HPH Glasflugel 304 MS Flight Manual Download

Page: 21 / 104

Document No.:G304MS/AFM

Date of Issue: 07/14

2-6

Approved

2.5

Powerplant instruments markings

Powerplant insrtument markings and their colour-code significance
are shown bellow:

Instrument

Normal

Range

Caution

Range

Maximum

Limit

Tachometer
RPM Indicator
[RPM /min]

Signal

Green

Yellow

Red

Range

2500 - 6500 6500 - 6700

over 6700

(RPM

blinking)

Coolant Liquid
Temperature
Indicator
[ºC]

Signal

---

buzzer

Range

40 - 105

---

over 105

(CHT

blinking)

Fuel Quantity
Indicator
[litres]

Signal

---

buzzer

---

Range

13 - 7

6 - 0

(FUEL

blinking)

---

NOTE

Engine values are indicated by the ILEC multi-function powerplant
control unit.

2.6

Weight

Max. takeoff weight .................................... 600 kg

1322 lbs

Max. landing weight .................................... 600 kg

1322 lbs

Max. weight of all non-lifting parts .............. 373 kg

822 lbs

(i.e. all parts incl. cockpit and baggage compartment load, with
water ballast inside the fuselage, trim ballast, stabilizator & elevator)

Maximum weight in baggage compartment ... 2 kg

4,4 lbs

Summary of Contents for Glasflugel 304 MS

Page 1: ...ED D S SA AI IL LP PL LA AN NE E Č Čá ás sl la av vs sk ká á 2 23 34 4 2 28 84 4 0 01 1 K Ku ut tn ná á H Ho or ra a C CZ ZE EC CH H R RE EP PU UB BL LI IC C t te el l 4 42 20 0 3 32 27 7 5 51 12 26 63 33 3 t te el l f fa ax x 4 42 20 0 3 32 27 7 5 51 13 34 44 41 1 info hph cz ...

Page 2: ...ppr are approved by EASA Signature Authority Stamp Original date of approval Approved under Ref No This sailplane is to be operated in compliance with information and limitations contained herein This Flight Manual must be located onboard the sailplane at all times Č Čá ás sl la av vs sk ká á 2 23 34 4 2 28 84 4 0 01 1 K Ku ut tn ná á H Ho or ra a C CZ ZE EC CH H R RE EP PU UB BL LI IC C t te el l...

Page 3: ...able 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 and the date will be shown on the bottom left hand of the page Rev No Affected Section Affected Pages Date of Issue Approval Date of approval Date of Insertion Signature R00 all a...

Page 4: ...7 14 2 11 Appr 07 14 0 3 07 14 2 12 Appr 07 14 0 4 07 14 2 13 Appr 07 14 0 5 07 14 2 14 Appr 07 14 1 1 0 07 14 1 1 07 14 1 2 07 14 3 3 0 Appr 07 14 1 3 07 14 3 1 Appr 07 14 1 4 07 14 3 2 Appr 07 14 1 5 07 14 3 3 Appr 07 14 1 6 07 14 3 4 Appr 07 14 3 5 Appr 07 14 3 6 Appr 07 14 2 2 0 Appr 07 14 2 1 Appr 07 14 2 2 Appr 07 14 2 3 Appr 07 14 2 4 Appr 07 14 2 5 Appr 07 14 2 6 Appr 07 14 2 7 Appr 07 14 ...

Page 5: ...pr 07 14 4 4 Appr 07 14 5 4 07 14 4 5 Appr 07 14 5 5 07 14 4 6 Appr 07 14 5 6 07 14 4 7 Appr 07 14 4 8 Appr 07 14 4 9 Appr 07 14 6 6 0 07 14 4 10 Appr 07 14 6 1 07 14 4 11 Appr 07 14 6 2 07 14 4 12 Appr 07 14 6 3 07 14 4 13 Appr 07 14 6 4 07 14 4 14 Appr 07 14 6 5 07 14 4 15 Appr 07 14 6 6 07 14 4 16 Appr 07 14 4 17 Appr 07 14 4 18 Appr 07 14 4 19 Appr 07 14 4 20 Appr 07 14 4 21 Appr 07 14 4 22 Ap...

Page 6: ...age Date of Issue Section Page Date of Issue 7 7 0 07 14 8 8 0 07 14 7 1 07 14 8 1 07 14 7 2 07 14 8 2 07 14 7 3 07 14 8 3 07 14 7 4 07 14 8 4 07 14 7 5 07 14 7 6 07 14 7 7 07 14 7 8 07 14 7 9 07 14 9 9 0 07 14 7 10 07 14 9 1 07 14 7 11 07 14 9 2 07 14 7 12 07 14 7 13 07 14 7 14 07 14 7 15 07 14 ...

