Pipistrel Alpha Electro Owner's manual

Copyright 2017, Pipistrel d.o.o. Ajdovščina
applies to all ALPHA Electro aircraft
equipped with 60 kW electric motor
Pilot’s Operating Handbook
REV A00.
(12th July, 2017)
SERIAL NUMBER
REGISTRATION NUMBER

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Performance - Specifications
ALPHA Electro 60 kW Electric
Stall speed (flaps extended) 35 kts (64 km/h)
Stall speed (flaps retracted) 43 kts (74 km/h)
Typical cruise speed 85 kts (157 km/h)
VNE 135 kts (250 km/h)
Standard endurance, traffic patterns 55 min + 30 min. reserve
Standard range at cruise 85 kts 65 NM (120 km)
Takeoff - ground roll - at MTOM 459 ft (140 m)
Takeoff total distance over 50 ft obst. at MTOM 738 ft (225 m)
Landing distance over 50 ft obst. 1510 ft (460 m)
Absolute ceiling at MTOM 12,800 ft (3900 m)
NOTE The above performance figures are based on an airplane weight of 1215 lbs (550 kg),
standard atmospheric conditions, level hard-surfaced dry runways and no wind. They are calcu-
lated values derived from flight tests conducted by Pipistrel d.o.o. Ajdovščina, under the super-
vision of the Slovenian CAA and under carefully documented conditions. Figures may vary based
on numerous factors (surface condition, temperature, water on wing, etc).
ALPHA Electro 60 kW Electric
Maximum weight takeoff 1215 lbs (550 kg)
Maximum weight landing 1215lbs (550 kg)
Empty aircraft weight (incl. PRS) 552 lbs (251 kg)
Battery capacity, total 21.0 kWh
Battery capacity, useful 20.0 kWh
Motor 60 kW E-Motor
Propeller three blade, fixed pitch propeller (wooden or com-
posite), diameter 1640 mm
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Coverage
The Pilot’s Operating Handbook (POH), found in the airplane at the time of delivery from Pipistrel
d.o.o. Ajdovščina, contains information applicable to the ALPHA Electro 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.
This POH consists of ten sections that cover all operational aspects of a standardly equipped air-
plane. Section 10 contains the supplements which provide amended operating procedures, perfor-
mance 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 indi-
vidual 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
effective 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 availa-
ble from www.pipistrel.eu.
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 applicable 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.).
Warnings, cautions and notes
Safety definitions used in the manual:
WARNING! Disregarding the following instructions leads to severe deterioration of flight
safety and hazardous situations, including such resulting in injury and loss of life.
CAUTION! Disregarding the following instructions leads to serious deterioration of flight
safety.
NOTE An operating procedure, technique, etc., which is considered essential to emphasize.
Online updates, service notice tracking
For updates and information related to service/airworthiness, please go to www.pipistrel.eu 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 man-
ufacturer’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
REV A00 Initial issue 11th July, 2017 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 Page status Rev. number Page number Page status Rev. number
Cover Original 0 3-5 Original 0
i-1 Blank Page - 3-6 Original 0
i-2 Original 0 3-7 Original 0
i-3 Original 0 3-8 Original 0
i-4 Original 0 3-9 Original 0
i-5 Original 0 3-10 Original 0
i-6 Original 0 3-11 Original 0
i-7 Blank Page - 3-12 Blank Page -
0-1 Original 0 4-1 Original 0
0-2 Blank Page - 4-2 Original 0
1-1 Original 0 4-3 Original 0
1-2 Original 0 4-4 Original 0
1-3 Original 0 5-1 Original 0
1-4 Original 0 5-2 Original 0
1-5 Original 0 5-3 Original 0
1-6 Original 0 5-4 Original 0
2-1 Original 0 5-5 Original 0
2-2 Original 0 5-6 Original 0
2-3 Original 0 6-1 Original 0
2-4 Original 0 6-2 Original 0
2-5 Original 0 6-3 Original 0
2-6 Original 0 6-4 Original 0
2-7 Original 0 7-1 Original 0
2-8 Original 0 7-2 Original 0
2-9 Original 0 7-3 Original 0
2-10 Original 0 7-4 Original 0
3-1 Original 0 7-5 Original 0
3-2 Original 0 7-6 Original 0
3-3 Original 0 7-7 Original 0
3-4 Original 0 7-8 Original 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.
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Log of Effective Pages (continued)
Page number Page Status Rev. number Page number Page Status Rev. number
7-9 Original 0 9-5 Original 0
7-10 Blank Page - 9-6 Original 0
8-1 Original 0 9-7 Original 0
8-2 Original 0 9-8 Original 0
8-3 Original 0 9-9 Original 0
8-4 Original 0 9-10 Original 0
8-5 Original 0 9-11 Original 0
8-6 Blank Page - 9-12 Original 0
9-1 Original 0 9-13 Original 0
9-2 Original 0 9-14 Blank Page -
9-3 Original 0
9-4 Original 0
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Table of contents
1 General
2 Aircraft and systems description
3 Operating limitations
4 Weight and balance
5 Performance
6 Emergency procedures
7 Normal procedures
8 Handling, service and maintenance
9 Appendix
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Introduction (1-2)
Technical brief (1-2)
3-view drawing (1-3)
Powerplant (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 Electro
Wing span 34’6’’(10.5 m)
Length 21’4’’ (6.5 m)
Height 6’’ 9’ (2.05 m)
Wing surface 102 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) 15 °, 25 °
Center of gravity (MAC) 20% - 38%
General
Introduction
This manual contains all the information needed for appropriate and safe use of ALPHA Electro .
IT IS MANDATORY TO CAREFULLY STUDY THIS MANUAL BEFORE USING THE AIRCRAFT.
Pipistrel d.o.o. Ajdovščina is not responsible for any damage or injury resulting from not following
the instructions contained in this manual.
All text, design, layout and graphics are owned by Pipistrel d.o.o. Ajdovščina. All rights reserved.
Reproduction or disclosure to third parties of this document or any part therof is not permitted, ex-
cept with the prior and express written permission of Pipistrel d.o.o Ajdovščina.
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3-view drawing
General
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General
Motor/controller, battery system
WARNING! The motor is not certified for aviation use, therefore, there is no assur-
ance it won’t fail during operation at any given moment, without prior notice.
Motor
TEMPERATURE °C PEM 60MVLC
Maximum takeoff power (1 min) 60 kW
Maximum continuous power 50 kW
Maximum operating temperature 90° C
Maximum ambient temperature 40° C
RPM PEM 60MVLC
Maximum allowable rpm 2500
Takeoff RPM (typical) 2400
Climb RPM (typical) 2250
Controller
POWER CONTROLLER H300A
Nominal power 60 kW
Maximum operating temperature 65° C
Maximum ambient temperature 40° C
WARNING! DO NOT, UNDER ANY CIRCUMSTANCES, ATTEMPT TO USE ANY OTHER BATTERIES
OTHER THAN PIPISTREL FACTORY-SUPPLIED BATTERIES. ONLY USE THEM WITH THE MOTOR AND
CONTROLLER MENTIONED IN THIS POH.
Battery system
Battery system PB345V105E-A
Maximum voltage 398 V
Minimum voltage 288 V
Recommended voltage range for storage 355 V - 365 V
Maximum operating temperature 55° C
Minimum operating temperature 5° C
Allowable temperature range for storage 10°C - 40° C
Minimum charging temperature 0° C
CAUTION! TEMPERATURES BELOW 10°C WILL CAUSE A DECREASE IN BATTERY CAPACITY.
PLAN YOUR FLIGHT ACCORDINGLY.
WARNING! DO NOT, UNDER ANY CIRCUMSTANCES, ATTEMPT TO CHARGE THE BATTERIES
WITH ANY THIRD PARTY CHARGERS. ONLY PIPISTREL ORIGINAL EQUIPMENT MUST BE USED.
WARNING! RESPECT OPERATING AND STORAGE TEMPERATURE LIMITS AT ALL TIMES.
FAILURE TO DO SO MAY RESULT IN BATTERY DAMAGE.

