FLIGHT DESIGN CTLS LSA Series Operating Instructions Manual Download Page 49 | Manualshive

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Aircraft Operating Instructions (AOI)

Type:

CT

Series:

CTLS

LSA

Page: 5-4

AU 010 11000

Revision No. 4

Date: 29 Apr 2008

5.3. Significance of the wind component

Wind directly affects the flight path and thus aircraft performance. Two diagrams are
presented below which show the significance of the wind component.

5.3.1.

Wind influence on take-off roll and landing

To determine whether the aircraft can take-off safely, it is necessary to determine the
prevailing crosswind component. On the one hand, this determines the appropriate
take-off procedure while, on the other hand, it ensures that the demonstrated
permissible crosswind component for take-off and landing is not exceeded. The
following diagram is used to determine the crosswind component.

Crosswind

Taxi- or Flight Direction

Headwind

Crosswind

Taxi- or Flight Direction

Headwind

An example is shown in the diagram. Take-off direction is 120°. The wind direction is
070°, wind speed 11 kts. The wind angle is thus 120° - 70° = 50°. Wind speed is
plotted along the circle segment (1) to the point where it intersects the wind angle (2).
The corresponding value on the x-axis (3) results in a head wind component of 7.1
kts, the value on the y-axis (4) in a crosswind component of 8.4 kts.

Values for landing are determined in a similar manner.

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Summary of Contents for CTLS LSA Series

Page 1: ...Aircraft Operating Instructions AOI THIS DOCUMENT AND THE TECHNICAL DATA HEREON DISCLOSED ARE PROPRIETARY TO FLIGHT DESIGN AND SHALL NOT BE USED RELEASED OR DISCLOSED IN WHOLE OR IN PART WITHOUT EXPRESS WRITTEN PERMISSION FROM FLIGHT DESIGN ...

Page 2: ...port form added Vasyl Sys 4 7 4 5 Autopilot operation chapter moved from 4 14 to 4 5 and updated 4 7 7 Apr 29 2008 Fuel system diagram corrected Vasyl Sys 1 1 1 1 Warning re formatted and reworded 1 2 1 2 Manufacturer address corrected house no 2 1 2 1 stall speed flaps 12 added note added 2 3 2 5 Idle engine speed corrected 7 26 7 5 green arc limits for flaps 12 case added 9 1 9 Chapter reworded ...

Page 3: ...eted 7 26 Flap s position 12 deleted 7 27 Flap s position 12 deleted Flap s position 12 deleted 6 1 6 10 Chapter 6 complete enhanced by weight and balance chart equipment chapter in contents unchanged 3 6 3 6 information updated to match Junkers Magnum Rescue System 7 7 17 7 19 May 07 2009 7 3 9 Information updated to match Junkers Magnum Rescue System Attitude angle corrected to 13 4th belt added...

Page 4: ... 4 1 6 4 4 13 6 7 4 4 8 6 4 1 1 7 4 4 14 4 7 5 4 8 8 7 4 2 1 6 4 15 6 7 6 4 9 9 1 5 2 2 4 4 16 6 7 7 4 10 10 1 5 2 3 5 4 cont 4 17 4 7 8 4 11 1 4 2 2 4 4 5 1 4 7 9 4 11 2 4 3 1 4 5 2 4 7 10 4 11 11 3 4 3 2 4 5 3 4 7 11 4 3 3 4 5 4 4 7 12 4 3 4 4 5 5 4 7 13 4 3 5 4 5 6 4 7 14 4 3 6 7 5 7 4 7 15 4 3 7 4 5 8 4 7 16 6 3 8 4 5 9 4 7 17 7 3 9 4 5 10 4 7 18 7 3 10 4 5 5 11 4 7 19 7 3 3 11 4 6 1 6 7 20 4 ...

Page 5: ...INADVERTENT SPIN 3 3 3 4 EMERGENCY LANDING 3 4 3 5 AFTER OVERTURN ON LANDING 3 5 3 6 DEPLOYING THE BALLISTIC RECOVERY SYSTEM 3 6 3 7 ENGINE FAILURE 3 7 3 8 CARBURETOR OR ENGINE FIRE 3 8 3 9 LOSS OF COOLANT 3 9 3 10 LOSS OF OIL 3 9 3 11 FAILURE OF FLAP CONTROL 3 10 3 12 DYNON EMS FAILURE IF INSTALLED 3 11 4 NORMAL PROCEDURES 4 1 4 1 NORMAL PROCEDURES CHECKLISTS 4 1 4 2 PREFLIGHT INSPECTION 4 5 4 3 ...

Page 6: ...ENT 6 9 7 AIRPLANE AND SYSTEMS DESCRIPTION 7 1 7 1 AIRFRAME 7 1 7 2 SYSTEMS 7 4 7 3 FLIGHT CONTROLS 7 12 7 4 COCKPIT 7 20 7 5 PLACARDS AND MARKINGS 7 26 8 HANDLING SERVICE MAINTENANCE 8 1 8 1 JACKING 8 1 8 2 SECURING THE AIRCRAFT FOR ROAD TRANSPORTATION 8 2 8 3 PARACHUTE RECOVERY SYSTEM MAINTENANCE 8 2 8 4 CLEANING AND CARE 8 3 8 5 MANDATORY AIRCRAFT INSPECTIONS 8 5 8 6 REPAIRS TO THE AIRFRAME 8 6...

