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P2006T - Aircraft Flight Manual

M

:

ANUFACTURER

COSTRUZIONI AERONAUTICHE

A

: P2006T

IRCRAFT MODEL

EASA T

C

YPE

ERTIFICATE

: ................................

S

ERIAL NUMBER

: ......................................

B

UILD YEAR

R

EGISTRATION MARKINGS

This Aircraft Flight Manual is approved by European Aviation Safety Agency

(EASA).

This Manual contains information required by the FAA to be furnished to the pilot

for operation in the U.S.A. plus information supplied by the manufacturer. It is

approved by EASA on behalf of the FAA per FAR 21.29.

This Manual must be carried in the airplane at all times.

The airplane has to be operated in compliance with procedures and limitations

contained herein.

Costruzioni Aeronautiche TECNAM S.p.A.

Via Maiorise

CAPUA (CE) – Italy

Tel. +39 (0) 823.62.01.34

WEB:

www.tecnam.com

Aircraft Flight Manual

Doc. No. 2006/044

Edition – Rev. 22

th

4

September 11, 2024

TECNAM P2006T

TECNAM

N

: A .185 (

O

DATED

: ..................

S.p.A.

TH

2009, J

5

)

UNE

Page 0 - 1

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Page 1 P2006T - Aircraft Flight Manual Page 0 - 1 Aircraft Flight Manual Doc. No. 2006/044 Edition – Rev. 22 September 11, 2024 TECNAM P2006T TECNAM ANUFACTURER S.p.A. COSTRUZIONI AERONAUTICHE : P2006T IRCRAFT MODEL EASA T : A .185 ( 2009, J...
Page 2 P2006T - Aircraft Flight Manual 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: Record Of Revisions
P2006T - Aircraft Flight Manual 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.
Page 4 P2006T - Aircraft Flight Manual Page 0 - 4 EASA Approval or Tecnam Approval Revised Description of Under DOA page Revision Privileges First issue D. Ronca M. Oliva M. Oliva 0-4,8 Amended ROR and LOEP Approved under the au- thority of DOA,...
Page 5 P2006T - Aircraft Flight Manual Page 0 - 5 EASA Approval or Revised Description of Tecnam Approval Under DOA page Revision Privileges 0-1, 5, 7 Amended. Blank page added. Typo in stabilator deflections values corrected. Reference to Oil Temp. Indicator...
Page 6 P2006T - Aircraft Flight Manual Page 0 - 6 EASA Approval or Revised Description of Tecnam Approval Under DOA page Revision Privileges Cover pages, ROR and LOEP 0-1, 6, 7 Updated and typo errors Update “Engine starting” checklist 4-16, 17...
Page 7 P2006T - Aircraft Flight Manual Page 0 - 7 EASA Approval or Revised Description of Tecnam Approval Under DOA page Revision Privileges Cover pages, ROR and LOEP 0-1, 7, 8 Approved under the au- Updated thority of DOA, F. Paloni D.
Page 8 P2006T - Aircraft Flight Manual Page 0 - 8 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.
Page 9 P2006T - Aircraft Flight Manual Page 0 - 9 INTENTIONALLY LEFT BLANK Edition - Rev. 0 Aircraft Flight Manual...
Page 10 P2006T - Aircraft Flight Manual 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.
Page 11: Sections List
P2006T - Aircraft Flight Manual Page 0 - 11 4. SECTIONS LIST General Section 1 (a non-approved Chapter) Limitations Section 2 - EASA Approved Chapter Emergency Procedures Section 3 (a non-approved Chapter) Normal Procedures Section 4 (a non-approved Chapter) Performances...
Page 12 P2006T - Aircraft Flight Manual Page 0 - 12 INTENTIONALLY LEFT BLANK Edition - Rev. 5 Aircraft Flight Manual...
Page 13 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.
Page 14 Page 1 - 2 INTENTIONALLY LEFT BLANK Edition, Rev 0 Section 1 – General...
Page 15 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 16 Page 1 - 4 2. T HREE VIEW AND DIMENSIONS Figure 1 – General views Edition, Rev 0 Section 1 – General THREE-VIEW AND DIMENSIONS...
Page 17 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 18: General Features
Page 1 - 6 3. C ONTROL URFACES RAVEL IMITS Ailerons Up 20° Down 17 ° (± 2°) Stabilator (refer to Trailing Edge) Up 15° Down 4° (± 2°) Stabilator trim tab (refer to Trailing Edge) Up 2°; Down 19° (± 2°) Rudder RH 26°...
Page 19 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 20: Standard Weights
Page 1 - 8 9. C OOLING Ram-air cooled cylinders, liquid Cooling system 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.
Page 21 Page 1 - 9 INTENTIONALLY LEFT BLANK Edition, Rev 0 Section 1 – General GENERAL FEATURES...
Page 22 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 23 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 24 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. Usable fuel is the fuel available for flight planning. Unusable fuel is the quantity of fuel that cannot be safely used in flight.
Page 25 Maximum Landing Weight is the maximum weight approved for the landing touchdown (for P2006T it is equiv- alent to the Maximum Takeoff Weight). Edition, Rev 0 Section 1 – General ACRONYMS AND TERMINOLOGYACRONYMS AND...
Page 26 Page 1 - 14 INTENTIONALLY LEFT BLANK Edition, Rev 0 Section 1 – General...
Page 27: 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 [kg] PEED...
Page 28 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...
Page 29 Page 1 - 17 INTENTIONALLY LEFT BLANK Edition, Rev 0 Section 1 – General...
Page 30 Page 1 - 18 INTENTIONALLY LEFT BLANK Edition, Rev 0 Section 1 – General...
Page 31 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 ..................
Page 32 Page 2 - 2 INTENTIONALLY LEFT BLANK Edition, Rev. 0 Section 2 – Limitations...
Page 33 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 –...
Page 34 Page 2 - 4 INTENTIONALLY LEFT BLANK Edition, Rev. 0 Section 2 – Limitations...
Page 35: Speed Limitations
Page 2 - 5 2. S PEED LIMITATIONS The following table addresses the airspeed limitations and their operational signifi- cance: SPEED KIAS KCAS REMARKS V NE Never exceed speed Do not exceed this speed in any operation. V NO Maximum Structural Cruising Do not exceed this speed Speed except in smooth air, and...
Page 36 Page 2 - 6 INTENTIONALLY LEFT BLANK Edition, Rev. 0 Section 2 – Limitations...
Page 37 Page 2 - 7 3. A IRSPEED INDICATOR MARKINGS Airspeed indicator markings and their colour code are explained in the following table. MARKING KIAS EXPLANATION White arc 53-93 Lower limit is V , upper limit is the maxi- mum allowable speed with flaps extended in FULL position.
Page 38 Page 2 - 8 INTENTIONALLY LEFT BLANK Edition, Rev. 0 Section 2 – Limitations...
Page 39: Powerplant Limitations
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) Max.
Page 40 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. 893110,893114 or 893115. 5. L UBRICANT Use only oil with API classification “SG” or higher. For additional info, refer to “Rotax Operators Manual”...
Page 41: Ambient Temperature
Page 2 - 11 9. M AXIMUM OPERATING ALTITUDE Maximum operating altitude is 14000 ft (4260 m) MSL. Flight crew is required to use supplemental oxygen according to applicable Air Operation Rules. CAUTION 10. A MBIENT TEMPERATURE Ambient temperature: from -25°C (-13° F) to +50°C (122° F). Flight in expected and/or known icing conditions is forbidden.
Page 42 Page 2 - 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 Normal Caution Maximum NSTRUMENT limit operating limit Propeller ---- 580 - 2265 2265 - 2388 2388 50 –...
Page 43 Page 2 - 13 13. W ARNINGS CAUTIONS AND ADVISORIES LIGHTS Following table addresses the warning, caution and advisory lights installed (unless differently specified) on the annunciator panel: Warnings (RED) Cause LH OVERVOLT LH electric system overvoltage RH OVERVOLT RH electric system overvoltage MAIN DOOR OPEN ALERT Main door open and/or unlocked REAR DOOR OPEN ALERT...
Page 44 Page 2 - 14 INTENTIONALLY LEFT BLANK Edition, Rev. 0 Section 2 – Limitations...
Page 45 Page 2 - 15 14. W EIGHTS Condition Weight Maximum takeoff weight 1180 kg 2601 lb Maximum landing weight 1180 kg 2601 lb Maximum zero wing fuel weight 1145 kg 2524 lb Refer to Para. 21.4 of this AFM Section for baggage loading limitations. NOTE EASA Approved Edition, Rev.
Page 46 Page 2 - 16 INTENTIONALLY LEFT BLANK Edition, Rev. 0 Section 2 – Limitations...
Page 47: Center Of Gravity Range
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 (0.725 ft) (16.5% MAC) aft of datum for all weights up to 1230 kg / 2712 lb...
Page 48 Page 2 - 18 INTENTIONALLY LEFT BLANK Edition, Rev. 0 Section 2 – Limitations...
Page 49: Approved Maneuvers
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 Turns in which the angle of bank is not more than 60°...
Page 50: Flight Conditions
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 severe turbulence is forbidden.
Page 51: Limitations Placards
Page 2 - 21 21. L IMITATIONS PLACARDS Hereinafter the placards, related to the operating limitations and installed on P2006T, are reported. 21.1. PEED LIMITATIONS On the left side instrument panel, above on the left, it is placed the following plac-...
Page 52: Operating Limitations
Page 2 - 22 21.2. 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 53: Inflight Engine Restart
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 54: Engine Oil Level
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 55 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 56: Rear Seats
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 57: Other Placards
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-...
Page 58 Page 2 - 28 INTENTIONALLY LEFT BLANK Edition, Rev. 0 Section 2 – Limitations Edition, Rev.0...
Page 59 Page 2 - 29 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. Flight in VFR Day and Night, IFR Day and Night is permitted only if the pre- scribed equipment is installed and operational.
Page 60 Page 2 - 30 Equipment VFR Day VFR Night IFR Day IFR Night ● ● ● ● Magnetic compass ● ● ● ● Airspeed indicator ● ● ● ● Altimeter ● ● ● ● Vertical speed indicator ● ● ● ●...
Page 61 Page 2 - 31 INTENTIONALLY LEFT BLANK Edition, Rev. 0 Section 2 – Limitations...
Page 62 Page 2 - 32 INTENTIONALLY LEFT BLANK Edition, Rev. 0 Section 2 – Limitations...
Page 63 Page 3 - 1 SECTION 3 – EMERGENCY PROCEDURES INDEX 1. Introduction ..................3 1.1. Engine failure during takeoff run ..............3 2. Airplane alerts ................. 5 2.1. Single generator failure / overvoltage ............5 2.2. Both generators failure ................... 6 2.3.
Page 64 Page 3 - 2 7.2. Complete Gear up or nose gear up landing ..........33 7.3. Partial Main LG extension ................34 7.4. Failed retraction .................... 36 7.5. Unintentional landing gear extension ............36 8. Smoke and fire occurrence ............38 8.1 Engine fire on the ground ................
Page 65 Page 3 - 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. Before operating the aircraft, the pilot should become thoroughly familiar with this manual and, in particular, with this Section.
Page 66 Page 3 - 4 In this Chapter, following definitions apply: Land as soon as possible: land without delay at the nearest suitable NOTE area at which a safe approach and landing is assured. Land as soon as practical: land at the nearest approved landing ar- ea where suitable repairs can be made.
Page 67 Page 3 - 5 2. A IRPLANE ALERTS The annunciator panel, located on the left side instrument panel, contains 16 lights for warnings, cautions and advisories. The colours are as follows: GREEN: to indicate that pertinent device is turned ON AMBER: to indicate no-hazard situations which have to be considered and which require a proper crew action...
Page 68 Page 3 - 6 2.2. OTH GENERATORS FAILURE In event of both LH and RH GENERATOR caution lights turned ON: 1. FIELD LH and RH BOTH OFF 2. FIELD LH and RH BOTH ON If the LH (or RH) GENERATOR caution stays displayed 3.
Page 69 Page 3 - 7 2.3. B OTH GENERATORS OVERVOLTAGE In event of both LH and RH OVERVOLT warning lights turned ON: 1. FIELD LH and RH BOTH OFF 2. FIELD LH and RH BOTH ON If the LH (or RH) GENERATOR caution stays displayed 3.
Page 70: On The Ground
Page 3 - 8 2.4. F AILED DOOR CLOSURE In case of door opening / unlocking, related MAIN or REAR DOOR ALERT warning light turns ON. ON THE GROUND 1. Passengers and crew seat belts Fasten and tighten 2. Affected door Verify correctly closed If door is open 3.
Page 71 Page 3 - 9 2.5. P ITOT HEATING SYSTEM FAILURE 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 sys- tem is functioning properly.
Page 72 Page 3 - 10 2.6. C OOLANT LIQUID LOW LEVEL When the engine coolant liquid level goes under the lower limit, the related LH or RH LOW COOLANT is turned ON. This condition may lead to high CHT/CT. When the warning light turns ON, apply following procedure: 1.
Page 73 Page 3 - 11 2.7. G UMP FAILURE 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 74: Engine Fire
Page 3 - 12 2.8. E NGINE FIRE In event of engine fire, LH or RH ENGINE FIRE warning light will turn ON. Re- fer to following procedures: FIRE ON THE GROUND: see Para. 8.1 FIRE DURING TAKEOFF RUN: see Para. 8.2 FIRE IN FLIGHT: see Para.
Page 75 Page 3 - 13 3. E NGINE 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 76 Page 3 - 14 4. P OWERPLANT EMERGENCIES 4.1. 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 77 Page 3 - 15 4.3. IL TEMPERATURE LIMIT EXCEEDANCE If oil temperature exceeds maximum limit (130°C – 266° F): 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 temperature does not decrease 4.
Page 78 Page 3 - 16 4.4. IL PRESSURE LIMITS EXCEEDANCE If oil pressure exceeds its lower or upper limit (0.8 – 7 bar / 11.5 – 101.5 psi), ap- ply following procedure: Excessive oil pressure drop leads to a high pitch propeller configuration with consequent propeller feathering and en- gine stopping.
Page 79 Page 3 - 17 4.5. OW FUEL PRESSURE Low fuel pressure indications are possible and allowed but the pressure must sta- bilize to the operating limit within 10 seconds. If not, and pressure decreases be- low the lower limit (2.2 psi), apply following procedure: Fuel press CHECK Fuel quantity...
Page 80: Other Emergencies
Page 3 - 18 5. O THER EMERGENCIES 5.1. MERGENCY DESCENT Descent with airspeed at VLE, idle power and gear down will pro- ° vide high descent rates and pitch attitudes up to -15 Anticipate altitude capture and return to level flight during emer- gency descent in order to assure a safe and smooth recovery from CAUTION maneuver.
Page 81 Page 3 - 19 5.3. 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 82: Unintentional Flight Into Icing Conditions
Page 3 - 20 5.4. 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 INCREASE to prevent ice build-up on the blades...
Page 83: Carburettor Icing
Page 3 - 21 5.5. ARBURETTOR ICING DURING TAKEOFF The carburettor icing in “full throttle” mode is unlikely. Take off in known or suspected icing condition is forbidden. Therefore, and in order to dispose of full engine take off power, the take-off must be performed with carburettor heating OFF.
Page 84 Page 3 - 22 5.6. 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 6 (Stall Speed) and an increased landing distance of about 25%.
Page 85 Page 3 - 23 6. O NE 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 86: Characteristic Airspeeds With One Engine Inoperative
Page 3 - 24 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. (V MTOW 1180 kg MTOW 1230 kg Best rate-of-climb speed OEI (V...
Page 87 Page 3 - 25 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 BOTH ON Operating engine Throttle Lever...
Page 88 Page 3 - 26 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- formed on ground.
Page 89 Page 3 - 27 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: Land as soon as possible...
Page 90 Page 3 - 28 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 Inoperative engine Propeller Lever FEATHER...
Page 91 Page 3 - 29 6.5. E 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 (crossfeed if needed)
Page 92 Page 3 - 30 6.6. One engine inoperative landing Thoroughly evaluate feasibility and plan in advance Single Engine Go- Around capabilities and expected climb gradient should a Missed Ap- proach / balked landing be necessary. Refer to Section 5, Para 13 and WARNING 14 (One-engine Rate of Climb at V and V...
Page 93 Page 3 - 31 INTENTIONALLY LEFT BLANK Edition, Rev. 0 Section 3 – Emergency procedures...
Page 94 Page 3 - 32 7. L ANDING GEAR FAILURES 7.1. 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. Light bulb operating status can be verified by pressing the LDG push-to-test button.
Page 95 Page 3 - 33 7.2. NOSE GEAR UP LANDING OMPLETE EAR UP OR 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 96 Page 3 - 34 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. 7.3. ARTIAL EXTENSION The following procedure applies if one or both Main Landing Gear legs are not completely extended and locked even after emergency ex-...
Page 97 Page 3 - 35 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 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 98 Page 3 - 36 7.4. 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 99 Page 3 - 37 INTENTIONALLY LEFT BLANK Edition, Rev. 0 Section 3 – Emergency procedures...
Page 100 Page 3 - 38 8. S MOKE 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, fuel, hydraulic fluid or oil spills.
Page 101 Page 3 - 39 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 MASTER SWITCH Parking Brake...
Page 102 Page 3 - 40 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 103 Page 3 - 41 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 Fire affected engine Electrical fuel pump...
Page 104 Page 3 - 42 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. CAUTION If smoke persists, shed electrical supply in order to isolate faulty source by: FIELD LH and RH...
Page 105 Page 3 - 43 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. Leave aircraft in upwind direction. WARNING Edition, Rev.
Page 106 Page 3 - 44 9. U NINTENTIONAL 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: Both engines throttles idle...
Page 107 Page 3 - 45 INTENTIONALLY LEFT BLANK Edition, Rev. 0 Section 3 – Emergency procedures...
Page 108 Page 3 - 46 10. L ANDING EMERGENCIES 10.1 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. Refer to Section 5, Para.
Page 109 Page 3 - 47 Before touch down Fuel Selector BOTH OFF Electrical fuel pump BOTH OFF Ignitions ALL OFF After aircraft stops: 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 110 Page 3 - 48 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 111 Page 3 - 49 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 board and remaining fuel type and quantity.
Page 112 Page 3 - 50 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 113 Page 3 - 51 11. A IRCRAFT 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 114 Page 3 - 52 12. D ITCHING 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 first.
Page 115 Page 3 - 53 INTENTIONALLY LEFT BLANK Edition, Rev. 0 Section 3 – Emergency procedures...
Page 116 Page 3 - 54 INTENTIONALLY LEFT BLANK Edition, Rev. 0 Section 3 – Emergency procedures...
Page 117: Table Of Contents
P2006T - Aircraft Flight Manual Page 4 - 1 SECTION 4 – NORMAL PROCEDURES INDEX Introduction .................. 3 1.1. Normal ops general recommendations ............... 3 Airspeeds ..................5 normal operations ..................... 5 2.1. 2.2. single engine training ..................5 Normal procedures checklist ............7 3.1.
Page 118 P2006T - Aircraft Flight Manual Page 4 - 2 INTENTIONALLY LEFT BLANK Edition, Rev. 0 Section 4 – Normal procedures TABLE OF CONTENTS...
Page 119: Introduction
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. As prescribed by the propeller/governor manufacturer, a drop of 400/500 propeller RPM should be produced during this check.
Page 120 RPM. Refer to SL-912-016R2 for additional information. 3. Suitable Fuels. Tecnam remember operators to fill the aircraft with approved and suitable fuels. Use of not approved/unknown fuels may cause damages to the engine. ONLY USE APPROVED FUELS...
Page 121: Airspeeds
P2006T - Aircraft Flight Manual Page 4 - 5 2. A IRSPEEDS NORMAL OPERATIONS 2.1. The following airspeeds are those which are significant for normal operations, with reference to both MTOW: 1180 kg and 1230 kg (if Supplement A19 - In- creased MTOW @1230 KG - is applicable).
Page 122 P2006T - Aircraft Flight Manual Page 4 - 6 In normal operations, shutting down an engine for training shall not become a habit, in particular for safety reasons and in order to optimise training; engine shutdown to per- form OEI shall be executed only when required by regulations (e.g. during flight check, skill tests or demonstration as per 14CFR Part61 or equivalent rule).
Page 123 P2006T - Aircraft Flight Manual Page 4 - 7 Normal procedures checklist 3.1. 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 124 P2006T - Aircraft Flight Manual Page 4 - 8 Tires show low pressure in cold weather: the required adjustments to inflation pressure should be performed on tires cooled to ambient temperature. If the crew detects ice, anti-icing products are not allowed. To remove ice, tow the aircraft in the hangar and operate with a soft brush or a humid cloth.
Page 125: Pre-Flight Check
P2006T - Aircraft Flight Manual Page 4 - 9 3.2. FLIGHT CHECK IRCRAFT 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 126 P2006T - Aircraft Flight Manual Page 4 - 10 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.
Page 127 P2006T - Aircraft Flight Manual Page 4 - 11 between the dogs with practically no friction at all further investigation is necessary. Turn propeller by hand in direction of engine rotation several times and observe engine for odd noises or excessive resistance and normal compression.
