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Flight manual

Storch Classic Jabiru

Rev. 0 – 07/2002

Pag. 25

FAST DESCENT

a.

Throttle

- at minimum

b.

Engine

- inside limits

c.

Flaps

- retracted

d.

Speed

- inside limits

NOTE: in hard wind condition or in wind-shear condition do not descend approach speed
more Than 10 km/h, (5 knots).

NOTE: when learning do not practice overshoot under 30m (100 ft)

In case of

TOUCH AND GO

-

Flaps

- take-off position

-

Same as take-off procedure

AFTER TOUCH-DOWN

a.

Throttle

- at minimum

b.

Flaps

- up

c.

Let free the runway

d.

Brakes

-

ENGINE SHUTDOWN

a.

Throttle

- at minimum

b.

Parking brakes

- engaged

c.

Electric Pump

- OFF

d.

Avionics

- OFF

e.

Magnetos

- OFF (one after the other)

f.

Contact

- OFF

FLYING IN RAINY CONDITIONS

NOTE: during a flight in rainy conditions the airplane performances are reduced, and also
the visibility. Flying in heavy rain must be avoided.

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Содержание STORCH CLASSIC

Страница 1: ...TWO SEATERS ULTRALIGHT AIRCRAFT STORCH CLASSIC ENGINE JABIRU 2200 FLIGHT MANUAL REV 0 ...

Страница 2: ...DITION TO THE AIRCRAFT LIMITATIONS REPORTED IN THIS MANUAL ALL THESE INFORMATION ARE NECESSARY FOR SAFE OPERATION OF THE AIRCRAFT THE FOLLOWING IS THE DATA SHEET FOR THIS PARTICULAR AIRCRAFT AIRCRAFT STORCH MODEL CL ENGINE TYPE JABIRU 2200 BUILDER FLY SYNTHESIS S R L EDITION JULY 2002 AIRCRAFT DATA SERIAL NUMBER DATE OF MANUFACTURE EMPTY WEIGHT TESTED KG FUEL WEIGHT WITH LIT KG ALLOWED WEIGHT FOR ...

Страница 3: ...VISIONS All the revisions to this manual excluding data concerning weight and load tests must be registered in the following table and in case of approved sections signed and stamped from CAAI Rev Nr Chapter Pages affected Date Approval Date Date of modify Signature ...

Страница 4: ...Flight manual Storch Classic Jabiru Rev 0 07 2002 Pag 4 LOG OF PAGES Chapter Pages Date Chapter Pages Date ...

Страница 5: ...cy Procedures Limitations Flight performances Adherence to these procedures is MANDATORY for the aircraft operator FLY SYNTHESIS Srl is not responsible for any damage or injury due to a total or partial non observance of directions procedures stated in this Flight Manual FLY SYNTHESIS Srl reserves all rights to the property of this Manual which can neither be reproduced partially nor integrally th...

Страница 6: ...ND DYNAMIC PORT 12 2 TECHNICAL DATA 13 DIMENSION 13 OVERALL DIMENSION 13 WING 13 AILERON 13 STABILATOR 13 HORIZONTAL TRIM 13 VERTICAL FIN RUDDER INCLUDED 13 RUDDER 13 WEIGHTS 13 LANDING GEAR 14 FUEL SYSTEM 14 ELECTRICAL SYSTEM 14 POWER PLANT 14 PERFORMANCE WITH JABIRU 2200 ENGINE 15 DIFFERENT USEFUL DIMENSION 15 GRAVITY CENTER POSITIONING 15 AIRCRAFT LIST OF PARTS 18 COCKPIT LIST OF PARTS 19 3 ROU...

Страница 7: ...NAL EMERGENCY LANDING 29 FIRE ON THE GROUND AND DURING STARTING PROCEDURE 29 FIRE DURING FLIGHT 29 FIRE IN FLIGHT DUE TO AN ELECTRICAL FAILL WITH SMOKE 30 FIRE ON THE GROUND DUE TO AN ELECTRICAL FAIL WITH SMOKE 30 FIRE IN THE COCKPIT DURING FLIGHT 30 NON INTENTIONAL FLIGHT IN ICING CONDITIONS 30 SPIN RECOVERY 30 LANDING WITH A FLAT TIRE 31 LANDING WITH BRAKE FAILURE 31 GLIDE 31 ELECTRIC PLANT FAIL...

