Orlican M-8 EAGLE 2022 User manual

ORLIČAN M-8 EAGLE
PILOT'S OPERATING
REVISION NO. 05
DATE OF ISSUE: MAY 02,
ORLIČAN S.R.O.
PAGE OF1 2
Airplane Registration Airplane
Serial Number Number
N602TG 2022001
THIS MANUAL MUST BE ON THE AIRPLANE BOARD DURING OPERATION.
THIS AIRPLANE MUST BE OPERATED IN COMPLIANCE WITH THE INFORMATION
AND LIMITATIONS STATED IN THIS MANUAL.
an

ORLIČAN M-8 EAGLE
PILOT'S OPERATING
REVISION NO. 05
DATE OF ISSUE: MAY 02,
ORLIČAN S.R.O.
PAGE OF2 2
Production
T
E
[email protected]
W
www.orlican.or
YOUR AIRPLANE SUPPLIER
ORLIČAN
Londýnská
120 00 Praha 2 –
Czech

ORLIČAN M-8 EAGLE
PILOT'S OPERATING
REVISION NO. 05
DATE OF ISSUE: MAY 02,
TABLE OF CONTENTS
PAGE OF3 10
1 TABLE OF CONTENTS

ORLIČAN M-8 EAGLE
PILOT'S OPERATING
REVISION NO. 05
DATE OF ISSUE: MAY 02,
TABLE OF CONTENTS
PAGE OF4 10
1. TABLE OF CONTENTS 3
2. LIST OF REVISIONS 9
3. TERMINOLOGY 10
3.1. GENERAL AIRSPEED TERMINOLOGY AND SYMBOLS 10
3.2. METEOROLOGICAL TERMINOLOGY 10
3.3. ENGINE POWER TERMINOLOGY 11
3.4. AIRPLANE PERFORMANCE AND FLIGHT PLANNING TERMINOLOGY 11
3.5. WEIGHT AND BALANCE TERMINOLOGY 11
3.6. ELECTRICAL AND AVIONICS TERMINOLOGY 12
4. REFERENCED DOCUMENTS 13
4.1. ASTM STANDARDS: 13
4.2. ROTAX ENGINE DOCUMENTATION 13
4.3. WOODCOMP PROPELLER DOCUMENTATION 13
4.4. DYNON AVIONICS DOCUMENTATION 13
4.5. ACK TECHNOLOGIES DOCUMENTATION 13
5. GENERAL INFORMATION 14
5.1. INTRODUCTION 14
5.2. IMPORTANT INFORMATION 14
5.3. ATTENTIONS, CAUTIONS, WARNINGS 15
5.4. AIRCRAFT DESCRIPTION 16
5.4.1. CHARACTERISTICS 16
5.4.2. AIRFRAME 16
5.4.3. CONTROLS 16
5.4.4. AIRCRAFT DIMENSIONS 17
5.4.5. AIRCRAFT WEIGHTS 17
5.4.6. THREE-VIEW DRAWING 18
5.5. AIRCRAFT CONFIGURATION 19
5.5.1. POWERPLANT 20
5.5.2. PROPELLER 21
5.6. AIRCRAFT EQUIPMENT 22
5.6.1. INSTRUMENTS 22
5.6.2. EQUIPMENT LAYOUT 24
6. LIMITATIONS 25
6.1. INTRODUCTION 25
6.2. AIRSPEED LIMITATIONS 25
6.3. AIRSPEED INDICATOR MARKINGS 26
6.3.1. ANALOG AIRSPEED INDICATOR MARKINGS 27
6.4. POWERPLANT LIMITATIONS 28
6.5. POWERPLANT INSTRUMENT MARKINGS 29
6.6. MISCELLANEOUS INSTRUMENT MARKINGS 29
6.6.1. FUEL QUANTITY INDICATOR DIGITAL AND ANALOG 29
6.7. WEIGHT LIMITS 30
6.8. CENTRE OF GRAVITY 31
6.9. OPERATING CEILING 31
6.10. WIND SPEED LIMITS 31