Page 7: ... of Light Sport aircraft are not Part 33 certified aviation engines The flight route must thus be chosen to ensure that an emergency landing after engine failure can be undertaken without difficulty The CTLS may only be operated under visual flight rules VFR Due to the high cruise speed and the great range pilots may encounter meteorologically critical weather conditions more often Flying into IFR...

Page 8: ... Page 1 2 AU 010 11000 Revision No 5 Date 16 Jan 2009 1 2 Manufacturer Flight Design GmbH Sielminger Str 51 70771 L Echterdingen Germany 1 3 In the USA contact Flight Design USA P O Box 325 South Woodstock CT 06267 860 963 7272 airworthiness flightdesignUSA com ...

Page 9: ...ich 1 Flight Design USA issues Safety Directives Notices of Corrective Action directed towards correcting Safety of Flight and Service Difficulty issues 2 The Owner Operator obtains and verifies that they have the latest safety of flight information developed by the manufacturer C Maintenance Instructions Provided to the Owner Operator and pertaining to 100 hour and annual condition inspections D ...

Page 10: ...ices of corrective actions and for complying with all applicable FAA regulations in regard to maintaining the airworthiness of the LSA airplane Airworthiness information will be sent to the Owner operator contact address of record Airworthiness information can also be obtained from Safety section of the Flightdesignusa com website E The Owner operator shall ensure that any needed corrective action...

Page 11: ...structions AOI Type CT Series CTLS LSA Page 1 5 AU 010 11000 Revision No 4 Date 29 Apr 2008 1 5 Three view main dimensions Main Dimensions Wing span 8 60 m 28 ft 2 in Length 6 61 m 21 ft 8 in Wing area 9 98 sq m 107 4 sq ft ...

Page 12: ...e Bing constant pressure carburetor Ignition electronically controlled dual ignition Propeller gear reduction 2 43 1 1 7 Propeller Various types of propeller are available for the CTLS Each propeller has its own operating handbook and maintenance manual published by the propeller manufacturer These documents are delivered with the aircraft and must also be studied in detail The following types of ...

Page 13: ...point one for each seat Magnetic compass with calibration card Engine instruments CHT Oil Temp Oil press RPM Aircraft documents national regulations apply 1 9 Recommended additional equipment Ballistic recovery system national regulations apply Emergency locator transmitter ELT mandatory in some countries Radio with intercom and headsets Transponder Mode C or S External lighting anti collision lig...

Page 14: ...ceed speed Vne vne 269 km h 145 kts CAS The never exceed speed VNE demonstrated during flight testing is 301 km h However VNE is limited by the maximum deployment speed for the ballistic recovery system or national regulatory requirements The maximum negative flap setting is limited dependent from the country where the aircraft is registered due to differences in national implementation of the LSA...

Page 15: ... Maximum mass per seat 118 kg 260 lbs Typical Empty weight incl recovery system 310 kg 730 lbs Maximum take off weight MTOW 600 kg 1320 lbs Baggage compartment 25 kg 55 lbs maximum on each side 50 kg 110 lbs maximum in total Center of gravity range 282 478 mm 11 1 inches 18 8 inches Nominal empty weight with minimum equipment The true empty weight depends greatly upon the equipment installed The c...

Page 16: ...start conditions 7 0 bar 101 psi Oil grade brand automotive engine oils no aviation oil refer to the relevant ROTAX operating handbook for information on viscosity Do not use oil additives Oil tank capacity 2 0 3 0 l 2 1 3 1 quarts Oil consumption maximum 06 l h 06 q h Fuel tank capacity 130 l 34 gals 2 wing tanks with 65 l 17 gallons each Usable fuel 128 l 32 gallons Type of fuel Premium Automoti...

Page 17: ...n refer to the current version of the relevant engine manual from the Rotax company 2 6 Other limitations Warning The aircraft is not certified for aerobatics The aircraft may only be operated during the day or night in visual flight conditions Flight into instrument meteorological conditions IMC is prohibited Flight into icing conditions is prohibited Turns steeper than 60 degrees of bank are pro...

Page 18: ...ith these detailed procedures before starting flight operations Spinning Controls neutral Rudder opposite direction of rotation Rotation stopped Throttle retard Elevator smooth recovery from dive Deploying the ballistic recovery system Ignition off Recovery system release Fuel shutoff valve off Emergency radio call transmit Master switch off Safety harness tight protective position taken Engine fa...

Page 19: ...mperature below 150 C Landing as soon as possible at airfield Loss of oil Ignition off Ignition key remove Fuel shutoff valve off Landing make an emergency landing Failure of flap control Alternator off Master switch off Master switch after 3 seconds to on Alternator on If everything okay end of procedure Flaps in cruise flight manually set to max negative Long runway landing flap max negative Sho...

