Flyitalia MD-3 Rider Technical specifications

PILOT'S OPERATING HANDBOOK
and
FLIGHT MANUAL
MD 3 RIDER
BE CAREFULL !
Followed text of flight manual is only informative - prepared as the
background for whole world, adapted according to notices from Czech
LAA certification process and dealers wishes …
It is not possible to use that without approving of domestic dealers or
certification offices in specific country verification.
( there is needed to be adapted mainly according to regional limits and
UL requirements directions )

Flight manual MD3 RIDER
Page 2
Aircraft Type: MD-3 Rider
/ version
Serial number:
Registration:
Date of issue:
LAA Approval number and date:
ULL - 02 / 2006
31.5. 2006
LTF Approval number and date:
Manufacturer – stamp and signature :
The airplane must be operated by the information and
limitations which are presented in this handbook.
This handbook must be available to pilot any time during the
flight.

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LIST OF THE REVISIONS AND THE REPAIRS
11.4. 2006
Ordinal No. Number of document -
bulletin
It concerns to
pages No. Date of issue
Signature

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1. GENERAL
1.1. Introduction
This handbook is provided with your aircraft to allow you to attain as
much knowledge about the aircraft and its operation as possible. Read
this manual before your first flight and make sure you understand all
the information contained here.
1.2. Certification bases
This aircraft was manufactured in accordance ultralight airworthiness
standards and does not conform to standard category airworthiness
requirements.
The following standards were used:
UL-2 – Czech Republic
LTF-UL - Germany
1.3. Warnings, cautions and notes
The following definitions apply to warning, cautions and notes used in
this manual:
WARNING: Information which could prevent personnel injury or
loss of life
CAUTION: Information which could prevent damage to equipment
NOTE: Information of special importance to pilot

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1.4. Aircraft basic description
MD-3 Rider is an all metal design, light high-wing ultralight airplane
with glued and riveted aluminum alloy airframe, welded cockpit cage
and aerodynamic shaped composite fuselage canopy and fairings.
The aircraft is equipped with 100HP Rotax 912 ULS engine (80HP
Rotax 912 UL as an option for MD-3 UL model) and Woodcomp SR
200 B 3-blade on ground adjustable propeller (other propeller are
optional – see Supplement 2)
Wing span
9,0 m
Length
5,9 m
Height
2,3 m
Wing area
9,9 m
2
MAC length
1,15 m
Forward swept wing
3°
Existing aircraft versions, approved by calculations and proofs coveres
installations of engines Rotax 912ULS (standard), Rotax 912 UL ,
Rotax 914 , using of folded wings ( FW ), and has a lot of option ( for
exmple standard UL version has light struts from aluminum alloy tubes, hand operated
flaps , not reinforced rear fuselage part without tailbump and aerodynamic areas in
Alclad)
Version SportRider is not covered by this manual because of all
another limits in LSA requirements!
Marking of specific aircraft version is shown in titul page 2 and its
extract definition is here :

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1.5. Three-view drawing

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2. LIMITATION
2.1. AIRSPEED LIMITATION
Speed IAS
km/h
V
NE
Never exceed speed
270
V
RA
Maximal speed in hard turbulence
200
V
A
Maneuvering speed
165
V
FE
Maximum flap extended speed
125
WARNING: Above Maneuvering speed use smaller deflection of
control surfaces only - the aircraft may be overloaded !
2.2. AIRSPEED INDICATOR MARKINGS
NORMAL
OPERATION
RANGE:
110
–
200
km/h
CAUTION
RANGE:
200 – 270
km/h
FLAPS
OPERATING
RANGE:
61 – 125 km/h
NEVER
EXCEED
SPEED:
270 km/h