ORLIČAN M-8 EAGLE
PILOT'S OPERATING
REVISION NO. 05
DATE OF ISSUE: MAY 02,
TABLE OF CONTENTS
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6.11. APPROVED MANEUVERS 32
6.12. MANEUVERING LOAD FACTORS 32
6.13. FLIGHT ENVELOPE 33
6.14. FLIGHT CREW 33
6.15. FUEL 34
6.16. OIL SPECIFICATION 35
6.17. COOLANT SPECIFICATION 35
6.18. KINDS OF OPERATION 36
6.19. FLIGHT SAFETY RESTRICTIONS 36
6.20. PLACARDS 37
6.20.1. PLACARD LIGHT SPORT AIRCRAFT 38
6.20.2. PLACARD OPERATING DATA AND LIMITS 38
6.20.3. REGISTRATION PLACARD 39
6.20.4. AIRCRAFT IDENTIFICATION PLATE 39
6.20.5. FUEL PLACARD 39
7. EMERGENCY PROCEDURES 40
7.1. INTRODUCTION 40
7.1.1. MAINTAIN AIRCRAFT CONTROL 40
7.1.2. ANALYZE THE SITUATION 40
7.1.3. TAKE APPROPRIATE ACTION 40
7.1.4. LAND AS SOON AS POSSIBLE 40
7.2. ENGINE FAILURE 41
7.2.1. INTRODUCTION 41
7.2.2. DURING TAKE-OFF RUN 42
7.2.3. DURING TAKE-OFF (IN AIR) 42
7.3. EMERGENCY LANDING 42
7.4. RESTARTING ENGINE IN FLIGHT 42
7.4.1. FLYING WITHOUT ENGINE POWER (GLIDING FLIGHT) 43
7.5. PRECAUTIONARY LANDING 43
7.6. IN CASE OF FIRE 43
7.6.1. FIRE ON GROUND, DURING ENGINE STARTING 43
7.6.2. FIRE ON GROUND, ENGINE RUNNING 43
7.6.3. FIRE ON GROUND, DURING TAKE-OFF 44
7.6.4. FIRE IN FLIGHT 44
7.6.5. ELECTRICAL FIRE 44
7.7. LANDING WITH A DAMAGED LANDING GEAR 44
7.8. LOW OIL PRESSURE 44
7.9. HIGH OIL PRESSURE 45
7.10. RECOVERY FROM UNINTENTIONAL SPIN 45
7.11. STALL RECOVERY 46
7.12. LOSS OF PRIMARY INSTRUMENTS 46
7.13. LOSS OF FLIGHT CONTROLS 46
7.13.1. AILERON OR RUDDER FAILURE 47
7.13.2. ELEVATOR FAILURE 47
7.13.3. WING FLAP FAILURE 47

ORLIČAN M-8 EAGLE
PILOT'S OPERATING
REVISION NO. 05
DATE OF ISSUE: MAY 02,
TABLE OF CONTENTS
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7.14. OTHER EMERGENCY PROCEDURES 47
7.14.1. EXCEEDING MAXIMUM AIRSPEED 47
7.14.2. VIBRATIONS 47
7.14.3. CARBURETOR ICING 47
8. NORMAL PROCEDURES 48
8.1. INTRODUCTION 48
8.2. PRE-FLIGHT INSPECTION 48
8.2.1. CABIN 49
8.2.2. FUSELAGE, WINGS AND TAIL SURFACES 49
8.2.3. CONTROL SURFACES, WING FLAPS 49
8.2.4. LANDING GEAR 49
8.2.5. ENGINE, PROPELLER, FUEL SYSTEM 49
8.3. ENGINE STARTING 49
8.3.1. AFTER ENTERING COCKPIT 49
8.3.2. ENGINE STARTING 50
8.4. ENGINE TEST 50
8.5. TAXIING 51
8.6. BEFORE TAKE-OFF 51
8.7. TAKE-OFF 51
8.8. CLIMBING 52
8.9. CRUISE 52
8.10. DESCENT 53
8.11. FINAL APPROACH 53
8.11.1. APPROACH UNDER TAILWIND CONDITIONS 53
8.11.2. APPROACH IN THE SLIP CONFIGURATION 53
8.11.3. APPROACH IN CROSSWIND CONDITIONS 53
8.12. LANDING 54
8.13. BALKED LANDING (GO-AROUND) 54
8.14. SHORT FIELD TAKEOFF 55
8.15. SHORT FIELD LANDING 55
8.16. SOFT FIELD TAKEOFF 55
8.17. SOFT FIELD LANDING 56
8.18. ACTIONS AFTER LANDING 56
8.19. ENGINE SHUT-OFF 56
8.20. STOPPING THE AIRCRAFT, PARKING 56
8.21. FLYING IN RAIN, SNOW 56
9. PERFORMANCE 57
9.1. INTRODUCTION 57
9.2. AIRSPEED INDICATOR SYSTEM CALIBRATION 57
9.3. STALL SPEEDS 58
9.4. TAKE-OFF PERFORMANCE 58
9.5. LANDING PERFORMANCE 58
9.6. CLIMBING PERFORMANCE 59
9.7. CRUISE PERFORMANCE 59

