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14 WPS 17B MC/AC AERO Test > Aero Test > Flashcards

Aero Test Flashcards

1
Q

Lift vs drag impact on airfoils

A

Lift is the force component perpendicular to oncoming flow. Contrasts with drag force, which is the component of surface force parallel to oncoming flow.

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2
Q

What causes airfoil to stall?

A

Stall occurs when AoA is increased beyond critical AoA and lift begins to decrease.

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3
Q

Relationship between flaps and angle of attack

A

For the same AoA, CL will increase with flaps extended

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4
Q

What will raising flaps do (if extended) during stall recovery?

A
  • change effective AoA
  • increase stall speed due to lower CL
  • reduce lift
  • increase sink rate
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5
Q

Definition of refusal speed

A

The maximum speed an aircraft can accelerate on all 4 engines and stop in the remaining runway available with following limits:

  • 1 engine windmilling (legacy)/ feathered (J)
  • one engine in ground idle
  • 2 symmetrical engines in reverse
  • max anti skid braking
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6
Q

Definition of Vmca1

A

Min speed at which you can loose and engine and still maintain directional control, based on this configuration:

  • # 1 windmilling on NTS (legacy)/ feathered (J)
  • max power on remaining engines (legacy)/ T/O power commanded and ATCS operating
  • bleeds off (legacy)
  • max rudder deflection 180lbs (legacy)/ 150lbs (J)
  • flaps 50%, gear down
  • (J) zero rudder trim, min flying weight
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7
Q

What does definition of Vmca1 guarantee?

A

ONLY guarantees you can overcome yawning and rolling tendencies with max rudder and aileron (as a function of temp/PA). NOT maintain level flight. Level flight is function of power available vs GW and that you can maintain an AoA for that weight.

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8
Q

Define critical Field Length (CFL)

A

Legacy - the greater of the total rwy distances, balanced or unbalanced, required to accelerate on all engines, experience and engine failure, then either continue the T/O or stop

J model- the total rwy distance required to accelerate on all engines to Critical engine failure speed, experience and engine failure, then continue the T/O or stop within the same distance

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9
Q

What is cruise ceiling

A

The altitude at which the max rate of climb capability at max continuous power, and best climb speed is 300 ft/min

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10
Q

What is service ceiling

A

The altitude at which the max rate of climb capability at max continuous power, and best climb speed is 100 ft/min

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11
Q

What is drift down (100 fpm)

A

The forced descent due to loss of engine

  • maintain drift down speed until descent drops to 100 fpm
  • maintain 100 fpm down to appropriate 2/3 engine service ceiling
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12
Q

Most descents are flown as __________

A

En route descents

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13
Q

List types of descents

A
  • Maximum range: flight idle, clean config - L/D Max
  • Penetration: Max range to 20K ft - 250 knots to level
  • Rapid Configured: flight idle, gear down, 100% flaps - 145 it to level
  • Rapid Dive Speed: flight idle, clean - dive speed to level
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14
Q

Which descent profile take the least distance, what are the controlling factors, and what happens to drag at higher density altitudes?

A
  • Rapid descent at dive speed
  • Drag and GW
  • drag has less effect at high density
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15
Q

Impacts and disparities between power-on and power-off stalls

A
  • Blown lift
  • 46% wing area immersed in prop slipstream (blown wing effect)
  • high velocity air flow, especially at high power settings
  • separation of boundary layer delayed on control surfaces
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16
Q

Doghouses

A

reference one note pictures

17
Q

Understand wingtip clearances and wing drop

A
  • wing tip is not level with belly of acft until 10.3 AOB

- ROT: wing drops 10 ft for every 10 deg AOB

18
Q

Describe basic forces on aircraft

A
  • To counter moment caused by net lift acting aft of the CG (center of lift aft of the CG is required for stability), the horizontal stabilizer produces balancing tail load.
  • Fwd CG = more “down” lift required by tail
  • more lift = more Di (induced drag)
  • more Di = more total drag
  • fuel burn moves CG fwd
19
Q

Define/describe structural stresses (bending, shear, etc)

