DYNAMIC WT 9 FLIGHT MANUAL

Flap span……….............................................2,28 m Flap area……..................................................0,75 m2 Horizontal tail span……………….…….........2,40 m Horizontal tail area…………………...............1,68 m2 Vertical tail span………………...............…....1,022 m Vertical tail area……………….................….. 1,02 m2 Landing gear Wheel spacing.……………………............…. 1,49 m Wheel base..................................................…. 2,27 m Main wheel diameter……………................…0,35 m Nose wheel diameter…………………………0,32 m Weights Empty weight with fixed undercarriage…..……..259 kg Empty weight with retractable undercarriage…....270 kg Maximum take-off weight…….....................…….450 kg Useful load……….....................................…….....190 kg Fuel tanks capacity………….................................75 or 126 litres The ROTAX 912 UL (59,6 kW) or ROTAX 912 ULS( 73 kW ) has a maximum rpm limitation on take off of 5800 1/min 912 UL, 5/min 912 ULS. The Woodcomp SR 2000 or Rospeller are 3 bladed in-flight electricaly adjustable propellers. Propeller diameter is 1,7 m. Date: 1.12.2001 DYNAMIC WT 9 FLIGHT MANUAL Section 1 Page 1-3 1.5 Three – view drawing Date: 1.12.2001 DYNAMIC WT 9 FLIGHT MANUAL Section 2 Page 2-1 SECTION 2 LIMITATIONS Page 2.1 Introduction 2-1 2.2 Airspeed 2-1 2.3 Airspeed indicator markings 2-2 2.4 Power plant 2-2 2.5 Power plant instrument markings 2-3 2.6 Miscellaneous instrument markings 2-6 2.7 Weight 2-7 2.8 Centre of gravity 2-7 2.9 Approved manoeuvres 2-7 2.10 Manoeuvring load factors 2-8 2.11 Flight crew 2-8 2.12 Kinds of operation 2-8 2.13 Fuel 2-8 2.14 Maximum passenger seating 2-9 2.15 Other limitations 2-9 2.16 Limitations placards 2-9 2.1 Introduction Section 2 includes operating limitations, instrument markings, and basic placards necessary for safe operation of the aeroplane, its engine, standard systems and standard equipment. The limitations included in this section and in Section 9 have been approved by the Civil Aviation Authority of the Slovak Republic. 2.2 Airspeed Airspeed limitations and their operational significance are shown below: IAS Speed km/h MPH knots Remarks VNE Never Exceed speed 280 174 150 Do not exceed this speed in any operation VNO Normal Operating Limit speed 250 156 135 Do not exceed this speed except in smooth air, and then only with caution VRA Rough Air speed 230 143 124 Do not exceed this speed except in smooth air. Air movements in lee-wave rotors, thunderclouds, visible whirlwind, or over mountain crests are to be understood as rough air Date: 1.12.2001 Change: 8.12.2003 „Appr“ DYNAMIC WT 9 FLIGHT MANUAL Section 2 Page 2-2 IAS Speed km/h MPH knots Remarks VA Manoeuvring speed 165 103 88 Do not make full or abrupt control movement above this speed, because under certain conditions the aircraft may be overstressed by full control movement VFE Maximum Flap Extended speed 140 88 75 Do not exceed these speeds with the given flap setting. VLO Maximum Landing Gear Operating Speed 140 88 75 Do not extend the landing gear above this speed. VLE Maximum Landing Gear Extended Speed 250 156 135 Do not exceed this speed with the landing gear extended. 2.3 Airspeed indicator markings Airspeed indicator markings and their colour-code significance are shown below: IAS value or range Marking km/h MPH knots Significance White arc 65 – 140 40 - 88 35 - 75 Positive Flap Operating Range. ( Lower limit is maximum weight 1.1 VSO in landing configuration. Upper limit is maximum speed permissible with flaps extended positive.) Green arc 70 – 230 43 - 143 37 - 124 Normal Operating Range. ( Lower limit is maximum weight 1.1 VS1 at most forward c.g. with flaps and landing gear retracted ( if retractable ). Upper limit is VRA . Yellow arc 230 – 280 143 - 174 124 - 150 Manoeuvres must be conducted with caution and only in smooth air. Yellow triangle 100 62 53 Minimum Approach speed Yellow line 165 103 88 VA Manoevring speed Red line 280 174 150 Maximum speed for all operations. 2.4 Powerplant Engine Manufacturer: ROTAX-Bombardier, Gunskirchen Engine Models: ROTAX 912 UL , ( ROTAX 912 ULS ) Maximum Power - Take-off: 59,6 kW / 80 HP ( 73,5 kW / 100 HP ) Continuous: 58 kW / 77,8 HP ( 69 kW / 93,8 HP ) Maximum Engine Speed – Take-off: 5800 1/min ( 5 min ) Continuous: 5500 1/min Maximum Cylinder Head Temperature: 150 ° C ( 135 ° C ) ( reading FLYdat CHT ) Maximum Oil Temperature: 140 ° C ( 130 ° C ) ( reading FLYdat OIL TEMP ) Oil Pressure: Minimum: 0,8 bar ( 12 psi ) Maximum: 7 bar ( 102 psi ) Fuel Pressure: Minimum: 0,15 bar ( 2.2 psi ) Maximum: 0,4 bar ( 5.8 psi ) Fuel Grade: the following fuels can be used: min. RON 95 Date: 1.12.2001 Change: 8.12.2003 „Appr“ DYNAMIC WT 9 FLIGHT MANUAL Section 2 Page 2-3 − EN 228 Premium − EN 228 Premium plus − Unleaded Automobile Gasoline AVGAS 100 Due to the higher lead content in AVGAS, the wear of the valve seats, the deposits in combustion chamber and lead sediments in the lubrication system will increase. Therefore, use AVGAS only if you encounter problems with vapour lock or if the other fuel types are not available. Oil Grade: motorcycle oil of a registered brand with gear additives. Use only oil with API classification „SF“ or „SG“! If using aircraft engine oil, then only blended one. Due to the high stresses in the reduction gears, oils with gear additives such as high performance motor cycle oils are required. Heavy duty 4-stroke motor cycle oils meet all the requirements. These oils are normally not mineral oils but semi- or full synthetic oils. , Oil capacity: 3,0 litre Minimum: 2,0 litre Oil consumption: max. 0,1 l/h WARNING Never use AVGAS, LB 95 with fully synthetic engine oils. Propeller Manufacturer: WOODCOMP Propeller Model: SR 2000, 3 blade, in flight electrically adjustable aircraft propeller Propeller Diameter: 1,7 m Propeller Blade Angle ( at 75 % station): 10 o from minimum angle - for engine ROTAX 912 UL: 15° / 25° - for engine ROTAX 912 ULS: 19,5° / 29,5° Time Between Overhaul ( TBO ) : 1200 hrs or 15 years ( whichever comes first ) Additional data can be found in Section 7, Subpart 7.9, in the Operator’s Manual for engine ROTAX 912 UL / 912 ULS and in the User’s Guide for electric variable pitch propeller SR 2000 or Rospeller propeller. WARNING Never run the engine without propeller, this inevitably causes engine damage and is an explosion hazard. 