WorksheetsPerformance 1
Total questions: 30
Worksheet time: 46mins
Refer to CAP698 Section 2 - SEP1 Page 10 Figure 2.4 Landing.
With regard to the graph for landing performance, what is the minimum headwind component required in order to land at Helgoland airport?
Given:
Runway length: 1300'
Runway elevation: MSL
Weather: assume ISA conditions
Mass: 3200 lbs
Obstacle height: 50'
5 KT
No wind
15 KT
10 KT
Refer to CAP698 Section 2 - SEP1 Page 10 Figure 2.4
With regard to the landing chart for the single engine aeroplane determine the landing distance from a height of 50'
OAT: ISA +15°C
Pressure Altitude: 0'
Aeroplane Mass: 2940 lbs
Headwind component: 10 KT
Flaps: Landing position (down)
Runway: short and wet grass - firm soil
Correction factor (wet grass): 1.38
A) approximately: 2000'
B) approximately: 1300'
C) approximately: 1450'
D) approximately: 1794'
Use Performance Manual MEP1 Figure 3.2; With regard to the graph for the light twin aeroplane, if the brakes are released before take-off power is achieved, the accelerate/stop distance will be:
shorter than the graphical distance.
the same as the graphical distance because both techniques are accounted.
longer than the graphical distance.
unaffected because all take-off techniques are accounted.
At reference or use or Performance Manual MEP 1 Figure 3.2 PAGE 5
Given:
OAT: 25°C
Pressure Altitude: 3000 ft
RWY: 24L
Wind: 310°/20kts
Take off Mass: 4400 lbs
Heavy Duty Brakes installed.
Other conditions as associated in the header of the graph.
What is the Accelerate and Stop Distance under the conditions given?
3350 ft
3750 ft
4000 ft
4300 ft
Refer to CAP698 Section 3 - MEP1 Figure 3.1 Take-off Normal Procedure
Given:
OAT +24°C
Pressure Altitude: 3000'
RWY 30R
Wind·060°/4 KT
Take-off Mass: 3800 lbs
Other conditions as associated in the header of the graph. What is the Take-off Distance under the conditions given?
2000'
1670'
1550'
2150
Refer to CAP698 Section 3 - MEP1 Figure 3.1 Normal Procedure
Given:
OAT 24 °C
Pressure Altitude 3000'
RWY, 12L
Wind· 080/12 KT
Take-off Mass: 3800 lbs
Runway Surface· Wet Grass - firm soil
Runway Slope: 2% downslope
What is the minimum runway length?
No stopway or clearway are available.
1400 ft
2850 ft
1750 ft
2550 ft
Refer to CAP698 Section 3 - MEP1 Figure 3.7 Climb Performance - Gear Retracted Maximum Continuous Power
Given:
OAT, - 20 °C
Pressure Altitude: 14 000 ft
Gross Mass 4.000 lbs Other conditions as associated in the header of the graph. What is the one engine inoperative rate of climb?
1250 ft/min
625 ft/min
175 ft/min
375 ft/min
OAT, 10 °C
Pressure Altitude: 2000 ft
Gross Mass 3750 lbs
Mixture: full rich
Other conditions as associated in the header of the graph. What is the two engine rate of climb for the conditions given?
430 ft/min
1770 ft/min
1570 ft/min
1970 ft/min
Refer to CAP698 Section 3 - MEP1 Figure 3.9 Landing Distance Normal Procedure
Given:
Flaps 40
Aerodrome pressure altitude: Sea level
Ambient temperature +15 °C
Landing weight 4000 lbs
Wind· calm
Runway paved and dry
What is the Landing Distance?
2040'
1240'
1400'
2400
The speed VSR is defined as:
safe rotation speed for take-off
design stress speed
as reference stall speed and may not be less than 1-g stall speed
speed for best specific range
What will be the influence on the aeroplane performance if aerodrome pressure altitude is increased?
It will increase the take-off distance available
It will decrease the take-off distance
It will decrease the take-off run
It will increase the take-off distance
A decrease in atmospheric pressure has, among other things, the following consequences on take-off performance:
an increased take-off distance and degraded initial climb performance
a reduced take-off distance and degraded initial climb performance
an increased take-off distance and improved initial climb performance
a reduced take-off distance and improved initial climb performance
The speed V1 is defined as:
take-off climb speed
speed for best angle of climb
take-off decision speed
engine failure speed
Which of the following are to be taken into account for the runway in use for take-off?