Page 7: ...mitations 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 7 a non approved section Sailplane handling care and maintenance 8 a non approved section Supplements 9 ...

Page 8: ... GH HT T M MA AN NU UA AL L Document No G304MS AFM Date of Issue 07 14 1 0 SECTION 1 1 General 1 1 Introduction 1 2 Certification basis 1 3 Warnings cautions and notes 1 4 Descriptive data 1 5 Three view drawing ...

Page 9: ...S 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 1 2 Certification basis This type of self launching powered sailplane has been approved by EASA in accordance with JAR 22 Amendement 7 1 st September 2003 Type Certificate No Issued on Category of Airworthiness utility Noise...

Page 10: ...anual 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 NOTE Draws the attention of any special item not directly related to safety but which is important or unusual ...

Page 11: ... the Rögger pivot hook The pilot is seated in a semi reclining position The landing gear is retractable and damped A C G release is fitted as standard and an Aerotow nose release can be fitted on request Wing The four piece wing is cantilever and double trapezoidal Removable wing extensions are optional It is constructed as a CFRP Foam Sandwich shell with extruded spar caps of parallel carbon fibe...

Page 12: ...he canopy may be used for ventilation too Battery box barograph tray and a water ballast system are installed Power plant The Glasflügel 304MS is the self launching variant of sailplane model Glasflügel 304S Model 304MS is mostly identical with the 304S model Points of difference are only at the engine compartment fuselage section The Glasflügel 304MS is powered by an liquid cooled 39 kW 53 HP SOL...

Page 13: ...ckpit height 0 83 m 2 72 ft Horizontal Tail Unit Span 2 5 m 6 89 ft Area 0 99 m 2 10 66 ft 2 Aspect ratio 6 33 Vertical Tail Unit Height 1 25 m 3 77 ft Area 1 05 m 2 9 58 ft 2 Aspect ratio 1 52 Landing gear Main wheel 5 00x5 Tail wheel 210x65 Powerplant Engine type SOLO 2625 01 Manufacturer Solo Kleinmotoren GmbH Germany Power at 6250 RPM 39 kW 53 HP Propeller type KS 1G 152 R 122 Manufacturer Tec...

Page 14: ...F FL LI IG GH HT T M MA AN NU UA AL L Document No G304MS AFM Date of Issue 07 14 1 6 1 5 Three view drawing ...

Page 15: ...2 2 Airspeed 2 3 Airspeed indicator markings 2 4 Powerplant fuel and oil 2 5 Powerplant instruments markings 2 6 Weight 2 7 Center of Gravity 2 8 Approved maneuvers 2 9 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 ...

Page 16: ... 1 Approved 2 1 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 ...

Page 17: ...lane may be overstressed by full control movement VFE Maximum speed with flaps 1 2 L 200 160 107 86 124 99 Do not exceed this speeds in any operation and do not use more than 1 3 of control deflection with flaps set on 1 2 L VT Maximum aerotowing speed 150 80 93 Do not exceed this speed during aerotowing VW Maximum winch launching speed 130 70 80 Do not exceed this speed during winch or autotow la...

Page 18: ...is 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 Altitude Never exceed speed vNE IAS m ISA ft ISA km h KIAS mph 0 1000 0 3281 260 260 140 140 161 161 2000 3000 4000 5000 6000 7000 8000 9000 10000 6562 9843 13123 16404 19685 22966 26247 29528 32808 260 260 260 248 234 221 209 197 185 140 1...

Page 19: ...00 45 107 52 124 Allowed range for Flaps set to positive position L white mark and letter at 160 km h 1 2 white mark and letters at 200 km h Green arc 94 200 50 107 58 124 Normal operating range Yellow arc 200 260 107 140 124 161 Maneuvers must be conducted with caution and only in smooth air Red line 260 140 161 Maximum speed for all operation Blue line 100 54 62 Best rate of climb speed vy Yello...

Page 20: ...SL ISA 39 kW 53 HP Max continuous power at 6200 RPM 39 kW 53 HP Maximum permitted coolant liquid temperature 115 C 239 F Fuel Two stroke mixture AVGAS 100 LL or unleaded premium gasoline EN 228 not below RON 95 Oil lubrication Fuel oil mixture mixing proportion for CASTROL Super TT 50 1 2 Propeller manufacturer Technoflug Leichtflugzeugbau GmbH 78713 Schramberg Germany Propeller model KS 1G 152 R ...

Page 21: ...inking Coolant Liquid Temperature Indicator ºC Signal buzzer Range 40 105 over 105 CHT blinking Fuel Quantity Indicator litres Signal buzzer Range 13 7 6 0 FUEL blinking NOTE Engine values are indicated by the ILEC multi function powerplant control unit 2 6 Weight Max takeoff weight 600 kg 1322 lbs Max landing weight 600 kg 1322 lbs Max weight of all non lifting parts 373 kg 822 lbs i e all parts ...