A
  • Torsion: twisting of a body by the exertion of forces tending to turn one end about a longitudinal axis, while the other is held fast or turned in opposite direction
  • Bending: the moment created by a transverse deflection of a body through and perpendicular to its longitudinal axis
  • Shearing: a force tending to cause deformation of a material by slippage along a plane or planes parallel to the imposed stressed
20
Q

Understand load limits

A
  • LL assume no corrosion, fatigue or other damage
    • If LL factors are exceeded, acft will suffer permanent
      objectionable deformation
    • Exceeding LLF doesn’t always result in permanent failure of
      Primary structure
  • Exceeding Ultimate Limit (UL) may cause catastrophic failure
    • UL factors by definition are 1.5 times the LLF
  • Overtime, structural damage may lead to structural failure
21
Q

How are asymmetric forces distributed

A

Max loads for unsymmetrical maneuvers are less than for symmetrical maneuvers. Check rolls/reversals greatly increase wing up bending for the down aileron wing.

22
Q

Ops limits for load limits (bank/flaps)

A

Do not exceed…

  • 60 deg AOB with flaps retracted
  • 45 dog with flaps extended
  • max 2.0g symmetrical/ 1.5g asymmetrical
23
Q

What is indicated by the g-meter and where is it measuring

A

Pilots g-meter reads the load factor accurately only at its location. The g-load at at the CG may be be quite different.

24
Q

Fin stall recovery

A
  • Reduce rudder force and/or use opposite rudder to bring acft back to coordinated flight
  • DO NOT apply full opposite rudder, structural damage and/or departure from controlled flight could occur
  • Smoothly recenter ball
25
Q

Why is fuel management important

A

Different combos of fuel load and distribution in the tanks impact the acft load limits.

  • Most of fuel is stored in wing tanks
  • Weight distribution can increase/decrease wing bending
  • Fuel in outboards decreases wing bending
  • Fuel in all other tanks increases wing bending
  • combo of up-bending/ torsion moments may limit airspeed
  • For any GW, the least wing bending in flight is with #1 & 4 tanks full
26
Q

Difference between symmetrical and asymmetrical maneuvers

A

Symmetrical- maneuvers performed with ailerons neutral
- limited to 3.0g in area A

Asymmetrical- maneuvers performed with ailerons deflected
- limited to 2.5g in area A

27
Q

T-storms penetration and turbulence speed

A

Power off stall +65 kts, 180 max (181-J)

Compromise for stall margin and prevention of structural damage

28
Q

Stall Characteristics of Stall Warning

A
  • Progresses from light to moderate to heavy buffet
  • Buffet intensity increases with increased GW
  • 0% flap light buffet precedes stall by 5-9kt, increasing to moderate buffet
  • Higher intensity buffet and more abrupt with flaps extended
  • Greatest stall warning margin with 50% flaps, less at 0 and 100
29
Q

Stall Recovery (exceeded AoA causes stall)

A
  • MAX, RELAX, ROLL
  • Altitude/energy permitting reduce AoA (back pressure)
  • Throttles flight idle if power is asymmetrical
  • Control roll with ailerons as these are last to stall
  • Rolling out reduces AoA, potentially breaking accelerated stall
  • Add power if available
30
Q

Why you stall as a function of AoA

A

The point where an increase in AoA no longer produces an increase in CL…or where critical AoA is exceeded

31
Q

Critical engine failure speed (CEFS)

A

Max speed the acft can accelerate on 4 engines, lose an engine, and either continue takeoff or stop within charted critical field length

32
Q

Rotation speed (Vrot)

A

(U/W) normal rotation speed is Vto -5 kts; not less than Vmca

33
Q

Min control speed ground

A

Minimum speed during ground run at which you can lose an engine and still maintain directional control

34
Q

MFLMETO

A

Length of runway required to accelerate to decision (refusal) speed, experience an engine failure and stop, or continue acceleration to 1.2 pwr on stall speed (U/H)….1.05 Vmu4 (J) in remaining runway

14 WPS 17B MC/AC AERO Test (1 decks)

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