Dyn'Aéro Sportster Technical specifications

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DATE :10/10/13
Operation REF: M EX NO 07 00
Serial number :
First issue:
Pages Date Written by Visa Checked by Visa
35 29/08/00 N. BOUCHOUT C. BELIN
Up-dates :
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+ garde 12/02/02 C. BELIN N. BOUCHOUT
+8, 15, 17 07/04/02 N. BOUCHOUT C. BELIN
100 HP MCR SPORTSTER
FLIGHT MANUAL

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0. WARNING
THIS DOCUMENT IS PROVIDED FOR
INFORMATION ONLY.IT IS THE
OWNER'S RESPONSABILITY TO
CHECK THE EXACTNESS OF THE
PRESENT MATERIAL WITH
RESPECT TO HIS/HER ACTUAL
AIRCRAFT.

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1. FLIGHT MANUAL
Model : MCR01 VLA
Serial Number :
Registration :
Document number :
Release date :
The pages identified by "Appr" are approved by :
Signature :
Authority :
Stamp :
Date of approval:
Certain details must be added by the builder to reflect the exact configuration and
installation of engine, Propeller and instrumentation.
THIS PLANE MUST ALWAYS BE USED IN ACCORDANCE WITH THE INFORMATION AND LIMITATIONS
CONTAINED IN THIS DOCUMENT.
THIS PLANE WAS BUILT FROM A KIT.
IT MUST NOT BE USED FOR HIRE OR REWARD.
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.
THIS FLIGHT MANUAL WAS ESTABLISHED ACCORDING TO FRENCH REGULATION.

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1.1. REGISTRATION OF THE OVERHAULS
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.
The new text or amendment in the revised pages will be indicated by a dark vertical line in the
left margin and the N° of the amendment and the date will be indicated on the bottom left corner
of the page.
Revision
N°
Affected
section
Affected
pages
Date
Approval
Date
Date of
insertion
Signed
1.2. LIST OF PAGES
Section
Page
Date
Section
Page
Date

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1.3. TABLE OF CONTENTS
Contenu
0. WARNING 2
1. FLIGHT MANUAL 3
1.1. REGISTRATION OF THE OVERHAULS 4
1.2. LIST OF PAGES 4
1.3. TABLE OF CONTENTS 5
2. GENERAL 9
2.1. INTRODUCTION 9
2.2. BASIS OF CERTIFICATION9
2.3. WARNINGS,ALARMS AND NOTES 9
2.4. SPECIFICATIONS 10
2.5. CONTROL SURFACE DEFLECTION 10
2.6. THREE VIEW DIAGRAM 11
3. LIMITATIONS 13
3.1. INTRODUCTION 13
3.2. AIRSPEED 13
3.3. INDICATED AIRSPEED INSTRUMENTS MARKINGS 14
3.4. ENGINE INSTALLATION 15
3.4.1. ROTAX 912 SENGINE 15
3.4.2. MT PROPELLER 16
3.4.3. MT FIXED PITCH PROPELLER TO BE USED WITH ROTAX 912S ENGINE ONLY 17
3.5. ENGINE INSTRUMENT MARKINGS 18
3.5.1. ROTAX 912 SENGINE 18
3.5.2. ROTAX 914 ENGINE 18
3.6. INSTRUMENT MARKINGS 19
3.7. WEIGHT 19
3.8. WEIGHT &BALANCE 19
3.9. APPROVED MANOEUVRES 19
3.10. MANOEUVRING LOAD FACTOR 20
3.11. MINIMUM FLIGHT CREW 20
3.12. TYPES OF FLIGHT 20
3.13. FUEL 20
3.14. MAXIMUM NUMBER OF SEATS 20
3.15. TIRE PRESSION 20
3.16. INSTRUMENT PANEL WEIGHT LIMITATION 20
3.17. SOLO FLIGHT 21
3.18. OTHER LIMITATIONS 21
3.19. PLACARDS 21

