Urban Air UFM - 13 LAMBADA Скачать руководство пользователя страница 62

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–

Date of Issue: 30. 1. 2008

5-7

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

Power

Economy

Cruise

Engine speed

[rpm]

5500

4500

IAS [km/h]

160

130

Airspeed

CAS [km/h]

165

132

Fuel

consumption

[l/h]

9.5

Range

[km]

825

1390

5.3.3

Demonstrated crosswind performance

Max. permitted cross wind velocity
for take-off and landing

m/s

Max. permitted head wind velocity
for take-off and landing

m/s

Содержание UFM - 13 LAMBADA

Страница 1: ...rations 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 ...

Страница 2: ......

Страница 3: ...M 1 13 3 Date of Issue 30 1 2008 0 1 0 Table of Contents 0 Table of Contents 0 11 1 General 1 0 2 Limitations 2 0 3 Emegency procedures 3 0 4 Normal procedures 4 0 5 Performance 5 0 6 Weight and Balance 6 0 7 Aeroplane and Systems Description 7 3 8 Aeroplane handling servicing and maintenance 8 13 9 Supplements 9 0 ...

Страница 4: ...LT TR RA AL LI IG GH HT T A AE ER RO OP PL LA AN NE E U UF FM M 1 13 3 Date of Issue 30 1 2008 1 0 Section 1 1 General 1 1 Introduction 1 1 1 2 Certification basis 1 1 1 3 Warnings cautions and notes 1 3 1 4 Descriptive data 1 4 1 5 Three view drawing 1 7 ...

Страница 5: ...oplane It also contains supplemental data supplied by the aeroplane manufacturer 1 2 Certification basis This type of aeroplane has been designed in compliance with Požadavky na letovou způsobilost Sportovních létajících zařízení Ultralehké letouny řízené aerodynamicky UL 2 část I Ultralight Airwor thiness Requirements UL 2 part I that is the valid Certification basis for the ULTRALIGHT category a...

Страница 6: ...F FL LI IG GH HT T M MA AN NU UA AL L F FO OR R U UL LT TR RA AL LI IG GH HT T A AE ER RO OP PL LA AN NE E U UF FM M 1 13 3 Date of Issue 30 1 2008 1 2 ...

Страница 7: ...ons 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 flight safety Note Draws the attention of any special item not directly related to safet...

Страница 8: ...The fuselage is a fibreglass shell with fibreglass seats integrated Safety belts are attached to the seats and to a shelf intended for putting off lightweight objects headphones maps etc The wing is a monospar construction with a sandwich skin com posed of two layers of fibreglass and special foam Control surfaces and empennage is of the same construction The aeroplane is controlled by dual push p...

Страница 9: ...30 1 2008 1 5 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 2 MAC 0 987 m Loading loading area with wing extension 37 34 9kg m 2 Flaperon area 0 82 m 2 Fuselage length 6 6 m width 1 08 m height 1 95 m Horizontal tail unit span 2 5 m area 1 3 m 2 elevator area 0 45 m 2 ...

Страница 10: ...RA AL LI IG GH HT T A AE ER RO OP PL LA AN NE E U UF FM M 1 13 3 Date of Issue 30 1 2008 1 6 Vertical tail unit height 1 2 m area 1 1 m 2 rudder area 0 44 m 2 Landing gear wheel track 1 54 m wheel base 4 16 m main wheel diameter 0 4 m tail wheel diameter 0 2 m ...

Страница 11: ...F FL LI IG GH HT T M MA AN NU UA AL L F FO OR R U UL LT TR RA AL LI IG GH HT T A AE ER RO OP PL LA AN NE E U UF FM M 1 13 3 Date of Issue 30 1 2008 1 7 1 5 Three view drawing ...

Страница 12: ...Airspeed 2 1 2 3 Airspeed indicator markings 2 2 2 4 Powerplant 2 3 2 5 Powerplant instrument markings 2 5 2 6 Miscellaneous instrument markings 2 6 2 7 Weight 2 7 2 8 Centre of gravity 2 7 2 9 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 Maximum passenger seating 2 10 2 15 Other limitations 2 11 2 16 Limitation placards 2 ...

