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A330/A340 FLEET PRO-SPO-25-30 P 1/2
FCOM 19 AUG 10
PROCEDURES
Applicable to: ALL
PREFLIGHT
VMO/MMO with landing gear down is 255 kt/M .60. In the avionics compartment, on 808VU, the
VMO-MMO switch must be set to the “L/G DOWN” position.
A330/A340 FLIGHT CREW
OPERATING MANUAL
PROCEDURES
SPECIAL OPERATIONS
FLIGHT WITH GEAR DOWN - PROCEDURES
Intentionally left blank
A330/A340 FLEET PRO-SPO-25-30 P 2/2
FCOM 19 AUG 10
A330/A340 FLIGHT CREW
OPERATING MANUAL
PROCEDURES
SPECIAL OPERATIONS
FLIGHT WITH GEAR DOWN - PERFORMANCE
A330/A340 FLEET PRO-SPO-25-40 P 1/22
FCOM 19 AUG 10
GENERAL
Applicable to: ALL
Consider the increase in drag to determine the takeoff weight and fuel consumption.
CONF 1 + F is the recommended takeoff configuration.
Note: Takeoff with tailwind is not recommended.
Penalties on takeoff performance affect second segment gradient, final takeoff, and enroute
conditions. The takeoff weight to be retained is the most limiting of these three conditions.
SECOND SEGMENT GRADIENT CONDITION
Applicable to:
The RTOW charts, or the quick reference tables, give the basic information for normal takeoff. To
simplify, a constant weight reduction is applied, whatever the limitation. This weight reduction covers
the most critical case presented, for flying over an obstacle.
Takeoff configuration 1 + F 2 3
Weight reduction 22 % 19 % 19 %
METHOD
Use the RTOW chart or the quick reference tables to define the maximum takeoff weight for the
conditions on the airport (temperature, pressure, wind, runway,...), then apply the above weight
reduction.
SECOND SEGMENT GRADIENT CONDITION
Applicable to: ,
The RTOW charts, or the quick reference tables, give the basic information for normal takeoff. To
simplify, a constant weight reduction is applied, whatever the limitation. This weight reduction covers
the most critical case presented, for flying over an obstacle.
Takeoff configuration 1 + F 2 3
Weight reduction 21 % 16 % 15 %
METHOD
Use the RTOW chart or the quick reference tables to define the maximum takeoff weight for the
conditions on the airport (temperature, pressure, wind, runway,...), then apply the above weight
reduction.
A330/A340 FLIGHT CREW
OPERATING MANUAL
PROCEDURES
SPECIAL OPERATIONS
FLIGHT WITH GEAR DOWN - PERFORMANCE
A330/A340 FLEET PRO-SPO-25-40 P 2/22
FCOM 19 AUG 10
FINAL TAKEOFF CONDITION
Applicable to:
The final takeoff speed is VLS + 12
Use the graph below to determine the maximum takeoff weight associated with the final takeoff
condition.
FINAL TAKEOFF CONDITION
Applicable to: ,
The final takeoff speed is VLS + 11
A330/A340 FLIGHT CREW
OPERATING MANUAL
PROCEDURES
SPECIAL OPERATIONS
FLIGHT WITH GEAR DOWN - PERFORMANCE
A330/A340 FLEET PRO-SPO-25-40 P 3/22
FCOM 19 AUG 10
Use the graph below to determine the maximum takeoff weight associated with the final takeoff
condition.
EN-ROUTE CONDITION
Applicable to:
Retain the lowest weight according to the most limiting condition (second segment or final takeoff).
Use the en-route net flight path (Refer to PRO-SPO-25-40 EN ROUTE NET FLIGHT PATH) to check
that, in case of engine(s) failure(s), the aircraft can clear the terrain on the route by 1 000 ft (climbing)
or 2 000 ft (descending). If necessary, reduce the takeoff weight. Read the speeds corresponding to
this weight in the RTOW chart or in the quick reference tables.
EN-ROUTE CONDITION
Applicable to: ,
Retain the lowest weight according to the most limiting condition (second segment or final takeoff).
Use the en-route net flight path (Refer to PRO-SPO-25-40 EN ROUTE NET FLIGHT PATH) to check
that, in case of engine failure, the aircraft can clear the terrain on the route by 1 000 ft (climbing) or
A330/A340 FLIGHT CREW
OPERATING MANUAL
PROCEDURES
SPECIAL OPERATIONS
FLIGHT WITH GEAR DOWN - PERFORMANCE
A330/A340 FLEET PRO-SPO-25-40 P 4/22
FCOM 19 AUG 10
2 000 ft (descending). If necessary, reduce the takeoff weight. Read the speeds corresponding to this
weight in the RTOW chart or in the quick reference tables.
GO AROUND PERFORMANCE
Applicable to: ALL
Refer to PER-GOA-GEN GENERAL for go around requirements.
Further decrease the basic limiting weight by 12 %.
FLIGHT PLANNING
Applicable to:
MAXIMUM ALTITUDE
In order to ensure that there is at any moment of the flight a minimum range of 20 kt between
VLS and the maximum speed (limited by thrust or VMO/MMO), the aircraft must remain below the
following profile.
　
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