Fig. 1
What is the maximun landing distance that may be used by a turbopropellerpowered, small transport category airplane to land on Rwy 24 (Dry) at the alternate airport? 5,490 feet 6,210 feet 6,405 feet.
Fig. 1
What is the maximum landing distance that may be used by a reciprocatingengine-powered, small transport category airplane to land on Rwy 24 (dry) at the destination airport? 5,490 feet. 6,210 feet. 6,405 feet.
Fig. 1
What is the maximun landing distance that may be used by a turbopropellerpowered small transport category airplane to land on Rwy 6 (dry) at the alternate airport? 5,460 feet 6,210 feet 6,370 feet.
Fig. 1
What is the maximun landing distance that may be used by a reciprocatingengine-powered, small transport category airplane to land on Rwy 6 (dry) at the destination airport? 5,460 feet 6,210 feet 6,370 feet.
Fig. 1
What is the maximun landing distance that may used by a turbine-enginepowered, small transport catergory airplane to land on Rwy 24 (dry) at the destination airport? 5,460 feet 5,490 feet 6,210 feet.
Fig. 1
What is the maximum landing distance that may be used by a turbine-enginepowered, small transport category airplane to land on Rwy 6 (wet) at the destination airport? 5,460 feet. 5,880 feet. 6,088 feet.
Fig. 2
What is the maximum landing distance that may be used by a turbopropellerpowered, small transport category airplane to land on Rwy 19 (dry) at the destination airport? 6,020 feet. 5,820 feet. 5,160 feet.
Fig. 2
What is the maximum landing distance that may be used by a reciprocatingengine- powered, small transport category airplane to land on Rwy 1 (dry) at the destination airport? 5,010 feet. 5,820 feet. 5,845 feet.
Fig. 2
What is the maximum landing distance that may be used by a turbine-enginepowered, small transport category airplane to land on Rwy 1 (dry) at the destination airport? 5,010 feet. 5,820 feet. 5,845 feet.
Fig. 2
What is the maximum landing distance that may be used by a turbine-enginepowered, small transport category airplane to land on Rwy 19 (dry) at the destination airport? 5,160 feet. 5,820 feet. 6,020 feet.
Fig. 2
May a small transport category, turbine-engine-powered airplane that has a computed landing distance of 5,500 feet use one or both of the runways depicted in the illustration at the destination airport? Neither Rwy 1 nor Rwy 19 may be used if dry conditions exist. Only Rwy 19 may be used provided dry conditions exist. Rwy 1 or Rwy 19 may be used whether conditions are wet or dry.
Fig. 2
May a small transport category, turboprop airplane that has a computed landing distance of 6,000 feet use either or both runways depicted in the illustration at the destination airport? Only Rwy 19 may be used if dry conditions exist. Neither Rwy 1 nor Rwy 19 may be used under any conditions. Either Rwy 1 or Rwy 19 may be used whether conditions are wet or dry.
Fig. 2
What is the maximum landing distance that may be used for a non-transport category, turbopropeller-driven airplane to land on Rwy 1 (dry) at the alternate airport? 5,010 feet. 5,845 feet. 6,020 feet.
Fig.2
Which condition meets FAR Part 135 operational requirements for a small, transport category, turboprop airplane to land at the destination airport that has the runway environment given in the illustration? The airport may be listed as the destination airport if the landing distance does not exceed 5,160 feet for Rwy 19. The airport may NOT be listed as the destination airport if the landing distance exceeds 5,100 feet for Rwy 19. The airport may be listed as the destination airport if the landing distance does not exceed 5,350 feet for either runway, wet or dry conditions.
What effective runway lenght is required for a turbojet-powered airplane at the destination airport if the runways are forecast to be wet or slippery at the ETA? 70 percent of the actual runway available, from a height of 50 feet over the threshold. 115 percent of the runway length required for a dry runway. 115 percent of the runway length required for a wet runway.
For which of these aircraft is the "clearway" for a particular runway considered in computing takeoff weight limitations? Those passenger-carrying transport aircraft certificated between August 26, 1957 and August 30, 1959. Turbine-engine-powered transport airplanes certificated after September 30, 1958. U.S. certified air carrier airplanes certificated after August 29, 1959.
How can turbulent air cause an increase in stalling speed of an airfoil? An abrupt change in relative wind. A decrease in angle of attack. Sudden decrease in load factor.
If an engine failure occurs at an altitude above single-engine ceiling, what airspeed should be maintained? Vmc. Vyse. Vxse.
What is the resulting performance loss when one engine on a twin-engine airplane fails? Reduction of cruise airspeed by 50 percent. Reduction of climb by 50 percent or more. Reduction of all performance by 50 percent.
Under what condition is Vmc the highest? Gross weight is at the maximum allowable value. CG is at the most rearward allowable position. CG is at the most forward allowable position.
What effect does landing at high elevation airports have on groundspeed with comparable conditions relative to temperature, wind, and airplane weight? Higher than at low elevation. Lower than at low elevation. The same as at low elevation.
Which maximum range factor decreases as weight decreases? Angle of attack. Altitude. Airspeed.
What performance is characteristic of flight at maximum L/D in a propellerdriven airplane? Maximum range and distance glide. Best angle of climb. Maximum endurance.
What should a pilot do to maintain "best range" airplane performance when a tailwind is encountered? Increase speed. Maintain speed. Decrease speed.
At what speed, with reference to L/Dmax, does maximum rate-of-climb for a jet airplane occur? A speed greater than that for L/Dmax. A speed equal to that for L/Dmax. A speed less than that for L/Dmax.
At what speed, with reference to L/Dmax, does maximum range for a jet airplane occur? A speed less than that for L/Dmax. A speed equal to that for L/Dmax. A speed greater than that for L/Dmax.
Fig. 12
Given the following conditions, what is the minimum torque for takeoff?
Pressure altitude ........................................................ 9,000 ft
Tempertaure (OAT) ......................................................... +3°C
Ice vanes ............................................................... Extended 3,100 foot-pound. 3,040 foot-pound. 3,180 foot-pound.
Fig. 12
Given the following conditions, what is the minimum torque for takeoff?
Pressure altitude ........................................................ 7,500 ft
Tempertaure (OAT) ....................................................... +35°C
Ice vanes .............................................................. Retracted 2,820 foot-pound. 2,880 foot-pound. 2,780 foot-pound.
Fig. 12
Given the following conditions, what is the minimum torque for takeoff?
Pressure altitude ........................................................ 7,500 ft
Tempertaure (OAT) ......................................................... +9°C
Ice vanes ............................................................... Extended 3,200 foot-pound. 3,160 foot-pound. 3,330 foot-pound.
Fig. 12
Given the following conditions, what is the minimum torque for takeoff?
Pressure altitude ........................................................ 3,500 ft
Tempertaure (OAT) ....................................................... +43°C
Ice vanes .............................................................. Retracted 3,000 foot-pound. 3,050 foot-pound. 3,110 foot-pound.
Fig. 12
Given the following conditions, what is the minimum torque for takeoff?
Pressure altitude ........................................................ 5,500 ft
Tempertaure (OAT) ....................................................... +29°C
Ice vanes .............................................................. Retracted 2,950 foot-pound. 3,100 foot-pound. 3,200 foot-pound.
Fig. 13
Given the following conditions, what is the takeoff distance over a 50-foot obstacle?
Pressure altitude ..................................................... Sea Level
Tempertaure (OAT) ....................................................... +12°C
Weight ................................................................... 16,000 lb
Wind component .................................................. 16 kts HW
Ice vanes .............................................................. Retracted 1,750 feet. 2,800 feet. 2,550 feet.