Page 128 P2006T - Aircraft Flight Manual Page 4 - 12 Left Flap and hinges Visual inspection Remove protective cap – Visual inspection Left static port Antennas Check for integrity Gear pump, external power and Check emergency landing gear extension battery compartment...
Page 129 P2006T - Aircraft Flight Manual Page 4 - 13 Right fuel tank Check that the refuelling port cap is proper- ly secured, then perform the fuel tank sump drainage operating the related valve which, after operation, must be checked closed.
Page 130 P2006T - Aircraft Flight Manual Page 4 - 14 3.3. OCKPIT INSPECTIONS Instruct passengers on how to use safety belts and normal / emergency exits. 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 131 P2006T - Aircraft Flight Manual Page 4 - 15 INTENTIONALLY LEFT BLANK Edition, Rev. 0 Section 4 – Normal procedures...
Page 132 P2006T - Aircraft Flight Manual Page 4 - 16 3.4. NGINE STARTING Avionics switches must be set OFF during engine starting to prevent avion- ic equipment damage. CAUTION Start clearance Obtain if needed CHRONOMETER START Right engine starting RH Throttle lever...
Page 133 P2006T - Aircraft Flight Manual Page 4 - 17 Left engine starting LH Throttle lever IDLE LH Carburetor heat LH Propeller Lever FULL FORWARD LH Choke ON if required LH Electrical Fuel pump ON, check advisory light ON and posi-...
Page 134: Before Taxiing
P2006T - Aircraft Flight Manual Page 4 - 18 3.5. EFORE TAXIING Let the engines warm up to a minimum oil temperature of 50°C (122°F) at 1200 Nav and taxi lights Audio panel Transponder Standby Passengers and crews seat belts...
Page 135 P2006T - Aircraft Flight Manual Page 4 - 19 3.7. 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: 90° - 110°C (194° - 230°F) (or 50 - 130 °C / 122°...
Page 136 P2006T - Aircraft Flight Manual Page 4 - 20 LH Ignitions switches Set L / R / BOTH (RPM drop with single ignition circuit selected must not exceed 210 prop’s RPM; maximum RPM difference by use of either cir- cuits LEFT or RIGHT cannot over-...
Page 137 P2006T - Aircraft Flight Manual Page 4 - 21 3.9. 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...
Page 138: Turbulent Air Operation
P2006T - Aircraft Flight Manual Page 4 - 22 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.
Page 139 P2006T - Aircraft Flight Manual Page 4 - 23 3.13. EFORE LANDING LH and RH Electrical Fuel pump BOTH ON On downwind leg: MTOW 1180kg MTOW 1230 kg Flaps T/O = 119KIAS =122KIAS Landing gear control knob - DOWN –...
Page 140 P2006T - Aircraft Flight Manual Page 4 - 24 3.15. FTER LANDING LH and RH Electrical Fuel pump BOTH OFF Flaps 0° Pitot Heat Landing light OFF when required Edition, Rev. 6 Section 4 – Normal procedures...
Page 141 P2006T - Aircraft Flight Manual Page 4 - 25 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...
Page 142: Postflight Checks
P2006T - Aircraft Flight Manual Page 4 - 26 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 143 P2006T - Aircraft Flight Manual Page 4 - 27 3. G ROUND TOWING PARKING AND MOORING 4.1 T OWING Before to move the a/c on the ground, the Master Switch must be turned ON for at least 5 seconds. CAUTION To tow the aircraft it is necessary to use a metal stiff bar connected to the nose gear.
Page 144 P2006T - Aircraft Flight Manual Page 4 - 28 Procedure 1. Position airplane on levelled surface and headed into the prevailing wind. 2. Center nose wheel, engage parking brake and/or use the wheel chocks. Do not engage the parking brakes at low ambient temperature;...
Page 145 P2006T - Aircraft Flight Manual Page 4 - 29 INTENTIONALLY LEFT BLANK Edition, Rev. 0 Section 4 – Normal procedures GROUND TOWING, PARKING AND MOORING...
Page 146 P2006T - Aircraft Flight Manual Page 4 - 30 INTENTIONALLY LEFT BLANK Edition, Rev. 0 Section 4 – Normal procedures GROUND TOWING, PARKING AND MOORING...
Page 147 Page 5 - 1 SECTION 5 - PERFORMANCES INDEX Introduction ..................2 Use of performances charts ............... 2 Airspeed indicator system calibration ..........3 ICAO Standard Atmosphere ..............4 Examples: .................... 4 Stall speed ................... 5 Crosswind .................... 6 Take-off performances ................ 7 Take-off Rate of Climb ..............
Page 148 Page 5 - 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” under conditions prescribed by EASA CS-23 regulation •...
Page 149: Airspeed Indicator System Calibration
Page 5 - 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 AIRSPEED INDICATOR SYSTEM CALIBRATION...
Page 150 Page 5 - 4 4. ICAO S TANDARD TMOSPHERE c.δA=2250 ft A.δA=1600 ft °C Figure 2 – ICAO chart 5. E XAMPLES Given Find a. Temperature = 20°C c. Corresponding Density Altitude = 2250’ b. Pressure altitude = 1600’ Given Find A.
Page 151: Stall Speed
Page 5 - 5 6. S TALL SPEED ° ° [deg] KIAS KCAS KIAS KCAS KIAS KCAS 1180 kg 2601 lb (FWD C.G.) NOTE Altitude loss during conventional stall recovery, as demonstrated during flight tests is approximately 200 ft with banking below 30°. Edition, Rev.
Page 152 Page 5 - 6 7. 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 153 Page 5 - 7 8. T OFF PERFORMANCES ° ° ° ° -25/-13 0/32 25/77 50/122 Ground Roll 208 (682) 258 (846) 313 (1027) 374 (1227) 290 (951) S.L. At 50 ft AGL 266 (872) 331 (1086) 404 (1325) 485 (1591) 373 (1223) Ground Roll 230 (754) 284 (932) 346 (1135) 413 (1355) 315 (1033)
Page 154 Page 5 - 8 ° ° ° ° -25/-13 0/32 25/77 50/122 Ground Roll 148 (485) 188 (617) 234 (768) 286 (938) 215 (705) S.L. At 50 ft AGL 193 (633) 246 (807) 306 (1004) 374 (1227) 281 (922) Ground Roll 165 (541) 210 (689) 261 (856)
Page 155 Page 5 - 9 ° ° ° ° -25/-13 0/32 25/77 50/122 Ground Roll 100 (328) 127 (417) 158 (518) 194 (636) 146 (479) S.L. At 50 ft AGL 131 (430) 167 (548) 207 (679) 254 (833) 190 (623) Ground Roll 112 (367) 142 (466) 177 (581)
Page 156: Take-Off Rate Of Climb
Page 5 - 10 9. T ATE OF LIMB ° ° ° ° -25/-13 0/32 25/77 50/122 S.L. 1347 1154 1048 2000 1200 1010 4000 1054 1180 kg 6000 8000 2601 lb 10000 12000 14000 -130 S.L. 1507 1302 1119 1190 2000 1351...
Page 157 Page 5 - 11 10. T ATE OF LIMB AT ° ° ° ° -25/-13 0/32 25/77 50/122 S.L. 1283 1102 1002 1000 1214 1034 2000 1145 1180 kg 3000 1076 4000 1008 2601 lb 5000 6000 7000 S.L. 1283 1102 1002 1000...
Page 158: Enroute Rate Of Climb
Page 5 - 12 11. E NROUTE ATE OF LIMB ° ° ° ° -25/-13 0/32 25/77 50/122 S.L. 1392 1205 1038 1102 2000 1249 1066 4000 1108 1180 kg 6000 8000 2601 lb 10000 12000 14000 S.L. 1560 1360 1182 1022 1251...
Page 159 Page 5 - 13 12. E NROUTE ATE OF LIMB AT ° ° ° ° -25/-13 0/32 25/77 50/122 S.L. 1315 1142 1047 1000 1249 1077 2000 1183 1013 1180 kg 3000 1118 4000 1052 2601 lb 5000 6000 7000 S.L.
Page 160 Page 5 - 14 13. O NGINE ATE OF LIMB ° ° ° ° -25/-13 0/32 25/77 50/122 S.L. 1000 2000 1180 kg 3000 4000 2601 lb 5000 -127 6000 -163 7000 S.L. 1000 2000 1080 kg 3000 4000 2381 lb 5000 6000 7000...
Page 161 Page 5 - 15 14. O NGINE ATE OF LIMB AT ° ° ° ° -25/-13 0/32 25/77 50/122 S.L. 1000 2000 1180 kg 3000 4000 2601 lb 5000 6000 -124 7000 -159 S.L. 1000 2000 1080 kg 3000 4000 2381 lb 5000 6000...
Page 162 Page 5 - 16 15. C RUISE PERFORMANCES Weight: 1150 kg (2535 lb) Pressure Altitude: 0 ft ISA – 30°C (-15°C) ISA + 30°C (45°C) ISA (15°C/59°F) ISA – 54°F (5°F) ISA + 56°F (113°F) RPM* KTAS F.C.** PWR KTAS F.C.** PWR KTAS F.C.**...
Page 163 Page 5 - 17 Weight: 1150 kg (2535 lb) Pressure Altitude: 3000 ft ISA – 30°C (-15°C) ISA + 30°C (45°C) ISA (15°C/59°F) ISA – 54°F (5°F) ISA + 56°F (113°F) RPM* PWR KTAS F.C.** PWR KTAS F.C.** PWR KTAS F.C.** [in.Hg] [lt/hr] [USg/hr]...
Page 164 Page 5 - 18 Weight: 1150 kg (2535 lb) Pressure Altitude: 9000 ft ISA – 30°C (-15°C) ISA + 30°C (45°C) ISA (15°C/59°F) ISA – 54°F (5°F) ISA + 56°F (113°F) RPM* PWR KTAS F.C.** PWR KTAS F.C.** PWR KTAS F.C.** [in.Hg] [lt/hr] [USg/hr]...
Page 165 Page 5 - 19 16. L ANDING PERFORMANCES ° ° ° ° -25/-13 0/32 25/77 50/122 Ground Roll 183 (600) 202 (663) 220 (722) 238 (781) 213 (699) S.L. At 50 ft AGL 288 (945) 312 (1023) 335 (1099) 358 (1174) 326 (1069) Ground Roll 190 (623) 209 (686)
Page 166 Page 5 - 20 ° ° ° ° -25/-13 0/32 25/77 50/122 Ground Roll 175 (574) 192 (630) 210 (689) 227 (745) 203 (666) S.L. At 50 ft AGL 271 (889) 293 (961) 315 (1033) 337 (1105) 306 (1004) Ground Roll 181 (594) 199 (653) 218 (715)
Page 167 Page 5 - 21 ° ° ° ° -25/-13 0/32 25/77 50/122 Ground Roll 150 (492) 166 (544) 181 (594) 196 (643) 175 (574) S.L. At 50 ft AGL 233 (764) 252 (827) 271 (889) 290 (951) 264 (866) Ground Roll 156 (512) 172 (564) 187 (613)
Page 168: Balked Landing Climb Gradient
Page 5 - 22 17. B ALKED LANDING CLIMB GRADIENT Flight conditions (ISA and SL): Weight: 1180 kg / 2601 lb Throttle levers Both FULL FORWARD Flaps Landing gear DOWN Weight MTOW (1180 kg / 2601 lb) Speed 66 KIAS Climb gradient 10.8% (6.2°) 18.
Page 169 Page 5 - 23 INTENTIONALLY LEFT BLANK Edition, Rev. 21 Section 5 - Performances...
Page 170 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 171 Page 6 - 2 INTENTIONALLY LEFT BLANK Edition, Rev 0 Section 6 – Weight and balance...
Page 172 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 173: 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 174: Weighing Record
Page 6 - 5 2.5. EIGHING RECORD Model P2006T S/N:________ Weighing no. ____ Date:_________ Datum: leading edge vertical [kg] or [lbs] [m] or [ft] Nose wheel weight W Plumb bob distance LH wheel LH wheel weight Plumb bob distance RH wheel...
Page 175 Page 6 - 6 2.6. (II) EIGHING RECORD Model P2006T S/N:________ Weighing no. ____ Date:_________ Datum: leading edge vertical [kg] or [lbs] [m] or [ft] Nose wheel weight W Plumb bob distance LH wheel LH wheel weight Plumb bob distance RH wheel...
Page 176: Baggage Loading
Page 6 - 7 3. W EIGHTS AND ALANCE DETERMINATION FOR FLIGHT The pilot is responsible for ensuring the correct useful load loading. In this subsection, the procedure to be used for the determination of aircraft weight and balance in flight is described. The weight and moment obtained must fall within the approved Weight-Moment Envelope (Figure 6-2).
Page 177 Page 6 - 8 Table 2- 1 – Weight and C.G. - Form Moment (M) = [kg] or (lb) [m] or (ft) W * Arm [kg*m] or (lb*ft) Empty weight USEFUL LOAD -0.893 (2,93 ft) Pilot -0.893 (2,93 ft) Co-Pilot 0.226 (0,741 ft) Passenger Passenger...
Page 178 Page 6 - 9 Table 2- 2 – Weight and C.G. - Example Moment (M) = [kg] or (lb) [m] or (ft) W * Arm [kg*m] or (lb*ft) Empty weight 790 (1742 lb) 0.478 (1,595 ft) 378 (2778,5 lb*ft) USEFUL LOAD 80 (176,3 lb) -0.893 (2,93 ft) -71.44 (-516,85 lb*ft)
Page 179 Page 6 - 10 Figure 6- 1 – Loading diagram Figure 6- 1 – Loading diagram Edition, Rev 22 Section 6 – Weight and balance BAGGAGE LOADING...
Page 180 Page 6 - 11 Figure 6- 2 – Weight and Moment Envelope *) applicable for aircraft embodying MOD2006/015; **) applicable for aircraft embodying MOD2006/416 Edition, Rev 22 Section 6 – Weight and balance BAGGAGE LOADING...
Page 181 Page 6 - 12 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 limitations 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 182 Page 6 - 13 INTENTIONALLY LEFT BLANK Edition, Rev 21 Section 6 – Weight and balance...
Page 183: Equipment List
Page 6 - 14 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 184 Page 6 - 15 QUIPMENT LIST IRCRAFT S EIGHT ESCRIPTION [kg] INSTRUMENTS & AVIONICS airspeed indicator – UMA T6-311 – 200 0.37 -1.4 airspeed indicator – Mikrotechna 1116.B2B2 0.37 -1.4 attitude indicator – Kelly Manufacturing RCA26AK-12 -1.4 altimeter – United Instruments 5934PM-3A84 01770028-05 -1.4 altimeter –...
Page 185 Page 6 - 16 QUIPMENT LIST IRCRAFT S EIGHT ESCRIPTION [kg] KI 525A Pictorial Navigation Indicator 1.53 -1.4 KG 102A Directional Gyro 1.95 KA 51B Slaving Control and Compensator Unit -1.4 KMT 112 Magnetic Slaving Transmitter 0.15 HONEYWELL Bendix/King KR87 ADF System ADF KR87 receiver Indicator KI 227 -1.4...
Page 186 Front RH seat GEVEN E5-01-004-T01 or E5-01-008-T01 or E5-01-010-T03 -0.89 Rear LH seat GEVEN E5-01-003-T01 or E5-01-007-T01 or E5-01-009-T03 0.23 Rear RH seat GEVEN E5-01-004-T01 or E5-01-008-T01 or E5-01-010-T03 0.23 Front LH Seat TECNAM 26-6-5100-001 -0.89 Front RH Seat TECNAM 26-6-5100-002 -0.89 Rear LH Seat TECNAM 210-10-5300-801 0.23 Rear RH Seat TECNAM 210-10-5400-801 0.23...
Page 187 Page 6 - 18 INTENTIONALLY LEFT BLANK Edition, Rev 0 Section 6 – Weight and balance...
Page 188 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 189 Page 7 - 2 INTENTIONALLY LEFT BLANK Edition, Rev 0 Section 7 – Airframe and Systems description...
Page 190 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 191 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 supporting the seats guides and other components.
Page 192 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 193 Page 7 - 6 Figure 4. – Stabilator structure Edition, Rev 0 Section 7 – Airframe and Systems description AIRFRAME...
Page 194: Flight Controls
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 195 Page 7 - 8 INTENTIONALLY LEFT BLANK Edition, Rev 0 Section 7 – Airframe and Systems description AIRFRAME...
Page 196: Power Plant
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 197 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 relief valve opens and the coolant will flow via a hose at atmospheric pressure to the transparent overflow bottle (4).
Page 198: Engine Features
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 199 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 200 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 201 Page 7 - 14 INTENTIONALLY LEFT BLANK Edition, Rev 0 Section 7 – Airframe and Systems description...
Page 202 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 203: Internal Lights
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: ➢...
Page 204: External Lights
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 205 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 206: 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 (26.42 US gallons) 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 207 Page 7 - 20 Figure 12. – Fuel system schematic Edition, Rev 0 Section 7 – Airframe and Systems description FUEL SYSTEM...
Page 208: 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 209 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 210 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 211 Page 7 - 24 INTENTIONALLY LEFT BLANK Edition, Rev 0 Section 7 – Airframe and Systems description LANDING GEAR SYSTEM...
Page 212 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 213: Cabin Heat
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. For aircraft embodying MOD2006/208 a fan is installed in order to convoy air in- to the cabin during on ground operations at low speeds, namely, when air inlets are ineffective.
Page 214 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 215: 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 216 Page 7 - 29 INTENTIONALLY LEFT BLANK Edition, Rev 0 Section 7 – Airframe and Systems description...
Page 217 Page 7 - 30 INTENTIONALLY LEFT BLANK Edition, Rev 0 Section 7 – Airframe and Systems description...
Page 218 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 219 Page 7 - 32 Description Placard Place Emergency Emergency distribu- gear extension tors compartment instructions Alternate static Central pedestal, left port location side (not applicable for air- craft embodying MOD2006/438) Alternate static Central pedestal, right port operating side instructions (not applicable for air- craft embodying MOD2006/438)
Page 220 Page 7 - 33 Description Placard Place Landing gear LG hydraulic com- hydraulic partment cap (fuselage cumulator: tail, left side) pressure limit hydraulic Fuselage tail, left side, compartment in correspondence of location LG hydraulic com- partment cap Towing limita- Nose LG forward door tions Stabilator Fuselage tail, left side,...
Page 221 Page 7 - 34 Steel boards: Fuselage tail, left side a/c identifica- tion marks (Sample) MLG leg, LH and RH Applicable for aircraft Main LG tires embodying inflation pres- MOD2006/266 and sure values MOD2006/314 Applicable for aircraft embodying MOD2006/317 Nose LG fork Nose LG tire Applicable for aircraft inflation pres-...
Page 222 Page 7 - 35 INTENTIONALLY LEFT BLANK Edition, Rev 0 Section 7 – Airframe and Systems description...
Page 223 Page 7 - 36 INTENTIONALLY LEFT BLANK Edition, Rev 0 Section 7 – Airframe and Systems description...
Page 224: Instruments Panel
Page 7 - 37 17. INSTRUMENTS PANEL Figure 16. – Instruments panel (typical layout) Tab 1 DESCRIPTION Airspeed indicator Attitutude Indicator Altimeter VOR/ILS Indicator ADF Indicator (Kit B) Vertical Speed Indicator Directional Gyro Indicator Turn Coordinator Annunciator Panel DME Indicator (Kit B) Directional Trim Indicator Cabin Heat / Defrost Dimmers...
Page 225 Page 7 - 38 Tab 2 DESCRIPTION Audio Panel Transponder ADF (Kit B) COMM/NAV SL30 (Kit A) GPS/NAV/COMM GNS 430 Available Avionic Switches Cross Bus Switches VOR/ILS Indicator Figure 18. – Central instruments panel (typical layout) Tab 3 DESCRIPTION Fuel Quantity Indicators Oil Pressure Indicators Oil Temperatures Indicators CHT Indicators...
Page 226 Page 7 - 39 Tab 4 DESCRIPTION DESCRIPTION Pitot Heating Switch Flap Control Available Flap Indicator LH Field Landing Light Switch Battery Master Switch Taxi Lights Switch RH Field Position Lights Switch Landing Gear lights Strobe Lights Switch Unsafe Light Instrument Lights Switch Light Test Landing Gear lever...
Page 227: Electrical System
Page 7 - 40 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 228 Page 7 - 41 The following loads are connected to the battery bus: Battery Bus Audio Panel VHF COMM 1 NAV 1 LH and RH Fuel electrical pump LH and RH Fuel pressure LH and RH Fuel quantity LH and RH oil pressure LH and RH oil temperature LH and RH CHT LH and RH RPM indicator...
Page 229 Page 7 - 42 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 NAV 2 RH attitude indicator A/P (*) A/P Pitch Trim (*) (*) if installed On the central pedestal (see Figure below) there are seven switches disposed on...
Page 230 Page 7 - 43 When both generators are correctly operating and all above mentioned switches are in ON position, all the busses are connected to the generators. The ignition switches, two for each engine and grouped on the over head panel, are instead independent from the airplane electrical system (generation and distri- bution);...
Page 231 Page 7 - 44 Figure 22. – Electrical system schematic Edition, Rev 0 Section 7 – Airframe and Systems description ELECTRICAL SYSTEM...
Page 232 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 233 Page 8 - 2 INTENTIONALLY LEFT BLANK Edition, Rev. 0 Section 8 – Aircraft Care and Maintenance...
Page 234: Inspection Intervals
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 235: Maintenance
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 236 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: For aircraft embodying For aircraft embodying MOD2006/266 and MOD2006/317...
Page 237 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 238 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 239: External Surfaces
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 240 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 241 Page 8 - 10 INTENTIONALLY LEFT BLANK Edition, Rev. 0 Section 8 – Aircraft Care and Maintenance...
Page 242 Page 9-1 SECTION 9 – SUPPLEMENTS 1. I NTRODUCTION This Section concerns the supplemental manuals of additional (or optional) instrumentation equipping the P2006T. Edition, Rev. 12 Section 9 - Supplements INTRODUCTION...
Page 243 Page 9-2 2. S UPPLEMENTS LISTS Aircraft S/N: __________ Registration marks: ________________ Date: ________________ SUPPLEMENTS LIST Applicablity Applied Sup. Rev. Title Date Garmin GNS-430W Gps/VHF Comm/Nav Garmin SL30 VHF Comm/Nav Garmin GMA 340 Audio Panel Garmin GTX 328Mode S Transponder Bendix-King Honeywell KR 87 ADF System Bendix-King Honeywell KN 63 DME System KCS 55A Compass System...
Page 244 Page 9-3 Aircraft S/N: __________ Registration marks: ________________ Date: ________________ SUPPLEMENTS LIST Applicablity Applied Sup. Rev. Title Date SMP for Analogic Configuration Alternators with 70A Mogas MG95 IS 2796:2017 Garmin GMA 345 Audio Panel GARMIN GTX345R Transponder Garmin G950 IFDS S-TEC Fifty Five X Autopilot Bendix-King Honeywell KR 87 ADF System for GARMIN G950...
Page 245 Page 9-4 Aircraft S/N: __________ Registration marks: ________________ Date: ________________ SUPPLEMENTS LIST Applicablity Applied Sup. Rev. Title Date GARMIN GTX345R Transponder Becker 3500 ADF for GARMIN NXi GARMIN GTS800 TAS for GARMIN NXi SMP Configuration for Garmin NXi Avionics Suite TABI-1800 Phase One 190MP Aerial System LMS-Q680I and Phase One 4-band Camera In-...
Page 246 Page A1-1 . A1 - G GNS-430W GPS/WAAS UPPLEMENT NO ARMIN COMM/NAV Record of Revisions EASA Approval Tecnam Approval Revised Description of or Under DOA page Revision Privileges Approved under DOA Editorial change A.Sabino C. Caruso M. Oliva No. EASA.21J.335...
Page 247 Page A1-2 INTRODUCTION This section contains supplemental information to operate, in a safe and efficient manner, the aircraft when equipped with Garmin GNS-430W device. GENERAL 1. GPS GNS-430W is an integrated system which contains, in addition to the GPS navigation system, a VHF COMM transceiver and a VOR/ILS receiver. 2.
Page 248: Limitations (Easa Approved)
Page A1-3 LIMITATIONS (EASA APPROVED) 1. The GARMIN 400W Series Pilot's Guide and Reference p/n 190-00356-00 rev. G, or a more updated version, must be available on board for the correct device use. 2. The system employment is allowed only in VFR flight conditions. 3.
