Taurus ELECTRO G2 Technical specifications
Flight manual and
Maintenance manual
applies to Taurus ELECTRO G2
WARNING!
This document MUST be present inside the cockpit at all times.
Should you be selling the aircraft make sure this document is given to the new owner.
© Copyright Pipistrel d.o.o. Ajdovščina, Slovenia EU
Revision 3
(24th April, 2015)
This is the original manual of Pipistrel d.o.o. Ajdovščina
Should third-party translations to other languages contain any discrepancies,
Pipistrel d.o.o. Ajdovščina denies all responsibility.
Aircraft Registration Number:
Aircraft Serial Number:
2TAURUS ELECTRO www.pipistrel.si
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Taurus model:
Factory serial number:
Date of manufacture:
Aircraft empty weight (kg):
Available crew weight (no front ballast):
Available crew weight (9 kg front ballast):
Available luggage weight:
List of equipment included in aircraft empty weight:
Date and place of issue: Ajdovščina,
To log into the Owner’s section, receive updates and Service Bulletins, go to: www.pipistrel.si and log in
the top right corner of the page with:
Username: owner1
Password: ab2008
THANK YOU!
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Flight manual and
Maintenance manual for
Model: Taurus ELECTRO
Data Sheet:
Factory serial number:
Registration number:
Date of Issue: May, 2013
Pages signed under“Approval”in section Index of revisions and List of valid pages
(pages 4 and 5 of this manual) are approved by:
Authority: SLO.DOA.002
Signature:
Stamp:
Original date of Approval: March, 2011
This aircraft is to be operated in compliance with information and limitations contained herein.
The original English Language edition of this manual has been approved as operating instruction
according to“Pravilnik o ultralahkih letalnih napravah” of Republic of Slovenia.
Approval of translation has been done by best knowledge and judgement.
Pipistrel d.o.o. Ajdovščina, Goriška cesta 50a, SI- 5270 Ajdovščina, Slovenija
www.pipistrel.si
Taurus ELECTRO
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Index of revisions
Enter and sign the list of revised pages in the manual into the spaces provided below. All revised pages
should be clearly designated in the upper right corner of the page, also, any changes in page content
should be clearly visible (e.g. marked with a bold black vertical line).
Name of
revision
Reason for
Revision
Revision No.,
date Description Affected
pages
Approval,
signature
Original / Rev. 0
27 October, 2012 First original release. / Tomazic
1Various
Updates
Revision 1
1 May 2013 Version No. 1 All Coates. M
Revision 2
Reordering of
chapters to
comply with
ASTM F2746-12
Revision 2
31 January, 2014 Revision 2 All Coates M
Revision 3
Operating
Temperature
Change
Revision 3
24 April, 2015 Revision 3 All Coates M
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List of valid pages
This manual contains 96 original and revised pages listed below.
Pages State
(Revision) Approval
Cover REV. 3
Page numbering REV. 1
Authority approval sheet 3REV. 1
Index of revisions 4REV. 3
List of valid pages 5REV. 1
Table of contents 7REV. 1
General 9 - 12 REV. 1
Limitations 13 - 20 REV. 3
Emergency procedures 21 - 28 REV. 1
Normal procedures 29 - 42 REV. 1
Performance 43 - 51 REV. 1
Weight and balance 53 - 59 REV. 1
Aircraft and systems on board 61 - 73 REV. 1
Handling and maintenance 75 - 84 REV. 1
Appendix 85 - 93 REV. 1
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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Table of contents
1 General
2 Limitations
3 Emergency procedures
4 Normal procedures
5 Performance
6 Weight and balance
7 Description of aircraft & systems
8 Handling and maintenance
9 Appendix
10 Supplements
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Introduction
Notes and remarks
Technical data
3-view drawing
General
General
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Introduction
This manual contains all information needed for appropriate and safe use of theTaurus Electro Aircraft.
IT IS MANDATORY TO CAREFULLY STUDY THIS MANUAL PRIOR TO USE
OF THE TAURUS AIRCRAFT
In case of aircraft damage or personal injury resulting from disobeying instructions in the manual
PIPISTREL d.o.o. Ajdovscina denies all responsibility.
All text, design, layout and graphics are owned by PIPISTREL d.o.o. Ajdovscina 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. Ajdovscina unless they are directly related to the opera-
tion of our aircraft by an owner or his appointed maintenance authority.
Notes and remarks
Safety definitions used in the manual:
WARNING! DISREGARDING THE FOLLOWING INSTRUCTIONS WILL LEAD TO SEVERE
DETERIORATION OF FLIGHT SAFETY AND HAZARDOUS SITUATIONS, INCLUDING SUCH
RESULTING IN INJURY AND LOSS OF LIFE.
CAUTION! DISREGARDING THE FOLLOWING INSTRUCTIONS WILL LEAD TO SERIOUS
DETERIORATION OF FLIGHT SAFETY.
