PILOT'S OPERATING HANDBOOK

with information for the safe and efficient operation of this aircraft. This handbook contains supplementary data supplied by the aircraft manufacturer. WARNING Airplane operator is also obligated to read carefully the Operators Manual for Rotax Engine Type 912 i Series, Ref. No.: OM-912 Series; the Operator’s Manual for – Electrical Adjustable Aircraft Propeller SR2000/DN, actual valid revision and all avionic manuals. 1.2. Certification basis The type of aircraft has been approved in Germany by the Deutscher Aero Club e.V. (DaeC) in accordance with the German Certification Regulations and Airworthiness Requirements for ultra light aircraft of the DaeC (BFU des DaeC, Ausgabe 10/95) and the Type Certificate No. 61179 has been issued on 23.10.2001. The Civil Aviation Authorities of Slovak Republic after studying the documentation Predpis MDPT SR L 8/A and LU č. P- ULL-1 SR has issued the 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 Pilot’s Operating Handbook 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 Draws the attention to any special item, not directly related to safety but which is important or unusual! PILOT’S OPERATING HANDBOOK WT9 Dynamic UL / Speed iS Date of revision: 20.01.2015 Revision: 00 Chapter 1, Page 3 1.4. Descriptive data 1.4.1. Aircraft description WT9 Dynamic Speed is low-wing monoplane with retractable landing gear. The airframe consists of a sandwich shells from advanced composite material. There are two places in the cockpit, side by side type. This aircraft is intended for sporting, recreation and tourist flying in accordance with VFR day. Models of WT9 Dynamic (MTOW 472,5 kg) Club are equipped with wide range of combinations of instruments, engines and propellers. This POH describes one of many combinations. Powerplant of the aircraft is the 4 cylinder, 4-stroke engine Rotax 912 iS Sport with a maximum take-off RPM limitation 5800 min-1. The aircraft is fitted with a 3-bladed in-flight electrically adjustable propeller WOODCOMP SR2000/DN with diameter 1700 mm. 1.4.2. Technical data 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 Wheel base 1,42 m Wheel track 2,24 m Nose wheel size 13x5,00-6 Main wheel size 15x6,00-6 Weights Empty weight 325,0 kg Maximum take-off weight 472,5 kg Max. useful load 147,5 kg Fuel tanks capacity 126 l PILOT’S OPERATING HANDBOOK WT9 Dynamic UL / Speed iS Date of revision: 20.01.2015 Revision: 00 Chapter 1, Page 4 Intentionally left blank PILOT’S OPERATING HANDBOOK WT9 Dynamic UL / Speed iS Date of revision: 20.01.2015 Revision: 00 Chapter 1, Page 5 1.5. Three view drawing Fig. 1.5-1 Three view drawing PILOT’S OPERATING HANDBOOK WT9 Dynamic UL / Speed iS Date of revision: 20.01.2015 Revision: 00 Chapter 2, Page 1 2. LIMITATIONS Chapter 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. ....................... WEIGHTS .................................................................................................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 .............................................................8 2.15. ..................... OTHER LIMITATIONS................................................................................8 2.16. ..................... LIMITATIONS PLACARDS ..........................................................................8 PILOT’S OPERATING HANDBOOK WT9 Dynamic UL / Speed iS Date of revision: 20.01.2015 Revision: 00 Chapter 2, Page 2 2.1. Introduction Chapter 2 includes operating limitations, instrument markings, and basic placards necessary for safe operation of the aircraft, its engine, standard systems and standard equipment. 2.2. Airspeeds Airspeed limitations and their operational significance are shown below: Airspeed description Airspeed Remarks KIAS IAS VNE Never Exceed speed 151 280 Do not exceed this speed in any operation. VNO Normal Operating speed 135 250 Do not exceed this speed except in smooth air, and then only with caution VRA Rough Air speed 124 230 Do not exceed this speed in rough air. Air movements in lee-wave rotors, thunderclouds, visible whirlwind, or over mountain crests are to be understood as rough air VA Manoeuvring speed 89 165 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 76 140 Do not exceed these speeds with the given flap setting. VLO Maximum Landing Gear Operating speed 76 140 Do not extend the landing gear above this speed. VSO Stall speed 35 65 Stall speed with flaps fully extended. VT Towing speed - - Limited by a glider to be towed. PILOT’S OPERATING HANDBOOK WT9 Dynamic UL / Speed iS Date