Tecnam P2002-JF Flight Manual Download | Manualshive

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Section 7 – Airframe and Systems description

Electrical System

3

rd

Edition, Rev 0

10.

E

LECTRICAL

S

YSTEM

The aircraft's electrical system consists of a 12 Volt DC circuit controlled by the
Master Switch located on the instrument panel. Electrical power is provided by an
alternator and by a buffer battery. Generator light is located on the right side of
the instrument panel.

WARNING

If the Ignition is in the position L, R, or BOTH, an accidental
movement of the propeller may start the engine with possible dan-
ger for bystanders.

F

IG

.7-4.

E

LECTRICAL

S

YSTEM

S

CHEMATIC

10.1.

G

ENERATOR LIGHT

Generator light (red coloured) illuminates either:



for a generator failure.



for a failure of the regulator/rectifier, with consequent overvoltage sensor
shut off.

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Summary of Contents for P2002-JF

Page 1: ...s manual contains information to be furnished to the pilot as required by EASA in addition to further information supplied by the manufacturer This manual must always present on board the aircraft The aircraft is to be operated in compliance with information and limitations con tained herein This Aircraft Flight Manual is approved by European Aviation Safety Agency EASA Costruzioni Aeronautiche TE...

Page 2: ...Page 0 2 3rd Edition Rev 0 Aircraft Flight Manual INDEX SECTION 0 INDEX 1 RECORD OF REVISIONS 3 2 LIST OF EFFECTIVE PAGES 6 3 FOREWORD 7 4 SECTIONS LIST 8 ...

Page 3: ...the Edition code will change to the next number 2 for the second edi tion 3 for the third edition etc Additions deletions and revisions to existing text will be identified by a revision bar black line in the left hand margin of the page adjacent to the change When technical changes cause expansion or deletion of text which results in un changed text appearing on a different page a revision bar wil...

Page 4: ...ano M Landi M Oliva EASA approval no 10022116 3 8 thru10 Update emergency procedures G Paduano M Landi M Oliva EASA approval no 10022116 4 9 and 11 Update normal procedures G Paduano M Landi M Oliva EASA approval no 10022116 6 12 thru14 Update equipment list G Paduano M Landi M Oliva EASA approval no 10022116 9 3 Amend Supplement list G Paduano M Landi M Oliva EASA approval no 10022116 Supplement ...

Page 5: ...Page 0 5 3rd Edition Rev 0 Aircraft Flight Manual RECORD OF REVISIONS Rev Revised page Description of Revision Tecnam Approval EASA Approval or Under DOA Privileges DO OoA HDO ...

Page 6: ...2th 2010 2nd Edition Rev 2 December 12th 2010 2nd Edition Rev 3 February10th 2011 2nd Edition Rev 4 April 20th 2011 3rd Edition Rev 0 June 20th 2012 3rd Edition Rev 1 December 20th 2012 3rd Edition Rev 2 June 10th 2013 3rd Edition Rev 3 February 28th 2014 Section Pages Revision Section 0 Pages 1 4 and 6 Rev 3 Pages 2 3 5 7 8 Rev 0 Section 1 Pages 1 thru 14 Rev 0 Section 2 Page 5 11 Rev 2 Pages 1 t...

Page 7: ...al information and it contains definitions symbols explana tions acronyms and terminology used Before using the airplane you are recommended to read carefully this manual a deep knowledge of airplane features and limitations will allow you for operating the airplane safely For further information please contact COSTRUZIONI AERONAUTICHETECNAMs r l Via MAIORISE CAPUA CE ITALY 39 0 823 62 22 97 airwo...

Page 8: ... Section 3 EASA Approved Chapter Normal Procedures Section 4 EASA Approved Chapter Performances Section 5 EASA Approved Chapter partially Weight and Balance Section 6 a non approved Chapter Systems Section 7 a non approved Chapter Ground Handling Servicing and Maintenance Section 8 a non approved Chapter Supplements Section 9 EASA approved parts if any are reported on the supplements ...

Page 9: ...el Limits 5 3 1 Engine 5 3 2 Propeller 5 3 3 Fuel 6 3 4 Lubrication 6 3 5 Cooling 6 3 6 weights 6 3 7 Standard weights 6 3 8 Specific loadings 7 3 9 4 ACRONYMS AND TERMINOLOGY 8 General Airspeed Terminology And Symbols 8 4 1 Meteorological terminology 9 4 2 Engine Power terminology 9 4 3 Aircraft performance and flight planning terminology 10 4 4 Weight and balance terminology 11 4 5 5 UNIT CONVER...

Page 10: ...on Agency in accordance with CS VLA dated 14 November 2003 and the Type Certificate No A 006 27th May 2004 Category of Airworthiness Normal Noise Certification Basis EASA CS 36 1st edition dated 17th October 2003 with reference to ICAO Annex 16 3rd edition dated 1993 Vol 1 Chapter 10 WARNING CAUTION NOTE 1 2 Following definitions apply to warnings cautions and notes used in the Aircraft Flight Man...

Page 11: ...EW AND DIMENSIONS THREE VIEW 2 1 Fig 1 1 General views Dimensions shown refer to normal operating tire pressure Propeller ground clearance 320mm Propeller ground clearance with deflated front tire and nose wheel shock ab sorber compressed by 102mm Minimum ground steering radius 5 5m ...

Page 12: ...ensions Wingspan 8 6 m Length 6 61 m Overall height 2 43 m Wing Wing surface 11 5 m2 Taper Ratio 0 6 Dihedral 5 Aspect ratio 6 4 Main Landing Gear Track 1 85 m Wheelbase 1 62 m Tire Air Trac 5 00 5 Wheel hub and brakes Cleveland 199 102 Nose Landing Gear Tire Sava 4 00 6 Optionally Air Trac 5 00 5 ...

Page 13: ... 15 Austrian T C No TW 9 ACG dated 27th November 1998 Engine type 4 cylinder horizontally opposed twins with overall displacement of 1352 c c mixed cooling water cooled heads and air cooled cylinders twin carburetors integrated reduction gear with torque damper Maximum power at declared rpm 73 5kW 98 5hp 5800rpm max 5 69 0kW 92 5hp 5500rpm cont PROPELLER 3 3 Manufacturer Hoffmann Propeller Certifi...

Page 14: ... Overall usable fuel 99 litres Overall unusable fuel 1 litre LUBRICATION 3 5 Lubrication system Forced type with external reservoir Oil Lubricant specifications and grade are detailed into the Rotax Operators Manual and in its re lated documents Oil capacity Max 3 0 litres min 2 0 litres COOLING 3 6 Cooling system Mixed air and liquid pressurized closed circuit system Coolant liquid Coolant type a...

Page 15: ... 580 kg MTOW 600 kg MTOW 620 kg Wing Loading 50 4 kg m2 52 2 kg m2 53 9 kg m2 Power Loading 5 9 kg hp 6 1 kg hp 6 3 kg hp Reference is made to each MTOW 580 kg 600 kg if Supplement A11 Increased MTOW 600kg is applicable and 620 kg if Sup plement A12 Increased MTOW 620kg is applicable NOTE ...

Page 16: ...t allowed to make full or abrupt control movement VFE Maximum Flap Extended speed is the highest speed permissible with flaps extended VNO Maximum Structural Cruising Speed is the speed that should not be exceeded except in smooth air and only with caution VNE Never Exceed Speed is the speed limit that may not be exceeded at any time VS Stall Speed VS0 Stall Speed in landing configuration flaps an...

Page 17: ...level is the atmospheric pressure reported at the medium sea level through the standard air pressure altitude relationship starting from the airport QFE OAT Outside Air Temperature is the air static temperature expressed in degrees Celsius C TS Standard Temperature is 15 C at sea level pressure altitude and decreased by 2 C for each 1000 ft of altitude HP Pressure Altitude is the altitude read fro...

Page 18: ...f fuel that cannot be safely used in flight G is the acceleration of gravity TOR is the takeoff distance measured from actual start to wheel liftoff point TOD is total takeoff distance measured from start to 15m obstacle clearing GR is the distance measured during landing from actual touchdown to stop point LD is the distance measured during landing from 15m obstacle clearing to actual stop S R is...

Page 19: ...oment by the total weight of the aircraft Standard Empty Weight is the weight of the aircraft with engine flu ids and oil at operating levels Basic Empty Weight is the standard empty weight to which it is added the optional equipment weight Useful Load is the difference between maximum takeoff weight and the basic empty weight Maximum Takeoff Weight is the maximum weight approved to perform the ta...

Page 20: ...0508 Meters per second m s Knots kts 1 853 Kilometres hour km h Kilometres hour km h 0 5396 Knots kts PRESSURE Atmosphere atm 14 7 Pounds sq in psi Pounds sq in psi 0 068 Atmosphere atm LENGTH Kilometres km 0 5396 Nautical miles nm Nautical miles nm 1 853 Kilometres km Meters m 3 281 Feet ft Feet ft 0 3048 Meters m Centimetres cm 0 3937 Inches in Inches in 2 540 Centimetres cm VOLUME Litres l 0 26...

Page 21: ... 15 4 0 3 11 4 20 5 3 4 15 1 25 6 6 6 22 7 30 7 9 8 30 3 35 9 2 10 37 9 40 10 6 12 45 4 45 11 9 14 53 0 50 13 2 16 60 6 60 15 9 18 68 1 70 18 5 20 75 7 80 21 1 22 83 3 90 23 8 24 90 9 100 26 4 26 98 4 110 29 1 28 106 0 120 31 7 30 113 6 130 34 3 32 121 1 140 37 7 34 128 7 150 39 6 36 136 3 160 42 3 38 143 8 170 44 9 40 151 4 180 47 6 45 170 3 190 50 2 50 189 3 200 52 8 55 208 2 ...

Page 22: ...Page 1 14 Section 1 General 3rd Edition Rev 0 INTENTIONALLY LEFT BLANK ...

Page 23: ... Propeller 8 8 Maximum operating altitude 9 9 Ambient temperature 10 10 Powerplant instruments markings 11 11 Other instruments markings 12 12 Weights 13 13 Center of gravity range 13 14 Approved maneuvers 14 15 Maneuvers load factor limits 14 16 Flight crew 15 17 Maximum passenger seating 15 18 Kinds of Operation Equipment List 16 19 Fuel 17 20 Demonstrated Cross Wind Safe Operations 18 21 Limita...

Page 24: ... Section 2 Limitations INTRODUCTION 1 INTRODUCTION Section 2 includes operating limitations instrument markings and basic placards necessary for safe operation of P2002 JF aircraft its engines and standard systems and equipment ...

Page 25: ...exceed this speed in any operation VNO Maximum Structural Cruising Speed 110 106 Do not exceed this speed except in smooth air and only with caution VA Design Manoeuvring speed 96 94 Do not make full or abrupt control movement above this speed because under certain conditions the air craft may be overstressed by full control movement VFE Maximum flaps extended speed FULL 67 69 Do not exceed this s...

Page 26: ... Operating Range lower limit is VSO at specified maximum weight and upper limit is the maximum speed permissi ble with landing flaps extension Green arc 40 110 Normal Operating Range lower limit is VS1 at specified maximum weight and most for ward c g with flaps retracted and upper limit is maximum structural speed VNO Yellow arc 110 138 Manoeuvres must be conducted with caution and only in smooth...

Page 27: ...ditions the maxi mum propeller s rpm should be 2100 100 Temperatures Max CHT 135 C Min Max Oil 50 C 130 C Oil normal operating range approx 90 C 110 C Oil Pressure Minimum 0 8 Bar 12psi below 1400 rpm prop Normal 2 5 Bar 29 73psi above 1400 rpm prop Maximum 7 Bar 102 psi above 1400 rpm prop Engine starting allowable temperature range OAT Min 25 C OAT Max 50 C WARNING In event of cold starting oper...

Page 28: ...e 2 6 3rd Edition Rev 0 Section 2 Limitations LUBRICANT 5 LUBRICANT Use viscosity grade oil as specified in the following table WARNING Use of Aviation Grade Oil with or without additives is not per mitted ...

Page 29: ...Page 2 7 3rd Edition Rev 0 Section 2 Limitations COOLANT LIQUID 6 COOLANT LIQUID Coolant type and specifications are detailed into the Rotax Operator s Manual and in its related documents ...

Page 30: ...ge 2 8 3rd Edition Rev 0 Section 2 Limitations PROPELLER 7 PROPELLER MANUFACTURER Hoffmann Propeller GmbH MODEL HO17GHM A 174 177 C TYPE Wood twin blade fixed pitch DIAMETER 1740 mm no reduction permitted ...

Page 31: ... altitude is 14000 ft 4260 m MSL CAUTION At altitudes above 12500 ft 3810 m up to and including 14000 ft 4260 m flight must be limited to 30 minutes unless the required mini mum flight crew is provided with and uses supplemental oxygen for that part of the flight at those altitudes that is of more than 30 minutes dura tion ...

Page 32: ...3rd Edition Rev 0 Section 2 Limitations AMBIENT TEMPERATURE Page 2 10 9 AMBIENT TEMPERATURE Ambient temperature from 25 C to 50 C WARNING Flight in expected and or known icing conditions is forbidden ...

Page 33: ...perating YELLOW ARC Caution RED LINE Maximum limit Propeller rpm 580 2265 2265 2388 2388 Oil temp C 50 90 110 50 90 110 130 130 CHT C 0 135 135 Oil pressure bar 0 8 2 5 0 8 2 5 7 1 7 Fuel press psi 2 2 2 2 5 8 3 5 8 3 Fuel Q ty litres 0 2 1 In event of cold starting operation it is permitted a maximum oil pressure of 7 bar for a short period 2 0 indication shows the unusable fuel quantity 0 5 litr...

Page 34: ... Limitations OTHER INSTRUMENTS MARKINGS 11 OTHER INSTRUMENTS MARKINGS INSTRUMENT RED LINE Minimum limit GREEN ARC Normal operating YELLOW ARC Caution RED LINE Maximum limit Voltmeter 10 5 Volt 12 14 Volt Suction Gage 4 0 inHg 4 5 5 5 inHg ...

Page 35: ... aft from datum 20 kg 13 CENTER OF GRAVITY RANGE Datum Propeller support flange without spacer Levelling Seat track supporting trusses ref to sect 6 for the procedure Forward limit 1 693 m 26 0 MAC aft of datum for all weights Aft limit 1 782 m 32 5 MAC aft of datum for all weights WARNING The pilot is responsible for ensuring that the airplane is properly loaded Refer to Section 6 for appropriate...

Page 36: ...ved manoeuvre are as follows Manoeuvre Speed KIAS Lazy eight 96 Chandelle 110 Steep turn max 60 96 Stall Slow deceleration 1 kts s WARNING Acrobatic manoeuvres including spins and turns with angle of bank of more than 60 are not approved for such a category WARNING imit load factor could be exceeded by moving abruptly flight controls at their end run at a speed above VA Manoeuvring Speed 96 KIAS 1...

Page 37: ...HT CREW 3rd Edition Rev 0 Page 2 15 16 FLIGHT CREW Minimum crew for flight is one pilot seated on the left side 17 MAXIMUM PASSENGER SEATING With the exception of the pilot only one passenger is allowed on board of this aircraft ...

Page 38: ...by national operational requirements and also depends on the airspace classification and route to be flown Altimeter Airspeed Indicator Heading Indicator Fuel Gauges Oil Pressure Indicator Oil Temp Indicator Cylinder Heads Temp Indicator Outside Air Temp indicator Tachometer Chronometer First Aid Kit Hand held fire extinguisher Emergency hammer WARNING Flight in expected and or known icing conditi...

Page 39: ...s by acting on the fuel selector valve located into the cabin APPROVED FUEL MOGAS ASTM D4814 MOGAS EN 228 Super Super plus min RON 95 AVGAS 100 LL ASTM D910 CAUTION Prolonged use of Aviation Fuel Avgas 100LL results in greater wear of valve seats and greater combustion deposits inside cylinders due to higher lead content Make reference to Rotax Maintenance Manual which prescribes dedicated checks ...

Page 40: ...ONSTRATED CROSS WIND SAFE OPERATIONS 3rd Edition Rev 0 Page 2 18 20 DEMONSTRATED CROSS WIND SAFE OPERATIONS The aircraft controllability during take offs and landings has been demonstrated with a cross wind components of 22 kts ...

Page 41: ...Section 2 Limitations DEMONSTRATED CROSS WIND SAFE OPERATIONS 3rd Edition Rev 0 Page 2 19 INTENTIONALLY LEFT BLANK ...

Page 42: ...shboard a placard states the following THIS AIRPLANE IS CLASSIFIED AS A VERY LIGHT AIRPLANE AP PROVED FOR DAY VFR ONLY IN NON ICING CONDITIONS ALL AEROBATIC MANEUVERS INCLUDING INTENTIONAL SPIN ARE PROHIBITED SEE FLIGHT MANUAL FOR OTHER LIMITATIONS NO SMOKING Near baggage compartment a placard will state the following FASTEN TIE DOWN NET MAXIMUM WEIGHT 20 KG MAX PRESS 12 5 kg dm2 On the wing root ...

Page 43: ...Section 2 Limitations LIMITATION PLACARDS 3rd Edition Rev 0 Page 2 21 INTENTIONALLY LEFT BLANK ...

Page 44: ...Section 2 Limitations LIMITATION PLACARDS 3rd Edition Rev 0 Page 2 22 INTENTIONALLY LEFT BLANK ...

Page 45: ...ressure 8 4 3 2 Oil Pressure limits exceedance 8 4 3 3 High Oil Temperature 9 4 3 4 CHT limit exceedance 10 5 In Flight Engine Restart 11 6 Smoke And Fire 12 6 1 Engine fire on the ground 12 6 2 Engine Fire During Takeoff 12 6 3 Engine Fire In Flight 13 6 4 Cabin Fire Electrical smoke in cabin during flight 13 6 5 Electrical smoke fire in cabin on the ground 13 7 Landing Emergency 14 7 1 Forced La...

Page 46: ...Page 3 2 Section 3 Emergency procedures INDEX 3rd Edition Rev 0 INTENTIONALLY LEFT BLANK ...

Page 47: ...re hereby given a Bold faces which must be known by heart and executed in the correct and com plete sequence as soon as possible as the failure is detected and recognized These procedures characters are boxed and highlighted an example is shown below BEFORE ROTATION ABORT TAKE OFF 1 Throttle IDLE 2 Rudder Keep heading control 3 4 b Other procedures which should be well theoretically know and maste...

Page 48: ... POWER SYSTEM MALFUNCTION Generator Light Illuminates Generator light may illuminate for a faulty alternator or when voltage is above 16V in this case the over voltage sensor auto matically shuts down the alternator 1 Generator switch OFF 2 Master switch OFF 3 Generator switch ON 4 Master switch ON If the problem persists 5 Generator switch OFF 6 Non vital electric equipment Shed WARNING A fully c...

Page 49: ... trim control be inoperative act as follows 2 Breakers CHECK 3 Trim switch LH RH CHECK for correct position 4 Speed adjust to control aircraft without excessive stick force 5 Land aircraft as soon as possible Runaway In event of trim runaway act as follows 1 Trim disconnect switch OFF 2 Speed adjust to control aircraft without excessive stick force 3 Land aircraft as soon as possible 2 4 AIRPLANE ...

Page 50: ...on 3 Emergency procedures Engine securing 3 ENGINE SECURING Following procedure is applicable to shut down the engine in flight 1 Throttle Lever IDLE 2 Magnetos OFF 3 Fuel Selector OFF 4 Electrical fuel pump OFF 5 Generator switch OFF ...

Page 51: ... Flaps as needed WARNING Stall speed increases with bank angle and longitudinal load factor Acoustic stall warning will in any case provide a cor rect anticipated clue of incipient stall At or right before touch down 4 Throttle IDLE fully out 5 Magnetos OFF 6 Fuel selector valve OFF 7 Electric fuel pump OFF 8 Generator Master switches OFF WARNING A single engine aircraft take off should always be ...

Page 52: ...as possible monitoring fuel pressure If engine stops 1 5 Land as soon as possible applying forced landing procedure See Para 7 4 3 2 Oil Pressure limits exceedance If oil pressure exceeds upper limit 7 bar 1 Throttle Lever REDUCE engine power as practical 2 OIL PRESS and OIL TEMP CHECK within limits 3 Land as soon as practical If oil pressure is under the lower limit 0 8 bar 1 Throttle Lever REDUC...

Page 53: ...l temperature does not decrease 2 Airspeed INCREASE If oil temperature does not come back within limits the thermostatic valve if embodied regulating the oil flow to the heat exchangers could be damaged or an oil leakage can be present in the oil supply line 3 Land as soon as practical If engine roughness vibrations erratic behaviour or high CHT is detected 4 Land as soon as possible applying forc...

Page 54: ...e Failure 4 3 4 CHT limit exceedance If CHT is above 135 C 1 Throttle Lever REDUCE Minimum practical 2 Land as soon as practical If CHT continues to rise and engine shows roughness or power loss 3 Land as soon as possible applying forced landing procedure See Para 7 ...

Page 55: ...antity indicator CHECK 4 Fuel Selector change the fuel feeding tank 5 Magnetos BOTH 6 Magnetos START 7 Throttle lever SET as required CAUTION After engine restart if practical moderate propeller rpm and throttle increase to allow OIL and CHT temperatures for stabilizing in the green arcs If the fuel quantity in the tank which feeds the stopped engine is low select the opposite side fuel tank by me...

