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Urban Air UFM -13 LAMBADA Operations And Flight Manual

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Operations and Flight Manual
UFM – 13 LAMBADA
Serial No. 105/13
Date of Issue: 30/01/2008
Urban Air s.r.o., T.G.Masaryka 897, 562 01 Ústí nad Orlicí, Czech Republic,
Tel./fax: +420 465 582 573, E-mail: urbanair@urbanair.cz

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  • Page 1 Operations and Flight Manual UFM – 13 LAMBADA Serial No. 105/13 Date of Issue: 30/01/2008 Urban Air s.r.o., T.G.Masaryka 897, 562 01 Ústí nad Orlicí, Czech Republic, Tel./fax: +420 465 582 573, E-mail: urbanair@urbanair.cz...
  • Page 3 – – 0. Table of Contents Table of Contents..............0-11 General..................1-0 Limitations ................2-0 Emegency procedures ............3-0 Normal procedures ..............4-0 Performance ................5-0 Weight and Balance..............6-0 Aeroplane and Systems Description ........7-3 Aeroplane handling, servicing and maintenance ....8-13 Supplements................9-0 Date of Issue: 30. 1. 2008...

  • Page 4: Table Of Contents

    – – Section 1 1. General Introduction..................1-1 Certification basis ................1-1 Warnings, cautions and notes.............1-3 Descriptive data................1-4 Three-view drawing ..............1-7 Date of Issue: 30. 1. 2008...

  • Page 5: Introduction

    – – Introduction This Flight Manual provides information useful for the safe and effi- cient operation of UFM - 13 ultralight aeroplane. It also contains supplemental data supplied by the aeroplane manufacturer. Certification basis This type of aeroplane has been designed in compliance with „Požadavky na letovou způsobilost Sportovních létajících zařízení...
  • Page 6 – – Date of Issue: 30. 1. 2008...

  • Page 7: Warnings, Cautions And Notes

    – – Warnings, cautions and notes The following definitions apply to warnings, cautions and notes in the flight manual. Warning Means that the non-observation of the corresponding proce- dure leads to an immediate or important degradation of the flight safety. Caution Means that the non-observation of the corresponding proce- dure leads to a minor or to a more or less long term degradation of the...

  • Page 8: Descriptive Data

    – – Descriptive data 1.4.1 Aeroplane description UFM - 13 ultralight aeroplane is intended for recreational and cross-country flying. It is not approved for aerobatic operation. UFM - 13 is a single engine, all- fibreglass aeroplane with side-by- side seats. aeroplane equipped with fixed main...
  • Page 9 – – 1.4.2 Basic Technical data Wing Span/span with wing extension ......12.94/14.95m Area/area with wing extension......12.16/12.87m MAC ..............0.987 m Loading/loading area with wing extension ..37/34.9kg/m Flaperon area ..............0.82 m Fuselage length ..............6.6 width..............1.08 m height ..............
  • Page 10 – – Vertical tail unit height ..............1.2 area ..............1.1 rudder area ............0.44 m Landing gear wheel track ............1.54 m wheel base............4.16 m main wheel diameter........... 0.4 tail wheel diameter ..........0.2 Date of Issue: 30. 1. 2008...

  • Page 11: Three-View Drawing

    – – Three-view drawing Date of Issue: 30. 1. 2008...
  • Page 12 – – Section 2 2. Limitations Introduction..................2-1 Airspeed ..................2-1 Airspeed indicator markings............2-2 Powerplant ..................2-3 Powerplant instrument markings..........2-5 Miscellaneous instrument markings ..........2-6 Weight ..................2-7 Centre of gravity ................2-7 Approved manoeuvres ..............2-7 2.10 Manoeuvring load factors............2-8 2.11 Crew ....................2-9 2.12 Kinds of operation ...............2-9 2.13 Fuel....................2-10 2.14...

  • Page 13: Introduction

    – – Introduction Section 2 includes Operating limitations, instrument markings, and basic placards necessary for safe operation of the aeroplane, its engine, standard systems and standard equipment. Airspeed Airspeed limitations and their operational significance are shown below: Airspeed Remarks [km/h] Never exceed Do not exceed this speed in speed...