Page 22: ...n the following diagram If the pilot with a parachute does not reach the placarded minimum cockpit load the appropriate amount of lead ballast must be carried in the nose One kg of lead ballast 2 2 lbs in the ballast box will compensate for 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 fr...

Page 23: ...F FL LI IG GH HT T M MA AN NU UA AL L Document No G304MS AFM Date of Issue 07 14 2 8 Approved ...

Page 24: ...VA 200 km h 107 KIAS 124 mph 2 65 air brakes retracted n 4 0 at air speed VNE 260 km h 140 KIAS 161 mph 1 5 air brakes retracted n 2 air brakes extended 2 10 Flight crew Number of seats 1 Minimum cockpit load 70 kg 154 lbs Maximum cockpit load 110 kg 242 lbs WARNING Check permanent tail water ballast trim before flight Exceeding the limitation could cause exceeding of the approved aft cg position ...

Page 25: ... approved type Minimum equipment 1 Airspeed indicator color marked as in par 2 3 1 Altimeter 1 Outside air temperature indicator OAT with sensor when flying with water ballast 1 Magnetic compass 1 Engine control unit indicating RPMs Coolant liquid temperature Fuel quantity Engine time Water pump failure 1 Rear view mirror 1 Set of four point safety harness 1 Automatic or manual parachute otherwise...

Page 26: ...mph Weak link in tow rope max 780 daN Minimum length of tow rope 40 m 130 ft Tow rope material Hemp or Nylon Winch launch powerplant retracted Only permissible with C G tow release in place Maximum launching speed 130 km h 70 KIAS 80 mph Weak link in winch cable max 780 daN WARNING Never use the nose release if installed for winch launching takeoff 2 14 Other limitations No smoking inside the sail...

Page 27: ...F FL LI IG GH HT T M MA AN NU UA AL L Document No G304MS AFM Date of Issue 07 14 2 12 Approved 2 15 Limitations placards MAX 2 kg INCL INSTALLED EQUIPMENT ...

Page 28: ...F FL LI IG GH HT T M MA AN NU UA AL L Document No G304MS AFM Date of Issue 07 14 2 13 Approved ...

Page 29: ...4000 m 13000 ft 260 km h 140 KIAS 161 mph VFE Max SPEED WITH FLAPS setting 1 2 200 km h 107 KIAS 124 mph setting L 160 km h 86 KIAS 99 mph AIRSPEED LIMITATION IAS VPOmax Max pwrplant ext ret speed 120 km h 64 KIAS 74 mph VPOmimMin pwrplant ext ret speed 90 km h 49 KIAS 56 mph VPE Max pwrplant ext speed 180 km h 96 KIAS 111 mph AIRSPEED LIMITATION IAS VA Maneuvering speed 200 km h 107 KIAS 124 mph ...

Page 30: ...NS AND CLOUD FLIGHTS ARE PROHIBITED Altitude Never exceed speed vNE IAS m ft km h KIAS mph 0 1000 0 3281 260 260 140 140 161 161 2000 3000 4000 5000 6000 7000 8000 9000 10000 6562 9843 13123 16404 19685 22966 26247 29528 32808 260 260 260 248 234 221 209 197 185 140 140 140 133 126 119 112 106 99 161 161 161 154 145 137 129 122 114 ...

Page 31: ...iral dive recovery 3 7 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 3 8 Fire 3 8 1 Engine fire on the ground 3 8 2 Engine fire during takeoff 3 8 3 Engine fire during flight 3 9 Other emergencies 3 9 1 Wingtip catching in high grass during takeoff 3 9 2 Towing rope release at low height 3 9 3 Flying w...

Page 32: ...cedures 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 Landing with extended powerplant is not dangerous ...

Page 33: ...ace if time permits 3 Canopy jettison acc to Sect 3 2 4 Release safety harness and spread them aside 5 Bend you legs under the body 6 Roll over the cockpit frame WARNING During bail out try to avoid interfering with the control stick that might result in non expected abrupt sailplane motion 3 4 Stall recovery 1 Push the control stick forward 2 Apply opposite ruder and aileron if necessary 3 After ...

Page 34: ...he rotation stops 6 Neutralize rudder and recover the dive 3 6 Spiral dive recovery 1 Engine Main Switch OFF 2 Balance the bank by coordinate use of rudder and ailerons controls 3 Recover the dive 3 7 Engine failure 3 7 1 Engine failure during takeoff 1 Throttle lever Idle 2 Engine Main Switch OFF 3 Fire valve CLOSE 4 Ignition switch OFF 5 Keep normal gliding speed for given flap setting 6 Straigh...

