Statistics for PERFORMANCE AND FLIGHT MONITORING 030

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Question	Answer	% Correct
Maximum Landing Mass (MLM) is best defined as:	Maximum permissible total mass on landing under normal operating conditions.	73%
Maximum Zero Fuel Mass (MZFM) is best defined as.	Maximum permissible mass of the aircraft with no useable fuel.	60%
What name is given to the load at which the aircraft structure will fail?	Ultimate Load.	60%
What is the colour of the caution speed range on an Air Speed Indicator, and what must the pilot be mindful of when operating in this range?	Yellow - This speed range should not be entered unless the air is smooth. Any manoeuvres should be made using small and gentle control inputs.	60%
An aircraft which has been grossly overloaded will: 1.require increased take-off and landing distances. 2. Have a higher stalling speed. 3. Have a reduced maximum level flight speed. 4. Have increased range and endurance. 5. Have a reduced rate of climb and operating ceiling. Which of the above are correct?	1, 2, 3, & 5.	58%
What V speed is it important not to exceed if sudden full-pitch, nose-up, control movements are planned, and why?	Va, sudden control movements can cause structural damage.	54%
Certification requirements stipulate that when loading a light aircraft:	The C of G should remain within the defined limits and the Maximum Take-off Mass must not be exceeded.	53%
An aircraft loaded in a dangerous manner, so that its C of G is beyond its forward limit will:	Have both an increased longitudinal stability and stalling speed.	50%
C of G limits are set by the manufacturer and:	Are mandatory.	49%
The consequences of operating an aeroplane with the C of G beyond the aft limit will be: I On the ground the aircraft would be tail heavy and passenger or crew movement or fuel usage could make it tip up. II The flying controls would be too sensitive increasing the risk of a tail strike at rotation. III The tendency to stall would increase and it may be impossible to achieve "hands off" balanced flight. IV Recovery from a spin would be much more difficult.	All statements are correct.	47%
What is used as the aircraft reference for the C of G limit, and upon which axis is that limit found? Axis / Reference	Longitudinal / Datum.	47%
An aircraft is loaded such that its C of G is on the aft limit: I The stalling speed decreases II Range and endurance increase III The stalling speed increses IV Stick forces increase	Only I and II are correct.	47%
Never exceed speed (VNE) is the red radial line on the ASI and marks the speed which:	Structural damage will occur.	47%
An aircraft weighing 2000 lbs with a total CofG moment of + 169400 lb in uplifts 440 lbs of fuel. If the effective arm of the fuel is 88.5 inches aft of the datum, what will be the aircraft's new mass and C of G moment?	2440 lbs +208340 lb in.	46%
Your aircraft has an oil reservoir with a capacity of 3 imp/gal which is positioned 20 inches aft of the datum. Given that the oil weighs 9.1 lbs/gal, the reservoir will possess a moment of:	546 lb in.	46%
Traffic Load:	Is the total mass of passengers, baggage and freight.	46%
Maximum Take Of Mass (MTOM) is defined best as:	Maximum permissible total mass at the start of the takeoff run.	46%
Your aircraft has: A Take-off Mass of = 2353 lbs. A calculated C of G for departure = 89.75 inches aft of the datum. An estimated fuel burn = 200 lbs with a C of G 85.00 inches aft of datum. The position of the C of G on landing will be?	90.19 inches aft of the datum.	45%
The flight characteristics of an aircraft which has its C of G at the forward limit will be:	Insensitivity to Pitch Control and great Longitudinal Stability.	44%
You plan to carry your aircraft's maximum permissible 'Traffic Load'. Your principal consideration during your flight planning will be that:	Your fuel load may have to be limited to prevent you exceeding the Maximum All Up Weight / Mass.	44%
What is the effect of runway slope on the take-off?	An uphill slope will increase the take-off distance.	42%
The Maximum Take-off Mass of an aircraft may be limited by:	Structural design load limits and/or altitude and temperature.	40%
When flying in very rough air what is the maximum speed to be adopted in order to avoid overstressing the airframe?	Vra or Va.	40%
Assuming the aircraft is at rest on the ground, what term best describes image A? (See LAPL/PPL 030-01)	Zero Fuel Mass.	40%
In which Category, Utility or Normal, would you expect to operate the aircraft represented in the attached CofG / Moment Envelope if its mass is 2100 lbs and its CofG Moment 90,000 lb inches? (See LAPL/PPL 030-02)	Normal.	38%
