Comco Ikarus C42 B Pilot Operating Handbook Download | Manualshive

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POH LTF-UL-2019 C42B Issue 1 • Pilot Operating Handbook

POH LTF-UL-2019 C42B Issue 1

Page 75 of 84

Requirements for a warranty

This warranty will not apply if the type or serial number on the aircraft has
been altered, deleted, duplicated, removed or made illegible. Comco Ikarus
reserves  the  right  to  refuse  from  free-of-charge  warranty  service  if  the
requested  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 original warranty period will not be extended. All
original parts that have been replaced shall become the property of Comco
Ikarus.  Comco  Ikarus  does  not  warrant  the  installation,  maintenance  and
service of the products, parts and accessories.

Comco Ikarus will not be responsible in any way for problems or damages
caused by not distributed by Comco Ikarus accessories which are connected
to the aircraft or used together with it. Neither does Comco Ikarus guarantee
trouble-free operation of the Comco Ikarus aircraft in conjunction with these
accessories.  Such  accessories  are  specifically  excluded  from  this
guarantee.

As  long  as  the  aircraft  is  used  in  conjunction  with  the  accessories  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 to the aircraft and
for  other  damages  of  the  aircraft  with  the  accessories,  when  such
accessories are not manufactured or distributed by Comco Ikarus.

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Summary of Contents for C42 B

Page 1: ...rcraft Serial No ________ ________ Issue 1 Date of issue 25 06 2021 This handbook is to be kept in the aircraft at all times The described options are certified for Germany and have been tested in Germany Please note Different regulations apply in different countries for the use of the C42 series as a tow plane for gliders for banner towing or to drop skydivers Please check with the authorities re...

Page 2: ...POH LTF UL 2019 C42B Issue 1 Page 2 of 84 RECORD OF MANUAL REVISIONS No Issue No Description of changes Date Sign 1 1 C42B according to LTF UL 2019 MTOW 540 kg 25 06 2021 H Lieb 2 3 4 5 6 7 8 9 10 ...

Page 3: ...572 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 ...

Page 4: ...n 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...

Page 5: ...ol 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 All values given in this man...

Page 6: ...POH LTF UL 2019 C42B Issue 1 Pilot Operating Handbook POH LTF UL 2019 C42B Issue 1 Page 6 of 84 Three sided views IKARUS C42B Figure 1 3 side view C42B ...

Page 7: ...imitations 11 1 4 Center of gravity limits 11 1 5 Airspeed markings 11 1 6 Engine rpm limitations 12 1 7 Rpm indicator markings 12 1 8 Flap settings 12 1 9 Propellers for ROTAX 912 UL 12 1 10 Propellers for ROTAX 912 ULS 13 1 11 Engine limitations ROTAX 912 UL ULS 14 2 Operating limitations 15 3 Dimensions 15 4 Minimum equipment 15 5 Approved equipment 16 6 Data plate manufacturer s information pl...

Page 8: ...mance 28 11 Pre flight inspection 29 11 1 Engine 29 11 2 Landing gear 29 11 3 Left wing 30 11 4 Left side of fuselage 30 11 5 Empennage 31 11 6 Right side of fuselage 31 11 7 Right wing 31 11 8 Cabin inside and outside 32 11 9 Instruments 32 11 10 Drainage 32 11 11 Safety clip draintap 33 12 Before take off checklist 34 13 Flight Operations 35 13 1 Taxiing 35 13 2 Take off and climb 35 13 3 Cruisi...

Page 9: ...g 52 16 2 Banner tow 59 16 3 Inspection and maintenance intervals 65 17 Features of the aircraft equipped for handicapped pilots 66 18 Additional instructions for dropping skydivers 68 19 Flying the aircraft with removed doors 70 20 Care and maintenance 71 21 COMCO IKARUS Manufacturer Warranty 73 22 Appendix 77 22 1 Placards 77 22 2 Reporting form 78 22 3 Inspections performed 79 22 4 Location of ...

Page 10: ...t climbing Flaps 0 VY 62 kn 115 km h Maximum speed with landing flap set Flaps 1 2 VFE 75 kn 140 km h Maximum manoeuver speed VA 88 kn 163 km h Maximum speed in turbulent air VB 100 kn 185 km h Never exceed speed VNE 120 kn 222 km h If VA speed is exceeded only little rudder movement are allowed 1 2 Weights Maximum Take off weight MTOW 1190 lbs 540 kg Empty weight see most recent weight balance pl...

