Zlin Aircraft Z 142 Flight Manual Download

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Summary of Contents for Z 142

Page 1: ... rr U cate qcrie s Category ER9BA IHAI ry f ae 4 I ro ZJC7 C2CC r NORMAL N Certification Bases FAR PART 23 with incorporated changes up to No 23_13 czech copy is approved by the srATE AVTATT N TNS ECTTON praque No 5326 1254t7g Hi Limitations given in Section 2 and 7 must be observed during operation Year of lssue fv pt h q K u l B 1 r ltt EEJFE r o i DtC cz27eg41u 1 I iil 201t1 H 1989 0 1 ...

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Page 5: ...TS SECTION 1 SECTION 2 sEcTtoN 3 SECTION 4 sEcTtoN 5 SECTION 6 sEcTtoN 7 General Operaling Limitations Emergency Procedures Normal Procedures Performances Weighl and C c Positions Supplemenls 3 1 5 1 6 1 7 l ...

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Page 7: ...CTION 1 1 GENERAL CONTENTS htroduction Changes Abbrevialions and Definitions Dimensional sketch of the z 142 Aircraft Specification Principal Technical Data Pilot s Cockpit Page t J t J 1 5 1 6 1 10 1 13 ...

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Page 9: ...s 1 The aircraft manufacturer will send the binding bulletin with changes or new correcteo pages of the Flighl Manual to the holder of the Flight Manual 2 The holder of the Flight Manual is under an obligation a of recording the obtained change into the LIST OF CHANGES item 1 2 2 b of carrying out of the change in accordance with the bulletin or of replacing the original pages by new corrected one...

Page 10: ...Date of issue of new pages Date of change incorporation and signature 1 z 142t29 1 11 Rev 7 1991 a z 142t31 2 5 2 7 2 8 4 7 4 8 4 9 4 10 4 12 4 13 4 14 Rev 2 2 1993 Z 142132a Rev 31 8 1995 Z 142136a 3 1 3 5 3 6 Rev Nov 12 1996 5 Z 142138a z o Rev Jan 16 1998 o Z 142143a Rev I 14 2 10a 2 10b Rev 20 5 2003 7 Z 142152a 14 2 20 4 16 74 7 6 Rev 28 2 2006 6 Z 142153a 14 2 5 2 11 2 12 Rev 24 1 1 2006 KUe...

Page 11: ...rcraft as shown on its pitot static airspeed indicator calibrated to reflect standard atmosphere ediabatic cornpressible flow effect at sea ievel unconected for airspeed syslem erors True airspeed means the airspeed of an aircraft rerative to undistributed air True airspeed is equal lo equivalent airspeed multiplied by qo q 1 2 I o specific weight of air at sea level Q specific weight of air at sp...

Page 12: ...SECTION 1 1 4 DIMENSIONAL SKETCH OF Z 42 AIRCRAFT ...

Page 13: ...in side_by side arrangement are adjustable into 4 posiiions The main pilot s seat is the lefl one Behind the seats the hand luggage platform is situated The canopy can be opened by sliding forward and is equipped with device for emergency release For locking the canopy in par y opened position the delent serves is of all metal structure with main and auxiliary spar The structure of the wrng is div...

Page 14: ...rod a mixture handle and a compressor rod The propeller rotation is operated by a push pull rod 1 5 6 Landino oear has three wheels and consists of the main landing gear and the nose gear The main gear includes flat steel springs attached to the spar of the centre section of the wing The main gear wheels are equipped with hydraulic disk brakes with automatic backlash elimination The braking plates...

Page 15: ... Svstem The oil tank is located in the engine compartment in front of lhe firewall 3 The fuel and oil systems enable to execute aerobatic maneuvers and inverted flights in AEROBATTC and UTlLtTy categories onty 1 5 9 Eouiornent 1 Electrical Svstem is of a single conductor type pole The earthing conductor pole is formed by the aircraft frame Rated network voltage rs 28 v The main power source is rep...

Page 16: ...raft on customer s wish The tow gear consists of a ceble mount rear view mirror and control of the cable disengaging device The control rod ofthe disengaging device is situated on the panel between the seats Maximum take off weight of the sailplane may be 500 kg lnslruments Following instruments for the supervision of the flight engine and airframe including signalizalion are mounted in the cockpi...

Page 17: ...ace HTS elevator lravel stabilizer area elevator area total area HTS Vertical Tail Surface Ml S rudder travel fin area ructder area total area ws Landing Gear wheel track wheel base wheel size main landing gear nose wheel lire pressure main landing gear nose wheel up down right left 730 kg i 3ol 1s sAr 1 Note Weight and C G positions agree for all categories A 1 6 2 Loadinos Category Loading Speci...

Page 18: ...ower in high 1200 m lSA 3 Short time operaling powerwith compressor SHUT time limiied to max 5 min 2000 mm Power RPM Manifold Pressure Power setting Power RPM Manifold pressure Note KW HP kPa al Maximum take off 154 2 210 t 2 5yo 2750 130 118 1 1 2 o ot 0 02 Maximum c0ntnu0us 125 2o o 170 2 5Yo 2600 I 3 98 l2 1 0 1 0 02 Maximum crursrng 103 ZYo 140 2 5 0 o 2400 3o o 90r2 0 92 r 0 02 1 Maximum crui...

Page 19: ...1 7 PILOT S COCKPIT a6 a rl tjt 6 z v il c r a l z 9 GJ GJ ilE rA s7 6 i a q A 9J AA 9d J e l J ...

Page 20: ... Magneto switch 22 Master switch 23 Starter pushbutton 24 Sectionalizing switches 25 Control of instrument lighting intensity 26 Generator function check 27 Signalling of fuel remainder L R 28 Signalling of Pitot system heating and ram pressure sensing unit 29 Pushbutton of signalling check stall waming and heating 30 Fuses 31 Earphone socket 32 Seat 33 Seat adjustment 34 Board extinguisher 35 Mag...

Page 21: ...e Tachometer ll Accelerometer locating acc to centre panel equipment VA meter Manifold pressure gauge Il Indicator of pressure in spar with filling valve Compensation placard Placards description and underlines in item 2 25 Intercom pushbutton Note Optional o ...

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Page 25: ...ata Airspeed Limilations Airspeed Indicator and Acceleromeler Markings Load Factors and Maneuvering Envelope Aerobatic Maneuvers Permissible Ambient Temperalure Maximum Allowable Wind Components Flights in lcing Conditions Application of Brakes Minimum Crew Maximum Number of Seats For passengers Smoking Minimum Nitrogen pressure in Main Spar Flange Markings of Nitrogen pressure in Main Spar Flange...

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Page 27: ... 2 142 atrcraft is approved for day fligts at ground visibirity vFR day frights operating the aircraft under IFR conditions and in icing condilions are orohibitlo_ Note The z 142 aircraft is approved for rimited night operation The purview of rimitations is set down by flight authoriry after consideration the detiation in righting from requisite provisioni 2 3 MAXIMUM TAtr OFF AND Procedure of max...

Page 28: ... shown in Section 6 X ln pilot s cockpit there are also permitted other combinations of payload till max weight 200 kg Caution 1 C G limit positions are valid for Aerobatic Utility and Normal category 2 The C G check procedure is shown in Seclion 6 t 2 4 MAXIMUM PERMISSIBLE PAYLOAD Category Max permissible payload kg Aerobatic 240 txilily 290 Normal CENTER OF GRAVITY POSITION C G limit position MA...

