Alpi Aviation PIONEER 300 User manual

DOCUMENT N° PD9B01M3
NOTE FOR PRINTING: ALL THESE PAGES NEEDS TO BE COLOUR PRINTED
DATE OF ISSUE OF LAST REVISION 23/07/2020
MAINTENANCE MANUAL
AIRCRAFT MODEL: PIONEER 300
THIS MANUAL ONLY APPLY FOR:
- P300 AND P300FG;
- FIXED AND VARIABLE PITCH PROPELLERS;
- ENGINE ROTAX 912 ULS, 912IS SPORT, 915IS;
- SHORT AND NORMAL WINGS.

A PD9B01M3 1ST ISSUE 23/07/2020
LIST OF VALID PAGES
This Manual is made by 34 pages (including the annexes), original and emended pages are herein
listed:
DOCUMENT REVISION SUMMARY
REVISION
DATE
CHANGES
0
1/07/2019
-Document issue
1
17/06/2020
-Definition of primary and secondary structures
-List of materials for quick repairs
2
25/06/2020
- aircraft TBO definition at 2000h
3
23/07/2020
Definition of special tools , placard and markings
Table 1: history of document revisions
CAUTION
THIS MANUAL IS VALID ONLY IF IT CONTAINS ALL OF THE ORIGINAL AND REVISED
PAGES LISTED ABOVE. EACH PAGE TO BE REVISED MUST BE REMOVED, SHREDDED
AND LATER REPLACED WITH THE NEW, REVISED PAGE IN THE EXACT SAME PLACE IN
THE MANUAL.

1 PD9B01M0 1ST ISSUE 1/07/2019
TABLE OF CONTENTS
LIST OF TABLES.......................................................................................................... 4
GLOSSARY................................................................................................................... 5
A. INTRODUCTION....................................................................................................... 7
A.1 Document references......................................................................................... 7
A.2 Original Equipment Manufacturer....................................................................... 7
A.3 Lifecycle Management........................................................................................ 8
A.4 Continuous Airworthiness................................................................................... 8
A.5 Document Organization...................................................................................... 8
B. WARNING, CAUTION AND NOTE........................................................................... 9
1GENERAL.................................................................................................... 10
1.1 ASTM F2483-12 Terminology ...................................................................... 10
1.2 How to read the operational sheets in the annexes...................................... 10
1.3 Standard equipment list................................................................................ 11
1.3.1 Approved engine types .....................................................................................12
1.3.2 Approved propeller types ..................................................................................12
1.4 Sources to purchase parts ........................................................................... 13
1.5 List of disposable replacement parts............................................................ 13
1.6 Weight and balance information................................................................... 13
1.7 Handling....................................................................................................... 13
1.7.1 Ground handling ...............................................................................................14
1.7.2 Parking and tie down.........................................................................................14
1.7.3 Jacking..............................................................................................................14
1.7.4 Towing..............................................................................................................15
1.7.5 Taxiing..............................................................................................................15
1.8 Tire inflation pressures................................................................................. 15
1.9 Approved oil and capacities ......................................................................... 15
1.10 Recommended fastener torque values......................................................... 15
1.11 General safety information ........................................................................... 15
1.12 Instruction for reporting information after maintenance................................ 16
1.12.1 Instruction for reporting possible safety/flight concerns.....................................16
1.12.2 Manual Improvements and feedbacks...............................................................16
1.12.3 Aircraft assembly ..............................................................................................16
1.12.4 Change in ownership ........................................................................................16

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2INSPECTIONS .............................................................................................16
2.1 Inspection panels..........................................................................................16
2.2 Airframe and systems inspection schedule...................................................17
2.3 Inspections and checks ................................................................................17
2.4 100 hour/annual check list............................................................................18
2.5 Corrosion prevention ....................................................................................18
2.6 Servicing.......................................................................................................19
2.7 Lubrication....................................................................................................19
2.7.1 Lubrication points..............................................................................................19
3STRUCTURES .............................................................................................20
3.1 Airframe........................................................................................................20
3.1.1 Wing..................................................................................................................21
3.1.2 Tail....................................................................................................................21
3.1.3 Landing gear (FIXED) .......................................................................................21
3.1.4 Landing gear (RETRACTABLE)........................................................................21
3.1.5 Control system and aerodynamic surfaces........................................................22
4ENGINE........................................................................................................22
4.1 Engine & Engine Mount................................................................................22
4.2 Engine cowling..............................................................................................23
4.3 Exhaust/Muffler system.................................................................................23
4.4 Air induction system......................................................................................23
4.5 Oil system.....................................................................................................23
4.6 Cooling system.............................................................................................23
5FUEL SYSTEM.............................................................................................23
6PROPELLER................................................................................................24
7UTILITY SYSTEMS......................................................................................24
7.1 Cabin heat and cooling.................................................................................24
8INSTRUMENTS AND AVIONICS.................................................................24
8.1 Instruments that require sensors ..................................................................24
8.2 Pitot-static system.........................................................................................25
9ELECTRICAL SYSTEM ...............................................................................25
9.1 Battery check, removal and installation ........................................................26
9.2 Internal AC Generator...................................................................................26

