FLIGHT AND OPERATORS MANUAL Am Flugplatz 11 D
Contents
1. 28 13 Attaching the 1 15 5 522 29 13 1 to the folding mechanism seeee 29 13 2 Attaching the wings to the 1 30 13 3 Folding the wings for hangaring 32 14 Pre flight inspection nennnessnnnnnennnnnnnennnnnnnennnnnnnennnnnnnennnnnnnennnnnnn 33 15 Care and maintenance eese 36 16 Rigging data kaaa akaka Kawawa asana 38 17 Information for ultralights with towing gear 41 17 1 Necessary equipment for towing aircraft 41 C42B Flight And Operators Manual Index Page 17 2 Operating 2 42 17 3 Flight characteristics and performance 44 17 4 ad ya AAA KAA AAA AA ehe 45 17 5 Emergency procedures during towing l 46 18 Inspection and maintenance intervals 48 19 Special features of aircraft equipped for handicapped pilots 53 20 Flying the IKARUS C42 Series with doors removed 55 21 Additional instructions for dropping parachutists from the IKARUS C42 Series a a aa asc o A 56 22 Comco Ikarus Warranty 2 esses 58 C42B Flight And Operators Manual Page 12. Febuary 2012 Amendments No Description Page Date Signature 1 Completely revised All Mai 2010 A Kurz 2 Care and maintenance 32 Odlobet A Kurz 2010 Appendix danuary 3 1 Graphics Page 5 2011 A Kurz January 4 1 Warranty 54 57 2011 A Kurz 5 Ground Handling 16 17 August 2011 A Kurz ndex nevv formatted 16 17 August 2011 A Kurz 6 7 Febuary 6 Helix Prop RS 25 26 2012 A Kurz Control surface Febuary deflections 99 2012 Akura C42B Flight And Operators Manua Page 2 May 2010 IKARUS C42 B C42B Flight And Operators Manual Page 3 May 2010 Introductory remarks This ultralight aircraft has been built in compliance with the airvvorthiness requirements for ultralight aircraft and has been certified in Germany To operate this aircraft the pilot needs a minimum of at least a SPL Sport Pilot Licence or in the case of Austria a valid licence issued by the Austro Control GmbH This aircraft is not to be flovvn unless it is registered and conforms to the relevant air traffic and aviation regulations for ultralight aircraft This aircraft is to be operated only from approved airfields approved instructor prior to flying this aircraft as it possesses characteristics that are unique to ultralight type aircraft Ultralight engines are not certified as aviation engines The flight path must therefore be chosen to ensure that a landing can be undertaken without risk shoul
3. Slowly insert the wing into position with the wing spars into the channels Before inserting into the spar channels make sure that the rear spar is properly positioned on the guide line so that it can be properly locked The right wing needs to be rotated clockwise to orient the locking pin properly the left wing must be rotated anti clockwise By moving slightly upwards the rear wing spar will lock into the locking pin and the forward spar is automatically in the correct position below the locking pin in the forward wing tube Push the forward wing spar into the attachment while slightly lowering the wing tip The forward wing spar will lock into the locking pin Insert the lower end of the wing strutt into the square frame Check that both wing spars have locked properly into place C42B Flight And Operators Manual Page 31 May 2010 Step6 Attention and now immediately 1 insert front wing bolt and safety pin 2 insert rear wing bolt and safety pin 3 insert strut bolt through square frame and struts block 4 all three bolts must have the safety pins 5 lift the wing at the wing tip and check the attachment of the wing strut block to the square frame Repeat Step 1 to 6 for the other wing Remove any control locks used Step 7 attach right and left aileron push rods to the see saw connection Carefully assure that the slide mechanism of the special link connectors are in completely locked position Step 8 left and right landing f
4. The deviation curve for the airspeed indicator can be interpolated from the following table enn 70 sa 90 to rto anto 14o 60 vo 170 60 ro eno Slekter C42B Flight And Operators Manual Page 5 May 2010 1 6 Engine rpm limitations Maximum engine rpm n 5800 rpm 5 min max Maximum continuous rpm n 5500 rpm 1 7 Rpm indicator markings Yellow arc n 5500 5800 rpm Red line n 5800 rpm 1 8 Flap settings Position 1 cruising Position 2 take off landing Position 3 landing 1 9 Propellers for Rotax 912 UL With propeller WARP DRIVE 2 blade 68 1 72 m 9 constant speed pitch 23 5 at 15 75 inches 0 40 m from hub full throttle rom on the ground max 5450 1 min Propeller rom approx n 2400 1 min With propeller WARP DRIVE 3 blade 68 1 72 m 9 pitch 21 0 at 15 75 inches 0 40 m from hub full throttle rom on the ground max 5200 1 min Propeller rom approx n 2300 1 min With propeller Sport Prop 3 blade 68 1 72 m 9 pitch 19 5 at 15 75 inches 0 40 m from hub full throttle rom on the ground max 4900 1 min Propeller rom approx n 2150 1 min With propeller GSC 3 blade 68 1 72 m 2 pitch 21 0 at 15 75 inches 0 40 m from hub full throttle rom on the ground max 4900 1 min Propeller rom 2150 1 min C42B Flight And Operators Manual Page 6 Febuary 2012 With propeller Neuform CR2 75 2 blade 69 1 75 m 2 pitch 27 0 at r 14 37 inches 0 365
5. gt 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 as much as 100 ft 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 The aircraft reacts similarly in all flap positions Stall speeds for the various flap position take off weight 1042 lbs 472 5 kg Vs1 flap position 1 cruising flight ca 40 kts 75 km h Vs2 flap position 2 take off landing ca 38 kts 70km h Vso flap position 3 landing ca 35 kts 65 km h The stall speeds above will be affected slightly with variations in take off weights 4 6 Descent and landing Begin with your approach in plenty of time in order to obtain the correct landing configuration without hurrying Activate carburettor heat The electrical fuel pump must be switched on Reduce airspeed to below Vre 60 kts 105 km h before extending flaps Optimum speed is approx 48 kts 90 km h During final approach maintain an airspeed of at least 48 kts 90 km h with the throttle at idle C42B Flight And Operators Manual Page 14 May 2010 For short landings use flap position 3 landing position The approach can be further shortened by slipping The glide angle in flap position 2 take off landing is significantly s
6. 2 Kinds of operation limitations gt Aerobatics and manoeuvres with more than 60 bank are prohibited Day light VFR conditions only No flight in icing conditions Do not attempt flight in turbulent conditions or in winds exceeding 22 kts 40 km h less if 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 engine Super leaded or unleaded AVGAS 100LL To start the engine Main fuel valve OPEN Electrical fuel pump ON Throttle IDLE Choke OPEN Carburettor heat OFF Ignition both magnetos ON Propeller area CLEAR Brakes ON After engine starts choke CLOSED If the engine does not start repeat the starting procedure C42B Flight And Operators Manual Page 10 May 2010 If the engine has been flooded close main fuel valve open the throttle to half and start the engine When the engine starts guickly reduce the throttle to idle A four stroke engine requires a fairly long warm up period Run the engine at 2000 rpm for at least 2 minutes then increase to 2500 rpm until the oil temperature is at least 122 F 50 C Perform the mag check at 3850 rpm drop should not exceed 300 rpm with a maximum difference between mags of 115 rpm 4 Flight Operations 4 1 Taxiing The nos
