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HPH Glasflugel 304 MS Flight Manual

For the powered sailplane
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  • Page 1 Č Č á á á á á á info@hph.cz...
  • Page 2 Č Č á á á á á á info@hph.cz Glasflügel 304 MS Type Certificate No.: Date of Issue: 07/14 Pages identified by “Appr” are approved by EASA: Signature: ..........Authority: ..........Stamp: Original date of approval: ..........Approved under Ref. No.: ..........
  • Page 3 Record of revisions Any revision of the present manual, except actual weighing data, must be recorded in the following table and in case of approved Sections endorsed by the responsible airworthiness authority. The new or amended text in the revised page will be indicated by a black vertical line in the left hand margin, and the Revision No.
  • Page 4 List of Effective Pages Section Page Date of Section Page Date of Issue Issue Appr. 07/14 07/14 2-10 Appr. 07/14 07/14 2-11 Appr. 07/14 07/14 2-12 Appr. 07/14 07/14 2-13 Appr. 07/14 07/14 2-14 Appr. 07/14 07/14 07/14 07/14 Appr. 07/14 07/14 Appr.
  • Page 5 Section Page Date of Section Page Date of Issue Issue Appr. 07/14 Appr. 07/14 Appr. 07/14 Appr. 07/14 Appr. 07/14 Appr. 07/14 Appr. 07/14 Appr. 07/14 Appr. 07/14 07/14 Appr. 07/14 07/14 Appr. 07/14 07/14 Appr. 07/14 Appr. 07/14 Appr. 07/14 07/14 4-10...
  • Page 6 Section Page Date of Section Page Date of Issue Issue 07/14 07/14 07/14 07/14 07/14 07/14 07/14 07/14 07/14 07/14 07/14 07/14 07/14 07/14 07/14 07/14 7-10 07/14 07/14 7-11 07/14 07/14 7-12 07/14 7-13 07/14 7-14 07/14 7-15 07/14 Document No.: G304MS/AFM 0 -4 Date of Issue: 07/14...

  • Page 7: Table Of Contents

    Table of Contents Section General ..................1 (a non-approved section) Limitations ................2 (an approved section) Emergency procedures ............3 (an approved section) Normal procedures ..............4 (an approved section) Performance ................5 (a partly approved section) Weight and balance / equipment list ........6 (a non-approved section) Sailplane and systems description ........

  • Page 8: General

    SECTION 1 1. General Introduction Certification basis Warnings, cautions and notes Descriptive data Three-view drawing Document No.: G304MS/AFM Date of Issue: 07/14...
  • Page 9 Introduction The Flight Manual for this powered sailplane has been prepared to provide pilots with information for the safe and efficient operation of Glasflügel 304 MS powered sailplane. This manual includes the material required to be furnished to the pilot by JAR-22. It also contains supplemental data supplied by the sailplane manufacturer.
  • Page 10 Warnings, cautions and notes The following definitions apply to warnings, cautions and notes in the flight manual. WARNING Means that the non-observation of the corresponding procedure leads to immediate or important degradation of the flight safety. CAUTION Means that the non-observation of the corresponding procedure leads to minor or to more or less long term degradation of the flight safety.
  • Page 11 Descriptive data Glasflügel 304 MS is single seat 18 m flapped powered sailplane (capable of self-launching) of 18 m FAI class, constructed from fiber reinforced plastics (FRP), featuring camber-changing flaps and a T- tail (with fixed horizontal stabilizer and elevator). Sailplane description Fuselage The fuselage shell is pure CFRP shell construction reinforced with...
  • Page 12 Cockpit interior Head-rest, back-rest and rudder pedals are adjustable in flight. The back-rest rotation point can only be adjusted on the ground. When the canopy is opened the instrument carrier pivots upward and renders possible a comfortable and unrestricted pilot entry and exit.
  • Page 13 Basic Technical Data Wing Span ......... 18 m ....59.06 ft Wing area ...... 11.8 m ....127.01 ft Aspect ratio ....27.43 Fuselage Length......6.79 m ....22.28 ft Width ......0.62 m ....2.03 ft Height ......1.48 m ....4.86 ft Cockpit height ....
  • Page 14 Three-view drawing Document No.: G304MS/AFM Date of Issue: 07/14...