Page 20: ...during recovery is 60 m 180 ft The angle of bank does not exceed 60 3 3 Inadvertent spin The aircraft shows no inclination to go into an inadvertent spin during normal stall or during stalls in turns Should the aircraft however inadvertently enter into a spin the following recovery procedure should be used All control surfaces in neutral position Rudder opposite to direction of rotation Retard thr...

Page 21: ...ng flare it is recommended that the engine be shut down in order to reduce as far as possible the danger of a fire Ignition off Fuel shutoff valve closed On touchdown the stick should be pulled back smoothly to prevent as far as possible overturning on landing caused by the nose wheel sinking into soft ground Apply the brakes smoothly to bring the aircraft to a controlled stop During landings in c...

Page 22: ... shards from the windshield or broken parts of the structure when you drop out of the seat Evacuate the aircraft as quickly as possible Warning Check for leaking fuel when evacuating the aircraft acute fire hazard the fuel system is not designed for the upside down position Warning If urgent help is required after an emergency landing the ELT if installed can be activated manually thus alerting th...

Page 23: ...arning Read recovery system operation manual for mandatory information provided by the recovery system manufacturer Warning Once the recovery system is activated the pilot gives up all active control of the aircraft There is no possibility to release the parachute and return to aerodynamic flight Warning The activation of the rescue system depends on the situation and is in the pilot s decision On...

Page 24: ...e starter The Rotax 912 ULS engine ignition is only active once a certain minimum propeller rpm is achieved above 1200 rpm If the propeller is wind milling it may be that the propeller rpm is too low to restart the engine In this case the starter must be used Warning Restarting the engine requires the full attention of the pilot The stress factor in the cockpit increases considerably and simple mi...

Page 25: ...mergency landing similar to that without engine power If the flames have been extinguished and an emergency landing cannot be performed without engine power an attempt may be made to restart the engine should it indeed restart an emergency landing should be made immediately The deployment of the recovery system can be a good alternative If the aircraft has become uncontrollable during the fire or ...

Page 26: ...engine power should be reduced enough to ensure that the cylinder head temperature remains within normal operation limits below 150 C 302 F If airspeed becomes too low the flaps may be partially extended 0 15 The aircraft can then be flown to a suitable airfield without causing permanent damage to the engine If the temperature cannot be held within operating limits one must decide whether one is p...

Page 27: ...ator switch and the master switch off and then on again It is safe to do this in flight as engine ignition is independent from the aircraft s power supply Should this not work the flaps can be set manually by moving the flap selection lever past the detent up or down To set the flaps to negative the flap lever is moved past and above the 6 position Once the desired setting has been reached the lev...

Page 28: ...utomatically adversely affect flight safety However should the Dynon EMS fail completely engine parameters can no longer be monitored by the pilot In order to reduce the risk of damage to a minimum the flight may be continued but engine speed should be kept moderate 185 km h 100 kts cruise speed with negative flaps Sailplane towing or banner towing should be stopped when this failure occurs ...

Page 29: ... be used easily in the cockpit This booklet can be augmented with specific operational aspects including helpful local information The amplified procedures augment those points of the checklists which can only be explained in detail Self explanatory points will not be further dealt with Both sources checklists and amplified procedures should be used during normal operation 21 24 23 22 29 15 1 12 4...

Page 30: ...25 Rudder check cables bolts 26 Rudder ACL check 27 Tow release check 28 Tail navigation light check PREFLIGHT INSPECTION C Right side of aircraft 29 Horizontal tail check 30 Vertical stabilizer check 31 Fin check 32 Fuselage l check 33 Baggage compartment locked 34 Main landing gear and tirecheck D Right wing 35 Wing flap check 36 Aileron check 37 Winglet wing tip check vent clear 38 Navigation l...

Page 31: ...n 51 C 122 F Alternator control lamp off Throttle idle Flaps set Pitch trim set neutral for takeoff Radios set Recovery system unlocked pin out ELT armed continued BEFORE TAKE OFF continued Passenger briefing complete Approach departure clear Parking brake release NORMAL TAKE OFF Wing flaps 0 15 Carburetor heat off Throttle full Take off rpm 4800 5000 rpm Best rate of climb 120 km h 67 kts flaps 1...

Page 32: ...ttle idle Brakes as required Carburetor heat off Landing light off Wing flaps retract GO AROUND Throttle full Carburetor heat off Wing flaps 15 Airspeed 110 km h Rate of climb confirm positive rate SHUTTING DOWN THE ENGINE Parking brake set Avionics off Electrical equipment off Alternator off Ignition off Master switch off Ignition key remove Recovery system lock pin in ELT check off Passenger bri...

Page 33: ... risk The various propellers which can be installed in the CTLS are made of light weight composite materials In comparison to propellers from the General Aviation sector these propellers do not consist of a wooden core which has been covered with composite material Should such a full composite propeller be damaged then the entire load carrying structure is affected The propeller can no longer be u...