Page 29: ...d other maximum operating limits in accordance with Flight Manuat 2 3 Extraordinary use of maximum take off power will be entered in the Engine Log Book Mixtured control adjustment for the maximum take off and continuous power setting acc to the table 4 3 2 2 6 2 CompressorUsino 1 During continuous using of swithed on compressor it is necessary to keep the rated manifold pressure in value range sp...

Page 30: ...ained Z 142 Flight Manuel Rev Jan 16 1998 2 8 lnstrument name Unit Red radial line Yelow arc Green arc RPM indicator LUN 1341 2 8 LUN 1345 2 8 RPM 500 3025 2680 2860 500 2680 LUN 1341 23 8 RPM 500 3025 2600 2860 500 2600 Manifold pressure gauge KPA 118 98 1 18 39 98 1 2 0 4 1 0 Oil temperature gaguge zc 85 25 40 80 85 40 80 Cylinder head temperature gauge 70 210 x 7 0 140 185 210 x 140 185 Fuel pr...

Page 31: ...ble fuel 122 220 zJA ENGINE OIL Limitation Percentual carbon residue musl nol exceed 0 4 of weight Recommendation FOR RUNNING IN max up to 50 hours a mineral oit e g AERO SHELL 100 or an equivalent is rerecommended ROF AFTER RUNNING lN operation a dispersant ash free oil is recommended FoR TEMPERATE cLtMATtc zoNE AERo SHELL w 100 or equivalent is recommenoeo FOR TROPICAL ZONE AERO SHELL W 120 or e...

Page 32: ...SPEEDLIMITATIONS Z 142 Flight Manual Rev 2 2 1993 9l z a Airspeed Abb Category Aerobatic Utility Normal tAs km h cAs km h IAS km h CAS km h Nevet exceed speed vNE tl a JJZ t 4 Normal operating limit speed Vr ro zl5 260 260 Design maneuvering speed Vn A u 284 264 270 252 ZJJ Maximum permissible flaps erlended soeed 189 185 188 185 ...

Page 33: ...ator IAS km h 273 333 103 273 88 189 Accelerometer Meaning of instrumenl markings Limil values Increased attention regime Normal Extending flaps Operating range 2 14 2 14 1 LOAD FACTORS AND MANEUVERING ENVELOPE Load Factors Category Load factor Aerobatic Ulility 3 Normal 3 8 1 ...

Page 34: ... SECTION 2 2 14 2 l eEr g SY9 9Pe Lood foctor 6 1 o 3 4 Leoend category AEROBATIC category UTILITY category NORMAL u F n ...

Page 35: ...J 00 Jed aJuspaaixe Jo rf ruanbag enl tr nilnJ gPF E o T3HF EE i 63 o 3 Lo r O trl af F a t a crt F c c LN F tr to LO F c O c O m I N _ l r o q a E c rq N Lf a c_ rtl rJ Lrl o tt o Z 142 Flight Manual Rev 20 5 2003 ...

Page 36: ... SECTION 2 Z 142 Flight Manual Rev 20 5 2003 INTENTIONALLY LEFT BLANK 2 10b ...

Page 37: ...issible number of turns max 6 b Intentional spins wjth wjng flaps extended are pROHIB TED c Intentional power on spins are PROHIBITED 6 Flick rolls are pROHtB TED 7 Aerobatic maneuvers are PROHIBITED a With fuel in auxiliary tanKs b With luggage in luggage compartment The forrowing is a rist of the arowed maneuvers for the aircraft in aerobatic category For the utility category only maneuvers 1 2 ...

Page 38: ...tted following flight maneuvers No Name Recommended Entry Speed km h IAS t 2 Steep turn angle of bank max 60 Chandelle Slip min 190 mtn zlu 140 2 6 PERMISSIBLE AMBIENT TEMPERATURE The range of permissible ambient temperature for operating the Z 142 aircraft is indicated by the area outlined by heavy lines in the following diagram Atiitude tkml 40 30 20 40 r20 f30 40 Temperotufe rcl Z 142 Flight Ma...

Page 39: ...speed for application of brakes is lOO km h Minimum aircraft crew is 1 pilot Maximum number of seats for passengers I right SMOKING On board of lhe Z 142 aircrafl SMOKING tS PROHIBITED Minimum permissible nitrogen pressure in the main spar flange is 150 kpa 1 5 kp cmr Caution 1 1l litl sen pressure drop berow specified minimum varue it is necessary to stop further aircrafl operation and to remove ...

Page 40: ...THE ACROBATIC CATEGORY OTHER OPEMTING LIMITATIONS WHICH MUST BE COMPLIEO WITH WHEN OPERATING THIS AIRPLANE IN THIS CATEGORY OR IN THE UTILITY AND NORMAL CATEGORY ARE CONTAINED IN THE AIRPLANE FLIGHT MANUAL APPROVED ACROBATIC MANEUVERS AND RECOMMENDED ENTRY SPEEDS IAS km h LOOP MtN 240 IMMELMANN TURN MIN 250 HALF ROLL AND DIVE OUT MAX 150 STALLED TURN MIN 180 ROLL MIN I8O SPIN 1 10 OUTSIDE LOOP FRO...

Page 41: ...ated on the L H and R H cockpit side at emergency rerease handre By pulling the handre on L H or R H side of cockpit backward rhe suspensrons are unlocked Force the canopy upwards Note Placard No 4 is located in the luggage mpartment 4 NoAER_o_BATrcs rs ALLowED wrrH FUEL rN luxtGnirnr rxs TAKE OFF AND LANDING ON RIGHT TANK 2 15 ...

Page 42: ...OSE HEA I TAIL HEAVY DIRECTIONAL TRIM Note DIRECTIONAL TRIM Placards No 1 2 are located at trim control WING FLAPS 4 FLAPS RETRAGTED I FLAPS START FLAPS LANDING Note Placard No 3 is located at wing flap control lever and shows coresponding position ot wing fla ps FUEL SHUTOFF VALVE FUEL TANKS 1l MAIN 60 L LC T I A t J AUXILIARY 50 L LET MAIN RIGHT OUL AUXILIARY 50 L RIGHT 2 16 ...

Page 43: ...OSED Note Placard No 4 is rocated at the fuer shutoff varve and gives a coffesponding position of rhe fuel shutoff valve and capacity of fuel tanks 5 6 o 8 HAND PUMP Note Placard No 5 is located at fuel hand pump control PRIMING Note Placard No 6 is located at priming control STARTER I UIXTURE l Note Placard No 7 is loceted al starter pushbutton and minure control rich I lean FIRE EXTINGUISHER PUL...

Page 44: ... REST PITOT SYSTEM CHECK Caution When signalling fuel rest flight time cca 5 min change over the fuel shutoff valve on second tank Note Placard No 10 is located at lighlening signalling on the instrument panet VENTILATION AND HEATING IN THE COCKPIT Note Placard No 11 is located at ventilation and heating control in the cockpit the 1 1 VENTILATION PULL HEATING TURN 2 18 ...