Страница 8: ...est glide ratio 34 fig 7 ROLL DISTANCE TAKE OFF DISTANCE 35 fig 8 LANDING RUN LANDING DISTANCE 36 fig 9 RELATIVE WIND DIAGRAM VERSUS WIND COMPONENT 37 fig 10 MAX RATE OF CLIMB DIAGRAM AT MAXIMUM RPM 38 fig 11 FLIGHT ENVELOPE 39 FIG 12 CONVERSION TABLE KILOMETERS HOUR km h KNOTS 43 fig 13 CONVERSION TABLE KNOTS knots METERS SECONDS m sec 43 fig 14 VERTICAL SPEED m sec feet min 44 fig 15 AIR CORRECT...

Страница 9: ...e belly of the fuselage through a welded tube structure and the bending element consists of two milled bars of light alloy LANDING GEAR The landing gear has a fixed tricycle configuration where the main part is mounted on two Self suspension high resistance aluminum entering of the lower part of the fuselage fixed inside connected by tube The front part is a light metal suspension fork independent...

Страница 10: ...on to which are fastened the metal wing ribs The Material Used Is aerospace Aluminum alloy The skin is riveted to the structure The aileron is built with the same principle as the wing to which it is connected through pods fastened to the ribs The wind bracing consists of metal structural elements of drop shaped cross section to increase the streamlining The wing and fuselage are connected to each...

Страница 11: ...IC REFUELING PUMP The electric pump is provided for tank refueling procedure FUEL SWITCHES The fuel switches are positioned between seats frontward at the central console WARNING The fuel tab must be in closed position in case of emergency landing during engine fire and during fuel plant inspection Always check before each flight that the position is open to avoid engine failure during take of ELE...

Страница 12: ...ng but the magnetos and the main switch is in the on position it is prohibited to turn the propeller manually This can start the engine with heavy consequences for person in the propeller area STATIC AND DYNAMIC PORT The total pressure intake is located on the tip of the right wing and is calibrated The static pressure is registered by the same pitot who has small lateral holes not disturbed by th...

Страница 13: ...With max forward trim position and stabilator max up and max down Travel 20 32 With max backward trim position and stabilator max up and max down VERTICAL FIN RUDDER INCLUDED Area 0 96 m2 Height 1 28 m Medium chord 0 93 m RUDDER Area 0 59 m2 Height 1 20 m Average chord 0 48 m Travel 22 Note angles are taken considering angle of top fuselage flange where windows are attached of 3 towards front side...

Страница 14: ...ced before mechanical and electrical pump Tank capacity 2 x 30 lt Not usable fuel 2 lt ELECTRICAL SYSTEM Type Independent circuit for magnetos ground 12 Volts Main circuit for instruments and battery generator link Rectifier with Voltage regulator Fuses on Main and auxiliary circuits Battery 12 Volts POWER PLANT Engine Jabiru 2200 4 Strokes Displacement 2200 cm3 Cylinder 4 Opposite cylinders Ignit...

Страница 15: ...d at 75 power 2350 rpm 124 km h 67 0 Kts Cruise speed at 2800 rpm 151 km h 81 5 Kts Cruise speed inside turbulence 145 km h 78 3 Kts Best glide ratio speed 110 km h 0 flap 59 4 Kts 0 flap Best glide ratio speed 89 km h 1 flap 48 1 Kts 1 flap Maneuvering Speed Va 130 km h 70 2 Kts Speed never exceed Vne 180 km h 97 2 Kts Take off run a s l ISA at Max weight 90 m 295 feet Landing run a s l ISA at Ma...

Страница 16: ...Flight manual Storch Classic Jabiru Rev 0 07 2002 Pag 16 fig 1 triptych STORCH CL MODEL 3 views ...

Страница 17: ...Flight manual Storch Classic Jabiru Rev 0 07 2002 Pag 17 fig 2 Sketch of Storch part list first part FIG 3 Sketch of Storch part list second part ...

Страница 18: ...n 8 Push pull wires for rudder and stabilator flight control 9 Aileron flight control rod inside cabin 10 Left rudder pedal 11 Steering wheel control rods 12 Right rudder pedal 13 Stick lever 14 Right wing tank 15 Refueling place 16 Battery 17 Left wing tank 18 Ballistic parachute 19 Main landing gear 20 Cockpit air intake 21 Engine cowling 22 Fuel draining 23 Front wheel 24 Engine 25 Propeller 26...

Страница 19: ...COCKPIT LIST OF PARTS 1 Wing frame 2 Parachute handle accessory 3 Trim handle 4 Flap handle located on ceiling back side of cabin 5 Instrument panel 6 Cabin strut 7 Right brake lever 8 Choke 9 Seat 10 Right fuel valve 11 Left fuel valve 12 Throttle lever 13 Left brake lever 14 Control lever 15 Rudder pedal ...

