PILOT OPERATING HANDBOOK AND TRAINING MANUAL 00 11/10/07 Complete manual revision Num. Date Description REVISION Issued Verified Approved FlySynthesis s.r.l. reserves it to terms of law the exclusive ownership of this manual and also forbids the partial reproduction of it. THIS DOCUMENT MUST BE CARRIED IN THE AIRCRAFT AT ALL TIMES
IDENTIFICATION: Page: 2 of 71 Manufacturer SRL Address Provincial Rd 78 Km 12.150 Mortegliano 33050 (UD) ITALY Model: STORCH Version: Airframe Serial No: Engine Model: Engine Serial No: Registration: Date: Signature: Stamp:
Page: 3 of 71 NOTE This manual may be revised in the future and pages/or sections re-issued in part or whole. Revisions will also be available on the Fly Synthesis website www.flysynthesis.com. Any revisions and/or sections should be printed and replaced in the manual at the earliest possible time for flight safety. The revisions added to the manual should be logged and recorded in the table under log of amendments of this manual, by the owner/user. DEFINITIONS Definitions used in this handbook such as WARNING, CAUTION and NOTE are employed in the following context. WARNING Procedures or instructions that if not followed correctly may result in injury or death CAUTION Procedures or instructions that if not followed correctly may result in damage to the aircraft or its parts NOTE: Procedures or instructions that affect safety of flight are highlighted INTELLECTUAL PROPERTY The data and information contained in this document is the property of FLYSYNTHESIS SRL. This document may not be reproduced or transmitted to a third party, in any form or by any means. Any unauthorized copy or distribution is illegal as per international agreements relating to property rights. THIS AIRCRAFT WAS MANUFACTURED IN ACCORDANCE WITH THE FOLLOWING LIGHT SPORT AIRCRAFT AIRWORTHINESS STANDARDS CS VLA, F2279, F2295 AND F2483 AND DOES NOT CONFORM TO STANDARD CATEGORY AIRWORTHNESS REQUIREMENTS.
Page: 4 of 71 LOG OF REVISIONS Revision No. Revision Date Signature
LOG OF EFFECTIVE PAGES Page: 5 of 71 Section Page Date Revision Section Page Date Revision - 01 11/10/07 0 5 41 11/10/07 0-02 11/10/07 0 5 42 11/10/07 0-03 11/10/07 0 5 43 11/10/07 0-04 11/10/07 0 6 44 11/10/07 0-05 11/10/07 0 6 45 11/10/07 0-06 11/10/07 0 6 46 11/10/07 0 1 07 11/10/07 0 7 47 11/10/07 0 1 08 11/10/07 0 7 48 11/10/07 0 1 09 11/10/07 0 7 49 11/10/07 0 1 10 11/10/07 0 7 50 11/10/07 0 1 11 11/10/07 0 8 51 11/10/07 0 1 12 11/10/07 0 8 52 11/10/07 0 2 13 11/10/07 0 8 53 11/10/07 0 2 14 11/10/07 0 8 54 11/10/07 0 2 15 11/10/07 0 8 55 11/10/07 0 2 16 11/10/07 0 8 56 11/10/07 0 2 17 11/10/07 0 8 57 11/10/07 0 2 18 11/10/07 0 3 19 11/10/07 0 TRAINING MANUAL SUPPLEMENT 3 20 11/10/07 0-58 11.10.07 0 3 21 11/10/07 0-59 11/10/07 0 3 22 11/10/07 0-60 11/10/07 0 3 23 11/10/07 0 1 61 11/10/07 0 3 24 11/10/07 0 2 62 11/10/07 0 3 25 11/10/07 0 2 63 11/10/07 0 4 26 11/10/07 0 2 64 11/10/07 0 4 27 11/10/07 0 3-4-5 65 11/10/07 0 4 28 11/10/07 0 5 66 11/10/07 0 4 29 11/10/07 0 6 67 11/10/07 0 4 30 11/10/07 0 6 68 11/10/07 0 4 31 11/10/07 0 6 69 11/10/07 0 4 32 11/10/07 0 7 70 11/10/07 0 4 33 11/10/07 0 8 71 11/10/07 0 4 34 11/10/07 0 5 35 11/10/07 0 5 36 11/10/07 0 5 37 11/10/07 0 5 38 11/10/07 0 5 39 11/10/07 0 5 40 11/10/07 0
INDEX Page: 6 of 71 Title Section Page IDENTIFICATION 2 DEFINITIONS 3 LOG OF REVISIONS 4 LOG OF EFFECTIVES PAGES 5 General information 1 7 Limitations 2 13 Emergency procedures 3 19 Normal operations 4 26 Performances 5 35 Weight and balance 6 44 Aircraft ground handling and service 7 47 Aircraft check list 8 51
SECTION 1 Page: 7 of 71 Title General information Page 1.1 Introduction 7 1.2 Warnings, suggestions and notes 7 1.3 Descriptive aircraft datas 7 1.4 Aircraft three views 12
1.1 INTRODUCTION Page: 8 of 71 This operating handbook contains the necessary information for a sure and efficient employment of the aircraft FLYSYNTHESIS STORCH S LSA ROTAX 912 UL 80 HP and STORCH S JABIRU 2200 85 HP. Unless indicated, all descriptive data are valid for both engine versions. The POH has been prepared to comply with the requirements of CS-VLA and where relevant the ASTM standard. The Pilot Operating Handbook is valid only for the particular aircraft identified on page 2, the identification page. 1.2 WARNINGS, SUGGESTIONS AND NOTES The observance of this manual is compulsory for the aircraft's use. FLYSYNTHESIS S.r.l. declines every responsibility for any damage to person and thing derived by a missed or partial observance of the prescriptions contained in this manual. FLYSYNTHESIS S.r.l. reserves it, to terms of law, the exclusive ownership of this manual and also forbids the partial or integral reproduction of it and however to communicate it to competing firms without a preventive written authorization. 1.3 DESCRIPTIVES AIRCRAFTS DATA TYPE OF AIRCRAFT Storch S is ultra light aircraft with airframe, wing and control surfaces in composite materials. The tail beam is made of aeronautical aluminum alloy, fixed on composite structure. The retangular shape high wing utilizes a laminar flow airfoil section. The ailerons are differential whilst the flaps are electrically operated plain type. The vertical tail control surface is composed by a fixed fin and by a mobile rudder, the horizontal tail control surface is completely mobile, hinged in the central part with integrated trim. The tricycle type landing gear is fixed, with dampened nose wheel and with main legs made of either spring steel or ERGAL aeronautical aluminum alloy. The Storch S aircraft is approved for Day VFR only. Flight into bad weather with IFR conditions by VFR pilots and aircraft is extremely dangerous. As the owner and operator of an aircraft you are responsible for the safety of your passenger and yourself. DIMENSIONS (valid for Rotax 912 UL and Jabiru 2200 engines) General Wing span: Length: Height: Wing Surface: Wing chord: Wing load: Flap Surface: 9.300 m 5.950 m 2.150 m 10.250 m2 1.100 m 44.500 kg/m2 0.620 m2
Span: 2.230 m Chord: 0.280 m Travel: 0-40 Aileron Surface: 0.410 m2 Span: 1.650 m Chord: 0.250 m Travel: down 20 / up 30 Stabilator Surface: 1.650 m2 Span: 2.450 m Chord: 0.700 m Travel: down 11 / up 16 Vertical fin (with rudder) Surface: Height: Mean chord: 1.120 m2 1.280 m 1.930 m Rudder Surface: 0.600 m2 Height: 1.200 m Mean chord: 0.480 m Travel: +/-22 Page: 9 of 71 WEIGHTS Rotax 912 UL Jabiru 2200 Empty weight 300 kg 297 kg Maximum allowed weight in baggage compartment 12 kg 12 kg Maximum Take Off Weight 500 kg 500 kg Minimum Pilot Weight 55 kg 55 kg LANDING GEAR (valid for Rotax 912 UL and Jabiru 2200 engines) Type: Tricycle type landing gear with dampened nose wheel Main gear track: 1.640 m Wheelbase: 1.340 m Tyre: Main: 4.00x6" Nose wheel: 4.00x4" Tyre pressure: Main: 2.2-2.4 bar Nose wheel: 1.8 bar Brakes: Main wheels hydraulic disc. FUEL SYSTEM (valid for Rotax 912 UL and Jabiru 2200 engines) Type: Two lines with mechanical and auxiliary eletric fuel pump Fuel plant draining system and return line system in the left tank Refueling by the fuel filler located on the upper layer of the wings
Tanks: Non-usable fuel Fuel filter: Fuel specification Page: 10 of 71 Two integrated tanks in glass fibers with 45 liters of capacity for each tank Fuel tank caps 2 liters for each tank Gascolator on firewall, entry fuel line filtered. Rotax 912ULS Jabiru 2200A Premium Automotive Unleaded fuel min 95Ron. Avgas 100LL. ELETRIC SYSTEM (valid for Rotax 912 UL and Jabiru 2200 engines) Type: POWERPLANT Engine: Type: Ignition: Battery: 12 V electrical wiring with starting battery Electrical wiring protected with fuses or circuit breakers External rectifier-regulator Rotax 912 UL 4 strokes, 4 cylinder horizontal opposed, spark ignition engine, liquid cooled cylinder heads, ram air cooled cylinders, two constant depression carburettors, mechanical fuel pump, dry sump forced lubrification. Increased electric ignition system HD Sealed Lead Acid Battery 12 Volts Standard propeller: DUC composite three blades propeller, diameter 1670 mm, ground variable pitch. DUC composite two blades propeller, diameter 1670 mm, ground variable pitch GT-2 wood two blades propeller, diameter 1660 mm, fixed pitch 1450 mm. Engine: Jabiru 2200 Type: 4 strokes, 4 cylinder horizontal opposed, spark ignition engine, ram air cooled cylinders, 2 carburatori a depressione costante, two constant depression carburettors, mechanical fuel pump, warm air at carburettor system. Ignition: Eletric ignition system Battery: Sealed Lead Acid Battery 12 Volts Standard propeller: DUC composite three blades propeller, diameter 1520 mm, ground variable pitch. DUC composite two blades propeller, diameter 1620 mm, ground variable pitch
Page: 11 of 71 GT-2 wood two blades propeller, diameter 1510/1520/1570 mm, fixed pitch 1050/1000 mm. Other propeller types as approved by the manufacturer and listed in appendix C of the maintenance manual. (Applicable to both engines) INSTRUMENTS (valid for Rotax 912 ULS and Jabiru 2200 engines) Standard instruments: air speed indicator, altimeter, vertical speed indicator, magnetic compass, bank indicator, flap angular range indicator, two low fuel level amber lamp, CHT, EGT, RPM, oil temperature indicator, oil pressure indicator, fuel pressure indicator, engine run time indicator, 12 V aux socket. OTHER STANDARD EQUIPMENTS (valid for Rotax 912 UL and Jabiru 2200 engines) Main wheels and nose wheel fairings, main legs and nose camper aerodynamic fairing, four points safety belts, electric flap system (travel: 0-40 ), manual trim regulation system, full moquette cabin covering, baggage compartment with baggage net.
