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ORLI

Č

AN M-8 EAGLE

PILOT'S OPERATING

REVISION NO. 05

DATE OF ISSUE: MAY 02,

EMERGENCY PROCEDURES

PAGE

OF

45

49

NOTE:

Full power should only be used following a loss of oil pressure when operating close to the ground and
only for the time necessary to climb to an altitude permitting a safe landing or analysis of the low oil
pressure indication to confirm oil pressure has been lost.

If low oil pressure is accompanied by normal oil temperature, it is possible that the oil pressure sensor,
gauge, or relief valve is malfunctioning. In any case, land as soon as practical and determine cause.

•

Throttle Lever

→

minimum required

•

Land as soon as possible

7.9. HIGH OIL PRESSURE

Cold oil or possible internal plugging may be the probable cause of the high oil pressure.

•

Throttle

→

reduce rpm to minimum for flight

•

Oil pressure indicator

→

monitor

•

Oil pressure normal

→

follow PRECAUTIONARY LANDING procedure as soon as possible, see section 7.5

•

Oil pressure high

→

follow EMERGENCY LANDING procedure as soon as possible, see section 7.3

7.10. RECOVERY FROM UNINTENTIONAL SPIN

M-8 Eagle has not tendency to spinning in normal flight conditions and within operating limits. Should an
inadvertent spin occur, the following recovery procedure should be used:

•

Throttle

→

idle

•

Rudder

→

full deflection opposite to spin direction

•

Ailerons

→

maintain neutral position

•

Elevator

→

gradually push fully forward (dive) without moving the ailerons

•

Rudder

→

neutral position immediately after rotation stopping

•

Elevator

→

gradually pull back to recover from dive

WARNING!

PROLONGED USE OF HIGH POWER SETTINGS AFTER LOSS OF OIL PRESSURE

WILL LEAD TO ENGINE MECHANICAL DAMAGE AND TOTAL ENGINE FAILURE,

WHICH COULD BE FATAL.

WARNING!

KEEP THE CONTROL YOKE CENTERED ALONG ITS LATERAL AXIS (NO AILERON

DEFLECTIONS THROUGHOUT THE RECOVERY PHASE)! DO NOT ATTEMPT TO STOP

THE AIRCRAFT FROM SPINNING USING AILERONS INSTEAD OF RUDDER!

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Содержание M-8 EAGLE 2022

Страница 1: ... MAY 02 ORLIČAN S R O PAGE OF 1 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 ...

Страница 2: ...ČAN M 8 EAGLE PILOT S OPERATING REVISION NO 05 DATE OF ISSUE MAY 02 ORLIČAN S R O PAGE OF 2 2 Production T E bervid orlican or W www orlican or YOUR AIRPLANE SUPPLIER ORLIČAN Londýnská 120 00 Praha 2 Czech ...

Страница 3: ...ORLIČAN M 8 EAGLE PILOT S OPERATING REVISION NO 05 DATE OF ISSUE MAY 02 TABLE OF CONTENTS PAGE OF 3 10 1 TABLE OF CONTENTS ...

Страница 4: ...ERAL 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 E...

Страница 5: ...UATION 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 F...

Страница 6: ...0 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 ...

Страница 7: ...TRODUCTION 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 7...

Страница 8: ...OR 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 OPERATIO...

Страница 9: ...ANDING 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 ...

Страница 10: ...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...

Страница 11: ...d 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 gre...

Страница 12: ...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 t...

Страница 13: ...ommunication 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 ...

Страница 14: ...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 r...

Страница 15: ...ithout 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...

Страница 16: ...ual 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 ...

Страница 17: ...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 Rudde...

Страница 18: ...ORLIČAN M 8 EAGLE PILOT S OPERATING REVISION NO 05 DATE OF ISSUE MAY 02 ...

Страница 19: ... 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 ...

Страница 20: ...ORLIČAN M 8 EAGLE PILOT S OPERATING REVISION NO 05 DATE OF ISSUE MAY 02 GENERAL INFORMATION PAGE 17 OF 99 ...

Страница 21: ...ORLIČAN M 8 EAGLE PILOT S OPERATING REVISION NO 05 DATE OF ISSUE MAY 02 6 THREE VIEW DRAWING ...

Страница 22: ...ORLIČAN M 8 EAGLE PILOT S OPERATING REVISION NO 05 DATE OF ISSUE MAY 02 GENERAL INFORMATION PAGE 18 OF 99 ...

Страница 23: ...AIRCRAFT MODEL M 8 EAGLE AIRCRAFT SERIAL NUMBER 2022001 AIRCRAFT PLACE YEAR OF MANUFACTURE ÚSTÍ NAD ORLICÍ 2021 ENGINE MANUFACTURER ROTAX ENGINE MODEL 912 ULS 2 ENGINE SERIAL NUMBER 9 573 673 PROPELLER MANUFACTURER WOODCOMP PROPELLERS S R O PROPELLER MODEL SR 200 PROPELLER SERIAL NUMBER 1900921 RESCUE SYSTEM MANUFACTURER RESCUE SYSTEM MODEL RESCUE SYSTEM SERIAL NUMBER ...