Page 35: ... of the flight performance 3 7 3 Engine starting in flight without electric starter CAUTION Before starting carry out Section 3 7 2 Engine Failure during Flight 1 Follow the normal checklist until the item Depress starter button 2 Throttle lever Idle 3 Flaps 0 4 Airspeed Accelerate to 160 km h 86 KIAS 100 mph so that the engine revs will quickly build up with an audible prop noise 5 Reduce speed t...

Page 36: ...ire valve CLOSE 3 Engine Main Switch OFF 4 Ignition switch OFF 5 Sailplane Evacuate 3 8 3 Engine fire during flight 1 Fire valve CLOSE 2 Throttle lever Full open 3 Engine Main Switch OFF 4 Ignition switch OFF 6 Airspeed Maintain min 94 km h 50 KIAS 58 mph 7 Emergency landing Carry out 8 Sailplane Evacuate 9 In the case of dangerous situation Bail out WARNING Discontinue flight and land immediately...

Page 37: ...vel flight the speed increases up to 15 with water ballast In a turn the speed should be increased according to the angle of bank In this manner the unintentional and unnoticed stalled flight will be avoided 3 9 3 Flying with uneven water ballast If on dumping water ballast the wing tanks are emptying unevenly or only on one side which is recognized at lower speeds by having to apply opposite aile...

Page 38: ...flight inspection 4 4 1 Check list before takeoff 4 4 2 Check list for self launching 4 5 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 Flight 4 5 6 Approach and landing 4 5 7 Flying with water ballast 4 5 8 Cloud flying 4 5 9 High altitude flight 4 5 10 Flight below zero 4 5 11 Flig...

Page 39: ... that the bellcranks on the root rib are in their neutral position and are actually engaging into the opposing socket fittings on the fuselage 4 Rig right wing with the same lever settings as left wing and push firmly together Ensure correct engagement of control as with left wing 5 Push the main pin fully home and lock 6 Rig both wing extensions Inset the rigging handle and turn clockwise until t...

Page 40: ...pin 5 Gently pull on the wingtips to separate each wing from the fuselage one at a time 4 3 Daily inspection Daily inspection should be performed before each flight day opening both after rigging the sailplane and parking in a hangar When inspecting the sailplane check for cracks in surface finish blisters or uneven surface and if in doubt check with authorized specialized personnel When inspectin...

Page 41: ...ck main landing gear for condition check tire pressure of main wheel Takeoff weight kg Main wheel pressure kPa 380 350 450 400 600 500 j Check function of tow release condition and spacing of cable deflector plates 2 a Check upper and lower wing surfaces for damage b Check condition and attachment of the wing wheel c Check aileron for full and free movement d Check aileron tip rib for damage e Che...

Page 42: ...Check if the holes for static pressure on the fuselage shell are clear Visual inspection of the powerplant WARNING Ignition to be switched off c Check the engine bay for foreign material and leaked fuel d Check fuel quantity e Check wing tank feed and vent hose connection if wing tank installed f Check propeller pylon during extension for sufficient clearance to the rim of the engine compartment g...

Page 43: ... seating n Check drive belt for wear o Rotate propeller by hand repeatedly and listen for abnormal noise Check for engine binding p Depress fuel drain at the bottom of the fuselage aft of the landing gear and discharge condensed water Check that the drain outlet is clear q Check function of water pump with ignition ON Check pump plug and hoses for proper attachment r Check coolant liquid quantity ...

Page 44: ...m 3 8 Refer to item 2 9 a Check fuselage front part for damage b Check the function of the nose release mechanism if installed NOTE After a hard landing or excessively high G loads the bending frequency of the wings must be checked and the sailplane carefully examined for any indications of damage acc to Maintenance manual instructions Dismantle the sailplane and check surface finish for cracks Lo...

Page 45: ... position 6 All controls and instruments within easy reach 7 Airbrakes locked 8 Control check Free full and correct movements of controls 9 Correct trim position 10 Canopy locked 11 Release check 12 Towline on correct release correct weak link 13 Flaps set for takeoff 14 Set Altimeter 4 4 2 Check list for self launching 1 Fuel quantity checked 2 Function of water pump checked NO flashing red signa...

Page 46: ...ap setting during aerotow 1 At rear C G positions the control stick should be pushed to lift the tail unit With rear C G position high take off weight or strong cross wind commence the takeoff run with flap setting 2 or 1 until sufficient aileron control is available Then move flap setting back to takeoff position 1 or 2 considerably below lift off speed in order to prevent ballooning After lift o...

Page 47: ...ching Winch tow must only be attempted on the C G release Before take off the trim is set to normal for forward and medium C G positions and nose heavy for medium to rear C G positions Flap setting for launching 1 When commencing the take off run use wheel brake slightly to prevent rolling over tow rope This sailplane shows normal behavior during winch tow and even with rear C G positions has only...