1.4 AIRCRAFT THREE VIEWS Page: 12 of 71
SECTION 2 Limitations Page: 13 of 71 Title 2.1 Introduction 14 2.2 Airspeed limitations 14 2.3 Anemometers marking 14 2.4 Powerplant and propeller limitations 15 2.5 Powerplant instruments marking 15 2.6 Weight limitations 16 2.7 Center of gravity limitations 16 2.8 Manoeuvre limitations 16 2.9 Load factor limitations 17 2.10 Crew 17 2.11 Placards 17 Page
2.1 INTRODUCTION Page: 14 of 71 This section contains the operational limitations and the instruments marking for use in safety condition the aircraft, the engine, the equipments and standard plant. The limitations of speed are been calculated following the BCAR-S rules, the structures are been tested following the same rules. 2.2 AIRSPEED LIMITATIONS Speed Vne Never Exceed speed Vmo Va Vfe Vs Vs1 Vso Maximum Structural Cruising Speed Manoeuvring speed Maximum speed with full flaps Stall speed without flap Stall speed in take off position (15 ) Stall speed in landing position - full flap (40 ) Rotax 912 ULS IAS 220 km/h 118 KTS 160 km/h 86 KTS 130 km/h 70 KTS 105 km/h 57 KTS 65 km/h 35 KTS 63 km/h 34 KTS 59 km/h 32 KTS 2.3 ANEMOMETERS MARKING (valid for Rotax 912 UL and Jabiru 2200 engines) Jabiru 2200 IAS 220 km/h 118 KTS 160 km/h 86 KTS 130 km/h 70 KTS 105 km/h 57 KTS 65 km/h 35 KTS 63 km/h 34 KTS 59 km/h 32 KTS Notes Never exceed this speed in every condition or configuration Never exceed this speed in turbolent air condition Do not use full stick and full rudder deflections above this speed Do not exceed this speed with flap extended Do not descende this speed without flap to avoid undesired stall conditions Do not descende this speed with flap in take off position to avoid undesired stall conditions Do not descende this speed with flap in landing position to avoid undesired stall conditions Marking Speed range (IAS) Definition White arc [Vs0 - Vfe] 59-105 km/h Speed range where flap may be extended [Vs0 - Vfe] 32-57 KTS Green arc [Vs - Vmo] 65-160 km/h [Vs - Vmo] 35-86 KTS Speed range of normal operation Yellow arc [Vmo- Vne] 160-220 km/h Manoeuvre the aircraft with great caution [Vmo- Vne] 86-118 KTS Red line [Vne] 220 km/h Maximum speed allowed [Vne] 118 KTS
2.4 POWERPLANT AND PROPELLER LIMITATIONS (Refer always to Rotax's or Jabiru operator manual) Page: 15 of 71 Engine manufacturer: Rotax Jabiru Aircraft Engine model: 912 UL 2200 Maximum take off power: 60 kw 63.4 kw Maximum continuos power: 58 kw 63.4 kw Maximum take-off RPM: 5800 rpm 3300 rpm Maximum continuos RPM: 5500 rpm 3300 rpm Minimum cylinder head temperature: 150 C 200 C Maximum oil temperature: 140 C 118 C Minimum oil pressure: 1.5 bar 2.2 bar Maximum oil pressure: 7 bar 5.25 bar Minimum fuel pressure: 0.15 bar 0.05 bar Maximum fuel pressure: 0.4 bar 0.2 bar Usable type of fuel: minimum 95 RON Avgas or >95 RON Usable type of oil: See engine manual specifications Propeller manufacturer: DUC Hélices GT Propellers Propeller model: Carbon three-blades Wood two-blades Carbon two-blades Ground variable pitch Fixed pitch Maximum diameter: 1670 mm 1660 mm 2.5 POWERPLANT INSTRUMENTS MARKING Rotax 912 UL engine version Strumento Red line Inf. yellow Green arc-normal Sup. yellow Red line Inf. limit arc -Caution operations arc -Caution Sup. limit RPM indicator n/a n/a 1.400-5.500 rpm 5.500-5.800 rpm 5.800 rpm Fuel pressure gauge 0.15 bar n/a 0.15-0.4 bar n/a 0.4 bar Oil pressare gauge 0.8 bar 0.8-2 rpm 2-5 bar 5-7 rpm 7 bar Oil temp. gauge 50 C 50-90 C 90-100 C 110-140 C 140 C CHT 50 C n/a 50-100 C 110-150 C 150 C Jabiru 2200 engine version Strumento Red line Inf. yellow Green arc-normal Sup. yellow Red line Inf. limit arc -Caution operations arc -Caution Sup. limit RPM indicator n/a n/a 900-3.300 rpm n/a 3.300 rpm Fuel pressure gauge 0.05 bar n/a 0.05-0.2 bar n/a 0.2 bar Oil pressare gauge 0.8 bar n/a 2.2-5.25 bar n/a 5.25 bar Oil temp. gauge 15 C 15-80 C 80-100 C 100-118 C 118 C CHT 50 C n/a 50-180 C 180-200 C 200 C EGT Below 70% of power Above 70% of power 680-750 C 640-780 C 2.6 WEIGHT LIMITATIONS
Page: 16 of 71 Rotax 912 UL Jabiru 2200 Empty weight 300 Kg 297 Kg Maximum fuel weight 69 Kg 69 Kg Maximum allowed weight in baggage compartment 12 Kg 12 Kg Maximum Take Off Weight 500 Kg 500 Kg 2.7 CENTER OF GRAVITY LIMITATIONS With the purpose to get the best performances of flight and operations in complete safety, according to the procedures described in this manual, the aircraft must have employed respecting all the schemes of load and balancing pointed out in the following pages. Pilot must consider the limit of weighing and all correlated parameters. Before the delivery of the airplane, centre gravity position and weight of the airplane are verified. NOTE: Empty weight & Centre gravity position must be updated after a new weighing, in the following case: - Substitution and/or modify of one or plus accessories and equipment; - After painting or reparations of fusolage. Weight and Centre Gravity position must be reported after every relief in the weighing report inside this manual only by authorized personnel. The location of the CG can be defined by reference to the % MAC. Maximum anterior limit: 30% M.A.C. correspondent to 330 mms Maximum back limit: 36% M.A.C. correspondent to 396 mms For methodology and conditions for weight and balance procedure, see section 6. 2.8 MANOEUVRE LIMITATIONS All aerobatics maneuvers are prohibited. The normal flight operations are the followings: - Every connected manoeuvre to the normal flight operation, - Stalls, with exclusion of the accelerated stall (superior to 1 g) - Low speed figure eight, chandelle, turns below 60 The use of the aircraft has to be conforming with the Rules of the State within it fly. WARNING Flight in known icing conditions, snow and heavy rain is prohibited. The pilot is responsible for determining the airworthiness of the aircraft for each flight including on board fuel lever verification. All maneuvers at load factor less than - 0.5 g, must be performed for no longer than 5 seconds. In single pilot operation, belt and shoulder harness of the vacant seat must be secured to avoid uncontrolled movement of seat back and belt.