Airport elevation, runway slope, standard temperature, pressure altitude and wind components
Airport elevation, runway slope, standard temperature, standard pressure and wind components
Airport elevation, runway slope, outside air temperature, standard pressure and wind components
Airport elevation, runway slope, outside air temperature, pressure altitude and wind components
Changing the take-off flap setting from flap 15° to flap 5° will normally result in:
a shorter take-off distance and an equal climb
a longer take-off distance and a better climb
a shorter take-off distance and a better climb
a better climb and an equal take-off distance
The take-off distance of an aircraft is 800 m in standard atmosphere, no wind at 0' pressure-altitude.
Using the following corrections:
± 20 m / 1000' field elevation
- 5 m / KT headwind
+ 10 m / KT tail wind
± 15 m / % runway slope
± 5 m / °C deviation from standard temperature
The take-off distance from an airport at 2000' elevation, temperature 21°C, QNH 1013.25 hPa, 2% up-slope, 5 KT tail wind is:
890 m
870 m
970 m
810 m
Which of the following answers is true?
V1 is higher VLOF
V1 is lower or equal to VR
V1 is lower VMCG
V1 is higher VR
The following parameters affect the take off ground run:
1 decreasing take off mass
2 increasing take off mass
3 increasing density
4 decreasing density
5 increasing flap setting
6 decreasing flap setting
7 increasing pressure altitude
8 decreasing pressure altitude
Which parameters will decrease the take off ground run?
2, 4, 5 and 7
1, 4, 6 and 8
2, 3, 6 and 7
1, 3, 5 and 8
An airport has a 3000 metres long runway, and a 2000 metres clearway at each end of that runway. For the calculation of the maximum allowed take-off mass, the take-off distance available cannot be greater than
4000 metres
6000 metres
5000 metres
4500 metres
During the flight preparation a pilot makes a mistake by selecting a V1 greater than that required. Which problem will occur when the engine fails at a speed immediately above the correct value of V1?
V2 may be too high so that climb performance decreases
The one engine out take-off distance required may exceed the take-off distance available
It may lead to over-rotation
The stop distance required will exceed the stop distance available
The take-off run is:
the horizontal distance along the take-off path from the start of the take-off to a point equidistant between the point at which VLOF is reached and the point at which the aeroplane is 35 ft above the take-off surface
the distance of the point of brake release to a point equidistant between the point at which VLOF is reached and the point at which the aeroplane attains a height of 50 ft above the runway assuming a failure of the critical engine at V1
1.15 times the distance from the point of brake release to the point at which VLOF is reached assuming a failure of the critical engine at V1
1.5 times the distance from the point of brake release to a point equidistant between the point at which VLOF is reached and the point at which the aeroplane attains a height of 35 ft above the runway with all engines operative
How is wind considered in the take-off performance data of the Aeroplane Operations Manuals?
Unfactored headwind and tailwind components are used
Not more than 50% of a headwind and not less than 150% of the tailwind
Since take-offs with tailwind are not permitted, only headwinds are considered
Not more than 80% headwind and not less than 125% tailwind
The induced drag of an aeroplane:
decreases with increasing gross weight
is independent of the airspeed
decreases with increasing airspeed
increases with increasing airspeed
The point where Drag coefficient / Lift coefficient is a minimum is:
the point where a tangent from the origin touches the drag curve
the lowest point of the drag curve
at stalling speed (VS)
on the 'back side' of the drag curve
Moving the centre of gravity from the forward to the aft limit (gross mass, altitude and airspeed remain unchanged)
decreases the induced drag and reduces the power required.
increases the induced drag.
affects neither drag nor power required.
increases the power required.
Any acceleration in climb, with a constant power setting
improves the rate of climb if the airspeed is below VY
improves the climb gradient if the airspeed is below VX
decreases rate of climb and increases angle of climb
decreases the rate of climb and the angle of climb
How does the best angle of climb and best rate of climb vary with increasing altitude for an aeroplane with a normal aspirated piston engine?
Both increase
Best angle of climb increases while best rate of climb decreases
Both decrease
Best angle of climb decreases while best rate of climb increases
The angle of climb with flaps extended, compared to that with flaps retracted, will normally be
Larger
Smaller
Increase at moderate flap setting, decrease at large flap setting
Not change
Following a take-off, limited by the 50' screen height, a light twin climbs on a gradient of 5%.
It will clear a 160 m obstacle in relation to the runway (horizontally), situated at 5000 m from the 50' point with an obstacle clearance margin of:
90 m
105 m
it will not clear the obstacle
75 m
The rate of climb is approximately equal to:
the still-air gradient multiplied by the TAS.
the angle of climb multiplied by the TAS.
the angle of climb divided by the TAS.
the still-air gradient divided by the TAS.
