WT9 Dynamic LSA Speed S Flight Manual

Main wheel diameter……………................…....... 0,35 m Nose wheel diameter…………………………....... 0,32 m Weights Empty weight ……………………………….….... 356,2 kg Maximum take-off weight…….....................……. 600,0 kg Useful load……….....................................……..... 243,8 kg Fuel tanks capacity………….................................. 126,0 litres The ROTAX 912 ULS (73 kW- 100HP) with a maximum rpm limitation on take off of 5800 1/min. airplane is fitted with 3 blades adjustable propeller SR 2000 D. Date: 28.10.2010, Rev.: 1 WT9 Dynamic LSA Speed S FLIGHT MANUAL Section 1 Page 1-3 1.5. Airplane views Date: 14.06.2011, Rev.: 2 WT9 Dynamic LSA Speed S FLIGHT MANUAL Section 1 Page 1-4 1.5.1 Three – view drawing Date: 28.10.2010, Rev.: 1 WT9 Dynamic LSA Speed S 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 2-4 2.7 Weight 2-5 2.8 Centre of gravity 2-5 2.9 Approved manoeuvres 2-5 2.10 Manoeuvring load factors 2-6 2.11 Flight crew 2-6 2.12 Kinds of operation 2-6 2.13 Fuel, oil 2-6 2.14 Maximum passenger seating 2-7 2.15 Other limitations 2-7 2.16 Limitations placards 2-7 2.1 Introduction Section 2 includes operating limitations, instrument markings, and basic placards necessary for safe operation of the airplane, its engine, standard systems and standard equipment. The limitations included in this section and in Section 9 have been approved by the aviation authority. 2.2 Airspeed Airspeed limitations and their operational significance are shown below: Speed IAS+ Remarks km/h MPH knots 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 225 140 122 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: 28.10.2010, Rev.: 1 WT9 Dynamic LSA Speed S FLIGHT MANUAL Section 2 Page 2-2 Speed IAS Remarks km/h MPH knots VA Manoeuvring speed 180 112 97 Do not make full or abrupt control movement above this speed, because under certain conditions the airplane 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: Marking IAS value or range Significance km/h MPH knots White arc 82 – 140 44 – 88 51 - 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 91 – 225 57 - 140 49 – 122 Normal Operating Range. ( Lower limit is maximum weight 1.1 VS1 at most forward c.g. with flaps . Upper limit is VRA . Yellow arc 225 – 280 140 - 174 122 - 150 Manoeuvres must be conducted with caution and only in smooth air. Yellow triangle 110 68 59 Minimum Approach speed Yellow line 180 112 97 VA Manoevring speed Red line 280 174 150 Maximum speed for all operations. 2.4 Powerplant Engine Manufacturer: ROTAX-Bombardier, Gunskirchen, Austria Engine Models: ROTAX 912 ULS Maximum Power - Take-off: 73,5 kW / 100 HP Continuous: 69 kW / 93,8 HP Maximum Engine Speed – Take-off: 5800 1/min ( 5 min ) Continuous: 5500 1/min Maximum Cylinder Head Temperature: 135 ° C Maximum Oil Temperature: 130 ° C 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: 28.10.2010, Rev.: 1 WT9 Dynamic LSA Speed S FLIGHT MANUAL Section 2 Page 2-3 - EN 228 Super (Unleaded Automotive Gasoline RON 95) - EN 228 Super plus (Unleaded Automotive Gasoline RON 98) - 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) - Fuel E10 (unleaded gasoline blended with 10% ethanol Oil Grade: - engine oil of a registered brand with gear additives. Use only oil with API classification “SG” or higher. - high performance 4-stroke motor cycle oils are recommended - If using airplane engine oil, then only blended one. Oil capacity: 3,0 litre Minimum: 2,0 litre Oil consumption: max. 0,06 l/h WARNING Never use AVGAS, LB 95 with fully synthetic engine oils. Propeller Manufacturer: WOODCOMP, Czech Propeller Model: SR 2000 D, 3 blade electricaly adjustable propeller Propeller Diameter: 1,7 m Propeller Blade Angle 24° Additional data can be found in Section 7, Subpart 7.9, in the Operator Manual for engine ROTAX 912 ULS and in the User Guide for propeller SR 2000 D. 