PS-POH-1-1-01

Approved types of fuel ...................................see chapter 2.11 Engine power: Maximum power at 5,800 RPM......................98.6 [hp] (73.5 [kW]) Max. continuous power at 5,500 RPM ...........92.5 [hp] (69 [kW]) PS-POH-1-1-01 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] (37 - 86 [mph]) 2.4 Maneuvering speed - VA Maneuvering speed (IAS) at 1,320 [lb]: 88 [knot] (101 [mph]) Maneuvering speed (IAS) at 900 [lb]: 70 [knot] (80 [mph]) 2.5 Maximum structural cruising speed – VNO Maximum structural cruising speed (IAS): 108 [knot] (124 [mph]) 2.6 Never exceed speed - VNE Never exceed speed (IAS): 138 [knot] (158 [mph]) 2.7 Service ceiling Service ceiling ............................................................... 14,378 [ft] 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-1-1-01 SECTION 2 LIMITATIONS Date of issue: 10/03/31 Revision: - 2-4 2.10 Operating weights and loading Max. takeoff weight............................................. 1,320 [lb] (600 [kg]) Max landing weight ............................................. 1,320 [lb] (600 [kg]) Max. weight of fuel.............................................. 180 [lb] (82 [kg]) Max. baggage weight in rear fuselage ................ 40 [lb] (18 [kg]) Max. baggage weight in each wing locker .......... 44 [lb] (20 [kg]) Empty weight (minimum equipment)................... 760 [lb] (345 [kg]) NOTE Actual empty weight is shown in Section 9, Supplement No. 02 WARNING Do not exceed maximum takeoff weight 1,320 [lb] (600 [kg]) ! Number of seats ................................................. 2 Minimum crew .................................................... 1 pilot on the left seat Minimum crew weight ......................................... 95 [lb] (43 [kg]) Maximum crew weight on each seat ................... 253 [lb] (115 [kg]) PS-POH-1-1-01 SECTION 2 LIMITATIONS Date of issue: 10/11/22 Revision: 2 2-5 2.11 Fuel Fuel volume: Wing fuel tanks capacity ................................2x15.06 [US gal] (2x57 [liter]) Total fuel capacity..........................................30.12 [US gal] (114 [liter]) Unusable fuel.................................................2x0.13 [US gal] (2x0.5 [liter]) Total usable fuel ............................................29.85 [US gal] (113 [liter]) 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-1-1-01 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: 98.6 hp (73.5 kW) at 5,800 rpm (max. 5 min.) Max. Continuous: 92.5 hp (69 kW) at 5,500 rpm Power Cruising (75%): 68.4 hp (51 kW) 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: 12 psi (0.8 bar) below 3,500 rpm Maximum: 102 psi (7 bar) cold engine starting Oil pressure Optimum: 29 - 73 psi (2 - 5 bar) above 3,500 rpm Minimum: 122° F (50° C) Maximum: 266° F (130° C) Oil temperature Optimum: 194 - 230° F (90 - 110° C) Minimum: 122° F (50° C) Cylinder head temper. (CHT) Maximum: 275° F (135° C) * Nominal: 1,472° F (800° C) Maximum: 1,562° F (850° C) Exhaust gas temperature (EGT) Max. Takeoff: 1,616° F (880° C) Minimum: 2.2 psi (0.15 bar) Fuel press. Maximum: 5.8 psi (0.4 bar) * 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-1-1-01 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] - 0-1,400 1,400-5,500 5,500-5,800 5,800 Oil Pressure 12 psi (0.8 bar) 12-29 psi (0.8-2 bar) 29-73 psi (2-5 bar) 73-102 psi (5-7 bar) 102 psi (7 bar) Oil Temperature 122°F (50°C) 122-194°F (50-90°C) 194-230°F (90-110°C) 230-266°F (110-130°C) 266°F (130°C) Cylinder head Temperature (CHT) - - 122-275°F (50-135°C) - 275°F (135°C) Exhaust Gas Temp. (EGT) - 752-932°F (400-500°C) 932-1,562°F (500-850°C) 1,562-1,616°F (850-880°C) 1,616°F (880°C) Fuel Pressure 2.2 psi (0.15 bar) - 2.2-5.8 psi (0.15-0.4 bar) - 5.8 psi (0.4 bar) 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-1-1-01 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 1,350 LBS (612 KG) AND MAX. VELOCITY 120 KNOTS ! WARNING MINIMUM 1.58 US GAL (6 LITRES) 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 32°F (0°C) or lower. PS-POH-1-1-01 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 29 [psi] ( 2 [bar]) 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 122 [°F] (50 [°C]). 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-1-1-01 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]. 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] (37 [mph]) 8. Airplane lift-off - 42 [knot] (48 [mph]) 9. Climb - after reaching airspeed 65 [knot] (75 [mph]) 10. Wing flaps - retract at safe altitude (max. airspeed for flaps using is 75 [knot], 86 [mph]) PS-POH-1-1-01 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] (64 [mph]) - Vy = 62 [knot] (71 [mph]) 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] (64 [mph]) 4.7 Best rate of climb speed (Vy ): 62 [knot] (71 [mph]) 4.8 Cruise Refer to Section 5, for recommended cruising figures 4.9 Descend 1. Optimum glide speed - 60 [knot] (70 [mph]) PS-POH-1-1-01 SECTION 4 NORMAL PROCEDURES Date of issue: 10/03/31 Revision: - 4-8 4.10 Approach 1. Approach speed - 60 [knot] (70 [mph]) 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] (70-86 [mph]) 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] (70 [mph]) 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-1-1-01 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] (75 [mph]) 3. Trim - adjust as necessary 4. Wing flaps - retract at safe altitude (max. airspeed for flaps using is 75 [knot], 86 [mph]) 5. Trim - adjust as necessary 6. Repeat circle pattern PS-POH-1-1-01 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-1-1-01 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-1-1-01 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 (1,320 [lb] / 600 [kg] ) and under ISA conditions. The performance shown in this section is valid for aircraft equipped with ROTAX 912 ULS engine with maximum power 98.6 [hp] (73.5 [kW]) 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-1-1-01 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 obstacle RUNWAY SURFACE ft ft CONCRETE 463 1,270 GRASS 702 1,499 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 obstacle Landing run distance (braked) RUNWAY SURFACE ft ft CONCRETE 1,188 479 GRASS 1,109 364 5.3 Rate of climb Conditions: Engine: full throttle Flaps: 0° Best rate of climb speed Vy (IAS) Rate of climb Vz Altitude knot mph fpm 0 ft 62 71 825 3000 ft 62 71 685 6000 ft 62 71 540 9000 ft 62 71 355 PS-POH-1-1-01 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 mph knot mph knot mph in Hg US gal/h 4,200 72 83 72 83 73 84 23.7 3.59 4,500 81 93 80 92 81 93 24.6 4.15 4,800 91 105 89 102 89 102 25.5 4.76 5,000 96 110 94 108 95 109 26.1 5.15 5,300 105 121 102 117 103 118 27.0 5.79 5,500 112 129 108 124 109 125 27.7 6.26 1,000 5,700 118 136 113 130 114 131 28.3 6.82 4,200 68 78 69 79 72 83 22.2 3.49 4,500 78 90 77 89 80 92 23.0 4.04 4,800 86 99 85 98 88 101 23.8 4.62 5,000 93 107 91 105 94 108 24.3 5.02 5,300 102 117 99 114 102 117 25.1 5.65 3,000 5,500 108 124 104 120 108 124 25.5 6.16 4,200 65 75 66 76 71 82 20.5 3.41 4,500 74 85 74 85 79 