czech sport aircraft SportCruiser User manual

This document contains information necessary for operation and maintenance of the airplane
according to LSA regulation.
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www.czechsportaircraft.com

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MIP
Date of issue: 04/2009 Revision No. 5
0- 1
RECORD OF REVISIONS
Rev.
No. Reason for revision Changed pages Issue date Date and
signature
1 initial all 01/2007
2 Design changes
See list of effective pages
01/2008
3
Ailerons and trims deflections, coolant
operation limits See list of effective pages
04/2008
4 Operating liquids
See list of effective pages 02/2009
5 Reissue All 04/2009

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Date of issue: 04/2009 Revision No. 5
0- 2
LIST OF EFFECTIVE PAGES
Chapter Page Date Chapter Page Date
0 0-1 04/2009 4-6 04/2009
0-2 04/2009 4-7 04/2009
0-3 04/2009 4-8 04/2009
0-4 04/2009
5 5-1 04/2009
5-2 04/2009
1 1-1 04/2009 5-3 04/2009
1-2 04/2009 5-4 04/2009
1-3 04/2009 5-5 04/2009
1-4 04/2009 5-6 04/2009
1-5 04/2009 5-7 04/2009
1-6 04/2009
1-7 04/2009
6 6-1 04/2009
6-2 04/2009
2 2-1 04/2009 6-3 04/2009
2-2 04/2009 6-4 04/2009
2-3 04/2009 6-5 04/2009
2-4 04/2009 6-6 04/2009
2-5 04/2009 6-7 04/2009
2-6 04/2009 6-8 04/2009
2-7 04/2009 6-9 04/2009
2-8 04/2009 6-10 04/2009
2-9 04/2009 6-11 04/2009
2-10 04/2009 6-12 04/2009
2-11 04/2009 6-13 04/2009
6-14 04/2009
6-15 04/2009
3 3-1 04/2009 6-16 04/2009
3-2 04/2009 6-17 04/2009
3-3 04/2009 6-18 04/2009
3-4 04/2009 6-19 04/2009
3-5 04/2009 6-20 04/2009
3-6 04/2009 6-21 04/2009
3-7 04/2009 6-22 04/2009
3-8 04/2009 6-23 04/2009
3-9 04/2009
7 7-1 04/2009
4 4-1 04/2009 7-2 04/2009
4-2 04/2009 7-3 04/2009
4-3 04/2009 7-4 04/2009
4-4 04/2009
4-5 04/2009

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Chapter Page Date Chapter Page Date
8 8-1 04/2009 10-18 04/2009
8-2 04/2009 10-19 04/2009
8-3 04/2009 10-20 04/2009
8-4 04/2009 10-21 04/2009
8-5 04/2009 10-22 04/2009
8-6 04/2009 10-23 04/2009
8-7 04/2009 10-24 04/2009
8-8 04/2009 10-25 04/2009
8-9 04/2009 10-26 04/2009
8-10 04/2009 10-27 04/2009
8-11 04/2009 10-28 04/2009
8-12 04/2009 10-29 04/2009
8-13 04/2009
8-14 04/2009
8-15 04/2009 11 11-1 04/2009
11-2 04/2009
11-3 04/2009
9 9-1 04/2009 11-4 04/2009
9-2 04/2009 11-5 04/2009
9-3 04/2009 11-6 04/2009
9-4 04/2009 11-7 04/2009
9-5 04/2009 11-8 04/2009
9-6 04/2009 11-9 04/2009
9-7 04/2009
9-8 04/2009
9-9 04/2009 12 12-1 04/2009
12-2 04/2009
12-3 04/2009
10 10-1 04/2009 12-4 04/2009
10-2 04/2009 12-5 04/2009
10-3 04/2009 12-6 04/2009
10-4 04/2009 12-7 04/2009
10-5 04/2009
10-6 04/2009
10-7 04/2009 13 13-1 04/2009
10-8 04/2009 13-2 04/2009
10-9 04/2009 13-3 04/2009
10-10 04/2009 13-4 04/2009
10-11 04/2009
10-12 04/2009
10-13 04/2009 14 14-1 04/2009
10-14 04/2009 14-2 04/2009
10-15 04/2009 14-3 04/2009
10-16 04/2009
10-17 04/2009