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8. about 90 and possibly holding on to the top of the door frame e changing his grip to the lower cockpit frame and the wing strut e leaving the aircraft to the side and in front of the wing strut e ensuring that there is sufficient distance between the parachutist and the propeller 4 Drop procedures After completing the climb to the agreed drop altitude level off the aircraft and continue horizontal flight at an airspeed of 90 to 110 km h Set the flaps to position 1 take off to this end The parachutist opens his waist seat belt takes up his jump position and signals to the pilot that he is ready to jump During the drop the pilot must compensate any balance changes slight climb tendency Once the drop has been completed the pilot should check that no objects have been caught up in the aircraft on the wing strut empennage which could adversely affect the control surfaces The seat belt safety harness on the co pilot seat must be secured During descent airspeed limitations must be observed A debriefing is practical and useful for the future C42B Flight And Operators Manual Page 58 January 2011 22 Comco lkarus Warranty Warranty Information Comco lkarus guarantees to you the original purchaser the microlight aircraft which you have purchased from an authorised Ikarus Flight Center to be in conformance with the applicable Comco Ikarus specifications current at the time of manufacture for a term of two 2 years from
9. accumulated moisture may freeze the brakes or when brakes are overheated C42B Flight And Operators Manual Page 18 August 2011 5 4 Tie Down When parking the aircraft in the open head into the wind if possible Set brakes After completing the preceding proceed to moor the aircraft as follows Tie ropes to the wing tie dovvn fittings upper end of each wing strut Secure the opposite ends of ropes to ground anchors Secure a tie dovvn rope no chains or cables to the exposed propeller shaft and secure the opposite end of the rope to a ground anchor Secure controls to the rearvvard position by using the seat belis Tie Down Points Liftstrut Tie Down Point Propeller Shaft C42B Flight And Operators Manual Page 19 6 Minimum eguipment Four point harness for each seat Airspeed indicator 0 116 kts 0 216 km h Altimeter vv 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 Cf following page C42B Flight And Operators Manual Page 20 May 2010 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 or inches behind the reference datum and then calculated as a percentage of the wing chord Re
10. are clean oil cooler water cooler Check air vents for blockage NACA intake free 2 Landing gear Check secure attachment of all components hub caps brake cylinders brake discs Check for deformation Check air pressure in gas spring damper aircraft level pull aircraft down and release gas spring damper must return to the fully extended position Check pressure and condition of tyres 3 Left wing Wing spar connections secure Wing struts properly attached and secure Auxiliary struts secured with quick release fasteners Pitot tube secure and free from blockage and water Check aileron shift levers and push rods by opening the zips on the underside of the wings C42B Flight And Operators Manual Page 34 May 2010 Check condition of fabric covering tears etc Check profiled struts for secure attachment Check wing tips and wing tube for deformation Check attachment of ailerons and flaps 4 Left side of fuselage Check condition of glass fibre fairing cracks holes etc Check secure attachment of glass fibre fairing check for missing screvvs at the upper underside connection Check elevator shift lever through the inspection hole in the fuselage wall baggage compartment Tank filler cap secure 5 Empennage Check attachment of horizontal stabiliser Check control surface hinges Check elevator inter connection Trim flap secure Check elevator push rod connections Horizo
11. be reduced and the towing speed increased immediately If this is not possible the towing cable should be released NOTE If possible the pilot of the towing aircraft should inform the glider pilot before releasing the towing cable During towing Lateral displacement of less than 30 vertical displacement of less than 30 high and 20 low can be corrected using the rudder and elevator In the case of greater displacement angles particularly high vertical displacement angles the towing cable should be released by the towing pilot Avoid circling with a long towing cable When circling make sure that the turn radius is sufficiently large so that the glider can follow the towing aircraft C42B Flight And Operators Manual Page 47 May 2010 If there is a danger of exceeding the maximum engine temperatures oil and cylinder head temperature reduce engine rpm and increase the towing speed c Failure of the release mechanism If the release mechanism of the towing aircraft fails execute final approach over an obstacle free area and land with tow hook released If both release mechanisms fail execute descent but do not exceed the maximum rate of descent of 295 3 ft min 1 5 m s and land with the tow hook released by employing the brake flaps of the glider make sure that towing cable is tense C42B Flight And Operators Manual Page 48 May 2010 18 Inspection and maintenance intervals NOTE The inspection and m
12. cause a slight nose heavy moment After reaching the safety altitude the electrical fuel pump can be switched off Trim the aircraft for 54 kts 100 km h and continue climb Slight right rudder is necessary to compensate both engine and propeller torque during climb Whenever possible take off into the wind The maximum demonstrated crosswind component for take off and landing is 16 kts 30 km h No special procedures are required The classical low wing procedure suffices keep luvward wing low and carry out course corrections using the rudder During the intial 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 for a gliding speed of 49 kts 90 km h push stick forward Avoid obstructions Using the flaps touch down at 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 C42B Flight And Operators Manual Page 12 May 2010 4 3 Cruising flight In cruising flight the most economical cruise speeds are between 70 and 90 kts 130 170 km h The power settings required depend upon aircraft load Max continous engine speed is 5500 rpm In order to fly the aircraft comfortably it should be tr
13. check that the throttle is still in the full throttle position 5 Excepting power changes LH remains constantly on the rudder control lever The various flight conditions e g horizontal flight turn slow flight side slip are not affected Landing Approach procedures are normal In the case of side wind we recommend a wing down approach Attention should be paid to the following when flaring out 1 Air speed approx 100 km h until flare out in approx 4 to 5 m above the runway LH on the rudder control lever 2 Throttle to idle using LH 3 LH immediately back to rudder control lever and steer aircraft during landing roll When carrying out circuits touch and go follow the procedures for take off C42B Flight And Operators Manual Page 55 May 2010 20 Flying the IKARUS C42 Series with doors removed Under the following conditions the micro light aircraft IKARUS C42A C42B may be flown with the doors removed All loose objects charts documents are properly secured e Objects may under no circumstances be dropped out of the aircraft during flight e Maximum speed for flights with one or both doors removed is 150 km h IAS e Side slipping is not permitted with doors removed e Turbulence in the cockpit will increase when the flaps are set to position Ill C42B Flight And Operators Manual Page 56 May 2010 21 Additional instructions for dropping parachutists from the IKARUS C42 Series 1 Per