Page 34: ... during flight The door latching mechanism should be demonstrated Particular emphasis should be placed on the fact that the doors must be pulled firmly against the door seals before locking the doors in order to prevent the latches from jamming Deployment of the recovery system should be explained Passengers must be told of the importance of the handle in the middle console and how to operate it I...

Page 35: ...0 seconds after the engine starts to turn then slowly push shut Adjust the throttle as required The throttle must be closed full aft on lever during choke operation for mixture enrichment to function Since the engine has a propeller gearbox start up impact loads should be avoided When starting the engine the throttle should not be more than 10 open Once the engine starts to turn the throttle shoul...

Page 36: ...ffices under the prevailing conditions surface conditions wind humidity temperature The relevant checklist should be properly executed before each take off Small mistakes such as the wrong flap setting can lead to unanticipated developments during take off and quickly lead to problems for example on short runways with obstacles 4 7 Typical pattern The typical pattern can serve as a guidance for th...

Page 37: ...Aircraft Operating Instructions AOI Type CT Series CTLS LSA Page 4 9 AU 010 11000 Revision No 6 Date 05 Feb 2009 ...

Page 38: ...Aircraft Operating Instructions AOI Type CT Series CTLS LSA Page 4 10 AU 010 11000 Revision No 6 Date 05 Feb 2009 ...

Page 39: ...lot must look for an appropriate reference point Pilots used to flying other types of aircraft are often confused by the strongly tapered fuselage nose of the CTLS tending to take off and land with a lot of sideslip The pilot s view straight ahead is very much to the left At first this appears to be far too far to the left but it is indeed correct The point can be located by drawing a vertical lin...

Page 40: ... flaps from 15 to 0 The climb can then be continued at 132 km h 73 kts When this speed is exceeded the flaps can be further adjusted to 6 The aircraft can then climb further and efficiently at 140 km h 78 kts Warning When adjusting the flaps to the negative position the drag and lift co efficient of the airfoil are reduced for the same angle of incidence The aircraft must thus be accelerated durin...

Page 41: ...ark plugs which in turn adversely affects the smooth running of the engine and performance Warning Never put on carburetor heat during take off and climb as carburetor heat reduces engine performance During cruise fuel consumption should be monitored closely The Dynon EMS if installed shows current consumption total consumption since take off and remaining fuel quantity Warning In order to achieve...

Page 42: ...as returned to normal flight attitude and the amount of fuel inside and outside the anti sloshing rib has evened out 4 10 Turns Each heading change is flown coordinated in the CTLS with aileron and rudder The horizon is held level with the stabilizer Maximum permissible airspeed dependent upon the ballistic recovery system should never be exceeded Steep turns should not be flown particularly at lo...

Page 43: ...ly before touch down lead very quickly to dynamic flight conditions which are very stressful for the pilot If in doubt abandon the approach and perform a go around This is always better than taking a chance of damaging the aircraft due to a hard landing Some power 10 20 should be maintained during approach This makes it easier to determine that the engine is running properly and is able to provide...

Page 44: ...ight instructor familiar with the CTLS The increased flap deflection does not reduce the attainable minimum speed it does however greatly increase drag This permits very short landings but can also create a rapid loss of speed during the landing flare Flaring too high above the ground will cause the aircraft to drop In this case apply full power immediately for a go around and a new approach A go ...

Page 45: ... is switched off These instruments are therefore still active when the power supply is switched off Since they are independent from the aircraft power system no damage can occur when the engine is shut down 4 14 Checking the emergency location transmitter ELT After every landing and especially after parking the aircraft the ELT should be checked for accidental deployment Under certain unfavorable ...

Page 46: ...vement It does not make a noticeable difference on this aircraft Take off speed flaps 15 85 km h 47 kts CAS flaps 0 100 km h 54 kts CAS Best rate of climb flaps 15 120 km h 62 kts CAS 3 7 m s 740 ft min flaps 0 132 km h 73 kts CAS 4 0 m s 800 ft min flaps 6 140 km h 78 kts CAS 3 8 m s 770 ft min Best angle of climb flaps 15 110 km h 61 kts CAS approx 8 1 flaps 0 120 km h 66 kts CAS approx 8 1 Maxi...

Page 47: ...rmance of which varies according to ambient temperature and pressure This is the reason that density altitude is so important The aerodynamic characteristics of the aircraft are also dependent upon this parameter Density altitudes can easily be calculated using the following table Using this density altitude as the input parameter the performance which can truly be expected will be calculated in t...

Page 48: ...ference pressure of the altimeter set to standard atmosphere 1013 25 hPa 29 92 in Hg only The corresponding density altitude is 6800 ft or 2100 m Performance values are thus equivalent to those given in the next chapter for 2100 m If the pressure altitude of 2400 m 8000 ft were used the performance figures would be wrong This difference can be very significant particularly in the summer months whe...