2.9 LOAD FACTOR LIMITATIONS Page: 17 of 71 The load factors limit used for the calculation of the structures conform with CS VLA rules: Flap retracted Flap extendeed - Maximum positive load factor 4.0 (+) - Maximum positive load factor 2.0 (+) - Maximum negative load factor 2.0 (-) - Maximum negative load factor 0.0 (+) 2.10 CREW The minimum crew for flight operations is a person. The owner can choose the place of pilotage to the right or to the left. The maximum number of people permitted on board is two. 2.11 PLACARDS The following placards are to be located and visible to the pilot where an inspection or function is relevant and required in the designated area. Located on the Instrument panel WARNING THIS AIRCRAFT WAS MANUFACTURED IN ACCORDANCE WITH LIGHT SPORT AIRCRAFT AIRWORTHINESS STANDARDS AND DOES NOT CONFORM TO STANDARD CATEGORY AIRWORTHINESS REQUIREMENTS. INFLATE NOSE WHEEL TO 1.8 bar (26.1 psi) INFLATE MAIN WHEEL TO 2.2 2.4 bar (32 35 psi) Located on Nose Leg fairing Located on both Main Leg fairing FUEL CAPACITY 45 LTRS MINIMUM 95 OCTANE AUTO FUEL OR 100 LL AVGAS Located next to fuel each filler cap BAGGAGE COMPARTMENT Maximum 12 Kg Evenly distribuited Located in baggage compartment
Page: 18 of 71 Located on fuselage next to fuel refill tap Located on fuselage next to fuel drain tap AUXHILARY RE FUELING POINT AUXHILARY FUEL DRAIN Located in Speed: KTS Weight: Kg Vne (Not Exceeded) 118 Maximum Take-off 500 Vmo (Max Operating) 86 Empty Weight 300 Va (Min Maneuvering) 70 Minimum Pilot 55 Vfe (Max Full Flap) 57 Maximum Pilot + Vs (Stall) 35 passenger 180 Vso (Stall with flap) 32 AEROBATIC MANOEUVRES AND SPINS ARE PROHIBITED baggage compartment Located in compartment STORCH 550 LSA DATA PLATE Aircraft s/n Fusolage s/n Date of Manufacture Engine Type Engine s/n Propeller type Propeller s/n Hub s/n baggage Located on internal and external side of doors
Title SECTION 3 Emergency procedures Page: 19 of 71 Page 3.1 Introduction 20 3.2 Ground emergency procedures 20 3.3 Take off emergency procedures 20 3.4 During flight emergency procedures 21 3.5 Electrical wiring failure 22 3.6 Landing emergency procedures 23 3.7 Opening parachute procedure 24 3.8 Other emergency 25
3.1 INTRODUCTION Page: 20 of 71 An emergency situation is extremely rare; even so, the pilot responsible for the aircraft should meticulously carry out daily pre-flight controls checks. A safe airworthy aircraft should be maintained according to the requirements of the accompanying maintenance manual. This section contains the recommended procedures should an emergency arise. It is strongly advised that Pilots become familiar with these procedures. 3.2 GROUND EMERGENCY PROCEDEDURES ENGINE ON FIRE 1. Fuel tank faucet - Close 2. Electric fuel pump - Off 3. Cabin heating - Off 4. Throttle - All forward 5. Master switch - OFF 6. Ignition magnets key - OFF 7. Get out of aircraft immediatly 8. If possible, use an extinguisher to extinguish the fire. WARNING: Don t remove the engine cowling until the complete extinction of the fire. Don't use water to extinguish the fire. 3.3 TAKE OFF EMERGENCY PROCEDURES TAKE OFF INTERRUPTION (during take off run) 1. Throttle - All rearward (reduce to minimum RPM) 2. Brakes - Brake and avoiding skidding the wheels 3. Flap - Retract 4. Ignition magnets key - OFF 5. Master switch - OFF 6. Fuel tank faucet - OFF ENGINE FAILURE DURING TAKE OFF (after rotation - below 50 mt) 1. Fuel tank faucet - Close 2. Electric fuel pump - OFF 3. Master switch & ignition magnets key - OFF 4. Safety belts - Tighten well 5. Maintain a linear line of flight, without turning if possible, and if the area allows it, get ready to a forced landing (see relative paragraph) ENGINE FAILURE DURING TAKE OFF (during climb) If the height allows it, proceed in the following way: 1. Best glide speed - (57 KTS) 2. Electric fuel pump - Verify ON 3. Fuel tank faucet - Verify LH tank faucet open 4. Fuel tank level - check fuel quantity
Page: 21 of 71 5. Fuel pressure - Verify within limits 6. Ignition magnets key - Verify ON 7. Throttle - Position warm engine starting 8. Engine start procedure - If the engine immediately starts up climb to a safe height and land ASAP for a check. - If the engine doesn't start up prepare for an emergency landing & proceed as follows: 9. Flap - As necessary (30 or 40 ) 10. Fuel tank faucet - Close 11. Electric fuel pump - Off 12. Master switch & ignition magnets key - Both Off WARNING: Land AS SOON AS POSSIBLE in case of fire on board. - Never perform a 180 turn from too low a height in an effort to return to the runway. 3.4 DURING FLIGHT EMERGENCY PROCEDURES ENGINE ROUGHNESS/ ENGINE SHUTDOWN 1. Throttle - Check position and friction 2. Check engine instruments - Check parameters 3. Choke lever - OFF / All rearward 4. Fuel tank faucet - Select more full tank 5. Electric fuel pump - ON 6. Fuel pressure - Verify within limits 7. Warm air to carburettors - ON 8. Ignition magnets key - Both / Verify 9. Master switch - Verify / ON 10. Throttle - Position warm engine starting 11. Start - Operate start procedure 12. Check all the engine parameters and land as soon as possible for a check If the engine doesn't start up choose a proper zone to an emergency landing procedure ENGINE ON FIRE 1. Fuel tank faucet - Close 2. Electric fuel pump - Off 3. Throttle - All forward 4. Vent system - All closed 5. Cabin heating system - Off 6. Master switch & ignition magneto key - Off 7. Best glide speed - (57 KTS) 9. Landing ASAP WARNING: Do not attempt to re-start the engine even if engine fire has ceased, but prepare for an emergency landing. STALL RECOVERY PROCEDURE 1. Apply full power to reduce the loss of height.
Page: 22 of 71 2. Push softly forward the control stick to eliminate the stall conditions. NON INTENTIONAL SPIN RECOVERY PROCEDURE WARNING: don't try to stop the rotation using the opposite ailerons 1. Throttle - At minimum RPM 2. Rudder pedals - All opposed to the sense of rotation 3. Control stick - Neutral, softly to dive 4. When the rotation stops and the aircraft is under control, return to level flight, WARNING: do not exceed the Vne speed. 3.5 ELETRICAL WIRING FAILURE GENERATOR WARNING LAMP LIGHTING 1. Voltmeter - Check voltage (if installed) 2. Non essential electric equipment - Off 3. Land ASAP A fully charged and functional battery should permit the operation of trim, flap and aux electric fuel pump for about 20 minutes. OVER VOLTAGE (Voltmeter indication [if installed] over 16 V) 1. Master switch - Off 2. Voltmeter - Verify the decrease of voltage 3. Master switch - On 4. Voltmeter - Verify the increase of voltage (within limits) If the voltage does not return within limits, proceed as follows 5. All non-essential electrical equipment must be switched off 6. Land ASAP A fully charged and functional battery should permit the operation of trim, flap and aux electric fuel pump for about 20 minutes. LOW VOLTAGE IN FLIGHT 1. Possible causes - Excessive consumption (Too many appliances on) - Damage of the alternator - Interrupted fuse 2. Landing ASAP LOW VOLTAGE ON GROUND 1. RPM - Reduce 2. Navigation and landing lights - Off 3. Voltmeter - Verify within limits 4. If the check has negative result - Shutdown engine ELECTRICAL WIRING or EQUIPMENT ON FIRE An electrical fire is recognizable by the distinct odor of burning plastic and white smoke. 1. Master switch - Off 2. Vent systems - All open 3. Cabin heating - Off
4. Landing ASAP Page: 23 of 71 WARNING: get ready to possibly land without the use of flaps and trim (if electric). SMOKE ELIMINATION FROM CABIN 1. Vent systems - All open 2. Cabin heating - Off 3. Master switch - Off 4. If the smoke remains dense land immediately. WARNING: absolutely DO NOT open the canopy. 3.6 LANDING EMERGENCY PROCEDURES LANDING WITHOUT FLAPS 1. Verify flap/trim circuit breaker is in the ON position. 2. Verify the position of both the flaps visually With flaps in symmetrical position (both retracted or extracted at the same angle) 3. Try to retract the flaps 4. Verify that there is enough free space from obstacles for a safe landing 5. Land as normal but maintain a landing speed not less than 48 Knots LANDING WITH A DEFLATED TIRE 1. Landing as per normal condition 2. Before contacting the ground shutdown the engine and turn off electrical equipment. 3. When landing hold-off contact with the ground on the side of the deflated tire for as long as possible 4. Get ready for a tendency to yaw on the side of the deflate tire 5. Maintain the directionality with rudder and nose wheel steering 6. If nose wheel is deflated maintain backpressure on control stick and keep the nose wheel in a central position. FORCED LANDING 1. Best glide speed - (57 KTS) 2. Safety belts - Tighten well 3. Throttle - All rearward (minimum position) 4. Fuel tank faucet - Closed 5. Electric fuel pump. - Off 6. Master switch & ignition magnetos key - Off CAUTION: Choose a suitable area for an emergency landing. 7. Flap - As necessary 8. Trim - As necessary 9. Final - Check velocity 10. Landing - Check velocity (at least 38 KTS, flap with 40 ). The contact with the ground should happen at the minimum possible speed, maintain lifted the nose wheel for the longest possible time. 3.7 OPENING PARACHUTE PROCEDURE (IF INSTALLED)
Page: 24 of 71 The emergency parachute is situated in a special container fixed to the inside of the fuselage and can be seen when the seat is tilted forward. The emergency parachute is fixed to the aircraft through two Kevlar ropes attached with a special plate to main landing gear strut bolts. The ropes passing through the internal part of the fuselage and only for the last part go out untill the canister. The emergency parachute must be used only in case of complete loss of the control of the aircraft. Simplified parachute opening procedures a. Shutdown the engine (magnetos OFF) b. Pull red handle fixed on the internal wing mount, at least 20 centimeters, c. Close both fuel faucets d. Tighten the safety belts e. Shutdown the electric plant (Master OFF) f. Protect your body (cover face and keep limbs close) For further information and notes on function and maintenance, consult the parachute manual.
