C42 Pilot Operating Handbook
Comco Ikarus C42C · Pilot's Operating Handbook
Overview
The C42 Pilot Operating Handbook provides essential information for operating the IKARUS C42 Series aircraft, including safety guidelines, operational limitations, and maintenance procedures. It is intended for pilots and must be kept in the aircraft at all times.
- The C42 Series is certified as Microlight, Ultralight, Advanced Ultralight, and Light Sport Aircraft.
- Pilots must hold the appropriate license for this category of aircraft.
- The aircraft should only be flown under daytime VFR conditions.
- Engine changes are prohibited as they invalidate airworthiness certificates.
- Smoking is prohibited on board for fire safety reasons.
- The pilot is responsible for the safety of all occupants and the aircraft.
- Emergency landing areas should always be in sight during cross-country flights.
- Different regulations may apply for towing operations in various countries.
Document
Source
Originally published by comco-ikarus.de. Sprinkle hosts a reference copy with an added summary, specifications and searchable full text.
Document details
- Type ·
- Pilot's Operating Handbook
- Year ·
- 2019
- File size ·
- 2.8 MB
- Publisher ·
- comco-ikarus.de
- Language ·
- en
What is the C42 Pilot Operating Handbook?
The C42 Pilot Operating Handbook is a pilot's operating handbook for the Comco Ikarus C42C, dated 2019.
Where does the C42 Pilot Operating Handbook come from?
This copy of the C42 Pilot Operating Handbook was originally published by comco-ikarus.de and is hosted on Sprinkle as a free, searchable reference copy.
What year was the C42 Pilot Operating Handbook published?
The C42 Pilot Operating Handbook — the Comco Ikarus C42C pilot's operating handbook on file — is dated 2019.
Most owners only have the POH. Here's the essential set for the Comco Ikarus C42C.
- Pilot's Operating Handbook / AFM
- Checklist
- Maintenance Manual
- Parts Catalog (IPC)
- Systems & Wiring
- Service Bulletins on file
- Type Certificate (TCDS)
More Comco Ikarus C42Cmanuals & documents
In this document
Operating Limitations
This section outlines airspeeds, weights, structural limitations, center of gravity limits, and engine RPM limitations.
Flight Operations
Details procedures for taxiing, take-off, climbing, cruising, turning, stalls, descent, landing, and engine shutdown.
Weight and Balance
Provides information on loading plans and weight distribution for safe operation.
Emergency Procedures
Outlines steps to take in case of engine failure and other emergencies.
Pre-flight Inspection
Lists checks for the engine, landing gear, wings, fuselage, and instruments before flight.
Care and Maintenance
Guidelines for the maintenance and care of the aircraft to ensure safety and performance.
Safety notes
- Do not operate the aircraft in a manner that endangers occupants or persons on the ground.
- Prepare for emergency landings in case of engine failure.
- Changes to the control system or structure are prohibited.
- Ensure the aircraft is registered and has a valid Permit to Fly.
- Pilots must be checked out by a qualified instructor before flying.
- Smoking is prohibited on board for fire safety.
Full document text
C42 Pilot Operating Handbook PILOT OPERATING HANDBOOK for the aircraft IKARUS C 42 Series Modell Nr. C42 / C42B / C42C / C42E / C42CS LTZ-Nr. 61141 / 61141.1 / 61141.5 / 61141.6 / 61141.7 Type IKARUS C42 Series Airplane Serial-No. _____________________________ Reference: POH C42 Series Issue 4 - Rev.5 23.08.2019 This handbook is to be kept in the aircraft at all times. The described options of the C42 Series use are certified for Germany and have been tested in Germany. Please note that for using the C42 Series as a tow plane for towing gliders, towing aerial signs or decanting sky divers, different regulations may apply in different countries. Please contact your local authorities for further clarification. POH Issue 4 Rev. 5 Page 2 of 91 RECORD OF MANUAL REVISIONS No. Issue No. Description of Changes Date Signature 1 4 Model C42CS added 02.11.2015 A. Kurz 2 4 Cooling system added 02.11.2015 A. Kurz 3 4 Rev.1 Empty weight centre of gravity deleted 20.11.2015 A. Kurz 4 4 Rev.1 Weight and Balance modify 20.01.2016 A. Kurz 5 4 Rev.2 Circuit diagram updated 02.12.2016 R. Neie 6 4 Rev.3 Page 76 - change LiFe battery 07.02.2017 A. Kurz 7 4 Rev.4 Page 91 - Circuit diagram update 26.07.2017 A. Kurz 8 4 Rev. 5 Page 45 - Step 10 added Page 46 - Point 4 added Page 48 - 14.4 extended Page 76 - new OVP Change flaps 0/1/2 to I/II/III 23.08.2019 H. Lieb C42 Series Pilot Operating Handbook POH Issue 4 Rev. 5 Page 3 of 91 Manufacturer Contact Information COMCO IKARUS GmbH Am Flugplatz 11 88367 Hohentengen / Swabia Germany Tel: +49 7572 600 80 Fax: +49 7572 3309 Email: post@comco - ikarus.de Owner 1. ________________________________ 2. ________________________________ 3. ________________________________ 4. ________________________________ This Pilot Operating Handbook belongs to the aircraft with serial-No._________________ and is to be kept in the aircraft at all times. C42 Series Pilot Operating Handbook POH Issue 4 Rev. 5 Page 4 of 91 Introduction C42 series aircraft are built in compliance with the airworthiness requirements of various countries and are certified as Microlight, Ultralight, Advanced Ultralight and Light Sport Aircraft. To operate the aircraft the pilot must hold a license or certificate appropriate to this category of aircraft. The aircraft is not to be flown unless it is registered, carries registration markings in accordance with the requirements of the country in which