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DTA DYNAMIC 450 Instructions for use

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WING INSTRUCTION
AND MAINTENANCE MANUAL
DYNAMIC 450
MAUT – EN DYN 450 Edition : June 2005 Copyright DTA –DTA ULM AU
Wing n°..........................................
Model : ..........................................
Year : ..................................................
SECTION 0 / PREAMBLE – PAGE INDEX
Symbols
DANGER Identifies an instruction which, if not observed, can cause
damage having fatal consequences.
ATTENTION Identifies a significant instruction which, if not followed, can
cause very serious damage.
Rappel, Note: Underlines a useful instruction which must be observed for the
proper use and operation of this DYNAMIC 450 Wing
GMP Group – Motor/Propeller
CF See
Warning
The information and the descriptions contained in this Handbook correspond to the current design.
It is in no case exhaustive.
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 incurring obligation.
The specifications are given in the metric system.
Note:
DTA SARL, a limited liability company, will not be held responsible for errors in translation. The
original and reference version of this document is in the French language, and held by DTA SARL
Copyright Details:
French Version DTA SARL – France 2005
English Version DTA ULM Australia – Australia 2005
No unauthorized copying of this document can be done with out consent, written or verbal, of DTA
SARL France.
MAUT-EN VOYAGEUR II Edition : June 2005 Section : 0 - 02
Index des pages
SECTION DESIGNATION PAGE DATE MISE A JOUR
SECTION 0 PREAMBULE – INDEX DES PAGES
Symbols - Warning
Page Index
0 – 02
0 – 03
JUNE 05
SECTION 1 GENERAL
Regulatory Reminder - Safety - Address
Adaptation to other trikes - Description
Three Plan Views
Structure
1 – 01
1 – 02
1 – 03
1 – 04
JUNE 05
SECTION 2 LIMITATIONS
Maximum load at 450 kg
Maximum load at 472.5 kg
Flight Envelope Limits – Koch 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 Use - Pitch - Roll - Yaw
Takeoff - Cruise - Landing -
Stalls - Load - Rain - Strong wind
Tie-down
3 – 01
3 – 02
3 – 03
3 – 04
3 – 05
3 – 06
3 – 06
3 – 07
3 – 07
JUNE 05
SECTION 4
MAINTENANCE - GUARANTEES
Transport - Maintenance - Storage
Ageing - Periodic controls
Revised – Guarantees
4 – 01
4 – 01
4 – 02
JUNE 05
SECTION 5 APPENDICES
Nomenclature
Maintenance Log (Example)
5 – 01
5 – 02
JUNE 05
MAUT DYN 450 Edition : June 2005 Section : 0 - 03
SECTION 1 / GENERAL
This Maintenance and Instruction manual is supplemented by the Users and Maintenance
Handbooks specific to the airframe, the engine and, if fitted, the parachute.
These handbooks define the conditions of use, as well as the maintenance regime required to
maintain the airworthiness and serviceability of this aircraft.
The Pilot-in-Command (PIC):
- will use this aircraft (ULM) for sport, leisure and air work only
- is responsible for the state of airworthiness of the aircraft (ULM) which he pilots
- is holder of a valid current certificate and/or license, necessary to the particular activity
- is the holder of an endorsement for this type of aircraft
- will abide by the Regulations and Rules pertaining to Aviation in the country of use and/or
registration.
- will conform to the recommendations stated in the Maintenance and Instruction manuals relating to
this aircraft (ULM), relating to, amongst other things, the flight envelope, the flight and weight
limitations and maintenance requirements
- will make sure that the aircraft (ULM) is used in conformity with its identification card and that it has
not been modified (it is forbidden to modify a whole or a part of the elements composing the 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 France), attached to the under-surface of the aerofoil, are easily
readable
- will observe the elementary rules of flight safety: a thorough PRE-FLIGHT, PRE-TAKEOFF, PRE-
LANDING and PRE-MANOEVER procedures and fly always with reference to the ‘CONE OF
FLIGHT SAFETY’, etc….
This document was drawn up in accordance with the current French Regulations, relating to
ultra/microlight (ULM) aircraft.
Note: Be aware of the Regulations regarding the maintenance of Microlight (ULM) aircraft and
the responsibilities of the Pilot in Command and/or owner of a Microlight (ULM) in the country
of registration of the Aircraft. DTA SARL will NOT be held responsible.
Be aware that Microlights (ULM) in France are not, subject to certification.
Safety
The information given by the instrumentation can be erroneous. The engine can break down. The
movement of air by nature is unpredictable. It can be sudden and violent and thus compromise the
safety of the aircraft.
To pilot an aircraft (ULM) is an activity which can involve dangers and which requires adequate
training.
Address
D.T.A SARL Aérodrome F-26200 MONTELIMAR
Tél. ** 33 (0)4 75 01 20 83 Fax ** 33 (0)4 75 51 36 72 [email protected]
MAUT – EN DYN 450 Edition : June 2005 Section : 1 - 01
Adaptation to other Airframes:
The DYNAMIC 450 Wing can be adapted for use on other airframes (trike base) than those
manufactured by DTA SARL (a limited liability company) subject to the compliance with the
following points:
• The Maximum Take-Off Weight of the wing is observed (including wing weight).
• the engine power rating is at least 37 kW minimum required for safe two-seater flight.
