Page 1 AFMS N°D01 FOR GARMIN GFC700 AUTOPILOT INSTALLATION AND RNAV/RNP NAVIGATION ELIGIBILITY Page 1A-20 Autopilot control panel The GDU1044 includes a set of additional softkeys dedicated to the control of Autopilot system. The following dedicated AFCS keys are located on the bezel of the MFD (refer picture below): 1) AP Key: Engages/ disengages the autopilot 2) FD Key: Activates/deactivates the flight director only...
Page 2 AFMS N°D01 FOR GARMIN GFC700 AUTOPILOT INSTALLATION AND RNAV/RNP NAVIGATION ELIGIBILITY Page 1A-21 12.2 P ILOT CONTROL WHEEL AND THROTTLE BUTTONS On the left side of pilot‘s and copilot‘s control wheels there are two PTT switches (the one on pilot control wheel is shown below as (1)) that, when pushed, allow radio transmission.
Page 3 AFMS N°D01 FOR GARMIN GFC700 AUTOPILOT INSTALLATION AND RNAV/RNP NAVIGATION ELIGIBILITY Page 1A-22 The above mentioned AFCS controls are depicted in the below figures. where: 1) PTT switch 2) AP DISC Switch 3) AP Trim Switch 4) CWS Button Ed. 1, Rev. 0 Section 1 –...
Page 4 AFMS N°D01 FOR GARMIN GFC700 AUTOPILOT INSTALLATION AND Page 1A-23 RNAV/RNP NAVIGATION ELIGIBILITY Ed. 1, Rev. 0 Section 1 – General AUTOPILOT DESCRIPTION...
Page 5 AFMS N°D01 FOR GARMIN GFC700 AUTOPILOT INSTALLATION AND Page 1A-24 RNAV/RNP NAVIGATION ELIGIBILITY AUTOPILOT FUNCTIONS AND FEATURES GFC 700 autopilot suite is deeply integrated with Garmin G1000 avionics suite which integrates both the a/p controls and the sensors providing the required data to the servos.
Page 6 AFMS N°D01 FOR GARMIN GFC700 AUTOPILOT INSTALLATION AND Page 1A-25 RNAV/RNP NAVIGATION ELIGIBILITY 13.1 ESP Garmin GFC 700 is equipped with an envelope protection feature referred as ESP (Electronic Stability & Protection). Electronic Stability and Protection continu- ously monitors the aircraft. The system works by applying a correcting force to the controls in order to nudge pilot to avoid extreme attitudes that may bring the aircraft, if not corrected, to exceed normal flying envelope.
Page 7 GPS. 13.1.1 P ITCH MODE Pitch attitude boundaries are set based on P2010 aircraft performances. Since pitch ESP augments the natural aircraft longitudinal stability, no special simbolo- gy is required.
Page 8 AFMS N°D01 FOR GARMIN GFC700 AUTOPILOT INSTALLATION AND Page 1A-27 RNAV/RNP NAVIGATION ELIGIBILITY When the aircraft reaches the engagement limit, ESP ramps up the servo torque command to adjust the aircraft back toward zero pitch attitude. ESP uses a rate command to drive the attitude back to the nominal range and does not try to con- trol to a specific attitude.
Page 9 AFMS N°D01 FOR GARMIN GFC700 AUTOPILOT INSTALLATION AND Page 1A-28 RNAV/RNP NAVIGATION ELIGIBILITY angle is increased, a region of an increasing force as a function of bank angle is entered. The envelope protection system adds bank stability in this region. As the bank angle is increased further, a constant force is applied to right the airplane.
Page 10 AFMS N°D01 FOR GARMIN GFC700 AUTOPILOT INSTALLATION AND Page 1A-29 RNAV/RNP NAVIGATION ELIGIBILITY How Underspeed Protection functions depends on which vertical flight director mode is selected. For the purpose of this discussion, the vertical flight director modes can be divid- ed into two categories: It is important to maintain altitude for as long as possible (altitude- critical modes).
Page 11 AFMS N°D01 FOR GARMIN GFC700 AUTOPILOT INSTALLATION AND Page 1A-30 RNAV/RNP NAVIGATION ELIGIBILITY 13.2.1 A (ALT, GS, GP, TO, LTITUDE CRITICAL MODES GA, FLC) When the airspeed trend vector (dedicated algorithm) reaches 65 +/- 2 KIAS a single aural ― AIRSPEED‖ will sound, alerting the pilot to the impending under- speed condition, which requires pilot action.
Page 12 If the aircraft is allowed to decelerate to an IAS below the minimum commanda- ble autopilot airspeed (65 Kts for P2010), a red ― UNDERSPEED PROTECT AC- TIVE‖ annunciation appear to the right of the vertical speed indicator.
Page 13 Page D01-7 INTENTIONALLY LEFT BLANK Ed. 1, Rev.0 Section 9 – Supplements Supplement no. D01 – GARMIN GFC700 AUTOPILOT INSTALLATION AND RNAV/RNP NAVIGATION ELIGIBILITY...
Page 14 Page D01-8 Supplement D01: pages replacement instructions 2 – LIMITATIONS ECTION Make sure you first applied instructions reported on the basic AFM, Section 2 Limitations According to A/C configuration apply following pages replacement: Supplement D01 LIMITATIONS Section 2 page page 2A-15 2-15 of basic AFM, Section 2 REPLACES...
Page 15 Page D01-9 INTENTIONALLY LEFT BLANK Ed. 1, Rev.0 Section 9 – Supplements Supplement no. D01 – GARMIN GFC700 AUTOPILOT INSTALLATION AND RNAV/RNP NAVIGATION ELIGIBILITY...
Page 16 AFMS N°D01 FOR GARMIN GFC700 AUTOPILOT INSTALLATION AND RNAV/RNP NAVIGATION ELIGIBILITY Page 2A-15 19 LIMITATIONS PLACARDS Hereinafter limitation placards, related to the operating limitations, are placed in plain view on the pilot. 19.1 S PEED LIMITATIONS On the left side instrument panel, above on the left, it is placed the following placard reporting the speed limitations: 19.2 O PERATING LIMITATIONS...
Page 17 RNAV/RNP NAVIGATION ELIGIBILITY Page 2A-17 AUTOPILOT LIMITATIONS The “Garmin G1000 Pilot’s Guide for the Tecnam P2010” (Part No. NOTE 190-01830-00 Revision A dated September 25, 2014 or a more up- dated version) must be carried in the aircraft and made available to the pilot at all time.
Page 18 AFMS N°D01 FOR GARMIN GFC700 AUTOPILOT INSTALLATION AND Page 2A-18 RNAV/RNP NAVIGATION ELIGIBILITY PBN (RNAV & RNP) OPERATIONAL ELIGIBILITY 21.1 G GNSS N ENERAL AVIGATION EQUIPMENT APPROVALS The GPS/GNSS receivers in the G1000 System are certified to TSO C129a Class A1 and ETSO C129a Class A1 or TSO C145a and ETSO 2C145a.
Page 19 AFMS N°D01 FOR GARMIN GFC700 AUTOPILOT INSTALLATION AND Page 2A-19 RNAV/RNP NAVIGATION ELIGIBILITY 21.2 G1000 GNSS (GPS/SBAS) N AVIGATION SYSTEM LIMITA- TIONS The pilot must confirm at system initialization that the Navigation database is cur- rent. Navigation database is expected to be current for the duration of the flight. If the AIRAC cycle will change during flight, the pilot must ensure the accuracy of navigation data, including suitability of navigation facilities used to define the routes and procedures for flight.
Page 20 AFMS N°D01 FOR GARMIN GFC700 AUTOPILOT INSTALLATION AND Page 2A-20 RNAV/RNP NAVIGATION ELIGIBILITY the flight plan from he database in their entirety, rather than loading route way- points from the database into the flight plan individually. Selecting and inserting individual named fixes from the database is permitted, provided all fixes along the published route to be flown are inserted.
Page 21 Page D01-10 INTENTIONALLY LEFT BLANK Ed 1, Rev. 0 Section 9 – Supplements Supplement no. D01 – GARMIN GFC700 AUTOPILOT INSTALLATION AND RNAV/RNP NAVIGATION ELIGIBILITY...
Page 22 Page D01-11 Supplement D01: pages replacement instructions 3 – EMERGENCY PROCEDURES ECTION Make sure you first applied instructions reported on the basic AFM, Section 3 Emergency Procedures According to A/C configuration apply following pages replacement: Supplement D01 EMERGENCY PROCEDURES Section 3 page page 3A-31 thru 35...