2.5 Powerplant instrument markings According to customer requirement, either round one–purpose needle instruments or multiple instrument FLYdat are fitted in the instrument panel. The FLYdat represents an instrument especially developed for ROTAX aircraft engines for indication and acquisition of engine operating data readily accessible for the pilot. The operating data is permanently compared with the engine specific operating limit. If the signalled operating data exceeds the stored operating limit, the FLYdat will warn the pilot by the warning light ( annunciator ). Date: 1.12.2001 „Appr“ DYNAMIC WT 9 FLIGHT MANUAL Section 2 Page 2-4 FLYdat indications and their significance are shown below: Display field Designation Unit Resolution 1 Engine speed rpm 1 2 Hours of operation h 0,1 3 Exhaust gas temperature cylinder PTO* oC or oF 1 4 Exhaust gas temperature cylinder MS** oC or oF 1 5 Cylinder head temperature oC or oF 1 6 x) 7 Oil temperature oC or oF 1 8 Oil pressure bar 0,1 x) Arrow indicating the line of cylinders from which the exhaust gas temperature is picked up. Arrow denotes left line of cylinders Arrow denotes right line of cylinders * Cylinder PTO is at power take off side ** Cylinder MS is at the magneto side The FLYdat has been configured for ROTAX 912 UL engine by the manufacturer. The following warn- and alarm limits are stored: Display Unit Warn limit Alarm limit Engine speed rpm 5 800 6 000 Exhaust gas temperature EGT oC 880 900 Cylinder head temperature CHT oC 150 160 Oil temperature oC 140 150 Oil pressure maximum bar 6,0 8,0 Oil pressure minimum bar 2,0 1,0 Date: 1.12.2001 „Appr“ DYNAMIC WT 9 FLIGHT MANUAL Section 2 Page 2-5 The FLYdat has been configured for ROTAX 912 ULS engine by the manufacturer. The following warn- and alarm limits are stored: Display Unit Warn limit Alarm limit Engine speed rpm 5 800 6 000 Exhaust gas temperature EGT oC 880 900 Cylinder head temperature CHT oC 135 150 Oil temperature oC 130 145 Oil pressure maximum bar 6,0 8,0 Oil pressure minimum bar 2,0 1,0 Distinguish between three ranges of readings control: Colour range Significance Green ( standard operation ) All readings are below or above ( min. oil pressure ) the warn limits programmed. Yellow ( exceeding of warn limits ) If one or more readings exceed the programmed warn limit, then the readings appears flashing on the display , and simultaneously the alarm output is periodically ( 0,25 sec. ) switched on and off, until no readings exceed warn limit. Red ( exceeding of alarm limits ) If one or more readings exceed the programmed alarm limit, then the readings appear flashing on the display and simultaneously the alarm output is permanently activated until no reading exceeds the warn limit. If one or more alarm limits have been exceeded, or the reading on the meter of the operating hours has surpassed the programmed TBO, the maintenance message reads as follows: „Service !“ . CAUTION Disregard of the warn- and alarm signals might result in injuries or endanger the life of operator or third party. BOMBARDIER-ROTAX as manufacturer, warrants every FLYdat for a period of not more than 9 consecutive months for private use owners or 12 consecutive months from date of shipment of the manufacturer or the first 150 operation hours. Date: 1.12.2001 „Appr“ DYNAMIC WT 9 FLIGHT MANUAL Section 2 Page 2-6 Powerplant instrument markings and their colour code significance are shown below: Instrument Unit Red Line Minimum Limit Green Arc Normal Operating Yellow Arc Caution Range Red Line Maximum Limit Tachometer rpm 1 400 1 800 – 5 500 5500–5800 5 800 Oil temperature indicator oC 50 90 – 110 50 – 90 110 – 1401) 110 – 1302) 140 1) 130 2) Cylinder-head temperature indicator oC 150 1) 135 2) Fuel-pressure indicator bar 0,15 0,5 Oil-pressure indicator bar 1,5 1,5 – 5 5 – 7 7 Fuel indicator l Red light annunciator above the fuel indicator will be illuminated with the remaining fuel of 7 litre in each fuel tank. 1) Indication is valid for ROTAX 912 UL engine 2) Indication is valid for ROTAX 912 ULS engine 2.6 Miscellaneous instrument markings According to option of the customer miscellaneous instrument can be mounted. The following miscellaneous instrument markings and their colour code significance are shown below: Instrument Unit Red Line Minimum Limit Green Arc Normal Operating Yellow Arc Caution Range Red Line Maximum Limit Boost-pressure gauge kPa x 100 0,58 – 1,16 1,16 – 1,2 1,2 Acceleration indicator G - 2 + 4 Fuel reserve indicator Red light annunciator above the fuel indicator will be illuminated with the remaining fuel of 7 litre in each fuel tank. Date: 1.12.2001 „Appr“ DYNAMIC WT 9 FLIGHT MANUAL Section 2 Page 2-7 2.7 Weight Empty weight - with fixed undercarriage …………….....269 kg - with tow system.......................................272 kg - with retractable undercarriage …..……...285 kg Note: 30 kg is rescue and towsystem weight NOTE Due to different equipment in each aircraft, the actual empty weight is included in the Section 6. Maximum take-off weight....……...............…….450 kg Maximum landing weight ……................………450 kg Maximum zero fuel weight……..................…….400 kg Useful load ………........................................……200 kg Maximum fuel weight ……............................…….50 or 91kg Maximum crew weight……….....................…….190 kg Minimum crew weight……….............……............77 kg Maximum weight in Baggage Compartment…...... 10 kg WARNING Maintain maximum take off weight 450 kg Depending on different countries rules 2.8 Centre of gravity Position of C.G.: Empty airplane.....................................12 ± 2% MAC Position of C.G. in flight…..................20 ÷ 30% MAC Aft centre of gravity limit is valid for en-route weight at maximum crew weight. Forward centre of gravity limit is valid for minimum pilot weight 77 kg and minimum capacity of the fuel tanks. Example to check the centre of gravity position is in Section 6. 