Pilot's Operating Handbook

updated constantly concerning new manual editions and continued airworthiness communications. 1-11 Ed.1 Rev.0  The ENGINE manuals These manuals are all available on FLYROTAX website in the technical support section. Tecnam strongly recommend to sub- scribe to the ROTAX mailing list in order to be always updated concerning the latest manuals editions/revisions, and also to be in- formed immediately when airworthiness affecting documents have been issued. Tecnam recommend to use the same e-mail address used to subscribe all the aircraft-related mailing lists. The direct link to the ROTAX T-Publications page is: http://www.flyrotax.com/customer-serviceImpressum/technical-publications.aspx Note that all the ROTAX engines suitable for Tecnam Astore air- craft are compliant with the ASTM F2339-06. 1-12 Ed.1 Rev.0  The avionics documentation Some version of Tecnam Astore is equipped with avionics covered by respective manufacturer's documentation in terms of Operator's Manual. The brands have their own website section with all rele- vant manuals. Link to these sections are the following (other brands information, if applicable, are covered within the related Supplement): Garmin  Avionic suites (EFIS/EMS);  Autopilot;  Radio equipment;  Transponder;  Audio Panels;  GPS; http://www.garmin.com /en-US/explore/intheair/ Dynon  Avionic suites (EFIS/EMS);  Autopilot;  Engine Monitoring;  Radio equipment;  Transponder; http://www.dynonavioni cs.com/index.html 1-13 Ed.1 Rev.0  The propeller documentation The Astore can be equipped with three types of propellers, two ground-adjustable and one wooden made-fabric covered (standard equipment). All of three are built in USA by Sensenich. Following the P/N and factory details to the web service page. 3B0R5R68C Three blades - ground ad- justable propeller with 68'' diameter http://www.sensenich.c om/support/documents 2A0R5R70EN Two blades - ground ad- justable propeller with 70'' diameter W68T2ET-70J Two blades wood propel- ler with glass fiber wrap and 68'' diameter 1-14 Ed.1 Rev.0  Tecnam Aircraft Continued Airworthiness instructions These instructions need the registration to the mailing list Tecnam. Tecnam website is provided with a LOG IN section in which all the latest manuals revisions are available and so all the safety in- formation, which are automatically sent also by e-mail. The fol- lowing is the link to the NEW ACCOUNT registration page: http://www.tecnam.com/Register-User.aspx If you have already an user name and password, you can link di- rectly to the LOGIN page to access the Manuals: http://www.tecnam.com/Login.aspx The links for the Tecnam support page and Service Bulletin page are following reported: http://tecnam.com/Customer-Care/Support.aspx http://tecnam.com/Customer-Care/Service-Bulletins.aspx 1-15 Ed.1 Rev.0 1.1. Airplane description The Tecnam Astore is a low wing, two-place, single-engine airplane equipped with tricycle landing gear. It is made entirely in metal with fairings and upper radome in carbon/glass fiber with epoxy matrix. The main landing gear is made by a couple of 7075T6 light alloy springs which are hinged inside the fuselage in order to maximize the wheel deflection and energy absorption. The springs are supported by machined components which discharge the load directly on the wing carry through and rear bulkhead. Two rawhide liners are inserted be- tween each spring-leaf and the external machined beam. Two bolts se- cure the individual spring-leaf to the edge of the beam via a light alloy clamp while a single bolt secures the inboard end of the leaf-spring to the hinge and inner machined beam. The nose gear is pivoting and the energy absorption is made via an oleo-pneumatic shock absorber. It is fitted directly on the first fuselage bulkhead. The horizontal tail is made by a stabilizer and elevator with tip balanc- ing horns. All the control surfaces, except for the flaps and trim tab, are balanced. In order to read more about the airframe and systems refer to the Sec- tion No.7. 