That part of a runway surface which is used for normal operations during take- off, excluding any clearway or stopway, is referred to as:	The take-off run available (TORA).	38%
When the density of the atmosphere is relatively low, the resulting reduction in:	Both lift and engine power will require a longer take-off distance.	37%
When calculating the MZFM (maximum zero fuel mass), the following are included:	Crew, Passengers, Baggage & Catering.	37%
Assuming the aircraft is at rest on the ground, what term best describes image "D"? (See LAPL/PPL 030-01)	Maximum All Up Mass.	37%
If the density of the atmosphere is reduced, the take-off distance will be:	Increased.	36%
Increasing the aeroplane's gross weight will have what effect on the take-off?	Increase the stall speed and the take-off run required.	36%
If the approach and landing speed is higher than recommended speed in the aircraft manual the effect will be that:	The landing distance will be increased.	35%
If the density of the air is increased above ISA conditions, the effect will be:	To increase the take-off performance.	35%
The maximum glide range will be achieved by:	A relatively low angle of attack being maintained.	33%
The main reason for taking off into wind is to:	Decrease the ground speed of the aircraft at lift-off.	33%
Climbing at Vy will achieve:	The greatest increase in altitude in a given period of time.	33%
In order to maximise the glide range, the aircraft should be flown:	At low angles of attack at VMD.	32%
What is the reason for increasing the speed in a prolonged climb?	To increase the flow of air through the engine and keep it cool.	32%
If weight is increased, the range of the aircraft will be:	Reduced.	31%
What would be the effect of an increase in temperature upon the air density and aircraft performance?	Reduced density and reduced aircraft performance.	31%
To gain the greatest amount of height in the shortest time period the aircraft should be flown at:	The best rate of climb speed (Vy).	31%
Compared to landing on a level runway, what would be the effect of landing on a downward sloping runway?	The landing distance will be increased.	31%
When landing, if an aircraft's true air speed is significantly less than the true ground speed then the aircraft is experiencing:	A tailwind.	29%
What is the maximum range speed for a piston engine aircraft?	VMD	29%
What speed should be flown for maximum range? (See LAPL/PPL 030-05)	B	28%
What effect would a 1% downslope have on the landing distance required?	Increase it by 5%.	28%
What effect will a higher aircraft mass have on rotate speed and stalling speed?	It will increase both speeds.	28%
Climbing at Vx will achieve:	The maximum angle of climb.	28%
The centre of gravity is moved backwards. The effect is?	An increased range and endurance.	27%
When gliding for maximum range, an aircraft with a greater weight will:	Have a faster descent speed but the same descent angle.	27%
What is the effect of an increase in mass on the stalling speed and landing distance required?	Increased stall speed and increased landing distance.	27%
Basic reason for calculating the density altitude is determining:	The aircraft performance.	27%
The Centre of Gravity range of most aircraft reduces as the aircraft mass increases, as a result of:	The forward C of G limit moving rearwards to reduce stability.	27%
Determine approximately density altitude of an airport, where the temperature is standard and an altimeter set to 1011hPa, reads 1,300 ft:	1,360 ft.	26%
If the stalling speed in the landing configuration is 55 knots. VREF would be approximately:	71kt.	26%
Which of the speeds indicated by A, B, C or D should be flown for maximum endurance? (See LAPL/PPL 030-05)	A	26%
How runway slope affects on the take-off and landing distances?	An uphill slope increases take-off distance but decreases landing distance.	26%
The indicated air speed for the best rate of climb when climbing to cruise altitude will tend to:	Decrease as the power of the engine decreases.	26%
Increasing the mass (and, therefore, weight) of the aircraft will:	Decrease the rate and angle of climb.	26%
Compared to gliding in still air, the effect of a tailwind will:	Increase the glide range but have no effect on the glide endurance.	26%
Landings are carried out into wind because:	It will reduce the ground speed and reduce the landing distance required.	26%
What speed must be flown to attain the maximum cruise range?	VMD.	26%
An aircraft cruising at 2000ft is cleared to climb to 8000ft. Calculate the time taken in minutes, the fuel used in gallons and the distance flown during the climb. The temperature is standard and the wind is calm. (See LAPL/PPL 030-04) Time (mins) / Fuel (gal) / Distance (nm)	12 / 2,3 / 17	24%