3 PD9B01M0 1ST ISSUE 1/07/2019
9.3 Exterior lights................................................................................................ 26
9.4 Stall warnings (if installed)............................................................................ 26
9.5 Flap computer (if installed)........................................................................... 27
9.6 External power source (for engine startup) .................................................. 27
10 STRUCTURAL REPAIR .............................................................................. 27
10.1 Type of maintenance.................................................................................... 27
10.2 Minimum level of certification ....................................................................... 27
10.3 Repair procedures........................................................................................ 27
10.4 Materials necessary for small repairs........................................................... 27
11 PAINTING AND COATINGS........................................................................ 28
12 FEEDBACK FORM...................................................................................... 28
ANNEX A: CHECKLIST OF MAINTENANCE OPERATIONAL SHEETS, PD9001A029
ANNEX B: REPORTING FLIGHT/SAFETY CONCERNS.......................................... 30
ANNEX C: IMPROVEMENTS, CORRECTIONS AND FEEDBACKS ........................ 31
ANNEX D: CHANGE OF ADDRESS/OWNERSHIP................................................. 32
ANNEX E: NOTICES APPLICATION LOG (1 OF … ) ................................................ 33
ANNEX F: MAINTENANCE LOG (1 OF … ) ............................................................. 34
ANNEX G: APPLICABLE PLACARD AND MARKINGS.......................................... 35
ANNEX H: SPECIAL TOOLS.................................................................................... 36

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LIST OF TABLES
Table 1: history of document revisions.......................................................................................II
Table 2: Standard configuration equipment..............................................................................12
Table 3: Approved engine types ..............................................................................................12
Table 4: Approved propeller types...........................................................................................13
Table 5: Disposable spare parts. .............................................................................................13
Table 6: Final securing procedure............................................................................................14
Table 7: Tire inflation pressure.................................................................................................15
Table 8: Approved oil grades and tank capacity.......................................................................15
Table 9: Daily servicing............................................................................................................19

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GLOSSARY
°C
Degrees Celsius (Centigrade)
°F
Degrees Fahrenheit
AOD
Aft of Datum
ASI
Air Speed Indicator
ASTM
American Standard for Testing & Materials
Aux
Auxiliary
BHP
Brake Horse Power
CG
Center of Gravity
CHT
Cylinder Head Temperature
EGT
Exhaust Gas Temperature
EGT-Split
Difference between the actual highest EGT value and the actual lowest
EGT value
EOM
Engine Operators Manual
FG
Fixed Gear
fpm
Feet per minute
ft
Feet
FTS
Flight Training Supplement
gal
Gallons
h
hour
IAS
Indicated Air Speed
IFR
Instrument Flight Rules
KCAS
Calibrated Air Speed in Km/h (and in Kts)
Kg
Kilograms
KIAS
Indicated Air Speed in Km/h (and in Kts)
kt
Knots
KTAS
Calibrated True Air Speed
L
Left
l
Liters
lb
Pounds
LE
Leading Edge
LMM
Line Maintenance Manual
MAC
Mean Aerodynamic Chord
MAUW
Maximum All UP Weight
max
Maximum
MRA
Major Repair and Alteration
MTOW
Maximum Takeoff Weight
nmi
Nautical Miles
OAT
Outside Air Temperature
ODDP
Owner Delivery Documentation Package
OEM
Original Equipment Manufacturer
OPT
Optional

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OS
Operational Sheets
POH
Pilot Operating Handbook
R
Right
RON
Research Octane Number
RPM
Revolution per Minute
sec
Seconds
SI
International System of Units
STD
Standard
VFR
Visual Flight Rules