Page 56: ...rator Master Switches OFF 7 Parking Brake ENGAGED 8 Aircraft Evacuation carry out immediately 6 2 ENGINE FIRE DURING TAKEOFF BEFORE ROTATION ABORT TAKE OFF 1 Throttle Lever IDLE 2 Rudder Keep heading control 3 Brakes As required With aircraft under control 1 Fuel Selector OFF 2 Electrical fuel pump OFF 3 Magnetos OFF 4 Cabin Heat OFF 5 Generator Master Switches OFF 6 Parking Brake ENGAGED 7 Aircra...

Page 57: ...OKE IN CABIN DURING FLIGHT 1 Cabin heating OFF 2 Cabin vents OPEN 3 Canopy OPEN if necessary 4 Try to choke the fire Direct the fire extinguisher towards flame base If smoke persists 1 Generator Master switches OFF 2 Land as soon as possible and evacuate the aircraft CAUTION If the MASTER SWITCH is set to OFF consider that flaps ex tension and pitch trim operation would be not possible 6 5 ELECTRI...

Page 58: ...every 1000ft Above Ground Level it is possible to cover ca 2 NM ca 4 km 7 2 POWER ON FORCED LANDING 1 Airspeed 69 KIAS 2 Flaps UP 3 Locate the most suitable terrain for emergency landing plan to approach it upwind 4 Safety belts Tighten 5 Canopy locks CHECK LOCKED When certain to land right before touch down 6 Flaps as necessary 7 Fuel selector valve OFF 8 Electric fuel pump OFF 9 Magnetos OFF 10 ...

Page 59: ...2 Flaps Land 3 Land the aeroplane on the side of runway opposite to the defective tire to compensate the change in direction which is to be expected during final rolling 4 Touchdown with the GOOD TIRE FIRST and hold aircraft with the flat tire off the ground as long as possible by mean of aileron and rudder con trol As aircraft stops 5 Engine securing Perform see Para 3 6 Airplane evacuation Perfo...

Page 60: ...e IDLE full out position 2 Rudder full in the opposite direction of the spin 3 Stick centralize and hold neutral As the spin stops 4 Rudder SET NEUTRAL 5 Aeroplane attitude smoothly recover averting speeds in excess of VNE and maximum load factor n 3 8 6 Throttle Readjust to restore engine power WARNING Keep full rudder against rotation until spin has stopped One complete turn and recovery takes a...

Page 61: ... or hail and OAT less than 10 C Airbox carbu rettor heater is designed to help prevent carburettor ice less ef fectively functions as a de icing system 1 Carburettor heating ON 2 Immediately fly away from icing conditions changing altitude and di rection of flight out of clouds visible moisture precipitations 3 Controls surfaces continue to move to maintain their movability 4 Propeller speed incre...

Page 62: ...Page 3 18 3rd Edition Rev 0 Section 3 Emergency Procedures OTHER EMERGENCIES INTENTIONALLY LEFT BLANK ...

Page 63: ...nspections 3 3 1 Cabin Inspection 3 3 2 Aircraft walk around 3 4 Checklists 7 4 1 Before Engine Starting After Preflight Inspection 7 4 2 Engine Starting 8 4 3 Before Taxiing 8 4 4 Taxiing 9 4 5 Prior To Take Off 9 4 6 Take off And Climb 10 4 7 Cruise 11 4 8 Before Landing 11 4 9 Balked Landing 11 4 10 After Landing 12 4 11 Engine Shut Down 12 4 12 Postflight Check 12 ...

Page 64: ... Supplement A11 Increased MTOW 600 KG is applicable and 620 kg if Supplement A12 Increased MTOW 620 KG is applicable MTOW FLAPS 580kg 600 kg 620 kg Rotation Speed in take off VR T O 42 KIAS 42 KIAS 42 KIAS Best Angle of Climb Speed VX 0 56 KIAS 56 KIAS 56 KIAS Best Rate of Climb speed VY 0 66 KIAS 66 KIAS 66 KIAS Approach speed T O 66 KIAS 66 KIAS 66 KIAS Final Approach Speed FULL 51 KIAS 51 KIAS ...

Page 65: ...n I Master switch OFF J Baggage check first aid kit canopy hammer ELT fire extinguisher lug gage stowage and fastened with restraint net 3 2 AIRCRAFT WALK AROUND To perform the aircrafr walk around carry out the checklist according to the station shown in Figure 4 1 WARNING Visual inspection is defined as follows check for defects cracks detachments excessive play unsafe or improper installation a...

Page 66: ...if provided and check the Pitot tube and the stat ic ports mounted on left wing are unobstructed do not blow inside vents C Left side leading edge and wing skin visual inspection D Left aileron trim tab and hinges visual inspection check free of play fric tion Left tank vent check for obstructions E Left flap and hinges visual inspection F Left main landing gear check inflation tire condition alig...

Page 67: ...ndition R Propeller and spinner condition check for nicks cracks dents and other defects propeller should rotate freely Check fixing and lack of play be tween blades and hub S Open engine cowling 1 Check no foreign objects are present 2 Verify coolant level in the overflow bottle level must be between min and max mark Replenish if required 3 Only before the first flight of the day a Verify coolant...

Page 68: ...ior to long flights oil should be added so that the oil level reaches the max mark 6 Inspect fuel circuit for leakages 7 Check integrity of silent block suspensions 8 Check connection and integrity of air intake system visually inspect that ram air intake is unobstructed 9 Check that all parts are secured or safetied T Close engine cowling check for proper alignment of cam locks U Visual inspectio...

Page 69: ...sition 10 Flap control cycle fully extended and then set T O 11 Pitch Trim cycle fully up and down from both left and right controls check for trim disconnect switch operation 12 Pitch trim set neutral WARNING Pitch trim other than in neutral position would affect take off per formance and take off rotation execution at the correct VR IAS 13 Nav light Strobe light ON 14 Fuel quantity compare the f...

Page 70: ... the propeller Forward lower sector visibility is not possible from inside the cockpit 7 Magnetos BOTH 8 Magnetos START 9 Check oil pressure rise within 10 sec maximum cold value 7 bar 10 Generator switch ON 11 Ammeter check green 12 Voltmeter check more than 14V 13 Engine instruments Check 14 Choke OFF 15 Propeller rpm 1000 1200 rpm 16 Electric fuel pump OFF 17 Check fuel pressure min 2 2 psi 3 5...

Page 71: ...ectric Fuel pump ON 5 Fuel valve select the fullest tank 6 Fuel pressure check 7 Propeller speed advance throttle to 1640 rpm a Ignition magnetos test select LEFT check speed drop within 130 propeller rpm b Select BOTH check propeller speed 1640 rpm c Select RIGHT check speed drop within 130 propeller rpm d Maximum difference of speed between LEFT and RIGHT 50 rpm e Select BOTH check propeller spe...

Page 72: ...pass and gyro direction indicator alignment 4 Full throttle set check approximately 2100 100 propeller rpm 5 Engine instruments check 6 Rotation speed VR MTOW 580kg MTOW 600kg MTOW 620kg Rotation Speed VR 42 KIAS 42 KIAS 42 KIAS 7 Flaps retract above flap retraction speed 50 KIAS MTOW 580kg MTOW 600kg MTOW 620kg Best of Rate Climb Speed VY 66 KIAS 66 KIAS 66 KIAS 8 Electric fuel pump OFF 9 Fuel pr...

Page 73: ...p the fuel feeding from one tank to another 3 10 BEFORE LANDING 1 Electric fuel pump ON 2 Fuel valve select the fullest tank 3 Landing Light ON 4 On downwind leg abeam touch down point Flaps set T O 15 MTOW 580kg MTOW 600kg MTOW 620kg Approach Speed 66 KIAS 66 KIAS 66 KIAS 5 On final leg Flaps set Land 40 MTOW 580kg MTOW 600kg MTOW 620kg Final Approach Speed 51 KIAS 51 KIAS 51 KIAS 6 Carburettor h...

Page 74: ...pm for about one minute in order to reduce la tent heat 3 Avionic equipment OFF 4 Magnetos OFF keys extracted 5 Strobe light OFF 6 Master Generator switches OFF 7 Fuel selector valve OFF 3 14 POSTFLIGHT CHECK 1 Flight controls lock by mean of seat belts 2 Wheel chocks and wing mooring lines Set 3 Parking brake release 4 Canopy Close and lock 5 Protection hoods set over pitot tube stall warning sta...

Page 75: ...3 AIRSPEED INDICATOR SYSTEM CALIBRATION APPROVED DATA 4 4 ICAO STANDARD ATMOSPHERE 5 5 STALL SPEED APPROVED DATA 6 6 CROSSWIND 7 7 TAKE OFF PERFORMANCES APPROVED DATA 8 8 TAKE OFF RATE OF CLIMB 11 9 EN ROUTE RATE OF CLIMB 12 10 CRUISE PERFORMANCES 13 11 LANDING PERFORMANCES APPROVED DATA 15 12 BALKED LANDING CLIMB 18 13 NOISE DATA 19 ...

Page 76: ...n graphs and or in tables were determined using Flight Test Data under conditions prescribed by EASA CS VLA regulation aircraft and engine in good condition average piloting techniques Each graph or table was determined according to ICAO Standard Atmosphere ISA s l evaluations of the impact on performances were carried out by theo retical means for Airspeed External temperature Altitude Weight Run...

Page 77: ...CHARTS Performances data are presented in tabular or graphical form to illustrate the effect of different variables such as altitude temperature and weight Given information is sufficient to plan the mission with required precision and safety Additional information is provided for each table or graph ...

Page 78: ...Data Graph shows calibrated airspeed VCAS as a function of indicated airspeed VIAS FIG 5 1 CALIBRATED VS INDICATED AIRSPEED Example Given Find KIAS 75 KCAS 74 Indicated airspeed assumes 0 as an instrument error 20 40 60 80 100 120 140 40 60 80 100 120 140 CALIBRATED AIRSPEED KCAS INDICATED AIRSPEED KIAS F L A P L A N D F L A P U P F L A P T O 77 NOTE ...

Page 79: ...HERE 3rd Edition Rev 0 4 ICAO STANDARD ATMOSPHERE FIG 5 2 ICAO CHART Examples Scope Given Find Density Altitude A Pressure altitude 1600ft B Temperature 20 C C Density Altitude 2550ft ISA Temperature D Pressure altitude 1600ft E ISA Air Temperature 12 C ...

Page 80: ... ground effect WEIGHT BANK ANGLE STALL SPEED FLAPS 0 FLAPS T O FLAPS FULL kg deg KIAS KCAS KIAS KCAS KIAS KCAS 580 FWD C G 0 40 49 35 46 30 39 15 41 50 36 47 31 40 30 45 53 40 49 34 42 45 53 58 47 54 41 47 60 67 70 61 65 53 56 Altitude loss during conventional stall recovery as demonstrated during flight tests is approximately 150 ft with banking below 30 NOTE ...

Page 81: ...OSSWIND 3rd Edition Rev 0 6 CROSSWIND Maximum demonstrated crosswind is 22 Kts Example Given Find Wind direction with respect to aircraft longitudinal axis 30 Headwind 17 5 Kts Wind speed 20 Kts Crosswind 10 Kts FIG 5 3 CROSSWIND CHART ...

Page 82: ...1 365 465 330 1000 Ground Roll 142 187 242 306 214 At 50 ft AGL 233 309 402 513 355 2000 Ground Roll 156 206 266 337 231 At 50 ft AGL 257 340 443 565 383 3000 Ground Roll 172 226 292 371 249 At 50 ft AGL 282 375 488 624 414 4000 Ground Roll 189 249 322 409 269 At 50 ft AGL 311 414 539 690 447 5000 Ground Roll 208 275 355 452 290 At 50 ft AGL 343 457 595 763 483 6000 Ground Roll 229 303 392 499 313...

Page 83: ...Ground Roll 124 163 211 267 187 At 50 ft AGL 203 269 350 446 309 2000 Ground Roll 136 179 231 294 201 At 50 ft AGL 223 297 385 492 334 3000 Ground Roll 150 197 255 323 217 At 50 ft AGL 246 327 425 544 360 4000 Ground Roll 164 217 281 357 234 At 50 ft AGL 271 360 469 601 389 5000 Ground Roll 181 239 309 394 252 At 50 ft AGL 299 398 519 664 421 6000 Ground Roll 199 264 342 435 273 At 50 ft AGL 330 4...

Page 84: ...0 Ground Roll 97 127 164 208 146 At 50 ft AGL 159 210 273 348 242 2000 Ground Roll 106 140 181 229 157 At 50 ft AGL 174 231 301 384 261 3000 Ground Roll 117 154 199 252 169 At 50 ft AGL 192 255 332 424 281 4000 Ground Roll 128 169 219 278 183 At 50 ft AGL 212 281 366 469 304 5000 Ground Roll 141 187 242 307 197 At 50 ft AGL 233 310 405 519 328 6000 Ground Roll 156 206 267 339 213 At 50 ft AGL 257 ...

Page 85: ...03 8000 65 480 246 37 151 254 10000 65 292 62 143 327 105 12000 65 104 121 322 503 44 14000 65 82 303 501 679 193 550 S L 66 1339 1077 842 631 933 2000 66 1140 882 651 443 777 4000 66 941 687 460 256 621 6000 65 742 493 271 70 464 8000 65 545 300 81 116 308 10000 65 348 107 107 301 152 12000 65 151 85 296 486 4 14000 64 44 276 483 669 161 500 S L 66 1532 1246 991 760 1089 2000 66 1315 1033 782 556...

Page 86: ...7 4000 65 604 370 161 27 378 5000 65 416 186 19 203 229 6000 65 228 3 198 379 80 7000 65 42 179 377 555 69 550 S L 66 1463 1201 966 755 1057 1000 66 1264 1006 775 567 901 2000 66 1065 811 584 380 745 3000 65 866 617 395 194 588 4000 65 669 424 205 8 432 5000 65 472 231 17 177 276 6000 65 275 39 172 362 120 7000 64 80 152 359 545 37 500 S L 66 1656 1370 1115 884 1213 1000 66 1439 1157 906 680 1043 ...

Page 87: ...C 15 C ISA 15 C ISA 30 C 45 C RPM PWR KTAS F C PWR KTAS F C PWR KTAS F C lt hr lt hr lt hr 2355 112 109 30 2 93 106 25 1 78 101 21 2312 106 107 28 6 88 103 23 6 73 99 19 7 2265 100 105 27 82 100 22 2 68 96 18 4 2214 94 102 25 2 76 98 20 6 63 92 17 2157 87 99 23 4 70 94 19 58 88 15 5 2094 80 96 21 4 64 90 17 3 52 84 13 9 2023 72 92 19 4 57 86 15 5 46 77 12 3 Propeller RPM Fuel Consumption Weight 58...

Page 88: ... 580 kg Pressure Altitude 8000 ft ISA 30 C 15 C ISA 15 C ISA 30 C 45 C RPM PWR KTAS F C PWR KTAS F C PWR KTAS F C lt hr lt hr lt hr 2331 92 107 24 8 75 102 20 2 62 96 16 7 2287 87 105 23 4 71 99 19 58 93 15 6 2239 82 102 22 66 96 17 8 53 89 14 4 2185 76 99 20 5 61 93 16 4 49 84 13 2 Propeller RPM Fuel Consumption Weight 580 kg Pressure Altitude 10000 ft ISA 30 C 15 C ISA 15 C ISA 30 C 45 C RPM PWR...

Page 89: ...1000 Ground Roll 128 141 154 167 148 At 50 ft AGL 252 277 302 328 290 2000 Ground Roll 133 146 160 173 152 At 50 ft AGL 261 287 314 340 299 3000 Ground Roll 138 152 166 180 157 At 50 ft AGL 271 298 325 353 308 4000 Ground Roll 143 158 172 186 162 At 50 ft AGL 281 309 338 366 317 5000 Ground Roll 149 164 178 193 167 At 50 ft AGL 292 321 350 380 327 6000 Ground Roll 154 170 185 201 172 At 50 ft AGL ...

Page 90: ...5 127 138 150 133 At 50 ft AGL 226 249 272 295 261 2000 Ground Roll 120 132 144 156 137 At 50 ft AGL 235 258 282 306 269 3000 Ground Roll 124 137 149 161 141 At 50 ft AGL 243 268 293 317 277 4000 Ground Roll 129 142 155 168 145 At 50 ft AGL 253 278 304 329 285 5000 Ground Roll 134 147 160 174 150 At 50 ft AGL 262 289 315 342 294 6000 Ground Roll 139 153 167 181 154 At 50 ft AGL 272 300 327 355 303...

Page 91: ...5 105 114 124 110 At 50 ft AGL 187 206 225 244 216 2000 Ground Roll 99 109 119 129 113 At 50 ft AGL 194 214 233 253 222 3000 Ground Roll 102 113 123 133 117 At 50 ft AGL 201 221 242 262 229 4000 Ground Roll 106 117 128 138 120 At 50 ft AGL 209 230 251 272 236 5000 Ground Roll 110 122 133 144 124 At 50 ft AGL 217 239 260 282 243 6000 Ground Roll 115 126 138 149 128 At 50 ft AGL 225 248 270 293 251 ...

Page 92: ...0 448 319 204 101 295 6000 397 270 156 53 255 7000 347 220 107 5 215 550 S L 777 635 508 394 557 1000 723 582 457 344 515 2000 669 530 405 293 473 3000 615 477 354 242 431 4000 562 425 302 192 389 5000 508 372 251 142 347 6000 454 320 200 91 304 7000 401 268 149 41 262 500 S L 915 759 620 494 674 1000 856 701 563 438 627 2000 796 643 506 383 581 3000 737 585 449 327 534 4000 678 527 393 272 488 50...

Page 93: ...Page 5 19 Section 5 Performances NOISE DATA 3rd Edition Rev 0 13 NOISE DATA Noise level determined in accordance with ICAO Annex 16 4th Ed July 2005 Vol I Chapter 10 is 62 36 dB A ...

Page 94: ...Page 5 20 Section 5 Performances 3rd Edition Rev 0 INTENTIONALLY LEFT BLANK ...

Page 95: ... and BALANCE INDEX 1 INTRODUCTION 2 2 WEIGHING PROCEDURES 3 2 1 PREPARATION 3 2 2 LEVELLING 3 2 3 WEIGHING 3 2 4 DETERMINATION OF C G LOCATION 3 3 WEIGHING REPORT I 5 4 WEIGHING REPORT II 6 5 WEIGHT AND BALANCE 7 5 1 USE OF WEIGHT BALANCE CHART 7 6 LUGGAGE 10 7 EQUIPMENT LIST 11 ...

Page 96: ... aircraft Loading procedure information is also provided Aircraft must be operated in accordance with the limits con cerning the maximum take off weight and CG excursion as re ported in Flight Manual Section 2 Pilot is responsible for checking the weight and CG excursion are compliant with the related limits CG excursion and weight limits are reported in Section 2 Limitations NOTE ...

Page 97: ...under each wheel 2 2 LEVELLING Level the aircraft Reference for levelling remove a seat and then place a level between the two seat s fwd and aft supporting trusses Center bubble on level by deflating nose tire 2 3 WEIGHING Record weight shown on each scale Repeat weighing procedure three times Calculate empty weight 2 4 DETERMINATION OF C G LOCATION Drop a plumb bob tangent to the leading edge at...

Page 98: ...ght and Balance WEIGHING PROCEDURES 3rd Edition Rev 0 1337 from the propeller s flange without sapacer W2 WL WR D B W1 A 15 mm inboard from rib n 7 4 2 1 3 6 5 7 W2 A W1 B 100 D D D 1370 W1 W2 Reference line MAC 1370 Fig 6 1 ...

Page 99: ...ference line Kg meters Nose wheel weight W1 Plumb bob distance 1 LH wheel AL LH wheel weight WL Plumb bob distance 1 RH wheel AR RH wheel weight WR Average distance AL AR 2 A W2 WL WR Bob distance from nose wheel 1 B Empty weight We W1 W2 D W A W B We 2 1 m 100 370 1 D D Empty weight moment M D 1 337 We Kg m Maximum takeoff weight WT Kg Empty weight We Kg Maximum payload WT We Wu Kg 1 To determine...

Page 100: ...eference line Kg meters Nose wheel weight W1 Plumb bob distance 1 LH wheel AL LH wheel weight WL Plumb bob distance 1 RH wheel AR RH wheel weight WR Average distance AL AR 2 A W2 WL WR Bob distance from nose wheel 1 B Empty weight We W1 W2 D W A W B We 2 1 m 100 370 1 D D Empty weight moment M D 1 337 We Kg m Maximum takeoff weight WT Kg Empty weight We Kg Maximum payload WT We Wu Kg 1 To determin...

Page 101: ...l it intersects with the abscissa relative to fuel weight carried on board A horizontal line is then drawn through this point up to the graph limit value of 100 liters and a new parallel to the oblique lines is drawn until abscissa is intercepted relative to baggage loaded on board behind the seats Another horizontal line is drawn and it is thus possible to verify that the intersection of this seg...

Page 102: ... 0 20 40 60 140 100 80 120 180 160 200 50 0 10 20 3 2 5 C M A 500 1000 700 800 900 1100 2 6 C M A 650 0 90 50 30 70 100 MTOW 600kg 600 548 550 350 450 400 Fuel Lt 0 72 kg l Total weight Kg Moment empty Kg m Pilot Passenger Kg Luggage Kg MTOW 620kg MTOW 580kg Fig 6 2 Weight Balance Chart ...

Page 103: ...Page 6 9 Section 6 Weight and Balance WEIGHT AND BALANCE 3rd Edition Rev 0 Fig 6 3 C G RANGE CHART Fig 6 4 LOAD POSITION WITH RESPECT TO DATUM ...

