WEIGHT AND CENTRE OF GRAVITY

1 Presentation Register of weight and centre of gravity Weighing procedure Weight and centre of gravity breakdown List of equipment Original issue: 31...

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CAP 10C

6. WEIGHT AND CENTRE OF GRAVITY

6.1

Presentation................................................................ 6-3

6.2

Register of weight and centre of gravity................... 6-3

6.3

Weighing procedure ................................................... 6-3

6.4

Weight and centre of gravity breakdown .................. 6-5

6.5

List of equipment........................................................ 6-12

Original issue: 31 January 2002 Revision: 0

Document: 1000809 GB Page 6-1 WEIGHT AND CENTRE OF GRAVITY

CAP 10C

Original issue: 31 January 2002 Revision: 0

Document: 1000809 GB Page 6-2 WEIGHT AND CENTRE OF GRAVITY

CAP 10C

6. WEIGHT AND CENTRE OF GRAVITY

6.1 PRESENTATION This section is approved by the French Airworthiness Authorities (D.G.A.C. Direction Générale de l'Aéronautique Civile). It contains necessary and useful information to fly the aircraft in complete safety.

6.2 REGISTER OF WEIGHT AND CENTRE OF GRAVITY Changes (in structure or equipment) that affect the weight and centre of gravity are listed in the A/C Individual I n s p e c t i o n R e c o r d (I.I.R.) to allow for permanent monitoring of aircraft changes throughout its service life.

6.3 WEIGHING PROCEDURE Longitudinal levelling: left horizontal canopy rail. The weighing procedure is described in the A / C I n d i v i d u a l I n s p e c t i o n Record. The aircraft weighing and centre of gravity report is included in the A / C I n d i v i d u a l I n s p e c t i o n R e c o r d (IIR).

Original issue: 31 January 2002 Revision: 0

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REGISTRE INDIVIDUEL DE CONTROLE PROCES VERBAL DE PESEE ET CENTRAGE Distance du C.G. (m)

A (c.a.m.) = 1,500 D= d=

REF

D P1

Poids lu

Tare

Roue gauche Roue - aux roues principales droite d1 = P2 x D / (P2 + P1) = Roue AR ………

A

d

Avion : CAP10C N° de série : Poids à vide + huile moteur (kg)

Feuille : Date : Poids net

……… +…...……

+……..…

P2

- à la référence Niveau : rail horizontal de verrière Poids à vide = P2 + P1 = ……….. Référence : bord d'attaque de voilure à 1,30 m du plan de d2 = d1 – d = ……… symétrie Poids à vide (kg) Bras de levier (m) Distance Moment à vide (par rapport à la référence) m.kg Centrage en % de la corde C.G. à vide aérodynamique moyenne Résultats (c.a.m.)

Avant = 3 litres

2,16 0,72

- 0,243 1,26

- 0,525 0,907

Arrière = 1 litre

Centrage = d2 ⋅100 = 1,500 ......... ⋅100 = … % 1,500

Limites de centrage et de chargement :

850

Masse (kg)

800

Catégorie U A

750 700 650 600 550

Centrage (%) 20 – 30 20 – 26

Masse (kg) 830 780

500

18 19 20 21 22 23 24 25 26 27 28 29 30 31 32 Centrage (%)

Visa de contrôle :

Visa de contrôle : GSAC

CAP 10C

Document: 1000809 GB Page 6-4 WEIGHT AND CENTRE OF GRAVITY

Pour information : essence résiduelle comprise dans la masse à vide Poids (kg) Bras de levier (m) Moment par rapport à la référence (m.kg)

6.3.1 Example of weighing and centre of gravity report

Original issue: 31 January 2002 Revision: 0

Firme : Usine :