Page 45: ...TION PUSH TO MAX Nole 13 Placard No 12 is located al airscrew control By PUSHING the angle of propeller setting is decreased higher revolution By PULLING the angle of propeller setting is increased lower revolufion SUPERCHARGER PUSH ON Note Placard No 13 is located at superchager controt Positions ON push OFF pull No Arrow position Sing on placard Healing function left 0 closed up front part of wi...

Page 46: ... I IJIA BEACON LIGHTING TRANS FORMER Ett t tr ar GENEMTOR STARTER RADIO FLIGHT INSTRUMENTS RADIO COMPASS PITOT HEATING Note Placards No 15 are located on panel between pilot seats at sectionalizing switches and show separate electrical circuits The actual location of switches depends on the particular aircraft equipment Z 142 Flight Manual Rev 28 2 2006 ...

Page 47: ... l a WIND SPEED COMPONENT DETERMINATION DIAGRAM r I V 30 l n h EMMPLE shown in broken lines 1 Wind speed u 13 m s 2 Angle 20o 3 Poinl of intersection determine the position of point 3 Parallel lines that are drawen from point 3 determine wind speed componenls 4 Opposite to take off direction w 12 2 m s 5 Cross wind v 4 5 m s ...

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Page 51: ... Abandoning the Aircreft by Parachute 3 3 Pressure Drop in Main Spar Flange 3 4 Exhaust Collector Bum Out 3 5 Electric system troubles 3 6 Stelling speed alarm failure 3 7 lnstrument troubles Z 142 Flight Manual Rev Nov 12 1996 Page it at 3 3 3 5 3 5 3 5 J O 3 6 3 1 ...

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Page 53: ...id for pilot s operating even in a case when flight high does not allow abandoning the aircraft by parachute or when the pilot is not equipped with a parachute 3 2 ABANDONING THE AIRCRAFT BY PARACHUTE Caution 1 During canopy emergency release DO NOT OPEN lhe lock ofthe canopy 2 During abandoning it is necessary not to manipulate the aircraft conlrol for example to strike on the control stick by le...

Page 54: ... 2 Trim tab as required 3 Magnetos off 4 Fuel shutoff valve off 5 Master switch off 6 Canopy emergency release pull emergency release lever DO NOT OPEN canopy lock 7 Execution of canopy release push with both hands up 8 Earphone throw out of the cockpit 9 Fastening belts release throw backward shoulder straps 10 Tum the body to the right kneel on the right seat with the right teg hotding of by han...

Page 55: ...airDort 2 lf possible do not overload supporting structure during the flighl EXHAUST COLLECTOR BURN OUT lf smell of exhaust gas experienced in the cockpit CLOSE HEATING immedialely and ventilale the cockoit 3 5 ELECTRIC SYSTEM TROUBLES 3 5 1 Generatorfailure Lighting up of a red light informs the pilot on the generator failure lf ihe GENERATOR switch is on and the engine speed is higher than 1 800...

Page 56: ...WITHIN 30 MINUTES LAND IN THE NEAREST SUITABLE AIRFIELD WARNING AFTER THE COMPLETION OF THE FLIGHT WTH THE ELECTRIC SYSTEM FAILURE OCCURRANCE A BATTERY MUST BE CHECKED AND SERVICED PRITOR TO A FOLLOWING FLIGHT STALLING SPEED ALARM FAILURE lf the stalling speed alarm does not function airborne pay enhanced attention to approach speed and low speed flighls INSTRUMENT TROUBLES On the basis of airborn...

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Page 59: ...4 tR 4 18 4 19 4 19 4 20 4 21 4 22 Before Entsring the Cockpit After Entering the Cockpit Starting the Engine Warm Up Ground Check Texiing Before Take Off Take Off Climb Cruising Descent Approach Landing Afler Landing Stopping the Engine Security the Aircran Recovery from Spins and Stalls Balked Landing Emergency Landing Night Ftights Gyro Horizon Control Oirecdional Gyro Control Aerobalics Flight...

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Page 61: ...AL PROCEDURES BEFORE ENTERING THE COCKPIT Preflioht Check Note 1 ffffii3 lfffirerlisht check and exerior inspection accororns to the rigure and 2 unless specified otherwise in corresponding ilems check the surface condition 4 3 ...

Page 62: ...ushion or parachute from the unoccupied seat b tie together fastening belts on the unoccupied seat Main spar flange pressure check min 150 kPa 1 5 kp cm1 Canopy a windows clean and transparent b sliding the cenopy c locking the canopy in closed posilion 1 2 3 4 0 2 3 Surface Free movement of elevator and rudder Play in elevator and rudder joints and balance tabs Pull rod connection to the elevator...

Page 63: ... Tyres condition end pressure in tyres 190 kpa 1 9 kp cm2 Landing gear spring condition Locking of cowlinos Prope er btedes intact StJi ilf n ftap and crankcase cooting btind ftange in accordance wilh air Tyre condition and pressure in t compression and shock o oro lli 3 oolPa 2 5 kptcm2 7 8 ct a free movement b ptay in joints c mass balance fastenino d surface Wing flaps Trailing edge Uprer v inr...

Page 64: ...GHT INSTRUMENTS 9 Check a Engine instruments function b Signalling check for function by pushing the button PITOT SYSTEM CHECK 1 stalling speed warning warning bell 2 Pitot tube heating white light Note PITOT HEATING switch must be ON befofe signalling check After checking it must be off STARTING THE ENGINE 1 Extemal power source connect 2 Fuel shutoff valve set to 2 R position RlcHT 3 Throttle an...

Page 65: ...tarter 4 Starting lhe engine a disconnect the radiostation from board network by swrtch on the radiostation control panel when engine starting b maximum time of starting is 10 sec 1 l it is possible to repeat starting the engine 3 times with intervals of 30 sec ldl another starting is po ible after cooti ng the starter maybe after 1O minutes t afler slarting the engine the starter puihbutton musi ...

Page 66: ... or instruments horizon radiostation etc Z 142 Flighl Manuel Rev 2 2 1993 4 3 1 Table for Startino the Enoine Ambient air temperature and starting conditions Control Primer Notes Throttle Mixure Engine starting on the ground above soc 114 to 112 ot stroke on the stop O 2lo 4 slrokes Turn manually lhe propeller 2 4 turns magnetos OFF below soc l or slightly enriched hot engine after flight 112 ol s...

Page 67: ...n check lil manifotd pressure 90 kpa 0 92 at b propeler contror set 2 3 times to extreme positions i e minimum and _ maxtmum propeller pitch angle 4 Range speed and engine power check according to table Z 142 Flight tvtanual Rev 2 2 1993 Operating values limitations Power setting max continuous max take off idling Time limitation 20 sec 10 sec unlimited tnronte maximum maxrmum idling Compressor of...

Page 68: ...The taxiing is permitted with wing flaps RETRACTED only 2 At taxiing the gyro horizon must be LOCKED ifthe direclional gyro horizon is not on Note 1 Set taxiing speed accoding to tenain conditions wind speed and wind direction 2 When taxiing utilize rudder control in curves with small radius use brakes 4 7 BEFORE TAKE OFF 1 Conlrol free movement 2 Trim tab neutral 3 Wing flaps start position 4 Fue...