Fig. 13
Given the following conditions, what is the takeoff ground roll and V1 speed?
Pressure altitude ........................................................ 4,000 ft
Tempertaure (OAT) ........................................................... 0°C
Weight ................................................................... 15,500 lb
Wind component .................................................. 10 kts TW
Ice vanes .............................................................. Extended 2,900 feet, 106 knots. 4,250 feet, 102 knots. 2,700 feet, 107 knots.
Fig. 13
Given the following conditions, what is the takeoff distance over a 50-foot obstacle?
Pressure altitude ........................................................ 2,000 ft
Tempertaure (OAT) ....................................................... +15°C
Weight ................................................................... 16,600 lb
Wind component .......................................................... Calm
Ice vanes ............................................................. Retracted 3,400 feet. 3,700 feet. 4,200 feet.
Fig. 13
Given the following conditions, what is the takeoff ground roll and V1 speed?
Pressure altitude ........................................................ 3,000 ft
Tempertaure (OAT) ....................................................... -10°C
Weight ................................................................... 15,000 lb
Wind component .................................................... 8 kts TW
Ice vanes .............................................................. Extended 2,200 feet, 105 knots. 2,000 feet, 113 knots. 1,900 feet, 103 knots.
Fig. 13
Given the following conditions, what is the takeoff distance over a 50 foot obstacle?
Pressure altitude ........................................................ 6,000 ft
Tempertaure (OAT) ....................................................... +35°C
Weight ................................................................... 14,500 lb
Wind component .................................................. 10 kts HW
Ice vanes ............................................................. Retracted 4,150 feet. 4,550 feet. 2,600 feet.
Fig. 14
Given the following conditions, what is the accelerate-stop field length?
Pressure altitude ........................................................ 5,000 ft
Tempertaure (OAT) ....................................................... +20°C
Weight ................................................................... 15,000 lb
Wind component .................................................. 10 kts HW
Ice vanes ............................................................ Rectracted 6,300 feet. 4,700 feet. 4,300 feet.
Fig. 14
Given the following conditions, what is the accelerate-stop field length?
Pressure altitude ........................................................ 2,000 ft
Tempertaure (OAT) ....................................................... -15°C
Weight ................................................................... 16,000 lb
Wind component .................................................... 5 kts HW
Ice vanes .............................................................. Extended 3,750 feet. 4,600 feet. 4,250 feet.
Fig. 14
Given the following conditions, what is the accelerate-stop field length?
Pressure altitude ........................................................ 6,000 ft
Tempertaure (OAT) ....................................................... +10°C
Weight ................................................................... 16,600 lb
Wind component .................................................. 15 kts HW
Ice vanes ............................................................ Retracted 4,950 feet. 4,800 feet. 5,300 feet.
Fig. 15 - 16 - 17
What is the two-engine rate of climb after takeoff in climb configuration for Operating Conditions BE-21? 1,350 ft/min. 2,450 ft/min. 2,300 ft/min.
Fig. 15 - 16 - 17
What is the single-engine climb gradient after takeoff in climb configuration for Operating Conditions BE-22? 6.8 percent gradient. 7.5 percent gradient. 5.6 percent gradient.
Fig. 15 - 16 - 17
What is the two-engine rate of climb after takeoff in climb configuration for Operating Conditions BE-23? 1,500 ft/min. 2,600 ft/min. 2,490 ft/min.
Fig. 15 - 16 - 17
What is the two-engine rate of climb after takeoff in climb configuration for Operating Conditions BE-24? 2,100 ft/min. 2,400 ft/min. 1,500 ft/min.
Fig. 15 - 16 - 17
What is the single-engine rate of climb after takeoff in climb configuration for Operating Conditions BE-25? 385 ft/min. 780 ft/min. 665 ft/min.
Fig. 14
Given the following conditions, what is the accelerate-stop field length?
Pressure altitude ........................................................ 8,000 ft
Tempertaure (OAT) .......................................................... -5°C
Weight ................................................................... 14,000 lb
Wind component .................................................... 4 kts TW
Ice vanes .............................................................. Extended 4,500 feet. 4,800 feet. 5,300 feet.
Fig. 14
Given the following conditions, what is the accelerate-stop field length?
Pressure altitude ..................................................... Sea Level
Tempertaure (OAT) ....................................................... +30°C
Weight ................................................................... 13,500 lb
Wind component .................................................. 14 kts HW
Ice vanes .............................................................. Retracted 2,500 feet. 2,850 feet. 3,050 feet.
Fig.15 - 18
What are the time, fuel, and distance from the start of climb to cruise altitude for Operating Conditions BE-21? 10.0 minutes; 290 pounds; 35 NM. 10.0 minutes; 165 pounds; 30 NM. 11.5 minutes; 165 pounds; 30 NM.
Fig. 15 - 18
What are the time, fuel, and distance from the start of climb to cruise altitude for Operating Conditions BE-22? 12.0 minutes; 220 pounds; 40 NM. 11.0 minutes; 185 pounds; 37 NM. 10.5 minutes; 175 pounds; 32 NM.
Fig. 15 - 18
What are the time, fuel, and distance from the start of climb to cruise altitude for Operating Conditions BE-23? 13.0 minutes; 180 pounds; 35 NM. 14.0 minutes; 210 pounds; 40 NM. 15.0 minutes; 240 pounds; 46 NM.
Fig. 15 - 18
What are the time, fuel, and distance from the start of climb to cruise altitude for Operating Conditions BE-24? 12.0 minutes; 220 pounds; 45 NM. 9.0 minutes; 185 pounds; 38 NM. 10.0 minutes; 170 pounds; 30 NM.
Fig. 15 - 18
What are the time, fuel, and distance from the start of climb to cruise altitude for Operating Conditions BE-25? 11.5 minutes; 170 pounds; 31 NM. 8.0 minutes; 270 pounds; 28 NM. 12.5 minutes; 195 pounds; 38 NM.
Fig. 19 - 20
At what altitude is the service ceiling with one engine inoperative for Operating Conditions BE-26? 13,000 feet. 14,200 feet. 13,600 feet.
Fig. 19 - 20
Which statement is true regarding performance with one engine inoperative for Operating Conditions BE-27? Cimb rate at the MEA is more than 50 ft/min. Service ceiling is below the MEA. Bleed air OFF improves service ceiling by 3,000 feet.
Fig. 19 - 20
At what altitude is the service ceiling with one engine inoperative for Operating Conditions BE-28? 1,500 feet above the MEA. 10,400 feet. 11,800 feet.
Fig. 19 - 20
Which statement is true regarding performance with one engine inoperative for Operating Conditions BE-29? Service ceiling is more than 100 feet above the MEA. Bleed air must be OFF to obtain a rate of climb of 50 ft/min at the MEA. Climb is not possible at the MEA.
Fig. 19 - 20
At what altitude is the service ceiling with one engine inoperative for Operating Conditions BE-30? 9,600 feet. 13,200 feet. 2,100 feet above the MEA.
Fig. 21 to 25
What is the en route time of the cruise leg for Operating Conditions BE-31? 1 hour 11 minutes. 1 hour 17 minutes. 1 hour 19 minutes.
Fig. 21 to 25
What is the en route time of the cruise leg for Operating Conditions BE-32? 1 hour 13 minutes. 1 hour 15 minutes. 1 hour 20 minutes.