2.9 Approved manoeuvres DYNAMIC WT9 is certified in the Normal Category – Ultralight aircraft. The following manoeuvres are permited: − Steep turns with the angle of bank up to 60° - appropriate entry speed is 140 km/h. − Lazy eighths - appropriate entry speed is 140 km/h. − Combat turns - appropriate entry speed is 200 km/h. WARNING Aerobatic manoeuvres and intentional spins are prohibited! Date: 1.12.2001 „Appr“ DYNAMIC WT 9 FLIGHT MANUAL Section 2 Page 2-8 2.10 Manoeuvring load factors Speed Manoeuvre speed km/h MPH knots Load factors VA- Manoeuvring speed 165 103 88 + 4 VNE – Never exceed speed 280 174 150 + 4 VA – Manoeuvring speed 165 103 88 -2 VNE – Never exceed speed 280 174 150 -2 VFE – Maximum Flap Extended speed 140 88 75 + 2 2.11 Flight crew The minimum flight crew with which the airplane is allowed to fly is one pilot sitting in the left pilot seat. The passenger or another pilot may occupy the right seat in the cockpit. 2.12 Kinds of operation The ultralight aircraft DYNAMIC WT9 is approved to perform flights in accordance with VFR only. Aerobatic manoeuvres and intentional spins are prohibited! WARNING IFR flights and flights in icing conditions are prohibited. For flight operations the following minimum equipment must be installed: - Magnetic compass - Sensitive barometric altimeter - Airspeed indicator - Pilot’s Safety belts 2.13 Fuel The following fuels can be used for the ultralight aircraft DYNAMIC WT9: - EUROSUPER ROZ 95 unleaded accordance DIN 516 07 and O NORM 1100, Unleaded Automobile Gasoline Super 95 - Leaded Automobile Gasoline Super 95 accordance DIN 516 00 O NORM 1100, - AVGAS 100 LL. Due to the higher lead content in AVGAS, the wear of the valve seats, the deposits in combustion chamber and lead sediments in the lubrication system will increase. Therefore, use AVGAS only if you encounter problems with vapour lock or if the other fuel types are not available. Date: 1.12.2001 „Appr“ DYNAMIC WT 9 FLIGHT MANUAL Section 2 Page 2-9 Left tank ( l ) Right tank ( l ) The total quantity of fuel in the tank 37,5 or 63 37,5 or 63 Unusable fuel in the tank 1,9 or 2,9 1,9 or 2,9 The total usable quantity of fuel in the tank 35,6 or 60,1 35,6 or 60,1 2.14 Maximum passenger seating The maximum number of passenger aboard is one passenger sitting in the right seat in the cockpit. 2.15 Other limitations The maximum crosswind component limit according to the airworthiness requirements for take off and landing is 6 m/s, 12 knots. NO SMOKING on board the ultralight aircraft. Maximum towing cable load is 3.000 N. If the strength of tow cable is more than 3000 N a weak link must by used. Maximum weight of towed glider is 525 kg. Maximum weight of towing aircraft by 1 pilot occupation is 440 kg. 2.16 Limitations placards Airspeed IAS km/h MPH knots Never Exceed speed VNE 280 174 150 Normal Operating Limit speed VNO 250 156 135 Rough Air speed VRA 230 143 124 Manoeuvring speed VA 165 103 88 Maximum Flap Extended speed VFE 140 88 75 Maximum Landing Gear Operating speed VLO 140 88 75 Aerobatics, intentional spins and stalls are prohibited! IFR flights and flights in icing conditions are prohibited ! Date: 1.12.2001 „Appr“ DYNAMIC WT 9 FLIGHT MANUAL Section 2 Page 2-10 Fixed undercarriage for 75 liters tank Maximum allowed filling of the fuel tanks in litres Crew weight (kg) Baggage weight (kg) 70 80 130 140 150 160 170 180 190 0 Full tanks 62 48 34 20 7 5 Full tanks 69 55 41 27 13 0 10 Full tanks 62 48 34 20 7 0 With tow system for 75 liters tank Maximum allowed filling of the fuel tanks in litres Crew weight (kg) Baggage weight (kg) 70 80 130 140 150 160 170 180 190 0 Full tanks 70 57 43 31 17 3 5 Full tanks 64 50 38 24 10 0 10 Full tanks 57 43 31 17 3 0 Retractable undercarriage for 75 liters tank Maximum allowed filling of the fuel tanks in litres Crew weight (kg) Baggage weight (kg) 70 110 120 130 140 150 160 170 179 0 Full tanks 69 56 42 28 14 1 5 Full tanks 63 49 35 21 7 0 10 Full tanks 69 56 42 28 14 0 0 Retractable undercarriage with tow system for 75 liters tank Maximum allowed filling of the fuel tanks in litres Crew weight (kg) Baggage weight (kg) 70 110 120 130 140 150 160 170 180 0 Full tanks 65 52 38 24 10 0 5 Full tanks 58 45 31 17 3 0 10 Full tanks 65 52 38 24 10 0 0 NOTE Due to different equipment in each aircraft, the actual empty weight is included in the Section 6. And actual Fuel filling table can be different. Date: 1.12.2001 „Appr“ Maximum Baggage weight 10 kg DYNAMIC WT 9 FLIGHT MANUAL Section 3 Page 3-1 SECTION 3 EMERGENCY PROCEDURES Page 3.1 Introduction 3-1 3.2 Engine failure 3-1 3.3 Air start 3-2 3.4 Smoke and fire 3-2 3.5 Glide 3-3 3.6 Landing emergency 3-3 3.7 Recovery from unintentional spin 3-4 3.8 Other emergencies 3-5 3.1 Introduction Section 3 provides checklist and amplified procedures for coping with emergencies that may occur. Emergencies caused by aeroplane or engine malfunction are extremely rare if proper preflight inspections and maintenance are practised. However, should an emergency arise, the basic guidelines described in this section should be considered and applied as necessary to correct the problem. 3.2 Engine failure 3.2.1 Engine failure at take-off run 1. Throttle lever - set to idle position 2. Ignition - both circuits switched off 3. Brakes - apply till stop 3.2.2 Engine failure at take-off up to height 50 m 1. Airspeed - modify to 120 km/h 2. Field selection - land straight ahead no more than 15° left or right into wind if possible. Ground loop if required. 3. Ignition - both circuits switched off 4. Main fuel cock - close 3.2.3 Engine failure at take-off above height 50 m 1. Airspeed - modify to 120 km/h 2. Field selection - select in the direction of the free area without obstacles, if possible into wind 3. Ignition - both circuits switched off 4. Main fuel cock - close 5. Flaps - extend as required Date: 1.12.2001 „Appr“ DYNAMIC WT 9 FLIGHT MANUAL Section 3 Page 3-2 3.2.4 Engine failure in flight 1. Airspeed - modify to 120 km/h 2. Field selection - according to height available 3. Air start - in accordance with item 3.3 4. In case of an unsuccessful air start, perform emergency landing in accordance with item 3.6.1. 