CAP 10C

6.4 WEIGHT AND CENTRE OF GRAVITY BRE AKDOWN The centre of gravity reference is defined by the leading edge of the reference profile located 1.30 m from the aircraft plane of symmetry. The reference chord length is 1.50 m. C of G limit Category U Category A Front C of G 0.30 m 20 % 0.30 m 20 % Rear C of G 0.45 m 30 % 0.39 m 26 % 6.4.1 Method - Assess weights. Make certain that the maximum weight is not exceeded. - Calculate the centre of gravity. Make certain that balance is within limits. - Locate the point (total weight and centre of gravity) on the graph. The point will then be within the weight and centre of gravity envelope. - Loading is acceptable if the point remains in the weight and centre of gravity envelope throughout the flight. To make certain that the point remains within the envelope throughout the flight, the pilot will calculate the centre of gravity at the end of the flight, taking the fuel consumed into account.

Original issue: 31 January 2002 Revision: 0

Document: 1000809 GB Page 6-5 WEIGHT AND CENTRE OF GRAVITY

CAP 10C

6.4.2 Loading category A Weight Lever arm (kg) (m) Empty weight a1 b1 Pilot a2 0,55 to 0,65 Passenger a3 0,55 to 0,65 Usable fuel FWD tank a4 - 0,243 Totals weight and moment A = Σan B = C/A Balance (B/1.5) x 100 = in kg, m and m.kg

Moment (m.kg) c1 = a1 x b1 c2 = a2 x b2 c3 = a3 x b3 c4 = a4 x b4 C = Σcn %

Balance must be between 20 % and 26 % (category A). Maximum weight: 780 kg (1 720 lb) Empty weight (a1): use of aircraft data in its real configuration. Take residual quantities (unusable) of oil and fuel into account. The empty weight (a1), the lever arm (b1) and the moment (c1) must be taken from the aircraft weight and centre of gravity report in the A/C Individual Inspection Record (I.I.R - R.I.C.). Weight of fuel: use 0.72 kg/litre (6 lb/gal) Hourly consumption in aerobatics: about 44 l/h Moment = weight x lever arm A: sum of a1 to a4 C: sum of c1 to c4

Original issue: 31 January 2002 Revision: 0

Document: 1000809 GB Page 6-6 WEIGHT AND CENTRE OF GRAVITY

CAP 10C

850 800

Weight (kg)

750 700

Cat. A

650 600 550 500 16

18

20

22

24

26

28

30

32

Balance (%)

6.4.3 Example of maximum forward balance in category A

CAUTION An extremely light pilot, flying alone, with the main tank full, may reach the forward balance limit.

Weight Lever arm Moment kg m m.kg Empty weight 550 0.297 163.4 Pilot 83 0.6 49.8 Passenger 0 0.6 0 Usable fuel FWD tank 40 - 0.243 - 9.72 Totals weight and moment 673 0.302 203,4 Balance (% of MAC) (B/1.5) x 100 = 20.2 % in kg, m and m.kg

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Document: 1000809 GB Page 6-7 WEIGHT AND CENTRE OF GRAVITY

CAP 10C

850 800

Weight (kg)

750 700

X

650 600 550 500 16

18

20

22

24

26

28

30

32

Balance (%)

6.4.4 Example of maximum aft balance in category A CAP10s with battery aft have higher aft balance. Pilot: 85 kg Co-pilot: 75 kg FWD tank: 40 kg (about 55 litres) Fuel consumption planned during flight: 25 kg (about 35 litres) Weight and centre of gravity assessment before flight: Weight Lever arm Moment kg m m.kg Empty weight 546.5 0.346 189.09 Pilot 85 0.6 51 Passenger 75 0.6 45 Usable fuel FWD tank 40 - 0.243 - 9.72 Totals weight and moment 746.5 0.3688 275.37 Balance (% of MAC) (B/1.5) x 100 = 24.59 % in kg, m and m.kg

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Document: 1000809 GB Page 6-8 WEIGHT AND CENTRE OF GRAVITY

CAP 10C

Weight and centre of gravity assessment after flight: Weight Lever arm Moment kg m m.kg Empty weight 546.5 0.346 189.09 Pilot 85 0.6 51 Passenger 75 0.6 45 Usable fuel FWD tank 15 - 0.243 -3.65 Totals weight and moment 721.5 0.39 281.44 Balance (% of MAC) (B/1.5) x 100 = 26.01 % in kg, m and m.kg 850 800

