MAINTENANCE MANUAL
Contents
1. orl ae Maintenance Manual V001 FRECCIA AEROSPACE SYSTEMS INSPECTIONS This section contains some requirements concerning inspections and basic maintenance which are to be observed in order to maintain the performance and reliability of a new airplane It also contains procedures for the correct handling of the airplane and servicing recommended by the airolane manufacturer It is reasonable to proceed according to a prescheduled scheme of lubrication and maintenance appropriate to the operating conditions and climate SCHEDULED AIRPLANE INSPECTIONS The scope and the intervals of the inspection schedule are defined Tasks to be carried out in relation to scheduled inspections of engine propeller rescue system and equipment are defined in the respective applicable manuals or operating and maintenance instructions The owner and operator are responsible to insure that all handling servicing and maintenance are only carried out by qualified personnel The table below indicates recommended maintenance periods Table legend Cc Check up visual only check for free play and whether everything is in position DO IT YOURSELF CL Cleaning DO IT YOURSELF LO Lubricating oiling lubricate all designated parts and spots using proper lubricant DO IT YOURSELF R Replacement replace designated parts regardless of state and condition You are encouraged to DO undemanding replacements YOURSELF otherwise have replacement2. z _ _ DETAIL 2 DETAIL 2 GROUP 2 ELEVATOR DETAIL 4 GROUPS4ELEVATOR O i fo DETAIL 5 f DETAIL 5 GROUP 5 AILERONS f Rigging of Ailerons Control In a neutral position the ailerons aft edge must be on the same line as the back part of the wing tip the maximum admissible difference upwards or downwars is of 2 mm Check if the positions at the end of ailerons running are correct If it isn t follow these steps 1 Put the aileron upwards 2 Loosen the push rod locknuts which are under the wing Act on the internal nut by un screwing top ut the aileron up or by screwing top ut it down until its trailing edge has the indicated distance from the tip s aft edge limit switch upwards 3 Consequently the limit switch downwards is correct thanks to the aileron s tranfer design Screw and lock the external checknut Seite 17 Maintenance Manual V001 2 FRECCIA W IAT IEE EE 7 FLOATING TRUSS SCS005 8 RIGHT BELLCRANK sceso Of LEFT BELLCRANK CS010 1 Control stick adjustment If the control stick is in a neutral position and the ailerons are not lined up with the respecti ve tips act as follows 1 Remove the door on the seats s floor 2 Unscrew the M nut to take off the connecting rod from the control stick transfer 3 Fix the aileron and the control stick in a neutral position 4 The connecting rod goes up an adjustable head unscrew the control for so
3. four stroke engines oil and engine filters first 25 hours cooling fluid level hoses radiators water radiator pressure caps PITOT STATIC LINING instrument to pitot tube lining instrument setting pitot tube condition clean firmly attached whole pitot static lining 3 2 INSPECTION AFTER FIRST 25 HOURS gt Prone AEROSPACE SYSTEMS TE TT alate O lt ry 500 hrs or 5 years ele nn fo refer to engine manual refer to engine manual ep i refer to engine manual tell EG E Note the inspections on engine after the first 25 hours of flight must be carried out in ac cordance with the engines operating manual as well as the following hours 1 Verify the correspondence of the final positions of the engine s control lever and the choke s control with the carburettors levers 2 Remove the wheels fairings lift the wheel and check it as regards the presence of axial play check the condition of the brakes discs of brakes brackets Check the tyres pressu re 3 Check the correspondence of the neutral positions of rudders of flaps and of ailerons with the neutral positions of controls and of control stick Check how the control levers work when smoothly Seite 36 N JET C1 IIICIECC Maintenance Manual V001 FRECCIA AEROSPACE SYSTEMS 3 3 INSPECTION AFTER 100 HOURS OF FLIGHT AT LEAST ONCE A YEAR Note the inspections on engine after 100
4. Dismantle the calliper w N Replace the brakes pads in the support and the brake discs when they are worn out REPLACEMENT OF THE MAIN WHEE S TYRE To replace the tyre Empty the air from the tyre Remove the tyre from the rim Push the valve in the rim hole and remove the inner tube if it s present Check the rim clean it Dry clean the internal surface of the tyre Put the tyre again with the eventual inner tube in the rim N OV oF FP W DN m Inflate the tyre till the adequate pressure 2 0 2 2 kgf cm approximately 2 bar MATERIALS USED IN MANUFACTURING PROCESS Composite parts are made of usable for small repairs Carbon fibre 200 g m2 Plain Glass fibre 300 g m2 Twill 200 g m2 Plain 160 g m2 Twill 80 g m2 Plain Foam oO Oo C OW mis tO nia mus O matin Resin Epoxy resin Filler for bonding Microfibres cab o sil glass boubble Paint Gelcoat Heat resistant protection Glass aluminium stainless steel sandwich All parts are made in moulds therefore no shape or structural differences can occur Seite 45 NERE _ Maintenance Manual V001 2 gt Maintenance Manual V001 FRECCIA MCA TIER EE MICA TIER EEs FRECCIA 7 INFORMATION SIGNS AND MARKINGS 7 2 FURTHER MARKINGS This chapter describes the labels and the location of signs are described on the aircraft MARKINGS 7 1 PANEL All designations for switches controls and fuses are printed directly on the panel The printing depends
5. Tactile for Trim j w MAXIMUM CONFIGURATION This cockpit shows the maximum configuration with analogue instruments The equipment can be configured differently Therefore deviate the actual features of this figure Control lamp Battery EE sess Fuel Pump avigation System Generator Flight Instrumens Engine Instruments Switches 1 Main Switch 2 FuelPump 3 8 Depends on config r a Jj Switch Left Stick lt gt Right Stick Display Trim Ignition Switch Tactile for Trim Breakers Choke Carburator Heating Cabin Heating Seite 24 N Maintenance Manual V001 M TITEL FRECCIA 2 15 PRIMARY FLIGHT DISPLAY AND ENGINE MONITOR SYSTEM DEPENDING CONFIGURATION PFD EMS ECLIPSE FLYBOX 080 E 100 110 120 130 140 5200 AS _ GS 108 ma LT 11 52 ey ye gt Fan E J Ar 10 5a A 26 2 bi 19 oc P BAR 22 c 35 0 258 106 1008 EGT i 1 10005 H 782 1013 A 30 G METER 2 2 mBAR 752 1234 122324 DESCRIPTION PFD Artificial horizon Anemometer Altimeter Compass Variometer G meter Turn coordinator EMS Fuel pressure Oil pressure Oil temperature 2x CHT 2x EGT Voltmeter RPM Hour meter MAP OAT Fuel quantity indicator Seite 25 _ N Maintenance Manual V001 _ Maintenance Manual V001 FRECCIA IPVOINEE SG IPVOINEE SG FRECCIA 2 16 ELECTRICAL SYSTEM 2 17 ENGINE ROTAX 912 ULS The aircraft is equipped with a 12 volt direct current