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3.19.1. DURING INITIAL EXPERIMENTATION PERIOD 21
3.19.2. IN FRONT OF PILOT VIEW21
3.19.3. AIR SPEED INDICATOR 21
3.19.4. ENGINE INSTALLATION INSTRUMENTS 21
3.19.5. CONTROL SYSTEM MARKINGS 21
3.19.6. MISCELLANEOUS PLACARDS AND MARKINGS 21
4. EMERGENCY PROCEDURES 23
4.1. INTRODUCTION 23
4.2. ENGINE FAILURE 23
4.2.1. ENGINE FAILURE ON TAKE-OFF RUN 23
4.2.2. ENGINE FAILURE IMMEDIATELY AFTER TAKE-OFF 23
4.3. IN-FLIGHT RESTART 24
4.3.1. STARTER MOTOR RESTART 24
4.3.2. DIVE RESTART 24
4.4. SMOKE AND FIRE 24
4.4.1. FIRE ON ENGINE START 24
4.4.2. AIRBORNE ENGINE FIRE 25
4.4.3. CABIN FIRE 25
4.5. GLIDING 25
4.6. FORCED LANDING 25
4.6.1. PLANNED FORCED LANDING WITH ENGINE STOPPED25
4.6.2. PLANNED FORCED LANDING WITH ENGINE RUNNING26
4.7. RECOVERY FROM AN UNINTENTIONAL SPIN 26
4.8. OTHER EMERGENCIES 26
4.8.1. VIBRATIONS AND ERRATIC ENGINE BEHAVIOUR :LIKELY CAUSES. 26
4.8.2. OIL FEED MALFUNCTION 26
4.8.3. ICING 26
4.8.4. ELECTRIC GENERATION FAILURE 26
4.8.5. LOW VOLTAGE (VOLTMETER). 26
5. NORMAL PROCEDURES 27
5.1. INTRODUCTION 27
5.2. DAILY CHECK 27
5.3. PRE-FLIGHT CHECK 29
5.4. NORMAL PROCEDURES AND CHECK-LISTS 29
5.4.1. CABIN CHECK PRIOR TO ENGINE START 29
5.4.2. COLD ENGINE START (ROTAX) 29
5.4.3. HOT ENGINE START 29
5.4.4. TAXIING 29
5.4.5. ENGINE GROUND RUN 30
5.4.6. PRE-TAKE-OFF CHECKS 30
5.4.7. TAKE-OFF 30
5.4.8. CLIMB 30
5.4.9. CRUISE 31
5.4.10. DESCENT 31
5.4.11. APPROACH 31
5.4.12. FINAL 31
5.4.13. GO-AROUND 31

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5.4.14. POST-LANDING CHECKS 31
5.4.15. ENGINE STOP 31
6. PERFORMANCES 33
6.1. INTRODUCTION 33
6.2. APPROVED DATA 33
6.2.1. AIRSPEED INDICATOR CALIBRATION 33
6.2.2. STALLING SPEED (KNOTS) 33
6.2.3. TAKE-OFF PERFORMANCES (ROTAX 912 S100 HP) 34
6.2.4. LANDING DISTANCES 34
6.2.5. TAKE-OFF DISTANCES CALCULATION 34
6.2.6. EFFECT OF RAIN AND INSECTS ON AIRCRAFT PERFORMANCE,FLYING AND HANDLING QUALITIES. 34
6.2.7. CROSS-WIND DEMONSTRATED PERFORMANCES 34
6.2.8. NOISE LIMITATIONS 34
7. WEIGHT & BALANCE 35
7.1. INTRODUCTION 35
7.2. WEIGHT &BALANCE REGISTRATION AND LOADING ENVELOPE 35
7.2.1. LOADING ENVELOPE 35
7.2.2. WEIGHT &BALANCE PROCEDURE 36
8. AIRCRAFT OPERATION, SERVICING AND MAINTENANCE 37
8.1. INTRODUCTION 37
8.2. AIRCRAFT MAINTENANCE SCHEDULE 37
8.3. AIRCRAFT MODIFICATIONS AND REPAIRS 37
8.4. PARKING 38
8.4.1. GROUND FIXING 38
8.5. CLEANING AND TREATMENT38
9. SUPPLEMENTARY SYSTEMS AND EQUIPMENTS 39
9.1. INTRODUCTION 39
9.2. MINIMUM EQUIPMENT LIST39
9.3. LIST OF THE SUPPLÉMENTARY SYSTEMS AND EQUIPMENTS 39
9.4. SUPPLEMENTARY ELEMENTS DESCRIPTIONS 39

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2. GENERAL
2.1. 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 that are imperative to be given to the MCR VLA pilot. It
also contains supplementary information given by the builder.
The builder should complete the information appropriate to the particular configuration
and selection of options.
A special place must be reserved on the luggage compartment floor in order to store this
flight manual.
2.2. BASIS OF CERTIFICATION
This type of aircraft was approved by in accordance with the regulations
applicable to kit aircraft, including the amendment and the certificate of
restricted Airworthiness N° has been issued on the .
Category of Airworthiness : Restricted (kit)
Basis of certification and/or acceptance:
2.3. WARNINGS,ALARMS AND NOTES
The following definitions apply to Warnings, Alarms & Notes used in the flight manual.
ALARM:
Signifies that a failure to observe the corresponding procedures will lead to an immediate or
important deterioration of the flight safety.
WARNING:
Signifies that a failure to observe the corresponding procedures will lead to a minor or major
deterioration of the long term flight safety.