the aircraft is to be flown, and has a Permit to Fly or certificate of Airworthiness valid in the country of operation. The aircraft is to be flown under daytime VFR conditions. Flights in other conditions than daytime VFR without the correct aircraft equipment and pilot ratings is extremely dangerous and can result in serious injury or death. Pilots holding licences for other categories, even higher ones, are required to be checked out by an appropriately qualified instructor prior to flying this aircraft as it possesses characteristics that are unique to light sport type aircraft. These characteristics include low inertia, susceptibility to turbulence and wind gradient and special engine considerations. The safety of all occupants, the aircraft and persons on the ground are the sole responsibility of the Pilot in command. Do not operate this aircraft in a manner that would endanger the occupants, the aircraft or persons on the ground. C42 Series Pilot Operating Handbook POH Issue 4 Rev. 5 Page 5 of 91 Bear in mind that the engines used in C42 aircraft are not certified aviation engines and thus may not offer the same safety standards found in other classes of aircraft. Prepare your flight so that you can always reach an emergency landing area should you experience engine failure. On cross country flights, ALWAYS keep an emergency landing field in sight. Changes to the control system, structure, wings and engine are prohibited. These changes would invalidate any certificate of airworthiness or permit to fly and as such would result in an insurance becoming null and void. All operating difficulties and equipment failures should be reported to your dealer or the manufacturer. For fire safety reasons, smoking is prohibited on board of the aircraft. C42 Series Pilot Operating Handbook POH Issue 4 Rev. 5 Page 6 of 91 Three side view: IKARUS C42 Series IKARUS C42 C42 Series Pilot Operating Handbook POH Issue 4 Rev. 5 Page 7 of 91 IKARUS C42B / C42E (C42B LSA) C42 Series Pilot Operating Handbook POH Issue 4 Rev. 5 Page 8 of 91 IKARUS C42C C42 Series Pilot Operating Handbook POH Issue 4 Rev. 5 Page 9 of 91 IKARUS C42CS C42 Series Pilot Operating Handbook POH Issue 4 Rev. 5 Page 10 of 91 Title page .................................................................................................... - Record of Manual Revisions ...................................................................... 2 Manufacturer Contact Information ............................................................. 3 Introductory remarks .................................................................................. 4 Three-side view.......................................................................................... 5 Table of contents ....................................................................................... 8 1 Operating limitations ........................................................................ 13 1.1 Airspeeds ....................................................................................... 13 1.2 Weights .......................................................................................... 13 1.3 Structural limitations ...................................................................... 14 1.4 Center of gravity limits ................................................................... 14 1.5 Airspeed markings ......................................................................... 14
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1.6 Engine rpm limitations ................................................................... 15 1.7 Rpm indicator markings ................................................................. 15 1.8 Flap settings .................................................................................. 15 1.9 Propellers for Rotax 912 UL .......................................................... 16 1.10 Propellers for Rotax 912 ULS ........................................................ 18 1.11 Engine limitations .......................................................................... 20 2 Kinds of operation limitations ......................................................... 21 3 Operation of the Engine ................................................................... 21 4 Flight Operations .............................................................................. 23 4.1 Taxiing ........................................................................................... 23 4.2 Take-off and climb ......................................................................... 23 4.3 Cruising flight ................................................................................. 25 4.4 Turning flight .................................................................................. 25 4.5 Stalls .............................................................................................. 26 4.6 Descent and landing ...................................................................... 27 4.7 Shutting down the engine .............................................................. 27 4.8 Sudden loss of engine power ........................................................ 28 4.9 Using the optional cowl flap on the aircraft C42 ............................ 29 4.10 Emergency procedures ................................................................. 30 C42 Series Pilot Operating Handbook POH Issue 4 Rev. 5 Page 11 of 91 5 Ground Handling .............................................................................. 32 5.1 Towing ........................................................................................... 