Page 11: ...White arc 42 75 kn 77 140 km h Green arc 48 100 kn 88 185 km h Yellow arc 100 120 kn 185 222 km h Yellow triangle VX 61 kn 112 km h Yellow line VA 88 kn 163 km h Red line VNE 120 kn 222 km h The deviation curve for the airspeed indicator can be interpolated from the following table IAS km h 70 80 90 100 110 120 130 140 150 160 170 180 190 200 210 220 230 EAS km h 75 83 90 98 106 117 126 135 147 15...

Page 12: ...00 5800 1 min Red n 5800 1 min 1 8 Flap settings Flaps 0 Cruising Flaps 1 Takeoff Landing Flaps 2 Landing 1 9 Propellers for ROTAX 912 UL With propeller Warp Drive 3 Blade Diameter 1 72 m Pitch 21 0 at 400 mm from hub Rpm on the ground at full throttle max approx 5200 1 min with propeller rpm n 2291 1 min With propeller Neuform CR3 75 3 Blade Diameter 1 75 m Pitch 24 0 at r 365 mm Rpm on the groun...

Page 13: ...ground at full throttle max approx 5200 1 min with propeller rpm n 2140 1 min With propeller Neuform CR3 75 3 Blade Diameter 1 75 m Pitch 27 0 at r 365 mm Rpm on the ground at full throttle max approx 4800 1 min with propeller rpm n 1975 1 min With propeller Helix H50F 1 75 m R S 14 3 3 Blade Diameter 1 75 m Pitch 17 0 at r 656 mm Rpm on the ground at full throttle approx approx 4800 1 min with pr...

Page 14: ... 4 or see ROTAX manual Oil quantity min 0 57 imp gallons 2 60 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 102 psi 7 bar Fuel Euro Super ROZ 95 unleaded DIN EN228 max 5 Ethanol Super Plus ROZ 98 unleaded DIN EN228 max 5 Ethanol AVGAS 100LL or...

Page 15: ...propriate regulations for this category of aircraft 3 Dimensions Dimensions can be found in the overview sheets which you will find at the beginning of this manual page 6 4 Minimum equipment four point seat belt for each seat airspeed indicator with correct colour coding altimeter with Kollsman window compass tachometer cooling temperature gauge oil temperature gauge oil pressure gauge fuel gauge ...

Page 16: ...rbox i 2 43 Approved propellers WARP DRIVE 3 Blade Propeller 68 ground adjustable propeller Neuform 3 Blade CR3 75 ground adjustable propeller Helix 3 Blade H50F 1 75 m R S 14 3 fix pitch propeller Approved parachute rescue systems Junkers Magnum Lightspeed BRS 6 1050 SP For more information on the function and use of the rescue system see chapter 13 10 Using the built in rescue system Fuel tank c...

Page 17: ...monstated crosswind component 8 kn 15 kn Maximum mass MTOW 1190 lbs 540 kg Max payload lbs kg Payload in cockpit min 121 lbs 55 kg with full fuel tanks max lbs kg Date of weighing tt mm jj Manufacturer s information plate in the back on fuselage tube Manufacturer COMCO IKARUS GmbH Country GERMANY Type C42 BFehler Verweisquelle konnte nicht gefunden werden Serial No ________ ________ Year of manufa...

Page 18: ...position on three scales with the stabilizer and elevator leveled 0 The centre of gravity is determined in cm at the distance to the BE and then converted to of the wing depth Figure 2 Position of the aircraft during weighing BP reference datum leading edge Wing chord MAC 53 5 inches 136 cm BE BP 39 37 inches 100 cm X1 9 inches 23 cm X2 69 68 inches 177 cm C42B ...

Page 19: ... C42B Issue 1 Pilot Operating Handbook POH LTF UL 2019 C42B Issue 1 Page 19 of 84 7 2 Loading plan Date Pilot Date Pilot It is the pilot s responsibility to ensure that the maximum take off mass MTOW is observed 10 10 ...

Page 20: ... 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 8 2 Hanging up This equipment is optional The aircraft may be lifted with a hoist of at least 1100 lb 0 5 tons capacity by using T support ceiling hangers Use suitable spring snap hooks for the three designated mo...