of revision: 20.01.2015 Revision: 00 Chapter 2, Page 3 2.3. Airspeed indicator markings Airspeed indicator markings and their colour code significance are shown below: Colour code significance Airspeed Significance KIAS IAS White arc 35 - 76 65 - 140 Operating range with extended flaps. (Lower limit is 𝑣𝑆0. Upper limit is 𝑣𝐹𝐸 .) Green arc 39 - 124 72 - 230 Normal operating range. (Lower limit is 𝑣𝑆. Upper limit is 𝑣𝐶 .) Yellow arc 124 - 151 230 - 280 Manoeuvres must be conducted with caution. (Lower limit is 𝑣𝐶 . Upper limit is 𝑣𝑁𝐸 .) Red line 151 280 Never exceeded speed 𝑣𝑁𝐸 2.4. Powerplant Engine Engine manufacturer - BRP-Powertrain GmbH, Austria Engine model - Rotax 912 iS Sport Maximum power Take-off (max. 5 min.) 73,5 kW / 100 hp Continuous 72,0 kW / 97 hp Maximum RPM Take-off (max. 5 min.) 5800 min-1 Continuous 5500 min-1 Coolant temperature Maximum 120 °C Oil temperature Minimum 50 °C Normal 90 - 110 °C Maximum 130 °C Oil pressure Minimum 0,8 bar / 12 psi Normal 2,0 - 5,0 bar / 29 - 73 psi Maximum 7 bar / 102 psi Fuel pressure Minimum 2,8 bar / 40,5 psi Normal 2,8 – 3,2 bar / 40,5 – 46,5 psi Maximum 3,2 bar / 46,5 psi Oil consumption Maximum 0,06 l/h PILOT’S OPERATING HANDBOOK WT9 Dynamic UL / Speed iS Date of revision: 20.01.2015 Revision: 00 Chapter 2, Page 4 Propeller Propeller manufacturer WOODCOMP spol. s r. o., Odolená Voda, Czech republic Propeller model SR2000DN, 3-bladed in flight electrically adjustable Propeller diameter 1700 mm WARNING Additional data can be found in Chapter 7.9 and in the Operators Manual for Rotax Engine Type 912 Series, Ref. No.: OM-912 i Series and in the Operator’s Manual for – Electrical Adjustable Aircraft Propeller SR2000DN, actual valid revision. WARNING Never run the engine without propeller! This inevitably causes engine damage and is an explosion hazard! PILOT’S OPERATING HANDBOOK WT9 Dynamic UL / Speed iS Date of revision: 20.01.2015 Revision: 00 Chapter 2, Page 5 2.5. Powerplant instrument markings Digital powerplant instrument Dynon SkyView SV-D1000 for monitoring of engine parameters complements an analogue manifold pressure indicator and a fuel pressure indicator. Ranges are marked with following colour code significance: Digital instrument (Dynon SV-D1000) Unit Red Line Minimum Limit Green Arc Normal Operating Yellow Arc Caution Range Red Line Maximum Limit Tachometer min-1 - 1400 - 5500 0 - 1400 5500 - 5800 5800 Manifold pressure inHg - 0,0 - 28,0 28,0 - 29,5 29,5 Coolant temperature oC 50 90 – 110 50 – 90 110 – 120 120 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 250 300-800 250-300 800-950 950 Fuel pressure bar 0 – 2,8 2,8 - 3,2 - 3,2 – 3,4 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. 2.6. Miscellaneous instrument markings No additional miscellaneous instruments. PILOT’S OPERATING HANDBOOK WT9 Dynamic UL / Speed iS Date of revision: 20.01.2015 Revision: 00 Chapter 2, Page 6 2.7. Weights Weights Maximum take-off weight 472,5 kg Maximum landing weight 472,5 kg Maximum fuel weight 90,7 kg Maximum occupant weight per seat 120,0 kg Minimum weight solo pilot 65,0 kg Maximum weight in baggage compartment 10,0 kg Maximum weight of glider to be towed 750,0 kg WARNING Maximum take-off weight is 472,5 kg! 2.8. Centre of gravity CG positions Empty aircraft 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 of the centre of gravity position check is in the Chapter 6. WARNING A flight shall not be commenced until the pilot-in-command is satisfied that the mass of the aircraft and centre of gravity location are such that the flight can be conducted safely! 2.9. Approved manoeuvres Manoeuvre Appropriate entry airspeed KIAS IAS Steep turns with the angle of bank up to 40° 97 180 Lazy eights 89 165 WARNING Aerobatic manoeuvres and intentional spins are prohibited! PILOT’S OPERATING HANDBOOK WT9 Dynamic UL / Speed iS Date of revision: 20.01.2015 Revision: 00 Chapter 2, Page 7 2.10. Manoeuvring load factors Airspeed description Airspeed Load factor KIAS IAS VFE Maximum Flap Extended speed 76 140 -0 / +2 VA Manoeuvring speed 89 165 -2 / +4 VNE Never exceed speed 151 280 -2 / +4 2.11. Flight crew The minimum flight crew with which the aircraft 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. During towing is allowed only pilot sitting in the left pilot seat. 2.12. Kind of operation The aircraft WT9 Dynamic Speed 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! 