  • Page 15: Limitations

    SECTION 2 2. Limitations Introduction Airspeed Airspeed indicator markings Powerplant, fuel and oil Powerplant instruments markings Weight Center of Gravity Approved maneuvers Maneuvering load factors 2.10 Flight crew 2.11 Kinds of operation 2.12 Minimum equipment 2.13 Aerotow and winch launch 2.14 Other limitations 2.15 Limitations placards Document No.:G304MS/AFM...
  • Page 16 Introduction Section 2 includes operating limitations, instrument markings, and basic placards necessary for safe operation of the sailplane, standard systems and standard equipment. The limitations included in this section and in Section 9. have been approved by the EASA. Document No.:G304MS/AFM Approved Date of Issue: 07/14...
  • Page 17 Airspeed Airspeed limitations and their operational significance are shown below: Speed KIAS Remarks [km/h] [mph] Do not exceed this speed in any Never exceed V NE operation and do not use more speed than 1/3 of control deflection Do not exceed this speed except in smooth air, and then only with V RA Rough air speed...
  • Page 18 CAUTION Keep in mind, that a difference between Indicated Air Speed (IAS) shown by your airspeed indicator and True Air Speed (TAS) is increasing with an altitude increase. This has no influence on the sailplane strength or load, however due to flutter safety the IAS limits shown in table below must not be exceeded in given altitudes.
  • Page 19 Airspeed indicator markings Airspeed indicator markings and their color-code significance are shown below: Value or range IAS Marking Significance [km/h] KIAS [mph] Allowed range for Flaps set to positive position L – white mark and letter at White arc 85 - 200 45 - 107 52 - 124 160 km/h...
  • Page 20 Powerplant, fuel and oil Engine manufacturer: Solo Kleinmotoren GmbH Stuttgarter Straße 41 71069 Sindelfingen Germany Engine model: SOLO 2625 01 Take-off power at 6200 RPM (MSL, ISA): 39 kW (53 HP) Max. continuous power at 6200 RPM: 39 kW (53 HP) Maximum permitted coolant liquid temperature: 115°...
  • Page 21 Powerplant instruments markings Powerplant insrtument markings and their colour-code significance are shown bellow: Normal Caution Maximum Instrument Range Range Limit Signal Green Yellow Tachometer over 6700 RPM Indicator Range 2500 - 6500 6500 - 6700 (RPM [RPM /min] blinking) buzzer Signal Coolant Liquid Temperature...
  • Page 22 3,49 kg (7 lbs) of the pilot‘s insufficient weight. Maximum lead ballast capacity of the ballast box is 12 kg (26 lbs). Suitable lead ballast plates are available from HPH Ltd. Permanent tail water ballast allows to pilot maintain the flight cg position at optimum range.
  • Page 23 Document No.:G304MS/AFM Approved Date of Issue: 07/14...
  • Page 24 Approved maneuvers This sailplane is certified in the UTILITY category. Intentional aerobatic maneuvers are prohibited. WARNING Aerobatic maneuvers and intentional spins are prohibited. Maneuvering load factors This sailplane is certified in the Utility category. The following load factors may not be exceeded during maneuvers: n = +5.3 at air speed V A = 200 km/h, 107 KIAS, 124 mph...
  • Page 25 2.11 Kinds of operation VFR flight by day permitted only. WARNING Intentional cloud flights are PROHIBITED. 2.12 Minimum equipment The instruments as well as the appropriate parts of the minimum equipment must be of an approved type. Minimum equipment: • 1 Airspeed indicator (color marked as in par.2.3.) •...
  • Page 26 2.13 Aerotow and winch launch Aerotow (powerplant retracted) - nose tow release preferable, although CG hook can be used Maximum towing speed: .... 150 km/h, 80 KIAS, 93 mph Weak link in tow rope: ....max. 780 daN Minimum length of tow rope: ..40 m (130 ft) Tow rope material: .....
  • Page 27 2.15 Limitations placards MAX 2 kg INCL. INSTALLED EQUIPMENT Document No.:G304MS/AFM 2-12 Approved Date of Issue: 07/14...
  • Page 28 Document No.:G304MS/AFM 2-13 Approved Date of Issue: 07/14...
  • Page 29 WEIGHT LIMITATION MAX.TAKEOFF WEIGHT 600 kg 1322 lbs MAX.WEIGHT OF NON-LIFTING PARTS 373 kg 822 lbs PERMITTED COCKPIT LOAD RANGE 70÷110 kg 154-242 lbs FOR COCPIT LOAD LIMITATION REFFER TO ACTUAL WEIGHT AND BALANCE DATA AT FLIGHT MANUAL SECTION 6 AIRSPEED LIMITATION IAS V NE Never exceed speed...
  • Page 30 AEROBATIC MANOEUVRES, INTENTIONAL SPINS CLOUD FLIGHTS ARE PROHIBITED Never exceed speed v Altitude [ft] [km/h] KIAS [mph] 1000 3281 2000 6562 3000 9843 4000 13123 5000 16404 6000 19685 7000 22966 8000 26247 9000 29528 10000 32808 Document No.:G304MS/AFM 2-15 Approved Date of Issue: 07/14...

