Aeros Aeros-2 User manual

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Aeros-2/Cross Country
ultralight
Maintenance Manual
Wing: PROFI
Engine: Rotax 912 UL
Manufactured by:
AEROS Ltd
Post-Volynskaya St.5
Kiev 03061
UKRAINE
December 2019
Tel: [phone]
Fax: [phone]
E-mail: [email protected]
http://www.aeros.com.ua

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CONTENTS
1. GENERAL INFORMATION_________________________________________________________________4
2. DESCRIPTION OF THE AIRCRAFT__________________________________________________________4
3. COMPONENTS OVERVIEW________________________________________________________________5
4. CENTRE OF GRAVITY____________________________________________________________________6
5. PLACARDS______________________________________________________________________________6
6. TOOLING________________________________________________________________________________9
7. SPECIAL HAZARDS_______________________________________________________________________9
8. TORQUING PROCEDURES_________________________________________________________________10
9. SCREW LOCKING DEVICES_______________________________________________________________10
10. CORROSION PROTECTION_______________________________________________________________11
11. INSPECTION AND SERVICING SCHEDULES________________________________________________11
12. SPECIAL INSTRUCTIONS________________________________________________________________16
13. PERIODIC MAINTENANCE_______________________________________________________________17
14. WING TUNING__________________________________________________________________________24
15. TRIKE ASSEMBLY AFTER SHIPPING PROCEDURE__________________________________________25
16. TOWING, TAXIING AND TRANSPORTATION_______________________________________________26
17. CLEANING______________________________________________________________________________27

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1. GENERAL INFORMATION
This manual contains factory recommended procedures and instructions for maintenance, service
and ground handling of the Aeros-2 ultralight.
The Aeros-2 trike will be used in conjunction with a certified wing, therefore the operator has to
refer to the wing manual for any issues that are related to the wing component of the aircraft.
Definitions
Definitions used in this Manual such as WARNING, CAUTION and NOTE are employed in the
following context:
WARNING
OPERATING PROCEDURES, TECHNIQUES, ETC. WHICH IF NOT FOLLOWED
CORRECTLY, MAY RESULT IN PERSONAL INJURY OR DEATH.
CAUTION
OPERATING PROCEDURES, TECHNIQUES, ETC. WHICH IF NOT STRICTLY
OBSERVED, MAY RESULT IN DAMAGE TO THE AIRCRAFT OR ITS INSTALLED
EQUIPMENT.
NOTE
Operating procedures, techniques, etc. which considered essential to highlight.
2. DESCRIPTION OF THE AIRCRAFT
Aeros-2 is advanced two-seater (in line) weight shift controlled aircraft. It has been developed to
provide the economy and durability combined with maximum safety and comfort.
Aeros-2 is designed for up to 472.5 kg maximum take-off weight. The aircraft has been designed
with wide speed range allowing slow speed flight at very low fuel consumption, short take off
and landing as well as cruising speeds up to 130 km/h. The electric trim system for trimming the
aircraft in pitch gives precise fingertip control at the speed range of 80 – 110 km/h.
The power plant is a push arrangement and consists of Rotax 912 UL 80 HP engine and a three-
blade ground adjustable Aerolux propeller.
It features a 54 liters fuel tank, allowing long cross-country touring.
The trike is attached to the wing by way of a universal joint which allows the free movement of
the trike in pitch and roll by which control is affected. The trike includes the tricycle
undercarriage, power plant and cockpit.
The engine is mounted to the engine platform at the base of the engine. The fuel tank is mounted
beneath the engine platform.
The pilot cockpit is designed to allow for various size pilots.
The cockpit has a windscreen for improved wind deflection.
The Profi wing is the result of continued refinement of Aeros trike wings over the years since
1991. The wing is designed for two-seater trikes. It is the result of an extensive design and
development program aimed at optimizing your level of safety and satisfaction as a pilot,
through high performance and strength of construction.
This wing is safely controllable and stable at a wide range of operating speeds. The strength of
the wing is sufficient for different conditions of flight with defined load. It is very stable, and has
been designed primarily for cross-country flying.
The Profi sail has several cloth and Velcro shear ribs, which combined with an excellent sail fit,

