PILOT'S OPERATING HANDBOOK

Table of Contents ............................................................................................... 10 1. Operating Limits ..................................................................................... 13 1.1 Air Speeds ........................................................................................... 13 1.2 Weights ................................................................................................ 13 1.3 Structural Limitations ........................................................................ 14 1.4 Center of Gravity Limits ..................................................................... 14 1.5 Air Speed Markings ............................................................................ 14 1.6 Engine RPM Limitations .................................................................... 15 1.7 RPM Gauge Markings ......................................................................... 15 1.8 Flap Settings ....................................................................................... 15 1.9 Maximal Speed for Flap Settings ...................................................... 15 1.10 Propellers for BRP ROTAX 912 UL ............................................... 16 1.11 Hélices pour BRP ROTAX 912 ULS............................................... 17 1.12 Noise Table for BRP ROTAX 912 UL and 912 ULS ...................... 18 1.12.1 ROTAX 912 UL ............................................................................ 18 1.12.2 ROTAX 912 ULS .......................................................................... 18 1.13 Engine Limitations ......................................................................... 19 2. Restrictions ............................................................................................. 20 3. Note to Engine Operation ...................................................................... 20 4. Flight Operations .................................................................................... 22 4.1 Taxiing ................................................................................................. 22 4.2 Take-off and Climb ............................................................................. 22 4.3 Cruise .................................................................................................. 24 4.4 Turn in Flight ....................................................................................... 25 4.5 Stall ...................................................................................................... 25 4.6 Approach and Landing ...................................................................... 26 4.7 Shutting Down the Engine ................................................................. 26 4.8 Sudden Loss of Engine Power .......................................................... 27 4.8.1 Loss of Engine Power During Take-off .................................... 27 4.8.2 Loss of Engine Power in Cruise Flight ..................................... 27 4.8.3 Start the Engine in Flight ........................................................... 28 Pilot Operating Handbook for the C42 Series POH C42 SERIES ISSUE1 (B) REV7 25/04/2020 Page 11 of 73 4.9 Equipped with Optional Cowl Flap ................................................... 29 4.10 Emergency Procedures ................................................................. 30 4.10.1 Stalling due to Low Speed ......................................................... 30 4.10.2 Sideslip ........................................................................................ 30 4.10.3 Spin .............................................................................................. 30 4.10.4 Spiral Dive ................................................................................... 30 4.10.5 Loss of Elevator Control ............................................................ 30 4.10.6 Loss of Aileron Control .............................................................. 31 4.10.7 Loss of Rudder Control ............................................................. 31 4.10.8 Carburetor Fire ........................................................................... 31 4.11 Parachute Deployment ................................................................... 32 5. Handling on Ground ............................................................................... 33 5.1 Maneuver ............................................................................................. 33 5.2 Suspension ......................................................................................... 33 5.3 Parking ................................................................................................ 34 5.4 Tie-Down ............................................................................................. 