  • Page 31: Emergency Procedures

    SECTION 3 3. Emergency procedures Introduction Canopy jettison Bailing out Stall recovery Spin recovery Spiral dive recovery Engine failure 3.7.1 Engine failure during takeoff 3.7.2 Engine failure during flight 3.7.3 Engine starting in flight without electric starter Fire 3.8.1 Engine fire on the ground 3.8.2 Engine fire during takeoff 3.8.3...
  • Page 32 Introduction Section 3 provides checklist and additional procedures for coping with emergencies that may occur. Emergency situations can be minimized by proper pre-flight inspections and maintenance. CAUTION If possible, always use the Engine Master Switch for engine emergency shut down. NOTE Extended powerplant does not have negative influence on safe flight termination.
  • Page 33 Canopy jettison 1. Engine Main Switch 2. Grasp (from below) the red grips (right and left of the canopy frame) 3. Pull them back 4. Push the canopy upward. Bailing out For bailing out, first the powerplant should be stopped and – if possible –...
  • Page 34 Spin recovery 1. Engine Main Switch 2. Control stick ailerons in neutral position 3. Flaps set 0 4. Rudder pedals full deflection opposite direction of the spin 5. Control stick push the control stick forward until the rotation stops 6. Neutralize rudder and recover the dive Spiral dive recovery 1.
  • Page 35 3.7.2 Engine failure during flight 1. Airspeed Maintain min. 94 km/h, (50 KIAS, 58 mph) 2. Fuel Quantity Check 3. Fire valve CLOSE 4. Ignition switch 5. Altitude Decide, select either engine starting in flight (Sect. 3.7.3) or landing procedure. NOTE Should the engine fail in flight due to the lack of fuel or a defect, retract the powerplant as quickly as possible to avoid any...
  • Page 36 Fire 3.8.1 Engine fire on the ground 1. Wheel brake Engage 2. Throttle lever Full open 3. Fire valve CLOSE 4. Engine Let run down 5. Engine Main Switch 6. Ignition switch 7. Sailplane Evacuate 3.8.2 Engine fire during takeoff 1.
  • Page 37 Other emergencies 3.9.1 Wingtip catching in high grass during takeoff Takeoff's from long grass runways should be avoided both for aerotow and winch-launching. Should a wingtip be caught in high grass, release immediately, delaying this may result in a ground loop. 3.9.2 Towing rope release at low height A speed within 85-90 km/h (46-49 KIAS, 53-56 mph) should be maintained after release at low height in straight and level flight (the...