Page 69: ...act in safety altitude Trim tab use as reouired Caution TAKE OFF IS PROHIBITED 1 The engine runs roughly 2 The engine inslruments readings are not wilhin the operaling limits 3 The speed drop exceeded SO RpM at ground check 4 Cross wind component exceeds allowable limits 5 Nilrogen pressure in main spar flange drops below 1SO kpa 1 5 kp cm2 Recommendation DO NOT BRAKE when performing take off from...

Page 70: ... A U category N 0 1000 140 150 1000 2000 135 145 2000 3000 130 140 3000 4000 125 135 4000 5000 120 5 Fuel shutoff valve affer 5 min flighl change over to position L R LEFT and RIGHT 2 3 4 o Power settino in acc rdance with table Operating values limitations Power setting Maximum lake off Maximum continuous Time limitation 5 min unlimitation Compressor on on off RPM 2750 30 2600 r 3 Manifold pressu...

Page 71: ...ep lhe manifold pressure to rated flight altitude 2 During cruising fright above rated fright artitude the compressof can be used for keeping prescribed manifold oressuie 2 Mixture a to the attitude 1S00 m 4920 ft ISA _ LEAN b above the altitude 1500 m 4920 ft tSA enrich as required i e approximatety for every 1000 m ISA altitude one arrested step to the leit _ to the sign Observe cylinder head th...

Page 72: ...ttle idling 2 Mixture set successively to vertical position LEAN 3 Speed 150 200 km h as required IAS 4 Trim tab as required Caution 1 lf cylinder head temperature drops below 70 C open the throttle to warm up cylinder heads 2 Before landing the cylinder head temperature must be min 100 C 4 12 APPROACH 1 Approach speed 130 km h IAS in category A U 140 km h IAS in category N 2 Wing flaps position F...

Page 73: ...Note On paved runway pull the control stick as required at finishing the landing run In accordance with FAR part 23 the maximum rate descent for landing is v6 2 7 7 AFTER LANDING 1 Compressor off 2 Trim tab elevator neutral rudder neutral 3 Sectionalizing switches off as required horizon etc STOPPING THE ENGINE 1 Temperature cool the heads of cylinders on temperature below 1400C 2 Throttle idting ...

Page 74: ...ilerons After rotation has stopped a Rudder neutral b Elevator pull steadily the control stick to perform the aircraft recovery from the dive Caution lf the procedure specified for revovering from the spin is not complied with the spin may be recovered with over turning Normal over tuming is to one tum since counteraction have started after one spin turn to 1 5 turn since counteraction have starte...

Page 75: ...tion has stopped a rudder neutral b elevator _ neutral pull steadily the control stick to perform the aircraft recovery from the dive 3 Unintentionalsoins 1l Retract the wing flaps in case lhey are extended 1 uelne posilion and direction of spin rolation 9 Rudder full deflection opposite to the direction of rotation 4 Elevator a push at normal soins b pu at inverted sDio 5 After rotalion has goppe...

Page 76: ... posilion corresponding to the spin performed and recover according to ilem 4 17 1 4 18 BALKED LANDING 1 Throttle maximum 2 Propeller PUSH TO MAx min angle 3 Compressor on 4 Trim as required to speed of 120 kr h IAS 5 Climb after speed of 120 km h IAS is reached 6 Wing flaps a at speed of km h IAS to FLAPS START position b at speed of 130 km h IAS to FLAPS RETRACTED position 7 Repeat landing maneu...

Page 77: ...ht before tanding Turn off landing light after tanding Caution Dfiing taxiing nd standing the landing light must be OFF risk of overheating and deformation of light cover 4 21 GYRO HORIZON CONTROL 4 21 1 In ceneral 1 The gyro horizon is actuated by an arestment tie rod and a knob for the aircraft symbol actuation 4 5 6 7 2 3 4 The a estment tie rod is rocated in the right corner of instrument and ...

Page 78: ...e gyroscop is started 3 ln case of necessity the instrument can be unlocked afler 25 sec following its turning on However its tunction is correct only after the glow tube is on 4 The gyro horizon operates at aerobatic maneuvers too only in spins its data are not reliable 4 22 DIRECTIOIIAL GYRO CONTROL 4 22 i ln General The directional gyro is conlrolled by the knob located on the instrument in the...

Page 79: ...al gyro according to lhe compass is carried out in 15 min intervals 4 23 AEROBATICS 4 23 1 The Z 142 aif aft is approved for aerobatic maneuvers specified in section 2 item 2 15 4 23 2 Individuar permitted aerobalic_maneuvers can be performed in an arbitrary sequence and various combinations in solo flight or wilh a co pilot when all limitations coroing io Seaion z item 2 15 t are observed 4 23 3 ...

Page 80: ... is permitted at max continuous engine power only i1 is at manifold pressure 100 kPa 1 02 at and 2600 RPM 3 Increasing of engine throttle in lhe first third part of motion range from idling to max throtile must be performed slowly and smoothly min wilhin 2 sec 2 When performing aerobetics select the entry allitude so as to be able to bring the aircraft into level flight at a safe altitude after an...

Page 81: ...e 10 11 12 13 14 1s lmmelman turn Half roll and dive out Stalled lurn Inverted flight Inverted tum Inverled loop from the inverled flight position lnveried loop from the normal horizontal flight Inverted spin 4 23 ...

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Page 83: ...oo Turn of 36o 3600 Kurve Virage de 160 Brpar ra 3600 _ r ___ _ _ I s A U A V N oin l8O nln 97 utrn 180 nin I90 nin l03 xtrs 190 kn h knot6 vu c kn h knots xu e A U N A Y H c 18o 2oo kmlh 97 lO8 knots 180 200 ru q ...

Page 84: ...4t StouPav6 ztt6 ka Z cllDblng Turn Stclgendc Kurwe par c ra6opcn Encoml Virage en mont a nt A U N A Y E l2O knr h d8 2 i o o tl I N r ll I A U N A V H n ln oln IfEo knfh knotr 220 l19 2n xu c ...

Page 85: ...3 3 i tippins S l ippen r x oJt bte Hre Giissade tar Nl trn 1YJ cYF 1ft Ez c 33 AI q l tts 6 t 8dr 5FF x Fx 3 sr g fJ s czQt l t ts 8d ut 8dt iflg ifls ...

Page 86: ...r fil n nt Vol piqud Sturzflug Ihxnposarrc o o rc F4 l4o kn h 76 knots I y c N 3 160 klrlh 86 knotc 160 rn q arax 333 kmlh nax l8O knots raxc 333 xn Al ...

Page 87: ...5 yrfi Vr i 11e Trudo ln IIIrouop o Ilo 59 I ITJ knr h kno be t v e 200 2 _o kn 108 lIs zoo 2 c knoLs xu u PeB 1988 ...

Page 88: ...effiiil thcrrchlag Ileur Eqclepoea o l5O o 49O feet K q w l7O kt7lr 92 knotr L7O t q t Itr I t 24O ko1lt 13O knotc 24O v c 2m kn h l19 knots Zfr rv c e ...

Page 89: ...7Xfii Tcnneau Rolle Bocrca o su t o EtrT J y x th8 r E EE o ga t o Ecl J I E QNO 1 r x EEI ...