34 6. Minimum Equipment List ....................................................................... 36 7. Dimensions ............................................................................................. 36 8. Weight and Balance ............................................................................... 37 8.1 Empty Weight and Center of Gravity ................................................ 38 9. Data Placard and Check-List ................................................................. 40 10. Before Take-off Checklist ...................................................................... 41 11. Approved Equipement ........................................................................... 42 12. Flight Performance ................................................................................. 44 12.1 Take-off Distance ............................................................................ 44 12.2 Climb Rate ....................................................................................... 44 12.3 Cruise Speed (Single Seated) ........................................................ 45 12.4 Performance with Engine Shut Down (Single Seated) ................ 45 13. Attaching Wings ..................................................................................... 46 13.1 Attaching Wings to the Fuselage .................................................. 46 13.2 Folding Wings for Hangaring ........................................................ 48 14. Pre-Flight Inspection .............................................................................. 49 14.1 Engine .............................................................................................. 49 14.2 Main Landing Gear ......................................................................... 49 14.3 Left Wing ......................................................................................... 50 14.4 Left Side of the Fuselage ............................................................... 50 Pilot Operating Handbook for the C42 Series POH C42 SERIES ISSUE1 (B) REV7 25/04/2020 Page 12 of 73 14.5 Empennage ..................................................................................... 50 14.6 Right Side of the Fuselage ............................................................ 51 14.7 Right Wing ....................................................................................... 51 14.8 Inside and Outside of the Cabin .................................................... 51 14.9 Instruments ..................................................................................... 51 14.10 Drainage .......................................................................................... 51 15. Care and Maintenance ........................................................................... 52 16. Parameter ................................................................................................ 54 17. Particularity with the Option Handicapped Equipment ...................... 58 17.1 Equipment ....................................................................................... 58 17.2 Assembling and Disassembling ................................................... 58 17.3 Operation ......................................................................................... 59 18. Flying the C42 Series without Doors .................................................... 60 19. Instructions for using of LiFe Battery .................................................. 60 20. COMCO IKARUS Manufacturer Warranty ............................................. 62 20.1 Warranty Information ..................................................................... 62 20.2 Warranty Service (After Sale) ........................................................ 62 20.3 Claim ................................................................................................ 63 20.4 Requirements for a Warranty ........................................................ 64 20.5 Warranty Exclusion ........................................................................ 65 21. Appendix ................................................................................................. 66 21.1 Placards ........................................................................................... 66 21.2 Data Placard .................................................................................... 67 21.3 Service Problem Report Form – Aircraft ...................................... 68 21.4 Inspections Performed................................................................... 69 21.5 Location of the Parachute Rescue System .................................. 70 21.6 Wiring Diagram ............................................................................... 