3.8 OTHER EMERGENCY Page: 25 of 71 WARNING: Flight in known icing conditions, snow and heavy rain is prohibited. If you meet unintentional icing condition during the flight, descend as soon as possible to a lower height. If the wing leading edge and the stabilator leading edge are covered by ice formations, remember that stall speed will increase, you will need more engine power to maintain the same velocity and the maneuverability of the airplane will decrease. 1. Carburetor heating system (if installed) - On 2. Engine RPM - Maintain the maximum continuous engine power 3. Cabin heating (if installed) - On 4. Move all control surfaces to break potential icing formations. ICING FORMATIONS ON CARBURETTORS You can recognize icing formations on carburetors if RPM decreases without moving the throttle. You can find this phenomenon during a descent with low RPM in a day with a lot of humidity. 1. Carburetor heating system (if installed) - On 2. Throttle - All forward when RPM starts to increase 3. Carburetor heating system (if installed) - Off 4. Reinstate normal flight conditions ABNORMAL ENGINE VIBRATIONS 1. Verify the reduction of the vibrations with a reduction of the RPM s 2. Land as soon as possible 3. Be prepared for a possible engine failure and to commence a forced landing LANDING WITH BRAKE SYSTEM FAILURE 1. Look for a long grassy runway with absence of obstacles (the grass has a light braking action) 2. Land with the flaps to the maximum extension and reduce speed to the minimum safe speed (After touching the ground) 3. Master switch & ignition magnets key - Off
SECTION 4 Normal procedures Page: 26 of 71 Title Page 4.1 Introduction 27 4.2 Speed for normal employment 27 4.3 Fuel circuit draining procedure and refuelling operations 27 4.4 Pre-flight Inspection 28 4.5 Flight inside heavy rain 34
4.1 INTRODUCTION Page: 27 of 71 This section contains the information for normal flight conditions and the checklist to follow before every flight. 4.2 SPEED FOR NORMAL EMPLOYMENT Except otherwise suitable, the following speeds refer to the maximum weight of take-off equal to 500 Kgs and can be used for any inferior weight. Take off (Flap 15 ) Rotax 912 UL and Jabiru 2200 Rotation Speed at 50 ft (15 m) obstacle Climb, (Flap retracted) Best angle of climb speed Vx, (5 flap), Best rate of climb speed Vy, (0 flap) Cruise Manoeuvring speed (Va) Max speed in turbulent air conditions (Vmo) Never Exceeding Speed (Vne) Landing Landing approach Landing (Flap 40 ) Touch & go (Maximum power, flap 20 ) Maximum demonstrated crosswind velocity (40 KTS) (43 KTS) (51 KTS) (67 KTS) (70 KTS) (86 KTS) (118 KTS) (57 KTS) (43 KTS) (46 KTS) (15 KTS) 4.3 FUEL CIRCUIT DRAINING PROCEDURE AND REFUELLING OPERATIONS The fuel circuit draining procedure must be done before the first flight of the day, 10 minutes after the refueling and if the aircraft has remained parked for more than three hours between two flights.the fuel circuit draining is performed through the Gascolator filter, situated in the right lower part of the firewall. Use a transparent and clean container, drain about 80-100 cc of fuel. Verify the absence of water. CAUTION: Perform the fuel circuit draining operation before moving the airplane from the parking area, to avoid any mixing of condensate water if present on the fuel tanks. If water is present repeat the fuel circuit draining operation until no water is evident. Refuel through the fuel filler located on the upper layer of the wings, either by jerry cans or directly with the gasoline pump. An optional on board electric fuel refilling pump may also be used. CAUTION: As the Storch S employs an overflow fuel system that returns excess fuel to the left hand side tank, it is recommended to always use the left side fuel tank. When the left tank is near empty use the right tank. To avoid the left tank being overfilled with excess fuel, frequently alternate the use of both fuel tanks during the cruise. The drawing of fuel simultaneously from both tanks is not recommended.
4.4 PRE-FLIGHT INSPECTION Page: 28 of 71 WARNING Before every flight pilot must check completely the airplane with great attention and accuracy. In this section there is a standard pre-flight check list. (Valid for each version) The pre-flight inspections must be carried out BEFORE EVERY FLIGHT. The pilot in command is responsible for such inspections. The inspection does not require any special tooling, although a flashlight can be useful for inspecting dark areas. The purpose of the pre flight inspection is to verify that there's no evidence of defective parts or problems that can endanger the safety of flight.
Remove all the protections 1. Pitot-cover, 2. Wheels stops, 3. Mobile surfaces stops, 4. Windshield covering, 5. Propeller protection, 6. Fuel draining procedure. Page: 29 of 71 Fuselage: left forward side (I) Fixing axle bolts Wheel fairing mounting bracket. Tire Damper Nose wheel support structure Alignment Fusolage: frontal side (II) Hub & blades Spinner check correct tightness good condition and free space between the wheel and general good condition, inflated correctly no signs of cracks or distorsion, free movement no signs of cracks or distorsion. check damper-rudder alignment no signs of cracks & clean. no signs of cracks, fixed correctly Fusolage: right forward side (III) Upper cowling remove Oil tank check level (for R 912UL remove the cap inside fusolage) Coolant tank check level (for R 912UL remove the cap inside fusolage) Radiator and air inlet no signs of cracks, free from obstructions Engine clean, no oil or refrigerant leakage Muffler & silencer manifold no signs of cracks, muffler hooked. Oil and coolant tube system correct functionality, no leakage Ignition & electric system correct functionality. Throttle & choke cables free movement Upper cowling reinstall and check tightness Right wing: forward side (IV) Wing surface Leading edge Wing strut mount Pitot tube absence of buckling absence of delaminations absence of delaminations, check joint, no signs of cracks no defects, no blockage and fixed correctly Right wing: rearward side (V) Trailing edge absence of delaminations, no signs of cracks Flap & aileron absence of delaminations, no signs of cracks, free movement, no excessive play on hinges, fixed correctly, balancing mass fixed correctly, no signs of lateral movement. Right main landing gear (VI) Leg no distorsion, bolts locked, no sign of cracks on the weldings Brake assembly condition and tightness Tire general good condition, inflated correctly
Wheel fairing mounting bracket. Page: 30 of 71 good condition and free space between the wheel and Fusolage: tail beam (VII) Tail beam Check joint tail beam/fuselage Bowden cables Check fixing Empennage (VIII) Vertical fin absence of buckling, absence of delaminations, check all rivets Rudder absence of delaminations, hinges fixed correctly Lower the tail of the aircraft to lift the nose wheel, check the free movement of the rudder, any problem on the hinge. Bowden cables fixed correctly. Stabilator free movement during all travel range, absence of buckling, absence of delaminations Stabilator hinge absence of delaminations, fixed correctly, no play Balancing mass fixed, no play Hinge pins fixed correctly Empennage (IX) Trim tab Stabilator trailing edge Fusolage: tail beam (X) Repeat point (VII) Left main landing gear (XI) Repeat point (VI) Left wing: rearward side (XII) Repeat point (V) Left wing: forward side (XIII) Repeat point (IV) Check inside cabin (XIV) Instruments panel Master switch ON Master switch OFF Control stick Rudder pedals Throttle & choke levers Brake lever and parking brake Trim lever Safety belts Seats Windshield Doors free movement, absence of defects, no play. absence of delaminations fixed correctly, all placards all instruments ON all instruments OFF free movement, fixed correctly in its support no distorsion, no signs of cracks, correct functionality, fixed correctly in its support, correct functionality of centring system. free movement, fixed correctly to the support Remove parking brake lock, check lever functionality. Insert parking brake. check correct functionality check correct functionality fixed correctly. clean, fixed correctly on fusolage clean, fixed correctly on fusolage, check locked system
Luggage Weight&balance BEFORE STARTING ENGINE Pre-flight check Seats Safety belts Doors Parking brake Flight controls Fuel faucets Trim secured. calculated. - completed - adjusted - adjusted and fastened - closed and locked - ON - full movement and free - LH open, RH closed - Neutral Page: 31 of 71 ENGINE START Choke lever: Engine cold - ON (all rearward) Engine warm - OFF (all forward) Electric fuel pump - ON for 10 sec. then OFF Throttle - At minimum + 1 cm. Master key - ON Generator warning lamp - ON Ignition magnets switch - each magnetos ON WARNING: Ensure that the propeller area is clear of any person or object CLEAR PROP Start button - Max 20 sec of starting, rest one minute before retrying Throttle - 2500 RPM for R912 UL -1200 RPM for Jabiru 2200 Oil pressure - Green arc in 5 sec. Generator warning lamp - OFF Electric fuel pump - OFF BEFORE TAXIING Electrical system - ON and checked Navigation instruments - checked Flaps - Position to take off (15 ) Parking brake - OFF TAXIING Brakes Flight control Flight instruments Throttle - check both operate equally - free full movement, stick and pedals - Check magnetic compass and set altimeter and set gyro s if fitted. - As necessary
Page: 32 of 71 ENGINE CHECK Rotax 912 UL Jabiru 2200 Parking brake - ON - ON Fuel tank faucets - LH Open, RH Closed - LH Open, RH Closed Temperature & pressure - Within limits, in green arc - Within limits, in green arc Trim - Neutral - Neutral Flight controls - Free - Free Check magnets - 3000 RPM maximum decrease - 2000 RPM maximum decrease 300 RPM for each magnets 300 RPM for each magnets Throttle - All forward, check minimum - All forward, check minimum 5000 RPM +/- 150 for 5 sec. 3000 RPM +/- 150 for 5 sec. Check minimum RPM - 1400 RPM - 900 RPM CAUTION: Don't apply full power before 60 C of CHT. During taxing don t allow the engine CHT to exceed 135 C BEFORE TAKE-OFF Flight controls - Free Trim - Neutral Electric fuel pump - ON Flaps - Set for take-off (15º) Fuel tank faucets - LH Open, RH Closed Engine instruments - Within limits Flight instruments - Check and regulated Safety belts - adjusted and fastened Cabin doors - check both locks are engaged and locked Parking brake - OFF TAKE-OFF Aircraft Throttle lever At (40 KTS) - Align with runway - Full open smoothly - Rotation Warning: for a take off from short runway with an obstable of 15 m, use flap with 20. - Rotation - (40 KTS) - Climb speed - (48 KTS) (Vx) At an altitude of 100 m (300 ft), if a steep climb is necessary to clear obstacles Flaps - Up Trim - As necessary Speed - Vx (flap 5 ) or Vy (flap 0 ) Throttle - As necessary Electric fuel pump - Off Note : Don't maintain the flaps extendeed with speed higher than (57 KTS) (Vfe).