6. Total length Max width Max height Frontal surface Max section surface Fuselage surface crossed by air flow TAIL PLANE HORIZONTAL TAIL Wing span Mean chord Aspect ratio Extension Angle of incidence 8 777 m 1202 m NOMS m 5o 1 741 m 0 27 m 0 47 m 24 1 up 12 1 down 1 741 m 0 38 m 0 66 m2 O 35 down 7 248 m 1 20 m 2 553 m 20 Tar POO 14 n 2 772 i O 750 m 22m 4 3 1 2 gt 7 PVOsSNELCl AEROSPACE SYSTEMS Maintenance Manual V001 FRECCIA ELEVATOR Elevator span Surface Stroke TRIM Width Chord Stroke VERTICAL FIN Vertical fin span Minimum chord Maximum chord Mean chord Surface Extension RUDDER Surface Steering angle ENGINE Engine model Maximum rotational speed of the propeller Maximum rotational speed of the engine BOVE we O77 m 20 up 15 down O 75 fan 0 075 m 20822 mp 20 2 down 351m 0 645 m 1 236 m 0 947 m 1 12 Tare 1 4 0 42 m2 25 a ROTAX 912 ULS 2400 2800 according to the engine model 5800 rpm in Smin 5600 Propeller According to the customer s demand UNDERCARRIAGE Width of the rear landing gear undercarriage 1 6m Distance between the turning wheel and the rear 15 m landing gear Seite 9 Maintenance Manual V001 FRECCIA 1 3 LIFETIME RESTRICTIONS General overhauls are fixed on 1200 flight hours or 10 year of use As for the engine and some special elements refe
7. and static pressure sensors 6 6 Lock the canopy and put on the cover 7 7 Position the propeller horizontally TYING DOWN we V TE e CN rla Seite 41 _ Maintenance Manual V001 2S FRECCIA MW CIAT IEE EE 4 4 LIFTING AND LEVELLING When jacking the airplane the following procedure should be followed 1 Puta stand under a rib under each wing to prevent the airplane from tilting 2 Locate jacks under the nose landing gear ferrule and the other each side next to the cabin walls under the main landing gear box 3 Apply wooden blocks Lift the airplane gradually to the required height Lift the airplane raising each jack evenly at the same time and avoid swaying After lifting the airplane should be leveled so that the cabin wall edges are horizontal see the illustration LEVELLING Seite 42 s 5 1 5 2 Idi 5 4 5 9 N gt Maintenance Manual V001 M 11 IE OE FRECCIA CLEANING AND CARE It is essential for the reliability of the airplane components to always keep them clean PAINTED EXTERNAL SURFACES Prior to clean take the following steps 1 Protect the wheels especially the brake discs covering them 2 Put the cover on the pitot and static pressure sensors 3 Mask off all holes and orifices Use clean water to remove all fine particles and then wash the surface with water adding mild soap Do not use detergents o
8. hours of flight must be carried out in accordance with the engine s operating manual as well as the following hours In addition to the inspections after the first 25 hours of flight 1 2 10 11 12 13 14 15 16 17 18 19 20 Make sure that the battery is disconnected and that the supply system valve is locked Check the lower part of wings and the engine cover by making sure of the absence of pet rol leaks from the fuel tanks and of oil leaks from the lubrication system Check the fixing of propeller spinner Remove the covers Check the engine by making sure of the absence of fluids leaks from the joining of the tubes and of the engine as well as the fixing of the elements Make the engine turn and make sure of the good working of all cylinders In case of cylin ders which are not so much warmed up or overheated identify the reason of this event Clean the cover the engine the propeller the elements the tubes the cables the filters of the radiator and of the cooler from the oil remains Clean the aircraft covering and the undercarriage from dirt and dust Tidy up the inside of the cockpit Check the fuel and oil reserves in the tanks and weigh up their respective consumptions The check up steps is the same as the pre flight check up in the Flight Manual Check the conditions of the undercarriage s axes and the mounting tools on the fuselage frame Check that there aren t any cracks or deteriorati
9. m s 3 95 60 mm 2 70 mm Opening for the rocket Release Lever Rescue System Rocket Softpack N Maintenance Manual V001 T T A n FRECCIA INSTALLATION DRAWINGS CABLE SETUP PARACHUTE BRIDLE CONNECTION POINT ENGINE MOUNT CABLE LENGTH 2200 mm CABLE LENGTH 2250 mm FRONT ATTACHMENT REAR ATTACHMENT POINT CABLE MOUNTING E ENGINE MOUNT FIREWALL a FRAME 914 DIN 982 M12X1 5 P N RS02 P N FL0603 RS T EYELET PN RS01 DIN 982 M10 Seite 49 N Maintenance Manual V001 D D Maintenance Manual V001 FRECCIA PrrOlNeLCl P rrOINILClO FRECCIA AEROSPACE SYSTEMS AEROSPACE SYSTEMS 8 3 MAINTENANCE OF THE MAGNUM LIGHTSPEED SOFTPACK a ss s 9 WEIGHING PROCEDURE Throughout the dismantling or assembly process never use violence or bring tension on the acti vation cord All steps must be made smooth Otherwise the rocket will activate This Section contains the limitations of the useful load within which the airplane may be opera ted safely During your work put the shooting out opening always away from yourself and check before star mn i i o ting work that there are no persons or object in shooting out opening If possible all works should Loading condition of the aircraft during weighing b done outside Equipment as per Equipment Inventory Including lubricants Please note that for all works done yourself are without warranty of function or security besides Petrol tank is em
10. on the cockpit configuration Example of an analog configuration MASTER START FUEL AVIONICS NAVI INSTRU CHOKE GENERATOR ARMED PUMP MENTS CARBURETOR HEATING CABIN HEATING min 95 ROZ unleaded Additionally the following warning is printed on the panel Aerobatics including spinning prohibited Flights at night at the risk of icing and thunderstorms are prohibited Refer to the flight manual for further operating limits Tankcover min 95 ROZ unleaded Baggage compartment max 20 kg load Maximum take off weight 472 5 kg Static port keep clean Minimum load 6S K Maximum load 98 5 kg The warnings may vary according to configuration are also available at other locations of the pa 7 3 AIRSPEEDINDICATOR MARKS nel however are always clearly visible to the pilot and may not be removed Marking IAS km h Remark White arc 69 119 Operating range with full flaps extended Seite 46 Seite 47 Maintenance Manual V001 FRECCIA 8 RESCUE SYSTEM SER 7 PVrOos TILCT C AEROSPACE SYSTEMS 8 1 TECHNICAL DATA OF THE MAGNUM LIGHT SPEED SOFTPACK Length of container Width of container Thickness of container Total weight Area of canopy Number of cords Max tested operating speed verage descent rate by 475 kg Opening time at standard speed min 100 km h Rocket container diameter Rocket container length RESCUE SYSTEM Firewall Seite 48 340 mm 240 mm 190 mm 9 65 kg 86 m2 32 300 km h 7 33
