MAINTENANCE MANUAL

MAINTENANCE MANUAL WT9 Dynamic LSA, WT-9 Dynamic Date: 06.05.2014 Revision: 00 Page 1-2 CONTENT Chapter Page 0. GENERAL 0-1 1. TECHNICAL DESCRIPTION 1-1 1.1. INTRODUCTION 1-4 1.2. CERTIFICATION BASIS 1-4 1.3. WARNINGS, CAUTIONS AND NOTES 1-4 1.4. BASIC AND GENERAL INFORMATION 1-5 1.4.1. AIRCRAFT DESCRIPTION 1-5 1.4.2. DESIGNATION 1-5 1.5. BASIC TECHNICAL DATA 1-6 1.5.1. THREE-VIEW DRAWING 1-6 1.5.1.1. MODEL CLUB “FG912 CONFIGURATION” 1-6 1.5.1.2. MODEL CLUB “FG912T CONFIGURATION” 1-7 1.5.1.3. MODEL SPEED “RG914 CONFIGURATION” 1-8 1.5.2. BASIC DIMENSIONS 1-9 1.5.3. WEIGHTS 1-9 1.5.4. CENTRE OF GRAVITY 1-9 1.6. TECHNICAL DESCRIPTION OF THE AIRCRAFT 1-10 1.6.1. FUSELAGE 1-10 1.6.2. WING 1-11 1.6.2.1. AILERON 1-11 1.6.2.2. WING FLAP 1-11 1.6.3. TAIL UNITS 1-12 1.6.3.1. HORIZONTAL TAIL UNIT 1-12 1.6.3.2. VERTICAL TAIL UNIT 1-12 1.6.4. LANDING GEAR 1-13 1.6.4.1. LANDING GEAR - MODEL CLUB 1-13 1.6.4.2. LANDING GEAR - MODEL SPEED 1-15 1.6.4.3. BRAKE SYSTEM 1-18 1.6.4.4. HYDRAULIC SYSTEM (ONLY MODEL SPEED) 1-20 1.6.5. CONTROL SYSTEMS 1-21 1.6.5.1. ELEVATOR CONTROL SYSTEM 1-21 1.6.5.2. AILERON CONTROL SYSTEM 1-22 1.6.5.3. RUDDER CONTROL SYSTEM 1-23 1.6.5.4. WING FLAP CONTROL SYSTEM 1-25 1.6.6. POWERPLANT 1-27 1.6.6.1. MODEL CLUB “FG912 CONFIGURATION” 1-27 1.6.6.1.1. ENGINE ROTAX 912 ULS 1-27 1.6.6.1.2. ENGINE SYSTEMS 1-29 1.6.6.1.3. PROPELLER EVRA PERFORMANCE LINE 175/XXX/805.5 1-34 1.6.6.2. MODEL CLUB “FG912T CONFIGURATION” 1-35 1.6.6.2.1. ENGINE ROTAX 912 ULS 1-35 1.6.6.2.2. ENGINE SYSTEMS 1-36 MAINTENANCE MANUAL WT9 Dynamic LSA, WT-9 Dynamic Date: 06.05.2014 Revision: 00 Page 1-3 1.6.6.2.3. PROPELLER WOODCOMP SR2000DN 1-38 1.6.6.3. MODEL SPEED “RG914 CONFIGURATION” 1-39 1.6.6.3.1. ENGINE ROTAX 914 UL 1-39 1.6.6.3.2. ENGINE SYSTEMS 1-41 1.6.6.3.3. PROPELLER WOODCOMP SR3000/2N 1-45 1.6.7. COCKPIT 1-46 1.6.7.1. INSTRUMENT PANELS 1-50 1.6.7.1.1. MODEL CLUB “FG912 CONFIGURATION” 1-51 1.6.7.1.2. MODEL CLUB “FG912T CONFIGURATION” 1-53 1.6.7.1.3. MODEL SPEED “RG914 CONFIGURATION” 1-55 1.6.7.2. BAGGAGE COMPARTMENT 1-57 1.6.7.3. COCKPIT HEATING AND VENTING 1-58 1.6.8. EMERGENCY PARACHUTE SYSTEM 1-60 1.6.9. ELECTRIC SYSTEM 1-61 1.6.9.1. MODEL CLUB “FG912 CONFIGURATION” 1-61 1.6.9.2. MODEL CLUB “FG912T CONFIGURATION” 1-62 1.6.9.3. MODEL SPEED “RG914 CONFIGURATION” 1-63 1.6.10. PITOT-STATIC SYSTEM 1-64 1.6.11. TOW RELEASE MECHANISM 1-66 1.6.12. PLACARDS 1-66 MAINTENANCE MANUAL WT9 Dynamic LSA, WT-9 Dynamic Date: 06.05.2014 Revision: 00 Page 1-4 1.1. Introduction The Maintenance Manual for aircraft WT9 Dynamic LSA and WT-9 Dynamic has been prepared to provide the information for the safe and efficient operation of this aircraft. This manual contains supplemental data supplied by the aircraft manufacturer. 1.2. Certification basis WT9 Dynamic LSA (MTOW 600,0 kg): CS-LSA – Certification Specifications for Light Sport Aeroplanes WT-9 Dynamic (MTOW 472,5 kg): German Certification Regulations and Airworthiness Requirements for ultra light aircraft of the DaeC (BFU des DaeC, Ausgabe 10/95). Type Certificate No. 61179 has been issued on 23.10.2001. The Civil Aviation Authorities of Slovak Republic following regulation MDPT SR L 8/A and LU č. P- ULL-1 SR. Type Certificate of Airworthiness No. V-80/2004 dated April 25th 2005 for Type WT-9 Dynamic. Category of Airworthiness : Normal 1.3. Warnings, cautions and notes The following definitions apply to warnings, cautions and notes used in the Maintenance Manual for aircraft WT9 Dynamic LSA and WT-9 Dynamic WARNING Means that the non-observation of the corresponding procedure leads to an immediate or important degradation of the flight safety! CAUTION Means that the non-observation of the corresponding procedure leads to a minor or to a more or less long term degradation of the flight safety! NOTE Draw the attention to any special item, not directly related to safety but that is important or