FLIGHT MANUAL - WT9 Dynamic LSA

WT9 Dynamic LSA Club LT is low-wing monoplane with fixed undercarriage. The airframe consists of a sandwich shells from advanced composite material. There are two places in the cockpit, side by side type. Airplane is equipped with towing hook. This aircraft is intended for sporting, recreation, glider towing and tourist flying in accordance with VFR day. Powerplant of the aircraft is the 4 cylinder, 4-stroke engine ROTAX 912 ULS with a maximum takeoff RPM limitation 5800 min-1. This plane is fitted with a 3 bladed in flight electrically adjustable propeller and the following type and model is approved: WOODCOMP SR2000D with diameter 1700 mm. 1.4.2. Technical data Airplane Wing area 10,30 m2 Wing span 9,00 m Length 6,40 m Height 2,00 m Wing aspect ratio 7,82 Aerodynamic mean chord (MAC) 1,185 m Control surfaces Aileron area 0,273 m2 Aileron span 1,25 m Flap area 0,75 m2 Flap span 2,28 m Horizontal tail area 1,68 m2 Horizontal tail span 2,40 m Vertical tail area 1,02 m2 Vertical tail span 1,022 m Landing gear Wheel spacing 1,49 m Wheel base 2,27 m Nose wheel diameter 0,32 m Main wheel diameter 0,35 m Weights Empty weight 316,0 kg Maximum takeoff weight 600 kg Useful load 284,0 kg Fuel tank capacity 126 l WT9 Dynamic LSA Club LT FLIGHT MANUAL Section 1, Page 4 Date of revision: 16.07.2012 Revision: 0 1.5. Airplane views WT9 Dynamic LSA Club LT FLIGHT MANUAL Section 1, Page 5 Date of revision: 16.07.2012 Revision: 0 1.5.1. Three view drawing Fig. 1 Three view drawing WT9 Dynamic LSA Club LT FLIGHT MANUAL Section 2, Page 1 Date of revision: 16.07.2012 Revision: 0 2. LIMITATIONS Section Page 2.1. ....................... INTRODUCTION .......................................................................................2 2.2. ....................... AIRSPEEDS...............................................................................................2 2.3. ....................... AIRSPEED INDICATOR MARKINGS ............................................................3 2.4. ....................... POWERPLANT..........................................................................................3 2.5. ....................... POWERPLANT INSTRUMENT MARKINGS ..................................................5 2.6. ....................... MISCELLANEOUS INSTRUMENT MARKINGS ..............................................5 2.7. ....................... WEIGHT ...................................................................................................6 2.8. ....................... CENTRE OF GRAVITY ................................................................................6 2.9. ....................... APPROVED MANOEUVRES .......................................................................6 2.10. ..................... MANOEUVRING LOAD FACTORS ..............................................................7 2.11. ..................... FLIGHT CREW...........................................................................................7 2.12. ..................... KIND OF OPERATION ...............................................................................7 2.13. ..................... FUEL ........................................................................................................7 2.14. ..................... MAXIMUM PASSENGER SEATING .............................................................7 2.15. ..................... OTHER LIMITATIONS................................................................................8 2.16. ..................... LIMITATIONS PLACARDS ..........................................................................8 WT9 Dynamic LSA Club LT FLIGHT MANUAL Section 2, Page 2 Date of revision: 16.07.2012 Revision: 0 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. 2.2. Airspeeds Airspeed limitations and their operational significance are shown below: Speed IAS Remarks km/h mph knots VNE Never Exceed speed 280 174 151 Do not exceed this speed in any operation. VNO Normal Operating Limit speed 250 155 135 Do not exceed this speed except in smooth air, and then only with caution. VRA Rough Air speed 225 140 121 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. VA Manoeuvring speed 180 112 97 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 87 76 Do not exceed these speeds with the given flap setting. WT9 Dynamic LSA Club LT FLIGHT MANUAL Section 2, Page 3 Date of revision: 16.07.2012 Revision: 0 2.3. Airspeed indicator markings Airspeed indicator markings and their colour code significance are shown below: Colour code significance Speed or speed range (IAS) Significance km/h mph knots White arc 76 - 140 47 - 87 41 - 76 Operating range with extended flaps. (Lower limit is ᡴ〠⡨. Upper limit is ᡴ〇〆 .) Green arc 89 - 225 55 - 140 48 - 121 Normal operating range. (Lower limit is ᡴ〠. Upper limit is ᡴ〄 .) Yellow arc 225 - 280 140 - 174 121 - 151 Manoeuvres must be conducted with caution. (Lower limit is ᡴ〄 . Upper limit is ᡴ〕〆 .) Yellow triangle 112 70 60 Minimum approach speed. Yellow line 180 112 97 Manoeuvring speed ᡴ。. Red line 280 174 151 Never exceeded speed ᡴ〕〆 . 