14. increase recommended towing speeds and take off distances depending upon the type of glider Appropriate instructions from the glider manufacturer should be follovved Rain or dirt particles have no significant influence on the performance of the IKARUS C 42 when towing Headwinds will reduce the take off distance as follows 10 kt take off distance with no wind x 0 7 20 kt take off distance with no wind x 0 65 30 kt take off distance with no wind x 0 6 c nstructions for towing operations Electrical fuel pump must be switched on while towing Test the tow hook before each tow Check the towing cable and the weak link for mechanical damage before each tow 17 4 Placards Nextto the airspeed indicator Observe towing speed Onthe release lever Tow hook pull open Onthe tow hook mount Weak link max 660 lbs 300 daN C42B Flight And Operators Manual Page 46 May 2010 17 5 Emergency procedures during towing a During take off Should one of the following situations arise the towing cable should be released by the towing pilot if the glider breaks out and the glider pilot does not react if the glider climbs above the tovving aircraft and the attitude of the tovving aircraft is no longer properly controllable if the tovving aircraft climbs prematurely and the tovved glider cannot follovv due to a lack of speed high surface loading vvater ballast etc the rate of climb of the towing aircraft should
15. the date of purchase of the aircraft Warranty Term This is the complete and exclusive warranty for a microlight aircraft and in lieu of all other warranties terms and conditions whether express or implied In no event shall Comco Ikarus be liable for damages nor loss in excess of the purchase price nor for any incidental special or consequential damages including without limitation loss of use loss of time inconvenience commercial loss lost profits or savings arising out of the use or inability to use the aircraft to the full extent such may be disclaimed by law This Warranty does not affect any statutory rights that you may have if you are a consumer such as a warranty of satisfactory quality and fit for the purpose for which products of the same type are normally used under normal use and service nor any rights against the seller of the aircraft arising from your purchase and sales contract How to get Warranty Service Should the microlight aircraft not comply with the warranted specifications the warranty claim consists of a repair of the defect by Comco lkarus at no charge You must inform Comco lkarus of the lack of conformity to the applicable specifications of the microlight aircraft promptly if you detect a defect in material workmanship or lack of conformity and in any event within a term not to exceed the Warranty Term and must immediately submit the aircraft for service to an authorised Ikarus Flight Center Ika
16. 0 2 3 54 0 39 90 mm 10 mm 9 84 250 mm Down 14 2 2 76 0 39 70 mm 10 mm 9 84 250 mm Rudder Left 32 f 2 8 86 0 39 210 mm 10 mm 16 24 410 mm Right 32 2 8 86 0 39 210 mm 10 mm 16 24 410 mm Elevator Up 28 2 8 27 0 59 210 mm 15 mm 16 24 410 mm down 20 2 5 12 0 59 130 mm 15 mm 16 24 410 mm Flaps Note Flap angle is measured at the flap underside relative to the underside of the wing at the root area tangent forward to rear spar Position 1 5 t 1 1 06 0 39 27 mm 10 mm 12 20 310 mm cruise Position 2 11 1 2 36 0 39 60 mm 10 mm 12 20 310 mm take off landing Position 3 32 1 6 69 0 39 170 mm 10 mm 12 20 310 mm landing Trim flap Lever nose dovvn Trim flap relative to rudder surface 5 5 C42B Flight And Operators Manual Page 40 May 2010 d Landing gear Main landing gear 2 0 2 5 bar 29 36 psi Nose landing gear 1 6 2 0 bar 23 29 psi Shock absorbers 28 0 34 0 bar 400 490 psi Amount of oil 0 42 pts 200 ml Hydraulic oil HVP 10 e Brakes Always use low viscosity mineral oil CASTROL LHM 1756 or PENTOSIN LHM Citroen Never use Glykol based brake fluid f Powerplant Torque moment for propeller attachment screws 25 Nm Torque moment for propeller blade setting screws 12 15Nm C42B Flight And Operators Manual Page 41 May 2010 17
17. 4 kts 90 100 km h look for a suitable landing field taking wind conditions into consideration The best glide ratio is approx 11 1 at 490 ft min 2 5 m s A lower sink rate can be achieved with flap position 2 take off landing approx 46 kts 85 km h it does not however result in a better glide angle With sufficient altitude you may attempt to restart the engine check 1 Fuel valve OPEN 2 Magneto switches ON 3 Fuel SUFFICIENT 4 Fuel pump ON lll Starting the engine in flight both magneto switches ON electrical fuel pump ON throttle Ya OPEN carburettor heat OFF fire up engine using starter Maintaining airspeed to windmill the prop can help C42B Flight And Operators Manual Page 16 May 2010 4 9 Emergency procedures VI Vil Vill In slow flight if a wing drops Reduce back pressure on the stick and lower the nose Recover Sideslipping Rudder in the opposite direction to the sideslip Reduce back pressure on stick Spins Throttle to idle Full rudder opposite to the direction of rotation Reduce back pressure on stick Slowly pull aircraft up Spiral dive Aileron and rudder opposite to the direction of rotation and pull back stick slightly Loss of elevator control Using the elevator trim flap the aircraft can be trimmed to speeds between 43 and 92 kts 80 und 170 km h In calm weather conditions it can also be used to try to land the aircraft If in doubt deploy the par
18. FLIGHT AND OPERATORS MANUAL Ultralight Aircraft IKARUS C 42 Issued Febuary 2012 This Flight Manual belongs to aircraft Type IKARUS C 42B Registration No Serial No Manufacturer COMCO IKARUS Leichtflugzeuge SN Am Flugplatz 11 D 88367 Hohentengen Germany Owner This handbook is to be kept in the aircraft at all times The described options of use for the C42B are certified for Germany and have been tested in Germany Please note that for using the C42B as a towplane 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 C42B Flight And Operators Manual Index Page Title page of contents Correction status 1 3 side view 2 Introductory remarks 3 1 Operating 2 4 1 1 8 ALA ae nen 4 1 2 Weights LE 4 1 3 Structural limitations areas een 4 1 4 Center of gravity limits 4 1 5 Airspeed 1145 5 4 1 6 Engine rpm limitations 66 5 mH 5 1 7 Rpm indicator markings Yellow arc n 5500 5800 rpm 5 1 8 Flap settinigs ie tte BUL 5 1 9 Propellers for Rotax 912 1 5 1 10 Propeller s for Rotax 912 UL 5 7 1 11 Engine limitations according to the Rotax operatin
19. Information for ultralights with towing gear l Glider towing 17 1 Necessary equipment for towing aircraft If the following additional equipment is installed the ultralight aircraft may be used to tow gliders 1 Powerplant Rotax 912 UL S 74 kW 100 hp Warp Drive 3 blade 68 diameter Neuform 3 blade CR3 75 ground adjustable Neuform 3 blade CR3 V R2H in flight adjustable Kiev Prop 3 blade BB 283 1800 ground adjustable 2 Tow hook mount 3 Tow hook 4 Comco release mechanism operated by the pilot 5 Rear mirror camera system 6 Engine monitoring instruments with appropriate markings 7 Placards at the airspeed indicator and tow hook Installation must follow the relevant instructions from the manufacturer Unauthorised alteration of the towing equipment is prohibited Towing cable and weak link Only cables which fulfill aviation DIN or factory standards may be used if these standards specifications are detailed enough and long term delivery quality is assured The cable connection must be protected against wear and tear by an appropriate cover C42B Flight And Operators Manual Page 42 May 2010 When using a towing cable without a weak link the true ultimate load of the towing cable must not exceed 300 daN In the case of cables with a higher ultimate load a weak link must be integrated to protect the ultralight aircraft and the glider Length of towing cable 131 197 ft 40 60 m Max nominal ultimate strength at wea