Fig. 21 to 25
What is the en route time of the cruise leg for Operating Conditions BE-33? 1 hour 50 minutes. 1 hour 36 minutes. 1 hour 46 minutes.
Fig. 21 to 25
What is the en route time of the cruise leg for Operating Conditions BE-34? 1 hour 6 minutes. 1 hour 3 minutes. 1 hour 11 minutes.
Fig. 21 to 25
What is the en route time of the cruise leg for Operating Conditions BE-35? 1 hour 6 minutes. 1 hour 8 minutes. 1 hour 10 minutes.
Fig. 21 to 25
What is the fuel consumption during the cruise leg for Operating Conditions BE-31? 812 pounds. 749 pounds. 870 pounds.
Fig. 21 to 25
What is the fuel consumption during the cruise leg for Operating Conditions BE-32? 1,028 pounds. 896 pounds. 977 pounds.
Fig. 21 to 25
What is the fuel consumption during the cruise leg for Operating Conditions BE-33? 1,165 pounds. 1,373 pounds. 976 pounds.
Fig. 21 to 25
What is the fuel consumption during the cruise leg for Operating Conditions BE-34? 668 pounds. 718 pounds. 737 pounds.
Fig. 21 to 25
What is the fuel consumption during the cruise leg for Operating Conditions BE-35? 900 pounds. 1,030 pounds. 954 pounds.
Fig. 26
What are the time and distance to descend from 18,000 feet to 2,500 feet? 10.3 minutes, 39 NM. 9.8 minutes, 33 NM. 10.0 minutes, 36 NM.
Fig. 26
What are the distance and fuel consumption to descend from 22,000 feet to 4,500 feet? 44 NAM, 117 pounds. 48 NAM, 112 pounds. 56 NAM, 125 pounds.
Fig. 26
What are the time and distance to descend from 16,500 feet to 3,500 feet? 9.3 minutes, 37 NAM. 9.1 minutes, 35 NAM. 8.7 minutes, 33 NAM.
Fig. 26
What are the distance and fuel consumption to descend from 13,500 feet to 1,500 feet? 30 NAM, 87 pounds. 29 NAM, 80 pounds. 38 NAM, 100 pounds.
Fig. 26
What are the time and distance to descend from 23,000 feet to 600 feet with an average 15-knot headwind? 14.2 minutes, 50 NAM. 14.6 minutes, 56 NAM. 14.9 minutes, 59 NAM.
Fig. 27 - 28
What is the landing distance over a 50-foot obstacle for Operating Conditions B-36? 1,900 feet. 1,625 feet. 950 feet.
Fig. 27 - 28
What are the approach speed and ground roll when landing under Operating Conditions B-36? 113 knots and 950 feet. 113 knots and 1,950 feet. 112 knots and 900 feet.
Fig. 27 - 28
What is the remaining runway length when stopped after landing over a 50- foot obstacle for Operating Conditions B-37? 2,500 feet. 2,000 feet. 2,600 feet.
Fig. 27 - 28
What are the approach speed and ground roll when landing under Operating Conditions B-37? 108 knots and 1,400 feet. 109 knots and 900 feet. 107 knots and 1,350 feet.
Fig. 27 - 28
What is the landing distance over a 50-foot obstacle for Operating Conditions B-38? 1,850 feet. 1,700 feet. 1,800 feet.
Fig. 27 - 28
What is the total runway used when touchdown is at the 1,000 foot marker for Operating Conditions B-38? 2,000 feet. 1,700 feet. 1,800 feet.
Fig. 27 - 28
What is the remaining runway length when stopped after landing over a 50- foot obstacle for Operating Conditions B-39? 2,300 feet. 2,400 feet. 2,500 feet.
Fig. 27 - 28
What are the approach speed and ground roll when landing under Operating Conditions B-39? 111 knots and 1,550 feet. 110 knots and 1,400 feet. 109 knots and 1,300 feet.
Fig. 27 - 28
What is the landing distance over a 50-foot obstacle for Operating Conditions B-40? 1,500 feet. 1,750 feet. 1,650 feet.
Fig. 45 - 46 - 47
What are V1 and Vr speeds for Operating Conditions A-1? V1 123.1 knots; Vr 125.2 knots. V1 120.5 knots; Vr 123.5 knots. V1 122.3 knots; Vr 124.1 knots.
Fig. 45 - 46 - 47
What are V1 and Vr speeds for Operating Conditions A-2? V1 129.7 knots; Vr 134.0 knots. V1 127.2 knots; Vr 133.2 knots. V1 127.4 knots; Vr 133.6 knots.
Fig. 45 - 46 - 47
What are V1 and Vr speeds for Operating Conditions A-3? V1 136.8 knots; Vr 141.8 knots. V1 134.8 knots; Vr 139.0 knots. V1 133.5 knots; Vr 141.0 knots.
Fig. 45 - 46 - 47
What are V1 and Vr speeds for Operating Conditions A-4? V1 128.0 knots; Vr 130.5 knots. V1 129.9 knots; Vr 133.4 knots. V1 128.6 knots; Vr 131.1 knots.
Fig. 45 - 46 - 47
What are V1 and Vr speeds for Operating Conditions A-5? V1 110.4 knots; Vr 110.9 knots. V1 109.6 knots; Vr 112.7 knots. V1 106.4 knots; Vr 106.4 knots.
Fig. 48 - 49 - 50
What is the ground distance covered during en route climb for Operating Conditions W-1? 104.0 NM. 99.2 NM. 109.7 NM.
Fig. 48 - 49 - 50
What is the ground distance covered during en route climb for Operating Conditions W-2? 85.8 NM. 87.8 NM. 79.4 NM.
Fig. 48 - 49 - 50
What is the ground distance covered during en route climb for Operating Conditions W-3? 86.4 NM. 84.2 NM. 85.1 NM.
Fig. 48 - 49 - 50
What is the ground distance covered during en route climb for Operating Conditions W-4? 58.4 NM. 61.4 NM. 60.3 NM.
Fig. 48 - 49 - 50
What is the ground distance covered during en route climb for Operating Conditions W-5? 68.0 NM. 73.9 NM. 66.4 NM.
Fig. 48 - 49 - 50
What is the aircraft weight at the top of climb for Operating Conditions W-1? 81,600 pounds. 81,400 pounds. 81,550 pounds.
What is the aircraft weight at the top of climb for Operating Conditions W-2?
(Refer to Figures 48, 49, and 50) 82,775 pounds. 83,650 pounds. 83,800 pounds.
What is the aircraft weight at the top of climb for Operating Conditions W-3?
(Refer to Figures 48, 49, and 50) 75,750 pounds. 75,900 pounds. 76,100 pounds.
What is the aircraft weight at the top of climb for Operating Conditions W-4?
(Refer to Figures 48, 49, and 50) 86,150 pounds. 86,260 pounds. 86,450 pounds.
What is the aircraft weight at the top of climb for Operating Conditions W-5? (Refer to Figures 48, 49, and 50) 89,900 pounds. 90,000 pounds. 90,100 pounds.
Fig. 51 - 52
What is the total time from starting to the alternate through completing the approach for Operating Conditions L-1? 30 minutes. 44 minutes. 29 minutes.
Fig. 51,52
What is the total time from starting to the alternate through completing the approach for Operating Conditions L-2? 36 minutes. 55 minutes. 40 minutes.
Fig. 51,52
What is the total time from starting to the alternate through completing the approach for Operating Conditions L-3? 1 hour. 1 hour 15 minutes. 1 hour 24 minutes.