ORLIČAN M-8 EAGLE
PILOT'S OPERATING
REVISION NO. 05
DATE OF ISSUE: MAY 02,
TABLE OF CONTENTS
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9.8. ENDURANCE AND RANGE 60
9.9. DEMONSTRATED CROSSWIND PERFORMANCE 60
9.10. OPTIMUM GLIDING SPEED 61
9.11. CEILING 61
10. WEIGHT AND BALANCE 62
10.1. INTRODUCTION 62
10.2. AIRPLANE WEIGHING PROCEDURE AND DETERMINING THE LOCATION OF CG 62
10.2.1. WEIGHING FOR AFT CENTER OF GRAVITY 62
10.2.2. WEIGHING FOR FORWARD CENTER OF GRAVITY 62
10.2.3. WEIGHT AND BALANCE RECORD OF THE AIRCRAFT 63
10.2.4. DETERMINATION OF PRE-FLIGHT CG 64
10.3. PERMITTED PAYLOAD RANGE 65
11. DESCRIPTION OF AIRPLANE AND SYSTEMS 66
11.1. INTRODUCTION 66
11.2. AIRFRAME 66
11.2.1. FUSELAGE 66
11.2.2. WING 66
11.2.3. HORIZONTAL TAIL UNIT 66
11.2.4. VERTICAL TAIL UNIT 66
11.3. CONTROL 66
11.4. CONTROLS IN COCKPIT 67
11.5. INSTRUMENT PANEL 67
11.6. SEATS AND SAFETY HARNESSES 68
11.7. CABIN DOORS 69
11.8. BAGGAGE COMPARTMENT 69
11.9. LANDING GEAR AND BRAKE SYSTEM 70
11.10. POWER UNIT 71
11.11. PROPELLER 72
11.12. FUEL SYSTEM 73
11.13. ELECTRICAL SYSTEM 74
11.14. PITOT-STATIC SYSTEM 75
11.15. LIGHTS 76
11.16. AVIONICS 76
12. HANDLING AND SERVICING 77
12.1. INTRODUCTION 77
12.2. AIRPLANE INSPECTION PERIODS 77
12.2.1. WARRANTY INSPECTION (FIRST 25 HOURS) 77
12.2.2. 100-HOUR (50-HOUR) / ANNUAL INSPECTION 77
12.2.3. 500-HOUR INSPECTION 77
12.3. AIRPLANE MODIFICATIONS OR REPAIRS 78
12.4. GROUND HANDLING 78
12.4.1. PARKING 78
12.4.2. ANCHORING 79
12.4.3. TOWING INSTRUCTIONS 79

ORLIČAN M-8 EAGLE
PILOT'S OPERATING
REVISION NO. 05
DATE OF ISSUE: MAY 02,
TABLE OF CONTENTS
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12.5. ASSEMBLY AND DISASSEMBLY OF THE AIRCRAFT 80
12.5.1. WING ASSEMBLY 80
12.5.2. HORIZONTAL STABILIZER (ELEVATOR) ASSEMBLY 81
12.5.3. WING DISASSEMBLY 82
12.5.4. HORIZONTAL STABILIZER (ELEVATOR) DISASSEMBLY 83
12.6. ROAD TRANSPORT 83
12.7. ENGINE COWLINGS 84
12.7.1. ENGINE COWLINGS REMOVAL AND INSTALLATION 86
12.8. DRAINING OF FUEL TANKS AND REFUELING 87
12.8.1. DRAINING OF FUEL TANKS 87
12.8.2. REFUELING 88
12.9. LONG-TERM STORAGE 89
12.9.1. BEFORE LONG-TERM STORAGE 89
12.10. CLEANING AND CARE 89
13. CONTINUED OPERATIONAL SAFETY 90