  • Page 14: Airspeed Indicator Markings

    – – Airspeed indicator markings Airspeed indicator markings and their colour-code significance are shown below: Range or value Marking Significance [IAS km/h] White 70 - 110 Positive Flap Operating Range Green 80 – 145 Normal Operating Range Manoeuvres must con- Yellow 145 –...

  • Page 15: Powerplant

    – – Powerplant Engine Manufacturer : Bombardier-Rotax GMBH Engine Model: Rotax 912 UL Power: Max. Take-off: 59,6 kW / 80 hp Max. Continuous: 58 kW / 78 hp at 5500 rpm Cruising: 53 kW / 71 hp at 4800 rpm Engine RPM: Max.
  • Page 16 – – Fuel pressure (if the fuel gauge and sensor are installed): Minimum: 0.40 bar Maximum: 0.15 bar Fuel: see 2.13 Oil: Automotive engine oil of registered brand with gear additives, but not aircraft oil (refer to engine Operator’s Manual). API classification „SF“...

  • Page 17: Powerplant Instrument Markings

    – – Powerplant instrument markings Function Minimum Normal Caution Maximum Operating Limit Range Range Range Engine speed 1400 1400-5500 5500-5800 5800 (RPM) Cylinder Head Temperature 60-100 100-150 (CHT) [° C] Temperature 90-110 110-140 [° C] 7.0 cold Pressure 1.5 – 4.0 4.0 –...

  • Page 18: Miscellaneous Instrument Markings

    – – Miscellaneous instrument markings • Fuel gauge A fuel reserve of 7 litres is indicated by a yellow warning lamp. Date of Issue: 30. 1. 2008...

  • Page 19: Weight

    – – Weight Empty weight …………………………………… 307 kg NOTE Actual empty weight is stated in SECTION 6, par. 6.2 Max. take-off weight........520 kg Max landing weight ......... 520 kg Max. baggage weight.......... 4 kg Centre of gravity Empty aeroplane C.G. position (standard) ... 32,0 %MAC Operating C.G.

  • Page 20: Manoeuvring Load Factors

    – – 2.10 Manoeuvring load factors Ude=15 m/s Ude=7.5 m/s v [km/h] Ude=-7.5 m/s Ude=-15 m/s Date of Issue: 30. 1. 2008...

  • Page 21: Crew

    – – 2.11 Crew Minimum crew............. 1 Maximum crew............ 2 2.12 Kinds of operation Day VFR flights only. Instruments and equipment for VFR flights: 1 Airspeed indicator (marked according to 2.3) 1 Altimeter 1 Vertical speed indicator 1 Magnetic compass 1 Bank indicator 2 Safety harnesses Date of Issue: 30.

  • Page 22: Fuel

    – – 2.13 Fuel automotive premium grade gasoline, leaded, according to DIN 516000,Ö-NORM C 1103 EUROSUPER RON 95 unleaded accord. to DIN 51607,Ö- NORM 1100 AVGAS 100 LL Due to higher lead content in AVGAS, the wear of valve seats and deposits in the combustion chamber will increase.

  • Page 23: Other Limitations

    – – 2.15 Other limitations • No smoking aboard the aeroplane. Date of Issue: 30. 1. 2008 2-11...

  • Page 24: Limitation Placards

    – – 2.16 Limitation placards Caution The owner (aeroplane operating agency) of this aeroplane is re- sponsible for placards readability during aeroplane service life. URBAN – AIR URBAN – AIR URBAN – AIR URBAN – AIR UFM 13 Empty weight 307 kg Max.
  • Page 25 – – Manufactured: URBAN – AIR s.r.o. Model: UFM 13 Date of produce: 2008 105/13 Registration: Empty weight: 307 kg Max. Take-Off Weight: 520 kg Permitted crew weight 25 l in fuel tank 148 kg 50 l in fuel tank 130 kg 75 l in fuel tank 112 kg...