Page 48: ...um towing height the cable will back release automatically however you should not neglect to pull the release knob several times WARNING The low performance winches with limited engine RPM and other limitations as well as the takeoff at the tail wind conditions calm air filled water tanks etc require special attention before take off to ensure that the winch is providing enough power in reserve to...

Page 49: ...ion 6 Prop Stop lever Full forward 7 Ignition switch ON 8 Throttle lever open 9 Primer Actuate 3 times by squeezing rubber bulb if engine is cold 10 Space around propeller Check free 11 Control stick Fully back tail wheel down 12 Starter button Depress until engine has definitely fired 13 Engine parameters Check NOTE Release starter button as soon as engine has definitely fired and adjust throttle...

Page 50: ...ing With a wheel fitted near the tip of the wing taxiing wing down is easily conducted flaps to be set at 0 or 1 otherwise a helper is required For taxiing the control stick should be kept fully back The wheel brake is actuated when airbrake lever is nearly fully deployed For taxiing wing down it is recommended to conduct larger directional changes such that the dragging wing is on the inside of t...

Page 51: ...il wheel down 4 Throttle lever Smoothly full open 5 Flaps 1 on reaching a speed of about 85 km h 45 KIAS 52 mph 6 Control stick Ease forward keeping the tail wheel down wheel on the ground 7 Lift off At 85 90 km h 46 49 kt 53 56 mph if flap setting L was used reset at 1 8 Climbing Up to 100 km h 54 KIAS 62 mph 9 Engine parameters Check The initial climb up to a safe height may be conducted with RP...

Page 52: ...nd 2 3 for the Airspeed limits and Airspeed Indicator Marking Aileron and rudder full deflections may be applied up to the Maneuvering speed Full control deflections of aileron and rudder are allowable up to VA 200 km h IAS 107 KIAS 124 mph Only 1 3 of the aileron and rudder full deflections may be used at Never exceed speed VNE 260 km h IAS 140 KIAS 161 mph Elevator deflections must be limited as...

Page 53: ...recovery from dives with airbrakes employed should be more gentle than with airbrakes deployed see Ch 2 7 load factors Slow speed flight stall characteristics For familiarization with Glasflügel 304 MS sailplane we recommend to perform stalling tests from a straight and level flight and from a turn of 45 bank The tests should be done of course at a safe altitude Refer to Section 5 par 5 2 2 for th...

Page 54: ...llability is adequate right up to the point where the longitudinal control reaches its rear stop With the elevator fully deflected the angle of attack cannot be increased any more The sailplane continues to fly in straight flight with increased rate of descent This situation shows up by spongy controls Slip and bank can be controlled If the stick is eased firmly forward than the stall is terminate...

Page 55: ...umed in glide should not be less than 500 m 1640 ft The maximum range in glide is achieved at a speed of about 120 km h 64 KIAS 74 mph resulting in an average speed of about 110 km h 59 KIAS 68 mph Should the sawtooth method be impracticable due to low cloud ceiling or because of airspace restrictions then cruising in level flight at a speed of about 150 km h 80 KIAS 88 mph is also possible The ra...

Page 56: ...km h 51 54 KIAS 59 62 mph to rotate the engine until propeller is vertical 14 Powerplant extend DOWN green LED lights in the switch retracted position 8 Engine Unit switch OFF 9 Engine Main Switch ON 10 Prop Stop lever Full forward 11 Wing tank valve OFF CAUTION Through the mirror observe the powerplant retracting to check that the propeller remains vertical and does not rotate NOTE The powerplant...

Page 57: ...uitable landing field is safer then e g restarting it at 500 m 1640 ft AGL above a forest or the like Should a flight be planned over long distance without any acceptable landing fields the prop should be extended at a height giving sufficient time for all emergency procedures and if necessary for re retracting the propeller Starting procedure 1 Airspeed Maintain to 100 km h 54 KIAS 62 mph 2 Fire ...

Page 58: ...s Minimal approach speed is 85 km h 45 KIAS 52 mph For better aileron control during strong turbulence the approach can be made with flap setting 2 or 1 at speed between 100 and 110km h 53 59 KIAS 62 68 mph The approach speeds have to be increased of approx 20 at the landing weight of 600 kg 1322 lbs Immediately before touch down the air brakes should be always open fully Sideslip is suitable for ...

Page 59: ... With powerplant extended the sailplane can be landed in the same manner as in clean configuration powerplant retracted Approach speed 100 km h 62 mph 54 KIAS mph without waterballast 115 km h 72 mph 62KIAS mph with waterballast On approach however it must be taken into account that the flight performance has deteriorated due to the extended powerplant The reduced performance however requires sign...