ORLIČAN M-8 EAGLE
PILOT'S OPERATING
REVISION NO. 05
DATE OF ISSUE: MAY 02,
TABLE OF CONTENTS
PAGE OF9 10
13.1. INSTRUCTIONS: 90
13.2. CONTINUED OPERATIONAL SAFETY FEEDBACK FORM 91
14. FLIGHT TRAINING SUPPLEMENT 92
14.1. INTRODUCTION 92
14.2. PILOT TRAINING 92
14.3. TRAINING SCHEDULE 92
14.4. PRACTICAL TRAINING FOR PILOT QUALIFICATION 93
14.4.1. LESSON 1: INTRODUCTORY FLIGHT 93
14.4.2. LESSON 2: STRAIGHT FLIGHT, EFFECTS OF CONTROLS 93
14.4.3. LESSON 3: TURNS WITH BANK ANGLE UP TO 15° 93
14.4.4. LESSON 4: TURNS WITH BANK ANGLE UP TO 45° 93
14.4.5. LESSON 5: SIDE SLIPS, SLOW FLIGHT, FLIGHT AT MAX CRUISE SPEED AND APPROACH TO A
STALL 94
14.4.6. LESSON 6: TAKE-OFF, TRAFFIC PATTERN, LANDING, AND BALKED LANDING 94
14.4.7. LESSON 7: CORRECTIONS OF IMPROPER APPROACH PLANNING, AND LANDING
CORRECTIONS 94
14.4.8. LESSON 8: PRECAUTIONARY LANDING 95
14.4.9. LESSON 9: EMERGENCY LANDING PRACTICE 95
14.4.10. LESSON 10: CROSSWIND TAKE-OFF AND LANDING 95
14.4.11. BLOCKED FLIGHT INSTRUMENTS / INSTRUMENT FAILURE 96
14.4.12. LESSON 11: CHECK BEFORE FIRST SOLO FLIGHT 96
14.4.13. LESSON 12: SOLO TRAFFIC PATTERN FLIGHT 96
14.4.14. LESSON 13: CHECK TRAFFIC PATTERN FLIGHT 96
14.4.15. LESSON 14: SOLO TRAFFIC PATTERN FLIGHT 96
14.4.16. LESSON 15: TURNS WITH BANK ANGLE 15 TO 45° 96
14.4.17. LESSON 16: SIDE SLIPS AND APPROACH TO A STALL 97
14.4.18. LESSON 17: TAKE-OFF, TRAFFIC PATTERN, APPROACH AND LANDING PRACTICE 97
14.4.19. LESSON 18: NAVIGATION FLIGHT 97
14.4.20. LESSON 19: 75 NM NAVIGATION FLIGHT 97
14.4.21. LESSON 20: 100KM NAVIGATION FLIGHT 97
15. SUPPLEMENTS 99
15.1. INTRODUCTION 99
15.2. LIST OF INSERTED SUPPLEMENTS 99

ORLIČAN M-8 EAGLE
PILOT'S OPERATING
REVISION NO. 05
DATE OF ISSUE: MAY 02,
2. LIST OF REVISIONS
•No part of this manual may be reproduced or changed in any manner without a written consent
of the Manufacturer.
• Any changes to applicable regulations or to this aircraft's construction will be published in the form of
a bulletin on http://orlican.com/bulletin/. It is the responsibility of each aircraft operator to keep all pages
of this manual to the latest revision status, by exchanging the relevant pages when a new revision has
been published.
• Any revision to the handbook, except actual weighing data, must be recorded in the following table
and in case of approved sections endorsed by the responsible airworthiness authority.
• The new or amended text in the revised pages will be marked by means of black vertical line on the
left margin of page and the revision number and date will be shown on the bottom margin of page.
• Revisions and Service Bulletins for the ROTAX engine are available on www.rotax-aircraft-engines.com.
NO.
DATE
REVISED
PAGES
TYPE OF REVISION
POSTED BY
00
Apr. 15th 2021
None
Original Issue
Bc. Jan Bartoš
01
Feb. 25th 2022
All
Overall revision
TomášStarý
02
Mar. 7th 2022
25, 26, 56
values correction
TomášStarý
03
Apr. 12th 2022
All
Overall revision
Michal Holý
04
Apr. 26th 2022
36, 76
Night VFR - specification
TomášStarý
05
May 2nd 2022
17, 30
MTOW value
TomášStarý
LIST OF REVISIONS
PAGE 9 OF 99

