POH SportCruiser

Maximum power at 5,800 RPM......................73.5 [kW] (98.6 [hp[) Max. continuous power at 5,500 RPM ...........69 [kW] (92.5 [hp[) PS-POH-1-1-02 SECTION 2 LIMITATIONS Date of issue: 10/11/22 Revision: 2 2-3 2.3 Flap extended speed range - VS0 to VFE Flap operating range (IAS): 32 - 75 [knot] (59 - 139 [km/h]) 2.4 Maneuvering speed - VA Maneuvering speed (IAS) at 600 [kg] (1,320 [lb]): 88 [knot] (163 [km/h]) Maneuvering speed (IAS) at 408 [kg] (900 [lb]): 70 [knot] (130 [km/h]) 2.5 Maximum structural cruising speed – VNO Maximum structural cruising speed (IAS): 108 [knot] (200 [km/h]) 2.6 Never exceed speed - VNE Never exceed speed (IAS): 138 [knot] (255 [km/h]) 2.7 Service ceiling Service ceiling ...............................................14,378 [ft] (4,382 [m]) 2.8 Load factors Maximum positive limit load factor ................................. + 4 g Maximum negative limit load factor................................ - 2 g 2.9 Approved maneuvers The PPiippeerrSSppoorrtt is approved for normal and below listed maneuvers: • Steep turns not exceeding 60° bank • Lazy eights • Chandelles • Stalls (except whip stalls) PS-POH-1-1-02 SECTION 2 LIMITATIONS Date of issue: 10/03/31 Revision: - 2-4 2.10 Operating weights and loading Max. takeoff weight............................................. 600 [kg] (1,320 [lb]) Max landing weight ............................................. 600 [kg] (1,320 [lb]) Max. weight of fuel.............................................. 82 [kg] (180 [lb]) Max. baggage weight in rear fuselage ................ 18 [kg] (40 [lb]) Max. baggage weight in each wing locker .......... 20 [kg] (44 [lb]) Empty weight (minimum equipment)................... 345 [kg] (760 [lb]) NOTE Actual empty weight is shown in Section 9, Supplement No. 02 WARNING Do not exceed maximum takeoff weight 600 [kg] (1,320 [lb]) ! Number of seats ................................................. 2 Minimum crew .................................................... 1 pilot on the left seat Minimum crew weight ......................................... 43 [kg] (95 [lb]) Maximum crew weight on each seat ................... 115 [kg] (253 [lb]) PS-POH-1-1-02 SECTION 2 LIMITATIONS Date of issue: 10/11/22 Revision: 2 2-5 2.11 Fuel Fuel volume: Wing fuel tanks capacity ................................2x57 [liter] (2x15.06 [US gal]) Total fuel capacity..........................................114 [liter] (30.12 [US gal]) Unusable fuel.................................................2x0.5 [liter] (2x0.13 [US gal]) Total usable fuel ............................................113 [liter] (29.86 [US gal]) Recommended fuel type: (Refer to the ROTAX Operator’s manual section 10.2.2 Fuel, Rotax Service Instruction SI-912-016) MOGAS European standard - min. RON 95, EN 228 Super, EN 228 Super plus US standard - ASTM D4814 Canadian standard - min. AKI 91, CAN/CGSB-3.5 Quality 3 CAUTION Fuels that contain more than 5% ethanol blend have not been tested and are not permitted for use. AVGAS US standard - AVGAS 100 LL (ASTM D910) AVGAS 100 LL places greater stress on the valve seats due to its high lead content and forms increased deposits in the combustion chamber and lead sediments in the oil system. Thus it should only be used in case of problems with vapor lock or when other types of gasoline are unavailable. PS-POH-1-1-02 SECTION 2 LIMITATIONS Date of issue: 10/03/31 Revision: - 2-6 2.12 