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A. INTRODUCTION
The Maintenance Manual here presented provides the guidelines for the qualifications to
accomplish the various levels of maintenance on Pioneer 300 aircrafts. It also represents a
continuous part of the Pilot’s Operating Handbook delivered together with this manual. For this
reason, some arguments will be just recalled instead of being fully re-written. A careful reading of
the engine and propeller manuals is strongly recommended in any case because it will give you
more information about safe maintaining and hence it will ensure a safer flight.
This manual contains very detailed indications about maintenance, repairs and alterations
providing illustrative sketches on how to do that. Furthermore, indications about periodic
inspections and advice about the right care of the overall Pioneer 300 aircrafts are also provided
into this manual in order to give you all the satisfactory indications towards the correct operations.
Pioneer 300 aircrafts are built with some parts not manufactured by Alpi Aviation, for those it is
necessary to refer to the original manufacturer’s manual in order to get complete information.
Pioneer 300 aircrafts legal WARRANTY is guaranteed only if:
1) the herein prescribed maintenance is carried out by the appropriate personnel, recorded in the
Table of ANNEX F and stored in the aircraft logbook;
2) the Mandatory Service Bulletins are applied and recorded in the Table of ANNEX E and stored
in the aircraft logbook.
A.1 Document references
This manual has been prepared according to the standard ASTM F2483-12, while Pioneer 300
aircrafts have been shown to comply with standard ASTM F2245. This aircraft must be maintained
following the standard ASTM F2295, Standard Practice for Continued Operational Safety
Monitoring of a Light Sport Aircraft. Please note that this standard describes the responsibilities of
the Owner/Operator.
Pioneer 300 aircrafts are included into a wider family of P300 aircraft types, mainly divided into
Fixed and Retractable landing gear, and for this the airplane only one P300 Maintenance Manual
exists.
In details the following ASTM standards have been used to demonstrate compliance and
therefore to prepare this document:
1) F2483-12 Standard Practice for Maintenance and the Development of Maintenance
Manuals for Light Sport Aircraft;
2) F2245-12d Standard Specification for Design and Performance of Light Sport Aircraft;
3) F2279-06 Standard Practice for Quality Assurance in the Manufacture of Fixed Wing Light
Sport Aircraft;
4) F2295-06 Standard Practice for Continued Operational Safety Monitoring of a Light Sport
Aircraft;
5) F2746-12 Standard Specification for Pilot’s Operating Handbook (POH) for Light Sport
Aircraft;
6) F2930-12 Standard Guide for Compliance with Light Sport Aircraft Standards.
A.2 Original Equipment Manufacturer
The Pioneer 300 aircrafts have been manufactured by Alpi Aviation Srl whose contact information
are herein listed:

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Name: Alpi Aviation Srl;
Location: Via dei Templari 24, 33080, San Quirino (PN), Italy
Phone N°: [phone]
Fax N°: [phone]
Email: [e-mail]
Website: www.alpiaviation.com
A.3 Lifecycle Management
The aircraft owner shall comply with all requirements, procedures and limitations with respect to the
Maintenance Manual instructions prescribed in this manual. It is responsibility of the aircraft owner
to maintain this manual up to date and to report the date of incorporation and his signature on the
Amendment Record Sheet. Whenever the revision status of his manual could be in question, each
owner should contact the local Alpi Aviation Dealer, or directly Alpi Aviation Srl in Italy. No entries
or endorsements may be made to this Manual except in the manner and by persons authorized for
the purpose. In case of aircraft damage or personal injury resulting from noncompliance to
instructions in the manual, Alpi Aviation Srl denies all responsibility. All text, design, layout and
graphics are owned by Alpi Aviation Srl. Therefore, this manual and any of its contents may not be
copied or distributed in any manner (electronic, web or printed) without the prior consent of Alpi
Aviation Srl.
WARNING
IT IS MANDATORY TO CAREFULLY STUDY THIS MANUAL PRIOR TO USE OF AIRCRAFT. IT
IS ASSUMED THAT THE OWNER THAT WILL NOT NOTIFY ANY “REQUEST OF
CLARIFICATION/MODIFICATION” USING THE ATTACHED FORM IN ANNEX CWITHIN 30
DAYS FROM THE AIRCRAFT PURCHASE, WILL FULLY AGREE ON THE CONTENT.
WARNING
IT IS MANDATORY TO FILL THE MAINTENANCE LOG SHEETS IN ANNEX FWITH ALL THE
USEFUL RECORDS THAT PERMIT TRACKING OF THE AIRCRAFT MAINTENANCE HISTORY.
THIS LOG MUST BE SIGNED BY THE PERSON IN CHARGE FOR THE SINGLE TASK
ACCOMPLISHED.
A.4 Continuous Airworthiness
It is a Pilot/Owner responsibility to get access to continuous airworthiness NOTICES by registering
himself into the Company website (Customer page), in order to get a Customer account. NOTICES
include:
- Safety Alert;
- Service Bulletin;
- Notification.
A.5 Document Organization
The document has been organized in sections as herein summarized:
CHAPTER 1 general information,
CHAPTER 2 inspections,