2.4. Powerplant Engine Engine manufacturer - ROTAX Bombardier, Gunskirchen, Austria Engine model - ROTAX 912 ULS Maximum power Takeoff (max. 5 min.) 73,5 kW / 100 hp Continuous 69,0 kW / 94 hp Maximum RPM Takeoff (max. 5 min.) 5800 min-1 Continuous 5500 min-1 Cylinder head temperature Maximum 135 °C Oil temperature Maximum 130 °C Minimum 50 °C Oil pressure Maximum 7 bar / 102 psi Minimum 0,8 bar / 12 psi Oil consumption Maximum 0,06 l/h Fuel pressure Maximum Airbox pressure + 0,40 bar / 5,80 psi Normal Airbox pressure + 0,25 bar / 3,63 psi Minimum Airbox pressure + 0,15 bar / 2,18 psi WT9 Dynamic LSA Club LT FLIGHT MANUAL Section 2, Page 4 Date of revision: 16.07.2012 Revision: 0 Oil grade: Motorcycle oil of a registered brand with gear additives. Use only oil with API classification „SG“ or higher! 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 engine cycle oils are required. Heavy duty 4-stroke engine cycle oils meet all the requirements. These oils are normally not mineral oils but semi or fully synthetic oils. WARNING Never use AVGAS, LB 95 with fully synthetic engine oils! Fuel grade: Following types of fuels can be used: • Min. RON 95 EN 228 Super (Unleaded Automotive Gasoline RON 95) • EN 228 Super Plus (Unleaded Automotive Gasoline RON 98) • AVGAS 100 LL (Due to higher lead content in AVGAS, the wear of the valve seats, depositing 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) Propeller Propeller manufacturer WOODCOMP spol. s r. o., Odolená Voda, Czech republic Propeller model SR2000D, 3-bladed in flight electrically adjustable Propeller diameter 1700 mm Additional data can be found in Section 7.9, or in the Operator’s Manual for engine and in the User’s Guide for propeller. WARNING Never run the engine without propeller! This inevitably causes engine damage and is an explosion hazard! WT9 Dynamic LSA Club LT FLIGHT MANUAL Section 2, Page 5 Date of revision: 16.07.2012 Revision: 0 2.5. Powerplant instrument markings According to customer requirement round one–purpose needle instruments can be mounted. Powerplant analogue instrument markings and their colour code significance are shown in table below: Analogue powerplant instruments are not installed. 2.6. Miscellaneous instrument markings According to option of the customer miscellaneous instrument can be mounted. Powerplant digital instrument markings and their colour code significance are shown table below: Digital instrument (Dynon SV-D1000) Unit Red Line Minimum Limit Green Arc Normal Operating Yellow Arc Caution Range Red Line Maximum Limit Tachometer RPM 1400 1400 - 5500 5500 - 5800 5800 Manifold pressure inHg - 0,0 - 28,0 28,0 - 29,5 29,5 Cylinder head temperature oC 50 90 – 110 50 – 90 110 – 135 135 Oil temperature oC 50 90 - 110 50 - 90 110 - 130 130 Oil pressure bar 0,8 2,0 - 5,0 0,8 - 2,0 5,0 - 7,0 7,0 Exhaust gas temperature oC 250 300-800 250-300 800-880 880 Fuel pressure bar 0,15 0,20 - 0,35 0,15 - 0,20 0,35 - 0,40 0,40 Fuel flow meter l/h - 0,0 - 25,0 - over 25,0 Fuel level l Red light annunciator will be illuminated with the remaining 7 litres of fuel in the fuel tank. WT9 Dynamic LSA Club LT FLIGHT MANUAL Section 2, Page 6 Date of revision: 16.07.2012 Revision: 0 2.7. Weight Weights Empty weight 316,0 kg Maximum takeoff weight 600 kg Maximum landing weight 600 kg Useful load 284,0 kg Maximum fuel weight 90,7 kg Maximum occupant weight per seat 120,0 kg Minimum weight solo pilot (with 40 kg of baggage) 54,0 kg Minimum weight solo pilot (without baggage) 72,2 kg Maximum weight in baggage compartment 40 kg WARNING Maximum takeoff weight is 600 kg! 2.8. Centre of gravity CG positions Empty airplane CG position 12 ± 2% MAC Position of CG in flight 20 ÷ 30% MAC Rear centre of gravity limit is valid for en-route weight at maximum crew weight and minimum fuel amount. 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. 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! 