Fig. 51,52
What is the total time from starting to the alternate through completing the approach for Operating Conditions L-4? 35 minutes. 19 minutes. 20 minutes.
Fig. 51,52
What is the total time from starting to the alternate through completing the approach for Operating Conditions L-5? 1 hour 3 minutes. 48 minutes. 55 minutes.
Fig. 51,52
What is the approximate landing weight for Operating Conditions L-1? 79,000 pounds. 83,600 pounds. 81,500 pounds.
Fig. 51,52
What is the approximate landing weight for Operating Conditions L-2? 65,200 pounds. 65,800 pounds. 69,600 pounds.
Fig. 51,52
What is the approximate landing weight for Operating Conditions L-3? 80,300 pounds. 85,400 pounds. 77,700 pounds.
Fig. 51,52
What is the approximate landing weight for Operating Conditions L-4? 73,200 pounds. 74,190 pounds. 73,500 pounds.
Fig. 51,52
What is the approximate landing weight for Operating Conditions L-5? 78,600 pounds. 77,000 pounds. 76,300 pounds.
What is the takeoff EPR for Operating Conditions R-1? (See Figures 53, 54, and 55) 2.04. 2.01. 2.035.
What is the takeoff EPR for Operating Conditions R-2? (See Figures 53, 54, and 55) 2.19. 2.18. 2.16.
What is the takeoff EPR for Operating Conditions R-3? (See Figures 53, 54, and 55) 2.01. 2.083. 2.04.
What is the takeoff EPR for Operating Conditions R-4? (See Figures 53, 54, and 55) 2.06. 2.105. 2.11.
What is the takeoff EPR for Operating Conditions R-5? (See Figures 53, 54, and 55) 1.98. 1.95. 1.96.
What is the takeoff safety speed for Operating Conditions R-1? (See figures 53, 54, and 55) 128 knots. 121 knots. 133 knots.
What is the rotation speed for Operating Conditions R-2? (See figures 53, 54, and 55) 147 knots. 152 knots. 146 knots.
What are V1, Vr, and V2 speeds for Operating Conditions R-3? (See figures 53, 54, and 55) 143, 143, and 147 knots. 138, 138, and 142 knots. 136, 138, and 143 knots.
What are critical engine failure and takeoff safety speeds for Operating Conditions R-4? (See figures 53, 54, and 55) 131 and 133 knots. 123 and 134 knots. 122 and 130 knots.
What are rotation and V2 bug speeds for Operating Conditions R-5? (See figures 53, 54, and 55) 138 and 143 knots. 136 and 138 knots. 134 and 141 knots.
What is the ground distance covered during en route climb for Operating Conditions V-1? (Refer to Figures 56, 57, and 58) 145 NM. 137 NM. 134 NM.
What is the ground distance covered during en route climb for Operating Conditions V-2? (Refer to Figures 56, 57, and 58) 84 NM. 65 NM. 69 NM.
What is the ground distance covered during en route climb for Operating Conditions V-3? (Refer to Figures 56, 57, and 58) 95 NM. 79 NM. 57 NM.
What is the ground distance covered during en route climb for Operating Conditions V-4? (Refer to Figures 56, 57, and 58) 63 NM. 53 NM. 65 NM.
What is the ground distance covered during en route climb for Operating Conditions V-5? (Refer to Figures 56, 57, and 58) 70 NM. 47 NM. 61 NM.
How much fuel is burned during en route climb for Operating Conditions V-1? (Refer to Figures 56, 57, and 58) 4,100 pounds. 3,600 pounds. 4,000 pounds.
How much fuel is burned during en route climb for Operating Conditions V-2? (Refer to Figures 56, 57, and 58) 2,250 pounds. 2,600 pounds. 2,400 pounds.
What is the aircraft weight at the top of climb for Operating Conditions V-3? (Refer to Figures 56, 57, and 58) 82,100 pounds. 82,500 pounds. 82,200 pounds.
What is the aircraft weight at the top of climb for Operating Conditions V-4? (Refer to Figures 56, 57, and 58) 102,900 pounds. 102,600 pounds. 103,100 pounds.
What is the aircraft weight at the top of climb for Operating Conditions V-5? (Refer to Figures 56, 57, and 58) 73,000 pounds. 72,900 pounds. 72,800 pounds.
What is the maximum climb EPR for Operating Conditions T-1? (See Figures 59 and 60) 1.82. 1.96. 2.04.
What is the maximum climb EPR for Operating Conditions T-2? (See Figures 59 and 60) 2.10. 1.99. 2.02.
What is the maximum climb EPR for Operating Conditions T-3? (See Figures 59 and 60) 2.11. 2.02. 1.90.
What is the maximum climb EPR for Operating Conditions T-4? (See Figures 59 and 60) 2.20. 2.07. 2.06.
What is the maximum climb EPR for Operating Conditions T-5? (See Figures 59 and 60) 2.00. 2.04. 1.96.
Fig. 61,62
What is the trip time for Operating Conditions X-1? 4 hours 5 minutes. 4 hours 15 minutes. 4 hours.
Fig. 61,62
What is the trip time for Operating Conditions X-2? 5 hours 5 minutes. 6 hours 15 minutes. 5 hours 55 minutes.
Fig. 61,62
What is the trip time for Operating Conditions X-3? 4 hours 15 minutes. 3 hours 40 minutes. 4 hours.
Fig. 61,62
What is the trip time for Operating Conditions X-4? 6 hours 50 minutes. 5 hours 45 minutes. 5 hours 30 minutes.
Fig. 61,62
What is the trip time for Operating Conditions X-5? 2 hours 55 minutes. 3 hours 10 minutes. 2 hours 50 minutes.
Fig. 61,62
What is the trip fuel for Operating Conditions X-1? 25,000 pounds. 26,000 pounds. 24,000 pounds.
Fig.61,62
What is the trip fuel for Operating Conditions X-2? 33,000 pounds. 28,000 pounds. 35,000 pounds.
Fig. 61,62
What is the trip fuel for Operating Conditions X-3? 36,000 pounds. 34,500 pounds. 33,000 pounds.
Fig. 61,62
What is the trip fuel for Operating Conditions X-4? 33,000 pounds. 31,500 pounds. 34,000 pounds.
Fig. 61,62
What is the trip fuel for Operating Conditions X-5? 15,000 pounds. 20,000 pounds. 19,000 pounds.
Fig. 63,64
What is the turbulent air penetration N1 power setting for Operating Conditions Q-1? 82.4 percent? 84.0 percent. 84.8 percent.
Fig. 63,64
What is the turbulent air penetration N1 power setting for Operating Conditions Q-2? 78.2 percent. 75.2 percent. 76.7 percent.
What is the turbulent air penetration N1 power setting for Operating Conditions Q-3? 77.8 percent. 82.6 percent. 84.2 percent.
Fig. 63,64
What is the turbulent air penetration N1 power setting for Operating Conditions Q-4? 76.8 percent. 75.4 percent. 74.0 percent.
Fig. 66,67
What is the trip time corrected for wind under Operating Conditions Z-1? 58.1 minutes. 51.9 minutes. 54.7 minutes.
Fig. 66,67
What is the trip time corrected for wind under Operating Conditions Z-2? 1 hour 35 minutes. 1 hour 52 minutes. 1 hour 46 minutes.
Fig. 66,67
What is the trip time corrected for wind under Operating Conditions Z-4? 48.3 minutes. 50.7 minutes. 51.3 minutes.