Page 104: ...tment is designed for a maximum load of 20 kg Luggage size shall prevent excessive loading of utility shelf maximum pressure 12 5 kg dm2 Maximum Luggage size is 80x45x32 cm Luggage must be secured using a tie down net to prevent any luggage movement during maneuvers Fig 6 5 CABIN DIMENSIONS ...

Page 105: ...ne and accessories B Landing gear C Electrical system D Instruments E Avionics the following information describes each listing Part number to uniquely identify the item type Item description Serial number Weight in kilograms Distance in meters from datum Items marked with an asterisk are part of basic installation Equipment marked with X in the Inst column are those actually installed on board re...

Page 106: ...n gear spring leafs p n 92 8 300 1 5 700 1 94 B2 Main gear wheel rims Cleveland 40 78B 2 050 1 94 B3 Main gear tires Air Trac 5 00 5 AA1D4 2 580 1 94 B4 Disk brakes Cleveland 30 9 0 800 1 94 B5 Nose gear wheel rim p n 92 8 880 1 1 300 0 310 B6 Nose gear tire Sava 4 00 6 1 200 0 460 B7 Nose gear fairing p n 92 8 410 1 2 1 500 0 460 B8 Main gear fairing p n 92 8 420 1 2 1 500 1 930 B9 Nose gear shoc...

Page 107: ...7 001G or Speed Com Instruments 0203 0 10 1 35 D14 Fuel Pressure Ind UMA 4 360 007U 0 13 1 35 D15 Oil pressure indicator Sorlini SOR 50 0 10 1 35 D16 RPM indicator Sorlini SOR 52 0 10 1 35 D17 Oil temperature indicator Sorlini SOR 54 0 10 1 35 D18 CHT temperature indicator Sorlini SOR 53 0 10 1 35 D19 VoltmeterIndicator Sorlini SOR 51 0 10 1 35 D20 Attitude indicator RCA 26EK 12 1 10 1 35 D21 Dire...

Page 108: ...1 Fire Extinguisher H3Rs Halon13 07655 0 60 2 32 E22 Garmin GTN 650 COM NAV GPS 3 20 1 35 E23 Garmin GNC 255A COM NAV 1 37 1 35 E24 Garmin GTR 225A COM 1 07 1 35 E25 Garmin GTN 750 COM NAV GPS 4 65 1 35 E26 Garmin GTX 33 XPDR 1 60 2 74 E27 Garmin audio panel GMA 35 1 00 1 35 E28 King KN 63 DME unit 1 27 2 74 E29 King KDI 572 DME indicator 0 40 1 35 E30 KA 61 DME antenna 0 20 1 00 E31 Garmin GDU 62...

Page 109: ...ettor Heat 4 4 2 Cabin Heat 4 4 3 Throttle Friction Lock 4 5 SEATS AND SAFETY HARNESS 5 6 CANOPY 6 7 LUGGAGE COMPARTMENT 7 8 POWERPLANT 8 8 1 ENGINE 8 8 2 PROPELLER 8 9 FUEL SYSTEM 9 10 ELECTRICAL SYSTEM 10 10 1 Generator light 10 10 2 Voltmeter and Ammeter 11 10 3 Oil and cylinder heads temp Oil pressure 11 10 4 O A T Indicator 11 10 5 Stall Warning System 11 10 6 Avionics 11 10 7 External Power ...

Page 110: ...f the fuselage is made of a mixed structure a truss structure with special steel members for cabin survival cell and a light alloy semi monocoque structure for the cabin s bottom section The aft part of the fuselage is constructed of an aluminium alloy semi monocoque structure The engine is isolated from the cabin by a firewall the steel engine mount is attached to the cabin s truss structure in f...

Page 111: ...erons differentially Aileron trimming is carried out on ground through a small tab positioned on left aileron Flaps are extended via an electric servo actuator controlled by a switch on the in strument panel Flaps act in continuous mode the indicator displays the two posi tions relative to takeoff 15 and landing 40 A breaker positioned on the right side of the instrument panel protects the electri...

Page 112: ...panel carbs receive maximum hot air During normal operation the knob is OFF 4 2 CABIN HEAT The cabin heat control knob is positioned on the lower left side of the instrument panel when knob is pulled fully outward cabin receives maximum hot air Vents are located by the rudder pedals and above instrument panel If necessary outside fresh air can be circulated inside cabin by opening the vents on the...

Page 113: ... HARNESS Aircraft features four point fitting safety belts with waist and shoulder harnesses adjustable via sliding metal buckle Seats are built with light alloy tube structure and synthetic material cushioning A lever located on the right lower side of each seat allows for seat adjustment ac cording to pilot size ...

Page 114: ...ng tracks located on fuselage sides canopy is made out of composite material Latching system uses a central lever located overhead and two additional levers positioned on canopy s sides The canopy could be opened both from in and outside In correspondence with each lock is present a placard indicating the emergency release procedure ...

Page 115: ...GAGE COMPARTMENT The Luggage compartment is located behind the pilots seats Luggage shall be uniformly distributed on utility shelf and its weight shall not exceed 20kg Tie down luggage using adjustable tie down net WARNING Before loading luggage check aircraft s weight and CG location see Sect 6 ...

Page 116: ...rizontally opposed 4 cylinder mixed air and water cooled twin electronic ignition forced lubrication Maximum rating 98 6hp 73 5kW 5800 rpm min 2388 rpm min prop Gear reduction ratio 2 4286 1 Max oil consumption Max 0 1 litres hour 8 2 PROPELLER Manufacturer Hoffmann Propeller Model HO17GHM A 174 177C N of blades 2 Diameter 1740 mm no reduction permitted Type wood fixed pitch ...

Page 117: ...ossible to select the following fuel feeding LEFT means a left tank feeding RIGHT means a right tank feeding and a third OFF position which could not be accidentally operated A strainer cup with a drainage valve Gascolator is located beneath the cabin just behind the firewall Fuel level indicators for each tank are located on instrument panel Fuel feed is through an engine driven mechanical pump a...

Page 118: ...an alternator and by a buffer battery Generator light is located on the right side of the instrument panel WARNING If the Ignition is in the position L R or BOTH an accidental movement of the propeller may start the engine with possible dan ger for bystanders FIG 7 4 ELECTRICAL SYSTEM SCHEMATIC 10 1 GENERATOR LIGHT Generator light red coloured illuminates either for a generator failure for a failu...

Page 119: ...or located on the right wing leading edge connected to a warning horn located near the in strument panel 10 6 AVIONICS The central part of the instrument panel holds room for avionics equipment The manufacturer of each individual system furnishes features for each system 10 7 EXTERNAL POWER SUPPLY On the right side of the tail cone an external power is present Using this device it is possible to f...

Page 120: ...SSURE SYSTEMS The airspeed indicator system for the aircraft is shown below Below the left wing s leading edge are positioned in a single group 1 both the Pitot tube 3 total pressure intake and a series of static ports 6 Two flexible hoses 5 feed the airspeed indicator 4 on the instrument panel FIG 7 5 AIRSPEED INDICATOR SYSTEM ...

Page 121: ...in land ing gear through disk brakes the same circuit acts as parking brake via an intercept valve 2 To activate brakes it is sufficient to verify that brake shut off valve 2 positioned on tunnel between pilots is OFF then activate brake lever 1 as necessary To activate parking brake pull brake lever 1 and set brake shut off valve 2 to ON 1 2 FIG 7 6 BRAKE SYSTEM ...

Page 122: ...Page 7 14 Section 7 Airframe and Systems description Brakes 3rd Edition Rev 0 INTENTIONALLY LEFT BLANK ...

Page 123: ...G SERVICE INDEX 1 Introduction 2 2 Aircraft Inspection Intervals 3 3 Aircraft Alterations or Repairs 4 4 Ground Handling 5 4 1 Towing 5 4 2 Parking and Tie Down 5 4 3 Jacking 5 4 4 Leveling 5 4 5 Road Transport 5 5 Cleaning And Care 6 6 Engine Cowling Check 7 6 1 Upper cowling 7 6 2 Lower Cowling 7 ...

Page 124: ...ound han dling and routine care and servicing It also identifies certain inspection and maintenance requirements which must be followed if the aircraft is to retain its new plane performance and dependability It is recommended to follow a planned schedule of lubrication and preventive maintenance based on climatic and flying conditions encountered locally ...

Page 125: ...ON INTERVALS Inspection intervals occur at 100 hours or at 1 year whichever occurs first and in accordance with special inspection schedules which are added to regularly scheduled inspections Correct maintenance procedures are described in the air craft s Maintenance Manual or in the engine s Maintenance Manual ...

Page 126: ... HANDLING SERVICE AIRCRAFT CHANGES OR REPAIRS 3rd Edition Rev 0 3 AIRCRAFT CHANGES OR REPAIRS Aircraft changes or repairs must be performed in accordance with Aircraft Maintenance Manual and only by TECNAM authorized personnel ...

Page 127: ...age to mov ing surfaces JACKING 4 3 Given the light empty weight of the aircraft lifting one of the main wheels can easily be accomplished even without the use of hydraulic jacks For an accepta ble procedure please refer to the Maintenance Manual LEVELING 4 4 Aircraft leveling may become necessary to check wing incidence dihedral or the exact location of CG Longitudinal leveling verification is ob...

Page 128: ...h use a soft cloth for drying The plastic windshield and windows should never be dusted when dry use lukewarm soapy water and dry using chamois only It is possible to use special glass detergents but in any case never use products such as gasoline alcohol acetone or other solvents To clean cabin interior seats upholstery and carpet it is generally recommend ed to use foam type detergents ...

Page 129: ... reference pins VIII Secure latches by applying light pressure check for proper assembly and fasten Cam locks WARNING Butterfly Cam locks are locked when tabs are horizontal and open when tabs are vertical Verify tab is below latch upon closing LOWER COWLING 5 2 I After disassembling upper cowling move the propeller to a horizontal position II Using a standard screwdriver press and rotate 90 the t...

Page 130: ...Page 8 8 Section 8 Aircraft Care and Maintenance ENGINE COWLING CHECK 3rd Edition Rev 0 INTENTIONALLY LEFT BLANK ...

Page 131: ...Page 9 1 Section 9 Supplements 3rd Edition Rev 0 SECTION 9 SUPPLEMENTS INDEX 1 Introduction 2 2 Supplements lists 3 ...

Page 132: ...Page 9 2 Section 9 Supplements SUPPLEMENTS LIST 3rd Edition Rev 0 1 INTRODUCTION This Section concerns the supplemental manuals of additional or optional instrumenta tion equipping the P2002 JF ...

Page 133: ...nstruments panel A4 Differential brake system A5 Central throttle control system A6 AFM supplement for CIS countries operators A7 Garmin G500 Avionics Display System A8 VFR Night equipment A9 VFR Night equipment Analogical version A10 AFMS for Malaysia Reg istered Aircraft A11 INCREASED MTOW 600 kg A12 INCREASED MTOW 620 kg 1 20 12 2012 A13 Variable Pitch Propeller A14 Rudder and throttle con trol...

Page 134: ...Page 9 4 Section 9 Supplements SUPPLEMENTS LIST 3rd Edition Rev 0 INTENTIONALLY LEFT BLANK ...

Page 135: ... SUPPLEMENT NO A01 GARMIN GNS 430 GPS VHF COMM NAV Record of Revisions Rev Revised page Description of Revision Tecnam Approval EASA Approval or Under DOA Privileges DO OoA HDO 0 List of Effective Pages Page Revision Page Revision A01 1 Rev 0 A01 4 Rev 0 A01 2 Rev 0 A01 5 Rev 0 A01 3 Rev 0 A01 6 Rev 0 ...

Page 136: ...ion 9 Supplements Supplement no A01 GARMIN GNS 430 GPS VHF COMM NAV 3rd Edition Rev 0 INDEX INTRODUCTION 3 GENERAL 3 LIMITATIONS 4 EMERGENCY PROCEDURES 5 NORMAL OPERATION 5 PERFORMANCE 5 WEIGHT AND BALANCE 5 SYSTEMS 5 ...

Page 137: ... receiver for GPS a VOR LOC antenna a VOR ILS receiver a VHF Comm antenna and a VHF Comm tranceiver 3 The main function of the VHF Comm is to allow communication with the control tower 4 The VOR ILS function is to receive and demodulate VOR and LOC sig nals 5 The GPS section is dedicated to signal acquisition from the GPS satellite system and to furnish real time information with respect to positi...

Page 138: ... GPS 2 00 COMM 1 22 VOR LOC 1 25 The software version of the main subsystem is displayed by the GNS 430 immediately after start up for 5 seconds Remaining subsystems software versions may be verified in sub page 2 of the AUX Group display for SOFTWARE DATA BASE VER 4 The following default settings must be keyed in in the SETUP 1 menu of the GNS430 receiver before any other operation DIS SPD nm kt ...

Page 139: ... pilot must use the VLOC receiver or an alternative navigation system 4 In emergency flight conditions pressing the COM flip flop knob for 2 se conds will automatically tune in the 121 500MHz emergency frequency NORMAL OPERATION 1 DETAIL FOR NORMAL OPERATION Normal operation is described in the Pilot s guide and Reference P N 190 00140 00 rev F dated July 2000 or later versions 2 GARMIN GNS 430 DI...

Page 140: ...Page A01 6 Section 9 Supplements Supplement no A01 GARMIN GNS 430 GPS VHF COMM NAV 3rd Edition Rev 0 INTENTIONALLY LEFT BLANK ...

Page 141: ... SUPPLEMENT NO A02 GARMIN GNS 530 GPS VHF COMM NAV Record of Revisions Rev Revised page Description of Revision Tecnam Approval EASA Approval or Under DOA Privileges DO OoA HDO 0 List of Effective Pages Page Revision Page Revision A02 1 Rev 0 A02 4 Rev 0 A02 2 Rev 0 A02 5 Rev 0 A02 3 Rev 0 A02 6 Rev 0 ...

Page 142: ...ion 9 Supplements Supplement no A02 GARMIN GNS 530 GPS VHF COMM NAV 3rd Edition Rev 0 INDEX INTRODUCTION 3 GENERAL 3 LIMITATIONS 4 EMERGENCY PROCEDURES 5 NORMAL OPERATION 5 PERFORMANCE 5 WEIGHT AND BALANCE 5 SYSTEMS 5 ...

Page 143: ... receiver for GPS a VOR LOC antenna a VOR ILS receiver a VHF Comm antenna and a VHF Comm tranceiver 3 The main function of the VHF Comm is to allow communication with the control tower 4 The VOR ILS function is to receive and demodulate VOR and LOC sig nals 5 The GPS section is dedicated to signal acquisition from the GPS satellite system and to furnish real time information with respect to positi...

Page 144: ...0 GPS 2 00 COMM 1 22 VOR LOC 1 25 The software version of the main subsystem is displayed by the GNS 530 immediately after start up for 5 seconds Remaining subsystems software versions may be verified in sub page 2 of the AUX Group display for SOFTWARE DATA BASE VER 4 The following default settings must be keyed in in the SETUP 1 menu of the GNS530 receiver before any other operation DIS SPD nm kt...

Page 145: ...ust use the VLOC receiver or an alternative navigation system 4 In emergency flight conditions pressing the COM flip flop knob for 2 se conds will automatically tune in the 121 500MHz emergency frequency NORMAL OPERATION 1 DETAIL FOR NORMAL OPERATION Normal operation is described in Garmin GNS 530 Pilot s guide P N 190 00181 00 rev A dated April 2000 or later versions 2 GARMIN GNS 430 DISPLAY Data...

Page 146: ...Page A02 6 Section 9 Supplements Supplement no A02 GARMIN GNS 530 GPS VHF COMM NAV 3rd Edition Rev 0 INTENTIONALLY LEFT BLANK ...

Page 147: ...dition Rev 0 SUPPLEMENT NO A03 NEW ANALOGICAL INSTRUMENT PANEL Record of Revisions Rev Revised page Description of Revision Tecnam Approval EASA Approval or Under DOA Privileges DO OoA HDO 0 List of Effective Pages Page Revision Page Revision A03 1 Rev 0 A03 3 Rev 0 A03 2 Rev 0 A03 4 Rev 0 ...

Page 148: ...ion 9 Supplements Supplement no A03 New Analogical Instrument Panel 3rd Edition Rev 0 INDEX INTRODUCTION 3 GENERAL 3 LIMITATIONS 3 EMERGENCY PROCEDURES 3 NORMAL OPERATION 3 PERFORMANCE 3 WEIGHT AND BALANCE 3 SYSTEMS 4 ...

Page 149: ... section contains supplementary information for safe and efficient operation of the aircraft if equipped with the new analogical instruments panel GENERAL No variations LIMITATIONS No variations EMERGENCY PROCEDURES No variations NORMAL OPERATION No variations PERFORMANCE No variations WEIGHT AND BALANCE No variations ...

Page 150: ...h a modular concept to im prove the instruments visibility The new instruments panel is divided into three main parts The left part with the flight instruments central part with the avionic instruments and the right part with the engine instruments The following picture shown the new analogical instruments panel OBS Figure A03 1 NEW ANALOGICAL INSTRUMENTS PANEL ...

Page 151: ...dition Rev 0 SUPPLEMENT NO A04 DIFFERENTIAL BRAKE SYSTEM Record of Revisions Rev Revised page Description of Revision Tecnam Approval EASA Approval or Under DOA Privileges DO OoA HDO 0 List of Effective Pages Page Revision Page Revision A04 1 Rev 0 A04 3 Rev 0 A04 2 Rev 0 A04 4 Rev 0 ...

Page 152: ...ection 9 Supplements Supplement no A04 Differential Brake System 3rd Edition Rev 0 INDEX INTRODUCTION 3 GENERAL 3 LIMITATIONS 3 EMERGENCY PROCEDURES 3 NORMAL OPERATION 3 PERFORMANCE 3 WEIGHT AND BALANCE 3 SYSTEMS 4 ...

Page 153: ...s section contains supplementary information for safe and efficient operation of the aircraft if equipped with the differential brake system GENERAL No variations LIMITATIONS No variations EMERGENCY PROCEDURES No variations NORMAL OPERATION No variations PERFORMANCE No variations WEIGHT AND BALANCE No variations ...

Page 154: ...voir 4 on the co pilot s brake pedals 1 The reservoir is directly connected to the brake master cylinders 3 Two flexible hoses connect the master cylin ders on the co pilot s brake pedals to the master cylinders on the pilot s brake pedals The parking brake valve 6 is mounted on the floor of the fuselage be low the seats and it s activated by lever 2 Each main wheel has a brake disc 7 C C C C FWD ...

Page 155: ...dition Rev 0 SUPPLEMENT NO A05 CENTRAL THROTTLE CONTROL SYSTEM Record of Revisions Rev Revised page Description of Revision Tecnam Approval EASA Approval or Under DOA Privileges DO OoA HDO 0 List of Effective Pages Page Revision Page Revision A05 1 Rev 0 A05 3 Rev 0 A05 2 Rev 0 A05 4 Rev 0 ...

Page 156: ...ion 9 Supplements Supplement no A05 Central Throttle Control System 3rd Edition Rev 0 INDEX INTRODUCTION 3 GENERAL 3 LIMITATIONS 3 EMERGENCY PROCEDURES 3 NORMAL OPERATION 3 PERFORMANCE 3 WEIGHT AND BALANCE 3 SYSTEMS 4 ...

Page 157: ...s section contains supplementary information for safe and efficient operation of the aircraft if equipped with the central throttle control system GENERAL No variations LIMITATIONS No variations EMERGENCY PROCEDURES No variations NORMAL OPERATION No variations PERFORMANCE No variations WEIGHT AND BALANCE No variations ...

Page 158: ... A05 3 shows the central throttle control system The engine throttle lever is located on the left site and the choke lever is located on the right site The levers friction is located on the lateral right site of the central throttle control system T H R O T T C H O K E ON OFF Figure A05 3 Central throttle control system ...

Page 159: ...ription of Revision Tecnam Approval EASA Approval or Under DOA Privileges DO OoA HDO 0 List of Effective Pages Page Revision Page Revision A06 1 Rev 0 A06 12 Rev 0 A06 2 Rev 0 A06 13 Rev 0 A06 3 Rev 0 A06 14 Rev 0 A06 4 Rev 0 A06 15 Rev 0 A06 5 Rev 0 A06 16 Rev 0 A06 6 Rev 0 A06 17 Rev 0 A06 7 Rev 0 A06 18 Rev 0 A06 8 Rev 0 A06 19 Rev 0 A06 9 Rev 0 A06 20 Rev 0 A06 10 Rev 0 A06 21 Rev 0 A06 11 Rev...

Page 160: ... 4 Operation from Unpaved Runways 4 Over Water Flights 4 Single Pilot Operations 4 Kind of Operations 4 EMERGENCY PROCEDURES 5 Engine Failures 5 Smoke and Fire 5 Recovery from Unintentional Spin 6 Other Emergencies 6 NORMAL OPERATION 8 Pre Flight Inspections 8 Checklist 11 Cold Weather Operations 14 PERFORMANCE 15 Stall Speed Approved data 15 Take Off Performances Approved data 16 Cruise 18 Landin...

Page 161: ...ht Manual Section 9 if the airplane is certified to the CIS configuration The in formation contained herein complements the basic information in the EASA Approved Aircraft Flight Manual For limitations procedures and performance information not contained in this supplement refer to the EASA Approved Air craft Flight Manual GENERAL AIRSPEED TERMINOLOGY AND SYMBOLS VLOF Lift off speed is the speed a...