Page: 33 of 71 CLIMB Rotax 912 UL Jabiru 2200 Engine RPM - 5000 RPM. - 3000 RPM. Engine instruments - Within limits - Within limits Trim - As necessary - As necessary CRUISE Rotax 912 UL Jabiru 2200 Throttle - As necessary - As necessary Engine RPM - Max continuos power 5500 rpm - Max continuos power 3300 rpm Engine instruments - Within limits - Within limits WARNING Check frequently engine instruments, do not overcome limits. Check fuel tank level. DESCENT Altimeter Warm air at carburetto system Throttle Trim Engine instruments LANDING Speed Flap Trim Throttle Electric fuel pump Parking brake check (see note b) Final Approach speed Touch down speed - Setting - As necessary - As necessary - As necessary - Within limits - (57 KTS) - As necessary - As necessary - As necessary - ON - Check - (48 KTS) - (40 KTS) NOTE: a) In condition of strong lateral wind or in presence of wind-shear, increase the landing speed at least (5 KTS) b) Before landing check brake system pressure by operating the brake lever a couple of times if the braking system is serviceable you should feel the resistance when pressure is applied. TOUCH & GO Throttle - All forward Trim - As necessary Flap - 15 Speed - Vx (flap 5 ) o Vy (flap 0 ) If you touch the ground repeat take off procedure.
Page: 34 of 71 AFTER LANDING Throttle Flaps Electric fuel pump Brakes ENGINE SHUTDOWN Throttle Parking brakes Electrical equipment Magnetos Master switch Fuel tank faucets - Idle - UP - OFF - Check functionality with warm brakes - Idle - ON - OFF - OFF (one by one) - OFF - closed 4.5 FLIGHT INSIDE OF HEAVY RAIN Flying inside heavy rain is forbidden as visibility and performance of the flight is reduced, however if unavoidable reduce speed to (80 KTS) and remember to increase the landing speed by at least (5 KTS) with wet wing.
SECTION 5 - Performances Page: 35 of 71 Title 5.1 General informations 36 Page
5.1 GENERAL INFORMATIONS Page: 36 of 71 This section contains all the performance data required for accurate pre-flight planning. SCHEME OF TAKE-OFF & LANDING PHASES Figure 5-1 show the take-off and landing phases and medium value recorded SPEED CONVERSION (DENSITY ALTITUDE) The density altitude chart (figure 5-2) is provided to determine the density altitude for outside air temperature and pressure altitude combinations. UNIT CONVERSION Figure 5-3 shows the linear scales for conversion of [Km/h KTS m/s]. Figure 5-4 shows the linear scales for conversion of [m/s - feet/min and KTS m/s]. Figure 5-5 shows the linear scales for conversion of [m feet]. DEMONSTRATED CROSS WIND COMPONENT The maximum demonstrated crosswind is 17 KTS Figure 5-6 shows the RELATIVE WIND DIAGRAM VERSUS WIND COMPONENT ENVELOPE DIAGRAM Figure 5.7 shows the envelope diagram.
Page: 37 of 71 Figure 5-1 Take off run Take off distance Take off speed 140 m 250 m 45 Knots Landing distance Landing run Landing speed 200 m 125 m 48 Knots Note: remember that speed and distances are indicative
Page: 38 of 71 SPEED CONVERSION (DENSITY ALTITUDE) This table help you to calculate the TAS (true airspeed) from the IAS (indicated airspeed) using the simplified formula: TAS = IAS*Cor. factor Figure 5-2
UNIT CONVERSIONS Page: 39 of 71 Figure 5-3
Page: 40 of 71 Figure 5-4
Page: 41 of 71 Figure 5-5
CROSS WIND TABLE Page: 42 of 71 Figure 5-6
ENVELOPE DIAGRAM Page: 43 of 71 Vso Stall Speed with flap 45 32 KTS Vs Stall Speed without flap 35 KTS Vfe Maximum speed with extendeed flap 579 KTS Va Maneuvering speed 70 KTS Vne Never exceed speed 118 KTS
SECTION 6 Page: 44 of 71 Weight & balance Title 6.1 Introduction 45 6.2 Weighing conditions 45 6.3 Weight & balance report 46 Page
6.1 INTRODUCTION Page: 45 of 71 This section contains the informations for a correct procedure of weight and balance of the aircraft. WARNING: exceeding the Centre of Gravity limits can provoke serious problems of stability and govern-ability of the aircraft. 6.2 WEIGHING CONDITIONS For the weighing of the aircraft, the followings conditions apply: - The equipment installed must be approved by the factory for the aircraft in question. - Must be included the brake fluid, engine oil, water coolant and the non-usable fuel. - Must use three independent scales for each tire horizontal plan and of a thread to lead. - To determinate the empty weight and the position of the Center of Gravity, the aircraft must be positioned on three autonomous scales, one for each wheel. It is fundamental that the longitudinal and lateral axes of the aircraft are both in the same horizontal plane. You can verify the horizontal datum position when the tail beam side reaches 4 with reference to ground level, as shown in the figure below. Using a plum bob mark a line on the ground directly beneath the leading edge of the wing. This point is your reference datum RD. Measurements are to be taken from this point. X1 is the distance from nose wheel axle center line to projection of RD. X2 is the distance from main wheel axle center line to projection of RD. The standard distance is: X1 = 880mm (±0.5%) X2 = 460mm (±0.5%).
The formula for CG calculation is the following: Where: Xt = ML / PT. [CG position in mm on the wing chord] ML = (P2DX + P2SX) x X2 - P1 x X1 Xt% = (Xt / MAC) x 100 [CG position in percentage to the wing chord] ML = Empty weight moment P2DX, P2SX = Weight measured on main wheel P1 = Weight measured on nose wheel 6.3 WEIGHT & BALANCE REPORT Page: 46 of 71 The first recording of the Weighing Report & the Center of Gravity Position of the aircraft is taken at the factory before the delivery of the same aircraft. The Factory Weight and Balance report will accompany the Aircraft on delivery. Every variation due to the installation of new components or repairs and painting, implicate a new calculation of the empty weight and the relative positioning of the center of gravity. Any weight and Balance changes should be recorded into the aircraft log book.
Title SECTION 7 Aircraft Ground Handling and Servicing Page: 47 of 71 7.1 Aircraft ground movement 48 7.2 Aircraft ground anchorage 48 7.3 Aircraft cleaning 49 7.4 Aircraft servicing 49 Page
7.1 AIRCRAFT GROUND MOVEMENT Aircraft ground movement with engine running is as follows: - Get on board - Either lock or secure the doors - Start engine - Verify the absence of obstacles or people/animals in the aircraft vicinity - Remove the parking brake Page: 48 of 71 - Use throttle to regulate the advancement speed and use the rudder pedals for steering the aircraft - When the aircraft has reached the destination, shut off the engine, operate the parking brake and leave the aircraft. WARNING: never leave the aircraft with engine running, this can be fatal both for you and for other people/animals in the aircraft vicinity. Aircraft ground movement with engine off is as follows: - Remove the parking brake - Take the aircraft for the tail beam and pressing downward to lift the dumper - Verify the absence of obstacles or people/animals in the aircraft range - Push or pull the aircraft and direct it using only the principal wheels - Operate the parking brake An optional front wheel tow bar is available for aircraft movement. 7.2 AIRCRAFT GROUND ANCHORAGE Anchorage of the aircraft can be performed by first setting ON the park brake then secure the ropes around each upper wing strut. When tightening the rope to ground mooring DO NOT apply too much tension force, a small amount of tension will suffice to secure the aircraft without risking the potential to stress surfaces inadvertently during heavy wind conditions. If possible point aircraft into the prevailing wind as this will minimize the potential for wind cock effect. CAUTION: It is a good practice to secure the control stick from inadvertent movement by latching to the seatbelts when the aircraft is left unattended or in windy conditions.