20. NTION Follow the instructions in the Rotax 912 operator s manual C42B Flight And Operators Manual Page 29 May 2010 13 Attaching the wings 13 1to the folding mechanism As an option the IKARUS C42B is also available with a folding wing thus reducing the amount of hangar space reguired For road transport the wings must however be removed completely The wings are attached to the folding mechanism as follovvs 1 Remove the stop ring from the slide tube 2 Place the vving parallel to the fuselage vvith the rear vving tip on the ground 3 Lift the vving and slide the attachment block 2 5 inches 5cm over the slide tube 4 Attach the stop cable to the latch in the middle of the slide tube Re attach the stop ring to the end of the slide tube If both wings are in the folded back position your C 42 can be easily moved by one person into the smallest of spaces in the hangar C42B Flight And Operators Manual Page 30 May 2010 13 2Attaching the wings to the fuselage The wings are attached to the fuselage as follovvs Step 1 Step 2 Step 3 Step 4 Step 5 Bring the vving main strut into correct position to the vving and attach the auxiliary struts at front and rear spar Grip the main strut and raise the vving tip Keeping the vving in a vertical position carry the wing forward at 90 to the fuselage Turn the wing into a horizontal position keeping the wing tip slightly higher than the wing root
21. Type Owner Registration No Total Flight Hours until Defect Engine Airframe Total Flight Hours Pilot on UL Aircraft Description of Damage Damage Report Name Date Signature C42B Flight And Operators Manual Appendix Page 4 C 42 Flight Manual Inspections performed Type C 42B Serial No Registration No Date Type of inspection Recognised expert C42B Flight And Operators Manual Appendix Page 5 Location of parachute rescue system C42B Flight And Operators Manual Appendix Page 6 Exit opening E Appendix Page 7 C42B Flight And Operators Manual Pd T ALS s uo4 y perg dd rq sr uneg z d dey AE JN 2 2 Bz 18 8 nr ydd rq 19p sdu puns D Ui Ot Sn z nm u l U C42B Flight And Operators Manual ZS sean Appendix Page 8 Bannerschlepp Blatt 2 von 5 Appendir Page 9 C42B Flight And Operators Manual g uoa c peig ddopgosisuueg x c ol C A Eo Sunjddmy 1801 M sojsm 2 Todoyos91sny rn yz ebnezOninuoie Appendix Page 10 C42B Flight And Operators Manual 0 p eig dd yy ss uneygi Aes 74 Y EI zu 22 onu S
22. YR eBnezBninuoie1 ee Appendir Page 11 C42B Flight And Operators Manual S FO a8nd sauung S U04 perg ddejgosronueg dy 760 WX p mpa dH c amp 0 0067 X 1 x 07 eqm ry Mauupg wbs gg fo iauueg ub g uoa oduejspdoyw 25 MN 05 n od uoynindas pasoddng NEP 05 ff sq niqiyo 2 dy p o Wpraosssunersmqus 0097 uue g agni prog 0067 Sdugysgdoyy 9 10 0I 3 ey Hd D3NDJ Appendix Page 12 C42B Flight And Operators Manual TTE 48puas ZIG xoro ayya dusg yo epg wou olg 3102415 an q ang Japuss aunssaud jo 20 3 150 WA qerrH 8002 20 81 HPI 1501 ng umoja ML pai YE 2002TVZ0 Ad s Wo Japuss 5 zi UMOJA 1 01974 pau m uaaJfi apa sword d sdwo B 5 youoj do S z 2 4 Says PH vs BU Aaa PIA UM Dao iin 141401 ov 50013 E vs sov 17 UMOJA
23. achute rescue system Loss of aileron control Use the rudder to create a roll moment due to side slip If in doubt deploy parachute rescue system Loss of rudder control Flat curves can be flown using the aileron Eventually while flying straight ahead emergency landing If in doubt deploy parachute rescue system Carburettor fire Main fuel valve OFF Electrical fuel pump OFF Full throttle Slip the aircraft Follow emergency landing procedures C42B Flight And Operators Manual Page 17 August 2011 5 Ground Handling 5 1 Towing Moving the aircraft by hand 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 turned by pivoting it about the main wheels 5 2 Hoisting The aircraft may be lifted with a hoist of at least 1000 Ib 0 5 tons capacity by using a ceiling hangers T support Using suitable spring snap hooks they can be hooked in at the brackets installed at the aircraft 5 3 Parking Parking precautions depend principally on local conditions As a general precaution set parking brake or chock the wheels and lock the controls In severe weather and high 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
24. aintenance instructions in the operating handbook for the E 85 tow hook must be followed at all times The maximum operating time of the tow hook between two general overhauls is 2 000 take offs or 10 000 releases The weak link must be replaced every 200 tows In addition to the inspection and maintenance instructions in the operating handbook for the E 85 tow hook the following should also be considered Check Bowden cable for freedom of movement and damage near the release lever and near the before each towing flight tow hook Check release force at release lever with every 200 tows unloaded tow hook lt 13 daN Clean and grease the bowden cable at the adjustment openings near the release lever and every 200 tows the tow hook C42B Flight And Operators Manual Page 49 May 2010 ll Banner tow 1 Equipment in the tow plane In order to perform a banner tow the aircraft must be equipped with the same equipment as described above for sailplane towing The following propellers are approved for banner towing when the aircraft is powered by a ROTAX 912 UL 80 PS Warp Drive 3 bladed 68 Neuform CR3 75 3 bladed ground adjustable propeller Kiev Prop BB 263 1700 3 bladed ground adjustable propeller Banners may only be picked up and towed according to approved procedures and by aircraft with the appropriate equipment Banners must be made of water repellent material Only banners may be used which fulfil the design requireme
25. d an engine failure in flight materialise Unauthorised alterations to the control system structure wings and engine are prohibited All in service problems and equipment failures are to be reported to the manufacturer or the appropriate national authority For fire safety reasons smoking is prohibited on board the aircraft C42B Flight And Operators Manual Page 4 May 2010 1 Operating limitations 1 1 Airspeeds Never exceed speed 116 kts 216 km h Speed in turbulent air Vg 180 km h Maximum manoeuver speed VA 139 km h Stall speed flap position 1 Vsi 75 km h flap position 2 Vs 70 km h flap position 3 Vs 65 km h 35 kts During speeds exceeding VA only little rudder movements are allowed 1 2 Weights Empty weight cf current weighing record Maximum take off weight 1041 165 472 5 kg Maximum payload cf page 18 Minimum payload 144 Ibs 65 kg 1 3 Structural limitations Positive limit load factor 44g Negative limit load factor 2g 1 4 Center of gravity limits Reference datum Wing leading edge at a rib station Forward center of gravity 11 8 inches aft of datum 300 mm Rearward center of gravity 20 4 inches aft of datum 520 mm 1 5 Airspeed markings White arc 38 57 kts 71 105 km h Green arc 43 97 kts 79 180 km h Yellow arc 97 116 kts 180 216 km h Yellow triangle Vy 51 kts 95 km h Yellow line Va 75 kts 139 km h Red line Vne 116 kts 216 km h
26. e 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 winds 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 make certain the runway and the traffic pattern is clear before you taxi to the take off positon Set trim to neutral Wing flaps in take off position flap position 2 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 unstick at approx 27 kts 50 km h Accelerate with the nose wheel 2 4 inches 5 10cm off the ground C42B Flight And Operators Manual Page 11 May 2010 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 kts 7Okm h Stick slightly forward and increase airspeed to 54 kts 100 km h in shallow climb Continue to climb at 54 kts 100 km h Retract flaps at a height of approx 150 ft This will