Fig. 66,67
What is the trip time corrected for wind under Operating Conditions Z-5? 1 hour 11 minutes. 56 minutes. 62 minutes.
Fig. 66,67
What is the estimated fuel consumption for Operating Conditions Z-1? 5,230 pounds. 5,970 pounds. 5,550 pounds.
Fig. 66,67
What is the estimated fuel consumption for Operating Conditions Z-2? 10,270 pounds. 9,660 pounds. 10,165 pounds.
Fig. 66,67
What is the estimated fuel consumption for Operating Conditions Z-3? 12,300 pounds. 11,300 pounds. 13,900 pounds.
Fig. 66,67
What is the estimated fuel consumption for Operating Conditions Z-4? 4,950 pounds. 5,380 pounds. 5,230 pounds.
Fig.66,67
What is the estimated fuel consumption for Operating Conditions Z-5? 6,250 pounds. 5,380 pounds. 7,120 pounds.
Fig, 68,69
What are the recommended IAS and EPR settings for holding under Operating Conditions O-1? 221 knots and 1.83 EPR. 223 knots and 2.01 EPR. 217 knots and 1.81 EPR.
Fig. 68,69
What are the recommended IAS and EPR settings for holding under Operating Conditions O-2? 210 knots and 1.57 EPR. 210 knots and 1.515 EPR. 210 knots and 1.45 EPR.
Fig, 68,69
What are the recommended IAS and EPR settings for holding under Operating Conditions O-3? 217 knots and 1.50 EPR. 215 knots and 1.44 EPR. 216 knots and 1.40 EPR.
Fig. 68,69
What are the recommended IAS and EPR settings for holding under Operating Conditions O-4? 223 knots and 1.33 EPR. 225 knots and 1.33 EPR. 220 knots and 1.28 EPR.
Fig. 68,69
What are the recommended IAS and EPR settings for holding under Operating Conditions O-5? 219 knots and 1.28 EPR. 214 knots and 1.26 EPR. 218 knots and 1.27 EPR.
Fig. 68,69
What is the approximate fuel consumed when holding under Operating Conditions O-1? 1,625 pounds. 1,950 pounds. 2,440 pounds.
Fig. 68,69
What is the approximate fuel consumed when holding under Operating Conditions O-2? 2,250 pounds. 2,500 pounds. 3,000 pounds.
Fig. 68,69
What is the approximate fuel consumed when holding under Operating Conditions O-3? 2,940 pounds. 2,520 pounds. 3,250 pounds.
Fig.68,69
What is the approximate fuel consumed when holding under Operating Conditions O-4? 2,870 pounds. 2,230 pounds. 1,440 pounds.
Fig. 68,69
What is the approximate fuel consumed when holding under Operating Conditions O-5? 2,950 pounds. 2,870 pounds. 2,400 pounds.
Fig. 70
How many minutes of dump time is required to reach a weight of 144,500 pounds?
Initial weight ........................................................ 180,500 lb
Zero fuel weight ................................................... 125,500 lb 13 minutes. 15 minutes. 16 minutes.
FigHow many minutes of dump time is required to reduce fuel load to 25,000 pounds?
Initial weight ........................................................ 179,500 lb
Zero fuel weight ................................................... 136,500 lb 10 minutes. 9 minutes. 8 minutes.
Fig.70
How many minutes of dump time is required to reach a weight of 151,500 pounds?
Initial weight ........................................................ 181,500 lb
Zero fuel weight ................................................... 126,000 lb 15 minutes. 14 minutes. 13 minutes.
Fig. 70
How many minutes of dump time is required to reduce fuel load to 16,000 pounds?
Initial weight ........................................................ 175,500 lb
Zero fuel weight ................................................... 138,000 lb 9 minutes. 10 minutes. 8 minutes.
Fig. 71,72
What is the approximate level-off pressure altitude after drift-down under Operating Conditions D-1? 19,400 feet. 18,000 feet. 20,200 feet.
Fig. 71,72
What is the approximate level-off pressure altitude after drift-down under Operating Conditions D-2? 14,700 feet. 17,500 feet. 18,300 feet.
Fig. 71,72
What is the approximate level-off pressure altitude after drift-down under Operating Conditions D-3? 22,200 feet. 19,800 feet. 21,600 feet.
Fig. 71,72
What is the approximate level-off pressure altitude after drift-down under Operating Conditions D-4? 27,900 feet. 22,200 feet. 24,400 feet.
Fig. 71,72
What is the approximate level-off pressure altitude after drift-down under Operating Conditions D-5? 8,800 feet. 9,600 feet. 13,000 feet.
Fig. 73,75
What is the go-around EPR for Operating Conditions L-1? 2.01 EPR. 2.03 EPR. 2.04 EPR.
What is the go-around EPR for Operating Conditions L-2? 2.115 EPR. 2.10 EPR. 2.06 EPR.
What is the go-around EPR for Operating Conditions L-3? 2.06 EPR. 2.07 EPR. 2.09 EPR.
What is the go-around EPR for Operating Conditions L-4? 2.056 EPR. 2.12 EPR. 2.096 EPR.
Fig. 73,75
What is the go-around EPR for Operating Conditions L 5? 2.00 EPR. 2.04 EPR. 2.05 EPR.
Fig. 73,74,75
What is Vref for Operating Conditions L-1? 143 knots. 144 knots. 145 knots.
Fig. 73,74,75
What is the reference speed for Operating Conditions L-2? 140 knots. 145 knots. 148 knots.
Fig. 73,74,75
What is Vref +20 for Operating Conditions L-3? 151 knots. 169 knots. 149 knots.
Fig. 73,74,75
What is Vref +10 for Operating Conditions L-4? 152 knots. 138 knots. 148 knots.
Fig. 73,74,75
What is the maneuvering speed for Operating Conditions L-5? 124 knots. 137 knots. 130 knots.
What is the maximum takeoff EPR for Operating Conditions G-1? (See Figures 81, 82, and 83) Engines 1 and 3, 2.22; engine 2, 2.16. Engines 1 and 3, 2.22; engine 2, 2.21. Engines 1 and 3, 2.15; engine 2, 2.09.
What is the maximum takeoff EPR for Operating Conditions G-2? (See Figures 81, 82, and 83) Engines 1 and 3, 2.15; engine 2, 2.16. Engines 1 and 3, 2.18; engine 2, 2.13. Engines 1 and 3, 2.14; engine 2, 2.11.
What is the maximum takeoff EPR for Operating Conditions G-3? (See Figures 81, 82, and 83) Engines 1 and 3, 2.08; engine 2, 2.05. Engines 1 and 3, 2.14; engine 2, 2.10. Engines 1 and 3, 2.18; engine 2, 2.07.
What is the maximum takeoff EPR for Operating Conditions G-4? (See Figures 81, 82, and 83) Engines 1 and 3, 2.23; engine 2, 2.21. Engines 1 and 3, 2.26; engine 2, 2.25. Engines 1 and 3, 2.24; engine 2, 2.24.
What is the maximum takeoff EPR for Operating Conditions G-5? (See Figures 81, 82, and 83) Engines 1 and 3, 2.27; engine 2, 2.18. Engines 1 and 3, 2.16; engine 2, 2.14. Engines 1 and 3, 2.23; engine 2, 2.22.
What is the takeoff safety speed for Operating Conditions G-1? (See Figures 81, 82, and 83) 122 knots. 137 knots. 133 knots.
What is the rotation speed for Operating Conditions G-2? (See Figures 81, 82, and 83) 150 knots. 154 knots. 155 knots.