Page 21: ...rakes are overheated 8 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 ...

Page 22: ...TF UL 2019 C42B Issue 1 Pilot Operating Handbook POH LTF UL 2019 C42B Issue 1 Page 22 of 84 Figure 5 Attachment point between cowling and propeller spinner Figure 4 Upper attachment point on front lift strut ...

Page 23: ...ngine start Main fuel valve O P E N Fuel pump O N Throttle I D L E Choke O N Carburettor heat O F F Magnetos both O N Propeller and area in front of airplane F R E E Parking brake S E T After engine starts choke slowly O F F If the engine does not start immediately operate the starter several times No longer than 10 sec followed by 2 min cooling of the starter If the engine has been flooded close ...

Page 24: ... max of the surface with tape or self adhesive neoprene On the ROTAX 912 iS and ROTAX 914 engine types the coolant and oil are cooled by separate cooling circuits Attention Observe the maintenance instructions in the ROTAX Operators Manual 9 2 Equipment with radiator flap The additional equipment of a radiator flap offers the possibility to influence the engine temperatures by manually regulating ...

Page 25: ...ht to light up but observe the temperature and open the flap manually at 194 230 F 90 110 C so that the temperatures are in the optimum range By reducing the engine power and increasing the airspeed during descent the cooling down to permissible or optimal temperatures can be supported During the pre flight check a functional check of the radiator flap must be carried out Careful observation of th...

Page 26: ...Fe starter battery is installed at the factory the C42 has an automatic overvoltage protection OVP built in which prevents too high damaging charging voltage An automatic interruption of the charging current is indicated by the charging indicator lamp The charging circuit can be closed again by pressing the reset button next to the charging indicator lamp or automatically after the battery voltage...

Page 27: ... m Take off distance over 50 ft approx 1083 ft 330 m approx 820 ft 250 m 15 m obstacle 10 2 Take off speed Take off speed ca 53 kn 98 km h Higher elevations and higher temperatures lengthen the take off distances Reference values may vary slightly from propeller to propeller 10 3 Rate of climb ROTAX 912 UL ROTAX 912 ULS Sea level 59 F 15 C calm wind Engine rpm 4800 1 min 4750 1 min Rate of climb 5...

Page 28: ...LS C42B 81 kn 150 km h 86 kn 159 km h Speed for maximum range 78 kn 145 km h Maximum range with 14 3 imp fuel gallons 65 l tank capacity when windless approx 325 nm 600 km 10 5 Engine off performance MTOW 1190 lbs 540 kg Minimum sink rate 492 ft min 2 5 m s at 59 kn 110 km h flap position I take off landing Best glide angle 1 to 11 at 65 kn 120 km h flap position 0 cruise ...

Page 29: ...or leakage under the engine cowling Check cooling liquids and lubricants Check secure attachment of the engine cowling Check that coolers are clean oil cooler water cooler Check air vents for blockage Check NACA intake for blockages Check function of radiator flap if installed 11 2 Landing gear Check secure attachment of all components hub caps brake cylinders brake discs Check for a visible defor...

Page 30: ...ormation Check attachment of ailerons and flaps Check the spring loaded locks at the sliding sleeves for proper power transmission they have to be locked properly at the front and rear end of the tubes 11 4 Left side of fuselage Check condition of fibre glass fairing cracks holes etc Check secure attachment of fibre glass fairing check for missing bolts at the upper lower connection Check static p...

Page 31: ...the elevator struts for a secured attachment and possible deformation Check rudder cables for being connected and secured Rudder connections Trim flap secured Check fabric covering rips chafing 11 6 Right side of fuselage Check condition of glass fiber fairing cracks holes etc Check secure attachment of glass fiber fairing missing bolts etc Check static ports for contamination and hose connection ...

Page 32: ...with a lock Check the brake lever incl stand lock parking brake Check aileron lever for being connected and secured Visually check aileron cables and pulleys Check Open fuel valve 11 9 Instruments Power supply switch on ignition Altimeter setting Amount of fuel Functioning of the radio and intercom system 11 10 Drainage Drainage of the fuel tank closed the drainage tap is located under the copilot...

Page 33: ...ll the safety clip off the drainage tap using your thumb and index finger as shown in the graphic below Alternatively the safety clip can also be removed from the drainage tap with the index finger only Attaching the safety clip When putting on the safety clip make sure that the tab is placed over the lever of the drainage tap and that the safety clip snaps into place on the curve of the drainage ...

