Aeropro CZ A240 User manual

AEROPRO CZ ,Producer of Light Sport Aircraft
Mladá 835, 687 25 Hluk, Czech Republic
Pilot Operating Handbook
and
Flight Training Supplement
AEROPRO CZ
A240
Light Sport Aircraft

Aeropro CZ - A240 - Pilot Operating Handbook and Flight Training Supplement
September 1, 2014
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Aircraft Type: A240
Serial Number:
Registration:
Date of Issue: September 01, 2014
version 1.0
This aircraft was manufactured in accordance with Light Sport Aircraft airworthiness standards
and does not conform to standard category airworthiness requirements.

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RECORD OF REVISIONS
Any revisions or amendments to the present manual shall be issued in the form of bulletins with attached
new pages. It is in the interests of every user to enter such revision into the table of revisions and to
replace the existing page by the new one. The revised or corrected text shall be indicated by a vertical line
on left page margin and the page shall bear revision number and date of its issue.
Rev. No.
Pages Affected
Date of Issue
Bulletin Number
New Page Inserted On, Signature

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TABLE OF CONTENTS:
RECORD OF REVISIONS.............................................................................. ..0-3
0. GENERAL INFORMATION..................................................................... 0-7
0.1 INTRODUCTION ....................................................................................... 0-7
0.2 CERTIFICATION BASIS............................................................................. 0-7
0.3 MANUFACTURER .................................................................................... 0-7
0.4 WARNING,CAUTION AND NOTE.............................................................. 0-7
1. AIRPLANE AND SYSTEMS DESCRIPTION......................................... 1-8
1.1 ENGINE................................................................................................... 1-9
1.2 PROPELLER............................................................................................. 1-9
1.3 FUEL AND FUEL CAPACITY ...................................................................... 1-9
1.4 OIL........................................................................................................ 1-11
1.5 OPERATING WEIGHTS &LOADING (OCCUPANTS,BAGGAGE,FUEL).........1-11
1.6 COCKPIT OVERVIEW...............................................................................1-12
1.7 AIRCRAFT ELECTRICAL SYSTEM........................................................... 1-17
1.8 Electric Backup Fuel Pump..…………………………………………………….1-17
1.9 Additional Equipment........................................................................... 1-17
2. OPERATING LIMITATIONS................................................................. 2-18
2.1 STALL SPEED AT MAXIMUM TAKE-OFF WEIGHT (VS AND VSO) ............ 2-18
2.2 FLAPS EXTENDED SPEED RANGE (VSO TO VFE)................................... 2-18
2.3 MAXIMUM MANEUVERING SPEED (VA) ................................................ 2-19
2.4 NEVER EXCEED SPEED (VNE)............................................................... 2-19
2.5 CROSSWIND AND WIND LIMITATION ...................................................... 2-19
2.6 SERVICE CEILING .................................................................................. 2-19
2.7 LOAD FACTORS..................................................................................... 2-19
2.8 PROHIBITED MANEUVERS...................................................................... 2-19
2.9 OTHER LIMITATIONS............................................................................. 2-20
3. WEIGHT AND BALANCE INFORMATION........................................ 3-21
3.1 INSTALLED EQUIPMENT LIST ................................................................. 3-21
3.2 CENTER OF GRAVITY (CG) RANGE AND DETERMINATION...................... 3-21
3.2.1 Weight and balance determination for flight ............................... 3-21
3.2.2 Detailed calculation of CG position…………………………...…. 3-21
4. PERFORMANCE...................................................................................... 4-24
4.1 TAKE-OFF AND LANDING DISTANCES..................................................... 4-24
4.2 RATE OF CLIMB..................................................................................... 4-24
4.3 CRUISE SPEEDS ..................................................................................... 4-24
4.4 RPM..................................................................................................... 4-24
4.5 FUEL CONSUMPTION ............................................................................. 4-25
4.6 OTHER PERFORMANCE DATA ................................................................ 4-25
5. NORMAL PROCEDURES....................................................................... 5-26
5.1 PREFLIGHT INSPECTION......................................................................... 5-26
5.1.1 Daily preparation ........................................................................ 5-26
5.1.2 Preflight Inspection...................................................................... 5-28
5.2 ENGINE STARTING................................................................................. 5-28
5.2.1 Use of External Power Supply ..................................................... 5-29
5.2.2 Engine Starting ............................................................................ 5-29
5.3 TAXIING................................................................................................ 5-29
5.3.1 Prior to taxiing............................................................................. 5-29