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NOTE:
Draws attention to a condition which although not particularly related to the flight safety is
important or unusual.
2.4. SPECIFICATIONS
Kit aircraft of the type : Dyn'Aéro MCR Sportster
Cantilever low-mounted wing.
Carbon structure with wing and control surface skins made in light alloy.
Span
6.63
m
Wing surface
5.2
m²
Aspect ratio
8.45
Cabin width
1.12
m
Fuel capacity
80
l
Overall Length
5.48
m
Height
1.43
m
2.5. CONTROL SURFACE DEFLECTION
Ailerons : - 5° (±1) trailing edge upwards
+3° (±1) trailing edge downwards
Flaps : 0-25° (+0-1)
Rudder : 20° (-0+5) in both directions (left and right)
Tailplane : - 10° (+0-2) trailing edge upwards
+3.5° (-0+1) trailing edge downwards

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2.6. THREE VIEW DIAGRAM

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3. LIMITATIONS
3.1. 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 and in section 9 were approved by
.
3.2. AIRSPEED
Airspeed limits and their operational significance.
Airspeed
(IAS)
Remarks
VNE
Never exceed speed
320 km/h
Velocity you must Never Exceed, in any case
173 kts
VNO
Maximum structural cruising speed
264 km/h
Do not exceed this Velocity in Normal Operations,
except in calm air, and then , only with great
cautions.
143 kts
VA
Manoeuvring speed
235 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.
127 kts
VFE
Maximum speed allowed with flaps
extended
170 km/h
Do not exceed this Velocity with Flaps Extended
92 kts

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3.3. INDICATED AIRSPEED INSTRUMENTS MARKINGS
Air speed indicator reference marks and colour significance.
Marking
(IAS)
Significance
White segment
(92 / 170 km/h)
(50 / 92 kts)
Speed range allowed with flaps extended
Green segment
(120 / 264 km/h)
(65 / 143 kts)
Speed range for normal operational flight
Yellow segment
(264 / 320 km/h)
(143 / 173kts)
Manoeuvres must be carried out with caution and
only in conditions of calm air
Red segment
(320 km/h)
(173 kts)
Maximum speed for all operations

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3.4. ENGINE INSTALLATION
3.4.1. Rotax 912 S Engine
Engine manufacturer
Rotax
Engine model
912 S
Maximum power
Take-off
100 HP
Continuous
92 HP
Maximum manifold pressure
Take-off
27.5” Hg / 930 mbar
Continuous
27” Hg / 920 mbar
Maximum engine RPM
Take-off
5800 RPM
Continuous
5500 RPM
Maximum Cylinder Head Temperature
135 °C / 275 °F
Maximum Oil Temperature:
130 °C / 266 °F
Oil pressure
Minimum:
0.8 Bar
Maximum:
7 Bars
Fuel pressure
Minimum:
0.15 Bar
Maximum:
0.40 Bar
Octane grade of fuel:
Refer to Rotax manual
Oil quality:
Refer to Rotax manual

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Engine manufacturer
Rotax
Engine type
914
Engine/propeller reduction ratio
2.43 / 1
Maximum power
Take-off
115 HP
Continuous
100 HP
Maximum engine RPM
Take-off
5800 RPM
Continuous
5500 RPM
Maximum Cylinder Head Temperature
135 °C / 275 °F
Maximum Oil Temperature:
130 °C / 266 °F
Oil pressure
Minimum:
1.5 Bar
Maximum:
7 Bars
Fuel pressure
Minimum:
pression admission + 0.15 Bar
Maximum:
pression admission + 0.35 Bar
Octane grade of fuel:
Refer to Rotax manual
Oil quality:
Refer to Rotax manual
3.4.2. MT Propeller
Propeller manufacturer
MT Propeller
Propeller model
MTV-7-A/156-122
Type
Three-bladed, electrical variable
pitch
Propeller diameter
1.56 m
Angle of Propeller blades
at 75% of Propeller radius
normal:
variable pitch
Maximum Propeller rotation speed
2400 rpm
Torque
4.6 daN.m

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Propeller manufacturer
MT Propeller
Propeller model
MTV-6-A/152-122
Type
Three-bladed, hydraulic variable
pitch
Propeller diameter
1.56 m
Angle of Propeller blades
at 75% of Propeller radius
normal:
variable pitch
Maximum Propeller rotation speed
2400 rpm
Torque
4.6 daN.m
3.4.3. MT fixed pitch Propeller to be used with Rotax 912S engine only
Propeller manufacturer
MT Propeller
Propeller model
MT 156-220-2M
Type
Two-bladed, fixed pitch propeller
Propeller diameter
1.56 m
Reference pitch setting (75% of propeller radius)
normal:
220 mm
Maximum allowed propeller rotation speed
2400 rpm
Torque
1.6 daN.m
!! Tighten propeller bolts before first flight, after 1 flight hour and 5 flight hours. Then control
tightening every 50 flight hours and after each ground period that last more than 1 mouth !!!!!!!!

