Dyn'Aéro MCR ULC ECOLIGHT HB-WAZ Technical specifications

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19, RUE DE L’AVIATION
F21121 DAROIS
FRANCE
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Ref : N EX NO 09 01
MCR ULC ECOLIGHT
Aircraft Flight Manual
3rd Edition – 2009/08/20

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THIS PLANE MUST ALWAYS BE USED IN ACCORDANCE WITH THE INFORMATION AND LIMITATIONS CONTAINED
IN THIS DOCUMENT.
THE USER IS RESPONSIBLE FOR THE USE OF THE AIRCRAFT ,ENSURING THAT IT COMPLIES WITH
REGULATIONS AND INFORMING ANY PASSENGER OF THE LIMITATIONS OF THE AIRCRAFT WITH RESPECT TO ITS
AIRWORTHINESS LIMITATIONS.
BUILDERS:DYN’AERO FRANCE

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THIS MANUAL BELONGS TO THE AIRCRAFT:HB-WAZ S/N: 363
0.1. REGISTRATION OF THE REVISIONS
All amendments to this document must be entered in the table below, except weighing data, and all
cases of approved sections, aimed and approved by the Authority responsible for Airworthiness.
Revision
N°
Affected
section
Affected
pages
Date
Approval
Date
Date of
insertion
Signed

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0.2. TABLE OF CONTENTS
0.1. REGISTRATION OF THE REVISIONS 5
0.2. TABLE OF CONTENTS 6
1. GENERAL 9
1.1. INTRODUCTION 9
1.2. CERTIFICATION BASIS 9
1.3. WARNINGS,CAUTIONS AND NOTES 9
1.4. DESCRIPTIVE DATA 10
1.5. THREE VIEW DRAWING 10
2. LIMITATIONS 11
2.1. INTRODUCTION 11
2.2. AIRSPEED 11
2.3. AIRSPEED INDICATOR MARKINGS 11
2.4. POWER PLANT 12
2.5. POWER PLANT INSTRUMENT MARKINGS 13
2.6. MISCELLANEOUS INSTRUMENT MARKINGS 13
2.7. WEIGHT 13
2.8. CENTRE OF GRAVITY 14
2.9. APPROVED MANOEUVRES 14
2.10. MANOEUVRING LOAD FACTOR 14
2.11. FLIGHT CREW 15
2.12. KINDS OF OPERATION 15
2.13. FUEL 15
2.14. MAXIMUM NUMBER OF SEATS 15
2.15. OTHER LIMITATIONS 16
2.16. PLACARDS 16
3. EMERGENCY PROCEDURES 19
3.1. INTRODUCTION 19
3.2. ENGINE FAILURE 19
3.3. AIR START 20
3.4. SMOKE AND FIRE 20
3.5. GLIDE 21
3.6. LANDING EMERGENCIES 21
3.7. RECOVERY FROM UNINTENTIONAL SPIN 22
3.8. PARACHUTE RESCUE SYSTEM OPERATION (IF FITTED). 22
3.9. OTHER EMERGENCIES 22
4. NORMAL PROCEDURES 26
4.1. INTRODUCTION 26
4.2. DAILY INSPECTION 26
4.3. PRE-FLIGHT INSPECTION 28
4.4. NORMAL PROCEDURES AND CHECK LIST 28

