Page 1 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 herein. Costruzioni Aeronautiche TECNAM srl Via Maiorise CAPUA (CE) – Italy Tel. +39 (0) 823.62.01.34 WEB: www.tecnam.com...
Page 2 Page 0 - 2 SECTION 0 INDEX RECORD OF REVISIONS ..............3 LIST OF EFFECTIVE PAGES ..............7 FOREWORD ..................10 SECTIONS LIST .................. 11 Edition - Rev. 0 Aircraft Flight Manual INDEX...
Page 3 Page 0 - 3 1. RECORD OF REVISIONS Any revision to the present Manual, except actual weighing data, is recorded: a Record of Revisions is provided at the front of this manual and the operator is ad- vised to make sure that the record is kept up-to-date. The Manual issue is identified by Edition and Revision codes reported on each page, lower right side.
Page 4 Page 0 - 4 EASA Approval or Tecnam Approval Revised Description of Under DOA page Revision Privileges First issue D. Ronca M. Oliva M. Oliva Amend ROR D. Ronca M. Oliva M. Oliva Amend LOEP D. Ronca M. Oliva M. Oliva...
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Page 7 Page 0 - 7 2. LIST OF EFFECTIVE PAGES The List of Effective Pages (LOEP), applicable to manuals of every operator, lists all the basic AFM pages: each manual could contain either basic pages or one variant of these pages when the pages of some Supplements are embodied. Should the Supplements be embodied in accordance with approved instructions, make reference to the LOEP addressed on the Supplements themselves.
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Page 10 Page 0 - 10 3. FOREWORD Tecnam P2006T is a twin-engine four-seat aircraft with high cantilevered wing and tri- cycle retractable landing gear. Section 1 supplies general 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.
Page 11 Page 0 - 11 4. SECTIONS LIST Section 1 (a non-approved Chapter) General Section 2 - EASA Approved Chapter Limitations Section 3 (a non-approved Chapter) Emergency Procedures Section 4 (a non-approved Chapter) Normal Procedures Section 5 (a non-approved Chapter) Performances Section 6 (a non-approved Chapter) Weight and Balance Airframe and Systems description Section 7 (a non-approved Chapter)
Page 12 Page 1 - 1 SECTION 1 - GENERAL INDEX 1. Introduction .................. 3 2. Three-view and dimensions ............4 3. Control Surfaces Travel Limits ............ 6 4. Engine ................... 6 5. Propeller ..................6 6. Governor ..................7 7. Fuel ....................7 8.
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Page 14 NTRODUCTION The Aircraft Flight Manual has been implemented to provide the owners with in- formation for a safe and efficient use of the aircraft TECNAM P2006T. Warning – Caution – Note Following definitions apply to warnings, cautions and notes used in the Aircraft Flight Manual.
Page 15 Page 1 - 4 2. T HREE VIEW AND DIMENSIONS Figure 1 – General views Edition, Rev 0 Section 1 – General THREE-VIEW AND DIMENSIONS...
Page 16 Page 1 - 5 Dimensions Overall dimensions Wingspan 11,4 m 37,4 ft Length 8,7 m 28,5 ft Overall height 2,58 m 8,46 ft Wing Wing surface 14,76 m 158,9 ft Mean Geometric Chord 1,295 m 4,25 ft Dihedral 1° Aspect ratio 8,80 Main Landing Gear Track...
Page 17 Page 1 - 6 3. C ONTROL URFACES RAVEL IMITS Ailerons Up 20° Down 17 ° ( 2°) Stabilator (refer to Trailing Edge) Up 4° Down 15° ( 2°) Stabilator trim tab (refer to Trailing Edge) Up 2°; Down 19° ( 2°) Rudder RH 26°...
Page 18 Page 1 - 7 OVERNOR Manufacturer Mt Propeller Model P-875-12 Type Hydraulic 7. F Approved fuel: MOGAS ASTM D4814 MOGAS EN 228 Super/Super plus (min. RON 95) AVGAS 100LL (ASTM D910) (see also Section 2) Fuel tanks Two integrated tanks (one in each wing) fitted with drainable sump and drain valve Capacity of each wing tan...
Page 19 Page 1 - 8 9. C OOLING Cooling system Ram-air cooled cylinders, liquid cooled cylinder heads (closed and pressurized circuit) Coolant liquid Certified for Water/Coolant mixture. Make reference to “Rotax Operators Manual” – last issue Overall circuit capacity 1410 cm WEIGHTS See Section 2.
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Page 21 Page 1 - 10 13. A CRONYMS AND TERMINOLOGY KCAS Calibrated Airspeed is the indicated airspeed expressed in knots, corrected taking into account the errors related to the instrument itself and its installation. KIAS Indicated Airspeed is the speed shown on the airspeed indicator and it is expressed in knots.
Page 22: Meteorological Terminology
Page 1 - 11 Meteorological terminology International Standard Atmosphere: is the air atmospheric standard condition at sea level, at 15°C (59°F) and at 1013.25hPa (29.92inHg). Official atmospheric pressure at airport level: it indicates the air- craft absolute altitude with respect to the official airport level. 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.
Page 23 Page 1 - 12 Aircraft performance and flight planning terminology is the velocity of the crosswind component Crosswind Velocity for the which adequate control of the air- plane during takeoff and landing is assured. is the fuel available for flight planning. Usable fuel is the quantity of fuel that cannot be safely Unusable fuel...
Page 24: Weight And Balance Terminology
Maximum Takeoff Weight the takeoff. is the maximum weight approved for the Maximum Landing Weight landing touchdown (for P2006T it is equiv- alent to the Maximum Takeoff Weight). Edition, Rev 0 Section 1 – General ACRONYMS AND TERMINOLOGYACRONYMS AND...
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Page 26: Unit Conversion Chart
Page 1 - 15 14. U NIT CONVERSION CHART  MOLTIPLYING YIELDS EMPERATURE Fahrenheit [°F] Celsius [°C]     [°F] Celsius [°C]   Fahrenheit       ORCES Kilograms [kg] 2.205 Pounds [lbs] Pounds [lbs] 0.4536 Kilograms...
Page 27 Page 1 - 16 15. L / US ITRES GALLONS CONVERSION CHART Litres US Gallons US Gallons Litres 11.4 15.1 22.7 30.3 37.9 10.6 45.4 11.9 53.0 13.2 60.6 15.9 68.1 18.5 75.7 21.1 83.3 23.8 90.9 26.4 98.4 29.1 106.0 31.7 113.6...
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Page 30 Page 2 - 1 SECTION 2 – LIMITATIONS INDEX Introduction ....................... 3 Speed limitations ....................5 Airspeed indicator markings ................7 Powerplant limitations ..................9 Lubricant ......................10 Coolant liquid ....................10 Propeller ......................10 Governor ......................10 Maximum operating altitude ................11 Ambient temperature ..................
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Page 32 Page 2 - 3 1. I NTRODUCTION 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. EASA Approved Edition, Rev. 0 Section 2 –...
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Page 34 GARMIN G950 IFDS – Increased MTOW (1230 kg) Page SW2-5 PEED LIMITATIONS The following table addresses the airspeed limitations and their operational signif- icance: SPEED KIAS KCAS REMARKS Never exceed speed Do not exceed this speed in V NE any operation. Maximum Structural Cruising Do not exceed this speed V NO...
Page 35 GARMIN G950 IFDS – Increased MTOW (1230 kg) Page SW2-6 INTENTIONALLY LEFT BLANK EASA Approved Edition, Rev. 0 Section 2 – Limitations...
Page 36 GARMIN G950 IFDS – Increased MTOW (1230 kg) Page SW2-7 IRSPEED INDICATOR MARKINGS Airspeed indicator markings and their colour code are explained in the following table. MARKING KIAS EXPLANATION White band Lower limit is V , upper limit is the maxi- 54-93 mum allowable speed with flaps extended in FULL position.
Page 37 GARMIN G950 IFDS – Increased MTOW (1230 kg) Page SW2-8 INTENTIONALLY LEFT BLANK EASA Approved Edition, Rev. 0 Section 2 – Limitations...
Page 38 Page 2 - 9 4. P OWERPLANT LIMITATIONS Following table reports the operating limitations for both engines installed: : Bombardier Rotax GmbH. NGINE MANUFACTURER : 912 S3 NGINE MODEL AXIMUM POWER Max Power Max rpm. Time max. kW (hp) Prop. rpm (engine) (minutes) 73.5 (98.6) 2388 (5800)
Page 39 Page 2 - 10 Fuel pressure: Minimum 2.2 psi (0.15 Bar) Maximum 5.8 psi (0.40 Bar) or 7.26 psi* (0.5 Bar) *only applicable for fuel pump part no. 893110 or 893114 5. L UBRICANT Use only oil with API classification “SG” or higher. For additional info, refer to “Rotax Operators Manual”...
Page 40 Page 2 - 11 9. M AXIMUM OPERATING ALTITUDE Maximum operating altitude is 14000 ft (4260 m) MSL. At altitudes above 12500 ft (3810 m) up to and including 14000 ft (4260 m), flight must be limited to 30 minutes, unless the required minimum flight crew is provided with and uses supplemental oxygen for that part of CAUTION the flight at those altitudes that is of more than 30 minutes duration.
Page 41 Page 2 - 12 11. P OWERPLANT INSTRUMENTS MARKINGS Powerplant instrument markings and their colour code significance are shown be- low: RED LINE GREEN ARC YELLOW ARC RED LINE Minimum Normal Caution Maximum NSTRUMENT limit operating limit Propeller ---- 580 - 2265 2265 - 2388 2388 Oil temp.
Page 42 GARMIN G950 IFDS - Supplement Page S2 - 13 13 Warning/caution alerts and safe operating annuncia- tions Following table addresses the warning and caution alerts and safe operating annun- ciations shown (unless differently specified) on the Annunciation Window: Warning alert (RED) Cause L BUS VOLT HIGH LH electric system overvoltage...
Page 43 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 GARMIN G950 IFDS – Increased MTOW (1230 kg) Page SW2-15 EIGHTS 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 Refer to Para. 21.4 of this AFM Section for baggage loading limitations. EASA Approved Edition, Rev.
Page 45 GARMIN G950 IFDS – Increased MTOW (1230 kg) Page SW2-16 INTENTIONALLY LEFT BLANK Edition, Rev. 0 Section 2 – Limitations...
Page 46 Page 2 - 17 15. C ENTER OF GRAVITY RANGE Datum Vertical plane tangent to the wing leading edge (the 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...
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Page 48 Page 2 - 19 16. A PPROVED MANEUVERS The aircraft is certified in normal category in accordance with EASA CS-23 regula- tion. Non aerobatic operations include: Any manoeuvre pertaining to “normal” flight  Stalls (except whip stalls)  Lazy eights ...
Page 49 Page 2 - 20 19. F LIGHT CONDITIONS The aircraft can be equipped for following flight operations (make reference to Pa- ra. 22 concerning the equipment list required on board to allow them):  VFR Day and Night  IFR Day and Night including IMC Flight in expected and/or known icing conditions, in proximity of storms or in turbulence is forbidden.
Page 50 Page SW2-21 21. L IMITATIONS PLACARDS Hereinafter the placards, related to the operating limitations and installed on P2006T, are reported. 21.1. S PEED 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) Edition, Rev.
Page 51 GARMIN G950 IFDS – Increased MTOW (1230 kg) Page SW2-22 21.2. O PERATING LIMITATIONS On the instrument panel, it is placed the following placard reminding the 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.
Page 52 Page 2 - 23 21.3. NFLIGHT ENGINE RESTART The inflight engine restart procedure is reported on a placard (shown below) in- stalled on the central console. 21.4. AGGAGE COMPARTMENT CAPACITY The placard shown below, and installed on the baggage compartment (vertical pan- el), concerns the baggage compartment load limitations herein reported: ...
Page 53 Page 2 - 24 21.5. NGINE OIL LEVEL On the engine nacelle, in 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.
Page 54 Page 2 - 25 21.7. ANDING YDRAULIC 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.
Page 55 Page 2 - 26 21.8. EAR 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. EASA Approved Edition, Rev. 0 Section 2 –...
Page 56 Page 2 - 27 21.9. THER PLACARDS Description Placard Place Smoking ban Instruments panel, right side Ditching emer- Ditching emergency gency exit: exit handle: internal opening side structions Ditching emer- Ditching emergency gency exit: exit handle: external opening side structions Door locking Main door and emer-...
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Page 58 GARMIN G950 IFDS - Supplement Page S2 - 29 22. K INDS OF PERATIONS QUIPMENT This paragraph reports the KOEL table, concerning the equipment list required on board under CS-23 regulations to allow flight operations in VFR Day, VFR Night, IFR Day and IFR Night conditions.
Page 59 GARMIN G950 IFDS - Supplement Page S2 - 30 Equipment VFR Day VFR Night IFR Day IFR Night ● ● ● ● Magnetic compass ● ● ● ● GDU 1040 - Display Unit (2) ● ● ● ● GIA 63W - Integrated Avionics Unit (2) ●...
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Page 62 Garmin G950 IFDS -Supplement Page S3 - 1 SECTION 3 – EMERGENCY PROCEDURES INDEX INTRODUCTION ....................3 1.1. Engine failure during takeoff run ................ 3 Airplane alerts ....................6 2.1 Single alternator failure / overvoltage..............7 2.2 Both alternators failure ..................8 2.3 Both alternators overvoltage ................
Page 63 Garmin G950 IFDS -Supplement Page S3 - 2 LANDING GEAR SYSTEM FAILURES..............42 7.1 Emergency landing gear extension ..............42 7.2 Complete Gear up or nose gear up landing ............43 7.3 Partial Main LG extension ................45 7.4 Failed retraction ....................47 7.5 Unintentional landing gear extension ..............
Page 64 Additionally operating the aircraft, the pilot should become thoroughly familiar with the Garmin G950 Pilot’s Guide for Tecnam P2006T (P/N 190-01146-XX) – last issue - and, in particular, with the present AFM Section. Garmin G950 Pilot’s Guide for Tecnam P2006T (P/N 190- 01146-XX) –...
Page 65 Garmin G950 IFDS -Supplement Page S3 - 4 Garmin G950 has a very high degree of functional integrity. However, the pilot must recognize that providing monitoring and/or self-test ca- pability for all conceivable system failures is not practical. Although unlikely, it may be possible for erroneous operation to occur without a WARNING fault indication shown by the G950.
Page 66 Garmin G950 IFDS -Supplement Page S3 - 5 INTENTIONALLY LEFT BLANK Edition, Rev. 0 Section 3 – Emergency procedures INTRODUCTION...
Page 67 Garmin G950 IFDS -Supplement Page S3 - 6 2. A IRPLANE ALERTS Annunciation Window, located to the right of the Altimeter and Vertical Speed Indicator, supplies 16 alerts for warnings and cautions along with safe operating annunciations. The colours are as follows: to indicate that pertinent device is turned ON GREEN: to indicate no-hazard situations which have to be considered and...
Page 68 Garmin G950 IFDS -Supplement Page S3 - 7 INGLE ALTERNATOR FAILURE OVERVOLTAGE Annunciation window Alert window L ALT FAIL Lh Alternator R ALT FAIL Rh Alternator 1. FIELD LH (or RH) 2. FIELD LH (or RH) If the LH (or RH) ALT caution stays displayed 3.
Page 69 Garmin G950 IFDS -Supplement Page S3 - 8 OTH ALTERNATORS FAILURE Annunciation window Alert window L ALT FAIL Lh Alternator R ALT FAIL Rh Alternator In event of both L and R ALT FAIL caution alerts displayed: 1. FIELD LH and RH BOTH OFF 2.
Page 70 Garmin G950 IFDS -Supplement Page S3 - 9 OTH ALTERNATORS OVERVOLTAGE Annunciation window Alert window L BUS VOLT HIGH Lh overvoltage R BUS VOLT HIGH Rh overvoltage In event of both L and R BUS VOLT HIGH warning alerts displayed: 1.
Page 71 Garmin G950 IFDS -Supplement Page S3 - 10 AILED DOOR CLOSURE Annunciation window Alert window PILOT DR OPEN Main door open REAR DR OPEN Rear door open In case of door opening / unlocking, related PILOT or REAR DR OPEN alert is displayed. In this case, apply following procedure: ON THE GROUND 1.
Page 72 Garmin G950 IFDS -Supplement Page S3 - 11 ITOT HEATING SYSTEM FAILURE Annunciation window Alert window PITOT HEAT ON Pitot heat PITOT HEAT Pitot heat When the Pitot Heating system is activated, the green PITOT HEAT advisory light is turned ON. If the amber PITOT HEAT caution light turns OFF, then the Pitot Heating system is functioning properly.
Page 73 Garmin G950 IFDS -Supplement Page S3 - 12 OOLANT LIQUID LOW LEVEL Annunciation window Alert window L COOLANT LOW Lh Low Coolant R COOLANT LOW Rh Low Coolant When the engine coolant liquid level goes under the lower limit, the related L or R COOLANT LOW warning alert is displayed.
Page 74 Garmin G950 IFDS -Supplement Page S3 - 13 UMP FAILURE Annunciation window Alert window GEAR PUMP ON Gear powered The GEAR PUMP ON caution light turns ON when the landing gear hydraulic pump is electrically supplied. After the landing gear retraction, if 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.
Page 75 Garmin G950 IFDS -Supplement Page S3 - 14 NGINE FIRE Annunciation window Alert window LH ENGINE FIRE Left engine fire detected 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.