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General
Propeller
ALPHA Electro FP03-60E
three blade, fixed pitch propeller (wooden or composite) 1640 mm
Motor instrument markings
Instrument Red line
(minimum)
Yellow arc
(caution)
Green arc
(normal)
Yellow arc
(caution)
Red line
(maximum)
Tachometer (RPM) / / 0-2399 2400-2499 2500
Motor temp. (°C) / / -20 - 89 90-94 95
Controller temp. (°C) / / -20 - 59 60-64 65
Battery sys. temp. (°C) 5 6-10 11-49 50-54 55
Weight limits
Basic model weights
WEIGHT ELECTRO
Empty aircraft weight (incl. PRS), std. battery system 379 kg
Max. takeoff weight (MTOW/MTOM) 550 kg
Minimum combined cockpit crew weight (depends on C.G. of empty aircraft) see p. 55
Maximum combined cockpit crew weight (depends on C.G. of empty aircraft) see p. 55
WARNING! SHOULD ONE OF THE ABOVELISTED VALUES BE EXCEEDED, OTHERS MUST BE
REDUCED IN ORDER TO KEEP THE MTOM BELOW 550 KG. FAILING TO COMPLY WITH ANY OF
THE WEIGHT LIMITATIONS MAY CAUSE UNCONTROLLED GROUND HANDLING AND/OR FLIGHT
DUE TO EXTREME CENTER OF GRAVITY POSITION.