Page 162: ...d by soil strength of 6 kg per sq Cen timetre σ 6kg cm2 OVER WATER FLIGHTS Extended over water flights are allowed within the limitations prescribed by CIS operational regulations distance from the coast shall not exceed gliding distance with engine failed SINGLE PILOT OPERATIONS In case of single pilot operations the right crew seat may not be occupied by a passenger without removal of control st...

Page 163: ... from the LEFT tank change to RIGHT or v v If the engine continues to run irregularly 7 Ignition key check both 8 Land as soon as possible Glide ratio is 12 8 landing gear up therefore with 1000ft eleva tion it is possible to cover 4km 2 nautical miles in zero wind conditions The lost of altitude by turning of 180 with bank angle of 30 is about 200ft on the VY SMOKE AND FIRE ENGINE FIRE WHILE PARK...

Page 164: ... maximum load factor n 3 8 OTHER EMERGENCIES ELECTRIC POWER SYSTEM MALFUNCTION Causes for malfunctions are hard to establish but in any case problems of this nature must be dealt with immediately The following may occur Generator Light Illuminates Generator light may illuminate for a faulty alternator or when voltage is above 16V in this case the over voltage sensor automatically shuts down the al...

Page 165: ...k 2 Trim switch Lh Rh check for correct position 3 Trim disconnect ON check 4 Speed adjust to control aircraft without excessive stick force 5 Land aircraft as soon as possible Runway If trim position indicator reads displacement without pilot s action on trim con trol follow procedure below 1 Trim power switch OFF 2 Speed adjust speed to control aircraft without excessive stick force 3 Land aircr...

Page 166: ...wed by an internal inspection as below detailed EXTERNAL INSPECTION To carry out the external inspection it will be necessary to follow the checklist below with the station order outlined in fig A06 1 WARNING Visual inspection is defined as follows check for defects cracks detachments excessive play unsafe or improper installation as well as for general condition For control surfaces visual inspec...

Page 167: ...H Vertical tail and rudder visual inspection I Right main landing gear check inflation 23 psi 1 6 bar tire condition alignment fuselage skin condition L Right flap and hinges visual inspection M Right aileron visual inspection Right side tank vent check for obstruc tions N Right leading edge and wing skin visual inspection O Right fuel filler cap check visually for desired fuel level then secure f...

Page 168: ...fuel circuit for losses V Check integrity of silent block suspensions VI Check connection and integrity of air intake system visually inspect that ram air intake is unobstructed VII Check that all parts are secured or safetied T Close engine cowling U Visual inspection of the Landing Light V Remove tow bar and chocks Avoid blowing inside Pitot tube and inside airspeed indicator sys tem s static ve...

Page 169: ... positions IX Trim control operate from both left and right controls the trim between its extreme positions checking the trim position indicator X Nav light Strobe light ON XI Landing light ON check XII Landing light OFF XIII Fuel quantity compare the fuel levels read by the fuel quantity indicators with the quantity present into the tanks see Pre flight inspection Ex ternal inspection XIV Flight ...

Page 170: ...l quantity indicators VI Flaps T O 15 VII Stick free and trim set at zero VIII Seat belts fastened and canopy closed and locked CRUISE Flights in the CIS airspace are allowed only along the routes with continuous ATC monitoring using RBS mode in the VHF covering zones I Reach cruising altitude II Set power and engine rpm s for cruise III Check engine instruments Oil temperature 90 110 C Temperatur...

Page 171: ...Edition Rev 0 BEFORE LANDING I Electric fuel pump ON II On downwind leg speed 68 KIAS for both MTOW Flaps T O 15 III On downwind base speed 65 KIAS for both MTOW Flaps T O 15 IV On final leg speed 63 KIAS for both MTOW Flaps Land 40 V Establish descent VI Optimal touchdown speed 51 KIAS for both MTOW ...

Page 172: ...ies Operators 3rd Edition Rev 0 COLD WEATHER OPERATIONS If the aircraft is operated in cold weather conditions from 25ºC till 5ºC it is necessary to perform following procedures Heat the cabin to 25ºC to avoid windshield frost in flight Heat the engines with external source to 20º C ...

Page 173: ... KIAS KCAS FLAP UP 40 49 45 53 53 58 67 70 FLAP TO 35 46 40 49 47 54 61 65 FLAP FULL 30 39 34 42 41 47 53 56 CONDITIONS Weight 600 kg Throttle idle No ground effect Lateral Bank 0 30 45 60 KIAS KCAS KIAS KCAS KIAS KCAS KIAS KCAS FLAP UP 41 50 46 53 54 59 68 70 FLAP TO 36 46 41 50 48 55 62 65 FLAP FULL 31 40 35 43 41 47 53 56 Altitude loss during conventional stall recovery as demonstrated during t...

Page 174: ... each 10Kts of ahead wind In crease distances by 20 for each 10 Kts of tailwind 2 Measurement distance for short grass less than 2 inches must be increased of 10 Measurement distance for high grass more than 2 inches must be increased of 15 3 A rising runway with a gradient of 1 causes an acceleration decreasing of the same intensity and consequently the takeoff run increases by5 NOTE Example Give...

Page 175: ...on Rev 0 CLIMB RATE IN TAKE OFF CONFIGURATION APPROVED DATA CONDITIONS 580 kg MTOW 600 kg MTOW Flaps 15 15 Engine Full throttle Full throttle Vobs 45 KIAS 46 KIAS Climb rate at maximum takeoff weight 580 600kg in demonstrated ISA s l conditions is 850 ft min for 580 kg MTOW and 800 ft min for 600 kg MTOW ...

Page 176: ...perators 3rd Edition Rev 0 CRUISE CONDITIONS ISA Wind zero MTOW For both MOTW Fig A06 3 CRUISE 90 95 100 105 110 115 120 0 1000 2000 3000 4000 5000 6000 7000 8000 9000 10000 11000 12000 TAS KTS DensityAltitude ft 75 70 65 60 55 50 45 2224 RPM 2059 RPM 1976 RPM 1894 RPM 2182 RPM 2141 RPM ...

Page 177: ... idle Slope 0 Wind zero Distance over the obstacle of 15 m OAT ISA 20 C Hp ft Total Distance m Ground Run m 0 235 88 2000 241 94 4000 248 99 6000 256 105 OAT ISA 10 C Hp ft Total Distance m Ground Run m 0 239 92 2000 246 97 4000 253 103 6000 261 109 OAT ISA 0 C Hp ft Total Distance m Ground Run m 0 243 95 2000 250 101 4000 258 107 6000 266 113 OAT ISA 10 C Hp ft Total Distance m Ground Run m 0 247...

Page 178: ... 10 Kts of headwind In crease distances by 20 for each 10 Kts of tailwind 2 For dry and paved runway operation increase ground run by 10 3 If it becomes necessary to land without flap extension flap mal function increase approach speed by 10 Kts increase by 40 distance pertaining to flap setting at 40 and increase Vobs to 56 KIAS for 580 kg MTOW and to 57 KIAS for 600 kg MTOW 4 Vobs speed over obs...

Page 179: ...Page A06 21 Section 9 Supplements Supplement no A06 AFM Supplement for CIS Countries Operators 3rd Edition Rev 0 WEIGHT AND BALANCE No variations SYSTEMS No variations ...

Page 180: ...Page A06 22 Section 9 Supplements Supplement no A06 AFM Supplement for CIS Countries Operators 3rd Edition Rev 0 INTENTIONALLY LEFT BLANK ...

Page 181: ... Revisions Rev Revised page Description of Revision Tecnam Approval EASA Approval or Under DOA Privileges DO OoA HDO 0 List of Effective Pages Page Revision Page Revision A07 1 Rev 0 A07 9 Rev 0 A07 2 Rev 0 A07 10 Rev 0 A07 3 Rev 0 A07 11 Rev 0 A07 4 Rev 0 A07 12 Rev 0 A07 5 Rev 0 A07 13 Rev 0 A07 6 Rev 0 A07 14 Rev 0 A07 7 Rev 0 A07 15 Rev 0 A07 8 Rev 0 A07 16 Rev 0 ...

Page 182: ...s Display System 3rd Edition Rev 0 INDEX INTRODUCTION 3 GENERAL 4 LIMITATIONS 5 Airspeed Limitations 5 Airspeed Indicator Markings 6 EMERGENCY PROCEDURES 7 In Flight Engine Restart 8 G500 System Failures 8 NORMAL OPERATION 9 PERFORMANCE 10 WEIGHT AND BALANCE 11 SYSTEMS 12 ...

Page 183: ... to operate in a safe and efficient manner the aircraft when equipped with Garmin G500 Avionics Display System Design Change MOD 2002 041 CAUTION Garmin G500 Pilot s Guide P N 190 01102 02 last issue must be carried on board the airplane at all times Garmin G500 Cockpit Reference Guide P N 190 01102 03 last issue provides a synthetic explana tion of system operation NOTE ...

Page 184: ...t displays In normal operating mode the Primary Flight Display PFD presents graphical flight instrumentation attitude heading airspeed altitude vertical speed re placing the traditional flight instrument cluster The Multi Function Display MFD normally displays a full color moving map with navigation information An analogue stand by airspeed indicator and a stand by altimeter provide the pi lot wit...

Page 185: ... Never exceed speed 141 138 Never exceed this speed in any operation VNO Maximum Structural Cruising Speed 112 108 Never exceed this speed unless in smooth air and then only with caution VA Manoeuvring speed 98 96 Do not make full or ab rupt control movements above this speed as this may cause stress in excess of limit load factor VFE Maximum flap extended speed LDG 68 70 Do not exceed these speed...

Page 186: ...ing tape Refer to Garmin G500 Pilot s Guide P N 190 01102 02 last is sue for airspeed indicator description MARKING KIAS SIGNIFICANCE White band 31 68 Positive Flap Operating Range lower limit is VSO at maximum weight 600 kg and upper limit is the maximum speed permissible with landing flaps ex tension Green band 41 112 Normal Operating Range lower limit is VS1 at maximum weight 600 kg and most fo...

Page 187: ...a very high degree of functional in tegrity However the pilot must recognize that providing monitoring and or self test capability for all conceivable system failures is not practical Although unlikely it may be possible for erroneous op eration to occur without a fault indication shown by the G500 It is thus the responsibility of the pilot to detect such an occurrence by means of cross checking w...

Page 188: ...RU function fails a large red X is typically displayed on the display field associated with the failed data In most of cases the red X annunciation is accompanied by an Alert Message Refer to G500 Pilot s Guide P N 190 01102 02 last issue Chapter 6 Annunciations and Alerts list LOSS OF AIRSPEED INFORMATION If the display system is not receiving airspeed input from the Air Data Comput er a red X is...

Page 189: ...02 last issue must be carried onboard the airplane at all times WARNING For safety reasons G500 operational procedures must be learned on the ground WARNING To reduce the risk of unsafe operation carefully review and un derstand all aspects of the G500 Pilot s Guide Thoroughly prac tice basic operation prior to actual use During flight operations carefully compare indications from the G500 to all ...

Page 190: ...e A07 10 Section 9 Supplements Supplement no A07 GARMIN G500 Avionics Display System 3rd Edition Rev 0 PERFORMANCE Garmin G500 Avionics Display System installation does not affect the aircraft performance ...

Page 191: ...tegrated EQUIPMENT LIST A C S N DATE REF DESCRIPTION P N INST WEIGHT kg DATUM m Garmin GDU 620 Display 2 9 1 35 Garmin GRS 77 AHRS 1 27 2 77 Garmin GDC 74A ADC 0 72 0 81 Garmin GMU 44 magnetometer 0 16 4 91 Garmin GTP 59 temperature probe 0 2 2 08 Stand by airspeed indicator Mid Continent P N 25020 0179 0 27 1 35 Stand by altimeter Mid Continent P N 15035 1102 0 36 1 35 Bank angle indicator option...

Page 192: ...ems and also provides an HSI for navigation The GRS 77 is an Attitude and Heading Reference System AHRS unit that provides aircraft attitude information to the G500 display The unit contains ad vanced tilt sensors accelerometers and rate sensors In addition the GRS 77 in terfaces with both the GDC 74A Air Data Computer and the GMU 44 magne tometer The GRS 77 also utilizes GPS data forwarded from t...

Page 193: ...een added to provide the pilot with main flight information also in case of G500 failure The above mentioned instruments are pneumatic and they don t need electrical supply CAUTION The G500 PFD and MFD displays use a lens coated with a spe cial anti reflective coating that is very sensitive to skin oils wax es and abrasive cleaners CLEANERS CONTAINING AMMONIA WILL HARM THE ANTI REFLECTIVE COATING ...

Page 194: ...hows the electrical system schematic The Garmin G500 units are connected to the avionic bus through dedicated cir cuit breakers When the G500 is installed also the design change 2002 026 Optional External Generator is applied to provide the necessary amount of current to the new electrical loads A dedicated breaker panel is therefore installed ...

Page 195: ...Page A07 15 Section 9 Supplements Supplement no A07 GARMIN G500 Avionics Display System 3rd Edition Rev 0 INSTRUMENTS PANEL The instrument panel typical layout is shown on the following figure ...

Page 196: ...Page A07 16 Section 9 Supplements Supplement no A07 GARMIN G500 Avionics Display System 3rd Edition Rev 0 INTENTIONALLY LEFT BLANK ...

Page 197: ...visions Rev Revised page Description of Revision Tecnam Approval EASA Approval or Under DOA Privileges DO OoA HDO 0 List of Effective Pages Page Revision Page Revision A08 1 Rev 0 A08 8 Rev 0 A08 2 Rev 0 A08 9 Rev 0 A08 3 Rev 0 A08 10 Rev 0 A08 4 Rev 0 A08 11 Rev 0 A08 5 Rev 0 A08 12 Rev 0 A08 6 Rev 0 A08 13 Rev 0 A08 7 Rev 0 A08 14 Rev 0 ...

Page 198: ...f Operation 4 Airspeed Indicator Markings 5 EMERGENCY PROCEDURES 6 Generator Warning Light 6 Instruments Lights Failure 6 Static Port Failure 6 Unintentional Flight Into Icing Conditions 7 NORMAL OPERATION 8 Pre Flight Inspections 8 PERFORMANCE 9 WEIGHT AND BALANCE 9 SYSTEMS 10 VFR Night Equipment 10 Electrical Systemand Instruments Panel 12 ...

Page 199: ...ange MOD 2002 041 Garmin G500 Avionics Dis play System Additionally following equipment must be installed Garmin GNS 430 or 530 GPS VHF COMM NAV or Garmin SL30 VHF COMM NAV Garmin SL40 VHF COMM NAV Garmin GTX328 Mode S Transponder GENERAL In order to allow flight in VFR Night conditions the airplane is fitted with addi tional equipment namely an airspeed indicating system connected to a heated Pit...

Page 200: ...R Night flight in VFR Night is permitted only if the prescribed addi tional equipment is installed and operational 2nd VHF COMM equipment Pitot heating system Instruments lights Landing light Strobe lights ELT Transponder Torch Dome light Flight into expected and or known icing conditions is prohibited Additional equipments may be asked to fulfill national or specific requirements It s a responsib...

Page 201: ...GS The following limitation placard is placed in clear pilot s view on the instru ments panel THIS AEROPLANE IS CLASSIFIED AS A VERY LIGHT AEROPLANE APPROVED FOR DAY AND NIGHT VFR IN NON ICING CONDITIONS ALL AEROBATIC MANOEUVRES IN CLUDING INTENTIONAL SPINNING ARE PROHIBITED SEE FLIGHT MANUAL FOR OTH ER LIMITATIONS ...

Page 202: ...ts mode switch Set to EMER 4 Radio calls Reduce at the strictly necessary 5 Five minutes before landing Pitot heat OFF 6 Limit the landing light use The battery is able to supply the electrical system for at least 30 minutes to complete flight in emergency conditions with normal flight electric loads including operation of flap and trim INSTRUMENTS LIGHTS FAILURE In event of failures affecting the...

Page 203: ...N 3 Get away from icing conditions by changing altitude or direction of flight in order to reach an area with warmer external temperature 4 Controls surfaces continue to move to maintain their movability 5 Increase RPM to avoid ice formation on propeller blades 6 Cabin heat ON WARNING In event of ice build up in correspondence of wing leading edges stall speed increases ...

Page 204: ...h TEST Instrument lights TEST Dome light TEST Pitot heating system Make sure plug is removed set to ON CHECK advisory light ON After about 5 seconds turn OFF Pitot heating system Check Pitot if warm Alternate static port CHECK closed Strobe lights mode switch NORM Strobe lights switch ON check wing and vertical fin strobe lights ON Strobe lights mode switch EMER check wing strobe lights OFF check ...

Page 205: ...erformance WEIGHT AND BALANCE For weight and balance make reference to Section 6 of this Manual addition ally the equipment list is so integrated EQUIPMENT LIST A C S N DATE REF DESCRIPTION P N INST WEIGHT kg DATUM m Instruments lights two items each 0 1 1 55 Alternate static port 0 03 1 55 Pitot heated 0 3 1 73 Dome light 0 1 2 70 Landing light AS GE 4509 0 5 0 2 ...

Page 206: ...e pilot with an additional mean to illuminate the cabin and the instruments panel TORCH An emergency torch is provided in the cabin ANNUNCIATOR PANEL Instruments panel features an annunciator panel consisting of three lights namely ALT warning light it indicates that the alternator is OFF or not work ing properly PITOT HEAT advisory light it indicates that Pitot heating system is ON FUEL PUMP advi...

Page 207: ...ight operations PITOT HEATING SYSTEM The airplane airspeed indicating system is connected to a heated Pitot tube heat ing system is activated by means of a switch which activates the advisory light PITOT HEAT on the annunciator panel The advisory light informs the pilot that the system is activated but it does not indicate whether it works properly ALTERNATE STATIC PORT The airplane is fitted with...

Page 208: ...Section 9 Supplements Supplement no A08 VFR Night Equipment 3rd Edition Rev 0 ELECTRICAL SYSTEMAND INSTRUMENTS PANEL The drawings below show the electrical system schematic and the instruments panel typical layout ...

Page 209: ...Page A08 13 Section 9 Supplements Supplement no A08 VFR Night Equipment 3rd Edition Rev 0 ...

Page 210: ...Page A08 14 Section 9 Supplements Supplement no A08 VFR Night Equipment 3rd Edition Rev 0 INTENTIONALLY LEFT BLANK ...

Page 211: ...ERSION Record of Revisions Rev Revised page Description of Revision Tecnam Approval EASA Approval or Under DOA Privileges DO OoA HDO 0 List of Effective Pages Page Revision Page Revision A09 1 Rev 0 A09 8 Rev 0 A09 2 Rev 0 A09 9 Rev 0 A09 3 Rev 0 A09 10 Rev 0 A09 4 Rev 0 A09 11 Rev 0 A09 5 Rev 0 A09 12 Rev 0 A09 6 Rev 0 A09 13 Rev 0 A09 7 Rev 0 A09 14 Rev 0 ...

Page 212: ...4 Kinds of Operation 4 Airspeed Indicator Markings 5 EMERGENCY PROCEDURES 6 Generator Warning Light 6 Instruments Lights Failure 6 Static Port Failure 6 Unintentional Flight Into Icing Conditions 7 NORMAL OPERATION 8 Pre Flight Inspections 8 PERFORMANCE 9 WEIGHT AND BALANCE 9 SYSTEMS 10 VFR Night Equipment 10 Electrical System and Instruments Panel 12 ...

Page 213: ... or 530 GPS VHF COMM NAV or Garmin SL30 VHF COMM NAV Garmin SL40 VHF COMM NAV Garmin GTX328 or GTX 320 or GTX 327 or GTX 330 Mode S Tran sponder ELT AK 450 or ARTEX ME406 ADF King KR87 ADF and a second radio are necessary if the aircraft is Italian registered In other cases please refer to local operating regula tion GENERAL In order to allow flight in VFR Night conditions the airplane is fitted w...

Page 214: ...ons in VFR Night flight in VFR Night is permitted only if the prescribed addi tional equipment is installed and operational 2nd VHF COMM equipment Pitot heating system Instruments lights Landing light Strobe lights ELT Transponder Torch Dome light Flight into expected and or known icing conditions is prohibited Additional equipments may be asked to fulfill national or specific requirements It s a ...

Page 215: ...OR MARKINGS The following limitation placard is placed in clear pilot s view on the instru ments panel THIS AEROPLANE IS CLASSIFIED AS A VERY LIGHT AEROPLANE APPROVED FOR DAY AND NIGHT VFR IN NON ICING CONDITIONS ALL AEROBATIC MANOEUVRES IN CLUDING INTENTIONAL SPINNING ARE PROHIBITED SEE FLIGHT MANUAL FOR OTH ER LIMITATIONS ...

Page 216: ...calls Reduce at the strictly necessary 4 Five minutes before landing Pitot heat OFF 5 Limit the landing light use Turn the light ON just 5 minutes before landing The battery is able to supply the electrical system for at least 35 minutes to complete flight in emergency conditions with normal flight electric loads including operation of flap and trim INSTRUMENTS LIGHTS FAILURE In event of failures ...

Page 217: ...tot heat ON 3 Get away from icing conditions by changing altitude or direction of flight in order to reach an area with warmer external temperature 4 Controls surfaces continue to move to maintain their movability 5 Increase RPM to avoid ice formation on propeller blades 6 Cabin heat ON WARNING In event of ice build up in correspondence of wing leading edges stall speed increases ...