32 5.2 Hoisting .......................................................................................... 32 5.3 Parking........................................................................................... 33 5.4 Tie-Down ....................................................................................... 33 6 Minimum equipment ......................................................................... 35 7 Dimensions ....................................................................................... 35 8 Weight and balance .......................................................................... 36 8.1 Loading plan .................................................................................. 37 9 Data placard and checklist .............................................................. 38 10 “Before take-off” checklist .............................................................. 39 11 Approved equipment ........................................................................ 40 12 Flight performance ........................................................................... 42 12.1 Take-off distance ........................................................................... 42 12.2 Rate of climb Rotax 912 UL Rotax 912 ULS ................................ 42 12.3 Cruising speed (solo) ..................................................................... 43 12.4 Engine off performance (solo) ....................................................... 43 13 Attaching the wings.......................................................................... 44 13.1 Attaching the wings to the fuselage ............................................... 44 13.2 Folding the wings for hangaring .................................................... 46 14 Pre-flight inspection ......................................................................... 47 14.1 Engine............................................................................................ 47 14.2 Landing gear .................................................................................. 47 14.3 Left wing ........................................................................................ 48 14.4 Left side of fuselage ...................................................................... 48 14.5 Empennage ................................................................................... 49 14.6 Right side of fuselage .................................................................... 49 14.7 Right wing ...................................................................................... 49 14.8 Cabin, inside and outside .............................................................. 49 14.9 Instruments .................................................................................... 50 14.10 Drainage ........................................................................................ 50 15 Care and maintenance ..................................................................... 51 C42 Series Pilot Operating Handbook POH Issue 4 Rev. 5 Page 12 of 91 16 Rigging data ...................................................................................... 53 17 Information for ultralights with towing device .............................. 57 17.1 Equipment of the towing aircraft .................................................... 57 17.2 Operating limitations ...................................................................... 58 17.3 Flight characteristics and performance ......................................... 60 17.4 Placards ......................................................................................... 62 17.5 Emergency procedures during towing ........................................... 62 18 Inspection and maintenance intervals ........................................... 64 19 Special features of the aircraft equipped for handicapped pilots71 20 Flying the IKARUS C42 Series with removed doors ..................... 73 21 Additional instructions for dropping skydivers ............................ 73 22 Instructions for the use of the LiFe-Battery ................................... 75 23 COMCO IKARUS Manufacturer Warranty....................................... 77 24 Appendix ........................................................................................... 81 24.1 Placards ......................................................................................... 81 24.2 Data placard .................................................................................. 82 24.3 Service Problem Report Form -Aircraft ......................................... 83 24.4 Inspections performed ................................................................... 84 24.5 Location of the parachute rescue system ...................................... 85 24.6 Banner towing ................................................................................ 88 24.7 Circuit diagram .............................................................................. 91 C42 SERIES Pilot Operating Handbook POH Issue 4 Rev. 5 Page 13 of 91 1 Operating limitations 1.1 Airspeeds Never-exceed speed C42 .......................................................................... VNE = 97 kn / 180 km/h C42B / C42E / C42C ............................................. VNE = 116 kn / 216 km/h C42CS ................................................................... VNE = 121 kn / 225 km/h Speed in turbulent air C42 / C42B / C42E / C42C ....................................... VB = 97 kn / 180 km/h C42CS .....................................................................VB = 101 kn / 187 km/h Maximum manoeuver speed C42 / C42B / C42E / C42C / C42CS ........................ VA = 80 kn / 148 km/h Speed with landing flap set Vfe until 2009 ................................................................ VFE = 57 kn / 105 km/h since 2009................................................................ VFE = 63 kn / 117 km/h Stall speed Flap position I: ....................................................... VS = 40 kn / 75 km/h Flap position II: ..................................................... VS1 = 38 kn / 70 km/h Flap position III: .................................................... VS0 = 35 kn / 65 km/h If VA speed is exceeded, only little rudder movement are allowed. 1.2 Weights Maximum take-off weight: ............................................... 992 lbs / 450,0 kg Maximum take-off weight with installed rescue system ................................................ 1041 lbs / 472,5 kg Empty weight (see last Weight and Balance plan) .......................... lbs / kg Minimum payload: (see last Weight and Balance plan) .......144 lbs / 65 kg C42 SERIES Pilot Operating Handbook POH Issue 4 Rev. 5 Page 14 of 91 1.3 Structural limitations Positive limit load factor ........................................................................ +4 g Negative limit load factor ....................................................................... -2 g 1.4 Center of gravity limits Reference datum ................................... Wing leading edge at a rib station Forward center of gravity ...................... 11.8 inches (300 mm) aft of datum Rearward center of gravity.................... 22.0 inches (560 mm) aft of datum 1.5 Airspeed markings until 2009 white arc.............................................................. 38 - 57 kn / 71 - 105 km/h since 2009 white arc.............................................................. 38 - 63 kn / 71 - 117 km/h Green arc C42 / C42B / C42E / C42C ................................. 43 - 97 kn / 79 - 180 km/h C42CS .............................................................. 43 - 101 kn / 79 - 187 km/h Yellow arc: C42B / C42E / C42C ....................................... 97 - 116 kn / 180 - 216 km/h C42CS .......................................................... 101 - 121 kn / 187 - 225 km/h Yellow triangle:.......................................................... VX = 54 kn / 100 km/h Yellow line: ................................................................ VA = 75 kn / 148 km/h Red line: C42 ......................................................................... VNE = 97 kn / 180 km/h C42B / C42E / C42C ............................................. VNE = 116 kn / 216 km/h C42CS .................................................................. VNE = 121 kn / 225 km/h ATTENTION: C42 - No yellow area! → VB = VNE C42 SERIES Pilot Operating Handbook POH Issue 4 Rev. 5 Page 15 of 91 The deviation curve for the airspeed indicator can be interpolated from the following table IAS kn 33 38 43 49 54 60 65 70 76 81 86 92 97 103 108 EAS kn 35 41 45 49 54 59 63 68 72 77 151 86 91 96 100 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 1.6 Engine rpm limitations Maximum engine rpm ...................................... n = 5800 1/min, 5 min. max Maximum continuous rpm .................................................... n = 5500 1/min 1.7 Rpm indicator markings Yellow arc ................................................................. n = 5500 - 5800 1/min Red line ................................................................................ n = 5800 1/min 1.8 Flap settings Position I: ......................................................................................... cruising Position II: ......................................................................... take-off / landing Position III: ....................................................................................... landing C42 SERIES Pilot Operating Handbook POH Issue 4 Rev. 5 Page 16 of 91 1.9 Propellers for Rotax 912 UL With propeller WARP DRIVE 2-blade, constant speed, 68” Ø (1,72 m), pitch 23.5° at 15.75 inches (400 mm) from hub, full throttle rpm on the ground ........................................... max. 5200 1/min Propeller rpm .......................................................... approx. n = 2300 1/min With propeller WARP DRIVE 3-blade, 68” Ø (1,72 m), pitch 21.0° at 15.75 inches (400 mm) from hub, full throttle rpm on the ground ........................................... max. 5200 1/min Propeller rpm .......................................................... approx. n = 2300 1/min With propeller Sport-Prop 3-blade, 68” Ø (1,72 m), pitch 19.5° at 15.75 inches (400 mm) from hub, full throttle rpm on the ground ........................................... max. 4900 1/min Propeller rpm .......................................................... approx. n = 2150 1/min With propeller GSC 3-blade, 68” Ø (1,72 m), pitch 21.0° at 15.75 inches (400 mm) from hub, full throttle rpm on the ground ........................................... max. 4900 1/min Propeller rpm .......................................................... approx. n = 2150 1/min C42 SERIES Pilot Operating Handbook POH Issue 4 Rev. 5 Page 17 of 91 With propeller Neuform CR2-75 2-blade, 69” Ø (1,75 m), pitch 27.0° at r = 14.37 inches (365 mm), full throttle rpm on the ground ........................................... max. 5100 1/min Propeller rpm .......................................................... approx. n = 2250 1/min With propeller Neuform CR3-75 3-blade, 69” Ø (1,72 m), pitch 24.0° at r = 14.37 inches (365 mm), full throttle rpm on the ground ........................................... max. 4800 1/min Propeller rpm .......................................................... approx. n = 2100 1/min With propeller Kiev Prop BB 263/1700 3-blade, 67” Ø (1,71 m), pitch 22,0° at 15.75 inches (400 mm) from hub, full throttle rpm on the ground ........................................... max. 4800 1/min propeller rpm ........................................................... approx. n = 2100 1/min With propeller Helix H50F-1,75m-R-SI-12-3 3-blade, 69” Ø (1,75 m), Pitch. 