unusual! MAINTENANCE MANUAL WT9 Dynamic LSA, WT-9 Dynamic Date: 06.05.2014 Revision: 00 Page 1-5 1.4. Basic and general information 1.4.1. Aircraft description WT9 Dynamic LSA and WT-9 Dynamic are a single engine, low-wing monoplanes with two side-by side seats and dual control. An airframe consists of a sandwich shells from advanced composite material. Models of WT9 Dynamic LSA (MTOW 600,0 kg) Model Club “FG912 configuration”: The aircraft is equipped with a fixed tricycle landing gear with a nose wheel. As a powerplant is used 4 cylinder, 4 stroke engines Rotax 912 ULS in combination with 3-blade ground adjustable propeller EVRA PERFORMANCE LINE 175/xxx/805.5. Model Club “FG912T configuration”: The aircraft is equipped with a fixed tricycle landing gear with a nose wheel. As a powerplant is used 4 cylinders, 4 stroke engines Rotax 912 ULS in combination with 3-blade in-flight electrically adjustable propeller WOODCOMP SR2000DN. Model Speed “RG914 configuration”: The aircraft is equipped with a retractable tricycle landing gear with a nose wheel. As a powerplant is used 4 cylinders, 4 stroke engines Rotax 914 UL in combination with 2-blade in-flight electrically adjustable propeller WOODCOMP SR3000/2N. Models of WT-9 Dynamic (MTOW 472,5 kg) Models of WT-9 Dynamic (MTOW 472,5 kg) are based on two basic models Club and Speed enabling a wide range of combinations of the above engines and propellers. 1.4.2. Designation WT9 Dynamic LSA and WT-9 Dynamic are intended for sporting, recreation, tourist flying and glider towing in accordance with VFR day. Aerobatic manoeuvres and intentional spins are prohibited! MAINTENANCE MANUAL WT9 Dynamic LSA, WT-9 Dynamic Date: 06.05.2014 Revision: 00 Page 1-6 1.5. Basic technical data 1.5.1. Three-view drawing 1.5.1.1. Model Club “FG912 configuration” Fig. 1.5.1.1-1 WT9 Dynamic LSA, model Club “FG912 configuration” MAINTENANCE MANUAL WT9 Dynamic LSA, WT-9 Dynamic Date: 06.05.2014 Revision: 00 Page 1-7 1.5.1.2. Model Club “FG912T configuration” Fig. 1.5.1.2-1 WT9 Dynamic LSA, model Club “FG912T configuration” MAINTENANCE MANUAL WT9 Dynamic LSA, WT-9 Dynamic Date: 06.05.2014 Revision: 00 Page 1-8 1.5.1.3. Model Speed “RG914 configuration” Fig. 1.5.1.3-1 WT9 Dynamic LSA, model Speed “RG914 configuration” MAINTENANCE MANUAL WT9 Dynamic LSA, WT-9 Dynamic Date: 06.05.2014 Revision: 00 Page 1-9 1.5.2. Basic dimensions Aircraft Wing area 10,31 m2 Wing span 8,93 m Length 6,47 m Height 1,85 m Wing aspect ratio 8,12 Aerodynamic mean chord (MAC) 1,185 m Control surfaces Aileron area 0,27 m2 Aileron span 1,13 m Flap area 0,75 m2 Flap span 2,27 m Horizontal tail area 1,68 m2 Horizontal tail span 2,40 m Vertical tail area 0,89 m2 Vertical tail span 1,18 m Landing gear Club Speed Wheel base 1,400 m 1,423 m Wheel track 2,24 m Nose wheel size 13x5,00-6 Main wheel size 15x6,00-6 1.5.3. Weights Weights Club Speed Average empty weight 335 kg 350 kg Maximum take-off weight (LSA/UL) 600,0 kg / 472,5 kg Maximum landing weight (LSA/UL) 600,0 kg / 472,5 kg Maximum fuel weight (126,0 litres) 90,7 kg Maximum baggage weight 40 kg 1.5.4. Centre of gravity CG positions Empty aircraft 12 ± 2% MAC Operating 20 ÷ 30% MAC MAINTENANCE MANUAL WT9 Dynamic LSA, WT-9 Dynamic Date: 06.05.2014 Revision: 00 Page 1-10 1.6. Technical description of the aircraft 1.6.1. Fuselage Fuselage is monocoque glass/carbon composite construction consisting of three parts that are glued together: right side, left side and lower section. Sandwich shells are made of external and internal shell layers from glass/carbon fibre fabrics and hard foam panel. In the right side of fuselage is glued steel rope for ballistic recovery system that is attached to the auxiliary spar. Fin and horizontal stabilizers are fixed parts of fuselage. There are two windows in baggage compartment. Main and auxiliary spar are glued in the central section of fuselage. Central section