Страница 24: ...lb 58 3 kg FUEL FUEL GRADE OCTANE INDEX automotive pump fuel min RON 95 min AKI 91 OIL TYPE Only oil with RON 424 classification At the selection of suitable lubricants refer to the additional information in the Service Information SI 912 016 latest edition OIL CAPACITY 0 793 U S gal 3 l without oil cooler and lines REDUCTION GEAR GEAR RATIO 2 43 1 FUEL TANK VOLUME 26 41 U S gal 100 l WARNING NEIT...

Страница 25: ...installation and maintenance delivered along with the aircraft PROPELLER MANUFACTURER Woodcomp Propellers s r o PROPELLER TYPE SR 200 NUMBER OF BLADES 3 MATERIAL OF BLADES Blade structure basic material ASH BEECH PROPELLER DIAMETER 66 14 inch 1680 mm PITCH ADJUSTMENT ground adjustable WARNING THE PROPELLER SHALL BE SENT TO THE MANUFACTURER FOR INSPECTION IN CASE OF EVEN THE SLIGHTEST DAMAGE OR IF ...

Страница 26: ...ponder Antenna TED TED Manufacturing N A ADSB SV ADSB 472 Dynon 14753 ADSB Antenna TED TED Manufacturing N A Radio SV COM X25 V Dynon 4528 Radio Antenna Composite ULA 1FL Airband antenna KONS 3117 Audio Com SV INTERCOM 2S Dynon 5124 Glass cockpit SV AP PANEL V Dynon 5439 Glass cockpit SV KNOB PANEL V Dynon 9676 Airspeed indicator Winter EBF 8026 Winter Instruments 40405 Altimeter Winter 8033 Winte...

Страница 27: ...ITED STATES www beaconregistration noaa go v INTERNATIONAL www 406registration com 1 3 LOCATION OF CONTROLS Ignition switch Left side of left instrument panel Starter Central bottom panel under fuel valve selector Choke Central bottom panel Throttle Central bottom panel Brakes Bottom part of middle panel Longitudinal trim Left control yoke Wing flaps Central bottom panel Closing of the cabin Front...

Страница 28: ...ORLIČAN M 8 EAGLE PILOT S OPERATING REVISION NO 05 DATE OF ISSUE MAY 02 2 EQUIPMENT LAYOUT GENERAL INFORMATION PAGE 24 OF 99 ...

Страница 29: ...aution VS Stall Speed Clean 40 74 Stall speed flap up VS0 Stall Speed Landing Configuration 38 70 Stalling speed at maximum take off weight and at the landing configuration Flaps deflection Degrees Use 15 Take off 30 Landing 40 Landing Short field landing 38 38 38 71 70 70 VFE Maximum Flap Extended Speed 65 120 Maximum allowed speed with flaps fully deflected 40 73 135 Maximum allowed speed with f...

Страница 30: ...een arc VS the stalling speed or the minimum steady flight speed at the maximum take off weight in the clean configuration flaps up Upper limit of green arc VN0 the maximum structural cruising speed Do not exceed this speed except in smooth air YELLOW ARC 108 130 124 149 200 240 Caution Range Operations must be conducted with caution and only in smooth air RED LINE 130 149 240 Maximum speed for al...

Страница 31: ...Y 02 LIMITATIONS PAGE OF 27 42 6 3 1 ANALOG AIRSPEED INDICATOR MARKINGS CAUTION ALL SPEEDS IN THIS MANUAL ARE DETERMINED BY PRIMARY AIRSPEED INDICATOR DISPLAYED ON EFIS DYNON SKYVIEW ANALOG AIRSPEED INDICATOR USED AS EMERGENCY ONE MAY INDICATE SLIGHTLY DIFFERENT SPEEDS ...

Страница 32: ...iod admissible at cold start min 12 psi 0 8 bar below 3500 rpm normal 29 73 psi 2 0 to 5 0 bar above 3500 rpm EXHAUST GAS TEMPERATURE max 1616 F 880 C COOLANT TEMPERATURE max 248 F 120 C AMBIENT TEMPERATURE max in flight 140 F 60 C due to manifold temp max at start 120 F 50 C due to ambient temp min at start 13 F 25 C due to oil temp FUEL PRESSURE max 5 8 psi 0 4 bar min 2 2 psi 0 15 bar FUEL auto...

Страница 33: ... is at the top of the green strip As the amount of fuel decreases the w h i t e l i n e m o v e s d o w n accordingly INSTRUMENT RED LINE LOWER WARNING YELLOW ARC LOWER CAUTION GREEN ARC NORMAL OPER RANGE YELLOW ARC UPPER CAUTION RED LINE UPPER WARNING TACHOMETER RPM 0 1400 1400 5500 5500 5800 5800 OIL TEMPERAT URE 120 F 50 C 120 176 F 50 80 C 176 230 F 80 110 C 230 266 F 110 130 C 266 F 130 C COO...