Page 23 Page D01-12 INTENTIONALLY LEFT BLANK Ed 1, Rev. 0 Section 9 – Supplements Supplement no. D01 – GARMIN GFC700 AUTOPILOT INSTALLATION AND RNAV/RNP NAVIGATION ELIGIBILITY...
Page 24 AFMS N°D01 FOR GARMIN GFC700 AUTOPILOT INSTALLATION AND RNAV/RNP NAVIGATION ELIGIBILITY Page 3A-31 AUTOPILOT EMERGENCY PROCEDURES In the 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.
Page 25 Trim Wheel. Make reference to “Garmin G1000 Integrated Avionic System Pilot’s Guide”for Tecnam P2010 (Part No. 190-01830-00 Revision A dated September 25, 2014 or a more updat- ed version).
Page 26 AFMS N°D01 FOR GARMIN GFC700 AUTOPILOT INSTALLATION AND RNAV/RNP NAVIGATION ELIGIBILITY Page 3A-33 12.4 A MPLIFIED EMERGENCY PROCEDURES The following observations provide additional information for more complete un- derstanding of the recommended course(s) of action in emergency situations. 1. An autopilot or autotrim malfunction occurs when there is an un- commanded deviation in the airplane flight path or when there is abnormal control wheel or trim wheel motion.
Page 27 AFMS N°D01 FOR GARMIN GFC700 AUTOPILOT INSTALLATION AND RNAV/RNP NAVIGATION ELIGIBILITY Page 3A-34 12.5 A BNORMAL PROCEDURES This table is a quick access table that provide additional information regarding re- sidual A/P capabilities in case loss of autopilot servos and/or pitch trim servo. With A/P engaged, in case of loss of both A/P servos and pitch trim NOTE servo, the disconnect tone will play continuously, until acknowledged...
Page 28 AFMS N°D01 FOR GARMIN GFC700 AUTOPILOT INSTALLATION AND RNAV/RNP NAVIGATION ELIGIBILITY Page 3A-35 This table is a quick access table that provide additional information regarding re- sidual A/P capabilities in case of loss of PFD or MFD. NOTES A/P reverts to PIT & ROLL (from any mode selected) ON →...
Page 29 Page D01-13 INTENTIONALLY LEFT BLANK Ed. 1, Rev. 0 Section 9 – Supplements Supplement no. D01 – GARMIN GFC700 AUTOPILOT INSTALLATION AND RNAV/RNP NAVIGATION ELIGIBILITY...
Page 30 Page D01-14 Supplement D01: pages replacement instructions 4 – NORMAL PROCEDURES ECTION Make sure you first applied instructions reported on the basic AFM, Section 4 Normal Procedures According to A/C configuration apply following pages replacement: Supplement D01 NORMAL PROCEDURES Section 4 page page 4A-27 thru 38...
Page 31 Page D01-15 INTENTIONALLY LEFT BLANK Ed. 1, Rev.0 Section 9 – Supplements Supplement no. D01 – GARMIN GFC700 AUTOPILOT INSTALLATION AND RNAV/RNP NAVIGATION ELIGIBILITY...
Page 32 For detailed description of A/P selections, behaviour and display out- NOTE look, refer to the “Garmin G1000 Pilot’s Guide for the Tecnam P2010” (Part No. 190-01830-00 Revision A dated September 25, 2014 or a more updated version); it must be always carried in the aircraft and made available to the pilot at all time.
Page 33 A/P. Do the Emergency Recovery procedure if A/P operation is erratic or does not correctly control the airplane. WARNING The “Garmin G1000 Pilot’s Guide for the Tecnam P2010” (Part No. NOTE 190-01830-00 Revision A dated September 25, 2014 or a more updated version) must be carried in the aircraft and made available to the pilot at all time.
Page 34 AFMS N°D01 FOR GARMIN GFC700 AUTOPILOT INSTALLATION AND Page 4A-29 RNAV/RNP NAVIGATION ELIGIBILITY ALTITUDE HOLD MODE (ALT) Turning the ALT knob while in Altitude Hold Mode changes the Selected NOTE Altitude, but not the FD Altitude Refrence, and does not cancel the mode.
Page 35 AFMS N°D01 FOR GARMIN GFC700 AUTOPILOT INSTALLATION AND Page 4A-30 RNAV/RNP NAVIGATION ELIGIBILITY AUTOPILOT ABNORMAL PROCEDURES Loss of a single GPS: In case of loss of a single GPS, RNAV guidance will still be available as the sys- tem will automatically revert to the other available GPS without losing any auto- pilot / FD guidance.
Page 36 AFMS N°D01 FOR GARMIN GFC700 AUTOPILOT INSTALLATION AND Page 4A-31 RNAV/RNP NAVIGATION ELIGIBILITY Changes in wind speed and/or wind direction compound the relative in- NOTE accuracy of DR Mode. Because of this degraded accuracy, other naviga- tion equipment must be relied upon for position awareness until GPS- derived position data is restored.
Page 37 AFMS N°D01 FOR GARMIN GFC700 AUTOPILOT INSTALLATION AND Page 4A-32 RNAV/RNP NAVIGATION ELIGIBILITY ADDITIONAL GUIDANCE FOR RNAV GPS Experience of RNAV systems, and Flight FMS in general, has identified the pit- falls of waypoint entry error at the receiver as well as inaccuracies and errors in the database itself.
Page 38 AFMS N°D01 FOR GARMIN GFC700 AUTOPILOT INSTALLATION AND Page 4A-33 RNAV/RNP NAVIGATION ELIGIBILITY (b) 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 ac- tive flight plan should be checked by comparing the charts, SID or other applica- ble documents, with the map display.
Page 39 AFMS N°D01 FOR GARMIN GFC700 AUTOPILOT INSTALLATION AND Page 4A-34 RNAV/RNP NAVIGATION ELIGIBILITY Route modifications in the terminal area may take the form of radar headings or ‗direct to‘ clearances and the flight crew must be capable of reacting in a timely fashion.
Page 40 AFMS N°D01 FOR GARMIN GFC700 AUTOPILOT INSTALLATION AND Page 4A-35 RNAV/RNP NAVIGATION ELIGIBILITY Whenever an approach is selected, the choice to either ― load‖ or ― activate‖ is giv- en. ― Loading‖ adds the approach to the end of the flight plan without immediately using it for navigation guidance.
Page 41 AFMS N°D01 FOR GARMIN GFC700 AUTOPILOT INSTALLATION AND Page 4A-36 RNAV/RNP NAVIGATION ELIGIBILITY Before reaching the IAF, the flight crew should verify that the correct procedure has been loaded into the receiver‘s route or flight plan. A comparison with the ap- proach chart should be made including the following: a) The waypoint sequence.
Page 42 AFMS N°D01 FOR GARMIN GFC700 AUTOPILOT INSTALLATION AND Page 4A-37 RNAV/RNP NAVIGATION ELIGIBILITY NOTE: The instrument approach procedures associated with RNP APCH are en- titled RNAV (GNSS) to reflect that GNSS is the primary navigation system. With the inherent onboard performance monitoring and alerting provided by GNSS, the navigation specification qualifies as RNP, however these procedures pre-date PBN, so the chart name has remained as RNAV.
Page 43 AFMS N°D01 FOR GARMIN GFC700 AUTOPILOT INSTALLATION AND Page 4A-38 RNAV/RNP NAVIGATION ELIGIBILITY The approach should always be discontinued:  If the receiver fails to engage the correct approach mode or;  In case of Loss Of Integrity (LOI) monitoring or; ...
Page 44 Page D01-16 Supplement D01: pages replacement instructions 5 – PERFORMANCE ECTION Make sure you first applied instructions reported on the basic AFM, Section 5 Performance According to A/C configuration refer to the basic AFM, Section 5 – Performance Ed. 1, Rev.0 Section 9 –...
Page 45 Page D01-17 INTENTIONALLY LEFT BLANK Ed. 1, Rev.0 Section 9 – Supplements Supplement no. D01 – GARMIN GFC700 AUTOPILOT INSTALLATION AND RNAV/RNP NAVIGATION ELIGIBILITY...
Page 46 Page D01-18 Supplement D01: pages replacement instructions 6 – WEIGHT AND BALANCE ECTION Refer to the basic AFM, Section 6 Weight and Balance Ed. 1, Rev.0 Section 9 – Supplements Supplement no. D01 – GARMIN GFC700 AUTOPILOT INSTALLATION AND RNAV/RNP NAVIGATION ELIGIBILITY...