ORLIČAN M-8 EAGLE
PILOT'S OPERATING
REVISION NO. 05
DATE OF ISSUE: MAY 02,
TERMINOLOGY
PAGE OF10 14
3. TERMINOLOGY
3.1. GENERAL AIRSPEED TERMINOLOGY AND SYMBOLS
CAS Calibrated Airspeed is indicated airspeed corrected for position and instrument error.
Calibrated airspeed is equal to true airspeed (TAS) in standard atmosphere at sea level.
KCAS Calibrated Airspeed expressed in “knots”.
IAS IndicatedAirspeedisthespeedshownontheairspeed indicator
KIAS Indicated Airspeed expressed in “knots”.
TAS TrueAirspeed is the airspeed relative of an airplane to undisturbed air which is the CAS
corrected for altitude, temperature and compressibility.
GS Ground Speed is the speed of an airplane relative to the ground.
VA Design Maneuvering Speed is the maximum speed at which application of full available
aerodynamic control will not overstress the airplane.
V0 Maximum Operating Maneuvering Speed is the maximum speed the airplane maybe stalled
without exceeding structural limitations.
VFE Maximum Flap Extended Speed is the highest speed permissible with wing flaps in a
prescribed extended position.
VN0 Maximum Structural Cruising Speed is the speed that should not be exceeded except in
smooth air and then only with caution.
VNE Never Exceed Speed is the speed limit that may not be exceeded at any time.
VS Stalling Speed or the minimum steady flight speed is the minimum speed at which the
airplane is controllable.
VS0 Stalling Speed or the minimum steady flight speed at which the airplane is controllable in the
landing configuration at the most forward center of gravity.
VX Best Angle of Climb Speed is the airspeed which delivers the greatest gain of altitude in the
shortest possible horizontal distance.
VY Best Rate of Climb Speed is the airspeed which delivers the greatest gain in altitude in the
shortest possible time.
3.2. METEOROLOGICAL TERMINOLOGY
OAT Outside Air Temperature is the free air static temperature obtained from inflight temperature
indications or from ground meteorological sources. It may be expressed in either degrees
Celsius or degreesFahrenheit.
ST Standard Temperature is 15°C at sea level pressure altitude and decreases by 2°C for each
1000 feet of altitude.
PA Pressure Altitude is the altitude read from an altimeter when the altimeter's barometric scale
has been setto 29.92 inches of mercury (1013 mb).
IMC Instrument Meteorological Conditions are meteorological conditions expressed in terms of
visibility, distance from cloud, and ceiling less than the minima for visual flight defined in FAR
91.155.
VMC Visual Meteorological Conditions
ISA International Standard Atmosphere (standard day) is an atmosphere in which
(1)The air is a dry perfect gas,
(2)The temperature at sea level is 15° C (59 °F),
(3)The pressure at sea level is 29.92 InHg (1013.2 mb),
(4)The temperature gradient from sea level to the altitude at which the temperature is -56.5° C (-69,7
°F) is - 0.00198° C (- 0.003564 °F) per foot and zero above that altitude.