Page 249 Page A1-4 EMERGENCY PROCEDURES 1. Should the Garmin GNS-430W information be unavailable or manifestly wrong, it is nec- essary to use other navigation instruments. 2. If during navigation (only in ENROUTE mode) GPS signal is lost, the instrument contin- ues to operate in DR (Dead Reckoning) mode. Aircraft position is estimated on the basis of the last GPS valid signal, but it can be significantly distorted by relative speed varia- tions.
Page 250 Page A2-1 . A2 - G SL30 VHF COMM/NAV UPPLEMENT NO ARMIN Record of Revisions EASA Approval Tecnam Approval Revised Description of or Under DOA page Revision Privileges Approved under DOA Editorial change A. Sabino C. Caruso M. Oliva No. EASA.21J.335...
Page 251 SL30 transmits with a power of 8watt. LIMITATIONS Garmin SL30 manuals do not address operating limitations more severe than those usually applicable to the P2006T. EMERGENCY PROCEDURES 1. Should Garmin SL30 information be unavailable or manifestly wrong, it is necessary to use other communication devices.
Page 252 Page A2-3 NORMAL OPERATIONS ETAILED OPERATING PROCEDURES Normal operating procedures are described on GARMIN SL 30 NAV COM Pilot’s guide (P/N 190-00486-00) rev. C or later. GARMIN SL 30 NAV COM Pilot’s guide (P/N 190-00486-00) NOTE - rev. C or later. - must be carried onboard the airplane at all times.
Page 253 Page A2-4 INTENTIONALLY LEFT BLANK Edition, Rev. 0 Section 9 - Supplements Supplement no. A2 - Garmin SL30 VHF COMM/NAV COMM/NAV...
Page 254 Page A3-1 . A3 - G GMA340 UPPLEMENT NO ARMIN AUDIO PANEL Record of Revisions EASA Approval Tecnam Approval Revised Description of or Under DOA page Revision Privileges Approved under DOA Editorial Change A. Sabino C. Caruso M. Oliva No. EASA.21J.335...
Page 255 Garmin GMA340 device. GENERAL Garmin GMA340 is the audio management device used on P2006T. The audio panel handles internal audio communications (INTERCOM), external audio communications (allowing COM1 to COM2 switching), those related to the markers during ILS approaches and, eventually, those related to the on board mu- sical entertainment (compact disc devices etc).
Page 256 Page A3-3 PERFORMANCES Garmin GMA340 audio panel employment does not affect the aircraft performances. WEIGHT AND BALANCE See Section 6 of this Manual. SYSTEMS Refer to GARMIN GMA 340 Pilot’s guide (P/N 190-00149-10) rev. C or later for a complete system description. Edition, Rev.
Page 257 Page A3-4 INTENTIONALLY LEFT BLANK Edition, Rev. 0 Section 9 - Supplements Supplement no. A3 - Garmin GMA340 audio panel...
Page 258 Page A4-1 . A4 - G GTX328 M UPPLEMENT NO ARMIN TRANSPONDER Record of Revisions EASA Approval Tecnam Approval Revised Description of or Under DOA page Revision Privileges Approved under DOA Editorial Change A. Sabino C. Caruso M. Oliva No. EASA.21J.335...
Page 259 Garmin GTX 328 is a transponder operating with A,C and S mode. LIMITATIONS Garmin GTX 328 manuals do not address operating limitations more severe than those usually applicable to the P2006T. EMERGENCY PROCEDURES In case of emergency conditions, transponder is able to sent codified messages to the Air Traffic Control;...
Page 260 Page A4-3 NORMAL OPERATIONS ETAILED OPERATING PROCEDURES Normal operating procedures are described on GARMIN GTX 328 Mode S Tran- sponder Pilot’s guide (P/N 190-00420-03) rev. A or later. GARMIN GTX 328 Mode S Transponder Pilot’s guide (P/N NOTE 190-00420-03) - rev. A or later - must be carried onboard the airplane at all times.
Page 261 Page A4-4 INTENTIONALLY LEFT BLANK Edition, Rev. 0 Section 9 - Supplements Supplement no. A4 - Garmin GTX328 Mode S transponder...
Page 262 Page A5-1 . A5 – KR 87 ADF S UPPLEMENT NO YSTEM Record of Revisions EASA Approval Tecnam Approval Revised Description of or Under DOA page Revision Privileges Approved under DOA Editorial Change A. Sabino C. Caruso M. Oliva No. EASA.21J.335...
Page 263 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. A5 – KR 87 ADF System...
Page 264 Page A5-3 EMERGENCY PROCEDURES Particular meteorological conditions can distort the equipment indications. There- fore, to avoid false indications about NDB direction, it is necessary to select ANT function in order to query the selected station and to listen to its identification code.
Page 265 Page A5-4 INTENTIONALLY LEFT BLANK Edition, Rev. 0 Section 9 - Supplements Supplement no. A5 – KR 87 ADF System...
Page 266 Page A6-1 . A6 – KN 63 DME S UPPLEMENT NO YSTEM Record of Revisions EASA Approval Tecnam Approval Revised Description of or Under DOA page Revision Privileges Approved under DOA Editorial Change A. Sabino C. Caruso M. Oliva No. EASA.21J.335...
Page 267 NAV1. LIMITATIONS DME KN 63 manuals do not address operating limitations more severe than those usually applicable to the P2006T. EMERGENCY PROCEDURES In determined conditions, near the beacon, DME signal can be lost or distorted.
Page 268: Detailed Operating Procedures
Page A6-3 NORMAL OPERATIONS ETAILED OPERATING PROCEDURES It is recommended that power to the KN 63 be turned on only after engine start- up, as this procedure increases the reliability of the solid state circuitry. The rotary switch on the front of the KDI 572 has four positions: Off, N1, Hold, and N2.
Page 269 Page A6-4 The distance measured by the KN 63 is slant-range distance (measured on a slant from aircraft to ground station) and should not be confused with actual ground dis- tance. The difference between ground distance and slant-range distance is smallest at low altitude and long range.
Page 270 Page A6-5 SYSTEMS The KN 63 is a remote mounted, 200 channel TSO'd DME employing a solid-state transmitter and large scale integrated circuit (LSI) technology. All tuning is done electronically; using a single crystal, digital, frequency synthesizer. Range, speed, and time-to-station are measured digitally, using two LSI's. Another LSI is em- ployed in the digital frequency synthesizer.
Page 271 Page A6-6 INTENTIONALLY LEFT BLANK Edition, Rev. 0 Section 9 - Supplements Supplement no. A6 – KN 63 DME System...
Page 272 Page A7-1 . A7 – KCS 55A C UPPLEMENT NO OMPASS YSTEM Record of Revisions EASA Approval Tecnam Approval Revised Description of or Under DOA page Revision Privileges Approved under DOA Editorial Change A. Sabino C. Caruso M. Oliva No. EASA.21J.335...
Page 273 LIMITATIONS KCS 55A manuals do not address operating limitations more severe than those usually applicable to the P2006T. EMERGENCY PROCEDURES If the power warning flag appears on the indicator, the system has experienced a power failure and the card indications are in error.
Page 274 Page A7-3 PERFORMANCES KCS 55A employment does not affect the aircraft performances. WEIGHT AND BALANCE See Section 6 of this Manual. SYSTEMS Refer to the guide “Bendix/King KCS 55A Compass System Pilot’s Guide” (P/N 006-08256-0004), dated 06/1992 or later, for a complete system description. Edition, Rev.
Page 275 Page A7-4 INTENTIONALLY LEFT BLANK Edition, Rev. 0 Section 9 - Supplements Supplement no. A7 – KCS 55A Compass System...
Page 276 Page A8-1 . A8 - G GNS-530W GPS/WAAS UPPLEMENT NO ARMIN COMM/NAV Record of Revisions EASA Approval Tecnam Approval Revised Description of or Under DOA page Revision Privileges Approved under DOA Editorial Change A. Sabino C. Caruso M. Oliva No. EASA.21J.335...
Page 277 Page A8-2 INTRODUCTION This section contains supplemental information to operate, in a safe and efficient manner, the aircraft when equipped with Garmin GNS-530W device. GENERAL 1. GPS GNS-530W is an integrated system which contains, in addition to the GPS navigation system, a VHF COMM transceiver and a VOR/ILS receiver. 2.
Page 278 Page A8-3 LIMITATIONS 1. The GARMIN 500W Series Pilot’s guide and Reference (p/n 190-00357-00) Rev G, or a more updated version, must be available onboard for the correct device use. 2. The system employment is allowed only in VFR flight conditions. 3.
Page 279 Page A8-4 EMERGENCY PROCEDURES 1. Should the Garmin GNS-530W information be unavailable or manifestly wrong, it is nec- essary to use other navigation instruments. 2. If during navigation (only in ENROUTE mode) GPS signal is lost, the instrument contin- ues to operate in DR (Dead Reckoning) mode. Aircraft position is estimated on the basis of the last GPS valid signal, but it can be significantly distorted by relative speed varia- tions.
Page 280 Page A8-5 NORMAL OPERATIONS ETAILED OPERATING PROCEDURES Normal operations procedures are reported on GARMIN 500W Series Pilot’s guide and Reference (p/n 190-00357-00) Rev G or later versions. PERFORMANCES The Garmin GNS-530W employment does not affect the aircraft performances. WEIGHT AND BALANCE See Section 6 of this Manual.
Page 281 Page A8-6 INTENTIONALLY LEFT BLANK Edition, Rev. 0 Section 9 - Supplements Supplement no. A8 – Garmin GNS-530W GPS/WAAS COMM/NAV...
Page 282 Page A9-1 . A9 - G GTX330 M UPPLEMENT NO ARMIN TRANSPONDER Record of Revisions EASA Approval Tecnam Approval Revised Description of or Under DOA page Revision Privileges Approved under DOA Editorial Change A. Sabino C. Caruso M. Oliva No. EASA.21J.335...
Page 283 Garmin GTX 330 is a transponder operating with A, C and S mode. LIMITATIONS Garmin GTX 330 manuals do not address operating limitations more severe than those usually applicable to the P2006T. EMERGENCY PROCEDURES In case of emergency conditions, transponder is able to sent codified messages to the Air Traffic Control;...
Page 284 Page A9-3 NORMAL OPERATIONS ETAILED OPERATING PROCEDURES Normal operating procedures are described on GARMIN GTX 330/330D Mode S Transponder Pilot’s guide (P/N 190-00207-00) rev. F or later versions. GARMIN GTX 330/330D Mode S Transponder Pilot’s guide NOTE (P/N 190-00207-00) - rev. F or later versions - must be car- ried onboard the airplane at all times.
Page 285 Page A9-4 INTENTIONALLY LEFT BLANK Edition, Rev. 0 Section 9 - Supplements Supplement no. A9 – Garmin GTX330 Mode S transponder...
Page 286 Page A10-1 . A10 - G GMA347 UPPLEMENT NO ARMIN AUDIO PANEL Record of Revisions EASA Approval Tecnam Approval Revised Description of or Under DOA page Revision Privileges Approved under DOA Editorial Change A. Sabino C. Caruso M. Oliva No. EASA.21J.335...
Page 287 Garmin GMA347 device. GENERAL Garmin GMA347 is the audio management device used on P2006T. The audio panel handles internal audio communications (INTERCOM), external audio communications (allowing COM1 to COM2 switching), those related to the markers during ILS approaches and, eventually, those related to the on board mu- sical entertainment (compact disc devices etc).
Page 288 Page A10-3 NORMAL OPERATIONS ETAILED OPERATING PROCEDURES Normal operating procedures are described on “GARMIN GMA 347 Pilot’s guide” (P/N 190-00325-00) rev. B or later versions. GARMIN GMA 347 Pilot’s guide” (P/N 190-00325-00) - rev. NOTE B or later versions - must be carried onboard the airplane at all times.
Page 289 Page A10-4 INTENTIONALLY LEFT BLANK Edition, Rev. 0 Section 9 - Supplements Supplement no. A10 – Garmin GMA347 audio panel...
Page 290 Page A11-1 . A11 – B BXP 6401-2-(01) UPPLEMENT NO ECKER TRANSPONDER Record of Revisions EASA Approval Tecnam Approval Revised Description of or Under DOA page Revision Privileges Approved under DOA Editorial Change A. Sabino C. Caruso M. Oliva No. EASA.21J.335...
Page 291 Becker BXP 6401-2-1 (01) is a transponder operating with A,C and S mode. LIMITATIONS Becker BXP 6401-2-1 (01) manuals do not address operating limitations more se- vere than those usually applicable to the P2006T. Edition, Rev. 0 Section 9 - Supplements...
Page 292 Page A11-3 EMERGENCY PROCEDURES In case of emergency conditions, transponder is able to sent codified messages to the Air Traffic Control; messages are classified as follows: Code Condition 7500 Aircraft subjected to illegal interference 7600 Loss of radio communications 7700 Emergencies NORMAL OPERATIONS ETAILED OPERATING PROCEDURES...
Page 293 Page A11-4 INTENTIONALLY LEFT BLANK Edition, Rev. 0 Section 9 - Supplements Supplement no. A11 – Becker BXP 6401-2-(01) Mode S Transponder...
Page 294 Page A12-1 . A12 – S-TEC F UPPLEMENT NO IFTY UTOPILOT Record of Revisions EASA Approval Tecnam Approval Revised Description of or Under DOA page Revision Privileges Approved under DOA Editorial Change A. Sabino C. Caruso M. Oliva No. EASA.21J.335...
Page 295 Page A12-2 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. 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 296: Limitations (Easa Approved)
Page A12-3 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 297 Page A12-4 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. A12 – S-TEC Fifty Five X Autopilot...
Page 298 Page A12-5 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 299 Page A12-6 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 300: Press And Hold
Page A12-7 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: PRESS and HOLD 1. AP DISC/TRIM INTR switch 2. TRIM MASTER SWITCH 3.
Page 301 Page A12-8 YRO DIRECTIONAL SIGNAL LOST When AP is engaged and the gyro directional electrical supply is lost (instrument warning flag displayed), an aural warning alerts the pilot to the failure; in this case the AP must be disconnected applying following procedure: Accomplish items 1 and 2 simultaneously: GRASP FIRMLY and OVERPOWER if 1.
Page 302 Page A12-9 NORMAL OPERATIONS Normal operating procedures, including pre-flight checks, are described on S-TEC “Pilot’s Operating Handbook Fifty Five X” (4th Edition – First Revision dated March 01, 2008 or a more updated version). The vertical speed mode is used to establish and hold a PILOT selected vertical speed.
Page 303 Page A12-10 SYSTEMS The System Fifty Five X Block Diagram is shown in the following figure. Edition, Rev. 0 Section 9 - Supplements Supplement no. A12 – S-TEC Fifty Five X Autopilot...
Page 304 Page A13-B-1 . A13-B - G GTN-650/750 GPS/WAAS UPPLEMENT NO ARMIN COMM/NAV Record of Revisions EASA Approval or Tecnam Approval Revised Description of Under DOA page Revision Privileges Approved under DOA Editorial Change A. Sabino C. Caruso M. Oliva No. EASA.21J.335 privi-...
Page 305 Page A13-B-2 INTRODUCTION This section contains supplemental information to operate, in a safe and efficient manner, aircraft when equipped with Garmin 650/750 COMM/NAV/GPS unit. GENERAL 1. GTN 650/750 is an integrated unit with touchscreen interface that contains a GPS navigation system in addition to a VHF COMM radio transceiver and a VOR/ILS receiver.
Page 306 Page A13-B-3 LIMITATIONS (EASA APPROVED) 1. The GARMIN GTN 650/750 Pilot's Guide and Reference p/n 190-01004-03 rev. E / p/n 190-01007-03 Rev. B, or a more updated version, must be available on board for the correct device use. 2. The system employment is allowed in IFR flight conditions. Main subsystem software version is indicated for 5 seconds immediately after the GTN 650/750 system has been turned on.
Page 307 Page A13-B-4 EMERGENCY PROCEDURES 1. Should the Garmin GTN 650/750 information be unavailable or manifestly wrong, it is necessary to use other navigation instruments. 2. If during navigation (only in ENROUTE mode) GPS signal is lost, the instrument contin- ues to operate in DR (Dead Reckoning) mode. Aircraft position is estimated on the basis of the last GPS valid signal, but it can be significantly distorted by relative speed varia- tions.
Page 308: Instrument Panel
Page A13-B-5 NORMAL OPERATIONS ETAILED OPERATING PROCEDURES Normal operations procedures are reported on the GARMIN GTN 650/750 Pilot's Guide and Reference p/n 190-01004-03 rev. E / 190-01007-03 Rev. B or later. GARMIN GTN 650 Pilot's Guide and Reference p/n 190- NOTE 01004-03 rev.
Page 309 Page A13-B-6 Tab 2 DESCRIPTION Audio Panel Transponder ADF (Kit B) COMM/NAV SL30 (Kit A) GPS/NAV/COMM GTN 650 Available Avionic Switches Cross Bus Switches VOR/ILS Indicator SYSTEMS Refer to GARMIN GTN 650 Pilot's Guide and Reference p/n 190-01004-03 rev. E / 190-01007-03 Rev.
Page 310 Page A14-1 . A14 – E UPPLEMENT NO NGINE STARTING BATTERY Record of Revisions EASA Approval Tecnam Approval Revised Description of or Under DOA page Revision Privileges Approved under DOA Editorial Change A. Sabino C. Caruso M. Oliva No. EASA.21J.335...
Page 311 Page A14-2 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 312 Page A14-3 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 313 Page A14-4 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 314 Page A15-1 . A15 – 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 Approved under DOA Editorial Change A. Sabino C. Caruso M. Oliva No.
Page 315 Page A15-2 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. A15 – POWER SUPPLY FROM BUILT-IN GENERATORS...
Page 316 Page A15-3 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 317 Page A15-4 EMERGENCY PROCEDURES In event of the following failure conditions (addressed on Section 3 of this Manual):  Single Engine operations  Single generator failure (Para. 3.2)  Single generator overvoltage (Para 3.4)  Both generators failure (Para. 3.1) ...
Page 318 Page A15-5 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 319 Page A15-6 INTENTIONALLY LEFT BLANK Edition, Rev. 0 Section 9 - Supplements Supplement no. A15 – POWER SUPPLY FROM BUILT-IN GENERATORS...
Page 320 Page A16-1 . A16 UPPLEMENT NO AFM S UPPLEMENT FOR COUNTRIES OPERATORS Record of Revisions EASA Approval Tecnam Approval Revised Description of or Under DOA page Revision Privileges Editorial Change (*) Note (*): this Supplement has been originally issued on 12 November 2010, after EASA Third Country Validation process completion.
Page 321 Page A16-2 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 322: Introduction
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 323: Limitations (Easa Approved)
Page A16-4 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 324: Over-Water Flights
Page A16-5 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 325: Other Placards
Page A16-6 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 326 Page A16-7 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 327: Emergency Procedures
Page A16-8 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 328: Loss Of Aileron Control
Page A16-9 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 329: One Engine Inoperative Procedures
Page A16-10 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 330: Inflight Engine Restart
Page A16-11 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 331: Landing Emergencies
Page A16-12 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 332: Normal Operations
Page A16-13 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 333: Aircraft Walk-Around
Page A16-14 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. A16 – AFM Supplement for CIS countries operators...
Page 334: Cockpit Inspections
Page A16-15 OCKPIT INSPECTIONS Make sure that passengers are familiar with the safety belts and emergen- cy 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 335: Takeoff And Climb
Page A16-16 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 FULL THROTTLE (about 2400 propeller rpm)
Page 336: Balked Landing
Page A16-17 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 337: Performances
Page A16-18 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 338 Page A16-19 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 339: Climb Performance (One Engine Inoperative)
Page A16-20 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 340 Page A16-21 INTENTIONALLY LEFT BLANK Edition, Rev. 0 Section 9 – Supplements Supplement no. A16 – AFM Supplement for CIS countries operators...
Page 341: Weight And Balance
Page A16-22 WEIGHT AND BALANCE For weight and balance, make reference to Section 6 of this Manual. Edition, Rev. 0 Section 9 – Supplements Supplement no. A16 – AFM Supplement for CIS countries operators...
Page 342 Page A16-23 SYSTEMS NSTRUMENTS PANEL Instruments panel (typical layout) Tab 1 DESCRIPTION Airspeed indicator Attitutude Indicator Altimeter (metric unit) VOR/ILS Indicator ADF Indicator (Kit B) Vertical Speed Indicator Directional Gyro Indicator Turn Coordinator Annunciator Panel DME Indicator (Kit B) Directional Trim Indicator Cabin Heat / Defrost Dimmers ELT Control Panel...
Page 343 Page A16-24 Tab 2 DESCRIPTION Audio Panel Transponder ADF (Kit B) COMM/NAV SL30 (Kit A) GPS/NAV/COMM GNS 430 Available Avionic Switches Cross Bus Switches VOR/ILS Indicator Central instruments panel (typical layout) Tab 3 DESCRIPTION Fuel Quantity Indicators Oil Pressure Indicators Oil Temperatures Indicators CHT Indicators RPM Indicators...
Page 344 Page A16-25 Tab 4 DESCRIPTION DESCRIPTION Pitot Heating Switch Flap Control Available Flap Indicator LH Field Landing Light Switch Battery Master Switch Taxi Lights Switch RH Field Position Lights Switch Landing Gear lights Strobe Lights Switch Unsafe Light Instrument Lights Switch Light Test Landing Gear lever Switches panels...
Page 345 Page A16-26 INTENTIONALLY LEFT BLANK Edition, Rev. 0 Section 9 – Supplements Supplement no. A16 – AFM Supplement for CIS countries operators...
Page 346 Page A17-1 . A17 UPPLEMENT NO BRAZILIAN AIRCRAFT FLIGHT MANUAL SUPPLEMENT (EASA APPROVED) Edition, Rev. 0 Section 9 – Supplements Supplement no. A17 – BRAZILIAN AFMS...
Page 347 Page A17-2 Record of Revisions EASA Approval Tecnam Approval Revised Description of or Under DOA page Revision Privileges Editorial Change Note (*): this Supplement has been originally issued on 4 March 2011, after EASA Third Country Validation pro- cess completion.