Page 90: ...PFckrut Ilnelnann Turn Irlc laann Ku nve Iloayletas Eecr cpoaa c lepeBoporor urerrxas Immelmann o t5 l3O l5O n x 425r49O feet ain min rtnH 250 135 250 kn h kno ts Rv q 65 knots L u c ...

Page 91: ...Zvrat Ha lf nol I and Dlve Our Schleifenfluo o qunapxui uefesopo r qepes kpllJro Retournement o o EC JJX 838 EP 3 Ef z s o Ec JJ 6od r r J xx l ctct4 EE E o r t o J t 14 fi x c r nl I I ...

Page 92: ...kn h P lL ilt a 80 l6s 1t7h 43 54 knots 120 140 6 E k 80 100 ru s lso 180 490 590 2 kn h lO8 knota 20O tcu q t ii mln l8O km h oln 97 knote rrE 180 rtr q 10 Souvr6t Stalled Turn Renversement Kehre troaopot ra o o ...

Page 93: ...It ii ioPi fn f li Ilu3 Vol sur ie dos mih 2OO min iOB tr c rg 200 k m h knots xu c ...

Page 94: ...t2 ffi li Virage ren vers d n ltldGch turn R ckenflugkeh re O6parxlil elpe r a o I I I I E EC JJts RgR ...

Page 95: ...oaltion Ob15cenf pFenet z letu na zSdech H3 iffil g eue dem 06patnas nerat If8 noteTa Ba cnuEe Looping retourn6 du vol sur le dos 80 tJ BO kn h knots xu s 18O m x r seo fiet DEh5 min min Mt B 260 t40 e60 ka h knot s t u rr 25o kn h 135 knots 250 xu 1 ...

Page 96: ...erted Loop frol the 14 15ff l Horizbntal Flrsht Obenrchlag aus dcr Rgllf 91 Hontzonra lf tug u opaaEa g e a t rlB BOpIa DEoro tro lele vo1 normal Loopi ng retourn6 du 8 43 80 ka h knot s av q k vltr vind ven t 250 l3s 250 kn h knot s xv c ...

Page 97: ...1 5 Y Ho n3oiiou n vr i I I e len v e r s e ii t t t t Q 1 R vokn h j i3i1 t TI s6 i t 1X l 1 N i z t i 0 xr u i z o kn h l3O knots 24D xuha K ...

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Page 101: ...un Take Off Distance Over 15 m Obstacle Meximum Rate of Climb Practical Ceiling Maximum Glide Landing Dislance Over 15 m Landing Roll Distance Cruising Speeds Maximum Speed in Level Flight Endurane Flighl Range Stall Speeds Airspeed Correction Chan Page 5 3 5 3 5 3 5 3 5 4 5 4 5 4 5 4 5 5 5 5 5 5 5 6 5 7 5 7 5 1 ...

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Page 103: ... category 1090 kg 5 2 TAKE OFF RUN Condilions altilude 0mlSA max take off Dower wing flaps in START position runway level dry concrete 5 3 TAKE FF DISTANCE OVER 15 m OBSTACL Conditions unslick soeed IAS safe take off soeed IAS remaining conditions as outlined in item 5 2 5 1 MAXIMUM RATE OF CLIMB Conditions foMard speed IAS altitude 0mlSA max take off power compressor ON wing flaps in RETMCTED pos...

Page 104: ...CE Conditions As soecitied in item 5 7 PRACTICAL CEILING Conditions engine power max continuous 2600 RPM manifold pressure 98 kpa it is 1 00 at max lhrotle above rated altitude compressor ON wing flaps RETMCTED speed according to item 4 9 4 MAXIMUM GLIDE Conditions Power setting idling 5 4 tl N m 5000 4700 4300 Wing flaps Speed IAS km h Glide A U N A U N Retracted 125 134 7 38 Start 118 126 6 80 L...

Page 105: ...ssor oN wing flaps in position RETMCTED 5 11 ENDURANCE Conditions As soecified in item 5 9 Power selting RPM Manifold pressure Speed km h kPa at TAS CAS IAS A U N A U N A U N Max continuous 2 600 98 1 00 213 208 208 203 2 t5 208 Max cruising 2 400 90 0 92 197 lon 192 186 197 189 Economy cruise 2 300 oz 0 84 170 171 175 167 178 147 Category Speed kmih cAs tAs Aerobatic A Utility U 231 225 234 Norma...

Page 106: ... kPa at A U N category A U Category N Max continuous 2 600 qR I 00 213 208 2 h 00 min 3 h 45 min Max cruising 2 400 90 0 92 197 190 2 h 40 min 5 h 00 min Economy cruise 2 300 82 0 84 179 171 3 h 20 min 6 h 10 min Power setting RPM Manifold pressure Speed TAs km h Flight range kPa at A U N Category A U Category N Max continuous 2 600 OR 1 00 213 208 425 780 Mex cruising 2 400 90 0 92 197 190 525 95...

Page 107: ...erted flight lower part of chart 3 Categories A U N 4 All positions of wing flaps 5 Whole range of operaling flight levels D Category Wng flaps position Stall speed CAS krn h IAS krn h Aerobalic A e70 ks RETRACTED START LANDING Vsr 113 Vsr 110 vso 102 103 88 Lxility U 1020 kg RETRACTED START LANDING Vsr 116 vs1 112 vso 104 107 102 o t Normal N 1090 kg RETRACTED START LANDING Vsr 120 Vsr l 16 vso 1...

Page 108: ...0 320 340 360 rAS kn h 5 t4 3 Diaoram application the example is shown with dash line 1 Erect a perpendicular line from relevant indicated speed IAS e 9 IAS 240 km h 2 From point of intersection of perpendicular line with airspeed correction curve for corresponding category the parallel line is led to lefi side of chart where airspeed conection 0 va is detined 0 va 10 km h CAS IAS 6 va CAS 240 10 ...

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Page 111: ...Empty Aircraft 6 5 Aircrefi Equipment 6 5 Payload 6 8 Weight and Payload Check 6 9 Center of Gravity Position check 6 9 Weight Payload and Center of Gravity Position check Procedure 6 I Weight Payload and Center of Gravity Position check Example 6 11 chart No 1 Pa9oad static Momer s 6 14 Chart No 2 Center of Gravity Position Check 6 15 6 1 ...

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Page 113: ... rear weight with jack G Total Gr G Gr Front jack weight Gs Rear jack weight Go Total G4 G5 G Empty weight G3 G6 L Distance between jacking points S Static moment S G Xr b MAC Aerodynamic chod length 1 460 Xr Center of gravity arm measured from reference plane Xr Center of gravity position ks ks ks ks ks ks ks m ksm m m e o NtAc o J ...

Page 114: ...mination The aircrafr is weighed in horizontal position It is supported by two jacks placed under the first fuselage bulkhead and tail skid soar is determinated by levelling points Nib No 2 3 on the fuselage shell m ksm MAc MAC ks a 2 Center of oravitv arm measured from reference plane Gz Gs Xr 1 0 043 Static moment S G Xr Center of oravitv oosition xT 0 300 a xT 100 1 46 s G 0 300 b Xr 100 1 46 C...

Page 115: ...e weight and C G position of empty aircraft are stated including delivered oFional equipment in the Weighing certificate and in item 6 7 1 of this Flight Manual 3 lfthe user installed additionally optional or supplementary equipment the aircratl should be reweighed and the C G position of empty aircraft should be recounted 6 3 AIRCRAFTEQUIPMENT The following is a list of weights M arms X and stati...