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Center of gravity range
•The aircraft's safe center of gravity position ranges between 20% and 38% of mean
aerodynamic chord.
•The center of gravity point ranges between 7.7'' (195 mm) and 14.5'' (368 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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General

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Introduction (2-2)
Cockpit controls (2-4)
Instrument panel (2-4)
Undercarriage (2-6)
Seats and safety harnesses (2-6)
Pitot-static system (2-6)
Power plant (2-7)
Energy storage and charging (2-8)
Wheel brake system (2-10)
2 Aircraft and systems
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Aircraft and Systems

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The ALPHA Electro is a 34’6’’ (10.5 m) wing-
span, two-seat T-tail high-wing motorplane
made almost entirely of composite materials.
It has a robust, tricycle undercarriage that
incorporates brake-equipped wheels, a
U-shaped composite strut and a steerable nose
wheel.
The ALPHA Electro features flaperons, mean-
ing that one movable surface on each wing
acts both as the flap and the aileron. Flaps offer
3 settings: retracted 0o, +15oand + 25o.
Full dual main flight control levers make the
ALPHA Electro ideal for initial and advanced
flight training. All aileron, elevator and flap
controls are connected to the cabin controls
using self-fitting push-pull tubes. The rudder is
controlled via cables. The elevator trim is a me-
chanical, spring type mechanism.
All aircraft ship with H type safety belts at-
tached to the fuselage at three mounting
points. The rudder pedals can be adjusted
before and also in-flight to suit your size and
needs.
The aircraft is equipped with two battery box-
es: one is located aft of the cabin bulkhead and
the other is aft of the firewall. The battery sys-
tem is ventilated and thermally protected.
The electric motor is a 60 kW peak power unit
capable of energy recuperation during de-
scent.
The windshield, doors and top window are
made of 2 mm anti-UV tinted Lexan, which was
specially developed not to shatter or split on
impact.
The main wheel brakes are hydraulically driven
disc type and activated via a cockpit hand-le-
ver. The hydraulic brake fluid used is DOT 3 or
DOT 4.
Cabin ventilation is achieved through special
vents fitted into the doors
The propeller is a fixed pitch three-blade de-
sign.
The resettable electric circuit breakers enable
the pilot to test individual circuit items and
disconnect the batteries from the circuit if re-
quired.
Navigational (NAV) lights, anti collision (AC)
lights and a landing (LDG) light are installed.
The firewall is reinforced with heat and noise
insulation.
Basic instruments come installed with opera-
tional limits pre-designated.
A PRS is present and located in aft fuselage.
Introduction
Aircraft and Systems
2-2
RIGHT WING
PROPELLER
SPINNER
ENGINE COVERS
FRONT WHEEL PEDALS
LEFT WHEEL
LANDING GEAR
RUDDER CABLES
ELEVATOR CONTROL TUBE
LEFT WING
LEFT FLAPERON
RUDDER
ELEVATOR
STICK
RIGHT FLAPERON
RIGHT WHEEL

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Composite parts are made of:
Fabric: GG160, GG200, GG300, 90070, 92120, 91125, 92140, 92145, KHW200
Roving: NF24
Foam: 55kg/m3, 75 kg/m3 PVC 3mm, PVC 5 mm, PVC 8mm
GFK: 3 mm, 5 mm, 7 mm of thickness
Paint: acrylic paint
Firewall glass-aluminium sandwich
Metal parts used are:
Tubes: materials: Fe0146, Fe 0147, Fe0545, Fe1430, AC 100, CR41 and LN9369
Sheet metal: materials: Fe0147 and Al 3571
Rods: materials: Fe 1221, Fe 4732, Č4130, Al 6082, CR41 in Al 6362
Cable: AISI 316
Bolts and nuts: 8.8 steel
All composite parts are made of glass, carbon and kevlar fiber manufactured by Interglas GmbH and
Sigratex carbon.
All parts have been tested at safety factor of a minimum 1.875.
All composite parts are made in moulds, therefore no shape or structural differences
can occur.
All parts and materials used in the ALPHA Electro are also used in the glider and
general aviation industry and thus comply with aviation standards.
Aircraft and Systems
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HANDBRAKE LEVER
RIGHT SEAT
FLAP LEVER
LEFT SEAT
RIGHT PEDALS
THROTTLE LEVER
RIGHT PILOT STICK
RIGHT DOOR LEVER
LEFT DOOR
INSTRUMENT PANEL
TRIM LEVER
FRONT LEXAN
RIGHT DOOR
LEFT PEDALS
LEFT PILOT STICK
LEFT DOOR LEVER
Cockpit controls
The ALPHA Electro cockpit levers are divided into two groups:
Individual control levers: pilot stick and rudder pedals
Dual control levers: throttle lever, handbrake lever, flap lever, trim lever, door handles and emergen-
cy parachute release handle.
Instrument panel (Note: European configuration depicted below)
Alpha Electro
Tachometer Variometer
ELT
Aera 660 - Atlantic database
Airspeed Indicator Altimeter
Elevator trim
control plate
EPSI570
Transponder
Radio
Slip indicator
Air Brakes
( optional)
COM
I/O SET MEM
DW
ATC
I/O VFR ID
MODE
HORIS
EPSI570
Aircraft and Systems
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