Technical data
PROPORTIONS ELECTRO
wing span 14.97 m
length 7.30 m
height (propeller extended) 2.7 m
wing area 12.26 m2
vertical tail area 0.86 m2
horizontal stabilizer and elevator area 1.275 m2
aspect ratio 18.30
positive flap deflection (down) 5°, 9 °, 18 °
negative flap deflection (up) -5°
centre of gravity (% of MAC) 23% - 45%
General
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3-view drawing
General
Dimensions in millimeters
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Introduction
Operational velocities
Motor
Weight limits
Centre of gravity limits
Manoeuvre limits
G-load factors
Cockpit crew
Types of operations
Minimum equipment list
Other restrictions
Warning placards
Limitations
Limitations
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Operational velocities
Speed limits
Velocity IAS
[km/h (kts)] Remarks
VNE Velocity never to be
exceeded 225 (121)
Never exceed this speed. Should the VNE be
exceeded, land as soon as possible and have
the aircraft verified for airworthiness by au-
thorised service personnel.
VPE Max. speed with
powerplant extended 120 (65) Do not exceed this speed with powerplant
extended.
VPO Max. speed to extend
or retract powerplant 100 (54) Do not extend or retract powerplant above
this speed.
VRA Maximum safe velocity
in rough air 163 (88) Also known as Vb. Turbulence penetration
speed.
VA Maneuvering velocity 163 (88)
Do not use rough or full stick and
rudder deflections above this speed.
VFE Max. velocity flaps
extended 130 (70) Do not exceed this speed with +5° or T flaps
extended. (VFE for L flaps is 110 km/h (59 kts))
VAE Max. velocity of
airbrake extension 163 (88) Do not extend spoilers above this
speed. Once fully extended, VNE is the limit.
VLO Max ldg. down speed 163 (88) Do not fly with landing gear extended
above this speed
Airspeed indicator markings
MARKING IAS [km/h (kts)] Definition
white arc 69 - 130
(37 - 70)
Speed range where flaps may be extended. Lower end is de-
fined as 110% of VS (stall speed in landing configuration at
MTOM), upper end of speed range is limited by VFE
(see above).
green arc 78 - 163
(42 - 88)
Speed range of normal operation. Lower end is defined as
110% of VS1 (stall speed at MTOM with flaps in neutral posi-
tion), upper end is limited by VRA (see above).
yellow arc 163 - 225
(88 - 121) Manoeuvre the aircraft with great caution in calm air only.
red line 225
(121) Maximum speed allowed.
blue line 100 (54) Best climb rate speed (VY)
Introduction
This chapter provides information about operational restrictions, instrument markings and basic
knowledge on safe operation of aircraft, motor and on-board appliances.
Limitations
WARNING! ABOVE PRESSURE ALTITUDE OF 1000 METERS 3300 FT ALL SPEED LIM
ITS MUST BE TREATED AS TRUE AIRSPEED TAS.
INDICATED AIRSPEED IAS MUST BE REDUCED ACCORDINGLY!
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Limitations
VNE at altitude (standard ICAO atmosphere)
The tables below indicate IAS to TAS relation for an altitude span of 0 - 5000m (0 - FL165) in different
atmospheres (variable is temperature). TAS is a constant of 225 km/h (122 kts) - VNE for the entire tables.
ISA-20 (-5°C at sea level):
Altitude (meters) 0 500 1000 1500 2000 2500 3000 3500 4000 4500 5000
Altitude (flight level) 0 FL16 FL33 FL50 FL66 FL82 FL98 FL115 FL131 FL148 FL165
VNE IAS (km/h) 225 225 223 218 213 209 203 198 194 189 185
VNE IAS (kts) 121 121 120 118 115 113 110 107 105 102 100
ISA-10 (5°C at sea level):
Altitude (meters) 0 500 1000 1500 2000 2500 3000 3500 4000 4500 5000
Altitude (flight level) 0 FL16 FL33 FL50 FL66 FL82 FL98 FL115 FL131 FL148 FL165
VNE IAS (km/h) 225 224 219 214 209 205 199 195 191 186 182
VNE IAS (kts) 121 121 118 116 113 111 108 105 103 100 98
ISA (15°C at sea level):
Altitude (meters) 0 500 1000 1500 2000 2500 3000 3500 4000 4500 5000
Altitude (flight level) 0 FL16 FL33 FL50 FL66 FL82 FL98 FL115 FL131 FL148 FL165
VNE IAS (km/h) 225 220 215 210 205 201 196 191 187 182 178
VNE IAS (kts) 121 119 116 113 111 109 106 103 101 98 96
ISA+10 (25°C at sea level):
Altitude (meters) 0 500 1000 1500 2000 2500 3000 3500 4000 4500 5000
Altitude (flight level) 0 FL16 FL33 FL50 FL66 FL82 FL98 FL115 FL131 FL148 FL165
VNE IAS (km/h) 220 215 211 206 202 197 192 188 184 179 175
VNE IAS (kts) 119 116 114 111 109 106 104 102 99 97 94
ISA+20 (35°C at sea level) :
Altitude (meters) 0 500 1000 1500 2000 2500 3000 3500 4000 4500 5000
Altitude (flight level) 0 FL16 FL33 FL50 FL66 FL82 FL98 FL115 FL131 FL148 FL165
VNE IAS (km/h) 216 211 207 202 197 193 189 184 180 175 171
VNE IAS (kts) 117 114 112 109 106 104 102 99 97 94 92
Note how VNE decreases at higher altitudes!