2.9. Approved manoeuvres Manoeuvre Appropriate entry speed (IAS) km/h mph knots Steep turns with the angle of bank up to 60° 145 90 78 Lazy eights 145 90 78 WARNING Aerobatic manoeuvres and intentional spins are prohibited! WT9 Dynamic LSA Club LT FLIGHT MANUAL Section 2, Page 7 Date of revision: 16.07.2012 Revision: 0 2.10. Manoeuvring load factors Speed IAS Load factor km/h mph knots VA Manoeuvring speed 180 112 97 +4 VNE Never exceed speed 280 174 151 +4 VA Manoeuvring speed 180 112 97 -2 VNE Never exceed speed 280 174 151 -2 VFE Maximum Flap Extended speed 140 87 76 +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. Kind of operation The aircraft WT9 Dynamic LSA Club LT 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 fuels that can be used for the aircraft WT9 Dynamic LSA Club LT operation are listed in Section 2.4 Powerplant and in the Operator’s Manual for engine ROTAX 912 ULS. Fuel tank's capacities are in table below: Left tank (l) Right tank (l) Total quantity of fuel in the tank 63,0 63,0 Unusable fuel quantity in the tank 2,9 2,9 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. WT9 Dynamic LSA Club LT FLIGHT MANUAL Section 2, Page 8 Date of revision: 16.07.2012 Revision: 0 2.15. Other limitations (a) Wind speed The maximum demonstrated crosswind velocity for takeoff and landing is 12,4 m/s (24 knots). (b) Smoking No smoking on board the aircraft. (c) Glider towing Maximum towing cable load is 3000 N. If the strength of tow cable is more than 3000 N a weak link must be used. Maximum weight of glider to be towed is 750 kg. Maximum crew of towing airplane is only a pilot. 2.16. Limitations placards Airspeed IAS Never Exceed speed VNE 151 knots Normal Operating Limit speed VNO 135 knots Rough Air speed VRA 121 knots Manoeuvring speed VA 97 knots Maximum Flap Extended speed VFE 76 knots Maximum Landing Gear Operating speed VLO 76 knots Aerobatic manoeuvres and intentional spins are prohibited! IFR flights and flights in icing conditions are prohibited! Maximum allowed filling of the fuel tanks in litres Baggage weight (kg) Crew weight (kg) 100 110 120 130 140 150 160 170 180 190 200 210 0 Full Full Full Full Full Full Full Full Full Full 116 102 20 Full Full Full Full Full Full Full Full 116 102 88 75 40 Full Full Full Full Full Full 116 102 88 75 61 47 Maximum baggage weight 40 kg! WT9 Dynamic LSA Club LT FLIGHT MANUAL Section 3, Page 1 Date of revision: 16.07.2012 Revision: 0 3. EMERGENCY PROCEDURES Section Page 3.1. ....................... INTRODUCTION .......................................................................................2 3.2. ....................... ENGINE FAILURE ......................................................................................2 3.3. ....................... AIR START ...............................................................................................3 3.4. ....................... SMOKE AND FIRE .....................................................................................3 3.5. ....................... GLIDE ......................................................................................................4 3.6. ....................... LANDING EMERGENCY .............................................................................4 3.7. ....................... RECOVERY FROM UNINTENTIONAL SPIN ..................................................5 3.8. ....................... OTHER EMERGENCIES ..............................................................................6 WT9 Dynamic LSA Club LT FLIGHT MANUAL Section 3, Page 2 Date of revision: 16.07.2012 Revision: 0 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 pre-flight 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 takeoff roll 1. Throttle lever: Set to idle position. 2. Ignition: Both circuits switched OFF. 3. Brakes: Apply until stop. 3.2.2. Engine failure at takeoff up to height 164 ft 1. Sufficient runway: Complete a normal landing without engine power. 2. Insufficient runway: Perform emergency landing according to procedure 3.6.1. 3.2.3. Engine failure at takeoff above height 164 ft A. Sufficient altitude 1. Air start: Start the engine according to procedure 3.3. 2. Unsuccessful start: Perform emergency landing according to procedure 3.6.1. B. Insufficient altitude 1. Insufficient altitude: Perform emergency landing according to procedure 3.6.1. 3.2.4. Engine failure in flight 1. Air start: Start the engine according to procedure 3.3. 2. Unsuccessful start: Perform emergency landing according to procedure 3.6.1. 3.2.5. Performance loss due to 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 due to emptying of fuel tank (indication is loss of fuel pressure): Select the non empty fuel tank. If everything fails: perform an emergency landing according to procedure 3.6.1. WT9 Dynamic LSA Club LT FLIGHT MANUAL Section 3, Page 3 Date of revision: 16.07.2012 Revision: 0 3.3. Air start 1. Airspeed: Modify to 65 knots. 2. Altitude flight: Check. 3. Field selection: Select according to height available. 4. Fuel selector: Open (non empty fuel tank selected). 