Operation
DA 40 NG AFM
Limitations
2.7 MASS (WEIGHT)
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Value |
Mass (Weight) |
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Maximum take-off mass |
1280 kg |
2822 lb |
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Maximum landing mass |
1216 kg |
2681 lb |
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Minimum flight mass |
940 kg |
2072 lb |
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Maximum zero fuel mass |
1200 kg |
2646 lb |
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' Standard: |
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Max. load in baggage compartment |
30 kg |
66 lb |
'(between rear seats and baggage frame)
' |
Max. load in baggage tube compartment (if installed) |
5 kg |
11 lb |
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' |
Max. load in short baggage extension |
15 kg |
33 lb |
' |
(if OÄM 40-331 is installed) |
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'Extended baggage compartment
'(if OÄM 40-164 is installed):
' |
Max. load in cockpit baggage compartment |
45 kg |
100 lb |
'(behind rear seats)
' |
Max. load in extended baggage compartment |
18 kg |
40 lb |
'(behind cabin baggage compartment)
' |
Max. load in cockpit baggage compartment and |
45 kg |
100 lb |
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extended baggage compartment |
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WARNING
Exceeding the mass limits will lead to an overstressing of the airplane as well as to a degradation of flight characteristics and flight performance.
NOTE
The maximum landing mass is the highest mass for landing conditions at the maximum descent velocity. This condition was used in the strength calculations to determine the landing gear loads during a particularly hard landing.
Page 2 - 14 |
Rev. 1 |
15-Mar-2011 |
EASA |
Doc. # 6.01.15-E |
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approved |
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DA 40 NG AFM
Operation
Limitations
NOTE
In some countries the beginning of a flight is defined by starting the engine. In those countries a maximum ramp mass
4 kg (9 lb) above the maximum take-off mass is approved.
At the time of lift-off the maximum permitted take-off mass must not be exceeded.
NOTE
The maximum zero fuel mass is the highest mass with empty fuel tanks.
Doc. # 6.01.15-E |
Rev. 1 |
15-Mar-2011 |
EASA |
Page 2 - 15 |
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approved |
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Operation
DA 40 NG AFM
Limitations
2.8 CENTER OF GRAVITY
Datum Plane
The Datum Plane (DP) is a plane which is normal to the airplane’s longitudinal axis and in front of the airplane as seen from the direction of flight. The airplane’s longitudinal axis is parallel with the upper surface of a 600:31 wedge which is placed on top of the rear fuselage in front of the vertical stabilizer. When the upper surface of the wedge is aligned horizontally, the Datum Plane is vertical. The Datum Plane is located 2.194 meter
(86.38 in) forward of the most forward point of the root rib on the stub wing.
Center of Gravity Limitations
The center of gravity (CG position) for flight conditions must be between the following limits:
Most forward CG:
2.40 m (94.5 in) aft of DP from 940 kg to 1080 kg (2072 lb to 2381 lb) 2.46 m (96.9 in) aft of DP at 1280 kg (2822 lb)
linear variation between these values
Most rearward CG:
2.53 m (99.6 in) aft of DP from 940 kg (2072 lb) to1280 kg (2822 lb)
WARNING
Exceeding the center of gravity limitations reduces the controllability and stability of the airplane.
Page 2 - 16 |
Rev. 1 |
15-Mar-2011 |
EASA |
Doc. # 6.01.15-E |
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approved |
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DA 40 NG AFM
Operation
Limitations
2.9 APPROVED MANEUVERS
The airplane is to be operated in the Normal Category in accordance with JAR 23.
Approved Maneuvers
1)All normal flight maneuvers;
2)Stalling (with the exception of dynamic stalling); and
3)Lazy Eights, Chandelles, as well as steep turns and similar maneuvers, in which an angle of bank of not more than 60° is attained.
CAUTION
Aerobatics, spinning, and flight maneuvers with more than 60° of bank are not permitted in the Normal Category.
CAUTION
Intentional negative g-maneuvers are not permitted.
Doc. # 6.01.15-E |
Rev. 1 |
15-Mar-2011 |
EASA |
Page 2 - 17 |
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approved |
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