czech sport aircraft SportCruiser Owner's manual

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Pilot’s Operating Handbook
Airplane Registration Number: N4465F
Airplane Serial Number: 08SC142

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S
Sp po or rt tC Cr ru ui is se er r a ai ir rc cr ra af ft t
i
is s d de es si ig gn ne ed d a an nd d m ma an nu uf fa ac ct tu ur re ed d b by y: :
Czech sport aircraft a.s.
Na Záhonech 1177/212, 686 04 Kunovice
Czech Republic
Website: www.czechsportaircraft.com
E-mail: [email protected]
Phone: [phone] (Sales Dept.)
Fax: [phone]

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SC-POH-1-1-17
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RECORD OF REVISIONS
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RECORD OF REVISIONS
No. Affected pages Revision name Date of Issue Signature

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SC-POH-1-1-17LIST OF EFECTIVE PAGES S
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LIST OF EFFECTIVE PAGES
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LIST OF EFFECTIVE PAGES (Cont’d)
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SC-POH-1-1-17LIST OF ABBREVIATIONS S
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LIST OF ABBREVIATIONS
ADI Attitude direction indicator
AGL Above Ground Level
ALT Altitude or Altimeter
ATC Air Traffic Control
ASI Airspeed Indicator
bar Pressure unit (1 bar = 14.5037 psi)
BEACON Anti-collision beacon
°C Temperature in degree of Celsius (°C = (°F - 32) / 1.8)
CAS Calibrated Airspeed
CDI Course deviation indicator
C.G. Center of Gravity
CHT Cylinder head temperature
COMM Communication transceiver
EFIS Electronic Flight Information System
ELT Emergency Locator Transmitter
EMS Engine Monitoring System
°F Temperature in degree of Fahrenheit (°F = (°C x 1.8) + 32)
ft Foot or feet (1 ft = 12 in = 0.305 m = 305 mm)
fpm Vertical speed in feet per minute (1 fpm = 0.0051 m/s)
GPS Global Positioning System
hp Power unit (1 hp = 0.7457 kW)
IAS Indicated Airspeed
IC Intercom
IFR Instrument Flight Rules
in Inch (1 in = 25.4 mm)
ISA International Standard Atmosphere
KCAS Calibrated Airspeed in Knots
kg Kilogram (1 kg = 2.205 lb)
KIAS Indicated Airspeed in Knots
km Kilometer (1 km = 1000 m = 0.54 NM = 0.621 SM)
km/h Airspeed in kilometers per hour
(1 km/h = 0.54 knots = 0.621 mph = 0.278 m/s)
knot Airspeed in NM per hour
(1 knot = 1.151 mph = 1.852 km/h = 0.514 m/s)
KTAS True Airspeed in Knots
kW Power unit (1 kW = 1.341 hp)
L Liter (1 L = 0.22 UK gal = 0.264 US gal)
lb Pound (1 lb = 0.454 kg)
lbf Force unit (1 lbf = 4.448 N)
m Meter (1 m = 1000 mm = 3.28 ft = 39.37 in)
mm Millimeter (1 mm = 0.03937 in)
MAC Mean Aerodynamic Chord
max. Maximum
min. Minimum or minute
mph Airspeed in statute miles per hour(1 mph = 0.87 knots = 1.61 km/h)

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SC-POH-1-1-17LIST OF ABBREVIATIONS S
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m/s Vertical speed in meters per second
(1 m/s = 196.8 fpm = 1.944 knots = 3.6 km/h)
N Newton - force unit (1 N = 0.225 lbf)
NM Nautical mile (1 NM = 1,852 m)
OFF System is switched off or control element is in off-position
ON System is switched on or control element is in on-position
OAT Outside Air Temperature
POH Pilot’s Operating Handbook
psi Pressure unit - pound per square inch (1 psi = 0.0689bar)
rpm Revolutions per minute
s or sec Second
SM Statute Mile (1 SM = 1,609 m)
TAS True Airspeed
US gal US gallon (1 US gal = 0.83 UK gal = 3.785 L)
V Volt
VFR Visual Flight Rules
VMC Visual Meteorological Conditions
VSI Vertical Speed Indicator
VTU Vertical tail unit
VAManeuveringairspeed
VFE Maximum flap extended speed
VNE Neverexceedspeed
VNO Maximumdesignedcruisingspeed
VSStallspeedwithwingflapsinretractedposition
VS1 Stallspeedwithwingflapsintakeoffposition
VSO Stallspeedwithwingflapsinextendedposition
VXBestangleofclimbspeed
VYBestrateofclimbspeed

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SC-POH-1-1-17ASTM STANDARDS
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ASTM STANDARD
The S Sp po or rt tC Cr ru ui is se er raircraft is designed and built according to following
ASTM LSA standards:
ASTM F 2245 – 09
Standard Specification for Design and performance of a Light Sport Airplane
ASTM F 2279 – 06
Standard Practice for Quality Assurance in Manufacture of Fixed Wing Light Sport
Aircraft
ASTM F 2295 – 06
Standard Practice for Continued Operational Safety Monitoring of a Light Sport
Aircraft
ASTM F 2316 – 08
Standard Specification for Airframe Emergency Parachutes for Light Sport Aircraft

