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Tecnam P2008 JC, Руководство по эксплуатации самолета


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AFMS for VFR NIGHT equipped airplanes 

 

          Page N7 - 2 

 

Section 7 – Airframe and Systems description 

INTRODUCTION

 

Ed. 1, Rev 0 

 

1.

 

INTRODUCTION 

This Section provides description and operation of the aircraft and its systems. 

2.

 

AIRFRAME 

 
P2008 JC’s airframe can be divided in the following main groups, as highlighted be-
low on: 
 

1) Wings 
2) Fuselage 
3) Empennage 
4) Landing gear 

 

 

Fig. 7-1.P2008JC

 

A

IRFRAME

 

2.1.

 

W

ING

 

Each  wing  is  connected  to  the  fuselage  by  means  of  two  bolt  attachments  and  a 
single strut brace per side. The wings are made up of a central light alloy torsion 
box; a light alloy leading edge is attached to the front spar whereas the flap (slot-
ted) and the aileron (“frise”) are attached to a rear spar through two hinges each. 
The torsion  box  consists of a front  and rear spar that represent  its front and rear 
vertical  walls;  a  series  of  ribs  and  wrap-around  panels  complete  the  structure. 
Front and rear spars are integrated with wing-fuselage attachment fittings.  
The ailerons and flaps are made by an aluminium spar attached to a formed sheet 
metal leading edge and metal ribs; an aluminium skin surrounds the aileron struc-
ture. 

Содержание P2008 JC

Страница 1: ...R SERIAL NUMBER REGISTRATION MARKINGS This Aircraft Flight Manual is approved by European Aviation Safety Agency EASA and applies only EASA CS VLA certified airplanes This Manual must be carried in the airplane at all times The airplane has to be operated in compliance with procedures and limitations contained herein Costruzioni Aeronautiche TECNAM srl Via Maiorise CAPUA CE Italy Tel 39 0 823 9975...

Страница 2: ...Page 0 2 Ed 1 Rev 0 Aircraft Flight Manual INDEX SECTION 0 INDEX 1 RECORD OF REVISIONS 3 2 LIST OF EFFECTIVE PAGES 8 3 FOREWORD 11 4 SECTIONS LIST 12 ...

Страница 3: ...ry tocompletely reissue a publication for contents and format changes 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 resul...

Страница 4: ...aft Flight Manual RECORD OF REVISIONS Rev Revised page Description of Revision Tecnam Approval EASA Approval or Under DOA Privileges DO OoA HDO 0 First issue G Paduano M Landi M Oliva EASA approved as part of Type Investigation ...

Страница 5: ...Page 0 5 Ed 1 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 ...

Страница 6: ...Page 0 6 Ed 1 Rev 0 Aircraft Flight Manual INTENTIONALLY LEFT BLANK ...

Страница 7: ...Aircraft Flight Manual Page 0 7 Ed 1 Rev 0 INTENTIONALLY LEFT BLANK ...

Страница 8: ...tsare embodied Pages affected by the current revision are indicated by an asterisk following the re vision code Edition 1 Rev 0 30th July 2013 Section Pages Revision Section 0 Pages 1 thru 12 Rev 0 Section 1 Pages 1 thru 14 Rev 0 Section 2 Pages 1 thru 30 Rev 0 Section 3 Pages 1 thru 22 Rev 0 Section 4 Pages 1 thru 18 Rev 0 Section 5 Pages 1 thru 16 Rev 0 Section 6 Pages 1 thru 12 Rev 0 Section 7 ...

Страница 9: ...Ed 1 Rev 0 Aircraft Flight Manual Page 0 9 INTENTIONALLY LEFT BLANK ...

Страница 10: ...Ed 1 Rev 0 Aircraft Flight Manual Page 0 10 INTENTIONALLY LEFT BLANK ...

Страница 11: ...on 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 997538 airworthness tecnam...

Страница 12: ...ations Section 2 Emergency Procedures Section 3 Normal Procedures Section 4 Performance Section 5 Weight and balance Section 6 Airframe and Systems description Section 7 Ground Handling and Service Section 8 AFM Supplements Section 9 non approved Section approved Section partially approved Section ...

Страница 13: ...TRODUCTION 3 2 CERTIFICATION BASIS 3 3 WARNINGS CAUTIONS NOTES 3 4 THREE VIEW AND DIMENSIONS 4 5 ENGINE 6 6 PROPELLER 6 7 FLIGHT CONTROL SURFACES TRAVEL 7 8 SPECIFIC LOADINGS 7 9 ACRONYMS AND TERMINOLOGY 8 10 UNIT CONVERSION CHART 13 11 LITRES US GALLONS CONVERSION CHART 14 ...

Страница 14: ...Page 1 2 Section 1 General Ed 1 Rev 0 INTENTIONALLY LEFT BLANK ...

Страница 15: ...ncluding Amendment 1 and the Type Certificate No EASA A 583 has been issued on date 27th September 2013 Category of Airworthiness Normal Noise Certification Basis EASA CS 36 Amendment 2 3 WARNINGS CAUTIONS NOTES Following definitions apply to warnings cautions and notes used in the Aircraft Flight Manual WARNING means that the non observation of the corresponding procedure leads to an immediate or...

Страница 16: ...Page 1 4 Section 1 General THREE VIEW AND DIMENSIONS Ed 1 Rev 0 4 THREE VIEW AND DIMENSIONS Figure 1 General views ...

Страница 17: ... Ratio 0 8 Wing chord 1 373 m 4 5 ft Fuselage Overall length 6 93 m 22 9 ft Overall width 1 20 m 3 9 ft Overall height 2 67 m 8 8 ft Empennage Stabilator span 2 90 m 9 51 ft Stabilator area 2 03 m2 21 8 ft2 Vertical tail area 1 06 m2 11 4 ft2 Landing Gear Wheel track 1 8 m 5 9 ft Wheel base 1 94 m 6 4 ft Main gear tire 5 00 5 Nose Gear tire 5 00 5 ...

Страница 18: ...ed cylinders two carburetors integrated re duction gear box with torsional shock ab sorber and overload clutch Maximum power at declared rpm 73 5 kW 98 6hp 5800 rpm 5 minutes maximum 69 0 kW 92 5hp 5500 rpm continu ous 6 PROPELLER Manufacturer GT Propeller Model GT 2 173 VRR FW101 SRTC Blades One piece 2 blade fixed pitch construct ed of wood materials protective layer of laminate Diameter 1730 mm...

Страница 19: ...TRAVEL Ailerons Up 22 Down 14 2 Stabilator refer to Trailing Edge Up 4 Down 15 2 Stabilator trim tab refer to Trailing Edge Up 2 Down 12 1 Rudder RH 25 LH 25 2 Flaps 0 35 1 8 SPECIFIC LOADINGS MTOW 630 kg 1388lb Wing Loading 51 kg m2 10 6 lb sqft Power Loading 6 29 kg hp 14 09 lb hp ...

Страница 20: ...xtended 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 VO Operating Manoeuvring speed is the speed above the which it is not allowed to make full or abrupt control movement VS Stall Speed...

Страница 21: ...the official airport level QNH Theoretical atmospheric pressure at sea 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...

Страница 22: ... 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 the s...

Страница 23: ...Center of Gravity is the point at which the airplane or equipment would balance if suspended Its distance from the reference datum is found by dividing the total mo ment 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 we...

Страница 24: ...Section 1 General Ed 1 Rev 0 Page 1 12 INTENTIONALLY LEFT BLANK ...

Страница 25: ...8 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 2642 ...

Страница 26: ... 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 ...

Страница 27: ... 8 8 PAINT 8 9 PROPELLER 9 10 MAXIMUM OPERATING ALTITUDE 9 11 AMBIENT TEMPERATURE 9 12 POWERPLANT INSTRUMENTS MARKINGS 10 13 OTHER INSTRUMENTS MARKINGS 10 14 WEIGHTS 12 15 CENTER OF GRAVITY RANGE 14 16 APPROVED MANOEUVRES 16 17 MANOEUVRES LOAD FACTOR LIMITS 17 18 DEMONSTRATED CROSS WIND SAFE OPERATIONS 18 19 FLIGHT CREW 18 20 KINDS OF OPERATION EQUIPMENT LIST KOEL 19 21 LIMITATIONS PLACARDS 21 22 ...

Страница 28: ...Page 2 2 Section 2 Limitations Ed 1 Rev 0 INTENTIONALLY LEFT BLANK ...

Страница 29: ...ction 2 Limitations INTRODUCTION 1 INTRODUCTION Section 2 includes operating limitations instrument markings and basic placards necessary for safe operation of the aeroplane its engine standard systems and standard equipment ...

Страница 30: ...Page 2 4 Ed 1 Rev 0 Section 2 Limitations INTENTIONALLY LEFT BLANK ...

Страница 31: ...ed this speed in any operation VNO Maximum Structural Cruising speed 113 111 Do not exceed this speed except in smooth air and only with caution VA Design Manoeuvring speed 99 98 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 VO Operating Manoeuvring speed VFE Maximum flaps extended speed 71 7...

Страница 32: ... 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 48 113 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 113 145 Manoeuvres must be conducted with caution and only in smooth...

Страница 33: ...rop rpm engine Time max minutes Max T O 73 5 98 6 2388 5800 5 Max Cont 69 92 5 2265 5500 Temperatures Max CHT 135 C Min Max Oil 50 C 130 C Oil Pressure Minimum 12psi below 1440 propeller rpm Maximum 102 psi above 1440 propeller rpm CAUTION In event of cold starting operation it is permitted a maximum oil pressure of 7 bar for a short period Engine starting allowable temperature range OAT Min 25 C ...

Страница 34: ...nce to Rotax Maintenance Manual which prescribes dedicated checks due to the prolonged use of Avgas 6 LUBRICANT Recommended by Rotax BRAND DESCRIPTION SPECIFICATION VISCOSITY CODE SHELL AeroShell Sport Plus 4 API SL SAE 10 W 40 2 Use only oil with API classification SG or higher see Rotax SI 912 016 R4 for list of alternative recommended commercial brands and types 7 COOLANT LIQUID 100 Propylene G...

Страница 35: ...of laminate TYPE Fixed pitch DIAMETER 1730 mm no reduction is permitted 10 MAXIMUM OPERATING ALTITUDE Maximum operating altitude is 13000ft 3962 m MSL CAUTION At altitudes above 10000ft 3048 m up to and including 13000 ft 3962 m flight crew is recommended to use supplemental oxygen 11 AMBIENT TEMPERATURE Ambient temperature from 25 C to 50 C WARNING Flight in expected and or known icing conditions...

Страница 36: ... limit GREEN ARC Normal operating YELLOW ARC Caution RED LINE Maximum limit Propeller rpm 577 2265 2265 2388 2388 Oil temp C 50 50 130 130 CHT C 0 135 135 Oil pressure psi OP LOW WARNING 12 psi 102 Fuel press psi FP LOW WARNING 2 2 psi 2 2 7 26 7 26 13 OTHER INSTRUMENTS MARKINGS INSTRUMENT RED ARC Minimum limit GREEN ARC Normal operating YELLOW ARC Caution RED ARC Maximum limit Voltmeter 10 10 5 V...