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5.3.2 Taxiing………………………………………………………………… 5-29
5.3.3 Engine warm-up, power check..................................................... 5-30
5.4 NORMAL TAKE-OFF............................................................................... 5-30
5.4.1 Prior to take-Off........................................................................... 5-30
5.4.2 Take-off........................................................................................ 5-31
5.5 BEST ANGLE OF CLIMB SPEED (VX) ...................................................... 5-31
5.5.1 Climbing....................................................................................... 5-31
5.6 BEST RATE OF CLIMB SPEED (VY)......................................................... 5-32
5.6.1 Climbing....................................................................................... 5-32
5.7 CRUISE.................................................................................................. 5-32
5.7.1 Cruise Flight................................................................................ 5-32
5.8 APPROACH............................................................................................ 5-32
5.8.1 Descent......................................................................................... 5-32
5.8.2 Downwind.................................................................................... 5-32
5.9 NORMAL LANDING................................................................................ 5-33
5.9.1 On base leg .................................................................................. 5-33
5.9.2 On final........................................................................................ 5-33
5.9.3 Landing........................................................................................ 5-33
5.9.4 After landing ................................................................................ 5-33
5.9.5 Engine stopping ........................................................................... 5-33
5.9.6 Post-flight check .......................................................................... 5-34
5.10 SHORT FIELD TAKE-OFF AND LANDING PROCEDURES............................. 5-34
5.11 ABORTED LANDING PROCEDURES ......................................................... 5-34
5.12 INFORMATION ON STALLS,SPINS AND ANY OTHER USEFUL PILOT INFORMATION.... 5-34
5.12.1 Rain.............................................................................................. 5-34
6. EMERGENCY PROCEDURES............................................................... 6-35
6.1 INTRODUCTION ..................................................................................... 6-35
6.2 ENGINE FAILURE AND EMERGENCY LANDINGS ..................................... 6-35
6.2.1 Engine failure during take-off Run .............................................. 6-35
6.2.2 Engine failure during take-off...................................................... 6-35
6.2.3 In-flight engine failure................................................................. 6-35
6.2.4 Additional information for engine failure and emergency landing procedures.... 6-36
6.2.5 Carburetor icing .......................................................................... 6-36
6.3 IN-FLIGHT ENGINE STARTING ............................................................... 6-37
6.4 FIRES .................................................................................................... 6-37
6.4.1 Engine fire on the ground............................................................ 6-37
6.4.2 Engine fire during take-off........................................................... 6-37
6.4.3 Engine fire in-flight...................................................................... 6-38
6.4.4 Cockpit or electrical fire.............................................................. 6-38
6.5 GLIDING................................................................................................ 6-38
6.6 PRECAUTIONARY LANDING................................................................... 6-38
6.7 BLOWN-OUT TIRE LANDING................................................................. 6-39
6.8 DAMAGED LANDING GEAR LANDING.................................................... 6-39
6.9 VIBRATIONS OR OTHER ENGINE PROBLEMS........................................... 6-39
6.10 INADVERTENT ICING ENCOUNTER ......................................................... 6-39
6.11 EXTREME TURBULENCE ENCOUNTER.................................................... 6-40
6.12 ELECTRICAL SYSTEM MALFUNCTIONS................................................... 6-40
6.12.1 Charging indicator is illuminated ................................................ 6-40
6.13 INADVERTENT RESCUE SYSTEM STALL AND SPIN RECOVERY ............... 6-40
6.13.1 The following general procedure should be followed should a stall occur: 6-40
6.13.2 The following general procedure should be followed should a spin occur: 6-40
6.14 RESCUE SYSTEM …………………………………………………...6-40
6.14.1 Operation of Rescue System……………………………………….….6-40

