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TORMSCOPE

Page ST7-46

Section 7 – Airframe and Systems description

WX500 Stormscope system

Ed.4, Rev.0

19.

WX500

TORMSCOPE SYSTEM

The thunderstorm detection passive sensor WX500 Stormscope is fully operated

and displayed via the Garmin G950 Multi function display, in the map menu. Is is

installed in order to shown the lightning data.
The sensor maps discharge the electrical activity for 360 degrees around the aircraft

to a distance of 200 nautical miles, in relation to the aircraft’s

Stormscope

antenna.

The estimated distance from the aircraft to the discharge point is reported in NM

while the bearing represents the angle between the fore and aft axis of the antenna,

which is in line with the longitudinal axis (nose) of the aircraft.
The WX-500 processor is installed in the right side of the baggage compartment

while the NY-163 antenna is installed on the bottom side of the tail.

For more details see WX-500 Installation Manual and the latest revision of the

Garmin G950 Pilot's guide Doc. No.: 190-00726-00.

19.1

WIRING

DIAGRAM

CABLE

INTERCONNECTION

In the following figure the

Stormscope

wiring diagram is reported.

Wiring diagram

Summary of Contents for P2006T

Page 1: ...by European Aviation Safety Agency EASA This Manual contains information required by the FAA to be furnished to the pilot for operation in the U S A plus information supplied by the manufacturer It is approved by EASA on behalf of the FAA per FAR 21 29 This Manual must be carried in the airplane at all times The airplane has to be operated in compliance with procedures and limitations contained he...

Page 2: ...Page 0 2 4th Edition Rev 0 Aircraft Flight Manual INDEX SECTION 0 INDEX 1 RECORD OF REVISIONS 3 2 LIST OF EFFECTIVE PAGES 7 3 FOREWORD 10 4 SECTIONS LIST 11 ...

Page 3: ... be necessary to completely 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...

Page 4: ...ement List D Ronca M Oliva M Oliva Add Supplement A24 D Ronca M Oliva M Oliva Add Supplement A25 D Ronca M Oliva M Oliva Add Supplement G14 D Ronca M Oliva M Oliva Add Supplement G16 D Ronca M Oliva M Oliva Add Supplement G17 D Ronca M Oliva M Oliva 2 4 3 4 Amend General recommendation D Ronca M Oliva M Oliva Approved under the au thority of DOA ref EASA 21J 335 MOD2006 290 170316 4 18 19 Amend Pr...

Page 5: ...Page 0 5 4th Edition Rev 0 Aircraft Flight Manual INTENTIONALLY LEFT BLANK ...

Page 6: ...4th Edition Rev 0 Aircraft Flight Manual Page 0 6 INTENTIONALLY LEFT BLANK ...

Page 7: ...r 22 2011 3rd Edition Rev 1 October 15 2012 3rd Edition Rev 2 June 4 2013 3rd Edition Rev 3 February 13 2014 3rd Edition Rev 4 May 5 2014 3rd Edition Rev 5 June 10 2015 4th Edition Rev 0 July 25 2015 4th Edition Rev 1 April 6 2016 4th Edition Rev 2 March 16 2017 Section Pages Revision Section 0 Pages 1 thru 3 5 6 8 trhu 11 Rev 0 Pages 4 7 Rev 1 Section 1 Pages 1 thru 18 Rev 0 Section 2 Pages 1 thr...

Page 8: ...Page 0 8 4th Edition Rev 0 Aircraft Flight Manual INTENTIONALLY LEFT BLANK ...

Page 9: ...4th Edition Rev 0 Aircraft Flight Manual Page 0 9 INTENTIONALLY LEFT BLANK ...

Page 10: ...ral 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 AERONAUTICHE TECNAM s r l Via MAIORISE CAPUA CE ITALY 39 0 823 62 01 34 ww...

Page 11: ...ection 3 a non approved Chapter Normal Procedures Section 4 a non approved Chapter Performances Section 5 a non approved Chapter Weight and Balance Section 6 a non approved Chapter Airframe and Systems description Section 7 a non approved Chapter Airplane Care and Maintenance Section 8 a non approved Chapter Supplements Section 9 EASA approved parts if any are reported on the supplements ...

Page 12: ...e view and dimensions 4 3 Control Surfaces Travel Limits 6 4 Engine 6 5 Propeller 6 6 Governor 7 7 Fuel 7 8 Lubrication 7 9 Cooling 8 10 Maximum weights 8 11 Standard weights 8 12 Specific loadings 8 13 Acronyms and terminology 10 14 Unit conversion chart 15 15 Litres US gallons conversion chart 16 ...

Page 13: ...Page 1 2 Section 1 General 4th Edition Rev 0 INTENTIONALLY LEFT BLANK ...

Page 14: ... apply to warnings cautions and notes used in the Aircraft Flight Manual WARNING The non observation of the corresponding procedure can lead as immediate effect to a significant reduction of the flight safety CAUTION The non observation of the corresponding procedure can lead to an equipment damage which leads to a reduction of the flight safe ty in a short or longer time interval Draws the attent...

Page 15: ...Page 1 4 Section 1 General THREE VIEW AND DIMENSIONS 4th Edition Rev 0 2 THREE VIEW AND DIMENSIONS P2006 T GENERAL VIEW Figure 1 General views ...

Page 16: ...ft Length 8 7 m 28 5 ft Overall height 2 58 m 8 46 ft Wing Wing surface 14 76 m2 158 9 ft2 Mean Geometric Chord 1 295 m 4 25 ft Dihedral 1 Aspect ratio 8 80 Main Landing Gear Track 2 0 m Wheelbase 2 9 m Tire 6 00 6 Wheel rim assembly Cleveland P N 40 59A Nose Landing Gear Tire 5 00 5 Wheel rim assembly Cleveland P N 40 77C ...

Page 17: ...S no E 121 dated 1 April 2008 Engine type 4 cylinders horizontally opposed with 1352 c c of overall displacement liquid cooled cylinder heads ram air cooled 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 5 PROPELLER Manufacturer MT...

Page 18: ...d with drainable sump and drain valve Capacity of each wing tan 100 litres 26 42 US gallons Tanks overall capacity 200 litres 52 8 US gallons Overall usable fuel 194 4 litres 51 35 US gallons Overall unusable fuel 5 6 litres 1 48 US gallons 8 LUBRICATION Lubrication system Forced type with external reservoir Oil Use only oil with API classification SG or higher For additional info refer to Ro tax ...

Page 19: ...perators Manual last issue Overall circuit capacity 1410 cm3 10 WEIGHTS See Section 2 11 STANDARD WEIGHTS Empty Weight see weighing record on Section 6 12 SPECIFIC LOADINGS NOTE Reference is made to both MTOW 1180 kg and 1230 kg if Supplement A19 or G10 Increased MTOW 1230 KG is applicable MTOW 1180 kg 2601 lb MTOW 1230 kg 2712 lb Wing Loading 80 kg m2 16 37 lb sqft 83 kg m2 17 1 lb sqft Power Loa...

Page 20: ...Page 1 9 Section 1 General GENERAL FEATURES 4th Edition Rev 0 INTENTIONALLY LEFT BLANK ...

Page 21: ...r extended VMC Minimum control speed is the minimum speed necessary to en sure an efficient aircraft control in case of one engine inopera tive 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 w...

Page 22: ...with respect to 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 decr...

Page 23: ...quantity of 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 s...

Page 24: ...or equipment would balance if suspended Its distance from the reference datum is found by dividing the total moment 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 tak...

Page 25: ...Page 1 14 Section 1 General 4th Edition Rev 0 INTENTIONALLY LEFT BLANK ...

Page 26: ...00508 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 2...

Page 27: ... 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 28: ...Page 1 17 Section 1 General 4th Edition Rev 0 INTENTIONALLY LEFT BLANK ...

Page 29: ...Page 1 18 Section 1 General 4th Edition Rev 0 INTENTIONALLY LEFT BLANK ...

Page 30: ...12 12 Other instruments markings 12 13 Warnings cautions and advisories lights 13 14 Weights 15 15 Center of gravity range 17 16 Approved maneuvers 19 17 Maneuvers load factor limits 19 18 Flight crew 19 19 Flight conditions 20 20 Fuel 20 21 Limitations placards 21 21 1 Speed limitations 21 21 2 Operating limitations 22 21 3 Inflight engine restart 23 21 4 Baggage compartment capacity 23 21 5 Engi...

Page 31: ...Page 2 2 Section 2 Limitations 4th Edition Rev 0 INTENTIONALLY LEFT BLANK ...

Page 32: ...INTRODUCTION EASA Approved 1 INTRODUCTION Section 2 includes operating limitations instrument markings and basic placards necessary for safe operation of P2006T aircraft its engines and standard systems and equipment This AFM Section is EASA approved ...

Page 33: ...Page 2 4 4th Edition Rev 0 Section 2 Limitations INTENTIONALLY LEFT BLANK ...

Page 34: ...speed 122 119 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 VLE Maximum Landing Gear ex tended speed 93 93 Do not exceed this speed with the landing gear ex tended VLO Maximum Landing Gear op erating speed 93 93 Do not exceed this speed when operating the landin...

Page 35: ...GARMIN G950 IFDS Increased MTOW 1230 kg Page SW2 6 Section 2 Limitations 3rd Edition Rev 0 EASA Approved INTENTIONALLY LEFT BLANK ...

Page 36: ... allowable speed with flaps extended in FULL position Red line 62 Minimum aircraft control speed with one en gine inoperative and flaps set to T O Green band 66 138 Normal aircraft operating range lower limit is VS1 stall speed in clean configuration and upper limit is the maximum structural cruise speed VNO Blue line 84 Best rate of climb speed with one engine in operative at sea level Yellow ban...

Page 37: ...GARMIN G950 IFDS Increased MTOW 1230 kg Page SW2 8 Section 2 Limitations 3rd Edition Rev 0 EASA Approved INTENTIONALLY LEFT BLANK ...

Page 38: ...0 Temperatures Max CHT 135 C Max CT 120 C Min Max Oil 50 C 130 C Oil normal operating range approx 90 C 110 C applicable for Engines up to serial no 4924543 included and repaired engine which doesn t change the cylinder head n 3 with new one part no 413195 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 En...

Page 39: ...For additional info refer to Rotax Operators Manual last issue Operating Media Section 6 COOLANT LIQUID Refer to Rotax Operators Manual last issue Operating Media Section 7 PROPELLER MANUFACTURER MT Propeller MODEL MTV 21 A C F CF178 05 TYPE wood composite 2 blade variable pitch hydraulically con trolled and fully featherable DIAMETER 1780 mm no reduction is permitted 8 GOVERNOR MANUFACTURER MT Pr...

Page 40: ...ove 12500 ft 3810 m up to and including 14000 ft 4260 m flight must be limited to 30 minutes unless the required minimum 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 duration 10 AMBIENT TEMPERATURE Ambient temperature from 25 C to 50 C WARNING Flight in expected and or known icing conditions is forbidden ...

Page 41: ...r 0 8 2 5 0 8 2 5 7 2 7 Fuel press psi 2 2 2 2 5 8 or 7 23 5 8 or 7 23 Fuel Q ty litres 0 4 12 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 1 applicable for Engines up to serial no 4924543 included and repaired engine which doesn t change the cylinder head n 3 with new one part no 41...

Page 42: ...and or unlocked LH ENGINE FIRE Left engine compartment fire detected RH ENGINE FIRE Right engine compartment fire detected LG TRANSITION warning light installed near the landing gear control lever One or more legs are in transition phase and or the selected retracted extended position is not yet reached Caution alert AMBER Cause L ALT FAIL LH generator failure R ALT FAIL RH generator failure PITOT...

Page 43: ...ASA Approved Aural means are provided by Garmin G950 System a repeating tone is associated to the warning alerts and a single chime is associated to the caution alerts Safe op erating annunciations do not have any aural chime generated Make reference to Garmin G950 Pilot s Guide for P2006T last issue Annuncia tions and alerts Appendix A ...

Page 44: ...ons WEIGHTS 3rd Edition Rev 0 EASA Approved 14 WEIGHTS Refer to Para 21 4 of this AFM Section for baggage loading limitations Condition Weight Maximum takeoff weight 1230 kg 2712 lb Maximum landing weight 1230 kg 2712 lb Maximum zero wing fuel weight 1195 kg 2635 lb NOTE ...

Page 45: ...GARMIN G950 IFDS Increased MTOW 1230 kg Page SW2 16 Section 2 Limitations 3rd Edition Rev 0 INTENTIONALLY LEFT BLANK ...

Page 46: ...aircraft must be levelled in the longitudinal plane Levelling Refer to the seat track supporting beams see procedure in Section 6 Forward limit 0 221 m 16 5 MAC aft of datum for all weights Aft limit 0 415 m 31 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 ...

Page 47: ...Section 2 Limitations 4th Edition Rev 0 Page 2 18 INTENTIONALLY LEFT BLANK ...

Page 48: ...vres including spins and turns with angle of bank of more than 60 are not approved for such a category In addition stall with one engine inoperative is forbidden WARNING Limit load factor could be exceeded by moving flight controls to maxi mum deflection at a speed above VA VO 118 KIAS Manoeuvring Speed 17 MANEUVERS LOAD FACTOR LIMITS Maneuver load factors limits are as follows Positive Negative 3...

Page 49: ... owner is responsible for ful filling these requirements Equipment list is addressed in Section 6 20 FUEL 2 TANKS 100 litres each one 26 42 US gallons MAXIMUM CAPACITY 200 litres 52 8 US gallons MAXIMUM USABLE FUEL 194 4 litres 51 35 US gallons 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 i...

Page 50: ...1 EASA Approved 21 LIMITATIONS PLACARDS Hereinafter the placards related to the operating limitations and installed on P2006T are reported 21 1 SPEED LIMITATIONS On the left side instrument panel the following placards reporting the speed limi tations are placed Speed limitations placard for MTOW 1230 kg 2712 lb ...

Page 51: ...e ob servance of aircraft operating limitations make reference to Para 22 for the list of equipment required on board to allow flight operations in VFR Day VFR Night IFR Day and IFR Night conditions This A C can be operated only in normal category DAY NIGHT VFR IFR with required equipment in non icing conditions All aerobatics manoeuvres in cluding spinning are prohibited For operational lim itati...

Page 52: ...ocedure is reported on a placard shown below in stalled on the central console 21 4 BAGGAGE COMPARTMENT CAPACITY The placard shown below and installed on the baggage compartment vertical pan el concerns the baggage compartment load limitations herein reported Maximum allowable load 80kg 176lb Maximum intensity of loading 0 9 kg dm2 19 lbs sqft ...

Page 53: ...correspondence of the engine oil reservoir access door it is located the following placard addressing the limitations concerning the oil level the oil volume and the oil type 21 6 FUEL TYPE In correspondence of each fuel tank filler cap it is located the following placard re porting the approved fuel type and the tank usable fuel OR ...

Page 54: ...YSTEM The placard shown below and located on the tail cone concerns the allowed low pressure limit for the landing gear emergency accumulator The low pressure limit is 20 bar If during pre flight inspection the value is below 20 bar the system must be re charged by means of the override button see Section 7 Para 9 ...

Page 55: ...Edition Rev 0 2nd Edition Rev 0 EASA Approved Page 2 26 21 8 REAR SEATS During Taxi Take OFF Landing including Emergency Landing both rear seats must be kept in the lowest and full aft position The following placard is located aside both rear seats ...

Page 56: ...ctions Ditching emergency exit handle internal side Ditching emer gency exit opening in structions Ditching emergency exit handle external side Door locking system by pass instruc tions Main door and emer gency exit external side Door locking system by pass instruc tions Main door and emer gency exit internal side Main door exit instructions Main door internal side Emergency ex it label Emergency ...

Page 57: ...Page 2 28 Section 2 Limitations 4th Edition Rev 0 2nd Edition Rev 0 INTENTIONALLY LEFT BLANK ...

Page 58: ...ed on board under CS 23 regulations to allow flight operations in VFR Day VFR Night IFR Day and IFR Night conditions Flight in VFR Day and Night IFR Day and Night is permitted only if the pre scribed equipment is installed and operational Additional equipment or a different equipment list for the intended operation may be required by national operational requirements and also depends on the route ...

Page 59: ...r electric StandbyAltimeter Pitot heating system Clock Breakers panels First Aid kit Fire extinguisher Fire detectors 2 Instruments lights Position lights Landing light Taxi light Strobe lights Torch Cabin light Cockpit lights Emergency light Volt Ammeter LG position and transition lights ELT Alternate static source MAP indicator dual RPM indicator 2 Oil pressure indicator 2 Oil temperature indica...

Page 60: ...Section 2 Limitations 4th Edition Rev 0 Page 2 31 INTENTIONALLY LEFT BLANK ...

Page 61: ...Section 2 Limitations 4th Edition Rev 0 Page 2 32 INTENTIONALLY LEFT BLANK ...

Page 62: ...16 2 12Loss of vertical speed information 17 2 13Loss of heading information 17 2 14Display failure 19 3 ENGINE SECURING 21 4 POWERPLANT EMERGENCIES 23 4 1 Propeller overspeeding 23 4 2 CHT limit exceedance 24 4 3 Oil temperature limit exceedance 25 4 4 Oil pressure limits exceedance 26 4 5 Low fuel pressure 27 5 Other emergencies 29 5 1 Emergency descent 29 5 2 Total electrical failure 29 5 3 Sta...

Page 63: ...sion 47 8 SMOKE AND FIRE OCCURRENCE 49 8 1 Engine fire on the ground 49 8 2 Engine fire during takeoff run 50 8 3 Engine fire in flight 52 8 4 Electrical smoke in cabin on the ground 52 8 5 Electrical smoke in cabin during flight 53 9 UNINTENTIONAL SPIN RECOVERY 55 10 LANDING EMERGENCIES 56 10 1Landing without engine power 56 10 2Landing with Nose landing gear tire deflated 58 10 3Landing with a k...

Page 64: ... the correct and complete sequence immediately after the failure is detected and confirmed These procedures characters are boxed and highlighted 1 1 ENGINE FAILURE DURING TAKEOFF RUN BEFORE ROTATION ABORT TAKE OFF 1 Throttle Lever BOTH IDLE 2 Rudder Keep heading control 3 4 b other procedures which should be well theoretically known and mastered but that can be executed entering and following step...

Page 65: ...y case as a failure or abnormal behaviour is detected pilots should act as follows 1 Keep self control and maintain aircraft flight attitude and parameters 2 Analyse the situation identifying if required the area for a possible emergency landing 3 Apply the pertinent procedure 4 Inform the Air Traffic Control as applicable For the safe conduct of later flights any anomaly and or failure must be co...

Page 66: ...Garmin G950 IFDS Supplement Page S3 5 Section 3 Emergency procedures INTRODUCTION 4th Edition Rev 0 INTENTIONALLY LEFT BLANK ...

Page 67: ... chime Caution alert text is shown in yellow in the Annunciation Window and is ac companied by a single chime and a flashing CAUTION Softkey annunciation Selecting the CAUTION Softkey acknowledges the presence of the caution alert Caution voice alerts repeat three times or until acknowledged by selecting the CAUTION Softkey All aircraft annunciations can be displayed simultaneously in the Annuncia...

Page 68: ...ential electrical power The battery and a single generator are able to supply the electrical power necessary for flight but redundancy is lost If conditions permit Switching CROSS BUS OFF will further reduce alternator load the decision mainly depends on weather conditions 6 CROSS BUS LH or RH OFF Equipment will be lost accordingly to the following table LH Gen Bus LH Avionic Bus RH Avionic Bus RH...

Page 69: ...drill Para 2 1 If both LH and RH ALT cautions stay displayed 3 FIELD LH and RH BOTH OFF 4 CROSS BUS LH and RH BOTH OFF If engine starting battery modification is applied 5 EMERG BATT switch ON 6 Land as soon as possible If engine starting battery modification is not applied 5 Land as soon as possible Equipment will be lost accordingly to the following table LH Gen Bus LH Avionic Bus RH Avionic Bus...

Page 70: ... ON one at a time If LH or RH BUS VOLT HIGH warning is still displayed 6 Verify good ammeter indications on restored alternator 7 Switch CROSS BUS on the restored alternator side 8 Refer to Single alternator failure overvoltage drill Para 2 1 If both LH and RH BUS VOLT HIGH warning are still displayed 6 FIELD LH and RH BOTH OFF If engine starting battery modification is applied 7 EMERG BATT switch...

Page 71: ...splayed In this case apply following procedure ON THE GROUND 1 Passengers and crew seat belts 2 Affected door Fasten and tighten Verify correctly closed If door is open 3 Relevant engine Shut down 4 Affected door Close and check If door is closed 3 Locking device Check If down in unlocked position 4 Abort mission IN FLIGHT 1 Passengers and crew seat belts 2 Affected door and locked device Fasten a...

Page 72: ...rned ON If the amber PITOT HEAT caution light turns OFF then the Pitot Heating system is functioning properly Anytime the amber PITOT HEAT caution light is ON at the same time the green PITOT HEAT light is ON then the Pitot Heating system is not functioning properly 1 Pitot heat switch OFF 2 Verify Pitot Heating circuit breaker is IN 3 Pitot heat switch ON 4 Check PITOT HEAT caution light If the a...