Engine operating speeds and limits Engine Model: ROTAX 912 ULS Engine Manufacturer: Bombardier-Rotax GMBH Max. Takeoff: 73.5 kW (98.6 hp) at 5,800 rpm (max. 5 min.) Max. Continuous: 69 kW (92.5 hp) at 5,500 rpm Power Cruising (75%): 51 kW (68.4 hp) at 5,000 rpm Max. Takeoff: 5,800 rpm (max. 5 min) Max. Continuous: 5,500 rpm Cruising (75%): 5,000 rpm Engine RPM Idling: 1,400 rpm (minimum) Minimum: 0.8 bar (12 psi) below 3,500 rpm Maximum: 7 bar (102 psi) cold engine starting Oil pressure Optimum: 2 - 5 bar (29 - 73 psi) above 3,500 rpm Minimum: 50° C (122° F) Maximum: 130° C (266° F) Oil temperature Optimum: 90 - 110° C (194 - 230° F) Minimum: 50° C (122° F) Cylinder head temper. (CHT) Maximum: 135° C (275° F) * Nominal: 800° C (1472° F) Maximum: 850° C (1562° F) Exhaust gas temperature (EGT) Max. Takeoff: 880° C (1616° F) Minimum: 0.15 bar (2.2 psi) Fuel press. Maximum: 0.4 bar (5.8 psi) * See the Rotax Operator’s manual section 10.1.2 Operating speeds and limits and section 10.2.1 Coolant, Rotax Installation manual section 12 Cooling system, Rotax Service Instruction SI-912-016, POH Section 8, paragraph 8.5.3 Coolant and Section 9, Supplement No. 02. Type of coolant used in engine. PS-POH-1-1-02 SECTION 2 LIMITATIONS Date of issue: 10/11/22 Revision: 2 2-7 2.13 Engine instruments markings Rotax 912ULS 73.5 [kW] (98.6 [hp]) Minimum Limit (red line) Caution Range (yellow arc) Normal Operating Range (green arc) Caution Range (yellow arc) Maximum Range (red line) Engine speed [RPM] - 0-1400 1400-5500 5500-5800 5800 Oil Pressure 0.8 bar (12 psi) 0.8-2 bar (12-29 psi) 2-5 bar (29-73 psi) 5-7 bar (73-102 psi) 7 bar (102 psi) Oil Temperature 50°C (122°F) 50-90°C (122-194°F) 90-110°C (194-230°F) 110-130°C (230-266°F) 130°C (266°F) Cylinder head Temperature (CHT) - - 50-135°C (122-275°F) - 135°C (275°F) Exhaust Gas Temp. (EGT) - 400-500°C (752-932°F) 500-850°C (932-1562°F) 850-880°C (1562-1616°F) 880°C (1616°F) Fuel Pressure 0.15 bar (2.2 psi) - 0.15-0.4 bar (2.2-5.8 psi) - 0.4 bar (5.8 psi) Manifold Pressure - - 10-29 inHg - 29 inHg 2.14 Other limitations • No smoking on board of the aircraft! • Approved for Day VFR flights only. • Flight in rain When flying in the rain, no additional steps are required. Aircraft qualities and performance are not substantially changed. However VMC must be maintained ! PS-POH-1-1-02 SECTION 2 LIMITATIONS Date of issue: 10/03/31 Revision: - 2-8 • Minimum instruments and equipment list for Day VFR flights: • Airspeed indicator • Altimeter • Compass (is not required by ASTM F 2245) • Fuel quantity indicator • Tachometer (RPM) • Engine instruments as required by the engine manufacturer : - Oil temperature indicator - Oil pressure indicator - Cylinder head temperature indicator • Safety harness for every used seat WARNING IFR FLIGHTS AND INTENTIONAL FLIGHTS UNDER ICING CONDITIONS ARE PROHIBITED! WARNING EMERGENCY PARACHUTE APPROVED FOR UP TO MTOW 612 KG (1,350 LBS) AND MAX. VELOCITY 120 KNOTS (222 KM/H)! WARNING MINIMUM 6 LITRES (1.58 US GAL) OF FUEL QUANTITY ALLOWS APPROXIMATELY 15 MINUTES OF SAFE OPERATION! CAUTION Install air intake shields in front of water and oil cooler, if ambient air temperature is 0°C (32°F) or lower. PS-POH-1-1-02 SECTION 4 NORMAL PROCEDURES Date of issue: 10/11/22 Revision: 2 4-5 CAUTION • The starter should be activated for a maximum of 10 [sec], followed by 2 [min] pause for starter cooling. • As soon as engine runs, adjust throttle to achieve smooth running at approx. 