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Date of issue: 04/2009 Revision No. 5
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Chapter Page Date Chapter Page Date
15 15-1 04/2009
15-2 04/2009
15-3 04/2009
15-4 04/2009
15-5 04/2009
15-6 04/2009
15-7 04/2009
15-8 04/2009
15-9 04/2009
15-10 04/2009
15-11 04/2009
15-12 04/2009
15-13 04/2009
15-14 04/2009
15-15 04/2009
15-16 04/2009
15-17 04/2009
15-18 04/2009
15-19 04/2009
15-20 04/2009
15-21 04/2009
15-22 04/2009
16 16-1 04/2009
16-2 04/2009
16-3 04/2009
16-4 04/2009
16-5 04/2009
16-6 04/2009
16-7 04/2009
16-8 04/2009
16-9 04/2009
17 17-1 04/2009
17-2 04/2009
17-3 04/2009
17-4 04/2009
17-5 04/2009

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Date of issue: 01/2007 Revision No. 1
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TABLE OF CONTENTS
Chapter 1 - General .....................................................................................1-1
Chapter 2 - Limitations/Maintenance checks ............................................2-1
Chapter 3 - Fuselage...................................................................................3-1
Chapter 4 - Wing..........................................................................................4-1
Chapter 5 - Tail unit.....................................................................................5-1
Chapter 6 - Controls....................................................................................6-1
Chapter 7 - Equipment ................................................................................7-1
Chapter 8 - Landing gear ............................................................................8-1
Chapter 9 - Fuel system..............................................................................9-1
Chapter 10 - Power unit ..............................................................................10-1
Chapter 11 - Electrical system....................................................................11-1
Chapter 12 - Pitot-static system/Instruments............................................12-1
Chapter 13 - Venting/Heating......................................................................13-1
Chapter 14 - Airplane handling...................................................................14-1
Chapter 15 - Airplane repairs......................................................................15-1
Chapter 16 - Wiring diagrams.....................................................................16-1
Chapter 17 - Appendices.............................................................................17-1

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GENERAL
Date of issue: 04/2009 Revision No. 5
1 - 1
CHAPTER 1 - GENERAL
1.1 Introduction............................................................................................................ 1-2
1.2 Airplane classification ............................................................................................ 1-2
1.2.1 Power unit................................................................................................. 1-2
1.2.2 Main technical data................................................................................... 1-3
1.3 Airplane manufacturer and type certificate holder................................................. 1-5
1.4 Chapter order......................................................................................................... 1-5
1.4.1 Page numbering ....................................................................................... 1-5
1.5 Warnings, cautions and notes ............................................................................... 1-5
1.6 Definitions and abbreviations................................................................................. 1-6

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GENERAL
Date of issue: 04/2009 Revision No. 5
1 - 2
Introduction
Czech Sport Aircraft a.s. as manufacturer of SPORTCRUISER airplane provides in
accordance with requirements of the ASTM LSA regulations information on maintaining
airworthiness of the SPORTCRUISER airplane. Information is also contained in the following
manuals issued by airplane manufacturer or by manufacturers of equipment used on the
airplane:
•Sportcruiser Pilot Operating Handbook
•Sportcruiser Maintenance and Inspection Procedures
•Sportcruiser Illustrated Parts Catalog
•Operator's Manual for ROTAX 912 ULS engine
•Maintenance Manual for ROTAX 912 ULS engine
•Technical description and operation instructions for the propeller
This document (Maintenance and Inspection Procedures) contains information on airplane
maintenance including description of airplane structure and function.
Airplane classification
SPORTCRUISER airplane is two-seat, single engine, low-wing, all-metal airplane with fixed
three-wheel landing gear.
The airplane is designed for basic and advanced training and for leisure time flying.
Power unit
Power unit consists of:
•four-stroke, four-cylinder engine with opposite pistons Rotax 912 ULS with max.
continuous power of 69 kW (92.5 hp) at 5500 RPM
•Three-blade, ground adjustable propeller.

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GENERAL
Date of issue: 04/2009 Revision No. 5
1 - 3
Main technical data
Wing
•span ..........................................................................8.81m (28.90 ft)
•area...........................................................................12.3m
2
(132.3 sqft)
•MAC ..........................................................................1500mm (59.1 in)
•wing loading..............................................................49kg/m
2
(10.0 lb/sqft)
•aileron area..............................................................0.46m
2
(4.98 sqft)
•flap area...................................................................0.65m
2
(7.0 sqft)
Fuselage
•length ........................................................................6.5m (21.33 ft)
•width..........................................................................1.28m (50.4 in)
•height ........................................................................2.37m (7.78 ft)
•cockpit width..............................................................1.17m (46 in)
Horizontal tail unit
•span ..........................................................................2.93m (9.61 ft)
•HTU area...................................................................2.2m
2
(23.7 sqft)
•elevator area.............................................................0.8m
2
(8.6 sqft)
Vertical tail unit
•height ........................................................................1.07m (3.51 ft)
•VTU area...................................................................1m
2
(10.7 sqft)
•rudder area................................................................0.4m
2
(4.3 sqft)
Landing gear
•wheel track................................................................1.52m (4.98 ft)
•wheel base................................................................2.07m (6.79 ft)
•nose landing gear wheel diameter............................343mm (13.5 in)
•main landing gear wheel diameter............................343mm (13.5 in)