X

Weight (kg)

750

X

700 650 600 550 500 16

18

20

22

24

26

28

30

32

Balance (%)

6.4.5 Loading in category U Weight Lever arm (kg) (m) Empty weight a1 b1 Pilot a2 0.55 to 0.65 Passenger a3 0.55 to 0.65 Usable fuel FWD tank a4 - 0.243 Usable fuel AFT tank a5 1.26 Luggage a6 1.1 Totals weight and moment A = Σan B = C/A Balance (% of MAC) (B/1.5) x 100 = in kg, m and m.kg Original issue: 31 January 2002 Revision: 0

Moment (m.kg) c1 = a1 x b1 c2 = a2 x b2 c3 = a3 x b3 c4 = a4 x b4 c5 = a5 x b5 c6 = a6 x b6 C = Σcn %

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CAP 10C

Balance must be included between 20 % and 30 % (category U). Maximum weight: 830 kg (1 830 lb) Empty weight (a1): use of aircraft data in its real configuration. Take residual quantities (unusable) of oil and fuel into account. The empty weight (a1), the lever arm (b1) and moment (c1) must be taken from the aircraft weight and centre of gravity register. Weight of fuel: use 0.72 kg/litre (6 lb/gal) Standard hourly consumption: 180 hp to 2 700 rpm 14.5 Gal/h 135 hp to 2 450 rpm (75%) 11 Gal/h 117 hp to 2 350 rpm (65%) 8.5 Gal/h

55 l/h 42 l/h 32 l/h

REMARK The maximum load in the luggage hold is 50 kg evenly distributed. Moment = weight x lever arm A: sum of a1 to a6 C: sum of c1 to c6 850 800

Cat. U

Weight (kg)

750 700 650 600 550 500 16

18

20

22

24

26

28

30

32

Balance (%)

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Document: 1000809 GB Page 6-10 WEIGHT AND CENTRE OF GRAVITY

CAP 10C

6.4.6 Example of calculation in category U Pilot: 85 kg Co-pilot: 75 kg Réservoir avant: 25 kg (about 35 litres) AFT tank: 45 kg (about 63.5 litres) Luggage: 50 kg Fuel consumption planned during flight: 60 kg (about 83 litres) Weight and centre of gravity assessment before flight: Weight Lever arm Moment (kg) (m) (m.kg) Empty weight 550 0.297 163.35 Pilot 85 0.6 51 Passenger 75 0.6 45 Usable fuel FWD tank 25 - 0.243 -6,08 Usable fuel AFT tank 45 1.26 56,7 Luggage 50 1.1 55 Totals weight and moment 830 0.440 364.98 Balance (% of MAC) (0.440/1.5) x 100 = 29.32 % in kg, m and m.kg

Weight and centre of gravity assessment after flight: Lever arm Moment Weight (kg) (m) (m.kg) Empty weight 550 0.297 163.35 Pilot 85 0.6 51 Passenger 75 0.6 45 Usable fuel FWD tank 10 - 0.243 -2.43 Usable fuel AFT tank 0 1.26 0 Luggage 50 1.1 55 Totals weight and moment 770 0.405 311.92 Balance (% of MAC) (0.405/1.5) x 100 = 27.01 % in kg, m and m.kg

Original issue: 31 January 2002 Revision: 0

Document: 1000809 GB Page 6-11 WEIGHT AND CENTRE OF GRAVITY

CAP 10C

850

X 800

Cat. U

Weight (kg)

750

X

700 650 600 550 500 16

18

20

22

24

26

28

30

32

Balance (%)

6.5 LIST OF EQUIPMENT The list of airborne instruments is included in the A/C Individual Inspection Record (I.I.R.).

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Document: 1000809 GB Page 6-12 WEIGHT AND CENTRE OF GRAVITY

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