Page 348 Page A17-3 TABLE OF CONTENTS INTRODUCTION ......................4 GENERAL ........................4 LIMITATIONS ......................5 Approved fuel ......................5 VHF/COMM system ..................... 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) ..
Page 349 Page A17-4 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 350: Approved Fuel
Page A17-5 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 351: Gps Systems
Page A17-6 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 352: Waas And Sbas Functionalities
Page A17-7 GPS GNS 430 GNS 530 OPERATION FOR AIRPLANES WITHOUT 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 353 Page A17-8 LACARDS IN ORTUGUESE Description Placard Place Smoking ban Instruments panel, right side Engine oil lev- On the engine na- el and specifi- celle, corre- cations spondence of the engine oil reservoir access door Fuel type and In correspondence quantity of each fuel tank filler cap.
Page 354 Page A17-9 Description Placard Place Ditching emer- Ditching emergen- gency exit: cy exit handle: ex- opening ternal side structions Ditching emer- Ditching emergen- gency exit: cy exit handle: in- opening ternal side structions Door locking Main door system: emergency exit: pass instruc- external side...
Page 355 Page A17-10 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. A17 – BRAZILIAN AFMS...
Page 356 Page A18-1 . A18 UPPLEMENT NO CHINESE AIRCRAFT FLIGHT MANUAL SUPPLEMENT (EASA APPROVED) Edition, Rev. 0 Section 9 - Supplements Supplement no. A18 – CHINESE AFMS...
Page 357 Page A18-2 Record of Revisions EASA Approval Tecnam Approval Revised Description of or Under DOA page Revision Privileges Editorial Change (*) A. Sabino C. Caruso M. Oliva Note (*): This Supplement was originally issued under third country validation. List of Effective Pages...
Page 358 Page A18-3 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. A18 – CHINESE AFMS...
Page 359 Page A18-4 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 360 Page A18-5 LIMITATIONS PPROVED FUEL MOGAS compliant with PRC National Standard GB17930-2006 - Octane Rating (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 361 Page A18-6 LACARDS IN HINESE Description/Place Placard Chinese 禁止吸烟 Smoking ban. Instruments panel, right side 滑油箱 Engine oil level and 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 362 Page A18-7 Description/Place Placard Chinese 水上迫降应急出口 Ditching emergency exit: opening instruc- tions. 1、旋转。 2、平稳向外推。 Ditching emergency exit handle: internal side 水上迫降应急出口 Ditching emergency exit: opening instruc- tions. 1、旋转。 2、平稳向内拉。 Ditching emergency exit handle: external side 应急通道 Door locking system: by-pass instructions. 1、按住红色扭。...
Page 363 Page A18-8 Description/Place Placard Chinese 警告 Main door: exit in- 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 应急出口 Emergency exit label. Emergency exit: inter- nal and external side 注意 Maximum steering angle. 牵引最大转弯角度：中立两侧20度。 Front of the aircraft. Edition, Rev. 0 Section 9 - Supplements Supplement no.
Page 364 Page A18-9 INTENTIONALLY LEFT BLANK Edition, Rev. 0 Section 9 - Supplements Supplement no. A18 – CHINESE AFMS...
Page 365: Cold Weather Operations
Page A18-10 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 366 Page A18-11 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 367 Page A18-12 INTENTIONALLY LEFT BLANK Edition, Rev. 0 Section 9 - Supplements Supplement no. A18 – CHINESE AFMS...
Page 368 Page A19-1 . A19 – I MTOW (1230 UPPLEMENT NO NCREASED ECORD OF EVISIONS EASA Approval Tecnam Approval Revised Description of Or Under DOA page Revision Privileges New Edition D. Ronca M. Oliva M. Oliva DOA privileges W5-16 Amend cruise performance table D.
Page 369 Page A19-2 LOEP Page Revision Cover pages A19-1 thru 2 Rev 2 A19-3 thru 12 Rev 0 Section 2 W2- 5 thru 8, Rev 0 15 thru 16, 21 thru 22 W5-16 Rev 1 Section 5 W5-1 thru 15, Rev 0 17 thru 22 Edition, Rev.2 Section 9 –...
Page 370 Page A19-3 INTRODUCTION This Supplement provides supplemental information to perform Increased Maximum Takeoff Weight, 1230 kg (2712 lb), operations when the Tecnam Service Bulletin SB 076-CS or Design Change MOD 2006/015 has been embodied on the airplane. The information contained herein supplements or supersedes the basic Aircraft...
Page 371 Page A19-4 Supplement A19: pages replacement instructions SECTION 1 - GENERAL See basic AFM - Section 1 Edition, Rev. 0 Section 9 – Supplements Supplement no. A19 – Increased MTOW (1230 kg)
Page 372 Page A19-5 Supplement A19: pages replacement instructions SECTION 2 - LIMITATIONS Apply following pages replacement procedure: Supplement A19 – Basic AFM LIMITATIONS page Section 2 page W2-5 REPLACES Page 2-5 W2-6 REPLACES Page 2-6 W2-7 Page 2-7 REPLACES W2-8 REPLACES Page 2-8 W2-15 REPLACES...
Page 373 Page A19-6 INTENTIONALLY LEFT BLANK Edition, Rev. 0 Section 9 – Supplements Supplement no. A19 – Increased MTOW (1230 kg)
Page 374: Speed Limitations
Increased MTOW (1230 kg) - Supplement Page W2-5 PEED LIMITATIONS The following table addresses the airspeed limitations and their operational signif- icance: SPEED KIAS KCAS REMARKS V NE Never exceed speed Do not exceed this speed in any operation. V NO Maximum Structural Cruising Do not exceed this speed Speed...
Page 375 Increased MTOW (1230 kg) - Supplement Page W2-6 INTENTIONALLY LEFT BLANK Edition, Rev. 0 Section 2 – Limitations...
Page 376 Increased MTOW (1230 kg) - Supplement Page W2-7 IRSPEED INDICATOR MARKINGS Airspeed indicator markings and their colour code are explained in the following table. MARKING KIAS EXPLANATION White arc 54-93 Lower limit is V , upper limit is the maxi- mum allowable speed with flaps extended in FULL position.
Page 377 Increased MTOW (1230 kg) - Supplement Page W2-8 INTENTIONALLY LEFT BLANK Edition, Rev. 0 Section 2 – Limitations...
Page 378 Increased MTOW (1230 kg) - Supplement Page W2-15 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 379 Increased MTOW (1230 kg) - Supplement Page W2-16 INTENTIONALLY LEFT BLANK Edition, Rev. 0 Section 2 – Limitations...
Page 380: Limitations Placards
Page W2-21 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, above on the left, it is placed the following placard reporting the speed limitations:...
Page 381: Operating Limitations
Increased MTOW (1230 kg) - Supplement Page W2-22 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 382 Page A19-7 Supplement A19: pages replacement instructions EMERGENCY PROCEDURES Apply following instruction: See basic AFM - Section 3 Because of MTOW increase, the best rate-of-climb speed with ) is 84 KIAS. Refer to “Characteris- one engine inoperative (V NOTE tic airspeeds with one engine inoperative” table reported on basic AFM Section 3.
Page 383 Page A19-8 Supplement A19: pages replacement instructions NORMAL PROCEDURES Apply following instruction: See basic AFM - Section 4 Edition, Rev. 0 Section 9 - Supplements Supplement no. A19 – Increased MTOW (1230 kg)
Page 384 Page A19-9 Supplement A19: pages replacement instructions PERFORMANCES Apply following instruction: Supplement A19 – PERFORMANCES pages replace basic AFM Section 5 as a whole. Edition, Rev. 0 Section 9 - Supplements Supplement no. A19 – Increased MTOW (1230 kg)
Page 385 Page A19-10 INTENTIONALLY LEFT BLANK Edition, Rev. 0 Section 9 - Supplements Supplement no. A19 – Increased MTOW (1230 kg)
Page 386 Increased MTOW (1230 kg) - Supplement Page W5 - 1 SECTION 5 - PERFORMANCES INDEX Introduction ......................2 Use of performances charts ................2 Airspeed indicator system calibration ............... 3 ICAO Standard Atmosphere ................4 Examples: ......................4 Stall speed ......................5 Crosswind ......................
Page 387 Increased MTOW (1230 kg) - Supplement Page W5 - 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 388: Airspeed Indicator System Calibration
Increased MTOW (1230 kg) - Supplement Page W5 - 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.
Page 389 Increased MTOW (1230 kg) - Supplement Page W5 - 4 4. ICAO S TANDARD TMOSPHERE c.δA=2250 ft A.δA=1600 ft °C Figure 2 – ICAO chart 5. E XAMPLES Given Find a. Temperature = 20°C c. Corresponding Density Altitude = 2250’ b.
Page 390: Stall Speed
Increased MTOW (1230 kg) - Supplement Page W5 - 5 6. 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.
Page 391 Increased MTOW (1230 kg) - Supplement Page W5 - 6 7. 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 392 Increased MTOW (1230 kg) - Supplement Page W5 - 7 8. 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 4000...
Page 393 Increased MTOW (1230 kg) - Supplement Page W5 - 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 394 Increased MTOW (1230 kg) - Supplement Page W5 - 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 395 Increased MTOW (1230 kg) - Supplement Page W5 - 10 9. 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 1196 6000...
Page 396 Increased MTOW (1230 kg) - Supplement Page W5 - 11 10. 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 3000 1076...
Page 397 Increased MTOW (1230 kg) - Supplement Page W5 - 12 11. 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 1408 1212...
Page 398 Increased MTOW (1230 kg) - Supplement Page W5 - 13 12. 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 1226 1062...
Page 399 Increased MTOW (1230 kg) - Supplement Page W5 - 14 13. 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 -116 S.L.
Page 400 Increased MTOW (1230 kg) - Supplement Page W5 - 15 14. 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 -109 S.L.
Page 401 Increased MTOW (1230 kg) - Supplement Page W5 - 16 15. 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] [lt/hr] [lt/hr]...
Page 402 Increased MTOW (1230 kg) - Supplement Page W5 - 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 25.7 24.3...
Page 403 Increased MTOW (1230 kg) - Supplement Page W5 - 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 20.9 19.7...
Page 404 Increased MTOW (1230 kg) - Supplement Page W5 - 19 16. 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 4000...
Page 405 Increased MTOW (1230 kg) - Supplement Page W5 - 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 406 Increased MTOW (1230 kg) - Supplement Page W5 - 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 407: Balked Landing Climb Gradient
Increased MTOW (1230 kg) - Supplement Page W5 - 22 17. B ALKED LANDING CLIMB GRADIENT Flight conditions (ISA and SL): Weight: 1230 kg (2712 lb) Both FULL FORWARD Throttle levers Flaps DOWN Landing gear MTOW 1230kg (2712 lb) Weight 72 KIAS Speed 9.4% (5.4°)
Page 408 Page A19-11 Supplement A19: page replacement instructions WEIGHT AND BALANCE See basic AFM - Section 6 Edition, Rev. 0 Section 9 - Supplements Supplement no. A19 – Increased MTOW (1230 kg)
Page 409 Page A19-12 Supplement A19: page replacement instructions AIRFRAME and SYSTEMS DESCRIPTION See basic AFM - Section 7 Edition, Rev. 0 Section 9 - Supplements Supplement no. A19 – Increased MTOW (1230 kg)
Page 410 Page A20-1 . A20 – V UPPLEMENT NO NCREASE ECORD OF EVISIONS EASA Approval Tecnam Approval Revised Description of Or Under DOA page Revision Privileges Editorial change (*) A. Sabino C. Caruso M. Oliva DOA Privileges Note (*): This Supplement has been originally issued under EASA approval 10041602 Edition, Rev.
Page 411 Page A20-2 LOEP Page Revision A20-1 Rev 0 A20-2 Rev 0 A20-3 Rev 0 A20-4 Rev 0 A20-5 Rev 0 A20-6 Rev 0 Edition, Rev. 0 Section 9 - Supplements Supplement no. A20 – Vlo/Vle Increase...
Page 412 Page A20-3 INTRODUCTION This Supplement provides supplemental information to increase the Vlo/Vle when the Tecnam Service Bulletin SB 106-CS or Design Change MOD 2006/033 has been embodied on the airplane. The information contained herein supersedes the basic Aircraft Flight Manual.
Page 413: Section 2 - Limitations
Page A20-4 SECTION 2 - LIMITATIONS EASA Approved Edition, Rev. 0 Section 9 - Supplements Supplement no. A20 – Vlo/Vle Increase...
Page 414: Speed Limitations
Page A20-5 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. 0 Section 9 - Supplements Supplement no.
Page 415 Page A20-6 INTENTIONALLY LEFT BLANK Edition, Rev. 0 Section 9 - Supplements Supplement no. A20 – Vlo/Vle Increase...
Page 416 Page A21-1 SUPPLEMENT NO. A21 – SOUTH AFRICAN AFM (SACAA APPROVED) Record of Revisions EASA Approval Tecnam Approval Revised Description of Or Under DOA page Revision Privileges Editorial Change A. Sabino C. Caruso M. Oliva See Note (*) Note (*): this Supplement has been originally issued on 2 May 2013, after EASA Third Country Validation pro- cess completion.
Page 417 Page A21-2 LOEP Page Revision Page Revision A21-1 Rev 0 A21-5 Rev 0 A21-2 Rev 0 A21-6 Rev 0 Rev 0 Rev 0 A21-3 A21-7 Rev 0 Rev 0 A21-4 A21-8 Edition, Rev. 0 Section 9 – Supplements Supplement no. A21 – South African AFM...
Page 418 Page A21-3 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 419 Page A21-4 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 420: Maximum Operating Altitude
Page A21-5 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 421: Gps Systems
Page A21-6 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 422: Waas And Sbas Functionalities
Page A21-7 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. A21 – South African AFM...
Page 423 Page A21-8 INTENTIONALLY LEFT BLANK Edition, Rev. 0 Section 9 – Supplements Supplement no. A21 – South African AFM...
Page 424 Page A22-1 SUPPLEMENT NO. A22 – ARGENTINE AFM Record of Revisions EASA Approval Tecnam Approval Revised Description of Or Under DOA page Revision Privileges Editorial Change A. Sabino C. Caruso M. Oliva See Note (*) Note (*): this Supplement has been originally issued on 5 May 2014, after EASA Third Country Validation process completion.
Page 425 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 426 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 427 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 428 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 429 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 430 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 (see suppl. A14) side Battery hous- On the battery 65x40 housing, left side, aircraft tail cone Engine oil lev-...
Page 431 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 432 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 433 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 434 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 435 Page A22-12 INTENTIONALLY LEFT BLANK Edition, Rev. 0 Section 9 – Supplements Supplement no. A22 – Argentine AFM...
Page 436 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 437 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 438: Introduction
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 439: Limitations
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 440: Kinds Of Operations Equipment List
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 441: Emergency Procedures
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 442: Normal Operations
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 443: Performances
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 444 Page A23-9 INTENTIONALLY LEFT BLANK Edition, Rev. 0 Section 9 - Supplements Supplement no. A23 – Ukrainian AFM Supplement...
Page 445 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 446 Page A23-11 INTENTIONALLY LEFT BLAN Edition, Rev. 0 Section 9 - Supplements Supplement no. A23 – Ukrainian AFM Supplement...
Page 447 Page A23-12 INTENTIONALLY LEFT BLAN Edition, Rev. 0 Section 9 - Supplements Supplement no. A23 – Ukrainian AFM Supplement...
Page 448 Page A24-1 . A24 - SMP UPPLEMENT NO FOR ANALOGIC CONFIGURATION ECORD OF EVISIONS EASA Approval Or Tecnam Approval Revised Description of Under DOA page Revision Privileges First issue D. Ronca C. Caruso M. Oliva DOA Approval Cover Editorial change A.
Page 449 Page A24-2 LOEP Pages Revision A24 – 3 thru 12,14 thru 24 Cover pages Rev. 1 A24-1,2,13 Rev. 2 SMP2 – 3 Rev. 0 Section S2 SMP3 – 4 thru 5 Section S3 Rev. 0 SMP3 – 8 thru 11 Rev.
Page 450 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 451 Page A24-4 INTENTIONALLY LEFT BLANK Ed. 4, Rev. 1 Section 9 - Supplements Supplement no. A24 – SMP...
Page 452 Page A24-5 Supplement A24: pages replacement instructions 1 – GENERAL ECTION Apply following instruction: See basic AFM - Section 1 Ed. 4, Rev. 1 Section 9 - Supplements Supplement no. A24 – SMP...
Page 453 Page A24-6 INTENTIONALLY LEFT BLANK Ed. 4, Rev. 1 Section 9 - Supplements Supplement no. A24 – SMP...
Page 454 Page A24-7 Supplement A24: pages replacement instructions 2 – LIMITATIONS ECTION Apply following pages replacement procedure: Supplement A24 - Basic AFM LIMITATIONS page Section 2 page SMP2 – 3 Page 2 – 3 REPLACES Ed. 4, Rev. 1 Section 9 - Supplements Supplement no.
Page 455 Page A24-8 INTENTIONALLY LEFT BLANK Ed. 4, Rev. 1 Section 9 - Supplements Supplement no. A24 – SMP...
Page 456 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 457 Page A24-9 INTENTIONALLY LEFT BLANK Ed. 4, Rev. 1 Section 9 - Supplements Supplement no. A24 – SMP...
Page 458 Page A24-10 Supplement A24: pages replacement instructions 3 – EMERGENCY PROCEDURES ECTION Apply following pages replacement procedure: Supplement A24 - Basic AFM LIMITATIONS page Section 3 page SMP3 – 4 thru 5 Page 3 – 4 thru 5 REPLACES SMP3 – 8 thru 11 Page 3 –...
Page 459 Page A24-11 INTENTIONALLY LEFT BLANK Ed. 4, Rev. 1 Section 9 - Supplements Supplement no. A24 – SMP...
Page 460 Page SMP3-3 1. I NTRODUCTION This section reports procedures to be replaced on basic AFM. The procedures af- fected by installation of the Special Mission Platform are the following:  Both generators failure  Single generator failure  Both generators overvoltage ...
Page 461: Engine Failure During Takeoff Run
Page SMP3-4 5. Failure lamp: when illuminated, indicates that the correspondent converter is not working properly and needs to be replaced. When all converters are working properly, the system is capable to output 40A@28V. If one con- verter fails, 12A@28V are lost. For this reason, the end-user mission can continue if the equipment demand is less than 25/28A.
Page 462 Page SMP3-5 2. AIRPLANE ALERTS The annunciator panel, located on the left side instrument panel, contains 16 lights for warnings, cautions and advisories. The colours are as follows: GREEN: to indicate that pertinent device is turned ON AMBER: to indicate no-hazard situations which have to be considered and which require a proper crew action RED: to indicate emergency conditions...
Page 463 Page SMP3-5 OTH GENERATORS FAILURE In event of both LH and RH GENERATOR caution lights turned ON: 1. FIELD LH and RH BOTH OFF 2. FIELD LH and RH BOTH ON If the LH (or RH) GENERATOR caution stays displayed 3.
Page 464 Page SMP3-7 OTH GENERATORS OVERVOLTAGE In event of both LH and RH OVERVOLT warning lights turned ON: 1. FIELD LH and RH BOTH OFF 2. FIELD LH and RH BOTH ON If the LH (or RH) GENERATOR caution stays displayed 3.
Page 465 Page SMP3-13 4. 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 After securing engine(s), after analysing situation, refer immediately to following procedures: ENGINE FAILURE IN FLIGHT: see Para.
Page 466 Page SMP3-18 5. O THER EMERGENCIES 5.1. E MERGENCY DESCENT Descent with airspeed at VLE, idle power and gear down will pro- ° vide high descent rates and pitch attitudes up to -15 Anticipate altitude capture and return to level flight during emer- gency descent in order to assure a safe and smooth recovery from CAUTION maneuver.
Page 467: Inflight Engine Restart
Page SMP3-25 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. Fuel Selector CHECK (Crossfeed if required) FIELD Ignition BOTH ON...
Page 468 Page SMP3-26 7.3 E NGINE FAILURE DURING TAKEOFF RUN BEFORE ROTATION: ABORT TAKE OFF Throttle Lever BOTH IDLE Rudder Keep heading control Brakes As required When safely stopped: 4. 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- formed on ground.
Page 469 Page SMP3-27 At safe altitude Inoperative engine Confirm and SECURE 10. Operative engine Electrical fuel pump Check ON 11. Operating engine Check engine instruments 12. Operating engine Fuel Selector Check correct feeding (crossfeed if needed) If engine restart is recommended: 13.
Page 470 Page SMP3-28 NGINE FAILURE DURING CLIMB Autopilot 2. Heading Keep control using rudder and ailerons 3. Attitude Reduce as appropriate to keep airspeed over 62 KIAS Operating engine Throttle Lever FULL THROTTLE Operating engine Propeller Lever FULL FORWARD 6. Operative engine Electrical fuel pump Check ON Inoperative engine Propeller Lever FEATHER...
Page 471: Engine Failure In Flight
Page SMP3-29 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 (crossfeed if needed) If engine restart is possible:...
Page 472: Master Switch
Page SMP3-38 8. S MOKE AND FIRE OCCURRENCE 8.1. E 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, fuel, hydraulic fluid or oil spills.
Page 473 Page SMP3-39 8.2. E 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 MASTER SWITCH Parking Brake...
Page 474 Page SMP3-40 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 475: Engine Fire In Flight
Page SMP3-41 8.3. E 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 Fire affected engine Electrical fuel pump...
Page 476 Page SMP3-42 8.5. E 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. Fire extinguisher use toward base of flames A tripped circuit breaker should not be reset.