2,500 [rpm]. Check the oil pressure, which should increase within 10 [sec]. Increase the engine speed after the oil pressure has reached 2 [bar] ( 29 [psi]) and is steady. • To avoid shock loading, start the engine with the throttle lever set for idling or 10 % open at maximum, then wait 3 [sec] to reach constant engine speed before new acceleration. • Only one magneto should be switched ON (OFF) during ignition magneto check. 4.2.3 Engine warm up, Engine check Prior to engine check block the main wheels using chocks. Initially warm up the engine to 2,000 [rpm] for approximately 2 [min], then continue to 2,500 [rpm] till oil temperature reaches 50 [°C] (122 [°F]). The warm up period depends on ambient air temperature. Check both ignition circuits at 4,000 [rpm] for Rotax 912 ULS. The engine speed drop during the time either magneto switched OFF should not exceed 300 [rpm]. The max. engine speed drop difference between circuits L and R should be 115 [rpm]. NOTE Only one magneto should be switched ON (OFF) during ignition magneto check. Set max. power for verification of max. static engine speed (5,000 ±100 [rpm]) with given propeller and engine parameters (temperatures and pressures). Check acceleration from idling to max. power. If necessary, cool the engine at idle [rpm] before shutdown. CAUTION The engine check should be performed with the aircraft heading upwind and not on a loose terrain (the propeller may suck grit which can damage the leading edges of blades). PS-POH-1-1-02 SECTION 4 NORMAL PROCEDURES Date of issue: 10/11/22 Revision: 2 4-6 4.3 Taxiing Apply power and brakes as needed. Apply brakes to control movement on ground. Taxi carefully when wind velocity exceeds 20 [knot] (11 [m/s]). Hold the control stick in neutral position. 4.4 Normal Takeoff 4.4.1 Before takeoff 1. Altimeter - set 2. Trim - set neutral position 3. Control system - check free movement 4. Cockpit canopy - closed and locked Recommendation: - Before takeoff, manually check the canopy is locked by pushing the canopy upwards. 5. Safety harness - fastened 6. Fuel selector - turn ON (left or right fuel tank) 7. Ignition switch - switched ON (both magnetos) 8. Wing flaps - extend as necessary 4.4.2 Takeoff 1. Brakes - apply to stop wheel rotation 2. Throttle - fully forward 3. Engine speed - check (5,000 ±100 [rpm]) 4. Engine gauges - within limits 5. Brakes - release 6. Elevator - control stick pull 7. Nose wheel unstick - 32 [knot] (59 [km/h]) 8. Airplane lift-off - 42 [knot] (78 [km/h]) 9. Climb - after reaching airspeed 65 [knot] (120 [km/h]) 10. Wing flaps - retract at safe altitude (max. airspeed for flaps using is 75 [knot], 139 [km/h]) PS-POH-1-1-02 SECTION 4 NORMAL PROCEDURES Date of issue: 10/11/22 Revision: 2 4-7 WARNING Takeoff is prohibited if: • Engine is running unsteadily • Engine instrument values are beyond operational limits • Aircraft systems (e.g. brakes or controls) work incorrectly • Crosswind velocity exceeds permitted limits (see Section 5 Performance, 5.7 Demonstrated wind performance) 4.5 Climb 1. Throttle - fully forward (max. 5,800 [rpm] for max. 5 [min], max. continuous power (5,500 [rpm]) 2. Airspeed - Vx = 56 [knot] (104 [km/h]) - Vy = 62 [knot] (115 [km/h]) 3. Trim - trim the airplane 4. Engine gauges - oil temperature, oil pressure and CHT within limits CAUTION If the cylinder head temperature or oil temperature and/or coolant temperature approaches or exceeds limits, reduce the climb angle to increase airspeed and possibly return within limits. If readings do not improve, troubleshoot causes other than high power setting at low airspeed. 