Page 47 Page D01-19 INTENTIONALLY LEFT BLANK Ed. 1, Rev.0 Section 9 – Supplements Supplement no. D01 – GARMIN GFC700 AUTOPILOT INSTALLATION AND RNAV/RNP NAVIGATION ELIGIBILITY...
Page 48 Page D01-20 Supplement D01: pages replacement instructions 7 – AIRFRAME AND SYSTEMS DESCRIPTION ECTION Make sure you first applied instructions reported on the basic AFM, Section 7 Airframe and Systems Description According to A/C configuration apply following pages replacement: Supplement D01 AIRFRAME AND SYSTEMS DESCRIPTION Section 7 page...
Page 49 Page D01-21 INTENTIONALLY LEFT BLANK Ed 1, Rev. 0 Section 9 – Supplements Supplement no. D01 – GARMIN GFC700 AUTOPILOT INSTALLATION AND RNAV/RNP NAVIGATION ELIGIBILITY...
Page 50 AFMS N°D01 FOR GARMIN GFC700 AUTOPILOT INSTALLATION AND Page 7A-8 RNAV/RNP NAVIGATION ELIGIBILITY 3 FLIGHT CONTROLS Aircraft flight controls are operated through conventional stick and rudder pedals. Longitudinal control acts through a system of push-rods and is equipped with a trim tab.
Page 51 AFMS N°D01 FOR GARMIN GFC700 AUTOPILOT INSTALLATION AND Page 7A-9 RNAV/RNP NAVIGATION ELIGIBILITY 4 INSTRUMENT PANEL The instrument panel is divided in three areas:  The left area holds Garmin G1000 PFD, a chronometer and the pitch trim indicator; The Central area holds the standby unit for PFI parameters, MD 302 suite, and the ...
Page 52 AFMS N°D01 FOR GARMIN GFC700 AUTOPILOT INSTALLATION AND RNAV/RNP NAVIGATION ELIGIBILITY Page 7A-20 9 ELECTRICAL SYSTEM Primary DC power is provided by an external alternator with a 28 VDC output, rated of 70 Amps @ 2700 rpm. During normal operations, it recharges the bat- tery.
Page 53 AFMS N°D01 FOR GARMIN GFC700 AUTOPILOT INSTALLATION AND RNAV/RNP NAVIGATION ELIGIBILITY Page 7A-21 .7-15. E LECTRICAL YSTEM RCHITECTURE 12.3 TALL ARNING YSTEM The aircraft is equipped with a stall warning system consisting of a sensor locat- ed on the right wing leading edge connected to a warning horn located near the instrument panel.
Page 54 AFMS N°D01 FOR GARMIN GFC700 AUTOPILOT INSTALLATION AND RNAV/RNP NAVIGATION ELIGIBILITY Page 7A-27 11.2 I NTERNAL LIGHTS On the cabin ceiling are located four map lights, two in the front area (pilot) and two in the rear area (passengers). In the central area of the cabin ceiling is located a spot light used to illuminate the pedestal during night flight operations.
Page 55 AFMS N°D01 FOR GARMIN GFC700 AUTOPILOT INSTALLATION AND RNAV/RNP NAVIGATION ELIGIBILITY Page 7A-33 ELT unit position placard: Breaker Panel placards: Ed. 1Rev 0 Section 7 – Airframe and Systems description PLACARDS...
Page 56 AFMS N°D01 FOR GARMIN GFC700 AUTOPILOT INSTALLATION AND RNAV/RNP NAVIGATION ELIGIBILITY Page 7A-33 Ed. 1Rev 0 Section 7 – Airframe and Systems description PLACARDS...
Page 57 Page D01-22 Supplement D01: pages replacement instructions 8 – GROUND HANDLING & SERVICE ECTION Make sure you first applied instructions reported on the basic AFM, Section 8 Ground Handling & Service According to A/C configuration refer to the basic AFM, Section 8 – Ground Handling &...
Page 58 Page D01-23 INTENTIONALLY LEFT BLANK Ed. 1Rev 0 Section 9 – Supplements Supplement no. D01 – GARMIN GFC700 AUTOPILOT INSTALLATION AND RNAV/RNP NAVIGATION ELIGIBILITY...
Page 59 Page D02-1 . D02 UPPLEMENT NO AFMS FOR VARIABLE PITCH PROPELLER EQUIPPED AIRPLANES Record of Revisions EASA Approval or Tecnam Approval Revised Description of Under DOA page Revision Privileges Approved under the authority of DOA – New Edition D. Ronca M.
Page 60 Page D02-2 NTRODUCTION The information contained herein supplements or supersedes the basic Aircraft Flight Manual: detailed instructions are provided to allow the owner for replac- ing the AFM pages containing information amended as per MT variable pitch propeller in subject. It is the owner’s responsibility to replace the mentioned pages in accordance with the instructions herein addressed section by section.
Page 61 Page D02-3 Supplement D02: pages replacement instructions 1 – GENERAL ECTION Make sure you first applied instructions reported on the basic AFM, Section 1 General Apply following pages replacement: Supplement D02 – GENERAL page Section 1 page REPLACES Page 1-6 of AFM, Section 1 Edition, Rev.
Page 62 Page D02-4 INTENTIONALLY LEFT BLANK Edition, Rev. 0 Section 9 – Supplements Supplement no. D02 –Variable pitch propeller...
Page 63 AFMS N°D02 FOR VARIABLE PITCH PROPELLER EQUIPPED AIRPLANES Page V1-6 5. ENGINE Manufacturer …………………………… Lycoming Engines Model …………………………………... IO-360-M1A Type Certificate ………………………... EASA TCDS no. IM.E.032 Engine type …………………………….. Fuel injected (IO), direct drive, four cylinder horizontally opposed, air cooled with down exhaust outlets.
Page 64 Page D02-5 INTENTIONALLY LEFT BLANK Edition, Rev. 0 Section 9 – Supplements Supplement no. D02 – Variable pitch propeller...
Page 65 Page D02-6 Supplement D02: pages replacement instructions 2 – LIMITATIONS ECTION Make sure you first applied instructions reported on the basic AFM, Section 2 Limitations Apply following pages replacement: Supplement D02 – LIMITATIONS page Section 2 page V2-7 REPLACES Page 2-7 of AFM, Section 2 V2-9 REPLACES Page 2-9 of AFM, Section 2...
Page 66 Page D02-7 INTENTIONALLY LEFT BLANK Edition, Rev. 0 Section 9 – Supplements Supplement no. D02 – Variable pitch propeller...
Page 67 AFMS N°D02 FOR VARIABLE PITCH PROPELLER EQUIPPED AIRPLANES Page V2-7 4. POWERPLANT LIMITATIONS Following table reports the operating limitations the installed engine: : Lycoming Engines NGINE MANUFACTURER : IO-360-M1A NGINE MODEL AXIMUM POWER Max Power Max rpm. Prop. rpm (hp) Max.
Page 68 AFMS N°D02 FOR VARIABLE PITCH PROPELLER EQUIPPED AIRPLANES Page V2-9 5. PAINT To ensure that the temperature of the composite structure does not exceed limits, the outer surface of the aeroplane must be painted with white paint, except for areas of registration marks, placards, and ornament.
Page 69 AFMS N°D02 FOR VARIABLE PITCH PROPELLER EQUIPPED AIRPLANES Page V2-10 4. POWERPLANT INSTRUMENT MARKINGS Powerplant instrument markings and their colour code significance are shown below: RED ARC WHITE ARC GREEN ARC YELLOW ARC RED ARC Minimum Advisory Safe Caution Maximum INSTRUMENT limit limit...
Page 70 Page D02-8 INTENTIONALLY LEFT BLANK Edition, Rev. 3 Section 9 – Supplements Supplement no. D02 – Variable pitch propeller...
Page 71 Page D02-9 Supplement D02: pages replacement instructions 3 – E ECTION MERGENCY ROCEDURES Make sure you first applied instructions reported on the basic AFM, Section 3 Emergency Procedures Apply following pages replacement: Supplement D02 – Emergency Procedures page Section 3 page V3-4 REPLACES Page 3-4 of AFM, Section 3...
Page 72 Page D02-10 INTENTIONALLY LEFT BLANK Edition, Rev. 0 Section 9 – Supplements Supplement no. D02 – Variable pitch propeller...
