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A project supported by AIRBUS and the CAAC
Date of the module
Mach
n
FL 350
given weight : 60t
Example : A320 200
Mmin= 0.65 Mmax> MMO (0.84)
1.3 g
6 - Buffet limit
1.3 g corresponds to
a bank angle of 39°
A project supported by AIRBUS and the CAAC
Date of the module
Mach
n
Zp1
Mmin Mmax
n1
given weight
At given altitude
and given weight,
there is a maximum
admissible load factor
6 - Buffet limit
nmax
M
This Mach allows the
higher load factor margin
with buffet limit
A project supported by AIRBUS and the CAAC
Date of the module
Mach
n
FL 350
Mmax> MMO
given weight : 60t
Example : A320 200
1.3 g
Mmin= 0.65 0.78
1.8 g
6 - Buffet limit
A project supported by AIRBUS and the CAAC
Date of the module
Mach
n
at Zp1
Zp1< Zp2< Zp3
1.3 g
Mmin Mmax
given weight
Effect of altitude : nmax decreases
lift range decreases
6 - Buffet limit
at Zp2
Zp3
At Zp3 nmax = 1.3g
A project supported by AIRBUS and the CAAC
Date of the module
 1.3 g buffet limited altitude :
 at this altitude, nmax = 1.3 g (or bank angle =
39°)
 above this altitude, maneuvers of less
than 1.3 g will create buffeting
 when the weight decreases (burn off),
1.3 g buffet limited altitude increases
6 - Buffet limit
A project supported by AIRBUS and the CAAC
Date of the module
Zp
weights
Optimum altitude
ISA or below
ISA + 20
Max cruise altitude
1.3 g buffet limit
 The maximum operational
altitude is the lowest
of :
 max cruise altitude
 1.3 g buffet limited
altitude
6 - Buffet limit
A project supported by AIRBUS and the CAAC
Date of the module
7. ATC Requirment
 Flight Level
 Final chosen maximum flight altitude is a adjacent
flight level
A project supported by AIRBUS and the CAAC
Date of the module
1 - Direct operating cost
2 - Specific range
3 - All engines operating cruise speeds
4 - Altitude optimisation
5 - Maximum cruise altitude
6 - Buffet limit
7 – ATC requirment
8 - Cruise optimisation
Table of Contents
A project supported by AIRBUS and the CAAC
Date of the module
 Step climb cruise :
 Ideal cruise should follow
the optimum altitude
 but ATC constraints
require level flight cruise
 airlines have to comply
with
Zp
weight
Optimum altitude
several level flights close to
the optimum altitude
8 - Cruise optimisation
A project supported by AIRBUS and the CAAC
Date of the module
Zp
weight
4000 ft
 Above FL290 :
 FL separation = 2000 ft
  step climb = 4000 ft
(except RVSM zones)
Optimum altitude
8 - Cruise optimisation
2000 ft from optimum altitude
:
Rs = 99% Rsmax
Long flight : 2 or 3 steps
Max cruise altitude can delay
the first climb...
A project supported by AIRBUS and the CAAC
Date of the module
Table of Contents
1 - Cruise
2 - Climb
3 - Descent
4 - Holding
A project supported by AIRBUS and the CAAC
Date of the module
1 - Climb angle and rate of climb
2 - Climb in operation
3 - Influencing parameters
4 - Cabin climb
Table of Contents
A project supported by AIRBUS and the CAAC
Date of the module
1 - Climb angle and rate of climb
2 - Climb in operation
3 – Influencing parameters
4 - Cabin climb
Table of Contents
A project supported by AIRBUS and the CAAC
Date of the module
TAS
rate of climb
TASmax TASRCmax
Maximum
rate of climb
Given
m, thrust, operationnal data
max = maximum air
climb gradient
1 - Climb angle and rate of climb
A project supported by AIRBUS and the CAAC
Date of the module
g
a <g
GS
a
TAS Rate of Climb
RC
1 - Climb angle and rate of climb
Headwind
A project supported by AIRBUS and the CAAC
Date of the module
1 - Climb angle and rate of climb
2 - Climb in operation
3 – Influencing parameters
4 - Cabin climb
Table of Contents
A project supported by AIRBUS and the CAAC
　
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