Mass and Balance	DA 42 NG AFM

6.4.3 CALCULATION OF LOADING CONDITION

NOTE

If the optional de-icing system (OÄM 42-053) is installed, the following must be observed:

The consumption of fuel causes a forward movement of the

CG. The consumption of de-icing fluid causes a rearward movement of the CG. Depending on the fuel flow and de-icing fluid flow, the overall movement of the CG can be a forward or a rearward movement. In order to cover all possible cases, the following table must be completed twice: with (as shown in the example) and without considering the on-board de-icing fluid. All four CG positions (fuel tank full/empty, de-icing fluid tank full/empty) must fall into the permitted area.

1.Complete the form on the next page.

2.Divide the total moments from rows 8 and 11 by the related total mass to obtain the CG positions.

In our example: empty tanks:	3958.7 kgm / 1655.5 kg = 2.391 m
	343,717 in.lb / 3651.0 lb = 94.14 in
full tanks:	4645.7 kgm / 1898.5 kg = 2.447 m
	403,356 in.lb / 4187.0 lb = 96,335 in

3.Locate the values in the diagram in Section 6.4.4 - PERMISSIBLE CENTER OF

GRAVITY RANGE. If the CG positions and related masses fall into the permitted area, the loading condition is allowable.

Our example shows allowable loading conditions.

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DA 42 NG AFM	Mass and Balance

					DA 42 NG			Your DA 42 NG
	CALCULATION OF				(Example)
	LOADING CONDITION			Mass		Moment		Mass		Moment
					[kg]	[kgm]		[kg]		[kgm]
					[lb]	[in.lb]		[lb]		[in.lb]
1.	Empty mass (from Mass and			1450		3488.0
	Balance Report)			3197		302,747
2.	Front seats			160		368.0
	Lever arm: 2.30 m (90.6 in)			353		31,982
3.	Rear seats			0		0.0
	Lever arm: 3.25 m (128.0 in)			0		0,0
4.	Nose baggage compt.			0		0.0
	Lever arm: 0.60 m (23.6 in)			0		0,0
5.	Cabin baggage compt.			10		38.9
	Lever arm: 3.89 m (153.1 in)			22		3,368
6.	Baggage extension			8		36.3
	Lever arm: 4.54 m (178.7 in)			18		3,217
7.	De-Icing fluid (if installed; see
	NOTE on previous page)			27.5		27.5
	(1.1 kg/liter) (9.2 lb/US gal)			61		2,403
	Lever arm: 1.00 m (39.4 in)
8.	Total mass & total moment			1655.5		3958.7
	with empty fuel tanks
				3651		343,717
	(Total of 1.-7.)
9.	Usable fuel, main tanks			159		418.2
	(0.84 kg/liter) (7.01 lb/US gal)
				351		36,329
	Lever arm: 2.63 m (103.5 in)
10.	Usable fuel, auxiliary tanks (if
	installed)			84		268.8
	(0.84 kg/liter) (7.01 lb/US gal)			185		23,310
	Lever arm: 3.20 m (126.0 in)
11. Total mass & total moment				1898.5		4645.7
	with fuel & de-icing fluid
				4187		403,356
	(Total of 8. through 10.)
Doc. No. 7.01.15-E			Rev. 1		18-Feb-2009					Page 6 - 11

Mass and Balance	DA 42 NG AFM

The CG's shown in the following diagrams are those from the example in Section

6.4.3 - CALCULATION OF LOADING CONDITION, rows 8 and 11.

6.4.4 PERMISSIBLE CENTER OF GRAVITY RANGE

[ Fl lM ib ga] thss

[in]	98									2.50
Center of Gravity Position	94 95 96 97									2.40 2.45	Center of Gravity Position [m]
	93									2.35
		1900	1850	1800	1750	1700	1650	1600	1550
	92									1500
			FlightMass[kg]

Page 6 - 12	Rev. 1	18-Feb-2009	Doc. No. 7.01.15-E

DA 42 NG AFM	Mass and Balance

The flight CG position must be within 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

Doc. No. 7.01.15-E	Rev. 1	18-Feb-2009	Page 6 - 13