REVISION NO.: INITIAL PPL EXAM
MAY 4, 2010
PPL – FLIGHT PERFORMANCE AND PLANNING
1. The four forces acting on an airplane in-flight are: lift, weight, thrust, and drag. lift, weight, gravity, and thrust. lift, weight, gravity, power, and friction
2. (Refer to figure 38.) Determine the approximate total distance required to land Over a 50-foot obstacle. OAT………………90°F Pressure …………. 4,000 Feet Weight …………….2,800 pounds Headwind component ..10knots 1,525 feet 1,950 feet 1,775 feet 3. To minimize the side loads placed on the landing gear during touchdown, the pilot should keep: direction of motion of the aircraft parallel to the runway. down wing lowered sufficiently to eliminate the tendency for the aircraft to drift. longitudinal axis of the aircraft parallel to the direction of its motion. 4. (Refer to figure 41) Determine the total distance required for takeoff to clear a 50-foot obstacle. OAT……………….............Std OAT……………….............Std Pressure …………. ……..4,000 ……..4,000 Feet Takeoff Weight ………….2,800 …………. 2,800 pounds Headwind component ….Calm 1,500 feet 2,000 feet 1,750 feet 5. If an altimeter setting is not available before flight, to which altitude should the pilot adjust the altimeter? The elevation of the nearest airport corrected to mean sea level. The elevation of the departure area. Pressure altitude corrected for nonstandard.
6. Loading an airplane to the most aft CG will cause the airplane to be: less stable at slow speeds, but more stable at high speeds. less stable at high speeds, but more stable at low speeds. less stable at all speed. 7. GIVEN: WEIGHT
MOMENT
ARM
Empty Weight
1495
151593
101.4
Pilot and pax (AVGAS) Fuel (30 gal Usable no reserve)
380
64 96
The CG is located how far to the aft of datum? CG 94.01 CG 92.44 CG 119.8
8. If it is necessary to set the altimeter from 29.15 to 29.85, what change occurs? 700-foot increase in indicated altitude. 70-foot increase in indicated altitude. 70-foot increase in density altitude.
9. The angle of attack at which an airplane wing will stalls: increase if the CG is moved forward remain the same regardless of gross weight. change with an increase in gross weight. 10. 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
11. (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? 7 knots 15 knots 17 knots
12. (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? 635 miles 645 miles 810 miles 13. (Refer to figure 11) What would be the endurance at an altitude of 7,500 feet, using 52 percent power? NOTE: with 48gallons of fuel – no reserve 6.1 hours 7.7 hours 8.0 hours 14. (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? 103 MPH TAS, 6.3 GPH 105 MPH TAS, 6.6 GPH 105 MPH TAS, 6.2 GPH 15. The CG of an aircraft can be determine by which of the following method’s? Dividing total arms by total moments Multiplying total arms by total weight Dividing total moments by total weight 16. 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 17. 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 18. (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 46 pounds 51 pounds 58 pounds
19. (Rfer to figure 14) GIVEN: Aircraft weight……………………………………….3,700 lb Airport pressure altitude……………………………4,000 ft Temperature at 4,000 ft…………………………….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 ft.? 30 pounds 37 pounds 46 pounds 20. What effect does an uphill runway slope have on takeoff performance? Increase takeoff speed Increase takeoff distance Decrease takeoff distance