Page 218: ...functional checks CABIN INSPECTION MASTER SWITCH ON Torch TEST Day Night Switch Set as required by lighting condition Instrument lights TEST Dome light TEST Pitot heating system Make sure plug is removed set to ON CHECK advisory light ON After about 5 seconds turn OFF Pitot heating system Check Pitot if warm Alternate static port CHECK closed Strobe lights switch ON check wing strobe lights ON Str...

Page 219: ...ircraft performance WEIGHT AND BALANCE For weight and balance make reference to Section 6 of this Manual additional ly the equipment list is so integrated EQUIPMENT LIST A C S N DATE REF DESCRIPTION P N INST WEIGHT kg DATUM m Instruments lights two items each 0 1 1 55 Alternate static port 0 03 1 55 Pitot heated 0 3 1 73 Dome light 0 1 2 70 Landing light AS GE 4509 0 5 0 2 ...

Page 220: ... additional mean to illuminate the cabin and the instruments panel TORCH An emergency torch is provided in the cabin ANNUNCIATOR PANEL Instruments panel features an annunciator panel consisting of three lights name ly ALT warning light it indicates that the alternator is OFF or not work ing properly PITOT HEAT advisory light it indicates that Pitot heating system is ON FUEL PUMP advisory light it ...

Page 221: ...ion Rev 0 The advisory light informs the pilot that the system is activated but it does not indicate whether it works properly ALTERNATE STATIC PORT The airplane is fitted with an alternate static port located in the cabin in corre spondence of the pedestal RH side It is activated by means of a lever ...

Page 222: ...ments Supplement no A09 VFR Night Equipment Analogical Version 3rd Edition Rev 0 ELECTRICAL SYSTEM AND INSTRUMENTS PANEL The drawings below show the electrical system schematic and the instruments panel typical layout N20 GEN IG L ...

Page 223: ...Page A09 13 Section 9 Supplements Supplement no A09 VFR Night Equipment Analogical Version 3rd Edition Rev 0 ...

Page 224: ...Page A09 14 Section 9 Supplements Supplement no A09 VFR Night Equipment Analogical Version 3rd Edition Rev 0 INTENTIONALLY LEFT BLANK ...

Page 225: ... SUPPLEMENT NO A10 AFMS FOR MALAYSIA REGISTERED AIRCRAFT Record of Revisions Rev Revised page Description of Revision Tecnam Approval EASA Approval or Under DOA Privileges DO OoA HDO 0 List of Effective Pages Page Revision Page Revision A10 1 Rev 0 A10 4 Rev 0 A10 2 Rev 0 A10 5 Rev 0 A10 3 Rev 0 A10 6 Rev 0 ...

Page 226: ...S for Malaysia Registered Aircraft 3rd Edition Rev 0 INDEX INTRODUCTION 3 GENERAL 3 LIMITATIONS 3 EMERGENCY PROCEDURES 3 NORMAL OPERATION 3 PERFORMANCE 3 WEIGHT AND BALANCE 3 SYSTEMS 4 Instrument Panel 4 Parking Brake Placard 5 Throttle Friction Placard 5 ...

Page 227: ...AFMS applicable to Malaysia registered airplanes provides information about instruments panel configuration parking brake and throttle friction plac ards GENERAL No variations LIMITATIONS No variations EMERGENCY PROCEDURES No variations NORMAL OPERATION No variations PERFORMANCE No variations WEIGHT AND BALANCE No variations ...

Page 228: ...ion Rev 0 SYSTEMS INSTRUMENT PANEL The instruments panel is divided into three main parts The left part with the flight instruments central part with the avionic instruments and the right part with the engine instruments The following picture show the analogical instruments panel configuration OBS ...

Page 229: ...MS for Malaysia Registered Aircraft 3rd Edition Rev 0 PARKING BRAKE PLACARD The parching brake placard is located on central tunnel between the two seats THROTTLE FRICTION PLACARD The throttle friction placard is located on central lower instrument panel ...

Page 230: ...Page A10 6 Section 9 Supplements Supplement no A10 AFMS for Malaysia Registered Aircraft 3rd Edition Rev 0 INTENTIONALLY LEFT BLANK ...

Page 231: ... MTOW 600KG Record of Revisions Rev Revised page Description of Revision Tecnam Approval EASA Approval or Under DOA Privileges DO OoA HDO 0 List of Effective Pages Page Revision Cover Pages A11 1 thru 11 Rev 0 Section 2 W2 3 Rev 0 W2 4 Rev 0 W2 13 Rev 0 W2 14 Rev 0 W2 19 Rev 0 W2 20 Rev 0 Section 5 W5 1 thru 20 Rev 0 ...

Page 232: ...ed MTOW 600kg 3rd Edition Rev 0 INDEX INTRODUCTION 3 SECTION 1 GENERAL 4 SECTION 2 LIMITATIONS 5 SECTION 3 EMERGENCY PROCEDURES 7 SECTION 4 NORMAL OPERATION 8 SECTION 5 PERFORMANCE 9 SECTION 6 WEIGHT AND BALANCE 11 SECTION 7 AIRFRAME AND SYSTEM DESCRIPTION 11 ...

Page 233: ...or Design Change MOD 2002 029 has been embodied on the airplane The information contained herein supplements or supersedes the basic Aircraft Flight Manual detailed instructions are provided to allow the owner for replacing the basic AFM pages containing information amended as per the Increased MTOW Design Change in subject It is the owner s responsibility to replace the mentioned pages in accorda...

Page 234: ...Page A11 4 Section 9 Supplements Supplement no A11 Increased MTOW 600kg 3rd Edition Rev 0 SECTION 1 GENERAL See basic AFM Section 1 Supplement A11 pages replacement instructions ...

Page 235: ... 0 SECTION 2 LIMITATIONS Apply following pages replacement procedure Supplement A11 Limitations page Basic AFM Limitations page W2 3 REPLACES 2 3 W2 4 REPLACES 2 4 W2 13 REPLACES 2 13 W2 14 REPLACES 2 14 W2 19 REPLACES 2 19 W2 20 REPLACES 2 20 Supplement A11 pages replacement instructions ...

Page 236: ...Page A11 6 Section 9 Supplements Supplement no A11 Increased MTOW 600kg 3rd Edition Rev 0 INTENTIONALLY LEFT BLANK ...

Page 237: ... not exceed this speed in any operation VNO Maximum Structural Cruising Speed 112 108 Do not exceed this speed except in smooth air and only with caution VA Design Manoeuvring speed 98 96 Do not make full or abrupt control movement above this speed because under certain conditions the air craft may be overstressed by full control movement VFE Maximum flaps extended speed FULL 68 70 Do not exceed t...

Page 238: ...e Flap Operating Range lower limit is VSO at specified maximum weight and upper limit is the maximum speed permissi ble with landing flaps extension Green arc 41 112 Normal Operating Range lower limit is VS1 at specified maximum weight and most for ward c g with flaps retracted and upper limit is maximum structural speed VNO Yellow arc 112 141 Manoeuvres must be conducted with caution and only in ...

Page 239: ... weight 2 26 m aft from datum 20 kg 13 CENTER OF GRAVITY Datum Propeller support flange without spacer Levelling Seat track supporting trusses ref to sect 6 for the procedure Forward limit 1 693 m 26 0 MAC aft of datum for all weights Aft limit 1 782 m 32 5 MAC aft of datum for all weights WARNING The pilot is responsible for ensuring that the airplane is properly loaded Refer to Section 6 for app...

Page 240: ... approved manoeuvre are as follows Manoeuvre Speed KIAS Lazy eight 98 Chandelle 112 Steep turn max 60 98 Stall Slow deceleration 1 kts s WARNING Acrobatic manoeuvres including spins and turns with angle of bank of more than 60 are not approved for such a category WARNING imit load factor could be exceeded by moving abruptly flight controls at their end run at a speed above VA Manoeuvring Speed 98 ...

Page 241: ...the dashboard a placard will state the following THIS AIRPLANE IS CLASSIFIED AS A VERY LIGHT AIRPLANE AP PROVED FOR DAY VFR ONLY IN NON ICING CONDITIONS ALL AEROBATIC MANEUVERS INCLUDING INTENTIONAL SPIN ARE PROHIBITED SEE FLIGHT MANUAL FOR OTHER LIMITATIONS NO SMOKING Near baggage compartment a placard will state the following FASTEN TIE DOWN NET MAXIMUM WEIGHT 20 KG MAX PRESS 12 5 kg dm2 On the ...

Page 242: ...Page W2 20 Section 2 Limitations MTOW 600kg Approved Maneuvres 3rd Edition Rev 0 INTENTIONALLY LEFT BLANK ...

Page 243: ...Page A11 7 Section 9 Supplements Supplement no A11 Increased MTOW 600kg 3rd Edition Rev 0 SECTION 3 EMERGENCY PROCEDURES See basic AFM Section 3 Supplement A11 pages replacement instructions ...

Page 244: ...Page A11 8 Section 9 Supplements Supplement no A11 Increased MTOW 600kg 3rd Edition Rev 0 SECTION 4 NORMAL OPERATION See basic AFM Section 4 Supplement A11 pages replacement instructions ...

Page 245: ...tion 9 Supplements Supplement no A11 Increased MTOW 600kg 3rd Edition Rev 0 SECTION 5 PERFORMANCE Supplement A11 Performances pages replace basic AFM Section 5 as a whole Supplement A11 pages replacement instructions ...

Page 246: ...Page A11 10 Section 9 Supplements Supplement no A11 Increased MTOW 600kg 3rd Edition Rev 0 INTENTIONALLY LEFT BLANK ...

Page 247: ...PEED INDICATOR SYSTEM CALIBRATION APPROVED DATA 4 4 ICAO STANDARD ATMOSPHERE 5 5 STALL SPEED APPROVED DATA 6 6 CROSSWIND 7 7 TAKE OFF PERFORMANCES APPROVED DATA 8 8 TAKE OFF RATE OF CLIMB 11 9 EN ROUTE RATE OF CLIMB 12 10 CRUISE PERFORMANCES 13 11 LANDING PERFORMANCES APPROVED DATA 15 12 BALKED LANDING CLIMB 18 13 NOISE DATA 19 ...

Page 248: ...rted in graphs and or in tables were determined using Flight Test Data under conditions prescribed by EASA CS VLA regulation aircraft and engine in good condition average piloting techniques Each graph or table was determined according to ICAO Standard Atmosphere ISA s l evaluations of the impact on performances were carried out by theo retical means for Airspeed External temperature Altitude Weig...

Page 249: ...NCES CHARTS Performances data are presented in tabular or graphical form to illustrate the ef fect of different variables such as altitude temperature and weight Given infor mation is sufficient to plan the mission with required precision and safety Additional information is provided for each table or graph ...

Page 250: ...ROVED DATA Graph shows calibrated airspeed VCAS as a function of indicated airspeed VIAS FIG 5 1 CALIBRATED VS INDICATED AIRSPEED Example Given Find KIAS 75 KCAS 74 Indicated airspeed assumes 0 as an instrument error 20 40 60 80 100 120 140 40 60 80 100 120 140 CALIBRATED AIRSPEED KCAS INDICATED AIRSPEED KIAS F L A P L A N D F L A P U P F L A P T O 77 NOTE ...

Page 251: ...ATMOSPHERE 3rd Edition Rev 0 4 ICAO STANDARD ATMOSPHERE FIG 5 2 ICAO CHART Examples Scope Given Find Density Altitude A Pressure altitude 1600ft B Temperature 20 C C Density Altitude 2550ft ISA Temperature D Pressure altitude 1600ft E ISA Air Temperature 12 C ...

Page 252: ... 26 No ground effect WEIGHT BANK ANGLE STALL SPEED FLAPS 0 FLAPS T O FLAPS FULL kg deg KIAS KCAS KIAS KCAS KIAS KCAS 600 FWD C G 0 41 50 36 46 31 40 15 42 51 37 47 32 40 30 46 53 41 50 35 43 45 54 59 48 55 41 47 60 68 70 62 65 53 56 Altitude loss during conventional stall recovery as demonstrated during flight tests is approximately 150 ft with banking below 30 NOTE ...

Page 253: ...0kg CROSSWIND 3rd Edition Rev 0 6 CROSSWIND Maximum demonstrated crosswind is 22 Kts Example Given Find Wind direction with respect to aircraft longitudinal axis 30 Headwind 17 5 Kts Wind speed 20 Kts Crosswind 10 Kts FIG 5 3 CROSSWIND CHART ...

Page 254: ...32 307 399 508 360 1000 Ground Roll 155 205 264 335 234 At 50 ft AGL 255 338 439 560 388 2000 Ground Roll 171 225 290 368 252 At 50 ft AGL 280 372 483 617 419 3000 Ground Roll 188 247 319 406 272 At 50 ft AGL 308 410 533 681 452 4000 Ground Roll 206 272 352 447 293 At 50 ft AGL 340 452 588 753 488 5000 Ground Roll 227 300 388 494 316 At 50 ft AGL 375 499 650 833 527 6000 Ground Roll 250 331 428 54...

Page 255: ... 1000 Ground Roll 124 163 211 267 187 At 50 ft AGL 203 269 350 446 309 2000 Ground Roll 136 179 231 294 201 At 50 ft AGL 223 297 385 492 334 3000 Ground Roll 150 197 255 323 217 At 50 ft AGL 246 327 425 544 360 4000 Ground Roll 164 217 281 357 234 At 50 ft AGL 271 360 469 601 389 5000 Ground Roll 181 239 309 394 252 At 50 ft AGL 299 398 519 664 421 6000 Ground Roll 199 264 342 435 273 At 50 ft AGL...

Page 256: ...24 1000 Ground Roll 97 127 164 208 146 At 50 ft AGL 159 210 273 348 242 2000 Ground Roll 106 140 181 229 157 At 50 ft AGL 174 231 301 384 261 3000 Ground Roll 117 154 199 252 169 At 50 ft AGL 192 255 332 424 281 4000 Ground Roll 128 169 219 278 183 At 50 ft AGL 212 281 366 469 304 5000 Ground Roll 141 187 242 307 197 At 50 ft AGL 233 310 405 519 328 6000 Ground Roll 156 206 267 339 213 At 50 ft AG...

Page 257: ...85 1 365 8000 66 439 212 10 173 220 10000 66 257 34 165 344 75 12000 65 75 144 339 515 70 14000 65 107 321 513 686 214 550 S L 66 1339 1077 842 631 933 2000 66 1140 882 651 443 777 4000 66 941 687 460 256 621 6000 65 742 493 271 70 464 8000 65 545 300 81 116 308 10000 65 348 107 107 301 152 12000 65 151 85 296 486 4 14000 64 44 276 483 669 161 500 S L 66 1532 1246 991 760 1089 2000 66 1315 1033 78...

Page 258: ...23 489 4000 66 563 336 134 49 344 5000 66 381 158 41 220 199 6000 65 199 20 215 391 54 7000 65 17 197 389 562 90 550 S L 66 1463 1201 966 755 1057 1000 66 1264 1006 775 567 901 2000 66 1065 811 584 380 745 3000 65 866 617 395 194 588 4000 65 669 424 205 8 432 5000 65 472 231 17 177 276 6000 65 275 39 172 362 120 7000 64 80 152 359 545 37 500 S L 66 1656 1370 1115 884 1213 1000 66 1439 1157 906 680...

Page 259: ...SA 30 C 15 C ISA 15 C ISA 30 C 45 C RPM PWR KTAS F C PWR KTAS F C PWR KTAS F C lt hr lt hr lt hr 2355 112 109 30 2 93 106 25 1 78 101 21 2312 106 107 28 6 88 103 23 6 73 99 19 7 2265 100 105 27 82 100 22 2 68 96 18 4 2214 94 102 25 2 76 98 20 6 63 92 17 2157 87 99 23 4 70 94 19 58 88 15 5 2094 80 96 21 4 64 90 17 3 52 84 13 9 2023 72 92 19 4 57 86 15 5 46 77 12 3 Propeller RPM Fuel Consumption Wei...

Page 260: ...Weight 580 kg Pressure Altitude 8000 ft ISA 30 C 15 C ISA 15 C ISA 30 C 45 C RPM PWR KTAS F C PWR KTAS F C PWR KTAS F C lt hr lt hr lt hr 2331 92 107 24 8 75 102 20 2 62 96 16 7 2287 87 105 23 4 71 99 19 58 93 15 6 2239 82 102 22 66 96 17 8 53 89 14 4 2185 76 99 20 5 61 93 16 4 49 84 13 2 Propeller RPM Fuel Consumption Weight 580 kg Pressure Altitude 10000 ft ISA 30 C 15 C ISA 15 C ISA 30 C 45 C R...

Page 261: ...8 302 1000 Ground Roll 137 151 165 179 158 At 50 ft AGL 269 296 324 351 311 2000 Ground Roll 142 157 171 185 163 At 50 ft AGL 279 307 336 364 320 3000 Ground Roll 148 162 177 192 168 At 50 ft AGL 290 319 348 377 330 4000 Ground Roll 153 169 184 199 173 At 50 ft AGL 301 331 361 392 340 5000 Ground Roll 159 175 191 207 178 At 50 ft AGL 312 344 375 406 350 6000 Ground Roll 165 182 198 215 184 At 50 f...

Page 262: ...oll 115 127 138 150 133 At 50 ft AGL 226 249 272 295 261 2000 Ground Roll 120 132 144 156 137 At 50 ft AGL 235 258 282 306 269 3000 Ground Roll 124 137 149 161 141 At 50 ft AGL 243 268 293 317 277 4000 Ground Roll 129 142 155 168 145 At 50 ft AGL 253 278 304 329 285 5000 Ground Roll 134 147 160 174 150 At 50 ft AGL 262 289 315 342 294 6000 Ground Roll 139 153 167 181 154 At 50 ft AGL 272 300 327 3...

Page 263: ...Roll 95 105 114 124 110 At 50 ft AGL 187 206 225 244 216 2000 Ground Roll 99 109 119 129 113 At 50 ft AGL 194 214 233 253 222 3000 Ground Roll 102 113 123 133 117 At 50 ft AGL 201 221 242 262 229 4000 Ground Roll 106 117 128 138 120 At 50 ft AGL 209 230 251 272 236 5000 Ground Roll 110 122 133 144 124 At 50 ft AGL 217 239 260 282 243 6000 Ground Roll 115 126 138 149 128 At 50 ft AGL 225 248 270 29...

Page 264: ...2 121 301 5000 411 286 175 75 263 6000 362 238 128 29 224 7000 313 190 81 17 185 550 S L 777 635 508 394 557 1000 723 582 457 344 515 2000 669 530 405 293 473 3000 615 477 354 242 431 4000 562 425 302 192 389 5000 508 372 251 142 347 6000 454 320 200 91 304 7000 401 268 149 41 262 500 S L 915 759 620 494 674 1000 856 701 563 438 627 2000 796 643 506 383 581 3000 737 585 449 327 534 4000 678 527 39...

Page 265: ...Page W5 19 Section 5 Performances MTOW 600kg NOISE DATA 3rd Edition Rev 0 13 NOISE DATA Noise level determined in accordance with ICAO Annex 16 4th Ed July 2005 Vol I Chapter 10 is 62 58 dB A ...

Page 266: ...Page W5 20 Section 5 Performances MTOW 600kg NOISE DATA 3rd Edition Rev 0 INTENTIONALLY LEFT BLANK ...

Page 267: ...Page A11 11 Section 9 Supplements Supplement no A11 Increased MTOW 600kg 3rd Edition Rev 0 SECTION 6 WEIGHT AND BALANCE See basic AFM Section 6 Supplement A11 pages replacement instructions ...

Page 268: ...Page A11 11 Section 9 Supplements Supplement no A11 Increased MTOW 600kg 3rd Edition Rev 0 SECTION 7 AIRFRAME AND SYSTEM DESCRIPTION See basic AFM Section 7 Supplement A11 pages replacement instructions ...

Page 269: ...14 Amend Warning G Paduano M Landi M Oliva DOA privileges 1 W5 6 Update Stall Speed Table G Paduano M Landi M Oliva DOA privileges 1 W5 11 12 Update Climb performance table G Paduano M Landi M Oliva DOA privileges List of Effective Pages Page Revision Cover Pages A12 1 thru 12 Rev 0 Section 2 W2 3 Rev 0 W2 4 Rev 0 W2 13 Rev 0 W2 14 Rev 1 W2 19 Rev 0 W2 20 Rev 0 Section 5 W5 1 thru 5 Rev 0 W5 6 Rev...

Page 270: ...ed MTOW 620kg 3rd Edition Rev 0 INDEX INTRODUCTION 3 SECTION 1 GENERAL 4 SECTION 2 LIMITATIONS 5 SECTION 3 EMERGENCY PROCEDURES 7 SECTION 4 NORMAL OPERATION 8 SECTION 5 PERFORMANCE 9 SECTION 6 WEIGHT AND BALANCE 11 SECTION 7 AIRFRAME AND SYSTEM DESCRIPTION 12 ...

Page 271: ...or Design Change MOD 2002 087 has been embodied on the airplane The information contained herein supplements or supersedes the basic Aircraft Flight Manual detailed instructions are provided to allow the owner for replacing the basic AFM pages containing information amended as per the Increased MTOW Design Change in subject It is the owner s responsibility to replace the mentioned pages in accorda...

Page 272: ...Page A12 4 Section 9 Supplements Supplement no A12 Increased MTOW 620kg 3rd Edition Rev 0 SECTION 1 GENERAL See basic AFM Section 1 Supplement A12 pages replacement instructions ...

