Pro.Mecc Freccia User manual

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

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CONTENTS
1. General ..................................................................................................... 5
1.1. Three-view drawings – Freccia ...............................................................6
1.2. Dimensions.............................................................................................8
1.3. Lifetime restrictions ..............................................................................10
1.4. Fuel and other liquids...........................................................................11
2. Technical description............................................................................... 12
2.1. Fuselage ...............................................................................................12
2.2. Engine cover.........................................................................................13
2.3. Engine mounts .....................................................................................13
2.4. Firewall .................................................................................................14
2.5. Tank ......................................................................................................14
2.6. Wings ...................................................................................................15
2.7. Empennages.........................................................................................16
2.8. Ailerons control ....................................................................................17
2.9. Flaps control.........................................................................................19
2.10. Elevator control ....................................................................................19
2.11. Trim control ..........................................................................................21
2.12. Rudder control......................................................................................22
2.13. Undercarriage.......................................................................................23
2.14. Equipment............................................................................................24
2.15. Primary Flight Display and Engine Monitor System (Dep. Configur.)....25
2.16. Electrical System...................................................................................26
2.17. Engine – ROTAX 912 ULS.....................................................................27
2.18. Pitot – static pressure system ...............................................................31
2.19. Propeller ...............................................................................................32
2.20. Brake system ........................................................................................32
3. INSPECTIONS ......................................................................................... 33
3.1. Scheduled Airplane Inspections...........................................................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
5.3. Propeller ..............................................................................................43
5.4. Engine ..................................................................................................43
5.5. Cabin interior........................................................................................43
6. REPARATIONS......................................................................................... 44
6.1. Main wheels’ assemblage and disassemblage.....................................44
6.2. Replacement of brakes’ pads...............................................................45
6.3. Replacement of the main wheel’s tyre..................................................45
6.4. Materials used in manufacturing process.............................................45
7. information signs and Markings.............................................................. 46
7.1. Panel.....................................................................................................46
7.2. Further markings ..................................................................................47
7.3. Airspeedindicator Marks ......................................................................47
8. RESCUE SYSTEM..................................................................................... 48
8.1. Technical data of the Magnum Light Speed Softpack..........................48
8.2. Installation drawings.............................................................................49
8.3. Maintenance of the Magnum Light Speed Softpack............................50
8.4. Maintenance during storage ................................................................50
9. Weighing Procedure ............................................................................... 51

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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
As for the engine group’s ordinary and extraordinary maintenance, the user must follow the
instructions in Rotax manual.
As for the propeller’s ordinary and extraordinary maintenance, the user must follow manu-
facturers operating manual’s 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 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.
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.

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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 m2
RUDDER AREA = 0,42 m2
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°
20
°
600
2972
35% mac
mac=
758
900
687
1200
1400
900
2972
8762
1
°
202
B
A
1741
900
299 AB
1741
8762
MAC
1938
66
FUSELAGE
1486
1/4 C
12°
24
°
AILERON DEFLECTION
A
B
A:
B:
35
°
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 m2
ROOT AIRFOIL = NACA 63.2 412
TIP AIRFOIL = NACA 63.2 412
WING ASPECT RATIO = 7,54
SWEEP = 1°
TAPER RATIO = 1,556

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1.2. DIMENSIONS
WING
Wing span 8,777 m
Wing chord 1,209 m
Wing surface 10,13 m2
Dihedral 5°
AILERONS
Aileron span 1,741 m
Mean chord 0,27 m
Aileron surface 0,47 m2
Steering angle (stroke) 24° ± 1°(up)
12° ± 1°(down)
FLAPS
Flap span 1,741 m
Mean chord 0,38 m
Flap surface 0,66 m2
Flaps positions 0° / 35° (down)
FUSELAGE
Total length 7,248 m
Max width 1,20 m
Max height 2,553 m
Frontal surface 1,20 m2
Max section surface 1,00 m2
Fuselage surface crossed by air flow 14 m2
TAIL PLANE (HORIZONTAL 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°
ENGINE
Engine model ROTAX 912 ULS
Maximum rotational speed of the propeller 2400/2800 according to the engine model
Maximum rotational speed of the engine 5800 rpm in 5min / 5600
Propeller According to the customer’s demand
UNDERCARRIAGE
Width of the rear landing gear (undercarriage) 1,6 m
Distance between the turning wheel and the rear
landing gear
1,5 m

