The EASA
ATPL Performance
test bank contains questions pertaining to
032-01-03 Climb and cruise performance
. The following list contains only a relatively small percentage of the pertinent
questions. Our software, which you are free to download now at no cost, will
generally contain a much more complete set of questions associated with this
test bank. This list is intended only to familiarize you in a general way with
the questions of the
Performance
test bank.
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That said, while the following questions are intended
as a general familiarization tool, this list may not be up-to-date nor accurate.
We do not update this website as often as we update our software, which will
contain at any moment all questions that we have for a given test / topic. Therefore,
if you need to actually study for your test, instead of using the list below,
we strongly, strongly encourage you to download our GroundSchool
EASA ATPL
Written Test Prep Software and Apps. Not only is it more complete and up-to-date, but is also considerably faster and more efficient as a study tool.
Sample Questions
from the EASA ATPL
Performance
Test Bank |
- To maintain the same angle of attack and altitude at a higher gross weight an aeroplane needs:
- When flying an aircraft on the back of the drag curve, maintaining a slower speed (but still faster than VS) would require:
- In a given configuration the endurance of a piston engine aeroplane only depends on:
- How does the best angle of climb and best rate of climb vary with increasing altitude?
- In which of the flight conditions listed below is the thrust required (Tr) equal to the drag (D)?
- For a jet aircraft, the speed to give the maximum rate of climb will be:
- To obtain the maximum possible range when flying into a headwind, the speed should be:
- With regard to a un-accelerated horizontal flight, which of the following statement is correct?
- The rate of climb depends on:
- In a power-off glide, an increase in aircraft mass will:
- The recommended range speed may exceed the theoretical speed for maximum range because of:
- Given:ROC = 860 ft / minTAS = 92 ktsWind = 16 kts Tail windWhat is the approximate gradient of climb?
- (For this Question use Figure 032_6-2)Using the Power Setting Table, for the single engine aeroplane, determine the cruise TAS and fuel flow (lbs/hr) with full throttle and cruise lean mixture in the following conditions: Given:OAT: 13° CPressure altitude: 8000 ftRPM: 2300
- (For this Question use Figure 032_6-2)Using the Power Setting Table, for the single engine aeroplane, determine the manifold pressure and fuel flow (lbs/hr) with full throttle and cruise lean mixture in the following conditions: Given:OAT: 13° CPressure altitude: 8000 ftRPM: 2300
- The climbing speed that will attain the maximum gradient of climb:
- Given:Still air gradient of climb: 5%TAS: 250 ktsG/S: 200 ktsThe rate of climb is:
- The force that exactly opposes and balances lift in a straight and un-accelerated climb is:
- With a headwind, compared to still air conditions, the rate of climb (i) and the climb angle relative to the ground (ii) will :
- In a banked turn:
- (For this Question use Figure 032_6-4)Using the Range Profile Diagram, for the single engine aeroplane, determine the range, with 45 minutes reserve, in the following conditions:Given:O.A.T.: ISA -15° CPressure altitude: 12000 ftPower: Full throttle (23,0 in/Hg. & 2300 RPM)
- On a reciprocating engine aeroplane, with increasing altitude at constant gross mass, angle of attack and configuration the power required:
- The induced drag of an aeroplane at constant gross weight and altitude is highest at
- (Refer to figure 032_8-3)Consider the graphic representation of the power required versus true air speed (TAS), for a piston engine aeroplane with a given mass. When drawing the tangent from the origin, the point of contact (A) determines the speed of:
- For a given aircraft mass the climb gradient is determined by:
The
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more information about the EASA ATPL
Performance
test bank, click here.
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