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 round one–purpose needle instruments could be fitted in the instrument panel. Date: 28.10.2010, Rev.: 1 WT9 Dynamic LSA Speed S FLIGHT MANUAL Section 2 Page 2-4 Powerplant instrument markings and their colour code significance are shown below: Instrument (indication within SkyView system) 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 – 130 130 Cylinder-head temperature indicator oC 50 90 – 110 50 – 90 110 – 135 135 Fuel-pressure indicator bar 0,15 0,4 Oil-pressure indicator bar 0,8 2– 5 0,8 - 2 5 – 7 7 Fuel indicator litre 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 in Hg 11,8 11,8-28 28-29,5 29,5 Exhaust gas temperature oC 250 300-800 250-300 800-880 880 Fuel flow meter LPH up to 25 25 Fuel reserve indicator litre Red light annunciator will be illuminated with the remaining fuel of 7 litre in each fuel tank. Date: 28.10.2010, Rev.: 1 WT9 Dynamic LSA Speed S FLIGHT MANUAL Section 2 Page 2-5 2.7 Weight Empty weight …..……........................................ 356,2 kg Maximum take-off weight....……...............……. 600 kg Maximum landing weight ……................……… 600 kg Useful load ………........................................…… 243,8 kg Maximum fuel weight ……............................……. 89,3 kg Maximum occupant weight per seat……......……. 115,0 kg Minimum weight solo pilot (no baggage, full tanks)..92,9 kg Maximum weight in Baggage Compartment…...... 40 kg WARNING Maximum take off weight 600 kg 2.8 Centre of gravity Position of C.G.: Empty airplane.....................................12 ± 2% MAC Position of C.G. in flight…..................20 ÷ 30% MAC Rear 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 and maximum capacity of the fuel tanks. Example to check the centre of gravity position is in Sect. 6. 2.9 Approved manoeuvres − Steep turns with the angle of bank up to 60°°°° - appropriate entry speed is 145 km/h. − Lazy eighths - appropriate entry speed is 145 km/h. − Combat turns - appropriate entry speed is 200 km/h. WARNING Aerobatic manoeuvres and intentional spins are prohibited! Date: 28.10.2010, Rev.: 1 WARNING A flight shall not be commenced until the pilot-in-command is satisfied that the mass of the airplane and centre of gravity location are such that the flight can be conducted safely! WT9 Dynamic LSA Speed S FLIGHT MANUAL Section 2 Page 2-6 2.10 Manoeuvring load factors Manoeuvre speed Speed Load factors km/h MPH knots VA- Manoeuvring speed 180 112 97 + 4 VNE – Never exceed speed 280 174 150 + 4 VA – Manoeuvring speed 180 112 97 - 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 airplane WT9 Dynamic LSA Speed S is approved to perform flights in accordance with VFR day 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 and oils can be used for the airplane WT9 Dynamic LSA Speed S : see chapter 2.4 Powerplant and the Operator’s Manual for engine ROTAX 912 ULS. Date: 28.10.2010, Rev.: 1 WT9 Dynamic LSA Speed S FLIGHT MANUAL Section 2 Page 2-7 Left tank ( l ) Right tank ( l ) The total quantity of fuel in the tank 63 63 Unusable fuel in the tank 2,9 2,9 The total usable quantity of fuel in the tank 60,1 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 a) Wind speed The maximum crosswind component limit according to the airworthiness requirements for take off and landing is 6 m/s, 12 knots. b) Smoking NO SMOKING on board the airplane. 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 225 140 122 Manoeuvring speed VA 180 112 97 Maximum Flap Extended speed VFE 140 88 75 Maximum Landing Gear VLO 140 88 75 Operating Speed Maximum Landing Gear VLE 250 156 135 Exceed Speed Date: 28.10.2010, Rev.: 1 Aerobatics, itentional spins and stalls are prohibited! IFR flights and flights in icing conditions are prohibited! WT9 Dynamic LSA Speed S FLIGHT MANUAL Section 2 Page 2- 8 Maximum allowed filling of the fuel tanks in litres Baggage weight (kg) Crew weight (kg) 140 160 170 180 190 200 210 220 230 0 full 116 103 89 75 61 47 33 19 20 116 89 75 61 47 33 19 5 0 40 89 61 47 33 19 5 0 0 0 Maximum Baggage weight 40 kg Date: 14.06.2011, Rev.: 2 WT9 Dynamic LSA Speed S 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 airplane 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 roll 1. Throttle lever - set to idle position 2. Ignition/ Starter switch - switch 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.. 