Page 49: ...rocedure while on the other hand it ensures that the demonstrated permissible crosswind component for take off and landing is not exceeded The following diagram is used to determine the crosswind component Crosswind Taxi or Flight Direction Headwind Crosswind Taxi or Flight Direction Headwind An example is shown in the diagram Take off direction is 120 The wind direction is 070 wind speed 11 kts T...

Page 50: ...ticeable influence on the forward progress of the aircraft over ground in cruise The relevant components can be easily calculated from the graph Crosswind Headwind Crosswind Tailwind Taxi or Flight Direction Calculation procedures are analogous to those used to determine take off procedures the only difference being the possible inclusion of a tailwind component ...

Page 51: ...8000 1 10 4 1 2 10 4 1 4 10 4 1 6 10 4 1 8 10 4 2 10 4 0 1000 2000 3000 4000 5000 6000 50 power 5500 rpm 62 power 5500 rpm 75 power 5500 rpm 87 power 5500 rpm 100 power 5500 rpm 100 power 5800 rpm Engine Power at Altitude and Power Setting Power kW Density Altitude ft Density Altitude m 2500 3000 3500 4000 4500 5000 5500 6000 10 20 30 40 50 60 70 80 Power 100 Power 75 Power 100 5 000 ft Power 75 5...

Page 52: ...sity altitude Field elevation is not sufficient as this dies neither consider local day air pressure nor local temperature Both have noticeable effect to the takeoff performance Warning Don t forget that these are handbook methods which in practice are heavily dependent upon many factors and in particular from the way the take off is actually performed The values are based on an aircraft in good c...

Page 53: ...4000 4500 5000 0 200 400 600 800 1000 1200 1400 400 kg 880 lb 450 kg 990 lb 500 kg 1 100 lb 550 kg 1 210 lb 600 kg 1 320 lb Roll Distance at Mass and Density Altitude Roll Distance ft Density Altitude ft Density Altitude m 250 400 550 700 850 1000 1150 1300 1450 1600 1750 1900 2050 2200 0 500 1000 1500 2000 2500 3000 3500 4000 4500 5000 0 200 400 600 800 1000 1200 1400 400 kg 880 lb 450 kg 990 lb ...

Page 54: ...4 inclination of runway app 14 x 1 14 app 12 x 1 12 tail wind 5 kt app 20 x 1 2 app 25 x 1 25 wet snow app 30 x 1 3 n a soaked soil 1 2 in 3cm deep app 16 x 1 16 n a Each factor occuring at a time has to be considered individually Example Takeoff at 1 100 lb 500 kg at 68 F 20 C at 2000 ft 600 m pressure altitude in high grass with a runway 2 inclination As by chapter 5 2 density altitude for this ...

Page 55: ...s for the aircraft performance Climb performance at flaps 0 Aircraft weight 472 5 kg 1042 lbs Aircraft weight 600 kg 1320 lbs density alt ft rate of climb ft min rate of climb m s at CAS kts km h rate of climb ft min rate of climb m s at CAS kts km h 0 1000 5 0 72 130 800 4 0 73 132 5 000 720 3 6 71 128 520 2 6 72 130 10 000 500 2 5 69 125 260 1 3 71 128 12 000 400 2 0 68 122 120 0 6 69 126 15 000...

Page 56: ...ctivity can prolong these distances Turbulence however usually leads to a reduction in gliding distance One should never expect favorable conditions when estimating a possible gliding distance Glide angle of the CTLS can be assumed in practice to be 8 5 to 1 With flaps extended this ratio gets worse One effect of moderately set flaps is to reduce the minimum sink but the speed at which the minimum...

Page 57: ...dge on the outer side of the root rib The transition to the fuselage is faired in the root rib area which can lead to an incorrect measurement The distance between the wheels must be measured during each weighing These values must be then be used in the tabulation If the original Flight Design weighing form is used as a spread sheet the distances must be recorded with a positive algebraic sign If ...

Page 58: ...al weight Deductions Empty Weight and cg Grey fields require inputs Weight and Balance of LSA Aircraft Signature Fedchun Kherson Ukraine City Engine Number Equipment list with date Scaling and Empty Aircraft cg Wing leading edge Tunnel roof in cabin horizontal Datum Point Weight of non lifting parts 700 62 lb Max weight of non lifting parts 1144 18 lb Summary Certification Basis Data of Aircraft A...

Page 59: ...ry trim ballast weight should be installed The weighing record is only valid in connection with the current equipment list Any changes to the aircraft must be appropriately registered It is also possible that national regulations require weighing to be carried out at specified intervals or after specified work on the aircraft It is the responsibility of the owner to conform to such national requir...

Page 60: ...r CTLS Mass kg lb Mass Moment kg m in lb Mass kg lb Mass Moment kg m in lb 1 Empty mass mass moment from most recent valid Weight and Balance Report 318 701 107 1 9 318 2 Combined pilot and passenger mass on front seats Lever arm 0 52 m 20 5 in 85 190 44 2 3 895 3 Mass loaded to luggage compartment behind the cabin Lever arm 1 140 m 45 in 12 25 13 7 1 125 4 Mass loaded to luggage compartments in f...

