Comco Ikarus C42 B Owner's manual

PILOT OPERATING HANDBOOK
for the aircrafts IKARUS C42 B according to
building standard LTF-UL-2019 from 15 January 2019
Modell No. C42 B
German Ident-No. 66141.1 (Issue 1)
Type IKARUS C42B with
reference to the TB-42-024-2020
Aircraft 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 responsible for your country.

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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

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Manufacturer Contact Information
COMCO IKARUS GmbH
Am Flugplatz 11
88367 Hohentengen
Germany
Tel: [phone]
Fax: [phone]
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.

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Introduction
C42 series aircraft are built in compliance with the airworthiness
requirements of various countries and are certified as Microlight, Ultralight,
Advanced Ultralight and Light Sport Aircraft.
To operate the aircraft the pilot must hold a license or certificate appropriate
to this category of aircraft. The aircraft is not to be flown unless it is
registered, carries registration markings in accordance with the
requirements of the country in which the aircraft is to be flown, and has a
Permit to Fly or certificate of Airworthiness valid in the country of operation.
The aircraft is to be flown under daytime VFR conditions. Flights in other
conditions than daytime VFR without the correct aircraft equipment and pilot
ratings is extremely dangerous and can result in serious injury or death.
Pilots holding licences for other categories, even higher ones, are required
to be checked out by an appropriately qualified instructor prior to flying this
aircraft as it possesses characteristics that are unique to light sport type
aircraft. These characteristics include low inertia, susceptibility to turbulence
and wind gradient and special engine considerations.
The safety of all occupants, the aircraft and persons on the ground are the
sole responsibility of the Pilot in command. Do not operate this aircraft in a
manner that would endanger the occupants, the aircraft or persons on the
ground.

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UL engines are not certified aircraft engines, the flight path must always be
selected so that a landing is safely possible in the event of engine failure.
Changes to the control system, structure,
wings and engine are prohibited.
These changes would invalidate any certificate of airworthiness or permit to
fly and as such would result in an insurance becoming null and void.
All operating difficulties and equipment failures should be reported to your
dealer or the manufacturer.
For fire safety reasons, smoking is prohibited on board of the aircraft.
All values given in this manual refer to the
MTOW and all speeds given are Indicated Air Speeds (IAS).

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Three-sided views
IKARUS C42B
Figure 1: 3-side view C42B

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Table of contents
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Title page ....................................................................................................... -
Record of Manual Revisions ........................................................................ 2
Manufacturer Contact Information ................................................................ 3
Introductory .................................................................................................. 4
Three-sided views ........................................................................................ 6
Table of contents .......................................................................................... 8
1 Operating limitations .......................................................................... 10
1.1 Airspeeds .................................................................................. 10
1.2 Weights ..................................................................................... 10
1.3 Structural limitations.................................................................. 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 plate ................................ 17
7 Weight and balance ............................................................................ 18
7.1 Weighing ................................................................................... 18
7.2 Loading plan ............................................................................. 19
8 Ground handling ................................................................................. 20
8.1 Shunting .................................................................................... 20
8.2 Hanging-up ............................................................................... 20

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8.3 Parking ...................................................................................... 21
8.4 Tie-Down ................................................................................... 21
9 Operation of the engine ...................................................................... 23
9.1 General information .................................................................. 23
9.2 Equipment with radiator flap ..................................................... 24
9.3 Notes for using the LiFe-starter battery .................................... 25
10 Flight performances ............................................................................ 27
10.1 Take-off distance ...................................................................... 27
10.2 Take-off speed .......................................................................... 27
10.3 Rate of climb ............................................................................. 27
10.4 Cruising speed .......................................................................... 28
10.5 Engine off performance ............................................................ 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 Cruising flight ............................................................................ 37
13.4 Turning flight ............................................................................. 37
13.5 Stalls ......................................................................................... 38
13.6 Descent and landing ................................................................. 39
13.7 Shutting down the engine ......................................................... 39
13.8 Sudden loss of engine power ................................................... 40
13.9 Emergency procedures ............................................................. 41
13.10 Use of the built-in parachute rescue system ............................ 43

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14 Attaching the wings ............................................................................ 45
14.1 Attaching the wings to the fuselage .......................................... 45
14.2 Folding the wings for hangaring ................................................ 47
15 Rigging data ........................................................................................ 48
16 Information for ultralights with towing device ................................. 52
16.1 Glider towing ............................................................................. 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 the parachute rescue system ................................. 80
22.5 Cirquit diagram C42 Series ....................................................... 83
23 List of illustrations .............................................................................. 84
24 List of tables ........................................................................................ 84