Page 73: ...warning alert is displayed Low coolant level condition may lead to high CHT CT When the warning is displayed apply following procedure 1 Check affected engine CHT CT If CHT is above 135 C or CT is above 120 C 2 Affected engine Reduce power setting to reduce CHT CT up to the minimum practical 3 Land as soon as practical If CH CT continues to rise and engine shows roughness or power loss 4 Affected ...

Page 74: ... the red TRANS light turns OFF and the GEAR PUMP ON caution stays turned ON this could indicate a gear pump relay failure to ON If TRANS light is OFF 1 Continue the mission monitoring the caution light If TRANS light is ON 2 Landing gear is not locked in UP position The electrical gear pump continuously supplied causes a current absorption which does not affect the mission unless this failure is c...

Page 75: ...tion window Alert window LH ENGINE FIRE Left engine fire detected OR RH ENGINE FIRE Right engine fire detected In event of engine fire the LH or RH ENGINE FIRE warning alert is displayed Refer to following procedures FIRE ON THE GROUND see Para 8 1 FIRE DURING TAKEOFF RUN see Para 8 2 FIRE IN FLIGHT see Para 8 3 ...

Page 76: ... a message advisory alert issuing a flashing ADVISORY Softkey annunciation which once selected acknowledges the presence of the message advisory alert and displays the alert text message in the Alerts Window Refer to G950 Pilot s Guide for Tecnam P2006T P N 190 01146 00 last issue Appendix A Message Advisories list 2 10 LOSS OF AIRSPEED INFORMATION AIRSPEED FAIL RED X ON DISPLAY FIELD Display syst...

Page 77: ...L RED X ON DISPLAY FIELD Display system is not receiving attitude information from the AHRS INSTRUCTION revert to standby analogical attitude indicator 2 11 LOSS OF ALTITUDE INFORMATION ALTITUDE FAIL RED X ON DISPLAY FIELD Display system is not receiving altitude input from the Air Data Computer INSTRUCTION revert to standby analogical altitude indicator ...

Page 78: ...ERT SPEED FAIL RED X ON DISPLAY FIELD Display system is not receiving vertical speed input from the Air Data Computer INSTRUCTION determine vertical speed on the basis of altitude information 2 13 LOSS OF HEADING INFORMATION HDG RED X ON DISPLAY FIELD Display system is not receiving valid heading input from AHRS INSTRUCTION revert to magnetic compass ...

Page 79: ...Garmin G950 IFDS Supplement Page S3 18 Section 3 Emergency procedures G950 SYSTEM FAILURES 4th Edition Rev 0 INTENTIONALLY LEFT BLANK ...

Page 80: ...g display in the same format as in normal operating mode The change to backup paths is completely automated for all LRUs and no pilot action is required if the system fails to detect a display problem 1 DISPLAY BACKUP button PUSH CAUTION If a display fails the related Integrated Avionics Unit IAU is cut off and can no longer communicate with the remaining dis play consequently the NAV and COM func...

Page 81: ...Garmin G950 IFDS Supplement Page S3 20 Section 3 Emergency procedures G950 SYSTEM FAILURES 4th Edition Rev 0 INTENTIONALLY LEFT BLANK ...

Page 82: ...tion BOTH OFF 3 Propeller Lever FEATHER 4 Fuel Selector OFF 5 Electrical fuel pump OFF After securing engine s after analysing situation refer immediately to following procedures ENGINE FAILURE IN FLIGHT see Para 6 5 SINGLE GENERATOR FAILURE see Para 2 1 or BOTH GENERATOR FAILURE see Para 2 2 INFLIGHT ENGINE RESTART see Para 6 2 ONE ENGINE INOPERATIVE LANDING see Para 6 6 or LANDING WITHOUT ENGINE...

Page 83: ...Garmin G950 IFDS Supplement Page S3 22 Section 3 Emergency procedures 4th Edition Rev 0 INTENTIONALLY LEFT BLANK ...

Page 84: ...speeding in flight apply following procedure 1 Throttle Lever REDUCE power to minimum practical 2 Propeller Lever REDUCE as practical not in feathering 3 RPM indicator CHECK If it is not possible to decrease propeller rpm apply engine securing procedure see Para 3 and land as soon as possible applying one engine inoperative land ing procedure See Para 6 6 CAUTION Maximum propeller rpm exceedance m...

Page 85: ...eck affected engine CHT CT If CHT is above 135 C or CT is above 120 C 2 Affected engine Reduce power setting to reduce CHT CT up to the minimum practical 3 Land as soon as practical If CHT CT continues to rise and engine shows roughness or power loss 4 Affected engine SECURE securing procedure on Para 3 5 Land as soon as possible applying one engine inoperative landing proce dure See Para 6 6 ...

Page 86: ...t 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 5 Land as soon as practical keeping the affected engine to the mini mum necessary power 6 Monitor OIL PRESS and CHT CT if engine roughness vibrations or erratic behaviour is detected 7 Affected engine SECURE engine securing procedu...

Page 87: ...ve oil pressure value can be counteracted by decreas ing propeller rpm 1 OIL PRESS CHECK If oil pressure exceeds upper limit 7 bar 2 Throttle Lever first REDUCE affected engine power by 10 3 Propeller Lever Keep low rpm 4 OIL PRESS CHECK verify if came back within the limits 5 Land as soon as practical If oil pressure is under the lower limit 0 8 bar 2 Land as soon as practical If oil pressure is ...

Page 88: ...wer limit 2 2 psi apply following proce dure 1 Fuel press CHECK 2 Fuel quantity CHECK 3 Fuel consumption MONITOR If a fuel leakage is deemed likely 5 Land as soon as possible If a fuel leakage can be excluded 4 Electrical fuel pump ON 5 Feed the affected engine by means of opposite side fuel tank If pressure does not come back within the limits 6 Land as soon as practical ...

Page 89: ...Garmin G950 IFDS Supplement Page S3 28 Section 3 Emergency procedures 4th Edition Rev 0 INTENTIONALLY LEFT BLANK ...

Page 90: ... VLO VLE 4 Landing gear DOWN 5 Airspeed Up to VLE 5 2 TOTAL ELECTRICAL FAILURE In case of electrical system overall failure apply following procedure 1 Emergency light ON if necessary 2 MASTER SWITCH OFF 3 FIELD LH and RH BOTH OFF 4 MASTER SWITCH ON 5 FIELD LH and RH BOTH ON If failure persists 9 EMERG BATT switch ON if engine starting battery installed 10 Land as soon as possible applying emergen...

Page 91: ...dures OTHER EMERGENCIES 4th Edition Rev 0 5 3 STATIC PORTS FAILURE In case of static ports failure the alternate static port in the cabin shown below must be activated 1 Cabin ventilation OFF hot and cold air 2 ALTERNATE STATIC PORT VALVE OPEN 3 Continue the mission ...

Page 92: ...ging altitude and or direction 4 Control surfaces Move continuously to avoid locking 5 Propellers rpm INCREASE to prevent ice build up on the blades WARNING In event of ice build up in correspondence of wing leading edges stall speed increases WARNING Ice build up on wing tail fin or flight control surfaces unexpected sud den roll and or pitch tendencies can be experienced and may lead to unusual ...

Page 93: ...ric precipi tation are present Generally an OAT to dew point temperature spread lower than 10 C and OAT less than 15 C with visibility lower than 5 km is a positive indication of likely ic ing formation condition Should an inadvertent flight into known or forecast icing condition happen carbu rettor heating should be selected ON as soon as possible the greater the ad vance carburettors are warmed ...

Page 94: ... O distance 50 ft height obstacle distance increased by about 20 1 Airspeed Keep below 93 KIAS 2 Land as soon as practical DURING APPROACH LANDING CAUTION If the flaps control fails consider the higher stall speed see Sec tion 5 Para 6 Stall Speed and an increased landing dis tance of about 25 1 Airspeed Keep over 75 KIAS 2 Land as soon as practical on a runway of appropriate length ...

Page 95: ...extended control surfaces will lead to a performances drop a quick pitch attitude re duction will allow to keep a minimum safety airspeed The higher is the airspeed the better will be lateral and directional control efficiency never allow airspeed to drop below VMCA CAUTION Best residual climb performances in OEI One Engine Inoperative condition have been recorded in Flap Up configuration and at V...

Page 96: ...ondition OEI pilot shall take into account the airspeeds shown below Conditions Speed KIAS Minimum aircraft control speed with one en gine inoperative and flaps set to T O VMC 62 Best rate of climb speed OEI VYSE MTOW 1180 kg MTOW 1230 kg 80 84 Best gradient speed OEI VXSE 79 83 Reference is made to MTOW 1180 kg and 1230 kg at Sea Level and ISA condition if Supplement G10 Increased MTOW 1230 KG is...

Page 97: ...Start push button PUSH 11 Propeller Lever SET at desired rpm 12 FIELD ON check for positive ammeter 13 Engine throttle levers SET as required If engine restart is unsuccessful 14 EMERG BATT switch ON if starting battery installed 15 Repeat engine restart procedure CAUTION After engine restart if practical moderate propeller rpm and throttle increase to allow OIL and CHT CT temperatures for stabili...

Page 98: ...ested GO NO GO criteria is abort take off until LG is still down and locked Once airborne accelerate to Blue Line Speed VYSE before command ing LG retraction Take off planning should take into account that high density altitude and aircraft mass may result in OEI negative climb rate VYSE with flap up shall be flown in order to achieve best possible rate of climb after landing gear retraction and e...

Page 99: ...ngine Check engine instruments 12 Operating engine Fuel Selector Check correct feeding crossfeed if needed If engine restart is recommended 13 Apply INFLIGHT ENGINE RESTART procedure see Para 6 2 If engine restart is unsuccessful or it is not recommended 13 Land as soon as possible 14 One engine inoperative landing procedure see Para 6 6 WARNING Following mechanical engine seizure fire major prope...

Page 100: ...heck ON 7 Inoperative engine Propeller Lever FEATHER 8 Inoperative engine Confirm and SECURE If engine restart is possible 9 Apply INFLIGHT ENGINE RESTART procedure see Para 6 2 If engine restart is unsuccessful or it is not recommended 9 Land as soon as possible 10 One engine inoperative landing procedure see Para 6 6 WARNING Following a mechanical engine seizure fire or a major propeller dam age...

Page 101: ...l Selector Check correct feeding crossfeed if needed If engine restart is possible 7 Apply INFLIGHT ENGINE RESTART procedure see Para 6 2 If engine restart is unsuccessful or it is not recommended 8 Land as soon as possible 9 One engine inoperative landing procedure see Para 6 6 WARNING Following a mechanical engine seizure fire or a major propeller dam age engine restart is not recommended WARNIN...

Page 102: ...gle engine go around Balked land ing climb and Para 13 and 14 One engine Rate of Climb at VYSE and VXSE WARNING Autopilot must be kept OFF 1 Seat belts Tightly fastened 2 Landing lights As required 3 Operating engine Fuel Selector Check correct feeding crossfeed if needed 4 Inoperative engine Propeller Lever CHECK FEATHER 5 Inoperative engine CHECK SECURED 6 Operative engine Electrical fuel pump O...

Page 103: ... TRANS indicates that one or more legs are moving and the PUMP ON amber light on the annunciator panel indicates the hydraulic gear pump is operating 1 Airspeed below applicable VLO VLE 2 Landing gear control lever DOWN 3 Emergency gear extension access door REMOVE 4 RH control lever ROTATE 90 counterclockwise 5 Wait at least 20 seconds Main Landing Gear legs green lights may be turned on thus ind...

Page 104: ... port number of persons on board and remaining fuel type and quanti ty If a complete Landing Gear up or a Nose Landing Gear up position is reported Preparation 1 Reduce fuel load if time and conditions permit 2 Crew and passengers safety belts Tightly fastened 3 Landing gear control lever UP 4 Green lights and TRANS light CHECK OFF 5 Flap setting plan approach with Flap Land Before ground contact ...

Page 105: ...R SYSTEM FAILURES 4th Edition Rev 0 14 Aircraft Evacuation carry out if necessary WARNING Consider use of ditching emergency exit to escape in case pilot or passenger doors are blocked watch for engine hot parts fuel hydraulic fluid or oil spills Leave aircraft in upwind di rection ...

Page 106: ... fly by at safe speed and altitude to have confirmation about its situation If possible coordinate fire brigade intervention along runway and re port number of persons on board and remaining fuel type and quanti ty Preparation 1 Reduce fuel load if time and conditions permit 2 Crew and passengers safety belts Tightly fastened 3 Landing gear control lever UP 4 Green lights and TRANS light CHECK OFF...

Page 107: ...H OFF 15 MASTER SWITCH OFF CAUTION Master switch to OFF impairs radio communication and outside air craft lighting 16 Aircraft Evacuation carry out if necessary WARNING Consider use of ditching emergency exit to escape in case pilot or passenger doors are blocked watch for engine hot parts fuel hydraulic fluid or oil spills Leave aircraft in upwind di rection ...

Page 108: ...onfiguration is not obtained 4 Emergency LG extension procedure Apply See Para 7 1 5 Land as soon as practical 7 5 UNINTENTIONAL LANDING GEAR EXTENSION CAUTION An unwanted landing gear extension with at least one leg moving downward may be caused by hydraulic fluid loss and it is signaled by significant aerodynamic noise increase light and counteractable nose down pitch moment red TRANS light turn...

Page 109: ...Garmin G950 IFDS Supplement Page S3 48 Section 3 Emergency procedures 4th Edition Rev 0 INTENTIONALLY LEFT BLANK ...

Page 110: ...ctors BOTH OFF 2 Ignitions ALL OFF 3 Electrical fuel pumps BOTH OFF 4 Cabin heat and defrost OFF 5 MASTER SWITCH OFF 6 Parking Brake ENGAGED 7 Aircraft Evacuation carry out immediately WARNING Consider use of ditching emergency exit to escape in case pilot or passenger doors are blocked watch for engine hot parts fuel hydraulic fluid or oil spills Leave aircraft in upwind di rection ...

Page 111: ...HE DECISION IS TAKEN TO CONTINUE THE TAKEOFF WARNING A take off abort should always be preferred if a safe stop can be per formed on ground A suggested GO NO GO criteria is abort take off until LG is still down and locked Once airborne accelerate to Blue Line Speed VYSE before commanding LG retraction Take off planning should take into account that high density altitude and aircraft mass may resul...

Page 112: ...e 9 Cabin heat and defrost BOTH OFF 10 Fire affected engine Fuel Selector Confirm and OFF 11 Fire affected engine Ignitions Confirm and BOTH OFF 12 Fire affected engine Electrical fuel pump Confirm and OFF 13 Fire affected engine FIELD OFF 14 Land as soon as possible applying one engine inoperative landing procedure See Para 6 6 ...

Page 113: ...control using rudder and ailerons 9 Attitude Adjust as appropriate to keep airspeed over 62 KIAS 10 Fire affected engine Field OFF 11 Cabin ventilation OPEN 12 Land as soon as possible applying one engine inoperative landing procedure See Para 6 6 8 4 ELECTRICAL SMOKE IN CABIN ON THE GROUND 1 MASTER SWITCH OFF 2 Cabin heat and defrost OFF 3 Throttle Lever BOTH IDLE 4 Ignitions ALL OFF 5 Fuel Selec...

Page 114: ...solate faulty source by 6 FIELD LH and RH OFF 7 AVIONICS LH and RH OFF 8 CROSS BUS LH and RH BOTH OFF CAUTION A fully charged battery can supply electrical power for at least 30 minutes If faulty source is found 9 It may be possible to restore non faulty power sources one at a time If smoke persists WARNING Before total electrical system shutdown consider gaining VMC condi tion at night set person...

Page 115: ...CURRENCE 4th Edition Rev 0 When on ground 12 Aircraft Evacuation carry out as necessary WARNING Consider use of ditching emergency exit to escape in case pilot or passenger doors are blocked watch for engine hot parts fuel hy draulic fluid or oil spills Leave aircraft in upwind direction ...

Page 116: ...emonstrated since certification process does not required it for this aircraft category Intentional spin is forbidden Stall with one engine inoperative is forbidden Should an unintentional spin occur the classic recovery ma noeuvre is deemed as being the best action to undertake 1 Both engines throttles idle 2 Flight Controls centralize 3 Rudder fully against rotation until it stops ...

Page 117: ...ted when sure on fi nal Flap can be set to T O or LAND when sure on final to reduce land ing ground roll on short field Touchdown speed can be as low as 50 kt with flap down 1 Airspeed MTOW 1180kg MTOW 1230 kg VY 83 KIAS VY 84 KIAS 2 Flaps UP 3 Emergency landing field Select WARNING Emergency landing strip should be chosen considering surface con dition length and obstacles Wind can be guessed by ...

Page 118: ... BOTH OFF 8 Electrical fuel pump BOTH OFF 9 Ignitions ALL OFF 10 MASTER SWITCH OFF When stopped 11 Aircraft Evacuation carry out if necessary WARNING Consider use of ditching emergency exit to escape in case pilot or passenger doors are blocked watch for engine hot parts fuel hydraulic fluid or oil spills Leave aircraft in upwind di rection ...

Page 119: ...ght 3 Flap setting plan approach with Flap Land Before ground contact 4 Fuel Selector BOTH OFF 5 Electrical fuel pump BOTH OFF 6 Ignitions ALL OFF On touch down 7 Landing attitude slight nose up and wings levelled 8 Touchdown speed as low as 50 KIAS with flap 9 Aircraft nose gently lower as speed bleeds off After aircraft stops 10 FIELD LH and RH BOTH OFF 11 MASTER SWITCH OFF CAUTION Master switch...

Page 120: ...ap Land Before ground contact 3 Ignitions ALL OFF 4 LH and RH Fuel Selector BOTH OFF 5 LH and RH Electrical fuel pump BOTH OFF On touch down 6 Align for approach on the runway centreline 7 Touchdown speed as low as 50 KIAS 8 Touchdown on the good tire gear only 9 Heading and direction maintain applying appropriate aileron and rudder steering control 10 Flattened tire keep off the ground as long as...

Page 121: ...wn if runway is deemed insufficient to decelerate 2 Fuel Selector BOTH OFF 3 Electrical fuel pumps BOTH OFF 4 Ignitions ALL OFF 5 FIELD LH and RH BOTH OFF 6 MASTER SWITCH OFF CAUTION Master switch to OFF impairs radio communication and outside air craft lighting Before end of runway or if runway departure is imminent 7 Landing gear control lever UP After aircraft stops 8 Aircraft Evacuation carry ...

Page 122: ...parts and fuel hydraulic fluid or oil spills when using fuselage doors If fuselage doors are unserviceable escape through the ditch ing emergency exit In case of engine fire escape from opposite or upwind aircraft side Verify if not yet performed 1 Fuel Selectors BOTH OFF 2 Ignitions ALL OFF 3 Electrical fuel pumps BOTH OFF 4 MASTER SWITCH OFF 5 Parking Brake ENGAGED 6 Leave the aircraft using eme...

Page 123: ... available put life vest on and set dinghy out first Inflate them only outside the aircraft If available try to approach any existing ship in the vicinity in order to be rapidly located and rescued right after ditching 1 Landing gear UP 2 Safety belts Tighten and fastened 3 Flaps FULL Before water impact 4 Fuel Selector BOTH OFF 5 Electrical fuel pump BOTH OFF 6 Ignitions ALL OFF 7 MASTER SWITCH O...

Page 124: ...Garmin G950 IFDS Supplement Page S3 63 Section 3 Emergency procedures DITCHING 4th Edition Rev 0 INTENTIONALLY LEFT BLANK ...

Page 125: ...old weather operations 9 3 2 Pre flight check aircraft walk around 11 3 3 Cockpit inspections 17 3 4 Engine starting 20 3 5 Before taxiing 22 3 6 Taxiing 22 3 7 Prior to takeoff 23 3 8 Line up 24 3 9 Takeoff and climb 25 3 10Cruise 26 3 11Turbulent air operation 26 3 12Descent and approach 27 3 13Before landing 27 3 14Balked landing missed approach 28 3 15After landing 28 3 16Parking shut down 29 ...

Page 126: ...Garmin G950 IFDS Supplement Page S4 2 Section 4 Normal procedures 4th Edition Rev 0 INTENTIONALLY LEFT BLANK ...

Page 127: ...lot to continue retarding the prop lever until a sudden and abrupt RPM change is observed This causes an excessive drop in propeller speed which in some cases may reach up to 800 RPM and consequently a drop of up to 2000 engine shaft rpm The long term result is a ma jor wear of engine gearbox bushings and pistons and in some cases may result in detonation In order to avoid these long term adverse ...

Page 128: ... propeller manifold combination is fol lowing reported 3 Suitable Fuels Tecnam remember operators to fill the aircraft with approved and suitable fuels Use of not approved unknown fuels may cause damages to the engine ONLY USE APPROVED FUELS For details refer to Section 2 of this manual or applicable Supplement and latest issue of Rotax SI 912 016 ...

Page 129: ...d and water data information for primary navi gation Basemap data is intended only to supplement other approved navi gation data sources and should be considered as an aid to enhance situa tional awareness Do not use outdated database information Databases used in the G950 system must be updated regularly in order to ensure that the information remains current Pilots using any outdated database do...

Page 130: ... the pilot profile is changed during the flight the HSI could not in dicate the correct LOC or VOR indication until the pilot manually tunes the active frequency Make sure that the displayed indication on the HSI indicator is consistent with the selected frequency The data contained in the terrain and obstacle databases comes from government agencies Garmin accurately processes and cross validates...