Page 61: ...oments of the individual positions To obtain the value select the correct weight or volume on the vertical axis Go horizontally to the intersection with the correct loading graph Go vertically down to the horizontal axis to obtain the mass moment value Enter this mass moment value to the correct line in the analysis table above The next chart Permissible Moment Range allows you to verify if your a...

Page 62: ...0 15 10 US gal Fuel Quantity Seats Fuel Tank Luggage 10 20 30 40 50 60 70 80 90 100 110 120 130 kg m 10 10 20 30 40 50 60 70 80 90 100 110 120 130 kg m 10 Footroom Storage Loading Diagram 25 225 200 175 150 125 100 75 50 250 kg 25 225 200 175 150 125 100 75 50 250 kg 100 500 450 400 350 300 250 200 150 550 lb 50 0 1 000 2 000 3 000 4 000 5 000 6 000 7 000 8 000 9 000 10 000 11 000 in lb 1 000 0 1 ...

Page 63: ...s 0 2 8 2 m 1 1 1 i n Permissible Moment Range 0 4 7 8 m 1 8 8 i n 0 3 0 0 m 1 1 8 i n 0 3 5 0 m 1 3 8 i n 0 4 0 0 m 1 5 7 i n 0 4 5 0 m 1 7 7 i n 800 1 200 1 150 1 100 1 050 1 000 950 900 850 1 350 lb 750 700 660 1 300 1 250 8 000 10 000 12 000 14 000 16 000 18 000 20 000 22 000 24 000 26 000 in lb 8 000 10 000 12 000 14 000 16 000 18 000 20 000 22 000 24 000 26 000 in lb 625 f o r w a r d l i m ...

Page 64: ...0 46 0 48 0 50 mm 0 28 Center of Gravity Flight Mass Permissible CG Range 375 575 550 525 500 475 450 425 400 600 kg 350 325 300 0 26 forward limit 282mm 11 1 in rear limit 478 mm 18 8 in max permitted flight mass 600 kg 1320 lb 625 800 1 200 1 150 1 100 1 050 1 000 950 900 850 1 350 lb 750 700 660 1 300 1 250 11 12 13 14 15 16 17 18 19 in The example shown in this diagram represents the verificat...

Page 65: ...the equipment The owner of the aircraft is responsible for ensuring that the equipment list is current The equipment list includes options which are not certified in all the countries in which the CTLS may be operated It is the responsibility of the owner to ensure that national regulations are followed for example with respect to the ballistic recovery system and the autopilot The equipment list ...

Page 66: ...Aircraft Operating Instructions AOI Type CT Series CTLS LSA Page 6 10 AU 010 11000 Revision No 6 Date 05 Feb 2009 ...

Page 67: ...zontal tail by means of a composite membrane which provides an aerodynamically clean attachment to the anti servo tab The spacious cockpit is comfortably accessible to the pilot and passenger via two large doors held open by gas struts The extensive acrylic windshield offers for a high wing aircraft outstanding visibility The rear side windows which have been added to the CTLS allow rearward visio...

Page 68: ...nature of composite materials and the necessary knowledge in the lay up of a specific structure repair work on the composite airframe may only be undertaken by a qualified facility For this reason only general information about the materials used is given in this handbook Should the aircraft structure be damaged detailed information must be requested from the manufacturer Carbon aramide glass fibe...

Page 69: ...aking it no longer controllable The baggage compartment in the fuselage barrel behind the pilots seats has a maximum payload of 25 kg 55 lbs on each side Inside each of the compartments hooks are attached to the fuselage walls with the help of which baggage can be secured The hat rack offers storage space for small and flat objects only The size of the object may not exceed 25 cm x 25 cm x 8 5 cm ...

Page 70: ...or the oil and water cooling systems Air is fed into the engine via an aluminum air box which fills both carburetors with equal volumes Fresh air is fed into the system via a cylinder air filter attached to the fire wall in an expanding chamber The expanding chamber is supplied by a NACA air inlet located on the right side of the lower cowling When the carburetor heat is on air flow into the alumi...

Page 71: ...monitoring of the correct propeller speed in flight very simple for the pilot Both variable pitch propellers are controlled via a hydraulic adjustment mechanism The lever is located in the central instrument panel behind the power quadrant The lever has several indexed positions To set the propeller the notch under the lever is released the lever moved to the desired position and the notch locked ...

Page 72: ...the upper winglets The vent tube is led through the tank in a loop along the upper wing skin along the main spar In this way the risk of fuel escaping into the vent tubes should the aircraft be parked with a wing low is minimised As the vent tubes left and right are coupled equal pressure prevails in both tanks even when the winglets experience different flow conditions Each tank outlet has a coar...

Page 73: ...in winglet Tank vent connection left right Right wing Flapper valve Flapper valve Sloshing rib with ventilation Tank ventilation A pillar left A pillar right Carburetors 2 Fuel pump engine driven Gascolator Firewall Fuel fine filter Flowmeter Fuel shutoff valve Sloshing rib with ventilation Tank ventilation X Filler cap Filler cap Coarse fuel inlet filters Fuel backflow NACA nozzle in winglet Drai...