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5. PERFORMANCES 31
5.1. INTRODUCTION 31
5.2. APPROVED DATA 31
5.3. ADDITIONAL INFORMATION34
6. WEIGHT &BALANCE 35
6.1. INTRODUCTION 35
6.2. WEIGHT &BALANCE REGISTRATION AND LOADING ENVELOPE 35
6.1. EQUIPEMENT LIST 38
7. AIRCRAFT AND SYSTEMS DESCRIPTION 40
7.1. INTRODUCTION 40
7.2. AIRFRAME 40
7.3. FLIGHTS CONTROLS 40
7.4. INSTRUMENT PANEL 41
7.5. LANDING GEAR SYSTEM 42
7.6. SEATS AND SAFETY HARNESS 42
7.7. BAGGAGE COMPARTMENT 42
7.8. CANOPY 42
7.9. POWER PLANT 42
7.10. FUEL SYSTEM 43
7.11. ELECTRICAL SYSTEM 44
7.12. PITOT AND STATIC PRESSURE SYSTEMS 46
7.13. MISCELLANEOUS EQUIPMENT 46
7.14. AVIONICS 46
8. AEROPLANE HANDLING,SERVICING AND MAINTENANCE48
8.1. INTRODUCTION 48
8.2. RIGGING AND DERIGGING 48
8.3. AIRCRAFT MAINTENANCE SCHEDULE 49
8.4. AIRCRAFT MODIFICATIONS AND REPAIRS 49
8.5. GROUND HANDLING 49
8.6. CLEANING AND TREATMENT49
9. SUPPLEMENTARY SYSTEMS AND EQUIPMENTS 50
9.1. INTRODUCTION 50
9.2. LIST OF THE SUPPLÉMENTARY SYSTEMS AND EQUIPMENTS 50
9.3. SUPPLEMENTARY ELEMENTS DESCRIPTIONS 50
10. SUPPLEMENT AEROTOW 51
10.1. PRELIMINARY LIMITATIONS: 51
10.2. GENERAL 51
10.3. LIMITATIONS 51
10.4. EMERGENCY PROCEDURES 51
10.5. NORMAL PROCEDURES 52
10.6. PERFORMANCES 52
10.7. AIRCRAFT AND SYSTEMS DESCRIPTION 53

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10.8. CARE AND MAINTENANCE 54
10.9. PLACARDS 54
11. SUPPLEMENT EDIATEC FLARM ECW 100 55
12. SUPPLEMENT TOW CABLE RETRACTOR WINCH TOST 62

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1. GENERAL
1.1. INTRODUCTION
The flight manual for the aircraft was designed to provide pilots and instructors with the
information necessary to efficiently and safely fly this very light aircraft.
This manual contains information's that are imperative to be given to the MCR ULC
ECOLIGHT pilot. It also contains supplementary information given by the builder.
1.2. CERTIFICATION BASIS
This aircraft was approved by ____________________________________
Category of Airworthiness: ECOLIGHT
Basis of acceptance: LTF UL 2003
Noise certification basis: ICAO Annex 16, Chapter 10
1.3. WARNINGS,CAUTIONS AND NOTES
The following definitions apply to Warnings, Alarms & Notes used in the flight manual.
WARNING:
Means that a failure to observe the corresponding procedures will lead to an immediate or important
deterioration of the flight safety.
CAUTION:
Means that a failure to observe the corresponding procedures will lead to a minor or major
deterioration of the long term flight safety.
NOTE:
Draws attention to a condition which although not particularly related to the flight safety is important
or unusual.

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1.4. DESCRIPTIVE DATA
Kit aircraft of the type : Dyn'Aéro MCR ULC
Cantilever low-mounted wing, fixed gear.
Flying tail.
2 seats.
Carbon structure.
Engine: From Rotax 912 to 914 (Only 914 will be described here, each other engine (912 and 912S) will be added as soon as it equips an aircraft.)
Propeller: Dyn’Aero-Prop two/three-blades, fix or variable pitch.
Span 8.62 m
Wing surface 8.31 m²
Aspect ratio 9.02
Wing loading
54.5
kg/ m²
Cabin width
1.12
m
Fuel capacity 72 l
Overall Length 5.53 m
Height 1.53 m
MAC 22/40 %
1.5. THREE VIEW DRAWING

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2. LIMITATIONS
2.1. INTRODUCTION
This section includes operating limitations, reference marks of instruments
and placards necessary for the safe use of the aircraft, its engine, standard
systems and equipment.
The limitations included in this section are approved by ______________________.
2.2. AIRSPEED
Airspeed limits and their operational significance.
Airspeed
(IAS)
Remarks
VNE
Never exceed speed
315 km/h
Velocity you must Never Exceed, in any case
VNO Maximum structural cruising speed 210 km/h Do not exceed this Velocity in Normal O
perations,
except in calm air, and then, only with great
cautions.
VA
Manoeuvring speed
180 km/h
Do not apply abrupt or full-range control
deflections beyond this speed, because under
certain conditions, the Aircraft might be exposed to
excessive loads.
VFE
Maximum speed allowed with flaps
extended
140 km/h Do not exceed this Velocity with Flaps Extended
Note : The maximum speed of the safety parachute deployment is 270km/h
2.3. AIRSPEED INDICATOR MARKINGS
Marking
(IAS)
Significance
White segment (70/140 km/h) Speed range allowed with flaps extended
Green segment
(99/210 km/h)
Speed range for normal operational flight
Yellow segment
(210/315 km/h)
Manoeuvres must be carried out with caution and
only in conditions of calm air
Red line
(315 km/h)
Maximum speed for all operations
Red triangle and red
“P”
(270 km/h) Maximum speed for the safety parachute
deployment

