Alpi Aviation Pioneer 200 Aircraft Technical specifications

PIONEER 200 Aircraft FLIGHT MANUAL
__________________________________________
Document N° F2-1.0/R80/F/EU Dated 20-04-2002
Cover page
MANUFACTURER : ALPI AVIATION S.r.l.
Address : Via dei Templari, 24
City : 33080 San Quirino (PN)
Country : Italy
Web Site : www.alpiaviation.com
Telephone: [phone]
E - mail : [email protected]
AIRCRAFT TYPE & MODEL
Type : Pioneer
Model : 200
Aircraft Mark :
Aircraft S/N :
By : www.aeroprogetti.net

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TABLE OF CONTENTS
SECTION
General 1
Limitations 2
Emergency Procedures 3
Normal Procedures 4
Performance 5
Weight and Balance Statement 6
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AMENDMENT RECORD SHEET
Revision No. Page(s)
affected
Signature. Date of
Incorporation
0 All pages 20-03-02
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INTRODUCTION
This Flight Manual applies only to the particular aircraft identified by the registration
marking and serial number on the Cover Page and contains the airworthiness
limitations and essential operating data for this aircraft.
The Flight Manual shall be carried in the aircraft on all flights.
Special operations requiring additional limitations and instructions are listed in the
"Supplements Section" and this section shall be consulted before undertaking any
such operations. For operating information not included in this manual, reference
should be made to the appropriate operations or manufacturer's manuals.
The pilot in command the aircraft shall comply with all requirements, procedures
and limitations with respect to the operation of the aircraft set out in the Flight
Manual for the aircraft.
Amendments shall be issued by Alpi Aviation as necessary and will take the form of
replacement pages, with the changes to the text indicated by a vertical line in the
margin together with the amendment date at the bottom of the page.
Interim/Temporary amendments may be issued in the same manner and are to be
inserted as directed. These amendments will be issued on coloured pages and will
take precedence over the stated affected page. It is the owner's responsibility to
incorporate in this manual all such amendments, and to enter the date of
incorporation and his signature on the appropriate Amendment Record Sheet.
No entries or endorsements may be made to this Flight Manual except in the
manner and by persons authorised for the purpose.

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REVISIONS
It is the responsibility of the owner to maintain this Manual in a current status when
it is being used for operational purposes.
Owners should contact Alpi Aviation S.r.l. whenever the revision status of their
Manual is in question.
A revision bar will extend the full length of new or revised text and/or illustrations
added on new or presently existing pages. This bar will be located adjacent to the
applicable revised area on the outer margin of the page.
All revised pages will carry the revision number and the date on the applicable
page.
The following List of Effective Pages provides the dates of issue for original and
revised pages, and a listing of all pages in the Manual. Pages affected by the
current revision are indicated by an asterisk (*) preceding the pages listed.