Page 76 NOTE 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.
Page 77 Garmin G950 IFDS -Supplement Page S3 - 16 2.10 L OSS OF ATTITUDE INFORMATION ATTITUDE FAIL ON DISPLAY FIELD Display system is not receiving attitude information from the AHRS. INSTRUCTION: revert to standby analogical attitude indicator 2.11 L OSS OF ALTITUDE INFORMATION ALTITUDE FAIL ON DISPLAY FIELD Display system is not receiving altitude input...
Page 78 Garmin G950 IFDS -Supplement Page S3 - 17 2.12 OSS OF VERTICAL SPEED INFORMATION VERT SPEED FAIL 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 OSS OF HEADING INFORMATION ON DISPLAY FIELD...
Page 79 Garmin G950 IFDS -Supplement Page S3 - 18 INTENTIONALLY LEFT BLANK Edition, Rev. 0 Section 3 – Emergency procedures G950 SYSTEM FAILURES...
Page 80 Garmin G950 IFDS -Supplement Page S3 - 19 2.14 ISPLAY FAILURE In the event of a display failure, the G950 System automatically switches to re- versionary (backup) mode. In reversionary mode, all important flight infor- mation is presented on the remaining display in the same format as in normal operating mode.
Page 81 Garmin G950 IFDS -Supplement Page S3 - 20 INTENTIONALLY LEFT BLANK Edition, Rev. 0 Section 3 – Emergency procedures G950 SYSTEM FAILURES...
Page 82 Garmin G950 IFDS -Supplement Page S3 - 21 3. ENGINE SECURING Following procedure is applicable to shut-down one engine in flight: Throttle Lever IDLE Ignition BOTH OFF Propeller Lever FEATHER Fuel Selector Electrical fuel pump After securing engine(s), after analysing situation, refer immediately to following procedures: ENGINE FAILURE IN FLIGHT: see Para.
Page 83 Garmin G950 IFDS -Supplement Page S3 - 22 INTENTIONALLY LEFT BLANK Edition, Rev. 0 Section 3 – Emergency procedures...
Page 84 Garmin G950 IFDS -Supplement Page S3 - 23 4. POWERPLANT EMERGENCIES ROPELLER OVERSPEEDING The aircraft is fitted with propeller/governor set by MT-Propeller such a way that the maximum propeller rpm exceedance is prevented. In case of propeller over- speeding in flight, apply following procedure: Throttle Lever REDUCE power to minimum practical Propeller Lever...
Page 85 Garmin G950 IFDS -Supplement Page S3 - 24 LIMIT EXCEEDANCE If CHT/CT exceeds its limit, 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.
Page 86 Garmin G950 IFDS -Supplement Page S3 - 25 IL TEMPERATURE LIMIT EXCEEDANCE If oil temperature exceeds maximum limit (130°C): 1. OIL PRESS CHECK If oil pressure is within limits 2. Affected engine Reduce power setting to minimum applicable 3. Affected engine Keep propeller speed higher than 2000 RPM If oil pressure does not decrease 4.
Page 87 Garmin G950 IFDS -Supplement Page S3 - 26 IL PRESSURE LIMITS EXCEEDANCE If oil pressure exceeds its lower or upper limit (0.8 – 7 bar), apply following pro- cedure: Excessive oil pressure drop leads to a high pitch propeller con- figuration with consequent propeller feathering and engine WARNING stopping.
Page 88 Garmin G950 IFDS -Supplement Page S3 - 27 OW FUEL PRESSURE If fuel pressure decreases below the lower 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 Land as soon as possible.
Page 89 Garmin G950 IFDS -Supplement Page S3 - 28 INTENTIONALLY LEFT BLANK Edition, Rev. 0 Section 3 – Emergency procedures...
Page 90 Garmin G950 IFDS -Supplement Page S3 - 29 5. O THER EMERGENCIES MERGENCY DESCENT Descent with airspeed at VLE, idle power and gear down will ° provide high descent rates and pitch attitudes up to -15 Anticipate altitude capture and return to level flight during CAUTION emergency descent in order to assure a safe and smooth recov- ery from maneuver.
Page 91 Garmin G950 IFDS -Supplement Page S3 - 30 TATIC PORTS FAILURE In case of static ports failure, the alternate static port in the cabin (shown below) must be activated. Cabin ventilation OFF (hot and cold air) ALTERNATE STATIC PORT VALVE OPEN Continue the mission Edition, Rev.
Page 92 Garmin G950 IFDS -Supplement Page S3 - 31 5.4 U NINTENTIONAL FLIGHT INTO ICING CONDITIONS Carburettor heat BOTH ON Pitot heat Fly as soon as practical toward a zone clear of visible moisture, precipita- tion and with higher temperature, changing altitude and/or direction. Control surfaces Move continuously to avoid locking Propellers rpm...
Page 93 Garmin G950 IFDS -Supplement Page S3 - 32 5.5 C ARBURETTOR ICING DURING TAKEOFF The carburettor icing in “full throttle” mode is unlikely. Take off in known or suspected icing formation is forbidden; in order to dispose of full engine take off power, take-off must be performed with carburettor heating OFF.
Page 94 Garmin G950 IFDS -Supplement Page S3 - 33 LAPS CONTROL FAILURE DURING TAKEOFF Flap UP take off, requires a T/O distance (50 ft height obstacle distance) increased by about 20%. CAUTION Airspeed Keep below 93 KIAS Land as soon as practical DURING APPROACH/LANDING If the flaps control fails, consider the higher stall speed (see Sec- tion 5, Para.
Page 95 Garmin G950 IFDS -Supplement Page S3 - 34 6 ONE ENGINE INOPERATIVE PROCEDURES The ineffectiveness of one engine results in asymmetric traction which tends to yaw and bank the aircraft towards the inoperative engine. In this condition it is essential to maintain the direction of flight compen- sating the lower traction and counteracting the yawing effects by mean of rudder pedals.
Page 96 Garmin G950 IFDS -Supplement Page S3 - 35 HARACTERISTIC AIRSPEEDS WITH ONE ENGINE INOPERATIVE In case of one engine inoperative condition (OEI), pilot shall take into account the airspeeds shown below: Speed Conditions (KIAS) Minimum aircraft control speed with one en- gine inoperative and flaps set to T.O.
Page 97 Garmin G950 IFDS -Supplement Page S3 - 36 6.2 I NFLIGHT ENGINE RESTART After: mechanical engine seizure; fire; major propeller damage WARNING engine restart is not recommended. Carburettor heat ON if required Electrical fuel pump Fuel quantity indicator CHECK Fuel Selector CHECK (Crossfeed if required) FIELD Ignition...
Page 98 Garmin G950 IFDS -Supplement Page S3 - 37 NGINE FAILURE DURING TAKEOFF RUN BEFORE ROTATION: ABORT TAKE OFF Throttle Lever BOTH IDLE Rudder Keep heading control Brakes As required When safely stopped: Failed Engine Ignition BOTH OFF Failed Engine Field Failed Engine Electrical fuel pump IF THE DECISION IS TAKEN TO CONTINUE THE TAKEOFF: A take-off abort should always be preferred if a safe stop can be per-...
Page 99 Garmin G950 IFDS -Supplement Page S3 - 38 At safe altitude Inoperative engine Confirm and SECURE Operative engine Electrical fuel pump Check ON Operating engine Check engine instruments Operating engine Fuel Selector Check correct feeding (crossfeed if needed) If engine restart is recommended: Apply INFLIGHT ENGINE RESTART procedure see Para 6.2 If engine restart is unsuccessful or it is not recommended:...
Page 100 Garmin G950 IFDS -Supplement Page S3 - 39 NGINE FAILURE DURING CLIMB Autopilot Heading Keep control using rudder and ailerons Attitude Reduce as appropriate to keep airspeed over 62 KIAS Operating engine Throttle Lever FULL THROTTLE Operating engine Propeller Lever FULL FORWARD Operative engine Electrical fuel pump Check ON...
Page 101 Garmin G950 IFDS -Supplement Page S3 - 40 NGINE FAILURE IN FLIGHT Autopilot Heading Keep control using rudder and ailerons Attitude Adjust as appropriate to keep airspeed over 62 KIAS Operating engine Monitor engine instruments Operative engine Electrical fuel pump Check ON Operating engine Fuel Selector Check correct feeding...
Page 102 Garmin G950 IFDS -Supplement Page S3 - 41 NE ENGINE INOPERATIVE LANDING Thoroughly evaluate residual Single Engine Go-Around capabilities and expected climb gradient should a Missed Approach / balked land- ing be executed. Refer to Section 5, Para. Single engine go around/Balked land- WARNING ing/climb and Para.
Page 103 Garmin G950 IFDS -Supplement Page S3 - 42 7 LANDING GEAR SYSTEM FAILURES MERGENCY LANDING GEAR EXTENSION Landing gear extension failure is identified by means of the green NOTE lights not illuminated: relevant gear leg may not be fully extended and/or locked.
Page 104 Garmin G950 IFDS -Supplement Page S3 - 43 OMPLETE EAR UP OR NOSE GEAR UP LANDING The following procedure applies if Nose Landing Gear is not extended and locked even after emergency extension procedure. CAUTION A Nose Landing Gear up leg not down and locked might lead to a hazardous situation, especially on uneven runways.
Page 105 Garmin G950 IFDS -Supplement Page S3 - 44 Aircraft Evacuation carry out if necessary 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- WARNING rection.
Page 106 Garmin G950 IFDS -Supplement Page S3 - 45 ARTIAL EXTENSION The following procedure applies if one or both Main Landing Gear legs are not completely extended and locked even after emergency ex- tension procedure. CAUTION A partial gear landing (RH and/or LH leg not down and locked) might turn into a hazardous situation, especially on uneven runways.
Page 107 Garmin G950 IFDS -Supplement Page S3 - 46 After aircraft stops: FIELD LH and RH BOTH OFF MASTER SWITCH Master switch to OFF impairs radio communication and outside air- craft lighting. CAUTION Aircraft Evacuation carry out if necessary 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.
Page 108 Garmin G950 IFDS -Supplement Page S3 - 47 AILED RETRACTION Airspeed Keep below applicable VLO/VLE Landing gear control lever DOWN A Landing Gear lever recycle (further retraction attempt) may result in a final partial Landing Gear Extension, which may then compromise safe landing aircraft capability. WARNING Landing Gear lights Check...
Page 109 Garmin G950 IFDS -Supplement Page S3 - 48 INTENTIONALLY LEFT BLANK Edition, Rev. 0 Section 3 – Emergency procedures...
Page 110 Garmin G950 IFDS -Supplement Page S3 - 49 8 SMOKE AND FIRE OCCURRENCE NGINE FIRE ON THE GROUND Fuel Selectors BOTH OFF Ignitions ALL OFF Electrical fuel pumps BOTH OFF Cabin heat and defrost MASTER SWITCH Parking Brake ENGAGED Aircraft Evacuation carry out immediately Consider use of ditching emergency exit to escape in case pilot or passenger doors are blocked, watch for engine hot parts,...
Page 111 Garmin G950 IFDS -Supplement Page S3 - 50 NGINE FIRE DURING TAKEOFF RUN BEFORE ROTATION: ABORT TAKE OFF Throttle Lever BOTH IDLE Rudder Keep heading control Brakes As required With aircraft under control Fuel Selector BOTH OFF Ignitions ALL OFF Electrical fuel pump BOTH OFF Cabin heat and defrost...
Page 112 Garmin G950 IFDS -Supplement Page S3 - 51 At safe altitude Cabin heat and defrost BOTH OFF Fire affected engine Fuel Selector Confirm and OFF Fire affected engine Ignitions Confirm and BOTH OFF Fire affected engine Electrical fuel pump Confirm and OFF Fire affected engine FIELD Land as soon as possible applying one engine inoperative landing procedure.
Page 113 Garmin G950 IFDS -Supplement Page S3 - 52 NGINE FIRE IN FLIGHT Cabin heat and defrost BOTH OFF Autopilot Fire affected engine Fuel Selector Confirm and OFF Fire affected engine Ignition Confirm and BOTH OFF Fire affected engine Throttle Lever Confirm and FULL FORWARD Fire affected engine Propeller Lever Confirm and FEATHER...
Page 114 Garmin G950 IFDS -Supplement Page S3 - 53 LECTRICAL SMOKE IN CABIN DURING FLIGHT Cabin ventilation OPEN Emergency light Standby attitude indicator switch Gain VMC conditions as soon as possible In case of cockpit fire: Fire extinguisher use toward base of flames A tripped circuit breaker should not be reset.
Page 115 Garmin G950 IFDS -Supplement Page S3 - 54 When on ground: Aircraft Evacuation carry out as necessary 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.
Page 116 Garmin G950 IFDS -Supplement Page S3 - 55 9 UNINTENTIONAL SPIN RECOVERY Spin behaviour has not been demonstrated since certification process does not required it for this aircraft category. Intentional spin is forbidden. Stall with one engine inoperative is forbidden. WARNING Should an unintentional spin occur, the classic recovery ma- noeuvre is deemed as being the best action to undertake:...
Page 117: Landing Emergencies
Garmin G950 IFDS -Supplement Page S3 - 56 LANDING EMERGENCIES 10.1 L ANDING WITHOUT ENGINE POWER In case of double engine failure both propellers should be feathered to achieve maximum efficiency. Best glide speed is attained with flap UP and equals V for current aircraft mass and air density altitude.
Page 118 Garmin G950 IFDS -Supplement Page S3 - 57 Before touch down Fuel Selector BOTH OFF Electrical fuel pump BOTH OFF Ignitions ALL OFF MASTER SWITCH When stopped Aircraft Evacuation carry out if necessary 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.
Page 119 Garmin G950 IFDS -Supplement Page S3 - 58 10.2 ANDING WITH OSE LANDING GEAR TIRE DEFLATED If possible, as a nose landing gear flat tire condition is known, coor- dinate fire brigade intervention along runway and report number of persons on board and remaining fuel type and quantity. WARNING If Nose Landing Gear flat tire is confirmed: Preparation...
Page 120 Garmin G950 IFDS -Supplement Page S3 - 59 10.3 ANDING WITH A KNOWN MAIN LANDING GEAR TIRE DEFLATED An asymmetrical landing gear tire condition (RH and/or LH tires de- flated) might turn into a hazardous situation, especially on uneven runways. WARNING If possible, as a landing gear tires condition is known, coordinate fire brigade intervention along runway and report number of persons on...
Page 121 Garmin G950 IFDS -Supplement Page S3 - 60 10.4 ANDING WITHOUT BRAKES If possible, select an airport with suitable runway length. Otherwise, evaluate the possibility to perform a gear up landing (re- fer to procedure reported on Para. 7.2). In the latter case consider the CAUTION increasing hazard of an uneven pavement.
Page 122 Garmin G950 IFDS -Supplement Page S3 - 61 11 AIRCRAFT EVACUATION Leave the aircraft when engines are fully stopped. Watch for engine hot parts and fuel, hydraulic fluid or oil spills when using fuselage doors. If fuselage doors are unserviceable escape through the ditch- ing emergency exit WARNING In case of engine fire escape from opposite or upwind aircraft side.
Page 123 Garmin G950 IFDS -Supplement Page S3 - 62 12 DITCHING Contact with water shall happen with aircraft longitudinal axis and direction of motion parallel to the wave at the minimum possible speed. Keep the nose up as long as possible. Once in the water, the aircraft shall be evacuated through the ditch- ing emergency exit, if available put life vest on and set dinghy out WARNING...
Page 124 Garmin G950 IFDS -Supplement Page S3 - 63 INTENTIONALLY LEFT BLANK Edition, Rev. 0 Section 3 – Emergency procedures DITCHING...
Page 125 Garmin G950 IFDS - Supplement Page S4 - 1 SECTION 4 – NORMAL PROCEDURES INDEX INTRODUCTION ....................3 1.1. Normal ops general recommendations .............. 3 AIRSPEEDS ......................7 1.2. Normal operations ....................7 1.3. Single engine training ..................8 Normal procedures checklist ................9 3.1 Recommendations for cold weather operations ..........
Page 126 Garmin G950 IFDS - Supplement Page S4 - 2 INTENTIONALLY LEFT BLANK Edition, Rev. 0 Section 4 – Normal procedures...
Page 127 ORMAL OPS GENERAL RECOMMENDATIONS The following points should be always brought to attention to pilot/instructor/operator when operating a Tecnam aircraft equipped with variable pitch propeller: 1. Propeller governor ground check: during the ground check of governor, as prescribed by the propeller/governor manufacturer, the drop should not be above 600/650 prop RPM. The aim of this ground check is to confirm governor efficiency, not the complete feathering func- tion.
Page 128 Useful guideline chart that could be used for best 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.
Page 129 G950 system use For safety reasons, G950 operational procedures must be learned on the ground. Document Garmin G950 Pilot’s Guide for Tecnam P2006T (P/N 190-01146- XX) – last issue, reports detailed instructions to operate the system in subject. Make always reference to the above mentioned document.
Page 130 NOTE ness of the data. Reference“Garmin G950 Pilot’s Guide for the Tec- nam P2006T” (P/N 190-01146-XX), last issue, Appendix B concern- ing SD card use and databases. Use of polarized eyewear may cause the flight displays to appear dim NOTE or blank.
Page 131 Garmin G950 IFDS - Supplement Page S4 - 7 AIRSPEEDS 2.1. N ORMAL OPERATIONS The following airspeeds are those which are significant for normal operations, with reference to both MTOW: 1180 kg and 1230 kg (if Supplement G10 - In- creased MTOW @1230 KG - is applicable).