is divided in longitudinal direction with a central tunnel that creates the space for two persons – pilot co-pilot. Pilot and co-pilot's seats are arranged side-by-side and consist of removable laminate seats and backrest that is glued with central tunnel and fuselage. Baggage compartment is situated between backrest and baggage bulkhead. Central tunnel passes through the baggage compartment and divides it in two sections. Each section of baggage compartment has 4 attaching point to which is baggage fixed by fastening straps and baggage net. Baggage bulkhead is sloped in the upper section and fitted with covered opening allowing access to the rear section of fuselage. Rear section of fuselage is stiffened with the elliptical bulkheads. There are integral fuel tanks each on the both sides of wing central section situated in front of main spar. There is a drain valve in the lowest point of each fuel tank. Model Club: Plywood firewall in the front section of fuselage is glued to the fuselage and stiffened from the interior side with carbon stiffener, interior floor and rescue system board. Firewall has stiffened areas for engine mount and nose landing gear leg attaching. From the engine compartment is covered with a fire-proof protection. In the wing central section are glued ribs to which the main landing gear legs are attached. In addition model Club “FG912T configuration” has adapted rear part of fuselage due to installation of tow release mechanism (see figures in chapter 1.5.1). Model Speed: Plywood firewall in the front section of fuselage is glued to the fuselage and stiffened from the interior side by central tunnel, interior floor and rescue system board. Firewall has cut-out due to nose landing gear leg and stiffened areas for engine mount attaching. From the engine compartment is covered with fire-proof protection. In the wing central section are situated boxes into which the main landing gear legs are retracted. Main landing gear legs are attached to the main and auxiliary spar. In the central tunnel of front fuselage section is situated box into which the for nose landing gear leg is retracted. MAINTENANCE MANUAL WT9 Dynamic LSA, WT-9 Dynamic Date: 06.05.2014 Revision: 00 Page 1-11 1.6.2. Wing The wing is trapezoidal shape and made of glass/carbon composite sandwich construction. Upper and lower skin is glued together with one main spar and auxiliary web. Tie-down point is attached to the main spar of each half of wing. Wing tips are fitted with winglets. There is a Pitot probe with angle of attack sensing installed on the lower skin of right half of wing. Main spar of each half of wing is attached to the central section main spar using two main pins. Auxiliary web of each half of wing is attached to the auxiliary spar of central section with an auxiliary pin. The outer pin is inserted from the main landing gear box (model Speed) or through the access hole of the lower wing surface (model Club). Inner pin is inserted from interior. There is an integral fuel tank in the each half of wing. Fuel tank is located in the wing root section in front of main spar. Wing tanks have aluminium filler necks with locking caps. There is a drain valve in the lowest point of each wing tank. Wing fuel tanks are connected with fuselage fuel tanks using simple hose connection. 1.6.2.1. Aileron Ailerons are made of glass/carbon composite sandwich construction. Aileron consists of upper and lower skin, ribs and web. Each aileron is attached to the wing’s upper skin by means of three carbon hinges. Ailerons have controlled weight and balance to be kept in verified range given by flutter investigation. The aileron of model Club is fitted with a balance weight. The aileron of model Speed has no balance weight installed. 