Pipistrel ALPHA Trainer User manual

WARNING!
This document MUST be present inside the cockpit at all times.
Should you sell this aircraft make sure this document is given to the new owner.
applies to all ALPHA Trainer LSA aircraft up to and including s/n 890 AT 912 LSA
as well as s/n 926 AT 912 LSA, 932 AT 912 LSA,
935 AT 912 LSA , 958 AT 912 LSA,equipped with a Rotax 912 (80 HP) engine
Pilot’s Operating Handbook
and Flight Training Supplement
REVISION B00
(24th October, 2019)
This publication includes the material required to be supplied
to the pilot by ASTM F2245, F2279 & F2295
Aircraft Registration Number:
Aircraft Serial Number:
Doc.no. : POH-162-00-40-050
All rights reserved. Reproduction or disclosure to third parties of this document or any part thereof is not permitted,
except with the prior and express written permission of Pipistrel Group’s R&D division, Pipistrel Vertical Solutions
d.o.o., which is authorized to publish technical documentation for Pipistrel Group’s subsidiaries.
N520AT
738 AT 912 LSA

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Performance - specifications
ALPHA Trainer 80 hp Rotax 912
Stall speed (flaps extended) 37 kts (68 km/h)
Stall speed (flaps retracted) 43 kts (80 km/h)
Cruise speed (5300 RPM) 108 kts (201 km/h)
Maximum horizontal speed at sea level 120 kts (222 km/h)
VNE 135 kts (250 km/h)
Standard endurance 108 knots cruise 3.0 hours + 30 min reserve
Standard range at 108 knots cruise 324 NM (600 km)
Fuel flow at 108 knots cruise speed (typical) 3.6 gph (13.6 L/h )
Best speed for maximum endurance 90 knots 4900-5000 rpm
Maximum endurance at 90 knots 3.6 hours + 30 min reserve
Takeoff - ground roll - at MTOM 555 ft (170 m)
Takeoff total distance over 50 ft obst. at MTOM 870 ft (265 m)
Landing distance over 50 ft obst. 1510 ft (460 m)
Absolute ceiling at MTOM 18,000 ft (5500 m)
NOTE The above performance figures are based on an airplane weight at 1212 lbs (550 kg), stan-
dard atmospheric conditions, level hard-surfaced dry runways and no wind. They are calculated val-
ues derived from flight tests conducted by Pipistrel, under the supervision of the Slovenian CAA and
under carefully documented conditions. Figures may vary based on numerous factors (surface condi-
tion, temperature, water on wing, etc).
ALPHA Trainer 80 hp Rotax 912
Maximum weight takeoff 1212 lbs (550 kg)
Maximum weight landing 1212 lbs (550 kg)
Standard empty weight 615 lbs (279 kg)
Payload without fuel 597 lbs (271 kg)
Payload with full fuel 518 lbs (235 kg)
Baggage allowance aft of the cabin* 22 lbs (10 kg)
Fuel capacity, total 13.2 US gal (50 L)
Fuel capacity, usable 12.7 US gal (48 L)
Fuel weight full 79.4 lbs (36 kg)
Oil system capacity 3.5 Liters
Engine Rotax 912 80 hp
Propeller Pipistrel FP02-80, dia. 65’’
1660 mm
* WARNING! only when baggage net or solid baggage compartment is installed ( p/n 6023077).
CG limits must be always respected!
Noise levels
According to independent testing performed by German LBA-LTF noise regulations the airplanes, the
equivalent exhibited noise measures 55.8 dBa. Noise is measured on the ground when the airplane
overflies at 500 ft at full power, at speed of best climb. Measures have been taken to make the cockpit
exceptionally quiet on the inside as well.
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Coverage
The Pilot’s Operating Handbook (POH), found in the airplane at the time of delivery from Pipistrel con-
tains information applicable to the ALPHA Trainer airplane and to the airframe designated by the serial
number and registration number shown on the title page. All information is based on data available at
the time of publication. Continued airworthiness is according to ASTM F2295, information is available
below.
This POH consists of ten sections that cover all operational aspects of a standardly equipped airplane.
Section 10 contains the supplements which provide amended operating procedures, performance data
and other necessary information for those airplanes that conduct special operations and/or are equipped
with both standard and optional equipment. Additional supplements are individual documents which
are issued/revised separately. The log of effective pages should be used to determine the status of each
supplement.