WARNING! RESPECT THE LISTED VALUES AT ALL TIMES, NOT TO EXCEED FLUTTER CRITI
CAL SPEED.
Indicated airspeed (IAS) to true airspeed (TAS) relation
Airspeed indicator measures the difference between total and static pressure (also called dynamic
pressure), which does not only change as speed increases, but is also linked with altitude. Flying
at high altitudes, where the air is getting thinner, results in incorrect airspeed being indicated. The
indicated airspeed value is actually lower than the true airspeed to which the aircraft is exposed.
The higher you fly, the bigger the difference between IAS and TAS. Be aware of this effect especially
when flying at high altitude at high speeds, not to exceed VNE unawarely. Bear in mind this can hap-
pen even with the indicator still pointing within the yellow arc!
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REV. 3 Limitations
Motor/controller, Battery System
Motor types: ELECTRO 40/30
WARNING! The motor is not certified for aviation use, therefore, there is no
assurance it cannot fail in its operation at any given moment, without prior notice.
The motor
TEMPERATURE °C / ELECTROMOTOR ELECTRO 40/30
maximum take-off power (1 min) 40 kW
maximum continuous power 30 kW
maximum operating temperature 100° C
maximum ambient temperature 40° C
RPM ELECTRO 40/30
maximum allowable 2200
take-off rpm (typical) 2150
climb rpm (typical) 1900
Controller
POWER CONTROLLER ELECTRO 40/30
maximum operating temperature 75° C
recommended max continuous temperature 45-55° C
WARNING! DO NOT, UNDER ANY CIRCUMSTANCES, ATTEMPT TO USE ANY OTHER
BATTERIES, OTHER THAN PIPISTREL FACTORY ORIGINAL BATTERY SYSTEM, WITH THIS MOTOR/
CONTROLLER
Battery system
Battery system Standard
Maximum voltage 285 V
Minimum voltage 204 V
Recommended voltage range for storage 240 V - 260 V
Maximum operating temperature 70° C
Minimum operating temperature 5° C
Allowable temperature range for storage 10°C - 40° C
CAUTION! TEMPERATURES BELOW 10°C WILL RESULT IN DECREASE OF 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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Limitations
Propeller
TAURUS ELECTRO
fixed pitch (wooden or composite) 1650 mm
Motor instrument markings
Instrument Red line
(minimum)
Green arc
(normal)
Yellow arc
(caution)
Red line
(maximum)
Tachometer (RPM)
Controller temp. (°C)
Battery system temp (°C)
Not Applicable
Not Applicable
5
0-2150
5-55
10-50
2150-2200
55-70
50-70
2200
70
70
Weight limits
Taurus electro basic model weights
WEIGHT ELECTRO
empty aircraft weight (incl. parachute rescue system), std battery system 306 kg
empty aircraft weight (incl. parachute rescue system), optional batteries sys. 323 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
water balance reservoir (max weight) 9 kg
allowable luggage weight 10 kg
WARNING! SHOULD ONE OF THE ABOVELISTED VALUES BE EXCEEDED, OTHERS MUST BE
REDUCED IN ORDER TO KEEP MTOM BELOW 550 KG. MAKE SURE MAXIMUM AND MINIMUM
COCKPIT CREW WEIGHT AS WELL AS AVAILABLE LUGGAGE WEIGHT ARE ALWAYS KEPT WITHIN
ALLOWABLE LIMITS. FAILING TO COMPLY WITH ANY OF THE WEIGHT LIMITATIONS MAY RESULT
IN AIRCRAFT BEING UNCONTROLLABLE ON GROUND AND/OR IN FLIGHT DUE TO EXTREME
CENTRE OF GRAVITY POSITION.
WARNING! CHECK THE WATER BALANCE RESERVOIR IN FRONTCABIN AND VERIFY
CREW’S WEIGHT BEFORE EVERY FLIGHT AS IT MAY INFLUENCE THE CENTRE OF GRAVITY OF
AIRCRAFT TO THE POINT WHERE IT IS NO LONGER CONTROLLABLE!