3.2.5 Performance loss and irregular running of the engine during flight This situation may occur with carburettor icing. Apply carburettor pre-heating as required to restore normal power, smooth running. Or it can happen because of empty fuel tank, the indicator is the fuel pressure loss – close the empty tank fuel cock. If everthihg fails perform an emergency landing. 3.3 Air start 1. Airspeed -modify to 120 km/h 2. Altitude flight - check 3. Field selection - select according to height available 4. Main fuel cock - open 5. Choke - if the engine is already in operating temperature, start the engine without choke 6. Throttle lever - at cold engine set to idle position - at warm engine slightly open 7. Ignition - both circuits switched on 8. Starter button - actuate As soon as engine runs, adjust throttle to achieve smooth running at 2500 r.p.m for approximately half a minute before increasing power as required. WARNING The rate of descent approx. 2.3 m/s causes measurable loss of altitude during the air start. If the air start is unsuccessful up to height 150 m above ground level, perform emergency landing according to item 3.6.1. 3.4 Smoke and fire 3.4.1 Engine fire on the ground 1. Fuel cocks - close 2. Throttle lever - full open 3. Ignition - both circuits switched off after consumption of the fuel 4. Crew - leave the cockpit immediately 5. Extinguish fire - with best available means 3.4.2 Engine fire in flight 1. Fuel cocks - close 2. Throttle lever - full open 3. Ignition - both circuits switched off after consumption of the fuel Date: 1.12.2001 Change: 22.09. 2004 „Appr“ DYNAMIC WT 9 FLIGHT MANUAL Section 3 Page 3-3 4. Try to extinguish the fire with side slip 5. Perform emergency landing in accordance with item 3.6.1. CAUTION After extinguishing the fire do not start engine again! 3.4.3 Fire in cockpit 1. Fire source - locate 2. Ignition - both circuits switched off 3. Master switch - off 4. Crew - leave the cockpit on the ground , - perform emergency landing accordance with item 3.6.1. 5. Try to extinguish - with best available means 3.5 Glide Glide path will determine the field selection for emergency landing. The optimum gliding performance is with retracted wing flaps ( retracted undercarriage ) and with stopped propeller. In case of engine failure it is necessary to maintain the following optimum speeds for given configuration. Landing gear position Retracted Extended km/h MPH knots km/h MPH knotsOptimum descent airspeed IAS 120 75 65 120 75 65 Maximum gliding range 14 10 Rate of descent 2,4 m/s 500 ft/min 3,0 m/s 600 ft/min 3.6 Landing emergency 3.6.1 Emergency landing 1. Airspeed - modify to 110 km/h 2. Field selection - select in the direction of the free area without obstacles, if possible into wind 3. Seat belts and harness - fasten 4. Flaps - extend as required 5. Main fuel cock - close 6. Ignition - both circuits switched off 7. Master switch - off CAUTION The loss of height for 360 ° turn is approx.. 120 m. Date: 1.12.2001 Change: 8.12.2003 „Appr“ DYNAMIC WT 9 FLIGHT MANUAL Section 3 Page 3-4 3.6.2. Precautionary landing In the event of the aeroplane failure, disorientation, shortage of fuel, dangerous deterioration of the meteorological conditions (visibility, thunderstorm) and approaching sunset, a precautionary landing should be conducted. 1. Select a suitable landing field, if possible into the wind. 2. Fly over selected field with wing flaps 15° and 110 km/h airspeed at a height 50 m AGL, noting the preferred area for touchdown for the next landing approach to inspect the terrain for obstructions and surface conditions. 3. Make landing circuit at a height 150 m AGL or at a safe altitude in accordance with the ceiling with flaps 15° and 110 km/h airspeed. Extend “down wind” position and make approach with sufficient power. 4. Don’t lose sight of the selected field in low visibility. 5. Landing approach with flaps for landing and sufficient power. 6. Arrange approach so that the desired touch down spot will be immediately after passing the edge of the selected landing field. 7. After touch down apply heavy breaking till stopped. ground loop if necessary. 8. When the aeroplane comes to a stop, shut down the engine, master switch off, Main fuel cocks close, secure the aeroplane and seek assistance. 3.6.3 Landing with a flat tyre 1. Landing approach - with flaps 38 ° and 110 km/h airspeed 2. Touch down - with the bank angle on the unflat tyre at minimum touch down speed, 3. Direction after landing - maintain ground roll direction. 3.7 Recovery from unintentional spin For recovery from an unintentional spin the following procedure should be used: 1. Throttle lever - set to idle position 2. Control stick - set neutral position, without deflection of the ailerons 3. Rudder control - apply full rudder opposite to the direction of rotation 4. Control stick - move forward of neutral in a brisk motion until rotation stops. 5. Rudder control - immediately as rotation stops, neutralize rudder position 6. Control stick - make a smooth recovery from the resulting dive. WARNING Intentional spins are prohibited ! Date: 1.12.2001 „Appr“ DYNAMIC WT 9 FLIGHT MANUAL Section 3 Page 3-5 3.8 Other emergencies 3.8.1 Control failures Aileron control fault - the aeroplane is possible to control laterally by the secondary effect of the rudder. Start and termination of the yawing up to bank angle 15° is possible using the rudder only. Rudder control fault - the yawing and the termination is conducted with help of the lateral control of the ailerons. . 3.8.2 Vibrations The power plant can be the source of the vibrations. 1. Reduce engine speed to minimize the vibrations. 2. Proceed to the nearest airport for landing or select a suitable precautionary landing field in accordance with item 3.6.2. 