4.6 Best angle of climb speed (Vx ): 56 [knot] (104 [km/h]) 4.7 Best rate of climb speed (Vy ): 62 [knot] (115 [km/h]) 4.8 Cruise Refer to Section 5, for recommended cruising figures 4.9 Descend 1. Optimum glide speed - 60 [knot] (110 [km/h]) PS-POH-1-1-02 SECTION 4 NORMAL PROCEDURES Date of issue: 10/03/31 Revision: - 4-8 4.10 Approach 1. Approach speed - 60 [knot] (110 [km/h]) 2. Throttle - as necessary 3. Wing flaps - extend as necessary 4. Trim - as necessary 5. Safety harness - tighten CAUTION It is not advisable to reduce the engine throttle control lever to minimum on final approach and when descending from very high altitude. In such cases the engine becomes under-cooled and a loss of power may occur. Descent at increased idle (approximately 3,000 [rpm]), speed between 60-75 [knot] (110-139 [km/h]) and check that the engine instruments indicate values within permitted limits. 4.11 Normal landing 4.11.1 Before landing 1. Throttle - as necessary 2. Airspeed - 60 [knot] (110 [km/h]) 3. Wing flaps - extend as necessary 4. Trim - as necessary 4.11.2 Landing 1. Throttle - idle 2. Touch-down on main wheels 3. Apply brakes - as necessary (after the nose wheel touch-down) 4.11.3 After landing 1. Throttle - engine rpm set as required for taxiing 2. Wing flaps - retract 3. Trim - set neutral position PS-POH-1-1-02 SECTION 4 NORMAL PROCEDURES Revision: 2 Date of issue: 10/11/22 4-9 4.11.4 Engine shut down 1. Throttle - idle 2. Instruments - engine instruments within limits 3. Switches - switch OFF - except Instrument and Master 4. Ignition switch - turn key to switch OFF 5. Instrument switch - switch OFF 6. Master switch - switch OFF 7. Fuel Selector - close CAUTION Rapid engine cooling should be avoided during operation. This happens above all during aircraft descent, taxiing and low engine [rpm] or at engine shutdown immediately after landing. Under normal conditions the engine temperatures stabilize during descent, taxiing and at values suitable to stop engine by switching the ignition off. If necessary, cool the engine at idle [rpm] to stabilize the temperatures prior to engine shut down. 4.12 Short field takeoff and landing procedures None 4.13 Balked landing procedures 1. Throttle - fully forward (max. 5,800 [rpm] for max. 5 [min], max. continuous power (5,500 [rpm]) 2. Climb - after reaching 65 [knot] (120 [km/h] 3. Trim - adjust as necessary 4. Wing flaps - retract at safe altitude (max. airspeed for flaps using is 75 [knot], 139 [km/h]) 5. Trim - adjust as necessary 6. Repeat circle pattern PS-POH-1-1-02 SECTION 4 NORMAL PROCEDURES Revision: - Date of issue: 10/03/31 4-10 4.14 Aircraft parking and tie-down 1. Ignition switch - OFF 2. Master switch - OFF 3. Fuel selector - close 4. Parking brake - use it as necessary (if installed) 5. Canopy - close, lock as necessary 6. Secure the airplane NOTE It is recommended to use parking brake (if installed) for short-time parking only, between flights during a flight day. After ending the flight day or at low temperatures of ambient air, do not use parking brake, but use the wheel chocks instead. NOTE Use anchor eyes on the wings and fuselage rear section to fix the airplane. Move control stick forward and fix it together with the rudder