5. Choke: Without choke. 6. Throttle lever: Slightly move forward. 7. Ignition: Both circuits switched ON. 8. Starter key: Start the engine. 9. Successful start: Adjust throttle to achieve smooth running at 2500 RPM for approximately half a minute before reaching required power. 10.Unsuccessful start: Perform emergency landing according to procedure 3.6.1. WARNING The rate of descent approximately 492 ft/min causes measurable loss of altitude during the air start. If the air start is unsuccessful up to height 492 ft above ground level, perform the emergency landing according to procedure 3.6.1! 3.4. Smoke and fire 3.4.1. Engine fire on the ground 1. Fuel selector: Close. 2. Throttle lever: Set full throttle. 3. Ignition: Both circuits switched OFF after the fuel has been consumed. 4. Crew: Leave the cockpit immediately. 5. Extinguish fire: With best available means. 3.4.2. Engine fire in flight 1. Fuel selector: Close. 2. Throttle lever: Set full throttle. 3. Ignition: Both circuits switched OFF after the fuel has been consumed. 4. Extinguish fire: Try to extinguish the fire with side slip. 5. Emergency landing: Perform emergency landing in accordance with procedure 3.6.1. CAUTION After the fire has been extinguished, do not start engine again! WT9 Dynamic LSA Club LT FLIGHT MANUAL Section 3, Page 4 Date of revision: 16.07.2012 Revision: 0 3.4.3. Fire in cockpit 1. Fire source: Locate. 2. Ignition: Both circuits switched OFF. 3. Master switch: Set OFF. 4. Crew: On the ground: Leave the cockpit. During flight: Perform an emergency landing in accordance with procedure 3.6.1. 5. Try to extinguish 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. Glide Optimum descent airspeed (IAS) km/h mph knots 130 81 70 Maximum gliding range 10 Rate of descent 3,0 m/s (590 ft/min.) 3.6. Landing emergency 3.6.1. Emergency landing 1. Airspeed: Modify to 65 knots. 2. Field selection: Select in the direction of the free area without obstacles, if possible against the wind. 3. Flaps: Extend as required. 4. Fuel selector: Close. 5. Ignition: Both circuits switched OFF. 6. Master switch: Set OFF. CAUTION The loss of height for 360° turn is approximately 492 ft! WT9 Dynamic LSA Club LT FLIGHT MANUAL Section 3, Page 5 Date of revision: 16.07.2012 Revision: 0 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 against the wind. 2. Fly over selected field with wing flaps 15° and 65 knots airspeed at a height 164 ft AGL, check properly the preferred area for landing to inspect the terrain properties (obstructions, surface conditions). 3. Make landing circuit at a height 492 ft AGL or at a safe altitude as allowed by cloud base with flaps 15° and 65 knots airspeed. Extend “down wind” position and make approach with sufficient power. 4. Don’t lose sight on the selected field in the case of low visibility. 5. Landing approach with flaps for landing and sufficient power. 6. Arrange approach so that the desired touchdown spot will be immediately after passing the edge of the selected landing field. In the case of object collision, perform obstacle avoidance manoeuvre to the side. 7. After touchdown apply heavy breaking till stopped. 8. When the airplane comes to a stop, shut down the engine, master switch off, close the main fuel selector, secure the airplane and seek assistance. 3.6.3. Landing with a flat tyre 1. Landing approach: With wing flaps 35° and airspeed 61 knots. 2. Touchdown: With the bank angle on the inflated tyre at minimum touchdown 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! WT9 Dynamic LSA Club LT FLIGHT MANUAL Section 3, Page 6 Date of revision: 16.07.2012 Revision: 0 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 are conducted with help of the lateral control of the ailerons. 3.8.2. Vibrations The powerplant 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 procedure 3.6.2. 3.8.3. Rescue system Not installed. WT9 Dynamic LSA Club LT FLIGHT MANUAL Section 3, Page 7 Date of revision: 16.07.2012 Revision: 0 3.8.4. Unsecured cockpit canopy If the „Before takeoff“ checklist is performed insufficiently (Section 4.5.5., point 13. Canopy of cockpit), there is a danger of partial cockpit canopy latching and insufficient 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 approx. 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 and 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. 3.8.4.1. During takeoff roll 1. Abort the takeoff, if the cockpit canopy unlatching, unlocking is detected during takeoff 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 Section 7.8). 3.8.4.2. After unstuck or during climbing 1. Safely terminate takeoff. 2. Climb to safety altitude. 