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produces a wing that has light handling and very comfortable in turbulence. The battens ends are
designed to be adjustable to vary tension for tuning the wing. The batten mechanism allows
effortless installation and removal the battens.
An airfoiled aluminium section is used for the down tubes and king post to achieve minimum
drag.
3. COMPONENTS OVERVIEW
There are most important areas of the trike shown in this section to aid the maintenance
personnel.
The list may not be comprehensive.
Trike structure:
Cockpit: Engine:

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Front fork assembly: Hang point:
4. CENTRE OF GRAVITY
Trike:
Centre of gravity limits are not critical on the trike. With the trike attached to the wing,
variations of cockpit loading and fuel loading cannot influence the aircraft balance. The Aeros-2
trike is therefore not critical in regards to centre of gravity, although the load distribution in the
trike has a minor affect on the in-flight attitude of the trike.
Wing:
Aeros-2 trike with Profi wing should fly straight and level without any pilot input with a cruising
speed of between 75 k/h and 90 k/h.
Moving the wing hang block forward on the wing keel tube will speed the wing up.
Swivel both wing tips down equally will speed the wing up.
5. PLACARDS
The placards on the aircraft are designed to provide necessary information for the safe operation
of the aircraft. Details of the placards are listed below.
Flight limitations placards:

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The flight limitations placards are located on the instrument panel.
Emergency parachute placard:
The emergency parachute placard is
located on the instrument panel.
Pilot operating handbook placard:
The pilot operating handbook placard is located on the instrument panel.
Clear prop placard:
The clear prop placard is located on the left and right side landing gear struts.

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Fuel placard:
The fuel placard is located on the right side of the cockpit next to the filler neck.
Step and no step placards:
The no step placards are located on the left and right side landing gear struts and on the left and
right side of the cockpit.
The step placards are located on the left and right footrests.
Wing and trike data placards:
The wing placard is located on the keel tube of the wing.
The trike placard is located on the right front side of the base tube.

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6. TOOLING
There are no specialized tools (except for the air shocks) required for the maintenance described
in this Manual. Loctite will be required in certain locations and should always be renewed after
disassembly.
There is a list of tools that may be required.
-Loctite 243
- Open ended spanner set
-Torque wrench
-Screw drivers flat head set
-Screw drivers cross head set
-Hex key set
-Pliers
-Tie wire and tooling
-Foot air pump
-Various general care items.
Note: This list may not be comprehensive.
WARNING! The Aeros 2 airframe is relatively simple, but like any other aircraft requires
skilled and qualified service. It is not recommended self repair or reassembly by other than
Aeros Ltd approved agent. No replacement parts should be fitted unless they are factory supplied
and identified. All replacements and servicing should be entered into the aircraft log book and
signed off by a qualified inspector.
7. SPECIAL HAZARDS
Propeller
Rotating propellers can cause potential danger. It is very hard to see; therefore special attention
should be made to keep people or animals clear of the aircraft once the engine has been started. It
is strictly forbidden to stand either in line with the arc of the propeller or behind it since there is
always a possibility that stones or other objects can be picked up and thrown at grate speed in
any direction. In the event of the propeller strike turn of the engine immediately and do not
restart until you are satisfied that no structural damage has been done to the propeller or
airframe. If any damage is visible, do not fly until the damaged blade has been repaired or
replaced and the engine has been inspected.
Exhaust system
WARNING: Do not touch parts of the exhaust system while the engine is running or directly
after it has been shut down. It will cause serious burns if touched.
Inspect the entire exhaust system for cracks and damage before and after each flight.
Radiator
WARNING: The cooling system is pressurized when the engine is warm. Never open the cap
until the engine is cooled down. The coolant in the system is very hot and will cause serious
burns.
Running engine on the ground
Whenever you need to start the engine particular care must be taken to observe the following
procedures:

