Pro.Mecc Freccia Maintenance Manual Download

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Maintenance Manual V001
FRECCIA

Maintenance Manual V001

FRECCIA

Seite 6

Seite 7

1.1. THREE-VIEW DRAWINGS – FRECCIA

2543

1600

1153

1154

5°

MAX=Ø1900

FRONVIEW

SIEDEVIEW

25°

947

645

1236

581

1351

mac

2111

VERTICAL TAIL AREA = 1,2 m

RUDDER AREA = 0,42 m

VERTICAL TAIL ASPECT RATIO = 1,4

660

4014

1500

3885

3707

7004

STATION 0 PROPELLER FLANGE

ARM OF VERTICAL TAIL
ARM OF HORIZONTAL TAIL

TOPVIEW

15°

600

2972

35% mac

mac=758

900

687

1200

1400

900

2972

8762

1°

202

1741

900

299

1741

8762

MAC

1938

FUSELAGE

1486

1/4

12°

AILERON DEFLECTION

PIVOT

A:A

HORIZONTAL TAIL AREA = 2,2 m

ELAVATOR AREA = 0,77 m

HORIZONTAL TAIL ASPECT RATIO = 4,3

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

Summary of Contents for Freccia

Page 1: ...MAINTENANCE MANUAL UL AIRCRAFT LTF UL 2003 Manufacturer No FRXXX Registration No D MXXX ...

Page 2: ...s 33 3 2 Inspection after 5 hours of flight 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 3 5 Lubrication instruction 39 4 Ground Handling 40 4 1 Relocating the Airplane on Ground 40 4 2 Parking 41 4 3 Tying Down 41 4 4 Lifting and Levelling 42 5 Cleaning and Care 43 5 1 Painted External Surfaces 43 5 2 Glass Panels 43 5 ...

Page 3: ... instructions 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 in...

Page 4: ...4 STATION 0 PROPELLER FLANGE ARM OF VERTICAL TAIL ARM OF HORIZONTAL TAIL TOPVIEW 15 2 0 600 2972 35 mac mac 758 900 687 1200 1400 900 2972 8762 1 202 B A 1741 900 299 A B 1741 8762 MAC 1938 66 FUSELAGE 1486 1 4 C 12 2 4 AILERON DEFLECTION A B A B 3 5 PIVOT A A HORIZONTAL TAIL AREA 2 2 m2 ELAVATOR AREA 0 77 m2 HORIZONTAL TAIL ASPECT RATIO 4 3 WING AREA 10 13 m2 FLAP AREA 0 66 m2 AILERON AREA 0 47 m...

Page 5: ...L TAIL Wing span 2 972 m Mean chord 0 758 m Aspect ratio 2 2 m2 Extension 4 3 Angle of incidence 1 2 ELEVATOR Elevator span 2 972 m Surface 0 77 m2 Stroke 20 up 15 down TRIM Width 0 75 m Chord 0 075 m Stroke 20 2 up 20 2 down VERTICAL FIN Vertical fin span 1 351 m Minimum chord 0 645 m Maximum chord 1 236 m Mean chord 0 947 m Surface 1 12 m2 Extension 1 4 RUDDER Surface 0 42 m2 Steering angle 25 1...

Page 6: ...tear damage Tools According to their state and condition Breakdown As the previous table some elements and subsets must be overhauled or replaced in the aircraft s lifetime 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 us...

Page 7: ...explained in the engine manual ENGINE MOUNTS Engine mount Engine only principle illustraion 2 TECHNICAL DESCRIPTION This Section contains a description of the airplane and its equipments 2 1 FUSELAGE 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 Engi...

Page 8: ...ewall is a structural element situated on the front part of the fuselage and it separates the engine from the cabin It s made of a composite material panel The part of the panel which is tur ned to the engine has the attachment fittings for supporting the battery case for the oil tank and for other components of the power plant and the aircraft systems The firwall is covered by a special material ...

Page 9: ...ers 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 Rigging of Ailerons Cont...

Page 10: ... 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 2 10 ELEVATOR CONTROL The stabilizer is slightly in nosedive position to facilitate the aircraft nose up especially o...