Page 273: ... 0 SECTION 2 LIMITATIONS Apply following pages replacement procedure Supplement A11 Limitations page Basic AFM Limitations page W2 3 REPLACES 2 3 W2 4 REPLACES 2 4 W2 13 REPLACES 2 13 W2 14 REPLACES 2 14 W2 20 REPLACES 2 20 W2 21 REPLACES 2 21 Supplement A12 pages replacement instructions ...

Page 274: ...Page A12 6 Section 9 Supplements Supplement no A12 Increased MTOW 620kg 3rd Edition Rev 0 INTENTIONALLY LEFT BLANK ...

Page 275: ...not exceed this speed in any operation VNO Maximum Structural Cruising Speed 114 110 Do not exceed this speed except in smooth air and only with caution VA Design Manoeuvring speed 100 97 Do not make full or abrupt control movement above this speed because under certain conditions the air craft may be overstressed by full control movement VFE Maximum flaps extended speed FULL 69 71 Do not exceed t...

Page 276: ...e Flap Operating Range lower limit is VSO at specified maximum weight and upper limit is the maximum speed permissi ble with landing flaps extension Green arc 41 114 Normal Operating Range lower limit is VS1 at specified maximum weight and most for ward c g with flaps retracted and upper limit is maximum structural speed VNO Yellow arc 114 142 Manoeuvres must be conducted with caution and only in ...

Page 277: ... weight 2 26 m aft from datum 20 kg 13 CENTER OF GRAVITY Datum Propeller support flange without spacer Levelling Seat track supporting trusses ref to sect 6 for the procedure Forward limit 1 693 m 26 0 MAC aft of datum for all weights Aft limit 1 782 m 32 5 MAC aft of datum for all weights WARNING The pilot is responsible for ensuring that the airplane is properly loaded Refer to Section 6 for app...

Page 278: ...pproved manoeuvre are as follows Manoeuvre Speed KIAS Lazy eight 100 Chandelle 114 Steep turn max 60 100 Stall Slow deceleration 1 kts s WARNING Acrobatic manoeuvres including spins and turns with angle of bank of more than 60 are not approved for such a category WARNING Limit load factor could be exceeded by moving abruptly flight controls at their end run at a speed above VA Manoeuvring Speed 10...

Page 279: ...Page W2 19 Section 2 Limitations MTOW 620kg Approved Maneuvres 3rd Edition Rev 0 INTENTIONALLY LEFT BLANK ...

Page 280: ...the dashboard a placard will state the following THIS AIRPLANE IS CLASSIFIED AS A VERY LIGHT AIRPLANE AP PROVED FOR DAY VFR ONLY IN NON ICING CONDITIONS ALL AEROBATIC MANEUVERS INCLUDING INTENTIONAL SPIN ARE PROHIBITED SEE FLIGHT MANUAL FOR OTHER LIMITATIONS NO SMOKING Near baggage compartment a placard will state the following FASTEN TIE DOWN NET MAXIMUM WEIGHT 20 KG MAX PRESS 12 5 kg dm2 On the ...

Page 281: ...Page A12 7 Section 9 Supplements Supplement no A12 Increased MTOW 620kg 3rd Edition Rev 0 SECTION 3 EMERGENCY PROCEDURES See basic AFM Section 3 Supplement A12 pages replacement instructions ...

Page 282: ...Page A12 8 Section 9 Supplements Supplement no A12 Increased MTOW 620kg 3rd Edition Rev 0 SECTION 4 NORMAL OPERATION See basic AFM Section 4 Supplement A12 pages replacement instructions ...

Page 283: ...tion 9 Supplements Supplement no A12 Increased MTOW 620kg 3rd Edition Rev 0 SECTION 5 PERFORMANCE Supplement A11 Performances pages replace basic AFM Section 5 as a whole Supplement A12 pages replacement instructions ...

Page 284: ...Page A12 10 Section 9 Supplements Supplement no A12 Increased MTOW 620kg 3rd Edition Rev 0 INTENTIONALLY LEFT BLANK ...

Page 285: ...PEED INDICATOR SYSTEM CALIBRATION APPROVED DATA 4 4 ICAO STANDARD ATMOSPHERE 5 5 STALL SPEED APPROVED DATA 6 6 CROSSWIND 7 7 TAKE OFF PERFORMANCES APPROVED DATA 8 8 TAKE OFF RATE OF CLIMB 11 9 EN ROUTE RATE OF CLIMB 12 10 CRUISE PERFORMANCES 13 11 LANDING PERFORMANCES APPROVED DATA 15 12 BALKED LANDING CLIMB 18 13 NOISE DATA 19 ...

Page 286: ...rted in graphs and or in tables were determined using Flight Test Data under conditions prescribed by EASA CS VLA regulation aircraft and engine in good condition average piloting techniques Each graph or table was determined according to ICAO Standard Atmosphere ISA s l evaluations of the impact on performances were carried out by theo retical means for Airspeed External temperature Altitude Weig...

Page 287: ...NCES CHARTS Performances data are presented in tabular or graphical form to illustrate the ef fect of different variables such as altitude temperature and weight Given infor mation is sufficient to plan the mission with required precision and safety Additional information is provided for each table or graph ...

Page 288: ...ROVED DATA Graph shows calibrated airspeed VCAS as a function of indicated airspeed VIAS FIG 5 1 CALIBRATED VS INDICATED AIRSPEED Example Given Find KIAS 75 KCAS 74 Indicated airspeed assumes 0 as an instrument error 20 40 60 80 100 120 140 40 60 80 100 120 140 CALIBRATED AIRSPEED KCAS INDICATED AIRSPEED KIAS F L A P L A N D F L A P U P F L A P T O 77 NOTE ...

Page 289: ...ATMOSPHERE 3rd Edition Rev 0 4 ICAO STANDARD ATMOSPHERE FIG 5 2 ICAO CHART Examples Scope Given Find Density Altitude A Pressure altitude 1600ft B Temperature 20 C C Density Altitude 2550ft ISA Temperature D Pressure altitude 1600ft E ISA Air Temperature 12 C ...

Page 290: ... 26 No ground effect WEIGHT BANK ANGLE STALL SPEED FLAPS 0 FLAPS T O FLAPS FULL kg deg KIAS KCAS KIAS KCAS KIAS KCAS 620 FWD C G 0 41 50 38 48 33 41 15 42 51 39 49 34 42 30 46 54 44 52 37 44 45 54 60 51 57 44 49 60 69 71 65 68 56 58 Altitude loss during conventional stall recovery as demonstrated during flight tests is approximately 150 ft with banking below 30 NOTE ...

Page 291: ...0kg CROSSWIND 3rd Edition Rev 0 6 CROSSWIND Maximum demonstrated crosswind is 22 Kts Example Given Find Wind direction with respect to aircraft longitudinal axis 30 Headwind 17 5 Kts Wind speed 20 Kts Crosswind 10 Kts FIG 5 3 CROSSWIND CHART ...

Page 292: ...2 335 434 553 392 1000 Ground Roll 169 223 287 364 255 At 50 ft AGL 277 368 478 610 423 2000 Ground Roll 186 245 316 401 275 At 50 ft AGL 305 405 526 672 456 3000 Ground Roll 204 269 348 442 296 At 50 ft AGL 336 446 580 742 492 4000 Ground Roll 225 296 383 487 319 At 50 ft AGL 370 492 641 820 531 5000 Ground Roll 247 327 423 538 345 At 50 ft AGL 408 543 708 907 574 6000 Ground Roll 272 360 466 594...

Page 293: ... 1000 Ground Roll 124 163 211 267 187 At 50 ft AGL 203 269 350 446 309 2000 Ground Roll 136 179 231 294 201 At 50 ft AGL 223 297 385 492 334 3000 Ground Roll 150 197 255 323 217 At 50 ft AGL 246 327 425 544 360 4000 Ground Roll 164 217 281 357 234 At 50 ft AGL 271 360 469 601 389 5000 Ground Roll 181 239 309 394 252 At 50 ft AGL 299 398 519 664 421 6000 Ground Roll 199 264 342 435 273 At 50 ft AGL...

Page 294: ...24 1000 Ground Roll 97 127 164 208 146 At 50 ft AGL 159 210 273 348 242 2000 Ground Roll 106 140 181 229 157 At 50 ft AGL 174 231 301 384 261 3000 Ground Roll 117 154 199 252 169 At 50 ft AGL 192 255 332 424 281 4000 Ground Roll 128 169 219 278 183 At 50 ft AGL 212 281 366 469 304 5000 Ground Roll 141 187 242 307 197 At 50 ft AGL 233 310 405 519 328 6000 Ground Roll 156 206 267 339 213 At 50 ft AG...

Page 295: ...54 27 328 8000 66 400 180 17 194 187 10000 66 223 7 187 361 47 12000 66 46 166 356 527 94 14000 66 130 338 525 693 235 550 S L 66 1339 1077 842 631 933 2000 66 1140 882 651 443 777 4000 66 941 687 460 256 621 6000 65 742 493 271 70 464 8000 65 545 300 81 116 308 10000 65 348 107 107 301 152 12000 65 151 85 296 486 4 14000 64 44 276 483 669 161 500 S L 66 1532 1246 991 760 1089 2000 66 1315 1033 78...

Page 296: ...2 8000 66 524 304 107 70 311 10000 66 347 131 63 237 171 12000 66 170 42 232 403 30 14000 66 6 214 401 569 111 550 S L 66 1463 1201 966 755 1057 2000 66 1264 1006 775 567 901 4000 66 1065 811 584 380 745 6000 65 866 617 395 194 588 8000 65 669 424 205 8 432 10000 65 472 231 17 177 276 12000 65 275 39 172 362 120 14000 64 80 152 359 545 37 500 S L 66 1656 1370 1115 884 1213 2000 66 1439 1157 906 68...

Page 297: ...SA 30 C 15 C ISA 15 C ISA 30 C 45 C RPM PWR KTAS F C PWR KTAS F C PWR KTAS F C lt hr lt hr lt hr 2355 112 109 30 2 93 106 25 1 78 101 21 2312 106 107 28 6 88 103 23 6 73 99 19 7 2265 100 105 27 82 100 22 2 68 96 18 4 2214 94 102 25 2 76 98 20 6 63 92 17 2157 87 99 23 4 70 94 19 58 88 15 5 2094 80 96 21 4 64 90 17 3 52 84 13 9 2023 72 92 19 4 57 86 15 5 46 77 12 3 Propeller RPM Fuel Consumption Wei...

Page 298: ...Weight 580 kg Pressure Altitude 8000 ft ISA 30 C 15 C ISA 15 C ISA 30 C 45 C RPM PWR KTAS F C PWR KTAS F C PWR KTAS F C lt hr lt hr lt hr 2331 92 107 24 8 75 102 20 2 62 96 16 7 2287 87 105 23 4 71 99 19 58 93 15 6 2239 82 102 22 66 96 17 8 53 89 14 4 2185 76 99 20 5 61 93 16 4 49 84 13 2 Propeller RPM Fuel Consumption Weight 580 kg Pressure Altitude 10000 ft ISA 30 C 15 C ISA 15 C ISA 30 C 45 C R...

Page 299: ...1 322 1000 Ground Roll 146 161 176 191 169 At 50 ft AGL 288 317 345 374 332 2000 Ground Roll 152 167 183 198 174 At 50 ft AGL 298 328 358 388 342 3000 Ground Roll 158 173 189 205 179 At 50 ft AGL 309 341 372 403 352 4000 Ground Roll 164 180 196 213 185 At 50 ft AGL 321 353 386 418 363 5000 Ground Roll 170 187 204 221 190 At 50 ft AGL 333 367 400 434 374 6000 Ground Roll 176 194 212 230 196 At 50 f...

Page 300: ...oll 115 127 138 150 133 At 50 ft AGL 226 249 272 295 261 2000 Ground Roll 120 132 144 156 137 At 50 ft AGL 235 258 282 306 269 3000 Ground Roll 124 137 149 161 141 At 50 ft AGL 243 268 293 317 277 4000 Ground Roll 129 142 155 168 145 At 50 ft AGL 253 278 304 329 285 5000 Ground Roll 134 147 160 174 150 At 50 ft AGL 262 289 315 342 294 6000 Ground Roll 139 153 167 181 154 At 50 ft AGL 272 300 327 3...

Page 301: ...Roll 95 105 114 124 110 At 50 ft AGL 187 206 225 244 216 2000 Ground Roll 99 109 119 129 113 At 50 ft AGL 194 214 233 253 222 3000 Ground Roll 102 113 123 133 117 At 50 ft AGL 201 221 242 262 229 4000 Ground Roll 106 117 128 138 120 At 50 ft AGL 209 230 251 272 236 5000 Ground Roll 110 122 133 144 124 At 50 ft AGL 217 239 260 282 243 6000 Ground Roll 115 126 138 149 128 At 50 ft AGL 225 248 270 29...

Page 302: ...188 88 266 5000 374 251 142 43 228 6000 326 204 95 3 190 7000 277 157 49 48 152 550 S L 777 635 508 394 557 1000 723 582 457 344 515 2000 669 530 405 293 473 3000 615 477 354 242 431 4000 562 425 302 192 389 5000 508 372 251 142 347 6000 454 320 200 91 304 7000 401 268 149 41 262 500 S L 915 759 620 494 674 1000 856 701 563 438 627 2000 796 643 506 383 581 3000 737 585 449 327 534 4000 678 527 393...

Page 303: ...Page W5 19 Section 5 Performances MTOW 620kg NOISE DATA 3rd Edition Rev 0 13 NOISE DATA Noise level determined in accordance with ICAO Annex 16 4th Ed July 2005 Vol I Chapter 10 is 65 74 dB A ...

Page 304: ...Page W5 20 Section 5 Performances MTOW 620kg NOISE DATA 3rd Edition Rev 0 INTENTIONALLY LEFT BLANK ...

Page 305: ...Page A12 11 Section 9 Supplements Supplement no A12 Increased MTOW 620kg 3rd Edition Rev 0 SECTION 6 WEIGHT AND BALANCE See basic AFM Section 6 Supplement A12 pages replacement instructions ...

Page 306: ...Page A12 12 Section 9 Supplements Supplement no A12 Increased MTOW 620kg 3rd Edition Rev 0 SECTION 7 AIRFRAME AND SYSTEM DESCRIPTION See basic AFM Section 7 Supplement A12 pages replacement instructions ...

Page 307: ...of Revision Tecnam Approval EASA Approval or Under DOA Privileges DO OoA HDO 0 List of Effective Pages Page Revision Cover Pages A13 1 thru 16 Rev 0 Section 1 VP1 thru 2 Rev0 VP1 5 thru 8 Rev 0 Section 2 VP2 5 thru 8 Rev 0 Section 3 VP3 1 thru 2 Rev 0 VP9 thru 12 Rev 0 Section 4 VP4 7 thru 12 Rev 0 Section 5 VP5 1 thru 20 Rev 0 Section 6 VP6 11 thru 14 Rev 0 Section 7 VP7 3 4 7 8 Rev 0 ...

Page 308: ...Pitch Propeller 3rd Edition Rev 0 INDEX INTRODUCTION 3 SECTION 1 GENERAL 4 SECTION 2 LIMITATIONS 5 SECTION 3 EMERGENCY PROCEDURES 7 SECTION 4 NORMAL OPERATION 9 SECTION 5 PERFORMANCE 11 SECTION 6 WEIGHT AND BALANCE 13 SECTION 7 AIRFRAME AND SYSTEM DESCRIPTION 15 ...

Page 309: ...ained herein supplements or supersedes the basic Aircraft Flight Manual detailed instructions are provided to allow the owner for replacing the basic AFM pages containing information amended as per the Variable Pitch Propeller Design Change in subject The application of this supplement invalidate the supplement A05 Central Throt tle control system It is the owner s responsibility to replace the me...

Page 310: ...n Rev 0 SECTION 1 GENERAL Apply following pages replacement procedure Supplement A13 Limitations page Basic AFM Limitations page VP1 1 REPLACES 1 1 VP1 2 REPLACES 1 2 VP1 5 REPLACES 1 5 VP1 6 REPLACES 1 6 VP1 7 REPLACES 1 7 VP1 8 REPLACES 1 8 Supplement A13 pages replacement instructions ...

Page 311: ...aces Travel Limits 5 3 2 Engine 5 3 3 Propeller 5 3 4 Governor 6 3 5 Fuel 6 3 6 Lubrication 6 3 7 Cooling 6 3 8 weights 7 3 9 Standard weights 7 3 10 Specific loadings 7 4ACRONYMS AND TERMINOLOGY 8 4 1 General Airspeed Terminology And Symbols 8 4 2 Meteorological terminology 9 4 3 Engine Power terminology 9 4 4 Aircraft performance and flight planning terminology 10 4 5 Weight and balance terminol...

Page 312: ...Safety Aviation Agency in accordance with CS VLA dated 14 November 2003 and the Type Certificate No A 006 27th May 2004 Category of Airworthiness Normal Noise Certification Basis EASA CS 36 1st edition dated 17th October 2003 with reference to ICAO Annex 16 3rd edition dated 1993 Vol 1 Chapter 10 WARNING CAUTION NOTE 1 2 Following definitions apply to warnings cautions and notes used in the Aircra...

Page 313: ...o TW 9 ACG dated 27th November 1998 Engine type 4 cylinder horizontally opposed twins with overall displacement of 1352 c c mixed cooling water cooled heads and air cooled cylinders twin carburetors integrated reduction gear with torque damper Maximum power at declared rpm 73 5kW 98 5hp 5800rpm max 5 69 0kW 92 5hp 5500rpm cont 3 3 PROPELLER Manufacturer Hoffmann Propeller Certification Basis Joint...

Page 314: ... and with drain fittings Capacity of each wing tan 50 litres Tanks overall capacity 100 litres Overall usable fuel 99 litres Overall unusable fuel 1 litre LUBRICATION 3 6 Lubrication system Forced type with external reservoir Oil Lubricant specifications and grade are detailed into the Rotax Operators Manual and in its re lated documents Oil capacity Max 3 0 litres min 2 0 litres COOLING 3 7 Cooli...

Page 315: ... see weighing record on Section 6 SPECIFIC LOADINGS 3 10 MTOW 580 kg MTOW 600 kg MTOW 620 kg Wing Loading 50 4 kg m2 52 2 kg m2 53 9 kg m2 Power Loading 5 9 kg hp 6 1 kg hp 6 3 kg hp Reference is made to each MTOW 580 kg 600 kg if Supplement A11 Increased MTOW 600kg is applicable and 620 kg if Sup plement A12 Increased MTOW 620kg is applicable NOTE ...

Page 316: ...ve the which it is not allowed to make full or abrupt control movement VFE Maximum Flap Extended speed is the highest speed permissible with flaps extended VNO Maximum Structural Cruising Speed is the speed that should not be exceeded except in smooth air and only with caution VNE Never Exceed Speed is the speed limit that may not be exceeded at any time VS Stall Speed VS0 Stall Speed in landing c...

Page 317: ...peller 3rd Edition Rev 0 SECTION 2 LIMITATIONS Apply following pages replacement procedure Supplement A13 Limitations page Basic AFM Limitations page VP2 5 REPLACES 2 5 VP2 6 REPLACES 2 6 VP2 7 REPLACES 2 7 VP2 8 REPLACES 2 8 Supplement A13 pages replacement instructions ...

Page 318: ...Page A13 6 Section 9 Supplements Supplement no A13 Variable Pitch Propeller 3rd Edition Rev 0 INTENTIONALLY LEFT BLANK ...

Page 319: ... no wind conditions the maxi mum propeller s rpm should be 2100 100 Temperatures Max CHT 135 C Min Max Oil 50 C 130 C Oil normal operating range approx 90 C 110 C Oil Pressure Minimum 0 8 Bar 12 psi below 1400 rpm prop Normal 2 5 Bar 29 73 psi above 1400 rpm prop Maximum 7 Bar 102 psi above 1400 rpm prop Engine starting allowable temperature range OAT Min 25 C OAT Max 50 C WARNING In event of cold...

Page 320: ...n 2 Limitations Variable Pitch Propeller LUBRICANT 3rd Edition Rev 0 5 LUBRICANT Use viscosity grade oil as specified in the following table WARNING Use of Aviation Grade Oil with or without additives is not per mitted ...

Page 321: ...P2 7 Section 2 Limitations Variable Pitch Propeller COOLANT LIQUID 3rd Edition Rev 0 6 COOLANT LIQUID Coolant type and specifications are detailed into the Rotax Operator s Manual and in its related documents ...

Page 322: ...on 2 Limitations Variable Pitch Propeller PROPELLER 3rd Edition Rev 0 7 PROPELLER MANUFACTURER Hoffmann Propeller GmbH MODEL HOV352F1 C170FQ 8 TYPE Wood twin blade variable pitch DIAMETER 1780 mm no reduction permitted ...

Page 323: ...ROCEDURES Apply following pages replacement procedure Supplement A13 Limitations page Basic AFM Limitations page VP3 1 REPLACES 3 1 VP3 2 REPLACES 3 2 VP3 7 REPLACES 3 7 VP3 8 REPLACES 3 8 VP3 9 REPLACES 3 9 VP3 10 REPLACES 3 10 VP3 11 REPLACES 3 11 VP3 12 REPLACES 3 12 Supplement A13 pages replacement instructions ...

Page 324: ...Page A13 8 Section 9 Supplements Supplement no A13 Variable Pitch Propeller 3rd Edition Rev 0 INTENTIONALLY LEFT BLANK ...