ORLIČAN M-8 EAGLE
PILOT'S OPERATING
REVISION NO. 05
DATE OF ISSUE: MAY 02,
TERMINOLOGY
PAGE OF11 14
3.3. ENGINE POWER TERMINOLOGY
MCP Maximum Continuous Power is the maximum power for abnormal or emergency operations.
BHP Brake Horsepower is the power developed by the engine.
RPM Revolutions Per Minute is engine speed.
Static RPM Static RPM is engine speed attained during a full throttle engine run up when the
airplane is on the ground and stationary.
3.4. AIRPLANE PERFORMANCE AND FLIGHT PLANNING TERMINOLOGY
DCV Demonstrated Crosswind Velocity is the velocity of the crosswind component for which
adequate control of the airplane during takeoff and landing was actually demonstrated
during certification tests. The value shown is not considered to be limiting.
Service Ceiling is the maximum altitude at which the aircraft at maximum weight has the capability of
climbing at a 100 ft/min.
GPH Gallons Per Hour is the amount of fuel consumed per hour.
FPM Feet Per Minute is the distance, in feet, travelled over the duration of one minute.
g One “g” is a quantity of acceleration equal to that of earth’s gravity.
T/O Take off
3.5. WEIGHT AND BALANCE TERMINOLOGY
Reference Datum Reference Datum is an imaginary vertical plane from which all horizontal distances
are measured for balance purposes.
C.G. Center of Gravity is the point at which an airplane would balance if suspended. Its
distance from the reference datum is found by dividing the total moment by the total
weight of the airplane.
Arm Arm is the horizontal distance from the reference datum to the center of gravity (C.G.)
of an item. The airplane’s arm is obtained by adding the airplane’s individual moments
and dividing the sum by the total weight.
Moment Moment is the product of the weight of an item multiplied by its arm.
C.G. Arm Center of Gravity Arm is the arm obtained by adding the airplane's individual moments
and dividing the sum by the total weight.
C.G. Limits Center of Gravity Limits are the extreme center of gravity locations within which the
airplane must be operated at a given weight.
MAC Mean Aerodynamic Chord is a chord of an imaginary rectangular airfoil having the
same pitching moments throughout the flight range as that of the actual wing.
Standard
Empty
Weight
Standard Empty Weight is the weight of a standard airplane, including unusable
fuel, full
operating fluids and full engine oil.
Basic Empty
Weight
Basic Empty Weight is the standard empty weight plus the weight of optional
equipment.
Payload
Payload is weight of occupants, cargo and baggage.
Maximum
Takeoff
Weight
Maximum Takeoff Weight is the maximum weight approved for the start of the
takeoff roll.
Maximum
Landing
Weight
Maximum Landing Weight is the maximum weight approved for the landing
touchdown.
Useful Load
Useful Load is the difference between basic empty weight and maximum takeoff
weight.

ORLIČAN M-8 EAGLE
PILOT'S OPERATING
REVISION NO. 05
DATE OF ISSUE: MAY 02,
3.6. ELECTRICAL AND AVIONICS TERMINOLOGY
AVN Avionics
AUX Auxiliary
ALT Alternator
BATT Battery
COM Communication
CAS Crew Alerting System
ELT Emergency Locator Transmitter
EMS Engine monitoring system
EFIS Electronic Flight Information System
GPS Global Positioning System
HSI Horizontal Situation Indicator
MFD Multi-Functional Display
NAV Navigation
LDG Landing
PFD Primary Flight Display
PTT Push-To-Talk
VHF Very High Frequency
XPDR Transponder
TERMINOLOGY
PAGE 12 OF 99

ORLIČAN M-8 EAGLE
PILOT'S OPERATING
REVISION NO. 05
DATE OF ISSUE: MAY 02,
4. REFERENCED DOCUMENTS
The following documents are regarded as supporting documents to this Pilot Operating Handbook:
4.1. ASTM STANDARDS:
• F 2245 - Specification for Design and Performance of a Light Sport Airplane
• F 2295 - Practice for Continued Operational Safety Monitoring of a Light Sport Airplane
• F 2746 - Standard Specification for Pilot’s Operating Handbook (POH) for Light Sport Airplane
• F 2972 - Standard Specification for Light Sport Aircraft Manufacturer’s Quality Assurance System
4.2. ROTAX ENGINE DOCUMENTATION
Please obtain, read, and follow all instructions given in the latest version of a manual specific for the
engine installed in your aircraft.
Operators Manual for ROTAX - https://www.flyrotax.com/services/technical-documentation.html
4.3. WOODCOMP PROPELLER DOCUMENTATION
Please obtain, read, and follow all instructions given in the latest version of a manual specific for the
propeller installed in your aircraft.
Propeller manual - http://www.woodcomp.cz/downloads/
4.4. DYNON AVIONICS DOCUMENTATION
Please obtain, read, and follow all instructions given in the latest version of a manual specific for the
system installed in your aircraft.
Dynon Avionics manual - https://www.dynonavionics.com/documentation-overview.php
4.5. ACK TECHNOLOGIES DOCUMENTATION
Please obtain, read, and follow all instructions given in the latest version of a manual specific for the
system installed in your aircraft.
ACK Emergency Locator Transmitter - https://www.ackavionics.com/technical-library/
REFERENCED DOCUMENTS
PAGE 13 OF 99