What are V1, Vr and V2 speeds for Operating Conditions G-3? (See figures 81, 82, and 83) 134, 134, and 145 knots. 134, 139, and 145 knots. 132, 132, and 145 knots.
What are V1 and V2 speeds for Operating Conditions G-4? (See figures 81, 82, and 83) 133 and 145 knots. 127 and 141 knots. 132 and 146 knots.
What are rotation and V2 bug speeds for Operating Conditions G-5? (See figures 81, 82, and 83) 120 and 134 knots. 119 and 135 knots. 135 and 135 knots.
Fig. 84,85
What are the recommended IAS and EPR settings for holding under Operating Conditions H-1? 264 knots and 1.80 EPR. 259 knots and 1.73 EPR. 261 knots and 1.81 EPR.
Fig. 84,85
What are the recommended IAS and EPR settings for holding under Operating Conditions H-2? 257 knots and 1.60 EPR. 258 knots and 1.66 EPR. 253 knots and 1.57 EPR.
Fig. 84,85
What are the recommended IAS and EPR settings for holding under Operating Conditions H-3? 226 knots and 1.30 EPR. 230 knots and 1.31 EPR. 234 knots and 1.32 EPR.
Fig. 84,85
What are the recommended IAS and EPR settings for holding under Operating Conditions H-4? 219 knots and 1.44 EPR. 216 knots and 1.42 EPR. 220 knots and 1.63 EPR.
Fig. 84,85
What are the recommended IAS and EPR settings for holding under Operating Conditions H-5? 245 knots andn 1.65 EPR. 237 knots andn 1.61 EPR. 249 knots andn 1.67 EPR.
Fig. 84,85
What is the approximate fuel consumed when holding under Operating Conditions H-1? 3,500 pounds. 4,680 pounds. 2,630 pounds.
FIG. 84,85
What is the approximate fuel consumed when holding under Operating Conditions H-2? 5,100 pounds. 3,400 pounds. 5,250 pounds.
Fig. 84,85
What is the approximate fuel consumed when holding under Operating Conditions H-3? 3,090 pounds. 6,950 pounds. 6,680 pounds.
Fig. 84,85
What is the approximate fuel consumed when holding under Operating Conditions H-4? 3,190 pounds. 3,050 pounds. 2,550 pounds.
Fig. 84,85
What is the approximate fuel consumed when holding under Operating Conditions H-5? 3,170 pounds. 7,380 pounds. 5,540 pounds.
Fig. 86,87
What are descent time and distance under Operating Conditions S-1? 24 minutes, 118 NM. 26 minutes, 125 NM. 25 minutes, 118 NM.
Fig. 86,87
What are descent fuel and distance under Operating Conditions S-2? 1,440 pounds, 104 NM. 1,500 pounds, 118 NM. 1,400 pounds, 98 NM.
Fig. 86,87
What are descent fuel and distance under Operating Conditions S-3? 1,490 pounds, 118 NM. 1,440 pounds, 110 NM. 1,550 pounds, 127 NM.
Fig. 86,87
What are descent time and distance under Operating Conditions S-4? 22 minutes, 110 NM. 21 minutes, 113 NM. 24 minutes, 129 NM.
Fig. 86,87
What are descent fuel and distance under Operating Conditions S-5? 1,420 pounds, 97 NAM. 1,440 pounds, 102 NAM. 1,390 pounds, 92 NAM.
Fig. 88,89
Which conditions will result in the shortest landing distance at a weight of 132,500 pounds? Dry runway using brakes and reversers. Dry runway using brakes and spoilers. Wet runway using brakes, spoilers and reversers.
Fig. 88
How much longer is the dry runway landing distance using brakes only compared to using brakes and reversers at 114,000 pounds gross weight? 1,150 feet. 500 feet. 300 feet.
Figure 88
How many feet will remain after landing on a 7,200-foot dry runway with spoilers inoperative at 118,000 pounds gross weight? 4,200 feet. 4,500 feet. 4,750 feet.
Figure 88
What is the maximum landing weight which will permit stopping 2,000 feet short of the end of a 5,400-foot dry runway with reversers and spoilers inoperative? 117,500 pounds. 136,500 pounds. 139,500 pounds.
Fig. 89
Which of the following configurations will result in the shortest landing distance over a 50-foot obstacle to a wet runway? Brakes and spoilers at 122,500 pounds gross weight. Brakes and reversers at 124,000 pounds gross weight. Brakes, spoilers, and reversers at 131,000 pounds gross weight.
How many feet will remain after landing on a 6,000-foot wet runway with reversers inoperative at 122,000 pounds gross weight? 2,200 feet. 2,750 feet. 3,150 feet.
Fig. 90
Which configuration will result in a landing distance of 5,900 feet over a 50 foot obstacle to an icy runway? Use of three reversers at 131,000 pounds gross weight. Use of brakes and spoilers at 125,000 pounds gross weight. Use of three reversers at 133,000 pounds gross weight.
Fig. 90
What is the transition distance when landing on an icy runway at a gross weight of 134,000 pounds? 400 feet. 950 feet. 1,350 feet.
Fig. 90
What is the maximum landing weight which will permit stopping 700 feet short of the end of a 5,200-foot icy runway? 124,000 pounds. 137,000 pounds. 108,000 pounds.
Fig. 90
What is the landing distance on an icy runway with reversers inoperative at a landing weight of 125,000 pounds? 4,500 feet. 4,750 feet. 5,800 feet.
Fig. 91
How much will landing distance be reduced by using 15° of flaps rather than 0° flaps at a landing weight of 119,000 pounds? 500 feet. 800 feet. 2,700 feet.
Fig. 91
What is the ground roll when landing with 15° of flaps at a landing weight of 122,000 pounds? 1,750 feet. 2,200 feet. 2,750 feet.
Fig. 91,92
What approach speed and ground roll will be needed when landing at a weight of 140,000 pounds if flaps are not used? 138 knots and 3,900 feet. 153 knots and 2,900 feet. 183 knots and 2,900 feet.
Fig. 91
How much more runway will be used to land with 0° flaps rather than 15° of flaps at a landing weight of 126,000 pounds? 900 feet. 1,800 feet. 2,700 feet.
Fig. 91,92
What approach speed and landing distance will be needed when landing at a weight of 140,000 pounds with 15° of flaps? 123 knots and 3,050 feet. 138 knots and 3,050 feet. 153 knots and 2,050 feet.
Fig. 92
What is the maximum charted indicated airspeed while maintaining a 3° glide slope at a weight of 140,000 pounds? 127 knots. 149 knots. 156 knots.
Fig.92
What is the thrust required to maintain a 3° glide slope at 140,000 pounds, with gear down, flaps 30°, and an airspeed of Vref +30 knots? 13,300 pounds. 16,200 pounds. 17,700 pounds.
Fig. 92
What thrust is required to maintain level flight at 140,000 pounds, with gear up, flaps 25°, and an airspeed of 172 knots? 13,700 pounds. 18,600 pounds. 22,000 pounds.
Fig. 92
What thrust is required to maintain level flight at 140,000 pounds, with gear down, flaps 25°, and an airspeed of 162 knots? 17,400 pounds. 19,500 pounds. 22,200 pounds.
Fig. 92
What thrust is required to maintain level flight at 140,000 pounds, with gear down, flaps 25°, and an airspeed of 145 knots? 16,500 pounds. 18,100 pounds. 18,500 pounds.