  • Page 38: Normal Procedures

    SECTION 4 4. Normal procedures Introduction Rigging and de-rigging 4.2.1 Rigging 4.2.2 De-rigging Daily inspection Preflight inspection 4.4.1 Check list before takeoff 4.4.2 Check list for self-launching Normal procedures and recommended speeds 4.5.1 Aerotow 4.5.2 Winch launch 4.5.3 Launch/engine starting, run up, taxying procedures 4.5.4 Takeoff and climbing 4.5.5...
  • Page 39 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. Rigging and de-rigging 4.2.1 Rigging 1. Clean and grease pins and bearings. 2. In the cockpit, set the flap level at high speed, the brake lever in the medium position, and the water ballast lever should be set in the closed position.
  • Page 40 4.2.2 De-rigging 1. Remove sealing tape from wings and tailplane. 2. Pull front tailplane connection pin out, with the help of the tool, and lift up tailplane. 3. Unlock and remove connecting pins of the wing extensions and apply the hand force to take the wing extension out of the wingtip.
  • Page 41 a) Check canopy for condition and cleanliness. b) Open the canopy, check if the main pin is installed and locked. c) Make a visual check of all accesible control systems in the cockpit. d) Check for full and free movements of the control elements. e) Check all switches –...
  • Page 42 a) Check airbrakes for free movement and close fit. b) With airbrakes opened, check the airbrake box for the possible water accumulation - water should be removed using a sponge. c) Check flap trailing edges for damage. Lightly shake flaps on the trailing edge to detect unusually large play in the system.
  • Page 43 Check engine door actuating mechanism for proper function. Check throttle control, manual primer (when squeezing rubber bulb, air must be expelled through hole in lid of carburetors) and prop arresting device for proper function. NOTE For prop stop mechanism acting on prop central drive wheel: With the prop arresting device open check that there is a clearance of about 1 mm (0.04 in.) through 2 mm (0.08 in.) between ball bearing and propeller hub.
  • Page 44 d) Check tire pressure 250 kPa in tail wheel. e) Check that the opening for the fuel tank vent line is clear. Check that the fin tank spill holes are clear. g) Check water ballast level in fin tank (in case of doubt, discharge ballast) h) Check that the dump hole for the fin tank in the tail wheel fairing is clear.
  • Page 45 Preflight inspection 4.4.1 Check list before takeoff 1. Water ballast in fin tank? 2. Loading charts checked? 3. Parachute correctly fitted? 4. Safety harness correctly and firmly adjusted? 5. Backrest and pedals locked in comfortable position? 6. All controls and instruments within easy reach? 7.
  • Page 46 Normal procedures and recommended speeds 4.5.1 Aerotow WARNING Only permissible with powerplant retracted! Approved ropes made of synthetic and natural fibers with minimum length from 40 m (131 ft.) may be used for aerotowing. If a nose hook is installed, we recommend to use this one. Nevertheless the C.G.
  • Page 47 the mechanism, therefore slide the control lever slowly and continuously. Should the sailplane be unintentionally displaced laterally, it should be cautiously but immediately steered back to normal aerotow position. Should the sailplane be displaced vertically too high, with a danger of over-flying the tow aircraft, the air brakes should be open. Rope release: Pull the release knob several times to be sure, that the rope was released.
  • Page 48 The high wing loading of this sailplane requires the pilot to abort the take-off and release, if the towing speed drops below 95 km/h (51 kts, 59 mph) (with water ballast 110 km/h (59 kts, 68 mph)). If possible, use small cable chutes to prevent deploying at flat climb angles.
  • Page 49 4.5.3 Launch/engine starting, run up, taxying procedures Extending the powerplant, engine starting WARNING Do not crank the hot engine by hand, the serious injury may occur! 1. Wheel brake Apply 2. Fire valve OPEN 3. Engine Main Switch 4. Engine Unit switch ON (green LED lights in the retracted position) 5.
  • Page 50 Engine run up Advance to full throttle prior to or during the takeoff run – make sure that engine reaches a minimum speed of about 5600 to 5800 RPM and runs smoothly. Be careful using the wheel brake during taxing and before takeoff to avoid nose down tendency.
