5863371
Description
Quiz by tsampikos pompou, updated more than 1 year ago
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Created by tsampikos pompou
almost 8 years ago
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Question 1
Question
52 If an aircraft is overloaded by 90 lbs (48 kgs),how much fuel has to be removed so that the aircraft loading will be within limits?
Answer
-
O '15 USG.
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O '12 USG.
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O '6 USG.
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O '9 USG.
Question 2
Question
53 What is the maximum baggage weight that can be loaded on the aeroplane so that the center of gravity remains within limits?(Fig FPP07)
Empty Weight = 1350 lb moment(/1000) = 51,5., Pilot and front passengers = 250 lb, Rear Passengers =400lbs, Fuel = (30
Answer
-
O '105 Ib.
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O '120 Ib.
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O '90 Ib.
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O '751b.
Question 3
Question
54 calculate the moment/1.000 of the following aircraft and check if it is loaded within the CG envelope limits.(Fig FPP07)], Βάρος κενό/Empty Weight = 1350 lb ροπή/moment(/1000) = 51,5. Πιλότος και επιβάτης εμπρός/Pilot and front passengers = 310 lb. Επιβάτ
Answer
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O '83.0 within limits.
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O '78.2. out of the CG envelope.
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O '88.3. within limits.
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O '80,2. out of the CG envelope.
Question 4
Question
55 What is the maximum amount of fuel which can be loaded on the aeroplane before take off, so that the total moment remains within the envelope limits? (Fig FPP07)]. Βάρος κενό/ Empty Weight = 1350 lb ροπή/moment(/1000) = 51,5. Πιλότος και επιβάτης εμπρός/P
Answer
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O '40 USG.
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O '34 USG.
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O '24 USG.
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O '46 USG.
Question 5
Question
56 Calculate the total moment and check if it is within the envelope limits. (Fig FPP07)]. Βάρος κενό/Empty Weight = 1350 lb ροπή/moment(/1000) = 51,5. Πιλότος και επιβάτης εμπρός/Pilot and front passengers = 340 lb. Επιβάτες πίσω/Rear Passengers = 310lbs.
Answer
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O '77,7 Ib-inches.
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O '69,9 Ib-inches.
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O '73,9Ib-inches.
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O '38,7Ib-inches.
Question 6
Question
57 Calculate the CG position and check if it is located within the envelope limits.(Fig FPP07)]. Βάρος κενό/Empty Weight = 1350 lb ροπή/moment(/1000) = 51,5. Πιλότος και επιβάτης εμπρός/Pilot and front passengers = 380 lb. Αποσκευές/Baggage = 45 lb. Καύσιμο/
Answer
-
O within limits, normal category.
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O within limits, utility category.
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O out of the CG envelope, to the left of the diagram.
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O out of the CG envelope ,to the right of the diagram.]
Question 7
Question
61 The Service Ceiling is the pressure altitude where :
Answer
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O the rate of climb reaches a specified value,
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O the rate of climb is zero
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O the rate of climb is 100fpm.
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O the a/c flies more efficient.
Question 8
Question
67 For a given aircraft mass, the climb gradient:
Answer
-
O decreases if flap angle increases, and if temperature increases.
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O increases if flap angle increases, and if temperature decreases.
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O decreases if flap angle increases, and if temperature decreases.
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O increases if flap angle increases, and if temperature increases.
Question 9
Question
74 When an aircraft reaches its service ceiling :
Answer
-
O it will have a small positive rate of climb
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O the excess power will be zero
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O the rate of climb will be zero
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O power required will decrease.
Question 10
Question
79 For a given aircraft mass, as altitude increases, the minimum total drag will;
Answer
-
O remain the same and the Vmd will remain the same .
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O decrease, and the Vmd will decrease
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O increase, and the Vmd will increase
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O remain the same and the Vmd will be diminished.
Question 11
Question
80 The maximum speed that can be achieved in level flight, will occur:
Answer
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O when the drag is equal to the maximum thrust available,
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O when the drag is a minimum
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O when CL / CD is a minimum
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O when CD is a minimum
Question 12
Question
102 Given that the regulations applied and control requirement is met, the speed at the 50 ft. screen must not be less than :
Answer
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O 30% above the stalling speed with landing flap.
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O 20% above the stalling speed with landing flap
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O 30% above the stalling speed with flaps up
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O stall speed.
Question 13
Question
109 In comparison to the true airspeed in still air conditions, the TAS for the best range in a strong tailwind will be:
Answer
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O slightlyO the same. lower.
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O the same.
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O slightly higher.
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O significantly lower, proportional to the tailwind component.
Question 14
Question
110 Consult Fig.4. Refering to this graph, the flight for maximum range in a piston engined aircraft is achieved by flying:
Answer
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O at that speed which provides the minimum power/ airspeed ratio.
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O significantly higher than the minimum drag speed (Vmd).
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O at the lowest density altitude environment that is safely possible.
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O at the same speed which provides the maximum power/airspeed ratio.