  • Page 26: Emergency Procedures

    – – Section 3 3. Emergency procedures Introduction..................3-1 Engine failure ................3-1 In-Flight start ................3-3 Smoke and fire ................3-3 Glide ....................3-6 Landing emergencies ..............3-6 Recovery from unintentional spin..........3-9 Other emergencies..............3-10 Date of Issue: 30. 1. 2008...

  • Page 27: Introduction

    – – Introduction Section 3 provides checklist and amplified procedures for coping with emergencies that may occur. Emergencies caused by aeroplane or engine malfunctions are ex- tremely rare if proper pre-flight inspections and maintenance are practised. However, should an emergency arise, the basic guidelines de- scribed in this section should be considered and applied as necessary to correct the problem.
  • Page 28 – – 8. Ignition - off 9. Safety harness - tighten 10. Master key - switch off position before landing 11. Land Note Skip 6-10 if necessary. 3.2.3 Engine failure in flight (Forced landing) 1. Speed - keep gliding speed at 100 km/h - sinking rate cca.

  • Page 29: In-Flight Start

    – – In-Flight start 1. Speed - keep speed a bit higher at 120 km/h 2. Altitude - check 3. Landing area - choose according to altitude (safest area) 4. Master switch - on 5. Fuel valve - open 6. Choke - as necessary (for cold engine) 7.
  • Page 30 – – 3.4.2 Fire during take-off 1. Fuel valve - off 2. Throttle - full 3. Speed - 110 km/h 4. Master switch - off 5. Ignition - off 6. Land and brake 7. Abandon the aeroplane 8. Extinguish fire if possible or call fire department. Date of Issue: 30.
  • Page 31 – – 3.4.3 Fire in flight 1. Fuel valve - off 2. Throttle - full 3. Master switch - off 4. Ignition - off after using up fuel in carburettors and engine stopping 5. Choose of area - heading to the nearest airport or choose emergency landing area 6.

  • Page 32: Glide

    – – 3.5. Glide Gliding may be used in case of engine failure. 1. Speed - ~ 100 km/h 2. Flaperon - retracted 3. Instruments - within permitted limits Landing emergencies 3.6.1 Emergency landing 1. An emergency landing may be carried out due to engine fail- ure and when the engine cannot be restarted.
  • Page 33 – – 3.6.2 Precautionary landing A precautionary landing may be carried out due to low fuel and/or bad weather conditions. 1. Choose landing area, determine wind direction 2. If a COMM is installed - report your plan to land and land area location to nearest ATC 3.
  • Page 34 – – 3.6.4 Landing with a defective landing gear 1. If the main landing gear is damaged, perform touch-down at the Lowest speed possible and maintain direction during landing run, if possible 2. If the tail wheel is damaged perform touch-down at the lowest possible speed and maintain direction during landing run, if possible.

  • Page 35: Recovery From Unintentional Spin

    – – Recovery from unintentional spin Warning Intentional spins are prohibited! There is no tendency of spontaneous uncontrollable spin entry if normal pilot techniques are used. Should an inadvertent spin occur, the following recovery procedure should be used: 1. Throttle retard to idle 2.

  • Page 36: Other Emergencies

    – – Other emergencies 3.8.1 Vibration If vibrations appear:: 1. Set engine speed to power setting where the vibrations are the lowest. 2. Land at the nearest airfield or perform a precautionary landing according to 3.6.2 3.8.2 Carburettor icing Carburettor icing mostly occurs when getting into an area of ice formation.
  • Page 37 – – Section 4 4. Normal procedures Introduction..................4-1 Assembly and disassembly............4-1 Pre-flight inspection..............4-1 Normal procedures..............4-6 4.4.1 Before entering cockpit ............4-6 4.4.2 After entering cockpit ............4-6 4.4.3 Before engine starting and Engine starting......4-7 4.4.4 Engine warm up, Engine check ...........4-8 4.4.5 Taxiing..................4-9 4.4.6 Before take-off ..............4-10...