11. 707 ARM OF VERTICAL TAIL 3885 ARM OF HORIZONTAL TAIL J ty ooo ag _ 4014 Eo 3 947 LO VERTICAL TAIL AREA 1 2 m Se mac RUDDER AREA 0 42 m2 N j VERTICAL TAIL ASPECT RATIO 1 4 2 1236 2111 FRONVIEW i MAX 1900 1194 2543 G Seite 6 Ns _ Jr rezo C AEROSPACE SYSTEMS TOPVIEW i 8762 1200 900 299 a 741 66 a 1741 1938 Maintenance Manual V001 FRECCIA mac 58 pop ee mac N o Be 15 cO N pee ee N HORIZONTAL TAIL AREA 2 2 m ELAVATOR AREA O 77 me HORIZONTAL TAIZFASPECT RATIO 43 Lasgo l _900 WING AREA 10 13 m FLAP AREA 0 66 m AILERON AREA 0 47 m ROOT AIRFOIL NACA 63 2 412 TIP AIRFOIL NACA 63 2 412 WING ASPECT RATIO 7 54 SWEEP 1 TAPER RATIO 1 556 8762 q D A A i PIVOT aS A A 4 bse B B T d AILERON DEFLECTION 1 MAC 202 B O a B Seite 7 Maintenance Manual V001 FRECCIA 1 2 DIMENSIONS Seite 8 WING Wing span Wing chord Wing surtace Dihedral AILERONS Aileron span Mean chord Aileron surface Steering angle stroke FLAPS Flap span Mean chord Flap surface Flaps positions FUSELAGE
12. STRUCTION UNIT Engine Nose gear Main gear Ailerons Flaps Tail Rudder pedals AREA OF LUBRICATION Throttle control cable into engine compartment Choke control cable into the engine compartment Nose gear leg and bearing of the link to rudder pedals Axle bearings Hinges Rod end bearing of the control system Hinges Rod end bearing of the control system Actuator hinges Rod end bearing of the elevator control system Rudder hinges and bearing Rudder Bowden cable Stabilizer Elevator hinges Hinges and movable parts of trim All moving parts in cockpit area LUBRICATION OVERVIEW 25 H Maintenance Manual V001 100 H X FRECCIA LUBRICANT Light oil Light oil Lubrication grease Lubrication grease Lubrication grease Lubrication grease Lubrication grease Lubrication grease Lubrication grease Lubrication grease Lubrication grease Lubrication grease Lubrication grease Lubrication grease Seite 39 NERE N Maintenance Manual V001 gt Maintenance Manual V001 FRECCIA PV ONTIENE PV E E FRECCIA 4 GROUND HANDLING 4 2 PARKING 1 1 Position the airplane pointing into wind The dimensions of the standard airplane are given in the airplane drawings This allows the size of the area required for the airplane in a hangar or for parking to be defined 2 2 Apply chocks to the main wheels 3 3 Secure the control sticks with the seat belts or tow ba
13. a 3 CENTRAL HINGE CE 2 UPPER SKIN NOT SHOWN FOR CLARITY FT DESRETON PN s 1 EATERALENGE e E 2 CENTRAL HINGE FTE0202 J 3_ BELLCRANK Fer Seite 16 MEE oA nET N Maintenance Manual V001 Pome FRECCIA 2 8 AILERONS CONTROL The ailerons control is differential when the right aileron moves upwards the left one goes down wards and vice versa The angle of steering on the upwards is wider than the angle of the one downwards The aileron course compared to neutral position is of 24 1 upwards and 12 1 downwards The consequence is the increase of ailerons efficiency especially in the big incidence flight also to make up for the different curvature between the back and the underside of the wing Replaced through connecting rods and transfers they efforts on the control handle are passed on the wing The controls assembly connects the right control stick with the left one and vice versa From each of them a transfer is connected to the respective wing through an extesible head con necting rod From that a bar inside the wing transmits the movement to the last transfer integra ted into one of two aileron hinges HALF FUSELAGE SHELL FLOOR SEATS NOT SHOWN FOR CLARYTY I r 914 FRAME 533 MAIN SPAR a I i i I gt s 7 i m in N 4 _ 4 i te e Eh k Pen ae waw Z
14. al use on automotive upholstery may be applied but the indica tions given on the packing should be strictly observed Seite 43 _ Maintenance Manual V001 FRECCIA AEROSPACE SYSTEMS 6 REPARATIONS Any repair or modification of the airplane design may only be pertormed by authorized personnel Note prior to any modification or reparation of the airplane consult with and obtain writ ten approvement by the manufacturer that the intended modification will not negatively affect the airworthiness of the airplane After completing the modification according to the instructions given in the Airplane Mainte nance Manual the aircraft should be re weighed and the respective weighing report sheet com pleted and the Weight and Balance schedule of this manual must be revised For every reparation consult with manufacturer to have the lamination and reparation plan show ing picture of the damage 6 1 MAIN WHEELS ASSEMBLAGE AND DISASSEMBLAGE As for the main wheels assemblage and disassembling at first remove the wheels mudgu ards Then 1 Puta jack under the iron tools which secure the undercarriage to the fuselage and jack the wheel up Unhook and unscrew the spacer on the wheel axle shaft Remove the wheel from the axle shaft Wash the bearings with gasoline and dry by blowing air oF UU N Check the bearings to found out eventual damages or corrosions In case of need replace them O After the check up greas
15. c Pressure System Pitot Pressure System Altimeter fis j Vertica speed indicator N fus 4 Alt encoder lav Airspeed indicator KT Static port Pitot Seite 31 _ Maintenance Manual V001 FRECCIA W INTEL 2 19 PROPELLER 3 2 20 Manufacturer DUC HELICES Model 3 blade Inconel SWIRL clockwise Diameter 1730 mm For propeller inspection and maintenance refer to original propeller manufacturer s Manuals Propeller removal installation and replacement can only done of Pro Mecc or propeller ma rJ nufacturer authorized service center BRAKE SYSTEM The braking system consists of one brake lever positioned in the middle of control panel that by the mean of a brake pump operate on the two brake system on the rear wheel The left and right brake share a common lluid reservoir installed on the top right of the firewall Care must be taken to avoid applying brake pressure when using rudder on the ground The parking brake control valve is mounted in the middle of the two seats rear to the central con trol panel The parking brake is OFF if the control lever is rotated vertically upwards and it is ON if the control lever is rotated orizzontally to the sense of flight Schematic of the system is represented below FLUID TANK FIREWALL COCKPIT BRAKE PUMP BRAKE PARKING BRAKE VALVE LEVER WHEELS Fluid replacement BRAKE FLUID DOT 4 Seite 32 7 PrVrO sTIEeC C