The VREF to be attained by the landing screen height of 50ft must be:	1.3 times the stalling speed in the landing configuration	24%
If the aircraft mass is increased by 15%, the landing distance required will increase approximately:	15% or by a factor of 1.15.	24%
GIVEN: mass (lb) arm(in) moment (lbxin) Empty mass 1,495.0 101.4 151,593.0 Pilot and passenger 380.0 64.0 Fuel (100LL 0,72 kg/l) 30 US gal 96.0 The CG is located how far aft of datum?	94.01 in.	24%
What is the effect of a headwind on the glide angle and glide distance?	Glide angle will increase and glide distance decrease.	24%
The lift produced by the wing of an aeroplane that is climbing and maintaining a constant airspeed will be:	Less than weight.	24%
Your speed is to low when the aircraft rotates. What is the consequence?	Take-off distance increases.	24%
If an aircraft does not give announcement from departure within 30 minutes from the time written in the flight plan, the phase that starts is called:	Uncertainty phase	24%
What speed must be flown to attain the maximum cruise endurance?	VMP.	24%
The easiest way to determine the pressure altitude is setting an altimeter to:	1013.2 hPa and reading the altitude.	23%
64 liters of 100LL weights:	46 kg	23%
Which forward speed is normally maintained, following an engine failure in flight in a light airplane?	Best glide speed.	23%
Which of the following is the best way to check the fuel amount before a flight?	Comparing fuel gauge reading and the amount measured from the tanks.	23%
When starting a climbing turn from straight climb without changing the power setting your climb rate (ft/min):	Is reduced	23%
If you load an aeroplane Centre of Gravity to the aft limit instead of the forward limit and fly at the same altitude and cruise power, you will notice that:	Maximum range increases	23%
Which one of the following statements concerning the mass and balance calculation is correct?	Moment = force x arm	23%
Which of the following statement concerning the 45 minutes final reserve fuel is correct?	That is the minimum amount of fuel that must be left after a flight. If this reserve is used during the flight it is an emergency situation.	23%
Which of the following is the density that is used when counting mass of 100LL fuel?	0,72 kg/l	22%
The centre of gravity of an aeroplane is:	A point where the whole mass of the aeroplane can be considered concentrated	22%
Performance figures given by the manufacturer of an aeroplane in its POH (pilot's operating handbook) are based on measurements and calulations in one of the below listed conditions. Choose the correct alternative:	ICAO standard atmosphere conditions	22%
In VFR flight, an aircraft must have enough fuel for:	Starting an engine, engine run-up, taxi, a flight from departure to destination aerodrome, and also a 45 minutes final reserve.	22%
The best rate of climb is achieved:	When flying at the speed for maximum excess power available.	22%
What is increase in density altitude if a temperature increases from 0 to 10°C and if the pressure altitude of an airport remains 3,000 ft?	1,200 ft.	21%
What is the effect of a temperature increase of 12°C on the density altitude?	1,440-foot increase.	21%
Determine the density altitude of an airport for these conditions: QNH 1025 hPa Temperature -4°C Elevation 3,850 ft	2,050 ft.	21%
What is a standard mass for a 2-12 years old child in flight operations with an aircraft which maximum certificated take-off mass is 5700 kg?	35 kg.	21%
What is a standard mass for an adult in flight operations with an aircraft which maximum certificated take-off mass is 5700 kg?	80 kg.	21%
Altitudes for Rovaniemi aerodrome traffic circuit can be found from:	AIP part 1	21%
AIP Supplements can be found from:	AIP part 1	21%
Runway lenghts available (TORA, TODA, ASDA, LDA) can be found from:	AIP part AD	21%
At takeoff from a short airfield with an airplane or a powered hang glider, which airspeed should you fly until cleared of obstacles?	Best angle-of-climb speed (Vx).	21%
AIP Supplements:	Change temporary information given in AIP.	21%
What effect does an uphill runway slope have on takeoff performance?	Increases takeoff distance.	21%
Determine if the aircraft mass is inside the limits (normal category). (See LAPL/PPL 030-10) mass (lb) moment/1000 (lbxin) Empty mass 1,350 51,5 Pilot and front passenger 360 Rear passengers 280 Fuel 30 US gal. Oil 8 qt -0,2	Inside limits.	21%
How does higher air humidity affect aircraft take-off performance? Take-off distances are:	Longer due to thinner air.	21%
What should be done first, following an aircraft's engine failure in flight?	Select the gliding attitude with best glide speed.	21%