Page 74: ...ged If properly maintained it has a very long service life Power is distributed via a common power bus which the fuses and circuit breakers of the individual instrument groups are directly connected Power is then transferred to the instruments and avionics using switches where necessary All ground lines are connected to the battery via a ground bus The avionics are grounded separately from the res...

Page 75: ...Aircraft Operating Instructions AOI Type CT Series CTLS LSA Page 7 9 AU 010 11000 Revision No 4 Date 29 Apr 2008 Block diagram power supply ...

Page 76: ...t Operating Instructions AOI Type CT Series CTLS LSA Page 7 10 AU 010 11000 Revision No 4 Date 29 Apr 2008 Block diagram avionics installation without VOR HS34 Block diagram avionics installation with VOR HS34 ...

Page 77: ...e middle console in the cockpit directly behind the throttle quadrant The parking brake can be locked before activating the brakes The brakes can then be activated once through the check valve The check valves keep the system under pressure thus making single hand operation of the parking brake simple Warning This does not however mean that chocks are not needed when the aircraft is parked Changes...

Page 78: ...this seat Thanks to the dual controls the aircraft is well equipped for training and instruction 7 3 2 Rudder and nose wheel steering The rudder is activated via control cables which are housed in a plastic sleeve in the tunnel on the fuselage floor The left and right foot pedals are coupled in the tunnel The turnbuckle units to tension the cables and the connection to the nose wheel steering are ...

Page 79: ...inge It is activated through a mechanical coupling when the stabilizer is deflected In this way the anti servo tab deflects in the opposite direction as the stabilator thus improving stabilator effectiveness and generating a proper force gradient on the control stick Warning When dismounted or when the controls are disconnected the anti servo tab must never be pushed beyond normal operating limits...

Page 80: ...rim indicator is located directly adjacent to the wheel The aircraft becomes nose heavy when the wheel is rotated forward and tail heavy when it is turned backward Via a Bowden cable the trim wheel activates a threaded spindle at the stabilator pivot bearing This spindle is self locking and adjusts the zero position of the anti servo tab Since the anti tab has a large span the required deflection ...

Page 81: ...wing diagram depicts the aileron controls orange and flap controls turquoise in the fuselage with mixer and with connection to the wings The aileron controls have return springs which ensure more harmonic force gradients These springs are attached to the rear of the main bulkhead and engage in the mixer 7 3 6 Aileron trim Aileron trim is activated by a trim wheel in the middle of the tunnel betwee...

Page 82: ...ng An individual maximum airspeed is defined for each wing flap setting The pilot must observe these to ensure that the aircraft and the flight controls are not over stressed The flap servo has an internal load limiting device which prevents the extension of the flaps at too high airspeeds without causing sustainable damage to the structure Should the indicator blink constantly when extending the ...

Page 83: ...turer has posted on its website Some of the videos show real life deployment filmed from the cockpit and illustrate well just how useful this system can be in doubtful situations The ballistic recovery system comprises a recovery parachute and a ballistic rocket which are located in the upper baggage compartment above the controls mixer behind the main bulkhead The rocket is activated via a pull c...

Page 84: ...hese belts through the roof In very rare cases extreme low aircraft weight and at stall speed it might happen that the belts do not tear open the aircraft roof In this case the aircraft will come down with little more pitch down and the rear belt not tightened Experience from a real CT ejection has shown this is a proper descent position The following picture shows the installation of the two vari...

Page 85: ...Aircraft Operating Instructions AOI Type CT Series CTLS LSA Page 7 19 AU 010 11000 Revision No 7 Date 07 May 2009 ...

Page 86: ...ercom Standardized numbering of equipment based on the table below is used for the diagrams on the following pages 1 EFIS Dynon 100 electronic flight information system 2 EMS Dynon 120 engine monitoring system 3 Autopilot CT Pilot 1 axis 2 axis 2 axis w vertical speed control 4 Back up airspeed indicator D 57 mm 2 1 4 5 not used 6 Back up altimeter D 57 mm 2 1 4 7 not used 8 not used 9 Slip indica...

Page 87: ...Type CT Series CTLS LSA Page 7 21 AU 010 11000 Revision No 4 Date 29 Apr 2008 7 4 2 Upper panel Panel with Glass cockpit without NAV radio Panel with Glass Cockpit with NAV radio 12 13 11 2 1 3 4 6 14 16 17 12 13 11 2 1 3 4 6 15 16 17 18 ...

Page 88: ...uit Breakers All circuit breakers except the circuit bearker for the flap controller which is located directly next to the flap controller are located in the lower part of the upper right panel Depending from the actual aircraft equipment these are installed The following illustration shows the order of the circuit breakers ...

Page 89: ...er panel varies only slightly If no avionics are installed there is no intercom Otherwise the controls and switches are always configured as shown below Fuel shutoff Alternator switch Flap selection switch Flap circuit breaker Flap position indicator Audio input jack Intercom Switches panel Master switch Ignition ELT remote control Selector XM or AUX music ...