Страница 13: ... Airspeed Airspeed limitations and their operational significance are shown below Airspeed IAS km h Remarks VNE Never exceed speed 200 Do not exceed this speed in any operation VNO Maximum structural cruising speed 145 Do not exceed this speed except in smooth air and then only with caution VA Manoeuvring speed 135 Do not make full or abrupt control movement above this speed because under certain ...

Страница 14: ...ed indicator markings Airspeed indicator markings and their colour code significance are shown below Marking Range or value IAS km h Significance White arc 70 110 Positive Flap Operating Range Green arc 80 145 Normal Operating Range Yellow arc 145 200 Manoeuvres must be con ducted with caution and only in smooth air Red line 200 Maximum speed for all opera tions ...

Страница 15: ...cturer 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 Take off 5800 rpm max 5 min Max Continuous 5500 rpm Cruising 4800 rpm Idling 1400 rpm Cylinder head temperature Minimum 60 C Maximum 150 C Oil temperature Minimum 50 C Maximum 140 C Opt operating 90 C 100 C ...

Страница 16: ...m 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 or SG Propeller VARIA 160 2 R Propeller diameter 1600 mm Warning The Rotax 912 UL has not been certified as an aircraft engine and its failure may occur at any time The pilot is fully responsi ble for consequences o...

Страница 17: ...10 140 140 Oil Pressure bar 1 5 1 5 4 0 4 0 5 0 7 0 cold engine starting Note In the TL engine instrument memory are stored the limits of 1 st and 2 nd level for Rotax 912 engine The values of limits are stated in Op erator s Manual for the TL engine instrument A limit overrun is indi cated by indicating lamp flashing and stored in the TL engine instru ment memory for further evaluation Make note ...

Страница 18: ... AL L F FO OR R U UL LT TR RA AL LI IG GH HT T A AE ER RO OP PL LA AN NE E U UF FM M 1 13 3 Date of Issue 30 1 2008 2 6 2 6 Miscellaneous instrument markings Fuel gauge A fuel reserve of 7 litres is indicated by a yellow warning lamp ...

Страница 19: ...tated in SECTION 6 par 6 2 Max take off weight 520 kg Max landing weight 520 kg Max baggage weight 4 kg 2 8 Centre of gravity Empty aeroplane C G position standard 32 0 MAC Operating C G range 20 35 MAC 2 9 Approved manoeuvres Aeroplane Category NORMAL The aeroplane is approved for Normal and Manoeuvres listed be low Steep turn not exceeding 60 bank Warning Aerobatics intentional spins and stalls ...

Страница 20: ...O OR R U UL LT TR RA AL LI IG GH HT T A AE ER RO OP PL LA AN NE E U UF FM M 1 13 3 Date of Issue 30 1 2008 2 8 2 10 Manoeuvring load factors 4 3 2 1 0 1 2 3 4 5 6 0 50 100 150 200 v km h n A D G Ude 15 m s Ude 15 m s Ude 7 5 m s Ude 7 5 m s E ...

Страница 21: ... UF FM M 1 13 3 Date of Issue 30 1 2008 2 9 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 ...

Страница 22: ... 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 There fore use AVGAS only if other fuel types are not available BA 95 Natural is recommended for Czech Republic For other suitable fuel types refer to the engine Operator s Manual 2 14 Maximum passenger seating Number of seat 2 Minimum crew weight 65 ...

Страница 23: ...L LI IG GH HT T M MA AN NU UA AL L F FO OR R U UL LT TR RA AL LI IG GH HT T A AE ER RO OP PL LA AN NE E U UF FM M 1 13 3 Date of Issue 30 1 2008 2 11 2 15 Other limitations No smoking aboard the aeroplane ...

Страница 24: ... placards Caution The owner aeroplane operating agency of this aeroplane is re sponsible for placards readability during aeroplane service life UFM 13 URBAN AIR URBAN AIR URBAN AIR URBAN AIR Empty weight 307 kg Max Take off weight 520 kg Min crew weight 65 kg Max baggage weight 4 kg Never exceed speed VNE 200 km h Stalling speed Vso 65 km h Fuel tank capacity 2 x 50 l ...