Page 34: ...d 2 Control system free and correct 3 Parachute system unlocked 4 Electric instruments O N 5 Check fuel level 6 Alimeter set 7 Engine fuel shut off valve O P E N 8 All electric fuel pumps O N 9 Choke O F F 10 Carburettor preheating O F F 11 Flaps flap position 1 take off landing 12 Check magnetos 4000 1 min 13 Wind direction 14 Runway approach C L E A R ...

Page 35: ...ion to avoid striking the propeller 13 2 Take off and climb After completing pre flight inspection Chapter 11 and Before take off checklist Chapter 12 Whenever possible take off into the wind The maximum demonstrated crosswind component for take off and landing is 15 kn No special procedures are required The starting direction must be ensured by a drift angle against the wind Make certain the runw...

Page 36: ...er to prevent stalling should a sudden loss of power be experienced Continue to climb at 65 kn 120 km h Retract flaps at a height of approx 328 ft 100 m 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 65 kn 120 km h and continue climbing Slight right rudder is necessary to compensate both engine and prope...

Page 37: ...m h 170 180 km h Fuel flow approx 2 86 3 30 gph 3 30 3 74 gph 13 15 l h 15 17 l h In a turbulent weather the maximum speed VB see operating limitations must be observed The maximum permissible speed VNE see operating limitations must not be exceeded At the first indication of carburettor icing rpm drop stuttering engine running increase in fuel consumption apply carburettor and if possible fly the...

Page 38: ... the elevator in detent the aircraft will enter a stable stall at full elevator deflection The loss of altitude when stalling from straight flight until horizontal flight is restored is up to Flap position 0 cruising flight ca 80 ft Flap position 1 take off landing ca 80 ft Flap position 2 landing ca 120 ft During a whip stall the aircraft clearly pitches down up to 40 By slightly releasing the el...

Page 39: ...orable On final approach with flap stage 2 maintain a speed of approx VX 61 kn 112 km h at engine idle The glide angle in flap position 1 take off landing is significantly more shallow and thus the flare distance is longer The approach speed should be about 61 kn 115 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 ...

Page 40: ... vegetation by extending the flaps to position 2 landing pull stick fully aft and allow the aircraft to sink into the vegetation II Loss of engine power during crusing 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 0 cruising flight speed at 65 68...

Page 41: ...sing engine starter Maintaining airspeed to windmill the prop can help 13 9 Emergency procedures I Tipping due to lower speeds Reduce back pressur on the stick and lower the nose Recover II Sideslip Set rudder in the opposite direction to a slideslip Reduce back pressur on stick III Spin Throttle to idle Rudder neutral until rotation stops Reduce back pressure on stick Slowly pull aircraft up IV S...

Page 42: ...aw induced rolling moments VII Loss of rudder control Controlling gentle turns is possible with the ailerons only If possible perform a field landing in a straight flight VIII Fire in engine compartment Main fuel valve O F F All electrical fuel pumps O F F Full throttle Sideslip flames away from the aircraft Follow emergency landing procedures If the emergency procedures do not have any effect the...

Page 43: ... in the stern Potential situations for triggering the rescue system Collisions with birds or other aircraft Engine failure over water or rough terrain Structural failure e g wing loss Aircraft not able to land safely due to loss of control Health problems of the pilot e g heart attack etc a o Operating the activation unit Remove the safety pin from the activation handle before starting to save tim...

Page 44: ...intenance servicing or periods of use of components of the rescue system please refer to the information provided by the rescue system manufacturer In particular it is essential to ensure that the parachute is protected from moisture If it has become wet it must be aired and repacked In the case of rescue equipment with an extraction rocket there is a time limit on its use Figure 8 Landing positio...

Page 45: ...t Step 4 Slowly push the wing against fuselage and wing spar brackets Step 5 Before pushing against the spar brackets look for the slideway at the rear spar intake so that to lead the rear wing spar in the locking position When the retaining bolt is touched rotate the right wing slightly clockwise the left wing must be rotated counter clockwise By moving slightly upwards the rear wing spar will lo...

Page 46: ...ng and check that the wing support is fixed by the toggle bolt really reliable Repeat Step 1 to 6 for the other wing Remove any aileron 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 ball joint connectors is in completely closed position and there is no vertical play Step 8 Left and right flaps connection...