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-Move the aircraft to area clear of people, animals, etc.
-Check the ground around the propeller for loose stones etc. and remove any such objects.
-Make sure the aircraft is securely chocked.
-Carry out a full pre-start security check (see the aircraft operating handbook).
-Maintain an adequate look-out while running the engine: people and animals may
approach from behind.
8. TORQUING PROCEDURES
This chapter provides required torque procedures that are to be used in all areas of the aircraft.
The use of these procedures will ensure the security of installation and will prevent overstressing
of components.
Side Strut
If your trike is equipped with the standard main wheel chock absorbers (spring damping) the
upper bolt of the chock absorber should be tighten to allow the free movement in the joint. If
your trike is equipped with the main wheel air damping (optional) there is no movement in the
joint required, therefore the upper bolt should be tighten up.
The side strut lower bolt has to be tightened to allow a free movement in the joint.
Wishbone axle
The wishbone axle upper bolt has to be tightened to allow a free movement in the joint.
Upper pylon
The upper pylon lower bolt has to be tightened to allow a free rotational movement.
Front forks
The front forks main bolt has to be tightened to allow a light resistance against rotational
movement. The same torque procedure is applied for all front fork bolts.
All other components of the trike are to be tightened to standard values.
9. SCREW LOCKING DEVICES
All bolts and nuts, except the self locking nuts, should be locked after installation. This prevents
them from loosening in flight due to vibration.
There are following screw locking methods used in the aircraft.
Self locking nuts and splints are used for the joints that subject neither the nut nor the bolt to
rotation in service. After a self locking nut has been tightened, at least one full thread pitch of the
bolt must protrude through the nut locking feature.
Lock wire is used for securing fuel drain cock, oil tank clamp, oil relief fitting, engine mount
bolts, radiator mount.
Loctite is used for bolts on the engine, brake discs, wheels and wheel fairings mounts.
WARNING: After repeated assembly and disassembly it is necessary to use Loctite for all self
locking nuts.

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10. CORROSION PROTECTION
During manufacturing all of the components have been protected with powder coat paint or
anodized.
Any time when the components are removed or inspected the opportunity should be taken to
inspect them for corrosion. If the aircraft is operated in coastal areas or ever been exposed to salt
water you will need to clean all the components with the fresh water regularly and perform a
careful check of all components for corrosion.
11. INSPECTION AND SERVICING SCHEDULES
All major repairs and spare part replacement must be done by authorized service personnel.
However, you are encouraged to take care of preventative maintenance yourself. This includes:
tire and wheel bearings replacements, safety wire replacement, safety harness replacement, light
bulb replacement, fuel hose replacement, battery servicing and replacement, spark plugs
replacement and air filter replacement.
The table bellow indicates recommended maintenance periods.
Trike Pre-
flight First 10
hours
Every
25
hours
Every
50
hours
Every
100
hours
Other
ENGINE MOUNT: check steel frame
for cracking and wear. Check rubber
mounts and all bolts for security.
check check
Replace
engine
mount
bolts and
bushings
every
300hours
CHOKE AND THROTTLE CABLES:
Check the cables are correctly adjusted
and full throttle opening is possible.
Check all carburetors are synchronized
in operation. Check the cable inner and
outer for wear and damage. Any broken
strands will require changing the cable
assembly.
Service
check
BRAKE SYSTEM: Check brakes for
operation. Check the fluid for level and
leaks. Check brake cable for corrosion or
damage.
Service
check
ELECTRICAL CONNECTIONS:
Check all connections are tight and no
corrosion is visible.
check
AIRFILTERS: Check condition. Clean
and re-oil as recommended by engine
manufacturer.
check
RADIATOR: Check coolant level.
Check all hoses for condition and
security. There should be no signs of
wear, fluid leakage.
Check check

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RADIATOR: Drain and flush the
radiator. Service Every
200hours
Engine
See Rotax engine manual for detailed
engine maintenance information
Pre-
flight First 10
hours
Every
25
hours
Every
50
hours
Every
100
hours
Other
In addition to Rotax manual:
PLUGS (912): See Rotax manual for
instructions check Replace after
200hrs
PLUGS (912S): See Rotax manual for
instructions check Replace after
100hrs
OIL AND FILTER: See Rotax manual for
instructions Renew
Fuel System Pre
flight First 10 hrs Every 25 hrs Every 50 hrs Annually
/100 hrs Other
CARBURETTORS: check and clean.
See Rotax Manual for instructions. Inspect Inspect
FUEL TANK: Flush out and check
vents. Ensure that all bits of dirt inside
the tank are removed. Ensure there is
no water contamination.
Service
Service
FUEL FILTERS: Check for
contamination, signs of dirt, if any
found replace fuel filter.
check Service
FUEL LINES: Check for cracking or
leaks. Check torque on all connectors.
Check the overall condition of the fuel
line. If there any signs of cracking or
wear it must be replaced.
check check
Propeller Pre
flight First 10
hrs
Every
25
hrs
Every
50 hrs Annually
/100 hrs Other
PROPELLER: Check for cracks and de-
lamination. Check along entire propeller
for stone chips or damage. Check the
propeller tape for security.
check
Check security and re-torque mounting
bolts. Check wire locking before each
flight. Check re-torque and re-wirelock
every 50 hours.
check Service
Trike frame Pre
flight First 10
hrs
Every
25
hrs
Every
50
hrs
Annually
/100 hrs Other
PYLON TUBE: Check for cracks and
bends (also after every hard landing).
Any damage require replacement.
check