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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, refer to the following table:
ENGINE, SYSTEM, PART LIFE SPAN SPARE PART REPLACEMENTS
ROTAX 912 ULS ENGINE First overhaul: after 1500
hours or 15 year of use
End of potential
Propeller See manufacturer’s user ma-
nual
End of potential
Engine fittings According to engine manual
or in accordance with their
state and condition.
End of potential or wear and
tear
Fuel filter 100 h End of potential
Battery 2 years End of potential
Fuel and oil sleeves According to their state and
condition
Wear and tear, damage
Engine mounts and main
undercarriage plate’s silent-
blocks
According to their state and
condition
Wear and tear, damage
Fuel pump According to their state and
condition
Breakdown
Brake small pads According to their state and
condition
Breakdown
Brake disc According to their state Breakdown
Life-saving equipment (if it’s
present)
See manufacturer’s user ma-
nual
See manufacturer’s user manual
Tyres According to their state and
condition
Wear and 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 use 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.
1.4. FUEL AND OTHER LIQUIDS
CAPACITY
ENGINE COOLING SYSTEM
Cooling fluid capacity 2,160 l
Radiator volume0,600 l
Engine cooling cavities volume 1,410 l
ENGINE LUBRICATION SYSTEM
System total volume 3 l
BRAKING SYSTEM
System total volume 0,150 l
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!
OIL
Synthetic motorcycle oil from 50W-40 to 20W-50, according to the respective ambient
temperature.
REMARK: The use of oil additives is forbidden!
COOLANT
Car anti-icing used for aluminium-alloy engines.
BRAKE FLUID
Car brake fluid.

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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
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.
ENGINE COVER
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 mountEngine 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.
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.

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2.6. WINGS
The aircraft is provided with a low and tapered wing made up of 2 half-wings in carbon fibre that
can be disassembled, with a main spar going through the fuselage and with a wing rib equipped
with wing-fuselage connection points. Wing tips can be removed.
The structure of wing, flap and aileron is identical to the one of tail unit.
2.4. FIREWALL
The firewall 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 heat and flame resistant.
FIREWALL
2.5. TANK
The tank are made of fibreglass and are in the right and left wing-halves. At the rear they have a
cylindrical screwing which is set in the hole rib; on the front it is secured to aluminium ribbing.
TANK

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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.
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.
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.
4 Screw and lock the external checknut.

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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 M6 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 some turns and
rig the head until it can enter easily in the control-stick bolt;
5 Screw again the M6 nut and lock the checknut;
6 Close the door.
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.
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 the elevator one through a bar.

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Adjustment of The Elevator Control
The control stick’s neutral position in the cockpit must correspond to the elevator control’s neutral
position.
The rigging of the elevator’s angles of steering is possible through an adjustable connecting-rod.
To modify the length:
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.
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 electric controlled by a switch located inside 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.

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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 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 at the back part of the fuselage.
4 At the end, they must be tightened gradually until the rudder is straight and it doesn’t
move.
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
Steering Nose Wheel Main Undercarriage
Dymension Pressure
Nose wheel 4.00 – 4” 8 ply 1.5 bar
Main wheel 13x5.00 - 6” 4 ply 1.8 bar

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2.14. EQUIPMENT
Control lamps
1 Generator
2 Battery
3 Fuel Pump
Switches
1 Main Switch
2 Fuel Pump
3 EFIS / EMS
Ignition Switch
Ignition Switch
Choke
Breakers
Switch
Left Stick <-> Right Stick
Primary Flight Display
Engine Monitor System
Display Trim
Tactile for Trim
MINIMUM 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
- Fuel Pump
- Generator
Switches
1 Main Switch
2 Fuel Pump
3-8 Depends on config.
Tactile for Trim
Ignition Switch
Carburator HeatingChoke Cabin Heating
Breakers
Switch
Left Stick <-> Right Stick
Display Trim
Flight Instrumens
Navigation System
Engine Instruments
MAXIMUM CONFIGURATION
2.15. PRIMARY FLIGHT DISPLAY AND ENGINE MONITOR SYSTEM (Depending Configuration)
PFD / EMS
DESCRIPTION
PFD Articial 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