1-16 Ed.1 Rev.0 1.2. Views and dimensions Following the three views of the aircraft with most relevant dimen- sions. 1-17 Ed.1 Rev.0 1.3. Data and Characteristics 1.3.1. Dimensions and areas Wing Span 28.4 ft 8.65 mt Wing Area 131 ft2 12.15 mt2 Aspect Ratio 6.2 Overall length 23.0 ft 7.0 mt Overall width (cabin) 45.3 in 1.15 mt Overall height 7.5 ft 2.3 mt Stabilator span 10.5 ft 3.2 mt Stabilator area 24.0 ft2 2.23 mt2 Vertical tail area 11.5 ft2 1.07 mt2 Wheel track 5.6 ft 1.7 mt Wheel base 5.6 ft 1.7 mt Main gear tire 5.00-5 Air Trac or Goodyear Nose Gear tire 5.00-5 Air Trac or Goodyear Wheels and brakes Marc-Ingegno or Cleveland 1-18 Ed.1 Rev.0 1.3.2. Weights and capacities MTOW 1320 lb 599 kg Ramp Weight 1324 lb 601 kg Maximum allowed empty weight (100 hp Rotax 912iS2) 892 lb 405 kg Maximum allowed empty weight (115 hp Rotax 914) 885 lb 402 kg Maximum allowed baggage weight 77 lb 35 kg Total usable fuel 2x14.4 US Gal 2x54.5 lt 1.3.3. Performances Top speed (S.L. - IAS) 128kt 237km/h Stall speed (S.L. - IAS) - clean 35kt 65km/h Stall speed (S.L. - IAS) - T/O 34kt 63km/h Stall speed (S.L. - IAS) - LDG 32kt 59km/h Full fuel endurance (+30' res.) Engine rpm: 5.100 Cruise speed (TAS): 115kt Pressure Altitude: 6.000ft 5h:05' Rate of Climb (Vx - IAS) 59kt 109km/h Rate of Climb (Vy - IAS) 67kt 124km/h 1-19 Ed.1 Rev.0 1.3.4. Engine type This manual refer to the engine type ROTAX 914 UL2, as per the cover page. Anyway, two alternative engines can be installed and their respective manuals managed via dedicated POH. The allowed engines are: ROTAX ROTAX ROTAX 912ULS2* 912iS2 914UL2** * basic aircraft configuration ** this POH equipment 1.3.5. Propeller type This manual refer to the propeller type Sensenich 3B0R5R68C. Anyway, alternative propellers can be installed and their respec- tive manuals managed via POH Supplements. Three alternative propellers will not need a POH Supplement as the resulting per- formances and weighing and balancing are negligible: SENSENICH SENSENICH GT-Tonini 2A0R5R70EN W68T2ET-70J GT-2/173/VRR- FW101 2 blades - ground adj 2 blades - fix pitch 2 blades - fix pitch 1-20 Ed.1 Rev.0 1.3.6. Fuel Following the list of approved fuel to be operated with Rotax 912ULS2, 912iS2 and 914UL2. CAUTION Refer and familiarize with the latest approved ROTAX manuals in or- der to have a continue check of approved fuels. This list is based on ROTAX SI-912-016R6 1-21 Ed.1 Rev.0 The Tecnam Astore is equipped with two leading edge tanks while the entire fuel line is located below the cabin floor. Following the capacity of each tank is shown: Total fuel capacity (both tanks): 29US Gal (110lt) Total Usable 28.8US Gal (109lt) 1.3.7. Oil The oil specification to be used on Rotax engines are within the latest applicable revisions of Operator's Manual. CAUTION Refer and familiarize with the latest approved ROTAX manuals in or- der to have a continue check of approved fuels. This list is based on ROTAX SI-912-016R6 The maximum oil consumption is 0.016USGal/hr 0.06l/hr while the table of allowed lubricants is following reported. This oil consumption is always enough to perform a maximum endurance flight as the dif- ference between the maximum and minimum oil level, at maximum hourly consumption, will need 8.3 hours to be consumed. The oil tank capacity is 0.8US Gal (3.0lt) without the oil line, so with- out radiator, engine and hoses. 