Page 132 Garmin G950 IFDS - Supplement Page S4 - 8 2.2. S INGLE ENGINE TRAINING is a speed selected as training aid for pilots in the handling of multi-engine aircraft. It is the minimum speed for intentionally rendering on engine inoperative in flight. This minimum speed provides the margin the manufacturer recommends for us when inten- tionally performing engine inoperative maneuvers during training.
Page 133 Garmin G950 IFDS - Supplement Page S4 - 9 ORMAL PROCEDURES CHECKLIST 3.1 R ECOMMENDATIONS FOR COLD WEATHER OPERATIONS Engine cold weather operation Refer to Rotax 912 Series Operators Manual, last issue, providing instructions for operating media (lubricant and coolant specifications) to be used in cold weather operation.
Page 134 Garmin G950 IFDS - Supplement Page S4 - 10 For cold weather operations, the crew must focus on the check of following parts of airplane (free of snow/ice/standing water).  control surfaces  fuselage  wings  vertical and horizontal stabilator ...
Page 135 Garmin G950 IFDS - Supplement Page S4 - 11 3.2 P – FLIGHT CHECK AIRCRAFT WALK AROUND To perform the aircraft walk-around, carry out the checklists according to the pattern shown in Figure 4-1. If ignition switches are turned ON, a propeller movement can cause the engine starting with consequent hazard for people nearby.
Page 136 Garmin G950 IFDS - Supplement Page S4 - 12 Pilot door and cabin Check door for integrity. Turn ON the Mas- ter Switch and check Stall Warning switch for operation and condition; check lighting of Landing/Taxi/Nav/Strobe lights, then turn OFF the Master Switch. Left main landing gear Check fuselage skin status, tire status (cuts, bruises, cracks and excessive wear), slip-...
Page 137 Garmin G950 IFDS - Supplement Page S4 - 13 dogs with practically no friction at all further investigation is necessary. Turn propeller by hand in direction of engine rota- tion several times and observe engine for odd noises or exces- sive resistance and normal com- pression.
Page 138 Garmin G950 IFDS - Supplement Page S4 - 14 Left wing top and bottom panels Visual inspection Left winglet, nav and strobe Check for integrity and fixing lights, static discharge wick Left aileron and balance mass Visual inspection, remove tie-down devices and control locks if employed.
Page 139 Garmin G950 IFDS - Supplement Page S4 - 15 defects and should rotate freely. Check fix- ing and lack of play between blades and hub. Right engine nacelle Apply check procedure reported in the walk-around station 5 and 6 Passenger door and cabin Check door for integrity.
Page 140 Garmin G950 IFDS - Supplement Page S4 - 16 INTENTIONALLY LEFT BLANK Edition, Rev. 0 Section 4 – Normal procedures...
Page 141 Garmin G950 IFDS - Supplement Page S4 - 17 3.3 C OCKPIT INSPECTIONS Instruct passengers on how to use safety belts and normal / emergency ex- its. Passenger embarkation should be done, avoiding contact with hot / oily parts such as engine exhaust pipes, drainage tubes and wheel brakes, or sharp wing control surfaces edges.
Page 142 Garmin G950 IFDS - Supplement Page S4 - 18 Cabin heat CLOSED Flaps Operate control to FULL position. Verify extension. Retract flaps. Pitch trim control Set to neutral position. Rudder trim control Set to neutral position. Eng. Starting Battery Voltmeter Check 12 to 14 Volt (if installed) Edition, Rev.
Page 143 Garmin G950 IFDS - Supplement Page S4 - 19 INTENTIONALLY LEFT BLANK Edition, Rev. 0 Section 4 – Normal procedures...
Page 144 Garmin G950 IFDS - Supplement Page S4 - 20 3.4 E NGINE STARTING Avionics switches must be set OFF during engine starting to prevent avion- ic equipment damage. CAUTION Start clearance Obtain if needed Right engine starting RH Throttle lever IDLE RH Carburetor heat RH Propeller Lever...
Page 145 Garmin G950 IFDS - Supplement Page S4 - 21 RH Choke RH Avionics RH Cross bus RH Ammeter CHECK Amps positive Voltmeter CHECK 12 to 14 Volt Chronometer Start Strobe light Left engine starting LH Throttle lever IDLE LH Carburetor heat LH Propeller Lever FULL FORWARD LH Choke...
Page 146 Garmin G950 IFDS - Supplement Page S4 - 22 3.5 B EFORE TAXIING Let the engines warm up to a minimum oil temperature of 50°C at 1200 RPM Nav , Taxi and Landing lights Transponder Stand-by Passengers and crews seat belts Fastened Passengers and crews headphones Set as required...
Page 147 Garmin G950 IFDS - Supplement Page S4 - 23 3.7 P RIOR TO TAKEOFF Parking Brake ENGAGED RH Fuel Selector RIGHT LH Fuel Selector LEFT LH and RH fuel pressure CHECK LH and RH Engine parameters checks:  Oil temperature: 50-110 °...
Page 148 Garmin G950 IFDS - Supplement Page S4 - 24 LH 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 restored with prop lever at full forward posi- tion.
Page 149 Garmin G950 IFDS - Supplement Page S4 - 25 3.9 T AKEOFF AND CLIMB Landing light LH and RH Electrical Fuel pump BOTH ON Carburettors heat CHECK OFF LH and RH Propeller Lever FULL FORWARD LH and RH Throttle Lever FULL POWER Engines instruments Parameters within green arcs...
Page 150 Garmin G950 IFDS - Supplement Page S4 - 26 3.10 RUISE LH and RH Propeller Lever SET to 1900-2250 RPM Throttles decrease should be made before propel- ler speed reduction below 2200 RPM, as, contrariwise, Propeller Lever in- crease RPM should be set before engine Throttle Levers are advanced. CAUTION Engine parameters check (LH and RH) ...
Page 151 Garmin G950 IFDS - Supplement Page S4 - 27 3.12 ESCENT AND APPROACH Propellers Set to Max Continuous 2250 RPM Carburettors heat As required Altimeter setting QNH set and crosscheck 3.13 EFORE LANDING Rear passengers seats Seats set at full aft and lower position LH and RH Electrical Fuel pump BOTH ON On downwind leg:...
Page 152 Garmin G950 IFDS - Supplement Page S4 - 28 3.14 ALKED LANDING MISSED APPROACH LH and RH Propeller Lever FULL FORWARD LH and RH Throttle Lever FULL POWER Propeller Lever increase to max RPM should be attained before engine Throt- tle Levers are advanced to max take off power.
Page 153 Garmin G950 IFDS - Supplement Page S4 - 29 3.16 ARKING SHUT DOWN It is always suggested to park the aircraft with the nose pointing into NOTE wind to improve cooling after shut down. Parking brake Engage Taxi light Engines Allow for cooling down 1 minute at idle power LH and RH AVIONIC BUS...
Page 154 Garmin G950 IFDS - Supplement Page S4 - 30 3.17 OSTFLIGHT CHECKS Protective cover for Pitot tubes, stall warning and stat- Install ic port plugs. Lock one control wheel with safety belt. Wheel chocks Place under MLG Aileron lock Place and tighten Pilot and passengers doors.
Page 155 Garmin G950 IFDS - Supplement Page S4 - 31 ROUND TOWING PARKING AND MOORING 4.1. OWING When the a/c is moved on the ground, the Master Switch must be turned ON until the a/c is parked. CAUTION To tow the aircraft it is necessary to use a metal stiff bar connected to the nose gear.
Page 156 Garmin G950 IFDS - Supplement Page S4 - 32 4.3. OORING The aircraft is moored to insure its immovability, protection, and security under various weather conditions. Mooring is strongly recommended when the wind is more than 15 knots and the a/c is completely refuelled. CAUTION Procedure 1.
Page 157 Garmin G950 IFDS - Supplement Page S4 - 33 Mooring – side view Edition, Rev. 0 Section 4 – Normal procedures PARKING and MOORING...
Page 158 Garmin G950 IFDS - Supplement Page S4 - 34 INTENTIONALLY LEFT BLANK Edition, Rev. 0 Section 4 – Normal procedures PARKING and MOORING...
Page 159 GARMIN G950 IFDS – Increased MTOW (1230 kg) Page SW5 - 1 SECTION 5 - PERFORMANCES INDEX Introduction ..................... 2 Use of performances charts ................2 Airspeed indicator system calibration ............3 ICAO Standard Atmosphere................4 Stall speed ...................... 5 Crosswind ......................
Page 160 GARMIN G950 IFDS – Increased MTOW (1230 kg) Page SW5 - 2 1. I NTRODUCTION This section provides all necessary data for an accurate and comprehensive plan- ning of flight activity from takeoff to landing. Data reported in graphs and/or in tables were determined using: “Flight Test Data”...
Page 161 GARMIN G950 IFDS – Increased MTOW (1230 kg) Page SW5 - 3 3. A IRSPEED INDICATOR SYSTEM CALIBRATION Graph shows calibrated airspeed V as a function of indicated airspeed V Figure 1 - IAS/CAS chart Example: Given Find KIAS 75 KCAS 74 Edition, Rev.0 Section 5 - Performances...
Page 162 GARMIN G950 IFDS – Increased MTOW (1230 kg) Page SW5 - 4 4. ICAO S TANDARD TMOSPHERE c.δA=2250 ft A.δA=1600 ft °C Figure 2 – ICAO chart Examples: Given Find a. Temperature = 20°C c. Corresponding Density Altitude = 2250’ b.
Page 163 GARMIN G950 IFDS – Increased MTOW (1230 kg) Page SW5 - 5 5. S TALL SPEED ° ° [kg] [deg] KIAS KCAS KIAS KCAS KIAS KCAS 1230 (FWD C.G.) NOTE Altitude loss during conventional stall recovery, as demonstrated during flight tests is approximately 250 ft with banking below 30°. Edition, Rev.0 Section 5 - Performances STALL SPEED...
Page 164 GARMIN G950 IFDS – Increased MTOW (1230 kg) Page SW5 - 6 6. C ROSSWIND Maximum demonstrated crosswind is 17 Kts  Example: Given Find Wind direction ( Headwind = 17.5 Kts with respect to air- ) = 30° craft longitudinal axis Wind speed = 20 Kts Crosswind = 10 Kts Figure 3 –...
Page 165 GARMIN G950 IFDS – Increased MTOW (1230 kg) Page SW5 - 7 7. T AKEOFF PERFORMANCES ° ° Ground Roll S.L. At 50 ft AGL Ground Roll 1000 At 50 ft AGL Ground Roll 2000 At 50 ft AGL Ground Roll 3000 At 50 ft AGL Ground Roll...
Page 166 GARMIN G950 IFDS – Increased MTOW (1230 kg) Page SW5 - 8 ° ° Ground Roll S.L. At 50 ft AGL Ground Roll 1000 At 50 ft AGL Ground Roll 2000 At 50 ft AGL Ground Roll 3000 At 50 ft AGL Ground Roll 4000 At 50 ft AGL...
Page 167 GARMIN G950 IFDS – Increased MTOW (1230 kg) Page SW5 - 9 ° ° Ground Roll S.L. At 50 ft AGL Ground Roll 1000 At 50 ft AGL Ground Roll 2000 At 50 ft AGL Ground Roll 3000 At 50 ft AGL Ground Roll 4000 At 50 ft AGL...
Page 168 GARMIN G950 IFDS – Increased MTOW (1230 kg) Page SW5 - 10 8. T ATE OF LIMB AT ° ° S.L. 1276 1088 2000 1133 4000 6000 1230 8000 10000 12000 14000 -164 S.L. 1507 1302 1119 1190 2000 1351 1150 1068 4000...
Page 169 GARMIN G950 IFDS – Increased MTOW (1230 kg) Page SW5 - 11 9. T ATE OF LIMB AT ° ° S.L. 1214 1037 1000 1147 2000 1080 3000 1013 1230 4000 5000 6000 7000 S.L. 1283 1102 1002 1000 1214 1034 2000 1145...
Page 170 GARMIN G950 IFDS – Increased MTOW (1230 kg) Page SW5 - 12 10. E NROUTE ATE OF LIMB AT ° ° S.L. 1317 1135 1036 2000 1179 1000 4000 1041 6000 1230 8000 10000 12000 14000 S.L. 1560 1360 1182 1022 1251 2000...
Page 171 GARMIN G950 IFDS – Increased MTOW (1230 kg) Page SW5 - 13 11. E NROUTE ATE OF LIMB AT ° ° S.L. 1241 1073 1000 1177 1011 2000 1114 3000 1050 1230 4000 5000 6000 7000 S.L. 1480 1295 1130 1194 1000 1410...
Page 172 GARMIN G950 IFDS – Increased MTOW (1230 kg) Page SW5 - 14 12. O NGINE ATE OF LIMB AT ° ° S.L. 1000 2000 3000 1230 4000 5000 -115 6000 -150 7000 -110 -185 S.L. 1000 2000 3000 1080 4000 5000 6000 7000...
Page 173 GARMIN G950 IFDS – Increased MTOW (1230 kg) Page SW5 - 15 13. O NGINE ATE OF LIMB AT ° ° S.L. 1000 2000 3000 1230 4000 5000 -113 6000 -148 7000 -108 -183 S.L. 1000 2000 3000 1080 4000 5000 6000 7000...
Page 174 GARMIN G950 IFDS – Increased MTOW (1230 kg) Page SW5 - 16 14. C RUISE PERFORMANCES Weight: 1150 kg (2535 lb) Pressure Altitude: 0 ft ISA – 30°C (-15°C) ISA (15°C) ISA + 30°C (45°C) F.C. F.C. F.C. KTAS KTAS KTAS [inHg] [lt/hr]...
Page 175 GARMIN G950 IFDS – Increased MTOW (1230 kg) Page SW5 - 17 Weight: 1150 kg (2535 lb) Pressure Altitude: 3000 ft ISA – 30°C (-21°C) ISA (9°C) ISA + 30°C (39°C) F.C. F.C. F.C. KTAS TCAS KTAS [inHg] [lt/hr] [lt/hr] [lt/hr] 2388 26.4...
Page 176 GARMIN G950 IFDS – Increased MTOW (1230 kg) Page SW5 - 18 Weight: 1150 kg (2535 lb) Pressure Altitude: 9000 ft ISA – 30°C (-33°C) ISA (-3°C) ISA + 30°C (27°C) F.C. F.C. F.C. KTAS KTAS KTAS [inHg] [lt/hr] [lt/hr] [lt/hr] 2388 21.1...
Page 177 GARMIN G950 IFDS – Increased MTOW (1230 kg) Page SW5 - 19 15. L ANDING PERFORMANCES ° ° Ground Roll S.L. At 50 ft AGL Ground Roll 1000 At 50 ft AGL Ground Roll 2000 At 50 ft AGL Ground Roll 3000 At 50 ft AGL Ground Roll...
Page 178 GARMIN G950 IFDS – Increased MTOW (1230 kg) Page SW5 - 20 ° ° Ground Roll S.L. At 50 ft AGL Ground Roll 1000 At 50 ft AGL Ground Roll 2000 At 50 ft AGL Ground Roll 3000 At 50 ft AGL Ground Roll 4000 At 50 ft AGL...
Page 179 GARMIN G950 IFDS – Increased MTOW (1230 kg) Page SW5 - 21 ° ° Ground Roll S.L. At 50 ft AGL Ground Roll 1000 At 50 ft AGL Ground Roll 2000 At 50 ft AGL Ground Roll 3000 At 50 ft AGL Ground Roll 4000 At 50 ft AGL...
Page 180 GARMIN G950 IFDS – Increased MTOW (1230 kg) Page SW5 - 22 16. B ALKED LANDING CLIMB GRADIENT Flight conditions (ISA and SL): 1230 kg (2712 lb) Weight: Throttle levers Both FULL FORWARD Flaps Landing gear DOWN MTOW 1230kg (2712 lb) Weight Speed 72 KIAS...
Page 181 GARMIN G950 IFDS – Increased MTOW (1230 kg) Page SW5 - 23 INTENTIONALLY LEFT BLANK Edition, Rev. 0 Section 5 - Performances...
Page 182 Page 6 - 1 SECTION 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.
Page 183 Page 6 - 2 INTENTIONALLY LEFT BLANK Edition, Rev 0 Section 6 – Weight and balance...
Page 184 Page 6 - 3 1. INTRODUCTION This section describes the procedure for establishing the basic empty weight and the moment of the aircraft. Loading procedure information is also provided. Aircraft must be operated in accordance with the limits con- NOTE cerning the maximum takeoff weight and CG excursion as re- ported in Flight Manual Section 2.
Page 185: Weighing Procedures
Page 6 - 4 2. WEIGHING PROCEDURES 2.1. REPARATION Carry out weighing procedure inside closed hangar Remove from cabin any object unintentionally left Make sure Flight Manual and mandatory documents are on board Align nose wheel Drain fuel via the specific drain valve Oil, hydraulic fluid and coolant liquid at the operating levels Move sliding seats to most forward position Raise flaps to fully retracted position...
Page 186 Page 6 - 5 2.5. EIGHING RECORD Model P2006T S/N:________ Weighing no. ____ Date:_________ Datum: leading edge vertical Kg or Lbs Meters or feet Nose wheel weight W Plumb bob distance LH wheel LH wheel weight Plumb bob distance RH wheel...