pedals. Make sure that the cockpit canopy is properly closed and locked. The anchoring before leaving the airplane is important if the airplane is not equipped with a parking brake. PS-POH-1-1-02 SECTION 5 PERFORMANCE Revision: 2 Date of issue: 10/11/22 5-1 SECTION 5 TABLE OF CONTENTS 5. PERFORMANCE 5.1 Takeoff distances 5-3 5.2 Landing distances 5-3 5.3 Rate of climb 5-3 5.4 Cruise speeds 5-4 5.5 RPM setting and fuel consumption 5-5 5.6 Airspeed indicator system calibration 5-10 5.7 Demonstrated wind performance 5-11 PS-POH-1-1-02 SECTION 5 PERFORMANCE Revision: 2 Date of issue: 10/11/22 5-2 5. PERFORMANCE The presented data has been computed from actual flight tests with the aircraft and engine in good conditions and using average piloting techniques. If not stated otherwise, the performance stated in this section is valid for maximum take-off weight (600 [kg]/1,320 [lb] ) and under ISA conditions. The performance shown in this section is valid for aircraft equipped with ROTAX 912 ULS engine with maximum power 73.5 [kW] (98.6 [hp]) and WOODCOMP KLASSIC 170/3/R three composite blades ground adjustable propeller with pitch setting 17.5°. CAUTION Airspeeds values are valid for standard AVIATIK WA037383 pitot-static probe. PS-POH-1-1-02 SECTION 5 PERFORMANCE Revision: 2 Date of issue: 10/11/22 5-3 5.1 Takeoff distances Conditions: - Altitude: 0 ft ISA - Engine power: full throttle - Flaps: 15° Take-off run distance Take-off distance over 50 ft (15 m) obstacle RUNWAY SURFACE ft m ft m CONCRETE 463 141 1,270 387 GRASS 702 214 1,499 457 5.2 Landing distances Conditions: - Altitude: 0 ft ISA - Engine power: idle - Flaps: 30° - Brakes fully depressed immediately after touch-down Landing distance over 50 ft (15 m) obstacle Landing run distance (braked) RUNWAY SURFACE ft m ft m CONCRETE 1,188 362 479 146 GRASS 1,109 338 364 111 5.3 Rate of climb Conditions: Engine: full throttle Flaps: 0° Best rate of climb speed Vy (IAS) Rate of climb Vz Altitude knot km/h fpm m/s 0 ft 62 115 825 4.2 3000 ft 62 115 685 3.5 6000 ft 62 115 540 2.7 9000 ft 62 115 355 1.8 PS-POH-1-1-02 SECTION 5 PERFORMANCE Revision: 2 Date of issue: 10/11/22 5-4 5.4 Cruise speeds Altitude Engine speed IAS CAS TAS MAP Fuel consumption ft rpm knot km/h knot km/h knot km/h in Hg l/h US gal/h 4,200 72 133 72 133 73 135 23.7 13.6 3.59 4,500 81 150 80 148 81 150 24.6 15.7 4.15 4,800 91 169 89 165 89 165 25.5 18.0 4.76 5,000 96 178 94 174 95 176 26.1 19.5 5.15 5,300 105 194 102 189 103 191 27.0 21.9 5.79 5,500 112 207 108 200 109 202 27.7 23.7 6.26 1,000 5,700 118 219 113 209 114 211 28.3 25.8 6.82 4,200 68 126 69 128 72 133 22.2 13.2 3.49 4,500 78 144 77 143 80 148 23.0 15.3 4.04 4,800 86 159 85 157 88 163 23.8 17.5 4.62 5,000 93 172 91 169 94 174 24.3 19.0 5.02 5,300 102 189 99 183 102 189 25.1 21.4 5.65 3,000 5,500 108 200 104 193 108 200 25.5 23.3 6.16 4,200 65 120 66 122 71 131 20.5 12.9 3.41 4,500 74 137 74 137 79 146 21.3 14.9 3.94 4,800 83 154 82 152 87 161 22.1 17.2 4.54 5,000 89 165 87 161 93 172 22.7 18.7 4.94 5,300 97 180 95 176 101 187 23.5 21.1 5.57 5,000 5,500 103 191 100 185 107 198 24.1 22.8 6.02 4,200 62 115 63 117 69 128 19.3 12.5 3.30 4,500 69 128 70 130 77 143 20.0 14.6 3.86 4,800 79 146 78 144 85 157 20.6 16.8 4.44 5,000 84 156 83 154 91 169 21.2 18.4 4.86 5,300 92 170 90 167 99 183 22.0 20.8 5.49 7,000 5,500 98 181 95 176 105 194 22.5 22.3 5.89 4,200 57 106 59 109 67 124 18.4 12.2 3.22 4,500 64 119 65 120 74 137 19.0 