ORLIČAN M-8 EAGLE
PILOT'S OPERATING
REVISION NO. 05
DATE OF ISSUE: MAY 02,
5. GENERAL INFORMATION
5.1. INTRODUCTION
The following pages contain the Pilot’s Operating Handbook and Airplane Flight Manual for M8-EAGLE
airplane designated by the serial number and registration number shown on the title page. All information
is based on data available at the time of publication.
This POH consists of fifteen sections that cover all operational aspects of a standard equipped airplane.
Section 15 contains the supplements which provide amended operating procedures, performance data and
other necessary information for airplanes conducting special operations and/or are equipped with both
standard and optional equipment installed in the airplane.
Additional supplements are individual documents and may be issued orrevised without regard to revision
dates which apply to the POH itself. The status of each supplement is determined in its Log of Effective
Pages.
This Manual is issued by aircraft manufacturer and must be kept on board of the aircraft during each flight.
5.2. IMPORTANT INFORMATION
Any damage to the aircraft shall be reported to applicable inspector-technician. The inspector-technician
will recommend the method of repair, supervise the repair and will make a technical inspection after the
repair has been completed. A record shall be entered into the aircraft documentation. Any damage which
potentially compromises the airworthiness of the aircraft must be reported to the appropriate aviation
authority.
GENERAL INFORMATION
PAGE 14 OF 99
ATTENTION!
THIS AIRCRAFT WAS MANUFACTURED IN ACCORDANCE WITH LIGHT SPORT AIRCRAFT
AIRWORTHINESS STANDARDS AND DOES NOT CONFORM TO STANDARD CATEGORY
AIRWORTHINESS REQUIREMENTS AND IT IS OPERATED ENTIRELY ON THE USER’S OWN
RISK.
WARNING!
DELIBERATE SPINS, STALLS AND AEROBATICS ARE PROHIBITED.

ORLIČAN M-8 EAGLE
PILOT'S OPERATING
REVISION NO. 05
DATE OF ISSUE: MAY 02,
GENERAL INFORMATION
PAGE OF15 21
5.3. ATTENTIONS, CAUTIONS, WARNINGS
Throughout this manual, small boxes are inserted reading ATTENTION, CAUTION, or WARNING. These
are items which require particularly close attention for special conditions or procedures.
WARNING!
THIS TEXT BOX REPRESENTS A HAZARDOUS SITUATION. WARNINGS ARE USED
TO CALL ATTENTION TO OPERATING PROCEDURES OR CONDITIONS WHICH, IF
NOT STRICTLY OBSERVED, MAY RESULT IN PERSONAL INJURY OR DEATH.