Страница 25: ...M 1 13 3 Date of Issue 30 1 2008 2 13 Manufactured URBAN AIR s r o Model UFM 13 Date of produce 2008 S N 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 full fuel tank 94 kg half an hour flight 157 kg ...

Страница 26: ... PL LA AN NE E U UF FM M 1 13 3 Date of Issue 30 1 2008 3 0 Section 3 3 Emergency procedures 3 1 Introduction 3 1 3 2 Engine failure 3 1 3 3 In Flight start 3 3 3 4 Smoke and fire 3 3 3 5 Glide 3 6 3 6 Landing emergencies 3 6 3 7 Recovery from unintentional spin 3 9 3 8 Other emergencies 3 10 ...

Страница 27: ...guidelines de scribed in this section should be considered and applied as necessary to correct the problem For best glide ratio speeds and performance please see section 5 performance 3 2 Engine failure 3 2 1 Engine failure during take off run 1 Throttle retard to idle 2 Ignition off 3 2 2 Engine failure immediately after take off 1 Speed keep gliding speed at 100 km h sinking rate cca 1 25 m s 2 ...

Страница 28: ...ip 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 1 25 m s 2 Altitude below 50 m land in take off direction over 50 m choose landing area 3 Wind evaluate direction and velocity 4 Landing area choose free area without obstacles 5 Flaperon extend as needed 6 Air brake extend as needed 7 Fuel valve off 8 Ignition off 9 Safety ha...

Страница 29: ...20 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 Throttle for 1 3 power 8 Ignition on 9 Starter turn switch box key 3 4 Smoke and fire 3 4 1 Fire on ground 1 Fuel valve off 2 Throttle full 3 Master switch off 4 Ignition off 5 Abandon the aeroplane 6 Extinguish fire if possible or call fire d...

Страница 30: ... A AE ER RO OP PL LA AN NE E U UF FM M 1 13 3 Date of Issue 30 1 2008 3 4 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 ...

Страница 31: ... 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 Emerg landing perform according to par 3 6 1 7 Abandon the aeroplane 8 Extinguish fire if possible or call fire department 3 5 Note Estimated time to pump fuel out of carburettors is of 30 sec ...

Страница 32: ...retracted 3 Instruments within permitted limits 3 6 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 2 Speed 100 km h 3 Trim trim the aeroplane 4 Safety harness tighten 5 Flaperon extend as needed 6 Air brake extend as needed 7 COMM if installed report your location if it is possible 8 Fuel valve of...

Страница 33: ...tended to the take off position at a speed of 110 km h to thoroughly inspect the area 4 Perform flight around the chosen area 5 Perform an approach at increased idling with fully extended flaps 6 Reduce power to idle when over the runway threshold and touch down at the very beginning of the chosen area 7 After stopping the aeroplane switch off all switches shut off the fuel valve lock the aeroplan...

Страница 34: ...ssue 30 1 2008 3 8 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 ...

Страница 35: ...ntry if normal pilot techniques are used Should an inadvertent spin occur the following recovery procedure should be used 1 Throttle retard to idle 2 Control stick hold ailerons neutralized 3 Rudder pedals apply full opposite rudder 4 Control stick forward elevator control as required to break the spin 5 Rudder pedals immediately after the stopping of a rotation neutralise the rudder 6 Recover fro...

Страница 36: ...ettor icing Carburettor icing mostly occurs when getting into an area of ice formation The carburettor icing shows itself through a decrease in engine power and an increase of engine temperatures To recover the engine power the following procedure is recom mended 1 Speed 110 km h 2 Throttle set for 1 3 power 3 If possible leave the icing area 4 Gradually increase the engine power to cruise conditi...

Страница 37: ...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 4 4 7 Take off 4 11 4 4 8 Climb 4 12 4 4 9 Cruise 4 12 4 4 10 Descent 4 13 4 4 11 Check before landing 4 13 4 4 12 On base leg 4 14 4 4 13 On final 4 14 4 4 14 Landing 4 14 4 4 15 Balked landing 4 15 4 4 16 After landing 4 15 4...