Revision tracking, filing and identifying
Pages to be removed or replaced in the Pilot’s Operating Handbook are determined by the log of effec-
tive pages located in this section. This log contains the page number and revision number for each page
within the POH. As revisions to the POH occur, the revision number on the effected pages is updated.
When two pages display the same page number, the page with the latest revision shall be used in the
POH. The revision number on the log of effective pages shall also coincide with the revision number of
the page in question. As an alternative to removing and/or replacing individual pages, the owner can also
print out a whole new manual in its current form, which is always available from www.pipistrel-aircraft.
com.
Revised material is marked with a vertical double-bar that will extend the full length of deleted, new, or
revised text added to new or previously existing pages. This marker will be located adjacent to the appli-
cable text in the marking on the outer side of the page.The same system applies when the header, figure,
or any other element inside this POH is revised. A list of revisions is located at the beginning of the log of
effective pages. Pipistrel is not responsible for technical changes/updates to OEM manuals supplied with
the aircraft (eg. radio, transponder, GPS, etc.).
Online updates, service notice tracking &
airworthiness reporting
To receive and report Issues and anomalies identified by the aircraft owner or maintainer during the op-
eration or maintenance of this aircraft or to report content errors in this manual then please log into the
Owner’s section of the Pipistrel website where you can report service difficulties and receive updates and
information relevant to service and airworthiness of your aircraft.
Go to: www.pipistrel-aircraft.com, go to support section - technical documentation, and log in with:
Username: owner1 Password: ab2008
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Index of revisions
The table below shows the revision history of this POH. Check your registration authority’s or the manu-
facturer’s website occasionally for the most up-to-date releases of operation-relevant documentation,
which includes this POH.
Designation Reason for revision Release date Affected
pages Issuer
Preliminary / 15 November, 2011 / Tomazic, Pipistrel LSA s.r.l.
Preliminary 2nd January 2012 Various Review
Before Release Coates, Pipistrel LSA s.r.l.
Release Revision 1 19th March 2012 Various Review
Before Release Coates, Pipistrel LSA s.r.l.
Revision 2 Added Section 10,
Language US English 19th December 2012 All and added Section 10 Coates, Pipistrel LSA s.r.l.
Revision 3 Specification
changes 22nd July 2013 Several Coates, Pipistrel LSA s.r.l.
Revision 4 Specification
changes 13th August 2013 Several Coates, Pipistrel LSA s.r.l.
Revision 5
Reordering of chapters
to comply with ASTM
F2746-12
31st January 2014 ALL Coates, Pipistrel LSA s.r.l.
Revision 6 Small Changes 31st March 2015 Cover, 5-5 and 9-6 Coates, Pipistrel LSA s.r.l.
Revision 7 Change operating tem-
perature 24th April 2015 Cover, 2-5 Coates, Pipistrel LSA s.r.l.
Revision 8 Changes 11th August 2015 Cover, i-2, 1-4, 1-5,
2-5, 4-5, 4-7, 5-2. Coates, Pipistrel LSA s.r.l.
Revision 9 Fuel information 24th January 2017 Cover, 1-4, 2-3, 2-6 Coates, Pipistrel LSA s.r.l.
Revision A00
New baggage restric-
tions, new company
website, release of SI-
160-001,
LX Instrument Suite,
Fuel system descrip-
tion improved, VAspeed
changed
30th Aug 2019 ALL SLO.DOA.002
Revision A01 Flapless landing NOTE
added 8th October 2019 Cover, I-4, I-5, 4-9 SLO.DOA.002
Revision B00
Instrument panel de-
scription improved
(supplement), Kinds of
operations, Flapless land-
ing limitet do day-time
24th October 2019 ALL SLO.DOA.002

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Log of Effective Pages
Use the table below to determine the currency and applicability of your POH. Pages affected
by the current revision are marked in bold text in the page number column.