2.13. Fuel The fuels that can be used for the operation of aircraft are listed in the Chapter 2.4 Powerplant and in the Operator’s Manual for Rotax Engine Type 912 i Series, Ref. No.: OM-912 i Series. Fuel tank's capacities are in table below: Fuel tanks Left Right l US gal l US gal Total quantity of fuel in the tank 63,0 16,6 63,0 16,6 Unusable fuel quantity in the tank 2,9 0,8 2,9 0,8 Total usable quantity of fuel in the tank 60,1 15,8 60,1 15,8 Maximum allowed filling of the fuel tanks in litres to not get over the MTOW Baggage weight (kg) Crew weight (kg) 70 80 90 100 110 120 130 140 150 160 170 180 0 107,6 93,8 79,9 66,0 52,1 38,2 24,3 10,4 0 0 0 0 5 100,7 86,8 72,9 59,0 45,1 31,3 17,4 3,5 0 0 0 0 10 93,8 79,9 66,0 52,1 38,2 24,3 10,4 0 0 0 0 0 WARNING Fuelling has to respect allowed CG range, see Chapter 6.3! PILOT’S OPERATING HANDBOOK WT9 Dynamic UL / Speed iS Date of revision: 20.01.2015 Revision: 00 Chapter 2, Page 8 2.14. Maximum passenger seating The maximum number of passenger on board is one passenger sitting in the right seat in the cockpit. 2.15. Other limitations (a) Wind speed The maximum demonstrated crosswind velocity for take-off and landing is 24 kts (12,4 m/s). (b) Smoking No smoking on board the aircraft. (c) Minimum equipment for flight operation: 1 Airspeed indicator. 2 Sensitive barometric altimeter. 3 Magnetic compass. 4 SkyView SV D1000 with following indications: a. Fuel quantity indication b. Engine RPM indication c. Oil temperature indication d. Oil pressure indication e. Cylinder head temperature indication f. Manifold pressure g. Fuel pressure 5 Safety harness for each occupied seat. 2.16. Limitations placards AIRSPEEDS: VNE 280 km/h VNO 250 km/h VRA 230 km/h VA 165 km/h VFE 140 km/h Maximum Baggage weight 10 kg PILOT’S OPERATING HANDBOOK WT9 Dynamic UL / Speed iS Date of revision: 20.01.2015 Revision: 00 Chapter 3, Page 1 3. EMERGENCY PROCEDURES Chapter 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. ....................... EMERGENCY LANDING .............................................................................4 3.7. ....................... RECOVERY FROM UNINTENTIONAL SPIN ..................................................5 3.8. ....................... OTHER EMERGENCIES ..............................................................................6 PILOT’S OPERATING HANDBOOK WT9 Dynamic UL / Speed iS Date of revision: 20.01.2015 Revision: 00 Chapter 3, Page 2 3.1. Introduction Chapter 3 provides checklist and amplified procedures for coping with emergencies that may occur. Emergencies caused by aircraft 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 chapter should be considered and applied as necessary to correct the problem. If any operations difficulties were observed, use a form in Annex 1 for notification to the manufacturer about this issue. 3.2. Engine failure 3.2.1. Engine failure at take-off roll 1. Throttle lever: Set to idle position. 2. Lane A/Lane B: Both circuits switch OFF. 3. Main and auxiliary fuel pumps: Both switched OFF. 4. Brakes: Apply until stop. 3.2.2. Engine failure at take-off up to height 200 ft (60 m) AGL 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 take-off above height 200 ft (60 m) AGL A. Insufficient altitude - below 500 ft (150 m) AGL 1. Insufficient altitude: Perform emergency landing according to procedure 3.6.1. B. Sufficient altitude - above 500 ft (150 m) AGL 1. Airspeed: Modify to 65 kts (120 km/h). 2. Field selection: Select in the direction the free area without obstacles, if possible against the wind. 3. Air start: Start the engine according to procedure 3.3. 4. Unsuccessful start: 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 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. PILOT’S OPERATING HANDBOOK WT9 Dynamic UL / Speed iS Date of revision: 20.01.2015 Revision: 00 Chapter 3, Page 3 3.3. Air start 1. Airspeed: Modify to 65 kts (120 km/h). 2. Altitude: Check. 3. Field selection: Select according to height available. 4. Fuel selector: Select non-empty tank. 5. Main and auxiliary fuel pumps: Both switched ON. 6. Throttle lever: Put between 1 to 2 cm of throttle opening. 7. Lane A/Lane B: Both circuits switched ON. 1. Starter key: Press until engine runs, then release to ACC position. 8. Successful start: Adjust throttle to achieve smooth running at 2500 min-1 for approximately half a minute before reaching required power. 9. Unsuccessful start: Perform emergency landing according to procedure 3.6.1. WARNING The rate of descent approximately 600 ft/min (3,0 m/s) causes measurable loss of altitude during the air start. If the air start is unsuccessful up to height 500 ft (150 m) 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: Set OFF. 2. Throttle lever: Set full throttle. 