Page 477 Page SMP3-43 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, hydraulic fluid or oil spills. Leave aircraft in upwind direction. WARNING Ed.
Page 478 Page A24-12 INTENTIONALLY LEFT BLANK Ed. 4, Rev. 1 Section 9 - Supplements Supplement no. A24 – SMP...
Page 479 Page A24-13 Supplement A24: pages replacement instructions 4 – NORMAL PROCEDURES ECTION Apply following pages replacement procedure: Supplement A24 - Basic AFM LIMITATIONS page Section 4 page SMP4 – 22 Page 4 – 22 REPLACES Ed. 4, Rev. 2 Section 9 - Supplements Supplement no.
Page 480 Page A24-14 INTENTIONALLY LEFT BLANK Ed. 4, Rev. 1 Section 9 - Supplements Supplement no. A24 – SMP...
Page 481 Page SMP4-22 4.7. C RUISE LH and RH Propeller Lever SET to 1900-2250 RPM Throttles MAP decrease should be made before propeller speed re- duction below 2200 RPM, as, contrariwise, Propeller Lever increase RPM should be set before engine Throttle Levers are advanced. CAUTION Engine parameters check (LH and RH): ...
Page 482 Page A24-15 INTENTIONALLY LEFT BLANK Ed. 4, Rev. 1 Section 4 - Normal procedures CHECKLISTS...
Page 483 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 484 Page A24-17 INTENTIONALLY LEFT BLANK Ed. 4, Rev. 1 Section 9 - Supplements Supplement no. A24 – SMP...
Page 485 Page A24-18 Supplement A24: pages replacement instructions 6 – WEIGHT AND BALANCE ECTION Apply following instruction: See basic AFM - Section 6 Ed. 4 Rev. 1 Section 9 - Supplements Supplement no. A24 – SMP...
Page 486 Page A24-19 INTENTIONALLY LEFT BLANK Ed. 4 Rev. 1 Section 9 - Supplements Supplement no. A24 – SMP...
Page 487 Page A24-20 Supplement A24: pages replacement instructions 7 – AIRFRAME AND SYSTEMS DESCRIPTION ECTION Apply following pages replacement procedure: Supplement A24 - Basic AFM LIMITATIONS page Section 7 page SMP7 – 40 thru 46 Page 7 – 40 thru 44 REPLACES Ed.
Page 488 Page A24-21 INTENTIONALLY LEFT BLANK Ed. 4 Rev. 1 Section 9 - Supplements Supplement no. A24 – SMP...
Page 489: Electrical Systems
Page SMP7-40 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 490 Page SMP7-41 The following loads are connected to the battery bus: Battery Bus Audio Panel VHF COMM 1 NAV 1 LH and RH Fuel electrical pump LH and RH Fuel pressure indicators LH and RH Fuel quantity indicators LH and RH oil pressure indicators LH and RH oil temperature indicators LH and RH CHT indicators LH and RH RPM indicators...
Page 491 Page SMP7-42 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 NAV 1 RH attitude indicator A/P (*)
Page 492 Figure 23 – 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 493: Converter Box
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 494 Page SMP7-45 In the following figures the new Electrical system schematic is reported. Figure 24 – Electrical system schematic (Page 1) Ed. 4, Rev. 0 Section 7 – Airframe and systems description ELECTRICAL SYSTEMS...
Page 495 Page SMP7-46 Figure 25 – Electrical system schematic (Page 2) Figure 26 – Electrical system schematic (Page 3) Ed. 4, Rev. 0 Section 7 – Airframe and systems description ELECTRICAL SYSTEMS...
Page 496 Page A24-22 INTENTIONALLY LEFT BLANK Ed. 4, Rev. 1 Section 7 – Airframe and systems description ELECTRICAL SYSTEMS...
Page 497: Ground Handling & Service
Page A24-23 Supplement A24: pages replacement instructions 8 – GROUND HANDLING & SERVICE ECTION Apply following instruction: See basic AFM - Section 8 Ed. 4, Rev. 1 Section 9 - Supplements Supplement no. A24 – SMP...
Page 498 Page A24-24 INTENTIONALLY LEFT BLANK Ed. 4, Rev. 1 Section 9 - Supplements Supplement no. A24 – SMP...
Page 499 Page A25-1 . A25 – 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 (*) A25-5 Blank page removed List of Effective Pages...
Page 500 Page A25-2 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 501 Alternators with 70A - Supplement Page A25-3 Section 3 – SECTION 3 - EMERGENCY PROCEDURES 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 INDEX following: ...
Page 502 Alternators with 70A - Supplement Page A25-4 Section 3 – INGLE GENERATOR FAILURE OVERVOLTAGE Emergency procedures INDEX In event of LH or RH GENERATOR caution light turned ON, apply following procedure: 1. FIELD LH (or RH) 2. FIELD LH (or RH) If the LH (or RH) GENERATOR caution stays displayed 3.
Page 503 Page A26-1 . A26 UPPLEMENT NO IRCRAFT LIGHT ANUAL UPPLEMENT MG95 IS 2796:2017 FOR MOGAS Record of Revisions EASA Approval or Tecnam Approval Revised Description of Under DOA page Revision Privileges A. Sabino Editorial change C. Caruso M. Oliva DOA Approval EASA Approval N°...
Page 504 Page A26-2 NTRODUCTION This supplement contains supplemental information to the basic information approved in EASA aircraft Flight Manual when the aircraft is modified with type certificate change MOD2006/284 and MOD2006/460. For Limitations, procedures, and performance information not contained in this sup- plement, refer to the basic Aircraft Flight Manual.
Page 505 Page A26-3 2 – LIMITATIONS ECTION The following pages should be added to the basic AFM Edition, Rev. 1 Supplement no. A26 MG95 IS 2796:2017 MOGAS...
Page 506 Page A26-4 FUEL The following fuel should be added to the ones listed in section 2 of the original • MOGAS MOGAS MG 95 compliant to IS 2796:2017, NOTE: For additional information, refer to Rotax Service Instruction No. 912-016, latest issue.
Page 507 Page A27-1 . A27 - G GMA345 UPPLEMENT NO ARMIN AUDIO PANEL Record of Revisions EASA Approval Tecnam Approval Revised Description of or Under DOA page Revision Privileges Approved under the First issue G. Valentino D. Ronca M. Oliva authority of DOA ref.
Page 508 Garmin GMA345 device. GENERAL Garmin GMA345 is the audio management device used on P2006T. The audio panel handles internal audio communications (INTERCOM), external audio communications (allowing COM1 to COM2 switching), those related to the markers during ILS approaches and, eventually, those related to the on board mu- sic entertainment.
Page 509: Normal Operations
Page A27-3 NORMAL OPERATIONS ETAILED OPERATING PROCEDURES Normal operating procedures are described on “GARMIN GMA 345 Pilot’s guide” (P/N 190-01878-01) rev. C or later versions. GARMIN GMA 345 Pilot’s guide” (P/N 190-01878-01) - rev. NOTE C or later versions - must be carried onboard the airplane at all times.
Page 510 Page A27-4 INTENTIONALLY LEFT BLANK Edition, Rev. 0 Section 9 - Supplements Supplement no. A27 – Garmin GMA345 audio panel...
Page 511 Page A28-1 . A28 - GARMIN GTX345R T UPPLEMENT NO RANSPONDER Record of Revisions EASA Approval Tecnam Approval Revised Description of or Under DOA page Revision Privileges Approved under the authority of DOA, ref. Initial issue G. Valentino D. Ronca M.
Page 512 Garmin GTX345R is a transponder operating with A, C and S mode. LIMITATIONS Garmin GTX345R manuals do not address operating limitations more severe than those usually applicable to the P2006T. EMERGENCY PROCEDURES In case of emergency conditions, transponder is able to send codified messages to the Air Traffic Control;...
Page 513 Page A28-3 PERFORMANCES Garmin GTX345R employment does not affect the aircraft performances WEIGHT AND BALANCE See Section 6 of this Manual. SYSTEMS GTX 345R is a Mode S transponder with ADS-B extended squitter capability and also includes UAT and 1090 receivers for ADS-B IN (optional)/OUT capabilities. It is mounted on a rack, located behind the PFD.
Page 514 Page A28-4 INTENTIONALLY LEFT BLANK Edition, Rev. 0 Section 9 - Supplements Supplement no. A28 – GARMIN GTX345R Transponder...
Page 515 Page G1-1 . G1 UPPLEMENT NO G950 IFDS ARMIN Record of Revisions EASA Approval Tecnam Approval Revised Description of or Under DOA page Revision Privileges See Note (*) Amend General rec- S4-3,4 D. Ronca C. Caruso M. Oliva ommendation S4-23,24 Update procedures D.
Page 516 Page G1-2 EASA Tecnam Approval Revised Description of Approval or page Revision Under DOA Privileges Approved under G1-1, 2 Update RoR and LoEP the authority of L. De Salvi D. Ronca M. Oliva DOA, ref. S2-13 EASA.21J.335 Typo errors S3-12 (MOD2006/405.210702)
Page 517 Page G1-3 LOEP Pages Revision G1-1,4,5,6 Rev 9 Cover pages G1-2,3 Rev.13 7,8,14,21,22,29,30 Rev 0 Section S2 Rev 8 2 thru 10, 13 thru 23, 28 Rev 0 thru 31, 34 thus 63 1 thru 6, 9, 33 Rev 5 Section S3 7, 8, 9 Rev.
Page 518 It is the owner’s responsibility to replace the mentioned pages in the AFM in accordance with the instructions herein addressed section by section. Garmin G950 Pilot’s Guide for Tecnam P2006T (P/N 190- 01146-XX) – last issue - must be carried onboard the airplane at all times.
Page 519 Page G1-5 Supplement G1: pages replacement instructions SECTION 1 - GENERAL See Basic AFM - Section 1 Edition, Rev. 9 Section 9 - Supplements Supplement no. G1 – GARMIN G950 IFDS...
Page 520 Page G1-6 Supplement G1: pages replacement instructions SECTION 2 - LIMITATIONS Apply following pages replacement procedure: Supplement G1 – LIMITATIONS Basic AFM page Section 2 page S2-7 REPLACES S2-8 REPLACES S2-13 2-13 REPLACES S2-14 2-14 REPLACES S2-21 2-21 REPLACES S2-22 2-22 REPLACES S2-29...
Page 521 GARMIN G950 IFDS - Supplement Page S2 - 7 Airspeed indicator markings The Airspeed Indicator displays airspeed on a rolling number gauge using a moving tape. The airspeed is displayed inside the black pointer. The pointer remains black until reaching never-exceed speed (V ), at which point it turns red.
Page 522 GARMIN G950 IFDS - Supplement Page S2 - 8 INTENTIONALLY LEFT IN BLANK Edition, Rev. 0 Section 2 – Limitations...
Page 523 GARMIN G950 IFDS - Supplement Page S2 - 13 13 Warning/caution alerts and safe operating annunciations 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 524 Safe operat- ing 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 525: Limitations Placards
GARMIN G950 IFDS - Supplement Page S2 - 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 limita-...
Page 526: Operating Limitations
GARMIN G950 IFDS - Supplement Page S2 - 22 21.2. O PERATING LIMITATIONS On the instrument panel, it is placed the following placard reminding the observance 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 527 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 528 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) ●...
Page 529: Section 3 - Emergency Procedures
Page G1-7 Supplement G1: pages replacement instructions SECTION 3 - EMERGENCY PROCEDURES Apply following page replacement procedure Supplement G1 – EMERGENCY PROCEDURES pages replace Basic AFM Section 3 as a whole Edition, Rev. 0 Section 9 - Supplements Supplement no. G1 – GARMIN G950 IFDS...
Page 530 Page G1-8 INTENTIONALLY LEFT IN BLANK Edition, Rev. 0 Section 9 - Supplements Supplement no. G1 – GARMIN G950 IFDS...
Page 531 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 532 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 ...............47 SMOKE AND FIRE OCCURRENCE ..............49 Engine fire on the ground .................49 8.2 Engine fire during takeoff run ................50...
Page 533: 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 534 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 535 Garmin G950 IFDS -Supplement Page S3 - 5 INTENTIONALLY LEFT BLANK Edition, Rev. 0 Section 3 – Emergency procedures INTRODUCTION...
Page 536 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: GREEN: to indicate that pertinent device is turned ON AMBER:...
Page 537 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 538 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 539 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 540: On The Ground
Garmin G950 IFDS -Supplement Page S3 - 10 AILED DOOR CLOSURE Annunciation window Alert window MAIN DR OPEN Main door open REAR DR OPEN Rear door open In case of door opening / unlocking, related MAIN or REAR DR OPEN alert is displayed. In this case, apply following procedure: ON THE GROUND 1.
Page 541: Pitot Heat
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 542 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 543 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 544: Engine Fire
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 545 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 546 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 547 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 548 Garmin G950 IFDS -Supplement Page S3 - 18 INTENTIONALLY LEFT BLANK Edition, Rev. 0 Section 3 – Emergency procedures G950 SYSTEM FAILURES...
Page 549: Display Failure
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 550 Garmin G950 IFDS -Supplement Page S3 - 20 INTENTIONALLY LEFT BLANK Edition, Rev. 0 Section 3 – Emergency procedures G950 SYSTEM FAILURES...
Page 551 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 552 Garmin G950 IFDS -Supplement Page S3 - 22 INTENTIONALLY LEFT BLANK Edition, Rev. 0 Section 3 – Emergency procedures...
Page 553 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 554 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 (275°F) or CT is above 120°C (248°F) 2. Affected engine Reduce power setting to reduce CHT/CT up to the minimum practical 3.
Page 555 Garmin G950 IFDS -Supplement Page S3 - 25 IL TEMPERATURE LIMIT EXCEEDANCE If oil temperature exceeds maximum limit (130°C/266°F): 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 temperature does not decrease 4.
Page 556 Garmin G950 IFDS -Supplement Page S3 - 26 IL PRESSURE LIMITS EXCEEDANCE If oil pressure exceeds its lower or upper limit (0.8 – 7 bar / 11.5 – 101.5 psi), apply following procedure: Excessive oil pressure drop leads to a high pitch propeller con- figuration with consequent propeller feathering and engine WARNING stopping.
Page 557: Low Fuel Pressure
Garmin G950 IFDS -Supplement Page S3 - 27 OW FUEL PRESSURE Low fuel pressure indications are possible and allowed but the pressure must stabilize to the operating limit within 10 seconds. If not, and pressure decreases below the lower limit (2.2 psi), apply following procedure: 1.
Page 558 Garmin G950 IFDS -Supplement Page S3 - 28 INTENTIONALLY LEFT BLANK Edition, Rev. 0 Section 3 – Emergency procedures...
Page 559: Other Emergencies
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 emergency descent in order to assure a safe and smooth recov- CAUTION ery from maneuver.
Page 560 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 561: Unintentional Flight Into Icing Conditions
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 562: Carburettor Icing
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 563 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 564: One Engine Inoperative Procedures
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 565: Characteristic Airspeeds With One Engine Inoperative
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 566: Inflight Engine Restart
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 567 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 568 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 569 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 570 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 571 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 572: Landing Gear System Failures
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 573 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 574 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 575 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 576 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 577 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 578 Garmin G950 IFDS -Supplement Page S3 - 48 INTENTIONALLY LEFT BLANK Edition, Rev. 0 Section 3 – Emergency procedures...
Page 579: Smoke And Fire Occurrence
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 580 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 581 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 582: Engine Fire In Flight
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 583 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 584 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 585: Unintentional Spin Recovery
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 586: 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 587 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 588 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 589 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 590 Garmin G950 IFDS -Supplement Page S3 - 60 Consider use of ditching emergency exit to escape in case pilot or passenger doors are blocked, watch for engine hot parts, fuel, hy- draulic fluid or oil spills. Leave aircraft in upwind direction. WARNING Edition, Rev.
Page 591 Garmin G950 IFDS -Supplement Page S3 - 61 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 592 Garmin G950 IFDS -Supplement Page S3 - 62 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 593 Garmin G950 IFDS -Supplement Page S3 - 63 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 594 Garmin G950 IFDS -Supplement Page S3 - 64 INTENTIONALLY LEFT BLANK Edition, Rev. 12 Section 3 – Emergency procedures...
Page 595: Section 4 - Normal Procedures
Page G1-9 Supplement G1: pages replacement instructions SECTION 4 - NORMAL PROCEDURES Apply following page replacement procedure Supplement G1 – NORMAL PROCEDURES pages replace Basic AFM Section 4 as a whole. Edition, Rev. 0 Section 9 - Supplements Supplement no. G1 – GARMIN G950...
Page 596 Page G1-10 INTENTIONALLY LEFT BLANK Edition, Rev. 0 Section 9 - Supplements Supplement no. G1 – GARMIN G950...
Page 597 Garmin G950 IFDS - Supplement Page S4 - 1 SECTION 4 – NORMAL PROCEDURES INDEX 1. INTRODUCTION ....................3 1.1. Normal ops general recommendations ............ 3 2. AIRSPEEDS ...................... 7 2.1. Normal operations ..................7 2.2. Single engine training ................8 3.
Page 598 Garmin G950 IFDS - Supplement Page S4 - 2 INTENTIONALLY LEFT BLANK Edition, Rev. 0 Section 4 – Normal procedures...
Page 599 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. As prescribed by the propeller/governor manufacturer, a drop of 400/500 propeller RPM should be produced during this check.
Page 600 RPM. Refer to SL-912-016R2 for additional information. 3. Suitable Fuels. Tecnam remember operators to fill the aircraft with approved and suitable fuels. Use of not approved/unknown fuels may cause damages to the engine. ONLY USE APPROVED FUELS...
Page 601 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 602 Garmin accurately processes and cross-vali- dates the data, but cannot guarantee the accuracy and completeness of the data. Reference“Garmin G950 Pilot’s Guide for the Tecnam P2006T” (P/N 190-01146-XX), last issue, Appendix B concerning SD card use and databases.
Page 603: Normal Operations
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 604: Single Engine Training
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 min- imum speed provides the margin the manufacturer recommends for us when intentionally performing engine inoperative maneuvers during training.
Page 605: Normal Procedures Checklist
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 606 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 607: Pre-Flight Check - Aircraft Walk-Around
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 608 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 609 Garmin G950 IFDS - Supplement Page S4 - 13 (3) Turn the propeller by hand to and fro, feeling the free rotation of 15°or 30° before the crankshaft starts to rotate. If the propeller can be turned between the dogs with practically no friction at all further investigation is neces- sary.
Page 610 Garmin G950 IFDS - Supplement Page S4 - 14 Left wing leading edge Visual inspection. Check cabin ventilation inlet and carburettor heating inlet for con- dition and free of obstruction. Check stall strip. Left wing top and bottom panels Visual inspection Left winglet, nav and strobe Check for integrity and fixing lights, static discharge wick...
Page 611 Garmin G950 IFDS - Supplement Page S4 - 15 closed. Fuel must checked for water and sediment. Verify the tank vent outlet is clear. Propeller and spinner: The propeller blades and spinner should be free of cracks, nicks, dents and other defects and should rotate freely.
Page 612 Garmin G950 IFDS - Supplement Page S4 - 16 INTENTIONALLY LEFT BLANK Edition, Rev. 0 Section 4 – Normal procedures...
Page 613: Cockpit Inspections
Garmin G950 IFDS - Supplement Page S4 - 17 3.3 C OCKPIT INSPECTIONS Instruct passengers on how to use safety belts and normal / emergency exits. 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 614 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 615 Garmin G950 IFDS - Supplement Page S4 - 19 INTENTIONALLY LEFT BLANK Edition, Rev. 0 Section 4 – Normal procedures...
Page 616: Engine Starting
Garmin G950 IFDS - Supplement Page S4 - 20 3.4 E NGINE STARTING Avionics switches must be set OFF during engine starting to prevent avi- onic equipment damage. CAUTION Start clearance Obtain if needed C HRONOMETER START Right engine starting RH Throttle lever IDLE RH Carburetor heat...
Page 617 Garmin G950 IFDS - Supplement Page S4 - 21 RH Ammeter CHECK Amps positive RH Voltmeter CHECK 12 to 14 Volt RH Electric fuel pump Left engine starting LH Throttle lever IDLE LH Carburetor heat LH Propeller Lever FULL FORWARD ON if required LH Choke LH Electrical Fuel pump...
Page 618: Before Taxiing
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 (122°F) at 1200 Nav , Taxi and Landing lights Transponder Stand-by Passengers and crews seat belts Fastened Passengers and crews headphones Set as required...