91 21.3 3.94 4,800 83 95 82 94 87 100 22.1 4.54 5,000 89 102 87 100 93 107 22.7 4.94 5,300 97 112 95 109 101 116 23.5 5.57 5,000 5,500 103 118 100 115 107 123 24.1 6.02 4,200 62 71 63 72 69 79 19.3 3.30 4,500 69 79 70 81 77 89 20.0 3.86 4,800 79 91 78 90 85 98 20.6 4.44 5,000 84 97 83 95 91 105 21.2 4.86 5,300 92 106 90 104 99 114 22.0 5.49 7,000 5,500 98 113 95 109 105 121 22.5 5.89 4,200 57 66 59 68 67 77 18.4 3.22 4,500 64 74 65 75 74 85 19.0 3.78 4,800 73 84 73 84 83 95 19.6 4.33 5,000 79 91 78 90 89 102 20.0 4.76 5,300 86 99 85 98 97 112 20.5 5.39 9,000 5,500 92 106 90 104 103 118 20.8 5.76 PS-POH-1-1-01 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 US gal/h 3.59 4.15 4.76 5.15 5.79 6.26 Fuel consumption l/h 13.6 15.7 18.0 19.5 21.9 23.7 knot 72 81 91 96 105 112 IAS mph 83 93 105 110 121 129 knot 72 80 89 94 102 108 CAS mph 83 92 102 108 117 124 knot 73 81 89 95 103 109 Airspeed TAS mph 84 93 102 109 118 125 Endurance and Range at 29.85 US gal (113 liters) Endurance hh:mm 8:18 7:11 6:16 5:47 5:09 4:46 NM 607 583 558 551 531 520 Range SM 698 670 642 633 611 598 Endurance and Range at 23.78US gal (90 liters) Endurance hh:mm 6:37 5:43 4:59 4:36 4:06 3:47 NM 483 464 445 439 423 414 Range SM 556 534 511 504 486 476 Endurance and Range at 15.85 US gal (60 liters) Endurance hh:mm 4:24 3:49 3:19 3:04 2:44 2:31 NM 322 309 296 292 282 276 Range SM 371 356 341 336 324 317 Endurance and Range at 7.93US gal (30 liters) Endurance hh:mm 2:12 1:54 1:39 1:32 1:22 1:15 NM 161 155 148 146 141 138 Range SM 185 178 170 168 162 159 Endurance and Range at 3.96 US gal (15 liters) Endurance hh:mm 1:06 0:57 0:49 0:46 0:41 0:37 NM 81 77 74 73 70 69 Range SM 93 89 85 84 81 79 PS-POH-1-1-01 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 US gal/h 3.49 4.04 4.62 5.02 5.65 6.16 Fuel consumption l/h 13.2 15.3 17.5 19.0 21.4 23.3 knot 68 78 86 93 102 108 IAS mph 78 90 99 107 117 124 knot 69 77 85 91 99 104 CAS mph 79 89 98 105 114 120 knot 72 80 89 95 103 109 Airspeed TAS mph 83 92 101 108 117 124 Endurance and Range at 29.85 US gal (113 liters) Endurance hh:mm 8:33 7:23 6:27 5:56 5:17 4:50 NM 616 591 569 559 539 523 Range SM 708 680 654 643 620 602 Endurance and Range at 23.78 US gal (90 liters) Endurance hh:mm 6:48 5:53 5:08 4:44 4:12 3:51 NM 490 471 453 445 429 417 Range SM 564 541 521 512 494 479 Endurance and Range at 15.85 US gal (60 liters) Endurance hh:mm 4:32 3:55 3:25 3:09 2:48 2:34 NM 327 314 302 297 286 278 Range SM 376 361 347 341 329 320 Endurance and Range at 7.93 US gal (30 liters) Endurance hh:mm 2:16 1:57 1:42 1:34 1:24 1:17 NM 163 157 151 148 143 139 Range SM 188 180 174 171 165 160 Endurance and Range at 3.96 US gal (15 liters) Endurance hh:mm 1:08 0:58 0:51 0:47 0:42 0:38 NM 82 78 75 74 72 69 Range SM 94 90 87 85 82 80 PS-POH-1-1-01 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 US gal/h 3.41 3.94 4.54 4.94 5.57 6.02 Fuel consumption l/h 12.9 14.9 17.2 18.7 21.1 22.8 knot 65 74 83 89 97 103 IAS mph 75 85 95 102 112 118 knot 66 74 82 87 95 100 CAS mph 76 85 94 100 109 115 knot 71 79 87 93 101 107 Airspeed TAS mph 82 91 100 107 116 123 Endurance and Range at 29.85 US gal (113 liters) Endurance hh:mm 8:45 7:34 6:34 6:02 5:21 4:57 NM 622 599 572 562 541 531 Range SM 715 688 658 646 622 610 Endurance and Range at 23.78 US gal (90 liters) Endurance hh:mm 6:58 6:02 5:14 4:48 4:16 3:56 NM 495 477 456 448 431 423 Range SM 569 548 524 515 496 486 Endurance and Range at 15.85 US gal (60 liters) Endurance hh:mm 4:38 4:01 3:29 3:12 2:50 2:37 NM 330 318 304 298 287 282 