Page 187 Page 6 - 6 2.6. (II) EIGHING RECORD Model P2006T S/N:________ Weighing no. ____ Date:_________ Datum: leading edge vertical Kg or Lbs Meters or feet Nose wheel weight W Plumb bob distance LH wheel LH wheel weight Plumb bob distance RH wheel...
Page 188 Page 6 - 7 3. WEIGHTS AND C.G. C.G. position can be defined by means of the chart below. The pilot is responsible for ensuring the correct useful load loading. MASS & BALANCE LOADING CONDITION (lbs) (lbs) (lbs) (lbs) (lbs) 176 265 176 265 176 265...
Page 189 Page 6 - 8 4. BAGGAGE LOADING The baggage loading in the dedicated compartment must be carried out in 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.
Page 190 Page 6 - 9 INTENTIONALLY LEFT BLANK Edition, Rev 0 Section 6 – Weight and balance...
Page 191: Equipment List
Page 6 - 10 5. EQUIPMENT LIST The following is a list of equipment 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.
Page 192 Page 6 - 11 _____ QUIPMENT LIST IRCRAFT S EIGHT ESCRIPTION INSTRUMENTATION GARMIN G950 IFDS SOFTWARE SD CARD P/N 0.37 airspeed indicator – UMA T6-311 – 200 -1.4 0.37 airspeed indicator - UMA T6-311 – -1.4 attitude indicator - Kelly Manufacturing -1.4 RCA26AK-3 altimeter - Altimeter - United Instruments...
Page 193 Page 6 - 12 _____ QUIPMENT LIST IRCRAFT S EIGHT ESCRIPTION ’ AVIONICS & MISCELLANEOUS ( CONT -1.4 Indicator KI 229 Static inverter Marathon PC-50 HONEYWELL Bendix/King DME KN 63 system Indicator DME KDI 572 -1.4 Transceiver DME KN 63 S-TEC Fifty Five X Autopilot System Turn coordinator S-TEC 6405-14L -1.4...
Page 194 Page 6 - 13 INTENTIONALLY LEFT BLANK Edition, Rev 0 Section 6 – Weight and balance...
Page 195 Page 7 - 1 SEZIONE 7 – AIRFRAME and SYSTEMS DESCRIPTION INDEX 1. INTRODUCTION ................3 2. AIRFRAME ..................3 3. POWERPLANT ................9 4. PEDESTAL CONTROLS..............12 5. CABIN OVER-HEAD PANEL CONTROLS ........15 6. INTERNAL LIGHTS ..............16 7.
Page 196 Page 7 - 2 INTENTIONALLY LEFT BLANK Edition, Rev 0 Section 7 – Airframe and Systems description...
Page 197 Page 7 - 3 1. INTRODUCTION This section provides aircraft and systems description and operation. 2. AIRFRAME 2.1. Each wing consists of a central light alloy torque box which carries all the wing bending, shear and torque loads; an aluminium leading edge is attached to the front spar while flap and aileron are hinged to the rear spar.
Page 198 Page 7 - 4 2.2. USELAGE The fuselage is constituted by a light-alloy semi-monocoque structure wrapped- around by stressed skin panels. Radome and stern fairing are of composite materi- al. Cabin and baggage compartment floor is a warping of beams and keelsons sup- porting the seats guides and other components.
Page 199 Page 7 - 5 2.3. MPENNAGES The vertical tail is entirely metallic: 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.
Page 200 Page 7 - 6 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.
Page 201 Page 7 - 7 2.4. LIGHT CONTROLS The main flight control system controls the airplane in three axes. All primary controls (ailerons, rudder and stabilator) are manually operated by a conventional control column and rudder pedals, pulleys, cables, bellcranks and rods. The secondary flight controls consist of a two-axis trim system and a flaps system.
Page 202 Page 7 - 8 INTENTIONALLY LEFT BLANK Edition, Rev 0 Section 7 – Airframe and Systems description AIRFRAME...
Page 203 Page 7 - 9 3. POWERPLANT P2006T is equipped with two four-cylinder four-stroke Rotax 912S engines of 98hp (73kW) each, both rotating clockwise. These are partially liquid cooled and they feature an integrated reduction gear driving constant speed propellers with pitch feathering devices.
Page 204 Page 7 - 10 The expansion tank is closed by a pressure cap (3) fitted with pressure relief valve and return valve. At temperature rise and expansion of the coolant, the pressure re- lief valve opens and the coolant will flow via a hose at atmospheric pressure to the transparent overflow bottle (4).
Page 205 Page 7 - 11 3.1. NGINE FEATURES Manufacturer Bombardier-Rotax GmbH Model 912 S3 Certification basis FAR 33, Amendment 15 Type Certificate EASA TCDS no. E.121 dated 1st 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 reduction gear box with shock absorber.
Page 206 Page 7 - 12 4. PEDESTAL CONTROLS Following picture shows the controls installed on the central pedestal. Figure 7. – Pedestal controls Description 1 and 2 Choke control Choke friction knob Upper levers friction knob LH and RH Throttle lever LH and RH Carburetor Heating lever 9-10 LH and RH Propeller Pitch Control lever...
Page 207 Page 7 - 13 Aircraft not embodying the Design Change 2006/66 “New Powerplant NOTE control setting layout” or the SB 039-CS “P2006T New powerplant con- trols layout” feature a different pedestal levers layout: propeller and carb. heat levers position are inverted.
Page 208 Page 7 - 14 INTENTIONALLY LEFT BLANK Edition, Rev 0 Section 7 – Airframe and Systems description...
Page 209 Page 7 - 15 5. CABIN OVER-HEAD PANEL CONTROLS Following picture shows the controls installed on the cabin over-head panel. Figure 8. – Cabin head panel controls Description Number Cabin Light LH Fuel selector valve LH Electric Starter LH electric fuel pump LH Engine ignition 1 LH Engine ignition 2 RH Engine ignition 1...
Page 210 Page 7 - 16 6. INTERNAL LIGHTS Internal lights system is composed by following equipment: • Cabin light, providing lighting for crew and passengers compartment; • Instruments lights, which in turn are composed by three sub-systems each one fit- ted with dimming device: Switches built-in lights Avionics lights Cockpit lights...
Page 211 Page 7 - 17 7. EXTERNAL LIGHTS External lights system consists of the following equipment (see Figure below): • NAV Lights: they provide, by means of three position lights, the aircraft flight direction identification. • Strobe Lights: they provide aircraft identification to prevent collision. They are located, like the above mentioned NAV lights, on the winglets and on the top of the vertical fin.
Page 212 Page 7 - 18 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 Edition, Rev 0 Section 7 – Airframe and Systems description EXTERNAL LIGHTS...
Page 213: Fuel System
Page 7 - 19 8. FUEL SYSTEM Fuel system consists of two integrated tanks inside the wing torque boxes and fit- ted with inspection doors. Each fuel tank has a capacity of 100 litres and is equipped with a vent valve (its outlet is located on the lower wing skin) and a sump fitted with a drain valve for water/moisture drainage purposes.
Page 214 Page 7 - 20 Figure 12. – Fuel system schematic Edition, Rev 0 Section 7 – Airframe and Systems description FUEL SYSTEM...
Page 215: Landing Gear System
Page 7 - 21 9. LANDING GEAR SYSTEM The landing gear retraction system is of electro-hydraulic type, powered by a re- versible pump which is electrically controlled by the LG control knob located on the LH instrument panel and by the legs position micro switches: these ones allow for detecting landing gear “down-locked”...
Page 216 Page 7 - 22 Hydraulic oil, contained in an integrated reservoir located inside the Hydraulic Power Pack, is pressurized by a reversible electric pump: as the LG control knob is placed in either the UP or DOWN position, the pump directs the fluid through the related pressure line toward each hydraulic jack.
Page 217 Page 7 - 23 The three green lights illuminate only when the respective gear is “down-locked”; the red light indicates the gear is in transit “up” or “down” and the amber caution light GEAR PUMP ON indicates that the pump is electrically supplied. The red transition light extinguishes only when all the three gear legs are “down- locked”...
Page 218 Page 7 - 24 INTENTIONALLY LEFT BLANK Edition, Rev 0 Section 7 – Airframe and Systems description LANDING GEAR SYSTEM...
Page 219 Page 7 - 25 10. BRAKES The A/C is provided with an independent hydraulically actuated brake system for each main wheel. A master cylinder is attached to each pilot/co-pilot’s rudder pe- dal: see schematic below. Hydraulic pressure, applied via the master cylinders, enters the brake via lines connected to an inlet fitting on the wheel brake caliper.
Page 220 Page 7 - 26 11. VENTILATION If required, pilot allows for ram-air entering the cabin via the two outlet ports re- spectively located on the left and right side of the instruments panel. Other two ram-air ventilation outlets are located on the cabin head, in the passengers’ zone. 12.
Page 221 Page 7 - 27 14. DOORS The cabin main door is located forward, on the left side of the fuselage while the emergency exit (passenger door) is located aft, on the right side of the fuselage. On the top of the cabin it is located the ditching emergency exit: see figure below. Figure 15.
Page 222: Baggage Compartment
Page 7 - 28 from outside. Instructions are reported on the placards near the by-pass lever, lo- cated in correspondence of the latch: to unlock it is necessary to push and hold the red tab down, after that the door can be opened operating the handle. After engine shut-down, the pressure drop can have a certain delay, preventing the door from being opened by normal means: do not force the handle but operate the override system above mentioned.
Page 223 Page 7 - 29 INTENTIONALLY LEFT BLANK Edition, Rev 0 Section 7 – Airframe and Systems description...
Page 224 Page 7 - 30 INTENTIONALLY LEFT BLANK Edition, Rev 0 Section 7 – Airframe and Systems description...
Page 225 Page 7 - 31 16. PLACARDS In addition to the limitation placards reported on Section 2, following placards are installed on the aircraft. Additionally, nearby the placards listed below (English lan- NOTE 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.
Page 226 Page 7 - 32 Description Placard Place Emergency Emergency distribu- gear extension tors compartment instructions Alternate static Central pedestal, left port location side Alternate static Central pedestal, right port operating side instructions Static ports lo- Static ports: fuselage - STATIC PORT cation both sides KEEP CLEAN...
Page 227 Page 7 - 33 Description Placard Place Landing gear hydraulic com- hydraulic partment cap (fuselage cumulator: tail, left side) pressure limit hydraulic Fuselage tail, left side, compartment in correspondence of location hydraulic com- partment cap Towing limita- Nose LG forward door tions Stabilator Fuselage tail, left side,...
Page 228 Page 7 - 34 Description Placard Place Steel boards: Fuselage tail, left side a/c identifica- tion marks (Sample) Main LG tires MLG leg, LH and RH inflation pres- sure values Nose LG tire Nose LG fork inflation pres- sure values Edition, Rev 0 Section 7 –...
Page 229 Page 7 - 35 INTENTIONALLY LEFT BLANK Edition, Rev 0 Section 7 – Airframe and Systems description...
Page 230 Page 7 - 36 INTENTIONALLY LEFT BLANK Edition, Rev 0 Section 7 – Airframe and Systems description...
Page 231 Garmin G950 IFDS - Supplement Page S7 - 37 17. INSTRUMENTS PANEL GARMIN G950 IFDS - Instruments panel (typical layout) Edition, Rev. 0 Section 7 – Airframe and Systems description INSTRUMENTS PANEL...
Page 232 Garmin G950 IFDS - Supplement Page S7 - 38 Item Description GDU 1040 (PFD) GMA 1347 Compass A/P Programmer/Computer GDU 1040 (MFD) LH fuel quantity indicator LH R.P.M. Dual M.A.P. indicator RH R.P.M. RH fuel quantity indicator LH CHT RH CHT LH Oil Temperature RH Oil Temperature LH oil pressure...
Page 233 Garmin G950 IFDS - Supplement Page S7 - 39 Item Description RH Field LH Cross bus switch Master switch RH Avionic switch LH Field LH Avionic switch Standby Airspeed indicator Chronometer LG control knob Voltammeter Indicator ADF control panel Cockpit light dimmer Cabin heat (warm air from RH engine) Avionics lights dimmer Cabin heat (warm air from LH engine)
Page 234 Garmin G950 IFDS - Supplement Page S7 - 40 INTENTIONALLY LEFT BLANK Edition, Rev. 0 Section 7 – Airframe and Systems description INSTRUMENTS PANEL...
Page 235: Electrical System
Garmin G950 IFDS - Supplement Page S7 - 41 18. ELECTRICAL SYSTEM Primary DC power is provided by two engine-driven generators which, during normal operations, operate in parallel. Each generator is rated at 14,2-14,8 Vdc, 40 Amp, and it is fitted with an integrat- ed regulator, which acts to maintain a constant output voltage, and with an auto- matic overvoltage device protecting the circuits and the electric components from an excessive voltage caused by generator failures.
Page 236 Garmin G950 IFDS - Supplement Page S7 - 42 The following loads are connected to the battery bus: 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...
Page 237 Garmin G950 IFDS - Supplement Page S7 - 43 The other loads are so divided among following busses: LH GEN Bus LH Avionic Bus RH GEN Bus RH Avionic Bus Pitot heat NAV lights Landing light Transponder Rudder trim COM 2 Taxi light Encoder altimeter Stall warning...
Page 238 Garmin G950 IFDS - Supplement Page S7 - 44 the pertinent generator bus (and related avionic bus supplied) is separated from the battery bus and from opposite generator bus. When both generators are correctly operating and all above mentioned switches are in ON position, all the busses are connected to the generators.
Page 240 Garmin G950 IFDS - Supplement Page S7 - 46 INTENTIONALLY LEFT BLANK Edition, Rev. 0 Section 7 – Airframe and Systems description ELECTRICAL SYSTEM...
Page 241 Page 8 - 1 SECTION 8 – AIRCRAFT CARE and MAINTENANCE INDEX 1. Introduction ..................3 2. Inspection intervals ................. 3 3. Aircraft changes or repairs ............. 3 4. Maintenance ..................4 4.1. Refuelling ................. 4 4.2. Oil level control ............... 4 4.3.
Page 242 Page 8 - 2 INTENTIONALLY LEFT BLANK Edition, Rev. 0 Section 8 – Aircraft Care and Maintenance...
Page 243 Page 8 - 3 NTRODUCTION This Section deals with main care and maintenance operations for P2006T. Refer to Aircraft Maintenance Manual to establish the controls / inspections / maintenance tasks (scheduled and unscheduled) to be performed. NSPECTION INTERVALS Scheduled inspections must be performed in accordance with the instructions addressed on the Aircraft Maintenance Manual.
Page 244 Page 8 - 4 AINTENANCE 4.1. EFUELLING - Do not perform aircraft refuelling near flames, sparks or similar. - Avoid fuel contact with the skin: a skin corrosion could occur. - Make sure that a fire extinguisher is available nearby during refuel- ling operations.
Page 245 Page 8 - 5 4.3. ANDING GEAR TIRES 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.
Page 246 Page 8 - 6 ROUND TOWING PARKING AND MOORING 5.1. OWING When the a/c is moved on the ground, either manually or by towing, the Master Switch must be turned ON until the a/c is parked. CAUTION To tow the aircraft it is necessary to use a metal stiff bar connected to the nose gear.
Page 247 Page 8 - 7 5.3. OORING The aircraft is moored to insure its immovability, protection, and security under various weather conditions. Mooring is strongly recommended when the wind is more than 15 knots and the a/c is completely refuelled. CAUTION Procedure 1.
Page 248 Page 8 - 8 Mooring – side view LEANING Aircraft surface must be kept clean to ensure expected flight performance. Excessively dirty surfaces can affect normal flight conditions. CAUTION 6.1. INDOWS For windows cleaning, it is allowed the use of acrylic products employed for glass and Plexiglas surfaces cleaning.
Page 249 Page 8 - 9 NTERNAL SURFACES Interiors must be cleaned with a rate of 3 to 6 months. Any object present in the cabin (like pens, lost property, 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.
Page 250 Page 8 - 10 INTENTIONALLY LEFT BLANK Edition, Rev. 0 Section 8 – Aircraft Care and Maintenance...
Page 251 Page 9-1 SECTION 9 – SUPPLEMENTS INDEX Introduction ..................... 3 Supplements lists .................... 4 SUPPLEMENTS LIST FOR AIRPLANES WITH ANALOGUE INSTRUMENTS Supplement no. A1 - Garmin GNS-430W GPS/WAAS COMM/NAV Supplement no. A2 - Garmin SL30 VHF COMM/NAV Supplement no. A3 - Garmin GMA340 audio panel Supplement no.
Page 252 Page 9-2 SUPPLEMENTS LIST FOR AIRPLANES WITH GARMIN G950 IFDS Supplement no. G1 – Garmin G950 IFDS Supplement no. G2 – S-TEC Fifty Five X Autopilot for GARMIN G950 Supplement no. G3 – KR 87 ADF System for GARMIN G950 Supplement no.
Page 253 NTRODUCTION This 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 Page 9-4 2. S UPPLEMENTS LISTS Aircraft S/N: Registration marks: Date: SUPPLEMENTS LIST FOR AIRPLANES WITH ANALOGUE INSTRUMENTS APPLICABLE: Sup. No. Title Rev. no. Date Garmin GNS-430W Gps/VHF Comm/Nav Garmin SL30 VHF Comm/Nav Garmin GMA 340 Audio Panel Garmin GTX 328 Mode S Transponder Bendix-King Honeywell KR 87 ADF System...