Page number Rev. number Page number Rev. number
Cover -4-7 0
i-1 - 4-8 0
i-2 0 4-9 0
i-3 0 4-10 0
i-4 0 5-1 0
i-5 0 5-2 0
i-6 0 5-3 0
i-7 - 5-4 0
0-1 0 5-5 0
0-2 - 5-6 0
1-1 0 5-7 0
1-2 0 5-8 -
1-3 0 6-1 0
1-4 0 6-2 0
1-5 0 6-3 0
1-6 0 6-4 0
2-1 0 6-5 0
2-2 0 6-6 -
2-3 0 7-1 0
2-4 0 7-2 0
2-5 0 7-3 0
2-6 0 7-4 0
2-7 0 7-5 0
2-8 0 7-6 0
2-9 0 7-7 0
2-10 0 7-8 0
2-11 0 7-9 0
2-12 - 7-10 0
3-1 0 7-11 0
3-2 0 7-12 -
3-3 0 8-1 0
3-4 0 8-2 0
3-5 0 8-3 0
3-6 - 8-4 0
4-1 0 8-5 0
4-2 0 8-6 0
4-3 0 9-1 0
4-4 0 9-2 0
4-5 0 9-3 0
4-6 0 9-4 0
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Log of Effective Pages (continued)
Page number Rev. number Page number Rev. number
9-5 0 10-5 0
9-6 0 10-6 0
9-7 0 10-7 -
9-8 0 10-8 0
10-1 0 10-9 -
10-2 0 10-10 0
10-3 0 10-11 -
10-4 0 Back cover 0
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.
IMPORTANT !
This Pipistrel ALPHA Trainer aircraft is sold globally in more than 40 countries. Many countries have their
own individual requirements for information required to be shown in an aircraft manual. This manual
is the only official manual for the ASTM-LSA version, published by Pipistrel, in some countries it may be
necessary to add supplements or inserts to comply with local regulations, these are listed in Section 10
if required.
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Warnings, Cautions and Notes
Safety definitions used in the manual:
WARNING! An operating procedure or technique that may result in personal injury or loss
of life if not followed.
CAUTION! An operating procedure or technique that may result in damage to equipment if
not followed.
NOTE An operating procedure or technique needing special emphasis.

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Table of contents
1 General
2 Operating limitations
3 Emergency procedures
4 Normal procedures
5 Performance
6 Weight and balance
7 Aircraft & systems
8 Handling and service
9 Appendix
10 Supplements
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Introduction (1-2)
Technical brief (1-2)
3-view drawing (1-3)
Powerplant, fuel, oil (1-4)
Weights (1-6)
Center of gravity range (1-6)
G-load factors (1-6)
1 General
General
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Technical brief
DIMENSIONS ALPHA Trainer
Wing span 34’ 6’’ (10.5 m)
Length 21’ 4’’ (6.5 m)
Height 6’’ 9’ (2.05 m)
Wing surface 102.4 sqft (9.51 m2)
Vertical fin surface 11.8 sqft (1.1 m2)
Horizontal stabilizer and elevator surface 11.6 sqft (1.08 m2)
Aspect ratio 11.8
Positive flap deflection (down)
0°- position (0),
+15° - position (+1),
+25° - position (+2)
In flight Center of Gravity (MAC) 25% - 36%
Propeller - fixed pitch Pipistrel FP02-80, dia. 65’’
1660 mm
General
Introduction
This manual contains all information needed for appropriate and safe use of ALPHA Trainer.
IT IS MANDATORY TO CAREFULLY STUDY THIS MANUAL BEFORE USING THE AIRCRAFT.
Pipistrel do.o. is not responsible for any damage or injury resulting from not following the instruc-
tions contained in this manual.
All text, design, layout and graphics are owned by Pipistrel d.o.o.. 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 Pipistrel d.o.o. unless they are directly related to the operation of our aircraft by an
owner or his appointed maintenance authority.
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3-view drawing
General
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Powerplant, fuel, oil
Engine manufacturer: ROTAX
Engine type: Rotax 912 (80 HP)
The engine
TEMPERATURE °C / ROTAX ENGINE 912 80 HP
Maximum coolant temp. (CT) 120
Maximum exhaust gas temperature (EGT) 880
Oil temperature (OIL TEMP); minimum, normal, highest 50; 90-110; 140
RPM, PRESSURE 912 80 HP
Oil pressure (OIL PRESS); lowest, highest bar (psi) 0.8; 2.0-5.0; 7.0
Maximum continuous speed (RPM) 5500
Take-o speed; maximum allowable 5 min (RPM) 5800
Magneto check at (RPM) 4000
Maximum single magneto drop (RPM) < 300
Fuel and oil
ROTAX ENGINE 912 80 HP
Recommended fuel **
minimum 90 RON
grade,
up to 10% alcohol
content permitted,
0% is preferable*
Also approved fuels ** leaded*or AVGAS
100 LL
Recommended oil **
SAE 10 W-40
AeroShell Oil Sport
Plus 4
Oil system capacity typical 3.5 L (check dipstick)
* Engine life is reduced. If using this type of fuel is unavoidable, changing the engine oil
every 50 flight hours is crucial. Please consult the manufacturer on which type of oil to use.