1-22 Ed.1 Rev.0 1-23 Ed.1 Rev.0 1.3.8. WARNING - CAUTION - NOTE The following definitions apply to warnings, cautions and notes used in this Pilot's Operating Handbook WARNING Means that the non-observation of the corresponding procedure leads to an immediate or important degradation of the flight safety CAUTION Means that the non-observation of the corresponding procedure leads to a minor or to a more or less long-term degradation of the flight safety NOTE Draws the attention to any special item not directly related to safety but which is important or unusual 2-1 Ed.1 Rev.0 2. Section No. 2 - Limitations 2.1. Airspeed Indicator The ASI (Air Speed Indicator) shows the airspeed in IAS (Indicated Air Speed). The correlation between the IAS and CAS (Calibrated Air Speed) is given in the Section 5 - Performances. Following the table of ASI markings is shown. Arc Color Lwr Limit IAS Upper Limit IAS Remarks White Vs0 = 32 VFE = 68 Flap Operating Range Green Vs1 = 35 VNO = 115 Normal Operating Range Yellow VNO = 115 VNE = 150 Caution Range* Red VNE = 150 Never Exceed Speed (red line) *Speeds above VNO and up to VNE can be reached and flown only in calm and smooth air. Flights into gusts conditions above VNO should be performed carefully. Maneuvering Speed (VA) is 97 KIAS 2-2 Ed.1 Rev.0 2.2. Stall Speeds The following table shows the stalling speeds at MTOW. The three flap position are shown in the table. Approach to stall is executed with engine idle and speed decrease 1kt/sec while the CoG is in its full fwd position. STALL SPEED TABLE Weight Bank Flaps 0° Flaps T/O Flaps LND [kg/lb] [deg] KIAS KCAS KIAS KCAS KIAS KCAS 599/1320 [FWD CoG] 0 35 44 34 43 32 38 15 36 46 35 44 32 39 30 39 49 38 46 35 41 45 45 54 44 51 40 46 60 58 64 55 61 50 54 2.3. Ceiling Maximum Service Ceiling is 15.500ft (residual rate of climb 100 ft/min). 2.4. Load Factors Clean configuration positive/negative load factors: +4 / -2 T/O and LND flap load factors: +2 / 0 2-3 Ed.1 Rev.0 2.5. Approved maneuvers This aircraft is intended for non-aerobatic and VFR operation only. Non-aerobatic operation includes:  Any maneuver pertaining to "normal" flight  Stalls (except whip stalls)  Lazy eights  Chandelles  Turns with maximum angle of bank of 60° WARNING Max entry speed for all these maneuvers is the VA WARNING Flight into expected and/or known icing conditions is prohibited IFR flight is prohibited Aerobatic flight is prohibited Intentional spins not allowed WARNING Limit load factor could be exceeded by moving the flight con- trols abruptly to full control deflection at a speed above VA (Maneuvering Speed) 2-4 Ed.1 Rev.0 2.6. Powerplant limitations This section refers to the 914 UL limitations and related markings. Re- fer to the dedicated POH if your aircraft is equipped with different en- gine (912 ULS or 912iS). 2.6.1. Power Output Max Power kW (hp) Max rpm. rpm prop.