  • Page 51 4.5.4 Takeoff and climbing Conduct takeoff check, (see Sect. 0) and observe page 5.2.3 (takeoff distances). With a wheel fitted near the tip of the wing, the takeoff run may be commenced “wing down”, otherwise it should be held level by an helper.
  • Page 52 CAUTION If, at high ambient temperatures, the coolant liquid temperature rises too high, the cause may also be the anti-freeze proportion being too much for such temperatures. The effectiveness of coolant liquid with less anti-freeze is significantly better! 4.5.5 Flight Powerplant retracted At a safe altitude, experiment with the air brakes and note loss of height at various speeds.
  • Page 53 The air brakes can be open up to V = 260 km/h (140 KIAS, 161 mph), however this should only be done in an emergency or when unintentionally exceeding the maximum permissible speeds shown in 2.2, which is indicated by a sudden deceleration. For this reason, ensure that your harness is tight, and that you do not unintentionally move or jolt the control column while operating the air brake lever.
  • Page 54 With aft cg position stall warning usually occurs 5 km/h (3-5 KIAS, 3-6 mph) above stalling speed. Stall warning is vibration of the sailplane and can be easily recognized. If the stick is pulled further back, these effects become more pronounced. After reaching the stalling speed the sailplane tends to drop the nose.
  • Page 55 Cruising on own power As clearly shown by the figures of section "Flight Performances", the longest range results from the "sawtooth"-method, which consists of the following flight sections being repeated as required: a climb at a speed of about 95 - 100 km/h, (51 - 54 KIAS, 59 - 62 mph) a glide in "clean"...
  • Page 56 Stopping the engine, retracting the powerplant 1. Throttle lever 20% power for 1 minute (to allow the engine cooling down) 2. Airspeed Reduce to 95 km/h, (51 KIAS, 59 mph) 3. Flaps “+2” 4. Ignition switch 5. Airspeed Maintain, until propeller has stopped 6.
  • Page 57 Extending the prop, starting the engine in flight With the prop extended and engine off, the rate of descent is approx. 2.3 m/s (453 fpm) at a speed of 105 km/h (57 KIAS, 65 mph), resulting in a glide ratio of only about 13:1 – contrary to the best L/D of 52 : 1 in clean configuration (prop retracted).
  • Page 58 NOTE The loss of height from extending the powerplant to the moment the engine is running is about 40 to 50 m (131-164 ft) and the time required for this procedure is approx. 35 - 40 seconds. 4.5.6 Approach and landing Powerplant retracted The normal flap setting for landing is at position “L”.
  • Page 59 CAUTION At weight of 600 kg (1322 lbs) and rear C.G. position, when the side rudder is fully deflected then rudder suction occurs. This phenomenon decrease the rudder control force nevertheless the sideslip can be controlled in the standard manner and does not require special pilot skills.
  • Page 60 4.5.7 Flying with water ballast At average climbing speeds of less than 1,5 m/sec (2,9 kts, 300 ft/min) the use of water ballast does not benefit. This is valid also for flights in tight thermals, which require steep angles of bank. CAUTION Do not add water ballast below 0°C (32 F), because of freezing...
  • Page 61 cockpit must be at closed position. Tanks are equipped with ribs to prevent water pouring in the tanks during turns. CAUTION The water ballast should be emptied before landing. It takes about 4 minutes when the tanks were full. During dumping check if the water is dumped simultaneously from both wings.
  • Page 62 Example If required load is 4 l, than seal holes marked from 0 to 3 l. All excessive water over 4 l will leak through the hole marked 4 l. Drainable tail water ballast tank Drainable tail water ballast tank is located inside of the fin – above the permanent tail water ballast tank, in front of the fin spar.
  • Page 63 Example If required load is 6 l, then seal holes marked from 1 to 5 l. All excessive water over 6 l will leak through the hole marked 6 l. 4.5.8 Cloud flying Cloud flying is prohibited. 4.5.9 High altitude flight CAUTION Keep in mind, that a difference between Indicated Air Speed (IAS) shown by your airspeed indicator and True Air Speed (TAS) is...
  • Page 64 4.5.10 Flight below zero The control system friction may increase when the temperature is below zero degrees of Centigrade, as well as during winter flying. Ensure that all control elements are free of moisture to prevent freezing. This, in particular, applies to the airbrakes. Continuously operate controls and air brakes at short intervals.

