the main wheels. B— nose, or out in front of the airplane. C— centerline of the nose or tailwheel, depending on the type of airplane.

5634. The CG of an aircraft can be determined by which of the following methods?. A— Dividing total arms by total moments. B— Multiplying total arms by total weight. C— Dividing total moments by total weight.

5635. The CG of an aircraft may be determined by. A— dividing total arms by total moments. B— dividing total moments by total weight. C— multiplying total weight by total moments.

5636. 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?. A— 86.0 inches. B— 116.8 inches. C— 125.0 inches.

5637. GIVEN: Weight A: 140 pounds at 17 inches aft of datum Weight B: 120 pounds at 110 inches aft of datum Weight C: 85 pounds at 210 inches aft of datum Based on this information, the CG would be located how far aft of datum?. A— 89.11 inches. B— 96.89 inches. C— 106.92 inches.

5638. GIVEN: Weight A: 135 pounds at 15 inches aft of datum Weight B: 205 pounds at 117 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?. A— 100.2 inches. B— 109.0 inches. C— 121.7 inches.

5639. 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?. A— 91.76 inches. B— 111.67 inches. C— 118.24 inches.

5164. Baggage weighing 90 pounds is placed in a normal category airplane’s baggage compartment which is placarded at 100 pounds. If this airplane is subjected to a positive load factor of 3.5 Gs, the total load of the baggage would be. A— 315 pounds and would be excessive. B— 315 pounds and would not be excessive. C— 350 pounds and would not be excessive.

5650. (Refer to Figure 38.) GIVEN: Empty weight (oil is included).......................... 1,271 lb 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?. A— Yes, the weight and CG is within limits. B— No, the weight exceeds the maximum allowable. C— No, the weight is acceptable, but the CG is aft of the aft limit.

5651. (Refer to Figure 38.) GIVEN: Empty weight (oil is included).......................... 1,271 lb 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. A— within the CG envelope. B— on the forward limit of the CG envelope. C— within the shaded area of the CG envelope.

5652. (Refer to Figure 38.) GIVEN: Empty weight (oil is included).......................... 1,271 lb 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?. A— Yes, the CG will remain within limits. B— No, the CG will be located aft of the aft CG limit. C— Yes, but the CG will be located in the shaded area of the CG envelope.

5646. GIVEN: Total weight...................................................... 4,137 lb CG location station................................................ 67.8 Fuel consumption......................................... 13.7 GPH Fuel CG station...................................................... 68.0 After 1 hour 30 minutes of flight time, the CG would be located at station. A— 67.79. B— 68.79. C— 70.78.

5649. GIVEN: Total weight...................................................... 3,037 lb CG location station................................................ 68.8 Fuel consumption......................................... 12.7 GPH Fuel CG station...................................................... 68.0 After 1 hour 45 minutes of flight time, the CG would be located at station. A— 68.77. B— 68.83. C— 69.77.

5647. An aircraft is loaded with a ramp weight of 3,650 pounds and having a CG of 94.0, 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 92.0?. A— 52.14 pounds. B— 62.24 pounds. C— 78.14 pounds.

5648. 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 (145 inches aft of datum) to the front compartment (45 inches aft of datum), what is the new CG?. A— 96.13 inches aft of datum. B— 95.50 inches aft of datum. C— 99.87 inches aft of datum.

5615. (Refer to Figure 31.) Rwy 30 is being used for landing. Which surface wind would exceed the airplane’s crosswind capability of 0.2 VS0, if VS0 is 60 knots?. A— 260° at 20 knots. B— 275° at 25 knots. C— 315° at 35 knots.

5616. (Refer to Figure 31.) If the tower-reported surface wind is 010° at 18 knots, what is the crosswind component for a Rwy 08 landing?. A— 7 knots. B— 15 knots. C— 17 knots.

5617. (Refer to Figure 31.) The surface wind is 180° at 25 knots. What is the crosswind component for a Rwy 13 landing?. A— 19 knots. B— 21 knots. C— 23 knots.

5618. (Refer to Figure 31.) What is the headwind component for a Rwy 13 takeoff if the surface wind is 190° at 15 knots?. A— 7 knots. B— 13 knots. C— 15 knots.

5302. What is the standard temperature at 10,000 feet?. A— -5°C. B— -15°C. C— +5°C.

5303. What is the standard temperature at 20,000 feet?. A— -15°C. B— -20°C. C— -25°C.

5305. What are the standard temperature and pressure values for sea level?. A— 15°C and 29.92" Hg. B— 59°F and 1013.2" Hg. C— 15°C and 29.92 Mb.

5234. The performance tables of an aircraft for takeoff and climb are based on. A— pressure/density altitude. B— cabin altitude. C— true altitude.

5300. What effect, if any, would a change in ambient temperature or air density have on gas turbine engine performance?. A— As air density decreases, thrust increases. B— As temperature increases, thrust increases. C— As temperature increases, thrust decreases.

5503. When diverting to an alternate airport because of an emergency, pilots should. A— rely upon radio as the primary method of navigation. B— climb to a higher altitude because it will be easier to identify checkpoints. C— apply rule-of-thumb computations, estimates, and other appropriate shortcuts to divert to the new course as soon as possible.