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2.4. POWER PLANT
2.4.1. Rotax 914
Engine manufacturer Rotax
Engine model
914 UL4
Power
Maximum: Take-off, max. 5 minutes 115 HP
Continuous:
100 HP
Manifold pressure
Maximum: Take-off, max. 5 minutes 39.9” Hg / 1350 hPa
Continuous 35.4” Hg / 1200 hPa
Engine RPM
Maximum: Take-off, max. 5 minutes 5800 RPM
Continuous 5500 RPM
Cylinder Head Temperature
Maximum
135 °C
Oil Temperature:
Maximum 130 °C
Oil pressure
Minimum: 0.8 Bar
Maximum: 7 Bars
Fuel pressure
Minimum: 0.15 Bar
Maximum: 0.35 Bar
Octane grade of fuel: Automotive Gasoline unleaded min.
95 RON or AVGAS 100LL
Oil quality: Motorcycle oil of a registered brand
with gear additives, API
classification SF or SG
Reduction gear with overload clutch 1:2.43

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2.4.2. Propellers
2.5. POWER PLANT INSTRUMENT MARKINGS
2.5.1. Rotax 914 UL
Instrumentation markings and their significance
ROTAX 914
a
Red line
Yellow sector
Green sector
Yellow sector
Red Line
Instrument
Units
Minimum
Warning
Normal
Warning
Maximum
Limit Range Range Range Limit
Tachometer Model1
(S/N 326, 349, 351)
RPM 1400 1400 - 3500 3500 to 5500 5500 to 5800 5800
Tachometer Model 2
(S/N 362, 363 and next)
RPM 0 to 1400 1400 to 5500 5500 to 5800 5800 and over
Tachometer model 3
(S/N 328 only )
RPM
0 to 1500
1500 to 1800
1800 to 5500
5500 to 5800
5800
Oil temperature
°C
50°C
50 to 90°C
90 to 110 °C
110 to 130 °C
130 °C
Cylinder Head
°C
60°C
60 to 80°C
80 to 110 °C
110 to 135 °C
135 °C
Temperature
Manifold pressure
In. HG
0 to 35.4 in Hg
35.4- 39.9 in. Hg
39.9 in. Hg
Oil Pressure Bar 0.8 Bars 0.8 to 2 Bars 2 to 5 Bars 5 to 7 Bars 7 Bars
2.6. MISCELLANEOUS INSTRUMENT MARKINGS
Fuel quantity indicator: placard of the usable fuel quantity: see 2.13
2.7. WEIGHT
Basic Empty Weight see Chapter 6.2.3
Maximum take-off weight : 472.5. kg (450 kg without parachute)
Maximum landing weight : 472.5 kg(450 kg without parachute)
Maximum allowed baggage weight 15 kg
x : possible combination
r : optimized for towing
O-C : optimized for cruise
O-STOL: optimized for STOL
performances

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2.8. CENTRE OF GRAVITY
Centre of Gravity range 22 / 40% M.A.C.
Datum M.A.C.
M.A.C. = 960 mm ; reference datum : 13.5 mm ahead of left wing leading-edge.
2.9. APPROVED MANOEUVRES
NORMAL CATEGORY
AEROBATIC FLIGHT IS PROHIBITED.
INTENTIONAL SPINS ARE PROHIBITED.
2.10.MANOEUVRING LOAD FACTOR
+4 / -2 g
+2.0 / 0 g (with flaps down)
225
250
275
300
325
350
375
400
425
450
475
500
20% 25% 30% 35% 40%
mass [kg]
% of MAC
Centre of Gravity range
with parachute
without parachute