Страница 34: ...MUM LANDING WEIGHT 1 320 598 7 MAXIMUM WEIGHT IN BAGGAGE COMPARTMENTS 33 15 MINIMUM CREW WEIGHT unlimited unlimited FUEL TANK CAPACITY MAX PAYLOAD US GAL PAYLOAD LB FULL TANKS 26 41 359 3 3 4 OF TANKS 19 81 399 0 1 2 OF TANKS 13 21 438 6 1 4 OF TANKS 6 60 478 3 30 MIN FUEL RESERVE 2 91 500 5 WARNING PAY SPECIAL ATTENTION TO LUGGAGE AND FUEL WEIGHT THESE APPLICABLE MASSES INFLUENCE THE CENTER OF GR...

Страница 35: ...tion from forward to backward 6 9 OPERATING CEILING 6 10 WIND SPEED LIMITS MAC XT INCH XT MM EMPTY AIRPLANE C G POSITION 29 96 15 65 397 51 MOST FORWARD C G 23 00 12 35 313 69 MOST REARWARD C G 37 00 18 98 482 09 OPERATING CEILING 14 000 ft MAXIMUM ALLOWED HEADWIND SPEED 20 KTS 10 m s MAXIMUM ALLOWED CROSSWIND SPEED 8 KTS 4 m s REMEMBER FAR 61 315 B 11 STATES THAT SPORT PILOT LICENSE PRIVELEGES DO...

Страница 36: ...up Maximum positive load factor in the center of gravity 4 0 g Maximum negative load factor in the center of gravity 2 0 g Flaps down Maximum positive load factor in the center of gravity 2 0 g Maximum negative load factor in the center of gravity 0 0 g LOAD FACTOR N 1 0 1 15 1 4 2 0 ATTITUDE CONFIGURATION 0 30 45 60 Flaps not extend ed Km h Kts 80 43 83 45 95 51 113 61 Flaps 30 extend ed Km h Kts...

Страница 37: ...05 DATE OF ISSUE MAY 02 LIMITATIONS PAGE OF 33 42 6 13 FLIGHT ENVELOPE 6 14 FLIGHT CREW Minimum crew 1 pilot Maximum crew 1 pilot 1 passenger Minimum weight of crew unlimited Maximum weight of crew 440 lb 200 kg Maximum weight per seat 242 lb 110 kg ...

Страница 38: ...ad sediments in the oil system Thus it should only be used in case of problems with vapor lock or when other types of gasoline are unavailable Note Risk a vapour formation if using winter fuel for summer operation It is not recommended to take off when both tanks contain less than 2 64 USG 10 liters of fuel FUEL TANK CAPACITY US GALLON L TOTAL CAPACITY 26 38 100 TOTAL USABLE 25 85 98 TOTAL CAPACIT...

Страница 39: ...with gear additives such as high performance motorcycle oils are required Because of the incorporated overload clutch oils with friction modifier additives are unsuitable as this could result in clutch slippage during normal operation Oil consumption max 0 06 l h 0 13 liq pt h Oil capacity without oil cooler and connecting lines min 3 l 0 8 US gal depending on the respective installation 6 17 COOL...

Страница 40: ...LIGHT SAFETY RESTRICTIONS Following is a list of critical situations to avoid It is forbidden to Fly in heavyrainfall Fly with wind above 25 knots Fly during thunderstorm activity Fly in ablizzard Fly in instrumental meteorological conditions IMC Fly into known icing conditions Fly whenoutsideair temperature OAT is below 4 F 20 C Flywhenoutsideairtemperature OAT reaches 120 F 50 C orhigher Perform...

Страница 41: ...ettering is to be clearly printed large enough and positioned so it is legible to the user All documented placards affixed to the aircraft should be clearly displayed to the user and passenger All placards and labels are to be placed on non critical surfaces so they are not likely to be defaced and removed during normal service When a placard is used it should be located near the aircraft system o...

Страница 42: ...C Visual Meteorological Conditions IFR Instrument Flight Rules IMC Instrument Meteorological Condition Location right part of instrument panel at the bottom on the right PLACARD 3 2 PLACARD OPERATING DATA AND LIMITS Location right part of instrument panel at the bottom on the left PLACARD 4 Empty weight 802 lb Never exceed speed VN E 135 KIAS Max take off weight 1 320 lb Max flap extended speed VF...

Страница 43: ...ORLIČAN M 8 EAGLE PILOT S OPERATING REVISION NO 05 DATE OF ISSUE MAY 02 LIMITATIONS PAGE OF 39 42 ...

Страница 44: ...ON PLACARD Location left side of the middle panel PLACARD 5 4 AIRCRAFT IDENTIFICATION PLATE Location either adjacent to and aft of the entrance door or on the fuselage surface near the tail surfaces 5 FUEL PLACARD Location Near fuel filler cup top wing surface LIMITATIONS PAGE 39 OF 99 ...

Страница 45: ...ORLIČAN M 8 EAGLE PILOT S OPERATING REVISION NO 05 DATE OF ISSUE MAY 02 ...