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7. AIRCRAFT GROUND HANDLING AND SERVICING...................... 7-41
7.1 SERVICING FUEL,OIL,COOLANT............................................................ 7-41
7.1.1 Servicing fuel .............................................................................. 7-44
7.1.2 Servicing oil................................................................................. 7-41
7.1.3 Servicing coolant ......................................................................... 7-41
7.2 LANDING GEAR TIRE DIMENSION AND PRESSURE................................... 7-42
7.3 TOWING AND TIE-DOWN INSTRUCTIONS ................................................ 7-42
7.3.1 Aircraft towing instructions ......................................................... 7-45
7.3.2 Aircraft tie-down instructions ...................................................... 7-42
7.4 PARKING BRAKE OPERATION...................................................................7-42
8. REQUIRED PLACARDS AND MARKINGS......................................... 7-43
8.1 AIRSPEED INDICATOR RANGE MARKINGS .............................................. 7-43
8.2 OPERATING LIMITATION ON INSTRUMENT PANEL .................................. 7-44
8.3 PASSENGER WARNING........................................................................... 7-44
8.4 “NO INTENTIONAL SPINS”...................................................................... 7-44
8.5 MISCELLANEOUS PLACARDS AND MARKINGS........................................ 7-44
9. SUPPLEMENTARY INFORMATION................................................... 8-45
9.1 FLIGHT FAMILIARIZATION PROCEDURES................................................ 8-45
9.2 PILOT OPERATING ADVISORIES.............................................................. 8-45
9.3 FURTHER INFORMATION ....................................................................... 8-45
10. APPENDIX
10.1 Airplane weight and balance statement………………………………..10-1

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0. General information
0.1 Introduction
This handbook is provided with your aircraft to allow you to attain as much knowledge about the aircraft
and its operation as possible. This manual is following ASTM F2746-14 Standard Specification for Pilot’s
Operating Handbook (POH) for Light Sport Airplane. Read this manual thoroughly before your first flight
and make sure you understand all the information contained within. This aircraft is equipped with a non-
certified engine that meets the ASTM F2339-06 engine standard. Flying this aircraft must always be done
with the possibility of a safe landing due to loss of engine power.
Pay attention to the fact that you as the pilot are fully responsible for the safety of your passengers and
persons or property on the ground.
0.2 Certification basis
This aircraft was manufactured in accordance with Light Sport Aircraft airworthiness standards and does
not conform to standard category airworthiness requirements.
0.3 Manufacturer
Aeropro CZ
Mladá 835
687 25 Hluk
Czech Republic
0.4 Warnings, cautions and notes:
In this handbook the following is used to highlight especially important information:
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 pilots

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1. Airplane and systems description
The Aeropro A240 is an S-LSA aircraft designed as a high-wing monoplane. A two-spar wing is equipped
with external airfoil flaperons. Fuselage is an open truss structure welded of chromoly steel tubes. Tail
unit is formed of a lattice-work tube frame. The A240 is equipped with tricycle-gear with a steerable
nosewheel.
Wing area including flaperons……………………………………….. 122.53 sq. ft
Chord length (including flaperon)……………………….…………… 4.265 ft
Wing loading............................................................................... 10.1 lbs/sq. ft
Power loading............................................................................. 12.35 lbs/HP
Aspect-ratio................................................................................. 6.74:1
Propeller clearance..................................................................... 11.5 inches