16. d temperatures are measured by sensors installed on cylinders heads 2 and 3 Temperature readings are taken by measuring the hottest point of cylinder head according to engine installation COOLING SYSTEM expansion tank POA lt CG aa Ey 77 7272 zz272222 gt overflow bottle x Coolant Fluid see Engine Operator Manual FUEL SYSTEM Freccia in basic version is equipped of a fuel tank installed inside right wing having capacity of 50 liters The drenable quantity of fuel is 48 5 liters It is available as option the second fuel tank that can be installed on the left wing System schema is represented below Seite 29 LEN Maintenance Manual V001 ae FRECCIA MW IAT IEE EE Fuel _ Fuel gsuge Fuel Cap ATX mg lt r gt EIS Fuel Cap ae wip a L I N ee N Erste ai s gt 7 i 7 M N E ul lasa Besser y pinli Left under Left wing tank Right under Wing Vent Wing Vent Wing tank installation T if applicable N Fuel EIS Fuel Shutoff Valve On N Pressure Ol is Electric Fuel Pump Switch Fi owal Pump On LED Light Return Line to Fuel tank Sunction Line Fuel Drain Electric Fuel Pump Gascolator Engine Fuel Fuel Pressure Sensor to EIS Left ROTAX FO Right ROTAX Carburetor Carburetor Gascolator inspection cleaning 1 Remove upper cowling and bottom cowling Make sure the Fuel Selector Valve is in the off positio
17. e choke one are fixed to a control box made of carbon fibre and they are BJA linked to steel sheath cables BATTERIA ACCESA The cables fastened to the fuselage structure pass the firewall and inside engine compartment are fixed to a box that has the function to double the controls in order to reach the throttle lever and the choke lever of the two engine carburetors ENGINE CONTROL Sheath CHIA VE ACCENSIONE Lever Fuel lever ri i I Quick draw Control engine cable a DD Control box FUSES Start Armed 2A Fuel Pump 2A Adjustment of engine control EFIS SA The engine control lever must move with a right effort In case of effort s weakening in flight the lever could move ahead spontaneously and the engine s power setting would increase In this Flap 3A case adjust the engine choke lever Loosen the M8 nut lock it with a proper spanner and secure Trim 1A consequently the friction increases and the engines control lever remain in a more appropriate position Seite 26 Seite 27 NERE N Maintenance Manual V001 D A Maintenance Manual V001 FRECCIA M CIA T IE E M CIAT IE E C FRECCIA ENGINE LUBRICATION SYSTEM The engine lubrication system limits the wear and tear of the engine elements and ensures their partial cooling and evacuate the rejects of wear and tear ROTAX 912 UL S engine is equipped with a dry sump forced system including a main oil pump with an integrated pressure regu
18. e the bearings The assemblage and the disassemblage of the wheel and of its fairing follow the reverse order with regard to the disassemblage 8 Then pump the braking circuit PUMPING OF BRAKING CIRCUIT The pumping of braking circuit needs two operators 1 First of all install a PVC tube on the relief valve cleaned from dust and incrustations The other edge of that tube must be dipped in a container to recover the brake fluid An operator puts on the brake lever and keeps it locked in brake position until the end The other operator following the order of the first one unscrews the valve of two turns and checks the flowing of air bubbles from the braking circuit 4 In this way the first operator causes the overflow of air bubbles until the stop and asks the second operator for screwing well the valve Then he releases the brake lever Repeat this operation until the air bubbles stop overflowing from the PVC tube In the pumping of braking circuit see the fluid level in the expansion container and in case of need fill up to not allow the level to go under a minimum and to avoid the air penetrati on in the circuit Seite 44 JET TITEL JET ELITE 6 2 6 3 6 4 N Maintenance Manual V001 FRECCIA AEROSPACE SYSTEMS REPLACEMENT OF BRAKES PADS As for the replacement of brakes pads and of brakes discs follow these steps Remove the wheel Disconnect the wheel from the brake disc and from the support
19. electrical system with grounded negative For engine inspection and maintenance refer to original Rotax manuals supplied with the aircraft pole E Operators Manual for ROTAX engine Type 912 Series The primary source of electrical energy is provided by the engine mounted interior alternator ge E Documentation for ROTAX aircraft engines CD ROM nerator with total power of 750 W M Service instruction fur ROTAX Type 912 und 914 series The internal alternator located at the rear of the engine block will charge the battery up to 13 5 M ROTAX service letter Warranty conditions for ROTAX engine types 912 and 914 series VDC E ROTAX engine Log book Power is supplied to the electrical and avionics circuits through a main bus bar located behind instrument panel this bus bar is energized anytime the Main switch is ON Each system is protected by circuit breaker which is permanently on If some circuit is overloaded UI Engine removal installation and replacement can only be done by Pro Mecc authorized then the circuit breaker disconnects that circuit L service center ELECTRICAL SYSTEM ENGINE CONTROL BATTERIA On the central control panel in the middle of the cockpit there are the handgrips relative to GENERATORE L6mnm Pea 16mm ne E Throttle lever u GROUND I _ M Choke push pull cable ra S INT KE Ke BATTERIA R ri N j SPIA l mm START MOTORE x GEN Qa C 22 000ur The power levers and th
20. fr f FEE y a MAINTENANCE MANUAL UL AIRCRAFT LTF UL 2003 Manufacturer No FRXXX Registration No D MXXX Maintenance Manual V001 FRECCIA _ CONTENTS Te General uu uuu E EER E E A A E qasa ass 5 1 1 Three view drawings Freccia a 6 12 DINO ON a E ENE E E E N 8 1 3 Lifetime restrictions reen reen entreen erne rer rnrnnee 10 tA eel geo 2757 al lle 6 u u u wa y ES renee renee emery eee rere 11 2 Technical d eriplieon u u uu u aakaastusyaspapaskwaqaswiwapkuspakasyasuwwwkuayaywiwksaqwaq 12 Dili TOSSA C u uum EEN ERNST ERE SEERE ERNE EEN 12 2 TERE SER oa aceon etary veneers E EEEE 13 o EA FOUN u esters cee oe eee eee eee eee 13 ERE O As SS S S sa 14 5 FEE SE E unun u nas n nu 14 Zig INOS Issa sa 15 SAV SEER EY SII SS vir u SE SER KOSEL SE E EE ENE EEE ENE E E E E 16 o AEON CONTO aaa E E EEA ER 17 any ame oa COTO E mer ne err EA E R 17 210 EVV ALO eontfeluuu uuu n re Eneee aE A EEEE 19 SE K TON O ee EEEE otsnemededuneseeanaubieoapansenieecqnterapsens 21 BAZ RRIF COMO ea E A EE E EN O ss 22 P E S e E u u ua E A A VAE A Eee Eee 23 io T oi e S U U U S A E dd u 24 2 15 Primary Flight Display and Engine Monitor System DEP CoNFIGuR 25 2 16 Tier Syst iiuuuuuu w n u akamaayaapanspatkahuskuasqpiqupaayaaqaskunpakukasphaqaskayqa 26 217 F gine RO1AX 912 UL esiaine a TERE Eo ETE 27 2 18 Ptot satie pressure sys O WT meneceri ee