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PYLON TUBE: Check all bolts for
security, check
check plates for distortion.
BASE TUBE: Check for cracks and
bends (also after every hard landing)
especially in the region of the front fork
due to heavy landing. Any damage
require replacement.
check
FRONT STRUT: check for cracks and
bends (also after every hard landing).
Any damage require replacement.
check
SEAT FRAME: Check for cracks and
bends. Check for security and
straightness.
check
HANG POINT check check
HANG BOLT: Hang bolt should be free
of wear and corrosion and should be
straight.
check Replace
500 hrs
Landing Gear Pre
flight
First
10
hrs
Every
25
hrs
Every
50 hrs Annually
/100 hrs Other
TYRES: check entire tire condition,
especially treads and sidewalls. check
check
TYRE PRESSURE: 2 atm. Check
the inner tube valve sits properly
through wheel.
check
FRONT FORK: Check for damage.
Check fork legs for straightness.
Nose wheel should be parallel to
fork.
check
check
BRAKES: Check pads and shoes for
wear. Check as required
BRAKES: Check brake cables. check
WHEEL BEARINGS: Check
condition. check
WHEEL HUBS: Check for
corrosion and dents. Check for
damage and wear after every hard
landing.
check
REAR SUSPENSION: Check rear
struts and chock absorbers. check
check
LANDING GEAR SEMI-AXLES:
Check the axle bend point for fatigue
cracks with magnifying glass.
check*
Replace
500 hours
(3000
landings)**
* - Inspection of semi-axles every 50 hours or after every 300 landings, whichever comes first.
** - This concerns all trikes up to serial number 02.12.207 only, with a total flight time of 500
hours or 3000 landings, whichever comes first. One-time replacement. Once semi-axles have

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been replaced with new parts, no further obligatory replacement after 500 hours (3000 landings)
is required.
Wing Pre
flight
First
10
hrs
Every
25
hrs
Every
50
hrs
Annually
/100 hrs Other
SAIL: Visually check wing sail. There
should be no cuts, ruptures, threadbare
holes and torn stitching on the sail.
check
check
BATTENS: Check profiles and ensure
they match with the template. check
CABLES: check all cables, including
washout cables for damage, corrosion,
broken strands, thimbles elongation. If
any found the cable must be replaced.
check
check Replace
washout
wires, all
bottom
wires,
cross bar
tensioning
wire
4 years
NOSE PLATES: Check for wear and
damage. check
check
TUBES: Visual check all tubes for
signs of damage, bends, and corrosion.
If any is found the part must be
removed and given a full visual check.
No damage is acceptable.
check
CONTROL FRAME: Check base tube
for fatigue cracks around holes, dents
and bends. Check uprights for damage
and straightness. Any damage is not
acceptable. Check top and bottom
uprights fittings security.
check
KEEL TUBE: Check for wear at pivot
point and for straightness. check
CROSS BAR: Check center plates and
bolts for wear. Check cross bar –
leading edge junction for wear. Check
tubes for wear and straightness.
check
HANG BRACKET: check whole
bracket, bolts and holes for wear. check
Electric Trim Device Pre
flight First 10
hrs
Every
25
hrs
Every
50
hrs
Annually
/100 hrs Other
Connected, operates correctly, full and
free movement. Check