Страница 20: ...king place to avoid that condense water present on tank bottom emulsify with fuel Check for water presence in tank In that case repeat fuel drain operation REFUELLING CAUTION use only type of gasoline as stated in engine manual Refueling must be done using electrical pump switched on inside cockpit PRE FLIGHT INSPECTION Warning All checks in this section should be carried out BEFORE EACH FLIGHT ev...

Страница 21: ...fects b Door and related attachments clean well fixed and without defects EMPENNAGE a External surface clean and without defects b Control surface movements without friction and No clearance c Trim without defects and no clearance d Stabilator hinge without defects and no clearance e Flying controls smoothness and no clearance f Balance weight well fixed FUSELAGE RIGHT SIDE a External surface clea...

Страница 22: ...lean well fixed and with no defects i Alignment pedals centered rudder aligned with nose COCKPIT a Ship s papers check due date b Check list on board c Parking brake on d Key not set in e Doors and windshield clean and with no defects f Fuel level gauge check fuel level g Gas throttle at the minimum position h Control sticks free movement with no friction i Flap control if installed check movement...

Страница 23: ...for 15 30 sec Warm engine OFF completely forward f Ensure that the propeller area is clear of any persons and objects g Ignition magneto ON h Push button START max 5 sec For each attempt i Fuel throttle medium position h Engine oil pressure inside limits j Generator pilot lamp OFF k Fuel pressure inside limits l Fuel pump ON m Head temperature inside limits n Oil temperature inside limits o Check ...

Страница 24: ...ntain direction NOTE with side component wind it may occurs to act on one of the brake levers to maintain direction This will result in a longer take off distance NOTE do not maintain extended flaps for any reason when the speed excess limits NOTE the best rate of climb decreases by increasing the angle of climb CRUISING a Flaps up b Throttle settled c Engine inside limits d Trim settled ATTENTION...

Страница 25: ...ce overshoot under 30m 100 ft In case of TOUCH AND GO Flaps take off position Same as take off procedure AFTER TOUCH DOWN a Throttle at minimum b Flaps up c Let free the runway d Brakes ENGINE SHUTDOWN a Throttle at minimum b Parking brakes engaged c Electric Pump OFF d Avionics OFF e Magnetos OFF one after the other f Contact OFF FLYING IN RAINY CONDITIONS NOTE during a flight in rainy conditions...

Страница 26: ...thorized take off weight is exceeded the flight performance will Decrease in all conditions WEIGHT BALANCE LIMITATIONS The reference point RD in relation to determinate the position of the center of gravity is tangent to the leading edge and perpendicular to the ground when the airplane is static or in flight and when the axis of the airplane is horizontal The weight calculation procedure and the ...

Страница 27: ...tial to resolve the problem ENGINE FAILURE Proceed to a forced landing POWER FAILURE a Fuel check both tanks b Fuel handle selected c Electric pump ON d Magneto s ON check e Throttle course check f In case of no results decrease engine rpm and land a s a p LOW ENGINE OIL PRESSURE a Oil temperature check b Oil pressure is not in the green But the temperature has a normal value land at the nearest a...

Страница 28: ...FF DURING CLIMB a Choose a safe landing zone b Throttle full foreword c Choke OFF full foreword d Fuel tank switch fully open e Magnetos ON f Fuel pump ON g Restart try ATTENTION if the engine restarts proceed for a secure climb and land for a check If the engine will not start proceed to a forced landing a Fuel switch OFF b Magnetos OFF c Contact OFF ATTENTION don t turn back Do not try to land d...

Страница 29: ...eck speed g Throttle set to maintain a correct approach speed h Electric pump ON i Flaps 2 3rd position j Touchdown must be effectuated at the lowest poss speed maintain the front wheel lifted as long as poss After contact a Fuel OFF b Magneto OFF c Main switch OFF NOTE if there is no convenient landing area close by try to land an upward run note that your touchdown speed must be higher than a la...

Страница 30: ...n b Engine air box heating if provided ON c Move continuous the flight commands d Increase the rpm of the propeller e Cabin heat ON ATTENTION in case of ice on the leading edge of the wing the stall speed will increase SPIN RECOVERY In case of a non intentional spin straight down a Throttle lever at minimum b Pedals opposite at the rotation c Ailerons neutral d Stabilator neutral e Flaps neutral f...

Страница 31: ...attention must be given to the wind direction ELECTRIC PLANT FAILURE GENERATOR INDICATOR ILLUMINATED DURING ENGINE RUN IN FLIGHT a Volt meter check indication b Less than 12 Volt indication switch off all electrical equipment Not needed to proceed the flight or To reach the nearest airport NOTE when the battery is in good or sufficient condition to continue one hour of flight in complete safety In...