3. Lane A/Lane B: Both circuits switched OFF after the fuel has been consumed. 4. Main and auxiliary fuel pumps: Both switched OFF. 5. Crew: Leave the cockpit immediately. 6. Extinguish fire: With best available means. 3.4.2. Engine fire in flight 1. Fuel selector: Set OFF. 2. Throttle lever: Set full throttle. 3. Lane A/Lane B: Both circuits switched OFF after the fuel has been consumed. 4. Main and auxiliary fuel pumps: Both switched OFF. 5. Extinguish fire: Try to extinguish the fire with side slip. 6. Emergency landing: Perform emergency landing according to procedure 3.6.1. CAUTION After the fire has been extinguished, do not start the engine again! PILOT’S OPERATING HANDBOOK WT9 Dynamic UL / Speed iS Date of revision: 20.01.2015 Revision: 00 Chapter 3, Page 4 3.4.3. Fire in cockpit 1. Fire source: Localize. 2. Lane A/Lane B: Both circuits switched OFF. 3. Main and auxiliary fuel pumps: Both switched OFF. 4. Master switch: Set OFF. 5. Crew: On the ground: Leave the cockpit. During flight: Perform an emergency landing according to procedure 3.6.1. 6. Extinguish fire: 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. Landing gear position Retracted Extended Optimum descent airspeed (IAS) KIAS IAS KIAS IAS 70 130 70 130 Maximum gliding range 14 10 Rate of descent ft/min m/s ft/min m/s 492 2,5 590 3,0 3.6. Emergency landing 3.6.1. Emergency landing 1. Airspeed: Modify to 65 kts (120 km/h). 2. Field selection: Select in the direction of the free area without obstacles, if possible against the wind. 3. Landing gear: Airfield or similar surface: Set DOWN. Other surfaces: Use one’s discretion. 4. Flaps: As required. 5. Fuel selector: Set OFF. 6. Lane A/Lane B: Both circuits switched OFF. 7. Main and auxiliary fuel pumps: Both switched OFF. 8. Master switch: Set OFF. CAUTION The loss of height for 360° turn is approx. 500 ft (150 m)! PILOT’S OPERATING HANDBOOK WT9 Dynamic UL / Speed iS Date of revision: 20.01.2015 Revision: 00 Chapter 3, Page 5 3.6.2. Precautionary landing In the event of the aircraft failure, disorientation, shortage of fuel, dangerous deterioration of the meteorological conditions (visibility, thunderstorm) and coming 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 kts (120 km/h) airspeed at a height 200 ft (60 m) AGL, check properly the preferred area for landing to inspect the terrain properties (obstructions, surface conditions). 3. Make landing circuit at a height 500 ft (150 m) AGL or at a safe altitude as allowed by cloud base with flaps 15 and 65 kts (120 km/h) 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. Landing gear: airfield or similar surface – set DOWN, other surfaces – use one’s discretion. 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 aircraft comes to a stop, shut down the engine, master switch off, close the main fuel selector, secure the aircraft and seek assistance. 3.6.3. Landing with a flat tyre 1. Landing approach: Flaps take-off position (35°), airspeed 65 kts (120 km/h). 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! PILOT’S OPERATING HANDBOOK WT9 Dynamic UL / Speed iS Date of revision: 20.01.2015 Revision: 00 Chapter 3, Page 6 3.8. Other emergencies 3.8.1. Control failures Aileron control fault: The aircraft 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 the 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. Emergency extension of the landing gear In the case of hydraulic pump malfunction switch OFF the switch labelled as "HYDRAULICS" (fig. 3.8.3-1) and the emergency extension of the landing gear is carried out by its own mass with the help of gas struts. The landing gear is extended even in the electric power loss. The emergency extension of the landing gear is terminated, when three green lights are illuminated on the instrument panel. Fig. 3.8.3-1 Emergency extension of landing gear 3.8.4. Rescue system Activation of rescue system: 1. Switch of the Fuel Pumps, Lane B and Lane A to stop the engine. 2. Lift off the emergency system actuator protector (1) (fig. 3.8.4-1). 3. Strongly pull the handle of rescue system. 4. Protect your head by hands. Fig. 3.8.4-1 Emergency system actuator protector For other information regarding operation and handling with the rescue system Magnum 501 refer to the Manual for Mounting and Use - Rescue Ballistic Parachute Systems Series Magnum. 