Page 47: ...lage to wing 6 First remove toggle bolts at the base of the wing support Second remove fastening bolts at the rear wing spar Third remove fastening bolts at the front wing spar 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 first the forward wing spar and then the rear one Step 2 Draw the wing back off the fuselage u...

Page 48: ...tube 8 5 Note The incidence angle is measured from the lower edge of the rear wing tube to the lower edge of the front wing tube at the root rib b Incidence angle of the horizontal stabilizer relative to the fuselage main tube 7 Note The stabiliser incidence angle is measured from the lower edge of the front tube to the lower edge of the rear tube of the horizontal stabiliser c Incidence angle dif...

Page 49: ...ace deflections Note The angle of the aileron bottom relative to the wing chord is 5 tangent front to rear spar It is defined by the length of the aileron push rods 5 Aileron Distance from axis of rotation Neutral 7 1 1 38 0 39 35 mm 10 mm Up 20 2 3 34 0 39 85 mm 10 mm Down 14 2 2 36 0 39 60 mm 10 mm Measuring point distance from the steering axis 9 84 250 mm ...

Page 50: ...m Elevator Up 28 2 7 68 0 59 195 mm 15 mm Down 20 2 5 51 0 59 140 mm 15 mm Measuring point distance from the steering axis 16 14 410 mm e Flaps Note Flap angle is measured from the flap bottom to the bottom of the wing at the root area tangent front to rear spar Position 0 5 1 1 06 0 39 27 mm 5 mm Position 1 11 1 2 36 0 39 60 mm 5 mm Position 2 32 1 6 5 0 39 165 mm 5 mm Measuring point distance fr...

Page 51: ...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 43 pts 200 ml Hydraulic oil HVP 10 h Brakes In the Ikarus C42 series different brake systems are used e g Sachs Magura Tost and Beringer brakes For service information please see our maintenance manual or ask one of our ISC or ITB i Engine For servi...

Page 52: ...ment of the towing aircraft If the following additional equipment is installed the ultralight aircraft may be used for towing gliders 1 Engine ROTAX 912 ULS 74 kW 100 hp with propeller Warp Drive 3 blade 68 Neuform 3 blade CR3 75 ground adjustable 2 Tow hook mount 3 Tow coupler E85 Tost 4 Comco release mechanism operated by towing pilot 5 Rear mirror camera system 6 Engine monitoring instruments w...

Page 53: ...00 daN In the case of tow ropes with a higher ultimate load a predetermined weak link must be installed for the protection of the aircraft and the glider Length of the tow rope 131 197 ft 40 60 m Max nominal breaking strength of the weak link 660 lbs 300 daN Joining ring pair on the tow rope according to LN 65091 II Operating limitations a Permissible take off weights The aircrafts of the IKARUS C...

Page 54: ...Depending upon the take off weight of the IKARUS C42 the following flap positions should be used at towing speeds below 59 kn 110 km h Take off weight below 882 lbs 400 kg Flap position 0 Take off weight between 882 lbs 400 kg and 1041 lbs 472 5 kg Flap position 1 The minimum speed of the majority of modern gliders generally lies above that of the ultralight towing aircraft This means that the min...

Page 55: ...ust agree on the towing speed III Flight characteristics and performance a Flight performance Tow plane take off weight 860 lbs 390 kg Runway conditions dry grass Temperature 59 F 15 C Elevation 0 ft AMSL Table 3 Flight performance with different glider types Take off weight of glider lbs Type of glider Take off distance 50 ft obstacle ft Towing speed kn IAS Rate of climb ft min 683 lbs Standardli...

Page 56: ...ing edge and raindrops can increase recommended towing speeds and take off distances depending upon the type of glider Appropriate instructions from the glider manufacturer should be followed Rain or dirt particles have no significant influence on the performance of the IKARUS C42 Series when towing Headwind will reduce the take off distance as follows 10 kn 18 km h take off distance with no wind ...

Page 57: ...by the towing pilot If the glider breaks out and the glider pilot does not react If the glider climbs above the towing aircraft and the attitude of the towing aircraft is no longer properly controllable If the towing aircraft climbs prematurely and the towed glider cannot follow due to a lack of speed high wing loading water ballast etc the rate of climb of the towing aircraft should be reduced an...