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GENERAL
Date of issue: 04/2009 Revision No. 5
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Fig. 1-1: Three-view drawing

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GENERAL
Date of issue: 04/2009 Revision No. 5
1 - 5
Airplane manufacturer and type certificate holder
Office:
Czech Sport Aircraft a.s.
Roháčova 188/37
13000 Praha 3
Czech Republic
Web page: www.czechsportaircraft.com
E-mail: [e-mail]
Production facility:
Czech Sport Aircraft a.s.
Na Záhonech č.e. 212
686 04 Kunovice
Czech Republic
Phone: [phone]
Fax: [phone]
Chapter Order
Chapters in this manual are ordered in ascending sequence from No. 1. Every chapter
describes one system or assembly.
Page numbering
Example:
12 – POWERPLANT
Page: 12 – 10 Chapter number and title
Chapter No. Page No.
Warnings, cautions and notes
Warning: Means that non-observation of the corresponding operating instruction,
inspection or maintenance procedure can lead to injury or death of persons.
Caution: Means that non-observation of the corresponding operating instruction,
inspection or maintenance procedure can lead to damage or destruction of
device.
Note: Means that the corresponding operating instruction, inspection or
maintenance procedure is considered to be important.

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GENERAL
Date of issue: 04/2009 Revision No. 5
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Definitions and abbreviations
ACCU Accumulator
ALT Altimeter
ATC Air Traffic Control
bar pressure unit (1 bar = 14,5037 psi)
BEACON anti-collision beacon
°C temperature in degree of Celsius (1°C = (°F - 32 ) / 1,8)
CAS Calibrated Airspeed
COMM Communication transmitter
EFIS Electronic Flight Instrument System
ELT Emergency Locator Transmitter
EMS Engine Monitoring System
°F temperature in degree of Fahrenheit (1°F = (°C x 1,8) + 32)
ft foot / feet (1 ft = 12 in = 0,3048 m = 304,8 mm)
ft/min vertical speed in feet per minute
GPS Global Positioning System
hp power unit (1 hp = 0,7457 kW)
HTU Horizontal Tail Unit
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 = 2,2046 lb)
knot speed in NM per hour
KIAS Indicated Airspeed in Knots
km/h speed in kilometer per hour
knot speed in NM per hour
kW power unit (1 kW = 1,341 hp)
I liter (1 l = 0,22 UK gal = 0,264 US gal)
lb pounds (1 lb = 0,4536 kg)
lbf force unit (1 lbf = 4.45 N)
m meter (1 m = 1000 mm = 3,28 ft = 39,37 in)
mm milimetre (1 mm = 0,03937 in)
MAC Mean Aerodynamic Chord
max. maximum
min. minimum or minute

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GENERAL
Date of issue: 04/2009 Revision No. 5
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mph speed in statute miles per hour
N Newton - force unit (1 N = 0.225 lbf)
NM Nautical Mile (1 NM = 1852 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
OFF system is switched off or control element is in off-position
ON system is switched on or control element is in on- position
POH Pilot Operating Handbook
psi pressure unit - pounds per square inch (1psi = 0.0689bar)
rpm revolutions per minute
sec. second
SM Statute Mile (1SM = 1,609 m)
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
V
A
maneuvering airspeed
V
FE
maximum flap extended speed
V
NE
never exceed speed
V
NO
maximum structural cruising speed
V
SO
stall speed with wing flaps in extended position
V
S1
stall speed with wing flaps in retracted position
V
X
best angle of climb speed
V
Y
best rate of climb speed
XPDR secondary radar transponder

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CHAPTER 2 – TIME LIMITS/MAINTENANCE CHECKS
2.1 General.................................................................................................................. 2-2
2.2 Airframe life limitation ............................................................................................ 2-2
2.3 Engine life limitation............................................................................................... 2-2
2.3.1 Engine parts with limited life..................................................................... 2-2
2.4 Ordering spare parts.............................................................................................. 2-2
2.5 Terms and list of aircraft regular maintenance works............................................ 2-2
2.5.1 General..................................................................................................... 2-2
2.5.2 Tables of inspection tasks ........................................................................ 2-3
2.6 Lubrication plan.................................................................................................... 2-11