• The flight tests are progressive and MUST be carried out SOLO, in stable conditions
and without wind, on a large/long runway with ample emergency egress. This will
make it safer to adapt the wing to the trike-body.
• Complete wing and keel clearance is essential, both in pitch and roll, “Control Bar full back”
and “Control Bar full forward”.
• The minimum safe distance from the propeller arc to the wing keel, from the lower
rear longitudinal cables and at the trailing edge of the wing MUST be at least 10 cm,
this MUST factor all possible wing positions and include flight positions.
• In flight - position of the control bar at cruise speed with maximum loading: at least 20 cm
from the belly of the pilot 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
related to the adaptation for the non-DTA airframe to the DTA wing as well as the flight testing.
Attention: poorly mounted powerful engines, the fitting of badly dimensioned or badly
positioned fairing can cause interaction between the wing and the airframe which can cause
the flight behaviour of the aircraft to change abruptly and render it uncontrollable.
Description
DYNAMIC 450:
Delta-wing billow shift aerofoil, double surfaced with integrated transverse partitions
Surface: 15,50 m²
Type of profile: 80%double surface (enclosed cross spars)
Wingspan: 10,20 m
Nose Angle: 125°
Aspect Ratio: 5,40
Overall length: 3,00 m
Height of Control Frame: 1.54 m
Overall height: 2.70 m
Upper Battens: 30
Lower Battens: 08
Empty weight 59 kg
Acceptable maximum weight in flight : 450 kg (472.5 kg with parachute)
Acceptable Max. weight suspended under wing : 391 kg (413.5 kg with parachute)
Wing load with the maximum weight: 29 kg/m² @ 450 kg (30,48 kg/m² @ 472.5 kg)
Max. Empty Weight (Wing + Airframe): 260 kg
Operational Load limit to 450 kg : + 4g - 0 g (- 2 g in turbulence)
MAUT – EN DYN 450 Edition : June 2005 Section : 1 - 02
3 Plan Views
MAUT – EN DYN 450 Edition : June 2005 Section : 1 – 03
Structure
MAUT DYN 450 Edition : June 2005 Section : 1 - 04
Control bar
Kingpost
Cross spar tensioning 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
Front lower cables
Upper front cable
Wing-tip Assembly
Nose (nose cap, nose plates, tensioning lever …)
SECTION 2 / PERFORMANCE
At the MTOW (Maximum Take-Off Weight) of 450 kg
DYNAMIC 450 Wing
Standard Conditions 15°C - 1013,2 hPa
Engine Type Rotax 503 Rotax 582 Hirth 3701ES Rotax 912 Rotax 912S
Rated Engine Power 37 kW 48 kW 74 kW 59,6 kW 73,5 kW
Maximum Weight 450 kg 450 kg 450 kg 450 kg 450 kg
Stalling speed (VSO) 62 km/h 62 km/h 62 km/h 62 km/h 62 km/h
Maximum Shown speed 177 km/h 177 km/h 177 km/h 177 km/h 177 km/h
Maximum speed Never exceed (VNE) 160 km/h 160 km/h 160 km/h 160 km/h 160 km/h
Maximum speed of operation (VA) 110 km/h 110 km/h 110 km/h 110 km/h 110 km/h
Maximum speed in turbulent air (VC) 110 km/h 110 km/h 110 km/h 110 km/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 fall 3 m/s 3 m/s 3 m/s 3 m/s 3 m/s
Speed of minimum rate of fall 70 km/h 70 km/h 70 km/h 70 km/h 70 km/h
Glide ratio 6,5 6,5 6,5 6,5 6,5
Take-off Roll 85 m 80 m 70 m 75 m 70 m
Take-off Distance to 15 m 210 m 190 m 170 m 180 m 170 m
Rate of rise at 75 km/h 2,5 m/s 3,5 m/s 4,5 m/s 4 m/s 4,5 m/s
Roll Rate (45°/45°) at 75 km/h 3,5 s 3,5 s 3,5 s 3,5 s 3,5 s
Roll Rate (45°/45°) at VA 3 s 3 s 3 s 3 s 3 s
Cross-wind Limit 20 km/h 20 km/h 20 km/h 20 km/h 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 - 01
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 472,5 kg 472,5 kg 472,5 kg
Stalling speed (VSO) 64 km/h 64 km/h 64 km/h 64 km/h
Maximum Shown speed 177 km/h 177 km/h 177 km/h 177 km/h
Maximum speed Never exceed (VNE) 160 km/h 160 km/h 160 km/h 160 km/h
Maximum speed of operation (VA) 110 km/h 110 km/h 110 km/h 110 km/h
Maximum speed in turbulent air (VC) 110 km/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 fall 3,2 m/s 3,2 m/s 3,2 m/s 3,2 m/s
Speed of minimum rate of fall 70 km/h 70 km/h 70 km/h 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 3,5 s 3,5 s 3,5 s
Roll Rate (45°/45°) at VA 3 s 3 s 3 s 3 s
Cross-wind Limit 20 km/h 20 km/h 20 km/h 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
Limits of the flight envelope
Maximum Angle of Bank NOT to exceed: 60°
Maximum Pitch Angle NOT to exceed: + / - 45°
The observation of the limits if the flight envelope is imperative. This Aircraft (ULM) 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.
Koch Diagram
The higher the elevation and/or an increase in ambient temperature, the greater the takeoff
distance required for your aircraft (ULM).
MAUT – EN DYN 450 Edition : June 2005 Section : 2 - 03