Page 58: ...ius is sufficiently large so that the glider can follow the towing aircraft If there is a danger of exceeding the maximum engine temperatures oil and cylinder head temperature reduce engine power 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 ...

Page 59: ...t must be equipped with the same equipment as described above for towing gliders The following propellers are approved for banner towing when the aircraft is equipped with a ROTAX 912 UL 80 PS Warp Drive 3 blade 68 Neuform CR3 75 3 blade ground adjustable propeller with a ROTAX 912 S ULS 100 PS Warp Drive 3 blade 68 Neuform CR3 75 3 blade ground adjustable propeller Banners may only be picked up a...

Page 60: ...ng tow rope breaking point Banner tow 200 daN d Length of the tow rope Laid out banner 131 ft 197 ft 40 60 m Roller banner 82 ft 131 ft 25 40 m e Speeds Minimum airspeed 46 kn 85 km h Best rate of climb airspeed 51 kn 95 km h Airspeed during tow 54 kn 100 km h Maximum airspeed 65 kn 120 km h Pay attention to the maximum flap speed VFE f Banner size Rotax 912 UL 1292 sq ft 120 m2 Rotax 912 ULS 914 ...

Page 61: ...pull open On the release lever IV Emergency procedures banner tow In the 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 the obstacle clearance V Normal procedures a The banner must be assembled and used in accordance with the ...

Page 62: ...mmendations d Except in the case of an emergency the banner must be dropped at safe airspeed and low altitude within the airfield over an open area with no risk to people or property After dropping the banner the C42 will accelerate slightly A landing with the banner attached is only permitted in an emergency VI Performance The take off distance over 50 ft 15 m obstacle increases by about 50 The g...

Page 63: ...70 m2 490 ft min 2 5 m s 1290 ft2 120 m2 390 ft min 2 0 m s Rotax 912 S 100 hp banner size Ground roll C42 Ground roll banner Take off distance 750 ft2 70 m2 360 ft 110 m 590 ft 180 m 1080 ft 330 m 1290 ft2 120 m2 490 ft 150 m 690 ft 210 m 1250 ft 380 m 1610 ft2 150 m2 590 ft 180 m 790 ft 240 m 1350 ft 410 m Rotax 912 S 100 hp banner size Rate of climb single seat 750 ft2 70 m2 690 ft min 3 5 m s ...

Page 64: ...owing resistance to towing speeds For a climb sufficient power should be set otherwise there will be a strong speed drop The operating limits of the drive unit must not be exceeded The relevant values should be constantly monitored Fuel consumption increases by approximately 30 Fuel consumption at 54 kn 100 km h Banner size 1075 sq ft 100 m2 approx 3 30 gph 15 l h Banner size 1615 sq ft 150 m2 app...

Page 65: ... 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 the freedom of movement and damage near the release lever and near the tow hook before each towing flight Check release force at release lever with unload...

Page 66: ...ith the instructions of the manufacturer The unauthorised alteration of the equipment for handicapped pilots is not permitted II Montage Demontage The rudder control lever is installed by attaching to the mounted axle in the main tube and bolting with a hexagonal bolt M8x40 The push rod which is attached to the rudder control lever is connected to the right pedal of the left seat by a quick releas...

Page 67: ...back to the rudder control lever and steer aircraft during take off run 4 After take off in approximately 16 to 33 ft 5 to 10 m above the runway use LH to check that the throttle lever is still in the full throttle position 5 Excepting in case of 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 af...

Page 68: ... experience of at least 100 hours as well as the aeronautical radio telecom licence The skydiver 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 II Technical requirements The C42 Series micro light aircraft may be used for dropping skydivers if the following technical requirements are fulfilled The doors or at least ...

Page 69: ...cockpit frame and the wing strut leaving the aircraft to the side and in front of the wing strut ensuring that there is sufficient distance between the skydiver and the propeller IV Drop procedures After completing the climb to the agreed drop altitude level off the aircraft and continue horizontal flight at the airspeed of 54 to 65 kn 100 to 120 km h For that set the flaps to position 1 take off ...

Page 70: ...n completed is practical and useful for the future 19 Flying the aircraft with removed doors Under the following conditions the C42 may be flown with the dismantled doors All loose items maps documents should be properly secured The dropping of objects during flight is prohibited Maximum speed for flights with one or both doors removed is 81 kn 150 km h IAS Side slipping is not permitted with dism...