Page 325: ...ssure 8 4 3 2 Oil pressure limits exceedance 8 4 3 3 High Oil Temperature 9 4 3 4 CHT limit exceedance 10 4 3 5 Propeller overspeeding 10 5 In Flight Engine Restart 11 6 Smoke And Fire 12 6 1 Engine fire on the ground 12 6 2 Engine Fire During Takeoff 12 6 3 Engine Fire In Flight 13 6 4 Cabin Fire Electrical smoke in cabin during flight 13 6 5 Electrical smoke fire in cabin on the ground 13 7 Land...

Page 326: ...Page VP3 2 Section 3 Emergency procedures Variable Pitch Propeller INDEX 3rd Edition Rev 0 INTENTIONALLY LEFT BLANK ...

Page 327: ...to the right 3 Flaps as needed WARNING Stall speed increases with bank angle and longitudinal load factor Acoustic stall warning will in any case provide a cor rect anticipated clue of incipient stall At or right before touch down 4 Throttle IDLE fully out 5 Magnetos OFF 6 Fuel selector valve OFF 7 Electric fuel pump OFF 8 Generator Master switches OFF WARNING A single engine aircraft take off sho...

Page 328: ...fuel pressure doesn t build up 4 Land as soon as possible monitoring fuel pressure 4 3 2 Oil Pressure limits exceedance If oil pressure exceeds upper limit 7 bar 1 Throttle Lever REDUCE engine power as practical 2 Propeller Lever Keep higher than 2000 RPM 3 OIL PRESS CHECK within limits 4 Land as soon as practical If oil pressure is under lower limit 0 8 bar 1 Throttle Lever REDUCE Minimum practic...

Page 329: ...ever Keep higher than 2000 RPM If oil temperature does not decrease 3 Airspeed INCREASE If oil temperature does not come back within limits the thermostatic valve if embodied regulating the oil flow to the heat exchangers could be damaged or an oil leakage can be present in the oil supply line 4 Land as soon as practical If engine roughness vibrations erratic behaviour or high CHT is detected 5 La...

Page 330: ...Propeller such a way that the maximum propeller rpm exceedance is prevented In case of propeller overspeeding in flight apply following procedure 1 Throttle Lever REDUCE power to minimum practical 2 Propeller Lever REDUCE as practical 3 Airspeed REDUCE as practical 4 RPM indicator CHECK If it is not possible to decrease propeller rpm and avoid overspeed 5 Engine SECURE see engine securing procedur...

Page 331: ...tor change the fuel feeding tank 5 Throttle lever IDLE 6 Propeller lever Full forward 7 Magnetos BOTH 8 Magnetos START 9 Propeller lever SET as required 10 Throttle lever SET as required CAUTION After engine restart if practical moderate propeller rpm and throttle increase to allow OIL and CHT temperatures for stabilizing in the green arcs If the fuel quantity in the tank which feeds the stopped e...

Page 332: ...RWARD 6 Cabin Heat OFF 7 Generator Master Switches OFF 8 Parking Brake ENGAGED 9 Aircraft Evacuation carry out immediately 7 2 ENGINE FIRE DURING TAKEOFF BEFORE ROTATION ABORT TAKE OFF 1 Throttle Lever IDLE 2 Rudder Keep heading control 3 Brakes As required With aircraft under control 1 Fuel Selector OFF 2 Electrical fuel pump OFF 3 Magnetos OFF 4 Cabin Heat OFF 5 Generator Master Switches OFF 6 P...

Page 333: ...SECTION 4 NORMAL OPERATION Apply following pages replacement procedure Supplement A13 Limitations page Basic AFM Limitations page VP4 7 REPLACES 4 7 VP4 8 REPLACES 4 8 VP4 9 REPLACES 4 9 VP4 10 REPLACES 4 10 VP4 11 REPLACES 4 11 VP4 12 REPLACES 4 12 Supplement A13 pages replacement instructions ...

Page 334: ...Page A13 10 Section 9 Supplements Supplement no A13 Variable Pitch Propeller 3rd Edition Rev 0 INTENTIONALLY LEFT BLANK ...

Page 335: ... check then set in OFF position 10 Flap control cycle fully extended and then set T O 11 Pitch Trim cycle fully up and down from both left and right controls check for trim disconnect switch operation 12 Pitch trim set neutral WARNING Pitch trim other than in neutral position would affect take off per formance and take off rotation execution at the correct VR IAS 13 Nav light Strobe light ON 14 Fu...

Page 336: ...esent in the area close to the propeller Forward lower sector visibility is not possible from inside the cockpit 8 Magnetos BOTH 9 Magnetos START 10 Check oil pressure rise within 10 sec maximum cold value 7 bar 11 Generator switch ON 12 Ammeter check green 13 Voltmeter check more than 14V 14 Engine instruments Check 15 Choke OFF 16 Propeller rpm 1000 1200 rpm 17 Electric fuel pump OFF 18 Check fu...

Page 337: ...heck 7 Propeller speed advance throttle to 1640 rpm a Ignition magnetos test select LEFT check max 130 rpm propeller speed drop b Select BOTH check propeller speed 1640 rpm c Select RIGHT check max 130 rpm propeller speed drop and max differ ence between LEFT and RIGHT 50 rpm d Select BOTH check propeller speed 1640 rpm 8 Carburettor heat test a Pull selector fully out b Propeller speed check 100 ...

Page 338: ...g with propeller speed rise and then power lever set forward 1 Parking brake OFF 2 Carburetor heat OFF 3 Check magnetic compass and gyro direction indicator alignment 4 Propeller FULL FORWARD 5 Throttle lever set full power check approximately 2100 100 propeller rpm 6 Engine instruments check 7 Rotation speed VR MTOW 580kg MTOW 600kg MTOW 620kg Rotation Speed VR 42 KIAS 42 KIAS 42 KIAS 8 Flaps ret...

Page 339: ...r valve Switch on the electric fuel pump prior to swap the fuel feeding from one tank to another 1 8 BEFORE LANDING 1 Propeller FULL FORWARD 2 Electric fuel pump ON 3 Fuel valve select the fullest tank 4 Landing Light ON 5 On downwind leg abeam touch down point Flaps set T O 15 MTOW 580kg MTOW 600kg MTOW 620kg Approach Speed 66 KIAS 66 KIAS 66 KIAS 6 On final leg Flaps set Land 40 MTOW 580kg MTOW ...

Page 340: ...F 3 Landing light OFF 1 11 ENGINE SHUT DOWN 1 Parking brake engage 2 Keep engine running at 1200 rpm for about one minute in order to reduce la tent heat 3 Avionic equipment OFF 4 Magnetos OFF keys extracted 5 Strobe light OFF 6 Master Generator switches OFF 7 Fuel selector valve OFF 1 12 POSTFLIGHT CHECK 1 Flight controls lock by mean of seat belts 2 Wheel chocks and wing mooring lines Set 3 Park...

Page 341: ...dition Rev 0 Section 9 Supplements Supplement no A13 Variable Pitch Propeller SECTION 5 PERFORMANCE Supplement A13 Performances pages replace basic AFM Section 5 as a whole Supplement A13 pages replacement instructions ...

Page 342: ...Page A13 12 3rd Edition Rev 0 Section 9 Supplements Supplement no A13 Variable Pitch Propeller INTENTIONALLY LEFT BLANK ...

Page 343: ...3 3 AIRSPEED INDICATOR SYSTEM CALIBRATION APPROVED DATA 4 4 ICAO STANDARD ATMOSPHERE 5 5 STALL SPEED APPROVED DATA 6 6 CROSSWIND 7 7 TAKE OFF PERFORMANCES APPROVED DATA 8 8 TAKE OFF RATE OF CLIMB 11 9 EN ROUTE RATE OF CLIMB 12 10 CRUISE PERFORMANCES 13 11 LANDING PERFORMANCES APPROVED DATA 15 12 BALKED LANDING CLIMB 18 13 NOISE DATA 19 ...

Page 344: ...ta reported in graphs and or in tables were determined using Flight Test Data under conditions prescribed by EASA CS VLA regulation aircraft and engine in good condition average piloting techniques Each graph or table was determined according to ICAO Standard Atmosphere ISA s l evaluations of the impact on performances were carried out by theo retical means for Airspeed External temperature Altitu...

Page 345: ...ERFORMANCES CHARTS Performances data are presented in tabular or graphical form to illustrate the ef fect of different variables such as altitude temperature and weight Given infor mation is sufficient to plan the mission with required precision and safety Additional information is provided for each table or graph ...

Page 346: ...TION APPROVED DATA Graph shows calibrated airspeed VCAS as a function of indicated airspeed VIAS FIG 5 1 CALIBRATED VS INDICATED AIRSPEED Example Given Find KIAS 75 KCAS 74 Indicated airspeed assumes 0 as an instrument error 20 40 60 80 100 120 140 40 60 80 100 120 140 CALIBRATED AIRSPEED KCAS INDICATED AIRSPEED KIAS F L A P L A N D F L A P U P F L A P T O 77 NOTE ...

Page 347: ...TANDARD ATMOSPHERE 3rd Edition Rev 0 4 ICAO STANDARD ATMOSPHERE FIG 5 2 ICAO CHART Examples Scope Given Find Density Altitude A Pressure altitude 1600ft B Temperature 20 C C Density Altitude 2550ft ISA Temperature D Pressure altitude 1600ft E ISA Air Temperature 12 C ...

Page 348: ...620 FWD C G 0 41 50 38 48 33 41 15 42 51 39 49 34 42 30 46 54 44 52 37 44 45 54 60 51 57 44 49 60 69 71 65 68 56 58 600 FWD C G 0 41 50 36 46 31 40 15 42 51 37 47 32 40 30 46 53 41 50 35 43 45 54 59 48 55 41 47 60 68 70 62 65 53 56 580 FWD C G 0 40 49 35 46 30 39 15 41 50 36 47 31 40 30 45 53 40 49 34 42 45 53 58 47 54 41 47 60 67 70 61 65 53 56 Altitude loss during conventional stall recovery as ...

Page 349: ...h Propeller CROSSWIND 3rd Edition Rev 0 6 CROSSWIND Maximum demonstrated crosswind is 22 Kts Example Given Find Wind direction with respect to aircraft longitudinal axis 30 Headwind 17 5 Kts Wind speed 20 Kts Crosswind 10 Kts FIG 5 3 CROSSWIND CHART ...

Page 350: ... 50 ft AGL 246 303 367 436 330 1000 Ground Roll 159 195 236 280 216 At 50 ft AGL 274 337 407 485 373 2000 Ground Roll 174 214 258 307 234 At 50 ft AGL 301 370 447 532 404 3000 Ground Roll 191 234 283 336 252 At 50 ft AGL 330 406 491 584 438 4000 Ground Roll 209 256 309 367 272 At 50 ft AGL 361 444 537 639 473 5000 Ground Roll 228 280 338 402 294 At 50 ft AGL 396 487 588 700 511 6000 Ground Roll 25...

Page 351: ... 268 320 242 1000 Ground Roll 116 143 172 205 158 At 50 ft AGL 201 247 298 355 273 2000 Ground Roll 128 157 189 225 171 At 50 ft AGL 220 271 327 390 296 3000 Ground Roll 140 172 207 246 185 At 50 ft AGL 242 297 359 428 321 4000 Ground Roll 153 188 226 269 199 At 50 ft AGL 264 326 393 468 346 5000 Ground Roll 167 205 248 294 215 At 50 ft AGL 290 357 431 513 374 6000 Ground Roll 183 225 271 322 232 ...

Page 352: ...3 210 249 189 1000 Ground Roll 91 112 135 160 124 At 50 ft AGL 157 193 233 277 213 2000 Ground Roll 100 122 148 175 134 At 50 ft AGL 172 211 256 304 231 3000 Ground Roll 109 134 162 192 144 At 50 ft AGL 189 232 280 334 250 4000 Ground Roll 119 146 177 210 156 At 50 ft AGL 206 254 307 365 270 5000 Ground Roll 130 160 193 230 168 At 50 ft AGL 226 278 336 400 292 6000 Ground Roll 143 175 212 251 181 ...

Page 353: ...376 248 500 8000 58 552 395 255 129 400 10000 56 426 272 135 11 300 12000 55 300 149 15 107 200 14000 53 175 27 105 224 100 550 S L 64 1263 1078 913 765 977 2000 62 1123 941 779 632 867 4000 61 983 804 645 501 757 6000 60 843 668 511 370 647 8000 58 704 531 378 239 537 10000 57 565 396 245 108 427 12000 55 427 261 112 21 317 14000 54 289 126 20 151 207 500 S L 63 1438 1238 1059 898 1128 2000 62 12...

Page 354: ... 8000 64 698 539 397 268 544 10000 63 570 413 274 148 442 12000 62 442 289 152 28 341 14000 61 315 165 30 91 239 550 S L 68 1424 1240 1076 928 1140 2000 67 1284 1104 942 797 1030 4000 66 1145 968 809 666 921 6000 65 1006 832 676 536 812 8000 64 868 697 544 406 702 10000 63 730 562 412 276 593 12000 62 593 427 280 147 483 14000 61 456 294 149 18 374 500 S L 68 1606 1410 1235 1077 1303 2000 67 1457 ...

Page 355: ...TAS F C PWR KTAS F C PWR KTAS F C lt hr lt hr lt hr 2388 26 4 98 125 25 7 93 125 24 3 88 124 23 1 2260 26 4 92 122 25 87 123 23 6 83 123 22 4 2260 26 88 120 23 9 84 121 22 6 79 121 21 5 2260 24 74 110 20 70 110 18 9 66 109 18 2260 22 59 97 16 56 95 15 1 53 91 14 3 2260 20 50 85 13 4 47 77 12 7 45 73 12 1 Propeller RPM Fuel Consumption Weight 580 kg Pressure Altitude 6000 ft ISA 30 C 15 C ISA 15 C ...

Page 356: ...1 115 18 7 2260 21 1 75 116 20 3 71 115 19 2 67 113 18 2 2260 20 68 109 18 3 64 107 17 2 60 104 16 3 2260 18 55 94 14 9 52 86 14 49 82 13 3 Propeller RPM Fuel Consumption Weight 580 kg Pressure Altitude 12000 ft ISA 30 C 15 C ISA 15 C ISA 30 C 45 C RPM MAP inHg PWR KTAS F C PWR KTAS F C PWR KTAS F C lt hr lt hr lt hr 2388 18 8 71 113 18 8 67 111 17 7 64 105 16 7 2260 18 8 68 111 18 2 64 109 17 2 6...

Page 357: ...28 340 352 335 1000 Ground Roll 121 134 146 158 140 At 50 ft AGL 320 333 345 357 339 2000 Ground Roll 126 139 151 164 144 At 50 ft AGL 325 338 350 363 343 3000 Ground Roll 131 144 157 170 149 At 50 ft AGL 330 343 356 369 348 4000 Ground Roll 136 149 163 177 153 At 50 ft AGL 335 348 362 376 352 5000 Ground Roll 141 155 169 183 158 At 50 ft AGL 340 354 368 382 357 6000 Ground Roll 146 161 176 190 16...

Page 358: ...0 Ground Roll 96 105 115 124 110 At 50 ft AGL 295 304 314 323 309 2000 Ground Roll 99 109 119 129 114 At 50 ft AGL 298 308 318 328 313 3000 Ground Roll 103 113 124 134 117 At 50 ft AGL 302 312 323 333 316 4000 Ground Roll 107 117 128 139 121 At 50 ft AGL 306 316 327 338 320 5000 Ground Roll 111 122 133 144 124 At 50 ft AGL 310 321 332 343 323 6000 Ground Roll 115 127 138 150 128 At 50 ft AGL 314 3...

Page 359: ...7 1000 Ground Roll 79 87 95 103 92 At 50 ft AGL 278 286 294 302 291 2000 Ground Roll 82 90 98 107 95 At 50 ft AGL 281 289 297 306 294 3000 Ground Roll 85 94 102 111 99 At 50 ft AGL 284 293 301 310 298 4000 Ground Roll 88 97 106 115 102 At 50 ft AGL 287 296 305 314 301 5000 Ground Roll 92 101 110 119 106 At 50 ft AGL 291 300 309 318 305 6000 Ground Roll 95 105 114 124 110 At 50 ft AGL 294 304 313 3...

Page 360: ...361 226 466 5000 612 447 298 165 415 6000 547 383 235 103 363 7000 482 319 173 42 312 550 S L 1116 924 753 601 819 1000 1044 854 684 530 763 2000 972 782 615 462 706 3000 899 710 545 396 648 4000 827 640 476 327 592 5000 753 570 407 258 535 6000 681 500 337 191 477 7000 608 428 267 122 421 500 S L 1268 1060 874 706 945 1000 1190 982 798 631 885 2000 1110 905 722 558 822 3000 1031 829 645 482 760 4...

Page 361: ...ge VP5 19 Section 5 Performances Variable Pitch Propeller NOISE DATA 3rd Edition Rev 0 13 NOISE DATA Noise level determined in accordance with ICAO Annex 16 6th Ed July 2011 Vol I Chapter 10 is 68 63 dB A ...

Page 362: ...Page VP5 20 Section 5 Performances Variable Pitch Propeller NOISE DATA 3rd Edition Rev 0 INTENTIONALLY LEFT BLANK ...

Page 363: ...3rd Edition Rev 0 SECTION 6 WEIGHT AND BALANCE Apply following pages replacement procedure Supplement A13 Limitations page Basic AFM Limitations page VP6 11 REPLACES 6 11 VP6 12 REPLACES 6 12 VP6 13 REPLACES 6 13 VP6 14 REPLACES 6 14 Supplement A13 pages replacement instructions ...

Page 364: ...Page A13 14 Section 9 Supplements Supplement no A13 Variable Pitch Propeller 3rd Edition Rev 0 INTENTIONALLY LEFT BLANK ...

Page 365: ...ine and accessories B Landing gear C Electrical system D Instruments E Avionics the following information describes each listing Part number to uniquely identify the item type Item description Serial number Weight in kilograms Distance in meters from datum Items marked with an asterisk are part of basic installation Equipment marked with X in the Inst column are those actually installed on board r...

Page 366: ...oil valve 26 9 9100 000 0 20 0 20 A14 Governor Jihostroj P 110 030 A 1 0 0 25 LANDING GEAR AND ACCESSORIES B1 Main gear spring leafs p n 92 8 300 1 5 700 1 94 B2 Main gear wheel rims Cleveland 40 78B 2 050 1 94 B3 Main gear tires Air Trac 5 00 5 AA1D4 2 580 1 94 B4 Disk brakes Cleveland 30 9 0 800 1 94 B5 Nose gear wheel rim p n 92 8 880 1 1 300 0 310 B6 Nose gear tire Sava 4 00 6 1 200 0 460 B7 N...

Page 367: ...ity Ind Road GmbH XID4800 0 56 1 35 D15 Amperometer Ind VDO 190 037 001G or Speed Com Instruments 0203 0 10 1 35 D16 Fuel Pressure Ind UMA 4 360 007U 0 13 1 35 D17 Oil pressure indicator Sorlini SOR 50 0 10 1 35 D18 RPM indicator Sorlini SOR 52 0 10 1 35 D19 Oil temperature indicator Sorlini SOR 54 0 10 1 35 D20 CHT temperature indicator Sorlini SOR 53 0 10 1 35 D21 Voltmeter Indicator Sorlini SOR...

Page 368: ...4 3 30 E17 VOR ILS Antenna Command Industries CI 138C 0 26 5 80 E18 ELT Antenna Kit Model ME 406 0 21 2 70 E19 Fire Extinguisher Enterprises Ltd BA51015 3 2 20 2 32 E20 First Aid Kit 0 28 2 30 E21 Altitude Encoder Amery King Ak 30 0 25 1 00 E22 Emergency Hammer Dmail 108126 0 35 2 30 E23 ADF Bendix King KR87 1 38 1 35 E24 ADF Antenna Bendix King KA44B 1 89 2 05 E25 Comm Garmin SL40 1 50 1 35 E26 F...

Page 369: ...v 0 SECTION 7 AIRFRAME AND SYSTEM DESCRIPTION Apply following pages replacement procedure Supplement A13 Limitations page Basic AFM Limitations page VP7 3 REPLACES 7 3 VP7 4 REPLACES 7 4 VP7 7 REPLACES 7 7 VP7 8 REPLACES 7 8 Supplement A13 pages replacement instructions ...

Page 370: ...Page A13 16 Section 7 Airframe and Systems description 3rd Edition Rev 0 INTENTIONALLY LEFT BLANK ...

Page 371: ...ailerons differentially Aileron trimming is carried out on ground through a small tab positioned on left aileron Flaps are extended via an electric servo actuator controlled by a switch on the instrument panel Flaps act in continuous mode the indicator displays the two positions relative to takeoff 15 and landing 40 A breaker positioned on the right side of the instrument panel protects the electr...

Page 372: ...is pulled fully outward from the instrument panel carbs receive maximum hot air During normal operation the knob is OFF 4 2 CABIN HEAT The cabin heat control knob is positioned on the lower left side of the instrument panel when knob is pulled fully outward cabin receives maximum hot air Vents are located by the rudder pedals and above instrument panel If necessary outside fresh air can be circula...

Page 373: ...GGAGE COMPARTMENT The Luggage compartment is located behind the pilots seats Luggage shall be uniformly distributed on utility shelf and its weight shall not exceed 20kg Tie down luggage using adjustable tie down net WARNING Before loading luggage check aircraft s weight and CG location see Sect 6 ...

Page 374: ...ing water cooled heads and air cooled cylinders twin carburetors inte grated reduction gear with torque damper Maximum rating 98 6hp 73 5kW 5800 rpm min 2388 rpm min prop Gear reduction ratio 2 4286 1 Max oil consumption Max 0 1 litres hour 6 2 PROPELLER Manufacturer Hoffmann Propeller Model HOV352F1 C170FQ 8 N of blades 2 Diameter 1780 mm no reduction permitted Type Variable pitch wood GOVERNOR M...

