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AIRPLANE FLIGHT MANUAL 

 

Z 242 L 

 

Document No. 003.012.1 

 

 

 

Serial No.: 

 ................................................ 

 

Registration Mark: 

 ................................................ 

 

Manufacturer:  

ZLIN AIRCRAFT a.s. 

 

OTROKOVICE 765 02 

 

CZECH REPUBLIC 

 

Category: 

ACROBATIC  

(A) 

 

UTILITY  

(U) 

 

NORMAL 

(N) 

 

Certification Basis:  

FAR Part 23 

as amended trough 

Amendment 23 - 41 

inclusive

 

 

FAR Part 36 

as amended trough 

Amendment Amdt. 36 - 20 

inclusive

 

 

ICAO, Annex 16. 

 

 

THIS DOCUMENT MUST BE CARRIED IN THE AIRPLANE AT ALL OPERATION TIMES! 

 

THIS AIRPLANE FLIGHT MANUAL IS EASA APPROVED UNDER APPROVAL NO.:  10042932. 

DATE OF APPROVAL: 7.1.2013 

 

The English version has been translated with care and is accurate to the best of editor’s 
knowledge. However in all official matters the original Czech version is the authoritative 
document. 

 

THIS AIRPLANE F

LIGHT MANUAL SUPERSEDES ALL “AIRPLANE FLIGHT MANUALS OF THE  

Z 242 L AIRCRAFT” ISSUED IN ENGLISH VERSION, WHICH ARE NOT MARKED ON THE TITTLE 
PAGE WITH DOCUMENT NUMBER 003.012.1 

 

   

    

Copyright © 2011 

 

   

    ZLIN AIRCRAFT a.s. 

 

   

    765 02 OTROKOVICE 

 

   

    Czech Republic 

 

ISSUE OF REVISION No. 3 IS APPROVED UNDER DOA No. EASA.21J.110 APPROVAL 

DATE OF APPROVAL: 9.3.2017  

Summary of Contents for Z 242 L

Page 1: ...IGHT MANUAL IS EASA APPROVED UNDER APPROVAL NO 10042932 DATE OF APPROVAL 7 1 2013 The English version has been translated with care and is accurate to the best of editor s knowledge However in all off...

Page 2: ...load spectrum 0 5 0 7 2 9 1 6 2013 2 Formal corrections in FM correction of values for weight and C G position calculation correction of inner dimensions of cockpit and correction of english translat...

Page 3: ...11 20 3 2011 20 3 2011 20 3 2011 20 3 2011 8 6 2016 20 3 2011 20 3 2011 20 3 2011 20 3 2011 20 3 2011 20 3 2011 2 1 2 2 2 3 2 4 2 5 2 6 2 7 2 8 2 9 2 10 2 11 2 12 2 13 2 14 2 15 2 16 2 17 2 18 2 19 2...

Page 4: ...35 7 36 25 2 2017 25 2 2017 25 2 2017 25 2 2017 25 2 2017 25 2 2017 25 2 2017 25 2 2017 25 2 2017 25 2 2017 25 2 2017 25 2 2017 25 2 2017 25 2 2017 25 2 2017 25 2 2017 25 2 2017 25 2 2017 25 2 2017 2...

Page 5: ...ear 7 13 7 17 Baggage compartment 7 13 7 19 Seats seat belts and shoulder harnesses 7 13 7 21 Doors windows and exits 7 15 7 23 Control locks 7 16 7 25 Engine 7 17 7 27 Propeller 7 22 7 29 Fuel system...

Page 6: ...Chapter 7 ZLIN AIRCRAFT a s Description of the aircraft and its system Flight Manual Z 242 L REVISION No 3 7 2 EASA Approved 25 2 2017 INTENTIONALLY LEFT BLANK...

Page 7: ...structure provided with a main and an auxiliary spar Two wing halves are attached to the fuselage The main spar of the wing is connected with the centre section in the fuselage by means of two expanda...

Page 8: ...ol The ailerons are controlled by means of the control stick via levers and control rods The aileron deflections are differentiated Diagram of lateral control is illustrated on Fig 7 1 c Directional c...

Page 9: ...a doubled control rod The longitudinal trim is illustrated in Fig 7 2 Sense of control i turning the control wheel forwards makes the aircraft nose heavy ii Turning the control wheel backwards makes t...

Page 10: ...ustable pedals set handle 24 Headphone connection socket 8 Magnetic compass I 25 Fuel selector valve 9 Towing gear control 26 Control stick lock 10 Ventilation and heating control 27 Switches 11 Ignit...

Page 11: ...hone connection socket 8 Magnetic compass I 25 Fuel selector valve 9 Towing gear control 26 Control stick lock 10 Ventilation and heating control 27 Switches 11 Ignition switch 28 Fuses 12 Master swit...

Page 12: ...E indicator 11 R P M indicator 12 Manifold pressure gauge 13 Airspeed indicator II 14 Attitude gyro II Turn and Bank ind II 15 Altimeter II 16 Four pointer engine indicator 17 Four pointer fuel gauge...

Page 13: ...eed indicator I 8 Four pointer fuel gauge indicator 9 CHT EGT indicator 10 Clock 11 Accelerometer 12 V A meter 13 R P M indicator 14 Manifold pressure gauge 15 Engine hours counter 16 ELT remote switc...