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Centre of gravity limits
•Aircraft's safe centre of gravity position ranges between 23% and 45% of MAC (Mean
Aerodynamic Chord)
•C.G. point ranges between 238 mm and 429 mm aft of datum, datum is leading edge
of wing root.
Manoeuvre limits
Taurus Electro is certified as an Ultralight aircraft. Therefore, no aerobatic manoeuvres
are permitted.
WARNING! FLYING IN CONSIDERABLE SIDESLIP WHEN THE MOTOR IS EXTENDED AND
RUNNING MAY DAMAGE THE MOTORPROPELLER ASSEMBLY. YOU ARE STRONGLY DISCOUR
AGED FROM SIDESLIPPING WHEN MOTOR IS EXTENDED AND RUNNING!
G-load factors
at VA at VNE
max. positive wing load: + 5.3 G + 4.0 G
max. negative wing load: – 2.65 G – 1.5 G
Cockpit crew
•Actual minimum and maximum combined cockpit crew weight heavily depend on the
centre of gravity of an empty aircraft. Minimum and maximum combined cockpit crew
weight is determined after weighing the aircraft each time. Procedure for the deter-
mination of minimum and maximum combined cockpit crew weight can be found on
page 57 of this manual. Inside the cockpit, there must be a clearly visible placard stating
the minimum and maximum combined weight of the crew.
•Maximum takeoff weight (MTOW) MUST NOT, under any circumstances, exceed 550 kg.
Types of operations
Taurus Electro is built to fly under day visual flight rules
(day VFR). Flight into known icing conditions or rain is prohibited.
Limitations
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Limitations
WARNING! SHOULD YOU FIND WATER DROPS ON THE AIRFRAME DURING PREFLIGHT
CHECKUP AT TEMPERATURES CLOSE TO FREEZING, YOU MAY EXPECT ICING TO APPEAR IN
FLIGHT. AIRBRAKES ARE ESPECIALLY PRONE TO ICING UNDER SUCH CIRCUMSTANCES. AS
WATER MAY ACCUMULATE UNDERNEATH THE TOP PLATES, SPOILERS MAY FREEZE TO THE
WING SURFACE. SHOULD THIS OCCUR, YOU WILL MOST DEFINITELY BE UNABLE TO EXTEND
SPOILERS BEFORE THE ICE MELTS. THEREFORE, FLYING UNDER CIRCUMSTANCES MENTIONED
ABOVE, IT IS RECOMMENDED TO EXTEND AND RETRACT THE SPOILERS IN FLIGHT FREQUENT
LY TO PREVENT ITS SURFACE FREEZING TO THE AIRFRAME.
Minimum equipment list
• Airspeed indicator (functional)
• Altimeter (functional)
• Compass (functional)
• Electric System Manager instrument (ESYS-MAN)
• Battery Management System (BMS, functional)
• Parachute rescue system (where required legally)
Other restrictions
Due to flight safety reasons it is forbidden to:
•fly in any rainfall;
•fly during thunderstorm activity;
•fly in a blizzard;
•fly according to instrumental flight rules (IFR) or attempt to fly in zero visibility condi-
tions (IMC);
•fly when outside air temperature (OAT) reaches 50°C (122°F )or higher;
•perform any form of aerobatic flying;
•take off and land with flaps retracted or set to negative (-5°) position;
•take off with spoilers extended.
•store the aircraft outside in the rain.
Warning placards
Taurus Electro is categorized as an Ultralight aircraft and must display a
warning placard as such. The placard indicates the aircraft is not certified
according to EASA standards and is therefore flown completely at pilot’s
own risk.
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Placards
Limitations
max useful load kg
max cockpit load
without water ballast kg
min cockpit load
without water ballast kg
Reduce min cockpit load for 2.3 kg per each litre of
water ballast. Remove water ballast for duo flight!
pilot max. kg
with 9 kg nose ballast kg
pilot min. kg
with 9 kg nose ballast kg
baggage max. 2kg
secure baggage at all times!
N
030
060
300
W
330
E
120
150
S
210
240
N
030
060
300
W
330
E
120
150
S
210
240
VSO
VS1
VFE
VA
VNO
34 kts
40 kts
70 kts
82 kts
82 kts
VNE
120 kts
Respect limits
from POH!
EAW
MTOW
CREW WT
LUGGAGE WT
lbs
1212 lbs
see POH
22 lbs
EAW
MTOW
CREW WT
LUGGAGE WT
kg
550 kg
see POH
10 kg
PULL FOR PARACHUTE
DEPLOYEMENT
WARNING
ROCKET FOR PARACHUTE
DEPLOYEMENT INSIDE
DANGER
EXPLOSIVE
EGRESS
This aircraft is equipped
with a rocket powered
ballistic rescue system.
This aircraft is equipped
with a rocket powered
ballistic rescue system.
Table of contents