Страница 37: ...Section 2 Limitations Ed 1 Rev 0 Page 2 11 INTENTIONALLY LEFT BLANK ...

Страница 38: ...s Ed 1 Rev 0 Page 2 12 14 WEIGHTS Condition Weight Maximum takeoff weight 630 kg 1388lb Maximum landing weight 630 kg 1388lb Baggage Compartment Maximum weight 20 kg 44lb Maximum specific pressure 12 5 kg dm2 256 lbs sq in ...

Страница 39: ...Section 2 Limitations Ed 1 Rev 0 Page 2 13 INTENTIONALLY LEFT BLANK ...

Страница 40: ...ust be levelled in the longitudinal plane Levelling Refer to the seat track supporting beams see procedure in Section 6 Forward limit 1 841 m 20 MAC aft of datum for all weights Aft limit 1 978 m 30 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 instruc tions ...

Страница 41: ...Section 2 Limitations Ed 1 Rev 0 Page 2 15 INTENTIONALLY LEFT BLANK ...

Страница 42: ...angle of bank is not more than 60 Recommended entry speeds for each approved manoeuvre are as follows Manoeuvre Speed KIAS Lazy eight 99 Chandelle 113 Steep turn max 60 99 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...

Страница 43: ...ED manOeuvREs Ed 1 Rev 0 Page 2 17 17 MANOEUVRES LOAD FACTOR LIMITS Manoeuvre load factors limits are as follows Positive Negative 4 g 2 g Manoeuvre load factors limits with flaps extended are as follows Positive 2 g Negative 0 g ...

Страница 44: ...ev 0 Page 2 18 18 DEMONSTRATED CROSS WIND SAFE OPERATIONS The aircraft controllability during take offs and landings has been demonstrated with a cross wind components of 15kts 19 FLIGHT CREW Minimum crew 1 pilot Maximum number of occupants 2 people including the pilot ...

Страница 45: ... operation may be required by national operational requirements and also depends on the airspace classification and route to be flown The owner is responsible for fulfilling these requirements Garmin G3X provides primary engine and electric system pa rameters information supported by caution warning lights in the annunciator panel and backup CHT indicator WARNING Garmin G3X indeed is NOT intended ...

Страница 46: ...uantity Indicators Analogue CHT indicator Garmin G3X suite Transponder Altitude Encoder Slip indicator Longitudinal Trim Indicator Flap Position Indicator COMM NAV equipment Audio Panel Marker beacon Landing Taxi Light Strobe Lights NAV Lights Annunciator Panel Breakers Panel Stall warning system First Aid Kit Hand held fire extinguisher ELT Pitot Heat Torch with spare batteries Cabin Light ...

Страница 47: ...he following plac ard reporting the speed limitations On the central side of the instrument panel the following placard is placed remind ing the observance of aircraft operating limitations according to installed equipment configuration see KOEL Para 20 On the right hand side of the instrument panel the following placard is placed re minding the observance for no smoking In the baggage compartment...

Страница 48: ...Section 2 Limitations Limitations placards Ed 1 Rev 0 Page 2 22 Below LH and RH Garmin G3X display and analogue instruments following plac ards are placed ...

Страница 49: ...Section 2 Limitations OTHER placards Ed 1 Rev 0 Page 2 23 22 OTHER PLACARDS Engine compartment placards Oil brakes reservoir placard ...

Страница 50: ...Section 2 Limitations OTHER placards Ed 1 Rev 0 Page 2 24 Usable fuel markings Allowed fuel placard Emergency exit placard Parking brake placard ...

Страница 51: ...Section 2 Limitations OTHER placards Ed 1 Rev 0 Page 2 25 Throttle marking Fuel selector valve marking Choke placard ...

Страница 52: ...Section 2 Limitations OTHER placards Ed 1 Rev 0 Page 2 26 Cabin heat defrost placard Carb heat placard Ignition key placard Master Generator placards ...

Страница 53: ...Section 2 Limitations OTHER placards Ed 1 Rev 0 Page 2 27 Flap indicator placard Backrest lever placard Safety equipment location placard Elt placard Battery placard ...

Страница 54: ...Section 2 Limitations OTHER placards Ed 1 Rev 0 Page 2 28 Annunciator panel Upper panel labels Switches labels Door lock lever ...

Страница 55: ...Section 2 Limitations OTHER placards Ed 1 Rev 0 Page 2 29 INTENTIONALLY LEFT BLANK ...

Страница 56: ...Section 2 Limitations OTHER placards Ed 1 Rev 0 Page 2 30 INTENTIONALLY LEFT BLANK ...

Страница 57: ...T0T0T0T0T0T0T0T0T0T0T0T0T0T0T0T0T0T0T0T0T0T0T0T0T0T0T0T0T0T0T0T0T0T0T0T0T0T0T0T0T0T0T0T0T0T0T0T0T0T0T0T0T0T0T0T0T0T0T0T0T0T0T0T0T0T0T0T0T0T0T0T0T0T0T0T0T0T0T0T0T0T0T0T0T0T0T0T0T0T0T0T0T0T0T0T0T0T0T0T0T0T0T0T0T0T0T0T0T0T0T0T0T0T0T0T0T0T0T0T0T0T0T0T0T0T0T0T0T0T0T0T0T0T0T0T0T0T0T0T0T0T0T0T0T0T0T0T0T0T0T0T0T0T0T0T0T0T0T0T0T0T0T0T0T0T0T0T0T0T0T0T0T0T0T0T0T0T0T0T0T0T0T0T0T0T0T0T0T0T0T0T0T0T0T0T0T0T0T0T0...

Страница 58: ...Page 3 2 Section 3 Emergency procedures INDEX Ed 1 Rev 0 INTENTIONALLY LEFT BLANK ...

Страница 59: ...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 mastered...

Страница 60: ...LERTS The alert lights located on the instrument panel can have the following colours GREEN to indicate that pertinent device is turned ON AMBER to indicate no hazard situations which have to be considered and which require a proper crew action RED to indicate emergency conditions ...

Страница 61: ...en voltage is above 16V in this case the over voltage sensor auto matically shuts down the alternator If ALTOUT caution is ON 1 Generator switch OFF 2 Master switch OFF 3 Generator switch ON 4 Master switch ON If ALTOUTcaution persists ON 5 Generator switch OFF 6 Pitot heat and audio panel OFF 7 Land as soon as practical The battery can supply electrical power for at least 25 minutes NOTE NOTE ...

Страница 62: ...RE In case of LH or RH display failure navigation and engine data will be automati cally available in the remaining display split mode INSTRUCTION revert to the remaining display 2 2 2 LOSS OF ENGINE PARAMETERS ON G3X INSTRUCTION refer to engine parameters warning lights OP LOW and FP LOW and CHT backup indicator ...

Страница 63: ...een PITOT HEAT ON safe operating annunciation is ON If the amber PITOT HEAT caution turns ON the Pitot Heat system is not functioning properly In this case apply following procedure 1 Pitot Heat switch OFF 2 Check Pitot Heat circuit breaker IN 3 Pitot Heat switch ON 4 Check PITOT HEAT caution light If the amber light stays ON avoid visible moisture conditions ...

Страница 64: ...arking brake ON 2 Seat belts unstrap completely 3 Headphones REMOVE 4 Door OPEN 5 Escape away from flames hot engine compartment spilling fuel tanks Hot brakes 4 ENGINE SECURING Following procedure is applicable to shut down the engine in flight 1 Throttle Lever IDLE 2 Ignition key OFF 3 Fuel Selector OFF 4 Electrical fuel pump OFF 5 Generator switch OFF ...

Страница 65: ... as needed WARNING Stall speed increases with bank angle and longitudinal load factor Acoustic stall warning will in any case provides a cor rect anticipated cue of incipient stall At or right before touch down 4 Throttle IDLE fully out and hold 5 Ignition key OFF 6 Fuel selector valve OFF 7 Electric fuel pump OFF 8 Alternator Master switches OFF WARNING A single engine aircraft take off should al...

Страница 66: ...uel Pressure If the fuel pressure indicator falls below 2 2 psi FP LOW warning is ON 1 Electric fuel pump ON 2 Fuel selector valve select opposite fuel tank if NOT empty 3 Fuel quantity indicators Check both If fuel pressure doesn t build up 4 Land as soon as possible applying forced landing procedure See Para 8 ...

Страница 67: ...2 Low Oil Pressure If oil pressure is below12 psi OP LOW warning is ON 1 Throttle Lever REDUCE to minimum practical 2 Land as soon as practical If oil pressure does not increase and OP LOW persists ON 3 Land as soon as possible applying forced landing procedure See Para 8 ...

Страница 68: ... temperature does not decrease 2 Airspeed INCREASE if practical If oil temperature does not come back within limits the thermostatic valve 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...

Страница 69: ...within limits 1 Throttle Lever REDUCE Minimum practical 2 Land as soon as practical If CHT does not come back within limits the thermo static valve regulating the water flow to the cylinder heads could be damaged or a coolant leakage can be present in the coolant supply line If CHT continues to rise and engine shows roughness or power loss 3 Land as soon as possible applying forced landing procedu...

Страница 70: ...not recommended 1 Carburettor heat ON if required 2 Electrical fuel pump ON 3 Fuel quantity indicator CHECK 4 Fuel Selector select opposite tank if not empty 5 Ignition key BOTH 6 Ignition key START 7 Throttle lever SET as required In case of unsuccessful engine restart 1 Engine SECURE see engine securing procedure on Para 4 2 Land as soon as possible applying forced landing procedure See Para 8 ...

Страница 71: ...Switches OFF 7 Parking Brake ENGAGED 8 Aircraft Evacuation carry out immediately 7 2 ENGINE FIRE DURING TAKEOFF BEFORE ROTATION ABORT TAKE OFF 1 Throttle Lever IDLE fully out and hold 2 Rudder Keep heading control 3 Brakes As required With aircraft under control 1 Fuel Selector OFF 2 Electrical fuel pump OFF 3 Ignition key OFF 4 Cabin Heat OFF 5 Alternator Master Switches OFF 6 Parking Brake ENGAG...

Страница 72: ...ELECTRICAL SMOKE IN CABIN DURING FLIGHT 1 Cabin heating OFF 2 Cabin vents OPEN 3 Try to choke the fire Direct the fire extinguisher towards flame base If smoke persists 4 Alternator Master switches OFF 5 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 is prevented 7 5 ELECTRICAL SMOKE FIRE IN CABI...