  • Page 65: Performance

    SECTION 5 5. Performance Introduction Approved data 5.2.1 Airspeed indicator system calibration 5.2.2 Stall speeds 5.2.3 Takeoff performance 5.2.4 Additional information Non-approved further information 5.3.1 Demonstrated crosswind performance 5.3.2 Flight polar 5.3.3 Range 5.3.4 Noise data Document No.:G304MS/AFM Approved Approved Date of Issue: 07/14...
  • Page 66 Introduction Section 5 provides approved data for airspeed calibration, stall speeds and non-approved further information. The data in the charts has been computed from actual flight tests with the sailplane using average piloting techniques. Approved data 5.2.1 Airspeed indicator system calibration Airspeed indicator system calibration 304S [ km/h ]...
  • Page 67 5.2.2 Stall speeds Air brakes Flaps Takeoff Weight CG position (% MAC) 464 kg 420 kg 427 kg 1023 lbs 926 lbs 941 lbs 46,4% Retracted 75 km/h 65 km/h 66 km/h “L” 40.4 KIAS 35 KIAS 35.6 KIAS 46.6 mph 40.3mph 41 mph 83 km/h...
  • Page 68 5.2.3 Takeoff performance All figures shown below refer to ICAO standard atmosphere and are based on the maximum permitted all-up mass of 600 kg (1322 lb). Total distance over 15m (50 ft) obstacle on dry grass runway: 397 m ( 1302 ft) Lift-off speed approx: 85–90 km/h (46-49 kt, 53-56 mph) Speed over 50 ft obstacle: 100 km/h (54 kt, 62 mph) Climb speed at Vy 100 km/h (54 kt, 62 mph): 2.58 m/s...
  • Page 69 Non-approved further information 5.3.1 Demonstrated crosswind performance During test flights the following takeoff & landing crosswind components were performed. No influence of the weight and CG position combinations to the safe, straight and smooth landing was observed. 420 kg (926 lbs) ....19.3 km/h 5.36 m/s 10.4 kts 600 kg (1322 lbs) ....
  • Page 70 5.3.3 Range a) Values below refer to level flight at cruising power (continuous RPM): Cruising speed approx.: 150 km/h (81 kt, 93 mph) Fuel consumption approx.: 17.00 Liter/h 4.49 US Gal./h 3.74 IMP Gal./h Fuel supplied from level Usable fuel optional optional flight...
  • Page 71 5.3.4 Noise data The noise limit is given in ICAO Annex 16 Chapter 10.4b. The noise limit for a MTOW of 600 kg is 70,8 dB(A). Measured noise level was 64,7 dB(A). Document No.:G304MS/AFM Date of Issue: 07/14...

  • Page 72: Weight And Balance / Equipment List

    SECTION 6 6. Weight and Balance Introduction Weight and Balance Record and permitted payload- range Maximum permitted load of permanent tail water ballast tank Maximum permitted load of wing water ballast tank Maximum permitted load of drainable tail water ballast tank Maximum fuel tank load Document No.:G304MS/AFM Date of Issue: 07/14...
  • Page 73 Introduction This Section contains the payload range within the sailplane may be safely operated. Procedures for weighing the sailplane and the calculation method for establishing the permitted payload range and a comprehensive list of all equipment available for this sailplane and the installed equipment during the weighing of the sailplane are contained in the applicable Maintenance Manual, Document Number G304S/MM.
  • Page 74 Weight and Balance Record and permitted payload-range valid for Serial No.: Permitted cockpit load [kg] or [lbs] Empty Approved weight with without [kg] water ballast water-ballast position ------------- Date behind Fuselage ref. point useful Max. Min. Max. Min. Date Signature [mm] load [kg]...
  • Page 75 Maximum permitted load of permanent tail water ballast tank Permanent tail tank CG position 4215 mm (165.95 in) aft of ref. point Total tank capacity max. 4.5 l (1.19 USGal; 0.99 ImpGal) standard 4.0 l (1.0 USGal; 0.8 ImpGal) Permanent tail water ballast allows to pilot maintain the flight cg position at optimum range.
  • Page 76 Maximum permitted load of wing water ballast tank Max. AUW 600 kg (1322 lbs) Wing tanks CG position 225 mm (8.86 in) aft of ref. point Total tank capacity 194 l (51.25 US Gal, 42.67 Imp. Gal) For filling procedure refer to chapter 4.5.4. Follow the table bellow for setting the maximum permitted load of wing water ballast tanks.
  • Page 77 Maximum permitted load of drainable tail water ballast tank Drainable tail tank CG position 4215 mm (165.95 in) aft of ref. point Total tank capacity 6 l (1.58 US Gal; 1.32 Imp. Gal)) WARNING Drainable tail water ballast may be used only for compensating the pitching moment of the wing water ballast...
  • Page 78 Maximum fuel tank load Fuel tank C.G. position 535 mm (21.1 in) aft of ref. point Total tank capacity 13,5 l (3.57 USGal; 2.97 ImpGal) = 9,7 kg (21.4 lbs) For filling procedure refer to Section 8.7. CAUTION The fuel tank may hold a max. load of 13,5 l (9,7 kg; 21.4 lbs) of the fuel, but must be considered when establishing maximum water ballast.