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LIST OF EFFECTIVE PAGES
The dates of issue for original & revised pages are:
Page Rev. Date Page Rev. Date Page Rev. Date
Section 0 Section 3 Section 5
0-1 0 20-04-02 3-1 0 20-04-02 5-1 0 20-04-02
0-2 0 20-04-02 3-2 0 20-04-02 5-2 0 20-04-02
0-3 0 20-04-02 3-3 0 20-04-02
0-4 0 20-04-02 3-4 0 20-04-02
0-5 0 20-04-02 3-5 0 20-04-02
0-6 0 20-04-02 3-6 0 20-04-02
0-7 0 20-04-02 3-7 0 20-04-02
0-8 0 20-04-02 3-8 0 20-04-02 Section 6
3-9 0 20-04-02 6-1 0 20-04-02
3-10 0 20-04-02 6-2 0 20-04-02
3-11 0 20-04-02 6-3 0 20-04-02
3-12 0 20-04-02 6-4 0 20-04-02
3-13 0 20-04-02
3-14
Section 1 Section 4
1-1 0 20-04-02 4-1 0 20-04-02
1-2 0 20-04-02 4-2 0 20-04-02
1-3 0 20-04-02 4-3 0 20-04-02
1-4 0 20-04-02 4-4 0 20-04-02
1-5 0 20-04-02 4-5 0 20-04-02
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Section 2 4-9 0 20-04-02
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4-18 0 20-04-02
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DEFINITIONS
AIRFIELD PRESSURE ALTITUDE The Airfield Pressure Altitude is that altitude registered
at the surface of the aerodrome by an altimeter with
the pressure subscale set to 1013 millibars
INDICATED AIRSPEED (I.A.S.) Indicated airspeed, which is the reading obtained from
an airspeed indicator having no calibration error.
TAKEOFF SAFETY SPEED The Takeoff Safety Speed is a speed chosen to
ensure that adequate control will exist under all
conditions, including turbulence and sudden and
complete engine failure, during the climb after takeoff.
LANDING SAFETY SPEED The Landing Safety Speed is the speed chosen to
ensure that adequate control will exist under all
conditions, including turbulence, to carry out normal
flare and touchdown.
NORMAL OPERATING SPEED This speed shall not normally be exceeded.
Operations above the Normal Operating Speed shall
be conducted with caution and only in smooth air.
Va MANOEUVRING SPEED Maximum for manoeuvres involving an approach to
stall conditions or full application of the primary flight
controls.
KCAS KNOTS CALIBRATED
AIRSPEED
Indicated airspeed corrected for position and
instrument error and expressed in knots. KCAS is
equal to KTAS in standard atmosphere at sea level
KIAS KNOTS INDICATED
AIRSPEED
The speed shown on the airspeed indicator and
expressed in knots.
KTAS KNOTS TRUE AIRSPEED The airspeed expressed in knots relative to
undisturbed air which is KCAS corrected for altitude
and temperature.
V fe MAXIMUM FLAP EXTENDED
SPEED
The highest speed permissible with wing flaps in the
prescribed extended position.
V no MAXIMUM STRUCTURAL
CRUISING SPEED
The speed that should not be exceeded except in
smooth air, and then only with caution.
V ne NEVER EXCEED SPEED The speed limit that may not be exceeded at any time.
V s0 STALLING SPEED The stall speed or minimum steady flight speed at
which the airplane is controllable in a specified
configuration.
V so STALLING SPEED
LANDING CONFIGURATION
The stall speed or minimum steady flight speed at
which the airplane is controllable in the landing
configuration at the most forward centre of gravity.

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V x BEST ANGLE-OF-CLIMB
SPEED
The speed which results in the greatest gain of altitude
in a given horizontal distance.
V y BEST RATE-OF-CLIMB SPEED The speed which results in the greatest gain in altitude
in a given time.
METEOROLOGICAL TERMINOLOGY
OAT OUTSIDE AIR
TEMPERATURE
The free static air temperature. It is expressed in either
degrees Celsius or degrees Fahrenheit.
STANDARD TEMPERATURE Standard Temperature is 15 degrees C at sea level
pressure altitude.
PRESSURE ALTITUDE The altitude read from the an altimeter when the
altimeter's barometric scale has been set to 1013 mb
(29.92 inches of mercury).
ENGINE POWER TERMINOLOGY
BHP BRAKE HORSEPOWER The power developed by the engine.
RPM REVOLUTIONS PER MINUTE Engine speed.
STATIC RPM The engine speed attained during a full-throttle engine
runup when the airplane is on the ground and
stationary.
AIRPLANE PERFORMANCE AND FLIGHT PLANNING TERMINOLOGY
MAXIMUM CROSSWIND VELOCITY The velocity of the crosswind component for which
adequate control of the airplane during takeoff and
landing was actually demonstrated during the
certification tests. The value shown is limiting.
USEABLE FUEL The fuel available for flight planning
UNUSABLE FUEL The quantity of fuel that cannot be safely used in flight
LPH LITRES PER HOUR The amount of fuel ( in litres ) consumed per hour
NMPL NAUTICAL MILES PER
LITRE
The distance ( in nautical miles ) which can be
expected per litre of fuel consumed at a specific
engine power setting and/or flight configuration.
g The acceleration due to gravity.