1 PILOT’S OPERATING HANDBOOK WT9 Dynamic UL / Speed iS Date of revision: 20.01.2015 Revision: 00 Chapter 3, Page 7 3.8.5. Unsecured cockpit canopy If the „Before take-off“ checklist is performed insufficiently (Chapter 4.5.5., Canopy), 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 canopy frame and it is secured by shot of the lock lever 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 airflow 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. 3.8.5.1. 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 Chapter 7.8). 3.8.5.2. After unstuck or during climbing 1. Climb to safety altitude. 2. Fly straight-line flight without side-slipping and carry out procedure 3.8.5.3 During level flight. 3.8.5.3. During level flight 1. Open both ventilation windows on cockpit canopy. 2. Reduce speed to 65 kts (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 both ventilation windows 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 aircraft descent due to increased total drag! PILOT’S OPERATING HANDBOOK WT9 Dynamic UL / Speed iS Date of revision: 20.01.2015 Revision: 00 Chapter 3, Page 8 3.8.6. Hot engine 1. Increase the airspeed and reduce the engine power. 2. Wait until the temperature will drop down and continue with the flying. 3. If temperature keeps increasing, land immediately. 3.8.7. Towing emergency procedure During glider towing this must be done before performing of any emergency procedure. 1. Transmit “RELEASE, RELEASE, RELEASE”. 2. If the glider pilot does not act, release the towing rope by pulling of tow release lever. 3. Follow the emergency procedure. 3.8.8. Fault indicated by the EMS lamps EMS lamps operating states Lane A Lane B Action OFF Flashing Limited flight operation* Flashing OFF Limited flight operation* OFF ON Land the aircraft Flashing Flashing Land the aircraft Flashing ON Land the aircraft ON OFF Land the aircraft ON Flashing Land the aircraft ON ON Land the aircraft *If one of the lamps is flashing while the other is off then limited flight operation are permitted up to a maximum of 10 hours. 3.8.9. Failure of the EMS power supply 1. If the EMS power supplies (alternator A) fails then the ECU automatically switches one time over to the second EMS power supply (alternator B). 2. While alternator B runs, no power drop is recognizable. 3. Failure of both EMS power supplies (alternator A/B) result in engine stoppage. Remedy: Switch “ON“ the Emergency switch. In this case the power supply is provided by the aircraft battery. 4. Land the aircraft at the next available opportunity. 5. A maintenance inspection should be carried out. NOTE Reduce engine power setting to the minimum necessary and curry out precautionary landing! NOTE No charging of battery! PILOT’S OPERATING HANDBOOK WT9 Dynamic UL / Speed iS Date of revision: 20.01.2015 Revision: 00 Chapter 4, Page 1 4. NORMAL PROCEDURES Chapter Page 4.1. ....................... INTRODUCTION .......................................................................................2 4.2. ....................... WING DERIGGING AND RIGGING .............................................................2 4.3. ....................... DAILY INSPECTION ...................................................................................5 4.4. ....................... PRE-FLIGHT INSPECTION ..........................................................................5 4.5. ....................... NORMAL PROCEDURES AND CHECK LIST ..................................................8 4.5.1. .................... BEFORE STARTING ENGINE ......................................................................9 4.5.2. .................... ENGINE STARTING ...................................................................................9 4.5.3. .................... ENGINE WARMING UP ........................................................................... 11 4.5.4. .................... TAXIING ................................................................................................ 11 4.5.5. .................... BEFORE TAKE-OFF.................................................................................. 12 4.5.6. .................... NORMAL TAKE-OFF................................................................................ 12 4.5.7. .................... CLIMBING .............................................................................................. 12 4.5.8. .................... CRUISE .................................................................................................. 13 4.5.9. .................... APPROACH ............................................................................................ 13 4.5.10................... LANDING ............................................................................................... 