COMMERCIAL PILOT - (CH. 8) AIRCRAFT PERFORMANCE

PREG20080433 Ref. Fig. 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?. 7 minutes. 8.4 minutes. 11.2 minutes.

PREG20080432 Ref. Fig. 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?. 43 pounds. 45 pounds. 49 pounds.

PREG20080431 Ref. Fig. 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.). 4 hours 50 minutes. 5 hours 20 minutes. 5 hours 59 minutes.

PREG20080430 Ref. Fig. 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.). 2 hours 27 minutes. 3 hours 12 minutes. 3 hours 42 minutes.

PREG20080429 Ref Fig. 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.). 3 hours 46 minutes. 4 hours 1 minute. 4 hours 31 minutes.

PREG20080447 Ref. Fig. 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?. 1,100 feet. 1,300 feet. 1,500 feet.

PREG20080459 The CG of an aircraft may be determined by. dividing total arms by total moments. dividing total moments by total weight. multiplying total weight by total moments.

PREG20080446 Ref. Fig. 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?. 1,180 feet. 1,350 feet. 1,850 feet.

PREG20080452 Ref. Fig. 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?. 4 hours 58 minutes. 5 hours 7 minutes. 5 hours 12 minutes.

PREG20080460 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?. 86.0 inches. 116.8 inches. 125.0 inches.

PREG20080469 Ref. Fig. 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. within the CG envelope. on the forward limit of the CG envelope. within the shaded area of the CG envelope.

PREG20080462 GIVEN: A 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?. 100.2 inches. 109.0 inches. 121.7 inches.

PREG20080445 Ref. Fig. 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?. 800 feet. 650 feet. 1,050 feet.

PREG20080476 A proper crosswind landing on a runway requires that, at the moment of touchdown, the. direction of motion of the airplane and its lateral axis be perpendicular to the runway. direction of motion of the airplane and its longitudinal axis be parallel to the runway. downwind wing be lowered sufficiently to eliminate the tendency for the airplane to drift.

PREG20080475 Which type of approach and landing is recommended during gusty wind conditions?. A power-on approach and power-on landing. A power-off approach and power-on landing. A power-on approach and power-off landing.

PREG20080474 A pilot's most immediate and vital concern in the event of complete engine failure after becoming airborne on takeoff is. maintaining a safe airspeed. landing directly into the wind. turning back to the takeoff field.

PREG20080473 When turbulence is encountered during the approach to a landing, what action is recommended and for what primary reason?. Increase the airspeed slightly above normal approach speed to attain more positive control. Decrease the airspeed slightly below normal approach speed to avoid overstressing the airplane. Increase the airspeed slightly above normal approach speed to penetrate the turbulence as quickly as possible.

PREG20080428 Ref. Fig. 11 What would be the approximate true airspeed and fuel consumption per hour at an altitude of 7,500 feet, using 52 percent power?. 103 MPH TAS, 6.3 GPH. 105 MPH TAS, 6.2 GPH. 105 MPH TAS, 6.6 GPH.

PREG20080418 Ref. Fig. 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?. 4 hours 17 minutes. 4 hours 30 minutes. 5 hours 4 minutes.

PREG20080416 What are the standard temperature and pressure values for sea level?. 15°C and 29.92" Hg. 59°F and 1013.2" Hg. 15°C and 29.92 Mb.

PREG20080415 What is the standard temperature at 20,000 feet?. -15°C. -20°C. -25°C.

PREG20080414 What is the standard temperature at 10,000 feet?. -5°C. -15°C. +5°C.

PREG20080413 What effect, if any, would a change in ambient temperature or air density have on gas turbine engine performance?. As air density decreases, thrust increases. As temperature increases, thrust increases. As temperature increases, thrust decreases.

PREG20080412 The performance tables of an aircraft for takeoff and climb are based on. pressure/density altitude. cabin altitude. true altitude.

PREG20080411 At higher elevation airports the pilot should know that indicated airspeed. will be unchanged, but groundspeed will be faster. will be higher, but groundspeed will be unchanged. should be increased to compensate for the thinner air.

PREG20080410 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 3.5Gs, the total load of the baggage would be. 315 pounds and would be excessive. 315 pounds and would not be excessive. 350 pounds and would not be excessive.

PREG20080442 What effect, if any, would a change in ambient temperature or air density have on gas turbine engine performance?. As air density decreases, thrust increases. As temperature increases, thrust increases. As temperature increases, thrust decreases.

PREG20080410 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 3.5Gs, the total load of the baggage would be. 315 pounds would be excessive. 315 pounds and would not be excessive. 350 pounds and would not be excessive.

PREG20080442 Ref. Fig. 31 The surface wind is 180° at 25 knots. What is the crosswind component for a Rwy 13 landing?. 19 knots. 21 knots. 23 knots.

PREG20080424 Ref. Fig. 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. 10 pounds. 14 pounds. 24 pounds.

PREG20080425 Ref. Fig. 10 Using a maximum rate of climb, how much fuel would be used from engine start to 10,000 feet pressure altitude?. 28 pounds. 35 pounds. 40 pounds.

PREG20080422 Ref. Fig. 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. 46 pounds. 51 pounds. 58 pounds.

PREG20080427 Ref. Fig. 11 What would be the endurance at an altitude of 7,500 feet, using 52 percent power? NOTE: (With 48 gallons fuel-no reserve.). 6.1 hours. 7.7 hours. 8.0 hours.

PREG20080441 Ref. Fig. 31 If the tower-reported surface wind is 010° at 18 knots, what is the crosswind component for a Rwy 08 landing?. 7 knots. 15 knots. 17 knots.