Which V-speed represents maneuvering speed?	VA.	21%
Under which condition will pressure altitude be equal to true altitude?	When standard atmospheric conditions exist	21%
What influence does the increased mass have on powered aircraft takeoff performance?	At given engine power the aircraft accelerates poorer; the airspeed required for the production of the lift necessary for leaving the ground is greater.	19%
Which speed would provide the greatest gain in altitude in the shortest distance during climb after takeoff?	Best angle-of-climb speed (Vx).	19%
Which of the factors below increases the density altitude of an airport?	Increase of temperature.	19%
The density altitude could be approximately calculated from the pressure altitude without using a navigation calculator by	Increasing/decreasing the pressure altitude by 120 ft for each °C deviation above/below the standard temperature.	19%
What effect does high density altitude have on aircraft performance?	It reduces climb performance.	19%
During landing on an airport with high elevation the true air speed (TAS) of an aircraft is higher than normal. What indicated speed (IAS) should be kept in such cases?	Normal speed, IAS.	19%
Density altitude means:	Pressure altitude in ISA conditions temperature correction.	19%
What is pressure altitude?	The altitude indicated when the barometric pressure scale is set to 1013.2 hPa.	19%
Clearway is:	TODA - TORA, and is has nothing to do with landing distance calculations.	19%
What is the proper use for the best-rate-of-climb speed (Vy)?	When trying to get cruising altitude quickly.	19%
What influence does the wind have on an airplane's angle-of-climb?	A headwind will steepen the angle-of-climb.	18%
After takeoff, which airspeed would the pilot use to gain the most altitude in a given period of time?	Best climb speed (Vy).	18%
What is the headwind component for a landing on Runway 18 if the tower reports the wind as 220°/30 kts? (See LAPL/PPL 030-06)	23 kts.	17%
Determine the moment with the following data: (See LAPL/PPL 030-10) mass (lb) moment/1000 (lbxin) Empty mass 1,350 51.5 Pilot and front passenger 340 Fuel (full std. tanks) Oil 8 qt -0.2	74.9 lbxin.	17%
Determine the density altitude of an airport for these conditions: QNH 1010 hPa Temperature 27°C Elevation 5,250 ft	7,890 ft.	17%
Which of the statements below, concerning take-off performance of a powered aircraft regarding the density altitude is correct? At higher density altitudes:	Aircraft accelerate poorer, because of reduced engine and propeller efficiency.	17%
The forward speed for minimum rate of descent of an aircraft, compared with its best glide speed, is:	Always lower.	17%
The aircraft's climb angle during a steady climb depends on:	Excess of thrust.	17%
Which combination of atmospheric conditions will reduce aircraft takeoff and climb performance?	High temperature, high relative humidity and high density altitude.	17%
An aircraft without an engine will fly the longest distance from a given altitude at the angle of attack at which:	Induced drag and parasite drag are equal.	17%
Maximum structural cruising speed is the maximum speed at which an airplane can be operated:	In smooth air.	17%
What does "Best Endurance Speed" for a propeller aircraft mean?	Maximum time aloft per unit of fuel (flying with least power).	17%
Should you use the normal approach speed when approaching to land in gusty wind conditions?	No. Add one half the "gust factor" to the calculated approach speed.	17%
Maneuvering speed (VA) is the highest speed at which even full abrupt deflection of the elevator will not exceed	Positive limit load factor.	17%
What is density altitude?	The pressure altitude corrected for nonstandard temperature.	17%
The airplane's or powered hang glider's best angle-of-climb speed (Vx) is used:	When clearing an obstacle.	17%
What is the maximum amount of fuel that may be aboard the airplane on takeoff if loaded as follows? (See LAPL/PPL 030-10) mass (lb) moment/1000 (lbxin) Empty mass 1,350 51,5 Pilot and front passenger 340 Rear passengers 310 Baggage 45 Oil 8 qt -0,2	40 USA gal	15%
What are the headwind and crosswind components with the reported wind of 030°/10 kts for a runway with the magnetic direction 330°? (See LAPL/PPL 030- 06)	5 kts headwind and 8 kts crosswind.	15%
What are the headwind and crosswind components with the reported wind of 280°/15 kts for a runway with the magnetic direction 220°? (See LAPL/PPL 030- 06)	7.5 kts headwind and 13 kts crosswind.	15%
What is the influence of the wind on an aeroplane's rate of climb?	No effect.	15%