14 4.5.11................... BALKED LANDING .................................................................................. 15 4.5.12................... AFTER LANDING .................................................................................... 15 4.5.13................... SECURING AIRCRAFT.............................................................................. 15 4.5.14................... TAKE-OFF AND LANDING WITHIN CROSSWIND....................................... 15 PILOT’S OPERATING HANDBOOK WT9 Dynamic UL / Speed iS Date of revision: 20.01.2015 Revision: 00 Chapter 4, Page 2 4.1. Introduction Chapter 4 provides checklist and amplified procedures for the conduct of normal operation. Normal procedures associated with optional systems can be found in Chapter 9. 4.2. Wing derigging and rigging Procedure for right wing derigging (from fig. 4.2-1 up to fig. 4.2-5): 1. Drain the fuel tanks. 2. Remove the adhesive tape covering the gap between wing and the wing central section. 3. Remove the Fokker needle (4) and disconnect the aileron pull-push rod 2 (13) from the aileron pull-push rod 1 (12). Release the fuel hoses clamps (15). 4. Put the flap control handle to the flaps fully extended position (35°) and disconnect the flap control rod (9) from wing flap lever (5). Disconnect the wing flap lever (5) from the wing flap hinge (6). 5. Remove the Fokker needles (4) auxiliary pin (3), inner pin (2) and outer pin (1). 6. Pull out the wing so that there is an approx. 100 mm distance between the wing central section and the wing root. Disconnect the pitot-static hoses (only right wing), the wing fuel tank hoses, conductive connection wiring and position lights connector. 7. Carefully remove the wing. Procedure for right wing rigging (from fig. 4.2-1 up to fig. 4.2-5): 1. Thoroughly clean and lubricate all the wing suspensions before wing assembly. 2. All pins easily lubricate (1, 2, 3). 3. Fit the wing spar of the central section spar and push the wing so that there will be a distance approx. 100 mm between wing and wing central section. 4. Connect the Pitot probe hoses (only right wing), conductive connection wiring and connect the position lights connectors. Avoid of pitot-static hoses twisting. Put on the hose clamps on the fuel hoses. 5. Push the wing closer, pull on the wing fuel tank hoses on the central section tanks sockets and pull the wing flap lever (5) on the central section flap hinge (6). 6. Fully push the wing into the wing central section. Insert the outer pin (1), inner pin (2) (slightly lift and lower the wing tip to make easy the pin insertion). Secure both pins with the Fokker needles (4). Insert the auxiliary pin (3) and secure it with the Fokker needle (4). 7. Tighten the fuel hoses clamps. 8. Lock the central section flap hinge using washer Ø6 (7) and self-locking nut M6 LN (8). 9. Connect the flap rod (9) to the wing flap lever bearing using a pin (10) and lock with the split pin (11). During this procedure, put the flap control lever to the flaps fully extended position. 10. Connect the aileron pull-push rods (12, 13) and secure the connection with a split pin (14). 11. Check the securing of all the connections. 12. Cover the gap between wing and wing central section using an adhesive tape. NOTE Take care of Pitot probe when handling with the right wing! 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! PILOT’S OPERATING HANDBOOK WT9 Dynamic UL / Speed iS Date of revision: 20.01.2015 Revision: 00 Chapter 4, Page 3 Fig. 4.2-1 Wing rigging Fig. 4.2-2 Outer pin (1) Fig. 4.2-3 Inner pin (2) 1 2 13 4 4 12 4 PILOT’S OPERATING HANDBOOK WT9 Dynamic UL / Speed iS Date of revision: 20.01.2015 Revision: 00 Chapter 4, Page 4 Fig. 4.2-4 Auxiliary pin (3) Fig. 4.2-5 Wing flap connection 6 5 9 10 11 7, 8 3 4 PILOT’S OPERATING HANDBOOK WT9 Dynamic UL / Speed iS Date of revision: 20.01.2015 Revision: 00 Chapter 4, Page 5 4.3. Daily inspection The daily inspection must be performed every day before flight of the aircraft. The scope of this inspection is to check the following: 1. Aircraft log-book and airworthiness certificate. 2. Aircraft technical log-book. 3. Cockpit. 4. Landing gear. 5. All control surfaces for full and free movement. 6. All surfaces of the aircraft 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. 