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ATPL(A) 081 Principles of Flight > 081.06 LIMITATIONS > Flashcards

081.06 LIMITATIONS Flashcards

1
Q

State if the following increases or reduces the risk of flutter:

  • Moving engines from fuselage to wings
  • Excessive free play or backlash
  • Flying at high IAS
A

State if the following increases or reduces the risk of flutter:

  • Moving engines from fuselage to wings → reduces
  • Excessive free play or backlash → increases
  • Flying at high IAS → increases
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2
Q

Aileron reversal may be caused by the wing twisting and (increasing/reducing) incidence when the aileron is lowered.

A

Aileron reversal may be caused by the wing twisting and (reducing) incidence when the aileron is lowered.

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3
Q

Define ‘VFE‘.

A

Maximum speed at which can be flown with the flaps extended.

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4
Q

Define ‘VLE‘.

A

Maximum speed at which can be flown with the landing gear extended.

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5
Q

Define ‘VLO‘.

A

Maximum speed at which the landing gear can be operated

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6
Q

Define ‘VA‘. It is (dependent/independent) on aeroplane mass and (dependent/independent) on pressure altitude.

A

Design-manoeuvring speed. It is (dependent) on aeroplane mass and (dependent)​ on pressure altitude.

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7
Q

Define ‘VC‘.

A

Design cruising speed

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8
Q

Define ‘VRO‘.

A

Rough air speed. Recommended turbulence penetration speed. Should be between VBmin and VBmax to protect the aeroplane from stalling or overstressing.

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9
Q

Define ‘VB‘.

A

Maximum speed at heavy gust intensity. At higher speed the maximum load factor would be exceeded during a heavy gust. May be devided in VBmin and VBmax. Then A speed lower than VBmin would result in a stall.

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10
Q

Define ‘VD‘.

A

Design-diving speed

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11
Q

The manoeuvring load-factor limits applicable to large jet transport aircraft (CS-25) are from (-3.0/-1.76/-1.52/-1/0.0) g to (+2.0/+2.5/+3.8/+4.4/+6.0) g. With flaps extended this changes to (-3.0/-1.76/-1.52/-1/0.0) g to (+2.0/+2.5/+3.8/+4.4/+6.0) g.

A

The manoeuvring load-factor limits applicable to large jet transport aircraft (CS-25) are from (-1.0) g to (+2.5) g.

With flaps extended this changes to (0.0) g to (+2.0) g.

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12
Q

The manoeuvring load-factor limits applicable to light normal aircraft (CS-23) are from (-3.0/-1.76/-1.52/-1/0.0) g to (+2.0/+2.5/+3.8/+4.4/+6.0) g.

A

The manoeuvring load-factor limits applicable to light normal aircraft (CS-23) are from (-1.52) g to (+3.8) g.

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13
Q

The manoeuvring load-factor limits applicable to light utility aircraft (CS-23) are from (-3.0/-1.76/-1.52/-1/0.0) g to (+2.0/+2.5/+3.8/+4.4/+6.0) g.

A

The manoeuvring load-factor limits applicable to light utility aircraft (CS-23) are from (-1.76) g to (+4.4) g.

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14
Q

The manoeuvring load-factor limits applicable to light aerobatic aircraft (CS-23) are from (-3.0/-1.76/-1.52/-1/0.0) g to (+2.0/+2.5/+3.8/+4.4/+6.0) g.

A

The manoeuvring load-factor limits applicable to light aerobatic aircraft (CS-23) are from (-3.0) g to (+6.0) g.

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15
Q

The ultimate load factor is limit load factor multiplied by (…).

A

The ultimate load factor is limit load factor multiplied by (1.5).

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16
Q

The extreme right limitation for both V-n (gust and manoeuvre) diagrams is created by the speed (Vflutter/VC/VD/VMO).

A

The extreme right limitation for both V-n (gust and manoeuvre) diagrams is created by the speed (VD).

source: https://www.uavnavigation.com/support/kb/general/general-system-info/flight-envelope

17
Q

The stall speed lines in the manoeuvring-load diagram originate from a point where speed is (0/VA/VS) and load factor is (0/+1).