Page 73 AFMS N°D02 FOR VARIABLE PITCH PROPELLER EQUIPPED AIRPLANES Page V3-4 1.1. R EFERENCE IRSPEEDS FOR EMERGENCY ROCEDURES Best glide speed (V 84 KIAS GLIDE No-flaps Approach Speed 80 KIAS Edition, Rev. 3 Section 3 – Emergency procedures...
Page 74 AFMS N°D02 FOR VARIABLE PITCH PROPELLER EQUIPPED AIRPLANES Page V3-14 6.3 P ROPELLER OVERSPEED In case of propeller overspeed in flight, apply following procedure: 1. Throttle Lever ……………. REDUCE power 2. Propeller Lever ……………. Decrease RPM 3. Mixture Lever ……………. As required 4.
Page 75 AFMS N°D02 FOR VARIABLE PITCH PROPELLER EQUIPPED AIRPLANES Page V3-18 6.10 D EFECTIVE ENGINE CONTROLS Defective Mixture Control Cable 1. Maintain altitude to the nearest arfield 2. During descent, check engine behaviour to a higher power setting. A lean mixture can lead to engine roughness and loss of power. Landing approach must be planned accordingly.
Page 76 AFMS N°D02 FOR VARIABLE PITCH PROPELLER EQUIPPED AIRPLANES Page V3-19 NFLIGHT ENGINE RESTART 7.1 P ROPELLER WINDMILLING In case of engine shutdown, propeller will keep windmilling and will not stop, preventing the use of ignition key. Engine inflight restart must be performed without using ignition key with propeller wind- milling in order to avoid possible engine damages.
Page 77 Page D02-11 INTENTIONALLY LEFT BLANK Edition, Rev. 0 Section 9 – Supplements Supplement no. D02 – Variable pitch propeller...
Page 78 Page D02-12 Supplement D02: pages replacement instructions 4 – N ECTION ORMAL ROCEDURES Make sure you first applied instructions reported on the basic AFM, Section 4 Normal Procedures Apply following pages replacement: Supplement D02 – Normal Procedures page Section 4 page V4-7 REPLACES Page 4-7 of AFM, Section 4...
Page 79 Page D02-13 INTENTIONALLY LEFT BLANK Edition, Rev. 0 Section 9 – Supplements Supplement no. D02 – Variable pitch propeller...
Page 80 AFMS N°D02 FOR VARIABLE PITCH PROPELLER EQUIPPED AIRPLANES Page – V4-7 3. AIRSPEEDS FOR NORMAL OPERATIONS The following airspeeds are those which are significant for normal operations. FLAPS 1160kg (2557lbs) Rotation Speed (V 60 KIAS Best Angle-of-Climb Speed (V 65 KIAS Best Angle-of-Climb Speed (V 0°...
Page 81 AFMS N°D02 FOR VARIABLE PITCH PROPELLER EQUIPPED AIRPLANES Page – V4-15 5. CHECKLISTS 5.1. EFORE TARTING ENGINE FTER REFLIGHT NSPECTION 1. Seat position and safety belts: adjust 2. Flight controls: operate full stroke checking for movement smoothness, free of play and friction. 3.
Page 82 AFMS N°D02 FOR VARIABLE PITCH PROPELLER EQUIPPED AIRPLANES Page V4-19 5.5. EFORE TAKEOFF 1. Parking brake: brake pedal press, ON 2. Engine instruments: Check within limits 3. ALT OUT caution: OFF (check) 4. Electric Fuel pump: ON 5. Fuel selector valve: select the fullest tank 6.
Page 83 AFMS N°D02 FOR VARIABLE PITCH PROPELLER EQUIPPED AIRPLANES Page V4-20 5.6. AKEOFF For 5000ft density altitude and above, or high ambient temperatures, a FULL RICH mixture may cause rough running of the engine or a loss of performance. The mixture may be ad- justed to obtain smooth engine operations.
Page 84 AFMS N°D02 FOR VARIABLE PITCH PROPELLER EQUIPPED AIRPLANES Page V4-21 5.7. LIMB Due to position of fuel sensors, during climb fuel gauges in cockpit will indicate a fuel NOTE quantity slightly lower than the real amount. Regaining level flight will immediately restore correct indications.
Page 85 AFMS N°D02 FOR VARIABLE PITCH PROPELLER EQUIPPED AIRPLANES Page V4-22 5.8. RUISE 1. Power: set performance as required, refer to table in section 5 of AFM 2. Propeller lever: 1800-2400 RPM 3. Fuel tank selector: as required to maintain symmetric balance 4.
Page 86 AFMS N°D02 FOR VARIABLE PITCH PROPELLER EQUIPPED AIRPLANES Page V4-23 5.10. ESCENT Due to position of fuel sensors, during descent fuel gauges in cockpit will indicate a fuel NOTE quantity slightly higher than the real amount. Regaining level flight will immediately re- store correct indications.
Page 87 AFMS N°D02 FOR VARIABLE PITCH PROPELLER EQUIPPED AIRPLANES Page V4-24 5.11. EFORE LANDING Electric fuel pump: ON Fuel valve: select the fullest tank Landing Light: ON On downwind, leg abeam touch down point: Flaps: set T/O (below 90KIAS) Expect to adjust pitch trim (pitch down) when extending flaps to T/O or NOTE LAND Approach speed: set...
Page 88 AFMS N°D02 FOR VARIABLE PITCH PROPELLER EQUIPPED AIRPLANES Page V4-25 5.15. NGINE SHUT DOWN Parking brake: set Keep engine running at 1200 propeller rpm for about one minute in order to reduce latent heat. Avionic equipment: OFF Throttle: idle Magnetos: Check OFF – BOTH Mixture: closed Ignition key: OFF, key extracted Strobe light: OFF...
Page 89 AFMS N°D02 FOR VARIABLE PITCH PROPELLER EQUIPPED AIRPLANES Page V4-26 5.17. FLIGHT IN RAIN Performance deteriorates in rain; this applies particularly to take-off distance and maximum Horizontal speed. The effect on flight characteristics is minimal. 5.18. REFUELLING Before refuelling, the airplane must be connected to electrical ground. 5.19.
Page 90 Page D02-14 Supplement D02: pages replacement instructions 5 – P ECTION ERFORMANCES Supplement D02- Performances pages replace basic AFM Section 5 as whole Edition, Rev. 0 Section 9 – Supplements Supplement no. D02 – Variable pitch propeller...
Page 91 Page D02-15 INTENTIONALLY LEFT BLANK Edition, Rev. 0 Section 9 – Supplements Supplement no. D02 – Variable pitch propeller...
Page 92 AFMS N°D02 FOR VARIABLE PITCH PROPELLER EQUIPPED AIRPLANES Page V5-1 SECTION 5 – PERFORMANCE INDEX 1. Introduction ..............2 2. Use of Performance Charts ..........2 3. Airspeed Indicator System Calibration ......3 4. ICAO Standard Atmosphere ........... 5 5. Stall speed ..............6 6.
Page 93 AFMS N°D02 FOR VARIABLE PITCH PROPELLER EQUIPPED AIRPLANES Page V5-2 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: ...
Page 94 AFMS N°D02 FOR VARIABLE PITCH PROPELLER EQUIPPED AIRPLANES Page V5-3 3. A IRSPEED NDICATOR YSTEM ALIBRATION Normal Static Source Graph shows calibrated airspeed V as a function of indicated airspeed V Airspeed Indication System Calibration Flap UP Flap T/O Flap LN Calibrated Airspeed [KCAS] Fig.
Page 95 AFMS N°D02 FOR VARIABLE PITCH PROPELLER EQUIPPED AIRPLANES Page V5-4 Alternate Static Source Alternate Static Air Open Vents Open Vents and Hot Air Open [kn] [ft] [kn] [ft] [kn] [ft] Pressure Altitude FLAP UP [ft] [kn] 1020 1010 1020 1020 1030 1020 1030...
Page 96 AFMS N°D02 FOR VARIABLE PITCH PROPELLER EQUIPPED AIRPLANES Page V5-5 4. ICAO S TANDARD TMOSPHERE . 5-2. ICAO C HART Examples: Scope Given Find A: Pressure altitude = 1600ft Density Altitude: → C: Density Altitude = 2550ft B: Temperature = 20°C →...