5661. With regard to the technique required for a crosswind correction on takeoff, a pilot should use. A— aileron pressure into the wind and initiate the lift-off at a normal airspeed in both tailwheel- and nosewheel-type airplanes. B— right rudder pressure, aileron pressure into the wind, and higher than normal lift-off airspeed in both tricycle- and conventional-gear airplanes. C— rudder as required to maintain directional control, aileron pressure into the wind, and higher than normal lift-off airspeed in both conventional- and nosewheel-type airplanes.

5662. When turbulence is encountered during the approach to a landing, what action is recommended and for what primary reason?. A— Increase the airspeed slightly above normal approach speed to attain more positive control. B— Decrease the airspeed slightly below normal approach speed to avoid overstressing the airplane. C— Increase the airspeed slightly above normal approach speed to penetrate the turbulence as quickly as possible.

5665. A proper crosswind landing on a runway requires that, at the moment of touchdown, the. A— direction of motion of the airplane and its lateral axis be perpendicular to the runway. B— direction of motion of the airplane and its longitudinal axis be parallel to the runway. C— downwind wing be lowered sufficiently to eliminate the tendency for the airplane to drift.

5614. What effect does an uphill runway slope have on takeoff performance?. A— Increases takeoff speed. B— Increases takeoff distance. C— Decreases takeoff distance.

5208. At higher elevation airports the pilot should know that indicated airspeed. A— will be unchanged, but groundspeed will be faster. B— will be higher, but groundspeed will be unchanged. C— should be increased to compensate for the thinner air.

5619. (Refer to Figure 32.) GIVEN: Temperature..........................................................75°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?. A— 50 pounds. B— 100 pounds. C— 300 pounds.

5620. (Refer to Figure 32.) GIVEN: Temperature..........................................................50°F Pressure altitude........................................... 2,000 feet Weight............................................................. 2,700 lb Wind.....................................................................Calm What is the total takeoff distance over a 50-foot obstacle?. A— 800 feet. B— 650 feet. C— 1,050 feet.

5621. (Refer to Figure 32.) GIVEN: Temperature........................................................100°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?. A— 1,180 feet. B— 1,350 feet. C— 1,850 feet.

5622. (Refer to Figure 32.) GIVEN: Temperature..........................................................30°F Pressure altitude............................................... 6,000 ft Weight............................................................. 3,300 lb Headwind.............................................................20 kts What is the total takeoff distance over a 50-foot obstacle?. A— 1,100 feet. B— 1,300 feet. C— 1,500 feet.

5628. (Refer to Figure 35.) GIVEN: Temperature..........................................................70°F Pressure altitude.............................................Sea level Weight............................................................. 3,400 lb Headwind.............................................................16 kts Determine the approximate ground roll. A— 689 feet. B— 716 feet. C— 1,275 feet.

5629. (Refer to Figure 35.) GIVEN: Temperature..........................................................85°F Pressure altitude............................................... 6,000 ft Weight............................................................. 2,800 lb Headwind.............................................................14 kts Determine the approximate ground roll. A— 742 feet. B— 1,280 feet. C— 1,480 feet.

5630. (Refer to Figure 35.) GIVEN: Temperature..........................................................50°F Pressure altitude.............................................Sea level Weight............................................................. 3,000 lb Headwind.............................................................10 kts Determine the approximate ground roll. A— 425 feet. B— 636 feet. C— 836 feet.

5631. (Refer to Figure 35.) GIVEN: Temperature..........................................................80°F Pressure altitude............................................... 4,000 ft Weight............................................................. 2,800 lb Headwind.............................................................24 kts What is the total landing distance over a 50-foot obstacle?. A— 1,125 feet. B— 1,250 feet. C— 1,325 feet.

5451. (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 reserve remaining?. A— 3 hours 8 minutes. B— 3 hours 22 minutes. C— 3 hours 43 minutes.

5452. (Refer to Figure 8.) GIVEN: Fuel quantity....................................................... 65 gal Best power (level flight)............................... 55 percent Approximately how much flight time would be available with a day VFR fuel reserve remaining?. A— 4 hours 17 minutes. B— 4 hours 30 minutes. C— 5 hours 4 minutes.

5453. (Refer to Figure 8.) Approximately how much fuel would be consumed when climbing at 75 percent power for 7 minutes?. A— 1.82 gallons. B— 1.97 gallons. C— 2.15 gallons.

5454. (Refer to Figure 8.) Determine the amount of fuel consumed during takeoff and climb at 70 percent power for 10 minutes. A— 2.66 gallons. B— 2.88 gallons. C— 3.2 gallons.

5455. (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?. A— 2 hours 34 minutes. B— 2 hours 49 minutes. C— 3 hours 18 minutes.

5456. (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°C. A— 46 pounds. B— 51 pounds. C— 58 pounds.

5457. (Refer to Figure 9.) Using a 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°C. A— 23 pounds. B— 31 pounds. C— 35 pounds.

5458. (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°C. A— 10 pounds. B— 14 pounds. C— 24 pounds.