Range SM 380 365 349 343 331 324 Endurance and Range at 7.93 US gal (30 liters) Endurance hh:mm 2:19 2:00 1:44 1:36 1:25 1:18 NM 165 159 152 149 144 141 Range SM 190 183 175 172 165 162 Endurance and Range at 3.96 US gal (15 liters) Endurance hh:mm 1:09 1:00 0:52 0:48 0:42 0:39 NM 83 79 76 75 72 70 Range SM 95 91 87 86 83 81 PS-POH-1-1-01 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 US gal/h 3.30 3.86 4.44 4.86 5.49 5.89 Fuel consumption l/h 12.5 14.6 16.8 18.4 20.8 22.3 knot 62 69 79 84 92 98 IAS mph 71 79 91 97 106 113 knot 63 70 78 83 90 95 CAS mph 72 81 90 95 104 109 knot 69 77 85 91 99 105 Airspeed TAS mph 79 89 98 105 114 121 Endurance and Range at 29.85 US gal (113 liters) Endurance hh:mm 9:02 7:44 6:43 6:08 5:26 5:04 NM 624 595 571 559 538 532 Range SM 718 685 657 643 619 612 Endurance and Range at 23.78 US gal (90 liters) Endurance hh:mm 7:12 6:09 5:21 4:53 4:19 4:02 NM 497 474 455 445 429 424 Range SM 572 545 523 512 493 487 Endurance and Range at 15.85 US gal (60 liters) Endurance hh:mm 4:48 4:06 3:34 3:15 2:53 2:41 NM 331 316 303 297 286 283 Range SM 381 364 349 341 329 325 Endurance and Range at 7.93 US gal (30 liters) Endurance hh:mm 2:24 2:03 1:47 1:37 1:26 1:20 NM 166 158 152 148 143 141 Range SM 191 182 174 171 164 162 Endurance and Range at 3.96 US gal (15 liters) Endurance hh:mm 1:12 1:01 0:53 0:48 0:43 0:40 NM 83 79 76 74 71 71 Range SM 95 91 87 85 82 81 PS-POH-1-1-01 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 US gal/h 3.22 3.78 4.33 4.76 5.39 5.76 Fuel consumption l/h 12.2 14.3 16.4 18.0 20.4 21.8 knot 57 64 73 79 86 92 IAS mph 66 74 84 91 99 106 knot 59 65 73 78 85 90 CAS mph 68 75 84 90 98 104 knot 67 74 83 89 97 103 Airspeed TAS mph 77 85 95 102 112 118 Endurance and Range at 29.85 US gal (113 liters) Endurance hh:mm 9:16 7:53 6:53 6:16 5:32 5:10 NM 621 584 572 558 537 534 Range SM 714 672 658 642 618 614 Endurance and Range at 23.78 US gal (90 liters) Endurance hh:mm 7:23 6:17 5:29 4:59 4:24 4:07 NM 495 465 456 445 428 425 Range SM 569 535 524 511 492 489 Endurance and Range at 15.85 US gal (60 liters) Endurance hh:mm 4:55 4:11 3:39 3:19 2:56 2:45 NM 330 310 304 296 285 283 Range SM 379 357 349 341 328 326 Endurance and Range at 7.93 US gal (30 liters) Endurance hh:mm 2:27 2:05 1:49 1:39 1:28 1:22 NM 165 155 152 148 143 142 Range SM 190 178 175 170 164 163 Endurance and Range at 3.96 US gal (15 liters) Endurance hh:mm 1:13 1:02 0:54 0:49 0:44 0:41 NM 82 78 76 74 71 71 Range SM 95 89 87 85 82 81 PS-POH-1-1-01 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 mph 35 41 40 45 45 49 50 54 55 58 60 63 65 67 70 72 75 76 80 81 85 85 90 89 95 94 100 98 105 103 110 107 115 112 120 116 125 121 130 125 135 130 140 134 145 139 150 143 155 148 160 152 PS-POH-1-1-01 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] Max. demonstrated crosswind velocity for take-off and landing: 12 [knot] 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-1-1-01 SECTION 5 PERFORMANCE Revision: 2 Date of issue: 10/11/22 5-12 Intentionally left blank PS-POH-1-1-01 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-1-1-01 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..................................2x15.06 [US gal] (2x57 [liter]) Unusable fuel quantity ...................................2x0.13 [US gal] (2x0.5 [liter]) 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 ........................................................0.87 [US gal] (3.3 [liter]) Maximum .......................................................1.0 [US gal] (3.8 [liter])