Page 71: ... Be especially careful in the maintenance and cleaning of the cabin glazing It is highly recommended to abundantly use clear water with a little detergent for softening and rinsing of contamination For drying a fine microfiber cloth should be used which is solely used for this purpose By no means solvent based or acid based detergents may be used 2 All maintenance works Must be carried out by appr...

Page 72: ...on should be carried out in accordance with the provisions of the C42 COMCO IKARUS GmbH Maintenance Manual and 912 ROTAX Maintenance Manual If not conducted the safety of the aircraft is not guaranteed and warranty claims may be omitted The periodical inspections should be conducted in one of our ITB Ikarus Technical Base or ISC Ikarus Service Center If periodical inspections should be conducted b...

Page 73: ...ercial 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 are entitled to from your purchase agreement such as warranty of fitness for an ordinary use and service which is common for things of the same kind so the claims against the seller of the aircraft u...

Page 74: ...ephone number of the owners Email address of the owner Comco Ikarus serial number Total flying hours Number of landings Description of the problem Digital photos if requested 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 repair or customer service is ha...

Page 75: ...Comco Ikarus does not warrant the installation maintenance and service of the products parts and accessories Comco Ikarus will not be responsible in any way for problems or damages caused by not distributed by Comco Ikarus accessories which are connected to the aircraft or used together with it Neither does Comco Ikarus guarantee trouble free operation of the Comco Ikarus aircraft in conjunction w...

Page 76: ...ner 2 Defects or damage resulting from misuse use with incompatible devices or accessories accident or neglect 3 Defects or damage due to improper operation testing maintenance installation adjustment unauthorized modifications 4 The aircrafts which are disassembled or repaired other than by Comco Ikarus or the IFC ISC ITB in such a manner as to adversely affect performance or prevent adequate ins...

Page 77: ...frame Flaps mechanical Roof frame Engine oil specifications Oil inspection cover Fuel specifications Filler neck Baggage loading Baggage compartment opening Deviation table Instrument panel Controls Center console Choke Heating Carburettor heat Cowl flap if available Fuel valve Center console left side Data placard Center console left side Type placard fire resistant Fuselage tube behind the tank ...

Page 78: ..._ Total Flight Hours until Defect __________________ Engine _____________________________________ Airframe ___________________________________ Total Flight Hours Pilot on Aircraft ______________ Description of damage _______________________________________ __________________________________________________________ __________________________________________________________ Damage Report ___________...

Page 79: ...POH LTF UL 2019 C42B Issue 1 Page 79 of 84 22 3 Inspections performed Type C42 BFehler Verweisquelle konnte nicht gefunden werden Serial No ________ ________Fehler Verweisquelle konnte nicht gefunden werden Marking ________ Date Type of inspection Recognised expert ...

Page 80: ...ation of the parachute rescue system Figure 11 Securing the rescue container against sliding down CAUTION Lay the cable tie 450x7 8 mm around the clamp of the ballistic rocket and trough the first front mounting flap of the rescue system and tighten it Thereby backward slipping of the parachute package is prevented ...

Page 81: ...2B Issue 1 Pilot Operating Handbook Appendix POH LTF UL 2019 C42B Issue 1 Page 81 of 84 Figure 12 Installation position rescue system until September 2013 Figure 13 Installation position rescue system from September 2013 ...

Page 82: ...POH LTF UL 2019 C42B Issue 1 Pilot Operating Handbook Appendix POH LTF UL 2019 C42B Issue 1 Page 82 of 84 Figure 14 Illustration of exit opening rocket rescue system ...

Page 83: ...POH LTF UL 2019 C42B Issue 1 Pilot Operating Handbook Appendix POH LTF UL 2019 C42B Issue 1 Page 83 of 84 22 5Cirquit diagram C42 Series Figure 15 Electric Masterplan ...

Page 84: ... Figure 9 Angle aileron bottom side to wing chord 49 Figure 10 Angle between trim tab and elevator 51 Figure 11 Securing the rescue container against sliding down 80 Figure 12 Installation position rescue system until September 2013 81 Figure 13 Installation position rescue system from September 2013 81 Figure 14 Illustration of exit opening rocket rescue system 82 Figure 15 Electric Masterplan 83...

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