27. equipment for handicapped pilots is not permitted 2 Installation Removal The rudder control lever is attached to the axle in the fuselage and screwed in place using a hexagonal M8xM40 screw The push rod which is attached to the rudder control lever is connected to the right pedal of the left seat by a quick release fastener The sliding sleeve of the quick release fastener is then checked for proper fit in the locked position Throttle lever length is then set so that the knob is approximately ten to thirty millimetres under the rudder control lever and has free movement under the latter The equipment is removed in reversed order C42B Flight And Operators Manual Page 54 May 2010 3 Operation The nose wheel and the rudder are activated via the rudder control lever which is operated by the left hand By pulling out the lever the aircraft is turned to the left by pushing it in the aircraft turns to the right The right hand remains constantly on the control stick and operates the elevator aileron and brakes The left hand operates the rudder control lever and the throttle which is located directly below the rudder control lever Take off 1 Line up the aircraft on the runvvay left hand LH on rudder control lever 2 Apply throttle expeditiously with LH 3 LH immediately back to the rudder control lever and steer aircraft during take off run 4 After take off in approximately 5 to 10 m above the runway use LH to
28. ference datum leading edge wing chord 53 5 inches 1360 mm determine measurements a and b center of wheel axle D xmm a 7 05 mm Git G2 AE o iit fed 1360 mm C42B Flight And Operators Manual Page 21 May 2010 Empty weight center of gravity Serial No Basic empty weight standard equipment kg Operating empty weight incl optional equipment kg Typ C 42 B Aircraft data sheet No a mm b mm Gir Gu kg Go kg G total It is the pilot s resb nsibility to ensure that the MTOW of 1041 Ibs 472 5 kg is not L exceeded Xs mm mm Xs max useful load kg MTOW 472 5 kg Wai abu ipie eden hes Signature Loading plan position weight x lever arm torque 1 se 2 fu 3 b ats el aggag total weight center of gravity CG total weight allowed range for CG 300 560 mm behind zero datum leading edge empty weight CG 280 460 mm behind zero datum leading edge C42B Flight And Operators Manual Page 22 May 2010 Loading plan weight x EK arm torque kp 1 seats 40 2 fuel 95 3 baggage 130 otal weight kp total torque center of gravity CG total weight allowed range for CG 300 560 mm behind zero datum leading edge empty weight CG 280 460 mm behind zero datum leading edge Loading plan weight x DEZ arm torque kp 1 1 seats 40 2 fuel 95 3 baggage 130 total weight kp total torque cente
29. g manual 8 2 Kinds of operation 52 9 3 Operation of the Engine esee 9 4 Flight Operations AA ea 10 4 1 AA 10 42 Take off AUA 10 43 Gruising flight ra ELLI 12 4 4 TUNGA al uwa 12 4 5 Stalls et KA t eme PED teo 13 4 6 Descent and landing 13 4 7 Shutting down the engine 14 4 8 Sudden loss of engine power 14 4 9 Emergency procedures WA 16 C42B Flight And Operators Manual Index Page 5 Ground Handling eese nennen 17 n NEN 17 52 Bloistirigic ie nt eee eb e 17 5 3 Parking nene dene ERHEeSRPIS 17 9 4 TIec DOWD Saison tec trem ede cendo 18 6 Minimum equipment 19 1 Dimensions e 19 8 Weight and balance eese YR R YY R nnn nnns 20 9 Data placard and checklist eee 23 10 Before take off checklist eee 24 11 Equipment 2 22 22 Herne an 25 12 Flight performance nnne 27 12 1 Take off 161 eects a e e AE a i a e 27 12 2 Climb 5 27 12 3 Cruise performance solo 28 12 4 Engine off
30. hallovver and the flare distance thus much longer At approximately 10 ft 3m begin rounding out to the landing flair Begin final flair at about 2 ft 0 6 m Landing speed is approx 35 kts 70 km h 4 7 Shutting dovvn 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 and radios before shutting down the engine 4 8 Sudden loss of engine power Loss of engine power during take off Depending upon speed and altitude lower nose and trim for gliding speed 48 54 kts 90 100 km h Do not attempt to return to airfield if altitude is below 260 ft 80 m 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 high grass reduce speed immediately overhead by extending the flaps to position 3 landing pull stick full aft and allow the aircraft to sink into the grass C42B Flight And Operators Manual Page 15 May 2010 II Loss of engine power during cruising flight Cross country flights should be planned to ensure that a suitable landing field can be reached in the case of loss of engine power Once gliding speed has been established flaps position 1 cruising flight Vias 48 5
31. ight performance 12 1 Take off distance Rotax 912 UL Rotax 912 ULS Sea level 15 C no wind Take off roll gross 345 ft 105 m 310 ft 95 m 1041 65 472 5 kg Take off distance over 50 ft 15 m obstacle solo 700 ft 210 m 605 ft 185 m gross 800 ft 245 m 705 ft 215 m Take off speed 38 kts 70 km h 38 kts 70 km h Speed at 50 ft 49 kts 90 km h 49 kts 90 km h 15 m obstacle Higher elevations and higher temperatures lengthen the take off distances The figures given are valid for a MTOW of 793 Ibs 360 kg flown solo and 1041 lbs 472 5 kgs with two persons on board No wind on dry even ground with short grass 12 2 Climb performance Sea level 415 C no wind Engine speed 5500 rpm 5200 rpm Rate of climb solo 1180 ft min 6 0 m s 1377 ft min 7 0 m s gross 944 ft min 4 8 m s 1082 ft min 5 5 m s Speed for best 49 kts 90 km h 49 kts 90 km h rate of climb C42B Flight And Operators Manual Page 28 May 2010 12 3 Cruise performance solo at engine speed 86 kts 160 km h 92 kts 170 km h 4700 rpm 65 Cruise speed 76 kts 140 km h 78 kts 145 km h for best range Maximum range with 14 3 imp fuel ca 350 nm 650 km 350 nm 650 km gallons 65 hand no wind 12 4Engine off performance MTOW 1041 Ibs 472 5 kg Minimum sink rate 393 ft min 2 m s at 46 kts 85 km h flap position 2 take off landing Best glide angle 1 to 11 at 51 kts 95 km h flap position 1 cruise ATTE
32. immed for 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 rpm 4500 rpm Airspeed 81 kts 150 km h 86 kts 160 km h Fuel flow 2 20 2 64 gph 2 42 2 86 gph 10 12 I h 11 13 I h The maximum speed of 116 kts 216 km h must never be exceeded In turbulent air the maximum airspeed is 97 kts 180 km h At the first indication of carburettor icing rpm drop rough engine increase in fuel consuption 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 co ordinated using the aileron and rudders The necessary amount of rudder deflection lessens with increased airspeed 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 C42B Flight And Operators Manual Page 13 May 2010 4 5 Stalls In cruising flight configuration flap position 1 the stalling speed is 39 kts 75 km n The engine cowling will be well above the horizon At approximately 43 kts 80 km h there will be a slight buffeting of the airframe When flown in this condition the aircraft is fully controllable However lateral attitude corrections must be done mainly with the rudder Example right wing low
33. k link 660 Ibs 300 daN Joining ring pair on towing cable according to LN 65091 17 2 Operating limitations a Permissible take off weights The ultralight aircraft IKARUS C 42 B is certified for glider towing with a maximum take off weight of 1433 Ibs 650 kg The maximum take off weight of the towing ultralight is 882 lbs 400 kg The maximum take off weight of 1041 lbs 472 5 kg of the towing ultralight may only then be used to the full if the weight of the glider does not exceed 882 lbs 400 kg Take off weight kg o o a 450 Towing capacity glider kg 400 400 450 MTOW IKARUS C42 kg C42B Flight And Operators Manual Page 43 May 2010 b Towing speeds The minimum speed of the tug glider combination depends upon the type of glider being towed It however must not be lower than the minimum tovving speed for the IKARUS C 42 Vmin tow 49 kts 90 km h Depending upon the take off weight of the IKARUS C 42 the following flap positions should be used at towing speeds below 53 kts 97 5 km h Take off weight below 882 lbs 400 kg Flap position 1 Take off weight between 882 lbs 400 kg and 1041 Ibs 472 5 kg Flap position 2 The minimum speed of the majority of modern gliders generally lies above that of the ultralight towing aircraft This means that the minimum speed of the combination depends upon the operating limitatio