21. he firewall is a structural element situated on the front part of the fuselage and it separates the The aircraft is provided with a low and tapered wing made up of 2 half wings in carbon fibre that engine from the cabin It s made of a composite material panel The part of the panel which is tur can be disassembled with a main spar going through the fuselage and with a wing rib equipped ned to the engine has the attachment fittings for supporting the battery case for the oil tank and with wing fuselage connection points Wing tips can be removed lu K u ii 2 eee The structure of wing flap and aileron is identical to the one of tail unit The firwall is covered by a special material heat and flame resistant FIREWALL N I UPPER SKIN NOT SHOWN FOR CLARITY 2 5 TANK The tank are made ot fibreglass and are in the right and left wino halves At the rear they have a cylindrical screwing which is set in the hole rib on the front it is secured to aluminium ribbino TANK Seite 14 Seite 15 NERE Maintenance Manual V001 2 FRECCIA AEROSPACE SYSTEMS 2 7 EMPENNAGES Classic type and provided with rudder tail plane elevator and trim electrically moved It is made of composite materials with a shell of sandwich panels composed of carbon glass fibre and p v c and the spar made of p v c carbon fibre UPPER SKIN NOT SHOWN FOR CLARITY AA ET DESCRPTON PN P 1 _ FITINGPLATE S Oa 2 aeae a
22. ighten the fixing bolts if need be Check the attaches of the oil tank tighten the fixing bolts if need be Remove the propeller cone check the propeller s attachments Check the attachments of the tubes and of propeller engine installation s electrical cables If necessary do the attachments again Check the fuel filter In case of the presence of anomalous particles in the filter it must be replaced and the tank must be cleaned Check the undercarriage s attachment fittings about the movement the axle s wear and the undercarriage s elements Check the covers locking lubricate them Open the inspection panels and check the cables attachment fittings check all the control cables channelling Possible pulleys must spin easily without any noises they mustn t have any traces of wear Check the fuselage shell s attachment fittings Verify the electrolyte s voltage and its density in the battery Remove the aft undercarriage s wheels check and clean the wheels bearings grease Check the wheels axle shafts about the presence of breaks and wear Remove the undercarriage s nose wheel check and clean its bearings grease settle the wheel Change the grease in all the joints and in all the control planes Check the tension of control cables Check the actuating rods their attachment fittings to the quick draws check the bolts tightening N JET oA nET AEROSPACE SYSTEMS 3 4 LUBRICATION IN
23. lator 1 and a oil pressure sensor 2 The integrated oil pump is activated through the camshaft Through the depressurizing created by the pump 3 the engine oil is driven from the tank 4 through the oil cooler 5 through the filter 6 to the lubrication points in the engine The oil in excess overflowing from the lubrication points accumulates in the bottom of crankcase and it s pushed back to the tank by blow s gas The oil circuit is vented by a bore on the oil tank The oil temperature sensor 8 is located on the oil pump housing ENGINE LUBRICATION SYSTEM Seite 28 ENGINE COOLING SYSTEM The function of ROTAX 912 UL S cooling system is to guarantee liquid cooling for cylinders heads and air cooling for cylinders Cylinders heads cooling system is at closed circuit with an expansion tank Cooling fluid is pushed by the pump set in motion through camshaft from radiator to cylinders heads From the top of cylinders heads cooling fluid reaches the expansion tank 1 Since usu ally the radiator position 2 is lower than the engine one the expansion tank located above the engine allows the cooling fluid to flow Expansion tank shut with a pressure cap 3 provided with overpressure valve and return valve opens and cooling fluid runs through an atmospheric pressu re tank to a transparent overpressure container 4 When cooling temperature begins to decrease fluid is sucked down to cooling circuit Cooling flui
24. me turns and rig the head until it can enter easily in the control stick bolt U1 Screw again the M nut and lock the checknut 6 Close the door Seite 18 N Maintenance Manual V001 Pome FRECCIA 2 9 FLAPS CONTROL Flaps control is electric type made of a linear actuator driven by electric switch The control sys tem is positioned inside the fuselage accessible removing the trunk Flaps control is an electric switch with up down positions located on the instrument panel in the cockpit on the control panel by means of it flaps can be adjusted in continuous movement from 0 to 35 positions gt FRAME 914 DESCRIPTION BR LINEAR ACTUATOR LEFTMOUNT RIGHT MOUNT CRANK o PUSHROD ER EH 2 3 U SUPPORT_ EN EN CH 2 10 ELEVATOR CONTROL The stabilizer is slightly in nosedive position to facilitate the aircraft nose up especially on take off The elevator travel respect to the neutral position is of 20 1 upward and 15 1 down ward The elevator control is consisting of handle connecting rod and quickdraw The duralumin tube is connected to axis by means of ball bearing The flapping of the pushed or pulled handle is limited by control stops on the two sides of the axis The axis is fastened to the fuselage frame s bottom tube through two bolts around them the con trol stick is rotated lenghtwise The control stick quickdraw is connected to
25. n Drain the Fuel gascolator by the draining vent on the fuel gascolator tank Remove all fuel from Fuel gascolator tank Remove Fuel filter tank from the Fuel gascolator Clean Fuel gascolator fuel strainer and sediment bowl Inspect the Fuel gascolator sealing for condition replace it if damaged 6 Install back Fuel filter tank from the Fuel gascolator The rest of the Fuel filter tank installati on process goes in reverse to the Fuel filter tank removing process 7 Move the Fuel Selector Valve to the Right tank position ON Inspect Fuel Gascolator for leakage 8 Install back the Upper cowling and Bottom cowling Seite 30 N V s Maintenance Manual V001 JEP CT IIMOE C FRECCIA 2 18 PITOT STATIC PRESSURE SYSTEM The pitot static tube is located under the leading edge of the right wing and consists of a air duct Total system pressure is sensed through the hole in the pitot tube face and static pressure is sensed through the holes on both sides of the rear part of fuselage Pressure distribution to individual instruments is received by means of flexible plastic hoses The tube supplies dynamic ram air pressure to the airspeed indicator and the static ports supply outside atmospheric pressure to the airspeed indicator altimeter and vertical speed indicator If installed the altitude hold portion of the autopilot or mode C transponder is also connected to the pitot system w w Static Pressure System Stati
