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At the MTOW (Maximum Take-Off Weight) of 472.5 kg

(with parachute - French regulation)

DYNAMIC 450 Wing

Standard Conditions 15°C - 1013,2 hPa

Engine Type

Rotax 582

Hirth 3701ES

Rotax 912

Rotax 912S

Rated Engine Power

48 kW

74 kW

59,6 kW

73,5 kW

Maximum Weight

472,5 kg

Stalling speed (VSO)

64 km/h

Maximum Shown speed

177 km/h

Maximum speed Never exceed (VNE)

160 km/h

Maximum speed of operation (VA)

110 km/h

Maximum speed in turbulent air (VC)

110 km/h

Horizontal maximum speed (VH)

126 km/h

138 km/h

130 km/h

138 km/h

Landing distance

75 m

Landing distance from 15 m

195 m

Minimum rate of fall

3,2 m/s

Speed of minimum rate of fall

70 km/h

Glide

ratio

6 6 6 6

Take-off Roll

85 m

75 m

80 m

75 m

Take-off Distance to 15 m

195 m

175 m

185 m

175 m

Rate of rise at 75 km/h

3 m/s

4 m/s

3,5 m/s

4 m/s

Roll Rate (45°/45°) at 75 km/h

3,5 s

Roll Rate (45°/45°) at VA

3 s

Cross-wind Limit

20 km/h

The performance data indicated are average performances. The model of airframe and the
presence of fairing can modify the data slightly.

MAUT – EN DYN 450

Edition : June 2005

Section : 2 - 02

Содержание DYNAMIC 450

Страница 1: ...WING INSTRUCTION AND MAINTENANCE MANUAL DYNAMIC 450 MAUT EN DYN 450 Edition June 2005 Copyright DTA DTA ULM AU Wing n Model Year...

Страница 2: ...DTA improves its production constantly and reserves the right to modify the specification the drawing the characteristics the model and or the equipment in the interests of Quality Assurance without i...

Страница 3: ...Diagram 2 01 2 02 2 03 JUNE 05 SECTION 3 USE Wing Assembly Disassembly Wing Photographs assembly disassembly Hang Bracket Position Washout Tension Dissymmetry Vibrations Modifications PREFLIGHT Wing...

Страница 4: ...he aircraft or to add elements by modifying the estimate of weight will check that the identification registration card is valid and that the identification markings a minimal height of 50 cm for Fran...

Страница 5: ...in fast flight and 30 cm from the front strut in slow flight in hang bracket position n 2 CF section 3 03 Note The person s who choose s to use a non DTA airframe will assume ALL the responsibilities...

Страница 6: ...3 Plan Views MAUT EN DYN 450 Edition June 2005 Section 1 03...

Страница 7: ...g cables Control frame Cross spar left Inner leading edge LEFT Lower side cable Upper side cable Lower rear cables Cross spar cable tensioning lever Keel Outer leading edge sleeve LEFT Washout tube Fr...

Страница 8: ...h 110 km h Horizontal maximum speed VH 115 km h 126 km h 138 km h 130 km h 138 km h Landing distance 70 m 70 m 70 m 70 m 70 m Landing distance from 15 m 190 m 190 m 190 m 190 m 190 m Minimum rate of...

Страница 9: ...h 110 km h 110 km h 110 km h Horizontal maximum speed VH 126 km h 138 km h 130 km h 138 km h Landing distance 75 m 75 m 75 m 75 m Landing distance from 15 m 195 m 195 m 195 m 195 m Minimum rate of fal...

Страница 10: ...LM is NOT designed for Aerobatic flight Inverted flight is completely prohibited Beyond these limits Bank 60 pitch 45 the loss of stability or of control structural failure or tumbling could occur Koc...

Страница 11: ...the wing a little dihedral lock the tension lever or goose neck using the pit pin 2 Note the end of the tension lever is divided lock it immediately On the level of the king post the left tensioning...

Страница 12: ...1 2 3 4 5 6 7 8 9 10 MAUT DYN 450 Edition June 2005 Section 3 02...

Страница 13: ...y close to the wing s stall speed Control deflections must be subtle The effort required to pull the control bar in will be more significant than in hang position n 2 At MTOW in position n 4 full fron...

Страница 14: ...ord on this side Vibration the appearance at high speed of a vibration of the wing trailing edges is a result of insufficient tension on the shock cord of the battens where the vibration occurs Modifi...

Страница 15: ...ashout tube dive stick is correctly inserted in the leading edge tube then immediately close the hatch again Walking towards the keel and visually check the batten position and the shock cord 5 Open t...

Страница 16: ...ack towards the pilot in order to preserve a trajectory parallel with the runway Let the Microlight ULM accelerate up to 80 km h before climbing out The climb out airspeed should not be lower than 75...

Страница 17: ...face disturbs the air flow The stall angle of the wing will be decreased The associated stall speed will increase by approximately 10 km h If you wipe the leading edges before the flight wipe both sid...

Страница 18: ...traviolet radiation emitted by the sun and reflected by the moon cause the ageing of the fabric and the seams As far as possible park your aircraft under shelter out of the sun between flights Four up...

Страница 19: ...onditions of use of the aircraft given to the purchaser The breaking of any regulatory provisions of the Civil Aviation Code or any related legislation of the country of registration of the aircraft h...

Страница 20: ...ASTIC CENTERING RING KEEL E2195 RIGHT LEADING EDGE REAR SECTION 450 E7177 CHC 6X80 12 CONTROL FRAME CHANNEL KEEL E2196 LEFT LEADING EDGE REAR SECTION 450 E7178 CHC 6X37 8 CONTROL FRAME SIDE UPPER KNUC...

Страница 21: ...Maintenance Log Date Hours Operations carried out Sign MAUT DYN 450 Edition June 2005 Section 5 02...

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