1.6.2.2. Wing flap Installed are slotted wing flaps that are made of glass/carbon composite sandwich construction. Wing flap consists of upper and lower skin, ribs and a web inside of flap. Each wing flap is attached to the wing by means of three carbon hinges and one carbon/metal root hinge. MAINTENANCE MANUAL WT9 Dynamic LSA, WT-9 Dynamic Date: 06.05.2014 Revision: 00 Page 1-12 1.6.3. Tail units 1.6.3.1. Horizontal tail unit Horizontal stabilizer: Horizontal stabilizer is made of glass/carbon composite sandwich construction. It consists of upper and lower skin, auxiliary web and a web inside of stabilizer up to ¼ of stabilizer span from the plane of symmetry. No outboard fins or winglets are installed on the stabilizer. Elevator: Elevator consists of two parts made of glass/carbon composite sandwich construction. It consists of upper and lower skin, ribs and front web. Each half of elevator is attached to the horizontal stabilizer by means of two carbon hinges. Both halves of elevator are joined together with metal hinge in a plane of symmetry. The elevator of model Club is fitted with a balance weight in the exposed horn. The elevator of model Speed has no balance weight installed. 1.6.3.2. Vertical tail unit Vertical stabilizer: Vertical stabilizer is integral part of fuselage. Rudder: Rudder is made of glass composite sandwich construction. Rudder is attached to the fin by means of three plywood hinges. Rudder is fitted with balance weight in the exposed horn. Rudder has controlled weight and balance to be kept in verified range given by flutter investigation. The rudder of model Club “FG912T configuration” has adapted trailing edge at root section due to safe distance from the towing rope. MAINTENANCE MANUAL WT9 Dynamic LSA, WT-9 Dynamic Date: 06.05.2014 Revision: 00 Page 1-13 1.6.4. Landing gear The model Club is equipped with a fixed tricycle landing gear with steerable nose wheel. The model Speed is equipped with a retractable tricycle landing gear. 1.6.4.1. Landing gear - model Club Main landing gear The main landing gear consists of two composite landing gear legs (1). The main gear legs are fixed in the inner (2) and outer ribs (3) inside of fuselage in the wing central section. Main landing gear is equipped with aluminium wheel discs (4) with tubeless tyres 15x6.00-6 (5). Wheel discs consist of split rim with two ball bearings. The main wheels are equipped with hydraulic brakes (fig. 1.6.4.1-1). Main wheels are fitted with aerodynamic fairings (6). Fig. 1.6.4.1-1 Main landing gear, model Club 1 2 3 4 5 6 MAINTENANCE MANUAL WT9 Dynamic LSA, WT-9 Dynamic Date: 06.05.2014 Revision: 00 Page 1-14 Nose landing gear The nose landing gear leg (1) is metal with a carbon fork (2) and attached to firewall in the lower (3) and upper (4) supports. The nose landing gear incorporates bungees (5) (nose leg - lower support) and rubber damper (nose leg - upper support). Nose leg is steerable and controlled by foot control pedals by means of pull-push rods. The nose landing gear is equipped with an aluminium wheel disc (6) with tubeless tyre 13x5.00-6 (7). The wheel disc consists of split rim with two ball bearings (fig. 1.6.4.1-2). The nose wheel is fitted with aerodynamic fairing (8). Fig. 1.6.4.1-2 Nose landing gear, model Club 2 1 8 4 5 3 6 7 MAINTENANCE MANUAL WT9 Dynamic LSA, WT-9 Dynamic Date: 06.05.2014 Revision: 00 Page 1-15 1.6.4.2. Landing gear - model Speed Main landing gear The main landing gear consists of two metal landing gear legs. The main gear legs are fixed to the central section spar (1) and auxiliary spar (2) through the bearings (3). Landing gear leg is fitted with a damper (4) between the main gear leg (5) and trailing link (6). Retracting is operated by a hydraulic cylinder (7) attached to the drag strut (8). Drag struts lock the landing gear legs in extended position. There are also gas strut (9) and spring (10) which is secondary system for locking of drag strut. Correct geometry of drag struts must be adjusted to lock the landing gear