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3.5. ENGINE INSTRUMENT MARKINGS
3.5.1. Rotax 912 S Engine
ROTAX 912 S
Red line
Green sector
Yellow sector
Red Line
Instrument
Units
Minimum
Normal
Warning
Maximum
Limit
Range
Range
Limit
Tachometer
Tr/Min
1500 to 5500
5500 to 5800
5800
Oil temperature
°C
50 °C
122 °F
90 to 100 °C
194 to 212 °F
110 to 130 °C
230 to 266 °F
130 °C
266 °F
Cylinder Head
°C
50 °C
80 to 120 °C
120 to 150 °C
150 °C
Temperature
122 °F
176 to 248 °F
248 to 275 °F
275 °F
Fuel Pressure
Bar
0.15 Bar
0.15 to 0.40 Bar
0.40 Bar
PSI
2.2 PSI
2.2 to 5.8 PSI
5.8 PSI
Oil Pressure
Bar
1.5 Bars
1.5 to 4 Bars
4 to 5 Bars
5 Bars
Fuel Quantity
Litre
1 Litre
79 Litres
Note carefully :
Do not switch off the main switch before turning off the engine.
Never run continuously the engine above 5 500 rpm more than 5 minutes.
3.5.2. Rotax 914 Engine
ROTAX 914
Red line
Green sector
Yellow sector
Red Line
Instrument
Units
Minimum
Normal
Warning
Maximum
Limit
Range
Range
Limit
Tachometer
Tr/Min
1500 to 5500
5500 to 5800
5800
Oil temperature
°C
50 °C
90 to 100 °C
110 to 130 °C
130 °C
°F
122 °F
194 to 212 °F
230 to 266 °F
266 °F
Cylinder Head
°C
50 °C
80 to 120 °C
120 to 135 °C
135 °C
Temperature
°F
122 °F
176 to 248 °F
248 to 275 °F
275 °F
Fuel Pressure
Bar
manifold
pressure.
+ 0.15 Bar
manifold pressure.
+ 0.15 to 0.40 Bar
manifold
pressure.
+ 0.40 Bar
PSI
+ 2.2 PSI
+ 2.2 to 5.08 PSI
+ 5.08 PSI
Oil Pressure
Bar
1.5 Bars
1.5 to 5 Bars
5 to 7 Bars
7 Bars
Fuel Quantity
Litre
1 Litre
80 Litres
Note carefully :
Do not switch off the main switch before turning off the engine.

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3.6. INSTRUMENT MARKINGS
(to be completed by the builder according to the actual instrument configuration)
3.7. WEIGHT
Maximum take-off weight : 490 kg
Maximum landing weight : 490 kg
Maximum weight without fuel 432 kg
3.8. WEIGHT &BALANCE
Centre of Gravity range 15 / 45% M.A.C.
Datum M.A.C.
M.A.C. = 800 mm ; reference datum : 13.5 mm ahead of left wing leading-edge.
3.9. APPROVED MANOEUVRES
250
300
350
400
450
500
10% 15% 20% 25% 30% 35% 40% 45% 50%
Balance ratio compared t o MAC
Mass (kg)

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THIS AIRCRAFT IS CERTIFIED IN THE NORMAL CATEGORY.
AEROBATIC FLIGHT IS PROHIBITED.
SPINS ARE PROHIBITED.
3.10. MANOEUVRING LOAD FACTOR
+3.8 / -1.5 g
3.11. MINIMUM FLIGHT CREW
Minimum flight crew is one pilot.
Two people onboard maximum.
3.12. TYPES OF FLIGHT
VFR / DAY.
3.13. FUEL
Total fuel : 80 l
Useable fuel : 79 l
Unusable fuel : 1 l
Fuel Octane grade approved: Refer to Rotax manual
3.14. MAXIMUM NUMBER OF SEATS
Two
3.15. TIRE PRESSION
Nose landing gear : 280 mm diameter wheel 2.2 bar
210 mm diameter wheel 3 bar
Main landing gear : 280 mm diameter wheel 2.2 bar
3.16. INSTRUMENT PANEL WEIGHT LIMITATION