16.0° at r = 25.82 inches (656 mm) full throttle rpm on the ground ........................................... max. 4880 1/min propeller rpm ........................................................... approx. n = 2150 1/min C42 SERIES Pilot Operating Handbook POH Issue 4 Rev. 5 Page 18 of 91 1.10 Propellers for Rotax 912 ULS With propeller WARP DRIVE 3-blade, 68” Ø (1,72 m), pitch 25.0° at 15.75 inches (400 mm) from hub, full throttle rpm on the ground ........................................... max. 5200 1/min Propeller rpm ........................................................... approx. n =2150 1/min With propeller GSC 3-blade, 68” Ø (1,72 m), pitch 25.0° at 15.75 inches (400 mm) from hub, full throttle rpm on the ground ........................................... max. 4900 1/min Propeller rpm .......................................................... approx. n = 2000 1/min With propeller Neuform CR3-75 3-blade, 69” Ø (1,75 m), pitch 27.0° at r = 14.37 inches (365 mm), full throttle rpm on the ground ........................................... max. 4900 1/min Propeller rpm .......................................................... approx. n = 2000 1/min With propeller Neuform CR3-V-R2H 3-blade, 69” Ø (1,75 m), adjustable, pitch 16° - 30° at r = 29.53 inches (750 mm), full throttle rpm on the ground ................................ max. 4200 - 5600 1/min Propeller rpm ............................................... approx. n = 1700 - 2300 1/min With propeller Kiev Prop BB 283/1800 3-blade, 71” Ø (1,80 m), Pitch 24,0° at r = 15.75 inches (400 mm) from hub, full throttle rpm on the ground .......................................... max. 4900 1/min Propeller rpm ......................................................... approx. n = 2000 1/min C42 SERIES Pilot Operating Handbook POH Issue 4 Rev. 5 Page 19 of 91 With propeller Helix H50F-1,75m-R-S-14-3 3-blade, 69” Ø (1,75 m), Pitch 17.0° at r = 25.82 inches (656 mm) full throttle rpm on the ground ....................................... approx. 4800 1/min Propeller rpm .......................................................... approx. n = 1975 1/min With propeller DUC-Flash-1,75m-3-blade, 1,75 m Ø), Pitch 23,5° at r = 0,66 mm full throttle rpm on the ground ....................................... approx. 5250 1/min Propeller rpm .......................................................... approx. n = 2160 1/min C42 SERIES Pilot Operating Handbook POH Issue 4 Rev. 5 Page 20 of 91 1.11 Engine limitations According to the ROTAX operating manual ROTAX 912 ROTAX 912S Take-off (5 min) 81 hp / 5800 1/min 100 hp / 5800 1/min Continuous 79 hp / 5500 1/min 95 hp / 5500 1/min 75% 59 hp / 5000 1/min 69 hp / 5000 1/min 65% 51 hp / 4800 1/min 61 hp / 4800 1/min 55% 43 hp / 4300 1/min 51 hp / 4300 1/min Type of oil AERO Shell Sport Plus 4 (resp. ROTAX operating manual) Amount of oil min 0.57 imp. gallons (2.6 l) max 0.67 imp. gallons (3.05 l) Oil temperature min 122°F (50°C) min 122°F (50°C) max 284°F (140°C) max 266°F (130°C) optimum 194°-230°F (90°-110°C) Oil pressure: normal operating pressure 29 - 72 psi (2 - 5 bar) (cold start 101.45 psi/7 bar) Fuel: Euro-Super ROZ 95 unleaded (DIN EN 228 with max. 5% ethanol) Super Plus ROZ 98 unleaded (DIN EN 228 with max. 5% ethanol) AVGAS 100 LL AVGAS UL91 Fuel pressure 2.17 - 5.80 psi (0.15 - 0.4 bar) Cylinder head temp. max 302°F (150°C) max. 275°F (135°C) optimum 230°F (110°C) optimum 230°F (110°C) Coolant temperature: max.248°F (120°C) optimal 212°F (100°C) Magneto check at 4000 1/min Rpm drop max. 300 1/min C42 SERIES Pilot Operating Handbook POH Issue 4 Rev. 5 Page 21 of 91 2 Kinds of operation limitations - Aerobatics and manoeuvres 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 22 kts (40 km/h) and less when it is gusty. - Always follow the appropriate regulations for this category of aircraft. 3 Operation of the Engine 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 ................................................................................ O P E N Electrical fuel pump ............................................................................... O N Throttle .............................................................................................. I D L E Choke.............................................................................................. O P E N Carburettor heat .................................................................................. O F F Ignition (both magnetos) ........................................................................ O N Propeller blade area .................................................................... C L E A R Brakes .................................................................................................... O N After engine starts, choke slowly ............................................. C L O S E D If the engine does not start, repeat the starting procedure. C42 SERIES Pilot Operating Handbook POH Issue 4 Rev. 5 Page 22 of 91 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 fairly long warm up period. Run the engine at 2000 1/min for at least 2 minutes then increase to 2500 1/min - 3000 1/min until the oil temperature is at least 122°F (50°C). The cylinder heads of the ROTAX 912UL engine are liquid-cooled whereas the cylinder barrels are air-cooled. In the case of the C42 / C42 UK, there are separate cooling systems for the coolant and the oil. In the case of the C42B / C42B UK / C42E / C42C / 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 of the C42B / C42B UK / C42E / C42C /C42CS are, 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 1/min. Rpm drop should not exceed 300 1/min with a maximum difference between MAGs of 115 1/min. In case your aircraft is equipped with a cowl flap, please refer to the instructions in the paragraph 4.9 : Using the optional cowl flap on the aircraft C42 C42 SERIES Pilot Operating Handbook POH Issue 4 Rev. 5 Page 23 of 91 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 C42 is small. 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 taxiing on bumpy grass strips, exercise caution to avoid striking the propeller. 4.2 Take-off and climb After completing the "before take-off" checklist, Make certain the runway and approach are free before you taxi to the take- off position. 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. 27 kn (50 km/h). Further accelerate with the nose wheel up 2-4 inches (5-10 cm) off the ground. C42 SERIES Pilot Operating Handbook POH Issue 4 Rev. 5 Page 24 of 91 Aircraft with the ROTAX 912 UL S (100 hp) have a greater engine torque which must be countered by a slight right rudder input. The aircraft will take-off at 38 kn (70 km/h). Push the stick slightly forward and increase airspeed to 59 kn (110 km/h) in shallow climb. Continue to climb at 59 kn (110 km/h). Retract flaps at a height of approx. 150 ft. This will cause a slight nose- heavy moment. After reaching the safe altitude the electrical fuel pump can be switched off. Trim the aircraft to 59 kn (110 km/h) 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 16 kn (30 km/h). 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 in order 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 54 kn (100 km/h) (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. C42 SERIES Pilot Operating Handbook POH Issue 4 Rev. 5 Page 25 of 91 4.3 Cruising flight In cruising flight the most economical cruise speeds are between 75 and 91 kn (140 – 170 km/h) – C42CS: 86 – 103 kn (160 – 190 km/h). The required engine performance depends upon aircraft load. Max continuous engine speed is 5500 1/min. 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. Typical cruising flight: Rotax 912 UL Rotax 912 ULS Engine speed 4500 1/min 4500 1/min Airspeed: 81 kn (150 km/h) 86 kn (160 km/h) Fuel flow: 2.20 - 2.64 gph 2.42 - 2.86 gph (10 -12 l/h) (11 - 13 l/h) The maximum speed of must never be exceeded. C42 ................................................................................... 97 kn (180 km/h) C42B / C42E / C42C ........................................................ 116 kn (216 km/h C42CS ............................................................................ 121 kn (225 km/h) In a turbulent weather the maximum airspeed is 97 kn (180 km/h), C42CS the maximum airspeed is 101 kn (187 km/h) At the first indication of carburettor icing (rpm drop, stuttering engine running, increase in fuel consumption as indicated by the flow meter, if installed) apply carburettor heat and, if possible, fly the aircraft into non- icing conditions. 4.4 Turning flight Turns are coordinated using the aileron and rudders. With the increase of airspeed, significantly less amount of rudder deflection is needed. C42 SERIES Pilot Operating Handbook POH Issue 4 Rev. 5 Page 26 of 91 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 Stalls In cruising flight configuration (flap position I), the stalling speed is 39 kn (75 km/h). The engine cowling will be well above the horizon. At approximately 43 kn (80 km/h) 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 → 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 position, take-off weight: 1042 lbs (472.5 kg): vS flap position I (cruising flight) .................................... ca. 40 kn (75 km/h) vS1 flap position II (take-off/landing) .............................. ca. 38 kn (70 km/h) vS0 flap position III (landing) .......................................... ca. 35 kn (65 km/h) The stall speeds above will be affected by variations in take-off weights. C42 SERIES Pilot Operating Handbook POH Issue 4 Rev. 5 Page 27 of 91 4.6 Descent 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 III (landing). Moreover, the glide path can be effectively shortened by a sideslip. Before proceeding to flap position III reduce the speed below velocity Vfe until 2009 .......................................................................... 57 kn (105 km/h) since 2009......................................................................... 64 kn (117 km/h) Favourably are about 48 - 54 kn (90 - 100 km/h). On final approach with flap position III keep the speed at about 48 kn (90 km/h) with the engine at idle. The glide angle in flap position II (take-off/landing) is significantly more shallow and thus the flare distance is much longer. The approach speed should be about 57 - 59 kn (105 - 110 km/h). At the height of approximately 10 ft (3 m) begin rounding out to the landing flair. Begin final flair at the height of about 2 ft (0.5 m). Landing speed is approx. 38 kn (70 km/h). 