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SAIL INSPECTION
WARNING
LEFT EXPOSED TO THE SUN WHEN NOT
BEEN USED, YOUR SAIL WILL
DETERIORATE RAPIDLY.
Traditionally, top surfaces of trike wings are made
from woven polyester sailcloth (Dacron). The
strength of this sailcloth degrades over time,
especially when exposed to sunlight (due to its high
ultraviolet light content). The Betts test is devised
to determine the condition of this kind of sailcloth.
For Dacron fabric the default Betts test applies.
Stitching on Dacron sail has to be tested with
bettsometer to 2000 grams.
More recently laminated sailcloth has been used for top surfaces of modern sails. Laminated
sailcloth which is in use for Aeros trike wings comes in layers of film with high-strength strands
integrated between them. Although, it is stronger and more durable than the Dacron sailcloth,
laminated sailcloth can still be degraded by sunlight. The Betts test is not appropriate for this
type of the sailcloth because on its construction.
There is the visual inspection specified to inspect the top surface of the wing with laminated
sailcloth. During the visual inspection look for direct signs of degradation such as delamination
of the laminate, broken strands within the laminate, embrittlement of the laminate (typically
evidenced by ‘crumbling’) and signs of distress around stitch holes at seams. Look for indirect
signs of degradation such as fading or other changes in colour.
Stitching on laminated sail has to be Betts tested to 2000 grams.
We recommend choosing a stitching for testing on the batten pockets. If stitching fails
accidentally this place is easy to repair.
If any stitching fails, the Owner may refer to Aeros for further investigation and a possible life
extension.
Any cuts or tears through the trailing edge, sail fixing points or similar high load areas must be
repaired at Aeros approved workshop.
TIME LIMIT FOR RUBBER PARTS
The following components and systems must be replaced every 5 years:
-venting hose of the carburetors;
-all rubber hoses of the cooling system;
-all rubber hoses of the fuel system;
-all rubber hoses of the lubrication system which are part of the engine supply volume
-carburetor sockets;
-diaphragm on both carburetors;
-rubber hoses on compensating tube.
CAUTION: This time limit must be followed independently and in addition to the visual
inspections of the respective components.
TIME LIMIT FOR COOLANT
Coolant must be replaced as per manufacturer’s instructions, at the latest during overhaul or
when the engine is replaced.

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12. SPECIAL INSTRUCTIONS
FATIGUE
At maximum intervals of 300 hours the following components should be inspected for signs of
fatigue crack damage, particularly at holes and joints:
Leading edges, keel, pylon, seat frame, trike base tube, front strut and channels, control frame
top and bottom fittings, control bar end holes, leading edge – cross bar junction holes in the
tubes, trike pylon fittings, trike base tube and seat frame bracket holes
The parts should be inspected by a qualified person using dye penetrant, radiographic or visual
high magnification methods.
Any instance of fatigue cracking must be reported to the Aeros. No cracked parts may be
returned to service. Unserviceable parts must be made unusable.
The following items have to be replaced as indicated:
Hang bolt – 500 hours. Grease hang point bolt with dry lubricant every time it is removed from
the hang block.
Control frame top bolt – 500 hours.
UNSCHEDULED MAINTENANCE CHECKS
Unscheduled maintenance is required due to abnormal flight loads such as severe turbulence or
heavy landings. The pilot is responsible for identification of these extreme operating conditions
and identification of the effected components. Where damage is found further checks should be
carried out upon areas that may be affected.
Thorough checks should be carried out after transportation and after extended storage periods of
the aircraft.
INSPECTION AFTER HEAVY LANDING
Check all attachment points and parts of the suspension system. Check shock absorbers for
normal operation. Check all welded parts for bending or cracking of paint, which may indicate
permanent deformation of the area. If any permanent deformation is identified then more serious
inspection of the aircraft is necessary, as permanent deformation indicates that extreme forces
have been experienced by the aircraft.
CHECK CLEARENCE
Measured dimensions should be in range of 10 to 20 mm.
The dimensions should be measured with the wing off, no pilot in the seat, as this will alter
dimensions.
If measured distance is lesser then the recommended distance this indicates significant
deformation of the trike base tube and that the trike has been subjected to significant abnormal
loads. The base tube should be replaced and thorough check of the rest of the aircraft should be
performed.
ATTACHMENT POINTS
Check attachment points for the wing to the trike, including the main hang bolt, wheel axles and
bearings. The wing should be also checked after any heavy landing.
Check the main structure including the base tube, landing gear attachment points and the engine
mount.
Check that all other components attached to the trike are in place and properly secured.
SEAT FRAME
If the airframe has experienced unusual loads then the seat frame should be checked thoroughly.
The weight of the pilot during impact may deform the seat frame.