Страница 32: ...the flaps are extended b Reduce the speed to the limit c In landing configuration remind that the lift is reduced Landing with flaps UP a Increase the speed in final with10 km h 5 knots b In case of engine failure maintain the flight limits c The approach must be effectuated in a flat flight configuration Landing with the flaps in T O position a Maintain a normal landing speed b With engine failur...

Страница 33: ...in a longer run and an increased ground speed during landing and take off NOTE we refer here to the concerned chapter With a headwind component the take off and landing run will be shorter app 8 10 meters each 5km h that the wind increases Example with a headwind of 10 km h the landing run will be 16 20 meters shorter With a side wind component we need to remember that a side wind with a certain a...

Страница 34: ...the best rate of glide to reach a landing area Important is to maintain the lowest angle of descent versus the lowest rate of descent For the STORCH CL the indicated airspeed related to the maximum glide rate E 13 8 at Veff max 89 km h IAS with 1st position flaps Following index indicates the maximum distance to go related to the height at the max Glide rate setting fig 6 Table showing available d...

Страница 35: ...400 500 600 700 800 900 1000 1100 1200 0 1640 3281 4921 FIELD ALTITUDE feet TAKE OFF RUN TAKE OFF DISTANCE TAKE OFF ft with screen of 50 ft TAXIING I S A PILOT TAXIING I S A 13 PILOT TAXIING I S A PILOT PASSENGER TAXIING I S A 13 PILOT PASSENGER TAXIING 50 ft SCREEN I S A PILOT TAXIING 50 ft SCREEN I S A 13 PILOT TAXIING 50 ft SCREEN I S A PILOT PASSENGER TAXIING 50 ft SCREEN I S A 13 PILOT PASSEN...

Страница 36: ... 1640 3281 4921 AIRFIELD ALTITUDE feet ROLLING DISTANCE LANDING DISTANCE feet WITH OBSTACLE 50 feet ROLLING DISTANCE I S A PILOT ONLY ROLLING DISTANCE I S A 13 PILOT ONLY ROLLING DISTANCE I S A PILOT PASSENGER ROLLING DISTANCE I S A 13 PILOT PASSENGER LANDING DISTANCE I S A PILOT ONLY LANDING DISTANCE I S A 13 PILOT ONLY LANDING DISTANCE I S A PILOT PASSENGER LANDING DISTANCE I S A 13 PILOT PASSEN...

Страница 37: ...h Classic Jabiru Rev 0 07 2002 Pag 37 WARNING Beware that between moment of engine failure and the max rate of glide setting the loose of height is about 75 meters 250 ft fig 9 RELATIVE WIND DIAGRAM VERSUS WIND COMPONENT ...

Страница 38: ...LIMB DIAGRAM AT MAXIMUM RPM Second norm BCAR SECTION S S 65 I S A CONDITIONS Temp 15 C Press 760 mmHg M S L 600 700 800 900 1000 1100 1200 0 1640 3281 4921 ALTITUDE feet Vy CLIMB RATE feet minute I S A 13 PILOT PASSENGER I S A PILOT PASSENGER I S A 13 PILOT ONLY I S A PILOT ONLY ...

Страница 39: ... Vso Stall speed with extended flaps 57 km h Vs Stall speed with retracted flaps 63 km h Vfe Maximum speed with extended flaps 30 110 km h Va Maneuvering speed 130 km h Vc Cruise speed 151 km h Vh Maximum leveled flight speed 165 km h Vne Velocity never to exceed 180 km h Load factor 4 2 ...

Страница 40: ...y to obtain a correct weight and balance and to avoid that the limits of these will be trespassed NOTE The empty weight and also the center of gravity changes in the following cases When adding or modifying equipment and or accessories After repairing and bodying or repainting structural parts The empty weight and the corresponding position of the center of gravity must be reported and registered ...

Страница 41: ...t balances under each landing wheel It is imperative that the airplane is fully horizontally stabilized A check must be established by referring a leaded wire on the right referring side of the airplane This procedure is done to determinate the RD At this place reference is reported for all measurement needed for a correct application of the formula mentioned before All the results of this test mu...

Страница 42: ...t conditions with brake liquid Oil cooling liquid Non usable fuel Support Full weight kg Tare kg net weight kg Arm m Frontal P1 X1 Outside left P2S X2S Outside right P2D X2D Empty weight PT kg Position of the CG related to the empty weight Moment in empty weight configuration ML PT x XT _______x_______ _______ kg x m Useful max weight Maximum weight kg Empty weight kg Useful weight kg Date to add ...