Страница 46: ...c actions can be applied to any emergency 1 MAINTAIN AIRCRAFT CONTROL Many minor aircraft emergencies turn into major ones when the pilot fails to maintain aircraft control To avoid this do not panic and do not fixate on a particular problem aviate navigate and communicate in this order Never let anything interfere with your control of the airplane Never stop flying 2 ANALYZE THE SITUATION Once yo...

Страница 47: ...the cause cannot be determined and corrected the emergency landing must be accomplished While performing the engine restart shutdown checklist maintain 65 kts and keep in mind where the landing zone is located Circle over the landing zone if needed until sufficient altitude has been lost to setup for a landing Do not dive toward the landing zone if at too high an altitude in order to attempt a saf...

Страница 48: ...ng area Gliding speed maintain speed 60 kts 110 km h minimum Altitude below 300 ft 90 m land in take off direction maneuvering the aircraft out of obstructions Wind evaluate direction and velocity Flaps as necessary Fuel valve selector OFF Ignition OFF Safety harnesses tighten Main switch OFF Side slipping the aircraft by cross controlling the rudder and ailerons will increase the rate of descent ...

Страница 49: ...and Apply take off flaps maintain speed 65 knots Fly above right side of selected landing area in the direction of planned landing at a height of 150 ft to estimate the area condition obstacles and to determine exact landing direction Carefully check the area Climb a little maintaining ground visibility if conditions permit fly small left circuit Perform a normal approach and landing Side slipping...

Страница 50: ...l and ventilation Use hand fire extinguisher if available Land immediately or as soon as practical if location for safe landing is not available 7 7 LANDING WITH A DAMAGED LANDING GEAR If main landing gear leg or tire is damaged perform touch down at the lowest speed possible and keep the damaged leg wheel above the ground for as long as possible using ailerons Begin braking intensively as soon as...

Страница 51: ... pressure normal follow PRECAUTIONARY LANDING procedure as soon as possible see section 7 5 Oil pressure high follow EMERGENCY LANDING procedure as soon as possible see section 7 3 7 10 RECOVERY FROM UNINTENTIONAL SPIN M 8 Eagle has not tendency to spinning in normal flight conditions and within operating limits Should an inadvertent spin occur the following recovery procedure should be used Throt...

Страница 52: ...dder Use to maintain lateral control 7 12 LOSS OF PRIMARY INSTRUMENTS Autopilot disengage Circuit breakers check reset once Main switch cycle ON OFF Land as soon as practicable 7 13 LOSS OF FLIGHT CONTROLS If loss of a control appears e g due to jamming or disconnection then some control might be still possible For all possible flight control failures ENSURE AUTOPILOT IS OFF and not causing a perc...

Страница 53: ...G MAXIMUM AIRSPEED Should the VNE 135 kts be exceeded reduce power and airspeed immediately Continue flight using minimum safe speed Land as soon as possible and have the aircraft verified for airworthiness by authorized service personnel 2 VIBRATIONS Proceed as follows should any unnatural vibrations occur Adjust engine speed to a value which minimizes the vibrations Land at nearest airport or pe...

Страница 54: ...ORLIČAN M 8 EAGLE PILOT S OPERATING REVISION NO 05 DATE OF ISSUE MAY 02 ...

Страница 55: ... following from system installation and optional equipment which require supplementation of this Manual are shown in section 15 Supplements 8 2 PRE FLIGHT INSPECTION The pre flight inspection is very important and must be accomplished by pilot before each flight An incomplete or careless inspection could allow airplane failure The following pre flight inspection procedure is recommended by the air...

Страница 56: ...k tire is correctly seated and not slipping around the rims 5 ENGINE PROPELLER FUEL SYSTEM Check fuel level and cleanliness check propeller and attachment to engine Check oil level according to engine manufacturer s manual check coolant Check engine cowling fastening Check tightness of fuels hoses tank caps fuel filters Check fuel filter for impurities and water 8 3 ENGINE STARTING 1 AFTER ENTERIN...

Страница 57: ...el pump turn off to determine that the engine pump is operating properly 8 4 ENGINE TEST Engine warming up always start to warm up the engine at approx 2000rpm for approx 2 minutes Continue at 2500rpm until cylinder head and oil temperature reaches 122 F 50 C minimum Perform the engine check heading upwind Test maximum rpm check transition from minimum to maximum rpm and back Check function of bot...

Страница 58: ...ntrol check free movement and function Flight control check free movement and function Fuel gauge check fuel quantity Fuel valve selector ON Instruments check adjust altimeter if necessary Engine operating values check temperatures and pressures Rescue system unlock Check the cabin tightened seat harnesses closed door removed secured loose objects Flaps 15 position Trim neutral position Propeller ...

Страница 59: ...and remaining fuel on board should be monitored Always make a comparison between estimated and actual time above any waypoint Take care when selecting the flight path avoid flying over large urban areas large forests or large water areas as well as over mountains Landing possibilities are very limited in case of engine failure or other emergency over those areas Always have some suitable landing a...

Страница 60: ...rward too far as this will cause higher airspeeds and result in a missed approach Hold an attitude that will maintain 55 to 60 kts during the side slip Ensure the airspeed does not fall below a minimum safe airspeed of 50 kts during the side slip Conducting an approach in the slip configuration will not require special skills nevertheless if not yet familiar with the aircraft we recommend initiall...