Страница 73: ...s for every 1000ft above Ground Level it is possible to cover ca 2 NM 8 2 POWER ON FORCED LANDING 1 Airspeed 71KIAS 2 Flaps UP 3 Locate the most suitable terrain for emergency landing plan to approach it upwind 4 Safety belts Tighten When certain to land right before touch down 5 Flaps as necessary 6 Fuel selector valve OFF 7 Electric fuel pump OFF 8 Ignition key OFF 9 Alternator and Master switch...

Страница 74: ... 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 4 6 Airplane evacuation Perfor...

Страница 75: ... Throttle IDLE full out position and hold 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 6 Throttle Readjust to restore engine power WARNING Keep full rudder against rotation until spin has stopped One complete turn and recovery takes about 500 feet...

Страница 76: ...rburettor ice less ef fectively functions as a de icing system 1 Carburettor heating ON 2 Immediately fly away from icing conditions changing altitude and direc tion of flight out and below of clouds visible moisture precipitations 3 Controls surfaces continue to move to keep free from ice build up 4 Throttle speed increase rpm 5 Cabin heat ON WARNING In case of ice formation on wing leading edge ...

Страница 77: ...sts 1 Trim cutout switch CHECKON 2 Speed adjust to control aircraft without excessive stick force 3 Land aircraft as soon as possible Trim Runaway In event of trim runaway act as follows 1 Trim cutout switch OFF 2 Speed adjust to control aircraft without excessive stick force 3 Land aircraft as soon as possible 10 3 FLAPS FAILURE In event of flaps up landing account for Approach speed 64 KIAS Land...

Страница 78: ...Ed 1 Rev 0 Section 3 Emergency procedures Page 3 22 INTENTIONALLY LEFT BLANK ...

Страница 79: ...abin Inspection 5 3 2 Aircraft Walk around 6 4 CHECKLISTS 12 4 1 Before Engine Starting After Pre flight Inspection 12 4 2 Engine Starting 13 4 3 Before taxiing 13 4 4 Taxiing 14 4 5 Prior to takeoff 14 4 6 Takeoff and climb 15 4 7 Cruise 15 4 8 Before Landing 16 4 9 Balked landing missed approach 16 4 10 After landing 16 4 11 Engine shut down 17 4 12 Postflight checks 17 ...

Страница 80: ...Section 4 Normal procedures INDEX Page 4 2 Ed 1 Rev 0 INTENTIONALLY LEFT BLANK ...

Страница 81: ...ue CHT could indicate a temperature up to 20 less than the G3X WARNING Garmin G3X indeed is NOT intended to be used as primary reference for flight and navigation information but only pro vides information for increased situational awareness primary flight information altitude airspeed and heading is provided by analogue instruments 2 AIRSPEEDS FOR NORMAL OPERATIONS The following airspeeds are tho...

Страница 82: ...Page 4 4 Section 4 Normal procedures Ed 1 Rev 0 INTENTIONALLY LEFT BLANK ...

Страница 83: ...rtificate of Airworthiness Noise certificate Radio COM certificate AFM check current and on board B Weight and balance calculate ref to Section 6 and check within limits C Safety belts connected to hard points check condition D Ignition key OFF key extracted E Master switch ON F Voltmeter check within the limits G Lights all ON check for operation H Acoustic stall warning check for operation I Mas...

Страница 84: ... in spection also involves additional check for freedom of movement and security Red lubber lines on bolts and nuts shall be intact WARNING Fuel level indicated by the fuel quantity indicators must be veri fied by visual check of actual fuel quantity embarked in the tanks graduated dipstick must be used WARNING If ignitions key is in L R BOTH position a propeller movement can cause the engine star...

Страница 85: ...th the aircraft parked on a level surface Check for water or other contaminants Make sure filler cap is closed B Pitot tube REMOVE pitot plug and check the pitot for obstructions Do not blow inside pitot tube C Left side leading edge and wing skin Visual inspection CHECK stall strips D Left strobe light Visual inspection CHECK for integrity and fixing E Left aileron hinges and LH tank vent line CH...

Страница 86: ...should be no sign of hydraulic fluid leakage M Right flap and hinges Visual inspection N Right aileron hinges and RH tank vent line Visual inspection check free of play friction Right side tank vent check for obstructions O Right strobe light leading edge and wing skin Visual inspection CHECK stall strips CHECK strobe light for integrity and fixing P Stall indicator switch CHECK for integrity and ...

Страница 87: ...actically no friction at all fur ther investigation is necessary Turn propeller by hand in direction of engine rotation several times and observe engine for odd noises or excessive resistance and normal compression 4 Carburettors check the throttle and choke cables for condition and installation 5 Exhaust inspect for damages leakage and general condition 6 Check engine mount and silent blocks for ...

Страница 88: ...LIGHT INSPECTIONS Ed 1 Rev 0 Z Tow bar and chocks REMOVE stow on board pitot static ports and stall warning protective plugs Avoid blowing inside Pitot tube and inside airspeed indicator system s static ports as this may damage instruments NOTE ...

Страница 89: ...Page 4 11 Section 4 Normal procedures Ed 1 Rev 0 INTENTIONALLY LEFT BLANK ...

Страница 90: ...mp noise 8 Electric fuel pump OFF 9 Avionic Master switch ON check instruments then set in OFF position 10 Flap control cycle fully extended and then set to T O 11 Pitch Trim cycle fully up and down from both LH and RH controls check for trim disconnect switch operation 12 Pitch trim set neutral WARNING Pitch trim position other than in neutral position would affect take off perfor mance and take ...

Страница 91: ...s present in the area close to the propeller Forward lower sector visibility is not possible from inside the cockpit 6 Ignition key BOTH 7 Ignition key START 8 Check oil pressure rises within 10 sec 9 Generator switch ON 10 Voltmeter check more 14V or more 11 Engine instruments Check within the limits 12 Choke OFF 13 Propeller rpm 1000 1200 rpm 14 Electric fuel pump OFF 15 Check fuel pressure min ...

Страница 92: ...el pressure check 7 Throttle speed advance throttle to 1640 rpm a Ignition key test select LEFT check speed drop within 130 pro peller 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 speed 1640 rpm 8 Carburettor heat test a Pull selector fully OUT b Th...

Страница 93: ...ents check parameters within the limits 5 Rotation speed VR 48 KIAS 6 Flaps retract above flap retraction speed 58 KIAS 7 Establish Climb rate VY 71 KIAS 8 Electric fuel pump OFF 9 Fuel pressure check minimum 2 2 psi 10 Throttle speed reduce at or below 2250 rpm 4 7 CRUISE 1 Set power at or below maximum continuous 2250 propeller rpm 2 Check engine instruments Oil temperature 50 130 C Temperature ...

Страница 94: ... point Flaps set T O Approach speed 58 KIAS 5 On final leg Flaps set LAND Final Approach Speed 54 KIAS 6 Carburettor heat OFF full IN 7 Optimal touchdown speed 54 KIAS 4 9 BALKED LANDING MISSED APPROACH 1 Throttle FULL 2 Speed keep over 61 KIAS climb to VY or VX as applicable 3 Flaps position TO 4 Electric fuel pump ON 4 10 AFTER LANDING 1 Flaps UP 2 Electric Fuel Pump OFF 3 Landing light OFF ...

Страница 95: ...OFF 6 Master Generator switches OFF 7 Fuel selector valve OFF WARNING Before disembarkation verify propeller is fully stopped CAUTION Instruct passenger to fully open RH door and depart avoiding contact with wheels and sharp wing control surfaces edges 4 12 POST FLIGHT CHECKS 1 Flight controls lock by mean of seat belts 2 Wheel chocks and wing mooring lines Set 3 Parking brake Release 4 Doors Clos...

Страница 96: ...Page 4 18 Section 4 Normal procedures CHECKLISTS Ed 1 Rev 0 INTENTIONALLY LEFT BLANK ...

Страница 97: ... PERFORMANCE CHARTS 2 3 AIRSPEED INDICATOR SYSTEM CALIBRATION 3 4 ICAO STANDARD ATMOSPHERE 4 5 STALL SPEED 5 6 CROSSWIND 6 7 TAKEOFF PERFORMANCE 7 8 TAKE OFF RATE OF CLIMB 10 9 EN ROUTE RATE OF CLIMB 11 10 CRUISE PERFORMANCE 12 11 LANDING PERFORMANCE 14 12 BALKED LANDING PERFORMANCE 15 13 NOISE DATA 15 ...

Страница 98: ... piloting techniques Each graph or table was determined according to ICAO Standard Atmosphere ISA s l evaluations of the impact on performance were carried out by theoret ical means for Airspeed External temperature Altitude Weight Runway type and condition 2 USE OF PERFORMANCE CHARTS Performance data are presented in tabular or graphical form to illustrate the effect of different variables such a...

Страница 99: ...indicated airspeed VCAS FIG 5 1 CALIBRATED VS INDICATED AIRSPEED Example Given Find KIAS 75 0 Flap UP KCAS 74 5 Indicated airspeed assumes 0 as an instrument error 20 30 40 50 60 70 80 90 100 110 120 130 140 150 160 40 50 60 70 80 90 100 110 120 130 140 150 Indicated Airspeed KIAS Calibrated Airspeed KCAS Airspeed Indication System Calibration Flap UP Flap T O Flap LN NOTE ...

Страница 100: ...OSPHERE Ed 1 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 ...

Страница 101: ...GHT BANK ANGLE STALL SPEED FLAPS 0 FLAPS T O FLAPS FULL kg deg KIAS KCAS KIAS KCAS KIAS KCAS 630 FWD C G 0 48 50 43 46 40 43 15 49 51 44 46 41 44 30 52 54 47 49 44 46 45 58 60 52 54 49 51 60 70 71 63 64 60 61 Altitude loss during conventional stall recovery as demonstrated during flight tests is approximately 350 ft with banking below 30 NOTE ...

Страница 102: ... CROSSWIND Ed 1 Rev 0 6 CROSSWIND Maximum demonstrated crosswind is 15 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 2 CROSSWIND CHART ...

Страница 103: ...6 225 At 50 ft AGL 265 331 406 490 375 1000 Ground Roll 172 216 267 323 242 At 50 ft AGL 289 361 442 533 402 2000 Ground Roll 187 236 291 353 259 At 50 ft AGL 314 392 481 580 430 3000 Ground Roll 205 258 318 386 279 At 50 ft AGL 342 427 524 631 461 4000 Ground Roll 224 281 347 421 299 At 50 ft AGL 373 466 571 688 494 5000 Ground Roll 244 308 380 461 322 At 50 ft AGL 406 508 622 750 530 6000 Ground...

Страница 104: ...l 141 177 219 265 198 At 50 ft AGL 238 298 365 440 332 2000 Ground Roll 154 193 239 289 213 At 50 ft AGL 259 324 397 478 355 3000 Ground Roll 168 211 261 316 228 At 50 ft AGL 282 353 432 521 380 4000 Ground Roll 183 231 285 346 245 At 50 ft AGL 308 384 471 568 408 5000 Ground Roll 200 252 311 378 264 At 50 ft AGL 335 419 514 619 437 6000 Ground Roll 219 276 341 413 284 At 50 ft AGL 366 457 560 676...