Page 97 AFMS N°D02 FOR VARIABLE PITCH PROPELLER EQUIPPED AIRPLANES Page V5-6 5. S TALL SPEED Weight: 1160 kg (2557 lb) Throttle Lever: IDLE CG: Most Forward (19%) No ground effect TALL PEED EIGHT NGLE 0° LAPS LAPS LAPS [kg] [deg] KIAS KCAS KIAS KCAS...
Page 98 AFMS N°D02 FOR VARIABLE PITCH PROPELLER EQUIPPED AIRPLANES Page V5-7 6. C ROSSWIND Maximum demonstrated crosswind is 12 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 .
Page 99 AFMS N°D02 FOR VARIABLE PITCH PROPELLER EQUIPPED AIRPLANES Page V5-8 7. T FF PERFORMANCES To account for likely in service performance variations apply a factored to distances of 1.10 NOTE Weight = 1160 kg (2557 lb) Corrections Flaps: T/O Headwind: -10 m for each kn Speed at Lift-Off = 60 KIAS Tailwind: +20 m for each kn Speed Over 50ft Obstacle = 65 KIAS...
Page 100 AFMS N°D02 FOR VARIABLE PITCH PROPELLER EQUIPPED AIRPLANES Page V5-9 Weight = 1060 kg (2337 lb) Corrections Headwind: -10 m for each kn Flaps: T/O Tailwind: +20 m for each kn Speed at Lift-Off = 60 KIAS Grass Runway: +10% to Ground Roll Speed Over 50ft Obstacle = 65 KIAS Runway slope: +10% to Ground Roll for each +1% Throttle and Propeller Lever: Full Forward...
Page 101 AFMS N°D02 FOR VARIABLE PITCH PROPELLER EQUIPPED AIRPLANES Page V5-10 Weight = 960 kg (2116 lb) Corrections Flaps: T/O Headwind: -10 m for each kn Speed at Lift-Off = 60 KIAS Tailwind: +20 m for each kn Speed Over 50ft Obstacle = 65 KIAS Grass Runway: +10% to Ground Roll Throttle and Propeller Lever: Full Forward Runway slope: +10% to Ground Roll for each +1%...
Page 102 AFMS N°D02 FOR VARIABLE PITCH PROPELLER EQUIPPED AIRPLANES Page V5-11 8. T ATE OF LIMB To account for likely in service performance variations apply a NOTE factored to rate of climb of 0.90 Full Forward Throttle Lever: Propeller: 2600 RPM Flaps: Take-Off Rate of Climb [ft/min] Climb...
Page 103 AFMS N°D02 FOR VARIABLE PITCH PROPELLER EQUIPPED AIRPLANES Page V5-12 9. E OUTE ATE OF LIMB To account for likely in service performance variations apply a NOTE factored to rate of climb of 0.90 Full Forward Throttle Lever: Propeller: 2600 RPM Flaps: UP Rate of Climb [ft/min] Climb...
Page 104 AFMS N°D02 FOR VARIABLE PITCH PROPELLER EQUIPPED AIRPLANES Page V5-13 10. C RUISE ERFORMANCE Corrections Weight: 1160 kg Mixture: FULL RICH Best Power: -10% to Full Rich F.C. Pressure Altitude: 0 ft Best Economy: -20% to Full Rich F.C. ISA – 30°C (-15°C) ISA (15°C) ISA + 30°C (45°C) RPM MAP...
Page 105 AFMS N°D02 FOR VARIABLE PITCH PROPELLER EQUIPPED AIRPLANES Page V5-14 Corrections Weight: 1160 kg Mixture: FULL RICH Best Power: -10% to Full Rich F.C. Pressure Altitude: 3000 ft Best Economy: -20% to Full Rich F.C. ISA – 30°C (-21°C) ISA (9°C) ISA + 30°C (39°C) RPM MAP F.C.
Page 106 AFMS N°D02 FOR VARIABLE PITCH PROPELLER EQUIPPED AIRPLANES Page V5-15 Corrections Weight: 1160 kg Mixture: FULL RICH Best Power: -10% to Full Rich F.C. Pressure Altitude: 6000 ft Best Economy: -20% to Full Rich F.C. ISA – 30°C (-27°C) ISA (3°C) ISA + 30°C (33°C) RPM MAP F.C.
Page 107 AFMS N°D02 FOR VARIABLE PITCH PROPELLER EQUIPPED AIRPLANES Page V5-16 Corrections Weight: 1160 kg Mixture: FULL RICH Best Power: -10% to Full Rich F.C. Pressure Altitude: 9000 ft Best Economy: -20% to Full Rich F.C. ISA – 30°C (-33°C) ISA (-3°C) ISA + 30°C (27°C) RPM MAP F.C.
Page 108 AFMS N°D02 FOR VARIABLE PITCH PROPELLER EQUIPPED AIRPLANES Page V5-17 11. L ANDING PERFORMANCES To account for likely in service performance variations apply a NOTE factored to distances of 1.67 Weight = 1160 kg (2557 lb) Corrections Headwind: -4 m for each kn Flaps: LAND Tailwind: +13 m for each kn Short Final Approach Speed = 66 KIAS...
Page 109 AFMS N°D02 FOR VARIABLE PITCH PROPELLER EQUIPPED AIRPLANES Page V5-18 12. B ALKED ANDING ERFORMANCE To account for likely in service performance variations apply a NOTE factored to rate of climb and to angle of climb of 0.90 Throttle and Propeller Lever: Full Forward Flaps: LAND Speed: 67 KIAS Steady Gradient of Climb [%]...
Page 110 AFMS N°D02 FOR VARIABLE PITCH PROPELLER EQUIPPED AIRPLANES Page V5-19 13. N OISE Noise level, determined in accordance with ICAO/Annex 16 6 Ed., July 2011, Vol. I°, Chapter 10 and 14 CFR 36.1581(c), is 80.58 dB(A). NOTE: No determination has been made by the Federal Aviation Administration that the noise levels of this aircraft are or should be acceptable or unacceptable for operation at, into, or out of, any airport.
Page 111 AFMS N°D02 FOR VARIABLE PITCH PROPELLER EQUIPPED AIRPLANES Page D02-16 INTENTIONALLY LEFT BLANK Edition, Rev. 0 Section 9 – Supplements Supplement no. D02 – Variable pitch propeller GENERAL FEATURES...
Page 112 AFMS N°D02 FOR VARIABLE PITCH PROPELLER EQUIPPED AIRPLANES Page D02-17 Supplement D02: pages replacement instructions 7 – A ECTION IRCRAFT AND YSTEMS ESCRIPTION Make sure you first applied instructions reported on the basic AFM, Section 7 Aircraft and Systems Description Apply following pages replacement: Supplement D02 –...
Page 113 AFMS N°D02 FOR VARIABLE PITCH PROPELLER EQUIPPED AIRPLANES Page D02-18 INTENTIONALLY LEFT BLANK Edition, Rev. 0 Section 9 – Supplements Supplement no. D02 – Variable pitch propeller...
Page 114 AFMS N°D02 FOR VARIABLE PITCH PROPELLER EQUIPPED AIRPLANES Page V7-10 NGINE CONTROL LEVER Engine handling is via three levers: Throttle, RPM lever, Mixture control lever. They’re situated on the center control; the use of “front/forward” and “rear/backward” is defined in relation to the direction of flight (longitudinal). Mixture control lever This lever (right hand lever with red handle) controls the fuel-air mixture, which is supplied to the engine.
Page 115 AFMS N°D02 FOR VARIABLE PITCH PROPELLER EQUIPPED AIRPLANES Page V7-11 LTERNATE Alternate Air knob is located on the central pedestal; when the knob is fully pulled outward from the instrument panel, injectors receive maximum hot air. During nor- mal operation, the knob is set in OFF position. EFROST AND ABIN Two knobs, located on the lower side of the central pedestal, allow Defrost and Cabin...
Page 116 AFMS N°D02 FOR VARIABLE PITCH PROPELLER EQUIPPED AIRPLANES Page V7-16 7. POWERPLANT 7.1. ENGINE Manufacturer …………………………… Lycoming Textron Model …………………………………... IO-360-M1A Type Certificate ………………………... EASA TCDS no. IM.E.032 Engine type …………………………….. Fuel injected (IO), direct drive, four cylinder horizontally opposed, air cooled with down exhaust outlets.
Page 117 AFMS N°D02 FOR VARIABLE PITCH PROPELLER EQUIPPED AIRPLANES Page V7-27 11.2 I NTERNAL LIGHTS On the cabin ceiling are located four map lights, two in the front area (pilot) and two in the rear area (passengers). In the central area of the cabin ceiling is located a spot light used to illuminate the pedestal during night flight operations.