Question 15
Question
114 (Refer to Fig.8). What is the effect of a temperature increase from -4?C to +10°C on the density altitude if the pressure altitude remains at 5,000 feet?
Answer
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O 1,650-foot increase.
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O 1,000-foot increase.
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O 1,300-foot increase.
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O 1950-foot increase.
Question 16
Question
115 (Refer to Fig.8). What is the effect of a temperature increase from +4?C to -15°C on the density altitude if the pressure altitude remains at 10,000 feet?
Answer
-
O 2,100-foot decrease.
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O 1,800-foot increase.
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O 1,500-foot decrease.
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O 1,000-foot increase.
Question 17
Question
116 (Refer to Fig.8). Determine the pres¬sure altitude with an indicated altitude of 1,380 feet MSL with an altimeter setting of 28.22" at standard temperature.
Answer
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O 3,010 feet MSL.
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O 1,250 feet MSL.
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O 1,373 feet MSL.
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O 2500 feet MSL.
Question 18
Question
117 (Refer to Fig.8). Determine the pres¬sure altitude with an indicated altitude of 1,820 feet MSL with an altimeter setting of 30.58" at standard temperature.
Answer
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O 1,200 feet MSL.
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O 2,440 feet MSL.
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O 2000 feet MSL.
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O none of them.
Question 19
Question
118 (Refer to Fig.8). Determine the density altitude for these conditions:
Altimeter setting...................................................29.25"
Runway temperature...........................................+27°C
Airport elevation......................................5,250 ft MSL
Answer
-
O 8,500 feet MSL.
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O 4,600 feet MSL.
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O 5,877 feet MSL.
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O 6000 feet MSL.
Question 20
Question
119 (Refer to Fig.8). Determine the density altitude for these conditions:
Altimeter setting...................................................30.15"
Runway temperature........................................... -1°C
Airport elevation......................................4,610 ft MSL
Answer
-
O 3,500 feet MSL.
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O 4,900 feet MSL.
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O 4,000 feet MSL.
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O 3,000 feet MSL.
Question 21
Question
120 (Refer to figure 8.) Determine the pressure altitude at an airport that is 4,563 feet MSL with an altimeter set¬ting of 29.96".
Answer
-
O 4,527 feet MSL.
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O 4,236 feet MSL.
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O 3,640 feet MSL.
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O 4,600 feet MSL.
Question 22
Question
121 (Refer to figure 8.) What is the effect of a temperature increase from -1?C to 10°C on the density altitude if the pressure altitude remains at 3,000 feet MSL?
Answer
-
O 1,300-foot increase.
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O 900-foot increase.
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O 1,100-foot decrease.
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O 1300-foot decrease.
Question 23
Question
122 (Refer to figure 8.) Determine the pressure altitude at an airport that is 1,386 feet MSL with an altimeter setting of 29.97".
Answer
-
O 1,341 feet MSL.
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O 1,451 feet MSL.
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O 1,562 feet MSL.
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O 1,212 feet MSL.
Question 24
Question
123 (Refer to figure 8.) Determine the density altitude for these conditions:
Altimeter setting...................................................30.35"
Runway temperature........................................... -4°C
Airport elevation......................................3,894 ft MSL
Answer
-
O 2,000 feet MSL,
-
O 1,500 feet MSL
-
O 2,900 feet MSL,
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O 3,500 feet MSL
Question 25
Question
124 (Refer to Fig.9) What is the headwind component for a landing on Runway 18 if the tower reports the wind as 220° at 30 knots?
Answer
-
O 23knots.
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O 19 knots.
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O 30 knots.
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O 34 knots.
Question 26
Question
125 (Refer to Fig.9) Determine the maxi¬mum wind velocity for a 45° crosswind if the maxi¬mum crosswind component for the airplane is 25 knots.
Answer
-
O 35 knots.
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O 18 knots.
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O 25 knots.
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O 29 knots.
Question 27
Question
126 (Refer to Fig.9) Determine the maxi¬mum wind velocity for a 50° crosswind if the maxi¬mum crosswind component for the airplane is 23 knots.
Answer
-
O 20 knots.
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O 28 knots.
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O 30 knots.
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O 32 knots.
Question 28
Question
127 (Refer to Fig.9) What is the maximum wind velocity for a 30? crosswind if the maximum crosswind component for the airplane is 12 knots?
Answer
-
O 23 knots.
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O 16 knots.
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O 20 knots.
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O 25 knots.
Question 29
Question
128 (Refer to Fig.9) What is the maximum wind velocity for a 35 ? crosswind if the maximum crosswind component for the airplane is 17 knots?
Answer
-
O 25 knots.
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O 20 knots.
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O 15 knots.
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O 17 knots.
Question 30
Question
129 (Refer to Fig.9) With a reported wind of north at 20 knots, which runway (6, 29, or 32) is acceptable for use for an airplane with a 13-knot maxi¬mum crosswind component?
Answer
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O Runway 32.
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O Runway 6.
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O Runway 29.
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O Out of limits.
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