081.06 LIMITATIONS

Question 1

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

Answer 1

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

Question 2

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

Answer 2

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

Question 3

Define ‘V_FE‘.

Answer 3

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

Question 4

Define ‘V_LE‘.

Answer 4

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

Question 5

Define ‘V_LO‘.

Answer 5

Maximum speed at which the landing gear can be operated

Question 6

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

Answer 6

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

Question 7

Define ‘V_C‘.

Answer 7

Design cruising speed

Question 8

Define ‘V_RO‘.

Answer 8

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

Question 9

Define ‘V_B‘.

Answer 9

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

Question 10

Define ‘V_D‘.

Answer 10

Design-diving speed

Question 11

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.

Answer 11

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.

Question 12

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.

Answer 12

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

Question 13

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.

Answer 13

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

Question 14

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.

Answer 14

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

Question 15

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

Answer 15

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

Question 16

The extreme right limitation for both V-n (gust and manoeuvre) diagrams is created by the speed (V_flutter/V_C/V_D/V_MO).

Answer 16

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

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

Question 17

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

Answer 17

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

Question 18

V_MO or V_NE (can/can not) be higher then V_C.

Answer 18

V_MO or V_NE (can not) be higher then V_C.

Question 19

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

Answer 19

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 C_L for a steep slope)
• aspect ratio → increase (large slope of curve)
• wing loading → decrease
• weight → decrease
• speed of vertical gust → increase

Question 20

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

• angle of sweep
• altitude
• wing area
• EAS

Answer 20

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

Question 21

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

Answer 21

The minimum gust speed that an aircraft must be designed to withstand at V_B 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

Question 22

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

Answer 22

The minimum gust speed that an aircraft must be designed to withstand at V_B 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

Question 23

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

Answer 23

The minimum gust speed that an aircraft must be designed to withstand at V_C 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

Question 24

In gust an manoeuvre load diagrams, the most limiting speed is (V_B/V_C/V_D/V_MO).

Answer 24

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

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

Question 25

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

Answer 25

The gust load diagram has a **(symmetrical)** shape with respect to the n = 1 line for speeds above V_B. source: https://encyclopedia2.thefreedictionary.com/\_/viewer.aspx?path=mgh%2Fav&name=f0324-07&url=https%3A%2F%2Fencyclopedia2.thefreedictionary.com%2Fgust%2Benvelope

Question 26

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

Answer 26

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