Page 118 AFMS N°D02 FOR VARIABLE PITCH PROPELLER EQUIPPED AIRPLANES Page V7-36 Pedestal placards: Edition, Rev. 0 Section 9 – Supplements PLACARDS...
Page 119 Page D03-1 Supplement no. D03- AFMS FOR ALTERNATIVE AVIONICS CONFIGURATION Record of Revisions EASA Approval or Tecnam Approval Revised Description of Under DOA page Revision Privileges First Issue D. Ronca M. Oliva M. Oliva Approved under the au- Amended to add the wording “Ap- thority of DOA ref.
Page 120 Page D03-2 INDEX INTRODUCTION ..................3 Section 1 – GENERAL ................5 Section 2 – LIMITATIONS ..............7 Section 3 – EMERGENCY PROCEDURES ..........10 Section 4 – NORMAL PROCEDURES ........... 13 Section 5 – PERFORMANCE ..............16 Section 6 – WEIGHT AND BALANCE ........... 18 Section 7 –...
Page 121 Page D03-3 INTRODUCTION 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 Garmin G500 in subject. It is the owner’s responsibility to replace the mentioned pages in accordance with the instructions herein addressed section by section.
Page 122 Page D03-4 INTENTIONALLY LEFT BLANK Ed. 1, Rev. 0 Section 9 - Supplements Supplement no. D03 - ALTERNATIVE AVIONICS CONFIGURATION...
Page 123 Page D03-5 Supplement D03: pages replacement instructions 1 – GENERAL ECTION Make sure you first applied instructions reported on the basic AFM, Section 1 General According to A/C configuration refer to the basic AFM, Section 1 – General Ed. 1, Rev. 0 Section 9 - Supplements Supplement no.
Page 124 Page D03-6 INTENTIONALLY LEFT BLANK Ed. 1, Rev. 0 Section 9 - Supplements Supplement no. D03 - ALTERNATIVE AVIONICS CONFIGURATION...
Page 125 Page D03-7 Supplement D03: pages replacement instructions 2 – LIMITATIONS ECTION Make sure you first applied instructions reported on the basic AFM, Section 2 Limitations According A/C configuration apply following pages replacement: Supplement D03 LIMITATIONS Section 2 page page 2G-13 Page 2-13 of basic AFM, Section 2 REPLACES Ed.
Page 126 Page D03-8 INTENTIONALLY LEFT BLANK Ed. 1, Rev. 0 Section 9 - Supplements Supplement no. D03 - ALTERNATIVE AVIONICS CONFIGURATION...
Page 127 AFMS N°D03 FOR ALTERNATIVE AVIONICS CONFIGURATION Page 2G-13 18. KINDS OF OPERATION EQUIPMENT LIST (KOEL) This paragraph reports the KOEL table, concerning the equipment list required on board under CS-23 regulations to allow flight operations in VFR Day/Night and IFR Day/Night. Flight in VFR Day/Night and IFR is permitted only if the prescribed equipment is in- stalled and operational.
Page 128 Page D03-09 INTENTIONALLY LEFT BLANK Ed. 1, Rev. 0 Section 9 - Supplements Supplement no. D03 - ALTERNATIVE AVIONICS CONFIGURATION...
Page 129 Page D03-10 Supplement D03: pages replacement instructions 3 – EMERGENCY PROCEDURES ECTION Make sure you first applied instructions reported on the basic AFM, Section 3 Emergency Procedures According A/C configuration apply following pages replacement: Supplement D03 EMERGENCY PROCEDURES Section 3 page page 3G-5 3-5 of basic AFM, Section 3...
Page 130 Page D03-11 INTENTIONALLY LEFT BLANK Ed 1, Rev. 0 Section 9 - Supplements Supplement no. D03 - ALTERNATIVE AVIONICS CONFIGURATION...
Page 131 AFMS N°D03 FOR ALTERNATIVE AVIONICS CONFIGURATION Page 3G-5 2. F AILURES INDICATED ON THE ANNUNCIATION PANEL The annunciator panel, located on the centre of the instrument panel, contains 9 lights for warnings, cautions and advisories. The colours are as follows: GREEN: to indicate that pertinent device is turned ON AMBER:...
Page 132 AFMS N°D03 FOR ALTERNATIVE AVIONICS CONFIGURATION Page 3G-6 2.2 P ITOT HEATING SYSTEM FAILURE When the Pitot Heating system is activated, the green PITOT HEAT ON ad- visory light turns on and the amber PITOT HEAT caution light turns OFF, indicating that the Pitot Heating system is functioning properly.
Page 133 AFMS N°D03 FOR ALTERNATIVE AVIONICS CONFIGURATION Page 3G-7 3. G500 S YSTEM AILURES 3.1 L OSS OF INFORMATION DISPLAYED When a LRU or a LRU function fails, a large red „X‟ is typically displayed on the display field associated with the failed data. In most of cases, the red “X”...
Page 134 AFMS N°D03 FOR ALTERNATIVE AVIONICS CONFIGURATION Page 3G-10 3.7 D ISPLAY FAILURE In case of display failure refer to backup instrument (MD302) for primary flight information, and to GTN650 for navigation information. 3.8 L OW FUEL QUANTITY LEFT If fuel quantity LH is under 24 litres 1.
Page 135 AFMS N°D03 FOR ALTERNATIVE AVIONICS CONFIGURATION Page 3G-16 6.7 O IL PRESSURE LIMITS EXCEEDANCE OW OIL PRESSURE If oil pressure is under the lower limit (25 psi) 1. Throttle Lever …………… REDUCE to minimum practical 2. Mixture Lever ...………….. as required 3.
Page 136 AFMS N°D03 FOR ALTERNATIVE AVIONICS CONFIGURATION Page 3G-17 6.8 L OW FUEL PRESSURE If fuel pressure decreases below the lower limit (14 psi) 1. Electric fuel pump………... ON 2. Fuel selector valve………..Select opposite fuel tank if NOT empty 3. Fuel quantity ……………..CHECK If fuel pressure doesn‟t build up: 1.
Page 137 AFMS N°D03 FOR ALTERNATIVE AVIONICS CONFIGURATION Page 3G-25 10. O THER EMERGENCIES 10.1 OSS OF SSENTIAL In case of loss of essential bus, the following will be lost (related breakers are listed): PFD/MFD FLAP ACTUATOR COM1 PITOT HEAT GPS/NAV1 STROBE LIGHT LANDING LIGHT FUEL PUMP AHRS...
Page 138 Page D03-12 INTENTIONALLY LEFT BLANK Ed 1, Rev. 0 Section 9 - Supplements Supplement no. D03 - ALTERNATIVE AVIONICS CONFIGURATION...
Page 139 Page D03-13 Supplement D03: pages replacement instructions 4 – NORMAL PROCEDURES ECTION Make sure you first applied instructions reported on the basic AFM, Section 4 Normal Procedures According A/C configuration apply following pages replacement: Supplement D03 – NORMAL PROCEDURES Section 4 page page 4G-4 REPLACES...
Page 140 Page D03-14 INTENTIONALLY LEFT BLANK Ed. 1, Rev.0 Section 9 - Supplements Supplement no. D03 - ALTERNATIVE AVIONICS CONFIGURATION...
Page 141 AFMS N°D03 FOR ALTERNATIVE AVIONICS CONFIGURATION Page 4G-4 2. IFR : G500 FLIGHT GROUND TRAINING PRE REQUISITES The aircraft is equipped with a Garmin G500 avionic suite that integrates radio aids navigation with GPS navigation, providing an outstanding capability to support IFR flight, from basic instrument flight training to complex IFR scenar- NOTE Depending on national regulations, in some countries flying IFR with a single...
Page 142 AFMS N°D03 FOR ALTERNATIVE AVIONICS CONFIGURATION Page 4G-5 NOTE The necessity to correct or modify flight plans in the Garmin G500 under these conditions may distract pilots from basic handling causing deviations from as- signed parameters, so careful attention must be exercised to avoid deviations on flying parameters.
Page 143 AFMS N°D03 FOR ALTERNATIVE AVIONICS CONFIGURATION Page 4G-9 4. P FLIGHT NSPECTION Before each flight, it is necessary to carry out a complete aircraft check including a cabin inspection followed by an external inspection, as below detailed. 4.1 C ABIN NSPECTION Aircraft documents (ARC, Certificate of Airworthiness, Noise certificate, Radio COM certificate, AFM): check current and on board...