Page 131: ... both MTOW 1180 kg and 1230 kg if Supplement G10 In creased MTOW 1230 KG is applicable MTOW FLAPS 1180kg 1230 kg Rotation Speed in takeoff VR T O 64 KIAS 65 KIAS Best Angle of Climb Speed VX 0 73 KIAS 72 KIAS Best Rate of Climb speed VY 0 80 KIAS 84 KIAS Approach speed T O 90 KIAS 90 KIAS Final Approach Speed FULL 70 KIAS 71 KIAS Manoeuvring speed VA 0 118 KIAS 122 KIAS Never Exceed Speed VNE 0 16...

Page 132: ...ill tests or demonstration as per 14CFR Part61 or similar A simulated feather condition is obtained with propeller lever full forward and throttle lever set at 13 5 in Hg MAP at 70 90 KIAS and 2000 4000 ft density alti tude In normal operations shutting down an engine for training shall not become a habit in particular for safety reasons and in order to optimise training engine shutdown to per for...

Page 133: ...s and the gears against the snow or ice accumulation Water and other freezable liquids should be removed from the airplane Standing water that could freeze should be removed from critical parts as flaps and ailerons hinges trim tabs hinges drain points LG doors cabin doors etc With an ambient temperature of below 20 C remove battery and store in a warm dry place additionally in order to prevent a ...

Page 134: ...re not allowed To remove ice tow the aircraft in the hangar and operate with a soft brush or a humid cloth WARNING Removal of snow ice accumulations is necessary prior to take off because they will seriously affect airplane performance Aircraft with ice snow accumulation is not cleared for flight If the aircraft must be operated in cold weather conditions within the range 25ºC to 5ºC it is suggest...

Page 135: ...r movement can cause the engine starting with consequent hazard for people nearby Visual inspection is defined as follows check for defects cracks de lamination excessive play unsafe or improper installation as well as for general condition presence of foreign objects slippage markers etc For control surfaces visual inspection also involves additional check for freedom of movement Always check the...

Page 136: ...ly Check fixing and lack of play between blades and hub 5 Left engine nacelle Perform following inspections a Check the surface conditions b Nacelle inlets and exhausts open ings must be free of obstructions If inlet and outlet plugs are installed they should be removed c Check radiators There should be no indication of leakage of fluid and they have to be free of obstructions d Only before the fi...

Page 137: ...nk Prior to long flights oil should be added so that the oil level reaches the max mark f Drain off Gascolator for water and sediment drain until no water comes off Then make sure drain valve is closed g Check drainage hoses clamps h Verify all parts are fixed or locked i Verify all inspection doors are closed 6 Air induction system Check engine air inlet for integrity and correct fixing The air i...

Page 138: ...egrity Remove tie down device if employed 18 Stabilator leading edge Check for integrity 19 Fuselage top and bottom skin Visual inspection 20 Right static port Remove protective cap Visual inspection 21 Right Flap and hinges Visual inspection 22 Right aileron and balance weight Visual inspection remove tie down devices and control locks if employed 23 Right winglet nav and strobe lights static dis...

Page 139: ...n the walk around Station 2 31 Wheel chock Remove if employed 32 Bottom fuselage antennas Check for integrity 33 Right cabin ram air inlet Visual inspection 34 Right Pitot tube Remove protective cap and check for any obstruction 35 Nose landing gear Check tire status cuts bruises cracks and excessive wear slippage markers integrity gear structure and retraction mechanism shock absorber and gear do...

Page 140: ...Garmin G950 IFDS Supplement Section 4 Normal procedures 4th Edition Rev 0 Page S4 16 INTENTIONALLY LEFT BLANK ...

Page 141: ...ide CHECK on board 3 Weight and balance CHECK if within the limits 4 Flight controls Remove seat belt used as lock 5 PFD and MFD CHECK clean 6 Seat Adjust as required 7 Seat belt Fastened 8 Passenger briefing Completed 9 Doors CLOSED AND LOCKED 10 Landing gear control lever CHECK DOWN 11 Breakers All IN 12 MASTER SWITCH ON 13 Fuel quantity CHECK 14 RH fuel selector RIGHT 15 LH fuel selector LEFT 1...

Page 142: ...t 4th Edition Rev 0 Page S4 18 27 Cabin heat CLOSED 28 Flaps Operate control to FULL position Verify extension Retract flaps 29 Pitch trim control Set to neutral position 30 Rudder trim control Set to neutral position 31 Eng Starting Battery Voltmeter if installed Check 12 to 14 Volt ...

Page 143: ...Garmin G950 IFDS Supplement Section 4 Normal procedures 4th Edition Rev 0 Page S4 19 INTENTIONALLY LEFT BLANK ...

Page 144: ...warm up period Hot engine Park the aircraft with the nose pointing into wind in order to aid cooling Keep chokes closed and slowly open the throttles one inch while cranking Flooded Engine after engine start failure Keep chokes closed open throttle fully and start the engine then quickly re duce throttles to idle 6 RH Electrical Fuel pump ON check advisory light ON and posi tive fuel press build u...

Page 145: ... FORWARD 4 LH Choke ON if required 5 LH Electrical Fuel pump ON check advisory light ON and posi tive fuel press build up 6 LH engine propeller zone CHECK free 7 LH ignitions switches BOTH ON WARNING Ensure that the area around engine propeller disc is clear from people and obstacles Call out for propeller free 8 LH start pushbutton PUSH 9 LH Field ON 10 LH engine oil gauge CHECK if increasing wit...

Page 146: ... 3 Transponder Stand by 4 Passengers and crews seat belts Fastened 5 Passengers and crews headphones Set as required 3 6 TAXIING Ensure that the main and passengers doors warning lights are turned off 1 LH RH Fuel Selector As required 2 LH and RH fuel pressure Monitor 3 Parking Brake RELEASE 4 Flight instruments CHECK 5 Engine instruments CHECK 6 Altimeter SET both and crosscheck max difference 15...

Page 147: ...ches Set L R BOTH RPM drop with single ignition circuit selected must not exceed 130 prop s RPM maximum RPM difference by use of either cir cuits LEFT or RIGHT cannot over come 50 RPM 9 RH Propeller Lever Governor check Retard the prop lever until 1100 RPM The purging cycle should be repeated up to 4 times with the governor closely firmly and posi tively control the rpm Verify 1650 prop RPM are re...

Page 148: ...asing about 100 RPM 16 LH Carburettor heat OFF 17 LH engine instruments CHECK parameters if within green arcs 18 LH and RH Fuel quantity indicator CHECK consistent with fuel plan 19 Flaps T O or as required see Section 5 Take OFF performances 20 Pitch trim and rudder trim SET neutral position 21 Flight controls Check free 22 Seat belts fastened and doors closed and locked CHECK 3 8 LINE UP 1 Parki...

Page 149: ...taxi lights OFF above 10000 ft 11 LH and RH Propeller Lever Set max cont power at safe altitude CAUTION Max take off power must be limited to 5 minutes Reduce Throttles MAP power before retracting Propeller to 2200 RPM or below 12 LH and RH Electrical Fuel pump BOTH OFF It is recommended to retract landing gear when a positive climb rate is ensured at the applicable best speed VY or VX as necessar...

Page 150: ...i 0 15 0 50 bar applicable for fuel pump part no 893110 and no 893114 3 Carburettor heat as needed see also instructions addressed on Section 3 Para 7 4 WARNING Deselect and do not use Auto Pilot if possible icing condition area is inadvert ently entered 4 Fuel balance and crossfeed check as necessary 3 11 TURBULENT AIR OPERATION In keeping with good operating practice used in all aircraft it is r...

Page 151: ...eats set at full aft and lower position 2 LH and RH Electrical Fuel pump BOTH ON 3 On downwind leg Flaps T O MTOW 1180kg MTOW 1230 kg VFE 119KIAS VFE 122KIAS 4 Speed below applicable VLO VLE Landing gear control knob DOWN Check green lights ON 5 Carburettors heat CHECK OFF 6 LH and RH Propeller Lever FULL FORWARD 7 On final leg speed below 93 KIAS Flaps FULL 8 Final Approach Speed MTOW 1180kg MTOW...

Page 152: ...X as applicable 5 Landing gear UP as positive climb is achieved 6 Flaps UP It is recommended to retract landing gear when a positive climb rate is ensured at the applicable best speed VY or VX as necessary It has been demonstrated that best climb rate is always obtained with flaps in UP position refer to Section 5 Take off rate of climb and Enroute rate of climb tables Noteworthily best climb grad...

Page 153: ... idle speed before selecting ignitions off 9 Ignitions Turn OFF one at time 10 Doors safety locks Check OFF 11 12 LH RH Field All external lights OFF OFF 13 Master Switch OFF 14 LH and RH Fuel Selector BOTH OFF 15 Emg Batt Emg cockpit light Check OFF WARNING Before disembarkation verify propellers are fully stopped CAUTION Instruct passengers to fully open pax door against nacelle stop and depart ...

Page 154: ...STS 4th Edition Rev 0 3 17 POSTFLIGHT CHECKS 1 Protective cover for Pitot tubes stall warning and stat ic port plugs Install 2 Lock one control wheel with safety belt 3 Wheel chocks Place under MLG 4 Aileron lock Place and tighten 5 Pilot and passengers doors Close and latch ...

Page 155: ...rked and headed in a di rection that will facilitate servicing 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 and install control locks 3 Secure pilot control wheel by wrapping t...

Page 156: ... parking brakes at low ambient temperature accumulation of moisture may cause the brakes to freeze In this case use wheel chocks 3 Secure pilot control wheel by wrapping the seat belt around it 4 Assure flaps are retracted 5 Electrically ground airplane by connecting ground cable to the engine muffle 6 Install control locks and protective plugs 7 Close and lock cabin doors 8 Secure tie down cables...

Page 157: ...Garmin G950 IFDS Supplement Section 4 Normal procedures PARKING and MOORING 4th Edition Rev 0 Page S4 33 Mooring side view ...

Page 158: ...Garmin G950 IFDS Supplement Section 4 Normal procedures PARKING and MOORING 4th Edition Rev 0 Page S4 34 INTENTIONALLY LEFT BLANK ...

Page 159: ...on 3 4 ICAO Standard Atmosphere 4 5 Stall speed 5 6 Crosswind 6 7 Takeoff performances 7 8 Take off Rate of Climb at Vy 10 9 Take off Rate of Climb at Vx 11 10 Enroute Rate of Climb at Vy 12 11 Enroute Rate of Climb at Vx 13 12 One Engine Rate of Climb at VySE 14 13 One Engine Rate of Climb at VxSE 15 14 Cruise performances 16 15 Landing performances 19 16 Balked landing climb gradient 22 17 Noise...

Page 160: ... 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 theoret ical means for airspeed external temperature altitude weight runway type and condition 2 USE OF PERFORMANCES CHARTS Performances data are presented in tabular or graphical form to illustrate the effect of ...

Page 161: ...Rev 0 Page SW5 3 Section 5 Performances AIRSPEED INDICATOR SYSTEM CALIBRATION 3 AIRSPEED INDICATOR SYSTEM CALIBRATION Graph shows calibrated airspeed VCAS as a function of indicated airspeed VIAS Figure 1 IAS CAS chart Example Given Find KIAS 75 KCAS 74 ...

Page 162: ...mances ICAO STANDARD ATMOSPHERE 4 ICAO STANDARD ATMOSPHERE Figure 2 ICAO chart Examples Given Find a Temperature 20 C b Pressure altitude 1600 c Corresponding Density Altitude 2250 Given Find A Pressure altitude 1600 ISA condition B ISA Air Temperature 12 C c δA 2250 ft A δA 1600 ft B C ...

Page 163: ...rw wa ar rd d 1 16 6 5 5 N No o g gr ro ou un nd d e ef ff fe ec ct t W WE EI IG GH HT T B BA AN NK K A AN NG GL LE E S ST TA AL LL L S SP PE EE ED D F FL LA AP PS S 0 0 F FL LA AP PS S T T O O F FL LA AP PS S F FU UL LL L kg deg KIAS KCAS KIAS KCAS KIAS KCAS 1230 FWD C G 0 66 65 59 57 54 55 15 67 66 58 58 55 56 30 71 70 61 61 59 59 45 79 78 68 68 65 65 60 95 93 83 81 79 78 Altitude loss during co...

Page 164: ...ition Rev 0 Section 5 Performances CROSSWIND 6 CROSSWIND Maximum demonstrated crosswind is 17 Kts Example Given Find Wind direction with respect to air craft longitudinal axis 30 Headwind 17 5 Kts Wind speed 20 Kts Crosswind 10 Kts Figure 3 Crosswind diagram ...

Page 165: ... e 5 5 t to o G Gr ro ou un nd d R Ro ol ll l f fo or r e ea ac ch h 1 1 P Pr re es ss su ur re e A Al lt ti it tu ud de e D Di is st ta an nc ce e m m T Te em mp pe er ra at tu ur re e C C I IS SA A f ft t 25 0 25 50 S L Ground Roll 207 263 328 401 301 At 50 ft AGL 271 345 429 525 394 1000 Ground Roll 231 294 366 447 330 At 50 ft AGL 303 385 479 586 432 2000 Ground Roll 258 328 409 500 362 At 50 ...

Page 166: ... t to o G Gr ro ou un nd d R Ro ol ll l f fo or r e ea ac ch h 1 1 P Pr re es ss su ur re e A Al lt ti it tu ud de e D Di is st ta an nc ce e m m T Te em mp pe er ra at tu ur re e C C I IS SA A f ft t 25 0 25 50 S L Ground Roll 148 188 234 286 215 At 50 ft AGL 193 246 306 374 281 1000 Ground Roll 165 210 261 319 235 At 50 ft AGL 216 274 341 418 308 2000 Ground Roll 184 234 291 356 258 At 50 ft AGL...

Page 167: ... t to o G Gr ro ou un nd d R Ro ol ll l f fo or r e ea ac ch h 1 1 P Pr re es ss su ur re e A Al lt ti it tu ud de e D Di is st ta an nc ce e m m T Te em mp pe er ra at tu ur re e C C I IS SA A f ft t 25 0 25 50 S L Ground Roll 100 127 158 194 146 At 50 ft AGL 131 167 207 254 190 1000 Ground Roll 112 142 177 216 160 At 50 ft AGL 146 186 231 283 209 2000 Ground Roll 125 159 197 242 175 At 50 ft AGL...

Page 168: ... kg g f ft t K KI IA AS S 25 0 25 50 1230 S L 86 1276 1088 920 768 985 2000 83 1133 948 783 634 873 4000 79 990 809 646 500 761 6000 76 848 670 510 366 649 8000 73 707 531 374 233 537 10000 70 565 393 239 100 425 12000 67 425 256 104 32 313 14000 64 285 118 30 164 201 1080 S L 85 1507 1302 1119 954 1190 2000 82 1351 1150 970 808 1068 4000 79 1196 998 822 662 946 6000 76 1041 847 674 517 825 8000 7...

Page 169: ... IS SA A k kg g f ft t K KI IA AS S 25 0 25 50 1230 S L 78 1214 1037 880 738 941 1000 76 1147 972 816 675 888 2000 75 1080 906 751 612 836 3000 74 1013 841 687 549 783 4000 73 946 776 623 486 731 5000 72 879 710 560 424 678 6000 71 813 645 496 361 626 7000 70 746 580 432 299 574 1080 S L 78 1283 1102 940 794 1002 1000 76 1214 1034 874 729 949 2000 75 1145 967 808 664 895 3000 74 1076 900 742 600 8...

Page 170: ...K KI IA AS S 25 0 25 50 1230 S L 84 1317 1135 973 827 1036 2000 83 1179 1000 841 697 928 4000 81 1041 865 709 568 819 6000 80 904 731 577 439 711 8000 78 767 598 446 310 603 10000 77 631 464 316 182 495 12000 75 495 332 186 54 387 14000 73 360 199 56 73 279 1080 S L 83 1560 1360 1182 1022 1251 2000 82 1408 1212 1037 879 1132 4000 80 1257 1064 892 737 1014 6000 78 1106 917 748 595 895 8000 76 956 7...

Page 171: ...K KI IA AS S 25 0 25 50 1230 S L 72 1241 1073 924 789 982 1000 72 1177 1011 863 729 932 2000 72 1114 949 802 669 882 3000 72 1050 887 741 609 832 4000 72 986 825 680 550 782 5000 72 923 763 619 490 732 6000 71 860 701 559 431 682 7000 71 797 639 498 371 632 1080 S L 72 1480 1295 1130 981 1194 1000 72 1410 1226 1062 915 1139 2000 72 1340 1158 995 848 1084 3000 72 1269 1089 928 782 1029 4000 71 1199...

Page 172: ...d V Vy yS SE E R Ra at te e o of f C Cl li im mb b f ft t m mi in n T Te em mp pe er ra at tu ur re e C C I IS SA A k kg g f ft t K KI IA AS S 25 0 25 50 1230 S L 84 330 230 142 62 176 1000 83 292 193 106 26 147 2000 82 254 157 69 9 117 3000 81 216 120 33 44 87 4000 80 179 83 3 80 58 5000 79 141 46 38 115 28 6000 79 104 10 74 150 1 7000 78 67 27 110 185 31 1080 S L 80 436 330 235 149 271 1000 80 3...

Page 173: ...SE E R Ra at te e o of f C Cl li im mb b a at t V Vx xS SE E f ft t m mi in n T Te em mp pe er ra at tu ur re e C C I IS SA A k kg g f ft t K KI IA AS S 25 0 25 50 1230 S L 83 325 227 140 61 174 1000 82 288 191 104 26 145 2000 81 251 155 69 9 116 3000 81 214 118 33 44 86 4000 80 177 82 2 78 57 5000 79 140 46 38 113 28 6000 78 103 10 73 148 1 7000 77 66 26 108 183 30 1080 S L 79 424 321 229 147 265...

Page 174: ...69 122 19 2 65 124 18 2 62 125 17 3 2250 24 59 115 16 6 56 116 15 7 53 117 14 9 2250 22 46 103 12 8 43 103 12 1 41 103 11 5 2250 20 39 96 11 37 95 10 4 35 94 9 9 2100 28 84 132 23 5 80 134 22 2 76 135 21 1 2100 26 66 121 18 5 63 122 17 5 60 123 16 7 2100 24 57 114 16 54 114 15 1 52 115 14 4 2100 22 43 100 12 1 41 100 11 5 39 100 10 9 2100 20 37 92 10 2 35 91 9 7 33 89 9 2 1900 26 61 117 17 1 58 11...

Page 175: ...1900 26 75 130 20 9 71 131 19 8 67 132 18 8 1900 24 63 121 17 7 60 122 16 7 57 123 15 9 1900 22 50 110 14 1 48 110 13 3 45 110 12 6 1900 20 42 101 11 7 40 101 11 1 38 100 10 6 Propeller RPM Fuel Consumption for each Engine Weight 1150 kg 2535 lb Pressure Altitude 6000 ft ISA 30 C 27 C ISA 3 C ISA 30 C 33 C RPM MAP PWR KTAS F C PWR KTAS F C PWR KTAS F C inHg lt hr lt hr lt hr 2388 23 6 83 139 23 3 ...

Page 176: ...100 18 51 116 14 2 48 116 13 4 46 116 12 7 1900 21 1 64 128 17 8 60 129 16 8 57 130 15 9 1900 20 57 122 16 54 123 15 1 51 123 14 3 1900 18 47 112 13 2 44 112 12 4 42 111 11 8 Propeller RPM Fuel Consumption for each Engine Weight 1150 kg 2535 lb Pressure Altitude 12000 ft ISA 30 C 39 C ISA 9 C ISA 30 C 21 C RPM MAP PWR KTAS F C PWR KTAS F C PWR KTAS F C inHg lt hr lt hr lt hr 2388 18 8 67 135 18 8 ...

Page 177: ...d d R Ro ol ll l f fo or r e ea ac ch h 1 1 P Pr re es ss su ur re e A Al lt ti it tu ud de e D Di is st ta an nc ce e m m T Te em mp pe er ra at tu ur re e C C I IS SA A f ft t 25 0 25 50 S L Ground Roll 199 219 239 259 231 At 50 ft AGL 308 334 359 384 349 1000 Ground Roll 206 227 248 269 238 At 50 ft AGL 318 344 370 396 358 2000 Ground Roll 214 236 257 279 245 At 50 ft AGL 328 355 382 408 367 30...

Page 178: ...ll l f fo or r e ea ac ch h 1 1 P Pr re es ss su ur re e A Al lt ti it tu ud de e D Di is st ta an nc ce e m m T Te em mp pe er ra at tu ur re e C C I IS SA A f ft t 25 0 25 50 S L Ground Roll 175 192 210 227 203 At 50 ft AGL 271 293 315 337 306 1000 Ground Roll 181 199 218 236 209 At 50 ft AGL 279 302 325 348 314 2000 Ground Roll 188 207 226 245 215 At 50 ft AGL 288 311 335 358 322 3000 Ground Ro...

Page 179: ... l f fo or r e ea ac ch h 1 1 P Pr re es ss su ur re e A Al lt ti it tu ud de e D Di is st ta an nc ce e m m T Te em mp pe er ra at tu ur re e C C I IS SA A f ft t 25 0 25 50 S L Ground Roll 150 166 181 196 175 At 50 ft AGL 233 252 271 290 264 1000 Ground Roll 156 172 187 203 180 At 50 ft AGL 240 260 280 299 270 2000 Ground Roll 162 178 194 211 185 At 50 ft AGL 248 268 288 309 277 3000 Ground Roll...