Page 619: Prior To Takeoff
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: 90°...
Page 620: Line-Up
Garmin G950 IFDS - Supplement Page S4 - 24 LH Propeller Lever GOVERNOR CHECK a) Reduce prop speed to 1200 RPM; b) move propeller lever back to full for- ward position; c) repeat a) and b) 3 times; d) verify that the governor closely and firmly controls the RPM;...
Page 621: Takeoff And Climb
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 622: Cruise
Garmin G950 IFDS - Supplement Page S4 - 26 3.10 RUISE LH and RH Propeller Lever SET to 1900-2250 RPM Throttles MAP decrease should be made before propeller speed reduction be- low 2200 RPM, as, contrariwise, Propeller Lever increase RPM should be set before engine Throttle Levers are advanced.
Page 623: Descent And Approach
Garmin G950 IFDS - Supplement Page S4 - 27 3.12 ESCENT AND APPROACH Propellers As required In order to control engine cooling and life, it is preferable to descend with NOTE power above idle and RPM lower than full continuous. Carburettors heat As required Altimeter setting...
Page 624: Balked Landing/Missed Approach
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 625: Parking/Shut Down
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 Flaps...
Page 626: Postflight Checks
Garmin G950 IFDS - Supplement Page S4 - 30 3.17 OSTFLIGHT CHECKS Protective cover for Pitot tubes, stall warning and static Install port plugs. Lock one control wheel with safety belt. Wheel chocks Place under MLG Aileron lock Place and tighten Pilot and passengers doors.
Page 627 Garmin G950 IFDS - Supplement Page S4 - 31 ADDITIONAL GUIDANCE FOR RNAV Experience of RNAV systems, and Flight FMS in general, has identified the pitfalls of way- point entry error at the receiver as well as inaccuracies and errors in the database itself. Research and experience have both shown that human error, often the result of a lack of familiarity with the airborne equipment, represents the major hazard in operations using RNAV systems.
Page 628 Garmin G950 IFDS - Supplement Page S4 - 32 2) Departure At system initialisation, the flight crew must confirm that the navigation database is current and verify that the aircraft position has been entered correctly. The active flight plan should be checked by comparing the charts, SID or other applicable documents, with the map display.
Page 629 Garmin G950 IFDS - Supplement Page S4 - 33 will also be unavailable over a wide area. Therefore, it is probable that the signal will also be unavailable at a nearby diversion aerodrome. Notwithstanding any normal operational requirements for the identification of an alternate aerodrome, where a RNAV approach is to be flown in conditions where a visual approach will not be possible;...
Page 630 Garmin G950 IFDS - Supplement Page S4 - 34 If the GPS receiver cannot be used for primary guidance, the appropri- ate navigation receiver must be used for the selected approach (e.g., VOR or ILS). The final course segment of ILS approaches, for example, must be flown by tuning the NAV receiver to the proper frequency and selecting that NAV receiver on the CDI The G950 SBAS GPS allows for flying LNAV and LPV approach service levels according...
Page 631 Garmin G950 IFDS - Supplement Page S4 - 35 Integrity Monitoring (RAIM) is a form of ABAS. Lateral guidance is linear with accuracy to within +/- 0.3 NM parallel to either side of the final approach track. LPV (Localiser Performance with Vertical Guidance) This is an Approach Procedure with Vertical Guidance.
Page 632 Garmin G950 IFDS - Supplement Page S4 - 36 However, this RAIM check assumes availability of the full constellation and will not take account of scheduled interruptions or failures. This can lead to a successful RAIM prediction at this point when the RAIM function itself is not available. If RAIM is lost after passing the FAF the equipment should continue to provide navigation, where possible for five minutes, before giving a RAIM loss indication and this should be enough to complete the approach.
Page 633: Ground Towing, Parking And Mooring
Garmin G950 IFDS - Supplement Page S4 - 37 ROUND TOWING PARKING AND MOORING 5.1. 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. Do not turn nose wheel above 20°...
Page 634: Mooring
Garmin G950 IFDS - Supplement Page S4 - 38 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 635 Page G1-11 Supplement G1: pages replacement instructions SECTION 5 - PERFORMANCES See basic AFM - Section 5 Edition, Rev. 0 Section 9 - Supplements Supplement no. G1 – GARMIN G950...
Page 636 Page G1-12 INTENTIONALLY LEFT BLANK Edition, Rev. 0 Section 9 - Supplements Supplement no. G1 – GARMIN G950...
Page 637: Weight And Balance
Page G1-13 Supplement G1: page replacement instructions SECTION 6 - WEIGHT AND BALANCE See basic AFM - Section 6 Edition, Rev. 0 Section 9 - Supplements Supplement no. G1 – GARMIN G950...
Page 638 Page G1-14 INTENTIONALLY LEFT BLANK Edition, Rev. 0 Section 9 - Supplements Supplement no. G1 – GARMIN G950...
Page 639 Page G1-15 Supplement G1: page replacement instructions SECTION 7 - AIRFRAME and SYSTEMS DESCRIPTION Apply following page replacement procedure: Supplement G1 – AIRFRAME and Basic AFM Section 7 SYSTEMS DESCRIPTION page page S7-37 thru S7-46 REPLACE 7-37 thru 7-44 Edition, Rev. 0 Section 9 - Supplements Supplement no.
Page 640 Page G1-16 INTENTIONALLY LEFT BLANK Edition, Rev. 0 Section 9 - Supplements Supplement no. G1 – GARMIN G950...
Page 641: Instruments Panel
Garmin G950 IFDS - Supplement Page S7 - 37 17. INSTRUMENTS PANEL The figure below shows a typical cockpit layout, alternative layouts are possible. GARMIN G950 IFDS - Instruments panel (typical layout) Edition, Rev. 9 Section 7 – Airframe and Systems description INSTRUMENTS PANEL...
Page 642 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 643 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 644 Garmin G950 IFDS - Supplement Page S7 - 40 INTENTIONALLY LEFT BLANK Edition, Rev. 0 Section 7 – Airframe and Systems description INSTRUMENTS PANEL...
Page 645: Electrical System
Garmin G950 IFDS - Supplement Page S7 - 41 18. ELECTRICAL SYSTEM Primary DC power is provided by two engine-driven generators which, during nor- mal operations, operate in parallel. Each generator is rated at 14,2-14,8 Vdc, 40 Amp, and it is fitted with an integrated regulator, which acts to maintain a constant output voltage, and with an automatic overvoltage device protecting the circuits and the electric components from an ex- cessive voltage caused by generator failures.
Page 646 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 647 Garmin G950 IFDS - Supplement Page S7 - 43 The other loads are so divided among following busses: LH GEN Bus LH Avionic Bus Pitot heat RH GEN Bus RH Avionic Bus Landing light Transponder Taxi light Encoder altimeter NAV lights Cabin Fan A/P (*) Rudder trim...
Page 648 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 649 Garmin G950 IFDS - Supplement Page S7 - 45 Electric system schematic Edition, Rev. 0 Section 7 – Airframe and Systems description ELECTRICAL SYSTEM...
Page 650 Garmin G950 IFDS - Supplement Page S7 - 46 INTENTIONALLY LEFT BLANK Edition, Rev. 0 Section 7 – Airframe and Systems description ELECTRICAL SYSTEM...
Page 651 Page G2-1 . G2 – S-TEC F UPPLEMENT NO IFTY UTOPILOT Record of Revisions EASA Approval or Tecnam Approval Revised Description of Under DOA page Revision Privileges A. Sabino Editorial change D. Ronca M. Oliva DOA privileges Approved under the...
Page 652 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 integrated avionics suite. 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 653: Limitations (Easa Approved)
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 654 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. G02 – S-TEC Fifty Five X Autopilot...
Page 655 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 656 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 657 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 658 Page G2-8 Heading information signal lost In case of loss of heading information due to AHRS failure (red X on display field): 1. A/P is still operative but its performances may be degraded since atti- tude information are computed by S-TEC internal slip and turn instru- ment;...
Page 659: Normal Operations
Garmin avionics (AFCS Status Box and/or PFD) and the S-TEC Fifty Five X Autopilot Display. Make reference to the applicable Garmin Avionics Pilot’s Guide for Tecnam P2006T. The vertical speed mode is used to establish and hold a PILOT selected vertical speed.
Page 660 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. G02 – S-TEC Fifty Five X Autopilot...
Page 661 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 662 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 663 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 664 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 665 . G4 – KN 63 DME S UPPLEMENT NO YSTEM ARMIN NTEGRATED VIONICS UITE Record of Revisions EASA Approval Tecnam Approval Revised Description of Or Under DOA page Revision Privileges See Note (*) Approved under the Amended title and references to...
Page 666 Take into account this likelihood when a beacon approach is performed. NORMAL OPERATIONS Normal operating procedures are reported on the applicable Garmin Integrated Avionics Suite Pilot’s Guide for Tecnam P2006T – last issue. Make reference also to “KN 63 Installation Manual ”, P/N 006-00176 Rev. 4 dat- ed October 2004.
Page 667 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 668 Page G4-4 INTENTIONALLY LEFT BLANK Edition, Rev. 0 Section 9 - Supplements Supplement no. G4 – KN 63 DME System for Garmin Integrated Avionics Suite...
Page 669 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 A.Sabino Editorial change (*) C.Caruso M.Oliva DOA privileges Extended applicability to G5-3 G.Valentino D. Ronca M.Oliva...
Page 670 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 671 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 672 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 673 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.
Page 674 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 675: Limitations (Easa Approved)
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 676 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 677 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 678 Page G6-6 INTENTIONALLY LEFT BLANK Edition, Rev. 0 Section 9 - Supplements Supplement no. G6 – POWER SUPPLY FROM BUILT-IN GENERATORS...
Page 679 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 Editorial change (*) A. Sabino C. Caruso M. Oliva DOA Privileges Note (*): this Supplement has been originally issued under EASA Major Design Change Approval no.
Page 680 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 681 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 682 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 683 . G4 – KN 63 DME S UPPLEMENT NO YSTEM ARMIN NTEGRATED VIONICS UITE Record of Revisions EASA Approval Tecnam Approval Revised Description of Or Under DOA page Revision Privileges See Note (*) Approved under the Amended title and references to...
Page 684 Take into account this likelihood when a beacon approach is performed. NORMAL OPERATIONS Normal operating procedures are reported on the applicable Garmin Integrated Avionics Suite Pilot’s Guide for Tecnam P2006T – last issue. Make reference also to “KN 63 Installation Manual ”, P/N 006-00176 Rev. 4 dat- ed October 2004.
Page 685 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 686 Page G4-4 INTENTIONALLY LEFT BLANK Edition, Rev. 0 Section 9 - Supplements Supplement no. G4 – KN 63 DME System for Garmin Integrated Avionics Suite...
Page 687 Page G5-1 . G5 – E UPPLEMENT NO NGINE STARTING BATTERY Record of Revisions EASA Approval or Tecnam Approval Revised Description of Under DOA page Revision Privileges A.Sabino Editorial change (*) C.Caruso M.Oliva DOA privileges Extended applicability to G5-3 G.Valentino D. Ronca M.Oliva...
Page 688 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 689 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 690 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 691 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 Editorial change (*) A. Sabino C. Caruso M. Oliva DOA privileges Note (*): this Supplement has been originally issued under EASA Major Design Change Approval no.
Page 692 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 693 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 694 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 695 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 696 Page G6-6 INTENTIONALLY LEFT BLANK Edition, Rev. 0 Section 9 - Supplements Supplement no. G6 – POWER SUPPLY FROM BUILT-IN GENERATORS...
Page 697 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 (*) Approved under the authority of DOA, L. De Salvi D. Ronca M.
Page 698 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 699: Introduction
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 700: Limitations (Easa Approved)
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 701: Over-Water Flights
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 702: Other Placards
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 703 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 704: Emergency Procedures
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 705: Loss Of Aileron Control
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 706: One Engine Inoperative Procedures
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 707: Inflight Engine Restart
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 708: Landing Emergencies
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 709: Normal Operations
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 710: Aircraft Walk-Around
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 711: Cockpit Inspections
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 712: Takeoff And Climb
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 FULL THROTTLE (about 2400 propeller rpm)
Page 713: Balked Landing
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 714: Performances
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 715 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 716: Climb Performance (One Engine Inoperative)
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 717 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 718 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 719 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 720 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 721 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 722 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 723 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 724 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 725: Vhf/Comm System
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 726: Gps Operation ( For Airplanes With Autopilot In- Stalled )
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 727: Gps Operation ( For Airplanes Without Autopilot In- Stalled )
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 728: Placards In Portuguese
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 729 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 730 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 731 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 732 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 G9-1 Rev 0...
Page 733 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 734 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 735 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 736 Page G9-6 LACARDS IN HINESE Description/Place Placard Chinese 禁止吸烟 Smoking ban. Instruments panel, right side 滑油箱 Engine oil level and 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 737 Page G9-7 Description/Place Placard Chinese 水上迫降应急出口 Ditching emergency exit: opening instruc- tions. 1、旋转。 2、平稳向外推。 Ditching emergency exit handle: internal side 水上迫降应急出口 Ditching emergency exit: opening instruc- tions. 1、旋转。 2、平稳向内拉。 Ditching emergency exit handle: external side 应急通道 Door locking system: by-pass instructions. 1、按住红色扭。...
Page 738 Page G9-8 Description/Place Placard Chinese 警告 Main door: exit in- 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 应急出口 Emergency exit label. Emergency exit: inter- nal and external side 注意 Maximum steering 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 739 Page G9-9 INTENTIONALLY LEFT BLANK Edition, Rev. 0 Section 9 – Supplements Supplement no. G9 – CHINESE AFMS...
Page 740 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 741 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 742 Page G9-12 INTENTIONALLY LEFT BLANK Edition, Rev. 0 Section 9 – Supplements Supplement no. G9 – CHINESE AFMS...
Page 743 Page G10-1 . G10 – I MTOW (1230 UPPLEMENT NO NCREASED ECORD OF EVISIONS EASA Approval Or Tecnam Approval Revised Description of Under DOA page Revision Privileges New Edition D. Ronca C. Caruso M. Oliva Approved under the au- Amend of Cruise performances...
Page 744 Page G10-2 LOEP Page Revision Cover pages G10-1 thru 2 Rev 3 G10-3 thru 12 Rev 0 Section 2 SW2- 5 Rev 0 SW2-6 Rev 0 SW2-7 Rev 0 SW2-8 Rev 0 SW2-15 Rev 0 SW2-16 Rev 0 SW2-21 Rev 0 SW2-22 Rev 0 Section 5...
Page 745 Deck System (Design Change MOD 2006/002). It contains supplemental information to perform Increased Maximum Takeoff Weight (1230 kg) operations when the Tecnam Service Bulletin SB 077-CS or Design Change MOD 2006/015 has been embodied on the airplane. The information contained herein supplements or supersedes the basic Aircraft...
Page 746 Page G10-4 Supplement G10: pages replacement instructions SECTION 1 - GENERAL See Section 1 of the Basic Manual Edition, Rev. 0 Section 9 – Supplements Supplement no. G10 – Increased MTOW (1230 kg)
Page 747 Page G10-5 Supplement G10: pages replacement instructions SECTION 2 - LIMITATIONS Make sure you first applied instructions reported on Supplement G1, Section 2 Limitations Apply following pages replacement procedure: Supplement G10 – Supplement G1 LIMITATIONS page Section 2 page SW2-5 REPLACES Page 2-5 of Basic AFM, Section 2 SW2-6...
Page 748 Page G10-6 INTENTIONALLY LEFT BLANK Edition, Rev. 0 Section 9 – Supplements Supplement no. G10 – Increased MTOW (1230 kg)
Page 749: Speed Limitations
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 V NE Never exceed speed Do not exceed this speed in any operation. V NO Maximum Structural Cruising Do not exceed this speed...
Page 750 GARMIN G950 IFDS – Increased MTOW (1230 kg) Page SW2-6 INTENTIONALLY LEFT BLANK EASA Approved Edition, Rev. 0 Section 2 – Limitations...
Page 751: Airspeed Indicator Markings
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 54-93 Lower limit is V , upper limit is the maxi- mum allowable speed with flaps extended in FULL position.
Page 752 GARMIN G950 IFDS – Increased MTOW (1230 kg) Page SW2-8 INTENTIONALLY LEFT BLANK EASA Approved Edition, Rev. 0 Section 2 – Limitations...
Page 753 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 754 GARMIN G950 IFDS – Increased MTOW (1230 kg) Page SW2-16 INTENTIONALLY LEFT BLANK Edition, Rev. 0 Section 2 – Limitations...
Page 755: Limitations Placards
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:...
Page 756 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 757 Page G10-7 Supplement G10: pages replacement instructions EMERGENCY PROCEDURES Apply following instruction: Section 3 - EMERGENCY PROCEDURES pages as per Supplement G1 Instructions are still valid Because of MTOW increase, the best rate-of-climb speed with ) is 84 KIAS. Refer to “Characteris- one engine inoperative (V NOTE tic airspeeds with one engine inoperative”...
Page 758 Page G10-8 Supplement G10: pages replacement instructions NORMAL PROCEDURES Apply following instruction: Section 4 - NORMAL PROCEDURES pages as per Supplement G1 instructions are still valid Edition, Rev. 0 Section 9 – Supplements Supplement no. G10 – Increased MTOW (1230 kg)
Page 759 Page G10-9 Supplement G10: pages replacement instructions PERFORMANCES Apply following instruction: Supplement G10 – PERFORMANCES pages replace basic AFM Section 5 as a whole. Edition, Rev. 0 Section 9 – Supplements Supplement no. G10 – Increased MTOW (1230 kg)
Page 760 Page G10-10 INTENTIONALLY LEFT BLANK Edition, Rev. 0 Section 9 – Supplements Supplement no. G10 – Increased MTOW (1230 kg)
Page 761 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 762 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 763: Airspeed Indicator System Calibration
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 764 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 765: Stall Speed
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 766 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 767 GARMIN G950 IFDS – Increased MTOW (1230 kg) Page SW5 - 7 7. T AKEOFF PERFORMANCES ° ° ° ° -25/-13 0/32 25/77 50/122 Ground Roll 207 (679) 263 (863) 328 (1076) 401 (1315) 301 (987) S.L. At 50 ft AGL 271 (889) 345 (1132) 429 (1407)
Page 768 GARMIN G950 IFDS – Increased MTOW (1230 kg) Page SW5 - 8 ° ° ° ° -25/-13 0/32 25/77 50/122 Ground Roll 148 (485) 188 (617) 234 (768) 286 (938) 215 (705) S.L. At 50 ft AGL 193 (633) 246 (807) 306 (1004) 374 (1227) 281 (922)
Page 769 GARMIN G950 IFDS – Increased MTOW (1230 kg) Page SW5 - 9 ° ° ° ° -25/-13 0/32 25/77 50/122 Ground Roll 100 (328) 127 (417) 158 (518) 194 (636) 146 (479) S.L. At 50 ft AGL 131 (430) 167 (548) 207 (679) 254 (833) 190 (623)