ORLIČAN M-8 EAGLE
PILOT'S OPERATING
REVISION NO. 05
DATE OF ISSUE: MAY 02,
5.4. AIRCRAFT DESCRIPTION
1. CHARACTERISTICS
The M-8 EAGLE aircraft is a two-seat, strut high-wing monoplane of all-composite structure designed for
sport or recreational flying. Favorable flight characteristics make the aircraft suitable for flight training.
The aircraft features spacious crew and baggage compartments. Large doors provide for comfortable
boarding of crew and loading of baggage. Adjustable seats allow the pilots of all heights to find
comfortable position. A stiff Kevlar cabin and three- point seat harnesses system provide maximum safety
of crew in emergency situations.
2. AIRFRAME
The fuselage is made of carbon-kevlar composite. Bulkheads are bonded into integrally stiffened skin to
receive forces from the landing gear, stabilizer, rudder, safety harnesses and wings. There are two doors
with a central-lock system mounted on flush hinges on the sides of fuselage, opening upwards.
Sandwich-type single-spar wings made of carbon-composite house two fuel tanks within leading section.
Wings are fitted with slotted Fowler flaps. Wings have rectangular center section with trapezoidal tips.
MS 313 wing profile is used. Roll along the longitudinal axis is controlled by ailerons with differentiated
deflection 12° down and 17° up. With aileron deflection up, a nose rises from profile, providing favorable
yawing moment. The wing strut is made of a steel strength tube with fittings and a laminate cover.
Trapezoidal horizontal tail unit is fixed into the fuselage bulkheads by pins and screws. Aerodynamically
balanced elevator has electrically servo-actuated trim tab. The elevator deflection is 19° up and 14° down.
Trapezoidal swept vertical tail. The rudder deflection is approximately 25°.
Rudder has dual cable control, ailerons are connected in the wings by a system of rods and controlled
through cables, elevator is rod-operated. Control yokes are used for hand-operated control. Rudder and
nose landing gear are operated by pedals with top-mounted shafts, which greatly improve the kinematics
of controls. Engine and landing gear brakes are controlled by appropriate controllers. The flaps are driven
by central actuator through a system of rods. The actuator control is located on the center panel.
Tricycle landing gear with steerable nose wheel. Main wheels - size 14x4-6 - are provided with hydraulic
disc brakes. These are carried on an all-composite leg. The nose wheel is fitted with spring and hydraulic
shock absorber. The front wheel has size 12x4-4. All wheels provided with fairings. Tire inflation of all
wheels is 2,5 bar (36psi).
3. CONTROLS
PEDALS
pressing left pedal turns aircraft left both on the ground and in the air, and vice
versa.
HAND
CONTROLS
pulling the yoke backwards, towards the pilot, raises the nose of aircraft (the
angle of attack increases) and the aircraft climbs. Pushing the yoke forward
dives the aircraft. Turning the yoke to the left banks the aircraft to the left,
turning the yoke to the right banks the aircraft to the right.
ENGINE
THROTTLE
pushing (or turning right) controller located on the middle-panel increases
engine output, and vice versa.
BRAKE
CONTROL
moving lever backwards, in the opposite direction of taxiing, brakes the aircraft.
The parking brake is controlled by separate valve.
GENERAL INFORMATION
PAGE 16 OF 99

ORLIČAN M-8 EAGLE
PILOT'S OPERATING
REVISION NO. 05
DATE OF ISSUE: MAY 02,

ORLIČAN M-8 EAGLE
PILOT'S OPERATING
REVISION NO. 05
DATE OF ISSUE: MAY 02,
4. AIRCRAFT DIMENSIONS
5. AIRCRAFT WEIGHTS
WING SPAN:
29,922 ft.
9,12 m
LENGTH:
22,671 ft.
6,91 m
HEIGHT, TOTAL:
8,924 ft.
2,72 m
WING SURFACE:
116,09 sq
ft.
10,785 m2
WING ASPECT RATIO:
7,678
DEPTH OF MAC (MEAN AERODYNAMIC
CHORD) BSAT:
47,36 in
1203 mm
WING PROFILE:
MS 313
AT ROOT:
51,181 in
1300 mm
AT TIP:
34,948 in
887 mm
WING FLAPS SURFACE:
9,106 sq ft.
0,846 m2
FLAPS DEFLECTIONS:
15° 30° 40°
HORIZONTAL TAIL PLANE SPAN:
9,187 ft.
2,8 m
HORIZONTAL TAIL PLANE SURFACE:
24,327 sq
ft.
2,26 m2
VERTICAL TAIL PLANE SURFACE:
10,484 sq
ft.
0,974 m2
CONTROL SURFACE DEFLECTIONS:
Ailerons:
up:
17°
dow
n:
12°
Elevator:
up:
19°
dow
n:
14°
Rudder:
left:
25°
right:
25°
EMPTY WEIGHT:
802 lb
363,8 kg
MAX. TAKE-OFF WEIGHT
1320 lb as an LSA
598,7 kg

ORLIČAN M-8 EAGLE
PILOT'S OPERATING
REVISION NO. 05
DATE OF ISSUE: MAY 02,
GENERAL INFORMATION
PAGE 17 OF 99