Page 180: ... BALKED LANDING CLIMB GRADIENT Flight conditions ISA and SL Weight 1230 kg 2712 lb Throttle levers Both FULL FORWARD Flaps Landing gear Weight Speed Climb gradient T O DOWN MTOW 1230kg 2712 lb 72 KIAS 9 4 5 4 17 NOISE DATA Noise level determined in accordance with ICAO Annex 16 4th Ed July 2005 Vol I Chapter 10 is 72 82 dB A ...

Page 181: ...GARMIN G950 IFDS Increased MTOW 1230 kg Page SW5 23 4th Edition Rev 0 Section 5 Performances INTENTIONALLY LEFT BLANK ...

Page 182: ...CTION 6 WEIGHT and BALANCE INDEX 1 INTRODUCTION 3 2 WEIGHING PROCEDURES 4 2 1 Preparation 4 2 2 Levelling 4 2 3 Weighing 4 2 4 Determination of C G location 4 2 5 Weighing record 5 2 6 Weighing record II 5 3 WEIGHTS AND C G 7 4 BAGGAGE LOADING 8 5 EQUIPMENT LIST 10 ...

Page 183: ...Page 6 2 Section 6 Weight and balance 4th Edition Rev 0 INTENTIONALLY LEFT BLANK ...

Page 184: ... aircraft Loading procedure information is also provided Aircraft must be operated in accordance with the limits con cerning the maximum takeoff 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 Lim itations NOTE ...

Page 185: ...ING Level the aircraft the reference for longitudinal levelling is made putting a spirit level on the cabin floor as shown in the Aircraft Maintenance Manual Adjust longitudinal attitude 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 wing leading edge a...

Page 186: ...t W1 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 100 339 1 D D Empty weight moment M D We m Kg or Ft Lbs Maximum takeoff weight WT kg or lbs Empty weight We kg or lbs Max useful load WT We Wu kg or lbs Signature __...

Page 187: ...ht W1 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 100 339 1 D D Empty weight moment M D We m Kg or Ft Lbs Maximum takeoff weight WT kg or lbs Empty weight We kg or lbs Max useful load WT We Wu kg or lbs Signature _...

Page 188: ...20 kg kg kg kg C G Limits FUEL MASS BAGGAGE FLIGHT MASS MASS BALANCE LOADING CONDITION 23 M AC 88 176 265 353 441 0 0 0 0 88 176 265 353 441 88 176 265 88 176 1984 2204 2425 2645 lbs lbs lbs lbs lbs 1180 kg 2600 lbs 3616 3472 3327 3182 3038 2893 2748 2604 2459 2315 2170 2025 1881 1736 1591 1447 1302 1157 1013 ft lbs m kg EMPTY A C MOMENT TO DATUM OCCUPANTS FRONT SEATS MASS OCCUPANTS REAR SEATS MAS...

Page 189: ... accord ance with diagram addressed on PAR 03 and with C G excursion and weight lim itations reported in Section 2 Pilot is provided with a red tie down net and snap fasteners allowing for securing the loads on the compartment floor CAUTION Loading the baggage make sure that you correctly stretched the net which must be secured to the four vertices of the floor ...

Page 190: ...Page 6 9 Section 6 Weight and balance 4th Edition Rev 0 INTENTIONALLY LEFT BLANK ...

Page 191: ...ment which may be installed in the P2006T The items marked with an X were installed on the airplane described at the be ginning of the list and they are included in the Basic Empty Weight It is the owner s responsibility to retain this equipment list and amend it to reflect changes in equipment installed in this airplane ...

Page 192: ...COMM NAV 3 18 1 4 B3 Garmin GMA340 audio panel 0 8 1 4 B4 Garmin GMA347 audio panel 0 8 1 4 B5 Garmin SL30 VHF COMM NAV 1 3 1 4 B6 Transponder Garmin GTX328 1 9 1 4 B7 Transponder Garmin GTX330 1 5 1 4 Transponder Garmin GTX33 1 5 1 4 B8 Becker BXP 6401 2 01 Mode S transponder 0 8 1 4 B9 Vor Loc GS Indicator Garmin GI106A 0 4 1 4 B10 Vor Loc GS Indicator MID Continental MD 200 306 0 4 1 44 B11 Dir...

Page 193: ... 1394T100 7Z 0 81 1 4 B24 PRGMR CMPTR 01192 0 2TF 1 36 1 4 B25 Roll servo 0105 5 R9 1 31 0 71 B26 Pitch servo 0107 11 P4 1 31 3 55 B27 Altitude Transducer 0111 0 2 1 9 B28 Pitch Trim servo S TEC 0105 T11 1 3 2 8 B29 ELT Adams Aviation Artex ME406 0 9 0 8 B30 LH Front and rear seat GEVEN E5 01 003 T01 or E5 01 007 T01 or E5 01 009 T03 9 0 893 B31 RH Front and rear seat GEVEN E5 01 004 T01 or E5 01 ...

Page 194: ...Page 6 13 Section 6 Weight and balance 4th Edition Rev 0 INTENTIONALLY LEFT BLANK ...

Page 195: ...AIRFRAME 3 3 POWERPLANT 9 4 PEDESTAL CONTROLS 12 5 CABIN OVER HEAD PANEL CONTROLS 15 6 INTERNAL LIGHTS 16 7 EXTERNAL LIGHTS 17 8 FUEL SYSTEM 19 9 LANDING GEAR SYSTEM 21 10 BRAKES 25 11 VENTILATION 26 12 CABIN HEAT 26 13 SEATS AND SAFETY BELTS 26 14 DOORS 27 15 BAGGAGE COMPARTMENT 28 16 PLACARDS 31 17 INSTRUMENTS PANEL 37 18 ELECTRICAL SYSTEM 40 ...

Page 196: ...Page 7 2 Section 7 Airframe and Systems description 4th Edition Rev 0 INTENTIONALLY LEFT BLANK ...

Page 197: ...to the rear spar The torque box houses an integrated fuel tank and supports the engine mount Flap and aileron respectively located inboard and outboard of wing and made up of light alloy are constructed with a central spar to which front and rear ribs are jointed Wrapped around aluminium stressed skin panels cover all the structures Steel alloy attachments connect left and right wing to each other...

Page 198: ...s and other components Two spar frames support on the top the wings attachments and on the bottom the sponson beans sustaining the main landing gear The forward frame to which ra dome is connected supports a steel trestle to which the nose landing gear is con nected The front and rear seats access occur by means of two doors located in the oppo site sides of the fuselage a ditching emergency exit ...

Page 199: ...lic vertical fin is made up of a twin spar with al uminium alloy stressed skin Rudder providing directional control of the airplane is made up of aluminium alloy The rudder is connected to the vertical tail at two hinge points A trim tab system increases directional stability of the airplane Figure 3 Vertical empennage structure ...

Page 200: ...h Edition Rev 0 The horizontal empennage is an all moving type stabilator its structure consists of a twin spar to which front and rear ribs are jointed and it is covered by stressed aluminium alloy skin The trim tab completes the assy Figure 4 Stabilator structure ...

Page 201: ...ush rods and cables a cable control circuit is confined within the cabin and it is connected to a pair of push pull rod systems positioned in each main wing which control ailerons differentially The U shaped control wheels hinged on the top of the control column control the ailerons Control wheel motion is transferred to the ailerons through a cable loop up to the interconnecting rod linking the t...

Page 202: ...Page 7 8 Section 7 Airframe and Systems description AIRFRAME 4th Edition Rev 0 INTENTIONALLY LEFT BLANK ...

Page 203: ...ng system is designed for liquid cooling of the cylinders heads and ram air cooling of the cylinders The liquid system is a closed circuit with an overflow bottle and an expansion tank The coolant flow is forced by a water pump driven from the camshaft from the radiator to the cylinder heads From the top of the cylinder heads the coolant pass es on to the expansion tank item 1 Figure below Since t...

Page 204: ... pressure regulator A thermostatic valve regulates the oil flow to the heat exchanger oil radiator on the basis of oil temperature this al lows the engine starting in cold conditions The oil tank is installed behind the firewall protected from heat sources Some holes on the bracket structure allow for air ventilation The reservoir is fitted with a dipstick a hose immediately located beneath the fi...

Page 205: ...inder heads ram air cooled cylinders two carburetors integrated reduction gear box with shock absorber Maximum power at declared rpm 73 5 kW 98 6hp 5800 rpm 5 min maximum 69 0 kW 92 5hp 5500 rpm continuous 3 2 PROPELLER FEATURES Manufacturer MT Propeller Type certificate LBA 32 130 086 MTV 21 series Model MTV 21 A C F CF178 05 Blades hub 2 wood composite blades aluminium hub Diameter 1780 mm no re...

Page 206: ...ows the controls installed on the central pedestal Figure 7 Pedestal controls No Description 1 and 2 Choke control 3 Choke friction knob 4 Upper levers friction knob 5 6 LH and RH Throttle lever 7 8 LH and RH Carburetor Heating lever 9 10 LH and RH Propeller Pitch Control lever 11 Parking brake 12 Windshield defrost control knob ...

Page 207: ...ible to adjust the throttle propeller and carburettor heat levers friction by appropriately tightening the friction knob located on the central console A similar device is provided for engine choke controls Carburettor heat control knobs are located between throttle and propellers levers when the knobs are fully pulled backwards carburettors receive maximum hot air During normal operations the kno...

Page 208: ...Page 7 14 Section 7 Airframe and Systems description 4th Edition Rev 0 INTENTIONALLY LEFT BLANK ...

Page 209: ... the controls installed on the cabin over head panel Figure 8 Cabin head panel controls No Number Description 1 Cabin Light 2 LH Fuel selector valve 3 LH Electric Starter 4 LH electric fuel pump 5 LH Engine ignition 1 6 LH Engine ignition 2 7 RH Engine ignition 1 8 RH Engine ignition 2 9 RH electric fuel pump 10 RH Electric Starter 11 RH Fuel selector valve ...

Page 210: ... panel in correspondence of the crew seats About the instrument lights controlled by a switch on the RH instrument panel the switches built in lights concern the instrument panels switches lighting the avionics lights concern the avionic equipment lighting and the cockpit lights con cern two lights located on the over head panel illuminating LH and RH instrument panels see Figure below All above m...

Page 211: ...ication to prevent collision They are located like the above mentioned NAV lights on the winglets and on the top of the vertical fin Taxi Light supports taxi maneuvering on the ground at night It is installed on the left wing leading edge Landing Light provides ground reference information during final approach touchdown ground roll and take off and illuminates any major obstructions in the airpla...

Page 212: ...ystems description EXTERNAL LIGHTS 4th Edition Rev 0 All mentioned lights whose circuits are protected by dedicated breakers are acti vated by the related switches on the right instrument panel see below Figure 11 Lights switches panel ...

Page 213: ...each engine are located on the RH instrument panel In normal conditions to supply fuel to engines each engine pump sucks fuel from the related tank crossfeed is allowed by fuel valves located on the front spar and controlled by Bowden cables from the fuel selectors located on the cabin over head panel Left fuel selector manages the left engine feeding allowing fuel supply from the left fuel tank o...

Page 214: ...Page 7 20 Section 7 Airframe and Systems description FUEL SYSTEM 4th Edition Rev 0 Figure 12 Fuel system schematic ...

Page 215: ... up positions and for alerting the pilot by aural means should the approach and landing configuration be incorrect in terms of flaps throttle levers landing gear position in order to avoid an uninten tional gear up landing The system operates in two modes normal and emergency Normal operation provides gear extension and retraction by means of hydraulic jacks Gears extension is helped by gravity al...

Page 216: ...rgency operation The emergency accumulator nitrogen pressure indicator is located on the tail cone left side on ground a red push button located beneath the pressure indicator al lows the electrical pump for charging the accumulator should the nitrogen pressure be below the lower limit indicated on the placard Emergency extension is controlled by two distributors located on the cabin floor under a...

Page 217: ...own limit switches control the LG lights lighting and pump operation on the basis of LG configuration set by the pilot through the LG control knob A push to test button is used to check that the landing gear position lights are operating A warning horn alerts the pilot when the LG control knob is in UP position and at least one of the two throttle levers and or flaps are respectively set to idle a...

Page 218: ...Page 7 24 Section 7 Airframe and Systems description LANDING GEAR SYSTEM 4th Edition Rev 0 INTENTIONALLY LEFT BLANK ...

Page 219: ...rrespondence of the cabin floor and operated by a knob on the cockpit central pedestal intercepts the hydraulic lines once the system is pressurized to hold the brake assemblies linings tightened round the main wheels brake discs Brakes can be operated from both pilot s and co pilot s pedals a single vented oil reservoir feeds the pilot side master cylinders which are connected via hoses with the ...

Page 220: ...ne heat exchanger right knob con trols the warm air from RH engine heat exchanger Crew heating system outlet ports are located on the cabin floor near the pedestal for passengers zone it is provided an outlet port on the cabin head Windshield defrost is operated via a knob positioned on the pedestal when knob is pulled the hot air flow for crew heating is deviated to the windshield 13 SEATS AND SA...

Page 221: ...Doors location Being the main door located in correspondence of the propeller disc its operation is limited to the engine shut down condition In fact in order to prevent crew injuries an electro mechanical device locks the door latch when left engine runs A pressure switch senses engine oil pressure and allows for electrical supply to a solenoid which engages the door lock mechanism This prevents ...

Page 222: ...ed ON The emergency exit is fitted with the same safety device in this case the pressure switch allowing for solenoid operation is activated from right engine oil pressure line should be the door open or closed and unlocked the REAR DOOR OPEN warning light is turned ON Any voluntary operation of the manual by pass solenoid lock causes related door warning light is turned on The ditching emergency ...

Page 223: ...Page 7 29 Section 7 Airframe and Systems description 4th Edition Rev 0 INTENTIONALLY LEFT BLANK ...

Page 224: ...Page 7 30 Section 7 Airframe and Systems description 4th Edition Rev 0 INTENTIONALLY LEFT BLANK ...

Page 225: ... listed below English lan guage directly translated placards in the language of the country in which the airplane is registered can be installed when required by the specific NAA Description Placard Place ELT equipment location Baggage compartment right side First Aid Kit location Baggage compartment aft cover panel Fire extin guisher loca tion Cockpit floor pilot side Emergency gear extension com...

Page 226: ...s compartment Alternate static port location Central pedestal left side Alternate static port operating instructions Central pedestal right side Static ports lo cation STATIC PORT KEEP CLEAN Static ports fuselage both sides Battery com partment loca tion Fuselage tail left side EXT power connection socket sche matic and in structions Fuselage tail left side ...

Page 227: ...uselage tail left side LG hydraulic compartment location Fuselage tail left side in correspondence of LG hydraulic com partment cap Towing limita tions Nose LG forward door Stabilator ex cursion range Fuselage tail left side in correspondence of the stabilator leading edge Aircraft grounding Close to the fuel filler cap Engine coolant expansion tank location Engine nacelle top side ...

Page 228: ...ms description 4th Edition Rev 0 Description Placard Place Steel boards a c identifica tion marks Sample Fuselage tail left side Main LG tires inflation pres sure values MLG leg LH and RH Nose LG tire inflation pres sure values Nose LG fork ...

Page 229: ...Page 7 35 Section 7 Airframe and Systems description 4th Edition Rev 0 INTENTIONALLY LEFT BLANK ...

Page 230: ...Page 7 36 Section 7 Airframe and Systems description 4th Edition Rev 0 INTENTIONALLY LEFT BLANK ...

Page 231: ...STRUMENTS PANEL 4th Edition Rev 0 Page S7 37 17 INSTRUMENTS PANEL 1 2 3 4 5 7 8 9 12 13 14 15 16 17 18 19 20 21 22 23 24 25 26 28 29 30 31 32 6 10 11 33 34 35 36 37 38 39 41 42 43 44 45 46 47 49 51 52 53 50 48 27 54 55 40 56 GARMIN G950 IFDS Instruments panel typical layout ...

Page 232: ...icator 9 RH R P M 10 RH fuel quantity indicator 11 LH CHT 12 RH CHT 13 LH Oil Temperature 14 RH Oil Temperature 15 LH oil pressure 16 RH oil pressure 17 RH breakers panel 18 RH ram air inlet 19 Instruments light switch 20 Strobe light switch 21 Navigation light switch 22 Taxi light switch 23 Landing light switch 24 Position flaps indicator 25 RH fuel pressure 26 LH fuel pressure 27 Flap switch 28 ...

Page 233: ...Chronometer 39 LG control knob 40 Voltammeter Indicator 41 ADF control panel 42 Cockpit light dimmer 43 Cabin heat warm air from RH engine 44 Avionics lights dimmer 45 Cabin heat warm air from LH engine 46 LH ram air inlet 47 Trim rudder indicator 48 Switches built in lights dimmer 49 ELT Indicator 50 RH breakers panel 51 Pitch trim indicator 52 Pitot heat switch 53 A P Master switch 54 A P trim m...

Page 234: ...Garmin G950 IFDS Supplement Section 7 Airframe and Systems description INSTRUMENTS PANEL 4th Edition Rev 0 Page S7 40 INTENTIONALLY LEFT BLANK ...

Page 235: ...ower source can be connected to the aircraft DC distribution system On the instruments panel right side it is installed a voltmeter ammeter The am meter section can indicate the current supplied by either left or right generator switching a dedicated selector There are five different busses make reference to Figure 11 Battery bus LH Generator bus RH Generator bus LH Avionics bus RH Avionics bus Th...

Page 236: ...led by the pertinent switches located on the LH breakers rack Battery Bus GMA 1347 Audio Panel GIA 1 GDU PFD Cooling Fan Converter 1 Standby attitude indicator LH and RH Fuel electrical pump LH and RH Fuel pressure LH and RH Fuel quantity LH and RH Oil pressure LH and RH Oil temperature LH and RH CHT LH and RH RPM indicator Cabin lights Cockpit lights Switches built in lights Avionics lights Strob...

Page 237: ...itches disposed on two rows on the first row there is the MASTER SWITCH which allows for con necting through the battery relay the battery to the battery bus LH and RH FIELD switches control the pertinent generator setting the switch to OFF puts the pertinent generator off line In correspondence of the second row there are 4 switches LH RH AVIONIC and LH RH CROSS BUS Central pedestal switches cons...

Page 238: ...rrectly operating and all above mentioned switches are in ON position all the busses are connected to the generators The ignition switches two for each engine and grouped on the over head panel are instead independent from the airplane electrical system generation and distri bution they only control and open the engine electrical circuit WARNING If ignition switches are turned ON a propeller movem...

Page 239: ...Garmin G950 IFDS Supplement Page S7 45 Section 7 Airframe and Systems description ELECTRICAL SYSTEM 4 th Edition Rev 0 Electric system schematic ...

Page 240: ...Garmin G950 IFDS Supplement Page S7 46 Section 7 Airframe and Systems description ELECTRICAL SYSTEM 4th Edition Rev 0 INTENTIONALLY LEFT BLANK ...

Page 241: ...tion intervals 3 3 Aircraft changes or repairs 3 4 Maintenance 4 4 1 Refuelling 4 4 2 Oil level control 4 4 3 Landing gear tires pressure control 5 5 Ground towing parking and mooring 6 5 1 Towing 6 5 2 Parking 6 5 3 Mooring 7 6 Cleaning 8 6 1 Windows 8 6 2 External surfaces 8 6 1 Propeller 8 6 2 Engine 8 6 3 Internal surfaces 9 7 Ice removal 9 ...

Page 242: ...Page 8 2 Section 8 Aircraft Care and Maintenance 4th Edition Rev 0 INTENTIONALLY LEFT BLANK ...

Page 243: ... to be performed The first scheduled engine inspection must be carried out after first 3 6 hours 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...

Page 244: ...rforming refuelling Make sure that the aircraft is electrically connected to the ground 4 2 OIL LEVEL CONTROL 1 Open the inspection cap on the engine nacelle 2 Prior to oil check switch off both ignitions circuits 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 wh...

Page 245: ... PRESSURE CONTROL 1 Remove wheel dust cover on main LG wheels 2 Unscrew the tire cap 3 Connect a gauge 4 Read the pressure value 5 If required rectify the pressure nose tire 1 7 Bar 24 Psi main landing gear tires 2 3 Bar 33 Psi 6 Fit the tire cap 7 Install wheel dust cover on main LG wheels ...

Page 246: ...ion that will facilitate servicing without regard to prevailing winds Ensure that it is sufficiently protected against adverse weather conditions and present no dan ger to other aircraft Procedure 1 Position airplane on levelled surface headed into the prevailing wind if practical 2 Engage parking brake 3 Install control locks 4 Secure pilot control wheel by wrapping the seat belt around it Do not...

Page 247: ...e when an accumulation of moisture may cause the brakes to freeze or when they become hot from severe use In these cases use wheel chocks 3 Secure pilot control wheel by wrapping the seat belt around it 4 Assure that flaps are retracted 5 Electrically ground airplane by connecting ground cable to the engine muffle 6 Install control locks 7 Install protective plugs 8 Close and lock cabin doors 9 Se...

Page 248: ...t allowed solvents or al cohol based products Died insects must be removed using hot water It is advisable to avoid outside aircraft parking for long periods it is always con venient to keep the aircraft in the hangar 6 1 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 solv...

Page 249: ...y maps etc must be removed The instrumentation as a whole must be cleaned with a humid cloth plastic sur faces can be cleaned with suitable products For parts not easily accessible perform cleaning with a small brush seats must be cleaned with a humid cloth 7 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 ...