34. karus Flight Center ITB Ikarus Technical Base ISC Ikarus Service Center f periodical inspections should be conducted by the owner himself these technical documents have to be ordered at IFC ITB ISC or directly at COMCO IKARUS GmbH in Hohentengen 7 Technical problems Technical problems or defects should be reported to the manufacturer the relevant national authority C42B Flight And Operators Manual Page 38 May 2010 16 Rigging data Wing span 30 84 ft 9 40 m Wing area 140 4 ft 13 05 m VVing chord at root 4 79 ft 1 435 m Wing dihedral 1 a Incidence angle of wing relative to fuselage main tube 8 5 Note The vving angle is the angle betvveen the lovver edge of the rear wing tube and the lower edge of the forward wing tube at the root rib b Incidence angle of stabiliser relative to the fuselage main tube 7 Note The stabiliser incidence angle is the angle betvveen the lovver edge of the forvvard tube and the lovver edge of the rear stabiliser tube Incidence angle difference between wing and stabiliser at the root rib 1 5 C42B Flight And Operators Manual Page 39 Febuary 2012 c Control surface deflections Note The angle of the aileron underside relative to the wing chord is 7 tangent forward to rear spar It is defined by the length of the aileron push rods 0 Distance from axis of rotation Aileron neutral p 7 t 1 1 38 0 39 35 mm 10 mm 9 84 250 mm Up 2
35. laps must be locked Step 9 position and fasten wing center section fairing C42B Flight And Operators Manual Page 32 May 2010 13 3Folding the wings for hangaring 1 Remove wing center section fairing 2 Unlock aileron push rods from see savv cross connection 3 Unlock landing flaps 4 first unlock strut block from lower square frame by removing strut bolt second unlock rear vving spar by removing vving bolt third unlock front wing spar by removing wing bolt The following 5 steps must be undertaken to fold back the wings Step 1 Lift right wing at the wing tip rotate slightly to unlock firest the forward wing spar and then the rear one Step 2 Draw the wing back off the fuselage until the stop ring on the slide tube is reached Step 3 Turn the vving into a vertical position underside of the vving forvvard Step 4 Swing wing tip back Step 5 Place wing tip on to the retainer bracket on the empennage Repeat steps 1 to 5 for the left vving C42B Flight And Operators Manual Page 33 May 2010 14 Pre flight inspection Before each flight the pilot must carry out a visual inspection of the aircraft 1 Engine Check propeller and spinner for damage and security Check cowling near the propeller for abrasion sign of defective engine suspension or improper covvling attachment Check for leakage under the engine cowling Check cooling liguids and lubricants Check engine cowling for security Check that coolers
36. m full throttle rom on the ground max 5100 1 min Propeller rom approx n 2250 1 min With propeller Neuform CR3 75 3 blade 69 1 75 m 2 pitch 24 0 at r 14 37 inches 0 365 m full throttle rom on the ground max 4800 1 min Propeller rom approx n 2100 1 min With propeller Kiev Prop BB 263 1700 3 blade 1 71 m 2 Pitch 22 0 at r 0 4 m from hub full throttle rom on the ground max 4800 1 min propeller rom approx n 2100 1 min With propeller Helix H50F 1 75m R SI 12 3 3 blade 1 75 m Pitch 16 0 at r 656 mm full throttle rom on the ground max 4880 1 min propeller rom approx n 2150 1 min C42B Flight And Operators Manual Page 7 Febuary 2012 1 10Propeller s for Rotax 912 UL S With propeller WARP DR VE 3 blade 68 1 72 m pitch 25 0 at 15 75 inches 0 40 m from hub full throttle rom on the ground max 5200 1 min Propeller RPM approx n 2150 1 min With propeller GSC 3 blade 68 1 72 m 9 pitch 25 0 at 15 75 inches 0 40 m from hub full throttle rom on the ground max 4900 1 min Propeller rom approx n 2000 1 min With propeller Neuform CR3 75 3 blade 69 1 75 m 2 pitch 27 0 at r 14 37 inches 0 365 m full throttle rom on the ground max 4800 1 min Propeller rom approx n 2000 1 min With propeller Neuform CR3 V R2H 3 blade 69 1 75 m adjustable pitch 16 30 at r 29 53 inches 0 75 m full throttle rom on the ground max 4200 5600 1 min Propeller rom appro
37. meter 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 Motor Rotax 912 UL S 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 adiustable prop Approved parachute rescue systems BRS 5 UL4 BRS 6 1050 SP DAeC Magnum 450 Speed MTOW 450 kg only Magnum High speed Soft pack Magnum Lightspeed Soft pack C42B Flight And Operators Manual Page 26 May 2010 Be certain to follow the instructions of manufacturer for installation reguired maintenance and particularly the avoidance of moisture in the parachute pack Should the chute get wet it must be aired and repacked There is a time limit on the use of the rocket cartridge in rocket deployed systems Before taking off remove the system safety pin After landing secure the system vvith the safety pin Fuel tank capacity approved versions 1 xor 2x 11 imp gallons 50 1 x or 2x 14 3 imp gallons 65 Aluminium wings Electrical flap drive C42B Flight And Operators Manual Page 27 May 2010 12 Fl
38. nce of the aircraft by Ikarus Flight Centers or Ikarus Service Centers only therefore it is important to keep a record of any previous repairs and make them available if questions arise concerning maintenance C42B Flight And Operators Manual Page 60 January 2011 Conditions This warranty will not apply if the type or works number on the aircraft has been altered deleted duplicated removed or made illegible Comco Ikarus reserves the right to refuse free of charge warranty service if the reguested documentation cannot be presented or if the information is incomplete illegible or incompatible with the factory records Repair at Comco Ikarus option may include the replacement of parts or accessories with functionally equivalent reconditioned or new parts Replaced parts or accessories are warranted for the balance of the original warranty time period The Warranty Term will not be extended All original parts and accessories that have been replaced shall become the property of Comco Ikarus Comco Ikarus does not warrant the installation maintenance or service of the products parts and accessories Comco Ikarus will not be responsible in any way for problems or damage caused by any ancillary equipment not furnished by Comco Ikarus which is attached to or used in connection with the aircraft or for operation of Comco Ikarus equipment with any ancillary equipment and all such equipment is expressly excluded from this warranty When
39. ng to verify any vvarranty claim All plastic surfaces and all other externally exposed parts that are scratched or damaged due to customer normal use Periodic maintenance and repair or replacement of parts due to normal wear and tear C42B Flight And Operators Manual Appendix Placards Topic Aerobatics vvarning Trim Flaps mechanical Engine oil specifications Fuel specifications Baggage loading opening Deviation table Levers Choke Heating Carburettor heat Fuel valve Data placard Type placard fire resistant Appendix Page 1 Location Instrument panel Roof frame Roof frame Oil control cap Fuel filler cap Baggage compartment Instrument panel Center console Center console Center console Fuselage tube behind tank C42B Flight And Operators Manual Appendix Page 2 Data placard Type IKARUS C 42 B Manufacturer OMCO IKARUS GmbHD 88367 Hohentengen Germany Serial No Year of production Never exceed speed 116 kts 216 km h Stall speed 35 kts 65 km h Structural limitations positive limit load factor 4g negative limit load factor 2g Load limits Maximum take off weight 1041 Ibs 472 5 kg Minimum useful load 143 Ibs 65 kg Useful load according to flight manual page 17 and 18 C42B Flight And Operators Manual Service Problem Report Form UL Aircraft Type Year of Manufacture Manufacture Appendix Page 3 Serial No Engine