73 Pilot Operating Handbook for the C42 Series POH C42 SERIES ISSUE1 (B) REV7 25/04/2020 Page 13 of 73 1. Operating Limits 1.1 Air Speeds Speed to never-exceed: C42 (C42A) VNE = 180 km/h (97 kts) C42B & C42C VNE = 216 km/h (116 kts) C42CS VNE = 225 km/h (121 kts) Speed in turbulent air: C42 (C42A), C42B & C42C VB = 180 km/h (97 kts) C42CS VB = 187 km/h (100 kts) Maximum maneuver speed: VA = 148 km/h (80 kts) Speed with landing flaps set: until 2009 : Vfe = 105 km/h (56 kts) since 2010 : Vfe = 117 km/h (63 kts) Stall speed: flap position I : VS = 75 km/h (40 kts) flap position II : VS1 = 70 km/h (38 kts) flap position III : VS0 = 65 km/h (35 kts) If VA speed is exceeded, only little rudder movement are allowed. 1.2 Weights Maximum take-off mass: 450,0 kg (992 lb) Maximum take-off mass, with installed rescue system: 472,5 kg (1041 lb) Empty weight: see last weighting report Payload: see last weighting report min. 65 kg (144 lb) Pilot Operating Handbook for the C42 Series POH C42 SERIES ISSUE1 (B) REV7 25/04/2020 Page 14 of 73 1.3 Structural Limitations Maximal admissible positive load factor: + 4 g Maximal admissible negative load factor: - 2 g 1.4 Center of Gravity Limits Reference datum (PB) : Wing leading edge at a rib station Forward center of gravity: 300 mm after PB (11.8 in) Rearward center of gravity: 560 mm after PB (22.0 in) 1.5 Air Speed Markings White arc: until 2009: 71 - 105 km/h (38 - 57 kts) since 2010: 71 - 117 km/h (38 - 63 kts) Green arc: C42 (C42A), B & C 79 - 180 km/h (43 - 97 kts) C42CS 79 - 187 km/h (43 - 100 kts) Yellow arc: C42 (C42A), B & C 180 - 216 km/h (97 – 116 kts) C42CS 180 - 225 km/h (97 – 121 kts) Yellow triangle: VX = 100 km/h (54 kts) Yellow line: VA =148 km/h (75 kts) Red line: C42 (C42A) VNE =180 km/h (97 kts) C42B & C42C VNE = 216 km/h (116 kts) C42CS VNE = 225 km/h (121 kts) ATTENTION : C42 - No yellow arc ! -> VB = VNE The deviation curve for the airspeed indicator can be interpolated from the following table. IAS km/h 60 70 80 90 100 110 120 130 140 150 160 170 180 190 200 EAS km/h 65 74 83 91 100 109 117 125 134 142 151 160 168 177 185 Pilot Operating Handbook for the C42 Series POH C42 SERIES ISSUE1 (B) REV7 25/04/2020 Page 15 of 73 1.6 Engine RPM Limitations Maximum engine RPM: n = 5800 trs/min, for 5 min. max Maximum continuous RPM: n = 5500 trs/min 1.7 RPM Gauge Markings Yellow arc: n = 5500 - 5800 rpm Red line: n = 5800 rpm 1.8 Flap Settings Position I: cruising Position II: take-off / landing Position III: landing 1.9 Maximal Speed for Flap Settings Position I: VNE (see 1.5) Position II: max. 135 km/h (73 kts) Position III: max. 120 km/h (65 kts) Pilot Operating Handbook for the C42 Series POH C42 SERIES ISSUE1 (B) REV7 25/04/2020 Page 16 of 73 1.10 Propellers for BRP ROTAX 912 UL With propeller WARP DRIVE 2-blade 68” (1.72 m Ø) constant speed, Pitch 23.5° à 400 mm from hub, Full throttle RPM on ground max. 5200 1/min Propeller RPM approx. n = 2300 1/min With propeller WARP DRIVE 3-blade 68” (1.72 m Ø) Pitch 21.0° à 400 mm from hub, Full throttle RPM on ground max. 5200 1/min Propeller RPM approx. n = 2300 1/min With propeller Sport-Prop 3-blade 68” (1.72 m Ø) Pitch 19.5° à 400 mm from hub, Full throttle RPM on ground max. 4900 1/min Propeller RPM approx. n = 2150 1/min With propeller GSC 3-blade 68” (1,72 m Ø) Pitch 21.0° à 400 mm from hub, Full throttle RPM on ground max. 4900 1/min Propeller RPM approx. n = 2150 1/min With propeller Neuform CR2-75 2-blade 69” (1,75 m Ø) Pitch 27.0° à r = 365mm from hub, Full throttle RPM on ground max. 5100 1/min Propeller RPM approx. n = 2250 1/min With propeller Neuform CR3-75 3-blade 69” (1,75 m Ø) Pitch 24.0° à r = 365 mm from hub, Full throttle RPM on ground max. 4800 1/min Propeller RPM approx. n = 2100 1/min With propeller Kiev Prop BB 263/1800 3-blade (1,71 m Ø) Pitch 22,0° à r = 400 mm from hub, Full throttle RPM on ground max. 4800 1/min Propeller RPM approx. n = 2100 1/min With propeller Helix H50F-1,75m-R-SI-12-3 3-blade (1,75 m Ø), Pitch 16.0° à r = 656 mm from hub Full throttle RPM on ground max. 4880 1/min Propeller RPM approx. n = 2150 1/min Pilot Operating Handbook for the C42 Series POH C42 SERIES ISSUE1 (B) REV7 25/04/2020 Page 17 of 73 1.11 Hélices pour BRP ROTAX 912 ULS With propeller WARP DRIVE 3-blade 68” (1,72 m Ø) Pitch 25.0° à 400 mm from hub, Full throttle RPM on ground max. 5200 1/min Propeller RPM approx. n =2150 1/min With propeller GSC 3-blade 68” (1,72 m Ø) Pitch 25.0° à 400 mm from hub, Full throttle RPM on ground max. 4800 1/min Propeller RPM approx. n = 1975 1/min With propeller Neuform CR3-75 3-blade 69” (1,75 m Ø) Pitch 27.0° à r = 365 mm from hub, Full throttle RPM on ground max. 4900 1/min Propeller RPM approx. n = 2000 1/min With propeller Neuform CR3-V-R2H 3-blade 71” (1,80 m Ø), variable Pitch de 16° à 30° à r = 750 mm from hub, Full throttle RPM on ground entre. 