Page 250: ...Page 8 10 Section 8 Aircraft Care and Maintenance 4th Edition Rev 0 INTENTIONALLY LEFT BLANK ...

Page 251: ...ansponder Supplement no A10 Garmin GMA347 audio panel Supplement no A11 Becker BXP 6401 2 01 Mode S transponder Supplement no A12 S TEC Fifty Five X Autopilot Supplement no A13B GTN 650 equipment Supplement no A14 Engine starting battery Supplement no A15 Power supply from built in generators Supplement no A16 AFM supplement for CIS operators Supplement no A17 Brazilian AFMS Supplement no A18 Chin...

Page 252: ...ry Supplement no G6 Power supply from built in generators Supplement no G7 AFM supplement for CIS operators Supplement no G8 Brazilian AFMS Supplement no G9 Chinese AFMS Supplement no G10 Increased MTOW 1230 KG MOD 2006 015 Supplement no G11 Increased Vle Vlo Supplement no G12 South African AFM Supplement no G13 Alternators with 70A Supplement no G14 SMP for Digital Configuration Supplement no G15...

Page 253: ...is Section concerns the supplemental manuals of additional or optional instrumenta tion equipping the P2006T Two lists are reported the first one applies to airplanes with analogue instruments the second one applies to airplanes embodying the Design Change MOD2006 002 Garmin G950 ...

Page 254: ...340 Audio Panel A4 Garmin GTX 328 Mode S Transponder A5 Bendix King Honeywell KR 87 ADF System A6 Bendix King Honeywell KN 63 DME System A7 KCS 55A Compass System A8 Garmin GNS 530W Gps VHF Comm Nav A9 Garmin GTX 330 Mode S Transponder A10 Garmin GMA 347 Audio Panel A11 Becker BXP 6401 2 01 Mode S transponder A12 S TEC Fifty Five X Auto pilot A13B GTN 650 equipment A14 Engine starting battery A15 ...

Page 255: ...R AIRPLANES WITH ANALOGUE INSTRUMENTS Sup No Title Rev no Date APPLICABLE YES NO A18 Chinese AFMS A19 Increased MTOW 1230 KG MOD 2006 015 A20 Increased Vle Vlo A21 South African AFM A22 Argentine AFM A23 Ukrainian AFM A24 SMP for Analogic Con figuration A25 Alternators with 70A A26 India AFMS A27 Oil Temp indicator up date ...

Page 256: ...Page 9 6 Section 9 Supplements SUPPLEMENTS LIST 4th Edition Rev 0 INTENTIONALLY LEFT BLANK ...

Page 257: ...ywell KR 87 ADF System for GARMIN G950 G4 Bendix King Honeywell KN 63 DME System for GARMIN G950 G5 Engine starting battery G6 Power supply from built in generators G7 AFM Supplement for CIS countries operators G8 Brazilian AFMS G9 Chinese AFMS G10 Increased MTOW 1230 KG MOD 2006 015 G11 Increased Vle Vlo G12 South African AFM G13 Alternators with 70A G14 SMP for Digital Configu ration G15 Reserve...

Page 258: ...Page 9 8 Section 9 Supplements 4th Edition Rev 0 INTENTIONALLY LEFT BLANK ...

Page 259: ...GENTINE AFM Record of Revisions Rev Revised page Description of Revision Tecnam Approval EASA Approval Or Under DOA Privileges DO OoA HDO 0 First issue D Ronca G Paduano M Oliva See Note Note this Supplement has been originally issued on 5th May 2014 after EASA Third Country Validation process completion ...

Page 260: ...ection 9 Supplements Supplement no A22 Argentine AFM LOEP Page Revision Page Revision A22 1 Rev 0 A22 10 Rev 0 A22 2 Rev 0 A22 11 Rev 0 A22 3 Rev 0 A22 12 Rev 0 A22 4 Rev 0 A22 5 Rev 0 A22 6 Rev 0 A22 7 Rev 0 A22 8 Rev 0 A22 9 Rev 0 ...

Page 261: ...Page A22 3 3rd Edition Rev 0 Section 9 Supplements Supplement no A22 Argentine AFM TABLE OF CONTENTS INTRODUCTION 4 General 5 1 Fuel 5 Limitations 5 1 Kind of Operation Equipment 5 2 Other Placards 6 ...

Page 262: ...upplemental information to the basic information approved in EASA aircraft Flight Manual when the aircraft is registered in Argentine For Limitations procedures and performance information not contained in this supplement refer to the basic Aircraft Flight Manual The information contained herein supplements or supersedes the basic Aircraft Flight Manual as applicable ...

Page 263: ...ents Supplement no A22 Argentine AFM GENERAL 1 FUEL Approved fuel MOGAS ASTM D4814 AVGAS 100LL ASTM D910 LIMITATIONS 1 KIND OF OPERATION EQUIPMENT The equipment appropriate for different types of operations must comply with ap plicable regulations ...

Page 264: ...nt location Baggage com partment right side 50x45 First Aid Kit location Baggage com partment aft cover panel 40x40 Fire extin guisher loca tion Cockpit floor pilot side 35x50 Emergency gear extension compartment location Removable cap 55x28 Emergency gear extension compartment location only if MOD2006 33 or SB 098 CS is installed Removable cap 55x28 ...

Page 265: ...ctions Emergency distributors compartment 55x28 Smoking ban Instruments panel right side 21x3 ESB voltmeter see suppl A14 Instruments panel right side 56x9 Battery hous ing On the battery housing left side aircraft tail cone 65x40 Engine oil lev el and specifi cations On the engine nacelle in cor respondence of the engine oil reservoir ac cess door 50x50 ...

Page 266: ... cap 70x50 Ground con nection during refuelling pro cedure In correspon dance of each tank filler cap 85x20 Baggage com partment ca pacity Baggage com partment ver tical panel 90x55 Ditching emer gency exit opening in structions Ditching emer gency exit handle internal side 77x46 Ø200 Ditching emer gency exit opening in structions Ditching emer gency exit handle exter nal side 77x46 Ø200 ...

Page 267: ...ncy ex it internal side 55x30 each Door locking system by pass instruc tions Main door and emergency ex it external side 55x30 each Main door exit instructions Main door in ternal side 67x20 Emergency exit label Emergency ex it internal and external side 200x20 Towing maxi mum turning angle Nose landing gear front door 88x52 Seat position advisory Behind pilot and co pilot seats 85x18 ...

Page 268: ...ing pres sure Near each main gear wheel 47x20 Nose gear tires inflating pres sure Near the nose wheel 47x20 External power socket Below the ex ternal power socket aircraft tail cone left side 50x48 Emergency tank max pres sure indicating On the emer gency tank in spection door left side air craft tail cone 150x15 Static port On each static port left and right side of aircraft tail cone 40x12 ...

Page 269: ...tion Rev 0 Section 9 Supplements Supplement no A22 Argentine AFM Description Placard Place Dimensions mm LG hydraulic compartment location Fuselage tail left side in correspondence of LG hydrau lic compart ment cap 80x20 ...

Page 270: ...Page A22 12 3rd Edition Rev 0 Section 9 Supplements Supplement no A22 Argentine AFM INTENTIONALLY LEFT BLANK ...

Page 271: ...nam Approval EASA Approval or Under DOA Privileges DO OoA HDO 0 See Note D Ronca M Oliva M Oliva DOA Note this Supplement has been originally issued on 12 January 2015 after EASA Third Country Validation process completion List of Effective Pages Page Revision Page Revision A23 1 Rev 0 A23 2 Rev 0 A23 3 Rev 0 A23 4 Rev 0 A23 5 Rev 0 A23 6 Rev 0 A23 7 Rev 0 A23 8 Rev 0 A23 9 Rev 0 A23 10 Rev 0 A23 ...

Page 272: ...S INTRODUCTION 3 GENERAL 3 FUEL 3 LIMITATIONS 4 Flight Altitude 4 Types of surface 4 Restriction flight area without HF COMM 4 Other placards 4 Kinds of Operations Equipment List 5 EMERGENCY PROCEDURES 6 Smoke and fire occurrence 6 NORMAL OPERATIONS 7 PERFORMANCES 8 Landing performances 8 WEIGHT AND BALANCE 10 ...

Page 273: ...t be applied to both P2006T digital and analogue configuration For limitations procedures and performance information not contained in this supple ment refer to the EASA Approved Aircraft Flight Manual GENERAL The information contained herein complements or supersedes the basic information in the EASA Approved Aircraft Flight Manual FUEL APPROVED FUEL MOGAS ASTM D4814 MOGAS EN 228 Super Super plus...

Page 274: ...gen supply must be provided for at least one passenger TYPES OF SURFACE Take off and landing operations must be conducted on dry or wet paved surfaces dry or grass surfaces with a maximum grass height of 10 centimeters or unpaved run ways with a soil strength greater than or equal to 6 kg per sq centimeter 2 6 cm kg RESTRICTION FLIGHT AREA WITHOUT HF COMM The flights of the airplane that are not e...

Page 275: ...ight Taxi light Strobe lights Torch Cabin light Cockpit lights Emergency light Volt Ammeter COMM NAV GPS equipment VOR LOC GS GPS CDI LG position and transition lights Transponder Audio Panel Marker beacon Altitude encoder ELT Alternate static source MAP indicator dual RPM indicator 2 Oil pressure indicator 2 Oil temperature indicator 2 CHT 2 Fuel pressure indicator 2 Fuel quantity indicator 2 Lon...

Page 276: ...age A23 6 Section 9 Supplements Supplement no A23 Ukrainian AFM Supplement 4th Edition Rev 0 EMERGENCY PROCEDURES SMOKE AND FIRE OCCURRENCE Use ventilation window in case of smoke in cabin for all cases ...

Page 277: ...Page A23 7 Section 9 Supplements Supplement no A23 Ukrainian AFM Supplement 4th Edition Rev 0 NORMAL OPERATIONS Make reference to Section 4 of this Manual ...

Page 278: ...fo or r a al lt te er rn na at te e a ai ir rp po or rt t F Fo or r w we et t r ru un nw wa ay y 9 92 2 t to o g gr ro ou un nd d r ro ol ll l f fo or r d de es st ti in na at ti io on n a ai ir rp po or rt t 6 64 4 t to o g gr ro ou un nd d r ro ol ll l f fo or r a al lt te er rn na at te e a ai ir rp po or rt t P Pr re es ss su ur re e A Al lt ti it tu ud de e D Di is st ta an nc ce e m m T Te e...

Page 279: ...Page A23 9 Section 9 Supplements Supplement no A23 Ukrainian AFM Supplement 4th Edition Rev 0 INTENTIONALLY LEFT BLANK ...

Page 280: ...Page A23 10 Section 9 Supplements Supplement no A23 Ukrainian AFM Supplement 4th Edition Rev 0 WEIGHT AND BALANCE For weight and balance make reference to Section 6 of this Manual ...

Page 281: ...Page A23 11 Section 9 Supplements Supplement no A23 Ukrainian AFM Supplement 4th Edition Rev 0 INTENTIONALLY LEFT BLAN ...

Page 282: ...Revision Tecnam Approval EASA Approval or Under DOA Privileges DO OoA HDO 0 See Note 1 G2 9 Add Warning M Landi M Oliva L Pascale DOA privileges Note this Supplement has been originally issued under EASA Major Design Change Approval no 10029331 dated 18 March 2010 List of Effective Pages Page Revision Page Revision G2 1 Rev 1 G2 6 Rev 0 G2 2 Rev 0 G2 7 Rev 0 G2 3 Rev 0 G2 8 Rev 0 G2 4 Rev 0 G2 9 R...

Page 283: ... the selected course along with the non rate quantities of heading error course error and course deviation indication When in control of the pitch axis the autopilot senses vertical speed acceleration and closure rate to the selected glideslope along with the non rate quantities of altitude and glideslope deviation indication These sensed data provide feedback to the autopilot which processes them...

Page 284: ...hen the aircraft is equipped with S TEC Fifty Five X autopilot The Autopilot is certified for Category I ILS Approaches with a decision height not lower than 200 feet AGL 61m Autopilot operation forbidden with flaps extended more than TO position During Autopilot operation a pilot with seat belt fastened must be seated at the left pilot position The use of Autopilot during single engine operation ...

Page 285: ... S TEC Fifty Five X Autopilot for Garmin G950 3rd Edition Rev 0 EASA Approved On the instrument panel in clear view of the pilot it is placed the following plac ard reminding the observance of aircraft operating limitations during Autopilot operation ...

Page 286: ...mmediately the aircraft control disconnecting the autopilot which must be set inoperative until the failure has been identified and corrected Altitude lost during a pitch axis autopilot malfunction and recovery Following table addresses the altitude lost during a pitch axis malfunction and re covery for each reported flight phase Flight phase Altitude loss Climb 200 ft Cruise 150 ft Descent 200 ft...

Page 287: ...ane control wheel GRASP FIRMLY and OVERPOWER if necessary to regain aircraft control 2 AP DISC TRIM INTR switch PRESS 3 AP MASTER SWITCH OFF 4 AP Circuit Breaker PULL CAUTION When Autopilot is disconnected as a consequence of a malfunc tion hold the control wheel firmly it may be necessary up to 35 pounds 15 8 daN of force on the control wheel to hold the airplane level When Autopilot is disconnec...

Page 288: ... mal function hold the control wheel firmly it could be necessary up to 35 pounds 15 8 daN of force on the control wheel to hold the airplane level When electric trim is disconnected it may be necessary operate the pitch trim through the Trim Wheel When electric trim is disconnected Autopilot system can be operated both in pitch and roll modes nevertheless when a pitch mode ALT HOLD VS GS is engag...

Page 289: ... Airplane control wheel GRASP FIRMLY and OVERPOWER if necessary to regain aircraft control 2 AP DISC TRIM INTR switch PRESS 3 AP MASTER SWITCH OFF 4 AP Circuit Breaker PULL 5 Refer to other navigation means for heading information CAUTION When Autopilot is disconnected as a consequence of a malfunc tion hold the control wheel firmly it may be necessary up to 35 pounds 15 8 daN of force on the cont...

Page 290: ...lot Display Make reference to Garmin G950 Pilot s Guide for Tecnam P2006T P N 190 01146 00 last issue WARNING The vertical speed mode is used to establish and hold a PILOT selected vertical speed Since the autopilot receives no airspeed information it is the responsibility of the pilot to ensure that the vertical speed selection is within the operating limits of the aircraft s capabilities Selecti...

Page 291: ...Page G2 10 Section 9 Supplements Supplement no G2 S TEC Fifty Five X Autopilot for Garmin G950 3rd Edition Rev 0 SYSTEMS The System Fifty Five X Block Diagram is shown in the following figure ...

Page 292: ...Record of Revisions Rev Revised page Description of Revision Tecnam Approval EASA Approval Or Under DOA Privileges DO OoA HDO 0 See Note Note this Supplement has been originally issued under EASA Major Design Change Approval no 10029633 dated 8 April 2010 List of Effective Pages Page Revision Page Revision G3 1 Rev 0 G3 3 Rev 0 G3 2 Rev 0 G3 4 Rev 0 ...

Page 293: ...ormation to operate in a safe and efficient manner the aircraft when equipped with ADF KR 87 device in conjunction with Garmin G950 system GENERAL KR 87 is an ADF for navigation with respect to the Non Directional Beacon sta tions LIMITATIONS ADF KR 87 manuals do not address operating limitations more severe than those usually applicable to the P2006T ...

Page 294: ...tions could arise also during night flights near mountainous reliefs and as effect of the coastal refraction NORMAL OPERATIONS Normal operating procedures are reported on the following documents 1 Garmin G950 Pilot s Guide for Tecnam P2006T P N 190 01146 00 last issue 2 ADF system Pilot s guide and Reference P N KIKR87 PG C last issue Bearing information is displayed on the Garmin G950 PFD to the ...

Page 295: ...9 Supplements Supplement no G3 KR 87 ADF System for Garmin G950 3rd Edition Rev 0 SYSTEMS Refer to the guide KR 87 P N KIKR87 PG C for a system description The inter face with Garmin G950 is shown on the following Figure ...

Page 296: ...Record of Revisions Rev Revised page Description of Revision Tecnam Approval EASA Approval Or Under DOA Privileges DO OoA HDO 0 See Note Note this Supplement has been originally issued under EASA Major Design Change Approval no 10029633 dated 8 April 2010 List of Effective Pages Page Revision Page Revision G4 1 Rev 0 G4 3 Rev 0 G4 2 Rev 0 G4 4 Rev 0 ...

Page 297: ...CY PROCEDURES In determined conditions near the beacon DME signal can be lost or distorted Take into account this likelihood when a beacon approach is performed NORMAL OPERATIONS Normal operating procedures are reported on Garmin G950 Pilot s Guide for Tec nam P2006T P N 190 01146 00 last issue Make reference also to KN 63 Installation Manual P N 006 00176 Rev 4 dat ed October 2004 The PFD softkey...

Page 298: ...MANCES DME KN 63 employment does not affect the aircraft performances WEIGHT AND BALANCE See Section 6 of this Manual SYSTEMS Refer to the guide KN 63 Installation Manual P N 006 00176 Rev 4 dated Oc tober 2004 for a complete system description The interface with Garmin G950 is shown on the following Figure ...

Page 299: ...Page G4 4 Section 9 Supplements Supplement no G4 KN 63 DME System for Garmin G950 3rd Edition Rev 0 INTENTIONALLY LEFT BLANK ...

Page 300: ... of Revision Tecnam Approval EASA Approval or Under DOA Privileges DO OoA HDO 0 See Note 1 G5 2 amend emergency procedures D Ronca G Paduano M Oliva DOA privileges Note this Supplement has been originally issued under EASA Major Design Change Approval no 10031750 dated 9 September 2010 List of Effective Pages Page Revision Page Revision G5 1 Rev 0 G5 3 Rev 0 G5 2 Rev 0 G5 4 Rev 0 ...

Page 301: ...IONS See Section 2 of this Manual EMERGENCY PROCEDURES In event of the following failure conditions addressed on Section 3 of this Manual and leading to fly without power generation system Both generators failure Para 3 1 Both generators overvoltage Para 3 3 Inflight engine restart Para 8 2 apply at the end of related checklist following procedure EMERG BATT switch ON WARNING push the Emergency ba...

Page 302: ...ry a dedicated engine starting battery is introduced The entire primary loads stand connected to the main battery itself and the engine starting battery is recharged by the generators This modification is transparent to the crew because it does not change deeply the usual normal and emergency procedures Additionally in event of the overall loss of power generation the starting battery can be put i...

Page 303: ...ERY 3rd Edition Rev 0 When the design change in subject is embodied following placards are installed on the airplane Description Placard Place Engine starting battery voltme ter location Close to the voltmeter Batteries com partment loca tion Fuselage tail cone left side ...

Page 304: ...evisions Rev Revised page Description of Revision Tecnam Approval EASA Approval or Under DOA Privileges DO OoA HDO 0 See Note Note this Supplement has been originally issued under EASA Major Design Change Approval no 10031748 rev 1 dated 17 November 2010 List of Effective Pages Page Revision Page Revision G6 1 Rev 0 G6 4 Rev 0 G6 2 Rev 0 G6 5 Rev 0 G6 3 Rev 0 G6 6 Rev 0 ...

Page 305: ... G6 POWER SUPPLY FROM BUILT IN GENERATORS 3rd Edition Rev 0 INTRODUCTION This section contains information to operate the airplane equipped with built in generators GENERAL The Rotax engine built in generators one for each engine feed two bus bars ...

Page 306: ...PPLY FROM BUILT IN GENERATORS 3rd Edition Rev 0 EASA Approved LIMITATIONS EASA APPROVED Following limitations must apply when the built in generators are operative During Take off Climb Landing and Single Engine operations LH and RH AUX FIELD switch BOTH OFF ...

Page 307: ...nerator failure Para 3 2 Single generator overvoltage Para 3 4 Both generators failure Para 3 1 Both generators overvoltage Para 3 3 Engine securing Para 5 Electrical system overall failure Para 7 1 All smoke and fire occurrences Para 10 1 to 10 5 apply following procedure LH and RH AUX FIELD switch BOTH OFF NORMAL OPERATIONS See Section 4 of this Manual PERFORMANCES See Section 5 of this Manual W...

Page 308: ...e are located also the breakers relat ed to the auxiliary power generation system LH breakers rack built in generators field switches and system related breakers panel type 1 When panel type 2 is installed see picture below each generator field is first ex cited selecting START on the toggle switch Then to allow power generation toggle switch must be set to ON position LH breakers rack built in ge...

Page 309: ...Page G6 6 Section 9 Supplements Supplement no G6 POWER SUPPLY FROM BUILT IN GENERATORS 3rd Edition Rev 0 INTENTIONALLY LEFT BLANK ...

Page 310: ...eges DO OoA HDO 0 See Note Note this Supplement has been originally issued on 12 November 2010 after EASA Third Country Valida tion process completion List of Effective Pages Page Revision Page Revision G7 1 Rev 0 G7 13 Rev 0 G7 2 Rev 0 G7 14 Rev 0 G7 3 Rev 0 G7 15 Rev 0 G7 4 Rev 0 G7 16 Rev 0 G7 5 Rev 0 G7 17 Rev 0 G7 6 Rev 0 G7 18 Rev 0 G7 7 Rev 0 G7 19 Rev 0 G7 8 Rev 0 G7 20 Rev 0 G7 9 Rev 0 G7...