40. ns of the glider In consultation with the glider pilot particular attention must be paid to the minimum speed during the entire towing procedure Maximum towing speed with the flaps in position 1 is 81 kts 150 km h In order to achieve optimum performance during take off and the towing of slow flying gliders towing with flaps in flap position 2 is permitted IMPORTANT Before towing the pilot of the towing aircraft and the pilot of the glider must agree on the towing speed C42B Flight And Operators Manual Page 44 Mai 2010 17 3 Flight characteristics and performance a Flight performance Glider take off weight 860 Ibs 390 kg Runvvay conditions dry grass Temperature 15 C Elevation 0 ft ASL Take off distance 50 ft Towing speed Rate of climb obstacle kts IAS ft min ft Take off weight of glider Ibs Type of glider 683 Ibs Standardlibelle 816 Ibs LS4 860 Ibs Kestrel 1300 Ibs ASK 21 1433 Ibs Duo Discus b External factors e Increase take off distance by 5 for every 10 C increase in ambient air temperature e Increase take off distance by 10 for every 1000 ft increase in pressure altitude e Decrease take off distance by 10 when taking off from a paved runway C42B Flight And Operators Manual Page 45 May 2010 A wet grass runway can considerably increase the take off distance Dirt on the glider surface particularly on the wing leading edge and raindrops can
41. ntal tail struts secure deformation Rudder cables secure Check fabric covering tears abrasion 6 Right side of fuselage Check condition of glass fibre fairing cracks holes etc Check secure attachment of glass fibre fairing missing screws etc 7 Right wing cf left wing C42B Flight And Operators Manual Page 35 May 2010 8 Cabin inside and outside Check condition of windscreen doors including locking mechanism cracks Check freedom of movement of controls stick pedals flap lever flap lever detent Check brake lever and detent Aileron shift lever secure Visually check aileron cables and pulleys Check fuel valve 9 Instruments Power supply ignition switch in position 1 Altimeter reading Amount of fuel Radio and intercom in working order 10 Drainage Drainage of the fuel tanks the drainage tap is located under the copilots seat C42B Flight And Operators Manual Page 36 October 2010 15 Care and maintenance 1 Care and cleaning All metal parts are corrosion resistant and reguire no special care Dirt on the aircraft and the fabric can be removed by using clear water Repair of the wing fabric Fix the smallest rips for your safety A wing fabric repair kit is available from the manufacturer Attach the patch on clean grease free area using contact cement Larger rips in the fabric or along the seams must be repaired by covering experts When in doubt contact the man
42. nts defined by the organisations DAeC and DULV 2 Limitations a Maximum permissible banner drag 80 daN b No of occupants 1 pilot or 2 pilots during tow training Warning Do not exceed maximum take off mass c Weak link rating tow rope Banner tow 100 daN d Length of tow rope Laid out banner 40 60m Rolled banner 25 40m e Speeds Minimum airspeed 85 km h Best rate of climb airspeed 95 km h Airspeed during tovv 100 km h Maximum airspeed 120 km h Flaps must be retracted at airspeeds above 105 km nl C42B Flight And Operators Manual f Banner size Rotax 912 UL 80 PS Rotax 912 ULS 100 PS Maximum banner height Maximum banner mass 3 Placards a In full view of the pilot on the instrument panel Aero tovving Page 50 May 2010 120 m 150 m 5m 20 kg Operating conditions for banner tow are to be found in the supplement to the Pilot s Operating Handbook b On the airspeed indicator Watch airspeed during tow c On the release lever Aero tow coupling pull open 4 Emergency procedures Banner tow Inthe case of an emergency e g engine loss loss of power the banner should be dropped over open country if possible If the banner cannot be dropped the aircraft must be landed with the banner attached paying close attention to obstacle clearance 5 Normal procedures a The banner must be assembled and used in accordance with the relevant instructions from the manufactu
43. r of gravity CG total weight allowed range for CG 300 560 mm behind zero datum leading edge empty weight CG 280 460 mm behind zero datum leading edge C42B Flight And Operators Manual Page 23 May 2010 9 Data placard and checklist Airspeeds Stall speed 35 kts 65 km n Never exceed speed 116 ks 216 km n Load factor Positive limit load factor 44 Negative limit load factor 29 Maximum recommended wind speeds for operation Steady winds 22 kts 40 km h Demonstrated cross wind component 16 kts 30 km h Capacity max cf page 17 min 65 kg The pilot operates this aircraft at his own risk Manufacturer Serial no Registration LTZ Nr Year of manuf Month Aircraft basic empty weight C42B Flight And Operators Manual Page 24 May 2010 10 Before take off checklist 1 Harnesses buckled correctly 2 Control system free and correct 3 Parachute system armed 4 Check fuel level 5 Aux fuel pump ON 6 Choke OPEN 7 Carburettor heat OFF 8 Electrical equipment ON 9 Altimeter set 10 Wing flaps flap position 2 11 Check magnetos 12 Wind direction 13 Runway and approach CLEAR C42B Flight And Operators Manual Page 25 Febuary 2012 11 Eguipment Engine Rotar 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 dia
44. rer Set flaps to position 2 take off landing for take off Fly low bank turns only Avoid aero towing in rain C42B Flight And Operators Manual b o Page 51 May 2010 Check the follovving before commencing aero tovv Tovv coupling release mechanism functionality rear mirror camera position Condition of tow rope and attachment elements knots connecting rings Check banner for damage and completeness The laying out and picking up of the banner must comply with manufacturer recommendations Except in the case of an emergency the banner must be dropped at safe airspeed and low altitude within the airfield area over open country with no risk to person or property After dropping the banner the C42 will accelerate slightly A landing with the banner attached is only permitted in an emergency 6 Performance The take off distance to clear the 50 ft obstacle increases by approximately 50 The ground roll for a laid out banner set up in accordance with the relevant manufacturer recommendations is not affected For a take off with a rolled banner the relevant distances may be extracted from the following tables Take off Ao Ground roll Ground roll distance to banner size aircraft banner clear 50 ft obstacle 70 m 110m 180m 330 m 120 m 150 m 210m 380 m 150 m 180m 240m 410m Take off 5 Ground roll Ground roll distance to banner size aircraft banner clear 50 f