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1.1 Engine
The A240 is powered by the Rotax 912ULS 100-hp engine. It is a four-cylinder, four-stroke, horizontally-
opposed, center-camshaft engine with overhead valves. Engine cooling is of a combined type; cylinder
heads are water-cooled while cylinders are air-cooled. The engine has dry-sump lubrication. The ignition
system is a dual, electronic and capacitor flywheel magneto type. The engine is equipped with an electric
starter, AC generator and a mechanical fuel delivery pump. The propeller is driven by an integrated
reduction gearbox with mechanical damping.
Engine manufacturer........................................ Rotax GmbH., Austria
Engine model...................................................... Rotax 912ULS
Max. power - take-off.................. 100 hp
- continuous............. 94 hp
Max. engine speed (MSL) - take-off................ 5800 RPM (max. 5 min)
- continuous........... 5500 RPM
Max. cylinder head temperature............................................. 280F
Min. oil temperature………………………………………….….... 122F for full-throttle operation
Normal operating temperature………………………………....…190 –230F
Max. oil temperature................................................................ 300F
Minimum oil pressure……………...................…...................… 12 psi min oil pressure below 3,500 rpm
Maximum oil pressure (cold start only)……………………........ 103 psi
Normal oil pressure range...................................................... 29 –73 psi
Oil consumption ……………………………………………….... max 0.06 quarts/hour
Fuel pressure - minimum............................................... .18 bar (2.2 psi)
- maximum.............................................. .4 bar (5.8 psi)
Propeller gearbox reduction ratio............................................. 2.43 : 1
For more details see Operator’s Manual for all versions of Rotax 912 supplied with the engine.
WARNING
This aircraft is equipped with a non-certified engine that meets the ASTM F-2339
engine standard.
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.
1.2 Propeller
The standard propeller is manufactured by Woodcomp in the Czech Republic. The propeller is a 3-blade,
ground-adjustable prop. Propeller is 68" diameter.
For additional propeller information see Operators Manual and Technical description supplied with the
propeller.
1.3 Fuel and fuel capacity
Fuel tank capacity - wing tanks (two)................................. 10.6 U.S. gallons each
- central connecting tank (header tank)........................... 1.3 U.S. gallons
Max. fuel quantity............................................................. 22.5 U.S. gallons
Usable fuel quantity......................................................... 22.0 U.S. gallons
Unusable fuel quantity...................................................... 0.5 U.S. gallons
Fuel specifications………...... premium unleaded auto fuel (Standard Spec. for Automotive
Spark-Ignition Engine, Fuel, ASTM D 4814) or AVGAS 100 LL

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Due to the higher lead content in AVGAS, the wear of the valve seats, deposits in the 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 additional information concerning fuel specification consult the Operator’s Manual for all versions
of Rotax 912 supplied with the engine.
The fuel system consists of two 10.6 U.S. gallons wing tanks, a 1.1 U.S. gallons central header tank
behind the left seat, a fuel drain valve positioned below the header tank, three fuel valves, one fuel filter,
an engine driven fuel pump, a backup electric fuel pump (not shown in the diagram below), and the
connecting fuel lines.
The fuel is gravity-fed from the right-hand and/or left-hand wing tank, through the wing tank fuel values,
into the central header tank. The fuel is then further directed from the central tank through the fuel filter
and the electric fuel boost pump through the main fuel valve and to the mechanical fuel pump on the
engine which then delivers the fuel to the carburetors.
The amount of fuel in each tank is indicated by a visual sight tube which is a part of each tank. Minimum
fuel quantity in the central tank is indicated by a red warning light on the instrument panel. The remaining
fuel (0.9 U.S. gallon), is enough for approximately 10 minutes of flight. The low fuel warning light can be
tested at any time by pushing the control button next to the light on the instrument panel. If the red light
does not light up when the control button is pushed and held, consider the bulb to be blown out and so do
not rely on the minimum fuel quantity warning light: - In this case, make a more conservative estimate for
fuel on board, regularly check the fuel quantity in wing tanks and land as soon as you are not confident of
the fuel quantity in the wing tanks.
Although it is normal to leave both wing tank fuel values open, occasionally, one tank will drain faster than
the other. Should this situation occur, manipulate the fuel tank valves to ensure continuous flow of fuel to
the engine is maintained.