Page 311: ...ntrol System 8 Loss of Stabilator Control 8 Loss of Aileron Control 9 Loss of Rudder Control 9 One engine inoperative procedures 10 Characteristic airspeeds with one engine inoperative 10 Inflight engine restart 11 Landing emergencies 12 Landing without engine power 12 Landing on the Airfield 12 NORMAL OPERATIONS 13 Cold weather operations 13 Airspeeds for normal operations 13 Aircraft walk around...

Page 312: ... supplement must be placed in EASA Approved P2006T Aircraft Flight Manual Section 9 if the airplane is certified to the CIS configuration The information con tained herein complements the basic information in the EASA Approved Aircraft Flight Manual For limitations procedures and performance information not con tained in this supplement refer to the EASA Approved Aircraft Flight Manual ...

Page 313: ...ore than 60 are not approved for such a category In addi tion stall with one engine inoperative is forbidden WARNING Limit load factor could be exceeded by moving flight controls to maxi mum deflection at a speed above VA VO 118 KIAS Manoeuvring Speed AMBIENT TEMPERATURE Ambient temperature from 25 C to 40 C FLIGHT ALTITUDE Flight Altitude limitation 3000 m 9800ft and 3600 m 11800ft for max 30 min...

Page 314: ...ASA Approved OVER WATER FLIGHTS Extended over water flights are allowed within the limitations prescribed by CIS op erational regulations FLIGHT CREW Minimum permitted 1 pilot Maximum people on board 4 people including pilot If right control wheel is not removed right seat may be occupied by the crew member NOTE ...

Page 315: ...opening in structions АВАРИЙНЫЙ ВЫХОД НА ВОДУ 1 Повернуть 2 Сильно толкнуть дверь Ditching emergency exit handle internal side Ditching emer gency exit opening in structions АВАРИЙНЫЙ ВЫХОД НА ВОДУ 1 Повернуть 2 Сильно толкнуть дверь Ditching emergency exit handle external side Door locking system by pass instruc tions ДЛЯ АВАРИЙНОГО ДОСТУПА 1 Нажать вниз и удержать красный флажок 2 Открыть дверь ...

Page 316: ...y pass instruc tions ДЛЯ АВАРИЙНОГО ВЫХОДА 1 Нажать вниз и удержать красный флажок 2 Открыть дверь Main door and emer gency exit internal side Main door exit instructions ПРЕДУПРЕЖДЕНИЕ Перед открытием двери убедиться что винт остановлен Выход в переднюю часть самолета Main door internal side Emergency exit label АВАРИЙНЫЙ ВЫХОД Emergency exit inter nal and external side ...

Page 317: ...turning 3 Control the aircraft with mechanical trim and engine power setting The increase of thrust causes a nose up moment the decrease of thrust causes a nose down moment The control by trim operation is related to the trim position trim UP for aircraft nose Up trim DOWN for aircraft nose DOWN CAUTION Perform approach and landing only in cruise configuration Flap 0 It is necessary to move the la...

Page 318: ...nd as soon as practical CAUTION Perform approach and landing only in cruise configuration Flap 0 Perform approach and landing with crosswind trend type landing LOSS OF RUDDER CONTROL In case of loss of pilot side rudder control disconnected or jammed apply following proce dure 1 Continue flight at the speed of 80 85 KIAS due to the aircraft weight in cruise configuration 2 Control airplane bank an...

Page 319: ...im prove the efficiency it is preferred to bank the aircraft to the side of the operating engine by about 5 Depending upon the circumstances that may arise apply the emer gency procedure as below CHARACTERISTIC AIRSPEEDS WITH ONE ENGINE INOPERA TIVE In case of one engine inoperative condition pilot shall take into account the air speeds shown below Conditions Speed KIAS Minimum aircraft control sp...

Page 320: ...d rpm 12 FIELD ON 13 Engine throttle levers SET as required If the fuel quantity in the tank which feeds the stopped engine is low select the opposite side fuel tank by means of the fuel selector After starter engagement during in flight engine restart PFD indica tion may be temporarily lost PFD Attitude recovery can last up to 3 4 minutes During attitude recovery it is necessary to maintain level...

Page 321: ...this way the time required to complete the extension is shorter by about 8 sec 4 Select landing field check for obstacles and wind 5 Safety belts FASTEN Before touch down 6 Fuel Selector BOTH OFF 7 Electrical fuel pump BOTH OFF 8 Ignitions ALL OFF 9 MASTER SWITCHES ALL OFF WARNING Emergency Landing outside of airfield shall be performed with land ing gear retracted and starting flaps extension in ...

Page 322: ...nt for normal operations FLAPS 1180kg 2600lb Rotation Speed in takeoff VR T O 64 KIAS Speed over a 15 meters obstacle Vobs Take Off T O 70 KIAS Best Angle of Climb Speed VX 0 80 KIAS Best Rate of Climb speed VY 0 80 KIAS Approach speed T O 90 KIAS Speed over a 15 meters obstacle Vobs Landing T O 70 KIAS Final Approach Speed FULL 70 KIAS Manoeuvring speed VA 0 118 KIAS Never Exceed Speed VNE 0 167 ...

Page 323: ...no G7 AFM Supplement for CIS countries operators 3rd Edition Rev 0 AIRCRAFT WALK AROUND In addition to the aircraft walk around checklist reported on basic AFM Section 4 perform following checks Left and right wing leading edge Check stall strip ...

Page 324: ...splaying in meters see G950 Pilot s Guide 6 Seat Adjust as required 7 Seat belt Fastened 8 Passenger briefing Completed 9 Doors CLOSED AND LOCKED 10 Landing gear control lever CHECK DOWN 11 Breakers All ON 12 MASTER SWITCH ON 13 Fuel quantity CHECK 14 RH fuel selector RIGHT 15 LH fuel selector LEFT 16 RH Electrical Fuel Pump ON check fuel pressure gauge correct operation 17 RH Electrical Fuel pump...

Page 325: ...ck green lights and TRANS light turned OFF 15 Speed over obstacle 70KIAS 16 Flaps 0 at 300 ft AGL 21 Landing and taxi lights OFF 17 Establish climb rate Above 80 KIAS 18 Trim adjustment 19 LH and RH Propeller Lever Set at 2250 rpm after reaching safe al titude 20 LH and RH Electrical Fuel pump BOTH OFF CRUISE Flights in the CIS airspace are allowed only along the routes with continuous ATC monitor...

Page 326: ... for CIS countries operators 3rd Edition Rev 0 BALKED LANDING 1 LH and RH Throttle Lever FULL THROTTLE 2 LH and RH Propeller Lever FULL FORWARD 3 Speed Over 70 KIAS 4 Flaps T O 5 Landing gear UP 6 Carburettor heat CHECK OFF 7 LH and RH Electrical Fuel pump CHECK ON ...

Page 327: ...of headwind the takeoff run decreases by 2 5m for each knot of wind 8 ft kt In case of tailwind the takeoff run increases by 10m for each knot of wind 33 ft kt Measurement distances for short grass less than 2 inches must be increased of 10 Measurement distances for high grass more than 2 inches must be increased of 15 A rising runway with a gradient of 1 causes an acceleration decreasing of the s...

Page 328: ...e of headwind the takeoff run decreases by 4m for each knot of wind 13 ft kt In case of tailwind the takeoff run increases by 14m for each knot of wind 40 ft kt Take off roll measurement distances for short grass less than 2 inches must be increased of 10 Take off roll measurement distances for high grass more than 2 inches must be increased of 15 A rising runway with a gradient of 1 causes a take...

Page 329: ...ment for CIS countries operators 3rd Edition Rev 0 CLIMB PERFORMANCE ONE ENGINE INOPERATIVE CONDITIONS AC Clean configuration One engine inoperative Max Cont Power Airspeed Weight kg VSSE KIAS 1180 80 1080 78 980 75 Figure 3 Rate of Climb one engine inoperative ...

Page 330: ...Page G7 21 Section 9 Supplements Supplement no G7 AFM Supplement for CIS countries operators 3rd Edition Rev 0 WEIGHT AND BALANCE For weight and balance make reference to Section 6 of this Manual ...

Page 331: ...for CIS countries operators 3rd Edition Rev 0 SYSTEMS INSTRUMENTS PANEL 1 2 3 4 5 7 8 9 12 13 14 15 16 17 18 19 20 21 22 23 24 25 26 28 29 30 31 32 6 10 11 33 34 35 36 37 38 39 41 42 43 44 45 46 47 49 51 52 53 50 48 27 54 55 40 56 57 Instruments panel typical layout ...

Page 332: ... A P indicator 9 RH R P M 10 RH fuel quantity indicator 11 LH CHT 12 RH CHT 13 LH Oil Temperature 14 RH Oil Temperature 15 LH oil pressure 16 RH oil pressure 17 RH breakers panel 18 RH ram air inlet 19 Instruments light switch 20 Strobe light switch 21 Navigation light switch 22 Taxi light switch 23 Landing light switch 24 Position flaps indicator 25 RH fuel pressure 26 LH fuel pressure 27 Flap sw...

Page 333: ...e slip indicator 39 LG control knob 40 Voltammeter Indicator 41 ADF control panel 42 Cockpit light dimmer 43 Cabin heat warm air from RH engine 44 Avionics lights dimmer 45 Cabin heat warm air from LH engine 46 LH ram air inlet 47 Trim rudder indicator 48 Switches built in lights dimmer 49 ELT Indicator 50 RH breakers panel 51 Pitch trim indicator 52 Pitot heat switch 53 A P Master switch 54 A P t...

Page 334: ...Page G8 1 Section 9 Supplements Supplement no G8 BRAZILIAN AFMS 3rd Edition Rev 0 SUPPLEMENT NO G8 BRAZILIAN AIRCRAFT FLIGHT MANUAL SUPPLEMENT EASA APPROVED ...

Page 335: ... Approval EASA Approval or Under DOA Privileges DO OoA HDO 0 See Note Note this Supplement has been originally issued on 4 March 2011 after EASA Third Country Validation process completion List of Effective Pages Page Revision Page Revision G8 1 Rev 0 G8 6 Rev 0 G8 2 Rev 0 G8 7 Rev 0 G8 3 Rev 0 G8 8 Rev 0 G8 4 Rev 0 G8 9 Rev 0 G8 5 Rev 0 G8 10 Rev 0 ...

Page 336: ...ev 0 TABLE OF CONTENTS INTRODUCTION 4 GENERAL 4 LIMITATIONS 5 Approved fuel 5 VHF COMM system 5 GPS systems 6 GPS operation for airplanes with autopilot installed 6 GPS operation for airplanes without autopilot installed 7 WAAS and SBAS functionalities 7 Placards in portuguese 8 ...

Page 337: ...or Brazilian registered aircraft GENERAL Information contained herein complements the basic information in the EASA Ap proved Aircraft Flight Manual when the aircraft is registered in Brazil For limitations procedures and performance information not contained in this Sup plement refer to the basic Aircraft Flight Manual ...

Page 338: ... 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 Mainte nance Manual who provides dedicated checks due to the pro longed use of Avgas VHF COMM SYSTEM When operating the VHF COMM system in Brazilian air space the selection of the channel spacing of 8 33 kHz can cause the loss of comm...

Page 339: ...light position must be verified every 15 minutes using other IFR approved navigation system During IFR in terminal area or non precision approach using GPS in case RAIM function becomes unavailable the GPS navigation must be discontinued Before an IFR non precision approach using GPS the availability of the RAIM function must be checked to the time and place predicted RAIM prediction If predicted ...

Page 340: ...on GPS is approved as supplemental means for navigation Use of GPS is prohibited for IFR in terminal area or in non precision approach operations If RAIM function becomes unavailable in en route phase of flight position must be verified every 15 minutes using other IFR approved navigation system WAAS AND SBAS FUNCTIONALITIES The WAAS and SBAS functionalities are not available in Brazil and these f...

Page 341: ...ion Placard Place Smoking ban Instruments panel right side Engine oil level and speci fications On the engine na celle in correspon dence of the engine oil reservoir access door Fuel type and quantity In correspondence of each fuel tank filler cap Baggage com partment ca pacity Baggage compart ment vertical panel ...

Page 342: ...t opening in structions Ditching emer gency exit handle external side Ditching emer gency exit opening in structions Ditching emer gency exit handle internal side Door locking system by pass instruc tions Main door and emergency exit external side Door locking system by pass instruc tions Main door and emergency exit in ternal side ...

Page 343: ...nt no G8 BRAZILIAN AFMS 3rd Edition Rev 0 Description Placard Place Main door exit instructions Main door internal side Emergency exit label Emergency exit internal and exter nal side Towing maxi mum turning angle Nose landing gear front door ...

Page 344: ...Page G9 1 Section 9 Supplements Supplement no G9 CHINESE AFMS 3rd Edition Rev 0 SUPPLEMENT NO G9 CHINESE AIRCRAFT FLIGHT MANUAL SUPPLEMENT EASA APPROVED ...

Page 345: ...of Revision Tecnam Approval EASA Approval or Under DOA Privileges DO OoA HDO 0 First issue P Violetti M Oliva L Pascale Third Country Validation List of Effective Pages Page Revision Page Revision G9 1 Rev 0 G9 7 Rev 0 G9 2 Rev 0 G9 8 Rev 0 G9 3 Rev 0 G9 9 Rev 0 G9 4 Rev 0 G9 10 Rev 0 G9 5 Rev 0 G9 11 Rev 0 G9 6 Rev 0 G9 12 Rev 0 ...

Page 346: ...Section 9 Supplements Supplement no G9 CHINESE AFMS 3rd Edition Rev 0 TABLE OF CONTENTS INTRODUCTION 4 GENERAL 4 LIMITATIONS 5 Approved fuel 5 Placards in Chinese 6 NORMAL OPERATIONS 10 Cold weather operations 10 ...

Page 347: ...for Chinese registered aircraft GENERAL Information contained herein complements the basic information in the EASA Ap proved Aircraft Flight Manual when the aircraft is registered in China For limitations procedures and performance information not contained in this Sup plement refer to the basic Aircraft Flight Manual ...

Page 348: ...28 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 It is therefore suggested to avoid using this type of fuel unless strictly nec essary Make reference to Rotax Maintenance Manual who provides dedicated checks due to the prolonged ...

Page 349: ...s On the engine nacelle in correspondence of the engine oil reser voir access door 滑油箱检查油位滑油油位最大 3Lt OK 最低 2Lt 滑油油位超出限制时禁止飞行只允许使用API规定的或更高级别的滑油 Fuel type and quanti ty In correspondence of each fuel tank filler cap GB17930 97号车用汽油 ASTM D4814车用汽油航空汽油 100LL ASTM D910 97升 25 6 U S 加仑合计可用容量 Baggage compartment capacity Baggage compartment vertical panel 最大行李载荷 80kg 176磅最大规定压强 0 9 kg dm2 19lbs ...

Page 350: ...cy exit handle internal side 水上迫降应急出口 1 旋转 2 平稳向外推 Ditching emergency exit opening instruc tions Ditching emergency exit handle external side 水上迫降应急出口 1 旋转 2 平稳向内拉 Door locking system by pass instructions Main door and emer gency exit external side 应急通道 1 按住红色扭 2 用把手打开门 Door locking system by pass instructions Main door and emer gency exit internal side 应急出口 1 按住红色扭 2 用把手打开门 ...

Page 351: ...d Edition Rev 0 Description Place Placard Chinese Main door exit in structions Main door internal side 警告打开门向飞机前方撤离前确认螺旋桨已经停止转动 Emergency exit label Emergency exit inter nal and external side 应急出口 Maximum steering angle Front of the aircraft 注意牵引最大转弯角度中立两侧20度 ...

Page 352: ...Page G9 9 Section 9 Supplements Supplement no G9 CHINESE AFMS 3rd Edition Rev 0 INTENTIONALLY LEFT BLANK ...

Page 353: ...es the wheels the blades and the gears against the snow or ice accumulation Water and other freezable liquids should be removed from the airplane Standing water that could freeze should be removed from critical parts as flaps and ailerons hinges trim tabs hinges drain points LG doors cabin doors etc With an ambient temperature of below 20 C remove battery and store in a warm dry place additionally...

Page 354: ...nflation pressure should be performed on tires cooled to ambient temperature If the crew detects ice 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 WARNING Removal of snow ice accumulations is necessary prior to takeoff because they will seriously affect airplane performance Aircraft with ice snow accumulation are for...

Page 355: ...Page G9 12 Section 9 Supplements Supplement no G9 CHINESE AFMS 3rd Edition Rev 0 INTENTIONALLY LEFT BLANK ...

Page 356: ... Vle Increase 3rd Edition Rev 1 SUPPLEMENT NO G11 VLO VLE INCREASE RECORD OF REVISIONS Rev Revised page Description of Revision Tecnam Approval EASA Approval Or Under DOA Privileges DO OoA HDO 1 First issue M Landi M Oliva L Pascale EASA approval 10041602 ...

Page 357: ...Page G11 2 Section 9 Supplements Supplement no G11 Vlo Vle Increase 3rd Edition Rev 1 LOEP Page Revision G11 1 Rev 1 G11 2 Rev 1 G11 3 Rev 1 G11 4 Rev 1 G11 5 Rev 1 G11 6 Rev 1 ...

Page 358: ...aft equipped with Garmin G950 Integrated Flight Deck System Design Change MOD 2006 002 and provides supplemental information to increase the Vlo Vle when the Tecnam Service Bulletin SB 098 CS or Design Change MOD 2006 033 has been embodied on the airplane The information contained herein supersedes the basic Aircraft Flight Manual ...

Page 359: ...Page G11 4 Section 9 Supplements Supplement no G11 Vlo Vle Increase 3rd Edition Rev 1 EASA Approved SECTION 2 LIMITATIONS ...

Page 360: ...lement no G11 Vlo Vle Increase 3rd Edition Rev 1 EASA Approved SPEED LIMITATIONS On the left side instrument panel above on the left it is placed the following plac ard reporting the speed limitations Maximum L G op speed VLO VLE 122 KIAS ...

Page 361: ...Page G11 6 Section 9 Supplements Supplement no G11 Vlo Vle Increase 3rd Edition Rev 1 INTENTIONALLY LEFT BLANK ...

Page 362: ...ICAN AFM SACAA APPROVED 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 See Note Note this Supplement has been originally issued on 2 May 2013 after EASA Third Country Validation pro cess completion ...

Page 363: ...2 2 Section 9 Supplements Supplement no G12 South African AFM 3rd Edition Rev 0 LOEP Page Revision Page Revision G12 1 Rev 0 G12 5 Rev 0 G12 2 Rev 0 G12 6 Rev 0 G12 3 Rev 0 G12 7 Rev 0 G12 4 Rev 0 G12 8 Rev 0 ...

Page 364: ... OF CONTENTS INTRODUCTION 4 LIMITATIONS 5 Maximum operating altitude 5 Inflight engine restart 5 GPS systems 6 GPS GNS 430 or GNS 530 operation for airplanes with autopilot installed 6 GPS GNS 430 or GNS 530 operation for airplanes without autopilot installed 6 WAAS and SBAS functionalities 7 ...

Page 365: ...tal information to the basic information approved in EASA aircraft Flight Manual when the aircraft is registered in South Africa For Limitations procedures and performance information not contained in this supplement refer to the basic Aircraft Flight Manual The information contained herein supplements or supersedes the basic Aircraft Flight Manual or the Supplement G1 as applicable ...

Page 366: ...2 000 feet 3658 m for longer than 120 minutes intended flight time or above 12 000 feet the aircraft shall not be operated unless the aircrew is provided with the supplemental oxygen as prescribed in Document SA CATS 91 and such oxygen may be used continuous ly whenever these circumstances prevail INFLIGHT ENGINE RESTART The inflight engine restart procedure is reported on a placard shown below in...

Page 367: ...nued Before an IFR non precision approach using GPS the availability of the RAIM function must be checked to the time and place predicted RAIM prediction If predicted the unavailability of the RAIM function navigation must be planned with others approved navigation systems Before a non precision approach using GPS the database information must be compared with that in the approach chart including ...

Page 368: ...ents Supplement no G12 South African AFM 3rd Edition Rev 0 WAAS AND SBAS FUNCTIONALITIES The WAAS and SBAS functionalities are not available in South Africa and these functions are not tested or approved in South African air space ...

Page 369: ...Section 9 Supplements Supplement no G12 South African AFM 3rd Edition Rev 0 Page G10 8 INTENTIONALLY LEFT BLANK ...

Page 370: ... NO G13 ALTERNATORS WITH 70 A INSTALLATION Record of Revisions Rev Revised page Description of Revision Tecnam Approval EASA Approval Or Under DOA Privileges DO OoA HDO 0 See Note List of Effective Pages Page Revision Page Revision G13 1 Rev 0 G13 6 Rev 0 G13 2 Rev 0 G13 7 Rev 0 G13 3 Rev 0 G13 4 Rev 0 G13 5 Rev 0 ...

Page 371: ...ity to replace the mentioned pages in the AFM in accordance with the instructions herein addressed section by section GENERAL When 70A alternators are installed replacing the standard 40A ones the electrical system logic is not affected by any substantial change Primary DC power is pro vided by two engine driven alternators which during normal operations operate in parallel Each alternator is rate...

Page 372: ...CTION 3 EMERGENCY PROCEDURES This section report some procedures which replace the same procedure in the basic AFM The procedures affected from the replacement of existing 40A alternators with 70A are the following Single alternator failure overvoltage Both alternators failure Both alternators overvoltage ...