A

The stall speed lines in the manoeuvring-load diagram originate from a point where speed is (0) and load factor is (0).

source: https://www.uavnavigation.com/support/kb/general/general-system-info/flight-envelope

18
Q

VMO or VNE (can/can not) be higher then VC.

A

VMO or VNE (can not) be higher then VC.

19
Q

State whether gust-load factor will increase or decrease for an increase in the following:

  • lift-curve slope
  • aspect ratio
  • wing loading
  • weight
  • speed of vertical gust
A

State whether gust-load factor will increase or decrease for an increase in the following:

  • lift-curve slope → increase (same increase in AoA generates larger change in CL for a steep slope)
  • aspect ratio → increase (large slope of curve)
  • wing loading → decrease
  • weight → decrease
  • speed of vertical gust → increase
20
Q

State whether gust-load factor will increase or decrease for an increase in the following:

  • angle of sweep
  • altitude
  • wing area
  • EAS
A

State whether gust-load factor will increase or decrease for an increase in the following:

  • angle of sweep → decrease ​(small slope of curve)
  • altitude → decrease
  • wing area → increase (lift increases and therefor the load factor)
  • EAS → increase
21
Q

The minimum gust speed that an aircraft must be designed to withstand at VD is (25/50/55/66) ft/sec.

A

The minimum gust speed that an aircraft must be designed to withstand at VB is (25) ft/sec.

source: https://encyclopedia2.thefreedictionary.com/_/viewer.aspx?path=mgh%2Fav&name=f0324-07&url=https%3A%2F%2Fencyclopedia2.thefreedictionary.com%2Fgust%2Benvelope

22
Q

The minimum gust speed that an aircraft must be designed to withstand at VB is (25/50/55/66) ft/sec.

A

The minimum gust speed that an aircraft must be designed to withstand at VB is (66) ft/sec.

source: https://encyclopedia2.thefreedictionary.com/_/viewer.aspx?path=mgh%2Fav&name=f0324-07&url=https%3A%2F%2Fencyclopedia2.thefreedictionary.com%2Fgust%2Benvelope

23
Q

The minimum gust speed that an aircraft must be designed to withstand at VC is (25/50/55/66) ft/sec.

A

The minimum gust speed that an aircraft must be designed to withstand at VC is (50) ft/sec.

source: https://encyclopedia2.thefreedictionary.com/_/viewer.aspx?path=mgh%2Fav&name=f0324-07&url=https%3A%2F%2Fencyclopedia2.thefreedictionary.com%2Fgust%2Benvelope

24
Q

In gust an manoeuvre load diagrams, the most limiting speed is (VB/VC/VD/VMO).

A

In gust an manoeuvre load diagrams, the most limiting speed is (VD).

source: https://encyclopedia2.thefreedictionary.com/_/viewer.aspx?path=mgh%2Fav&name=f0324-07&url=https%3A%2F%2Fencyclopedia2.thefreedictionary.com%2Fgust%2Benvelope

25
Q

The gust load diagram has a (symmetrical/asymmetrical) shape with respect to the n = 1 line for speeds above VB.

A

The gust load diagram has a (symmetrical) shape with respect to the n = 1 line for speeds above VB.

source: https://encyclopedia2.thefreedictionary.com/_/viewer.aspx?path=mgh%2Fav&name=f0324-07&url=https%3A%2F%2Fencyclopedia2.thefreedictionary.com%2Fgust%2Benvelope

26
Q

All gust lines in the gust load diagram originate from a point where the speed is (0/VS/VB) and teh load factor is (0/+1).

A

All gust lines in the gust load diagram originate from a point where the speed is (0) and teh load factor is (+1).

source: https://encyclopedia2.thefreedictionary.com/_/viewer.aspx?path=mgh%2Fav&name=f0324-07&url=https%3A%2F%2Fencyclopedia2.thefreedictionary.com%2Fgust%2Benvelope

ATPL(A) 081 Principles of Flight (9 decks)

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