4200 - 5600 1/min Propeller RPM approx. n = 1700 - 2300 1/min With propeller Kiev Prop BB 283/1800 3-blade (1,80 m Ø), Pitch 24,0° à r = 400 mm from hub, Full throttle RPM on ground max. 4900 1/min Propeller RPM approx. n = 2000 1/min With propeller Helix H50F-1,75m-R-S-14-3 3-blade (1,75 m Ø), Pitch 17.0° à r = 656 mm from hub Full throttle RPM on ground max. 4800 1/min Propeller RPM approx. n = 1975 1/min With propeller DUC Hélices Flash -1,75m 3-blade Composite (1,75 m Ø), Pitch 23.5° à r = 660 mm from hub Full throttle RPM on ground max. 5250 1/min Propeller RPM approx. n = 2160 1/min Pilot Operating Handbook for the C42 Series POH C42 SERIES ISSUE1 (B) REV7 25/04/2020 Page 18 of 73 1.12 Noise Table for BRP ROTAX 912 UL and 912 ULS The C42 Series is in accordance with the regulations in force and does not exceed the noise limit of 65dB (A) 1.12.1 ROTAX 912 UL Propellers dB (A) C42 C42B C42C C42CS WARP DRIVE 2 blade 58.1 58.1 58.1 58.1 WAPR DRIVE 3 blade 59.4 59.4 59.4 59.4 Sport-Prop 3 blade 60.0 60 60.0 n/a GSC 3 blade 59.27 59.27 59.27 n/a Neuform CR2-75 2 blade 59.3 59.3 59.3 59.3 Neuform CR3-75 3 blade 55.8 55.8 55.8 55.8 Kiev Prop BB 263/1800 3 blade 59.1 59.1 59.1 59.1 Helix H50F 3 blade 59.6 59.6 59.6 59.6 1.12.2 ROTAX 912 ULS Propellers dB (A) C42 C42B C42C C42CS WAPR DRIVE 3 blade 59.8 59.8 59.8 59.8 GSC 3 blade 59.8 59.8 59.8 n/a Neuform CR3-75 3 blade 58.5 58.5 58.5 58.5 Neuform CR3-V-R2H 3 blade 59.0 59.0 59.0 59.0 Kiev Prop BB 283/1800 3 blade 59.7 59.8 59.8 59.8 Helix H50F 3 blade 59.7 59.7 59.7 59.7 DUC Flash 3 blade 59.5 59.5 59.5 59.5 Pilot Operating Handbook for the C42 Series POH C42 SERIES ISSUE1 (B) REV7 25/04/2020 Page 19 of 73 1.13 Engine Limitations According to the operating manual ROTAX engines: ROTAX 912 UL ROTAX 912 ULS Take-off (5 min) 81 hp / 5800 rpm 100 hp / 5800 rpm Continuous 79 hp / 5500 rpm 95 hp / 5500 rpm 75% 59 hp / 5000 rpm 69 hp / 5000 rpm 65% 51 hp / 4800 rpm 61 hp / 4800 rpm 55% 43 hp / 4300 rpm 51 hp / 4300 rpm Type of oil AERO Shell Sport Plus 4 (for other types, see operating manual ROTAX) Oil Quantity min. 2.6 l à max. 3.05 l Oil temperature min. 50°C min. 50°C max. 140°C max. 130°C optimum 90°-110°C Oil pressure Pression normale 2 - 5 bar (Démarrage froid 7 bar) Fuel Euro-Super ROZ 95 sans plomb (DIN EN228 max. 5% éthanol) Super Plus ROZ 98 sans plomb (DIN EN228 max 5% éthanol) AVGAS 100 LL ou AVGAS UL91 Fuel pressure 0.15 - 0.4 bar Cyl. Head temp. max. 150°C max. 135°C optimum 110°C Magneto check à 4000 trs/min RPM drop max. 300 trs/min Pilot Operating Handbook for the C42 Series POH C42 SERIES ISSUE1 (B) REV7 25/04/2020 Page 20 of 73 2. Restrictions • Aerobatics and maneuvers with more than 60° bank are prohibited • Daylight, VFR conditions only. • No flight in icing conditions • Do not attempt flight in turbulent conditions or in winds exceeding 40 km/h (22 kts), and less when it is gusty. • Always follow the appropriate regulations for this category of aircraft. 3. Note to Engine Operation The Rotax 912 is a 4-cylinder, four stroke, horizontally opposed, water- cooled engine. Never move the prop with the ignition (MAG) switches on! Fuel type for four-stroke 912 UL and 912 ULS engine: Super leaded or unleaded (according to DIN EN 228 with max. 5% ethanol), AVGAS 100 LL or AVGAS UL91 To start the engine: Main fuel valve OPEN Electrical fuel pump ON Throttle IDLE Choke OPEN Carburetor heat OFF Ignition (both magnetos) ON Propeller area CLEAR Brakes PARK After engine starts, choke CLOSED If the engine does not start, repeat the starting procedure. Pilot Operating Handbook for the C42 Series POH C42 SERIES ISSUE1 (B) REV7 25/04/2020 Page 21 of 73 If the engine has been flooded, close main fuel valve, open the throttle to a half and start the engine. When the engine starts, quickly reduce the throttle to idle. A four-stroke engine requires a long warm up period. Run the engine at 2000 rpm for at least 2 minutes then increase to 2500 rpm – 3000 rpm until the oil temperature is at least 50°C (122°F). The cylinder heads of the ROTAX 912 engine are liquid-cooled whereas the cylinder barrels are air-cooled. In the case of the C42 (C42A), there are separate cooling systems for the coolant and the oil. In the case of the C42B, C42C and C42CS only the coolant is cooled by a cooler. The coolant and oil systems are connected to one heat exchanger; thus, the temperatures of both fluids adapt to each other. The temperatures of the coolant, oil and cylinder head is therefore, almost identical. Due to heat exchange the oil also warms up faster during the run-up phase. It is, however, still necessary to mask the water cooler if optimum engine temperature (>90°C) is to be achieved during cold weather operation (max. one third of the surface may be covered with tape or self-adhesive neoprene). Perform the MAG check at 4000 rpm. Rpm drop should not exceed 300 rpm with a maximum difference between MAGs of 115 rpm. In case your aircraft is equipped with a cowl flap, please refer to the instructions in the paragraph 4.9 : Equipped with Optional Cowl Flap Pilot Operating Handbook for the C42 Series POH C42 SERIES ISSUE1 (B) REV7 25/04/2020 Page 22 of 73 4. Flight Operations 4.1 Taxiing The nose wheel steering is conventional and is directly connected to the rudder pedals. Push the right pedal to turn right. Push the left pedal to turn left. Taxiing is simple. The turning radius of the C-42 is small, and the plane handles cross wind during taxing very well. When taxiing with a strong tail wind, hold the control stick firmly in the neutral or nose-down position. When taking off or landing on bumpy grass strips, exercise caution to avoid striking the propeller. 