Page: 49 of 71 7.3 AIRCRAFT CLEANING The aircraft is supplied with a kit for complete cleaning. The following procedure is suggested for cleaning the aircraft. - Do not use a pressure cleaner directly on the aircraft, as the gel-coat is hygroscopic. - Use a micro-fiber cloth and neutral soap to clean the aircraft. - Avoid water bathing of metallic parts. - Rinse with a damp and clean micro-fiber cloth. - Dry excess moisture using a deerskin, natural or synthetic chamois. - The cockpit can be cleaned with a dry micro-fiber cloth and a vacuum cleaner. CAUTION: to avoid corrosion problems make sure that the metallic parts are not left damp. The use of a water dispersant spray and or approved lubricant is advised. 7.4 AIRCRAFT SERVICING Servicing fuel - Make sure the plane is set on the parking brake. - Open the fuel cap. - Pour in fuel as per specification. - Check that the amount poured equates to the reading from the dipstick. - Close the cap and make sure the fuel cap vent is directed to the front. - Make sure no spilled fuel is left on the plane. Remove if necessary. Servicing Oil - Remove top cowling. - Make sure the ignition and both magnetos are off. - Turn propeller 5-6 times in the normal direction for flight. - Open the oil tank cap and check the level of the oil by the dipstick. - Oil should read within marked limits. - Add oil if necessary. - Close the cap. Servicing Coolant (Rotax engine) - Remove the top cowling. - Open the cap of the coolant tank and add coolant to fill up the tank. - Make sure the ignition and both magnetos are off. - Turn propeller 5-6 times in the normal direction for flight - Make sure that no air is inside the cooling system. - Close the coolant tank cap and if necessary add coolant to the expansion tank.
Page: 50 of 71 NOTE:
Title SECTION 8 Aircraft Check Lists Page: 51 of 71 8.1 Aircraft on board check lists 52 8.2 Aircraft ground pre flight check list 56 (NOTE: these pages can be cut out and plasticize) Page
Storch S 912 UL - Check list (page 1) Storch S 912 UL - Check list (page 2) PRE-FLIGHT CHECK - completed TAXIING Seats - adjusted Brakes - check both operate equally Safety belts - adjusted and fastened Flight control - free full movement, stick and pedals Doors - closed and locked Flight instruments - Check magnetic compass, gyro's Parking brake - ON and set altimeter QNH Flight controls - free and full movement Throttle - As necessary Fuel faucets - LH open, RH closed ENGINE CHECK Trim - Neutral Fuel tank faucets - LH Open, RH Closed Oil Temp & pressure. - Within limits, in green arc Trim - Neutral ENGINE START Flight controls - Free and full movement Choke lever: Engine cold - ON (all rearward) Check magnetos - 3000 RPM maximum decrease Engine warm - OFF (all forward) 300 RPM for each magneto Electric fuel pump - ON for 10 sec. then OFF Throttle - All forward, check minimum Throttle - At minimum + 1 cm. 5000 RPM +/- 150 for 5 sec. Master switch - ON Check minimum RPM - 1400 RPM Generator warning lamp - ON Ignition magnets key - each magnets ON BEFORE TAKE-OFF Ensure the propeller area is clear of any person or object "CLEAR PROP" Flight controls - Free Start procedure - Max 20 sec, pause one Trim - Neutral minute before retrying Electric fuel pump - ON Throttle - 1800 RPM Flaps - check for take-off position (15º) Oil pressure - Green arc in 5 sec. Fuel tank faucets - LH Open, RH Closed Generator warning lamp - OFF Engine instruments - Within limits Electric fuel pump - OFF Flight instruments - Check and regulated BEFORE TAXIING Safety belts - adjusted and fastened Electrical system - ON and checked Doors - check both locks are engaged. Navigation instruments - checked Flaps - Position for take-off (15 ) Parking brake - OFF Parking brake - OFF Ballistic parachute if fitted - Remove safety pin before flight Provincial Road n.78 Km 12.150 Page: 52 of 71
Storch S 912 UL - Check list (page 3) Storch S 912 UL - Check list (page 4) TAKE-OFF LANDING Aircraft - Align with runway Speed - (56 KTS) Throttle lever - Full open smoothly Flap - As necessary At (40KTS) - Rotation Trim - As necessary For a take off from short runway with an obstacle of 15 m, use 20 flap Throttle - As necessary - Rotation - 40 KTS Electric fuel pump - ON - Climb speed - (Vx) 48 KTS Parking brake check - Check Flaps - Up Final Approach speed - (48 KTS) Trim - As necessary Touch down speed - (40 KTS) Speed - Vx or Vy TOUCH & GO Throttle - As necessary Throttle - All forward Max power Electric fuel pump - Off Trim - As necessary CLIMB Flap - 15 Engine RPM - 5000 RPM. Speed - Vx o Vy Engine instruments - Within limits If you touch the ground repeat take off procedure. Trim - As necessary AFTER LANDING CRUISE Throttle - Idle Throttle - As necessary Flaps - UP Engine RPM - Max continuous power 5500 RPM Electric fuel pump - OFF Engine instruments - Within limits Brakes - Check functionality Warning: Check frequently engine instruments, do not exceed limits. with "warm brakes" The speeds are only indicative ENGINE SHUTDOWN Speed (90 KTS) - 4000 rpm Throttle - Idle Speed (97 KTS) - 4800 rpm Parking brakes - ON Speed (100 KTS) - 5000 rpm Electrical equipment - OFF Speed (105 KTS) - 5500 rpm Magnetos -OFF (one by one) DESCENDING Master switch - OFF Altimeter - Setting Fuel tank faucets - closed Carburetor heat - As necessary Throttle - As necessary Trim - As necessary Engine instruments - Within limits Provincial Road n.78 Km 12.150 Page: 53 of 71
Storch S Jabiru 2200 - Check list (page 1) Storch S Jabiru 2200 - Check list (page 2) PRE-FLIGHT CHECK - completed TAXIING Seats - adjusted Brakes - check both operate equally Safety belts - adjusted and fastened Flight control - free full movement, stick and pedals Doors - closed and locked Flight instruments - Check magnetic compass, gyro's Parking brake - ON and set altimeter QNH Flight controls - free and full movement Throttle - As necessary Fuel faucets - LH open, RH closed ENGINE CHECK Trim - Neutral Fuel tank faucets - LH Open, RH Closed Oil Temp & pressure. - Within limits, in green arc Trim - Neutral ENGINE START Flight controls - Free and full movement Choke lever: Engine cold - ON (all rearward) Check magnetos - 2000 RPM maximum decrease Engine warm - OFF (all forward) 300 RPM for each magneto Electric fuel pump - ON for 10 sec. then OFF Throttle - All forward, check minimum Throttle - At minimum + 1 cm. 3000 RPM +/- 150 for 5 sec. Master switch - ON Check minimum RPM - 900 RPM Generator warning lamp - ON Ignition magnets key - each magnetos ON BEFORE TAKE-OFF Ensure the propeller area is clear of any person or object "CLEAR PROP" Flight controls - Free Start procedure - Max 20 sec, pause one rim - Neutral minute before retrying Electric fuel pump - ON Throttle - 1200 RPM Flaps - check for take-off position (15º) Oil pressure - Green arc in 5 sec. Fuel tank faucets - LH Open, RH Closed Generator warning lamp - OFF Engine instruments - Within limits Electric fuel pump - OFF Flight instruments - Check and regulated BEFORE TAXIING Safety belts - adjusted and fastened Electrical system - ON and checked Doors - check both locks are engaged Navigation instruments - checked Flaps - Position for take-off (15 ) Parking brake - OFF Parking brake - OFF Ballistic parachute if fitted - Remove safety pin before flight Provincial Road n.78 Km 12.150 Page: 54 of 71
Storch S Jabiru 2200 - Check list (page 3) Storch S Jabiru 2200 - Check list (page 4) TAKE-OFF LANDING Aircraft - Align with runway Speed - (56 KTS) Throttle lever - Full open smoothly Flap - As necessary At (40KTS) - Rotation Trim - As necessary For a take off from short runway with an obstacle of 15 m, use 20 flap Throttle - As necessary - Rotation - 40 KTS Electric fuel pump - ON - Climb speed - (Vx) 48 KTS Parking brake check - Check Flaps - Up Final Approach speed - (48 KTS) Trim - As necessary Touch down speed - (40 KTS) Speed - Vx or Vy TOUCH & GO Throttle - As necessary Throttle - All forward Max power Electric fuel pump - Off Trim - As necessary CLIMB Flap - 15 Engine RPM - 3000 RPM. Speed - Vx o Vy Engine instruments - Within limits If you touch the ground repeat take off procedure. Trim - As necessary AFTER LANDING CRUISE Throttle - Idle Throttle - As necessary Flaps - UP Engine RPM - Max continuous power 5500 RPM Electric fuel pump - OFF Engine instruments - Within limits Brakes - Check functionality Warning: Check frequently engine instruments, do not exceed limits. with "warm brakes" The speeds are only indicative ENGINE SHUTDOWN Speed (94 KTS) - 2200 rpm Throttle - Idle Speed (97 KTS) - 2800 rpm Parking brakes - ON Speed (100 KTS) - 3000 rpm Electrical equipment - OFF Speed (105 KTS) - 3300 rpm Magnetos -OFF (one by one) DESCENDING Master switch - OFF Altimeter - Setting Fuel tank faucets - closed Carburetor heat - As necessary Throttle - As necessary Trim - As necessary Engine instruments - Within limits Provincial Road n.78 Km 12.150 Page: 55 of 71