Page 255 Page 9-5 Aircraft S/N: Registration marks: Date: SUPPLEMENTS LIST FOR AIRPLANES WITH ANALOGUE INSTRUMENTS APPLICABLE: Sup. No. Title Rev. no. Date Chinese AFMS Increased MTOW - 1230 KG (MOD 2006/015) Increased Vle/Vlo South African AFM Argentine AFM Ukrainian AFM SMP for Analogic Con- figuration Alternators with 70A India AFMS...
Page 256 Page 9-6 INTENTIONALLY LEFT BLANK Edition, Rev. 0 Section 9 - Supplements SUPPLEMENTS LIST...
Page 257 Page 9-7 Aircraft S/N: Registration marks: Date: SUPPLEMENTS LIST FOR AIRPLANES WITH GARMIN G950 IFDS APPLICABLE: Sup. No. Title Rev. no. Date Garmin G950 IFDS S-TEC Fifty Five X Auto- pilot for GARMIN G950 Bendix-King Honeywell KR 87 ADF System for GARMIN G950 Bendix-King Honeywell...
Page 258 Page 9-8 INTENTIONALLY LEFT BLANK Edition, Rev. 0 Section 9 - Supplements...
Page 259 Page A22-1 SUPPLEMENT NO. A22 – ARGENTINE AFM Record of Revisions EASA Approval Tecnam Approval Revised Description of Or Under DOA page Revision Privileges First issue D. Ronca G.Paduano M. Oliva See Note (*) Note (*): this Supplement has been originally issued on 5 May 2014, after EASA Third Country Validation process completion.
Page 260 Page A22-2 LOEP Page Revision Page Revision Rev 0 Rev 0 A22-1 A22-10 Rev 0 Rev 0 A22-2 A22-11 Rev 0 Rev 0 A22-3 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 Edition, Rev.
Page 261 Page A22-3 TABLE OF CONTENTS INTRODUCTION ...................... 4 General........................5 1. Fuel ......................... 5 Limitations ......................5 1. Kind of Operation Equipment ................5 2. Other Placards ....................6 Edition, Rev. 0 Section 9 – Supplements Supplement no. A22 – Argentine AFM...
Page 262 Page A22-4 INTRODUCTION This Supplement applies for Argentine registered aircraft. It contains supplemental 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.
Page 263 Page A22-5 ENERAL 1. F Approved fuel: MOGAS ASTM D4814 AVGAS 100LL (ASTM D910) IMITATIONS 1. K IND OF PERATION QUIPMENT The equipment appropriate for different types of operations must comply with ap- plicable regulations. Edition, Rev. 0 Section 9 – Supplements Supplement no.
Page 264 Page A22-6 2. O THER LACARDS Dimensions Description Placard Place (mm) ELT equipment Baggage com- 50x45 location partment, right side First Aid Kit Baggage com- 40x40 location partment, aft cover panel Fire extin- Cockpit floor, 35x50 guisher loca- pilot side tion Emergency Removable...
Page 265 Page A22-7 Dimensions Description Placard Place (mm) Emergency Emergency 55x28 gear extension distributors instructions compartment Smoking ban Instruments 21x3 panel, right side ESB voltmeter Instruments 56x9 panel, right side (see suppl. A14) Battery hous- On the battery 65x40 housing, left side, aircraft tail cone Engine oil lev-...
Page 266 Page A22-8 Dimensions Description Placard Place (mm) Fuel type and In correspond- 70x50 quantity ence of each fuel tank filler cap. Ground con- In correspon- 85x20 nection during dance of each refuelling pro- tank filler cap cedure Baggage com- Baggage com- 90x55 partment ca- partment (ver-...
Page 267 Page A22-9 Dimensions Description Placard Place (mm) Door locking Main door and 55x30 each system: by- emergency ex- pass instruc- it: internal side tions Door locking Main door and 55x30 each system: by- emergency ex- pass instruc- it: external side tions Main door: exit Main door, in-...
Page 268 Page A22-10 Dimensions Description Placard Place (mm) Coolant tank On the coolant 17x19 content tank Main gear tires Near each main 47x20 inflating pres- gear wheel sure Nose gear tires Near the nose 47x20 inflating pres- wheel sure External power Below the ex- 50x48 socket...
Page 269 Page A22-11 Dimensions Description Placard Place (mm) 80x20 LG hydraulic Fuselage tail, compartment left side, in location correspondence of LG hydrau- lic compart- ment cap Edition, Rev. 0 Section 9 – Supplements Supplement no. A22 – Argentine AFM...
Page 270 Page A22-12 INTENTIONALLY LEFT BLANK Edition, Rev. 0 Section 9 – Supplements Supplement no. A22 – Argentine AFM...
Page 271 Page A23-1 Supplement no. A23 Ukrainian Aircraft Flight Manual Supplement Record of Revisions EASA Approval Tecnam Approval Revised Description of or Under DOA page Revision Privileges D. Ronca See Note (*) M. Oliva M. Oliva Note (*): this Supplement has been originally issued on 12 January 2015, after EASA Third Country Validation process completion.
Page 272 Page A23-2 TABLE OF CONTENTS 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 ...............
Page 273 Page A23-3 INTRODUCTION This supplement must be placed in EASA Approved P2006T Aircraft Flight Manual Section 9, if the airplane is delivered in Ukraine. This supplement must 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.
Page 274 Page A23-4 LIMITATIONS LIGHT LTITUDE “For flight at altitudes above 3600 m (11811 ft) the crew must use oxygen equip- ment. Flights between 3000m (9842 ft) and 3600 (11811) altitude without oxygen equip- ment for the crew are limited to a maximum of 30 minutes. For airplane operation above 3000 m (9842 ft) for more than 30 minutes, Oxygen supply must be provided for at least one passenger.”...
Page 275 Page A23-5 INDS OF PERATIONS QUIPMENT Equipment VFR Day VFR Night IFR Day IFR Night ● ● ● ● Magnetic compass ● ● ● ● Airspeed indicator ● ● ● ● Altimeter ● ● ● ● Vertical speed indicator ● ●...
Page 276 Page A23-6 EMERGENCY PROCEDURES MOKE AND FIRE OCCURRENCE Use ventilation window in case of smoke in cabin for all cases. Edition, Rev. 0 Section 9 - Supplements Supplement no. A23 – Ukrainian AFM Supplement...
Page 277 Page A23-7 NORMAL OPERATIONS Make reference to Section 4 of this Manual. Edition, Rev. 0 Section 9 - Supplements Supplement no. A23 – Ukrainian AFM Supplement...
Page 278 Page A23-8 PERFORMANCES ANDING PERFORMANCES ° ° Ground Roll S.L. At 50 ft AGL Ground Roll 1000 At 50 ft AGL Ground Roll 2000 At 50 ft AGL Ground Roll 3000 At 50 ft AGL Ground Roll 4000 At 50 ft AGL Ground Roll 5000 At 50 ft AGL...
Page 279 Page A23-9 INTENTIONALLY LEFT BLANK Edition, Rev. 0 Section 9 - Supplements Supplement no. A23 – Ukrainian AFM Supplement...
Page 280 Page A23-10 WEIGHT AND BALANCE For weight and balance, make reference to Section 6 of this Manual. Edition, Rev. 0 Section 9 - Supplements Supplement no. A23 – Ukrainian AFM Supplement...
Page 281 Page A23-11 INTENTIONALLY LEFT BLAN Edition, Rev. 0 Section 9 - Supplements Supplement no. A23 – Ukrainian AFM Supplement...
Page 282 Page G2-1 . G2 – S-TEC F UPPLEMENT NO IFTY UTOPILOT FOR GARMIN G950 Record of Revisions EASA Approval Tecnam Approval Revised Description of or Under DOA page Revision Privileges See Note (*) 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.
Page 283 Page G2-2 INTRODUCTION This section contains supplemental information to operate, in a safe and efficient manner, the aircraft when equipped with S-TEC Fifty Five X autopilot device interfacing Garmin G950 IFDS. GENERAL The System Fifty Five X is a rate based autopilot. When in control of the roll axis, the autopilot senses turn rate, as well as closure rate to the selected course, along with the non-rate quantities of heading error, course error and course deviation indication.
Page 284 Page G2-3 LIMITATIONS (EASA APPROVED) The S-TEC “Pilot’s Operating Handbook Fifty Five X”(4 Edition NOTE – First Revision dated March 01, 2008 or a more updated version) must be carried in the aircraft and made available to the pilot at all time.
Page 285 Page G2-4 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: EASA Approved Edition, Rev. 0 Section 9 - Supplements Supplement no. G2 – S-TEC Fifty Five X Autopilot for Garmin G950...
Page 286 Page G2-5 EMERGENCY PROCEDURES In event of autopilot malfunction, or when the system is not per- NOTE forming as expected or commanded, take immediately 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-...
Page 287 Page G2-6 Autopilot hardover or failure to hold the selected heading In case of Autopilot hardover or failure to hold the selected heading, apply follow- ing procedure: Accomplish items 1 and 2 simultaneously: 1. Airplane control wheel GRASP FIRMLY and OVERPOWER if necessary to regain aircraft control 2.
Page 288 Page G2-7 Electric trim malfunction In case of Electric Trim malfunction (either in AP Autotrim mode or when manu- ally operated through the Manual Electric Trim Switch), apply following proce- dure: 1. AP DISC/TRIM INTR switch PRESS and HOLD 2. TRIM MASTER SWITCH 3.
Page 289 Page G2-8 Heading information signal lost When AP is engaged and the heading information is lost (red X on display field – make also reference to Supplement G1 – Emergency procedures), the AP must be disconnected applying following procedure: Accomplish items 1 and 2 simultaneously: 1.
Page 290 G950 (AFCS Status Box and/or PFD) and the S-TEC Fifty Five X Autopi- lot Display. Make reference to Garmin G950 Pilot’s Guide for Tecnam P2006T (P/N 190-01146- 00) – last issue. The vertical speed mode is used to establish and hold a PILOT selected vertical speed.
Page 291 Page G2-10 SYSTEMS The System Fifty Five X Block Diagram is shown in the following figure. Edition, Rev. 0 Section 9 - Supplements Supplement no. G2 – S-TEC Fifty Five X Autopilot for Garmin G950...
Page 292 Page G3-1 . G3 – KR 87 ADF S G950 UPPLEMENT NO YSTEM FOR ARMIN Record of Revisions EASA Approval Tecnam Approval Revised Description of Or Under DOA page Revision Privileges See Note (*) Note (*): this Supplement has been originally issued under EASA Major Design Change Approval no. 10029633...
Page 293 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. Edition, Rev. 0 Section 9 - Supplements Supplement no. G3 – KR 87 ADF System for Garmin G950...
Page 294 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 lower sides of the HSI: the PFD softkeys BRG1 and BRG2 cycles respectively Bearing 1 and Bearing 2 Information Window through the different bearing sources, including ADF/frequency.
Page 295 Page G3-4 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. Edition, Rev. 0 Section 9 - Supplements Supplement no. G3 – KR 87 ADF System for Garmin G950...
Page 296 Page G4-1 . G4 – KN 63 DME S G950 UPPLEMENT NO YSTEM FOR ARMIN Record of Revisions EASA Approval Tecnam Approval Revised Description of Or Under DOA page Revision Privileges See Note (*) Note (*): this Supplement has been originally issued under EASA Major Design Change Approval no. 10029633...
Page 297 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.
Page 298 Page G4-3 PERFORMANCES 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 INTENTIONALLY LEFT BLANK Edition, Rev. 0 Section 9 - Supplements Supplement no. G4 – KN 63 DME System for Garmin G950...
Page 300 Page G5-1 . G5 – E UPPLEMENT NO NGINE STARTING BATTERY Record of Revisions EASA Approval Tecnam Approval Revised Description of or Under DOA page Revision Privileges See Note (*) 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.
Page 301 Page G5-2 INTRODUCTION This section contains information to operate the airplane equipped with a supple- mental battery dedicated to engines starting. GENERAL The engine starting battery is housed in a dedicated box under the main battery box: both batteries are accessible through the inspection cap F10 on the left side of the tail cone.
Page 302 Page G5-3 PERFORMANCES See Section 5 of this Manual. WEIGHT AND BALANCE For weight and balance, make reference to Section 6 of this Manual; additionally, the equipment list reported on Para. 5 is so integrated: QUIPMENT LIST IRCRAFT S EIGHT ESCRIPTION &...
Page 303 Page G5-4 When the design change in subject is embodied, following placards are installed on the airplane: Description Placard Place Engine starting Close to the voltmeter battery voltme- ter location Batteries com- Fuselage tail cone, left partment loca- side tion Edition, Rev.
Page 304 Page G6-1 . G6 – P UPPLEMENT NO OWER SUPPLY FROM BUILT IN GENERATORS Record of Revisions EASA Approval Tecnam Approval Revised Description of or Under DOA page Revision Privileges See Note (*) Note (*): this Supplement has been originally issued under EASA Major Design Change Approval no. 10031748,...
Page 305 Page G6-2 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. Edition, Rev. 0 Section 9 - Supplements Supplement no. G6 – POWER SUPPLY FROM BUILT-IN GENERATORS...
Page 306 Page G6-3 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 Edition, Rev. 0 EASA Approved Section 9 - Supplements Supplement no.
Page 307 Page G6-4 EMERGENCY PROCEDURES In event of the following failure conditions (addressed on Section S3 of this Man- ual):  Single Engine operations  Single generator failure (Para. 3.2)  Single generator overvoltage (Para 3.4)  Both generators failure (Para. 3.1) ...
Page 308 Page G6-5 SYSTEMS When the airplane embodies the design change in subject, the Rotax engine built- in generators are enabled in order to supply power to two 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 breakers relat- ed to the auxiliary power generation system.
Page 309 Page G6-6 INTENTIONALLY LEFT BLANK Edition, Rev. 0 Section 9 - Supplements Supplement no. G6 – POWER SUPPLY FROM BUILT-IN GENERATORS...
Page 310 Page G7-1 . G7 UPPLEMENT NO AFM S UPPLEMENT FOR COUNTRIES OPERATORS Record of Revisions EASA Approval Tecnam Approval Revised Description of or Under DOA page Revision Privileges See Note (*) Note (*): this Supplement has been originally issued on 12 November 2010, after EASA Third Country Valida- tion process completion.
Page 311 Page G7-2 TABLE OF CONTENTS INTRODUCTION ...................... 3 GENERAL ........................ 3 LIMITATIONS (EASA APPROVED) ................4 Approved maneuvers ....................4 Ambient Temperature .................... 4 Flight Altitude ......................4 Airfield elevation ....................4 Operation from unpaved runways ................4 Over-water flights ....................5 Flight crew ......................
Page 312 This supplement applies for CIS countries operators. GENERAL This 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.
Page 313 Page G7-4 LIMITATIONS (EASA APPROVED) PPROVED MANEUVERS Non aerobatic operations include: Any manoeuvre pertaining to “normal” flight  Stalls  Lazy eights  Turns in which the angle of bank is not more than 60°  Chandelle  Acrobatic manoeuvres, including whip stalls, spins and turns with angle of bank of more than 60°, are not approved for such a category.
Page 314 Page G7-5 WATER FLIGHTS Extended over-water flights are allowed within the limitations prescribed by CIS op- erational regulations. LIGHT 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 NOTE crew member.
Page 315 Page G7-6 THER PLACARDS Description Placard Place Smoking ban Instruments panel, right side НЕ КУРИТЬ Ditching emer- Ditching emergency gency exit: exit handle: internal opening side structions АВАРИЙНЫЙ ВЫХОД НА ВОДУ 1. Повернуть 2. Сильно толкнуть дверь Ditching emer- Ditching emergency gency exit:...
Page 316 Page G7-7 Description Placard Place Door locking Main door and emer- system: gency exit: internal pass instruc- side tions ДЛЯ АВАРИЙНОГО ВЫХОДА 1. Нажать вниз и удержать красный флажок 2. Открыть дверь Main door: exit Main door, internal instructions side ПРЕДУПРЕЖДЕНИЕ...
Page 317 Page G7-8 EMERGENCY PROCEDURES MOKE AND FIRE OCCURRENCE Use ventilation window in case of smoke in cabin for all cases. AILURE OF ONTROL YSTEM OSS OF TABILATOR ONTROL In case of loss of pilot side stabilator control (disconnected or jammed), apply following pro- cedure: 1.
Page 318 Page G7-9 OSS OF ILERON ONTROL In case of loss of pilot side aileron 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.
Page 319 Page G7-10 NE ENGINE INOPERATIVE PROCEDURES The ineffectiveness of one engine results in an asymmetric traction NOTE condition which tends to yaw and to bank the aircraft. In this condi- tion it is essential to maintain the direction of flight compensating the lower traction through the operating engine and counteracting the yawing effects through the use of pedals and rudder trim.
Page 320 Page G7-11 NFLIGHT ENGINE RESTART It is preferred to restart the engine at an altitude below 4000ft NOTE and at the suggested speed of 80 KIAS or more Carburettor heat ON if required Electrical fuel pump Fuel quantity indicator CHECK Fuel Selector CHECK (Crossfeed if required) FIELD...
Page 321 Page G7-12 ANDING EMERGENCIES ANDING WITHOUT ENGINE POWER Landing on the Airfield Both engines failure condition requires both propellers feath- ered and aircraft attitude set to maximum efficiency until the selection of the field, on which to perform an emergency land- CAUTION ing, is made.