  • Page 79: Sailplane And Systems Description

    SECTION 7 7. GENERAL SAILPLANE AND SYSTEMS DESCRIPTION Introduction Cockpit controls Instrument panel Landing gear system Seats and safety harness Pitot and static system Airbrake system Baggage compartment Water-ballast system 7.10 Powerplant 7.11 Fuel system 7.12 Electrical system Document No.:G304MS/AFM Date of Issue: 07/14...
  • Page 80 Introduction This Section provides description and operation of the sailplane and its systems. Refer to Section 9, Supplements, for details of optional systems and equipment. Document No.:G304MS/AFM Date of Issue: 07/14...
  • Page 81 Cockpit controls The below listed controls marked by the appropriate placards (refer to 2.15) are installed in the cockpit. More detailed description of some of the systems may be found below. Control column Radio button is mounted on the control column: press to transmit. Wheel brake It is controlled by the airbrake lever, at it’s aft position.
  • Page 82 Flaps Unlock (outwards) grey lever on the left cockpit side, and select flap setting. Flap settings: L: landing position +2: circling in wide thermals +1: circling in narrow thermals and for aero towing 0: best L/D performance (95–140 km/h) -1: normal operation speed (130–180 km/h) -2: hi-speed operation speed (160 km/h –Vne) Keep in mind that the optimum flap setting for given speed is significantly conditioned by current flight weigh.
  • Page 83 Backrest adjustment Backrest position may be adjusted with a black "T" lever on the right cockpit side under the vent slit opening. Rudder pedal adjustment By pulling the black "T" - grip under the instrument panel, the panel adjustment is unlocked. Forward adjustment: Pull black "T"-grip while pushing pedals forward with heels, release grip and let pedals lock into position.
  • Page 84 Instrument panel For safety reasons, only a CFRP panel made in accordance to the lay-up plan specified by the manufacturer may be used. Instruments of more than 1 kg (2.2 lbs) need additional support beyond the screws provided. This can be done by means of aluminum straps fixed to the box in front of the instrument panel.
  • Page 85 7.3.1 Powerplant control unit 1 Display for either engine speed (RPM) and coolant liquid temperature or battery voltage and fuel capacity 2 RPM signals (3 LED) 3 Signal for battery voltage and generator function 4 Powerplant extension / retraction switch 5 Signal for powerplant fully extended 6 Signal for powerplant not fully extended 7 Signal for powerplant fully retracted...
  • Page 86 Landing gear system The sailplane is fitted with a damped retractable main wheel and auxiliary tail wheel. The main landing gear is operated with a black lever located on the cockpit right side. Retract: Unlock handle, pull backwards, then lock. Extend: Unlock, push handle forward and lock.
  • Page 87 Airbrake system The air brakes are controlled with the blue lever located on the left side of the cockpit. Extend: Pull the lever rearward. Retract: Push the lever forward. Baggage compartment The baggage compartment may carry up to 2 kg (4,4 lbs) of baggage.
  • Page 88 1 Engine Fire valve 2 Propeller 10 Fuel tank 3 Li-Ion batteries 11 Fuel installation 4 Linear engine 12 Vertical wall 5 Control sticks 13 Exhaust system 6 Control unit (display unit) 14 Barrier 7 Fuse box, board battery 15 Tube with weak link 8 Relay Retraction Mechanism Main parts:...
  • Page 89 Weak link works like security system, fixing powerplant system in open position and in emergency situations. During powerplant retraction the weak link id inserted into the plastic tube by an elastic cable. Exhaust system is retracted from fuselage contour and is fixed on own frame.
  • Page 90 Refuelling fuel pump This pump is used to fill the main tank with fuel. The pump is operated by the emergency switch, located before powerplant installation in the fuselage. Fire gauge Fire gauge is an mechanical gauge, located between the feed fuel pump and the engine behind an firewall.
  • Page 91 NOTE: For proper function of wing tanks both connection hoses (for each tank) have to be connected. In case of glider de-rigging both wing tanks have to be drained empty. CAUTION Never fill the water ballast into inner tanks if wing fuel tanks contains fuel.
  • Page 92 7.12 Electrical system Main parts: Batteries Wiring Switches Fuses Powerplant control system Batteries The whole system is supplied by three (optionally four) batteries. Battery 2. located on the cabin floor under the instrument panel. It is standard 12V/17-22Ah lead battery (size 181x76x167mm). This battery supplies powerplant unit with accessories and it can be used for supply of instruments too.
  • Page 93 Charging connector: Three poles charging connector is located on the panel with fuses. It is used for charging Pb and Li-Ion batteries. Due to different charging charakteristic of Pb and Li-Ion batteries it is necessary to use correct plug and battery charger. Charging Pb batteries: - use charging plugs marked "Pb"...
  • Page 94 Fuses There are 11 fuses used in the system, placed in the fuses containment in the front part of the cabin and are accessible directly from pilot seat. Document No.:G304MS/AFM 7-15 Date of Issue: 07/14...
  • Page 95 Wiring plan Document No.:G304MS/AFM 7-16 Date of Issue: 07/14...