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CHAPTER 3 primary structure,
CHAPTER 4 engine and power plant,
CHAPTER 5 fuel system,
CHAPTER 6 propeller,
CHAPTER 7 utility systems,
CHAPTER 8 instrument and avionics,
CHAPTER 9 electrical system,
CHAPTER 10 structural repair approach,
CHAPTER 11 painting and coating aspects,
CHAPTER 12 feedback form
ANNEX A Checklist of maintenance operation
ANNEX B reporting flight/safety concerns format
ANNEX C improvements, corrections and feedbacks format
ANNEX D changing the address or ownership format
ANNEX E notices application format
ANNEX F maintenance log format
B. WARNING, CAUTION AND NOTE
WARNING
MEANS THAT THE NON-OBSERVATION OF THE CORRESPONDING PROCEDURE LEADS
TO AN IMMEDIATE OR IMPORTANT DEGRADATION OF THE FLIGHT SAFETY.
CAUTION
MEANS THAT THE NON-OBSERVATION OF THE CORRESPONDING PROCEDURE LEADS
TO A MINOR OR TO A MORE OR LESS LONG TERM DEGRADATION OF THE FLIGHT
SAFETY.
NOTE
Draws the attention of any special item not directly related to safety but which is important or
unusual.

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1 General
Pioneer 300 aircrafts are twin seat, single engine, low wing, hybrid composite/wood structure
monoplane with tricycle landing gear and steerable nose gear. It is an ASTM compliant aircraft
designed to be flown by Sport Pilot rated pilots or higher rated pilots. Additional information on
your particular aircraft type is provided into related POH strictly connected to this maintenance
manual.
WARNING
THIS MAINTENANCE MANUAL CANNOT BE SOLD AND/OR DISTRIBUTED WITHOUT ITS
RELATED PILOT’S OPERATING HANDOOK BECAUSE THIS LATTER CONSTITUTES AN ITS
FUNDAMENTAL PART.
1.1 ASTM F2483-12 Terminology
The following items aim to resume the definitions of ASTM F2438-12 standard that are invoked into
this maintenance manual:
•Heavy maintenance
Any maintenance, inspection, repair or alteration a manufacturer has designed that requires
specialized training, equipment or facilities.
•Line maintenance
Any repair, maintenance, scheduled checks, servicing, inspections or alterations not
considered heavy maintenance that is approved by the manufacturer and is specified in the
manufacturer’s maintenance manual.
•LSA repairman inspection
U.S. FAA-certified repairman (light sport aircraft) with an inspection rating as defined by 14
CFR Part 35, authorized to perform the annual condition inspection on experimental light
sport aircraft or an equivalent rating issued by other civil aviation authorities.
•LSA repairman maintenance
U.S. FAA-certified repairman (light sport aircraft) with an inspection rating as defined by 14
CFR Part 35, authorized to perform line maintenance on aircraft certified as special LSA
aircraft.
•MRA: Major repair, alteration or maintenance
Any repair, alteration or maintenance for which instructions to complete the task excluded
from the maintenance manual supplied to the consumer are considered major.
•100-h inspection
Same as an annual condition inspection, except the interval of inspections is 100 h of
operation instead if 12 calendar months. This inspection is utilized when the LSA is being
used for commercial operations such as flight instruction or rental, or both.
1.2 How to read the operational sheets in the annexes
Illustrative instructions are given through accurate operational (OP) sheets listed into the “Checklist
of Maintenance Operational Sheets” attached to ANNEX A. This checklist resumes all the time
intervals and modalities for the correct maintaining of the aircraft and shows the relative OP sheet
required to accomplish a particular task.
Each OP sheet contained in that table follows an Alpi Aviation internal standard, according to
which important preliminary information is written at the header of the document.