in extended position (fig. 1.6.4.2-1). The main landing gear is retracted into the boxes between main and auxiliary central section spars. There are included also doors partially covering the boxes for main gear legs during the flight with landing gear in retracted position. The main landing gear is equipped with the aluminium wheel discs (11) with tubeless tyres 15x6.00-6 (12). Wheel discs consist of split rim with two ball bearings. The main wheels are equipped with hydraulic brakes (fig. 1.6.4.2-1). Fig. 1.6.4.2-1 Drag strut geometry, main landing gear MAINTENANCE MANUAL WT9 Dynamic LSA, WT-9 Dynamic Date: 06.05.2014 Revision: 00 Page 1-16 Fig. 1.6.4.2-2 Main landing gear, model Speed Nose landing gear The nose landing gear is metal and is attached to the engine mount. Landing gear is equipped with a damper (1) between nose gear leg (2) and trailing link (3). It is operated by hydraulic cylinder (4) attached to the drag strut (5). Drag strut locks the landing gear leg in extended position. There is also gas strut (6) that is secondary system for locking of drag strut. Correct geometry of drag struts must be adjusted to lock the landing gear in extended position (fig. 1.6.4.2-3). The nose landing gear is retracted backward into the box in the central tunnel. Nose leg is steerable and controlled by foot control pedals by means of control cables. The nose landing gear is equipped with an aluminium wheel disc (7) with tubeless tyre 13x5.00-6 (8). The wheel disc consists of split rim with two ball bearings (fig. 1.6.4.2-4). 1 2 3 4 5 6 7 8 9 10 11 12 MAINTENANCE MANUAL WT9 Dynamic LSA, WT-9 Dynamic Date: 06.05.2014 Revision: 00 Page 1-17 Fig. 1.6.4.2-3 Drag strut geometry, nose landing gear Fig. 1.6.4.2-4 Nose landing gear, model Speed 1 7 8 5 6 4 2 3 MAINTENANCE MANUAL WT9 Dynamic LSA, WT-9 Dynamic Date: 06.05.2014 Revision: 00 Page 1-18 1.6.4.3. Brake system Main gear wheels are equipped with hydraulic brakes Beringer that are controlled by a brake lever (1) located on the top of central tunnel. In the central tunnel is also located the brake fluid reservoir (2). Brake lever acts directly on master cylinder (3) located inside of central tunnel. Master cylinder is connected with a pressure limiter (4) (located under the pilot seat) and both callipers (5) by hydraulic hoses (6). Brake discs (7) are inserted into to the shaped wheel rim and locked by a wire. Callipers are attached to the wheel axes for model Club (fig. 1.6.4.3-1) or to the trailing link for model Speed (fig. 1.6.4.3-2). It is possible to lock the brake lever in its aft position to works as a parking brake using groves at slotted link (fig. 14). Fig. 1.6.4.3-1 Brake system, model Club 1 3 6 2 4 6 6 2 6 5 7 3 4 MAINTENANCE MANUAL WT9 Dynamic LSA, WT-9 Dynamic Date: 06.05.2014 Revision: 00 Page 1-19 Fig. 1.6.4.3-2 Brake system, model Speed 1 3 6 2 4 6 6 2 6 5 7 3 4 MAINTENANCE MANUAL WT9 Dynamic LSA, WT-9 Dynamic Date: 06.05.2014 Revision: 00 Page 1-20 1.6.4.4. Hydraulic system (only model Speed) Hydraulic system consists of hydraulic unit installed under the co-pilot seat and hydraulic cylinders operated the retracting and extending of landing gear legs (fig. 1.6.4.4-1). Hydraulic pump (1) creates the pressure that is distributed to the hydraulic accumulator (2), return valve (3), pressure sensors (4) and 4-way 3-position distributor (5). Pressure sensors control the pressure of hydraulic oil in the system and control turning the hydraulic pump ON or OFF. 4-way 3-position distributor directs the hydraulic oil to the distribution boxes (6, 7) from which leads the hydraulic hoses to the hydraulic cylinders in dependence on landing gear controller switch position. In the case of electric power loss the return valve (3) releases the pressure and emergency landing gear extending is ensured by landing gear legs mass and acting of gas struts. For wiring diagram see Annex A.4.2.15. Fig. 1.6.4.4-1 Hydraulic unit CAUTION In case that the Hydraulic pump indication light is shining for more than 20 seconds switch OFF the hydraulic pump circuit breaker (see Chapter 1.6.7.1). The continuing running of hydraulic pump will cause damage of hydraulic system. This can be caused of loose of hydraulic pressure because of hose leaking or other reason. Fly with extended landing gear and after landing contact authorised technician to find and solve the problem. 