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The fuel drain valve outlet is located behind and below the left seat on the outside of the fuselage; to
check for water and dirt, push the neck of the drain pipe gently upwards, into the fuselage and
subsequently a fuel sample can be taken.
For refuelling information see section 7.1
1.4 Oil
Oil tank capacity…………………………………………………. 3.2 quarts
Maximum oil quantity……………………………………………. 2.6 quarts
Minimum oil quantity……………………………………………. 2.1 quarts
Oil specification:
Use semi-synthetic 10w40 motorcycle type oil of a registered brand name. Caution: When selecting the
most suitable lubricants refer to the additional information in the Rotax Service Information SI-18-1997.
Normally the recommended oil is Aeroshell Sport 4 (a 10w40 semi-synthetic oil).
—Use only oil with API classification "SF" or "SG"!
—Due to the high stresses in the reduction gears, oils with gear additives such as high
performance motor cycle oils are required
—Because of the incorporated friction clutch, oils with friction modifier additives are
unsuitable as this could result in a slipping clutch during normal operation.
—Heavy duty 4-stroke motor cycle oils meet all the requirements. These oils are normally
not mineral oils but are semi- or full synthetic oils.
—Oils primarily for Diesel engines are insufficient due to high temperature properties
and additives which favor clutch slipping, generally therefore are unsuitable.
CAUTION: If the engine is mainly run on AVGAS more frequent oil changes will be required. See Rotax
Service Information SI-18-1997.
For additional information concerning oil system consult Operator’s Manual for all versions of Rotax
912 supplied with the engine.
The maximum and minimum oil level is indicated by two marks on the dipstick in the oil tank.
1.5 Operating weights and loading (occupants, baggage, fuel, ballast)
Empty weight (with typical options)....................................... 655 lbs
Max. take-off weight............................................................. 1235 lbs
Max. landing weight............................................................... 1235 lbs
Max. fuel weight…………………………………………………. 135 lbs
Max. baggage weight in baggage compartment……………. 50 lbs
Maximum number of persons on board…………………....... 2
Minimum crew weight…………………………………………… 121 lbs
WARNING
Make sure that above-mentioned weight limits are strictly followed.
Structural failures which result from overloading of the aircraft may
be dramatic and catastrophic.
The additional stress placed on the structural parts by overloading can accelerate the occurrence of metal
fatigue failures. Also, flight characteristics might change significantly when aircraft is overloaded. Take-off
and landing distance is significantly longer for overloaded aircraft. Overloading of the aircraft is one of the
causes of accidents.

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1.6 Cockpit overview
LAYOUT OF CONTROLS AND INSTRUMENTS (see following pages for details concerning Figures 1-9)
Fig.1 airspeed indicator
1. control stick
19. area for GPS or iPad installation
Fig.2 engine start up
2. rudder pedals
20. air vents
Fig.3 main fuel valve
3. flaperon control knob
21. EIS engine instrumentation
Fig.4 EIS engine instrument
4. elevator trim control knob
22. intercom
Fig.5 central control panel
5. main fuel valve
23. ELT panel controller
Fig.6 flaps, trim
6. boost pump switch
24. Rotax fuel pressure gauge
Fig.7 switches and circuit breakers
7. keyed igntion switch
25. cigarette lighter type power socket
Fig.8 control lights
8. magneto on/off switches
26. circuit breaker for power socket
Fig.9 door lock mechanism
9. airspeed indicator
27. mapbox
10. altimeter/VSI
28. throttle
11. transponder
29. carb heat knob
12. radio
30. cockpit heat knob
13. EFIS/attitude indicator (optional)
31. oil cooler flap knob
14. annunciator test button
32 brake lever
15. low fuel level warning light
33. choke lever
16. low voltage warning light
34. switches
17. EIS warning light
35. circuit breakers
18. compass