14.3 3.86 4,800 73 135 73 135 83 154 19.6 16.4 4.33 5,000 79 146 78 144 89 165 20.0 18.0 4.76 5,300 86 159 85 157 97 180 20.5 20.4 5.39 9,000 5,500 92 170 90 167 103 191 20.8 21.8 5.76 PS-POH-1-1-02 SECTION 5 PERFORMANCE Revision: 2 Date of issue: 10/11/22 5-5 5.5 RPM setting and fuel consumption Altitude ft 1,000 Engine speed rpm 4,200 4,500 4,800 5,000 5,300 5,500 l/h 13.6 15.7 18.0 19.5 21.9 23.7 Fuel consumption US gal/h 3.59 4.15 4.76 5.15 5.79 6.26 knot 72 81 91 96 105 112 IAS km/h 133 150 169 178 194 207 knot 72 80 89 94 102 108 CAS km/h 133 148 165 174 189 200 knot 73 81 89 95 103 109 Airspeed TAS km/h 135 150 165 176 191 202 Endurance and Range at 113 liters (29.85 US gal) Endurance hh:mm 8:18 7:11 6:16 5:47 5:09 4:46 NM 607 583 559 551 531 520 Range km 1123 1080 1035 1020 984 962 Endurance and Range at 90 liters (23.77 US gal) Endurance hh:mm 6:37 5:43 5:00 4:36 4:06 3:47 NM 483 464 445 438 423 414 Range km 895 860 824 812 784 767 Endurance and Range at 60 liters (15.85 US gal) Endurance hh:mm 4:24 3:49 3:20 3:04 2:44 2:31 NM 322 310 297 292 282 276 Range km 596 573 549 541 523 511 Endurance and Range at 30 liters (7.92 US gal) Endurance hh:mm 2:12 1:54 1:40 1:32 1:22 1:15 NM 161 155 148 146 141 138 Range km 298 287 275 271 261 256 Endurance and Range at 15 liters (3.96 US gal) Endurance hh:mm 1:06 0:57 0:50 0:46 0:41 0:37 NM 81 77 74 73 71 69 Range km 149 143 137 135 131 128 PS-POH-1-1-02 SECTION 5 PERFORMANCE Revision: 2 Date of issue: 10/11/22 5-6 Altitude ft 3,000 Engine speed rpm 4,200 4,500 4,800 5,000 5,300 5,500 l/h 13.2 15.3 17.5 19.0 21.4 23.3 Fuel consumption US gal/h 3.49 4.04 4.62 5.02 5.65 6.16 knot 68 78 86 93 102 108 IAS km/h 126 144 159 172 189 200 knot 69 77 85 91 99 104 CAS km/h 128 143 157 169 183 193 knot 72 80 89 95 103 109 Airspeed TAS km/h 133 148 165 176 191 202 Endurance and Range at 113 liters (29.85 US gal) Endurance hh:mm 8:33 7:23 6:27 5:56 5:16 4:50 NM 616 591 568 559 539 524 Range km 1142 1094 1052 1035 997 970 Endurance and Range at 90 liters (23.77 US gal) Endurance hh:mm 6:49 5:52 5:08 4:44 4:12 3:51 NM 491 471 453 445 429 417 Range km 909 872 838 825 794 773 Endurance and Range at 60 liters (15.85 US gal) Endurance hh:mm 4:32 3:55 3:25 3:09 2:48 2:34 NM 327 314 302 297 286 278 Range km 606 581 559 550 530 515 Endurance and Range at 30 liters (7.92 US gal) Endurance hh:mm 2:16 1:57 1:42 1:34 1:24 1:17 NM 164 157 151 148 143 139 Range km 303 291 279 275 265 258 Endurance and Range at 15 liters (3.96 US gal) Endurance hh:mm 1:08 0:58 0:51 0:47 0:42 0:38 NM 82 78 75 74 71 70 Range km 152 145 140 137 132 129 PS-POH-1-1-02 SECTION 5 PERFORMANCE Revision: 2 Date of issue: 10/11/22 5-7 Altitude ft 5,000 Engine speed rpm 4,200 4,500 4,800 5,000 5,300 5,500 l/h 12.9 14.9 17.2 18.7 21.1 22.8 Fuel consumption US gal/h 3.41 3.94 4.54 4.94 5.57 6.02 knot 65 74 83 89 97 103 IAS km/h 120 137 154 165 180 191 knot 66 74 82 87 95 100 CAS km/h 122 137 152 161 176 185 knot 71 79 87 93 101 107 Airspeed TAS km/h 131 146 161 172 187 198 Endurance and Range at 113 liters (29.85 US gal) Endurance hh:mm 8:45 7:35 6:34 6:02 5:21 4:57 NM 622 599 572 562 541 530 Range km 1152 1110 1059 1041 1002 982 Endurance and Range at 90 liters (23.77 US gal) Endurance hh:mm 6:58 6:02 5:13 4:48 4:15 3:56 NM 495 477 455 448 431 422 Range km 917 884 843 829 798 782 Endurance and Range at 60 liters (15.85 US gal) Endurance hh:mm 4:39 4:01 3:29 3:12 2:50 2:37 NM 330 318 303 298 287 