4 3 2 1 4 5 6 7 MAINTENANCE MANUAL WT9 Dynamic LSA, WT-9 Dynamic Date: 06.05.2014 Revision: 00 Page 1-21 1.6.5. Control systems Aircraft is equipped with dual control systems for elevator, ailerons and rudder. 1.6.5.1. Elevator control system Both control sticks (1) are fitted with bearings, attached to the control stick's torsion tube (2) and linked inside of torsion tube with connecting pull-push rod (3). Torsion tube turns in sliding bearings (4) which are attached to the central section main spar. Elevator is controlled through 3 pull-push rods that are equipped with adjustable bearing eyes. Pull-push rods are situated in the central tunnel. Movement from control sticks is transferred to the elevator through the pull-push rod 1 (5), two-armed lever (6), pull-push rod 2 (7), support lever (8) and pull-push rod 3 (9) to the elevator lever (10). Elevator lever is fixed to the both halves of elevator and hinged through the bearing to the elevator root hinge (11). Elevator root hinge is attached to the horizontal stabilizer aft web. Range of elevator control movement is limited by front stop (12) (installed on the central section main spar) and aft stop (13) (tube with a bolt installed inside of the central tunnel). Control stick’s torsion tube is connected with a trim spring (14) (attached in holder in front of central section main spar) and trim lever (15) (attached to the central tunnel) by means of adjustable pull-push rod (16) and connecting pull-push rod (17). For adjusting of required trim effect of the spring are used slots in the slotted link on the top of central tunnel (fig. 1.6.5.1-1). Fig. 1.6.5.1-1 Elevator control system 1 2 3 4 13 14 5 6 7 8 9 11 10 12 16 17 15 MAINTENANCE MANUAL WT9 Dynamic LSA, WT-9 Dynamic Date: 06.05.2014 Revision: 00 Page 1-22 1.6.5.2. Aileron control system Ailerons are controlled through the control sticks, attached to the control stick's torsion tube. Movement from control sticks is transferred to the ailerons through the pull-push rod 1 (1), pull-push rod 2 (2), bellcrank (3) and pull-push rod 3 (4) to the ailerons (5). Pull-push rods 1 are equipped with adjustable bearing eye at one and revolving fork at the other. Pull-push rods 2 are equipped with adjustable bearing eyes on both ends and are guided in two sliding bearings (6) in the wing (in the root rib and support rib). Bellcranks are fitted with bearings and fixed in the consoles (7) that are attached to the wing spar (8). Bellcranks provide necessary differentiation of the ailerons deflections. The deflections of the ailerons are differentiated 1:1,6. Pull-push rods 3 are equipped with adjustable bearing eyes on both ends and are connected to the aileron root ribs. Range of aileron control movement is limited by stops (9) on the control stick’s torsion tube (10) (fig. 1.6.5.2-1). Fig. 1.6.5.2-1. Aileron control (only right side is shown) 1 2 4 7 5 3 6 6 8 9 10 MAINTENANCE MANUAL WT9 Dynamic LSA, WT-9 Dynamic Date: 06.05.2014 Revision: 00 Page 1-23 1.6.5.3. Rudder control system Model Club: The rudder pedal’s torsion tubes (1) are attached to the floor in four holders (2). The motion of pedals (3) transfers through the torsion tubes arms and control cables (4) to the rudder root levers (5). The polyurethane casings are attached to the fuselage structure to guide the control cables. There are turnbuckles (6) for adjusting of control cables tension. The rudder control