26. ne and its equipments the fuselage and are fixed each other through collblock In the lower part of the cover there are the air intakes to cool the engine Fuselage is made up of a shell like structure in carbon fibre epoxy resin Fin is an integral part of the fuselage Wing attaching points are made up of 2 carbon fibre spars going through the shell Engine mounting pylon is made up of welded steel tubes The engine is separated from the fuse lage by means of a firewall protection Cockpit seats are positioned side by side and their shape is rigid and ergonomic not adjustable Safety belts have three junction points and are adjustable and provided with a single lock easy to unfasten The baggage compartment is located behind pilots seats it is allowed to transport a maximum of 10 kg A Plexiglas canopy can be opened lifting 2 3 ENGINE MOUNTS The engine mounts are made of a three dimensional frame with steel tubes The engine mounts have the fittings with the fuselage and the engine through bolts and rubber silent blocks The oil radiator and cooling fluid radiator are installed on some props The order of radiators installation in the engine systems is explained in the engine manual ENGINE MOUNTS Engine only principle illustraion Engine mount Seite 12 Seite 13 N N Maintenance Manual V001 V apasqa Maintenance Manual V001 FRECCIA IPOD VELG IPR OS VELG FRECCIA 2 4 FIREWALL 2 6 WINGS T
27. nside the cockpit on the stick grips and which transmits the movement to the actuator positioned inside the elevator Adjustment of the travel is possible by the pushrod that join the actuator to the trim bellcrank UPPER SKIN AND SPAR NOT SHOWN FOR CLAFITY E DPEsmETON TEN T r Fi 2 frano HINGE msama 3 ACTUATOR SUPPORT FTEG26F2 E ste Seite 21 NERE Maintenance Manual V001 FRECCIA W IAT IEE EE 2 12 RUDDER CONTROL Rudder control constists of pedals connecting rods bearings bowed cables The left and right pedals have independent rotation axles Two cables the left one and the right one are fixed on the eyelets welded to the pedals The cables are fixed on their other edge to the rudder bellcrank which are installed on the rudder through a plate glued and screwed The control system ends with the connecting rods which link the pedals to the front undercarriage nose wheel The control stops of rudder steering are put on the support of the steering bellcrank The rudder s angle of steering on the left and on the right is of 25 Adjustment of The Rudder Control The angles of steering from the neutral position are of 25 2 As for the adjustment you must 1 Putthe nose wheel in neutral 2 Itis necessary that neutral position of the rudder pedals correspond to neutral position of nose wheel Access to nose wheel rudder pedals pushrods for check and adjustment are tw
28. o inspection holes on the firewall 3 Then check or adjust the uniball that connect Bowden cable to rudder bellcrank so also the rudder is in neutral position The cables cross at the back part of the fuselage 4 Atthe end they must be tightened gradually until the rudder is straight and it doesn t move Em DESCRIPTION PN day i PEDAL repoa dal 2 BoT IN 931 m6x40 4 3 8 20 B0LT DIN 931 XA 4 Seite 22 N Maintenance Manual V001 IPO IMe E FRECCIA 2 13 UNDERCARRIAGE It is a fixed three wheel undercarriage with a turning nose wheel and disc brakes on the main lan ding gear Fairing are installed as optional components The front undercarriage leg is made of steel and it is provided with shock absorber Front under carriage is connected to rudder pedals The main undercarriage legs are made of composite materials UNDERCARRIAGE s I N Steering Nose Wheel Main Undercarriage Dymension Pressure Nose wheel 4 00 4 8ply 1 5 bar Main wheel 13x5 00 6 4 ply 1 8 bar Seite 23 _ Maintenance Manual V001 gt FRECCIA M INTEL 2 14 EQUIPMENT MINIMUM CONFIGURATION Control lamps Switches Display Trim 1 Generator 1 Main gomz s 2 Battery 2 Fuel Pump Switch Primary Flight Display 3 Fuel Pump g 3 EFIS EMS Left Stick lt gt Right Stick Engine Monitor System Gp M lgnition Switch Breakers Ignition Switch
29. ol stick rudder pedals damage centered paral rudder wire rope bolts visible bearings tail fuselage difficult to reach bearings wings under cabin floor aileron elevator and rudder hinges flap handle elevator trim ENGINE In addition to Rotax manual four strokes engines overhaul every 2000 hours engine cover screws engine mount engine mount dumpers and other rubber parts air filters electric terminals joints and connectors hoses radiator mount exhaust muffler exhaust pipe springs and fire protection throttle choke propeller wire drive ENGINE CONTROL choke and throttle lever wire ropes levers PROPELLER AND SPINNER surface condition fastening bolts propeller pitch propeller balance FUEL SYSTEM general leakage water inside gascolator dirt and gascolator filter wing fuel tank caps fuel tank caps o ring fuel valves and leakage Maintenance Manual V001 FRECCIA SC R every 500 hrs or 5 years c eme c cC c eme HEM _ _ B ci I REM _ _ i See manufacturer s manual C C HEM c m c _ E O every 500 hrs or 5 years c psc C sc SC lt CL CL HER ed Co Seite 35 Maintenance Manual V001 FRECCIA ELECTRICAL WIRING battery battery fluids instrument panel wires and connectors NAV AC and LDG lights fuses OIL AND WATER LINES oil and cooling fluids level oil and cooling fluids leakage
30. ons at the welding spots Check the wheels verify the condition of the rims about the presence of cracks or deforma tions Make sure of the good fastening of the wheels fixing nuts Check the tyres verify if there s an irregular consumption The tyres must be replaced in the case of these defects Anomalous inflation in a part of the tyre Wear of the covering throughout to the chord Cuts and tears on the covering for more than 30 mm Verity if the tyres aren t turned compared to the rims Verity the tyres pressure Front 1 6 bar Maingear 1 8 bar Check the tubes of braking circuit by making sure of the absence of brake fluid Make sure of the absence of cracks and of deteriorations of the wheels fairings Check the wing relatively to the absence of cracks and detormations Check the wing flap aileron s covering about the paint s deterioration In case of cracks or slivers of the lacquered varnish it s necessary to renovate through a second coat Seite 37 Maintenance Manual V001 FRECCIA Seite 38 21 22 23 24 25 26 27 28 29 30 31 32 33 34 35 36 gt 7 PrrOo sJTILC C AEROSPACE SYSTEMS Check by a protractor the rudder surfaces angles of deviation If these deviations are more important than their tolerances adjust them Remove the cover s top check the fuel circuit s tubes and the valves about the absence of fuel leaks Check the fixings of the battery box t