45. rus Technical Basis or a karus Service Center C42B Flight And Operators Manual Page 59 January 2011 Comco lkarus shall not be bound by product related statements not directly made by Comco Ikarus nor any warranty obligations applicable to the seller In most cases the authorized Ikarus Flight Center which sold and or installed your aircraft and original accessories will honour a warranty claim and or provide warranty service Claiming In order to claim the warranty service you must return the microlight aircraft and or accessory in question to an authorised Ikarus Flight Center or Ikarus Service Center in the original configuration as supplied by Comco Ikarus The microlight aircraft should be accompanied with the following information Name of the owner z Address of the owner Telephone numer of the owners Email address of the owner Comco Ikarus works number Total flying hours Number of landings Description oft he problem Digital photos if reguested In order to be eligible to receive warranty service you must present your receipt of purchase or a comparable substitute proof of purchase bearing the date of purchase You must ensure that all and any repairs or servicing is handled at all times by an authorized lkarus Flight Center or karus Service Center in accordance with Comco Ikarus service requirements In some cases you may be requested to provide additional information concerning the maintena
46. sonnel pre requisites n order to use the micro light aircraft C42A C42B to drop parachutists the follovving pre requisites must be fulfilled e The pilot must have a valid licence and flight experience of at least 100 hours as vvell as an aeronautical radio licence e The parachutist must have a valid licence and have carried out at least 100 jumps with manual release and at least 12 jumps in the last 12 months 2 Technical pre requisites The C42A C42B micro light aircraft may be used for dropping parachutists if the following technical pre requisites are fulfilled e The doors or at least the right door must be removed before take off It is not permitted to open the door during flight The additional instructions for flying the micro light aircraft C42A C42B with doors removed must be followed e During flight the parachutist must fasten at least the waist seat belt e The pilot and the parachutist must be able to communicate with each other at all times C42B Flight And Operators Manual Page 57 May 2010 3 Measures prior to take off The pilot and parachutist must agree on the following points before take off e drop zone drop altitude drop airspeed agreed signals function and activation of aircraft s ballistic recovery system Prior to take off the course of action for jumping out of the aircraft must be demonstrated and practised on the ground e opening the waist seat belt e the parachutist turning outward
47. t obstacle 70 m 140m 180m 360 m 120 m 180m 210m 410m C42B Flight And Operators Manual Page 52 May 2010 Bes Rate of climb 100 PS single seat occupation banner size 70 m 3 5 m s 120 m 3 0 m s 150 m 2 5 m s 2 Rate of climb 60 PS single seat occupation banner size 70 m 2 5 m s 120 m 2 0 m s Sufficient povver should be set for climb as the banner reduces airspeed considerably The operating limits of the povver plant may not be exceeded The relevant values should be constantly monitored Fuel consumption increases by approximately 30 Fuel consumption at 100 km h Banner size 100 m approx 15 l h Banner size 150 m approx 17 I h Schleppwiderstand 100 0 80 0 60 0 40 0 kp 20 0 0 0 100 4 110 120 130 T T oo ceo o km h 50 60 4 70 4 C42B Flight And Operators Manual Page 53 May 2010 19 Special features of aircraft eguipped for handicapped pilots 1 Eguipment If the following additional eguipment is installed in the aircraft it can be operated without using the feet to control the nose wheel and the rudder 1 modified throttle shaft including throttle lever extension 2 rudder control lever vvith push rod 3 placard on rudder control lever Installation must be undertaken in accordance with the instructions of the manufacturer The unauthorised alteration of the
48. the aircraft is used in conjunction with ancillary equipment not supplied by Comco Ikarus Comco Ikarus does not warrant the operation of the product combination and Comco Ikarus will not honour any warranty claim where the aircraft is used in such a combination and it is determined by Comco Ikarus that there is no fault with the aircraft Comco Ikarus specifically disclaims any responsibility for any damage whether or not to Comco Ikarus equipment caused in any way by the use of the aircraft parts or accessories when such parts or accessories are not manufactured or supplied by Comco Ikarus C42B Flight And Operators Manual Page 61 January 2011 Whatis not covered by the warranty This warranty is not valid if the defects are due to damage misuse tampering neglect or lack of care and in case of alterations or repair carried out by unauthorized persons The follovving are examples of defects or damage not covered by this product vvarranty 1 15 or damage resulting from use of the aircraft in other than is normal and customary manner Defects or damage from misuse access to incompatible sources accident or neglect Defects or damage from inproper testing operation maintenance installation adjustment or any alteration Or modification of any kind Aircraft disassembled or repaired other than by Comco Ikarus or an IFC ISC in such a manner as to adversely affect performance or prevent adequate inspection and testi
49. ufacturer Exercise due care in the maintenance and cleaning of the cabin glazing We recommend the opulent use of clear water and sparse rinsing agent for moistening and washing away staining For drying a fine microfibre cloth should be used which is solely used for this purpose By no means solvent containing or acetic acid containing cleaning agents may be used 2 All maintenance work must be carried out by appropriately qualified persons For Austria only The relevant regulations with respect to maintenance work ZLLV 1995 BGBINr 191 in their current versions must be upheld at all times 3 Especially Repair work and major changes must be reported and officially inspected 4 Airworthiness inspections in Germany must be carried out by the manufacturer or by DAeC inspectors In Austria inspectors are named by Austro Control 5 Repair work Repairs by the owner are limited to the exchange of defect parts Only approved spare parts may be used Damaged parts may never be repaired and re installed C42B Flight And Operators Manual Page 37 May 2010 6 Periodical inspections Periodical inspections 25 50 100 hour inspection should be carried out Cf inspection list for details of the C42 COMCO IKARUS maintenance manual and the ROTAX 912 maintenancemanual If not conducted the safety of the aircraft is not guaranteed and warranty claims may be cancelled The periodical inspections should be conducted in one of our IFC I
50. x n 1700 2300 1 min With propeller Kiev Prop BB 283 1800 3 blade 1 80 m 2 Pitch 24 0 at r 0 4 m from hub full throttle rom on the ground max 4850 1 min propeller rom approx n 2000 1 min With propeller Helix H50F 1 75m R S 14 3 3 blade 1 75 m Pitch 17 0 bei r 656 mm full throttle rom on the ground ca 4480 1 min propeller rom ca n 2 1975 1 min C42B Flight And Operators Manual Page 8 May 2010 1 11Engine limitations according to the Rotax operating manual ROTAX 912 ROTAX 912S Take off 5 mins 81 hp 5800 rpm 100 hp 5800 rpm Continuous 79 hp 5500 rpm 95 hp 5500 rpm 7596 59 hp 5000 rpm 69 hp 5000 rpm 6596 51 hp 4800 rpm 61 hp 4800 rpm 5596 43 hp 4300 rpm 51 hp 4300 rpm Type of oil automotive oils API SF or SG Amount of oil min 0 57 imp gallons 2 6 max 0 67 imp gallons 3 05 1 Oil temperatur min 122 F 50 C min 122 F 50 C max 284 F 140 C max 266 F 130 C optimum 194 230 F 902 1102 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 51603 Super Plus ROZ 98 unleaded DIN 51607 AVGAS 100 LL 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 Magneto check at 4000 rpm rpm drop max 300 rpm C42B Flight And Operators Manual Page 9 May 2010
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