3. Fly straight line flight without side-slipping and carry out procedure 3.8.5.3 During level flight. 3.8.4.3. During level flight 1. Open the left ventilation sliding window on cockpit canopy. 2. Reduce speed to 65 knots. 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. 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 Club LT FLIGHT MANUAL Section 4, Page 1 Date of revision: 16.07.2012 Revision: 0 4. NORMAL PROCEDURES Section Page 4.1. ....................... INTRODUCTION .......................................................................................2 4.2. ....................... RIGGING AND DERIGGING .......................................................................2 4.3. ....................... DAILY INSPECTION ...................................................................................5 4.4. ....................... PRE-FLIGHT INSPECTION ..........................................................................5 4.5. ....................... NORMAL PROCEDURES AND CHECK LIST ..................................................8 WT9 Dynamic LSA Club LT FLIGHT MANUAL Section 4, Page 2 Date of revision: 16.07.2012 Revision: 0 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 possibility of the wings disassembling 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 before each assembling. 1. Fit the spar end of the 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. Connect the hoses from the Pitot probe (only right wing), prepare and adjust the wing fuel tank hoses and connect the wiring for fuel tank conductive connection (if the wing is equipped with fuel tanks) and position lights (Fig. 2). 2. Fully push the wing into the wing central panel and slide the wing tank fuel hoses on their sockets together with theirs clamps. Carefully insert the wing flap lever on the wing flap hinge. Take care of the hoses from the Pitot probe (only right wing) and for fuel hoses (if the wing is equipped with fuel tanks) which must not be twisted! 3. Insert wing's pins to connect wing spar with the wing central section. The outer wing pin is inserted through the access hole on the lower wing surface. The inner wing pin is inserted from the cockpit interior (slightly lift and lower the wing tip to ease the pin's insertion). 4. Insert rear spar into the fitting of the central section's rear spar. Secure all 6 pins with safety pins (Fig. 3a and Fig. 3b). 5. Connect the wing flap lever with the wing flap hinge. Connect the flap control rod to the wing flap lever using the wing flap rod pin. During this procedure the flap control lever in the cockpit shall be set to the rearmost position and the wing flap shall be deflected to maximum down position (Fig. 4). 6. Connect the aileron control rod 2 with the aileron control rod 1 and secure the nut (Fig. 3a) with the safety pin. Tight the fuel hose clamps (if the wing is equipped with fuel tanks). 7. Stick the adhesive tape on the gap between wing and wing centre section. 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 probe and fuel hoses! WT9 Dynamic LSA Club LT FLIGHT MANUAL Section 4, Page 3 Date of revision: 16.07.2012 Revision: 0 Fig. 2 Insertion of the wing spar into the wing centre section, position of the wing pins (1, 2 and 3) and the support points (A, B and C) Fig. 3a Outer main wing pin and aileron's connection Attachment bolt of aileron control rod Safety pin Aileron control rod 1 Outer main wing pin Aileron control rod 2 WT9 Dynamic LSA Club LT FLIGHT MANUAL Section 4, Page 4 Date of revision: 16.07.2012 Revision: 0 Fig. 3b Inner main and auxiliary wing pin Fig. 4 Wing flap control connection 4.2.2. Derigging of the wings 1. Drain central section fuel tanks and wing tanks (if the wing is equipped with fuel tanks). 2. Remove the adhesive tape covering the gap between wing and the wing centre section. 3. Disconnect aileron control rod 2 from the aileron control rod 1 (Fig. 3a). Release the fuel hoses clamp (if the wing is equipped with fuel tanks). 4. Disconnect the flap control rod from wing flap lever. Disconnect the wing flap lever from the wing flap hinge (Fig. 4). 5. Pull out all wing's pins (connecting the wing's main and auxiliary spar with the wing central section) (Fig. 3a and Fig. 3b). 6. Pull out the wing along its longitudinal axis so that there is an approx. 100 mm distance between the wing central section and the wing root (Fig. 2). Disconnect the hoses from the Pitot probe (only right wing), the wing fuel tank hoses and wiring for fuel tank conductive connection (if the wing is equipped with fuel tanks) and position lights. 