Fig. 92
What is the change of total drag for a 140,000-pound airplane when configuration is changed from flaps 30°, gear down, to flaps 0°, gear up, at a constant airspeed of 160 knots? 13,500 pounds. 13,300 pounds. 15,300 pounds.
Fig. 93
What is the maximum charted indicated airspeed while maintaining a 3° glide slope at a weight of 110,000 pounds? 136 knots. 132 knots. 139 knots.
Fig. 93
What is the thrust required to maintain a 3° glide slope at 110,000 pounds, with gear down, flaps 30°, and an airspeed of Vref +20 knots? 9,800 pounds. 11,200 pounds. 17,000 pounds.
Fig. 93
What thrust is required to maintain level flight at 110,000 pounds, with gear down, flaps 40°, and an airspeed of 118 knots? 17,000 pounds. 20,800 pounds. 22,300 pounds.
Fig. 93
What thrust is required to maintain level flight at 110,000 pounds, with gear up, flaps 25°, and an airspeed of 152 knots? 14,500 pounds. 15,900 pounds. 16,700 pounds.
The maximum speed during takeoff that the pilot may abort the takeoff and stop the airplane within the accelerate-stop distance is V2. Vef. V1.
The minimum speed during takeoff, following a failure of the critical engine at Vef, at which the pilot may continue the takeoff and achieve the required height above the takeoff surface within the takeoff distance is indicated by
symbol V2min. V1. Vlof.
The symbol for the speed at which the critical engine is assumed to fail during takeoff is V2. V1. Vef.
Fig. 103
What CAS should be used to maintain the fixed TAS at the proposed altitude? 157 knots. 167 knots. 172 knots.
(Refer to Figures 115, 116, and 117.)
Due to traffic, LAX Center radar vectored PTL 130 to TRM, then cleared the flight to PHX via J169 BLH, direct to Arlin Intersection. What approximate indicated MAch should be maintained to arrive over the BLH VORTAC 8 minutes after passing TRM VORTAC? .84 Mach. .82 Mach. .86 Mach.
A definition of the term "viscous hydroplanning" is where the airplane rides on standing water. a film of moisture covers the painted or rubber-coated portion of the runway. the tires of the airplane are actually riding on a mixture of steam and melted rubber.
Which term describes the hydroplanning which occurs when an airplane's tire is effectively held off a smooth runway surface by steam generated by friction? Reverted rubber hydroplanning. Dynamic hydroplanning. Viscous hydroplanning.
At what minimum speed (rounded off) could dynamic hydroplanning occur on main tires having a pressure of 121 psi? 90 knots. 96 knots. 110 knots.
At what minimum speed will dynamic hydroplanning begin if a tire has an air pressure of 70 psi? 85 knots. 80 knots. 75 knots.
What is the best method of speed reduction if hydroplanning is experienced on landing? Apply full main wheel braking only. Apply nosewheel and main wheel braking alternately and abruptly. Apply aerodynamic braking to the fullest advantage.
Compared to dynamic hydroplanning, at what speed does viscous hydroplanning occur when landing on a smooth, wet runway? At approximately 2.0 times the speed that dynamic hydroplannin occurs. At a lower speed than dynamic hydroplanning. At the same speed as dynamic hydroplanning.
What effect, if any, will landing at a higher-than-recommended touchdown speed have on hydroplanning? No effect on hydroplanning, but increases landing roll. Reduces hydroplanning potential if heavy braking is applied. Increases hydroplanning potential regardless of braking.
Which place in the turbojet engine is subjected to the highest temperature? Compressor discharge. Fuel spray nozzles. Turbine inlet.
What effect would a change in ambient temperature of air density have on gas-turbine-engine performance? As air density decreases, thrust increases. As temperature increases, thrust increases. As temperature increases, thrust decreases.
The most important restriction to the operation of turbojet or turboprop engines is limiting compressor speed. limiting exhaust gas temperature. limiting torque.
An outside air pressure decreases, thrust output will increase due to greater efficiency of jet aircraft in thin air. remain the same since compression of inlet air will compensate for any decrease in air pressure. decrease due to higher density altitude.
What effect will an increase in altitude have upon the available equivalent shaft horsepower (ESHP) of a turboprop engine? Lower air density and engine mass flow will cause a decrease in power. Higher propeller efficiency will cause an increase in usable power (ESHP) and thrust. Power will remain the same but propeller efficiency will decrease.
What effect, if any, does high ambient temperature have upon the thrust output of a turbine engine? Thrust will be reduced due to the decrease in air density. Thrust will remain the same, but turbine temperature will be higher. Thrust will be higher because more heat energy is extracted from the hotter air.
What characterizes a transient compressor stall? Loud, steady roar accompanied by heavy shuddering. Sudden loss of thrust accompanied by a loud whine. Intermittent "bang", as backfires and flow reversals take place.
What indicates that a compressor stall has developed and become steady? Strong vibrations and loud roar. Occasional loud "bang" and low reversal. Completes loss of power with severe reduction in airspeed.
Which type of compressor stall has the greatest potential for severe engine damage? Intermittent "backfire" stall. Transient "backfire" stall. Steady, continuous flow reversal stall.
What recovery would be appropriate in the event of compressor stall? Reduce fuel flow, reduce angle of attack, and increase airspeed. Advance throttle, lower angle of attack, and reduce airspeed. Reduce throttle, reduce airspeed, and increase angle of attack.
Under normal operating conditions, which combination of MAP and RPM produce the most severe wear, fatigue, and damage to high performance reciprocating engines? High RPM and low MAP. Low RPM and high MAP. High RPM and high MAP.
What effect does high relative humidity have upon the maximum power output of modern aircraft engines? Neither turbojet nor reciprocating engines are affected. Reciprocating engines will experience a significant loss of BHP. Turbojet engines will experience a significant loss of thrust.
Equivalent shaft horsepower (ESHP) of a turbo-prop engine is a measure of turbine inlet temperature. shaft horsepower and jet thrust. propeller thrust only.
Minimum specific fuel consumption of the turbo-prop engine is normally available in which altitude range? 10,000 feet to 25,000 feet. 25,000 feet to the tropopause. The tropopause to 45,000 feet.
Where is the critical altitude of a supercharged reciprocating engine? The highest altitude at which a desired manifold pressure can be obtained. Highest altitude where the mixture can be leaned to best power ratio. The altitude at which maximum allowable BMEP can be obtained.
What is controlled by the waste gas of a turbo-charged reciprocating engine? Supercharger gear ratio. Exhaust gas discharge. Throttle opening.
How should thrust reversers be applied to reduce landing distance for turbojet aircraft? Immediately after ground contact. Immediately prior to touchdown. After applying maximum wheel braking.
Which condition reduces the required runway for takeoff? Higher-than-recommended airspeed before rotation. Lower-than-standard air density. Increased headwind component.
Which performance factor decreases as airplane gross weight increases, for a given runway? Critical engine failure speed. Rotation speed. Accelerate-stop distance.
Maximum range performance of a turbojet aircraft is obtained by which procedure as aircraft weight reduces? Increasing speed or altitude. Increasing altitude or decreasing speed. Increasing speed or decreasing altitude.
Which procedure produces the minimum fuel consumption for a given leg of the cruise flight? Increase speed for a headwind. Increase speed for a tailwind. Increase altitude for a headwind, decrease altitude for a tailwind.
How should reverse thrust propellers be used during landing for maximum effectiveness in stopping? Gradually increase reverse power to maximum as rollout speed decreases. Use maximum reverse power as soon as possible after touchdown. Select reverse-pitch after landing and use idle power setting of the engines.