(engine) Time max. (min) Max. 84.5 (115) 2386 (5800) 5 Max cont. 73.5 (98.5) 2263 (5500) - 2-5 Ed.1 Rev.0 2.6.2. Temperature/Pressure limits Following, with reference to the current version of ROTAX 914 UL operator's manual, the table with the temperature and pressure limits. ITEM value value Remarks Max. coolant tempera- ture 120°C 248°F Max. CHT 135°C 275°F MIN oil temperature 50°C 120°F MAX oil temperature 130°C 266°F Normal oil temp. range 90-110°C 190-230°F MIN oil pressure 0.8bar 12psi Rpm < 3.500 Normal oil pressure range 2.0-5.0bar 29-73psi Rpm > 3.500 MAX oil pressure 7.0bar 102psi Short period at cold start MIN temperature at start -20°C -13°F Oil temp. MAX OAT at start 50°C 120°F On ground MAX OAT at start 60°C 140°F In flight MIN fuel pressure (Air- box Pressure + Value) Airbox Pressure + 0.15bar Airbox Pressure + 2.18psi 2-6 Ed.1 Rev.0 MAX fuel pressure (Air- box Pressure + Value) Airbox Pressure + 0.35bar Airbox Pressure + 5.08psi NORMAL fuel pressure (Airbox Pressure + Val- ue) Airbox Pressure + 0.25bar Airbox Pressure + 3.63psi MAX EGT 950°C 1742°F Acceleration max -0.5g max 5sec. NOTE Tecnam strongly recommend to be always updated concerning the lat- est manuals editions/revisions. The direct link to the ROTAX T-Publications page is: http://www.rotax-owner.com/en/support-topmenu/engine-manuals 2.7. Weights MTOW 1320 lb 599 kg Ramp Weight 1324 lb 601 kg Maximum allowed baggage weight 77 lb 35 kg 2-7 Ed.1 Rev.0 2.8. Center of Gravity FWD Limit 19% MAC 1.86mt [73.3in] All weights AFT Limit 32% MAC 2.04mt [80.3in] All weights Datum engine flange without spacer (See sect.6) or MAC leading edge (See sect.6) Level plane Baggage compartment floor (both planes) 2.9. Pilot's seat The PIC (Pilot In Command) can seat either on Left or Right seat as all flight controls can be easily reached. NOTE If two pilots are flying together, the PIC is the pilot seating on the Left NOTE The flight instructor seats on the Right 3-1 Ed.1 Rev.0 3. Section No. 3 - Emergency Procedures 3.1. Introduction This Section 3 includes checklists and procedures to be used in the event of emergencies. Emergencies caused by a malfunction of the aircraft or engine is extremely rare if appropriate maintenance and pre-flight inspections are carried out. In case of emergency, suggestions of the present section should be considered and applied as necessary to correct the problem. Before operating the aircraft, the pilot should be familiar with the pre- sent manual and so with the present section. Further, a continued and appropriate training program should be provided to be always able to manage simulated emergencies. In case of emergency the pilot should act as follows:  Keep control of the airplane  Analyze the situation  Apply the pertinent procedure  Inform the Air Traffic Control if time and conditions allow AIRSPEEDS FOR EMERGENCY SITUATIONS - KIAS Engine failure after takeoff (T/O flaps) 67 Knots Engine failure during flight 71 Knots Manoeuvring speed 97 Knots Maximum glide 71 Knots Standard safety equipment, even if not part of Minimum Equipment List, includes a Fire Extinguisher and Hammer. 3-2 Ed.1 Rev.0 3.2. Emergency frequencies and codes First radio ALERT MESSAGE to the FREQUENCY in use Radio EMERGENCY FREQ. = 121.50 Mhz Transponder CODE = 7700 NOTE If your aircraft is equipped with ELT, refer to the related POH Sup- plement in the Section 9 3-3 Ed.1 Rev.0 3.3. Emergency Checklists 3.3.1. Engine fire ON GROUND Throttle IDLE Fuel Pump OFF Fuel Valve OFF Cabin heat OFF Parking brake APPLY Master switch & key OFF Fire extinguisher IF POSSIBLE GRAB IT Emergency EXIT ESCAPE FROM THE A/C 3.3.2. Engine fire DURING TAKE OFF BEFORE ROTATION: ABORT TAKE OFF Throttle Lever IDLE Rudder Keep heading control Brakes As required With Aircraft Under Control Fuel Pump OFF Ignition Key OFF Fuel Selector OFF Cabin Heat OFF Master & Generator Switches OFF Parking Brake ENGAGED Fire extinguisher IF POSSIBLE GRAB IT Emergency EXIT ESCAPE FROM THE A/C 3-4 Ed.1 Rev.0 3.3.3. Engine fire IN FLIGHT Throttle IDLE Fuel Pump OFF Ignition Key OFF Cabin heat OFF Fuel Valve OFF Cabin vents OPEN communicate the emergency to the ATC Master & Generator Switches OFF Forced Landing APPLY CHECKLIST WARNING Do not attempt an in-flight engine restart 3.3.4. Cabin fire IN FLIGHT Cabin heat OFF Cabin vents OPEN communicate the emergency to the ATC Master switch & key OFF Fire extinguisher SPRAY TO THE FLAME BASE Forced Landing APPLY CHECKLIST WARNING If the MASTER SWITCH is set to OFF, consider that flaps extension and pitch trim operation would be not possible. 