Page 322 Page G7-13 NORMAL OPERATIONS OLD WEATHER OPERATIONS If the aircraft is operated in cold weather conditions (from -25ºC till -5ºC) it is neces- sary to perform following procedures: Heat the cabin to +25ºC to avoid windshield frost in flight Heat the engines with external source to + 20º C Check the pressure in hydraulic system, recharge if necessary IRSPEEDS FOR NORMAL OPERATIONS The following airspeeds are those which are significant for normal operations.
Page 323 Page G7-14 IRCRAFT 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. Edition, Rev. 0 Section 9 – Supplements Supplement no. G7 – AFM Supplement for CIS countries operators...
Page 324 Page G7-15 OCKPIT INSPECTIONS Make sure that passengers are familiar with the safety belts and emer- gency exits employment and that they do not smoke on board. Passengers NOTE boarding, paying attention to the propeller disc, is under the pilot’s re- sponsibility.
Page 325 Page G7-16 AKEOFF AND CLIMB Call TWR for takeoff Check for clear final and wind on run- Direction and intensity LH and RH Electrical Fuel pump BOTH ON Carburettors heat CHECK OFF LH and RH Propeller Lever FULL FORWARD LH and RH Throttle Lever ...
Page 326 Page G7-17 ALKED LANDING LH and RH Throttle Lever FULL THROTTLE LH and RH Propeller Lever FULL FORWARD Speed Over 70 KIAS Flaps Landing gear Carburettor heat CHECK OFF LH and RH Electrical Fuel pump CHECK ON Edition, Rev. 0 Section 9 –...
Page 327 Page G7-18 PERFORMANCES AKEOFF PERFORMANCES Takeoff ground roll CONDITIONS:  Flaps: T/O  Throttle levers: FULL FORWARD  Runway: paved Figure 1 - Takeoff ground roll In case of headwind, the takeoff run decreases by 2.5m for each NOTE knot of wind (8 ft/kt). In case of tailwind, the takeoff run increases by 10m for each knot of wind (33 ft/kt).
Page 328 Page G7-19 Takeoff distance CONDITIONS:  Flaps: T/O  Throttle levers: FULL FORWARD  Runway: paved Figure 2 - Takeoff distance (50 ft. Obs) In case of headwind, the takeoff run decreases by 4m for each NOTE knot of wind (13 ft/kt). In case of tailwind, the takeoff run increases by 14m for each knot of wind (40 ft/kt).
Page 329 Page G7-20 CLIMB PERFORMANCE ONE ENGINE INOPERATIVE CONDITIONS:  AC Clean configuration  One engine inoperative  Max Cont. Power – Airspeed: Weight [kg] [KIAS] 1180 1080 Figure 3 – Rate of Climb (one engine inoperative) Edition, Rev. 0 Section 9 – Supplements Supplement no.
Page 330 Page G7-21 WEIGHT AND BALANCE For weight and balance, make reference to Section 6 of this Manual. Edition, Rev. 0 Section 9 – Supplements Supplement no. G7 – AFM Supplement for CIS countries operators...
Page 331 Page G7-22 SYSTEMS NSTRUMENTS PANEL Instruments panel (typical layout) Edition, Rev. 0 Section 9 – Supplements Supplement no. G7 – AFM Supplement for CIS countries operators...
Page 332 Page G7-23 Item Description GDU 1040 (PFD) GMA 1347 Compass A/P Programmer/Computer GDU 1040 (MFD) LH fuel quantity indicator LH R.P.M. Dual M.A.P. indicator RH R.P.M. RH fuel quantity indicator LH CHT RH CHT LH Oil Temperature RH Oil Temperature LH oil pressure RH oil pressure RH breakers panel...
Page 333 Page G7-24 Item Description RH Cross bus switch RH Field LH Cross bus switch Master switch RH Avionic switch LH Field LH Avionic switch Standby Airspeed indicator Side slip indicator LG control knob Voltammeter Indicator ADF control panel Cockpit light dimmer Cabin heat (warm air from RH engine) Avionics lights dimmer Cabin heat (warm air from LH engine)
Page 334 Page G8-1 . G8 UPPLEMENT NO BRAZILIAN AIRCRAFT FLIGHT MANUAL SUPPLEMENT (EASA APPROVED) Edition, Rev. 0 Section 9 – Supplements Supplement no. G8 – BRAZILIAN AFMS...
Page 335 Page G8-2 Record of Revisions EASA Approval Tecnam Approval Revised Description of or Under DOA page Revision Privileges See Note (*) Note (*): this Supplement has been originally issued on 4 March 2011, after EASA Third Country Validation process completion.
Page 336 Page G8-3 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: ................
Page 337 Page G8-4 INTRODUCTION This supplement applies for 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 Page G8-5 LIMITATIONS PPROVED FUEL AVGAS 100 LL (ASTM D910) PPROVED FUEL Use of automotive gasoline (MOGAS) is not allowed for op- CAUTION eration in Brazil. Use of Aviation Fuel Avgas 100LL results in greater wear of valve seats and greater combustion deposits inside cylinders due to higher lead content.
Page 339 Page G8-6 SYSTEMS OPERATION FOR AIRPLANES WITH AUTOPILOT IN- STALLED - Use of GPS for precision approach navigation mode is not allowed. - Use of GPS is prohibited as primary means for navigation. GPS is approved as supplemental means for navigation; - Navigation using of the GPS system as the source of information is limited to IFR en route, terminal area and non-precision approach mode;...
Page 340 Page G8-7 OPERATION FOR AIRPLANES WITHOUT AUTOPILOT IN- STALLED - Use of GPS for precision approach navigation mode is not allowed. - Use of GPS is prohibited as primary means for navigation. GPS is approved as supplemental means for navigation; - Use of GPS is prohibited for IFR in terminal area or in non-precision approach operations;...
Page 341 Page G8-8 LACARDS IN PORTUGUESE Description Placard Place Smoking ban Instruments panel, right side Engine On the engine na- level and speci- celle, in correspon- fications dence of the engine oil reservoir access door Fuel type and In correspondence quantity of each fuel tank filler cap.
Page 342 Page G8-9 Description Placard Place Ditching emer- Ditching emer- gency exit: gency exit handle: opening external side structions Ditching emer- Ditching emer- gency exit: gency exit handle: opening internal side structions Door locking Main door system: emergency exit: pass instruc- external side tions Door...
Page 343 Page G8-10 Description Placard Place Main door: exit Main door, internal instructions side Emergency exit Emergency exit: label internal and exter- nal side Towing maxi- Nose landing gear turning front door angle Edition, Rev. 0 Section 9 – Supplements Supplement no. G8 – BRAZILIAN AFMS...
Page 344 Page G9-1 . G9 UPPLEMENT NO CHINESE AIRCRAFT FLIGHT MANUAL SUPPLEMENT (EASA APPROVED) Edition, Rev. 0 Section 9 – Supplements Supplement no. G9 – CHINESE AFMS...
Page 345 Page G9-2 Record of Revisions EASA Approval Tecnam Approval Revised Description of or Under DOA page Revision Privileges Third Country P. Violetti First issue M. Oliva L. Pascale Validation List of Effective Pages Page Revision Page Revision Rev 0 Rev 0...
Page 346 Page G9-3 TABLE OF CONTENTS INTRODUCTION ...................... 4 GENERAL ........................ 4 LIMITATIONS ......................5 Approved fuel ......................5 Placards in Chinese ....................6 NORMAL OPERATIONS ..................10 Cold weather operations ..................10 Edition, Rev. 0 Section 9 – Supplements Supplement no. G9 – CHINESE AFMS...
Page 347 Page G9-4 INTRODUCTION This supplement applies 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 Page G9-5 LIMITATIONS PPROVED FUEL MOGAS compliant with PRC National Standard GB17930-2006 - Octane Rat- ing (RON) 97 MOGAS ASTM D4814 MOGAS EN 228 Super/Super plus (min. RON 95) AVGAS 100 LL (ASTM D910) 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.
Page 349 Page G9-6 LACARDS IN HINESE Description/Place Placard Chinese Smoking ban. 禁止吸烟 Instruments panel, right side Engine oil level and 滑油箱 specifications. 检查油位滑油油位最大 3Lt On the engine nacelle, OK 最低 2Lt in correspondence of the engine oil reser- 滑油油位超出限制时，禁止飞行。 voir access door 只允许使用API规定的或更高级别的滑油。...
Page 350 Page G9-7 Description/Place Placard Chinese Ditching emergency 水上迫降应急出口 exit: opening instruc- tions. 1、旋转。 2、平稳向外推。 Ditching emergency exit handle: internal side Ditching emergency 水上迫降应急出口 exit: opening instruc- tions. 1、旋转。 2、平稳向内拉。 Ditching emergency exit handle: external side Door locking system: 应急通道 by-pass instructions. 1、按住红色扭。...
Page 351 Page G9-8 Description/Place Placard Chinese Main door: exit in- 警告 structions. 打开门，向飞机前方撤离前，确认螺旋桨已经停止转动。 Main door, internal side Emergency exit label. 应急出口 Emergency exit: inter- nal and external side Maximum steering 注意 angle. 牵引最大转弯角度：中立两侧20度。 Front of the aircraft. Edition, Rev. 0 Section 9 –...
Page 352 Page G9-9 INTENTIONALLY LEFT BLANK Edition, Rev. 0 Section 9 – Supplements Supplement no. G9 – CHINESE AFMS...
Page 353 Page G9-10 NORMAL OPERATIONS OLD WEATHER OPERATIONS Engine cold weather operation Refer to Rotax 912 Series Operators Manual, last issue, providing instructions for operating media (lubricant and coolant specifications) to be used in cold weather operation. Parking When the airplane is parked in cold weather conditions and it is expected to be soaked at temperatures below freezing, some precautions need to be taken.
Page 354 Page G9-11 Preflight Flight in expected and/or known icing conditions is forbidden. WARNING An external inspection of the aircraft is performed before each flight, as prescribed on Section 4. For cold weather operations, the crew must focus on the check of following parts of airplane (free of snow/ice/standing water).
Page 355 Page G9-12 INTENTIONALLY LEFT BLANK Edition, Rev. 0 Section 9 – Supplements Supplement no. G9 – CHINESE AFMS...
Page 356 Page G11-1 . G11 – V UPPLEMENT NO NCREASE ECORD OF EVISIONS EASA Approval Tecnam Approval Revised Description of Or Under DOA page Revision Privileges EASA approval First issue M. Landi M. Oliva L. Pascale 10041602 Edition, Rev. 1 Section 9 - Supplements...
Page 357 Page G11-2 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 Edition, Rev. 1 Section 9 - Supplements Supplement no. G11 – Vlo/Vle Increase...
Page 358 This Supplement applies to aircraft 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.
Page 359 Page G11-4 SECTION 2 - LIMITATIONS EASA Approved Edition, Rev. 1 Section 9 - Supplements Supplement no. G11 – Vlo/Vle Increase...
Page 360 Page G11-5 PEED 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 = 122 KIAS EASA Approved Edition, Rev. 1 Section 9 - Supplements Supplement no.
Page 361 Page G11-6 INTENTIONALLY LEFT BLANK Edition, Rev. 1 Section 9 - Supplements Supplement no. G11 – Vlo/Vle Increase...
Page 362 Page G12-1 SUPPLEMENT NO. G12 – SOUTH AFRICAN AFM (SACAA APPROVED) Record of Revisions EASA Approval Tecnam Approval Revised Description of Or Under DOA page Revision Privileges 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 Page G12-2 LOEP Page Revision Page Revision Rev 0 Rev 0 G12-1 G12-5 Rev 0 Rev 0 G12-2 G12-6 Rev 0 Rev 0 G12-3 G12-7 Rev 0 Rev 0 G12-4 G12-8 Edition, Rev. 0 Section 9 – Supplements Supplement no. G12 – South African AFM...
Page 364 Page G12-3 TABLE 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: ................
Page 365 Page G12-4 INTRODUCTION This Supplement applies for South African registered aircraft It contains supplemental 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.
Page 366 Page G12-5 LIMITATIONS AXIMUM OPERATING ALTITUDE Maximum operating altitude is 14000 ft (4260 m) MSL. At altitudes between 10 000 feet (3048 m) and 12 000 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 CAUTION prescribed in Document SA-CATS 91 and such oxygen may be used continuous-...
Page 367 Page G12-6 SYSTEMS GPS GNS 430 GNS 530 OPERATION FOR AIRPLANES WITH AUTOPILOT INSTALLED - Use of GPS for precision approach navigation mode is not allowed. - Use of GPS is prohibited as primary means for navigation. GPS is approved as supplemental means for navigation;...
Page 368 Page G12-7 WAAS 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. Edition, Rev. 0 Section 9 – Supplements Supplement no. G12 – South African AFM...
Page 369 Page G10 - 8 INTENTIONALLY LEFT BLANK Edition, Rev. 0 Section 9 – Supplements Supplement no. G12 – South African AFM...
Page 370 Page G13-1 . G13 – A 70 A UPPLEMENT NO LTERNATORS WITH INSTALLATION Record of Revisions EASA Approval Tecnam Approval Revised Description of Or Under DOA page Revision Privileges See Note (*) List of Effective Pages Page Revision Page Revision...
Page 371 Page G13-2 INTRODUCTION This section contains supplemental information to operate, in a safe and efficient manner, the aircraft when 70A alternators are installed replacing the standard, 40A ones (Design Change MOD 2006/202). The information contained herein supplements or supersedes the basic Aircraft Flight Manual: detailed instructions are provided to allow the owner for replacing the AFM pages containing information amended as per the Design Change in sub- ject.
Page 372 Page G13-3 SECTION 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 ...
Page 373 Alternators with 70A - Supplement Page G13-4 Section 3 – Emergency INGLE ALTERNATOR FAILURE OVERVOLTAGE procedures Annunciation window Alert window INDEX L ALT FAIL Lh Alternator R ALT FAIL Rh Alternator 1. FIELD LH (or RH) 2. FIELD LH (or RH) If the LH (or RH) ALT caution stays displayed 3.
Page 374 Alternators with 70A - Supplement Page G13-5 Section 3 – OTH ALTERNATORS FAILURE Emergency Annunciation window Alert window procedures INDEX L ALT FAIL Lh Alternator R ALT FAIL Rh Alternator In event of both L and R ALT FAIL caution alerts displayed: 1.
Page 375 Alternators with 70A - Supplement Page G13-6 Section 3 – OTH ALTERNATORS OVERVOLTAGE Emergency procedures Annunciation window Alert window INDEX L BUS VOLT HIGH Lh overvoltage R BUS VOLT HIGH Rh overvoltage In event of both L and R BUS VOLT HIGH warning alerts displayed: 1.
Page 376 Alternators with 70A - Supplement Page G13-7 Section 3 – Emergency procedures INDEX INTENTIONALLY LEFT BLANK Edition, Rev. 0 Section 9 - Supplements Supplement no. G13 – Alternators with 70A installation...
Page 377 Page G14-1 . G14 - SMP UPPLEMENT NO FOR DIGITAL CONFIGURATION ECORD OF EVISIONS EASA Approval Tecnam Approval Revised Description of Or Under DOA page Revision Privileges First issue D. Ronca C. Caruso M. Oliva DOA Approval Ed.4, Rev.0 Section 9 - Supplements Supplement no.
Page 378 Page G14-2 LOEP Pages Revision G14 – 1 thru 23 Cover pages Rev. 0 SMP2 – 3 Section 2 Rev. 0 SSMP3 – 3 thru 5 Section 3 Rev. 0 SSMP3 – 7 thru 9 Rev. 0 SSMP3 – 21 Rev.
Page 379 NOTE 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.
Page 380 Page G14-4 INTENTIONALLY LEFT BLANK Ed.4, Rev.0 Section 9 - Supplements Supplement no. G14 – SMP FOR DIGITAL CONFIGURATION...
Page 381 Page G14-5 Supplement G14: pages replacement instructions 1 – GENERAL ECTION Apply following instruction: See Basic AFM - Section 1 Ed.4, Rev.0 Section 9 - Supplements Supplement no. G14 – SMP FOR DIGITAL CONFIGURATION...
Page 382 Page G14-6 INTENTIONALLY LEFT BLANK Ed.4, Rev.0 Section 9 - Supplements Supplement no. G14 – SMP FOR DIGITAL CONFIGURATION...
Page 383 Page G14-7 Supplement G14: pages replacement instructions 2 – LIMITATIONS ECTION Apply following pages replacement procedure: Supplement G14 - Basic AFM LIMITATIONS page Section 2 page SMP2 – 3 Page 2 – 3 of Basic AFM, Section 2 REPLACES Ed.4, Rev.0 Section 9 - Supplements Supplement no.
Page 384 Page G14-8 INTENTIONALLY LEFT BLANK Ed.4, Rev.0 Section 9 - Supplements Supplement no. G14 – SMP FOR DIGITAL CONFIGURATION...
Page 385 NTRODUCTION Section 2 includes operating limitations, instrument markings and basic placards necessary for safe operation of P2006T aircraft, its engines and standard systems and equipment. LH and RH AUX FIELDS, enabling the converter box operations for Special Mission purpos- es, should be kept OFF during take-off, climb, landing and any abnormal procedure that affects...
Page 386 Page G14-9 INTENTIONALLY LEFT BLANK Ed.4, Rev.0 Section 9 - Supplements Supplement no. G14 – SMP FOR DIGITAL CONFIGURATION...
Page 387 Page G14-10 Supplement G14: pages replacement instructions 3 – EMERGENCY PROCEDURES ECTION Apply following pages replacement procedure: Supplement G14 - Supplement G1 EMERGENCY Section 3 page PROCEDURES page SSMP3 – 3 thru 5 Page S3 – 3 thru 5 of Supplement G1, Section 3 REPLACE SSMP3 –...