4.2 Take-off and Climb After completing the "before take-off" checklist: Runway and approach are cleared: LINE UP Set trim to neutral. (with an electrical trim the third lamp from above) Wing flaps in take-off position (flap position II). Gently bring the throttle to full forward position, check tachometer. At full throttle, the tips of the propeller blades produce hard knocking sounds. Pull the stick slightly back during the initial roll. The nose wheel will lift off at approx. 50 km/h (27 kts). Further accelerate with the nose wheel up 5-10cm off the ground. Pilot Operating Handbook for the C42 Series POH C42 SERIES ISSUE1 (B) REV7 25/04/2020 Page 23 of 73 Aircraft with the Rotax 912 ULS (100 hp) have a greater engine torque which must be countered by a slight right rudder input. The aircraft will take-off at 70 km/h (38 kts). Push the stick slightly forward and increase airspeed to 110 km/h (59 kts) in shallow climb. Continue to climb at 110 km/h (59 kts). Retract flaps at a height of approx. 150 ft (50m). This will cause a slight nose-heavy moment. After reaching a safe altitude the electrical fuel pump can be switched off. Trim the aircraft to 110 km/h (59 kts) and continue climbing. Slight right rudder is necessary to compensate both engine and propeller torque during climbing. Whenever possible, take-off into the wind. The maximum demonstrated crosswind component for take-off and landing is 30 km/h (16 kts). No special procedures are required. The starting direction must be ensured by " Provision upwind. During the initial take-off phase, it is essential that the aircraft accelerate sufficiently to prevent stalling, should a sudden loss of power be experienced. By a loss of engine power at altitudes below 260 ft (80 m) do not attempt course corrections of more than 90°. Quickly trim the aircraft to a gliding speed of 100 km/h (54 kts) (push stick forward). Avoid obstructions. Using the flaps touch down at a low speed. The approach phase can be shortened by slipping. Before undertaking an emergency landing in rough terrain, turn off the fuel valve and the ignition. Pilot Operating Handbook for the C42 Series POH C42 SERIES ISSUE1 (B) REV7 25/04/2020 Page 24 of 73 4.3 Cruise In cruising flight the most economical cruise speeds are between 140 and 170 km/h (75 – 91 kts) for the models C42 (C42A), C42B and C42C, or between 160 km/h and 190 km/h (86 kts et 102kts) for the C42CS. The required engine performance depends upon aircraft load at the maximal continuous engine speed is 5500 rpm. In order to fly the aircraft comfortably, it should be trimmed to the desired airspeed with the throttle set for the appropriate rpm for horizontal flight. Example: Typical cruising set up: Rotax 912 UL Rotax 912 ULS Engine RPM: 4500 rpm 4500 rpm Air Speed : 150 km/h (81 kts) 160 km/h (86 kts) Fuel consumption: 10 -12 l/h 11 - 13 l/h The maximum speed of must never be exceeded (VNE): C42 (C42A) : 180 km/h (97 kts) C42B & C42C : 216 km/h (116 kts) C42CS : 225 km/h (121 kts) In a turbulent weather the maximum airspeed is 180 km/h (97 kts) for the C42 (C42A), C42B and C42C, or 187 km/h (100 kts) for the C42CS. At the first indication of carburetor icing (rpm drop, stuttering engine running, increase in fuel consumption as indicated by the flow meter, if installed) apply carburetor heat and, if possible, fly the aircraft into non- icing conditions Pilot Operating Handbook for the C42 Series POH C42 SERIES ISSUE1 (B) REV7 25/04/2020 Page 25 of 73 4.4 Turn in Flight Turns are coordinated using the aileron and rudders. With the increase of airspeed, significantly less amount of rudder deflection is needed. Banks of 45° degrees or more are not recommended, a banking angle of more than 60 degrees is prohibited. In steep banks keep the nose and airspeed under control by means of the rudders and elevator. 