Page 373: ...LD LH or RH OFF 2 FIELD LH or RH ON If the LH or RH ALT caution stays displayed 3 FIELD LH or RH OFF Equipment will be lost accordingly to the following table The battery and a single generator are able to supply the electri cal power necessary for flight but redundancy is lost LH Gen Bus LH Avionic Bus RH Avionic Bus RH Gen Bus Pitot Heat DME ADF NAV Lights Landing Light Transponder COM 2 Rudder ...

Page 374: ... restored alternator 2 Refer to Single alternator failure overvoltage drill Para 2 1 If both LH and RH ALT cautions stay displayed 3 FIELD LH and RH BOTH OFF 4 CROSS BUS LH and RH BOTH OFF If engine starting battery modification is applied 5 EMERG BATT switch ON 6 Land as soon as possible If engine starting battery modification is not applied 5 Land as soon as possible Equipment will be lost accor...

Page 375: ... BOTH OFF 4 FIELD LH and RH BOTH OFF 5 FIELD LH and RH BOTH ON one at a time If LH or RH BUS VOLT HIGH warning stays displayed 6 Verify good ammeter indications on restored alternator 7 Switch CROSS BUS on the restored alternator side 8 Refer to Single alternator failure overvoltage drill Para 2 1 If both LH and RH BUS VOLT HIGH warning stay displayed 7 FIELD LH and RH BOTH OFF If engine starting ...

Page 376: ...Alternators with 70A Supplement Section 9 Supplements Supplement no G13 Alternators with 70A installation 3rd Edition Rev 0 Page G13 7 Section 3 Emergency procedures INDEX INTENTIONALLY LEFT BLANK ...

Page 377: ... DIGITAL CONFIGURATION Ed 4 Rev 0 SUPPLEMENT NO G14 SMP FOR DIGITAL CONFIGURATION RECORD OF REVISIONS Rev Revised page Description of Revision Tecnam Approval EASA Approval Or Under DOA Privileges DO OoA HDO 0 First issue D Ronca C Caruso M Oliva DOA Approval ...

Page 378: ...ev 0 LOEP Pages Revision Cover pages G14 1 thru 23 Rev 0 Section 2 SMP2 3 Rev 0 Section 3 SSMP3 3 thru 5 Rev 0 SSMP3 7 thru 9 Rev 0 SSMP3 21 Rev 0 SSMP3 29 Rev 0 SSMP3 36 thru 40 Rev 0 SSMP3 49 thru 53 Rev 0 Section 4 SSMP4 26 thru 27 Rev 0 Section 7 SSMP7 41 Rev 0 SSMP7 44 thru 47 Rev 0 ...

Page 379: ...h during normal operations operate in parallel Each alternator is rated at 14 2 14 8 Vdc through two external first fuselage frame installed voltage regulators 70 Amp and is provided with an automatic overvolt age device protecting the circuits and the electric components from an excessive voltage caused by alternator s failures The power rating of the each generator is such that if one generator ...

Page 380: ...Page G14 4 Section 9 Supplements Supplement no G14 SMP FOR DIGITAL CONFIGURATION Ed 4 Rev 0 INTENTIONALLY LEFT BLANK ...

Page 381: ...e G14 5 Section 9 Supplements Supplement no G14 SMP FOR DIGITAL CONFIGURATION Ed 4 Rev 0 SECTION 1 GENERAL Apply following instruction See Basic AFM Section 1 Supplement G14 pages replacement instructions ...

Page 382: ...Page G14 6 Section 9 Supplements Supplement no G14 SMP FOR DIGITAL CONFIGURATION Ed 4 Rev 0 INTENTIONALLY LEFT BLANK ...

Page 383: ...P FOR DIGITAL CONFIGURATION Ed 4 Rev 0 SECTION 2 LIMITATIONS Apply following pages replacement procedure Supplement G14 LIMITATIONS page Basic AFM Section 2 page SMP2 3 REPLACES Page 2 3 of Basic AFM Section 2 Supplement G14 pages replacement instructions ...

Page 384: ...Page G14 8 Section 9 Supplements Supplement no G14 SMP FOR DIGITAL CONFIGURATION Ed 4 Rev 0 INTENTIONALLY LEFT BLANK ...

Page 385: ... Mission purpos es should be kept OFF during take off climb landing and any abnormal procedure that affects electrical generating system including single engine operation During Take off Climb Landing and Single Engine Operations LH and RH AUX FIELD switches BOTH OFF This limitation only applies when both 70Amp alternators and converter box are installed Safety provisions as following described au...

Page 386: ...Page G14 9 Section 9 Supplements Supplement no G14 SMP FOR DIGITAL CONFIGURATION Ed 4 Rev 0 INTENTIONALLY LEFT BLANK ...

Page 387: ...ge SSMP3 3 thru 5 REPLACE Page S3 3 thru 5 of Supplement G1 Section 3 SSMP3 7 thru 9 REPLACE Page S3 8 thru 11 of Supplement G1 Section 3 SSMP3 21 REPLACES Page S3 21 of Supplement G1 Section 3 SSMP3 29 REPLACES Page S3 29 of Supplement G1 Section 3 SSMP3 36 thru 40 REPLACE Page S3 36 thru 40 of Supplement G1 Section 3 SSMP3 49 thru 53 REPLACE Page S3 49 thru 53 of Supplement G1 Section 3 Suppleme...

Page 388: ...Page G14 11 Section 9 Supplements Supplement no G14 SMP FOR DIGITAL CONFIGURATION Ed 4 Rev 0 INTENTIONALLY LEFT BLANK ...

Page 389: ...nection of converter box is very simple and in most of abnormal cases is automatically managed by relays and safety provisions The converter box following described in Section 7 is managed by the pilot only via two switches located in the bottom LH side of pilot seat on a single panel provided by two switches two breakers and two indicating lamps Only when pilot selects BOTH switches ON right and ...

Page 390: ...These procedures characters are boxed and highlighted 1 1 ENGINE FAILURE DURING TAKEOFF RUN BEFORE ROTATION ABORT TAKE OFF 1 Throttle Lever BOTH IDLE 2 Rudder Keep heading control 3 4 b other procedures which should be well theoretically known and mastered but that can be executed entering and following step by step the AFM current section appropriate checklist Additionally operating the aircraft ...

Page 391: ...anding 3 Apply the pertinent procedure 4 Inform the Air Traffic Control as applicable For the safe conduct of later flights any anomaly and or failure must be communicated to the National Authorities in charge in order to put the aircraft in a fully operational and safe condition In this Chapter following definitions apply Land as soon as possible land without delay at the nearest suitable area at...

Page 392: ...or OR R ALT FAIL Rh Alternator 1 FIELD LH or RH OFF 2 LH and RH AUX FIELD switch BOTH OFF 3 FIELD LH or RH ON If the LH or RH ALT caution stays displayed 1 FIELD LH or RH OFF If the LH or RH GENERATOR caution persists displayed 1 CROSS BUS LH or RH OFF 2 Land as soon as practical The battery and a single generator are able to supply the electrical power necessary for the entire mission but redunda...

Page 393: ...tion alerts displayed 1 FIELD LH and RH BOTH OFF 2 LH and RH AUX FIELD switch BOTH OFF 3 FIELD LH and RH BOTH ON If both LH and RH ALT cautions stay displayed 1 FIELD LH and RH BOTH OFF 2 CROSS BUS LH and RH BOTH OFF If engine starting battery modification is applied 1 EMERG BATT switch ON 2 Land as soon as possible If engine starting battery modification is not applied 1 Land as soon as possible ...

Page 394: ...ning stays displayed 1 FIELD LH or RH OFF if both LH and RH OVERVOLT warning stay displayed 1 CROSS BUS LH and RH BOTH OFF 2 FIELD LH and RH BOTH OFF 3 FIELD LH and RH BOTH ON one at a time If LH or RH OVERVOLT warningt stays displayed 1 FIELD LH or RH OFF 2 CROSS BUS LH or RH ON If both LH and RH OVERVOLT warning stay displayed 1 FIELD LH and RH BOTH OFF 2 CROSS BUS LH and RH BOTH OFF If engine s...

Page 395: ...mp OFF 6 LH and RH AUX FIELD switch BOTH OFF If necessary this procedure is applicable to both engines When both engines are secured both CROSS BUS switches must be set to OFF After securing engine s after analysing situation refer immediately to following procedures ENGINE FAILURE IN FLIGHT see Para 6 5 SINGLE GENERATOR FAILURE see Para 2 1 or BOTH GENERATOR FAILURE see Para 2 2 INFLIGHT ENGINE R...

Page 396: ...OWN 5 Airspeed Up to VLE 5 2 TOTAL ELECTRICAL FAILURE In case of electrical system overall failure apply following procedure 1 Emergency light ON 2 Standby attitude indicator switch ON 3 MASTER SWITCH OFF 4 FIELD LH and RH BOTH OFF 5 LH and RH AUX FIELD switch BOTH OFF 6 MASTER SWITCH ON 7 FIELD LH and RH BOTH ON If failure persists 9 EMERG BATT switch ON if engine starting battery installed 10 La...

Page 397: ...ler Lever FULL FORWARD 11 Start push button PUSH 12 Propeller Lever SET at desired rpm 13 FIELD ON check for positive ammeter 14 Engine throttle levers SET as required If engine restart is unsuccessful 15 EMERG BATT switch ON if starting battery installed 16 Repeat engine restart procedure CAUTION After engine restart if practical moderate propeller rpm and throttle increase to allow OIL and CHT C...

Page 398: ... A suggested GO NO GO criteria is abort take off until LG is still down and locked Once airborne accelerate to Blue Line Speed VYSE before command ing LG retraction Take off planning should take into account that high density altitude and aircraft mass may result in OEI negative climb rate VYSE with flap up shall be flown in order to achieve best possible rate of climb after landing gear retractio...

Page 399: ...and RH AUX FIELD switch BOTH OFF 8 Inoperative engine Propeller Lever FEATHER 9 Inoperative engine Confirm and SECURE If engine restart is possible 10 Apply INFLIGHT ENGINE RESTART procedure see Para 6 2 If engine restart is unsuccessful or it is not recommended 11 Land as soon as possible 12 One engine inoperative landing procedure see Para 6 6 WARNING Following a mechanical engine seizure fire o...

Page 400: ...ON 7 Operating engine Fuel Selector Check correct feeding crossfeed if needed If engine restart is possible 8 Apply INFLIGHT ENGINE RESTART procedure see Para 6 2 If engine restart is unsuccessful or it is not recommended 9 Land as soon as possible 10 One engine inoperative landing procedure see Para 6 6 WARNING Following a mechanical engine seizure fire or a major propeller dam age engine restart...

Page 401: ...FF 2 Ignitions ALL OFF 3 LH and RH AUX FIELD switch BOTH OFF 4 Electrical fuel pumps BOTH OFF 5 Cabin heat and defrost OFF 6 MASTER SWITCH OFF 7 Parking Brake ENGAGED 8 Aircraft Evacuation carry out immediately WARNING Consider use of ditching emergency exit to escape in case pilot or passenger doors are blocked watch for engine hot parts fuel hydraulic fluid or oil spills Leave aircraft in upwind...

Page 402: ...t in upwind direction IF THE DECISION IS TAKEN TO CONTINUE THE TAKEOFF WARNING A take off abort should always be preferred if a safe stop can be per formed on ground A suggested GO NO GO criteria is abort take off until LG is still down and locked Once airborne accelerate to Blue Line Speed VYSE before commanding LG retraction Take off planning should take into account that high density altitude a...

Page 403: ...H AUX FIELD switch BOTH OFF 10 Cabin heat and defrost BOTH OFF 11 Fire affected engine Fuel Selector Confirm and OFF 12 Fire affected engine Ignitions Confirm and BOTH OFF 13 Fire affected engine Electrical fuel pump Confirm and OFF 14 Fire affected engine FIELD OFF 15 Land as soon as possible applying one engine inoperative landing procedure See Para 6 6 ...

Page 404: ...g Keep control using rudder and ailerons 10 Attitude Adjust as appropriate to keep airspeed over 62 KIAS 11 Fire affected engine Field OFF 12 Cabin ventilation OPEN 13 Land as soon as possible applying one engine inoperative landing procedure See Para 6 6 8 4 ELECTRICAL SMOKE IN CABIN ON THE GROUND 1 MASTER SWITCH OFF 2 Cabin heat and defrost OFF 3 LH and RH AUX FIELD switch BOTH OFF 4 Throttle Le...

Page 405: ...y source by 6 FIELD LH and RH OFF 7 LH and RH AUX FIELD switch BOTH OFF 8 AVIONICS LH and RH OFF 9 CROSS BUS LH and RH BOTH OFF CAUTION A fully charged battery can supply electrical power for at least 30 minutes If faulty source is found 10 It may be possible to restore non faulty power sources one at a time If smoke persists WARNING Before total electrical system shutdown consider gaining VMC con...

Page 406: ...Page G14 12 Section 9 Supplements Supplement no G14 SMP FOR DIGITAL CONFIGURATION Ed 4 Rev 0 INTENTIONALLY LEFT BLANK ...

Page 407: ...GURATION Ed 4 Rev 0 SECTION 4 NORMAL PROCEDURES Apply following pages replacement procedure Supplement G14 NORMAL PROCEDURES page Supplement S1 Section 4 page SSMP4 26 thru 27 REPLACE Page S4 26 thru 27 of Supplement G1 Section 4 Supplement G14 pages replacement instructions ...

Page 408: ...Page G14 14 Section 9 Supplements Supplement no G14 SMP FOR DIGITAL CONFIGURATION Ed 4 Rev 0 INTENTIONALLY LEFT BLANK ...

Page 409: ...0 110 C Oil pressure 2 5 bar Fuel pressure 2 2 5 8 psi 2 2 7 26 psi 0 15 0 50 bar applicable for fuel pump part no 893110 and no 893114 3 Carburettor heat as needed see also instructions addressed on Section 3 Para 7 4 WARNING Deselect and do not use Auto Pilot if possible icing condition area is inadvert ently entered 4 Fuel balance and crossfeed check as necessary 3 10 1 CONVERTER BOX TURN ON 1 ...

Page 410: ...onditions 3 12 DESCENT AND APPROACH 1 Propellers Set to Max Continuous 2250 RPM 2 Carburettors heat As required 3 Altimeter setting QNH set and crosscheck 3 13 BEFORE LANDING 1 Rear passengers seats Seats set at full aft and lower position 2 LH and RH Electrical Fuel pump BOTH ON 3 On downwind leg Flaps T O MTOW 1180kg MTOW 1230 kg VFE 119KIAS VFE 122KIAS 4 Speed below applicable VLO VLE Landing g...

Page 411: ...o equipped with holes in the cabin and or tailcone ready for third parties sensor s integration While the Tecnam intent is to offer a plat form ready for sensors integration it is end user responsibility to receive the approval from authority for each equipment instal lation including the supplement of Section 5 should the equip ment affect it i e protruding cameras Supplement G14 pages replacemen...

Page 412: ...Page G14 16 Section 9 Supplements Supplement no G14 SMP FOR DIGITAL CONFIGURATION Ed 4 Rev 0 INTENTIONALLY LEFT BLANK ...

Page 413: ...17 Section 9 Supplements Supplement no G14 SMP FOR DIGITAL CONFIGURATION Ed 4 Rev 0 SECTION 6 WEIGHT AND BALANCE Apply following instruction See Basic AFM Section 6 Supplement G14 pages replacement instructions ...

Page 414: ...Page G14 18 Section 9 Supplements Supplement no G14 SMP FOR DIGITAL CONFIGURATION Ed 4 Rev 0 INTENTIONALLY LEFT BLANK ...

Page 415: ...SYSTEMS DESCRIPTION Apply following pages replacement procedure Supplement G14 AIRFRAME AND SYSTEMS DESCRIPTION page Supplement S1 Section 7 page SSMP7 41 REPLACES Page S7 41 of Supplement G1 Section 7 SSMP7 44 thru 47 REPLACE Page S7 44 thru 46 of Supplement G1 Section 7 Supplement G14 pages replacement instructions ...

Page 416: ...Page G14 20 Section 9 Supplements Supplement no G14 SMP FOR DIGITAL CONFIGURATION Ed 4 Rev 0 INTENTIONALLY LEFT BLANK ...

Page 417: ...ternal DC power source can be connected to the aircraft DC distribution system On the instruments panel right side it is installed a voltmeter ammeter The am meter section can indicate the current supplied by either left or right alternator switching a dedicated selector There are five different busses make reference to Figure 11 Battery bus LH Alternator bus RH Alternator bus LH Avionic bus RH Av...

Page 418: ...rting with consequent hazard for people nearby 18 1 MISSION POWER CONTROL When the airplane embodies the design change Power supply from built in gen erators the Rotax engine built in generators are enabled in order to supply power to two available bus bars Each built in generator is activated by means of a switch LH and RH AUX FIELD located on the LH breakers rack where are located also the break...

Page 419: ...s the amount of power surplus available due to the 2006 202 design change 5 The same switches shown in the MOD2006 046 and reported in the figure above enable the relays that feed the converters 6 Four relays enable the external power to feed also the converter box for ground test purposes when external socket is connected 7 A connector box allows the end user to have a maximum current of 40Amp at...

Page 420: ...P FOR DIGITAL CONFIGURATION Page SMP7 46 Section 7 Airframe and Systems description ELECTRICAL SYSTEM Ed 4 Rev 0 In the following figures the new Electrical system schematic is reported Electrical system schematic Page 1 ...

Page 421: ...N G950 IFDS SMP FOR DIGITAL CONFIGURATION Page SMP7 47 Section 7 Airframe and Systems description ELECTRICAL SYSTEM Ed 4 Rev 0 Figure 25 Electrical system schematic Page 2 Electrical system schematic Page 3 ...

Page 422: ...Page G14 21 Section 9 Supplements Supplement no G14 SMP FOR DIGITAL CONFIGURATION Ed 4 Rev 0 INTENTIONALLY LEFT BLANK ...

Page 423: ... Section 9 Supplements Supplement no G14 SMP FOR DIGITAL CONFIGURATION Ed 4 Rev 0 SECTION 8 GROUND HANDLING SERVICE Apply following instruction See Basic AFM Section 8 Supplement G14 pages replacement instructions ...

Page 424: ...Page G14 23 Section 9 Supplements Supplement no G14 SMP FOR DIGITAL CONFIGURATION Ed 4 Rev 0 INTENTIONALLY LEFT BLANK ...

Page 425: ...VE STAND BY INSTRUMENT Ed 4 Rev 0 SUPPLEMENT NO G16 MD302 ALTERNATIVE STAND BY INSTRUMENT RECORD OF REVISIONS Rev Revised page Description of Revision Tecnam Approval EASA Approval Or Under DOA Privileges DO OoA HDO 0 First issue D Ronca C Caruso M Oliva DOA Approval ...

Page 426: ...LTERNATIVE STAND BY INSTRUMENT Ed 4 Rev 0 LOEP Pages Revision Cover pages G16 1 thru 25 Rev 0 Section 2 MD2 12 Rev 0 Section 3 SMD3 15 thru 16 Rev 0 SMD3 30 Rev 0 Section 4 SMD4 15 Rev 0 Section 6 MD6 11 Rev 0 Section 7 MD7 29 Rev 0 SMD7 37 Rev 0 SMD7 39 Rev 0 ...

Page 427: ... to the following design change MOD2006 212 MD302 Alternative Stand By Instrument The information contained herein supplements or supersedes the basic Aircraft Flight Manual or the Supplement G1 as applicable detailed instructions are pro vided to allow the owner for replacing the Basic AFM Supplement G1 pages con taining information amended as per the Design Change in subject It is the owner s op...

Page 428: ...Page G16 4 Section 9 Supplements Supplement no G16 MD302 ALTERNATIVE STAND BY INSTRUMENT Ed 4 Rev 0 INTENTIONALLY LEFT BLANK ...

Page 429: ...6 5 Section 9 Supplements Supplement no G16 MD302 ALTERNATIVE STAND BY INSTRUMENT Ed 4 Rev 0 SECTION 1 GENERAL Apply following instruction See Basic AFM Section 1 Supplement G16 pages replacement instructions ...

Page 430: ...Page G16 6 Section 9 Supplements Supplement no G16 MD302 ALTERNATIVE STAND BY INSTRUMENT Ed 4 Rev 0 INTENTIONALLY LEFT BLANK ...

Page 431: ...LTERNATIVE STAND BY INSTRUMENT Ed 4 Rev 0 SECTION 2 LIMITATIONS Apply following pages replacement procedure Supplement G16 LIMITATIONS page Basic AFM Section 2 page MD2 12 REPLACES Page 2 12 of Basic AFM Section 2 Supplement G16 pages replacement instructions ...

Page 432: ...Page G16 8 Section 9 Supplements Supplement no G16 MD302 ALTERNATIVE STAND BY INSTRUMENT Ed 4 Rev 0 INTENTIONALLY LEFT BLANK ...

Page 433: ...ress psi 2 2 2 2 5 8 or 7 23 5 8 or 7 23 Fuel Q ty litres 0 4 12 OTHER INSTRUMENTS MARKINGS If MOD2006 212 is embodied markings are unchanged so refer to the basic AFM for information 1 applicable for Engines up to serial no 4924543 included and repaired engine which doesn t change the cylinder head n 3 with new one part no 413195 2 In event of cold starting operation it is permitted a maximum oil...