Страница 61: ...descend rate increases markedly Maintain speed 50 knots 90 km h Crosswind approaches can best be accomplished by using the wing down top rudder method touching first on the down wing side main wheel followed by the other main wheel and finally lowering the nose wheel all the while keeping the yoke into the wind 8 13 BALKED LANDING GO AROUND Throttle full engine power 5700 rpm max Flaps take off po...

Страница 62: ...ble landing area Airspeed 60 70 KIAS 110 130 IAS flaps UP Wing Flaps 40 Airspeed MAINTAIN 54 KIAS 100 IAS Power REDUCE to idle as obstacle is cleared Touchdown MAIN WHEEL FIRST Brakes APPLY HEAVILY Wing Flaps RETRACT 8 16 SOFT FIELD TAKEOFF When taking off in a soft field grass gravel snow it all comes down to one goal transferring your aircraft s weight from wheels to wings as soon as possible By...

Страница 63: ...n Engine rpm as necessary Observe taxiing rules speed up to 5 knots 10 km h 8 19 ENGINE SHUT OFF Engine rpm idle Instruments observe if engine instruments are within limits Avionics OFF Ignition OFF Section switches OFF Main switch OFF Fuel valve selector close 8 20 STOPPING THE AIRCRAFT PARKING Taxi very carefully before stopping the aircraft paying attention to obstacles and terrain Brake the ai...

Страница 64: ...chniques If not stated otherwise the performance data given in this section is valid for max takeoff weight and under International Standard Atmosphere ISA conditions 9 2 AIRSPEED INDICATOR SYSTEM CALIBRATION The following table contains test derived data for the determination of Calibrated Airspeed from Indicated Airspeed IAS KNOTS CAS KNOTS FLAPS 0 FLAPS 15 FLAPS 30 FLAPS 40 40 44 41 38 38 45 48...

Страница 65: ...TS IAS KM H HIGHT LOSS DURING RECOVER Y FT HORIZONTAL FLIGHT 0 43 80 150 15 38 71 200 30 38 70 200 40 38 70 200 TURN WITH 30 BANK ANGLE 0 45 83 200 15 39 72 200 30 39 72 200 RUNWAY SURFACE TAKE OFF RUN FT TAKE OFF DISTANCE OVER 50 FT OBSTACLE FT PAVED 463 141 m 1149 350 m GRASS 466 142 m 1230 375 m RUNWAY SURFACE LANDING DISTANCE OVER 50 FT OBSTACLE FT BRAKING DISTANC E FT PAVED 459 140 m 312 95 m...

Страница 66: ...uum pressure 24 inHg CONDITIONS MAX CONTINUOUS POWER 5500RPM AIRCRAFT WEIGHT 1320 LB IDEAL CLIMBING SPEED RATE KNOTS IAS FT MIN M S 1500 FT ISA 65 994 5 05 4000 FT ISA 65 970 4 93 8000 FT ISA 65 919 4 67 ALTITUD E FT ISA ENGINE SPEED RPM CRUISE SPEED KIAS 150 0 400 0 69 440 0 82 460 0 88 480 0 93 500 0 98 520 0 103 540 0 106 560 0 110 600 0 400 0 64 440 0 77 460 0 83 480 0 88 500 0 93 520 0 97 ...

Страница 67: ...ORLIČAN M 8 EAGLE PILOT S OPERATING REVISION NO 05 DATE OF ISSUE MAY 02 PERFORMANCE PAGE OF 60 63 540 0 100 560 0 104 ...

Страница 68: ...f and landing 20 Knots 10 m s Max allowed crosswind speed for take off and landing 8 knots 4 m s Max allowed tailwind speed for take off and landing 4 knots 2 m s Crosswind Calculation Chart Source FAA Pilot Handbook Of Aeronautical Knowledge ALTITUDE FT ISA 1500 ft FUEL ON BOARD US GAL 26 4 ENGINE SPEED RPM 4400 480 0 500 0 5200 550 0 FUEL CONSUMPTION US GAL H 3 362 4 0 95 4 5 40 5 039 5 8 84 FLI...

Страница 69: ...F ISSUE MAY 02 9 10 OPTIMUM GLIDING SPEED 9 11 CEILING PERFORMANCE PAGE 61 OF 99 CAUTION REMEMBER FAR 61 315 B 11 STATES THAT SPORT PILOT LICENSE PRIVELEGES DO NOT ALLOW FLIGHT AT AN ALTITUDE OF MORE THAN 10 000 FEET MSL OR 2 000 FEET AGL WHICHEVER IS HIGHER ...

Страница 70: ...N OF CG Place the aircraft on horizontal floor with its wheels positioned on three scales one scale for each wheel 1 WEIGHING FOR AFT CENTER OF GRAVITY Move seats to rearmost position Fill baggage compartment with maximum allowed load Empty fuel tanks Seat two persons of appropriate weight for MTOW 2 WEIGHING FOR FORWARD CENTER OF GRAVITY Empty baggage compartment Move seats to foremost position F...