Page 144 AFMS N°D03 FOR ALTERNATIVE AVIONICS CONFIGURATION Page 4G-15 5. C HECKLISTS 5.1 B EFORE TARTING ENGINE FTER REFLIGHT NSPECTION 1. Seat position and safety belts: adjust 2. Flight controls: operate full stroke checking for movement smoothness, free of play and friction.
Page 145 AFMS N°D03 FOR ALTERNATIVE AVIONICS CONFIGURATION Page 4G-16 5.2 E NGINE TARTING (a) Cold engine Engine throttle: 1cm above idle Fuel selector valve: select the tank with less fuel Electric fuel pump: ON Mixture: full open for 3 – 5” (positive fuel flow indication) then CUT-OFF Propeller area: check that area is clear of persons / objects Check to insure no person or object is present in the area close to the propeller.
Page 146 AFMS N°D03 FOR ALTERNATIVE AVIONICS CONFIGURATION Page 4G-17 (b) Warm engine Engine throttle: idle Fuel selector valve: select the tank with less fuel Electric fuel pump: ON Propeller area: check for area clear of persons / objects Check to insure no person or object is present in the area close to the propel- ler.
Page 147 AFMS N°D03 FOR ALTERNATIVE AVIONICS CONFIGURATION Page 4G-18 5.3 B EFORE TAXIING 1. Flight instruments and avionics: set, TEST functions 2. Altimeter: set 3. Pitot Heat: ON, test for ammeter indication, then OFF 4. Taxi light: ON 5. Parking brake: OFF When taxiing at close range to other aircraft, or during night flight in clouds, fog or haze, the strobe lights should be switched OFF.
Page 148 AFMS N°D03 FOR ALTERNATIVE AVIONICS CONFIGURATION Page 4G-20 5.6 T AKEOFF For 5000ft density altitude and above, or high ambient temperatures, a FULL RICH mixture may cause rough running of the engine or a loss of performance. The mixture may be ad- justed to obtain smooth engine operations.
Page 149 AFMS N°D03 FOR ALTERNATIVE AVIONICS CONFIGURATION Page 4G-24 5.11 EFORE LANDING 1. Electric fuel pump: ON 2. Fuel valve: select the fullest tank Landing Light: ON On downwind, leg abeam touch down point: Flaps: set T/O (below 90KIAS) Expect to adjust pitch trim (pitch down) when extending flaps to T/O or NOTE LAND 5.
Page 150 Page D03-15 INTENTIONALLY LEFT BLANK Ed. 1, Rev. 0 Section 9 - Supplements Supplement no. D03 - ALTERNATIVE AVIONICS CONFIGURATION...
Page 151 Page D03-16 Supplement D03: pages replacement instructions 5 – PERFORMANCE ECTION Make sure you first applied instructions reported on the basic AFM, Section 5 Performance According to A/C configuration refer to the basic AFM, Section 5 – Performance Ed. 1, Rev.0 Section 9 - Supplements Supplement no.
Page 152 Page D03-17 INTENTIONALLY LEFT BLANK Ed. 1, Rev.0 Section 9 - Supplements Supplement no. D03 - ALTERNATIVE AVIONICS CONFIGURATION...
Page 153 Page D03-18 Supplement D03: pages replacement instructions 6 – WEIGHT AND BALANCE ECTION Refer to the basic AFM, Section 6 Weight and Balance Ed. 1, Rev. 0 Section 9 - Supplements Supplement no. D03 - ALTERNATIVE AVIONICS CONFIGURATION...
Page 154 Page D03-19 INTENTIONALLY LEFT BLANK Ed. 1, Rev. 0 Section 9 - Supplements Supplement no. D03 - ALTERNATIVE AVIONICS CONFIGURATION...
Page 155 Page D03-20 Supplement D03: pages replacement instructions 7 – AIRFRAME AND SYSTEMS DESCRIPTION ECTION Make sure you first applied instructions reported on the basic AFM, Section 7 Airframe and Systems Description According A/C configuration apply following pages replacement: Supplement D03 – AIRFRAME AND SYSTEMS Section 7 page page...
Page 156 Page D03-21 INTENTIONALLY LEFT BLANK Ed 1, Rev. 0 Section 9 - Supplements Supplement no. D03 - ALTERNATIVE AVIONICS CONFIGURATION...
Page 157 AFMS N°D03 FOR ALTERNATIVE AVIONICS CONFIGURATION Page 7G-8 3. FLIGHT CONTROLS Aircraft flight controls are operated through conventional stick and rudder pedals. Longitudinal control acts through a system of push-rods and is equipped with a trim tab. a cable control circuit is confined within the cabin and it is connected to a pair of push-pull rod systems positioned in each main wing which control ailerons differen- tially.
Page 158 AFMS N°D03 FOR ALTERNATIVE AVIONICS CONFIGURATION Page 7G-9 4. INSTRUMENT PANEL The instrument panel installed on P2010, when equipped with G500 suite, is present- ed below:  N° 1 Garmin GDU 620 (PFD/MFD), (5);  N° 1 Garmin GTN 650 (Com/Nav/Gps), (9);...
Page 159 AFMS N°D03 FOR ALTERNATIVE AVIONICS CONFIGURATION Page 7G-20 5. ELECTRICAL SYSTEM Primary DC power is provided by an external alternator with a 28 VDC output, rated of 70 Amps @ 2700 rpm. During normal operations, it recharges the bat- tery. Secondary DC power is provided by a lead type battery (GILL G-247) which provides the energy necessary for feeding the essential electrical loads in the event of an alternator failure.
Page 160 AFMS N°D03 FOR ALTERNATIVE AVIONICS CONFIGURATION Page 7G-21 .7-15. E LECTRICAL YSTEM RCHITECTURE 9.1 S TALL ARNING YSTEM The aircraft is equipped with a stall warning system consisting of a sensor locat- ed on the right wing leading edge connected to a warning horn located near the instrument panel.
Page 161 P2010 avionic system, in this equipment configuration, is mainly based on avi- onics package Garmin G500. The G500 suite installed on P2010 is based on a single display layout. It pro- vides the pilot with all primary flight information and is able to act as a naviga- tion indicator for external navigation sources such as VHF NAV and GPS.
Page 162 AFMS N°D03 FOR ALTERNATIVE AVIONICS CONFIGURATION Page 7G-23 9.3 E XTERNAL OWER UPPLY On the right side of the tail cone, an external power is present. Using this device it is possible to feed the electric system directly on the main bus bar, by an ex- ternal power source.
Page 163 Page 7G-24 10. PITOT-STATIC PRESSURE SYSTEMS The P2010 air speed/altitude indicating systems are connected with a Pitot-Static system based on a total pressure/Pitot probe (simple Pitot tube, heated for icing protection) mounted on left wing strut and two static pressure ports connected in parallel and located in correspondence of engine firewall on left and right side of fuselage.
Page 164 AFMS N°D03 FOR ALTERNATIVE AVIONICS CONFIGURATION Page 7G-27 11.2 I NTERNAL LIGHTS On the cabin ceiling are located four map lights, two in the front area (pilot) and two in the rear area (passengers). In the central area of the cabin ceiling is located a spot light used to illuminate the pedestal during night flight operations.
Page 165 Page D03-22 Supplement D03: pages replacement instructions 8 – GROUND HANDLING & SERVICE ECTION Make sure you first applied instructions reported on the basic AFM, Section 8 Ground Handling & Service Refer to the basic AFM, Section 8 – Ground Handling & Service Ed.
Page 166 Page D03-23 INTENTIONALLY LEFT BLANK Ed. 1Rev 0 Section 9 - Supplements Supplement no. D03 - ALTERNATIVE AVIONICS CONFIGURATION...
Page 167 Page D04-1 Supplement no. D04- AFMS FOR AUTOMOTIVE FUEL Record of Revisions EASA Approval or Tecnam Approval Revised Description of Under DOA page Revision Privileges First Issue D. Ronca C. Caruso M. Oliva Approved under the au- Amended to add the wording “Ap- thority of DOA ref.
Page 168 Page D04-2 INDEX INTRODUCTION ..................3 Section 1 – GENERAL ................5 Section 2 – LIMITATIONS ..............7 Section 3 – EMERGENCY PROCEDURES ..........10 Section 4 – NORMAL PROCEDURES ........... 12 Section 5 – PERFORMANCE ..............14 Section 6 – WEIGHT AND BALANCE ........... 16 Section 7 –...