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Starting from the left, just below the Alpi Aviation logo, are indicated some maintenance
instructions regarding:
- The person who can perform the actions illustrated in the document;
- The type of the maintenance;
- Special training requirements to accomplish the tasks.
The nomenclature follows the definition adopted by the ASTM F2483-12 standard practice for
maintenance and development of maintenance manuals for light sport aircraft, see para. 1.1.
Just beside the Alpi Aviation logo, are listed different information such as:
- The identification code name of the document, enclosed into a red coloured box;
- The argument of the document, at the header of the blue table;
- The aircraft model applicability;
- The history revisions list.
WARNING
EACH OPERATIONAL SHEET APPLYES ONLY TO THE ITEMS MARKED WITH A FULL BLUE
COLORED DOT.
WARNING
SOME OPERATIONAL SHEETS ARE REFERRED TO “P300 KITE” MODEL THAT IS THE OLD
DESIGNATION FOR THE ACTUAL P300FG CONFIGURATION.
1.3 Standard equipment list
Table 2 represents the standard format of components installed on a Pioneer 300 aircraft. Usually
this table is used to perform the weight & balance operation before each flight. For this reason, in
the present manual has been reported a most general format of the standard equipment list in
which the engine and propeller types are left blank because dependent on the required
configuration.
Anyway, the complete standard equipment list is provided into related POH.
ITEM
CHK
Powerplant
Engine
X
Propeller
X
Flight Instruments
Airspeed Indicator
X
Altimeter
X
Turn & Bank Indicator
X
Compass
X
Vertical Speed Indicator
X
Digital Engine Instruments and Avionics
Includes:
-
- 2 x CHT
- 2 x EGT
- Oil Temp Indicator
- Oil Press Indicator
- Airbox temp indicator + O.A.T.
- voltmeter
- ammeter
- fuel press
- MAP
- fuel computer
- RPM indicator

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- hour-meter
Miscellaneous Equipment
4 Points Seat Belts
X
Engine kill switch
X
Fuel Valve
X
Cabin Fresh Air Intake
X
Key Canopy Lock
X
Aileron Electric Trim
X
Elevator Electric Trim
X
Electronic Flaps Controller
X
Gas Nose landing gear
X
Gear Legs Fairings
X
Wheels Fairings
X
Toe Brakes Pilot's Side
X
Plus Cabin Heating
X
Oil Inspection Door
X
Landing Lights inside E. Cowling
X
Strobe and Nav Lights
X
Radio Prewiring
X
Auxiliary Electric Socket
X
Fiber Panel and Consolle
X
White Paint with Sticker Livery
X
Pioneer Canopy Cover*
X
POH, Maintenance Manual *
X
Tools*
X
*NOTE: those items are not considered part of the aircraft configuration from the empty weight point of
view.
**Special tools are available on request and payment. Please refer to PZ1012A0 attached.
Table 2: Standard configuration equipment.
1.3.1 Approved engine types
Table 3 lists the engine types that are allowed to be installed on the Pioneer 300 aircrafts and for
those it is available the necessary documentation aimed to the maintenance.
MANUFACTURER: ROTAX GmbH&Co KG
TYPE
MAX. RATED POWER
912 ULS
100 hp
912iS SPORT
100 hp
915iS
141 hp
Table 3: Approved engine types
1.3.2 Approved propeller types
Table 4 lists the engine types that are allowed to be installed on the Pioneer 300 aircrafts and for
those it is available the necessary documentation aimed to the maintenance.
MANUFACTURER: DUC
Model
3-BLADES
Type
SWIRL INCONEL
Diameter
1730 mm (68 inch)
Pitch
Fixed –Ground adjustable
MANUFACTURER: AVTEK
Model
2-BLADES
Type
AVY 2HS (or AH140)
Diameter
1760 mm (69 inch)
Pitch
Variable
MANUFACTURER: WOODCOMP
Model
2-BLADES

