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Revision:

  

The complete revision wing is MANDATORY every 200 hours of flight or every 2 years

.

 

 

The side cables * MUST be changed every 400 hours or 6 years.

 

The revision is carried out by a complete disassembling of the wing structure, the replacement of 
all nuts and bolts *, a check of all the different components: straightness of the tubes, the state of 
the cables, checking of the batten profiles, etc. 
 

* Nuts, bolts, cables, tubes, plates, knuckles, sail, MUST be replaced by original parts sold by DTA 
SARL, and refitted in an identical manner. 

 

Any used NYLOCK self-locking nut must be replaced and be fitted using standard Loctite. 

 

 

Guarantee 

 
The guarantee of DTA SARL on the wing is limited to a duration of one (1)  year starting from the 
date on the commercial invoice. During the delivery, the delivery documentation must be filled out 
and signed by the customer.  
 
The guarantee only applies if the use of the aircraft conforms to the instructions stated in the 
User's manuals or any technical document stating the conditions 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, having as a consequence an accident or incident, exonerates 
DTA SARL (a limited liability company) of any guarantee with respect to the operator/owner/pilot 
infringing said Civil Aviation regulations or provisions.  
 
Normal wear of renewable components is not included in any guarantee.  
 
Any modification of the aircraft by the purchaser, as well as the replacement of parts by parts not 
being original, will involve the forfeiture of the guarantee by DTA SARL unless the modification has 
been approved, in writing, by DTA SARL.  
 
The guarantee is limited to the replacement or repair in the workshops of DTA SARL or by a 
workshop approved by DTA SARL. 
 
The guarantee covering the engine and its accessories, the propeller, the accessories not built by 
DTA SARL, will be guaranteed by the conditions and limits fixed by the manufacturers of those 
products. 
 
The obligations of DTA limited liability companies stated above constitute the limit of the granted 
guarantees. 
 
 
 
 
 
 
 
 
 
 
 
 
 
 

 

MAUT – EN DYN 450 

Edition : June 2005 

Section : 4 - 02 

Summary of Contents for DYNAMIC 450

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

Page 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...

Page 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...

Page 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...

Page 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...

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

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

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

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

Page 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...

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

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