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WEIGHT AND BALANCE TERMINOLOGY
STATION Only two load stations are specified: ie Seat Station
which is the centre of the fixed seats and Fuel Station
which is the centre of the fixed fuel tank.
C.G. CENTRE OF GRAVITY The point at which an airplane, or equipment, would
balance if suspended.
C.G. LIMITS The extreme centre of gravity locations within which
the airplane must be operated at a given weight.
STANDARD EMPTY WEIGHT The weight of a standard airplane, including unusable
fuel, full operating fluids and full engine oil.
BASIC EMPTY WEIGHT The standard empty weight plus the weight of optional
equipment.
USEFUL LOAD - The difference between ramp weight and the basic
empty weight.
MTOW MAXIMUM TAKEOFF
WEIGHT
The maximum weight approved for the start of the
takeoff run.

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Section1 - General
Table of Contents
1.1. AIRCRAFT THREE VIEW DRAWING 2
1.2. TECHNICAL DATA 4
1.2.1. ENGINE 4
1.2.2. PROPELLER 4
1.2.3. APPROVED FUEL TYPES AND GRADES 4
1.2.4. FUEL CAPACITY 4
1.2.5. APPROVED OIL GRADES 5
1.2.6. COOLANT 5
1.2.7. OIL CAPACITY 5
1.2.8. TYRE INFLATION PRESSURES 5

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1.1. AIRCRAFT THREE VIEW DRAWING

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Ground Turning Radius = 6 metres.

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1.2. TECHNICAL DATA
1.2.1. ENGINE
Manufacturer: ROTAX GmbH
Aircraft Engine
Type: 912 UL Series liquid cooled
1.2.2. PROPELLER
Manufacturer: TONINI
Type: Fixed Pitch Wooden
GT 166X142
Diameter: 166 cm
Pitch: 142 cm
1.2.3. APPROVED FUEL TYPES AND GRADES
-UNLEADED MOGAS (98 Octane or greater - 90 RON or greater)
-100 LL or 100/130 grade aviation gasoline
(only for short utilization time, with carbon level inspection)
1.2.4. FUEL CAPACITY
Total: 54 Litres
Useable 50 Litres

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1.2.5. APPROVED OIL GRADES
Motorcycle oil of a registered brand with gear additive
Specification API classification "SJ" or "SG"
Exemples : Shell - Advance VSX 4 (SAE 20W-40)
Castrol - Syntetic Blend (SAE 5W-50)
Shell - Synthetic Blend (SAE 10W-30)
For temp. Above and belove stated check Rotax engine manuals
For AVGAS use chech Rotax engine manuals
1.2.6. COOLANT
Antifreeze concentrate with additives against corrosion should be used with 50%
water in normal condition, and down 20% water in cold environment.
Capacity Max 2,3 litres Min 2,2 litres
Overflow or filler tank Max 0,2 lt Min 0,1 lt
1.2.7. OIL CAPACITY
Sump capacity is : 3 Litres
1.2.8. TYRE INFLATION PRESSURES
Standard Mains: bar = 2.2 (psi = 32.3)
Nose: bar = 2.2 (psi = 32.3)

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INTENTIONALLY LEFT BLANK

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Section 2 - Limitations
Table of Contents
Table of contents 1
2.1. Introduction 2
2.2. Type of operation 2
2.3. Airspeed limitations 2
2.4. Weights and loading 3
2.5. Centre of gravity limits 3
2.6. Powerplant limitations 4
2.7. Other limitations 4
2.7.1. Authorised manoeuvres and limitations 4
2.7.2. Smoking 4
2.7.3. Max. air temperature for operations 5
2.7.4. Flights with doors removed 5
2.7.5. Maximum number of occupants 5
2.7.6. Maximum crosswind velocity 5
2.8. Placards 6

