Operating Limitations	DA 42 NG AFM

Audible Warning Alerts

Audible warning	Meaning / Cause
alert

GEAR

RETRACTED CHIME TONE

(repeating)

Resounds if the landing gear is retracted while the flaps move into position LDG or when the power lever is placed in a position below 25%.

2.7 MASS (WEIGHT)

Value	Mass (Weight)
Minimum flight mass	1510 kg	3329 lb
Maximum take-off mass	1900 kg	4189 lb
Maximum zero fuel mass	1765 kg	3891 lb
Maximum landing mass (see NOTE below)	1805 kg	3979 lb
Max. load in nose baggage compartment	30 kg	66 lb
(in fuselage nose)
Max. load in cabin baggage compartment	45 kg	100 lb
(behind rear seats)
Max. load in baggage extension	18 kg	40 lb
(behind cabin baggage compartment)
Max. load, cabin baggage compartment and baggage	45 kg	100 lb
extension together

WARNING

Exceeding the mass limits will lead to overstressing of the airplane as well as to degradation of flight characteristics and flight performance.

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DA 42 NG AFM	Operating Limitations

NOTE

In some countries the beginning of a flight is defined by starting the powerplant. In those countries a ramp mass of maximal MTOM + 8 kg (MTOM + 18 lb) is approved. At the time of lift-off the maximum permitted take-off mass must not be exceeded.

NOTE

A landing with a mass between 1805 kg (3979 lb) and

1900 kg (4189 lb) is admissible. It constitutes an abnormal operating procedure. A "Hard Landing Check" is only required after a hard landing, regardless of the actual landing mass.

EASA

Doc. No. 7.01.15-E Rev. 1 18-Feb-2009 Page 2 - 17 approved

Operating Limitations	DA 42 NG AFM

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 floor of the nose baggage compartment. When the floor of the nose baggage compartment is aligned horizontally, the datum plane is vertical. The datum plane is located 2.196 meters (86.46 in) forward of the most forward point of the root rib on the stub wing (refer to figure in Section 6.2).

Center of Gravity Limitations

The center of gravity (CG position) for flight conditions must be between the following limits:

Most forward flight CG:

2.357 m (92.80 in) aft of datum plane at 1510 kg (3329 lb)

2.418 m (95.20 in) aft of datum plane at max. take-off mass (see Section 2.7) linear variation in between

Most rearward flight CG:

2.460 m (96.85 in) aft of datum plane at 1510 kg (3329 lb)

2.480 m (97.64 in) aft of datum plane at 1700 kg (3748 lb)

2.480 m (97.64 in) aft of datum plane at max. take-off mass (see Section 2.7) linear variation in between

Refer to Section 6.4.4 for a graphical illustration of the CG limitations.

WARNING

Exceeding the center of gravity limitations reduces the

	controllability and stability of the airplane.
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DA 42 NG AFM	Operating Limitations

2.9 APPROVED MANEUVERS

The airplane is certified 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. Stalling with asymmetric power or one engine inoperative is not permitted.

CAUTION

Intentional negative g- maneuvers are not permitted.

EASA

Doc. No. 7.01.15-E Rev. 1 18-Feb-2009 Page 2 - 19 approved