3-5 Ed.1 Rev.0 3.3.5. Cabin fire ON GROUND Generator Switch OFF Throttle Lever IDLE Ignition Key OFF Fuel Selector OFF Master Switch OFF Emergency EXIT ESCAPE FROM THE A/C 3.3.6. Engine failure DURING TAKE OFF Throttle IDLE Brakes APPLY Fuel Pump OFF when the aircraft is under control Fuel Valve OFF Master switch & key OFF Parking brake APPLY Emergency EXIT ESCAPE FROM THE A/C 3-6 Ed.1 Rev.0 3.3.7. Engine failure IMMEDIATELY AFTER TAKE OFF Airspeed 67 KIAS Throttle IDLE Fuel Pump OFF Fuel Valve OFF Flaps LANDING Landing area NO MORE OF ±45° (LEFT OR RIGHT AHEAD) Forced Landing APPLY CHECKLIST Just before touch down Canopy UNLATCH CENTRAL* 3.3.8. Engine failure IN FLIGHT (RESTART) Airspeed 71 KIAS Throttle ~75% Fuel Pump ON Fuel Valve CHANGE TANK Carb Heat ON Key START If the engine does not restart Forced Landing APPLY CHECKLIST 3-7 Ed.1 Rev.0 3.3.9. POWER-OFF Forced landing Airspeed 71 KIAS Throttle IDLE Fuel Pump OFF Fuel Valve OFF Safety Belts TIGHT CANOPY LATCHES UNLOCK LH & RH Once a safe landing area has been located Communication with ATC ESTABLISH Flaps AS NEEDED Touchdown Speed 41 KIAS Just immediately before touchdown CANOPY LATCHES UNLOCK CENTRAL* *The canopy has been designed in order to avoid hitting the passen- gers heads when opened. Before normal take-off, check if your and your passenger's heads are clear from the canopy track. 3-8 Ed.1 Rev.0 3.3.10. POWER-ON Forced landing Airspeed 71 KIAS Throttle AS NEEDED Safety Belts TIGHT CANOPY LATCHES UNLOCK LH & RH Once a safe landing area has been located Communication with ATC ESTABLISH Flaps AS NEEDED Touchdown Speed 41 KIAS Just immediately before touchdown CANOPY LATCHES UNLOCK CENTRAL* after touchdown Throttle IDLE Fuel Pump OFF Fuel Valve OFF Master swtich & key OFF 3-9 Ed.1 Rev.0 3.3.11. Engine OUT GLIDING Flaps RETRACTED Airspeed 71 KIAS Engine RESTART PERFORM Glide ratio is 11.5 therefore with 1000 ft of altitude, it is pos- sible to cover ~1.9 nautical miles in zero wind conditions 3.3.12. FLAT NLG TIRE landing Pre-landing checklist COMPLETE Once landed maintain aircraft NOSE HIGH attitude as long as possible 3.3.13. FLAT MLG TIRE landing Pre-landing checklist COMPLETE Align the a/c on the opposite side of runway in respect of the defective tire side to compensate for change in direction, which is to be expected during final rolling. Touchdown with the GOOD TIRE FIRST and hold aircraft with the flat tire off the ground as long as possible unless crosswind component does not avoid this 3-10 Ed.1 Rev.0 3.3.14. Loss of OIL PRESSURE - IN FLIGHT Throttle AS MIN. AS POSSIBLE Land as soon as practical NOTE Check oil system and register the event in the engine logbook indicat- ing duration and pressure reached. Carry out unscheduled mainte- nance check according to the ROTAX AMM. 3.3.15. Loss of OIL PRESSURE - ON GROUND Throttle IDLE Fuel Pump OFF Fuel Valve OFF Master switch & key OFF Parking Brake APPLY NOTE Check oil quantity in the tank, Check the oil quality. Register the event in the engine logbook indicating duration and pressure reached. Carry out unscheduled maintenance check according to the ROTAX AMM.