7. Carefully pull the wing away from the wing centre section and put on soft mats. 8. Repeat above process also for second wing. Inner main wing pin Auxiliary wing pin Safety pin Safety pin Safety pin Flap control rod Flap rod pin Wing flap lever Wing flap hinge Wing flap WT9 Dynamic LSA Club LT FLIGHT MANUAL Section 4, Page 5 Date of revision: 16.07.2012 Revision: 0 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-book. 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. Powerplant and propeller. 8. Service fluids. WARNING If any problems are found they must be corrected before flying! 4.4. Pre-flight inspection It is most important to perform a pre-flight inspection carefully to prevent possible trouble. The pre-flight inspection is essential for flight safety. Pre-flight inspection proceeding is on Fig. 5. CAUTION Special attention must be devoted to the parts, which are affected by high vibrations and high temperatures! Fig. 5 Pre-flight inspection proceeding WT9 Dynamic LSA Club LT FLIGHT MANUAL Section 4, Page 6 Date of revision: 16.07.2012 Revision: 0 A. 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 “0” (zero). Cockpit canopy glass: Clean, check cockpit canopy lock. Safety harness: Inspect. Rescue system actuator: Remove secure lock (if installed). Fuel: Check fuel quantity, check fuel selector. B. Wing: Surface: State of wing surface. Connection: Wing pins fully inserted and secured. Fuel tank caps: State of fuel tank caps. Pitot probe: Pitot probe 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. C. Fuselage: Surface: Without damage. Static pressure receivers: Check opening for blockage. Antennas: Fixed, without damage. Cockpit wing walks: Without damage. D. Tail units: Surface: Without damage. Control surfaces: Check for freedom of movement, without excess play. Tail skid: Check for secure attachment. E. 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 of rotation. WT9 Dynamic LSA Club LT FLIGHT MANUAL Section 4, Page 7 Date of revision: 16.07.2012 Revision: 0 F. 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. State of the engine cowlings. State of the exhaust system attachment. Check coolant level and oil level. Engine attachment in rubber silentblocks. Carburettors attachment. State of hoses holders. Condition and integrity of wires, plugs Fuel filters. 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 Club LT FLIGHT MANUAL Section 4, Page 8 Date of revision: 16.07.2012 Revision: 0 4.5. Normal procedures and check list The standard cockpit control arrangement is shown in Fig. 6 and the actual instrument panel is shown in Fig. 7 (see Section 7.4). Fig. 6. The standard cockpit controls (see also Section 7.4) 1. Headset socket/jack 11. Choke 2. Seat and safety belt 12. Ignition, starter key, master switch 3. Pocket 13. Instrument panel 4. Brake lever 14. Flight instruments 5. Wing flap lever 15. GPS, radio, transponder 6. Trim lever 16. Tachometer 7. Control stick 17. Powerplant instruments 8. Fuel selector 18. Magnetic compass 9. Rudder pedals 19. Ventilation flow baffle 10. Throttle lever 20. Ventilation sliding window 7 9 6 4 5 3 1 2 13 20 20 19 19 11 12 16 15 17 14 10 8 2 7 3 18 9 WT9 Dynamic LSA Club LT FLIGHT MANUAL Section 4, Page 9 Date of revision: 16.07.2012 Revision: 0 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 to 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. Brake: Function check. 11. Propeller pitch range: Only electrically adjustable propellers: Check the min. and max. propeller blade's pitch. 12. Canopy of cockpit: Latched and locked. 4.5.2. Engine starting Cold engine: 1. Brakes: Set on parking position. 2. Fuel selector: Left tank. 3. Choke: Activate. 4. Throttle lever: Set to idle position. 5. Master switch: Switch ON. 6. Starter key: Switch to 1st position. 7. Fuel pump: Switch ON and establish the fuel pressure and then switch OFF. 8. Ignition: Both circuits switch ON. 9. Starter key: Actuate. Activate starter for max. 10 sec only without interruption followed by a cooling period. 10. As soon as engine runs: Adjust throttle lever to achieve smooth running at approximately 2500 RPM, check if oil pressure has risen within 10 sec to 2 bar and monitor oil pressure. 11. Choke: De-activate. 12. Warming up: Start warming up procedure according to procedure 4.5.3. WT9 Dynamic LSA Club LT FLIGHT MANUAL Section 4, Page 10 Date of revision: 16.07.2012 Revision: 0 Warm engine (if the engine is already at operating temperature): 1. Brakes: Set on parking position. 2. Fuel selector: Left tank. 3. Throttle lever: Set to idle position. 4. Master switch: Switch ON. 5. Starter key: Switch to 1st position. 6. Ignition: Both circuits switch ON. 7. Starter key: Actuate. Activate starter for max. 10 sec only without interruption followed by a cooling period. 