Page 770 GARMIN G950 IFDS – Increased MTOW (1230 kg) Page SW5 - 10 8. T ATE OF LIMB AT ° ° ° ° -25/-13 0/32 25/77 50/122 S.L. 1276 1088 2000 1133 4000 6000 1230 8000 10000 12000 14000 -164 S.L. 1507 1302 1119...
Page 771 GARMIN G950 IFDS – Increased MTOW (1230 kg) Page SW5 - 11 9. T ATE OF LIMB AT ° ° ° ° -25/-13 0/32 25/77 50/122 S.L. 1214 1037 1000 1147 2000 1080 3000 1013 1230 4000 5000 6000 7000 S.L.
Page 772 GARMIN G950 IFDS – Increased MTOW (1230 kg) Page SW5 - 12 10. E NROUTE ATE OF LIMB AT ° ° ° ° -25/-13 0/32 25/77 50/122 S.L. 1317 1135 1036 2000 1179 1000 4000 1041 6000 1230 8000 10000 12000 14000 S.L.
Page 773 GARMIN G950 IFDS – Increased MTOW (1230 kg) Page SW5 - 13 11. E NROUTE ATE OF LIMB AT ° ° ° ° -25/-13 0/32 25/77 50/122 S.L. 1241 1073 1000 1177 1011 2000 1114 3000 1050 1230 4000 5000 6000 7000 S.L.
Page 774 GARMIN G950 IFDS – Increased MTOW (1230 kg) Page SW5 - 14 12. O NGINE ATE OF LIMB AT ° ° ° ° -25/-13 0/32 25/77 50/122 S.L. 1000 2000 3000 1230 4000 5000 -115 6000 -150 7000 -110 -185 S.L.
Page 775 GARMIN G950 IFDS – Increased MTOW (1230 kg) Page SW5 - 15 13. O NGINE ATE OF LIMB AT ° ° ° ° -25/-13 0/32 25/77 50/122 S.L. 1000 2000 3000 1230 4000 5000 -113 6000 -148 7000 -108 -183 S.L.
Page 776 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 + 30°C (45°C) ISA (15°C/59°F) ISA – 64°F (5°F) ISA + 54°F (113°F) F.C.
Page 777 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 + 30°C (39°C) ISA (9°C/48°F) ISA – 64°F (-6°F) ISA + 54°F (102°F) F.C. F.C.
Page 778 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 + 30°C (27°C) ISA (-3°C/27°F) ISA – 64°F (-27°F) ISA + 54°F (81°F) F.C. F.C.
Page 779 GARMIN G950 IFDS – Increased MTOW (1230 kg) Page SW5 - 19 15. L ANDING PERFORMANCES ° ° ° ° -25/-13 0/32 25/77 50/122 Ground Roll 199 (653) 219 (718) 239 (784) 259 (850) 231 (758) S.L. At 50 ft AGL 308 (1010) 334 (1096) 359 (1178)
Page 780 GARMIN G950 IFDS – Increased MTOW (1230 kg) Page SW5 - 20 ° ° ° ° -25/-13 0/32 25/77 50/122 Ground Roll 175 (574) 192 (630) 210 (689) 227 (745) 203 (666) S.L. At 50 ft AGL 271 (889) 293 (961) 315 (1033) 337 (1105) 306 (1004)
Page 781 GARMIN G950 IFDS – Increased MTOW (1230 kg) Page SW5 - 21 ° ° ° ° -25/-13 0/32 25/77 50/122 Ground Roll 150 (492) 166 (544) 181 (594) 196 (643) 175 (574) S.L. At 50 ft AGL 233 (764) 252 (827) 271 (889) 290 (951) 264 (866)
Page 782: Balked Landing Climb Gradient
GARMIN G950 IFDS – Increased MTOW (1230 kg) Page SW5 - 22 16. B ALKED LANDING CLIMB GRADIENT Flight conditions (ISA and SL): Weight: 1230 kg (2712 lb) Throttle levers Both FULL FORWARD Flaps Landing gear DOWN Weight MTOW 1230kg (2712 lb) Speed 72 KIAS Climb gradient...
Page 783 Page G10 - 11 Supplement G10: page replacement instructions WEIGHT AND BALANCE See Section 6 of the Basic Manual Edition, Rev. 0 Section 9 – Supplements Supplement no. G10 – Increased MTOW (1230 kg)
Page 784 Page G10 - 12 Supplement G10: page replacement instructions AIRFRAME and SYSTEMS DESCRIPTION Apply following instruction: Section 7 – AIRFRAME and SYSTEMS DESCRIPTION pages as per Supplement G1 instructions are still valid Edition, Rev. 0 Section 9 – Supplements Supplement no. G10 – Increased MTOW (1230 kg)
Page 785 Page G11-1 . G11 – V UPPLEMENT NO NCREASE ECORD OF EVISIONS EASA Approval Tecnam Approval Revised Description of Or Under DOA page Revision Privileges Editorial change (*) A. Sabino C. Caruso M. Oliva DOA Approval (*) This supplement was originally issued under EASA approval no. 10041602.
Page 786 Page G11-2 LOEP Page Revision G11-1 Rev 0 G11-2 Rev 0 G11-3 Rev 0 G11-4 Rev 0 G11-5 Rev 0 G11-6 Rev 0 Edition, Rev. 0 Section 9 - Supplements Supplement no. G11 – Vlo/Vle Increase...
Page 787 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 788: Section 2 - Limitations
Page G11-4 SECTION 2 - LIMITATIONS EASA Approved Edition, Rev. 0 Section 9 - Supplements Supplement no. G11 – Vlo/Vle Increase...
Page 789: Speed Limitations
Page G11-5 PEED LIMITATIONS On the left side instrument panel, above on the left, it is placed the following placard reporting the speed limitations: Maximum L.G. op. speed = 122 KIAS EASA Approved Edition, Rev. 0 Section 9 - Supplements Supplement no.
Page 790 Page G11-6 INTENTIONALLY LEFT BLANK Edition, Rev. 0 Section 9 - Supplements Supplement no. G11 – Vlo/Vle Increase...
Page 791 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 Editorial Change A. Sabino C. Caruso M. Oliva See Note (*) Note (*): this Supplement has been originally issued on 2 May 2013, after EASA Third Country Validation pro- cess completion.
Page 792 Page G12-2 LOEP Page Revision Page Revision G11-1 Rev 0 G11-5 Rev 0 Rev 0 Rev 0 G11-2 G11-6 G11-3 Rev 0 G11-7 Rev 0 G11-4 Rev 0 G11-8 Rev 0 Edition, Rev. 0 Section 9 – Supplements Supplement no. G12 – South African AFM...
Page 793 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 794 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 795: Inflight Engine Restart
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 pre- CAUTION scribed in Document SA-CATS 91 and such oxygen may be used continuously...
Page 796 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 797 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 798 Page G12 - 8 INTENTIONALLY LEFT BLANK Edition, Rev. 0 Section 9 – Supplements Supplement no. G12 – South African AFM...
Page 799 Page G13-1 . G13 – A 70 A UPPLEMENT NO LTERNATORS WITH INSTALLATION Record of Revisions EASA Approval Or Tecnam Approval Revised Description of Under DOA page Revision Privileges Editorial change A. Sabino C. Caruso M. Oliva DOA Privileges. Approved under the au- G13-1, 4, 5, thority of DOA, ref.
Page 800 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 801: Section 3 - Emergency Procedures
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 802 Alternators with 70A - Supplement Page G13-4 Section 3 – INGLE ALTERNATOR FAILURE OVERVOLTAGE Emergency Annunciation window Alert window procedures L ALT FAIL INDEX 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 803 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 804 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 805 Page G14-1 . G14 UPPLEMENT NO G950 A ARMIN VIONICS ECORD OF EVISIONS EASA Approval Or Tecnam Approval Revised Description of Under DOA page Revision Privileges D. Ronca C. Caruso M. Oliva DOA Approval First issue Integration of information A. Sabino C.
Page 806 Page G14-2 LOEP Pages Revision Cover pages G14 – 3 thru 22 Rev. 0 G14 – 1, 2 Rev. 4 Section 2 SMP2 – 3 Rev. 0 Section 3 SSMP3 – 3 thru 5 Rev. 0 SSMP3 – 7 thru 9 Rev.
Page 807 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 808 Page G14-4 INTENTIONALLY LEFT BLANK Ed.4, Rev.0 Section 9 - Supplements Supplement no. G14 – SMP FOR DIGITAL CONFIGURATION...
Page 809 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 810 Page G14-6 INTENTIONALLY LEFT BLANK Ed.4, Rev.0 Section 9 - Supplements Supplement no. G14 – SMP FOR DIGITAL CONFIGURATION...
Page 811 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 812 Page G14-8 INTENTIONALLY LEFT BLANK Ed.4, Rev.0 Section 9 - Supplements Supplement no. G14 – SMP FOR DIGITAL CONFIGURATION...
Page 813 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 814 Page G14-9 INTENTIONALLY LEFT BLANK Ed.4, Rev.0 Section 9 - Supplements Supplement no. G14 – SMP FOR DIGITAL CONFIGURATION...
Page 815 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 816 Page G14-11 INTENTIONALLY LEFT BLANK Ed.4, Rev.0 Section 9 - Supplements Supplement no. G14 – SMP FOR DIGITAL CONFIGURATION...
Page 817 GARMIN G950 IFDS – SMP FOR DIGITAL CONFIGURATION Page SSMP3-3 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 818: 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 819 GARMIN G950 IFDS – SMP FOR DIGITAL CONFIGURATION Page SSMP3-5 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 820 GARMIN G950 IFDS – SMP FOR DIGITAL CONFIGURATION Page SSMP3-7 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 821 GARMIN G950 IFDS – SMP FOR DIGITAL CONFIGURATION Page SSMP3-8 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 822 GARMIN G950 IFDS – SMP FOR DIGITAL CONFIGURATION Page SSMP3-9 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 823 GARMIN G950 IFDS – SMP FOR DIGITAL CONFIGURATION Page SSMP3-21 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 824: Other Emergencies
GARMIN G950 IFDS – SMP FOR DIGITAL CONFIGURATION Page SSMP3-29 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 emergency descent in order to assure a safe and smooth recov- CAUTION ery from maneuver.
Page 825 GARMIN G950 IFDS – SMP FOR DIGITAL CONFIGURATION Page SSMP3-36 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 826 GARMIN G950 IFDS – SMP FOR DIGITAL CONFIGURATION Page SSMP3-37 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 827 GARMIN G950 IFDS – SMP FOR DIGITAL CONFIGURATION Page SSMP3-39 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 828: Engine Failure In Flight
GARMIN G950 IFDS – SMP FOR DIGITAL CONFIGURATION Page SSMP3-40 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 829: Smoke And Fire Occurrence
GARMIN G950 IFDS – SMP FOR DIGITAL CONFIGURATION Page SSMP3-49 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 830 GARMIN G950 IFDS – SMP FOR DIGITAL CONFIGURATION Page SSMP3-50 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 831 GARMIN G950 IFDS – SMP FOR DIGITAL CONFIGURATION Page SSMP3-51 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 832 GARMIN G950 IFDS – SMP FOR DIGITAL CONFIGURATION Page SSMP3-52 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 833 GARMIN G950 IFDS – SMP FOR DIGITAL CONFIGURATION Page SSMP3-53 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 834 Page G14-12 INTENTIONALLY LEFT BLANK Ed.4, Rev.0 Section 9 - Supplements Supplement no. G14 – SMP FOR DIGITAL CONFIGURATION...
Page 835 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 REPLACE Page S4 – 26 thru 27 of Supplement G1, Section 4 Ed.4, Rev.0 Section 9 - Supplements Supplement no.
Page 836 Page G14-14 INTENTIONALLY LEFT BLANK Ed.4, Rev.0 Section 9 - Supplements Supplement no. G14 – SMP FOR DIGITAL CONFIGURATION...
Page 837 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 838: Turbulent Air Operation
GARMIN G950 IFDS – SMP FOR DIGITAL CONFIGURATION Page SSMP4-27 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 839 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 840 Page G14-16 INTENTIONALLY LEFT BLANK Ed.4, Rev.0 Section 9 - Supplements Supplement no. G14 – SMP FOR DIGITAL CONFIGURATION...
Page 841 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 842 Page G14-18 INTENTIONALLY LEFT BLANK Ed.4, Rev.0 Section 9 - Supplements Supplement no. G14 – SMP FOR DIGITAL CONFIGURATION...
Page 843 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 844 Page G14-20 INTENTIONALLY LEFT BLANK Ed.4, Rev.0 Section 9 - Supplements Supplement no. G14 – SMP FOR DIGITAL CONFIGURATION...
Page 845: Electrical Systems
GARMIN G950 IFDS – SMP FOR DIGITAL CONFIGURATION Page SSMP7-41 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 846 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 847 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 848 GARMIN G950 IFDS – SMP FOR DIGITAL CONFIGURATION Page SSMP7-46 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 849 GARMIN G950 IFDS – SMP FOR DIGITAL CONFIGURATION Page SSMP7-47 Figure 25 – Electrical system schematic (Page 2) Electrical system schematic (Page 3) Ed.4, Rev.0 Section 7 – Airframe and Systems description...
Page 850 GARMIN G950 IFDS – SMP FOR DIGITAL CONFIGURATION Page SSMP7-48 INTENTIONALLY LEFT BLANK Ed.4, Rev.0 Section 7 – Airframe and Systems description...
Page 851: Ground Handling & Service
Page G14-21 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 852 Page G14-22 INTENTIONALLY LEFT BLANK Ed.4, Rev.0 Section 9 - Supplements Supplement no. G14 – SMP FOR DIGITAL CONFIGURATION...
Page 853 Page G15-1 SUPPLEMENT NO. G15 JAPANESE AFMS Record of Revisions EASA Approval Or Tecnam Approval Revised Description of Under DOA page Revision Privileges First issue D. Ronca C. Caruso M. Oliva See Note (*) Note (*): this Supplement has been originally issued after EASA Third Country Validation process.
Page 854 Page G15-2 LOEP Page Revision Page Revision G15-1 Rev 0 Rev 0 G15-2 G15-3 Rev 0 G15-4 Rev 0 G15-5 Rev 0 Rev 0 G15-6 Rev 0 G15-7 G15-8 Rev 0 Edition, Rev. 0 Section 9 – Supplements Supplement no. G15 – Japan AFMS...
Page 855 Page G15-3 TABLE OF CONTENTS INTRODUCTION ..............................4 LIMITATION ..............................5 1.1. Approved Fuel .............................. 5 Japanese Placards ............................6 Operating Limitations ..........................6 2.1. 2.2. Rear Seats ..............................6 Other Placards ............................. 7 2.3. Edition, Rev. 0 Section 9 – Supplements Supplement no.
Page 856: Introduction
It contains supplemental information to the basic information approved in EASA aircraft Flight Manual when the aircraft is registered in Japan. This supplement is applicable to both P2006T digital and analogue configuration. For Limitations, procedures, and performance information not contained in this supplement, refer to the basic Aircraft Flight Manual.
Page 857: Limitation
Page G15-5 1. LIMITATION 1.1. Approved Fuel - MOGAS ASTM D4814 - MOGAS EN 228 Super/Super plus (min. RON 95) - AVGAS 100 LL (ASTM D910) NOTE: For additional information, refer to Rotax Service Instruction No. 912-016, latest issue. 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 858: Japanese Placards
Page G15-6 2. Japanese Placards Hereinafter the placards, related to the operating limitations and installed on P2006T, are reported. 2.1. Operating Limitations On the instrument panel, it is placed the following placard reminding the observance 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 859: Other Placards
Page G15-7 2.3. Other Placards Description Placard (English and Japanese) Place Instruments Smoking ban. panel, right side Ditching emergency Ditching emergency exit: exit handle: internal opening instructions side Ditching emergency Ditching emergency exit: exit handle: external opening instructions side Main door and Door locking system: emergency exit: by-pass instructions...
Page 860 Page G15-8 Emergency exit: Emergency exit internal and external label side Main door: exit Main door, instructions internal side Edition, Rev. 0 Section 9 – Supplements Supplement no. G15 – Japan AFMS...
Page 861 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 EASA Approval No. First issue D. Ronca C. Caruso M. Oliva 10058288...
Page 862 Page G16-2 LOEP Pages Revision Cover pages G16–1 thru 10 Rev. 1 SMD3 – 15 thru 16 Section 3 Rev. 0 SMD3 – 30 Rev. 0 SMD4 – 6 Section 4 Rev. 1 MD7 – 29 Section 7 Rev. 0 SMD7 –...
Page 863 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 864 Page G16-4 Supplement G16: pages replacement instructions 1 – GENERAL ECTION Apply following instruction: See Basic AFM - Section 1 Ed.4, Rev.1 Section 9 - Supplements Supplement no. G16 – MD302 A LTERNATIVE TAND NSTRUMENT...
Page 865 Page G16-5 Supplement G16: pages replacement instructions 2 – LIMITATIONS ECTION Apply following instructions: See Basic AFM - Section 2 Ed.4, Rev.1 Section 9 - Supplements Supplement no. G16 – MD302 A LTERNATIVE TAND NSTRUMENT...
Page 866 Page G16-6 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 S3–15 thru 16 of Supplement G1, Section 3 REPLACE MD3 –...
Page 867 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 868 GARMIN G950 IFDS – MD302 A LTERNATIVE TAND NSTRUMENT Page SMD3-16 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 869 GARMIN G950 IFDS – MD302 A LTERNATIVE TAND NSTRUMENT Page SMD3-30 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 870 Page G16-7 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 – 6 Page S4–6 Supplement G01, Section 4 REPLACES Ed.4, Rev.1 Section 9 - Supplements Supplement no.
Page 871 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 872 Page G16-8 Supplement G16: pages replacement instructions 5 – PERFORMANCE ECTION Apply following instruction: See Basic AFM - Section 5 Ed.4, Rev.1 Section 9 - Supplements Supplement no. G16 – MD302 A LTERNATIVE TAND NSTRUMENT...
Page 873 Page G16-9 Supplement G16: pages replacement instructions 6 – WEIGHT AND BALANCE ECTION Apply following instruction: See Basic AFM - Section 6 Ed.4, Rev.1 Section 9 - Supplements Supplement no. G16 – MD302 A LTERNATIVE TAND NSTRUMENT...
Page 874 Page G16-10 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 875: Stand -B Y Instrument
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 876 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 877 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 878 Page G16-11 Supplement G16: pages replacement instructions 8 – GROUND HANDLING & SERVICE ECTION Apply following instruction: See Basic AFM - Section 8 Ed.4, Rev.1 Section 9 - Supplements Supplement no. G16 – MD302 A LTERNATIVE TAND NSTRUMENT...
Page 879 Page G16-12 INTENTIONALLY LEFT BLANK Ed.4, Rev.1 Section 9 - Supplements Supplement no. G16 – MD302 A LTERNATIVE TAND NSTRUMENT...
Page 880 Page G17-1 . G17 - S UPPLEMENT NO TORMSCOPE ECORD OF EVISIONS EASA Approval Or Tecnam Approval Revised Description of Under DOA page Revision Privileges First issue D. Ronca C. Caruso M. Oliva DOA Approval Page replacement and A.Sabino C. Caruso M.Oliva...
Page 881 Page G17-2 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 on G950 or  MOD 2006/367- Stormscope installation on G1000 Nxi Phase I or ...
Page 882 Page G17-3 1 – GENERAL ECTION The following information supplements Section 1 of basic AFM and related supplements. The Stormscope does neither replace a weather ra- NOTE dar nor weather information. The Stormscope is only used as an additional source of information beside approved weather information.
Page 883 Page G17-4 7 – AIRFRAME AND SYSTEMS DESCRIPTION ECTION The following information supplements Section 7 of basic AFM and related supplements. WX500 S TORMSCOPE SYSTEM The thunderstorm detection passive sensor WX500 Stormscope is fully operated and dis- played via the Garmin G950 Multifunction display or Garmin G1000 Nxi, in the map menu. Is is installed in order to shown the lightning data.
Page 884 Page G17-5 8 – GROUND HANDLING & SERVICE ECTION See Section 8 of basic AFM and related supplements. Ed.4, Rev.1 Section 9 – Supplements Supplement no. G17 - STORMSCOPE...
Page 885 Page G17-6 INTENTIONALLY LEFT BLANK Ed.4, Rev.1 Section 9 – Supplements Supplement no. G17 - STORMSCOPE...
Page 886 Page G19-1 SUPPLEMENT No. G19 G1000 NXi, Increased MTOW, Increased V and MD302 Edition, Rev. 7 Section 9 - Supplements AFMS G19 – G1000 NXI, Increased MTOW, Increased V and MD302...
Page 887 Page G19-2 ECORD OF EVISIONS EASA Approval or Under Tecnam Approval Revised Description of DOA Privileges page Revision EASA Approval N° Initial issue A. Sabino C. Caruso M. Oliva 10062361 Suppressed, information re- S2-6,8,12,16 ported in basic AFM A. Sabino C.
Page 888 Page G19-3 EASA Approval or Under Tecnam Approval Revised Description of DOA Privileges page Revision G19-1,2,3,4 RoR and LoEP updated S2-13 Typo errors S3-12 G19-5 Approved under the authority of DOA, ref. S2-14 L. De Salvi D. Ronca M. Oliva Garmin Pilot’s guide Part No.
Page 889 Page G19-4 LOEP Pages Revision G19- 7, 17 Rev 5 Cover pages 6, 8 thru 16, 18 thru 22 Rev 0 G19-1,2,5 Rev 7 G19-3, 4 Rev 11 15 thru 16,21,22,29 Section S2 Rev 0 Rev 3 13, 14 Rev. 7 5, 7, 12 Rev.
Page 890 It is the owner’s responsibility to replace the mentioned pages in the AFM in accordance with the instructions herein addressed section by section. Garmin Pilot’s Guide for Tecnam P2006T (P/N 190-02286- XX or 190-02668-XX, as applicable) – last issue – must be carried on board the air- plane at all times.
Page 891 Page G19-6 INTENTIONALLY LEFT BLANK Edition, Rev. 0 Section 9 - Supplements AFMS G19 – G1000 NXI, Increased MTOW, Increased V and MD302...
Page 892: Section 1 - General
Page G19-7 Supplement G19: pages replacement instructions SECTION 1 - GENERAL See Basic AFM - Section 1 Edition, Rev. 0 Section 9 - Supplements AFMS G19 – G1000 NXI, Increased MTOW, Increased V and MD302...
Page 893 Page G19-8 INTENTIONALLY LEFT BLANK Edition, Rev. 0 Section 9 - Supplements AFMS G19 – G1000 NXI, Increased MTOW, Increased V and MD302...
Page 894 Page G19-9 Supplement G19: pages replacement instructions SECTION 2 - LIMITATIONS Apply following pages replacement procedure: Supplement G19 – LIMITATIONS Basic AFM page Section 2 page S2-5 REPLACES S2-7 REPLACES S2-12 2-12 REPLACES S2-13 REPLACES 2-13 S2-14 2-14 REPLACES S2-15 2-15 REPLACES S2-21...
Page 895 Page G19-10 INTENTIONALLY LEFT BLANK Edition, Rev. 0 Section 9 - Supplements AFMS G19 – G1000 NXI, Increased MTOW, Increased V and MD302...
Page 896: Speed Limitations
G1000 NXi, Increased MTOW, Increased V and MD302 Page S2 - 5 2. S PEED LIMITATIONS The following table addresses the airspeed limitations and their operational signifi- cance: SPEED KIAS KCAS REMARKS V NE Never exceed speed Do not exceed this speed in any operation.
Page 897 G1000 NXi, Increased MTOW, Increased V and MD302 Page S2 - 7 3. A IRSPEED INDICATOR MARKINGS The Airspeed Indicator displays airspeed on a rolling number gauge using a moving tape. The airspeed is displayed inside the black pointer. The pointer remains black until reaching never-exceed speed (V ), at which point it turns red.