4.5 Stall In cruising flight configuration (flap position I), the stalling speed is 75 km/h (39 kts). The engine cowling will be well above the horizon. At approximately 80 km/h (43 kts) there will be a slight buffeting of the airframe. When flown in this condition the aircraft is fully controllable. However, lateral altitude corrections must be done mainly with the rudder. Example: right wing low à rudder deflection to the left. If the aircraft is stalled slowly with the elevator in detent, it will enter into a stable stalled descent. Altitude loss can be up to 100 ft (30 m). During a whip stall, the aircraft clearly pitches down (up to 40°). By slightly releasing the elevator, airspeed will increase and the aircraft will return to horizontal flight. Maximum altitude loss is 250 ft (75 m). The aircraft reacts similarly in all flap positions. Stall speeds for the various flap positions at a take-off weight: 472.5kg (1042 lbs): Vs flap position I (cruising flight) ca. 75 km/h (40 kts) Vs1 flap position II (take-off/landing) ca. 70km/h (38 kts) Vs0 flap position III (landing) ca. 65 km/h (35 kts) The stall speeds above will be affected by variations in take-off weights. Pilot Operating Handbook for the C42 Series POH C42 SERIES ISSUE1 (B) REV7 25/04/2020 Page 26 of 73 4.6 Approach and Landing Begin with your approach early enough in order to set the correct landing configuration without hurrying. • Activate carburettor heat. • The electrical fuel pump must be switched on. In order to be able to steeply approach short landing strips, use flap position 2 (landing). Moreover, the glide path can be effectively shortened by a sideslip. Before proceeding to flap position 2 reduce the speed below velocity Vfe : Until 2009 : 105 km/h (57 kts) Since 2010 : 117 km/h (63 kts) The best speed to engage the flaps is between 90 and 100 km/h (48 and 54 kts) On final approach with flap position III keep the speed at about 90 km/h (48 kts) with the engine at idle. The glide angle in flap position II (take-off/landing) is significantly shallower and thus the flare distance is much longer. The approach speed should be about 105 to 110 km / h (57 – 59 kts). At the height of approximately 3 m begin rounding out to the landing flair. Begin final flair at the height of about 50 cm. Landing speed is approx. 70 km/h (38 kts). 4.7 Shutting Down the Engine Shut off all electrical accessories and radios before shutting down the engine. Under normal conditions, the engine will have cooled down sufficiently during descent and taxiing so that it can be shut down by turning off the ignition. Pilot Operating Handbook for the C42 Series POH C42 SERIES ISSUE1 (B) REV7 25/04/2020 Page 27 of 73 4.8 Sudden Loss of Engine Power 4.8.1 Loss of Engine Power During Take-off Depending on the speed and altitude, lower nose and trim to gliding speed at 100 km/h (54 kts), with flaps at position II. Do not attempt to return to airfield if altitude is below 1000 ft after gliding speed has been reached. At lower altitudes, it is best to land straight ahead without attempting any course corrections. Before attempting an emergency landing in rough terrain, turn off the fuel valve and switch off the ignition. When landing in a high vegetation (grain or similar) reduce speed directly above the vegetation by extending the flaps to position III, pull stick fully aft and allow the aircraft to sink into the vegetation. 4.8.2 Loss of Engine Power in Cruise Flight Cross-country flights should be planned to ensure that a suitable landing field could be reached in the case of a loss of the engine power. Once gliding speed has been established (flap position I = cruising flight, VIAS = 90 - 100 km/h (48 - 54 kts)), look for a suitable landing field taking into consideration wind conditions. The best glide ratio is approx. 11:1 at 2.5 m/s (490 ft/min). A lower rate of descent can be achieved with flap position II (take- off/landing), at approx. 90 km/h (48 kts), it does not however result in a better glide path. Pilot Operating Handbook for the C42 Series POH C42 SERIES ISSUE1 (B) REV7 25/04/2020 Page 28 of 73 With sufficient altitude, you may attempt to restart the engine, check: • Fuel valve OPEN • Magneto switches ON • Fuel SUFFICIENT • Fuel pump ON 4.8.3 Start the Engine in Flight • both magneto switches ON • electrical fuel pump ON • throttle ¼ OPEN • carburetor heat OFF • fire up engine using starter Maintaining airspeed to windmill the prop can help. Pilot Operating Handbook for the C42 Series POH C42 SERIES ISSUE1 (B) REV7 25/04/2020 Page 29 of 73 4.9 Equipped with Optional Cowl Flap If your aircraft is equipped with the cowl flap, you have a possibility to control the temperatures of your engine via manual adjustment of the cooling air. There by, you are in the position to keep the engine temperatures in the optimal range (90°-110°C) independent of outside temperatures. It works in C42 both for the oil and cylinder head temperature and coolant temperature due to the installed oil and water heat exchanger. Moreover, you can considerably shorten warm-up period by starting up the engine with a fully closed cowl flap. It does not only protect the engine but also saves fuel. Though, for a reasonable and secure handling of the cowl flap it is necessary to closely monitor