8. As soon as engine runs: Adjust throttle lever to achieve smooth running at approximately 2500 RPM, 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 ROTAX 912 ULS start the warming up period at 2000 RPM for approx. 2 minutes, continue at 2500 RPM, duration depending on ambient temperature, until oil temperature reaches 50 °C. Check temperatures and pressures. Engine ground test: 1. Ignition check: Check the two ignition circuits at 4000 RPM. Speed drop with only one ignition circuit must not exceed 300 RPM. Max. difference 115 RPM of speed by use of either circuit A or B. 2. Throttle response: Short full throttle ground test, speed must not exceed 5800 RPM. 3. Minimum speed: Minimum speed on the ground at full throttle must be 5500 ±200 RPM depending on ambient temperature and pressure. 4. Idle speed: Check the idle speed 1600 ±100 RPM. 5. Propeller pitch range: Only hydraulic adjustable propellers: Set up engine speed at 4000 RPM, set up min. pitch and then max. pitch. Between these ends positions of propeller pitch should be observed significant engine speed variation and acoustic manifestation generated by propeller. 4.5.4. Taxiing Using of the throttle control (movement forward or backward) adjust power during taxiing. Taxiing of the aeroplane is controlled by the 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. WT9 Dynamic LSA Club LT FLIGHT MANUAL Section 4, Page 11 Date of revision: 16.07.2012 Revision: 0 4.5.5. Before takeoff 1. Rudder pedals: Freedom of movement. 2. Control stick: Freedom of movement. 3. Elevator trim control: Set neutral position. 4. Wing flaps: Set takeoff position. 5. Fuel selector: Left tank. 6. Powerplant instrument: Check for correct readings. 7. Flight instrument: Check altimeter setting. 8. Propeller: Set minimum fine angle (takeoff position) (only when equipped with pitch adjustable propeller). 9. Seat and safety harness: Adjust and lock. 10. Canopy of cockpit: Latched and locked. 4.5.6. Normal takeoff 1. Fuel pump: Switch ON. 2. Throttle lever: Full throttle. 3. Control stick: Set into neutral position. 4. Direction on the ground: Control by rudder pedals. 5. Unstick: At speed at 49 – 51 knots (according to takeoff weight). 6. Accelerating: Accelerate to speed 65 – 70 knots (after unstuck). 7. Fuel pump: Should be switched OFF after takeoff in safety altitude. 8. Throttle lever: Adjust throttle lever to max. continues power (5500 RPM). 9. Flaps retracting: At height 164 ft AGL retract the wing flaps. 4.5.7. Climbing Normal climb is conducted at climb speeds 70-76 knots in accordance with the takeoff 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. WT9 Dynamic LSA Club LT FLIGHT MANUAL Section 4, Page 12 Date of revision: 16.07.2012 Revision: 0 4.5.8. Cruise The range of cruising speeds is from 76 to 135 knots in accordance with the engine speed setting from 4000 to 5500 RPM. The economy airspeed for best fuel economy is 97 knots, the optimum operation is between 97 - 121 knots. In case of turbulence reduce the cruising speed below 121 knots. 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 (RPM) Performance (kW) Torque (Nm) Manifold pressure (inHg) Takeoff power 5 800 73,5 121,0 27,5 Continuous power 5 500 69,0 119,8 27,0 75 % 5 000 51,0 97,4 26,0 65 % 4 800 44,6 88,7 26,0 55 % 4 300 38,0 84,3 24,0 4.5.9. Approach Approach is conducted at airspeeds 65 - 70 knots with the throttle lever set to idle position. For increasing the rate of descent it is recommended setting of wing flaps to landing position (35° flaps deflection) and proceeding at airspeed 65 knots. In this configuration the gliding range is 1:8. Side slipping is conducted with airspeed 70 knots, and bank angle 30° with help of full rudder deflection. The side slip direction is controlled by the bank. 4.5.10. Landing Check fuel before approach for landing. Landing approach is conducted at small glide slope angle due to long distance of the float before aeroplane's touchdown. 1. Propeller: Set minimum angle (only when equipped with pitch adjustable propeller). 2. Fuel selector: Left tank. 3. Fuel pump: Switch ON. 4. Approach: Conduct at speed 65-70 knots according to the weight. 5. Wing flaps: As required extend the flaps down at speed below 76 knots. 6. Elevator trim: Adjust as required. 7. Levelling: Begin approx. 10 - 6,5 ft above ground. 8. Touchdown: Touchdown should be made with power-off and on the main wheels first. The nose wheel should be lowered smoothly to the runway as speed is diminished. WT9 Dynamic LSA Club LT FLIGHT MANUAL Section 4, Page 13 Date of revision: 16.07.2012 Revision: 0 9. Control during landing: Control the aeroplane with help of the rudder pedals. 10. Braking: Apply braking as required. The main wheel brakes are actuated via the handle on the top of central tunnel between the pilot seats. 