Page 116: ...hting Map lamp Aircraft coating standerd Airspeed indicator ll M 337 AK v 500 z 42 2900 z 42 56 10 20 z 42 5630 z 142 5700 142 7271 81 z 142 7900 z 42 8110 z 42 8120 z 142 8130 z 142 8150 z 42 8160 z 142 8170 z 42 8261 z 142 8263 z 142 8266 z 142 8400 z 42 8623 z 142 8630 LUN 3524 20 z 142 8670 z 142 8970 oss 6 l z 142 8910 z 142 8920 z 142 8940 142 000 01 00 uN 1 106 157 750 25 00 0 759 1 634 0 4...

Page 117: ... gauge quadruPle VA meter Board clock Accelerometer 1 Converter installation Board battery LUN 1 107 LUN 1121 LUN t147 LUN 1202 LUN 1213 LUN 1221 LUN 1272 LUN 1341 2 LUN 1380 LUN 1401 LUN 1521 LUN 1639 LUN 2715 Aes 1o AM 10 PAG 1 FP z142 8520 PS 12 24 0 500 0 500 0 500 1 450 1 069 0 370 1 500 1 000 0 360 0 220 0 570 0 700 0 400 0 650 0 27E 19 000 0 386 0 386 0 386 0 386 0 386 0 386 0 386 0 386 0 3...

Page 118: ...ts M r arms X and static moments Su of maximum permissible payload for the aircraft with standard equipment Caution 1 Maximum permissible payload of the pilot s seats is given in category A U including parachutes in category N without parachutes including back rest cushions Payload Specification Weight MU ftS Arm x m Static moment Su kSm Pilots Pilot s seal posilion forward 200 00 0 846 169 200 mi...

Page 119: ...re is shown in item 6 7 Calculation example is shown in item 6 8 6 6 CENTER OF GRAVIry POSITION CI IECK For every flight the C G posilion musl be in specified limiis according to Seclion 2 item 2 5 Recommendation C G position checking procedure is shown in item 6 7 4 Calculation example is shown in item 6 8 4 6 7 WEIGHT PAYLOAD ANO CENTER OF GRAVIW POSITION CHECK PROCEDURE 6 7 1 Weioht and Static ...

Page 120: ...oil luggage determined in accodance with the chart No 1 item 6 9 6 7 3 Gross Weioht M I The gross weighl MD is given by a sum of empty weight M as outlined in ilem 6 7 and actual payload Mu as outlined in item 6 7 2 Mr M Mu 6 7 4 Center of Gravitv Position MAC For C G position determination use chart No 2 item 6 10 as follows 1 Nilark following values in chart No 2 C c position check A on vertical...

Page 121: ... CHECX EXAM LE v Conditions category Aerobatic A Crew 2 pilots 150 kg including parachutes Seats position fronl Fuel main tanks 120 wing tip tanks 0 without fuel Oil I I Luggage 0 must not be in aircraft in category A U 6 8 1 Weioht and Static Moment of Emptv Aircraft Following values are determined in accordance with Weighing Certiflcate with placard in the aircraft of by reweighing C Empty weigh...

Page 122: ...eterminalion in accordance with item 6 8 3 following points should be marked in the chart No 2 item 6 10 Point A is on the vertical scale and corresponds to the gross weight Mr 959 kg Point B is on the horizontal scale and corresponds to lhe total static moment s 582 kgm Point C is point of interseclion of parallele line that is led with course of tolal static moments Sv ftom point B with perpendi...

Page 123: ...SECTION 6 6 8 5 Conclusion point C falls within the area of permissible C G position and weight for the category Aerobatic The aircraft is airworthy 6 13 ...

Page 124: ...SECTION 6 6 9 CHART No 1 PAYLOAD STATIC MOMENTS 30 35 40 45 Stotic moment ro Sk ic moment 60 85 k 20 25 30 35 40 45 Pitois inctuding porochules or bock rest cushions Stotic momeni ksn 6 14 ...

Page 125: ...SECTION 6 6 10 CHART No 2 CENTER oF GRAVITY POSITION CHECK Center of Orovity pos 1 MAC a 3 tt o e 670 660 650 540 Totot stotic moment Su 6 15 ...

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Page 129: ...alidity 7 3 7 3 Supplement No 1 Tow of Sailplanes 7 4 7 4 Supplement No 4 Romanian placards translation 7 5 Supplement No 6 Concorde RG 24 20 Battery 7 6 Supplement No 10 Draining of Fuel Filter with New Cup Finish 7 7 Pilot s Cockpit 7 8 List of Pilot s Guides ...

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Page 131: ...n operating limitations and procedures which aDorv to the z 142 aircrafi derivered by the manufacrurer with conesponding bptionat equipmeni VALIDITY Operating fimitations and procedures given in Section 7 apply lo Z 142 aircrafi with corresponding optional equipment only 7 2 7 3 ...

Page 132: ...performing the tow of sailplanes the limitations must be observed in accordance with Section 2 in range for category NORMAL N 2 lf tow rope tensile strength exceeds 4900 N 500 kp breaking piece dimensioned to the tensile strength of 49800 N 500 kp must be located on the tow rope TOWING CABLE RELEASE Note This placard is located on the towing gear lever section4 1 Take otf according to item 4 8 2 C...

Page 133: ...rcraft is provided with Romanian placard The information contained herein supplements or supersedes the basic AFM information onty In sections listed herein Limitations procedures and information not contained in this Supplement are included in the basic CM approved AFM lssuE oF SUPPLEMENT No 4 oF THE z 142 A RCRAFT FLTGHT MANUAL rs AppRovED oN THE BASIS OF THE DOA APPROVAL No EASA 21J 1 t0 DATEOF...

Page 134: ... ZLIN AIRCRAFT a s Otrokovice Supplement No 4 LIST OF EFECTIVE PAGES Page No Date of issue 1 Apr 12 2010 2 Apr 12 2010 Apt 12 2O1O 4 Apr 12 2010 o Apr 12 2010 o Apt 12 2010 7 Apt 12 2010 I Apt 12 2010 o o zotc Apr 12 2010 ...

Page 135: ... eCnOen nCA ALTE LIMITAfiII DE SERVIGIU CARE TREBUIE SA FIE RESPECTATE l A FIJNCTIOi AREA AVIOiIULUt iN ACEASTA CLA SA SAU iI I CLASA DE ANTREIJATdENT O NORMAI A s NT ti ilDtcATE t fifANuALt L DEZBOR I nnerunrnAnt EcRoBAncE ADMtstBtLE t vrrEzE DE iNTRARE REcoMAtr DATE I 4S km ceas LUPING MIN 240 vtRA iLll trdMELtsANN fdtN 250 RETUBB ANilE IT MAX 150 RAT IVERSARE MIN 180 TONOU MIN 180 VRILA 110 LUP...

Page 136: ...f cockpit backward the suspensions are unlocked 2 Force the canopy upwards EXECUTAREA FIGI RILORACROtsATIC E CU BAGAJ E LA BORD ESTE INTERASA Note Placard No 4 is located in the luggage compartment BLOCAREACUPOLEI Note Placard No 5 is located at canopy arrestment lever locking in open position on the ground FOLOSITT NUMA CABLU CU ELEMENT DESTGUMNTA PENTRU4900N 500 kgf s 6 Note Placard No 6 is loca...

