Pipistrel Taurus ELECTRO G2 Technical specifications

Flight manual and
Maintenance manual
applies to Taurus ELECTRO G2
WARNING!
This booklet MUST be present inside the cockpit at all times!
Should you be selling the aircraft make sure this manual is handed over to the new owner.
REV. 0
(9 March, 2011)
This is the original manual of Pipistrel d.o.o. Ajdovščina
Should third-party translations to other languages contain any discreptancies,
Pipistrel d.o.o. Ajdovščina denies all responsibility.

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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: March, 2011
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
tel: [phone], fax: [phone], e-mail: [email protected]
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
9 March, 2011 First original release. / Tomazic

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List of valid pages
This manual contains 96 original and revised pages listed below.
Pages State
(Revision) Approval:
Cover REV. 0
Page numbering REV. 0
Authority approval sheet 3REV. 0
Index of revisions 4REV. 0
List of valid pages 5REV. 0
Table of contents 7REV. 0
General 9 - 12 REV. 0
Limitations 13 - 20 REV. 0
Emergency procedures 21 - 28 REV. 0
Normal procedures 29 - 42 REV. 0
Performance 43 - 51 REV. 0
Weight and balance 53 - 59 REV. 0
Aircraft and systems on board 61 - 73 REV. 0
Handling and maintenance 75 - 84 REV. 0
Appendix 85 - 93 REV. 0
CAUTION!
This manual is valid only if it contains all of the original and revised pages listed above.

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Table of contents
General
Limitations
Emergency procedures
Normal procedures
Performance
Weight and balance
Aircraft and systems on board
Handling and maintenance
Appendix

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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 Taurus Electro
IT IS MANDATORY TO CAREFULLY
STUDY THIS MANUAL PRIOR TO USE
OF AIRCRAFT
In case of aircraft damage or people injury
resulting form 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 man-
ner (electronic, web or printed) without the
prior consent of PIPISTREL d.o.o. Ajdovscina
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




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Introduction
Operational velocities
Motor, fuel, oil
Weight limits
Centre of gravity limits
Manoeuvre limits
G-load factors
Cockpit crew
Types of operations
Minimum equipment list
Other restrictions
Warning placards
Limitations
Limitarions

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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
Manoeuvering velocity
163
(88)
Do not use rough or full stick and
rudder deflecions 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 extention
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 po-
sition), upper end is limited by VRA (see above).
yellow arc
163 - 225
(88 - 121)
Manouvre the aircraft with great caution in calm air only.
red line
225
(121)
Maximum speed allowed.
blue line
100
(54)
Best climb rate speed (V
Y
)
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)
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)
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)
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)
Altitude (meters)
0
500
1000
1500
2000
2500
3000
3500
4000
4500
5000
Altitude (flight level)
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)
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)
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 misinterpreting airspeed which is 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 happen even with the indicator still pointing within the yellow arc!

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Limitations
Motor/controller, Battery System
Motor types: ELECTRO40/30
WARNING! The motor is not certified for aviation use, therefore, there is no assur-
ance 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 continous 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 continous 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
270 V
Minimum voltage
190 V
Recommended voltage range for storage
230 V - 250 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)
1650mm
Motor instrument markings
WARNING! USER IS TO FILL IN MOTOR SPECIFIC VALUES.
Instrument
Red line
(minimum)
Green arc
(normal)
Yellow arc
(caution)
Red line
(maximum)
Tachometer (RPM)
Controller temp. (°C)
Battery system temp (°C)
/
/
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)
472.5 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 ballance reservoir (max weight)
9 kg
allowable luggage weight
10 kg
WARNING! SHOULD ONE OF THE ABOVELISTED VALUES BE EXCEEDED, OTHERS MUST BE
REDUCED IN ORDER TO KEEP MTOM BELOW 472.5 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 FRONTCABIN 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 manoeuvers
are permitted.
WARNING! FLYING IN CONSIDERABLE SIDESLIP WHEN THE MOTOR IS EXTENDED AND
RUNNING MAY DAMAGE THE MOTORPROPELLER ASSEMBLY. YOU ARE STRONGLY DISCOUR
AGED FROM SIDESLIPPING 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 minumum and maximum combined cockpit crew weight heavily depend on the
centre of gravity of an empty aircraft. Minumum 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 472.5
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
CHECKUP 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 PLATES, 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 40°C 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 categorised as an Ultralight aircraft and must wear 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
GEARUP
AIRBRAKE
GEAR DN
FLAPS
FLAPS
TRIM
UP
DN
OUT
IN
0°
+5°
L
-5°
AIRBRAKE
GEAR BRK
pilot min. kg pilot max. kg
ENGIN E R E T R ACTI O N
1. throttle idle, ignition off
2. reduce IAS to 75 km/h
3. after prop. stops IAS 90 km/h,
- engine DOWN
4. when prop. retracted
- master switch I
VARIO
RADIO AUX
XPDR 12V
socket
ENG
INST
ENG
SYSTEM
T
INTERCOM
ON
OFF
L MAGNETOS R P
R
I
M
E
R
ON
OFF
THROTTLE
ON
OFF
F
U
E
L
SC MODE ON
OFF
with 9 kg nose ballast kg
with 9 kg nose ballast kg
pilot min. kg
WARNING!
If battery is removed
M I C
HEADSET
ON
OFF
F
U
E
L