4.5.11. Balked landing 1. Throttle lever: Smoothly adjust the throttle lever to full open (a thrust yawing moment is manifested in case of the steep setting of the throttle lever). 2. Airspeed: Modify to 65 knots. 3. Flaps: Retract the wing flaps if safe. 4. Elevator trim: Adjust as required and proceed in climbing. 4.5.12. After landing 1. Engine RPM: Adjust throttle for taxiing. 2. Wing flaps: Retract the wing flaps. 3. Elevator trim: Set to most rear position of neutral. 4. Fuel pump: Switch OFF. 5. Taxiing: To the parking position. 4.5.13. Securing aeroplane 1. Brakes: Set to “park” position. 2. Throttle lever: Set to idle. 3. Propeller: Set minimum pitch (takeoff position) (only when equipped with pitch adjustable propeller). 4. Instruments: Switch OFF all electronic instruments (avionics). 5. Ignition: Switch OFF the first circuit and after 2-3 s switch OFF the second circuit. 6. Master switch: Switch OFF. 7. Fuel selector: Close. 8. Rescue system: Lock the actuator (if installed). 9. Cockpit leaving: After cockpit leaving the canopy should be covered with the cloth dust-cover, to avoid the effects of the sun. WT9 Dynamic LSA Club LT FLIGHT MANUAL Section 4, Page 14 Date of revision: 16.07.2012 Revision: 0 4.5.14. Takeoff and landing within crosswind Operation in direct crosswinds of 12,4 m/s (24 knots) has been demonstrated. Takeoffs under strong crosswind conditions normally are performed with the minimum flap setting (position 0 or 1) necessary for the field length, to minimize the drift angle immediately after takeoff. With the ailerons partially deflected into the wind, the airplane is accelerated to a speed slightly higher than normal, then the elevator control is used to quickly, but carefully; lift the airplane off the ground and to prevent possible settling back to the runway while drifting. When clear of the ground, make a coordinated turn into the wind to correct for drift and continue in takeoff. When landing in a strong crosswind, use the minimum flap setting (position 1 or 2 maximum, never position 3) required for the field length. Although the crab or combination method of drift correction may be used, the wing low method gives the best control. After touchdown, hold a straight course with the steerable nose wheel, with aileron deflection as applicable and occasional braking if necessary. 4.5.15. Aero towing See 2.15 "Other limitations" for aero towing. Takeoff and climbing with towed glider up to MTOW 410 kg do with flaps in position 15°. At safe height (minimum 164 ft) retract the wing flap. Takeoff and climbing with towed glider with water ballast or from MTOW 410 kg up to MTOW 750 kg do with flaps in position 0°. WARNING Take care for maximum towing speed of towed glider! CAUTION After release of the glider the maximum speed for retracting rope is 86 knots (when retracting mechanism is installed)! WARNING When appropriate and necessary, use guillotine lever of tow rope (when retracting mechanism is installed)! WT9 Dynamic LSA Club LT FLIGHT MANUAL Section 5, Page 1 Date of revision: 16.07.2012 Revision: 0 5. PERFORMANCE Section Page 5.1. ....................... INTRODUCTION .......................................................................................2 5.2. ....................... APPROVED DATA .....................................................................................2 5.2.1. .................... AIRSPEED INDICATOR SYSTEM CALIBRATION ...........................................2 5.2.2. .................... STALL SPEED ............................................................................................2 5.2.3. .................... TAKEOFF PERFORMANCE .........................................................................2 5.2.4. .................... LANDING DISTANCE .................................................................................3 5.2.5. .................... CLIMB PERFORMANCE .............................................................................3 5.3. ....................... ADDITIONAL INFORMATION ....................................................................3 5.3.1. .................... BALKED LANDING CLIMB .........................................................................3 5.3.2. .................... EFFECT ON FLIGHT PERFORMANCE AND CHARACTERISTICS ......................3 5.3.3. .................... DEMONSTRATED CROSSWIND PERFORMANCE ........................................3 5.3.4. .................... NOISE DATA ............................................................................................4 5.3.5. .................... AERO TOWING PERFORMANCE ................................................................4