31. pty except for the residual amount they have been proved by anybody authorized from Junkers Profly GmbH When weighing the aircraft in both axes must be horizontal Horizontal reference line is the lower cockpit entry edge Reference point is the front wing edge at the transition to the fuselage Airplane against rolling off Under each wheel fix a weighing scale and determine the weights All work done by yourself are at your own risk and responsibility The rescue system is free of maintenance works if used appropriately for the duration of 6 years After activating the system or after this span of 6 years the rescue system has to be sent to the ee ee WEIGHING PROCEDERE This check may only be executed by the manufacturer BE For every damage during the use which might endanger the safety of the product Junkers Profly assures repair of the rescue system and its reduction into the original condition Every damage must be communicated to Junkers Profly It is recommended to change all fixing cords out of Kevlar or Polyamide after 12 years or after 18 years F 8 4 MAINTENANCE DURING STORAGE After air traffic the system has to be saved with transport lock Xj It is approved to connect transport lock with firing key 3 Gre Li G Therefore you avoid that the rescue system is locked mistaken during the flight i In case of long term storage the rescue system should kept under dry and room temperature con BE Reference Plane di
32. r Enner enap E 31 A ROPO u EE E E EE E EE 32 Le BE SS IT a r E E etre pee E ees eee enone eee 32 3 MISE TONG ireren SEE E Eee 33 3 1 Scheduled Airplane IRspections uu Lu a sasawaiwassiwkuswiiwuyupaqais 33 32 epecion anora hours Ol Wl INE omen reen eee EE NE 36 3 3 Inspection after 25 hours at least once a month 38 3 4 Inspection after 100 hours of flight at least once a year 38 Syd TE algte Hop S ei D ee E T 39 Seite 2 7 PVrO STIEC Cl AEROSPACE SYSTEMS N a 7 PVOsSNILCl AEROSPACE SYSTEMS Maintenance Manual V001 FRECCIA 4 Ground Handling SES usss assasi asa 40 4 1 Relocating the Airplane on Ground 40 1 FYING vost u E uyssssqsspasasspqyiasaqumaayapanqsayaesennasqakusqpasuuypspasnanta 41 VADON u uum s NEEE EE 41 44 TLiu ngangkevel ingu u uu u eres EE 42 5 Cleaning and Gare uuu uu asa ere NESES TEO as 43 Sle PamieqtrEwaepi s G u uuu pasaspaqa ee ere 43 e S y u uma ma ERE ar ne eer 43 2o Ppl SEE eee ss 43 S Erigi a aasakanawiiewapawaepalussakasa uyqhuywyawaqmywayapaqqhuispathukayasakamumaqteialpwpqhutspan 43 z s CENI TO SEE AEE A E NAT E AE 43 Gs REPARATIONS SSB EEN ENE SE E E S od 6 1 Main wheels assemblage and disassemblage 44 6 2 Replacement of brakes padss a 45 6 3 Replacement of the main wheel s
33. r gust lock far Note the size of the required area is to be increased Respectively to provide space for supplementary equipment such as antennas of radio 4 4 Lock the cockpit canopy and apply a canvas cover if available equipment or other equpment installed according to the operators options 4 3 4 1 RELOCATING THE AIRPLANE ON GROUND If using the towing bar on a level surface one person is able to move the airplane The tow bar Is to be fixed to the nose wheel by means of two lugs If the ground is not even and there are difficulties in moving the airplane two people may manage the relocation balancing the plane on the main wheels One person should guide the wingtip and the other should control the move ment with the tow bar ir Do not push or pull the airplane by control surfaces and fairinos Push not on the winos except the position in following illustration FORWARD HANDLING Seite 40 TYING DOWN If available lugs for the tie down for roping the airplane When tying down the following should be observed 1 1 lt is recommended to have the airplane pointed into wind 2 2 Put chocks in front of the main wheels 3 3 Apply locks to the ailerons rudder and elevator or fasten the control sticks with safety belts 4 4 Put the ropes through the specified lugs and attach the rops to the ground anchors The re should only be slight tension on the tie downs to prevent sagging 5 5 Apply the cover to the pitot
34. r soaps which are acid alkaline or abrasive To remove spots of grease or oil use a piece of cloth with degraseing solvent After use of degraseing solvent the surface should be re waxed and polished To polish the painted surfaces a soft cloth or chamois leather should be used Aged painted surfaces can be treated with automotive waxes or good quality polishing com pounds GLASS PANELS The greatest care should be taken to avoid scratches when cleaning glass panels of plexiglass Never wipe the glass panels when dry Rinse the panel with clean water or solution of mild soap and then wipe with soft clean cloth soonge or chamois leather To remove films of oil or grease use tribasic sodium phosphate well dissolved in water Sediments of grease or oil if difficult to remove should be cleaned with methanol hexane or naphtha Finally rinse with clean water avoiding excessive rubbing of the glass panel surface F Caution Do not use petrol benzene acetone anti icing compounds or paint solvents because these substances soften the plexiglass or may give rise to a network of fine cracks PROPELLER The propeller is to be cleaned in the same way as the painted surfaces ENGINE The engine is to be cleaned as indicated in the Engine Maintenance Manual CABIN INTERIOR The seats carpets and upholstery have to be cleaned with a vacuum cleaner Do not use water to clean items of cloth or fabric Foam based shampoos for gener
35. r to the following table ENGINE SYSTEM PART ROTAX 912 ULS ENGINE Propeller Engine fittings Fuel filter Battery Fuel and oil sleeves Engine mounts and main undercarriage plate s silent blocks Fuel pump Brake small pads Brake disc Life saving equipment if it s present Tyres Tools LIFE SPAN First overhaul after 1500 hours or 15 year of use See manufacturer s user ma nual According to engine manual or in accordance with their state and condition 100 h 2 years According to their state and condition According to their state and condition According to their state and condition According to their state and condition According to their state See manufacturer s user ma nual According to their state and condition According to their state and condition SPARE PART REPLACEMENTS End of potential End of potential End of potential or wear and tear End of potential End of potential Wear and tear damage Wear and tear damage Breakdown Breakdown Breakdown See manufacturer s user manual Wear and tear damage Breakdown As the previous table some elements and subsets must be overhauled or replaced in the aircraft s litetime The technical staff who guarantee the use of the aicraft must check frequently these ele ments good conditions and dependability and they must replace them according to their state and condition Any yielding found out in the u