3. Ignition/ Starter switch - switch off 4. Fuel selector valve - 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/ Starter switch - switch off 4. Fuel selector valve - close 5. Flaps - extend as required Date: 28.10.2010, Rev.: 1 WT9 Dynamic LSA Speed S 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 – select the non empty fuel tank. If everything 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. Fuel selector valve - 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/ Starter switch - position “both” starting for max. 10 sec. only without interruption 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. 2.5 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 selector valve - close 2. Throttle lever - full open 3. Ignition/ Starter switch - switch 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 selector valve - close 2. Throttle lever - full open 3. Ignition/ Starter switch - switch off after consumption of the fuel Date: 28.10.2010, Rev.: 1 WT9 Dynamic LSA Speed S 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/ Starter switch - switch off 3. Bat1, Bat2 - 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 and with stopped propeller. In case of engine failure it is necessary to maintain the following optimum speeds for given configuration. Optimum descent airspeed IAS km/h MPH knots 120 75 65 Maximum gliding range 11 Rate of descent 3,1 m/s 620 ft/min 3.6 Landing emergency 3.6.1 Emergency landing 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. Seat belts and harness - fasten 4. Extend landing gear - during landing on airfield or similar surface 5. Flaps - extend as required 6. Fuel selector valve - close 7. Ignition/ Starter switch - switch off 8. Bat1, Bat2 - switch off CAUTION The loss of height for 360 ° turn is approx.. 200 m. Date: 28.10.2010, Rev.: 1 WT9 Dynamic LSA Speed S FLIGHT MANUAL Section 3 Page 3-4 3.6.2. Precautionary landing In the event of the airplane 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 120 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 120 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 airplane comes to a stop, shut down the engine, master switch off, Main fuel selector close, secure the airplane 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: 28.10.2010, Rev.: 1 WT9 Dynamic LSA Speed S FLIGHT MANUAL Section 3 Page 3-5 3.8 Other emergencies 3.8.1 Control failures Aileron control fault - the airplane 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 “HYDRLCS” is in the up position at normal operation. In case of the electrical driven hydraulic pump malfunction or the overswitch is set in the down position, the emergency extension of the undercarriage is carried out by its own mass with the help of a three-way valve. “HYDRLCS OFF/INOP” light on announciator panel gets illuminated. 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 gear announciator panel. Fig. 2 Emergency extension of L/G overswitch 3.8.4 Rescue system For operation and handling with rescue system to see Operation manual delivered by producer of equipment. See Section 9 “Supplement” Date: 14.06.2011, Rev.: 2 WT9 Dynamic LSA Speed S FLIGHT MANUAL Section 3 Page 3-6 3.8.5 Unsecured cockpit canopy If the „Before Take-off“ Checklist is performed insufficiently (page 4-9, paragraph 4.5.5. , point 14 canopy of cockpit – latched, locked), there is a danger of partial cockpit canopy latching or non locking. The canopy is equipped with a lock on the upper rear section of the frame and it is secured by the lock lever shot backwards. The lock pin is projected as latch with compression spring. The gap cca. 8-12 mm will be rise between fuselage and cockpit canopy, which is constant during straight line flight without side-slipping due to the air flow and the function of the gas struts. Partial cockpit canopy latching or non locking will stack up by the noise increase due to the agitated air through the gap between fuselage and cockpit canopy. Partial cockpit canopy latching is possible to close safely during straight line flight without side- slipping by the following way according to appropriate stage of flight: 3.8.5.1 During take-off roll 1. Abort the take-off, if the cockpit canopy unlatching, unlocking is detected during take-off roll. 2. Latch and lock the cockpit canopy by normal procedure after stopping. (the cockpit canopy handle pull down and check the cockpit canopy latching and locking by canopy frame and the red ring position ) (see page 7-6, paragraph 7.8) 3.8.5.2 After unstick or during climbing 1. Safely terminate take-off 2. Climb to safety altitude 3. Fly straight line flight without side-slipping and carry out procedure for level flight. 