Page 388 Page G14-11 INTENTIONALLY LEFT BLANK Ed.4, Rev.0 Section 9 - Supplements Supplement no. G14 – SMP FOR DIGITAL CONFIGURATION...
Page 389 GARMIN G950 IFDS – SMP FOR DIGITAL CONFIGURATION Page SMP3-3 1. I NTRODUCTION Section 3 includes checklists and detailed procedures for coping with various types of emergency conditions that could arise after a system failure. The procedures affected from installation of the Special Mission Platform are the following: ...
Page 390: Engine Failure During Takeoff Run
Additionally operating the aircraft, the pilot should become thoroughly familiar with the Garmin G950 Pilot’s Guide for Tecnam P2006T (P/N 190-01146-XX) – last issue - and, in particular, with the present AFM Section. Garmin G950 Pilot’s Guide for Tecnam P2006T (P/N 190- 01146-XX) –...
Page 391 GARMIN G950 IFDS – SMP FOR DIGITAL CONFIGURATION Page SMP3-5 In any 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.
Page 392 GARMIN G950 IFDS – SMP FOR DIGITAL CONFIGURATION Page SMP3-7 2.1. INGLE ALTERNATOR FAILURE OVERVOLTAGE Annunciation window Alert window L ALT FAIL Lh Alternator R ALT FAIL Rh Alternator 1. FIELD LH (or RH) 2. LH and RH AUX FIELD switch BOTH OFF 3.
Page 393 GARMIN G950 IFDS – SMP FOR DIGITAL CONFIGURATION Page SMP3-8 OTH ALTERNATORS FAILURE Annunciation window Alert window L ALT FAIL Lh Alternator R ALT FAIL Rh Alternator In event of both L and R ALT FAIL caution alerts displayed: 1. FIELD LH and RH BOTH OFF 2.
Page 394 GARMIN G950 IFDS – SMP FOR DIGITAL CONFIGURATION Page SMP3-9 OTH ALTERNATORS OVERVOLTAGE Annunciation window Alert window L BUS VOLT HIGH Lh overvoltage R BUS VOLT HIGH Rh overvoltage In event of both L and R BUS VOLT HIGH warning alerts displayed: 1.
Page 395 GARMIN G950 IFDS – SMP FOR DIGITAL CONFIGURATION Page SMP3-21 3. E NGINE SECURING Following procedure is applicable to shut-down one engine in flight: 1. Throttle Lever IDLE 2. Ignition BOTH OFF 3. Propeller Lever FEATHER 4. Fuel Selector 5. Electrical fuel pump 6.
Page 396 GARMIN G950 IFDS – SMP FOR DIGITAL CONFIGURATION Page SMP3-29 5. O THER EMERGENCIES MERGENCY DESCENT Descent with airspeed at VLE, idle power and gear down will ° provide high descent rates and pitch attitudes up to -15 Anticipate altitude capture and return to level flight during CAUTION emergency descent in order to assure a safe and smooth recov- ery from maneuver.
Page 397 GARMIN G950 IFDS – SMP FOR DIGITAL CONFIGURATION Page SMP3-36 NFLIGHT ENGINE RESTART After: mechanical engine seizure; fire; major propeller damage WARNING engine restart is not recommended. 1. Carburettor heat ON if required 2. Electrical fuel pump 3. Fuel quantity indicator CHECK 4.
Page 398 GARMIN G950 IFDS – SMP FOR DIGITAL CONFIGURATION Page SMP3-37 NGINE FAILURE DURING TAKEOFF RUN BEFORE ROTATION: ABORT TAKE OFF Throttle Lever BOTH IDLE Rudder Keep heading control Brakes As required When safely stopped: Failed Engine Ignition BOTH OFF Failed Engine Field LH and RH AUX FIELD switch BOTH OFF Failed Engine Electrical fuel pump...
Page 399 GARMIN G950 IFDS – SMP FOR DIGITAL CONFIGURATION Page SMP3-39 NGINE FAILURE DURING CLIMB Autopilot Heading Keep control using rudder and ailerons Attitude Reduce as appropriate to keep airspeed over 62 KIAS Operating engine Throttle Lever FULL THROTTLE Operating engine Propeller Lever FULL FORWARD Operative engine Electrical fuel pump Check ON...
Page 400 GARMIN G950 IFDS – SMP FOR DIGITAL CONFIGURATION Page SMP3-40 NGINE FAILURE IN FLIGHT Autopilot Heading Keep control using rudder and ailerons Attitude Adjust as appropriate to keep airspeed over 62 KIAS LH and RH AUX FIELD switch BOTH OFF Operating engine Monitor engine instruments Operative engine Electrical fuel pump...
Page 401 GARMIN G950 IFDS – SMP FOR DIGITAL CONFIGURATION Page SMP3-49 8 SMOKE AND FIRE OCCURRENCE NGINE FIRE ON THE GROUND Fuel Selectors BOTH OFF Ignitions ALL OFF LH and RH AUX FIELD switch BOTH OFF Electrical fuel pumps BOTH OFF Cabin heat and defrost MASTER SWITCH Parking Brake...
Page 402 GARMIN G950 IFDS – SMP FOR DIGITAL CONFIGURATION Page SMP3-50 NGINE FIRE DURING TAKEOFF RUN BEFORE ROTATION: ABORT TAKE OFF Throttle Lever BOTH IDLE Rudder Keep heading control Brakes As required With aircraft under control Fuel Selector BOTH OFF Ignitions ALL OFF LH and RH AUX FIELD switch BOTH OFF...
Page 403 GARMIN G950 IFDS – SMP FOR DIGITAL CONFIGURATION Page SMP3-51 At safe altitude LH and RH AUX FIELD switch BOTH OFF Cabin heat and defrost BOTH OFF Fire affected engine Fuel Selector Confirm and OFF Fire affected engine Ignitions Confirm and BOTH OFF Fire affected engine Electrical fuel pump Confirm and OFF Fire affected engine FIELD...
Page 404 GARMIN G950 IFDS – SMP FOR DIGITAL CONFIGURATION Page SMP3-52 NGINE FIRE IN FLIGHT Cabin heat and defrost BOTH OFF LH and RH AUX FIELD switch BOTH OFF Autopilot Fire affected engine Fuel Selector Confirm and OFF Fire affected engine Ignition Confirm and BOTH OFF Fire affected engine Throttle Lever Confirm and FULL FORWARD...
Page 405 GARMIN G950 IFDS – SMP FOR DIGITAL CONFIGURATION Page SMP3-53 LECTRICAL SMOKE IN CABIN DURING FLIGHT 1. Cabin ventilation OPEN 2. Emergency light 3. Standby attitude indicator switch 4. Gain VMC conditions as soon as possible In case of cockpit fire: 5.
Page 406 Page G14-12 INTENTIONALLY LEFT BLANK Ed.4, Rev.0 Section 9 - Supplements Supplement no. G14 – SMP FOR DIGITAL CONFIGURATION...
Page 407 Page G14-13 Supplement G14: pages replacement instructions 4 – NORMAL PROCEDURES ECTION Apply following pages replacement procedure: Supplement G14 - Supplement S1 NORMAL Section 4 page PROCEDURES page SSMP4 – 26 thru 27 Page S4 – 26 thru 27 of Supplement G1, Section 4 REPLACE Ed.4, Rev.0 Section 9 - Supplements...
Page 408 Page G14-14 INTENTIONALLY LEFT BLANK Ed.4, Rev.0 Section 9 - Supplements Supplement no. G14 – SMP FOR DIGITAL CONFIGURATION...
Page 409 GARMIN G950 IFDS – SMP FOR DIGITAL CONFIGURATION Page SSMP4-26 3.10 C RUISE LH and RH Propeller Lever SET to 1900-2250 RPM Throttles MAP decrease should be made before propeller speed reduction below 2200 RPM, as, contrariwise, Propeller Lever increase RPM should be set be- fore engine Throttle Levers are advanced.
Page 410 GARMIN G950 IFDS – SMP FOR DIGITAL CONFIGURATION Page SMP4-27 3.11 T URBULENT AIR OPERATION In keeping with good operating practice used in all aircraft, it is recommended that when turbulent air is encountered or expected, the airspeed be reduced to maneuvering speed to reduce the structural loads caused by gusts and to allow for inadvertent speed build-ups, which may occur as a result of the turbulence or of distractions caused by the conditions.
Page 411 NOTE 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.
Page 412 Page G14-16 INTENTIONALLY LEFT BLANK Ed.4, Rev.0 Section 9 - Supplements Supplement no. G14 – SMP FOR DIGITAL CONFIGURATION...
Page 413 Page G14-17 Supplement G14: pages replacement instructions 6 – WEIGHT AND BALANCE ECTION Apply following instruction: See Basic AFM - Section 6 Ed.4, Rev.0 Section 9 - Supplements Supplement no. G14 – SMP FOR DIGITAL CONFIGURATION...
Page 414 Page G14-18 INTENTIONALLY LEFT BLANK Ed.4, Rev.0 Section 9 - Supplements Supplement no. G14 – SMP FOR DIGITAL CONFIGURATION...
Page 415 Page G14-19 Supplement G14: pages replacement instructions 7 – AIRFRAME AND SYSTEMS DESCRIPTION ECTION Apply following pages replacement procedure: Supplement G14 - AIRFRAME AND Supplement S1 SYSTEMS Section 7 page DESCRIPTION page SSMP7 – 41 Page S7 – 41 of Supplement G1, Section 7 REPLACES SSMP7 –...
Page 416 Page G14-20 INTENTIONALLY LEFT BLANK Ed.4, Rev.0 Section 9 - Supplements Supplement no. G14 – SMP FOR DIGITAL CONFIGURATION...
Page 417 GARMIN G950 IFDS – SMP FOR DIGITAL CONFIGURATION Page SMP7-41 LECTRICAL SYSTEMS Primary DC power is provided by two engine-driven alternators which, during normal operations, operate in parallel. Each alternator is rated at 14,2-14,8 VDC, 70 Amp, and it is fitted with an exter- nal voltage regulator, which acts to maintain a constant output voltage, and with an automatic overvoltage device protecting the circuits and the electric compo- nents from an excessive voltage caused by alternator failures.
Page 418 The below figure presents the control panel for the built-in generators which in turn activate the converter box: Switches panels Next paragraph describes the converter and connector box installed in the P2006T baggage compartment floor. This box allows the operator to have a source of 28Volt/40Amp electrical power for different mission equipment.
Page 419 NOTE 14VDC GPU only can be used, as done on standard P2006T. the minimum GPU capacity to properly feed mission equipment should be at least 150Amp @14VDC The FIELD AUX switches needs to be "ON" to test converter box connected equipment, "OFF"...
Page 420 GARMIN G950 IFDS – SMP FOR DIGITAL CONFIGURATION Page SMP7-46 In the following figures the new Electrical system schematic is reported. Electrical system schematic (Page 1) Ed.4, Rev.0 Section 7 – Airframe and Systems description ELECTRICAL SYSTEM...
Page 421 GARMIN G950 IFDS – SMP FOR DIGITAL CONFIGURATION Page SMP7-47 Figure 25 – Electrical system schematic (Page 2) Electrical system schematic (Page 3) Ed.4, Rev.0 Section 7 – Airframe and Systems description ELECTRICAL SYSTEM...
Page 422 Page G14-21 INTENTIONALLY LEFT BLANK Ed.4, Rev.0 Section 9 - Supplements Supplement no. G14 – SMP FOR DIGITAL CONFIGURATION...
Page 423 Page G14-22 Supplement G14: pages replacement instructions 8 – GROUND HANDLING & SERVICE ECTION Apply following instruction: See Basic AFM - Section 8 Ed.4, Rev.0 Section 9 - Supplements Supplement no. G14 – SMP FOR DIGITAL CONFIGURATION...
Page 424 Page G14-23 INTENTIONALLY LEFT BLANK Ed.4, Rev.0 Section 9 - Supplements Supplement no. G14 – SMP FOR DIGITAL CONFIGURATION...
Page 425 Page G16-1 . G16 - MD302 A UPPLEMENT NO LTERNATIVE TAND NSTRUMENT ECORD OF EVISIONS EASA Approval Tecnam Approval Revised Description of Or Under DOA page Revision Privileges First issue D. Ronca C. Caruso M. Oliva DOA Approval Ed.4, Rev.0 Section 9 - Supplements Supplement no.
Page 426 Page G16-2 LOEP Pages Revision G16 – 1 thru 25 Cover pages Rev. 0 MD2 – 12 Section 2 Rev. 0 SMD3 – 15 thru 16 Section 3 Rev. 0 SMD3 – 30 Rev. 0 SMD4 – 15 Section 4 Rev.
Page 427 Page G16-3 INTRODUCTION This section contains supplemental information to operate, in a safe and efficient manner, the aircraft when equipped with Garmin G950 Integrated Flight Deck Sys- tem (Design Change MOD 2006/002) and with MD302. The MD302 refers to the following design change: ...
Page 428 Page G16-4 INTENTIONALLY LEFT BLANK Ed.4, Rev.0 Section 9 - Supplements Supplement no. G16 – MD302 A LTERNATIVE TAND NSTRUMENT...
Page 429 Page G16-5 Supplement G16: pages replacement instructions 1 – GENERAL ECTION Apply following instruction: See Basic AFM - Section 1 Ed.4, Rev.0 Section 9 - Supplements Supplement no. G16 – MD302 A LTERNATIVE TAND NSTRUMENT...
Page 430 Page G16-6 INTENTIONALLY LEFT BLANK Ed.4, Rev.0 Section 9 - Supplements Supplement no. G16 – MD302 A LTERNATIVE TAND NSTRUMENT...
Page 431 Page G16-7 Supplement G16: pages replacement instructions 2 – LIMITATIONS ECTION Apply following pages replacement procedure: Supplement G16 - Basic AFM LIMITATIONS page Section 2 page MD2 – 12 Page 2 – 12 of Basic AFM, Section 2 REPLACES Ed.4, Rev.0 Section 9 - Supplements Supplement no.
Page 432 Page G16-8 INTENTIONALLY LEFT BLANK Ed.4, Rev.0 Section 9 - Supplements Supplement no. G16 – MD302 A LTERNATIVE TAND NSTRUMENT...
Page 433 MD302 A LTERNATIVE TAND NSTRUMENT Page MD2-12 11. P OWERPLANT INSTRUMENTS MARKINGS Powerplant instrument markings and their colour code significance are shown below: RED LINE GREEN ARC YELLOW ARC RED LINE Minimum limit Normal Caution Maximum limit NSTRUMENT operating Propeller ---- 580 - 2265 2265 - 2388...
Page 434 Page G16-9 INTENTIONALLY LEFT BLANK EASA Approved Ed.4, Rev.0 Section 2 – Limitations Supplement no. G16 – MD302 A LTERNATIVE TAND NSTRUMENT...
Page 435 Page G16-10 Supplement G16: pages replacement instructions 3 – EMERGENCY PROCEDURES ECTION Apply following pages replacement procedure: Supplement G16 - Supplement S1 EMERGENCY Section 3 page PROCEDURES page MD3 – 15 thru 16 Page 3 – 15 thru 16 of Supplement S1, Section 3 REPLACE MD3 –...
Page 436 Page G16-11 INTENTIONALLY LEFT BLANK Ed.4, Rev.0 Section 9 - Supplements Supplement no. G16 – MD302 A LTERNATIVE TAND NSTRUMENT...
Page 437 NOTE 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.
Page 438 GARMIN G950 IFDS – MD302 A LTERNATIVE TAND NSTRUMENT Page MD3-16 2.10 L OSS OF ATTITUDE INFORMATION ATTITUDE FAIL ON DISPLAY FIELD Display system is not receiving attitude information from the AHRS. INSTRUCTION: revert to stand-by attitude indicator 2.11 L OSS OF ALTITUDE INFORMATION ALTITUDE FAIL ON DISPLAY FIELD...
Page 439 GARMIN G950 IFDS – MD302 A LTERNATIVE TAND NSTRUMENT Page MD3-30 MD 302 BATTERY FAILURE The MD302 internal battery will recharge itself from aircraft power while in normal mode. A battery capacity check occurs each time the unit is powered on. If the battery capacity is determined to be less than 80%, WARNING there will be a battery pack warning.
Page 440 Page G16-12 INTENTIONALLY LEFT BLANK Ed.4, Rev.0 Section 9 - Supplements Supplement no. G16 – MD302 A LTERNATIVE TAND NSTRUMENT...
Page 441 Page G16-13 Supplement G16: pages replacement instructions 4 – NORMAL PROCEDURES ECTION Apply following pages replacement procedure: Supplement G16 - Supplement S1 NORMAL Section 4 page PROCEDURES page SMD4 – 15 Page 4 – 15 Supplement S1, Section 4 REPLACES Ed.4, Rev.0 Section 9 - Supplements Supplement no.
Page 442 Page G16-14 INTENTIONALLY LEFT BLANK Ed.4, Rev.0 Section 9 - Supplements Supplement no. G16 – MD302 A LTERNATIVE TAND NSTRUMENT...
Page 443 GARMIN G950 IFDS – MD302 A LTERNATIVE TAND NSTRUMENT Page MD4-15 MD302 system use “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 WARNING attached to this AFM and kept onboard the aircraft.
Page 444 Page G16-15 INTENTIONALLY LEFT BLANK Ed.4, Rev.0 Section 9 - Supplements Supplement no. G16 – MD302 A LTERNATIVE TAND NSTRUMENT...