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2.1. INTRODUCTI0N
Section 2 includes operating limitations, instrument markings and basic
placards necessary for the safe operation of the airplane, its engine,
standard systems and standard equipment. Observance of these
operating limitations is required.
The aeroplane shall be operated so that the limitations and instructions
included in this section are observed.
2.2. TYPE OF OPERATION
VFR by Day
see also para 2.7.1. Authorised mamoeuvres and limitations.
2.3. AIRSPEED LIMITATIONS
Airspeed limitations and their operational significance are shown below.
SPEED Km/h REMARKS
V ne Never exceed speed 240 Do not exceed this speed in any
operation.
V no Maximum structural
cruising speed
215 Do not exceed this speed except in
smooth air, and then only with caution.
V a Manoeuvring speed 180 Do not make full or abrupt control
movements above this speed.
V fe Maximum flap extended
speed
Vso Stall speed
100
63
Do not exceed this speed with flaps
down.
Whit extended flaps

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Airspeed Indicator Markings and their operational significance are
shown below.
MARKING Km/h
Range
SIGNIFICANCE
White Arc 65 - 100 Full-flap operating range. Lower limit is max. weight
Vso in landing configuration. Upper limit is max.
speed permissible with flaps extended.
Green Arc 100 - 180 Normal operating range. Lower limit is Take-off
Safety speed. Upper limit is max. structural cruising
speed.
Yellow Arc 180 - 215 Operations must be conducted with caution and only
in still air.
Red Line 240 Vne
2.4. WEIGHTS and LOADING
Maximum takeoff weight 450 Kg
Maximum landing weight 450 Kg
2.5. CENTRE OF GRAVITY LIMITS
Forward :600 mm aft of datum up to & including 350 Kg
685 mm aft of datum @ 450 Kg.
Variation is linear between 350 & 450 kg.
Aft : 768 mm aft of datum at all weights
Datum :Fire-guard bulcked
Leveling Means:
Longitudinal Spirit Level placed lateral canopy strut
Lateral Spirit Level crossing canopy

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2.6. POWERPLANT LIMITATIONS
Instrument Yellow Arc Green Arc Red Radial
Line/Arc
Tachometer 1000 - 1400RPM 1400 - 5500 RPM 5800 RPM
Oil Temp. 50° - 90° C
(120° - 190° F)
90o- 110oC
(190° - 230° F)
140° C
(285° F)
Oil Pressure 0,8 - 2,0 bar
(12 - 29 psi)
2,0 - 5,0 bar
(29 - 73 psi)
7 bar
(102 psi)
Cylinder Head
Temperature
90° - 150° C
(190° - 300° F)
150° C
(300° F)
Minimum Oil
Temperature for Takeoff
Needle must be seen to move off the stop
before Takeoff
Minimum Oil Pressure in Level Flight or climb 2 bar (29 psi)
In Descent 0,8 bar (12 psi)
Maximum Cylinder Head Temperature 150° C (300° F)
Maximum RPM for all operations 5800
Full Throttle Static RPM Not Above 5500
Not Under 5300
2.7. OTHER LIMITATIONS
2.7.1. AUTHORISED MANOEUVRES AND ASSOCIATED
LIMITATIONS
Acrobatic maneuver, including spins, are not permitted.
2.7.2. SMOKING

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Prohibited.
2.7.3. MAXIMUM AIR TEMPERATURE FOR OPERATIONS
40oC for takeoff at gross weight.
2.7.4. MAXIMUM PERMISSIBLE NUMBER OF OCCUPANTS
Two (including Pilot).
2.8 MAXIMUM CROSSWIND VELOCITY
25 Km/h