Страница 38: ...list and amplified procedures for the con duct of normal operation 4 2 Assembly and disassembly Refer to 8 4 7 a 8 4 8 for assembly and disassembly procedures 4 3 Pre flight inspection The pre flight inspection is very important because an incomplete or careless inspection could allow aeroplane failure The following pre flight inspection procedure is recommended by the aeroplane Manufacturer ...

Страница 39: ...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 Check of tips attachment Condition and attachment of position lights if installed 3 Flaperon Surface condition Attachment Play 4 Fuselage rear Surface condition 5 Vertical tail unit Surface condition Play Free movement Pitot tube inspecti...

Страница 40: ...rizontal 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 see 1 12 Landing gear Check of main landing gear and tail wheel attachment Tail wheel steering Condition and inflation of tires Condition and attachment of wheel fairings if installed ...

Страница 41: ... Fuel and Electrical system visual check Fuel system drain 14 Propeller Propeller attachment Blades Hub Spinner condition 15 Cockpit Ignition key off Switch box off Master switch off Instruments check of condition Fuel gauge fuel quantity check for fuel quantity check switch on Switch box and Master switch then switch off Caution It is advisable to turn the propeller by hand with ignition off if t...

Страница 42: ... A AE ER RO OP PL LA AN NE E U UF FM M 1 13 3 Date of Issue 30 1 2008 4 5 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 ...

Страница 43: ...r switch off 4 4 2 After entering cockpit 1 Rudder control free movement check Correct 2 Brakes check of function 3 Hand control free movement check Correct 4 Trim check control movement 5 Flaperon check of function 6 Engine controls throttle and choke lever movement 7 Fuel valve off 8 Fuel gauge fuel quantity check 9 Switch box off 10 Circuit breakers off 11 Ignition off 12 Instruments COMM condi...

Страница 44: ...g 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 Check of free area clear 8 Master switch on 9 Ignition key on start 10 After starting set throttle to idling 11 Oil pressure within 10 sec min pressure 12 Choke off 13 Engine warm according to 4 4 4 ...

Страница 45: ...ld 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 To avoid shock loading start the engine with throttle lever set for idling or max 10 opened then wait 3 sec to reach con stant engine sp...

Страница 46: ...UF FM M 1 13 3 Date of Issue 30 1 2008 4 9 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 ...

Страница 47: ... 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 Fuel valve open 8 Fuel gauge fuel quantity check 9 Circuit breakers in 10 Instruments COMM within limits frequency set 11 Safety harness secured and tightened 12 Cockpit canopy condition lock ...

Страница 48: ... tail wheel and rudder Slightly push the stick to lift the tail wheel maximum to the centre position The aeroplane takes off at a speed above 70 km h then slightly push forward the stick to reach climb speed of 110 km h Refer to the par 5 2 5 for optimum climb speed Max flaps extended speed is 110 km h Warning The Take off is prohibited if The engine run is unsteady The engine instruments values a...

Страница 49: ...s needed to reduce stick pressure 4 Instruments CHT Oil temp and pressure within limits 4 4 9 Cruise The aeroplane flight characteristics are very forgiving within per mitted limits of airspeeds configurations and C G range The aeroplane can be controlled very easily Refer to the Section 5 par 5 3 1 Caution If cylinder head or oil temperature exceed limits reduce the angle of climb to increase air...

Страница 50: ... 4 4 11 Check before landing 1 Fuel fuel quantity check 2 Safety harness tightened 3 Brakes check function 4 Trim adjust as required 5 Landing area check runway Base leg 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 The engine becomes overcooled and a loss of power occurs When descending apply increased id...

Страница 51: ...d 4 Throttle as necessary 5 Instruments within limits 4 4 13 On final 1 Speed 110 km h 2 Flaperon LANDING position 3 Trim adjust as required 4 Throttle as necessary 5 Instruments within limits 4 4 14 Landing The airspeed during final is slowly reduced so that the touch down speed is about 70 km h Gradually pull the stick after touch down The landing run can be shortened by braking Caution When the...