Страница 105: ...l 113 143 176 214 160 At 50 ft AGL 193 241 296 357 269 2000 Ground Roll 124 156 192 233 171 At 50 ft AGL 210 263 322 388 288 3000 Ground Roll 135 170 210 255 184 At 50 ft AGL 229 286 351 423 309 4000 Ground Roll 148 186 229 278 198 At 50 ft AGL 250 312 382 461 331 5000 Ground Roll 161 203 251 304 213 At 50 ft AGL 272 340 417 502 355 6000 Ground Roll 177 222 275 333 229 At 50 ft AGL 297 371 455 548...

Страница 106: ...7 438 295 550 6000 65 636 461 305 164 441 8000 64 497 325 172 34 331 10000 64 359 190 40 96 221 12000 63 221 56 92 226 112 14000 63 84 79 224 355 2 580 S L 67 1182 987 814 657 881 2000 66 1034 843 672 518 765 4000 65 887 698 530 379 649 6000 65 739 555 390 241 533 8000 64 593 411 249 103 417 10000 63 447 269 109 34 302 12000 63 301 126 30 171 186 14000 62 156 16 169 307 70 530 S L 66 1331 1123 937...

Страница 107: ... 631 6000 67 702 558 430 314 541 8000 65 588 447 321 207 451 10000 64 474 336 212 101 362 12000 62 361 225 104 5 272 14000 61 249 115 4 111 182 580 S L 71 1171 1011 869 740 924 2000 69 1050 893 753 626 829 4000 68 929 774 637 513 734 6000 66 808 657 521 399 639 8000 65 688 539 406 286 544 10000 64 568 422 291 174 449 12000 62 449 305 177 62 354 14000 61 330 189 63 50 259 530 S L 71 1317 1147 995 8...

Страница 108: ...f weight 3 3 3 4 CRUISE PERFORMANCE Pressure Altitude ft OAT ISA deg C Propeller RPM KTAS Fuel Consumption lt hr Endurance hr mm Range nm Specific Range nm lt 0 15 2388 120 25 8 4 40 562 4 64 2250 110 21 3 5 40 624 5 16 2100 99 17 4 7 00 689 5 70 2000 92 15 3 7 50 725 5 99 1900 85 13 7 8 45 748 6 18 1800 78 12 5 9 40 751 6 21 2000 11 2388 118 24 1 5 00 593 4 90 2250 108 20 0 6 00 653 5 40 2100 98 ...

Страница 109: ...ange nm Specific Range nm lt 4000 7 2388 117 22 6 5 25 624 5 16 2250 107 18 9 6 25 681 5 63 2100 96 15 9 7 35 731 6 04 2000 89 14 3 8 25 750 6 20 1900 82 13 2 9 10 750 6 21 1800 75 12 4 9 45 728 6 02 6000 3 2250 105 18 0 6 40 706 5 84 2100 94 15 3 7 50 744 6 16 2000 87 14 0 8 35 753 6 22 1900 80 13 1 9 25 741 6 13 1800 73 12 5 9 40 705 5 83 8000 1 2250 103 17 2 7 00 726 6 01 2100 93 14 9 8 05 752 ...

Страница 110: ...t AGL 358 373 388 403 382 1000 Ground Roll 154 170 186 201 178 At 50 ft AGL 363 379 395 410 387 2000 Ground Roll 160 176 192 209 183 At 50 ft AGL 369 385 401 418 392 3000 Ground Roll 166 183 200 216 189 At 50 ft AGL 375 392 409 425 398 4000 Ground Roll 172 190 207 225 195 At 50 ft AGL 381 399 416 434 404 5000 Ground Roll 179 197 215 233 201 At 50 ft AGL 388 406 424 442 410 6000 Ground Roll 186 205...

Страница 111: ...ssure Altitude Rate of Climb ft min angle of climb deg Temperature C ISA kg ft 25 0 25 50 630 S L 881 9 750 7 633 6 528 5 678 6 2000 781 8 653 6 538 5 434 4 600 5 4000 682 6 556 5 443 4 341 3 523 5 6000 583 5 459 4 348 3 248 2 445 4 8000 485 4 363 3 254 2 156 1 367 3 10000 387 3 267 2 160 1 64 0 289 2 12000 289 2 171 1 66 0 28 0 211 2 14000 191 1 76 1 27 0 120 1 133 1 13 NOISE DATA Noise level det...

Страница 112: ...Page 5 16 Section 5 Performances Ed 1 Rev 0 INTENTIONALLY LEFT BLANK ...

Страница 113: ...ON6 WEIGHT AND BALANCE INDEX 1 INTRODUCTION 3 2 WEIGHING PROCEDURES 3 2 1 Preparation 3 2 2 Levelling 3 2 3 Weighing 3 2 4 Determination of C G location 4 2 5 Weighing record 5 2 6 Weighing record II 6 3 WEIGHTS AND C G 7 4 BAGGAGE LOADING 9 5 EQUIPMENT LIST 10 ...

Страница 114: ...Page 6 2 Section 6 Weight and balance Ed 1 Rev 0 INTENTIONALLY LEFT BLANK ...

Страница 115: ... PREPARATION Carry out weighing procedure inside closed hangar Remove from cabin any objects unintentionally left Insure Flight Manual and mandatory documents are on board Align nose wheel Drain fuel via the specific drain valve Oil hydraulic fluid and coolant to operating levels Move sliding seats to most forward position Raise flaps to fully retracted position 0 Place control surfaces in neutral...

Страница 116: ...ark on the floor see Figure on Para 2 5 or 2 6 Repeat the operation for other wing Stretch a taught line between the two marks Measure the distance between the reference line and both main and nose wheel axis A and B distances respectively Using recorded data it is possible to determine the aircraft C G location and the aircraft moment see following table ...

Страница 117: ... Plumb bob distance LH wheel AL LH wheel weight WL Plumb bob distance RH wheel AR RH wheel weight WR Average distance AL AR 2 A W2 WL WR Plumb bob distance from nose wheel B Empty weight We W1 W2 kg or lbs We B W A W D 1 2 m or Ft 100 5 4 373 1 ft or m D D Empty weight moment M D 1 566 We m kg or ft lbs Maximum takeoff weight WT 630 Kg 1388 lbs Empty weight We kg or lbs Max useful load WT We Wu kg...

Страница 118: ...1 Plumb bob distance LH wheel AL LH wheel weight WL Plumb bob distance RH wheel AR RH wheel weight WR Average distance AL AR 2 A W2 WL WR Plumb bob distance from nose wheel B Empty weight We W1 W2 kg or lbs We B W A W D 1 2 m or ft 100 5 4 373 1 ft or m D D Empty weight moment M D 1 566 We m kg or ft lbs Maximum takeoff weight WT 630 Kg 1388 lbs Empty weight We kg or lbs Max useful load WT We Wu k...

Страница 119: ...ight k g Momen t kgm Li ter Weight kg Momen t kgm Weight k g Momen t kgm 10 18 10 7 2 15 91 5 12 05 20 36 20 14 4 31 82 10 24 10 30 54 30 21 6 47 74 15 36 15 40 72 40 28 8 63 65 20 48 20 50 90 50 36 79 56 60 108 60 43 2 95 47 70 126 70 50 4 111 38 80 144 80 57 6 127 30 90 162 90 64 8 143 21 100 180 100 72 159 12 110 198 110 79 2 174 95 120 216 120 86 4 190 86 130 234 124 89 3 197 26 140 252 150 27...

Страница 120: ...ts and baggage from the previous chart 4 Sum the weight and the moment columns 5 Divide the total moment by the total weight to get the arm 6 Check that the total weight does not exceed maximum gross weight of 630 Kg 1388 lb 7 Check that the arm falls within the C G range CoG Position Computation Chart Weight kg Arm m Moment kg m EmptyWeight Fuel 2 209 Pilot Passenger 1 800 Baggage 2 417 Total MOM...

Страница 121: ...e In this example the gross weight is under the max gross weight of 630 kg 1388 lbs and the Arm or C G is within the C G range listed above 4 BAGGAGE LOADING The baggage loading in the dedicated compartment behind the pilots seats must be carried out in accordance with C G excursion and weight limitations reported in Section 2 Baggage must be uniformly distributed on compartment floor Pilot is pro...

Страница 122: ...nd 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 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 relative to aircraft...

Страница 123: ...ms Cleveland199 10200 2 05 2229 2 B2 Main gear tires Air Trac 5 00 5 2 58 2229 2 B3 Disk brakes Cleveland 164 17 0 80 2229 2 B4 Nose gear wheel rim p n4077C 1 30 418 1 B5 Nose gear tire Air Trac 5 00 5 1 20 418 1 B6 Nose gear fairing p n28 8 1110 1 28 8 1112 1 1 50 418 1 B7 Main gear fairing p n 92 8 410 1 2 1 50 2229 2 B8 Nose gear shock p n28 8 500 000 1 45 770 1 ELECTRICAL SYSTEM C1 Battery FIA...

Страница 124: ...lini SOR 53 0 30 1084 1 D12 VoltmeterIndicator Sorlini SOR 51 0 30 1084 1 D13 G3X Display LH RH GDU 370 1 60 1084 2 D14 G3X AHRS GSU 73 1 60 1900 1 D15 G3X Magnetometer GMU 44 0 23 4697 1 D16 OAT probe GTP 59 0 10 2060 1 AVIONICS AND OTHER E1 Nav Comm Garmin SL30 Pack and connectors 1 50 1084 1 E2 ELT Artex ME 406 1 10 1900 1 E3 Transponder Garmin GTX328 1 00 1084 1 E4 Audio panel Garmin GMA 340 0...

Страница 125: ...lage 3 2 3 Empennages 3 2 4 Landing gear 4 3 FLIGHT CONTROLS 5 4 INSTRUMENT PANEL 5 4 1 Carburettor Heat 6 4 2 Cabin Heat 6 5 SEATS AND SAFETY HARNESS 7 6 DOORS 7 7 POWERPLANT 8 7 1 ENGINE 8 7 2 PROPELLER 8 8 FUEL SYSTEM 9 9 ELECTRICAL SYSTEM 11 9 1 Stall Warning System 11 9 2 Avionics 11 9 3 External Power Supply 13 10 PITOT STATIC PRESSURE SYSTEMS 14 11 BRAKES 15 ...

Страница 126: ...strut brace per side The wings are made up of a central light alloy torsion box a light alloy leading edge is attached to the front spar whereas the flap slot ted and the aileron frise are attached to a rear spar through two hinges each The torsion box consists of a front and rear spar that represent its front and rear vertical walls a series of ribs and wrap around panels complete the structure F...

Страница 127: ... fin are a unique body 2 3 EMPENNAGES The horizontal tail is an all moving type the stabilizer and elevator form a single uniform plane called stabilator that rotates to the desired pitch setting The stabilator structure is made up by an aluminium spar 1 and ribs 2 Aluminium skin panels are riveted to the above elements 3 1 2 3 4 Fig 7 2 STABILATOR STRUCTURE A trim tab 4 provides stick force adjus...