282 Range km 612 589 562 553 532 521 Endurance and Range at 30 liters (7.92 US gal) Endurance hh:mm 2:19 2:00 1:44 1:36 1:25 1:18 NM 165 159 152 149 144 141 Range km 306 295 281 276 266 261 Endurance and Range at 15 liters (3.96 US gal) Endurance hh:mm 1:09 1:00 0:52 0:48 0:42 0:39 NM 83 80 76 75 72 70 Range km 153 147 141 138 133 130 PS-POH-1-1-02 SECTION 5 PERFORMANCE Revision: 2 Date of issue: 10/11/22 5-8 Altitude ft 7,000 Engine speed rpm 4,200 4,500 4,800 5,000 5,300 5,500 l/h 12.5 14.6 16.8 18.4 20.8 22.3 Fuel consumption US gal/h 3.30 3.86 4.44 4.86 5.49 5.89 knot 62 69 79 84 92 98 IAS km/h 115 128 146 156 170 181 knot 63 70 78 83 90 95 CAS km/h 117 130 144 154 167 176 knot 69 77 85 91 99 105 Airspeed TAS km/h 128 143 157 169 183 194 Endurance and Range at 113 liters (29.85 US gal) Endurance hh:mm 9:02 7:44 6:43 6:08 5:25 5:04 NM 624 596 572 559 538 532 Range km 1155 1104 1059 1035 996 985 Endurance and Range at 90 liters (23.77 US gal) Endurance hh:mm 7:12 6:09 5:21 4:53 4:19 4:02 NM 497 475 455 445 428 424 Range km 920 879 843 824 793 785 Endurance and Range at 60 liters (15.85 US gal) Endurance hh:mm 4:48 4:06 3:34 3:15 2:53 2:41 NM 331 316 304 297 286 283 Range km 613 586 562 550 529 523 Endurance and Range at 30 liters (7.92 US gal) Endurance hh:mm 2:24 2:03 1:47 1:37 1:26 1:20 NM 166 158 152 148 143 141 Range km 307 293 281 275 264 262 Endurance and Range at 15 liters (3.96 US gal) Endurance hh:mm 1:12 1:01 0:53 0:48 0:43 0:40 NM 83 79 76 74 71 71 Range km 153 147 141 137 132 131 PS-POH-1-1-02 SECTION 5 PERFORMANCE Revision: 2 Date of issue: 10/11/22 5-9 Altitude ft 9,000 Engine speed rpm 4,200 4,500 4,800 5,000 5,300 5,500 l/h 12.2 14.3 16.4 18.0 20.4 21.8 Fuel consumption US gal/h 3.22 3.78 4.33 4.76 5.39 5.76 knot 57 64 73 79 86 92 IAS km/h 106 119 135 146 159 170 knot 59 65 73 78 85 90 CAS km/h 109 120 135 144 157 167 knot 67 74 83 89 97 103 Airspeed TAS km/h 124 137 154 165 180 191 Endurance and Range at 113 liters (29.85 US gal) Endurance hh:mm 9:15 7:54 6:53 6:16 5:32 5:11 NM 621 585 572 559 537 534 Range km 1149 1083 1059 1035 995 989 Endurance and Range at 90 liters (23.77 US gal) Endurance hh:mm 7:22 6:17 5:29 5:00 4:24 4:07 NM 494 466 455 445 428 425 Range km 915 863 844 824 793 788 Endurance and Range at 60 liters (15.85 US gal) Endurance hh:mm 4:55 4:11 3:39 3:20 2:56 2:45 NM 330 310 304 297 285 283 Range km 610 575 562 549 528 525 Endurance and Range at 30 liters (7.92 US gal) Endurance hh:mm 2:27 2:05 1:49 1:40 1:28 1:22 NM 165 155 152 148 143 142 Range km 305 288 281 275 264 263 Endurance and Range at 15 liters (3.96 US gal) Endurance hh:mm 1:13 1:02 0:54 0:50 0:44 0:41 NM 82 78 76 74 71 71 Range km 153 144 141 137 132 131 PS-POH-1-1-02 SECTION 5 PERFORMANCE Revision: 2 Date of issue: 10/11/22 5-10 5.6 Airspeed indicator system calibration IAS CAS knot 30 35 35 39 40 44 45 48 50 53 55 57 60 62 65 66 70 71 75 75 80 79 85 84 90 88 95 93 100 97 105 102 110 106 115 111 120 115 125 120 130 124 135 129 140 133 IAS CAS km/h 55 64 60 68 70 77 80 86 90 95 100 104 110 113 120 122 130 131 140 140 150 149 160 158 170 167 180 176 190 185 200 194 210 203 220 212 230 221 240 230 250 239 255 243 PS-POH-1-1-02 SECTION 5 PERFORMANCE Revision: 2 Date of issue: 10/11/22 5-11 5.7 Demonstrated wind performance Max. demonstrated headwind velocity for take-off and landing: 24 [knot] (13 [m/s]) Max. demonstrated crosswind velocity for take-off and landing: 12 [knot] (6,5 [m/s]) Wind components figure Example: 1. Wind velocity .......15 knots 3. Headwind component...... 