Page 445 Page G16-16 Supplement G16: pages replacement instructions 5 – PERFORMANCE ECTION Apply following instruction: See Basic AFM - Section 5 Ed.4, Rev.0 Section 9 - Supplements Supplement no. G16 – MD302 A LTERNATIVE TAND NSTRUMENT...
Page 446 Page G16-17 INTENTIONALLY LEFT BLANK Ed.4, Rev.0 Section 9 - Supplements Supplement no. G16 – MD302 A LTERNATIVE TAND NSTRUMENT...
Page 447 Page G16-18 Supplement G16: pages replacement instructions 6 – WEIGHT AND BALANCE ECTION Apply following instruction: Supplement G16 - Basic AFM WEIGHT AND Section 6 page BALANCE page MD6 – 11 Page 6 – 11 of Basic AFM, Section 6 REPLACES Ed.4, Rev.0 Section 9 - Supplements...
Page 448 Page G16-19 INTENTIONALLY LEFT BLANK Ed.4, Rev.0 Section 9 - Supplements Supplement no. G16 – MD302 A LTERNATIVE TAND NSTRUMENT...
Page 449 MD302 A LTERNATIVE TAND NSTRUMENT Page MD6-11 _____ QUIPMENT LIST IRCRAFT S EIGHT ESCRIPTION INSTRUMENTATION GARMIN G950 IFDS SOFTWARE SD CARD P/N 0.37 airspeed indicator – UMA T6-311 – 200 -1.4 0.37 airspeed indicator - UMA T6-311 – -1.4 attitude indicator - Kelly Manufacturing -1.4 RCA26AK-3 altimeter - Altimeter - United Instruments...
Page 450 Page G16-20 INTENTIONALLY LEFT BLANK Ed.4, Rev.0 Section 6 – Weight and balance Supplement no. G16 – MD302 A LTERNATIVE TAND NSTRUMENT...
Page 451 Page G16-21 Supplement G16: pages replacement instructions 7 – AIRFRAME AND SYSTEMS DESCRIPTION ECTION Apply following pages replacement procedure: Supplement G16 - Basis AFM/Supplement S1 AIRFRAME AND Section 7 SYSTEM DESCRIPTION page page MD7 – 29 Page 7 – 29 of Basic AFM, Section 7 REPLACES SMD7 –...
Page 452 Page G16-22 INTENTIONALLY LEFT BLANK Ed.4, Rev.0 Section 9 - Supplements Supplement no. G16 – MD302 A LTERNATIVE TAND NSTRUMENT...
Page 453 16. MD302 A LTERNATIVE TAND NSTRUMENT In order to improve the digital version cockpit layout of the P2006T in terms of human-machine interface, weight saving and reliability this backup instrument V.1.0.5 is installed. For more details refer to MOD2006/212. All MD302 Stand-by Attitude Module settings, set up during the aircraft delivery or after a maintenance activity, must not be modified.
Page 454 GARMIN G950 IFDS – MD302 A LTERNATIVE TAND NSTRUMENT Page SMD7-37 17. INSTRUMENTS PANEL GARMIN G950 IFDS - Instruments panel (typical layout) GARMIN G950 IFDS - Instruments panel - layout with MD302 digital stand-by instrument(MOD2006/212) Ed.4, Rev.0 Section 7 – Airframe and Systems description INSTRUMENT PANEL...
Page 455 GARMIN G950 IFDS – MD302 A LTERNATIVE TAND NSTRUMENT Page SMD7-39 Item Description RH Field LH Cross bus switch Master switch RH Avionic switch LH Field LH Avionic switch Standby Airspeed indicator Chronometer LG control knob Voltammeter Indicator ADF control panel Cockpit light dimmer Cabin heat (warm air from RH engine) Avionics lights dimmer...
Page 456 Page G16-23 INTENTIONALLY LEFT BLANK Ed.4, Rev.0 Section 9 - Supplements Supplement no. G16 – MD302 A LTERNATIVE TAND NSTRUMENT...
Page 457 Page G16-24 Supplement G16: pages replacement instructions 8 – GROUND HANDLING & SERVICE ECTION Apply following instruction: See Basic AFM - Section 8 Ed.4, Rev.0 Section 9 - Supplements Supplement no. G16 – MD302 A LTERNATIVE TAND NSTRUMENT...
Page 458 Page G16-25 INTENTIONALLY LEFT BLANK Ed.4, Rev.0 Section 9 - Supplements Supplement no. G16 – MD302 A LTERNATIVE TAND NSTRUMENT...
Page 459 Page G17-1 . G17 - S UPPLEMENT NO TORMSCOPE ECORD OF EVISIONS EASA Approval Tecnam Approval Revised Description of Or Under DOA page Revision Privileges First issue D. Ronca C. Caruso M. Oliva DOA Approval Ed.4, Rev.0 Section 9 - Supplements...
Page 460 Page G17-2 LOEP Pages Revision G17 – 1 thru 21 Cover pages Rev. 0 ST1 – 9 Section 1 Rev. 0 ST6 – 12 Section 6 Rev. 0 ST7 – 46 Section 7 Rev. 0 Ed.4, Rev.0 Section 9 - Supplements Supplement no.
Page 461 Page G17-3 INTRODUCTION This section contains supplemental information to operate, in a safe and efficient manner, the aircraft when equipped with WX500 Stormscope; this equipment refers to the following design change:  MOD2006/216 – 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.
Page 462 Page G17-4 INTENTIONALLY LEFT BLANK Ed.4, Rev.0 Section 9 - Supplements Supplement no. G17 – STORMSCOPE...
Page 463 Page G17-5 Supplement G17: pages replacement instructions 1 – GENERAL ECTION Apply following instruction: See Basic AFM - Section 1 Ed.4, Rev.0 Section 9 - Supplements Supplement no. G17 – STORMSCOPE...
Page 464 Page G17-6 INTENTIONALLY LEFT BLANK Ed.4, Rev.0 Section 9 - Supplements Supplement no. G17 – STORMSCOPE...
Page 465 TORMSCOPE Page ST1-9 The Stormscope does neither replace a weather radar nor NOTE weather information. The Stormscope is only used as an additional source of information beside approved weather information. Ed.4, Rev.0 Section 1 - General GENERAL FEATURES...
Page 466 Page G17-7 INTENTIONALLY LEFT BLANK Ed.4, Rev.0 Section 9 - Supplements Supplement no. G17 – STORMSCOPE...
Page 467 Page G17-8 Supplement G17: pages replacement instructions 2 – LIMITATIONS ECTION Apply following instruction: See Basic AFM and Supplement S1 - Section 2 Ed.4, Rev.0 Section 9 - Supplements Supplement no. G17 – STORMSCOPE...
Page 468 Page G17-9 INTENTIONALLY LEFT BLANK Ed.4, Rev.0 Section 9 - Supplements Supplement no. G17 – STORMSCOPE...
Page 469 Page G17-10 Supplement G17: pages replacement instructions 3 – EMERGENCY PROCEDURES ECTION Apply following instruction: See Supplement S1 - Section 3 Ed.4, Rev.0 Section 9 - Supplements Supplement no. G17 – STORMSCOPE...
Page 470 Page G17-11 INTENTIONALLY LEFT BLANK Ed.4, Rev.0 Section 9 - Supplements Supplement no. G17 – STORMSCOPE...
Page 471 Page G17-12 Supplement G17: pages replacement instructions 4 – NORMAL PROCEDURES ECTION Apply following instruction: See Supplement S1 - Section 4 Ed.4, Rev.0 Section 9 - Supplements Supplement no. G17 – STORMSCOPE...
Page 472 Page G17-13 INTENTIONALLY LEFT BLANK Ed.4, Rev.0 Section 9 - Supplements Supplement no. G17 – STORMSCOPE...
Page 473 Page G17-14 Supplement G17: pages replacement instructions 5 – PERFORMANCES ECTION Apply following instruction: See Basic AFM - Section 5 Ed.4, Rev.0 Section 9 – Supplements Supplement no. G17 – STORMSCOPE...
Page 474 Page G17-15 INTENTIONALLY LEFT BLANK Ed.4, Rev.0 Section 9 – Supplements Supplement no. G17 – STORMSCOPE...
Page 475 Page G17-14 Supplement G17: pages replacement instructions 6 – WEIGHT AND BALANCE ECTION Apply following instruction: Supplement G17 - Basic AFM WEIGHT AND Section 6 BALANCE page page ST6 – 12 Page 6 – 12 of Basic AFM, Section 6 REPLACES Ed.4, Rev.0 Section 9 –...
Page 476 Page G17-15 INTENTIONALLY LEFT BLANK Ed.4, Rev.0 Section 9 – Supplements Supplement no. G17 – STORMSCOPE...
Page 477 TORMSCOPE Page ST6-12 _____ QUIPMENT LIST IRCRAFT S EIGHT ESCRIPTION ’ AVIONICS & MISCELLANEOUS ( CONT -1.4 Indicator KI 229 Static inverter Marathon PC-50 HONEYWELL Bendix/King DME KN 63 system Indicator DME KDI 572 -1.4 Transceiver DME KN 63 S-TEC Fifty Five X Autopilot System Turn coordinator S-TEC 6405-14L 0.81 -1.4...
Page 478 Page G17-16 INTENTIONALLY LEFT BLANK Ed.4, Rev.0 Section 6 – Weight and balance Supplement no. G17 – STORMSCOPE...
Page 479 Page G17-17 Supplement G17: pages replacement instructions 7 – AIRFRAME AND SYSTEMS DESCRIPTION ECTION Apply following instruction: Supplement G17 - Supplement S1 AIRFRAME AND Section 7 SYSTEM DESCRIPTION page page ST7 – 46 Page 7 – 46 of Supplement S1, Section 7 REPLACES Ed.4, Rev.0 Section 6 –...
Page 480 Page G17-18 INTENTIONALLY LEFT BLANK Ed.4, Rev.0 Section 6 – Weight and balance Supplement no. G17 – STORMSCOPE...
Page 481 TORMSCOPE Page ST7-46 19. WX500 S 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.
Page 482 Page G17-19 INTENTIONALLY LEFT BLANK Ed.4, Rev.0 Section 9 - Supplements Supplement no. G17 – STORMSCOPE...
Page 483 Page G17-20 Supplement G17: pages replacement instructions 8 – GROUND HANDLING & SERVICE ECTION Apply following instruction: See Basic AFM - Section 8 Ed.4, Rev.0 Section 9 - Supplements Supplement no. G17 – STORMSCOPE...
Page 484 Page G17-21 INTENTIONALLY LEFT BLANK Ed.4, Rev.0 Section 9 - Supplements Supplement no. G17 – STORMSCOPE...
Page 485 Page G18-1 . G18 – O UPPLEMENT NO IL TEMPERATURE INDICATOR UPDATE ECORD OF EVISIONS EASA Approval Tecnam Approval Revised Description of Or Under DOA page Revision Privileges First issue D. Ronca C. Caruso M. Oliva DOA Approval Ed.4, Rev.0 Section 9 - Supplements Supplement no.
Page 486 Page G18-2 LOEP Pages Revision Cover pages G18 – 1 thru 22 Rev. 0 OT2 – 12 Rev. 0 Section 2 Section 4 SOT4 – 26 Rev. 0 Ed.4, Rev.0 Section 9 - Supplements Supplement no. G18 – OIL TEMPERATURE INDICATOR UPDATE...
Page 487 Page G18-3 INTRODUCTION This section contains supplemental information to operate, in a safe and efficient manner, the aircraft when equipped with Garmin G950 Integrated Flight Deck Sys- tem (Design Change MOD 2006/002) and with an update of the Oil temperature in- dicator.
Page 488 Page G18-4 INTENTIONALLY LEFT BLANK Ed.4, Rev.0 Section 9 - Supplements Supplement no. G18 – OIL TEMPERATURE INDICATOR UPDATE...
Page 489 Page G18-5 Supplement G18: pages replacement instructions 1 – GENERAL ECTION Apply following instruction: See Basic AFM - Section 1 Ed.4, Rev.0 Section 9 - Supplements Supplement no. G18 – OIL TEMPERATURE INDICATOR UPDATE...
Page 490 Page G18-6 INTENTIONALLY LEFT BLANK Ed.4, Rev.0 Section 9 - Supplements Supplement no. G18 – OIL TEMPERATURE INDICATOR UPDATE...
Page 491 Page G18-7 Supplement G18: pages replacement instructions 2 – LIMITATIONS ECTION Apply following pages replacement procedure: Supplement G18 - Basic AFM LIMITATIONS page Section 2 page OT2 – 12 Page 2 – 12 of Basic AFM, Section 2 REPLACES Ed.4, Rev.0 Section 9 - Supplements Supplement no.
Page 492 Page G18-8 INTENTIONALLY LEFT BLANK Ed.4, Rev.0 Section 9 - Supplements Supplement no. G18 – OIL TEMPERATURE INDICATOR UPDATE...
Page 493 IL TEMPERATURE INDICATOR UPDATE Page OT2-12 11. P OWERPLANT INSTRUMENTS MARKINGS Powerplant instrument markings and their colour code significance are shown below: RED LINE GREEN ARC YELLOW ARC RED LINE Minimum limit Normal Caution Maximum limit NSTRUMENT operating Propeller ---- 580 - 2265 2265 - 2388 2388...
Page 494 Page G18-9 INTENTIONALLY LEFT BLANK Ed.4, Rev.0 Section 2 – Limitations Supplement no. G18 – OIL TEMPERATURE INDICATOR UPDATE...
Page 495 Page G18-10 Supplement G18: pages replacement instructions 3 – EMERGENCY PROCEDURES ECTION Apply following instruction: See Basic AFM - Section 3 Ed.4, Rev.0 Section 9 - Supplements Supplement no. G18 – OIL TEMPERATURE INDICATOR UPDATE...
Page 496 Page G18-11 INTENTIONALLY LEFT BLANK Ed.4, Rev.0 Section 9 - Supplements Supplement no. G18 – OIL TEMPERATURE INDICATOR UPDATE...
Page 497 Page G18-12 Supplement G18: pages replacement instructions 4 – NORMAL PROCEDURES ECTION Apply following pages replacement procedure: Supplement G18 - Supplement S1 NORMAL Section 4 page PROCEDURES page SOT4 – 26 Page 4 – 26 of Supplement S1, Section 4 REPLACES Ed.4, Rev.0 Section 9 - Supplements...
Page 498 Page G18-13 INTENTIONALLY LEFT BLANK Ed.4, Rev.0 Section 9 - Supplements Supplement no. G18 – OIL TEMPERATURE INDICATOR UPDATE...
Page 499 IL TEMPERATURE INDICATOR UPDATE Page SOT4-26 3.10 RUISE LH and RH Propeller Lever SET to 1900-2250 RPM Throttles MAP decrease should be made before propeller speed reduction below 2200 RPM, as, contrariwise, Propeller Lever increase RPM should be set be- fore engine Throttle Levers are advanced.
Page 500 Page G18-14 INTENTIONALLY LEFT BLANK Ed.4, Rev.0 Section 9 - Supplements Supplement no. G18 – OIL TEMPERATURE INDICATOR UPDATE...
Page 501 Page G18-15 Supplement G18: pages replacement instructions 5 – PERFORMANCE ECTION Apply following instruction: See Basic AFM - Section 5 Ed.4, Rev.0 Section 9 - Supplements Supplement no. G18 – OIL TEMPERATURE INDICATOR UPDATE...
Page 502 Page G18-16 INTENTIONALLY LEFT BLANK Ed.4, Rev.0 Section 9 - Supplements Supplement no. G18 – OIL TEMPERATURE INDICATOR UPDATE...
Page 503 Page G18-17 Supplement G18: pages replacement instructions 6 – WEIGHT AND BALANCE ECTION Apply following instruction: See Basic AFM - Section 6 Ed.4, Rev.0 Section 9 - Supplements Supplement no. G18 – OIL TEMPERATURE INDICATOR UPDATE...
Page 504 Page G18-18 INTENTIONALLY LEFT BLANK Ed.4, Rev.0 Section 6 – Weight and balance Supplement no. G18 – OIL TEMPERATURE INDICATOR UPDATE...
Page 505 Page G18-19 Supplement G18: pages replacement instructions 7 – AIRFRAME AND SYSTEMS DESCRIPTION ECTION Apply following instruction: See Basic AFM - Section 7 Ed.4, Rev.0 Section 9 - Supplements Supplement no. G18 – OIL TEMPERATURE INDICATOR UPDATE...
Page 506 Page G18-20 INTENTIONALLY LEFT BLANK Ed.4, Rev.0 Section 9 - Supplements Supplement no. G18 – OIL TEMPERATURE INDICATOR UPDATE...
Page 507 Page G18-21 Supplement G18: pages replacement instructions 8 – GROUND HANDLING & SERVICE ECTION Apply following instruction: See Basic AFM - Section 8 Ed.4, Rev.0 Section 9 - Supplements Supplement no. G18 – OIL TEMPERATURE INDICATOR UPDATE...
Page 508 Page G18-22 INTENTIONALLY LEFT BLANK Ed.4, Rev.0 Section 9 - Supplements Supplement no. G18 – OIL TEMPERATURE INDICATOR UPDATE...

Tecnam P2006T Aircraft Flight Manual

Introduction

Limitations

Emergency Procedures

Normal Operations

Weight and Balance

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Summary of Contents for Tecnam P2006T

Table of Contents