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2.3. Engine
The MD-3 Rider is powered by ROTAX 912ULS engine, MD-3 UL
model is powered by Rotax 912 UL.
Aircraft
Engine model MD-3 UL
Rotax 912 UL
MD-3
ROTAX 912 ULS
Max. power- take-off (kW) 59,6 73,5
- continuous (kW) 58 69
Max. engine speed (5 min) 5 800 RPM
Max. engine speed
(continuous) 5 500 RPM
Max. cylinder head
temperature (°C) 115 115
Max. oil temperature (°C) 140 130
Oil pressure minimum (bar) 0,8 below 3500 RPM,
2,0 above 3500 RPM
Oil pressure maximum (cold
start only, bar) 7
Oil pressure normal
operation (bar) 2,0 – 5,0
Fuel pressure (min-max, bar) 0,15 – 0,4
-25°C
Operation outside
temperature range 50°C
For more details see Operator’s Manual for all versions of Rotax 912
supplied with the engine.
WARNING: Flying this aircraft must always be done with the
possibility of a safe landing due to loss of engine power. The pilot
is fully responsible for consequences of such failure

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2.4. Engine instrument marking
The aircraft is equipped with an integrated engine display FLYDAT
Display panel Description Unit Resolution
1 RPM [1/min]
2 Operation hours [hours]
3 Exhaust gas temperature [ºC]
4 Exhaust gas temperature [ºC]
5 Cylinder head temperature [ºC]
6 ←(→) indicates symbolizes left (right) cylinders,
7 Oil temperature [ºC]
8 Oil pressure [bar]
Indicator Unit Warning limits
912UL 912ULS
Max. RPM 5800 5800
EGT - Exhaust gas temperature (ºC) 860
860
CHT - Cylinder head temperature, (ºC) 115 115
Oil temperature, (ºC) 140 130
Oil pressure, max (bar) 6 6
Oil pressure, min (bar) 0,8
0,8
Oil pressure, normal (bar) 2 – 5 2 – 5
• When a warning limit is exceeded - corresponding value will
blink on the Flydat display and also the alarm lamp on the
instrument panel blinks.
• When a not-permissible value (alarm limit value) is reached -
corresponding value will blink on the Flydat display and also
the alarm lamp on the instrument panel blinks – longer
intervals.

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2.5. Weight limitation
912 UL 912UL
S
Empty weight (standard version, kg) 286 295
Max. take-off weight (NO Ballistic Recovery
System installed, kg) 450 450
Max. take-off weight (Ballistic Recovery
System installed, kg) 472,5 472,5
Max. crew weight - calculated for (kg) 200 200
Min. crew weight (kg) 55 55
Max. weight in the baggage compartment (kg) 15 15
MAXIMAL CREW WEIGHT (kg)
depend on fuel and baggage quantity
Fuel gauge
indication →
→→
→full 3/4 1/2 1/4 30 min of flight
Fuel tank
filling
→
→→
→Fuel quantity
in liters →
92 69 46 23 5
Max: 15 kg
½ : 7,5 kg
Baggage
weight
→
→→
→Without baggage
WARNING: Do not exceed these weight limits. Pay attention to
fuel quantity especially when 2 persons are on board –
DO NOT EXCEED maximum take-off weight
2.6. Center of gravity
Front center of gravity limit 19 % MAC
Rear center of gravity limit 30 % MAC
See Section 6 for Center of gravity calculation.
2.7. Approved maneuvers
Steep turn (max. bank 60°)
Climbing turn
Lazy eight
Entry speed to these maneuvers – max. 165 km/hod
WARNING: Aerobatics, intentional stalls and spins are prohibited.
Maximum angle of bank : 60°

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2.8. Maneuvering load factors G
Maximum positive center of gravity load factor
+ 4
Flap
up (0°) Maximum negative center of gravity load factor
- 2
Maximum positive center of gravity load factor
+ 2
Flaps
down Maximum negative center of gravity load factor
0
2.9. Flight crew
Minimum crew 1 pilot
Maximum number of persons on board 2 persons
2.10. Kind of operation
WARNING: Only VFR day flights are permitted.
WARNING: IFR flights and flying in clouds is prohibited.
Flight into know icing is prohibited
2.11. Fuel
2.11.1. Approved fuel types
Premium unleaded auto fuel (Natural 95 in Czech - Standard Spec. for
Automotive Spark-Ignition Engine Fuel, ASTM D 4814) or AVGAS 100 LL.
Note: Due to the higher lead content in AVGAS, the wear of the valve
seats, the deposits in combustion chamber and lead sediments in the
lubrication system will increase. Therefore, use AVGAS only if you
encounter problems with vapor lock or if other fuel types are not
available.
For more details see Operator’s Manual for all versions of Rotax 912
supplied with the engine.
2.11.2. Fuel capacity
Fuel tank capacity (each wing tank)
46 liters
Total fuel capacity
92 liters
Unusable fuel
1 liter