pedals are connected to the nose landing gear leg (7) by means of push-pull rods (8) fitted with bearing eyes. Hole in the firewall for push-pull rod is protected with a flange with fireproof sleeve (9). There are control handles (10) that release the locking pins for adjusting of pedals position. Pedals are fitted with springs for return to the rearward position during adjusting. There are 3 possible positions for pedals (fig. 1.6.5.3-1). Fig. 1.6.5.3-1 Rudder pedals, model Club Model Speed: The rudder pedal’s torsion tubes (1) are attached to the rescue system board in four holders (2). The motion of pedals (3) transfers through the torsion tubes arms and control cables (4) to the rudder root levers (5). The polyurethane casings are attached to the fuselage structure to guide the control cables. There are springs (6) attached to the rescue system board and rudder pedals that stretch the control cables. The rudder control pedals are connected to the nose landing gear leg by means of control cables (7) fitted with bearing eyes. Control cable Bowdens are fixed in the holders (8) at the top of nose wheel box and continue under the cockpit floor to the nose leg. Control cables Bowdens are attached to the engine mount (9) and control cables are attached to the nose leg by means of adjustable eyes (10). There are control handles (11) that release the locking pins for adjusting of pedals position. Pedals are fitted with springs for return to the rearward position. There are 3 possible positions for pedals (fig. 1.6.5.3-2 and fig. 1.6.5.3-3). 2 2 5 4 1 1 10 10 3 9 7 9 8 8 6 6 5 4 3 3 2 3 Stop Stop MAINTENANCE MANUAL WT9 Dynamic LSA, WT-9 Dynamic Date: 06.05.2014 Revision: 00 Page 1-24 Fig. 1.6.5.3-2 Rudder control 1, model Speed Fig. 1.6.5.3-3 Rudder control 2, model Speed 1 1 2 2 2 2 3 3 3 3 4 4 5 5 6 6 7 7 11 11 8 8 7 9 10 MAINTENANCE MANUAL WT9 Dynamic LSA, WT-9 Dynamic Date: 06.05.2014 Revision: 00 Page 1-25 1.6.5.4. Wing flap control system The wing flaps are operated manually by a lever (1) on the top of central tunnel between pilot and co-pilot. Wing flaps lever moves in the slotted link (2) that determinates four positions: 1. Retracted, 2. Take-off position (15°), 3. Mid-position (24°), 4. Fully extended position (35°) Movements from wing flap lever are transferred through the pull-push rod 1 (3) and bell crank (4) to the flap's torsion tube (5). Flap’s torsion tube is fixed in three sliding bearings (6) which are attached to the central section auxiliary spar (middle bearing) and outer ribs (left and right bearing). It makes mechanical interconnection between left and right wing flap. Torsion tube is connected with the wing flap lever (7) by means of pull-push rods (8) with fork at the one and adjustable bearing eye at the other one. Wing flap lever is fixed at the wing flap (9) and attached to the flap root hinge (10). There is a booster (11) (gas spring) installed in the flap control system which modify pilot’s operating force during extending/retracting of wing flaps. Booster is situated in the baggage compartment and attached to the central tunnel and flap’s torsion tube. It is protected by laminate cover (fig. 1.6.5.4-1). For model Speed there is in addition attached console for wing flaps buzzer sensor (12) (attached to the bellcrank) and holder for wing flaps position sensor (13) (attached to the sliding bearing) (fig. 1.6.5.4-2). Fig. 1.6.5.4-1 Wing flap control system, model Club 3 2 1 4 5 6 6 6 9 8 7 10 11 6 5 4 11 MAINTENANCE MANUAL WT9 Dynamic LSA, WT-9 Dynamic Date: 06.05.2014 Revision: 00 Page 1-26 Fig. 1.6.5.4.-2 Wing flap control system, model Speed 3 2 1 4 5 6 6 6 9 8 7 10 11 6 5 4 11 12 13 MAINTENANCE MANUAL WT9 Dynamic LSA, WT-9 Dynamic Date: 06.05.2014 Revision: 00 Page 1-27 1.6.6. Powerplant 1.6.6.1. Model Club “FG912 configuration” Powerplant of model Club “FG912 configuration” consists of engine Rotax 912 ULS and propeller EVRA PERFORMANCE LINE 175/xxx/805.5. 