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INSPECTION AFTER HEAVY TURBULANCE
Check that all components attached to the base are in place and properly secured.
Turbulence is most likely to structurally affect the wing of the aircraft than the trike. The wing
manual should be refered for detailed instructions.
LIFTING THE TRIKE
The trike may be lifted using the main attachment point for the wing (the whole trike).
Alternatively it can be partly lifted for local maintenance. In any case the wing should be taken
off before lifting the trike
Be careful when front part of the trike is lifted .from the ground to prevent the propeller from
contacting the ground.
13. PERIODIC MAINTENANCE
GENERAL
The aircraft has been designed to permit its easy inspection and servicing.
This section provides details necessary to carry out routing scheduled periodic maintenance and
the servicing procedures necessary for service Aeros-2 aircraft and its equipment.
WARNING! The Aeros 2 airframe is relatively simple, but like any other aircraft requires
skilled and qualified service. It is not recommended self repair or reassembly by other than
Aeros Ltd approved agent. No replacement parts should be fitted unless they are factory supplied
and identified. All replacements and servicing should be entered into the aircraft log book and
signed off by a qualified inspector.
FUEL SYSTEM
The fuel system of Aeros-2 consists of the fuel tank located under the seat, fuel hoses and the
fuel pump. All of the components for the engine are standard as per the Rotax manual should be
consulted for maintenance information.
The fuel system features:
-single fuel tank, capacity of 54 liters;
-fuel drain tap;
-fuel filter;
-breather system;
-fuel gage.
CAUTION: The fuel gage reading can alter in flight due to the turbulence, pitch and bank angle.
The emergency remaining fuel indicator starts lighting when 10 – 15 liters of fuel remains in the
fuel tank.
Fuel filter has to be replaced within 200 hours.
There is a fuel drain tap at the rear and right of the fuel tank that may be used to check the fuel
quality or to drain the fuel if it is necessary and to remove any water from the fuel tank.
The fuel should be regularly checked for water and contaminants by draining a sample of the
fuel into a clear glass container. Any water present will sink to the bottom. If any water is found
in the tank, check the carburetor fuel bowls for water before the next flight. If fuel was in a tank
without use for extended period of time it is advisable to replace it for fresh one.
If the aircraft is not in use for more than one week it is necessary to drain the fuel from the fuel
tank and also from the carburetors.

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WARNING: Gasoline is extremely flammable and can be explosive under certain conditions.
Do not perform any maintenance on the fuel system in conjunction with maintenance on the
electrical system.
Whenever draining or refueling make sure the master switch is set to OFF (key in full left
position).
Refuel in a well ventilated area with the engine stopped.
Never fill the tank so that the level rises into the filler neck. If the tank is overfilled, heat may
cause the fuel to expand and overflow through the tank vents.
After fueling make sure the fuel cap is securely tighten.
Be careful not to spill fuel when refueling. If any fuel is spilled, make sure the area is dry before
starting the engine.
Avoid prolonged or repeated contact with skin or breathing of vapor.
OIL SYSTEM
Before each flight it is necessary to visually check the oil system for leeks and the parts for
possible damage.
Special attention should be paid to the gear box – crankcase junction, cylinder head – cylinder
junction, cylinder – crankcase junction. Make sure there is no leek from the vent hole in the
lower part of the crankcase under the water pump. Check the engine vent line.
The oil level in the oil tank should be between the two marks (max./min.) on the dip-stick, but
must never fall below the min. mark and be higher the max. mark. Difference between max. and
min. marks is 0.75 liters.
The oil replenishment time interval is after first 25 hours and then every 100 hours.
The oil specification is given in the Rotax Manual. In general use only synthetic or semi
synthetic oil, API classification “SF” or “SG” or higher quality oils. Multigrade is recommended.
These oil types are detergent types. Consult the current Rotax manual for correct grade of oil for
the ambient operating temperature. Refer to the Rotax service instruction SI-18-1997 R5 or to
the latest version of the Rotax service instruction.
Refer to Rotax Manual and Rotax Service Instructions which detail how to check and replenish
the oil.
Consult the Rotax manual for the correct type and grade of oil.
The oil sump is drained by removing the sump plug. Ensure the sump plug is correctly replaced
and lock wired before refilling the engine with oil. Measure the amount of oil to be replaced,
refill, check the level, run the engine and recheck again.
Any time the oil is replaced the opportunity should be taken to replace the oil filter.
.
AIR FILTER
The condition of the air filter should be checked each 25 hrs as per the maintenance schedule,
and also after any extended hangarage or after operating in extreme conditions.
Every 50 hours the air filters have to be cleaned as described below.
-Disconnect the air filter intake crimp hose.
-Disconnect the filters clamps and remove the receiver.
-Unscrew the screws from the receiver and remove the filter out.
-Spray K&N air filter cleaner onto the entire element and let soak for 10 minutes.
-Rinse air filter with warm low pressure water. Do it always from inside to outside,
removing the dirt and not allowing soak it into the element.
-Let the element dry naturally.
-Apply K&N air filter oil to the filter after it is dry. Wait 20 minutes and re-oil any white
spots left.
Assemble the air filter and receiver in the reverse order.

