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FIRST SEGMENT SECOND SEGMENT THIRD SEGMENT FINAL SEGMENT
Minimum
climb gradient Twin 0.0% 2.4% - 1.2%
(N-1) engines Quad 0.5% 3.0% - 1.7%
Start when VLOF reached Gear fully retracted Acceleration height reached (min 400 feet) En route configuration Achieved
Slats / Flaps Configuration Engine rating Speed reference Landing gear Weight reference Takeoff TOGA/FLEX VLOF Retraction Weight at the start of the gear retraction Takeoff TOGA/FLEX V2 Retracted Weight when the gear is fully retracted Slats / Flaps retraction TOGA/FLEX Acceleration from V2 to Green Dot Retracted Weight at the start of the acceleration segment Clean MCT Green Dot Retracted Weight at the end of the acceleration segment
Ground effect Without Without Without Without
Table C4: Takeoff Segment Characteristics
4.1.3. Minimum and Maximum Acceleration Heights
4.1.3.1. Minimum Acceleration Height
“JAR/FAR 25.111 (c)(2) The aeroplane must reach V2 before it is 35 ft above the takeoff surface and must continue at a speed not less than V2 until it is 400 ft above the takeoff surface”
“JAR/FAR 25.111
(c)(3) At each point along the takeoff flight path, starting at the point at which the aeroplane reaches 400 ft above the takeoff surface, the available gradient of climb may not be less than:
.
1.2% for a two-engined airplane
.
1.7% for a four-engined airplane”
So, below 400 feet, the speed must be maintained constant to a minimum of V2. Above 400 feet, the aircraft must fulfill a minimum climb gradient, which can be transformed into an acceleration capability in level flight. Therefore, the regulatory minimum acceleration height is fixed to 400 feet above the takeoff surface.
Nevertheless, during the acceleration segment, obstacle clearance must be ensured at any moment. Therefore, the operational minimum acceleration height is equal to or greater than 400 feet (Figure C16).
4.1.3.2. Maximum Acceleration Height
The Maximum Takeoff Thrust (TOGA) is certified for use for a maximum of 10 minutes, in case of an engine failure at takeoff, and for a maximum of 5 minutes with all engines operating.
The Maximum Continuous Thrust (MCT), which is not time-limited, can only be selected once the enroute configuration is achieved (i.e. when the aircraft is in clean configuration at green dot speed).
As a result, the enroute configuration (end of the third segment) must be achieved within a maximum of 10 minutes after takeoff, thus enabling the determination of a maximum acceleration height (Figure C16).
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