Страница 43: ...159 4 86 46 4 38 9 21 11 3 100 1 54 29 1 161 2 87 46 9 40 8 22 11 8 101 9 55 29 7 163 1 88 47 5 42 6 23 12 4 103 8 56 30 2 164 9 89 48 0 44 5 24 13 0 105 6 57 30 8 166 8 90 48 6 46 3 25 13 5 107 5 58 31 3 168 6 91 49 1 48 2 26 14 0 109 3 59 31 8 170 5 92 49 6 50 0 27 14 6 111 2 60 32 4 172 3 93 50 2 51 8 28 15 1 113 0 61 32 9 174 2 94 50 1 53 7 29 15 6 114 9 62 33 5 176 1 95 51 3 55 6 30 16 2 116 ...

Страница 44: ...51 6 6 1 12 23 6 22 9 45 88 6 39 6 78 153 5 6 6 13 25 6 23 4 46 90 6 40 1 79 155 5 7 1 14 27 6 23 9 47 92 5 40 6 80 157 5 7 6 15 29 5 24 4 48 94 5 41 1 81 159 4 8 1 16 31 5 24 9 49 96 5 41 7 82 161 4 8 6 17 33 5 25 4 50 98 4 42 2 83 163 4 9 1 18 35 4 25 9 51 100 4 42 7 84 165 4 9 7 19 37 4 26 4 52 102 4 43 2 85 167 3 10 2 20 39 4 26 9 53 104 3 43 7 86 169 3 10 7 21 41 3 27 4 54 106 3 44 2 87 171 3...

Страница 45: ...8 0 9428 1 0299 3 000 914 9 056 48 301 0 8962 0 9151 1 0454 4 000 1219 7 075 44 735 0 8636 0 8881 1 0611 5 000 1524 5 094 41 169 o 8320 0 8616 1 0773 6 000 1829 3 113 37 603 0 8013 0 8358 1 094 1 000 2134 1 132 34 037 0 7716 0 8106 1 1108 8 000 2438 0 85 30 471 0 7427 0 7859 1 128 9 000 2743 2 831 26 904 0 7147 0 7619 1 1457 10 000 3050 4 812 23 338 0 6876 0 7384 1 1638 11 000 3353 6 793 19 772 0 ...

Страница 46: ...14 45 93 14 33 47 154 20 24 38 80 262 47 4 57 15 49 21 14 63 48 157 48 24 69 81 265 75 4 88 16 52 49 14 94 49 160 76 24 99 82 269 03 5 18 17 55 77 15 24 50 164 04 25 30 83 272 31 5 48 18 59 06 15 54 51 167 32 25 60 84 275 59 5 79 19 62 34 15 85 52 170 60 25 91 85 278 87 6 10 20 65 62 16 15 53 173 88 26 21 86 282 15 6 40 21 68 90 16 46 54 177 17 26 52 87 285 43 6 71 22 72 18 16 76 55 180 45 26 82 8...

Страница 47: ...inch Hg 22 8 z 0 mbar 1013 3 inch Hg 29 9 z 2300 mbar 165 7 inch Hg 22 6 z 50 mbar 1007 3 inch Hg 29 7 z 2350 mbar 760 9 inch Hg 22 5 z 100 mbar 1001 3 inch Hg 29 6 z 2400 mbar 756 2 inch Hg 22 3 z 150 mbar 995 4 inch Hg 29 4 z 2450 mbar 751 4 inch Hg 22 2 z 200 mbar 989 4 inch Hg 29 2 z 2500 mbar 746 7 inch Hg 22 1 z 250 mbar 983 6 inch Hg 29 z 2550 mbar 742 1 inch Hg 21 9 z 300 mbar 977 7 inch H...

Страница 48: ...45 337 8 1534 800 2625 9 8 282 8 0 9819 690 6 9389 0 9087 0 1156 1 1342 0 9254 1 0395 337 4 15146 900 2953 9 15 282 15 0 9797 682 3 9276 0 8978 0 1145 1 1232 0 9164 1 0446 337 15 59 1000 3281 8 5 281 5 0 9774 674 1 9165 0 887 0 1134 1 1122 0 9074 1 0498 336 6 15 71 1100 3609 7 85 280 85 0 9752 665 9 9053 0 8762 0 1123 1 1013 0 8985 1 055 336 2 15 83 1200 3937 7 2 280 2 0 9729 657 9 8944 0 8656 0 1...

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