Dyn'Aéro MCR 4S Technical specifications

S.A.
19, rue de l'Aviation 21121 DAROIS FRANCE : (33) 03 80 35 60 62 Fax: [phone]
DATE : 28/02/06
Exploitation REF: Q EX NO 07 00
MCR 4S FLIGHT
MANUAL
N° d'exemplaire
Edition de base:
Pages Date Rédigé par Visa Vérifié par Visa
39 30/04/01 N. BOUCHOUT C. BELIN
Mise à jour:
17 28/06/01 N. BOUCHOUT C. BELIN
(+1) ; 11-17
; 33-36 13/05/02 N. BOUCHOUT C. BELIN
13-14 ;18 05/03/03 N. BOUCHOUT C. BELIN
29-31 25/08/03 N. BOUCHOUT C. BELIN
38 19/04/04 N. BOUCHOUT C. BELIN
38 11/01/05 N. MAHUET C. BELIN
24-26 ;
30 ;31 27/01/05 N. BOUCHOUT C. BELIN
18 ,37 28/02/06 C. BELIN N. MAHUET

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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 : MCR 4S
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 NOTE 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 ACCORDNG 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

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1.2. LIST OF PAGES
Section Page Date Section Page Date

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1.3. TABLE OF CONTENTS
0. WARNING 2
1. FLIGHT MANUAL 3
1.1. REGISTRATION OF THE OVERHAULS 4
1.2. LIST OF PAGES 5
1.3. TABLE OF CONTENTS 6
2. GENERAL 9
2.1. INTRODUCTION 9
2.2. BASIS OF CERTIFICATION 9
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
3.5. ENGINE INSTRUMENT MARKINGS 18
3.6. INSTRUMENT MARKINGS 19
3.7. WEIGHT 19
3.8. WEIGHT & BALANCE 19
3.9. APPROVED MANOEUVRES 20
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 21
3.16.INSTRUMENT PANEL WEIGHT LIMITATION 21
3.17.SOLO FLIGHT 21
3.18.OTHER LIMITATIONS 21
3.19.PLACARDS 21
4. EMERGENCY PROCEDURES 23
4.1. INTRODUCTION 23

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4.2. ENGINE FAILURE 23
4.3. IN-FLIGHT RESTART 24
4.4. SMOKE AND FIRE 24
4.5. GLIDING 25
4.6. FORCED LANDING 25
4.7. RECOVERY FROM AN UNINTENTIONAL SPIN 26
4.8. OTHER EMERGENCIES 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
6. PERFORMANCES 33
6.1. INTRODUCTION 33
6.2. APPROVED DATA 33
7. WEIGHT & BALANCE 35
7.1. INTRODUCTION 35
7.2. WEIGHT & BALANCE REGISTRATION AND LOADING ENVELOPE 35
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
8.5. CLEANING AND TREATMENT 38
8.6. DE-RIGGING AND RIGGING 38
9. SUPPLEMENTARY SYSTEMS AND EQUIPMENTS 39
9.1. INTRODUCTION 39
9.2. MINIMUM EQUIPMENT LIST 39
9.3. LIST OF THE SUPPLÉMENTARY SYSTEMS AND EQUIPMENTS 39
9.4. SUPPLEMENTARY ELEMENTS DESCRIPTIONS 39

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Intentionally left blank

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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 4S 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:
Attracts the 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 4S
Cantilever low-mounted wing.
Carbon structure and wing skin with control surface skins made in light alloy.
Engine and Propeller
Span 8.66 m
Wing surface 8.15 m²
Aspect ratio 9.2
Cabin width 1.17 m
Fuel capacity 2 x 60 l
Overall Length 6.72 m
Height 1.95 m
2.5. CONTROL SURFACE DEFLECTION
Ailerons : - 20° (±1) trailing edge upwards
+10° (±1) trailing edge downwards
Flaps : 0-30° (+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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Intentionally left blank

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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 were approved by .
3.2. AIRSPEED
Airspeed limits and their operational significance.
Airspeed (IAS) Remarks
VNE Never exceed speed 306 km/h Velocity you must Never Exceed, in any case
165 kts
VNO Maximum structural cruising speed 243 km/h
131 kts Do not exceed this Velocity in Normal Operations,
except in calm air, and then , only with great
cautions.
VA Manoeuvring speed 219 km/h
118 kts 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 160 km/h Do not exceed this Velocity with Flaps Extended
86 kts

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3.3. INDICATED AIRSPEED INSTRUMENTS MARKINGS
Air speed indicator reference marks and colour significance.
Marking (IAS) Significance
White segment (83 / 160 km/h)
(45 / 86 kts) Speed range allowed with flaps extended
Green segment (112 / 243 km/h)
(61 / 131 kts) Speed range for normal operational flight
Yellow segment (243 / 306 km/h)
(131 / 165 kts) Manoeuvres must be carried out with caution and only in conditions of calm air
Red segment (306 km/h)
(165 kts) Maximum speed for all operations