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2.16. ELECTRICAL SYSTEM
The aircraft is equipped with a 12-volt, direct-current electrical system with grounded negative
pole.
The primary source of electrical energy is provided by the engine mounted interior alternator/ge-
nerator with total power of 750 W.
The internal alternator located at the rear of the engine block will charge the battery up to 13.5
VDC.
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,
then the circuit breaker disconnects that circuit.
ELECTRICAL SYSTEM
FUSES
Start Armed 2 A
Fuel Pump 2 A
EFIS 3 A
Flap 3 A
Trim 1 A
2.17. ENGINE – ROTAX 912 ULS
For engine inspection and maintenance refer to original Rotax manuals supplied with the aircraft:
■Operator´s Manual for ROTAX engine Type 912 Series
■Documentation for ROTAX aircraft engines (CD – ROM)
■Service 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 power levers and the choke one are fixed to a control box made of carbon fibre and they are
linked to steel-sheath cables.
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
Control box
Quick draw Control-engine cable
Sheath
Fuel lever
Lever
Adjustment of engine control
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
case, adjust the engine choke lever. Loosen the M8 nut, lock it with a proper spanner and secure;
consequently, the friction increases and the engine’s control lever remain in a more appropriate
position.

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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 regulator (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
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 fluid 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
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.

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Gascolator inspection/cleaning
1 Remove upper cowling and bottom cowling.
2 Make sure the Fuel Selector Valve is in the off position.
3 Drain the Fuel gascolator by the draining vent on the fuel gascolator tank. Remove all fuel
from Fuel gascolator tank.
4 Remove Fuel filter tank from the Fuel gascolator
5 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.
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.
Static Pressure System
Static Pressure System
Pitot Pressure System

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3. 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
airplane manufacturer.
It is reasonable to proceed according to a prescheduled scheme of lubrication and maintenance,
appropriate to the operating conditions and climate.
3.1. 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:
CCheck-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
RReplacement - 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
OOverhaul
2.19. PROPELLER
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-
nufacturer authorized service center.
2.20. 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 fluid 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 replacement: BRAKE FLUID DOT 4.

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 Daily first 5
hours
25
hours
100
hours
200
hours
500
hours
1000
hours
10 000
hours
CHECK LIST FROM ENGINE’S MANUFACTURER MANUAL C       
       
CHECK LIST FROM PROPELLER MANUFACTURER MANUAL C       
       
WING AND TAIL SURFACES     SC SC O
surface and structure condition C C C C SC   
deflection without free play C    SC   
bearings - moving parts‘ bushing C  LO LO SC   
Lights (if installed) C       
self-adhesive sealing tape C       
horizontal tail mount C C C C SC   
drain holes C   CL    
       
FUSELAGE      SC SC O
surface and structure condition C C C C SC  SC 
elevator control tube bearing C   LO SC   
undercarriage struts attaching points C C C SC SC   
doors, hinges C   LO SC   
rudder control wires and hinges C   LO SC   
       
CABIN      SC SC O
control levers, instrument panel, seats C   C    
control levers‘ free play C C C C SC   
instruments and pitot-static Ccheck yearly
glass surface: clean, attached C       
safety harnesses and attach. points C   C    
parachute rescue system activation handle Csee manufacturer‘s manual
wing connectors: fuel, electrical C C C C SC   
bolts and spar pins C C C C SC   
wing main bushing, control connectors C C C C SC   
       
UNDERCARRIAGE      SC SC O
tires Creplace on condition or every 5 years
main strut, tail/nose wheels 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   
difficult-to-reach bearings (wings, under cabin floor)    LO SC
LO+SC  
aileron, elevator and rudder hinges C   LO SC   
flap handle C   C SC   
elevator trim C   C SC   
       
ENGINE        
In addition to Rotax manual:        
four-strokes engines (overhaul every 2000 hours) 
engine cover screws C C  C    
engine mount C C  SC    
engine mount dumpers and other rubber parts  C  SC R every 500 hrs or 5 years
air filters C C  CL  SC  
electric terminals, joints and connectors, hoses, radiator mount C C  SC    
exhaust muffler C C  SC  SC  
exhaust pipe springs and fire protection C C  SC  R  
throttle, choke, propeller wire drive    SC  R  
       
ENGINE CONTROL        O
choke and throttle lever wire ropes C   C+LO SC R  
levers C   C SC   
       
PROPELLER AND SPINNER See manufacturer‘s manual
surface condition C       
fastening bolts   C C R   
propeller pitch C    SC   
propeller balance C     SC  
       
FUEL SYSTEM O every 500 hrs or 5 years
general leakage C   SC SC SC  
water inside gascolator C  SC SC SC SC  
dirt and gascolator filter C CL CL CL CL R  
wing fuel tank caps C       
fuel tank caps o-ring     R every 500 hrs or 5 years
fuel valves and leakage C       
       