5459. (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°C. A— 28 pounds. B— 35 pounds. C— 40 pounds.

5482. (Refer to Figure 13.) GIVEN: Aircraft weight.................................................. 3,400 lb Airport pressure altitude................................... 6,000 ft Temperature at 6,000 feet.................................... 10°C Using a maximum rate of climb under the given conditions, how much fuel would be used from engine start to a pressure altitude of 16,000 feet?. A— 43 pounds. B— 45 pounds. C— 49 pounds.

5483. (Refer to Figure 13.) GIVEN: Aircraft weight.................................................. 4,000 lb Airport pressure altitude................................... 2,000 ft Temperature at 2,000 feet.................................... 32°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?. A— 7 minutes. B— 8.4 minutes. C— 11.2 minutes.

5484. (Refer to Figure 14.) GIVEN: Aircraft weight.................................................. 3,700 lb Airport pressure altitude................................... 4,000 ft Temperature at 4,000 feet.................................... 21°C Using a normal climb under the given conditions, how much fuel would be used from engine start to a pressure altitude of 12,000 feet?. A— 30 pounds. B— 37 pounds. C— 46 pounds.

5485. (Refer to Figure 14.) GIVEN: Aircraft weight.................................................. 3,400 lb Airport pressure altitude................................... 4,000 ft Temperature at 4,000 feet.................................... 14°C Using a normal climb under the given conditions, how much time would be required to climb to a pressure altitude of 8,000 feet?. A— 4.8 minutes. B— 5 minutes. C— 5.5 minutes.

5486. (Refer to Figure 15.) GIVEN: Airport pressure altitude................................... 4,000 ft Airport temperature.............................................. 12°C Cruise pressure altitude................................... 9,000 ft Cruise temperature................................................-4°C What will be the distance required to climb to cruise altitude under the given conditions?. A— 6 miles. B— 8.5 miles. C— 11 miles.

5487. (Refer to Figure 15.) GIVEN: Airport pressure altitude................................... 2,000 ft Airport temperature.............................................. 20°C Cruise pressure altitude................................. 10,000 ft Cruise temperature................................................. 0°C What will be the fuel, time, and distance required to climb to cruise altitude under the given conditions?. A— 5 gallons, 9 minutes, 13 NM. B— 6 gallons, 11 minutes, 16 NM. C— 7 gallons, 12 minutes, 18 NM.

5463. (Refer to Figure 12.) GIVEN: Pressure altitude............................................. 18,000 ft Temperature........................................................-21°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.). A— 3 hours 46 minutes. B— 4 hours 1 minute. C— 4 hours 31 minutes.

5464. (Refer to Figure 12.) GIVEN: Pressure altitude............................................. 18,000 ft Temperature........................................................-41°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.). A— 2 hours 27 minutes. B— 3 hours 12 minutes. C— 3 hours 42 minutes.

5465. (Refer to Figure 12.) GIVEN: Pressure altitude............................................. 18,000 ft Temperature..........................................................-1°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.). A— 4 hours 50 minutes. B— 5 hours 20 minutes. C— 5 hours 59 minutes.

5625. (Refer to Figure 34.) GIVEN: Pressure altitude............................................... 6,000 ft Temperature.........................................................+3°C Power.........................................2,200 RPM — 22" MP Usable fuel available........................................... 465 lb What is the maximum available flight time under the conditions stated?. A— 6 hours 27 minutes. B— 6 hours 39 minutes. C— 6 hours 56 minutes.

5626. (Refer to Figure 34.) GIVEN: Pressure altitude............................................... 6,000 ft Temperature........................................................-17°C Power.........................................2,300 RPM — 23" MP Usable fuel available........................................... 370 lb What is the maximum available flight time under the conditions stated?. A— 4 hours 20 minutes. B— 4 hours 30 minutes. C— 4 hours 50 minutes.

5627. (Refer to Figure 34.) GIVEN: Pressure altitude............................................... 6,000 ft Temperature.......................................................+13°C Power.........................................2,500 RPM — 23" MP Usable fuel available........................................... 460 lb What is the maximum available flight time under the conditions stated?. A— 4 hours 58 minutes. B— 5 hours 7 minutes. C— 5 hours 12 minutes.

5460. (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?. A— 635 miles. B— 645 miles. C— 810 miles.

5461. (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.). A— 6.1 hours. B— 7.7 hours. C— 8.0 hours.

5462. (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?. A— 103 MPH TAS, 6.3 GPH. B— 105 MPH TAS, 6.2 GPH. C— 105 MPH TAS, 6.6 GPH.

5623. (Refer to Figure 33.) GIVEN: Weight............................................................. 4,000 lb Pressure altitude............................................... 5,000 ft Temperature......................................................... 30°C What is the maximum rate of climb under the given conditions?. A— 655 ft/min. B— 702 ft/min. C— 774 ft/min.

5624. (Refer to Figure 33.) GIVEN: Weight............................................................. 3,700 lb Pressure altitude............................................. 22,000 ft Temperature........................................................-10°C What is the maximum rate of climb under the given conditions?. A— 305 ft/min. B— 320 ft/min. C— 384 ft/min.