Page 60: ...illing water must be avoided Before water ballast is added check the table in section 6 4 for the maximum weight of water ballast The total capacity of the wing tanks is 194 liters aprox 42 UKgal 51 USgal Let the actuating lever in closed position fill through the openings at the upper wing surface CAUTION As the holes in the filler cap also serves for venting the tank it must always be kept open ...

Page 61: ...anent tail water ballast tank is 4 0 liters aprox 0 9 UKgal 1 0 USgal Permanent tail water ballast allows to pilot maintain the flight C G position at optimum range It could be used either for flights with or without wing water ballast Adding this ballast limits the minimum pilot s weight Filling hose is located under the elevator lid on the left side of the side rudder This filling hose could be ...

Page 62: ...th wing water ballast Filling hose is located under the elevator lid on the right side of the side rudder This filling hose could be connected with the appropriate filling can by tube of max outer diameter 6 mm 0 234 in CAUTION Tank must not be pressurized e g fill directly from the water hose The tank has six 6 spill holes on the port side all properly marked from 1 to 6 l according to the ballas...

Page 63: ...ed 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 Altitude Never exceed speed vNE IAS m ISA ft ISA km h KIAS mph 0 1000 0 3281 260 260 140 140 161 161 2000 3000 4000 5000 6000 7000 8000...

Page 64: ...trols and air brakes at short intervals During flights with water ballast note the recommendation under 4 5 7 4 5 11 Flight in rain Although no degradation of the flight behavior requiring special pilot skills during flight at rain was reported rain drops frost and ice impair the aerodynamic qualities and also alter the flying behavior Therefore in such conditions the quoted minimum speeds for str...

Page 65: ...rmance 5 1 Introduction 5 2 Approved data 5 2 1 Airspeed indicator system calibration 5 2 2 Stall speeds 5 2 3 Takeoff performance 5 2 4 Additional information 5 3 Non approved further information 5 3 1 Demonstrated crosswind performance 5 3 2 Flight polar 5 3 3 Range 5 3 4 Noise data Approved Approved ...

Page 66: ...peeds and non approved further information The data in the charts has been computed from actual flight tests with the sailplane using average piloting techniques 5 2 Approved data 5 2 1 Airspeed indicator system calibration Airspeed indicator system calibration 304S 60 80 100 120 140 160 180 200 220 240 60 80 100 120 140 160 180 200 220 240 CAS km h IAS km h Approved ...

Page 67: ...8 km h 42 1 KIAS 48 4 mph 70 km h 37 7 KIAS 43 4 mph Extended L 80 km h 43 1 KIAS 49 7 mph 70 km h 37 7 KIAS 43 4 mph 72 km h 38 8 KIAS 44 7 mph Air brakes Flaps Takeoff Weight CG position MAC 600 kg 1322 lbs 27 594 kg 1309 lbs 37 600 kg 1322 lbs 46 5 Retracted L 78 km h 42 1 KIAS 48 4 mph 78 km h 42 1 KIAS 48 4 mph 77 km h 41 5 KIAS 47 8 mph 0 92 km h 49 6 KIAS 57 1 mph 91 km h 49 1 KIAS 56 5 mph...

Page 68: ...ver 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 Shown performance data may vary according to local meteorological conditions crosswind temperature field elevation and wing loading WARNING Wet and or soft ground lengthens the take off distance...

Page 69: ...S 31 3 kg m2 m 370 kg m S 50 8 kg m2 m 600 kg 5 3 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 16 5 km h 4 58 m s 8 9...

Page 70: ...k 13 3 43 2 86 x 0 76 114 km 61 nm 24 2 91 2 42 x x 1 41 211 km 113 nm 35 2 91 2 42 x x x 2 01 300 km 162 nm b The following values are based on the sawtooth method see page 4 5 3 at an all up mass of 530 kg 1169 lb and the climb effected at max power Average cruising speed approx 110 km h 59 KIAS 68 mph Fuel consumption approx 21 50 Liter h 5 68 US Gal h 4 73 IMP Gal h Usable fuel Fuel supplied f...

Page 71: ... MA AN NU UA AL L Document No G304MS AFM Date of Issue 07 14 5 6 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 ...

Page 72: ...ight and Balance 6 1 Introduction 6 2 Weight and Balance Record and permitted payload range 6 3 Maximum permitted load of permanent tail water ballast tank 6 4 Maximum permitted load of wing water ballast tank 6 5 Maximum permitted load of drainable tail water ballast tank 6 5 Maximum fuel tank load ...

Page 73: ...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: ...range valid for Serial No Date Empty weight kg Fuselage useful load kg CG position behind ref point mm Permitted cockpit load kg or lbs Approved with water ballast without water ballast Max Min Max Min Date Signature Refer to Operating Maintenance and Repair Manual Document Number G304S MM for minimum and maximum pilot weight calculation ...