3.8.3 Emergency extension of the undercarriage An overswitch on the instrument panel labelled “Hydraulic On” is in the up position at normal operation. In case of the electrical driven hydraulic pump malfunction, the overswitch is set in the down position labelled “Emergency extension of L/G”. The emergency extension of the undercarriage is carried out by its own mass with the help of a three-way valve. The drag stay is arrested with the help of the springs. The undercarriage is extended even in an electrical power loss. The emergency extension of the undercarriage is terminated, when three green lights are illuminated on the instrument panel. Fig. 2 Emergency extension of L/G overswitch 3.8.4 * Rescue system 1. Remove the safety pin of rescue system control 2. Pull out the rescue system control * Optional Date: 1.12.2001 „Appr“ Hydraulic ON EMERGENCY EXTENSION OF THE UNDERCARRIAGE DYNAMIC WT 9 FLIGHT MANUAL Section 4 Page 4-1 SEKCTION 4 NORMAL PROCEDURES Page 4.1 Introduction 4-1 4.2 Rigging and derigging 4-1 4.3 Daily inspection 4-4 4.4 Preflight inspection 4-4 4.5 Normal procedures and check list 4-7 4.1 Introduction Section 4 provides checklist and amplified procedures for the conduct of normal operation. Normal procedures associated with optional systems can be found in Section 9. 4.2 Rigging and derigging 4.2.1 Rigging of the wings The aeroplane has the wings disassembled for transportation purposes or to save space in the hangar. There is a description for the rigging procedure of the right wing. The procedure for the left wing is analogous. Thoroughly clean and lubricate all the wing fitings and pins so pins locate easily. Rigging: 1. Fit the spar end of the right wing into the spar end ( fork ) of the wing central section and push the wing along its longitudinal axis so that a connection slot between the wing central section and the wing root is approx. 100 mm ( Fig. 3 ). Connect the hoses from the Pitot-static tube (connect the wiring for position lights, strobe lights, if lights installed ). 2. Fully push the wing into the wing central panel and slide the wing tank fuel houses on theirs sockets together with theirs clamps. Carefully insert the pin of the extended wing flap hinge into the fitting of the wing central panel. Take care of the hoses from the Pitot-static tube, they must not be twisted and for fuel houses. 3. Insert wing pins to connect wing spar end with the wing central panel. The outer pin is inserted through the undercarriage box of the retractable version ( for model SPEED ) or through the access hole on the lower wing surface ( for model CLUB and TOW ). The inner pin is inserted through the hole in the cockpit below pilot seat ( slightly lift and lower the wing tip to ease the pin insertion ). 4. Insert rear spar into the fitting to lecate the rear spar to the centre section. Secure all 6 pins with safety pins ( Fig.4 ). 5. Insert connecting pin of the flap rod. During this procedure the flap control lever in the cockpit shall be set to the rearmost position and the flap shall be deflected to maximum down position. Date: 1.12.2001 „Appr“ DYNAMIC WT9 FLIGHT MANUAL Section 4 Page 4-2 7. Connect the aileron control rod with the rod in the wing centre section and secure the nut ( Fig.4 ) with the safety pin. Than tight the fuel houses clamps. 8. Repeat the procedure with the second wing. After checking the security of the all connection. The connection slot between wing and the wing centre section should be sealed with sticky tape. WARNING After rigging of the wings check for correct operation and security of the aileron control pins and the flap control pins as well as the connection of the hoses from the Pitot-static tube and fuel houses. Fig. 3 Insertion of the wing spar into the wing centre section, position of the wing pins and the support points. Fig. 4. Connecting bolt + safety pin of aileron connection. Date: 1.12.2001 „Appr“ Jacking pionts for lifting the aircraft (below rear spar of wing centre section and below the firewall. Insertion of the wing spar Flap Safety pin ( No.3 at the rear spar with the security ) Attachment bolt of the aileron rod DYNAMIC WT 9 FLIGHT MANUAL Section 4 Page 4-3 4.2.2 Derigging of the wings Use the opposite sequence for derigging: 1. Drain all fuel tanks – for 126 liters tank only. 2. Disconnect aileron rod from the rod in the wing centre section. 3. Remove the sticky tapes from the connection slot between wing and the wing centre section. Unlock the joints of the fla shaft. 4. Pull out all wing pins. (Pull out the fixation pins for connection of the wing spar end with the wing central panel and the auxiliary rear pin.) 5. Pull out the wing along its longitudinal axis so that there is a distance between the wing and the wing root of approx. 100 mm ( Fig. 3 ). Disconnect the hoses from the Pitot-static tube (disconnect the position lights wires etc, if lights installed ). 6. Carefully pull the wing away from the wing centre section and put on soft mats. Fig. 5 Connecting position for the flap and the aileron. Date: 1.12.2001 „Appr“ Aileron rod connection Flapshaft DYNAMIC WT 9 FLIGHT MANUAL Section 4 Page 4-4 4.3 Daily inspection The daily inspection must be performed every day before flight of the ultralight aeroplane. The scope of this inspection is to check the following: 1. Aeroplane log-book and airworthiness certificate 2. Aeroplane technical log-book 3. Cockpit 4. Landing gear 5. All control surfaces for full and free movement 6. All surfaces of the ultralight aeroplane for cracks, nicks or any visible damage. 7. Power plant and propeller 8. Check fuel, oil, coolant liquid. WARNING If any problems are found they must be corrected before flying. 