Page 90: ...vision No 4 Date 29 Apr 2008 7 4 5 Throttle quadrant The throttle quadrant is located in the middle console tunnel in front of the lower instrument panel It can be easily operated from both seats although it is primarily designed to be operated from the left seat by the pilot in command ...

Page 91: ...en Danger Dark Blue The Quantum Eye is a multi level Carbon Monoxide Detector It provides a visual indication of carbon monoxide contamination Each detector is packaged in a protective bag that when opened activates it Once activated the minimum product lifetime is 18 months Adhesive backing allows it to be easily mounted in the cockpit or any clearly visible surface Operating temperature range is...

Page 92: ...il pressure indicator Red line 266 F 130 C oil temperature indicator Red line 248 F 120 C water temperature indicator Metal identification plate on the airframe inside the engine compartment or the left side rear fuselage near the stabilator Calibration card after calibration below the compass Warnings and load limits upper half central instrument panel Warnings left instrument panel Take off chec...

Page 93: ... handbook recovery system handbook and on recovery system Baggage payload Posted on both sides of the baggage compartment Baggage payload hat rack Posted on both sides of the hat rack at the back Warning Posted on all sides of the baggage compartment Door opening instructions Posted on the outside of each door Posted on the inside of each door handle Warning Danger Parachute recovery system hatch ...

Page 94: ...is placed under the lower end of the landing gear strut The wheel can now be removed When work must be carried out on the nose wheel the aircraft remains standing on the main wheels Using the tail tie down belt and ballast e g a jerry can filled with water the tail is held down until the nose wheel is free Alternatively the aircraft can be jacked exactly under the firewall bulkhead making sure tha...

Page 95: ...separate CTLS LSA maintenance manual 8 3 Parachute recovery system maintenance The parachute recovery system requires no maintenance except observance of the pack intervals for the parachute and the exchange intervals for the rocket These intervals are recorded in the recovery system handbook The recovery system should only be removed from the aircraft by an authorized workshop Depending upon nati...

Page 96: ...e the Rohacell foam core to disintegrate if they penetrate to the core A rippled surface is an indication of such disintegration Components damaged in this way cannot be repaired and have to be replaced The wing spars of the CTLS cannot be damaged in this way Products from the ComposiClean series which has been specially developed for aircraft made of composite materials are approved as cleaning a...

Page 97: ...commends the use of a standard degreaser Please follow the instructions given in the operating handbook and make sure that the degreaser does not come in contact with the airframe Warning If a moisture based cleaning agent is used on the engine the electronics must be protected from getting damp High pressure cleaning devices should never be used to clean the engine ...

Page 98: ...erved Provision is made for these items in the 100 h and 200 h inspection lists The current maintenance list as required by the engine manufacturer is mandatory for engine maintenance The inspection items listed here only give a general indication of the condition of the installation as a whole not of the engine itself These inspections do not supersede any mandatory airworthiness inspections requ...

Page 99: ...arning Anti freeze from different manufacturers must not be mixed as they may react with each other and flocculate If in doubt the mixture should be completely drained off and replaced Flight Design uses BASF Protect Plus as recommended by Rotax If the anti freeze is changed an aluminum compatible anti freeze recommended by Rotax should be used Warning Flight Design advises against the use of Evan...

Page 100: ...ing flaps greatly influence aircraft characteristics The correct surface deflections are defined within the Aircraft Maintenance Manual The aileron flap mixer system is highly sensitive to adjustments in the control elements Modifying the adjustment of a bellcrank may change the mixing function All adjustments to the control system must be done according to Flight Design specifications We therefor...

Page 101: ...wing of gliders is therefore not permitted Warning Even when the towing hook is already installed to the aircraft towing of sailplanes is not permitted with the CTLS LSA Your local Flight Design Dealer can inform you when the system is ready tested and released for use This requires replacement of this chapter of the AOI against the released version containing all operation limitations and procedu...

Page 102: ...ng of banners is therefore not permitted Warning Even when the towing hook is already installed to the aircraft towing of banners is not permitted with the CTLS LSA Your local Flight Design Dealer can inform you when the system is ready tested and released for use This requires replacement of this chapter of the AOI against the released version containing all operation limitations and procedures f...

Page 103: ... 11 1 CURRENT WEIGHING REPORT The current weighing report should be inserted here Old weighing reports should be kept so that the history of the aircraft is properly documented They should be marked by hand with the word INVALID The owner of the aircraft is responsible for ensuring that a valid weighing report is made available ...

Page 104: ... 2 CURRENT EQUIPMENT LIST The current equipment list should be inserted here Old equipment lists should be kept so that the history of the aircraft is properly documented They should be marked by hand with the word INVALID The owner of the aircraft is responsible for ensuring that a valid equipment list is available ...

Page 105: ...Aircraft Operating Instructions AOI Type CT Series CTLS LSA Page 11 3 AU 010 11000 Revision No 4 Date 29 Apr 2008 11 3 SAFETY OF FLIGHT REPORT FORM ...

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