Страница 128: ...he fuselage structure via two couples of ma chined aluminium beams Wheels are cantilevered on gear struts and feature hydraulically actuated disc brakes controlled by toe A Pivoting nose gear is attached to the firewall reinforcement plate The Hydraulic shock absorber is fitted on the upper machined component and directly on the nose landing gear structure In the following figure is shown 1 Hydrau...

Страница 129: ...nstrument panel gives full authority to pilot or co pilot control switch An analogue trim indicator provides information about the surface position In case of a trim control runaway a trim disconnect switch is available on the instrument panel 4 INSTRUMENT PANEL The instrument panel is divided in four areas The left area holds primary analogue and pilot s situational awareness G3X LH display fligh...

Страница 130: ... HEAT Carburettor heat control knob is located lower LH portion of the instrument panel when the knob is pulled fully outward from the instrument panel carburettors re ceive maximum hot air During normal operation the knob is set in OFF position 4 2 CABIN HEAT The cabin heat control knob is positioned on the lower right side of the instrument panel when knob is pulled fully outward cabin receives ...

Страница 131: ... A lever located on the right lower side of each seat allows for seat adjustment ac cording to pilot size 6 DOORS Two doors are provided for P2008 JC on Pilot and co pilot side A sketch of the door is shown below RH and LH doors are specular Fig 7 6 DOOR The door is equipped with a gas spring fixed to the fuselage that facilitates door opening Gas spring support Fuselage side Gas spring Gas spring...

Страница 132: ...ntally 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 7 2 PROPELLER Manufacturer GT Propellers Model GT 2 173 VRR FW101 SRTC N of blades 2 Diameter 1730 mm no reduction permitted Type wood fixed pitch ...

Страница 133: ...C Each fuel tank is integrated within the wing ribs box The capacity of each tank is 62 liters for a total of 124 liters The internal side of fuel tank is accessible for inspection through two dedicated doors The fuel tank filler cap is located on the top of the wing in the area outside of the tank and it is easily accessible from the leading edge of the aircraft At the lowest point of the tank it...

Страница 134: ... Airframe and Systems description FUEL SYSTEM The fuel selector is operated by a fuel selector control knob located in the cabin on the central panel The fuel selector control and the fuel valve are connected via a rigid control rod ...

Страница 135: ...y bus in order to provide energy for the electric equipment Each electrically fed instrument is connected to a dedicated circuit breaker which protects the cable from the battery bus to the associated electric equipment 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 9 1 STALL WARNING SYSTEM Th...

Страница 136: ...ovides SSR Secondary Surveillance Radar responses this unit is capable of both mode S and mode C An external altitude encoder ACK A 30 allows altitude reporting this information is also presented on GTX 328 dis play An automatic reversion mode is integrated within the system in order to continue providing the pilot with the flight and engine information in the event of a LH or RH display failure F...

Страница 137: ...should be used at the engine start up in cold weather condition For en gine start below 17 C OAT it is advisable to use the external power source Follow this procedure to start the engine using the external power source 1 Magnetos Master switch Generator switch OFF 2 Open the receptacle door and insert the external power source s plug into the socket 3 Engine start up procedure see Sect 4 in this ...

Страница 138: ...n parallel and located in corre spondence of engine firewall on left and right side of fuselage Flexible plumbing connects total pressure and static ports to primary analogue instruments anemometer and altimeter Garmin G3X ADAHRS GSU73 unit installed on the rear of the fuselage near the battery acts as an air data computer for Garmin G3X suite it is connected to both static and total pressure line...

Страница 139: ...es connect ed to the caliper A parking brake valve mounted in correspondence of the cabin floor and operated by a knob on the cockpit central pedestal intercepts the hydraulic lines once pressur ized by toe brakes to hold the brake assemblies linings tightened round the main wheels brake discs Brakes can be operated from either pilot s and co pilot s pedals a single vented oil reservoir feeds the ...

Страница 140: ...Page 7 16 Ed 1 Rev 0 Section 7 Airframe and Systems description BRAKES INTENTIONALLY LEFT BLANK ...

Страница 141: ...4 4 MAINTENANCE 5 4 1 Refuelling 5 4 2 Oil level control 5 4 3 Landing gear tires pressure control 5 5 ENGINE COWLING CHECK 6 5 1 Upper cowling 6 5 2 Lower Cowling 6 6 GROUND HANDLING 7 6 1 Towing 7 6 2 Parking and Tie Down 7 6 3 Mooring 8 6 4 Jacking 8 6 5 Road Transport 8 7 CLEANING AND CARE 9 7 1 Windows 9 7 2 External surfaces 9 7 3 Propeller 9 7 4 Engine 9 7 5 Internal surfaces 9 ...

Страница 142: ...factory recommended procedures for proper ground han dling and routine care and servicing It also identifies certain inspection and maintenance requirements It is recommended to follow a planned schedule of lubrication and preventive maintenance based on climatic and flying conditions encountered locally ...

Страница 143: ... annual inspection has to be performed All required inspections are reported in the Aircraft Maintenance Manual As far as the scheduled unscheduled engine maintenance is concerned refer to the engine manufacturer Maintenance Manual CAUTION Unscheduled inspections maintenance tasks are necessary when one or more of following conditions occur 1 Emergency landing 2 Breaking damage of propeller or in ...

Страница 144: ... GROUND HANDLING SERVICE AIRCRAFT CHANGES OR REPAIRS Ed 1 Rev 0 3 AIRCRAFT CHANGES OR REPAIRS Aircraft changes or repairs must be performed in accordance with Aircraft Main tenance Manual and Job cards provided by TECNAM ...

Страница 145: ...n the engine cowling RH 2 Prior to oil check switch off ignition circuit and turn the propeller by hand in direction of engine rotation several times to pump oil from the engine into the oil tank or let the engine idle for 1 minute This process is finished when air is returning back to the oil tank and can be noticed by a murmur from the open oil tank 3 Clean the dipstick and soak it in the reserv...

Страница 146: ...erence 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 5 2 LOWER COWLING I After disassembling upper cowling move the propeller to a horizontal position II Using a standard screwdriver press and rotate 90 the two C...

Страница 147: ...cing without regard to prevailing winds Ensure that it is sufficiently protected against adverse weather conditions and present no danger to other aircraft Procedure 1 Position airplane on levelled surface headed into the prevailing wind if practical 2 Engage parking brake 3 Secure pilot control stick by wrapping the seat belt around it Do not engage the parking brakes at low ambient temperature w...

Страница 148: ...ground cable to the engine muffle 6 Install control locks 7 Install protective plugs 8 Close and lock cabin doors 9 Secure tie down cables to the nose gear leg and to the wings in correspondence of wing struts and tail cone tie down rings at approximately 45 degree with re spect to the ground Additional preparation for high winds includes tie down ropes from the main landing gear employment 6 4 JA...

Страница 149: ...ircraft in the hangar 7 3 PROPELLER To preserve its functionality avoiding wear and corrosion the propeller manufac turer uses for external surface painting an acrylic paint which is resistant to all solvents In any case it is advisable to clean the propeller using exclusively soapy water 7 4 ENGINE Engine cleaning is part of the scheduled maintenance Refer to the engine manu facturer Maintenance ...

Страница 150: ...e 8 10 Section 8 GROUND HANDLING SERVICE ICE REMOVAL Ed 1 Rev 0 8 ICE REMOVAL Anti icing products are not allowed To remove ice tow the aircraft in the hangar and operate with a soft brush or a humid cloth ...

Страница 151: ...Page 9 1 SECTION 9 AFM Supplements SUPPLEMENTS LIST 1st Ed Rev 0 SECTION 9 AFM SUPPLEMENTS INDEX INDEX 1 1 Introduction 2 2 Supplements list 3 ...

Страница 152: ...t Ed Rev 0 1 INTRODUCTION This Section concerns the supplemental manuals of additional or optional instrumen tation equipping the P2008JC and or information and limitations related to installed equipment configuration or needed to fit local national rules ...

Страница 153: ...ements SUPPLEMENTS LIST 1st Ed Rev 0 2 SUPPLEMENTS LIST Aircraft S N Registration marks Date SUPPLEMENTS LIST FOR AIRPLANES WITH ANALOGUE INSTRUMENTS Sup No Title Rev no Date APPLICABLE YES NO S1 VFR Night equipment configuration ...

Страница 154: ...Page 9 4 Section 9 Supplements SUPPLEMENTS LIST 3rd Edition Rev 0 INTENTIONALLY LEFT BLANK ...

Страница 155: ...e Description of Revision Tecnam Approval EASA Approval or Under DOA Privileges DO OoA HDO 0 First Issue G Paduano M Landi M Oliva EASA approved as part of Type Investigation List of Effective Pages Page Revision Cover Pages S1 1 thru 20 Rev 0 Section 2 N2 1 thru 30 Rev 0 Section 3 N3 1 thru 24 Rev 0 Section 4 N4 1 thru 18 Rev 0 Section 7 N7 1 thru 18 Rev 0 ...

Страница 156: ...FIGURATION Ed 1 Rev 0 INDEX INTRODUCTION 3 SECTION 1 GENERAL 5 SECTION 2 LIMITATIONS 7 SECTION 3 EMERGENCY PROCEDURES 9 SECTION 4 NORMAL PROCEDURES 11 SECTION 5 PERFORMANCE 13 SECTION 6 WEIGHT AND BALANCE 15 SECTION 7 AIRFRAME AND SYSTEM DESCRIPTION 17 ...

Страница 157: ... 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 VFR Night Equipment Configuration in subject It is the owner s responsibility to replace the mentioned pages in accordance with the instructions herein addressed section by section ...

Страница 158: ...Page S1 4 Supplement no S1 VFR NIGHT EQUIPMENT CONFIGURATION Ed 1 Rev 0 INTENTIONALLY LEFT BLANK ...

Страница 159: ...Page S1 5 Supplement no S1 VFR NIGHT EQUIPMENT CONFIGURATION Ed 1 Rev 0 SECTION 1 GENERAL Refer to Basic AFM Section 1 Supplement S1 pages replacement instructions ...

Страница 160: ...Page S1 6 Supplement no S1 VFR NIGHT EQUIPMENT CONFIGURATION Ed 1 Rev 0 INTENTIONALLY LEFT BLANK ...

Страница 161: ... S1 7 Supplement no S1 VFR NIGHT EQUIPMENT CONFIGURATION Ed 1 Rev 0 SECTION 2 LIMITATIONS Supplement S1 Limitations pages replace basic AFM Section 2 as a whole Supplement S1 pages replacement instructions ...

Страница 162: ...Page S1 8 Supplement no S1 VFR NIGHT EQUIPMENT CONFIGURATION Ed 1 Rev 0 INTENTIONALLY LEFT BLANK ...