PREG20080440 Ref. Fig. 31 Rwy 30 is being used for landing. Which surface wind would exceed the airplane's crosswind capability of 0.2 Vso, if Vso is 60 knots?. 260° at 20 knots. 275° at 25 knots. 315° at 35 knots.

PREG20080439 What effect does an uphill runway slope have on takeoff performance?. Increases takeoff speed. Increases takeoff distance. Decreases takeoff distance.

PREG20080438 When diverting to an alternate airport because of an emergency, pilots should. rely upon radio as the primary method of navigation. climb to a higher altitude because it will be easier to identify checkpoints. pply rule-of-thumb computations, estimates, and other appropriate shortcuts to divert to the new course as soon as possible.

PREG20080437 Ref. Fig. 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?. 5 gallons, 9 minutes, 13 NM. 6 gallons, 11 minutes, 16 NM. 7 gallons, 12 minutes, 18 NM.

PREG20080426 Ref. Fig. 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?. 635 miles. 645 miles. 810 miles.

PREG20080435 Ref. Fig. 14 GIVEN: 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?. 4.8 minutes. 5 minutes. 5.5 minutes.

PREG20080434 Ref. Fig. 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?. 30 pounds. 37 pounds. 46 pounds.

PREG20080436 Ref. Fig. 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?. 6 miles. 8.5 miles. 11 miles.

PREG20080454 Ref. Fig. 35 GIVEN: Temperature .............................................................. 85°F Pressure Altitude ................................................... 6,000 ft Weight ................................................................ 2,800 lb Headwind ............................................................... 14 kts Determine the approximate ground roll. 742 feet. 1,280 feet. 1,480 feet.

PREG20080457 If all index units are positive when computing weight and balance, the location of the datum would be at the. centerline of the main wheels. nose, or out in front of the airplane. centerline of the nose or tailwheel, depending on the type of airplane.

PREG20080456 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. all usable fuel, full oil, hydraulic fluid, but does not include the weight of pilot, passengers, or baggage. all usable fuel and oil, but does not include any radio equipment or instruments that were installed by someone other than the manufacturer.

PREG20080458 The CG of an aircraft can be determined by which of the following methods?. Dividing total arms by total moments. Multiplying total arms by total weights. Dividing total moments by total weight.

PREG20080455 Ref. Fig. 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?. 1,125 feet. 1,250 feet. 1,325 feet.

PREG20080453 Ref. Fig. 35 GIVEN: Temperature .............................................................. 70°F Pressure Altitude ................................................ Sea level Weight ................................................................ 3,400 lb Headwind ............................................................... 16 kts Determine the approximate ground roll. 689 feet. 716 feet. 1,275 feet.

PREG20080472 With regard to the technique required for a crosswind correction on takeoff, a pilot should use. aileron pressure into the wind and initiate the lift-off at a normal airspeed in both tailwheel- and nose-wheel-type airplanes-. right rudder pressure, aileron pressure into the wind, and higher than normal lift-off airspeed in both tricycle- and conventional-gear airplanes. 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.

PREG20080461 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 fat aft of datum?. 89.11 inches. 96.89 inches. 106.92 inches.

PREG20080471 Who has the final authority to accept or decline any land and hold short A (LAHSO)clearence. Pilot in command. ATC Tower control. Airplane owner operator.

PREG20080468 Ref. Fig. 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?. Yes, the weight and CG is within limits. No, the weight exceeds the maximum allowable. No, th weight acceptable, but the CG is aft of the aft limit.

PREG20080467 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. 68.77. 68.83. 69.77.

PREG20080466 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?. 96.13 inches aft of datum. 95.50 inches aft of datum. 99.87 inches aft of datum.

PREG20080465 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?. 52.14 pounds. 62.24 pounds. 78.14 pounds.

PREG20080464 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. 67.79. 68.79. 70.78.

PREG20080463 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?. 91.76 inches. 111.67 inches. 118.24 inches.

PREG20080470 ef. Fig. 38 A 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 in flight?. Yes, the CG will remain within limits. No, the CG will be located aft of the aft CG limit. Yes, but the CG will be located in the shaded area of the CG envelope.

PREG20080443 Ref. Fig. 31 What is the headwind component for a Rwy 13 takeoff if the surface wind is 190° at 15 knots?. 7 knots. 13 knots. 15 knots.

PREG20080444 Ref. Fig. 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?. 50 pounds. 100 pounds. 300 pounds.

PREG20080417 Ref Fig. 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?. 3 hours 8 minutes. 3 hours 22 minutes. 3 hours 43 minutes.

PREG20080423 Ref. Fig. 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. 23 pounds. 31 pounds. 35 pounds.

PREG20080421 Ref. Fig. 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. 2 hours 49 minutes. 3 hours 18 minutes.

PREG20080420 Fig.8 Determine the amount of fuel consumed during takeoff and climb at 70 percent power for 10 minutes. 2.66 gallons. 2.88 gallons. 3.2 gallons.

PREG20080419 Ref. Fig. 8 Approximately how much fuel would be consumed when climbing at 75 percent power for 7 minutes?. 1.82 gallons. 1.97 gallons. 2.15 gallons.

PREG20080450 Ref. Fig. 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?. 6 hours 27 minutes. 6 hours 39 minutes. 6 hours 56 minutes.

PREG20080451 Ref. Fig. 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?. 4 hours 20 minutes. 4 hours 30 minutes. 4 hours 50 minutes.

PREG20080449 Ref. Fig. 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?. 305 ft/min. 320 ft/min. 384 ft/min.

PREG20080448 Ref. Fig. 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?. 665 ft/min. 702 ft/min. 774 ft/min.