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COOLING SYSTEM
Rotax recommends the coolant to be replaced within 2 years interval or after 200 hours.
If the coolant needs to be replaced for any reasons refer to Rotax Manual and Service
Instructions for details.
EXHAUST SYSTEM
The exhaust system inspection and reinstalling is simple and obvious.
Inspect the condition of the exhaust system for corrosion and holes that may be present. Make
sure that it is correctly secured.
When reinstalling the exhaust system the Loctite should be used as recommended by Rotax. (See
Rotax manual for detailed instructions).
If any minor damage has occurred to the exhaust system it can be easily repaired. If a new
component is required contact an Aeros dealer.
LANDING GEAR
The Aeros 2 landing gear is a tricycle type and consists of main undercarriage and front
undercarriage.
Both the main and the front suspension incorporate air chocks. The life of air chocks should
exceed that of the trike due to the minimal amount of travel they do on the ground. Nevertheless
they have to be checked regularly for proper operation.
With the weight removed from each wheel
check that each component is not loose.
Check each of the bearings, tire wear and
condition of the brake line. Each of the pivot
components should not have more than 0.5
mm of movement when load is applied. For
wheels and suspension pivots the wheels
should be lifted from the ground when testing
the movement.
To remove the extra movement in the front
undercarriage fork assembly it is necessary to
remove the splint, tighten the castle nut and
splint it again (see figure).
Both the main and the front undercarriage allow for minor damage that does not result in
dimensional changes of the components. Any permanent deformation should result in full
checking of all possible affected parts.

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TYRE INFLATION
The recommended tires inflation pressure is 2 Bar for both front and rear tires .When checking
the tires pressure it is recommended to take the opportunity and to examine tires for wear, cuts,
bruises, slippage and other defects.
LUBRICATION
All lubrication points should be lubricated as directed or every three months.
Most of the pivot points of the trike are lubricated with grease.
For the throttle, choke and brake cables lubrication use VD-40.
The wheels support guides have to be lubricated after 50 hours of air time. The lubrication
procedure is described below.
- Remove the wheel spat.
-Lift up both the back sides of the trike with a winch.
-Turn off the wheel nut and remove the wheel with the wheel support guide.
-Clean out dirt and dust from the assembly and apply Litol 24 grease.
-Assemble the wheel and wheel support guide in the reverse order. Install the wheel spat.
ELECTRICAL SYSTEM
Electrical schematic for the ultralight is shown on the diagrams supplied with the trike.
The Electrical circuit consists of:
· instrumentation circuit. The 12 V DC supply is protected by a 25 amp fuse at the battery. The
master switch on the dash, when in the off position, disables the DC power socket, flight
instrument and the electric start push button;
· engine management circuit;
· ignition circuit.
It should be noted that the ignition circuit is a fail-safe system whereby the engine will run in the
event of the ignition circuit becoming disconnected. Switching the coil to ground stops the
engine.
When stopping the engine both switches on the dash should be switched off. The master switch
on the dash should then be turned to the off position to remove supply to the accessories.
Refer to the Rotax manual for more details for the engine electrical system.
The electrical system of the aircraft consists of 12 V battery, the Rotax alternator and
accessories. Electrical schematic is shown on the diagrams.
The electric system maintenance should include periodic inspection of the wiring for chafing and
other damage through the entire length. Damaged wiring should be replaced.
For the maintenance of engine electrical system consult the Rotax manual.
BATTERY
Aeros -2 is supplied with 14AH led-acid battery with no maintenance required.
FUSES
The fuses for the electrical equipment are located on the instrument panel and, depending on the
trike equipment, next to the battery (electric trimmer and battery).
PITOT STATIC SYSTEM
The main problems associated with Pitot static system are leaks, moisture and obstructions.
Other than that the maintenance is not required.
The blockage or moisture can be removed from the Pitot static system by applying a pressure
either to Pitot or static system. The system should be disconnected at both the instrument ends
and blown in with clean, dry air from that end. Do not blow through by mouth as this will cause