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ELECTRICAL WIRING      SC SC R
battery C   C SC   
battery fluids    C SC   
instrument panel wires and connectors    C SC   
NAV, AC and LDG lights C       
fuses C       
       
OIL AND WATER LINES O evry 500 hrs or 5 years
oil and cooling fluids level C       
oil and cooling fluids leakage C       
four-stroke engines oil (and engine filters) first 25 hours refer to engine manual
cooling fluid (level) refer to engine manual
hoses C   SC SC R  
radiators C       
water radiator pressure caps refer to engine manual
       
PITOT-STATIC LINING      SC SC O
instrument to pitot tube lining    C C   
instrument setting C       
pitot tube condition (clean, firmly attached) C   C C   
whole pitot-static lining    C C   
3.2. INSPECTION AFTER FIRST 25 HOURS
Note: the inspections on engine after the first 25 hours of flight must be carried out in ac-
cordance with the engine’s 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.
3.3. INSPECTION AFTER 100 HOURS OF FLIGHT (AT LEAST ONCE A YEAR)
Note: the inspections on engine after 100 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 Make sure that the battery is disconnected and that the supply-system valve is locked.
2 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.
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 case of cylin-
ders which are not so much warmed-up or overheated, identify the reason of this event.
7 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.
8 Clean the aircraft covering and the undercarriage from dirt and dust. Tidy up the inside of
the cockpit.
9 Check the fuel and oil reserves in the tanks and weigh up their respective consumptions.
10 The check-up steps is the same as the pre-flight check-up in the Flight Manual.
11 Check the conditions of the undercarriage’s axes and the mounting tools on the fuselage
frame. Check that there aren’t any cracks or deteriorations at the welding spots.
12 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.
13 The tyres must be replaced in the case of these defects: Anomalous inflation in a part of
the tyre
14 Wear of the covering throughout, to the chord
15 Cuts and tears on the covering for more than 30 mm
16 Verify if the tyres aren’t turned compared to the rims.
17 Verify the tyres’ pressure: Front 1,6 bar, Maingear 1,8 bar).
18 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.
19 Check the wing relatively to the absence of cracks and deformations. Check the wing, flap,
aileron’s covering about the paint’s deterioration.
20 In case of cracks or slivers of the lacquered varnish it’s necessary to renovate through a
second coat.

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21 Check by a protractor the rudder surfaces’ angles of deviation. If these deviations are more
important than their tolerances, adjust them.
22 Remove the cover’s top, check the fuel circuit’s tubes and the valves about the absence of
fuel leaks.
23 Check the fixings of the battery box, tighten the fixing bolts if need be.
24 Check the attaches of the oil tank, tighten the fixing bolts if need be.
25 Remove the propeller cone, check the propeller’s attachments.
26 Check the attachments of the tubes and of propeller-engine installation’s electrical cables.
If necessary, do the attachments again.
27 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.
28 Check the undercarriage’s attachment fittings about the movement, the axle’s wear and the
undercarriage’s elements.
29 Check the covers’ locking, lubricate them.
30 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.
31 Check the fuselage shell’s attachment fittings.
32 Verify the electrolyte’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 Check the actuating rods, their attachment fittings to the quick draws, check the bolts’
tightening.
3.4. LUBRICATION INSTRUCTION
UNIT AREA OF LUBRICATION 25 H 100 H LUBRICANT
1Engine
Throttle control cable into engine
compartment X X
Light oil
Choke control cable into the engine
compartment X X
Light oil
2Nose gear Nose gear leg and bearing of the
link to rudder pedals X X
Lubrication grease
3Main gear Axle bearings X X Lubrication grease
4Ailerons
Hinges X X Lubrication grease
Rod end bearing of the control
system X X
Lubrication grease
5Flaps
Hinges X X Lubrication grease
Rod end bearing of the control
system X X
Lubrication grease
Actuator hinges X X Lubrication grease
6Tail
Rod end bearing of the elevator
control system X X
Lubrication grease
Rudder hinges and bearing
Rudder Bowden cable X X
Lubrication grease
Stabilizer – Elevator hinges X X Lubrication grease
Hinges and movable parts of trim X X Lubrication grease
7Rudder
pedals All moving parts in cockpit area X X
Lubrication grease
LUBRICATION OVERVIEW
1
2
3
45
67