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SC-POH-1-1-17CONTACT INFORMATION S
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CONTACT INFORMATION
Czech Sport Aircraft a.s.
Na Záhonech 1177/212, 686 04 Kunovice
Czech Republic
Website: www.czechsportaircraft.com
E-mail: [email protected]
Phone: [phone] (Sales Dept.)
Fax: [phone]

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TABLE OF CONTENTS S
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TABLE OF CONTENTS
1. General Information
2. Limitations
3. Emergency Procedures
4. Normal Procedures
5. Performance
6. Weight and Balance
7. Description of Airplane and Systems
8. Handling and Servicing
9. Supplements

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SECTION 1
GENERAL INFORMATION
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SECTION 1
TABLE OF CONTENTS
1. GENERAL INFORMATION
1.1 Airplane specification 1-2
1.2 Summary of performances 1-5

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GENERAL INFORMATION
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1. GENERAL INFORMATION
This Pilot’s Operating Handbook (POH) has been prepared to provide pilots
with information for the safe and efficient operation of the S Sp po or rt tC Cr ru ui is se er r aircraft
and contains 9 sections. It also contains supplementary information
considered to be important by the aircraft manufacturer.
Date of issue is written in the yy-mm-dd format.
NOTE
All airspeeds shown in the POH are IAS, except of shown otherwise.
Warnings, Cautions and Notes
The following definitions apply to warnings, cautions and notes in the POH.
WARNING
Means that the non-observation of the corresponding procedure leads to an
immediate or important degradation of the flight safety i.e. to injury or death of
persons.
CAUTION
Means that the non-observation of the corresponding procedure leads to a minor or
possible long term degradation of the flight safety.
NOTE
Draws attention to any special item not directly related to safety but which is
important or unusual.
1.1 Airplane specification
S
Sp po or rt tC Cr ru ui is se er ris the airplane intended especially for recreational and cross-
country flying, and non-aerobatics operation.
S
Sp po or rt tC Cr ru ui is se er ris a single-engine, all metal, low-wing monoplane of semi-
monocoque structure with two side-by-side seats. The airplane is equipped
with a fixed tricycle undercarriage with castering nose wheel.

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GENERAL INFORMATION
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Main airplane dimensions:
Wing span......................................................28.22 ft
Length............................................................21.72 ft
Height ............................................................7.6 ft
Wing area ......................................................132.3 sq ft
Wing loading..................................................10 lb/sq ft
Cockpit width .................................................46 in
Flight control surfaces travel:
Rudder...........................................................30° ±2° to each side
Elevator .........................................................+24° / -24° ±2°
Aileron ...........................................................+15° / -15° ±1°
Flaps..............................................................0° to 30° ±1°
Aileron trim ....................................................+ 20° / -20° ±2°
Elevator trim ..................................................+ 22° / -28° ±2°
Engine:
Manufacturer .................................................BRP-Powertrain GmbH&Co.KG
Model number................................................912 ULS
Maximum power rating ..................................98.6 hp at 5,800 RPM
Cooling ..........................................................liquid and air
Type ...................... 4-stroke, 4 cylinder, horizontally opposed, spark ignition
enginewithonecentralcamshaft-push-rod-OHV
Propeller:
Manufacturer .................................................WOODCOMP s.r.o.
Model number................................................KLASSIC 170/3/R
Number of blades ..........................................3
Diameter ........................................................68 in
Pitch setting ...................................................17.5 ± 0.5°
Type ..............................................................three composite blades,
groundadjustable
2-4
Date of Issue: 12/2007 Revision: 2.0
Airframe
All-metal construction, stressed skin, single curvature metal skins riveted
to stiffeners. Construction is of 6061-T6 aluminum sheet metal riveted to
aluminum angles with Avex rivets. This high strength aluminum alloy
construction provides long life and low maintenance costs thanks to its
durability and corrosion resistance characteristics.
The wing has a high lift airfoil equipped with slotted flaps.
Control system
The plane is equipped with a dual stick control, the adjustable rudder
pedals with pedal hydraulic brakes for easy ground control of the
castering nose wheel.
The elevator and aileron trim are electrically actuated by buttons on the
control stick. Wing flaps are electrically actuated by the rocker switch
located on the middle panel.
Deflections:
Rudder deflections ............................... 30to each side
Elevator deflections..............................+ 28- 25
Aileron deflections................................ + 20- 15
Flap deflections.................................... 0to 30
Aileron trim deflections.........................+ /- 
Elevator trim deflections....................... + 22- 28
Landing gear
Tricycle landing gear with the castering nose wheel. Main landing gear
uses two fiberglass spring elements.