3.8.5.3 Level flight 1. Open the left ventilation sliding window on cockpit canopy 2. Reduce speed to 120 km/h 3. Hold control stick by one hand 4. The cockpit canopy handle pull down for cockpit canopy latching and locking 5. Check the cockpit canopy latching and locking by canopy frame and red ring position 6. Close the left ventilation sliding window on cockpit canopy 7. Adjust flight airspeed to cruising speed Date: 14.06.2011, Rev.: 2 WARNING During side-slipping flights ( incorrect turn –slipping turn, skidding turn, and side slipping for landing ) with partial cockpit canopy latching or non locking due to asymmetrical flow over fuselage by the air flow, the cockpit canopy will be carved through the gap and subsequently will be full open by help of the gas struts. The cockpit canopy will become the braking shield, what will cause abnormal airplane descent due to increased total drag. WT9 Dynamic LSA Speed S FLIGHT MANUAL Section 4 Page 4-1 SECTION 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 airplane 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 fittings 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 and prepare and adjust the wing fuel tank hoses, connect the wiring for fuel tank conductive connection ans position lights 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 and for fuel houses they must not be twisted. 3. Insert wing pins to connect wing spar end with the wing central panel. The outer pin is inserted through the access hole on the lower wing surface . 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: 28.10.2010, Rev.: 1 WT9 Dynamic LSA Speed S 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: 28.10.2010, Rev.: 1 Jacking pionts for lifting the airplane (below rear spar of wing centre section and below the firewall. Insertion of the wing spar Safety pin ( No.3 at the rear spar with the security ) Attachment bolt of the aileron rod WT9 Dynamic LSA Speed S FLIGHT MANUAL Section 4 Page 4-3 4.2.2 Derigging of the wings Use the opposite sequence for derigging: 1. Drain central section fuel tanks and wing tanks 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 flap 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, the wing fuel tank hoses, disconnect the wiring for fuel tank conductive connection and position lights. 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: 28.10.2010, Rev.: 1 Flapshaft Aileron rod connection WT9 Dynamic LSA Speed S 4.3 Daily inspection The daily inspection must be performed every day before flight of the airplane. The scope of this inspection is to check the following: 1. Airplane log-book and airworthiness certificate 2. Airplane technical log 3. Cockpit 4. Landing gear 5. All control surfaces for full and free movement 6. All surfaces of the airplane for cracks, nicks or any visible damage. 7. Power plant and propeller 8. Check fuel, oil, coolant liquid. 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. Special attention must be devoted to the parts, which are affected by high vibrations and high temperatures. Preflight inspection procedure: Date: 28.10.2010, Rev.: 1 WT9 Dynamic LSA Speed S FLIGHT MANUAL Section 4 Page 4 The daily inspection must be performed every day before flight of the airplane. The scope of this inspection is to check the following: book and airworthiness certificate Airplane technical log-book All control surfaces for full and free movement All surfaces of the airplane for cracks, nicks or any visible damage. Power plant and propeller oil, coolant liquid. WARNING If any problems are found they must be corrected before flying. It is most important to perform a preflight inspection carefully to prevent possible 