Страница 71: ...7 36 𝐿 𝑖 𝑛 66 73 C G POSITION CALCULATION C G CALCULATION WEIGHT CALCULATION 𝐺 𝐿 𝑋 𝑖 𝑛 𝑋 𝑖 𝑛 𝐿 𝑋 100 𝐺 𝐺 𝐺 𝐶 𝐸 𝐿 𝐾 𝑆 𝐴 𝑇 CRE W LB FUEL GAL BAG LB NOSE WHEE L 𝑮 𝒍 𝒃 MAIN GEAR 𝑮 𝒍 𝒃 TOTA L WEIG HT 𝑮 𝒍 𝒃 C G FROM REFERENCE PLANE 𝑿 𝑪 𝒊 𝒏 𝑿 0 0 0 158 3 643 9 802 2 15 65 29 96 0 0 33 149 5 685 7 835 3 16 87 32 55 132 0 0 177 7 756 8 934 5 16 13 30 98 132 3 0 180 6 772 4 953 16 17 31 07 220 0 0 187 2 835...

Страница 72: ... M 8 EAGLE PILOT S OPERATING REVISION NO 05 DATE OF ISSUE MAY 02 WEIGHT AND BALANCE PAGE OF 64 67 Calculated position of C G is within a permitted range of 23 37 bSAT 396 13 2 33 218 7 1093 9 1312 6 17 7 34 4 ...

Страница 73: ...lculation of Mean Aerodynamic Chord WEIG HT LB S ARM INCHE S MOMENT WEIGHT X ARM INCH LBS MAXIMU M ALLOWA B L E I N C H LBS PILOT AND PASSENGER INCLUDES DOOR POCKETS 397 8 20 09 7 991 8 9 745 7 BAGGAGE 33 0 46 61 1 538 1 1 538 1 FUEL 90 0 14 86 1 337 4 2 360 0 AIRCRAFT TYPICAL EMPTY WEIGHT INCLUDES OIL AND UNUSABLE FUEL 802 2 15 65 12 554 4 12 554 1 TOTAL 1 323 0 17 70 23 421 7 MOMENT C G inches T...

Страница 74: ...ORLIČAN M 8 EAGLE PILOT S OPERATING REVISION NO 05 DATE OF ISSUE MAY 02 10 3 PERMITTED PAYLOAD RANGE WEIGHT AND BALANCE PAGE 65 OF 99 ...

Страница 75: ...er and elevator and it 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 4 VERTICAL TAIL UNIT Trapezoidal swept vertical tail The rudder deflection is approximately 25 11 3 CONTROL Airplane control consists of ailerons elevator and rudder Rudder has dual cable control ailer...

Страница 76: ...7 77 11 4 CONTROLS IN COCKPIT 1 Control yokes 2 Main switch 3 Engine throttle 4 Choke 5 Fuel valve selector Starter under fuel valve selector 6 Ruder control pedals 7 Wing flap control 8 Switch ignition 1 switch ignition 2 9 Trim control 11 5 INSTRUMENT PANEL More information in section 5 6 2 Aircraft Equipment Layout ...

Страница 77: ... pedals and the instrument panel the seats are sliding on a rail and can be folded down for easier access to the luggage compartment Each of seats is fitted with three point safety harness which is composed of belly belts shoulder straps and central lock The seat belts are attached to airplane structure one point behind the seats on the baggage compartment bulkhead the other two points on the floo...

Страница 78: ...t side lock 2 Both pins are operated simultaneously by rotating a common central handle 11 8 BAGGAGE COMPARTMENT Baggage compartment is positioned behind seat rests Maximum weight of baggage is 33 lbs 15 kg The baggage compartment is fitted with a safety net for baggage fixation All items in the baggage compartment must be secured in place by means of this safety net 1 2 locking WARNING WARNING IN...

Страница 79: ...si pressure Brake system is composed of brake lever main wheel cylinder hoses for leading brake liquid brake yokes with wheel cylinders brake pads and brake disks By pulling the brake lever a pressure is created in brake circuit and hydraulic cylinders press the brake pads onto the brake disks Braking pressure can be regulated only by force of brake lever pulling The airplane is equipped with a pa...

Страница 80: ...pulled out then this position corresponds to idle SWEPT VOLUME 82 5 in3 1352 ccm TAKE OFF POWER MAX 73 5kW 5800rpm CRUISING POWER MAX 69 0kW 5500rpm DRY WEIGHT 128 lb 58 3 kg FUEL FUEL GRADE OCTANE INDEX automotive pump fuel min RON 95 min AKI 91 OIL TYPE Only oil with RON 424 classification At the selection of suitable lubricants refer to the additional information in the Service Information SI 9...

Страница 81: ...1 680 mm Max RPM 2500 RPM Propeller is allowed to be used on engines having the power output within 19 80 kW The own inertia moment 1450 kg cm Designation TRACTOR Drilling the circumferential holes 6x diameter 8 mm on spacing 75 mm Central hole diameter 25 mm 47mm Blade structure basic material ASH BEECH The basic supporting parts thickness in mm 8 8 8 8 8 8 Gluing glue Epoxy 1200 press temperatur...