Page 434: ...Page G16 9 Ed 4 Rev 0 Section 2 Limitations Supplement no G16 MD302 ALTERNATIVE STAND BY INSTRUMENT EASA Approved INTENTIONALLY LEFT BLANK ...

Page 435: ...ION 3 EMERGENCY PROCEDURES Apply following pages replacement procedure Supplement G16 EMERGENCY PROCEDURES page Supplement S1 Section 3 page MD3 15 thru 16 REPLACE Page 3 15 thru 16 of Supplement S1 Section 3 MD3 30 REPLACES Page 3 30 of Supplement S1 Section 3 Supplement G16 pages replacement instructions ...

Page 436: ...Page G16 11 Section 9 Supplements Supplement no G16 MD302 ALTERNATIVE STAND BY INSTRUMENT Ed 4 Rev 0 INTENTIONALLY LEFT BLANK ...

Page 437: ...s accompanied by a message advisory alert issuing a flashing ADVISORY Softkey annunciation which once selected acknowledges the presence of the message advisory alert and displays the alert text message in the Alerts Window Refer to G950 Pilot s Guide for Tecnam P2006T P N 190 01146 00 last issue Appendix A Message Advisories list 2 10 LOSS OF AIRSPEED INFORMATION AIRSPEED FAIL RED X ON DISPLAY FI...

Page 438: ...ORMATION ATTITUDE FAIL RED X ON DISPLAY FIELD Display system is not receiving attitude information from the AHRS INSTRUCTION revert to stand by attitude indicator 2 11 LOSS OF ALTITUDE INFORMATION ALTITUDE FAIL RED X ON DISPLAY FIELD Display system is not receiving altitude input from the Air Data Computer INSTRUCTION revert to stand by altitude indicator ...

Page 439: ...ry capacity check occurs each time the unit is powered on If the battery capacity is determined to be less than 80 there will be a battery pack warning If the warning persists more than once in a short time the battery must be replaced 5 4 STATIC PORTS FAILURE In case of static ports failure the alternate static port in the cabin shown below must be activated 1 Cabin ventilation OFF hot and cold a...

Page 440: ...Page G16 12 Section 9 Supplements Supplement no G16 MD302 ALTERNATIVE STAND BY INSTRUMENT Ed 4 Rev 0 INTENTIONALLY LEFT BLANK ...

Page 441: ...VE STAND BY INSTRUMENT Ed 4 Rev 0 SECTION 4 NORMAL PROCEDURES Apply following pages replacement procedure Supplement G16 NORMAL PROCEDURES page Supplement S1 Section 4 page SMD4 15 REPLACES Page 4 15 Supplement S1 Section 4 Supplement G16 pages replacement instructions ...

Page 442: ...Page G16 14 Section 9 Supplements Supplement no G16 MD302 ALTERNATIVE STAND BY INSTRUMENT Ed 4 Rev 0 INTENTIONALLY LEFT BLANK ...

Page 443: ...UCTION Ed 4 Rev 0 MD302 system use WARNING The detailed description operation and functionalities of MD302 Stand By Attitude Module are provided on MD302 Stand By Attitude Module Pi lot s Guide document P N 9017846 rev D which is to be considered to be attached to this AFM and kept onboard the aircraft ...

Page 444: ...Page G16 15 Section 9 Supplements Supplement no G16 MD302 ALTERNATIVE STAND BY INSTRUMENT Ed 4 Rev 0 INTENTIONALLY LEFT BLANK ...

Page 445: ...16 Section 9 Supplements Supplement no G16 MD302 ALTERNATIVE STAND BY INSTRUMENT Ed 4 Rev 0 SECTION 5 PERFORMANCE Apply following instruction See Basic AFM Section 5 Supplement G16 pages replacement instructions ...

Page 446: ...Page G16 17 Section 9 Supplements Supplement no G16 MD302 ALTERNATIVE STAND BY INSTRUMENT Ed 4 Rev 0 INTENTIONALLY LEFT BLANK ...

Page 447: ... ALTERNATIVE STAND BY INSTRUMENT Ed 4 Rev 0 SECTION 6 WEIGHT AND BALANCE Apply following instruction Supplement G16 WEIGHT AND BALANCE page Basic AFM Section 6 page MD6 11 REPLACES Page 6 11 of Basic AFM Section 6 Supplement G16 pages replacement instructions ...

Page 448: ...Page G16 19 Section 9 Supplements Supplement no G16 MD302 ALTERNATIVE STAND BY INSTRUMENT Ed 4 Rev 0 INTENTIONALLY LEFT BLANK ...

Page 449: ... 1 4 B2 Garmin GNS 530W GPS WAAS COMM NAV 3 18 1 4 B3 Garmin GMA340 audio panel 0 8 1 4 B4 Garmin GMA347 audio panel 0 8 1 4 B5 Garmin SL30 VHF COMM NAV 1 3 1 4 B6 Transponder Garmin GTX328 1 9 1 4 B7 Transponder Garmin GTX330 1 5 1 4 B8 Becker BXP 6401 2 01 Mode S transponder 0 8 1 4 B9 Vor Loc GS Indicator Garmin GI106A 0 4 1 4 B10 Vor Loc GS Indicator MID Continental MD 200 306 0 4 1 44 B11 Dir...

Page 450: ...Page G16 20 Section 6 Weight and balance Supplement no G16 MD302 ALTERNATIVE STAND BY INSTRUMENT Ed 4 Rev 0 INTENTIONALLY LEFT BLANK ...

Page 451: ...ION Apply following pages replacement procedure Supplement G16 AIRFRAME AND SYSTEM DESCRIPTION page Basis AFM Supplement S1 Section 7 page MD7 29 REPLACES Page 7 29 of Basic AFM Section 7 SMD7 37 REPLACES Page 7 37 of Supplement S1 Section 7 SMD7 39 REPLACES Page 7 39 of Supplement S1 Section 7 Supplement G16 pages replacement instructions ...

Page 452: ...Page G16 22 Section 9 Supplements Supplement no G16 MD302 ALTERNATIVE STAND BY INSTRUMENT Ed 4 Rev 0 INTENTIONALLY LEFT BLANK ...

Page 453: ...n machine interface weight saving and reliability this backup instrument V 1 0 5 is installed For more details refer to MOD2006 212 WARNING All MD302 Stand by Attitude Module settings set up during the aircraft delivery or after a maintenance activity must not be modified WARNING In case of replacement of MD302 Stand by Attitude Module verify proper software load and confirm that its software vers...

Page 454: ...22 23 24 25 26 28 29 30 31 32 6 10 11 33 34 35 36 37 38 39 41 42 43 44 45 46 47 49 51 52 53 50 48 27 54 55 40 56 GARMIN G950 IFDS Instruments panel typical layout 1 2 3 4 5 7 8 9 12 13 14 15 16 17 18 19 20 21 22 23 24 25 26 57 30 31 32 6 10 11 33 34 35 36 38 39 41 42 43 44 45 46 47 49 51 52 53 50 48 27 54 55 40 56 GARMIN G950 IFDS Instruments panel layout with MD302 digital stand by instrument MOD...

Page 455: ... 39 LG control knob 40 Voltammeter Indicator 41 ADF control panel 42 Cockpit light dimmer 43 Cabin heat warm air from RH engine 44 Avionics lights dimmer 45 Cabin heat warm air from LH engine 46 LH ram air inlet 47 Trim rudder indicator 48 Switches built in lights dimmer 49 ELT Indicator 50 RH breakers panel 51 Pitch trim indicator 52 Pitot heat switch 53 A P Master switch 54 A P trim master switc...

Page 456: ...Page G16 23 Section 9 Supplements Supplement no G16 MD302 ALTERNATIVE STAND BY INSTRUMENT Ed 4 Rev 0 INTENTIONALLY LEFT BLANK ...

Page 457: ...tion 9 Supplements Supplement no G16 MD302 ALTERNATIVE STAND BY INSTRUMENT Ed 4 Rev 0 SECTION 8 GROUND HANDLING SERVICE Apply following instruction See Basic AFM Section 8 Supplement G16 pages replacement instructions ...

Page 458: ...Page G16 25 Section 9 Supplements Supplement no G16 MD302 ALTERNATIVE STAND BY INSTRUMENT Ed 4 Rev 0 INTENTIONALLY LEFT BLANK ...

Page 459: ...ment no G17 STORMSCOPE Ed 4 Rev 0 SUPPLEMENT NO G17 STORMSCOPE RECORD OF REVISIONS Rev Revised page Description of Revision Tecnam Approval EASA Approval Or Under DOA Privileges DO OoA HDO 0 First issue D Ronca C Caruso M Oliva DOA Approval ...

Page 460: ...Page G17 2 Section 9 Supplements Supplement no G17 STORMSCOPE Ed 4 Rev 0 LOEP Pages Revision Cover pages G17 1 thru 21 Rev 0 Section 1 ST1 9 Rev 0 Section 6 ST6 12 Rev 0 Section 7 ST7 46 Rev 0 ...

Page 461: ...6 216 Stormscope installation The information contained herein supplements or supersedes the basic Aircraft Flight Manual or the Supplement G1 as applicable detailed instructions are pro vided to allow the owner for replacing the Basic AFM Supplement G1 pages con taining information amended as per the Design Change in subject It is the owner s operator s responsibility to replace the mentioned pag...

Page 462: ...Page G17 4 Section 9 Supplements Supplement no G17 STORMSCOPE Ed 4 Rev 0 INTENTIONALLY LEFT BLANK ...

Page 463: ...Page G17 5 Section 9 Supplements Supplement no G17 STORMSCOPE Ed 4 Rev 0 SECTION 1 GENERAL Apply following instruction See Basic AFM Section 1 Supplement G17 pages replacement instructions ...

Page 464: ...Page G17 6 Section 9 Supplements Supplement no G17 STORMSCOPE Ed 4 Rev 0 INTENTIONALLY LEFT BLANK ...

Page 465: ...tion 1 General GENERAL FEATURES Ed 4 Rev 0 The Stormscope does neither replace a weather radar nor weather information The Stormscope is only used as an additional source of information beside approved weather information NOTE ...

Page 466: ...Page G17 7 Section 9 Supplements Supplement no G17 STORMSCOPE Ed 4 Rev 0 INTENTIONALLY LEFT BLANK ...

Page 467: ... G17 8 Section 9 Supplements Supplement no G17 STORMSCOPE Ed 4 Rev 0 SECTION 2 LIMITATIONS Apply following instruction See Basic AFM and Supplement S1 Section 2 Supplement G17 pages replacement instructions ...

Page 468: ...Page G17 9 Section 9 Supplements Supplement no G17 STORMSCOPE Ed 4 Rev 0 INTENTIONALLY LEFT BLANK ...

Page 469: ...ge G17 10 Section 9 Supplements Supplement no G17 STORMSCOPE Ed 4 Rev 0 SECTION 3 EMERGENCY PROCEDURES Apply following instruction See Supplement S1 Section 3 Supplement G17 pages replacement instructions ...

Page 470: ...Page G17 11 Section 9 Supplements Supplement no G17 STORMSCOPE Ed 4 Rev 0 INTENTIONALLY LEFT BLANK ...

Page 471: ...age G17 12 Section 9 Supplements Supplement no G17 STORMSCOPE Ed 4 Rev 0 SECTION 4 NORMAL PROCEDURES Apply following instruction See Supplement S1 Section 4 Supplement G17 pages replacement instructions ...

Page 472: ...Page G17 13 Section 9 Supplements Supplement no G17 STORMSCOPE Ed 4 Rev 0 INTENTIONALLY LEFT BLANK ...

Page 473: ...Page G17 14 Section 9 Supplements Supplement no G17 STORMSCOPE Ed 4 Rev 0 SECTION 5 PERFORMANCES Apply following instruction See Basic AFM Section 5 Supplement G17 pages replacement instructions ...

Page 474: ...Page G17 15 Section 9 Supplements Supplement no G17 STORMSCOPE Ed 4 Rev 0 INTENTIONALLY LEFT BLANK ...

Page 475: ... no G17 STORMSCOPE Ed 4 Rev 0 SECTION 6 WEIGHT AND BALANCE Apply following instruction Supplement G17 WEIGHT AND BALANCE page Basic AFM Section 6 page ST6 12 REPLACES Page 6 12 of Basic AFM Section 6 Supplement G17 pages replacement instructions ...

Page 476: ...Page G17 15 Section 9 Supplements Supplement no G17 STORMSCOPE Ed 4 Rev 0 INTENTIONALLY LEFT BLANK ...

Page 477: ...F 1 36 1 4 B25 Roll servo 0105 5 R9 1 31 0 71 B26 Pitch servo 0107 11 P4 1 31 3 55 B27 Altitude Transducer 0111 0 2 1 9 B28 Pitch Trim servo S TEC 0105 T11 1 3 2 8 B29 ELT Adams Aviation Artex ME406 0 9 0 8 B30 LH Front and rear seat GEVEN E5 01 003 T01 or E5 01 007 T01 or E5 01 009 T03 9 0 893 B31 RH Front and rear seat GEVEN E5 01 004 T01 or E5 01 008 T01 or E5 01 010 T03 9 0 226 B32 Fire exting...

Page 478: ...Page G17 16 Section 6 Weight and balance Supplement no G17 STORMSCOPE Ed 4 Rev 0 INTENTIONALLY LEFT BLANK ...

Page 479: ...COPE Ed 4 Rev 0 SECTION 7 AIRFRAME AND SYSTEMS DESCRIPTION Apply following instruction Supplement G17 AIRFRAME AND SYSTEM DESCRIPTION page Supplement S1 Section 7 page ST7 46 REPLACES Page 7 46 of Supplement S1 Section 7 Supplement G17 pages replacement instructions ...

Page 480: ...Page G17 18 Section 6 Weight and balance Supplement no G17 STORMSCOPE Ed 4 Rev 0 INTENTIONALLY LEFT BLANK ...

Page 481: ...n to the aircraft s Stormscope antenna The estimated distance from the aircraft to the discharge point is reported in NM while the bearing represents the angle between the fore and aft axis of the antenna which is in line with the longitudinal axis nose of the aircraft The WX 500 processor is installed in the right side of the baggage compartment while the NY 163 antenna is installed on the bottom...

Page 482: ...Page G17 19 Section 9 Supplements Supplement no G17 STORMSCOPE Ed 4 Rev 0 INTENTIONALLY LEFT BLANK ...

Page 483: ...ge G17 20 Section 9 Supplements Supplement no G17 STORMSCOPE Ed 4 Rev 0 SECTION 8 GROUND HANDLING SERVICE Apply following instruction See Basic AFM Section 8 Supplement G17 pages replacement instructions ...

Page 484: ...Page G17 21 Section 9 Supplements Supplement no G17 STORMSCOPE Ed 4 Rev 0 INTENTIONALLY LEFT BLANK ...

Page 485: ... RECORD OF REVISIONS Rev Revised page Description of Revision Tecnam Approval EASA Approval Or Under DOA Privileges DO OoA HDO 0 First issue D Ronca C Caruso M Oliva DOA Approval Section 9 Supplements Supplement no G18 OIL TEMPERATURE INDICATOR UPDATE Ed 4 Rev 0 ...

Page 486: ...Page G18 2 LOEP Pages Revision Cover pages G18 1 thru 22 Rev 0 Section 2 OT2 12 Rev 0 Section 4 SOT4 26 Rev 0 Section 9 Supplements Supplement no G18 OIL TEMPERATURE INDICATOR UPDATE Ed 4 Rev 0 ...

Page 487: ...perature indicator update The information contained herein supplements or supersedes the basic Aircraft Flight Manual or the Supplement G1 as applicable detailed instructions are pro vided to allow the owner for replacing the Basic AFM or the Supplement G1 pages containing information amended as per the Design Change in subject It is the owner s operator s responsibility to replace the mentioned p...

Page 488: ...Page G18 4 INTENTIONALLY LEFT BLANK Section 9 Supplements Supplement no G18 OIL TEMPERATURE INDICATOR UPDATE Ed 4 Rev 0 ...

Page 489: ... G18 5 SECTION 1 GENERAL Apply following instruction See Basic AFM Section 1 Supplement G18 pages replacement instructions Section 9 Supplements Supplement no G18 OIL TEMPERATURE INDICATOR UPDATE Ed 4 Rev 0 ...

Page 490: ...Page G18 6 INTENTIONALLY LEFT BLANK Section 9 Supplements Supplement no G18 OIL TEMPERATURE INDICATOR UPDATE Ed 4 Rev 0 ...

Page 491: ...replacement procedure Supplement G18 LIMITATIONS page Basic AFM Section 2 page OT2 12 REPLACES Page 2 12 of Basic AFM Section 2 Supplement G18 pages replacement instructions Section 9 Supplements Supplement no G18 OIL TEMPERATURE INDICATOR UPDATE Ed 4 Rev 0 ...

Page 492: ...Page G18 8 INTENTIONALLY LEFT BLANK Section 9 Supplements Supplement no G18 OIL TEMPERATURE INDICATOR UPDATE Ed 4 Rev 0 ...

Page 493: ...uel Q ty litres 0 4 12 OTHER INSTRUMENTS MARKINGS 1 applicable for Engines up to serial no 4924543 included and repaired engine which doesn t change the cylinder head n 3 with new one part no 413195 2 In event of cold starting operation it is permitted a maximum oil pressure of 7 bar for a short period 3 only applicable for fuel pump part no 893110 or 893114 4 0 indication shows the unusable fuel ...

Page 494: ...Page G18 9 INTENTIONALLY LEFT BLANK Ed 4 Rev 0 Section 2 Limitations Supplement no G18 OIL TEMPERATURE INDICATOR UPDATE ...

Page 495: ... SECTION 3 EMERGENCY PROCEDURES Apply following instruction See Basic AFM Section 3 Supplement G18 pages replacement instructions Section 9 Supplements Supplement no G18 OIL TEMPERATURE INDICATOR UPDATE Ed 4 Rev 0 ...

Page 496: ...Page G18 11 INTENTIONALLY LEFT BLANK Section 9 Supplements Supplement no G18 OIL TEMPERATURE INDICATOR UPDATE Ed 4 Rev 0 ...

Page 497: ...acement procedure Supplement G18 NORMAL PROCEDURES page Supplement S1 Section 4 page SOT4 26 REPLACES Page 4 26 of Supplement S1 Section 4 Supplement G18 pages replacement instructions Section 9 Supplements Supplement no G18 OIL TEMPERATURE INDICATOR UPDATE Ed 4 Rev 0 ...

Page 498: ...Page G18 13 INTENTIONALLY LEFT BLANK Section 9 Supplements Supplement no G18 OIL TEMPERATURE INDICATOR UPDATE Ed 4 Rev 0 ...

Page 499: ...ssed on Section 3 Para 7 4 WARNING Deselect and do not use Auto Pilot if possible icing condition area is inadvert ently entered 4 Fuel balance and crossfeed check as necessary To evaporate possibly accumulated condensation water once per flight day for approximately 5 minutes 100 C 212 F oil tem perature must be reached 3 11 TURBULENT AIR OPERATION In keeping with good operating practice used in ...

Page 500: ...Page G18 14 INTENTIONALLY LEFT BLANK Section 9 Supplements Supplement no G18 OIL TEMPERATURE INDICATOR UPDATE Ed 4 Rev 0 ...

Page 501: ...8 15 SECTION 5 PERFORMANCE Apply following instruction See Basic AFM Section 5 Supplement G18 pages replacement instructions Section 9 Supplements Supplement no G18 OIL TEMPERATURE INDICATOR UPDATE Ed 4 Rev 0 ...

Page 502: ...Page G18 16 INTENTIONALLY LEFT BLANK Section 9 Supplements Supplement no G18 OIL TEMPERATURE INDICATOR UPDATE Ed 4 Rev 0 ...

Page 503: ...7 SECTION 6 WEIGHT AND BALANCE Apply following instruction See Basic AFM Section 6 Supplement G18 pages replacement instructions Section 9 Supplements Supplement no G18 OIL TEMPERATURE INDICATOR UPDATE Ed 4 Rev 0 ...

Page 504: ...Page G18 18 INTENTIONALLY LEFT BLANK Section 6 Weight and balance Supplement no G18 OIL TEMPERATURE INDICATOR UPDATE Ed 4 Rev 0 ...

Page 505: ...ON 7 AIRFRAME AND SYSTEMS DESCRIPTION Apply following instruction See Basic AFM Section 7 Supplement G18 pages replacement instructions Section 9 Supplements Supplement no G18 OIL TEMPERATURE INDICATOR UPDATE Ed 4 Rev 0 ...

Page 506: ...Page G18 20 INTENTIONALLY LEFT BLANK Section 9 Supplements Supplement no G18 OIL TEMPERATURE INDICATOR UPDATE Ed 4 Rev 0 ...

Page 507: ...ECTION 8 GROUND HANDLING SERVICE Apply following instruction See Basic AFM Section 8 Supplement G18 pages replacement instructions Section 9 Supplements Supplement no G18 OIL TEMPERATURE INDICATOR UPDATE Ed 4 Rev 0 ...

Page 508: ...Page G18 22 INTENTIONALLY LEFT BLANK Section 9 Supplements Supplement no G18 OIL TEMPERATURE INDICATOR UPDATE Ed 4 Rev 0 ...

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Summary of Contents for P2006T

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Tecnam P2006T, Aircraft Flight Manual

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Summary of Contents for P2006T

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