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3.4. ENGINE INSTALLATION
Only the following engine and propeller configurations are authorised.
3.4.1. Rotax 912 S Engine
Engine manufacturer Rotax
Engine type 912 S
Engine/propeller reduction ratio 2.43 / 1
Maximum power
Take-off 99 HP
Continuous 93 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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3.4.2. Rotax 914 Engine
Engine manufacturer Rotax
Engine type 914
Engine/propeller reduction ratio 2.43 / 1
Maximum power
Take-off 113 HP
Continuous 100 HP
Maximum manifold pressure
Take-off 38.4 "Hg / 1300 mbar
Continuous 34 "Hg / 1150 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: 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

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3.4.3. MT variable pitch Propeller
Propeller manufacturer MT Propeller
Propeller model MTV-6-A/156-122
Type Three-bladed, hydraulic variable
pitch
Propeller diameter 1.56 m
Reference pitch setting (75% of propeller radius)
normal: variable pitch
Maximum allowed propeller rotation speed 2400 rpm
Torque 4.6 daN.m
Propeller manufacturer MT Propeller
Propeller model MTV-21-A/170-125
Type Two-bladed, hydraulic variable
pitch
Propeller diameter 1.70 m
Reference pitch setting (75% of propeller radius)
normal: variable pitch
Maximum allowed propeller rotation speed 2400 rpm
Torque 4.6 daN.m

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3.5. ENGINE INSTRUMENT MARKINGS
3.5.1. Rotax 912 S Engine
ROTAX 912 S
Red line Yellow sector Green sector Yellow sector Red Line
Instrument Units Minimum Warning Normal Warning Maximum
Limit Range Range Range Limit
Tachometer Tr/Min 1400 1400 - 3500 3500 - 5500 5500 - 5800 5800
Oil temperature °C 50 50 - 90 90 - 110 110 - 130 130
°F 122 122 - 194 194 - 230 230 - 266 266
Cylinder Head °C 60 60 - 80 80 - 110 110 to 135 135
Temperature °F 140 140 - 176 176 - 230 230 to 275 275
Fuel Pressure Bar 0.15 0.15 - 0.40 0.40
PSI 2.2 2.2 – 5.8 5.8
Oil Pressure Bar 0.8 0.8 - 2 2 - 5 5 - 7 7
Fuel Quantity Litre 1 2x60
Note carefully :
Do not switch off the main switch before turning off the engine.
3.5.2. Rotax 914 Engine
ROTAX 914
Red line Yellow sector Green sector Yellow sector Red Line
Instrument Units Minimum Warning Normal Warning Maximum
Limit Range Range Range Limit
Tachometer Tr/Min 1400 1400 - 3500 3500 - 5500 5500 - 5800 5800
Oil temperature °C 50 50 - 90 90 - 110 110 - 130 130
°F 122 122 - 194 194 - 230 230 – 266 266
Cylinder Head °C 60 60 - 80 80 - 110 110 - 135 135
Temperature °F 140 140 - 176 176 - 230 230 - 266 266
Fuel Pressure Bar Manifold
pressure.
+ 0.15
Manifold
pressure.
+ 0.15 to 0.35
Manifold
pressure.
+ 0.35
PSI + 2.2 + 2.2 to 5.08 + 5.08
Oil Pressure Bar 0.8 0.8 - 2 2 - 5 5 - 7 7
Fuel Quantity Litre 2x60
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 : 750 kg
Maximum landing weight : 750 kg
Maximum weight without fuel 664 kg
3.8. WEIGHT & BALANCE
Centre of Gravity range 15/42% M.A.C.
Datum Cma
350
400
450
500
550
600
650
700
750
800
10% 15% 20% 25% 30% 35% 40% 45%
Centrage (m)
m (kg)
M.A.C. = 960 mm ; reference datum : wing leading-edge.

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3.9. APPROVED MANOEUVRES
THIS AIRCRAFT IS CERTIFIED IN THE NORMAL CATEGORY.
AEROBATIC FLIGHT IS PROHIBITED.
SPINS ARE PROHIBITED.
3.10. MANOEUVRING LOAD FACTOR
+3.8 / -1.52 g
3.11. MINIMUM FLIGHT CREW
Minimum flight crew is one pilot.
Four people onboard maximum.
3.12. TYPES OF FLIGHT
VFR / DAY.
3.13. FUEL
Total fuel : 120 l
Useable fuel : 118 l
Unusable fuel : 2 l
Fuel Octane grade approved: Refer to Rotax manual
3.14. MAXIMUM NUMBER OF SEATS
Four