1.6.6.1.1. Engine Rotax 912 ULS Rotax 912 ULS is 4-stroke, 4-cylinder horizontally opposed, spark ignition engine, one central camshaft-push-rods-OHV. Liquid cooled cylinder heads, ram air cooled cylinders. Dry sump forced lubrication. The engine is fitted with electric starter, AC generator, mechanical fuel pump. Propeller is driven via integrated gearbox with mechanical shock absorber and overload clutch. For more details see the Maintenance Manual for Rotax Engine Type 912 Series, Ref. No.: MML-912. Engine power (ISA) Max. take-off power 73,5 kW / 100 hp (at 5800 min-1) Max. continuous power 69,0 kW / 94 hp (at 5500 min-1) Engine limitations Engine speed Maximum take-off 5800 min-1 (max. 5 min) Maximum continuous 5500 min-1 Idling ≈1400 min-1 Cylinder head temperature Max. 135 °C Coolant temperature Max. 120 °C Oil temperature Min. 50 °C Normal 90-110 °C Max. 130 °C Oil pressure Min. 0,8 bar / 12 psi (below 3500 min-1) Normal 2-5 bar / 29-73 psi (above 3500 min-1) Max. 7 bar / 102 psi (for short period admissible at cold start) Fuel pressure Min. 0,15 bar / 2,20 psi Max. 0,50 bar / 7,26 psi Engine start, operating temperature Min. -25 °C Max. +50 °C MAINTENANCE MANUAL WT9 Dynamic LSA, WT-9 Dynamic Date: 06.05.2014 Revision: 00 Page 1-28 The engine is fixed to the airframe by means of engine mounts (1). Engine mounts are attached to the engine by four bolts and to the firewall by means of four rubber silentblocks (2) (fig. 1.6.6.1.1-1). Fig. 1.6.6.1.1-1 Engine attachment, model Club Engine compartment is covered by upper and lower laminate cowlings. Upper cowling is fitted with the oil door for easy check of oil level. There are landing lights installed in the lower engine cowling. The disassembly of an upper cowling is easy, just release the quick-closing locks. The quick-closing locks releases by means of a suitable screwdriver with a 90° counter clockwise slewing. The releasing starts at a rear corner with the simultaneous raising of the cowling. The quick-closing locks releases have to remain over a cowling until the disassembly of all cowling. The lower cowling can be removed after disconnecting of the water radiator and oil cooler holders (the water radiator and oil cooler remain connected with the inlet hoses), landing lights wires and air hoses for airbox intake and venting flap intake from the ram air tunnel. To remove the lower cowling, unscrew the attachment screws at the fuselage rim. 1 2 2 2 MAINTENANCE MANUAL WT9 Dynamic LSA, WT-9 Dynamic Date: 06.05.2014 Revision: 00 Page 1-29 1.6.6.1.2. Engine systems Engine compartment and location of engine systems components is displayed at fig. 1.6.6.1.2-1. 1. Oil cooler holder 8. Airbox 2. Oil thermostat 9. Air filter holder with preheating 3. Oil cooler 10. Regulator 4. Ignition 11. Air hose for airbox 5. Carburettor 12. Air hose for venting flap 6. Oil tank 13. Expansion tank 7. Coolant overflow bottle 14. Ram air tunnel Fig. 1.6.6.1.2-1 Engine systems, model Club “FG912 configuration” Fuel system: The integral fuel tanks are located in the forward box of the wing central section and both halves of wing. The wing and central section tanks are connected by a simple hose connection with clamps. There is one large diameter hose between tanks, which serves the fuel from the wing tanks to central section tanks. There are two small diameter hoses, one of them is venting line of wing tank and second one is connects the both tanks (air connection). The integral fuel tanks are covered by a special paint resistive to fuel with a less electrical resistance. There is a rib in the each tank for preclusion of a rapid fuel flowage during the flight manoeuvres. The fuel tank filler caps are located on a wing upper surface. There is a drain valve in the lowest point of each tank (fig. 1.6.6.1.2-2). 14 13 12 5 11 9 8 7 6 5 2 1 4 3 10