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 Walk-around inspection Section 4 Page 4-4 The daily inspection must be performed every day before flight of the airplane. All surfaces of the airplane for cracks, nicks or any visible damage. If any problems are found they must be corrected before flying. It is most important to perform a preflight inspection carefully to prevent possible Special attention must be devoted to the parts, which are WT9 Dynamic LSA Speed S FLIGHT MANUAL Section 4 Page 4-5 1. Cockpit: Flight controls - check for freedom of movement BAT 1 - switched off BAT 2 - switched off Ignition/ Starter switch - position off Electrical control switches - all off Circuit brakers - all in Gear operating switch - down Loose items - secure or remove Cockpit canopy glass - clean, check cockpit canopy lock Safety harness - inspect 2. Wing Surface - state of wing surface Connection - wing pins fully inserted and secured Pitot static tube - 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 Main wheel tyres - state, inflation ( 250 kPa ) Brakes - visually check condition of pads, brake system for leaks Legs - state without damage, attachment Nose wheel leg - nose wheel tyre state, inflation ( 200 kPa ) attachment, suspension check, wheel free rotation Date: 14.06.2011, Rev.: 2 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 - check coolant level and oil level - 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. WT9 Dynamic LSA Speed S FLIGHT MANUAL Section 4 Page 4-6 Date: 28.10.2010, Rev.: 1 WT9 Dynamic LSA Speed S 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 actual instrument panel is shown in fig.9. Fig. 7. The standard cockpit controls (see also fig.9 on page 7 – 3) 1. Control stick 9. Instrument panel 2. Rudder pedals 10. Ventilation sliding window 3. Trim lever 11. Ventilation flow baffle 4. Brake control lever 12. Choke 5. Flaps lever 13. Ignition, Starter key, Master 6. Pocket switch 7. Headset socket / jack 14. Tachometer 8. Seat and safety belt 15. GPS, Radio, Transponder 16. Powerplant instruments 17. Flight instruments 18. Throttle lever Date: 28.10.2010, Rev.: 1 1 3 2 4 18 6 7 8 9 10 11 12 13 14 15 16 17 5 WT9 Dynamic LSA Speed S FLIGHT MANUAL Section 4 Page 4-8 4.5.1 Before starting engine 1. Ignition/ Starter switch - position off 2. Rudder pedals - freedom of movement 3. Control stick - freedom of movement 4. Throttle lever - freedom of movement, set to idle position 5. Seat and safety harness - adjust and lock 6. Brake - set “brake” position 7. Canopy of cockpit - shut and latched 4.5.2 Engine starting WARNING Before starting engine check position of the landing gear overswitch . Overswitch position – EXTENSION ( L/G extended ). Cold engine: 1. Fuel selector valve - select left tank 2. Choke - set open 3. Throttle lever - set to idle position 4. Bat 1 - switch on 5. Bat 2 - switch on 6. Storbe lights - switch on 7. Fuel pump - switch on for 5 sec. than switch off 8. Ignition/ Starter switch - position “both” starting for max. 10 sec. Only without interruption 9. Hydraulics - switch on 10. Avionics - switch on 11. As soon as engine runs - adjust throttle lever to achieve smooth running at approximately 2000 r.p.m, choke off 12. Oil pressure - check in green 13. Voltage - check in green 14. Generator - check “OK” 15. Alternator - check > 0 Amps 16. Nav lights - as required 17.Dashboard lights - as required 18.Handle control rescue system - remove secure lock Warm engine: if the engine is already at operating temperature 1. Fuel selector valve - select left tank 2. Choke - set close 3. Throttle lever - set to slight open position 4. Bat 1 - switch on 5. Bat 2 - switch on 6. Storbe lights - switch on 7. Fuel pump - switch on for 5 sec. than switch off 8. Ignition/ Starter switch - position “both” starting for max. 10 sec. Only without interruption Date: 14.06.2011, Rev.: 2 9. Hydraulics - switch on 10. Avionics - switch on 11. As soon as engine runs - adjust throttle lever to achieve smooth running at approximately 2000 r.p.m 12. Oil pressure - check in green 13. Voltage - check in green 14. Generator - check “OK” 15. Alternator - check > 0 Amps 