Страница 163: ...T 8 7 COOLANT LIQUID 8 8 PAINT 8 9 PROPELLER 9 10 MAXIMUM OPERATING ALTITUDE 9 11 AMBIENT TEMPERATURE 9 12 POWERPLANT INSTRUMENTS MARKINGS 10 13 OTHER INSTRUMENTS MARKINGS 10 14 WEIGHTS 12 15 CENTER OF GRAVITY RANGE 14 16 APPROVED MANOEUVRES 16 17 MANOEUVRES LOAD FACTOR LIMITS 17 18 DEMONSTRATED CROSS WIND SAFE OPERATIONS 18 19 FLIGHT CREW 18 20 KINDS OF OPERATION EQUIPMENT LIST KOEL 19 21 LIMITAT...

Страница 164: ...AFMS for VFR NIGHT equipped airplanes Page 2N 2 Section 2 Limitations Ed 1 Rev 0 INTENTIONALLY LEFT BLANK ...

Страница 165: ... 2N 3 Ed 1 Rev 0 Section 2 Limitations INTRODUCTION 1 INTRODUCTION Section 2 includes operating limitations instrument markings and basic placards necessary for safe operation of the aeroplane its engine standard systems and standard equipment ...

Страница 166: ...AFMS for VFR NIGHT equipped airplanes Page 2N 4 Ed 1 Rev 0 Section 2 Limitations INTENTIONALLY LEFT BLANK ...

Страница 167: ... 141 Do not exceed this speed in any operation VNO Maximum Structural Cruising Speed 113 111 Do not exceed this speed except in smooth air and only with caution VA Design Manoeuvring speed 99 98 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 VO Operating Manoeuvring speed VFE Maximum flaps ext...

Страница 168: ...71 Positive 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 48 113 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 113 145 Manoeuvres must be conducted with caution an...

Страница 169: ...r kW hp Max rpm Prop rpm engine Time max minutes Max T O 73 5 98 6 2388 5800 5 Max Cont 69 92 5 2265 5500 Temperatures Max CHT 135 C Min Max Oil 50 C 130 C Oil Pressure Minimum 12 psi below 1440propeller rpm Maximum 102 psi above 1440 propeller rpm CAUTION In event of cold starting operation it is permitted a maximum oil pressure of 7 bar for a short period Engine starting allowable temperature ra...

Страница 170: ...ad content Make reference to Rotax Maintenance Manual which prescribes dedicated checks due to the prolonged use of Avgas 6 LUBRICANT Recommended by Rotax BRAND DESCRIPTION SPECIFICATION VISCOSITY CODE SHELL AeroShell Sport Plus 4 API SL SAE 10 W 40 2 Use only oil with API classification SG or higher see Rotax SI 912 016 R4 for list of recommended commercial brands and types 7 COOLANT LIQUID 100 P...

Страница 171: ...otec tive layer of laminate TYPE Fixed pitch DIAMETER 1730 mm no reduction is permitted 10 MAXIMUM OPERATING ALTITUDE Maximum operating altitude is 13000ft 3962 m MSL CAUTION At altitudes above 10000 ft 3048 m up to and including 13000 ft 3962 m flight crew is recommended to use supplemental oxygen 11 AMBIENT TEMPERATURE Ambient temperature from 25 C to 50 C WARNING Flight in expected and or known...

Страница 172: ...ENT RED LINE Minimum limit GREEN ARC Normal operating YELLOW ARC Caution RED LINE Maximum limit Engine rpm 577 2265 2265 2388 2388 Oil temp C 50 50 130 130 CHT C 0 135 135 Oil pressure OP LOW Warning 12 psi OP HIGH Warning 102 psi Fuel pressure FP LOW Warning 2 2 psi 13 OTHER INSTRUMENTS MARKINGS INSTRUMENT RED ARC Minimum limit GREEN ARC Normal operating YELLOW ARC Caution RED ARC Maximum limit V...

Страница 173: ...AFMS for VFR NIGHT equipped airplanes Section 2 Limitations Ed 1 Rev 0 Page 2N 11 INTENTIONALLY LEFT BLANK ...

Страница 174: ... 2 Limitations WEIGHTS Ed 1 Rev 0 Page 2N 12 14 WEIGHTS Condition Weight Maximum takeoff weight 630 kg 1388 lb Maximum landing weight 630 kg 1388 lb Baggage Compartment Maximum weight 20 kg 44 lb Maximum specific pressure 12 5 kg dm2 256 lbs sq in ...

Страница 175: ...AFMS for VFR NIGHT equipped airplanes Section 2 Limitations WEIGHTS Ed 1 Rev 0 Page 2N 13 INTENTIONALLY LEFT BLANK ...

Страница 176: ...ange the aircraft must be levelled in the longitudinal plane Levelling Refer to the seat track supporting beams see procedure in Section 6 Forward limit 1 841 m 20 MAC aft of datum for all weights Aft limit 1 978 m 30 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 instruc tions ...

Страница 177: ...AFMS for VFR NIGHT equipped airplanes Section 2 Limitations Ed 1 Rev 0 Page 2N 15 INTENTIONALLY LEFT BLANK ...

Страница 178: ...ep turns in which the angle of bank is not more than 60 Recommended entry speeds for each approved manoeuvre are as follows Manoeuvre Speed KIAS Lazy eight 99 Chandelle 113 Steep turn max 60 99 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 ...

Страница 179: ...tations Manoeuvres load factor limits Ed 1 Rev 0 Page 2N 17 17 MANOEUVRES LOAD FACTOR LIMITS Manoeuvre load factors limits are as follows Positive Negative 4 g 2 g Manoeuvre load factors limits with flaps extended are as follows Positive 2 g Negative 0 g ...

Страница 180: ...e Operations Ed 1 Rev 0 Page 2N 18 18 DEMONSTRATED CROSS WIND SAFE OPERATIONS The aircraft controllability during take offs and landings has been demonstrated with a cross wind components of 15kts 19 FLIGHT CREW Minimum crew 1 pilot Maximum number of occupants 2people including the pilot ...

Страница 181: ...escribed equipment is in stalled and operational WARNING VFR NIGHT operation is limited to airfields providing centre line illumination Additional equipment or a different equipment list for the intended operation may be required by national operational requirements and also depends on the airspace classification and route to be flown The owner is responsible for fulfilling these re quirements WAR...

Страница 182: ...UE CHT INDICATOR ANALOGUE RPM INDICATOR ANALOGUE OIL TEMPERATURE INDICATOR ANALOGUE VOLTMETER GARMIN G3X SUITE TRANSPONDER ALTITUDE ENCODER SLIP INDICATOR LONGITUDINAL TRIM INDICATOR FLAP POSITION INDICATOR COMM NAV EQUIPMENT AUDIO PANEL MARKER BEACON LANDING TAXI LIGHT STROBE LIGHTS NAV LIGHTS ANNUNCIATOR PANEL BREAKERS PANEL STALL WARNING SYSTEM FIRST AID KIT HAND HELD FIRE EXTINGUISHER ELT PITO...

Страница 183: ... it is placed the following plac ard reporting following speed limitation On the central side of the instrument panel the following placard is placed remind ing the observance of aircraft operating limitations according to the installed equipment configuration see KOEL Para 20 On the right hand side of the instrument panel the following placard is placed re minding the observance for no smoking In...

Страница 184: ...AFMS for VFR NIGHT equipped airplanes Section 2 Limitations Limitations placards Ed 1 Rev 0 Page 2N 22 Below the G3X screens and analogue instruments the following labels are placed ...

Страница 185: ...AFMS for VFR NIGHT equipped airplanes Section 2 Limitations OTHER placards Ed 1 Rev 0 Page 2N 23 22 OTHER PLACARDS Engine compartment placards Oil brakes reservoir placard ...

Страница 186: ...AFMS for VFR NIGHT equipped airplanes Section 2 Limitations OTHER placards Ed 1 Rev 0 Page 2N 24 Usable fuel markings Allowed fuel placards Emergency exit placard Parking brake placard ...

Страница 187: ...AFMS for VFR NIGHT equipped airplanes Section 2 Limitations OTHER placards Ed 1 Rev 0 Page 2N 25 Throttle marking Fuel selector valve marking Choke placard Alternate static port placard ...

Страница 188: ...MS for VFR NIGHT equipped airplanes Section 2 Limitations OTHER placards Ed 1 Rev 0 Page 2N 26 Cabin heat defrost placard Carb heat placard Ignition key placard Master Generator placards Map light placard ...

Страница 189: ...FMS for VFR NIGHT equipped airplanes Section 2 Limitations OTHER placards Ed 1 Rev 0 Page 2N 27 Flap indicator placard Backrest lever placard Safety equipment location placard Elt placard Battery placard ...

Страница 190: ...AFMS for VFR NIGHT equipped airplanes Section 2 Limitations OTHER placards Ed 1 Rev 0 Page 2N 28 Annunciator panel Upper panel labels Switches labels Day Night switch label Door lock lever ...

Страница 191: ...AFMS for VFR NIGHT equipped airplanes Section 2 Limitations OTHER placards Ed 1 Rev 0 Page 2N 29 ...

Страница 192: ...AFMS for VFR NIGHT equipped airplanes Section 2 Limitations OTHER placards Ed 1 Rev 0 Page 2N 30 INTENTIONALLY LEFT BLANK ...

Страница 193: ...plement no S1 VFR NIGHT EQUIPMENT CONFIGURATION Ed 1 Rev 0 SECTION 3 EMERGENCY PROCEDURES Supplement S1 Emergency Procedures pages replace basic AFM Section 3 as a whole Supplement S1 pages replacement instructions ...

Страница 194: ...Page S1 10 Supplement no S1 VFR NIGHT EQUIPMENT CONFIGURATION Ed 1 Rev 0 INTENTIONALLY LEFT BLANK ...

Страница 195: ...l Pressure 11 5 3 3 High Oil Temperature 12 5 3 4 CHT limit exceedance 13 6 IN FLIGHT ENGINE RESTART 14 7 SMOKE AND FIRE 15 7 1 Engine fire on the ground 15 7 2 Engine Fire During Takeoff 15 7 3 Engine Fire In Flight 16 7 4 Cabin Fire Electrical smoke in cabin during flight 16 7 5 Electrical smoke fire in cabin on the ground 16 8 LANDING EMERGENCIES 18 8 1 Forced Landing Without Engine Power 18 8 ...

Страница 196: ...AFMS for VFR NIGHT equipped airplanes Page 3N 2 Section 3 Emergency procedures INDEX Ed 1 Rev 0 INTENTIONALLY LEFT BLANK ...

Страница 197: ...ncy procedures are 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 theoreticall...

Страница 198: ...ALERTS 2 AIRPLANE ALERTS The alert lights located on the annunciator panel feature the following colours GREEN to indicate that pertinent device is turned ON AMBER to indicate no hazard situations which have to be considered and which require a proper crew action RED to indicate emergency conditions ...