Страница 82: ...ORLIČAN M 8 EAGLE PILOT S OPERATING REVISION NO 05 DATE OF ISSUE MAY 02 DESCRIPTION OF AIRPLANE AND SYSTEMS PAGE OF 73 77 11 12 FUEL SYSTEM Scheme of fuel system ...

Страница 83: ...ORLIČAN M 8 EAGLE PILOT S OPERATING REVISION NO 05 DATE OF ISSUE MAY 02 DESCRIPTION OF AIRPLANE AND SYSTEMS PAGE OF 74 77 11 13 ELECTRICAL SYSTEM ...

Страница 84: ...atic tube face Static pressure is sensed through openings on the tube circumference System of pressure distribution to individual instruments are made by means of flexible plastic hoses Static pressure is led to altimeter airspeed indicator and ADAHRS 200 Total pressure is led only to the airspeed indicator Keep the system clear to assure its correct function If water gets inside the system discon...

Страница 85: ... 5 6 2 Equipment layout 11 16 AVIONICS The aircraft is equipped with traditional analogue instruments together with glass cockpit incorporating flight engine and navigation instruments including a transponder For description of navigation and communication equipment refer to section 15 Supplements DESCRIPTION OF AIRPLANE AND SYSTEMS PAGE 76 OF 99 CAUTION INSTRUMENT NAVIGATION AND ANTI COLLISION LI...

Страница 86: ...ied out at the latest in the following intervals 1 WARRANTY INSPECTION FIRST 25 HOURS The inspection after first 25 flight hours is performed in conjunction with the engine oil and filter change by the airplane owner if is trained for the airplane s maintenance or performed by an FAA qualified inspector following the First 25 hour inspection checklist If the aircraft is used for commercial operati...

Страница 87: ...ING It is advisable to park the aircraft inside a hangar or other enclosed space with constant temperature sufficient air exchange ventilation low humidity and dust free environment if possible PARKING THE AIRCRAFT CHECKLIST TASK STATUS Remove or open all necessary inspection plates access doors fairing and cowling Thoroughly clean the aircraft and aircraft engine after initial visual inspection f...

Страница 88: ...ircraft should be towed using tow bar attached to the hole after a pin is removed from front landing gear leg Passing through narrow areas requires assistance of trained person at wingtips The tow bar serves for manipulation with an empty aircraft on the ground only The M 8 EAGLE manufacturer also approves the following handling methods To move the aircraft backwards push at the rectangular part o...

Страница 89: ...lage with bolts and new self locking nuts Connect strut to the wing insert the end of the strut into the fitting on the wing and secure with bolt and new self locking nut Install aerodynamic cover of wing strut and strut fitting covers Connect the upper fuel level gauge hose to the tank and tighten the hose clamp Connect strobe light and fuel gauge connectors Insert the aileron and flap rod forks ...

Страница 90: ...bilizer into the fuselage from a side and insert elevator pins Figure 5 into fuselage bulkhead Screw the stabilizer mounting and secure the bolts with securing wire Slide the elevator rudders into the hinges on the stabilizer and screw them to the coupling Secure the screws with wire Connect the trim cable connector Check rudder control Install rudder control cover Check function of rudder control...

Страница 91: ...iliary wing connection Figure 9 Unscrew nut from main wing spar connection Figure 10 Unscrew nut from auxiliary wing spar connection Unscrew aerodynamic covers of wing struts Unscrew nuts from wing side strut pins Secure support wing against movement at wingtip Remove upper pin from strut turn strut towards ground Remove wing pins from main and auxiliary spar forks Release hose clamps and disconne...

Страница 92: ...rizontal stabilizer rearwards to loosen front pins Carefully pull horizontal stabilizer sideways Store horizontal stabilizer on stand or in transport cover 12 6 ROAD TRANSPORT The aircraft may only be transported with wings removed When transporting over longer distance or in closed cargo bay of a truck elevator must be removed If elevator is not removed it must be fitted with red pennants or acco...

Страница 93: ...located Figure 12 items 1 and 2 On the left side of the lower engine cover in flight direction 1 air intake for oil cooler is located Figure 12 item 4 To this air intake an air tunnel equipped with two toggle latches is glued from the reverse side Figure 13 In the rear part of the lower engine cover on the left side there is a hole for the exhaust pipe Figure 12 item 5 Upper engine cowling is atta...

Страница 94: ...ORLIČAN M 8 EAGLE PILOT S OPERATING REVISION NO 05 DATE OF ISSUE MAY 02 HANDLING AND SERVICING PAGE OF 85 93 Figure 13 Lower cowling inner Figure 14 Upper cowling ...

Страница 95: ... pins from toggle latches on the air tunnel for oil cooler and unclip the toggle latches Disconnect the front light connector Unscrew all bolts on the lower cowling and remove it carefully ENGINE COWLINGS INSTALLATION Make sure that the ignition switch is set to OFF Before installation check engine cowlings for cracks Carefully put lower cowling to appropriate position Attach lower cowling using w...

