The following concerns to Airbus
3.3. Go-Around Performance Requirements
A minimum climb gradient must be observed, in case of a go-around. The
minimum air climb gradients depend on the aircraft type.
3.3.1. Approach Climb
JAR 25.121 Subpart B
FAR 25.121 Subpart B
This corresponds to an aircraft’s climb capability, assuming that one engine is
inoperative. The “approach climb” wording comes from the fact that go-around
performance is based on approach configuration, rather than landing configuration.
For Airbus fly-by-wire aircraft, the available approach configurations are CONF 2 and
3.
3.3.1.1. Aircraft Configuration
•
One engine inoperative
•
TOGA thrust
•
Gear retracted
•
Slats and flaps in approach configuration (CONF 2 or 3 in most cases)
•
1.23 VS1g ≤V ≤1.41 VS1g and check that V ≥ VMCL
3.3.1.2. Requirements
The minimum gradients to be demonstrated:
Approach Climb
Minimum
climb gradient
one engine out
Twin 2.1%
Quad 2.7%
An approach configuration can be selected, as long as the stall speed VS1g of this configuration does not exceed 110% of VS1g of the related “all-engines-operating“ landing configuration.
3.3.2. Landing Climb
JAR 25.119 Subpart B
FAR 25.119 Subpart B
The objective of this constraint is to ensure aircraft climb capability in case of a
missed approach with all engines operating. The “Landing climb” wording comes from
the fact that go-around performance is based on landing configuration. For Airbus
FBW, the available landing configurations are CONF 3 and FULL.
3.3.2.1. Configuration
•
N engines
•
Thrust available 8 seconds after initiation of thrust control movement from
minimum flight idle to TOGA thrust
•
Gear extended
•
Slats and flaps in landing configuration (CONF 3 or FULL)
•
1.13 VS1g ≤ V ≤ 1.23 VS1g and check that V ≥ VMCL
.
3.3.2.2. Requirements
The minimum gradient to be demonstrated is 3.2% for all aircraft types.
N engines
TOGA thrust
gear extended
landing configuration
minimum
gradient: 3.2%
For all Airbus aircraft, this constraint is covered by the approach climb
requirement. In its operational documentation (FCOM), Airbus publishes the
maximum weight limited by the approach climb gradient only. Landing climb
performance is found in the AFM