4.7 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. Shut off all electrical accessories (radio, transponder etc.) before shutting down the engine. C42 SERIES Pilot Operating Handbook POH Issue 4 Rev. 5 Page 28 of 91 4.8 Sudden loss of engine power I Loss of engine power during take off Depending upon speed and altitude, lower nose and trim to gliding speed (ca.54 kn / 100 km/h). 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. II Loss of engine power during cruising 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 = 48 - 54 kn / 90 - 100 km/h), look for a suitable landing field taking into consideration wind conditions. The best glide ratio is approx. 1:11 at 490 ft/min (2.5 m/s). A lower rate of descent can be achieved with flap position II (take- off/landing), at approx. 48 kn (90 km/h), however it does not result in a better glide path. C42 SERIES Pilot Operating Handbook POH Issue 4 Rev. 5 Page 29 of 91 With sufficient altitude you may attempt to restart the engine, check: 1. Fuel valve.................................................................................... O P E N 2. Magneto switches .............................................................................. O N 3. Fuel ............................................................................ S U F F I C I E N T 4. Fuel pump .......................................................................................... O N III Starting the engine in flight Starting during flight with the engine intact is done as follows: - both magneto switches .................................................................. O N - electrical fuel pump ........................................................................ O N - throttle ................................................................................. ¼ O P E N - carburettor heat .......................................................................... O F F - fire up using engine starter Maintaining airspeed to windmill the prop can help. 4.9 Using the optional cowl flap on the aircraft C42 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 194° - 230°F (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 watch the oil and cylinder head temperature. C42 SERIES Pilot Operating Handbook POH Issue 4 Rev. 5 Page 30 of 91 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 not to forget to close the cowl flap, there will be installed an additional factory-provided warning light (orange) which flashes up and buzz when reaching the cylinder head temperature and coolant temperature of 243°F (117°C). In this case, the cowl flap should be immediately fully opened. The cooling down of the cylinder head temperature to admissible and optimal temperatures can be supported by reducing the engine power 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 194° - 230°F (90° - 110°C). 4.10 Emergency procedures I Tipping due to lower speeds - Reduce back pressure on the stick and lower the nose - Recover II Sideslip - Set rudder in the opposite direction to a sideslip - Reduce back pressure on stick III 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 C42 SERIES Pilot Operating Handbook POH Issue 4 Rev. 5 Page 31 of 91 IV 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 V Loss of elevator control - With the elevator trim flap, the aircraft can be trimmed to speeds between 43 and 92 kn (80 and 170 km/h). - In calm weather conditions it can also be used to try to land the aircraft. - If in doubt, deploy the parachute rescue system. VI Loss of aileron control - Use the rudder to control the aircraft via yaw-induced rolling moments. - If in doubt, deploy parachute rescue system. VII Loss of rudder control - Controlling gentle turns is possible with the ailerons only. - If possible, perform a field landing in a straight flight. - If in doubt, deploy parachute rescue system. VIII Carburettor fire - Main fuel valve ............................................................................ O F F - Electrical fuel pump .................................................................... O F F - Full throttle - Sideslip - Follow emergency landing procedures C42 SERIES Pilot Operating Handbook POH Issue 4 Rev. 5 Page 32 of 91 5 Ground Handling 5.1 Towing 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 have to 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 Hoisting The aircraft may be lifted with a hoist of at least 1000 lb (0.5 tons) capacity by using T-support ceiling hangers. Use suitable spring snap hooks for the three designated mounting points on the cabin roof. C42 SERIES Pilot Operating Handbook POH Issue 4 Rev. 5 Page 33 of 91 5.3 Parking When parking consider a number of factors: - as a general precaution, set parking brake - block the wheels with wheel blocks or brake blocks - flap to zero = position I 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 (frozen moisture can block brakes)or when brakes are overheated. 