16. Nav lights - as required 17.Dashboard lights - as required 18.Handle control rescue system - remove secure lock 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. Speed drop with only one ignition circuit must not exceed 300 r.p.m. Max. difference 115 r.p.m of speed by use of either circuit A or B 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 4. Check idle speed 1800 r.p.m 4.5.4 Taxying Use of the throttle will help with smooth adjustments of power during taxying. Taxying of the airplane is controlled 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 to green line 4. Wing flaps - as required 5. Fuel selector valve - left tank 6. Fuel pump - switch on 7. Pitot heating - as required 8. Landing gear operating switch - down 9. Hydraulics - check switched on 10. Power plant instrument - check for correct reading; green 11. Flight instruments - check altimeter setting 12. Propeller - set 5400 r.p.m. (take off position) 13. Seat and safety harness - adjust and lock 14. Canopy of cockpit - latched WT9 Dynamic LSA Speed S FLIGHT MANUAL Section 4 Page 4-9 Date: 14.06.2011, Rev.: 2 WT9 Dynamic LSA Speed S 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 controlled 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 ) - at positive climb gear up - at height 50 m AGL wing flaps up 4.5.7. Climbing Normal climbs are conducted at climb speeds 130 - 140 km/h in accordance with the take off weight of the airplane. 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. At safety altitude switch fuel pump off. 4.5.8. Cruise The range of cruising speeds is from 140 to 230 km/h in accordance with the engine speed setting from 4000 to 5500 r.p.m. The economy airspeed for best fuel economy is at 180 km/h, the optimum operation is between 180 km/h to 230 km/h. In case of turbulence reduce cruising speed below 180 km/h. Under certain conditions the airplane may be overstressed. The airplane 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 ULS Engine power setting Engine Speed ( r.p.m ) Performance ( kW ) Torque ( Nm ) Manifold pressure ( in Hg ) Take-off power 5 800 73,5 119,0 27,5 Max. continuous 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: 14.06.2011, Rev.: 2 WT9 Dynamic LSA Speed S FLIGHT MANUAL Section 4 Page 4-11 4.5.9. Descending Descending is conducted at airspeeds 120 – 130 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 of a 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. Mannifold pressure - 15 in. Hg 2. Propeller - set 5.400 rpm 3. Fuel valve - left tank 4. Fuel pump - switch on 5. Landing light - switch on 6. Landing gear operating switch - below 80KIAS down, check 3 greens 7. Wing flaps - as required flaps down at speed below 140 km/h 8. Approach speed - 110-120 km/h according to the weight and wind 9. Elevator trim - adjust as required 10. Actual touch down should be made with power-idle and on the main wheel first. The nose wheel should be lowered smoothly to the runway as speed is diminished 11. During landing run control the aeroplane with help of the rudder pedals. 12. Apply braking as required. The main wheel brakes are actuated via the handle on the pedestall between the pilot seats. 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 Date: 14.06.2011, Rev.: 2 WT9 Dynamic LSA Speed S FLIGHT MANUAL Section 4 Page 4-12 4.5.12 After landing 1. Engine r.p.m. - adjust throttle for taxying 2. Wing flaps - retract 3. Elevator trim - set to rearmost position of neutral 4. Landing gear - check if in down position 5. Fuel pump - switch off 6. Landing lights - switch off 7. Taxying - to the parking position 4.5.13. Securing aeroplane 1. Brakes - set “park” position 2. Throttle - set idling 3. All electrics switches except strobe. - switch off 4. Ignition/ Starter switch - position “left” after 2-3 s. position “off” 5. Bat 1 - switch off 6. Bat 2 - switch off 7. Handle control rescue system - secure with the lock 8. After leaving the cockpit, the canopy should be covered with the cloth dust cover, to avoid the effects of the sun. Date: 14.06.2011, Rev.: 2 WT9 Dynamic LSA Speed S 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 Balked landing climb 