4.4-1. CAUTION Special attention must be devoted to the parts, which are affected by high vibrations and high temperatures! Fig. 4.4-1 Pre-flight inspection proceeding PILOT’S OPERATING HANDBOOK WT9 Dynamic UL / Speed iS Date of revision: 20.01.2015 Revision: 00 Chapter 4, Page 6 A. Cockpit: Flight controls: Check for freedom of movement. Master switch: Switched OFF. Lane A/Lane B: Both circuits switched OFF. Emergency (backup battery) switch: Switched OFF. Hydraulic pump: Switched OFF. Landing gear: Set DOWN. Loose items: Secure or remove. Check instruments: Set “0” (zero). Cockpit canopy glass: Clean, check cockpit canopy lock. Safety harness: Inspect. 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. Wing 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 gear legs: Main wheel tyres state and inflation (250 kPa), attachment, suspension check. Brakes: Visually check condition of brake pads, brake system for leaks. Legs: State without damage, attachment. Nose gear leg: Nose wheel tyre state and inflation (200 kPa) attachment, suspension check, wheel free of rotation. PILOT’S OPERATING HANDBOOK WT9 Dynamic UL / Speed iS Date of revision: 20.01.2015 Revision: 00 Chapter 4, Page 7 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. Fuel system: Drain the fuel tanks: 1. Place a suitable bottle below the drain valve. 2. Open the fuel tank filling cap. 3. Drain a small quantity of fuel by pushing of drain valve (fig. 4.4-2) to remove accumulated water if any. 4. Close and check the drain valve. Fig. 4.4-2 Drain valves 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! PILOT’S OPERATING HANDBOOK WT9 Dynamic UL / Speed iS Date of revision: 20.01.2015 Revision: 00 Chapter 4, Page 8 4.5. Normal procedures and check list The cockpit controls arrangement is shown in fig. 4.5-1 and the instrument panel is shown in detail in the Chapter 7.4. Fig. 4.5-1 Cockpit controls arrangement 1. Headset socket/jack 8. Central console (see Chapter 7.4) 2. Seat and safety belt 9. Rudder pedals 3. Pocket 10. Instrument panel (see Chapter 7.4) 4. Brake lever 11. Gas strut 5. Wing flap lever 12. Ball vents 6. Trim lever 13. Ventilation sliding window 7. Control stick - 1 2 2 3 3 7 7 5 4 8 6 9 9 11 11 10 12 12 13 13 PILOT’S OPERATING HANDBOOK WT9 Dynamic UL / Speed iS Date of revision: 20.01.2015 Revision: 00 Chapter 4, Page 9 4.5.1. Before starting engine 1. Master switch: Switched OFF. 2. Lane A/Lane B: Both circuits switched OFF. 3. Emergency switch: Switched OFF. 4. Control stick: Freedom of movement. 5. Throttle lever: Freedom of movement, set to idle position. 6. Elevator trim control: Set to neutral position. 7. Fuel quantity: Check. 8. Instruments: Setting and check up of the value. 9. Circuit breakers: Check. 10. Radio: Function check. 11. Seat and safety harness: Adjust and lock. 12. Brake: Function check. 13. Landing gear: Set DOWN. 14. Propeller pitch range: Check the min. and max. propeller pitch and adjust minimum pitch. 15. Canopy: Latched and locked. 16. Rescue system actuator: Remove the lock (1) (fig. 4.5.1-1). Fig. 4.5.1-1 Emergency system actuator lock 4.5.2. Engine starting WARNING Before starting the engine, check the position of landing gear switch to be set “DOWN” (landing gear extended)! 1. Brakes: Set on parking position. 2. Fuel selector: Select non-empty tank. 3. Master switch: Switch ON. 4. Flight Display: Activate. 5. ACL lights: Switch ON. 6. Main fuel pump: Switch ON. WARNING Switch only one fuel pump when starting the engine! Switching on both fuel pumps – Main and Auxiliary, can lead to a bad starting behavior! 1 PILOT’S OPERATING HANDBOOK WT9 Dynamic UL / Speed iS Date of revision: 20.01.2015 Revision: 00 Chapter 4, Page 10 7. Fuel pressure: Check if it has reached 3 bars. 8. Lane A/Lane B: Both circuits switch ON and check if Lane A and Lane B Warning Lamps extinguish within 6 seconds. 9. Starter key: Switch to Start Power position. 10. Warning lamps: Check if illuminate and extinguish within 3 seconds. 11. Throttle lever: Put between 1 to 2 cm of throttle opening. 12. Starter key: Press until the engine runs and release to ACC position after engine has reached 1500 min-1 or more (stable engine run). CAUTION Activate starter for maximum of 10 seconds only (without interruption), followed by a cooling period of 2 minutes! 13. As soon as engine runs: Adjust throttle lever to achieve smooth running at approx. 2500 min-1and hold speed at least 5 seconds (await generator shift from Gen B to Gen A). CAUTION Increasing engine speed is only permitted at steady oil pressure readings above 3 bar! WARNING If after the engine start a warning lamp flashes or lights up, perfrom a LANE and IGNITION check. After the check both warning lamps must be deactivated. Otherwise the error must be located and repaired before the flight! CAUTION Cooling of the engine is insufficient when idling on the ground. If idling is needed never do that for a longer time, monitor temperatures and preferably relocate the plane into upwind position! 