the oil and cylinder head temperature. Attention: If the cowl flap is closed the cooling air supply to the radiator will not be sufficient over a longer period, i.e. the oil and cylinder head temperature and coolant temperature will rise to an inadmissible range (the red warning light range). In order to not to forget to close the cowl flap, there will be installed an additional factory-provided warning light which flashes up when reaching the cylinder head temperature and coolant temperature of 117° C. In this case, the cowl flap should be immediately fully opened. The cooling down of the cylinder head temperature to admissive and optimal temperatures can be supported by reducing the engine output and increasing the airspeed in descending. The functionality test of the cowl flap is made during pre-flight inspection. Principally, you should not wait for flashing of the caution lamp, but you have to observe the temperature and to open the cowl flap manually at the temperature of 90°-110°. Pilot Operating Handbook for the C42 Series POH C42 SERIES ISSUE1 (B) REV7 25/04/2020 Page 30 of 73 4.10 Emergency Procedures 4.10.1 Stalling due to Low Speed • Reduce back pressure on the stick and lower the nose. • Recover 4.10.2 Sideslip • Set rudder in the opposite direction to a sideslip • Reduce back pressure on stick 4.10.3 Spin • Throttle to idle. • Apply rudder opposite to the direction of rotation until the rotation will stop • Reduce back pressure on stick • Slowly pull aircraft up 4.10.4 Spiral Dive • Set aileron and rudder opposite to the direction of rotation and • pull back the stick slightly until a horizontal position will be taken. 4.10.5 Loss of Elevator Control With the elevator trim flap, the aircraft can be trimmed to speeds between 80 and 170 km/h (43 and 92 kts). In calm weather condition it can also be used to try to land the aircraft. If in doubt, deploy the parachute rescue system. Pilot Operating Handbook for the C42 Series POH C42 SERIES ISSUE1 (B) REV7 25/04/2020 Page 31 of 73 4.10.6 Loss of Aileron Control Use the rudder to control the aircraft via skidding rolling moments. If in doubt, deploy parachute rescue system 4.10.7 Loss of Rudder Control Controlling flat curves is possible with the ailerons only. • If possible, perform a field landing in a straight flight. • If in doubt, deploy parachute rescue system. 4.10.8 Carburetor Fire • Main fuel valve OFF • Electrical fuel pump OFF • Full throttle • Sideslip • Follow emergency landing procedures Pilot Operating Handbook for the C42 Series POH C42 SERIES ISSUE1 (B) REV7 25/04/2020 Page 32 of 73 4.11 Parachute Deployment Attenttion: Follow the instructions in the BRS or JUNKERS PROFLY– parachute operator’s manual provided with your aircraft. (COMCO IKARUS cannot be held responsible for any malfunctions of the parachute unless it is proven that the malfunction is caused by a faulty installation.) Every Aircraft equipped with a parachute is provided with adequate instruction manual depending of the parachute manufacture, and a registered functioning certificate. Be certain to follow the instructions of the manufacturer for required maintenance and particularly the avoidance of moisture in the parachute pack. Should the parachute get wet, it must be aired and repacked. (Only by the manufacture) The parachute is placed in the fuselage as described in the appendices of this manual. There is a time limit on the use of the rocket cartridge in rocket-deployed systems. (Please follow the provided manufacturer instructions delivered with your aircraft) Removal, replacement or placement of a parachute should be undertaken by an authorized person or by the aircraft manufacturer to allow proper guarantee on the product and on the aircraft. Before taking off, remove the system’s safety pin. After landing secure the system with the safety pin. Should you need to make use of the rescue system, you should try to be in the frame of the parameters described in the parachute user manual: Shut down the engine before deploying the parachute. • Pull the rescue clutch located between and above the 2 occupants • Try to steer the aircraft to a less agglomerated direction and ground Pilot Operating Handbook for the C42 Series POH C42 SERIES ISSUE1 (B) REV7 25/04/2020 Page 33 of 73 5. Handling on Ground 5.1 Maneuver Manual moving of the aircraft is accomplished by using the tail struts upper connections as push points. Since there is no tow bar applicable at the nose gear, you must press down the tail to raise the nose wheel off the ground. With the nose wheel clear of ground, the aircraft can be simply steered by pivoting it on the main wheels. 