Page: 56 of 71 Remove all the protections 1. pitot-cover, 2. wheels stops, 3. mobile surfaces stops, 4. windshiel covering, 5. propeller protection 6. fuel draining procedure Fusolage: left forward side (I) Fixing axle bolts check correct tightness Wheel fairing good conditions and free space between the wheel and it. Tire general good condition, inflated correctly Damper no signs of cracks or distorsion, free movement Nose wheel support structure no signs of cracks or distorsion. Alignment check damper-rudder alignment Fusolage: left forward side (I) Fixing axle bolts check correct tightness Wheel fairing good conditions and free space between the wheel and it. Tire general good condition, inflated correctly Damper no signs of cracks or distorsion, free movement Nose wheel support structure no signs of cracks or distorsion. Alignment check damper-rudder alignment Fusolage: frontal side (II) Hub & blades Spinner no signs of cracks & clean. no signs of cracks, fixed correctly Fusolage: right forward side (III) Upper cowling remove Oil tank check level (for R 912UL remove the cap inside fusolage) Coolant tank check level (for R 912UL remove the cap inside fusolage) Radiator and air inlet no signs of cracks, free from obstructions Engine clean, no oil or coolant leakage Muffler & silencer manifold no signs of cracks, muffler hooked. Oil and coolant tube system correct functionality, no leakage Ignition & electric system correct functionality. Throttle & choke cables free movement Upper cowling reinstall and check tightness Right wing: forward side (IV) Wing surface absence of buckling absence of delaminations Leading edge absence of delaminations, Wing strut mount check joint, no signs of cracks Pitot tube no defects, fixed correctly, check tubes joint Right wing: rearward side (V) Trailing edge absence of delaminations, no signs of cracks Flap & aileron absence of delaminations, no signs of cracks, free movement, no excessive play on hinges, fixed correctly, balancing mass fixed correctly, no signs of lateral movement. Right main landing gear (VI) Leg no distorsion, bolts locked, no sign of cracks on the weldings Brake assembly condition and tightness Tire general good condition, inflated correctly Wheel fairing good conditions and free space between the wheel and fairing. Fusolage: tail beam (VII) Tail beam Bowden cables Check joint tail beam/fusolage Check fixing
Page: 57 of 71 Empennage (VIII) Vertical fin Rudder absence of buckling, absence of delaminations, check all rivets absence of delaminations, hinges fixed correctly Lower the tail of the aircraft to lift the nose wheel, check the free movement of the rudder, any problem on the hinge. Bowden cables Stabilator Stabilator hinge Balancing mass Hinge pins fixed correctly. free movement during all travel range, absence of buckling, absence of delaminations absence of delaminations, fixed correctly, no play fixed, no play fixed correctly Empennage (IX) Trim tab free movement, absence of defects, no play. Stabilator trailing edge absence of delaminations Fusolage: tail beam (X) Repeat point (VII) Left main landing gear (XI) Repeat point (VI) Left wing: rearward side (XII) Repeat point (V) Left wing: forward side (XIII) Repeat point (IV) Check inside cabin (XIV) Instruments panel fixed correctly, all placards Master switch ON all instruments ON Master switch OFF all instruments OFF Control Stick free movement, fixed correctly in its support Rudder pedals no distorsion, no signs of cracks, correct functionality, fixed correctly in its support, correct functionality of centring system. Throttle & choke levers free movement, fixed correctly in the support Brake lever and parking brake Remove parking brake lock, check lever functionality. Insert parking brake. Trim lever check correct functionality Safety belts check correct functionality Seats fixed correctly. Windshield clean, fixed correctly on fusolage Doors clean, fixed correctly on fusolage, check locking system Luggage secured. Weight&balance calculated.
Page: 58 of 71 TRAINING MANUAL 00 11/10/07 Complete manual revision Num Date Description. REVISION Issued Verified Approved FlySynthesis s.r.l. reserves it to terms of law the exclusive ownership of this manual and also forbids the partial reproduction of it.
Page: 59 of 71 INDEX Title Section Page General information 60 Introduction 1 61 Fuel and Fuel/Oil consumption 2 62 Engine controls 3 65 Seat belts 4 65 Cockpit entry and Pilot etiquette 5 65 Flight controls 6 67 Ground handling 7 70 Recommended on board tools 8 71
Page: 60 of 71 Title SECTION 1 General information Page 1. Introduction 61 1.1 Notice to operators 61 2. Fuel and Fuel/Oil Consumption 62 2.1 Fuel tank capacity 62 2.2 Re Fueling 63 2.2 Oil 64 3. Engine controls 65 3.1 Engine indicators 65 4. Seat belts 65 5. Cockpit entry and pilot etiquette 65 5.1 Cabin door operation 66 6. Flight controls 67 6.1 Flap system 68 6.2 Landing Gear 68 6.3 Tire pressure 69 6.4 Brake system 69 7. Ground handling 70 7.1 Aircraft tie down 70 8. Recommended on board tools 71
Page: 61 of 71 1. INTRODUCTION This Flight Training supplement is designed for maximum utilisation as an operating guide. This manual is intended to offer further specific detail of relevant information useful when the Storch S is used as a training platform. This supplement is not designed as a substitute for adequate and competent flight instruction, knowledge of current procedures and a sound knowledge of the aircrafts systems and limitations. This manual should be read in conjunction with the Pilot Operating Handbook. The pilot in command is responsible for determining that the aircraft is safe for flight and for remaining within the operating limitations as outlined by the instrument markings, placards, operating manual and this flight-training supplement. 1.1 NOTICE TO OPERATORS 1. Unless fitted with the optional flight timer operated by an air switch the standard (Hobbs) hour meter will run anytime the master key is switched ON. NOTE: TURN OFF MASTER KEY SWITCH WHEN AIRCRAFT NOT IN USE When carrying out the pre start check, follow the check list and ensure the time between Master on and engine start is minimal. (a) To reduce the battery drain (b) To keep the VDO time as close as possible to engine running time. (c) If the aircraft is fitted with an air switch, the reading obtained from the air switch clock can be used for purposes of airframe and engine maintenance. 2. The checking of the rudders is NOT to be carried out whilst the aircraft is stationary. The checking of the rudders should only be carried out while taxiing. Moving the rudder pedals on any aircraft with nose wheel steering, whilst it is stationary, will over stress the rudder mechanism. 3. Prior to leaving the aircraft, after the parking check is complete, leave the parking brake off and turn the fuel cocks OFF (a) Chock the aircraft as soon as practical to prevent accidental movement. (b) Prevents hydraulic pressure being trapped in the lines for long periods. (c) Prevents fuel from transferring across with uneven ground.
Page: 62 of 71 4. Please refrain from placing the headset on the instrument combing panel as it may scratch the underside of the windscreen. The headset should be placed on appropriate hooks if available or in the rear baggage compartment. 5. It is not good airmanship to leave the flight controls unrestrained, especially in windy conditions. Always restrain the control stick by using the seat belt, to reduce any possibility of damage to the flight control mechanism. 2. FUEL AND FUEL/OIL CONSUMPTION This section relates to Fuel / Oil consumption, type and capacity. Rotax 912 UL Jabiru 2200A Economy cruise 16 Litres p/h N/A For cruise 18.5 Litres p/h 13 Litres p/h For takeoff and climb 20 Litres p/h 21 Litres p/h Rotax Normal Fuel Premium unleaded MOGAS >95 RON Jabiru Normal Fuel AVGAS 100 LL Rotax engines NOTE: Due to the higher lead content in AVGAS, the wear of the valve seats, the deposits in the combustion chamber and lead sediments in the lubrication system will increase. Therefore only use AVGAS if other fuel types are not available. For detailed information on the approved fuels, refer to the ROTAX and JABIRU operator s manual. Jabiru recommends using AVGAS 100LL, AVGAS 100/130 and MOGAS with Minimum 95 RON. Do not use fuel additives such as Octane boosters or MOGAS with any level of added Alcohol. 2.1 FUEL TANK CAPACITY: - Fuel tank capacity 2 x 45 L - Un usable fuel 2 x 2 L - Usable fuel 86 L NOTE: It is good practice to allow a minimum of 45 minutes of reserve fuel on board.
Page: 63 of 71 Pic 1 Left & Right Low fuel warning lamps Pic 2 Fuel tank dipstick 2.2 RE FUELING The Storch S 500 is refuelled by the fuel caps located on top of the port and starboard wing. Each tank is fitted with a fuel measuring dip stick to determine approximate quantity. In most cases a ladder may be required for bowser filling. CAUTION: If an Earth cable is available at the refueling station it must be connected to the Aircraft earth located at the front nose leg. If fitted, the (optional) on board electric re fuelling pump can siphon the fuel directly from a jerry can and supply each tank providing the fuel tap is selected ON for that tank. The Auxiliary fuel pump switch is located on the central control panel and can be operated with out the Master switch being on. A fuel hose with built in fuel filter is supplied when this option is available. Pic 1 Re fuelling direct from Jerry Can Pic 2 Fuel tank selector Taps NOTE: Smoking during re fuelling is strictly prohibited. Re fuelling must be done outdoors and not in aircraft hangars. Clean and wipe up any spilled fuel.
Page: 64 of 71 2.3 Oil Prior to checking the engine oil level, turn the propeller by hand several times to pump the oil from the engine in to the oil tank. This process is finished when air is returning back to the oil tank and can be noticed by a murmur from the open oil tank. Oil level should be between the min and max mark, but never below the minimum mark. Prior to longer periods of operation ensure that the oil level is at least up to the mid position. Oil Quantity Normal Rotax 3.0 liters Jabiru 3.4 liters Minimum oil consumption 0.1 l/hr 0.1 l/hr For detailed information on recommended oil grades refer to the ROTAX and JABIRU operator s manual. Recommended engine oils for Rotax engines running on Unleaded Auto Fuel Oil Capacity: 3.0 Litres MOBIL 1 (5w- 30) or (15W-50) SHELL Advance VSX 4 (10W-40) or (15W-50) SHELL Advance Ultra 4 (10W-40) VALVOLINE Dura blend Synthetic (10W-40) PENNZOIL Motorcycle Motor Oil (20W-50) Recommended engine oils for Rotax engines running on AVGAS fuel SHELL Advance VSX 4 (10W-40) or (15W-50) SHELL Formula (10W-30) or (20W-50) SHELL Formula Synthetic Blend (10W-30) VALVOLINE Dura blend Synthetic (10W-40) NOTE: Remeber if using AVGAS in Rotax engine the Engine oil will require more regular oil changes. Recommended engine oils for Jabiru 2200A engines running on AVGAS fuel Oil Capacity: 3.4 Litres AEROSHELL W100 or equivalent.