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List of typical installed instruments and other equipment including options:
Type
Serial No.
airspeed indicator
ASI 150 M-3
altimeter and vertical speed indicator
MGL ALT-3 electronic
slip indicator (in EFIS)
magnetic compass
CM - 13
fuel pressure
BDT1/31/B
ELT
ELT345
radio-intercom
ATR833-OLED and PM1000II
transponder with encoder
Funkwerk Avionics TRT800H-OLED
EFIS or attitude indicator (optional)
Figure 1 - Airspeed Indicator marking
Figure 2 - Ignition and master switch
Ignition OFF
Ignition ON

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Figure 3 - Main Fuel Valve open and closed position
Figure 4 - EIS Model 4000 for Rotax 912-series engines
Display panel description (shown is EIS page 1 - default display page)
tachometer - engine RPM
OAT - outside air temperature
H2O –coolant temperature
oil temperature
flight timer
EGT - exhaust gas temperature (hottest EGT)
oil pressure
Indicator unit alert limits max limit
Engine rotation speed (rpm)..........................5600 ................. 5800
EGT/Exhaust gas temperature (ºF) ..............1650 .................. 1850
H2O/coolant temperature (ºF) ..................... 228 ................... 248
Oil temperature, (ºF) ..................................... 260 ................... 300
Oil pressure, max (psi) ................................. 84 ................... 100
Oil pressure, min (psi) .................................. 28 .................. 12 (minimum)
Oil pressure, normal (psi)............... 29 - 72

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The EIS system not only alerts you when reaching an actual system limit, it also has the
capability to provide alerts when reaching a Warning Limit that is just short of the actual non-
permissible limit.
When one or more Warning Limits are exceeded –the corresponding value blinks on the EIS
display, the alarm lamp on the instrument panel blinks. When the pilot presses the “Next/Ack”
button on the EIS, the Alarm Lamp goes steady until the out of tolerance condition is corrected.
When the actual limit is reached, the EIS reacts in the same manner as a new fault, except the
alarm lamp blinks at longer intervals. The pilot must press Next/Ack again to turn both the
blinking alarm light and EIS display to steady.
Figure 5 –central panel
Note: Rotate throttle lever knob for fine power settings (clockwise to increase power, counterclockwise to reduce
power), for larger changes push/pull throttle when the button is pressed and held.

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Figure 6 –Flaps and trim
Figure 7 –Switches and fuses panel (older panel shown...)
Figure 8 –Control lights and fuel reserve bulb check button

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Figure 9 –Door locking mechanism
The battery (Powersafe SBS8, 12v, 7 ah) is located behind the right-hand pilot’s seat. Nominal voltage in
aircraft system is 13.5 to 14.2 V. The engine is equipped with an integrated AC generator with external
rectifier-regulator (12 V, 20A DC).
1.7 Aircraft lighting equipment
The A240 features the Whelen Microburst-III LED wingtip lights. This system consists of a white
rearward-facing LED lights and a flashing LED strobe light on the side of both wingtips, a green forward-
facing LED light on the right wingtip and a red forward-facing light on the left wingtip. There is also a
landing light fitted to the lower nose cowling which also acts as a taxi light. Power for the light system is
taken from the aircraft's main power supply.
NOTE: The A240 is NOT approved for night flight, and the exterior aircraft lighting does not comply with all
the FAR requirements for night flight.
1.8 Electric fuel pump
The A240 is equipped with an electric fuel pump with an on/off switch and "on" indicator light on the
instrument panel. The electric fuel pump serves as a booster or backup to the engine-driven mechanical
fuel pump. The electric fuel pump should be used at any time when the sudden failure of the
engine-driven mechanical fuel pump and a loss of fuel pressure could cause a loss of engine
power and compromise safety. Normally this will mean utilizing the electric fuel pump during
takeoff, during climb-out to a safe minimum altitude, during any low-altitude operations, and
during landing.
1.9 Additional equipment
reserved