Страница 52: ...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 Trim as necessary 7 Engine speed Max cont power 8 Instruments within limits 9 Climb at 120 km h 4 4 16 After landing 1 Engine speed set as necessary for taxiing 2 Flaps retracted and locked 3 Trim neutral position ...

Страница 53: ...2008 4 16 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 Aeroplane qualities and performance are not substantially changed ...

Страница 54: ...f 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 Move the lever slowly 2 Start with ignition key Caution After the engine off the engine could be cooled down Use the choke in this case Note Whit the feathered propeller is disconnected the engine starter circuit It is im...

Страница 55: ...30 1 2008 5 0 Section 5 5 Performance 5 1 Introduction 5 1 5 2 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 5 3 Additional information 5 6 5 3 1 Cruise 5 6 5 3 2 Endurance 5 7 5 3 3 Demonstrated crosswind performance 5 7 ...

Страница 56: ...a 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 If not stated otherwise the performance data given in this section is valid for max takeoff weight and under International Standard Atmosphere ISA condition...

Страница 57: ... LA AN NE E U UF FM M 1 13 3 Date of Issue 30 1 2008 5 2 5 2 Performance 5 2 1 Airspeed indicator system calibration V IAS δ δ δ δV V CAS km h km h km h 70 5 65 80 3 77 90 2 88 100 1 99 110 0 110 120 1 121 130 2 132 140 3 143 150 4 154 160 5 165 170 6 176 180 7 187 190 9 199 200 10 210 215 13 228 ...

Страница 58: ...s Warning speed Stalling Speed Stall Flaps posi tion Engine Power IAS km h CAS km h IAS km h CAS km h RETRACTED idling 85 82 80 77 TAKE OFF idling 75 70 70 65 Wing level stall LANDING idling 75 70 70 65 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 ...

Страница 59: ... off performance Take off distances stated in the following table are valid at sea level and for MTOW Take off run distance m Take off distance over 15 m obstacle m Grass 150 275 5 2 4 Landing Landing distances stated in the following table are valid at sea level and for MTOW Landing distance over 15 m obstacle m Landing run distance full braking m Grass 285 80 ...

Страница 60: ... NU UA AL L F FO OR R U UL LT TR RA AL LI IG GH HT T A AE ER RO OP PL LA AN NE E U UF FM M 1 13 3 Date of Issue 30 1 2008 5 5 5 2 5 Climb performance Best Rate of climb speed is 110 km h IAS corresponding Rate of climb is 5 m s ...

Страница 61: ...OP PL LA AN NE E U UF FM M 1 13 3 Date of Issue 30 1 2008 5 6 5 3 Additional information 5 3 1 Cruise Regime Economy Cruise Max Continuous Power Max Take Off Power Time limitation unlimited unlimited max 5 min Engine speed 4500 5500 5800 Altitude m ISA IAS km h IAS km h IAS km h 130 160 190 ...

Страница 62: ...nsumptions endurances and ranges for RPM settings of UFM 13 ultralight aeroplane Regime Max Continuous Power Economy Cruise Engine speed rpm 5500 4500 IAS km h 160 130 Airspeed CAS km h 165 132 Fuel consumption l h 20 9 5 Range km 825 1390 5 3 3 Demonstrated crosswind performance Max permitted cross wind velocity for take off and landing 5 m s Max permitted head wind velocity for take off and land...

Страница 63: ...O OR R U UL LT TR RA AL LI IG GH HT T A AE ER RO OP PL LA AN NE E U UF FM M 1 13 3 Date of Issue 30 1 2008 5 8 5 3 4 Speed polar Polar U M F13 15 R otax 912 7 6 5 4 3 2 1 0 60 80 100 120 140 160 180 200 km hod m s 13m 450kg 15m 450kg 13m 350kg ...

