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4 FLIG. PER. EXAM. PREP.
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Questions in this quiz (25)
177 To obtain the maximum possible range when flying into a headwind, the speed should:
- AO be higher than the optimum speed for still air,
- BO be the same as the optimum speed for still air
- CO proceed an appropriate fuel management.
- DO be lower than the optimum speed for still air
278 If the aircraft's C.G. is moved into a more forward position
- AO the drag and lift will be increased and the range will be decreased
- BO the drag and lift will be increased and the range will be increased
- CO the drag will be increased, lift will be decreased and the range will be decreased
- DO the drag will be decreased, the lift will be increased and the range will be increased.
379 For a given aircraft mass, as altitude increases, the minimum total drag will;
- AO remain the same and the Vmd will remain the same .
- BO decrease, and the Vmd will decrease
- CO increase, and the Vmd will increase
- DO remain the same and the Vmd will be diminished.
480 The maximum speed that can be achieved in level flight, will occur:
- AO when the drag is equal to the maximum thrust available,
- BO when the drag is a minimum
- CO when CL / CD is a minimum
- DO when CD is a minimum
581 The scheduled landing distance required, is the distance :
- AO from a screen of a designated height to the point at which the aircraft has come to a complete stop,
- BO from touch down to the point at which the aircraft has vacated the runway in use.
- CO from touch down to the point at which the aircraft has come to a complete stop
- DO from the point at which the aircraft is 50 metres above the runway to the point at which the aircraft has come to a complete stop, with brakes full.
682 The landing distance required will be increased as a result of all of the following';
- AO increased temperature, increased pressure altitude, downhill runway slope,
- BO increased temperature, increased pressure altitude, uphill runway slope.
- CO decreased temperature, decreased pressure altitude, uphill runway slope
- DO increased temperature, decreased pressure altitude, downhill runway slope.
783 Which of the following statements relating to hydroplaning is true :
- AO When the wheel begins to hydroplane the wheel drag decreases.
- BO Hydroplaning can only occur if the depth of the contaminant exceeds 5 mm.
- CO Hydroplaning can only occur if the brakes are applied and releasing the brakes will stop the hydroplaning.
- DO Hydroplaning can be reduced when tιre chambers are more flat, (reduced tιre pressure).
8102 Given that the regulations applied and control requirement is met, the speed at the 50 ft. screen must not be less than :
- AO 30% above the stalling speed with landing flap.
- BO 20% above the stalling speed with landing flap
- CO 30% above the stalling speed with flaps up
- DO stall speed.
9103 If the runway is wet, the landing distance required for a dry runway :
- AO must be increased by 15% (X1.15)
- BO may be used unfactored '
- CO must be considered unpredictable
- DO must be increased by 10% (X1.10)
10104 The landing distance required must not exceed :
- AO 70% of the landing distance available at destination and alternate aerodromes.
- BO 70% of the landing distance available at a destination aerodrome; and 50% of the
landing distance available at an alternate aerodrome. - CO 50% of the landing distance available at a destination aerodrome, and 70% of the
landing distance available at an alternate aerodrome. - DO 50% of the landing distance available at destination and alternate aerodromes.
11108 For a grass runway, the landing distance required for a paved runway should be :
- AO increased by 15%,
- BO decreased by 5%
- CO increased by 5%
- DO decreased by 15%
12109 In comparison to the true airspeed in still air conditions, the TAS for the best range in a strong tailwind will be:
- AO slightly lower.
- BO the same.
- CO slightly higher.
- DO significantly lower, proportional to the tailwind component.
13110 Consult Fig.4. Refering to this graph, the flight for maximum range in a piston engined aircraft is achieved by flying:
- AO at that speed which provides the minimum power/ airspeed ratio.
- BO significantly higher than the minimum drag speed (Vmd).
- CO at the lowest density altitude environment that is safely possible.
- DO at the same speed which provides the maximum power/airspeed ratio.
14113 The best rate of climb is achieved.
- AO when there is a maximum excess of power above that required to maintain straight and level flight.
- BO when climbing into wind at the best angle of climb.
- CO when cored into a thermal.
- DO when the mixture is full rich and the throttle fully advanced and the aeroplane maintaining cruise speed.
15114 (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?
- AO 1,650-foot increase.
- BO 1,000-foot increase.
- CO 1,300-foot increase.
- DO 1950-foot increase.
16115 (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?
- AO 2,100-foot decrease.
- BO 1,800-foot increase.
- CO 1,500-foot decrease.
- DO 1,000-foot increase.
17116 (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.
- AO 3,010 feet MSL.
- BO 1,250 feet MSL.
- CO 1,373 feet MSL.
- DO 2500 feet MSL.
18117 (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.
- AO 1,200 feet MSL.
- BO 2,440 feet MSL.
- CO 2000 feet MSL.
- DO none of them.
19118 (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
- AO 8,500 feet MSL.
- BO 4,600 feet MSL.
- CO 5,877 feet MSL.
- DO 6000 feet MSL.
20119 (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
- AO 3,500 feet MSL.
- BO 4,900 feet MSL.
- CO 4,000 feet MSL.
- DO 3,000 feet MSL.
21120 (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".
- AO 4,527 feet MSL.
- BO 4,236 feet MSL.
- CO 3,640 feet MSL.
- DO 4,600 feet MSL.
22121 (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?
- AO 1,300-foot increase.
- BO 900-foot increase.
- CO 1,100-foot decrease.
- DO 1300-foot decrease.
23122 (Refer to figure 8.) Determine the pressure altitude at an airport that is 1,386 feet MSL with an altimeter setting of 29.97".
- AO 1,341 feet MSL.
- BO 1,451 feet MSL.
- CO 1,562 feet MSL.
- DO 1,212 feet MSL.
24123 (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
- AO 2,000 feet MSL,
- BO 1,500 feet MSL
- CO 2,900 feet MSL,
- DO 3,500 feet MSL
25124 (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?
- AO 23knots.
- BO 19 knots.
- CO 30 knots.
- DO 34 knots.
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- 4 FLIG. PER. EXAM. PREP.
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