36. s done by AUTHORISED SERVICE PERSONNEL SC Special check up measuring verifying tolerances and functionality DONE BY AUTHORISED SERVICE PERSONNEL ONLY O Overhaul Seite 33 Maintenance Manual V001 FRECCIA CHECK LIST FROM ENGINE S MANUFACTURER MANUAL CHECK LIST FROM PROPELLER MANUFACTURER MANUAL WING AND TAIL SURFACES surface and structure condition deflection without free play bearings moving parts bushing Lights if installed self adhesive sealing tape horizontal tail mount drain holes FUSELAGE surface and structure condition elevator control tube bearing undercarriage struts attaching points doors hinges rudder control wires and hinges CABIN control levers instrument panel seats control levers free play instruments and pitot static glass surface clean attached safety harnesses and attach points parachute rescue system activation handle wing connectors fuel electrical bolts and spar pins wing main bushing control connectors UNDERCARRIAGE tires main strut tail nose wheels strut condition wheel axis and wheels hyd brake lines brake fluid brake discs wheel bearing wheel fairings Seite 34 Prone AEROSPACE SYSTEMS 100 hours first 5 hours Daily RE O LO LO eee R 500 hrs or 5 years R on condition gt 7 PrrOosTILC Cl AEROSPACE SYSTEMS CONTROLS LO every 100 hrs or yearly general free play contr
37. se must be put right and every parts where some yieldings have been found must be checked carefully The list of the elements and the subsets which are subject to replacement is quoted in the engine manuals The replacement and installation techniques of the aircraft s other elements and subsets are quo ted in the respective chapters Seite 10 ae u i IPVOIMNMEE GS FRECCIA Maintenance Manual V001 AEROSPACE SYSTEMS 1 4 FUEL AND OTHER LIQUIDS CAPACITY ENGINE COOLING SYSTEM Cooling fluid capacity 2 160 Radiator volumeO 600 Engine cooling cavities volume 1 410 ENGINE LUBRICATION SYSTEM System total volume 3 BRAKING SYSTEM System total volume Oo FUEL OIL AND OTHER LIQUIDS FUEL Car fuel at a 90 octane rating for ROTAX 912UL at a 95 octane rating for ROTAX 912 ULS REMARK the use of leaded petrol is forbidden mm OIL Synthetic motorcycle oil from 50W 40 to 20W 50 according to the respective ambient temperature UI REMARK The use of oil additives is forbidden s COOLANT Car anti icing used for aluminium alloy engines BRAKE FLUID Car brake fluid Seite 11 NET LEN Maintenance Manual V001 D Maintenance Manual V001 FRECCIA M CIA T IE E MM CIA T IE EE FRECCIA 2 TECHNICAL DESCRIPTION S gt 2 2 ENGINE COVER _ The engine is covered by a cover made of a top part and a lower one The two pieces are fixed to This Section contains a description of the airpla
38. the elevator one through a bar Seite 19 NERE N Maintenance Manual V001 V Maintenance Manual V001 FRECCIA M TITEL M TITEL FRECCIA HALF FUSELAGE SHELL FLOOR SEATS NOT SHOWN FOR CLARYTY L uu 914 I _ 7 a t a fl Ta s t f FRAME 533 e _ an DETAIL 2 DETAIL 1 GROUP 1 ELEVATOR AND AILERONS DETAIL 2 GROUP 2 ELEVATOR Zz DETAIL 3 GROUP 3 ELEVATOR i re DETAIL 5 DETAIL 4 GROUP 4 ELEVATOR i DETAIL 5 GROUP 5 AILERONS 2 11 Seite 20 Adjustment of The Elevator Control The control stick s neutral position in the cockpit must correspond to the elevator control neutral position The rigging of the elevator s angles of steering is possible through an adjustable connecting rod To modify the lenoth 1 unscrew the connecting rod from the elevator s bellcrank 2 unscrew the locknut 3 then screw or unscrew the adjustable head Check of the system is made in the following points 1 open inspection hole below the fuselage to have access to stick group 2 remove the trunk to have access to the control quickdrarws 3 check nuts and locking nuts of the system TRIM CONTROL Trim adjusts the elevator position in a more accurate way to avoid continual corrections by the control stick in flight Its movement is electric controlled by a switch located i
39. the engine groups ordinary and extraordinary maintenance the user must follow the m instructions in Rotax manual g As for the propeller s ordinary and extraordinary maintenance the user must follow manu m facturers operating manual s instructions r NOTE 1 At the moment for maintenance related to tightening or substitution of detacha ble match elements you should mark the revised elements with an indelible colour The colour must be different according to the kink of maintenance frequency replacement tightening etc The legend with the colours which have been used and the kind of main tenance which have been carried out will be included enclosed in the aircraft s maintenance booklet NOTE 2 in any case refer to the manufacturer to specialized firms or to authorized resel lers and render a precise account of maintenances ir All major repairs and spare part replacements MUST be done by authorised service person nel However you are encouraged to take care of preventative maintenance yourself This includes tire and wheel bearings replacements safety wire replacements door and safety harness replace ment light bulb replacements fuel hose replacements battery servicing and replacement sparks and spark plugs replacements and air filter replacements Seite 4 Seite 5 Maintenance Manual V001 FRECCIA MM IAT IUE ES 1 1 THREE VIEW DRAWINGS FRECCIA te 7004 lt STATION 0 PROPELLER FLANGE E 3
40. tions BP Reference Point BL horizontal Reference Line Other maintenance works will not be necessary S Center of Gravity Arm X3 Moment Frontwheel 850 mm G3 Weight Frontwheel Xu Moment Mainwheel left 650 mm GL Weight Mainwheel left XRe Moment Mainwheel right 605 mm Gre Weight Mainwheel right Calculation Center of Gravity Arm w CG OJ X Aig Ge X Aes Gs XXS as 7 Giz Gea t O3 CG m on CG Range Center of Gravity Arm a at 290 kg 1 78 206 mm mae 295 300 305 310 315 320 325 330 335 340 at 340 kg 188 233 mm Empty Weight kg The CG is in the weight and balance If changes to the equipment to be made a new El weighing with the determination of the CG must be done Seite 50 Seite 51
41. tyre a 45 6 4 Materials used in manufacturing process 45 7 information signs and Markings 46 FA i E A E s SEE E 46 la Tupi ii u u uuu uuu asna NERE RTE aaa 47 7 0 Airspeedindicator MARKS ornare nere kE EE Eb Ness seen 47 0 RESCUE SY OI EI ES e Eee 48 8 1 Technical data of the Magnum Light Speed Softpack 48 92 AS Ra AU IAC UI sect orc u NEN EE EE 49 8 3 Maintenance of the Magnum Light Speed Softpack 50 8 4 Maintenance during storage nerne een 50 9 Weighing Procedure uuu aun asa iis n EEE E T A A 51 Seite 3 YW Maintenance Manual V001 D D Maintenance Manual V001 FRECCIA PrrOolHeCl PrrOolNIeLCl FRECCIA AEROSPACE SYSTEMS AEROSPACE SYSTEMS 1 GENERAL This Maintenance Manual is updated regularly The latest versions can be downloaded as a PDF file on the Web site of the manufacturer www promecc com The current version number is prin ted on each page in the header V Respect the copyright This flight manual may not be copied or distributed without the written consent of the originator not even in a modified form MANUFACTURER of the aircraft PRO MECC s r l Zona Artigianale S S 16 Km 976 73022 Corigliano D Otranto LE ITALY www promecc com UJ As for
Download Pdf Manuals
Related Search