  • Page 38: Introduction

    – – Introduction Section 4 provides checklist and amplified procedures for the con- duct of normal operation. Assembly and disassembly Refer to 8.4.7 a 8.4.8 for assembly and disassembly procedures. Pre-flight inspection The pre-flight inspection is very important because an incomplete or careless inspection could allow aeroplane failure.
  • Page 39 – – ⇒ Check if ignition is switched off in the cockpit 1. Wing • Wing surface condition • Leading edge condition • check if the flaperon controls are correctly shifted in the automatic gripping 2. Wing tips • Surface condition •...
  • Page 40 – – 6. Horizontal tail • Surface condition • Attachment • Play • Free movement • check if the elevator control is correctly shifted in the automatic gripping 7. see. 5 8. see. 4 9. see. 3 10. see. 2 11.
  • Page 41 – – 13. Motor • Engine cowlings condition • Engine mount condition • Engine attachment check • (after 1 minute engine run) Oil quantity check • Cooling liquid quantity check • Fuel and Electrical system visual check • Fuel system drain Caution It is advisable to turn the propeller by hand with ignition off if the engine has been out of operation for a long time.
  • Page 42 – – • Controls - visual check check for proper function check of plays check of flaps extension check of free movement up to the stops • Check for loose items - secure papers • Canopy - Condition of attachment, cleanliness Date of Issue: 30.

  • Page 43: Normal Procedures

    – – Normal procedures 4.4.1 Before entering cockpit 1. Aeroplane surface - check of covers and caps 2. Cockpit - items inside the cockpit 3. Ignition - off 4. Master switch - off 4.4.2 After entering cockpit 1. Rudder control - free movement check - Correct? 2.

  • Page 44: Before Engine Starting And Engine Starting

    – – 4.4.3 Before engine starting and Engine starting 1. Fuel valve - on 2. Switch box - turn the key 3. Circuit breakers - in 4. Throttle - set for idling 5. Choke - according to engine temperature 6. Control stick - fully pulled 7.

  • Page 45: Engine Warm Up, Engine Check

    – – Caution The starter should be activated for max.10 sec., then 2 min. pause for engine cooling. After engine starting adjust the throttle for smooth running at 2500 rpm. Check oil pressure which should increase within 10 sec. Increase engine speed after oil pressure reaches2 bars and is steady.

  • Page 46: Taxiing

    – – 4.4.5 Taxiing The maximum recommended taxiing speed is 15 km/h The direc- tion of taxiing can be controlled by the steer able rear wheel – rudder. There is installed the lever on the control stick to operate the brakes. Keep control stick always fully pulled during taxiing.

  • Page 47: Before Take-Off

    – – 4.4.6 Before take-off 1. Brakes - fully applied 2. Rudder control - check of free movement 3. Hand control - check of free movement 4. Trim - neutral position 5. Flaperon - "TAKE-OFF" position 6. Engine controls - choke off 7.

  • Page 48: Take-Off

    – – 4.4.7 Take-off Gradually increase the throttle (max. power) to set the aeroplane into motion. The direction of take-off run can be controlled by steerable tail wheel and rudder. Slightly push the stick to lift the tail wheel – maximum to the centre position.

  • Page 49: Climb

    – – 4.4.8 Climb 1. Throttle - Max. Continuous Power 2. Speed - 110 km/h 3. Trim - adjust as needed to reduce stick pressure 4. Instruments - CHT, Oil temp. and pressure within limits. Caution If cylinder head or oil temperature exceed limits, reduce the angle of climb to increase airspeed and allow better cooling.

  • Page 50: Descent

    – – 4.4.10 Descent 1. Throttle - idling 2. Speed - 110 km/h 3. Trim - as necessary to reduce stick pressure 4. Instruments - within limits Caution When on long final or descending from a very high altitude, it is not advisable to reduce the engine Throttle control lever to idle.

  • Page 51: On Base Leg

    – – 4.4.12 On base leg 1. Speed - 110 km/h 2. Flaperon - extend to "TAKE-OFF“ position 3. Trim - adjust as required 4. Throttle - as necessary 5. Instruments - within limits 4.4.13 On final 1. Speed - 110 km/h 2.