5-3 5.3.2 Effect on flight performance and characteristics 5-3 5.3.3 Demonstrated crosswind performance 5-3 5.3.4 Noise data 5-3 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 airplane 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 55 60 100 112 125 137 146 165 176 184 CAS ( km/h ) 55 60 65 100 110 120 130 140 160 170 180 IAS ( km/h ) 203 225 245 267 285 CAS ( km/h ) 200 220 240 260 280 IAS = indicated airspeed CAS = calibrated airspeed Date: 28.10.2010, Rev.: 1 WT9 Dynamic LSA Speed S FLIGHT MANUAL Section 5 Page 5-2 5.2.2 Stall speed Maximum weight 600 kg, C.G. in 30% MAC, idle engine speed Position wing flaps 0°°°° 15°°°° 38°°°° Stall speed IAS in km/h 85 76 70 Stall speed CAS in km/h 87 79 74 5.2.3 Take-off performance The data is valid for following conditions: MTOW 600kg, H = 260 m MSL, Temperature t = 15 ° C, Wing flaps position 15°, engine ROTAX 912 ULS, propeller SR 2000 D Surface of the runway Take-off run distance ( m ) Take-off distance up to 15m ( m ) Paved runway 147 313 Non paved – grass 173 348 5.2.4 Landing distance The data is valid for following conditions: H = 260 m MSL, Temperature t = 15 ° C Wing flaps position 38° , landing speed 1,3 VSo, landing roll is braked. Surface of the runway Landing distance (m) from height 15 m Landing roll distance ( m ) Paved runway 263 75 Non paved - grass 272 84 5.2.5 Climb performance The data is valid for max.weight 600 kg , without flaps, ROTAX 912 ULS, engine speed 5000 r.p.m, propeller SR 2000 D Altitude (m MSL) Speed IAS km/h Rate of climb m/s 0 130 4,55 1000 130 3,16 2000 130 2,54 The service ceiling is 5500 m at the max. continuous power. Date: 28.10.2010, Rev.: 1 WT9 Dynamic LSA Speed S FLIGHT MANUAL Section 5 Page 5-3 5.3 Additional information 5.3.1 Balked landing climb The data is valid for maximum landing weight 600 kg , wing flaps position 38o. Engine ROTAX 912 ULS, engine speed 5500 r.p.m, SR 2000 D Flight altitude (m) Airspeed IAS km/h Rate of climb m/s 0 120 4,22 1000 120 2,85 2000 120 2,20 5.3.2 Effect on flight performance and characteristics No disturbing effects on flight performance and characteristic of the aeroplane WT-9 Dynamic LSA Speed were recorded during the flight tests. 5.3.3 Demonstrated crosswind performance The maximum demonstrated crosswind speed for take-off and landing is 6 m/s according to the airworthiness requirements. 5.3.4 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. Date: 28.10.2010, Rev.: 1 WT9 Dynamic LSA Speed S FLIGHT MANUAL Section 6 Page 6-1 SECTION 6 WEIGHT AND BALANCE / EQUIPMENT LIST Page 6.1 Introduction 6-1 6.2 Weighing procedure 6-1 6.3 Weight and balance record and permitted payload range 6-2 6.4 Master minimum equipment list 6-4 6.1 Introduction This section contains the payload range with which the airplane may be safely operated. C.G. position is very important parameter which effects the safety of flight. NOTE Weight and balance data listed in this section is informative. True data will be given after manufactured plane balancing 6.2 Weighing procedure To define the airplane C.G. it is necessary to weigh the empty airplane with standard and optional equipment, with operating fluids of the engine but without the fuel in the tanks. The airplane is weighed with the help of three weighing-machines located below the left and right main wheels and below the nose wheel. The airplane position for weighing has to be parallel with the horizontal plane which passes through the side edge of the cockpit. The reference point (datum point = DP) is leading edge of wing root section. To measure the distance from centre of main landing wheel axle and of nose wheel axle to reference point DP. C.G. position is calculated from the reference point DP (leading edge) and C.G. position is calculated in % aerodynamic mean chord (MAC) too. The leading edge of the MAC is located in distance 77 mm rear from DP. Centre of gravity position after loading airplane (crew, fuel, baggage or additional equipment) is calculated as following: The sum moments of airplane all components mass is added to the total moment of the empty airplane and divided by total weight. Date: 28.10.2010, Rev.: 1