Страница 64: ...T M MA AN NU UA AL L F FO OR R U UL LT TR RA AL LI IG GH HT T A AE ER RO OP PL LA AN NE E U UF FM M 1 13 3 Date of Issue 30 1 2008 6 0 Section 6 6 Weight and Balance 6 1 Introduction 6 1 6 2 Permitted payload range 6 2 ...

Страница 65: ...08 6 1 6 1 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 ...

Страница 66: ... Issue 30 1 2008 6 2 6 2 Permitted payload range 0 20 40 60 80 100 120 60 80 100 120 140 160 180 Crew and baggage weight kg Fuel quantity liter Empty weight of airplane is 306 kg Section 7 Permitted crew weight 25 l in fuel tank 148 kg 50 l in fuel tank 130 kg 75 l in fuel tank 112 kg full fuel tank 94 kg half an hour flight 157 kg ...

Страница 67: ...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 7 3 Controls in the cockpit 7 5 7 4 Instrument panel 7 6 7 5 Landing gear 7 7 7 6 Seats and Safety harness 7 7 7 7 Baggage compartment 7 7 7 8 Canopy 7 7 7 9 Engine 7 4 7 10 Fuel system 7 9 7 11 Electrical system 7 10 7 12 Pitotstatic system 7 11 7 13 Miscellaneous equipment 7 11 7 14...

Страница 68: ...rframe 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 7 2 2 Wing The fibreglass wing has one main spar with carbon flanges no ribs the stressed skin is of sandwich construction with a foam core 7 2 3 Horizontal Tail Unit HTU HTU is of the same con...

Страница 69: ...F FL LI IG GH HT T M MA AN NU UA AL L F FO OR R U UL LT TR RA AL LI IG GH HT T A AE ER RO OP PL LA AN NE E U UF FM M 1 13 3 Date of Issue 30 1 2008 7 5 7 3 Controls in the cockpit ...

Страница 70: ... of Issue 30 1 2008 7 6 7 4 Instrument panel 1 Heating 10 Vertical speed indicator 2 Air speed indicator 11 Altimeter 3 TL engine instrument 12 Throttle 4 Compass 13 Magnetos 5 Slip ball 14 Switches and fuses 6 Fuel tank valve and switch 15 12 V socket 7 Main key 8 Main fuses 9 Fuel indicator 2 1 3 4 5 15 14 8 9 7 6 10 11 13 12 ...

Страница 71: ...tegral part of the fuselage Back rests are formed by a fibre glass skeleton covered with upholstery Four points safety harness with a central lock 7 7 Baggage compartment The shelf intended for putting off light weight objects headphones maps etc is located behind the heads of pilots 7 8 Canopy Canopy is made from the clear Plexiglas The canopy frame is formed by a fibreglass profile The canopy is...

Страница 72: ...E U UF FM M 1 13 3 Date of Issue 30 1 2008 7 8 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 ...

Страница 73: ...te 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 Further a coarse filter fuel valve and fine filter are parts of the fuel sys tem For draining use blow down valve located on the bottom of the wing ...

Страница 74: ...F FL LI IG GH HT T M MA AN NU UA AL L F FO OR R U UL LT TR RA AL LI IG GH HT T A AE ER RO OP PL LA AN NE E U UF FM M 1 13 3 Date of Issue 30 1 2008 7 10 7 11 Electrical system ...

Страница 75: ...nd the wing trailing edge Pressure distribution to individual instruments is done through flexible plas tic hoses Keep the system clear to assure its correct function If water gets inside the system disconnect hoses from the instruments and slightly blow into the system Cover or remove pitot tube during transport 7 13 Miscellaneous equipment Besides the standard instruments the UFM 13 aeroplane is...

Страница 76: ... 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 Cylinder head temperature Oil temperature Oil pressure Overrun of data limits Refer to the TL engine instrument Operator s Manual for more de tails The UFM 13 aeroplane is additionally equipped with electric F...

Страница 77: ...icing and mainte nance 8 1 Introduction 8 14 8 2 Aeroplane inspection periods 8 14 8 3 Aeroplane alterations or repairs 8 14 8 4 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 Aeroplane Disassembly 8 20 8 5 Cleaning and care 8 21 ...