Page 137: ...ard No 3 is located al wing flap control lever and shows corresponding position of wing flaos 4 FUEL SHUTOFF VALVE POMPADEATVIORSARE Note Placard No 5 is located at fuel hand pump control 21 3 Note Placard No 4 is located at the fuel shutoff valve and gives a conespondlng position of the fuel shutotf valve and capacity of fuel tanks 5 Apt 12 2010 5of8 ...

Page 138: ...lean EXflNCOR TREGE Note Placard No 8 is located at engine extinguisher control PRESIUNlIAZOTULUI DIN LONJERON Note Placard No 9 is located at filling valve of pressure check of spar LIGHTENING SIGNALLING Caution When signalling fuel rest flight time cca 5 min change over the fuel shutoff valve on the second tank Note Placard No 10 is located at lightening signalling on the instrument panel 71 8 e...

Page 139: ...at ventilation and heating control in the cockpit TURATIA MAX ELICE imptrus coMPLET Note Placard No 12 is located at airscrew control COMPRESOR cUPLAT ilrltpll ls Note Placard No 13 is located at supercharger control Positions ON push OFF pull FRAI A PARCARE COMPLET TRAS Note Placard No 14 is located at parking brake control Positions oN pull OFF push 14 0 Aor 12 2010 7 of I ...

Page 140: ...seats at sectionalizing switches and show separale electrical circuils o DE TRACTIUNE Note Placard No 16 is located at towing gear lever in the cockpit SECTION 3 EMERGENCY PROCEDURE No changes SECTION 4 NORMAL PROCEDURES No changes SECTION 5 PERFORMANCES No changes SECTION 6 WEIGHT AND BALANCE No changes Aot 12 2010 8of8 ...

Page 141: ...tained herein supplements or supersedes the basic AFM informalion only in sections listed herein Limitations procedures and information not contained in this Supplement are included in the basic CAA aooroved AFM ISSUE OF SUPPLEMENT No 6 OF THE Z 142 AIRCRAFT FLIGHT MANUAL tS APPROVED ON THE BASIS OF THE DOA APPROVAL No EASA 21J 1 10 Serial No Registration Mark c423 n 7r r I I LU T t 6 I t ev t ulu...

Page 142: ...z 142 Flight Manual ZLIN AIRCRAFT a s Otrokovice Supplement No 6 LIST OF EFFECTIVE PAGES Page No Date of issue I 2010 05 17 2 2010 05 17 t 2010 05 17 4 2010 5 17 o ...

Page 143: ...source and consists from 12 lead acid cells connected in series The open circuit voltage ot the 12 cell battery is approximately 24 V Open circuit voltage is the voltage of the battery when it is not connected to a load Each cell of accumulator battery has positive and negative plates arranged alternately and insulated from each other by separators Each plate consists of a framework called the pla...

Page 144: ... SECTION 3 EMERGENCY PROCEDURES No change SECTION 4 NORMAL PROCEDURES No change SECTION 5 PERFORMANCE No change SECTION 6 WEIGHTS AND CENTRES OF GRAVITY 6 3 Aircraft Equioment Ord No Name Type standard draw No Weight M ko lb Arm X m in Static moment S kom 48 Baitery CONCORDE RG 24 20 19 000 1 775 2010 05 10 ...

Page 145: ...ust be contained in the Flight Manual of aircraftZ 142 in chapler 7 in case that there s installed fuel filter LUN 7620 8 or LUN 7620 01 8 in the aircraft in type with draining valve in the bottom part of cup APPROVED BY CAA DATE OF APPROVAL ft 11 t Y t 3 02 2006 26 1119e7 Approved by CAA Page 1 of3 ...

Page 146: ...Supplement No 10 LIST OF EFFEGTryE PAGES Paoe No Date of issue 1 1997 11 24 2 1997 11 26 3 1597 11 26 Page 2 of 3 Approved by CAA 26 1 1 1997 ...

Page 147: ...ischarge of fuel filter LUN 7620 8 or LUN 7620 01 8 with new cup finish provided with draining valve is possible to execute by pushing on protruding part of draining valve with consequent moving round a slight amount to left 8 T Fuel filter finish with draining valve in the bottom part of draining cup CHAPTER 5 PERFORMANCE Without change CHAPTER 6 WEIGFITS AIdD CEi TR ES OF GRAVITY POSITIOI S With...

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Page 149: ...ormation contained herein supplements or supersedes the baslc AFM information onlv In sections listed herein Limitations procedures and information not contained in this Suoplem ent are included in the basic CAA aooroved AFM ISSUE OF SUPPLEMENT PILOT S COCKPIT OF THEZ 142 AIRCMFT FLIGHT MANUAL IS APPROVED ON THE BASIS OF THE DOA APPROVAL No EASA 21J 110 1 3 01 010 DATE OF APPROVAL Aor 12 2010 10f ...

Page 150: ...z 142 Flight Manual ZLIN AIRCMFT a s Otrokovice LIST OF EFECTIVE PAGES Page No Date of issue 1 Apt 12 2010 z Apr 12 2010 3 Apr 12 m10 4 Apt 12 2010 c Apr 12 2010 o Apt 12 2010 2ofG Aot 12 2010 ...

Page 151: ...ZLIN AIRCRAFT a s Otrokovice z 142 Flight Manual SECTION 1 GENERAL 1 7 PtLOT S COCKPTT l f l il l o l r rffi Aor 12 2010 3of6 ...

Page 152: ...k indicator 17 Compressor control 48 Veftical speed indicator ll 18 Mixture control 49 Altimeter ll 19 Fuel shut off valve 50 Four pointer indicator 20 Ventilating and heating control 51 R P M indicator ll 21 Magneto switch 52 Accelerometer 22 Master switch fi V A meter 23 Starter pushbutton 54 Manifold orcssure indicator ll 24 Sectionalizing switches 55 Clock 25 Control of instrument lighting int...

Page 153: ...HTING CONVERTOR BATTERY GENERATOR DtAflttrt COMM GPS FLIGHT INSTRUMENTS XPDR PITOT HEATING 16 17 18 Note Placards No 15 are located on panel between pilot seats at sectionalizing switches and show seoarate electrical circuits COMMIXPDRIGPS 3A I 3 1sA 3 154 Note Placards No 16 are located on panel between pilot seats USE TOWING CABLE WITH 49OO N SAFETY PIN ONLY Note Placard No 17 is located on the ...

Page 154: ...ECTION 4 NORMAL PROCEDURES No changes SECTION 5 PERFORMANCES No changes SECTION 6 WEIGHT AND BALANCE 6 3 AIRCMFT EQUIPMENT Nots 20 uro No Name Type standard draw No Weight M ks Arm x m Static moment S ksm 49 50 5 t 52 53 54 VHF Transceiver Transponder Enconding Altimeter GPS Antenna COMM Transponder Antenna KY 96A GTX 328 AK 350 GPS MAP 496 ct 292 1 KA 61 1 320 1 100 0 181 0 400 0 220 0 090 0 280 ...