Page 898 G1000 NXi, Increased MTOW, Increased V and MD302 Page S2 - 12 OWERPLANT INSTRUMENTS MARKINGS Powerplant instrument markings and their colour code significance are shown below: HITE GREEN LINE YELLOW ARC LINE LINE LINE Normal Caution NSTRUMENT Minimum Advisory Maximum operating limit limit...
Page 899 G1000 NXi, Increased MTOW, Increased V and MD302 Page S2 - 13 13. W ARNINGS CAUTIONS AND ADVISORIES LIGHTS Following table addresses the warning and caution alerts and safe operating annunciations shown (unless differently specified) on the Annunciation Window: Warning alert (RED) Cause L BUS VOLT HIGH LH electric system overvoltage...
Page 900 Safe operat- ing annunciations do not have any aural chime generated. Make reference to Garmin Pilot’s Guide for P2006T (P/N 190-02286- 00 or 190- 02668-XX), last issue.
Page 901 G1000 NXi, Increased MTOW, Increased V and MD302 Page S2 - 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 Refer to Para. 21.4 of this AFM Section for baggage loading limitations. NOTE EASA Approved Edition, Rev.
Page 902: Limitations Placards
MD302 Page S2 - 21 21. L IMITATIONS PLACARDS Hereinafter the placards, related to the operating limitations and installed on P2006T, are reported. 21.1. PEED LIMITATIONS On the left side instrument panel, the following placards reporting the speed limita-...
Page 903 G1000 NXi, Increased MTOW, Increased V and MD302 Page S2 - 22 21.2. O PERATING LIMITATIONS On the instrument panel, it is placed the following placard reminding the observance 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 904 G1000 NXi, Increased MTOW, Increased V and MD302 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 905 G1000 NXi, Increased MTOW, Increased V and MD302 Page S2 - 30 Equipment VFR Day VFR Night IFR Day IFR Night ● ● ● ● Magnetic compass ● ● ● ● GDU 1050 - Display Unit (2) ● ● ● ●...
Page 906: Section 3 - Emergency Procedures
Page G19-11 Supplement G19: pages replacement instructions SECTION 3 - EMERGENCY PROCEDURES Supplement G19 Section 3 – EMERGENCY PROCEDURES replaces Basic AFM Section 3 as a whole Edition, Rev. 0 Section 9 - Supplements AFMS G19 – G1000 NXI, Increased MTOW, Increased V and MD302...
Page 907 Page G19-12 INTENTIONALLY LEFT IN BLANK Edition, Rev. 0 Section 9 - Supplements AFMS G19 – G1000 NXI, Increased MTOW, Increased V and MD302...
Page 908 G1000 NXi, Increased MTOW, Increased V and MD302 Page S3 - 1 SECTION 3 – EMERGENCY PROCEDURES INDEX INTRODUCTION ..................... 3 1.1. Engine failure during takeoff run ..............3 AIRPLANE ALERTS ..................6 Single alternator failure / overvoltage ............7 Both alternators failure .................
Page 909 G1000 NXi, Increased MTOW, Increased V and MD302 Page S3 - 2 One engine inoperative landing ..............41 LANDING GEAR SYSTEM FAILURES ............42 Emergency landing gear extension ............42 Complete Gear up or nose gear up landing ..........43 Partial Main LG extension ................
Page 910: Engine Failure During Takeoff Run
AFM current sec- tion appropriate checklist. Additionally operating the aircraft, the pilot should become thoroughly familiar with the Garmin Pilot’s Guide for Tecnam P2006T(P/N 190-02286- XX or 190-02668-XX, as applicable) – last issue - and, in particular, with the present AFM Section.
Page 911 G1000 NXi, Increased MTOW, Increased V and MD302 Page S3 - 4 Garmin G1000 NXI has a very high degree of functional integrity. How- ever, the pilot must recognize that providing monitoring and/or self-test capability for all conceivable system failures is not practical. Although unlikely, it may be possible for erroneous operation to occur without a WARNING fault indication shown by the G1000 NXI.
Page 912 G1000 NXi, Increased MTOW, Increased V and MD302 Page S3 - 5 INTENTIONALLY LEFT BLANK Edition, Rev. 0 Section 3 – Emergency procedures INTRODUCTION...
Page 913 G1000 NXi, Increased MTOW, Increased V and MD302 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.
Page 914 G1000 NXi, Increased MTOW, Increased V and MD302 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 915 G1000 NXi, Increased MTOW, Increased V and MD302 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.
Page 916 G1000 NXi, Increased MTOW, Increased V and MD302 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 917 G1000 NXi, Increased MTOW, Increased V and MD302 Page S3 - 10 AILED DOOR CLOSURE Annunciation window Alert window MAIN DR OPEN Main door open REAR DR OPEN Rear door open In case of door opening / unlocking, related MAIN or REAR DR OPEN alert is displayed. In this case, apply following procedure: ON THE GROUND 1.
Page 918 G1000 NXi, Increased MTOW, Increased V and MD302 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.
Page 919 G1000 NXi, Increased MTOW, Increased V and MD302 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 920 G1000 NXi, Increased MTOW, Increased V and MD302 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 921: Fire In Flight
G1000 NXi, Increased MTOW, Increased V and MD302 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 922 NOTE in the Alerts Window. Refer to Garmin Pilot’s Guide for Tec- nam P2006T (P/N 190-02286-XX or 190-02668-XX, as applicable), last issue, Appendix A, Mes- sage Advisories list. 2.10 L...
Page 923 G1000 NXi, Increased MTOW, Increased V and MD302 Page S3 - 16 2.11 L OSS OF ATTITUDE INFORMATION ATTITUDE FAIL ON DISPLAY FIELD Display system is not receiving attitude information from the AHRS. INSTRUCTION: revert to standby attitude indicator 2.12 L OSS OF ALTITUDE INFORMATION ALTITUDE FAIL ON DISPLAY FIELD...
Page 924 G1000 NXi, Increased MTOW, Increased V and MD302 Page S3 - 17 2.13 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 2.14 OSS OF HEADING INFORMATION ON DISPLAY FIELD...
Page 925 G1000 NXi, Increased MTOW, Increased V and MD302 Page S3 - 18 INTENTIONALLY LEFT BLANK Edition, Rev. 0 Section 3 – Emergency procedures G1000 NXI SYSTEM FAILURES...
Page 926 G1000 NXi, Increased MTOW, Increased V and MD302 Page S3 - 19 2.15 ISPLAY FAILURE In the event of a display failure, the G1000 NXi System automatically switches to reversionary (backup) mode. In reversionary mode, all important flight infor- mation is presented on the remaining display in the same format as in normal op- erating mode.
Page 927 G1000 NXi, Increased MTOW, Increased V and MD302 Page S3 - 20 INTENTIONALLY LEFT BLANK Edition, Rev. 0 Section 3 – Emergency procedures G1000 NXI SYSTEM FAILURES...
Page 928 G1000 NXi, Increased MTOW, Increased V and MD302 Page S3 - 21 3. ENGINE SECURING Following procedure is applicable to shut-down one engine in flight: Throttle Lever IDLE Ignition BOTH 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 929 G1000 NXi, Increased MTOW, Increased V and MD302 Page S3 - 22 INTENTIONALLY LEFT BLANK Edition, Rev. 0 Section 3 – Emergency procedures...
Page 930 G1000 NXi, Increased MTOW, Increased V and MD302 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...
Page 931 G1000 NXi, Increased MTOW, Increased V and MD302 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 (275°F) or CT is above 120°C (248°F) 2. Affected engine Reduce power setting to reduce CHT/CT up to the minimum practical 3.
Page 932: Oil Press
G1000 NXi, Increased MTOW, Increased V and MD302 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.
Page 933 G1000 NXi, Increased MTOW, Increased V and MD302 Page S3 - 26 IL PRESSURE LIMITS EXCEEDANCE If oil pressure exceeds its lower or upper limit (0.8 – 7 bar/11.5 – 101.5 psi), apply following procedure: Excessive oil pressure drop leads to a high pitch propeller con- figuration with consequent propeller feathering and engine stop- WARNING ping.
Page 934 G1000 NXi, Increased MTOW, Increased V and MD302 Page S3 - 27 OW FUEL PRESSURE Low fuel pressure indications are possible and allowed but the pressure must stabilize to the operating limit within 10 seconds. If not, and pressure decreases below the lower limit (2.2 psi), apply following procedure: 1.
Page 935 G1000 NXi, Increased MTOW, Increased V and MD302 Page S3 - 28 INTENTIONALLY LEFT BLANK Edition, Rev. 0 Section 3 – Emergency procedures...
Page 936: Other Emergencies
G1000 NXi, Increased MTOW, Increased V and MD302 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 emergency descent in order to assure a safe and smooth recov- CAUTION...
Page 937 G1000 NXi, Increased MTOW, Increased V and MD302 Page S3 - 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.
Page 938 G1000 NXi, Increased MTOW, Increased V and MD302 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, precipitation and with higher temperature, changing altitude and/or direction. Control surfaces Move continuously to avoid locking Propellers rpm...
Page 939: During Takeoff
G1000 NXi, Increased MTOW, Increased V and MD302 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 940 G1000 NXi, Increased MTOW, Increased V and MD302 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...
Page 941: One Engine Inoperative Procedures
G1000 NXi, Increased MTOW, Increased V and MD302 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 com- pensating the lower traction and counteracting the yawing effects by mean of rudder pedals.
Page 942 G1000 NXi, Increased MTOW, Increased V and MD302 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 943: Inflight Engine Restart
G1000 NXi, Increased MTOW, Increased V and MD302 Page S3 - 36 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)
Page 944 G1000 NXi, Increased MTOW, Increased V and MD302 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:...
Page 945 G1000 NXi, Increased MTOW, Increased V and MD302 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...
Page 946 G1000 NXi, Increased MTOW, Increased V and MD302 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...
Page 947: Engine Failure In Flight
G1000 NXi, Increased MTOW, Increased V and MD302 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 948 G1000 NXi, Increased MTOW, Increased V and MD302 Page S3 - 41 NE ENGINE INOPERATIVE LANDING Thoroughly evaluate residual Single Engine Go-Around capabilities and expected climb gradient should a Missed Approach / balked landing be executed. Refer to Section 5, Para. Single engine go around/Balked landing/climb WARNING and Para.
Page 949: Landing Gear System Failures
G1000 NXi, Increased MTOW, Increased V and MD302 Page S3 - 42 LANDING GEAR SYSTEM FAILURES MERGENCY LANDING GEAR EXTENSION Landing gear extension failure is identified by means a warning message “LANDING GEAR” illuminated: relevant gear leg may not be fully extended and/or locked. Additionally, the light inside the switch and the warning “LANDING GEAR”...
Page 950 G1000 NXi, Increased MTOW, Increased V and MD302 Page S3 - 43 OMPLETE EAR UP OR NOSE GEAR UP LANDING The following procedure applies if Nose Landing Gear is not ex- tended 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 951 G1000 NXi, Increased MTOW, Increased V and MD302 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.
Page 952 G1000 NXi, Increased MTOW, Increased V and MD302 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 extension 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 953 G1000 NXi, Increased MTOW, Increased V and MD302 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 954 G1000 NXi, Increased MTOW, Increased V and MD302 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.
Page 955 G1000 NXi, Increased MTOW, Increased V and MD302 Page S3 - 48 INTENTIONALLY LEFT BLANK Edition, Rev. 0 Section 3 – Emergency procedures...
Page 956: Smoke And Fire Occurrence
G1000 NXi, Increased MTOW, Increased V and MD302 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...
Page 957 G1000 NXi, Increased MTOW, Increased V and MD302 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...
Page 958 G1000 NXi, Increased MTOW, Increased V and MD302 Page S3 - 51 At safe altitude Cabin heat and defrost BOTH OFF Confirm and OFF Fire affected engine Fuel Selector 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 959 G1000 NXi, Increased MTOW, Increased V and MD302 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 960 G1000 NXi, Increased MTOW, Increased V and MD302 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 961 G1000 NXi, Increased MTOW, Increased V and MD302 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 962: Unintentional Spin Recovery
G1000 NXi, Increased MTOW, Increased V and MD302 Page S3 - 55 9 UNINTENTIONAL SPIN RECOVERY Spin behaviour has not been demonstrated since certifica- tion process does not required it for this aircraft category. Intentional spin is forbidden. Stall with one engine inoperative is forbidden. Should an unintentional spin occur, the classic recovery WARNING manoeuvre is deemed as being the best action to under-...
Page 963: Landing Emergencies
G1000 NXi, Increased MTOW, Increased V and MD302 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 al- titude.
Page 964 G1000 NXi, Increased MTOW, Increased V and MD302 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 965 G1000 NXi, Increased MTOW, Increased V and MD302 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.
Page 966 G1000 NXi, Increased MTOW, Increased V and MD302 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.
Page 967 G1000 NXi, Increased MTOW, Increased V and MD302 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 CAUTION the increasing hazard of an uneven pavement.
Page 968 G1000 NXi, Increased MTOW, Increased V and MD302 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 969 G1000 NXi, Increased MTOW, Increased V and MD302 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 970: Section 4 - Normal Procedures
Page G19-13 Supplement G19: pages replacement instructions SECTION 4 - NORMAL PROCEDURES Supplement G19 Section 4 – NORMAL PROCEDURES replaces Basic AFM Section 4 as a whole Edition, Rev. 0 Section 9 - Supplements AFMS G19 – G1000 NXI, Increased MTOW, Increased V and MD302...
Page 971 Page G19-14 INTENTIONALLY LEFT BLANK Edition, Rev. 0 Section 9 - Supplements AFMS G19 – G1000 NXI, Increased MTOW, Increased V and MD302...
Page 972 G1000 NXi, Increased MTOW, Increased V and MD302 Page S4 - 1 SECTION 4 – NORMAL PROCEDURES INDEX INTRODUCTION .................. 3 1.1. Normal ops general recommendations ..........3 AIRSPEEDS ..................7 2.2. Normal operations ................7 2.3. Single engine training ................. 8 NORMAL PROCEDURES CHECKLIST ..........
Page 973 G1000 NXi, Increased MTOW, Increased V and MD302 Page S4 - 2 INTENTIONALLY LEFT BLANK Edition, Rev. 0 Section 4 – Normal procedures...
Page 974 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. As prescribed by the propeller/governor manufacturer, a drop of 400/500 propeller RPM should be produced during this check.
Page 975 RPM. Refer to SL-912-016R2 for additional information. 3. Suitable Fuels. Tecnam remember operators to fill the aircraft with approved and suitable fuels. Use of not approved/unknown fuels may cause damages to the engine. ONLY USE APPROVED FUELS...
Page 976 For safety reasons, G1000 NXi operational procedures must be learned on the ground. Document Garmin Pilot’s Guide for Tecnam P2006T (P/N 190- 02286-XX or 190-02668-XX, as applicable) – last issue, reports detailed instructions to operate the system in sub- ject. Make always reference to the above mentioned document.
Page 977 Reference“Garmin Pilot’s Guide for the Tec- nam P2006T” (P/N 190-02286-XX or 190-02668-XX, as applicable), last issue, Appendix B concern- ing SD card use and databases. Use of polarized eyewear may cause the flight displays to appear NOTE dim or blank.
Page 978: Normal Operations
G1000 NXi, Increased MTOW, Increased V and MD302 Page S4 - 7 AIRSPEEDS 2.1. 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 979 G1000 NXi, Increased MTOW, Increased V and MD302 Page S4 - 8 2.2. 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 min- imum speed provides the margin the manufacturer recommends for us when intentionally performing engine inoperative maneuvers during training.
Page 980: Normal Procedures Checklist
G1000 NXi, Increased MTOW, Increased V and MD302 Page S4 - 9 NORMAL 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 981 G1000 NXi, Increased MTOW, Increased V and MD302 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 982 G1000 NXi, Increased MTOW, Increased V and MD302 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 983 G1000 NXi, Increased MTOW, Increased V and MD302 Page S4 - 12 Pilot door and cabin Check door for integrity. Turn ON the Master Switch and check Stall Warning switch for operation and con- dition; 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), slippage markers integrity,...
Page 984 G1000 NXi, Increased MTOW, Increased V and MD302 Page S4 - 13 e) Check oil level and replenish as required. Prior to oil check, switch off both ignitions circuits and turn the propeller by hand in direction of engine rotation several times to pump oil from the engine into the oil tank.
Page 985 G1000 NXi, Increased MTOW, Increased V and MD302 Page S4 - 14 Check emergency landing gear extension system pres- Gear pump, external power and bat- tery compartment sure (low pressure limit: 20 bar), external power and battery compartments closure. Check the actuating mechanism of control surfaces and Horizontal and vertical empennage the connection with related tabs.
Page 986 G1000 NXi, Increased MTOW, Increased V and MD302 Page S4 - 15 Right main landing gear Apply check procedure reported in the walk-around Station 2 Wheel chock Remove if employed Bottom fuselage antennas Check for integrity Right cabin ram-air inlet Visual inspection Right Pitot tube Remove protective cap and check for any obstruction...
Page 987 G1000 NXi, Increased MTOW, Increased V and MD302 Page S4 - 16 INTENTIONALLY LEFT BLANK Section 4 – Normal procedures Edition, Rev. 0 CHECKLIST...
Page 988 G1000 NXi, Increased MTOW, Increased V and MD302 Page S4 - 17 3.3 C OCKPIT INSPECTIONS Instruct passengers on how to use safety belts and normal / emergency exits. 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 989 G1000 NXi, Increased MTOW, Increased V and MD302 Page S4 - 18 Alternate static port CHECK closed Cabin heat CLOSED Flaps Operate control to LND position. Verify extension. Retract flaps. Pitch trim control Set to neutral position. Rudder trim control Set to neutral position.
Page 990 G1000 NXi, Increased MTOW, Increased V and MD302 Page S4 - 19 Ensure that the area around engine propeller disc is clear from people and obstacles. Call out for propeller free. WARNING RH start pushbutton PUSH RH engine oil gauge CHECK if increasing within 10 sec.
Page 991 G1000 NXi, Increased MTOW, Increased V and MD302 Page S4 - 20 LH Choke LH Field LH Avionics LH Cross bus LH Ammeter CHECK Amps positive LH Voltmeter CHECK 12 to 14 Volt LH Electrical fuel pump Cabin Fan AS REQUIRED 3.5 B EFORE TAXIING Let the engines warm up to a minimum oil temperature of 50°C (122°F) at 1200 RPM...
Page 992 G1000 NXi, Increased MTOW, Increased V and MD302 Page S4 - 21 3.7 P RIOR TO TAKEOFF Parking Brake ENGAGE RIGHT RH Fuel Selector LH Fuel Selector LEFT CHECK LH and RH fuel pressure LH and RH Engine parameters checks: •...
Page 993 G1000 NXi, Increased MTOW, Increased V and MD302 Page S4 - 22 LH Ignitions switches Set L / R / BOTH (RPM drop with single Ignition circuit selected must not exceed 210 prop’s RPM; maximum RPM difference by use of either circuits LEFT or RIGHT cannot overcome 65 RPM) LH Propeller Lever GOVERNOR CHECK...
Page 994 G1000 NXi, Increased MTOW, Increased V and MD302 Page S4 - 23 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 995: Turbulent Air Operation
G1000 NXi, Increased MTOW, Increased V and MD302 Page S4 - 24 3.10 RUISE LH and RH Propeller Lever SET to 1900-2250 RPM Throttles MAP decrease should be made before propeller speed reduction be- low 2200 RPM, as, contrariwise, Propeller Lever increase RPM should be set before engine Throttle Levers are advanced.
Page 996: Before Landing
G1000 NXi, Increased MTOW, Increased V and MD302 Page S4 - 25 3.12 ESCENT AND APPROACH Propellers As required In order to control engine cooling and life, it is preferable to descend with NOTE power above idle and RPM lower than full continuous. Carburettors heat As required Altimeter setting...
Page 997 G1000 NXi, Increased MTOW, Increased V and MD302 Page S4 - 26 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 998 G1000 NXi, Increased MTOW, Increased V and MD302 Page S4 - 27 3.16 ARKING SHUT DOWN It is always suggested to park the aircraft with the nose pointing into wind NOTE to improve cooling after shut down. Engage Parking brake Taxi light Engines Allow for cooling down 1 minute at idle power...
Page 999 G1000 NXi, Increased MTOW, Increased V and MD302 Page S4 - 28 3.17 OSTFLIGHT CHECKS Install Protective cover for Pitot tubes, stall warning and static port plugs. Lock one control wheel with safety belt. Wheel chocks Place under MLG Aileron lock Place and tighten Pilot and passengers doors.
Page 1000 G1000 NXi, Increased MTOW, Increased V and MD302 Page S4 - 29 ADDITIONAL GUIDANCE FOR RNAV Experience of RNAV systems, and Flight FMS in general, has identified the pitfalls of way- point entry error at the receiver as well as inaccuracies and errors in the database itself. Research and experience have both shown that human error, often the result of a lack of familiarity with the airborne equipment, represents the major hazard in operations using RNAV systems.