14. Warming up: Start warming up procedure according to the procedure in 4.5.3. 15. Fuel quantity: Check. 16. Avionics: Switch ON and Set. Function check. PILOT’S OPERATING HANDBOOK WT9 Dynamic UL / Speed iS Date of revision: 20.01.2015 Revision: 00 Chapter 4, Page 11 4.5.3. Engine warming up In accordance with the Operator’s Manual for Rotax Engine Type 912 i Series, Ref. No.: OM-912 i, start the warming up period at 2000 min-1 for approx. 2 minutes, continue at 2500 min-1, duration depending on ambient temperature, until oil temperature reaches 50 °C. Check temperatures and pressures. Engine ground test: 1. Brakes: Brakes set on full. 2. LANE and ignition check: Check the two ignition circuits (LANE A/B) at 4000 min-1. Speed drop with only one ignition circuit must not exceed 180 min-1. Max. difference 75 min-1 of speed by use of either circuit A or B. Check power supply and minimum voltage of 12V at each LANE. 3. Throttle response: Short (maximum of 10 seconds) full throttle ground test, speed must not exceed 5800 min-1 (at min. propeller pitch). 4. Minimum speed: Minimum speed on the ground at full throttle (100%) must be 5500 ±200 min-1 depending on ambient temperature and pressure (at min. propeller pitch). 5. Idle speed: Check the idle speed 1600 ±100 min-1. 6. Fuel pumps check: Set both fuel pumps ON and engine speed to 2000 min-1. Turn auxiliary fuel pump OFF for 5 seconds, check fuel pressure, then turn auxiliary fuel pump ON. Turn main fuel pump OFF for 5 seconds, check fuel pressure, then turn main fuel pump ON. WARNING If fuel pressure is not within the limits, the cause must be determinated and repaired before the flight! 4.5.4. Taxiing Use of the throttle control (screw in, screw out) what will help with smooth adjustments of power during taxiing. Taxiing of the aircraft 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. During taxiing check the rudder pedals freedom of movement. In addition before glider towing: 1. Taxi to the front of a glider to can attach the towing rope. 2. Set the aircraft to take-off configuration (use manual propeller control). 3. Start slowly taxiing to tighten the rope. 4. Check in the rear mirror if the glider wings are levelled and an area in front of glider is clear. PILOT’S OPERATING HANDBOOK WT9 Dynamic UL / Speed iS Date of revision: 20.01.2015 Revision: 00 Chapter 4, Page 12 4.5.5. Before take-off 1. Control stick: Freedom of movement. 2. Elevator trim control: Set neutral position. 3. Wing flaps: Set take-off position (15°) (see also Chapter 4.5.14). 4. Fuel selector: Select non-empty tank. 5. Main and auxiliary fuel pumps: Both switched ON. 6. Landing gear: Set DOWN. 7. Hydraulic pump: Switch ON. 8. Powerplant instrument: Check for correct readings. 9. Flight instrument: Check altimeter setting. 10. Seat and safety harness: Adjust and lock. 11. Canopy: Latched and locked. 12. Landing lights: Switch ON. 4.5.6. Normal take-off 1. Throttle lever: Full open. 2. Control stick: Set into neutral position. 3. Direction on the ground: Control by rudder pedals. 4. Unstick: At speed at 49-51 kts (90-95 km/h) (according to take-off weight). 5. Accelerating: Accelerate to 65-70 kts (120-130 km/h) (acceleration after unstuck). With glider: 1. Throttle lever: Full open. 2. Control stick: Set into neutral position. 3. Direction on the ground: Control by rudder pedals. 4. Unstick: At speed at 49-51 kts (90-95 km/h). 5. Glider: Check in mirror if the glider is airborne. If not, keep the aircraft approx. 7 ft (2 m) above ground and wait until the glider is airborne. 6. Accelerating: Accelerate up to the glider towing speed. For take-off from short runway keep the wing flaps retracted and at speed 32 kts (60 km/h) set the flaps to the take-off position (15°) (see also the Chapter 4.5.14). 4.5.7. Climbing Monitor cylinder head temperature and oil pressure during climb. Oil temperature limits must not be exceeded. In the case of high readings, increase airspeed and reduce engine power setting. Without glider: 1. Throttle lever: Throttle lever to max. continues power. 2. Airspeed: Conduct at speed 70-76 kts (130-140 km/h). 3. Flaps retracting: At height 200 ft (60 m) AGL retract the wing flaps slowly. 4. Landing lights: Switch OFF. 5. Auxiliary fuel pump: Should be switched OFF after take-off in safety altitude 500 ft (150 m).