  • Page 96: Sailplane Handling, Care And Maintenance

    SECTION 8 8. Sailplane handling, care and maintenance Introduction Sailplane inspection periods Sailplane alterations or repairs Powerplant alterations or repairs Ground handling / road transport Cleaning and care Refuelling Document No.:G304MS/AFM Date of Issue: 07/14...
  • Page 97 Introduction This Section contains manufacturer's recommended procedures for proper ground handling and servicing of the powered sailplane. It also identifies certain inspection and maintenance requirements which must be followed if the sailplane is to retain that new-plane performance and dependability. It is wise to follow a planned schedule of lubrication and preventive maintenance based on climatic and flying conditions encountered.
  • Page 98 Ground handling / road transport The sailplane should only be stored or parked in well ventilated areas. Closed trailers should be equipped with sufficiently large ventilation. Always store with empty water tanks. For storage, transport and ground handling keep the powerplant retracted.
  • Page 99 Cleaning and care Wash the surface only with clean water, sponge and chamois. Clean the leaked fuel with dry cloth. CAUTION Never use petrol, alcohol or thinners. Soap additives in water should not be used too often. Polish as often as you wish, but take care not to heat up the surface when using a polishing machine, as otherwise the surface quality will suffer.
  • Page 100 Refueling Refueling is done by an inbuilt fuel pump and special hose with coupling. The connecting point of the refueling system is located on the left side of the language space. The pump is operated by the emergency switch, located the front main wing connection tube. Full tank capacity is 13,5 liters (3.57 US Gal;...
  • Page 101 Wing tanks refueling procedure 1. Connect venting hose. 2. Connect filling hose with external pump and filter. (Figure 8-5) 3. The second end of filling hose place in to fuel container with properly mixed fuel. 4. Turn on the pump. 5.

  • Page 102: Supplements

    SECTION 9 9. Supplements Introduction List of inserted supplements Supplements inserted Document No.:G304MS/AFM Date of Issue: 07/14...
  • Page 103 Introduction List of inserted supplements Date of Doc.No. Title of inserted supplement insertion Document No.:G304MS/AFM Date of Issue: 07/14...
  • Page 104 Supplements inserted Document No.:G304MS/AFM Date of Issue: 07/14...

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