04 - MTOW v1

Maximum Take-Off Weight

MTOW



Maximum Take Off Weight



Calculating the MTOW



Take Off limitations



Optimization : Airbus philosophy

Maximum Take Off Weight

limitations

Structural : Aircraft’s features Company’s needs

Ground Gr ound installations : Runway’s characteristics Obstacles

 MTOW

Performance : T.O. Parameters Mother Nature’s influence

T/O optimization

MTOW



Maximum Take Off Weight



Calculating the MTOW



Take Off limitations



Optimization : Airbus philosophy

Calculating the MTOW

Operating speeds : 0.84



T/O chosen parameters :

V1 VR

1

•

V2 1.13 1.35, 1.4, 1.5 V Flap setting, V1, V2. They influence performance. S

•

Range :

according to the type of aircraft.



flaps : Conf 1+F, Conf 2, Conf 3



V1 : position around V R  (ground phase)



V2 : position around V S (in-flight phase) Remember: V1 Vr 1.13 Vs1g V2 according to the regulation.

Calculating the MTOW 



T/O chosen parameters : •

Flap setting, V1, V2. They influence performance.

•

Range : 

flaps : Conf 1+F, Conf 2, Conf 3



V1 : position around V R  (ground phase)



V2 : position around V S (in-flight phase)

Principle : •

At given Conf (and all sustained parameters), Take Off Weight limitations are set as a function function of V1/VR  and V2/VS.

Calculating the MTOW 



T/O chosen parameters : •

Flap setting, V1, V2. They influence performance.

•

Range : 

flaps : Conf 1+F, Conf 2, Conf 3



V1 : position around V R  (ground phase)



V2 : position around V S (in-flight phase)

Principle : •

At given Conf (and all sustained parameters), Take Off Weight limitations are set as a function function of V1/VR  and V2/VS.

•

MTOW is calculated for a fixed V 2 and a full range of V 1 , ( or fixed V1 and full range of V 2 ).

Calculating the MTOW 

T/O chosen parameters : •

Airport :

Runway :

Obstacle :

Sea level

TORA = 2300 m

Distance = 6450 m

•

Temperature Range : = 20 °C

TODA = 2300 m

Height = 260 ft

no wind

ASDA = 2400 m

Flap setting, V1, V2. They influence performance.



flaps : Conf 1+F, Conf 2, Conf 3 no slope



V1 : position around V R  (ground phase)

Aircraft :



Conf 1+F, V2/VS = 1.21, 0.84 < VA320-211, phase) 2 : position around V S (in-flight

V1