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Type
KW-20W
Diameter
1709 mm (67 inch)
Pitch
Variable
MANUFACTURER: MT-PROPELLER
Model
2-BLADES
Type
MT-21-A/175-51
Diameter
1750 mm (69 inch)
Pitch
Variable
Table 4: Approved propeller types.
1.4 Sources to purchase parts
Spare parts can be requested to Alpi Aviation Srl using the contact information listed in paragraphs
A.2 and A.3 or directly to the nearest local dealer. Dealers list is published into the company web
site www.alpiaviation.com under the “Dealers” sub menu. Illustrated Part Catalogs are available as
well as Spare Parts Order Form after registration inside the company web site under the “Customer
Area”. Registration requires a new account creation following the step-by-step procedure described
into the web site.
1.5 List of disposable replacement parts
Table 5 lists the disposable spare parts:
PART
SUPPLY DATA
Air Filter
Alpi Aviation
Fuel Filter
Alpi Aviation
Oil Filter
Alpi Aviation or Rotax
Nose Wheel tire
Sava 4,00-4” tire&tube or may be replaced with eq. aircraft tire or tube
Main wheel tire
Sava 4,00-6” tire&tube or may be replaced with eq. aircraft tire or tube
Oil
See Notes in Para. 1.4 & refer to Rotax Manuals
Coolant
See Notes in Para. 1.4 & refer to Rotax Manuals
Table 5: Disposable spare parts.
1.6 Weight and balance information
A detailed explanation of weight and balance calculation can be found in the related POH, at
Chapter 6. Anyway, additional indications are given in ANNEX A (Fuselage Body group).
1.7 Handling
WARNING
NEVER HANDLE FUEL IN AN ENCLOSED AREA OR WHERE FUMES COULD REACH
IGNITION POINT. DO NOT SMOKE OR ALLOW OPEN FLAMES OR SPARKS IN THE
VICINITY. NEVER ADD FUEL WHILE THE ENGINE IS RUNNING.
WARNING
NEVER REFUEL AN AIRCRAFT IF FUEL COULD BE SPLIT ON HOT ENGINE COMPONENTS.
WARNING
USE ONLY APPROVED FUEL CONTAINERS AND NEVER TRANSPORT FUEL IN AN UNSAFE
MANNER.
WARNING

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ALWAYS CHECK FOR FUEL CONTAMINATION. CONTAMINATION IS A MAJOR CAUSE OF
ENGINE FAILURE. ONCE YOUR FUEL IS IN THE CONTAINER A VERY HAZARDOUS
POTENTIAL EXISTS. USE A CLEAN SAFETY APPROVED STORAGE CONTAINER. DO NOT
OVERFILL THE CONTAINER - ALLOW FOR EXPANSION.
WARNING
THE ENGINE IS DESIGNED FOR USE WITH UNLEADED MOGAS HAVING AN OCTANE
RATING OF 95 RON OR 91 AKI OR ASTM D4814 (OR GREATER). USE AVIATION GASOLINE
ONLY FOR SHORT PERIODS AND INSPECT FREQUENTLY FOR CYLINDER DEPOSITS. BE
SURE TO USE PRODUCTS OF AT LEAST THE STANDARD SHOWN IN SECTION 1.
WARNING
ALWAYS GROUND THE AIRCRAFT THROUGH THE EXHAUST PIPE BEFORE REMOVING
THE FUEL CAP.
WARNING
BEFORE THE FIRST FLIGHT OF THE DAY, AND AFTER EACH REFUELING, USE A
SAMPLER CUP AND DRAIN A SMALL QUANTITY OF FUEL FROM THE FUEL TANK SUMP
QUICK DRAIN VALVE - CHECK FOR WATER, SEDIMENT AND CONTAMINATION.
1.7.1 Ground handling
Move the aircraft on the ground by pulling on the propeller blades close to the hub. An optional tow
bar can be attached to fittings. Aircraft can be steered using the rudder or, for sharp turns, by
lowering the tail to raise nose wheel off the ground. In this case, towing to the favourable CG
location, a gentle push on the tail cone just ahead of empennage surfaces is all that is needed.
Avoid dragging nose wheel sideways and do not attempt to counter any movement of the aircraft
by handling it by its wing tips.
CAUTION
AS A GENERAL RULE, APPLY FORCE TO AIRCRAFT STRUCTURE ONLY ON MAIN
STRUCTURAL ELEMENTS SUCH AS FRAMES, RIBS OR SPARS.
See ANNEX A (Document & Miscellaneous group) to better understand how perform do this
operation.
1.7.2 Parking and tie down
It is recommended to use chocks when parking outdoors or in a hanger. If chocks are not
available, use the parking brake. If possible, park the aircraft into the wind. Tie down points are
located under the wing, use them in order to attach the aircraft to the ground using belts or ropes.
Whenever the aircraft needs to be parked or tie down, the following checks are required:
ITEM
DEVICE
VALUE
1
Radio/Intercom
OFF
2
Ignition Switches
OFF
3
Master Switch
OFF
4
Controls
LOCK with seatbelt
5
Fuel
OFF
Table 6: Final securing procedure.
1.7.3 Jacking
See ANNEX A (Document & Miscellaneous group) for more details about this operation.
CAUTION