5.4 Tie-Down Parking of ultralight aircraft outdoors: if possible, let the nose of the aircraft point in the direction of the wind. Apply parking brakes or lock wheels with brake pads. Use ropes or belts (no chains, wire or steel cables) and fasten them to the tie down points (upper end of the front wing struts). Then secure them to the ground anchors. Additionally, mount a rope or strap between the engine cowling and propeller spinner and secure to another ground anchor. On IKARUS C42 Series models equipped with a towing device, the towing hook can be used as a third anchorage point. The control stick must be secured with the help of the safety belt in a fully retracted position. C42 SERIES Pilot Operating Handbook POH Issue 4 Rev. 5 Page 34 of 91 Tie-Down Point at the Upper Front Strut Area Tie-Down Point between the Engine Cowling and Propeller Spinner C42 SERIES Pilot Operating Handbook POH Issue 4 Rev. 5 Page 35 of 91 6 Minimum equipment - Four point seat belt for each seat - Airspeed indicator with correct 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 - Checklist 7 Dimensions Dimensions can be found in the overview sheets, which you will find at the beginning of this manual. C42 SERIES Pilot Operating Handbook POH Issue 4 Rev. 5 Page 36 of 91 8 Weight and balance Place the aircraft in a level position on three scales with the stabilizer and elevator leveled (0°). The center of gravity is measured in mm or inches in relation to the reference datum and then calculated as a percentage of the wing chord. X1 is to be used as a positive and X2 as a negative value in the formula. BP: reference datum (leading edge) Wing chord MAC = 53.5 inches (1360 mm) BE BP = 39.37 inches (1000 mm) X1 = 9 inches (230 mm) X2 for C42 / B / C = 69.68 inches (1770 mm) X2 for C42CS = 69.88 inches (1775 mm) C42 SERIES Pilot Operating Handbook POH Issue 4 Rev. 5 Page 37 of 91 8.1 Loading plan Loading plan position weight x lever arm = torque kp cm cm kp empty weight 1. seats 40 2. fuel 95 3. baggage 130 total weight kp total torque kp total torque [cm kp] center of gravity CG = ------------------------------------------ = cm total weight [kp] allowed range for CG: 300 - 560 mm behind zero datum (leading edge) empty weight CG: 280 - 460 mm behind zero datum (leading edge) Date:________________ Signature:________________ Loading plan position weight x lever arm = torque kp cm cm kp empty weight 1. seats 40 2. fuel 95 3. baggage 130 total weight kp total torque kp total torque [cm kp] center of gravity CG = ------------------------------------------ = cm total weight [kp] allowed range for CG: 300 - 560 mm behind zero datum (leading edge) empty weight CG: 280 - 460 mm behind zero datum (leading edge) Date:________________ Signature:________________ It is the pilot’s responsibility to ensure that the MTOW of 1041 lbs (472.5 kg) is not exceeded. C42 SERIES Pilot Operating Handbook POH Issue 4 Rev. 5 Page 38 of 91 9 Data placard and checklist Airspeeds Never-exceed speed C42 ................................................................................... 97 kn (180 km/h) C42B / C42E / C42C ....................................................... 116 kn (216 km/h) C42CS ............................................................................ 121 kn (225 km/h) Stall speed .......................................................................... 35 kn (65 km/h) Load factor Positive limit load factor ....................................................................... + 4 g Negative limit load factor ...................................................................... - 2 g Maximum recommended wind speeds for operation Steady winds....................................................................... 22 kn (40 km/h) Demonstrated cross-wind component ................................ 16 kn (30 km/h) Capacity MAX ..................................................... lbs ( kg) MIN .................................................. 143 lbs (65 kg) The pilot operates this aircraft at his own risk. Manufacturer __________________________________________ Serial no. __________________________________________ Registration LTZ-Nr __________________________________________ Year of manufacture __________________________________________ Month __________________________________________ Aircraft basic empty weight __________________________________________ C42 SERIES Pilot Operating Handbook POH Issue 4 Rev. 5 Page 39 of 91 10 “Before take-off” checklist 1. Are the seat belts fastened 2. Control system free and correct 3. Parachute system unlocked 4. Check fuel level 5. Engine fuel shut off valve ........................................................ O P E N 6. Electric fuel pump........................................................................... O N 7. Choke .......................................................................................... O F F 8. Carburettor preheating ................................................................ O F F (C42B / C42E / C42C / C42CS) 9. Electric instruments ........................................................................ O N 10. Altimeter set 11. Flaps ..................................................flap position II (take-off/landing) 12. Check magnetos .................................................................................. 13. Wind direction 14. Runway and approach ......................................................... C L E A R C42 SERIES Pilot Operating Handbook POH Issue 4 Rev. 5 Page 40 of 91 11 Approved equipment Engine: ROTAX 912 UL C-gearbox, 2.27 to 1 reduction ratio Approved propellers: - WARP DRIVE 2-blade, 68” diameter - WARP DRIVE 3-blade, 68” diameter - Sport-Prop 170R 3-blade - GSC 3-blade propeller, 68” diameter - Neuform 2-blade CR2-75 ground adjustable propeller - Neuform 3 blade CR3-75 ground adjustable propeller - Kiev Prop 3-blade BB 263/1700 ground adjustable propeller - Helix 3-blade H50F-1,75m-R-SI-12-3 ground adjustable propeller Engine: Rotax 912 ULS C-gearbox, 2.43 to 1 reduction ratio Approved propellers: - WARP DRIVE 3-blade, 68” diameter - GSC 3-blade propeller, 68” diameter - Neuform 3-blade CR3-75 ground-adjustable prop. - Neuform 3-blade CR3-V-R2H in-flight-adjustable prop. - Kiev Prop 3-blade BB 283/1800 ground-adjustable prop. - Helix 3-blade H50F-1,75m-R-S-14-3 ground-adjustable prop - DUC Flash 3-Blatt-Propeller