  • Page 52: Balked Landing

    – – 4.4.15 Balked landing 1. Throttle - full 2. Engine speed - 5200 rpm 3. Flaperon - set at the "TAKE-OFF" position at a speed of 110 km/h 4. Trim - as necessary 5. Flaperon - retract at a height of 50 m 6.

  • Page 53: Engine Shutdown

    – – 4.4.17 Engine shutdown 1. Engine speed - idling 2. Instruments - engine instruments within limits 3. COMM + intercom - off 4. Ignition key - off 5. Circuit breakers - off 6. Master switch - off 7. Fuel valve - off 4.4.18 Flight in rain When flying in the rain, no additional steps are required.

  • Page 54: Feathering Of The Propeller

    – – 4.4.19 Feathering of the propeller 1 Shut off engine with ignition key (off position) 2 After the engine stops, turn propeller control lever to rear posi- tion 4.4.20 Engine restarting 1Turn the propeller control lever forward into the operating posi- tion.
  • Page 55 – – Section 5 5. Performance Introduction..................5-1 Performance................5-2 5.2.1 Airspeed indicator system calibration ........5-2 5.2.2 Stall speeds................5-3 5.2.3 Take-off performance............5-4 5.2.4 Landing ................5-4 5.2.5 Climb performance...............5-5 Additional information..............5-6 5.3.1 Cruise...................5-6 5.3.2 Endurance................5-7 5.3.3 Demonstrated crosswind performance ........5-7 Date of Issue: 30. 1. 2008...

  • Page 56: Introduction

    – – Introduction Section 5 provides approved data for airspeed calibration, stall speeds and take-off performance and additional information. The data in the charts has been computed from actual flight tests with the aeroplane and engine in good condition and using average piloting techniques.

  • Page 57: Airspeed Indicator System Calibration

    – – Performance 5.2.1 Airspeed indicator system calibration δ δ δ δ V V IAS V CAS [km/h] [km/h] [km/h] Date of Issue: 30. 1. 2008...

  • Page 58: Stall Speeds

    – – 5.2.2 Stall speeds Warning speed Stalling Speed Flaps posi- Engine Stall tion Power [km/h] [km/h] [km/h] [km/h] idling RETRACTED Wing level "TAKE-OFF“ idling stall "LANDING“ idling Note When the stall develops the aeroplane moves downward with- out pitching, is fully controllable and level flight may be recov- ered without excessive loss of altitude.

  • Page 59: Take-Off Performance

    – – 5.2.3 Take-off performance Take-off distances stated in the following table are valid at sea level and for MTOW. Take-off run Take-off distance over distance 15 m obstacle Grass 5.2.4 Landing Landing distances stated in the following table are valid at sea level and for MTOW.

  • Page 60: Climb Performance

    – – 5.2.5 Climb performance Best Rate-of-climb speed is 110 km/h IAS, corresponding Rate of climb is 5 m/s. Date of Issue: 30. 1. 2008...

  • Page 61: Additional Information

    – – Additional information 5.3.1 Cruise Regime Economy Cruise Max. Continuous Max. Take-Off Power Power Time limitation unlimited unlimited max. 5 min. Engine speed 4500 5500 5800 Altitude [m ISA] [km/h] [km/h] [km/h] Date of Issue: 30. 1. 2008...

