THE
PILOT
performance
ATPL
STUDENT
pilot
resume
all info you need to pass atpl exams
,GENERAL
➢ ↑ Aerodrome Pressure Altitude = ↑ Altitude
➢ GROSS Performance = Average Performance
➢ The clearway used can't exceed 50% of the TORA
➢ Contaminated Runway: more than 25% of RWY:
• More than 3mm of water, slush or snow, Ice
➢ Absolute Ceiling: ROC =0
➢ Service Ceiling: ROC = 100ft/min (PROP), 500ft/min (JET)
➢ Aerodynamic Ceiling: the altitude at which the speeds for low speed buffet and for high
speed buffet are the same.
➢ Wind: no effect in ROC
➢ Low Altitudes → Usar constant IAS
➢ High Altitudes → Usar Constant MACH
, CLIMBING CONSTANT IAS:
➢ IAS ↑
➢ MACH ↑
CLIMBING CONSTANT MACH:
➢ TAS ↓
➢ IAS ↓
➢ Climb/Descent Gradient ALWAYS > (HIGHER) than Climb/Descent Angle
➢ Climb/Descent Angle → air mass related
➢ Flight-path Angle → ground related
➢ TOD will increase ↑ by 20% for each 10% increase ↑ in mass
➢ TOD will increase ↑ by 20% for a tailwind component of 10% of the lift off speed
UNACCELERATED CLIMB
➢ W cos(y) = Lift
➢ Thrust = Drag + W sin(y)
EXCESS THRUST = THRUST – DRAG
➢ Vx – speed best climb angle, max excess thrust, max value of the vector; W x sin(Y),
increases with altitude
➢ Vy – speed best rate of climb, max excess power, decreases with altitude
➢ Positive Climb: Vx ALWAYS < (LESS) Vy
➢ These Vx and Vy are worse with flaps.
➢ Rate of Descent: Depends on Velocity
PILOT
performance
ATPL
STUDENT
pilot
resume
all info you need to pass atpl exams
,GENERAL
➢ ↑ Aerodrome Pressure Altitude = ↑ Altitude
➢ GROSS Performance = Average Performance
➢ The clearway used can't exceed 50% of the TORA
➢ Contaminated Runway: more than 25% of RWY:
• More than 3mm of water, slush or snow, Ice
➢ Absolute Ceiling: ROC =0
➢ Service Ceiling: ROC = 100ft/min (PROP), 500ft/min (JET)
➢ Aerodynamic Ceiling: the altitude at which the speeds for low speed buffet and for high
speed buffet are the same.
➢ Wind: no effect in ROC
➢ Low Altitudes → Usar constant IAS
➢ High Altitudes → Usar Constant MACH
, CLIMBING CONSTANT IAS:
➢ IAS ↑
➢ MACH ↑
CLIMBING CONSTANT MACH:
➢ TAS ↓
➢ IAS ↓
➢ Climb/Descent Gradient ALWAYS > (HIGHER) than Climb/Descent Angle
➢ Climb/Descent Angle → air mass related
➢ Flight-path Angle → ground related
➢ TOD will increase ↑ by 20% for each 10% increase ↑ in mass
➢ TOD will increase ↑ by 20% for a tailwind component of 10% of the lift off speed
UNACCELERATED CLIMB
➢ W cos(y) = Lift
➢ Thrust = Drag + W sin(y)
EXCESS THRUST = THRUST – DRAG
➢ Vx – speed best climb angle, max excess thrust, max value of the vector; W x sin(Y),
increases with altitude
➢ Vy – speed best rate of climb, max excess power, decreases with altitude
➢ Positive Climb: Vx ALWAYS < (LESS) Vy
➢ These Vx and Vy are worse with flaps.
➢ Rate of Descent: Depends on Velocity