Page 375: ...tional Controls 3rd Edition Rev 0 SUPPLEMENT NO A14 RUDDER AND THROTTLE ADDITIONAL CONTROLS Record of Revisions Rev Revised page Description of Revision Tecnam Approval EASA Approval or Under DOA Privileges DO OoA HDO 0 List of Effective Pages Page Revision A14 1 thru 54 Rev 0 ...

Page 376: ...14 Rudder and Throttle Additional Controls 3rd Edition Rev 0 INDEX INTRODUCTION 3 GENERAL 3 LIMITATIONS 5 EMERGENCY PROCEDURES 6 NORMAL PROCEDURES 23 PERFORMANCES 43 WEIGHT AND BALANCE 45 AIRFRAME AND SYSTEMS DESCRIPTION 47 GROUND HANDLING SERVICE 53 ...

Page 377: ...rake System A05 Central Throttle Control System A013 Variable Pitch Propeller The related equipment in fact cannot be incorporated when the design change of this Supplement A14 is embodied in the P2002JF GENERAL The Design Change MOD2002 141 provides the installation of additional hand con trols which allows disabled pilots to fly the airplane without relying on the rudder pedals for directional c...

Page 378: ...Page A14 4 Section 1 General Additional Controls Introduction 3rd Edition Rev 0 INTENTIONALLY LEFT BLANK ...

Page 379: ...Page A14 5 Section 3 Emergency procedures Additional Controls Introduction 3rd Edition Rev 0 LIMITATIONS Standard basic AFM limitations are unchanged ...

Page 380: ...es which must be known by heart and executed in the correct and com plete sequence as soon as possible as the failure is detected and recognised These procedures characters are boxed and highlighted an example is shown below BEFORE ROTATION ABORT TAKE OFF 1 Throttle Hand Control IDLE rotate fully counter clockwise or Throttle standard control IDLE fully out 2 Rudder Keep heading control 3 4 b Othe...

Page 381: ... 1 ELECTRIC POWER SYSTEM MALFUNCTION Generator Light Illuminates Generator light may illuminate for a faulty alternator or when voltage is above 16V in this case the over voltage sensor au tomatically shuts down the alternator 1 Generator switch OFF 2 Master switch OFF 3 Generator switch ON 4 Master switch ON If the problem persists 5 Generator switch OFF 6 Non vital electric equipment Shed WARNIN...

Page 382: ...the electrical fuel pump light central annunciator panel light is OFF the rea son can be Electrical fuel pump not electrically fed Light inoperative Apply the following procedure 1 Electrical fuel pump switch OFF 2 Electrical fuel pump switch ON 3 Fuel pressure CHECK raise If fuel pressure doesn t build up Land as soon as possible monitoring fuel pressure Fuel Pump Light ...

Page 383: ... be inoperative act as follows 1 Breakers CHECK 2 Trim switch LH RH CHECK for correct position 3 Speed adjust to control aircraft without excessive stick force 4 Land aircraft as soon as possible Runaway In event of trim runaway act as follows 1 Trim disconnect switch OFF 2 Speed adjust to control aircraft without excessive stick force 3 Land aircraft as soon as possible ...

Page 384: ...ames hot engine compartment spilling fuel tanks Pilots can grab the additional external handles to help themselves exiting the cockpit Simulated emergency evacuations even if there is not a maximum escape time given from the rules CS VLA is strongly recommended during the training of disabled people Simulated emergency evacuations should be part of on ground training 3 ENGINE SECURING Following pr...

Page 385: ... the right 3 Flaps as needed WARNING Stall speed increases with bank angle and longitudinal load factor Acoustic stall warning will in any case provide a cor rect anticipated clue of incipient stall At or right before touch down 4 Throttle Hand Control IDLE rotate fully counter clockwise or Throttle standard control IDLE fully out 5 Ignition key OFF 6 Fuel selector valve OFF 7 Electric fuel pump O...

Page 386: ...toring fuel pressure If engine stops 1 5 Land as soon as possible applying forced landing procedure See Para 7 4 3 2 Oil Pressure limits exceedance If oil pressure exceeds upper limit 7 bar 1 Throttle Hand Control or standard throttle REDUCE engine power as practical 2 OIL PRESS and OIL TEMP CHECK within limits 3 Land as soon as practical If oil pressure is under the lower limit 0 8 bar 1 Throttle...

Page 387: ...CE Minimum practical If oil temperature does not decrease 2 Airspeed INCREASE If oil temperature does not come back within limits the thermostatic valve if embodied regulating the oil flow to the heat exchangers could be damaged or an oil leakage can be present in the oil supply line 3 Land as soon as practical If engine roughness vibrations erratic behaviour or high CHT is detected 4 Land as soon...

Page 388: ... Rev 0 4 3 4 CHT limit exceedance If CHT is above 135 C 1 Throttle Hand Control or standard throttle REDUCE Minimum practical 2 Land as soon as practical If CHT continues to rise and engine shows roughness or power loss 3 Land as soon as possible applying forced landing procedure See Para 7 ...

Page 389: ...tity indicator CHECK 4 Fuel Selector change the fuel feeding tank 5 Ignition key position BOTH 6 Ignition key position START 7 Throttle Hand Control or standard throttle SET as required CAUTION After engine restart if practical moderate propeller rpm and throttle increase to allow OIL and CHT temperatures for stabilizing in the green arcs If the fuel quantity in the tank which feeds the stopped en...

Page 390: ...OFF 6 Generator Master Switches OFF 7 Parking Brake ENGAGED 8 Aircraft Evacuation carry out immediately 6 2 ENGINE FIRE DURING TAKEOFF BEFORE ROTATION ABORT TAKE OFF 1 Throttle Hand Control IDLE ROTATE COUNTER CLOCKWISE or Throttle standard control IDLE fully out 2 Rudder Keep heading control 3 Brakes As required With aircraft under control 1 Fuel Selector OFF 2 Electrical fuel pump OFF 3 Ignition...

Page 391: ... ELECTRICAL SMOKE IN CABIN DURING FLIGHT 1 Cabin heating OFF 2 Cabin vents OPEN 3 Canopy OPEN if necessary 4 Try to choke the fire Direct the fire extinguisher towards flame base If smoke persists 1 Generator Master switches OFF 2 Land as soon as possible and evacuate the aircraft CAUTION If the MASTER SWITCH is set to OFF consider that flaps extension and pitch trim operation would be not possibl...

Page 392: ...conditions every 1000ft Above Ground Level it is possible to cover ca 2 NM ca 4 km 7 2 POWER ON FORCED LANDING 1 Airspeed 69 KIAS 2 Flaps UP 3 Locate the most suitable terrain for emergency landing plan to approach it upwind 4 Safety belts Tighten 5 Canopy locks CHECK LOCKED When certain to land right before touch down 6 Flaps as necessary 7 Fuel selector valve OFF 8 Electric fuel pump OFF 9 Ignit...

Page 393: ...st Complete 2 Flaps Land 3 Land the aeroplane on the side of runway opposite to the defective tyre to compensate the change in direction which is to be expected during final rolling 4 Touchdown with the GOOD TIRE FIRST and hold aircraft with the flat tyre off the ground as long as possible by mean of aileron and rudder control As aircraft stops 5 Engine securing Perform see Para 3 6 Airplane evacu...

Page 394: ...ly counter clockwise or Throttle standard control IDLE fully out 2 Rudder full in the opposite direction of the spin 3 Stick centralize and hold neutral As the spin stops 4 Rudder SET NEUTRAL 5 Aeroplane attitude smoothly recover avoiding speeds in excess of VNE and maximum load factor n 3 8 6 Throttle Hand Control Readjust to restore engine power WARNING Keep full rudder against rotation until sp...

Page 395: ... rain snow or hail and OAT less than 10 C Airbox car burettor heater is designed to help prevent carburettor ice less ef fectively functions as a de icing system 1 Carburettor heating ON 2 Immediately fly away from icing conditions changing altitude and direction of flight out of clouds visible moisture precipita tions 3 Controls surfaces continue to move to maintain their movabil ity 4 Propeller ...

Page 396: ...Page A14 22 Section 3 Emergency procedures Additional Controls OTHER EMERGENCIES 3rd Edition Rev 0 INTENTIONALLY LEFT BLANK ...

Page 397: ...iarization shall be executed to the extent required to achieve and master the new system granting at least normal PPL flight toleranc es and up to the point that pilot s self confidence is sufficiently reinforced P2002JF aircraft incorporating Additional Flight Controls MOD2002 141 shall be operated by authorised crew only as per competent Civil Aviation Authority specific approval Execute flight ...

Page 398: ...rol mounted switch flap selector switch to normal and hand control positions pitch trim standard controls pitch trim selector switch pitch trim disconnect canopy locking system emergency egress handles canopy hammer just behind your seat in the central upper position ELT switch located on the RH panel Fire Extinguisher baggage compartment 2 RH seated pilot safety pilot or Flight Instructor Examine...

Page 399: ...Page A14 25 Section 4 Normal Procedures Additional Controls Checklists 3rd Edition Rev 0 Complete view of cockpit panel equipped with MOD2002 141 Fig A14 2 Cockpit view ...

Page 400: ...ing Simulate as possible sudden obstacle avoidance e g person nel vehicles etc so that pilots using hand controls can reinforce instinctive control and reaction to avoid unwanted a c motions and mishandling Especially for pilots with previous flight experience on a c equipped with side steering wheels or side stick flight controls errors are possible as Additional Hand Control engine throttle rota...

Page 401: ...instinctual directional control and reaction and will be useful for X wind take off take off reject and landing roll out Avoid brakes wear and over temperature after repetitive high speed taxiing During acceleration and stop exercise it is useful to visualise the following Addi tional Hand Control use scheme Acceleration increase power while pulling the Additional Hand Control Deceleration decreas...

Page 402: ...ltitude and go around practice shall be done as well Later on touch and goes can be planned and executed by mean of hand controls solely Training is also suggested for en route phase of flight coordinated turns climbs power settings and flap configuration changes climbing turns Typical tolerances to be obtained during training might be Airspeed 5kias Sideslip 1 2 ball on slip indicator Engine 100r...

Page 403: ...applicable and 620 kg if Supplement A12 Increased MTOW 620 KG is ap plicable MTOW FLAPS 580kg 600 kg 620 kg Rotation Speed in take off VR T O 42 KIAS 42 KIAS 42 KIAS Best Angle of Climb Speed VX 0 56 KIAS 56 KIAS 56 KIAS Best Rate of Climb speed VY 0 66 KIAS 66 KIAS 66 KIAS Approach speed T O 66 KIAS 66 KIAS 66 KIAS Final Approach Speed FULL 51 KIAS 51 KIAS 51 KIAS Manoeuvring speed VA 0 96 KIAS 9...

Page 404: ...I Master switch OFF J Baggage check first aid kit canopy hammer ELT fire extinguisher lug gage stowage and fastened with restraint net AIRCRAFT WALK AROUND To perform the aircraft walk around carry out the checklist according to the station shown in Figure 4 1 WARNING Visual inspection is defined as follows check for defects cracks detachments excessive play unsafe or improper installation as well...

Page 405: ... Close filler cap B Remove protection plug if provided and check the Pitot tube and the stat ic ports mounted on left wing are unobstructed do not blow inside vents C Left side leading edge and wing skin visual inspection D Left aileron trim tab and hinges visual inspection check free of play fric tion Left tank vent check for obstructions E Left flap and hinges visual inspection F Left main landi...

Page 406: ...e and rubber shock absorber discs condition R Propeller and spinner condition check for nicks cracks dents and other defects propeller should rotate freely Check fixing and lack of play be tween blades and hub S Open engine cowling 1 Check no foreign objects are present 2 Verify coolant level in the overflow bottle level must be between min and max mark Replenish if required 3 Only before the firs...

Page 407: ...ong flights oil should be added so that the oil level reaches the max mark 6 Inspect fuel circuit for leakages 7 Check integrity of silent block mountings 8 Check connection and integrity of air intake system visually inspect that ram air intake is unobstructed 9 Check that all parts are secured or safetied T Close engine cowling check for proper alignment of cam locks U Visual inspection of the L...

Page 408: ...landing taxiing turns due to Rotax engine spring loaded throttle cable devices 5 Circuit Breakers check all IN 6 Master switch ON Check generator light ON and Voltage at least 10 5 V 7 Electric fuel pump ON check for audible pump noise and fuel pressure build up 8 Electric fuel pump OFF 9 Avionic Master switch if installed ON instruments check then set in OFF position 10 Flap control 10 1 Switch s...

Page 409: ...re flight inspection External inspection In absence of RH seat occupant fasten seat belts around the seat to prevent any interference with the aeroplane flight control opera tion and with rapid egress in an emergency 15 Canopy Closed and locked CAUTION Avionic Master switch if installed must be set OFF during the en gine s start up to prevent avionic equipment damage NOTE ...

Page 410: ...esent in the area close to the propeller Forward lower sector visibility is not possible from inside the cockpit 7 Ignition key BOTH 8 Ignition key START 9 Check oil pressure rise within 10 sec maximum cold value 7 bar 10 Generator switch ON 11 Ammeter check green 12 Voltmeter check more than 14V 13 Engine instruments Check 14 Choke OFF 15 Propeller rpm 1000 1200 rpm 16 Electric fuel pump OFF 17 C...

Page 411: ...uel pump ON 5 Fuel valve select the fullest tank 6 Fuel pressure check 7 Propeller speed rotate hand throttle control clock wise to 1640 rpm a Ignition test select LEFT check speed drop within 130 propeller rpm b Select BOTH check propeller speed 1640 rpm c Select RIGHT check speed drop within 130 propeller rpm d Maximum difference of speed between LEFT and RIGHT 50 rpm e Select BOTH check propell...

Page 412: ...MTOW 580kg MTOW 600kg MTOW 620kg Rotation Speed VR 42 KIAS 42 KIAS 42 KIAS 7 Flaps retract above flap retraction speed 50 KIAS MTOW 580kg MTOW 600kg MTOW 620kg Best of Rate Climb Speed VY 66 KIAS 66 KIAS 66 KIAS 8 Electric fuel pump OFF 9 Fuel pressure check green arc 10 Propeller speed reduce at or below 2250 rpm Indicated airspeed higher than Vy 67 Kias can be used for pro longed climb legs in o...

Page 413: ...Page A14 39 Section 4 Normal Procedures Additional Controls Checklists 3rd Edition Rev 0 Climb Performances at VCLMB 85kIAS ...

Page 414: ...ding Light ON 4 Throttle friction adjust CAUTION Pilots shall adjust throttle friction in order to grant smooth and precise throttle control through both throttle systems Hand Control rotation Normal Throttles push pull and at the same time it shall be ensured that no inadvertent throttle increase may happen after sudden a c decelerations e g during braking landing taxiing turns due to Rotax engin...

Page 415: ...FF 3 Landing light OFF 3 13 ENGINE SHUT DOWN 1 Parking brake engage 2 Keep engine running at 1200 rpm for about one minute in order to reduce la tent heat 3 Avionic equipment OFF 4 Ignition key OFF keys extracted 5 Strobe light OFF 6 Master Generator switches OFF 7 Fuel selector valve OFF 3 14 POSTFLIGHT CHECK 1 Flight controls lock by mean of seat belts 2 Wheel chocks and wing mooring lines Set 3...

Page 416: ...Page A14 42 Section 4 Normal Procedures Additional Controls Checklists 3rd Edition Rev 0 INTENTIONALLY LEFT BLANK ...

Page 417: ...ev 0 PERFORMANCES The performances of the basic AFM apply except for the followings 1 GENERAL INFORMATION As additional Hand Control is used Where indicated Replace with Throttle lever Throttle Hand control Full forward Full power rotate fully clockwise IDLE Rotate fully counter clockwise ...

Page 418: ...Page A14 44 Section 5 Performances Additional Controls General Information 3rd Edition Rev 0 INTENTIONALLY LEFT BLANK ...

Page 419: ... of Rudder and Throttle Additional Controls Design Change MOD2002 141 must be completed by an additional group of items This paragraph displays only those additional items that can be considered as a removable kit Other additional items remains on board when the aircraft is returned to the standard configuration and will be computed during the aircraft weighing according to sect 6 of the basic AFM...

Page 420: ...TE RIF DESCRIPTION WEIGHT kg DATUM m MOMENT kg m BASIC AIRCRAFT REFER TO WEIGHING REPORTS 3 AND 4 OF THE BASIC AFM We _____ M _____ ADDITIONAL CONTROLS REFER TO EQUIPMENT LIST 1 1 OF THIS SUPPLEMENT A _____ B _____ TOTAL A C EMPTY WT ______ MT ______ CENTER OF GRAVITY C G EMPTY MT WT _______ m C G EMPTY C G EMPTY 1 370 100 _______ Use the 5 of the basic AFM to determine the aircraft s take off CG ...

Page 421: ...ft must be configured according to the MOD2002 146 Stick mounted brake hand control that provides the installation of a brake control lever on the standard left stick WING The right wing leading edge has been reinforced to enable its use as support Reinforce ments are located along the wing leading edge span and at the fuselage attachment point FUSELAGE The support for the directional and throttle...

Page 422: ...Page A14 48 Section 7 Airframe and systems description Rudder and Flight Additional Controls 3rd Edition Rev 0 Fig A14 5 Hand control and Brake lever Fig A14 6 Instrument panel ...

Page 423: ... throttle and flap control Directional Control The central stick acts on a lever installed on the support located on the forward fuselage struc ture and connected to the basic directional control system The central stick is then mechani cally connected to rudder pedals Movement along stick axis acts on rudder and steering see Fig A14 2 PUSH for rudder and nose wheel deployment to left A C nose lef...

Page 424: ...k is mechanically connected to the airplane engine control system then actua tion of the central stick moves the throttle lever on the instrument panel left side Movements around stick axis act on engine as follows turn clockwise to increase power turn counter clockwise to decrease power Proper set stops approximately 45 warn pilot of the IDLE and FULL positions CAUTION Pilots shall adjust throttl...

Page 425: ...of the brakes system an additional pump has been installed on standard left stick this pump is connected to the airplane brake system and is operated by a lever see Fig A14 4 Pilot pulls lever to operate brakes Fig A14 9 Brakes system CANOPY In order to ease access to cabin additional external handles have been installed on the canopy see Fig A14 4 Fig A14 10 External Handles on Canopy Structure ...

Page 426: ...Page A14 52 Section 7 Airframe and systems description Rudder and Flight Additional Controls 3rd Edition Rev 0 INTENTIONALLY LEFT BLANK ...

Page 427: ... apply In addition considering the following CLEANING Normal care is required for rudder and throttle additional controls This includes keep ing all joints clean and free of dirt and drying them thoroughly to prevent the onset of corrosion The use of ACF 50 compound in addition with the greases for joint and bearing lubri cation is allowed to prevent the corrosion accretion ...

Page 428: ...Page A14 54 Section 8 Ground Handling Service Rudder and Flight Additional Controls 3rd Edition Rev 0 INTENTIONALLY LEFT BLANK ...

Page 429: ... SUPPLEMENT NO A15 GARMIN GTN 750 GPS VHF COMM NAV Record of Revisions Rev Revised page Description of Revision Tecnam Approval EASA Approval or Under DOA Privileges DO OoA HDO 0 List of Effective Pages Page Revision Page Revision A15 1 Rev 0 A15 4 Rev 0 A15 2 Rev 0 A15 5 Rev 0 A15 3 Rev 0 A15 6 Rev 0 ...

Page 430: ...ion 9 Supplements Supplement no A15 GARMIN GTN 750 GPS VHF COMM NAV 3rd Edition Rev 0 INDEX INTRODUCTION 3 GENERAL 3 LIMITATIONS 4 EMERGENCY PROCEDURES 5 NORMAL OPERATION 6 PERFORMANCE 6 WEIGHT AND BALANCE 6 SYSTEMS 6 ...

Page 431: ...udes a GPS WAAS antenna a VOR ILS an tenna and a VHF Comm antenna 3 The main function of the VHF Comm is to allow communication with the control tower 4 The VOR ILS function is to receive and demodulate VOR LOC GS sig nals 5 The GPS section is dedicated to signal acquisition from the GPS satellite system and to furnish real time information with respect to position speed and time 6 With appropriat...

Page 432: ...Page A15 4 Section 9 Supplements Supplement no A15 GARMIN GTN 750 GPS VHF COMM NAV 3rd Edition Rev 0 LIMITATIONS No variations ...

Page 433: ...manifestly wrong the pilot must continue flight reverting to visual refer ences 2 If the message LOI appears in the lower left portion of the display the RAIM function is unavailable The pilot must use the VLOC receiver or revert to visual references 3 In the event of a loss of COM radio tuning pressing the volume knob for 2 seconds will automatically tune in the 121 500MHz emergency frequency ...

Page 434: ...e specific aircraft configuration an external indicator is installed such as a Garmin GI 106A analog CDI indicator b Garmin GDU 620 digital display if MOD 2002 041 is installed 3 The following default settings must be keyed in in the System Units page of the GTN 750 receiver before any other operation DIS SPD nm kt select navigation unit to nautical miles and knots ALT VS ft fpm select altitude to...

Page 435: ...Page A15 7 Section 9 Supplements Supplement no A15 GARMIN GTN 750 GPS VHF COMM NAV 3rd Edition Rev 0 INTENTIONALLY LEFT BLANK ...

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