4.4 Preflight inspection It is most important to perform a preflight inspection carefully to prevent possible trouble. The preflight inspection is essential for flight safety. CAUTION Special attention must be devoted to the parts, which are affected by high vibrations and high temperatures. Preflight inspection procedure: Fig. 6 Walkaround inspection Date: 1.12.2001 „Appr“ DYNAMIC WT 9 FLIGHT MANUAL Section 4 Page 4-5 1. Cockpit: Flight controls - check for freedom of movement Master switch - switched off Ignition switch - both circuits switched off Loose items - secure or remove Check instruments - set “O” Cockpit canopy glass - clean, check cockpit canopy lock Safety harness - inspect Fuel - check fuel quantity, check fuel cock Propeller - main stop system check. With the engine not running, adjust the propeller pitch from one end position to the other. If the system is functioning normally, the propeller reaches its end pitch position and the appropriate lamp (green or red) shines continuously, the servomotor stops. If the main stop system is faulty the servomotor continues to operate after it has reached its final normal position and there is also a specific clicking noise produced by the clutch slipping. If this occurs the propeller should not be used until repaired by the producer or service center. Do not fly. 2. Wing Surface - state of wing surface Connection - wing pins fully inserted and secured Pitot static head - pitot tube cover removed, check opening for blockage. Leading edges - without damage, clean Ailerons - check for freedom of movement and security Flaps - without play, check hinges for security 3. Fuselage Surface - without damage Static pressure receivers - check opening for blockage Antennas - fixed, without damage Cockpit wing walks - without damage 4. Tail units Surface - without damage Control surfaces - check for freedom of movement , without excess play Auxiliary tail skid - check for secure attachment 5. Landing gear Fixed undercarriage: Main wheel tyres - state, inflation ( 250 kPa ) Brakes - visually check condition of pads, brake system for leaks Laminated legs - state without damage, attachment Spats - attachment, state without damage, Nose wheel leg - nose wheel tyre state, inflation ( 200 kPa ) attachment, springed rubber components state spat attachment, wheel free rotation Date: 1.12.2001 „Appr“ 6. Powerplant Propeller - attachment, leading edge blade state, check for nicks and security, check spinner for cracks and attachment. Engine - check for any operating fluids leaks below engine cowlings - state of the cowlings - state of the exhaust system attachment - state of the engine attachment into the rubber engine mants. - check coolant level and oil level - check attachment of carburettors - check electric system state - state of the holder hoses - check condition and integrity of wires, plug - check fuel filter - turn the propeller by hand several times for odd noises or excessive resistance and normal compression. WARNING Before cranking the propeller switch off both ignition circuits. The propeller must be caught at the blade surface every time. Do not catch at the edge. Date: 1.12.2001 „Appr“ DYNAMIC WT 9 FLIGHT MANUAL Section 4 Page 4-6 DYNAMIC WT 9 FLIGHT MANUAL Section 4 Page 4-7 4.5 Normal procedures and check list The standard cockpit control arrangement is shown in fig.7 and the instrument panel is shown in fig.9. Fig. 7. The cockpit controls, see also fig.9 on page 7 – 3 1. Control stick/ propeller control 9. Instrument panel 2. Rudder pedals 10. Ventilation sliding window 3. Elevator trim control lever 11. Ventilation 4. Brake control lever 12. Fuel cock 5. Wing flaps control lever 13. Chock 6. Pocket *14. Tow cable release 7. Headset socket / jack 15. Ventilation flow baffle 8. Seat and safety harness 16. Canopy ventilation * Optional Date: 1.12.2001 „Appr“ 14 15 15 16 13 DYNAMIC WT 9 FLIGHT MANUAL Section 4 Page 4-8 4.5.1 Before starting engine 1. Ignition - both circuits switched off 2. Rudder pedals - freedom of movement 3. Control stick - freedom of movement 4. Throttle lever - freedom of movement, set to idle position 5. Elevator trim control - set neutral position 6. Fuel quantity - check 7. Instruments - setting and check up of the value 8. Radio - function check 9. Seat and safety harness - adjust and lock 10.Break - function check 11.Canopy of cockpit - shut and latched 4.5.2 Engine starting Cold engine: WARNING Before starting engine check position of the landing gear overswitch . Overswitch position – EXTENSION ( L/G extended ). 1. Fuel cock - left tank 2. Fuel pump - switch on and check the fuel pressure then switch off 3. Choke - open 4. Throttle lever - set to idle position 5. Brakes - set on parking position, control lever secured 6. Master switch - switched on 7. Ignition - both circuits switched on 8. Starter button - actuate, activate starter for max. 10 sec only without interruption 9. As soon as engine runs - adjust throttle lever to achieve smooth running at approximately 2000 r.p.m, check if oil pressure has risen within 10 sec to 2 bar and monitor oil pressure, choke off 10. Warming up - start warming up period at 2000 r.p.m for approx. 2 minutes, continue at 2500 r.p.m, duration depending on ambient temperature, until oil temperature reaches 50 oC Warm engine: if the engine is already at operating temperature WARNING Before starting engine check position of landing gear overswitch. Overswitch position – EXTENSION ( L/G extended ). 1. Fuel cock - left tank 2. Throttle lever - set to slight open position 3. Brakes - set on parking position, control lever secured Date: 1.12.2001 „Appr“ DYNAMIC WT 9 FLIGHT MANUAL Section 4 Page 4-9 4. Master switch - switched on 5. Ignition - both circuits switched on 6. Starter button - actuate, activate starter for max. 10 sec only without interruption 7. As soon as engine runs - adjust throttle lever to achieve smooth running at approximately 2000 r.p.m, check if oil pressure has risen within 10 sec to 2 bar and monitor oil pressure, 4.5.3 Engine warming up In accordance with the Operator’s Manual for all versions of ROTAX 912 as follow: Start warming up period at 2000 r.p.m for approx. 2 minutes, continue at 2500 r.p.m, duration depending on ambient temperature, until oil temperature reaches 50 oC. Engine ground test: 1. Ignition check – check the two ignition circuits at 4000 r.p.m ( approx. 1650 r.p.m propeller ). Speed drop with only one ignition circuit must not exceed 300 r.p.m ( approx. 125 r.p.m propeller ). 120 r.p.m ( approx. 50 r.p.m propeller ) max. difference of speed by use of either circuit A or B. ( Note: the propeller speed depends on the actual reduction ratio ). 