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2 - TIME LIMITS/MAINTENANCE CHECKS
Date of issue: 04/2009 Revision No. 5
2 - 1
General
This chapter contains information about:
•airframe life limitations
•engine life limitations
•terms and list of aircraft regular maintenance works
•lubrication plan
Airframe life limitation
Initial airframe life is 5000 flight hours.
Engine life limitation
Time to overhaul of ROTAX 912 ULS engine is 1500 flight hours or 10 years whichever is the
sooner.
Engine parts with limited life
The following parts must be exchanged every 5 years:
•air-bleeding hoses of carburetors
•all rubber hoses of engine cooling system
•all rubber hoses of engine oil system
•carburetor flanges
•carburetor diaphragms
•rubber hoses of the compensation tube connecting carburetors
•fuel pump including fuel hoses
•Cooling liquid must be exchanged every two years
Ordering spare parts
Order spare parts through the Airplane failures card, see section 17.4.
Terms and list of aircraft regular maintenance works
General
Maintenance system serves to maintain flight airworthiness of SPORTCRUISER airplane.
Maintenance system is composed of periodic inspections, which must be performed at least in
the following intervals:
Caution: The intervals of engine inspections and the list of works are shown in
Maintenance Manual (Line Maintenance) for installed engine. The intervals of
propeller inspections and the list of works are shown in Technical description and
operation instructions for the installed propeller. If the periodical inspection is
performed before reaching the specified time interval, then the following
inspection must be performed at the latest within the specified time interval from
this inspection (e.g. if the first 100-hour inspection is performed after 87 flight
hours then the following 100-hour inspection must be performed at the latest after
187 flight hours).

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2 - TIME LIMITS/MAINTENANCE CHECKS
Date of issue: 04/2009 Revision No. 5
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(a) preflight inspection is performed within the scope given in Flight Manual, section 4
(b) propeller inspection after first 5, 20 and 50 flight hours (see Technical description of the
propeller)
Note: To be performed with a newly installed propeller or with the propeller that was
dismantled and reinstalled on the airplane.
(c) Inspection after the first 25 flight hours - engine inspection.
Caution: Inspection after the first 25 flight hours to be performed with the new engine or
with the engine after overhaul.
(d) Periodical inspection after 50 flight hours - inspection of engine and propeller
(e) Periodical inspection after 100+5 flight hours - airframe and propeller inspections, engine
inspection according to maintenance system, which is described in Maintenance Manual (Line
Maintenance) for installed engine.
Caution: 100-hour term can be exceeded max. by 5 hours providing that this exceeding will
be just to finish flight which started before reacting 100-hour term or for flight with
the purpose to reach a place where the inspection will be carried out. Operation
time, which exceeded 100-hour interval, must be included as a time flown for
determination of the next 100-hour inspection.
(f) Annual inspection contains works of 100-hour inspection and other specified works
(inspections of airframe, engine and propeller).
Tables of inspection tasks
Tables of inspection tasks include the list of all works, which are performed during inspection.
Number of chapter is indicated in the first column of this Maintenance Manual where you can
also find more detailed information for performing individual works.
The description of works, which are performed during inspection, is indicated in the second
column.
Caution: All defects found out during aircraft inspections must be eliminated!

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2 - TIME LIMITS/MAINTENANCE CHECKS
Date of issue: 04/2009 Revision No. 5
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PERIODICAL INSPECTION AFTER
FIRST 25 FLIGHT HOURS
Aircraft S/N: ………………… Total flight hours: …………
Registration mark: ………………… No. of takeoffs: …………
Page: 1 of 1
Chpt.
Prescribed works Made by Checked by
Engine and propeller
List of performed operations for engine is shown in
Maintenance Manual (Line Maintenance) for installed
engine
List of performed operations for propeller is shown in
Technical description and operation instructions for
installed propeller
Remove and check engine cowlings for evident signs of
heat damage or cracks.
Inspect and check tightening and securing bolts on the
engine brackets and the engine mount.
Check the engine mount for occurrence of cracks.
Check the exhaust system (and its attachment) for
occurrence of cracks on the exhaust system and welds
(see 10.4.5).
10
Inspect and clean the fuel filter insert.
Notes:
Date: ………………… Signature: …………………