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2.11.FLIGHT CREW
Minimum flight crew is one pilot.
Two people onboard maximum.
2.12.KINDS OF OPERATION
VFR / DAY.
2.13.FUEL
For S/N 326, 328,
389
For S/N 349, 351,
362, 363
Total fuel:
73 L
81 L
Usable fuel:
72 L 80 L
Unusable fuel: 1 L 1 L
Fuel Octane grade approved: Unleaded Automotive Gasoline min. 95 RON or avgas 100LL
2.14.MAXIMUM NUMBER OF SEATS
Two

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2.15.OTHER LIMITATIONS
2.15.1. Tire pressure
Nose landing gear: 260 mm diameter wheel 2.5 bar
Main landing gear: 280 mm diameter wheel (11X4.00) 2.2 bar
2.16.PLACARDS
Minimum 3 cm high placard "ECOLIGHT AIRCRAFT" must be placed next to each cabin opening.
2.16.1. Flight limitations and airworthiness placards:
Sized 100*20mm and so that both pilots can easily read it, the following placard
:
Sized 75*35 and so that both pilots can easily read it, the following placard
ID Plate: 100*50mm, 100*50mm (Inox)
“HB-XXX” : Height: 15mm Depth: 1mm
In the back frame of the luggage compartment.
2.16.2. Air speed indicator See paragraph 2.3.

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2.16.3. Engine installation instruments
See paragraph 2.5.1.
2.16.4. Control system markings
Each control system other than main flight control systems is marked in order to explain its function
and operation mode. This is an overview of the markings you should have on your aircraft if it is
equipped with the corresponding device. It includes: lights, switches, breakers, handles and levers
markings.

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2.16.5. Fuel
See paragraph 2.13
2.16.6. Miscellaneous placards and markings
In luggage compartment : MTOW 472.5 kg or 450 kg w/o parachute.
Fuel tank filler :
To be stuck around the fuel hole filler. Either with 72 or 80 L depending on the aircraft S/N. Inside diameter: 80 mm
Oil tank filler:
To be stuck on the hidden side of the oil filler door.
Water tank filler:
To be stuck on the hidden side of the coolant filler door.
Placards and Markings for Aerotow:
See section 10

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3. EMERGENCY PROCEDURES
3.1. INTRODUCTION
This section provides a list of appropriate actions in the event of certain emergencies.
Providing that the aircraft is well maintained and proper pre-flight inspections are made,
emergencies due to failure of the aircraft, aircraft engine or other systems is very rare.
However, should an emergency occur, the procedures described in this section of the manual
should be adopted.
3.2. ENGINE FAILURE
3.2.1. Engine failure on take-off run
If there is enough runway length remaining :
- Fully reduce power and apply brakes.
If there is insufficient runway length remaining :
- Fully reduce power
- Brake hard
- Fuel valve .................................................................................... closed
- Magnetos .........................................................................................OFF
- Master .........................................................................................OFF
3.2.2. Engine failure immediately after take-off
- Airspeed ................................................................................ 134 km/h
-Fuel valve .................................................................................... closed
- Magnetos .........................................................................................OFF
- Flaps .............................................................................as required
- Master .........................................................................................OFF
Never attempt to turn back to the runway.

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3.3. AIR START
3.3.1. Starter motor restart
If the altitude is sufficient to attempt to restart the engine :
- Airspeed ................................................................................ 134 km/h
- Fuel valve .......................................................................................open
- Electric fuel pump.................................................................................... on
- Throttle setting.........................................................................................1/2
- Magnetos .................................................................................."BOTH"
- Starter ........................................................................................... on
If the motor does not start, plan to make a forced landing.
3.3.2. Dive restart
If the altitude is sufficient to attempt to restart the engine (minimum altitude lost 1500 feet) :
Nose dive as explained :
- Airspeed .............................................................................. >250 km/h
- Fuel valve .......................................................................................open
- Electric pump ................ on
- Throttle setting.........................................................................................1/2
- Magnetos .................................................................................."BOTH"
If the motor does not start, plan to make a forced landing.
3.4. SMOKE AND FIRE
3.4.1. Fire on engine start
Continue starting the engine (or leave it running if it is has already started)
- Throttle setting.............................................................................fully open
- Electric fuel pump....................................................................................off
- Fuel valve .................................................................................... closed
If the fire persists :
- Magnetos ...........................................................................................off
- Master …………………………………………………………………..off
EVACUATE THE AIRCRAFT