2. Throttle response – short full throttle ground test, speed must not exceed 5800 r.p.m. 3. The minimum speed on the ground must be 5000 r.p.m depending on ambient temperature and pressure. ( approx. 2060 r.p.m propeller ) 4. Check idle speed 2000 r.p.m ( approx. 820 r.p.m propeller ) 4.5.4 Taxying Use of the Vernier throttle (screw in, screw out) will help with smooth adjustments of power during taxying. Taxying of the aeroplane is controled by he rudder pedals which are connected to the nose wheel steering. The wheel brakes are actuated by sliding the brake lever rearwards in the centre console. 4.5.5. Before take-off 1. Rudder pedals - freedom of movement 2. Control stick - freedom of movement 3. Elevator trim control - set neutral position 4. Wing flaps - set take off position 5. Fuel cock - left tank, check fuel quantity 6. Fuel pump - switched on 7. Power plant instrument - check for correct readings 8. Flight instrument - check altimeter setting 9. Propeller - set minimum fine angle ( take off position ) 10. Seat and safety harness - adjust and lock 11. Canopy of cockpit - latched Date: 1.12.2001 „Appr“ DYNAMIC WT 9 FLIGHT MANUAL Section 4 Page 4-10 4.5.6. Normal Take-off Throttle lever – full open, - control stick set into neutral position - direction on the ground run controled by rudder pedals - unstick at speed at 80-85 km/h ( according to take off weight ) - accelerating at speed 110-120 km/h ( acceleration after unstick ) - reduce engine rpm to 5500 – 5700 by using the electonic propeller control (this increases the angle of blades ) - at height 50m AGL wing flaps up - adjust cruising power ( engine speed 5500 r.p.m ) 4.5.7. Climbing Normal climbs are conducted at climb speeds 110 - 120 km/h in accordance with the take off weight of the aeroplane. Monitor cylinder head temperature and oil pressure during climb. Oil temperature limits must not be exceeded. In case of high readings, increase airspeed and reduce engine power setting. 4.5.8. Cruise The range of cruising speeds is from 140 to 250 km/h in accordance with the engine speed setting from 4000 to 5200 r.p.m. The economy airspeed for best fuel economy is at 140 km/h, the optimum operation is between 180 km/h to 200 km/h. In case of turbulence reduce cruising speed below 160 km/h. Under certain conditions the aeroplane may be overstressed. The aeroplane is able to be trimmed through the range of the cruising speeds. Due to economy reasons is recommended to maintain the following data: Engine ROTAX 912 UL Engine power setting Engine Speed ( r.p.m ) Performance ( kW ) Torque ( Nm ) Manifold pressure ( in Hg ) Take-off performance 5 800 59,6 98,1 Full throttle Cruising power 5 500 58 100,7 Full throttle 75 % 5 000 43,5 83 27,2 65 % 4 800 37,7 75 26,5 55 % 4 300 31,9 70,8 26,3 EngineROTAX 912 ULS Engine power setting Engine Speed ( r.p.m ) Performance ( kW ) Torque ( Nm ) Manifold pressure ( in Hg ) Take-off performance 5 800 73,5 119,0 27,5 Cruising power 5 500 69,0 121,8 27 75 % 5 000 51,0 97,4 26 65 % 4 800 44,6 88,7 26 55 % 4 300 38,0 84,3 24 Date: 1.12.2001 „Appr“ DYNAMIC WT 9 FLIGHT MANUAL Section 4 Page 4-11 4.5.9. Descending Descending is conducted at airspeeds 110 – 120 km/h with the throttle lever set to idle position. For increasing the rate of descent it is recommended wing flaps set to landing position ( 38° flaps deflection ) and proceed at airspeed 120 km/h. In this configuration the gliding range is 1:8. Side slipping is conducted with airspeed 120 km/h, and bank angle 30° with help of the full rudder deflection. The side slip direction is controlled by the bank. 4.5.10 Landing Check systems ( fuel ) before approach for landing. Landing approach conduct at small glide slope angle due to long distance of the float before aeroplane touch-down 1. Propeller - set minimum fine angle ( take off position ) 2. Fuel pump - switched on 3. Approach speed 110-120 km/h according to the weight. 4. Wing flaps - as required flaps down at speed below 135 km/h 5. Elevator trim – adjust as required 6. Begin levelling out at height circa 2-3 m. 7. Actual touchdown should be made with power-off and on the main wheelsfirst. The nose wheel should be lowered smoothly to the runway as speed is diminished. 8. During landing run control the aeroplane with help of the rudder pedals. 9. Apply braking as required. The main wheel brakes are actuated via the handle on the pedestal between the pilot seats. WARNING The light and audible warning signal for retracted landing gear will not operate, if the landing is made without the wing flaps set down in landing position. 4.5.11 Balked landing 1. Smoothly adjust the throttle lever – full open ( a thrust yawing moment is manifested in case of the steep setting of the throttle lever ) 2. Airspeed modify to 120 km/h 3. The wing flaps setting reduced to take-off position 4. Elevator trim – adjust as required and proceed in the climb out 4.5.12 After landing 1. Engine speed - adjust for taxying Date: 1.12.2001 „Appr“ DYNAMIC WT 9 FLIGHT MANUAL Section 4 Page 4-12 2. Wing flaps - retract 3. Elevator trim - set to rearmost position of neutral 4. Fuel pump - switched off 5. Taxying - into the parking position 4.5.13. Securing aeroplane 1. All electronic instruments ( avionics ) - switched off 2. Ignition - switched off 3. Master switch - switched off 4. Fuel cock - closed in case of lengthy duration on the ground 5. Brakes - set on parking position, control lever secured 6. After leaving the cockpit, the canopy should be covered with the cloth dust- cover, to avoid the effects of the sun. 4.5.14 Aerotowing Aircraft WT 9 DYNAMIC is approved for aerotowing of sailplanes in MTOM 525 kg. (see 2.15 “Other limitations”) Take off and climbing do with wing flaps position 15° (max. TOW of towed sailplane up to 410 kg) at safe height (min 50 m) wing flaps up Take off and climbing do with wing flaps position 0° ( towed sailplane with water ballast or TOW more than 410 kg to 525 kg ) Note: Take care for max. towing speed of towed sailplane. Date: 1.12.2001 „Appr“ DYNAMIC WT 9 FLIGHT MANUAL Section 5 Page 5-1 SECTION 5 PERFORMANCE Page 5.1 Introduction 5-1 5.2 Approved data 5-1 5.2.1 Airspeed indicator system calibration 5-1 5.2.2 Stall speed 5-2 5.2.3 Take-off performance 5-2 5.2.4 Landing distance 5-2 5.2.5 Climb performance 5-2 5.3 Additional information 5-3 5.3.1 Cruise 5-3 5.3.2 Endurance 5-3 5.3.3 Balked landing climb 5-4 5.3.4 Take-off measurements 5-4 5.3.5 Effect on flight performance and characteristics 5-4 5.3.6 Demonstrated crosswind performance 5-5 5.3.7 Noise data 5-5 5.3.8 Towing flights 5-5 5.1 Introduction Section 5 provides approved data for airspeed calibration, stall speed and take-off performance and non-approved additional information. The data in the charts has been computed for condition of the standard atmosphere from actual flight tests with the aeroplane at maximum take-off weight and engine in good condition and using average piloting techniques. 