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2.12. Other limitation
WARNING: No smoking
Max. crosswind component
10 knots
(5 m/s)
Max. wind in runway direction
24 knots
(12 m/s)
Maximum outside temperature
50 °C
Minimum outside temperature
- 25 °C
Heavy rain or extensive moisture can cause mild decrease airplane
performance. During the flight with expressive moisture we still
recommend to increase the take-off and landing speed approximately
about 10 km/hour

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2.13. PLACARDS
Registration label
Matriculation:
Producer: GRYF Aircraft spol. s r.o.
Type/Name : MD3 Rider
Production number/year:
Empty weight: kg
Max. take-off weight: kg
Basic international placards :
AIRSPEED IAS
Never exceed 270 km/hour
Maneuvering 165 km/hour
Stalling 82 km/hour
Stalling with flaps 61 km/hour
This ultra-
light aircraft has been
approved only for VFR day flights
under no icing conditions.
AEROBATICS maneuvers
and
intentional spins are PROHIBITED !

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Page 2-8
Examples of next specific placards :
Next used placards are classical for all aircraft – open/close,
instrument description etc.
Baggage
max.
15 kg
46 litre
unleaded fuel
min. MON 85 RON 95
tyre 180 +20 kPa
ENGINE SPEED
Max. Take-off (max 5min) 5 800 rpm
Max. continuous 5 500 rpm
Idling 1 400 rpm

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As example of specific regional placards, followed there are shown
translated LAA CZ placards :
OPERATION INFORMATION AND LIMITS
Matriculation :
Empty weight :
kg
Max. take-off weight :
kg
Max. payload :
kg
Max. baggage weight:
15
kg
Min. pilot weight:
55
kg
Max. permissible speed V
NE
:
270
km/hod
Stall speed in landing
configuration V
SO
:
61
km/hod
Max. permissible speed with
flaps V
FE
:
125
km/hod
MAXIMAL CREW WEIGHT (kg)
depend on fuel and baggage quantity
Fuel gauge
indication →
→→
→full 3/4 1/2 1/4 30 min of flight
Fuel tank
filling
→
→→
→Fuel quantity
in liters →
92 69 46 23 5
Max: 15 kg
½ : 7,5 kg
Baggage
weight
→
→→
→Without baggage
This product is not liable to approving of
Civil Aircraft Administration and is used in
own risk of user.
Intended spins, stalls and aerobatics are
prohibited.

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3. EMERGENCY PROCEDURES
This section provides checklist and amplified procedures for coping
with emergencies that may occur. Emergencies caused by airplane or
engine malfunction are extremely rare if proper pre-flight inspections
and maintenance are practiced. However, should an emergency arise,
the basic guidelines described in this section should be considered and
applied as necessary to correct the problem. All air speed values in this
chapter are presented in km/hod Indicated Airspeed unless indicated
otherwise.
3.1. Engine failure and emergency landings
3.1.1. Engine failure during take-off run
- throttle reduce to idle
- ignition off
- master switch off
- brakes as required
3.1.2. Engine failure during take-off
- airspeed - 125 km/hod
- choose a landing site - below 150 ft - land ahead, if possible
- above 150 ft - choose suitable landing site
The landing site is to be preferably chosen in the runway direction or
the nearest suitable site clear of obstacles
- master switch off
- ignition off
- fuel tank valves shut
- flaps extend as needed
- safety belts tighten
after touchdown:
- brakes as required