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AS A GENERAL RULE, APPLY FORCE TO AIRCRAFT STRUCTURE ONLY ON MAIN
STRUCTURAL ELEMENTS SUCH AS FRAMES, RIBS OR SPARS.
1.7.4 Towing
The aircraft can be towed pulling it by the propeller. Never push it by the tail surface or the tail cone
as well. When pulling by the propeller, the nose wheel will rotate freely following the direction
decided by the pilot permitting to address the aircraft to the desired place.
When/if backwards movements are required, lower at first the tail raising the nose wheel and then
pull backward the aircraft or turn it as necessary.
See ANNEX A (Document & Miscellaneous group) for more details about this operation.
1.7.5 Taxiing
When taxiing, it is important that speed and use of brakes are minimized and that all controls are
utilized to maintain directional control and balance. Taxiing over loose gravel or cinders should be
done at low engine speed to avoid abrasion and pebbles damage to the propeller.
NOTE
DO NOT accelerate over loose gravel or cinders or propeller damage will result.
1.8 Tire inflation pressures
DESCRIPTION
VALUE
Standard Mains
2.2 bar (32 psi)
Nose
2 bar (29 psi)
Table 7: Tire inflation pressure.
1.9 Approved oil and capacities
DESCRIPTION
VALUE
Specification
RON 424
Oil Tank capacity
3 l (0.8 gal)
Motorcycle oil of a registered brand with gear additive
NOTE: apply to all Rotax Engine types.
Table 8: Approved oil grades and tank capacity.
1.10 Recommended fastener torque values
All satisfactory information about the fastener torque values are provided into ANNEX A
(Document & Miscellaneous group).
1.11 General safety information
Complete information about safety devices such as seat and seat belts, parachute system,
baggage compartment, canopy handling and ELT have already been provided into related POH
(ANNEX C of POH).
For what concern the maintenance of these safety elements, see ANNEX A (Fuselage Body
group).

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1.12 Instruction for reporting information after maintenance
1.12.1 Instruction for reporting possible safety/flight concerns
The form in ANNEX B must be used by the owners to report safety of flight concerns found
during inspection/maintenance. Please copy that page, cut out along the marked borders
and send it to the Company contacts indicated in paragraphs A.2.
1.12.2 Manual Improvements and feedbacks
The form in ANNEX C must be used by the owners to report improvements or corrections to
this Manual. Please copy that page, cut out following the borders and send it to the
Company contacts, see paragraph A.2.
1.12.3 Aircraft assembly
In case it is necessary to disassemble or assemble the aircraft after or for transportation or
maintenance activities, follow the indications provided into ANNEX A (Aircraft Assembly
group).
1.12.4 Change in ownership
The form in ANNEX D must be used by the owners to report a change of address/ownership.
Please copy this page, cut out following the borders and send it to the Company contacts, see
paragraph A.2.
2 Inspections
Alpi Aviation considers the inspection schedule outlined below compulsory for safety operation on
the airframe and systems over an extended period of time.
The described servicing requirements pertain to operation in non-extreme climatic conditions.
✓For all the prescribed Rotax engines, unless otherwise stated, it is compulsory to adhere to
maintenance requirements as listed in the latest revision/release applicable, at the time of
maintenance, in the Engine Operators Manual and Engine Maintenance Manual.
✓For all the prescribed propeller types, refer to the latest revision/release applicable, at the time
of maintenance, of its Instruction Manual.
2.1 Inspection panels
Inspection points that are not in plain view may be accessed through specific inspection panels or
fairings described below and shown in the ANNEX A (Fuselage Body group):
Inspection panels on wing underside - access to:
✓aileron bell cranks;
- cabin (main spar and torque box);
- inspection of the wing tank drains;
- flap actuation bar
✓Tail cone underside inspection panel - access to:
- Main structure frame/control cables;
- elevator relay to control lever;
✓Tail cone end-fairing access to:
- elevator relay to control lever;
- attachment of vertical stabilizer aft spar;
- elevator pushrod.