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2. Operating limitations
Airspeed indicator system calibration:
As requested by ASTM F-2245-04 §9.1 all flight speeds are presented as calibrated airspeeds in miles
per hours (MPH). As the calibrated airspeed cannot be usually determined by a simple reading of the
aircraft airspeed indicator, corresponding Indicated airspeeds in miles per hours (MPH) are also
presented in this document. All airspeed values in this handbook assume no instrument error.
2.1 Stall speed at maximum take-off weight (VSand VSO)
Aircraft configuration
Stall speed –angle of bank 0°
MPH (Indicated Air speed)
MPH (Calibrated Air speed)
Flaps down (Vso)
41
45
Flaps up (V s)
.49
.50
WARNING
The stall speed mentioned above are with wings level. Once any angle of bank
(e.g. turn) is encountered the stall speed is significantly increasing.
example: angle of bank 60° ……. VS = 73 MPH
The more bank –the higher the stall speed. This simple rule is especially important when a turn at
maximum permitted angle of bank (60°) is performed. Do not start the turn until you have sufficient
airspeed reserve –recommended entry speed is 92 MPH. Full throttle is also essential to have sufficient
thrust reserve as the drag is increasing during a steep turn.
2.2 Flaps extended speed range (VSO to VFE)
MPH (Indicated Air Speed)
MPH (Calibrated Air Speed)
Lower limit
41
45
Upper limit
93
90
MPH
(Indicated Air
speed)
MPH
(Calibrated Air
speed)
40 44
46 48
57 59
69 69
81 79
92 89
104 99
115 109

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2.3 Maximum maneuvering speed (VA)
MPH (Indicated Air Speed)
MPH (Calibrated Air Speed)
Max. maneuvering speed (VA)
109
104
2.4 Never exceed speed (VNE)
MPH (Indicated Air Speed)
MPH (Calibrated Air Speed)
Never exceed speed (VNE)
143
134
2.5 Crosswind and wind limitation
Maximum permitted wind speed components for take-off and landing:
max. headwind ………………….…………….............. 28 mph (25 knots)
crosswind……………………………………………..…. 17 mph (15 knots)
tail wind………………………………………………..…. 7 mph (6 knots)
Crosswind take-offs and landings require training and experience, the higher crosswind component, the
better your skill must be. Do not fly without proper experience when the wind speed is approaching the
limit.
Avoid take-offs with a tail wind when possible –the total take-off distance is significantly longer and longer
ground distance is required to gain altitude.
When landing with a tail wind the aircraft ground speed is higher resulting in longer landing distance.
2.6 Service ceiling
Service ceiling.................................................................. 14,760 ft (standard day)
WARNING
Oxygen mask and/or other equipment as required to reach
maximum ceiling, consult respective regulations.
2.7 Load factors
Flaps up:
Maximum positive load factor (measured at CG)………..…… +4 Gs
Maximum negative load factor (measured at CG)…………… - 2 Gs
Flaps down:
Maximum positive load factor (measured at CG)…………….. +2 Gs
Maximum negative load factor (measured at CG)……………. 0 Gs
2.8 Prohibited maneuvers
WARNING
Aerobatics and intentional spins are prohibited.
Maximum angle of bank: 60°

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2.9 Other Limitations
WARNING
No smoking.
WARNING
Flights with rear cockpit cover removed are prohibited.
WARNING
Flights at ambient temperature between 14F and 32F are permitted only
under no icing conditions and when the carburetor heating is activated.
WARNING
IFR flights and flying in clouds is prohibited.
Night Flights are prohibited.
Flight into know icing conditions is prohibited.
This aircraft is not certified for operation in IMC (Instrument meteorological conditions). Always stay clear
of clouds and have visual contact with the ground. Follow the airspace classification regarding distance
from clouds. Always evaluate weather during your flight and try to get weather information from your
destination using radio whenever possible. When weather is deteriorating make a diversion or turn back
before the low cloud base and/or low visibility are critical. The aircraft is not certified to be flown at night.