Pilot’s Operating Handbook

Rev. No.: - Date: 2011-10-24 1-6 PS-POH-1-1-12 SECTION 1 GENERAL INFORMATION PPSS--2288 C Crruuiisseerr NOTE Altitude losses shown in the table present max. values determined on the basis of flight tests using average piloting skill. 2.3 Flap extended speed range - VS0 to VFE Flaps operating range .......................................................31 - 75 KIAS 2.4 Manoeuvring speed - VA Manoeuvring speed at 600 kg ...........................................88 KIAS 2.5 Maximum structural cruising speed – VNO Maximum structural cruising speed ...................................108 KIAS 2.6 Never exceed speed - VNE Never exceed speed ..........................................................138 KIAS 2.7 Service ceiling Service ceiling ..................................................................15,090 ft 2.8 Load factors Maximum positive limit load factor ....................................+ 4 g Maximum negative limit load factor ...................................- 2 g Maximum positive limit load factor with flaps extended ........ + 2 g Maximum negative limit load factor with flaps extended..... 0 g 2.9 Approved manoeuvres The PPSS--2288 C Crruuiisseerr is approved for normal and below listed manoeuvres: • Steep turns not exceeding 60° bank • Lazy eights • Chandelles • Stalls (except whip stalls) Date: 2011-10-24 2-3 EASA approved Rev. No.: - PS-POH-1-1-12 SECTION 1 GENERAL INFORMATION PPSS--2288 C Crruuiisseerr 2.10 Operating weights and loading Max. takeoff weight ...........................................................600 kg Max landing weight ...........................................................600 kg Max. weight of fuel ............................................................82 kg Max. baggage weight in rear fuselage ...............................18 kg Max. baggage weight in each wing locker ..........................10 kg Maximum empty weight ....................................................405 kg NOTE Actual empty weight is shown in Section 9, Supplement No. 02 WARNING Do not exceed maximum takeoff weight 600 kg. Number of seats ...............................................................2 Minimum crew (only on the left seat) .................................1 pilot Minimum crew weight .......................................................55 kg Maximum crew weight on each seat ..................................115 kg Date: 2014-05-29 2-4 EASA approved Rev. No.: 2 PS-POH-1-1-12 SECTION 1 GENERAL INFORMATION PPSS--2288 C Crruuiisseerr 2.11 Fuel Fuel volume: Wing fuel tanks capacity ...................................................2x 57 L Total fuel capacity.............................................................114 L Unusable fuel ....................................................................2x 0.5 L Total usable fuel ...............................................................113 L Maximum allowable difference in fuel tanks.......................30 L Recommended fuel type: NOTE Refer to the ROTAX Operator’s Manual, section 2.4 Fuel, and Rotax Service Instruction SI-912-016 MOGAS European standards - min. RON 95, EN 228 Super, EN 228 Super plus US standard - ASTM D4814 Canadian standards - 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. Date: 2011-10-24 2-5 EASA approved Rev. No.: - PS-POH-1-1-12 SECTION 1 GENERAL INFORMATION PPSS--2288 C Crruuiisseerr 2.12 Engine operating speeds and limits Engine Model: ROTAX 912 ULS2 Engine Manufacturer: BRP-Powertrain GmbH Power Max. takeoff: 73.5 kW at 5,800 rpm (max. 5 min.) Max. continuous: 69 kW at 5,500 rpm Cruising (75%): 51 kW at 5,000 rpm Engine speed Max. takeoff: 5,800 rpm (max. 5 min.) Max. continuous: 5,500 rpm Cruising (75%): 5,000 rpm Idling: 1,400 rpm (minimum) Oil pressure Minimum: 0.8 bar below 3,500 rpm Maximum: 7 bar cold engine starting Normal: 2 - 5 bar above 3,500 rpm Oil temperature Minimum: 50 °C Maximum: 130 °C Normal: 90 - 110 °C Cylinder head temp. (CHT) Maximum: 135 °C Exhaust gas temp. (EGT) Nominal: 800 °C Maximum: 850 °C Max. takeoff: 880 °C Fuel press. Minimum: 0.15 bar Maximum: 0.4 bar 0.5 bar* Engine start, operating temperature Minimum: -25°C Maximum: 50 °C Limit of engine operation at zero gravity and in negative “g” condition Maximum: 5 seconds at max. -0.5 g * Applicable only for fuel pump from S/N 11.0036. Date: 2014-05-29 2-6 EASA approved Rev. No.: 2 PS-POH-1-1-12 SECTION 6 WEIGHT & BALANCE PPSS--2288 C Crruuiisseerr - Obtain measurement LN by measuring horizontally and parallel to the airplane center line, from center of nose wheel axle left sides, to the datum on the left wing. Repeat on right side and average the measurements. 5. Using weights from item 3 and measurements from item 4 the airplane weight and C.G. can be determined. 6. Basic Empty Weight may be determined by completing appropriate table. 6.3 Operating weights and loading Weights: Max. takeoff weight ...........................................................600 kg Max landing weight ...........................................................600 kg Max. weight of fuel ............................................................82 kg Max. baggage weight in rear fuselage ...............................18 kg Max. baggage weight in each wing locker ..........................10 kg Maximum empty weight ....................................................405 kg Crew: Number of seats ...............................................................2 Minimum crew (only on the left seat) ................................1 pilot Minimum crew weight .......................................................55 kg Maximum crew weight on each seat ..................................115 kg Arms: Pilot/Passenger.................................................................700 mm Baggage compartment ......................................................1,310 mm Wing lockers.....................................................................600 mm Fuel tanks .........................................................................180 mm NOTE Actual Empty weight is shown in Section 9, Supplement No. 02. NOTE For the needs of this Handbook the fuel specific weight of 0.72 kg / L was used to convert volume units into weight units. EASA approved Rev. No.: 2 Date: 2014-05-29 6-3 PS-POH-1-1-12 SECTION 6 WEIGHT & BALANCE PPSS--2288 C Crruuiisseerr 6.4 Weight and balance C.G. layout 6.5 C.G. range and determination 6.5.1 Aircraft C.G. range: Empty weight C.G. range .................................. 28.5 to 29.5 % of MAC 427.5 to 442.5 mm of MAC Operating C.G. range........................................ 28 to 35 % of MAC 420 to 525 mm of MAC EASA approved Rev. No.: - Date: 2011-10-24 6-4