8.6 knots 2. Wind direction......55° 4. Crosswind component ..... 12.3 knots PS-POH-1-1-02 SECTION 5 PERFORMANCE Revision: 2 Date of issue: 10/11/22 5-12 Intentionally left blank PS-POH-1-1-02 Revision: - Date of issue: 10/03/31 SECTION 8 HANDLING AND SERVICING 8-3 8.3 Towing instructions To handle the airplane on ground use the Tow Bar, or if pushing the airplane by hand, push on the aft fuselage, placing your hands over an area of skin supported by a bulkhead. CAUTION Avoid excessive pressure at the airplane airframe-especially at control surfaces. Keep all safety precautions, especially in the propeller area. 8.4 Tie-down instructions The airplane should be moored when parked outside a hangar after the flight day. The mooring is necessary to protect the airplane against possible damage caused by wind and gusts. For this reason the aircraft is equipped with mooring eyes located on the lower surfaces of the wings. Tie-down procedures: 1. Fuel Selector close, Master switch and other switches switched OFF, Ignition switch switched OFF 2. Fix the hand control using e.g. safety harness 3. Close air vent 4. Close and lock canopy 5. Moor the aircraft to the ground by means of a mooring rope passed through the mooring eyes located on the lower surfaces of the wings and below rear fuselage. NOTE In the case of long term parking, especially during winter, it is recommended to cover the cockpit canopy or possibly the whole aircraft by means of a suitable tarpaulin attached to the airframe. 8.5 Servicing operating fluids See appropriate chapters in the ROTAX engine Maintenance and Operator’s manuals and PPiippeerrSSppoorrtt aircraft Maintenance manual for more instructions. PS-POH-1-1-02 Revision: 2 Date of issue: 10/11/22 SECTION 8 HANDLING AND SERVICING 8-4 8.5.1 Approved fuel grades and specifications Recommended fuel type: (refer to the ROTAX Operator’s manual section 10.2.2 Fuel, Rotax Service Instruction SI-912-016) MOGAS European standard - min. RON 95, EN 228 Super, EN 228 Super plus US standard - ASTM D4814 Canadian standard - min. AKI 91, CAN/CGSB-3.5 Quality 3 CAUTION Fuels that contain more than 5% ethanol blend have not been tested and are not permitted for use. AVGAS US standard - AVGAS 100 LL (ASTM D910) AVGAS 100 LL places greater stress on the valve seats due to its high lead content and forms increased deposits in the combustion chamber and lead sediments in the oil system. Thus it should only be used in case of problems with vapor lock or when other types of gasoline are unavailable. Fuel volume: Wing fuel tanks volume..................................2x57 [liter] (2x15.06 [US gal]) Unusable fuel quantity ...................................2x0.5 [liter] (2x0.13 [US gal]) 8.5.2 Approved oil grades and specifications Recommended oil type: (refer to the Rotax Operator’s manual section 10.2.3 Lubricants, Rotax Service Instruction SI-912-016) Motorcycle 4-stroke engine oil of registered brand with gear additives. Use only oil with API ”SG“ classification or higher! Use multi-grade oil. Use of mineral oil is not recommended. Type of oil used by aircrafts manufacturer: - see Section 9, Supplement No. 02 Oil volume: Minimum ........................................................3.3 [liter] (0.87 [US gal]) Maximum .......................................................3.8 [liter] (1.0 [US gal])