Page 155: ...R ZCF This List of Pilot s guides must be included in the Flight Manual of lhe z 142 airctaft in section 7 hereof airplane ISSUE OF SUPPLEMENT LIST OF PILOT S GUIDES OF THE Z 142 AIRCRAFT FLIGHT MANUAL IS APPROVED ON THE BASIS OF THE DOA APPROVAL No EASA 21J i i0 i 3 01 010 DATE OF APPROVAL Aor 12 2010 1of2 ...

Page 156: ...Page No Dale of issue 1 Apt 12 2010 Apt 12 2010 LIST OF PILOT S GUIDES 1 2 3 Pilot s Guide KY 96 A and KY 97A Pilot s Guide GTX 328 Owner s Manual GPS MA P 496 delivered seoarated VHF COMM Transceivers Mode S Transoonder Portable Aviation Receiver 4 10 164 2of2 Aor 12 2010 ...

Page 157: ...KY9 A Bendix King VHF Communications Trans ceivers This operat ions guide may be detached from the brochure and retained in the aircrafr ibr easr access 1o operational infbrmation on the KY 96A and KY 97A COMM transceiters o o ...

Page 158: ...in the Active tuequency display Liquid Crlsta l Display Frequenry seleation knobs Also used to charge coannetnumoerJ a At the outside limits of the band the dis playwill wrap around to the other end of the band going from 136MHz to I 18MHz 2 Press the transfer button to activate the new frequency The newly entered fre quenry in the STBY window flip flops with the frequencv in the USE window This n...

Page 159: ...eraring in the Chan nel mode proceed as foilows Rotate the Mllz frequincy knob left or right beyond 136 or I l8 MHz Dashes will appear in the STBI window This indicari s that the affected channel number u ill be skipped when operating in the Channel m00e 6 To exit the Program mode momentarily press the Channel ICFIAN button The irnit wiil atso automatically exit the Pro gram mode if approximately ...

Page 160: ...ure MomentarilY pressing the Transfer button will retuin the c6ntrol unit to the Specifications TS0 compliance Transmitter TSO C37c Class 3 or 4 Receiver TSO C38c Class A C Dimensions Height 1 35 inches 3 43 cm Width 6 312 inches t6 032 cm Depth 10 776 inches 27 37 cmJ Weight 2 8 lbs 1 27 Kg Temperature Ranqe 20 C to 55 e with short time operation at 70 C BEIII IXIKWA General Aviation Avionics Div...

Page 161: ...GTX 328 Made S Transponder o o pilot s guide ...

Page 162: ...BOUND BY THE TERMS AND CONDITIONS OF THE FOIIOWING SOFTWARE L CENSE AGREEMENT PLEASE READ THIS AGREEMENT CAREFULLY Garmin grants you a limited license to use the software embedded in this device the software in binary executable form in the normal operation of the product Title ownership rights and intellectual property rights in and to the Sofrware remain in Garmin You acknowledge that the Softwa...

Page 163: ...0R FRON4 DEFECTS IN THE PRODUCT Some states do not allow the exclusion oi incidental or consequential damages so the above iimitations may not apply to you Garmin retains the exciusive nght to repair or replace the unit or software or offer a full refund of the purchase price at its sole discretion SUCH REMEDY SFLALL BE YOUR SOLE AND EXCLUSIVE REMEDY FOR ANY BREACH OF ARMNTY To obtarn alranty sen ...

Page 164: ...l x ff Jlil fi il xitH iitjj Hili titilil Hi and 9 keys F5ffi r ff ff ti il ffi i 1 i t f 5 keys Altitude Trend lndicator hen the PRESSURE ALI page is displayed an arrow may be displayed to the nght of the altitude indicating that the altitude is increasrng or decreasing One of two sues of arrows may be displayed depending on the vertrcai speed rate The sensitivity of these arrows is set by an aut...

Page 165: ...The ALT mode maybe selected in aircraft not equipped rnth an optionai altitude encoder however rhe repiy signal wrli not include altitude information Any rime the function ON or ALI is selected the rransponder becomes an acrive part of the Air Traffic Control Radar Beacon Sysrem ATCRBS The rransponder also responds Lo intenogations from TCAS equipped aircraft m Code Selection Code selection is don...

Page 166: ...essing the VFR Key again restores the previous identificatron code lf the VFR Key is disabled dependent upon installation configuration a VFR Key Disabled message appears to indicate that no operation took place FUNC Changes the page shown on the right side of the display Display data includes Pressure Altrtude Fiight Time Altrtude 4onitor Count Up and Count Down timers Also displays Outside Air T...

Page 167: ...imer to zero To operate the Count Down timer 1 Press the FUN Key until COUNT DOWN is displayed 2 Press CRSR and use the 0 9 keys to set the initial time AII digits must be entered use the 0 Key to enter leading zeros 3 Press START STOP to begin count down 4 Press START STOP again to pause the timer 5 When the Count Down timer expires the COUNT DOWN banner is replaced with a flashing EXPIRED and th...

Page 168: ...this configuration alteration of Lhe FLT ID by the fiight crew is not possible Enterlng a Flight lD hlumber When configured for FLT ID P R UP ENTRY at insrallation rhe ftight cre i must enier theFlightlDbeloretheGTX32Brvilloperate AftertheflightcrewentersthecorrectFlight lD the aircraft identincation that is transmitted in response to MC radar interrogations ts properly correlated u ith the associ...

Page 169: ... FLT ID When FLT ID entry is complete the transponder begtns normal operation lf an enor is made while entering a FLr ID press the cLR Key ro back up ro any poinr including highlighting the OK field If an incorrect FLT ID is discovered after the unir hpoinc nnprqtinn turn the GTX 328 ofi Then turn it back on again and reenter the correct FLT ID Audio Alerts Setting options male female voice or ton...

Page 170: ...tional Inc 1200 East l5lst Street Olathe Kansas 66062 U S A Garmin Europe Ltd Unit 5 The Quadrangle Abbey Park lndustriai Estate Romsell SO51 gAQ U K Gamin Corporation No 68 Jangshu 2nd Road Shijr Taipei Count Taiwan mnrgannin com Part Number 190 00420 03 Rev A ...

Page 171: ...d monitoring units on some Zlin Z 42 seties aircrafl has revealed that the real intensity of aerobatic operation of some aircraft considerably exceeded the original expectations that had been used io determine the operational limitations As a result these aircraft exceeded the calculated total limit load spectra and limit design aerobatic load spectrum Further investigations determined the need to...

Page 172: ... Service Bulletin sB as applicable to type ComDliance 2 For aircraft havinq accumulated 190 FH Time or less in A U cateqorv 2 1 Belore further flight after the effective date of this directive modify the AFM to introduce prohibition of operations under the A category and to introduce the pre flight inspection of the upper wings bolts of the airframe wing attachment as instructed in the S 4 1 4 for...

Page 173: ...Service Bulletins Z42l55a tot 242 Z42M and Z42MU airqaft 2142154a for 2142 aictaft 2142C 31a tot 2142C aircraft and Z242Ll51a tot 2242L aucrcfl at original issue or later approved revisions ofthese documents Remarks 1 lf requested and appropriately substantiated the responsible EASA manager for the related product has the authority to accept Alternative Methods of Compliance AMOCS for this AD 2 Th...

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