** See latest edition of Rotax Service Instruction SI-912-016R10 Selection of suitable operating
uids for Rotax Engine.
IMPORTANT!
Four-stroke engines should only be powered by unleaded fuel, for lead sedimentation inside the en-
gine shortens its life. Provided you are unable to use unleaded fuel, make sure engine oil and the oil
filter are replaced every 50 flight hours.
WARNING! Use of fuels with alcohol content exceeding 10% is not permitted. See Rotax
specification - please refer to SI-912-016 “Selection of suitable operating fluids“ latest issue.
NOTE Please refer to the applicable Rotax operator’s manual for additional engine operating limi-
rations.
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NOTE The fuel indicator is equipped with coloured markings for fuel status which indicates the
percentage of fuel tank capacity. The fuel indicator is electric and may not be reliable at all times. Pilot
caution is advised.
When fuelling or de-fuelling, verify that the vent tube remains unobstructed from contamination.
Propeller
ALPHA Trainer Propeller
Rotax 912 (80 HP) Pipistrel FP02-80, diameter 1660 mm
Engine instrument markings
Instrument Red line
(minimum)
Green arc
(normal)
Yellow arc
(caution)
Red line
(maximum)
Tachometer (RPM) / 1400-5500 5500-5800 5800
Oil temperature 50°C
(122°F)
90-110°C
(194-230°F)
110-125°C
(230-257°F)
140°C
(266°F)
Coolant temp
/ /
110-120°C
(230-248°F)
120°C
(248°F)
Oil pressure
1.0 bar (14.5 psi)
1.5 - 5.0 bar
(21.7 - 72.5 psi)
5.0 - 6.5 bar
(72.5 - 94.0 psi)
6.5 bar (94.3 psi)
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Weights
ALPHA Trainer weights
WEIGHT ALPHA Trainer
Standard empty weight 615 lbs (279 kg)
Maximum takeo weight (MTOM) 1212 lbs (550 kg)
Fuel capacity (full) 13.2 US gal (50 L)
Fuel capacity (usable) 12.7 US gal (48 L)
Maximum fuel weight allowable 79.4 lbs (36 kg)
Payload with full fuel 518 lbs (235 kg)
Minimum combined cockpit crew weight 121 lbs (55 kg)
Baggage allowance aft of the cabin* Maximum 22 lbs (10 kg)
* WARNING!only when baggage net or solid baggage compartment is installed (p/n 6023077).
CG limits must be always respected.
WARNING! MTOM must be kept at or below 1212 lbs (550 kg). Exceeding baggage weight or
c.g. limits can shift aircraft’s balance to the point when the flight becomes uncontrollable! More
information on baggage allowance can be found in chapter “Weight and Balance”.
Center of gravity range
•The aircraft's in-flight safe center of gravity position ranges between 25% and 36%
of mean aerodynamic chord.
•The in flight center of gravity point ranges between 10 7/16'' (265 mm) and 14 21/64''
(364 mm) aft of the datum. The datum is the wing's leading edge at the fuselage root.
G-load factors
Max. positive wing load: + 4 G
Max. negative wing load: – 2 G
All parts have been tested to a safety factor of a minimum 1.875, meaning they were subjected to at
least a load of 7.5 G
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2 Limitations
Limitations
2-1
Introduction (2-2)
Airspeed limitations (2-2)
Powerplant limitations (2-3)
Weights (2-4)
Center of gravity range (2-4)
G-Load factors (2-5)
Service ceiling, crosswind (2-5)
Maneuver limits (2-5)
Kinds of operations (2-6)
Minimum equipment list (2-6)
Fuel limitations (2-6)
Other restrictions (2-7)
Placards (2-8)

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Airspeed limitations
Velocity IAS
[kts (km/h)] Remarks
VS Stall speed
Clean 43 (80) Stall speed aps up (0) position.
VS0 Stall speed
Landing conguration 37 (68) Stall speed flaps full (+2) position.
VFE Max. velocity aps
extended 70 (130) Do not exceed this speed with aps extended.
VA
Design maneuvering
speed 96 (177) Do not make full or abrupt control movements above this speed.
VNE
Velocity never to be
exceeded 135 (250) Never exceed this speed in any operation.
VNO Velocity normal oper-
ating 108 (201) Maximum structural cruising speed in tur- bulent air.
Airspeed indicator markings
MARKING IAS [kts (km/h)] Denition
White band 37 -70
(68 - 130)
Full Flap Operating Range. Lower limit is the maximum
weight VS0 in landing conguration. Upper limit is maxi-
mum speed permissible with aps extended.