3. ENGINE CONTROLS Page: 65 of 71 Engine power is controlled by a push pull throttle control lever, operating both carburettors simultaneously. A choke is provided for starting a cold engine. The twin-magneto ignition system is controlled by the key operated switch. The electrical bus system is activated by the Master switch and needs to be ON for the magneto key switch to be operable. An Electric fuel pump supplies fuel pressure prior to the engine starting and running and is used as back up for the engine driven fuel pump in case of failure. 3.1 ENGINE INDICATIONS The rpm indicator indicates engine speed (RPM). This is an electronic unit. The cylinder head temperature (CHT) indicator shows engine temperature. The oil pressure indicator indicates oil pressure. A separate indicator indicates the oil temperature. An Exhaust Gas Temperature system (EGT) is also installed. The fuel pressure indicator indicates fuel pressure with the engine pump and/or aux electric fuel pump in use. This fuel pressure indicator is a mechanical unit. A standard sealed accumulating hours-meter (Hobbs meter), counts the total time the ignition key is switched on. An optional air switch may be fitted that accumulates time on an air switch clock when the aircraft attains a speed greater than 30 knots. The air switch time can be used for purposes of airframe and engine maintenance. 4. SEAT BELTS AND SEAT ADJUSTMENTS Pilot and passenger seats are made from a chromemoly steel frame with padded sponge seat cushions. The seats can be easily removed to enable inspection of the controls below the seat. Each seat can be adjusted fwd and aft as well as the recline position to suit pilot and passenger s size. WARNING: Never try to change seat adjustment in flight! Each seat is equipped with safety belts, which are locked together with a bayonet quick release latching system. The safety belts are attached to the main structure and each can be adjusted for occupant comfort. Belts should be replaced if frayed, cut, stitching is broken or latching defective. 5. COCKPIT ENTRY AND PILOT ETIQUETE Entry into cockpit is achieved by entering rear end first. By placing your bottom on the lower door sill you are now able to hoist yourself into the cabin seat. Once seated swing one leg at a time over the control stick so that both feet now reach the pedals. DO NOT Step onto the wheel fairing in an attempt to hoist your body into the cabin as doing so may damage the wheel fairing. See pic 1and 2 below.
Page: 66 of 71 Pic 1 Hoisting on board. 5.1 CABIN DOOR OPERATION Pic 2 Do Not use the wheel fairing as a means of hoisting into the cabin. The Storch doors are made from composite material and clear Lexan. The gull type doors are hinged at the top and can be locked in the open position for entry and exit. Doors can be removed for summertime operation and wind deflectors attached to minimise turbulence within the cabin. WARNING: Never try to open the doors during the flight! Ensure they are fully locked. Pic 1 Door in locked position Pic 2 Door removed and wind deflector installed
Page: 67 of 71 6. FLIGHT CONTROL The airplane has standard three axis controls, with dual stick and dual rudder pedals. All control surfaces are made from composite material. The control surfaces are mounted on metal hinges and in-turn operated by metal mechanisms. All three control surfaces are mass weight balanced to prevent flutter. The pitch is controlled by the stabilator, commonly known as flying tail. There is no fixed elevator section and a negatively geared trim tab is used to position the stabilator in the correct pitch and also to trim the aircraft. The two control sticks in the cockpit are inter-connected and Bowden type push-pull cable rods transfer the movement to the stabilator. The mechanical trim is achieved by changing the zero position of the geared tab. The manual trim lever is positioned centrally above the head of the pilot and it moves the trim through a push-pull flexible cable, Roll control is by ailerons. Push-pull rods operate the ailerons. These are differential ailerons where the angular movement up is greater then the angular movement down. Directional control is by a rudder installed on the vertical fin stabilizer. Rudder pedal motion is transmitted via Bowden flexible steel cables rods to the rudder bell-crank. The rudder pedals are connected at the front of the aircraft to the steerable nose wheel, which completes the rudder control loop. Tensioned shock rope helps to centralize the rudder and improve pilot's control feel. CAUTION Do not operate rudder pedals whilst stationary. Excessive pressure applied to rudder pedals may result in damage to the rudder control pedal structure. Pic 1 Trim lever Pic 2 Trim tab (anti servo) Roll control is by ailerons. Push-pull rods operate the ailerons. These are differential ailerons where the angular movement up is greater than the angular movement down. Directional yaw control is by a rudder installed on the vertical fin. Rudder pedal motion is transmitted via a flexible steel cable to the rudder bell crank.
Page: 68 of 71 6.1 FLAP SYSTEM The flap surfaces are constructed of composite materials. Each flap is attached to the wing by 2 hinges. Both flaps are mechanically interconnected. This is asymmetry protection. See pic 2 below Flap operation is achieved by a 3-position spring return switch mounted on the central console. The switch operates an electric motor through a reduction gearbox, located within the right hand wing. See pic 1 below The motor, through the reduction gearbox and a screw jack transmits the motion into the flaps interconnecting torque shafts. An angular position transducer installed near the gearbox transmits the flap position to the flap indicator on the instrument panel. Pic 1 Flap selector switch and Flap angle indicator Pic 2 Flaps in full flap position 6.2 LANDING GEAR Main gear track 1.640 m Main wheel Nose wheel base 1.340 m The main gear assembly consists of a main spar, made of steel tube and bolted at four points to the fuselage structure underneath the seating area. The landing gear struts are made of high strength spring steel and bolted into the gear spar. Providing they are not bent due to heavy landings can be used indefinitely. Alternatively Ergal alloy steel landing gear struts are available and have a time limited period of 300 hours. Main gear shock absorption is by the elasticity of the leg. Each wheel of the main gear is equipped with a disk brake.
Page: 69 of 71 6.3 TIRE PRESSURES It is essential to maintain your tires in good condition. When checking tire pressure, examine for tire wear, cuts, bruises and slippage. Remove oil, grease and mud from tires with soap and water. NOTE: Recommended tire pressures should be maintained, especially in cold weather. Any drop in temperature of air inside the tire causes a corresponding drop in tire pressure. Main wheel tire 4.00x6 or (13x5x6), inflation pressure 2.2 2.4 bar (32 35 psi) Large main wheel tire 15x6x6, inflation pressure 2.2 2.4 bar (32 35 psi) Nose wheel tire 4.00x4, (100/75-5) inflation pressure: 1.8 bar (26.1 psi) NOTE: When doing long distance cross country exercises it would be advisable to carry a spare tube or puncture repair kit especially if you re likely to land on rough strips. A minimum set of tools would also be required for field repairs, see section 8. 6.4 BRAKE SYSTEM Hydraulically operated disk brakes are installed on each main wheel. Both brakes are actuated by the one brake lever mounted centrally between the seats. Pulling the brake lever operates both brakes. The braking force will increase by the same amount of pressure applied on the brake lever. The hand brake locking lever is mounted on the main brake lever. Application of the hand brake is effected by raising the main brake lever and then pushing down the small park lever to lock in the braking pressure. Once operated the hand brake assures efficient braking for 10 minutes, necessary for a pre-flight engine check or short parking time. See pic 1and 2 below. Pic 1 Parking brake lever disengaged Pic 2 Parking brake lever engaged
Page: 70 of 71 7. GROUND HANDLING Aircraft ground movement with engine off is as follows: - Remove the parking brake if ON. - Rotating the aircraft is best achieved by holding down the tail beam which will lift the front wheel off the ground allowing the main wheels to act as a pivot. See pic 1 below - Moving the aircraft forward or backward is best achieved by applying pressure to the propeller root nearest the spinner. See pic 2 below. - When the aircraft is in its desired place operate the parking brake, or if hangared use wheel chocks. WARNING: DO NOT apply excessive force on the front wheel to achieve steering. DO NOT press onto the spinner itself. Pic 1 Push down to lift the front wheel off. Pic 2 Fwd & Aft movement via the prop hub 7.1 AIRCRAFT TIE DOWN Anchorage of the aircraft can be performed by first setting ON the park brake then secure the ropes around each upper wing strut. When tightening the rope to ground mooring DO NOT apply too much tension force, a small amount of tension will suffice to secure the aircraft without risking the potential to stress surfaces inadvertently during heavy wind conditions. If possible point aircraft into the prevailing wind as this will minimize the potential for wind cock effect. See pic 1 CAUTION: It is good practice to secure the control stick from inadvertent movement by latching to the seatbelts when the aircraft is left unattended or in windy conditions. See Pic 2
Page: 71 of 71 Pic 1 Wing tied down example. Pic 2 Control stick fastened. 8. RECOMMENDED ON BOARD TOOLS The Storch utilises metric fasteners throughout the aircraft and with a small list of tools most simple repairs can be carried out in the event of temporary or emergency repairs. The following tools are suggested to be carried on board when cross country flight or long distance NAV exercises are intended. Open end or ring spanners 6mm, 8mm, 10mm, 13mm Hex key set 4mm - 10mm Double sided screw driver flat head and Phillips Shifting spanner up to 20mm opening Pliers Tie down kit Flash light Puncture repair kit