Page 14: ...TEST 8 white STATIC TEST NOTES No 1 L FUEL LOW LEVEL fuel rest in the left tank No 2 R FUEL LOW LEWEL fuel rest in the right tank No 3 GENERATOR generator voltage drop below 26 2 V in the electric sy...

Page 15: ...e alternator to or from the network FUEL PUMP turns ON and OFF the electrical fuel pump ENGINE INSTR turns ON and OFF the fuel meters the four pointer indicator fuel pressure oil temperature oil press...

Page 16: ...anical controlled by means of a lever located between the seats Wing flaps have 3 arrested positions RETRACTED 0o TAKE OFF 14o LANDING 37o The arrestment is controlled by a pushbutton located on a lev...

Page 17: ...t and it is accessible from the cockpit The floors of the baggage compartment are provided with fastening straps and elastic for baggage put CAUTION THE BAGGAGE MUST ALLWAYS BE PROTECTED AGAINST MOVEM...

Page 18: ...ED 5 To shorten the straps lenght pull the free ends of the straps 6 To release the belts turn the lock gate A into the position RELEASE in this position all three pawls are released After being relea...

Page 19: ...lever through 180o forward and slide the canopy forward The canopy can be locked from outside by key during airplane parking Canopy emergency jettisoning The lever for emergency release is located bo...

Page 20: ...tick can be locked by meams of a red latch which is located beneath the left instrument panel closer to central panel The pilot gets the information about the manual control being locked by means of a...

Page 21: ...dle of throttle b Engine speed by blue handle is controlled the engine speed Pushing the handle increased the R P M low angle pulling the handle decrease the R P M high angle The handle is arrested wh...

Page 22: ...ng flap control 2 mixture control 3 propeller control 4 throttle control 5 left throttle control Fig 7 10a Diagram of engine controls applicable for aircraft s up to S N 0689 incl 2 mixture control 3...

Page 23: ...tmosphere via an oil separator 7 the separator oil is returned into the engine through the hose The diagram of the oil system is illustrated in Fig 7 10 On the figure are also shows the system of meas...

Page 24: ...located in the head of the right rear of cylinder Thermoelectric sensor of the exhaust gas temperature EGT is located in the exhaust manifold of the right rear of cylinder The engine speed indicator...

Page 25: ...n Fig 7 11 Winterization plates are inserted into the front engine cover to reduce low oil temperatures or cylinder head temperatures at low ambient temperatures In the lower front parts of engine cov...

Page 26: ...ine in which one or more cylinders were replaced it should be operated in flight at the cruising power in the range of 65 to 75 for the period from 50 operation hours or until the oil consumption is s...

Page 27: ...pump 5 is engaged the bypass valve 4 behind the strainer closes the direct flow from the strainer to the engine fuel pump 7 and opens the way from the strainer via the electric pump 5 in the engine f...

Page 28: ...ducer 9 fuel filter 10 fuel cock 11 four pointer indicator oil pressure oil temperature fuel pressure fuel consumption 12 four pointer fuel indicator 13 fuel draining valve 14 venting outlet 15 single...

Page 29: ...means of the parking brake which controls both brakes simultaneously NOTE DIRECTIONS FOR OPERATING THE PARKING BRAKE a BRAKING 1 Brake pedals simultaneously TREAD DOWN FULLY 2 Parking brake control P...

Page 30: ...e fuselage The emergency power supply consists from the two batteries is located in baggage compartment Supply to the turn an bank indicator and the auxiliary lighting in case of either the both prima...

Page 31: ...cal system 7 37 1 V A meter The V A meter is a combined instrument which indicates the voltage and the current in the airplane electric network 1 the left indicator indicates the voltage range 0 to 40...

Page 32: ...placard with the name of the circuit protected Each cap with fuses is designated by a placard with the value and name of the circuit protected Circuit breaker switch on procedure if installed Disconne...

Page 33: ...tarter ANN PAN 2 A annunciator light panel VA METER 2x1 A V A meter CHECK 1 A annunciator check TURN C 1 A turn and bank indicator ATT GYR 1 A attitude gyro DIR GYR 1 A directional gyro INT LIGHT 1 A...

Page 34: ...n equipment can be turned OFF simultaneously by two avionics master switches COM NAV 1 and COM NAV 2 if installed CAUTION PRIOR TO ENGINE STARTING STOPPING AND DURING THE CONNECTION OF THE AIRPLANE EX...

Page 35: ...the fixed frame of canopy To turn the light ON use the switch on the light body The interior light is connected directly to the battery MASTER SWICH and BATTERY switch need not be ON when using the i...

Page 36: ...air flows out beneath the airplane fuselage 2 Turning the heating handle arrow upwards the outlet of hot air into the outer atmosphere is closed and open the inlet of hot air on the windshield 3 Turn...

Page 37: ...on the cockpit central panel The air flow is closed by pushing the handle fully forward Pulling the handle backwards opens the airflow to the venting ducts from which it is directed to the front part...

Page 38: ...ation screw of the alternate static pressure 16 this adjustment is perform by the manufacturer at the airplane test flight and is locked by cover after adjustment NOTE Switching the from main static p...

Page 39: ...1 altimeter II 2 altimeter I enconding altimeter 3 vertical speed indicator 4 airspeed indicator I with stall warning signalling 5 drainage sump 6 static pressure pipe 7 total pressure pipe 8 stall wa...

Page 40: ...e cockpit a Emergency Locator Transmitter on request The ELT is designed to identify the position after an emergency landing or crash of an aircraft The ELT is activated automatically after an acciden...

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