Page 75: ... weight For filling procedure refer to chapter 4 5 4 Exceeding the maximum permitted useful load of the fuselage stated at table 6 2 must be avoided Follow the table bellow for setting the maximum permitted load of permanent tail water ballast tank Minimum pilot seat load pilot parachute kg Permanent tail water ballast l Date 0 1 2 3 4 4 5 WARNING Check permanent water ballast tank load before eac...

Page 76: ... Check if the max AUW 600 kg will not be exceeded for loading according to the white marked fields Example Empty weight 330 kg Weight of pilot and parachute 125 kg Maximum permanent tail water ballast 4 5 l Luggage compartment load 2 kg Wing ballast 134 2 132kg Max drainable tail water ballast 6 kg see ch 6 5 AUW 330 125 4 5 2 132 6 599 5 kg 600 kg see tab 2 4 Fuselage useful load 125 4 5 2 6 137 ...

Page 77: ... chapter 4 5 4 Exceeding the maximum permitted useful load of the fuselage stated at table 6 2 must be avoided Follow the table bellow for setting the maximum permitted load of drainable tail water ballast tank Min wing water ballast load l 194 190 160 130 100 80 60 40 20 0 0 1 2 3 4 5 6 Max drainable tail waterballast load l Example Empty weight 330 kg Weight of pilot and parachute 75 kg Maximum ...

Page 78: ...max AUW 600 kg 1322 lbs will not be exceeded for loading according to the white marked fields Left Wing fuel tank optional CG position 225 mm 8 86 in aft of ref point Total tank capacity 11 l 2 9 US Gal 2 42 Imp Gal Right Wing fuel tank optional CG position 225 mm 8 86 in aft of ref point Total tank capacity 11 l 2 9 US Gal 2 42 Imp Gal For filling procedure refer to chapter 8 7 NOTE For proper fu...

Page 79: ...RAL SAILPLANE AND SYSTEMS DESCRIPTION 7 1 Introduction 7 2 Cockpit controls 7 3 Instrument panel 7 4 Landing gear system 7 5 Seats and safety harness 7 6 Pitot and static system 7 7 Airbrake system 7 8 Baggage compartment 7 9 Water ballast system 7 10 Powerplant 7 11 Fuel system 7 12 Electrical system ...

Page 80: ... UA AL L Document No G304MS AFM Date of Issue 07 14 7 1 7 1 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 ...

Page 81: ...it Wheel brake It is controlled by the airbrake lever at it s aft position Tow release The yellow grip under the left side of the instrument panel is activating both releases Air brakes Air brakes are operated by a blue lever located on the left side of the cockpit Extend Unlock inwards blue lever on the left cockpit side and pull towards the rear Retract Push lever forward and lock Trim lever Is ...

Page 82: ...it frame serve for the canopy opening closing Closing Handle the canopy frame pull it downward and push white grips forward until they snap Opening Pull both white grips rearward and push canopy frame upward Cockpit ventilation Cockpit ventilation is consists of valve at the sailplane nose It is controlled by the wheel located at the slit opening on the right side of the cockpit Steer the wheel up...

Page 83: ...l pedals back with black grip Propeller arresting device Propeller arresting device is operated by a red lever located on the left side of the cockpit Lever at forward position Arresting device released Lever in rearward position Arresting device applied Throttle control Throttle control is operated by a black lever located on the left side of the cockpit Lever at forward position Full throttle Le...

Page 84: ... 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 Equipment with operating controls must be fitted conveniently within reach when the pilot is secured in the seat safely Flight monitoring instruments like ASI and altimeter must be mounted within the pilots field of view from which the ASI shoul...

Page 85: ...erature 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 8 Display selector button fuel entry 9 Ignition switch 10 Test switch for ignition circuit 1 and 2 ...

Page 86: ...onal parking brake could be installed 7 5 Seats and safety harness The sailplane is fitted with an adjustable backrest as well as headrest The backrest position may be adjusted with a black T lever on the right cockpit side To adjust the backrest position Release the lever release weight on the backrest and move your body forward the backrest moves forward To adjust the headrest Lift the locking b...

Page 87: ... integral water ballast tanks in wing can carry up to 194 liters approx 42 UKgal 51 USgal 7 10 Powerplant The powerplant system consists of these main parts SOLO 2625 01 Technoflug propeller retraction mechanism engine bay door operation mechanism electro installation battery wiring safety circuits control and display units fuel system fuel tanks refueling system and fuel feed system The engine is...

Page 88: ...llation 12 Vertical wall 13 Exhaust system 14 Barrier 15 Tube with weak link Retraction Mechanism Main parts Electrical linear engine Driving components Actuated components Tube with weak link Exhaust system The mechanism is driven by electrical linear engine The electrical linear engine is maintenance free water chemicals and dust resistant It is operated electrically by 12VDC The system is self ...