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3.1.3. In-flight engine failure
- airspeed 125 km/hod
- trim trim
- landing site selection select
check situation ( actual flight level etc.) and continue
according to procedure 3.2. (in-flight engine starting) or procedure
3.1.2 - if the engine cannot be started up
3.1.4. Carburator icing
- airspeed 140 km/hod ) min.115,
- throttle try to find RPM with smallest lose of
power
- leave the icing area (if possible)
- increase slowly the engine power to cruise after 1-2 minutes
- when engine power is not recovered, land on the nearest airfield or
off-airfield - following the procedure described in 3.1.2
3.2. In-flight engine starting
- airspeed 130 km/hod
- master switch on
- fuel tank valves open to tank with more fuel
- choke activate (cold engine only)
- throttle idle (when choke is activated), 1/3 of
travel otherwise.
- ignition on
- starter start up
- if the engine cannot be started up (not enough power from battery),
increase the airspeed to 150-170 km/hod to rotate the propeller to
support the engine starting
WARNING: Loss of height needed for in-flight engine starting is
approximately 600 ft.

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3.3. FIRES
3.3.1. Engine fire on the ground
- fuel tank valves shut
- throttle full
- ignition off
- master switch off
- abandon the aircraft and extinguish fire (if possible)
- fire damage inspect
WARNING: DO NOT CONDUCT ANOTHER FLIGHT BEFORE THE
FIRE CAUSE HAS BEEN DETERMINED AND REPAIRED
3.3.2. Engine fire during takeoff
- throttle idle
- fuel tank valves shut
- IF already airborne keep airspeed of 115 km/hod and land
- brakes as required to stop the aircarft
after the aircraft come to stop:
- throttle full
- ignition off
- abandon the aircraft and extinguish fire (if possible) once is stopped
3.3.3. Engine fire in flight
- fuel tank valves shut
- throttle full
- airspeed increase – try to „cut-off“ flames.
Do not exceed V
NE
- landing site selection the nearest airfield, or a suitable
landing site for emergency landing
- ignition off
- master switch off
- airspeed 125 km/hod
- wings flaps extend as needed
- safety belts tighten
- perform emergency landing
- abandon the aircraft and extinguish fire (if possible)
WARNING: DO NOT ATTEMPT TO RESTART THE ENGINE
WARNING: DO NOT CONDUCT ANOTHER FLIGHT BEFORE THE
FIRE CAUSE HAS BEEN DETERMINED AND REPAIRED

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3.3.4. Cockpit or electrical fire
- cockpit door open to remove smoke from
the cockpit
- radio, gps or other switches off
Land as soon as possible. Extinguish fire as soon as possible.
3.4. Gliding
optimum gliding speed
125 km/hod
Gliding ratio (at 110 km/hod)
1:10
3.5. Precautionary Landing
- choose suitable landing site, evaluate wind (direction and speed),
surface, slope and obstacles
- perform a fly-over at a speed of 120 km/hod above the selected
landing site at suitable height (150 ft suggested), observe the landing
site
- Follow normal landings checklist and land,
after touchdown perform the following:
- ignition off
- master switch off
- fuel tank valves shut
- brakes as required
3.6. Blown-Out Tire Landing
Use normal approach and landing procedure, keep the damaged wheel
above ground during the flare as long as possible using ailerons (or
elevator for the nose wheel).
3.7. Damaged Landing Gear Landing
Use normal approach and landing procedure, keep the damaged wheel
above ground during the flare as long as possible using ailerons (or
elevator for the nose wheel).

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3.8. Vibrations or other engine problem
Vibrations:
- set engine speed to such power setting where the vibrations are
minimum
- land as soon as possible, consider off-airfield landing, especially
when vibrations are increasing
Oil pressure drop – an engine failure is probable in this case:
Reduce the engine power and land as soon as possible (before an
failure occurs ), consider off-airfield landing.
3.9. Inadvertent icing encounter
- throttle increase above normal cruise settings
- course reverse or alter as required to avoid icing
- altitude climb (if possible)
3.10. Extreme turbulence encounter
- Airspeed reduce to 160 km/hod
- safety belts tighten
- loose objects secure
3.11. Electrical system malfunctions
Charging indicator illuminated: - switch all instruments not necessary
for the flight as all are only battery powered in this case.
3.12. Inadvertent Stall and spin recovery
Stall or spin should not occur during normal aircraft operation and are
prohibited.
3.12.1. Stall recovery:
-lower the nose by pushing the control stick
-gradually increase power
Loss of flight level in straight direction after stall is
150 - 200 ft = 45 - 60 m.