Which runway (06, 14, 24, 32) will you choose for landing, if tower reports south wind 20 kts and if maximum allowed crosswind component for your aircraft is 13 kts? (See LAPL/PPL 030-06)	RWY 14.	15%
What will be the airspeed of an airplane in level flight under the following conditions? (See LAPL/PPL 030-07) pressure altitude 8,000 ft temperature 20°C below standard power setting 55%	104 kts.	14%
What is the crosswind component for a landing on Runway 18 if the tower reports the wind as 220°/30 kts? (See LAPL/PPL 030-06)	19 kts.	14%
Determine the maximum wind velocity for a 30° crosswind if the maximum crosswind component for the airplane is 10 kts? (See LAPL/PPL 030-06)	20 kts.	14%
What is the expected fuel consumption for a 350-nautical flight under the following conditions? (See LAPL/PPL 030-07) pressure altitude 4,000 ft temperature 20°C below standard power setting 60% wind calm	22.7 USA gal.	14%
Approximately what engine RPM should be set during cruising at the pressure altitude 2,000 ft and with standard temperature in order to develop 60% of power? (See LAPL/PPL 030-07)	2300 RPM.	14%
If the outside air temperature (OAT) at a given altitude is lower than standard, the density altitude is:	Higher than pressure altitude.	14%
With the reported wind of 360°/20 kts you are approaching an airport. Which runway (06, 14 or 24) would you choose for landing, if your airplane had a 13- knots maximum allowed crosswind component on landing? (See LAPL/PPL 030- 06)	RWY 32.	14%
Why should speeds in flight above VNE is prohibited?	The design limit factor may be exceeded, if gusts are encountered.	14%
What is the maximum amount of baggage that may be loaded aboard the normal category airplane for CG to remain inside proper limits? (See LAPL/PPL 030-10) mass (lb) moment/1000 (lbxin) Empty mass 1,350 51.5 Pilot and front passenger 250 Rear passengers 400 Fuel 30 US gal. Baggage Oil 8 qt -0.2	105 lbs.	13%
Determine the total distance over a 50-foot obstacle required to land. (See LAPL/PPL 030-09) pressure altitude 1,500 ft temperature 30°C mass 2300 lb wind calm surface tarmac	1,350 ft.	13%
What is the expected fuel consumption under the following conditions? (See LAPL/PPL 030-07) pressure altitude 8,000 ft temperature 20°C below standard power setting 55%	6.2 USA gal/h.	13%
Determine the total distance required to land. (See LAPL/PPL 030-09) pressure altitude 1,000 ft temperature 30°C mass 2300 lb wind head 9 kt surface tarmac	1197 ft.	12%
Determine the maximum wind velocity for a 40° crosswind if the maximum crosswind component for the airplane is 10 kts? (See LAPL/PPL 030-06)	15 kts.	12%
Determine the ground roll distance after landing. (See LAPL/PPL 030-09) pressure altitude 0 ft temperature 15°C mass 2300 lb wind calm surface tarmac	520 ft.	12%
The aircraft's rate-of-climb during a steady climb depends on	Excess of power.	12%
Determine the takeoff distance over a 50-foot obstacle under the following conditions: See LAPL/PPL 030-08 Pressure altitude 0 ft temperature standard mass 1900 lb wind calm surface grass, dry	1,030 ft	10%
Determine the ground roll distance required for takeoff: (See LAPL/PPL 030-08) Pressure altitude 2,000 ft temperature 40°C mass 2100 lb wind tail 4 kt surface tarmac	1,120 ft.	10%
Determine the total distance over a 50-foot obstacle required to land. (See LAPL/PPL 030-09) pressure altitude 0 ft temperature 0°C mass 2300 lb wind head 18 kt surface grass, dry	1,140 ft.	10%
Determine the takeoff distance over a 50-foot obstacle under the following conditions: (See LAPL/PPL 030-08) pressure altitude 2,000 ft temperature 30°C mass 2100 lb wind head 18 kt surface grass, dry	1,350 ft.	10%
Determine the maximum wind velocity for a 45° crosswind if the maximum crosswind component for the airplane is 25 kts? (See LAPL/PPL 030-06)	35 kts.	10%
Determine the ground roll distance after landing. (See LAPL/PPL 030-09) pressure altitude 3,000 ft temperature 20°C mass 2300 lb wind calm surface grass, dry	855 ft.	10%
What is the expected fuel consumption for a 250-nautical flight under the following conditions? (See LAPL/PPL 030-07) pressure altitude 6,000 ft temperature 20°C above standard power setting 60% wind calm	15.1 USA gal.	9%
Determine the total distance over a 50-foot obstacle required to land. (See LAPL/PPL 030-09) pressure altitude 1,000 ft temperature 10°C mass 2300 lb wind tail 10 kt surface tarmac	1,900 ft.	9%
Determine the takeoff distance over a 50-foot obstacle under the following conditions: (See LAPL/PPL 030-08) pressure altitude 4,000 ft temperature 15°C mass 2300 lb wind calm surface asphalt	2,100 ft.	9%
Determine the ground roll distance after landing. (See LAPL/PPL 030-09) pressure altitude 0 ft temperature 10°C mass 2300 lb wind head 10 kt surface grass, dry	739 ft.	6%