Page 169 Page D04-3 INTRODUCTION This section contains supplemental information to operate, in a safe and efficient manner, the aircraft when it uses Automotive Fuel MOGAS EN 228:2008(E). It is the owner’s responsibility to replace the mentioned pages in accordance with the instructions herein addressed section by section. Ed.
Page 170 Page D04-4 INTENTIONALLY LEFT BLANK Ed. 1, Rev. 0 Section 9 – Supplements Supplement no. D04 – AUTOMOTIVE FUEL...
Page 171 Page D04-5 Supplement D04: pages replacement instructions 1 – GENERAL ECTION Make sure you first applied instructions reported on the basic AFM, Section 1 General According to A/C configuration refer to the basic AFM, Section 1 – General Ed. 1, Rev. 0 Section 9 –...
Page 172 Page D04-6 INTENTIONALLY LEFT BLANK Ed. 1, Rev. 0 Section 9 – Supplements Supplement no. D04 – AUTOMOTIVE FUEL...
Page 173 Page D04-7 Supplement D04: pages replacement instructions 2 – LIMITATIONS ECTION Make sure you first applied instructions reported on the basic AFM, Section 2 Limitations According to A/C configuration apply following pages replacement: Supplement D04 LIMITATIONS Section 2 page page 2AF-8 2-8 of basic AFM, Section 2 REPLACES...
Page 174 Page D04-8 INTENTIONALLY LEFT BLANK Ed. 1, Rev. 0 Section 9 – Supplements Supplement no. D04 – AUTOMOTIVE FUEL...
Page 175 AFMS N°D04 FOR AUTOMOTIVE FUEL Page 2AF-8 FUEL 120 litres each one (31.7 US gallons) ANKS 240 litres (63.4 US gallons) AXIMUM CAPACITY 231 litres (61 US gallons) AXIMUM USABLE FUEL AVGAS Grade 91/96 or 100LL (ASTM D910) or PPROVED FUEL Automotive Fuel MOGAS EN228:2008(E) For additional information, refer to Lycoming Service Instruction No.
Page 176 Page D04-9 INTENTIONALLY LEFT BLANK Ed. 1, Rev. 0 Section 9 – Supplements Supplement no. D04 – AUTOMOTIVE FUEL...
Page 177 Page D04-10 Supplement D04: pages replacement instructions 3 – EMERGENCY PROCEDURES ECTION Make sure you first applied instructions reported on the basic AFM, Section 3 Emergency Procedures According to A/C configuration refer to the basic AFM, Section 3 – Emergency Proce- dures Ed.
Page 178 Page D04-11 INTENTIONALLY LEFT BLANK Ed. 1, Rev. 0 Section 9 – Supplements Supplement no. D04 – AUTOMOTIVE FUEL...
Page 179 Page D04-12 Supplement D04: pages replacement instructions 4 – NORMAL PROCEDURES ECTION Make sure you first applied instructions reported on the basic AFM, Section 4 Normal Procedures According to A/C configuration refer to the basic AFM, Section4 – Normal Procedures Ed.
Page 180 Page D04-13 INTENTIONALLY LEFT BLANK Ed. 1, Rev.0 Section 9 – Supplements Supplement no. D04 – AUTOMOTIVE FUEL...
Page 181 Page D04-14 Supplement D04: pages replacement instructions 5 – PERFORMANCE ECTION Make sure you first applied instructions reported on the basic AFM, Section 5 Performance According to A/C configuration refer to the basic AFM, Section 5 – Performance Ed. 1, Rev.0 Section 9 –...
Page 182 Page D04-15 INTENTIONALLY LEFT BLANK Ed. 1, Rev.0 Section 9 – Supplements Supplement no. D04 – AUTOMOTIVE FUEL...
Page 183 Page D04-16 Supplement D04: pages replacement instructions 6 – WEIGHT AND BALANCE ECTION Make sure you first applied instructions reported on the basic AFM, Section 6 Weight and Balance According to A/C configuration apply following pages replacement: Supplement D04 LIMITATIONS Section 6 page page...
Page 184 Page D04-17 INTENTIONALLY LEFT BLANK Ed. 1, Rev.0 Section 9 – Supplements Supplement no. D04 – AUTOMOTIVE FUEL...
Page 185 1041 83280 1041 83280 1583 Baggages Fuel (liters) 63936 Useful load 249118 1160 441960 29,8% CoG pos. NOTE: All data are referred to the P2010 S/N 003. Ed. 1, Rev. 0 Section 6 – Weight and balance WEIGHTS AND C.G.
Page 186 Page D04-18 INTENTIONALLY LEFT BLANK Ed. 1, Rev. 0 Section 9 – Supplements Supplement no. D04 – AUTOMOTIVE FUEL...
Page 187 Page D04-19 Supplement D04: pages replacement instructions 7 – AIRFRAME AND SYSTEMS DESCRIPTION ECTION Make sure you first applied instructions reported on the basic AFM, Section 7 Airframe and Systems Description According to A/C configuration apply following pages replacement: Supplement D04 AIRFRAME AND SYSTEMS DESCRIPTION Section 7 page...
Page 188 Page D04-20 INTENTIONALLY LEFT BLANK Ed. 1, Rev. 0 Section 9 – Supplements Supplement no. D04 – AUTOMOTIVE FUEL...
Page 189 AFMS Page 7AF-30 N°D04 FOR AUTOMOTIVE FUEL Allowed Fuel Placard: Tire Pressure placard: Stabilator degrees placard: Ed. 1, Rev. 0 Section 7 – Airframe and Systems description PLACARDS...
Page 190 Page D04-21 INTENTIONALLY LEFT BLANK Ed. 1, Rev. 0 Section 9 – Supplements Supplement no. D04 – AUTOMOTIVE FUEL...
Page 191 Page D04-22 Supplement D04: pages replacement instructions 8 – GROUND HANDLING & SERVICE ECTION Make sure you first applied instructions reported on the basic AFM, Section 8 Ground Handling & Service According to A/C configuration refer to the basic AFM, Section 8 – Ground Handling &...
Page 192 Page D04-23 INTENTIONALLY LEFT BLANK Ed. 1, Rev. 0 Section 9 – Supplements Supplement no. D04 – AUTOMOTIVE FUEL...
Page 193 Page D5-1 . D5 UPPLEMENT NO RGENTINE IRCRAFT LIGHT ANUAL UPPLEMENT Record of Revisions EASA Approval Tecnam Approval Revised Description of or Under DOA page Revision Privileges A. Sabino Editorial revision. C. Caruso M. Oliva List of Effective Pages Page...
Page 194 Page D5-2 NTRODUCTION This supplement contains supplementary information for a safe and efficient operation of the aircraft delivered in the Argentina For limitations, procedures, and performance information not contained in this supple- ment, refer to the EASA Approved Aircraft Flight Manual. LIMITATIONS The information contained herein complements or supersedes the basic information in the EASA Approved Aircraft Flight Manual.
Page 195 Page D5-3 THER PLACARDS Door Placard Baggage Door Internal door Placard Ed.2, Rev.0 Supplements no. D5 Supplement no. D5 – Argentine AFM supplement...
Page 196 Page D5-4 Emergency Exit internal placard Open baggage placard Door Handle locking Ed.2, Rev.0 Supplements no. D5 Supplement no. D5 – Argentine AFM supplement...
Page 197 Page D5-5 External Power Socket and baggage compartment placards Static source placards No Step placard Fuel Limitation placard Ed.2, Rev.0 Supplements no. D5 Supplement no. D5 – Argentine AFM supplement...
Page 198 Page D5-6 Safety equipment location placard ELT placard Ed.2, Rev.0 Supplements no. D5 Supplement no. D5 – Argentine AFM supplement...
Page 199 Page D07-1 Supplement no. D07- AFMS FOR GARMIN GFC700 AUTOPILOT AND VARIABLE PITCH PROPELLER EQUIPPED AEROPLANES Record of Revisions EASA Approval or Tecnam Approval Revised Description of Under DOA page Revision Privileges Approved under the authority of DOA Editorial Change F.
Page 200 Page D07-2 INDEX INDEX ..................... 2 INTRODUCTION ..................3 Section 1 – GENERAL ................5 Section 2 – LIMITATIONS ..............7 Section 3 – EMERGENCY PROCEDURES ..........9 Section 4 – NORMAL PROCEDURES............ 11 Section 5 – PERFORMANCE ..............13 Section 6 –...

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