What effect does an uphill runway slope have upon takeoff performance? Increases takeoff distance. Decreases takeoff speed. Decreases takeoff distance.
Under which condition during the landing roll are the main wheel brakes at maximum effectiveness? When wing lift has been reduced. At high groundspeeds. When the wheels are locked and skidding.
Which condition has the effect of reducing critical engine failure speed? Slush on the runway or inoperative antiskid. Low gross weight. High density altitude.
What action is appropriate when encountering the first ripple of reported clear air turbulence (CAT)? Extend flaps to decrease wing loading. Extend gear to provide more drag and increase stability. Adjust airspeed to that recommended for rough air.
If severe turbulence is encountered, which procedure is recommended? Maintain a constant altitude. Maintain a constant attitude. Maintain constant airspeed and altitude.
Which is the definition of V2 speed? Takeoff decision speed. Takeoff safety speed. Minimum takeoff speed.
What is the correct symbol for minimum unstick speed? Vmu. Vmd. Vfc.
Which is the correct symbol for design cruising speed? Vc. Vs. Vma.
Which is the correct symbol for the minimum steady-flight speed or stalling speed in the landing configuration? Vs. Vs1. Vso.
Which is correct symbol for the stalling speed or the minimum steady flight speed at which the airplane is controllable? Vso. Vs. Vs1.
What is the name of a plane beyond the end of a runway which does not contain obstructions and can be considered when calculating takeoff performance of turbine-powered aircraft? Clearway. Stopway. Obstruction clearance plane.
What is an area identified by the term "stopway"? An area, at least the same width as the runway, capable of supporting an airplane during a normal takeoff. An area designated for use in decelerating an aborted takeoff. An area, not as wide as the runway, capable of supporting an airplane during a normal takeoff.
Which operational requirement must be observed by a commercial operator when ferrying a large, three-engine, turbojet-powered airplane from one facility to another to repair an inoperative engine? The computed takeoff distance to reach V1 must not exceed 70 percent of the effective runway length. The existing and forecast weather for departure, en route, and approach must be VFR. No passengers may be carried.
A commercial operator plans to ferry a large, four-engine, reciprocatingengine- powered airplane from one facility to another to repair an inoperative engine. Which is an operational requirement for the three-engine flight? The gross weight at takeoff may not exceed 75 percent of the maximum certificated gross weight. Weather conditions at the takeoff and destination airports must be VFR. The computed takeoff distance to reach V1 must not exceed 70 percent of the effective runway length.
Which operational requirement must be observed when ferrying an air carrier airplane when one of its three turbine engines is inoperative? The weather conditions at takeoff and destination must be VFR. The flight cannot be conducted between official sunset and official sunrise. Weather conditions must exceed the basic VFR minimums for the entire route, including takeoff and landing.
Fig.94,95,96
What is the ETE from Chicago Midway Airport to Greater Buffalo Int'l? 2 hours 12 minutes. 2 hours 15 minutes. 2 hours 18 minutes.
Fig. 94,95,96
What are the fuel requirements from Chicago Midway Airport to the Greater Buffalo Int'l? 2,224 pounds. 1,987 pounds. 1,454 pounds.
Fig. 94,95,96
What TAS should be maintained to arrive over CRL VORTAC 42 minutes after level-off? 166 knots. 168 knots. 171 knots.
Fig.98,100,102
What is the ETE from DFW Int'l to IAH? 1 hour 2 minutes. 1 hour 4 minutes. 1 hour 6 minutes.
Fig.98-100/102
What is the total fuel required from DFW Int'l to IAH? 1,555 pounds. 1,863 pounds. 1,941 pounds.
Fig.98-100/102
Determine the TAS required to arrive at CUGAR, 31 minutes after level-off? 269 knots. 264 knots. 258 knots.
Which operational requirement must be observed when ferrying a large, turbine-engine-powered airplane when one of its engines is inoperative? The weather conditions at takeoff and destination must be VFR. Weather conditions must exceed the basic VFR minimums for the entire route, including takeoff and landing. The flight cannot be conducted between official sunset and sunrise.
When a turbine-engine-powered airplane is to be ferried to another base for repair of an inoperative engine, which operational requirement must be observed? Only the required flight crewmembers may be on board the airplane. The existing and forecast weather for departure, en route, and approach must be VFR. No passengers except authorized maintenance personnel may be carried.
Fig. 98,100,102
Determine the TAS required to arrive at CUGAR, 29 minutes after level-off? 285 knots. 290 knots. 295 knots.
Fig. 103,104,105,106
Estimate the total fuel required to be on the aircraft, prior to taxi at Tucson Int'l. 2,223 pounds. 2,327 pounds. 2,447 pounds.
Fig. 103,104,105,106
Determine the ETE for the flight from Tucson Int'l to Los Angeles Int'l. 2 hours 10 minutes. 2 hours 15 minutes. 2 hours 19 minutes.
(Refer to Figures 115, 116, 117, 118, and 118C)
What is the total fuel required at .78 Mach? 22,140 pounds. 22,556 pounds. 22,972 pounds.
(Refer to Figures 115, 116, 117, 118, and 118C)
What is the specific range in nautical miles per 1,000 pounds of fuel from level-off to the ARLIN Intersection using .78 Mach? 46.1 NAM/1,000 pounds. 48.2 NAM/1,000 pounds. 50.0 NAM/1,000 pounds.
(Refer to Figures 115, 116, 117, 118, and 118C)
What is the ETE at .80 Mach? 1 hour 02 minutes. 1 hour 04 minutes. 1 hour 07 minutes.
(Refer to Figures 115, 116, 117, 118, and 118C)
What is the total fuel required at .80 Mach? 22,836 pounds. 22,420 pounds. 22,256 pounds.
(Refer to Figures 115, 116, 117, 118, and 118C)
What approximate indicated Mach should be maintained to arrive over the BZA VORTAC 6 minutes after passing IPL VORTAC? .73 Mach. .74 Mach. .715 Mach.
(Refer to Figures 107, 115, 116, 117, 118, and 118C)
What is the ETE at .82 Mach? 1 hour 05 minutes. 1 hour 07 minutes. 1 hour 03 minutes.
(Refer to Figures 115, 116, 117, 118, and 118C)
What is the total fuel required at .82 Mach? 22,420 pounds. 22,284 pounds. 22,700 pounds.
Fig. 119 to 122
What is the ETE from BUF to ORD using .78 Mach? 1 hour 09 minutes. 1 hour 07 minutes. 1 hour 05 minutes.
Fig. 119 to 122
What is the total fuel required for the flight from BUF to ORD using .78 Mach? 19,033 pounds. 21,739 pounds. 22,189 pounds.
Fig. 119 to 122
What is the specific range in nautical miles per 1,000 pounds of fuel from level-off to start of descent using .78 Mach? 48.8 NAM/1000. 52.5 NAM/1000. 55.9 NAM/1000.
Fig. 119 to 122
What is the ETE from BUF to ORD using .80 Mach? 1 hour 01 minutes. 1 hour 04 minutes. 1 hour 08 minutes.
Fig. 119 to 122
What is the total fuel required for the flight from BUF to ORD using .80 Mach? 19,388 pounds. 22,094 pounds. 21,644 pounds.
(Refer to Figures 158, 159, 160, 160A, and 161)
The required amount of fuel (in pounds) to be on N711JB, prior to taxi, is 5,993 pounds. 6,408 pounds. 6,641 pounds.
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