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A330/A340 FLEET PER-FPL-FLP-FTK P 26/26
FCOM 19 AUG 10
PERFORMANCE
GO AROUND
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A330/A340 FLIGHT CREW
OPERATING MANUAL
PERFORMANCE
GO AROUND
PRELIMINARY PAGES - TABLE OF CONTENTS
A330/A340 FLEET PER-GOA-PLP-TOC P 1/2
FCOM 19 AUG 10
PER-GOA-PLP PRELIMINARY PAGES
TABLE OF CONTENTS......................................................................................................................................1/2
PER-GOA-GEN GENERAL
GENERAL............................................................................................................................................................1/2
PROCEDURE......................................................................................................................................................1/2
PER-GOA-ACG APPROACH CLIMB LIMITING WEIGHT
PER-GOA-ACG-NOR NORMAL
CONF 2............................................................................................................................................................... 1/4
CONF 3............................................................................................................................................................... 3/4
PER-GOA-ACG-CAT CATII
CAT II CONF 2................................................................................................................................................... 1/2
CAT II CONF 3................................................................................................................................................... 2/2
A330/A340 FLIGHT CREW
OPERATING MANUAL
PERFORMANCE
GO AROUND
PRELIMINARY PAGES - TABLE OF CONTENTS
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A330/A340 FLEET PER-GOA-PLP-TOC P 2/2
FCOM 19 AUG 10
A330/A340 FLIGHT CREW
OPERATING MANUAL
PERFORMANCE
GO AROUND
GENERAL
A330/A340 FLEET PER-GOA-GEN P 1/2
FCOM 19 AUG 10
GENERAL
Applicable to:
In the go around configuration corresponding to the all engine procedure, the minimum steady
gradient one engine inoperative required by the regulations is 2.7 %, at a speed not exceeding 1.4
Vs. This requirement is also called approach climb performance by regulations.
The following tables allow to determine the go around limiting weight which satisfies the required
gradient with the certified go around configurations 3 and 2.
The required gradient of 2.7 % is considered at the airport reference altitude. The power setting
is “GO AROUND” thrust with the air conditioning ON. The speed is 1.23 Vs of the specified
configuration. For the occasional cases where approach climb performance is found restrictive, a
correction is given for an increased speed, up to 1.4 Vs.
Note: Landing climb performance (4 engines running) is never limiting.
GENERAL
Applicable to: ,
In the go around configuration corresponding to the all engine procedure, the minimum steady
gradient one engine inoperative required by the regulations is 2.1 %, at a speed not exceeding 1.4
Vs. This requirement is also called approach climb performance by regulations.
The following tables allow to determine the go around limiting weight which satisfies the required
gradient with the certified go around configurations 3 and 2.
The required gradient of 2.1 % is considered at the airport reference altitude. The power setting
is “GO AROUND” thrust with the air conditioning ON. The speed is 1.23 Vs of the specified
configuration. For the occasional cases where approach climb performance is found restrictive, a
correction is given for an increased speed, up to 1.4 Vs.
Note: Landing climb performance (2 engines running) is never limiting.
PROCEDURE
Applicable to:
According to airport pressure altitude and temperature determine if the slats/flaps setting must be
restricted as a function of the landing weight, in order to meet the go around gradient requirement of
2.7 %.
Establish the final approach configuration with one more step of flaps. If the approach is interrupted,
retract the flaps by one step during the go-around.
A330/A340 FLIGHT CREW
OPERATING MANUAL
PERFORMANCE
GO AROUND
GENERAL
A330/A340 FLEET PER-GOA-GEN P 2/2
FCOM 19 AUG 10
Note: 1. If circumstances dictate, landing may be made at a weight corresponding to the
maximum structural takeoff weight. (Refer to 99 Duref Cible FCOM).
2. When icing conditions are predicted during the flight and TAT is 10 °C or below and there
is evidence of significant ice accretion, to take into account ice formation on the non
heated structure :
decrease ‐ the approach climb limiting weight by 5 %
　
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