Страница 96: ...ke sure that the ignition switch is set to OFF Remove engine cowlings according to chapter 12 7 Disconnect fuel hose downstream electrical fuel pump Install drain hose onto fuel pump and prepare clean jerry cans Set the main switch to ON and turn the fuel valve selector on one of the tanks Switch on the fuel pump and pump all fuel from the tank into the prepared jerry cans Turn the fuel valve sele...

Страница 97: ... EAGLE aircraft has two grounding points for this purpose One of them is copper grounding strip at landing gear leg The other is exhaust manifold which is better suited for attachment of grounding clip of refueling station Do not handle fuel tank before completing the grounding Open fuel cap and insert filling nozzle into tank It is not necessary to use strainer as certified refueling stations alw...

Страница 98: ...tatic probe and engine covers The windshield and windows only to be cleaned by washing with ample stream of lukewarm water with addition of appropriate detergents using soft rag sponge or wash leather Use suitable polishing agent after wiping rests of water The instrument panel and control knobs need only to be wiped clean with a soft damp cloth The multifunction display primary flight display and...

Страница 99: ...g the airworthiness of the LSA The aircraft owner may submit written comments and questions regarding any mandatory Notice to the organization who issued the Notice The aircraft owner is responsible to report unsafe conditions and service difficulty issues to the manufacturer via Safety and Maintenance Report Feedback Form part of Aircraft Maintenance Manual The aircraft owner is responsible to ob...

Страница 100: ...NSIBLE TO PROVIDE CURRENT CONTACT INFORMATION TO THE MANUFACTURER THAT ARE SUITABLE FOR DELIVERY OF COS NOTICES CONTINUED OPERATIONAL SAFETY FEEDBACK FORM NAME CONTACT INFO NOTICE DATE AIRCRAFT MODEL AIRCRAFT S N ISSUE DESCRIPTION ORLIČAN S R O LONDÝNSKÁ 376 57 120 00 PRAGUE 2 CZECH REPUBLIC BERVID ORLICAN ORG PHONE 420 605 231 920 WWW ORLICAN ORG ...

Страница 101: ...ORLIČAN M 8 EAGLE PILOT S OPERATING REVISION NO 05 DATE OF ISSUE MAY 02 CONTINUED OPERATIONAL SAFETY PAGE 91 OF 99 ...

Страница 102: ... and other material available from the trainee s Instructor and in general terms would proceed according to the steps below Though individual trainees will proceed through each of these stages at different rates depending on existing skills available time continuity of training and their speed of learning the various tasks the indicative stage training times may be a useful guide To explain the de...

Страница 103: ...me the student strives to maintain constant air speed and to keep slip indicator ball in center position throughout the turn This Lesson includes performance of turns to a preselected compass heading Before each turn the student checks that the area into which he she turns is free Conditions for passing The student performs turns at small bank angle on his her own finishing them to a specific head...

Страница 104: ...nd landing to the student Special attention must be paid to gaining speed after lift off to allow climb at correct climbing speed also to the correct shape of traffic pattern altitude at different sectors for traffic pattern and correct planning of landing with stable descent without the need to change engine power to change angle of approach As far as planning of landing is concerned the instruct...

Страница 105: ...aking into account the altitude position of aircraft in traffic pattern wind speed and direction and other operating conditions Having mastered emergency landing at an airfield the instructor and the student leave the airfield and enter the practice area where the instructor reduces engine power to idle the instructor does not signal the time of reducing engine power to idle beforehand and the stu...

Страница 106: ...y changing aircraft s performance during take off and climb and is markedly different performance on approach with longer hold off and lower stall speed The instructor will also instruct the student how to handle possible engine failure during all phases of traffic pattern flight If the student shows any signs of stress and or nervousness the instructor must add a dual flight Student s uncertainty...

Страница 107: ...nding to 1 3 of runway length without further use of engine power to correct angle of descent 19 LESSON 18 NAVIGATION FLIGHT All conditions must be VFR Training methodology The instructor defines flight route with landing at different airfield A Triangular navigation flight with landing at two different airfields is planned with a minimum flight distance The student performs complete navigation pr...

Страница 108: ...esson 18 The only difference is that the student flies solo The instructor verifies correctness and completeness of navigation preparation and permits the flight Stopover landing must not be planned at airfield where properly instructed person is not available Fuel onboard must suffice for planned flight and 20 more minutes Planned time of landing at home airfield must be at least 30 minutes befor...

Страница 109: ... the standard airplane 15 2 LIST OF INSERTED SUPPLEMENTS SUPPL NO TITLE OF INSERTED SUPPLEMENT DATE 01 SkyView_HDX_Pilots_Users_Guide Rev_F_v16 pdf 02 SV INTERCOM 2S_Installation_and_Pilots_User_Guide Rev_A pdf 03 Rotax Operators Manual_912 Series_ED4_R0 pdf 04 Rotax engine Logbook 05 Woodcomp SR200 Assembly Instruction and Guarantee Certificate 06 ACK_E 04_Emergency Locator Transmitter_Manual pdf...

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