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✓Aft cabin bulkhead and baggage compartment floor –access to:
- inspection of aft fuselage section and attachments;
- inspection of elevator/rudder control system and of cable pulleys for rudder control;
- access to flap actuator.
✓Forward cabin central fairing - access to:
- the fuel valves;
- the rudder control cables;
- retractable landing gear mechanism (if applicable).
✓Instrument panel cover - access to instrumentation and radio;
✓Engine cowling - access to:
- engine and related systems;
- access to main components of electrical system;
- access to nose gear strut and steering assembly mechanism.
✓Propeller spinner - access to propeller hub.
✓Main and nose landing gear fairings –access to:
- Wheel and tires;
- Wheel installation bolts;
- Brakes pad and discs;
2.2 Airframe and systems inspection schedule
Airframe and systems inspection schedule is as follows:
✓Inspections for airworthiness before first flight of day as specified in POH;
✓First inspection at 25 hours (In order to improve the maintenance attention and the overall
safety, based on the company experience and mainly based on the engine early operation
issue, the company, in addition to the 100 hr inspection, requires the first scheduled
maintenance at 25 hours);
✓Periodic inspections at every 100 hours;
✓Special inspections, added to normal periodic inspections;
✓Singular inspection, when aircraft has been exposed to conditions that may have damaged
one or more of its components;
✓If aircraft is rarely used, a “100-hour inspection” must be performed yearly;
✓Replacement of parts subjected to usage limitations are specified in the ANNEX A;
2.3 Inspections and checks
Inspections and checks, unless specifically indicated, apply the following:
✓Structures in general: Condition of panel covers, ribs, frames, stringers etc., absence of
cracks, deformation, corrosion and any other apparent sign of damage;
✓Moving parts: Lubrication, security of attachment, securing of bolts, absence of excessive
play, proper adjustment, proper travel, condition of attachments and hinges, absence of
corrosion, deformation, cleanliness;
✓Fluid lines and hoses: Absence of leaks, cracks, dents, chafing, proper radius,
deterioration;
✓Bolts and attachments: Proper tightening and securing, absence of cracks or nicks, damage
to thread, wear and excessive play, absence of any corrosion form.

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2.4 100 hour/annual check list
After this first 25 hours maintenance, all other scheduled maintenances actions follow the 100
hours intervals. The check list for the maintenance actions are listed in the ANNEX A that clearly
reports the prescribed actions subdivided in:
✓I: Inspections actions;
✓M: Maintenance actions;
✓R: Replacements actions;
✓C: On condition (check and replace if necessary) actions.
For each of the prescribed actions and for each functional group, the OS point out when and what
to do, referring to detailed sheets that are part of the document as well.
2.5 Corrosion prevention
Keeping the aircraft in cleaned conditions and removing any collection of corrosive agents such as
oil, grease, dregs and other foreign matter it is of crucial importance for the integrity of the
structure. To avoid damage to the surface finishing, do not use polishing detergents. Composite
materials or polymer related parts are subjected to degradation if not properly protected from
environmental factors. Any undesirable change in properties or appearance of a composite
material can be considered such as a form of degradation.
One of the first indicators of degradation is the change in the surface appearance or gloss,
followed by a change in the color of the surface resin. Wood parts are not strictly affected by
corrosion but may be affected by excess and prolonged exposition to humid environment hot and
cold both.
In order to avoid premature degradation of wood characteristics, the aircraft must be stored within
the prescribed limitations, see POH. Original or equivalent corrosion/degradation prevention must
be re-applied after any alteration or repair.
If any trace of corrosion is detected it must be removed as soon as possible and immediately
treated with the aim to prevent dangerous degradation of the affected component and related parts
that could compromise the safety of overall flying operations. The general guidelines to prevent
corrosion/degradation of various materials are:
For steel parts: with the exception of highly stressed components or stainless steel, it is possible
to use abrasives, power brushes, steel brushes if operated manually and steel wool. Removing
corrosion by products from highly stressed steel components (main gear steel spring) requires
particular care.
For aluminum parts: treatment consists in mechanically removing as much as possible corrosion
by products, applying corrosion inhibitor and replacing original finish. Steel wool, emery or steel
brushes (unless stainless steel) along with other highly abrasive material should not be used since
steel or emery particles become embedded in the softer material causing corrosion.
After cleaning surface corrosion, parts must be treated with an anti-corrosion finish prepared as
follows:
✓Applying corrosion inhibitor;
✓Accurate brushing with a sturdy fiber brush will rid most of the corrosion and insure that the
anti-corrosion agent will penetrate completely in the cracks;
✓Leave the corrosion inhibitor on the part for at least five minutes and then remove excess
with water or a damp cloth;
✓Apply protective finish the same day in which treatment begins.
For composite parts: composite material or polymeric material degradation treatment is
particularly difficult and requires special skill. If any composite or polymeric material degradation is