5.2 Approved data 5.2.1 Airspeed indicator system calibration IAS ( km/h ) 50 65 70 80 90 100 110 120 130 140 160 CAS ( km/h ) 65 76 80 87 92 100 110 118 127 136 156 IAS ( km/h ) 180 200 220 240 260 280 CAS ( km/h ) 175 195 215 233 252 272 IAS = indicated airspeed CAS = calibrated airspeed Date: 1.12.2001 „Appr“ DYNAMIC WT 9 FLIGHT MANUAL Section 5 Page 5-2 5.2.2 Stall speed Maximum weight 450 kg, C.G. in 25% MAC, idle engine speed Position wing flaps 0° 15° 38° Stall speed IAS in km/h 60 55 50 Stall speed CAS in km/h 72 70 65 5.2.3 Take-off performance The data is valid for following conditions: H = 0 m MSL, Temperature t = 15 ° C Wing flaps position 15° and engine ROTAX 912 ULS Surface of the runway Take-off run distance ( m ) Take-off distance up to 15m ( m ) Paved runway 75 252 Non paved – grass 86 264 5.2.4 Landing distance The data is valid for following conditions: H = 0 m MSL, Temperature t = 15 ° C Wing flaps position 38° , landing run is braked. Surface of the runway Landing distance (m) from height 15 m Landing run distance ( m ) Paved runway 267 152 Non paved - grass 258 144 5.2.5 Climb performance The data is valid for max.weight 450 kg , without flaps. Engine ROTAX 912 ULS, speed 5500 r.p.m Propeller SR 2000 Altitude (m) Speed IAS km/h Rate of climb m/s 0 120 6,2 1000 120 5,9 2000 120 5,2 The service ceiling is 5000 m for models equipped by engine ROTAX 912 UL. The service ceiling is 5500 m for models equipped by engine ROTAX 912 ULS at the cruising power. Date: 1.12.2001 „Appr“ DYNMIC WT 9 FLIGHT MANUAL Section 5 Page 5-3 5.3 Additional information 5.3.1 Cruise The following graph shows the reached speeds depending on the engine speed and the fuel consumption. Fuel consumption of the aeroplane DYNAMIC with engine ROTAX 912 ULS, propeller SR 2000 Fuel consumption ( L/h ) IAS (km/h) Engine speed (1/min / r.p.m) Fig. 8 Fuel consumption graph 5.3.2 Endurance The power requirement of propeller in the dependence of the airspeed has the quadrate running. The power consumption and also the fuel consumption increases with square of the airspeed. The flight altitude is another factor, which effects the fuel consumption, because the performance drop with increasing flight altitude. The minimum fuel consumption is at lift-over-drag maximum speed, which is 115 km/h. The minimum fuel consumption is at lift-over-drag maximum speed, which is 115 km/h. The good compromise for effective cruising performance is the airspeed range from 180 to 220 km/h. Date: 1.12.2001 „Appr“ DYNAMC WT 9 FLIGHT MANUAL Section 5 Page 5-4 The following table shows the fuel consumption for engine ROTAX 912 ULS with take-off performance 73,5 kW at different engine speeds. The fuel consumption for engine ROTAX 912 UL with take-off performance 59,6 kW is about 10 % less. The propeller setting is not determined, due to flat running of the propeller curve optimum. The engine speed has greater effect in its upper section. Engine speed 1/min 4900 4800 4700 4600 4500 4500 4500 4500 4500 4500 4500 Propeller blade angle o 25o 24o 23o 22,5o 21,9o 21,5o 21o 20,5o 20o 19,5o 19o Fuel consumption l/h 18 17 16 15 13,5 12,5 11,2 10,7 9,9 9,5 8,6 Airspeed IAS km/h 250 240 230 220 210 200 190 180 170 160 150 Endurance h:min 3:50 4:04 4:19 4:36 5:07 5:31 6:16 6:27 6:58 7:16 8:00 Max. range km 958 975 990 1010 1070 1100 1170 1160 1185 1160 1200 The table is valid for: Flight altitude1000 m MSA , take-off performance 73,5 kW, the total usable quantity of fuel in the tanks is 69 litres. With 126 liters fuel tanks is the renge extended for cca. 550 km, depending on the engine setting. 5.3.3 Balked landing climb The data is valid for maximum landing weight 450 kg , wing flaps position 38o. Engine ROTAX 912 ULS, engine speed 5500 r.p.m, Propeller SR 2000 Flight altitude (m) Airspeed IAS km/h Rate of climb m/s 0 115 4,7 1000 115 4,2 2000 115 3,6 5.3.4 Take-off measurements The data is valid for following conditions: H = 0 m MSL, Temperature t = 15 ° C Wing flaps position 15° and engine ROTAX 912 ULS Surface of the runway Take-off run distance ( m ) Take-off distance up to 15m ( m ) Non paved - grass 86 264 5.3.5 Effect on flight performance and characteristics No disturbing effects on flight performance and characteristic of the ultralight aeroplane DYNAMIC WT9 were recorded during the flight tests. Date: 1.12.2001 „Appr“ DYNAMIC WT 9 FLIGHT MANUAL Section 5 Page 5-5 5.3.6 Demonstrated crosswind performance The maximum demonstrated crosswind speed for take-off and landing is 6 m/s according to the airworthiness requirements. 5.3.7 Noise data The maximum noise data 56,7 dB (A) was measured during the flight tests according to the German noise requirement LS – UL 96. 5.3.8 Aerotowing performance 5.3.8.1 Take off and climbing The following table shows the take-off and climbing performance Distance ( m ) Time of climb up to Glider Type MTOM ( kg ) take off run take of up to 15m 400 m 600 m Airspeed IAS ( km/h ) Rate of climb (m/s) Luňák LF107 315 140 449,26 2:38,1 3:54,6 110 2,65 Blaník L13 501 201 523,5 3:03,5 5:09,2 110 2,0 VTC CIRUS 405 170 533,8 2:45,1 4:10,6 120 2,46 VTC CIRUS 405 170 521,7 2:43,3 4:13,0 110 2,55 LS 8b 525,7 240 597,8 3:07,1 4:47,9 130 2,11 LS 8b 525,7 240 563,9 2:53,7 4:08,9 120 2,45 VENTUS C 525 205 526,3 2:56,2 4:08,0 130 2,45 Date: 1.12.2001 „Appr“