Page 11: ...e 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 2 11 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...

Page 12: ...nt you must 1 Put the nose wheel in neutral 2 It is 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 two 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 ...

Page 13: ... differently Therefore deviate the actual features of this figure Control lamp Battery Fuel Pump Generator Switches 1 Main Switch 2 Fuel Pump 3 8 Depends on config Tactile for Trim Ignition Switch Carburator Heating Choke Cabin Heating Breakers Switch Left Stick Right Stick Display Trim Flight Instrumens Navigation System Engine Instruments MAXIMUM CONFIGURATION 2 15 PRIMARY FLIGHT DISPLAY AND ENG...

Page 14: ... instruction fur ROTAX Type 912 und 914 series ROTAX service letter Warranty conditions for ROTAX engine types 912 and 914 series ROTAX engine Log book Engine removal installation and replacement can only be done by Pro Mecc authorized service center ENGINE CONTROL On the central control panel in the middle of the cockpit there are the handgrips relative to Throttle lever Choke push pull cable The...

Page 15: ...ads 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 allo...

Page 16: ...elector Valve to the Right tank position ON Inspect Fuel Gascolator for leakage 8 Install back the Upper cowling and Bottom cowling 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...

Page 17: ... 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 replacements done by AUTHORISED SERVICE PERSONNEL SC Special check up measuring verifying tolerances and functionality DONE BY AUTHORISED SERVICE PERSONNEL ONLY O Overhaul 2 19 PROPELLER ...

Page 18: ...els strut condition C C C C SC wheel axis and wheels C SC hyd brake lines C C SC R brake fluid C C SC R 500 hrs or 5 years brake discs C SC R on condition wheel bearing C SC R wheel fairings C C C CONTROLS LO every 100 hrs or yearly SC SC R general free play C C SC control stick C LO SC rudder pedals damage centered paral C C SC rudder wire rope C C SC bolts visible bearings tail fuselage C C SC d...

Page 19: ...y making sure of the absence of pet rol leaks from the fuel tanks and of oil leaks from the lubrication system 3 Check the fixing of propeller spinner 4 Remove the covers 5 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 6 Make the engine turn and make sure of the good working of all cylinders In c...

Page 20: ...lyte s voltage and its density in the battery 33 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 34 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 35 Check the tension of control cables 36 C...

Page 21: ...uld control the move ment with the tow bar Do not push or pull the airplane by control surfaces and fairings Push not on the wings except the position in following illustration FORWARD HANDLING BACKWARD HANDLING 4 2 PARKING 1 1 Position the airplane pointing into wind 2 2 Apply chocks to the main wheels 3 3 Secure the control sticks with the seat belts or tow bar gust lock 4 4 Lock the cockpit can...

Page 22: ...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 5 2 GLASS PANELS The greatest care should be taken to avoid scratches when cleaning glass panels of plexiglass Never wipe the glass panels whe...

Page 23: ...rcraft 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 ar...

Page 24: ...Zuladung 67 5 kg Maximale Zuladung 98 5 kg 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 Maximum take off weight 472 5 kg Minimum load 67 5 kg Maximum load 98 5 kg The warnings may vary according to configuration are al...

Page 25: ... descent rate by 475 kg 7 33 m s Opening time at standard speed min 100 km h 3 9 s Rocket container diameter 60 mm Rocket container length 270 mm RESCUE SYSTEM Opening for the rocket Firewall Softpack Rocket Release Lever Rescue System 8 2 INSTALLATION DRAWINGS CABLE SETUP CABLE MOUNTING 7 PARACHUTE BRIDLE CONNECTION POINT CABLE LENGTH 2200 mm FIREWALL ENGINE MOUNT ENGINE MOUNT FRAME 914 DIN 931 M...

Page 26: ...DURING STORAGE After air traffic the system has to be saved with transport lock It is approved to connect transport lock with firing key Therefore you avoid that the rescue system is locked mistaken during the flight In case of long term storage the rescue system should kept under dry and room temperature con ditions Other maintenance works will not be necessary 9 WEIGHING PROCEDURE This Section c...

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