  • Page 62: Endurance

    – – 5.3.2 Endurance In the following table are stated fuel consumptions, endurances and ranges for RPM settings of UFM – 13 ultralight aeroplane. Regime Max. Continuous Economy Power Cruise Engine speed [rpm] 5500 4500 IAS [km/h] Airspeed CAS [km/h] Fuel [l/h] consumption...
  • Page 63 – – 5.3.4 Speed polar P o la r U M F 1 3 /1 5 /R o ta x 9 1 2 1 0 0 1 2 0 1 4 0 1 6 0 1 8 0 2 0 0 (1 3 m 4 5 0 k g ) (1 5 m 4 5 0 k g ) (1 3 m 3 5 0 k g )

  • Page 64: Weight And Balance

    – – Section 6 6. Weight and Balance Introduction..................6-1 Permitted payload range .............6-2 Date of Issue: 30. 1. 2008...
  • Page 65 – – Introduction This sections contains the payload range within which the UFM-13 aeroplane may be safely operated. Procedures for weighing the aeroplane and the calculation method for establishing the permitted payload range are contained in the Technical Description, Operating, Maintenance and Repair Manual for UFM – 13 ultralight aeroplane.
  • Page 66 – – 6.2 Permitted payload range Crew and baggage weight [kg] Empty weight of airplane is 306 kg. Permitted crew weight 25 l in fuel tank 148 kg 50 l in fuel tank 130 kg 75 l in fuel tank 112 kg Section 7 full fuel tank...

  • Page 67: Aeroplane And Systems Description

    – – 7. Aeroplane and Systems Description Introduction..................7-4 Airframe..................7-4 7.2.1 Fuselage ................7-4 7.2.2 Wing ..................7-4 7.2.3 Horizontal Tail Unit (HTU)............7-4 7.2.4 Vertical tail unit (VTU) ............7-4 Controls in the cockpit..............7-5 Instrument panel................7-6 Landing gear ................7-7 Seats and Safety harness ............7-7 Baggage compartment..............7-7 Canopy ..................7-7 Engine ..................7-4...

  • Page 68: Introduction

    – – Introduction This section provides description and operation of the aeroplane and its system. Refer to Section 9, Supplements, for details of optional systems and equipment. Airframe UFM – 13 airframe is all-fibreglass monocoque construction. 7.2.1 Fuselage All-fibreglass monocoque construction with integrated seats. There are stiffening ribs inside the fuselage rear and the fin reinforced with foam.

  • Page 69: Controls In The Cockpit

    – – Controls in the cockpit Date of Issue: 30. 1. 2008...

  • Page 70: Instrument Panel

    – – Instrument panel Heating Vertical speed indicator Air speed indicator Altimeter TL-engine instrument Throttle Compass Magnetos Slip ball Switches and fuses Fuel tank valve and switch 12 V socket Main key Main fuses Fuel indicator Date of Issue: 30. 1. 2008...

  • Page 71: Landing Gear

    – – Landing gear The plane has a two wheel main landing with a tail wheel. The main fibreglass legs, main wheel size 400 x 100, hydraulically operated brakes. The steer able tail wheel of 200 x 60 size is controlled by the rud- der pedals.
  • Page 72 – – Dry sump forced lubrication. Dual breaker less capaci- tor discharge ignition. The engine is fitted with electric starter, AC generator and mechanical fuel pump. Prop drive via reduction gear with integrated shock ab- sorber. Oil quantity check Coolant quantity check Date of Issue: 30.

  • Page 73: Fuel System

    – – On-ground adjustable, 2 blade, composite propeller VARIA is at- tached to the propeller flange by means of 6 bolts, and covered with a conic spinner. 7.10 Fuel system The 100 litre main fuel tanks are an integral part of the wings, a fuel quantity sensors are located inside the wings.

  • Page 74: Electrical System

    – – 7.11 Electrical system Date of Issue: 30. 1. 2008 7-10...

  • Page 75: Pitotstatic System

    – – 7.12 Pitot-static system The pitotstatic system consists of a pitot tube on the fin and static ports located on the fuselage sides c. 1m behind the wing trailing edge. Pressure distribution to individual instruments is done through flexible plas- tic hoses.