Страница 78: ...n the condition of the operation and on overall condition of the aeroplane The producer recommends to accomplish maintenance checks and peri odic inspections in the following periods at least After each year of operation clean and lubricate the bearings per Lubricating Chart Contact the Aeroplane Manufacturer when plays are excessive Refer to the Engine Operator s Manual for maintenance The propel...

Страница 79: ...e aeroplane a short distance by holding the blade root because the empty weight of this aeroplane is relatively low Suitable surfaces to hold the aeroplane airframe are the rear part of the fuselage before the fin and wing roots 8 4 2 Parking It is advisable to park the aeroplane inside a hangar or eventually inside other weather proof space such as a garage with a stable tem perature good ventila...

Страница 80: ...ary to protect the aeroplane against possible damage caused by wind gusts For reason the aeroplane is equipped with tie down strips on the wing tips Procedure Check Fuel valve off Circuit breakers and Master switch off Switch box off Block the control stick up e g by means of safety harness Close and lock cockpit Shut all the ventilation windows Tie down the aeroplane to the ground by means of the...

Страница 81: ...arts Press down on the rear of the fuselage in front of the fin to lift the front and then support under the firewall To jack the rear of the fuselage grab the fuselage near the auxiliary tail skid lift it upward and support To lift the wings push on the wings lower surface at the main spar Do not lift by the wing tips 8 4 5 Levelling Refer to the Operating Maintenance and Repair Manual for UFM 13...

Страница 82: ...lane 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 Then screw the front screw and secure with safety pin ...

Страница 83: ...30 1 2008 8 19 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 Connect fuel sensor and fuel hose from left and right fuel tank ...

Страница 84: ...80 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 Check control system and fuel gauge function Use an adhesive tape to cover the gap between the centre section and the wing root 8 4 8 Aeroplane Disassembly Follow the Assembly steps in reverse order ...

Страница 85: ... cleaned only by washing it with luke warm water and mild detergents using clean soft cloth sponge or deer skin Then use suitable polishers to clean the canopy Caution Never clean the canopy under dry conditions it will scratch and never use gasoline or chemical solvents Upholstery and covers may be removed from the cockpit brushed or washed in lukewarm water with mild detergents Dry the upholster...

Страница 86: ...UA AL L F FO OR R U UL LT TR RA AL LI IG GH HT T A AE ER RO OP PL LA AN NE E U UF FM M 1 13 3 Date of Issue 30 1 2008 9 0 Section 9 9 Supplements 9 1 Introduction 9 1 9 2 List of inserted supplements 9 1 9 3 Supplements inserted 9 2 ...

Страница 87: ...3 3 Date of Issue 30 1 2008 9 1 9 1 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 9 2 List of inserted supplements Date Title of inserted supplement ...

Страница 88: ...F FL LI IG GH HT T M MA AN NU UA AL L F FO OR R U UL LT TR RA AL LI IG GH HT T A AE ER RO OP PL LA AN NE E U UF FM M 1 13 3 Date of Issue 30 1 2008 9 2 9 3 Supplements inserted ...

Страница 89: ...O OR R U UL LT TR RA AL LI IG GH HT T A AE ER RO OP PL LA AN NE E U UF FM M 1 13 3 Date of Issue 30 1 2008 9 3 9 4 Service records 9 4 1 Summary of repairs checking parts changes etc Operation reason date hours flown sign done by controlled by ...

Страница 90: ...LI IG GH HT T M MA AN NU UA AL L F FO OR R U UL LT TR RA AL LI IG GH HT T A AE ER RO OP PL LA AN NE E U UF FM M 1 13 3 Date of Issue 30 1 2008 9 4 Operation reason date hours flown sign done by controlled by ...

Страница 91: ... AN NU UA AL L F FO OR R U UL LT TR RA AL LI IG GH HT T A AE ER RO OP PL LA AN NE E U UF FM M 1 13 3 Date of Issue 30 1 2008 9 5 9 4 2 Bulletin of producer Serial number bulletin number date remarks sign done by controlled by ...

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