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1 Operating limitations
1.1 Airspeeds
All speeds are Indicated Air Speeds (IAS).
Stall speeds
Flaps 0: .............................................................. VS1 = 43 kn / 80 km/h
Flaps 1: ................................................................ VS = 41 kn / 75 km/h
Flaps 2: .............................................................. VS0 = 38 kn / 70 km/h
Speed for best 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 plan) .................. lbs / kg
Minimum payload (see. most recent weight & balance plan)
min. .......................................................................................121 lbs / 55 kg

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1.3 Structural limitations
Positive limit load factor ....................................................................... + 4 g
Negative limit load factor ...................................................................... - 2 g
1.4 Center of gravity limits
Reference datum ................................... Wing leading edge at a rib station
Forward center of gravity ...................... 11.8 inches (300 mm) aft of datum
Rearward center of gravity .................... 22.0 inches (560 mm) aft of datum
1.5 Airspeed markings
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 98 106 117 126 135 147 157 167 177 186 195 206 214 223
Table 1: Calibration table oft he airspeed indicator
IAS
kn 38
43 49 54 59 65 70 76 81 86 92 97 103 108 113 119 124
EAS
kn 41
45 49 53 57 63 68 73 79 85 90 95 100 105 111 116 120

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1.6 Engine rpm limitations
Maximum engine rpm ................................. n = 5800 1/min, max. for 5 min
Maximum continuous rpm .................................................... n = 5500 1/min
Idle rpm ........................................................................ min. n = 1400 1/min
1.7 Rpm indicator markings
Yellow ....................................................................... n = 5500 - 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 ground at full throttle ........................ max. approx. 4800 1/min
with propeller rpm ................................................................ n = 2115 1/min

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1.10 Propellers for ROTAX 912 ULS
With propeller Warp Drive 3- Blade,
Diameter: 1.72 m,
Pitch 25.0° at 400 mm from hub,
Rpm on the 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 propeller rpm ................................................................ n = 1975 1/min

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1.11 Engine limitations ROTAX 912 UL / ULS
According to the ROTAX operating manual
ROTAX 912 UL ROTAX 912 ULS
Takeoff (5 min) ........... 81 hp / 5800 1/min .................... 100 hp / 5800 1/min
Continuous ................. 79 hp / 5500 1/min ..................... 95 hp / 5500 1/min
75 % ........................... 59 hp / 5000 1/min ..................... 69 hp / 5000 1/min
65 % ........................... 51 hp / 4800 1/min ..................... 61 hp / 4800 1/min
55 % ........................... 43 hp / 4300 1/min ..................... 51 hp / 4300 1/min
Type of oil: AERO Shell Sport Plus 4
(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 see ROTAX manual)
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)
Coolant temperature: max.248°F (120°C) optimal 212°F (100°C)
Magneto-Check: at 4000 1/min
with
max. Rpm drop: max. 300 1//min

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2 Operating limitations
- Aerobatics and manoeuvres with more than 60° bank are prohibited!
- Daylight VFR conditions only.
- No flights in icing conditions.
- Max. crosswind component is 15 kn.
- Always follow the appropriate 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
- generator charge control
- data plate
- Pilot’s Operating Handbook (POH)
- parachute rescue system
- checklist

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5 Approved equipment
according to the published data sheets (66141.7)
Engine: ROTAX 912 UL
C-gearbox i=2.27
Approved propellers:
- WARP DRIVE 3-Blade-Propeller 68" ground adjustable propeller
- Neuform 3-Blade CR3-75 ground adjustable propeller
Engine: ROTAX 912 ULS
C-gearbox 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 capacity:
- 1x 14.3 imp gallons (65 l) tank
- 2x 14.3 imp gallons (65 l) double tank equipment
More approved equipments:
- ceiling suspension
- towing equipment (see chapter 16)

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6 Data plate & manufacturer`s information plate
Data plate (side cover pilot side in cockpit)
Speeds
Stall speed .......................................................................... 38 kn / 70 km/h
Never exceeded speed ................................................... 120 kn / 222 km/h
Max. demonstated 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 manufacture: ________
Callsign: ________
Max. takeoff mass: 1190 lbs / 540 kg

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7 Weight and balance
7.1 Weighing
Place the aircraft in a level 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)

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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

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8 Ground handling
8.1 Shunting
Manual moving of the aircraft is accomplished by using the tail struts upper
connections as push points. Since there is no tow bar applicable at the nose
gear, you have to press down the tail to raise the nose wheel off the ground.
With the nose wheel clear of ground, the aircraft can be simply steered by
pivoting it on the main wheels.
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 mounting points on
the cabin roof.
Figure 3: Suspension points on the roof frame