Green band 43 -108
(83 - 201)
Normal Operating Range Lower end is maximum weight
VS1 at most forward C.G. with aps retracted. Upper limit is
maximum structural cruising speed.
Yellow band 108 - 135
(201 - 250) Maneuver the aircraft with caution in calm air only.
Red line 135 (250) Maximum speed for all operations. VNE
Blue line 76 (140) Best climb rate speed (Vy)
/58 (108) Best angle of climb speed (Vx)
Introduction
This section includes operating limitations, instrument markings and basic placards necessary for the
safe operation of the airplane, it’s engine, standard system and standard equipment.
The limitations included in this section have been approved by target authority.
Observance of these operating limitations is required by law.
Limitations
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Limitations
Powerplant limitations
Engine manufacturer: ROTAX
Engine type: Rotax 912 UL2 (80 HP)
Data below is data relevant for the pilot. Consult the original Rotax engine manual for all other details.
The engine
TEMPERATURE °C / ROTAX ENGINE 912 80 HP
Maximum coolant temp. (CT) 120
Maximum exhaust gas temperature (EGT) 880
Oil temperature (OIL TEMP); minimum, normal, highest 50; 90-110; 140
RPM, PRESSURE 912 80 HP
Oil pressure (OIL PRESS); lowest, highest bar (psi) 0.8; 2.0-5.0; 7.0
Maximum continuous speed (RPM) 5500
Take-o speed; maximum allowable 5 min (RPM) 5800
Magneto check at (RPM) 4000
Maximum single magneto drop (RPM) < 300
Fuel and oil
ROTAX ENGINE 912 UL2 (80 HP)
Recommended fuel **
minimum 90 RON grade,
up to 10% alcohol
content permitted, 0% is
preferable *
Also approved fuels ** leaded*or AVGAS 100LL*
Recommended oil ** SAE 10 W-40
AeroShell Oil Sport Plus 4
* Engine life is reduced. If using this type of fuel is unavoidable, changing the engine oil
every 50 flight hours is crucial. Please consult the manufacturer on which type of oil to use.
** See latest edition of Rotax Service Instruction SI-912-016R10 Selection of suitable operating
uids for Rotax Engine.
IMPORTANT!
Four-stroke engines should only be powered by unleaded fuel, for lead sedimentation inside the en-
gine shortens its life. Provided you are unable to use unleaded fuel, make sure engine oil and the oil
filter are replaced every 50 flight hours.
WARNING! Use of fuels with alcohol content exceeding 10% is not permitted.
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Limitations
Propeller
ALPHA Trainer Propeller
with Rotax 912 UL2 (80 HP) Pipistrel FP02-80 diameter 65’’ (1660 mm)
Engine instrument markings
Instrument Red line
(minimum)
Green arc
(normal)
Yellow arc
(caution)
Red line
(maximum)
Tachometer (RPM) / 1400-5500 5500-5800 5800
Oil temperature 50°C
(122°F)
90-110°C
(194-230°F)
110-125°C
(230-257°F)
140°C
(266°F)
Coolant temp
/ /
110-120°C
(230-248°F)
120°C
(248°F)
Oil pressure 1.0 bar (14.5 psi) 1.5 - 5.0 bar
(21.7 - 72.5 psi)
5.0 - 6.5 bar
(72.5 - 94.0 psi) 6.5 bar (94.3 psi)
Weights
ALPHA Trainer weights
WEIGHT ALPHA Trainer
Maximum takeo weight (MTOM) 1212 lbs ( 550 kg)
Minimum combined cockpit crew weight 121 lbs ( 55 kg)
Baggage aft of the cabin* 22 lbs (10 kg). Always verify baggage
allowance with a center of gravity
calculation!
* WARNING! only when baggage net or solid baggage compartment is installed ( p/n
6023077) and payload secured. CG limits must be always respected.
WARNING! MTOM must be kept at or below 1212 lbs (550 kg). Exceeding baggage weight or
c.g. limits can shift aircraft’s balance to the point when the flight becomes uncontrollable! More
information on baggage allowance can be found in chapter “Weight and Balance”.
Center of gravity range
•The aircraft's in-flight safe center of gravity position ranges between 25% and 36% of
mean aerodynamic chord.
•The in-flight center of gravity point ranges between 25% and 36% of MAC or 10 7/16''
(265 mm) and 14 21/64'' (364 mm) aft of the datum. The datum is the wing's leading
edge at the fuselage root.
2-4