Страница 199: ...r a faulty alternator or when voltage is above 16V in this case the over voltage sensor auto matically shuts down the alternator If ALTOUT caution is ON 1 Generator switch OFF 2 Master switch OFF 3 Generator switch ON 4 Master switch ON If ALTOUTcaution persists ON 5 Generator switch OFF 6 Audio Panel OFF 7 Land as soon as practical The battery can supply electrical power for at least 30 minutes N...

Страница 200: ...vated the green PITOT HEAT ON safe operating annunciation is ON If the amber PITOT HEAT caution turns ON the Pitot Heat system is not functioning properly In this case apply following procedure 1 Pitot Heat switch OFF 2 Check Pitot Heat circuit breaker IN 3 Pitot Heat switch ON 4 Check PITOT HEAT caution light If the amber light stays ON avoid visible moisture conditions ...

Страница 201: ...Ed 1 Rev 0 Section 3 Emergency procedures AIRPLANE ALERTS 2 3 G3X FAILURES In case of LH or RH display failure navigation and engine data will be automati cally available in the remaining display split mode INSTRUCTION revert to the remaining display ...

Страница 202: ...ped if practical 1 Parking brake ON 2 Seat belts unstrap completely 3 Headphones REMOVE 4 Door OPEN 5 Escape away from flames hot engine compartment spilling fuel tanks Hot brakes 4 ENGINE SECURING Following procedure is applicable to shut down the engine in flight 1 Throttle Lever IDLE 2 Ignition key OFF 3 Fuel Selector OFF 4 Electrical fuel pump OFF 5 Generator switch OFF ...

Страница 203: ...o the right 3 Flaps as needed WARNING Stall speed increases with bank angle and longitudinal load factor Acoustic stall warning will in any case provides a cor rect anticipated cue of incipient stall At or right before touch down 4 Throttle IDLE fully out and hold 5 Ignition key OFF 6 Fuel selector valve OFF 7 Electric fuel pump OFF 8 Alternator Master switches OFF WARNING A single engine aircraft...

Страница 204: ... 5 3 ENGINE FAILURES DURING FLIGHT 5 3 1 Low Fuel Pressure If FP LOW warning is ON 1 Electric fuel pump ON 2 Fuel selector valve select opposite fuel tankif NOT empty 3 Fuel quantity indicators Check both If FP LOW warning persists ON 4 Land as soon as possible applying forced landing procedure See Para 8 ...

Страница 205: ...ction 3 Emergency procedures ENGINE FAILURE 5 3 2 Low Oil Pressure If OP LOW warning is ON 1 Throttle Lever REDUCEto Minimum practical 2 Land as soon as practical If OP LOWwarning persists ON 3 Land as soon as possible applying forced landing procedure See Para 8 ...

Страница 206: ...ing are OFF 1 Throttle Lever REDUCE Minimum practical If oil temperature does not decrease 2 Airspeed INCREASE if practical If oil temperature does not come back within limits the thermostatic valve 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 h...

Страница 207: ...e If oil pressure is within limits OP HIGH and OP LOW warnings are OFF 1 Throttle Lever REDUCE to Minimum practical 2 Land as soon as practical The thermostatic valve regulating the water flow to the cylinder heads could be damaged or a coolant leakage can be present in the coolant supply line If CHTdoes not decrease and engine shows roughness or power loss 3 Land as soon as possible applying forc...

Страница 208: ...Electrical fuel pump ON 3 Fuel quantity indicator CHECK 4 Fuel Selector select opposite tank if not empty 5 Ignition key BOTH 6 Ignition key START 7 Throttle lever SET as required If the fuel quantity in the selected tank which feeds the engine is low select the opposite side fuel tank by means of the fuel se lector In case of unsuccessful engine restart 1 Engine SECURE see engine securing procedu...

Страница 209: ...6 Alternator Master Switches OFF 7 Parking Brake ENGAGED 8 Aircraft Evacuation carry out immediately 7 2 ENGINE FIRE DURING TAKEOFF BEFORE ROTATION ABORT TAKE OFF 1 Throttle Lever IDLE fully out and hold 2 Rudder Keep heading control 3 Brakes As required With aircraft under control 1 Fuel Selector OFF 2 Electrical fuel pump OFF 3 Ignition key OFF 4 Cabin Heat OFF 5 Alternator Master Switches OFF 6...

Страница 210: ...ara 8 7 4 CABIN FIRE ELECTRICAL SMOKE IN CABIN DURING FLIGHT 1 Cabin heating OFF 2 Cabin vents OPEN 3 Try to choke the fire Direct the fire extinguisher towards flame base If smoke persists 1 Alternator 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 is prevented 7 5 ELECTRIC...

Страница 211: ...AFMS for VFR NIGHT equipped airplanes Page 3N 17 Ed 1 Rev 0 Section 3 Emergency procedures SMOKE AND FIRE INTENTIONALLY LEFT BLANK ...

Страница 212: ...n zero wind conditions every 1000ft above Ground Level it is possible to cover ca 2 NM 8 2 POWER ON FORCED LANDING 1 Airspeed 71 KIAS 2 Flaps UP 3 Locate the most suitable terrain for emergency landing plan to approach it upwind 4 Safety belts Tighten When certain to land right before touch down 5 Flaps as necessary 6 Fuel selector valve OFF 7 Electric fuel pump OFF 8 Ignition key OFF 9 Generator ...

Страница 213: ...checklist Complete 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 4 6 Airpla...

Страница 214: ...re should be used 1 Throttle IDLE full out position and hold 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 6 Throttle Readjust to restore engine power WARNING Keep full rudder against rotation until spin has stopped One complete turn and recovery t...

Страница 215: ...event carburettor ice less effectively 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 and below of clouds visible moisture precipita tions 3 Controls surfaces continue to move to keep free from ice build up 4 Throttle speed increase rpm 5 Cabin heat ON WARNING In case of ice formation on wing leadi...

Страница 216: ...s 1 Breaker CHECK IN 2 LH RH Trim switch CHECK for correct position If jamming persists 1 Trim cutout switch CHECK ON 2 Speed adjust to control aircraft without excessive stick force 3 Land aircraft as soon as possible Trim Runaway In event of trim runaway act as follows 1 Trim cutout switch OFF 2 Speed adjust to control aircraft without excessive stick force 3 Land aircraft as soon as possible ...

Страница 217: ...ase of static ports failure the alternate static port in the cabin identified by the placard below must be activated In this case apply following procedure 1 Cabin heat OFF 2 ALTERNATE STATIC PORT VALVE OPEN 3 Continue the mission 10 4 FLAPS FAILURE In event of flaps up landing account for Approach speed 64 KIAS Landing length 35 increased ...

Страница 218: ...AFMS for VFR NIGHT equipped airplanes Ed 1 Rev 0 Section 3 Emergency procedures OTHER EMERGENCIES Page 3N 24 INTENTIONALLY LEFT BLANK ...

Страница 219: ... Supplement no S1 VFR NIGHT EQUIPMENT CONFIGURATION Ed 1 Rev 0 SECTION 4 NORMALPROCEDURES Supplement S1 Normal Procedures pages replace basic AFM Section 4 as a whole Supplement S1 pages replacement instructions ...

Страница 220: ...Page S1 12 Supplement no S1 VFR NIGHT EQUIPMENT CONFIGURATION Ed 1 Rev 0 INTENTIONALLY LEFT BLANK ...

Страница 221: ...light Inspections 5 3 1 Cabin Inspection 5 3 2 Aircraft Walk around 6 4 Checklists 12 4 1 Before Engine Starting After Pre flight Inspection 12 4 2 Engine Starting 13 4 3 Before taxiing 13 4 4 Taxiing 14 4 5 Prior to takeoff 14 4 6 Takeoff and climb 15 4 7 Cruise 15 4 8 Before Landing 16 4 9 Balked landing missed approach 16 4 10 After landing 16 4 11 Engine shut down 17 4 12 Post flight checks 17...

Страница 222: ...AFMS for VFR NIGHT equipped airplanes Section 4 Normal procedures TABLE OF CONTENTS Page 4N 2 Ed 1 Rev 0 INTENTIONALLY LEFT BLANK ...

Страница 223: ...for situa tional awareness Primary flight information is provided by analogue instru ments and for engine parameters pilot will rely upon cau tion warning lights in the annunciator panel 2 AIRSPEEDS FOR NORMAL OPERATIONS The following airspeeds are those which are significant for normal operations FLAPS 630kg Rotation Speed in takeoff VR T O 48 KIAS Best Angle of Climb Speed VX 0 65 KIAS Best Rate...

Страница 224: ...AFMS for VFR NIGHT equipped airplanes Page 4N 4 Section 4 Normal procedures AIRSPEEDS FOR NORMAL OPERATIONS Ed 1 Rev 0 INTENTIONALLY LEFT BLANK ...

Страница 225: ...documents ARC Certificate of Airworthiness Noise certificate Radio COM certificate AFM check current and on board B Weight and balance calculate ref this AFM sect 6 check within limits C Safety belts connected to hard points check condition D Ignition key OFF key extracted E Master switch ON F Voltmeter check 10 12 V G Lights all ON check for operation H Acoustic stall warning check operation I Ma...

Страница 226: ...rol surfaces visual in spection also involves additional check for freedom of movement and security Red lubber lines on bolts and nuts shall be intact WARNING Fuel level indicated by the fuel quantity indicators must be veri fied by visual check of actual fuel quantity embarked in the tanks graduated dipstick must be used WARNING If ignitions key is in L R BOTH position a propeller movement can ca...

Страница 227: ...on must be carried with the aircraft parked on a level surface Check for water or other contaminants Make sure filler cap is closed B Pitot tube REMOVE pitot plug and check the pitot for obstructions Do not blow inside pitot tube C Left side leading edge and wing skin Visual inspection CHECK stall strips D Left strobe light Visual inspection CHECK for integrity and fixing E Left aileron hinges and...

Страница 228: ...Right flap and hinges Visual inspection N Right aileron hinges and Right side tank vent Visual inspection check free of play friction Right side tank vent check for obstructions O Right strobe light leading edge and wing skin Visual inspection CHECK stall strips CHECK strobe light for integrity and fixing P Stall indicator micro switch CHECK for integrity and free of play Q Right side fuel filler ...

Страница 229: ...nd in direction of engine rotation several times and observe engine for odd noises or excessive resistance and normal compression 4 Carburettors check the throttle and choke cables for condition and installation 5 Exhaust inspect for damages leakage and general condition 6 Check engine mount and silent blocks for condition e Check oil level and replenish as required Prior to oil check switch off b...

Страница 230: ...IGHT equipped airplanes Page 4N 10 Section 4 Normal procedures PRE FLIGHT INSPECTIONS Ed 1 Rev 0 Avoid blowing inside Pitot tube and inside airspeed indicator system s static ports as this may damage instruments NOTE ...

Страница 231: ...AFMS for VFR NIGHT equipped airplanes Page 4N 11 Section 4 Normal procedures PRE FLIGHT INSPECTIONS Ed 1 Rev 0 INTENTIONALLY LEFT BLANK ...