  • Page 76: Avionics

    – – 7.14 Avionics • Flight instruments : Airspeed indicator Altimeter Compass Vertical speed indicator Slip ball • Engine instruments : The integrated engine instrument TL-engine instrument provides all engine information. • Engine rpm • Engine hours • Exhaust gases temperature •...
  • Page 77 – – 8. Aeroplane handling, servicing and mainte- nance Introduction................8-14 Aeroplane inspection periods`...........8-14 Aeroplane alterations or repairs ..........8-14 Ground handling / Road transport..........8-15 8.4.1 Towing................8-15 8.4.2 Parking ................8-15 8.4.3 Tieing-Down ...............8-16 8.4.4 Jacking ................8-17 8.4.5 Levelling ................8-4 8.4.6 Road transport ..............8-17 8.4.7 Aeroplane Assembly ............8-18 8.4.8...

  • Page 78: Introduction

    – – Introduction This section contains factory-recommended procedures for proper ground handling and servicing of the aeroplane. It also identifies certain inspection and maintenance requirements which must be followed if the aeroplane is to retain that new-plane per- formance and dependability. It is wise to follow a planned schedule of lubrication and preventive maintenance based on climatic and flying conditions encountered.

  • Page 79: Ground Handling / Road Transport

    – – If the aeroplane weight is affected by an alternation, a new weight and balance will be necessary. A revised "Weight and Balance Record / Permitted payload range" and Placard "LOAD LIMITS" must be filled out and attached to the aeroplane. Refer to the Operating, Maintenance and Repair Manual for UFM –...
  • Page 80 – – It is necessary to tie-down the aeroplane when parking outside. When the plane must be tied-down outdoors for extended periods, it is advisable to cover the cockpit canopy, and if possible, the entire aero- plane using a suitable cover. 8.4.3 Teeing-Down The aeroplane is usually tied-down after a flight day or when...

  • Page 81: Jacking

    – – 8.4.4 Jacking Because the empty weight of this aeroplane is relatively low it is easy to lift the aeroplane using 2 persons. First prepare two suitable jacks to support the aeroplane. The aeroplane should be lifted by the following parts: Press-down on the rear of the fuselage in front of the fin to lift the front and then support under the firewall.

  • Page 82: Aeroplane Assembly

    – – 8.4.7 Aeroplane Assembly Note No special qualification needed for assembling/disassembling. Degrease and clean all connecting parts and grease again using suitable lubricants. • Horizontal Tail Unit (HTU) Installation: Set the HTU on the two main pins and at the same time insert the elevator control bell into automatic grip- ping.
  • Page 83 – – • Wing Installation: Set the left half of the wing on the pins and check automatic connection of control rods. Then secure the rear auxiliary pin. Follow with the right half of the wing, insert the wing in automatic connection device and secure the rear auxiliary pin.

  • Page 84: Aeroplane Disassembly

    – – Insert the main eccentric pin, turn it 180 ° to tig hten both halves of the wing together. Then secure the main pin with a clip through the spar end and at the rear with a safety pin. Don’t forget to secure the main eccentric pin with wire.

  • Page 85: Cleaning And Care

    – – Cleaning and care Use cleaning detergents to clean aeroplane surface. Oil spots on aeroplane surface (except the canopy!) may be cleaned with appropriate degreasers. The canopy clean should be cleaned only by washing it with luke- warm water and mild detergents, using clean, soft cloth sponge or deer- skin.
  • Page 86 – – Section 9 9. Supplements Introduction..................9-1 List of inserted supplements ............9-1 Supplements inserted..............9-2 Date of Issue: 30. 1. 2008...
  • Page 87 – – Introduction This section contains the appropriate supplements necessary to safely and efficiently operate the aeroplane when equipped with various optional systems and equipment not provided with the standard aeroplane. List of inserted supplements Date Title of inserted supplement Date of Issue: 30.
  • Page 88 – – Supplements inserted Date of Issue: 30. 1. 2008...
  • Page 89 – – Service records 9.4.1 Summary of repairs, checking, parts changes etc. Operation: (reason) date hours flown sign: done by… controlled by… Date of Issue: 30. 1. 2008...
  • Page 90 – – Operation: (reason) date hours flown sign: done by… controlled by… Date of Issue: 30. 1. 2008...
  • Page 91 – – 9.4.2 Bulletin of producer Serial bulletin date remarks sign: done by… number number controlled by… Date of Issue: 30. 1. 2008...

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