5.2 Suspension The aircraft may be lifted with a hoist of at least 500 kg (1000 lbs) capacity by using T-support ceiling hangers. Use suitable spring snap hooks for the three designated mounting points on the cabin roof. Pilot Operating Handbook for the C42 Series POH C42 SERIES ISSUE1 (B) REV7 25/04/2020 Page 34 of 73 5.3 Parking When parking please consider following factors: • as a general precaution, set parking brake • block the wheels with wheel blocks or brake blocks • flap to zero = position 0 In severe weather and strong wind conditions, tie down the aircraft as outlined in paragraph 5.4 if a hangar is not available. Caution: Do not set parking brakes during cold weather (when accumulated moisture may freeze the brakes) or when brakes are overheated. 5.4 Tie-Down When parking the aircraft outdoors, nose into the wind if possible. Set parking brakes or block wheels with brake pads. Use ropes or belts and fasten them to the tie down points (upper end of the front wing struts). Then secure them to the ground anchors. Do not use chains, wire or steel cables to tie down the aircraft. Additionally, mount a rope or strap between the engine cowling and propeller spinner and secure to another ground anchor. The control stick must be secured with the help of the safety belt in a fully retracted position. Pilot Operating Handbook for the C42 Series POH C42 SERIES ISSUE1 (B) REV7 25/04/2020 Page 35 of 73 Tie down point at the upper front strut area. Tie down point between the engine cowling and propeller spinner. Pilot Operating Handbook for the C42 Series POH C42 SERIES ISSUE1 (B) REV7 25/04/2020 Page 36 of 73 6. Minimum Equipment List • Four-point harness for each seat • Airspeed indicator true Colour Coding • Altimeter with Kolsmann window • Compass • Tachometer • Cooling liquid temperature gauge • Oil temperature gauge • Oil pressure gauge • Fuel gauge • Generator charge control • Data placard • Pilot’s operating handbook • Parachute rescue system (optional) • Checklist 7. Dimensions Dimensions can be taken from page 6 to 9 and from the annex of this pilot operating handbook. Pilot Operating Handbook for the C42 Series POH C42 SERIES ISSUE1 (B) REV7 25/04/2020 Page 37 of 73 8. Weight and Balance Place the aircraft in a level position on three scales with the stabilizer and elevator leveled. The center of gravity is measured in mm behind the reference datum and then calculated as a percentage of the wing chord. Reference datum (leading edge) Wing chord l = 1360 mm. X1 = 230 mmm X2 = 1770 mm ou 1775 mm (C42CS) Pilot Operating Handbook for the C42 Series POH C42 SERIES ISSUE1 (B) REV7 25/04/2020 Page 38 of 73 8.1 Empty Weight and Center of Gravity Serial Number: ________________ Type : __________ Identification Code: _____________________ Weightinh: Reference weight: ___________ kg Empty weight: ___________ kg X1 = mm, X2 = mm G2 G2R : kg + G2L: kg =__________ kg G1 =__________ kg G total =__________ kg xs mm: mm xs % : % L It is the pilot’s responsibility to respect and verify that the aircraft does not surpasses the maximal take-off weight. Empty weight: __________ kg Maximal payload: __________ kg Maximal payload with full tank: __________ kg Maximal take-off mass: 450,0 kg 472,5 kg (Strike the unnecessary weight indication) Place and Date: ______________________________________ Signature : __________________________________________ Pilot Operating Handbook for the C42 Series POH C42 SERIES ISSUE1 (B) REV7 25/04/2020 Page 39 of 73 Loading plan weight x lever arm = torque Empty weight kg mm kg mm 1. Passenger 400 2. Fuel 950 3. Lugage (max 10kg) 950 total weight: total torque: lever arm = !"!#$ !"&'() [+, --] /0/12 34567/ [86] = mm Maximum lever arm authorized: at max weight: 300 – 560 mm (from the reference point BP) at empty weight: 280 – 460 mm Place and Date: ______________________________________ Signature : __________________________________________ Loading plan weight x lever arm = torque Empty weight kg mm kg mm 1. Passenger 400 2. Fuel 950 3. Lugage (max 10kg) 950 total weight: total torque: lever arm = !"!#$ !"&'() [+, --] /0/12 34567/ [86] = mm Maximum lever arm authorized: at max weight: 300 – 560 mm (from the reference point BP) at empty weight: 280 – 460 mm Place and Date: ______________________________________ Signature : __________________________________________ Pilot Operating Handbook for the C42 Series POH C42 SERIES ISSUE1 (B) REV7 25/04/2020 Page 40 of 73 9. Data Placard and Check-List Air Speed Speed to never-exceed: C42 (C42A) 180 km/h (97 kts) C42B & C42C 216 km/h (116 kts) C42CS 225 km/h (121 kts) Stall speed 65 km/h (35 kts) Load factor Positive load factor +4 g. Negative load factor - 2 g. Maximum wind speed for operation Steady wind 22 kts (40 km/h) Demonstrated cross-wind component 16 kts (30 km/h) Payload Max kg Min 65 kg The pilot operating this aircraft at his own risk Manufacturer: COMCO IKARUS GmbH Serial Number: ____________________________ Identification Code: ____________________________ Year of manufacture: ____________________________ Month : ____________________________ Empty weight: ____________________________