Страница 232: ... pump noise 8 Electric fuel pump OFF 9 Avionic Master switch ON check instruments then set in OFF posi tion 10 Flap control cycle fully extended and then set to T O 11 Alternate static port check closed 12 Pitch Trim cycle fully up and down from both LH and RH controls check for trim disconnect switch operation 13 Pitch trim set neutral WARNING Pitch trim position other than in neutral position wo...

Страница 233: ...rson or object is present in the area close to the propeller Forward lower sector visibility is not possible from inside the cockpit 6 Ignition key BOTH 7 Ignition key START 8 Check OP LOW warning turns OFF within 10 sec 9 Generator switch ON 10 Voltmeter check more than 14V 11 Engine parameters all cautions warnings OF OT within the limits 12 Choke OFF 13 Propeller rpm 1000 1200 rpm 14 Electric f...

Страница 234: ...el pressure check FP LOW warning OFF 7 Throttle speed advance throttle to 1640 rpm a Ignition key test select LEFT check speed drop within 130 propel ler 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 speed 1640 rpm 8 Carburettor heat test a Pull sele...

Страница 235: ... OFF 2 Carburetor heat OFF 3 Full throttle set and check approximately 2100 100 propeller rpm 4 Engine parameters check all cautions warnings OFF 5 Rotation speed VR 48 KIAS 6 Flaps retract above flap retraction speed 58 KIAS 7 Establish Climb rate VY 71 KIAS 8 Electric fuel pump OFF 9 Fuel pressure check FP LOW warning OFF 10 Propeller speed reduce at or below 2250 rpm 4 7 CRUISE 1 Set power at o...

Страница 236: ...eg abeam touch down point Flaps set T O Approach speed 58 KIAS 5 On final leg Flaps set LAND Final Approach Speed 54 KIAS 6 Carburettor heat OFF full IN 7 Optimal touchdown speed 54 KIAS 4 9 BALKED LANDING MISSED APPROACH 1 Throttle FULL 2 Speed keep over 61 KIAS climb to VY or VX as applicable 3 Flaps position TO 4 Electric fuel pump ON 4 10 AFTER LANDING 1 Flaps UP 2 Electric Fuel Pump OFF 3 Lan...

Страница 237: ...ted 5 Strobe light OFF 6 Master Generator switches OFF 7 Fuel selector valve OFF WARNING Before disembarkation verify propeller is fully stopped CAUTION Instruct passenger to fully open RH door and depart avoiding contact with wheels and sharp wing control surfaces edges 4 12 POST FLIGHT CHECKS 1 Flight controls lock by mean of seat belts 2 Wheel chocks and wing mooring cables Set 3 Parking brake ...

Страница 238: ...AFMS for VFR NIGHT equipped airplanes Page 4N 18 Section 4 Normal procedures CHECKLISTS Ed 1 Rev 0 INTENTIONALLY LEFT BLANK ...

Страница 239: ...Page S1 13 Supplement no S1 VFR NIGHT EQUIPMENT CONFIGURATION Ed 1 Rev 0 SECTION 5 PERFORMANCE Refer to Basic AFM Section 5 Supplement S1 pages replacement instructions ...

Страница 240: ...Page S1 14 Supplement no S1 VFR NIGHT EQUIPMENT CONFIGURATION Ed 1 Rev 0 INTENTIONALLY LEFT BLANK ...

Страница 241: ...Page S1 15 Supplement no S1 VFR NIGHT EQUIPMENT CONFIGURATION Ed 1 Rev 0 SECTION 6 WEIGHT AND BALANCE Refer to Basic AFM Section 6 Supplement S1 pages replacement instructions ...

Страница 242: ...Page S1 16 Supplement no S1 VFR NIGHT EQUIPMENT CONFIGURATION Ed 1 Rev 0 INTENTIONALLY LEFT BLANK ...

Страница 243: ... S1 VFR NIGHT EQUIPMENT CONFIGURATION Ed 1 Rev 0 SECTION 7 AIRFRAME AND SYSTEM DESCRIPTION Supplement S1 Airframe and System Description pages replace basic AFM Section 7 as a whole Supplement S1 pages replacement instructions ...

Страница 244: ...Page S1 18 Supplement no S1 VFR NIGHT EQUIPMENT CONFIGURATION Ed 1 Rev 0 INTENTIONALLY LEFT BLANK ...

Страница 245: ...Fuselage 3 2 3 Empennages 3 2 4 Landing gear 4 3 Flight Controls 5 4 Instrument Panel 6 4 1 Internal Lights System 7 4 2 Carburettor Heat 7 4 3 Cabin Heat 8 5 Seats And Safety Harness 9 6 Doors 9 7 Powerplant 10 7 1 ENGINE 10 7 2 PROPELLER 10 8 Fuel System 11 9 Electrical System 12 9 1 Stall Warning System 12 9 2 Avionics 13 9 3 External Power Supply 14 10 Pitot Static Pressure Systems 15 11 Brake...

Страница 246: ...ments and a single strut brace per side The wings are made up of a central light alloy torsion box a light alloy leading edge is attached to the front spar whereas the flap slot ted and the aileron frise are attached to a rear spar through two hinges each The torsion box consists of a front and rear spar that represent its front and rear vertical walls a series of ribs and wrap around panels compl...

Страница 247: ...uselage and vertical fin are a unique body 2 3 EMPENNAGES The horizontal tail is an all moving type the stabilizer and elevator form a single uniform plane called stabilator that rotates to the desired pitch setting The stabilator structure is made up by an aluminium spar 1 and ribs 2 Aluminium skin panels are riveted to the above elements 3 1 2 3 4 Fig 7 2 STABILATOR STRUCTURE A trim tab 4 provid...

Страница 248: ...gs are attached to the fuselage structure via two couples of ma chined aluminium beams Wheels are cantilevered on gear struts and feature hydraulically actuated disc brakes controlled by toe A Pivoting nose gear is attached to the firewall reinforcement plate The Hydraulic shock absorber is fitted on the upper machined component and directly on the nose landing gear structure In the following figu...

Страница 249: ...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 three mark ings related to 0 takeoff T O and landing FULL positions A breaker posi tioned on the right side of the instrument panel protects the electric circuit Longitudinal trim is performed by the trim tab located on the stabilator through...

Страница 250: ...t out switch and LH RH selector switch the dimming devices for G3X for flexible support mounted panel lights and for instruments Nav Com instrument Garmin GNC 255A the GTX 328 transponder and the annunciator panel Electric fuel pump ON GREEN Low Oil Pressure RED Low Fuel Pressure RED Alternator Fail AMBER Pitot heat operation lights GREEN AMBER High Oil Pressure warning light RED The lower LH port...

Страница 251: ...d 2 LED lights above the annunciator panel Panel DIM device 2 emergency lights located in side area of the cabin ceiling and 1 LED light above the annunciator panel all controlled by red Emergency Switch 1 adjustable map light located in the center area of the cabin ceiling 4 2 CARBURETTOR HEAT Carburettor heat control knob is located lower LH portion of the instrument panel when the knob is pulle...

Страница 252: ...ntrol knob is positioned on the lower right side of the instrument panel when knob is pulled fully outward cabin receives maximum hot air If the outlets are kept closed hot air only performs windshield defrost Vents are located by the rudder pedals If necessary outside fresh air can be circulated inside cabin by opening the vents on the doors windows ...

Страница 253: ... material cushioning A lever located on the right lower side of each seat allows for seat adjustment ac cording to pilot size 6 DOORS Two doors are provided for P2008 JC on Pilot and co pilot side A sketch of the door is shown below RH and LH doors are specular Fig 7 6 DOOR The door is equipped with a gas spring fixed to the fuselage that facilitates door opening Gas spring support Fuselage side G...

Страница 254: ...Type 4 stroke horizontally 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 7 2 PROPELLER Manufacturer GT Propellers Model GT 2 173 VRR FW101 SRTC N of blades 2 Diameter 1730 mm no reduction permitted Type wood fixed pitch ...

Страница 255: ...y of each tank is 62 liters for a total of 124 liters The internal side of fuel tank is accessible for inspection through two dedicated doors The fuel tank filler cap is located on the top of the wing in the area outside of the tank and it is easily accessible from the leading edge of the aircraft At the lowest point of the tank it is positioned a drain sump The engine is equipped with an engine g...

Страница 256: ... is only connected to the G3X units It is installed beside the main battery and is housed in a dedicated box The switch between the energy sources alternator and main battery is automatic and no action is required in order to activate the alternate energy source For ground maintenance and or starting an external power socket is provided The alternator and battery are connected to the battery bus i...

Страница 257: ...3X also embodies a GPS WAAS receiver whose information intended for situ ational awareness only are presented on RH display moving map Two dedicated indicators provide the pilot with information about the flaps and pitch trim position Stand alone external COM NAV and transponder sources Garmin GNC 255A and GTX 328 are installed Garmin GNC 255A navigation information is presented on the display cou...

Страница 258: ...nal power source It should be used at the engine start up in cold weather condition For en gine start below 17 C OAT it is advisable to use the external power source Follow this procedure to start the engine using the external power source 1 Magnetos Master switch Generator switch OFF 2 Open the receptacle door and insert the external power source s plug into the socket 3 Engine start up procedure...

Страница 259: ...d in correspon dence of engine firewall on left and right side of fuselage Flexible plumbing con nects total pressure and static ports to primary analogue instruments anemometer and altimeter An alternate static source is located in the cabin operated by a dedi cated control Garmin G3X ADAHRS GSU73 unit installed on the rear side of the fuselage near the battery acts as an air data computer for Ga...

Страница 260: ...rs the brake via lines con nected to the caliper A parking brake valve mounted in correspondence of the cabin floor and operated by a knob on the cockpit central pedestal intercepts the hydraulic lines once pressu rized by toe brakes to hold the brake assemblies linings tightened round the main wheels brake discs Brakes can be operated from either pilot s and co pilot s pedals a single vented oil ...

Страница 261: ...AFMS for VFR NIGHT equipped airplanes Page N7 17 Section 7 Airframe and Systems description BRAKES Ed 1 Rev 0 INTENTIONALLY LEFT BLANK ...

Страница 262: ...AFMS for VFR NIGHT equipped airplanes Page N7 18 Section 7 Airframe and Systems description BRAKES Ed 1 Rev 0 INTENTIONALLY LEFT BLANK ...

Страница 263: ...Page S1 19 Supplement no S1 VFR NIGHT EQUIPMENT CONFIGURATION Ed 1 Rev 0 SECTION 8 GROUND HANDLING SERVICE Refer to Basic AFM section 8 Supplement S1 pages replacement instructions ...

Страница 264: ...Page S1 20 Supplement no S1 VFR NIGHT EQUIPMENT CONFIGURATION Ed 1 Rev 0 INTENTIONALLY LEFT BLANK ...

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