Page 89: ... door The door is operating on pure mechanical principles without any operating elements The main door has two pieces This door remains open when the engine is operating The engine retraction has these phases door open engine out 7 11 Fuel system Main parts Fuel tank Feed pump Refuelling pump Fire gauge Tank ventilation Fuel tank There is one fuel tank in the fuselage of total capacity 13 5 l Feed...

Page 90: ...ilation The tanks are ventilated to the top fuselage surface Fuel leakage may occur at this point if the fuel tank is full Wing tanks Wing tanks may be optionally installed in inner part of both wings These tanks are made of elastic plastic material Each tank capacity is 11 liters of fuel Wing tank connection with main fuel system is provided by two hoses One hose serves for connection with main t...

Page 91: ...14 7 12 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 Fuel system scheme ...

Page 92: ... latch release Battery 1 can be installed optionally is used for all board instruments except engine control unit It is placed ahead of rudder pedals Battery 1 is standard 12V 12 15Ah lead battery size 150x97x93mm Two packs of Li Ion batteries are located behind the pilot s head These supplies energy only to linear drive of extension mechanism and engine starter Alternator charges battery 2 in pow...

Page 93: ...atteries all main switches are switched off choose BATT 1 or BATT 2 on the battery switch connect charging plug and switch on a battery charger Charging Li Ion batteries use charging plugs marked Li Ion with battery charger suitable for Li Ion batteries all main switches are switched off connect charging plug and switch on a battery charger WARNING NEVER CHARGE BOTH TYPE OF BATTERIES AT ONE TIME W...

Page 94: ...T M MA AN NU UA AL L Document No G304MS AFM Date of Issue 07 14 7 15 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 ...

Page 95: ...F FL LI IG GH HT T M MA AN NU UA AL L Document No G304MS AFM Date of Issue 07 14 7 16 Wiring plan ...

Page 96: ...of Issue 07 14 8 0 SECTION 8 8 Sailplane handling care and maintenance 8 1 Introduction 8 2 Sailplane inspection periods 8 3 Sailplane alterations or repairs 8 4 Powerplant alterations or repairs 8 5 Ground handling road transport 8 6 Cleaning and care 8 7 Refuelling ...

Page 97: ...ing conditions encountered 8 2 Sailplane inspection periods Refer to the Operating Maintenance and Repair Manual Document Number G304S MM for more information on the sailplane periodical inspections 8 3 Sailplane alterations or repairs It is essential that the responsible airworthiness Authority be contacted prior to any alterations on the sailplane to ensure that the airworthiness of the sailplan...

Page 98: ...correctly stored in a wide fuselage molding in front of the C G release and supported by the tail wheel The Tailplane is stored in two profile true slings separated 1 5 2 m 5 6 6 ft and with the L E pointing downward Under no circumstances attach the tailplane into the trailer by using the tailplane main attachment fittings Sailplanes which stay rigged for the whole year or longer periods should b...

Page 99: ...ten 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 Exposure to moisture should be avoided as with all other sailplanes Protect from intensive sun radiation heat and unnecessary permanent load Please note that the surface of all parts which are exposed to sun radiation must be colored white Colors othe...

Page 100: ...k capacity is 13 5 liters 3 57 US Gal 2 97 Imp Gal Refueling procedure 1 Plug the refueling hose to the coupling and the free end to the canister 2 Plug the vent pipe to the vent outlet and the free end to the canister 3 Press ON 4 To stop the refueling process press OFF 5 When the tanks are full the fuel starts escaping through the vent pipe Shut the pump off immediately WARNING Use AVGAS 100 LL ...

Page 101: ... 5 3 The second end of filling hose place in to fuel container with properly mixed fuel 4 Turn on the pump 5 Wing tank is full when fuel starts flow through venting hose 6 Turn off the pump 7 Disconnect filling hose 8 Connect main tank connection hose 9 Repeat procedure for second wing tank NOTE Wing tanks can be drained reverse the pump Turn on fuel pump with reverse polarity Fig 8 5 Refueling ho...

Page 102: ...F FL LI IG GH HT T M MA AN NU UA AL L Document No G304MS AFM Date of Issue 07 14 9 0 SECTION 9 9 Supplements 9 1 Introduction 9 2 List of inserted supplements 9 3 Supplements inserted ...

Page 103: ...F FL LI IG GH HT T M MA AN NU UA AL L Document No G304MS AFM Date of Issue 07 14 9 1 9 1 Introduction 9 2 List of inserted supplements Date of insertion Doc No Title of inserted supplement ...

Page 104: ...F FL LI IG GH HT T M MA AN NU UA AL L Document No G304MS AFM Date of Issue 07 14 9 2 9 3 Supplements inserted ...

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HPH Glasflugel 304 MS, Flight Manual

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